BHT-412-SI-73

SERVICE INSTRUCTION
FOR FLIGHT DATA
RECORDER

EFFECTIVITY

KIT NUMBER MODEL SERIAL NUMBER

412-706-084-101 412 36087 and Subsequent

COPYRIGHT NOTICE
COPYRIGHT 2007
BELL ® HELICOPTER TEXTRON INC.
AND BELL HELICOPTER TEXTRON
CANADA LTD.
ALL RIGHTS RESERVED

27 AUGUST 2007
BHT-412-SI-73

PROPRIETARY RIGHTS NOTICE

These data are proprietary to Bell Helicopter Textron Inc. Disclosure,

reproduction, or use of these data for any purpose other than helicopter
operation or maintenance is forbidden without prior written authorization from
Bell Helicopter Textron Inc.

Additional copies of this publication may be obtained by contacting:

Commercial Publication Distribution Center
Bell Helicopter Textron Inc.
P. O. Box 482
Fort Worth, Texas 76101-0482

PN 27 AUG 2007
 BHT-412-SI-73

LOG OF REVISIONS

Insert latest revision pages and dispose of superseded ones.

On a revised page, the text and/or illustration affected by the latest revision is shown by a vertical line. A revised
page with only a vertical line next to the page number indicates that text has shifted or that non-technical
correction(s) were made on that page.

Original ........................... 0......................... 27 AUG 07

LOG OF PAGES

Page No. Rev No. Page No. Rev No.

Title .............................................................................0 1-11/1-12 .................................................................... 0

PN...............................................................................0 1-13/1-14 .................................................................... 0
A/B ..............................................................................0 1-15 – 1-22 ................................................................. 0
i/ii ................................................................................0 1-23/1-24 .................................................................... 0
Help ............................................................................0 2-1/2-2 ........................................................................ 0
Customer Feedback ...................................................0 2-3/2-4 ........................................................................ 0
1-1/1-2 ........................................................................0 3-1/3-2 ........................................................................ 0
1-3 – 1-8 .....................................................................0 3-3 – 3-6 ..................................................................... 0
1-9/1-10 ......................................................................0

LIST OF CHAPTERS

Chapter Description Page

1 Installation Procedures ................................................................................................. 1-1

2 Operation and Maintenance ......................................................................................... 2-1
3 Parts Information and Kit Inventory .............................................................................. 3-1

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 BHT-412-SI-73

APPROVAL AND VERIFICATION

The Engineering aspects of this document are FAA approved.

Kit 412-706-084-101 has been verified by first article installation on Model 412 S/N 36373, dated 25 February
2005.

27 AUG 2007 i/ii

 H ELP

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L OGISTICS

P UBLICATIONS

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incorrect or unclear. Please be as specific as possible.

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You may use the enclosed Customer Feedback form, as

applicable, to inform us where we have erred.

Your assistance is sincerely appreciated.

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 BHT-412-SI-73

CHAPTER 1 — INSTALLATION PROCEDURES

TABLE OF CONTENTS

Paragraph Page
Number Title Number

1-1 General Information ............................................................................................ 1-3

1-2 Preparation ......................................................................................................... 1-4
1-3 Flight Data Recorder Kit Components — Installation ......................................... 1-4
1-4 Flight Data Recorder (FDR) — Installation .................................................... 1-4
1-5 Air Data Computer (ADC) — Installation ....................................................... 1-4
1-6 Flight Data Acquisition Unit (FDAU) — Installation........................................ 1-4
1-7 Relay and Accelerometer — Installation........................................................ 1-8
1-8 Pitot Static — Modification .................................................................................. 1-8
1-9 Pitot Static Without Flight Director Kit Installed — Modification..................... 1-8
1-10 Pitot Static With Flight Director Kit Installed — Modification.......................... 1-15
1-11 Leak Test ............................................................................................................ 1-22
1-12 Tail Rotor Pedal — Calibration and Test ............................................................ 1-22
1-13 Restoration.......................................................................................................... 1-23

FIGURES

Figure Page
Number Title Number

1-1 Flight Data Recorder Kit Components — Installation ......................................... 1-5

1-2 Flight Recorder Data — Wiring Diagram ............................................................ 1-9
1-3 Pitot Static — Modification .................................................................................. 1-16

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INSTALLATION PROCEDURES

1-1. GENERAL INFORMATION

WARNING

MATERIALS REQUIRED
BEFORE USING S O LV E N T S ,
Refer to BHT-ALL-SPM for specifications. EXTINGUISH ALL FLAMES AND PILOT
L I G H T S . K E E P P R O DU C T A N D I T S
NUMBER NOMENCLATURE VAPORS AWAY FROM HEAT, SPARKS,
AND FLAMES. AVOID USING SPARK
C-100 Chemical Film Material PRODUCING ELECTRICAL EQUIPMENT
SUCH AS SWITCHES, APPLIANCES,
C-101 Corrosion Preventive
ETC. DURING APPLICATION AND UNTIL
Compound, Grade 1
VA P O R S ARE GONE. AV O I D
C-104 Corrosion Preventive PROLONGED BREATHING OF VAPORS
Compound, Grade 2 AND REPEATED CONTACT WITH SKIN.

C-204 Epoxy Polyamide 4. Following any drilling or cutting, remove burrs

Primer and metal particles and wipe area with MEK (C-309).
For aluminum, brush with chemical film material
C-309 MEK (C-100). Follow application with a thin coat of epoxy
polyamide primer (C-204) to bare metal.

5. When installing ground wires, or components

requiring ground, clean structure surface to bare metal
CAUTION to provide good electrical bond. Apply one coat of
epoxy polyamide primer (C-204) over bond joint after
completion.
ALL OPENINGS AND PORTS IN
COMPONENTS, HOSES AND/OR TUBES
DISCONNECTE D OR RE MOVED TO 6. Apply Grade 2, corrosion preventive compound
FACILITATE MODIFICATION SHALL BE (C-104) on all exposed bolt shanks prior to kit
CAPPED, PLUGGED, OR OTHERWISE installation. After installation and torquing, coat bolt
SEALED TO PREVENT CONTAMINATION heads, nuts, washers and all external exposed threads
DURING MODIFICATION. with Grade 1, corrosion preventive compound (C-101).

