523-0759332-30 1 1 14

May 1/67
3rd Revision, Mar 1/73

COLLINS

maintenance manual
(with installation data)

AP=lO3F/FD=108,
A P - 1 0 3F/FD - 1 0 8 G ,
and AP - 1 0 3F/FD 1 0 9G =

Flight Control Systems

Printed in United States of America

WARNING
INFORMATION SUBJECT TO EXPORT CONTROL LAWS

This document may contain information subject to the International Traffic in ArmS
Regulation (ITAR) or the Export Administration Regulation (EAR) of 1979 which may
not be exported. released, or disclosed to foreign nationals inside or outside of the
United States without first obtaining an export license. A violation of the ITAR or EAR
may be subject to a penalty of up to 10 years imprisonment and a fine of up to
S1.ooO.000 under 22 U.S.C.2778 of the Arms Export Control Act of 1976 or section
2410 of the Export Adminislration Act of 1979. Include this notice with any reprodmed
portion of this document.

0 Copyright 1999 Rockwell Collins, Inc. All rights reserved.

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Collins Radio Company Cedar Rapids, lo wa 1
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RECORD O F REVISIONS

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RECORD O F TEMPORARY REVISIONS

TEMPORARY
REMOVED

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LIST O F EFFECTIVE PAGES

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Collins Radio Company welcomes your comments concerning this instruction book. Send your comments to: Collins Radio Company
.Although every effort has b w n made to keep it free of errdrs. some do occur. Publications Engineering Department
\\'hen reporting a specific problem. please describe it briefly and include the in- Mail Station 108-275
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401/177 May 1/67 Check 602 May 1/67
401/178 Blank 603 May 1/67
401/179 May 1/67 604 May 1/67
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Adjustment/ 501 May 1/67

Test 502 May 1/67
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 aI MAINTENANCE MANUAL

SERVICE BULLETIN LIST

SERVICE MANUAL MANUAL

BULLETIN SUBJECT REVISION REVISION
NO NUMBER DATE

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-

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TABLE OF CONTENTS

SUBJECT .
PAGE

DESCRIPTION AND OPERATION ........, ........... 1

1.General . . . . . . . . . . . . . . . . . . . . . . . . . . . 1
2 . Purpose of Equipment . . . . . . . . . . . . . . . . . . . . . 3
3 . Equipment Specifications . . . . . . . . . . . . . . . . . . . 4
4 . Equipment Description . . . . . . . . . . . . . . . . . . . . 7
A . AP-103F Automatic Flight Control System . . . . . . . . . 7
B . FD-108. FD-108G. and FD-109G Integrated Flight Systems . . 14
5 . Theory of Operation . . . . . . . . . . . . . . . . . . . . . 26
A . General . . . . . . . . . . . . . . . . . . . . . . . . . 26
B . Automatic Flight Control System Theory of Operation . . . . 26
C . Integrated Flight System Theory of Operation . . . . . . . . 38

TROUBLESHOOTING .......................... 101

1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . 101

SERVICING (Not Applicable) . . . . . . . . . . . . . . . . . . . . . . . 30 1

RE MOVA L/INSTA LLATION . . . . . . . . . . . . . . . . . . . . . . . 40 1

1.General . . . . . . . . . . . . . . . . . . . . . . . . . . . 401
2 . Preparation for Initial Installation . . . . . . . . . . . . . . . 401
A . Unpacking . . . . . . . . . . . . . . . . . . . . . . . . 401
B . Aircraft Preparation . . . . . . . . . . . . . . . . . . . 401
.
C Equipment Preparation .................. 441
. ............
D 562C-4 Autopilot Amplifier Strapping 441
.
E 562A-5G Flight Computer Logic Board Strapping . . . .
... 449
. ...
F 590A-3E Altitude Controller Parameter Switch Strapping 461
.
G 344C-1F Instrument Amplifier Monitor Logic Strapping. ... 462
.
3 Removal and Replacement . . . . . . . . . . . . . . . . . . . 462
A . 121A-2 Emergency Disconnect . . . . . . . . . . . . ... 464
B . 161A-1 T r i m Coupler . . . . . . . . . . . . . . . . . . . 464
C . 161E-1 Mode Coupler . . . . . . . . . . . . . . . . . . . 464
D. 327D-1W T r i m Indicator . . . . . . . . . . . . . . . . . 465
E . 329B-7( ) Flight Director Indicator . . . . . . . . . . . . . 465
F . 329B-8G Flight Director Indicator . . . . . . . . . . . . . 466
G. 331A-6A Course Indicator . . . . . . . . . . . . . . . . . 466
H . 332G-2Rate Gyro . . . . . . . . . . . . . . . . . . . . 467
I . 344C-1D. 344C-1G and 344C-1F Instrument Amplifier . . . . 468
J . 344C-3( ) Primary Servo and 351B-3( ) Servo Mount . . . . . 468
K . 344D-2-33( ) T r i m Tab Servo . . . . . . . . . . . . . . . 469
.
L 345A-4B Sensing Unit ................... 469
.

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SUBJECT PAGE
M. 390D-6A Shockmount . . . . . . . . . . . . . . . . . . . 469
N. 562A-5G Flight Computer and 562C-4 Jutopilot Amplifier . . . 470
0. 590A-3E Altitude Controller . . . . . . . . . . . . . . . . 471
P. 590B-2 Airspeed Sensor . . . . . . . . . . . . . . . . . . 471
Q. 614E-2F. 614E-2G. or 614E-2G1 Pedestal Controller . . . . . 472
R. 79OC-1 Shockmount . . . . . . . . . . . . . . . . . . . . 472
S. 790M-1 Shockmount . . . . . . . . . . . . . . . . . . . . 473
T. 790M-1A Hard Mount ................... 473
U. 8905-1 Shockmount . . . . . . . . . . . . . . . . . . . . 474
V. 8 9OP-1 Shockmount . . . . . . . . . . . . . . . . . . . . 474

ADJUSTMENT/TEST .......................... 501

1.General ......................... .. 501

.
2 Post Installation Test for AP-103F/FD-108; AP-103F/FD-l08G;
.......
and AP-103F/FD-l09G Flight Control Systems .. 501
A. Loads .......................... 501
.
B System Check . . . . . . . . . . . . . . . . . . . . . . 501
.
C Command Gain Check ................. .. 504
. ...............
D Vertical Reference Level .. 504
.
E Gaincheck ....................... 504
.
3 Preflight Test Procedures ................... 506
.
4 Flight T e s t Procedures .................... 525
INSPECTION/CHECK ......................... 601

1. General . . . . . . . . . . . . . . . . . . . . ....... 601

2 . Inspection Procedures . . . . . . . . . . . . . . . . . . . . 601
A . Emergency Disconnect . . . . . . . . . . . . . . . . . . 601
B . RateGyro . . . . . . . . . . . . . . . . . . . . . . . . 601
C . Primary Servo . . . . . . . . . . . . . . . . . . . . . . 601
D . Trim Tab Servo (If Installed) . . . . . . . . . . . . . . . 601
E . T r i m Coupler (If Installed) . . . . . . . . . . . . . . . . 602
F . . Sensing Unit . . . . . . . . . . . . . . . . . . . . . . . . 602
G . Autopilot Amplifier . . . . . . . . . . . . . . . . . . . . 602
H . Altitude Controller . . . . . . . . . . . . . . . . . . . . 602
I . Airspeed Sensor . . . . . . . . . . . . . . . . . . . . . 602
J . Pedestal Controller . . . . . . . . . . . . . . . . . . . . 603
K . Flight Director Indicator and Course Indicator . . . . . . . . 603
L . Instrument Amplifier and Flight Computer . . . . . . . . . 60 3
M . Mode Coupler . . . . . . . . . . . . . . . . . . . . . . 604

CLEANING/PAINTING . . . . . . . . . . . . . . . . . . . . . . . . . 701
1. General . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
2.Cleaning . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
3 . Painting . . . . . . . . . . . . . . . . . . . . . . . . . . . 701
APPROVED REPAIRS . . . . . . . . . . . . . . . . . . . . . . . . . 801
ILLUSTRATIONS (Not Applicable) . . . . . . . . . . . . . . . . . . . . . 901

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 MAINTENANCE MANUAL
COLLINS AP- 103F/FD- 108

LIST OF ILLUSTRATIONS
FIGURE PAGE

1 AP-103F/FD-108, AP-103F/FD-l08G, and AP-103F/FD-l09G Flight

Control Systems (TPO-3135-017) (TPO-4577-017) (TPO-4699-017)
I2 (TPO-4366-017) , . . . . . . . . . . . . . . . . . . . 1
Equipment Supplied . . . . . . . .
. . . . . .. . . . .- . 1
3 Recommended Associated Equipment . . .. . .. . . . . . . . 4
4 System Specifications .. . . . . .. . .
. . .. . . . . . . 5
5 121A-2 Emergency Disconnect (TPO-5459-017) . . . . . . . . . . . 8
6 614E-2F and 614E-2G( ) Pedestal Controller .(C1042-30-P)
Pedestal Controller Control/Indicator Functions (TPO-5096-012) .
.
. . .. .
. . .
. 11
12
7
8 329B-7A Flight Director Indicator (TPO-5431-012). . . . . .
. . . . . 15
9 329B-7C Flight Director Indicator (TPO-4552-012). . . . . . . . . . 16
10 32 9B -7 ( ) Flight Director Indicator Control/Indicator Functions
(TPO-4561-013) . . . . . . . . . . . . . . .
. . . 17
11 329B-8G Flight Director Indicator (TPO-3614-012) . . . .
. . . . . 19
12 32 9 B -8 G Flight Director Indicator Control/Indicato r Functions
(C117 7 -04 -4) . . . . . . . . . . . . . . . . . . . . . 20
13 331A-6A Course Indicator (TPO-3613-012) . . . . . . . . . . . . 22
14 331A-6A Course Indicator Control/Indicator Functions
(C 119 6-03 -4) . . . . . . e . . . . . . . . . . . . . . 23
15 AP-103F/FD-108 Flight Control System, Functional Block Diagram , . . . 57
16 AP-103F/FD-l08G, FD-109G Flight Control System, Functional Block
Diagram (TPO-43 29 -013) . .
. . . . . . . . . .
. . . . . 59
17 AP-103F Pitch Channel, Functional Block Diagram (TPO-3045-034) . . . . 61
18 AP-103F Roll Channel, Functional Block Diagram (TPO-2636-024) . . . . 67
19 AP-103F Rudder Channel, Functional Block Diagram (TPO-3106-014) . . . 71
20 FD-108, FD-l08G, and FD-1O9G Attitude Display, Functional Block Diagram
(TPO-4 6 11- 0 14) . . . . . . . .. . . . . . . . . . . . . 73
21 FD-109G Runway Localizer and Altitude Display, Functional Block Diagram
(TPO-3668-015) . . . . . . . . . . . . . . . . . . . . . 75
22 FD-108, FD-l08G, and FD-1O9G Course and Heading Display, Functional
Block Diagram (TPO-4912-014). . . . . . . . . . . . . . . . 77
23 FD-108, FD-l08G, and FD-109G Roll Steering Command, Functional
Block Diagram (TPO-3622-016). . . . . . , . . . . . . . . . 79
24 FD-108, FD-l08G, and FD-1O9G Steering Command Processing, Functional
Block Diagram (TPO-4446-014). . . . . . . . . . . . . . . . 83
25 FD-108 Pitch Steering Command, Functional Block Diagram (TPO-5421-014) . 85
26 PD-108G and FD-109G Pitch Steering Command, Functional Block Diagram
(TPO-3619-014) . . . . . . . . . . . . .
. . . . . . . . 87
27 FD-108G and FD-109G Back Course Localizer Interlock, Simplified
. . . . . . . . . .
Sch em ati c Diagram (T P 0 - 512 9 - 0 12 ) . . . . 89
28 Pitch Synchronization Circuit, Functional Block Diagram (TPO-5147-012) . . 89
29 .
FD-108 Altitude Hold Interlock, Simplified Schematic (TPO-5132-012) . . 90
30 FD-1O8G and FD-109G Altitude Hold Interlock, Simplified Schematic
(TPO-4364-012) . . . . . . . . . . . . . . . . .
. . . . 90
401 121A-2 Emergency Disconnect, Outline and Mounting Dimensions
(C1022-99-X) . . . . .. . . . . . . . .
. . . . . . . 407

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cokiis AP- 103F/FD- 108

FIGURE PAGE
402 161A-1A Trim Coupler, Outline and Mounting Dimensions (TPO-4923-012) . . 408
403 161E-1 Mode Coupler and 89OP-1 Shockmount, Outline and Mounting
Dimensions (772-4764-001) . . . . . . . . . . . . . . . . . 409
404 327D-1W Trim Indicator, Outline and Mounting Dimensions (C1240-01-3). . . 411
405 329B-7 ( ) Flight Director Indicator, Outline and Mounting Dimensions
(C1105-09-4) . . . . . . . . . . . . . . . . . . . . . . 412
406 329B-8G Flight Director Indicator, Outline and Mounting Dimensions
(C1177-02-4) . . . . . . . . . . . . . . . . . . . . . 413
407 331A-6A Course Indicator, Outline and Mounting Dimensions (C949-16-3) , , 414
408 332G-2 Rate Gyro, Outline and Mounting Dimensions (C484-233-3) . . . . . 415
409 334C-3( ) Primary Servo with 351B-3 and 351B-3A Servo Mount, Outline and
Mounting Dimensions (C484-16-5) . . . . . . . . . . . . . . . 416
410 334D-2-33( ) Trim Tab Servo, Outline and Mounting Dimensions
(C454-94-5) . . . . . . . . . . . . . . . . . . . . . . . 417
411 344C - l D Instrument Amplifier, Outline and Mounting Dimensions
(C1024-04-3) . . . . . . . . . . . . . . . . . . . . . 419
412 344C-lF/lG Instrument Amplifier ,'Outline and Mounting Dimensions . . . . 420
413 345A-4B Sensing Unit, Outline and Mounting Dimensions (C484-07-4) . . . . 421
414 351B-3B and 351B-3C Servo Mount, Outline and Mounting Dimensions
(554-2624-005, 554-2625-005) . . . . . . . . . . . . 423
415 351B-3E Servo Mount, Outline and Mounting Dimensions (772-8511-001) . . . 425
416 390D-6A Shockmount, Outline and Mounting Dimensions (TPO-5426-012) . . . 427
417 390R-5B Hard Mount, Outline and Mounting Dimensions (TPO-4924-013) . . . 428
418 562A-5G Flight Computer, Outline and Mounting Dimensions (TPO-3617-014) . 429
419 562C -4 Autopilot Amplifier, Outline and Mounting Dimensions
(C1173-01-4) . . . . . . . . . . . . . . . . . . . . . . 430
420 590A-3E Altitude Controller and 79OC-1 Shockmount, Outline and Mounting.
Dimensions (554-0495-005) . . . . . . . . . . . . . . . . . 431
4 21 590B-2 Airspeed Sensor, Outline and Mounting Dimensions (TPO-4432-012) . . 432
422 614E -2F Pedestal Controller, Outline and Mounting Dimensions
(C1042-18-4) . . . . . . . . . . . . . . . . . . . . . 433
423 614E-2G( ) Pedestal Controller, Outline and Mounting Dimensions
(761-3067-001) (C1042-07-4) . . . . . . . . . . . . . . . . . 434
4 24 790M-1 Shockmount, Outline and Mounting Dimensions (C1173-04-5) . . . . 435
4 25 790M-1A Hard Mount, Outline and Mounting Dimensions (C1173-05-4). . . . 437
426 8905-2 Shockmount, Outline and Mounting Dimensions . . . . . . . . . 439
427 Aircraft Phasing Chart . . . . . . ... . . . . . . . . . . . . 442
428 . . . ,
Primary Servo, Torque Setting Diagram (C1022-94-P) . . . . . 443
429 . .
Spanner Wrench, Fabrication Diagram (C1234-02-2) . . . . . . . 443
430 . . .
562C-4 Autopilot Amplifier, Strapping Combinations . . . . . . . 445
4 31 . .
562C-4 Autbpilot Amplifier, Reversing Links Positioning (C1241-02-3) , 447
432 5 62C -4 Autopilot Amplifier, Elevator Board, Strapped Functions
(C1186-06-4) . . . . .
. . . . . . , . . . . . . . . . . 448
433 562C -4 Autopilot Amplifier, Aileron Board, Strapped Functions
(C1186-07-4) . . .
. . . . .
. . . . .
. . . . , . . . . 451
434 562C-4 Autopilot Amplifier, Rudder Board, Strapped Functions
(C1186-05-4) . . . . . .
. . . . .
. . . . .
. . . . . , 453
435 . . .
562A-5G Flight Computer, Logic Board TB4 Functions (C1238-02-4) . 455

22-03-00
nlustr at io&
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Mar 1/73
 MAINTENANCE MANUAL
COLLINS AP- 103F/FD- 108

FIGURE PAGE
436 . . .
562A-5G Flight Computer, Logic Board TB5 Functions (C1238-03-4) 45 6
43 7 .
590A-3E Altitude Controller, Parameter Switch Strapping (TPO-4363-011) 46 1
438 Cable Connectors. . . . . . . . . . . . . . . . . . . . . 462
439 AP-103F/FD-108 Master, Interconnecting Wiring Diagram (767-8250-001) . 475
440 AP- 103F/ FD- 108 Aer ocommander 68OT , Inter connecting Wiring
Diagram (767-8251-00) . . . . . . . . . . . . . . . . . . 483
441 AP- 103F/FD- 108 Aerocommander 1121 Jet, Interconnecting Wiring Diagram . 491
442 AP- 10 3 F/ F D- 10 8 Allegheny CV- 580, Interconnecting Wiring Diagram
(767-8253-00) . . . . . . . . . . . . . . . . . . . . . 499
443 AP-l03F/FD- 108 Allegheny F-2 7J, Interconnecting Wiring
Diagram . . . . . . . . . . . . . . . . . 401/7
444 AP-103F/FD-108 Dove, Interconnecting Wiring Diagram (TBS)
(767-8255-00) . . . . . . . . . . . . . . . . . . . . . 401/15
445 AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram . . . . . . . 401/23
446 AP-103F/FD-108 Fairchild F-27, Interconnecting Wiring Diagram . . . . 401/31
44 7 AP-103F/FD-108 Falcon (3-Axis), Interconnecting Wiring
Diagram . . . . . . . . . . . . . . . . . . . . . . . 401/39
44 8 AP-103F/FD-108 Gulfstream G-159, Interconnecting Wiring Diagram . . . 401/47
449 AP-103F/FD-108 Nord 262, Interconnecting Wiring Diagram (TBS)
(767-8261-00) . . . . . . . . . . . . . . . . . . . . . 401/55
450 AP- 103F/FD- 108 Sabreliner, Interconnecting Wiring
D i a g r a m . . . . . . . . . . . . . . . . . . . . . . . 401/63
451 AP-103F/FD-108 Piaggio PD-808, Interconnecting Wiring Diagram
(767-8232-00) . . . . . . . . . . . . . . . . . . . . . 401/71
452 AP-103F/FD-108 Ozark FH-227, Interconnecting Wiring Diagram . . . . 401/79
453 AP- 103F/FD-108 Fair child FH-227, Interconnecting Wiring
Diagram (767-8234-00) . . . . . . . . . . . . . . . . . . 401/87
454 AP-103F/FD-108 Beech King Air, Interconnecting Wiring Diagram
(767-8235-00) . . . . . . . . . . . . . . . . . . . . . 401/95
455 AP-103F Aerocommander 1121 Jet, Interconnecting Wiring Diagram. . . .401/103
456 AP-103F/FD-108 Falcon (2-Axis), Interconnecting Wiring Diagram . . . .401/111
45 7 AP- 103F/FD-108 HFB-32 0, Interconnecting Wiring Diagram (767-0830-00) .401/119
45 8 AP-103F/FD-l08G Master, Interconnecting Wiring Diagram (777-2563-001). 401/127
45 9 AP-103F/FD-l09G Falcon (3-Axis), Interconnecting Wiring
Diagram (772-45 25- 0 0 1) . . . . . . . . . . . . . . . . . 4 01/13 5
460 AP-103F/FD-l09G King Air, Interconnecting Wiring Diagram . . . . . .401/143
461 AP- 103F/ FD- 109 G Ae r ocommande r 1121 Jet, Interconnecting
Wiring Diagram (772-4527-001) . . . . . . . . . . . . . . .401/151
462 AP- 103F/FD-l09G Gulfstream I , Interconnecting Wiring Diagram
(772-4528-001) . . . . . . . . . . . . . . . . . . . . .401/159
463 AP- 103 F/ FD- 10 9G Sabre1ine r , Inter c onnect ing Wiring Diagram
(772-4529-001) . . . . . . . . . . . . . . . . . . . . .401/167
464 AP-103F/FD-l09G F-27J, Interconnecting Wiring Diagram (772-4530-001) .401/175
465 AP- 103F/FD- 109G DH- 125, Interconnecting Wiring Diagram
(772-4532-001) . . . . . . . . . . . . . . . . . . . . .401/183
5 01 Pitch Limit Resistor Selection Chart . . . . . . . . . . . . . . 503
502 Go-Around Pitch-up Resistor Selection Chart . . . . . . . . . . . 504
503 VOR Selected Resistor as a Function of Speed . . . . . . . . . . . 5 05
504 Altitude Gain Resistor Selection Chart. . . . . . . . . . . . . . 506
-

22-03-00
Illustrations
Page 3
Mar 1/73
 MAINTENAIVCE MANUAL
COLLINS AP- 103F/FD- 108
ww
FIGURE -
PAGE
505 AP-103F Preflight Test Procedure . . . . . . . . . . . . . 507
506 Trim Indicator Phasing (C1241-03-3) . . . . . . . . . . . . . 511
507 FD-108 Preflight Test Procedure . . . . . . . . . . . . . . 513
508 FD-108G Preflight Test Procedure . . . . . . . . . . . . . . 517
509 FD-109G Preflight Test Procedure . . . . . . . . . . . . . . 521
510 AP-103F Flight Test Procedure . . . . . . . . . . . . . . 52 7
511 FD-108 Flight Test Procedure . . . . . . . . . . . . . . 535
512 FD-108G Flight Test Procedure . . . . . . . . . . . . . . 539
513 FD-109G Flight Test Procedure . . . . . . . . . . . . . . 543

22-03-00
Illustrations
Page 4
M a r 1/7 3
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MAINTENANCE MANUAL
AP- 1 03F/FD- 108
wlw

FORE WORD
0

This manual has been prepared in accordance with A i r Transport Association Specification
No. 100 for Manufacturer's Technical Data. If used as intended, this manual will facilitate
the effective , continued operation of the AP-103F/FD-108, AP-103F/FD-l08G and AP-lOSF/
FD-109G Flight Control Systems.

This manual is intended for use by flight line and hangar maintenance personnel. A detailed
description, including complete specifications , is given for each equipment. Operation of the
overall system is described. Preinstallation and postinstallation test procedures, mounting,
and cabling information are presented a s an aid both to initial installation and to periodic
maintenance. Troubleshooting information is limited to procedures required to trace a
trouble to an easily replaceable unit.

The following is a list of related publications.

PU BLICA T ION COLLINS PART NO.

A P - 1 03F/FD-108, AP-103F/FD-l08G , and A P -103F/FD-l09G 523 -075 9327

Flight Control Systems Pilot's Guide

121A-2 Emergency Disconnect, Overhaul Manual 523 -075545 9

161A -1/1A Trim Coupler, Unit Instructions 523-0756021

161E -1 Mode Coupler, Overhaul: Manual 523-0759287

327D-1( ) Trim Indicator, Overhaul Manual 523 -0755463

329B-7/7( ) Flight Director Indicator, Overhaul Manual 523-0756711

329B-8G Flight Director Indicator, Overhaul Manual 523 -075 9268

331A-6A Course Indicator, Overhaul Manual 523-0756910

334C-3 Primary Servo and 351B( ) Servo Mount, Overhaul 523-0755470

Manual -

334D-2-33( ) Trim Tab Servo, Overhaul Manual 523-0755471

344C - l D Instrument Amplifier , Overhaul Manual 523-0756317

344C-1F Instrument Amplifier , Overhaul Manual 523-0758842
345A-4( ) Sensing Unit and 332G-2 Rate Gyro, Overhaul Manual 523-0755240

22-03-00
Fore word
Page 1
M a r 1/73
 a
COLLINS
MAINTENANCE MANUAL
AP- 103F/FD- 108
ww
I PUBLICATION COLLINS PART NO.

562A-5G Flight Computer, Overhaul Manual 523-0758123

562C-4 Autopilot Amplifier, Overhaul Manual 5 23 -075 813 0

590A-3E Altitude Controller, Overhaul Manual 523 -0757 95 6

590B-2 Airspeed Sensor, Overhaul Manual 523 -075 8131

614E-2F/2G Pedestal Controller, Overhaul Manual 523 -075 8132

Electromechanical Components, Overhaul Manual 523-0757895

The following is a list of unusual or uncommon abbreviations and symbols which a r e used
throughout this manual.

~ ~~

SYMBOL/ABBREVIATION IDENTIFICATION

ALT Altitude hold function

ANN Annunciator

APPR Approach mode

CAP Capture

CMPTR Computer flag

DEV Deviation

DE3 Disengage

DME Distance meaE wing equipment

.
ENG Engage

GA Go-around mode

GS Glideslope function

GS EXT Glideslope extension function

22-03-00
Foreword
Page 2
Mar 1/73
 I MAINTENANCE MANUAL
-1
COLLINS AP- 103F/FD- 108

SY MBO L/A PPREVIATION IDENTIFICATION

HDG Heading mode

HZ Hertz

ILS Instrument landing system

LOC Localizer mode

MAN PITCH Manual pitch function

MDA Minimum decision altitude

MG Motor -generator

NAV Navigation mode

PITCH SYNC Pitch synchronization function

sc Steering command (go-around mode)

SYNC Synchronizer (heading)

V/L VOR /localizer (NAV /LOC mode)

VOR Vhf omnirange

When logic functions a r e grouped within a diamond-shaped

symbol in the logic-block diagrams included in this manual,
a dot (.) between these logic functions indicates an AND
function. An AND function requires that all inputs must
be present to provide an output.
+ When logic functions a r e grouped within a diamond-shaped
symbol in the logic-block diagrams included in this manual,
a plus (+) between these logic functions indicates an OR
function. An OR function requires that only one of the in-
puts be present to provide an output.
_c

GS When a logic function is overscored, it indicates a NOT

function. A NOT function requires that the overscored
logic function NOT be present to achieve the logic condi-
tion shown.

22-03-00
Foreword
Pages 3/4
M a r 1/73
 MAINTENANCE MANUAL
AP- 703F/FD- 108

614E'ZF
PEDESTAL CONTROLLER 590A.3E 562C-4
ALTITUDE CONTROLLER AUTOPILOT AMPLIFIER

121A.1
790C.1 790M.1
EMERGENCY DISCONNECT SHOCKMUUNT SHOCKMOUNT

3340.2.33C 334c.3
TRIM TAB SERVO PRIMARY SERVO WITH
3518.3 SERVO MOUNT

332G.2 5908.2 345A.45

RATE GYRO AIRSPEED SENSOR SENSING UNIT

A. AP-103F AUTOMATIC FLIGHT CONTROL SYSTEM

AP-103F/FD-108, AP-103F/FD-1O8Gy and

A P -103F/F D-109G Flight Control Systern s
77-03-00
Figure 1
Figure 1 (Sheet 1 of 4) Page 1
M a r 1/73
 aI MAINTENANCE MANUAL

-1
C o i ~ i N s AP- IO3F/FD- 108

331A.6 COURSE INDICATOR 3298.7A FLIGHT DIRECTOR

IN DIGATOR

3900.6~ SHOCKMOUNT

562A.5G FLIGHT COMPUTER 344C-ID INSTRUMENT AMPLIFIER

B. FD.108 INTEGRATED FLIGHT SYSTEM :PO.& 77 0 1 7

AP-lOSF/FD-lOS, AP-103F/FD-l08G, and

AP-103F/FD-l09G Flight Control Systems
22-03-00
Figure 1
Figure 1 (Sheet 2) Page 2
M a r 1/73
 a
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MAINTENANCE MANUAL
AP- IO3F/FD- 108
ww

331A.6A COURSE INDICATOR 3298-7C FLIGHT DIRECTOR INDICATOR

562A-5G FLIGHT COMPUTER

344C-1F INSTRUMENT AMPLIFIER

161E-1 MODE COUPLER

8901-2 SHOCKMOUNT
C. FD.IO8G INTEGRATED FLIGHT SYSTEM TPO. 46 99.01 7

AP-103F/FD-108, AP-103F/FD-l08G, and

AP-103F/FD-l09G Flight Control Systems
22-03-00
Figure 1
Figure 1 (Sheet 3) Page 3
Mar 1/73
 a
COLLINS
MAINTENANCE MANUAL
AP- 103F/FD- 108
wlw

331A6A COURSE INDICATOR

3298.8G FLIGHT DIRECTOR INDICATOR

562A-5G FLIGHT COMPUTER 344C-1F INSTRUMENT AMPLIFIER

161E-1 MODE COUPLER 8901.2 SHOCKMOUNT

-
0. FD-lO9G INTEGRATED FLIGHT SYSTEM
i P 5 t S 66 3 1 :

AP-103F/FD-108, AP-103F/FD-l08G, and 77-03-00

AP-103F/FD-l09G Flight Control Systems Figure 1
Figure 1 (Sheet 4) Page 4
M a r 1/73
 Flight Control Systems
-
a
COLLINS
MAIKTENANCE
MANUAL

AP - 1 0 3F/FD - 1 0 8, AP - 10 3F/FD - 108G, and AP - 1 O3F/FD - 1 09G

- Description and Operation

1. GENERAL.

This section presents purpose, specifications, general description, and general theory of
operation of the A P - 1 O3F/FD-108, AP-l03F/FD -108G, A P -103F/FD -109G Flight Control
Systems, hereinafter called the Flight Control System. The AP-103F Automatic Flight
Control System (figure l A ) , when combined with either the FD-108 (figure l B ) , the
FD-108G (figure l C ) , or the FD-1O9G (figure 1D) Integrated Flight Systems, form one of
the three Flight Control Systems covered in this manual.

Figure 2 contains a list of the Flight Control System equipment covered in this manual.
The equipment is presented in groups according to subsystem, that is, AP-l03F,
FD-108, etc.

COLLINS PART
EQUIPMENT DE SCRIPTION NUMBER

AP-103F

121A-2 Emergency Disconnect Removes system power 5 22 -121 6 -001

161A-1A Trim Coupler Drives electrical t r i m system 522-4517-001

327D-1W T r i m Indicator Displays control surface 45 8 -04 05 -0 0

command

332G-2 Rate Gyro Provides yaw r a t e signal 229-0236-00

334C-3 Primary Servo Drives aircraft control 52 2 -12 25 -00

334C -3A Primary Servo surf ace s 522-2857-001

3341)-2-33D Trim Tab Servo Drives aircraft trim 522 -3466-00

334D-2-33F Trim Tab Servo system 522-4865-00

345A -4B Sensing Unit Provides pitch and roll r a t e 522-3851-000

signals

351B-3 Servo Mount Houses 334C-3( ) 522-1226-00

351B-3A Servo Mount Houses 334C-3( ) 522-2228-00
351B-3B Servo Mount Houses 334C-3( ) 522-3389-00
351B-3C Servo Mount Houses 334C-3( ) 522 -3390 -00
351B-3E Servo Mount Houses 334C-3( ) 552-5027-001

390R-5B Hard Mount Holds 161A-1A 522 -3744-00

May 1/67 Equipment Supplied (Sheet 1 of 3) 22 -03-00

Figure 2 Page 1
 COLLINS
MAINTEIVANCE
w MANUAL

COLLINS PART
EQUIPMENT DESCRIPTION
NUMBER

562C-4 Autopilot Amplifier Generates command signals 522 -2852-001

590A -3E Altitude Controller Provides altitude e r r o r signals 522 -47 98 -001

590B-2 Airspeed Sensor Provides gain change 270-2196-010

infor mation

614E-2F Pedestal Controller Provides operating controls for 522-3637-002

614E-2G Pedestal Controller Flight Control System 52 2 -401 7 -002
614E -2G1 Pedestal Controller 52 2 -4903 -001

7 9OC -1 Shockmount Holds 59OA-3E 5 22 -3251 -00

790M-1 Shockmount Dual mount for 562C-4 and 522-3682-00

790M-1A Hard Mount 562A-5G 522-3683-00

FD-108

329B-7A Flight Director Provides roll and pitch visual 522-3206-006

Indicator display

331A-6A Course Indicator Provides course and heading 522-2782-035

visual display

344C - l D Instrument P r o c e s s e s steering commands 522-3120-005

Amplifier for indicators

390D-6A Shockmount Holds 344C-lD 522-3746-001

562A-5G Flight Computer Computes steering commands 522 -32 07 -003

FD-108G

161E-1 Mode Coupler Provides switching 5 2 2 -4 2 19 -001

329B-7C Flight Director Provides roll and pitch 522 -3487 -004
Indicator - visual display

331A-6A Course Indicator Provides course and heading 522-2782-035

visual display

344C - l D Instrument P r o c e s s e s steering commands 522-31 20-005

Amplifier for indicators (Option 1)

344C -1F Instrument P r o c e s s e s steering commands 522-3226-001

Amplifier for indicators (Option 2)

22-03-00 Equipment Supplied (Sheet 2 of 3) May 1/67

Page 2 Figure 2
 Mh
COLLINS
MAINTENANCE
MANUAL

COLLINS PART
EQUIPMENT DESCRIPTION
NUMBER

390D-6A Shockmount Holds 344C-lD (Option 1) 522-3746-001

5 62A -5G Flight Computer Computes steering commands 522-3207 -003

8905-2 Shockmount Holds 344C-1F (Option 2) 772 -5129-001

FD-109G

161E-1 Mode Coupler Provides switching 522-4219-001

329B-8G Flight Director Provides roll and pitch visual 522-4529-001

Indicator display

331A-6A Course Indicator Provides course and heading 522-2782-035

d i sp1ay

344C -1F Instrument P r o c e s s e s steering commands 522-3226-001

Amplifier

562A-5G Flight Computer Computes steering Cornmand s 522-3207-003

8905-2 Shockmount Holds 344C -1F 772 -51 29 -001

89OP-1 Shockmount Holds 161E-1 772-51 27-001

Equipment Supplied (Sheet 3 of 3)

Figure 2

2. PURPOSE OF EQUIPMENT.

The Flight Control System provides commands to automatically maneuver the aircraft
during flight and during approach to runways equipped with all-weather instrument land-
ing systems (ILS), in response to various data inputs. Visual displays are also provided
for use in'monitoring the AP-103F when the system is engaged or for manually control-
ling the aircraft when the system is disengaged.

Figure 3 is a list of associated equipment that provide data inputs to the Flight Control
System.

Nov 1/68 22-03-00

Page 3
 a
C 0LLIN S
MAINTENASCE
w M-4KUAL

COLLINS PART
EQUIPMENT DE SCRIPTION FUNCTION
NO.

Navigation receiver , 522 -2450-000 Navigation receiver Provides VOR and ILS
51RV-1, o r deviation data
equivalent

Compass system, 522-1421-000 Magnetic compass Provides magnetic

MC-102 or heading data
equivalent

Vertical reference , 522-3985-000 Gyro horizon Provides pitch and

332D-11, o r roll data
equivalent

Radio altimeter , (Optional) Radio altitude Provides altitude trip

AL-101, or point data
e quiv ale nt

Marker beacon r e - 522-2996-000 Marker beacon Middle marker trip

ceiver, 512-4, or data
equivalent

DME receiver , 522-2702-000 Airborne distance Digital distance data

860E -2, o r measuring
equivalent e quip ment

Recommended Associated Equipment

Figure 3

3. EQUIPMENT SPECIFICATIONS.

The Flight Control System specifications a r e listed in figure 4.

NOTE: Specifications provided in figure 4 a r e the minimum requirements for the

equipment when operated as a Flight Control System and do not reflect the
performance capabilities of the individual equipment units. To determine
unit specifications for the characteristics listed in figure 4,refer to the
applicable equipment overhaul manual.

22-03-00 May 1/67

Page 4
 COLLINS
MCIAISTESASCE
MAlUUAL

CHARACTERISTIC SPECIFICATION

TSO compliance Conforms to FAA TSO C52a; meets applicable portions

of C ~ CC3a,
, C ~ Cand
, C9c

Power requirements 115 volts, 400 H z , single-phase

(phase must be same a s for gyro and compass
outputs)
28 volts dc
5 volts, 400 Hz , single-phase , o r
5 volts dc (for lighting)

System weight

AP -103F/FD -108 95.3 pounds

AP-lO3F/FD-l08G 1 0 1 pounds
AP-103F/FD-l09G 103.8 pounds

Operating temperature range -22 to +131 " F (-30 to +55 "C)

Stor age temperature range -85 to +158 "F (-65 to +70 "c)
Humidity range 0- to 95-percent relative humidity at +89.6 "F (+32 "C)

Maximum altitude -1000 to +40,000 feet

Signal inputs

Radio deviation signal A reversible dc signal originating in the navigation

receiver. Signal amplitude is proportional to the
angular displacement of the aircraft from the se-
lected VOR or localizer course.

Heading e r r o r signal A 400-Hz signal from the heading e r r o r synchro

control transformer in the course indicator;
generated by adjusting the HDG knob.

Course datum signal A 400-Hz signal from the course datum synchro
control transformer in the course indicator; generated
by adjusting the COURSE knob.

Bank attitude signal A reversible-phase 400-Hz signal proportional to

the bank angle of the aircraft. Signal originates i n
the vertical reference.

System Specifications (Sheet 1 of 3)

