Of Contents: Section Section Section Section

T.O.
1-IM-34
TABLE OF CONTENTS
PAGE
SECTION AIR-TO-SURFACE MUNITIONS 1-1
SECTION FUZES 2-1
SECTION III SPECIAL EQUIPMENT 3-1
SECTION IV AIR-TO-AIR MISSILES 4-1
SECTION V SUSPENSION EQUIPMENT 5-1
SAFE ESCAPE/SAFE SEPARATION 6-1
SUPPLEMENTARY DATA, ERROR 7-1

ANALYSIS
MISSION PLANNING
(to be published at a later date)
INDEX-1
i/(ii blank)
T.O. 1—1M—34
FOREWORD
PURPOSE AND SCOPE

This manual is applicable to multiple aircraft and provides a single source for com
mon descriptive and procedural information. Common is defined as information
appropriate for more than one aircraft. Generally, the information is limited to
standardized descriptions of common air-to-air and air-to-surface conventional
munitions, fuzes, suspension equipment, safe escape data, mission planning, and
weapons oriented avionics. When a conflict exists between the T.0.-1 Flight Manual
and this technical manual, the flight manual will take precedence.
SUPPLEMENTS TO THIS MANUAL

This manual is intended to be used in conjunction with the aircraft unique Dash 34
volumes including T.O.-34-1, T.O.-34-1-1, T.O.-34-1-2, T.0.-34-1-1-1(C), and
T.0.-34-1-2-1(0. These manuals provide descriptive and procedural data which are
appropriate for a single aircraft.
SECTION I, AIR-TO-SURFACE MUNITIONS

Section I contains a description of the physical and functional characteristics of
nonnuclear munition systems and controls, nonnuclear combat munitions, and non
nuclear training munitions and equipment.
SECTION II, FUZES

Section II contains a description of nonnuclear munition fuzes and associated fuze
support equipment. The section includes physical and functional characteristics of
the fuzes and fuze/munition compatibility data.
SECTION III, SPECIAL EQUIPMENT

Section III contains a description of special equipment necessary for mission sup
port and/or weapon delivery, i.e., target acquisition devices, target illuminators,
data link pods, resupply containers, special dispensers, etc. The information
includes a physical and functional description of the equipment, its utility, and
operation.
SECTION IV, AIR-TO-AIR MISSILES

This section contains a general discussion of air-to-air missile types, employment
concepts, guidance and control groups, and warheads. The information includes a
physical and functional description of each missile and its components.
Ill
T.O. 1-1M-34
SECTION V, SUSPENSION EQUIPMENT

This section contains a description of ejector racks, missile launchers, and prac
tice bomb dispensers for both air-to-air and air-to-surface munitions. The informa
tion includes a physical and functional description of each system and its
components.
SECTION VI, SAFE ESCAPE/SAFE SEPARATION

This section defines terms and standardizes the methods for determining minimum safe
release altitude and minimum safe fuze arming time data for mission planning. The
section also includes a description of methods for ensuring fragment deconfliction
for flight attacks and sample problems for minimum safe fuze arming time.
SECTION VII, SUPPLEMENTARY DATA, ERROR ANALYSIS

This section contains data and methodologies necessary for accurate munition deliv
ery and considers effects not normally included in ballistics and other delivery
data, i.e., wind correction and release errors. The section also provides error
analysis data for estimating miss distances attributable to errors in specific
delivery parameters.
SECTION VIII, MISSION PLANNING

This section includes considerations which must be made in mission planning. The
section describes the mission planning form and its preparation. Terms and methodol
ogies are defined and sample problems are provided.
EXTERNAL STORES LIMITATIONS

The Flight Manual, T.0.-1, provides limitations for carriage, release, and jettison
of certified stores. Only the stores listed in the Flight Manual are authorized,
unless interim flight clearance is received from the appropriate aircraft system
manager.
STORE CERTIFICATION
New nonnuclear munitions and external stores certification will be implemented as
established in USAF PMDs for the SEEK EAGLE Program. Operating commands will
generate these requirements by Statements of Operational Need (SON) in accordance
with AFR 57-1.
FLIGHT CLEARANCE
Authorization for flight clearance will be requested through the appropriate
aircraft system manager after any necessary testing and analysis acertains and veri
fies that an aircraft/store combination will not cause an unacceptable risk for a
specific limited purpose such as DT&E, IOT&E, or FOT&E.
IV
T.O. 1—1M—34
DEFINITION WORDS "SHALL,” "WILL,”

"SHOULD,” AND "MAY”
The words ’’shall1 and ’’will” indicate a mandatory requirement. The word ’’should”
indicates a nonmandatory desire or preferred method of accomplishment. The word
’’may” indicates an acceptable or suggested means of accomplishment.
WARNINGS, CAUTIONS, AND NOTES

The following definitions apply to Warnings, Cautions, and Notes found throughout
the manual.
Operating procedures, techniques, etc., which

will result in personal injury or loss of
life if not carefully followed.
!; CAUTION i!
Operating procedures, techniques, etc., which

will result in damage to equipment if not
carefully followed.
NOTE
An operating procedure, technique, etc.,

which is considered essential to emphasize.
YOUR RESPONSIBILITY - TO LET US KNOW

Every effort is made to keep this manual current. Review conferences with
operating personnel and a constant review of accident and flight test reports
assure inclusion of the latest data in the manual. We cannot correct an error
unless we know of its existence. In this regard, it is essential that you do your
part. Comments, corrections, and questions regarding this manual or any phase of
the flight manual program are welcomed. These should be forwarded through your
command channels on AF Form 847 to: HQ TAC/DOOW, Langley AFB, Virginia 23665—5000
with information copies to 3246 TESTW/TYD, Eglin AFB, Florida 32542-5000 and
SA-ALC/MMUA, Kelly AFB, Texas 78241-5000.
V
T.O. 1—IM—34
GLOSSARY
ADVERSE YAW - A yaw opposite to the direction of turn, induced by rolling motion and
aileron deflection.
AIMING POINT - The point on the ground used as a reference to determine bomb release.
AIRCRAFT AXIS - There are three axes, which are mutually perpendicular and have a
common point of intersection:
1. Longitudinal axis: This axis is parallel to the fuselage

reference line. Rotating the longitudinal axis will change the
aircraft angle of attack (AOA) and/or pitch.
2. Vertical axis: This axis is perpendicular to the longitudinal

axis. The aircraft rotates about this axis when yawing.
3. Lateral axis: This axis rotates about the longitudinal axis

when the aircraft is rolled or banked.
AN - A prefix to denote use by Army, Air Force, and Navy.
ANGLE OF ATTACK (AOA) - The angle between the fuselage reference line and the
relative wind.
ANGLE-OFF - The angular measurement between the longitudinal axis of two or more
aircraft.
ANGLE OF GUNFIRE (AGF) - The angle between the gun bore line and the flightpath.
ANGLE OF INCIDENCE - A fixed angle between the wing chord line and the fuselage
reference line.
ANGLE OF PITCH - The angle of the aircraft flightpath relative to a level plane.
BOMB STICK - The number of bombs released during a ripple delivery.
BOMB TRAIL - The distance the bomb trails behind the aircraft after release.
BOMB TRAJECTORY - The path of a bomb from release to impact.
BULLET DENSITY - The number of rounds passing through an area of 1 square foot per
unit of time.
BULLET DISPERSION - Deviation of a bullet trajectory from the aiming point.
COCKPIT G - Acceleration forces on the aircraft as read from the g-meter.
CORRECTED SIGHT DEPRESSION - True sight depression corrected for a headwind or

tailwind component.
DUD - A round or bomb that fails to explode.
VI
T.O. 1-1M-34
EFFECTIVE SIGHT DEPRESSION - The depression from desired flightpath. Varies with
release conditions. When preplanned parameters are
met, effective depression equals required depression.
FIRE BOMB - An incendiary or napalm-filled bomb.
FIRE PULSE - An electrical impulse transmitted to fire/release stores.
FLIGHTPATH - The line or plane that describes the longitudinal motion of the
aircraft.
FUSELAGE REFERENCE LINE (FRL) - A basic reference line through the fuselage parallel
to the longitudinal axis of the aircraft.
GROUND RANGE - The horizontal distance from the point directly below the aircraft to
the target.
GROUND TRACK - The actual line of movement of an aircraft over the ground.
GUN BORE LINE (GBL) - Extension of the initial bullet muzzle velocity.
HARMONIZATION - The adjustment (or boresighting) of the gun barrel so that, when
the guns are fired at the most effective range, the pipper will be
on the bullet impact point.
HEAD-UP DISPLAY (HUD) - An optical and electronic device that projects flight infor
mation into the pilot’s forward field of view (FOV), and
provides primary and standby weapon delivery capability.
INITIAL POINT (IP) - A point over which an aircraft begins an attack.
KNOTS CALIBRATED AIRSPEED (KCAS) - This is the indicated airspeed for installation
error.
KNOTS INDICATED AIRSPEED (KIAS) - This airspeed is read directly from the airspeed
indicator.
KNOTS TRUE AIRSPEED (KTAS) - This is the equivalent airspeed corected for atmos
pheric density.
LAUNCHER LINE (LL) - A line through a rocket launcher tube extended to infinity.
LINE OF DEPARTURE (LOD) - The path that a rocket follows after leaving the aircraft.
MIL - A milliradian which is 1/1000 of a radian (17.45 mil = 1 degree). One mil
subtends approximately 1 foot at a 1,000-foot range.
MISSILE HANGFIRE - When a missile fails to launch after all normal procedures have
been accomplished, and smoke or smoldering is observed. A poten
tial launch is considered possible within the next 15 minutes.
VII
T.O. 1-1M-34
MISSILE MISFIRE - When a missile fails to launch after all normal procedures have
been accomplished, and no smoke or smoldering is observed within
3 minutes.
PARALLAX - The linear separation of the sight and weapons as they are installed in
the aircraft.
PICKLE - The act of depressing the weapon release button.
PREDICTION ANGLE - Total lead angle required after calculations.
PYLON - A component attached to the aircraft to carry, arm, release, or jettison

external stores.
RADIAL G - Cockpit g plus or minus the component of gravity.
REQUIRED SIGHT DEPRESSION - The amount of depression below the zero sight line (ZSL)
necessary to accurately define bomb range.
RIP - Ripple - A release mode in which the quantity and interval of bombs may be
selected.
SIGHTLINE (SL) - The base or zero line for all sight computations that has been
corrected for parallax.
SIGHT SETTING - The value in mils to which the aiming reticle is depressed.
SLANT RANGE - Line-of-sight distance from the aircraft to the target.
STANDBY AIMING RETICLE - A backup display on the HUD, depressible over the same
range as the primary.
TRAJECTORY - Flightpath from release to impact.
TRAJECTORY SHIFT - The angular shift of the bullet or rocket trajectory from bore
line toward the flight path of the aircraft.
TRUE SIGHT DEPRESSION - A no-wind sight setting computed for preplanned flight
conditions.
UPWIND AIMING POINT - Point upwind of the target used to determine bomb release.
VELOCITY VECTOR - A vector quantity denoting both magnitude and direction.
VIP - Visual identification point.
ZERO SIGHT LINE (ZSL) - The pipper line of sight when the optical sight is set on
zero mil depression.
VIII
T.O. 1-IM-34
LIST OF ILLUSTRATIONS
Number Title Page Number Title Page
1-1 Explosives Filler Chart .... 1-5 1-20 GBU-15(V)1/B Guided Bomb ... 1-33
1-2 GP Bomb ..................... 1-8 1-21 Low Altitude Indirect

Attack ............... 1-35
1-3 Adapter Booster (Typical) ... 1-9
1-22 High Altitude Indirect
1-4 Arming Wire/Lanyard Routing Attack ............... 1-36
(Typical) ............. 1-10
1-23 RT-1210/AXQ-14 Data Link
1-5 Arming Wire to Fuze and Pod .................. 1-38
ATU-35 (Typical) ..... 1-11
1-24 BLU-107/B (Durandal)
1-6 FMU Arming Wire Routing Penetrator Bomb ..... 1-39
(Typical) ... 1-12
1-25 Durandal Release Sequence .. 1-40
1-7 FMU Series Fuzing .......... 1-12
1-26 AGM-65A, -65B Missiles .... 1-42
1-8 MK 82, MK 83, and MK 84
GP Bombs (Typical) ... 1-14 1-27 AGM-65A, -65B Video Display. 1-45
1-9 MK 82 Snakeye and MK 36 1-28 Effect of G Bias on Missile

Destructor ............ 1-15 Flightpath ........... 1-47
1-10 MK 82 Air Inflatable Retarder 1-29 AGM-65D (IR) Missile ...... 1-49
(AIR) HDGP Bomb ...... 1-17
1-30 AGM-65D (IR) Video Display.. 1-51
1-11 MK 84 Air Inflatable Retarder
(AIR) HDGP Bomb ...... 1-19 1-31 A/A37A Training Guided
Missile (TGM-65) .... 1-55
1-12 BLU-109/B (I-2000/Target
Buster) Penetrator Bomb .... 1-20 1-32 Event Markers .............. 1-58
1-13 M117 GP Bomb ................ 1-21 1-33 AGM-45 Missile ............. 1-59
1-14 M117R (Retarded) GP Bomb/ 1-34 MC-1 Gas Bomb .............. 1-60
M117D (Destructor) GP Bomb .. 1-22
1-35 BLU-27 ..................... 1-61
1-15 M118 Demolition Bomb ....... 1-24
1-36 BLU-52 Chemical Bomb ...... 1-63
1-16 Paveway I Laser Guided Bombs. 1-25
1-37 M129E1 and E2 Leaflet Bombs
1-17 Paveway II Laser Guided and MJU-1 Chaff Bomb . 1-64
Bombs ................. 1-26
1-38 Cluster Bombs and
1-18 LGB Detector .............. . . 1-27 Dispensers ........... 1-66
1-19 LGB Flightpath .............. 1-31 1-39 Cluster Bomb Chart ...... 1-67
IX
T.O. 1-1M-34
1-40 SUU-13 Dispensers .......... 1-68

1-60 2.75-Inch Rocket Motor
1-41 CDU-12/B Canister/BLU-39/B23 (Typical) .................. 1—97
CS Bomblet ............ 1-70
1-61 2.75-Inch Warheads ......... 1-98
1-42 CBU-38 Series Munitions
Configuration and Weight 1-62 CRV7 Rocket ................ 1-100
Chart .... ............. 1-70
2-1 Fuze Classification ........ 2-3
1-43 BLU-49 Bomblet .............. 1-71
2-2 Fuze Function .............. 2-5
1-44 SUU-30B/B, H/B Dispensers ... 1-73
2-3 Fuze Explosive Train ....... 2-6
1-45 BLU Bomblet (Typical) ...... 1-74
2-4 Fuze Safety Features ....... 2-7
1-46 SUU-64/B, -65/B Tactical
Munitions Dispenser ........ 1-77 2-5 FMU-54/B Tail Fuze ........ 2-9
1-47 BLU-97/B Bomblet ........... 1-79 2-6 FMU-54A/B Tail Fuze and
MK 43 TDD ...... 2-10
1-48 BLU-91/B or BLU-92/B (Gator)
Mine ........................ 1-80 2-7 M904 Nose Fuze ............ 2-12
1-49 MK 20 Mod 2, 3, and 4 2-8 Ml and M1A1 Fuze Extenders.. 2-13

(Rockeye II) Cluster Bomb ... 1-82
2-9 M905 Tail Fuze ............ 2-15
1-50 MK 20 Rockeye II, MK 118
Bomblet ..................... 1-84 2-10 ATU-35 Drive Assembly ..... 2-15
1-51 Delivery Considerations .... 1-85 2-11 M907 Nose Fuze ............ 2-16
1-52 BL-755 Cluster Bomb ........ 1-86 2-12 AN-M147A1 and FMU-107/B Nose
Fuze . 2-18
1-53 BDU-33 Practice Bomb ....... 1-88
2-13 MK 339 Mod 0 Nose Fuze .... 2-21
1-54 BDU-48/B Practice Bomb ..... 1-89
2-14 MK 339 Nose Fuze Installed
1-55 MK 106 Practice Bomb ....... 1-90 on MK 20 Rockeye .... 2-23
1-56 20mm Ammunition ............. 1-92 2-15 FMU-7 Fuze and Initiator ... 2-24
1-57 30mm Ammunition ............. 1-94 2-16 FMU-26A/B and FMU-26B/B

Fuzes ................ 2-25
1-58 M505 Series Fuzes .......... 1-95
2-17 FMU-26A/B and FMU-26B/B
1-59 2.75-Inch FFAR Rocket Modes ................ 2-26
(Typical) ................... 1-96
2-18 FMU-72/B Long-Delay Fuze ... 2-29
X
T.O. 1—1M-34
2-19 FMU-81/B Short-Delay Fuze ... 2-32 2-39 Retaining Clips ............ 2-59
2-20 FMU-112/B System ........... 2-34 2-40 Fuze/Bomb Compatibility .... 2-60
2-21 FMU-112/B Arming ........... 2-36 3-1 AN/AVQ-23A/B PAVESPIKE Pod.. 3-3
2-22 FMU-124A/B Impact Bomb 3-2 AN/AVQ-23A/B PAVE SPIKE

Fuze ................. 2-38 Optical System .............. 3-5
2-23 ADU-421A/B Fuze Adapter .... 2-40 3-3 AN/AVQ-23A/B PAVE SPIKE
LOS/Gimbal Limits .. 3-6
2-24 FMU-56B/B and FMU-56D/B
Fuzes ........ ....... 2-41 3-4 AN/AVQ-26 PAVE TACK Pod .... 3-8
2-25 FMU-56B/B, D/B Selectable 3-5 PAVE TACK Pod Assembly..... 3-9
Arming Times and HOB ..... 2-42
3-6 AN/AA-35(V)(1)(TISL)......... 3-10
2-26 FMU-110/B Proximity Nose
Fuze ....................... 2-45 3-7 AN/PAQ-1 LTD ................ 3-11
2-27 FMU-110/B Selectable Arming 3-8 AN/PAQ-3 MULE ............... 3-12

Times and HOB .............. 2-46
3-9 G/VLLD ............. 3-12
2-28 FMU-113/B Proximity Nose
Fuze ....... 2-49 3-10 LTD, MULE, G/VLLD System
Parameters .................. 3-13
2-29 Flight Delivery ............ 2-50
3-11 A/A 37U-15 Tow Target
2-30 MK 75 Arming Kit (Typical).. 2-51 System ...................... 3-15
2-31 MK 32 Mod 1 Arming Device .. 2-52 3-12 A/A 37U-33 Aerial Gunnery
Target System (AGTS) ....... 3-17
2-32 FZU-l/B and FZU-2/B Fuze
Boosters ............. 2-53 3-13 AN/ALQ-119(V) ECM Pod ....... 3-20
2-33 FZU-37A/B Fuze Initiator ... 2-55 3-14 C-6631/ALQ-119 Control

Panel ........... 3-22
2-34 FZU-39/B Proximity Sensor .. 2-56
3-15 C-9492A/ALQ-119 Control
2-35 FZU-39/B Selectable Arming Panel ............... 3-23
Time, HOB, and Spin Rate ... 2-57
3-16 AN/ALQ-131(V) ECM Pods ...... 3-26
2-36 Battery Firing Device ...... 2-58
3-17 C-9492B/ALQ-131 Control
2-37 MAU-162 Firing Lanyard Panel ....................... 3-27
Adjuster ................... 2-58
3-18 C-6631/ALQ-131 Control
2-38 Swivel and Link........... 2-59 Panel ....................... 3-31
XI
T.O. 1—IM—34
3-19 SUU-16/A and SUU-23/A 5-1 MAU-12 Bomb Ejector Rack

20mm Gun Pods ............... 3-34 (Typical) ................ . 5-2
3-20 GPU-5/A 30mm Gun Pod ....... 3-38 5-2 MAU-12 Bomb Rack Operational
Schematic ...... ...... 5-4
3-21 SUU-25C/A and E/A Flare
Dispensers ........ ......... 3-40 5-3 MAU-40/A Bomb Ejector Rack .. 5-5
3-22 LUU-l/B, 5/B, 6/B Target 5-4 MAU-50/A Bomb Ejector Rack .. 5-6
Marker Flares ............... 3-42
5-5 TER-9, 9/A Triple Ejector
3-23 LUU-2/B and LUU-2A/B Rack (TER) ............... 5-7
Flares ...................... 3-43
5-6 MER-10, 10/A, 10/N Multiple
3-24 LUU-2A/B Flare Profile ..... 3-45 Ejector Rack (MER) ...... . 5-9
3-25 AIS Pod with Aero-3B/ 5-7 AER0-3B, LAU-105 Missile

LAU-114A/A Launcher ........ 3-46 Launcher .............. 5-10
3-26 AIS Pod Variants ........... 3-47 5-8 LAU-34/A Missile Launcher ... 5-11
3-27 CTU-2/A Resupply Container... 3-48 5-9 LAU-114A/A Missile Launcher.. 5-13
3-28 MXU-648/A Cargo Pod ........ 3-50 5-10 LAU-88/A Missile Launcher ... 5-14
3-29 AN/DSQ-T34 Laser Target 5-11 LAU-117/A Missile Launcher .. 5-16

Designator Scoring System ... 3-51
5-12 LAU-3/A, A/A, B/A, -60A
4-1 Missile Types .............. 4-2 Rocket Launcher ............. 5-17
4-2 Homing Techniques .......... 4-3 5-13 LAU-68A/A, B/A Rocket

Launcher .. 5-20
4-3 Types of Guidance .......... 4-4
5-14 LAU-5003/A Rocket Launcher .. 5-21
4-4 Motor Types ................ 4-5
5-15 SUU-20/A, A/M, A/A, B./A
4-5 AIM-7 Sparrow Missile - Practice Bomb and Rocket
General Operations ......... 4-7 Dispenser ............. 5-23
4-6 AIM-7 Sparrow Family 5-16 SUU-21/A Practice Bomb

Differences ................. 4-11 Dispenser ............. 5-26
4-7 AIM-9 Series Guided Missile.. 4-13 6-1 Maximum Bomb/Rocket Fragment
Travel Chart ...... ... 6-9
4-8 AIM-9 Model Configurations/
Characteristics ........... 4-14 6-2 Horizontal Deconf1iction for
CBU .............. 6-11
XII
T.O. 1—1M—34
7-1 Reference Lines ............ 7-3 7-18 Popup Attack ............... 7-34
7-2 Release Geometry ........... 7-7
7-3 Total Depression ........... 7-7
7-4 Rollout Geometry ........... 7-8
7-5 Horizontal/Vertical Parallax

Corrections .......... 7-10
7-6 Release Point Error (Airspeed/

Dive Angle) .......... 7-14
7-7 Release Point Error

(Altitude) ........... 7-14
7-8 Effect of Release Altitude

Error (Same Airspeed/Dive
Angle) ................ 7-15
7-9 Effect of Dive Angle Error

(Same Airspeed/Altitude) .... 7-16
7-10 Effect of Airspeed Error

(Same Al titude/Dive Angle) •• 7-17
7-11 Actual Horizontal Range .... 7-19
7-12 Error Analysis Chart ....... 7-25
7-13 Effect of G-Loading (Same

Airspeed/Altitude) ... 7-28
7-14 Effect of Skid (Planned

Altitude/Airspeed/Dive
Angle) ................ 7-29
7-15 Effect of Releasing Ordnance

in a Bank ............ 7-30
7-16 Apparent Shortening of Ground

Distances ............. 7-31
7-17 Crab Offset Vs Drifting

Offset - Common Upwind Aiming
Point ................. 7-33
XIII
T.O. 1-IM-34
ABBREVIATIONS
A CEM Combined Effects Munition
CG Center of Gravity
AB Afterburner CITS Centrally Integrated Test
ACD Adapter Control Detector Sys tern
ACM I Air Combat Maneuvering CRT Cathode-Ray Tube
Instrumentation CTVS Cockpit Television Sensor
ACP Armament Control Panel CW Continuous Wave
ACS Armament Control System
ADI Attitude Director Indicator D
ADL Armament Datum Line
AFG Air Foil Group DC Direct Current
AFSC Air Force Systems Command DDS Display and Debriefing
A/G Air-to-Ground Subsys tern
AGF Angle of Gunfire DEP Depression
AGL Above Ground Level DFP Depression from Flightpath
AGM Air-to-Ground Missile DL Data Link
AID Attached Inflatable Decelerator DLCP Data Link Control Panel
AIM Air Intercept Missile
AIR Air Inflatable Retarder E
AIS Aircraft Instrumentation
Subsystem E Net Error
AIU Aircraft Integration Unit ECCM Electronic Counter
ALSC Aluminum Linear Shaped Charge Countermeasure
AOA Angle of Attack ECM Electronic Countermeasure
AOD Aim of Distance ECU Electronic Control Unit
AOP Aim of Point EMI Electromagnetic Interference
AP Armor-Piercing EO Electro-Optical
API Armor-Piercing Incendiary EOB Electronic Order of Battle
ATU Anemometer-Vane-Type-Unit EOD Explosive Ordnance Disposal
AVTR Airborne Video Tape Recorder EWS Electronic Warfare Systems
AZ Azimuth
F
B
FBL Fixed Bore Line -
BDU Bomb, Dummy Unit (practice FFAR Folding Fin Aircraft Rocket
muni t ion) FGL Fixed Gun Line
BFD Battery Firing Device FFOD Firefighting Operational
BIT Built-In Test Distance
BITE Built-In Test Equipment FM Frequency Modulation
BLU Bomb, Live Unit FMU Fuze, Munition Unit
BR Bomb Range FOV Field of View
B/W Black on White (contrast) fps Feet per Second
c
CAS Close Air Support
CBU Cluster Bomb Unit
CCG Computer Control Group
CCS Control and Computation
Subsys tern
XIV
T.O. 1-1M-34
ABBREVIATIONS (Continued)
G Gravity LD Low Drag

GB Guided Bomb LDGP Low-Drag, General-Purpose
GBL Gun Bore Line LGB Laser Guided Bomb
GBU Guided Bomb Unit LL Launcher Line
G&C Guidance and Control LCD Line of Departure
GHz Gigahertz LOS Line of Sight
GP General-Purpose LRU Line-Replaceable Unit
G/VLLD Ground or Vehicular Laser LSS Laser Spot Seeker
Locator Designator LTD Laser Target Designator
LTDSS Laser Target Designator Scoring
H Sys tern
LUU Illumination Unit
HARS Heading Attitude Reference
Sys tern M
HAS Hydraulic Actuation System
HD High Drag MAU Miscellaneous Armament Unit
HDGP High-Drag, General-Purpose MCM Manual Countermeasure
HE High Explosive MER Multiple Ejector Rack
HEAP High-Energy, Armor-Piercing mil Milliradian
HEAT High-Explosive, Antitank MK Mark (Navy weapon designation)
HEI High-Explosive, Incendiary MLV Memory Loader Verifier
Hg Mercury mm Millimeter
HOB Height of Burst MOD Modification
HUD Head-Up Display MPS Mission Planning Section
Hz Hertz MRD Missile Restraining Device
msec Millisecond
I MSL Mean Sea Level
IDS Infrared Detecting Set N

IF Intermediate Frequency
IHC Integrated Hand Control N Nose
INS Inertial Navigation System NFOV Narrow Field of View
IP Initial Point NM Nautical Mile
IPP Initial Pipper Placement NNMSB Nonnuclear Munitions Safety
IR Infrared Board
N/T Nose and/or Tail
J
JMEM Joint Munitions Effectiveness 0

Manual
OAP Offset Aiming Point
K
KCAS Knots Calibrated Airspeed

kHz Kilohertz
KTAS Knots True Airspeed
km Kilometer
XV
T.O. 1—IM—34
ABBREVIATIONS (Concluded)
P TP Target Practice
TPT Target Practice Tracer
PCO Power Changeover TV Television
PD Pulse Doppler
PIM Pulse Interval Modulation U
PMI Pearlite Malleable Iron
PRF Pulse Repetition Frequency UHF Ultra-High Frequency
PSA Phase-Scanned Array
PSI Pounds per Square Inch V
R VIP Visual Identification Point
RAT Ram Air Turbine W

RF Radio Frequency
RGPO Range Gate Pulloff W/B White on Black (contrast)
RHAW Radar Homing and Warning WCU Weapon Control Unit
RKT Rocket WD Warhead
RPE Release Point Error W/D Weapon Delivery
rpm Revolutions per Minute WDL Weapon Data Link
WFOV Wide Field of View
S WP White Phosphorous
SAF Safe, Arming, and Fuzing Z

SAFU Safety, Arming, and Functioning
Unit ZSL Zero Sight Line
SL Sight Line
SMU Suspended Multi launcher Unit
SON Statement of Operational Need
SR Slant Range
SSLO Solid-State Local Oscillator
STS Search Track Set
SUU Suspension and Release Unit
T Tail
TAS True Airspeed
TDD Target Detecting Device
TE Trajectory Error
TER Triple Ejector Rack
TGM Training Guided Missile
TIS Tracking Instrumentation
Subsys tern
TISEO Target Identification System,
Electro-Optical
TISL Target Identification Set, Laser
(PAVE PENNY)
TMD Tactical Munitions Dispenser
TOF Time of Fall or Time of Flight
XVI
T.O. 1-1M-34
SECTION I
AIR-TO-SURFACE MUNITIONS
CONTENTS
PAGE
BOMB-TYPE MUNITIONS........................................................................................................................ 1-4

GP Bombs.............................................................................................................................................. 1-4
Demolition Bombs............................................................................................................................... 1-4
Fragmentation Bombs.......................................................................................................................... 1-4
Penetration Bombs............................................................................................................................... 1-4
BOMB EFFECTS....................................................................................................................................... 1-4
Blast................................................................. •*................................................................ 1-7
Fragmentation....................................................................................................................................... 1-7
Cratering................................................................................................................................................ 1-7
GENERAL-PURPOSE BOMBS.................................................................................................................. 1-8
Charging Well....................................................................................................................................... 1-9
Suspension Lugs................................................................................................................................... 1-9
Adapter Boosters................................................................................................................................... 1-9
Conical Fin Assembly........................................................................................................................... 1-9
Arming Wire and Lanyard ....................................................... 1-10
FMU Series Fuzing ............................................................ 1-10
Explosive Fillers..................................................................................................................................
MK 82 LD, MK 83 LD, MK 84 LDGP BOMBS........... ............................................................................. 1-13
MK 82 HDGP (SNAKEYE I) BOMB.......................................................................................................... 1-14
MK 36 (DESTRUCTOR) GP BOMB.......................................................................................................... 1-16
MK 82 AIR INFLATABLE RETARDER (AIR) HDGP BOMB.............................................................. 1-16
MK 84 AIR INFLATABLE RETARDER (AIR) HDGP BOMB.............................................................. 1-18
BLU-109/B (I-2000/TARGET BUSTER) PENETRATOR BOMB.......................................................... 1-20
M117 GP BOMB.......................................................................................................................................... 1-21
M117R (RETARDED) GP BOMB.............................................................................................................. 1-21
M117D (DESTRUCTOR) GP BOMB........................................ 1-23
M118 DEMOLITION BOMB..................................................................................................................... 1-23
GBU-10 AND GBU-12 LASER-GUIDED BOMBS (LGB)....................................................................... 1-24
LGB Components................................................................................................................................. 1-27
Flightpath Characteristics.................................................................................................................... 1-30
Optimum Guidance Time.................................................................................................................... 1-32
Fuzes....................................................................................................................................................... 1-32
Coding..................................................................................................................................................... 1-32
GBU-15 DATA LINK WEAPON SYSTEM............................................................................................... 132
DSU-27A/B Target Detecting Device................................................................................................... 1"3^
ADU-452 A/B Guidance Adapter......................................................................................
MXU-724/B Airfoil Group..................................................................................................................
WCU-8/B Weapon Control Unit..........................................................................................................
OA-8921/AXQ-14 Weapon Data Link.................................................................................................
1-1
T.O. 1- 1M- 34
CONTENTS (CONTINUED)
PAGE
GBU-15(V)(T-1)/B TRAINING BOMB................................................................................................... 1-37

RT-1210/AXQ-14 DATA LINK POD..................................................................................................... 1-38
BLU-107/B (DURANDAL) PENETRATOR BOMB............................................................................. 1-39
AGM-65 MAVERICK MISSILE............................................................................................................. 1-41
AGM-65A AND AGM-65B (EO) MAVERICK MISSILES..................................................................... 1-41
Forward Section................................................. 1-41
Aft Section......................................................................................................................................... 1-43
Video Display..................................................................................................................................... 1-44
Guidance.............................................................................................................................................. 1-46
AGM-65 Operational Limitations..................................................................................................... 1-48
AGM-65D (IR) MAVERICK MISSILE................................................................................................... 1-48
Forward Section................................................................................................................................. 1-48
Aft Section ................................................................. 1-51
Video Display..................................................................................................................................... 1-51
Guidance.............................................................................................................................................. 1-52
Target Acquisition. . . ......................................................................................................................... 1-53
A/A37A TRAINING GUIDED MISSILE (TGM-65)............................................... 1-54
TGM Time Limitations...................................................................................................................... 1-56
TGM Recorder................................................................................................................................... 1-57
AGM-45 SHRIKE MISSILE.................................................................................................................... 1-57
MC-1 GAS BOMB...................................................................................................................... 1-57
BLU-27 FIRE BOMBS............................................................................................................................. 1-59
BLU-52 CHEMICAL BOMBS.................................................................................................................. 1-62
M129E1 AND E2 LEAFLET BOMBS AND MJU-1 CHAFF BOMB.................................................... 1-63
CLUSTER BOMBS AND DISPENSERS................................................................................................. 1-65
SUU-13 DISPENSERS............................................................................................................................. 1-65
SUU-13/A............................................................................................................................................ 1-65
SUU-13A/A......................................................................................................................................... 1-65
SUU-13B/A............................................................................... 1-65
SUU-13C/A.......................................................................................................................................... 1-65
CBU-30/A CLUSTER BOMB AND BLU-39/B23 CS COMBLET............................................................. 1-67
CBU-38 CLUSTER BOMB.......................................................................................... 1-69
BLU-49/B Bomblet............................................................................................................................. 1-69
BLU-49A/B Bomblet............................................................................................................................. 1-71
BLU-49B/B Bomblet............................................................................................................................. 1-72
SUU-30 DISPENSERS........................................... 1-72
SUU-30B/B Dispenser ......................................................................................................................... 1-72
SUU-30H/B Dispenser........................................................................................................................... 1-72
CBU-24B/B CLUSTER BOMB.................................................................................................................. 1-72
CBU-49B/B CLUSTER BOMB......................................... ,........................................................................ 1-75
M224 Random Time Delay Fuze.......................................................................................................... 1-75
CBU-52B/B CLUSTER BOMB.................................................................................................................. 1-75
CBU-58/B CLUSTER BOMB.......................................................................................................................1-75
CBU-58A/B CLUSTER BOMB ..................................................... 1-75
CBU-71/B CLUSTER BOMB.......................................................................................................................1-76
CBU-71A/B CLUSTER BOMB.................................................................................................................. 1-76
SUU-64/B, -65/B TACTICAL MUNITIONS DISPENSERS..................................................................... 1-76
SUU-64/B.............................................................................................................................................. 1-76
SUU-65/B.............................................................................................................................................. 1-78
CBU-87 CLUSTER BOMB (COMBINED EFFECTS MUNITIONS)................................................. . . 1-78
CBU-89 CLUSTER BOMB (GATOR)........................................................................................................1-80
MK 20 MOD 2, 3, AND 4 (ROCKEYE II) CLUSTER BOMB............................................... 1-81
MK 7 Mod 2 Dispenser......................................................................................................................... 1-81
MK 7 Mod 3 Dispenser (MK 20 Mod 3) .............................................................................................1-83
MK 7 Mod 4 Dispenser (MK 20 Mod 4)............................................................................................... 1-83
1-2
T.O. 1-1M-34
CONTENTS (CONCLUDED)
PAGE
MK 339 Mechanical Time Fuze..................... ..... 1-83
MK 118 Mod 0 Bomblet............... ........................... 1-83
MK 118 Mod 1 Bomblet ................................ 1-83
MK 20 Rockeye Delivery Considerations............................................................................. 1-84
BL-755 CLUSTER BOMB AND BL-755 BOMBLET........................................................ 1-85
PRACTICE BOMBS........................................... 1-87
BDU-33 .............................................................. 1-87
BDU-33B/B........... ....................... .. ................. ........................................... 1-88
BDU-33D/B................................................................................................................................... ... 1-88
BDU-48/B....................... . ...................................1-89
MK 106....................................................................................................... 1-89
MK 4 Mod 3 and MK 4 Mod 4 Signal Cartridge............................................... 1-90
20MM AMMUNITION.............................................................................................. . . .......................... 1-91
M55A1/A2 Target Practice Round (M220 TP Tracer Round).......................................................... 1-91
M53 Armor-Piercing Incendiary Round............................................................ 1-91
M56 High-Explosive Incendiary Round (XM242 HEI Tracer).......................................................... 1-91
30MM AMMUNITION....................... 1-93
M505 PROJECTILE NOSE FUZE......................................................................... 1-93
2.75-INCH FOLDING FIN AIRCRAFT ROCKET (FFAR).............................. 1-93
2.75-lnch Rocket Motor....................................................................................................................... 1-93
2.75-lnch Rocket Warheads..................... 1-96
CRV7 ROCKET............................................................... . . '................................. 1-99
CM151 TRAINING ROCKET.............. ................ . .............................................................................. 1-100
2.75-lnch Rocket Fuzes..................................................................................................... 1-100
1-3
T.O. 1—IM—34
BOMB-TYPE MUNITIONS
Bombs are generally categorized according to the ratio of explosive weight to total
weight (FIGURE 1-1). Categories include general purpose (GP) , demolition, fragmen
tation, and penetration. GP bombs can be used against a variety of targets. Since
the body case is approximately one-half-inch thick, the casing creates a fragmen
tation effect at the moment of detonation. Also, since the explosive filler consti
tutes approximately 50 percent of the total weight, considerable damage from the
blast effect can be expected at the target. In addition to these effects, a mining
effect can be gained through the use of delayed-action fuzes. GP bombs can be made
into a semiarmor piercing bomb by retaining the original nose closure plug and
installing only a tail fuze. This configuration will penetrate medium hard targets.
The bomb was given the designation GP because of its versatility.
GP BOMBS
The explosive weight equals approximately 50 percent of the total weight. These
bombs normally weigh between 250 to 2,000 pounds and produce relatively good blast
and fragmentation. Examples of this type are the MK 82 and 84 series bombs.
DEMOLITION BOMBS
The explosive weight equals approximately 65 to 80 percent of the total weight.
These bombs have a relatively thin-walled casing to maximize blast effects while
penetration and fragmentation effects are limited. An example of this type is the
M118 demolition bomb.
FRAGMENTATION BOMBS
As the name implies, these bombs are intended to disperse and project high-
velocity fragments. The fragments are the principle damage mechanism of the
weapons, with blast effects being a secondary consideration. The charge to total
weight ratio varies from 10 to 20 percent. No bomb presently in the inventory is
primarily a fragmentation bomb although GP bombs do produce a relatively good
fragmentation effect. CBU munitions are primarily fragmentation weapons.
PENETRATION BOMBS
These bombs are designed to penetrate and explode inside a hard target such as a
concrete bunker. They are built with heavy cases and are aerodynamically designed
to counter break-up. The explosive charge is approximately 25 to 30 percent of the
total weight. The AGM-65 Maverick missile with its shaped charge penetrating
warhead and the 1-2000 are good examples of penetrating munitions.
BOMB EFFECTS
The destructive effect of a high-explosive bomb is due primarily to the detonation of
the high-explosive filler. The chemical reaction which takes place upon initiation
14
T.O. 1—IM—34
EXPLOSIVES FILLER CHART
The following high explosives are the most commonly used and are arranged in rela
tive order of decreasing sensitivity:
1. MERCURY FULMINATE: This is an initiating compound which is extremely sensitive

to heat, friction, spark, flame, or shock. For all practical purposes, this com
pound has been replaced by lead azide.
2. LEAD AZIDE: This is an initiating compound used to detonate light explosives.

It is sensitive to flame and impact. Lead azide is used in detonator assemblies in
fuzes.
3. TETRYL: Tetryl is sufficiently insensitive when compressed to be used as a

booster explosive. Tetryl is also used as a burster in chemical shells and bombs,
in a 70:30 ratio with TNT.
4. RDX: This explosive is manufactured by the nitration of hexamethylenetetramine.

Two types of RDX are used for military purposes. It is sometimes referred to as
Hexogen. RDX is less sensitive to electric spark than are tetryl or TNT. It is
suspected to be more sensitive to impact than tetryl, although limited tests indi
cate it approximately equals it in impact sensitivity. It is the second most power
ful military explosive and is often used in small weapons.
5. EDNATOL: Ednatol is a mixture of Haleite (ethylene dinitramine) and TNT. It is

less sensitive than tetryl but more sensitive than TNT.
6. CYCLOTOL: This is a mixture of 60 percent RDX and 40 percent TNT. It is some

times called Composition B-2. Unlike Composition B, it does not contain any wax and
is more sensitive than Composition B.
7. COMPOSITION B: This is a mixture of RDX, TNT, and beeswax or similar wax. It

is less sensitive than tetryl but more sensitive than TNT.
8. TNT: Trinitrotoluene, commonly known as TNT, is one of the most stable of high
explosives. It is relatively insensitive to blows or friction. Confined TNT, when
detonated, explodes with violence. It is readily detonated by lead azide, mercury
fulminate, and tetryl.
9. AMATOL: This is a mixture of ammonium nitrate and TNT. It has approximately

the same general characteristics as TNT. Either a 50:50 or 80:20 mixture is used in
bombs. The first figure in each ratio represents the percentage of ammonium nitrate
in the mixture.
10. H-6: This explosive has the following composition: 45 percent RDX, 29.5 percent
TNT, 21 percent aluminum, 4 percent D-2 wax, and 0.5 percent calcium chloride. It
is used in the AGM-12B (MK 19 Mod 0) warhead.
11. TRITONAL: Tritonal is the name given to explosives containing TNT and aluminum,
generally in the ratio of 80:20. Tritonal produces a greater blast effect than
either TNT or Composition B.
12. EXPLOSIVE D: Of all the military explosives, this is the least sensitive to
shock and friction. Therefore, it is used as a bursting charge in Armor-Piercing
Bombs, which must pass through armor without exploding. Explosive D is also known
as ammonium picrate.
FIGURE 1-1 (Continued)
1-5
T.O. 1-IM-34
13. PICRATOL: Picratol is a mixture containing 52 percent Explosive D and 48 per

cent TNT. It has the same resistance to shock as that of Explosive D. Picratol is
used in some Semi-Armor-Piercing Bombs.
14. PENTOLITE: Pentolite is a mixture of PETN and TNT (50/50), usually in a melt
cast formation. The impact sensitivity of Pentolite is about the same as TNT. It
is used in bomb boosters, shape charges, and projectiles.
15. OCTOL: Octol is a mixture of TNT and HMX (25/75 or 30/70). Its sensitivity is
about the same as HMX. It is a melt cast form. Its principle uses are in shape
charges, high energy projectiles, and as bomb fillers.
16. HTA-3: This is a mixture of HMX/TNT/aluminum (49/29/22) and is a melt cast form
with a sensitivity similar to Octol. Its principle uses are in high energy projec
tiles and bomb fillers.
17. HBX-1: This is a mixture of RDX/TNT/aluminum/D-2 wax/calcium chloride

(40/38/17/5/.5). It is a melt cast. Its principle uses are in bomb fillers and
high-explosive charges.
18. DESTEX: This is a mixture of TNT/aluminum/D-2 wax/carbon wax (74.7/18.7/4.7/1.9).

It is used as filler in penetrating bombs and projectiles. It is less sensitive than
Tritonal.
19. MINOL II: This is a compound of TNT, ammonium nitrate, and aluminum (40/32/28).
It is an authorized alternate fill for Tritonal and has a similar sensitivity.
EXPLOSIVE FACTOR3
EXPLOSIVE PENTOLITE TNT H-6 TRITONAL COMP B

BASE BASE BASE BASE BASE
Comp B 1.02 1.13 0.87 0.92 1.00

Cyclotol D 1.09 1.21 0.93 0.98 1.07
Des tex 1.11 1.23 0.95 1.00 1.09
H-6 1.17 1.30 1.00 1.05 1.15
HBX-1 1.08 1.20 0.92 0.97 1.06
HTA-3 1.10 1.22 0.94 0.99 1.08
Minol II 1.01 1.12 0.86 0.91 0.99
Octol 0.96 1.07 0.82 0.86 0.94
Pentolite 1.00 1.11 0.85 0.90 0.98
Picratol 0.83 0.92 0.71 0.75 0.81
TNT 0.90 1.00 0.77 0.81 0.88
Tritonal 1.11 1.23 0.95 1.00 1.09
Weight of base explosive equivalent to one pound of the explosive. For

example, one pound of H-6 explosive will provide blast pressure and im
pulse equal to 1.17 pounds of Pentolite. The above explosive factors
apply to bare charges. They may vary for real cased charges.
FIGURE 1-1 (Concluded)
1-6
T.O. 1—1M—34
of the explosive train is the fundamental action required to attack and defeat a
specified target. Generally, the explosive train is used to achieve one of three
basic effects in the target area. These are blast, fragmentation, or cratering.
BLAST
The blast effect is caused by the tremendous overpressures generated by the detona
tion of a high explosive. Complete detonation of high explosives can generate
pressures up to 700 tons per square inch and temperatures in the range of 3,000 to
4,500 °C prior to bomb case fragmentation. Approximately half of the total energy
generated will be case fragmentation. Approximately half of the total energy
generated will be used in swelling the bomb casing to 1.5 times its normal size
prior to fragmenting and then imparting velocity to those fragments. The remainder
of this energy is expended in compression of the air surrounding the bomb and is
responsible for the blast effect. This effect is most desirable for attacking
industrial complexes or habitable structures with the intention of blowing down
walls, collapsing roofs, destroying or damaging machinery, etc. Blast is confined
to relatively short distances in its effectiveness on personnel. The maximum
distance is 110 feet at which the blast from a 2,000-pound bomb is considered effec
tive against personnel. Blast is usually maximized by using a GP bomb with a fuzing
system that will produce a surface burst with little or no confinement of the
overpressures generated.
FRAGMENTATION
Fragments of a bomb case can achieve velocities comparable to those of a small-arms
projectile (3,000 to 5,000 fps) and can cause great impact effects. Fragmentation
is effective against troops, vehicles, aircraft, and other soft targets. The
fragmentation generated from the detonation of a high-explosive bomb has greater
effective range than blast, usually up to approximately 3,000 feet regardless of
bomb size. The fragmentation effect can be maximized by using a bomb specifically
designed for this effect, or by using a GP bomb with an airburst functioning fuze.
CRATERING
With conventional aircraft-delivered bombs, the cratering effect is normally
achieved by using a GP bomb with a delayed fuzing system. This system allows bomb
penetration before the explosion occurs and permits the formation of a larger crater
as a result. This effect is most desirable in interdiction of supply routes and
area denial operations. It also finds application in attacks on multiple-storied
buildings. Rather than functioning the bomb instantaneously on impact with the roof
of a building, the delayed fuzing will allow the bomb to penetrate and use the con
finement of the building walls to increase the destructive effect of the bomb.
1-7
T.O. 1-1M -34
NOTE
Care must be exercised when employing GP

bombs against hard targets. If the bomb
impact angle is less than 40 degrees it will
likely ricochet; if the velocity is too
great, it will deflagrate (rapid burning).
Both factors are interdependent. If exact
combinations (angle/velocity) are required,
consult your JMEM Weapon’s Characteristic
Manual.
GENERAL-PURPOSE BOMBS
GP bombs are all cylindrical in shape and are equipped with conical fins or retard
ers for external high-speed carriage. They are adapted for both nose and tail fuzes
to insure reliability and to cause the desired effects, which may be blast, cra
tering, or fragmentation.
GP bombs in the current inventory are all similar in construction; therefore, the MK
82 bomb will be used as a typical example (FIGURE 1-2). The bomb body contains the
high explosive, charging well, and suspension lugs. Other parts added to make a
complete munition are adapter boosters, fin assembly, arming wires, and fuzes.
GP BOMB SUSPENSION LUG
FUZE SEAT LINER
FIGURE 1-2
1-8
T.O. 1—IM—34
CHARGING WELL
GP bombs are constructed with a charging well connected to the nose and tail fuze
wells. The charging well, located just aft of the forward suspension lug, is
usually closed with a threaded plug that must be removed for installation of braided
steel arming cables or lanyards used with the fuze, munition, and live unit (FMU)
fuzes. The steel cables or lanyards are threaded through the conduits inside the
bomb and extend out of the top of the charging well for attachment to the aircraft
solenoids.
SUSPENSION LUGS
Bombs weighing less than 2,000 pounds are equipped with two-point 14-inch suspension
lugs. The MK 84 and M118, which are in the 2,000-pound class and above, are
equipped with two-point 30-inch suspension lugs.
ADAPTER BOOSTERS
Nose and tail adapter boosters (FIGURE 1-3) are required when mechanical fuzes are
installed in bombs. The typical adapter consists of an adapter bushing and booster
charge assembled in a cylindrical
metal casing. The bushing has
external threads for installation in
ADAPTER BOOSTER (TYPICAL) the bomb fuze well and internal
threads to accommodate the fuze.
The body consists of a fuze seat
liner, a booster charge of two per
forated tetryl pellets, two felt
spacer disks, and inert filler. The
body is enclosed within a metal
casing. A protector plug, in the
form of a metal tube closed at one
end, extends through the per
forations in the booster charge and
closes the casing at the booster
end •
NOTE
There are various models of adapter

boosters and exact design will vary
slightly.
CONICAL FIN ASSEMBLY

FIGURE 1-3
The purpose of the conical fin
assembly is to help stabilize the
bomb in flight. Fins are made of light metal and may be easily bent. Spot welds
and other joints may be damaged. A bent fin may ruin the bomb’s ballistic
trajectory.
V9
T.O. 1—1M—34
ARMING WIRE AND LANYARD

Arming wires and lanyards are installed on bomb-type munitions to allow the pilot to
release an armed bomb or a safe bomb. Arming wires are used with mechanical fuzes
and arming lanyards are used with FMU series fuzes. Arming wires and lanyards arp
rigged to provide the highest possible probability that the munition will arm as
desired.
A typical arming wire/lanyard routing is shown in FIGURE 1-4. Prior to uploading

the bomb on the suspension equipment, arming wires are attached to the bomb suspen
sion lugs. One end of the nose arming wire is secured to the left side of the aft
suspension lug. The other end is inserted through an arming wire swivel loop and
then through the front suspension lug. The tail fuze arming wire is attached to the
right side of the front suspension lug, inserted through a swivel loop, and then
through the aft suspension lug. The bomb is now ready for uploading onto the
appropriate suspension equipment. Once uploaded, the free ends of the arming wires
are then attached or threaded through safety devices in the fuze, thus maintaining
the fuze in a safe (unarmed) condition (FIGURE 1-5). A beryllium or copper
Fahnstock clip is placed over the ends of the arming wires to prevent accidental
slippage prior to release. The arming wire passes through the arming wire swivel
loops. These are inserted into the proper arming solenoids (FIGURE 1-6).
ARMING__WIRE/LANYARD ROUTING (TYPICAL)

___________
FMU SERIES FUZING

For example, on FMU-fuzed bombs the lanyard (FIGURE 1-7) cable is inserted through
the internal conduit to the charging well. A swivel and link is then attached to
the arming lanyard. The swivel is inserted into the appropriate solenoid.
RELEASE
If the weapon is released armed, the energized solenoid will hold the swivel and
link assembly and cause the metal clips to be stripped off the arming wire, allowing
it to pull from the fuze, which then arms. If the munition is configured with an
1-10
T.O. 1—1M—34
ARMING WIRE TO FUZE AND ATU-35 (TYPICAL)
FIGURE 1-5
FMU-type fuze, the solenoid will normally hold the swivel and link assembly. This
causes a sharp pull on the lanyard or cable which then activates the FMU fuze.
SAFE
If the bomb is released in the safe condition, the arming wire swivel loops are
released from the pylon arming solenoids, the arming wires remain in the fuze safety
devices, and the fuzes cannot arm. Without fuze operation, the bomb will usually be
a dud. Low-order detonations may result from very high impact shock. A low-order
detonation results when the high explosive is incompletely exploded. A high-order
detonation results when all components of a high-explosive train decompose as
planned. With an FMU-fuzed munition, the swivel loop is also released with the bomb
and the fuze is not activated.
EXPLOSIVE FILLERS
The primary high-explosive filler used in the GP bombs is Tritonal, but there are a
relatively small number of bombs in the inventory filled with H-6.
1-11
T.O. 1-IM-34
FMU ARMING WIRE ROUTING (TYPICAL)
ARMING SOLENOID
NOTE
TYPICAL NOSE AND TAIL
ARMING WIRE ROUTING
FORWARD SUSPENSION LUG
SWIVEL & LINK ASSEMBLY
TAIL ARMING WIRE
FIGURE 1-6
FMU SERIES FUZING
FIGURE 1-7
1-12
T.O. 1-1M-34
Tritonal is the name given to explosives containing trinitrotoluene (TNT) and

aluminum, generally in the ratio of 80:20. H-6 has the following composition:
45 percent RDX, 29.5 percent TNT, 21 percent aluminum, 4 percent D-2 wax, and 0.5
percent calcuim chloride.
Knowledge of what type of explosive is used in bombs can be important. H-6 is more
sensitive to impact than Tritonal. A test was conducted with MK 84 bombs fitted
with inert fuzes to compare Tritonal and H-6 filled bombs. Seventy-five percent of
the H-6 bombs exploded on impact (impact velocity 1,030 fps). The Tritonal-filled
bombs all survived (1,040 fps). This has several important implications for
employment of Tritonal and H-6 bombs.
Tritonal is much less impact sensitive than is H-6. Because of this, Tritonal-
loaded GP bombs provide significantly improved penetration and survivability. A
Tritonal bomb is preferable for a target requiring penetration.
When a safe release is planned, the safe

escape and fragment considerations must
always be planned for, especially when
releasing H-6 filled bombs, because they are
more likely to detonate upon impact.
Some bombs will be marked Tritonal or H-6 somewhere on the bomb body. If the bomb
is not marked, the type of explosive can be determined by requesting the infor-
mation from explosive personnel or supply.
A Mod 2 version of the bomb has an exterior thermal protective coating, an improved
interior lining, and a new base sealing compound to make it more resistant to
cookoff in an open fire. The MK 82 Mod 2 can be recognized by a bumpy exterior sur
face and two yellow stripes around the bomb body.
MK 82 LD, MK 83 LD, MK 84 LDGP BOMBS

The MK 82 (500-pound class), MK 83 (1,000 pound class), and MK 84 (2,000-pound
class) low-drag, general-purpose (LDGP) bombs are similar in construction and vary
only in size and weight (FIGURE 1-8). The bombs have a streamlined cylindrical
body with a tapered aft section to which a conical fin assembly is attached. The
conical fin assembly will accept the ATU-35 series drive.
The MK 82 LD is equipped with the MK 82 conical-type fin or MAU-93/B conical fin.

The total weight of the MK 82 is 531 pounds, and it contains 192 pounds of Tritonal
high-explosive filler.
1-13
T.O. 1—1M—34
■ ■ ■
MK 82, MK 83, AND MK 84 GP BOMBS (TYPICAL)
CHARACTERISTICS
MK82 MK83 MK84
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 531 LB_ _ _ _ _ _ _ _ _ _ _ _ _ _ 985 LB 1972 LB
LENGTH 7 FT 2 IN 9 FT 11 IN_ _ _ _ _ 12 FT 8 IN.
DIAMETER 11 IN 14 IN--------------- 18 IN.
FIN SPAN 15 IN 20 IN. _ ...... - 25 IN.
FIN ASSEMBLY MK82 OR MAU-93/B_ _ _ MK83-------------- MK84
SUSPENSION LUG SPACING_ _ _ 14 IN. ._ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 IN--------------- 30 IN.
FIGURE 1-8
The MK 83 LD is equipped with the MK 83 conical-type fin or MAU-91 conical fin. The
total weight of the MK 83 is 985 pounds, and it contains 416 pounds of Tritonal or
H-6 high-explosive filler.
The MK 84 LD is equipped with the MK 84 conical-type fin. The total weight of the
MK 84 is 1,972 pounds, and it contains 945 pounds of Tritonal or H-6 high-explosive
filler.
MK 82 HDGP (SNAKEYE I) BOMB

The MK 82 (500-pound class) Snakeye I, a high-drag, general-purpose (HDGP) bomb
(FIGURE 1-9), is a MK 82 GP bomb that is modified by attaching a MK 15 series
retarding tail assembly. This configuration allows for low level releases and
steeper impact angles. The four MK 15 retarding fins are linked to a sliding collar
so all four fins must open at the same time. In the LD configuration, the retarder
fins are held closed by a retaining band. The retaining band is under 40 pounds of
tension provided by leaf springs under the retarder fins. After approximately 32
inches of fall from the aircraft, the fin release wire/lanyard is fully extracted
from the weapon, releasing the retaining band. At this time the leaf springs force
the retarder fins into the airstream. Airloads complete the opening of the fins,
extending them approximately perpendicular to the airstream to provide maximum drag
and stability.
1-14
T.O. 1—1M—34
CHARACTERISTICS MK82 SNAKEYE MK 36
W EIG H T_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 570 LB_ _ _ _ _ _ _ _ _ _ 572 LB

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 7 FT 6 IN_ _ _ _ _ _ _ _ _ 7 FT 3 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 11 IN._ _ _ _ _ _ _ _ _ _ _ 11 IN.
FIN SPAN (BEFORE RELEASE)_ _ _ _ 15 IN_ _ _ _ _ _ _ _ _ _ _ _ 15 IN.
FIN SPAN (AFTER RELEASE)--------- 65 IN_ _ _ _ _ _ _ _ _ _ _ _ 65 IN.
FIN ASSEMBLY_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ MK 15SERIES_ _ _ _ MK 15 SERIES
SUSPENSION LUG SPACING_ _ _ _ _ _ 14 IN_ _ _ _ _ _ _ _ _ _ _ _ 14 IN.
FIGURE 1-9
The MK 82 Snakeye can be released in either the HD configuration (retarding fins

open after release) or in the LD configuration (retarding fins remain closed). The
release configuration is determined by arming wire/lanyard routing and may be
cockpit selectable. Refer to the appropriate aircraft Dash 34 for detailed infor
mation concerning the required arming configuration for this capability.
If the cockpit selectable release option is

used, the prescribed arming wire/lanyard
routing must be utilized.
The MK 15 Mod 3A and Mod 4 tail assemblies are restricted to a maximum of 500 knots
calibrated airspeed (KCAS). When released HD, the MK 15 Mod 3 is restricted to a
maximum of 400 KCAS. HD deliveries (Mod 3A and Mod 4) below 450 KCAS may, and
below 400 KCAS will, cause the fins to partially open. This results in the bomb
impacting long.
1-15
T.O. 1—1M—34
HD deliveries above 5,000 feet above ground level (AGL) may, and above 10,000 feet
AGL will, cause bomb impact errors up to hundreds of yards.
MK 36 (DESTRUCTOR ) GP BOMB
The MK 36 (500-pound class) destructor is a MK 82 Snakeye I bomb fitted with a MK 75
arming kit which converts the bomb into a land or water mine (FIGURE 1-9). The
weapon is deployed HD only. The MK 36 destructor uses MK 82 Snakeye I ballistic
data. The MK 75 arming kit consists of a MK 32 arming device fitted into the nose
of the bomb and a MK 42 firing device that fits in the tail fuze well.
MK 82 AIR INFLATABLE RETARDER (AIR) HDGP BOMB

The MK 82 (500-pound class) AIR (FIGURE 1-10) is a MK 82 bomb that is modified by
attaching a BSU-49/B AIR tail assembly. The AIR provides a high-speed, low-
altitude delivery capability by use of bomb retardation. This increases bomb trail
and reduces the danger of the aircraft being hit by weapon fragments. The probabil
ity of bomb ricochet is reduced by increased impact angles.
The BSU-49/B AIR tail assembly consists of a ED stabilizer canister unit, the
ballute (combination of balloon and parachute), and the retarder release lanyard
assembly. The stabilizer canister unit acts as a container for the ballute and pro
vides aerodynamic stability during carriage and LD delivery. Four ballute attach
ment straps connect the ballute to an attachment plate near the center of the
stablizer unit. The aft end of this stablizer assembly is held in place by a latch
assembly until release. Forward of the attachment plate is a door for insertion of
the ATU-35 series arming drive. The entire canister is connected to the bomb with
an attachment ring. The ballute assembly is made from high strength, low-porosity
nylon fabric and is approximately 8 inches in circumference at the point it enters
the stabilizer canister. Ram air inflation is accomplished through four air inlet
ports toward the aft end of the ballute.
The retarder release lanyard assembly, located between two fins along the top side
of the stablizer canister, consists of a lanyard held in place by an adjustable
retracting spring. The lanyard connects the arming solenoid to the latch assembly
holding the baseplate onto the canister. As the bomb is ejected from the suspen
sion rack, the lanyard pulls the safety latch pin, and the baseplate is forced into
the airstream by compressed springs. Airloads continue to pull on the baseplate,
withdrawing the ballute until airflow through the ram air inlets inflate it to full
size. During this process, the lanyard cable pulls on the swivel and loop assembly,
shearing it. The lanyard is retained by the bomb, preventing damage to the aircraft
by the lanyard.
The MK 82 AIR release is cockpit selectable in either the HD configuration (ballute

inflated) or in the LD configuration (ballute not inflated) provided arming wire/
lanyard routing is accomplished during loading for these options. Refer to the
appropriate aircraft Dash 34 for detailed information concerning the required arming
configuration for this capability.
1-16
T.O. 1—1M—34
GUIDE LOOP ARMING WIRE ACCESS HOLE
LANYARD SAFETY LATCH PIN

RETRACTING
SPRING
SAFETY
LATCH
MK 82 BOMB
RETARDER
RELEASE
DETAIL A
LANYARD
FUZE ACCESS COVER
LANYARD CLIP
LATCH
DETAIL B
STOWAGE
SPRING
CLIP AFT COVER
ASSEMBLY
LANYARD
DETAIL A SWIVEL LOOP
BSU-49/B
RETARDER
HIGH-DRAG CONFIGURATION
ATU-35
LOW-DRAG CONFIGURATION
COVER
CHARACTERISTICS COVER
RETAINERS
WEIGHT_ _ _ _ _ _ _ _ _ 56 LB
LENGTH_ _ _ _ _ _ _ _ _ 26 IN.
FIN SPAN_ _ _ _ _ _ _ _ 15 IN. RELEASE
COMBINED WEIGHT SPRING
(MK 82/BSU-49/B) _ 550 LB
COMBINED LENGTH ARMING WIRE DETAIL B
(MK 82/BSU-49/B)_ 7 FT 7 IN. EXIT HOLE
SUSPENSION LUG SPACING__14 IN.
FIGURE 1-10
1-17
T.O. 1—1M—34

The BSU~49/B AIR assembly provides the capability to deliver HD MK 82s at airspeeds
from 200 to 700 KCAS, depending on type of aircraft and fuzing. Refer to the appro
priate aircraft Dash 34 tables for fuze arming. LD deliveries should be limited to
a maximum of 600 KCAS as testing has found excessive dispersion caused by ballistic
instability at delivery speeds above 600 KCAS.