1. Tag all parts removed to gain access to work 7. When installing this kit, exercise care to prevent
areas, including attaching hardware (unless otherwise damage to adjacent structure and equipment.
noted). Protect parts from damage until reinstalled.
8. Do not tie or clamp wire bundles until all kit wiring
2. Consumable materials may or may not be has been routed and connected.
supplied with kit, depending on customer’s
requirements for consumable items at the time kit was 9. Perform continuity check on all wiring newly
ordered. To inform maintenance personnel of installed or disturbed during this modification.
consumables required, a MATERIALS REQUIRED
statement is provided at the beginning of each 10. Unless otherwise noted, all hose clamps should
paragraph, as required. Refer to the BHT-ALL-SPM for be installed to provide optimum clearance between
information on consumable materials (C-XXX). hoses and structure.

3. Refer to the BHT-ELEC-SPM for electrical For information and maintenance procedures, refer to
installation procedures. the BHT-412-MMS-4.

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BHT-412-SI-73

1-2. PREPARATION 10. Verify electrical bonding of mount (8) is less than
10 milliohms.

WARNING NOTE
For wiring diagram, refer to Figure 1-2.
ENSURE ELECTRICAL POWER IS OFF. 11. Check wires, ground, and continuity.

1. Open nose access door (BHT-412-MM).

12. Position flight data recorder (7) on mount (8) and
push carefully into place.
2. Disconnect battery.
13. Place the two tray-locking mechanisms over flight
1-3. FLIGHT DATA RECORDER KIT data recorder (7) crow feet and secure by turning
COMPONENTS — INSTALLATION locking mechanism until hand-tight.

1-4. FLIGHT DATA RECORDER (FDR) — 14. Verify that flight data recorder (7) is securely
INSTALLATION mounted to mount (8) and no looseness is evident.

1. In the nose, remove existing connector clamp, as 1-5. AIR DATA COMPUTER (ADC) —
shown in Figure 1-1, View A. INSTALLATION

2. Unstow 27A1P1 connector (11) and remove all 1. Unstow 27A2P1 connector by removing
wired contacts from connector. Mark wires for hardware from mounting bracket and attaching
reinstallation. clamps.

2. Remove mounting bracket from shelf.

3. Remove back cover from mount (8).

3. Prepare surface for bonding (BHT-ELEC-SPM).

4. Insert cable assembly through mount (8) hole.
4. Install strip (2, Figure 1-1) between 3413CP1
5. Insert wires previously marked in step 2 into coupler and 27A2 air data computer (3).
27A1P1 connector. Refer to the BHT-412-MMS-4 for
the wiring diagram.
5. Position air data computer (3) and secure with
four screws (4) and washers (5), as shown in View A.
NOTE Electrically bond, Class R-I (BHT-ELEC-SPM).

Make sure connector (11) indexing pins are 6. Verify electrical bonding is less than
aligned with associated flight data recorder 2.5 milliohms.
(7) indexing pins.
7. Connect 27A2P1 connector.
6. Position connector (11) on mount (8) and secure
with four screws (12) and nuts (13).
1-6. FLIGHT DATA ACQUISITION UNIT (FDAU)
— INSTALLATION
7. Reinstall back cover on mount (8).
1. In the nose, remove existing connector clamp, as
8. Prepare surface for bonding (BHT-ELEC-SPM). shown in Figure 1-1, View B.

9. Position mount (8) and spacer (9), and secure 2. Secure FDAU 27AR1P1 connector (15) to
with screws (10), as shown in View A. Electrically mount (18) with four screws (16), washers (17), and
bond, Class R-II (BHT-ELEC-SPM). nuts (13).

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 BHT-412-SI-73

A A

B B

1 27MT1

SEE DETAIL C
STA
129.00
REF

2 1 3 7 27A2

4
3413CP1
(REF) 5 6 27K1

STA
0.00
REF

7 2 27A1
2337A1
(REF)
8 2

11 3 4 9
VIEW A
ROTATED 90° CW 12 10

13
412_SI_73_0001

Figure 1-1. Flight Data Recorder Kit Components — Installation (Sheet 1 of 3)

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BHT-412-SI-73

27AR1 2 14

2337S1 (REF)

STA
22.82
REF
VIEW B 13 3
ROTATED 90° CW 15 18 2

16 19
STA
129.00 17 20
REF
1 27MT1

21

25

23 24 22 6

23
DETAIL C 412_SI_73_0002

Figure 1-1. Flight Data Recorder Kit Components — Installation (Sheet 2 of 3)

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 BHT-412-SI-73

1. Accelerometer (3001-01-101-2)
2. Strip (120-055-2-4)
3. Air Data Computer (412-375-014-101)
4. Screw (MS27039-4-08) 4 Reqd
5. Washer (NAS1149D0416J) 4 Reqd
6. Relay (M83536/2-024M)
7. Flight Data Recorder (177045-01-01)
8. Mount (95387-2)
9. Spacer (412-075-106-103) 2 Reqd
10. Screw (MS24693-S55) 4 Reqd
11. Connector (Ref)
12. Screw (MS35206-216) 4 Reqd
13. Nut (MS21042L04) 8 Reqd
14. Flight Data Acquisition Unit (412-375-013-101)
15. Connector (Ref)
16. Screw (MS35206-249) 4 Reqd
17. Washer (NAS1149DN416J) 4 Reqd
18. Mount (404A-38-S-1/DPX2-0)
19. Spacer (412-075-106-105) 2 Reqd
20. Screw (NAS1189-04P7) 4 Reqd
21. Support Assembly (Ref)
22. Screw (MS27039-1-09) 2 Reqd
23. Washer (NAS1149D0332J) 4 Reqd
24. Screw (MS27039-1-08) 2 Reqd
25. Door Assembly (Ref)

NOTES

1 Use existing hardware.

2 Electrically bond Class R-II.

3 Remove existing connector clamp.

4 Disconnect all wires. Mark them for reinstallation.

5 Use existing clamp, bracket and hardware.

6 Discard existing screw and washer, at two places.

7 Electrically bond Class R-I.

412_SI_73_0003

Figure 1-1. Flight Data Recorder Kit Components — Installation (Sheet 3 of 3)

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BHT-412-SI-73

3. Prepare surface for bonding (BHT-ELEC-SPM).

NOTE

4. Position mount (18) and spacer (19), and secure For wiring diagram, refer to Figure 1-2.
with screws (20), as shown in View B. Electrically
bond, Class R-II (BHT-ELEC-SPM). 6. Check wires, power, ground, and continuity.

