412 MMS Sar CH97
412 MMS Sar CH97
412 MMS Sar CH97
CHAPTER 97 AVIONICS
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Paragraph Chapter/Section Page
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Number Title Number Number
I-
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AVIONICS SYSTEMS
00000
00000
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97-2 Avionics systems - description ................ 97-00-00 5
97-3 Airframe components ........................... 97-00-00 5
'a)
97-4 Energizing power buses for functional tests .... 97-00-00 5
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00000000
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97-7 Test procedure ................................. 97-00-00 9
97-10 Troubleshooting ................................ 97-00-00 13
CCD-
97-22 97-00-00 17
00000000
00000000
00000000
00000000
Navigation system (GNS-X) ......................
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00000000
00000000
00000000
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97-23 Test procedure ................................. 97-00-00 17
97-24 Troubleshooting ................................ 97-00-00 17
97-25 Removal procedures ........................... 97-00-00 19
97-35 Installation procedures ......................... 97-00-00 20
97-45 Inspection procedures .......................... 97-00-00 21
97-46 Cleaning procedures ........................... 97-00-00 21
97-47 Repair or replacement ......................... 97-00-00 21
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Paragraph Chapter/Section Page
Number Title Number Number
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97-59 Repair or replacement ......................... 97-00-00 26
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00000000
00000000
00000000
00000000
00000000
00000000
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97-61 Test procedures ................................ 97-00-00 27
97-62 Troubleshooting ................................ 97-00-00 29
97-63 Removal procedures ........................... 9700-00 31
97-67 Installation procedures ......................... 97-00-00 31
97-71 Inspection procedures .......................... 97-00-00 31
97-72 Cleaning procedures ........................... 97-00-00 32
97-73 Repair or replacement ......................... 97-00-00 32
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97-75 Test procedures ................................ 97-00-00 33
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97-94 97-00-00 47
000
97-00-00
Page 2
BHT-412-MMS-SAR
FIGURES
C
Figure Page
Number Title Number
0
97-5 Doppler - major component location ........................................ 24
97-6 Radio altimeter system - major component location ........................ 28
I
97-7 Weather radar system - major component location ......................... 34
97-8 DATA NAV III system wiring diagram ........................................ 49
97-9 GNS-X system wiring diagram ............................................... 51
97-10 Doppler velocity sensor wiring diagram ...................................... 55
O
TABLES
Table Page
Number Title Number
17
-' -'
97-00-00
Page 314
BHT-412-MMS-SAR
AVIONICS
AVIONICS SYSTEMS
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97-1. AVIONICS SYSTEMS. AC FEEDERS BUS 2 115V
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AC FEEDERS BUS 3 115V
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97-2. AVIONICS SYSTEMS -
DESCRIPTION. AC FEEDERS EMERG BUS 115V
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W
The supplemental avionic equipment installed AC FEEDERS BUS 1 26V
m
000
m
in the search and rescue (SAR) configured
model 412 helicopter consists of the radio AC FEEDERS BUS 2 26V
m
m
altimeter system, and the weather radar
system. Other customizing avionic equipment AC FEEDERS BUS 3 26V
m
m
CO
installed includes Doppler, DATA NAV Ill, and
navigation system (GNS-X). AC FEEDERS EMERG BUS 26V
m
m
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NO. 1 ESNTL BUS FEEDERS (4)
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97-3. AIRFRAME COMPONENTS.
NO. 2 ESNTL BUS FEEDERS (4)
m
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Components that are a part of the avionics
configuration and are termed airframe
.-
electrical items:
GEN 2 FIELD
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z
97-4. ENERGIZING POWER BUSES FOR C. Set INV 1 switch and INV 2 switch to
>
m
1. The following is a general procedure for d. Close all remaining ac circuit breakers
energizing ac and do buses when using an to load the inverters.
external power source during functional
X
MANUAL.
a. Set BATTERY BUS 1 switch and
BATTERY BUS 2 switch to ON. 2. To energize avionics systems or sets,
refer to functional test procedures for
b. Close the following circuit breakers: individual systems or sets.
97-5. ILLUSTRATIONS.
MASTER CAUTION
For information/location of supplemental
AC FEEDERS BUS 1 115V avionics systems or customizing components
C
97-00-00
Page 5
BHT-412-MMS-SAR
installed in search and rescue configuration Table 97-1. Avionics equipment list
figures 97-1
helicopter, refer to figures 97-7
97-1 through 97-7. (Cont)
0
CD
CD
CD
For code designation correlation, refer to
o
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a)
Avionics Equipment List (Table 97-1) and REF DES NOMENCLATURE
0 3
0
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r
figures 97-8
figures 97-13 for supplemental
97-8 through 97-13
avionic systems wiring diagrams installed in 3408E3P1 CONN, RADIO ALTIMETER
search and rescue configured helicopters. ANTENNA
3408E4 ANTENNA
Table 97-1. Avionics equipment list 3408 E4 P 1 CONN, RADIO ALTIMETER
ANTENNA
REF DES NOMENCLATURE 3408J1 CONN
3408J2 CON N, TAI LBOOM
DISCONNECT
2301 C P2J 1 A CONN, PILOT ICS
3408J3 CONN, TAI LBOOM
2301 C P2 P 1 A CONN, PILOT ICS
DISCONNECT
2303CP2J1 A CONN , COM 2
CO
3408J4 CONN
2303C P2 P 1 A CONN , COM 2
3408J5 CONN, TAILBOOM
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3405J5 3408 P 1
000000
DISCONNECT 3408P2 CONK
3405 R E2 RECEIVER, NAV
0
3408P3 CONN
3405 R E2 P2 CONN, NAV RECEIVER 3408P4 CONN
3406CB1 CIRCUIT BREAKER, ADF 3408P5 CONK
3406RE1 RECEIVER, ADF 3408P6 CONN
3406RE1P1 CONN, ADF RECEIVER 3408TR 1 ALTIMETER, RADIO
3408CB1 CIRCUIT BREAKER, RAD
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ALT ALTM
3408DS2P1 CONN, PILOT RAD ALT 3410CP1J1A CONK, TRANSPONDER
INDICATOR 3410CP1 P1 A CONN,TRANSPONDER
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97-00-00
Page 6
BHT-412-MMS-SAR
Table 97-1. Avionics equipment list Table 97-1. Avionics equipment list
3
E
(Copt) (Cont)
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T
TEST PROCESSOR UNIT
3415A1 NAVIGATION 3415RE1P2 CONK, RECEIVER
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MANAGEMENT UNIT (NMU) PROCESSOR UNIT
3415A1 P1 A CONN, GNS-X NMU 3415WT1 TERMINAL BOARD,
T
3415A1P1B CONN, GNS-X NMU GROUND
3415A2 CONFIGURATION MODULE 3420A1 CONTROL, WEATHER
RADAR
3415A2P1 CONK, CONFIGURATION
C
0
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COMPUTER, DATA NAV
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MODULE 3420A2
3415A3 PORTABLE DATA 3420A2 P 1 CONN, DATA NAV
TRANSFER UNIT COMPUTER
3420CB1 CIRCUIT BREAKER, WXRAD
0
3415A3P1 CONK, PORTABLE DATA
TRANSFER UNIT STB
3420CB3 CIRCUIT BREAKER, DATA
0
3415CB1 CIRCUIT BREAKER, NMU
NAV
3415CB2 CIRCUIT BREAKER, RPU
3420C P 1 DATA NAV CONTROL UNIT
3415CP1 CONTROL DISPLAY UNIT
(CDU) 3420CP1P1 CONN, DATA NAV
CONTROL UNIT
3415CP1P1 CONN, CDU
Z
00
3420DS1 P1
3415CR2 DIODE
3420DS1 P2 CONN , COLOR INDICATOR
3415CR3 DIODE
3415C R4 DIODE
3420E1 ANTENNA
CONN , ANTENNA
,--
3420E1 P1
3415C R5 DIODE
CONK , TEE
W
3420J1
3415DS1 LIGHT, COPILOT DISPLAY
3415DS2 LIGHT, PILOT DISPLAY
3420J1 C CONN
3420J2 CONK , TEE
3415DS3 LIGHT, COPILOT DISPLAY
3415DS4 LIGHT, PILOT DISPLAY
3420J2C CONK
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CONK , TEE
00000000
3420J3
0
CONN , TEE
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3420J5
3415E4 ANTENNA, G PS
3415E4P1 CONN, G PS ANTENNA
3420J5C CONN
3415G2 DOWN CONVERTER
3420 P 1 A CONN
3415G2P1 CONN, DOWN CONVERTER
3420P1 B CONK
3420 P 1 P1 CONN , WEATHER RADAR
3415G2P2 CONN, DOWN CONVERTER
CONTROL
3415J2 CONK 3420P2A CONN
000
97-00-00
Page 7
BHT-412-MMS-SAR
Table 97-1. Avionics equipment list Table 97-1. Avionics equipment list
(Cont) (Cont)
97-00-00
Page 8
BHT-412-MMS-SAR
..................}
-I
2
96
96.
DO NOT OPERATE RADAR
97-6. DATA NAV III SYSTEM. SYSTEM, WITHOUT 115VAC 400
HZ SUPPLY TO SYSTEM TURNED
The DATA NAV III system is comprised of the ON. WITHOUT RECEIVER-
following major components: DATA NAV TRANSMITTER COOLING BLOWER
computer (3420A2), DATA NAV control unit OPERATING CIRCUIT BREAKER
(3420CP1), color indicator (3420DS1), and DAMAGE AND/OR AUTOMATIC
figure 97-1
the DATA NAV keyboard (figure 97-1). SHUT DOWN COULD OCCUR.