The MK 84 (2,000-pound class) AIR (FIGURE 1-11) is a MK 84 bomb that is modified by
attaching a BSU-50/B AIR tail assembly. The BSU-50/B assembly is similar to the
BSU-49/B AIR assembly and consists of a LD stabilizer canister unit, a ballute, and
the retarder release lanyard assembly. The BSU-50/B operation is identical to
BSU-49/B operation. The release configuration is determined by arming wire/lanyard
routing and may be cockpit selectable. Refer to the appropriate aircraft Dash 34
for detailed information concerning the required fuze arming configuration.

The BSU-50/B AIR assembly provides the capability to deliver the MK 84 at airspeeds
to 700 KCAS. Decelerating forces to initiate fuze arming determine minimum release
airspeeds. The minimum airspeeds are significantly higher than those required to
arm the BSU-49/B. The BSU-50/B is only 12 percent larger than the BSU-49/B, but the
MK 84 is four times heavier than the MK 82. This increase in weapon mass, coupled
with a very small increase in ballute size, forces a higher delivery airspeed for
proper g forces sensed by the fuze. Minimum release airspeeds for HD employment of
the MK 84 AIR are:
1. FMU-54/B - 550 KCAS
2. FMU-54A/B - 550 KCAS
3. FMU-112/B - 460 KCAS.
1-18
T.O. 1—1M—34
MK 84 AIR INFLATABLE RETARDER (AIR ) HDGP BOMB

MK 84
BOMB
SAFETY
LATCH
I SAFETY
LATCH
PIN
COTTER PIN
RELEASE
SPRING
_ATU35
LOW DRAG
CONFIGURATION
CHARACTERISTICS
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ ._ _ _ _ . 97 LB
LENGTH 30 IN.
FIN SPAN. ................ 37 IN.
COMBINED WEIGHT
(MK 84/BSU-50/B) 2020 LB
COMBINED LENGTH
(MK84/BSU-50/B)" FT
SUSPENSION LUG SPACING_ _ 30 IN.
FIGURE 1-11
1-19
T.O. 1—1M—34
BLU-109/B (I-2000/TARGET BUSTER) PENETRATOR BOMB

The BLU-109/B (I-2000/target buster) (2,000-pound class) Penetrator Bomb (FIGURE
1 — 12) is an improved GP bomb. Improvements include: no forward fuze well, use of
high strength forged steel, increased bomb wall thickness, and a stronger tail fuze
well baseplate assembly which is connected internally by conduit to the fuze well.
The bomb body is flared on the rear to provide compatibility with the MK 84 tail
assembly.
BLU-109/B (I-2OOO/TARGET BUSTER) PENETRATOR BOMB
CHARACTERISTICS
WEIGHT._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1925 LB
LENGTH 8 FT 3 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 IN.
FIN ASSEMBLY MK 84 COMPATIBLE
SUSPENSION LUG SPACING 30 IN.
FIGURE 1-12
NOTE
Impact angle and velocity are critical for

proper weapon function. Refer to the
appropriate aircraft Dash 34 ballistic
tables.
The weapon contains 550 pounds of Tritonal explosive filler. An FMU-124A/B Mod 1
fuze (modified with a pyrotechnic delay) is installed in the tail fuze well of the
bomb. The FZU-32B/B initiator is installed in the charging well of the bomb and
provides electrical power to arm the fuze at release.
1-20
T.O. 1-1M-34
M117 GP BOMB
The M117 (750-pound class) LDGP bomb (FIGURE 1-13) has a cylindrical metal body with
an ogival nose and a tapered aft section to which a MAU-103/B or MAU-103A/B fin
assembly is attached. The MAU-103/B differs from the MAU-103A/B only in size and
material. Both fin assemblies will accept the ATU-35 series drive. Bombs marked
M117A1E1 or M117A3 contain 386 pounds of Tritonal explosive filler whereas those
marked M117A1E2 contain 386 pounds of Minol II explosive filler.
M117 GP BOMB ATU-35

ACCESS
HOLE
SUSPENSION LUGS
TAIL FIN
ACCESS HOLE
CHARACTERISTICS
WEI G HT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 823 LB

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 7 FT 6 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 16 IN.
FIN SPAN
M A U-10 3 / B __ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 19 IN.
MAU-103A/B_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 22 IN.
FIN ASSEMBLY ___________ MAU-103/B OR
MAU-103A/B
FIGURE 1-13
M117R (RETARDED) GP BOMB

The M117R (750-pound class) bomb (FIGURE 1-14) consists of an M117 bomb body
with a MAU-91A/B or MAU-91B/B retarding tail assembly. The fin assembly replaces
the conical fin and provides for a high- or low-drag employment. The HD or
1-21
T.O. 1- 1M-34
M117R (RETARDED) GP BOMB
M117D (DESTRUCTOR) GP BOMB
CHARACTERISTICS
WE IG HT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 857 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 7 FT 7 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 16 IN.
FIN SPAN (CLOSED) 22 IN.
FIN SPAN (OPEN)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 6 FT 11 IN.
RETARDING ASSEMBLY MAU-91A/B OR
MAU-91B/B
FIGURE 1-14
1-22
T.O. 1—1M—34
LD configuration is determined by arming wire/lanyard routing and may be cockpit

selectable. Refer to the appropriate aircraft Dash 34 for detailed information
concerning the required arming configuration for this capability.
WARNING

The fin assembly consists of four extendable drag plates attached to the bomb body
by a flange and support tube. In the LD configuration, the drag plates are held
closed by a release band. In the HD configuration, the release band latch is pulled
by the lanyard attached to the arming solenoid and allows the drag plates to deploy.
The drag plates are snapped open by a leaf spring under each plate and by the
airstream. The drag plates stop approximately perpendicular to the airstream to
provide maximum drag area and stability.
M117D (DESTRUCTOR) GP BOMB

The M117D (750-pound class) destructor (FIGURE 1-14) differs from the M117R in one
respect. The M117D is fuzed with components of the MK 75 arming kit (Refer to
Section IT.). The weapon is released HD only and is used for ground implant and
shallow water mining operations. Ballistic data are the same for both M117R and
M117D bombs.
M118 DEMOLITION BOMB

The M118 (3,000-pound class) LD demolition bomb (FIGURE 1-15) has a cylindrical
metal body with an ogival nose and a tapered aft section to which an M132 conical fin
assembly is attached. The demolition bombs are designed for higher blast effect
than a GP bomb of comparable weight. Approximately 65 percent of the total bomb
weight is an explosive charge of Tritonal. The case is relatively thin walled and
as a result would not be a good penetrator. The M118E1 differs from the M118 in
that threaded lug wells are provided to receive threaded suspension lugs. Both
bombs contain 1,888 pounds of Tritonal filler.
The M132 conical fin assembly will accept the ATU-35 series drive (required for M905
tail fuze) by use of a modified access hole cover. This fin is used on the M118
bomb and is not compatible with the M118E1 bomb. The M132E1 conical fin is used on
the M118E1 bomb and is not compatible with the M118 bomb. The fins are not inter
changeable between bombs because of a difference in physical makeup. The bolt holes
and attachment points vary between bombs and fins.
1-23
T.O. 1—1M—34
M118 DEMOLITION BOMB
CHARACTERISTICS
WEIGHT 3020 LB
LENGTH 15 FT 5 IN.
DIAMETER 24 IN.
FIN SPAN 37 IN.
SUSPENSION LUG SPACING_ _ 30 IN.
FIGURE 1-15
GBU-10 AND GBU-12 LASER-GUIDED BOMBS (LGB)

The GBU-10 and GBU-12 are GP bomb bodies (MK 84 and MK 82, respectively) equipped
with electronic and mechanical assemblies that provide laser terminal guidance. A
computer control group (CCG) with guidance canards is attached to the front of the
warhead to provide steering commands. A wing assembly is attached to the aft end
to provide lift. The LGB is a maneuverable free-fall weapon requiring no electronic
interconnect to the aircraft. It has an internal semiactive guidance system that
detects laser energy and guides the weapon to a target illuminated by an external
laser source. The LGB samples the reflected laser energy from the target and cor
rects its trajectory as it glides. There are two generations of LGBs: Paveway I
with fixed wings and Paveway II with folding wings (FIGURES 1-16 and 1—17,
respectively).
Paveway I models are: GBU-10/B, A/B, and GBU-12/B, A/B. The airfoil group for
these weapons can be either in the slow speed (big canards and wings) configuration
or in the high speed (small canards and wings) configuration. The slow speed con
figuration is recommended for use by all aircraft as it outperforms the high speed
configuration in all delivery regimes. In addition, the slow speed configuration
provides low altitude, low angle, and loft/toss delivery capabilities which are not
available with the high speed configuration.
1-24
T.O. 1—1M—34
PAVEWAY I LASER GUIDED BOMBS

SLOW SPEED
PORTION
COMPUTER CONTROL WEAPON BODY WING ASSEMBLY*

AND GUIDANCE (CCG) (WARHEAD)
*AIRFOIL GROUP (AFG) COMPONENTS
GBU-10 CHARACTERISTICS GBU-12 CHARACTERISTICS
WEIGHT 2052 LB WEIGHT 600 LB

LENGTH----------------------------------- 14 FT LENGTH 10 FT 6 IN.
DIAMETER 18 IN DIAMETER 11 IN.
WlNGSPAN 54 IN. WINGSPAN 39 IN.
SUSPENSION LUG SPACING 30 IN. SUSPENSION LUG SPACING 14 IN.
COMPONENT REFERENCE CHART
ITEM GBU-10/B GBU-10A/B GBU-10B/B GBU-12/B GBU-12A/B
WARHEAD MK 84 MK 84 MK 84 MK 82 MK 82
GUIDANCE KIT KMU-351A/B KMU-351B/B KMU-351C/B KMU-388/B KMU-388A/B

KMU-388A/B
COMPUTER MAU-157/B MAU-157A/B MAU-157B/B MAU-157/B MAU-157A/B

MAU-157A/B
WING ASSEMBLY MXU-600/B MXU-600A/B MXU-600A/B MXU-602/B MXU-602A/B

(COLOR) YELLOW YELLOW (2) YELLOW (2) ORANGE ORANGE (3)
CANARDS
HIGH SPEED YELLOW YELLOW YELLOW ORANGE ORANGE
LOW SPEED BROWN BROWN GREEN GREEN
(1) EITHER THE GBU-12/B OR A/B CAN BE MADE A CONSTANT CODE BOMB BY THE ADDITION
OF THE MAU-157B/B COMPUTER.
(2) LOW SPEED WING ASSEMBLY EXTENDERS ARE COLORED BROWN.
(3) LOW SPEED WING ASSEMBLY EXTENDERS ARE COLORED GREEN.
FIGURE 1-16
1-25
T.O. 1-1M-34
PAVEWAY II LASER GUIDED BOMBS
*AIRFOIL GROUP(AFG) COMPONENTS
GBU-10 CHARACTERISTICS GBU-12 CHARACTERISTICS
WEI G HT__ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2081 LB WEIGHT 610 LB

LENGTH _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 FT2 IN LENGTH._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 10 FT 11 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 18 IN. DIAMETER 11 IN.
WINGSPAN.. ________ 28/66 IN. WINGSPAN 18/52 IN.
SUSPENSION LUGSPACING__ _ 30 IN. SUSPENSION LUG SPACING_ _ _ 14 IN.
COMPONENT REFERENCE CHART
ITEM GBU-10C/B GBU-10D/B GBU-10E/B GBU 12B/B GBU-12C/B GBU-12D/B
WARHEAD MK84 MK84 MK84 MK82 MK82 MK82
GUIDANCE KIT KMU-351D/B KMU-351E/B KMU-351F/B KMU-388C/B KMU-388D/B KMU-388iE/B

KMU-388F/B
COMPUTER MAU-169/B MAU-169A/B MAU-169B/B MAU-169/B MAU-169A/B MAU-169B/B

MAU-169D/B MAU-169D/B
WING
ASSEMBLY MXU-651/B MXU-651/B MXU-651/B MXU-650/B MXU-650/B MXU-650/B
(COLOR) YELLOW YELLOW YELLOW ORANGE ORANGE ORANGE
CANARD
COLOR YELLOW YELLOW YELLOW ORANGE ORANGE ORANGE
FIGURE 1-17
Paveway II models are: GBU-10C/B, D/B, E/B, and GBU-12B/B, C/B, D/B. These weapons
are an improved version of the Paveway I series of weapons. The improvements con
sist of the following:
1. The detector optics and housing are made of injection-molded plastic

instead of glass and metal to reduce weight and cost.
2. The detector field of view (FOV) is increased.
1-26
T.O. 1—1M—34
3. The detector sensitivity is increased.
4. The thermal battery delay after release is reduced.
5. The maximum canard deflection is increased.
6. Laser coding is provided.
7. Wings are folded for carriage.
LGB COMPONENTS
All LGB weapons consist of a COG, warhead (bomb body with fuzes), and an airfoil
group. The following description includes the differences between Paveway I and
Paveway II weapons (FIGURES 1 — 16 and 1—17).
SEEKER HEAD
The seeker head (FIGURE 1-18) contains the detector assembly, optics, and electronic
circuitry that determines the direction of the laser reflected energy and generates
appropriate error correction signals. The seeker head, which is free to move in
pitch and yaw, is always streamlined into the relative wind by a ringtailed stabi
lizer mounted around its circumference. Gimbal limits of the seeker head are +18
degrees for both Paveway I and II. The Paveway II instantaneous FOV is 30 percent
greater than the Paveway I FOV.
FOUR-QUADRANT
DETECTOR
ASPHERIC FOCUSED
DETAIL OF DETECTOR OPERATION INFRARED SPOT
FILTER TO PREAMP
PLASTIC
DOME
OPTICAL AXIS
THE ENERGY FROM POINTTARGET OFFTHE

OPTICAL AXIS IS FOCUSED AT A POINT
REFLECTED ENERGY FROM PROPORTIONALLY OFF-AXIS TO THE DETECTOR
TARGET (OFF AXIS)
FIGURE 1-18
Instead of focusing the laser energy directly on the detector, the lens is moved
closer to the detector which defocuses the spot. A filter allows only light of the
desired laser wavelength to pass (FIGURE 1-18).
1-27
T.O. 1-1M-34
DETECTOR SUBASSEMBLY
A four-quadrant3 light-sensitive disk produces a very small electrical signal when

the laser spot hits it. The disk is mounted perpendicular to the axis of the seeker
head. Since the seeker is stabilized into the relative wind, the location of the
spot of light on the detector corresponds to the relative position of the target
(FIGURE 1-18). If the spot of light falls in the upper right hand quadrant, the
bomb electronics indicate the target is down and left, relative to its present
flightpath.
BOMB GUIDANCE COMPUTER
The computer section contains circuitry that processes signals from the detector and
transmits directional command signals to the appropriate pair(s) of canards. Other
circuitry in the computer contains the guidance logic, and in the Paveway II has
pulse repetition frequency (PRF) or pulse interval modulation (PIM) coding
capabilities.
GUIDED BOMB CONTROL SECTION
The control assembly includes the thermal battery, gas generator, associated mani
folds, valves, and pistons that actuate the canards. The thermal battery is
activated by an external lanyard when the bomb is released. The thermal battery has
a 70-second life in Paveway I and a 55-second life in Paveway II. After a 3-second
delay (Paveway I) or 2-second delay (Paveway II except MAU-169D/B), an electrical
pulse fires the gas generator. Gas from the generator is controlled through a mani
fold assembly with four cylinders. A solenoid for each cylinder is controlled by
directional signals from the computer. Actuation of the solenoids permits gas to
enter the corresponding cylinder and move the pistons that are mechanically con
nected to the canards.
NOTE
The current versions of the Paveway II,

GBU-10E/B and GBU-12D/B, use the MAU-169D/B
CCG. The CCG fires the gas generator after
laser acquisition. This feature improves
weapon ballistics for long-range loft/toss
deliveries. However, this feature induces a
2.4- to 3.1-second delay in guidance after
acquisition is declared. Therefore, to pro
vide the 8 seconds of optimum guidance, a
minimum time of fall or flight (TOF) of 11
seconds is recommended for weapons using the
MAU-169D/B CCG.
1-28
T.O. 1-IM-34
GUIDANCE CANARDS
Guidance canards are attached to each quadrant of the control unit to change the
flightpath of the weapon. Opposing canards always respond simultaneously (act in
pairs) with 5.5-degree deflections (Paveway I), or 10.5-degree deflections (Paveway
II), to generate up/down or left/right directional changes. The deflections are
always full scale (bang, bang guidance). The bomb is not roll stabilized and may
rotate randomly about its longitudinal axis. The guidance computer is able to func
tion and cope with the slow roll rates generated. Paveway I canards snap into
sockets on the control unit and lock into place. Paveway II canards are held in
place with setscrews. (Refer to FIGURE 1-17 for various configurations.)
AIRFOIL GROUP COMPONENTS

The airfoil group consists of the adapter collar (which is bolted to the nose of the
bomb for installation of the CCG), the canards, and the tail assembly. On Paveway I
weapons, a fixed tail is bolted to the bomb and extenders are bolted to the wing to
form a long winged bomb (slow speed configuration).
Paveway II weapons which have the folding wings have a tail assembly which contains
four wings, each with a deployment spring. The wings are linked to a mechanism that
ensures simultaneous movement. Wing deployment is activated at release by an exter
nal lanyard connected to a bomb rack sway brace. Upon release, shock absorbers
restrict wing deployment for safe aircraft separation.
NOTE
The GBU-10A/B and GBU-12A/B Paveway I weapons

are available in a high speed (short wing)
version or in a slow speed (long wing) ver
sion which was developed for use on slower
aircraft. Due to large control surfaces, the
slow speed bomb has greater maneuverability
and, therefore, a larger release envelope
than the high speed version. There is no
carriage or employment airspeed difference
between the high speed and slow speed
weapons. It is desirable to employ the long
wing (slow speed) version when carriage
allows because of the increased capabilities.
Canards are packaged in the long wing version
with a separation groove so the tip can be
broken off to form the short wing. The tail
assembly is packaged as a short wing version
with extenders which must be bolted on to
obtain the long wing. The short wing (high
speed) bombs are capable of dive releases,
but offer low probability of success from
level or loft/toss releases because of the
limited control surfaces area and maneuvering
g available.
1-29
T.O. 1-1M-34
FLIGHTPATH CHARACTERISTICS
The flightpath (FIGURE 1-19) of the LGB is adjusted by the guidance and control sec
tion to meet the required impact criteria. However, the design of the system may
result in some effects that can significantly degrade the performance of the weapon.
The following explanation of the typical LGB flightpath discusses these effects on
performance.
The LGB flightpath can be divided into three phases: ballistic, transition, and
terminal guidance. The ballistic (unguided) phase, consists of the period of flight
which lasts at least as long as the gas generator delay. The ballistic phase may
last the entire flight, depending on the FOV and/or detector sensitivity constraints
that restrict target acquisition and guided response.
During the ballistic phase, the weapon continues on the unguided trajectory
established by the flightpath of the delivery aircraft at the moment of release. In
the ballistic phase, the delivery attitude takes on additional importance. If
released in a loft/toss mode (a positive climb angle), the weapon continues its
climb, increasing in altitude but losing velocity. For level release, the weapon
begins to lose velocity almost immediately and continues to decelerate until it has
established a steep dive angle. Altitude permitting, it now ceases to lose velocity
and slowly accelerates. If released in a high angle dive mode, the weapon normally
accelerates from the moment of release to impact or until it reaches terminal
velocity.
The change in weapon velocity during the ballistic flight can be critical. This is
especially true if the velocity loss before acquisition is substantial. The
maneuverability of the LGB is related to the weapon velocity during terminal
guidance. Therefore, airspeed lost during the ballistic phase (and not recovered
before acquisition) equates to a proportional loss of maneuverability during ter
minal guidance.
The transition phase begins at acquisition. The following conditions must be

satisfied to accomplish acquisition:
1. The target must be within the detector FOV.
2. The reflected laser energy from the target must be of sufficient intensity
to activate and maintain guidance circuits.
3. The gas grain generator delay must have expired and there must be suf
ficient gas pressure buildup to activate the canards.
At acquisition, there is usually a large error between the weapon velocity vector
and the line of sight (LOS) to the target. In the transition phase, the weapon
attempts to reduce this error by aligning the velocity vector with the LOS vector to
the target. This phase usually takes from 0 to 3 seconds. During this period, the
commands to the control surfaces are generally sustained for longer periods, causing
additional energy loss.
The terminal guidance phase begins when the apparent guidance error is reduced and
the weapon develops an oscillating pattern around the LOS. An oscillatory flight
path is produced because (1) the detector senses only the direction (not magnitude)
of error, and (2) the canard deflections are always full scale.
1-30
T.O. 1-1M-34
LGB FLIGHTPATH
LGB DELIVERY
LASER DESIGNATOR AIRCRAFT
AIRCRAFT LGB RELEASE
LGB ACQUISITION
AND GUIDANCE
TRANSMITTED INITIATION
IR ENERGY
REFLECTED
IR ENERGY
LGB BALLISTIC
TRAJECTORY
TARGET
LGB LOS FROM

ACQTO TARGET
ANGLE ERRORSENSED
UP COMMAND PRODUCED
LGB GUIDED FLIGHTPATH
TARGET
FIGURE 1-19
1-31
T.O. 1—1M—34
During terminal guidance, the LGB attempts to keep its velocity vector aligned with
the instantaneous LOS. At the instant alignment occurs, the reflected laser energy
centers on the detector and commands the canards to a trail position. At this time,
the weapon flies ballistically with gravity biasing the velocity vector short of the
target. Therefore, the reflected energy is moved from the detector center which
generates an up command. In effect, the weapon’s velocity vector tends to oscillate
about a point short of the target which may cause the LGB flightpath to sag. The
extent of this sag is dependent on the delivery angle and airspeed.
OPTIMUM GUIDANCE TIME

Release tables for LGBs are generated with consideration for the gas generator safe
separation delay, and provide for 5 seconds of guidance. However, field experience
has shown that an optimum guidance time of 8 seconds provides a much greater proba
bility of success. Thus, release parameters should be selected that provide optimum
guidance time. The minimum TOFs to ensure optimum guidance time are:
Paveway I (all)........................ 11 seconds
Paveway II (early versions)........... 10 seconds
Paveway II (GBU-10E/B, GBU-12D/B) 11 seconds
FUZES
Fuzing options available for LGBs are depicted in the fuze/bomb compatibility chart,
Section II.
CODING
Coding has two purposes: (1) to meet the requirement for target identification in a
multilaser environment and (2) to provide effective operation in the presence of
enemy countermeasures. As a result, two code formats have been developed for use:
PRF and PIM. Refer to classified supplements of aircraft Technical Orders (T.O.)
for amplification.
GBU-15 DATA LINK WEAPON SYSTEM

The GBU-15(V)1/B (FIGURE 1-20) provides the capability for accurate standoff TV
(automatic/manual) guided delivery of the MK 84 bomb at increased ranges. Effective
standoff range is increased because it is not necessary to acquire the target area
before release; the target area and specific aiming point can be located after
release during weapon flight by observing the video transmitted from the weapon.
The weapon midcourse flightpath may be adjusted either automatically or manually.
Likewise, terminal guidance may be closed-loop automatic tracking with aiming point
updating, or if desired, the weapon may be manually steered to impact.
The weapon may be remotely controlled before and after release by means of the
AN/AXQ-14 data link (DL) system. Major components of the DL system are the DL pod,
the cockpit data link control panel (DLCP), and the weapon data link (WDL) installed
on the weapon.
1-32
T.O. 1-1M-34
■ ’
GBU-15(V)1/B GUIDED BOMB
0A-8921/XQ-14
MXU-724/B WEAPON
AIRFOIL GROUP DATA LINK
DSU-27A/B TARGET
DETECTING DEVICE
\ WCU-8/8 WEAPON
\CONTROL UNIT
WINGS (4)
CONTROL
SURFACES (4)
ADU-452A/B
GUIDANCE
/
FMU-124A/B
ADAPTER FUZES (2)
CHARACTERISTICS
TOTAL WEIGHT 2515 LB

LENGTH 13 FT
WINGSPAN._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT 11 IN.
STRAKE SPAN 29 IN.
DIAMETER
TARGET DETECTING DEVICE_ _ _ 15 IN.
WARHEAD 18 IN.
CONTROL UNIT 16 IN.
FIGURE 1-20
1-33
T.O. 1—1M—34
The DL system provides simultaneous transmission and reception of command signals

and video information between the command aircraft and the weapon. Video data from
the weapon are transmitted by the WDL to the DL pod on the command aircraft for front
and rear cockpit display. Command signals for control of the weapon are transmitted
to the WDL by the DL pod, which is controlled by the weapon system operator (WSO)
through the DLCP.
Inflight remote control (primary indirect attack mode) of the GBU-15 is provided by
the RT-1210/AXQ-14 DL pod. The indirect attack mode provides operational flexi
bility in both the release and guidance envelopes. This is made possible by the
video/command DL between the delivery aircraft or a standoff control aircraft and
the weapon.
In the indirect attack mode (See FIGURES 1-21 and 1-22.) the DL pod receives video
from the weapon and, under control of the WSO, transmits command signals to effect
weapon control. The WDL accepts and processes these commands and transmits the
weapon video to the controlling aircraft to form the basis for operator decisions
and commands. Weapon video is generated in the Target Detecting Device (TDD) in the
nose of the weapon.
The GBU-15 may be released in a backup, direct mode (without DL) as well as in the
primary indirect attack mode. The direct attack option is useful for targets of
opportunity. It is also useful as a backup mode in the event of a malfunction in
the DL subsystem (control panel, DL pod, or WDL). The weapon may be released from
low or high altitudes, but is always released in terminal mode without DL control.
The direct attack weapon is locked onto the target before release. After target
acquisition and lock-on, the weapon is released from the aircraft in the terminal
mode. The target detecting and control unit components generate the required
signals (yaw, pitch, and roll attitude) for the weapon to maintain or correct the
designated heading to target impact.
DSU-27A/B TARGET DETECTING DEVICE

The TDD (FIGURE 1-20) contains the optical dome, TV camera (seeker), stabilized
platform, logic, video processor, automatic tracker, weapon mode switch, and power
supply. The camera provides the scene sensing functions for target acquisition,
manual and automatic tracking and weapon steering. In the captive and midcourse
modes of operation, the seeker can automatically track a target or can be manually
positioned up to ±30 degrees in azimuth and elevation from the weapon longitudinal
axis. LOS rate signals from the TDD generate steering signals to the automatic
pilot .
ADU-452A/B GUIDANCE ADAPTER

The guidance section adapter provides the mechanical interface between the TDD and
warhead nose. It has attachment points for the strake and conduit assemblies. An
opening in the right side provides an entry point for the conduit electrical wire
harness. The wire harness connects the control unit to the TDD. An access door
located on the right side allows weapon assembly operations, nose fuze inspection
for safe/armed condition, fuze arming lanyard connection/inspect ion, and selection
of the TDD weapon mode switch position.
1-34
T.O. 1—1M—34
LOW ALTITUDE INDIRECT ATTACK

AUTOTERMINAL
OR
TERMINAL
PRERELEASE COMMAND^
TRANSITION
COMMAND TERMINAL
RELEASE
TRANSITION
MIDCOURSE
PLATFORM
ANGLE -24
COMMAND LOCKOUT
LEVEL (SAFE SEPARATION)
RELEASE
STABILIZED PITCH COMMAND

1.75 BODY
CLIMB ANGLE‘S
aO , nO SEC ANGLE,
RELEASE
ACCELERATION -4.2°
COMMAND MODE
RANGE TERMINAL
TERMINAL
COMMAND
WEAPON
PRERELEASE MIDCOURSE TRANSITION TERMINAL FLIGHT
CONTROL
> HEADING COMMANDS > SEEKER STEERING S SEEKER STEERING YAW
> ACCELERATION • -24° PITCH PLATFORM

(G-BIAS) ANGLE LIMIT • SEEKER STEERING PITCH
e ATTITUDE • ATTITUDE
e SET UP WEAPON • RELEASE WEAPON S FLY PREPLANNED • FLY PREPLANNED

EOR RELEASE > EXECUTE TURN EGRESS EGRESS
• SET UP DATA LINK e TRACK TARGET OR > SELECT TRANSITION • SELECT TERMINAL OR
POD TARGET AREA ALLOW
AIRCREW ACTIONS
$ ACQUIRE AND • SLEW (PLATFORM) • TRACK TARGET AUTOTERMINAL

IDENTIFY TARGET • FREE GYRO • SLEW(GATE) ACTIVATION
OR TARGET AREA • AUTO TRACK • AUTO TRACK • TRACKTARGET
IF VISIBLE • SLEW/UPDATE
> ADJUST WEAPON S ARM FUZE # RELOCK WEAPON
• SELECT EO HEADING (OPTIONAL) OR
• ARM FUZE • STEER TO IMPACT
(OPTIONAL) • AUTOMATIC FUZE
ARM IF NOT DONE
PREVIOUSLY
FIGURE 1-21
1-35
T.O. 1—1M—34
TRANSITION AUTOTERMINAL OR
TARGET COMMAND TERMINAL COMMAND
WEAPON RELEASE ACQUISITION
SEPARATION
^-PRERELEASE-* -MIDCOURSE TRANSITION TERMINAL-*!
COMMAND BODY PLATFORM

ANGLE -4.2 ANGLE -24°
1.75
SEC
TRANSITION
ENABLED
MOMENTARILY
TO INHIBIT
G-BIAS
RANGE
WEAPON
PRERELEASE MIDCOURSE TRANSITION TERMINAL FLIGHT
CONTROL
® HEADING COMMANDS • SEEKER STEERING • SEEKER STEERING YAW
e -24° PITCH PLATFORM

• ATTITUDE ANGLE LIMIT • SEEKER STEERING PITCH
• ATTITUDE
• SET UP WEAPON © RELEASE WEAPON • FLY PREPLANNED • FLY PREPLANNED

FOR RELEASE •EXECUTE TURN EGRESS EGRESS
• SET UP DATA LINK S DESELECTTRANSITION • SELECT TRANSITION ® SELECT TERMINAL OR

POD (SELECT EO 3SEC ALLOW
AIRCREW ACTIONS
> ACQUIRE AND AFTER RELEASE) • TRACK TARGET AUTOTERMINAL

IDENTIFY TARGET • TRACK TARGET OR * SLEW(GATE) ACTIVATION
OR TARGET AREA TARGET AREA • AUTO TRACK • TRACKTARGET
• SLEW (PLATFORM) • SLEW/UPDATE
® SELECT • FREE GYRO • ARM FUZE • RELOCK WEAPON
TRANSITION ® AUTO TRACK (OPTIONAL) • OR MANUALLY
e ADJUST WEAPON STEER TO IMPACT
HEADING • AUTOMATIC FUZE
e ARM FUZE ARM IF NOT DONE
(OPTIONAL) PREVIOUSLY
FIGURE 1-22
1-36
T.O. 1—1M—34
MXU-724/B AIRFOIL GROUP

This group consists of the four cruciform configured forward strakes, wings, and
control surfaces. The strakes are attached to the guidance adapter, and the wings
and control surfaces are attached to the control unit. The control surfaces are
linked to the wings and the control unit pneumatic actuation system. Signals from
the TDD to the automatic pilot drive the control unit actuator output shafts, which
in turn, cause control surface movement and provide aerodynamic control of the
weapon. The conduit and umbilical assembly are also components of the airfoil
group. The conduit provides the electrical interface between the TDD and control
unit. It attaches to the right side (looking forward) of the weapon. The umbilical
assembly, located on the top center line of the control unit, provides the electri
cal interface between the aircraft and the weapon. The umbilical connector mates
with the aircraft pylon wiring harness.
WCU-8/B WEAPON CONTROL UNIT

The weapon control unit (WCU) is attached to the aft end of the warhead and contains
subcomponents that process data received from the DSU-27A/B TDD and Receiver-
Transmitter Group, to provide control of the weapon during flight. The WCU is
attached to the aft end of the warhead and consists of the body assembly, pneumatic
actuation system, two accelerometers, inverter/converter, wire harness assembly, two
gyroscopes, automatic pilot, and battery. The body section provides attachment
points for the wings, control surfaces, umbilical assembly, and conduit assembly.
The wire harness assembly provides the electrical interface between components in
the control unit, WDL, conduit assembly, and umbilical located on the top cen
terline. A safety pin protects against inadvertent activation of the electrical
squib systems (pneumatic actuator and battery) during ground handling. When acti
vated by the pickle signal, the pneumatic actuation system supplies the energy to
position the control surfaces. An access door located on the left side allows
weapon assembly operations, tail fuze inspection for safe/armed conditions, arming
lanyard connection and inspection, and inspection of the battery fault indicators.
OA-8921/AXQ-14 WEAPON DATA LINK

The WDL is attached to the aft end of the control unit. It simultaneously transmits
video from the TDD to the control aircraft DL pod and receives commands from the
control aircraft DL pod to the weapon. The video transmitter radiates low power
video at station select and automatically switches to a high power video when the
weapon ready mode is initiated. The radio frequency channel must be selected prior
to flight with the channel select switch on the back cover. Multiple tactical chan
nels and one training channel are available.
GBU-15(V)(T-1)/B TRAINING BOMB

The GBU-15(T-l)/B training bomb is a captive weapon used to train aircrews in the
delivery of the GBU-15. It is identical in appearance to the GBU-15(V)1/B bomb and
uses the same modules with the exception of the WCU. The WCU-6(T-1)/B training
control unit contains a modified automatic pilot which prevents normal weapon
release, and it uses a power supply unit instead of a battery to supply weapon
voltages. The control surfaces of this training bomb are locked in place to permit
safe separation in the event of jettison.
1-37
T.O. 1-1M-34
RT-1210/AXQ-14 DATA LINK POD

The DL pod (FIGURE 1-23) is an aerodynamically shaped body suspended from the bomb
rack on the centerline station. It is not jettisonable.
RT-121O/< ATA LINK POD

PHASE-
SCANNED
ARRAY
ANTENNA
CONNECTOR
ACCESS CENTER
DOOR STRUCTURE
HORN
AFT
ANTENNA RADOME
FWD
RADOME
ELECTRONICS
UNIT ♦
COVER
FWD
EQUIPMENT AFT
ACCESS EQUIPMENT
DOOR SLIDE-MOUNTED
ACCESS
DOOR
CHARACTERISTICS
WEIGHT 435 LB
LENGTH _......................... 10FT10 IN.
DIAMETER......... .............. . 20 IN.
SUSPENSION LUG SPACING— 30 IN.
FIGURE 1-23
Commands to the DL pod are converted into weapon guidance and control (G&C) signals
by the pod and then transmitted to the WDL for weapon control. Simultaneously, the
pod receives weapon video for display in the command aircraft. The pod also uses
one of two selectable antennas for transmission/reception: a rear Phase-Scanned
Array (PSA) antenna for use in the aft and side sectors of the command aircraft or a
front horn antenna for forward sector coverage. To minimize enemy detection of pod
radiation, the pod transmits only when a discrete command is issued and stops 2
seconds after the command is terminated. However, pressing and holding the action
switch on the Integrated Hand Control (IHC) causes the command transmitter to con
tinuously transmit until 2 seconds after the action switch is released. Thus,
holding the action switch pressed unnecessarily defeats the silent unless keyed
transmitter mode.
1-38
T.O. 1—IM-34
The DL pod has two transmitting power levels, low for prerelease checkout and high
for weapon control during free flight. The power levels are determined by controls
on the DLCP.
BLU-107/B (DURANDAL) PENETRATOR BOMB

The BLU-107/B (Durandal) (FIGURE 1-24) is a demolition bomb designed for low alti
tude release, to penetrate thick unreinforced concrete, and to create large craters
that cause buckling of airfield surfaces. The weapon design incorporates a two-
stage parachute retardation system that allows for low altitude delivery while pro
viding safe separation. Penetration velocity is achieved by rocket-boosted kinetic
energy. It is designed for level delivery at 250 feet AGL and for release speeds up
to 620 KCAS.
The Durandal has three main sections: the parachute, rocket motor, and the warhead.
The parachute section is a cylindrical metal casing which contains two folded
parachutes and is attached to the rocket motor section by the separation frame. The
rear cover of the casing acts as the extractor for the 21.5-square-foot surface area
brake chute. The brake chute is attached to the rear frame by a swivel shackle.
The swivel shackles are used to prevent parachute malfunction caused by rotation.
The R1500 pyrotechnic delay is a timing delay between brake chute and main chute
deployment and is housed in the separation frame.
■ > W ' -
BLU-107/B (DURANDAL) PENETRATOR BOMB
CHARACTERISTICS
WEIGHT 450 LB
LENGTH 8 FT 2 IN.
DIAMETER 9 IN.
FIN SPAN 16 IN.
FIN ASSEMBLY BLU-107
SUSPENSION LUG SPACING_ _ _ 14 IN.
FIGURE 1-24
1-39
T.O. 1-1M-34
The rocket motor and sequencer are surrounded by a skirt and four stabilizer fins.
The sequencer contains a bobweight and senses deceleration caused by the parachute
system and the R350 pyrotechnic delay. The delay, a nominal 300 milliseconds (ms),
provides the time required to sense proper deceleration of the bomb and provides the
required delay between main chute deployment and firing of the R2500 pyrotechnic
delay. This delay between the sequencer and rocket motor provides a nominal 1,700
ms delay between deceleration verification and rocket motor initiator firing.
The warhead contains 33 pounds of TNT-base explosive surrounded by a cylindrical

metal casing and capped with an aerodynamic nose. The nose cap covers a cutting
surface which prevents ricochets. The warhead fuze, which is connected to the
sequencer, protrudes through the rear of the warhead.
The post-release sequence is depicted in FIGURE 1-25. At weapon release, the bomb
rack solenoid extracts the arming wire. During extraction the arming wire locks the
brake chute shackle to the rear frame of the parachute container and the main chute
DURANDAL RELEASE SEQUENCE

________________________________________ U_____________________________________________ ■
FIGURE 1-25
1-40
T.O. 1—1M—34
shackle to the separation frame. The rear parachute cover is released into the free
airstream and pulls out the brake chute. Simultaneously, the R1500 delay is ini
tiated. Following the delay, the parachute container and brake chute are jettisoned
and the main chute is deployed. During this sequence, the rocket motor ignition
system is armed, the sequencer bobweight is released, and the R350 delay (300 ms) is
initiated. If the bobweight senses an 8-g deceleration for the duration of the R350
delay, the bomb functional sequence continues (The warhead fuze arms, and the R2500
delay fires.). If the proper deceleration is not felt, the functional sequence is
stopped. This delay provides proper separation between the aircraft and the bomb at
fuze arming and, in conjunction with the bobweight, provides a safety factor by not
allowing the bomb to arm if the chute fails. The R2500 delay (1,700 ms) allows the
bomb to attain the desired angle of incidence (35 degrees or greater) before the
main chute is jettisoned. Following the R2500 delay, the rocket motor initiator
ignites the rocket motor and the separation frame and main chute are jettisoned.
The rocket motor burns for 0.45 second. Upon impact with the target, a 1-second
warhead detonator delay is actuated, allowing the warhead sufficient time to
penetrate several feet below the target surface prior to detonation.
AGM-65 MAVERICK MISSILE

The Maverick is a rocket propelled air-to-ground missile that uses a shaped charge
optimized for use against armored vehicles, bunkers, boats, radar vans, and small,
hard targets. The Maverick is capable of launch-and-leave operations, relying on
automatic self-guidance. Various modes of guidance exist in the Maverick missile
series. The Air Force has procured three models, the Electro-Optical (EO) AGM-65A
and B, and the Infrared (IR) AGM-65D. The A/A37A Training Guided Missile (TGM) is
used for training in AGM-65 employment. The aft section, containing the power
supply, rocket motor, warhead, and hydraulic actuation system, is common to the
AGM-65A, B, and D. The missile guidance sections, however, are different, with
minor changes between the AGM-65A and B, and a major variation in the AGM-65D.
All Maverick missiles are carried and launched from the LAU-88 or LAU-117 launcher
described in Section V.
AGM-65A AND AGM-65B (EO) MAVERICK MISSILES

The AGM-65A and AGM-65B are TV-guided models of the Maverick air-to-surface missile
family. Both models contain a shaped-charge warhead and an EO, centroid-type
tracker. Targets must be visually acquired and missile video acquisition must be
accomplished prior to launch. Both models are guided autonomously, providing a
launch-and-leave capability. The AGM-65B has an improved guidance unit and a
magnified target image which allows target video acquisition and launch at greater
standoff ranges; other portions of the B model missile are the same as the AGM-65A.
A typical AGM-65, associated launchers, and statistics are shown in FIGURE 1-26.
The missile consists of two major sections: (1) a forward section containing the
target seeker and missile guidance electronics and (2) an aft section containing the
warhead, rocket motor, and flight control unit.
FORWARD SECTION
The nose of the missile has a clear , dome-shaped, glass window that is protected by
a slightly opaque, frangible glass dome cover. The dome cover is shattered as the
141
T.O. 1—IM—34
SHEAR PIN
RECEPTACLE
CHARACTERISTICS
WEIGHT_ _ 464 LB
LENGTH_ 8 FT 2 IN.
DIAMETER 12 IN.
WINGSPAN 28 IN.
AFT ROCKET
SHEAR
GUIDANCE FORWARD PIN HOOK MOTOR
SECTION HOOK
DOME COVER
ACTUATOR
UMBILICAL
DOME HYDRAULIC
COVER ACTUATION
SYSTEM
U
GIMBALED
GYRO AND
CAMERA WARHEAD SA & F BATTERY WIRING ROCKET MOTOR GAS CONTROL
UNIT HARNESS IGNITER CABLE BOTTLE SURFACE
FIGURE 1-26
missile is selected for launch. Immediately behind the window is a seeker unit com
posed of a vidicon (TV camera) surrounded by a ring-shaped gyro mounted on a two-
axis gimbal structure. FIGURE 1-26 shows the gimbal limit, launch limit, and FOV of
both the AGM-65A and AGM-65B. The seeker is positioned by push rods connected from
the gyro to two electrical torquer motors. Specific cockpit switch procedures can
place the seeker/guidance unit in four modes: ready, align, slew, and track. In
the ready mode, electrical power is supplied to spin the gyro and braking mechanisms
1-42
T.O. 1—1M—34
on the torquer motors hold the seeker in a fixed position. When the missile is in
the align mode, the brakes are relaxed and the seeker is held at the boresight posi
tion by electrical power applied to the torquer motors. In the slew mode, the
seeker is positioned by left/right and up/down commands given to the two torquer
motors from manual cockpit controls. When in the track mode, the torquer motors
respond to commands from the target tracking portion of the guidance unit. The
guidance unit electronics contain the circuits necessary to operate the seeker unit,
track the target, and generate missile steering commands.
CAUTION
® The AGM-65 (A or B) missile must not be main

tained in the ready mode in excess of 60
minutes on any single mission. Since 3 min
utes are necessary for the gyro to reach
rated speed, the missile can only be operated
an additional 57 minutes.
• The AGM-65 (A or B) missile must not be main

tained in a full power mode (align, slew, or
track) in excess of 3 minutes on any single
attack if the missile is intended to be
launched on that attack.
® These missile operational time limits repre

sent missile design capability. As a general
rule, the missile may be operated for longer
time periods if the image presented on the
cockpit display is usable.
The seeker optics and vidicon assembly are protected by an automatically operated
sun shutter that closes when frontal light reaches harmful intensity. The shutter
will remain closed until the seeker is directed away from the intense light source.
During the tracking phase of missile operation, the sun shutter circuitry is deac
tivated and the shutter will remain open.
AFT SECTION
Located behind the missile guidance unit is a 125-pound conical shaped-charge
warhead designed to penetrate heavy armor or reinforced structures. Housed in the
aft core of the warhead is a safe, arming, and fuzing (SAF) unit. As a missile
encounters a designed acceleration/time envelope during launch, the SAF arms the
warhead. Warhead detonation is initiated by a contact trigger in the nose of the
missile or by a mechanical backup detonator in the SAF which functions when the
missile encounters a lateral deceleration of at least 75 g.
1-43
T.O. 1-1M-34
The missile is propelled by a 104-pound solid propellant rocket motor. The boost
sustain type motor consists of a case, liner, and blast tube. The boost phase pro
duces approximately 10,000 pounds thrust and lasts approximately 0.5 second; the
sustain phase produces approximately 2,000 pounds thrust for approximately 3.5
seconds. After rocket motor burnout, the remainder of the missile flight is
unpowered. Rocket motor ignition is accomplished through an igniter cable on the
aft end of the missile. Before takeoff, the ground crew attaches the igniter cable
to the receptacle on the launcher.
The missile uses aircraft electrical power until the missile has started to launch.
When the launch command is received, the missile thermal battery is activated and
reaches rated voltage in approximately 0.5 second. As the missile begins to travel
forward along the launcher rail, the umbilical plug in the aft end of the missile
separates from the launcher-mounted receptacle. At this point, the missile battery
assumes the electrical load of the missile. The battery will continue to supply
adequate power for a minimum of 105 seconds.
NOTE
Should too short a launch signal be provided,

commonly referred to as a quick or short
pickle, the battery may be activated and the
rocket motor fail to fire. In this case, the
thermal battery will rapidly overheat and may
fail to provide adequate voltage for success
ful guidance. A second launch of the missile
should be attempted only if it can be done
immediately on the same attack and safe
launch parameters can be achieved.
The aft portion of the missile also contains the Hydraulic Actuation System (HAS),
the flight control servo mechanism which processes the steering signals from the
guidance unit into aerodynamic control of the missile. The HAS derives its mechani
cal power from a bottle of helium gas that provides pressure as the umbilical plug
separates during launch. The gas pressure drives a hydraulic pump which feeds
hydraulic fluid to actuating cylinders for the control surfaces. Flow of the
hydraulic fluid is controlled by valves which respond proportionally to the signals
from the guidance unit. Thus, control surface deflections are proportional to the
amount of flightpath correction required.
VIDEO DISPLAY
The AGM-65A seeker 5-degree FOV is presented on the cockpit video display as shown
in FIGURE 1-27. A set of crosshairs that span the entire display is also presented.
The intersection of the crosshairs is open to represent the tracking gate which has
a minimum size of 1.8 mils (milliradians) high by 1.4 mils wide. The crosshair gap
expands to accommodate the target size. A solid lock-on is achieved when the
crosshairs become steady and centered on the target. Even with steady crosshairs,
the smallest target dimension must fill at least one-half of the crosshair gap
before attempting launch. Before missile launch, the seeker must be pointing within
1-44
T.O. 1- 1M—34
AGM-65A,-65B VIDEO DISPLAY
BACKGROUND
GATES S 2.5° OR 44 MILS
POINTING
CROSS
FIGURE 1-27
15 degrees of the missile centerline in order to maintain successful track during

transient forces encountered during launch.
The seeker of the AGM-65B has a 2.5-degree FOV and a 0.9-mil-high by 0.7-mil-wide
tracking gate. A larger vidicon lens is used to double the size of the apparent
target. The cockpit video display also presents a magnified image, and the sym
bology for the tracking gate is a rectangular arrangement of four small squares
(background gates). A small crosshair, called a pointing cross, shows seeker posi
tion relative to the missile centerline. Before missile launch, the seeker must be
aimed within 10 degrees of the missile centerline in order to maintain successful
track during transient launch forces. The pointing cross flashes on and off to
indicate when the 10-degree launch angle limit is exceeded. In addition, the
1-45
T.O. 1-1M-34
pointing cross also flashes when the target size is too small to ensure that lock-on
will be maintained during launch. A scene magnification identifier is located in
the upper left corner of the video to indicate Maverick video versus F-4 Target
Identification System Electro-Optical (TISEO) video is present.
NOTE
Target size is computed by the missile on the

basis of area. In some cases, the target may
present sufficient area to cause a steady
pointing cross, yet have an apparent dimen
sion that is too small to ensure that lock-on
is maintained. Before AGM-65B launch, the
smallest target dimension must fill at least
one-half of the gap between the four
background gates.
GUIDANCE
Light from the target scene enters through a window in the nose of the missile and
is converted to an electrical charge pattern on a plate in the vidicon tube. The
charge pattern varies in intensity corresponding to variations in brightness in the
target scene. Electrical signals representing the target scene along with electron-
nically generated reference symbols are sent to the cockpit display. The target
scene signals are also sampled to determine brightness at particular points.
Points inside the target area (defined by the opening at the intersection of
crosshairs for the AGM-65A or the area bounded by the four background gates for the
AGM-65B) are compared with points just outside the target area (background). In
the automatic contrast mode, the guidance unit selects the contrast logic, light
target on dark background or dark target on light background, based on the target-
area/background-area relationship as referenced to an average brightness between the
two areas. The average brightness level is established as the threshold between
target and background at the time of the target lock-on.
NOTE
Due to the longer time required to obtain a

lock-on, use of the automatic contrast mode
is not recommended when target contrast can
be visually determined.
Choice of target area as an area lighter or darker than the background is normally
controlled by the setting of the contrast polarity switch in the cockpit. If
white-on-black (W/B) contrast is selected, the target area is defined as an area
lighter than the background. In this mode, the missile will not lock onto a dark
target. The opposite is true if black-on-white (B/W) contrast is selected.
After lock-on, the target area and the background area are continually sampled to
determine if the target is still in the center of the scene. If the target moves or
1-46
T.O. 1—IM-34
if the missile LOS begins to drift off the target, the seeker is slewed to realign
it with the center of the target area. The resulting misalignment between the
seeker and the missile line of flight is detected by the guidance unit which sends
correction signals to steer the missile back into alignment with the seeker.
After launch, the missile flies a humped course which is designed to allow the
missile to achieve long range and maintain a higher terminal velocity. The missile
function which produces this upward steering course is called g-bias. The effects
of g-bias on missile flightpath are illustrated in FIGURE 1-28. At lock-on, the
missile determines the upward direction in relation to the wings of the aircraft, not
the horizon. While a wings-level attitude is most desirable at lock-on, aircraft
bank should not exceed 30 degrees at launch or vary more than 30 degrees from lock-
on to launch. Otherwise, g-bias programming will be less than optimum. The g-bias
of the AGM-65A programs a nominal 3.5-g pull in the upward direction until the
missile detects a 20-degree look-down angle. The AGM-65B has a nominal 4.5-g pull
until it reaches a 16-degree look-down angle.
EFFECT OF G BIAS ON MISSILE FLIGHTPATH
GROUND RANGE (FT x 1000)
FIGURE 1-28
As the missile flies toward the target, the target grows in apparent size. This
change is detected by the missile guidance unit, which continually redefines the
target boundaries to adapt to the increasing target area. When the target size
1-47
T.O. 1-1M-34
fills a large portion of the FOV, 62.5 percent for the AGM-65A and 70 percent for
the AGM-65B, the guidance unit stops increasing the defined target area and correc
tion signals are held at a constant rate for the remainder of the flight. This is
known as last rate memory and occurs during the last 0.25 to 0.50 second of flight
for most armor-sized targets.
AGM-65 OPERATIONAL LIMITATIONS

The AGM-65 missile will not be launched under conditions which exceed the following
limits:
1. Launch speed: Maximum, mach 1.2.
2. Maximum gimbal offset angle: AGM-65 A—15 degrees; AGM-65B--10 degrees.
3. Maximum dive angle: 60 degrees.
4. Maximum bank angle: 30 degrees.
5. Maximum roll rate: 30 degrees per second.
6. Minimum/maximum load factor: +0.5 g/+3.0 g.
AGM-65D (IR) MAVERICK MISSILE

The AGM-65D missile (FIGURE 1-29) is separated into forward and aft sections. The
aft section containing the missile wings, warhead, SAF unit, rocket motor, and
hydraulic activation system is identical to the AGM-65A and B. The forward section
is significantly different from EO Mavericks. The AGM-65D guidance unit uses an IR
seeker that converts IR energy into electrical signals. The signals are then con
verted by a digital computer into a TV video image from which the aircrew is able to
identify and lock onto objects within the seeker FOV. The digital computer also
allows the missile to make logical decisions prior to, during, and after launch,
decreasing aircrew workload and enhancing missile performance. A dual FOV capabil
ity was added to provide selection of wide FOV (WFOV) for search and narrow (NFOV)
for improved target identification and increased launch range. The IR seeker
expands the missile launch environment to include night and degraded visual
conditions.
FORWARD SECTION
The forward section is a hermetically sealed guidance unit consisting of an IR dome,
IR seeker, electrical contact trigger, autopilot, and electronics assemblies
including the digital computer. The entire forward section may be rotated on the
missile body to orient the seeker head when the missile is mounted on a shoulder
rail of the LAU-88 launcher. The guidance unit window in the nose of the missile is
protected by a glass dome cover identical to that used on the EO Maverick. The pur
pose of the cover is to protect the second and third missiles in the launch sequence
from the rocket motor exhaust of the first missile. The dome cover must be shat
tered prior to employing the AGM-65D because the material in the cover will atten
uate and distort the IR energy.
1-48
T.O. 1-1M-34
AGM-65D (IR) MISSILE
WINGS
AFT
HOOK / s'
)1
SHEAR PIN \
RECEPTACLE
FORWARD
HOOK /
ROTATING \ ZX Vz CONTROL
JOINT \ /X / SURFACE
CHARACTERISTICS
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ 500 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ 8 FT 2 IN.
/ \o \ N\ DIAMETER 12 IN.
y y’
V TELESCOPE
rRYO
WINGSPAN,
ELECTRONICS
28 IN.
AUTOPILOT
SENSORS
if. :f
/^GUIDANCE \
SECTION
SEEKER GIMBAL LIMIT +30u -54° VERTICAL /W