5. Verify electrical bonding of mount (18) is less than 1-8. PITOT STATIC — MODIFICATION
10 milliohms.
1-9. PITOT STATIC WITHOUT FLIGHT
DIRECTOR KIT INSTALLED —
6. Disconnect and remove 3410TR1 transponder MODIFICATION
and attach wire bundles to clean area.

NOTE CAUTION
For wiring diagram, refer to Figure 1-2.

7. Check wires, ground and continuity. TORQUE ALL PLASTIC FITTINGS TO

15 ±5 INCH-POUNDS (1.695 NM).
8. Position flight data acquisition unit (14) on
mount (18) and push carefully into place. NOTE
Ensure all lines and fittings to be installed
9. Place the two tray-locking mechanisms over flight are free of water traps; use drain
data acquisition unit (14) crow feet and secure by caps (50-012-02N400) to meet these
turning locking mechanism until hand-tight. requirements.

10. Verify that Flight Data Acquisition Unit (14) is 1. On left frame, locate hole for copilot pitot air line,
securely mounted to mount (18) and no looseness is as shown in Figure 1-3, View B.
evident.
2. Mark and drill three 0.193 to 0.198 inch (4.90 to
5.03 mm) (#10) diameter holes using dimensions
11. Reinstall 3410TR1 transponder.
shown on Figure 1-3, sheet 1.

1-7. RELAY AND ACCELEROMETER —

3. Locate existing copilot pitot nylon tube (10), and
INSTALLATION
cut to fit, as shown in View B.

1. At station 129.0, as shown in Figure 1-1, remove

4. Install tee assembly (9) and three inserts (8).
existing clamps and mounting bracket. Discard
existing screws and washers.
5. Remove cap (7) from existing tee fitting and
retain, as shown in View B.
2. Unstow 27MT1P1 connector.

6. Install insert (8) on existing tee fitting.

3. Position 27MT1 accelerometer (1, Figure 1-1) on
support assembly (21) with two screws (24) and
washers (23). NOTE
Tubing furnished in bulk quantity. Cut to fit
4. Position existing clamps and mounting bracket during installation.
with two screws (22) and washers (23), as shown in
Detail C.
NOTE
5. Connect 27K1 relay (6) with existing screw and Tubing (29) to be installed in copilot system
washer, as shown in View A. only.

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 BHT-412-SI-73

FLIGHT DATA RECORDER

27A1 W9
27A1P1 27CB2
J1
115 VAC 1 FDR-38A22 1 1 3400TB3 3400TB3P1

FLT DATA RECORDER

63 FDR-42A22WHT 1
P FDR-42A22BLU 2
PLAYBACK OUT (A) 9 FDR-23A22WHT
PLAYBACK OUT (B) 10 FDR-23A22BLU 67

7 P 43 C97C22 3
FDAU DATA IN (A) FDR-24A22WHT
FDAU DATA IN (B) 8 FDR-24A22BLU 27TB1 27TB1P1
FDR-35A22N 89 W76C22 4
PITCH 7
CHASSIS GND 6 FDR-36A22N TRANSDUCER 13 W11F22 5
7 9MT1 W9
9MT1J1 FDR-23A22WHT 6
POWER GND 2 FDR-37A22N FDR-23A22BLU 7
T FDR-24A22WHT 8
FAULT OUT 21 FDR-8A22 2 D FDR-25B22WHT
FDR-24A22BLU 9
F FDR-25B22BLU
FAULT EXCITATION IN 23 FDR-41A22 3 E FDR-25B22ORN

27TB1P1 27TB1
MAINTENANCE FLAG OUT 22 FDR-10A22 4
ROLL
P
TRANSDUCER FDR-25A22WHT 1
T 22WT1 FDR-25A22WHT 10
7 9MT2 W9 FDR-25B22WHT 2
T FDR-25A22BLU 11
9MT2J1 FDR-25C22WHT 3
T F FDR-40A22N 12
FDR-25D22WHT 4
D
T
FDR-25C22WHT FDR-25E22WHT T 5
5 22WT1 F FDR-25C22BLU FDR-25A22BLU 8
E FDR-25C22ORN FDR-25B22BLU 9
D FDR-37A22N
C FDR-36A22N FDR-25C22BLU 10
B FDR-35A22N FDR-25D22BLU 11
YAW
FDR-25E22BLU 12
TRANSDUCER
FDR-25B22ORN 32
7 9MT3 W9
FDR-25F22 33
5 22WT1 9MT3J1
FDR-25C22ORN 36
X FDR-19A22N T
D FDR-25D22WHT FDR-25G22 37
W FDR-18A22N
F FDR-25D22BLU
E FDR-25D22ORN FDR-25D22ORN 40
FDR-25H22 41
AIR DATA COMPUTER
27A2 W9 FDR-25E22ORN 44
COLLECTIVE
27A2P1 FDR-25J22 45
TRANSDUCER
8 9MT6 W9
28 VDC 1 FDR-17A22 3
9MT6J1 FDR-25J22 13
POWER GND 2 FDR-18A22N
FDR-19A22N FDR-25H22 14
T
P D FDR-25E22WHT FDR-25G22 15
ADC DATA OUT (A) 3 FDR-20A22WHT
F FDR-25E22BLU FDR-25F22 16
ADC DATA OUT (B) 4 FDR-20A22BLU
E FDR-25E22ORN 22WT1
P
OAT IN HI 13 FDR-21A22WHT
Y FDR-26A22N 17
OAT IN LO 14 FDR-21A22BLU