E
computes range and bearing information from to display normal or emergency procedures
the latitude and longitude figures of the and to check off specific actions as the
aircraft present position and the navigation technician sequences through the procedure.
system entered waypoints. After computation,
range and bearing information plus 2. For typical check lists displays, refer to
--h
CD
CD
instructions for waypoint identification is Honeywell, DATA NAV III manual.
passed to the display processor.
calculator mode.
any faulty mechanical mountings or electrical
connections. Connect external power,
C
C
adjusted to 27.5 Vdc, to helicopter power b. Alternate functions are available for 13
0
CUURSE2
0[1]90;0El 0
13420A21
LOOKING INBOARD AT UH SIDE OF CONSOLE LOOKING DOWN AT UPPER SHELF L/H SIDE
412-SAR-97-1
97-00-00
Page 10
BHT-412-MMS-SAR
0
0
WXD
SKIP MODE A
0
PAGE
m
LIST INDEX
NORM EMER
INDEX 7),__L_. LIST RCL
-1
LINE
m
ENTR
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V
AUX
C
CANCEL
0
J
0
0
0
OFF/NORM INDEX, NORM LISTIWDXIEMER 6 CANCEL
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1
-ic_a
INDEX, EMER LISTINAVIAUX* Momentary pushbutton switch used in
C
C
Rotary switch used to turn DATA NAV III OFF navigation operation to return waypoint
C
>
s0>
or to turn it on by selection of checklist, designator to home position. With same
_c.)
weather (WXD), long-range NAVigation, or long-range nay systems, CANCEL will return
C
--
AUXiliary operation. original waypoint to screen and cancel offset
0000
waypoint.
U)
@I:: SKIP
0
Momentary pushbutton switch used to
m
ENTR
advance from one LINE to next during Momentary pushbutton switch used in
>
0
C
0
C
a
checklist operation. navigation operation to send
0
0
CD
-a
3 PAGE
long-range nay system. Not all nay systems
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Momentary pushbutton switch used to
.
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advance from one PAGE to next during can use this feature.
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-
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Momentary pushbutton switch used in advance from one LINE to next during
0.
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-
C
0
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CD
C)
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fixed rotation.
0
9 i:RCL
Momentary pushbutton switch used to
:::I:i:: 5 Joystick
Wobble-type control used to move designator
RECALL first item skipped during checklist
>a)- 0
0
C
>
0 C,0
CD
CD
0
CD
-.
display.
-
CD
CO
412-SAR-97-2
97-00-00
Page 11
BHT-412-MMS-SAR
ra a aaa CLR
oaaoa
aaooa
4
a
CLE
ENTER +/-
a a DEL SBS
Q + BOS
CR
a 1_4i 1_J LJ 0
Q x
SP a
Q [o If 1 IM0DE1 HC
412-SAR-97-3
97-00-00
Page 12
BHT-412-MMS-SAR
INDICATION OF
TROUBLE PROBABLE CAUSE CORRECTIVE ACTION
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0
NOTE
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Refer to Honeywell, DATA
NAV III System Description
and Installation Manual,
Publication Number
I B8023133 for system
troubleshooting.
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WARNING CAUTION
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OFF. OFF POSITION BEFORE
CONNECTING/DISCONNECTING
97-12. Color indicator. THE KEYBOARD UNIT. FAILURE
TO DO SO WILL BE DETRIMENTAL H
1. Disconnect electrical connector.
TO THE LIFE OF THE
INTEGRATED CIRCUITS IN THE
KEYBOARD UNIT.
C
indicator to mount.
1. Loosen spring lock fasteners that secure
3. Remove color indicator. control unit to pedestal assembly.
97-13. DATA NAV computer. 2. Lift control unit far enough out of pedestal
to reach and disconnect electrical connector.
1. Release fasteners that secure computer
to mount.
0
97-00-00
Page 13
BHT-412-MMS-SAR
m
97-17. DATA NAV computer.
1. Remove moisture and loose dirt with a
>
1. Position DATA NAV computer in mount. soft, clean cloth.
2. Secure DATA NAV computer to mount by 2. Remove dust and dirt from system
E
engaging fasteners. components with a soft, clean cloth.
0
replacement, must be conducted at an
authorized repair facility.
97-00-00
Page 15116
BHT-412-MMS-SAR
0
(3415A1), GNS-X control display unit operation of the system.
(3415CP1), GNS-X receiver processor unit
(3415RE1), GNS-X configuration module
(3415A2), and a portable data transfer unit 97-23. TEST PROCEDURE.
m
figure 97-4
(3415A3) (figure 97-4).
-
The GNS-X interfaces with DAFCS, EFIS, 1. Visually inspect equipment and correct
z
DATA NAV III System, and Doppler velocity any faulty mechanical mountings or electrical
sensor.
connections. Connect external power,
0
4-'
composite navigation filter.
breakers are closed, interconnecting cabling
x
INDICATION OF
0
NOTE
Refer to Global-Wulfsburg
System GNS-X manual for
troubleshooting.
0
97-00-00
Page 17
BHT-412-MMS-SAR
UT ACTUATOR POSITION
M® N01$i PWR ® ®C - (/
N Op O O pNe
UR -
)s
ON
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FT ® l©i LO (0
7 YAW ROllo nTCM
'j ® HOISTI OFF
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{YS ROTOR FORCE MYOR {Y{
PRIM NO
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OR
3415CP1
LTi I O
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Gov rAAr fEr O
N
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NORM
ENG
GOv
AI'f0
Io
oD lJ C Lam' C a o R
DYRp DN IGEL OVRD DN YWGAL
Rrltawrca
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TIfT MIf 1
EMOINI 7
rV OM Na- py f
MR
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TfIT MI{e i
Rrep ar
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3415A1 sari ten ar
3415A2
NAV 1 ++2
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Q' ar as w NY
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AI+ AIi iDSEI LOLL CPL
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3415A1 I ®© ut.n nn luau vttrND
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HEADING COUR{Ei
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3415RE1 cR rq rar u_
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NAVIGATION COMrA{{ CONTROL
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412-SAR-97-4
97-00-00
Page 18
BHT-412-MMS-SAR
0
mounting hardware.
ENSURE ELECTRICAL POWER IS
OFF. 3. Remove down converter.
C
p.
C
1. Disconnect electrical connectors. 1. Disengage RPU retaining handle.
L
2. Remove and retain screws and other 2. Remove RPU from mount.
0
0
mounting hardware.
3. Remove air data computer. 97-32. VLF antenna.
<
1. Remove attaching screws from antenna
97-27. Navigation management unit mount.
(NMU).
1. Disengage NMU retaining handle. 2. Cut and remove sealant between airfoil
and antenna mount.
2. Remove NMU from mount.
3. Disconnect antenna coaxial cable
connector from antenna base and protect
97-28. Configuration module. open end with cap and electrical tape.
3
C
rear of navigation management unit. mount.
1. Remove navigation management unit.
0
1. Loosen spring lock fasteners that secure 1. Remove attaching screws from antenna
control display unit to pedestal assembly. mount.
2. Lift control display unit far enough out of 2. Cut and remove sealant between airfoil
4F-+
Page 19
BHT-412-MMS-SAR
0
WARNING
2. Secure unit by engaging RPU retaining
handle.
ENSURE ELECTRICAL POWER IS
OFF.
97-42. VLF antenna.
97-36. Air data computer.
MATERIALS REQUIRED
1. Position and secure air data computer
with attaching screws and mounting NUMBER NOMENCLATURE
m
hardware.
C-308
C-308 Adhesive
2. Connect electrical connectors.
C
C
0 E
97-37. Configuration module. coaxial cable connector.
E
0
0
0
0
C
C
with attaching screws and mounting hardware receptacle on base of antenna.
to rear of NMU mounting tray.
3. Position antenna on its mounting surface
2. Install navigation management unit. and secure with antenna base mounting
C
screws.
97-38. Navigation management unit
4. Apply adhesive (C-308)
C-308 bead to
0
(NMU).
mounting surface at antenna base periphery.
1. Position NMU in mount.
0
0
NUMBER NOMENCLATURE
1. Connect electrical connector to back of
0
0
C-308
C-308 Adhesive
control display unit.
2. Position control display unit in place on 1. Remove protective cap from antenna
pedestal assembly. coaxial cable connector.
3. Secure control display unit to pedestal 2. Connect antenna cable to connector
assembly with spring lock fasteners.
receptacle on base of antenna.
97-40. GPS downconverter. 3. Position antenna on its mounting surface
and secure with antenna base mounting
1. Position and secure down converter with screws.
attaching screws and mounting hardware.
4. Apply adhesive (C-308)
C-308 bead to
2. Connect electrical connectors. mounting surface at antenna base periphery.
.
97-00-00
Page 20
BHT-412-MMS-SAR
0
0
MATERIALS REQUIRED
soft, clean cloth.
w
C
0E
coaxial cable connector.
CLEANING COMPOUND FUMES
mm
2. Connect antenna cable to connector
m
0
0
0
C
C
0
receptacle on base of antenna. ARE FLAMMABLE AND TOXIC.
3. Position antenna on its mounting surface 3. Remove grease, fungus, and ground-in
and secure with antenna base mounting dirt with a soft, clean cloth dampened with
screws. approved cleaning compound.
97-00-00
Page 21/22
BHT-412-MMS-SAR
0
C)
O
aircraft movement, to the computer of an (9CB4), RATE GYRO NO.1 (9CB31), AFCS
0
0
0
figure 97-5
aircraft navigation system (figure 97-5). NO.1 PWR (9CB31), AFCS NO. 1 ADD/CAUT
(9CB32), and FORCE TRIM (9CB3).
The Doppler sensor unit provides velocity
data to the computer of the helicopters 6. Close circuit breakers AFCS 26V NO. 2
0
navigation system. (9CB7), RATE GYRO NO. 2 (9CB30), AFCS
NO. 2 PWR (9CB2), AFCS NO.2 CAUT
The Doppler sensor unit uses two modes of (9CB33), and ENC ALT (3410CB1).
transmission: interrupted continuous wave,
and continuous wave. During normal
operation in the interrupted continuous wave 7. Set EFIS MASTER switch to ON.
mode a significant reduction in signals from
rain, when flying in or above the rain, is 8. Set NAV control panel, DPLR switch to
<
0
C
0
achieved. NORM.