Figure 4

May 1/67 22-03-00

Page 5
 CHARACTERISTIC
-
a
COLLINS
MAINTENANCE
MANUAL

~~~

SPECIFICATION
~ -

Pitch attitude signal A reversible-phase 400-Hz signal proportional to the

pitch angle of the aircraft. Signal originates in the
vertical reference. (This signal is also applied to the
flight computer manual pitch command input circuit
a s the pitch command signal after first being routed
through the flight director indicator and the mode
coupler .)

Altitude e r r o r signal A 400-Hz signal proportional to the change in aircraft

altitude from a reference altitude. Signal is furnished
by the altitude controller.

Glideslope signal A reversible dc signal from the navigation receiver,

proportional to the angular displacement of the a i r -
craft from a selected glideslope course.

Autopilot manual pitch A reversible 400-Hz signal originating in the pedestal

command signal controller; generated by rotation of the pitch control.

Yaw r a t e signal A reversible-phase ac signal produced by the yaw r a t e

gyro. The signal is proportional to the yaw r a t e of
the aircraft.

Roll r a t e signal A reversible-phase ac signal from the roll r a t e gyro

in the sensing unit. The signal is proportional to the
roll r a t e of the aircraft.

Pitch r a t e signal A reversible-phase ac signal from the pitch r a t e

gyro in the sensing unit. The signal is proportional
to the pitch r a t e of the aircraft.

Compass signal A 400-Hz, standard 3-wire signal derived from the

aircraft compass system.

Radio altitude signal A reversible dc signal originating in the radio alti-

meter. Signal amplitude is proportional to the radio
altitude of the aircraft from 0 to 200 feet.

Distance display signal Three 400-Hz signals from the DME receiver repre-
senting distance in nautical miles to the radio
facility. One signal for each of units, tens, and
hundreds of miles.

System Specifications (Sheet 2 of 3)

Figure 4

22-03-00 . May 1/67

Page 6
I CHARACTERISTICS

Signal outputs
-
COLLINS
MAINTENANCE
MAKUAL

SPECIFICATION

V-bar steering command The V-bar roll and vertical steering command signals
outputs a r e reversible dc signals that provide magnitude and
direction of required flight attitude changes a s presen-
ted on the flight director indicator.
Servo outputs The aileron, rudder, and elevator servo signals are
reversible dc signals applied to the primary servos
and to the t r i m coupler o r trim tab servo. Since the
control fields of the elevator primary servo, the
armature of the elevator t r i m servo, or the t r i m
coupler a r e paralleled, the same elevator control
signal drives both units.
Each servo amplifier is capable of providing the neces-
s a r y power to the respective servo to obtain the
required horsepower output.

Pitch integrator signal The pitch integrator signal is a reversible-phase ,

400-Hz signal from the servo amplifier to the pedes-
tal controller.

System Specifications (Sheet 3 of 3)

Figure 4

4. EQUIPMENT DESCRIPTION.

A. AP-103F Automatic Flight Control System.

121A-2 Emergency Disconnect. (See figure 5 . )

The 121A-2 Emergency Disconnect is a panel-mounted switch that removes

power from the AP-103F in the event of an emergency (operational failure).
-The A / P EMERGENCY DISCONNECT switch has two positions. In the EN-
GAGE position, the switch permits engaging the AP-103F from the pedestal
controller. The DISENGAGE position, electrically disconnects power from the
AP-103F engage circuit and the servo motors.

332G-2 Rate Gyro.

The 332G-2 Rate Gyro supplies yaw r a t e signals for damping in the rudder axis
and for complementing the aileron channel signals. Signals a r e proportional
to the r a t e of rotation about the input axis perpendicular to the gyro base.
-

May 1/67 22 -03 -00

Page 7
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TPO 5 4 5 9 . 0 I 7

121A-2 Emergency Disconnect

Figure 5

(3) 334C-3( ) Primary Servo.

Three 334C-3( ) Primary Servos a r e used in the AP-103F. The aileron, rudder,
and elevator control surfaces a r e each positioned by a 334C-3( ) P r i m a r y Servo.
The 334C-3( ) contains a direct-drive motor-generator that turns a capstan
through a torque-limiting clutch and an electric engage clutch. The engage clutch
couples the input clutch plate to the output clutch plate and output shaft when the
servo is engaged. The output shaft is coupled through a servo mount to the air-
craft control system. An adjustable torque-limiting clutch controls maximum
torque output and permits the servo to be overpowered. The 334C-3( ) contains
a position synchro that provides feedback information to the servo system. The
334C-3( ) is shipped in a lightweight transit case. The transit case can be used
to protect the 334C-3( ) from damage when it is removed from the servo mount.

(4) 334D-2:33( ) Trim Tab Servo or 161A-1A Trim Coupler.

The 334D-2-33( ) T r i m Tab Servo is used in aircraft that have mechanically

driven t r i m systems, while the 161A-1A Trim Coupler is used in aircraft that
have electrical trim systems.

(a) 334D-2-33( ) T r i m Tab Servo.

To meet different aircraft installation requirements, either a 334D-2-33D,

334D-2-33E, o r 334D-2-33F T r i m Tab Servo may be used with the AP-103F.
Differences in the trim tab servos a r e in the different sprocket diameters,
the chain types, and in the gear ratios that are used (refer to overhaul manual).

22-03 -00 May 1/67

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The 334D-2-33( ) is a direct drive servo that controls the position of the
aircraft elevator trim tab. The servo is engaged when a magnetic clutch
couples the output to the drive motor. A dry disc friction clutch (or backup
clutch) is located between the magnetic clutch and the sprocket. The servo
may be overpowered through the magnetic clutch or through the backup clutch.
The 334D-2-33( ) is connected to the control system with a chain drive or
cable.

(b) 161A-1A Trim Coupler.

The 1 6 1 A - 1 A Trim Coupler actuates the aircraft electrical t r i m system. The

161A-1A senses elevator servo torque and then commands trim to reduce
the torque. The 161A-1A outputs pulse the trim-up and trim-down inputs of
the aircraft t r i m system. The maximum t r i m r a t e is limited. A trim failure
monitor output is provided to light a warning lamp when the 1 6 1 A - l A is not
functioning properly.

(5) 345A-4B Sensing Unit.

The 345A-4B Sensing Unit contains a pair of r a t e gyros to provide r a t e informa-

tion in the pitch and roll axes to the AP-103F. Signals proportional to aircraft
pitch and roll r a t e s a r e routed from pickoff potentiometers in the 345A-4B to the
AP-103F autopilot amplifier.

(6) 351B-3( ) Servo Mount.

351B-3( ) Servo Mounts are used with each of the 334C-3( ) P r i m a r y Servos in
the AP-103F. The mounts a r e bolted directly to the a i r f r a m e , and the capstans
o r lever a r m s a r e connected to the aircraft control system.

(7) 390R-5B Hard Mount.

The 390R-5B Hard Mount, used to mount the 161A-1A Trim Coupler, provides
mating connectors and an extractor mechanism that facilitates removal of the
161A-1 A .

(8) 562C-4 Autopilot Amplifier.

The 562C -4 Autopilot Amplifier contains three main circuit channels: aileron,
elevator, and rudder. In the aileron and elevator channels, the 562C-4 receives
processed command signals from the flight computer, r a t e information from the
rate gyros, and command signals from the pedestal controller. The elevator
channel also receives information from the altitude controller. Tkie signals are
mixed in the 562C-4, and a command signal is generated that is applied to the
appropriate primary servo. The command signal in the aileron channel is r a t e
limited to prevent transient commands from making course changes. In the
rudder channel, the 562C-4 receives r a t e information from the rate gyro and a
coordination signal from the aileron channel to provide yaw damping and turn
coordination.

May 1/67 22 -03-00

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(9) 590A-3E Altitude Controller.

The 590A-3E Altitude Controller provides accurate altitude e r r o r information to

the Flight Control System. The 590A-3E contains a precision altitude (barome-
t r i c ) sensor and associated null-seeking servo loop to drive the sensor pickoff to
a null position. Altitude e r r o r signals result from disabling the servo loop. Ad-
justable switch contacts provide AP-103F system gain changes (factory set to
18,000 feet), and may provide reduced e r r o r signals above the switching,point
when properly strapped,

(10) 590B-2 Airspeed Sensor.

The 590B-2 Airspeed Sensor signal to the autopilot amplifier provides continuous
gain changing as a function of indicated airspeed. The 590B-2 utilizes the pitot
and static air systems to drive a sensor. The sensor in turn drives the a r m s of
a pair of precision potentiometers. Potentiometer a r m position is a function of
air speed.
(11)614E-2F Pedestal Controller and 614E-2G o r 614E-2G1 Pedestal Controller with
327D-1W T r i m Indicator. (See figure 6.)

The pedestal controller is the control center for the Flight Control System. The
pedestal controller provides power and mode switching control and manual
maneuvering in some operating modes. The following controls (figure 7) are
located on the front panel of the pedestal controller:

(a) A.P. POWER toggle switch applies electrical power to the 562C-4 Autopilot
Amplifier and to the engage circuits.

(b) The mode selector is a 4-position rotary switch that is used to select the
desired operating mode for the AP-103F and/or the FD-108/FD-l08G/
FD-109G.

-
1. In GYRO position, when the AP-103F is engaged, the aircraft can be
maneuvered with the TURN knob. When the TURN knob is in detent, the
aircraft maintains a heading. The flight director indicator indicates
basic attitudes, with the V-bar command indicator biased from view,
when the system is engaged o r disengaged.

-
2. In HEADING position, the Flight Control System turns to, and holds, a
-heading selected with the HDG knob on the course indicator.

-
3. In NAV/LOC position, the Flight Control System holds the heading s e -
lected with the HDG knob on the course indicator until a computed cap-
ture point is reached. A t this point, the Flight Control System turns the
aircraft and begins tracking the VOR o r ILS course. Automatic c r o s s -
wind correction is provided as required.

- In APPR mode (ILS mode with 614E-2G1), the Flight Control System cap-
4.
tures the localizer in the same way as for VOR. When the glideslope is
intercepted, automatic glideslope capture occurs: glideslope gain is re-
duced at the middle marker and the glideslope extension phase begins.

22-03-00 May 1/67

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COLLINS
MAINTENAR’CE

614E-2F and 614E-2G( ) Pedestal Controller

Figure 6 -

May 1/67 22-0 3 -00

Page 11
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CONTRO L/INDICATOR FUNCTION

@) DISENGAGE indicator

Indicates that the automatic flight control system is dis-

engaged and the A.P. POWER switch is on.
DISENGAGE

Pitch control

7 Provides means of changing pitch attitude of aircraft wher

the automatic flight control system is engaged. Rotating
control toward U P will r a i s e the nose of the aircraft and

i
UP
toward DN will lower the nose of the aircraft. Altitude
hold will automatically go to off if pitch control is moved.

HEADING NAV/LOC
Mode selector

Provides means of selecting the automatic flight control

system and integrated flight system modes of operation.
Modes include GYRO (stabilization), HEADING (capture
and hold), NAV/LOC (intercept and track), and APPR
GyR@pR
(glide-path intercept and track).

A. P. POWER
A.P. POWER switch

Applies electrical power to the automatic flight control

system.

ENGAGE control

@ ENGAGE
Engages the automatic flight control system if the A.P.
POWER switch is on, TURN control (knob) is in detent,
and the mode selector is set to GYRO or HEADING.

ITURN , TURN control (knob)

Commands a smooth-coordinated turn if the automatic

flight control system is operating in GYRO mode. A i r - .
craft will maintain heading when control is returned to
center position.

22-03-00 Pedestal Controller Control/Indicator Functions (Sheet 1 of 2) May 1/67

Page 1 2 Figure 7
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MANUAL

CONTRO L/INDICA TOR FUNCTION

ALTITUDE switch

61
ALT ITU DE

Commands the automatic flight control system to hold

the aircraft at the barometic altitude when the switch is
set to on and the automatic flight control system is
engaged. In APPR (ILS) mode, switch will automatically
go to off when glide path is captured. Also if pitch con-
trol is moved o r the automatic flight control system is
engaged or disengaged , the switch will automatically
return to off. Provides altitude hold commands to inte-
grated flight system if automatic flight control system is
disengaged.

Trim indicators

Provide a visual indication of the force exerted by the

L
automatic flight control system servos on each control
surface: RUD(rudder) , AIL(aileron), and EL(e1evator) I

Pedestal Controller Control/Indicator Functions (Sheet 2 of 2)

Figure 7

The ALTITUDE switch is a solenoid-held microswitch that applies altitude

hold mode voltage to the autopilot amplifier , altitude controller , flight
computer, and mode coupler. When the ALTITUDE switch is turned to ON,
the altitude controller provides an e r r o r signal if the aircraft deviates from
the selected altitude. The e r r o r signal is proportional to the amount of de-
viation and is used to generate and apply commands to thk aircraft control
system to compensate for the deviation. A steering command is also pre-
sented by the V-bar command indicator in the flight director indicator.

The pitch control,knobs provide manual control of the aircraft pitch attitude
in GYRO, HEADING, and NAV/LOC modes and in APPR mode before GS
capture. After GS capture, o r when the automatic flight control system is
disengaged, the pitch control knobs a r e synchronized by the pitch control
motor to the aircraft pitch attitude.

The TURN knob has a center detent position that is interlocked with the en-
gage circuits, so the automatic flight control system cannot be engaged
unless the TURN knob is in detent. In GYRO mode, the TURN knob commands
coordinated turns in the direction of control knob rotation. When the TURN
knob is returned to detent, the aircraft rolls out and holds the heading that
was reached at the point of returning the control knob to detent.

May 1/67 22-03-00

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The DISENGAGE indicator is an amber-colored lamp that lights when the

automatic flight control system is disengaged and the A.P. POWER switch
is set to ON.

When the pushbutton ENGAGE switch is pressed, the automatic flight

control system is engaged only if the A.P. POWER switch is set to ON, the
TURN knob is in detent, and the mode selector switch is set to GYRO o r
HEADING.

RUD, AIL, and EL t r i m indicators a r e located at the top of the 614E-2F

Pedestal Controller. The t r i m indicators provide a visual display of the
force being applied to the aircraft control surface by the primary servos.

The 614E-2G and 614E-2G1 Pedestal Controllers do not contain trim indi-
cators. Instead, a 327D-1W Trim Indicator is used with these pedestal
controllers to provide similar display (other panel t r i m indicators may be
used if desired).

7 9OC -1 Shockmount.

The 79OC-1 Shockmount provides a cushioned mounting base for the 590A-3E
Altitude Controller. The 79OC-1 contains mating connectors and an extractor
mechanism that facilitates removal of the 590A-3E.

790M-1 Shockmount o r 790M-1A Hard Mount.

The 790M-1 Shockmount provides a cushioned, dual mounting base for the 562C-4
Autopilot Amplifier and the 562A-5G Flight Computer. The 790M-1 contains
mating connectors and an extractor mechanism. The 790M-1A Hard Mount is
identical to the 790M-1 Shockmount, except that raised hard mounts replace the
shockmount cushioned isolators .

NOTE: The 790M-1A Hard Moun€ should not be used except in specified vibra-
tion a r e a s o r on shelves which a r e shockmounted.

B. FD-108, FD-l08G, and FD-109G Integrated Flight Systems.

161E-1 Mode Coupler (FD-108G and FD-109G only).

The 161E-1 Mode Coupler contains various relays and solid-state switches to
provide a pitch synchronizer, back-course and go-around switching, annunciator
switching, VOR/LOC self-test disable, and transient suppression. Electrical
connections a r e made to two electrical connectors at the r e a r of the mode
coupler.

329B-7A Flight Director Indicator (FD-108 only),

The 329B-7A Flight Director Indicator shown in figure 8 is the basic attitude and
command display for the FD-108. The instrument consists of servo-driven at-
titude and command displays and meter movements that control glideslope and
localizer deviation displays. Other meter movements control the glideslope
(GS) , GYRO, COMPUTER, and localizer warning flags. A pitch command (PITCH

22-03-00 May 1/67

Page 1 4
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COLLINS
MAINTEKANCE

TPO-5431-012

329B-7A Flight Director Indicator

Figure 8

CMD) control can be adjusted to select the desired pitch attitude for climb or
descent, and a mode selector switch permits selection of operating mode. (The
mode selector is covered and cannot be used in the AP-103F/FD-108. Mode
selections a r e made with the mode selector switch on the pedestal controller.)
Figure 1 0 illustrates and describes the controls and indicators and their functions
for the 329B-7A.

The flight director indicator is mounted on the instrument panel and can be re-
moved as a single unit for servicing. The flight director indicator is housed in
a dustproof nonmagnetic case. A l l electrical connections to the flight director
indicator a r e made through two connectors at the r e a r of the case.

(3) 329B-7C Flight Director Indicator (FD-108G Only),

The 329B-7C Flight Director Indicator shown in figure 9 is the basic attitude and
command display for the FD-108G. The instrument consists of servo-driven
attitude and command displays and meter movementsfor glideslope, localizer,

May 1/67 22 -03 -00

Page 15
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w
and radio altitude displays. Other meter movements control the GYRO, COM-
PUTER, GS, RAD ALT, and localizer warning flags. Figure 1 0 illustrates and
describes the function of each control/indicator for the 329B-7C.

The flight director indicator is mounted on the instrument panel and can be r e -
moved a s a single unit for servicing. The flight director indicator is contained
in a nonpressurized dustproof can, and all electrical connections a r e made
through two connections at the r e a r of the case.

UNDER PLATE

TPO- 4552'012

329B-7C Flight Director Indicator

Figure 9

22-03-00 May 1/67

Page 1 6
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COLLINS
MAINTENANCE
MANUAL

CONTROL/INDICA TOR FUN CT ION

r - V-bar command indicator

Displays combined and computed pitch and bank com-

mands to capture selected heading or radio aid and to
maintain de sired altitude .

Aircraft symbol

Fixed reference for attitude and command information.

Bank pointer and scale (FD-108 only)

Displays bank attitude of aircraft. Marks a r e at 1 0 , 20,

30, 45, and 60 degrees. Operational throughout 360
degrees.

Bank pointer and scale (FD-108G only)

Displays bank attitude of aircraft. M a k r s a r e at 1 0 ,

20, 30, 45, and 60 degrees. Operational throughout
360 degrees.

Attitude tape
90 *UP
-70-UP- Marks indicate pitch attitude to h90 degrees. Display
turns with bank pointer and scale to indicate bank
-5O-W- attitude.
I
- -30-UP- -
-
-
15-15

Glideslope scale and pointer

Displays aircraft deviation from the glideslope beam

center. Pointer biased out of view at top end of scale
when not in use.

329B-7 ( ) Flight Director Indicator Control/Indicator Functions (Sheet 1 of 3)

May 1/67 Figure 1 0 22 -03 -00
Page 1 7
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COLLINS
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CONTROL/INDICATOR FU NC TION

Localizer deviation pointer and scale

Displays lateral deviation from runway localizer course.

Radio altitude pointer and scale (FD-108G only)

Displays 0- to 200-foot radio altitude. Pointer biased

out of view at bottom end of scale when not in use.

Glide slope (GS) warning flag

A red flag indicating a malfunction of the glideslope

receiver o r reception of an unreliable signal.

GYRO warning flag

A r e d flag indicating a failure in the vertical reference

o r the attitude display.
COMPUTER warning flag

A red flag indicating a failure in the flight computer o r

command display.

Radio altitude (RAD ALT) warning flag (FD-108G only)

A red flag indicating a failure in the radio altimeter.

Localizer warning flag

A plain black flag covering the localizer display in the

event of failure of the navigation receiver or reception
of an unreliable signal.

Inclinometer (slip indicator)

A weighted ball in a liquid-filled glass tube monitoring

slip o r skid in turns.

329B-7( ) Flight Director Indicator Control/Indicator Functions (Sheet 2 of 3)

Figure 1 0
22-03-00 May 1/67
Page 1 8
 CONTROL/INDICATOR
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COLLINS
MAINTEKANCE

FUNCTION

Pitch command control knob (FD-108 only)

Provides manual selection of +15 degrees to -5 degrees

of vertical adjustment of the V-bar command indicator.

Mode selector control (FD-108 only)

Selects operating mode of integrated flight system. (Not

used in AP-103F/FD-108. Covered with a knob cover.)

329B-7( ) Flight Director Indicator Control/Indicator Functions (Sheet 3 of 3)

Figure 1 0

(4) 329B-8G Flight Director Indicator (FD-109G Only).

The 329B-8G Flight Director Indicator shown in figure 11 is the basic attitude
and command display for the FD-109G. The instrument consists of servo-
driven attitude, command, and runway localizer and radio altitude displays and
a meter movement f o r glideslope display. The warning flags a r e also controlled
by meter movements. Figure 1 2 illustrates and describes the controls and
indicators and their functions for the 329B-8G.

The flight director indicator is mounted on the instrument panel and can be r e -
moved a s a single unit for servicing. The flight director indicator is protected
by a removable aluminum alloy c a s e . A l l electrical connections a r e made through
three connectors a t the r e a r of the case.

I *\ /'
i
I \ il I

TPO-3614-012

May 1/67 329B- 8G Flight Director Indicator 22- 03 - 00

Figure 11 Page 19
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COLLINS
MAIXTEKANCE
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CONTROL/INDICATOR FUNCTION

V-Bar command indicator

-
e- Displays computed steering commands to obtain and
hold desired flight path.
Aircraft symbol
The fixed reference for attitude and command
information.

Bank pointer and scale

Displays bank attitude of aircraft. Marks are at 10, 20,

30, 45, and 60 degrees and are operational throughout
360 degrees.

Attitude tape

Marks indicate pitch attitude to h90 degrees. Display

turns with bank pointer and scale to show bank attitude.
50 - U P -

30-UP-

50 - DOWN -
70 -DOWN

Glideslope scale and pointer

- Displays aircraft deviation from the glideslope beam
center. Dots indicate half- and full-scale deflection
above o r below the beam. Glideslope pointer may be
biased out of view at top end of scale.
Runway-altitude symbol and scale
Displays aircraft deviation from the localizer beam
center and 0- to 200-foot radio altimeter altitude.
Go-around (GA) lamp
Lights to show the system is in go-around mode.

329B-8G Flight Director Indicator Control/Indicator Functions (Sheet 1 of 3)

22-03-00 Figure 12 May 1/67
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CONTROL/INDICATOR FUNCTION

Se If -te st switch

The PRESS TO TEST button, when pressed, activates

circuits to display 10-degree pitch-up and 20-degree
bank right. It tests attitude and command display s y s -
t e m s and GYRO flag circuits.

Glideslope (GS) flag

Indicates a malfunction of the glideslope receiver o r an

unreliable glideslope signal to warn that glideslope in-
formation is unusable.

Inclinometer

Monitors slip o r skid in turns.

GYRO flag

Indicates failure of the vertical refer nce and/ r the

attitude display servo system,

Localizer (RUNWAY) flag

Indicates a malfunction of the navigation receiver, an

unreliable radio altimeter signal, o r a failure in the
localizer display.

Computer flag

Indicates failure of the flight computer and command

display.

SPEED flag

Indicates a malfunction of the speed computer o r speed

signal (masked off).

Speed command scale and pointer

0 Displays speed information from speed system (masked

I off).
L!OW

329B-8G Flight Director Indicator Control/Indicator Functions (Sheet 2 of 3)

May 1/67 Figure 1 2 22-03-00
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CONTROL/INDICATOR FUNCTION

Minimum decision altitude (MDA) lamp

Lights when the preset altitude is reached; at which time

the land or go-around decision must be made.

Rate -of -turn deviation

Bar-type pointer at the bottom of the instrument dis-

plays turn r a t e information (masked off).

Rate -of -turn flag

Partially obscures the rate-of-turn pointer and scale in

case of failure of the rate-of-turn signal (masked off).

329B-8G Flight Director Indicator Control/Indicator Functions (Sheet 3 of 3)

Figure 1 2

(5) 331A-6A Course Indicator.

The 331A-6A Course Indicator, shown in figure 13, is the course andheading display
for the Flight Control System. The course indicator displaysposition and heading of
the aircraft with respect to the compass and to the selected heading and course.
Digital readouts a r e provided for the selected course and DME distance. The
glideslope pointer provides the same information a s the glideslope display on the
flight director indicator. The GS flag obscures the glideslope display whenever
glideslope information is unreliable. Both the GS flag and pointer may be biased

22-03-00 331A-6A Course Indicator May 1/67

Page 22 Figure 1 3
 COLLINS
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w MANUAL

off scale when not in use. Additional warning flags monitor the VOR/localizer
signal and operation of the compass and compass card servo systems. Figure 14
shows and describes the function of each control/indicator on the course indicator.
The course indicator is housed in a standard ATR-4 case per ARINC Specifica-
tion No. 408 and is integrally lighted.

CONTROL/INDICATOR FUNCTION

Glideslope pointer ,and scale

. A triangular pointer at the left side of the instrument

face displays aircraft deviation from the center of the
glideslope beam. Pointer deflection above the center
.. reference mark indicates that the glideslope beam is
above the aircraft. The two marks on either side of the
center mark indicate half- and full-scale deflection. The
glideslope pointer is driven by a linear dc meter
mechanism directly from the output of the glideslope
receiver. When not in use, the glideslope pointer may
be biased out of view at the top of the scale.

Digital distance display and shutter

An external DME transceiver may be used with the

@
MILES

course indicator. Distance to the ground station may

be measured by selecting the DME frequency of the
m
MILES

U
ground station and reading the slant range distance to
this station on the digital readout. When the DME r e -
ceiver output decreases below a fixed level, a shutter
obscures the distance display.

Warning flags

Three r e d flags warn of loss of usable compass signal,

glideslope signal, and VOR/localizer signal. The glide-
slope flag, labeled GS, also covers the glideslope pointer
and scale to prevent accidental acceptance of faulty
indications. It may be biased off scale, along with the
glideslope pointer, when not in use. All flags are
actuated by dc meter mechanisms.

To-from pointer

The to-from pointer indicates the direction to the VOR

station along the radial selected by the course control.
The to-from pointer is biased from view in the approach
mode.

331A-6A Course Indicator Control/Indicator Functions (Sheet 1 of 2)

May 1/67 Figure 1 4 22 -0 3 -00
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CONTRO L/INDICATOR F U N C T ION

Aircraft reference symbol

This symbol is mounted a t the center of the display and
I indicates the position of the aircraft with respect to the
selected course (lateral deviation b a r ) . When the a i r -
craft symbol is pointed toward the lateral deviation b a r ,
the actual aircraft is headed toward the selected course;
and when the deviation bar is aligned with the aircraft
symbol, the aircraft itself is on the course.

V Selected heading marker and knob

Rotating the HDG (heading) knob adjusts the heading
marker to the desired heading; the marker then rotates
with the compass card a s aircraft heading changes. The
difference between current and selected aircraft heading
@ is indicated by the displacement of the marker in rela-
tion to the lubber line.

Course arrow, selector knob, and digital display

im The desired omnirange radial o r localizer course is se-
f lected on the compass card by rotating the course arrow
with the COURSE knob. Once set, the course arrow will
rotate with the compass card a s aircraft heading changes.
The selected course also is displayed by a digital coun-
t e r in the upper right corner of the instrument face.

@ I

Lubber line and compass card

Driven by the aircraft compass system, the compass

card rotates a s the aircraft heading changes. Heading
i s indicated beneath the lubber line at the top center of
the instrument.

Lateral deviation b a r and scale

The lateral deviation bar represents the selected course
..0..

I and moves in a direction perpendicular to its length to

indicate deviation from the course. Deviation is in-
dicated by the deflection of the bar to the left or right
of center (the bar is centered when it is aligned with
the course arrow). The lateral deviation bar rotates
with the compass card a s the aircraftheading changes.

22-03-00 331A-6A Course Indicator Control/Indicator Functions (Sheet 2 of 2) May 1/67

Page 24 Figure 14
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MAINTENANCE

(6) 344C-1D Instrument Amplifier (FD-108 and Option 1 of FD-108G Only).

The 344C-lD Instrument Amplifier is packaged in a short 1/4 ATR case. The
344C-1D is constructed of modules: a converter module, a gyro flag ampli-
fier module, a command warning monitor module, and five servo-amplifier
modules,

Circuits include a pitch command converter channel and a roll command con-
v e r t e r channel to drive the servo motors that position the V-bar command
indicator in the flight director indicator. A pitch servo channel and a roll servo
channel drive the pitch attitude and roll attitude display servo motors in the
flight director indicator.

Warning monitor circuits operate the COMPUTER warning flag and the GYRO
warning flag meter mechanisms in the flight director indicator and the COM-
PASS warning flag meter mechanism in the course indicator.

(7) 344C-1F Instrument Amplifier (FD-109G and Option 2 of FD-108G Only).

The 344C-lF Instrument Amplifier is packaged in a short 1/4 ATR case. It

contains servo amplifier, converter, and monitor circuit boards.

The compass servo amplifier completes the heading servo loop to drive the
azimuth card servo motor in the course indicator.

The pitch and bank servo amplifiers drive the servo motors that position the
attitude display in the flight director indicator. The pitch command and roll
command servo amplifiers drive the servo motors that control the V-bar com-
mand indicator in the flight director indicator. The V-bar command indicator
is biased out of view when the 344C-1F is operating in the gyro mode. The
localizer and altitude servo amplifiers a r e not used in the AP-103F/FD-l08G.

The 344C-1F combines monitoring signals from external units with internal
monitoring of the servos, The internal monitors check the level of the e r r o r
signal in the servo loop. This detects low gain, amplifier failure, servo-
motor failure, gear-train failure, and synchro excitation failure. Monitor
circuits provide signals to warning flag meter mechanisms in the flight director
indicator and the course indicator.

(8) 344C-1G Instrument Amplifier (FD-109G.)

The 344C-lG Instrument Amplifier may be used as a direct replacement for o r in

lieu of the 344C -1F Instrument Amplifier in the FD-108G (using the 344C -1F
Instrument Amplifier) and FD-109G Integrated Flight Systems. The 344C - l G
will mount directly in the 8905-2 Shockmount without changing connector keying
o r aircraft interconnect. Operation of the 344C-1G Instrument Amplifier is
identical to that of the 344C-lG except for the addition of back localizer switching.

(9) 390D-6A Shockmount (FD-108 and Option 1 of FD-108G Only).

The 390D-6A Shockmount provides a cushioned mounting base for the 344C-1D
Instrument Amplifier. The 390D-6A contains mating connectors and an ex-
tractor mechanism that facilitates removal of the 344C-1D.
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I (10) 562A-5G Flight Computer.

The 562A-5G Flight Computer receives data from external sources , provides
command steering outputs to drive the V-bar command indicator servos in the
flight director indicator, and monitors the Integrated Flight System. The flight
computer consists of command channels , monitor channels, and power supply.

The flight computer monitors all applicable data sources , all computer power
sources, and the pitch and roll command servo systems. The flag circuits
require that the computer data source be self-monitoring. The self -monitor
logic from the data sources is processed in the computer and added to the com-
puter self-monitor; only the functions applicable to the selected mode are
monitored,

The flight computer has a self-contained power supply that operates from
separate 115-voltY400-Hz attitude and heading inputs. The dc voltage is
generated internally for mode selection switching.

(11)8905-2 Shockmount (FD-109G and Option 2 of FD-108G Only).

The 8905-2 Shockmount provides a cushioned mounting base for the 344C-lF
Instrument Amplifier. The 8905-2 contains mating connectors and an extractor
mechanism that facilitates removal of the 344C-1F.

I (12) 89OP-1 Shockmount (FD-108G and FD-109G Only).

The 89OP-1 Shockmount provides a cushioned mounting base for the 161E-1
Mode Coupler.

5. THEORY OF OPERATION.

A. General.

Theory of operation for AP-103F/FD-108, A P -1O3F/FD-108GY AP-103F/FD-l09G

Flight Control Systems is discussed in two major groups: automatic flight control
system theory of operation and integrated flight system theory of operation. Auto-
matic flight control system theory is a discussion of the theory of operation of the
AP-103F Automatic Flight Control System which is the autopilot system used in all
three of the flight control systems covered in this manual. Operation of the A P -
103F is the same in each of the three applications. Integrated flight system theory
explains the operation of the FD-108, FD-108GYand FD-109G Integrated Flight
Systems. These a r e the three systems that combine individually with the AP-103F
to provide the A P -103F/FD-108, A P -103F/FD-l08G, and A P -103F/FD -109G Flight
Control Systems.

B. Automatic Flight Gontrol System Theory of Operation. (See figures 15 and 16.)

(1) General.

The AP-103F Automatic Flight Control System operates in four modes as se-
lected by the mode selector switch on the pedestal controller.- Selection of the

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desired operating mode establishes logic for switching input data received from
sensors for processing by the flight computer and autopilot amplifier, The
processed data provides guidance commands that are applied to the aircraft
control system. Heading select , automatic radio beam capture, tracking, and
crosswind correction functions a r e processed by the flight computer to provide
a lateral guidance command signal to the autopilot amplifier. Heading hold and
manual turn functions a r e also available by using the manual TURN knob on the
pedestal controller. In the pitch modes, a computed glideslope command is
available to the autopilot amplifier from the flight computer. The autopilot
amplifier utilizes either the computed glideslope command, the altitude hold
e r r o r signal, o r the manual pitch signal from the pitch knobs on the pedestal
controller to produce the vertical guidance command. Operation of the AP-103F
is presented in two levels: simplified theory of operation, which is a study of
the system operating principles; and functional theory of operation, which exa-
mines system theory in more detail.

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(2) Simplified Theory of Operation.

Operating principles for the AP-103F (utilizing the flight computer a r e discussed
with an analysis of the four operating modes a s selected by the mode selector
switch: GYRO (gyro mode), HEADING (heading mode), NAV/LOC (navigation/
localizer mode), and APPR (approach mode).

(a) Gyro Mode.

With the pedestal controller mode selector switch set to GYRO and the
AP-103F Automatic Flight Control System engaged, the AP-103F operates
in the gyro mode. When the TURN control is rotated, the aircraft responds
by making a coordinated turn, and when the TURN control is returned to
detent, the aircraft rolls out and holds the heading that was reached at the
time the TURN control was centered. The TURN control output provides
input data to the turn control gain adjust circuits in the autopilot amplifier
where the lateral servo command is developed. When a change in aircraft
pitch attitude is desired, the pedestal controller pitch control is rotated in
the direction of the desired change. Rotating the pitch control toward DN
lowers the aircraft nose, and rotating the pitch control toward U P r a i s e s the
nose. Rotation of the pitch control provides pitch control command data
inputs to the autopilot amplifier where the data is summed with processed
pitch data from the flight computer to form the pitch servo command.

To hold the aircraft at a constant barometric altitude, the ALTITUDE switch

is set to ON. This provides an altitude e r r o r data input to the flight com-
puter and to the autopilot amplifier from the altitude controller.

(b) Heading Mode.

Switching the mode selector on the pedestal controller to HEADING with the
AP-103F engaged puts the AP-103F in the heading mode of operation.

Operation of the AP-103F is the same in heading mode a s in gyro mode,

except that heading information is generated by rotating the HDG knob on
the course indicator instead of the TURN control on the pedestal controller.
The heading e r r o r signal from the course indicator is applied to the heading
e r r o r input circuit in the flight computer where it is processed to form the
processed bank command. A bank data signal from the vertical reference is
also applied to the flight computer to form a processed bank data signal. The
processed bank command signal and the processed bank data signal a r e
routed separately to the autopilot amplifier. The two signals a r e mixed with
the roll r a t e signal from the sensing unit to form the bank servo command
that is applied to the primary servo.

Development of the pitch servo command in the heading mode is the same
a s in the gyro mode and includes altitude hold capability.

(e) Navigation/Localizer Mode (VOR Function).

To operate in the VOR function of the NAV/LOC mode, the mode selector
must first be set to GYRO or HEADING. Then the navigation receiver is

May 1/67 22-03-00

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 tuned to a VOR frequency, and the course indicator course arrow is set to
the desired radial by the COURSE knob. The course indicator HDG knob is
adjusted to select the desired intercept heading, an8 the mode selector is
switched to NAV/LOC.

The course datum signal from the course indicator, the radio deviation
signal from the navigation receiver, and the bank attitude signal from the
vertical reference a r e all applied a s inputs to a complementary filter in
the flight computer.

The complementary filter output is summed with the rate-limited radio

deviation signal and the result is summed with an amplified course datum
signal to form a processed bank command signal. The processed bank
command signal and the processed bank data signal a r e routed to the auto-
pilot amplifier where the bank servo command is developed in the same way
a s in the heading mode.

Altitude hold may be selected in this mode, and pitch operation is the same
a s in gyro and heading modes.

(d) Navigation/Localizer Mode (LOC Function).

Operation of the A P -103F in the localizer function of navigation/localizer

mode is the same as in the VOR function except that the navigation receiver
is tuned to a localizer frequency. The flight computer provides bank steer-
ing commands to capture and maintain the selected localizer course.
Generation of the bank and pitch servo commands in the LOC function is the
same a s in VOR function, except that signal gains and limits a r e automa-
tically set at different values to give optimum performance while flying the
localizer course.

(e) Approach Mode.

After the navigation receiver has been tuned to the localizer frequency and
the course indicator course arrow has been set to the localizer course,
setting the mode selector switch to APPR a r m s the flight computer for
automatic localizer capture. Lateral commands from the AP-1O3F to the
aircraft control surfaces a r e produced in the same way a s in the NAV/LOC
mode. A s the aircraft nears the glideslope, the course indicator and flight
director indicator glide slope pointers move into view.

Before glideslope capture, the AP-103F may be operated in altitude hold or

manual pitch functions. These functions a r e identical to pitch operation in
other modes.

A t glideslope capture, if the AP-103F has been operating in the altitude hold
function, the ALTITUDE switch automatically returns to off. The flight
computer mixes the glideslope signal with pitch attitude data from the v e r -
tical reference ar-i routes the combined signal to the autopilot amplifier a s
the ac pitch ste ring signal. The ac pitch steering signal is summed with
the pitch r a t e signal and the up-elevator signal to produce the pitch servo
command.

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(3) Functional Theory of Operation. (See figures 15 and 1 6 ) .

(a) General.

Functional theory of operation for the AP-103F is explained by tracing the

input data a s it is processed through each of the three guidance command
channels: pitch channel (figure 1 7 ) , roll channel (figure 18), and rudder
channel (figure 19). Flight control data from units of the AP-103F/FD-108,
AP-103F/FD-l08G, or AP-103F/FD-l09G Flight Control Systems, and
associated equipment, is processed by the flight computer and the autopilot
amplifier to provide guidance commands to primary servos connected to
the aircraft control surfaces. Mode switching voltages a r e produced in the
pedestal controller and in the flight computer. Gain adjustment strapping
in the equipment is performed with the equipment installed in the aircraft
and after the most desirable flight characteristics of the aircraft have been
determined by in-flight testing, In the block diagrams (figures 12, 1 8 , and
19) switching circuits a r e shown a s being operated by AND and OR circuits.
An AND circuit requires that all inputs must be present to produce an out-
put. An OR circuit requires only one input present to furnish an output.

(b) Pitch Channel. (See figure 12.)

The elevator channel of the autopilot amplifier provides pitch servo com-
mands to the elevator primary servo. This command is developed in the
pitch channel of the flight computer and the elevator channel of the auto-
pilot amplifier from input data from associated sensors. The pitch (ele-
vator) channel is operated in one of three functions: manual pitch, altitude
hold, and glideslope. Functional theory for the pitch channel includes an
explanation of each of these functions and a description of the up-elevator
signal.

-
1. Manual Pitch Function.

Pitch attitude data from the vertical reference is a phase-sensed a c

signal of nominally 200 millivolts per degree of aircraft pitch e r r o r .
The pitch attitude data is applied to the flight computer where the data
is adjusted by an analog adjust circuit to match the incoming signal to
the flight computer pitch attitude circuits. The adjusted signal is am-
plified and routed to the autopilot amplifier as processed pitch data.

When the AP-103F is engaged, and the pitch knobs on the pedestal con-
troller a r e rotated, a pitch knob command signal is applied to the auto-
pilot amplifier. The pitch knob command signal is summed with the
processed pitch data from the flight computer and then amplified. The
result is a signal equal to the difference between existing pitch attitude
and commanded pitch attitude. The difference signal is passed through a
quadrature rejection filter where components 90 degrees out of phase
with command power a r e removed. The filtered difference signal is
applied to a summation point at the input to a gain-controlled amplifier.

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The pitch rate signal from the sensing unit is applied to a pitch rate gain
adjust circuit in the autopilot amplifier. The signal is gain adjusted
to establish the degrees p e r second of pitch rate that are required to
command one degree of change in pitch attitude. The gain adjusted signal
is mixed with the gain-adjusted up-elevator signal, and the result is
summed with the difference signal output from the quadrature rejection
filter.

The combined signal is amplified by the gain-controlled amplifier, which

provides two outputs. One output is returned to the flight computer where
it is converted to de to provide the V-bar pitch steering command signal
to the instrument amplifier. The second amplifier output is applied to
the elevator gain adjust circuit as the pitch servo command signal. In
the elevator gain adjust circuit, installation strapping determines the
degree of pitch servo command required to produce one degree of elevator
primary servo-capstan rotation. The gain-adjusted signal is applied to
the input of a limiting amplifier to limit maximum amplitude of com-
mands. The resulting signal is passed through the reversing links to a
phase detector in the elevator servo amplifier. The phase detector
output is summed with rate and position feedback signals from the p r i -
mary servo. Since the signals are of opposite phase, they tend to cancel
each other, with the result being a signal that is applied to the differential
de amplifier. The output from the differential amplifier drives a motor
field winding in the primary servo depending upon the input signal phase.
A signal applied to one side of the amplifier provides bias to switch off the
other side, removing drive from one-half of the winding in the control
motor of the primary servo. As a result, rotation of the motor reposi-
tions the aircraft elevator control surface.

In aircraft with electrical t r i m systems, the pitch servo command is

also routed as trim-up o r trim-down signals to the t r i m coupler. The
de current input to the t r i m coupler is applied to a magnetic amplifier
and converted to a pulsing de voltage signal. The voltage signal is ap-
plied to a pulse-synchronizing network where it is converted to a s e r i e s
of positive-controlled square-wave pulses. The pulses pass through a
switch that gates' other switches open to receive pulses from the pulse
generator. The result is either a trim-up o r trim-down signal that is
applied to the aircraft elevator t r i m tabs.

In aircraft with mechanically driven t r i m systems, the pitch servo com-

mand is routed to a t r i m tab servo. In the t r i m tab servo, the pitch
-servo command drives a s e r v o d r i v e motor that repositions the aircraft
elevator t r i m tabs.

The pitch servo command output from the autopilot amplifier is also
routed to the elevator t r i m indicator. The t r i m indicator provides a
visual display of the degree of pitch steering force that is being applied
to the aircraft control surface.

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Altitude Hold Function.

MAINTENANCE
MANUAL

When the ALTITUDE switch on the pedestal controller is set to ON,

altitude hold is initiated. An altitude hold mode voltage from the pedestal
controller disables glideslope and manual pitch circuits in the flight
computer and autopilot amplifier. Altitude e r r o r signals from the altitude
controller are applied to the flight computer and to the autopilot amplifier.
When the AP-103F is disengaged, the altitude e r r o r signal is summed in
the flight computer with the pitch attitude input signal to provide the V-bar
pitch steering command that is routed to the instrument amplifier (refer
to paragraph 5.C.(3)(i)2.b.(4J. The pitch attitude signal is also routed to
the autopilot a m p l i f i e r a s processed pitch data.

When the AP-103F is engaged, an altitude e r r o r signal from the altitude

controller is selected by mode voltages for processing by the autopilot
amplifier. The altitude e r r o r signal is transformer coupled to the altitude
gain adjust network. Here the level of the incoming signal is adjusted to
establish the angle of pitch necessary to correct f o r each 100 feet of
altitude e r r o r . The altitude e r r o r signal is next fed to an amplifier, the
gain of which is decreased linearly as airspeed is increased from 100 to
500 knots. The altitude e r r o r signal is mixed with the processed pitch
data signal from the flight computer to produce a signal that is proportional
to the amount of pitch required to hold the aircraft at the selected altitude.
The altitude e r r o r signal is also combined with the pitch control motor
rate signal to control the speed of the pitch control motor in the pedestal
controller. An altitude integration gain adjust network controls the amount
of rate, and the signal is mixed with pitch knob command e r r o r data,
amplified, and returned to the pitch control servo in the pedestal con-
troller. The pitch control servo rotates the pitch control knobs to remove
any altitude standoff due to pitch attitude.

The pitch e r r o r signal is amplified, passed through asquadrature rejection

filter, and summed with the pitch rate signal from the pitch rate gyro and
the up-elevator signal from the aileron channel. The summed output is
the pitch servo command. Processing of the pitch servo command in the
altitude hold function is the same as in the manual pitch function.

-
3. Glideslope Function.

In the glideslope function, the flight computer uses glideslope deviation

data from the navigation receiver and pitch attitude data from the vertical
reference to compute the a c pitch steering signal that is routed to the
autopilot amplifier.

The glidesIope deviation data from the navigation receiver is a de signal

proportional to the vertical displacement of the aircraft from the glide-
slope beam center. The signal is applied to a chopper where it is con-
verted to ac. The a c signal is amplified and applied to the glideslope gain
change circuit where the gain is reduced in glideslope extension function.
The gain is reduced by adding resistance to the circuit through an elec-
tronic switch that is energized by a mode voltage. The signal is also
applied to the glideslope beam sensor which provides logic at glideslope

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capture. This logic is used to change the gain of various circuits. The
output from the glideslope gain change circuit is mixed with low-pass
filtered pitch attitude data, and the resulting signal is applied to the
pitch limiter. The pitch limiter adjusts the pitch signal to a limit that
has been predetermined as the maximum allowable pitch in the approach
mode. The output from the pitch limiter is routed to the autopilot
amplifier as the a c pitch steering signal.

The glideslope extension mode is initiated by the ac middle m a r k e r signal

from the middle m a r k e r receiver o r by the altitude extension override
signal from the radio altimeter. The signal is applied to the glideslope
gain change circuit to reduce the gain. The result is an ac pitch steering
signal with a small glideslope correction. All other circuit operation in
glideslope extension mode is identical to operation in glideslope mode.

In the autopilot amplifier, the ac pitch steering signal is applied to a

fader circuit that smooths out rough commands during the transition to
glideslope mode. The fader output is summed with the pitch rate signal
from the pitch rate gyro in the sensing unit and with the up-elevator signal
from the aileron channel. Further processing of the elevator servo com-
mand is the same as in the manual pitch function, except that the external
pitch steering signal is not routed back to the flight computer f o r pro-
cessing as the V-bar pitch steering command.

- Up-Elevator Signal.
4.

When the aircraft is making a turn, an up-elevator signal proportional

to the bank angle is required to prevent loss of altitude during the turn.
The up-elevator circuit demodulates the bank data signal from the aileron
channel, and a chopper converts the resulting dc signal into an a c signal
that is in phase with command power. A gain-change circuit reduces the
level of the signal as airspeed increases to 500 knots. The level of the
signal is also adjusted to compensate f o r the reduced lift that occurs
during the turn.

(c) Roll Channel. (See figure 18.)

The roll (aileron) channel provides lateral servo commands to the aileron
primary servo. Signals are fed to the roll channel of the flight computer and
the aileron channel of the autopilot amplifier from units of the Flight Control
System and associated equipment, In the flight computer, the signals are
selected and processed and then routed to the autopilot amplifier where they
are mixed with other signals to develop the aileron servo command. The
aileron servo command is applied to the aileron primary servo to reposition
the aircraft aileron control surface. Functional theory for the roll (aileron)
channel describes the development of aileron servo commands to provide
heading select, manual turn and heading hold, VOR and localizer automatic
capture and tracking, and crosswind correction.

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1. Heading Select. -
When operating in heading mode, the Flight Control System automatically
turns to, and maintains, a specific heading selected with the HDG knob
on the course indicator. In VOR/LOC and APPR modes, the heading is
maintained until capture of the desired radial.

Adjusting the HDG knob on the course indicator generates a heading e r r o r

signal that is applied to an input circuit in the flight computer. The head-
ing e r r o r signal is a phase-sensed a c signal of 300 millivolts nominal f o r
each degree of e r r o r in aircraft heading. The signal is analog adjusted
to match the incoming signal to the flight computer circuits. A quadrature
rejection filter removes signals that are 90 degrees out of phase with the
heading e r r o r signal. The heading e r r o r signal is summed with a yaw
rate (external bank command) signal from the autopilot amplifier, and
the combined signal is applied to a bank limiter that adjusts the level
of the signal to establish bank limits of from 2.5 to 37.5 degrees. The
limited signal is amplified and routed to the autopilot amplifier as the
processed bank command.

The processed bank data is produced from the bank attitude signal input
to the flight computer. The bank attitude signal is a phase-sensed ac
signal nominally 200 millivolts f o r each degree of bank e r r o r . The bank
attitude signal originates in the vertical reference, which is powered by
aircraft attitude power, and applied to flight computer circuits that are
referenced to heading power; therefore, the signal must be phase adjusted
by applying it to a phase converter where it is converted to heading phase,
The phase-adjusted signal is applied to an analog adjust circuit in which
installation strapping adjusts the incoming signal to 200 millivolts to
match flight computer circuits. The signal is amplified and applied to
the autopilot amplifier.

In the autopilot amplifier, if the AP-1O3F is engaged but not operating in

gyro mode, the processed bank command from the flight computer is
applied to a rate limiter. The rate limiter smooths out the signal and
prevents surges in aileron servo commands from reaching the aircraft
ailerons. The rate limiter output is summed with the processed bank
data from the flight computer and with the gain-adjusted roll rate signal
from the roll rate gyro in the sensing unit. Summing the processed bank
command with the processed bank data produces a difference signal that
is equivalent to the degree of bank required to bring the aircraft to the
desired altitude. Addition of the roll rate signal at this point establishes
the maneuvering rate and provides stabilization to bring the aircraft
smoothly to the desired bank attitude. The combination of the three sig-
nals produces the aileron servo command.

The aileron servo command is amplified by an amplifier that is gain

controlled by airspeed. The amplifier output provides the external roll
steering signal and the aileron servo command.

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If the Flight Control System is engaged but has nbt captured glideslope,
the external roll steering signal is routed to the flight computer to pro-
vide the V-bar roll steering command, which the flight computer supplies
to the instrument amplifier.

The amplified aileron servo command is passed through the aileron chan-
nel gain adjust circuit. Here the gain is adjusted to establish the amount
of aileron servo command required to produce one degree of primary
servo-capstan rotation. The aileron servo command is then applied to a
fader circuit where engage transients in the command are smoothed out.
When the AP-103F is disengaged, the fader circuit is an open switch,
preventing the passage of the aileron servo command. The fader output
is applied to a limiter amplifier where the aileron servo command is
limited to a predetermined maximum level to prevent excessive primary
servo-capstan travel. The limited output is routed through the reversing
links to the aileron servo amplifier. Signal processing in the aileron
servo amplifier is the same as in the elevator servo amplifier described
-
in paragraph 5.B.(3)(b)l.

-
2. Manual Turn and Heading Hold.

When operating the AP-103F in gyro mode, rotating the TURN knob on the
pedestal controller applies a turn control signal to the autopilot amplifier.
The turn control signal is an a c voltage with phase and amplitude deter-
mined by direction and degree of rotation of the TURN knob. The turn
control signal is applied to the turn knob gain adjust network, Resistor
strapping in the gain adjust network establishes the maximum bank angle
that can be commanded with the TURN knob. The gain-adjusted turn
control signal is summed with the yaw rate signal from the rate gyro.
The yaw rate signal is a reversible-phase a c signal with signal phase and
amplitude determined by direction and rate of yaw.

When the TURN knob is in detent position, no turn control signal is

received by the autopilot amplifier and the AP-103F operates in heading
hold. In heading hold, aircraft heading is maintained by comparing the
data from the aircraft magnetic compass with the position of the heading
synchronizer control transformer. The electronic switch in the heading
synchronizer is opened by mode voltages, and no feedback signal is
applied to the heading synchronizer motor generator. If aircraft heading
deviates from the heading established when the TURN knob was positioned
to detent, a heading e r r o r signal is developed in the heading synchronizer.
The heading synchronizer control transformer provides a heading e r r o r
signal output that is summed with the yaw rate signal in place of the turn
control signal.

Data from the a i r c r a f t magnetic compass, containing a deviation signal

caused by compass rotation to a commanded heading, is applied to the
heading synchronizer circuit in the autopilot amplifier. With the TURN
knob out of detent, feedback from the heading synchronizer amplifier is
passed through the closed electronic switch to the heading synchronizer
motor -generator. The heading synchronizer motor .rotates the heading

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synchronizer control transformer, tracking the compass data, and can-

celing the compass deviation signal so that no heading e r r o r signal is
developed.

The combined signal, a combination of either turn control and yaw rate o r
heading e r r o r and yaw rate signals, is applied to the rate limiter as the
aileron servo command signal. In the manual turn o r heading hold func-
tions, the aileron servo command is processed in the same way as in the
heading select function.

-
3. Automatic Beam Capture and Tracking.

When the AP-103F is operating in the VOR/localizer mode, the navigation

receiver is tuned to a VOR o r localizer frequency, and the AP-103F roll
servo command is developed to maneuver the aircraft to capture and track
the VOR o r localizer beam.

Switching the pedestal controller mode selector switch from HEADING to

NAV/LOC with no localizer voltage present puts the AP-103F in the NAV
mode, and the flight computer beam sensor is armed for NAV capture.
If a localizer voltage is present when the mode selector switch is moved
from HEADING to NAV/LOC, the AP-103F will operate in localizer mode,
and the flight computer beam sensor is armed for localizer capture.
AP-103F operation is the same in either mode, with the exception that
in localizer mode, the localizer mode voltage adjusts the radio rate
limiter and the complementary filter circuit parameters.

In the NAV and localizer modes, mode voltages in the flight computer
select the radio deviation signal, the course datum signal, and the bank
attitude signal to develop the processed bank command and processed
bank data signals for routing to the autopilot amplifier.

The radio deviation signal from the navigation receiver is a dc signal

proportional to the lateral displacement of the aircraft from the radio
beam. It is applied through contacts in the back-course relay in the mode
coupler to a chopper in the flight computer where it is converted to ac.
The a c signal is amplified and applied to a rate limiter, The rate limiter
reduces the signal after the beam sensor indicates VOR o r localizer cap-
ture and the system is tracking. The rate limited radio deviation signal
is used in three ways. It is applied to a quadrature rejection filter where
the t r i p level is adjusted to provide switching for beam capture; it is gain
adjusted and applied to the complementary filter input; and it is summed
with the complementary filter output.

The course datum signal from the course indicator is an ac signal pro-
portional to the difference between the selected course and the aircraft
magnetic heading. The course datum signal is routed through back-
course relay contacts in the mode coupler to the course datum input c i r -
cuit in the flight computer. The course datum input circuit consists of an
adjustable impedance matching network. The course datum signal voltage
is analog adjusted to match the millivolts-per-degree requirement of the
flight computer circuits. The analog-adjusted _signal is amplified and used

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three ways. It is routed through the overcone memory circuit to the

course-cut amplifier; it is applied to a rate limiter, together with the
radio deviation signal; and it is applied to a quadrature rejection filter.
The quadrature rejection filter output is a square wave that is in phase
with heading power. The square-wave signal is gain adjusted and applied
to the complementary filter; it is also summed with the course-cut
limiter output and applied to the bank limiter.

The bank attitude signal, previously discussed, is applied to the comple-

mentary filter input through a bank rate gain adjust circuit as well as to
the autopilot amplifier as processed bank data.

In the complementary filter, the radio deviation, course datum, and bank
attitude signals are rate gain adjusted, with the amounts of rate gain
determined by separate installation strapping f o r each of the signals.
Amount of rate gain is measured at the center frequency of the comple-
mentary filter output. Essentially, the complementary filter is an adjust-
able bandpass filter with the output used to provide smoothing to prevent
sudden rate changes in the command signal. The complementary filter
rate-of-change time constant is adjustable to provide selection of a rate-
of-change response to match the operating mode. The complementary
filter provides filtering of the high-frequency radio components that are
principally noise, while deriving rates from the low-frequency components
that contain usable information. The course datum and bank attitude sig-
nals compensate f o r the radio signal components that a r e removed. The
complementary filter passes the course datum signal permitting the air-
craft to take up any heading without standoff. The complementary filter
output signal approximates the rate at which the aircraft is approaching
the selected VOR o r localizer course.

The complementary filter output is combined with the rate-limited radio

deviation signal to stabilize the approach to the selected radio course and
to provide automatic crosswind correction. The combined signal is
amplified and applied to the radio command limiter where it is passed
without limiting in the NAV capture mode. The signal is then applied to
the course-cut amplifier. If the computer is not tracking in the NAV mode,
course datum is mixed with the radio deviation signal at the input to the
course-cut amplifier. The amplified signal is applied to the course-cut
limiter. The course-cut limiter limits the intercept angle when flying a
NAV capture course. The amount of limiting is adjusted by strapping.
When the computer is in NAV mode but not tracking, the course-cut
limit is reduced to permit a l a r g e r course-intercept angle. When the
computer starts tracking , the course -cut limiter reduces the intercept
angle to command a turn to the VOR radial. The output from the course-
cut limiter is summed with the course datum square-wave output from the
quadrature rejection filter. The combined signal is applied to the bank
limiter where the degree of bank command is limited to provide the
optimum bank angle f o r a specific aircraft type. The amount of bank
limit is determined by strapping. The signal is amplified and routed to
the autopilot amplifier as the processed bank command signal.

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Processing of the processed bank command signal and the processed bank
data in the autopilot amplifier to develop the aileron servo command is
the same f o r automatic beam capture and tracking as f o r heading select.

- Altitude Switching.
4.
F o r high-altitude operation in some types of aircraft, an altitude switching
circuit in the aileron channel of the autopilot amplifier may be strapped to
provide automatic gain change. When the aircraft reaches the altitude
switching point, a signal from the altitude controller activates the switch-
ing circuit, which reduces aileron channel gain 3:l.

(d) Rudder Channel, (See figure 19.)

The AP-103F rudder channel provides yaw damping commands during level
flight and turn coordination commands during aircraft turns. The autopilot
amplifier processes roll coordination data from the aileron channel, and roll
rate data from the roll rate gyro in the sensing unit, and combines the
results with a y a w rate signal from the rate gyro to produce a rudder servo
command.

Roll data from the aileron channel is applied to a coordination adjust network
in the rudder channel. The coordination adjust network is strapped during
installation to establish the amount of roll data that is required for each
degree of yaw rate p e r second. A s airspeed increases, the roll coordination
data is attenuated by the gain change circuit to reduce rudder deflection at
higher airspeeds.

The roll rate signal from the sensing unit is applied to the adverse yaw
adjust circuit. The adverse yaw adjust circuit is strapped at installation to
establish the degrees of roll rate p e r second that are equivalent to one degree
of yaw rate per second. Adverse yaw compensation is not normally required
and is a function of aircraft characteristics.

The yaw rate signal from the rate gyro is the rudder command signal and
provides yaw damping information which is combined with the roll coordina-
tion data.

The roll coordination data and yaw rate signal (and roll rate signal when
used) are summed to form the rudder servo command. The rudder servo
command is applied to a gain-controlled amplifier where amplifier gain is
decreased linearly as airspeed increases. The amplified rudder servo com-
mand is applied to a channel gain adjust network, which is strapped at
installation to establish the degrees of yaw rate per second required to
furnish one degree of capstan rotation in the rudder primary servo. The
gain-adjusted signal is passed through a limiting amplifier to limit rudder
servo-capstan travel. The amplified rudder servo command is routed
through reversing links to a phase detector in the rudder servo amplifier.
Operation of the rudder servo amplifier and the rudder primary servo is
the same as in the aileron channel.

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The de rudder servo command to the primary servo is also routed through
the washout reversing links to the rudder t r i m indicator and to the torque
washout circuit. In the torque washout circuit, the de feedback signal is con-
verted to ac by a chopper and applied to a phasing network. The phasing
network output is a half-wave rectified signal that is phased to oppose the
rudder servo command. An electronic switch, operated by the AP-1O3F
engage voltage, connects the signal to either an integrator o r a low-pass filter.
When the AP-103F is engaged, the switch enables the integrator and disables
the low-pass filter. The integrator builds up the feedback signal to an ampli-
tude equal to the rudder servo command at the input to the limiting amplifier.
Since the phase of the feedback signal is opposite to that of the rudder servo
command, the effect is to cancel the rudder servo command. When the
AP-103F is not engaged, the integrator is disabled and the feedback signal
is shunted to ground through the low-pass filter.

(e) Airspeed Gain Change Circuit.

A circuit that generates a pulse-width continuous gain change drive signal

proportional to airspeed is mounted on the autopilot amplifier q d d e r channel
board.

An airspeed signal from the airspeed sensor is appiied to the continuous gain
change circuit. The airspeed signal is a de voltage that has maximum value
at 100 h o t s o r l e s s of airspeed. Voltage level decreases to 0 as airspeed
increases to 500 knots o r greater. Operation of the switching circuit is con-
trolled by a ramp generator. The switching circuit provides dual outputs:
gain change 1, and gain change 2. When airspeed is 500 h o t s o r greater,
gain change 1 output is 3.0 volts de, and gain change 2 output is 0 volt. When
airspeed is reduced to 100 knots o r less, gain change 2 output becomes 3.0
volts de, and gain change 1 output reduces to 0 volt. Gain change switching
is a linear function: as one output decreases, the other output increases
proportionally.

C. Integrated Flight System Theory of Operation. (See figures 15 and 16.)

. (1) General.

Theory of operation f o r each of the FD-108, FD-108G7 and FD-1O9G Integrated

Flight Systems is identical, except f o r minor differences that result from the use
of different flight director indicators and instrument amplifiers, and because a
mode coupler is used only in the FD-108G and FD-1O9G Integrated Flight Systems.
In the following discussion, whenever reference is made to the Integrated Flight
System, the information given applies equally to all systems. Differences in
system operation a r e noted where they occur, and major circuit differences a r e
identified and described in separate paragraphs.

The Integrated Flight System uses input data from associated equipment to
develop and present an easily interpreted display of the flight situation and to
provide steering commands necessary to attain the desired flight path. Operation
of the Integrated Flight System is presented in two levels: simplified theory of
operation and functional theory of operation.
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(2) Simplified Theory of Operation.

(a) General.
Operation of the Integrated Flight System may be divided into three functions:
display, command, and monitor. The display function provides the attitude
display; the runway localizer and altitude display presented by the flight
director indicator (figures 20 and 21); and the heading and digital distance
display presented by the course indicator (figure 22). The command func-
tion provides the steering commands presented by the flight director indica-
t o r (figures 23 through 26). Monitor functions a r e provided by warning flags
in the flight director indicator and course indicator.

(b) Display Function.

The Integrated Flight System display function provides the roll and pitch
attitude display presented by the flight director indicator and the heading and
digital distance display presented by the course indicator. The flight director
indicator attitude display and the course indicator heading and digital distance
displays are servo driven. The course indicator also provides VOR lateral
and glideslope vertical deviation displays that are operated by meter move-
ments. A glideslope deviation display in the flight director indicator is also
operated by a meter movement. In the FD-108G separate radio altitude and
runway localizer displays a r e operated by m e t e r movements, while in the
FD-1O9G the runway symbol is driven laterally and vertically by servos to
display both runway localizer and altitude deviation information. In the
FD-108 there is no altitude deviation display, and the runway localizer
symbol is driven by a m e t e r mechanism.

Signals representing actual aircraft roll and pitch attitude a r e provided by

the vertical reference. The signals a r e routed directly to the flight director
indicator to drive the pitch attitude tape and the bank attitude indicator to
positions that represent aircraft pitch and bank attitude.

Signals representing aircraft magnetic heading a r e received by the course

indicator from the aircraft compass system. The compass signals position
the azimuth card s o that the aircraft magnetic heading is read beneath the
lubber line.

Glideslope deviation signals are provided by the navigation receiver. These

signals represent the position of the aircraft with respect to glideslope beam
center. The glideslope deviation signals actuate the glideslope m e t e r move-
ments in the flight director indicator and course indicator, resulting in a
corresponding movement of the glideslope pointers,

VOR and localizer signals a r e also provided by the navigation receiver when
the aircraft drifts away from the selected VOR radial o r localizer beam.
These signals drive m e t e r movements that control the lateral deviation b a r
in the course indicator and the runway symbol in the FD-108 and FD-108G
flight director indicator. The signals a r e applied to the instrument amplifier,
which drives a servo to control the runway symbol in the flight director

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indicator in the FD-109G. Another signal from the navigation receiver

drives the to-from arrow in the course indicator to indicate the direction
to the selected VOR station.

The radio altitude deviation signal from the radio altimeter represents from
0 to 200 feet of aircraft radio altitude. This signal drives a m e t e r movement
in the FD-108G flight director indicator, and a servo in the FD-1O9G flight
director indicator, to display the radio altitude. There is no radio altitude
display in the FD-108.

Distance measuring information is routed to the course indicator from the

aircraft DME receiver. This information provides three synchro signal
inputs to drive the units, tens, and hundreds counters in the digital distance
display. The digital distance display indicates the slant range in nautical
miles to a selected VOR/DME station.

(c) Command Function.

-
1. General.

The Integrated Flight System command function provides pitch and roll
axis steering commands as presented by the V-bar command indicators
in the flight director indicator.

-
2. Pitch Axis.

The pitch channel of the flight computer generates a pitch steering com-
mand proportional to the direction and degree of pitch required to achieve
the desired flight attitude. Mode voltages select from the manual pitch
command, altitude e r r o r , glideslope deviation, and pitch attitude data
inputs to produce the required V-bar pitch steering command. The V-bar
pitch steering command is then processed by the instrument amplifier to
obtain the V-bar pitch command servo-drive signal that drives the V-bar
pitch command servo to position vertically the V-bar command indicator
in the flight director indicator.

-
3. Roll Axis.

The roll channel of the flight computer compares aircraft attitude and
flight path deviation signals to produce a V-bar roll steering command
that is proportional to the direction and degree of roll necessary to fly
the aircraft in a desired manner, Mode voltages, originating in the
pedestal controller, select from VOR/LOC deviation, course datum,
heading e r r o r , manual turn command, and bank attitude data f o r process-
ing by the flight computer to produce the V-bar roll steering command,
The V-bar roll steering command is then processed by the instrument
amplifier to obtain the V-bar roll command servo-drive signal that
drives the V-bar roll command servo to position laterally the V-bar com-
mand indicator in the flight director indicator.

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 (d) Monitor Function.
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The Integrated Flight System monitor function provides warning flag displays,
V-bar command indicator out-of-view logic, and shutter control. Annunciator
output voltages a r e also provided to display the mode of operation in asso-
ciated equipment.

All input data to the Integrated Flight System is monitored for validity by the
system providing the data. The monitor signals are applied to monitor c i r -
cuits in the flight computer and instrument amplifier where monitor control
voltages are developed. When the incoming data signal is invalid, no monitor
voltage is generated, and the warning flag o r shutter is displayed.