FDR-20A22WHT 18
9 99 FDR-20A22BLU 19
2300P1 B A 114
6 22WT1
2300J1 10 112 113 9
110 111 FDR-20A22WHT E FDR-39A22N 20
OUTSIDE AIR TEMP 115 116 FDR-20A22BLU
27E1 117 118 9
10
27E1P1 119

P 2301TB1 6
OAT HI 1 FDR-21B20WHT
OAT LO 2 FDR-21B20BLU 27TB1P1 27TB1 27TB1P1 D5 2AUD-34B22 21
3 E5
412-077-044-107 F5 6
CABLE ASSEMBLY REF G5
412_SI_73_0009

Figure 1-2. Flight Recorder Data — Wiring Diagram (Sheet 1 of 3)

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FLIGHT DATA AQUISITION UNIT

3400TB3P1 3400TB3 12
27AR1 13 FLIGHT DATA AQUISITION UNIT
FDR-17A22
W9 T W9 27AR1
119 FDR-41A22 W9
27AR1P1A 14 27AR1P1B
J1A J1B 27AR1P1B
27CB1
11 13 PRI HYD PRESSURE W9 109 J1B
27AR1P1A 5 FDR-1A22 6 28 VDC IN T
15 PITCH ATTITUDE (X) 51 F813C22WHT 22
P J1A 100
1 FDR-42A22WHT 68 CVR TIMING (A) FDAU PITCH ATTITUDE (Y) 49 F813C22BLU 23
2 FDR-42A22BLU 69 CVR TIMING (B) T 2CMPS-11D22WHT
HEADING (X) 48 PITCH ATTITUDE (Z) 48 F813C22ORN 24
HEADING (Y) 51 2CMPS-11D22BLU PITCH ATTITUDE (H) 50 F816C22WHT 25
HEADING (Z) 49 2CMPS-11D22ORN
3 C97C22 15 SAS FAULT 2CMPS-10D22 3400TB1P1 3400TB1 12 T
HEADING (H) 50 ROLL ATTITUDE (X) 62 F816C22BLU 26
W9 ROLL ATTITUDE (Y) 60 F816C22ORN 27
4 W76C22 30 MASTER CAUTION 100 27AR1P1B ROLL ATTITUDE (Z) 59 F170E22 28
ROLL ATTITUDE (H) 61 F170F22 29
5 W11F22 34 ENG 1 FIRE
P 11 13 SEC HYD PRESSURE
6 FDR-23A22WHT 7 FDR PLAYBACK IN (A) 22WT1 5
8TB3 11
7 FDR-23A22BLU 8 FDR PLAYBACK IN (B)
P R FDR-2A22N 2 PWR GND
8 FDR-24A22WHT 71 FDAU DATA OUT (A)
5 LN LP U FDR-5A22N 5 CHASSIS GND
9 FDR-24A22BLU 72 FDAU DATA OUT (B)
LT LW BATTERY TEMP 15 W161F22 30

PWR TURBINE 1 SPEED (H) 32 E59F22 ROTOR BRAKE 2 ON 16 W126D22 31

22WT1 5
PWR TURBINE 1 SPEED (C) 33 FDR-44A22N
P G 22WT1 5 TRANSMISSION OIL TEMP 18 D22E22 32
10 FDR-25A22WHT 92 TRANSDUCER EXCITATION (H)
11 FDR-25A22BLU 93 TRANSDUCER EXCITATION (C) 5 S FDR-3A22N 3 DIGITAL SIGNAL GND
12 FDR-40A22N T FDR-4A22N 4 ANALOG SIGNAL GND
P 5 KN KR
ENG 1 TORQUE 0-5V (H) 40 E52F22WHT
KP KS
ENG 1 TORQUE 0-5V (L) 41 E52F22BLU BAGGAGE COMPARTMENT SMOKE 30 W26D22 33
5 KT KY
P AUTOPILOT 2 ENGAGED 25
KW KZ
ENG 1 OUT 31 W104E22 ENG 2 FIRE 34 W31E22 34
5 LH LC GEARBOX OIL TEMP 17 E90E22 35
MAIN ROTOR SPEED (H) 98 D2G22 LG LD
MAIN ROTOR SPEED (C) 99 FDR-30A22N
11
11 RA RC
RB RD FDAU FAULT 72 FDR-9A22 36
11
20 SAS/AFCS 1 FAULT
7 21 AFCS 1 ATT MODE AFCS 2 SAS MODE 22
22 AFCS 1 SAS MODE 27TB1P1 27TB1 2301TB1 6 AFCS 2 ATT MODE 21 7
SAS/AFCS 2 FAULT 20
19 E2 2AUD-35B22 14 VHF 2 KEY
18 D2 PWR TURBINE 2 SPEED (H) 32 E62F22 37
22WT1 6
AUTOPILOT 1 ENGAGED 25 17 F2 PWR TURBINE 2 SPEED (C) 33 FDR-31A22N 38
Z 5 16 G2
FDR-43A22 15 P
EVENT MARKER 19 ENG 2 TORQUE O-5V (H) 40 E56F22WHT 39
ENG 2 TORQUE 0-5V (L) 41 E56F22BLU 40
13 FDR-25J22 1 COLLECTIVE POSITION 83
14 FDR-25H22 2 PEDAL POSITION 84 ENG 2 OUT 31 W150E22 41
15 FDR-25G22 3 CYCLIC POSITION LAT 85
16 FDR-25F22 11 CYCLIC POSITION LONG 120 FDR-10A22 75 FDR MAINTENANCE FLAG IN
16
121
17 FDR-26A22N ROTOR BRAKE 1 ON 16 W125D22 22 FDR-46A22N 42
PROG SELECT 1 105
P PROG SELECT 2 104
18 FDR-20A22WHT 53 AIR DATA IN (A) 3400TB3P1 3400TB3 12 PROG SELECT 4 103
19 FDR-20A22BLU 54 AIR DATA IN (B)
XMSN OIL PRESS 18 D23E22 92