The Doppler sensor unit transmits four beam 9. After 30 seconds check operation of
0
C
0
frequencies that are continuously checked for Doppler by pressing HOV switch on EFIS
W
consistency with each other and to detect the display controller. Verify Doppler is valid.
tracking of a false signal in any beam. During
approach to and pull-away from a hover, the
Doppler sensor unit checks the signal NOTE
strengths of the four beams and the axis Amber Doppler display and no
velocities in order to detect false tracking.
This is known as Valid Lock Monitoring. velocity bars - use light lateral cyclic
inputs to gently rock helicopter.
Velocity bars are displayed and
97-49. TEST PROCEDURES. amber Doppler extinguished,
validates Doppler.
1. Visually inspect equipment and correct
any faulty mechanical mountings or electrical 10. Failure of the Doppler is indicated by
0
connections. Connect external electrical `FAIL` being displayed on the NAV control
power, adjusted to 27.5 Vdc, to helicopter panel.
power receptacle.
paragraph 97-
97-50. TROUBLESHOOTING.
2. Energize power buses per paragraph 97-
4
4.
It is assumed that all appropriate circuit
3. Close circuit breakers DPLR (3425CB1), breakers are closed, interconnecting cabling
m
NMU (3415CB1), and RPU (3415CB2). is in normal operational condition, and power
is applied to the system. (See appropriate
4. Close EFIS No. 1 circuit breakers ADI wiring diagram.)
(3440CB1), HSI (3440CB3), SG/DL
97-00-00
Page 23
BHT-412-MMS-SAR
412-SAR-97-5
97-00-00
Page 24
BHT-412-MMS-SAR
INDICATION OF
TROUBLE PROBABLE CAUSE CORRECTIVE ACTION
WARNING WARNING
OFF. OFF.
0
C
0
0
navigation control unit.
1. Loosen spring lock fasteners that secure 2. Position navigation control unit in place
0
C
mounting panel to pedestal assembly. on pedestal assembly.
3. Secure navigation control unit to pedestal
2. Lift navigation control unit, far enough out assembly with spring lock fasteners.
of pedestal assembly to reach, and
disconnect electrical connector from back of
control unit. 97-56. Doppler velocity sensor.
C
m
1. Remove moisture and loose dirt with a 97-59. REPAIR OR REPLACEMENT.
m
<
L
2. Remove dust and dirt from system control knobs or system components.
components with a soft, clean cloth.
2. Replace defective panel light bulbs.
WARNING 3. Replace defective or inoperative units.
4. Further repairs, other than removal or
CLEANING COMPOUND FUMES replacement, must be conducted at an
ARE FLAMMABLE AND TOXIC. authorized repair facility.
97-00-00
Page 26
BHT-412-MMS-SAR
m
RADIO ALTIMETER SYSTEM
m
m
The radio altimeter system is comprised of Positioning the DH SET knob to `X`
deactivates the DH function and the
the radio altimeter receiver/transmitters DH warning annunciator.
(3408TR1 and 3408TR2) and the radio
altimeter indicator (3408DS1 and 3408DS2)
figure 97-6
(figure 97-6).
4. Rotate the DH SET knob on the radio
altimeter indicator (3808D51 and 3408DS2) to
The primary display for the No. 1 RAD ALT is set the decision height index to 2 " (200
on the copilot EADI and EHSI. The secondary feet). The indicator pointer should
display is the pilot electromechanical immediately mask. After approximately 35
seconds warmup, the red power OFF flag on
w
indicator. The primary display for the No. 2
RAD ALT is the pilot EADI and EHSI. The the indicator should mask, the DH
secondary display is the copliot annunciator should illuminate, and the
'
0
E
0
0
The radio altimeter system provides altitude
minute stabilization period then adjust the
zero height control, located below the
0
display of 0 to 1500 feet. The indicator has, in 3408TR1 J1 and 3408TR2J2 connector of the
0
addition to the altitude display, a red power radio altimeter receiver-transmitter (3408TR1
OFF warning flag, a TEST switch (button) for and 3408TR2). Remove hole plug and adjust
confidence testing, a decision height (DH) zero height control for a pointer indication of 0
knob for setting a DH index, and a DH ± 5 feet.
warning annunciator. Two antennas are used
C
O
connections. Connect external electrical should return to 0 ± 5 feet, and the DH
power, adjusted to 27.5 Vdc, to helicopter annunciator should remain lighted; the power
0
0
paragraph 97-
2. Energize power buses per paragraph 97- NOTE
4
4.
The DH index may be positioned to
3. Close RAD ALT 1 and RAD ALT 2 circuit below zero feet to deactivate the DH
breakers (3408CB1 and 3408CB2). function and annunciator.
CAUTION
................. extinguishes.
DO NOT ENERGIZE THE SYSTEM 8. Turn off all equipment, open all circuit
WITH TRANSMIT ANTENNA breakers and disconnect the external power
DISCONNECTED. source.
97.00-00
Page 27
BHT-412-MMS-SAR
3408E4
I I I
LBL BL RBL
14.00 10.00 14.00
m
97-00-00
Page 28
BHT-412-MMS-SAR
0
wiring diagram.)
INDICATION OF
TROUBLE PROBABLE CAUSE CORRECTIVE ACTION
0
Power OFF flag remains in Defective radio altimeter Replace radio altimeter
E
view with pointer remaining in receiver-transmitter. receiver-transmitter.
zero position after warmup.
?-h
E
indicator. indicator.
Power OFF flag in view with Defective radio altimeter Replace radio altimeter
a
00
Pointer remains behind mask Defective radio altimeter Replace radio altimeter
0
3
0
cable(s).
NOTE
100 ± 20 feet.
97-00-00
Page 29
BHT-412-MMS-SAR
E
INDICATION OF
TROUBLE PROBABLE CAUSE CORRECTIVE ACTION
a
0
0
0
responds incorrectly, to the receiver-transmitter. receiver-transmitter.
TEST condition, after power
OFF flag is masked from
view.
a
0
0
E
indicator. indicator.
Indicator shows TEST altitude Defective radio altimeter Replace radio altimeter
a
0
--
a
0
receiver-transmitter. receiver-transmitter.
NOTE
receiver-transmitter.)
Altimeter pointer reading out Defective radio altimeter Replace radio altimeter
a
0
of t o I e r a n c e. A I I o t h e r receiver-transmitter. receiver-transmitter.
indications normal.
a
0
0
indicator. indicator.
97-00-00
Page 30
BHT-412-MMS-SAR
0
mounting screws and other hardware.
;44444444444444444
other hardware.
EXCESSIVE CLAMP TENSION MAY
zzz
3. Remove radio altimeter receiver/ DEFORM INDICATOR AND CAUSE
transmitter.
ERRONEOUS READING.
0
rear of indicator.
1. Disconnect cable connector from
3
antenna connector.
1. Position antenna in place on access panel
O
0
0
2. Inspect switches and controls on radar 3. Remove grease, fungus, and ground-in
altimeter system components for proper dirt with a soft, clean cloth dampened with
mechanical action. approved cleaning compound.
3. Inspect components to ensure panel 4. Remove dirt from connectors with a soft
lights illuminate with electrical power on. bristle brush; remove moisture with a clean,
r.,:
dry cloth.
4. Inspect electrical connections for
corroded or bent pins and proper mating, 97-73. REPAIR OR REPLACEMENT.
m
W
interconnecting cable for frayed or broken
insulation, and circuit breakers for proper 1. Tighten or replace loose or cracked
operation. control knobs or system components.
97-72. CLEANING PROCEDURES. 2. Replace defective panel light bulbs.
m
m
1. Remove moisture and loose dirt with a 3. Replace defective or inoperative units.
soft, clean cloth.
4. Further repairs, other than removal or
2. Remove dust and dirt from system replacement, must be conducted at an
components with a soft, clean cloth. authorized repair facility.
WARNING
97-00-00
Page 32
BHT-412-MMS-SAR
97-74. WEATHER RADAR SYSTEM. The radar controller, used for dual mode
operation, contains secondary controls to
The weather radar system consists of the operate the weather radar system.
0
following major components: receiver/
transmitter unit (3420TR1), antenna
97-75. TEST PROCEDURES.
m
(3420E1), indicator (3420DS1), and radar
figure 97-7
controller (3420A1) (figure 97-7).
SPECIAL TOOLS REQUIRED
m
C
The weather radar system is a high-
resolution, high-power airborne ground/sea
system optimized for over-water search and NUMBER NOMENCLATURE
m
z
rescue missions.
Commercial Inclinometer
0
Dual operation is allowed with any
0
C
slaved to the other control, resulting in that it can be moved in tilt and azimuth axis
identical displays on both displays. Dual with no binding action.
mode gives the appearance of having two
radar systems on the aircraft. 2. Check waveguide, cable, and black box
installation to determine they are
0
N
0 0
uT ACTUATOR POSITION
NOISi PWP ® Y.' 1(.' l R Ur KJ
D
T
ET U® OFf
sol lO O pNO
raw ROllo IITCN
VI
} NO1ST
I ®
y
NO , O
fYf fTfP ROTOR fORt! NYOR fYf
TRIy
RPM ,TRIM
0
NO e
fo GLOFUL
© o0
RAISF Au010
D/r ` art
NN
L1 I
flaw Drr
ENG
r OOV rAAr sfr O IAAt ur GOV
ll'10
OOCJOO NOAY NOIIY AI'TA
o
DUE
a a aY aW KaY a
p
a
1 I S/ e, TEET ENGINf
DYRD GN
f! W M AAa DN VANDAL
IIgIN Fle
U
oN N oN r
O IL
0l
TEST IUEI 1
INC
i
MR
ATT NDG ET
'
CM
RESET RfV RFr RfV
r 11 fr
I °Or
_ Q pY
Ir
T 1
IaNR TOVAOCl01l
CI/ ll
PR lull rR
VA IN100M VA
Y
T
TANK
ou
IY
r1
'
'
NW lxW
APT A/T
,"w
(L l
LNw rwK
ld 1 I[n la
xrv7
ovaoclal rANK
ar
ar p f D. al
D Dal r11 °"bTa MO
MP
O A
V1
A"
(t D
CM SO ATr NDO
REV FT
® P G RfSET REV REr
1
0 0
a oa as
°Iw>.su o
ruu Yu IN
v asrD NW LNW
e lNW IMW
IT
(-yaarI a® .