When the vertical reference is operating normally, a monitor signal is ap-

plied to the instrument amplifier monitor channel. Loss of the vertical refer-
ence monitor signal indicates an invalid roll o r pitch attitude signal. The
instrument amplifier internally monitors operation of the instrument
amplifier-flight director indicator attitude display servo. When operation is
normal and the vertical reference monitor signal is present, a monitor volt-
age is produced by the instrument amplifier. The monitor voltage is applied
to the flight director indicator to hold the GYRO warning flag out of view and
to the flight computer and the instrument amplifier monitor command circuit
to control the COMPUTER (CMPTR in FD-109G) warning flag.

Normal operation of the aircraft compass system is indicated by receipt of

a compass warning monitor signal in the instrument amplifier monitor chan-
nel. Loss of the compass monitor signal indicates an invalid compass head-
ing signal. The instrument amplifier internally monitors operation of the
instrument amplifier-course indicator compass heading servo. When opera-
tion is normal and the compass monitor signal is present, a monitor voltage
is applied to the compass shutter to cover the COMPASS warning flag in the
course indicator.

When the DME receiver is operating normally, monitor signals a r e applied

to a m e t e r movement in the course indicator. When the distance measuring
information is valid, the shutter covering the digital distance display is
biased out of view.

Normal operation of the navigation receiver is indicated by receipt of VOR/

localizer and glideslope monitor signals by the flight director indicator and
the course indicator. In the FD-108 and FD-l08G, if valid VOR/localizer
deviation signals a r e being received, the VOR LOC warning flag in the
course indicator and the localizer shutter in the flight director indicator
a r e biased out of view. In the FD-109G, if valid VOR/localizer deviation
signals a r e being received, the VOR LOC warning flag in the course indica-
t o r and the RUNWAY flag in the flight director indicator are biased out of
view. Below the altitude t r i p point (in glideslope extension mode), the GS
warning flags in the course indicator and flight director indicator are biased
out of view if the glideslope low-level flag voltage is present.

In the FD-l08G, normal operation of the radio altimeter is indicated by

receipt of a radio altitude monitor signal in the flight director indicator

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when the aircraft is below the altitude trip point. If the radio altitude de-
viation signal is valid, the RAD ALT warning flag is biased from view.

In the FD-lOSG, the radio altitude monitor voltage is applied to the instru-
ment amplifier, and loss of the radio altitude monitor voltage indicates an
invalid radio altitude signal. Below the altitude t r i p point, o r middle m a r k e r ,
the RUNWAY flag monitors the radio altitude monitor voltage.

(3) Functional Theory of Operation,

(a) General.
In the following paragraph, the theory of operation f o r the Integrated Flight
System display, command, and associated functions is presented in g r e a t e r
detail.

(b) Attitude Display. (See figure 20.)

1. Bank Attitude Display.

-
Signals representing actual aircraft bank attitude are provided by the
vertical reference. The phase and amplitude of the signal is proportional
to the direction and degree of bank displacement from level. The bank
attitude signal is applied to the stator of the bank attitude control trans-
f o r m e r in the flight director indicator.

The bank attitude control transformer compares the bank attitude signal
with the position of the bank attitude display, that is driven by a motor-
generator, to produce a bank attitude e r r o r signal. The phase and
amplitude of the bank attitude e r r o r signal a r e dependent upon the position
of the bank control transformer rotor. The bank attitude motor-generator
produces a bank attitude rate signal that is used to provide damping. The
amplitude of the bank attitude rate signal is proportional to the speed of
the bank attitude motor-generator and is 180 degrees out of phase with the
bank attitude e r r o r signal. The bank attitude e r r o r and rate signals a r e
summed and then amplified by the bank servo amplifier in the instrument
amplifier and applied as the bank attitude servo-drive signal to the bank
attitude motor-generator. This signal drives the bank attitude servo
motor until the bank attitude e r r o r signal is reduced to a minimum. With
the bank attitude e r r o r signal at a minimum, the flight director indicator
bank attitude display represents true aircraft bank attitude.

2.
- Pitch Attitude Display.

Signals representing actual aircraft pitch attitude a r e provided by the

vertical reference. The phase and amplitude of the signal are propor-
tional to the direction and degree of pitch displacement from level. The
pitch attitude signal is applied to the stator of the pitch attitude control
transformer in the flight director indicator.

The pitch attitude control transformer compares the pitch attitude signal
with the position of the motor-generator-driven pitch attitude tape to

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 produce a pitch attitude e r r o r signal. The phase and amplitude of the
pitch attitude e r r o r signal is dependent upon the position of the pitch con-
t r o l transformer rotor. The pitch attitude motor-generator produces a
pitch attitude rate signal which is used to provide damping. The amplitude
of the pitch attitude rate signal is proportional to the speed of the pitch
attitude motor-generator and is 180 degrees out of phase with the pitch
attitude e r r o r signal. The pitch attitude e r r o r and rate signals a r e sum-
med and then amplified by the pitch servo amplifier in the instrument
amplifier and applied as the pitch attitude servo-drive signal to the pitch
attitude motor-generator. This signal drives the pitch attitude servo
motor until the pitch attitude e r r o r signal is reduced to a minimum. When
the pitch attitude e r r o r signal is reduced to a minimum, the flight director
indicator attitude tape represents true aircraft pitch attitude.

(c) FD-108 and FD-1O8G Localizer Deviation Display.

In the FD-108 and FD-108G Integrated Flight Systems, the localizer deviation
signal from the navigation receiver is a de signal proportional to the lateral
displacement of the aircraft from the selected localizer beam. The signal is
routed directly to a m e t e r mechanism in the course indicator. The meter
mechanism controls the position of the lateral deviation bar, which represents
true aircraft position with respect to the localizer beam when compared with
the course arrow.

In the FD-108, the de localizer deviation signal is also applied directly to a

m e t e r mechanism in the flight director indicator. This m e t e r mechanism
controls the position of the runway symbol, which also represents true air-
craft position with respect to the localizer beam. In the FD-108GYthe de
localizer deviation signal is first routed through contacts of the back-course
relay in the mode coupler before being applied to the m e t e r mechanism in
the flight director indicator. When flying the back course, energizing the
back-course relay reverses the polarity of the localizer deviation signal, and
the runway symbol presents an accurate representation of aircraft position.

(d) FD-1O9G Localizer Deviation Display. (See figure 21.)

In the FD-1O9G Integrated Flight System, the de localizer deviation signal

from the navigation receiver is routed through contacts of the back-course
relay in the mode coupler and applied to a chopper in the instrument amplifier
where the signal is converted to ac. The a c signal is then amplified. If the
localizer mode voltage is present, electronic switches are closed, and the
localizer deviation signal is mixed with the runway localizer position signal
from the flight director indicator. The runway localizer position signal repre-
sents the actual lateral position of the runway symbol. Any existing e r r o r
signal is amplified and applied to a quadrature rejection filter to remove
signal components that are 90 degrees out of phase with command power.
The e r r o r signal is then mixed with the runway localizer rate signal from the
flight director indicator to provide damping and to prevent overshoot. The
runway localizer rate signal is proportional in amplitude to the speed of the
runway localizer motor-generator and 180 degrees out of phase with the e r r o r
signal. The damped runway localizer e r r o r signal is then amplified by the
localizer servo amplifier and applied as the runway localizer servo-drive

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signal to the runway localizer servo motor until the runway localizer position
e r r o r signal is reduced to a minimum. When the e r r o r signal is minimum,
the flight director indicator runway symbol represents true aircraft position
with respect to the localizer beam.

The dc localizer deviation signal from the navigation receiver is also routed
directly to a m e t e r mechanism in the course indicator where the signal is
used to position the lateral deviation bar. The position of the lateral deviation
b a r with respect to the course arrow represents true aircraft position with
respect to the localizer beam.

(e) FD-108G Radio Altitude Deviation Display.

In the FD-108G Integrated Flight System, the radio altitude deviation signal
from the radio altimeter is a dc signal proportional to the altitude of the air-
craft from 0 to 200 feet. The signal is applied directly to a m e t e r mechanism
in the flight director indicator, At the altitude t r i p point, a 500-microampere
signal is applied to the flight director indicator. The RAD ALT flag is biased
out of view, and the radio altitude pointer is positioned at the 200-foot mark.
As the radio altitude is decreased, the radio altitude deviation signal de-
c r e a s e s proportionally and the pointer moves down indicating the true radio
altitude position of the aircraft.

(f) FD-1O9G Radio Altitude Deviation Display. (See figure 21.)

-
1. In-View.

In the FD-1O9G Integrated Flight System, radio altitude deviation is dis-

played with the runway symbol. An ac bias signal generated in the instru-
ment amplifier is proportional to the amplitude required to bias the runway
symbol to an in-view position. If the localizer voltage is present and the
altitude t r i p signal is not present, the a c bias signal is mixed with the
position X signal. The result is an e r r o r signal proportional to the
amount of correction needed to position the runway symbol. The e r r o r
signal is then amplified and applied to a quadrature rejection filter to
remove signal components that are 90 degrees out of phase with the ap-
plied power. The e r r o r signal is then amplified and applied to a quadra-
ture rejection f i l t e r to remove signal components that are 90 degrees out
of phase with the applied power. The e r r o r signal is then mixed with the
runway altitude rate signal from the flight director indicator to provide
damping and to prevent overshoot. The runway altitude rate signal is
proportional in amplitude to the speed of the runway altitude motor-
generator and 180 degrees out of phase with the e r r o r signal. The damped
runway altitude e r r o r signal is amplified by the altitude servo amplifier
and applied as the runway altitude servo drive signal to the runway altitude
motor-generator. This signal drives the runway altitude servo motor
until the runway altitude position X signal is equal to the ac bias signal.
When the two signals a r e equal, the flight director indicator runway sym-
bol is in view.

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The radio altitude deviation signal from the radio altimeter is a dc signal
proportional to the altitude of the aircraft. The signal is applied to a
chopper in the instrument amplifier to convert it to ac, then amplified and
mixed with the runway altitude position signal from the flight director
indicator. The runway altitude position signal represents the actual
vertical position of the runway symbol. Combining the two signals results
in the creation of an e r r o r signal proportional to the amount of correction
needed to position the runway symbol. If the altitude t r i p voltage o r glide-
slope extension signal is present, the e r r o r signal is amplified and applied
to a quadrature rejection filter. The quadrature rejection filter removes
the signal components that a r e 90 degrees out of phase with command
power. The e r r o r signal is then mixed with the runway altitude rate sig-
nal from the flight director indicator to provide damping and to prevent
overshoot. The damped e r r o r signal is then amplified by the altitude
servo amplifier and applied as the runway altitude servo-drive signal to
the runway altitude motor-generator. This signal drives the runway
altitude servo motor until the runway altitude position e r r o r signal is
reduced to a minimum. When the position e r r o r signal is minimum, the
flight director indicator runway symbol represents true aircraft position
with respect to the radio altitude.

(g) Course and Heading Display. (See figure 22.)

A compass heading signal, which represents aircraft magnetic heading, is

provided by the compass system. The compass heading signal is applied
to the azimuth, course datum, and heading e r r o r control transformers in
the course indicator.

The azimuth control transformer is mechanically coupled to the azimuth

card and azimuth card motor-generator. The azimuth control transformer
compares the position of the azimuth card with the aircraft magnetic heading
to produce an azimuth card e r r o r signal. The azimuth card motor-
generator produces an azimuth card rate signal of opposite phase to the
azimuth c a r d e r r o r signal. The azimuth card rate signal provides a damping
effect. The azimuth card e r r o r and azimuth card rate (damping) signals a r e
applied to the compass servo amplifier in the instrument amplifier. The
output of the compass servo amplifier is zipplied, as the azimuth c a r d servo-
drive signal, to the azimuth card servo motor. When the azimuth card and
azimuth control transformer are driven to the point where the azimuth card
e r r o r signal is reduced to minimum, the azimuth card presents aircraft
magnetic heading as read under the lubber line.

The course datum control transformer and course resolver a r e driven by

the manual COURSE knob on the front of the course indicator. The course
datum control transformer output is a reference signal that represents the
difference between the selected course (as displayed by the course arrow)
and the aircraft magnetic heading. The reference signal (course datum) is
applied to the flight computer where it is processed and summed with other
signals to generate steering commands. The input to the course resolver
from the navigation receiver is a variable-phase reference signal. The

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phase of the reference signal is shifted when the rotor of the course resolver
is turned by rotating the COURSE knob. The course resolver output consists
of a 30-Hz signal and a reference phase signal plus 90 degrees. The signals
a r e applied to a phase comparator in the navigation receiver where radio
deviation information is generated.

The heading e r r o r control transformer is driven by the manual HDG (heading)

control on the front of the course indicator. The heading e r r o r control trans-
f o r m e r output is a reference signal that represents the difference between
the selected heading (as displayed by the heading marker) and the aircraft
magnetic heading. The reference signal (heading e r r o r ) is applied to the
flight computer where it is processed and summed with other signals to gen-
erate steering commands.
(h) V-Bar Roll Steering Command Functions. (See figure 23.)

1. General.
-
The V-bar roll steering commands for the Integrated Flight System a r e
computed in the flight computer and processed in the instrument amplifier.
Functional block diagram theory is provided in this manual. If more
detailed circuit information is required, refer to the appropriate equip-
ment overhaul manual.

-
2. Roll Steering Commands by Operating Mode.

a. Gyro Mode.
-

The gyro mode is selected by switching the pedestal controller mode

selector to GYRO. An out-of-view signal is provided by the flight
computer to drive the V-bar command indicator in the flight director
indicator out of view. The flight director indicator provides only the
basic attitude display when operated in the gyro mode.

-
b. Heading Mode.

With the mode selector on the pedestal controller set to HEADING

position, the Integrated Flight System operates in the heading mode.
In heading mode, the flight computer computes a V-bar roll steering
command using the heading e r r o r and bank attitude signal inputs.

The heading e r r o r signal f r o m the course indicator is an ac signal

proportional to the difference between the aircraft magnetic heading
and the heading as selected by the HDG knob on the course indicator.
In the FD-108, the heading e r r o r signal is applied directly to the head-
ing input and analog adjust circuit in the flight computer. In the
FD-108G and FD-109G, the heading e r r o r signal is routed through the
mode coupler to the heading input and analog adjust circuit in the
flight computer. The heading e r r o r signal is then passed through a
quadrature rejection filter to remove signals 90 degrees out of phase,
The signal is next applied to a bank limiter where the desired degree
of bank limit is established.

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MMAIIVTEIVASCE
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The bank attitude signal from the vertical reference is an ac signal

proportional to the actual bank angle of the aircraft. The bank attitude
signal is applied to the bank attitude input circuit in the flight computer,
then to a phase converter, and then to an analog adjust circuit, The
phase converter holds the bank attitude signal in phase with applied
heading power, the phase reference f o r the flight computer. The analog
adjust circuit is adjusted to match the millivolts-per-degree output of
the vertical reference. The bank attitude signal is then amplified and
combined with the bank limited heading e r r o r signal.

The combination of bank limited heading e r r o r signal and bank attitude

signal produces a signal proportional to the difference between the
commanded bank and the actual bank. This signal is amplified and then
phase detected to produce a dc V-bar roll steering command.

-
c. NAV/Localizer Modes.

The NAV/localizer modes are selected by switching the pedestal con-

troller mode selector switch to NAV/LOC. Switching the mode selector
to NAV/LOC in the absence of a localizer voltage from the navigation
receiver puts the flight computer in the NAV modes, and switching the
mode selector with a localizer voltage present puts the flight computer
in the localizer mode.

(lJ NAV Modes.

Switching the pedestal controller mode selector directly from

HEADING to NAV/LOC puts the Integrated Flight System in the
heading-NAV submode. In the heading-NAV submode, flight
computer circuit operation is the same as in heading mode, except
that the beam sensor and the NAV/localizer deviation channel are
armed f o r NAV capture, and a NAV a r m annunciation output is
provided. The desired course-cut intercept angle is determined
by the position of the HDG knob on the course indicator. When the
desired signal level is obtained, the beam sensor turns off the
heading mode and turns on the NAV mode. After NAV oapturs, the
flight computer uses VOR deviation, course datum, and bank attitude
signals to compute the V-bar roll steering command. \

The VOR deviation signal from the navigation receiver is a dc sig-

nal proportional to the lateral displacement of the aircraft from
the selected VOR course. In the FD-108 the signal is applied
directly to the flight computer, but in the FD-108G and FD-1O9G
the signal is routed through contacts of the back-course relay in
the mode coupler before being applied to the flight computer. In
the flight computer, the signal is applied to a chopper and converted
to ac. The a c signal is amplified and applied to a rate limiter.
The rate limiter reduces the signal after the beam sensor indicates
NAV capture and the system is tracking o r when localizer voltage
is present. The rate limited VOR deviation signal is used in three
ways. It is applied to a quadrature rejection network where the

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t r i p level is adjusted to provide switching f o r NAV capture; it is

gain adjusted and applied to the complementary filter input; and it
is summed with the complementary filter output.
The course datum signal from the course indicator is an ac signal
proportional to the difference between the selected course and the
aircraft magnetic heading. In the FD-108 the signal is applied
directly to the flight computer, but in the FD-108G and FD-1O9G
the signal is routed through contacts of the back-course relay in
the mode coupler before being applied to the flight computer. The
course datum input circuit in the flight computer is an adjustable
impedance matching network. The course datum signal voltage is
analog-adjusted to match the millivolts-per-degree requirement
of the flight computer circuits. The analog-adjusted signal is
amplified and used three ways. It is routed through the overcone
memory circuits to the course-cut amplifier; it is applied to a
rate limiter, together with the VOR deviation signal; and it is ap-
plied to a quadrature rejection filter. The quadrature rejection
filter output is a square-wave signal in phase with heading power.
The square-wave signal is gain adjusted and applied to the comple-
mentary filter; it is also summed with the course-cut limiter
output and applied to the bank limiter.

The bank attitude signal previously described, in addition to being

routed to the bank limiter, is amplified and applied to the comple-
mentary filter through a bank rate adjust circuit.

The VOR deviation, course datum, and bank attitude signals a r e

r a t e gain adjusted i n the complementary filter. The amount of rate
gain is determined by strapping and is measured at the center fre-
quency of the complementary filter output. The complementary
filter is essentially an adjustable bandpass filter where the output
is used to provide smoothing to prevent sudden rate changes in the
command signal. The complementary filter rate of change time
constant is adjustable. This provides selection of the rate of
change response for the desired operating mode. The comple-
mentary filter provides filtering of the high-frequency radio
components that are principally noise while deriving rates from
the low frequency components that contain useful information.
The course datum and bank attitude signals compensate f o r the
radio signal components that a r e removed. The complementary
filter passes the course datum signal, allowing the aircraft to take
up any heading without standoff. The complementary filter output
signal approximates the rate at which the aircraft is approaching
the selected VOR o r localizer course.

The complementary filter output is combined with the VOR devia-

tion signal to stabilize the approach to the selected VOR course
and to provide automatic crosswind correction. The combined
signal is amplified and applied to the radio command limiter
where it is passed without limiting in the NAY capture mode. The
signal is then applied to the course-cut amplifier. If the computer

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 COLLINS
MAINTENANCE
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is not tracking in the NAV mode, course datum is mixed with the
radio deviation signal at the input to the course-cut amplifier. The
amplified signal is applied to the course-cut limiter. The course-
cut limiter limits the intercept angle when flying a NAV capture
course. The amount of limiting is adjusted by strapping. When the
computer is in NAV mode but not tracking, the course-cut limit is
reduced to permit a l a r g e r course-intercept angle. When the
computer starts tracking, the course-cut limiter reduces the inter-
cept angle to command a turn to the VOR radial. The output from
the course-cut limiter is summed with the course datum square-
wave output from the quadrature rejection filter. The combined
signal is applied to the bank limiter where the degree of bank com-
mand is limited to provide the optimum bank angle f o r a specific
aircraft type. The amount of bank limit is determined by
strapping.
The bank limited signal is amplified and combined with the bank
attitude signal, amplified again, and phase detected to provide the
dc V-bar roll steering command.

(2J Localizer Modes.

Switching the pedestal controller mode selector directly from

HEADING to NAV/LOC with the localizer voltage present puts the
Integrated Flight System in the heading-localizer submode. In the
heading-localizer submode, operation is the same as in select
heading capture as described in the heading-NAV submode, except
that the beam sensor is armed f o r localizer capture. The localizer
voltage adjusts the beam sensor t r i p level, the radio rate limiter,
and the complementary filter parameters. After capture of the
localizer beam, the flight computer switches to localizer mode
operation. Operation in the roll channel in this mode is identical
to operation in NAV mode after capture, except that the localizer
voltage adjusts the radio rate limiter and the complementary filter
parameters.

(3J FD-108G and FD-1O9G Back-Course Localizer.

In the FD-108G and FD-109G, relays a r e provided in the mode

coupler to r e v e r s e the polarity of VOR/localizer deviation and
course datum signals during back-course operation. The r e v e r s e
polarity course datum signal is applied to the flight computer.
In the FD-108G the reverse polarity VOR/localizer deviation sig-
nal is applied to the flight computer and also directly to the runway
symbol m e t e r mechanism in the flight director indicator. In the
FD-1O9G the r e v e r s e polarity VOR/localizer deviation signal is
applied to the flight computer and to the instrument amplifier. In
the instrument amplifier the signal is processed for application to
the runway servo in the flight director indicator.

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When the navigation receiver is tuned to a localizer frequency and

the mode selector on the pedestal controller is set to HEADING o r
NAV/LOC, pressing the externally mounted back-course switch
energizes the back-course relays.

Back course relay K201 r e v e r s e s the polarity of the course datum

signal, and back-course relay K203 r e v e r s e s the polarity of the
VOR/localizer deviation input. An interlock circuit holds the system
in the back-course mode (figure 27). Switching the mode selector
to GYRO o r APPR position r e s t o r e s normal system operation.

d_. Approach Mode.

Switching the mode selector on the pedestal controller to APPR with the
localizer mode voltage present will put the Integrated Flight System in
the approach mode. Operation in the roll channel in this mode is iden-
tical to that described f o r localizer mode.
e. Go-Around Mode.
-
The go-around mode is selected with an externally mounted switch but
only when the Integrated Flight System is operating in the approach
mode.

(1) FD-108 Go-Around Mode.

In the FD-108, when the go-around switch is pressed, the externally

mounted go-around relay is energized. Relay contacts open to dis-
connect operating power f r o m the AP-103F and to open the altitude
hold interlock circuit. Other relay contacts close to apply oper-
ating voltage to the go-around circuits in the flight computer to
provide a wings-level V-bar roll steering command.

2
(J FD-108G and FD-1O9G Go-Around.

In the FD-108G and FD-1O9G when the go-around mode is selected,

the go-around circuit in the mode coupler is energized, disengaging
any other operating modes previously selected with the mode
selector switch on the pedestal controller. In the go-around mode,
the flight computer uses only the bank attitude signal from the
vertical reference to provide a wings -level V-bar roll steering
command. All other signals into the flight computer are switched
off. Rotating the mode selector switch to any other operating
position except HEADING will restore normal system operation.
In go-around mode, switching the system to HEADING provides
--
split-axis go-around ( r e f e r to paragraph 5.C.(3)(h)2.e.).

-
3. Roll Steering Command Processing. (See figure 24.)

The dc V-bar roll steering command from the flight computer is applied
to a chopper in the instrument amplifier, converted t o ac, and applied to
an amplifier. In all operating modes except gyro, the amplifier output is

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MANUAL

mixed with the V-bar roll position and V-bar roll command r a t e feedback
signals from the flight director indicator. Roll command position trans-
mitter B1 supplies the V-bar roll position feedback, and V-bar roll com-
mand motor-generator MG1 provides the V-bar roll command r a t e
feedback. In gyro mode, the V-bar command indicator is biased out of
view, and no V-bar roll steering command is used. In all other operating
modes, the combined signal is amplified and applied to a quadrature
rejection filter that removes 90-degree signal components. The filtered
signal is amplified by the roll command servo amplifier before being
applied to the motor control windings of MG1. The motor is mechanically
coupled to the V-bar command indicator and positions the indicator
laterally in response to the V-bar roll command servo-drive signal.

(i) V-Bar Pitch Steering Command Functions. (See figures 25 and 26.)

-
1. General,

The V-bar pitch steering commands for the htegrated Flight System a r e
computed in the flight computer and processed in the instrument amplifier.
Functional block diagram theory is given in the following paragraphs. If
more detailed information is required, r e f e r to the specific equipment
overhaul manual.

-
2 . Pitch Steering Commands by Operating Mode.

-
a. Gyro Mode.

The gyro mode is selected by switching the mode selector on the

pedestal controller to GYRO position. A mode voltage is provided
from the flight computer to an off-scale bias circuit in the instrument
amplifier to drive the V-bar command indicator in the flight director.
indicator out of view. In the gyro mode, the only information provided
by the flight director indicator is the basic attitude display.

- Heading Mode.
b.

(l
J General.

Switching the mode selector on the pedestal controller to HEAD-

ING puts the Integrated Flight System in the manual pitch submode
o r , if the ALTITUDE switch on the pedestal controller is in the
ON position, in the altitude hold submode.

(3 FD-108 Manual Pitch Submode. (See figure 25.)

In manual pitch submode for the FD-108, the manual pitch com-
mand is provided by adjusting the PITCH CMD knob on the flight
director indicator to provide the degree of climb o r descent
required. Adjusting the PITCH CMD knob generates the manual
pitch command in synchro transmitter B9. The manual pitch
command is applied to the manual pitch command input circuit

May 1/67 22-03-00

Page 51
 in the flight computer where it is converted to dc. When the FD-
108 is not operating in altitude hold o r glideslope submodes, the
manual pitch command is amplified and phase detected to produce
the V-bar pitch steering command.

(3J FD-108G and FD-1O9G Manual Pitch Submode. (See figure 26.)

In the manual pitch submode for the FD-108G and FD-lOSG, the
manual pitch command originates in the vertical reference. The
pitch attitude signal from the vertical reference is applied to
pitch attitude control transformer B 6 in the flight director indica-
tor. The pitch attitude e r r o r signal output from B6 is mechani-
cally coupled to pitch attitude transmitter B7. The pitch attitude
transmitter output is applied to pitch synchronizer control trans-
former B702 in the mode coupler. If the Integrated Flight System
is not operating in altitude hold, glideslope capture, go-around, o r
gyro modes, or if the pitch synchronization button has not been
pressed, B702 provides a pitch command output signal. The pitch
command is a phase-sensed ac signal of 200 millivolts per degree
of pitch attitude. The ac signal is applied to the manual pitch
command input circuit in the flight computer and converted to dc.
When the FD-1O8G o r FD-109G is not operating in altitude hold o r
glideslope submodes, the pitch command is amplified and phase
detected to produce the V-bar pitch steering command.

- Altitude Hold Submode.

(4)

In the altitude hold submode, the flight computer selects altitude

e r r o r and pitch attitude signals to compute V-bar pitch steering
commands to maintain the desired altitude.

The altitude e r r o r signal is a phase-reversible ac signal equal to

1 0 millivolts per foot of altitude e r r o r , and it originates in the
altitude controller. The amplitude of the signal is proportional
to the difference between the actual altitude and the selected alti-
tude, and the phase of the signal is determined by whether the
aircraft is above o r below the selected altitude. In the altitude
hold submode, the altitude e r r o r signal is applied to an altitude
analog adjust circuit that is strapped to adjust the computer c i r -
cuits to match the millivolts-per-foot output of the altitude con-
troller. The e r r o r signal is amplified and applied to a quadrature
rejection filter to remove signal components that a r e 90 degrees
out of phase with the altitude e r r o r signal. The filtered signal is
applied to the altitude gain adjust circuit where it is adjusted to
match the desired feet per degree of pitch.

The pitch attitude signal from the vertical reference is an ac

signal proportional to the actual pitch angle of the aircraft. The
pitch attitude signal is applied to the pitch analog adjust circuit
that adjusts the computer circuit to match the millivolts-per-
degree output of the vertical reference. The pitch attitude signal

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MANUAL

is amplified, low-pass filtered, and combined with the altitude

e r r o r signal. The combined signal is amplified, limited to a
predetermined number of degrees, then amplified and phase de-
tected to produce the dc V-bar pitch steering command.

-
c . NAV/Localizer Modes.

Switching the mode selector on the pedestal controller to NAV/LOC

position puts the pitch channel of the Integrated Flight System in the
manual pitch or altitude hold submodes. Operation of the manual pitch
submode and the altitude hold submode in the navigation/localizer mode
is the same a s that described for the heading mode.

-
d . Approach Mode.

Switching the mode selector on the pedestal controller to APPR posi-

tion puts the pitch channel of the Integrated Flight System in either
the manual pitch, altitude hold, glideslope, or glideslope extension
submodes of the approach mode. Before glideslope beam capture, the
operating mode is either manual pitch or altitude hold, and operation
is the same as previously described for manual pitch and altitude hold
operation in the heading mode, except that in the approach mode the
glideslope beam sensor is armed for glideslope beam capture. After
glideslope beam capture, operation is in glideslope or glideslope ex-
tension with glideslope extension submode initiated by receipt of the
middle marker o r altitude trip voltage.

When operating in the glideslope submode, the flight computer selects

glideslope deviation and pitch attitude signal inputs to compute the dc
V-bar pitch steering command.

The glideslope deviation signal from the navigation receiver is a dc

signal proportional to the vertical displacement of the aircraft from
the glideslope beam center. The signal is applied to a chopper in the
flight computer where it is converted to ac. The ac signal is ampli-
fied and applied to the glideslope gain change circuit where the gain
is reduced in glideslope extension submode. This is accomplished by
adding resistance to the circuit through an electronic switch that is
energized by a mode voltage.

The pitch attitude signal from the vertical reference is applied to the
pitch analog adjust circuit, amplified, applied to a low-pass filter,
combined with the glideslope deviation signal , and amplified again.
Then the signal is limited and combined with the pitch command signal.
The pitch command signal represents zero pitch position of the V-bar
command indicator in the flight director indicator. The zero pitch
position is determined in the FD-108 by the position of the PITCH CMD ,

knob, and in the FD-108G and FD-109G by pressing the pitch synchro-
nization button when the .pitch angle h a s been established manually.
Combining the pitch attitude and pitch command signals produces a
signal that represents the difference between the actual attitude of the

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MANUAL

aircraft and the commanded pitch attitude. The combined signal is

amplified and phase detected to provide the V-bar steering command.

The glideslope extension submode is initiated by receipt of the ac

middle marker signal from the marker beacon receiver o r the altitude
extension override signal from the radio altimeter. The signal is
applied to the glideslope gain circuit, which reduces the glideslope
gain by applying the signal to a divider network. The result is a V-bar
pitch steering command with a small glideslope correction. Otherwise ,
operation in the glideslope extension submode is identical to operation
in glideslope submode.

e. Go-Around Mode.
-
The go-around mode is selected with an externally mounted switch but
only while in the approach mode. In the FD-108, pressing the go-
around switch energizes the externally mounted go-around relay. When
the relay is energized, relay contacts open to remove system power
from the AP-103F and to disengage any other FD-108 operating mode
previously selected with the mode selector on the pedestal controller.
In the FD-108G and FD-lOgG, the go-around circuit in the mode coup-
l e r is energized to disengage the operating mode. In go-around mode,
circuits in the flight computer generate a fixed pitch-up command in
response to go-around mode switching logic. The fixed pitch-up com-
mand is an ac signal that is amplified and phase detected to provide a
dc V-bar pitch steering command to the instrument amplifier.

In the FD-108G and FD-lOgG, when the go-around decision has been
made, and the go-around switch has been pressed, the climb-out pitch
attitude is established manually, and then the pedestal controller mode
selector is switched to HEADING before pressing the externally
mounted pitch synchronization switch. Pressing the pitch synchro-
nization switch while in the HEADING mode, and with the pitch attitude
established, stops the pitch synchronization circuit in the mode coupler
and sets the V-bar command indicator to the zero position, providing
a reference point for the maintenance of the climb-out pitch attitude.
Any deviation from the climb-out pitch attitude will result in a pitch
e r r o r signal from the pitch synchronization circuit. The pitch e r r o r
signal is applied to the flight computer where it is used to develop a
dc V-bar pitch steering command. The pitch deviation is displayed by
the V-bar command indicator so that manual correction can be made
to r e s t o r e the desired aircraft pitch attitude.
-
f. FD-108G and FD-1O9G Pitch Synchronization.
In the FD-108G and FD-109G, the pitch attitude signal from the verti-
cal reference is routed to pitch control transformer B6 in the flight
director indicator. The pitch attitude control transformer is mechani-
cally coupled to pitch transmitter B7, which produces a matching output
that is applied to control transformer B702 in the pitch synchronization
circuit in the mode coupler. The control transformer provides either
a pitch command or a pitch synchronization feedback signal output
(figure 28). The pitch synchronization feedback s’ignal is controlled by

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w MANUAL

an electronic switch which is in turn controlled by an OR gate. In

normal operation the switch is closed and the feedback signal is applied
to the motor of motor-generator B702, which mechanically rotates the
control transformer and synchronizes it to the incoming signal. In
altitude hold, glideslope capture, o r go-around submodes; or with the
pitch synchronization switch closed; o r in autopilot manual pitch mode
with the AP-103F engaged, the electronic switch opens, disconnecting
the feedback signal. With the pitch synchronization feedback signal
removed, the control transformer provides the pitch command that is
applied to the flight computer. In the flight computer the pitch com-
mand is amplified and converted to dc to form the V-bar pitch steer-
ing command. The V-bar command indicator in the flight director
indicator is r e s e t to zero position at the aircraft pitch attitude in
effect at time of receipt of the pitch command from the pitch synchro-
nization circuit.

-
3. Pitch Steering Command Processing. (See figure 24.)

The dc V-bar pitch steering command from the flight computer is applied
to a chopper in the instrument amplifier, converted to ac, and then fed to
an amplifier. The amplifier output is summed with the V-bar pitch posi-
tion feedback signal from the pitch command position transmitter B2 in
the flight director indicator. In all operating modes except gyro, the
combined signal is summed with the V-bar pitch command r a t e feedback
signal from V-bar pitch command motor-generator MG3. In gyro mode,
the combined pitch steering command and V-bar pitch position feedback
signal is not used. Instead, the V-bar pitch command rate feedback signal
is summed with the V-bar off-scale bias voltage from the pitch command
position transmitter. In either c a s e , the resultant signal is amplified and
applied to a quadrature rejection filter where signals 90 degrees out of
phase a r e removed. The filtered signal is amplified by the pitch command
servo amplifier before being applied to the motor control windings of the
V-bar pitch command motor -generator. The motor is mechanically
coupled to the V-bar command indicator and positions the indicator out of
view in response to the off-scale bias voltage in gyro mode or vertically
in response to the V-bar pitch steering commands in all other operating
modes ,

4. Altitude Hold Interlock.

-
In the pedestal controller, when the AP-103F is disengaged, the altitude
hold voltage of 27.5 volts dc is applied through contacts 8 and 1 3 of de-
energized relay K l . With the pedestal controller mode selector switch
S 1 set to any position except GYRO, the 27.5 volts dc is connected
through contacts of S1 and contacts 2 and 1 of switch S5 to one side of
ALTITUDE switch S4. When the AP-103F is engaged, the 27.5-volt dc
altitude hold voltage is applied through contacts 6 and 5 of energized re-
lay K1, diode CR2, and the normally closed contacts of the altitude cut-
out switch S2, to one side of ALTITUDE switch S4. Switch S4 contacts
a r e held in the ON position by a solenoid that is energized through an
altitude hold interlock circuit.

May 1/67 22-03-00

Page 55
 In the FD-108, when the ALTITUDE switch is set to ON, the 27.5 volts is
routed through contacts 1 and 3 of S4 to terminal 51-34 in the altitude
controller and to terminal J l A ( T P ) - 4 7 i n the flight computer (figure 29).
In the flight computer, the voltage activates altitude hold on and off
switches Q184 and Q185, providing a ground return for the ALTITUDE
switch solenoid in the pedestal controller. The ground return is applied
through flight computer terminal J l A ( T P ) -46 and the normally closed
contacts of the externally mounted go-around relay to pedestal controller
terminal 51-W and through diode C R 3 to the solenoid winding.

In the FD-108G and FD-lOgG, when the ALTITUDE switch is set to ON,
the 27.5 volts dc is routed through contacts 1 and 3 of S4, and terminal
J1-V to terminal 52-50 in the mode coupler (figure 30). From the mode
coupler, the voltage is routed through terminal 51-40 to the altitude con-
troller for altitude hold operation. A s part of the interlock circuit, the
voltage is also applied through diode CR401 and terminal 51-27 to termi-
nal J l A ( T P ) - 4 7 in the flight computer. In the flight computer, the voltage
activates altitude hold on and off switches Q184 and Q185, providing a
ground return through terminals 51A(TP)-46 and 51-39, to the winding of
relay K301 in the mode coupler. Energizing relay K301 applies a ground
return through K301 contacts 3 and 8 and diode CR402 to terminal 52-39.
The ground return is applied through pedestal controller terminal 51-W
and diode C R 3 to the solenoid winding of ALTITUDE switch S4.

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 a MAIKTENANCE
COLLINS
MANUAL

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A I L E R O N STEERING C O M M A N D
COURSE
IINDICATOR COURSE D A T U M
I
COURSE DATUM
CHANNEL I DIRECTOR
INDICATOR CA HI LAENRNOEL
N RATE A N 0 P O S I T I O N FEEDBACK

-J .NGAGE VOLTAGE
P R O C E S S E O B A N K DATA
I-I
PROCESSED B A N K C O M M A N D r -1
P I T C H A N 0 R O L L A T T I T U D E DISPLAY
I EMERGENCY
I
DISCONNECT

MAGNETIC
COMPASS
I--1
I (PART O F ’ NOTES:

I S E N S I N G UNIT)
R O L L RATE QUSED I N A I R C R A F T WITH INSTALLED ELECTRICAL T R I M S Y S T E M S .

@USED I N AIRCRAFT W I T H O U T I N S T A L L E D ELECTRICAL T R I M S Y S T E M S .

I HEADING DATA T O HEADING SYNCHRONIZER

TPO-468-018

AP-103F/FD-108 Flight Control System, Functional Block Diagram

Figure 15

Nov 1/68 22-03-00

Pages 57/58
 e
COLLINS
MAISTENANCE
v MANUAL

I
- - -I
- - - - - - 1 COUPLER
ELEVATOR T R I M TRIM TO

r
I
---- AIRCRAFT
ELECTRICAL
TRIM SYSTEM

I
I I
r-i
r' - i
I
I --- I I

MIDDL E M I D D L E MARKER
FLIGHT COMPUTER

PITCH RATE
I AUTOPILOT
AMPLIFIER
I! I

TO

MARKER
RECEIVER
I
GLIDE SLOPE DEVIATION
.
m
PITCH
CHANNEL
II
I P R O C E S S E D PITCH D A T A
AC PITCH STEERING

A L T I T U D E ERROR --
EL EVAT O R
CHANNEL
MOTOR CONTROL AIRCRAFT
ELEVATOR
TRIM TAB

I V-BAR P I T C H C O M M A N I
M A N U A L PITCH C O M M A N D
I
I
4
l i
r-7
I --
i
PITCH STEERING C O M M A N D ELEVATOR A I REVATOR
EL AiAFT
NAVIGATION PRIMARY
RECEIVER
VOR LOC DEVIATION a

,,1
RATE A N D POSITION FEEDBACK

U P ELEVATOR
I r-7 I
I
I f I
I - 1 I
I RATE
r - A'-* TO

1
PART O F B A N K DATA [ GYRO Y A W RATE
RUDDER RUDDER STEERING C O M M A N D RUDDER RUDDER
*IRCRAFT
ODE CJNTROL INFORMATION PEDESTAL
VERTICAL
REFERENCE
MODE
1 CONTROLLER I GAIN CONTROL CHANNEL
7 I
SWITCHING
I
I
I I PRIMARY

L TA
CIRCUITS AIRSPEED
1 SENSOR
"
r 1
I INSTRUMENT
I
1 / A1 / 51 -
AMPLIFIER GAIN CONTROL

MANUAL TURN C O M M A N D
1

i l l
-r-1 AILERON
PRIMARY I
~~d

r-1 HEADING DATUH

J'
I MODE
-1

COUPLER
I
VOR/LOC DEVIATION
HEADING DATUM
I

ROLL
CHANNEL
V-B'AR R O L L C O M M A N D
PTI?N:D
ROLL C O M M A N D
-1
VERTICAL
I
AILERON
CHANNEL
.
I
AILERON STEERING C O M M A N D
RATE A N D P O S I T I O N F E E D B A C K
-4
SERVO TO

COURSE D A l U M I N OICATOR REFERENCE

PITCH C O M M A N D
4
--J ENGAGE VOLTAGE

T-
PROCESSED B A N K DATA

PITCH DATA
' I I EMERGENCY
DISCONNECT 1
P I T C H A N D R O L L A T T I T U D E DISPLAY J
I NOTES:

I
S E N S I N G UNIT)
ROLL RATE
R0.L RATE
I QUSED IN AIRCRAFT WITH I N S T A L L E D ELECTRICAL TRIM S Y S T E M S .

L ToJ U S E D I N AIRCRAFT W I T H O U T I N S T A L L E D ELECTRICAL T R I M S Y S T E M S .

HEADING DATA T O HEADING SYNCHRONIZER
TPO- 4329-0 I 7

AP-103F/FD-l08G, FD-1O9G Flight Control System, Functional Block Diagram

Figure 1 6

May 1/67 22-03-00

Pages 59/60
 a
COLLINS
MAIKTEKANCE
w MANUAL

ALTITUDE
ANALOG QUADRATURE GAIN
CONTROLLER ADJUST REJECTION ADJUST

I L A

I I
I
I I
I
I

w-t-$
I
I

NAVl GAT1 ON
RCVF, LIMITER

T
GS
V
I -
DEVIATION

lr-53
GLIDE
SLOPE
BEAM
SENSOR
PITCH
LMAN
~ T C H STEERING
NEEDLE COMMAND
sc GAIN TO
+- INSTRUMENT
ENG. GS I 1 AMPL
1 I

I/
I
I
I
I I
I
I 1 I
VERTICAL I

-
REFERENCE

PITCH
ATTITUDE
Ii
PITCH
A T T I T U DE
INPUT
. ANALOG
ADJUST
PROCESSED PITCH DATA
I t

CIRCUIT

I
I I
I I
I
I
I
I
I
1 - 0
I
STEERING COMMAND
0:ENG*GS -

MODE)

PITCH
COMMAND
I
I
INPUT
CIRCUIT

I MODE COUPLER I I FLIGHT COMPUTER I TPO-1045-034

AP-103F Pitch Channel, Functional Block Diagram (Sheet 1 of 3)

May 1/67 Figure 17 22-03-00
Pages 61/62
 COLLINS
MAIKTENANCE
MANUAL

[TEETOR
--------------
-D'
1
SERVO AMPLIFIER I I
I
I I
I
I
P ,C

FADER
PC PITCH STEERIN( SAWTOOTH
GENERATOR
I
I
I
PITCH I
KNOB

h
a-+@
QUADRATURE
REJECTION

I I! - 1
1- I I
I
I
GAIN CHANGE 2

I
I
'. I
I
I

1 ;

r--
D rd;
CIRCUIT
PROCESSED PITCHDATA
LIMITER
1
LINK 1
PITCH
RATE I I
PITCH
RATE
GAIN
PITCH R A T E SIGNAL

GYRO) ADJUST
t i [GAIN CHANGE I

E L E VATOR
CHANGE GAIN
ADJUST
I UP-ELEVATOR
I I I SIGNALFROM
AILERON CHfNNEL

*
FEEDBACK
INPUT
CIRCUIT
-C PHASE
DETECTOR
- ELEVATOR
H , & ~ ~ ~ A ~ s SERVO FEEDBACK SIGNALS

I - - - - - - - - -
E L E V A T O R POSITION AND R A T E F E E D B A C K S I G N A L

MOTOR C O N T R O L VOLTAGE
TPO-3045-034

AP-103F Pitch Channel, Functional Block Diagram (Sheet 2 of 3)

May 1/67 Figure 1 7 2 2 -03 -00
Pages 63/64
 -
a
C 0LLI N S
MAINTENANCE
MANUAL

I
POSITION
SYNCHRO

I ELEVATOR PRtMARY
SERVO
I
I

ARM UP

T RI M UP
TO AIRCRAFT
E L ECTRICAL
TRIM SYSTEM

,
ARM DOWN

NOTES:
I I I I THE FOLLOWING SYMBOL REPRESENTS A
LOGIC CONDITION.
TRIM COUPLER

7--1
HAVE E L E C T R L A L T R I M SYSTEMS)-

0
2 I N AP-l03F/FD-l09G, TERMINALS 37AND 27
ARE SHORTED TOGETHER.
3 NON-STANDARD ABBREVIATIONS:
GS-GLIDE SLOPE
ALT-ALTITUDE HOLD
TRIM TAB SERVO S C - STEERING COMMAND
(USED IN AIRCRAFT T H A T DO NOT H A V E GA- GO AROUND
TPO-3045-034

AP-103F Pitch Channel, Functional Block Diagram (Sheet 3 of 3)

Figure 1 7

May 1/67 22-03-00

Pages 65/66
 a
COLLINS
MAINTENANCE
v MANUAL

TRACK’

I N AVlG
RECEIVER
AT10 N i-t<-

I COURSE
.INDICATOR I

Ii
I-- FEEDBACK

“i? BANK ATTITUDE SIGNAL

1-1 VERTICAL
REFERENCE
1 BANK
-
PHASE
CONVERTER
-
PROCESSED BANK DATA

I - - - - -
FLIGHT COMPUTER - - - -I

ROLL RATE SIGNAL

D

EXTERNAL BANK COMMAND

E

I GYRO
RATE t ) G >
YAW RATE SIGNAL
F

L-J COMPASS DATA

G

TURN CONTROL SIGNAL

H
TPO-2636-024

AP-103F Roll Channel, Functional Block Diagram (Sheet 1 of 2)

May 1/67 Figure 18 22 -03 -00
Pages 67/68
 COLLINS
MAISTENASCE
w MANUAL

AILERON POSITION AND RATE FEEDBACK SIGNAL

I

) ; " . : : { -E '
I I
'
-
ROLLRATE
GAIN
ADJUST
I
EXTERNALROLL STEERING

I ? .
CHANNEL
GAIN
ADJUST
+ FADER REVERSING
LINK
- j - = DETECTOR
PART
OF
PIA
PART
OF
PIA
SERVO -1
AILERON PRIMARY

Ft *LENGAGE
-
ADJUST
I I1

I I

P
ENGAGE CHANGE GAIN CHANGE 2 SAWTOOTH I
GENERATOR

I I -
1

,."
I
I
TO

II AILERON- -SERVO
AIRCRAFT

- - - - -AMPLIFIER
- 1 AILERONS

->
I
INDICATOR
TURN KNOB EXTERNAL
IN DETENT BANK
+
C-
-<35q BANK DATA
INPUT AMPL
ENGAGE
UP ELEVATOR AND
COMMAND
OUTPUT
CIRCUIT
454>

I
-D

<<36eb CIRCUIT RUDDER COORDINATION

AUTOPILOT AMPLIFIER
I
D-

E-

F-

G-
NOTES:

Q
THE FOLLOWING SYMBOL REPRESENTS A LOGIC CONDITION:
THE CONDITIONS SPECIFIED WITHIN THE SYMBOL CAUSES T H E
SYMBOLIC SWITCH TO BE IN THE POSITION SHOWN. ANY OTHER 0
CONDITION CAUSES THE SWITCH TO BE IN THE OPPOSITE POSITION. A DOT ( e )
INDICATES AN'~ND"FUNCTION WHILE A PLUS (+) INDICATES AN"OR" FUNCTION.
MODE COUPLER NOT USED IN FD-108 INPUT DATA IS APPLIED DIRECTLY
TPO-2636-024

H- TO T H E F L I G H T COMPUTER.

AP-103F Roll Channel, Functional Block Diagram (Sheet 2 of 2)

Figure 1 8

May 1/67 22 -03-00

Pages 69/70
 a
COLLINS
MAIIVTEIVANCE
v MANUAL

- - - - - - 1NOTE:
AUTOPILOT AMPLIFIER
GAIN CHANGE I
--------------------- --- T H E FOLLOWING SYMBOL REPRESENTS
A LOGIC CONDITION;

r 1
1
SENSOR CIRCUIT GAIN CHANGE 2 T O R Q U E WASHOUT C I R C U I T

-I
I
1I INTEGRATOR - 0
6 . C
I
I 1 I
I I'

0 -iLl I
RAMP THE CONDITION SPECIFIED WITHIN T H E
I1GENERATOR SYMBOL CAUSES T H E SYMBOLIC
SWITCH TO B E I N T H E POSITION
ENGAGE CHOPPER
SHOWN. ANY OTHER CONDITION
YAW R A T E SIGNAL CAUSES T H E SWITCH TO BE IN
T H E OPPOSITE POSITION.

I1
-----------
RUDDER SERVO AMPL

SENSING

(ROLL)
ROLL
RATE
INPUT
Cl RCUl T
- ADVERSE
YAW
ADJUST ADJUST
REVERSING
LINK
REVERSING
LINK
TO RUDDER

*
I I I
I

'
I
I
R O L L COORDINATION DATA
FROM AILERON CHANNEL ADJUST NETWORK
SAWTOOTH
GENE RATOR
I

i
PHASE
DETECTOR
I 1 I
CHANGE
NETWORK I-
I
I

I
1 &
I
I----- .i
I
I
I --
PART OF
PIA

-1
AIRCRAFT
RUDDER

RUDDER POSITION AND R A T E FEEDBACK S I G N A L [+

I RUDDER PRIMARY
I SERVO I 1P 0 - 3 1 0 6 - 014

AP-103F Rudder Channel, Functional Block Diagram

Figure 1 9
May 1/67 22-03-00
Pages 71/72
 -
COLLINS
MMAINTEIVANCE

I BANK ATTITUDE
I
I
I
{- x:?zk PITCH ATTITUDE ERROR \
\
)’
I
I
NOTE: PITCH ATTITUDE
I FOR SYSTEMS WITH 344C-ID
INSTRUMENT AMPLIFIERS
SUBSTITUTE CONNECTOR
TERMINALS AS FOLLOWS:
*2:*k
I

+24*
PITCH ATTITUDE RATE I
I PITCH
SERVO PITCH ATTITUDE DRIVE
I
CONTROL XMFR
/
/
/
/
I
BANK ATTITUDE ERROR /
/

I
I 0

I
. .
I
1/
344C- IF
I I I
INSTRUMENT AMPLIFIER
I I FLIGHT DIRECTOR INDICATOR

FD-108, FD-l08G, and FD-1O9G Attitude Display, Functional Block Diagram

Figure 20

May 1/67 22-03-00

Pages 72/74
 a
-
COLLINS
MAINTENANCE

- - ~
RADIO
ALTI~UDE
LLTITUDE
I
I
CONVERTER 200 F T I
I
I
ALTIMETER
RUNWAY
ALTITUDE I
I
SERVO DRIVE--(_(,
FLIGHT
RUNWAY D I RECTOR
IND I CATOR

I ALTITUDE
RATE I
I I
I POSITION I
'.
. I iI
I
\
\

LOCALIZER
I LOCALIZER CONVERTER I LOCALIZER
SERVO
AMPLIFIER
I
I
------
I
~ DEVIATION
I MODE COUPLER 110
I (BACKCOURSE I QUADRATURE
FILTER SERVO DRIVE
I RELAY) 111

I I.
NAVIGATION
RECEIVER

I
POSIT ION
TRANS MlTTER
/
/
/

I
1
I I
INSTRUMENT AMPLIFIER I I
-------I---

FD-109G Runway Localizer and Altitude Display Functional Block Diagram

Figure 21

May 1/67 2 2 -03-00

Pages 75/76
 COLLINS
MAINTENANCE
MANUAL

I
A Z I M U T H C A R D SERVO DRIVE -(1-< -f+
'I
12
I COURSE INDICATOR
I

A Z I M U T H CARD R A T E
a 13
344C-ID
JIB
344C-IF
JIB

(_c< I
14

I \
I I AZIMUTH CONTROL \ 20
I I TRANSFORMER \
I \
\ 18 13
---------- L -----.
A Z I MU T H CARD ERROR
e-
3 4 4 C - IF
I N S T R U M E N T A M P L l F l ER

QENS,
I

e---, I
I
I
HUNDREDS;I

I
DME RECEIVER
L J II
-d17
19
+> i i
'I
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' ERROR CONTROL I I

! I!

!
TRANSFORMER

COMPASS S Y S T E M COMPASS H E A D I N G
II
*(
r-%i
?' - -. ... - . -. . . .. .
'

MODE COUPLER

\
\
7
I
I
I

1
I
I
I

r
I
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NAVIGATION RECEIVER R E F PH t 90° I
I

I V A R I A B L E PH +
e-}A
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L(3i
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I
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DATUM CONTROL
TRANSFORMER
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85

P, l2 S
*,}G

P-
I NAL COURSETODATUM
FLIGHT

COMPUTER VIA
c-q I1
13
I
MODE COUPLER
TPO -4912-014

FD-108, FD-l08G, and FD-1O9G Course and Heading Display, Functional Block Diagram
May 1/67 Figure 2 2 22-03-00
Pages 77/78
 .
COLLINS
MAISTENASCE
MANUAL

,-
QUADRATURE SUPPRESSION
REJECTION SENSOR
NETWORK
TIMER

PART C
OF
PIA

VOR/ LOC
DEVIATION
- CHOPPER
RATE GAIN D

-
NAVIGATION LIMITER ADJUST
RECEIVER
I
I I I I

I '
I
I I
I I
I I
I
I
I
I I
I K203 I
f BACK I I
I COURSE ! I I II
I
I

0
I
I I I
I
I
I SUPPRESSION
I

I COURSE
INDICATOR

p cKF
I
COURSE DATUM
INPUT CIRCUIT AMPL *
QUADRATURE
REJECTION F
AND
3 +l ANALOG ADJUST
NETWORK

1 1 HDGA:?OR
INPUT CIRCUIT

ANALOG ADJUST

I PART OF FLIGHT COMPUTER

FD-108, FD-l08G, and FD-109G Roll Steering Command,

Functional Block Diagram (Sheet 1 of 2)
May 1/67 Figure 2 3 2 2 -0 3 -0 0
Pages 79/80
 COLLINS
MAIYTENANCE
w

NOTES:
THE FOLLOWING SYMBOL REPRESENTS A LOGIC " C l I O N ;

I
B 0 - 1 p c CONE SUPPRESSION
0 T H E CONDITION SPECIFIED WITHIN THE SYMBOL CAUSES T H E SYMBOLIC SWITCH TO BE
I N T H E POSITION SHOWN. ANY OTHER CONDITION CAUSES THE SWITCH TO BE I N THE
OPPOSITE POSITION.
@ A D O T ( 0 ) DENOTES AN AND FUNCTION.
@ NONSTANDARD ABBREVIATION;
-

-r *
HDG HEADING
@ MODE COUPLER NOT USED IN FD-108. SIGNALS ARE APPLIED DIRECTLY TO T H E FLIGHT
COMPUTER.

--I COMPLEMENTARY
FILTER 1 1 1 RADIO COMMAND
LIMITER

7-
J

E
la I

F I v
> PHASE
DETECTOR
- ROLL
STEERING
NEEDLE -
PART
OF
PIA

21
I
V-BAR ROLL
-STEERING COMMAND
GAIN TO INSTRUMENT AMPL
ADJUST

r1
1 GAIN
ADJUST 1
H 1

PART OF FLIGHT COMPUTER TPO-3622-016

FD-108, FD-l08G, and FD-109G Roll Steering Command,

Functional Block Diagram (Sheet 2 of 2)
May 1/67 Figure 23 2 2 -0 3-00
Pages 81/82
 I r
-
COLLINS
MAINTENANCE
MANUAL

I
---- 7 -------- ------ --- I
I
ROLL COMMAND
POSITION TRANSMITTER
FLIGHT DIRECTOR INDICATOR
I
344C-IF

JIB
INSTRUMENT AMPLIFIER

I
POSITION

\
\
iI
f <-@$---\-
I

r----
I
COMMAND
V-BAR ROLL
RATE

V-BAR
\\

I
I

i
[ROLL COMMAND
V-BAR
ROLL STEERING

FLIGHT COMPUTER
- CWPPER .-. OUADRATURE.
REJECTW
I
I
I
I V-BAR ROLL
COMMAND SERVO
DRIVE
<-
I MGI

I
8

I
I
I t
I
I

i
GYRO I I

i
I
I
!I I
I
I
I
I I I I
I I ' I I
V-BAR
PITCH STEERING II IlJIA)63I >,- V-BAR PITCH
<- I

i
CHOPPER -D OUADRATURE
REJECTION I * I
CDMYAND
DRIVE
SERVO
/
,-I
I JIA , I ' I I
A I I V-BAR I
61 *+BAR
PITCH POSITON
OFF-SCALE BIAS
I
I
PITCH COMMAND
SERVO AMPL
I
I I I I P l T C H COMMAND
I - I/ I
I

i
MG3
L-----l I I /
/
I
I
V-BAR PITCH
444
I I I COMMAND RATE

II GMMAND
POSITION
PITCH TRANSMITTER
I

- NOTE:
FOR SYSTEMS WITH 3 4 4 C - I D
INSTRUMENT AMPLIFIER SUBSTITUTE
V-BAR PITCH
POSIT1ON
-'("
x-(
41
I
40
I
i
I
I

CONNECTOR T E R M I N A L S AS FOLLOWS:

344C-ID I 344C-IF

JIB-11 JIA-63
I JIB-8 I JlA-62 1

.. 1

FD-108, F D - l 0 8 G , and FD-1O9G Steering Command Processing, Functional Block Diagram

Figure 24

May 1/67 2 2 -03-0 0

Pages 83/84
 a
COLLIN s
MAINTENASCE
MANUAL

FLIGHT
COMPUTER
I
II
-
PART
OF
PIA I

-
I
ALTITUD E I
OUADRATURE ALTITUDE
ERROR I ANALOG REJECTION GAIN

.---e
ONTROLLER INPUT ADJUST NETWORK ADJUST
CIRCUI T
I

I
I
I
, q @ G S CAP.

I I

GS BEAM
SENSOR GS ARM

I
+/-HpFi%/l+F
PHASE
DETECTOR
PITCH
STEERING
NEEDLE
GAIN
ADJUST
PART
OF

21hS T EVE- RB IANRG PCOMMAND

I
ITCH
TO I N S T R U M E N T
AMPLIFIER

I/ I

I /
I! I
L
BIAS
I
FILTER
I I NOTES:
I . T H E F O L L O W I N G SYMBOL R E P R E S E N T S A
LOGIC F U N C T I O N :

PITCH

REFERENCE INPUT
ANALOG
ADJUST -
A
QUADRATURE
REJECTION
NETWORK
0-F 3
CIRCUIT T H E CONDITION S P E C I F I E D W I T H I N T H E
S Y M B O L CAUSES T H E S Y M B O L SW I T C H TO

- B E I N T H E POSITION SHOWN. ANY OTHER

0 CONDITION C A U S E S T H E S W I T C H TO B E

-1
P I T C H SYNC I N T H E OPPOSITE POSITION.
2. NONSTANDARD ABBREVIATION :
OS - G L I D E S L O P E
G A - GO AROUND

-- 3. A PLUS (t) DENOTES AN OR FUNCTION.

I FLIGHT DIRECTOR
INDICATOR
B9 I I m

I I I TPO-5411-014

FD-108 Pitch Steering Command, Functional Block Diagram

Figure 25

May 1 / 6 7 22-03-00
Pages 85/86
 COLLINS
MAINTEKASCE
w MANUAL

FLIGHT
COMPUTER --1
I

-
PART
OF
I PIA I

CONTROLLER
A L T IT U DE
ERROR
INPUT
I
I
I ANALOG
A DJ U S T
QUADRATURE
REJECTION
NETWORK
- ALTITUDE
GAIN
ADJUST
FIXED
PITCH

CIRCUIT
I -
I
I

I1
I
I
I , q P G S CAP.

GS B E A M
SENSOR GS ARM I
- I
PART
OF
II
4
I
-
I
GS GAIN
CHANGE
P!TCH
LIMITER 4 DETECTOR
PHASE HTfl/;cp
ADJUST I
V-BAR PITCH
S T E E R I N G COMMAND
TO I N S T R U M E N T
AMPLIFIER
?

I
II I/
i BIAS F I LTER
I
I
I NOTES:

I
I
I
I I. T H E F O L L O W I N G SYMBOL REPRE S E N T S A
LOGIC F U N C T I O N :

I
PITCH
VERT I C A L
REFERENCE
ANALOG
- 2UADRATURE
REJECTION

-0
ADJUST
~

CIRCUIT NETWORK THE CONDITION SPECIFIED W I T H I N T H E

I SYMBOL CAUSES T H E SYMBOL S W I T C H TO

1-e
BE I N T H E POSITION SHOWN. ANY OTHER
CONDITION CAUSES T H E S W I T C H TO BE
P I T C H SYNC I N T H E OPPOSITE POSITION.
2. NONSTANDARD A B B R E V I A T I O N :
.PITCH OS - G L I D E SLOPE
G A - GO AROUND

I 3. A P L U S ( + ) DENOTES AN OR FUNCTION.

TPO-3619-014

FD-108G and FD-109G Pitch Steering Command, Functional Block Diagram

Figure 26

May 1/67 2 2 -03-00

Pages 87/88
 COLLINS
MAINTENANCE

w MANUAL

2 8 VDC

r)r
J2

K204
COURSE
SWITCH
FR>Y CR205

-LE
2.f
2 8 VDC

K202
BACK
COURSE COURSE
RELAY
RELAY

I3

NOTES:
NOT APPLICABLE TO FD-108

. @ ALL RELAYS SHOWN IN

DEENERGIZED CONDITION TPO-SIZS -012

FD-108G and FD-109G Back Course Localizer Interlock,

Simplified Schematic
Figure 27

PKCH
SYNCHRONIZER
8102
PITCH ERROR SIGNAL PITCH COMMAND
FROM FLIGHT TO FLIGHT
DlRECfOR INDICATDR COMPUTER

I
I &- -
6-- ?

TPPIl47-012

Pitch Synchronization Circuit, Functional Block Diagram

Figure 28

May 1/67 22 -03 -00,

Page 89
 PEDESTAL C O N T R O L L E R
-
a
COLLINS
MAINTENANCE
MANUAL

SI
MODE SELECTOR
s4 FLIGHT COMPUTER
OGYRO ALTITUDE
HE AD ING

m
0184
a185

ENGAGE
V 747

ALTITUDE
+27.5 VDC 3e CR2
CUTOUT
0
6 ;
CR3
CR4 W
U
KI
ENGAGE
NOTES :
I. EXTERNALLY MOUNTED RELAY I GO AROUND ! TPO -5132- 012
2. A L L SWITCHES AND RELAYS
SHOWN DEENERGIZED.

FD-108 Altitude Hold Interlock, Simplified Schematic

Figure 29

P E D E S T A L CONTROLLER
SI
MODE SELECTOR MODE CO U P L E R
JI
r I<4 0 e T O ALTITUDE CONTROLLER
F L I G H T COMPUTER

47

J-j3
I I
I I
I I
I I
PITCH OFF
. . I GS OFF
C27.5 V D C j e
39 I ALT HOLD ON
; t5
rEc.
- .".;:;u,;
CR2

CUTOUT
+28 VDC*-O-< 39
KI
ENGAGE K301 TPD-4364-012

FD-108G and FD-109G Altitude Hold Interlock, Simplified Schematic

Figure 30

22-03-00 May 1/67

Page 90
 COLLINS
MAISTENASCE
MANUAL

AP - 1 OSF/FD - 1 0 8 , AP - 1 OSF/FD - 1 0 8 G , and AP - 103F/FD - 109G

Flight Control Systems - Troubleshooting
1. GENERAL.

Troubleshooting information is presented in tabular form with the preflight and flight test
procedures in the adjustment/test section of this manual.

May 1/67 22-03 -00

Page 101/102
 a
COLLINS
MAISTEKANCE
MANUAL

-
A P - 103F/FD 1 0 8 , AP - 1 OSF/FD - 1 0 8 G , and AP - 1 OSF/FD - 109G
Flight Control Systems - Servicing
(Not Applicable)

May 1/67 22-03-00

Pages 301/302
 a
COLLINS
MAIKTENANCE
ww MANUAL

AP - 1 OSF/FD - 1 0 8 , AP - 1 0 3F/FD - 1 O8G, and AP - 1 OSF/FD - 1 09G

Flight Control Systems - Removal /Installation

1. GENERAL.

This section provides information for installing the Flight Control Systems. The informa-
tion includes unpacking, aircraft wiring, and mechanical preparation. Installation drawings
and logic module strapping information are also included.

2. PREPARATION FOR INITIAL INSTALLATION.

A. Unpacking.

Unpack the equipment carefully and inspect each unit f o r possible shipping damage.
Each unit of the Flight Control Systems has been inspected and tested by the manu-
facturer p r i o r to shipment. All claims f o r damage in shipment should be filed promptly
with the transportation company. If damage claims a r e filed, save the original
shipping containers and packing materials.

B. Aircraft PreDaration.

(1) Preliminary Preparations.

(a) General.
Each Flight Control System installation is designed to meet the requirements
of a specific aircraft. Before equipment installation can be completed,
several requirements must be considered if the installation is to meet FAA
certification limits.

(b) 334C-3( ) P r i m a r y Servo Torque Limits.

To determine the required servo-torque limits, a calculation must be made

of the gearing from the servo outputs to the aircraft control surfaces.
Design criteria for gearing calculations are contained in the following steps:

1. Minimum stick force p e r g, as measured at the control column in the ele-

-
vator channel.
. . -2. Minimum wheel f o r c e f o r maximum roll rate, as measured at the control
wheel in the aileron channel.

-
3. Minimum force required f o r limiting rudder deflection o r yaw angle.

-
4. Torque adjustment limitations f o r the primary servos provide f o r a min-
imum limit of 30 inch/pounds and a maximum of 245 inch-pounds, with
a desired nominal torque of 150 inch-pounds.
5. F o r steps 1,2, and -
- 3 above, the primary-servo output command limitations
-
are *40 degrees.
May 1/67 22 -03-00
Page 401
 COLLINS
MAINTENAXCE
MANUAL

-
6. Maximum cable travel allowed when using the 351B-3 o r 351B-3A Servo
Mount is &15.5 inches to provide total deflection of the aircraft control
surface.

-7. Maximum lever a r m travel allowed when using the 351B-3B o r 351B-3C
Servo Mount is a function of push-rod installation design. During servo-
mount location, c a r e should be taken when determining tolerance build-
up s o that travel of the control surface is not limited, and so that the
lever a r m push-rod assembly does not travel overcenter at maximum de-
flection of the control surface.

(c) 351B-3( ) Servo Mount Installation Requirements.

After final maximum torque limits have been determined, a s t r e s s analysis
of the servo-mount installation must be made to satisfy FAA requirements.
The following conditions should be met.

-1. A cable preload minimum tension of 80 pounds is required.

-
2. From the center line of the servo-mount capstan to the center line of the
bull wheel, a minimum distance of 18 inches is desired.

(2) Interconnecting Cabling.

Figures 439 through 465 are interconnection wiring diagrams for typical AP-l03F/
FD-108, AP-103F/FD-l08G, and AP-103F/FD-l09G Flight Control Systems in-
stallations. The diagrams include wiring terminations f o r associated equipment
items. Associated equipment items are matters of customer preference and of
individual installation requirements. Wiring diagrams f o r specific a i r c r a f t in-
stallations that meet customer requirements will be provided separately upon
written request to Collins Radio Company, Field Service Department, Cedar
Rapids, Iowa.

NOTE: Optimum performance of Flight Control Systems equipment will result

if a few precautions are observed. All p a r t s of the aircraft electrical
system, such as charging generator, ignition system, etc. should be
bonded and shielded. The Flight Control Systems cables should not be
installed n e a r heavy current-carrying circuits, pulse transmitting equip-
ment, o r other sources of noise.

The input power source is divided to serve four separate functions: heading,
runway, command, and attitude power. The heading power to the instrument
amplifier and flight computer must be the same phase as the power supplying
the associated gyrostabilized magnetic compass. The attitude power to the above
equipment must be the same phase as the power to the associated vertical
reference .

22 - 03 - 0 0 May 1/67
Page 402
 (3) Mechanical Preparation.
-
a
COLLINS

(a) 12lA-2 Emergency Disconnect.

MAIKTENANCE
MANUAL

The 121A-2 Emergency Disconnect is mounted s o that both the pilot and
copilot have easy a c c e s s to the switch. Mounting details are provided in the
outline and mounting dimensions, figure 401.

(b) 161A-1A T r i m Coupler.

The 161A-1A T r i m Coupler is contained in a standard 1/4 ATR short case

that is installed in an aircraft equipment rack. The 16lA-1A is mounted in
a 390R-5B Hard Mount. Additional details a r e given in the outline and
mounting dimensions, figure 402.

(e) 161E-1 Mode Coupler.

The 161E-1 Mode Coupler is mounted in a Collins 89OP-1 Shockmount.
Additional mounting information is available in the outline and mounting
dimensions, figure 403.

(d) 327D-1W T r i m Indicator..

The 327D-1W T r i m Indieator is mounted on the aircraft pedestal immediately

above the 614E-2G (or 614E-2G1) Pedestal Controller. The 327D-1W is
positioned so the indicators are clearly visible to the pilot and the copilot.
Mounting details are shown in outline and mounting dimensions, figure 404.

(e) 329B-7( ) and 329B-8G Flight Director Indicator.

The Flight Director Indicator should be mounted directly above the course
indicator and should be positioned laterally near the center of the pilot's
line of vision. The Flight Director Indicator should be positioned vertically
s o that the top of the instrument remains visible when the pilot's seat is in
the highest, and most forward, position used. The fore-aft center line of the
instrument should be at an angle of 14 to 30 degrees from the pilot's line of
vision. The 14- to 30-degree angle should be provided regardless of air-
craft instrument panel angle. See figures 405 and 406, outline and mounting
dimensions.

(f) 331A-6A Course Indicator.

The 331A-6A Course Indicator should be mounted close to, and slightly below,
the pilot's normal line of vision through the cabin windscreen. When mounted
in this manner, the COURSE and HDG controls are within easy reach,

The 331A-6A can be front o r rear mounted using clamps o r screw fastenings.
A mooring plate, Collins p a r t number 553-6590-004, is required for either
front o r rear mounting. An adapter plate, Collins p a r t number 553-6594-003,
is used when front mounting the 331A-6A on a panel that is tapped for mount-
ing screws. See course indicator outline and mountidg dimensions, figure
407, for additional mounting details.

May 1/67 22-03-00

Page 403
 COLLINS
MAINTENANCE

wv MANUAL

(g) 332G-2 Rate Gyro.

NOTE: The 332G-2 Rate Gyro must be solidly mounted to the aircraft frame.
Mounting must be rigid enough to eliminate metal warp in the mount-
ing bracket, which may be caused by airframe bending.

The 332G-2 Rate Gyro is aligned with the yaw axis of the aircraft. The 332G-2
should be mounted as close to the 345A-4B Sensing Unit as possible. Mount-
ing details are provided in figure 408, outline and mounting dimensions.

(h) 334C-3( ) P r i m a r y Servo.

The 334C-3( ) P r i m a r y Servo is mounted in the 351B-3( ) Servo Mount.

Customer preference determines placement of the 334C-3( ) i n the aircraft.
Mounting details a r e provided in figure 409, outline and mounting dimensions.

(i) 334D-2-33( ) T r i m Tab Servo.

The 334D-2-33( ) T r i m Tab Servo must be solidly mounted in the aircraft.
Customer preference determines placement in the aircraft, but c a r e must be
taken to ensure that the t r i m system friction level at the tie-in point is not
less than 10 pounds, as measured at the t r i m servo sprocket o r capstan.
Mounting details are given in figure 410, outline and mounting dimensions.

(j) 344C-1D Instrument Amplifier.

The 344C-1D Instrument Amplifier is contained in a standard 1/4 ATR short

case that is mounted in a 390D-6A Shockmount, and installed in an aircraft
equipment rack conforming to ARINC Specification No. 404. The 344C-1D
should be mounted near the 562A-5G Flight Computer. Additional mounting
details are provided in figure 411, outline and mounting dimensions.

(k) 344C-1F Instrument Amplifier.

The 344C-1F Instrument Amplifier is contained in a standard 1/4 ATR short

I case that is mounted in the Collins 8905-2 Shockmount, and installed in an
equipment rack conforming to ARINC Specification No. 404. The 344C-IF
should be mounted near the 562A-5G Flight Computer. Additional mounting
details a r e available in figure 412, outline and mounting dimensions.

(1) 345A-4B Sensing Unit.

NOTE: The 345A-4B Sensing Unit must be rigidly mounted to prevent

generation of operational noise. Mounting requirements are the
same as f o r the 332G-2 Rate Gyro.

The 345A-4B Sensing Unit is mounted with the applicable rate gyros aligned
with the pitch and roll axes of the aircraft. The 345A-4B should be mounted
as close to the 332G-2 Rate Gyro as possible. Mounting details are given in
figure 413, outline and mounting dimensions.

22-03-00 Nov 1/68

Page 404
 -
a
COLLINS

351B-3( ) Servo Mount.

MAINTER’AKCE
MANUAL

The 351B-3( ) Servo Mount houses the 334C-3( ) P r i m a r y Servo. The 351B-
3( ) must be positioned in the aircraft so enough space is provided for re-
moval of the 334C-3( ) P r i m a r y Servo without removing the 351B-3( ).
Mounting details are provided in figures 414 and 415, outline and mounting
dimensions.

390D-6A Shockmount.

The 390D-6A Shockmount is used to mount the standard 1 / 4 ATR short-cased

344C-1D Instrument Amplifier. Mounting details are given in figure 416,
outline and mounting dimensions.

390R-5B Hard Mount.

The 390R-5B Hard Mount is used to mount the standard 1/4 ATR short case-
enclosed 161A-1A T r i m Coupler. The 390R-5B is installed in an aircraft
equipment rack. Mounting details a r e provided in figure 417, outline and
mounting dimensions.

562A-5G Flight Computer.

The 562A-5G Flight Computer is contained in a 1/4 ATR short case that is
designed to be mounted in an aircraft equipment rack. The 562A-5G is
dual-mounted with the 562C-4; either shockmounted in the 790M-1 Shock-
mount (then installed in a rigid equipment rack), o r hard mounted in the
790M-1A Hard Mount (and installed in a shockmounted equipment rack). The
562A-5G should be installed close to the 344C-1F Instrument Amplifier.
Mounting details f o r the 562A-5G are given in figure 418, outline and mount-
ing dimensions.

562C-4 Autopilot Amplifier.

The 562C-4 Autopilot Amplifier is dual-mounted with the 562A-5G Flight

Computer (refer to paragraph 2. B. (3) (p)). Mounting details are given in
the outline and mounting dimensions, figure 419.

590A-3E Altitude Controller.

The 590A-3E Altitude Controller is contained in a standard 3/8 ATR short

case. The 590A-3E is mounted in a 79OC-1 Shockmount and installed in a
standard aircraft equipment rack. The 590A-3E may be located in any con-
venient place. The static line must originate at the port, and may not
exceed 20 feet f o r 1/4-inch tubing (ID = 5/16 inch). If the static p r e s s u r e
varies with pitch attitude, the static port shall be located so that a pitch-down
attitude will result in an increase in static pressure. All values and con-
nections shall have an ID approximately equal to the ID of the tubing used to
ensure free movement of the air. Mounting details are given in figure 420,
outline and mounting dimensions.

May 1/67 22-03-00

Page 405
 COLLINS
MAINTENANCE
w MANUAL

(s) 590B-2 Airspeed Sensor.

The 590B-2 Airspeed Sensor is mounted directly to the airframe, but may be
located in any convenient place. The static line must originate at the inter-
section of the two static lines from the dual ports, o r at the port itself if only
one port is used. The static line may not exceed 21) feet for 1/4-inch tubing
(ID = 5/16 inch). If the static p r e s s u r e varies with pitch attitude, the static
port shall be located s o that a pitch-down attitude will result in a n increase
in static pressure. All values and connectors shall have an I D approximately
equal to the ID of the tubing used to ensure f r e e movement of the air. Mount-
ing details are provided in figure 421, outline and mounting dimensions.

(t) 614E-2F Pedestal Controller.

The 614E-2F Pedestal Controller is mounted on the aircraft pedestal, and
placed s o the pilot and copilot have easy access to all switches and controls,
and so all switches, controls, and indicators are in clear view. Mounting
details a r e shown in figure 422, outline and mounting dimensions.

(u) 614E-2G( ) Pedestal Controller.

The 614E-2G (or 614E-2G1) Pedestal Controller is mounted on the aircraft

pedestal just below the 327D-1W T r i m Indicator (or equivalent) and placed s o
the pilot and copilot have easy a c c e s s to all switches and controls, and s o
all switches, controls, and indicators a r e in clear view. Mounting details
are given in figure 423, outline and mounting dimensions.
(v) 79OC-1 Shockmount.
The 79OC-1 Shockmount is used to mount the standard 3/8 ATR short case of
the 590A-3E Altitude Controller. Mounting details are provided in figure
420, outline and mounting dimensions.

(w) 790M-1 Shockmount.

The 790M-1 Shockmount is a dual mount used to mount the standard 3/8 ATR
short case of the 562C-4 Autopilot Amplifier and the standard 1/4 ATR short
case of the 562A-5G Flight Computer. The 790M-1 is used with aircraft
equipment mounts of rigid construction. Mounting details a r e given in figure
424, outline and mounting dimensions.
(x) 7-90M-1A Hard Mount.
The 790M-1A Hard Mount is a dual mount used to mount the standard 3/8 ATR
short case of the 562C-4 Autopilot Amplifier and the standard 1/4 ATR short
case of the 562A-5G Flight Computer. The 790M-1A is used with shockmounted
a i r c r a f t equipment racks. Mounting details are shown in outline and mount-
ing dimensions, figure 425.
(y) 8905-2 Shockmount.
The 8905-2 Shockmount is used to mount the 1/4ATR short case of the 344C-1F
Instrument Amplifier. Mounting details a r e given in the outline and mounting
dimensions, figure 426.

22- 03-00 Nov 1/68

Page 406
 -
a
COLLINS
MAINTENANCE
MANUAL

AP-103F 121A- 2 522-1216-001

-.I28 DIA. AND COUNTERSINK

F'7
zl

F
30"

121A-2 Emergency Disconnect, Outline and Mounting Dimensions

Figure 401

May 1/67 22 -03 - 00

Page 407
 -
a
COLLINS MAINTENANCE
MANUAL

EQUIP. T Y P E PART NUMBER

161A-IA 5 2 2 - 4 5 1 7-0 01

NOTES
I CENTER OF GRAVITY MEASUREMENTS , 2 2 1 - C . 0 0 5D I A F O R S P R I N G
LOADED R E A R H O L D DOWN PIN
ARE A P P R O X I M A T E .
2. WEIGHT 3 0 L B S

\
\ -+ k.500i.005
1 8 7 k 0 0 5 D I A . 2 HOLES
PER ARlNC I N D E X
CODE 2

i CONNECTOR - C A N N O N D P A - 3 2 - 3 4 P - I
( 3 7 0 - 2 0 7 1 - 0 0 ) MATES W I T H DPA 3 2 - 3 3 s - 3
(370-2072- 00)

T P O - 4 9 2 3- 0 I 2

161A-1A Trim Coupler, Outline and Mounting Dimensions

Figure 402

22- 03 -00 May 1/67

Page 408
 e
COLLINS
MAIKTEKAKCE
w MANUAL

3$ APPROX y

CONNECTOR, PYLE
M S 2 4 2 6 4 - R - 2 2 - 8 - 55FlOX
(CPN 359-0035-00)-\

CONNECTOR, AMPHENGL
M S 2 4 2 6 4 - 2 2 - 8 - 55PNX
I I
(CPN 359-4011-00)

I 1
772-4764-001

I
~

I I I 00
m

I ~

-e- 8 -~
0- e-
HGUUTING HOLE PATTERN

161E-1 Mode Coupler and 89OP-1 Shockmount,

May 1/67 Outline and Mounting Dimensions 22-03 -00
Figure 403 Pages 409/410
 N
N.

,I: I

In

:
L W
n

.I9 R 1
/
y

1.
,
I

4.05 MAX
.

A 4 D l A HOLE AND C'BORE, .I90 DlA X .062 DEEP,

r . 7 5 71.03 ,
4

C1240-01-1
6 MTG HOLES

UMBER

327D-1W Trim Indicator, Outline and Mounting Dimensions

Figure 404

May 1/67 22 - 03 - 0 0
Page 411
 6
-
a
COLLINS

R T Y P 16 PLACES
MAIYTENANCE
MANUAL

CONTROLS
\

1.250 M A X y ] l - 7 3 Mr$i A MS24264R-22-8-55P- 7 X

MATES WITH
MS24264R-22-8-55P-6X
MATES WITH
.I30 2.005 M S 2 4 2 6 6 R - 22- B - 5 5 8 - 7 MS24266R-22-8-55s-6
4 .220*.005 0 Q
NOTES:
0 DIMENSIONS APPLY TO OUTSIDE OF CASE AN0 BEZEL EXTENSION.
@ MOUNTING ARRANGEMENTS-FRONT MOUNTING: USE MARMAN DIV,
AEROQUIP C O W CLAMP, (COLLINS PART NO. 139-3157-00): OR USE
ADAPTOR PLATE AND MOORING PLATE I N ACCORDANCE WITH ARlNC
SPEC NO. 4 0 8 (COLLINS PART NO. 5 5 3 - 6 5 9 4 - 0 0 3 AND 5 5 3 - 6 5 9 0 - 0 0 4 ) .

LACES
1
4.010+.010 TYP REAR MOUNTING: USE MOORING PLATE I N ACCORDANCE WITH ARlNC
SPEC N 0 . 4 0 8 (COLLINS PART NO. 5 5 3 - 6 5 9 0 - 0 0 4 ) .
@ FOR CLAMP MOUNTING, THE HOLES FOR THE 8 - 3 2 ADJUSTING SCREWS
MUST BE ,218 DIA.
2 PLACES
2. 005 2.010 T Y P
@ WEIGHT: 3 2 9 6 - 7 - 5 . 0 L B MAX.
3 2 9 B -7 ( 1-5.2 L B MAX.

1.930f .005 TYP Q EQUIPMENT TYPE COLLINS PART NO.

3 2 9 8 -7 5 2 2 -3 1 2 2 -0 0 4
-
522 3 1 2 - 0 0 5
5 2 2 -3 1 2 2 -0 0 6
5 2 2 -3 1 2 2 -0 0 8
5 2 2 - 3 1 2 2 -0 0 9
3 2 9 8 -7 A 522-3206-004
522-3206-005
-
522 3 2 0 6 - 006
-
522 3206-007
-
5 2 3206-008
522- 3206-009
3 2 9 0 - 7C 522- 3 4 8 7 - 001
522-3487-002
522-3487-003
522 -3487- 004
522 - 3 4 8 7 - 0 0 6
3 2 9 8 -7 F 5 2 2 -3 6 1 8 - 001
522-3618-003
,177 DIA T Y P 4 HOLE
3 2 9 B -7 F l 5 2 2 -3 7 5 2 -0 0 1
3298-70 5 2 2 -3 6 6 7 -0 0 1
3296-7J -
5 2 2 3 8 6 7 -0 0 1
522 -3867-002
3298-7K 522 - 3 8 7 7 - 0 0 1
3298-7M 522-3908-001
PANEL CUTOUT DETAIL

329B-7( ) Flight Director Indicator, Outline and Mounting Dimensions

Figure 405

22- 03 - 00 May 1/67

Page 412
 a
COLLINS