20 FDR-39A22N P
GEARBOX OIL PRESS 17 Q69E22 103 LAT ACCEL (PROV) (H) 63 FDR-12C22WHT 43
LAT ACCEL (PROV) (C) 64 FDR-12C22BLU 44
P FDR-15C22WHT FDR-13C22 45
VERT ACCEL (H) 59 ACCEL 28 VDC OUT 76
VERT ACCEL (C) 60 FDR-15C22BLU ACCEL GND 77 FDR-14C22 46
P FDR-16C22WHT FDR-15C22WHT 47
LONG ACCEL (H) 63
LONG ACCEL (C) 64 FDR-16C22BLU FDR-15C22BLU 48
21 2AUD-34B22 14 VHF 1 KEY 22WT1 FDR-16C22WHT 49
FDR-45A22N H 5 FDR-16C22BLU 50

412_SI_73_0011

Figure 1-2. Flight Recorder Data — Wiring Diagram (Sheet 2 of 3)

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 BHT-412-SI-73

27TB1P1 27TB1

T
50
22WT1
57 NOTES
V FDR-6A22N
22 F813C22WHT 61 1 Refer to Maintenance Manual, Chapter 98, for AC power wiring diagram.
23 F813C22BLU
T
24 F813C22ORN 65
25 F816C22WHT
2 To 27XK1 relay socket, pin X1.
W9
69
27K1 27XK1 3 To 27CB1 circuit breaker.
26 F816C22BLU
27 F816C22ORN 73 B3
28 F170E22 B2
4 To 27AR1P1B connector, pin 75.
29 F170F22 53 B1
54 A3 FDR-6A22N 5 Refer to Maintenance Manual, Chapter 98, for power plant wiring diagram.
A2 FDR-7A22
77 A1 6 Refer to Maintenance Manual, Chapter 98, for intercommunication system wiring diagram.
88 X1 FDR-8A22 17 7 Refer to Maintenance Manual, Chapter 98, for AFCS or DDAFCS wiring diagram.
30 W161F22
92 X2 FDR-9A22
31 W126D22 8 Refer to Maintenance Manual, Chapter 98, for flight director or DDAFCS wiring diagram.
80
32 D22E22 103 9 Refer to Maintenance Manual, Chapter 98, for weather radar kit wiring diagram.
107
124 10 Refer to Maintenance Manual, Chapter 98, for GNS-X wiring diagram.

11 Refer to Maintenance Manual, Chapter 98, for caution and lighting diagram.
33 W26D22 22WT1 5
12 Refer to Maintenance Manual, Chapter 98, for AHRS wiring diagram.
34 W31E22 A
MASTER CAUTION PNL
35 E90E22
11 8A1 W9 13 To 27A2P1 air data computer, pin 1.
8A1P1
8TB2 5 14 To 27A1P1 flight data recorder, pin 23.
36 FDR-9A22 FDR SYS FAIL 29 FDR-7A22
5 LN LP 15 Refer to Maintenance Manual, Chapter 98, for DC power wiring diagram.
LT LW

5 KT KW 16 To 27A1P1 flight data recorder, pin 22.

P
KZ KY
5
5 KN KP 17 To 27A1P1 flight data recorder, pin 21.
37 E62F22 KS KR
38 FDR-31A22N
5 LA LB
39 E56F22WHT LF LE
40 E56F22BLU 11
11 RJ RL
41 W105E22 RK RM
11

22WT1 5

42 FDR-46A22N K

ACCELEROMETER
W9 W9 W4 W40
W40 27MT1
22J14 22P14 5 1J8 1P8 5
27MT1P1
24
43 FDR-12C22WHT P 16 P FDR-12B22WHT P U P FDR-12A22WHT P G SPARE
44 FDR-12C22BLU 17 FDR-12B22BLU V FDR-12A22BLU F SPARE
45 FDR-13C22 18 FDR-13B22 W FDR-13A22 D 28 VDC
46 FDR-14C22 19 FDR-14B22 X FDR-14A22 E PWR GND
47 FDR-15C22WHT P 20 P FDR-15B22WHT P Y P FDR-15A22WHT P A VERT ACCEL (H)
48 FDR-15C22BLU 21 FDR-15B22BLU Z FDR-15A22BLU FDR-15D22 B SIG COMMON
49 FDR-16C22WHT P 22 P FDR-16B22WHT P A P FDR-16A22WHT P C LONG ACCEL (H)
50 FDR-16C22BLU 23 FDR-16B22BLU B FDR-16A22BLU H SPARE
FDR-40A22N
412_SI_73_0012

Figure 1-2. Flight Data Recorder — Wiring Diagram (Sheet 3 of 3)

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14. Install pitot and static tubings (29) on bracket (31)

NOTE
with clamp (30), screw (32), two washers (13), and
Identify pitot line (P) using tape (4) nut (33).
(instrument air) and tape (5) (pitot), where
length and access permit. Identify static line 15. Cut two new pieces of tubing (29) approximately
(S) using tape (4) (instrument air) and 5.5 inches (140.0 mm) long.
tape (6) (static), where length and access
permit.
16. Install pitot tubing (29) to “P” port on air data
computer (1) with union (24), packing (25), and
7. Install pitot tubing (29) to tee assembly (9)
insert (8).
forward of copilot airspeed indicator using insert (8).

17. Install static tubing (29) to “S” port on air data

NOTE computer (1) with reducer (26), packing (27), nut
assembly (28), and insert (8).
Tubing (29) to be installed in copilot system
only.
18. Install tee assembly (9) to each tubing installed in
step 16 and step 17 using three inserts (8).
NOTE
Identify pitot line (P) using tape (4) 19. Install union (24), insert (8), and caps (34) in tee
(instrument air) and tape (5) (pitot), where assembly (9).
length and access permit. Identify static line
(S) using tape (4) (instrument air) and 20. Check pilot and copilot pitot static systems for
tape (6) (static), where length and access leakage in accordance with the BHT-412-MM.
permit.