+42° HORIZONTAL / /
LAUNCH LIMIT-CLASSIFIED DOME'' / \ \ \ ROTATING JOINT
WIDE FIELD OF VIEW-CLASSIFIED COVER / /
NARROW FIELD OF VIEW-CLASSIFIED IRDOME \ \ \TORQUER ASSEMBLY
\ DETECTOR
DELAY LINE/ BAIL RING
PREAMPLIFIER
____ ASSEMBLY
LAUNCH L t --------- Z-ryY-'"--- —
LIMIT J:_ _ _ _ _ _
GIMBAL
LIMITS
L-NARROWFIELDOFVIEW
— WIDE FIELD OF VIEW
FIGURE 1-29
1-49
T.O. 1—1M—34
The missile seeker is located immediately behind the guidance unit window. The
seeker is gyro-stabilized and free to move left and right 42 degrees, up 30 degrees,
and down 42 degrees from the longitudinal axis of the missile. The seeker gyro
requires a delay of 3 minutes after electrical power application to reach operating
speed. Missile electronics should inhibit missile activation until the seeker gyro
has reached 90 percent of full operating speed.
CAUTION
A minimum of 3 minutes must be allowed

beween seeker gyro electrical power applica
tion and any attempt to uncage the seeker.
IR energy from the target scene enters the seeker after passing through the guidance
unit window (FIGURE 1-29). The window contains a special material which allows IR
energy to pass through it without distortion. As the IR energy enters the seeker, a
set of telescope lenses focuses the IR scene on a folding mirror. The scene is
reflected from the folding mirror through another series of lenses which give a dual
FOV capability. The scene is then reflected from a rotating scan mirror, through a
viewing lens which focuses the IR energy onto an array of IR detectors. The
rotating scan mirrors break up the scene into a series of narrow bands. Each band
is then further reduced to a series of electrical signals by the detector array.
The signals are electronically manipulated and reconstructed into the TV image pre
sented on the cockpit display. A special design feature of the scan mirrors pro
duces an area of enhanced resolution in the center of the display. The super scan
area allows the tracking of smaller targets at longer range.
The seeker is positioned by torquer motors which function in the same manner
described for the EO Maverick. When the missile is in the ready mode, mechanical
brakes in the torquer motors attempt to hold the seeker gyro at the boresight
position. However, when the aircraft pulls positive g while maneuvering, the
torquer motor brakes may slip and allow the seeker to slowly move to a gimbal limit.
This slippage can cause unnecessary delays in the lock-on process. The seeker
electrically aligns at the rate of 8 to 10 degrees per second; aircraft turn rates
in excess of that will cause the seeker to lag behind the aircraft.
<»*#♦******< (
:: caution ::
• The AGM-65D missile must not be maintained in

the ready mode in excess of 60 minutes on any
single mission. Because 3 minutes are
necessary for the gyro to reach rated speed,
the missile can only be operated an addi
tional 57 minutes.
• The AGM-65D missile must not be maintained in

full-power mode (align, slew, or track) in
excess of 3 minutes on any single attack if
the missile is intended to be launched on
that attack.
1-50
T.O. 1—1M—34
The forward section also contains the electronic circuits which operate the seeker
unit, track the target, and generate missile steering commands. The autopilot com
bines these steering commands with gyro-sensed yaw, roll, pitch, and lateral accel
eration rates. From this information, the autopilot computes course corrections to
steer the missile on a collision path to the target.
AFT SECTION
The description of the AGM-65D IR Maverick missile aft section is the same as that
for the AGM-65A and B missiles.
VIDEO DISPLAY
The AGM-65D cockpit video image (FIGURE 1-30) is composed of an IR scene video and
electronically generated symbols consisting of crosshairs, a pointing cross, seeker
depression angle markers, and four NFOV markers. The crosshairs are a set of hori
zontal and vertical lines extending through the center of the display. The
AGM-65D (IR) VIDEO DISPLAY
NARROW
FIELD OF VIEW
(NFOV) MARKERS
HORIZONTAL
CROSSHAIR
POINTING
CROSS
NFOV MARKERS
FIGURE 1-30
1-51
T.O. 1-1M-34
intersection of the lines is gapped to delineate the tracking window, the area in
which the tracker defines the boundaries of the target based on differences in IR
radiation level. The adjustments of the tracker to accommodate the expanding
apparent size of a target being approached produces a widening of the crosshair gap.
The displacement of the pointing cross from the center of the display shows the
relative bearing between the LOS of the missile seeker and the longitudinal axis of
the missile. Any portion of the pointing cross that is coincident with the tracking
window is blanked so as not to interfere with target identification. The three
seeker depression angle markers at 5 degrees, 10 degrees, and 15 degrees assist the
aircrew in estimating the displacement of the pointing cross.
When first activated by the uncage signal, the missile will display WFOV, and the
cockpit display will contain the four L-shaped NFOV markers. A second application
of the uncage signal will select NFOV, and the portion of the video between the NFOV
markers will fill the entire display. In NFOV the four markers will not be present
on the display.
NOTE
If the missile is tracking a target in WFOV,

activation of uncage will change the FOV, but
the lock-on will be broken and the seeker
will return to memory boresight or slave
mode. To regain lock-on rapidly when
selecting NFOV, slew enable must be commanded
before activating uncage. This will allow
the seeker to remain fixed in angle and facil
itate target reacquisition. The missile may
be launched in either NFOV or WFOV.
All display symbols may be displayed as either black or white. If W/B contrast is
selected for tracking a target (white) that is warmer than its background (black),
the display symbology will be white. Black symbols will be displayed for B/W
contrast selection.
GUIDANCE
The IR Maverick does not use a hot spot tracker typically found in heat seeking air-
to-air missiles. The AGM-65D uses rotating scan mirrors and IR detectors to
generate a video scene and uses the differences in temperature (displayed as
contrast) between the target and its background to define and track the target.
The IR Maverick guidance unit differs from the EO version by the addition of a digi
tal computer which processes the analog video signals. The computer then provides
several programs which enhance missile employment. The computer uses a launch tran
sient assist program which provides a memory of the target image should the
tracking gate drift during the initial phase of flight. This program automatically
begins to search and relock the seeker on the proper target. An event program pre
vents an abnormal tracking condition from pulling the tracker off the intended
target. A motion program prevents the seeker from losing a lock on a moving target.
A correlator track program provides guidance when the centroid tracking gate expands
1-52
T.O. 1-1M-34
to approximately 70 percent of the FOV as the target is approached. The correlator

track program uses memorized data to establish directions and rates of motion which
are then used to compute terminal steering commands.
The AGM-65D has the capability to memorize a seeker boresight position within 6
degrees of the longitudinal axis of the missile. This feature allows the aircrew to
correct for boresight errors which may occur during loading. In addition, for night
use it may be desirable to boresight the missile below the aircraft flightpath vec
tor. Boresight memory can be set by adjusting aiming reference (gunsight) to the
intended boresight position, placing the aiming reference over a visual target iden
tifiable on the display, locking onto the target, selecting the auto position on the
contrast polarity switch, depressing and releasing the slew enable button, then
placing the contrast polarity switch to either B/W or W/B. After accomplishing
these steps, the seeker position will be stored in computer memory and will return
to this position each time the missile is put in the align mode.
NOTE
Missiles loaded on a LAU-88/A or LAU-117/A

must each be boresighted individually.
A centroid tracker program tracks the centroid of the IR target in a manner similar
to that of the tracker in the EO Maverick. The tracker also uses an automatic gain
control in conjunction with threshold levels to determine tracking gate size and
position. An aided target acquisition program helps the tracker lock on when the
target is not centered in the tracking gate. A good lock program indicates when a
valid lock-on exists. As in the AGM-65B, a steady pointing cross on the TV display
indicates a good lock, and a flashing pointing cross indicates a high probability
of break-lock at launch. The pointing cross is steady when: the IR contrast
between the target and background is sufficient, the target apparent size is large
enough, and the relative bearing of the target is within the missile launch angle
cri teria.
TARGET ACQUISITION
When a target is sighted visually, uncage the missile to activate missile video and
align the seeker to boresight. Fly the aircraft to place the gunsight or head-up
display (HUD) aiming reference on the target, and depress the slew enable button to
stabilize the seeker gyro. Observe the cockpit display, and verify that the correct
target is centered in the tracking window. Release the slew enable button to com
mand lock-on. Even if the target is not quite centered in the tracking window,
release of the slew enable button will activate the aided target acquisition program
and effect target lock-on. (If a FOV change is desired or required, it should be
accomplished prior to release of the slew enable button, or subsequent rotation of
the dual FOV lenses will cause target break-lock.) Once lock-on is commanded,
observe the cockpit display to ensure the desired target is centered in the
crosshairs and that the pointing cross is steady. Because the pointing cross is
initially steady prior to evaluation, allow approximately 1 second for the good lock
program to function before commanding launch. If the pointing cross remains steady
for 1 second or longer, depress and hold the weapons release button to launch the
missile. If the pointing cross is flashing, fly toward the pointing cross to
1-53
T.O. 1-1M-34
center it in the display and change to NFOV if not already selected. Depress and
hold the slew enable button before commanding FOV change (uncage) to prevent the
seeker from returning to the boresight position. Reaccomplish the lock-on and
reevaluate the display. If the pointing cross is still flashing, continue to fly
toward the target or select a different target. The aircrew must ensure that the
missile is launched within its maximum aerodynamic range. Aircraft sensors such as
PAVE TACK, AN/ARN-101, and AN/APR-38 may be used to slave the IR Maverick FOV to the
target. The aircraft must be properly wired, and the missile must be loaded on a
LAU-117/A or a modified LAU-88/A launcher. With the missile in the align mode,
locate the target with the active sensor and activate the slave switch. As this
procedure is essentially a search for the target, leave the Maverick in WFOV and
command slave. This missile seeker will slave to the same point as the selected
sensor is pointing. The seeker will accept slaving signals from the selected sensor
within 30 degrees of the missile longitudinal axis. Contrast selection may be made
once the target appears on the cockpit display. If the target appears inside the
NFOV markers, the uncage signal may be applied to change missile FOV. Lock-on and
launch considerations are the same as those in visual target area procedures. As
the slave signal may be some distance off boresight, the aircraft may have to be
maneuvered to place the pointing cross within missile launch limits.
A/A37A TRAINING GUIDED MISSILE (TGM-65)

The Maverick TGM is a captive training device designed to train aircrews in the use
of the AGM-65A, B, and D missiles. It provides realistic training in systems opera
tion, target acquisition, and tactics. The TGM can be configured as a TGM-65A, B,
or D, with or without a recorder. Because of the similarity of the operational and
training systems, only the differences will be discussed. In most respects the TGM
(FIGURE 1-31) is physically identical to the live missile. The differences are:
the external control surfaces are not present, the warhead has been replaced by a
signal processing unit, and the rocket motor and the hydraulic actuation system have
been replaced by a film recorder and/or ballast. The TGM can be suspended from any
LAU-88/A or LAU-117A launcher. The TGM has no igniter cable. The TGM is completely
inert because it contains no warhead, rocket motor, hydraulic actuation system, or
battery. Electrical control is provided by the launcher electrical assembly.
The TGM is a modular training device made up of any one of four guidance units mated
to any one of two center/aft sections. The T3 and T4 guidance units provide the
same cockpit display as does the AGM-65A. The T5 guidance unit simulates the
AGM-65B, and the T8 guidance unit provides the AGM-65D IR display. These guidance
units differ from their respective tactical missile guidance units in external
markings, lack of autopilot, and lack of dome cover. The T7 center/aft section is
equipped with the film recorder, but the T6 center/aft section has ballast in place
of the recorder. The inflight switch positions are the same for the TGM as for the
live missile.
CAUTION
Improper switchology may result in the

jettisoning of the TGM and associated suspen-
sion equipment.
1-54
T.O. 1—1M—34
A/A37A TRAINING
■ GUIDED MISSILE
. (TGM-65)
GUIDANCE UNIT CENTER/AFT SECTION
CHARACTERISTICS
LENGTH 8 FT 2 IN.
DIAMETER 12 IN.
WINGSPAN 29 IN.
SUSPENSION—_ _ _ _ _ _ _ LAU-88 OR LAU-117 MISSILE LAUNCHER
WEIGHT (A/B) 464 LB (APPROX) (445 WITHOUT RECORDER)
(D) 478 LB (459 WITHOUT RECORDER)
RECORDING TIME 30 MINUTES AT 3.75 FRAMES PER SECOND
15 MINUTES AT 7.5 FRAMES PER SECOND
FIGURE 1-31
The TGM provides the same cockpit control response as the operational AGM-65
missile, except it does not launch. Launch is simulated by blanking the cockpit
video display 1 second after depressing the pickle button. When the weapons
release button is depressed to simulate launch, the TGM performs an orderly shut
down, which takes approximately 1 second.
1-55
T.O. 1-1M-34
caution ::
If the weapons release button is depressed

for less than 0.5 second (quick pickle), the
cockpit video display may blank but the
seeker may still remain in the track mode.
If this occurs, excessive heat buildup may
cause damage to the TGM guidance unit.
Deselecting the station after a pass with a
TGM-65A or B will preclude this problem. In
addition, in the A and B model TGM the sun
shutter circuitry will be disabled, causing
vidicon damage should the seeker be pointed
at the sun during target pulloff.
When a TGM with an IR guidance unit is carried on a LAU-117 launcher, the video does
not blank with a quick pickle. Instead, the missile will be placed in the align
mode by the launcher and the seeker will return to the boresight position. TGM
quick pickle can be corrected by momentarily deselecting the TGM station when safety
permits. This removes the seeker from the full-power mode (video blanks), applies
the seeker mechanical brakes, and allows the TGM to reset by initiating an orderly
shutdown.
The guidance unit functions only to enable acquisition, tracking, and designation of
a target. The EO picture or IR picture is relayed to the cockpit video display.
The TGM tracking window will expand to continue bounding the target as the aircraft
closes on the target. This expansion will continue until the attack is terminated
by a simulated launch, the guidance unit enters last rate memory, the tracker breaks
lock during pulloff, or the missile is placed in the ready mode by deselection.
TGM TIME LIMITATIONS

Do not operate the TGM in excess of 40 minutes in the ready mode or in excess of 30
minutes in the full-power mode (video present). The 30-minute full-power limitation
is cumulative video time during the mission.
• Three minutes are required for gyro spin-up,

to prevent damage due to gyro tumble, prior
to uncaging the seeker head.
• Three minutes of constant video on a single

pass is maximum allowable time to prevent
heat damage to the guidance unit.
• Do not operate the TGM in excess of 15 min

utes on the ground to prevent heating
problems.
1-56
T.O. 1—1M—34
The AGM-65 requirement for 45 seconds between an aborted launch and subsequent
missile callup does not apply to the TGM, because the missile is not intended for
flight.
TGM RECORDER
TGMs with a T7 center/aft section contain a camera (FIGURE 1-31) which records TGM
video on 16mm film for postflight evaluation. The full film magazine contains
approximately 30 minutes of film at 3.75 frames per second, and 15 minutes at 7.5
frames per second (better picture clarity). TGMs generate event markers (FIGURE
1-32) to depict align, slew, track, and launch modes. Launch gimbal limits, missile
polarity, and pass number markers are also depicted. Event markers are not pre
sented on the cockpit video display.
AGM-45 SHRIKE MISSILE

The AGM-45 (FIGURE 1-33) is an antiradiation air-to-surface missile designed for the
destruction of ground- or sea-based radar systems. Twelve versions were produced
and each version has a preset frequency coverage that is set at missile buildup, and
once set is not field changeable. The frequency range of a particular Shrike ver
sion is denoted by a suffix number to the AGM-45 designation.
Electronic order of battle (EOB) is gathered by the WILD WEASEL aircraft using its
on-board equipment. The emitters are targeted, switches are set and when launch
parameters are met, the missile is fired.
After leaving the aircraft, the Shrike continually senses the radar emissions and
generates command signals to home-in on the targeted radar.
In the final phase, a proximity fuze sets off a high explosive fragmentation warhead
which is designed to destroy or damage radar components.
MC-l GAS BOMB

The MC-l (FIGURE 1-34) is a nonpersistent gas bomb designed by modifying the M117 GP
bomb. The MC-l has a cylindrical metal body with an ogival nose and a tapered aft
section to which a fin assembly is attached. The basic structural material of the
bomb is steel. The bomb body is filled with 24 gallons (220 pounds) of chemical
agent. The filler tube is permanently welded shut at the time filling is
accomplished. The bomb is designed for use with both a nose fuze and a tail fuze.
A hollow burster tube runs through the center of the bomb and connects the nose and
tail cavities. Fuze wells are installed at both ends of the tube to accommodate
nose and tail fuzes. Prior to loading, an M32 burster charge containing an explo
sive is installed in the tube.
Other components used are arming wires and adapter-boosters. The arming wires are
threaded through safety devices in the fuze, thus maintaining the fuze in a safe
(unarmed) condition until release. The adapter-boosters serve to accommodate the
fuze bodies and to contain a booster charge which ensures proper operation of the
burster charge. The MC-l gas bomb uses mechanical fuzes (nose and tail) in the same
manner as GP bombs do. When the bomb impacts, the fuzes function, causing the
1-57
T.O. 1-1M-34
EVENT MARKERS
_____________ _____ ___________________
EVENTS
A B C D E
MODE SLEW LAUNCH LAUNCH (SEEKER ANGLE

ALIGN TRACK EXCEEDING LIMIT)
CONTRAST WHITE ON BLACK BLACK ON WHITE AUTO BLACK ON WHITE BLACK ON WHITE
MARKER LENGTH VALUE PASS LENGTH VALUE PASS LENGTH VALUE PASS LENGTH VALUE PASS LENGTH VALUE PASS
PASS 1 L 1 S 0 L 1 S 0 L 1
2 S 0 L 2 L 2 L 2 S 0
4 S 0 1 S 0 2 S 0 3 S 0 10 L 4 21
8 s 0 s 0 s 0 L 8 S 0
16 s 0 s 0 s 0 S 0 L 16
NOTE; LONG (L) OR SHORT (S).

LONG MARKERS ARE ASSIGNED THE CORRESPONDING NUMERICAL VALUE, SHORT MARKERS ARE ALWAYS ZERO VALUE.
THE PASS NUMBER IS DETERMINED BY SUMMING THE VALUES OF ALL FIVE PASS MARKERS.
FIGURE 1-32
1-58
T.O. 1-1M-34
AGM-45_________
MISSILE ___
TAIL FIN
ASSEMBLY
WING
ASSEMBLY
WARHEAD
SECTION
ROCKET MOTOR
SECTION
(TYPICAL)
CONTROL
SECTION
GUIDANCE
SECTION
CHARACTERISTICS
WEIGHT__ 395 LB
LENGTH — 10 FT
DIAMETER. 8 IN.
WINGSPAN. 3 FT
FIGURE 1-33
burster to detonate. The detonation of the burster ruptures the bomb body and
disperses the chemical agent, forming tiny droplets of liquid which quickly evap
orate to a gas.
The MAU-103 fins used on the MC-1 gas bomb are conical, LD assemblies consisting of
an elongated cone and four identical streamlined fins assembled perpendicular to the
cone. All fin assemblies used on the MC-1 gas bombs will accept the ATU-35 series
drive.
BLU-27 FIRE BOMBS

The BLU-27 series fire bombs (FIGURE 1-35) are incendiary munitions that are factory
loaded with Napalm B incendigel mix, a slightly toxic, highly viscous fluid. The
BLU-27 fire bombs are designed to break on impact, dispersing the burning napalm
against such targets as dug-in troops, parked aircraft, supply installations, com
bustible materials, and land convoys.
The base structure of the bomb body is aluminum, with a reinforced area along the
top center section to provide for suspension, sway-bracing, and forced ejection from
1-59
T.O. 1-1M-34
WEIGHT 725 LB
LENGTH 7 FT 6 IN.
DIAMETER 16 IN.
FIN SPAN
MAU-103/B 19 IN.
MAU-103A/B 22 IN.
FIGURE 1-34
the aircraft. The ends are cone-shaped with a filler hole and cap in the forward
end. On the aft end, a tail end cap or a fin assembly may be used. The fin
assembly is either the MXU-469/B or MXU-393/B, which are interchangeable and produce
the same trajectory.
The BLU-27 series fire bomb is fuzed with the FMU-7 series fuze. This consists of an
FMU-7 impact detonating fuze installed in an AN-M23A1 igniter in both the fore and
aft bulkhead receptacles. They are connected via internally routed electrical
cables to an FMU-7 thermal battery initiator installed in the initiator well between
the two suspension lugs.
The white phosphorus in the igniter liquifies

at 111 °F and may leak through filter plug if
exposed to high temperature. Leaking ignit
ers can be determined by the presence of
smoke and/or flame or by the presence of
white material on the igniter. If any of
these conditions are observed, notify EOD
personnel immediately.
1-60
T.O. 1—1M—34
MXU-393/B
ARMING WIRE ARMING WIRE
CHARACTERISTICS
WEIGHT __ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 870 LB (UNFINNED)

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 10 FT 10 IN. (UNFINNED)
01 AM ETE R_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 19 IN. (UNFINNED)
FIN WEIGHT,_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 15 LB
FIN LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 17 IN.
FIN DIAMETER ._ _ _ _ _ _ _ _ _ _ 24 IN.
SUSPENSION LUG DISTANCE 14 IN.
FUZE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ FMU-7 SERIES
FIGURE 1-35
1-61
T.O. 1—1M—34
The AN-M23A1 igniter is issued separately from the BLU-27B/B. The igniter body is
in the form of a short cylinder rounded at one end with an internally threaded fuze
well on the rounded end. The other end of the igniter is flat and threaded exter
nally for installation in the BLU-27B/B. The flat end also contains a filler plug,
which is used during manufacture. The igniter is installed in the BLU-27B/B after
it is loaded on the aircraft. The igniter contains 1.20 pounds of white phosphorus,
which is initiated by the fuze detonation and which in turn, ignites the bomb
filler .
Do not fly through fire bomb smoke within 20

seconds of burst, as a compressor stall or
flameout may occur .
Operation of the arming sequence starts when the weapon is released and the arming
lanyard is extracted from the initiator. This permits a firing pin to fire a ther
mal battery contained in the initiator and to electrically arm the fuze. Upon
impact, the tank ruptures and the fuze(s) function, bursting the igniter, which con
tains white phosphorous. The white phosphorus causes immediate ignition of the
splattered fuel from the ruptured tank.
The BLU-27/B, A/B, B/B, and C/B are similar in design and construction. The only
external differences are A/B has a 3-inch red band painted on each end, B/B has
larger external arming wire guides, and C/B has threaded suspension lugs.
BLU-52 CHEMICAL BOMB

The BLU-52/B and BLU-52A/B chemical bombs (FIGURE 1-36) are tanks (BLU-1C/B) filled
with an incapacitating agent. The bomb body consists of nose, center, and tail sec
tions. Reinforced areas along the top of the center section provide for suspension
sway-bracing, and forced ejection from the aircraft. The tanks are designed to
break upon impact, dispersing the agent.
The nose section is fitted with an aerodynamic fairing, and the tail section with an
MXU-393/B or MXU-469/B fin. The BLU-52/B is filled with CS-1 chemical agent, and
the BLU-52A/B is filled with CS-2 chemical agent. Both CS-1 and CS-2 are white
micropulverized powders that are highly irritating to the eyes, skin, and respira
tory system.
1-62
T.O. 1—1M—34
BLU-52 CHEMICAL BOMB MXU-393/B

MXU-469/B
SUSPENSION LUGS
END CAP
CHARACTERISTICS
WEIGHT.____________ 350 LB
LENGTH 12 FT 4 IN.
DIAMETER 19 IN.
FIN ASSEMBLY_ _ _ _ _ _ _ 2_ _ _ _ _ _ MXU-393/B OR
MXU-469/B
FIGURE 1-36
WARNING
In case of a suspected leak or emergency

involving the bomb, immediately evacuate to
an upwind area. Notify appropriate EOD per
sonnel immediately.
Approximately 250 pounds of chemical agent are used. The total weight of the bomb
may vary with packing density and/or degree of humidity. This bomb does not use a
fuze or initiator.
M129E1 AND E2 LEAFLET BOMBS AND MJU-1 CHAFF BOMB

The M129E1 and E2 (FIGURE 1-37) are leaflet bombs designed for use in delivery and
distribution of leaflet type material. When these bomb bodies are filled with
chaff, they are called MJU-1 chaff bombs. The bomb has a cylindrical body with an
ogival nose and a tapered aft section. It is constructed of fiberglass and has an
external configuration similar to the M117 GP bomb. The bomb body is split longitu
dinally into two sections which are held together by four latches on each side. A
steel reinforcing plate below the suspension lugs is added for forced ejection from
1-63
T.O. 1-1M-34
M129E1 AND E2 LEAFLET BOMBS AND MJU-1 CHAFF BOMB
CHARACTERISTICS
WEIGHT, EMPTY 92 LB
WEIGHT, FULL 203 LB (DEPENDS ON
WEIGHT OF PAPER)
LENGTH 7 FT 6 IN.
DIAMETER 16 IN.
FIN SPAN 22 IN.
FIN ASSEMBLY._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ M148
FIGURE 1-37
the aircraft. The fuze well, which is located in the nose of the bomb body, will
accommodate a mechanical time fuze designed for airburst operation. Tail fuzes are
not used or provided for in the M129E1, E2 bombs. The fin (M148) consists of an
elongated fiberglass cone about 20 inches long and four streamlined blades assembled
perpendicular to the cone.
Other components include an arming wire, an adapter-booster assembly, and a deto

nating cord (PRIMACORD). The arming wire is threaded through the fuze safety
device, thus keeping the fuze in a safe condition until release. The adapter
booster accommodates the fuze and retains the detonating cord in the proper
position. The detonating cord is used to effect separation of the two bomb body
sections .
Operation of the bomb occurs at a predetermined number of seconds after release.

Functioning of the fuze causes the booster to ignite and detonate the 12-foot-long
detonating cord. The detonating cord is inserted through the adapter-booster and
longitudinally around the entire bomb. Detonation of the detonating cord separates
the two body sections, detaches the fins, and allows the leaflets to be released and
scattered. If the nose fuze fails to function, the bomb will disintegrate upon
impact.
1-64
T.O. 1- 1M-34
CLUSTER BOMBS AND DISPENSERS

Cluster bombs (FIGURE 1-38) are dispensers loaded with submunitions and may remain
attached to the aircraft or released as a free-fall unit. Dispensers that remain
attached to the aircraft dispense the submunition by ejection to the rear or by
ejection through the bottom of the dispenser. Dispensers that are released as free
fall units are designed as clamshells with either two longitudinal sections (SUU-30)
or three longitudinal sections (SUU-64/65) (See FIGURE 1-38.). The clamshells blow
apart at a predetermined time after release, or at a given altitude, and the sub
munitions inside are released. The submunitions (FIGURE 1-39) are bomblets or mines
designed for use against such targets as light material, personnel, or armor.
SUU-13 DISPENSERS
SUU-13/A
The SUU-13/A dispenser (FIGURE 1-40) is an externally mounted pod containing a
40-tube assembly that dispenses downward various types of submunitions. The
dispenser is a rectangular shape with a curved hardback section. Some models of the
SUU-13/A have aerodynamic aft fairings and some models have a flat (bobtail) aft
fairing. A removable pallet is attached by internal wrenching bolts to the bottom
of the dispenser to prevent inadvertent release of the payload and to protect the
dispenser. The pallet is removed prior to flight. On the SUU-13B/A and C/A
dispensers, the intervalometer safety pin must be removed prior to removal of the
pallet and replaced after the removal. Each of the tubes contains devices for
retaining the bombs in the dispenser and a cartridge assembly used to eject them.
The weapon release system supplies power to fire an electrically primed cartridge of
one tube assembly and activates a stepping mechanism controlled by the inter
valometer as set prior to flight. The available intervalometer settings are 0.1,
0.2, 0.3, 0.4, and 0.5 second. The release signal must be continuously applied to
the SUU-13/A timing circuit for a time duration (3.9 to 19.5 seconds) which may be
determined by multiplying the selected intervalometer setting by bomb releases (n)
minus one (39). For example, n-l(39) x 0.2 (intervalometer setting) = 7.8 seconds.
SUU-13A/A
The SUU-13A/A dispenser differs from the SUU-13/A dispenser in the following
respects: the SUU-13A/A removable pallet is attached with quick-release fasteners
in lieu of internal wrenching bolts and the intervalometer settings are 0.05, 0.1,
0.2, 0.3, and 0.4 second. The SUU-13A/A has flat (bobtail) aft fairings.
SUU-13B/A
The SUU-13B/A dispenser differs from the SUU-13A/A dispenser in the following
respect: the intervalometer safety pin must be removed prior to the removal of the
pallet and replaced after its removal. The dispenser has been modified to accept
this new safety pallet.
SUU-13C/A
The SUU-13C/A dispenser differs from the SUU-13B/A in the following respect: the
intervalometer settings for the SUU-13C/A are 0.025, 0.05, 0.1, 0.2, and 0.3 second.
1-65
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T.O. 1-1M-34
CLUSTER BOMB CHART

APPROXIMATE TOTAL
MUNITION DISPENSER SUBMUNITION NUMBER OF WEIGHT
BOMBLETS (LB)
CBU-30/A SUU-13/A BLU-39/B23 1280 385

CBU-38/A SUU-13 A/A BLU-49/B 40 820
CBU-38A/A SUU-13B/A BLU-49A/B 40 822
CBU-38B/A SUU-13C/A BLU-49A/B 40 806

CBU-38C/A SUU-13C/A BLU-49B/B 40 806
CBU-24B/B SUU-30B/B BLU-26/B 665 832
CBU-49B/B SUU-30B/B BLU-59/B 665 832

CBU-52B/B SUU-30H/B BLU-61A/B 217 785
CBU-58/B SUU-30H/B BLU-63/B 650 810
CBU-58A/B SUU-30H/B BLU -6 3 A/ B 650 820

CBU-71/B SUU-30H/B BLU-86/B 650 810
CBU-71A/B SUU-3OH/B BLU-86 A/B 650 820
MK 20 (ROCKEYE) MK 7 MK 118 247 500

BL-755 BL-755 BL-755 147 600
CBU-87 SUU-64 BLU-97/B 202 950
CBU-89 (GATOR) SUU-6 5 BLU-91/B 72 680
BLU-92/B 22
FIGURE 1-39
CBU-30/A CLUSTER BOMB AND BLU-39/B23 CS BOMBLET

The CBU-30 cluster bomb comprises the SUU-13/A dispenser with the 40 vertical tubes
loaded with CDU-12/B bomb cluster canisters(FIGURE 1-41).Each bomb cluster canister
contains 32 BLU-39/B23 antipersonnel chemical bomblets.
The canister is retained in the dispenser tube by four screws, which are sheared
when the canister is ejected by the tube impulse ejection cartridge. The downward
ejection velocity of the canister from the dispenser is approximately 90 fps.
FIGURE 1-40 depicts a typical SUU-13/A tube assembly with a CDU-12/B canister
installed. Each canister contains a delay assembly and an expulsion tube. When the
tube assembly cartridge is fired, the hot gases created are vented to the canister
delay assembly while creating sufficient pressure on the canister to shear the
tube’s four canister retaining screws. After 0.3 to 0.5 second, the delay assembly
ignites black powder contained in the canister expulsion tube and ignites the fuze
igniter of each BLU-39 bomblet. The burning black powder in the canister expulsion
tube forces the bomblets through the thin fiberglass walls of the canister. The
bomblet will start to dispense CS smoke 5 to 6 seconds after it is released from the
bomb package. The CS will be dispensed from each bomblet for approximately 10 to 15
seconds causing the bomblet, after impact on a cleared surface, to skitter about
due to the violent expulsion of the CS from an orifice in the end of the bomblet.
1-67
T.O. 1—1M--34
SUU-13 DISPENSERS
SAFETY
PALLET
INTERVALOMETER ITEM CBU-30/A CBU-38/A CBU-38A/A CBU-38B/A CBU-38C/A

SAFETY PIN
SECONDS DISPENSER SUU-13/A SUU-13A/A SUU-13B/A SUU-13C/A SUU-13C/A
WEIGHT 385 LB 820 LB 822 LB 806 LB 806 LB
^INTERVALOMETER BOMBLET BLU-39/B23 BLU-49/B BLU-49A/B BLU-49A/B BLU-49B/B
SAFING SCREW
SUU-13 DISPENSER CHECK

TUBE NUMBER
DESIGNATION
(TYPICAL)
TUBE FIRING
ORDER (TYPICAL)
BOTTOM VIEW
CHARACTERISTICS
EMPTY WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 157 LB

WIDTH/HEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 15 X 14 IN.
LENGTH W/REAR FAIRING 8 FT 5 IN.
LENGTH W/O REAR FAIRING 7 FT 9 IN.
LENGTH W/BOBTAIL FAIRING 7 FT 6 IN.
NUMBER OF TUBES 40
FIGURE 1-40
1-68
T.O. 1—1M—34
NOTE
The bomblet will start to dispense CS smoke 5

to 6 seconds after release. Release con
ditions that provide a time of flight of less
than 6 seconds should be selected.
CBU-38 CLUSTER BOMB

The CBU-38 cluster bomb is made up of the SUU-13 dispenser and BLU-49 series
bomblets (FIGURE 1-42). A single BLU-49 antimaterial high-explosive (HE) bomblet
(FIGURE 1-43) is carried in each of the SUU-13A/A dispenser’s 40 ejection tubes to
make up the CBU-38/A. The bomblets are ejected downward from the dispenser at
approximately 62 fps. Ejection forces imparted by the dispenser tube ejection
cartridges shear six pins which hold the bomblet in the tube.
If all submunitions cannot be confirmed

dispensed, the SUU-13 should be jettisoned
prior to landing the aircraft to prevent
aircraft/runway damage caused by hung sub
munitions which may fall out on landing.
NOTE
Release conditions must be selected which

provide a BLU-49A/B or BLU-49B/B bomblet a
time of flight greater than 3.5 seconds to
assure adequate time for the fuze to arm
prior to impact. A minimum dispensing
airspeed of 400 KTAS is recommended for the
CBU-38A/A, CBU-38B/A, or CBU-38C/A to ensure
safe delivery at minimum altitudes.
BLU-49/B BOMBLET
As the bomblet emerges from the tube, three wind tabs within the bomblet tail
assembly force the stabilizer ringtail into the extended position. Extension of the
ringtail actuates the fuze system. The bomblet is armed in 5.5±1 seconds and deto
nates on impact.
1-69
T.O. 1—1M—34
CDU-12/B CANISTER
EJECTION CARTRIDGE
SLEEVE
ASSEMBLY BLU-39/B23 CS BOMBLET
GASKET
PUSHER PLATE
ASSEMBLY FUZE
BLU-39/823 IGNITER
BOMB
DELAY
ASSEMBLY DELAY
EXPULSION FUZE
TUBE
SHELL
ASSEMBLY
IGNITION
COMPOUND
TUBE PYROTECHNIC AND

ASSEMBLY CS MIXTURE
SHEER SCREW (4)
COVER PLATE
CHARACTERISTICS
CDU-12/B BLU-39/B23 CS
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 10 LB _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 0.13 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ WIN. _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ 5 IN. _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1 IN.
FIGURE 1-41
CBU-38 SERIES MUNITIONS CONFIG-

URATION AND WEIGHT CHART
MUNITION DISPENSER BOMBLET WEIGHT (LB)
CBU-38/A SUU-13A/A BLU-49/B 820

CBU-38A/A SUU-13B/A BLU-49A/B 822
CBU-38B/A SUU-13C/A BLU-49A/B 806

CBU-38C/A SUU-13C/A BLU-49B/B 806
FIGURE 1-42
1-70
T.O. 1-1M-34
CARTRIDGE
ASSEMBLY
CYLINDER ASSEMBLY BLU-49

W/1 HE BLU-49 BOMBLET
FRAGMENTATION
lot l 2 'J 2J Lj BOMBLET
date :: „ 3 - 2 3; 3
CYLINDER
ASSEMBLY
O-RING
SHEAR RIVET
DOUBLER
CLOSURE
TUBE DISPENSER BLU-49 BOMBLET
CHARACTERISTICS
TUBE DISPENSER BLU-49 BOMBLET
WEIGHT_ _ _ _ _ _ 13 LB WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 13 LB
LENGTH_ _ _ _ _ 10 IN. LENGTH
DIAMETER_ _ _ 5 IN. IN CANISTER_ _ _ _ _ _ _ _ _ _ _ 10 IN.
RINGTAIL EXTENDED_ _ _ _ 14 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 5 IN.
FIGURE 1-43
BLU-49A/B BOMBLET
The single difference between the BLU-49A/B and the BLU-49/B is the fuzing. The
arming time for the BLU-49A/B was reduced to a minimum of 2.25 seconds and a maximum
of 3.50 seconds. The BLU-49A/B has a safety device that prevents the bomblet from
arming when it senses an impact greater than 25 g after the ringtail has been
extended and before the arming time (2.25 to 3.50 seconds) is reached.
If the bomblet must penetrate jungle canopy, the resultant deceleration should not
be sufficient to cause the inertial weights to fire the detonator. The bomblet then
will penetrate and explode following impact with the ground. Upon water or mud
impact (which does not provide sufficient deceleration to fire the detonator by the
action of the inertial weights), another means is provided to fire the detonator.
1-71
T.O. 1—1M—34
Openings in the face of the fuze will allow the fluid media to enter and push a
piston against the firing pin. The firing pin then fires the detonator and ignites
the explosive train.
BLU-49B/B BOMBLET
The BLU-49B/B contains slightly more explosive material (including a small incen
diary component) than the BLU-49A/B and has a slightly longer body. In all other
respects they are the same.
SUU-30 DISPENSERS
SUU-3OB/B DISPENSER
The SUU-30B/B (FIGURE 1-44) is a cylindrical metal dispenser that is divided in half
longitudinally. The upper half contains a strongback section that provides for
forced ejection and sway-bracing. The lugs are mounted on metal rods that extend
through the dispenser and are attached to the lower half. The two halves are locked
together by a nose locking cap at the forward end and by a base plate bolted to the
aft end. The nose locking cap consists of a lanyard tube, four shear pins, cap
coupling, adapter, breech cap, and nose plug. A dual set of external arming wire
guides is positioned along the top half of the dispenser to prevent excess arming
wire vibration and to route the arming wire around the bomb rack ejector foot. Four
cast aluminum fins are attached at 90 degrees to the aft end of the dispenser and
are canted 1.25 degrees to impart spin-stabilized flight. Additionally, a small fin
tab is attached to the outer edge of each fin to provide stability during separation
from the aircraft.
When the dispenser is released from the aircraft, the arming wire/lanyard initiates
the fuze arming and delay cycle. At fuze function the fuze booster is ignited,
blowing the fuze and nose locking cap forward and unlocking the forward end of the
dispenser. Ram air action on the dispenser forces the two halves apart, instan
taneously dispensing the payload and causing the bomblets to spin-arm and self
dispense from the center of the trajectory at the point of release. The result is a
doughnut-shaped void in the center of the pattern. Minimum delivery altitudes for
SUU-30 type CBUs are a function of bomblet arming plus SUU-30 fuzing requirements.
SUU-3OH/B DISPENSER
The SUU-30H/B dispenser fin tabs are located on the trailing edges of the fins and
are called drag plates. In other respects it is the same as the SUU-30B/B dispenser.
CBU-24B/B CLUSTER BOMB

The SUU-30B/B is loaded with 665 BLU-26 bomblets to create the CBU-24B/B. The
BLU-26 bomblet (FIGURE 1-45) is a spin-armed, self-dispensing fragmentation sub
munition that detonates upon impact. When the bomblet is released into the
airstream, the bomblet flutes produce a high rate of spin. Spinning induces disper
sion and initiates arming of the M219 fuze. Weights holding the rotor in the
1-72
T.O. 1—1M—34
SUU-3OB/B, H/B DISPENSERS

. __________________________'______________________ . V (
OUTLET
CLUSTER BOMBLETS TOTAL

BOMB DISPENSER WEIGHT
CBU- SUU- BLU- QUANTITY (LB)
24B/B 26/B 670 822

49B/B 30B/B
59/B
52B/B 61A/B 217 785
58/B 63/B
58A/B 30H/B 63A/B 650 818
71/B 86/B
71A/B 86A/B
CHARACTERISTICS
LENGTH 7 FT 6 IN.
DIAMETER 16 IN.
WEIGHT
(EMPTY)198 LB
(LOADED)735 -832 LB
FIGURE 1-44
1-73
T.O. 1-IM-34
BLU BOMBLET (TYPICAL)

STRAP
TOP HEMISPHERE
FUZE
HIGH EXPLOSIVE CHARGE

STEEL BALLS
ALUMINUM ALLOY MATRIX
LEAD CUP
BLU-63/B, -63A/B,
-86/B, -86A/B
BLU-26/B, -59/B
CHARACTERISTICS
BLU-61A/B BLU-26/B BLU-63/B, -63A/B

BLU-59/B BLU-86/B, -86A/B
DIAMETER_ _ _ _ _ _ _ _ _ _ _ 3.5 IN. _ _ _ _ _ 2.38 IN. __ _ _ _ _ 2.94 IN.

WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ 2.7 LB _ _ _ _ _ 0.93 LB ___ _ _ _ _ 0.93 LB
EXPLOSIVE WEIGHT_ _ __ 0.65 LB _ _ _ _ _ 0.182 LB __ _ _ _ _ 0.25 LB
FIGURE 1-45
1-74
T.O. 1-IM-34
unarmed position are released by the centrifugal force caused by spinning. To arm,
the hammer weights move back, releasing the firing pin from the rotor. The M219
fuze is sensitive to impact from any direction. Impact detonates the HE filler that
bursts the bomblet case and propels steel balls at high velocity (approximately
4,000 fps) in a radial direction.

The SUU-30B/B is loaded with 665 BLU-59/B bomblets to create the CBU-49B/B. The
BLU-59/B differs from the BLU-26/B bomblet used in the CBU-24B/B in that the
BLU--59/B is equipped with an M224 time delay fuze that causes the bomblets to deto
nate randomly after impact (FIGURE 1-45). In all other respects it is identical to
the BLU-26/B bomblet.
M224 RANDOM TIME DELAY FUZE

The M224 is a random time delay, spin-armed fuze that arms between 2,400 and 3,200
rpm. It is used to detonate the BLU-59/B and BLU-86/B, A/B bomblets which fill the
SUU-30B/B and SUU-30H/B, respectively. The fuze firing train consists of a detona
tor, lead charge of pressed RDX, and a spring-actuated firing pin released when the
delay rotor reaches the necessary displacement. This rotor is timed by a variable
viscosity lubricant. The detonator is out-of-line until after arming.

The SUU-30H/B is loaded with 217 BLU-61A/B bomblets to create the CBU-52B/B. The
BLU-61A/B is similar in shape and function to the BLU-26/B bomblet used in the
CBU-24 and uses the same M219 fuze. The BLU-61A/B is approximately 50 percent
larger, however, which produces heavier fragments with improved penetration capabil
ity. Average fragment velocity is 5,000 fps. The case consists of three parts. A
liner made of zirconium tin provides incendiary effects against flammable targets.
A coined steel fragmenting case surrounds the liner, and the outer urethane plastic
case surrounds the steel case. The aerodynamic flutes are molded in the plastic.
CBU-58/B CLUSTER BOMB

The SUU-30H/B is loaded with 650 BLU-63/B bomblets to make the CBU-58/B. The
BLU-63/B is similar in size, shape, and function to the BLU-26/B used in the CBU-24
and uses the same M219 fuze. The average fragment velocity is 4,500 to 4,900 fps.
The main difference between the two submunitions is that the BLU-63/B has a scored
steel fragmenting case that produces 260 fragments as opposed to the steel ball/cast
aluminum case of the BLU-26/B.
CBU-58A/B CLUSTER BOMB

The SUU-30H/B is loaded with 650 BLU-63A/B bomblets to make the CBU-58A/B. The
BLU-63A/B differs from the BLU-63/B bomblet in that the BLU-63A/B contains two
1-75
T.O. 1—1M—34
5-gram titanium pellets. The titanium is an incendiary used for additional capabil
ity against flammable targets. In all other respects it is identical to the
BLU-63/B bomblet.
CBU-71/B CLUSTER BOMB

The SUU-30H/B is loaded with 650 BLU-86/B bomblets to make the CBU-71/B. The
BLU-86/B differs from the BLU-63/B bomblet (FIGURE 1-45) in that the BLU-86/B
incorporates the M224 time delay fuze, which detonates at random times after impact.
In all other respects it is identical to the BLU-63/B.
CBU-71A/B CLUSTER BOMB

The SUU-30H/B is loaded with 650 BLU-86A/B bomblets to make the CBU-71A/B. The
BLU-86A/B differs from the BLU-63A/B incendiary bomblet (FIGURE 1-45) in that the
BLU-86A/B incorporates the M224 time delay fuze, which detonates at random times
after impact. In all other respects it is identical to the BLU-63A/B.
Avoid low altitude overflights of areas where

time delayed munitions have been employed.
SUU-64/B, -65/B TACTICAL MUNITIONS DISPENSERS

The Tactical Munitions Dispenser (TMD) (FIGURE 1-46) is a cluster munitions
dispenser. The TMD is made in two major versions designated the SUU-64/B and
SUU-65/B. The major difference between the two versions is the tail sections. The
SUU-64/B has a nonspin tail section, and the SUU-65/B has a fin cant mechanism to
provide aerodynamic spinning of the dispenser and to enhance submunition dispersion.
SUU-64/B
The components in the SUU-64/B can be grouped into three main assemblies: body,
tail, and nose (FIGURE 1-46).
The body is an aluminum cylinder that is welded to the forward bulkhead. This forms
the main structure to which the remaining components are attached. The strongback
is a single piece of aluminum attached to the inside of the cylinder and provides
the strength and rigidity necessary for suspension and carriage. Two electrical
harnesses are attached to the body: the fuze harness and the body harness. The
fuze harness connects the fuze to the proximity sensor and to the body harness. The
cutting network consists of a manifold and a lead, three longitudinal strands of
1-76
T.O. 1—1M—34
SUU-64/B, -65/B TACTICAL MUNITIONS DISPENSER

TAIL HARNESS
AFT BULKHEAD
SPIN TAIL
ASSEMBLY
TAIL LANYARD
FUZE ARM AND
OPTION LANYARDS
SKIN
TAIL
SECTION
FIN
RELEASE BAND
BODY SECTION FAIRINGS
FINS CANTED 56
FOR SPIN
NOSE
TAIL HARNESS SECTION
FUZE ASSEMBLY PROXIMITY SENSOR (OPTIONAL)
CHARACTERISTICS
SUU-64/B SUU-65/B
WEIGHT
EMPTY _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 195 LB 215 LB
LOADED _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 651 LB 950 LB
LENGTH _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 7 FT8 IN 7 FT8 IN.
DIAMETER _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 16 IN 16 IN.
SUSPENSION LUG SPACING 14 IN 14 IN.
FIGURE 1-46
aluminum linear shaped charges (ALSC), and a circumferential strand of ALSO at the
aft bulkhead. Its function is to cut the dispenser body into three longitudinal
pieces and separate the tail section. The aft bulkhead provides the primary struc
tural support for the aft end of the body and acts as a seal for the cargo section.
The lanyard system consists of three lanyards in two aluminum conduits and three
lanyard extractors. The lanyard system is used to release the fins, initiate fuze
arming, and select the fuze mode. The forward conduit carries the fuze arming and
the fuze option lanyards, and the rear conduit carries the fin release lanyard.
Each lanyard is tied off at one end and connected to its particular function at the
other end. The use of lanyard extractors with break links allows the lanyards to be
retained by the dispenser after release.
1-77
T.O. 1—1M—34
The extractor has two break links. The lower break link is attached to the conduit
and will break with a pull of 54 to 79 pounds. It is used to assure that the
extractor will be pulled free of the solenoid jaws without pulling the lanyard when
the arming solenoid is not energized. The upper break link breaks under a pull of
108 to 140 pounds. When the dispenser is released with the arming solenoid
energized, the extractor becomes taut and breaks the lower break link. This allows
the extractor to pull the lanyard until it engages its stop and the upper link
breaks. The lanyard and extractor remain with the dispenser, and only the loop
remains attached to the ejector rack. Fuze option is determined by the arming sole
noid selection. The tail solenoid is used to pull the fuze arming lanyard, and the
nose solenoid is used to pull the fuze option lanyard. The fin release, lanyard is
tied off on the ejector rack sway brace and is always pulled regardless of arming
solenoid selection.
The tail section is attached to the aft bulkhead and has four extendable fins which
are held in the retracted position by a fin release band. When the fin release
lanyard is pulled, the fins are extended in unison by four pairs of springs and a
gang pulley assembly. The fins are then locked in the extended position.
The nose section is attached to the forward bulkhead and consists of two fairing
sections which form the aerodynamic profile of the nose, an optional proximity sen
sor, and a fuze.
SUU-65/B
The SUU-65/B is a SUU-64/B with a modified tail section that imparts spin to the
dispenser.
The spin tail differs from the nonspin tail in that it contains a fin cant mechanism
and an explosive bolt and tail harness. The tail harness connects the body harness
to the explosive bolt assembly. When the spin mode is selected, a signal is sent
from the fuze through the body harness which detonates the explosive bolt. This
allows the spring-loaded fin cant mechanism to rotate the fins to the fully canted
position.
CBU-87 CLUSTER BOMB (COMBINED EFFECTS MUNITIONS)

The Combined Effects Munition (CEM) is a SUU-65/B containing BLU-97/B (FIGURE 1-47)
bomblets. The BLU-97/B case is made of scored steel designed to fragment into
approximately 300 preformed 30-grain fragments for defeating light armor and person
nel. It contains a forward-firing, shaped-charge liner for defeating armor, and a
zirconium ring for incendiary capability. An Air Inflatable Decelerator (AID) that
provides drag, orientation, and flight stability for the bomblet is held encased by
a cap called a spyder.
When the BLU-97/B is released into the airstream from the SUU-65 dispenser and
attains a minimum airspeed of 175 KCAS or greater, the airflow releases the cap
which pulls the cup assembly rearward, exposing the AID to the airstream. As the
AID is inflated by ram air, it orients and stabilizes the BLU-97/B for proper target
impact by despinning the submunition and reducing the descent rate to approximately
125 fps. The AID transmits the air-induced loads to a shaft in the fuze which arms
1-78
T.O. 1—1M—34
BLU-97/B BOMBLET
CHARACTERISTICS
DIAMETER 2 IN.
WEIGHT, TOTAL 3 LB
EXPLOSIVE CYCLOTOL
WEIGHT 0.65 LB
LENGTH
STOWED -------------------- 7 IN-
DEPLOYED-_ _ _ _ _ _ _ _ _ 10 IN.
FIGURE 1-47
the submunition. Release of the cap also allows a standoff tube to deploy forward.
When the BLU-97/B impacts the target, the standoff tube is driven rearward to deto
nate the submunition. In the event the BLU-97/B impacts the target other than
straight on, a secondary firing system will detonate the submunition.
1-79
T.O. 1-1M-34
CBU-89 CLUSTER BOMB (GATOR)

The CBU-89 is made up of a SUU-64/B dispenser containing BLU-91/B and BLU-92/B sub
munitions (FIGURE 1-48). The BLU-91/B antitank mine is a delayed-action, target
sensing submunition. The BLU-91/B consists of a safe and arming device, a clearing
charge, a bidirectional shaped-charge warhead, a magnetic sensor, and electronic
components. All components are contained in a compact plastic aeroballistic shape
adapter. Mine arming begins when the SUU-64 dispenser opens and is completed
shortly after ground impact. Self-contained batteries keep the BLU-91/B armed until
detonation. Detonation occurs when the magnetic sensor detects a target or the mine
is disturbed. If no target is detected before the preset self-destruct time is
reached, the mine detonates at the expiration of the preset time period. If the
battery voltage drops below a specified level, the mine will detonate. The BLU-91/B
is effective against tanks and armored vehicles.
CHARACTERISTICS
BLU-91/B BLU-92/B
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 LB_ _ _ _ _ _ 4 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 6 IN_ _ _ _ _ _ 6 IN.
WIDTH __ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 5 IN,_ _ _ _ _ 5 IN.
HEIGHT...... ............... __ _ _ _ _ _ _ 3 IN__ _ __ 3 IN.
EXPLOSIVE_ _ _ _ _ _ _ _ _ _ _ _ _ _ RDX_ _ _ _ COMP B
WEIGHT._ _ _ _ _ _ _ _ _ _ __ _ _ _ _ _ 1.3 LB_ _ _ _ 0.905 LB
FIGURE 1-48
1-80
T.O. 1—1M—34
The BLU-92/B antipersonnel mine closely resembles the BLU-91/B in appearance and
function. The BLU-92/B bursts on the ground; its fragmenting case warhead is
triggered by tripwires. The BLU-92/B contains eight tripwires and tripwire sensors,
four, per face. Maximum tripwire deployment length is 40 feet. The four upward-
facing tripwires deploy at mine arming. Mine arming is otherwise similar to the
BLU-91/B arming process. Detonation occurs when a target actuates the tripwires or
when the mine is disturbed. BLU-92/B self-destruct processes are the same as for
the BLU-91/B.
MK 20 MOD 2,3, AND 4 (ROCKEYE II) CLUSTER BOMB

The MK 20 Rockeye (FIGURE 1-49) is an antiarmor cluster bomb consisting of the MK 7
clamshell dispenser, MK 339 mechanical fuze, and MK 118 bomblets. The weapon is
produced, delivered, and loaded as a complete unit.
MK 7 MOD 2 DISPENSER
The MK 7 Mod 2 bomb dispenser consists of a nose fairing, cargo section, and tail
section. The nose fairing contains an upper and lower nose fairing assembly, and
houses the MK 339 mechanical time fuze. The upper nose* fairing has two observation
windows. One is for viewing the safe/arm indicator and the other is to view the
fuze time setting dials. Two access holes are provided in the lower fairing for
changing fuze time settings. During ground handling, a fuze cover is installed over
the fuze impeller and fuze safety pin.
The cargo section is made of aluminum. It is thick at the top for suspension pur
poses, but thins to 0.125 inch for the cargo walls. It houses 247 MK 118 antitank
bomblets which are secured and protected by plastic spacers. A linear charge is
secured to both inner walls of the cargo section. This charge is used to cut the
dispenser in half longitudinally when the MK 339 fuze functions after release. This
allows the MK 118 bomblets to spread in a free-fall trajectory.
The tail section consists of a conical body equipped with four foldable spring-
loaded fins. Until release, these fins are held in the folded position by a fin
release band which, in turn, is held closed by a fin release wire, and a fin safety
pin. Two conduits are provided along the top of the dispenser, one for the fin
release wire, which is tied off to a rear sway brace, when loaded, and one for the
MK 339 arming wire.
NOTE
In the MK 20 Mod 2 bomb cluster, the MK 339

option wire is removed and the option pin is
extended. The consequences are that the
option time will be utilized. To avoid con
fusion when employing MK 20 Mod 2 put both
primary and option timer on the same setting.
1-81
T.O. 1—1M—34
MK 20 MOD 2,3, AND 4 (ROCKEYE II) CLUSTER BOMB
TAILCONE
ASSEMBLY
SAFETY PIN
(WITH STREAMER) —
FIN RELEASE
BAND
EXTRACTOR
SUSPENSION LUG
FUZE MK 6 MOD 0
ARMINGWIRE OR MS3314
(IN CONDUIT) FIN RELEASE
EXTRACTOR
FIN RELEASE WIRE

(IN CONDUIT)
— MECHANICAL TIME FUZE

MK 339 MOD 0
FUZE COVER
ASSEMBLY
MK 20 MOD 2 CLUSTER BOMB
PILOT OPTION
EXTRACTOR
FUZE ARMING
WIRE EXTRACTOR
FUZE ARMING
WIRE AND PILOT OPTION
WIRE (IN CONDUIT)
— FIN RELEASE
EXTRACTOR
FUZE
OBSERVATION
WINDOW
MK 7 MOD 3 BOMB DISPENSER
NOTE
BROKEN LINES (—) APPLY TO
— FUZE SETTING MK 7 MOD 4 DISPENSER
OBSERVATION WINDOW
MK 20 MOD 3 AND MOD 4 CLUSTER BOMB
CHARACTERISTICS
WEIGHT 500 LB.