MAIKTENANCE
MAYVUAL

7M S 2 4 2 6 4 R - 2 2 - 6 - 5 5 P 7 X MATES
WITH M S 2 4 2 6 6 R - 2 2 - B - 5 5 S 7
M S 2 4 2 6 4 R - 2 2 - 8 - 5 5 P l O X MATES
WITH M S 2 4 2 6 6 R - 2 2 - B - 5 5 S I O

\ F 4 . 9 2 0 M A X -
/

rfl- --
.060 C.030 R
TYP 8 PLACES
PANEL CUTOUT

t
\

I"s
I N

-~ !+j
I
f&4 MTG HOLES AS REP0
(THRU OR TAPPED) FOR
NO, 10-32 UNF-PA SCREWS.
45' TYP 4 PLACES 45O TYP 4 PLACES

MS 2 4 2 6 4 R - 2 2 - 8 - 5 5 P 6 X MATES
WITH M S 2 4 2 6 6 R - 2 2 - 8 - 5 5 8 6

2 0 9 DIA CBORE ,375 DIA X &

T
r---
i- 3: APPROX - '1
I
I
I
I
P-
I
I
- _-
I
I
I + CG
-
-
I
I
I
I
I -
. 3 7 5 G - L - 7 i MAX , 7 9 5 MAX
1.400 MAX

NOTES:
WEIGHT: 8.5 LB MAX.
@ THIS DIAGRAM A P P L I C A B L E TO:
COLLINS PART
NUMBER

3296-EA 5 2 2 -3 7 0 0 - 001
522-3700-002
522-3700-003
522-3700-004
522-370e006
3296-86 522-4194-001
3296-BC 522-4063-001
522-4063-003
3298-8F 522-4430-001
522-4430-002
522-4430-003
522-4430-005
C1177-02-4
3296-8G 522-4529-001

329B- 8G Flight Director Indicator, Outline and Mounting Dimensions

Figure 406 -

May 1/67 22 -03 -00

Page 413
 a MAINTENAKCE
COLLINS
v

-4.060 t ,010 TYP-

2 PLACES
MATES WITH
MATES WITH
MS24266-R-22-E-55s-8

F 2.005
2 PLACES
pLr
3.860 f ,005TYP

T Y : t.O1O T f ,005
1.930
2 PLACES
Y q NOTES:

Q
I DIMENSION APPLIES TO OUTSIDE OF
CASE AND B E Z E L EXTENSION,
MOUNTING ARRANGEMENTS-FRONT
MOUNTING: USE MARMAN DIV, AEROPUIP
CORP. CLAMP, PART NO. 54622 i OR USE
ADAPTER P L A T E AND MOORING P L A T E
IN ACCORDANCE WI T H ARINC SPEC. NO. 408.
L . 0 9 5 R MAX T'YP REAR MOUNTING: USE MOORING P L A T E IN
8 PLACES ACCORDANCE WI T H ARINC SPEC NO. 408
I
Q FOR CLAMP MOUNTING,THE HO L E S FOR
T H E 8-32 ADJUSTING SCREWS MUST B E
.216 DIAMETER.
Q WEIGHT: 5.3 L B MAX.
Q
4 PLACES
522-2782-004

522-4279-002
4 HOLES 522-4279-003
PANEL CUTOUT DETAIL
C949-16-3

331A-6A Course Indicator, Outline and Mounting Dimensions

Figure 407

22 - 03- 00 May 1/67

Page 414
 COLLINS MAINTENASCE
w MANUAL

I
0 .+--
.I
P -3 I!
16 32
NOTES
QTHlS DRAWING APPLICABLE TO.
EQUIP

3320-2 229-0236-000

@WEIGHT: 1.8 POUNDS MAXIMUM

L . 3 - M1A X
64

332G-2 Rate Gyro, Outline and Mounting Dimensions

Figure 408

May 1/67 22- 03- 00

Page 415
 -
COLLINS
MAINTEKAKCE
MAKUAL

@ WEIGHT: I1 POUNDS MAXIMUM.

CAPSTAN DATA
-
SERVO MOUNT PITCH DIA OUTSIDEDIA CABLE DIA MAXCABLETRAVEL
3516-3 3.000 3.250 IN. +1551N.

3518-3A 3 ,000 3.250 &IN. t15.51N

334C-3( ) P r i m a r y Servo with 3 5 1 B - 3 and 351B-3A Servo Mount,

Outline and Mounting Dimensions
Figure 409
22- 03 - 00 May 1/67
Page 4 1 6
 a
COLLINS
MAINTEIVANCE
w 3IANUAL

f
N'a
I
c

NOTES:
I FOR GULFSTREAM INSTALLATION, 334D2-33A, THESE
DIMENSIONS ARE REDUCED BY
32
x.
@ MAXIMUM TORQUE: 55 L B IN.

33341)-2-33A SPROCKET: 2 4 TEETH, DIAMOND 8WRENOLD 110500 CHAIN.

3 3 4 0 - 2 - 3 3 6 SPROCKET: 15 TEETH, DIAMOND 88/RENOLD 110500 CHAIN
334D-2-33C SPROCKET: 30 TEETH, AMERICAN STANDARD N0.25 CHAIN
@ APPROXIMATE CENTER OF GRAVITY LOCATIONS.

I EQUIP
TYPE I PART
NUMBER I 5 DISTANCE REQUIRED FOR REMOVAL OF MOTOR AND GEAR UNIT. UNIT
MAY BE REMOVED WITHOUT DISTURBING MOUNT.
6 SEVEN PIN CONNECTOR AN3102A-16S-IP (MATING CABLE
CONNECTOR AN3106A-16S-IS).
@ CHAIN GUARD POSTS MAY BE POSITIONED AT 30° INTERVALS.
8 FOR 334D-2-330: SPROCKET PITCH DIAMETER IS 2.393 IN., USED
WITH CHAIN TYPE NUMBER 25 OF AMERICAN STANDARD. FOR 334-2-33F:
SUBSTITUTE CAPSTAN FOR SPROCKET, CAPSTAN PITCH DIAMETER
2.75 IN., USED WITH 0.0625 IN. CABLE.

334D-2-33( ) T r i m Tab Servo, Outline and Mounting Dimensions

Figure 410

May 1/67 22 -03-0 0

Pages 417/418
 -
a
COLLINS
MMAINTENAR’CE
MANUAL

TYPE DPA-32-34P-I
(COLLINS PART NO.
370- 2071 -00)
MATES WITH
DPA-32-33s-3 MAX
(COLLINS PART NO.
370-2072-00)

NOTES
SIADED AREA CONTAINS ,125 MA. VENTILATING
HOLES.
@ PI AND P 2 ARE THE SAME PART NUMBER. -
O W E I G H T 7.4 LB MAX.
@
EOUlPWlENT COLLINS
TYPE NUMBER PART NUMBER

344C-1D Instrument Amplifier, Outline and Mounting Dimensions

Figure 411

May 1/67 22-03-00

Page 419
 a
COLLINS
MAIKTENANCE
w MANUAL

1L+L-
8
EauiP
TYPE

- 32
I PART
NUMBER I

-, I
N
I

.221 DIA HOLE

FOR GUIDE PIN-

/CANNON DPXZMAS-A67P-A67P-34B-0201
MATES WITH
CANNON DPX2MAS-A67S-A67S-33B-0201

NOTES'
I. POWER REQUIREMENTS: I IJVAC, 4OOCPS.
2. COOLING AIR REQUIRED- NONE.
3. OUTLINE AND INSTALLATION DATA GIVEN IS IN
ACCORDANCE WITH ARlNC CHARACTERISTIC NO. 404. TPO-3618-014

344C -1F / l G Instrument Amplifier, Outline and Mounting Dimensions

Figure 412

22-03-00 Nov 1/68

~age::'420
 COLLINS
MAINTENANCE
v MANUAL

M S 3102A-16S-IP
CONNECTORS

NOTES:
THIS DRAWING APPLICABLE TO:

EQUIP

345A-48 522-3851-000

@ WEIGHT: 4 . 2 POUNDS MAXIMUM.

-___ 7--

l7 1 4 . 0 6 2 ~ 1 ' ALLOW 2$ INCHES

FOR PLUG REMOVAL

-55-
4$APPROX d- I
I

t
10

0 0

UP

345A-4B Sensing Unit, Outline and Mounting Dimensions

Figure 413

22-03-00
May 1/67 Pages 421/422
 a NOTES:
4
Q SERVO MAY BE REMOVED WITHOUT
DISTURBING SERVO MOUNT.

+
@ 5.5 INCHES CLEARANCE NECESSARY TO
REMOVE SERVO FROM SERVO MOUNT.

@ THE SERVO MOUNT IS FASTENED FLAT

WITHIN 0 . 0 0 3 INCH TO THE SURFACE.
.I260 DIA

I- APPROX

DIM.
PN X Y TYPE
554-2624-005

554-2625-005 1 3.75

5.25
6

7; 1 3516-38

351B-3C 1
-I 1.547 f ,053 k-
4f I

32

FSELF-ALIGNING
BALL BEARING 1

, X
I f
9
-1%
- $ , le Q
W

L
-d
32 -_$ DIA,4HOLES
i 4: MAX -1

351B-3B and 351B-3C Servo Mount, Outline and Mounting Dimensions

Figure 414

May 1/67 22-03-00

Pages 423/424
 +. ,0005 DIA I
,1260 .oooo
--c
I- I~APPROX

. I APPROX

. 1
I

I n N0.6-32 N C - 2 8 TAPPED HOLES,QTY 18

I 20OAPART ON A 3.500 DIA B.C.

V
32 N F - 3 B TAPPED H O L E S , QTY 4
1.9687 D I A B.C.

I EQUIPMENT
TYPE I PART NUMBER

3518-3E 772-5027-001

+ 1
2.937- $‘ DIA,4HOLES

351B-3E Servo Mount, Outline and Mounting Dimensions

Figure 415

May 1/67 22-03 -00

Pages 425/426
 COLLINS
MAIKTEKANCE
%w MANUAL

+-----e 4---

I W

4
199 2 005 D I A - 8 HOLES CLEARANCE
FOR NO 8 BASE P L A T E MTG SCREWS

IO; I
-9 &fy
‘7-
4 h-i (REF)

CONNECTORS P I AND P 2
CANNON D P A - 3 2 - 3 3 s - 3
COLLIN S PART NO. 3 7 0 - 2 0 7 2 - 0 0 1

3
-38-

BASE PLATE
NOTES:

INDEX P I N L E T T E R CODE SHOWN AS V I E W E D FROM FRONT O F SHOCKMOUNT.

@ POSITION OF INDEX P I N HOLE P A T T E R N W I T H REFERENCE TO MOUNTING R A I L

SURFACE IS THE SAME FOR E I T H E R A S I NG L E OR D O U B L E PLUG A P P L I C A T I O N
@ T H I S DRAWING A P P L I C A B L E TO:

TPO-5426-0 I 2
@ WEIGHT: 1.3 POUNDS MAXIMUM.

390D-6A Shockmount, Outline and Mounting Dimensions

Figure 416

May 1/67 * 22-03-00

Page 427
 COLLINS
MAINTENANCE
w MANUAL

DPA-32-33s-3370-m72-001
t
MATES WITH DPA-3-32-34P-I
FRAME MOUNTING
SURFACE
1: +I

Pn!

--$----

,147 DIA, 4 HOLES

TPO-4924-013

390R-5B Hard Mount, Outline and Mounting Dimensions

Figure 417

22- 03-00 May 1/67

Page 428
 a
COLLINS
MAINTEKAKCE
w MARUAL

EQUIP PART
TYPE NUMBER

5628% 522-3207-003

,221
FOR
U

HOLDDOWN

k5EAPPROX
CANNON DPX2-57P57P-345-0201
MATES WITH
CANNON DPX2-57S57S-338-0001
12 5 MAX
NOTES:
I. POWER REQUIREMENTS: I ISVAC, 4OOCPS, 52VA MAX.
2. COOLING AIR REQUIRED- NONE.
3. OUTLINE AND INSTALLATION DATA GIVEN IS IN ACCORDANCE
WITH AlRlNC CHARACTERISTIC NO. 4 0 4 .
4. WEIGHT 8.0 LBS.

562A-5G Flight Computer, Outline and Mounting Dimensions

Figure 4 1 8

May 1/67 22- 03-00

Page 429
 COLLINS
MAIKTENANCE
w MANUAL

/ r 6 APPR0X-I
12 MAX
REAR
I I NOTES:
CANNON CONNECTOR
DPX2MAS-67P67P-346-0201 NO COOLING AIR REQUIRED.
(COLLINS PART NO. 3 7 0 - 5 3 7 8 - 0 0 0 )
MATES WITH CANNON CONNECTOR OUTLINE AND I NS T A L L A T I O N DATA GIVEN
DPX2MAS-67S67S-336-0201 IS IN ACCORDANCE WITH ARINC
(COLLINS PART NO. 3 7 0 - 5 3 7 3 - 0 0 0 ) CHARACTERISTIC N U M B E R 404.

* INDICATES DIMENSIONS THAT ARE

NOMINAL A RlNC REFERENCE DIMENSIONS.
THIS UNIT WI L L ENGAGE IN A MOUNTING
RACK CONSTRUCTED TO ARINC NUMBER
NUMBER 404 SPECIFICATIONS.
WEIGHT: 10.5 POUNDS MAXIMUM.

APPROX

562C-4 Autopilot Amplifier, Outline and Mounting Dimensions

Figure 419

22 - 03 - 00 May 1/67
Page 430
 COLLINS
MAIKTENANCE
v MANUAL

,l5% MAX
1

SWAY S P
T I P BOTH

162 DIA. 2 MTG HOLES

*1.414t ,015 + /- '

DETAIL A
SCALE 111
CG

CG.

NOTES
I CANNON CONNECTOR D P i m - 4 6 - 3 3 5 - 0 0 0 3 O N S H O C K Y O U N T ( C O L L I N S PART NUMBER 3 7 0 - 5 2 1 6 - 0 0 )
MATES WITH C A N N O N - O P X B - 4 5 - 3 4 P - 0 0 0 3 ON A L T I T U D E C O N T R O L (COLLINS RART NUMBER 3 7 0 - 5 2 0 6 - 0 0 )
@ MOUNTING PER A R l N C S P E C I F I C A T I O N 404
@ STLllC L I N E WST BE FLEXIBLE ADJACENT TO T I E G W N E C T I O N TO THE UNlI
@ CENTER OF GRAVITY N Q I IS 59OA-Y! ALTITUY COlllROLLER ONLY.
CENTER OF GRAWTI ma z IS THE COYBINED C.G. I5 9 0 ~ 3 )A L n i u M CONTROLLER AND 7 9 ~ - ISHOCKMOUNT.)
@ MIS DRIIMNG APPLICABLE TO

590A-3E Altitude Controller and 79OC-1 Shockmount,

Outline and Mounting Dimensions
Figure 420

May 1/67 22-03-00

Page 431
 a
COLLINS MAINTEKAKCE
w MANUAL

NOTES:
QTHIS DRAWING APP-
p 2.63 MAX -q LICABLE TO:

PORTS $ - 2 7 ANPT 5908-2

NUMBER
270-2196-010

MAX
APPROX
4 1 @WEIGHT:0.7 POUNDS
MAXIMUM.

STATIC PRESSURE PORT IDENTIFICATION

PITOT PR

8 :L
32

-196 +L
-32
1
NO. 6-32 U N C - 2 8 x 3 0 MIN DEEP
BENDIX RECEPTACLE PTIH-IO-6P
PIN ORIENTATION MAY VARY lBOo
4 HOLES MATES WITH
BENDIX P T O 6 A -IO-GS(SR)
COLLINS PART NO. 371-6361 - 0 0
TPO-4432-012

590B-2 Airspeed Sensor, Outline

and Mounting Dimensions
Figure 421

22-03- 00 May 1/67

Page 432
 COLLINS
MAINTEKANCE
w MANUAL

r
= 1%

i IL
APPROX

APPROX

CONNECTOR-BENDIX PIGMY MS-3112E-22-55P

EPUlP
(CPN 371-2011-00) MATES WITH PT06A22-55S(SR)
(CPN 371-6225-00)

614E-2F Pedestal Controller, OutIine and Mounting Dimensions

Figure 422

May 1/67 22-03-00

Page 433
 COLLINS
MAINTENANCE
MANUAL

.
NOTES:
Q614E-2GI PEDESTAL CONTROLLER IS
IDENTICAL TO 614E-26, EXCEPT ILS
POSITION OF MODE SELECTOR REPLACES
APPR POSITION.

EQUIPMENT PART
TYPE NUMBER
614E-2G 522-4017-002
614E-2GI 522-4903-001

3D
I--I(

r'$7
APPROX
CONNECTOR-BENDIX PYGMY TYPE^
I

MS3112E-22-55P(CPN 371-201 1-00)

MATES WITH PT06A-22-55S (SR)
(CPN 371-6225-00).

614E-2G( ) Pedestal Controller, OLitline and Mounting Dimensions

Figure 4 2 3

22-03 - 00 May 1/67

Page 4 3 4
 -J
-
a
COLLINS
MAINTEKARCE
MANUAL

+ +SWAY SPACE
BOTH ENDS
t-66MAX 1- F i S W A Y SPACE
BOTH SIDES

L I 3 MAX
-IE-1-9&--4

p1-
15cMAX
32
LSEE
DETAIL A

NOTES:

I EQUIP
I PART I CANNON CONNECTOR D P X 2 - 5 7 S 5 7 S - 3 3 B - 0 2 0 1 ON SHOCKMOUNT ( C O L L I N S PART
TYPE NUMBER
ON a
NUMBER 370-5254-00) MATES WITH CANNON CONNECTOR D P X 2 - 5 7 P 5 7 P - 3 4 B - 0 2 0 1
ATR CASE ( C O L L I N S PART N U M B E R 3 7 0 - 5 2 9 6 - 0 0 ) .

I
790M-I 522-3682-000

@ CANNON CONNECTOR D P X Z M A S - A 6 7 S - A 6 7 S - 3 3 B - 0 2 0 1 ON SHOCKMOUNT (COLLINS PART

NUMBER 3 7 0 - 5 3 7 3 - 0 0 0 ) M A T E S WITH CANNON CONNECTOR D P X 2 M A S - A 6 7 P - A 6 7 P - 3 4 8 - 0 2 0 1
ON ATR CASE ( C O L L I N S PART NUMBER 3 7 0 - 5 3 7 8 - 0 0 0 ) .

DETAIL A 9 @ REAR ISOLATORS ARE LORD J - 5 5 7 2 - 2 , RANGE 3.0-6.0 POUNDS ( C O L L I N S PART

NUMBER 2 0 0 - 1 0 2 4 - 0 0 0 ) .
+
+I
OD
(D
@ FRONT ISOLATORS ARE LORD J - 5 5 7 2 - 4 , RANGE 4 . 5 - 9 . 0 POUNDS (COLLINS PART
NUMBER 200- 1023-000).

@ MAXIMUM DIMENSIONS DO NOT INCLUDE SWAY SPACE.

@ MOUNTING PER ARINC SPECIFICATION 404.
@ CONNECTORS PER ARINC REVISED S U P P L E M E N T NUMBER 2 OF SPECIFICATION 404.
@ CONNECTOR INDEXING PIN ARRANGEMENT IS AS SHOWN. THE DARK AREA IS T H E
PROTRUDING PART OF T H E P O L A R I Z I N G POSTS.

May 1 / 6 7 790M-1 Shockmount, Outline and Mounting Dimensions 22-03 -00

Figure 4 2 4 Pages 435/436
 a
COLLIN s
MAINTENANCE
w MANUAL

It-7
\

+l~~--$&-dLN0.8-32
32
1
27
5 MAX
~
4 MTG POSTS
UNC-2B
.1
L
5
’
-
6 $ MAX 1
NOTES:
MOUNTING PER ARINC SPECIFICATION 404.
@ CONNECTORS PER ARINC REVISED SUPPLEMENT NO. 2 OF SPECIFICATION 404.
3 CONNECTOR INDEXING PIN ARRANGEMENT IS AS SHOWN. T H E DARK A R E A IS T H E
PROTRUDING PART OF T H E P O L A R I Z I N G POSTS.
@ ( J 2 ) CANNON CONNECTOR DPX2MAS-A67S-A67S-336-0201 ON MOUNT (COLLINS PART NUMBER 3 7 0 - 5 3 7 3 - 0 0 0 )
MATES WITH CANNON D P X M A S - A 6 7 P - A 6 7 P - 3 4 B - O 2 O l ON 318 ATR CASE (COLLINS PART NUMBER 3 7 0 - 5 3 7 8 - 0 0 0 )
@ (JI) CANNON CONNECTOR D P X 2 - 5 7 S 5 7 S - 3 3 6 - 0 2 0 1 ON MOUNT (COLLINS P A R T NUMBER 3 7 0 - 5 2 5 4 - 0 0 0 ) M A T E S
W I T H CANNON D P X 2 - 5 7 P 5 7 P - 3 4 6 - 0 2 0 1 ON 1/4 A I R CASE (COLLINS P A R T NUMBER 3 7 0 - 5 2 9 6 - 0 0 1 .

1 EQUIP
TYPE
790M-lA
~ N Z R
522-3683-000
1
790M-1A Hard Mount, Outline and Mounting Dimensions
Figure,4 2 5

May 1/67 22-03-00

Pages 437/438
 a
COLLINS
MAISTENASCE
MANUAL

DETAIL FOR -9 -6-

i7
89OJ SERIES

I
I

.ISS’dg’lB HOLES. CLEARANCE

I
FDR NO. 8 BASE P L A T E MTG. SCREWS
.+-- -It

R
e
LL
K
W

104

r
ISOLATOR (2)
COLLINS PART NO. 2 00-1940-000

COLLINS PART NO. 2 0 0 -1 9 4 0 -0 0 0

I EPUIPMENT
TYPE
89OJ-2
~ NUMBER
PART
772-5129-001
1 I -
1.
I I I
’ f Q MAX. (INCLUDING SWAY SPACE) 1
NOTE:
L A S E PLATE ISOLATOR, COLLINS PART NO. 200-1942-000 1
INDEX PIN L E T T E R CODE SHOWN AS VIEWED FROM F R O N T O F SHOCKMOUNT. TPI- 4168-014

8905-2 Shockmount, Outline and Mounting Dimensions

Figure 426

Nov 1/68 22- 03-00

Pages 439/440
 a
COLLINS
MAINTEKANCE
w MANUAL

C. Equipment Preparation.

(1) General.

The following paragraphs contain special instructions required to place each equip-
ment in proper operating condition/mode for insertion into the Flight Control
System.

(2) Aircraft Equipment Phasing.

The phasing requirements differ with the different type of aircraft t r i m and servo
systems. The a i r c r a f t phasing chart (figure 427) gives the possible phasing hook-
ups and the c o r r e c t wiring for each.

(3) 334C-3 P r i m a r y Servo, Servo-Torque Setting.

Use mating connector MS3106A-lOSL-3S (Collins p a r t number 357-4086-00) f o r
application of dc power, Wire pins A and B of mating connector to the dc power source.

(a) Apply 27.5 volts dc between pins P2-A and P2-B of the 334C-3. This engages
the electromagnetic clutch in the unit.

(b) U s e a 5/16-inch socket adapter with torque wrench (Snap-On Tools Corp.,
Kenosha, Wisconsin, 300-0-300 inch-pounds o r equivalent).

(c) Lock gear train of the 334C-3 by inserting the shaft of a Phillips screwdriver
through the motor plate hole as shown in figure 428.

(d) Drive the g e a r s with a torque wrench in either counterclockwise o r clockwise

rotation. Note indication on the torque wrench dial and check the appropriate
service information letter for proper values.

(e) Adjust mechanical clutch tension with spanner wrench (see figure 429). Turn
the clutch adjusting nut away from the front panel (where the connector is lo-
cated) to release the tension on the mechanical clutch.

(f) Mark the torque setting on the'nameplates of the 351B-3 Servo Mount and the
334C-3 P r i m a r y Servo.

(4) 161A-1A Trim Coupler, Gain Setting.

Refer to the applicable service information letter f o r gain adjustments of the
161A-1A T r i m Coupler.

D. 562C-4 Autopilot Amplifier Strapping.

(1) General.

This paragraph explains the purpose and effects of 562C-4 strapping; hpwever,
it does not explain specific strapping for any aircraft type. This information
may be used to determine strapping necessary for proper automatic flight con-
trol of a particular aircraft type.

May 1/67 22-03-00

Page 441
 TRIM INDICATOR PHASING ELEVATOR TRIM SERVO PHASING

I OPTIONS I’RIM COUPLER TRIM TAB SERVO

SERVO-
562C-4
4IRCRAF’I CAPSTAN
4TTITUDE ROTATION LEVERSING FROM TO I T W MINIATURE TRIM TAB
LINKS
(See note 1) 562C-4 614E-2F (See note (See notes 562C-4 16lA-1A ROTATION 562C-4 334D-2-331
2 , 3)
2 :G!2 .
1 iHoN^.L T
7
JlTP-331 J1-h
1 1; 1 RE91’p”

CLOCKWISE AIL
e----. JlTP-34 J1-i PpW..
AILERON (-I‘?”‘
RIGIIT NOT APPLICABLE
TURN JlTP-33 J1-i A+ PLAIN
(-)
COUNTER-
CLOCKWISE
I I JlTP-34

JlTP-52
J1-h

J1-n
A-

R-
REDDOT
(+)

PLAIN
4-
(-)
CLOCKWISE
JlTP-531 J1-m I Rt I REDDOT
RUDDER (+)
RIGHT NOT APPLICABLE
YAW JlTP-53 J1-m R+ REDDOT
COUNTER- f IRUD (+)
CLOCKWISE
JlTP-52 J1-n R- PLAIN
I Iw/o (-)

JlBP-33 J1-j E- RED DOT

CLOCKWISE
(+)
CLOCKWISE
llBP-35 51-24 JlBP-33
PLAIN
:LEVATOR
JlBP-34 J1-k E+
(-) llBP-36
1 l coUNTER- I 1
51-22 JlBP-34
PITCH
UP
JlBP-33 PLAIN
J1-k EI CLOCKWISE
(-)
COUNTER-
CLOCKWISE
EL E- REDDOT
JlBP-34 J1-j
I I (+)

iOTES: 1. Servo rotation when viewed from capstan o r sprocket end.

2. Used with 614E-2G, r e q u i r e s an external s e r i e s r e s i s t o r for each channel. (See notes on appropriate interconnecting
wiring diagram.)

3. Honeywell miniature types: For aileron HCM 3/4-100-41,

F o r elevator and rudder HCM 3/4-100-27.
 COLLINS
MAINTENANCE
MANUAL

SLIP CLUTCH
ADJUSTING NUT
I

TORQUE WF
PORT

P r i m a r y Servo, Torque Setting Diagram

Figure 428

I. MATERIAL: 4
FLAT STOCK STEEL.
-
2. ALL DIMENSIONS I N INCHES. FRACTIONAL TOLERANCE :&.
3. REMOVE BURRS AND SHARP EDGES.

Spanner Wrench, Fabrication Diagram

Figure 429

May 1/67 22-03-00

Page 443
 Strapping Effects.

Figure 430 lists all possible strapping combinations f o r each adjustment section
and the relative effect of each upon gains o r levels as applicable. Figure 431
shows locations and positioning for elevator, aileron, rudder, and rudder washout
reversing links. Locations of all adjustment sections and terminals to be strapped
are shown on figures 432 through 434.
Reversing Link Functions.

Elevator, aileron, and rudder reversing links are positioned to establish the output
phase of their respective servo amplifiers, necessary to drive a i r c r a f t control
surfaces in the desired directions.

The rudder washout link is used to r e v e r s e the phase of the rudder washout signal
and it must always be installed the same as the rudder reversing link. Rudder
washout is a feedback applied to the rudder channel (servo amplifier input) ahead
of the rudder reversing link. It cancels any rudder torque after 3 to 4 seconds s o
the rudder will be streamlined.

Elevator Channel Adjustment Functions.

Elevator Command Gain Adjust. (See A, figure 432.)

Adjusts overall gain of the elevator channel by establishing the degrees of

pitch required f o r a degree of elevator servo-capstan movement.

Altitude Integration Rate Adjust. (See B yfigure 432.)

Sets altitude integration rate by controlling speed of pitch knob to prevent

overshoot and oscillation as the pitch knobs integrate an altitude e r r o r .
Establishes the degrees of pitch p e r second for a foot of altitude e r r o r .

Pitch Rate Gain Adjust. (See C, figure 432.)

Adjusts pitch rate gain to establish degrees p e r second of pitch r a t e required

to command a 1-degree change in pitch attitude.

Up-Elevator Gain Adjust. (See D, figure 432.)

Adjusts level of up-elevator (pitch) signal required to compensate for de-

creased lift that occurs during a turn. Establishes degrees of pitch p e r
degree of bank.

Altitude Gain.Adjust. (See E, figure 432.)

Adjusts gain of altitude channel to provide the c o r r e c t amount of pitch to cor-

rect an altitude e r r o r when altitude hold is engaged. Establishes degrees of
pitch p e r 100 feet of attitude e r r o r .

22-03-00 May 1/67

Page 444
 COLLINS
R.IAIIVTEIVAKCE
MANUAL

R LA TIVE ADJUSTMEN' ' LEVELS AND TERMINALS STRAPPED TOGETHER FOR EACH (See note)
ADJUSTMENT SECTION/
LOCATION - FIGURE I I I I I I I
4 1 5
Elevator command gain/A-42 73, 71 73, 69, 71 74, 73, All
70, 71

Altitude integration rate/

B-422
76, 79 78, 79 78, 76, 79 81, 79 81, 76, 79 81, 78, 79 81, 78,
1 7 6 , 79 I 82, 79
I 82, 76, 79 82, 78, 79 82, 78,
176, 79 1 82, 81, 79 82, 81,
176, 79 82, 79
78, 81, I
Pitch rate gain/C-422 84, 87 86, 87 86, 84, 87
7 89, 87 89, 84, 87 89, 86, 87 1 ::::;, P O , 87 190, 84, 87 190, 86, 87
184, 87
90, 89,
86, 87
I
All

Up-elevator gain/D-422 92, 95 94, 95 94, 92, 95 97, 95 97, 92, 95 97, 94, 95 98, 92, 95 98, 94, 95
92, 95 94, 95
I

Altitude gain/E -422 100, 104

l l 100, 1041 I I
102, 104 102, 100, 104 106, 104 106, 100, 104 106, 102, 104 106, 102 107, 104 107, 100, 104 107, 102, 104 107, 102,
1100,104 I 107, 106, 1 0
100, 104
107, 106,
102, 104

I
Aileron command gain/B -42 3 131, 129 130, 129 130, 131, 129 127, 130, 129 127, 130,126, 129
131, 129
126, 131, 129 126, 130, 129 126, 127,
130, 129

I
Roll rate gain/C-423

Rudder command gain/C-424

125, 122

72, 69
I 123, 122

71, 69
/ 123, 125, 122

71, 72, 69 68, 69

I

68, 72, 69
121, 123, 122 121, 123,120, 122

68, 71, 69
125, 122

68, 71, 67, 69

120, 125, 122 120, 123, 122 120, 123

67, 72, 69 67, 71, 69

125, 122

67, 71,
120, 121, 122120, 121,

67, 68, 69
125, 122 I123,

67, 68,
2 O , 122
121,

72, 69 72, 69 72, 69 71, 69

Coordination/B-424 79, 77 78, 77 78, 79, 77

-I 76, 77 76, 79, 77 76, 78, 77 76, 78,

179, 77 I 75, 77
I 75, 79, 77 75, 78, 77 :; 1 ,; I
1
75, 7
6
-
78, 77

I
Adverse yaw/A -42 4 90, 87 89, 87 89, 90, 87 86, 87 86, 90, 87 86, 89, 87 85, 90, 87 85, 89, 87 lgo,
85, 89,
87 85, 86, 87 85, 86,
90, 87 89, 87

Turn knob limit/D-423

Roll command rate/A-423

164, 25 123, 2 5 127, 25

NOTE: Numbers 1 to 1 5 show relative adjustment levels f r o m the lowest (1)t o the highest (15); however, these n u m b e r s are a r b i t r a r y and have n o significance
as f a r as specific values are concerned. T h e elevator, aileron, and r u d d e r channel adjustment function subparagraphs which follow this figure specify
the types of r a t i o s adjusted by this strapping. Only two a i d t h r e e adjustment levels are provided f o r the TURN knob limit and roll command r a t e ,
respectively.

562C-4 Autopilot A m p l i f i e r , Strapping Combinations

Figure 430

M a y 1/67 22-03-00
Pages 445/446
 t
a
0
+
REVERSING LINKS

RUDDER
RUDDER WASHOUT
/ NON REVERS1 NO

00
REVERSING
POSIT ION P O S I T ION

REAR _.I

562C-4 Autopilot Amplifier, Reversing Links Positioning

Figure 431

(5) Aileron Channel Adjustment Functions.

Aileron Command Gain Adjust. (See B, figure 433.)

Adjusts overall gain.of the aileron channel by establishing degrees of bank

required for a degree of aileron servo-capstan movement.

Roll Rate Gain Adjust. (See C, figure 433.)

Adjusts roll rate gain to establish degrees p e r second of roll rate required to
command a 1-degree change in bank.

TURN Knob Limit Adjust. (See D, figure 433.)

Sets maximum degrees of bank that can be commanded with the TURN knob.

Roll Command Rate Adjust. (See A , figure 433.)

Sets aircraft rate of roll in response to a roll command by establishing com-

manded degrees of bank p e r second.

Aileron Channel Gain Reduction.

Removing a jumper wire in the gain change circuit of the aileron board pro-
vides a 3-to-1 reduction in channel gain when the aircraft is operating above
18,000 feet. (Refer to appropriate service information letter and 562C-4
Autopilot Amplifier Overhaul Manual for complete details.)

May 1/67 22- 03- 00

Page 447
 COLLINS MAINTEIVANCE
w MANUAL

STRAPPED FUNCTIONS

L-----__
ELEVATOR COMMAND
I O

GAIN

ALTITUDE INTEGRA%
------_

PITCH RATE

---____ GAIN

UP ELEVATOR
I GAIN

7
ALTITUDE GAIN

ELEVATOR

562C-4 Autopilot Amplifier, Elevator Board, Strapped Functions

Figure 432

22-03- 00 May 1/67

Page 448
 e
COLLINS
MAISTEKASCE
v MANUAL

(6) Rudder Channel Adjustment Functions.

(a) Rudder Command Gain Adjust. (See C yfigure 434.)

Adjusts overall gain of the rudder channel by establishing degrees p e r second

of yaw rate required for a degree of rudder servo-capstan movement.

(b) Coordination Adjust. (See B yfigure 434.)

Adjusts roll data input by establishing input degrees of bank (roll data)
equivalent to a 1-degree p e r second yaw rate input. Provides proper rudder
positioning for turn coordination.

(e) Adverse Yaw Adjust. (See A , figure 434.)

Strapped only for aircraft types that require adverse yaw during turns.
Adjusts adverse yaw input by establishing degrees p e r second of roll r a t e
input equal to a degree p e r second of yaw rate.

E. 562A-5G Flight Computer Logic Board Strapping.

(1) General.

This paragraph explains general functions and strapping of 562A-5G logic boards
TB4 and TB5; however, it does not explain specific strapping for any a i r c r a f t
type. Information contained herein may be used to determine strapping necessary
to obtain required flight characteristics, modes of operation, and analog scaling
for a particular aircraft type.

The 562A-5G is shipped from the factory with certain strapping already incor-
porated on the logic boards. This strapping satisfies minimum requirements for
initial operation of the system and should be changed as required to satisfy
specific requirements of the particular aircraft type.

(2) Analog Adjustments.

Analog strapping adjustments on the logic boards scale analog voltage inputs from
associated equipment to make them compatible with 562A-5G input requirements.
If an input analog is unknown, the voltage must be measured with an rms-type
voltmeter and the analog (in millivolts/degree o r foot) must be determined. A l l
adjustment values for analog strapping on the logic boards are computed for
input analog voltages with a 0-degree phase angle. If an input voltage with phase
shift is employed, its effective analog value must be computed and used as the
basis f o r strapping. The effective analog value in millivolts/degree o r foot can be
computed by multiplying the measured r m s value of the input by the cosine of its
phase angle.

(a) Bank Analog. (See A , figure 435.)

With no bank-analog strapping on logic board TB4, the 562A-5G accepts a
130-millivolt/degree bank input analog. Other bank input analogs may be

May 1/67 22- 03- 00

Pages 449/450
 COLLINS
MAISTENANCE
v MANUAL

i
0 0

ROLL COMMAND RATE

I AILERON COMMAND GAIN
---------

------- R35
C

P D\
\
I

cxgFB@
TURN KNOB L I M I T

STRAPPED FUNCTIONS

AILERON

562C-4 Autopilot Amplifier, Aileron Board, Strapped Functions

Figure 433

May 1/67 22-03-00

Pages 451/452
 -
COLLINS
MAINTENAKCE
MANUAL

STRAPPED FUNCTIONS

r 0

I ADVERSE YAW

COORDINATION

R16 109

R17

)
U
RUDDER COMMAND GAIN I

- u

O I
PI
l o
RUDDER

5 6 2 C - 4 Autopilot Amplifier, Rudder Board, Strapped Functions

Figure 4 3 4 -

May 1/67 22 - 03 -00

Page 4 5 3
 a
COLLINS
MAINTENANCE
w MANUAL

used by strapping terminals 53, 54, 55, and/or 56 (40, 80, 20, and/or 1 0 milli-
volts/degree, respectively) to 83. Select terminal(s) to be strapped (53, 54,
55, and/or 56) so the corresponding value o r sum of values added to 130
equals the bank input analog.

Heading Analog. (See B, figure 435.)

With no heading-analog strapping on logic board TB4, the 562A-5G accepts a

240-millivolt/degree heading input analog. Other heading input analogs may
be used by strapping terminals 51, 52, 57, and/or 58 (60, 120, 30, and/or
15 millivolts/degree, respectively) to 82. Select terminal(s) to be strapped
s o the corresponding value o r sum of values added to 240 equals the heading
input analog.

Course Datum Analog. (See K, figure 435.)

With no course datum-analog strapping on logic board TB4, the 562A-5G

accepts a 240-millivolt/degree course datum input analog. Other course
datum input analogs may be used by strapping terminals 38, 39, 68, and/or
69 (60, 120, 30, and/or 15 millivolts/degree, respectively) to 7 0 . Select
terminal(s) to be strapped s o the corresponding value o r sum of values added
to 240 equals the course datum input analog.

Altitude Analog. (See B, figure 436.)

With no altitude-analog strapping on logic board TB5, the 562A-5G accepts

an altitude e r r o r signal input analog of 5 millivolts/foot. Other altitude input
analogs may be used by strapping terminals 14, 15, 16, and/or 1 7 (8, 2, 1,
and/or 4 millivolts/foot, respectively) to 9. Select terminal(s) to be strapped
(14, 15, 16, and/or 17) s o the corresponding value o r sum of values added t o
5 equals the altitude e r r o r signal input analog.

Pitch Analog Millivolts. (See Cy figure 436.)

With no pitch analog strapping on logic board TB5, the 562A-5G accepts a
130-millivolt/degree pitch input analog. Other pitch input analogs may be
used by strapping terminals 18, 19, 20, and/or 21 (80, 20, 10, and/or 40
millivolts/degree, respectively) to 8. Select terminal(s) to be strapped (18,
19, 20, and/or 21) s o the corresponding value o r sum of values added to 130
equals the pitch input analog.

(3) Limit Adjustments.

(a) Bank Limits. (See F, figure 435.)

With no bank limit strapping on logic board TB4, the 562A-5G limits aircraft
bank to 10 degrees in all modes. Bank limits of 15, 25, 30, o r 35 degrees
can be established in any of the modes by properly strapping terminal 61,
47, 34, o r 35, respectively. Only one terminal can be selected and strapped
for each mode and at no time should any of these terminals be strapped to
each other. -

22-03-00 May 1/67

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C 0LLI N S
MAINTENANCE
ww MANUAL

BANK ANALOG M V

0 0 VOLTS
Q::k APPROACH

EXTERNAL ROLL
STEER VOLTS

LOC O N L Y VOLTS

C OBMAMNAKN D
OR H D G V O L T S
OFF
:OURSE D A T U M S I G N A L

V / L CAPTURE ANN

V/L A R M ANN

G
-+ITCH
MVNITOR

COMPASS MON~~ORJ -GYRO MONITOR

I l N A VFLAG S P A R E ,t28 VDC R E G U L A T E D
!BANK RATE 1.2-, VOLTS

COMPLEMENTARY

H ______ FILTER INPUT

AMPL
TB5-51-
%$3 5 20 23
9 @_-% @-COMPLEMENTARY
FILTER OUTPUT

B E A M SENSOR AMPL

0 0
184 FRONT VIEW
TB5-49

i RADIO IN T O B E A M SENSOR f STEERING FLAG

GRD

RADIO I N T O
CONE SUPPRESSION

-COURSE CUT
AMPL

COURSE DATUM ANALOG MV

_ I - -
-
C 1238.02-4

May 1/67 562A-5G Flight Computer, Logic Board TB4 Functions 22-03 -00
Figure 435 Page 455
 a
COLLINS
MAIKTENANCE
w MANUAL

A L T I T U D E RA T E

A L T I T U DE ANALOG MV
- 7 - 0 TB4-5

SPARE-
PITCH S T E E R

e- R32

AC GRD
GS CAPTURE

+ 2 8 VDC
REGULATED -ALTITUDE H O L D MODE VOLTS
PITCH O F F A L T E R N A T E MONITOR

GS AUTO
SPARE
PITCH BACK COURSE MODE
EXTERNAL
STEER MO D E

T B 5 FRONT VIEW

GS I N AMPL,-\ / -A L T I T UDE RATE IN AMPL

AL T I T U DE I N A M P L GS GAIN

-LOW APPROACH
\

562A-5G Flight Computer, Logic Board TB5 Functions

Figure 436
22 -03 -00 May 1/67
Page 456
 To increase bank limits in a particular mode, first determine the amount of
additional bank required by subtracting 1 0 degrees from the desired bank
limits. Strap spare terminal 32, 31, 48, 60, o r 79 (E, figure 435) to the ter-
minal (61, 47, 34, o r 35) that provides the amount of additional bank required.
Connect the cathode (banded end) of a 1N645 diode to the selected spare ter-
minal. Connect the anode of this diode to terminal 27, 28, 30, 49, o r 59 (D,
figure 435) for increased (strapped) bank limits in heading, localizer and ap-
proach, VOR, o r localizer, respectively. Diodes a r e used to isolate the
heading, navigation, approach, VOR, and/or localizer voltages and to allow
strapping of the same, or different, bank limits f o r each type of operation.

(b) Pitch Limits. (See F, figure 436.)

The value of resistor R34 between terminals 25 and 46 on logic board TB5
determines the pitch limits. A resistance value of 4.87K establishes pitch
limits of 12 degrees. Resistor R34 can be changed to obtain other pitch
limits; however, the Collins field service representative must be consulted
to determine the resistance value required.

(4) Rate Gain Adjustments.

Course Datum Rate. (See G, figure 435.)

With no course datum rate strapping on logic board TB4, the 562A-5G course
datum rate gain at complementary filter center frequency is 3.2 degrees of
bank p e r degree of course datum. This gain can be changed for specific
modes by proper strapping of terminal 7 and/or 8. When a mode voltage is
applied to terminal 7 o r 8, the 3.2-degree gain is changed to a 2.7- or
2.2-degree gain, respectively. If a mode voltage is applied to both 7 and 8,
the gain becomes 1.7 degrees of bank p e r degree of course datum.

Terminal 7 and/or 8 may be strapped to terminal 27, 28, 30, 49, o r 59 (D,
figure 435) to change the course datum rate gain in heading, localizer and
approach, VOR, o r localizer. To change the gain in two or more modes,
strapping must be accomplished using 1N645 isolation diodes and spare
terminals as explained in paragraph 2.E.(3)(a) of this section. If the
desired mode voltages are strapped to terminal 33, 34, 47,and/or 61 (F,
figure 435), terminal 7 and/or 8 can be strapped to one of these.

Bank Rate. (See H, figure 435.)

With no bank rate strapping on logic board TB4, the 562A-5G bank rate gain
at complementary filter center frequency is 1.2 degrees of bank p e r degree
of bank input. This gain can be changed in a specific mode by strapping ter-
minal 24, 19, and/or 6 to a specific mode voltage as explained in (a) above.
Terminal 24, 19, and/or 6 should be strapped so the sum of corresponding
values (0.1, 0.2, and 0.4, respectively) subtracted from 1.2 equals the desired
gain. The bank rate gain can be changed for all modes by strapping the
selected terminals (24, 19, and/or 6) to terminal 64 (+28 volts dc).

May 1/67 22-03-00

Page 457
 (e) Radio Rate. (See I, figure 435.)
With no radio rate strapping on logic board TB4, the 562A-5G radio rate gain
at complementary filter center frequency is 30 degrees of bank p e r dot (30
microamperes) of radio deviation. This gain can be changed in a specific
mode by strapping terminals 73, 66, 42, and/or 37 to the desired mode voltage
as explained in (a) above. Terminals 73, 66, 42, and/or 37 should be strapped
s o the sum of corresponding values (2, 4, 8, and 16, respectively) subtracted
f r o m 30 equals the desired gain. The radio rate gain can be changed for all
applicable modes by strapping the selected terminals (73, 66, 42, and/or 37)
to terminal 64 (+28 volts de).

(d) Altitude Rate. (See A , figure 436.)

The altitude rate signal input is not used f o r normal operation of the 562A-5G.
Terminal 1 0 should be strapped to terminal 53 to ground this input and prevent
noise from being picked up.

(5) Miscellaneous Adjustments.

(a) Radio in to Beam Sensor. (See J , figure 435.)

Resistors and strapping installed on terminals 2, 3, 40, and/or 41 determine
the 562A-5G trip points for automatic capture of VOR and localizer beams.
Resistor R16 connected between terminals 3 and 40 provides the same trip
point for optimum capture in both VOR and localizer. (Decreasing the value
of R16 produces more overshoot.)

If a different trip point is required for localizer, terminals 2 and 41 must be

strapped together, and two resistors, R14 and R15, must be added. R14 should
be connected between terminals 3 and 41, and R15 should be connected be-
tween terminals 2 and 40. Resistor values f o r optimum capture are selected
empirically during initial flight tests for the specific aircraft type. (As
total series resistance of R14 and R15 is reduced, overshoot is increased.)

(b) Altitude Gain. (See H, figure 436.)

With terminal 44 on logic board TB5 disconnected, the 562A-5G commands

a degree of corrective pitch p e r 25 feet of altitude e r r o r during altitude hold
operation. Altitude gain can be reduced by connecting a r e s i s t o r between
terminals 44 and 27. Selection of a 6.81K, 3.48K, o r 1.62K resistor will
provide a degree of corrective pitch p e r 50, 75, o r 125 feet altitude e r r o r .

(c) Pitch-Down in Approach. (See I, figure 436.)

With no pitch-down strapping on TB5, the 562A-5G adds 4 degrees of downward
pitch to commanded pitch, during the approach mode at glideslope capture.
Terminal 43, 36, and/or 35 must be strapped to 27 (H, figure 436) to obtain
the proper added pitch-down command for optimum capture of the glideslope
beam. Terminals 43, 36, and/or 35 should be strapped so the sum of cor-
responding values (0.5, 1.3, and 2.5, respectively) subtracted
- from 4 degrees
equals the pitch-down required.
22 -03-00 May 1/67
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COLLINS MAIXTENANCE
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(d) Fixed Pitch-Up in GA. (See G, figure 436.)

Terminal 45 on TB5 is used only when a fixed pitch-up command is required

for GA (go-around) mode operation. If fixed pitch-up in GA is employed, the
external pitch steering input (PlA-27, P1A-37) on the 562A-5G must be
shorted in the aircraft wiring. A 10-percent, 1/8-watt r e s i s t o r must be
connected between terminals 45 and 26 on TB5. The selected value of this
r e s i s t o r determines the amount of pitch-up commanded in GA. Resistor
values and corresponding amounts of pitch-up command are as follows:

PITCH-UP RESISTANCE PITCH-UP RESISTANCE

(degrees) (ohms) (degrees) (ohms)

1 1470 11 30,100

2 3320 12 36,500

3 487 0 13 42,2 00

4 6810 14 51,100

5 9090 15 61,900

6 11,500 16 71,500

7 14,000 17 86,600

8 17,800 18 110,000

9 21,500 19 140,000

10 26,100 20 196,000

(6) Mode Strapping.

Mode and submode strapping normally required for 562A-5G operation is

explained in this paragraph. A Collins field service representative should be
consulted to determine specific strapping for special requirements.

(a) Gyro Mode.

Mode strapping is not normally required for the gyro mode; however, the
gyro mode voltage is available at terminal 11 on TB4 (D, figure 435).

(b) Heading Mode.

The heading mode voltage is available a t terminal 27 on TB4 (D, figure 435).
Terminal 27 may be strapped to one of the bank limit terminals as explained
in 2.E.(3)(a) of this section. Terminal 27 must be strapped to terminal 25
(F, figure 435) and is normally strapped to terminal 18 as well. Termihal
1 8 strapping provides selected angle capture of VOR o r localizer beam.

May 1/67 22 -03-00

Page 459
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COLLINS
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(c) NAV/LOC Mode.

NAV/LOC mode and submode voltages are available a t terminals 28, 49, and
59 on TB4 (D, figure 435). Any of these terminals may be strapped to one of
the bank limit terminals as explained in 2.E.(3)(a) of this section. Terminal
28 provides a mode voltage during the entire localizer and approach opera-
tion. A voltage is present on terminals 49 and 59 only during VOR o r
localizer operation respectively.

Terminal 77 (G, figure 435) may be strapped to 62 for N/L (NAV/localizer

capture annunciation. N/L a r m annunciation is available by strapping termi-
nal 77 to 46 instead of to 62. N/L a r m annunciation is normally provided on
pin 6 of connector PlB(BP).

(d) Approach Mode.

The approach mode voltage is available a t terminal 30 on TB4 (D, figure

435). Terminal 30 may be strapped to any one of the bank limit terminals
as explained in 2.E.(3)(a) of this section.

A NAV mode voltage must be applied to terminal 29 during automatic glide-

slope operation. To provide this voltage, connect a 1N645 diode between
terminals 32 and 29 with the cathode (banded end) connected to terminal 29.
Strap terminal 32 to 4 (I, figure 435) and s t r a p terminal 49 on TB5 to
terminal 42 on TB5 (J, figure 436).

Terminal 33 on TB5 (K, figure 436) is strapped to terminal 38 to provide a

low approach voltage a t the middle marker. Terminal 38 may be strapped
to 41 instead of 33 if the low approach submode is initiated by some other
method (+28 volts de, step o r steady state) and the middle marker is not
used, Terminal 40 (L, figure 436) must be strapped to terminal 39 to pro-
vide a gain reduction of approximately 3 4 0 - 1 in the low approach submode.

(e) @-Around Mode.

The flight director indicator will command a wings level condition during
go-around. To provide this capability, connect a 1N645 diode between
terminals 80 (D, figure 435) and 79 with the cathode (banded end) connected
to terminal 79. Strap terminal 79 to terminal 78 (F, figure 435).

(f) Miscellaneous Mode Strapping.

When the AP-103F is engaged and glideslope capture has not occurred,
steering inputs for the 562A-5G steering circuits are supplied by the
autopilot amplifier, The bank command and bank attitude inputs to the
562A-5G roll steering circuits must be removed when autopilot amplifier
supplied steering inputs a r e used. A 1N645 diode must be connected between
terminals 78 ( F , figure 435) and 43 (H, figure 435) on TB4 to provide this
capability, The diode cathode (banded end) should be connected to terminal
78.
-

22 -03-00 May 1/67

Page 460
 COLLINS
MAIIVTEKANCE
w MANUAL

(7) Other Logic Board Terminals.

A number of other terminals located on logic boards TB4 and TB5 (figures 435
and 436, respectively) a r e not mentioned in the preceding paragraphs. These
terminals a r e available as test points for certain voltages and signals, and are
also available for future strapping that may be required as operating concepts
and requirements change.

F. 590A-3E Altitude Controller Parameter Switch Strapping.

(1) General.

This paragraph explains altitude e r r o r analog signals and system gain provision
for the 590A-3E Altitude Controller.

(2) Analog Adjustments.

The 590A-3E is strapped at the factory to provide 1 0 millivolts/foot of altitude

throughout the operational range. Dual adjustable parameter switch points are
factory set at 18,000 feet. One switch point is available for system gain
changing; the other may be strapped by the customer to reduce the altitude
e r r o r analog to 5 millivolts/foot of altitude above 18,000 feet (terminals 37 to
46, figure 437). (Refer to overhaul manual and service information letters for
information concerning adjustment of parameter switch to a switching point other
than 18,000 feet.)

TOP

T BI

R 24

t
TPO-4363-011

590A-3E Altitude Controller , Parameter Switch Strapping

Figure 437

May 1/67 22-03-00

Page 461
 G.
-
a
COLLINS
MAINTEKANCE
MANUAL

344C-1 F Instrument Amplifier Monitor Logic Strapping.

For flag and out-of-view logic, the instrument amplifier monitor inputs provide for
logic strapping that is performed at installation to meet customer requirements.
(Refer to the appropriate servi.ce information letters and to the 344C-1F Instrument
Amplifier Overhaul Manual for complete details .)

3. REMOVAL AND REPLACEMENT,

Removal and installation procedures given in this section apply only after necessary
preparations have been made. This includes having all holes drilled and tapped and having
mounts installed for equipment using mounts. (See figure 438 for a list of cable connec-
t o r s and mating connectors .)

CONNECTOR CONNECTORTYPE MATING

EQUIPMENT
DESIGNATION (Collins P a r t No.) CONNECTOR

121A-1 J1 KO2 -19 -2 OPN K03-19-20SN

Emergency 371-0083-000 371-0087-000
Disconnect 6 4 5 -19-1/2 right-
angle cable clamp:
371-0116-000)

161A-1A J1 DPA-32-34P-1 DPA-32-33s-3

T r i m Coupler 370-2071-000 370 -2 072 -0 0 0

161E-1 J1 MS242 64R-22B -55P1 OX m52 42 66R-22 B -5 5510

Mode Coupler 359-0035-000 359-4077-010

52 MS242 64R-22 B -55P NX m5242 66R-22 B -5 55n

359-4011-000 359 -40 16 -000

329B-7( ) J1 MS242 64R-22 B -55P6X m52 42 66R-22 B -B5 556

Flight Director 359 -4012 -000 359 -40 17-00 1
Indicator
52 MS24264R-22 B-55P7X MS24266R-22B-55S7
359-4013-000 359 -401 8 -000

329B-8 G J1 MS24264R-22 B-55P6X m5242 66R-22 -B55S6

Flight Director 359-4012-000 359-4017 -001
Indicator
52 MS242 64R-22B-55P7X m5242 6613-22 B-55S7
359 -40 13-0 0 0 359 -401 8 -000
53 MS242 64R-22 B -55P 1OX m52 42 66R-22 B -5 5510
359-0035-010 359 -407 7 -0 10

Cable Connectors (Sheet 1 of 2)

Figure 438

22-03-00 May 1/67

Page 462
 EQUIPMENT CONNECTOR
DESIGNATION
-
COLLINS
MAINTENANCE

CONNECTORTYPE
(Collins Part No.)
MATING
CONNECTOR

331A-6A J1 MS242 64R-22 B -55P8X MS242 66R-22 B-55S8

Course Indicator 359 -4014-000 359 -4019 -001

52 MS242 64R-22 B -5 5P9X MS242 6 6R-22 B-5 5S9

359-4015-000 359 -402 0-001
332G-2 J1 AN3102A-16S-lP AN3106A-16s -1s
Rate Gyro 357 -3007 -000 357 -4006-000
and
345A-4B
Sensing Unit

334C-3( ) P1 CA3106A -2 4-2 8 P(SPL) MS3101A-24 -2 8S

P r i m a r y Servo 357-5089 -000 357-2177-000
(Bulkhead flange)
P2 MS3102A-1 OSL-3s MS3106A-lOSL-3S
357-3007-000 357-4006-000
344C-1D P1 and P 2 (2) DPA-32-34P-lAlOl DPA-32 -338-3
Instrument 370-2071-000 37 0 -2 0 7 2 -0 00
Amplifier

344C-1 F P1A and P1B DPX2MAS-A67P-A67P- DPX2MAS-A67S -A67S-

Instrument Dual Connector 34B-02 0 1 33B-0201
Amplifier 370-5378-000 370-5373-000
562A-5G P1A and P1B DPX2 -57P57 P -34B -02 0 1 DPX2 -5 7S57 s -33B-02 01
Flight Dual Connector 370-5250-000 37 0-5255-000
Computer

562C-4 P1A and P1B DPX2MAS-67P67P-34B-0201 DPX2MAS-67 S67S-33B -

Autopilot Dual Connector 370-5378-000 02 01
Amplifier 37 0-5373-000

59 OA-3 E P1 DPXB-45 -34P-0003 DPXB-45 -33s-00 03

Altitude . 37 0 -52 06 -0 00 37 0-5216-000
Controller
590B-2 PTlH-1 0-6P PT06A-10 -6S(SR)
Airspeed 371-2 166 -0 0 0 371-6361-000
Sensor
614E-2( ) Jl PT02A-22 -55P P T 06A-22 -55S( SR)
Pedes tal 37 1-2 0 11-0 0 0 37 1-622 5 -0 00
Controller
Cable Connectors (Sheet 2 of 2)
Figure 438
May 1/67 22-03-00
Page 463
 A.
-
a
COLLINS

121A-2 Emergency Disconnect.

(1) Removal.
MAINTENANCE
MANUAL

(a) Remove screws from top and bottom of front panel.

(b) Pull 121A-2 out from the mounting panel far enough to reach connector.
Remove connector, and remove the 121A-2 Emergency Disconnect.

(2) Installation.

(a) Connect the 121A-2 Emergency Disconnect to the mating connector.

(b) Slide the 121A-2 into position and fasten in place with the two mounting
screws.

B. 161A-1A Trim Coupler.

Removal.

(a) Loosen the adjustable retainer nut on the hard mount o r equipment rack until
the nut disengages.

(b) Slide the 161A-1A T r i m Coupler forward and remove from the hard mount o r
equipment rack.

Installation.

CAUTION: USE EXTREME CARE WHEN INSTALLING THE 161A-1A TO ENSURE

THATCONNECTORSMATEPROPERLY.

(a) Slide the 161A-1A into the hard mount o r equipment rack until the connectors
are properly engaged.

(b) Tighten the adjustable retainer nut until the 161A-1A is held securely in
place.

C. 161E-1 Mode Coupler.

~

(1) Removal,

(a) Loosen the retainer nut on the front of the shockmount until the retainer nut
disengages.

(b) Slide the 161E-1 forward far enough to reach connectors.

(c) Disconnect the two connectors at the rear of the 161E-1.

(2) Installation.

(a) Connect the two connectors to the rear of the 161E-1.

22 -03-00 May 1/67

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COLLINS
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w MANUAL

(b) Slide the 161E-1 into the shockmount until the rear edge of the 161E-1 base
is gripped by the slot a t the rear of the shockmount.

(e) Tighten the locknut until the 161E-1 is held securely in place.
D. 327D-1W Trim Indicator.

(1) Removal.

(a) Remove the six screws that hold the 327D-1W in place: one screw on each
side, and two screws on the top and on the bottom. Do not remove the end
screws o r the middle screw.

(b) Lift the 327D-1W carefully until the terminals a t the rear of the unit are
accessible.

(e) Tag and unsolder the leads from the 327D-1W.

(d) Remove the 327D-1W from the mounting position.

(2) Installation.

(a) With the 327D-1W held near the mounting position, solder the leads to the
appropriate rear terminals.

CAUTION: DO NOT PINCH CABLE.

(b) Carefully slide 327D-1W into position.

(e) Fasten the 327D-1W in place using the six mounting screws.

E. 329B-7( ) Flight Director Indicator.

(1) Removal.

(a) Front Mounted Instruments.

-
1. Loosen the screws that hold the clamp to the instrument case.

-
2. Position the instrument case a few inches away from the aircraft instru-
ment panel.

-
3. Remove the two cable connectors from the rear of the instrument case.

(b) Rear Mounted Instruments.

-
1. Loosen the screws that hold the front adapter assembly and the 329B-7( )
to the aircraft instrument panel,
2. Position the instrument case a few inches away f r o m the aircraft instru-
ment panel.
-
3. Remove the two cable connectors from the rear of the instrument case.

May 1/67 22 -03-00

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 COLLINS
MAIfiTEIVAh’CE
w MARUAL

(2) Installation.

(a) Front Mounted Instruments,

-
1. Connect the two cable connectors to the rear of the instrument case.

2. Slide the 329B-7( ) into place in the instrument panel,

-
3. Tighten the screws that hold the clamp to the instrument case.

(b) Rear Mounted Instruments.

-
1. Connect the two cable connectors to the rear of the instrument case.

2. Install the front adapter assembly over the front of the 329B-7( ),

-
3. Slide the 329B-7( ) into place in the instrument panel.

-
4. Tighten the screws that hold the adapter assembly and the 329B-7( ) to
the aircraft instrument panel.

F. 329B-8G Flight Director Indicator.

(1) Removal.

(a) Remove the four mounting screws that hold the 329B-8G to the instrument
panel.

(b) Slide the 329B-8G forward far enough to reach the connectors.

(c) Disconnect the three connectors from the rear of the 329B-8G.
(2) Installation.

(a) Connect the three connectors to the rear of the 329B-8G.

(b) Slide the 329B-8G into the instrument panel and secure in place with the
four mounting screws.

G. 331A-6A Course Indicator.

(1) Removal.

(a) Front Mounted Course Indicators.

-
1. Remove the screws that hold the clamp to the 331A-6A.

-2. Slide the 331A-6A forward far enough to reach the connectors.

-
3. Disconnect the two connectors from the rear of the 331A-6A.

22 -03-00 May 1/67

Page 466
 -
a
COLLINS

(b) Rear Mounted Course Indicators

-
1.
MAINTENAKCE
MANUAL

Remove the screws that hold the front adapter assembly and the 331A-6A
to the instrument panel.

-
2. Slide the 331A-6A forward far enough to reach the connectors.
3.. Disconnect the two connectors from the rear of the 331A-6A.

(2) Installation.

(a) Front Mounted Course Indicators.

-
1. Connect the two cable connectors to the rear of the 331A-6A.

-
2 . Slide the 331A-6A into place in the instrument panel.

-
3. Tighten the screws that hold the clamp to the 331A-6A.

(b) Rear Mounted Course Indicators.

-
1. Connect the two connectors to the rear of the 331A-6A.

-
2. Install the front adapter assembly over the front of the 331A-6A.

-
3. Slide the 331A-6A into place in the instrument panel.

-
4. Tighten the screws that hold the adapter assembly and the 331A-6A to the
instrument panel.

H. ~
332G-2 Rate Gyro.

(1) Removal.

(a) Remove connector from 332G-2 connector receptacle.

(b) Remove the four mounting screws and lift the 3 3 2 6 - 2 from the mounting
position.

( 2 ) Installation.

-(a) Set the 332G-2 in position and fasten in place with four mounting screws.
NOTE: In the A P - 1 0 3 F , the 332G-2 Rate G y r o is aligned with the yaw
axis.
(b) Connect the mating connector with the 332G-2 connector receptacle.

May 1/67 22-03-00

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 a
COLLINS
MAINTEKANCE
w MANUAL

I I* 344C-lD, 344C-lG and 344C-lF Instrument Amplifier.

(1) Removal.

(a) Loosen the adjustable retainer nut on the front of the shockmount o r aircraft
equipment rack until the retainer nut disengages.

(b) Slide the 1/4 ATR case forward until free of the mount.

(2) Install at ion .

CAUTION: USE EXTREME CARE WHEN INSTALLING THE 344C-1D OR 344C-1F
TOENSURETHATCONNECTORSMATEPROPERLY.

(a) Slide the 1/4 ATR case into the shockmount o r aircraft equipment rack until
the connectors a r e properly engaged.

(b) Tighten the adjustable retainer nut until the instrument amplifier i s held
securely in place.

J. 344C-3( ) P r i m a r y Servo and 351B-3( ) Servo Mount.

(1) Removal.

(a) Remove electrical connector from 344C-3( ) plug P2.

(b) Remove primary servo plug P1 from mating connector.

(c) Loosen the six hexhead bolts that fasten the 344C-3( ) to the 351B-3( )
Servo Mount.

(d) Carefully remove the 344C-3( ) from the 351B-3( ).

(e) Disconnect the aircraft control cable from the capstan (or the push-rod from
the lever a r m ) .

(f) Remove the four mounting bolts and lift the 351B-3( ) from the mounting
position.

(2) Installation.

(a) Position the 351B-3( ) and secure in place with four mounting bolts.

(b) Connect the aircraft control cable to the 351B-3( ) capstan (or the push-rod
to the lever arm).

CAUTION: USE EXTREME CARE WHEN SLIDING THE 344C-3( ) INTO THE
351B-3( ) SERVO MOUNT TO AVOID DAMAGING THE GEARS.

(c) Slide the 344C-3( ) into place in the 351B-3( ).

(d) Fasten the 344C-3( ) to the 351B-3( ) with the six captive hexhead bolts.
22 -03 -00 Nov 1/68
Page 468
 (e) Connect primary servo plug P1 to the mating connector.

(f) Connect mating connectors to primary servo plug P2.

(g) Adjust servo torque (refer to paragraph 2.C.(3)).

K. 344D-2-33( ) T r i m Tab Servo.

(1) Removal.

(a) Disconnect mating connector from connector receptacle on 344D-2 -33( ).

(b) Remove the master link from the chain, and disassemble chain from sprocket.

(c) Remove the three mounting screws from the base of the 344D-2-33( ) and
lift the unit from the mounting position.

(2) Installation.

(a) Set the 344D-2-33( ) in mounting position and s e c u r e in place with three
mounting screws.

(b) Feed the t r i m chain around the 344D-2-33( ) sprocket and assemble the
master link. (Refer to 344D-2-33( ) overhaul manual for chain tension
adjustment procedures .)

(e) Connect mating connector to 344D-2-33( ) connector receptacle.

L. 345A-4B Sensing Unit.

(1) Removal.

(a) Disconnect mating connectors from the connector receptacles on the two r a t e
gyros that comprise the 345A-4B.

(b) Loosen the four captive mounting screws in the base of 345A-4B and lift the
unit from the mounting position.
(2) Install ation.

NOTE: The 345A-4B must be positioned so the alignment with the aircraft pitch
and roll axes is in accordance with equipment markings.

(a) Set the 345A-4B in position and secure in place with the four captive mounting
screws.

(b) Connect mating connectors to the connector receptacles on the two r a t e gyros.

M. 390D-6A Shockmount.
(1) Removal.
(a) Remove the 344C-1D from the 390D-6A.
May 1/67 22 -03-00
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 -
a
COLLINS
MAINTENANCE

(b) Remove the four mounting screws from the mounting bracket,

(e) Remove the four mounting screws from each of the two connectors and
remove the connectors.

(d) Remove the two mounting screws from the base of each of the five isolators,
disconnect the ground s t r a p , and lift the shockmount free of the mounting
bracket.

(e) Remove the mounting screw from the top of each of the isolators and dis-
assemble the isolators from the shockmount.

(2) Installation.

(a) Assemble the isolators to the shockmount with the top mounting screws.
(b) Set the shockmount in place on the mounting bracket and reconnect the
ground strap.

(e) With the two base mounting screws in each isolator secure the shockmount
to the mounting bracket.

(d) Replace the two electrical connectors and fasten in place with four screws
each.

(e) Set the shockmount in position and mount in place with four mounting screws
through the four holes in the mounting bracket.

N. 562A-5G Flight Computer and 562C-4 Autopilot Amplifier.

(1) Removal.

(a) Loosen the adjustable retainer nuts on the 79OM-1/79OM-lA, o r on the

equipment rack until the nuts disengage.

(b) Slide the 562A-5G o r the 562C-4 forward until clear of the mount o r rack.
(2) Installation.

CAUTION: USE EXTREME CARE WHEN INSTALLING THE 562A-5G OR

562C-4 TO ENSURE THAT CONNECTORS MATE PROPERLY.

(a) Slide the 562A-5G o r 562C-4 into the mount o r equipment rack until the
connectors are properly engaged.

(b) Tighten the adjustable retainer nut until the 562A-5G o r 562C-4 is held
securely in place.

22 -03 -00 May 1/67

Page 470
 COLLINS
3lAINTENASCE
MANUAL

0. 590A-3E Altitude Controller.

(1) Removal.

(a) Disconnect the aircraft static air line from the static air port on the front of
the 590.4-3E.

(b) Loosen the adjustable retainer nuts on the 79OC-1, o r the equipment rack
until the nuts disengage.

(c) Slide the 590A-3E forward until clear of the mount o r rack.
>
(2) Installation.

CAUTION: USE EXTREME CARE WHEN INSTALLING THE 590A-3E TO ENSURE

THAT CONNECTIONS MATE PROPERLY, AND TO AVOID DAMAGE
TO THE AIRCRAFT STATIC AIR LINE.

(a) Slide the 590A-3E into the mount o r equipment rack until the connectors are
properly engaged.

(b) Tighten the adjustable retaining nuts until the 59OA-3E is held securely in
place.

(c) Connect the static air line to the static a i r port on the front of the 590A-3E.
P. 590B-2 A i r m e e d Sensor.

(1) Removal.

(a) Disconnect the mating connector from the electrical connector receptacle on
the 590B-2.

(b) Disconnect the aircraft pitot and static a i r lines from the PITOT and STATIC
air ports, respectively, on the 590B-2.

(c) Remove the four mounting screws f r o m the 590B-2 and lift the unit from the
mounting position.

(2) Installation.

CAUTION: USE EXTREME CARE WHEN INSTALLING THE 590B-2 TO AVOID

DAMAGE TO THE AIRCRAFT PITOT AND STATIC AIR LINES.

(a) Set the 590B-2 in mounting position and fasten in place with four mounting
screws.

(b) Connect the static air line to the STATIC air port, and the pitot air line to
the PITOT air port.

(c) Connect the mating connector to the electrical connector receptacle on the
590B-2.

May 1/67 22-03-00

Page 471
 C 0LLI N S
MAINTENANCE
w MANUAL

9. 614E-2F. 614E-2G. o r 614E-2G1 Pedestal Controller.,

(1) Removal.

(a) Loosen the four captive mounting screws on the face of the pedestal
controller.

(b) Lift the pedestal controller free of the mounting positions until the con-
nector is accessible.

(e) Disconnect the mating connector receptacle on the rear of the unit.
(2) Installation.

(a) Connect the mating connector to the connector receptacle on the

pedestal controller.

(b) Slide the pedestal controller into position and s e c u r e in place with the four
captive mounting screws.

R. 79OC-1 Shockmount.

(1) Removal.

(a) Remove the altitude controller from the 79OC-1.

(b) Remove the two mounting screws from each of the four isolators.

(e) Remove the two top screws that secure the rear plate and disassemble the
rear plat e.

(d) Remove the four screws that fasten the connector to the mount. Remove the
connector.

(e) Remove the ground strap.

(2) Installation.

(a) Scrape the metal surface to provide a good electrical contact and connect
the grounding strap.

(b) Fit -the electrical connector in place and secure with the four mounting
screws.

(e) Replace the r e a r plate and secure with the two top screws.

(d) Set the 79OC-1 in position and fasten in place with two mounting screws in
each of the four isolators.

22 -03-00 May 1/67

Page 472
 COLLINS
MAINTENANCE
w MANUAL

S. 790M-1 Shockmount.

(1) Removal.

(a) Remove the 562A-5G and the 562C-4 from the 79OM-1.
(b) Remove the four mounting screws from each of the four isolators.

(c) Remove the dust cover from the connectors.

(d) Remove the four mounting screws from each connector, and disassemble the
connect0rs .
(e) Remove the ground strap.

(2) Installation.

(a) Scrape the metal surface to provide a good electrical contact, and connect
the grounding strap.

(b) Fit the connectors into place and secure with the four mounting screws on
each connector.

(c) Replace the dust cover.

(d) Set the 790M-1 in position and fasten in place with four mounting screws in
each of the four isolators.

T. 790M-1A Hard Mount.

(1) Removal.

(a) Remove the 562A-5G and the 562C-4 from the 790M-1A.
(b) Remove the mounting screw from each of the four mounting posts (screws
are reached from the underside of the shelf).

(c) Remove the dust cover from the connectors.

(d) Remove the four mounting screws from each connector and disassemble the
connectors.

(e) Remove the ground strap.

(2) Installation.

(a) Scrape the metal surface to provide a good electrical contact and connect
the ground strap.

(b) Fit the connectors into place and secure with the four mounting screws on
each connector. -

May 1/67 22 -03 -00

Page 4 7 3
 COLLINS
MAINTENANCE
ww MANUAL

(c) Replace the dust cover.

(d) Set the 790M-1A in position and fasten in place with one mounting screw in
each of the four mounting posts (screws are inserted from the underside
of the shelf).

U. 8905-1 Shockmount.
(1) Removal.

I (a) Remove the 344C-1F from the 8905-2.

(b) Remove the four mounting screws from the mounting bracket.

(c) Remove the four mounting screws from the connector and remove the
connector.

(d) Remove the two mounting screws from the base of each of the five isolators,
remove the ground s t r a p , and lift the shockmount off the mounting bracket.

(e) Remove the mounting screw from the top of each of the isolators and dis-
assemble the isolators from the shockmount.

(2) Installation.
(a) Assemble the isolators to the shockmount with one screw each.
(b) Replace the ground strap.

(c) Assemble the shockmount to the mounting bracket by fastening in place with
two screws in each isolator.

(d) Replace the connector and fasten in place with four screws.

(e) Set the 8905-2 in position in the equipment rack and fasten in place with four
mounting screws through the four holes in the mounting bracket.

V. 89OP-1 Shockmount.
(1) Removal.
(a) Remove the 161E-1 from the 89OP-1.
(b) Remove the four mounting screws from each of the four isolators.
(c) Remove the ground strap.

(2) Installation.
(a) Scrape the metal surface to provide a good electrical contact for the ground
s t r a p , and connect the ground strap.

(b) Set the 89OP-1 in position and fasten in place with four mounting screws in
each of the four isolators.

22 -03 -00 Nov 1/68

Page 474
 a
COLLINS
MAINTEIVAYCE

FLIGHT
ANNW- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER MISC POWER AMPLIFIER WIRE FUNCTIOk SERVOS MISC DISCONNECT JjOX

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Y P I T C H ATTITUDE CT Y : 20-B AILERON ENGAGE VOLTAGE F
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AP-103F/FD-108 Master, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 439

May 1/67 22 -03-00

Pages 475/476
 a
COLLINS MAINTENANCE
w MANUAL

-
FLIGHT
._
ANNUN- COLUSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT TRIM EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE F W C T I O N AMPLIFIER COMPUTER COMPASS POWER AWLIFIER WiRE FUNCTION SERVOS INDICATOR DISCONNECT J-BOX

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19
12
: 5b- HEADING RATE C2
HDG MOT CONT C 1
:
:
2
2
0
1
:
:
:
:
:
: . .
: : : 2 2 ::

-
11 HDG MOT CONT M l AIRSPEED
: 4 : HEADING DATUM SYNCHRO C' : : 2 3 : SENSOR
: 5 : HEADING DATUM SYNCHRO H ' : f 33 DME 5900-2
12 : : COURSE DATUM SYNCHRO C ' : : 29 8bOE-2 (Jl)
13 : : COLUSE DATUM SYNCHRO H ' : : 39 (Jl) 59 AIRSPEED SIGNAL
DISTANCE INDICATOR FLAG +
95
9b
97
:
:
:
: DISTANCE INDICATOR FLAG
DISTANCE INDICATOR 2b VAC H
- :
:
:
:
9
10
2
58
--
bo :
..
AIRSPEED EXCITATION H
AIRSPEED EXCITATION C

98 7 : DISTANCE INDICATOR 2 b VAC C .. .._ .. . .. .

99- : F A :
50 : DISTANCE INDICATOR UNITS SYNCHRO X : : : : 9
51 : : DISTANCE INDICATOR UNITS SYNCHRO Y : : : : 3
51 : : DISTANCE INDICATOR TENS SYNCHRO X : b
53 : : DISTANCE INDICATOR TENS SYNCHRO Y : : : 5
59 : DISTANCE INDICATOR HUNDREDS SYNCHRO X : : : 7

.. .. . . .. .. .. :Q b9 ++ ELEVATOR SERVO POWER X

PITCH STEERING + UP . I -
. -
-
: 3-31 : tRD-1 :
: PITCH STEERING + DN
ROLL STEERING + LEFT
.: 9-21 :
- . ; @ ;
.. .. :
: ROLL STEERING + RIGHT .
12
13-
31
PI
:
: . . :
:
GO AROUND
BUTTON
:
GO MOUND '

.T HOLD
.:. .:. W : ALTITUDE HOLD INTERLOW . . . ALTITUDE HOLD INTERLOCK
t
:
. 9b
. :. . ALTITUDE HOLD INTERLOW
. . .... .... ...
I
- .
.. .
..
I
..
. ... ... : bb -
- DISCONNECT SWITCH H

-. . :
.. .- ..
39-95 :
:
:
b?
9b - DISCONNECT SWITCH C
GLIDE SLOPE M D E +

..-
DISCONNECT
. .
:
.. : CONTROLLER
: : ALTITUDE
:
SWITCH
.~.
.. .- :: 590A-3A
: :
. . .
-
(Jl)
~. HOLD MODE + I
-
: : 9?-39@
. . V
:
ALTITUDE
ALTITUDE RATE H ' -----SI : 34 19
: ALTITUDE RATE C' -A : 29 15
. . :
:
ALTITUDE
ALTITUDE
ERROR H ' +I
ERROR C '
:
:
33
23-27
l b :
:
91
92 : TPI-1405-044

A P-103F/FD-10 8 M a s k r, I n k rconnecting
Mar 1/73 Wiring Diagram 22-0 3-00
Figure 439 (Sheet 2) Pages 477/478
 a
COLLINS
MAINTENANCE

ww MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUfENT FLIGHT ALTINDE AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATIY( WIRE FUNCTION AWLIFIER COWER CONTROLLER POWER AWLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

33lA-bA bIYE-ZG 3298-7A

0 J1 52 JI J1 J2
AILERON 121A-Z

-
339L3 JI
(JI)

-
13
14
15 -
12 __C_ P I T C H BOOTSTRAP TRANSMIlTER X

-
P I T C H BOOTSTRAP TRANSMITTER Y
I P I T C H BOOTSTRAP TRANSMITER 2
P I T C H BOOTSTRAP EXCITATION H
:
:
:
:
:
:
:
:
:
3
+
9
w
3
f
:

..
:
Y3
99
Y5
.
-
.-
ALTITUDE GAIN CHANGE EXCITATION
A L T I N D E G M N CHANGE NO. I
A L T I W U M = I N CHMGE NO. 2

Ib
2b

- : P I T C H BOOTSTRAP EXCITATION C
BANK BOOTSTRAP TRANSMITTER X
:
:
:
:
:
:
:
35-
37-GW . .-C M U T E R K I N +

--
17 : BANK BOOTSTRAP TRANSMITER Y : 15 : 59
. . 28 BANK BOOTSTRAP TRANSMITTER 2 I 18 ++ EXT P I T C H STEERING A
29 BANK BOOTSTRAP EXCITATION H : 19 '-56EXT P I T C H STEERING B
30 __C__ BANK BOOTSTRAP EXCITATION C I 25 -+ AC P I T C H STEERING A
: HEADING WARNING DATA X 1b -6 AC P I T U I STEERING B
: HEADING WARNING DATA Y : 27 PROCESSED PITCH DATA A
HEADING WARNING DATA 2 : 28 -*
- PROCESSED PITCH DATA B

:
HEADING WARNING DATA H
HEADING WARNING DATA C
HEADING WARNING DATA H '
:
:
18
98
:
:
:
:
1s
57
bO
: SP-
- INTERNAL P I T M S E E R I N G OFF
ALT HOLD OFF +
EXT ROLL STEERING A
+

HEADING WARNING DATA C' 19 -6 EXT ROLL STEERING B

15 : 5 P - PROCESSED BANK CMD A
I b -6 PROCESSED BANK CMD B
35 : 5- PROCESSED BANK DATA A
3b -6 PROCESSED BANK DATA B
. .- 55 . 5-EXT BANK CMD B

: PITCH MONITOR +
- I1 12 : . - ..
59 -6
.. EXT BANK CMD A

- --
GS Mhl : : G L I D E SLOPE ARM. ANN. : b :
. : . .. ..
GS EXT GLIDE SLOPE EXT. ANN. 91
N I L ARM : NAV/LOC ARM. ANN. : b :
: : : 39 :
N I L CAPT NAV/LOC CAPTURE ANN.
. . Q . .
PUR
G S W T f
.: .
38 -RUNWAY -
ANNUNCIATOR POWER 3
RAG . 5
.
: :
.. .. . ... ...
: : : M R BCN
: . .
..-. ....
: : RCVR
: - .. :
..
GA GO AROUND ANN. Ib 512-1
.. : (51)
: : MIDDLE MARKER 43-9
: : : I 8 : 57 : INTERNAL ROLL STEERING OFF +
A : PITCH CONTROL EXC A . . . : 21 NAV NAV : 51RV-I
. LB A N G P I T C H CONTROL
I S . . 10 RCVR CON1 : SELF-TEST
C : P I T C H CONTROL EXC B .. .. .. : 11 SIRV-I 313N-3 : RELAY
D . - .
F TURN CONTROL EXC A 11 .: . .
F TURN CONTROL EXC B a2 :
G TURN CONTROL SIGNAL R 20 :
N I N S MOTOR CONTROL VOLTAGE : .
bl . . -.
P : I N 1 Bb VAC MOTOR EXCITATION C 21t .: - . n : I &

R I N T MOTOR PATE SIGNAL : .

b3 . . !
S I N T MOTOR SIGNAL COMMON
. . : .
2Y . . 55
T : 28 M C PANEL L I G H T PWR . . . K f
1 4
U
X
GRD
.. .. . .
: : GRD ..
.
- - I

Y : ENGAGE VOLTAGE .. .. .- . .
: z .
a : ENGAGE P U S E . . . : 5b
: b : DISENGAGE VOLTAGE
ENGAGE READY
. . .
. _ .
:
:,
37
55
: .. .. .
ALTITUDE HOLD MODE + c
. 38.
.

X .. -. .. . : 53 - YAW DAMPER ENGAGE MOh +

I
Y
z
SPARE
.
..
.
.-
.
..
.
:
.
9 SENSING
m I T h ,,
AA
... .. .. 33YSA-98 @ i 11
BB
. . (ROLL) YAW DAMP SW
CC
... .- .. b5 : ROLL RATE hQTOR GRD A
DD : GYRO MODE
.. .. 8 : 115 VAC POWER B U

AP-10 3F/F D-10 8 Mask r, Interconnecting

Mar 1/73 Wiring Diagram 22-03 -00
Figure 439 (Sheet 3) Pages 47 9/480
 a
COLLINS
MAIYTEIVANCE
ww MANUAL

FLIGHT AUTOPILOT
INSTRUMENT FLIGHT SENSING EMERGENCY
ANNUN- COURSE PEDESTAL DIRECTOR
AMPLIFIER COsWUTER MISC POWER AMPLIFIER WIRE FUNCTION SERVOS UNIT DISCONNECT J-SOX
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION

3YYC-1D 5b2A-5G 15 AILERON 33Y5A-YB l2lA-2

331A-bA blYE-2G 32%-?A
J1 J2 J 1 A J1B 33%-3 J l
9 J1 J2 J l J1 J2 (J1)

- - (PITCH)

I
-
: 21 PITCH DIFFERENTIAL RESOLVER X
: 22 PITCH DIFFERENTIAL RESOLVER Y
:
:
E
10 -
-
PITCH RATE MOTOR a t C
115 VAC POWER
A
c
:
: -23 -PITCH
2Y
DIFFERENTIAL RESOLVER 2
P I T C H DIFFERENTIAL RESOLVER H
:
:
32
31 -
P I T C i i RATE EXCITATIOI. C
PITCH RATE EXCITATIOli H F
: 25-PITCH
- DIFFERENTIAL RESOLVER C : 29 - PITCI! RATE SIGNAL X G
I? -
:
. . 2b
. P .~
I T C H DIFFERENTIAL RESOLVER H ’
~~ ~~ ~~

i-
: P I T C n D:FFERE\TIAL ES3-ViQ C ’ YAW RATE
i@{ z
: 33
-
-
B A W 3IFFEREhTIA. RZSOLVER X
3 A h 6 DIFFERELTIA. ? E S O L E R Y
3A\d DIFFER:\TIA. RESO-MR 2
GYRO
3320-2
bb : YAW RATE MOTOR GRD A
31- BANK DIFFERENTIAL RESOLVER H 13 : 115 VAC POWER B
32 -BANK DIFFERENTIAL RESOLVER C 51 : YAW RATE EXCITATION C E
3 3 -BANK DIFFERENTIAL RESOLVER H ’ 50 : YAW RATE EXCITATION H F
3Y -BANK DIFFERENTIAL RESOLVER C ’ Y8 : YAW RATE SIGNAL X G

SYMBOLS USED: 10. THE 5bZC-9 AND 5b2A-56 SHOULD EE MoUNTEC AS CLOSE TOGETHER AS POSSIBLE,
PREFERABLY ON A DUAL MOUNT. THESE SIGNAL LEADS MUST BE TWISTED AND WIRED
SI W I S T E D SHIELDED PAIR-ADJACENT POINT TO POINT BETWEEN THE UNITS. THE TWISTED PAIRS SHOULD BE KEPT AS
SA WIRES AS SHOWN ON DWWING
SHORT AS PRACTICAL AND MUST ALSO BE SHIELDED I F OVER TWO FEET LONG.
SG SHIELD T I E D TO GROUND AT U N I T COMPARATOR WARNING RESOLVERS. W NOT USE FOR OTHER PURPOSES UNLESS LOADING
11.
SI SINGLE SHIELDED WIRE EFFECT IS EVALUATED.
8 ALL S1 SHIELDED T I E D TO X 1 ETC.
NOTES
STY FOUR WIRES W I S T E D WITH SHIELD
12.

NOTES: 13.
14.
1. ALL WIRE SIZES ARE NO. 22 UNLESS ESIGNATED OTHERWISE BY NUhBERS I N SOUARES. WITH TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING L I N K S INSTALLED
SHIELDED WIRES ARE GROUNDED AT ONE END ONLY- FOR CORRECT SERVO PHASING THE PfiIMARY SERVO CAPSTAN SHOULD TLRN CLOCKWISE MAKE CONNECTIONSASSHOWN BELOW
2. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE WHEN VIEWED FROM THE CAPSTAN END UNDER THE FOLLOWING AIRCRAFT ATTITUDES:
GROUNDED AT M E 51RV-I.
3. FOUR WIRES TWISTED WITH SHEILD FOR COMPATIBILITY I N FUTURE ARINC INSTALLATIONS.
-
Y. A RELAY W S T B E INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF
TEST FEATURE OF THE 51RV-1 WHEN THE AUTOPILOT I S ENGAGED.
AILERON
ELEVATOR
RUDDER
-- RIGHT BAVK
PITCH UP
RIGHT YAW
614E-ZG
Jl
562A.5G
J i A JlB
BOA 3A
!Jli..
SSZC-4
J1 J1
5. THE ALTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N W I S DRAWING REFLECTS !TPi !BPI (TP‘ ,BPI
LOADS AS FOLLOWS: 15. POWER FROM A PARTICULAR C I R C U I T BREAKER OR FUSE MAY PROVIDE POWER FOR MORE
THAN ONE EQUIPMENT. T H I S K L L BE INDICATED I N THE INTERCONNECT POWER COLUMN
V ................. ALTITUDE HOLD MODE+ ........................ 34
AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS ALTITUDE HOLD MODE+ 47 ................... 20 ................................ 38
BY A LETTER WITH kh OCTAGON SYMBOL AROUND I T , CAPITAL LETTERS FOR DC AND LOWER
CASE LETTERS FOR AC.
200 OHMS TO-FROM 100 OHMS JUMPER BP-93 TO BP-33 OF 51RV-1
500
500
OHMS
OHMS
GLIDE SLOPE POINTER
GLIDE SLOPE FLAG
200
250
OHMS
OHMS
JUWER
JUMPER
TP-8 TO TP-8 AND TP-3 OF SIRV-1
TP-21 TO TP-2b OF 51RV-1
A - -
28 VDC DIMMING CIRCUIT a - -
5 VDC DIMMING CIRCUIT
500
500
OHMS
OHMS
LOC FLAG
COURSE BAR
250
200
OHMS
OHMS
JUMPER
JUMPER
DP-32 TO EP-Y1 OF 51RV-1
BP-39 TO BP-30 AND BP-YE OF 51RV-1 G -
B 1 CI DI E 2 8 VDC 5 AMP
28VDCl/\MP - -
b, c , d 115 VAC 2 AMP
e g 115 VAC 1 AMP
f - 115 VAC 3 AMP
b. THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE
lb. M E GO AROUND RELAY I S INSTALLED FOR WINGS LEVEL. PITCH UP GO AROUND.
AUTOMATIC FLIGHT CONTROL SYSTEM-
GO AROUND BUTTON I S N O W L L Y OPEU AND NORMALLY I S INSTALLED ON CONTROL
?. POWER LEADS DENOTED BY “ D I W SHOULD BE T I E D TO COCKPIT L I G H T DIMMING CIRCUITS.
COLUMN WHEEL. TO DEACTIVATE GO WOUND PROVISION REMOVE THE RELAY AND
R. SENSING W I T 395A-Y( ) AND RATE GYRO 3320-2 SHOULD BE LOCATED AS CLOSE TOGETHER
CONNECT THOSE WIRES TOGETHER THAT ARE CONNECTED BY THE NORMALLY CLOSED
AS POSSIBLE. CONTACTS OF THE RELAY.
9. W N W C I A T O R S MOSEN HJST NOT EXCEED 1W M - A COLMDW +28 VDE I S USED FOR
17. EQUIPMENT SHOWN I N MISC COLUMNS M Y NOT HAVE COMPLETE WIRING INFORMATION
W N W I A T O R WKR. AWUICIATION V M I E S VlW THE PAQTICUAQ INSTALLATION.
INDICATED. BEFORE WIRING A P P L I C m L E SYSTEM MANUALS FOR THAT EQUIPMENT
DEPENDING UPON DESIRED OPERATICMI S P E C I F I C AMU(CIATQ(S M Y Bf DELETED.
SHOULD B E CHECKED.
18. CONNECTIONS TO TRIM TAB MOTOR COliTROL DEPENDS ON AIRCRAFT RIGGING.
19. PROVISIONS FOR RADIO ALTIMETER (OPTIWAL).

AP-103F/FD-108 Master, Interconnecting

M a r 1/73 Wiring Diagram 22 -03-00
Figure 439 (Sheet 4) Pages 481/482
 e
COLLINS
hIAISTENASCE
Qv lMANUAL

FD-108lAP-103F AFCS FOR AEROCOMMANDER b8DT

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRMNT FLIGHT A
AUTOPILOT
LPLIFIER EERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION MPLIFIER WUTER MSC POWER W I F E FUNCTION SERVOS MISC DISCONNECT J-BOX

331A-bA LlYE-2F 3298-7A 12-

@ Jl J1 Jl Jl J2 J1

.
-..
....
.
...
.
...
b
7
8 -
e&-
PITCH ATTITUDE ERROR H '
e +
P I T O I ATTITUDE ERROR

9-PITCH
C'
PITCH ATTITUDE SERVO DRIVE M2
ATTITUDE SERVO DRIVE C-
29
23
28
27
-
-
-
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
: :
+AILERON FIELD NUBER 1 A
B
C
E

--
13 AILERON 51- SIGNAL C
.
10 e+ PITCH A T T I T W E RATE G2 25
- : : : VERT 19 AILERON EXCITATION C
..
..
..
...
..

..
.
..
.
11 e&-
1-?-
2 e&-
Y2
-3Y
Y Y e+
- PITCH ATTITUOE RATE C2
hUNUAL PITCH COMMAND H'
MWUAL PITCH C O W D C'
V-SAR P I T C H COMMAND SERVO DRIVE M I
V-SAR PITCH C W A N D SERVO DRIVE C-
V-BAR P I T M COMMAND RATE
2b
: -
.
:
:
:
11
10
8
3b
2b

'
:

:
:
'
:

:
:
REF
: 332D-11
: (J1)

i
i
15 I
l b -
+
AILERON
AILERON
12 --t--sj+ AILERON
11
...-+- ...
l?
AILERON
AILERON
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
SERVO ORD
RATE SIGNAL
G
H
L
R
S

I I !I ... ..
... ...-
-
95-6V-BAR PITCH C O W D S I G C O M A 9

...
YO -P- V-BAR PITCH POS XMTR X
v m PITCH ?os m r
v i e&- ..
. (J2,

f
..
.....
..
.

...
.....
.
Y

17 -
3 _C_ PITCH A T T I T W E CT X

-
PITCH ATTITUDE CT Y
5 __C__ PITCH A l T I T U D E CT Z
BANK ATTITUDE CT X
t
30-A
20-0

.
:
3D-D
C
.
.
~.
.. ..
....
.
..
...
AILERON ENGAGE VOLTAGE
A I L E W ENGAGE VOLTAGE
E
F

-
18 BANK ATTITUDE CT Y 2 0 - E
19 BANK A T T I T U N CT 2 F ELCVATOR
.. .. 20 -+ BANK ATTITUDE ERROR H '
i. i. i. i . 13963

.. ..--
21 e&- BANK ATTITUDE ERROR C'
-
17
18
. . (Jl)

...
.
...
.
12
23-BANK
BY - 9
25 e&-
-
-
B w ( ATTITUDE SERVO W I V E M2
A T T I T W E SERVO DRIVE C-21
BAHK ATTITUDE RATE G2
BAM( ATTITUDE RATE C2
22

-
19
I I I
: : :
i
:
.
12 b5
g+
ELEVATOR
28 VDC
+ELEVATOR

-
13 - S t ELEVATOR
F I E L D NUHBER 1

FIELD N M E R 2
PGNAL C
A
B
C
E

-
-
3b V-BAR ROLL C W D SERVO DRIVE U2 28 : : a : 19 ELEVATOR EXCITATION C i
.~. .. 37 V-M m u CWD SERM DRIVE c 27 : : J : 15 ELEVATOR POSITION EXCITATION H G
..
.. - . . i: :i i : l b --5+ ELEVATOR RATE EXCITATION H H

. ..-- 38 e+
39-6
V-BAR ROLL C O W D RATE G2
V-BM mu CWD SG
I COM-
28
ab H-
a E i z ! T
GQD
:
:
12
11
++-
ELEVATOR
ELEVATOR
POSITION SIGNAL
SERVO GQD
L
d

-..
.....
..
...
..
.....
..-
...
.. 3~

:
31
:
MAR
3s e&-
:
-+

-
-
ROLL POS XMTR ~i
v - 8 ~m u POS XMTR c i

18
:
:
115 VAC ATTITUDE P W E R
GIROMDN+
GYRO HIGH LEVEL FLAG

-
GIRO HIGH LEVEL FLAG
+
-
--
5
29
31
32
.
:
P
23
: : .
:
:
9
:

:
:
:

10
:
: I

:
:
:
G

N
:
:
Q
- :
...
...
..
17
...++
ELEVATOR

...
..
RATE SIGNAL

ELEVATOR ENGAGE VOLTAGE

S

(J1)
J
:
.
:
Y-STEER
.
:
FLAG 2 : : NAV
Rcm .. .. ELEVATOR ENGAGE VOLTAGE H

.-. ...
STEERFLAG 82-2
. . . -.. ...
: lb -
- +28 VDC FLAG POWER 5Y
: 5lRV-1
(TP)
:
. .
3
33

35
.
:
f
10
11 -
12 - G L I D E
GLIDE SLOPE DEV + UP
GLIDE SLOPE DEV + DN
SLOPE LOW LEVEL FLAG +
. 2 2 - 9
: 21
. . RUDDER
33YC-3
(J1)
3b
. - : 13-GLIDE SLOPE LOW LEVEL FLAG - . 22 +RUDDER F I E L D NLWER 1 A

29
28
1

.
.
.~
.. ..
.
.
:
.
:
:
:
.
5
9
:
-
GLIDE SLOPE HIGH LEVEL FLAG +
t 51- COLRSE RESOLVER A

b -VORlLOC DEV + LEFT

- V W l L O C DEV + RIGHT
V W l L O C HIGH LEVEL FLAG
LOC FREQ VOLTAGE +
+
. .
:

:
:
11-27
. :.
t
:
f
32-
22-
11 -39
lb
(BP)
90

50
@ bi
9
93 -
19
95-
9b
f
-
-+
1
28 VDC
f RUDDER
RUDDER
RUDDER
RUDDER
RUDDER
F I E L D NUhBER 2
SIWAL C
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION C
B
C

G
H

? : :
:
5- COURSE RESOLVER B . : :
t

:
93-38
: ?
:
I
Y2 -
91
f
-* RUDDER POSITION SIGNAL
RWDER SERVO GQD
L
R
8
3 :
SV+ COLRSE RESOLVER H
STY- COURSE RESOLVER C :
21
23 .
97 --C-Sf
. RUDDER RATE SIGNAL S
(J1)
Y
5
:
:
:
5- COURSE RESOLVER D
-5.3- COURSE RESOLVER E
. . :
:

:
2Y .
.. ... RUDMR ENGAGE VOLTAGE
RUDDER ENGAGE WLTAGE
b 5- COURSE RESOLVER F
.: 2b2? .-. ..
...-
7 X COLRSE RESCCVER G TRIM
31
32
VORlLOC FLAG +
V W l L O C FLAG- . . .: 92Y3
Y1
... TAB
SERVO

.. ..
2b TO-FROM ARROY (+ TO) 33YL2-33D
27
... . .... ....
TO-FROM MROW ( + FROM)
... ... ....
:
.... .....
9Y (J1)

.. ...- . .
: GQDG
-QD
2 8 v M PWER
B
A
. . . . .. . . . . .~.
. .- TRIM ENGAGE VOLTAGE
T R I M ENGAQ (RD
L
M

:
:
.
: : .
..
: :
:
.

.l
:
l
h
I

. . . . . . .
53
52
:

-
34 -dc- TRIM TAB K)T CONT
. 33 4 CTRIM TAB WT CONT
-
33 -AILERON
34
TRIM INDICATOR
AILERON TRIM INDICATOR
RUDDER TRIM INDICATOR
m CER TRIM INDICATOR
F

767-82s-00'

AP-103F/FD-108 Aerocommander 680T, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 440

May 1/67 22-03-00

Pages 483/484
 a
COLLINS
MAINTENANCE
w MANUAL

INSTRUhikT FLIGHT AJTOP;LOT

E'!:RGE!.CY
WIRE FiiNCTIOIl MPLIFIER COVPUTER COMPASS POWER AWPLIFIER h'IHh R h C T I O h
SEHVOS :xsc DISCOhHECT
331A-bA blYE-2F 3298-7A AILEfiOl.
8 Jl J2 J1 J1 J2 23%-3
....
l?lk-2
J l

: J NAV/LOC MODE + : : 9 b : : 47
: 94-49 - : GO AROUND MODE +
: 1 4 - d :

ALT

AP-103F/FD-108 Aerocommander 680T,

Mar 1/73 Interconnecting Wiring Diagram 22 -03 -00
Figure 440 (Sheet 2) Pages 485/486
 COLLINS
MAINTENANCE
w MANUAL

FLIGHT
AhNUN- COURSE PEDESTAL SIRECTOR INSTRUMENT FLIGHT ALTITUDE AvTOPILOT
EMERGENCY
CIATORS I LICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIEP COMPUTER CONTROLLER POWER AV'LIFIER WIRE FlrkCTiOII SERVOS
MISC DISCOldiECT J40X
3,lh-bA LIVE-2F 3290-?A 3YYC-lD 5b2A-5G 590A-3A & AILEROli
@ i. J2 JI J1 52 33,c-3 121M
fJ1) Jl
12 : PITCH 3OOTSTRAP TRANSMITTER X : : : 3 9 . 43- ALTITUDE GAIN CHAivGE EXCITATION
13
1Y
:
:
P I T C F BOOTSTRAP TRAiiSMITTER Y
P I T C l i 2OOTSTRAP TRA?!SMITER Z
:
:
:
:
:
:
9
9
2
3
:
:
49
45-
-ALTITUDE
ALTITUDE
GAIN CHANGE NO. 1
GAIN MAVGE NO. 2
15 : P I T C H 3OOTSTRAP EXCITATION H : : : 3b-
1b
2b
27
:
:
:
P I T C H SOOTSTRAP EXCITATION C
BANK BOOTSTRAP TRANSMITTER X
DANK BOOTSTRAP TRANSMITTER Y
:
:
:
:
:
:
35-8
37 - GRD
: 59 - COMPUTER MON +
26 : DANK BOOTSTRAP TRAkSMITTER Z : i n -SFL EXT PITCH STEERINS A
25 : BANK BOOTSTRAP EXCITATION H : 19 - - S b EXT PITCH STEERINI D
30 : BANK BOOTSTRAP EXCITATION C . 25 --S+ AC PITCH STEERING A
: HEADING WARNING DATA X : 2 6 --Sb AC PITCH STEERING 5
: HEADING WARNING DATA Y : 27 PROCESSED P I T C H D I T A A
.
:
HEADING WARNING DATA Z
HE4DING WARNING DATA H :
:
28 -
57
bo
-
6 PROCESSED PITCH DZTA 0

- INTERNAL PITCH SlliERING OFF

ALT HOLD OFF +
+
HEADING YARNING DATA H' 1H : S- EXT ROLL STEERING A
HEADING WARNING DATA C' :9 : s b EXT ROLL SXERNIG B
25 -FL PROCESSED BAVK CMO A
2b : 5 6 PROCESSED BANK CMD B
35 : S S i PROCESSED BANK DATA A
36 - S b PROCESSED BANK DATA B
55 : S- EXT BANK CMD B
54 : 5 6 EXT BANK CMD A
PITCH MONITOR + - 12 :
:
- : 12

- --
GS ARhl : : GLIDE SLOPE ARM. ANN. : b :
GS EXT : : GLIDE SLOPE EXT. ANN. : 92 :
li1L ARM : NAVlLOC ARM. ANN. : : b :
N I L CAPT : : : NAVlLOC CAPTURE ANN. : : 3 9 :
. . .
PWR
GS CAPT : :
:
38
ANNUNCIATOR POWER
-
RUNWAY FLAG - ..
1
..
5 :
..
: : : MKR BCh
: : : RCV2
GA GO AROUND ANN. - .
:
l b
:
: 512-4
: (J1)
. 93-4
: : 1 8 : 57 : INTERNAL mu STEERING OFF c
. . . : 21 NAY NAV : 51RV-1
a : PITCH CONTROL SIGNAL . . . : 20 RCYR CONT : SELF-TEST
C
D
: PITCH CONTROL EXC B
... ..
.
..
.
: 22 51RV-1
(J2)
313N-3
(J2)
:
:
RELAY

: E : TURN CONTROL EXC A . . . 21 : 19

1 : TURK CONTROL EXC 0 . . . 22 : L : i
G : TURN COHTROL SIGNAL . . . 20 :
I
I
N : 1f:T MOTOR CONTROL VOLTAGE . . . . b2 54
P : I N T 2b VAC hOTOR EXCITATIO:! C . . . 24 : n : i
R : I N S MOTOR RATE SIGNAL . . . : b3 I
: s : I k T MOTOR SIGNAL COlNnON . . . : 24 55
: T 28 VDC PANEL L I G d T PWR . . . K : I
: : :
,I GRD
..
.
. .
. .
.
GRD
- A

X . . .
SPARE .. .. .. : 9
2 .. .. .. UIjIT
AA .. .. .. 3395A-40 @ :
BD . . . (ROLL) : YAW DAMP SW

AP-103F/FD-108 Aerocommander 680T,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 440 (Sheet 3) Pages 487/488
 a
COLLINS
MAINTENANCE
Qw MANUAL

FLIGHT
hh!NUI!- COURSE PEDESTAL DIRECTOR I N S T W * X N T FLIGHT AUTOPILOT
CIATORS INDICATOR COXTROLLER INDICATOR SENSING EMERGENCY
WIRE FUNCTION AMPLIFIER COMPUTER MISC POWER AMPLIFIER WIRE FU:II.TION SERVOS UNIT DISCONiECT J-BOX

9
331A-bA
J1 JZ
blYE-ZF
Jl
3298-?A
J1 J2 Q AILERON
33YC-3 331151143 121k2
(Jl) Jl
: 21 -
- PITCH DIFFERENTIAL RESOLVER X
- (PITCH)
:
:
f22
23 -
-
PITCH
PITCH
DIFFERENTIAL RESOLVER Y
~~~~~ ~