8. Install tubing (29) to existing tee fitting, previously 1-10. PITOT STATIC WITH FLIGHT DIRECTOR
uncapped, using inserts (8). KIT INSTALLED — MODIFICATION

NOTE
CAUTION
Discard existing screw and clamp.

9. Install pitot and static tubings (29) with two TORQUE ALL PLASTIC FITTINGS TO
clamps (11), clamp previously removed, screw (20), 15 ±5 INCH-POUNDS (1.695 NM).
two washers (13), spacer (21), spacer (22), and nut
(23) in existing hole.
NOTE

10. Continue routing and install pitot and static Tubing furnished in 36-inch length.
tubings (29) with two clamps (11), screw (16), washer
(13), spacer (17), and nut (18) in hole previously NOTE
drilled.
Ensure all lines and fittings to be installed
are free of water traps; use drain
11. Continue routing and install pitot and static caps (50-012-02N400) to meet these
tubings (29) with two clamps (11), screw (16), washer requirements.
(13), spacer (17), and nut (18), two places, in holes
previously drilled. 1. Disconnect existing lines from 9A7 air data
sensor (3, Figure 1-3), as shown in Detail A.
12. Locate relay bracket (36) on shelf beside air data
computer (1), as shown in Detail D. 2. Cut and install tee assemblies (9) on each line
using insert (8), as shown in Detail D. Recommended
13. Install bracket (31) on bracket (36) using existing position of the new tee assemblies is at approximately
hardware, as shown in Detail D. 9 inches (228.6 mm) from the 9A7 air data sensor.

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BHT-412-SI-73

3.50 IN.
13.50 IN. (88.9 mm)
(342.9 mm)

7.50 IN.
(190.5 mm)
1
0.75 IN. (19.05 mm)
CONST

9A8
WL
DETAIL A 24.75
9A7 REF

STA
-10.80
REF

VIEW LOOKING INBOARD AT LH SIDE

412_SI_73_0004

Figure 1-3. Pitot Static — Modification (Sheet 1 of 6)

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 BHT-412-SI-73

4
6 11
4
6
13
5 29
19 3
2 29
20

21

22

23

18 17 16 13 11

6 11

12

13

14

15
7

8 9

5
10 4
C

VIEW B
WITHOUT FLIGHT DIRECTOR KIT INSTALLED

412_SI_73_0010

Figure 1-3. Pitot Static — Modification (Sheet 2 of 6)

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Figure 1-3. Pitot Static — Modification (Sheet 3 of 6)

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 BHT-412-SI-73

8
8
26 13
1 24 29 2
27 30
25
28 31
WL 32
35.82
REF 33

36
ADC
27A2
29 3
(REF)
8
3 29
9

24

34
BL LBL
0.00 14.00
REF REF
WITHOUT FLIGHT DIRECTOR KIT INSTALLED

8
8
26 35
1 2
24
27
25
28
WL
35.82
REF

3 35

3
8

BL LBL
0.00 14.00
REF REF
WITH FLIGHT DIRECTOR KIT INSTALLED
DETAIL D 412_SI_73_0006

Figure 1-3. Pitot Static — Modification (Sheet 4 of 6)

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BHT-412-SI-73

1. Air Data Computer (Ref) 19. Clamp (MS21919WDG13) (Ref)

2. Air Data Sensor (Ref) 20. Screw (MS27039-1-39)
3. Air Data Sensor (Ref) 21. Spacer (NAS43DD3-40)
4. Tape (31-033-5A) 22. Spacer (NAS43DD3-52)
5. Tape (31-032-48A) 23. Nut (MS21042L3)
6. Tape (31-032-32A) 24. Union (50-012-08N400) 1 Reqd for Mod -109,
7. Cap (50-012-02N400) (Ref) 3 Reqd for Mod -105
8. Insert (50-012-01N404) 25. Packing (MS28778-4)
14 Reqd for Mod -105, 8 Reqd for Mod -109 26. Reducer (MS21916W5-4)
9. Tee Assembly (50-012-15N400) 27. Packing (MS28778-5)
3 Reqd for Mod -105, 2 Reqd for Mod -109 28. Nut Assembly (50-012-06N400)
10. Existing Nylon Tube (Ref) 29. Tubing (130-052-4W)
11. Clamp (MS25281-F4) 8 Reqd 30. Clamp (MS21919WDG7)
12. Screw (MS27039-1-23) 2 Reqd 31. Bracket (MS9592-024)
13. Washer (NAS1149D0332J) 7 Reqd 32. Screw (MS27039-1-08)
14. Spacer (NAS43DD3-40) 2 Reqd 33. Nut (MS21042L3)
15. Nut (MS21042L3) 2 Reqd 34. Cap (50-012-02N400) 2 Reqd
16. Screw (MS27039-1-39) 35. Tubing (130-052-4W288)
17. Spacer (NAS43DD3-104) 36. Bracket (Ref)
18. Nut (MS21042L3)

NOTES

1 Drill three 0.193 to 0.198 inch (4.90 to 5.03 mm) diameter holes through structure and
pick up new clamping arrangement.

2 Identify static line using tape (4) (instrument air) and Bell pitot line with tape (6) (static)
where length and access permit.