NAV 1 NAV 1 '(' l aDi ox Nub wl ar
IW D YIO
.
I
., ,n Arl iDSEL COIL CR
xW
YYT'I II"a:
.. c 4Sari Il.pllr vflxlD
a ON
rr, DI
'LL..r rr
T T ''
I COMM ruu RNl RAl
ICS
I _e :cSR'
DW IrxC OY
oYY Q Y VY Vm
o c;
t; ee°
r**,1
&
L e
L\
l
. .-/ [ N a ar
® (,j j
J
) ..
QQ
. utt COMPASS
,
cN
CONTROL
W"
I ulr
rll /)
wRD woLR
wx
tM IwLL [Nr
rN1 ral
r
__p
D.rl NW
^ / 0OoOo
YGr IvuNCr r/yry IW
// IC..
w. Rxl
vv / / T TI OYU
J' oc 41f00 /T V
"N1 4Aw Yal YODI 111 rill
OY( r VOl 0 ®
0
(2 /a 6W ONNS iy 'U
COCKPIT VOICE RECORDER
97-00-00
Page 34
BHT-412-MMS-SAR
paragraph 97-
6. Energize power buses per paragraph 97-
a
0
4
4. WARNING
C
TEST pattern is displayed.
WARNING
6. Adjust TILT knob on indicator between
+15 and -15 degrees. Verify tilt angle is
I
TESTS INVOLVING RADIATION OF displayed.
RF ENERGY BY THE RADAR
ANTENNA MUST NOT BE MADE IN 7. Verify Red/Green sense indication block
THE VICINITY OF FUELING is Red at the left.
OPERATIONS, OR WHEN
PERSONNEL ARE STANDING 8. Press VRM button on indicator. Verify that
DIRECTLY IN FRONT OF THE variable range mark is displayed.
>
RADAR ANTENNA. RF ENERGY IS
9. Slew range mark in/out on indicator.
0
GENERATED IN ALL MODES
z
BRT -
ROTATE FULL CW NOTE
m
MODE - SBY
Zmm
TILT - + 15 DEG.
12. Select HDG display (via menu). Verify
correct heading is displayed at top center of
2. Set RAD controller as follows: indicator.
0
Z
0
and adjust tilt for ground or weather targets. GAIN - OFF (Use menu or simultaneous
TGT and *CR on the controller)
MODE - SBY.
a. Select 300 NM range and MAX variable
gain. d. Verify only one control source is active.
b. Verify receiver noise is visible in e. Position flat plate dead ahead by hand.
0
C
display.
f. Use an inclinometer to measure and
16. Slew ranges through all selections. adjust flat plate tilt angle so that it is vertical
Verify proper operation. ± 0.1 degree.
g. Remove vertical reference sensor from
97-77. Stabilization Check. its mount and install it on a tilt table or
similar device.
NOTE
2. Pitch Adjustment.
Use the following procedures to
check and calibrate antenna a. Set the following:
stabilization whenever a new
installation is made, whenever a GAIN - MANUAL
stabilization circuit in either the R/T STAB - ON.
or antenna has been serviced, or
0
0
0
0)0L
error.
0
c. Switch radar on and select the f. Measure flat plate angle and determine
following: difference between vertical reference sensor
97-00-00
Page 36
BHT-412-MMS-SAR
plate recorded in step a and the look down e. Tilt vertical reference sensor to an
I-
angle of the flat plate. Difference should not attitude of approximately 20 degrees right
exceed 1 degree. wing down. Measure and record the exact roll
angle.
g. If necessary, adjust pitch gain
potentiometer to reduce error noted in step f f. Measure flat plate angle and determine
by 50 percent. difference between vertical reference roll
sensor plate recorded in step a and the look-
3. Roll Adjustment. up angle of the flat plate. Difference should
0
GAIN - PRESET
g. If necessary, adjust roll gain
potentiometer to reduce error noted in step f
STAB - ON.
by 50 percent.
nose up ±1 degree. If necessary, adjust roll is in normal operational condition, and power
-
gain potentiometer on R/T unit so that flat is applied to the system. (See appropriate
plate looks down by the amount recorded in wiring diagram.)
step b.
Table 97-6. Troubleshooting - weather radar system
INDICATION OF
0
Noise band missing or weak Defective R/T unit. Replace R/T unit.
0
or too strong.
0
0
0
0
0
No TRB noise in noise band. Defective R/T unit. Replace R/T unit.
Replace indicator.
0
97-00-00
Page 37
BHT-412-MMS-SAR
INDICATION OF
TROUBLE 0 PROBABLE CAUSE CORRECTIVE ACTION
0
No azimuth/bearing! track Defective R/T unit. Replace R/T unit.
graphics.
Replace sensor.
NOTE
indicator. All errors are stored in a
0
Critical functions in the R/T and nonvolatile memory. Exit from the
indicator are continuously monitored. "hidden" page is accomplished by
The indicator displays both indicator using the menu feature.
and R/T errors on a "hidden" display
97-00-00
Page 38
BHT-412-MMS-SAR
w
failed.
m
03 AFC Error Indicates that the AFC is
0
R/T
0
0
m
0
04
0
R/T
0-a
operating outside its permitted
control range.
R/T Mixer Error Indicates that one or both mixer
m
0
05
0
0
tolerance.
IOP Error Error in input/output processor
0
m
0
06 R/T
0
circuit.
07 DSP Fault (INT) Error in the digital signal
0
R/T
0
08
0
09
0 0 0 0
R/T
OA R/T IOP RAM RAM data error.
OB R/T Modulator Modulator errors for four seconds.
0
OD R/T Boot Checksum Processor detects a corrupt
checksum in the boot program.
OF HS 429 Indicates errors in the hardware
0
R/T
circuit which filters high speed
ARINC 429 data.
R/T LS 429 Indicates errors in the hardware
0
10
circuit which filters low speed
ARINC 429 data.
Power Supply Indicates that the +5 V, +15 V, or
0
11 R/T
0
+
13 R/T
circuit which filter the control bus
data.
14 R/T Magnetron Drive Indicates that the magnetron drive
voltage is out of tolerance.
97-00-00
Page 39
BHT-412-MMS-SAR
Description
z
0
3
E
17 R/T Overheat Indicates that the R/T is
overheated, probably due to fan
malfunction.
18 R/T DSP Indicates errors in the digital
signal processor circuit.
31 Indicator Horiz Def Malfunction in horizontal
deflection circuitry.
32 Indicator >Vert Def Malfunction in vertical deflection
circuitry.
33 Indicator Computer Error in indicator's control
processor system.
34 Indicator Graphics Error in indicator's graphics
C'3
processor system.
35 Indicator HVPS Malfunction in the indicator's high
<
0
voltage power supply.
37 Indicator EWXPD Error in the indicator's EWXPD
m
W
0
38
L
input circuitry or data.
39 Indicator UDI Error in the indicator's UDI input
interface circuitry or data.
61 Antenna Scan Azimuth errors greater than 5
degrees are detected.
Antenna Elevation errors greater than 5
m
62 Elevation
>
69
annunciated if the R/T is
programmed for digital altitude
data.
6A
m
available.
6B Transmit Switch off Only annunciated if the R/T is
a)-
Analog ALT
4-+
0
Only annunciated if R/T is
programmed for analog altitude.
6E External Analog HDG Indicates that analog (synchro)
I
C
heading is invalid, and that it is
required for NAV functions or
HDG display.
Only annunciated if the R/T is
programmed for analog heading.
6F External Selected Course Indicates that the synchro or
course OBS selected course input
is invalid.
Only annunciated if the R/T is
programmed for external course
input.
70 External 115 V ac Indicates that the 115 V ac 400
Hz input is below 90 or above
N
135 volts.
Indicates that the R/T is not
m
71 External ESCI
receiving control bus signals from
the indicator or controller.
97-00-00
Page 41
BHT-412-MMS-SAR
WARNING WARNING
m
m
ENSURE ELECTRICAL POWER IS
OFF. OFF.
0
L
C
0
C
panel.
2. Loosen fasteners that secure radar
0
0
0
with fasteners.
3. Remove radar indicator from instrument
a
0
E
0
radar indicator.
97-83. Receiver/transmitter.
97-88. Receiver/transmitter.
1. Disconnect electrical connectors.
1. Position and secure receiver/transmitter
2. Remove and retain screws and other
0
0
0
3. Lift weather radar control free of pedestal 3. Secure weather radar control with spring
assembly. lock fasteners.
97-00-00
Page 42
BHT-412-MMS-SAR
C
bristle brush; remove moisture with a clean,
2. Inspect switches and controls on weather dry cloth.
radar system components for proper
mechanical action. 97-92. REPAIR OR REPLACEMENT.
3. Inspect components to ensure panel 1. Tighten or replace loose or cracked
lights illuminate with electrical power on. control knobs or system components.
4. Inspect electrical connections for 2. Replace defective panel light bulbs.
corroded or bent pins and proper mating,
interconnecting cable for frayed or broken 3. Replace defective or inoperative units.
D
insulation, and circuit breakers for proper
operation. 4. Further repairs, other than removal or
replacement, must be conducted at an
C
97-91. CLEANING PROCEDURES. authorized repair facility.