LENGTH 7 FT 6 IN.
DIAMETER 13 IN.
FIN SPAN
CLOSED 17 IN.
OPEN 35 IN.
FIGURE 1-49
1-82
T.O. 1—1M—34
MK 7 MOD 3 DISPENSER (MK 20 MOD 3)

The MK 7 Mod 3 dispenser differs from the MK 7 Mod 2 dispenser in that on the Mod 3
a pilot option wire is added to allow the pilot to select, while airborne, either of
the two fuze function times set on the MK 339 fuze. The conduit for the fuze wire
is modified to allow routing of the pilot option wire to the tail solenoid.
MK 7 MOD 4 DISPENSER (MK 20 MOD 4)

The MK 7 Mod 4 dispenser differs from the MK 7 Mod 3 dispenser in that the Mod 4
dispenser section has two additional threaded lug wells to permit the center of
balance to be shifted forward by repositioning the suspension lugs. In addition,
the MK 7 Mod 4 contains the MK 118 Mod 1 which arms in 0.5 second. The fin release
wire and conduit are lengthened to permit attachment of fin release extractors in
two additional places.
MK 339 MECHANICAL TIME FUZE

A discussion of the MK 339 mechanical time fuze used with the MK 7, Mod 2, Mod 3, and
Mod 4 dispensers can be found in Section II, Nonnuclear Weapons Fuzes.
MK 118 MOD 0 BOMBLET

MK 118 MOD 0 antitank bomblet (FIGURE 1-50) is used in the MK 20 Mod 2 and Mod 3
Rockeye. The bomblet consists of three fixed plastic stabilizing fins, the body,
and a fuzing system. The body consists of a strong alloy outer shell and standoff
probe, a 0.4 pound explosive shaped-charge of Octal, and a shaped-charge copper
liner. The fuzing system consists of a piezoelectric nose assembly, a base fuze
assembly, and an arming vane. Upon separation from the MK 7 dispenser, rotation of
the arming vane initiates the arming cycle. The bomblet requires at least 200 knots
to arm. It takes a total of 1.2 seconds to fully arm. Fuze detonation is initited
by either of two methods. Upon impact with a hard target, an electrical charge is
extracted from the piezoelectric nose crystal and transferred through wiring to set
off an electric detonation in the base fuze. Upon impact with soft targets, the
base fuze firing pin fires a stab detonator, which fires the electric detonator.
The explosive charge functions the same whether initiated by the nose element or the
base element. The shock waves of detonation within the shaped charge produce a
high-velocity gas jet and collapse the copper liner into a slug. When the gas jet
strikes the target, pressures up to 250,000 psi are focused at the point of impact,
allowing penetration of approximately 7.5 inches of armor. Little lateral blast or
temperature effects are produced by the shaped charge; however, fragmentation
effects from the outer shell are appreciable.
MK 118 MOD 1 BOMBLET

The MK 118 Mod 1 bomblet differs from the MK 118 Mod 0 in that the MK 118 Mod 1
total arming time is reduced to 0.5 second. It is used in the MK 20 Mod 4 Rockeye.
In all other respects both bomblets are identical.
1-83
T.O. 1—1M—34
MK__20 ROCKEYE II, MK 118 BOMBLET

__
MK 118 BOMBLET
FIN
EXPLOSIVE
MK20 COMPONENTS ARMING
NO. OF DRAG SURFACES VANE
MK 20 MK7 MK 339 MK 118
MOD DISPENSER FUZE BOMBLET BOMBLETS
BASE FUZE
2 MOD 2 MOD 0 MOD 0 247 ASSEMBLY
3 MOD 3 MOD 0 OR 1 MOD 0 247
4 M0D4 MOD 1 MOD 1 247
SHAPED CHARGE
LINER
PIEZOELECTRIC NOSE ELECTRICAL LEADS

ASSEMBLY FROM NOSETO FUZE
(NOT INCLUDED IN LATER PRODUCTIONS)
CHARACTERISTICS
LENGTH 13 IN.
DIAMETER 2 IN.
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1 LB
FIGURE 1-50
NOTE
In current MK 118 Mod 0 and Mod 1 bomblets,

the piezoelectric nose assembly has been
removed and the bomb relies on the base ele
ment for detonation, for both hard and soft
targets.
MK 20 ROCKEYE DELIVERY CONSIDERATIONS

Arming time for the total munition depends on the MK 339 fuze function time and the
bomblet arming time. Minimum TOF is based on the MK 339 1.2 ±0.1 seconds setting as
depicted in FIGURE 1-51.
1-84
T.O. 1—1M—34
DELIVERY CONSIDERATIONS
MK 20 MK 20
MOD 2 and 3 MOD 4
DISPENSER (MK 339) 1.1 to 1.3 1.1 to 1.3

Seconds Seconds
BOMBLET (MK 118) 1.2 Seconds 0.5 Second
TOTAL ARM TIME 2.3 to 2.5 1.6 to 1.8

Seconds Seconds
FIGURE 1-51
caution
When the MK 20 Mod 4 is released, the

aircraft may not be clear of the submunition
fragment envelope at submunition fuze arming.
Refer to appropriate safe separation data.
The MK 20 Rockeye is more efficiently used against area targets that require
penetration to kill, although it can be employed against soft targets. Its proba
bility of kill against any target is driven by impact angle and bomblet density.
The recommended method to increase bomblet density is to make a multiple release.
Bomblet impact patterns have no doughnut effect, and the bomblets are generally
evenly spaced throughout an elipse. These can be varied by dive angle, airspeed,
and height of burst (HOB) (release altitude and fuze function time).
BL-755 CLUSTER BOMB AND BL-755 BOMBLET

The BL-755 cluster bomb (FIGURE 1-52) has not received safety certification by the
USAF Nonnuclear Munitions Safety Board (NNMSB). The munition is certified only for
the contingency rearming of USAF aircraft at allied bases with BL-755 munitions from
their inventories. The electrical detent, a primary safety feature, must be negated
before flight. The remaining safety features, which prevent dispenser functioning
and submunition dispersal while carried on the aircraft, do not meet USAF design
safety criteria.
The BL-755 is a British munition (similar to the MK 20 Rockeye) composed of a bomb

body, a nose fairing, and a tail unit. The bomb cluster contains 147 armor-piercing
bomblets. The nose fairing contains the safety, arming, and functioning unit
(SAFU), which is a factory installed impeller driven mechanical nose fuze. A
minimum airspeed of 270 knots must be sensed for proper operation of the arming
1-85
T.O. 1-1M-34
TAIL FIN TAIL UNIT EXTENDABLE

ARMING
LANYARD FINS
WIRE/LANYARD -
ASSEMBLY
SPRING
ELECTRICAL MOTOR
LEAD HARDBACK SUSpENS|0N LANYARD
(REMOVED) LUGS
TOP
SKIN
NOSECONE
ARMING
IMPELLER FIN
SAFETY PIN
FORWARD AND
SPRING MOTOR_ _ /
AFT SHEAR
SAFETY PIN
WIRE GUIDES
FUZE BOTTOM
SAFETY
SKIN
PIN
DISPENSER
CHARACTERISTICS
WEIGHT (LOADED)_ _ _ _ _ _ _ _ 600 LB (APPROX)

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 8 FT
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ 16 IN.
BOMBLET COMPRESSED FIN SPAN (OPEN)_ _ _ _ _ _ _ _ _ 28 IN.
(CLOSED)_ _ _ _ _ _ _ 22 IN.
SUSPENSION LUG DISTANCE 14 IN.
BOMBLET EXTENDED
PROBE
ASSEMBLY
BOMBLET
CHARACTERISTICS BODY SECTION
ARMING TAIL
LENGTH (COMPRESSED)_ _ _ _ _ _ _ _ _ _ _ _ 6 IN. UNIT ASSEMBLY
(EXTENDED)_ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 IN
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3 IN.
WEI G HT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 16 LB
NUMBER OF BOMBLETS
PER CLUSTER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 147
NOMINALARMING TIME 0.7 SEC
FIGURE 1-52
1-86
T.O. 1-1M-34
vane. The bomb body consists of two main bulkheads spanned by a suspension beam
(hardback) and enclosed by an upper and lower skin that houses the armor-piercing
bomblets. The tail unit consists of four spring-loaded extendable fins. Two arming
wires/lanyards are used, one for the SAFU and one for the tail unit. Both lanyards
are equipped with shear links. The arming wire/lanyard for the tail unit is secured
to the bomb rack sway brace so that the fins will extend under any condition for
safe separation of the bomb from the aircraft. The arming wire/lanyard for the SAFU
and time delay unit is installed in the bomb rack tail arming solenoid. At bomb
release, the tail fins extend, the lockpin is removed from the arming impeller and
the time delay starts. At a preset time, the primary cartridge fires to blow off
the thin upper and lower skins. Then, a secondary cartridge fires and ejects the
BL-755 bomblets outward from the dispenser in a controlled sequence. All components
except the arming wire/lanyards are installed during manufacture to make a complete
munition.
The MK 1 was built for British use and has four fuze time settings.
SETTING FUZE FUNCTION TIME
A 1.13 seconds
B 1.38 seconds
C 1.64 seconds
D 2.00 seconds
The MK 2 was built for German use and has a longer hardback than the MK 1. The MK 2
has four fuze time settings.
SETTING FUZE FUNCTION TIME
E 0.68 second
F 0.80 second
G 0.94 second
H 1.13 seconds
The desired time delay is set prior to takeoff by removal of the arming vane to gain
access to the fuze time setting selection lever. Premature operation of the SAFU
time is indicated by red in the arm/safe indicator on the face of the SAFU adjacent
to the time selector mechanism.
The BL-755 submunition is designed to be compressed when loaded in the bomb cluster
by telescoping the probe and tail assemblies over the bomblet body. Upon ejection
from the bomb cluster, the probe and tail extend and the arming cycle begins. The
probe gives the bomblet the standoff distance required to achieve maximum effec
tiveness from the shaped charge. The BL-755 bomblet produces more fragmentation
than does the MK 118 Rockeye bomblet.
PRACTICE BOMBS
BDU-33
The BDU-33 is a 24-pound practice bomb (FIGURE 1-53), designed for pilot training
in weapons delivery techniques. The teardrop-shaped body is cast metal with a
1-87
T.O. 1-1M-34
BDU-33 PRACTICE BOMB•__________________________________________ ■
CHARACTERISTICS
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ 24 LB
LENGTH 23 IN.
DIAMETER 4 IN.
FIGURE 1-53
cavity running lengthwise through the center. A conical fin is attached to the bomb
body and has a hollow tube that serves as an extension of the bomb signal cavity. A
single-suspension lug is installed.
BDU-33B/B
From nose to tail , the signal cavity of an assembled BDU-33B/B bomb contains an
MK 1 Mod 0 firing pin assembly, MK 4 Mod 3 or MK 4 Mod 4 signal cartridge, inertia
tube, and cotter pin. The BDU-33B/B also has a safety (cotter) pin installed be
tween the signal cartridge and the firing pin assembly. Once the safety pin is
removed, it cannot be reinstalled in the bomb until the bomb is disassembled.
Impact of the bomb drives the signal cartridge, aided by the inertia tube, against
the firing pin assembly and detonates the cartridge. The cartridge expels smoke and
a flash from the tail of the bomb, permitting visual observation of bombing accuracy.
Instead of the signal cartridge, a CXU-2/B (titanimun tetrachloride) spotting charge
can be used in the bomb. The safety clip on the CXU-2/B can be reinstalled without
disassembly.
BDU-33D/B
The BDU-33D/B differs from the BDU-33B/B in that the BDU-33D/B spotting charge has
been relocated from the tail to the nose of the bomb. The spotting charge reloca-
tion results in a new firing pin on the nose of the bomb which utilizes a safety
1-88
T.O. 1-1M-34
block to prevent the firing pin from being moved during handling operations. The
safety block is held in place by a cotter pin or a safety pin. The safety block may
be reinstalled after removal without disassembling the bomb.
BDU-48/B
The BDU-48/B is a practice bomb designed to simulate the ballistics of the MK 82
(retarded) (FIGURE 1-54). It is similar to the MK 106 practice bomb and is com
patible with MER/TER and SUU-20/SUU-21 dispensers.
BDU-48/B PRACTICE BOMB

SUPPORTTUBE
(SINGLE PIECE)
LUG ASSEMBLY
COTTER
PIN
END CAPS
(IDENTICAL)
SHELL
(SINGLE PIECE)
MK 1 MOD 0
FIRING PIN
ASSEMBLY
CHARACTERISTICS
WEIGHT 10 LB
LENGTH 19 IN.
DIAMETER_ _ _ _ _ _ _ _ _4 IN.
FIGURE 1-54
MK 106
The MK 106 (FIGURE 1-55) is a thin-skinned practice bomb designed for aircrew
training in retarded weapons delivery techniques. The bomb consists of an outer
cylinder, an inner cylinder (sleeve), a firing device, a signal cartridge, and a box
fin assembly. The box fin assembly consists of four metal vanes welded to the aft
end of the inner sleeve. On the MK 106 Mod 4, the firing device has been changed to
a flat circular nose plate the same diameter as the outer cylinder.
The MK 4 Mod 3 or Mod 4 signal cartridge is installed in the sleeve with the primer
toward the bomb nose. The firing device is installed and secured in the bomb nose.
1-89
T.O. 1—1M—34
MK 106 PRACTICE BOMB
PLUNGER
SAFETY CLIP
CHARACTERISTICS
WEIGHT 5 LB
LENGTH 19 IN.
DIAMETER 4 IN.
FIGURE 1-55
Impact of the bomb after release causes the spring-loaded firing device to collapse,
detonating the signal cartridge. Smoke from the cartridge permits visual obser
vation of bomb accuracy.
NOTE
The ballistics for practice weapons differ

sufficiently to require a separate set of
bombing tables, one set for the SUU-20 and
one set for the SUU-21 bomb dispensers.
MK 4 MOD 3 AND MK 4 MOD 4 SIGNAL CARTRIDGE

The MK 4 Mod 3 signal cartridge closely resembles a 10-gauge shotgun shell. The
cartridge has an aluminum case with a commercial shotgun primer. The case is filled
with an expelling charge of smokeless powder and a marker load of stabilized red
phosphorus.
The MK 4 Mod 4 signal cartridge differs from the MK 4 Mod 3 in that in the Mod 4 the
red phosphorus has been replaced by colored (red) powder due to fire hazards encoun
tered when phosphorus is used. In all other respects the signal cartridges are
identical .
1-90
T.O. 1-1M-34
20MM AMMUNITION
The components that make up a complete round are: a brass cartridge case, an
electric primer, propellant powder, and the projectile (See FIGURE 1-56.). The pro
jectile is fired when an electrical pulse is applied to the primer. The resulting
flame passes through a gas vent leading to the propellant chamber and ignites the
propellant. As the propellant burns, it forms a gas which forces the projectile
through the gun barrel .
The only significant difference between the five types of ammunition is in the pro
jectile. Located at the rear of all projectiles is a band of soft metal that seats
in the the grooves of the gun barrel. The grooves in the barrel are twisted so that
the projectile receives a rotating motion as it travels through and leaves the gun
barrel. This rotation is induced to provide stability in flight. The soft band
also serves to prevent the propelling gas from escaping past the projectile.
NOTE
The dummy ammunition color code may be either

bronze or shades of grey or tan. The case
will be steel or plastic. Dummy ammuni t ion
is used to check out the gun system.
M55A1/A2 TARGET PRACTICE ROUND (M220 TP TRACER ROUND)

The M55A1 and M55A2 target practice (TP) round is ball ammunition. The body of the
projectile is made of steel. The projectile is hollow and does not contain a
filler.
M53 ARMOR-PIERCING INCENDIARY ROUND

The body of the M53 armor-piercing incendiary (API) projectile is composed of solid
steel. The nose of the projectile is made of aluminum alloy, charged with an incen
diary composition, and sealed with a closure disk. The projectile does not require
a fuze because it functions upon impact.
M56 HIGH-EXPLOSIVE INCENDIARY ROUND (XM242 HEI TRACER)

The M56 high-explosive incendiary (HEI) round (FIGURE 1-56) contains an HEI
projectile. The round is used against aircraft and light material targets. The
projectile explodes with an incendiary effect after penetrating the surface of the
target. HEI projectiles require a fuze to complete the explosive train.
The fuze has a delay arming distance of 20 to 35 feet from the muzzle of the gun.
Centrifugal force, created by the projectile spin, allows the detonator to align
with the firing pin and the booster; the projectile is now armed. Upon impact, the
projectile presses into its target, crushing the nose of the fuze and forcing the
firing pin against the detonator. The booster, initiated by the detonator, causes
the projectile to explode.
1-91
T.O. 1—1M—34
20MM AMMUNITION
M55 TP (BALD/M220 TP-T (TRACER)
CHARACTERISTICS BLUE
(WHITE LETTERING)
WEIGHT
COMPLETE ROUND 0.56 LB
PROJECTILE _ _ _ _ _ ___0.22 LB
LENGTH
COMPLETE ROUND 6.62 IN.
CARTRIDGE CASE .... 4.02 IN.
PROJECTILE 2.98 IN.
DIAMETER, PROJECTILE_ _ _ 0.79 IN.
PROPELLANT
CASE VENT SEAL

ELECTRIC PRIMER M52A3B1
(ENLARGED) ELECTRIC
(TYPICAL ALL THREE ROUNDS) PRIMER M52A3B1
INCENDIARY
UNPAINTED COMPOSITION
ALUMINUM
BLACK CLOSURE
M53 API (RED DISC
CHARACTERISTICS LETTERING)
WEIGHT SHAPED STEEL

COMPLETE ROUND—_ _ _ _ 0.57 LB PROJECTILE
PROJECTILE_ _ _ _ _ _ _ _ _ _ _ 0.22 LB
LENGTH PROPELLANT
COMPLETE ROUND_ _ _ _ _ _ 6.62 IN.
CARTRIDGE CASE_ _ _ _ _ _ _ 4.02 IN.
PROJECTILE_ _ _ _ _ _ _ _ _ _ 2.98 IN.
DIAMETER, PROJECTILE_ _ _ 0.79 IN. CASE VENT SEAL
ELECTRIC
PRIMER M52A3B1
FUZE, POINT
BRASS DETONATING (PD)
YELLOW RDX
(BLACK
M56 HEI/XM242 HEI-T (TRACER) LETTERING)
CHARACTERISTICS INCENDIARY
COMPOSITION
WEIGHT
COMPLETE ROUND—_ _ _ _ 0.56 LB BASE COVER
PROJECTILE 0.22 LB
LENGTH
COMPLETE ROUND 6.62 IN. PROPELLANT
CARTRIDGE CASE 4.02 IN.
PROJECTILE 3.03 IN. CASE VENT SEAL
DIAMETER, PROJECTILE_ _ _ 0.79 IN.
ELECTRIC
PRIMER M52A3B1
FIGURE 1-56
1-92
T.O. 1-1M-34
30MM AMMUNITION
The PGU-13/B 30mm round (FIGURE 1—57) has been developed specifically for the
GAU~8/A weapon and ammunition handling system and can be used in the GPU-5 pod. It
includes TP, HEI, and API rounds. Common to all rounds is a lightweight percussion
primed cartridge case.
The aluminum cartridge case contains an M-36 A1E1 primer, flash tube assembly, and a
single or double base propellant. The WEC0M-30 tube, FFFG black powder, and disk
comprise the flash tube assembly.
The functional/operational sequence of this cartridge is as follows: The firing pin

strikes the primer, the primer is ignited by being crushed between the cap and
anvil, and the flame from the primer mix shoots through the flash hole and ignites
the black powder in the flash tube. Flame from the black powder ignites the pro
pellant, and high-pressure gases from the burning propellant drive the projectile
out the rifled barrel. The rifling spin stabilizes the projectiles via the plastic
rotating bands. The TP round has an inert projectile assembly. The HEI projectile
consists of a fragmenting steel body, a modified M505 nose fuze, and an HE incen
diary mix. The API projectile contains a depleted uranium penetrator, a non
discarding aluminum carrier, and a nose cap.
M5O5 PROJECTILE NOSE FUZE

The M505A2 or M505A3 (FIGURE 1-58) fuze is used in the 20mm M56 HE and the 30mm
PGU-13/B HE projectiles. The fuze has a point-detonating system that uses delay
arming and detonator safety. The mechanical point-detonating feature consists of an
aluminum windshield that crushes upon impact, shearing the firing pin flange and
driving the pin into the detonator. The delay arming and detonator safety are
accomplished by an out-of-line, unbalanced ball-rotor. The firing pin cannot ini
tiate the detonator, nor can the detonator initiate the booster, until the fuze
reaches a spin rate of 70,000 rpm when the ball-rotor is released from its retaining
C-clamp and precessed into the proper orientation. Although a minimum arming
distance of 15 meters is desired, the fuze will arm between 3 and 10 meters. It is
insensitive to light brush and rain but will detonate on 0.040 inch 2024T aluminum.
2.75- INCH FOLDING FIN AIRCRAFT ROCKET (FFAR)

The 2.75-inch FFAR (FIGURE 1-59) is an air-launched rocket used to deliver HE, high-
explosive antitank (HEAT), flechette, and white phosphorous (WP) warheads. Warheads
are selected to best satisfy operational requirements. The 2.75-inch FFAR also has
a plaster-loaded inert head for TP. A complete rocket and round consists of a
motor, warhead, and fuze. The 2.75-inch FFAR is fired from LAU-68 series launchers.
2.75-INCH ROCKET MOTOR

The 2.75-inch FFAR uses MK 4 and MK 40 rocket motors (FIGURE 1-60). The motor tube
is made of aluminum, weighs 11.4 pounds, and is 39.4 inches long. Both motors
include an igniter, propellant grain, stabilizing rod, and nozzle and fin assembly.
1-93
T.O. 1- 1M-34
30MM AMMUNITION
CHARACTERISTICS
TP API HEI
WEIGHT, COMPLETE ROUND_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1.50 LB 1.60 LB 1.50 LB

WEIGHT, PROJECTILE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ . 0.84 LB 0.97 LB 0.82 LB
WEIGHT, CARTRIDGE CASE (AFTER FIRING)_ _ _ _ _ _ 0.34 LB 0.34 LB 0.34 LB
LENGTH, COMPLETE ROUND_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 11.4IN. 11.4 IN. 11.4 IN.
LENGTH, CARTRIDGE CASE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 6.8 IN. 6.8 IN. 6.8 IN.
LENGTH, PROJECTILE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 5.6 IN. 5.6 IN. 5.6 IN.
DIAMETER, PROJECTILE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1.2 IN. 1.2 IN. 1.2 IN.
NOTE: DUMMY COLOR CODE MAY BE EITHER BRONZE OR SHADES OF GREY OR TAN
FIGURE 1-57
1-94
T.O. 1-IM-34
M5O5 SERIES FUZES

FIRING PIN
COVER FIRING PIN
NOSE CAP
CENTRIFUGAL
ROTOR SAFETY SPRING
DETONATOR
ROTOR ASSEMBLY
DETONATOR
ROTOR ASSEMBLY
BODY
DETONATOR
DETONATOR
U-SHAPED
CENTRIFUGAL
BODY ROTOR SAFETY
SPRING
BOOSTER BOOSTER
ASSEMBLY ASSEMBLY
M505A2 M505A3
FIGURE 1-58
The rocket is ignited by aircraft electrical power. When a firing impulse is

applied to the igniter contact disk, electric current passes through the igniter
circuit and ignites the squib, which ignites the main igniter charge. The salt-
covered stabilizing rod prevents unstable burning and reduces flash and after
burning of the propellant grain.
Gas pressure from the burning igniter charge ruptures the igniter case, and burning
particles of the igniter charge ignite the propellant charge. Burning propellant
blows or burns away the nozzle seals and fin retainer and provides propulsion gases
from the rocket. After the rocket leaves the launcher, gas pressure on a piston
and crosshead in the nozzle and fin assembly forces the fins open. The opened fins
stabilize the rocket in flight.
The MK 40 rocket motor uses scarfed nozzles that impart a spin to the rocket for
additional stabilization while in flight. A rocket equipped with the MK 40 motor is
designated a low-spin FFAR. FIGURE 1-60 depicts a comparison between standard
nozzles and scarfed nozzles.
1-95
T.O. 1—1M—34
MK 1 (HE)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ .4 FT _ _ _ _ _ _ _ _ 2.75_ _ _ _ _ _ _ 18_ _ _ _ _ OD/YELLOW BAND

MK 5 (HEAT)_ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT _ _ _ _ _ _ _ _ 2.75_ _ _ _ _ _ _ 18_ _ _ _ _ OD/YELLOW BAND
MK 61 (TP)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT _ _ _ _ _ _ _ _ _ 2.75_ _ _ _ _ _ _ 18_ _ _ _ BLUE/WHITE LETTERS
M151 (PMI) _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT5 IN._ _ _ _ 2.75_ _ _ _ _ _ _ 22_ _ _ _ _ OD/YELLOW BAND
M156(WP) _ _ _ _ _ _ _ _ _ _ _ _ _ _ . 4 FT 5 IN._ _ _ _ 2.75_ _ _ _ _ _ _ 22_ _ _ _ _ GREEN/RED LETTERS
WTU-1/B (TP)_ _ _ _ _ _ _ _ _ _ _ _ _ . 4 FT 5 IN._ _ _ _ 2.75_ _ _ _ _ _ _ 22_ _ _ _ _ BLUE/WHITE LETTERS
WDU-4A/A (FLECHETTE)_ _ _ .4 FT 6 IN._ _ _ _ _ 2.75_ _ _ _ _ _ _ _ 22_ _ _ _ _ OD/YELLOW BAND
WDU-13A (FLECHETTE)_ _ _ _ 4FT6IN.—_ _ 2.75 _ _ _ _ _ 22_ _ _ _ _ OD/YELLOW BAND
FIGURE 1-59
2.75-INCH ROCKET WARHEADS

MK 1 WARHEAD (HE)
The MK 1 HE warhead (FIGURE 1-61) has a steel case and an HE charge of 1.4 pounds of
HBX-1, and uses the MK 176 or MK 178 fuze. With the MK 178 fuze installed, the
warhead weighs 6.5 pounds. The primary effect of the MK 1 warhead is fragmentation.
MK 5 WARHEAD (HEAT)
The MK 5 warhead (FIGURE 1-61) is similar in external configuration to the MK 1

warhead. The filler is 0.92 pound of Composition B in the form of a shaped charge.
A booster pellet is located at the base of the shaped charge. With the MK 181 fuze
installed, the warhead weighs 6.6 pounds. The warhead is intended for use against
tanks and armor.
When the MK 5 warhead impacts and the fuze functions, a shaped-charge booster in the
fuze projects a shock wave through the cone and flash tube of the warhead to the
warhead booster pellet. The warhead booster pellet detonates and ignites the
warhead shaped charge, which is designed to focus all the energy from the detonation
into a narrow, high-velocity jet. Pressures up to 25,000 psi are produced on the
1-96
T.O. 1-1M-34
> ■ ■ ■ ■ • ■ ' ■ ■■ " '■ ■ :
2.75-INCH ROCKET MOTOR (TYPICAL)

_____ ___________________________________________________________________________________ _____________________________________________
FIGURE 1-60
point of impact. Depth of penetration is a function of target density. Since all

energy is directed forward, there is little appreciable lateral blast effect from
the MK 5 warhead.
M151 WARHEAD (PMI)

The M151 warhead (FIGURE 1—61) has a pearlite malleable iron (PMI) case filled with
2.32 pounds of Composition B4 and uses the M427 fuze. With the M427 installed, the
warhead weighs 9.6 pounds. The primary effect of the M151 warhead is fragmentation.
M156 WARHEAD (WP)

The M156 (FIGURE 1-61) is a target-marking warhead. The external appearance of the
M156 is identical to that of the M151 HE warhead. Because of this similarity in
appearance, markings must be carefully observed and maintained. With the M427 fuze
installed, the warhead weighs 10.75 pounds, and contains 0.125 pound of Composition
B4 and 2.3 pounds of WP.
1-97
T.O. 1-IM-34
2.75-INCH WARHEADS
BRAZING GROOVE HBX-1FUZE
EXPLOSIVE FILLER
BOOSTER
PELLET
SHAPED CHARGE CONE
MK 5 WARHEAD (HEAT)
BRAZING
WDU-4 A/A AND WDU-13/A WARHEADS (FLECHETTE)
FIGURE 1-61
1-98
T.O. 1—1M—34
When the warhead impacts and the fuze functions, the fuze booster initiates the
warhead burster charge. The burst charge ruptures the warhead case and scatters
the phosphorus, which ignites spontaneously to provide dense smoke. Incendiary
effect is minor.
WDU-4A/A AND WDU-13/A WARHEADS (FLECHETTE)

The WDU-4A/A antipersonnel flechette warhead (FIGURE 1-61) weighs 9.1 pounds and
contains 5.5 grams of explosive. The warhead contains 2,200 20-grain flechettes.
The WDU-13/A warhead differs from the WDU-4A/A warhead in that the WDU-13/A has
approximately 720 60-grain flechettes. Both warheads have a base fuze, ejecting
charge, piston, an aerodynamic nose cone, and contain a red dye marker to provide
visual identification of warhead functioning.
The fuze is installed during assembly and is an integral part of the warhead. At
launch, acceleration forces arm the fuze. At 1.6 seconds after launch, an airburst,
initiated by deceleration forces, allows the spring-loaded firing pin to ignite the
ejecting charge. The ejecting charge generates gas pressure against the pusher
plate, which transmits the pressure through the flechettes to the shear pins on the
nose cone. The shear pins break, the nose cone is ejected, and the flechettes
follow the nose cone. The flechettes are packed alternating fore and aft.
Aerodynamic force causes the tail-forward flechettes to tumble and streamline after
ejection. This weather vaning causes dispersion.
Slant range at launch is the critical factor in determining slant range at warhead
function. Slant range at function must be known to determine dispersion and weapon
effectiveness. Refer to aircraft ballistic tables to determine optimum launch
conditions.
MK 61 WARHEAD (TP)
The MK 61 TP warhead has an inert, solid iron head and simulates the ballistic
characteristics of the MK 1 warhead. It has the same appearance as the MK 1
warhead. The MK 61 weighs 6.5 pounds.
WTU-l/B WARHEAD (TP)

WTU-l/B TP warhead is an inert, one-piece cast warhead that simulates the ballistic
characteristics of the M151 warhead. The WTU-l/B weighs 9.4 pounds.
CRV7 ROCKET
The CRV7 rocket (FIGURE 1-62) is designed for air-to-ground use. The rocket con
sists of a C14 motor which is assembled in various combinations of heads and fuzes
to meet mission requirements. The wraparound fins are held in the closed position
by a shearpin ring and three shearpins. When the rocket is loaded in the launcher,
the shearpin ring is clamped between the aft bulkhead of the launcher and the
detachable retaining bulkhead. This secures the rocket in the launcher. When the
rocket is not loaded in a launcher, the ignition circuit is grounded to the rocket
case by a shorting clip. The wraparound fins are fully deployed within 14 inches of
exit from the launcher and quickly stabilize the rocket in flight.
1-99
T.O. 1—1M—34
CRV7 ROCKET
CHARACTERISTICS
ROCKET WITH WARHEAD LENGTH DIAMETER WEIGHT COLOR CODE

(IN.) (LB)
MK 1 (HE)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT 5 IN. _ _ _ _ 2.75_ _ _ _ _ _ _ 21_ _ _ _ _ _ 0D/YELL0WBAND

MK 5 (HEAT)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT 5 IN. _ _ _ _ 2.75_ _ _ _ _ _ _ _ 21_ _ _ _ _ _ 0D/YELL0W BAND
MK 61 (TP)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT 5 IN. _ _ _ _ 2.75_ _ _ _ _ _ _ 21_ _ _ _ _ _ BLUE/WHITE LETTERS
M151 (HE) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT9 IN. _ _ _ _ 2.75_ _ _ _ _ _ _ 24_ _ _ _ _ _ OD/YELLOW BAND
M156(WP) _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT9 IN. _ _ _ _ 2.75_ _ _ _ _ _ 24_ _ _ _ _ _ GREEN/RED LETTERS
WTU-1/B (TP)_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 4 FT9 IN. _ _ _ _ 2.75_ _ _ _ _ _ 24_ _ _ _ _ BLUE/WHITE LETTERS
WDU-4A/A (20 GR FLECHETTE)_ 4 FT 11 IN.,_ _ _ _ 2.75_ _ _ _ _ _ _ 24_ _ _ _ _ OD/YELLOW BAND
WDU-13/A (60 GR FLECHETTE)_ _ 4 FT 11 IN. _ _ _ _ 2.75_ _ _ _ _ _ 24_ _ _ _ _ OD/YELLOW BAND
FIGURE 1-62
CM151 TRAINING ROCKET

The CM151 training rocket consists of a CRV7 rocket with a WTU-l/B warhead.Both of
these components are described in this section.
2.75-INCH ROCKET FUZES
MK 176 AND MK 178 IMPACT ROCKET WARHEAD FUZES
The MK 176 and MK 178 impact fuzes are used with the MK 1 warhead. The fuzes have
cone-shaped steel bodies that enclose an arming mechanism, a firing mechanism, and
an explosive train. The explosive train consists of a primer, detonator, booster,
and in the MK 176 a 3-mil1isecond delay. In the unarmed condition, the arming
mechanism is positioned and locked so that the primer delay element and detonator
are out of alignment with the firing pin and booster lead-in. The fuze is armed by
sustained acceleration. Once armed, the fuze remains armed until detonation.
1-100
T.O. 1—1M—34
When the rocket is launched, inertial forces resulting from acceleration cause the
setback weights to move aft and free the rotor to turn. Sustained acceleration
turns and locks the unbalanced rotor in the armed position and aligns the explosive
train under the firing pin. On impact, the firing pin is driven against the
primer, and the exploding primer initiates the explosive train.
The MK 178 differs from the MK 176, in that the MK 178 delay element between the
primer and the detonator has been removed and replaced by a flash tube to reduce
fuze function time.
M427 IMPACT ROCKET WARHEAD FUZE

The M427 fuze is a superquick action, impact fuze used on the M151 and M156
warheads. The fuze assembly consists of an inertial arming device, a mechanical
firing mechanism, and an explosive train consisting of a primer, detonator, lead-in,
and booster. The primer and booster are housed in an unbalanced arming rotor. In
the unarmed condition, the rotor is locked in position so that the primer and deto
nator are out-of-line with the firing pin and booster. Fuzing elements are housed
in a conical aluminum case. The fuze is graze-sensitive with superquick action on
impact, and requires 20 g for approximately 1 second to arm.
When the rocket is launched, inertial forces resulting from acceleration move a set
back weight aft and free the arming rotor to turn. Sustained acceleration causes
the unbalanced arming rotor to turn and lock in the armed position. The explosive
train is in line and the primer is aligned with the firing pin. The firing pin is
driven against the primer on impact. The primer functions and initiates the explo
sive train.
MK 181 IMPACT ROCKET WARHEAD FUZE
The MK 181 fuze assembly is used with the MK 5 warhead and consists of an arming
device, a firing mechanism, and a shaped-charge booster. The fuze contains an
impact-sensitive primer and does not require a firing pin. Fuze arming is actuated
by sustained rocket acceleration of approximately 20 g.
When the rocket is launched, inertial acceleration forces the rotor free. Sustained
acceleration forces turn and lock the unbalanced rotor in the armed position. The
explosive train is then in line. On impact, the primer functions and initiates the
explosive train. The shaped-charge booster detonates and projects a shock wave
against a booster pellet at the base of the warhead. The booster pellet then
ignites the warhead shaped charge.
WDU-4A/A AND WDU-13/A FUZE

The fuze used in the WDU-4A/A and WDU-13/A is an integral part of the warhead.
The fuzing element consists of an acceleration-actuated arming mechanism, a

deceleration-actuation spring-loaded firing mechanism, a percussion primer, and an
explosive charge. The primer is housed in an unbalanced arming rotor. In the
unarmed condition, the rotor is locked in a position so that the primer is out of
1-101
T.O. 1—1M—34
alignment with the firing mechanism and explosive charge. A pusher plate is
installed between the explosive charge and the payload.
When the rocket is fired, inertial acceleration forces free the fuze arming rotor.
The unbalanced rotor turns to the armed position and is locked in place. The primer
is in line with the firing mechanism, and the fuzing mechanism is armed. At decel
eration through 11 g the firing pin strikes the primer. The primer initiates the
explosive charge behind the pusher plate of the warhead. Pressure resulting from
the exploding charge shears the warhead nose retaining pin and the flechettes are
expelled.
1-102
T.O. 1- 1M-34
SECTION II
FUZES
CONTENTS
PAGE
FUZES.......................................................................................................................................................... 2-3
General Description................................................................................................................................ 2-3
Fuze Classification................................................................................................................................ 2-3
Methods of Arming................................................................................................................................ 2-4
Arming Time Interval .......................................................... 2-4
Methods of Functioning....................................................................................................................... 2-4
Explosive Train...................................................................................................................................... 2-5
Safety Features...................................................................................................................................... 2-6
FMU-54TAIL FUZES................................................................................................................................ 2-8
FMU-54/B Tail Fuze..............................................................................................................................2-8
FMU-54A/B Tail Fuze............................................................................................................................2-10
M904 NOSE FUZE...................................................................................................................................... 2-12
Arming and Operating Sequence.......................................................................................................... 2-12
Safety Features...................................................................................................................................... 2-13
M1 and M1A1 Fuze Extenders............................................................................................................ 2-13
M905 TAIL FUZE . . . ................................................................................................................................ 2-14
Safety Features...................................................................................................................................... 2-15
ATU-35 Fuze Drive Assembly...............................................................................................................2-15
M907 NOSE FUZE...................................................................................................................................... 2-16
Safety Features...................................................................................................................................... 2-17
AN-M147A1, M909, AND FMU-107/B NOSE FUZES............................................................................ 2-17
Safety Features..................................................................................................................................... 2-18
MK 339 NOSE FUZE.................................................................................................................................. 2-19
MK 339 Mod 0...................................................................................................................................... 2-19
Safety Features......................................................................................................................................2-20
MK 339 Mod 1........................................ ............................................................................................. 2-22
FMU-7 FUZESAND INITIATORS............................................................................................................ 2-22
AN-M23A1 Igniter.......................................................... .....................................................................2-22
FMU-26 FUZES...........................................................................................................................................2-24
FMU-26 A/B Nose Fuze....................................................................................................................... 2-24
FMU-26 B/B Nose or Tail Fuze............................................................................................................ 2-27
FMU-72/B LONG-DELAY FUZE...............................................................................................................2-28
2-1
T.O. 1—1M—34
PAG E
Safety Features.................................... . 2-31

FMU-81/B SHORT-DELAY FUZE............................................................................................................ 2-31
Arming and Operating Sequence................... ...................................................................................... 2-31
Safety Features................. ................................................................................................................ 2-33
FMU-112 FUZE...........................................................................................................................................2-33
Arming and Operating Sequence...................................................... ................................................... 2-35
Safety Features........................................................................................ . ........... 2-35
Operating Limitations........................................................................................................................... 2 37
FMU-124 IMPACT FUZE....................................... ................................................................................... 2-37
Arming and Operating Sequence......................................................................................................... 2 39
Safety Features. .................... ............................................................................................................... 2-39
ADU-421A/B FUZE ADAPTER.................................................................................................................2-39
FMU-56 NOSE FUZES.............................. ................................................................................................ 2-39
FMU-56B/B Nose Fuze......................................................................................................................... 2-42
ECM Mode of Operation......................................................................................................................... 2-43
Safety Features...................................................................................................................................... 2-43
Operational Limitations...................................................................................................................... 2-44
FMU-56D/B Nose Fuze............. ............................................................................. 2-44
FMU-110/B PROXIMITY NOSE FUZE........................................................ ........................................... 2-45
Arming and Operating Sequence................................................... 2-46
ECM Mode ........................ .. . .................... 2-48
Safety Features............................................................... 2-48
FMU-113/B PROXIMITY NOSE FUZE............................ .......................................................................2-48
Safety Features...................................................................................................................................... 2-49
MK 75 ARMING KIT.................................. 2-50
MK 32 Mod 1 Arming Device.............................................................................................................. 2-51
MK 59 Booster...................................................................................................................................... 2-52
MK 42 Firing Mechanism..................................................................................................................... 2-53
FZU-1/B FUZE BOOSTER............................................................................................................................ 2-53
FZU-2/B FUZE BOOSTER............................................... 2-54
FZU-37A/B INITIATOR....................................................................................................... 2-54
FZU-39/B PROXIMITY SENSOR.............................................................................................................. 2-54
BATTERY FIRING DEVICE..................................................................................................................... 2-54
MAU-162 Firing Lanyard Adjuster..................................................................................................... 2-54
Swivel and Link Assembly..................................................................................................................... 2-59
Retaining Clips...................................................................................................................................... 2-59
2-2
T.O. 1-1M-34
FUZES
GENERAL DESCRIPTION
Only aircrew-selectable, internal fuzes will be presented in this section. A fuze
is a device used to initiate bomb detonation at a predetermined time and under the
desired circumstances. Since targets are usually selected in advance of a mission
and the structure of the target indicates the type of fuzing that would produce the
best results, it is imperative that the correct fuzing system be installed in the
weapon. Additionally, many weapons can accommodate a large variety of fuzes that
can drastically change the weapon effects. Aircrews must be familiar with the
classification and operation of fuzes to effectively plan the mode of delivery and
ensure safe escape.
FUZE CLASSIFICATION
Fuzes for nonnuclear weapons are located in the nose or tail (FIGURE 2-1) of the
munition or in both the nose and tail. The distinction between nose and tail fuzes
is important because of the differences in sensitivity on impact and because of the
directional effect on fragmentation. The nose fuze (used in bombs, rockets, projec
tiles, and some guided missiles) is frequently a fuze that functions on impact. The
tail fuze may be an inertia fuze initiated by the deceleration of the bomb on
impact. A properly adjusted fuze can be sensitive enough to be initiated by impact
with the lightest roofing material. As mentioned previously, the location of the
fuze affects the direction in which fragments are projected. A nose fuze tends to
deflect sidewall fragments away from the nose of the bomb, whereas a tail fuze tends
to deflect them away from the tail. If your target were troops in the open and you
wanted maximum fragmentation effect, it would be desirable to have bombs that had
been fuzed with a nose fuze. This would result in more fragmentation deflection
FUZE CLASSIFICATION
I —•—•
TAIL
--------- NOSE
FIGURE 2-1
2-3
T.O. 1-1M-34
above ground level (AGL) - where your target is. The addition of a tail fuze may
also be appropriate in this situation to increase overall munition detonation
reliability.
METHODS OF ARMING
Fuzes are armed in one or a combination of the following four methods:
1. Vane - The arming vane is a small propeller rotated after weapon release by
airflow as the bomb falls. When the vane rotates the required number of times, the
fuze is armed.
2. Pin - The arming pin is ejected or withdrawn by spring action when the bomb
is released. The ejection of the pin releases the arming mechanism and allows the
fuze to arm.
3. Inertia - Abrupt changes in the velocity of the falling bomb arm the fuze
by deploying fins or ballutes.
4. Electric - The fuze is armed by a thermal battery that is activated at bomb

release by the extraction of the arming lanyard.
ARMING TIME INTERVAL

Direct arming fuzes are armed immediately when the arming pin is ejected or when the
arming vane has rotated the required number of revolutions. Delay arming fuzes have
an arming pin or vane that initiates a time delay mechanism that arms the fuze after
a predetermined time lapse.
METHODS OF FUNCTIONING
A fuze functions by one of the following methods (FIGURE 2-2):
1. Impact - This type of fuze is designed to function upon impact or after a

delay. The time delay (if any) is measured from the instant of impact.
2. Proximity - The proximity fuze is a miniature doppler radar set. The fuze
transmits radar waves that are reflected back to the fuze by the target. When the
lag time between transmission and reception reaches a set value, the fuze functions.
The lag time between transmission and reception is precomputed and translated into
selectable burst height values in altitude above the target. Burst height values
vary among different fuzes.
3. Time - In a time fuze, the delay is initiated at bomb release from the
aircraft and not at the instant of impact. The time element is obtained by a mechan
ical or electrical device.
4. Hydrostatic - This type of fuze is employed in depth bombs for underwater

demolition work. The fuze operates on the principle of a bellows or diaphragm that
2-4
T.O. 1-1M-34
FIGURE 2-2
expands with an increase in water pressure as the bomb sinks to counteract the force
exerted by a spring. When the spring force is overcome, the firing pin is released
and driven against the primer by spring action.
EXPLOSIVE TRAIN
The explosive train (FIGURE 2-3) controls the detonation of the bomb. The train is
a sequence of explosions in which a small quantity of very sensitive explosive sets
off a large quantity of much less sensitive explosive.
The type of explosive used in bombs must be relatively insensitive to shock and heat
to provide a reasonable degree of safety in storing, shipping, and handling. It
must also permit the bomb to penetrate a resistant target such as armor plate,
earth, or concrete before exploding. Conversely, the type of explosive used in
fuzes must be very sensitive, so that it will explode when impacted by the firing
pin. Such an explosive is not safe to handle except in minute quantities and,
therefore, is strongly compressed into a metal capsule called a detonator that is
built into the fuze. The explosion of a detonator is not of sufficient strength to
detonate the insensitive main charge explosive. A small quantity of explosive more
2-5
T.O. 1-1M-34
PRIMER
DELAY
DETONATOR
BOOSTER
BURSTING CHARGE
FIGURE 2-3
sensitive than the main charge is placed next to the detonator. This element is
called the booster. The booster is sufficiently sensitive for the shock of the
boosted explosion to detonate the bursting charge (main charge) of the bomb. Such
an arrangement of elements is basic to all explosive ammunition.
The explosive train sequence in both nose and tail fuzes may be an instantaneous or
a delayed action sequence. The instantaneous sequence begins immediately upon
weapon impact when the firing pin is driven into the detonator. The blast from the
detonator explodes the booster, which relays and amplifies the blast, causing the
main charge to explode. A delayed action train allows bomb penetration of a target.
The delay action requires two additional components, a primer and a delay element,
which are placed ahead of the detonator, booster, and main charge. The action is
started as a detonation but is converted into a delaying flame by the delay element.
SAFETY FEATURES
For safety reasons, a bomb must be incapable of explosion through fuze action before
it is clear of the aircraft. Fuzes are constructed in such a manner that they
should not function while unarmed. To prevent premature or accidental functioning
of a fuze, a safety feature is incorporated during manufacture. Common safety
features in fuzes are detonator-out-of-1ine, arming stem-safe, safety block-safe,
and electrically safe.
DETONATOR OUT OF LINE
A detonator-out-of-1ine arrangement (FIGURE 2-4) in a fuze holds one of the explo

sive train elements out of alignment with the other elements. For example, the
detonator may be held out of line with the firing pin until the fuze is armed.
2-6
T.O. 1—1M—34
FUZE SAFETY FEATURES

____________________ ____
SAFETY BLOCK - SAFE AND DETONATOR OUT OF LINE
ARMING STEM - SAFE
VANE
REDUCTION
GEARS
NOTE: ARMING STEM
AS VANE ROTATES, REDUCTION GEARS

WITHDRAW ARMING STEM FROM PLUN
GER, FREEING IT. UPON IMPACT,
PLUNGER COMPRESSES ANTI CREEP
SPRING AND FIRES PRIMER DETONATOR PLUNGER
ANTICREEP
SPRING
PRIMER
ARMING STEM
DETONATOR
SCREWED OUT-
ARMED
FIGURE 2-4
2-7
T.O. 1—1M—34
ARMING STEM-SAFE
A safety feature found in some tail fuzes is an arming stem (FIGURE 2-4), which is
screwed into the firing pin plunger. The detonator in this type of fuze is located
immediately beneath the firing pin. Vane rotation during arming unscrews the arming
stem from the firing pin plunger, thus freeing the plunger; an anticreep spring pre
vents premature movement of the plunger and firing pin, caused by velocity changes
of the bomb during free-fall.
SAFETY BLOCK-SAFE
This safety feature, commonly found in nose fuzes (FIGURE 2-4), is a block between
the striker and the fuze body, which prevents the firing pin from contacting the
primer or detonator. The arming vane drives a gear train which permits the safety
block to be ejected after a definite interval.
ELECTRICALLY SAFE
The firing contacts of an electrical fuze are kept out of alignment until the fuze
has been armed. Additional features may be used to electrically prevent the fuze
from arming unless the proper release conditions have been fulfilled. Usually the
electrical contacts are brought in line. This safing principle resembles the
detonator-out-of-line principle.
FMU-54 TAIL FUZES

There are two versions of the FMU-54, the FMU-54/B and the FMU-54A/B. The differen
ces are the arming delay times and compatibility with the MK 43 target detecting
device (TDD). Refer to the Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.
FMU-54/B TAIL FUZE

The FMU-54/B tail fuze (FIGURE 2-5) is a mechanically operated retardation sensing
device. Arming time delays are from 0.75 to 3.50 seconds in 0.25-second increments.
The fuze is used in the MK 82 Snakeye (SE) I, MK 82 air-inflatable retarder (AIR),
MK 84 AIR, and M117R. The fuze is not visible when installed. The fuze is approxi
mately 2 inches in diameter, 6 inches long, and weighs 3 pounds. Refer to the
Fuze/Bomb Compatibility Chart (FIGURE 2-40) for specific details.
ARMING AND OPERATING SEQUENCE

When the bomb is released the lanyard is pulled, allowing the fuze to operate. The
release of the retardation device causes a rapid deceleration of the bomb, ini
tiating the fuze arming cycle. If the retardation device malfunctions, the fuze
should not arm. The retardation sensor ensures a sufficient force of 3.5 ±0.5 g for
0.6 second before releasing the arming timer. If at any time retardation is lost
during this 0.6 second, the fuze does not arm. If the bomb impacts before the fuze
is armed, the fuze should not function.
2-8
T.O. 1—IM—34
FMU-54/B TAIL FUZE
FIGURE 2-5
SAFETY FEATURES
The fuze requires a 0.6-second, sustained-g loading in the front-to-rear direction
in order to arm. An initiated fuze can be subjected to repeated impacts from the
front but will not arm unless the impacts are 0.6 second or longer. Detonator-out-
of-line safety mechanism is used on the FMU-54/B. If the retarder has not caused
the fuze to arm, the fail-safe g weight will function upon impact and prevent
arming.
If the retardation device fails during

opening, the retardation should be insuf
ficient to arm the fuze. BSU-49 failure
(flagger) may result in an armed munition.
2-9
T.O. 1—1M—34
OPERATING LIMITATIONS
In order to achieve the required retardation force for arming, the minimum release
airspeed is 330 knots calibrated airspeed (KCAS) for MK 82 AIR, 350 KCAS for MK 82
Snakeye, 550 KCAS for MK 84 AIR, and 175 KCAS for M117 when used with the FMU-54/B
fuze. These are minimum airspeeds; bombs will not detonate if released slower.
NOTE
The fuze type and arming delay setting

should be recorded on the side of the bomb
or on a red warning tag attached to the
bomb. This should be checked during pre
flight of the munition.
FMU-54A/B TAIL FUZE

The FMU-54A/B (FIGURE 2-6) is a modified version of the FMU-54/B with selectable
arming time delays of 2.5 to 6.0 seconds in 0.25-second intervals. The MK 43 TDD
can be used with the FMU-54A/B. The FMU-54A/B used alone behaves in the same
manner as the FMU-54/B; when used with the MK 43 TDD, it becomes a proximity fuze.
The TDD electrically activates the fuze at a set function altitude above the ground.
Refer to the Fuze/Bomb Compatibility Chart (FIGURE 2-40) for specific details.
FMU-54A/B
*
TAIL FUZE AND MK 43 TDD
FMU-54A/B TAIL FUZE
FIGURE 2-6
2-10
T.O. 1—1M—34

During an armed release, the FMU-54A/B functions as follows:
1. When the cord assembly attached to the arming solenoid stretches to its
elastic limit, the swivel fails and initiates the fuze arming cycle.
2. The lanyard assembly is activated, releasing the retarder.
3. When the retarder opens, an arming wire is withdrawn from the striker rod
in the MK 43 TDD.
4. If the FMU-54A/B fuze is used alone or if the MK 43 TDD fails to function,

the spring-loaded firing pin initiates the detonator at impact.
SAFETY FEATURES
Safety features and operational limitations are the same as those for the FMU-54/B
in addition to the following:
1. A cable assembly safing pin provides ground safety. The cable assembly
permits removal of the safing pin through the aft end of the retarded fin prior to
aircraft launch.
2. The FMU-54A/B is armed if the red band on the cord assembly is visible in
the charging well after installation in the bomb.
MK 43 TARGET DETECTING DEVICE

The MK 43 TDD (FIGURE 2-6) is an electronic proximity sensor that provides an
electrical signal to detonate the FMU-54A/B fuze. The TDD fits into the nose fuze
well of the MK 82 Snakeye I. The TDD contains no explosive components. The nominal
function height for the MK 43 is 16 feet.
The MK 43 TDD consists of a cylindrical metal body with a dark green plastic nose
cone attached to the forward end. The battery initiating striker rod protrudes from
the nose cone. The spring-loaded striker rod is held in place by a safety clip. A
receptacle for an electrical connection is located at the rear of the cylindrical
body. The TDD is initiated by withdrawal of the arming wire from the striker rod.
This occurs when the high-drag (HD) device is deployed shortly after release. The
spring-loaded striker rod ignites the thermal battery through an electric pyrotech
nic match. The thermal battery reaches operating voltage in approximately 2
seconds. The target signal amplifier output is fed to the radio frequency (RF)
oscillator detector where pulsed RF energy is radiated outward in a lobal pattern.
As the bomb approaches the target, the interaction between the emitted and reflected
RF energy causes a doppler signal to the oscillator detector. This signal is then
applied to the target signal amplifier to be amplified sufficiently to trigger the
firing circuit. Energy is then applied to the electric detonator, which detonates
the bomb.
2-11
T.O. 1-1M-34
M904 NOSE FUZE

The M904 (FIGURE 2-7) is a mechanical impact nose fuze used in general purpose (GP)
bombs. It is 9 inches long and 2 inches in diameter at the fuze threads. The fuze
uses an arming vane to arm. Arming delay times for the M904E1 are 4, 6, 8, 12, or
20 seconds with a tolerance of +20 percent. For the M904E2 and M904E3 arming, delay
times range from 2 to 18 seconds in 2-second increments with a tolerance of +10 per
cent. For arming times below 6 seconds, a stop screw must be removed. Arming time
is independent of release airspeed. Set arm time is measured by the nose vane,
mechanical governor and constant-speed rotating gear train. Refer to the Fuze/Bomb
Compatibility Chart (FIGURE 2-40) for details.
M904 NOSE FUZE

' __________________
M904E3
SEAL
WIRE
FIGURE 2-7

Arming begins when the arming wire is withdrawn from the vane and the vane spins in
the airstream (operating range is 150 to 600 knots). Thirty revolutions equal 1
second of arming time. After the selected arming time has expired, the spring-
loaded rotor is permitted to rotate and align the detonator with the rest of the
explosive train. The rotor is locked in position, and the fuze is fuly armed. When
the bomb impacts, the fuze nose assembly moves rearward, causing the firing pin to
strike the detonator, which initiates the explosive train. Required impact forces
are approximately 250 g. Function delay times are provided by inserting a delay
element in the cavity beyond the firing pin. The delay increments are instan
taneous; 0.010, 0.025, 0.05, 0.10, and 0.25 second.
2-12
T.O. 1—1M—34
SAFETY FEATURES
The fuze includes a rotor containing the detonator which is locked out of line with
the rest of the explosive train until air arming is completed,
The delay element cavity acts as an interrupter to the explosive train when the
delay element is not installed.
Fuze arm/safe indications are visible in two windows; one located above the booster
(not visible when installed), the other on the fuze body. On the M904E1 and M904E2,
any red indicates the fuze is armed. On the M904E3, a black A on a red background
indicates the fuze is armed.
Ml AND M1A1 FUZE EXTENDERS

The fuze extension devices (FIGURE 2-8), sometimes called daisy cutters, are physi
cally compatible with the T45 nose adapter booster and any bomb which will accept
the M904E1, M904E2, and M904E3 nose fuzes. The T45 is a bushing (with an explosive
booster charge) which is threated on the outside for assembly to the bomb, and on
the inside for assembly to the fuze. The T45 is required to adapt the 2-inch thread
size of the M904 nose fuze to the large diameter bomb wells. The Ml and M1A1 fuze
extenders are authorized for use with MK 82 low-drag, general-purpose (LDGP) and MK
84 LDGP bombs. The M904 is the only fuze recommended for use with the extenders.
Fuze extenders are available in 18- , 24-, and 36-inch lengths. An aluminum arming
wire guide tube is attached to the fuze extender, to prevent arming wire slip or
breakage. The Ml is filled with cast tetrytol, and the M1A1 is filled with Comp B.
Ml AND M1A1 FUZE EXTENDERS

*
FIGURE 2-8
2-13
T.O. 1-1M-34
WARNING
When attempting a safe release/jettison,

there is an increased probability of low-
order detonation because of the explosive
contained in the fuze extender.
NOTE
• Existing LDGP bombing tables, fuze arming

data, and safe escape data should be used
for bombs on which the fuze extenders are
used.
® Fuze extenders allow detonation of the bomb

before bomb impact with the ground, result
ing in increased blast and fragmentation
effects. Use only instantaneous function
times with extenders.
M905 TAIL FUZE

The M905 (FIGURE 2-9) is a mechanical impact tail fuze used with M147 or T46 adapter
boosters in general-purpose (GP) bombs. It is 6 inches long and 2 inches in
diameter at the thread. The M147 or T46 tail adapter booster is used to permit
installation of the M905 tail fuze to the larger wells of GP bombs. The arming is
effected by an ATU-35 arming device assembly through a flexible shaft. Arming time
is independent of release airspeed and is accomplished by the arming drive assembly,
flexible shaft, mechanical governor, and constant-speed rotating gear train. The
desired arming time is set on a calibrated dial with selective delay times of 4, 6,
8, 12, 16, and 20 seconds; tolerance is +20 percent. Impact detonation delay times
are provided by inserting a delay element in the cavity just beyond the firing pin.
The delay elements are available in the following delay increments: instantaneous;
0.01, 0.025, 0.05,0.10, and 0.25 second. Refer to the Fuze/Bomb Compatibility Chart
(FIGURE 2-40) for details.

Fuze arming starts when the arming wire is withdrawn from the vane tab of the arming
drive assembly. This action permits the vane tab to rotate the inner parts of the
fuze (operating range of the fuze is 150 to 600 knots). After the selected arming
time has expired, the firing pin is free to move in the direction of flight upon
sufficient deceleration of the fuze. An anticreep spring prevents premature move
ment of the firing pin attributed to velocity changes of the bomb during free fall.
At approximately the same time the firing pin arms, the rotor containing the detona
tor is released so it may rotate by spring action, bringing the detonator in line
2-14
T.O. 1-1M-34
with the rest of the explosive train.

When the detent locks the rotor in the
M905 TAIL FUZE armed position, the fuze is armed. When
the bomb impacts, the inertia generated
ARMING STEM (TO by the impact causes the firing pin
BE CONNECTED TO assembly to move forward and strike the
DRIVE ASSEMBLY)
primer in the delay element, initiating
the explosive train. Required impact
forces are approximately 250 g.
SAFETY FEATURES
Safety features include a rotor con
taining the detonator, which is locked
out of line with the rest of the explo
sive train until air arming is complete,
and two warning windows. One window is
located in the fuze body, and one is just
above the booster. If the fuze is armed,
TIME SCALE FOR ARMING the warning in the body shows a red flag.
DELAY SETTING The fuze is not visible when installed.
FIGURE 2-9 ATU-35 FUZE DRIVE ASSEMBLY

The ATU-35A/B or B/B (FIGURE 2-10) arming
drive assembly is used to provide the rotational force required to arm the M905 tail
fuze. The drive assembly consists of a blade anemometer, housing, mounting plate,
restraining pin that prevents inflight chatter, and safing pin. The ATU-35B/B dif
fers from the A/B, in that the dimensions of the restraining pin have been changed.
ATU-35 DRIVE ASSEMBLY

ANEMOMETER
FIGURE 2-10
2-15
T.O. 1—1M—34
If the safety pin is inadvertently pulled before the arming wire is installed, the
vane restraining pin will retract, and reinstallation of the safety pin or arming
wire will not be possible. The ATU-35 drive assembly is a direct drive, and the
output speed is transmitted to the fuze through a MAU-86/B flexible drive shaft and
MAU-87 ,/B governed coupler. The arming time is independent of release airspeed,
because the spring-loaded centrifugal governor reduces high revolutions to a
constant speed of l,800±100 revolutions per minute.
M907 NOSE FUZE

The M907 mechanical time fuze (FIGURE 2-11) is used for airburst functioning of the
SUU-30 series dispensers. It is 5.48 inches long, 2.5 inches in diameter, and
: ■ ■ ■ ■ ■ ' - ■ .
M907 NOSE FUZE

SLIDER PORT FOIL DISK
WINDOW (ARMING INDICATION)
TIME SETTING INDEX ARMING WIRE
FUNCTION TIME SETTING DIAL

SAFETY WIRE
SAFETY DEVICE
ARMING PIN
ARMING PIN BRACKET

ARMING VANE VANE PLATE
RETAINING CLIP
FIGURE 2-11
weighs 2.2 pounds. Arming is accomplished by an arming vane. The arming time is
independent of release airspeed. Refer to the Fuze/Bomb Compatibility Chart (FIGURE
2-40) for details.

The arming wire is pulled when the munition is released from the aircraft, allowing
the vane to rotate and the arming pin to be ejected from the fuze. The arming vane
drives a constant-speed rotating gear train and timing disk. As the disk rotates,
the slot once occupied by the arming pin will align with the arming stem, allowing
the primer to slide into line with the firing pin and booster, arming the fuze.
When function time is greater than 10 seconds, the arming time is automatically
2-16
T.O. 1—1M—34
set at one-half the function time. For function times less than 10 seconds but not
the minimum, arming time is at least one-half the function time. For the minimum
selection of 4-second function time, arming time is 1.5 seconds after release.
Delivery airspeeds encompass a range of 100 to 600 knots true airspeed (KTAS).
However, the fuze is more reliable at speeds above 175 KTAS.
Normal airburst function occurs as the timing disk continues to rotate. The arming
slot will trigger a disengagement lever, which releases the spring-loaded firing
pin. The firing pin strikes the primer, firing the fuze.
The function time is set on a calibrated dial on the fuze body. Function times may
be set from 4 to 92 seconds at 0.5-second increments. When the function time is set
below 45 seconds, a tolerance of 1 second exists. At settings above 45 seconds, the
tolerance is 1.5 seconds. If impact occurs before expiration of set function time,
the fuze will detonate.
NOTE
The M907 is not consistently reliable. Use

only if no other SUU-30 fuze is available.
SAFETY FEATURES
Safety features include a slider detonator block containing the detonator that is
locked out of line with the rest of the explosive train until arming time is
complete. An arming pin prevents functioning of the timing mechanism and locks the
firing pin in position, blocking movement of the slider detonator block. The arming
pin is spring-ejected when the arming wire is pulled during weapons release. The
fuze has two visible safety indicators: (1) the aluminum foil disk in the fuze body
indicates the fuze is safe if the disk is intact and the brass slider assembly is
not visible; (2) a warning window forward of the foil disk indicates the fuze is
safe when the head of the arming stem is positioned under the arming disk.
AN-M147A1, M909, AND FMU-1O7/B NOSE FUZES

The AN-M147A1 and the FMU-107/B (FIGURE 2-12) are mechanical time fuzes used to open
the M129 leaflet bomb and are the same fuze except for the difference in functional
delays. Arming delay of both fuzes is 4.5 seconds. The functioning delay settings
for the AN-M147A1 fuze are from 5 to 92 seconds. The functioning delay settings for
the FMU-107/B fuze are from 13 to 92 seconds. All three fuzes use a combination of
vane and pin for arming. The M909 mechanical time fuze is used only to open the
M129. The M909 is the same as the M907 and will not be discussed here. Refer to
the Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.

The bomb is released from the aircraft, extracting the arming wire from the arming
vane, allowing it to rotate in the airstream. The arming pin is forced out of the
2-17
T.O. 1-1M-34
COTTER PIN
ARMING WIRE GUIDE

ARMING WIRE VANE TAB
RETAINING CLIP
SAFETY WIRE
STRIKER STOP
ARMING VANE
SAFETY BLOCK
TIME SET SCREW

CALIBRATED DIAL
FIGURE 2-12
fuze by a spring, leaving the clockwork mechanism to operate. The clock turns the
disk at a uniform rate until the timing disk lever drops into the notch and releases
the firing lever and firing pin.
The time is set by rotating the head of the fuze to locate the timing disk lever at
such a distance from the arming pin as will give the time desired. A thumbscrew is
provided to lock the head in position after the setting is made. The time settings
are engraved around the base of the head. Upon completion of the preset time inter
val, a small detonator charge is moved into position under the firing pin. The
firing pin is propelled into the detonator by a spring. The detonator, in turn,
detonates the booster lead, which detonates the explosive cord to separate the two
halves of the bomb body.
SAFETY FEATURES
A sealed safety wire, with attached'instruction tag, is threaded through a vane stop
strap, the arming wire guide, the striker stop, and the eye of the cotter pin which
secures the arming pin. This wire locks the mechanical arming system.
A safety block, located between the striker and vane, prevents the firing pin from
being driven inward prematurely. Evidence of arming is indicated by the absence of
a safety block, by complete or partial ejection of an arming pin, and by failure of
the trigger mechanism to support the striker clear of the safety block.
2-18
T.O. 1-1M-34
MK 339 NOSE FUZE

The MK 339 is a mechanical timed airburst nose fuze used in the MK 20 Rockeye II and
SUU-30 dispensers. There are two fuze variations, Mod 0 and Mod 1. Refer to the
Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.
MK 339 MOD O
The MK 339 Mod 0 nose fuze (FIGURE 2-13) has a fixed arming time of l.l±0.1 second,
which starts when the primary time wire is removed from the fuze at weapon release.
Two independent arming events must occur:
1. A clamping and sealing band is removed from the fuze impeller, allowing the
impeller to spin in the airstream. The minimum airspeed for arming is 224 KCAS.
2. The arming timer will self-start. At 1.1 seconds, the timer arming pin
will disengage from a slider, allowing the slider to move to the armed position
(provided the centrifugal clutch has functioned). At 1.2 seconds, the timer safe
mechanism will place the fuze firing mechanism in the firing mode.
At expiration of the preset time (primary/option) the fuze will function. A MK 43

Mod 1 detonator is the only explosive contained in the fuze. This initiates the
linear-shaped charge in the MK 20, which cuts the dispenser in half.
The fuze has two selectable function times, primary and option, with a setting range
of 1.2 to 50 seconds in 0.1-second increments for each function time. The function
timers are accurate to within ±0.1 second time settings from 1.2 to 10.0 seconds,
and 1 percent of all settings above 10.0 seconds. Any setting within the above
range may be selected. The fuze settings are preset at the time of manufacture to
1.2 seconds for primary and 4.0 seconds for option.
NOTE
A fuze function timer, set at 0.9 second or

below, will function as if set at 50 seconds.
For settings from 1.0 to 1.2 seconds, it
functions at 1.2 seconds and not before.
This is a design safety feature to prevent
early fuze functioning when released.
Function times used by the fuze are determined by the position of the fuze option
pin. The option pin is normally held depressed by the option wire, which is
installed at the time of.manufacture. With the option wire installed and the option
pin depressed, the fuze will function at the expiration of the selected primary time.
When the option wire is pulled, allowing the option pin to extend, the fuze will
function at the expiration of the selected option time. Once the option wire has
been removed, it cannot be reinstalled and the fuze is committed to the option time
setting.
2-19
T.O. 1 — 1M—34
caution
The times set on the fuze must be carefully

checked by maintenance personnel and aircrew.
A timer setting that appears to be 1.2
seconds might possibly be 12.0 seconds and
could easily be overlooked (FIGURE 2-13).
NOTE
The primary time is the first time read when

viewed from the front. The option time is
the second time showing when viewed from
front to back (FIGURE 2-13).
When installed in the MK 20 Mods 3 and 4, the MK 339 fuze is configured with an
option wire, allowing use of either the primary or the option time setting as the
mission requires. The aircrew selects the time to be used by pulling or not pulling
the option wire at weapon release.
NOTE
Selection of the option mode only will result

in a dud.
The option wire is secured in the ejector rack rear solenoid. The fuze arming wire
secures both the impeller and the primary starting pin until the wire is withdrawn
at release. The fuze arming wire is secured in the forward rack solenoid. For the
Mod 3 and 4 munitions, the mechanical fuzing switch is positioned to get either the
primary or the option function.
Nose-Arms munitions and selects primary time
Tail-Duds munition
N/T-Arms munition and selects option time.
SAFETY FEATURES
The fuze arming wire passes through a timer starting pin and impeller sealing band
release stud. With the arming wire installed, the timer starting pin prevents timer
rundown, and the sealing band prevents impeller (arming value) rotation. The fuze
incorporates a safe/arm indicator that is visible through a window in the upper half
of the Rockeye nose fairing. The indicator is a clear plastic bubble that extends
from the case of the fuze (FIGURE 2-14). When the fuze is armed, an indicator pin
with a black tip or a red flat surface extends from the fuze into the bubble. On
2-20
T.O. 1- 1M-34
MK 339 MOD
PRIMARY TIME INSIDE HALF
(SECONDS AND TENTHS)
PRIMARY/OPTION
TIME SETTING
SAFETY PIN
WINDOW
ASSEMBLY
OPTION PIN SAFE/ARM
AND BRACKET INDICATOR
BUBBLE
OPTION
SEALING BAND TIME
WIRE
SAFETY
PIN
ASSEMBLY
FRONT
IMPELLER
PRIMARY PIN
AND BRACKET
OPTION
ARMING PRIMARY TIME
(PRIMARY TIME) TIME SETTER
BAND
WIRE SETTER
RELEASE
STUD
FIGURE 2-13
2-21
T.O. 1—IM—34
later models of Mod 0 and all the Mod 1 models of the fuze, the base of the bubble
is covered by a green foil disk. When the fuze is safe, the bubble is empty and, on
later models, the green foil is visible and intact.
MK 339 MOD 1
The Mod 339 Mod 1 differs from the MK 339 Mod 0 as follows: the function delay for
both the primary and the option mode can be set from the 1.2 to 100.0 seconds. A
function mode indicator, which indicates the fuze has been shifted from primary to
option mode, is visible in the time setting observation window. Selection of the
option mode only will result in a dud. A safety clip has been added to increase
pull force because of the design of the Mod 1 fuze option spring pin.
FMU-7 FUZES AND INITIATORS

The FMU-7 fuzes and initiators (FIGURE 2-15) are used in conjunction with the
AN-M23A1 igniter in the BLU-27 fire bomb. The fuze functions instantaneously on
impact at any angle and can be used as a nose or a tail fuze. The fuze is electri
cally armed by the FMU-7 initiator assembly installed between the munition suspen
sion lugs, or by external arming wires. The initiator assembly consists of a
spring-loaded firing pin, a 1.5-volt battery, and electric cabling that connects the
initiator to the fuzes. In the fire bomb, the fuze is installed in the AN-M23A1
igniter and forms part of the fuzing network consisting of an arming lanyard, ini
tiator, and electric cabling. Refer to the Fuze/Bomb Compatibility Chart (FIGURE
2-40) for details.