DIFFERENTIAL RESOLVER Z
:
:
E
10 -
-
PITCH RATE MOTOR GRD
115 VAC POWER
A
8
:
:
:
2Y
25
26
-
-
PITCH
PITCH
PITCH
DIFFERENTIAL RESOLVER H
DIFFERENTIAL RESOLVER C
DIFFL'RENTIAL RESOLVER !I'
:
:
:
32
31
29
-
-
P I T C H RATE EXCITATION C
P I T C H RATE EXCITATION H
PITCH RATE SIGNAL X
E

28 -
1'7 -PITCH
bAhK
DIFFERENTIAL RESOLVER C '
DIFFERENTIAL RESOLVZR X YAW RATE

30 -
29 -BALK

- SANK
DIFFERENTIAL RESOLVER Y
DIFFERENTIAL RESOLVER Z
GYRO
332G-2
31
32 -
-
SALK
BANK
DIFFERENTIAL RESOLVER H
DIFFERENTIAL RESOLVER C
bb
10
:
:
YAW RATE MOTOR GitD
115 VAC POWER
A
B
33
39 - SAliK
SANK
DIFFERENTIAL RESOLVER H '
DIFFERENTIAL RESOLVER C'
51
50
Y8
:
.
:
YAW RATE EXCITATION C
YAW RATE EXCITATION H
YAW RATE SIGNAL X
E
F
G

SYIWOLS "SED:
11. COMPARATOR WARNING RESOLVERS. DO NOT USE FOR OTHER PURPOSES UNLESS LOADING
59 TWISTED SHIELDEC PAIR-ACJACENT EFFECT I S EVALUATED.
S& WIRES AS SHOW:: ON OR&'ING 12. TOTAL WIRE RUN FROM BUSS TO 12IA-8 TO 5b2C-Y TO 33YC-3 ( P I N 8 ) FOR EACH
SG SHIELD T I E D TO GROUtrD AT U N I T PRIMARY SERVO MVST NOT EXCEED 90 FEET I F AWG 20 WIRE I S USED. WHEN GREATER
51 SINGLE SHIELDED h'IRE THAN 40 FEET. INSTALL TERMINALS AT SbPC-Y MOUNT AND RUN AWG 20 WIRE FROM

8 ALL SI SHIELUED T I E D TO X l ETC.

t1OTES
STY FOUR WIRES TWISTED I!ITd SHIELD
13.
1Y.
Sb2C-Y TO TERMINAL AND AWG I b WIRE FROM TERMINAL 344C-3 P I N 0.
AN ISOLATED W D E SWITCH E PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.
A E K ' O H M S 112 WATT 10% RESISTOR I S REQUIRED ON EACH TRIM INDICATOR MOVEMENT.
WITH TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING L I N K S INSTALLED
r!OTES: FOR CORRECT SERVO PHASING THE PRIMARY SERVO CAPSTAN SHOULD TURN CLOCKWISE MAKE CONNECTIONS AS SHOWN BELOW.
WHEN VIEWED FROM THE CAPSTAN EtID UNDER THE FOLLOWING AIRCRAFT ATTITUDES: PEDESTAL FLIGHT ALTITUDE AUTOPILOT
1. ALL 'VIRE S I Z E S ARE NO. 22 UNLESS DESIGNATED OTHER!,/ISE 2Y NUMBERS I N SQUARES.
SHIELDED WIRES ARE GROUNDED AT ONE END ONLY. - CONTROLLER WIREFUNCTION COMPUTER CONTROLLER AMPLIFIER

--
AILERON RIGHT DANK
2.
2- SHIELDS 0 11 'THE
011 Tb hAV RESOLVER LEADS FROV, THE NAVIGATION RECEIVER SHOULD EE ELEVATOR PITCH [OWN J1
614E-2G 562A6G 590A.3A 562C.4
GROUUDED AT THE 51RV-1. RUDDER RIGHT YAW J l A J l B fJl1 Jl J1
3. FOUR WIRES TWISTED WITIi SHEILD FOR C O M P A T I B I L I R I N FUTURE ARINC INSTALLATIONS. ITPI @Pi IT?) 13PI
Y. A RELAY W S T BE IhSTALLED I P ! THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF 15. POWER FROM A PARTICULAR C I R C U I l BREAKER OR FUSE MAY PROVIDE POWER FOR MORE V ......... ........ ALTITUDE HOLD MODE+ .............. ..._........34
TEST FEATURE OF THE 51RV-1 WHEL THE AUTOPILOT IS ENGAGED. THAN ONE EQUIPMENT. T H I S WILL BE INDICATED I N THE INTERCONNECT POWER COLUMN ALTITUDE HOLD MODE+ 47 .................... 20. ................. ...................... 33
5. THE AUTOMATIC FLIGHT COhTROL SYSTEM AS CONNECTED I N T H I S DRAWING REFLECTS BY A LETTER WITH AN OCTAGON SYMBOL AROUND I T . CAPITAL LETTERS FOR DC AND LOWER
LOADS AS FOLLOWS: CASE LETTERS FOR AC.