1. Remove moisture and loose dirt with a
soft, clean cloth.
2. Remove dust and dirt from system
components with a soft, clean cloth.
WARNING
97-00-00
Page 43/44
BHT-412-MMS-SAR
m
VHF COMM AND ADF SYSTEMS
The KTR-908 factory-adjusted radio is ADF King Radio P/N 066-1077-01 shall be
C
incompatible with the NAT installed in SAR helicopters. P/N 066-1077-01
intercommunication system installed in the is not interchangeable with basic P/N 066-
JMSA SAR helicopters. When it is necessary 1077-00.
to replace the radio, it shall be replaced with
a radio which has been readjusted for Minor modification to the VHF COMM and
compatibility with the NAT ICS. Refer to the ADF airframe wiring is illustrated in EFIS
appropriate customizing drawing for radio Chapter 98
Modification Wiring Diagram, Chapter 98.
settings.
Likewise, to maintain the direction finding
(DF) function provided by VHF COMM 2, the
97-00-00
Page 45/46
BHT-412-MMS-SAR
97-94. AVIONICS SYSTEM WIRING segment letter and the wire size of the
DIAGRAMS. conductor. Identification of wires may be
accomplished by using the wiring
This chapter contains wiring diagrams for Chapter 98
identification code figure in Chapter 98.
each of the SAR avionic systems that may be
installed in the Bell Model 412 helicopter 97-96. USE OF UNDERLINED CAPITAL
C
0
figures 97-8
(figures 97-13
97-8 through 97-13). LETTERS.
97-95. WIRING IDENTIFICATION. Many letters have similar upper case and
lower case forms. To eliminate this possible
All wires on the wiring diagrams are identified source of error in identifying connector pin
by codes exactly as they are marked in the designations, underlined upper case (Capital)
helicopter. The code or wire number indicates letters (A, B, C, etc) are used to signify the
the circuit function, wire number, wire lower case pin letters (a, b, c, etc).
97-00-00
Page 47148
BHT-412-MMS-SAR
3420A2 342ODS 1
N
N
DNC-1002
DATA NAV COMPUTER COLOR INDICATOR
342OA2P1
4
J1 J2
N
jODS1P2]
4
SHIELD RETURN
RED VIDEO (P) 88
P
DNAV-1A24 (WHT) n. RED VIDEO (P)
000
4
RED VIDEO (N) 80 DNAV-1A24 (BLU) - _ 13 RED VIDEO (N)
GREEN VIDEO (P) 91 DNAV-2A24 (WHT) I418 GREEN VIDEO (P)
GREEN VIDEO (N) 90 DNAV-2A24 (BLU)- 6 GREEN VIDEO (N)
BLUE VIDEO (P) 89 s DNAV-3A24 (WHT)
P= 9 BLUE VIDEO (P)
BLUE VIDEO (N) 102 DNAV-3A24 (BLU) - 3 BLUE VIDEO (N)
VIDEO SELECT (P) 79 DNAV-4A24 (WHT)
Px 16 VIDEO SELECT (P)
VIDEO SELECT (N) 38 L1 DNAV-4A24 (BLU) - 1L
x 12 VIDEO SELECT (N)
VREF (P) VERTICAL SYNC 87 L DNAV-5A24 (WHT) 10 VREF (P) VERTICAL SYNC
VREF (N) VERTICAL SYNC 40 DNAV-5A24 (BLU) - 4 VREF (N) VERTICAL SYNC
HREF (N) HORIZONTAL SYNC 104 8
00
00
HREF (N) HORIZONTAL SYNC 65 DNAV-6A24 (BLU) - 15 HREF (N) HORIZONTAL SYNC
RNG 2 (2) (N) INDICATOR RANGE 19 DNAV-7A24 (WHT) 5 RNG 2 (2) (N) INDICATOR RANGE
RNG 2 (1) (N) INDICATOR RANGE 7 l DNAV-7A24 (BLU) - 11 RNG 2 (1) (N) INDICATOR RANGE
RNG 2 (0) (N) INDICATOR RANGE 55 P
DNAV-8A24 (WHT) RNG 2 (0) (N) INDICATOR RANGE
DC RETURN
RES (LCHK-N)
5
69
r DNAV-8A24 (BLU) -
DATA NAV
17
7
1
DC RETURN
SHIELD RTN
+27.5 VDC SUPPLY 92 DNAV-9A22 5 ESNTL 28VDC BUS 1 2 RESERVED
+27.5 VDC SUPPLY 105 DNAV-9B22 14 RESERVED
342OCB3
54 9WT30
C)
0
N
PWRIGND 93 DNAV-1OA22N 3400TB3 DCNP-1003
PWRIGND 106 DNAV-11 A22N W DATA NAV CONTROL UNIT
0
0
AR SEL 2 (N) 62 DNAV-12A22N Y 342OCP1P1 J1
N
AR SEL 2 RTN GND 46 DNAV-13A22N DNAV-45A22 37 PANEL LAMP (HI) 27.5 VDC
0000000
44444444
N
N
6
DOWN (N)
RIGHT (N) 15 DNAV-29A22 - 3 RIGHT (N)
UP (N) 28 DNAV-30A22 - 1 UP (N)
DNAV-31 A22 -
C)
N
N
GND RESERVED
GND 29 I"'L GNS-X NMU 1
RESERVED
4
bdiJ3415A1P1A
ARINC 2-WIRE INPUT A 26 RESERVED
ARINC 2-WIRE INPUT B 71 DNAV-34A24 (BLU) - A15
ARINC 2-WIRE OUTPUT A 44 DNAV-35A24 (WHT)
P- A5
SPARE
22 SPARE
ARINC 2-WIRE OUTPUT B 45 DNAV-35A24 (BLU)- A6 SPARE
DATA HI 32
U SPARE
0
SKIP (N)
RCL (N) 67 DNAV-37A22 35 RCL (N)
T DNAV-38A22 IWHT )
HDG X 53 34 SPARE
0001
_ P
26VAC 400HZ IN 2
t::: DNAV-39A22 (WHT)
N
18
DNAV-38A22 (BLU) 33
N
0
N
342OJ2
DNAV-38A22 (ORN)
GND DNAV-4OA22 r 21
000000000
444444444
DNAV-42A22 (WHT) t
KBD3 82
P
DNAV-42A22 (BLU)- 1 D 5
KBD4 68 DNAV-43A22 (WHT) DATA NAV KEYBOARD
KBD5 DNAV-43A22 (BLU) -
P
4
KBST 94 DNAV-44A22 (WHT) f
+5 VDC 74 DNAV-44A22 (BLU)- E
N
SHIELD RTN 42
I
DISC
PILOT ENTRY KEYBOARD 412-SAR-97-8
0
97-00-00
Page 49/50
BHT-412-M MS-SAR
SHT 2
3415A1
-
3440TB1P1 3440761 3440TB1P1 NAVIGATION MANAGEMENT UNIT
(NMU)
3415A1P1A
J1A
CMPS-11 A221WHT1 GNS-21A22 (WHT(
m
II E13 HEADING (X(
1 II
--- GNS-21A22 (BLU)
II E14 HEADING (Y)
3415E4
3440A1
3440A1P2A
D J
-1CMP5.11A22(ORNI' GNS-21A22 (ORN)
ii
\ E15 HEADING (Z)
3415RE1 GPS ANT
COPLT SYMB GEN
I GNS-22A22 E11 HOG AC REF (H)
N
N
4
N
N
1EFIS-106F22
RECEIVER PROCESSOR UNIT
IRPU) J2 3415E4P1
26 VAC IN (PRI) 13 1EFIS-106J22 -T
9
3415RE1P2 3415J2 3415G2P2
N
3415P2 3415G2P1 3415WT1
GNS-201 A ---GNS-201 B GNS-202A
C)
2
0
2222
0
z
N
N
4
GPS ANTENNA
2222
GNS-23A22N
2
E12 HOG AC REF (C)
2222
222Z
RPU GNS-24A22N F10 ATT AC REF (C)
C
F GNS-68A22N
3415RE1P1 3415C62
GNS-67A22N
N
28 VDC 5 GNS-49A16 7.5A
22
0)
22
28 VDC ESNTL BUS 2
PWR GND
--CIII 3415WT1 3440TB3P1 3440TB3 3440TB3P1
18
'f-GNS-28A22 (WHT) GNS-28A22 (WHT)
NNN N
-' GNS-28A22(BLU)
+I+I
POS XMIT + 19
+ POS REC
GNS-28A22 (BLU)
000
DID
A12
24 GNS-29A22 (WHT) GNS-29A22 (WHT) A13
NN
+ P05 XMIT
P05 REC
{ii 25 GNS-29A22 (BLU)
s
2
GNS-30A22
N
N
F9 ATT AC REF (H)
9781
0)0)
2
0 0 0
ANTENNA (H) 55 DME-57A22 (WHT)' A2
IS)
C757E22 i +
N
ANTENNA (L) 56 3 DME-56A22 (BLU)' B14
RC 0.0 RD GNS-30A22 DME ARINC 429
2U2
1 EFIS-197A22 LV 9CR51 4
NN
ANTENNA PWR SHLD 51 DNAV-35A24 (BLU) 7 A6
It)
2EFIS-197A22 LV RJ RK
I
GNS-31A22N C9
NAV 1 TUNE DISABLE
GNS-70A22N CHASSIS GND 3415CR5 I GNS-32A22N 09
N22
I I
GNS-33A22N C10
NAV 1 TUNE DISABLE
RPU CONTROL 12 GNS-34A22N D10
STRAP GND 36 TJ 0-0 TL
TK 0.0 TM
GNS-36A22
L GNS-35A22 E8
E9
TUNE STRAP
TUNE STRAP
C8 MARK ON TARGET
2
GNS-36A22
N
N
3440TB1P1 344OTB1 3440TB1P1
3440A1P2B
3415A1P1B
4
JlB
-)
_.00000
SYMB GEN - F144D22(VI01 84 G3
N
>
0
(WHT) ROLL (X(
JJJJJ
GNS-37A22 )WHT)
ARINC 429 BUS + III GNS-37C22 (WHT( G5 ROLL IX)
EI3 G4
0)
F144D22(VBLU) GNS-37A22 (BLU) - GNS-37B22 18LUp ROLL (Y)
1{ GNS-37C22 (BLU) G6 ROLL (Y)
92
0)
2
F144022(VORN) (ORN). GNS-37A22 G7 ROLL (Z)
T
1
C
3440A2P26 - F141D22(VIO)
N
N
>
13 GNS-39A22 (WHT) GNS-39822 (WHT) G8 PITCH (XI
0.0.0.0.0.