Arming begins when the arming lanyard, which is connected from the initiator
assembly to the bomb rack solenoid, pulls the initiator cap and is retained by the
arming solenoid. As a result, a spring-loaded firing pin is released, forcing it
against the primer and activating the thermal battery. The output of the thermal
battery rises to a 1.5-volt pulse. The pulse is passed through the electric cabling
in the fire bomb to a bellows motor in the fuze. The bellows motor withdraws the
arming pin, which frees the firing pin. The fuze is armed. The time from firing of
the thermal battery to completion of fuze arming is 0.5 to 1.1 seconds for the
FMU-7/B and 0.3 to 0.9 second for the FMU-7A/B, B/B, and C/B fuzes. The FMU-7/B
fuze will have a pin protruding from the center of the fuze head when armed.
AN-M23A1 IGNITER
The AN-M23A1 igniter is cylindrical and rounded at one end. A fuze well in the
rounded end is designed to receive the FMU-7/B, A/B, or C/B bomb fuzes. The body of
the igniter is filled with 1.2 pounds of white phosphorus (WP). When the fuze
impacts a target, the fuze functions and the booster in the fuze detonates, bursting
the igniter and scattering the WP filling. The phosphorus ignites spontaneously
upon exposure to the air and ignites the scattered filling of the bomb. Safety
features are of the arming stem-safe principle.
2-22
T.O. 1-1M-34
MK 339 NOSE FUZE INSTALLED

_____________________________ . ON MK 20 ROCKEYE
1. FUZE SAFE/ARM INDICATOR BUBBLE

2. PILOT OPTION WIRE (IF INSTALLED)
3. FUZE SETTING OBSERVATION WINDOW
4. TIMER STARTING PIN
5. OPTION TIME SETTER
6. SAFETY WIRE GUIDE TUBE
7. PRIMARY TIME SETTER
8. BAND RELEASE STUD
9. ARMING WIRE
10. SAFETY TAG AND WARNING WIRE
11. IMPELLER
12. SEALING BAND
13. OPTION PIN
1 4. SAFE/ARM INDICATOR OBSERVATION WINDOW
SAFE ARMED
OLDER MOD 0
NEWER MOD 0 AND MOD 1

SAFE/ARM INDICATOR BUBBLE
FIGURE 2-14
2-23
T.O. 1-1M-34
FMU-7 FUZE AND INITATOR

FZU-17/B
CLIP
SAFETY WIRE
LANYARD
FUZE WELL
FMU-7A/B, B/B, C/B
PUNCTURE PORT
(FOIL RECESSED)
CABLE RECEPTACLE
(COVER INSTALLED)
AN-M23A1 IGNITER
FMU-7/B SAFETYW|RE
FZU-17/B
FMU-7/B CLIP
PUNCTURE PORT
(FOIL SURFACE)
SHEAR
FMU-7 SERIES FUZE WIRE
(NOSE AND TAIL)
FMU-7A/B, B/B FMU-7C/B
CABLE SAFETY WIRE
ASSEMBLY (SOME FMU-7B/B) FMU-7 SERIES INITIATOR
FIGURE 2-15
FMU-26 FUZES
There are two variations of FMU-26 (FIGURE 2-16) electric fuzes. The fuzes are
powered by an internal thermal battery. Both are used in SUU-30 dispensers for air
burst opening. The FMU-26B/B is a nose or tail fuze and is also used in GP bombs.
The FMU-26A/B is a nose fuze only and is only used with SUU-30 dispensers. Both
fuzes use the FZU-l/B booster. Only the FMU-26B/B uses the FZU-2/B booster.
Neither fuze is visible during preflight. Refer to the Fuze/Bomb Compatibility
Chart (FIGURE 2-40) for details.
FMU-26A/B NOSE FUZE

The FMU-26A/B electric fuze opens SUU-30 dispensers. It is 6.4 inches long, 2.87
inches in diameter, and weighs 3 pounds. The thermal battery is initiated by a
battery-firing device (BFD) which runs from the fuze well through a swivel and link
and is secured to the dispenser. During loading, the swivel and link is installed
in the bomb rack arming solenoid. When a dispenser containing an FMU-26A/B fuze is
released, the bomb rack arming solenoid holds the swivel and link that remains with
2-24
T.O. 1- 1M-34
FMU-26A/B AND FMU-26B/B FUZES

TAIL FUZE LANYARD
LANYARD
LOCK
NOSE FUZE LANYARD
CHARGING WELL
LANYARD LOCKNUT
BATTERY FIRING
DEVICE FMU-26B/B FUZE
BATTERY FIRING
FMU-26B/B FUZE
DEVICE
EVENT/ARM
SELECTOR
NOSE PLUG SWITCH
FUZE FACE
BOOSTER EVENT/ARM
END SELECTOR
SWITCH
SAFE PIN
FMU-26 FUZE SEAL PIN
(BOTH ENDS OF BOMB)
FMU-26B/B
SAFING PLUG SAFETY SWITCH FZU-l/B (AIRBURST)
HELD IN BLUE (A) BOOSTER
(AIRBURST)
POSITION
SAFE PIN
FMU-26A/B
FZU-l/B
BOOSTER SAFING PLUG
SAFETY BRACKET REMOVED
SWITCH SET FOR AIRBURST
BOOSTER END SAFETY SWITCH FZU-l/B (AIRBURST)
HELD IN BLUE BOOSTER
(AIRBURST) GREEN (GROUND RED (GROUND
ROTOR KEYS POSITION BURST) 6.6-SEC BURST) SHORT
ARM DELAY ARM DELAY
BLUE
(AIRBURST) FZU-2/B
BOOSTER
(RDX)
SAFING PLUG REMOVED SAFETY SWITCH SAFING PLUG

(SAFE INDICATION) FZU-l/B SAFING PLUG
BOOSTER REMOVED SPRING-LOADED REMOVED
BRACKET TO GREEN
SET FOR AIRBURST SET FOR GROUNDBURST
FIGURE 2-16
2-25
T.O. 1-1M-34
the bomb rack as the BFD is withdrawn through the swivel and link. The BFD remains
attached to the dispenser. This action cocks and releases the firing pin, which
initiates the thermal battery in the fuze. The fuze timing circuitry provides an
arming signal at the preset arming time. This arming signal is used to rotate the
detonator from the out-of-line position to the in-line or firing position. The fuze
timing circuitry then provides the firing signal at the preset time for airburst
function.
NOTE
The fuze was designed to perform the follow

ing functions: airburst, impact short delay,
and impact medium delay (FIGURE 2-17). The
FMU-26A/B is certified for airburst (BLUE)
only in the SUU-30 munition. The fuze was
never certified for the impact short delay
mode (RED) because of an early burst problem.
The impact medium delay (GREEN) was not cer
tified because of its nonsettable, extremely
short safe arm time (1 second).
FMU-26A/B AND FMU-26B/B MODES

MODE ARMING TIME FINAL EVENT TIME EVENT TOLERANCE
Airburst 1 Selectable Selectable
FMU-26A/B, B/B 1.9 to 99.9 sec in occurs 0.1 sec ±3 sec

0.5-sec increments after arming
Impact 2 Selectable Selectable
Short-del ay 2.0 to 20.0 sec in Nondelay; 0.010, ±10% or ±0.002 sec

FMU-26B/B only 2.0-sec increments 0.020, 0.050, 0.100, sec, whichever is
or 0.250 sec greater
FIGURE 2-17
The function and arm times are displayed in the windows on the face of the fuze.
The safing pin locks the fuze rotor in the out-of-line position until after the fuze
is installed in the bomb. Before flight, the safing pin is removed from the fuze
and replaced with the seal pin. The seal pin prevents entry of moisture into the
fuze. The aft end of the fuze has a pie-shaped section to accept a booster. A
5-gram M5 propellant booster, the FZU-l/B, is secured to the fuze by a metal bracket.
The bracket is also used to activate the airburst mode.
2-26
T.O. 1—1M—34
SAFETY FEATURES
The aft end of the fuze has a safe plug and a safety switch. The safe plug is in
the fuze only during shipping and handling and is removed prior to installation of
the fuze into the dispenser. The BFD is installed in the cavity vacated by the safe
plug.
The safety switch must be on the BLUE position for the A/B fuze and can only be
selected when the FZU-l/B is installed. The FZU-l/B booster has a metal bracket
that holds the spring-loaded safety switch in BLUE. When the FZU-l/B booster and
its bracket are removed, the safety switch will spring to GREEN. The airburst mode
is inoperative when the safety switch is not in BLUE. If the fuze selector switch
is set in the airburst mode, but the safety switch is not set in BLUE, the fuze will
not detonate airburst, but will detonate at impact.
FMU-26B/B NOSE OR TAIL FUZE

The FMU-26B/B electric fuze is used as a nose or tail fuze and provides airburst for
SUU-30 dispensers and impact-initiated burst for GP bombs. It is 6.5 inches long, 3
inches in diameter, and weighs 3 pounds. It is compatible with bombs that have
internal plumbing and the standard 3-inch fuze wells (nose and tail).
Upon release, the bomb rack arming solenoid holds the swivel and link as the arming
lanyard is withdrawn. The arming lanyard remains attached to the bomb by the
lanyard lock. This action cocks and releases the firing pin, which initiates the
thermal battery in the fuze. The thermal battery provides the electrical power for
fuze operations. The fuze timing circuitry provides an arming signal at the preset
arming time. This arming signal is used to arm the fuze, that is, to rotate the
detonator from the out-of-line position to the firing position. The fuze timing
circuitry then provides the firing signal at impact or the preset time for airburst
function. The function and arm times are displayed in the windows on the face of
the fuze. The arm and function delays are the same as those for the FMU-26A/B.
The safing pin locks the fuze rotor in the out-of-line position until after the fuze
is installed in the bomb. Before flight, the safing pin is removed from the fuze
and replaced with the seal pin. The seal pin prevents entry of moisture into the
fuze.
The aft end of the fuze has a pie-shaped section to accept a booster. The FMU-26B/B
uses the FZU-l/B to open the SUU-30 dispenser. The FZU-2/B is used with the
FMU-26B/B in high-explosive bombs.
SAFETY FEATURES
The fuze safety switch has three positions: RED, GREEN, and BLUE. GREEN keeps the
firing circuit to the detonator disabled for approximately 6.6 seconds after bomb
release. RED (no delay) bypasses the 6.6-second delay. The safety switch should be
kept in GREEN for all short-delay settings except when operational delivery con
ditions are such that the time from bomb release to impact will be less than 6.6
seconds.
2-27
T.O. 1 -1M-34
NOTE
The impact medium delay is not certified, and

attempting any medium delay (GREEN) will
cause the fuze to dud.
For release conditions where the bomb time of fall is less than 6.6 seconds, the
safety switch must be set to RED to ensure the fuze is armed at impact. BLUE can be
selected only when the FZU-l/B (airburst) booster is installed. The FZU-l/B booster
has a metal bracket that holds the spring-loaded safety switch in BLUE. If the fuze
selector is set to airburst mode, but the safety switch is not set to BLUE, the fuze
will not function as an airburst but will detonate on impact. When used in high-
explosive bombs, nose installation permits easier access for inspection and permits
changes of arming and function times.
Whether the fuze safety switch is set to RED,

GREEN, or BLUE, the minimum release altitude
for safe escape must be observed.
NOTE
• If the FMU-26/B is used in the nose of a

laser-guided bomb (LGB), the fuze well will
be covered by the guidance kit.
• The arming time tolerance for the FMU-26/B

short delay mode (FIGURE 2-17) is +0.30
second. With this mode, the minimum
allowable bomb time of flight (to prevent
duds) will be the arming delay setting plus
0.30 second.
• The fuze contains a safing device which makes

the fuze dud if impact occurs prior to arming.
FMU-72/B LONG-DELAY FUZE

The FMU-72/B (FIGURE 2-18) is a long-delay impact fuze used to detonate MK 82/84 GP
bombs up to 36 hours after impact. It is electrically armed and can be used as a
nose or tail fuze. It is 7 inches long, 3 inches in diameter, and weighs 3.5
pounds. The settings must be made prior to installing the fuze in the fuze well.
If a change in a setting is required after installing the fuze, it must be removed
from the bomb to make the change. Refer to the Fuze/Bomb Compatibility Chart
2-28
T.O. 1-1M-34
FMU-72/B LONG-DELAY FUZE
FIGURE 2-18
2-29
T.O. 1-1M-34
NOTE
The fuze settings are not visible for inspec

tion. The fuze type and arming delay setting
should be recorded on the side of the bomb or
on a red warning tag attached to the bomb.
This should be checked during preflight of
the aircraft.

The swivel and link assembly held by the arming solenoid pulls the lanyard and stays
with the aircraft. This pull (greater than 36 pounds) cocks and releases the firing
pin, which initiates the liquid ammonia battery in the fuze. The battery provides
electrical power for fuze operation. The arming circuitry provides a fuzed delay
for the signal for arming. The arming signal is used to arm the fuze; that is,
rotate the detonator from the out-of-line position to the in-line or firing posi
tion. To assure that the detonator does not fire at arming, it is grounded until
impact occurs, and the power source that fires the detonator is not charged until
33 ±10 seconds after impact. The fuze timing and counting circuitry provide the
firing or final function time at the set function time after impact. The arming
time and selectable function times are as follows:
Arming time: Fixed at 6.0 (+1.5, -1.0) seconds
Function times:
20-minute increments - 20 minutes-5 hours

1-hour increments - 5-16 hours
Function delay tolerance is +12 percent
If for any reason, the fuze is disturbed or rotated prior to function time, an anti
disturbance switch will send a signal to the fire output circuit, causing it to fire
the detonator and initiate the explosive train. Activation time of the anti
disturbance feature is 33 ±10 seconds after impact because of the power source
charging delay.
WARNING
When the FMU-72/B is used in GP bombs,

select minimum release altitudes that will
provide safe escape from bomb fragments for
instantaneous or contact bursts. This is
required to protect the aircraft and aircrew
in the event of a premature bomb detonation
at initial impact.
2-30
T.O. 1-1M-34
SAFETY FEATURES
The fuze contains a safing switch that duds the fuze if impact occurs prior to
arming*
Deliveries should be planned to prevent bomb impact in the proximity of previously

dropped bombs after their antidisturbance activation time has lapsed.
To prevent sympathetic detonation, bombs should be delivered so the distance between

individual bombs at impact is in excess of 75 feet. If sympathetic detonation is
desired, the spacing between individual bombs should be 30 feet or less.
To ensure adequate time for the FMU-72/B fuze to arm prior to impact, the last muni
tion to leave the aircraft must have a minimum time of flight (TOF) of 7.5 seconds.
The FMU-72/B is used more effectively in the tail fuze well. This location provides
a higher success ratio in functioning at the preset function time.
FMU-81/B SHORT-DELAY FUZE

The FMU-81/B (FIGURE 2-19) is an electrically armed, short-delay impact fuze
intended for use with GBU-10 and GBU-12 LGBs, but it can be installed in any GP
bomb. It is 11 inches long, 3 inches in diameter, and weighs 4 pounds. Refer to
the Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.
The FMU-81/B consists of three major assemblies: fuze, FZU-2/B fuze booster, firing
lanyard adjuster (MAU-162/A), and lanyard assembly. An auxiliary booster clip is
provided as an accessory for guided bomb (GB) applications. Contained within the
fuze body are a battery, a safing and arming mechanism, and an electronics assembly.
The nose contains two thumbwheel setting knobs, one for arming delay and one for
impact delay, held in place by a fuze nose plug and connected to selector switches
in the electronics assembly by two mating shafts. A seal plug and safety clip with
warning tag complete the unit. The BFD is integral to the recessed end of the fuze
body. It contains a firing pin held in restraint by a shear wire until initiated by
a pull from the lanyard. The lanyard assembly is a braided steel cable connected to
the BFD by a ball and shank.
The fuze booster is shaped to fit the contour of the fuze booster cavity and is
snapped into position under the booster clip.
The firing lanyard adjuster (MAU-162/A) consists of a lanyard tie-off block, a pull
ring, and a shear wire.
The auxiliary booster clip is a spring-steel holder that holds three supplementary
boosters in place around the BFD when the fuze is used in a GB.

Any of nine arming-delay settings (4, 5, 6, 7, 8, 10, 12, 14, or 20 seconds, with a
tolerance of 5 percent) or a SAFE setting can be selected by means of the
thumbwheel knob of the arming-delay selector switch. The tolerance on the arming
2-31
T.O. 1—IM—34
FMU-81/B SHORT-DELAY FUZE
FIGURE 2-19
2-32
T.O. 1—1M -34
delay time is 5 percent of the selected setting. The arming delay settings may be
made before or after installation of the fuze in the bomb. Any of six impact delay
settings (0.0, 0.01, 0.02, 0.05, 0.10, or 0.25 second) can be selected by means of
the thumbwheel setting knob of the impact-delay selector switch. The impact-delay
settings may be made before or after installation of the fuze in the bomb.
Upon bomb release, a lanyard pull of 20 pounds or more shears a pin in the BFD and
releases the BFD firing pin. The firing pin initiates a primer cap which, in turn,
initiates the battery. The battery produces the 11 volts necessary to operate the
timing and control circuitry in the fuze. At approximately 3/4 of the set arm time,
the enable bellows motor is activated, removing the safing pin block on the safe and
arm mechanism. At the set arm time, the arming bellows motor moves the detonator to
the fire position. On impact, the fuze functions after elapse of the preset impact
del ay.
SAFETY FEATURES
A SAFE position on the arming delay setting thumbwheel renders the arming circuit
inoperative. Locking plates behind the arming delay and impact delay setting
thumbwheels prevent accidental movement of the thumbwheels during ground-handling of
the fuze. A safing pin reveals potentially armed conditions of the fuze by visibly
protruding through a seal plug on the fuze nose. The safing pin holds the rotor out
of line until the pin is driven through the plug by the arm-enable bellows.
A safety clip on the fuze nose prevents the safing pin from releasing the rotor
until the safety clip is manually removed during installation in a bomb. If the BFD
is accidentally initiated during handling, the safing pin permanently locks the
safety clip in place to reveal a defective fuze condition to the munition handler.
A hitch pin prevents actuation of the BFD until manually removed during bomb
installation.
The safe and arm mechanism provides out-of-line safety until the rotor is freed by
movement of the safing pin, and is propelled in line by an arming bellows after BFD
installation. If an impact of greater than 250 g should occur prior to arming, the
safing switch and/or the detonator enable switch will function and prevent the fuze
from arming. If an arming signal is generated prior to removal of the safing pin,
the rotor will attempt to rotate and will deform a locking tang that permanently
locks the rotor out of line. The safe and arm mechanism also prevents battery
voltage from reaching the event circuitry before mechanical arming occurs.
The arm-enable circuitry prevents premature actuation of the arm-enable bellows by

means of a resistor-capacitor combination that limits the enable-bellows charging
current until the preset timing circuit releases a voltage pulse and triggers the
capacitor to discharge into the bellows.
FMU-112 FUZE
The FMU-112/B (FIGURE 2-20) can be used as a nose or tail fuze in high- and low-drag
GP bombs. The fuzing system consists of the FMU-112/B fuze and the FZU-37A/B tur
bine generator power supply/initiator. An electrical cable assembly is routed from
the fuze internally to an FZU-37A/B located in the charging well between the lugs.
2-33
T.O. 1-1M-34
FMU-112/B SYSTEM
FZU-37A/B
AIRSTREAM
noSEob^LoaO^
BOOSTER
SAFING PIN
CABLE
ASSEMBLY
FUZE, COMMON
FMU-112
FUZE INITIATOR
(FZU-37A/B)
GAG LOCK AND

SHUTTER PORT DETONATE DELAY
SELECTION DIAL
EVENT
SAFE
^MILLISECONDS^ INTERFACE CONNECTOR PORT

(COVER REMOVED BYCCW TWIST)
ARM
SECONDS
ARM DELAY SAFING PIN PORT
SELECTION DIAL (RECESSED)
FACEPLATE
(SHOWN SAFE)
FIGURE 2-20
2-34
T.O. 1-1M-34
The FZU-37A/B is a mechanically actuated air turbine which generates electrical

power from the slipstream of the bomb. Refer to the Fuze/Bomb Compatibility Chart

The FMU-112/B is capable of both low-drag and high-drag arming, with the high-drag
arming mode taking priority if retardation is detected by drogue sensors. When a
high-drag weapon release is sensed by the fuze, all ground-set arming times are
automatically reduced to 2.6 seconds, unless the special arm time of 6/4 seconds is
selected. The special 6/4 setting provides a 6.0-second low-drag arm time, which is
automatically shortened to 4.0 seconds when a valid high-drag release is sensed.
This provides a greater safety margin for slower releases, where 2.6 seconds does
not provide safe separation. Ground-selectable impact functional delay times are
instantaneous; 0.005, 0.010, 0.025, 0.050, 0.1, and 0.2 second +5 percent.
FUZE ARMING (LOW DRAG)

The fuze has eight ground-selectable low-drag arm times of 4, 5, 6, 7, 10, 14, 20,
or 6/4 seconds. The low-drag arming cycle begins 0.3 second after weapon release,
when the FZU-37A/B initiator reaches a sufficient power level (FIGURE 2-21). This
power initiates both a nonelectric timer and an electric timer. The remaining power
is stored in a capacitor. The fuze uses the detonator out-of-line principle with
the nonelectric timer, removing a lock from the rotor 2.0 seconds after release. If
valid free-flight (i.e., nonretarded flight) is sensed, the electric timer uses the
power stored in the capacitor to remove a second lock at the expiration of the set
arming time, or at 6 seconds if the special 6/4 setting is used. At this time, the
detonator is electrically rotated into the firing position, and the fuze is armed.
The fuze is electrically detonated, either instantaneous or delay, after sustaining
40 to 80 g deceleration.
FUZE ARMING (HIGH DRAG)

The FMU-112/B fuze arms in the high-drag mode if 3.0 g deceleration is sustained
(FIGURE 2-21). The FZU-37A/B requires a 0.1 second to initiate power. As in low
drag, the nonelectric timer is initiated and removes its lock from the rotor 2.0
seconds after release. The retardation of the ballute or fins actuates a bidirec
tional, axial g switch that overrides any low-drag timer setting. After 2.5
seconds, the second electrically actuated lock is removed by power stored in the
capacitor, arming the fuze by 2.6 seconds. If the special 6/4 setting is used,
however, high-drag arming is delayed until 4.0 seconds.
SAFETY FEATURES
The FMU-112/B fuze incorporates both mechanical and electrical safety features.
Proper fuze initiation, timing, and high-drag profile, as well as proper sequencing
of unlock, arming, and impact are monitored. Out-of-tolerance or improperly
sequenced events will cause the fuze to be a dud.
2-35
T.O. 1-IM-34
FMU-112/B ARMING
LOW DRAG RELEASE
HIGH DRAG RELEASE
-0.1 0 1 2 3 4 5 SECONDS X
1 WEAPON RELEASE
2 FUZE TIMER
3 DUAL DECELERATION DETECTION CAUSES GAG LOCK REMOVAL
4 AUTO HIGH DRAG ARM AT 2.6 SECONDS OCCURS FOR ANY
DIAL SETTING OF 4, 5, 6, 7, 10, 14, OR 20 SECONDS
5 AUTO HIGH DRAG ARM AT 4 SECONDS OCCURS FOR SPECIAL 6/4
DIAL SETTING
6 IMPACT DETONATION OCCURS.
FIGURE 2-21
2-36
T.O. 1-1M-34
The fuze uses the basic detonator out-of-line principle. The nonelectric timer acts
as an independent lock, and the electric lock maintains the detonator out of line
even during safe jettison release and impact. If the retardation device failure
occurs during opening, retardation is insufficient to arm the fuze.
WARNING
BSU-49 failure (flagger) may result in an

armed fuze.
All fuze operating power is cut and the detonator will not fire if any of the
following occur:
1. Impact occurs before arming
2. Electrical unlock occurs before 2.0 seconds
3. Loss of high-drag retardation occurs prior to 2.0 second after retardation

begins
4. Sensing logic issues a command during the first 2.0 seconds
5. The two timers do not agree.
6. The detonator arms before electrical lock occurs.
OPERATING LIMITATIONS
Minimum delivery airspeed for low-drag bombs and MK 82 AIR is 250 KCAS. Minimum
delivery airspeed for MK 82 Snakeye is 275 KCAS.
The fuze firing capacitor requires 0.2 seconds to charge. This delay, along with
the 0.1-second FZU-37A/B initiator delay, constitutes a total inherent delay of 0.3
second for the FMU-112.
FMU-124 IMPACT FUZE

The FMU-124/B impact fuze (FIGURE 2-22) is used for fuzing the nose and tail of
GBU-15 bombs. Fuze arming, is accomplished by both mechanical and electrical means.
The fuze is housed in a cylinder 8 inches long and 3 inches in diameter. The front
of the fuze is equipped with a safety release assembly, an electrical connector to
accept operating power and electrical signals, and a screwdriver-adjustable selector
switch to select arming and functional delay times. A retractile cable connects
to the rear of the fuze. The cable is terminated in a connector that mates with an
2-37
T.O. 1—IM -34
FMU-124A/B IMPACT BOMB FUZE
CONNECTOR
REAR FUZE
MOUNTING
SELECTOR
ARMING
SWITCH
ROD
MOUNTING
RETAINER
RETRACTILE
CABLE
FIGURE 2-22
2-38
T.O. 1- 1M—34
ADU-421A/B adapter mounted in the charging well of the bomb. The adaptor provides
the means of electrically connecting the nose and tail fuzes. Refer to the
Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.

The FMU-124A/B fuze has selectable arming delay times of 5.5 or 12 seconds.
Functional delays are 0, 0.01, or 0.025 second. Upon bomb release from the
aircraft, the arming wire is extracted from the arming rod, and a mechanical timer
starts a timing cycle of approximately 5 seconds during which an arming power isola
tion switch is closed and a blocking gag rod is removed from the rotor. Upon
receipt of electrical power (arm command from the aircraft) firing capacitors are
charged, which activates dual electronic timer switches having selectable delays of
either 5.5 or 12 seconds. Upon delay expiration, both timer switches close, and a
bellows motor actuator rotates the rotor. The rotor then latches in the arm posi
tion, mechanically aligning the fuze explosive train, completing the arming cycle.
The fuze is capable of airburst functioning upon application of an electrical deto
nation signal, but it is not used in this manner in the GBU-15 bomb. Impact results
in instantaneous detonation or 10- or 25-millisecond delayed detonation, as
selected on the fuze.
SAFETY FEATURES
The fuze safety release assembly is held in the safe position by a safety pin with a
warning flag attached. The safety pin and warning flag are replaced by an arming
wire when installed in the bomb. Arming can occur only if the arming rod is
extended and electrical power is applied.
ADU-421A/B FUZE ADAPTER

The ADU-421A/B fuze adapter (FIGURE 2-23) is installed in the charging well of the
GBU-15 bomb and provides interconnection for the nose and tail fuzes of the bomb.
It is cylindrical in shape and contains two electrical connectors side by side in
the base. The adapter is fastened into the charging well by means of a retaining
ring.
FMU-56 NOSE FUZES

The FMU-56B/B and FMU-56D/B fuzes (FIGURE 2-24) are self-powered doppler radar
proximity nose fuzes used to open SUU-30 dispensers. They have 10 arming time set
tings and 10 height of burst (HOB) settings (FIGURE 2-25) for above ground fuze
functioning. Additionally, the FMU-56 fuze has provisions for selecting an elec
tronic countermeasures (ECM) mode. Refer to the Fuze/Bomb Compatibility Chart
2-39
T.O. 1—1M—34
ADU-421A/B FUZE ADAPTER
RETAINING RING
FRONT VIEW DUST COVERS
REAR VIEW
FIGURE 2-23
2-40
T.O. 1-1M-34
FMU-56B/B AND FMU-56D/B FUZES
PITOT TUBE
KNOCKOUT
EXTENDED
POSITION
OF PITOT TUBE
(FUZE ARMED)
ARMING
TIMER
SWITCH
HEIGHT OF
BURST SWITCH
MECHANICAL
STOP
THREADED
COLLAR
ECM SWITCH
BOOSTER WITH
BOOSTER FUZE
HOLDER ATTACHED
SAFING PIN
BATTERY
FIRING
DEVICE
INITIATOR
BOOSTER
RETAINER BATTERY
BOOSTER FIRING
DEVICE
LANYARD
BOOSTER
IGNITION
PORT
FIGURE 2-24
2-41
T.O. 1-IM-34
FMU-56B/B, D/B SELECTABLE ARMING TIMES AND HOB
ARMING HEIGHT OF BURST
SWITCH ARMING SWITCH HOB

POSITION TIMEa POSITION (FT)
(SEC)
X SAFE A 250
3 3 B 500
4 4 C 800
5 5 D 1100
6 6 E 1500
7 7 F 1800
8 8 G 2000
9 9 H 2200
10 10 J 2500
18 18 K 3000
a Tolerance: + 10 percent or +0.5 second,

whichever is greater
FIGURE 2-25
FMU-56B/B NOSE FUZE

When the CBU is released from the aircraft, the swivel and link assembly pulls the
lanyard, activating the BFD. The initiator firing pin strikes the battery primer
and activates the battery; this applies power to the fuze circuitry and starts the
arming timer.
The FMU-56B/B has a two-step arming timer. First, a pitot tube is extended from the
radome to activate the velocity sensor system. The velocity sensor must sense an
airflow of at least 150 knots. At the end of the second step, the fuze will arm if
the velocity sensor switch is closed. When the CBU reaches the preset height of
burst (HOB), the detonator fires through the booster ignition port of the housing,
setting off the booster. Ignition of the booster opens the CBU.
The FMU-56B/B outer gate is HOB plus 120 feet; its middle gate is HOB plus 60 feet.
Arming must occur prior to reaching the outer gate. It must sense 200 feet per
second (fps) downward vertical velocity (minimum) as it passes through both range
gates and the HOB. If the fuze does not sense passing through the outer gate and
the middle gate after fuze arming and prior to HOB, the fuze will not function.
2-42
T.O. 1-1M-34
ECM MODE OF OPERATION

The ECM mode is incorporated into the FMU-56B/B and D/B fuzes to provide a backup
function 2.0 ±0.5 seconds after expiration of the safe arming time. This mode pro
vides fuze function if the fuze sees an electromagnetic environment sufficient to
mask the radar return. The electronic countermeasures (ECM) mode switch is set
during manufacture in the ECM ON position and is restrained in that position by a
spring lever. The safe arming time tolerance is the same for all FMU-56 fuzes (10
percent of the preset value or 0.5 second, whichever is greater). For mission
planning purposes, the safe arming time plus ECM tolerances should be considered
cumulative. For example:
Safe arming time of 3.0 ±0.5 seconds plus

ECM backup of 2.0 ±0.5 seconds equals
Function time of 5.0 ±1.0 seconds
In this case, if the fuze senses an ECM environment, it would be expected to func
tion between 4.0 and 6.0 seconds after release. In this type environment, fuze
function approximating the desired time/altitude might be obtained if the fuze safe
arming time were set at a value approximately 2 seconds less than the TOF from
release to function. For example, if TOF from release to HOB were 10 seconds
(obtained from ballistic tables), a safe arming time of 8 seconds might be selected
in an ECM environment as follows:
Arm time - 8.0 ±0.5

ECM backup - 2.0 ±0.5
Function - 10.0 ±1.0
In this situation, if the fuze were jammed, you would expect it to function at any
time from 9 to 11 seconds. This would be near your planned HOB. TOF to HOB for
planned parameters would be 10 seconds.
SAFETY FEATURES
Both the FMU-56B/B and the FMU-56D/B possess the safety features described in the
following paragraphs.
The safing pin operates a switch that disables the arming timer by disconnecting the
timer from the battery and shorting the arm pulse output. Should the battery be ini
tiated while the safing pin is installed, the fuze will not arm.
When the SECONDS-TO-ARM switch is set to SAFE, the arming timer will not run, and
the safing and arming device will not receive an arm signal; it will remain in SAFE.
When the velocity of air sensed by the pitot boom is less than 150 knots, the switch
will remain open, breaking the arm circuit to the safing and arming device.
When installed in the fuze subassembly, the uninitiated BFD locks the safing and
arming rotor in SAFE. The safing and arming rotor is an out-of-line safety device.
The detonator is seated in the rotor.
Should the fuze impact the ground prior to expiration of the preset arm time, the
impact switch will prevent the fuze from arming.
2-43
T.O. 1—IM-34
When the pitot tube in the radome is extended, the fuze may be armed. The extended
pitot tube is an indication that the battery may have been ignited. When it is
retracted the fuze is safe. The BFD of the fuze contains a safety indicator (two
holes) located on the rear of the BFD. If tabs protrude through these two holes,
the fuze has been initiated and is a dud.
OPERATIONAL LIMITATIONS
Simultaneous release of more than one CBU with FMU-56 fuzes is not recommended.
Spatial separation is required in order that the fuze radar does not confuse other
fuze radar signals with its own. Radar interference from other fuzes could cause
the fuze to malfunction. An increased dud rate must be expected if more than four
FMU-56B/B fuzed munitions are ripple released on one pass. Refer to appropriate
aircraft Dash 34 to determine minimum release altitudes and minimum release interval
settings which provide adequate munition separation distance for ripple release.
NOTE
If different HOB settings are used, the first

munition should be set to the lowest HOB to
preclude subsequent dispensers falling through
the dispensed munitions.
FMU-56D/B NOSE FUZE

The FMU-56D/B has an integrated circuit timer which contains digital logic circuits
that extend a pitot tube 0.5 second before arming. Extension of the pitot tube
activates a velocity-sensing system. The timer logic circuits require the velocity
sensor be open before the pitot tube is extended and closed within 0.5 seconds prior
to arming, or it will not arm. The FMU-56D/B must be armed prior to reaching the
preset HOB, and it must sense a minimum of 200 fps downward vertical velocity as it
passes through the range gates and the HOB. The fuze must sense passing through the
outer gate (HOB plus 500 feet) and the middle gate (HOB plus 250 feet) after 3.7
seconds and prior to the HOB. Because of a receding target (i.e., the release
aircraft), the range gate logic prevents the fuze from functioning. The fuze will
sense and remember the range gates, if they occur after 3.7 seconds and prior to or
after arming time, because the fuze radar is operational at 3.7 seconds, regardless
of the set arming time. If all other criteria are satisfied and the munition passes
through both range gates and the HOB before arming, the munition will function imme
diately upon expiration of the arming time, Ripple releases of up to 12 FMU-56D/B
fuzed munitions may be accomplished. However, if more than six munitions are
rippled on one pass, an increased dud rate must be expected. For all FMU-56D/B
ripple releases, the munitions must attain a spatial separation of 20 feet when HOB
is 2,200 feet or lower, 24 feet when HOB is 2,500 feet, and 38 feet when HOB is
3,000 feet. Refer to appropriate Aircraft Dash 34 to determine minimum release
altitude and minimum release interval settings which provide adequate munition
separation distance for ripple release.
2-44
T.O. 1—1M—34
NOTE
If different HOBs are used, the first muni

tion released should be set to the lowest HOB.
An FMU-56D/B fuzed cluster munition will be a
dud if, during flight, the munition is flown
in medium rain at 550 KCAS in excess of 8 min
utes , or at 450 KCAS in excess of 30 minutes.
Under these flight conditions, radome erosion
will cause the pitot tube to sense a pressure
differential which is premature in the
FMU-56D/B arming sequence; this will cause
the fuze to be a dud.
Operational limits, safety features, and ECM mode of operation for the FMU-56D/B are
the same as those for the FMU-56B/B.
FMU-11O/B PROXIMITY NOSE FUZE

The FMU-110/B (FIGURE 2-26) is an electrical proximity, airburst (doppler radar
ranging) fuze powered by an internal battery. It is used as a nose fuze to open
SUU-30 series CBU munitions. An ECM mode can be selected. The FMU-110/B has 10
arming-time settings and 10 HOB settings (FIGURE 2-27). Refer to the Fuze/Bomb
Compatibility Chart (FIGURE 2-40) for details.
FMU-11O/B PROXIMITY NOSE FUZE
FIGURE 2-26
2-45
T.O. 1—1M—34
FMU-11O/B SELECTABLE ARMING TIMES AND HOB
ARMING HEIGHT OF BURST
SWITCH ARMING SWITCH

POSITION TIME POSITION HOB
(SEC) (FT)
X SAFE A 300
3 3 B 500
4 4 C 700
5 5 D 900
6 6 E 1200
7 7 F 1500
8 8 G 1800
9 9 H 2200
10 10 J 2600
18 18 K 3000
FIGURE 2-27
The fuze subassembly contains the doppler ranging radar, battery, and safing and
arming device. The fuze subassembly safing pin must be removed before flight. A
booster fuze (FZU-l/B) is attached to the rear of the fuze assembly. Detonation
of the booster causes the nose cap of the CBU to separate. The BFD is integral to
the fuze and consists of a steel initiator, a retaining clip, and a steel lanyard.
The lanyard is routed through the CBU lanyard tube.

Upon release of the munition from the aircraft, a 15-pound lanyard pull removes one
lock on the safing and arming rotor, and the BFD initiator strikes the battery
primer, igniting the battery. Voltage from the battery provides power for the
electronic circuitry. The fuze contains an arming time that starts on battery igni
tion. The timer runs for the preselected time set on the arming timer switch,
unless it is in the X position. In the X position, the timer will not run and the
fuze will not arm. The arming timer deploys a pop-out arm indicator rod and removes
a locking rod from the safe and arm device 0.5 second prior to expiration of set
arming time. The pop-out arm indicator rod ejects a protective cap from the nose of
the fuze; this exposes a port on a velocity sensor. The air velocity sensor samples
the airstream, and the contacts of the velocity switch close if an airflow greater
than 120 KCAS is detected. When the contacts close, an impulse cartridge is fired,
rotating the safing and arming rotor to the armed position.
When energized, the radar circuitry of the fuze is continually checking the height
of the CBU above the ground and the vertical component of its velocity with respect
2-46
T.O. 1-1M-34
to the ground. Height above the ground is measured by determining the time required
for the radar pulse to reach the ground and return to the fuze. The closing velo
city of the CBU is determined from the amount of doppler shift in the returned
signal with respect to the internal reference oscillator in the fuze. When the
height above the ground, as measured by the fuze, is the same as the preset height
of burst, and the closing velocity of the munition is greater than a predetermined
minimum value, the fuze functions to open the dispenser and disperse the payload.
The criteria that must be met for the FMU-110/B to function normally at the preset
HOB are:
1. The fuze must be armed prior to reaching the HOB
2. The fuze must sense 100 fps downward vertical velocity as it passes
through the HOB.
The arming time tolerance for the FMU-110/B fuze is 10 percent of the select value
or 0.5 second, whichever is greater. During mission planning where FMU-110/B fuzed
munitions are involved, the munition TOF from release to function altitude must be
greater than the arming timer setting plus the tolerance. This procedure must be
carefully observed. If the munition passes' through the selected function height
prior to the expiration of the preset arming time, the fuze function is uncertain
and a dud round may result. To assure adequate time for all fuze functional
requirements to be met, the fuze should be fully armed no less than 2 seconds prior
to the preset HOB.
Alt radar proximity sensing begins after 2.7 seconds, regardless of the arming time
setting. If the munition passes through the HOB after 2.7 seconds but before the
fuze arms, the fuze will function immediately after the arming time expires
(assuming all other functioning criteria have been met). If the munition passes
through a HOB of 1,500 feet before the radar is operational (after 2.7 seconds), the
fuze will function at the backup HOB of 700 ±50 feet after arming. If the fuze sees
a slant range that corresponds to the vertical HOB, it will function. For example,
if the fuze is 100 feet below its HOB when the radar is operational (at 2.7
seconds), it may not see a true vertical HOB of 1,500 feet, but it may see slant
range that equates to 1,500 feet. If the fuze does not see a slant range of 1,500
feet, it will function at the alternate HOB.
The FMU-110/B incorporates an alternate HOB feature that allows a proximity function
at a secondary HOB other than the ground-selectable HOB. This alternate HOB is
internal to the fuze and is preset by the manufacturer at 700 ±50 feet. If the fuze
is armed and has not functioned prior to 700 ±50 feet, it should function at that
altitude. Even though the fuze may function at 700 feet, it is very doubtful that
the dispenser will have time to open and that all the bomblets fully arm; the enve
lope is very small for a 700-foot HOB. At slow delivery airspeeds, dud bomblets can
be expected.
For proper operation of the FMU-110/B fuzes in ripple releases of up to 12 cluster

munitions, the munitions must attain a spatial separation of 20 feet within the HOB
range for HOBs of 2,200 feet and below. Refer to appropriate Aircraft Dash 34 to
determine minimum release altitude and minimum release interval settings which pro
vide adequate munition separation distance for ripple release.
2-47
T.O. 1-IM-34
ECM MODE
An ECM mode of operation is incorporated into the FMU-110/B fuze to provide a backup
function after expiration of the arming time. This feature provides an optional
fuze function if the fuze sees an electromagnetic environment sufficient to mask the
radar return. The ECM mode of operation is selectable at the antenna support collar
by placing the ECM switch to ON. Selection of OFF precludes the fuze function (a
dud fuze) in the presence of an electromagnetic environment sufficient to mask a
radar return. ON allows the fuze to function in an electromagnetic environment. If
the FMU-110/B senses an ECM environment, the fuze should be expected to function
approximately 2 seconds after expiration of the arming time. If an ECM environment
is expected, the arming timer should be set to approximately 2 seconds less than
time from release to HOB. This will give the munition its best chance to function
at or near the planned HOB.
SAFETY FEATURES
Before the FMU-110/B will arm, the following sequence of events must occur:
1. The safing pin must be removed
2. The battery must be ignited by pulling the arming lanyard
3. The arming timer switch must be set to a position other than X
4. Airflow sensed by the velocity sensor ports at the expiration of safe

separation time must exceed 120 KCAS. Test data indicate fuze arming range is 120
to 184 KCAS.
When a safing pin is installed in the front of the fuze, the safing pin locks the
safing and arming rotor in SAFE. If the battery is ignited while the safing pin is
installed and the arming timer switch is in a setting other than SAFE, the safing
pin will physically block removal of a mechanical lock on the safing and arming
rotor. When the arming timer switch is set to SAFE, the safe separation timer will
not run, and the safing and arming device will not receive an arm signal and will
remain in SAFE. When the velocity of air sensed at the velocity sensor ports is
less than 120 KCAS, the switch will remain open, breaking the arm circuit to the
safing and arming device. The FMU-110/B fuze has a visual arm indicator. With the
safing pin installed and the SECONDS TO ARM switch in the X position, the fuze is
unarmed•
FMU-113/B PROXIMITY NOSE FUZE

The FMU-113/B nose fuze (FIGURE 2-28) is a low-altitude, radar proximity fuze used
in GP bombs. It is 13.75 inches long, 5.6 inches in diameter, and weighs 8 pounds.
A FZU-2 booster is required to be installed on the fuze prior to installation in the
bomb. The fuze has a safe/arm indicator that can be viewed after installation in
the bomb. The fuze is mechanically armed and has ground-selectable arming time set
tings of 5, 6, 7, 8, 9, 10, and 18 seconds, as well as a SAFE position. Initiation
of the fuze is accomplished by a bungee lanyard pulled at release. The fuze has no
stored arming energy; power for sensor operation is obtained from an air-turbine-
2-48
T.O. 1-1M-34
FMU-113/B PROXIMITY NOSE FUZE BUNGEE

LANYARD
FUZE ARM
ARM INDICATOR TIME WINDOW
RADOME
NOSE
PLUG
FUZE ARM
TIME SELECT
RING
ARM INDICATOR
SWIVEL
WINDOW
SAFING PIN AND LINK
AND FLAG
FIGURE 2-28
powered alternator. The sensor portion of the fuze is designed to provide a 0- to

25-foot (15-foot nominal) HOB. The fuze has an impact burst backup feature. Refer
to the Fuze/Bomb Compatibility Chart (FIGURE 2-40) for details.

The fuze contains a velocity threshold device that must be overcome at munition
release (FIGURE 2-29) for fuze operation. The munition must be released at 250 KCAS
or greater to assure proper fuze operation.
The flight time of the munition must allow for the vertical velocity of the munition
to exceed 200 fps and also for the arming time, including the inherent 0.5-second
delay in fuze operation, to expire. The munition flight time must be greater than
the sum of the arming time setting, plus the 10 percent tolerance, plus 0.5 second.
If sufficient flight time is not allowed, the munition may be a dud (if impact
occurs before expiration of arm time), or it may function on impact (if impact
occurs after expiration of arm time but prior to expiration of the fixed delay).
SAFETY FEATURES
If for any reason the fuze arms and fails to fire, the arm indicator rod will indi-
cate RED through the arm indicator window.
2-49
T.O. 1—1M—34
FLIGHT DELIVERY
RELEASE
(NO ARMING ENERGY AVAILABLE)
MUNITION VELOCITY MUST EXCEED

250 KNOTS TO OPERATE
GROUND
FIGURE 2-29
Any RED or RED/GREEN showing in the window

indicates an armed fuze. Only GREEN showing
(no RED) indicates an unarmed fuze. Explo
sive ordnance disposal (EOD) personnel should
be notified immediately of any armed fuze.
MK 75 ARMING KIT
The MK 75 arming kits are mated to MK 82 Snakeye I bombs to form the MK 36 destruc
tor (FIGURE 2-30) and they also fuze the M117 destructor. The arming kit consists
of the MK 32 arming device in the nose fuze well, a MK 42 firing mechanism in the
tail fuze well, a MK 59 booster, and a MK 95 battery.
2-50
T.O. 1- 1M-34
MK 75 ARMING KIT (TYPICAL)
ARMING DEVICE BOOSTER MK 59

MK32
EXPLOSIVE FIRING MECHANISM

RELAY MK 33 MK 42 MOD 0,1, 2, 3
MOD 0
CABLE WELL EXPLOSIVE FILLER
NOSE FUZE
TAIL FUZE
WELL
CABLE CONDUIT BOMB CUTAWAY VIEW CABLE CONDUIT
FIGURE 2-30
NOTE
Ballistic data are the same for both the MK

82 Snakeye I and the MK 36 destructor bombs.
Ballistic data are the same for both the
M117R and the M117D.
MK 32 MOD 1 ARMING DEVICE

The MK 32 Mod 1 arming device (FIGURE 2-31) is a mechanical time-delay device that
requires both an airstream (vane arming) and an impact (g sensing) in order to arm.
The device provides a fixed delay of 2.16 seconds from the time the last arming wire
is withdrawn until enabling of the impact mode. Function delay is controlled by the
MK 33 Mod 0 delay system. The actual recorded fuze setting shoud be checked against
the briefed setting. Arming wires and lanyards should be checked for proper
routing, security, and clip installation.
2-51
T.O. 1—1M—34
MK 32 MOD 1 ARMING DEVICE
FIGURE 2-31
MK 59 BOOSTER
The MK 59 booster is an explosive device installed in the nose fuze well of the
bomb; it explosively links the arming device to the main charge of the bomb.
The MK 59 booster contains three different explosive elements, a MK 70 Mod 0

electric detonator, an explosive lead, and the main charge. The electric detonator
is located in the keyway on the side of the well and is electrically connected to
the firing mechanism through the bomb M72 cable assembly. The explosive relay of
the arming device aligns with the detonator when the arming device is mated with the
booster. The explosive lead is located at the base of the well next to the main
charge of the booster.
The booster is electrically initiated and functions upon receiving an electrical

signal mechanism from the firing mechanism. The signal fires the MK 70 electric
detonator in the side of the well. The detonator, in turn, fires the explosive
relay. The explosive relay is inserted into the arming device during mine buildup.
There is an explosive element in the relay. This explodes and detonates the fixed
2-52
T.O. 1~1M—34
element that sets off the detonator in the rotor of the arming device. The detona
tor in the rotor will fire the explosive lead at the base of the well in the
booster. The explosive lead sets off the booster main charge which then detonates
the main charge of the destructor. If the arming device is not armed, the detonator
in the rotor of the arming device will not fire because of its out-of-line con
dition. Thus, the booster fulfills two explosive functions: it initiates explosive
train of the destructor, and it sets off the main charge of the destructor.
MK 42 FIRING MECHANISM
The MK 42 firing mechanism is initially activated by the opening of the fins (high
drag) or by an arming wire being withdrawn (low drag). Either action pulls the pop-
out pin, enabling the device. The MK 42, at a selectable time after impact, is sen
sitive to electromagnetic interference (EMI). The explosive train of the destructor
mine is activated when the MK 42 sends an electric signal to the MK 59 booster.
Refer to appropriate Aircraft Dash 34 for employment information and related
fuzing data.
FZU-l/B FUZE BOOSTER

The FZU-l/B airburst booster (FIGURE 2-32) contains 5 grams of M5 propellant in a
metal container topped by a foam filler. The booster is attached to the rear of the
fuze subassembly. The booster may have two configurations, with or without an
attached holding clip. When initiated by the fuze detonator, the booster propels
the fuze which acts in piston-like fashion to open the dispenser.
FZU-l/B AND FZU-2/B FUZE BOOSTERS
FIGURE 2-32
2-53
T.O. 1—1M—34
FZU-2/B FUZE BOOSTER

The FZU-2/B high-explosive booster (FIGURE 2-32) contains RDX explosives. When ini
tiated by the fuze detonator, the booster detonates the bomb. It is used with FMU
fuzes installed in GP bombs. It is shaped to fit in a cutout position over the
detonator flash hole in the rear of the fuze. When the fuze detonates, the explo
sion penetrates the seal over the detonator flash hole and explodes the booster to
assure the explosion of the bomb filler.
FZU-37A/B INITIATOR
The FZU-37A/B fuze initiator (FIGURE 2-33) is an air-driven turbine power supply
that is used with the FMU-112/B. The initiator is installed in the bomb charging
well and provides electrical power and interconnection between the fuzes. When the
bomb is dropped and the lanyard pulled (exposing the turbine to the airstream), the
initiator provides electrical power to the fuzes. A minimum airstream velocity of
200 KCAS is required to start, and a minimum of 140 KCAS is required to sustain
turbine generator operation.
FZU-39/B PROXIMITY SENSOR

The FZU-39/B (FIGURE 2-34) is a proximity sensor used on the SUU-64/B (CBU-89/B) and
SUU-65/B (CBU-87/B). When activated, the FZU-39/B transmits an omnidirectional
signal which it uses to measure the vertical height above ground level. When the
measured height above the ground equals the preset function altitude, the sensor
sends a fire pulse to the integral fuze, opening the SUU-64 dispenser (FIGURE 2-35).
When the preset SUU-65/B function altitude is reached, the FZU-39/B sends a signal
for fin cant, causing the dispenser to spin. Upon reaching the selected spin rate
setting, the SUU-65/B opens. The pilot has the option of changing from time func
tion to proximity function by arming both the nose and the tail solenoids.
BATTERY FIRING DEVICE

The BFD (FIGURE 2-36) initiates the battery of electrical fuzes upon armed release
of the munition. The BFD consists of a machined steel initiator, retaining clip,
and lanyard. It replaces the fuze safing plug after the fuze is installed in the
munition.
MAU-162 FIRING LANYARD ADJUSTER

The MAU-162A and B/A firing lanyard adjuster (FIGURE 2-37) is used with the FMU-81/B
and permits adjustment of the fuze lanyard to variable lengths for attachment to the
aircraft bomb rack solenoid. The tie-off block contains three small holes through
which the fuze lanyard is threaded to adjust lanyard length. The MAU-162 consists
of a lanyard tie-block, pull ring, and shear wire. The shear wire is designed to
break, between 80 and 120 pound of pull, leaving the lanyard and tie-block with the
munition.
2-54
T.O. 1-1M-34
FZU-37A/B FUZE INITIATOR
FIGURE 2-33
2-55
T.O. 1-1M-34
FZU-39/B PROXIMITY SENSOR
FZU-39/B
PROXIMITY
SENSOR
FIGURE 2-34
2-56
T.O. 1- IM-34
FZU-39/B SELECTABLE ARMING

TIME, HOB, AND SPIN RATE
ARMING TIMER OPTIONS
SETTING SECONDS TOLERANCE
M 0.63 +0.12
N 0.95 +0.14
0 1.28 +0.16
P 1.60 + 0.18
R 1.92 +0.20
S 2.23 +0.25
T 2.55 +0.27
U 2.87 +0.31
V 3.19 +0.34
X 3.51 +0.37
Y 3.83 +0.40
Z 4.15 +0.44
HOB OPTIONS
SETTING HOB (FT) TOLERANCE
A 300 ±50
B 500 ±50
C 700 ±50
D 900 ±75
E 1200 ±75
F 1500 ±75
G 1800 ±100
H 2200 ±100
J 2600 ±100
K 3000 ±100
SPIN RATE OPTIONS
SETTING RPM
1 0
2 500
3 1000
4 1500
5 2000
6 2500
FIGURE 2-35
2-57
T.O. 1-1M-34
BATTERY FIRING DEVICE
FIGURE 2-36
MAU-162 FIRING LANYARD ADJUSTER
TIE BLOCK
FIGURE 2-37
2-58
T.O. 1-IM-34
SWIVEL AND LINK ASSEMBLY
The swivel and link (FIGURE 2-38) is a double-loop assembly that provides the
mechanical link between the fuze arming wire/lanyard and the bomb arming solenoid
on the aircraft bomb racks.
SWIVEL AND LINK
FIGURE 2-38
RETAINING CLIPS
The FZU-17/B (brass Fahnstock) and FZU-18/B (copper beryllium) (FIGURE 2-39)
retaining arming wire safety clips are stamped and formed from flat metal. They
provide a gripping force through spring tension, to prevent inadvertent extraction
of arming wires. The FZU-18/B has a minimum stripping force of 15 pounds, and the
FZU-17/B has a stripping force of 2 to 8 pounds.
RETAINING CLIPS
FZU-17/B (FAHNSTOCK) FZU-18/B (BERYLLIUM)
FIGURE 2-39
2-59
T.O. 1—1M—34
FUZE/BOMB COMPATIBILITY
TYPE ARM TIME

FUZE (N-NOSE MUNITION SELECTABLE TOLERANCE/ FUNCTIONAL
T-TAIL) ARM TIMES INHERENT DELAY
DELAY3
FMU-7/B 0.8 sec

FMU-7A/B N, T BLU-1 0.6 sec ±0.3 sec Instantaneous
FMU-7B/B BLU-27 0.6 sec
FMU-7C/B 0.6 sec
CBU-24 Airburst,
FMU-26A/B CBU-49 1.9 to 99.9 0.1 sec
FMU-26B/B N CBU-52 sec in 0.5- ±0.3 sec after
CBU-58 sec incr arming
CBU-71
MK 82 Impact,
MK 83 selectable
MK 84 2.0 to 20.0 0,0.01,0.02,
FMU-26B/B N, T M117 sec in 2.0- ±0.3 sec 0.05,0.10,and
M118 sec incr 0.25 sec (greater
GBU-10 of 10% or
GBU-12 0.002 sec)
0.75 to 3.5
FMU-54/B sec in 0.25-
sec incr
MK 82 SE
T MK 82 AIR Instantaneous
MK 84 AIR ±10% only
M117R 2.5 to 6.0 Inherent
FMU-54A/B sec in 0.25- delay (sec)
sec incr KTAS delay
FMU-54A/B T 2.5 to 6.0

with MK 82 SE sec in 0.25- Instantaneous
MK 43 TDD N sec incr at 16 ft AGL
CBU-24 Airburst,
FMU-56B/B CBU-49 3,4,5,6,7, Greater of selectable
FMU-56D/B N CBU-52 8,9,10, and 10% or 0.5 250,500,800,
CBU-58 18 sec sec 1100,1500,1800,
CBU-71 2000,2200,2500,
and 3000 ft AGL
a Used to determine vertical drop for fuze arming when arm times are selected
which do not appear in safe escape/safe separation charts.
FIGURE 2-40 (Sheet 1 of 4)
2-60
T.O. 1—1M—34
RELEASE AS METHOD OF METHOD OF ACCESSORIES SAFE

MIN/MAX FUNCTION ARMING SEPARATION
Impact Electric AN-M23A1 No

igniter
Time Electric A/B:FZU-1/B No

B/B:FZU-1/B
Time Electric B/B:FZU-2/B No
No
MK 82 SE:
Min 330 KCAS
MK 82 AIR: Impact Inertia
min 330 KCAS
~ MK 84 AIR:
min 550 KCAS No
M117
min 175 KCAS
Proximity
(impact Inertia MK 43 TDD Yes
backup)
All CBU
min 150 KCAS
(munition Proximity Electric FZU-l/B No
velocity)
FIGURE 2-40 (Sheet 1 of 4 continued)
2-61
T.O. 1—1M—34
TYPE ARM TIME

DELAY3
Selectable 20-
min incr from
MK 82 20 min to 5 hr;
FMU-72/B N, T MK 83 6.0 sec +1.5 to 1-hr incr from
MK 84 -1.0 sec 5 to 16 hr; 2-hr
incr from 16 to
30 hr; 3-hr incr
from 30 to 36 hr
Selectable
FMU-81/B N, T GBU-10 4,5,6,7,8, 0,0.01,0.02,
GBU-12 10,12,14, ±5% 0.05,0.10, and
and 20 sec 0.25 sec
FMU-107 4.5 sec Selectable

13 to 92 sec
M909 N M129 See M907 Not See M907

specified
Selectable
AN-M147A1 4.5 sec 5 to 92 sec
0.5-sec incr
CBU-24 Airburs t,
CBU-49 3,4,5,6,7,8, Greater of selectable
FMU-UO/B N CBU-52 9,10, and 18 ±10% or 300,500,700,
CBU-58 sec and SAFE ±0.5 sec 900,1200,1500,
CBU-71 1800,2200,2600,
and 3,000 ft AGL
MK 82 Unretarded:
MK 82 SE 4,5,6,7,10,14
FMU-112/B N, T MK 82 AIR and 20 sec ±5% Selectable 0,
MK 84 or 6 sec if Inherent 0.005,0.01
MK 84 AIR 6/4 selected delay: 0.025,0.05,0.10
GBU-10 Retarded: 2.6 0.3 sec and 0.2 sec
GBU-12 sec or 4 if
6/4 selected
2-62
T.O. 1—1M—34
SAFE
RELEASE AS METHOD OF METHOD OF ACCESSORIES SEPARATION
MIN/MAX FUNCTION ARMING
Impact Electric No
Min 100 KTAS Impact Electric FZU-2/B No