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS A - 28 VDC DIMMING CIRCUIT
-
a - -5 VDC DM
I MN
IG CIRCUIT

200 OHMS
500 OHMS
TOJROM
GLIDE SLOPE POINTER
100 OHMS
200 OHMS
JUMPER
JUMPER
B P 4 3 TO BP-33 OF 51RV-1
TP-8 TO TP-Z AND TP-3 OF 51RV-1
G -
0, C, D, E 28 VDC 5 AMP
2 8 V D C l M -
b , C, d 115 VAC 2 AMP
e 115 VAC I AMP
f - 115 VAC 3 liMp
500 OHMS GLIDE SLOPE FLAG 250 OHMS JUHPER T P - Z l TO TP-2b OF 51RV-1
500 OHMS LOC FLAG 250 OHMS JUMPER BP-32 TO BP-Yl OF 51RV-1 lb. THE GO AROUND RELAY I S INSTALLED FOR WINGS LEVEL, PITCH UP GO AROUND.
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO EP-30 AND BP-48 OF 51RV-1 GO AROWD BUTTON IS NORMALLY OPEN RID NORMALLY I S INSTALLED ON CONTROL
COLUMN WHEEL- TO DEACTIVATE GO AROUND PROVISION REMOVE THE RELAY AND
b. THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE CONNECT THOSE WIRES TOGETHER T W T ARE CONNECTED BY THE NORMALLY CLOSED
AUTOMATIC FLIGHT CONTROL SYSTEM. CONTACTS OF THE RELAY.
?. POWER LEADS DENOTED BY "DIM" SHOULD BE T I E D TO COCKPIT L I G H T DIMMING CIRCUITS. 17. EQUIPMENT SHOWN I N M I X COLUMNS MAY NOT HAVE COMPLETE WIRING INFORMATION
8. SENSING U N I T 3Y5A-Y( ) AND RATE GYRO 3 3 2 6 2 SHOULD BE LOCATED AS CLOSE TOGETHER INDICATED. BEFORE WIRING APPLI:ABLE SYSTEM MANUALS FOR THAT EQUIPMENT
AS POSSIBLE. SHOULD BE CHECKED.
9. ANNUNCIATORS CHOSEN MUST NOT EXCEED 100 MA. A COMMON +88 W C IS USED FOR 18. CONNECTIONS TO TRIM TAB MOTOR CI14TROL DEPENDS ON AIRCRAFT RIGGING.
ANNUNCIATOR POWER. ANNUNCIATION VARIES WITH THE PARTICULAR INSTALLATION. 19. PROVISIONS FOR RADIO ALTIMETER (OPTIONAL).
DEPENDING W O N DESIRED OPERATION, S P E C I F I C ANNUNCIATORS MAY B E DELETED.
10. THE 5b2C-4 AND 5b2A-5G SHOULD BE MOUNTED AS CLOSE TOGETHER AS POSSIBLE,
PREFERABLY ON A DUAL MOUNT. THESE SIGNAL LEADS W S T B E TWISTED AND WIRED
POINT TO POINT BETWEEN THE UNITS. THE TWISTED P A I R S SHOULD B E KEPT AS
SHORT AS PRACTICAL MID MUST ALSO BE SHIELDED I F O M R TWO FEET LONG. THE
WIRING SHOULD BE POINT TO POINT.

AP-103F/FD-108 Aerocommander 680T,

Mar 1/73 Interconnecting Wiring Diagram 22 -0 3-00
Figure 440 (Sheet 4) Pages 489/490
 a
COLLINS
JIAISTESASCE
MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL WlRE FUNCTION AUTOPI LOT
DIRECTOR INSTRUMENT FLIGHT SERVOS EM ERG EN CY
CIATORS INDICATOR CONTROLLER INDICATOR AMPLIFIER COMPUTER MlSC POWER AMPLIFIER WIRE FUNCTION AILERON MlSC DISCONNECT J-BOX
33 I A-6A 614E-2F 329B-7A 344c- IO 562A-5G I Q 562C-4 334c-3 12 I A - 2
@ JI J2 JI JI J2 JI J2 JIA JIB
I I JI JI (JI) JI
I I I I (TP) (BP) (TP) (BP) (TP) I I
6 S p PITCH ATTITUDE ERROR H' 24 14
I I I I A
I I 7 S- PITCH ATTITUDE ERROR C'
I @ 62 B I
I I 8 PITCH ATTITUDE SERVO DRIVE M 2 -28
23 I I I I I C I
9 PITCH ATTITUDE SERVO DRIVE C -27 I I I I I Y
S I - AILERON SIGNAL C
I I IO S -PITCH
P
ATTITUDE RATE G2 25
I I I
VERT
I
13
14 AILERON EXCITATION C
E
F I
I I I1 S-PITCH ATTITUDE RATE C2 26 REF 15 AILERON POSITION EXCITATION H - G I
I
I S- MANUAL PITCH COMMAND H' 36 I 332D- I I 16 SI - AILERON RATE EXCITATION H H
I 2 S1MANUAL PITCH COMMAND C' 26 (Jl) I
I I 42 V-BAR PITCH COMMAND SERVO DRIVE M I II I I I 12
II
S I -AILERON POSITION SIGNAL
X I- AILERON SERVO GRD
L
R I
43 V-BAR PITCH COMMAND SERVO DRIVE C IO I ;I I 17 S I - AILERON RATE SIGNAL S
I I 44 S -V-BAR PITCH COMMAND RATE
8 I I I 37
I I
I I 45 SPV-BAR
PITCH COMMAND SIG COM 9
I I
P 27

I I
40 S-V-BAR PITCH POS XMTR X 7
uIl
w
I 28
41 S e V-BAR PITCH POS XMTR Y 6 I I I (J2) I
I I 3 PITCH ATTITUDE CT X 30 A I AILERON ENGAGE VOLTAGE A E
4 PITCH ATTITUDE CT Y 20 B
I I
I I 5 PITCH ATTITUDE CT Z C
AILERONENGAGEVOLTAGE B F

- I I I I
I I 17 BANK ATTITUDE CT X 30 0
18 BANK ATTITUDE CT Y 20 - E
I I
I I 19 BANK ATTITUDE CT Z F
I ELEVATOR I
I I 20 S- BANK ATTITUDE ERROR H' 18 I I I '7 I 334c-3
21 S BANK ATTITUDE ERROR C' 17
I I I
R
I I I (JI)
I I 22 BANK ATTITUDE SERVO DRIVE M 2 - I A
I I
23 BANK ATTITUDE SERVO DRIVE C 22
21 I I I :I I
B
24 S -BANK ATTITUDE RATE G2 19
- I I C
I
I
I
I
25
36
s BANK ATTITUDE RATE c 2
V-BAR ROLL COMMAND SERVO DRIVE M 2
20
28 II II i
3 I I
I
I3
14-
- S2 -ELEVATOR SIGNAL C
ELEVATOR EXCITATION C
E
F

I
I
I
I
37
I
38
I S
V-BAR ROLL COMMAND SERVO DRIVE C

-V-BAR ROLL COMMAND RATE G2 I

27
I
25
I
I
I
I
9
.I-

K
FAST
ERECT
I
I
15
16
12-
- ELEVATOR POSITION EXCITATION H
- SZ-ELEVATOR
S2-ELEVATOR
RATE EXCITATION H
POSITION SIGNAL
- G
H
L
39 sI-
V-BAR ROLL COMMAND SIG COM 26 H -GRO I I II - X2-ELEVATOR SERVO GRD R
I I 34 S ---BAR ROLL POS XMTR H' 24 I I I 17- 5 2 -ELEVATOR RATE SIGNAL S
I I 35 S e V-BAR ROLL POS XMTR C' 23 I I G I
I I
I I I 15 VAC ATTITUDE POWER
GYRO MON t
5
29 10- N
A @ I I
I
I
I I I I
I I 31 GYRO HIGH LEVEL FLAG t 31
I I I (J2)

I
18- GYRO HIGH LEVEL FLAG - 32 I NAV RCVR I ELEVATORENGAGEVOLTAGE A J
I 4- STEER FLAG - 2 II I 51RV-I
I ELEVATORENGAGEVOLTAGE B H
I I I STEER FLAG - 2 28 UP)
I I
I I I 1 I
I I 16 -t28 VCC FLAG POWER 54 I I I I
I 33 IO -GLIDE SLOPE DEV t UP 32 8 0 RUDDER
I
34 I I -GLIDE SLOPE OEV t DN 22 9 I 334c-3
I 35 12 -GLIDE SLOPE LOW LEVEL FLAG t 21 I (JI) I
I 13 -GLIDE SLOPE LOW LEVEL FLAG - S3 - RUDDER FIELD NUMBER I A
36
I I GLIDE SLOPE HIGH LEVEL FLAG t II
22
27 S 3 - 2 8 VDC B
I
I I I I (BPI 5 3 -RUDDER FIELD NUMBER 2 C I
I 29 6- VOR/LOC OEV t LEFT 32 - 40 43 5 3 -RUDDER SIGNAL C E
I
28 5- VOR/LOC DEV t RIGHT 22 -39 44 RUDDER EXCITATION C F
I I 9 - VOR/LOC HIGH L E V E L FLAG t II -50 45 RUDDER POSITION EXCITATION H - G I
I I LOCFREQVOLTAGEt 43 -38 I
46 5 3 -RUDDER RATE EXCITATION H H
I
42 S 3 -RUDDER POSITION SIGNAL L
I 41 X3-RUDDERSERVOGRD R I
: :
~

I S -COURSE RESOLVER H 21 47 5 3 -RUDDER RATE SIGNAL S

Q 3 s PCOURSE
RESOLVER c 23 (J2)
I
4 S -COURSE RESOLVER0 24 RUDDER ENGAGEVOLTAGE A B
5 s ECOURSE
RESOLVER E 25 RUDDER ENGAGEVOLTAGE B c TPI-3124-064

AP-103F/FD-108 Aerocommander 1121 J e t , Interconnecting Wiring Diagram (Sheet 1 of 6)

Figure 441

Nov 1/68 2 2 -03 -00

Pages 491/492
 FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT SERVOS EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER N A V RCVR POWER AMPLIFIER WIRE FUNCTION AILERON MISC DISCONNECT J-BOX
33 I A-6A
JI J2
6 I4E-2F
JI
3298-7A
JI J2
344C- ID
JI J2 JIA
562A-5G
JIB
51RV-I
Q JI
562C-4
JI
334c-3
(J 1:
121A-2
JI
Q l I I (7% (BPI (TP) (8P) (TP)
I (TP) (BP) I
6
I I I
S- COURSERESOLVERF
I I I
26
I I I I
7 S COURSE RESOLVER G 27 I I I I
31 VOR/LOC FLAG t 41 TRIM
32 VOR/LOC FLAG - 42 I I I COUPLER
26 TO-FROM ARROW (+ TO)
TO-FROM ARROW (+ FROM)
43
44
I I I 161A-I
27
I I I I I ARM UP
I I I
I I TRIM UP
UP RELAY GRD
I
I
FAILURE WARNING LIGHT TO AIRCRAFT I
I ARM DN
TRIM DN I
I
GRD-
I
I
I !
DN RELAY GRD
X 4 - T R I M COUPLER GRD
31
I
II
I I 5 VAC 8 I
I I I
I I COMPASS @I I 1
TRIM ENGAGE VOLTAGE
TRIM ENGAGE GRD
20
32
L
M
I I 1 @ 328A-2A I 36-S4-TRIM -
INPUT DN 24
I I (JI)
'
(J2),
I 35 - S4-TRIM INPUT DN t 22
ELEVATOR TRIM INDICATOR
I 34 -S4 -TRIM UP - 13
ELEVATOR TRIM INDICATOR 3 3 3 -S4-TRIM UP t II
h
i
AILERON TRIM INDICATOR
AILERON TRIM INDICATOR
33
34
I
I I 1 RUDDER TRIM INDICATOR 52 I
I I
n RUDDER TRIM INDICATOR
1 I 53 I
I I I I I , I I
COMPASS MON - 30 I I
I I COMPASS MON + 29 14- 25 I I I

I I I l l I
'P't 78
COMPASS DATA Y
I I I ? I I
11-3 COMPASS DATA 2 I
1 I 4 50 -COMPASS DATA Y
I I I 3 I 5l- COMPASS DATA Z
30 COMPASS FLAG + 31
I 24 COMPASS FLAG - 32
27-
1 1
GRD
I
I 15 26 VAC HDG PWR 15 22- 5
I
I 16
20 -
S
COMMON
HEADING ERROR SYNCHRO C'
16
17
30- I
I
I 21 S
-
S P
HEADING ERROR SYNCHRO H'
HEADING RATE G2
18
I 13
14 S- HEADING RATE C2
19
20
I 12 HDG MOT CONT C I 21
I II HOG MOT CONT M I 22 I
4 HEADING DATUM SYNCHRO C' 23 I AIRSPEED
I 5 HEADING DATUM SYNCHRO H' 33 DM E I SENSOR
12 COURSE DATUM SYNCHRO C' 24 860E-2 5908-2
13
45
COURSEDATUMSYNCHROH' 34 (JI) I (JI)
DISTANCE INDICATOR FLAG t 9 59 AIRSPEED SIGNAL
46 DISTANCE INDICATOR FLAG - IO 58 AIRSPEED EXCITATION H
47 DISTANCE INDICATOR 26 VAC H 2 60 AIRSPEED EXCITATION C
48 ) DISTANCE INDICATOR 26 VAC C I E
49 D
50 DISTANCE INDICATOR UNITS SYNCHRO X 4 F TPI-3124-064

AP-103F/FD-108 Aerocommander 1 1 2 1 J e t , Interconnecting Wiring Diagram (Sheet 2 of 6)

Figure 441
Nov 1/68 22-03-00
Pages 493/494
 a
COLLINS MAIiYTENANCE
ww MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT SERVOS AIRSPEED EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER DME POWER AMPLIFIER WIRE FUNCTION AILERON SENSOR DISCONNECT J-BOX
0 33 I A-6A
JI :2
6 I4E-2F
JI
3298-7A
j I J2
344C- I D
JI J2 J IA
562A-5G
JIB
860E-2
(J I ) I JI
562C-4
JI
334C-3
(JI)
5908-2
(JI)
12 IA-2
.I

I I I I (TP)
I
(BP)
I
UP)
I
(BP)
I
I I (TP)
I
(BP)
I
51 DISTANCE INDICATOR UNITS SYNCHRO Y 3
I
52
53
DISTANCE INDICATOR
DISTANCE INDICATOR
TENS SYNCHRO X
TENS SYNCHRO Y
6
5 I I I
54 DISTANCE INDICATOR HUNDREDS SYNCHRO X 7 I I I
55 DISTANCE INDICATOR HUNDREDS SYNCHRO Y 8 I I
I I I I I I I I I I
I I I I I
I I I I I
1 48 2 6 VAC COMMAND PWR 12 I I I I I
- I I
I 32
33
S
S
2 6 VAC ATTITUDE PWR
26 VAC ATTITUDE PWR COM
15
16 I I i I I I I
24 19 -5 VAC LIGHTING PWR
0 I
25 20 -
5 VAC LIGHTING PWR COM I I
I I I I I
I
57 I
I
DC GRD
I I 5 VAC HEADING PWR
I- I
5
- I
55
I
I I 15 VAC ATTITUDE PWR 4 I
g
e
t 2 8 V D C POWER+
+ 2 8 VDC SERVO CLUTCH POWER -m I
I I I I
I I I I GRD
GRD El N
I I I 61- 28 VDC POWER P
I I I I I @ RUDDERSERVOPOWER S
I I I I i B I 0 63
SG-RUDDER
SG -AILERON SERVO
SERVO POWER
POWER
T

I I I I OI @ 61 SG-AILERON SERVO POWER

I I I I 1 0I I @ 64-
ELEVATORSERVOPOWER
SG-ELEVATOR SERVO POWER
W
[ 20 v XU
PITCH STEERING t UP
PITCH STEERING t DN
3- 31 I I GRD -I
I GO AROUND
4- 21 I
I I RELAY
ROLL STEERING t LEFT 12 31 I GO AROUND
ROLL STEERING +RIGHT 13 21
,
I I I BUTTON
I n 1
L GYRO MODE t 13 41 40 I
K HEADING MODE 4 47 64 I
J NAV/LOC MODE t 46 47

I I 44-44 - GO AROUND MODE t

H APPROACH MODE t
I 14 I I I
APPRDACHMODEt
I I 45 42 - APPROACH MODE t
I

EXT STR t DN I I
I EXT STR t UP 37 I1 I I
W ALTITUDE HOLD INTERLOCK
I I
ALTITUDE HOLD INTERLOCK -
u
I

I I 46 ALTITUDE HOLD INTERLOCK

I
I I I I I I I
I I
I

I 39 -4 5 I
666
46
7 -
-
DISCONNECT SWlTCH H
DISCONNECT SWITCH C
GLIDE SLOPE MODE t
fl-
PILOT'S COPILOT'S I
I I I
ALTITUDE
1 DISCONNECT

I I CONTROLLER I SWITCH

1
I
I
II 590A-3A I
V ALTITUDE HOLD MODE t 47
(Jl)
34 Q I
ALTITUDE RATE H' S 34 14 I
ALTITUDE RATE C' S 24 15 I 074.6374. IO0
ALTITUDE ERROR H' S 33 ~
16 41
ALTITUDE ERROR C' S 23 27 42 TPI-3124-064

AP-103F/FD-108 Aerocommander 1121 J e t ,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 441 (Sheet 3) Pages 495/496
 a
COLLINS
>I.U.\'TES.4.\'CE
>IASL!AL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTITUDE AUTOPl LOT SERVOS NAV NAV
CIATORS lNDl CATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER CONTROLLER POWER AMPLIFIER WIRE FUNCTION AILERON RCVR CONT J-BOX
33 IA-6A 614E-2F 329B-7A 344C- ID 562A-5G 590A-3A 6 @ 562C-4 334C-3 51RV- 3 13N-3
@
I
JI J2 JI
I
I
J2
I
JI
UP)
J2
(BPI
JIA
(TPI

I
JIB
(BP)

I
(JI)
I
I
i JI
(TP)

I
JI
(BPI
I
(J 1) tJ2)
I
(J2)
I
I I I I I
12 PITCH BOOTSTRAP TRANSMITTER X
I I 39 43 -ALTITUDE GAIN CHANGE EXCITATION I I
I 13 PITCH BOOTSTRAP TRANSMITTER Y
I
42 44 -ALTITUDE GAIN CHANGE NO. I
I -ALTITUDE GAIN CHANGE NO. I I
I
14
15
PITCH BOOTSTRAP TRANSMITTER Z
PITCH BOOTSTRAP EXClTATlON H
I I
43
36 4
-GRD
' 45
I
2

I
I 16 PITCH BOOTSTRAP EXCITATION C 35
26 BANK BOOTSTRAPTRANSMITTERX I I 37 -GRD I I I
27 BANK BOOTSTRAP TRANSMITTER Y 15 59 -COMPUTER MON t
28 BANK BOOTSTRAP TRANSMITTER2 19 I8 -S - EXT PITCH STEERING A I
29 BANK BOOTSTRAP EXCITATION H 9 19 -SA EXT PITCH STEERING B I
30 BANK BOOTSTRAP EXCITATION C 49 25- S- AC PITCH STEERING A
I HEADING WARNING DATA X 40 26- S -P
AC PITCH STEERING B I
I
HEADING WARNING DATA Y
HEADING WARNING DATA Z
35
25
27-
28-
S -PROCESSED
1
PITCH DATA A
s PROCESSED PITCH DATA B
I
I HEADING WARNING DATA H 18 57- INTERNAL PITCH STEERING OFF t I
HEADING WARNING DATA C 48 60 - ALT HOLD OFF t
I I
I HEADING WARNING DATA H' 19 18 S- EXT STEERING A
I HEADING WARNING DATA C' 19 S EXT STEERING B I I
I I I I 49 25 S - PROCESSED BANK CMD A I I
26 S PROCESSED BANK CMD B
I I I 35 35 S p PROCESSED BANK D A T A A I I
I I I 25 36 S -PROCESSED B A N K D A T A B
I I
I 7 55 S - EXT BANK CMD B
I I I I
I I I PITCH MONITOR t 12 -12
17
I
54
I I
S EXT BANK CMD A
I I
GS ARM GLIDE SLOPE ARM. ANN. - 6 I
I

GZ EXT GLIDE SLOPE EXT. ANN. - 42 I I I I I

N/L ARM
N/L CAPT
NAV/LOCARM.ANN.-
NAV/LOC CAPTUREANN.-
6
39
I I I I
PWR ANNUNCIATOR POWER I I I
- - I
G!: CAPT
I
38 RUNWAY FLAG 5
I I I I
MKR BCN I I
I
- 1
R CVR
I I
GA GO AROUND ANN. 16
I
512-4
I I I I
@ I I (JI)
I I
I
MIDDLE MARKER 43
18
4
57 INTERNAL ROLL STEERING OFF t
I I
A PITCH CONTROL EXC A 21 I

'
B PITCH CONTROL SIGNAL 20
C PITCH CONTROL EXC B 22
D
E TURN CONTROLEXCA
I
21
I 19
I i

F TURN CONTROLEXCB 22 I
I L 4
G TURN CONTROL SIGNAL 20 I I I I
N INT MOTOR CONTROL VOLTAGE 62 54
P
R
INT 26 VAC MOTOR EXCITATION C
INT MOTOR RATE SIGNAL
24
63
I I m - I

S INT MOTOR SIGNAL COMMON 24 55

I I I
I
T 28 VDC PANEL LIGHT PWR
U GRD GRD
I
X I 1.
Y ENGAGE VOLTAGE
z I
a ENGAGE PULSE 56
b DISENGAGE VOLTAGE 37 5 IRV- I F
C ENGAGEREADY 55 SELF-TEST
TPI -3124-064 RELAY

AP-103F/FD-108 Aerocommander 1121 Jet, Interconnecting Wiring Diagram (Sheet 4 of 6)

Figure 441

Nov 1/68 22-03-00

Pages 497 /498
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECT OR INSTRUMENT FLIGHT MKR BCN AUTOPILOT SERVOS EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER RCVR POWER AMPLIFIER WIRE FUNCTION AILERON MlSC DISCONNECT J-BOX
33 I A - 6 A 614E-2F 329B-7A 344c- IO 562A-5G 5 12-4 @ 562C-4 334c-3 121A-2
@ JI J2 JI

I
JI J2

I
JI
(TP)
J2
(BP)
J IA
(TP)
JIB
(BP)
(J 1 )
'
I
JI
(TP)
I
6();
JI (J I) JI
I
@ d
I ALTITUDE HOLD MODE t i8 I
I I I I I I
I I
f HEADING SYNCH CUTOUT
-Izo/ Q
38
I I
P
9
I15VACAUTOPlLOTPWR
I I 5 VAC POWER
I
7 I I
r INT 2 6 VAC MOTOR EXCITATION H 23 I I
5 ENGAGE INTERLOCK 54
I
I .,
E

11
t c

U AILERON CLUTCH VOLTAGE 39

v ELEVATOR CLUTCH VOLTAGE 39
W RUDDER CLUTCH VOLTAGE 56 2 0 -A
- 1
M + 2 8 VDC AUTOPI LOT PWR R "
x
I I 53 -YAW DAMPER ENGAGE MON +
Y SPARE 9 SENSING
2
AA
I I I UNIT
345A-46 @
8B I I I (ROLL) YAWDAMPSW -
cc I 65 ROLL RATE MOTOR GRD A

I
DD . GYROMODE 8 I I 5 VAC POWER B
EE HEADING MODE 32 ROLL RATE EXCITATION C E
FF NAV/LDC MODE @ 31 ROLL RATE EXCITATION H F
GG APPROACH MODE 1 ROLL RATE SIGNAL X G
HH MODE VOLTAGE H I
I I (PITCH)
I I
8- PITCH RATE MOTOR GRD A
21 PITCH DIFFERENTIAL RESOLVER X
IO - I I 5 VAC POWER B
22
23
PITCH DIFFERENTIAL RESOLVER Y
32 - PITCH RATE EXCITATION C E
PITCH DIFFERENTIAL RESOLVER Z
31 - PITCH RATE EXCITATION H F
24
25
PITCH DIFFERENTIAL RESOLVER H
PITCH DIFFERENTIAL RESOLVER C
29 - PITCH RATE SIGNAL X G

26 PITCH DIFFERENTIAL RESOLVER H'

27 PITCH DIFFERENTIAL RESOLVER C' I YAW RATE
GYRO
Q 28
29
BANK DIFFERENTIAL RESOLVER X
BANK DIFFERENTIAL RESOLVER Y
I 332G-2
66 YAW RATE MOTOR GRD A
30 BANK DIFFERENTIAL RESOLVER Z
IO ll5VACPOWER B
31 BANK DIFFERENTIAL RESOLVER H
51 YAW RATE EXCITATION C E
32 BANK DIFFERENTIAL RESOLVER C
50 YAW RATE EXCITATION H F
33 BANK DIFFERENTIAL RESOLVER H'
48 YAW RATE SIGNAL X G TPI-3124-064
34 BANK DIFFERENTIAL RESOLVER C'

AP-103F/FD-108 Aerocommander 1121 Jet,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 441 (Sheet 5) Pages 498A/498B
 CYMeoLs U S E D :

- SF TWISTED SHIELDED PAIR-ADJACENl

- S- MIIRES AS SHOWN ON DRAWING
SG SHIELD TIED TO GROUND AT UNIT
SI SINGLE SHIELDED WIRE
XI A L L S I SHIELDED TIED TO XI ETC.
0 NOTES

NOTES:
17. WHEN OPTIONAL 590A-3A SERVICE BULLETIN NO. 3 IS INCORPORATED,
I. A L L WIRE SIZES ARE NO. 2 2 UNLESS DESIGNATED OTHERWlSE BY NUMBERS IN SQUARES. SHIELDED WIRES ARE GROUNDED AT ONE END ONLY.
THE FOLLOWiNG INTERCONNECTING WIRING CHANGES ARE APPLICABLE:
2. SHIELDS O N T H E N A V R E S O L V E R L E A D S F R O M T H E N A V l G A T I O N R E C E l V E R S H O U L D B E G R O U N D E D A T T H E 5 1 R V - I .
REMOVE CONNECTION BETWEEN J I ( B P F 3 8 OF THE 562C-4 AUTO-
3. JUMPER WlRE FROM J l - 2 TO J 1-3 OF THE COURSE INDICATOR SHOULD B E NO LONGER THAN SIX INCHES. PILOT AM'LIFIER AN0 J l - d O F T H E 614E-2G PEDESTAL CDNTROL-
LER. REMOVE CONNECTION BETWEEN J1-V OF THE 614E-2G
4. A RELAY MUST BE INSTALLED IN THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF-TEST FEATURE OF THE 5 I R V - I WHEN THE AUTOPILOT
PEDESTAL CONTROLLER AND J l A ( T P p 4 7 OF THE 562A-5G FLIGHT
IS ENGAGED.
COMPUTER.
5. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWING REFLECTS LOADS AS FOLLOWS:
MAKE CONNECTIONS AS SHOWN BELOW.
AFC LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS
PEDESTAL FLIGHT ALTITUDE AUTOPILOT
2 0 0 OHMS TO-FROM IO0 OHMS JUMPER BP-43 TO BP-33 OF 5 IRV- I CONTROLLER WIRE FUNCTION COM'UTER CONTROLLER AM>LIFIER
5 0 0 OHMS GLIDE SLOPE POINTER 2 0 0 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 5 IRV- I
614E-2G 562A-5G 590A-3A 562C-4
5 0 0 OHMS GLIDE SLOPE FLAG 2 5 0 OHMS JUMPER TP-2 I TO TP-26 OF 5 IRV- I
JI JlA JIB (JI) JI J l
5 0 0 OHMS LOC FLAG 2 5 0 OHMS JUMPER BP-32 TO BP-4 I OF 5 IRV- I
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO BP-30 AND BP-48 OF 5 IRV- I (TP) (BP) (TP) (BP)
v ----------ALTITUDE HOLD MIIDE t -------- 3 4
6. THEPOWERFORTHECOMPASS SYSTEM M U S T B E O F T H E S A M E P H A S E AS T H E R E S T O F T H E A U T O M A T ~ C F L ~ G H TCONTROLSYSTEM. ALTITUDE HOLD MODE +47 ______- ------------.
2 0 --- 38
7. POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT LIGHT DIMMING CIRCUITS.

?. SENSING UNIT 3 4 5 A - 4 ( ) AND RATE GYRO 332G-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE.

9. ANNUNCIATORS CHOSEN MUST NOT EXCEED 100 MA. A COMMON t 2 8 VDC I S USED FOR ANNUNCIATOR POWER

IO. THESE LEADS MUST B E TWISTED AND SHIELDED IF OVER TWO FEET LONG.

I I. COMPARATOR WARNING RESOLVERS.

12.

13.

14.

AILERON
LEFT
CLOCKWISE I J ITP-34 __-____--_________________
PED h

TURN

RIGHT
TURN

ELEVATOR
UP

15. POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT. THIS WILL BE INDICATED IN
THE INTERCONNECT POWER COLUMN BY A LETTER WITH AN HEXAGON SYMBOL AROUND I T . CAPITAL LETTERS FOR DC AND LOWER CASE LETTERS
FOR AC.
-
A 2 8 VDC DIMMING CIRCUIT, a - 5 VAC DIMMING CIRCUIT.
-
6, C, D, E, 28 VDC 5 AMP b , C, 1 I 15 VAC 2 AMP -
-
G 2 8 VDC I AMP e-115VACIAMP
f - II5VAC3AMP
16. THE GO AROUND RELAY I S USED IN CONJUNCTlON WITH APPLICABLE FSB FOR WINGS LEVEL, PITCH UP GO AROUND. GO AROUND BUTTON I S NOR-
MALLYOPEN ANDSHOULDBE LOCATED D N T H E W H E E L I F POSSIBLE.TDDEACTlVATEGOAROUND PROVISION REMOVETHERELAYAND CONNECT
THOSEWIRESTOGETHERTHATARE CONNECTEDTOBYTHENORMALLYCLOSED CONTACTS D F T H E R E L A Y .

AP-103F/FD-108 Aerocommander 1 1 2 1 Jet,

Mar 1/73 Interconnecting Wiring Diagram 22 -03 -00
Figure 441 (Sheet 6) Pages 498C/498D
 a
COLLINS
MAINTEIVANCE
w& MANUAL

FLIGHT
AH- mS
E PEDESTM DIRECTOR INSIR*EWT FLIWT WlOPILOT EWERGENCl
CIATORS ItQICATOR WNTROLLER INDICATOR WLIFIER CoCvTER MISC PW€R WLIFIER WIRE F W T I O N SERVOS MISC OISCOWI(ECT JdoX

--
3 3 M bI1EdF Y B 7 A 3wc-lD AILERON 121M
Q J1 J2 J1 J l J2 J I
(TP)
J2
(WP)
33163 J I
(Jl)
1 b -
- 21
.... ....
-
b -
9
- P I T C H A T T I T W E ERROR H ' 11 AILERON FIELD H V s E R I
1Y
15
23
7
8
9
7 -A-

s _c_
P I T C H ATTITUDE ERROR C'
8 _C_ P I T C H ATTITUDE SERVO W I V E M2
PITCH ATTITUDE WIVE swvo
-
c-
17
23
28
:
:
:
-
: :
.
@ b:

13
: 5 1
28 VDC
+AILERON
AILERON
FIELD N W R 2
SIGNAL C
A
B
C
E
37 10 10 P I T O I ATTITUDE RATE G2 25 : : : VERT IY AILERONEXCITATION C F
38 22 11 -+ P I T C H A T T I T W E RATE C2 2b : : : REF 15 - A I L E R O ( ( P O S I T I O N EXCITATION H G
-+

-
10
39 23 -9-1 W M PITCH C W D H ' I 36 : 332D-11 I b AILERON RATE E X C I T A T I f f l H H
11
25 2 _csb M W P I T C H C W D C' . 2b : (Jl) 12 -
t AILERON POSITION S I W L
:
2b 1 2 __C_ V-BAR P I T C H COMMND SERVO W I V E - M I1 :
1 i 11 -
h- AILERON SERVO GRD R

-
12
13 27 13-V-L)NtPITCH COMUND SERVO WIVE C - 1 0 : : :1 -
h- AILERON RATE SIGNAL S
28 . .

-
't4 - 9
- V - W R P I T C H C W D RATE 8
w 29 15 -A- V - W R P I T C H C W D S I C COLI- 9 I -1 i
-
a YO V - B N t P I T C H POS XMTR X

-
31 Y1 V-BAR P I T C H POS MlR Y 37 : (J2)
32 3 P I T C H A T T I T W E CT X . 30-A AILERON ENGAGE VOLTAGE

3
35
36
33

17
Y
5

-
-
P I T C H ATTITUDE CT Y
P I T C H A T T I T W E CT 2
@AN( A T T I T V M CT X
: 20-B

f
:
30-D
C
27
za
:
AILERON ENGAGE HXTAGE

-
18 M ATTITUDE CT Y 20-E : ELEVATOR
37 I9 M A T T I M E CT 2 F 33163
38 : : :
39
20 -
21
9
- M ATTITUDE EWfOR H '
B M ATTITUDE ERROR C'
I8
17
- : : : El
i @-t
-ELEVATOR FIELD NUBER 1
(JI)

10 22 ATTITUX SERVO m m )ry

- 22 : : :
Ii b i 28VDC A
8

-
@AN(
SERVO m I v E c

-
12 23 @AN( ATTITWE 21 : : : : Y 1ELEVATOR FIELD N U S H 2 C
Y3 21 -
9
- B W A T T I T U X RATE 6 2 19 : : : : 13 4
-+ ELEVATOR SIGNAL C E

-
-
45 : : : :

- -
Y1) 25 -A- RATE Q
@AN( A T T I T = 20 I1 ELEVATOR EXCITATION C F
36 __C_ V a ROLL W D SERVO W I V E M2 28 : : : 15 ELEVATOR POSITION EXCITATION H G
. . . : -+

-
1b 37 V-BAR ROLL C W D SERVO WIVE C 27 : : l b ELEVATOR R T E EXCITATION H H
: 12 ---5+ ELEVATOR POSITION S I Q l M L
77
98 38 V-BAR ROLL C W O RATE G2 25 : : ERECT: : 11 ELEVATOR SERVO GRD R
: : s

--
39 -b V 4 4 R ROLL C O W D S I G COM 2b GRD : 17 M t ELEVATOR RATE SIGNAL
.

-
19
50 31 V-BAR ROLL POS XMTR H I 21 : : -F
35 V-BAR ROLL POS XMTR C I : 2 3 : :
115VAC A T T I T U M P O M R _ ! d
51 : GYROWON+ 29 10 N (J2)
52
53
51
31
:
:
-
18
Y-STEER
GIRO HIGH LEVEL FLAG +
GIRO HIGH LEVEL FLAG
FLAG -- - 31
32
:
:
2 :
:
:
: H
:
:
A v
ELEVATOR ENGAGE VOLTACE
ELEVATOR ENGAGE VOLTAGE

55 STEER FLAG 2-28 RCH(

-I .-
: -
-
l b +28 VDC FLAG WVER
-: .
!
- 51
91PV-I
(TP)
:
- DEV + w

-
33 10 GLIDE SLOPE
. +
3Y
35
3b
:
:
11
12
13
-
-
GLIDE
GLIDE
GLIDE
SLOPE
SLOPE
SLOPE
DEV DN
L W LEIlEL FLAG
LON LEVEL FLAG
+
-+
: 22 -c
z
:
21
22 R W A Y FLAG
: GLIDE SLOPE HIGH LEVEL FLAG 11 -+- 27 RELAY

2s b-
- VCWLOC DEV + LEFT
: : :
: 32-90
(BPI

-
28
:
:
5
4
38
-
-
VORlLOC DEV + RIGHT

-
VORlLOC HIGH LEVEL FLAG
RUWAY FLAG
+
; 22
: 11-
34
50
RUNYAY FLAG - '
' PEDESTAL
: LCC FREQ VOLTAGE + . Y3- 38 WNTF!OLLER
8 ; 5- COtSSE RESOLVER H
: 5 :
: 21
RUDDER
33YC-3 i_--
- I
J1-H
(Jl)
: SA- :

-
COLRSE RESOLVER C 23 f RUDER F I E L D NLWBER I A

5
;
:
59- COLRSE RESOLVER D
5 6 COLRSE RESOLVER E
:
:
2*
25 Q f 28 wc
F I E L D NLWBER 2
f RVDDER
0
C
b
7
: 5- COLRSE RESOLVER F
X COLRSE RESOCVER G
:
:
2b
27
93 -+ SIGNAL C RUDDER E
YY EXCITATION C RUDDER
31
32
2b
VORlLOC FLAG +
VCWLOC FLAG
TO-FROM ARROY (+ TO)
- :
T
:
11
e
93
Y5
1b
12
-+
-+
RUDDER
POSITION EXCITATION H
PATE EXCITATION H
RUDDER
G
H

27 TO-FROM ARROW (+ FROM)

.. .. ... 11 11 -* RUDDER SERVO GRD
RUDDER
W S I T I O H SIGNAL L
R

.
:
. .
I
. .
:
.
Y7 -c-5+ RUDDER RATE S I G N A l
..-.
S
t 13,

.... .... ...-

RWDER ENGAGE VOLTAGE I 0
RUDDER ENWGE VOLTAGE C
TRIM SERVO
. . . 33YD-2-33D ( J l )
:
:
k
j
EL TRIM
EL TRIM
.
.
31) -+ TRIM TAB MDT CONT
33 ---S1c TRIM TAB WOT CONT

AP-103F/FD-108 Allegheny CV-580, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 442

May 1/67 22 -03-00

Pages 499/500
 a
COLLINS
MMAIKTENANCE
w MANUAL

FLIGHT
ANNUN- CWRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS iNDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COWUTER COMPASS PWER MLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J&X

331A-bA LIYE-2F 329&7A AILERON 181A-Z

Q J1 J2 J1 J1 J2 33YC3
(Jl)
J l

. . . .
.. .. :
:
:
:
:
:
: 87-CRD
. .
.. .. . . : :
: 3 2
.
~. . . . : : 22-5
.. ..
: : : : 30-3
:
:
:
:
COMPWSMON-
COWPASS M O N +
f
-
3
29-
0 : :
1Y - 17
25
.
. . COWASS DATA X
I ; .I . ; " & r .. ..
X l t T R I M MOTOR G R O M
28MC
B
A

'Pt,: i f COWASS DATA Y

. . .. .. ..
. . ..
b 3 R I M ENGAGE VOLTAGE
TRIM ENGAGE OROVND
L
M
11c 3 COWASS DATA 2
11
r 9
. .
- . Yq -
- COWPASS OATA X

. .
COKPASS FLAG +
.
:
. . . Y C
3<
f
:
.
50
51
.
- COWASS OATA Y
COWASS DATA 2
30
:
:
2Y
15
COMPASS FLAG -
2 b VAC H f f i PWR
:
f
3
3
1
1
2
5
:
:
:
:
:
: .. ..
: lb > C W N . l b : :
: 2D f 5(L HEADING ERROR SYNUlRO C ' . 1 7 : :
.:
...
:
:
21
13
:
:
5 6 HEADING ERROR SYNCHRO H '
S'+ HEADING RATE G2
18
1 9
:
: :
:
..
. 4 : 1 - 5 6 HEADING RATE C2 . Z D : :
...
: 18 : Hffi MOT CON1 C1 .
:
21 : : ..

-
: 11 I HDG MOT CON1 M 1 2 2 : : AIRSPEED
: 9 I HEADING DATUM SYNCHRO C' . . : 2 3 SENSM
: 5 . HEADING DATUM SYNCHRO H ' . 33 D
.M-
E: 590B-2
18 . COLRSE DATUM SYNCHRO C ' :
f
I -
29 8bOE-Z J1
13 : COURSE D A M SYNCHRO H ' . I 3Y (J1) 59 AIRSPEED SIQIM
95
Yb
I
f :
DISTANCE INDICATOR FLAG +
DISTANCE INDICATOR FLAG - :

.
:
:
f
:
9
ID
:
:
58
bO P
AIRSPEED EXCITATION H
AIRSPEED EXCITATION C
1:
C
47 f f DISTANCE INDICATOR 2 b VAC H : : 2 :
. . E
Y8
99 -T
- :
I . .. DISTANCE INDICATOR 2 b VAC C
. . ... ..
f t 1 :
.
D
F
. . -.. .
..-.
. 0 5 DISTANCE INDICATOR U N I T S SYNCHRO X I f Y :
51 f DISTANCE INDICATOR UNITS SYNCHRO Y f : : I 3 :
58 . DISTANCE INDICATOR TENS SYNCHRO X : : f b :
..
-
f
53 : DISTANCE INDICATOR TENS SYNCHRO Y : .
. . :
f 5 :
..
5Y
..
55
:
.I.
I
I
DISTANCE INDICATOR HUNDREDS SYNCHRO X
DISTANCE INDICATOR WNDREDS SYNCHRO Y
7:
P 8 : .
Y8 2b VAC C O W N PYR 12 : : : :
38 : 5- 2 b VAC ATTITUDE PHR 15 : : : :
24
25 :
33
:
:
- :
19
20 -
-' 8 b VAC ATTITUDE PWR COM-
5 VAC LIGHTING PNR R
5 VAC L I G H T I N G PYR COM
l b : :
-
: -57
: :
: . .

.. ... ... .. .. . - N
P

. . ... . ... 4 @ b iAc

RUDDER S E R M PWW
t RUDMR SERVO WER --n-
-1b :
:
S
T
- . . .... .. .
.
... 0
B
@
5- AILERON SERVO PWER -1b.
eo
- U

... ..- .--. .

bl-ct AILERON SERVO M E R : V GO MOUND
. D ELEVATOR SERVO WWER Ib . N RELAY
: @bi d ( C ELEVATOR SERVO POWER 3
X

:I
. .
i P1 P1 I
H
.. . AppROAol MODE +
; iLii-Yi GO A
ROm m E
APPROACH U I D E
+
+ 1 -T -- I f ELAT

..
: :
. 1 5 . .. ..
W-AppROACHMoM+
L
: :
EXT S T R + DN
EXTSTR+LQ
2?
3 7 1 ; i .. . I 4
i . . A L T I M E HOLD INTERLOCK M T I N D E W L D INTERLW(

. . ..
:
....: Y
.... .... ..
b .
: bb -
- ALTITUDE HOLD INTEFLOCK
DISCONNECT SNITCH H
.
..
.
..
. ..
:
. -

..:- 3 9 - 9 5 ALTITUDE
... :
-

:
:
.

..
:
b7.
_
..
Yb - DISCONNECT N .I .
GLIDE SLOPE MODE
T C.H C
+ PILOT'S
b l - - 5

DISCONNECT SWITCH
COPILOT'S
:
t

. . - . . : CONTROLLER :
.. .
:
. :. :: 590A-3A ...
:
.
-
(J1)
-. 43Y7-
; ALTIME HOLD MODE + . - C 3 1 : Q I .
: ALTITUDE RATE H' 4\ c 1Y :
: ALTITUDE RATE C' ---5) . 2Y 15 : -C
: ALTIME ERROR H '-+\ . 33 l b 4 . Y l
: ALTINOE ERROR C' 4) : 23-274 : Y2

AP-103F/FD-108 Allegheny CV-580,

M a r 1/73 Interconnecting Wiring Diagram 22 -03-0 0
Figure 442 (Sheet 2) Pages 401/1, 401/2
 e
COLLINS MAIIYTENANCE
MANUAL
WW

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTITUDE AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER CWRLTER CDKTROLLER POWER AMPLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX
331A-bA blYE-2F 3298-?A
3WC-10 5b2A-5G 59DPr3A @ 5b2C-Y AILERON 121A-2
@

-
Jl J2 Jl Jl J2 J l J2 J1A JlB (J1) J1 J1 33YC-3 J1
(J1)

... ...-
(TP) (Bp) (TP>(Bp) (TP) (BPI
-
-
-
-21 PITCH BOOTSTRAP TRANSMITTER X : : : : 39s : Y3 ALTITUDE GAIN CHANGE EXCITATION
.:
-..
13 P I T C H BOOTSTRAP TRANSMITTER Y : :
:
: Y2-l YY
- A L T I T U M : GAIN CHANGE NO. 1

...-.
19 I P I T C H BOOTSTRAP TRANSMITTER 2 : : Y3* 95 ALTITUDE GAIN CHANGE NO. 2
Q
-
1 5 _C_ P I T C H BOOTSTRAP EXCITATION H : : : 3b+
.~. lb P I T C H BOOTSTRAP EXCITATION C : : : : 35-GRD

-
: : :
-
26 _C_ BANK BOOTSTRAP TRANSMITTER X : 37t-GR.D
: - +
...
27 _C_ BANK BOOTSTRAP TRANSMITTER Y : 15 : 59 COhPVTER MON
.. 28
29
BANK BOOTSTRAP TRANSMITTER 2
6ANK BOOTSTRAP EXCITATION H
.
f
M P I T C H STEERING A
18 --S-
19 I EXT P I T C H STEERING B
++
f .

30 SANK BOOTSTRAP EXCITATION C : 25 AC P I T C H STEERING A

.

--
HEADING WARNING DATA X 2 b 46AC P I T C H STEERING B
+-

-
HEADING WARNING DATA Y Z 27 PROCESSED PITCH DATA A
++
HEADING WARNING DATA 2
HEADING WARNING DATA C
HEADING WARNING DATA V. : : w :
:
:
28
57
bO
-
P m c E s s m PITCH DATA B

-
INTERNAL P I T C H STEERING OFF
ALT HQLD OFF +
+

... .--
HEADING WARNING DATA C'
HEADING WARNING DATA H' . . 18
19
EXT ROLL STEERING A
EXT ROLL STEERING B
25 -T- PmcEssED BANK CMD A
~. . . 2b : 5 6 PRDQSSED BANK CMD B
-+
...~ .- . . 35
3b :
P m C E s s E D BANK DATA A
P m c E s s E D BANK DATA B
- . 5 5 U - E X T BANK CMD B

PITCH MONITOR + - :
5Y __r_sb EXT BANK CMD A

--
: : 12 12
Gsm : G L I D E SLOPE APA. ANN. : b : :
.: -. .
Gs EXT I
--
G L I D E SLOPE EXT. ANN. 42 :

...
N I L ARM : NAVILOC ARM. 4". : b :
N/L CAP : : NAV/LOC CAPTURE ANN. I 39 :
..
--
pM( ANNUNCIATOR POMR
I: I ..
..
GA .
I GO M U N D ANN I; MR'BCK
GsCAP
..
Z
.. GS CAP ANN
:
5
:
:
:
RCVR
5124
.. .. : : : (J1)
.
:
.: MIDDLE W E R :
: 93-Y
+
.. .. A PITCH comm EXC A
:
a
: : l a
. 21
5; INTERNAL ROLL STEERING OFF
NAV NAV 51RV-1
B P I T C H CONTROL SIGNAL W 20 SELF TEST
C P I T C H CONTROL EXC B 0 22
. .. .. .. . . RELAY
D . .
E TURN CONTROL EXC A I 21 :
F TURN CONTROL EXC 8 22 . . . :
G TURN CONTROL SIGNAL 3 20
. . _ .
: :- ; t
-. ...
N I N 1 MOTOR CONTROL VOLTAGE b2 5Y I
k I N 1 2bVAC MOTOR EXCITATION C 2Y : n
.. R I K T MOTOR RATE SIGNAL : b3 t
.. S I N 1 MOTOR SIGNAL CObWN ,
. . . . 2Y. 55
':

4
. T
U
28VDC PANEL L I G H T PYR
GROUND
K
: ! t Q
.. .- 2 . ... ... ._. .
. .. a ENGAGE FULSE . . . . 5b
.. . b f DISENGAGE VOLTAGE f 37
.
..--
ENGAGE READY 55
.. A L T I M E HOLD M3DE +
:
: 38
:
...
HEADING SYNCH CCROLIT 38
.. h
i
AILERON TRIM
AILERON T R I M
3
33 . - . .
:
:
... .- m RU)DER T R I M 4 53 . :
.. ... n
P
RUDDER TRIM
115 VAC ALTO P I L O T P V R a f
52
. . .
:

.. ..-
q
I
115 VAC POWER
I N 1 2bVAC MOTOR EXCITATION H
?
23
:
:
.. 5 ENGAGE INTERLOO(
. . . . .
- t
U AILERON CLVTCH WLTAOE 5
V ELEVATOR CLUTCH VOLTAGE
w RUDDER CLUTCH VOLTAGE
M
X
. . + 2 8 M C AUTO P I L O T PVR
.. ..
.
..
.
.. . : 53 - YAW D M E R ENGAGE MON +
.... ..
. . .. . .
- ..
Y SPARE : 9 SDISING

... ..... ...... ..

2 UNIT
.. ..- .
... .
AA
. 395A-W @ :
. . 88
cc
DD
EE
FF
oc
. .
GYRO MODE
HEADING MODE
NAVILOC W E
APPROACH MODE
...
.
..
.....
.....
..
.....
....-
.... ..
... .
.. -.
:
:
:
:
b5
8
32
31
29
- .

:
ROLL RATE MOTOR GRD
115 VAC POWER
ROLL RATE EXCITATION C
ROLL RATE EXCITATION
ROLL RATE SIGNAL X
H
(ROLL)

G
A
: YAW D M SW

. . . . .. ..
nH MODE VOLTAGE H

AP-103F/FD-108 Allegheny CV-580,

Mar 1/73 Interconnecting Wiring Diagram 22 -0 3 -0 0
Figure 442 (Sheet 3) Pages 401/3, 401/4
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
IUUWN- COLRSE PEDESTAL DIRECTOR INSTRUENT FLIGHT AUTOPILOT SENSING EMERGENCY
CIPTORS INDICATOR CONTROLLER INDICATOR WIRE N N C T I O N AMPLIFIER COWUTER MISC POYER AMPLIFTER WIRE FUNCTION SERVOS UNIT DISCONNECT J-BOX
331A-U blYE-2F 3298-?A AILERON 121A-2
@ J l J2 J1 J l J2 Q 8 J1

.. ... ... ... . . .

: 8 -
- P I T C H RATE MOTOR GRD
(PITCH)
A

. .
:
:
ID
32-
-
115 VAC POWER
PITCH R AE EXCITATION C
B

.-
: 31 P I T C H RATE EXCITATION H

.. ... ... . .
: 29 P I T C H RATS SIGNAL X G

.....
. ...- . YAW RATE

. ..
Gym
.
-
332c-z
bb : YAW RATE DTOR OR0 A
10 f 115 VAC POWER B
51 : YAW RATE EXCITATION C E
50 YAW R4TE EXCITATION H F
Y8 YAW RATE SIGNAL X G

..: ..3 ..8

Y? 8
: 3 STOW NEAR P I L O T ' S ANN. PANEL
49 ? 8 :
50
51
8
19
GYRO W I T O R FOR TRANSFER-
CDDPASS MONITOR FOR TRANSFER - 10
9 :
:
u
?
la
15
52

52 15 11 : 8 lb
53 17 1Y : 13 2b
54 35 30 : 17 27
55 3b ': 28 29
37 : 29 3b
39 : 38 37
: Y1 :
: 5D 38
: 51 Y2
STOW I N A I P JUNCTION BOX : 52 Y8
: 53 5D
: 55 51
Y5 : 56 52
Yb : 5? 53
Y7 .-. ... ...
... ... .._
Y8
Y9

... ..- ...

50
5
._1
52 .. .. ..
53
54 ... ... .._
. .... ..--
.... i
55
@ WHEN OPTIONAL 590A.3ASERVlCE BULLETIN NO 3 I SINCORPORATED
. . THE FOLLOWING INTERCONNECTING W I R I N G CHANGES A R E APPLICABLE

SMOLS USED: MAKE CONNECTIONS AS SHOWN BELOW,

REVISION A: LPDATE DRAWING REMOVING ERRORS. 1 2 - 8 4 5 TRL
S? ' M I S T E D SHIELDED P A I R A 1 W E S T E E R I H i CDDPUTER TO F L I G H T COWUTER PEDESTAL FLIGHT ALTITUDE AUTOPILOT
SA CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMPLIFIER
A2 W G E A V I W I L G T COWPUTER TO A U T W I L O T A h P L I F I E R
SG SHIELD T I E D TO GROUND AT U N I T A3 W G E VOR TO ' U V 614E.2G 562A.5G
J1A J18 590A.3A
Id11 J562C
l 4J l
S1 SINGLE SHIELDED WIRE Jl

8 ALL S1 SHIELDED T I E D TO W ETC.

NOTES
[TP! (BPI
.......................... 34
V - - - - - - - - . - ALTITUDE HOLD MODE+
:TP: IBP!

ALTITUDE HOLD MODE+ 47 ................... 20 ............................. 3

REVISION 8: LPDATE PER INSTALLiTION. 1-3-bb TRL
B l MANGE N M 337D-2-33E TO 33W-Z-33D
82 REVERSE TRIM L l A D S h AND 1, k, m WD n
NOTES:

1. ALL WIRE S I P S ARE NO. 22 W L E S S DESIGNATED OTHERWISE BY NULBERS I N SQUARES. b. THE P W E Q FOR THE W A S S SYSTEM WST BE OF THE SADE PHASE AS THE REST OF THE AUTOMATIC F L I G H T CONTROL SYSTEM.
2- SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOUD BE GROWDED AT THE 5lRV-1. ?. POWER LEADS DENOTED BY "DIM" SHOULD BE T I E D TO COCKPIT L I G H T D I M I N G CIRCUITS.
3- JUWER WIRE FROM J l - 2 TO 9-3 OF THE COURSE INDICATOR S H O U D BE NO L O N E R THAN S I X INCHES. 8. SENSING U N I T 3 Y U 4 ( ) AND RATE GYRO 3 3 2 6 2 S W D B E LOCATED AS CLOSE TOGETHER AS POSSIBLE.
9. A RELAY MIST BE INSTALLED I N THE AIRCPAFT JUNCTION BOX TO E L I M I N A T E THE SELF TEST F E A W E OF THE 5 l R V - 1 W E N 9. ANNWCIATORS MOSEN WST NOT EXCEED 100 MA. A C W N +28vDC I S USED FOR ANNUNCIATOR POWER.
THE AUTOPILOT I S ENGAGED. 10. THESE LEADS WST BE M S T E D AND SHIELDED I F OVER lW0 FEET LONG.
5. THE A U O M A T I C FLIGHT CON'IROL SYSTEM AS CONNECTED I N T H I S DRAWING REFLECTS LOADS A5 FOLLOWS: 11. CZWARATOR WARNING RESOLVERS. Do NOT USE FOR OTHER P W O S E S UNLESS LOADING EFFECT I S EVALUATED.
12. TOTAL WIRE RVI FROM BUSS TO l 2 l M TO 5b2C-V TO 3 3 6 3 ( P I N 6) FOR EACH P R I M Y SERVO MJST NOT EXCEED 90 FEET
AFCS LOAD CIRCUIT R E W I R E D LOAD ADDITIONAL LOADS I F AWG 20 WIRE I S LED. W E N OREATER THAN 90 FEET, INSTALL T E M N A L S AT 5b2C-4 MOUNT AND RUH AWG BD WIRE FROM
5 b 2 G Y TO TERMINAL AND AWG l b WZRE FROM TERMINAL 3 4 4 6 3 P I N 8.
200 OHMS TO-FROM 1OD OMS JUWER W 4 3 TO W-33 OF 5 l R V - 1 13. AN ISOLATED WDE SWITM I S PROVIDED FOR USE WITH COPILOTS F L I G H T DIRECTOR.
SOD OtW GLIDE SLOPE POINTER BDO OHMS JUWER TP-8 TO TP-2 AND TP-3 OF 51RV-1 1Y. WITH THE TRIM INDICATOR CONNECTIMIS SHOWN, TI€ P R I M M Y SERVO CAPSTAN S W D TURN CLOCKWISE W E N V I R I E D FROM THE
5DO OHMS GLIDE SLOPE FLAG 250 OHMS JUWER TP-21 TO F - Z b OF 5 l R V - 1 CAPSTAN END UNDER TrlE FOLLOWING AIRCRAFT A T T I N D E S :
5DD
500
OHMS
OHMS
LOC FLAG
COURSE BAR
250 OHPS
?DO OHMS
JUWER
JUWER
W-32 TO W 4 1 OF 5 l R V - 1
W-39 TO BP-30 AND W 4 8 OF 51RV-1 AILEWN -- L E F T WNK
ELEVATOR
R V W - PITCH U p
LEFT YAW

15. POMR FROM A PARTO

I LAR a R c u I T BREAKER OR FUSE MAY PROVIDE POWER FOR MORE TWN OM EQUP
I MNT. THSI WILL BE
INDICATED I N M INERCONNECT POWER C O L W BY A LETTER WITH AN OCTAGON SYhBOL AROUND I T . CAPITAL LETTERS FOR
DC AND LOWER WE LkTTERS FOR AC.

- - d-
- -
A 2 8 W C DlMMlNG CIRCUIT. a SVAC DM
IN
IG CR
I CUT
I
6, C, D, E 2 8 W C 5 Me b,
FI G 2 8 W C 1 Mp e
f
--
C, l l N A C 2 Mp
115VAC I A ~ P
l l N A C 3 AhP

lb. CONNECTIONS TO TRIM TAB MOTOR CONTROL DEPENDS ON AIRCRAFT RIGGING.