3 Identify pitot line using tape (4) (instrument air) and Bell with tape (5) (static) where length
and access permit.

4 Cut existing nylon tube to fit.

5 Discard existing screw and reinstall clamp.

6 Use existing hole.

412_SI_73_0007

Figure 1-3. Pitot Static — Modification (Sheet 5 of 6)

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 BHT-412-SI-73

ADAPTER ADAPTER
AIRSPEED (REF) AIRSPEED (REF)
PILOT PITOT TUBE PILOT PITOT TUBE
UPPER RIGHT UPPER RIGHT
SIDE STATIC RIGHT SIDE STATIC RIGHT
PORT ROOF MOUNT PORT ROOF MOUNT
STATIC PORT ALTIMETER (REF) STATIC PORT ALTIMETER (REF)

LOWER LEFT LOWER LEFT

SIDE STATIC SIDE STATIC
PORT VERTICAL (REF) PORT VERTICAL (REF)
SPEED SPEED

D (REF)
AIR DATA
D SENSOR 9A8

ALTERNATE ALTERNATE

(REF) (REF)
PRIMARY PRIMARY

PILOT PILOT

ADAPTER ADAPTER
AIRSPEED (REF) AIRSPEED (REF)
COPILOT PITOT TUBE COPILOT PITOT TUBE
LOWER RIGHT LOWER RIGHT
SIDE STATIC LEFT SIDE STATIC LEFT
PORT ROOF MOUNT PORT ROOF MOUNT
STATIC PORT ALTIMETER (REF) STATIC PORT
ALTIMETER (REF)

UPPER LEFT UPPER LEFT

SIDE STATIC SIDE STATIC
PORT VERTICAL (REF) PORT VERTICAL (REF)
SPEED SPEED

D D (REF)
AIR DATA AIR DATA
D COMPUTER 27A2 D SENSOR 9A7

AIR DATA
COMPUTER 27A2

COPILOT COPILOT

WITHOUT FLIGHT DIRECTOR KIT INSTALLED WITH FLIGHT DIRECTOR KIT INSTALLED

SYSTEM SCHEMATIC

PITOT LINE ADDED BY THIS MOD

PITOT LINE EXISTING
STATIC LINE ADDED BY THIS MOD
STATIC LINE EXISTING
DRAIN D
412_SI_73_0008

Figure 1-3. Pitot Static — Modification (Sheet 6 of 6)

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BHT-412-SI-73

3. Cut two new pieces of tubing (35) approximately e. When the airspeed indicator reaches
10.5 inches (266.7 mm) long. 130 knots, cut the pressure.

f. After a period of 5 minutes, the airspeed

NOTE indication shall not decrease more than 10 knots.
Identify pitot line (P) using tape (4)
(instrument air) and tape (5) (pitot), where 1-12. TAIL ROTOR PEDAL — CALIBRATION
length and access permit. Identify static line AND TEST
(S) using tape (4) (instrument air) and
tape (6) (static), where length and access
1. Enable the hydraulic systems.
permit.

4. Install pitot tubing (35) to “P” port on air data 2. Apply full left pedal.
computer (1) with union (24), packing (25), and
insert (8), and connect other end of tubing (35) to the 3. Disconnect 9MT3J1 connector.
tee assembly (9) on pitot line using insert (8).
4. Measure and note the resistance (Ω) between
5. Install static tubing (35) to “S” port on 27A2 air pins D and F of 9MT3 CMT.
data computer (1) with reducer (26), packing (27), nut
assembly (28), and insert (8), and connect other end
5. Multiply resistance value (noted in step 4)
of tubing (35) to the tee assembly (9) on static line
by 12.0%. Note the value determined.
using insert (8).

6. Install pitot and static tubing (35) to “S” port and 6. Multiply resistance value (noted in step 4)
“P” port on 9A7 air data sensor (3). by 0.5%. Note the value determined.

7. Perform a leak test (paragraph 1-11). 7. Reconnect the multimeter across pins E and F of
9MT3 CMT.

1-11. LEAK TEST

8. Loosen the jam nut on the CMT and adjust the
transducer shaft until this 12.0% value is obtained
NOTE (±25Ω).

Refer to the BHT-412-MM-10, Chapter 96

for complete procedure. 9. Tighten the jam nut and verify the resistance is
still within ±25Ω of the calculated input value.
1. With the instruments and related equipment
connected to the pitot static lines, check the system for 10. Reconnect 9MT3J1 connector.
leakage, as follows:
11. With the caution panel "FDR SYST FAIL" light on,
a. Seal static port on one side of the fuselage apply power to the 115 VAC BUS #3 and verify that
and the cabin roof. "FDR SYS FAIL" light extinguishes.

b. Apply vacuum to port on the opposite side of 12. Center the pedals and wait several seconds.
the fuselage until the altimeter indicates 1000 feet
above the ambient pressure altitude.
13. Apply full left pedal and hold for several seconds.
c. Stop vacuum for a period of 1 minute. The
loss of indicated altitude shall be less than 100 feet on 14. Apply full right pedal and hold for several
the altimeter. seconds.

d. Seal the pitot tube and apply air pressure. 15. Re-center the pedals.

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 BHT-412-SI-73

d. Adjust the transducer shaft to increase the

NOTE
pin E to F resistance value by 0.5% (see step 6) of the
Word #18 (Rotor Pedal #1 subframe) and total resistance value.
word #50 (Rotor Pedal #2 subframe) are
used to record the tail rotor pedal position 18. Repeat step 9 through step 16 until both full left
parameters. and right pedal readings are within the specified
ranges.
16. Download the FDR data file and verify from the
readout if the pedals are within the specified ranges, 19. Reconnect 9MT3J1 connector.
as follows:
1-13. RESTORATION
SPECIFIED RANGE
PEDAL POSITION (ROTOR PEDAL) 1. Ensure all hardware is secured and properly
PARAMETER (%) safetied.

MIN MAX
2. Check all new wiring, connections, and clamps
Fully Left -106 -94 for security.
Fully Right 94 106
3. Install all access doors removed to gain access to
17. If the values are not within the specified ranges, work area.
proceed as follows:
4. Revise helicopter weight and balance.
a. Remove power to the 115 VAC BUS #3.
5. Connect battery.
b. Disconnect 9MT3J1 connector.
6. Perform operational test procedure
c. Apply full left pedal and loosen the jam nut. (BHT-412-MMS-4).

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 BHT-412-SI-73

CHAPTER 2 — OPERATION AND MAINTENANCE

TABLE OF CONTENTS

Paragraph Page
Number Title Number

2-1 Operation Procedures......................................................................................... 2-3

2-2 Maintenance Procedures .................................................................................... 2-3
2-3 Weight and Balance............................................................................................ 2-3

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 BHT-412-SI-73

OPERATION AND MAINTENANCE

2-1. OPERATION PROCEDURES 2-3. WEIGHT AND BALANCE

Refer to the BHT-412-MMS-4.