Max 600 KTAS MAU-162
Time Vane No
Min 120 to
184 KCAS Proximity Electric FZU-l/B No
(munition
velocity)
Min 200 KCAS Impact Electric FZU-37A/B No
2-63
T.O. 1-1M -34
TYPE ARM TIME

DELAY3
MK 82 5,6,7,8,9, ±10% 0 to 25 ft AGL

FMU-113/B N MK 84 10, and 18 Inherent (15 ft AGL
M117 sec delay: nominal)
0.5 sec
FMU-124/B N, T GBU-15 5.5 or 12 Not Selectable

sec specified 0,0.01,0.025 sec
MK 339 Seiectabie
MOD 0 1.2 to 50 sec
in 0.1-sec incr
N MK 20 1.1 sec ±0.1 sec
SUU-30
Selectable
MOD 1 1.2 to 100 sec
in 0.1 sec incr
±20%
Inherent
delay for
4,6,8,12,16, all M904
M904E1 and 20 sec fuzes (high
MK 82 LD drag only)
MK 82 SE SE: 0.3 sec
MK 82 AIR AIR: delay
MK 84 is airspeed Selectable
N MK 84 AIR dependent 0,0.01,0.025,
MK 83 0.05,0.1, and
M117 0.25 sec
M904E2 M118
MC-1 2 to 18 sec
in 2.0-sec ±10%
incr
M904E3
2-64
T.O. 1—1M—34
SAFE
Proximity Air
Min 250 KCAS (impact turbine FZU-2/B Yes
backup) powered
alternator
Impact Electric ADU-421A/B No
Min 224 KCAS Time Vane No
M148/T45 booster
Min 150 KCAS/ Impact Vane Ml and M1A1 No
Max 600 KCAS extender
2-65
T.O. 1-1M-34
TYPE ARM TIME

DELAY3
MK 82 LD
MK 82 AIR
MK 84 LD
MK 84 AIR 4,6 ,8,12,16, Selectable
M905 T MK 83 and 20 sec + 20X 0,0.01,0.025
M117 0.025,0.1, and
M118 0.25 sec
MC-1
GBU-10
GBU-12
CBU-24 1/2 of function Selectable

CBU-49 delay when greater 4 to 92 sec in
M907 N CBU-52 than 4 sec; 1.5 sec 0.5~sec incr
CBU-58 for 4-sec function
CBU-71 delay
2-66
T.O. 1-IM-34
SAFE
Min 150 KCAS/ Impact Vane M148/T45 booster No

Max 600 KCAS ATU-35 w/MAU-86/B
and MAU-87/B
Min 100 KCAS/

max 600 KCAS
(decreased Time Vane No
reliabi 1ity
below 175 KCAS)
FIGURE 2-40 (Sheet 4 of 4 concluded)
2-67/(68 blank)
T.O. 1-1M-34
SECTION III
SPECIAL EQUIPMENT
CONTENTS
PAGE
AN/AVQ-23A/B PAVE SPIKE POD.................................................................................................... 3-3

Pod Structure.................................. ............................................................. ................................. 3-4
Laser System.................................................................................................. ................................. 3-4
TV Camera System......................................................................................................................... 3-5
Optical System................................................................................................................................ 3-5
Stabilization and Beam Pointing System....................................................................................... 3-7
AN/AVQ-26 PAVE TACK POD.................................. ............................................ ........................... 3-7
AN/AA-35(V)(1) TARGET IDENTIFICATION SET, LASER (TISL) OR PAVE PENNY............. 3-10
AN/PAQ-1 LASER TARGET DESIGNATOR (LTD)......................................................................... 3-10
AN/PAQ-3 MODULAR UNIVERSAL LASER EQUIPMENT (MULE)............................................. 3-12
GROUND OR VEHICULAR LASER DESIGNATOR (G/VLLD). .................................................... 3-12
A/A 37U-15 TOW TARGET SYSTEM..................... .......................................................................... 3-12
Boom and Launcher........................................................................................................................ 3-14
Parachute Recovery System.................................. .
Tow Reel................................................................................................ .......................................... 3-14
Tow Target Operation................................ ..................................................................................... 3-14
TDU-10/B Target (Dart)................................................................................................................. 3-14
A/A 37U-33 AERIAL GUNNERY TARGET SYSTEM (AGTS)................................ ....................... 3-16
Target Deployment.......................................................................................................................... 3-16
Scoring.................................... ........................................................................................................ 3-16
Cable Release..................... ............................................................................................................ 3-16
RMK-33/A Aerial Target Tow Set.................................. :........................... ......................... .. 3-19
TDK-36/A Towed Aerial Target Set................................................................................................ 3-19
AN/ALQ-119(V) ECM POD............................................................................... ............ ..................... 3-20
Control Indicators............................................................................................................................ 3-21
AN/ALQ-119 Pod Preflight System Check ............................................................ ....................... 3-24
AN/ALQ-131(V) ECM POD ....................................... .......................................................................... 3-25
General Description..........................................................................................................................3-25
System Operation...................................................................................................... .....................3-25
AN/ALQ-131 Jamming Techniques................................................................................................ 3-32
GUN PODS.......................... ..................................... ............. ........... 3-33
SUU-16/A 20mm Gun Pod............................................................................................................. 3-33
SUU-23/A 20mm Gun Pod........................................................................ ....................................3-36
GPU-5/A 30mm Gun Pod............................................................................................................... 3-37
3-1
T.O. 1—1M—34
CONTENTS (CONCLUDED)
PAGE
SUU-25C/A AND E/A FLARE DISPENSERS............................................................................................ 3-39

LUU-1/B, 5/B, 6/B TARGET MARKER FLARES...................................................................................... 3-39
LUU-2/B FLARE........................................................................................................................................... 3-41
LUU-2A/B FLARE.......................................... 3-44
FLARE DISPENSING................................................................................................................................... 3-44
AIR COMBAT MANEUVERING INSTRUMENTATION (ACMI) SYSTEM............................................. 3-44
Aircraft Instrumentation Subsystem (AIS)............................................................................................ 3-45
CTU-2/A RESUPPLY CONTAINER..............................................................................................................3-47
MXU-648/A CARGO POD.............................................................................................................................3-49
AN/DSQ-34 LASER TARGET DESIGNATOR SCORING SYSTEM (LTDSS)......................................... 3-49
3-2
T.O. 1-1M-34
AN/AVQ-23A/B PAVE SPIKE POD
NOTE
This information is provided for aircrews of

non-PAVE SPIKE aircraft.
The PAVE SPIKE pod (FIGURE 3-1) is an electro-optical laser designator pod used
with selected F-4D and F-4E aircraft. It provides laser illumination and continuous,
accurate, angular position and range to selected day-visual targets. The pod may be
used to designate for a parent-released [laser-guided bomb (LGB)] or to buddy-lase
for a non-PAVE SPIKE aircraft. In addition, the PAVE SPIKE may be used to improve
conventional bomb delivery accuracy or to enhance navigation updates on visual check
point .
AN/AVQ-23A/B PAVE SPIKE POD
LEFT FORWARD
MISSILEWELL
CHARACTERISTICS
WEIGHT 422 LB
LENGTH —_ _ _ __ _ _ _ _ _ _ _ _ _ 12 FT
DIAMETER 10 IN.
Figure 3-1
The PAVE SPIKE may be operated independently, or it can be completely integrated with
the aircraft’s weapon release computer set, thereby taking advantage of radar target
acquisition, offset target acquisition, automatically computed weapon release, and
target memory. When integrated with the aircraft, the system is the AN/ASQ-153(V)~3
Target Designator System.
Basic integrated operation of the Target Designator System consists of the

following:
1. Acquiring a selected target, using visual or radar-aided cueing
3-3
T.O. 1-1M-34
2. Identifing the target on the cockpit television (TV) display and initiating
track and laser ranging, to provide accurate target position information for weapon
release and laser illumination for LGB guidance
3. Using the attack steering commands for more accurate release of the weapon
4. Continuously tracking the target during the escape maneuver to provide laser
designation of the target until bomb impact.
The PAVE SPIKE pod is carried in the left forward AIM-7 missile well of the F-4D or
F-4E aircraft. It contains a laser transmitter, a TV camera, an optical system, a
beam-pointing and stabilization system, an environmental control system, and a laser
coding system.
POD STRUCTURE
The nose of the pod has a glass dome which is protected by a visor when the pod is
stowed. The visor is rotated upward, under the aircraft surface when the pod is in
use. The visor protects the dome during supersonic flight and flight through rain.
The visor contains a heater to minimize icing in the window area. The pod nose
compartment is pressurized with nitrogen and contains a heat exchanger to control
humidity and temperature. A plunger-type indicator provides preflight inspection of
the nitrogen pressure.
The pod nose section is connected to, and rolls with, the sensor assembly. The sen
sor assembly is covered by an inner shell. The inner shell is mounted on bearings
within the outer shell and driven by a roll drive motor. The outer shell supports
the forward mounting lug.
The pod middle section contains the umbilical plugs, the mounting lugs, and access
doors to the electrical and cooling connections. The pod aft section outer shell
covers the laser power supply and the electronics assembly, and it can be removed
with the pod mounted on the aircraft. A surface heat exchanger is attached to the
outside surface of the aft shell. An aft end cap provides access to the phase
change, material-status indicator (an environmental sensor), the elapsed time meter,
the laser pulse counter, and various hydraulic connectors.
LASER SYSTEM
The laser system includes a laser transmitter, a laser receiver, and the laser coder
control unit.
The laser transmitter produces a narrow beam of pulsed laser energy. The beam is
used for LGB guidance. The pulses are also used to measure slant range. The laser
pulses are produced in the transmitter by a xenon flash-lamp which serves as the
pump source for the laser rod.
The laser receiver detects each laser pulse reflected from the target and sends an
amplified signal to the range circuits in the laser control electronics. The range
circuits provide accurate range to the last target detected in the range window.
The laser-derived slant range is compared with a computer slant range derived from
aircraft system inputs. The laser range is rejected if it appears invalid. Laser
3-4
T.O. 1—1M—34
transmitter cooling is accomplished by circulating a coolant (flurocarbon mixture)

through cavities around the flash-lamp and laser rod. The heat generated by the
laser transmitter is passed to a heat exchanger in the pod nose section.
TV CAMERA SYSTEM
The TV image presented on the scope is held relatively constant over a wide range of
light levels. The stabilization and beam pointing system keeps the view stabilized
during aircraft buffet.
OPTICAL SYSTEM
The optical system (FIGURE 3-2) couples the laser transmitter, laser receiver, TV
camera, TV field-of-view (FOV) selection, TV reticle, and line-of-sight (LOS) beam
pointing and stabilization. The TV LOS and laser LOS are boresighted together and
pointed by using a gyro-stabilized gimbaled mirror.
LOS coverage and gimbal limits are shown in FIGURE 3-3. The LOS limits are reduced
further by obscuration caused by aircraft stores.
AN/AVQ-23A/B PAVE SPIKE OPTICAL SYSTEM

TV
CONTROL SCOPE DISPLAY TV

ELECTRONICS RETICLE LOCATION
GIMBAL ANGLE USED FOR
COMPUTED SLANT RANGE
Figure 3-2
3-5
T.O. 1- 1M- 34
*
AN/AVQ-23A/B PAVE SPIKE LOS/GIMBAL LIMITS
0°
+15°EL -2° EL
CENTER OF TV
LOS EL ANGLE REFERENCE AND LASER LOS
(SHOWNATZERO DEGREES)
TIME
TO GO CUE
(TTG)
— -90°EL
LOS ELEVATION
+15° EL -12QQEL
GIMBAL MIRROR
LIMIT BOMB
12—VIS RELEASE -155°EL
-2° EL RED ELEVATION
FLAG APPEARS CUE ~160°EL
(T0) -176° B1T3
(NO ELEVATION —180°EL
FLAG AREA)
YELLOW ELEVATION
FLAG AREA
(-155° TO -160°)
-120°EL GREEN ELEVATION

-90° EL FLAG AREA
(-120° TO -155°)
POD HEAD ROLL

(VIEW LOOKING FORWARD)
NOTE
WHEN GREEN ELEVATION
FLAG IS UP, POD HEAD
ROLL POINTER MUST BE
IN GREEN ARC.
FIGURE 3-3
3-6
T.O. 1—1M—34
STABILIZATION AND BEAM POINTING SYSTEM

Inputs to the stabilization and beam-pointing system are obtained from the aircraft
inertial navigation system (INS), the weapons release computer set, and the antenna
hand control. During acquisition mode, the system receives LOS positioning com
mands. During track mode, the system receives rate commands. The rate commands
induced by antenna hand control movements permit continuous tracking of a target.
AN/AVQ-26 PAVE TACK POD

NOTE

non-PAVE TACK aircraft.
The PAVE TACK pod (FIGURE 3-4) is an imaging infrared (IR), day and night, laser
designator pod used with the F-111F and AN/ARN-101 equipped F-4E and RF-4C aircraft.
It provides a 24-hour, adverse weather delivery system. Capabilities include navi
gation updating, enhanced target recognition, precise target tracking, and target
position definition for precision weapon delivery. The pod may be used to designate
for a parent-released LGB or to buddy-lase for a non-PAVE TACK aircraft.
The pod contains an IR detecting set (IDS) which provides high-resolution, thermal
imaging. The IDS senses the radiated IR energy and converts it into a video signal
which in turn provides a TV display in the cockpit.
The PAVE TACK pod assembly (FIGURE 3-5) is composed of two major sections: (1) a
rotating head section and (2) a fixed-base section. The head section contains a
turret with an optical bench which supports the mirror control assembly, the
AN/AAQ-9 IDS, the AN/AVQ-25 laser rangefinder/target designator, and the optical
assembly. The turret has a pod window assembly which includes an IR filter for
transmission of the IDS wavelengths and two glass windows for the laser transmit and
receive beams. The turret rotates about the pitch axis of the head section to
follow the target LOS in pitch, while the entire head section rotates about the
longitudinal axis of the pod (in roll), allowing the sensor-window assembly to
follow the target LOS throughout the full lower hemisphere.
The base section, mounted to the aircraft via the pod adapter, houses the necessary
electronics and power supplies to operate the pod. The base structure consists of a
thin shell with major bulkheads and frames to carry the pod loads and support line-
replaceable units (LRU). The LRUs are readily accessible for service and main
tenance through structural access doors. Space has also been allocated in the base
section for installation of a video tracker and a video recorder at a later date.
The forward portion of the nose section is an aerodynamic fairing.
The base section contains the following LRUs:
1. Digital computer
2. Signal generator
3-7
T.O. 1-1M-34
3. Target designator pod control
4. Electronic control amplifier
5. Power supply
6. Laser power supply
7. IDS power supply
8. Power distribution panel
9. Environmental control unit.
CHARACTERISTICS
LENGTH—_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 163 IN.

DIAMETER—......... ......................... _..... 20 IN.
WEIGHT: PAVE TACK POD—_ _ _ _ _ _ _ _ 1277 LB
POD ADAPTER__ _ _ —_ _ _ _ 70 LB
FIGURE 3-4
3-8
T.O. 1-1M-34
PAVE TACK POD ASSEMBLY
Figure 3-5
The head section consists of two assemblies: a fixed transition assembly, which is
joined to the base section, and a rotating turret assembly.
The transition assembly contains the head roll servo gear train which drives a ring
gear to produce roll motions of the head. Roll motion is provided through a bearing
set located at the interface with the rotating head. This head structure extends
aft and carries the pitch turret on a bearing axis aligned perpendicular to the head
roll axis. A pitch servo and gear train drives a pitch gear located on the perim
eter of the turret.
The turret assembly, which includes the entire PAVE TACK optical system, is ball
shaped with a flat surface formed by the pod window assembly. The turret has remov
able sections which allow installation and removal of internal equipment. An
optical bench is mounted within the turret, and all electro-optical components are
supported by this bench which, in turn, is mounted on an isolation system to at
tenuate input turret shock and vibration environments.
The head section assembly consists of a designator head section which supports the
turret section, plus a strut assembly, a pitch and roll drive assembly, and head
3-9
T.O. 1—IM—34
fairings. The primary function of the head section is to provide precision pointing
and stabilization over the entire lower hemisphere coverage region. Hence, it con-'
tains the necessary windows, gimbals, optics, sensors, and electronic elements which
must rotate with respect to the pod base section. The major elements within this
assembly are as follows:
1. Turret assembly
2. Mirror control assembly
3. Infrared detecting set
4. Laser rangefinder/target designator (optics/electronics)
5. Head structure and cabling.
The laser rangefinder/target designator produces a narrow beam of pulsed laser

energy. The beam makes an invisible spot on the target to which the laser guided
bombs home. The laser receiver detects each laser pulse reflected from the target
and determines slant range. The laser is compatible with present laser coding
sys terns•
AN/AA-35(V)(1) TARGET IDENTIFICATION SET, LASER(TISL)

OR PAVE PENNY
NOTE

non-PAVE PENNY aircraft.
AN/AA-35(V)( 1 )(TISL) The TISL (PAVE PENNY) is a forward-looking

laser seeker and tracker system. The
system consists of a laser illumination
detector pod, adapter control detector
(ACD), and control panel. The detector pod
is attached to an adapter pylon and weighs
32 pounds (FIGURE 3-6). The TISL system
function is to search for coded laser
energy reflected from a target illuminated
by a coded laser designator, to lock on and
track, and to provide a target location
indicator to the aircraft avionics systems.
The target location indicator is presented
on the head-up display (HUD) and/or the
attitude director indicator (ADI).
AN/PAQ-l LASER TARGET

DESIGNATOR (LTD)
The LTD (FIGURE 3-7) is a snub-nosed,
rifle-like laser designator weighing
3-10
T.O. 1—1M—34
approximately 16 pounds. It is used by a forward observer to designate targets,

The laser energy can be used to designate for LGBs or to illuminate the target for
PAVE PENNY equipped aircraft. (See FIGURE 3-10 for system parameters.)
AN/PAQ-1 LTD
FIGURE 3-7
NOTE
Continuous operation is limited to 1 minute

to prevent overheating of the LTD battery.
3-11
T.O. 1—IM—34
AN/PAQ-3 MULE AN/PAQ-3 MODULAR

UNIVERSAL LASER
EQUIPMENT (MULE)
The MULE (FIGURE 3-8) laser designator/
rangefinder is a precision target loca
tor for conventional artillery. It
furnishes range, azimuth, and elevation
data on moving and stationary targets.
It can be used by forward observers to
designate the target. The laser energy
can be used to designate for LGBs or to
illuminate the target for PAVE PENNY
equipped aircraft. With an AN/TAS-4
night sight added, the system can oper
ate under reduced visibility conditions.
The MULE weighs 38.5 pounds. (See FIG
URE 3-10 for system parameters.)
GROUND OR VEHICULAR
LASERLOCATOR DESIGNATOR
(G/VLLD)
G/VLLD
The G/VLLD (FIGURE 3-9) is a precision
target locator and detector. It fur
nishes range, elevation, and azimuth of
moving and stationary targets. Laser
energy can be used to designate for LGBs
or to illuminate the target for PAVE
PENNY equipped aircraft. It may be used
by forward observers or mounted on
vehicles and, with the attachment of an
AN/TAS-4 night sight, it is operational
under reduced visibility conditions.
The unit and tripod assembly weigh 61
pounds. See FIGURE 3-10 for system
parameters•
A/A 37U-15 TOW

TARGET SYSTEM
The A/A 37U-15 tow target system (FIGURE
3-11) consists of a tow reel pod, a tow
reel, a boom and launcher for installing
the TDU-10/B, and facilities for incor
porating a parachute recovery system for
the target. The tow system has the
3-12
T.0.1—1M—34
LTD,' MULE,'__G/VLLD SYSTEM PARAMETERS

*________________________
DESIGNATION AND RANGEFINDING LTD MULE G/VLLD
Designation range - Stationary target (2.7) (5) (3.8) (7) (4.9) (9)
(NM) (km)
Designation range - Moving target (NM) (km) (1.9) (3.5) (2.7) (5) (3.5) (6.5)
Minimum target size (meters per kilometers 0.50 0.25 0.13

of range). Size = 2 x range x tan (B/2)
Standard target size (meters) 2.3 by 2.3 2.3 by 2.2 2.3 by 2.3
Beam divergence, B, maximum (microradians) 500 250 130
MISCELLANEOUS
Setup time (minutes) 0 <3 <5
CODING
Type PRF PRF PRF
Limits (pulses/second) 9 to 20 9 to 20 9 to 20
OPERATOR MANNING
Transportation (No. of personnel) 1 2 2
Operation (No. of personnel) 1 1 1
TRANSMITTER PERFORMANCE
Laser type Neodymium Neodymium Neodymium

(YAG) (YAG) (YAG)
Wavelength 1.06 1.06 1.06
Pulse width (nanoseconds) 10 to 30 15 to 25 15 to 25
Emitted energy (millijoules) >80 >80 >100
Pulse repetition frequency - Nominal 10 to 20 10 to 20 10 to 20

(pulses/second)
Beam divergence (microradians) 500 250 130
Diameter of output beam (inches) 2 3 4
FIGURE 3-10
3-13
T.O. 1—1M—34
following capabilities: target launch, cable reel-out, tow, and cable cut. Normal
aircraft conventional weapon controls are used for these functions.
BOOM AND LAUNCHER

The boom and launcher, attached to the side of the adapter, provide mounting facili
ties for the tow target. The boom and launcher hold the target until launch. A
nose guide channel holds the nose of the target and keeps the target stable during
flight.
PARACHUTE RECOVERY SYSTEM

A parachute recovery system may be used to recover the tow target. The parachute
and canister are attached to the aft end of the pod by cloth tape. The cable is
attached to the parachute canister which, in turn, is attached to a 15-foot nylon
rope. The rope is attached to a bridle loop cable on the tow target. When cut, the
falling cable drags behind the target, causing the parachute canister to tumble 180
degrees. The canister reversal allows the wind pressure to move aerodynamically
operated levers which release the canister lid. The lid acts as a drogue and
deploys the recovery parachute.
TOW REEL
The tow reel, mounted in the center section of the tow reel pod, is a one-way reel
capable of carrying approximately 2,300 feet of 11/64-inch cable or 5,000 feet of
1/8-inch cable. Cable reel-out speed is controlled by a self-energized inertial
brake acting on the one-way wheel drum. The brake is operated by a centrifugal
force built up in flyweights on the drum. A duct admits ram air through the nose of
the pod to cool the tow reel braking unit.
TOW TARGET OPERATION

The weapon release button is used to launch the target and to cut the tow cable.
When required enabling is accomplished, the target is launched and the cable is
completely reeled out by pressing the weapon release button once. When the mission
is complete, the tow cable is cut by pressing the weapon release button a second
time. The first time the weapon release button is pressed, a rotary solenoid
releases the target. When the weapon release button is released, the rotary sole
noid shifts a transfer switch to the cutter circuits. The cable cutter is operated
by an explosive squib. An emergency cutting circuit is available.
TDU 10/B TARGET (DART)

The TDU-10/B target (FIGURE 3-11) consists of four fins, or wings, mounted together
to form a dart-like shape. A bridle cable loop and a 15-foot nylon rope form a
leader assembly between the tow cable and the target. The bridle loop is attached
to the target, and the nylon rope attaches to the reel cable and the bridle loop.
The rope provides a dampening effect for the target during launch. While the target
3-14
T.O. 1—1M—34
A/A 37U-15 TOW TARGET SYSTEM

MA-4B0MB
RACK
SWAY BRACES
TOW REEL POD
DARTTARGET
GUIDE IN SLOT
TDU-10/B TARGET (DART)
CHARACTERISTICS
WEIGHT:
COMPLETE SYSTEM (2300 FT OF
11/64 IN. CABLE AND
TDU-10/B INSTALLED)845 LB
EMPTY POD AND
ADAPTER ONLY 521 LB
CABLE 153 LB
TDU-10/B 171 LB
LENGTH:
BOOM AND LAUNCHER 11 FT
TD U-10/B 16 FT
TDU-10/B WINGSPAN 5 FT
FIGURE 3-11
3-15
T.O. 1—1M—34
is stowed s the slack in the bridle cable and nylon rope is lockwired and taped to
the target fins. This prevents the cable and rope from whipping during flight and
causing damage to the target. When the target is launched, the lockwire and tape
pull loose.
A/A 37U-33 AERIAL GUNNERY TARGET SYSTEM (AGTS)

The AGTS is a recoverable, aerial gunnery tow target, equipped with a real-time
acoustical scorer. The target can be towed at airspeeds up to 500 KCAS (or 0.9
mach), altitudes up to 35,000 feet, and acceleration forces up to 5 g. The target
system has two major subassemblies (FIGURE 3-12):
1. AN/RMK-33/A 37U-33 Tow Set, aerial target
2. AN/TDK-36/A 37U-33 Target Set, aerial towed.
A receiver antenna and receiver are in the tow set. All other components are in the
target set. Operation of the target system includes deployment, scoring, an<;
release.
TARGET DEPLOYMENT
As the target falls from the aircraft, the tow cable is extracted from the tow set.
When the tow cable reaches full length, it forces the tow arm forward. This causes
power to be supplied to the transmitter and allows deployment of the tetraplane.
Target deployment is limited to an airspeed of 220 to 250 knots calibrated airspeed
(KCAS), 1,000 to 25,000 feet altitude, and level flight. Deployment normally is
accomplished in 15 seconds. Target deployment is recommended at an altitude of
18,000 feet or below to reduce deployment shock on the tow cable.
SCORING
Real-time scoring of rounds fired at the target is achieved through acoustical
scoring. A microphone housed in the nose of the target senses the shock wave of a
passing projectile. The acoustical scoring system is capable of accurately scoring
20mm projectiles passing through two spherical zones, 2 meters forward of the nose
of the microphone (FIGURE 3-12). Two sets of scoring zones are selectable. One has
an inner radius of 2 meters and an outer radius of 3 meters. The other (only avail
able at 20,000 feet and below) has an inner radius of 3 meters and an outer radius
of 5 meters. The magnitude of the acoustical disturbance is a function of air den
sity; therefore, the scoring altitude must be manually set in the control panel.
CABLE RELEASE
Recommended cable release conditions are 800 to 1,000 feet AGL at an airspeed of 220
to 250 KCAS in level flight. A special wire bundle between the tow set and the
pylon is used. There is a backup system for the nose and for the tail arm cir
cuitry, but it will activate both cable releases in the event of dual carriage. An
electric motor opens the hook to* release the cable in less than 3 seconds. Therefore,
the bomb button should be held pressed for 3 seconds, for cable release.
3-16
T.O. 1-1M-34
A/A 37U-33 AERIAL GUNNERY TARGET-SYSTEM (AGTS)
RMK-33/A
TOW SET
LATEST CONFIGURATION
HAS CABLE TIED AT TWO
ATTACH POINTS
TOW SET
AN/TDK-36/A
TARGET
FIGURE 3-12 (Continued)
3-17
T.O. 1—1M“34
TOW SET ON
AIRCRAFT STATION
TARGET RELEASED
TARGET SET
5 FT
18 FT
1 FT
TOW CABLE
1640 FT
(500 METERS) 7 FT
TETRAPLANE DEPLOYS
WHEN TOW CABLE
REACHES FULL LENGTH
10 IN.
MICROPHONE TRANSMIT ANTENNA
1. POWER SELECTOR
2. INNER SCORING WINDOW
3. OUTER SCORING WINDOW
(Total inner and outer zone
hits.)
4. RESET BUTTON
5. ALTITUDE SELECT
6. FIELD SELECT
7. RECORDER RECEPTACLE GUNNERY TARGET CONTROL PANEL
CHARACTERISTICS
RMK-33/A TDK-36
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 357 LB 107 LB

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 8 FT 7 FT
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 IN. 10 IN.
SUSPENSION LUG SPACING_ _ _ _ _ _ 14 IN. 14 IN.
FIGURE 3-12 (Concluded)
3-18
T.O. 1-1M-34
RMK-33/A AERIAL TARGET TOW SET

The RMK-33/A tow set is 14 inches in diameter, approximately 8 feet long, and weighs
357 pounds fully loaded (FIGURE 3-12). Although not normally released during
flight, it can be jettisoned in emergencies. Carriage of the RMK-33/A does not
cause any adverse flight characteristics. No special procedures are required for
takeoff, but pretakeoff asymmetric trim is required.
The tow cable contained in a cable charger. The cable charger is a cylindrical con
tainer that slips into the rear of the tow set and locks into place. The tow cable
is a nylon rope 1,640 feet (500 meters) long.
TDK-36/A TOWED AERIAL TARGET SET

The TDK-36/A target set (FIGURE 3-12) has an aluminum body with replaceable nose
cone and fins. The target has a tow arm for the tow cable attach point and 14-inch
suspension lugs. The target is 10.2 inches in diameter and weighs 107 pounds. The
tow cable is routed forward along the surface of the tow set, locally secured to the
front with breakaway cord, and then attached to the tow arm of the target.
MICROPHONE
The microphone is housed in a protective target head. A protective cover separates
from the nose during target deployment.
TETRAPLANE
The tetraplane is used for visual aid. The primary material of the tetraplane is
nylon mesh with a folding crossarm structure and metallic radar reflector.
GUNNERY TARGET CONTROL PANEL

The control panel (FIGURE 3-12) includes a switch for turning the power (PWR) on, a
receptacle for plugging in a recorder, a reset button, and dials for selecting
altitude and scoring zones. After turn-on, the altitude and scoring zones are
selected by rotating the knob marked FIELD to either position 1 for 2-meter inner
and 3-meter outer scoring field, or position 2 for a 3-meter inner and 5-meter
outer scoring field.
The digital readout on the inner and outer windows provide a cumulative count of
hits recorded. The inner scoring window displays the number of projectiles passing
through the inner firing zone. The outer scoring window displays total inner and
outer zone hit count. The RESET button causes the display to show 88 in each window
(to check display lights) and then returns the display count to zero.
The scoring windows also display incorrect setting information. If the 3-5 zone is
selected with an altitude above 20,000 feet set, the inner and outer display windows
show EE, indicating an imcompatible scoring setup has been selected. In addition,
the scoring display will flash whenever signal strength has been lost from the
3-19
T.O. 1—IM—34
transmitter. The scoring function remains active, and scoring will continue imme
diately if signal strength returns. Flashing can be stopped by pressing the reset
button.
AN/ALQ-119(V) ECM POD

The AN/ALQ-119(V) ECM pod is of modular construction, with each module self-
contained in an integral pod shell and gondola. The pod is carried externally and
is currently available in two versions, the AN/ALQ-119(V)-15 and AN/ALQ-119(V)-l7.
The AN/ALQ-119(V)-15 pod contains low band and mid/high band modules (FIGURE 3-12).
The AN/ALQ-119(V)-17 pod contains the mid/high band module only (FIGURE 3-13).
The AN/ALQ-119 has a closed-loop, circulating-liquid cooling system.
CHARACTERISTICS
(V)-15 (V)-17
WEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 576 LB 406 LB

LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ 11 FT 11 IN. 9 FT 7 IN
WIDTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 12 IN. 12 IN.
HEIGHT_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 21 IN. 21 IN.
SUSPENSION LUGS_ _ _ _ _ _ 30 IN. 30 IN.
FIGURE 3-13
3-20
T.O. 1—1M—34
The AN/ALQ-119 ECM pod should not be operated

on the ground when ground personnel are
within 6 feet of the pod.
H CAUTION
The AN/ALQ-119 should not be operated on the

ground in any transmit position in excess of
10 minutes in any 1 hour without a cooling
unit connected and operating.
CONTROL INDICATORS
The AN/ALQ-119 pod can be controlled by the C-9492A, C-6631, C-6175, or the C-7854
control indicators. The C-6175 is the nomenclature given to two miniature C-6631
indicators, and the C-7854 is a modified C-6631. The operation of the C-6175 and
C-7854 control indicators is identical to that of the C-6631. The control indica
tors are used to turn the system on, enable (activate) preset groups of techniques,
and display system status. The C-9492A control, being more versatile than the
C-6631, can mix techniques from preset groups and also provide a more detailed
status display.
C-6631 CONTROL PANEL

The AN/ALQ-119 can be programmed for three different combinations of jamming techni
ques that are selectable in flight by the XMIT-1, XMIT-2, and BOTH positions on the
C-6631 control indicator (see FIGURE 3-14). C-6631 control and fault indications
are explained in the following paragraphs.
1. Operate Knob. This knob selects the mode of operation as follows:
a. OFF - The AN/ALQ-119 pod is off.
b. STBY “ Puts the AN/ALQ-119 pod in standby status. STBY 1 and STBY 2
lamps illuminate after a 200-second warmup delay.
c. XMIT-1 - The AN/ALQ-119 pod transmits a preselected jamming program;

generally an all-repeater program. XMIT-1 lamp illuminates. STBY 1 lamp is off.
STBY 2 lamp illumnates.
3-21
T.O. 1-1M-34
C-6631/ALQ-119 CONTROL PANEL
OPERATE KNOB STANDBY INDICATOR LAMPS (WHITE)
OVERLOAD INDICATOR LAMP (RED)
FIGURE 3-14
d. XMIT-2 - The AN/ALQ-119 pod transmits a second preselected jamming pro

gram. The XMIT-2 lamp illuminates and the STBY 2 lamp is off. STBY 1 lamp
illuminates.
e. BOTH - The AN/ALQ-119 pod transmits a third preselected jamming pro

gram. XMIT-1 and XMIT-2 lamps illuminate. STBY 1 and STBY 2 lamps are off.
2. RESET Button. When depressed, reset places AN/ALQ-119 into standby mode
until the button is released. It is used for a look-through period to have an
unobstructed look at the radar warning system or to clear temporary pod malfunc
tions. If fault remains, recycle the pod to OFF and immediately back to operate.
If the fault still remains, turn the pod OFF for 30 seconds, then back to STBY.
When the pod completes a 3-minute warmup, turn the pod back to operate. If the
malfunction fails to clear, as indicated by fault lights, the equipment should be
turned OFF.
3. STBY 1 Lamp. This is a white lamp that illuminates (after a 200-second

warmup delay) when the operate switch is set to STBY. The light goes off when the
operate switch is set to XMIT-1 or both. The light illuminates when XMIT-2 is
selected, indicating that the XMIT-1 circuits are in standby.
4. STBY 2 Lamp. This is a white lamp that illuminates (after a 200-second

warmup delay) when the operate switch is set to STBY. The light goes off when the
operate switch is set to XMIT-2 or BOTH. The light illuminates when XMIT-1 is
selected, indicating that XMIT-2 circuits are in standby.
3-22
T.O. 1-1M-34
5. XMIT-1 Lamp. This is a green lamp that illuminates when the operate switch
is set to XMIT-1 or BOTH. The STBY 1 lamp is off.
6. XMIT-2 Lamp. This is a green lamp that illuminates when the operate switch
is set to XMIT-2 or both. The STBY 2 lamp is off.
7. Flashing XMIT-1 or XMIT-2 Lamp. When a XMIT-1 or XMIT-2 light flashes at a

1-Hz rate, high-band faults are indicated.
8. Overload Lamp. This red lamp flashing at a 1-Hz rate indicates low-band
fault.
9. AI Lamp. This red lamp flashing at a 1-Hz rate indicates midband fault.
C-9492A CONTROL PANEL

The C-9492A control panel is designed to control an AN/ALQ-119 pod, or to control an
AN/ALQ-119 pod with reduced flexibility and one or two analog control-type systems
that would normally be controlled by a C-6631 (e.g., AN/ALE-38 chaff pod). The
front panel of the C-9492A contains eight pushbutton switches and two toggle switches
to control the AN/ALQ-119 pod (see FIGURE 3-15). C-9492A control and fault indica
tions are explained in the following paragraphs.
C-9492A/ALQ-119 CONTROL PANEL
FIGURE 3-15
3-23
T.O. 1-1M-34
1. Power Switch. The power switch is a three-position, positive-locking

toggle switch. In the OFF position, all power is removed from the control panel and
the AN/ALQ-119 pod. The STBY position puts the AN/ALQ-119 in standby status and/or
initiates a 3-minute warmup period. After warmup, the "S" in button S8 should come
on to indicate the system is ready for operation. The OPR position allows all
control indicator circuits to operate and the pod to transmit jamming programs. The
selection of jamming programs is determined by the XMIT toggle switch and/or the
eight pushbuttons, SI through S8. Pushbuttons will come on to indicate that OPR has
been selected.
2. XMIT switch. The XMIT switch is a three-position toggle switch with posi
tive locking for each of its three positions. It functions when the power switch is
in OPR. Position 1 places the system in mode 1 operation. Additional jamming func
tions are available by depressing pushbuttons. Position 2 places the system in mode
2 operation. Additional jamming functions are available by depressing pushbuttons.
Position 3 places the system in mode 3 operation.
3. Pushbuttons. The SI through S7 buttons are push-to-engage and push-to-

release. Each button has an alphanumeric symbol in the upper right quadrant. All
other dots and symbols are nonfunctional. The alphanumeric symbols will come on
when the power switch is in OPR and the AN/ALQ-119 is operational. These symbols
will not come on if the appropriate fault lights are lit. The "A” symbol comes on
to indicate the button is depressed. The S8 button provides an alternate jamming
program in XMIT-1. It has no effect in XMIT-2 or XMIT-3. The "S" comes on to indi
cate the AN/ALQ-119 is in standby. The ”L,” ”M,” and ”H” symbols come on to indi
cate faults in the low, medium, and high bands. The "L” will remain on after warmup
when the AN/ALQ-119(V)-17 pod is loaded.
4. DIM control. The DIM control adjusts the intensity of the lights inside the
eight pushbutton switches. Edge lighting is controlled by the console lights
rheostat.
5. RESET button. When depressed, the RESET button places the AN/ALQ-119 into
standby mode until the button is released. It is used for a look-through period to
have an unobstructed look at the radar warning system or to clear temporary pod
malfunctions. If the fault remains, recycle pod to OFF and immediately back to
OPR. If the fault still remains, turn the pod OFF for 30 seconds, then back to
STBY. When the pod completes a 3-minute warmup, turn the pod back to OPR. If the
malfunction fails to clear as indicated by fault lights, the equipment should be
turned off.
6. BIT button. When depressed, the BIT button allows a built-in-test of about
80 percent of the C-9492A. It causes all pushbutton lights to come on, but has no
effect on operation of the AN/ALQ-119 pod. The BIT button can be activated at any
position of the power switch except OFF.
AN/ALQ-119 POD PREFLIGHT SYSTEM CHECK

The AN/ALQ-119 pod preflight system check can be accomplished any time after power
is applied to the aircraft. Since maintenance personnel do not activate the pod
once it is loaded on the aircraft, this check will provide aircrew confidence and
ensure that all the programs set into the pod are activated and thus self-tested
3-24
T.O. 1—1M—34
by the fault detect and system monitor capability of the C-9492A control indicator.
Refer to appropriate aircraft Dash 34 for preflight system checks.

GENERAL DESCRIPTION
The AN/ALQ-131(V) (FIGURE 3-16) is an advanced electronic countermeasures (ECM) pod
design. It provides an aircrew-activated, computer-controlled ECM pod with improved
jamming performance, growth potential, and maintainability. The AN/ALQ-131 is modu-
larly constructed for multiple band capability and ease of maintenance. FIGURE 3-16
illustrates the system’s modularity and reconfiguration capability.
Cooling for the AN/ALQ-131 is provided by an I-beam (hardback) structure that houses
a Freon-to-ram air cooling system. The I-beam structure is composed of individual
sections that correspond in length to the equipment canisters. The modular
canisters housing the AN/ALQ-131 electronic components are mounted to both sides and
the bottom of the I-beam hardback and are easily removable for maintenance.
Operation of the AN/ALQ-131 is controlled by a digital computer in the pod. The data
that define the pod’s jamming techniques are specified on a punched tape called the
Blue Tape. A Blue Tape selected for a particular mission can be loaded into the
portable memory loader verifier (MLV) at the field shop. The MLV can then be used to
program the AN/ALQ-131 while the pod is installed on the mission aircraft. After
loading the pod’s computer memory with the new Blue Tape data, the MLV verifies that
the Blue Tape data have been correctly loaded. Flight line reprogramming can be
accomplished on one pod in approximately 15 minutes.
SYSTEM OPERATION
CONTROL PANEL-GENERAL
Cockpit control of the AN/ALQ-131 is achieved using the C-9492B or the C-6631
control panel (FIGURES 3-17 and 3-18). The C-9492B provides the most flexibility
for the operation of the AN/ALQ-131. Either control panel controls pod operation
and has the following common characteristics:
1. Power Switch. The power switch is a three-position, psitive-locking toggle

switch. In the OFF position, all power is removed from the control panel and
AN/ALQ-131 pod. The STBY position places AN/ALQ-131 into standby and/or initiates a
3-minute pod warmup. During warmup, ”F” lights will be on under buttons 4 and 5,
and a ”L0" light will be on the ALT button. After warmup, ”F” lights should go out
and ”S” lights come on, indicating bands 4 and 5 are ready to transmit. ”S” lights
on buttons 1, 2, and 3 will never come on, indicating bands 1, 2, and 3 are not in
the ’’shallow” pod. The OPR position enables the pod to transmit jamming programs®
Program selection is determined by the XMIT switch and/or pushbuttons.
2. XMIT Switch. The XMIT switch is a three-position toggle switch with

positive-locking in each of its three positions. This switch functions when the
power switch is in OPR.
3-25
T.O. 1- 1M- 34
AN/ALQ-131(V) ECM PODS
(LOW DRAG)
(BANDS 4 AND 5)
DEEP CONFIGURATION
(BANDS 3.4, AND 5)
CHARACTERISTICS
WEIGHT 535 LB
LENGTH 9 FT 3 IN.
HEIGHT 14 IN.
SUSPENSION LUG SPACING
FIGURE 3-16
3-26
T.O. 1—IM—34
FIGURE 3-17
a. Position 1 places the system in the XMIT-1 mode of operation and acti
vates a set of preset jamming techniques* Buttons 1 through 5 disable. If pushed
in, ”A” lights will not come on. ”T” lights on buttons 3, 4, or 5, or any com
bination, could come on, indicating bands 4 and/or 5 are in a transmit condition.
b. Position 2 places the system in the XMIT-2 mode of operation and acti
vates a second set of preset jamming techniques. Button operation and light indica
tions are the same as those for XMIT-1.
c• Position 3 places the system in the XMIT-3 mode and requires one or
more of the pushbuttons 1 through 5 to be depressed. When so selected, a preset
jamming technique can be activated. In XMIT-3, when any button (1 through 5) is
depressed, the "A" light will come on, indicating only that it is selected. Any
time band 4 or 5 is activated in the jamming program, the "T" light in the respec
tive button will come on whether the button has been depressed or not.
3. RESET Button. When depressed, the RESET button momentarily changes poa
status from operate to standby. Pod malfunctions and faults discovered by continu
ous centrally integrated test system (CITS) may be corrected, but faults discovered
by interruptive CITS will not be corrected. The appropriate "F" light will go out
if the fault is cleared.
C-9492A CONTROL PANEL
BIT Button
The BIT button is depressed and held for 3 seconds. When depressed, the system runs
an interruptive CITS and an in-depth self-test of each pod function. If depressed
3-27
T.O. 1-IM-34
when the power switch is set to STBY, high voltage is not applied to the bands and
energy is not radiated from the pod. If depressed with the power switch in OPR, a
test is conducted on the high voltage applied to the bands and power is radiated
from the pod antenna.
Do not perform BIT check on the ground in

OPR, unless required by maintenance person
nel. Ensure all ground personnel are well
clear of aircraft before initiating test.
This CITS test requires 30 seconds to perform, and jamming is interrupted during
this period. The ”C” light under the FRM button will come on during the test, indi
cating CITS is in progress. A lamp test on the control indicator is also performed.
NOTE
Crew activation of interruptive CITS should

be routinely accomplished twice during each
mission, regardless of fault indications, to
provide an interruptive CITS history for use
by maintenance technicians. Recommend CITS
be performed near the beginning and the end
of each mission.
Numbered Pushbuttons
The numbered (1 through 5) pushbuttons operate only with the XMIT-3 mode of opera
tion and are inoperative in XMIT-1 and XMIT-2. XMIT-3 with none of the buttons
depressed will place the pod in standby (silent mode). Depressing any button, 1
through 5, in the XMIT-3 mode will direct the pod onboard computer to initiate new
jamming techniques in the appropriate bands and channels as specified in each Blue
Tape. If more than one button is depressed on the control panel (for example, but
tons 1 and 4), a hybrid jamming program will be initiated in the pod. This new
program will be composed of jamming techniques associated with the highest priority
threats identified in the Blue Tape for both buttons 1 and 4. In general, multiple
buttons should not be depressed unless the Blue Tape loaded in the pod has been
expressly designed for this purpose.
3-28
T.O. 1—1M—34
NOTE
Premission briefings should define when

XMIT-3 multiple button mode is required.
Formation and Special Buttons

Formation (FRM) and special (SPL) buttons have unique priority characteristics.
Depressing the FRM button will override all other transmit modes, i.e., XMIT-1 and
XMIT-2. For example, XMIT-3 with button 1 and FRM depressed will result in only the
set of jamming techniques specified for the FRM button. SPL also has override capa
bilities and overrides all modes, i.e., XMIT-1 and XMIT-2, or XMIT-3 with any button
depressed including FRM. In other words, if the pod is in operate, depressing SPL
will set the SPL jamming techniques specified on the Blue Tape for SPL, regardless
of the mode switch position.
Altitude Button
The altitude (ALT) button is active in any operational mode and permits crew selec
tion of two altitudes modes. Depressing the ALT button activates the high mode and
illuminates the HI symbol; releasing the button illuminates the LO symbol. The ALT
button position controls two pod functions: the pod’s fore and/or aft transmit
antenna tilt angle and the priority of jam techniques associated with each threat.
The specific antenna tilt angles and threat priorities are specified on each Blue
Tape •
Pushbutton Symbology
Each pushbutton on the C-9492B control panel has from one to four symbols that illu
minate under the following conditions:
1. Symbol ”A” indicates that the affected pushbutton has been depressed. The
”A” has no direct connection with transmitting in a particular band.
2. Symbol ”S” indicates that the band reflected by the button number is in
standby mode; i.e., an illuminated ”S” on button 4 indicates that band 4 in the pod
is in standby. An ”S” symbol should be expected when the pod has timed in and is in
STBY in XMIT 3 with no buttons pressed, or if the Blue Tape requires no jamming out
put in the band indicated by the illuminated button.
3. Symbol ”T” indicates that the band reflected by the button number is trans
mitting; i.e., an illuminated ”T” on button 3 indicates that band 3 is transmitting.
4. Symbol ”F” indicates that a fault has been discovered in the indicated band
by CITS. Aircrew reaction: When an ”F” light illuminates as a result of continuous
CITS, the crewmember should immediately depress the RESET button for 1 to 5 seconds
and release. If the fault remains, two options exist. If a 30-second interruption
in jamming can be tolerated, the BIT button should be depressed to initiate
3-29
T.O. 1—1M—34
interruptive CITS, which would store the fault in pod memory. The second option is
to try an alternate jamming mode. Turning the pod off and back to operate is not
recommended, because the "F" light may go out but the fault may remain.
Symbol "HI-LO" is displayed only on the ALT button and, as discussed previously, it
indicates that the high-* or low-altitude mode has been selected. LO will be
displayed until the power switch is placed in the OPR position.
Symbol "C" is present only on the FRM button. The "C" light illuminates when the
BIT button has been depressed by the crewmember and remains illuminated while
interruptive CITS is in progress.
NOTE
Jamming transmission is interrupted while the

"C" light is illuminated. The interruptive
CITS program requires approximately 30
seconds for completion.
Symbol "RP" and "RG" are present only on the SPL button and, if illuminated, indi
cate that the receiver-processor or the ram air turbine generator has failed. "RP”
and ”RG” have no functions in current AN/ALQ-131 pods.
Symbol "IC" (interface control) on the SPL button indicates that the pod computer or
the computer memory has failed. Aircrew reaction: (1) Do not change jamming mode
and/or button; (2) do not initiate interruptive CITS; and (3) do not depress the
reset button until all mission requirements have been met. Rationale: If the pod
is set up and operating properly prior to the computer fault, there is a good possi
bility that the pod will remain in an acceptable configuration if it is not directed
to change by the faulted computer. When mission requirements have been met, BIT is
depressed to record CITS data and attempt to clear the fault.
C-6631 CONTROL PANEL

The AN/ALQ-131 pod can be controlled with the C-6631 control indicator (FIGURE
3-18). XMIT-1 and XMIT-2 operate identically to the XMIT-1 and XMIT-2 of the
C-9492B. The C-6631 BOTH position will select the jamming mode programmed under the
SPL button of the C-9492B. Only one altitude mode is available when using the
C-6631. This is programmed in the aircraft tape (part of the Blue Tape) and can be
programmed for high or low altitude.
Light Indications
STBY 1 and STBY 2 will come on after the 3-minute time-in. During this period, the
overload lamp will be illuminated. This will go out when the 3-minute time-in
is complete. When XMIT-1 is selected, the XMIT-1 lamp will illuminate, and the
STBY 1 lamp will go out. XMIT-2 operation is identical. When both is selected, the
3-30
T.O. 1- 1M-34
C-6631/ALQ-131 CONTROL PANEL
OPERATE KNOB STANDBY INDICATOR LAMPS (WHITE)
OVERLOAD INDICATOR LAMP (RED)
FIGURE 3-18
XMIT-1 and XMIT 2 lamps will be illuminated, and the STBY 1 and STBY 2 lamps will go
out. Band 3-4-5 and interface control (IC) fault will illuminate the overload lamp
and Band 1-2, ”RP”, ”RG”, and "IC” faults will illuminate the airborne intercept
(AI) 1amp•
Interrupt!ve CITS
The STBY interruptive CITS will be conducted each time the control indicator is
switched from OFF to STBY. An operate (XMIT) interruptive CITS will be conducted
once when the pod has gone through a time-in sequence and is placed in a XMIT mode.
Operate CITS will not be conducted again until the system is turned off for more
than 10 seconds and timed-in again.
Fault Summary
A fault in Band 3, 4, or 5 will be displayed by the overload lamp. "IC” faults will be
displayed by both the overload lamp and the ”AI” light. Band 1-2 and ”RP-RG" faults
will be displayed by the AI light.
Antenna Modules
The forward and aft transmit antenna modules each contain a Band 3, 4, and 5 trans
mit antenna. The receive antenna module located on the bottom pod contains six
3-31
T.O. 1—1M—34
receiver antennas: two for each band, one pointed forward, and the other pointed
aft. Refer to appropriate classified aircraft Dash 34 for antenna coverage.
Transition Module
The transition module section provides the mechanical and aerodynamic transition
from the forward radome to the canister housing. The transition module contains the
air inlet for ram air, the electromagnetic interference (EMI) filters, and the power
relays.
Interface and Control (IC) Module
The IC module provides control of system modes of operation and performs the major
system management functions. The IC module has the capability to activate and
control Band 3, 4, and 5 transmitter jamming techniques. It generates the various
jamming waveforms required for the operation of each band and serves as a communica-
tions center for all critical data flow between modules, with a special interface
provided for the control panel.
AN/ALQ-131 JAMMING TECHNIQUES

The basic ECM techniques available can be grouped into three general categories:
noise, repeater, and transponder. Each of the bands in the AN/ALQ-131 offers the
operator some combination of two or three of these categories.
NOISE
Jammer transmission is independent of the reception of a radio frequency (RF) signal

from the threat environment. The jamming signal originates from a noise generator
within the jammer equipment. The resulting signal, which may or may not have decep
tion modulation impressed upon it, is transmitted at rated power.
REPEATER
Jammer transmission is initiated by the reception of an RF signal from the threat
environment. In general, the received signal is amplified (at constant gain), has
amplitude and/or frequency modulation impressed upon it, and is subsequently re
transmitted to the threat environment. The amplitude modulation provides angle
deception, and the frequency modulation provides velocity deception.
TRANSPONDER
Jammer transmission is initiated by the reception of an RF signal from the threat

environment. In general, the received signal is stretched and amplified in a keyed-
oscillator RF memory circuit within the jammer, and deception modulation is im
pressed. The stretched pulse is used to implement range gate pull-off (RGPO) tech
niques. Subsequent transmission of the modulated signal is accomplished at or near
saturated power.
3-32
T.O. 1—1M—34
GUN PODS
SUU-16/A 20MM GUN POD

The SUU-16/A gun pod (FIGURE 3-19) contains the M61A1 20mm gun, a ram air turbine
(RAT) drive assembly, an ammunition feed assembly, an electrical control package,
and the ammunition drum. The M61A1 gun has six rotating barrels. Each barrel fires
once per revolution to fire a total of 6,000 rounds per minute (100 rounds per
second) when the gun is rotating at 1,000 revolutions per minute (rpm). The muzzle
velocity is 3,380 feet per second (fps). The M61A1 gun fires electrically primed,
steel-case, 20mm ammunition, M50 series. The gun pod has an ammunitiom capacity of
1,200 rounds, of which approximately 50 to 70 rounds are unusable.
^***——-^
CAUTION ;
€ The usable ammunition in the pod can be com

pletely fired out with a single burst, or
fired in short bursts; however, to reduce
possible gun damage and prolong gun life, a
single burst should not exceed 3 seconds.
® Firing bursts in the autoclear mode with less

than a 2-second interval will cause extensive
damage to the gun.
The gun has two operating modes: autoclear and nonclear. The purpose of the
autoclear mode is to remove live rounds from the firing position at the completion
of each burst. The purpose of the nonclear mode is to preclude the ejection of live
rounds from the gun and to provide immediate gun-firing when the trigger is pulled.
The RAT is extended into the airstream when electrical power is applied to the gun
pod. Electrical power is received from the aircraft, converted within the gun pod,
and used to fire the cartridge and operate the clutch/brake actuator solenoid.
Mechanical power to rotate the gun is received from the RAT; therefore, the RAT
directly controls the rate of fire. The RAT rotates at a constant speed to provide
mechanical power to drive the gun and the ammunition feed system. The speed of the
RAT is maintained at 12,000+600 rpm by a mechanical governor. Any change in rpm
will cause the governor to change the turbine blade pitch accordingly, to maintain a
constant speed. A minimum airspeed of 330 KCAS is required to drive the system at a
steady rate of 12,000 rpm. The gun can fire at lower than 330 KCAS; however, the
rate of fire will diminish. The clutch assembly transmits the power developed by
the RAT to the ammunition feed system and the gun. When the trigger is actuated, a
drive clutch is engaged by a solenoid to place a gear train in action which reduces
the 12,000 rpm to rotate the gun at 1,000 rpm, which causes 6,000 rounds a minute to
be fired from the gun.
3-33
T.O. 1—IM—34
SUU-16/A AND SUU-23/A 20MM GUN PODS
SUU-16/A RAT SUU-23/A
CHARACTERISTICS
--------------------------- SUU-16/A SUU-23/A
WEIGHT, LOADED 1693 LB-------- 1722 LB

WEIGHT, 50 - 70 ROUNDS REMAINING 1043 LB 1072 LB
LENGTH 17 FT 4 IN.
DIAMETER 22 IN.
AMMO CAPACITY_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1200 ROUNDS
(50T0 70 ROUNDS UNUSABLE)
M61A1 20MM GUN

NUMBER OF GUN BARRELS6
6000 ROUNDS PER MIN
RATE OF FIRE (6 BARRELS)
3 SEC
MAX RECOMMENDED BURST TIME
AMMO 20MM-M56E2 (HEI)
20MM - M53 (API)
20MM -M55A2 (TP)
HARMONIZATION RANGE 2250 FT
FIGURE 3-19
3-34
T.O. 1—1M—34
During a nonfiring condition, the RAT freewheels while the gun and feed system are
held fixed by the brake band. When the fire command is given, a solenoid engages
the clutch band against a drum and releases the brake band to allow the RAT to drive
the system. The ammunition drum stores the major portion of the ammunition.
During firing operation, the ammunition drum discharges the ammunition into an
endless conveyor unit which picks up each cartridge and delivers it to the gun. The
cartridges are placed into the gun where a cam-operated, sliding-bolt assembly picks
up the cartridge and carries it forward and locks it in the breech (or firing
position). The cartridge is fired as it passes an electrical contact, and the empty
case is extracted as the gun rotates toward the lower left side. The empty case (or
a dud cartridge) is extracted from the breech and ejected from the lower left side
of the pod by the case ejector with sufficient velocity to clear the aircraft.
At the end of each burst, in the autoclear mode, an automatic clearing function is
initiated which prevents the bolts from carrying the cartridges forward into their
breech position during gun deceleration.
As the gun decelerates to approximately 3,750 shots per minute, the bolts are auto
matically cleared to the rear of the gun out of the breech position. Firing voltage
remains to fire out the rounds that enter the breech prior to initiation of the
clearing action. With the bolts out of the breech, air is permitted to pass through
the gun barrel to aid gun-cooling.
Firing voltage is on the firing pin when the trigger is pulled and remains on the
firing pin for 1 second after the trigger is released. When operating in the
nonclear mode, the gun starts firing immediately when the trigger switch is pulled.
When operating in the autoclear mode, the gun starts firing after it has rotated
one-third revolution to position a cartridge in contact with the electrical firing
pin; the time required for this operation may be considered instantaneous. The time
required for the gun to obtain maximum firing rate is approximately 0.4 second for
both operating modes.
The gun stops rotating between 0.2 to 0.6 second after the trigger is released,
depending on the adjustment of the clutch and brake assembly, regardless of the
operating mode. For the autoclear mode, the gun stops firing when the clearing
action is initiated. The clearing action begins when the gun has decelerated to
approximately 3,750 rounds per minute; approximately four to six rounds will be
fired during this period. Approximately four to six live rounds will be ejected
overboard before the gun stops rotating. For the nonclear mode, the gun stops rota
ting; approximately 8 to 12 rounds will be fired during this period.
To fire successive bursts in autoclear mode, the gun must first stop rotating and
then accelerate for one-third revolution; 2 seconds should be allowed between
trigger release and next trigger pull. When operating in the nonclear mode, the
gun starts firing when the trigger is pulled, regardless of the gun rotating speed.
The gun should be operated in the nonclear mode when it is desirable to fire short
bursts with a minimum of time delay between trigger-pull and first-shot. The bolts
remain in the firing cycle when the gun is operated in the nonclear mode, to clear
the gun of live rounds. A live round remaining in the breech after a long burst in
the nonclear mode could cook off if the gun is hot. This will not cause the gun to
3-35
T.O. 1—1M—34
malfunction. When a gun malfunction occurs, the cause will most often be the
jamming of the feed system. Another type of malfunction that might occur is the
jamming of the bolt assembly operation in the autoclear mode; the nonclear mode is
not susceptible to this type of malfunction.
Complete fire-out of all ammunition is not possible; approximately 50 rounds must

remain in the feed system to maintain control of the flexible feed chute. A last
round switch in the ammunition drum stops the feed system before the last round in
the ammunition drum reaches the feed system. Firing voltage is removed by the last
round switch as if the trigger switch were released, and the autoclear clearing
action is initiated regardless of the mode selected; all cartridges are removed from
the breech.
The M61A1 gun can develop 3,800 pounds of reverse thrust when firing at its maximum •
rate. For short bursts of less than 1 second, the reverse thrust of the guns will
cause negligible movement of the pipper and, consequently, the shot pattern. The
pilot should anticipate the effect of reverse thrust and aim at the top of the
target or to the side of the target.
SUU-23/A 20MM GUN POD

The SUU-23/A gun pod (FIGURE 3-19) is similar to the SUU-16/A gun pod, except it
contains the GAU-4 20mm gun and does not have a RAT drive system. Instead, it has
an internal electric inertia start motor which accelerates the gun. With the gun
selected, the inertial start motor begins to develop operating speed when the gun is
armed. For gun pod systems with a prestart capability, a prestart cable is pro
vided which starts the SUU-23/A inertia motor. Prestarting of the inertia motor
eliminates the 20- to 30-second delay in firing.
CAUTION
To avoid inertia motor burnout, avoid select

ing this mode during ground operations or any
operations not directly involving the gun
pod.
When the trigger is squeezed, the inertia motor accelerates the gun to 5,400 shots
per minute. At 5,400 shots per minute, the motor disengages and a gas drive system
extracts gun gas from four of the six barrels to further accelerate the gun to the
maximum firing rate of 6,000 shots per minute. The maximum gun firing rate is
obtained 0.2 to 0.4 second after the trigger is pulled.
The gas drive system sustains the driving rate of the gun and linkless feed system.
The electric inertia start motor disengages but continues to run. If a malfunction
occurs (such as misfire of four or more consecutive rounds), or if the driving rate
falls below 900 rpm (5,400 shots per minute), the electric inertia start motor
3-36
T.O. 1—IM—34
en£ages to achieve firing rate, and again disengages. All data pertaining to the
SUU-16/A gun pod are applicable to the SUU-23/A gun pod except when noted.
BURST LIMITER
Some gun pods may be modified to include a burst limiter. The burst limiter can be
set by armament crew personnel when it is desired to limit the number of rounds to
be fired during one flight. The burst limiter has two controls; a burst limiter
setting knob and a burst limiter switch.
Burst Limiter Setting Knob