00000
II GNS-39C22 (WHT) ' G10 PITCH (X)
. F144D22 (VBLU) 10 GNS-39A22 (BLU) GNS-39B22(BLU) G9 PITCH (Y)
I1 GNS-39C22 (SW) Glt PITCH (V)
F144022(VORN) 17
t GNS-39A22 (ORN) G12 PITCH (Z)
A2
+
GNS-47A22 (WHT) + ARINC 429 BUS
D
-GNS-47A22 (BLU) A3
00
II
GNS-47D22 (WHT) 5 B1
NN
NN
2222 2222
GNS-47822 (WHT)
2222 2222
000U NNNNN
NNNN NNNN
9TB1
T
GNS-47C22 (WHT)
0U)
IIh- DPLR-102A22N
GNS-47D22 (WHT)
GNS-47E22 (WHT( dEE KH GNS-48A22 03 WEIGHT ON WHEELS
'GNS-47B22(BLU)
.GNS-47C22(BLU)
GNS-47E22 (WHT) GNS-47D22 (BLU)
GNS-47E22 (BLU) GNS-47E22 (BLU) SHT 2
412-SAR-97.9-i
97-00-00
D)
Page 51/52
BHT-41 2-MMS-SAR
SHT 1
341 5A1
NAVIGATION MANAGEMENT UNIT
5CB]
(NMU) NMU
2
C
3415A1PiC] 341 5DS2
Jic I-
28VDC GNS-iAi6 )PLT)
10 5 :, 28 VDC ESNTL BUS 2 i5EIJ
GNS-63B22 0
000
222
LORAN ANT
rococo
0L)0
03030
2
PWR GND
2
9
3
GNS-2Ai 6N
GNS-59B22
GNS-6OB22
C
B
I
C)
5 II34i5C!IJ I BAT
7 L__34i5E3Pi1
P1-
2
CONTROL DISPLAY UNIT
:
0 -
-GNS-i03A
00)
ANT 12 GNS-65A22 __.Ik_: GNS-65B22 A
22
2
)CDU)
8 L3415CP1P1 I 34i5CP1Pj GNS-65C22
13
Ji Ji
ii GNS-3A20 C DC RETURN
X20
GNS-3A20
X00
C,)
341 5DS4
CO
6
00
GNS-4A2O GNS-4A20 5- 28 VDC (FILTERED)
- -F. 28 VDC (SWITCHED) 8TBi )PLT)
q
GNS 5A20 GNS-5A2O
-
GNS-63C22
WOO
222
000
0030
0003
28 VDC LIGHT M - GNS-57A2O NZ
0
0
U)
- GNS-41A22 ___1kc: GNS-4iB22 C
I
JiB I 34i5AiPiB j
22WT7 GNS-41 C22
GNS-6A22 - - GNS-6A22 -15VDC -T1
00 <
00
K15
NN2
WIC
>
0
_C
XTRK
I
Gi GNS-7A22 (WHT) (II7A99 IWWT% - - GNS-58A20N
:' LIGHT GND
C)
I
2
CO
0
:4 CDU TRANSMIT
C
H2 GNS-7A22 (BLU GNS:7A22(BLU; i} WPT
C,
J;
- GNS-61B22 __-_Lh::z: GNS-6iC22 A
22
' S+
GNS-6i D22
J1A Ei SAl
- F-
L 3400TBj
0
03
XCO
Bi 1 GNS-8A22 (WHT) GNS-8A22 (WHT)
0303
C
00
CDU RECEIVE
2
0
>
Bi 2 GNS-8A22 (BLU GNS-8A2 2(BLU)
CCC
GNS-52A22N DR ANNUN V - GNS-59A22 'hA NB - GNS-59B22
)0
222
GND Ki2 GNS-9A22 (BLU)-, D 28 VDC DTU PWR WPT ANNUN - GNS-6iA22 NE NF - GNS-6OB22
001
Z-0
GNS-38A2O
I
020
0030
NG NH - GNS-6OC22
NNN
GNS-4OA22 ANNUN TEST
I
34i5A2
01
[i4i 5A2P1j GNS-56A22 E RPU CONTROL NJ NK - GNS-6iB22 341 5DS1
N
Ji CONFIG NM - GNS-6iE22
A
NL
02
00
0
0
(COPLT)
0
MODULE GNS-63A22 - NN NP - GNS-63B22
5Ai
I
COCA
N
N
6
JiB NR N - GNS-63C22
0100
5
0)010)
GNS-64B22
222
(0030
0003
d0)0
CLK F12 GNS-1OA22 4 NT NW GNS-59C22 C
NNNN
SEL Ci2 3 NY NX
GNS-i 1A22 GNS-6OC22
T1
I 0 03
D IN Cli GNS-i 2A22 4i 5CR4]
MSGI DR
0
0
D OUT C1O GNS-i 3A22 PA PB
BAT
Ai4 DNAV-34A22 (WHT) (342OAiPi-26) -
A
PC
GNS-1 4A22- PE
PD
PF - GNS-65A22
I GNS-65D22 -.ckc:: GNS-65E22 A -J
00
0)
01
DATA NAV OUT
Ai5 DNAV-34A22 (BLU) (3420A1P1-7i) - - GNS-65D22 GNS-65F22
2
I
{i PH
PJ PK
03
J4i 5CR1] 5CR21 I 3415CR3 I
C4 GNS-i 4A22 PM - GNS-4iA22
0
XTRACK WARN PP
PL - GNS-4iD22
GNS-43A22 - PR PS
PT PW
SHT 1 f- )34i5REiPi-i 1) GNS-53A22 - Px
2
PY 341 5D53
01
0
F 34i5A3 I [34i4 )COPLT)
000
222
010)C)
RB
003
0100
000
TRANSFER UNIT RC RD GNS-64C22
I 3400WT5] - GNS-56A22 - RE RF - GNS-54A22 (34i5REiPi.i2)-4 SHT 1 GNS-4i D22 GNS-4i E22
HI.
03030303 03030303
1-F
003
CO
J
K2 - GNS-i5A22 (WHT)- .1 A RJ RK
DTU XMIT K3
K6
GNS-i5A22(BLU) -
- GNS-i6A22 (WHT) - XI
1'I -J B
fr-i
ANNUN
TEST
RL RM
XTRK
WPT
0
RN RP
22)->
DTU REC
K5 - GNS-i6A22 (BLU) - 11 1 D RR RS GNS-6i E22 GNS-61 F22 A
-GNS-i7A22 -
II
CONFIG G2 V
N)0
RT RW GNS-61 G22
- GNS-18A2ON - V RY RX
ANNUN TEST =
z
<C
02
b- GNS-19A22N -
2
NOTE
0
+28 VDC
REFER TO DUAL DIGITAL AFCS WIRING DIAGRAM.
z
AIR DATA COMP GNS-42B22
N
N
C2 GNS-66A22 (WHT) FDR-2OA22 )WHTk REFER TO DATA NAV III WIRING DIAGRAM.
ADC
0
z2
REFER TO MASTER CAUTION, RPM CAUTION, AND
34i 5WT1 CYCLIC STICK CENTERING INDICATOR LIGHTS WIRING
SHT 1
I
00
REFER TO FLIGHT DATA RECORDER
032
41 2.SAR.97.9.2
03
WIRING DIAGRAM (BASIC MANUAL).