AP-103F/FD-108 Allegheny CV-580,

M a r 1/73 Ink rconne c ting W i r i n g Diagram 22 -03-00
Figure 442 (Sheet 4) Pages 401/5, 401/6
 ~ ~

e
COLLINS
MAISTES.4NCE
MASUAL

COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT AUTOPILOT EMERGENCY

SERVOS
ANNUNCIATORS IND CONTROLLER DIRECTOR IND WIRE FUNCTION AMPLIFIER COMPUTER MlSC POWER AMPLIFIER WIRE FUNCTION AILERON MlSC DISCONNECT J-BOX
33 1 A-6A 6 1 4E-2G 3 2 9 B- 7 A 344C-1 D 562A-5G 562C-4 33a-3 121A-2
JI J2 JI JI
I
J2 -JI J2 JIA JIB
Q JI J1 (J11 J1

I 6 +-.++ PITCH ATTITUDE ERROR H'

(TP)

2 4 1
(BPI (TP)

I
(BP)

1 I AILERON FIELD NUMBER 1 A

I
7
8 ' - PITCH ATTITUDE ERROR C'
PITCH ATTITUDE SERVO DRIVE M2-
-
28
23 2 8 VDC
AILERON FIELD NUMBER 2
B
C

I
9 1 PITCH ATTITUDE SERVO DRIVE C 27
II 'I II 1 AILERON S E N A L C E
1
11
o . v PITCH ATTITUDE RATE G2
PITCH ATTITUDE RATE C2 25
26
VERT
REF
AILERON EXC C
AILERON POSITION EXC H
F
G I
I '
MANUAL PITCH CMD H'
I 1
36 332D-11 AILERON RATE EXC H n

*
2 *. MANUAL PITCH CMD C' (J1) 12 AILERON POSITION SIGNAL L

I 42 I
V-BAR PITCH CMD SERVO D R N E M I
I
; :I, ;2 I R
43
44
45
V-BAR PITCH CMD SERVO D R N E C
V-BAR PITCH CMD RATE
V-BAR PITCH CMD SIG COM 1
1
8
9 I 1 p
M7
S

(J2)
I
40
41
I
I
u
I
V-BAR PITCH POS XMTR X
V-BAR PITCH POS XMTR Y
l 7

I I
W ' I AILERON ENGAGE VOLTAGE
AILERON ENGAGE VOLTAGE
A
B
E
F
3
4
5
'
'
PITCH ATTITUDE CT X
PITCH ATTITUDE CT Y
PITCH ATTITUDE CT 2
I
I
I
1
1
30
20 ; A
B
C
I I
17
I
I BANK ATTITUDE CT X
I I
' 3 0 - D
I I
1 ELEVATOR

I
I I
18 BANK ATTITUDE CT Y I 20-E 33461

.L;' i
I '
19 BANK ATTITUDE CT 2 F (J1)
20
21
BANK ATTITUDE ERROR H'
BANK ATTITUDE ERROR C' 1 8 1 I ;3 I Q
ELEVATOR FIELD NUMBER 1
28 VDC
A
E
-2 2
22
23 I
BANK ATTITUDE SERVO DRIVE M 2
BANK ATTITUDE SERVO DRIVE C - 21 1 7 1 1 1 :3
I I
4 ELEVATOR FIELD NUMBER 2
ELEVATOR SIGNAL C
C
E
24
25
-.++-f
I
1
u
,
BANK ATTITUDE RATE G2
BANK ATTITUDE RATE C2 I I I :3 I
I ELEVATOR EXC C
ELEVATOR POSITION EXC H
F
c
'
'' -
36 V-BAR ROLL CMD SERVO DRIVE M 2 28 a ELEVATORRATEEXCH H
37 V-BAR ROLL CMD SERVO DRIVE C I 27 I I J d 6x ELEVATOR POSITION SIGNAL L
I I I I I ELEVATORSERVOGND R
V-BAR ROLL CMD RATE G2 25 ERECT S
39 V-BAR ROLL CMD SIG COM 26 H --
V-BAR ROLL POS XMTR HI 24
1 1
35 U V-BAR ROLL POS XMTR C I
1 1 5 VAC ATTITUDE POWER
GYRO MON +
4
29
' 2 3

I IO-
G

Y
- ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGAGE V O L T M E
-
-
U2)
A
B
J
H
31 GYRO HIGH LEVEL FLAG t 31 ' I
18 GYRO HIGH LEVEL FLAG - 32 I I NAV
4

16
I
STEER FLAG
STEER FLAG +
-
+28 VDC FLAG POWER
2
1 2
28
54
I RCVR
51RV-I
(TP)
I RVDDER
33U-3
I 1 1 I (J1)

0z7=&
32
33 IO GLIDESLOPE DEV + UP RUDDER FIELD NUMBER 1 A
8 0
34 11 GLIDESLOPE DEV + DN 22 9 12 4 28 VDC B
35 12 GLIDESLOPE LOW LEVELFLAG + 21 RUDDER FIELD NUMBER 2 C
36 13 GLIDESLOPE LOW LEVEL FLAG - I I
22 RUDDER SIGNAL C E

I
29 6
I GLIDESLOPE HIGH LEVEL FLAG +

VOWLOC DEV + LEFT

VOR/LOC DEV + RIGHT
11 I
I
3 2 -40
-39
27
(WP)
:=F
45
46
RUDDER E X C C
RUDDER POSITION EXC H
RUDDERRATEEXCH
F
G
H
28

I
5
9 VOWLOC HIGH LEVEL FLAG t
LOC FREQVOLTAGE t
22
11
43
-
-
50
38 47
RUDDER POSITION SIGNAL
RUDDER SERVO GND
RUDDER RATE SIGNAL
L
R
S
f i t
8 I , 8 COURSE RESOLVER H 21
2 i;
I ,
Q 3 - 2
4
n
I I
*
COURSERESOLVER C
COURSERESOLVER D
23
24 RUDDER ENGAGE VOLTAGE
U2)
A B
I ,
5 COURSE RESOLVER E 25 RUDDER ENGAGE V O L T M E B C

31
6
7
,
I I
v
I

'
*P
COURSERESOLVERF
COURSERESOLVERG
VOR/LOC FLAG +
26
27
41
32 VOR/LOC FLAG - 42
26 TO-FROM ARROW (+TO) 43
27 TO-FROM ARROW (+FROM) 44 TPI-9605- 055

AP-103F/FD-108 Allegheny F-2 75, Interconnecting W i r i n g D i a g r a m

- 1/69
Aug (Sheet 1 of 5) 22-03-00
F i g u r e 443 Pages 401/7, 401/8
 a
COLLINS
3I.AISTENASCE
MANUAL

POWER

ANNUN80RS
COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT AUTOPILOT TRIM T A B TRIM EMERG ENCY
IND CONTROLLER DIRECTOR IND WIRE FUNCTION AMPLIFIER COMPUTER COMPASS @ AMPLIFIER WIRE FUNCTION SERVO IND DISCONNECT J-BOX
3 3 1 A-6A 6 1 4E-2G 32957A 344C- 1 D 562A-5G 328A-2A @ 562C-4 3340-2-33D 327D-IW 121A-2
J1 J2 J1 JI J2 JI J2 JIA J1B (Jl) (J2) J J1 J1 (J1) J1

I I I I 1 COMPASS MON
(TP) (BPI
30
(TP) (BPI I
17 II I (TP)
I
(BP)
1 I I
I
9-1
I
- I I 1 COMPASS MON +
COMPASSDATAX
I

I
I
29
1
I
I

1
I

14-25
1 2 28 VDC PWR
B
A I
I
10-2
17 J
$
I I I TRIM TAB MOT L
COMPASS DATA Y 3 TRIM ENGAGE GND E M
I 18
-
1
1 1 1 I I I l l ' I I
I
34 A
x
TRIM T A B MOT CONT c--
I
=
11-3 4 33 TRIM T A B MOT CONT F + E
COMPASS DATA 2
I
30

I
I
l9

:,"
16
I
I
I
I
I
I
I
I
1
I
1
I
I
1
I - ) P
COMPASS FLAG
COMPASS FLAG
2 6 VAC HDG PWR
COMMON
+
-
I
I
I
I
31
32
15
16
' I
I
I
1
I
I
1
I I
I
22-
30-
I
I
I
5
1
I
I
I
33
34

53
52

I 1-
I
I
I
AILERON TRIM I N 0
AILERON TRIM IND
RUDDER TRIM IND
RUDDER TRIM IND
- +
-
+ R
A@ I
I
I
20
21 I I I I I
w
HEADING ERROR SYNCHRO C'
HEADING ERROR SYNCHRO H'
I
I
17
ia I I 11
-
49 COMPASS DATA X I
'
I I I h l I
13 HEADING RATE G2 I 19 4 I 50 COMPASS DATA Y

I
14
12
I
I
I
I I "I I HEADINGRATE C2
hEADlNG MOT CONT C I
I
I
20
21
I
I 1 3
27
I

I 'i-
COMPASS DATA 2
I
11
I
I
I
1
I hEADlNG MOT CONT M I II 2 2 [ I
23
GND
I AIRSPEED I
1 ; I I I
HEADING DATUM SYNCHRO C'
I I 1 33 I I 1 SENSOR

I
HEADING DATUM SYNCHRO H' DME
I I 1 I I
590E-2
12 COURSE DATUM SYNCHRO C' I 24 ~ ~ O E - Z
13
I
I
I
1
I
1
COURSE DATUM SYNCHRO H'
I I
34 (JI) I I 1 JI
+
45
46
I
I
I
I
1
I
DISTANCE IND FLA?
DISTANCE IND FLAG -
I
I
I
I
I
I
1
I
1
IO
9
I 59
58 I
AIRSPEED SIGNAL
AIRSPEED EXC H I
47
48 - I I I
DISTANCE IND 26 VAC H
DISTANCE IND 26 VAC C
1 1 1
' I
' 2
1
I 60

I 1
I AIRSPEED EXC C
I
49 J I 1 1 I D
I
50
I I I DISTANCE IND UNITS SYNCHRO X II II I I 4 F
51
52
I
I
I
I
I
I
DISTANCE IND UNITS SYNCHRO Y
DISTANCE IND TENS SYNCHRO X
I I
I

'
I

'
3
6 I I I I
53 DISTANCE IND TENS SYNCHRO Y
I I
l ' 5
I I I
54
I
I
I
I
I
I
DISTANCE IND HUNDREDS SYNCHRO X
I
I 1
I I I 7
I 1 I
55
I I 48 I
DISTANCE IND HUNDREDS SYNCHRO Y '
1
1
1
a
I I
I I 32
33
-h-F 26 VAC
26 CMD PWR PWR
VAC ATTITUDE
26 VAC ATTITUDE PWR COM
1

:;I
2 1

I I
I I
24
25
I
19
20
W

5 VAC LIGHTING PWR

5 VAC LIGHTING PWR COM I I I I I I I
I DCGND
I I 1-57 I I I I
I 1 1 5 VAC HEADING PWR
I
I 1 1 5 VAC ATTITUDE PWR
9
e
+za VDC PWR
+28VDCSERVOCLUTCH PWR
I
II I
I ' I I I I 61 - 28VDCPWR
U
P
RUDDER SERVO PWR
RUDDER SERVO PWR
AILERON SERVO PWR
AILERON SERVO PWR
ELEVATOR SERVO PWR W
I
PITCH STEERING + UP 3 - 3 1 ELEVATOR SERVO PWR X
PITCH STEERiYG + DN
ROLL STEERING + LEFT I 12 31 GND- 1
ROLL STEERING RIGHT+ I 13 21 1 1
L GYRO MODE + 13 41 40
K HEADING MODE + 47 64 I
J NAV/LOC MODE + 46 47 TPI-9605-055

AP-103F/FD-108 Allegheny F-27J, Interconnecting Wiring Diagram

lug 1/69 (Sheet 2 of 5) 22-03-00
Figure 443 Pages 401/9, 401/10
 a
COLLINS MAINTENANCE
w &IANUAL

COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT ALTITUDE AUTOPILOT EMERGENCY

ANNUNCIATORS IND CONTROLLER DIRECTOR IND WIRE FUNCTION AMPLIFIER COMPUTER CONTROLLER POWER AMPLIFIER WIRE FUNCTION SERVOS MlSC DISCONNECT J-BOX
(3 331A-6A 6 1 4E-2G 329&7A 344C-1 D 562A-5G 590A-3A
Q 562C-4 121A-2

fa
JI J2 JI J1 J2 JI J2 JIA J1B JI J1 J1

I I GO AROUND
BUTTON

I I I I I I
I - I I
I I I I 44-44
14 II II II 1
GO AROUND MODE t

3
I
'
1
h APPROACH MODE t I
APPROACH MODE t

I I 1 45
I I I
I 48 -APPROACH MODE t 3 I3
I W
I /
EXT STR t DN
EXT STR t UP
ALTlTUDE HOLD INTERLOCK
I I I I I ALTITUDE HOLD INTERLOCK
I

I I ' I I I I
ALTITUDE HOLD INTERLOCK
I
46
I
I I I
I
I
/
I
II I I 1
66 - DISCONNECT SWITCH H
4
I I 1 1
I
39-45
t I I I 67- DISCONNECT SWTCH C
I
I I I
I
I
I
I I I
I I I 'p- GLIDESLOPE MODE t PILOT'S
DISCONNECT
SWITCH
GO AROUND

I I I I I I I I ! I RELAY

I I
V

I
ALTITUDE HOLD MODE t
ALTITUDE RATE H'
ALTITUDE RATE C'
jI 47
34
24
I
I
I
14
15
'
I I ALTITUDE ERROR H'
ALTITUOE ERROR C' I ,
33
23 ' 16
27
I
41
42
-ALTITUDE GAIN CHANGE EXC
v
I

I I l2
l3
I
I
PITCH BOOTSTRAP TRANSMITTER X
PITCH BOOTSTRAP TRANSMITTER Y
39
42
I
I
43
44 - ALTITUDE GAIN CHANGE NO. 1
PITCH BOOTSTRAP TRANSMlTTER Z ALTITUDE GAIN CHANGE NO. 2

I I l4
l5
16
I
I
PITCH BOOTSTRAP EXC H
PITCH BOOTSTRAP EXC C 35 -
I I 26
27
I
I
I
BANK BOOTSTRAP TRANSMITTER X
BANK BOOTSTRAP TRANSMITTER Y 15
3 7 -GND

I I
59 - COMPUTER MDN t
BANK BOOTSTRAP TRANSMITTER Z 18 - EXT PITCH STEERING A
I
28
I 29 'I
I

BANKBOOTSTRAPEXC H I
I
I
I
19 - EXT PITCH STEERING 6
BANKBOOTSTRAPEXCC 25- AC PITCH STEERING A
30 I
I I I
HEADING WARNING DATA X
HEADING WARNING DATA Y
I
1 i 26-
27 -
AC PITCH STEERING El
PROCESSED PITCH DATA A

(0
I
I
I
I
I
I

I
HEADING
HEADING
WARNING
WARNING
DATA 2
DATA H
.
25
I, I I i 1
I

I
! 28- PROCESSED PITCH DATA B
INTERNAL PlTCM STEERlNG OFF t
A L T HDLO OFF t
HEADING WARNING DATA C
I I

I HEADING WARNING DATA H' ROLL STEERING A

I I I
22 HEADING WARNING DATA C' ROLL STEERINC B
I I I
I
PROCESSED BANK CMDA

I I I I
I
26
35
I
PROCESSED BANK CMD B
PROCESSED BANKDATAA

I I I P I
I
36
55
I
I
PROCESSED BANK DATA B
EXT BANK CMO B RUNWAY
54 EXT BANK CMO A FLAG
I I I PITCH MONITOR +
GLIDESLOPE ARM ANN -
12-12 1I 1I 1'
GS ARM
I I
GS EXT I GLIDESLOPE EXT ANN - 42 I II I'
N/L ARM
I
I
I

I
NAV/LOC ARM ANN - 6
N/L CAP
PWR
I I NAV/LOC CAPTURE ANN
ANNUNCIATOR PWR -
- 39 I I I
G S CAP
I
38 -RUNWAY FLAG - I I 1 RUNWAY FLAG - I

I I I 1 MKR BCN I t
I

GA
I I GO AROUND ANN- 16 I
R CVR
512-4
(11)
I 1
I MIDDLE MARKER 43
18
4
17
1 1 INTERNAL ROLL STEERING OFF t
A PITCH CONTROL E X C A 21
B PITCH CONTROL SIGNAL ~
20 TPI -9605 -055

AP-103F/FD-108 Allegheny F-27J,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 443 (Sheet 3) Pages 401/11, 401/12
 a
COLLINS
MAINTEKASCE
MANUAL
WW

COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT AUTOPILOT SERVOS EMERGENCY

ANNUNCIATORS IND CONTROLLER DIRECTOR IN0 WIRE FUNCTION AMP LIFlER COMPUTER MISC POWER AMPLIFIER WIRE FUNCTION MISC DISCONNECT J-BOX
33 1A-6A 614E-2G 329&7A 344C-1 D 562A-5G @ 562C-4 121A-2
J1 J2 J1 J1 J2 J1 J2 JlA JIB J1 J1 J1
1 I (TP) (BPI (TP) (BP) I CrP) (BPI
I
I PITCH CONTROL EXC B I
C 22
D I I I I NAV
RCVR
NAV
CONT
I
F
I
TURN CONTROLEXCB
I
22 51RV-1 313N-3 I
G
N
I
1
TURN CONTROL SlGNAL
INT MOTOR CONTROLVOLTAGE
I
I
20 I
62
(J2)
19
(J2)
I i
I
P
I
INT26VACMOTOREXCC
I
I
24 I L I
I
- 1
INT MOTOR RATE SIGNAL 54
I
I INT MOTOR SIGNAL COMMON
I I =
n
I
I
-
28 VOC PANEL LIGHT PWR
I
G ND I '/ 55 I
"
I

I
I
ENGAGE VOLTAGE
CYD
I
I
I I
K
I
I
ENGAGE PULSE
1
! 56 II
I DISENGAGE VOLTAGE I
' 37
ENGAGE READY I 55
Q f I
1
ALTITUDE HOLD MODE +
I

I
I 38
I 5lRV-1
f

r,
I
I
HEADING SYNCH CUTOUT
1 1 5 VAC AUTO PILOT FWR
1 1 5 VAC PWR
]201 I
7 1
1 SELF TEST
RELAY

r
I
1
INT 26 VAC MOTOR EXC H
I
23 I I
-S
I
I
I
ENGAGE INTERLOCK 54
-
-U
-V I
AILERON CLUTCH VOLTAGE 39
I
if
q-
ELEVATOR CLUTCH VOLTAGE 1 3 9
I
w- RUDDER CLUTCH VOLTAGE ~20- A
I 56 I
M +28 VDC AUTO PILOT PWR
-
X
I I 53 -YAW DAMPER ENGAGE MON +
L SPARE SENSING
I
AA I 65
1 ; 345A-48 @
BB
cc
DD
I GYRO MODE
I I ROLLRATEMOTORGNO
(ROLL)

I
EE HEADING MODE ll5VACPWR B
I YAW DAMP SW
FF NAV/LOC MODE 8
32 1 ROLL RATE EXC C E
I
GG APPROACH MODE 31 ROLLRATEEXC H F
I
nn MODE VOLTAGE H J 29 I ROLL RATE SIGNAL X G
21 PITCH DFFERENTLAL RESOLVER X
PITCH DIFFERENTIAL RESOLVER Y
P n C H D I F F E R E N T U L RESOLVER 2
I
1 10
b-
-
PITCH RATE MOTOR GND
115VACPWR
(PITCH)
A
B
32 -
PITCH DIFFERENTIAL RESOLVER H
PITCH OlFFERENTlAL RESOLVER C I 31
29
-
-
PITCH RATE EXC C
PITCHRATEEXCH
PITCH RATE SIGNAL X
E
F
G
16 PITCH DIFFERENTIAL RESOLVER H'

Q 27
28
PITCH DIFFERENTIAL RESOLVER C'
M I I K DFFERENTLAL RESOLVER X I 1 YAW RATE
GYRO

30
29 BANK DIFFERENTIAL RESOLVER Y
BANK O F F E R E N T U L RESOLVER Z
I I YAW RATE MOTOR GNO
3326-2
A
66 I
31
32
33
BAYK DlFFERENTlAL RESOLVER H
BANK DIFFERENTIAL RESOLVER C
W K DIFFERENTIAL RESOLVER H'
10
51
50
'
I
1 1 5 VPC PWR
YAWRATE E X C C
YAW RATE EXC H
B
E
F
.34 BANK DIFFERENTIAL RESOLVER C' 41) I YAW RATE S E N A L X G

TPI -9605 -055

A P -10 3 F/ FD-10 8 Allegheny F -2 7J

M a r 1/73 I n k r conne ct ing W i r ing Diagr a m 22-03-00
Figure 443 (Sheet 4) Pages 401/13, 401/14
 COLLINS
MAINTENANCE
ww MANUAL

NOTES:

A L L WIRE SIZES ARE NO. 2 2 UNLESS DESIGNATED OTHERWISE BY NUMBERS I N SQUARES.

Q SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BEGROUNDED AT THE 51RV-1

Q JUMPER WIRE FROM J I - 2 TO J1-3 OF THE COURSE INDICATOR SHOULD BE LONGER THAN SIX INCHES

@ A RELAY MUST BE INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE
51RV-1 WHEN THE AUTOPILOT IS ENGAGED.

Q THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWNG REFLECTS LOADS AS FOLLOWS.

AFCS LOA0 CIRCUIT REQUIRED LOAD ADDITIONAL LDADS

200 OHMS TO-FROM 100 OHMS JUMPER BP-43 TO BP-33 OF 51RV-1

500 OHMS GUDESLOPE POINTER 200 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 51RV-1
500 OHMS GUDESLOPE FLAG 250 OHMS JUMPER TP-21 TO TP-26 OF 51RV-1
500 OHMS LOC FLAG 250 OHMS JUMPER BP-32 TO BP-41 Cf S l R V - I
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO BP-30 AND BP-48 OF 5 1 RV-I

THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL
SYSTEM.

POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT LIGHT DIMMING CIRCUITS.

SENSING UNIT 345A-4( )AND RATE G Y R O 332G-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE.

ANNUNCIATORS CHOSEN MUST NOT EXCEED 100 MA. A COMMON +28 VDC IS USED FOR ANNUNCIATOR POWER.
THESE LEADS MUST BE TWISTED AND SHIELDED IF OVER TWO FEET LONG.

Q COMPARATOR WARNING RESOLVERS. DO NOT USE FOR OTHER PURPOSES UNLESS LOADING EFFECT IS EVALUATED

Q TOTAL WlRE RUN FROM BUS TO 1 2 1 A - 2 TO 562C-4 TO 3 4 4 C - 3 (PIN B) FOR EACH PRIMARY SERVO MUST NOT
EXCEED 90 FEET I F AWG 2 0 WIRE IS USED. WHEN GREATER THAN 90 FEET, INSTALL TERMINALS AT 562'2-4
MOUNT AND RUN AWG 2 0 WIRE FROM 562C-4 TO TERMINAL AND AWG 1 6 WIRE FROM TERMINAL 3 4 4 C - 3 PIN B.

Q AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.

0 A 12K OHMS 1/2 WATT 10% RESISTOR IS REQUIRED ON EACH TRIM INDICATOR MOVEMENT. WITH THE TRIM IN-
DICATOR CONNECTIONS AS ShOWN AND THE REVERSING LINKS INSTALLED FOR CORRECT SERVO PHASING ThE
PRIMARYSERVO CAPSTAN SHOULD TURN CLOCKWISEWHENVIEWED FROM THE CAPSTAN END UNDER THE FOL-
LOWING AIRCRAFT ATTITUDES:

AILERON - LEFT BANK

ELEVATOR - PITCHUP
-
RUDDER RIGHT YAW

POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT. THIS WILL
BE INDICATED I N THE INTERCONNECT POWER COLUMN BY A LETTER WITH AN HEXAGON SYMBOL AROUND IT, CAPITAL LETTERS
FOR OC AND LOWER CASE LETTERS FOR AC.

A -2 8 VDC DIMMING CIRCUIT -

a 5 VAC DIMMING CIRCUIT
B,C,D,E - 2 8 VDC 5 AMP b,c,d - 1 1 5 VAC 2 AMP
F,G -
2 8 V D C 1 AMP e - 1 1 5 VAC 1 AMP
f - 115VAC3AMP

8 THE GO AROUND RELAY IS INSTALLED IN CONJUCTION WITH APPLICABLE F S B FOR WINGS LEVEL, PITCH UP
GO AROUND. GO AROUND BUTTON IS NORMALLY OPEN AND NORMALLY IS INSTALLED ON CONTROL COLUMN
WHEEL. TO DEACTIVATE GO AROUND PROVISION REMOVE THE RELAY AND CONNECT THOSE WIRES TOGETHER
THATARE CONNECTED BYTHENORMALLYCLOSED CONTACTSOF THERELAY.

Q WHEN OPTIONAL 5 9 0 A - 3 A
ARE APPLICABLE:
SERVICE BULLETIN N0.3 IS INCORPORATED, THE FOLLOWING INTERCONNECTING WIRING CHANGES

REMOVE CONNECTION BETWEEN J I ( B P ) - 3 8 OF T H E 5 6 2 C - 4 AUTOPILOT AMPLIFIER AND JI-d OF T H E 614E-2G

PEDESTAL CONTROLLER. REMOVE C O N N E C T I O N BETWEEN JI-V OF T H E 614E-2G PEDESTAL CONTROLLER AND
JIA(TP)-47 OF T H E 5 6 2 A - 5 0 FLIGHT COMPUTER, M A K E CONNECTIONS AS SHOWN BELOW.
PEDESTAL FLIGHT ALTITUDE AU OPILOT
CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMJUFIER

614E-2G 562A-5G 590A-3A 562C-4

JI JIA J I B (JI) JI JI
(TP) (BP) (TP) (BP)
V _ _ _ _ _ _ _ALTITUDEHOLD MODE + ___________
ALTITUDE HOLD MODE t 47
34
20 38
TPI-9605-055

AP-103F/FD-108 Allegheny F-27J,

Mar 1/73 Interconnecting Wiring Diagram 22 -03 -00
F igure 443 (Sheet 5) Pages 401/14A, 401/14B
 a
COLLINS
MAINTENASCE
MANCAL

(To Be Supplied)

Pages 401/17, 401/18; 401/19, 401/20; and

401/21, 401/22 reserved for additional
sheets of figure.

AP-l03F/FD-108 Dove, Interconnecting Wiring Diagram (TBS)

Figure 444

May 1/67 22-03-00

Pages 401/15, 401/16
 COLLINS
lI.IISTES.4SCE
SIASUUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR AMPLIFIER AILERON DISCONNECT
CONTROLLER DIRECTOR AMPLIFIER COMPUTER VERT

@ 331A-6A
INDICATOR 3 4 4 C - 1D 562A-5G REF 0 562C-4 334c-3 12 IA-2
6 14E-2G 3296-7A JI J2 JIA JIB 3320-11 J1 JI JI JI
JI J2 JI J1 J2 (TP) (BP) (TP) (BP) (J 1 ) UP)
I 6 6 ;"; PITCH ATTITUDE ERROR H ' 24 14 AILERON FIELD NUMBER I A
I 1
14 7 7 L, PITCH ATTITUDE ERROR C' 23
15 ' 8 a PITCH ATTITUDE SERVO DRIVE M 2 28 Q 62
5--- ,.' AILERON
2 8 VDC FIELD NUMBER 2 C
B
23 9 9 PITCH ATTITUDE SERVO DRIVE C 27 AILERON SIGNAL C E
37 IO IO :-', PITCH ATTITUDE RATE G2 25 AILERON EXCITATION C F
38
39
40
22
23
25
II
I
._.
I I

:-;
I ,
,_,
PITCH ATTITUDE RATE C2
MANUAL PITCH COMMAND H '
MANUAL PITCH COMMAND C'
26
36
;:--_t
15
16
12
'a:
;,
AILERON
AILERON
AILERON
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
- G
H
L

,!.*
2 26
41 26 42 V-BAR PITCH COMMAND SERVO DRIVE M I II II AILERON SERVO GRD R
17 < I AILERON RATE SIGNAL S
42 27 -4 V-BAR PITCH COMMAND SERVO DRIVE C IO
(J2)

-
43 28 ;-; a
44 29
44
I ,
V-BAR PITCH COMMAND RATE
MJ
P AILERON ENGAGE VOLTAGE A E
30
45
40
,-.
\-, V-BAR PITCH COMMAND SIG COM
V-BAR PITCH POS XMTR X
9
AILERON ENGAGE VOLTAGE B F
W 7
u
I I 7
I I
31 41 ,_, V-BAR PITCH POS XMTR Y 6 E LEVATOR
334c-3
32 PITCH ATTITUDE CT X A-3 (J1)
33 4 PITCH ATTITUDE CT Y 20 B
34 5 PITCH ATTITUDE CT 2 C ELEVATOR FIELO NUMBER I A
35 17 BANK ATTITUDE CT X 30- D 2BVDC B
36 18 BANK ATTITUDE CT Y 20- E ELEVAJOR FIELD NUMBER 2 C
37
38
-1
20
,-. BANK ATTITUDE CT Z
BANK ATTITUDE ERROR H ' 18
F ELEVATOR SIGNAL C
ELEVATOR EXCITATION C
E
F
39 21
I I
, I
~~ BANK ATTITUDE ERROR C' 17 '71
R ELEVATOR POSITION EXCITATION H - G
40 22 BANK ATTITUDE SERVO DRIVE M 2 22 ELEVATOR RATE EXCITATION H H
42 23 BANK ATTITUDE SERVO DRIVE C 21 T ELEVATOR POSITION SIGNAL L
43 24 BANK ATTITUDE RATE G2 19 ELEVATOR SERVOGRD R
44 25 ._.
I ,
BANK ATTITUDE RATE C2 20 ELEVATOR RATE SIGNAL S
. 45 36 V-BAR ROLL COMMAND SERVO DRIVE M 2 --
7R fJ2)
46 37 V-BAR ROLL COMMAND SERVO DRIVE C 27 ELEVATOR ENGAGE VOLTAGE A. J
j N 2 FAST
ELEVATOR ENGAGE VOLTAGE B H
47 38 I.-\I
V-BAR ROLL COMMAND RATE G2 25 K ERECT
48 39 I.-a ' V-BAR ROLL COMMAND SIG COM 26 H GRD RUDDER
49 34 V-BAR ROLL POS XMTR H I -.
74 334c-3
50 35 V-BAR ROLL POS XMTR C I 23 G T RUDDER FIELD NUMBER 1 (J
I I5VAC ATTITUDE POWER 5 - 28 VDC B
51 GYRO MON t 29 10-N -
RUDDER FIELD PlUMBER 2 C
52 31 GYRO HIGH LEVEL FLAG t 31 I*,
43 RUDDER SIGNAL C E
53 18- GYRO HIGH LEVEL FLAG - 32 ..
...
NAV 'd
RUDDER EXCITATION C F
54
55
4- STEER FLAG-
STEERFLAG- 2
2
28
RCVR
51RV-I
45 RUDDER POSITION EXCITATION H - G
46 I
*,
,
RUDDER RATE EXCITATION H H
16- t 2 8 VDC FLAG POWER 54 (TP) 42 I*,
RUDDER POSITION SIGNAL L
33 1- GLIDE SLOPE DEV + U P I ,
32 8 0 41 RUDDERSERVOGRD R
34 I -I GLIDE SLOPE DEV t DN 22 9 47 A RUDDER RATE SIGNAL S
.35 12- GLIDE SLOPE LOW LEVEL FLAG t 21 5-1
(J2)
36 I3- GLIDE SLOPE LOW LEVEL FLAG - 22
RUDDER ENGAGE VOLTAGE A B
GLIDE SLOPE HIGH LEVEL FLAG t II 27
RUDDER ENGAGEVOLTAGE B C
(64 TRIM TRIM
29 6- VOR/LOC OEV t LEFT 32-40
.~ SERVO INDICATOR
334D-2-33D 3 2 7 D - Iw
J 8 5- VOR/LOC OEV +RIGHT 22-39 (J 1)
PVOR/LOC HIGH LEVEL FLAG t I 1-50
TRIM TAB MOT CONT F-
GS CAP 38- RUNWAY FLAG - 5
@ E
LDCFREQVOLTAGEt 43 -38 33 TRIM TAB MOT CONT G t
,-. 21
8 I I COURSE RESOLVER H GRD B
TRIM MOTOR GROUND
!I
._.
I O
COURSE RESOLVER C 23
28VDC
TRIM ENGAGE VOLTAGE
A
D L
4 :-: COURSE RESOLVER D 24
TRIM ENGAGE GROUND E M
5 !.! COURSE RESOLVER E 25
6 :-; COURSE RESOLVER F 26
7 ._,
, I
COURSE RESOLVER G 27
31 VORILOC F L A G 4 41
32 VORILOC FLAG - 42
26 TO-FROM ARROW ( 7 TO) 43
27 TO-FROM ARROW ( * FROM) 44 TPI-3122-044

AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 445
Nov 1/68 22-03-00
Pages 401/23, 401/24
 a
COLLINS
MAISTES.1SCE
SlASUAL

ANNUN- COURSE PEDESTAL FLIGHT DIRECTOR WIRE FUNCTION INSTRUMENT FLIGHT MlSC
POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC
CIATORS INDICATOR CONTROLLER INDICATOR AMPLIFIER COMPUTER AMPLIFIER EMERGENCY J-BW
DISCONNECT

344C-ID 562A-5G
COMPASS
328A-2A 6
Q 562C-4
33 IA-6A 6 14E-2G 3298-7A 121A-2
JI J2 JI JI JI
0 JI 52 JI JI
UP) (Bp)
JIA
(TP)
JIB
(BP) 27R
-D
J2
(TO (BP) JI
COMPASS MON- 71-3
COMPASS M O N t 29 14-25
COMPASS DATA X

COMPASS DATA Y
: I ,o l
COMPASS DATA Z
AIRSPEED
7 z I : II 49 -COMPASS DATA X SENSOR
4 50- COMPASS DATA Y
30 COMPASS FLAG t 31 5906-2
3 51- COMPASS DATA Z JI
24
15
COMPASS FLAG
2 6 VAC HDG PWR
- 32 59 AIRSPEED SIGNAL
15 58 AIRSPEED EXCITATION H
16 COMMON 16 60 AIRSPEED EXCITATION C
I-,
20 I I HEADING ERROR SYNCHRO C' 17 E
21 I I
%_I
HEADING ERROR SYNCHRO H ' li? D
13 ;-; HEADING RATE G2 19
4 ,
14 $-, HEADING RATE C2 20
12 HDG MOT CONT C I - 21
II HDG MOT CONT M I 22
4 HEADING DATUM SYNCHRO C' 23
5 HEADING DATUM SYNCHRO H' 33 DME
12 COURSE DATUM SYNCHRO C' 24 860E
13 COURSE DATUM SYNCHRO H' 34 (JI)
45 DISTANCE INDICATOR FLAG t 9
46 DISTANCE INDICATOR FLAG - IO
47 DISTANCE INDICATOR 26 VAC H 2
8 4 DISTANCE INDICATOR 2 6 V A C C I
49
50 DISTANCE INDICATOR UNITS SYNCHRO X 4
51
52
DISTANCE INDICATOR UNITS SYNCHRO Y
DISTANCE INDICATOR TENS SYNCHRO X
3
6 RUOOERSERVO POWER
-
-
16 S
53 DISTANCE INDICATOR TENS SYNCHRO Y 5
2 RUDDER SERVO POWER 20 T
54 DISTANCE INDICATOR HUNDREDS SYNCHRO X 7 AILERON SERVO POWER v
- U
55 DISTANCE INDICATOR HUNDREDS SYNCHRO Y 8 I*' AILERON SERVO POWER -
20 V
-4 26 VAC COMMAND PWR 12
7; -
16 W
32
33 !-!
26 VAC ATTITUDE PWR
2 6 VAC ATTITUDE PWR COM
15
16
SERVO POWER -
"0 X

24 19- 5 VAC LIGHTING PWR

25 20- 5 VAC LIGHTING PWR COM
T r 5 7
OC GROUND I- - 1 I GRD
I I 5 VAC HEADING f W R 5 5;

115VAC ATTITUDE PWR 4 d6 C

9 t28MCPOWER 54
e t 2 8 VDC SERVO CLUTCH POWER
PITCH STEERING + U P
a 3-3 I
6

PITCH STEERING t DOWN 4-2 I Q 9

ROLL STEERING t LEFT 12 31
ROLL STEERING t RIGHT 13-1 -.
L GYRO MODE t 13 :I -60 .-
K HEADING MODE + 47 64
J NAV/LOC MODE t 46 47
H APPROACH MODE t 45 48
66 -DISCONNECT SWITCH H
67 -DISCONNECT SWITCH C -.5-5 1
3 9 4 5 46- GLIDE SLOPE MODE t P I LOT'S COPILOT'S
W ALTITUDE HOLD INTERLOCK 46 DISCONNECT
SWITCH TPI-3122-044

AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 445

Nov 1/68 22-03-00

Pages 401/25, 401/26
 COLLINS
lI.IISTES.4SCE
SIASUUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR AMPLIFIER AILERON DISCONNECT
CONTROLLER DIRECTOR AMPLIFIER COMPUTER VERT

@ 331A-6A
INDICATOR 3 4 4 C - 1D 562A-5G REF 0 562C-4 334c-3 12 IA-2
6 14E-2G 3296-7A JI J2 JIA JIB 3320-11 J1 JI JI JI
JI J2 JI J1 J2 (TP) (BP) (TP) (BP) (J 1 ) UP)
I 6 6 ;"; PITCH ATTITUDE ERROR H ' 24 14 AILERON FIELD NUMBER I A
I 1
14 7 7 L, PITCH ATTITUDE ERROR C' 23
15 ' 8 a PITCH ATTITUDE SERVO DRIVE M 2 28 Q 62
5--- ,.' AILERON
2 8 VDC FIELD NUMBER 2 C
B
23 9 9 PITCH ATTITUDE SERVO DRIVE C 27 AILERON SIGNAL C E
37 IO IO :-', PITCH ATTITUDE RATE G2 25 AILERON EXCITATION C F
38
39
40
22
23
25
II
I
._.
I I

:-;
I ,
,_,
PITCH ATTITUDE RATE C2
MANUAL PITCH COMMAND H '
MANUAL PITCH COMMAND C'
26
36
;:--_t
15
16
12
'a:
;,
AILERON
AILERON
AILERON
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
- G
H
L

,!.*
2 26
41 26 42 V-BAR PITCH COMMAND SERVO DRIVE M I II II AILERON SERVO GRD R
17 < I AILERON RATE SIGNAL S
42 27 -4 V-BAR PITCH COMMAND SERVO DRIVE C IO
(J2)

-
43 28 ;-; a
44 29
44
I ,
V-BAR PITCH COMMAND RATE
MJ
P AILERON ENGAGE VOLTAGE A E
30
45
40
,-.
\-, V-BAR PITCH COMMAND SIG COM
V-BAR PITCH POS XMTR X
9
AILERON ENGAGE VOLTAGE B F
W 7
u
I I 7
I I
31 41 ,_, V-BAR PITCH POS XMTR Y 6 E LEVATOR
334c-3
32 PITCH ATTITUDE CT X A-3 (J1)
33 4 PITCH ATTITUDE CT Y 20 B
34 5 PITCH ATTITUDE CT 2 C ELEVATOR FIELO NUMBER I A
35 17 BANK ATTITUDE CT X 30- D 2BVDC B
36 18 BANK ATTITUDE CT Y 20- E ELEVAJOR FIELD NUMBER 2 C
37
38
-1
20
,-. BANK ATTITUDE CT Z
BANK ATTITUDE ERROR H ' 18
F ELEVATOR SIGNAL C
ELEVATOR EXCITATION C
E
F
39 21
I I
, I
~~ BANK ATTITUDE ERROR C' 17 '71
R ELEVATOR POSITION EXCITATION H - G
40 22 BANK ATTITUDE SERVO DRIVE M 2 22 ELEVATOR RATE EXCITATION H H
42 23 BANK ATTITUDE SERVO DRIVE C 21 T ELEVATOR POSITION SIGNAL L
43 24 BANK ATTITUDE RATE G2 19 ELEVATOR SERVOGRD R
44 25 ._.
I ,
BANK ATTITUDE RATE C2 20 ELEVATOR RATE SIGNAL S
. 45 36 V-BAR ROLL COMMAND SERVO DRIVE M 2 --
7R fJ2)
46 37 V-BAR ROLL COMMAND SERVO DRIVE C 27 ELEVATOR ENGAGE VOLTAGE A. J
j N 2 FAST
ELEVATOR ENGAGE VOLTAGE B H
47 38 I.-\I
V-BAR ROLL COMMAND RATE G2 25 K ERECT
48 39 I.-a ' V-BAR ROLL COMMAND SIG COM 26 H GRD RUDDER
49 34 V-BAR ROLL POS XMTR H I -.
74 334c-3
50 35 V-BAR ROLL POS XMTR C I 23 G T RUDDER FIELD NUMBER 1 (J
I I5VAC ATTITUDE POWER 5 - 28 VDC B
51 GYRO MON t 29 10-N -
RUDDER FIELD PlUMBER 2 C
52 31 GYRO HIGH LEVEL FLAG t 31 I*,
43 RUDDER SIGNAL C E
53 18- GYRO HIGH LEVEL FLAG - 32 ..
...
NAV 'd
RUDDER EXCITATION C F
54
55
4- STEER FLAG-
STEERFLAG- 2
2
28
RCVR
51RV-I
45 RUDDER POSITION EXCITATION H - G
46 I
*,
,
RUDDER RATE EXCITATION H H
16- t 2 8 VDC FLAG POWER 54 (TP) 42 I*,
RUDDER POSITION SIGNAL L
33 1- GLIDE SLOPE DEV + U P I ,
32 8 0 41 RUDDERSERVOGRD R
34 I -I GLIDE SLOPE DEV t DN 22 9 47 A RUDDER RATE SIGNAL S
.35 12- GLIDE SLOPE LOW LEVEL FLAG t 21 5-1
(J2)
36 I3- GLIDE SLOPE LOW LEVEL FLAG - 22
RUDDER ENGAGE VOLTAGE A B
GLIDE SLOPE HIGH LEVEL FLAG t II 27
RUDDER ENGAGEVOLTAGE B C
(64 TRIM TRIM
29 6- VOR/LOC OEV t LEFT 32-40
.~ SERVO INDICATOR
334D-2-33D 3 2 7 D - Iw
J 8 5- VOR/LOC OEV +RIGHT 22-39 (J 1)
PVOR/LOC HIGH LEVEL FLAG t I 1-50
TRIM TAB MOT CONT F-
GS CAP 38- RUNWAY FLAG - 5
@ E
LDCFREQVOLTAGEt 43 -38 33 TRIM TAB MOT CONT G t
,-. 21
8 I I COURSE RESOLVER H GRD B
TRIM MOTOR GROUND
!I
._.
I O
COURSE RESOLVER C 23
28VDC
TRIM ENGAGE VOLTAGE
A
D L
4 :-: COURSE RESOLVER D 24
TRIM ENGAGE GROUND E M
5 !.! COURSE RESOLVER E 25
6 :-; COURSE RESOLVER F 26
7 ._,
, I
COURSE RESOLVER G 27
31 VORILOC F L A G 4 41
32 VORILOC FLAG - 42
26 TO-FROM ARROW ( 7 TO) 43
27 TO-FROM ARROW ( * FROM) 44 TPI-3122-044

AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 445
Nov 1/68 22-03-00
Pages 401/23, 401/24
 a
COLLINS
MAISTES.1SCE
SlASUAL

ANNUN- COURSE PEDESTAL FLIGHT DIRECTOR WIRE FUNCTION INSTRUMENT FLIGHT MlSC
POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC
CIATORS INDICATOR CONTROLLER INDICATOR AMPLIFIER COMPUTER AMPLIFIER EMERGENCY J-BW
DISCONNECT

344C-ID 562A-5G
COMPASS
328A-2A 6
Q 562C-4
33 IA-6A 6 14E-2G 3298-7A 121A-2
JI J2 JI JI JI
0 JI 52 JI JI
UP) (Bp)
JIA
(TP)
JIB
(BP) 27R
-D
J2
(TO (BP) JI
COMPASS MON- 71-3
COMPASS M O N t 29 14-25
COMPASS DATA X

COMPASS DATA Y
: I ,o l
COMPASS DATA Z
AIRSPEED
7 z I : II 49 -COMPASS DATA X SENSOR
4 50- COMPASS DATA Y
30 COMPASS FLAG t 31 5906-2
3 51- COMPASS DATA Z JI
24
15
COMPASS FLAG
2 6 VAC HDG PWR
- 32 59 AIRSPEED SIGNAL
15 58 AIRSPEED EXCITATION H
16 COMMON 16 60 AIRSPEED EXCITATION C
I-,
20 I I HEADING ERROR SYNCHRO C' 17 E
21 I I
%_I
HEADING ERROR SYNCHRO H ' li? D
13 ;-; HEADING RATE G2 19
4 ,
14 $-, HEADING RATE C2 20
12 HDG MOT CONT C I - 21
II HDG MOT CONT M I 22
4 HEADING DATUM SYNCHRO C' 23
5 HEADING DATUM SYNCHRO H' 33 DME
12 COURSE DATUM SYNCHRO C' 24 860E
13 COURSE DATUM SYNCHRO H' 34 (JI)
45 DISTANCE INDICATOR FLAG t 9
46 DISTANCE INDICATOR FLAG - IO
47 DISTANCE INDICATOR 26 VAC H 2
8 4 DISTANCE INDICATOR 2 6 V A C C I
49
50 DISTANCE INDICATOR UNITS SYNCHRO X 4
51
52
DISTANCE INDICATOR UNITS SYNCHRO Y
DISTANCE INDICATOR TENS SYNCHRO X
3
6 RUOOERSERVO POWER
-
-
16 S
53 DISTANCE INDICATOR TENS SYNCHRO Y 5
2 RUDDER SERVO POWER 20 T
54 DISTANCE INDICATOR HUNDREDS SYNCHRO X 7 AILERON SERVO POWER v
- U
55 DISTANCE INDICATOR HUNDREDS SYNCHRO Y 8 I*' AILERON SERVO POWER -
20 V
-4 26 VAC COMMAND PWR 12
7; -
16 W
32
33 !-!
26 VAC ATTITUDE PWR
2 6 VAC ATTITUDE PWR COM
15
16
SERVO POWER -
"0 X

24 19- 5 VAC LIGHTING PWR

25 20- 5 VAC LIGHTING PWR COM
T r 5 7
OC GROUND I- - 1 I GRD
I I 5 VAC HEADING f W R 5 5;

115VAC ATTITUDE PWR 4 d6 C

9 t28MCPOWER 54
e t 2 8 VDC SERVO CLUTCH POWER
PITCH STEERING + U P
a 3-3 I
6

PITCH STEERING t DOWN 4-2 I Q 9

ROLL STEERING t LEFT 12 31
ROLL STEERING t RIGHT 13-1 -.
L GYRO MODE t 13 :I -60 .-
K HEADING MODE + 47 64
J NAV/LOC MODE t 46 47
H APPROACH MODE t 45 48
66 -DISCONNECT SWITCH H
67 -DISCONNECT SWITCH C -.5-5 1
3 9 4 5 46- GLIDE SLOPE MODE t P I LOT'S COPILOT'S
W ALTITUDE HOLD INTERLOCK 46 DISCONNECT
SWITCH TPI-3122-044

AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 445

Nov 1/68 22-03-00

Pages 401/25, 401/26
 a
COLLINS MAINTEIVANCE
w &IANUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POKlR AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER ALTITUDE AMPLIFIER DISCONNECT
@ 33 IA-6A I14E-2G
INDICATOR
3296-7A
CONTROLLER @
344c- I O 562A-5G 590A-3A 562C-4 12 IA-2
JI J2 JI JI J2 JI J2 JIA JIB JI JI J1 VI
(TP) (Bp) (TP) (BP) UP) (BP)
V ALTITUDE HOLD MODE +
I-,
47 34 @
ALTITUDE RATE H ' ,I I
34 14
ALTITUDE RATE C' 1-1 24 15
ALTITUDE ERROR Hi ,-\ 33 16 41
,I I,
ALTITUDE ERROR C' I , 23 27 42
-1 PITCH BOOTSTRAP TRANSMITTER X 39 -4 ALTITUDE GAIN CHANGE EXCITATION
-51 PITCH BOOTSTRAP TRANSMITTER Y 42 :4 ALTITUDE GAIN CHANGE NO. 1
-I PITCH BOOTSTRAP TRANSMITTER Z 43 45 ALTITUDE GAIN CHANGE NO. 2
15 PITCH BOOTSTRAP EXCITATION H 36 @
16 PITCH BOOTSTRAP EXCITATION C 35 GRO
26 BANKBOOTSTRAPTRANSMITTERX 37 GRD
27 BANKBOOTSTRAPTRANSMITTER Y 15 59 COMPUTER MON +
28 BANKBOOTSTRAPTRANSMITTERZ EXT PITCH STEERING A
29 BANK BOOTSTRAP EXCITATION H EXT PITCH STEERING B
30 BANK BOOTSTRAP EXCITATION C AC PITCH STEERING A
HEADING WARNING DATA X AC PITCH STEERING B
HEADING WARNING DATA Y PROCESSED PITCH DATA A
HEADING WARNING DATA Z PROCESSED PITCH DATA B
Q
- HEADING WARNING DATA H INTERNAL PITCH STEERING OFF t
I 20 HEADING WARNING DATA C 48 60- A L T HOLD OFF +
HEADING WARNING DATA H'
,-, ROLL STEERING A
18
I ! ROLL STEERING B
HEADING WARNING DATA C' 19 -'
I 49 25
,-*
, I PROCESSED BANK CMD A
PROCESSED BANK CMO 6
PROCESSED BANK DATA A
I 25 36
I 1
2
,-\
PROCESSED BANK DATA B
55 EXT BANK CMO B
,I II
54 I_'
EXT BANK CMO A
GS ARM GLIDE SLOPE ARM. ANN. - 6
GS EXT GLIDE SLOPE EXT. ANN. - 42
N/L ARM NAV/LOC ARM. ANN. - 6
N/L CAP NAV/LOC CAPTURE ANN. - 39
PWR ANNUNCIATOR POWER
PITCH MONITOR t 12- 12 MKR BCN
RCVR
5 12-4
(J 1)
MIOOLE MARKER 43 4
18 57 INTERNAL ROLL STEERING OFF t
A PITCH CONTROL EXC A 21 NAV NAV 51RV-I
B PITCH CONTROL SIGNAL 20 RCVR CONT SELF TEST
C PITCH CONTROL EXC B 22 51RV-I 313N-3 RELAY
D (J2) (52)
E TURN CDNTROLEXCA 21
F TURNCONTRDLEXCB 22 I ?

G TURN CONTROL SIGNAL 20 L C

N INT MOTOR CONTROL VOLTAGE 62 It
I
P INT 26VAC MOTOR EXCITATION C 24 54 i
R INT MOTOR RATE SIGNAL 63
S INT MOTOR SIGNAL COMMON 24
T 28VOC PANEL LIGHT FWR
U GROUND GRD
X
Y ENGAGE VOLTAGE

4
L

a ENGAGE PULSE 56
b DISENGAGE VOLTAGE 37
ENGAGE READY 55
ALTITUDE HOLD MODE t 38
TPI-3122-044

Mar 1/73 AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram 22-03-00

Figure 445 (Sheet 3) Pages 401/27, 401/28
 a
COLLINS
MMAIIVTENANCE
ww MANUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS IN0 ICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER TRIM INDICATOR DISCONNECT
@ 33 I A-6A 614E-2G
INDICATOR
3296-7A 344C- ID 562A-5G
15
562C-4 3270- IW 12 I A - 2

JI J2 J1 JI J2 JI J2 JIA JIB JI JI JI
(TP) (BP) (TP) (BP) (TP) (BPI
f HEADING SYNCH CUTOUT 38
33
9 I I 5 VAC POWER 1- 7 @ A
34 t
_I& -vv- -
I INT 26VAC MOTOR EXCITATION H 23 O R
P
s
I 1 5 VAC AUTO PILOT PWR
ENGAGE INTERLOCK
a 5:
54
t

"
*
U

W
AILERONCLUTCHVOLTAGE
RUDDER CLUTCHVOLTAGE
35
56 a
53 D
A
I
M t 2 8 V O C AUTO PILOT PWR R -,
* I

" ELEVATOR CLUTCHVOLTAGE 39 E K

-5 YAW DAMPER ENGAGE MON+

- "
Y SPARE 9
SENSING UNIT
YAW DAMP SW u

1
00 GYRO MODE
EE HEADING MODE ROLL RATE MOTOR GRO A
FF NAV/LOC MODE @ - 1 I 5 VAC POWER B
GG APPROACH MODE 32 ROLL RATE EXCITATION C E
HH MODE VOLTAGE H 31 ROLL RATE EXCITATION H F
ROLL RATE SIGNAL X G
2 -I PITCH DIFFERENTIAL RESOLVER X (PITCH)
2 2- PITCH DIFFERENTIAL RESOLVER Y -B PITCH RATE MOTOR GRO A
2+ PITCH DIFFERENTIAL RESOLVER Z IO- I 15 VAC POWER B
24- PITCH DIFFERENTIAL RESOLVER H 32- PITCH RATE EXCITATION C E
2 5- PITCH DIFFERENTIAL RESOLVER C 31- PITCH RATE EXCITATION H F
2-6 PITCH DIFFERENTIAL RESOLVER H ' -2 PITCH RATE SIGNAL X G
2 7- PITCH DIFFERENTIAL RESOLVER C' YAW RATE
0 2 0 BANK DIFFERENTIAL RESOLVER X GYiW
2 1 BANK DIFFERENTIAL RESOLVER Y 3326-2
3- BANK DIFFERENTIAL RESOLVER Z 66 YAW RATE MOTOR GRO A
31- BANK DIFFERENTIAL RESOLVER H IO I 15 VAC POWER B
32- BANK DIFFERENTIAL RESOLVER C 51 YAW RATE EXCITATION C E
33 - BANK DIFFERENTIAL RESOLVER H' 50 YAW RATE EXCITATION H F
34 - BANK DIFFERENTIAL RESOLVER C' 40 YAW RATE SIGNAL X G

SYMBOLS USED:

0 NOTES
NOTES:

I. A L L WIRE SIZES ARE NO. 2 2 UNLESS DESIGNATED OTHERWISE B Y NUMBERS IN SQUARES. I I. COMPARATOR WARNING RESOLVERS.
2. SHIELDS ON THE NAVRESOLVER LEADS FROMTHE NAVIGATION RECEIVERSHOULD B E G R O U N O E O A T T H E 5 I R V - I . 12. TOTAL WIRE RUN FROM BUSS TO 121A-2 TO 562C-4 TO 334-3 (PIN B) FOR EACH PRIMARY SERVO MUST NOT EXCEED 90 FEET IF AWG 2 0 W I R E IS
3. JUMPER WIRE FROM J 1-2 TO J 1-3 OF THE COURSE INDICATOR SHOULD B E NO LONGER THAN SIX INCHES. USED. WHEN GREATER THAN 90 FEET, INSTALL TERMINALS AT 5 6 2 C - 4 MOUNT AND RUN AWG 2 0 WIRE FROM 562C-4 TO TERMINAL AND AWG 16
4. A RELAY MUST BE INSTALLED IN THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE 5 1 R V - I WHEN THE AUTOPILOT IS ENGAGED. WIRE FROM TERMINAL 3 4 4 C - 3 PIN B.
5. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWING REFLECTS LOADS AS FOLLOWS: 13. AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.
AFCS LOAD CIRCUIT REQUIRED LOA0 ADDITIONAL LOADS 14. A 12K OHMS 1/2 WATT RESISTOR IS REQUIRED ON EACH TRIM INDICATOR MOVEMENT.
15. POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT. THIS W I L L BE INDICATED IN THE
2 0 0 OHMS TO-FROM 100 OHMS JUMPER B P - 4 3 TO B P - 3 3 0 F 5 1 R V - I INTERCONNECT POWER COLUMN B Y A LETTER WITH AN OCTAGON SYMBOL AROUND IT, CAPITAL LETTERS FOR DC AND LOWER CASE LETTERS FOR AC.
5 0 0 OHMS GLIDE SLOPE DEVIATION 200 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 5 1 R V - I
500 OHMS GLIDE SLOPE FLAG 2 5 0 OHMS JUMPER TP-2 I TO TP-26 OF 5 I R V - I -
A 2BVDC DIMMING CIRCUIT. -
a 5VAC DIMMING CIRCUIT
500 OHMS VOR/LOC FLAG 250 OHMS JUMPER BP-32 TO BP-4 I OF 5 IRV- I -
B, C ,0, E 28VDC 5 AMP e -C ,1 I5VAC
b, d- I l5VAC
I AMP
2AMP
500 OHMS VOR/LOC DEVIATION 2 0 0 OHMS JUMPER B P - 3 9 T 0 BP-30AND BP-4BOF 5 1 R V - I -
G 2BVDC I AMP
-
f I I5VAC 3 A M P
6 . THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL SYSTEM. 16. WHEN OPTIONAL 590A-3A SERVICE BULLETIN NO. 3 IS INCORPORATED, THE FOLLOWING INTERCONNECTING WIRING CHANGES ARE APPLICABLE:
7. POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT LIGHT DIMMING CIRCUITS. REMOVE CONNECTION BETWEEN J l ( B P F 3 8 OF THE 562C-4 AUTOPILOT AMPLIFIER AN0 J I - d OF THE 614E-2G PEDESTAL CONTROLLER.
8. SENSING UNIT 3 4 5 A 4 0 A N D RATE GYRO 332G-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE. REMOVE CONNECTION BETWEEN JI-V OF THE 614E-2G PEDESTAL CONTROLLER AN0 J l A ( T P F 4 7 OF THE 562A-5G FLIGHT COMPUTER.
9. ANNUNCIATORS CHOSEN MUST NOT EXCEED IOOMA. A COMMON t2BVOC IS USED FOR ANNUNCIATOR POWER.
MAKE CONNECTIONS AS SHOWN BELOW.
I O . THESE LEADS MUST BE TWISTED AND SHIELDED IF OVER TWO FEET LONG. TPI- 3122-044
PEDESTAL FLIGHT ALTITUDE AUTOPILOT

M a r 1/73 AP-103F/FD-108 HS-125, Interconnecting Wiring Diagram 2 2 -0 3 -00

Figure 445 (Sheet 4) Pages 401/29, 401/30
 e
COLLINS
JI.4ISTES.ASCE

PP-103 F L I G H T CONTROL SYSTCM

7b7-8258-1301
IMPORTANT: READ ALL NOTES CAREFULLY. NLIMBERS I N 0 APFLY TO A S P E C I F I C NOTE.