The burst limiter setting knob can be set from 50 to 250 rounds, in units of 5
rounds. The actual setting indicated by the posisiton of the V-notch in the knob,
may vary by three rounds, i.e., if 150 rounds is set, the limiter may be set on
either 147 or 153.
Burst Limiter Switch

The burst limiter switch has two positions; limit and no limit. With the limit
position selected, the trigger circuit is interrupted when the set number of rounds
has been fired. The gun stops firing and cannot be fired again during flight.
Therefore, the gun pod must be operated in the autoclear mode when the burst limiter
is used. If the gun pod is operated in the nonclear mode the burst limiter stops
gun firing in the nonclear mode, and the gun breech cannot be cleared of live rounds
prior to landing.
When the burst limiter is used, the gun pod

must be operated in the autoclear mode to
ensure that the gun is cleared of live rounds
in the breech prior to landing.
When the no limit position is selected, the burst limiter is removed from the gun
circuit; the gun pod then may be operated in either mode, nonclear or autoclear.
GPU-5/A 30MM GUN POD

The GPU-5/A gun pod (FIGURE 3-20) contains a GAU-13/A, 30mm, pneumatically driven,
four-barrel Gatling-type gun; a closed-loop ammunition feed and storage system; an
electronic control unit (ECU); and a precharged pressure vessel. The gun pod is
suspended from the bomb rack and can be jettisoned.
3-37
T.O. 1-1M-34
GPU-5/A 30MM GUN POD
CHARACTERISTICS
GUN_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ GAU-13/A
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 14 FT 2 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 28 IN.
WEIGHT, EMPTY_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1273 LB
WEIGHT, LOADED_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 1865 LB
AMMO CAPACITY_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 353 ROUNDS
FIRING RATE_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 2400 SHOTS/MIN
MUZZLE VELOCITY 3200 FPS
Figure 3-20
The aircraft gun fire circuit for the SUU-23 gun pod is used for the GPU-5/A gun
pod. After each burst, the gun reverses direction of rotation to clear the gun of
unfired rounds. The unfired rounds are returned to the feed system for use during
the next trigger pull. Empty cases are retained in the gun pod.
There is no cockpit indication that the gun

is cleared of live rounds.
The gun pod has one fire rate (40 shots per second) and two selectable firing modes
on the pod: combat and training. In combat mode, the gun can be fired out in one
burst (353 rounds). In the training mode, the total number of rounds fired in a
single burst is limited to 30, and the total rounds fired during a single flight is
limited to 117
3-38
T.O. 1-1M-34
Three types of ammunition are available: target practice (TP), armor-piercing incen
diary (API), and high-explosive incendiary (HEI). All cartridges are percussion-
primed. For a description of projectile functions, see 30mm Ammunition (Section I).
SUU-25C/A AND E/A FLARE DISPENSERS

The SUU-25 series flares dispensers (FIGURE 3-21) are capable of dispensing eight
LUU-2 or MJU-3 series flares, or eight LUU-l/B, LUU-5/B, or LUU-6/B markers. The
flare dispenser is designed to be returned and used for more than one mission.
There is only one difference in the SUU-25E/A and the SUU-25C/A flare dispensers;
the SUU-25E/A forward shear pins (retaining link) are visible and accessible from
outside the dispenser. This allows visual confirmation that the forward flares are
secure.
The dispenser is a tubular body of all-metal construction, consisting of four tubes

clustered and enclosed by an outer skin with a bulkhead at each end. Located at the
top center of the dispenser are two electrical receptacles for connection with the
aircraft electrical system.
Flares/markers are loaded against a compression cushion and are retained by eight
shear pins, four located in the forward section and four in the aft end. Each of
the four tubes has two breech assemblies loaded with impulse cartridges. One breech
is routed to a chamber between the forward and aft flares. The aft flare is dis
pensed first by cartridge gases creating a temporary compression chamber between the
flares. Single flare dispensing is controlled through the dispenser intervalometer,
which causes one flare to be dispensed with each release pulse. However, if the aft
munition fails its launching sequence, the forward munition firing sequence will
purge the tube, launching both munitions together. On the right side of the dis
penser, in the center section, is a jack in which a shorting pin can be inserted on
the right side of the dispenser to interrupt the electrical circuit between the two
electrical receptacles and the breeches. This pin electrically safes the dispenser.
Located in the center, on each side of the dispenser, is an access door with a notch
at the top and bottom to allow the forward retaining link shear blocks to extend
outside the dispenser (FIGURE 3-21). The retaining link assembly is designed with a
slot in which to insert a shear pin that secures the forward munition within the
dispenser tube. Information as to type of munitions loaded, fuze settings, and date
loaded is written on the side of the dispenser. The area around the lugs is rein
forced with a strongback to permit sway-bracing and forced ejection.
To confirm the SUU-25C/A dispenser is loaded with munitions, the aft end of each
tube should be checked for the bottom end of a munition with a sealing cap ring.
To confirm the SUU-25E/A dispenser is loaded with munitions, the aft end of each
tube should be checked for the bottom end of a munition with a sealing cap ring. A
manually set/remotely controlled intervalometer and breeches are located at the for
ward bulkhead.
LUU-l/B, 5/B, 6/B TARGET MARKER FLARES

The LUU-l/B, 5/B, 6/B target marker flares (FIGURE 3-22) are designed to burn for 30
minutes on the ground, providing a colored flame. It is intended that the color be
3-39
T.O. 1- 1M-34
SUU-25C/A AND E/A FLARE DISPENSERS

SUSPENSION LUGS
ACCESS DOOR
NOSE CONE
SHORTING PIN
BREECH
BREECH CAP
RETAINING LINK
AND SHEAR PINS SUU-25 C/A
INTERVALOMETER
BREECH
FIRING LEADS FORWARD
(8) SHOWN RETAINING
BREECH CAP CONNECTED LINK
SUU-25E/A
CHARACTERISTICS
FIRING LEADS
(8) SHOWN WEIGHT, EMPTY_ _ _ _ _ _ _ _ 260 LB
CONNECTED WEIGHT, LOADED_ _ _ _ _ _ _ 500 LB (APPROX)
LENGTH _ _ _ _ _ _ _ _ _ _ _ _ _ _ 8 FT
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ 14 IN.
TUBE DIAMETER _ _ _ _ _ _ _ 5 IN.
SUSPENSION LUG SPACING 14 IN. ACCESS DOOR NOTCHES
FIGURE 3-21
3-40
T.O. 1—1M—34
distinguisable in the presence of burning illumination flares. The LUU-1/B burns

with a red flame, the LUU-5/B burns green, the LUU-6/B burns maroon. The candle
burning surface is on the end connected with the parachute to reduce chances of
snuffing out the flame on ground impact. A steel suspension cable links the
parachute and the wooden suspension block located on the bottom of the candle. The
suspension cable passes through a 2.75-inch-diameter protective core in the center
of the candle, and extends 6.0 feet from the top of the candle to a point where the
cable is connected to eight 6-foot shroud lines. The parachute for the target maker
flare uses two 7.5- by 2-foot panels sewn together in the form of a plus ( + ) sign.
The parachute is designed to provide a 30-fps rate of descent and to snag in the top
of heavy foliage, making it useful in jungle areas. After flare ignition, the flare
has a rate of descent of approximately 15.0 fps.
A 5- to 30-second delay ejection fuze and a 10- to 30-second delay ignition fuze are
used for target marker flares.
When the marker is loaded in the SUU-25 dispenser, the arming lanyard extension is
removed, and a KMU-361 adapter kit is installed on the marker. An adapter arming
lanyard and the marker arming lanyard are both attached to the marker safety pin
keyring. Ejection of the marker from the dispenser pulls the adapter free of the
marker, which in turn pulls the marker safety pin and the marker arming lanyard,
arming the ejection fuze.
NOTE
During mission planning, a release altitude,

an ejection fuze setting, and an ignition
fuze setting that assure flare ignition prior
to ground impact must be selected.
The ejection and ignition fuzes must be set before loading. Upon release, the pull
on the lanyard ignites the ejection fuze. At the conclusion of the ejection fuze
delay, an ejection charge expels the candle and deploys the parachute. The ejection
charge also ignites the ignition fuze delay element. The candle is ignited at the
expiration of the ignition fuze delay.
LUU-2/B FLARE
The LUU-2/B flare (FIGURE 3-23) is a pyrotechnic illuminating device with a burn
time of approximately 5 minutes. The flare burns at an average of 2 million candle
power.
The desired free-fall distance in feet (delay time) must be set into the timer
before loading. The available settings into the timer are 500, 1,500, 3,000, 4,000,
5,000, 6,500, 7,500, and 8,500 feet.
The timer knob is removed as the flare is ejected from the aircraft, which starts
the timer. After the selected delay time, The release mechanism is tripped,
allowing the timer and cover to be ejected from the flare case by a spring. As the
3-41
T.O. 1—1M—34
LUU-l/B, 5/B, 6/B TARGET MARKER FLARES
CHARACTERISTICS
WEIGHT 26 LB
LENGTH 36 IN.
DIAMETER 4.87 IN.
FIGURE 3-22
timer is ejected, it pulls the parachute with it. Deployment of the main parachute
produces a shock force on the support cables through the ignition lanyard to rotate
a bellcrank in the ignition system, shearing a safety pin and cocking and releasing
a firing pin. The firing pin strikes and initiates a primer, which ignites boron
pellets. The boron pellets ignite a wafer of propellant, which ignites the flare
candle. Pressure buildup on flare ignition blows out pressure relief plugs in the
igniter housing, after which the flare case burns through and the ignition housing
falls free.
The flare burns for approximately 5 minutes. The average rate of descent of the
flare after parachute deployment is 8.0 fps, and the flare descends approximately
2,500 feet during the 5-minute burn time.
3-42
T.O. 1—1M—34
NOTE
At 5,000 feet density altitude, the flare

descends approximately 11.5 fps and falls
approximately 3,500 feet during the 5-minute
burn time.
The pyrotechnic candle consumes the flare housing. This reduces the flare weight,
which allows the flare to hover during the last 2 minutes of burn time. At candle
burnout an explosive bolt is initiated; this releases one parachute support cable,
causing the parachute to collapse.
When the flare is installed in the SUU-25 dispensers, a KMU-361 adapter kit (FIGURE
3-23) is installed on the flare. A 6-inch lanyard is attached from the adapter kit
to the flare timer knob key ring. Ejection of the flare from the dispenser pulls
the adapter free of the flare; this, in turn, pulls the flare timer knob from the
flare.
LUU-2/B AND LUU-2A/B FLARE

PARACHUTE DROGUE
IGNITER CANDLE DEPLOYMENT PARACHUTE DECELERATOR
PROPELLANT CABLE
TRIGGER
MECHANISM
TIMER AND
PRIMER IGNITER EXPLOSIVE RELEASE
LANYARD BOLT MECHANISM
LUU-2A/B
KNOB TIMER KEYRING
LATCH 5000 FT
SETTING SETTING (ATTACHED TO
DIAL TIMER KNOB)
FLARE
LANYARD LANYARD
LATCH KEYRING 5-IN.
LANYARD KMU-361
LUU-2/B
WHITE LINE CAP
CHARACTERISTICS
WEIGHT 29 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3 FT
DIAMETER 5 IN.
FIGURE 3-23
3-43
T.O. 1—1M—34
LUU-2A/B FLARE
The LUU-2A/B incorporates an improved timer for higher reliability and increased
flexibility. This is the only respect in which it differs from the LUU-2/B. The
feet-of-fall settings for the LUU-2A/B are 500, 1,000, 2,000, 3,000, 4,000, 5,000,
6,000, 7,000, 8,000, 9,000, 10,000, and 11,000.
FLARE DISPENSING
The flare delivery aircraft approaches the target in level flight at the preplanned
release altitude. The flare profile and parameters are illustrated in FIGURE 3-24.
Release airspeed is not a critical parameter. Release altitude is critical only

when it is desirable to have flare burnout above the ground. The flare-dispensing
table (FIGURE 3-24) provides the minimum release altitude above ground level (AGL)
that will provide flare burnout at impact. The desired burnout altitude AGL must be
added to the minimum release altitude AGL to determine the actual release altitude
AGL. The flare-dispensing table also provides the horizontal distance traveled and
the vertical drop of the flare prior to ignition. The flare ejection fuze delay
time and the flare ignition fuze delay time are set according to the mission
requirements and the data on the flare-dispensing table. To properly position the
flare at ignition; rangewind effect and crosswind offset (feet) may be determined by
multiplying the rangewind or crosswind component (knots) times 1.7 times the sum of
the ejection and ignition fuze delay settings.
AIR COMBAT MANEUVERING INSTRUMENTATION

(ACMI) SYSTEM
The ACMI system uses the combination of distance measuring equipment, airborne sen
sors, and inertial-measuring equipment to provide real-time measurement of position
and attitude of aircraft instrumentation subsystem (AIS) equipped aircraft to ground
station. The ACMI system provides a capability for (1) training and maneuvering,
(2) recognizing weapons envelopes, and (3) weapon system employment evaluation. The
ACMI system consists of instrumentation that allows radio communications and pre
sents real-time graphic and alphanumeric displays of aircraft and weapon status
data. This ACMI presentation can also be recorded and reviewed later for mission
debrief. Computer simulations of missiles are used for training in achieving weapon
firing envelopes. The ACMI system is organized into four subsystems: the tracking
instrumentation subsystem (TIS), the AIS, the control and computation subsystem
(CCS), and the display and debriefing subsystem (DDS). The AIS is the only air
borne subsystem in the ACMI system and the only subsystem described here.
NOTE
Aircrews should provide the ACMI operator

with AIS pod number and aircraft station
number prior to flight.
3-44
T.O. 1—IM—34
LUU-2A/B FLARE PROFILE
1 MINIMUM RELEASE ALTITUDE AGL REQUIRED

TO PROVIDE FLARE BURNOUT.
2 VERTICAL DROP PRIOR TO FLARE IGNITION .
3 EJECTION FUZE DELAY TIME.
4 IGNITION FUZE DELAY TIME.
5 FLARE BURNING TIME.
6 DESIRED FLARE BURNOUT HEIGHT AGL.
7 HORIZONTAL FLARE TRAVEL PRIOR TO IGNITION.
FIGURE 3-24
AIRCRAFT INSTRUMENTATION SUBSYSTEM (AIS)

The AIS pod (FIGURE 3-25) is carried on all flights utilizing the ACMI system. It
consists of an AIM-9 missile shell which contains a transponder, a digital interface
unit, an inertial reference unit, an air data sensor unit, and a digital data link
receiver and transmitter. These units measure flight data which are transmitted to
the TIS for computation of space positioning of all pod-carrying aircraft on the
ACMI range.
The AIS pod operates from standard aircraft power available from various launchers.
It receives electrical power any time that electrical power is on the aircraft. No
specific pod switches are utilized to operate the AIS pod. In addition to transmit
ting flight parameters to the ground, fire control system information is monitored
by the pod to reflect proper fire control switchology and transmit fire signals to
the ACMI computer.
3-45
T.O. 1—1M—34
AIS POD WITH AERO-3B/LAU-114A/A LAUNCHER
AER0-3B/LAU-114A/A
LAUNCHER
UMBILICAL
RECEPTACLE
AIS POD LUGS

AIS POD UMBILICAL
CHARACTERISTICS RAM AIR INTAKE
LENGTH_ 11 FT9 IN.

WEIGHT_ _ 123 LB
DIAMETER 5 IN. PITOTTUBE
FIGURE 3-25
Each ground-to-air and air-to-ground transmission consists of a digital data message

and ranging tones. The AIS pod receives an uplink ranging and data message from one
of the ground stations designated as the interrogator and returns a downlink ranging
and data message which all ground stations may receive. The downlink data message
contains aircraft attitude, velocity, and pressure data, and missile firing data.
The uplink data message contains attitude and velocity corrections for updating the
inertial reference unit data processor and pod identification.
Attitude and velocity corrections are derived in the CCS real-time filter based on
the tracking data from the TIS combined with attitude, velocity, and barometric data
downlinked from the AIS pod. These corrections are used to update the inertial
reference unit platform state, forming a closed loop between AIS, TIS, and CCS.
Current variants (FIGURE 3-26) include the T-ll, T-13, T-17, and T-20. The T-ll
utilizes a modular component design which requires a ram air intake for cooling.
The T-13, and subsequent variants, reduced pod weight 30 pounds by converting to a
five black box line-replacable unit (LRU) concept. The T-17 was developed to pro
vide AIS pod interface with aircraft electronic warfare systems (EWS). Other
features include a self-contained radar altimeter and ultra-high frequency (UHF)
3-46
T.O. 1—1M—34
uplink. The separate UHF uplink permits ACMI operators to uplink 1 of 12 prere
corded voice messages to the aircrew via the AIS pod at the press of a button. The
T-20 is the same as the T-17 pod except it does not have the UHF uplink and radar
altimeter features.
AIS POD VARIANTS
AIR FORCE VENDOR UNIQUE FEATURE

NOMENCLATURE NOMENCLATURE
AN/ASQ T-ll P3 Modular maintenance, ram air cooling
AN/ASQ T-13 P4 Five LRU concept, no cooling scoop
AN/ASQ T-17 P4A EWS interface radar, alt, UHF uplink
AN/ASQ T-20 P4AX EWS interface
FIGURE 3-26
CTU-2/A RESUPPLY CONTAINER

The CTU-2/A is a parachute retarded container used to deliver combat supplies to
ground forces (FIGURE 3-27). The container may be loaded with any equipment up to a
maximum weight of 500 pounds, provided the equipment can be loaded to maintain the
container center of gravity (CG) within allowable limits.
NOTE
The parachute system limits the delivery

speed to 450 KCAS maximum and the delivery
altitude to 300 feet AGL minimum.
The CTU-2/A consists of three basic assemblies: the fin stabilized container, an
XM5 cartridge-actuated parachute release assembly, and the parachute assembly. At
release, the initiator cable attached to the bomb rack causes detonation of the
cartridge-actuated release assembly. After a 0.3-second delay, the release assembly
ejects the tail cone and deploys the pilot parachute. The pilot parachute, in turn,
deploys the main parachute to a reefed diameter of 36 inches. Explosive cutters
then part a reefing line and initiate blossoming to full diameter. Container
descent is controlled to an impact velocity of approximately 30 fps and at a nearly
vertical impact angle.
At release, the aerodynamic stability of the loaded container is specifically depend

ent on maintaining the loaded container CG within specified limits. The appropriate
3-47
T.O. 1—1M—34
CTU-2/A RESUPPLY CONTAINER
CHARACTERISTICS
WEIGHT, EMPTY 213 LB

MAX CONTAINER LOAD 500 LB
LENGTH 8 FT 10 IN.
DIAMETER_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _21 IN.
FIGURE 3-27
3-48
T.O. 1-1M-34
authority must therefore verify that the weight and CG locations are within allow-
able limits as a function of the planned payload and release airspeed. A plot is
provided so that the aircrew may establish the CG required for a stable separation.
The chart in FIGURE 3-27 is provided to establish a CTU-2/A CG limit in order to

verify container stability at release. The chart locates the most aft allowable CG
position as a function of container payload weight and release calibrated airspeed
(CAS). The measurement is expressed as the distance between the leading edge of the
gravity center section (station 20) and the most aft CG. The allowable CG therefore
includes any point forward of the aft limit. The allowable CG is obtained from the
chart in the following manner: (1) locate the planned payload weight on the chart,
(2) project to the planned release CAS and then down to arrive at the aft limit; the
actual CG must be forward of this point.
CAUTION
If the actual CG is aft of the chart measure

ment, then the release speed and/or payload
weight must be adjusted to establish an ac
ceptable CG position. Failure to observe the
required CG limits can result in unstable
separation characteristics.
MXU-648/A CARGO POD

The MXU-648/A cargo pod (FIGURE 3-28) is a modified BLU-1 or BLU-27 firebomb shell.
It is an aluminum canister consisting of tapered nose and tail sections, and a cen
ter section with a hinged access door. The cargo pod has a reinforced strongback
for sway-bracing. Empty pod weight varies from 98 to 125 pounds, depending on type
of BLU canister used in the modification. The pod is nonjettisonable, and a maximum
of 300 pounds can be carried.
AN/DSQ-34 LASER TARGET DESIGNATOR

SCORING SYSTEM (LTDSS)
The LTDSS (FIGURE 3-29) is a portable, battery-operated, laser scoring system. The
system can be used as an aid in laser designation training or as an operational
check of laser designator equipment. The system registers laser pulses striking the
unit or a nearby target through an electromechanical counter; it transmits an
audible tone of a UHF frequency as the laser pulses are registered. The system may
be operated by ground range personnel for scoring, or left unattended when only a
tone is required.
The LTDSS consists of a remote control and a pulse detector. The remote control
assembly contains a transceiver radio, two electromechanical counters, radio control
switches, and associated wiring. The pulse detector assembly consists of a pho
tographic lens, light filter, light detector diode, and a pulse amplifier. A
3-49
T.O. 1—1M—34
■ . . • . I
MXU-648/A CARGO POD
SUSPENSION
CHARACTERISTICS
WEIGHT, EMPTY._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 98 - 125 LB

LENGTH .. ................................... 10 FT 10 IN.
DIAMETER 19 IN.
FIGURE 3-28
rechargable 28-volt nickel-cadium battery pack is mounted in the bottom of the system
container. The LTDSS weighs approximately 75 pounds.
Under no circumstances should magnifying

devices (binoculars, monoculars, etc.) be
used to view the laser designating aircraft
or the target area during periods of laser
designation. Laser light can cause permanent
and irreversible damage to eyesight.
3-50
T.O. 1—1M—34
AN/DSQ-T34 LASER TARGET DESIGNATOR SCORING SYSTEM
FIGURE 3-29
3-51(3-52 blank)
T.O. 1-1M-34
SECTION IV
AIR-TO-AIR MISSILES
CONTENTS
PAGE
MISSILE TYPES........................................................................................................................................ 4-2

TYPES OF GUIDANCE........................................................................................................................... 4-2
Lead Pursuit........................................................................................................................................ 4-3
Deviated Pursuit.................................................................................................................................. 4-3
Pure Collision...................................................................................................................................... 4-4
Lead Collision...................................................................................................................................... 4-4
Command Guidance .......................................................... 4-4
Beam Rider.......................................................................................................................................... 4-5
Constant Load Factor......................................................................................................................... 4-5
Proportional Navigation..................................................................................................................... 4-5
MOTOR TYPES........................................................................................................................................ 4-5
All-Boost............................................................................................................................................... 4-5
All-Sustain............................................................................................................................................. 4-5
Boost-Sustain...................................................................................................................................... 4-6
AIM-7 SPARROW MISSILE..................................................................................................................... 4-6
Description.......................................................................................................................................... 4-6
Air Frame............................................................................................................................................. 4-6
Guidance Section........................................................................................................ ....................... 4-6
Control Section.............................................................. 4-8
Warhead Section.................................................................................................................................. 4-8
Rocket Motor Section....................................................................................................................,. . . 4-9
Missile Operation .............................................................................................................................. 4-9
AIM-7E3 SPARROW MISSILE................................................................................................................. 4-10
AIM-7F SPARROW MISSILE..................... 4-10
AIM-7M SPARROW MISSILE................................................................................................................... 4-10
AIM-7 EXERCISE WARHEAD................................................................................................................. 4-12
AIM-7 TELEMETRY SET......................................................................................................................... 4-12
AIM-9 SIDEWINDER MISSILE............................................................ 4-12
4-1
T.O. 1-1M-34
MISSILE TYPES
A missile may be either guided or unguided (FIGURE 4-1). Unguided missiles follow
the natural laws of motion to establish a ballistic trajectory. Guided missiles may
either home to the target, or follow on a nonhoming course. Nonhoming guided
missiles are either inertially guided or preprogrammed. Homing missiles may be
active, semiactive, or passive.
MISSILE TYPES .
MISSILE
GUIDED UNGUIDED
NONHOMING HOMING
INERTIAL PROGRAMMED ACTIVE SEMIACTIVE PASSIVE
FIGURE 4-1
An active missile carries the radiation source on board the missile. Radiation from
the missile is emitted, strikes the target, and is reflected back to the missile.
The missile then is self-guided on this reflected radiation.
A passive missile uses radiation originated by the target or by some source not a
part of the overall weapon system. Typically, this radiation is in the infrared
(IR) region (Sidewinder) or the visible region (EO Maverick), but may also occur in
the microwave region (Shrike).
A semiactive missile has a combination of active and passive characteristics. A

source of radiation is part of the system but is not carried in the missile. The
source (usually at the launch point) radiates energy to the target, from which the
energy is reflected back to the missile. The missile senses the reflected radiation
and homes to it.
TYPES OF GUIDANCE
Guidance is the means by which a missile steers to, or is steered to, a target
(FIGURE 4-2). This definition included ballistic missiles, in which gravity and
other forces of nature determine where the missile will go. This is generally
referred to as ballistic guidance. All gunnery involves ballistics. For ballistic
missiles, the guidance occurs before launch in the form of prelaunch attempts to
reduce aiming errors.
4-2
T.O. 1-1M—34
HOMING TECHNIQUES
A) ACTIVE-MISSILE
CARRIES RADIATION
SOURCE
B) PASSIVE-RADIATION
SOURCE CARRIED
BY TARGET
FIGURE 4-2
For guided missiles the guidance occurs after launch. By guiding after launch, the
effect of prelaunch aiming errors can be minimized. As a result, the primary pur
pose of postlaunch guidance is to reduce prelaunch requirements. Postlaunch
guidance can be done in a number of ways (FIGURE 4-3). Some of the prominent types
of guidance are discussed in the following paragraphs.
LEAD PURSUIT
The launch aircraft directs its velocity vector at an angle from the target so that
missiles or projectiles launched from any point on the course will impact on the
target if within the range of the weapon. Note lead pursuit is flown by the launch
aircraft in conjunction with the missile trajectory.
DEVIATED PURSUIT
The missile tracks the target and produces guidance commands to establish a fixed
lead angle (X). When the fixed lead angle is zero, deviated pursuit becomes pure
pursuit. No current missile is designed to fly deviated pursuit; however, random
errors and unwanted bias lines often result in a deviated pursuit course. Also,
quite often the launch aircraft flies a deviated pursuit course.
4-3
T.O. 1-1M-34
TYPES OF GUIDANCE
DEVIATED
PURSUIT
FIGURE 4-3
PURE COLLISION
Pure collision is a straight line course flown by a launch aircraft or weapon such
that it will collide with the target.
LEAD COLLISION
Lead collision is a straight line course flown by a launch aircraft such that it
will achieve a single given firing position. The time of flight (TOF) of the weapon
is a constant.
COMMAND GUIDANCE
The launch aircraft tracks the target with one radar and tracks the missile with a
second radar. A computer on the launch aircraft determines if the missile is on the
proper trajectory to intercept the target. If it is not, steering commands are
generated by the computer and transmitted to the missile.
4-4
T.O. 1-1M-34
BEAM RIDER
The launch aircraft tracks the target with a V-shaped beam. The missile flies at
the bottom of the V. If the missile moves out of the bottom of the V, sensing cir
cuits in the missile cause the missile to return to the correct position. As long
as the launch aircraft continues to track the target, and the missile continues to
ride the radar beam, the missile will intercept the target.
CONSTANT LOAD FACTOR

This is a course flown by a launch aircraft or missile so that a constant g load
factor on the aircraft/missile will result in collision with the target. No
missiles presently fly constant load factors. Normal acceleration is constant in
this course.
PROPORTIONAL NAVIGATION
This is a course flown such that the lead angle is changed at a rate proportional to
the angular rate (AX) of the line of sight (LOS) to the target.
MOTOR TYPES
There are three basic air-to-air missile
MOTOR TYPES motor types: all-boost, all-sustain, and
boost-sustain (FIGURE 4-4).
ALL-BOOST
ALL-BOOST
An all-boost motor typically will make the
missile accelerate rapidly, causing a high
TIME
peak velocity. The short TOF for a given
range causes high missile drag and high
ALL-SUSTAIN aerodynamic heating. This motor type is
adequate for rear hemisphere, tail chase
encounters•
ALL-SUSTAIN
BOOST-SUSTAIN
The all-sustain motor produces slow missile
acceleration, resulting in less aerodynamic
drag and longer flight time, for a given
range. Because the motor burns for a long
period of time, the motor can be used to
TIME overcome gravity in a look-up engagement,
and to provide sufficient velocity for
maneuvering at high altitude. This type of
FIGURE 4-4 motor is suitable for head-on engagements,
or in look-up engagements to high altitude.
4-5
T.O. 1-1M-34
BOOST-SUSTAIN
The boost-sustain motor represents an attempt to combine the best features of the
all-boost and the all-sustain motors. The boost-sustain motor is designed so that
the sustain phase of propulsion will maintain the velocity achieved at the end of
boost.
AIM-7 SPARROW MISSILE

DESCRIPTION
The AIM-7 is a supersonic, air-to-air guided missile designed for ejection launch.
The missile can intercept and destroy targets in adverse weather conditions. The
AIM-7 is a semiactive missile which is guided on either continuous wave (CW) or
pulse doppler (PD) radio frequency (RF) energy radiated by the launching aircraft
and reflected by the target. The missile is guided, controlled, and detonated by
the target seeker and flight control sections. The warhead is of continuous-rod
design which expands upon detonation of its explosive charge to produce target
destruction. The solid propellant rocket motor provides the thrust (all-boost,
AIM-7E3 and boost-sustain, AIM-7F/M).
AIR FRAME
Four major sections comprise the AIM-7 Sparrow missile (FIGURE 4-5): the guidance
section (radome and target seeker); the control section (autopilot and wings); the
warhead; and the rocket motor. The sections of the missile are coupled together and
locked into position by screws. Four delta-shaped wings are plugged into the wing
hub sockets. Four tail fins are attached to the rocket dovetail pad. A wiring har
ness provides the electrical connection between the target seeker and control sec
tion, and a waveguide provides an RF connection from the rear antenna to the target
seeker. The missile is attached to the launcher by a set of hooks on the rocket
motor and one lug on the flight control section. An umbilical cable and a rocket
motor fire connector provide an electrical interface between missile and launcher.
A safe and arming device on the rocket motor permits manual arming of the motor
after installation.
GUIDANCE SECTION
RADOME
The radome forms the nosepiece of the missile and covers the seeker head assembly.
It forms an important part of the external contour of the missile and is a vital link
in the electromagnetic path of RF energy reflected from the target to the missile
front antenna. The AIM-7F/M has an ogive shape which provides optimum balance be
tween aerodynamic drag and electromagnetic requirements. The ogive shape is flaired
into a cylindrical aft section, allowing for antenna size and eliminating RF inter
ference at antenna gimbal limit angles.
4-6
AIM-7 SPARROW
__________ MISSILE-GENERAL OPERATIONS
___ __ ______________________________
IM -3 4
FIGURE 4-5
T.O. 1—IM—34
TARGET SEEKER
The AIM-7 Sparrow target seeker receives and compares the radar energy acquired
directly from the target illuminator on the launch aircraft and radar energy
reflected by the target. The guidance system uses range rate, angle, and angle rate
information to produce guidance signals for the autopilot. The target seeker con
sists of electronic modules packaged around the hydraulic system for the missile
antenna gimbals. The antenna gimbal system provides antenna pitch and yaw motion
about the missile body axis.
CONTROL SECTION
The control section consists of the autopilot and the hydraulic control group. The
functions of the control section are to process angular error information and pro
vide wing control signals to guide the missile and to stabilize the missile in
pitch, yaw, and roll. The launching aircraft supplies the control section with
attitude control voltages (English bias), which provide the missile with course
correction commands used during the boost portion of the missile flight. The
launching aircraft supplies a roll command signal which aids the missile in
establishing a normal postlaunch flight attitude (umbilical up). The wing hub
assembly consists of the steel midsection shell and the internal hub block. The hub
block acts as a structural stiffener and functions as a foundation and support for
the components required for wing operation. The assembly mounts contain the
hydraulic accumulator, the valve manifold, wing servo valves, wing locks, four sets
of double linear actuators, and wing socket assemblies. All four wings are actuated
in pitch and yaw, while two of the wings also control roll rate. A maximum of ±22
degrees of rotary motion is available in each wing. Before activation, wing motion
is restrained by spring-loaded locks to ±0.25 degree deflection. The hydraulic
control group reacts to the signals from the autopilot to control the flightpath of
the missile. The accumulator supplies the hydraulic power necessary to move the
wings as required by the flight command signals from the autopilot.
WARHEAD SECTION
WARHEAD
The continuous-rod bundle is made up of pairs of 3/16-inch-square cross-sections of
steel rods which are assembled in two interconnecting layers. The effective length
of each inner and outer rod is approximately 8 inches. Each rod in the outer layer
is welded at its forward end to the forward end of the adjacent rod in the inner
layer. The welded points are the pivot points for the outer and inner layers. The
resulting continuous construction is similar to an expansion bracelet, and can
extend into a zig-zag hoop. The rods are tightly pressed together in the assembled
condition.
SAFE AND ARM DEVICE

The safe and arm device is mounted at the forward end of the central axis of the
warhead. The basic function of the safe and arm device is to maintain the warhead
in an unarmed condition until the missile has intentionally been launched and has
4-8
TO. 1-IM-34
traveled a safe distance from the launching aircraft. After the missile reaches a
safe distance, the safe and arm device arms the warhead so that upon receipt of a
firing pulse from the guidance section, the warhead will be detonated.
ROCKET MOTOR SECTION

ROCKET MOTOR
The AIM-7 rocket motors are solid propellant motors providing thrust (all-boost,
AIM-7E3 and boost-sustain, AIM-7F/M) for the missile. The motor is attached to the
aft end of the missile warhead (AIM-7E3) or the control section (AIM-7F/M) and con
sists of three major subassemblies: a case propellant grain, a safe and arm igniter
assembly, and a nozzle weather seal assembly. The motor case consists of a cylin
drical tube section with an integral forward dome and an aft boattail section. The
boattail incorporates four fin support brackets (dovetails) and an antenna mount.
SAFE AND ARM IGNITER ASSEMBLY
The safe and arm igniter assembly is a manually operated mechanism that can be
locked in either the safe or armed position. The initiator gases are contained
within the free volume of the device when the safe and arm igniter assembly is in
the safe position. The safe and arm igniter assembly is attached to the rocket
motor case and requires a separate arming tool to actuate the mechanism. A red
streamer is attached to the handle of the arming tool to visually indicate that the
igniter is in the safe position. The arming tool is removed after the igniter is
armed. The igniter contains a main charge and a booster charge. When the rocket
motor ignition is commanded, the gases exhaust through the perforated aft end of the
case. The booster charge is ignited with redundant single-bridgewires by electric
heat ing.
REAR ANTENNA ASSEMBLY
The rear antenna is a structural waveguide used to receive the RF energy emitted by
the launching aircraft and conduct it to the target seeker. On the AIM-7F/M, the
rear antenna waveguide is constructed in two sections.
MISSILE OPERATION
Homing guidance is accomplished by the semiactive radar target seeker which is com
patible with either PD or CW illumination (AIM-7E3 is CW only). The seeker antenna
receives the target-reflected energy which is then processed to obtain speed, range,
and directional information, using the doppler principle. The AIM-7 Sparrow
achieves velocity tracking by comparing target-reflected energy received through the
front antenna with a reference signal received through the rear antenna. The com
parison yields a doppler or difference signal which is proportional to the missile-
to-target closing velocity. Because the missile must be able to accept a wide range
of closing velocities, a tracking speedgate is used to search over the frequency
range containing targets of interest. Range information is extracted from the
4-9
T.O. 1—1M—34
ranging frequency modulation (FM) on the illuminator’s transmitted signal. The

ranging signal is present on the target-reflected energy but is time delayed with
respect to the ranging signal received at the missile rear antenna. Comparison of
the front signals and rear signals yields a doppler which is frequency modulated at
the ranging frequency with a peak deviation proportional to range. This information
is extracted in the range comparator to arm the fuze at the proper distance from
intercept and to switch to an internal FM to retain a speedgate lock as the range
diminishes to zero. Directional information for the missile in flight is obtained
by conically scanning the antenna beam. Conical scanning of the received energy
results in amplitude modulation whenever an error exists between the antenna to
target LOS and the antenna boresight axis. Errors ar© detected, filtered, and fed
to the front antenna as tracking commands and to the autopilot as guidance commands.
Conical scanning is only initiated at a speedgate lock so that the full antenna gain
is available for target acquisition. The primary function of the autopilot is to
convert LOS rate into actual missile lateral acceleration. Basically, the autopilot
consists of three tight acceleration feedback loops using rate gyros for the proper
pitch, yaw, and roll damping. Autopilot gain switching is incorporated into the
missile to optimize flight performance under varying conditions. This switching is
automatically accomplished by a command from the fire control computer and is a
function of interceptor altitude and target altitude.
AIM-7E3 SPARROW MISSILE

The AIM-7E3 Sparrow missile (FIGURE 4-6) is the oldest operational version of the
AIM-7 missiles. The target seeker and flight control sections are connected
together with the warhead between the control section and the rocket motor. The
missile internal power is generated by a gas grain generator. The rear antenna is a
one-piece waveguide which connects to the rear of the control section. The rocket
motor is all-boost only. Homing guidance is accomplished by the semiactive target
seeker which is compatible with CW illumination only.
AIM-7F SPARROW MISSILE

The AIM-7F Sparrow missile (FIGURE 4-6) is a larger version of the AIM-7 missiles.
The warhead is larger and is placed between the target seeker section and the flight
control section. The gas grain generator used in the AIM-7E3 version was replaced
by a battery. The rear antenna is constructed in two sections. The forward section
connects to the internal microwave circuitry in the guidance section. The forward
section also serves as a cover for the tunnel connecting cable which provides
electrical connection between the guidance and control section. The rear antenna
aft section is joined to the forward section at the forward rocket motor joint. It
has a boost-sustain rocket motor designed to maintain the velocity achieved at the
end of the boost. Homing guidance is accomplished by the semiactive radar target
seeker which is compatible with either PD or CW illumination.
AIM-7M SPARROW MISSILE

In most respects, the AIM-7M Sparrow missile is like the AIM-7F. The primary dif
ference is an increased electronic countermeasure (ECM) and electronic counter
countermeasure (ECCM) capability.
4-10
T.O. 1—1M—34
AIM-7 SPARROW FAMILY DIFFERENCES
TAILFIN ROCKET MOTOR
WARHEAD
WING GUIDANCE CONTROL
AIM-7E3
TAIL FIN
ROCKET MOTOR
WING
WARHEAD
GUIDANCE CONTROL
AIM-7F/M
CHARACTERISTICS
AIM-7E3 AIM-7F AIM-7M
LENGTH 12 FT 1 IN_ _ _ _ 12 FT 12 FT
DIAMETER-_ _ _ _ _ _ _ _ _ _ 8 IN. -------------- 8 IN------------------------ 8 IN.
WINGSPAN_____ 40 IN-------------- 40 IN---------------------- 40 IN.
TAIL SPAN 32 IN 32 IN. 32 IN.
WEIGHT 425 LB 510 LB 510 LB
ROCKET MOTOR BOOST BOOST-SUSTAIN_ BOOST-SUSTAIN
GUIDANCE CW CW/PD CW/PD
ANTENNA GIMBAL 55 DEG 55 DEG 60 DEG
FIGURE 4-6
4-11
T.O. 1—1M—34
AIM-7 EXERCISE WARHEAD

The exercise warhead is used for training and practice and can be used in place of
the tactical warhead. The weight and size of the exercise warhead are similar to
those of the tactical warhead. The exercise warhead has two signal types which upon
firing emit a brilliant flash, permitting observation of the moment of simulated
warhead detonation. The exercise heads use the same safe and arm devices employed
in the tactical warhead.
AIM-7 TELEMETRY SET

A telemetry set may be used in place of the tactical warhead to transmit missile
flight data to telemetry receiving stations. The telemetry data provide information
necessary for the detailed analyses and evaluation of missile performance. The
telemetry sets and the missiles they are used with consist of the following:
1. AN/DKT-30(V)1, (V)2 telemetry sets are used with AIM-7E3 missiles.
2. AN/DKT-37A(V) telemetry set is used with the AIM-7F missile.
The telemetry sets are of two types, full pack and video pack. The full pack con
sists of a telemetry unit installed in a duplicate warhead shell. The unit monitors
approximately 30 missile functions, and transmits radar receiver functions, missile
attitude, and autopilot instructions. The video pack is installed in a duplicate
warhead shell and monitors missile speedgate, doppler, and fuzing. Closing velocity,
lock-time, and miss distance are obtained from the transmitted data. For training
flights where neither warhead nor telemetry is required, an exercise warhead shell
is used, which approximates the warhead in weight and size.
AIM-9 SIDEWINDER MISSILE

The AIM-9 Sidewinder missile (FIGURE 4-7) is a supersonic air-to-air intercept
missile. The missile consists of four external sections: guidance and control
(G&C), warhead, influence fuze, and rocket motor. The missile has an IR radiation
seeker in the G&C unit which controls the missile guidance and provides a tone in
the pilot’s headset. The aural tone indicates that the seeker head is operating and
is used to monitor target detection and tracking. The IR system is a passive means
of detection. Because the missile does not require guidance from the launching
aircraft, the pilot may take evasive action immediately after the missile is
launched. The missile warhead is detonated on contact or by an influence fuze when
the target is within effective radius of the warhead.
Three suspension hangers attached to the motor enable loading on launcher rails.
Four stabilizing wings are attached in the X-configuration at the rear of the rocket
motor. Each wing contains a rolleron device which effectively opposes the roll rate
of the missile during flight. An umbilical cable on the G&C and two contacts
mounted in the forward hanger provide the electrical connection to the aircraft
missile firing circuitry. The umbilical cable is attached to a connector which is
sheared when the missile is launched.
4-12
T.O. 1—IM-34
AIM-9 SERIES GUIDED MISSILE

UMBILICAL CABLE UMBILICAL
NOSE GUIDANCE AND RETAINING CLIP
COVER CONTROL SECTION
1R DOME
AIM-9L/M
SHORTING PLUG
INFLUENCE
FUZE
UMBILICAL BLOCK
HANGERS
GUIDANCE
AIM-9B CANARD (4)
WARHEAD WING (4)
CONTACT
AIM-9E BUTTONS
INFLUENCE
FUZE COVER ROCKET MOTOR
ROLLERON (4)
AIM-9J/P SHORTING
CLIP
FIGURE 4-7
Various combinations of rocket motors and influence fuzes, with a given G&C unit,
are available (FIGURE 4-8). Configuration identification begins with the letter
designation of the G&C unit and is then followed by a dash number.
The difference between the AIM-9B, E, J, and P models, other than the physical
characteristics, is in the G&C units. The AIM-9L/M missile (FIGURE 4-8) is similar
to the other AIM-9 missiles but has an active optical target detector, is more
maneuverable, has an all-aspect capability, has a more sensitive IR sensor, and has
coolant gas for the IR detector. The coolant is provided by a small replaceable
tank mounted within the G&C unit.
4-13
T.O. 1- 1M-34
AIM-9 MODEL CONFIGURATIONS/CHARACTERISTICS
WEIGHT LENGTH DIAMETER WINGSPAN

MODEL MOTOR FUZE (LB) (IN.) (IN.) __(IN-)
B MK 17 MK 303 167 112 5 22

B-l MK 17 DSU-21/Ba 167 112 5 22
B-2 SR-116-HP-1 MK 303 180 112 5 22
B-3 SR-116-HP-1 DSU-21/Ba 180 112 5 22
E MK 17 MK 303 171 118 5 22

E-l MK 17 DSU-21/Ba 171 118 5 22
E-2 SR-116-HP-1 MK 303 184 118 5 22
E-3 SR-116-HP-1 DSU-21/Ba 184 118 5 22
J/P MK 17 MK 303 165 120 5 22

J-l/P-1 MK 17 DSU-21/Ba 165 120 5 22
J-2/P-2 SR-116-HP-1 MK 303 178 120 5 22
J-3/P-3 SR-116-HP-1 DSU-21/Ba 178 120 5 22
L MK 36 DSU-15/B, 191 113 5 25

A/Bb
M MK 36 DSU-15/B, 233 115 5 25

A/Bb
a DSU-21/B target detector for the AIM-9B, I5, J, P.

b DSU-15/B, A/B target detector for the AIM--9L/M.
FIGURE 4-8
4-14
T.O. 1-1M-34
SECTION V
SUSPENSION EQUIPMENT
CONTENTS
PAGE
BOMB AND EQUIPMENT RACKS......................................................................................................... 5-2

MAU-12B/A, C/A, D/A Bomb Ejector Rack.........................................................................................5-2
MAU-40/A Bomb Ejector Rack........................................................................................................... 5-3
MAU-50/A Bomb Ejector Rack. .......................................................................................................... 5-3
TER-9,9/A Triple Ejector Rack (TER)............................................................................................ 5-3
MER-10,10/A, 10/N Multiple Ejector Rack (MER)......................................................................... 5-8
AIR-TO-AIR MISSILE LAUNCHERS.................................. .................................................................... 5-8
AER0-3B, LAU-105 Missile Launcher...............................................................................................5-8
LAU-34/A Missile Launcher................................................................................................................ 5-8
LAU-114A/A Missile Launcher............................................................................................................ 5-12
AIR-TO-GROUND MISSILE/ROCKET LAUNCHERS.............................................................................. 5-12
LAU-88/A Missile Launcher...................................................................................................................5-12
LAU-117/A Missile Launcher................... 5-15
LAU-3/A, A/A, B/A, -60A Rocket Launcher.................................................................................... 5-15
LAU-68A/A, B/A Rocket Launcher................................................................................................... 5-19
LAU-5003/A Rocket Launcher........................................................................................................... 5-19
TRAINING WEAPONS AND EQUIPMENT............................................................................................... 5-22
SUU-20/A, A/M, A/A, B/A Practice Bomb and Rocket Dispenser.................................................... 5-22
SUU-21/A Practice Bomb Dispenser................................................................................................... 5-25
5-1
T.O. 1—1M—34
BOMB AND EQUIPMENT RACKS
MAU-12B/A, C/A, D/A BOMB EJECTOR RACK

The MAU-12B/A, C/A, D/A bomb ejector rack (FIGURE 5-1) is a universal bomb rack
installed in pylons. The bomb rack has electrically fired impulse cartridges and a
gas operated mechanism. It will carry and forcibly eject suspension equipment and
or munitions up to a combined weight of 5,000 pounds and with diameters from 9.0 to
30.5 inches. The rack contains three electromechanical arming solenoids, two gas
operated bomb ejector feet, four adjustable sway braces, and two sets of suspension
hooks (one set spaced 14 inches apart and one set spaced 30 inches apart). Both
sets of hooks are connected by a common linkage system which is positively locked in
position by a latch mechanism of over-center bellcrank design.
MAU-12 BOMB EJECTOR RACK (TYPICAL)

TAIL
IN-FLIGHT SAFETY IN-FLIGHT LOCK SWAY ARMING
NOSE LOCKOUT BOLT MANUAL RELEASE BRACES (4) SOLENOID
ARMING (INSTALLED)
SOLENOID HOOK MANUAL
RELEASE
ORIFICE GROUND SAFETY ELECTRICAL
LOCKPIN HOLE RECEPTACLE
ORIFICE
30 IN 30 IN. HOOK
CARTRIDGE BOMB EJECTOR

RETAINERS SENSING SWITCH FOOT
BOMB EJECTOR CENTER PLUNGER
FOOT ARMING
SOLENOID
SENSING SWITCH
GUARD
CHARACTERISTICS
WEIGHT 75 LB
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ .2FT8 IN.
WIDTH 3 IN.
HEIGHT 6 IN.
SUSPENSION HOOK SPACING —14 AND 30 IN.
FIGURE 5-1
5-2
T.O. 1—1M—34
The arming solenoids, when armed by cockpit switch selection, retain the munition
arming wire/lanyard swivel loops upon munitions release. The nose arming option
will arm the forward and center solenoid and the tail arming option will arm only
the aft solenoid (except A-7 aircraft). With nose/tail arming option, all three
solenoids will be armed. To remove the munition swivel and link assembly from the
arming solenoids requires 10 to 14 pounds of force when the solenoid is in the safe
position and 150 pounds of force when it is in the armed (energized) position.
Two ejection pistons are equipped with orifices to vary the ejection force of each
piston and allow compensation for various bomb centers of gravity (CG). The release
mechanism and ejection pistons are operated by gas pressure from the electrically
fired cartridges with dual electrical circuits. In the event one cartridge misfires
electrically, it will be fired by the hot gases from the ignited cartridge traveling
through the interconnecting port within the dual cartridge breech. The rack has pro
visions for a ground safety pin and an in-flight safety lock (FIGURE 5-2). The
ground safety pin is installed to prevent accidental firing of the cartridges when
the aircraft is on the ground.
The in-flight safety lock is used to prevent operation of the pivot arm without
appropriate nuclear consent switch settings. When configured for use with conven
tional munitions, an in-flight safety lockout bolt must be installed or no release
will occur. This bolt is not streamered. The MAU-12C/A is completely interchangeable
with the MAU-12B/A bomb rack. Essentially, MAU-12C/A is a strengthened MAU-12B/A
with steel, instead of aluminum, side plates. The MAU-12D/A is the same as the
MAU-12C/A.
MAU-40/A BOMB EJECTOR RACK

The MAU-40/A (FIGURE 5-3) is a universal bomb rack that is essentially a
MAU-12C/A, D/A except it does not contain the safety wiring and in-flight safety
lock required for nuclear munitions. All other descriptive items and operation
for the MAU-40/A are the same as for the MAU-12C/A, D/A.

The MAU-50/A (FIGURE 5-4) rack is shorter than the MAU-12C/A, D/A, and can carry
only stores having 14-inch suspension lug spacing, weighing up to 2,000 pounds,
and having a diameter between 9 and 30 inches. The MAU-50/A does not contain
the safety wiring and in-flight safety lock required for nuclear munitions. All
other details, descriptions of components, and operations are the same as those
for the MAU-12C/A, D/A.
TER-9, 9/A TRIPLE EJECTOR RACK (TER)

The TER-9, 9/A (FIGURE 5-5) is an auxiliary suspension rack used to increase the
number of munitions aircraft pylons (with MAU racks installed) can carry. A TER can
carry and sequentially eject up to three stores weighing up to 1,000 pounds each and
16 inches in diameter. The rack consists of a structural unit (strongback) with
three ejector units and associated wiring. Each ejector unit (FIGURE 5-5) has pro
visions for suspension, sway-bracing, sensing, electromechanical arming, and
5-3
T.O. 1—1M—34
MAU-12 BOMB RACK OPERATIONAL SCHEMATIC
LOCKED
HOOK ACTUATING
PORT
FIGURE 5-2
54
T.O. 1—1M—34
CHARACTERISTICS
WEIGHT 65 LB
LENGTH 32 IN.
WIDTH 3 IN.
HEIGHT 6 IN.
SUSPENSION HOOK SPACING 14 AND 30 IN.
FIGURE 5-3
munition ejection to operate functionally the same as a MAU rack. The TER strong
back attaches to a pylon with 30-inch spaced lugs and provides 14-inch suspension
hook spacing on the ejector units. Each ejector unit has a gas operated ejector
foot to forcibly eject the munition. The gas is supplied by a cartridge installed
in the front of the unit which is electrically fired through an umbilical cable.
A control panel (FIGURE 5-5) at the aft end of the TER has a CBU/rocket switch, an
electrical safety pin receptacle, and a manual stepper switch. The CBU/rocket
switch should be in the rocket position for firing from SUU-25 series flare dispen
sers only. All other weapons are released in the CBU position. The electrical
safety pin is used for ground safing and when inserted in the receptacle interrupts
the electrical circuit. The manual stepper switch is used only during maintenance.
Store release/ejection is accomplished sequentially by fire-and-step logic. Each

pulse fires one station (ejector unit) and causes the stepper switch to select the
next station in firing order and wait for the next fire-and-step pulse. Firing
order for the TER is centerline, left, and right station. Within this order, cir
cuitry in the rack assemblies automatically skips unloaded stations; therefore,
every fire-and-step signal will fire a loaded store.
5-5
T.O. 1—1M—34
CHARACTERISTICS
WEIGHT 45 LB
LENGTH 23 IN.
WIDTH 3 IN.
HEIGHT 6 IN.
SUSPENSION HOOK SPACING 14 IN.
FIGURE 5-4
The TER-9/A functions differ from the TER-9 as follows:
1. Only the loaded TER-9/A stations receive a release pulse regardless of the
nose/tail arm switch position.
2. The TER-9/A is automatically homed to the first loaded station in sequence

each time power is applied to the aircraft.
3. The step switch on the TER-9/A is used for ground checkout operation.
A hung munition may sometimes be released by re-homing the TER to the first loaded
station. (See the appropriate aircraft Dash 34 for re-homing procedures.)
Arming is accomplished through cockpit setting for either nose, tail, or both to
select the two arming solenoids. These solenoids provide arming wire/lanyard swivel
loop retention for fuze arming in the same manner as does the MAU rack.
Ground safety is provided by an electrical safety pin in the aft plate, one mechani
cal safety pin in each loaded ejector unit, and the MAU rack mechanical safety pin.
If a single ejector unit safety pin is not removed, a hung munition will occur, but
the next munition in the release sequence will be released.
5-6
T.O. 1—IM—34
TER-9, 9/A TRIPLE EJECTOR RACK (TER)
ARMING SOLENOIDS
ROCKET/CBU JUMPER PLUGS
MANUAL RELEASE
SUSPENSION HOOKS
UMBILICAL RECEPTACLE
CARTRIDGE BREECHES
ELECTRICAL
SWAY BRACES SENSING SWITCH PLUNGER SAFETY PIN
EJECTOR FEET
MECHANICAL
SUSPENSION ARMING SUSPENSION SAFETY PIN
HOOK SOLENOID HOOK HOLE
BREECH CAP
MANUAL
STEPPER
CARTRIDGE SWITCH
BREECH
CBU/ROCKET SWITCH
ARMING SENSING EJECTOR FOOT AFT END TER
SOLENOID SWITCH SWAY BRACE SAFETY PIN INSTALLED
SWAY BRACE
LEFT <4 ► RIGHT
TER-9/A
CENTER
TER RELEASE SEQUENCE
(VIEW FROM AFT)
CHARACTERISTICS
WEIGHT 95 LB
LENGTH 5 FT 7 IN.
WIDTH 15 IN.
SUSPENSION HOOKSPACING------------ 14 IN.
SUSPENSION LUG SPACING._ _ _ _ _ _ _ _ 30 IN.
FIGURE 5-5
5-7
T.O. 1—1M—34
MER-10, 10/A, 10/N MULTIPLE EJECTOR RACK(MER)

The MER-10, 10/A, 10/N (FIGURE 5-6) is an auxiliary suspension rack used to increase
the number of munitions the aircraft pylon (with MAU racks installed) can carry. A
MER can carry and sequentially eject up to six stores weighing up to 1,000 pounds
each and 16 inches in diameter. The MER is mounted to the pylon using 30-inch
suspension lugs which can be adjusted either in an aft or a forward position to
maintain the CG and loads within design limits. All details and descriptions of
components and circuitry discussed for the TER-9, 9/A (including differences between
the two models) apply to the MER-10, 10/A. The MER-10 operates exactly as the
MER-10/A does. The only change is the configuration of the firing leads to the
cartridges. The firing leads are more accessible for maintenance, inspection, and
repair. The MER release sequence is rear center, front center, rear left, front
left, rear right, and front right.
AIR-TO-AIR MISSILE LAUNCHERS

AERO-3B, LAU-105 MISSILE LAUNCHER
The AER0-3B missile launcher (FIGURE 5-7) is used to carry and fire AIM-9 Sidewinder
missiles. The LAU-105 is an AER0-3B launcher that has been modified to allow
carriage of the AIM-9L/M missile.
The AERO-3B/LAU-105 provides launching rails for the missiles and secures them
during takeoff, flight, and landing. Major components are a power supply, a detent
and snubber assembly, and a rail assembly. The power supply, located in the center
of the launcher, provides power for the AIM-9 missile during captive flight as well
as power for firing. The detent and snubber assembly consists of three functional
units. A detent extending through the rail restrains the missile in vertical and
lateral directions and provides two contact points for the missile motor firing
pulse. When the rocket motor ignites, the thrust overrides the detent spring and
allows the missile to travel forward along the launcher rails.
Snubber cams extending through slots in the rail engage the forward and aft missile
hangers to prevent movement of the missile until it is fired. Upon missile firing,
guides provide for the locking of the forward cams to clear the rail for passage of
the missile hangers.
The launcher may be fitted with a streamered safety pin inserted into the top of the
launcher forward fairing. The safety pin must be removed before flight. If
inserted, the pin will prevent accidental firing of the missile motor while on the
ground, but it will not prevent inadvertent firing of the gas grain generator in the
guidance and control unit.
LAU-34/A MISSILE LAUNCHER

This assembly (FIGURE 5-8) must be used to carry and launch the AGM-45 missile. The
launcher contains the electrical circuits and relays which are responsible for the
dispersal of missile pre-heat, pre-arm, and missile launch voltage. The launcher
also contains a cartridge-fired jettison gun assembly. When the jettison system is
activated, expanding gas from -the detonated cartridge operates the assembly and
5-8
T.O. 1—1M—34
MER-10, 10/A, 10/N MULTIPLE EJECTOR RACK (MER)
SWAY BRACES
SAFFTY
HOCKrT
M
SWAY BRACE PADS
EJECTOR
FOOT
REMOVABLE ROCKET OR SUSPENSION

CBU HARNESS ASSEMBLY HOOKS
(INSTALLED WHEN APPLICABLE)
MULTIPLE EJECTOR RACK (MER)
EJECTOR UNIT
(TYP 6 PLACES)
EJECTOR REMOVAL PIN
SOLENOIDS
AFT POSITION
MOUNTING HOLES
AFT POSITION
EXTENSION LUGS
FORWARD POSITION
EXTENSION LUGS
FORWARD POSITION
EXTENSION LUGS
FORWARD
FORWARD POSITION
MOUNTING HOLES
LEFT RIGHT
CHARACTERISTICS
WEIGHT 220 LB
LENGTH 13 FT
WIDTH _ 15 IN.
MER -10N MER RELEASE SEQUENCE
HEIGHT „ 16 IN.
SUSPENSION LUG SPACING _ 30 IN.
SUSPENSION HOOK SPACING _ 14 IN.
FIGURE 5-6
5-9
T.O. 1-1M-34
AERO-3B, LAU-1O5 MISSILE LAUNCHER
STRIKER DETENT LOCKING 1.37-IN. SPACERS

POINTS SAFETY PIN <T1 3-IN. SPACERS
DETENT
INBOARD
PYLON
SNUBBER
AERO 3B
SAFETY
PIN
DETENT AND
SNUBBER
AERO 3B
SAFETY PIN ACCESS
AIM-9L UMBILICAL RECEPTACLE LAUNCHER UMBILICAL

AIM-9 J/P ELECTRICAL ASSEMBLY
ADAPTER STOWED
LAUNCHER
NOSE FAIRING
NOSE COVER
ATTACHING RAIL FIN RETAINING SPRINGS
BOLT ASSEMBLY
LAUNCHER TO PYLON
ELECTRICAL CABLE ATTACHING
BOLT
CHARACTERISTICS
WEIGHT 49 LB
rO AFTER TO 11L1-3-15-515, THE SAFETY PIN LENGTH 7 FT 3 IN.
REMAINS INSTALLED DURING FLIGHT. IT
RESTRAINS REARWARD MOVEMENT OF THE WIDTH-_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 3 IN.
MISSILE DURING FLIGHT. HEIGHT._ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ 5 IN.
FIGURE 5“7
5-10
T.O. 1-1M-34
FIGURE 5-8
5-11
T.O. 1-1M-34
slides the missile rearward, free of the launcher rails. Impulse cartridges are not
installed in MAU-12 breeches of stations configured with the LAU-34/A launcher.
This weapon system will function with or without the installation of the MAU-12
in-flight safety lockout pin.
LAU-114A/A MISSILE LAUNCHER