97-00-00
Page 53/54
BHT-472-MMS-SAR
9TB30
P.C
DPLR-3A22 (WHT) 25
011000
3425TR1 DPLR-3B22 (VIO) 26
DPLR-3C22 (VIP) P 27
0
0
DOPPLER
00 J1 3425TR1P1 34000P30
DPLR-3D22 (WHT)
DPLR-3E22 (WHT) P
28
29
NAV CONTROL DPLR-3F22 (WHT) 30
34000P30P1 J1
412.899.718 S5B S5A F' r'T1 ii P
U,
U,
A 31
00
115 VAC 400 HZ (H) (REAR WAFER) (FRONT WAFER)
NN
0)0)0)0)0)0)
115 VAC 400 HZ (L) U DOPPLER (NON-SHORTING) DOPPLER (SHORTING) DPLR-3A22 IBLU) 94
0
DPLR-120A22
N
-. P DS1P1 DS1 DS1P1 95
0
DPLR-3B22(VBLU)
AIRNC 429 PR) A I - . DPLR-105E22
x-423 20)D
DPLR3A22 (WHT)
99
©x310101-1o
T 1 DPLR-3C22 (VBLU) 11 T- 96
22
NN
i DPLR 14A22 2 NORM OFF 2 ON
AIRNC 429 PRI BP DPLR-3A22(BLU)- DPLR-3D22 (BLU)
br: 97
JJ
l DPLR-117A22
SHIELD RTN W DPLR-5A22 DPLR-101A22
0
r - DPLR-104A22 DPLR-3E22 )BLU) 98
ii
DPLR-108A22
00
Q DPLR-3F22 (BLU) 99
VLM DPLR-14A22 4 3 ON DPLR-108822
C
NNN N
CALM ON
0
100
2
SWITCH RETURN DPLR-5A22 TEST 4
TEST DPLR-6A22 DPLR-6A22 _1 DPLR-102A22-4
1'
00
DPLR-105C22 DPLR-105D22
J
CW DPLR-7A22 DPLR-7A22 -- -DPLR-103A22
DPLR-109A22 3440A2P2B
DPLR-117A22 DPLR-109822
9
D DPLR3B22 (VIP)
NN
LOWER POWER DPLR-107A22 DPLR-3B22 (VBLUI
3440A1P2B
- DPLR-105B20
+28 VDC IN DPLR3C22 (VIO)
DPLR-106A20 XK2
2
DPLR-12A20 DPLR-106A22
99
0
AIRCRAFT EARTH 3425CB1 DPLR-119A22N DPLR-119B22
N
N
2
DPLR-122A22
ALONG D.C. +VE BB 9A2P1C
0)
DPLR DPLR-109C22
ALONG D.C. -VE CC DPLR-104A22
NON-ESNTL 28 VDC BUS 2 5
ACROSS D.C. -VE DD DOPPLER POWER DPLR-3D22 (WHT)
ACROSS D.C. -VE EE
-
-DPLR-3D22IBLU)
VERTICAL D.C. +VE FF I( r DPLR-118C22N --DPLR-118A22N B1
VERTICAL D.C. -VE GG --DPLR-1 10A22
-Ij
N
N
X1
0
DPLR-110B22
0
RETURN HH
C)
DPLR-8C22
0
9
CR3
2
9
0
2
DOPPLER FAIL
FAIL/LOCK IV) F DPLR-11A22 DPLR-111A22
0 0
51j0.1
DPLR-11A22
0 0
DPLRR113A22 X2
GOOD -:t P
C)
DPLR-4A22 -DPLR-4A22
D
DPLR-112A22
0
0
DPLR-3E22 (WHT)
--- DME-55A22 --{ '-DME-134A22 DPLR3E22 (BLU)
0000 00
- DME-60A22N U
DME-17A22 (WHT) -. K DME-120A22
0
DME-17A22 (BLU) ._4*__ DME-117622 DPLR-113A22
0
U,
N
N
DPLR-8B22
DPLR-113622
000
-DME-21A22 (BLU) r---DME-117A22 3415A1P1B
U,$
55 00 0000000
2 DPLR-115622
2i
v 1
9
DME-21A22 (WHT)
N
DPLR-115A22
DPLR-3F22 (WHT)
I-'
1
p DPLR-3F22 (BLU)
0
2
TX INHIBIT 2EFIS-122B22 NAV 2
11
2 Iih -- DPLR-10A22N
:x
N
TEST INHIBIT DPLR-8A22 - DME-61A22N --DME-136A22 HOLD
I
3
U,
N
9TB32
0! INAV 1
21>
1EFIS-122B22 XK3
- DME-62A22
000
1
000
DPLR-119C22 A3 DPLR-8C22
S4 DME
DME-137A22- 1-_-0
0
Z DPLR-8B22
N
28 V W DME-63A22 DPLR-108C22 -1A2 i DPLR-8A22
2
MKR-10A24 C DME-107A22 MKR BCN
555 000
ALONG D.C. L HI Al
-MKR-8A24 B 2
ACROSS D.C. M h--DME-108A22 LO S3 83 3
555
- MKR-15A24 -- H
20 KTS/4OKTS H
MKR-5A24 (WHT) n G F-- DME-115A22
DME-105A22 I
DOPPLER MEM
C)
2
MKR BCN VOL
U,
0
DPLR-115A22 --- X2 NOTES
X
-MKR-5A24 (BLU) - . IF CW
1 REFER TO DIGITAL AFCS WIRING DIAGRAM.
DME-112B22
-MKR-12A22 (BLU) E 000DME-112A22 2 REFER TO GNS-X SYSTEM WIRING DIAGRAM.
D DME-111A22. a.
N
MKR-12A22 (WHT)
x 3 REFER TO EFIS (PILOT) WIRING DIAGRAM.
N
r
C
C
IC)
DPLR-113B22-J
0
.MKR-13A24N DME-113A22N B
dig 4 REFER TO EFIS (COPILOT) WIRING DIAGRAM.
DPLR-114822 -
E REFER TO ICS WIRING DIAGRAM (BASIC MANUAL).
MKR-14A24-'f A I }--DME-114A22 Q1
MKR31A22N B DME-131A22 I1
2
412-SAR-97.10
97-00-00
Page 55/56
BHT-41 2-MMS-SAR
ImwWN
1ALT-2A22 )WHT) 1ALT-2B22 )WHT)
I - )3440A1P2A-69) 1EFIS-133A22 IVIO)
- )344OA2P2B-36) 1EFIS-133F22 LH BLKHD
DISC
a
)344OTB1-55) iEFIS-i33B22
CI)
I_
L3408TR1 J 1ALT-2A22 (BLU) 1ALT-2B22 (BLU) I 3408J4 3408P4 08
0
0
COPILOT RADIO
0
U)
1
L 3408TR1P1 P [_3408DS2PJ
I -(344OA2P2B-37) 1EFIS-133F22 (VBLU)
N
REC/XMTR U ALT ND
CI)
ALTITUDE W IL (344OTB1-59( 1EFIS-133C22 T
ANN
200
1ALT-2C22 )WHT) T
N
000
1ALT-2A22(WHT) ALTITUDE
OUTPUT COMMON N S
0
U
CU
0
FLG WRN Y R 1ALT-4C22-
TEST
S
T t-
iii 1ALT-6A22 NNONDNDNDN . 1ALT-6B22
P
1ALT-6C22 -
N
E
FLAG WRN
NNN N
4444444
S TEST
Z
T T T
+15VDC i ALT-7A22 (WHT) -
NNN
1ALT-7A22 )WHT) 1ALT-7B22 )WHT) H +15VDC
000Z29
-15VDC A 1ALT-7A22 (BLU)- 1ALT-7A22 1ALT-7B22 (BLU)- J -15VDC
0C)
-
I
M 1ALT-7A22 (ORN)- -
CC)
-
POWER GROUND B 1ALT-1OA22N,------ . 1ALT-1D22
G DH ANNUN LIGHT
28VDC INPUT
:E 1ALT-1E22
N
1ALT-1E22 1ALT-1C22 1ALT-1 1A22N V GROUND
N
N
AUX OUTPUT x 1ALT-5A22N------- M 28 V LIGHTING
ALT TRIP COMMON P
b
1ALT-12A22 P 5 V LIGHTING
50 FT TRIP R I__344OTB3P1] 344OTB3 I 3440TB3P1 ]
1ALT-13A22N LIGHTING GROUND
C
0
250 FT TRIP V
N
F DH BUS
400 FT TRIP L
\ 1ALT-6A22 1ALT-6B22----'
C)
-1ALT-15A22 DAY/NIGHT LOGIC
0
1200 FT TRIP U ________)344OA1 P2B-76) 1 EFIS-1 73A22 LV
'0N
N
L SPARE
N
INHIBIT 1ALT-16A22- 1ALT-4A22
N
1ALT-4B22 A SPARE
C)C>
L\{
0
)9A2P1C-53) 2EFIS-17D22 LV
SPARE F
G fI4O] I 340OTBj
N
SPARE
SPARE H
SPARE J 1ALT-1 2A22
SPARE K
1ALT-1OA22N
9WT31
9WT33 t__3400TB3P1 ]
1ALT-15A22 - BTB2
120 1ALT-1D22
1ALT-1 7A22N
121 1ALT-1C22
127 1ALT-1B22
I 3400WT3]
RECEIVE ANTENNA
J3 [08TR1 P3]
1ALT-1O1B
34O8P6 34O8J6
1ALT-i Oi A 1ALT-13A22N
1ALT-11A22N
- C
D
8] 3400J2 3408CB1
NOTE 3400P2
0
34O8E4 RAD ALT 1
REFER TO EFIS (PILOT) WIRING DIAGRAM.
-
0
U)
1ALT-1B22 1ALT-1A22 NON-ESNTL 28 VDC BUS 1
I 3408TR1P21 34O8P5 34O8J5 REFER TO EFIS (COPILOT) WIRING DIAGRAM.
J2
N
3408E3
412-SAR-97-1 1
97-00-00
Page 57/58
BHT-412-MMS-SAR
ALT-6A22
3408DS1
2
3408TR2
C-
J1 COPILOT
00
n, J1 RAD ALT IND
--
9
PILOT RADIO ALTIMETER 3408TR2P1 3408DSiP1
0
-
RECIXMTR
P..