NOTE
2-2. MAINTENANCE PROCEDURES The weight quoted is the delta weight effect
of this kit. This includes weight and effect of
Refer to the BHT-412-MMS-4. the items removed when this kit is installed.

LONGITUDINAL *LATERAL

HELICOPTER KIT NUMBER WEIGHT ARM MOMENT ARM MOMENT

412 412-706-084-101 23.9 12.0 287 -3.1 -74

(10.8) (305) (33) (-79) (-9)

*In lateral calculations, - is left, + is right.

WEIGHT pounds (kilograms)

ARM inches (millimeters)

MOMENT inch-pounds ⎛ kg × mm
----------------------- ⎞
⎝ 100 ⎠

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 BHT-412-SI-73

CHAPTER 3 — PARTS INFORMATION AND KIT INVENTORY

TABLE OF CONTENTS

Paragraph Page
Number Title Number

3-1 Kit Information..................................................................................................... 3-3

3-2 Kit Inventory (412-706-084-101) ......................................................................... 3-3

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 BHT-412-SI-73

PARTS INFORMATION AND KIT INVENTORY

3-1. KIT INFORMATION

NOTE

This chapter lists assemblies, subassemblies, and Common hardware packed with kit may
detail parts for the Flight Data Recorder kit. vary from that in the following parts list.
Some items of this kit may be shipped
pre-assembled. All modifications required
3-2. KIT INVENTORY (412-706-084-101) for field installation of this kit will be
annotated with flagnotes.
Part numbers in parentheses ( ) are alternate or
superseded part numbers.

QUANTITY PART NUMBER NOMENCLATURE

1 412-706-084-101 Accessory Kit, Flight Data Recorder, Consisting of:

2 412-075-106-103 Spacer

2 412-075-106-105 Spacer

1 412-375-013-101 Flight Data Acquisition Unit

1 412-375-014-101 Air Data Computer

1 1 412-575-205-105 Modification, Pitot Static, Consisting of:

5 MS21042L3 Nut

1 AS5230W0504 Reducer
(MS21916W5-4)

1 MS21919WDG7 Clamp

8 MS25281-F4 Clamp

1 MS27039-1-08 Screw

2 MS27039-1-23 Screw

2 MS27039-1-39 Screw
1 MS28778-4 O-ring

1 MS28778-5 Packing

1 MS9592-024 Bracket
7 NAS1149D0332J Washer

1 NAS43DD3-104N Spacer
(NAS43DD3-104)

3 NAS43DD3-40N Spacer
(NAS43DD3-40)

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BHT-412-SI-73

QUANTITY PART NUMBER NOMENCLATURE

1 412-706-084-101 (Cont) Accessory Kit, Flight Data Recorder, Consisting of:

1 1 412-575-205-105 (Cont) Modification, Pitot Static, Consisting of:

1 NAS43DD3-52N Spacer
(NAS43DD3-52)

10 feet 2 130-052-4W Tubing

(3 m)

3 feet 3 31-032-32A Tape

(91.4 cm)

3 feet 4 31-032-48A Tape

(91.4 cm)

3 feet 3 4 31-033-5A Tape

(91.4 cm)
14 50-012-01N400 Insert, Fitting
(50-012-01N404)

2 50-012-02N400 Cap

1 50-012-06N400 Nut Assembly

3 50-012-08N400 Union

3 50-012-15N400 Fitting-union

1 5 412-575-205-109 Modification, Pitot Static, Consisting of:

1 AS5230W0504 Reducer
(MS21916W5-4)

1 MS28778-4 Packing

1 MS28778-5 Packing
1 130-052-4W288 Tubing

3 feet 3 31-032-32A Tape

(91.4 cm)

3 feet 4 31-032-48A Tape

(91.4 cm)

3 feet 3 4 31-033-5A Tape

(91.4 cm)

8 50-012-01N400 Insert, Fitting

(50-012-01N404)

1 50-012-06N400 Nut Assembly

1 50-012-08N400 Union

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 BHT-412-SI-73

QUANTITY PART NUMBER NOMENCLATURE

1 412-706-084-101 (Cont) Accessory Kit, Flight Data Recorder, Consisting of:

1 5 412-575-205-109 (Cont) Modification, Pitot Static, Consisting of:

2 50-012-15N400 Fitting-union

8 MS21042L04 Nut
4 MS24693-S55 Screw

2 MS27039-1-08 Screw

2 MS27039-1-09 Screw

4 MS27039-4-08 Screw

4 MS35206-216 Screw

4 MS35206-249 Screw
1 M83536/2-024M Relay

4 NAS1149DN416J Washer

4 NAS1149D0332J Washer
4 NAS1149D0416J Washer

4 NAS1189-04P7 Screw

1 120-055-2-4 Strip

1 177045-01-01 Flight Data Recorder

1 3001-01-101-2 Accelerometer

1 404A-38-S-1/DPX2-0 Mount
1 95387-2 Mount

1 BHT-412-MMS-4 Maintenance Manual Supplement

1 BHT-412-SI-73 Service Instruction

NOTES:

1 For helicopters S/N 36087 and subsequent, and S/N 33214 and subsequent without 412-706-024 Auxiliary
Kit Flight Director installed.

2 Bell STD 130-052-4W is supplied in bulk length to be cut to fit at installation.

3 Identify Static line per MIL-STD-1247 using Bell STD 31-033-5A tape (Instrument Air) and Bell STD
31-032-32A tape (Static) where length and access permit.

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BHT-412-SI-73

NOTES (CONT):

4 Identify Pitot line per MIL-STD-1247 using Bell STD 31-033-5A tape (Instrument Air) and Bell STD
31-032-48A tape (Pitot) where length and access permit.

5 For helicopters S/N 36087 and subsequent, and S/N 33214 and subsequent with 412-706-024 Auxiliary Kit
Flight Director installed.

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