The LAU-114A/A (FIGURE 5-9) missile launchers are basically the same as AERO-3B
launchers. However, the LAU-114A/A contains an umbilical receptacle underneath the
forward fairing for directly connecting AIM-9L/M missile umbilical cables.
AIM-9L/M missile umbilical cables are connected directly to the launcher umbilical
receptacle underneath the forward fairing. If an AIM-9J/P missile is loaded on the
launcher, an electrical adapter plug is connected in series with the umbilical cable
and receptacle. When AIM-9L/M missiles are loaded, the adapter is stowed in the
forward fairing housing.
The LAU-114A/A is also equipped with the fin retainer springs for use with the
AIM-9L/M only. The fin retainer springs snap over the trailing edge of each pair of
missile fins to prevent fin flutter during captive flight. The fin retainer springs
automatically disengage when the missile is launched.
SUSPENDED MULTILAUNCHER UNIT (SMU)

The SMU is a machined aluminum block designed to adapt two modified AERO-3B or two
LAU-114 launchers to 14-inch suspension. The SMU consists of the aluminum block
with covers and fairings, suspension lugs, electrical components, and a ground
safety/captive switch.
AIR-TO-GROUND MISSILE/ROCKET LAUNCHERS

The LAU-88/A launcher (FIGURE 5-10) is designed to carry, control, and launch up to
three AGM-65 missiles. The TGM-65 training missile can also be carried and
controlled on the LAU-88/A. The launcher consists of three track-rail assemblies
attached to a central structure which contains the electronic unit. The order of
release and the station empty signals come from the electronic unit mounted behind
the rear bulkhead. All control and switching circuits for the launcher and missiles
are also contained in the electronic unit.
The missiles are restrained on the rails by a shear pin, installed midway on each
rack, and by two bumpers at the rear of each rail. Between these two bumpers, a
retractable electrical umbilical connector is rotated forward and connected to the
missile after it is loaded.
At missile launch, the rocket motor thrust exceeds the shear pin strength, allowing
the missile to leave the rail. Launch sequence is outboard, center, and inboard.
5-12
T.O. 1—1M—34
LAU-U4A/A MISSILE LAUNCHER
AIM-9J/P
ELECTRICAL
ADAPTER
(LAU-114)
LAUNCHER
SAFETY PIN
RAIL
ASSEMBLY
LAU-114/AER0 3B
MISSILE LAUNCHERS
SMU ADAPTER
FORWARD
DETENT REAR DETENT
AND DETENT
LOCKING PIN
u \NG
CHARACTERISTICS
WEIGHT 55 LB
MOTOR FIRE AND LENGTH 7 FT9 IN.
INFLUENCE FUZE WIDTH _ 3 IN.
STRIKER POINTS LAU-114 HEIGHT. 5 IN.
FIGURE 5-9
5-13
T.O. 1—1M—34
CHARACTERISTICS
WEIGHT 465 LB
LENGTH 7 FT 9 IN.
WIDTH 27 IN.
HEIGHT 18 IN.
SUSPENSION LUG SPACING __ _ 30 IN.
FIGURE 5-10
Aircraft control systems will not automatically sequence between different stations
after a missile launch to alternate launching from different stations. The
appropriate aircraft Dash 34 manual must be consulted for missile sequencing if
LAU-88/As are loaded on more than one station.
NOTE
Due to high initial electrical power require

ments of the AGM-65D, only two missiles can
be loaded on a LAU-88/A.
5-14
T.O. 1—1M—34

The LAU-117/A missile launcher (FIGURE 5-11) provides AGM-45 carriage control, and
launch of a single AGM-65 missile. The launcher is equipped with two removable lug
fittings that provide bomb rack sway brace pads and ejector fittings. The lug fit
tings may be adjusted for 14- or 30-inch suspension spacing.
Restraint of an installed missile is accomplished by use of a mechanical pin

inserted into the missile holdback pin bushing. The mechanical pin is designed to
be forced back (retracted) mechanically whenever the missile motor thrust exceeds
2,500 pounds.
If USAF is not visible in the notch of the

missile restraining device (MRD) cover plate,
the MRD may be in the Navy position. With
the MRD in the Navy position on USAF aircraft,
the rocket motor will fire at launch command,
but the missile will not leave the launcher
rail, even at maximum rocket motor thrust.
NOTE
AGM-65 missiles cannot be jettisoned from

LAU-117 launchers. The LAU-117 launcher can
be jettisoned when carted.
The launcher electronics assembly provides an electrical interface between the

aircraft and the missile. The umbilical cable connector, which is housed in the
umbilical engagement mechanism assembly, interfaces the electrical signals from the
aircraft and launcher circuits to the missile. Interface is accomplished during
missile installation on the launcher.
LAU-3/A, A/A, B/A, -60A ROCKET LAUNCHER

The LAU-3/A, A/A, B/A, -60A rocket launcher (FIGURE 5-12) can carry and launch nine
teen 2.75-inch folding fin aircraft rockets (FFAR). The flight configuration con
sists of the loaded center-section assembly with streamlined fairings installed and
locked onto the ends. When the launcher is fired, the front fairing is shattered by
rocket impact, and the tip of the rear fairing is shattered by rocket blast. The
frangible fairings are made of treated paper and shatter readily after rocket impact
and blast.
Approximately 11 inches of the base of the rear fairing will remain on the adapter
to channel rocket debris away from the undersurface of the wing.
5-15
5-16
LAU-117/A
_______ MISSILE LAUNCHER
______________________
ENGAGE -7^^) )
1M -34
INDICATOR y/ENGAGE
MISSILE APPROXIMATE LAUNCHER
FITTING SUSPENSION RESTRAINT CENTER OF GRAVITY AIRCRAFT ELECTRONIC RAIL
FAIRING LUG (2) DEVICE (MRD) (REFERENCE ONLY' CONNECTOR (J1) ASSEMBLY (LEA) STOP
MISSILE
II© © © IGNITER
CONNECTOR
(W2J1)
UMBILICAL
ENGAGEMENT
FORWARD ALTERNATE LUG LAUNCHER SUPPORT MRD GROUND MISSILE UMBILICAL
MECHANISM
FAIRING SUSPENSION RETAINER RAIL TRACK BRACKET (2) CABLE STRAP CONNECTOR (W1P2)
LUG (2) (W3) AND SHROUD (UNDER
CONNECTOR SHROUD
COVER)
USAF LEGEND
SUPPORT
BRACKETS
AIRCRAFT AFT
CONNECTOR COVER
7^
CHARACTERISTICS
WE I G HT_________________ 130 LB
FITTING LUG FITTING (2) LENGTH ____________ ____ 7 FT 10 IN.
FAIRING WIDTH_________________ _ 11 IN.
HEIGHT___________ _ 11 IN.
SUSPENSION LUG SPACING 140R 30 IN.
FIGURE 5-11
T.O. 1—1M—34
LAU-3/A, A/A, B/A, -60A ROCKET LAUNCHER

AFT
CHARACTERISTICS
WEIGHT
EMPTY 78 LB
LOADED 420 TO 534 LB (VARIES WITH TYPE OF ROCKET)
LENGTH_ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ _ .7 FT 5 IN.
DIAMETER 16 IN.
FIGURE 5-12
5-17
T.O. 1—IM—34
CAUTION
Not using the rear fairing may damage the

wing during firing.
The launcher center section is constructed of 19 paper tubes clustered together and
is wrapped with a thin aluminum outer skin. Detent devices within the tubes
restrain the rockets against normal flight loads and provide electrical contact to
ignite the rockets. Contact fingers on the aft bulkhead provide a ground to
complete the circuit through the rockets. Two receptacles on top of the center sec
tion provide the connection to the aircraft rocket-firing circuitry. The recep
tacles are wired in parallel; therefore, only one of them is connected to the
aircraft. A shorting pin is inserted in the left side of the LAU-3/A, A/A, B/A
launcher as a ground safety device which is removed prior to flight. The LAU-60/A
contains a breaker switch on the top of the launcher behind the aft electrical
receptacle. Electrical power for the rocket ignition system supplied to the
launcher is 28 volts direct current (de). The intervalometer, located within the
launcher, converts the aircraft firing voltage into a ripple-fire pulse with a
10-millisecond delay interval which will ripple-fire the rockets in pairs until the
launcher is empty. The launcher should completely fire-out in approximately 0.1
second. MER and TER switches must be positioned on rocket to provide the ripple
fire sequence.
WARNING
The CBU position would cause the high voltage

to burn out the wire-type intervalometer at a
rate that will produce a near salvo-fire
effect, and the rockets will collide upon
leaving the launcher.
Certain aircraft have limitations and possible warning notes which apply to LAU-3/A
launchers. Refer to the appropriate aircraft Dash 34 manual for this information.
NOTE
Several intervalometers are available for use

with the LAU-3/A; some are reusable. A burn
out type unit supports the ripple-fire mode
only. The reusable type supports both the
ripple- and single-fire modes and includes a
reset switch to select the firing modes. In
a singles mode, two rockets are fired with
each fire pulse.
5-18
T.O. 1-1M-34
LAU-68A/A, B/A ROCKET LAUNCHER

The LAU-68A/A, B/A rocket launcher (FIGURE 5—13) can carry and launch seven
2.75-inch FFARs. The LAU-68A/A, B/A versions are basically the same as the LAU-3/A,
only smaller. The descriptions of construction and operation of the LAU-3/A apply
to the LAU-68A/A, B/A versions with the following exceptions:
1. The LAU-68A/A has a 26-pin electrical receptacle forward and a 5-pin

electrical receptacle aft. The LAU-68B/A has a 5-pin electrical receptacle forward
and aft.
2. The tail fairings of the LAU-68A/A, B/A versions are constructed of metal
and shaped like a funnel, with a hole on the aft end. During rocket launching, the
tail fairing functions to channel rocket debris away from the underside of the
aircraft wing.
CAUTION
Not using the rear fairing may damage the

wing during firing.
3. The launchers utilize a reusable electromechanical intervalometer to route

the fire pulse to the different rocket tubes. A single/ripple switch and an inter
valometer control, which must be positioned during aircraft loading, are located on
the aft end of the launcher. With the s ingl e/ripple switch in single, one tube is fired
with each fire pulse received by the launcher; with the switch in ripple, all tubes
are fired in sequential order with a 60-mil1isecond interval between tube firings.
The intervalometer control has a load position for ground safety, an arm position,
and firing positions 1 through 7.
NOTE
The interface of the LAU-68 intervalometer

and ripple/pairs mode causes system anomalies.
When the launcher is mounted on a TER-9/A,
these anomalies may cause hung rockets. In
this case, if a ripple mode is desired,
select ripple on the LAU-68 single/ripple
switch and use the aircraft single mode.
4. Certain aircraft have limitations and possible warning notes which apply to
LAU-68/A launchers. Refer to the appropriate aircraft Dash 34 for this information.
LAU-5OO3/A ROCKET LAUNCHER

The LAU-5003/A rocket launcher (FIGURE 5-14) is used to launch the CRV7 rockets.
The launcher is a cluster of 19 resin-impregnated paper tubes bonded together and
5-19
T.O. 1- 1M— 34
LAU-68A/A, B/A ROCKET LAUNCHER

SINGLE/RIPPLE
CHARACTERISTICS
WEIGHT
EMPTY 67 LB(WITHFAIRINGS)
LENGTH 6FT1 IN.(WITH FAIRINGS)
DIAMETER 10 IN.
SUSPENSION LUG SPACING_ _ _ _ 14 IN.
FIGURE 5-13
5-20
T.O. 1—IM—34
LAU-5OO3/A ROCKET LAUNCHER
FORWARD FAIRING
CHARACTERISTICS
WEIGHT
EMPTY 78 LB
LENGTH_ _ _ _ _ _ _ ._ _ _ _ _ _ _ _ _ _ _ _6 FT 5 IN. (WITH FAIRINGS)
DIAMETER 16 IN.
FIGURE 5-14
5-21
T.O. 1—1M—34
enclosed in a thin aluminum outer skin. On the top of the launcher are two elec
trical connectors, wired in parallel, for connection to the aircraft armament
circuitry. The shorting pin on the side of the launcher is used to safe the
launcher firing circuit. On the aft bulkhead of the launcher is a single or ripple
mode selector switch and the intervalometer. The mode switch must be positioned to
the desired selection (single or ripple) prior to takeoff. In the ripple mode, the
intervalometer will fire the rockets at 40-millisecond intervals. A detachable
retaining bulkhead is secured to the aft bulkhead to secure the rockets in the
tubes and provide the circuitry for the rocket ignition circuits. The frangible
forward fairing shatters on rocket impact. The open end aluminum aft fairing
directs debris away from the aircraft.
TRAINING WEAPONS AND EQUIPMENT

SUU-2O/A, A/M, A/A, B/A PRACTICE BOMB
AND ROCKET DISPENSER
The SUU-20 dispenser (FIGURE 5-15) is an aerodynamically shaped container which
carries practice bombs and/or rockets for weapons delivery training. The SUU-20 can
carry up to six practice bombs and four 2.75-inch diameter rockets. The structure
of the dispenser consists of two cast aluminum end caps and a heavy gauge aluminum
weldment center section. The center section is recessed on the underside to accom
modate the bombs; the rocket tubes are located in the upper section, two on each
side. The dispenser incorporates a stiffener beam hardback along the top surface
for lug attachment and has modified bomb sway braces. The modified sway braces pro
vide a positive bomb-lock condition by insertion of a safety pin through the inspec
tion slot of the ejector gun housing.
The bombs are held in place by individual ejector racks and are stabilized by sway
braces. The bombs are retained in the rack by ice-tong clamps and ejected by a
piston and rod assembly that operates within a breech housing. The assembly is
driven by gas from an electrically fired ejector cartridge. The four 84-inch rocket
launch tubes of the dispenser provide initial flight stability, since the rockets
must travel from the aft end of the tubes during launch. The rockets are fired by
an electrical pulse supplied to each rocket through a spring-loaded plunger mounted
in the aft end of each rocket tube. Inadvertent release of bombs or firing of
rockets during ground operation is prevented by a streamered safety spring inserted
near the lower aft end of the dispenser. The safety spring actuates a switch which
safes the dispenser electrical circuits. In addition, each bomb is saftied by a
bomb retainer lock which is hooked to one retention arm, closed around the bomb, and
secured with a streamered safety pin to the other retainer arm. All streamered pins
(a maximum of seven) must be removed before flight. The bomb rack ejector cartridge
breeches (six) are removable and are usually installed when the cartridges are
installed. When the breeches and cartridges have been installed in the dispenser, a
cartridge retainer pin will be inserted in the lower portion of each breech. These
pins remain in place during flight.
A rocket-firing intervalometer and a bomb-release intervalometer (FIGURE 5-15) are

located in the lower portion of the SUU-20 dispenser just forward of bomb dispenser
stations 1 and 3. FIGURE 5-15 shows two similar dispenser intervalometers. The
rocket intervalometer is forward of the number 1 station while the bomb inter
valometer is forward of the number 3 station. The only difference in the two inter
valometers is the number of stepping positions for the ripple and single modes of
5-22
T.O. 1—1M—34
SUU-2O/A, A/M, A/A, B/A PRACTICE

BOMB AND ROCKET DISPENSER
v'S;.' './t M ' • ■ . ■' ■. ■ ■ • S 6 ' ■ • ■ ■ ■ -■
INTERVALOMETERS
SADDLEBACK
ARMS
BOMB EJECTOR RACK BOMB EJECTOR RACK
(SUU-20B/A) (SUU-20/A-M AND SUU 20A/A)
TOP VIEW AFT VIEW
RELEASE SEQUENCES
CHARACTERISTICS
WEIGHT
EMPTY 320 LB
LOADED_______________________ -554LB
LENGTH____________________ — 10 FT 2 IN.
WIDTH 19 IN.
FIGURE 5-15
5-23
T.O. 1-1M-34
operation. These positions conform to the number of bomb and rocket positions; 6
and 4 respectively. The power required for dispenser operation is furnished by the
weapon selection and the master arm switches. When the master arm switch is in the
ARM position, the pickle button sends a signal to the aircraft intervalometer.
Proper cockpit weapon select knob energizes a relay within the SUU-20 dispenser
carrying station. This is accomplished by directing the firing pulses through this
relay to the appropriate dispenser intervalometer. The dispenser relay completes
the circuit to either the bomb or rocket intervalometer. Each bomb or rocket inter
valometer has three mode positions of operation: SINGLE, RIPPLE, and SALVO (SALVO:
SUU-20A/M only). Each mode has an ARM and a SAFE position. When positioned to ARM,
the intervalometer will automatically step then fire through the selected mode
sequence during release operations. Intervalometer modes of operation must be
selected prior to flight. Each intervalometer will be selected prior to flight.
Each intervalometer will be in a SAFE position during preflight operations. The
appropriate mode arm position will be selected immediately prior to flight. The
intervalometers are constructed so that rotation of the mode selector must be in a
clockwise direction. It may be necessary to rotate the selector through an arm
release sequence in order to reach the desired arm position.
NOTE
The bomb firing intervalometer must be set to

ARM on the empty station prior to the desired
loaded station. If the intervalometer is set
on a loaded station with the intent of drop
ping the next bomb in the sequence, a double
release may occur.
Operation of the SUU-20 bomb or rocket dispenser intervalometer in the SINGLE mode
allows the release of one practice bomb or the launch of one rocket at a time. The
SUU-20 intervalometer requires approximately 50 to 75 milliseconds to step from one
station to the next. Operation of the SUU-20 intervalometer in the RIPPLE mode
allows release of a series of bombs or rockets at a fixed 100-millisecond interval.
NOTE
A weapon release switch must be held depressed

for the duration of the SUU-20 ripple release
sequence which is approximately 0.5 second.
The SALVO mode of dispenser intervalometer operation releases all dispenser bombs
or rockets simultaneously. In addition to the SINGLE, RIPPLE, and SALVO modes of
the SUU-20, the aircraft intervalometer may also be used for bomb releases. In
release of nonnuclear practice bombs, the cockpit selections of step single, step
pairs, step all, ripple single, ripple pairs, or ripple salvo are available using
the respective release option switch on the weapons control panel. In SUU-20 prac
tice rocket release, these selections are also available with the exception of step
or ripple pairs. If the SUU-20 intervalometer is set for RIPPLE mode, an aircraft
5-24
T.O. 1-1M-34
step release option switch must be selected If a ripple release option is

selected, the aircraft and dispenser intervalometer will not be synchronized and
skipped releases will probably result.
NOTE
The SUU-20 in tervalometer (s) must be posi

tioned to BOMB SINGLE when using the aircraft
intervalometer.
The SUU-20 dispenser may be jettisoned, when necessary, by either the external
stores jettison switch or by selective jettison procedures. Refer to the appropri
ate aircraft Dash 34 manual for detailed procedures.
SUU-21/A PRACTICE BOMB DISPENSER

The SUU-21/A practice bomb dispenser (FIGURE 5-16) contains six spring-loaded ejec
tor mechanisms permitting up to six practice bomb releases. The SUU-21A has elec
trically operated conformal doors which are opened for weapon delivery. The act of
loading a practice bomb forces the ejector plunger upward, compressing a spring
until toggle arms snap into a cocked position around the bomb, securing it to the
ejector. As the ejector operates (cocking or releasing), an indicator pin extends
from the side of the dispenser near the ejector being loaded and then retracts
within the dispenser contour. A red flagged stop guard is inserted into a slot over
the indicator pin hole to prevent release of a bomb-loaded ejector. The guards must
be removed prior to flight.
The relay box, located in the aft bay of the dispenser, contains circuits that con
trol door operations and the sequence of practice bomb releases. The circuit breaker
guards power to the door actuator motor in the dispenser and must be closed (pushed
in) prior to flight. The relay box also contains a two-position switch with AUTOMA
TIC and MANUAL positions. The switch determines if the doors close automatically or
remain open after each release. The rotary selector switch on the relay box can be
manually positioned to any of the ejector positions prior to takeoff and the switch
will automatically step to the next position after each release.
5-25
T.O. 1—1M—34
*
SUU-21/A PRACTICE BOMB DISPENSER
-_____ r______________________________
CHARACTERISTICS
WEIGHT, EMPTY 470 LB

LENGTH 13 FT
DIAMETER 17 IN.
FIGURE 5-16
5-26
T.O. 1-1M-34
SECTION VI
SAFE ESCAPE/SAFE SEPARATION
CONTENTS
PAGE
SAFE SEPARATION/SAFE ESCAPE.......................................................................................................
CD CD CD CD CD CD CD
CXI
Safe Escape ..........................................................................................................................................
CO
Safe Separation.....................................................................................................................................
ID
Safe Escape IVIaneuvers
CD CD
EXPLANATION OF SAFE ESCAPE/SAFE SEPARATION CHARTS.................................................
Minimum Release Altitude for Fuze Arming......................................................................................
00
Fragment Deconfliction for Formation Flights...............................................................................
6-1
T.O. 1- 1M-34
SAFE ESCAPE/SAFE SEPARATION
This section is designed to standardize terminology and methods of calculation for

safe escape/safe separation. Specific values for planning are aircraft-unique and
are found in appropriate aircraft Dash 34s.
Mission planning must include consideration

of safe escape requirements, safe separation
requirements for proximity-fuzed GP bombs,
vertical drop required for fuze arming, and
altitude lost during dive recovery. The
highest applicable altitude/time must be
used .
The release altitude derived for the mission planning form must include considera
tion of safe escape, safe separation, vertical drop required for fuze arming, and
altitude lost during dive recovery. The highest applicable altitude/time must be
used. Safe escape is the minimum release altitude that will provide the delivery
aircraft acceptable protection for weapon fragmentation. For all munitions, except
cluster bomb units (CBU) and flagging air-inflatable retarders (AIR), safe escape
is based on normal functioning of the munitions, with detonation at ground impact.
For the CBU, safe escape is based on failure of the canister to open and detonation
of the intact cluster at ground impact. Flagging AIR (MK 82/84) data are for the
AIR which fails to fully inflate. Safe separation corresponds to the minimum detona
tion time after release which will provide the delivery aircraft acceptable protec
tion from early weapon detonation (airburst). Safe separation requirements must be
met when employing proximity-fuzed general-purpose (GP) munitions. Safe separation
is not required for impact-fuzed GP bombs, because there is small likelihood of pre
mature detonation at fuze arming.
When MK 82 Snakeye I, MK 82 AIR, or MK 84 AIR

are configured for inflight high- or low-drag
selectability, the minimum M904 nose fuze arm
delay setting is 6 seconds, and the minimum
FMU-54 tail fuze arm delay setting is 2.5
seconds. These minimum settings do not apply
if the high-drag bomb release altitude
exceeds the low-drag bomb safe escape minimum
release altitude.
6-2
T.O. 1-1M-34
The Safe Escape/Safe Separation Charts (appropriate aircraft Dash 34) include two
sets of data which must be considered during mission planning to ensure safe
escape/safe separation criteria are satisfied. These data are as follows:
1. Time of Fall (Seconds). This is the minimum time from release at which the
weapon can detonate and satisfy the safe separation criteria. It equates to the
weapon time of fall from minimum safe release altitude for low-altitude delivery.
2. Minimum Release Altitude for Safe Escape (Feet). This altitude represents
the minimum altitude for release of a particular munition to ensure criteria for
safe escape are satisfied.
Safe escape/safe separation data consider all weapon fragments except an extreme few.
Lug/hardback components of bombs are an exception to published safe escape/safe
separation tables, in that they can travel higher and farther than normal bomb case
fragments. Fragments from the lug/hardback area are not normally included in the
computer model. Since most bombs are spin-stabilized, the probability of the
lug/hardback area fragments being aimed at the delivery aircraft is very small.
Also, weapons occasionally produce fragments not normally anticipated, which may fly
further than predicted. However, the frequency of these events causes them to be
treated as anomalies, and they are also not included in the computer model. The
behavior of the lug/hardback area fragments and the anomalies are not included in
the model, because they cannot be accurately predicted. It is operationally
accepted that the probability of being hit by these fragments is less than 1 in
The fragmentation model is redistributed in the computer solution to account for

weapon impact velocity. Also, the predicted impact angle is rotated 10 degrees to
account for possible flightpath disturbance and/or slight changes in the fragmen
tation pattern attributed to nose versus tail fuzing.
SAFE ESCAPE
The safe escape data provided are used in mission planning to determine the minimum
release altitude that will provide the delivery aircraft acceptable protection from
weapon fragmentation. These data are determined through a complex computer analysis
of weapon fragmentation envelopes relative to the specified delivery profile and
specific escape maneuver of the delivery aircraft. The data represent a probability
of being hit that is less than or equal to 1 chance in 1,000 (£0.001).
6-3
T.O. 1—1M—34
The safe escape data are provided only for single or

pairs release and level ripple/train deliveries followed
by a level, constant-speed, no-turn escape maneuver. For
ripple/train deliveries, when initiation of the escape
maneuver is delayed by the duration of the ripple
release, the minimum release altitude must be increased
to provide safe escape from the first weapon detonation
as follows:
For dive ripple/train deliveries, the release altitude

must be increased such that the last weapon is released
at or above the minimum release altitude. Add the alti
tude lost during the ripple/train release to the data
provided in the Safe Escape/Safe Separation Chart to
determine the increased minimum release altitude.
For level ripple/train deliveries followed by either a

level turn or pullup escape maneuver, increase the mini
mum release altitude by adding the ripple/train release
time (N-l times the release interval) to the listed time
of fall. Use this increased time of fall to find the
increased minimum release altitude in the ballistic
tables or in the Minimum Release Altitude for Fuze Arming
Chart. Since ballistic data are not provided for intact
CBU munitions, the increased minimum release altitude can
be estimated by using MK 82 low-drag, general-purpose
(LDGP) data.
NOTE
• The safe escape information presented is based upon a

probability of less than or equal to one chance in a
thousand (<0.001) that the delivery aircraft will be hit
by fragments when delivering a single bomb at the
minimum altitude for fragment clearance.
S Safe escape data are provided for target density alti

tudes of 0 and 5,000 feet. For density altitudes between
0 and 5,000 feet, a reasonable approximation may be
obtained by linear interpolation. For target density
altitudes above 5,000 feet, a reasonable approximation
may be obtained by extrapolation. Extrapolation is not
recommended for target density altitudes above 10,000
feet.
6-4
T.O. 1—1M—34
SAFE SEPARATION
Safe separation requirements must be met when employing proximity-fuzed GP bombs.
Safe separation is not required for impact-fuzed GP bombs. Safe separation differs
from safe escape (ground burst) in that it provides the delivery aircraft protection
from early weapon detonation (airburst). Therefore, safe separation requirements
are met by using a minimum fuze arming time that provides sufficient aircraft-to-
weapon separation prior to the fuze arming. The separation time required is the
time of fall listed for the minimum release altitude for safe escape.
WARNING
® When determining the minimum fuze arming time for safe

separation, the negative fuze arming tolerance and fuze
inherent delays must be included to ensure that the ear
liest possible arming time meets or exceeds the safe
separation time required.
• The safe separation data are provided only for single or

pairs release and level ripple/train deliveries followed
by a level, constant-speed, no-turn escape maneuver. For
ripple/train deliveries, when initiation of the escape
maneuver is delayed by the duration of the ripple release,
the minimum safe fuze arming time must be increased to
provide safe separation from the first weapon as follows:
The new minimum fuze arming time is determined by adding

the ripple/train release time (N-l times the release
interval) to the time of fall shown for the desired air
speed and escape maneuver.
NOTE
• The safe separation information presented is based upon a

probability of less than or equal to one chance in a
thousand (<0.001) that the delivery aircraft will en
counter fragments when delivering a single bomb at the
minimum altitude for fragment clearance.
• Safe separation data are provided for target density

altitudes of 0 and 5,000 feet. For density altitudes be
tween 0 and 5,000 feet, a reasonable approximation may be
obtained by linear interpolation. For target density
altitudes above 5,000 feet, a reasonable approximation
may be obtained by extrapolation. Extrapolation is not
recommended for target density altitudes above 10,000
feet.
65
T.O. 1-1M-34
SAFE ESCAPE MANEUVERS

The safe escape data are provided for specific safe escape maneuver profiles in the
appropriate aircraft Dash 34s.
Safe escape data are not provided for all

maneuver/weapon combinations. When planning
weapon deliveries at minimum release con
ditions, nominal deviations from planned con
ditions may result in a significant increase
in the risk of self-damage. Therefore, the
aircrew must observe the appropriate delivery
parameters, minimum release alti-tudes, and
recovery maneuvers required for safe escape.
EXPLANATION OF SAFE ESCAPE/SAFE

SEPARATION CHARTS
These charts provide safe escape/safe separation and vertical drop data required for
fuze arming for various weapons/fuze combinations, delivery parameters, and escape
maneuvers. Use the proper chart for mission plannning. The charts are located in
appropriate aircraft Dash 34.
The Safe Escape/Safe Separation Charts include three sets of data that must be con
sidered during mission planning to ensure safe escape/safe separation for munition
detonation and vertical drop to ensure fuze arming. These factors are defined as
follows:
1. Time of Fall (Seconds). This is the minimum time from release at which the
weapon can detonate and satisfy the safe separation criteria. It equates to the
weapon time of fall from minimum safe release altitude for low-altitude delivery.
For GP bombs with proximity fuzes, when arming time must be considered, the time of
fall is also the safe separation minimum fuze arming time.
2. Minimum Release Altitude for Safe Escape (Feet). This altitude represents
the minimum altitude for release of a particular munition to ensure criteria for
safe escape are satisfied.
6-6
T.O. 1~1M—34
WARNING
For ripple/train deliveries where initiation

of the escape maneuver is delayed by the dura
tion of the ripple/train release, the minimum
release altitude must be increased to provide
safe escape from the first weapon detonation.
If safe separation is required, the safe fuze
arming time must also be increased.
NOTE
Specific guidance for ripple/train deliveries

is provided for each aircraft Safe Escape and
Fuze Arming Chart.
3. Vertical Drop for Fuze Arming (Feet). These data include all delays that
affect fuze arming (wiring, retardation device opening time, fuze inherent delays,
and the positive tolerances on arming time. Vertical drop for fuze arming require
ments must be used in mission planning; this applies to both impact- and proximity-
fuzed weapons.
Mission planning must include consideration of

safe escape requirements, safe separation
requirements for proximity-fuzed GP bombs, ver
tical drop required for fuze arming, and alti
tude lost during dive recovery. The highest
applicable altitude/time must be used.
MINIMUM RELEASE ALTITUDE FOR FUZE ARMING

These charts are provided to supplement the Vertical Drop for Fuze Arming Data pro
vided in the Safe Escape Charts and are provided in the appropriate Dash 34.
If an arm time is selected for which data are not available in the Safe Escape
Charts, the user must determine the required release altitude using the Minimum
Release Altitude for Fuze Arming Charts provided in the appropriate aircraft Dash
34. First, inherent fuze delays and the positive arm time tolerance must be added
to the selected arm time to determine the required time of fall. Inherent delays
for specific fuzes are provided in the Fuze/Bomb Compatibility Chart in Section II.
Next, enter the Minimum Release Altitude for Fuze Arming Charts at that TOF to
6-7
T.O. 1—IM—34
determine the release altitude to insure fuze arming. Example: Safe separation
time and altitude required for fuze arming:
Aircraft A-10
Weapon MK 82 LDGP
Fuze FMU-113/B (inherent delay 0.5 sec)
Release mode Ripple
Number of weapons 6
Ripple interval 0.24 sec (240 msec)
Release angle -15 deg
Release velocity 300 KTAS
Escape maneuver 4-g/2-sec, wings-level (in-plane) pullup
Density altitude 5000 ft
Because the FMU-113/B is a proximity fuze, safe separation must be considered.

Enter the Safe Escape/Safe Separation Chart (A-10 used in this example) to find the
required safe separation time (presented as Time of Fall). For this example, the
value is 4.78 seconds.
However, because this is a ripple release, the required time of fall value must be
increased by the ripple release time. In this case, N-l equals 5, and the release
interval is 240 msec (0.24 sec). For this ripple release, the time of fall required
is :
4.78 + (5 x 0.24) = 4.78 + 1.2 = 5.98 sec
A 5-second arm time selection would result in the fuze potentially arming at exactly
5.0 seconds when the negative fuze tolerance (-0.5 second) and the inherent delay
(0.5 second) are considered. Therefore, a 5-second fuze setting will not satisfy
safe separation criteria. A 6-second fuze setting (5.90-second possible arm time)
will also not satisfy safe separation criteria. The 7-second setting allows fuze
arming as early as 6.80 seconds (7.0 - 0.7 + 0.5). Since 6.80 seconds is greater
than 5.98 seconds, safe separation criteria are satisfied.
In this case, 7 seconds is not listed in the Safe Escape/Safe Separation Chart.
Therefore, to determine this release altitude, enter the Minimum Release Altitude
for Fuze Arming Charts (appropriate aircraft Dash 34) with 8.2 (7.0 + 0.7 + 0.5)
seconds. For the A-10 aircraft, this value is 2,740 feet. The FMU-113/B is used to
detonate a bomb at 15 feet AGL (nominal). To ensure fuze arming above this
altitude, the last bomb must be released at or above 2,755 feet AGL.
FRAGMENT DECONFLICTION FOR FORMATION FLIGHTS
WARNING
During simultaneous formation deliveries,

the wingman must consider safe escape from
both his own and his leader’s munitions.
6-8
T.O. 1- 1M-34
MAXIMUM BOMB/ROCKET FRAGMENT TRAVEL CHART

ALTITUDE HORIZONTAL RANGE TIME OF FLIGHT
IMPACT (FEET) (FEET) (SECONDS)
MUNITION ANGLE
(DEGREES) SEA 5000 SEA 5000 SEA 5000
LEVEL FEET LEVEL FEET LEVEL FEET
MAXIMUM BOMB FRAGMENT TRAVEL
MK 82 2050 2325 2310 2625 24.0 25.5

ALL TYPES
MK 84 2750 3100 3100 3350 30.0 31.2

ALL TYPES
CBU
(INTACT 1380 1575 1645 1850 19.4 20.6
CLUSTER)
ALL TYPES
BLU-26/B
(CBU-24/B)
960 1085 1160 1310 16.3 17.3
BLU-59
(CBU-49/B)
BLU-61A/B 665 755 775 880 14.2 15.0

(CBU-52/B)
BLU-63/B, A/B
(CBU-58/B)
430 490 490 560 11.6 12.3
BLU-86/B, A/B
(CBU-71/B, A/B)
MK 20 ROCKEYE 1380 1575 1645 1850 19.4 20.6

(INTACT CLUSTER)
MK 118 695 790 800 915 14.7 15.5

(MK 20)
MAXIMlJM ROC KE T FRAGM1ENT TRAVEL
5 1030 1170 1430 1630 17.1 18.1

MK 1 10 1015 1150 1425 1630 16.9 17.9
20 985 1110 1425 1620 16.5 17.5
30 930 1045 1410 1610 16.0 17.0
5 1190 1360 1620 1850 18.5 19.5

MK 5 10 1175 1340 1620 1845 18.3 19.4
20 1140 1300 1615 1840 18.0 19.1
30 1110 1265 1600 1825 17.7 18.8
5 1010 1145 1335 1515 17.1 18.2

M151 10 1000 1135 1330 1515 17.0 18.1
20 990 1110 1325 1510 16.9 17.8
30 965 1085 1300 1500 16.6 17.6
FIGURE 6-1
6-9
T.O. 1-1M-34
MAXIMUM BOMB FRAGMENT TRAVEL
A Maximum Bomb Fragment Travel Chart is provided in FIGURE 6-1. These date must be
used to determine fragment deconf1iction between multiple aircraft attacks. The
envelopes present the maximum altitude and maximum horizontal range anticipated for
the worst-case fragment of the bomb case, and the time from detonation until all
bomb case fragments have settled to the ground. Data are provided for sea level and
5,000 feet target density altitudes. Interpolation between sea level and 5,000 feet
and extrapolation up to 10,000 feet are permissible.
NOTE
Maximum fragment travel envelopes consider

all except an extreme few of the weapon
fragments. Lug/hardback components of bombs
are an exception, in that they can travel
higher and farther than bomb case fragments.
However, their behavior cannot be accurately
predicted, and it is operationally accepted
that the probability of being hit by these
fragments is less than one in 1,000.
FRAGMENT DECONFLICTION
For all weapons employment involving simultaneous or sequential deliveries on the

same target or on separate targets in the same area, flights must ensure that either
time, altitude, or horizontal fragment deconflietion is achieved.
Time Deconfliction
Time separation between aircraft deliveries must be equal to or greater than the
time the preceding weapon’s fragments are in the air, plus the delivery time of fall
of the preceding munition. For example, 30 seconds spacing is the minimum time
between aircraft using MK 82 deliveries at sea level with a bomb TOF of 6 seconds
(24 seconds fragment TOF +6 seconds bomb TOF = 30 seconds). See FIGURE 6-1.
Altitude Deconfliction
Following aircraft must recover above the maximum altitude for the fragment envelope
for the preceding attacker’s munition. For example, a 3,100-foot minimum altitude
is required for a MK 84 delivery at a 5,000-foot target density altitude. See
FIGURE 6-1.
6-10
Horizontal Deconfliction
Following aircraft must remain outside the maximum horizontal range of the fragment
envelope for the preceding attacker’s munition. For example (FIGURE 6-1), 2,310
feet lateral separation provides deconfliction from a MK 82 at sea level. For CBU
munitions, the horizontal deconflietion (FIGURE 6-1 and FIGURE 6-2) must be equal to
or greater than the larger of the following:
1. Maximum horizontal range of

fragment envelope for the intact cluster
HORIZONTAL DECON
2. Sum of CBU pattern half-width/
FLICTION FOR CBU radius and maximum horizontal range of the
fragment envelope for the submunition.
Single dispenser pattern data may be found
in JMEM document TH61A1-3-2.
For simultaneous formation deliveries on

the same target or area, when time, alti
tude, or horizontal deconf1iction will not
be achieved, the wingmen must be in close
(fingertip) or line-abreast formation and
level with to higher than the leader. In
this type of delivery, fragment protection
is provided by the safe escape minimum
release altitude.
The wingmen must not drop back to

any type of route or trail posi
tion during formation deliveries;
the probability of being hit by
fragments will be significantly
increased.
FIGURE 6-2
10
6-11(6-12 blank)
T.O. 1—IM—34
SECTION VII
SUPPLEMENTARY DATA, ERROR
ANALYSIS
CONTENTS
PAGE
WEAPON DELIVERY............................................................................................................................ 7-2

Armament Reference Lines. .............................................................................................................. 7-2
Bombing Geometry................... ........................................................................................................ 7-2
ERROR ANALYSIS................................................................................................................................. 7-12
Bombs.................................................................................................................................................. 7-12
Errors Affecting Ordnance Impact................................ ....................................................................7-12
Release Altitude Error........................................................................................................................... 7-13
Dive Angle Error................................................................................................................................... 7-13
Airspeed Error........................................................................................................................................ 7-13
Miss Distances Attributed to Delivery Error...................................................................................... 7-18
Effect of TAS Error............................................................................................................................. 7-20
Effect of Release Altitude Error............................................................................................ 7-22
Effect of Dive Angle Error.................................................................................................................. 7-23
Error Analysis Chart............................................................................................................................. 7-24
Rockets/Guns........................................................................................................................................ 7-24
Other Delivery Errors........................................................................................................................... 7-27
Miscellaneous Supplementary Data..................................................................................................... 7-29
T.O. 1—1M—34
WEAPON DELIVERY
ARMAMENT REFERENCE LINES

The various reference lines used in this manual are illustrated in FIGURE 7-1•
BOMBING GEOMETRY
In dive deliveries, the bomb is released manually from a fixed dive angle; approach
to the target is at a preplanned airspeed and altitude. After release, the bomb is
accelerated downward by gravity and slowed by aerodynamic drag. These factors cause
the bomb to travel along a curved path and to impact the ground some distance short
of the intersection of the aircraft’s extended flightpath and the ground.
The geometry of a manual dive bombing problem is illustrated in FIGURES 7-2 through
7-4. The ballistic tables for free-fall munitions contained in the appropriate
aircraft Dash 34 give sight depression from flightpath (DFP) in mils. DFP is predi
cated on four factors: gravity, drag, ejection forces that provide aircraft/bomb
separation, and parallax.
Gravity, drag, and ejection forces are used for a given dive angle, altitude, and
airspeed. Using trigonometry, the DFP can be calculated with bomb range, release
altitude, and dive angle.
NOTE
Level bombing is a specific case of dive

bombing where the dive angle is zero. There
fore, by using a dive angle equal to zero,
this discussion applies equally to dive and
level bombing.
The following parameters are defined:
r - Denotes parameters at weapon release
Yr - Release altitude, feet above ground level (AGL)
BR - Bomb range, feet
0 - Dive angle, degrees (measured below horizontal)
0r - DFP at release
Sp - Slant range from release point to target, feet
ar - Zero sight line angle of attack (AOA) at release
7-2
T.O. 1- 1M-34
REFERENCE LINES
NOTE:
WING AND FUSELAGE PYLONS,STANDBY RETICLE ZSL, A-7
RADAR, AND GUN BORE LINES ARE ALL PARALLELTO EACH
OTHER AND ARE DEPRESSED 3° FROM THE FUSELAGE STANDBY RETICLE EYE
REFERENCE LINE (FRL).
A STANDBY RETICLE ZERO SIGHTLINE (ZSL) D GUN BORE LINE

B FUSELAGE REFERENCE LINE (FRL) E FLIGHTPATH
C FUSELAGE AND WING PYLON LINE, RADAR LINE F DEPRESSED SIGHTLINE
1 STANDBY RETICLE ZERO SIGHTLINE ORIENTATION

(3° BELOW FRLPARALLELWITH PRL)
2 ZERO SIGHTLINE ANGLE OF ATTACK
3 SIGHTLINE DEPRESSION FROM FLIGHTPATH (FROM
BOMBING TABLES)
4 ACTUALSIGHTSETTING
7-3
T.O. 1-1M-34
A ZERO SIGHTLINE (ZRL) D GUN BORE LINE

B FUZELAGE REFERENCE LINE (FRL) E FLIGHTPATH (VELOCITY VECTOR)
C LAUNCHER LINE F DEPRESSED SIGHTLINE
2 ANGLE OF ATTACK(a)
3 SIGHTLINE DEPRESSION FROM FLIGHTPATH (DFP)
(OBTAIN FROM WEAPON DELIVERY TABLES FOR BOMBS, STORES, AND GUN)
4 ACTUAL SIGHT SETTING
NOTES:
• ZERO SIGHTLINE (ZSL) IS PARALLELTO FUSELAGE REFERENCE LINE (FRL)
• EFFECTIVE GUN BORE LINE IS BELOW FRL (1° 55' 50")
• BASED UPON GUN AND INSTALLATION ANGLE 0(2°O6' 39") BELOW FRL
FUSELAGE AND WIRE PYLON LINE 4° BELOW FRL
• GUN PARALLAX ERROR (61.0 INCHES)
7-4
T.O. 1—1M—34
REFERENCE LINES
A GUN CROSS LINE, ZERO SIGHTLINE
B WATER LINE (WL), FUSELAGE REFERENCE LINE, RADAR BORESIGHT LINE
C AIM-9 MISSILE BORESIGHT LINE
D AIRCRAFT FLIGHTPATH
E DEPRESSED PIPPER SIGHTLINE
ANGLES
1 ANGLE OF ATTACK
2 GUN CROSS ELEVATION ANGLE (2° or 35 MILS ABOVE WL)
3 PIPPER DEPRESSION ANGLE FROM ZERO SIGHTLINE
4 PIPPER DEPRESSION ANGLE FROM FLIGHTPATH
5 AIM-9 WEAPON DEPRESSION ANGLE (0.5u OR 9 MILS)
F-16 15°(261.75 MILS) OVER THE

NOSE VISION LIMIT
FS 140.0
0° REFERENCE LINES (PARALLELTO FRL)

A A/C LONGITUDINAL AXIS, FRL, WING CHORD, RADAR ZERO REFERENCE LINE
B GUN BORE LINE
C HUD ZERO SIGHTLINE, HUD MINIMUM ERROR BORESIGHT NOTE
3° (52.35 MILS) REFERENCE LINES (3° DOWN FROM FRL) HUD SIGHTLINE AND GUN BORE LINE
D WING PYLONS DO NOT INTERSECT
E AIM-9 MISSILES
1.72° (30.01 MILS) REFERENCE LINE (1.72° DOWN FROM FRL)
F CENTERLINE PYLON (STATION 5)
7-5
T.O. 1—1M—34
F-4
REFERENCE LINES
A FUSELAGE REFERENCE LINE (FRL); PIPPER SIGHTLINE AT ZERO MILS DEPRESSION
B AIRCRAFT FLIGHTPATH
C RADAR ANTENNA BORESIGHT (BST) LINE
D DEPRESSED PIPPER SIGHTLINE
ANGLES
1 ANGLES OF ATTACK
2 2° (35 MILS) BELOW FRL
3 SIGHT DEPRESSION FROM ZERO SIGHTLINE, OR FROM FRL (ACTUAL SIGHT SETTING)
4 SIGHT DEPRESSION FROM FLIGHTPATH (DFP)
F-111
A WING CHORD LINE

B FUSELAGE REFERENCE LINE (FRL)
C GUN BORE LINE
D LAUNCHER LINE, CAGED SIGHTLINE
E FLIGHTPATH (VELOCITY VECTOR) (TYPICAL)
F DEPRESSED SIGHTLINE (TYPICAL)
G ZERO SIGHTLINE (ZSL)
1 ANGLE OF ATTACK
2 SIGHT DEPRESSION FROM FLIGHTPATH (DFP)
3 ZERO SIGHTLINE ANGLE OF ATTACK
4 ACTUAL SIGHT SETTING
7-6
T.O. 1-1M-34
RELEASE GEOMETRY
TOTAL DEPRESSION
FIGURE 7-3
7-7
T.O. 1-1M-34
ROLLOUT GEOMETRY ■ ■ - - • ■ .
FIGURE 7-4
D - Total depression set in the HUD/sight for weapon release
i - Denotes initial parameters (rollout)
AOD - Aim off-distance, feet
Yi - Rollout altitude, feet
IPP - Initial pipper placement, mils
- Zero sight line (ZSL) AOA at rollout
d) £ - Depression from flightpath at rollout
S - Sight line from the pilot’s eye to target, at rollout
C - Horizontal range from target at rollout
7-8
T.O. 1—1M—34
Using these parameters, DFP at release (^r) is calculated as follows:
The angle Yr is the sum of dive angle and DFP.
Therefo re
= Yr - e ’
The tangent of Yr equals Yr divided by BR.
Yr
tan Y r = —~
BR
and
■ _ /Yr\ '
— tan i —) ~ 9
_ \ BR /
This yields a DFP predicted on gravity, drag, and ejection force. Parallax is caused
by the distance from the bomb to the pilot’s eye, and will cause a small change in
DFP. For any dive angle, the horizontal (Ph) and vertical (Pv) components of
parallax can be found in FIGURE 7-5.
Release altitude corrected for parallax (Yp) is:
Yp = Yr + (Pv> FIGURE 7-5)
Bomb range corrected for parallax (BRp) is:
BRp = BR - (PH, FIGURE 7-5)
Therefore, DFP (expressed in mils) predicted on gravity, drag, ejection forces, and
parallax is:
DFP (^r) = 17.45
For a given release altitude (Yr), dive angle (6) and knots true airspeed (KTAS), BR,
SR, and 0r are given in the appropriate aircraft Dash 34 ballistics tables. DFP is
not the total sight setting. The aircraft has some AOA that must be considered when
calculating total sight depression. In dive bombing, the zero sight line (sight
angle when zero mils is set into the HUD/sight is used as a reference. The zero
sight line angle of attack (ZSL AOA) is given in Section VIII as a function of
release KCAS, aircraft gross weight, and dive angle.
The total depression (or sight setting) is the sum of DFP and ZSL AOA at release:
D = + ar
7-9
T.O. 1—1M—34
HORIZONTAL/VERTICAL PARALLAX CORRECTIONS
DIVE
ANGLE A-7 A-10 F-4 F-15 F-16 F-lll
(DEG)
HORIZONTA l parall;VX CORRE(3TIONS (13h, FEEri
0 15.4 17.5 18 21 17.3 30

5 15.6 18.0 18.5 21.4 17.6 30.2
10 15.6 18.3 18.9 21.6 17.7 30.2
15 15.5 18.5 19.2 21.6 17.7 30.0
20 15.3 18.5 19.3 21.4 17.6 29.6

25 15.0 18.4 19.3 21.1 17.3 28.9
30 14.6 18.2 19.1 20.7 16.9 28.0
35 14.0 17.8 18.8 20.1 16.4 26.9
40 13.4 17.3 18.3 19.3 15.7 25.6

45 12.7 16.6 17.7 18.4 14.9 24.0
50 11.8 15.8 16.9 17.3 14.0 22.3
55 10.9 15.0 16.1 16.1 13.0 20.5
60 9.9 13.9 15.1 14.8 11.9 18.5
VERTICAL PARALLAX CORRECTIONS (I’v, FEET)
0 2.5 6.0 7.0 5.0 3.8 4.0

5 1.1 4.5 5.4 3.2 2.3 1.4
10 -0.2 2.9 3.8 1.3 0. 7 -1.3
15 -1.6 1.3 2.1 -0.1 -0.8 -3.9
20 -2.9 -0.3 0.4 -2.5 -2.3 -6.5

25 -4.2 -2.0 -1.3 -4.3 -3.9 -9.1
30 -5.5 -3.6 -2.9 -6.2 -5.4 -11.5
35 -6.8 -5.1 -4.6 -7.9 -6.8 -13.9
40 -8.0 -6.7 -6.2 -9.7 -8.2 -16.2

45 -9.1 -8.1 -7.8 -11.3 -9.5 -18.4
50 -10.2 -9.6 -9.3 -12.9 -10.8 -20.4
55 -11.2 -10.9 -10.7 -14.3 -12.0 -22.3
60 -12.1 -12.2 -12.1 -15.7 -13.1 -24.0
FIGURE 7-5
T.O. 1—1M—34
For the planned combination of dive angle, altitude, and airspeed, this sight set
ting will define the proper release point. Any variation in any parameter will
nullify this relationship, and the sight setting will be in error (it will not de
fine the proper bomb range).
Several other relationships exist that are useful in solving the dive bombing
problem.
The AOD is the distance from the target to the point where the theoretical extension
of the aircraft flightpath intersects the ground. This point is called AOP and is
useful in solving the dive bombing problem. In order to arrive at the proper point
in space, as defined by the sight setting, the aircraft must be flown along the
flightpath ending at the AOP, as depicted in FIGURE 7-4. If the AOP can be visual
ized on the ground, the aircraft can be flown toward the AOP with the proper dive
angle to intercept the preplanned flightpath. Normally the AOP is difficult to
visualize; therefore, another method must be used to point the aircraft fightpath
toward the AOP.
The aircraft flightpath can be pointed toward the AOP using the geometric relation
ships depicted in FIGURE 7-4. If rollout is achieved at the preplanned point and
the pipper is positioned the proper distance short of the target at rollout, the
flightpath will necessarily be the proper distance (AOD) past the target. This IPP
is measured in mils short of the target, and can be computed as follows:
IPP = D - 0^ -
The ZSL AOA at rollout is given in Section VIII as a function of rollout KCAS, gross
weight, and dive angle.
Just as (j)r subtends the AOD at release altitude (FIGURE 7-2), subtends the AOD at
rollout altitude and is computed in the same manner as (|)r.
IPP = D -
NOTE
Parallax applies to rollout conditions simi

lar to release conditions. However, it is a
very small correction and is essentially zero.
AOD and rollout DFP (0^) can also be determined using the aim off-distance charts in
Section VIII.
7 11
T.O. 1—IM—34
ERROR ANALYSIS
BOMBS
Variations in delivery parameters change the bomb trajectory and affect the accuracy
of the sight setting. If the bomb is released from the preplanned bomb range, but
planned delivery parameters are not attained, the bomb will miss the target. This
miss distance is called trajectory error (TE).
The sight setting is computed using the planned bomb range, altitude, dive angle,
and airspeed. Any change in these parameters will change the required DFP and/or
ZSL AOA and, therefore, the sight setting. If preplanned delivery parameters are
not attained and the bomb is released using the precomputed sight setting (pipper
on the target), the bomb will miss the target. This miss distance is called release
point error (RPE).
The miss distance caused by the combination of trajectory error and release point
error is called net error (E). Release point and trajectory errors can be either
compounding or compensating. Net error therefore is the algebraic sum of RPE and TE.
E = RPE + TE
NOTE
Net error is always in the direction of RPE.

(When RPE and TE are compensating errors, RPE
is always larger, In instances where TE is
larger than RPE, the two are compounding
errors.)
ERRORS AFFECTING ORDNANCE IMPACT

The effect of varying each delivery parameter can be examined independently. In
each case, only the parameter listed will be varied; all other parameters are
constant. The pipper is always on the target.
To understand the specifics of TE and RPE, the two phenomena can be thought of as
discussed in the following paragraphs.
TRAJECTORY ERROR
The product of a rate and a time equals a distance (distance = rate x time). In
bombing, rate is horizontal velocity, time is the time of fall, and distance is bomb
range. Therefore, the bomb range depends on the horizontal velocity at release and
the time of fall of the weapon. Any change in a delivery parameter that will change
the time of flight (TOF) or the horizontal velocity at release will change the bomb
range. If horizontal velocity and/or TOF are increased, the bomb range will
increase; and, if the bomb is released from the preplanned bomb range, a long TE
will result. The opposite is true of decreased velocity or TOF.
7-12
T.O. 1—1M—34
RELEASE POINT ERROR

The preplanned sight setting provides the proper sight depression from the planned
flightpath, based on planned release conditions. Variations in release parameters
will cause an incorrect sight depression from the planned flightpath. The actual
depression from the planned flightpath is called effective depression. Effective
depression determines the actual range from the target at release. With an in
creased effective depression, the pipper will arrive on target later than required.
This late sight-picture will cause a long RPE. Conversely, decreased effective
depression will cause an early sight-picture and a short RPE (FIGURE 7-6 and 7-7).
RELEASE ALTITUDE ERROR

Ordnance release at an altitude higher than planned will impact short of the target
(FIGURE 7-8). The increased altitude causes an early sight-picture that produces an
RPE short of the target. The higher release altitude will increase the TOF and bomb
range, and cause a TE that tends to be long. In this case RPE and TE are compensat
ing but RPE is greater, resulting in a net error short of the target. The opposite
is true of ordnance released lower than planned. A late sight-picture causes a long
RPE, and the decreased bomb range tends toward a short TE. Net error, because of the
dominance of RPE, is long. The fallacy of releasing low (pressing) becomes imme
diately apparent, as the ordnance will overshoot the target, and the aircraft will
be further exposed to the bomb blast and fragmentation envelope.
DIVE ANGLE ERROR

Ordnance released at a dive angle shallower than planned will impact short of the
target (FIGURE 7~9). The decreased dive angle causes an early sight-picture that
produces a short RPE. The decreased downward velocity at release will increase TOF,
and the increased bomb range will cause a TE that tends to be long. Again RPE and
TE are compensating, with RPE being greater and net error short of the target. A
steeper than planned dive angle results in a late sight-picture and long RPE. The
increased downward velocity at release will decrease TOF, decrease bomb range, and
cause a TE that tends to be short. Again RPE and TE are compensating, with RPE
being greater and net error long of target.
AIRSPEED ERROR
Ordnance released at an airspeed slower than planned will impact short of the target
(FIGURE 7-10). As airspeed is decreased AOA must be increased to maintain the same
flightpath. As angle of attack is increased, the effective sight depression below
flightpath is reduced, causing an early sight-picture. As in other cases, an early
sight-picture produces a short RPE. The lower release airspeed will reduce horizon
tal velocity and bomb range, producing a short TE. RPE and TE are compounding
errors in this case, and net error is necessarily short of the target. Increased
airspeed will reduce AOA, increase effective sight depression, cause a late sight
picture, and result in a long RPE. The bomb range will be increased, resulting in a
long TE. Again RPE and TE are compounding errors, resulting in a long net er Dr.
7-13
T.O. 1—1M—34
RELEASE POINT ERROR (AIRSPEED/DIVE ANGLE)
1 SIGHT DEPRESSION WITH PLANNED PARAMETERS.

2 DECREASED EFFECTIVE DEPRESSION DUE TO DECREASED AIRSPEED OR DIVE ANGLE.
3 INCREASED EFFECTIVE DEPRESSION DUE TO INCREASED AIRSPEED OR DIVE ANGLE.
FIGURE 7-6
RELEASE POINT ERROR (ALTITUDE)
1 SIGHT PICTURE WITH PLANNED PARAMETERS.

2 EARLY SIGHT PICTURE DUE TO REDUCED RELEASE ALTITUDE.
3 LATE SIGHT PICTURE DUE TO INCREASED RELEASE ALTITUDE.
FIGURE 7-7
7-14

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T.O.

SECTION AIR-TO-SURFACE MUNITIONS 1-1

SECTION FUZES 2-1

SECTION III SPECIAL EQUIPMENT 3-1

SECTION IV AIR-TO-AIR MISSILES 4-1

SECTION V SUSPENSION EQUIPMENT 5-1

SAFE ESCAPE/SAFE SEPARATION 6-1

SUPPLEMENTARY DATA, ERROR 7-1

PURPOSE AND SCOPE

SUPPLEMENTS TO THIS MANUAL

SECTION I, AIR-TO-SURFACE MUNITIONS

SECTION II, FUZES

SECTION III, SPECIAL EQUIPMENT

SECTION IV, AIR-TO-AIR MISSILES

SECTION V, SUSPENSION EQUIPMENT

SECTION VI, SAFE ESCAPE/SAFE SEPARATION

SECTION VII, SUPPLEMENTARY DATA, ERROR ANALYSIS

SECTION VIII, MISSION PLANNING

EXTERNAL STORES LIMITATIONS

DEFINITION WORDS "SHALL,” "WILL,”

WARNINGS, CAUTIONS, AND NOTES

Operating procedures, techniques, etc., which

Operating procedures, techniques, etc., which

An operating procedure, technique, etc.,

YOUR RESPONSIBILITY - TO LET US KNOW

1. Longitudinal axis: This axis is parallel to the fuselage

2. Vertical axis: This axis is perpendicular to the longitudinal

3. Lateral axis: This axis rotates about the longitudinal axis

AN - A prefix to denote use by Army, Air Force, and Navy.

BOMB STICK - The number of bombs released during a ripple delivery.

BOMB TRAJECTORY - The path of a bomb from release to impact.

BULLET DISPERSION - Deviation of a bullet trajectory from the aiming point.

COCKPIT G - Acceleration forces on the aircraft as read from the g-meter.

CORRECTED SIGHT DEPRESSION - True sight depression corrected for a headwind or

DUD - A round or bomb that fails to explode.

FIRE BOMB - An incendiary or napalm-filled bomb.

FIRE PULSE - An electrical impulse transmitted to fire/release stores.

INITIAL POINT (IP) - A point over which an aircraft begins an attack.

PICKLE - The act of depressing the weapon release button.

PREDICTION ANGLE - Total lead angle required after calculations.

PYLON - A component attached to the aircraft to carry, arm, release, or jettison

RADIAL G - Cockpit g plus or minus the component of gravity.

SLANT RANGE - Line-of-sight distance from the aircraft to the target.

TRAJECTORY - Flightpath from release to impact.

VELOCITY VECTOR - A vector quantity denoting both magnitude and direction.

VIP - Visual identification point.

1-2 GP Bomb ..................... 1-8 1-21 Low Altitude Indirect

1-9 MK 82 Snakeye and MK 36 1-28 Effect of G Bias on Missile

Number Title Page Number Title Page

1-40 SUU-13 Dispensers .......... 1-68

1-49 MK 20 Mod 2, 3, and 4 2-8 Ml and M1A1 Fuze Extenders.. 2-13

1-57 30mm Ammunition ............. 1-94 2-16 FMU-26A/B and FMU-26B/B

Number Title Page Number Title Page

2-22 FMU-124A/B Impact Bomb 3-2 AN/AVQ-23A/B PAVE SPIKE

2-27 FMU-110/B Selectable Arming 3-8 AN/PAQ-3 MULE ............... 3-12

2-33 FZU-37A/B Fuze Initiator ... 2-55 3-14 C-6631/ALQ-119 Control

Number Title Page Number Title Page

6. CYCLOTOL: This is a mixture of 60 percent RDX and 40 percent TNT. It is some

13. PICRATOL: Picratol is a mixture containing 52 percent Explosive D and 48 per

There are various models of adapter