!i
--
ALTITUDE W ALT-2D22 (WHT) T
NNNN
NNNN
ALTITUDE
C
ALT-2A22 (WHT( ALT-2B22 (WHT) ALT-2C22 (WHT)'
l-O
0
N v ---
-4+m0
OUTPUT COMMON ALT-2D22 (BLU) - ALT-2A22 (BLU) ALT-2B22 (B ALT--2C22 (BLU(' U OUTPUT COMMON
ALT-4022 -
f
Y
-
FLAG WRN -ALT-4C22 N
03030703030
ALT-4A22 ALT-4822 FLAG WRN
030303
NNNNNNNN
NNNNNNNZ
TEST ALT-6C22 - ALT-5A22 ALT-5822 ALT-5822 E +9 VDC IND REF
+9 VDC IND REF S ALT-5A22 --- ALT-6822 S TEST
03
ALT-6A22
0
ALT--6B22
+
0'4
+
ALT-7A22
+
-15 VDC A ALT-8A22--
NNN NN
ALT-8A22 ALT-8822 ALT.8B22 J -15VDC
M ALT-9A22-
15 VDC COMMON
POWER GROUND - ALT.1OA22N-
ALT-1E22-
e ALT-9A22
. ALT-10A22N
ALT-9822
ALT-10B22N
ALT--9B22
ALT-1022
K 15 VDC COMMON
G DH ANNUN LIGHT
28VDCINPUT -- ALT-1E22 ALT-1C22 ALT-11A22N V GROUND
AUX OUTPUT X M 28 V LIGHTING
ALT TRIP COMMON P ALT-12A22 P 5 V LIGHTING
00000
-r4
NZ
R
"i=44_4-4
50 FT TRIP R
0000
C')
1200 FT TRIP U L
D ALT-16A22- 87 AFCS COMPUTER SPARE
INHIBIT ALT-2D22 (WHT)
Nm>N
ALT-2A22 (WHT) J A
OUTPUT TEST E ALT-17A22N (3440A2P2A-69) 2EFIS-133A22 (VIO) SPARE
W
D
D SPARE
SPARE A 2 (3440A1P2B-36( 2EFIS-133E22 (VIO(
B 3400WT8 L8782 I1 SPARE
SPARE 5---(3440TB3P1.32(2EFIS-133822(WHT)
SPARE C
SPARE F ALT-2D22 (BLU) ALT-10B22N
2
ALT-2A22 (BLU)
N
N NN
2
SPARE G --(3440A2P2A-7O( 2EFIS-133A22(VBLU) ALT-11A22N ALT-15A22
H ALT-13A22N
-n
SPARE $(3440A1P2B-37(2EFIS-133E22(VBLU)
J
D
C-
SPARE
Cod,
(3440TB3.36(2EFIS-133B22(BLU(
SPARE K
ALT 4022 ALT-4A22
N
5--(9A1P1C-53( 2EFIS-17D22 LV
NNN N
3400TB3 I 3400T83P1 NOTES
NNNN
1
$--(3440A2P1A-78) 2EFIS-17A22 LV
2F (344OA1P1A-79)2EFI5-17822LV
1 REFER TO EFIS (PILOT) WIRING DIAGRAM
NN
(9A2P1C-42( 2EFIS-17C22 LV 2 REFER TO EFIS (COPILOT) WIRING DIAGRAM
N
3400J2 3400P2 3408CB2
N
3408P2 3408J2
N
J2
N
3408TR2P2
0
RAD ALT 2
0(D-
3408TR2P3
J3
I 3400WT6
3408E2P1
1
3408E2
412-SAR-97-12
00
97-00-00
Page 59/60
BHT-412-MMS-SAR
13420TR1P1I
I342OTR1P1I
J201
3420TR1 I J201 ________ WXR-17A22N 13420E1!iI J301
6
RECIXMTR .;
9
.1P WXR-3A22(WHTI
WXR-3A22(BLU)
WXR-3422(WHT) ''' M HIN
ANTENNA
WXR-3A22(BLU) LO
7 WXR-4A22IWHTI WXR-4A22IWHT) _____________________ V HI
10 ELVTACH ( WXR-4A22 (BLUI WXB-4A22 BLU) _______________ LO
11 EXT CRS SEL NO) AZ RESLV Si 1 WXR-5A22 (WHT) WXR-5A22 (WHTI F AZ RESLV Si
18 OBSIG) 14 -
':'
AZRESLVS2 WXR-5A22(BLU) wxR-5A228Lw E
26
27
NOEFIS(NO)
200 MV/DEGREE NO)
AZRESLVS3 iT - WXR-6A22IWHT) WXR-6A22(WHTI
'a AZRESLVS2
D AZRESLVS3
AZ RESLV 54 15 WXR-6A22 (RIG) E AZ RESt/I 54
32
33
CRS (X)/08S ID> RES 1 16 : .WXR7A22 wxR6022 (BLU/
WXR-7A22 B RES 1
CR5 (51/085 IF) BBS 2 17- WXR-8A22 - C RES 2
34 CRS )Z)/OBS El ELV RESLV Si 21 - WXR-9A22 )WHT) WXR-9A22 )WHT) - P ELV RESLV Si
38 AAS SELECT (NO) ELV RESLV 52 23 - WXR-9A22 IBLU) WXR-9A22 (BLU) - B ElM RESLV 52
35 TRANSMIT ON (NO//SYNC/F) 12 - jWXRi0A22 (WHY)
41
44
SPARE
SPARE
ELy RESLV S3
ELV RESLV 54 24 - _ WXR-i0A22 )BLU(
25 - ----WXR-i iA22
WXR-10A22 (WHT(
WXRi0A22 (BLU( - U
T ELV RESLV 53
ELV RESLV 54
p K +2R VDC (SW(TCHEO(
+28 VDC (SWITCHED) WXR-i 1A22
51 ARINC5BRDATA(P( AZDR(VEA(P/ ----WXR-i2A22(WHT( WXR-i2A22(WHT(- A AZDRIVEA(P(
52 SPARE
AZDRIVEB(P/ ___-__WXR-i2A22/BLU/ WXR-i2A22(BLU) AZDRIVEB(P(
ELVMTR+ WXR-13A22 (WHT( WXR-13A22 (WHT( -
60 iWXR-i3A22(RLU) ) ELV MOTOR
ARINC 56R SYNC (N)
ELVMTR-
_ -I-WXR-i4A22 WXR-i3A22(BLU/ _
I
61 TO(P( WXR-14A22- _ +23V0C
__
+26 VOC
WXR-i5A22 -
_
62 FROM (F)
ANTENNA GND 7K -WXR-i5A22 ________ ANTENNA GROUND
63 RM((P( WXR-i6A22 ______________ I 3420CBi
__________________________I
P500 GND BUSFEEDER
64
65
68
69
RMI(Y)
RMI(Y(
A(RSPEEDSIG
A(RSPEED REN
ANALOG ATT/HDG (NO)
115VAC400HZ (
8
?
- WXR-iB22 _____________________________________________
WXR-38A22N
WXR-39A22N _____________
________ WXR-iA22X8Bi8 1
WXR-41A22N
_______
I3420A1P1I _
_________________________
F CHASSIS GND
1EFIS-i8E22 _________ 3K -I __________ WHT____________________________________ WHT
;P 54 HDG VAL (PD) RT ESCI BUS (P) WHT N NT ESCI BUS (F)
CC
55 11 3 -4
III III
1EF(S-163A22(WHT) LTEWXPO)P) SIESC(BUS)N) BLU BLU BLU 'J ESCIBUS)N)
tiF 1 EFIS-163A22 (BLU( 55 LT EWXPD (N) I 0- WXR-26A20N
IP E +Z8VDC BiN
1791_I__.:Y
__________ so _______
_________ _______
_________
EJ I ___________ J LIGHTING SIN
9C,)
1EFIS-i64A22 (WHY)
\[ EFIS LT ESC( BUS (F) WXR-28A20N
:? I(iP 1EFIS-i64A22 (BLU( I 97 EFIS LT ESCI BUS (N) N EEC DISABLE )N)
Z__.:J 1IO-1EFI5-230A22N-------'
E1 Ei1
9TB4
:
cj
0000
________ ANNUNCIATOR PWR 28/14VDC
L;'h_.-
_
_ ______WXR-3iA22 C
I 3420CB2
2EFIS-163A22)WHT) : 74 RTEWXPD(P) WXR 32A22 3 +28 V LIGHTING
68 Jj1 2EFIS-163A22(BLU( 76 RTEWXPD(N) 35
+2SVDC 36 - -WXR-2D22 VS WXR-2Ai6 _________________-_WXR-2Ai6
-WXR-29022 P FSR1 /NO((W.O.W.)
T RTON1
L. ,IP
+
i 2EFIS-i64A22)WHT) 89 EFISRTESC(BUS)P(
{ 37 VC WXR-2G16 WXR-2G16 ------- - WXR-2H20 D VDC
EElS SI ESCI BUS (N)
_ IIEF)S-23022
96
_
-WXR-20B22 S REMOTEON)NO)
U
REMOTE ON ________
T
i1C22(WHT( _________ 29
.T HDG)X) WXR-20C22
_________
I34200S1P1J _ JiOl
RADARIND(CATOR
35 1CMPS-1 1C22 (BLU) 30 HOG )Y) 56 - WXR-40B22N
-24---4-------iCMPE-iiC22(ORN( 31 HDG)Z( 07 XR-2K20 ___________ N +28 VI3C
j
,.-..-_J +28VDCRTN
iCMPE-40A22N---CtI 58 - WXR-40D22N
R-20C22 E REMOTE ON (NO)
i_27TB1Pi
°°
28 SYNCHRO REF 28 VAC HI -WXR-42A20 +o V LIGHTING
WXR-47A22N 04 SYNCHROREF2BVACLO
(I'' -WXR-33A2I7N B
!
_ IiJ
________ -P
___________ ,-P
WXR-43B22(WHT( __________
-P
___________ _______._P
WXR-43A22)WHT( __________ PITCH HI
LT ESCI BUS (F)
LT ESCI BUS (N) '34
WHT
__________BLIJ
_______________________________________________
WHT
I3'0TB2Pi
_________
jEiJJ
i:iEiJ I27TB1P1
________I
__________
__ I
IDDI___________ WXR-43B22(BLU( __________ -
___________ WXR-43A22(BLU) _________
- ___________ L-'p F
___________
_ BLU
WXR-29D22
_______
49 ROLL HI
_
WXR-44B22(WHT) WXR29A22
____________ __________ _____________
WXR-44A22(WHT)
I1 50 ROLLLO
-ri- ___________
iii _' : .P1
________ ________
I TB2I,
)
_
. WXR-29C22 H FSR1 )NO( (WOW.)
I: P ' I
;-cI I ''
611131
_II
115_____________
III
______________It )
WXR-50A22)WHT) :;;
'I,
ALT(TI.IDEARINC429A
II --
-_
WXR-36A20N
___________________________________________
______________________________________________ ...P
_______________
D
F
LIGHTING BiN
ESCI BUS (FL Li
______________ G ESCIBUS)N)LT
NOTE
_________________________
DIAGRAM )BAS(C MANUAL).
4i2-SAR-97i3
3
CD
CD
CD
E
97-00-00
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