FLIGHT
ANNUN- COURSE 'EDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGFNCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER MISC POWER AMPLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

Q
331A-bA
J1
blYE-2G
J1
3298-71
J1 J2
394C-lD
J1 32
5b2A-5G
J l A J1B
Q J1
5b2C-4
J1
AILERON
334c-3
121A-2
J1
(TP) (BP) (TP)(BP)

-;-S.4:;;7
(TP) (BP) (J1)

b
7
.
:
5% PITCH ATTITUDE ERROR H '
S b PITCH ATTITUDE ERROR C '
-
- 24
23 :
: :
:
:
:
b; F I E L D NUMBER 1
B
A
-
8
9
10
:
:
-
P I T C H ATTITUDE SERVO DRIVE M2
P I T C H ATTITUDE SERVO DRIVE C
: S V - PITCH ATTITUDE RATE G2
28
27
25
:
:
:
:
:
:
:
:
: VERT
13
: 5
:
1 1-
51-
AILERON
AILERON
F I E L D NUMBER 2
SIGNAL C
C

1LI : AILERON EXCITATION C F

11 : S b P I T C H ATTITUDE RATE C2 2b : : : REF 15 : AILERON P O S I T I O N EXCITATION H G
:

-
1 : S V - MANUAL P I T C H COMMAND H ' 3b : 332D-11 1b : 51- AILERON RATE EXCITATION H H

-
2 -b MANUAL P I T C H COMMAND C ' : 26 : (J1) 12 : 51- AILERON P O S I T I O N SIGNAL L
92 : V-BAR P I T C H COMMAND SERVO DRIVE M 1 11 : : 11 X-1- AILERON SERVO GRD R
113
LIY
: V-BAR P I T C H COMMAND SERVO D P I V E C
: 5 7 - V-BAR P I T C H COMMAND RATE
10 : : I 17 : 51- AILERON RATE SIGNAL S

95
LID
e&- V-BAR P I T C H COMMAND S I G COM
: 5V- V-BAR P I T C H POS XMTR X
j ; ; j ;I
Y l
3 :
: 5 6 V-BAR P I T C H POS XMTR Y
P I T C H A T T I N D E CT X
i :
, ' j ;
30-A
;I (J2)
AILERON ENGAGE VOLTAGE E
9 : PITCH ATTITUDE CT Y : 20-0 AILERON ENGAGE VOLTAGE
5 : P I T C H ATTITUDE CT 2 : : : c
17 : BANK ATTITUDE CT X : : 30-D
18 : BANK ATTITUDE CT Y : : 20-E
19 : BANK ATTITUDE CT Z . - F EL EVATOR

-;:;;
: S V - BANK ATTITUDE ERROR H'
20
21 : 5 6 BANK ATTITUDE ERROR C ' j ; i ;I 33LIc-3
(J1)
22
23
:
:
BANK ATTITUDE SERVO DRIVE M2
BANK ATTITUDE SERVO DRIVE C
: S V - BANK ATTITUDE RATE G2
- :
i :; :; ;I : Q
t-ELEVATOR F I E L D N M E R
+28 VDC
1 A
8

-.
29 19

El
+ELEVATOR F I E L D NUmER 2 C
25 : 5 6 BANK ATTITUDE RATE C2 20 : : : -+ ELEVATOR SIGNAL C E
3b
37
:
:
V-BAR ROLL COMMAND SERVO DRVIE MZ
V-BAR ROLL COMMAND SERVO DRIVE C --+- 27
28
:
. .. ..
:
:
: a
J 15 -
-+
ELEVATOR
ELEVATOR
EXCITATION C
P O S I T I O N EXCITATION H G

38 : 5 7 - V-BAR ROLL COMMAND RATE G2 i: 25 : : f 3 E i Z : T

lb
12 --S
ELEVATOR
t ELEVATOR
RATE EXCITATION H
P O S I T I O N SIGNAL
H

39
3Y
:
:
S b V-BAR ROLL COMMAND S I C COM
5 7 - V-BAR ROLL POS XMTR H 1 :
2b
2 4
:
: :
: H -GRD 11 -+ ELEVATOR SERVO GRD P
17 -2- ELEVATOR RATE SIGNAL S
35 : S b V-BAR ROLL POS XMTR C 1 : 23 : : G y .
115 VAC A T T I N D E POWER
GYRO MON + 29
5 :
:
:
: 1 0 - N
:
Q
: GYRO HIGH LEVEL FLAG +
31
:
:
18
4
-
- GYRO HIGH LEVEL FLAG
STEER FLAG-
-
31
32
:
:
.
2
:
.
:
:
:
:
NAV RCVR
51PV-1
ELEVATOR ENGAGE VCLTAGE
(J2)
J
ELEVATOR ENGAGE VOLTAGE H
STEER FLAG+ 2 : : 28 (TP)

: - . . .. __:
l i

#e--
?b +18 VDC FLAG POWER : :51(
33 : : 10 - GLIDE SLOPE DEV + UP : 32-8 Q RUDDER
34 : : 11-GLIDE SLOPE DEV + DN : 22-9 334c-3
: : SLOPE LOW LEVEL FLAG + . :

-
35 12-GLIDE 21
3b : : 1 3 -GLIDE SLOPE LOW LEVEL FLAG - : : : 22 F I E L D NUMBER 1
(J1)
A
9
GLIDE SLOPE HIGH LEVEL FLAG + : 11 27

: : - VORlLOC DEV + LEFT

Y 1 . *RUDDER F I E L D NUMBER 2 C
29
28 : :
:
b
5 -
-
VORlLOC DEV + RIGHT
+
22 - 39
- 50
93
YY
:
I
5 3 - RUDDER
RUDDER
SIGNAL C
EXCITATION C
E

..- 38
9 VORlLOC HIGH LEVEL FLAG 11 95 : RUDDER P O S I T I O N EXCITATION H G

I : : 57-
LOC FREQ VOLTAGE +
COURSE RESOLVER A ... ..
.
Y3 Yb
Y2
:
:
5
5
*
f RUDDER
RUDDER
RATE EXCITATION H
P O S I T I O N SIGNAL
H
L
2 : : 5 6 COURSE RESOLVER B : : : 22 lil - X f RUDDER SERVO GRD R
8 : : 57- COURSE RESOLVER H : : : 21 117 I 5- RUDDER RATE SIGNAL S
3 : : 5 6 COURSE RESOLVER C : : : 23 (J2)
Y : : SV- COURSE RESOLVER D : : : B Y RUDDER ENGAGE VOLlAGE B
5 : : S b COURSE RESOLVER E : : : 25 RUDDER ENGAGE VOLTAGE . C
b : : 57- COURSE RESOLVER F : : : a b
7 : : 5 6 COURSE RESOLVER G : : : 27
31 : VOR/LOC FLAG + : : : Yl
32 : VORlLOC FLAG - : : : 42
TRIM TAB
SERVO
2b : TO-FROM ARROW ( c TO) : : : Y3 339D-2-380
27 : TO-FROM ARROW ( + FROM) : : : YY (J1)
: : : R A D
: : : ALT
: : : (BP)
i @ .
1; 4 7 - RADIO ALTITUDE FLAG
53 a b RADIO ALTITUDE FLAG
+
-
:
:
:
:
:
:
1
1
2
1
50 : S V - AUX DC ALTITUDE + . : 47
51 : 5 6 AUX DC ALTITUDE - :
.. :
.. :
TRIM
...
Yb INDICATOR
.. .. .. 8 ; .I X L C GRD B 3270-1W
. . T28
RIM
VDC
TAB
POWER
MOT A
. . . L
..
.

..
I .

... TRIM ENGAGE GRD M

.. .. ..
. .
... ... ... : 39 ---5CT R I M TAB MOT CONT c v - E
.. . ... : 33 -C TRIM TAB MOT CONT F-+
... .._ . 33 .
.
AILERON TRIM INDICATOR
Q i
. . 3Y
:
AILERON T R I M INDICATOR + A
. . . 53 RUDDER T R I M INDICATOR

.
+ R
52 : RUDDER T R I M INDICATOR TPI-3121-044:

AP-103F/FD-108 Fairchild F-27, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 446

Nov 1/68 22-03-00

Pages 401/31, 401/32
 COLLINS
MAINTENANCE
WW
IMPORTANT: READ A L L NOTES CAREFULLY. NLMBERS I N APPLY TO A S P E C I F I C NOTE.
FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT F L I G H T AUTOPILOT TRIM EMERGENCY
CIAT09S INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTE4 MISC POWER AMPLIFIER WIRE FUNCTION SERVOS INDICATOR DISCONNECT J-BOX

331A-bA blliE-2G 3290-7A 349C-1D SbZA-SG 328A-2A 6?) Sb2C-li AILERON 327D-1W 121A-2
Q J l J2 J1 J1 J2 33%-3
(J1)

.
:
:
COMPASS MON
COMPASS ,MON +
COMPASS DATA X
- :
:
30
29
..
-
. .
- : :
111
17
25
: 2 :
. .. .
:l c l;
: COMPASS DATA Y
.." ... .. : 3 :

: COMPASS DATA Z
.. .. . : * :
-
.
:
:
.
:
:
:
:
:
1 1
-4
-3
:
:
:
119
50 -
5 1 -COMPASS
CoMPASS DATA X
COMPASS DATA Y
D9TA Z
: COMPASS FLAG +
COMPASS FLAG - :
:
31
3 2
:
: :
: 27 - GRD

: 2b VAC HDG PI!R : 15 : : 22- 5 :

: CMrYlON : l b : : 30- 1 :
: SFL HEADING ERROR SYNCHRO C ' : 1 7 . :
: S b HEADING ERROR SYNCHRO H ' : 1 8 : :
: ST- HEADING RATE G2 : 1 9 : :
: l* : 5 6 HEADING RATE C 2 : 2 0 : :
: it' : HDG MOT CONT U . a : :
: 1: : HDG MOT CONT M 1 . 22 : : AIRSPEED
: ' i . HEADING DATUM SYNCHRO C ' : : 2 3 : SENSOR
: 5 HEADING DATUM SYNCHRO H ' : : 33 DME 5908-2
12 : : COURSE DATUM SYNCHRO C ' : : Zli 8bDE-2 (J1)
13 :
:
:
:
COURSE DATUM SYNCHRO H '
DISTANCE INDICATOR FLAG +
: : 34 (J1) 59 : AIRSPEED SIGNAL -
'15 : : : 9 58 : AIRSPEED EXCITATIOli H
Yb : : DISTANCE INDICATOR FLAG - : : : l o bo : AIRSPEED EXCITATIOfl C
'i? : DS
I TANCE INDICATOR 2b VAC H . . . 2
'18 -. : DISTANCE INDICATOR 2b VAC C .. .. ..
*9 --T : . . .
50 : : DISTANCE INDICATOR UNITS SYNCHRO X : . . .
51 : : DISTANCE INDICATOR UNITS SYNCHRO Y : . . .
52 : : DISTANCE INDICATOR TENS SYNCHRO X : . . .
53 : : DISTANCE INDICATOR TENS SYNCHRO Y : . . .
5'1 : DISTANCE INDICATOR HUNDREDS SYNCHRO X : : :
:
.: .: .:
55 : DISTANCE INDICATOR HUNDREDS SYNCHRO Y
.. .. ...
.. .. .
'18 : 2 b VAC COMMAND PWR 12 : : :

:
32
33
:
:
:
-
SP- 2b VAC ATTITUDE R I R
5 6 26 VAC ATTITUDE PWR COM
5 VAC LIGHTING PWR
- 15
lb
.
:
.
.
:
.
.
.
:
2'1
25 :
19
20 - 5 VAC LIGHTING PWR COM . . : <a) :

9
e
:
:
:
:
:
DC GRD
115 VAC
1 1 5 VAC
1 2 8 VDC
1 2 8 VDC
HEADING PVR
ATTITUDE Pi!R
POI!ER
SERVO CLUTCH POVER a:
.
4 :
5-55

:
... ..-
.. ..
5li - 5b

...
..
i:

I
9 :

.. ..
.. ..
..
.
: GRD :

Q.
: b l - GRD
28 VDC POWER
RUDDER SERVO POWER :
w
T
- N
P
S
..
3

.. . . : @ b3 : S G - RUDDER SERVO R)WER T

... ... @: : : & : U
..
. .. .. : D :
: @ 6; : 2- G- AILEPON SERVO POWER
AILERON SERVO POWER
ELEVATOR SERVO POVEP : & : v
W
. . ."
PITCH STEERING i UP : 3-31 : GRD - IQ 1
b; - 5 r -
:
ELEVATOR SERVO PO~*ISR w : Y

-
P I T C H STEERING i D N : li-21 :
ROLL STEERING + LEFT : 12 I 3 1 :
ROLL STEERING + RIGHT 13 21 :
.
I

L GYRO MODE i 17 'I1 40 : 7 I nr, A" I

K : HEADING MODE + : : Y ? : bli : I

J NAV/LOC MODE i : : L i b : : Y? I
: 9li-Y4 - : GO AROUND MODE +
I
: 1 4 d :
I

AP-103F/FD-108 Fairchild F-27,

M a r 1/73 Interconnecting Wiring Diagram 22 -03 -00
Figure 446 (Sheet 2) Pages 401/33, 401/34
 MAINTENANCE
COLLINS
ww MANUAL

IMPORTANT: READ ALL NOTES CAREFULLY. NUMBERS I N 0 APPLY TO A SPECIFIC NOTE.

FLIGHT
ANNIN- COURSE PEDESTAL DIRECTOR EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

331A-bA blYE-2G 3293-?A 31111C-1D 5b2A-IG 590A-3A 5b2C-4 AILERON 121A-2

J1 J2 J1 J1 J2 J1 J? JLA J1B (J1) @ J1 JL 33K-3 Jl
(TP) (BP) (TP)(BP) (TP) (BP) (Jl)

12 : PITCH BOOTSTPAP TRANSMITTER X . . : 39 : 113 -hLTITUDE GAIN CHANGE EXCITATION

. .
13
14
:
:
PITCH BOOTSTRAP TRANSMITTE? Y
PITCH BOOTSTRAP TPANSMITTER Z .
... .
.
:
:
112
113
-
:
: Li5 -
1111 -ALTITUDE GAIN CHANGE NO. 1
ALTITUDE GAIN CHANGE NO. 2
15
l b
:
:
PITCH BOOTSTRAP EXCITATION H
PITCP BOOTSTRAP EXCITATION C . .. ... 3b
35-8
2b : BANK BOOTSTRAP TRANSMITTER X : : : 37- GRD
2)
28
:
:
SANK BOOTSTRAP TRANSMITTER Y
BANK BOOTSTRAP TRANSMITTER Z
: 15 : :
:
59 -EXT
1 8 +Si
COMPUTER MON +
PITCH STEERING A
29 : BANK BOOTSTRAP EXCITATION H : 19 -e EXT PITCH STEERING B
30 : BANK BOOTSTRAP EXCITATION C : 25 +FL AC PITCH STEERING A
fib : HEADING WARNING DATA X : 2b +e AC PITCH STEERING B
: HEADING WARNING DATA Y : 2 7 -5- PROCESSED PITCH DATA A
:
:
:
HEADING WARNING DATA 2
HEADING WARNING DATA H
HEADING YARNING DATA C
:
:
:
28 -6
57
bo
-
-
PROCESSED PITCH DATA 0
INTERNAL PITCH STEERING OFF
ALT HOLD OFF +
i

: HEADING WARNING DATA H ' 18 : S F L ROLL STEERING A

HEADING IbIARNING DATA C' 19 : 5 6 ROLL STEERING S
25 : S F L PROCESSED BANK CMD A
2b : 5 6 PROCESSED BANK CMD B
35 : S F PROCESSED BANK DATA I
.. .. 3b : S b PROCESSED WNK 2ATA E
55 : S F EXT BANK CMD 0
54 : 5 6 EXT BANK CMD A
: PITCH MONITOR + : 1 2 -i2 : 1 .

GS ARV : GLIDE SLOPE ARM. ANN. - : b :

GS EX7 GLIDE SLOPE EXT. ANN. - . 112 :
N / L ARP : NAVILOC A W . ANN. - : : b :
h 1 L CAPT : NAVILOC CAPTURE ANN. - : : 3 9 :
PW?
G S CAP7 . :
:
38 - ANNUNCIATOR P W E R
-
QUNI,IAY FLAG 1
. ;
.
.
;
..
. : : MKQ BCN
: : : RCVR
(.r GO AROUND ANN. - : Ib : 512-4
: : : (J1)
MIDDLE MARKER : 113-+
: : 1 8 : 57 : INTERNAL ROLL STEERICG OFF i
i PITCH CONTROL EXC A . . ^ : 21 NAV NAV : 51RV-1
: B : PITCH CONTROL SIGNAL . . . : 20 RCVR CONT : SELF-TEST
C PITCH CONTROL EXC B . . . : 22 51RV-1 313N-3 : RELAY
D . . . (J2) (J2) :
E TURN CONTROL EXC A . . . 21 :
1 : TURN CONTROL EXC B . ^ . 22 :
G TURN CONTROL SIGNAL . . _ 20 :
N I N T MOTOR CONTROL VOLTAGE : b2
P : I N T 2b VAC MOTOR EXCITATION C 24 :
h : I H T NOTOR PATE SIGNAL : b3
S : I N T MOTOR SIGNAL COMMON . . . : 211
T : 2 8 VDC PANEL LIGHT P W . . .
U : GQD .. .. .. GRD
X . _ .
:
.. .. ..
:l
ENGAGE VOLTAGE
2
.
_ . . T
a ENGAGE PULSE . . . : 5b
-
b : DISENGAGE VOLTAGE . " . : 37
ENGAGE READY . , : 55
- . : ALTITUDE HOLD MODE i
... .
..
.
..
: 38
.. .. ..
f
P
q
:
:
:
HEADING SYNCH CUTOUT
-m
11s VAC AUTO P I L O T PIdR
1 1 5 VAC POL!ER . . .
1 .
7 :
I "
38 :

r : . . .
I N T 2b VAC MOTOR EXCITATION H 23 :
-
5 : ENGAGE INTERLOCK .. .. ."
3
. " . @
54

u : AILE?ON CLUTCH VOLTAGE . , 39 .

V : ELEVATOR CLUTCH VOLTAGE . . . : 39
W : RUDDER CLUTCH VOLTAGE . . - 5b :
E4 : t28 VDC AUTO PILOT PWR m .. .. .
X . . .
-Y SPARE
.. ." .I
. . .
I . .

AA 3345A-110 @ :
80 . .. ._
.. .. ..
(ROLL) : YAW DAMP SW - VI
Y

cc b5 : ROLL RATE MOTOR GRD A

DD GYRO llODE .. .. .. 8
. : . I . 115 VAC POWER B
EE HEADING MODE .. .. . 32 : ROLL RATE EXCITATION C E
FF : NAVILOC WODE 31 : ROLL RATE EXCITATION H F
GG APPROACH MODE . . . 29 . ROLL RATE SIGNAL X G
HH : VlODE VOLTAGE H .. . . . ..
. . . : TPI-3121-044

AP-103F/FD-108 Fairchild F-27,

M a r 1/73 Interconnecting Wiring Diagram 22 -03 -00
Figure 446 (Sheet 3) Pages 401/35, 401/36
 a
COLLINS
MAINTEKANCE
Qw MANUAL

IMPORTANT: READ ALL NOTES CAREFULLY. YUMBERS I N 0 APPLY TO A SPECIFIC NOTE.

FLIGPT AUTOPILOT SENSING EMERGENCY

ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AMPLIFIER WIRE FUNCTION SERVOS UNIT DISCONNECT J-BOX
C I A I YRS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER CONVPUTER VISC PO'JPR
%IC-4 AILERON 33'iSA-110 121A-2
331A-bA bl'lE-2G 329e--n PLIYC-lD 5b2A-5G 15 JI J1 334c-3 J1
9 J1 J2 J1 J1 J1 J2 J1A J I B (TP)

pi -
(BP) (J11
(TP) (BP) (TP)(BPl
." .. .. - (PITCH)
:
: 22 --
-
PITW
DIFFERENTIAL RESMMR X
PITCH
DIFFERENTlAL RESOLVER Y ...
..
.
._
.
..
8
10 -
- 115 VAC POWER -
PITCH RATE MOTOR GRD A
B
- .I ..
j 1 2 3 DIFFERENTIAL RESOLVER 7.
PITCli
24
-
PITCH
DIFFERENTIAL RESOLVER H 1

.. .

. .

.
32
31 -
-
PITCH RATE EXCITATION C
PITCH R T E EXCIT4TION H F

.
25 PITCH
DIFFERENTIAL RESOLVER C
. .. .. 29 PITCH RATE SIGNA. X G
:
26 -PITCH
27 -PITCH
DIFFERENTIAL RESOLVER H '
DIFFERENTIAL RESOLVEP C' ." .. ..
. . . YAW RATE
-
L9 -
11 28 -BANK DIFFERENTIAL RESOLVER x
BANK PIFFERENTIAL RESOLVER Y ..
. ..
...
..
...
._.
CVR"
3326-2
30-
3 1 -BANK
BANK DIFFERENTIAL RESOLVER 2
DIFFERENTIAL RESOLVER H .. bb . YAW RATE WTOP GIID A

... . . 10 : 115 VAC POWER B

.. ..
32 -BANK DIFFERENTIAL RESOLVER C 51 : YAW RATE EXC1TAT:ON C E

3Y. -
33 -BANK DIFFERENTIAL RESOLVE9 H'
BANK DIFFERENTIAL RESOLVER C ' -.. ..".
~.
..
. 50
98
:
.
YAW RATE EXCITAT'ON H
YAW RATE SIGNAL ::
F
G
.. . .
I . .
.. --

SYYBOLS USED:
ID. THE 5b2C-11 AND 5bZA-5G SHOULD BE MOUNTED AS CLOSE TOGETHER AS POSSIBLE.
PREFERABLY ON A DUAL MOUNT. THESE SIGNAL LEADS MUST BE TWISTED AND WIRED
SV i V I S i E D SHIELDED PAIR-ADJACEN?
POINT TO POINT BETWEEN THE UNITS. THE TWISTED PAIRS SHOULD BE KEPT AS
SI WIRES AS SHOWN Q4 DRAWING
SHORT AS PRACTICAL AND MUST ALSO BE SHIELDED I F OVER TU0 FEET LONG.
SG SHIELD T I E D TO GROUND AT U N I T
11. COMPARATOR WARNING RESOLVERS. DO NOT USE FOR OTHER PURPOSES UNLESS LOADING
SI SINGLE SHIELDED WIRE
EFFECT IS EVALUATED.
XI ALL 5 1 SHIELDED T I E D TO X I ETC. ST4 FOUR WIRES 'P'ISTED WITH SHIELD
NOTES
12. BUSS TO 121A-2
TOTAL WIRE RUN FROM ~~. ..~ TO
. 562C-q
~ ~~ TO 3P1C-3
. ._
. . 0 ) .FOR F A r U
.. LPTN -. -
W PRIMARY-SERVO MUST NOT EXCEED 90 FEET I F AWG 20 WIRE I S USED. WHEN GREATER
THAN 9D FEET, INSTALL TERMINALS AT 5b2C-V MOUNT AND RUN AWG 20 WIRE FRDM
5b2C-4 TO TERMINAL AND AWG 1 6 WIRE FROM TERMINAL 344C-3 P I N 8.
NOTES:
13- AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.
14. A 1 2 K OHMS 112 WATT 107; RESISTOR IS REQUIRED ON EACH TRIM INDICATOR MOVEMENT.
1. ALL WIRE S I Z E S ARE NO. 22 UNLESS DESIGNATED OTHERYISE BY NUMBERS I N SQUARES.
WITH TRIM INDICATOR CONNECTIOVS AS SHOWN AND THE REVERSING LINKS INSTALLED
2. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD B E
FOR CORRECT SERVO PHASING THE PRIMARY SERVO CAPSTAN SHOULD TURN CLOCKWISE
GROUNDED AT THE 51RV-1.
WHEN VIEWED FROM THE CAPSTAN i N D UNDER THE FOLLOWING AIRCRAFT ATTITUDES:
3. PROVISION FOR INSTALLATION OF RADIO ALTIMETER.
9. A RELAY MUST BE INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF
AILERON - RIGHT &INK
TEST FEATURE OF THE 51RV-1 WHEN THE AUTOPILOT I S ENGAGED.
-
5. THE AUTOMATIC
LOADS AS FOLLOWS:
FLIGHT CONTROL SYSTEM AS CONNECTED IN mrs DRA'IING REFLECTS ELEVATOR
RUDDER - PITCH U?
RIGHT YAW

15. POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE
AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS
THAN ONE EQUIPMENT. THIS WILI. BE NIDCIATED IN THE INTERCONNECT-POWER COLUMN
BY A LETTER WITH AN OCTAGON SfMBOL AROUND I T , CAPITAL LETTERS FOR DC AND LOWER
200 OHMS TO-FRM 100 OHWS JUMPER BP-113 TO BP-33 OF 51RV-1
CASE LETTERS FOR AC.
500 OHMS GLIDE SLOPE POINTER 200 OHNS JUMPER TP-8 TO TP-2 AND TP-3 OF 51RV-1
SOD
500
OHMS
OHMS
GLIDE SLOPE FLAG
LOC FLAG
250 OHkS
250 OHVS
JUMPER
JUMPER
TP-21 TO TP-2b OF 5 l R V - 1
BP-32 TO BP-41 OF 51RV-I
A- 28 VDC DIMMING CIRCUI;
B e CI D e E- VDC 5 - M P
a - -
5 VDC DIMMING
b , C, C
CIRCUIT
115 VAC 2 M I ?
500 OHMS COURSE BAR , 200 OHh'S JUMPER BP-39 TO BP-30 AND BP-118 OF 51RV-1
G- 28 VDC 1 AMP e - g - 115 VAC 1 AMP
b. M E POWER FOR THE CMnPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE f - 115 VAC 3 LMP
AUTOMATIC F L I G H T CONTROL SYSTEM.
?. lb. THE GO AROUND RELAY I S INSTALLED FOR WINGS LEVEL, PITCH UP GO AROUND.
POWER LEADS DENOTED BY "DIM" SHOULD EE T I E D TO COCKPIT LIGHT DIMMING CIRCUITS.
GO AROUND BUTTON I S NORMALLY OPEN AND NORMALLY I S INSTALLED ON CONTROL
8. SENSING U N I T 345A-Y( ) AND RATE GYRO 3320-2 SHOULD BE LOCATED AS CLOSE TOGETHER
COLUMN WHEEL. TO DEACTIVATE ( 0 AROUND PROVISION REMOVE THE RELAY AND
AS POSSIBLE.
CONNECT THOSE WIRES TOGETHER :HAT ARE CONNECTED BY THE NORMALLY CLOSED
5. ANNUNCIATORS CHOSEN MUST NOT EXCEED 1 0 0 MA. A COWON +28 VDC I S USED FOR
CONTACTS OF THE RELAY.
ANNUNCIATOR POWER.
17. EQUIPMENT SHOWN I N MISC COLUMtS MAY NOT HAVE COMPLETE WIRING INFORMATION
INDICATED. BEFORE WIRING APPLICABLE SYSTEM MANUALS FOR THAT EQUIPMENT
SHOULD B E CHECKED.
18. CONNECTIONS TO TRIM TAB MOTOR CONTROL DEPENDS ON AIRCRAFT RIGGING.
19. WHEN OPTIONIL 5 9 0 4 - 3 4 SERVICE BULLETIN NO. 3 I S INCORPORATE0,THE FOLLOWING INTERCONNECTING WIRING CH4NGES ARE 4PPLICABLE:
REMOVE CONNECTION BETWEEN JIIBPI-38 OF THE562C-4 AUTOPILOT 4MPLlFlER A N D Jl-0 OF THE 6141-20 PEDEST4L CONTROLLER.
REMOVE CONNECTION BETWEEN JI-V OF THE 614E-2G PEDESlALCONTROLLER4ND JIAITPI-47 OF THE 5624-5G FLIGHT COMPUTER.
M4KE CONNECTIONS A S SHOWN BELOW.
PEDESTlL
CONTROLLER WiREFUNCTiON CF~AGGER %LY#~LER%X~KBTR
614E-2G
JI 562A-56 5904-31 562C-4
JI1 JIB lJI1 JI JI
(TP) (BPI (TPI (BPI
V ______ ALTITUDE HOLD MODE+ _______
4LTlTUDE HOLDHODEW? 'PO__________38 TPI-3121-044

AP-103F/FD-108 Fairchild F-27,

M a r 1/73 I n k r connec t ing Wiring Diagram 22 -03-0 0
Figure 446 (Sheet 4) Pages 401/37, 401/38
 a
COLLINS
JI.AISTES.4SCE
MAXUAL

COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT AUTOPILOT EMERGENCY

SERVOS
ANNUNCIATORS IND CONTROLLER DIRECTOR IND WIRE FUNCTION AWPLIFIER COMPUTER MISC POWER AMPLIFIER WIRE FUNCTION AILERON MISC DISCONNECT J-BOX
3 3 1 A-6A 614E-2G 329B-7A 344C-1 D 562A-5G 562C-4 334c-3 121A-2
J1 J2 J1 JI
I
J2
I
-J1 J2 JlA JIB
Q J1 JI (Jl) J1

I 7
PITCH ATTITUDE ERROR H'
PITCH ATTITUDE ERROR C'
4TP) (BPI (TP) (BP) (TP) (BP)
AILERON FIELD NUMBER 1 A

I 8
9
'
1
" PITCH ATTITUDE SERVO DRIVE M2-
PITCH ATTITUDE SERVO DRIVE C -27
28
2 8 VDC
AILERON FIELD NUMBER 2
AILERON SIGNAL C
B
C
E
I 11
PITCH ATTITUDE RATE G2
PITCH ATTITUDE RATE C2 26
VERT
REF
AILERON EXC C
AILERON POSITION EXC H
F
G

I 2 v
MANUAL PITCH CMD H '
MANUAL PITCH CMD C'
I
I
I
36
26
332D- 1 1
(J1)
16
12
I
AILERON RATE EXC H
AILERON POSITION SIGNAL
H
L
V-BAR PITCH CMD SERVO DRIVE M I R
I
42
43 V-BAR PITCH CMD SERVO DRIVE C vx7 17 S
V-BAR PITCH CMD RATE I I
45 V-&iR PITCH CMD SIG COM
1
1
8
9 I p"7 37 I (J2)
I

V-BAR PITCH POS XMTR X AILERON ENGAGE VOLTAGE A E

41 . ,, V-BAR PITCH POS XMTR Y
l
,
I
7
6 1 1 W AILERON ENGAGE VOLTAGE B F
3 l - PITCH ATTITUDE CT X 30
; A
I /

*
I 1
4
5
1
1
I
PITCH ATTITUDE CT Y
PITCH ATTITUDE CT Z
I 1
20

''
B
C I.
I
I I
17
18
19
BANK ATTITUDE CT X
BANK ATTITUDE CT Y
BANK ATTITUDE CT 2
I
I
I
1 I
30-
20-
D
E
F I I ! ELEVATOR
334c-3
(J1)
I 20 BANK ATTITUDE ERROR H'
I 1 ELEVATOR FIELD NUMBER 1 A
I I&%
*
21 BANK ATTITUDE ERROR C' 2 8 VDC B
-2 2
22 BANK ATTITUDE SERVO DRIVE M 2
1 1 3 16 ELEVATOR FIELD NUMBER 2
23
24
I BANK ATTITUDE SERVO DRIVE C
BANK ATTITUDE RATE G2
BANK ATTITUDE RATE C2
21 1 7
19
20
1

I 1 I '3 I ELEVATOR SIGNAL C

ELEVATOR EXC C
ELEVATOR POSITION EXC H
E
C
F
G
25 I w
I
' '
36 V-BAR ROLL CMD SERVO DRIVE M 2 28 a ELEVATORRATEEXC H H
37 I V-BAR ROLL CMD SERVO DRIVE C ' 27 I I J d 16x ELEVATOR POSITION SIGNAL - L
I
39
I V-BAR ROLL CMD RATE G2
V-BAR ROLL CMD SIG COM ' 2
I
25
6
I
1
I
1 K-
H
-tFAST ERECT
ELEVATOR SERVOGND R
S

34* . V-BAR ROLL POS XMTR H I

I 24

-
, I
v V-BAR ROLL POS XMTR C I G (J2)
1 1 5 VAC ATTITUDE POWER 5 ELEVATOR ENGAGE VOLTAGE -A J
-B
31
18
GYRO MON +
GYRO HIGH LEVEL FLAG +
GYRO HIGH LEVEL FLAG -
329
32
1 I
I I 'p- N

NAV
ELEVATOR ENGAGE VOLTAGE H

I 4
I
STEER FLAG
STEER FLAG
-
2 26
R CVR
51RV-I RUDDER

I 16
I
+ 2 8 VDC FLAG POWER
I
54
I
(TP)
I
334c-3
(Jl)
33 IO GLIDESLOPE DEV + UP 32 8
Q RUDDER FIELD NUMBER 1 A
34
35
11
12
GLIDESLOPE
GLIDESLOPE
DEV + DN
LOW L E V E L F L A G +
22 9
21
Q 4
2 8 VDC
RUDDER FIELD NUMBER 2
B
C
36 13 GLIDESLOPE LOW LEVEL FLAG - I 1 22 RUDDER SIGNAL C E
HIGH LEVEL FLAG +
I GLIDESLOPE 11 I
I -
27
(BP) 45
RUDDER E X C C
RUDDER POSITION EXC H
F
G
29
28
6
5
VOR/LOCDEV+LEFT
VOR/LOC DEV + RIGHT
+
32
22 -
-
40
39
46
42 yr
RUDDER RATE EXC H
RUDDER POSITION SIGNAL
H
L

8
I 9

r \ +
VOR/LOC HIGH LEVEL FLAG
p LOC FREQVOLTAGE +
COURSERESOLVER H
11
43 -
50
38
21
41
47
RUDDER SERVO GND
V RUDDER RATE SIGNAL
R
S
1 1
2 I 1

Q 4
I
n
I 1
1
+
COURSERESOLVER C
COURSERESOLVER D
23
24 RUDDER ENGAGE VOLTAGE
(J2)
A B
5
6
I 1
U
c\
I
I 1
t
' COURSE RESOLVER E
COURSERESOLVERF
25
26
RUDDER ENGAGE VOLTAGE B C

7 W COURSERESOLVERG 27
31 VOR/LOC FLAG + 41
32 VOR/LOC FLAG - 42
26 TO-FROM ARROW (+TO) 43
27 TO-FROM ARROW (+FROM) 44 TPl-9622-055

AP-l03F/FD- 108 Falcon (3-Axis) Interconnecting Wiring Diagram

Aug 1/69 (Sheet 1 of 5 ) 22-03-00
Figure 447 Pages 40 1/3 9, 40 1/40
 a
COLLINS
MAINTENASCE
RIANUAL

ANNUNCIATORS COURSE POWER

PEDESTAL FLIGHT INSTRUMENT FLIGHT AUTOPILOT TRIM T A B TRIM EMERGENCY
@ IND
3 3 1 A-6A
CONTROLLER
61 4E-2G
DIRECTOR IN0
3 2 9 8 - 7A
WIRE FUNCTION AMPLIFIER
344C-1 D
COMPUTER
562A-5G
COMPASS
328A-2A @
@
I AMPLIFIER WIRE FUNCTION SERVO IN0 DISCONNECT J-BOX
562'2-4 334D-2-33D 327D-1W 121A-2
J1 J2 J1 J1 J2
J1 J2 J1A J1B (Jl) (J2) J1 J1 (J1) J1
I I I 1 I
I I
I
(TP) (BPI (TP) (BPI (TP) (BP)
I COMPASS MON -
' 30
' 17
I
9-1
I
10-2
I
17
-
I
I
I
I
1
1
COMPASS MON t
COMPASS DATA X I
29
I 1
1;-25
1 2
I
2 8 VOC PWR
TRIM TAB MOT
B
A
1
I L
II
COMPASS DATA Y - 3 TRIM ENGAGE GNO E I M
I I
18 2
- I 1 1 I 1 I l l ' I I 34 A TRIM TAB MOT CONT c--
I

=
11-3 COMPASS D A T A Z 4
1 33 TRIM TAB MOT CONT F t E
I l9 I I I 33 AILERON TRIM IND t
30
I I I COMPASS FLAG t " 31 I
1I
l l I
I
I 34 II AILERON TRIM IND - A@
I :5" I I I COMPASS FLAG
26 VAC HDG PWR
- I
I
32
15 I' 22-
1 53 I RUDDER TRIM IND
t
R

I
16 - I 1 1
COMMON I 16 30-
5
1
52 RUDDER TRIM IND
I
20
I I
I
I n + P
114 HEADING ERROR SYNCHRO C'
'
I 17 1 1 I I 1
I
21
I I
x + HEADING ERROR SYNCHRO H' 18 I I 11-
' 49 - COMPASS DATA X I
'
I I
13
I I
HEADING RATE G2 I 19 4 50 -COMPASS DATA Y
I
' '' I
I 1 5i- I
14 COMPASS DATA Z
1 I I "I HEADINGRATE C2 20 I 1 3
12
I I 1 HEADING MOT CONT C1 21 I 27
11
I I I HEADING MOT CONT M I
HEADING DATUM SYNCHRO C'
II 2 2 / I I
GND
I
1 ;
23
I
I
I
I
I
1 HEADING DATUM SYNCHRO H' I I
I 33 DME I I 1 AIRSPEED
SENSOR
12
13
45
I
I
I
I
I
I
COURSEDATUMSYNCHRO C'
COURSE DATUM SYNCHRO H'
DISTANCE IN0 FLAG t
I
I
I
I I 24
34
860E-2
(J1) I I I 590B-2
J1
I
46
47 I
I I
I
I
I
DISTANCE IN0 FLAG
DISTANCE IND 26 VAC H
-
I
I
I
I
I
I
'
I
I
IO
9
I 59
58 I
AIRSPEED SIGNAL
AIRSPEED EXC H I
48
I I I
DISTANCE IND 26 VAC C I I
'
' I
1 2
I 60 I AIRSPEED EXC C
I
49 J I 1 1 I I I
I I
I
1
I I I i- I
I
50
I I I
DISTANCE IND UNITS SYNCHRO X 4 I
51 I I I I
52
I
I
I
I
I
I
DISTANCE IND UNITS SYNCHRO Y
DISTANCE IND TENS SYNCHRO X I
I
I
I
"
I
6
I
3
I I
53
54
55
I
I
I
I
I
I
DISTANCE IND TENS SYNCHRO Y
DISTANCE IND HUNDREDS SYNCHRO X I I 1 1 ; I I I
I I 4% I
DISTANCE IND HUNDREDS SYNCHRO Y
26 VAC CMD PWR
I t ' I 8
I I t ,
32 26 VAC ATTITUDE PWR 1 2 1 1 1
I
24
I 33
5 VAC
26 VACLIGHTING
ATTITUDEPWR
PWR COM :ti I I I I I
I I
W
19
25 I 20 5 VAC LIGHTING PWR COM I 1 I I

I 1 1 I
I
I I I I
9
e
I
t 2 8 V D C S E R V O CLUTCHPWR I
6
n
I
I
i
I GND
' I
G ND N
I
28 VDC PWR
RUDDERSERVOPWR
RUDDER SERVO PWR
AILERON SERVO PWR U
AILERON SERVO PWR V
ELEVATOR SERVO PWR W
PITCH STEERING t UP 3 -3 1 ELEVATOR SERVO PWR X
PITCH STEERING t DN
; 4 - 2 1
I
I ROLL STEERING t LEFT
ROLL STEERING t RIGHT
I
l2
13
31
21 1 1
L GYRO MODE t 13 41 40
K
J
HEADING MODE t
NAV/LOC MODE t
47 64 1
46 47
TPl-9622-055

AP-103F/FD-108 Falcon (3-Axis) Interconnecting Wiring Diagram

l u g 1/69 (Sheet 2 of 5) 22-03-00
Figure 447 Pages 401/41, 401/42
 COLLINS
MAINTENANCE
MANUAL

COURSE PEDESTAL FLIGHT INSTRUMENT FLIGHT ALTITUDE AUTOPILOT EMERGENCY

ANN UN ClATOR S IND CONTROLLER DIRECTOR IND WIRE FUNCTION AMPLIFIER COMPUTER CONTROLLER POWER AMPLIFIER WIRE FUNCTION StRVO DISCONNECT J-BOX
344C-1 D 562A-5G 590A-3A 121A-2
3 3 1 A-6A
J1 J2
6 1 4E-2G
JI
3 2 9 6- 7A
J1 J2 J1 J2 JlA JIB (J1) Q 562C-4
JI J1 J1

I I I I
(TP) (BP) (TP) (BP)
I I (TP) (BP) GO AROUND
I I I I BUTTON

I I I I I
44-44 I * I I I I G O AROUND MODE t
I I
I I I
I
I
H APPROACH MODE t APPROACH MODE t
I I I I
45 1 48 -APPROACH MODE t
EXT STR t DN
EXT STR + U P I I I I
I
I
I I ]
66 -DISCONNECT SWITCH H -I
_ I

I I I 1 67 -DISCONNECT SWITCH C

I I
I I
I l2
l3
I
I I

I 14
15
16
;
I
DITCH BOOTSTRAP TRANSMITTER Z
PITCH BOOTSTRAP EXC H
PITCH BOOTSTRAP EXC C 35 -
I 4/5- ALTITUDE GAIN CHANGE NO. 2

I
I 26
27
I
'
BANKBOOTSTRAPTRANSMITTERX
BANK BOOTSTRAP TRANSMITTER Y
37 -G ND
59 - COMPUTER MON +
28 I BANK BOOTSTRAPTRANSMITTERZ
I
i 18 - EXT PITCH STEERING A
I 29
30 I
BANKBOOTSTRAPEXC H
BANKBOOTSTRAP EXC C
I
I '
, 19-
25
EXT PITCH STEERING B
- AC PITCH STEERING A
I
I I I I I
16 HEADING WARNING DATA X 26- AC PITCH STEERING B
17
I I HEADING WARNING DATA Y
I
27 - PROCESSED PITCH DATA A
I I I l k - PROCESSED PITCH DATA B
18
19 I
I
I
I
HEADING WARNING DATA Z
HEADING WARNING DATA H 18
I
I "
'I
I
I
I
I
28
57 - INTERNAL PITCH STEERING OFF t
20
I I
HEADING WARNING DATA C 48 P I 60 - A L T HOLD OFF t
21
22
I I HEADING WARNING DATA H'
HEADING WARNING DATA C'
1 I
l8
l9
I
I
ROLL STEERING A
ROLL STEERING B
I
I I I I
25
26 ' PROCESSED BANK CMDA

I I @ I
I
35
I
PROCESSED BANK CMD B
PROCESSED B A N K D A T A A

I I I I
I
36
55
'
I
EXT
PROCESSED
BANK CMD
BANKB DATA B

I 54
I
EXT BANK CMD A
I I I PITCH MONITOR t - 1 2 -12 II II I'
GS ARM GLIDESLOPE ARM ANN
I I
GS EXT
N/L ARM
I
I
I
I
GLIDESLOPE EXT ANN
NAV/LOC ARM ANN
6
42 1
6
I I 1
N/L CAP
PWR
I I NAV/LOC CAPTUREANN 39 I I 1
GS CAP
I
38
ANNUNCIATOR PWR
-
RUNWAY FLAG - 5 1 -
G
I I
I
I I 1 MKR BCN I I
GA
I I GO AROUND ANN 16 I
R CVR
512-4
(J1) I I
I MIDDLE MARKER 43
18
4 I
57
I INTERNAL ROLL STEERING OFF t
A PITCH CONTROL E X C A 21
B PITCH CONTROL SIGNAL 20 TPl-9622-055,

AP-103F/FD-108 Falcon (3-Axis)

M a r 1/73 Interconnecting Wiring Diagram 22 -03 -00
Figure 447 (Sheet 3) Pages 401/43, 401/44
 COURSE PEDESTAL
-
a
COLLINS

FLIGHT
MAINTENANCE
MANUAL

INSTRUMENT FLIGHT AUTOPILOT EMERGENCY

ANNUNCIATORS [No CONTROLLER DIRECTOR IND WIRE FUNCTION AMPLIFIER COMPUTER MlSC POWER AMPLIFIER WIRE FUNCTION SERVOS MlSC DISCONNECT J-BOX
33 1 A-6A 614E-2G 329B-7A 344C-1 D 562A-5G 562C-4 121A-2
J1 J2 J1 J1 J2 J1 J2 J1A J1B Q J1 J1 J1
I
I (TP) (BP) (TP) (BP) I UP) (BP)
I
I
C PITCH CONTROL EXC B . 22
D
E
I TURN CONTROL EXC A
I I
21 I NAV
RCVR
NAV
CONT
I
F
G
I
I
TURNCONTROLEXCB
TURN CONTROL SIGNAL
I
I
22
20 I 51RV-1 313N-3 I
(J2) (J2)
I I I
N INT MOTOR CONTROLVOLTAGE 62 19
I I I
P
I
INT 26VACMOTOR E X C C
I 24 1 L
I
rn
e

R INT MOTOR RATE SIGNAL

I I I 63 54 I IJ
S INT MOTOR SIGNAL COMMON n u
I I
T 2 8 VDC PANEL LIGHT PWR 55
I I I
U G NO GNO K
I
u

X
Y
I
ENGAGE VOLTAGE
I -
a
I
I ENGAGE PULSE
I
I
I
I 56 II T U 1
Qf
b
I
I
I
DISENGAGE VOLTAGE
ENGAGE READY
ALTITUDE HOLD MODE +
I
I
I
'
I
I
37
55
38
I +i
51RV-1
f
-P
I
I
HEADING SYNCH CUTOUT
1 1 5 VAC AUTO PILOT PWR 3I8 I 1 SELF TEST
RELAY
9
I
1 1 5 VAC PWR
7 1
r
-5
I

I
INT 26 VAC MOTOR EXC H
ENGAGE INTERLOCK
II 23

I
54 I n

- AILERON CLUTCH VOLTAGE 39 I

zq?j
U
I
-V I
ELEVATOR CLUTCH VOLTAGE 39
W
- I
RUDDER CLUTCH VOLTAGE 56
I
M t 2 8 VDCAUTO PILOT PWR
-
X

-Y
I SPARE
1 53 -YAW DAMPER ENGAGE MON f
SENSING
z
LA
BB
I I ; 345A-48 @
cc
DD
I GYRO MODE
I I
65 ROLLRATEMOTORGND
(ROLL)

I
EE HEADING MODE 8 ' 1 1 5 VAC PWR B
I YAW DAMP SW
FF NAV/LOC MODE 32 I ROLLRATEEXC C E
I
GG APPROACH MODE 31 I ROLL RATE EXC H F
I 29 ROLL RATE SIGNAL X G
HH MODE VOLTAGE H
21 PITCH DIFFERENTIAL RESOLVER X I (PITCH)
22 PITCH DIFFERENTIAL RESOLVER Y 8 -PITCH RATE MOTOR GND A
23 PITCH DIFFERENTIAL RESOLVER 2 10 -1 1 5 V A C P W R B
24 PITCH DIFFERENTIAL RESOLVER H 32 -PITCH RATE EXC C E
25 PITCH DIFFERENTIAL RESOLVER C 31 -PITCH RATE EXC H F
26 PITCH DIFFERENTIAL RESOLVER H' 29 -PITCH RATE SIGNAL X G

Q 27
28
PITCH DIFFERENTIAL RESOLVER C'
BANK DIFFERENTIAL RESOLVER X
I YAW RATE
GYRO
29
30
BANK DIFFERENTlAL RESOLVER Y
BANK DIFFERENTIAL RESOLVER 2
I YAW RATE MOTOR GND
332G-2
A
66 I
31 BANK DIFFERENTlAL RESOLVER H 1 1 5 VAC PWR B
lo I YAW RATE EXC C
32 BANK DIFFERENTIAL RESOLVER C E
51 I
33 BANK DIFFERENTIAL RESOLVER H' 50 YAW RATE EXC H F
34 BANK DIFFERENTIAL RESOLVER C' 48 I YAW RATE SIGNAL X G

TPI -9622 -055

AP-103F/FD-108 Falcon (3-Axis),

Mar 1/73 Interconnecting Wiring Diagram 22 -0 3 -00
Figure 447 (Sheet 4) Pages 401/45, 401/46
 COLLINS
MAINTENANCE

ww MANUAL

NOTES:

Q A L L WIRE SIZES ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY NUMBERS IN SQUARES.

Q SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE GROUNDED AT THE 51RV-1,

Q JUMPER WIRE FROM J1-2 TO JI-3 OF THE COURSE INDICATOR SHOULD BE NO LONGER T H A N SIX INCHES.

A RELAY MUST BE INSTALLED IN THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE
51RV-1 WHEN THE AUTOPILOT IS ENGAGED.

THE AUTOMATlC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWING REFLECTS LOADS AS FOLLOWS:

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS

200 OHMS T 0-FR OM 1 0 0 OHMS JUMPER BP-43 TO BP-33 OF 51RV-1

500 OHMS GUDESLOPE POINTER 200 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 51RV-1
500 OHMS GUDESLOPE FLAG 2 5 0 OHMS JUMPER TP-21 TO TP-26 OF 51RV-1
500 OHMS LOC FLAG 2 5 0 OHMS JUMPER BP-32 TO BP-41 OF 51RV-1
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO BP-30 AND BP-48 OF 5 1 RV-1

8 THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL
SYSTEM.

POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT LIGHT DIMMING CIRCUITS.

SENSING UNIT 3 4 5 A - 4 ( )AND RATE GYRO 3 3 2 6 - 2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE.

ANNUNCIATORS CHOSEN MUST NOT EXCEED 1 0 0 MA. A COMMON +28 VDC IS USED FOR ANNUNCIATOR POWER.

@ THESE LEADS MUST BE TWISTED AND SHIELDED I F OVER TWO FEET LONG.

Q COMPARATOR WARNING RESOLVERS. DO NOT USE FOR OTHER PURPOSES UNLESS LOADING EFFECT IS EVALUATED.

Q TOTAL WIRE RUN FROM BUS TO 1 2 1 A - 2 TO 562C-4 TO 3 4 4 C - 3 (PIN B) FOR EACH PRIMARY SERVO MUST NOT
EXCEED 90 FEET IF AWG 20 WIRE IS USED. WHEN GREATER THAN 90 FEET, INSTALL TERMINALS AT 562C-4
MOUNT AND RUN AWG 20 WIRE FROM 5 6 2 C - 4 TO TERMINAL AND AWG 16 WIRE FROM TERMINAL 3 4 4 C - 3 PIN B.

Q AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.

@ A 12K OHMS 1/2 WATT 10% RESISTOR IS REQUIRED ON EACH TRIM INDICATOR MOVEMENT. WITH THE TRIM IN-
DICATOR CONNECTIONS AS SHOWN AND THE REVERSING LINKS INSTALLED FOR CORRECT SERVO PHASING THE
PRIMARY SERVO CAPSTAN SHOULD TURN CLOCKWISE WHEN VIEWED FROM THE CAPSTAN END UNDER THE FOL- '
LOWING AIRCRAFT ATTITUDES:

AILERON -
LEFT BANK
ELEVATOR PITCH UP-
-
RUDDER RIGHT YAW

Q POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT. THIS WILL
BE INDICATED IN THE INTERCONNECT POWER COLUMN BY A LETTER WITH AN HEXAGON SYMBOL AROUND IT, CAPITAL LETTERS
FOR DC AND LOWER CASE LETTERS FOR AC.

A - 2 8 VDC DIMMING CIRCUIT a - 5 VAC DIMMING CIRCUIT

B,C,D,E - 28 VDC 5 AMP b,c,d - 1 1 5 VAC 2 AMP
F,G - 2 8 V D C 1 AMP e , f - l 1 5 V A C l AMP
g - 1 1 5 VAC 3 AMP

@ THE GO AROUND RELAY IS INSTALLED IN CONJUCTION WITH APPLICABLE F S B FOR WINGS LEVEL, PITCH UP
GO AROUND. GO AROUND BUTTON I S NORMALLY OPEN AND NORMALLY IS INSTALLED ON CONTROL COLUMN
WHEEL. TO DEACTIVATE GO AROUND PROVISION REMOVE THE RELAY AND CONNECT THOSE WIRES TOGETHER
T H A T A R E CONNECTED BYTHENORMALLYCLOSED CONTACTSOFTHERELAY.
Q WHEN OPTIONAL 590A-3A SERVICE BULLETIN N0.3 I S INCORPORATED, THE FOLLOWING INTERCONNECTING
WIRING CHANGES ARE APPLICABLE:
REMOVE CONNECTION BETWEEN JI(BPI-38 OF THE 5 6 2 C - 4 AUTOPILOT AMPLIFIER AND JI-d OF THE 6 1 4 E - 2 G
PEDESTAL CONTROLLER. REMOVE CONNECTION BETWEEN JI-V OF THE 614E-2G PEDESTAL CONTROLLER
AND J I A ( T P k 4 7 OF T H E 5 6 2 A - 5 G FLIGHT COMPUTER. MAKE CONNECTIONS AS SHOWN BELOW.
PEDESTAL FLIGHT ALTITUDE AUTOPILOT
CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMPLIFIER
614E-2G 562ASG 590A-3A 562C-4
JI JIA JIB ( JI) JI JI
(TPI (BP) (TP) (BP)

v - - - - -- - - -- _-ALTITUDEHOLD MODE+ -------- 34

ALTITUDE HOLD MODE4-47 20 _ _ _ _ _ _
-____- ________38
TPI-9622-055

AP-103F/FD-108 Falcon (3-Axis),

Mar 1/73 I n k r c onne ct ing Wiring Diagram 22 -03 -00
Figure 447 (Sheet 5) Pages 401/46A, 401/46B
 COLLINS
MAINTEIVANCE
w MANUAL

FLIGHT
UINW- COLRSE PEDESTAL DIRECTOR INSTRLMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER CWUTER MISC POWER MLIFIER WIRE F W C T I O N SERVOS MISC DISCONNECT J40X

331A-bA blYE-?G 3298-?A AILERON 121A-z

@ J1 J2 J l J l J2 3rrc-3 J1
(J1)

I
1Y
15
b
7
8
b
7-6
8 -
e?-
P I T C H A T T I T W E ERROR H'
P I T C H A T T I T W E ERROR C '
-
-
-
P I T C H ATTITUDE SERVO D R I V E M2
23
2Y

-
28
27
19:
:
:
:
:
:
:
:
:
:@
:
:
b i
. t5
13 -
q
t
- 1
t AILERON
28 W C
t AILERON
FIELD M E R 1

F I E L D NLHBER 2
A
B
C
e

-
23 9 9 __C__ P I T C H ATTITUDE SERVO D R I V E C AILERON SIGNAL C
37 10 10 P I T C H ATTITUDE RATE G2 25 : : : VERT : 1Y AILERON EXCITATION C F
I1 : 5 6 P I T C H ATTITUDE RATE C2 : : : : 15 G

- -
38 22 2b REF AILERON P O S I T I O N EXCITATION H
39 23 I -7- M N U A L PITCH C O M D H ' : 3b : 332D-11 : l b - t AILERON RATE EXCITATION H H
YO 25 2- 6 MANUAL P I T C H CUmANO C ' 2b : (J1) : 12 - t AILERON P O S I T I O N SIGNAL L
Yl 2b Y2 __C_ V 4 A Q P I T C H C W D SERVO D R I V E M- 11 : : 11 -X+ AILERON SERVO a t 0 R
92 27 Y3 V 4 A Q P I T C H C W D SERVO r X l I V E C ID : : i 17 - - r - - - - 5 t AILERON RATE SIGNAL S

-
r3 28 YY : 5?- V d A R P I T C H C O M D RATE
YY 29 '15 -6 V 4 A R P I T C H C o m A w D S I G COM
: M Y O e?-

-
V d A R P I T C H POS XMTR X
: 31 Y1- 6 V 4 A R P I T C H POS XMTR Y (52)
: 32 3 PITCH A T T I T V M CT X : 30-A .. ..- AILERON ENGAGE VOLTAGE E

.. - F
.-
: 33 Y I P I T C H ATTITUDE CT Y : 20-B AILERON ENGAGE VOLTAGE
: T t 5 P I T C H ATTITUDE CT 2 C
: 35 17 BANK A T T I T W E CT X : 30-D : 27 :
: : : :
: 3 6 18 __L_ B A M A T T I T V D E CT Y 20-E
. .
28 ELEVATOR

-
: : : : : 33*G3
:
37
38
19
20 e?-
BANK ATTITUDE CT 2
BAM( A T T I T W E ERROR H ' . . _ F
. . (J1)
: 39 21 ; 5 6 B A N K A T T I T W E ERROR C ' +ELEVATOR F I E L D N U E R 1 A
: YO 22 BANK ATTITUDE SERVO D R I K 8
: Y2

- -
-32 BANK A l l I T U D E SERVO DRIVE C
@+
:
:
93
YY
2Y
25 - 6
BANM ATTITLODE RATE 62
BANK A T T I T W E RATE C2
19
20
:
:
:
:
:
:
3
:
:
:
:
13
1Y -
-
ELEVATOR SIGNAL C
ELEVATOR E X C I T A T I W C
c
F
:
:

:
95
Yb

t7 38
3 b __C_ V-BAQ ROLL C W D SERVO D R I V E M2 I
37

:
V ~ A QROLL COMO

5 7 - V a A R ROLL C W D RATE 62 -
SERVO ORIVE c
28
27

.
:
.. .. :._
:
25 : :
:

ERECT:
:
:
:
:

:
15
lb - - b

I1
ELEVATOR P O S I T I O N EXCITATION H
t ELEVATOR RATE EXCITATION H
ELEVATOR SERVO GRD
G
H
L
R

-
: Y8 39 -6 V a A R ROLL C W D S I G COM 2b : : H--Q I D : 17 4 C ELEVATOR RATE SIGN#. S
: : 2 4 : :

-
Y9 39 V 4 A R ROLL POS YJ4lR H l
: 5 o 35 __C_ V 4 A R ROLL POS XMTR C l : 2 3 : :
115VAC A T T I T W E POWER
- .. .
: Mw +
.... ,.
(J2)

-
51
: 52 31
-
GYRO
GYRO H I G H LEVEL FLAG
-
+
29 V 10
31 : : :
N
.. ELEVATOR ENGAGE VOLTAGE J
:
:
53 :
: - 18
-
GYRO H I G H L E K L FLAG 32 : : :
: : .. ..-
ELEVATOR ENGAGE VOLTAGE H
5Y 4 STEER FLAG 2 NAV
..
STEER FLAG +
...
: 55 2 28 RCVR
.
- : : : 5lRV-1
.. .-
33
:
:
l b
10 - +28 VDC FLAG POWER
G L I D E SLOPE DEV + W
DEV + DN :
5Y ~ (TP)
..
: :
.
SI
35
36
;
:
:
12
13
-
11 - G L I D E

-
SLOPE
G L I M SLOPE
G L I M SLOPE
LCU LEVEL FLAG +
LOU LEVEL FLAG - :
22-9

: :
:
2
21
2
.. ..-
G L I D E SLOPE HIGH LEVEL FLAG +
. .
: 11-27 .. ..
29 ; b -
- VORlLOC DEV + L E F T
+
: : 32
:
- (BP)
YO
-..
.. ..
..
28
:
5
-
-
VQIlLOC DEV RIGHT

- +
:
:
22- 39
. .. RWMR

E-
9 VQIlLOC H I G H LEVEL FLAG 11-50
t s cA p : : 38 R U W A Y FLAG : 5 : 33'tC-3

: 5-
LOC FREQ VOLTAGE + :
.. :.. :..
:
: 43-38
i@ (JI)

-
8 COURSE RESOLVER H 21 bi 28 VDC F I E L D N L M E R
f RVDDER 1 A
B
: 5 6 COURSE RESOLVER C . . .- 23 : Y I 3-- W M R F I E L D NUDBER 2 C
: : : : E

--
5- COURSE RESOLVER D 2Y Y3 5+RVDDERSIGNM C
5 : 5 6 COLRSE RESOLVER E : YY RUDDER E X C I T A T I O N <
b : : 5?- COLRSE RESOLVER F : 2b : Y5 RWDER P O S I T I O N EXCITATION H G
7 : 5 6 COURSE RESOLVER G : : : 2 7 : Yb -f RLODER RATE EXCITATION H H
+ : : : * I :
31
32
VOR/LOC FLAG
VORfLOC FLAG - : : : w :
Y2
'tl
.
5- RUDDER P O S I T I O N SIGNAL
RUDDER SERVO GRD
L
R
2b
27 :
TO-FROM ARROW (+ TO)
TO-FROM ARROW (+ FROM)
: :
:
93
YY ..
:
..
97 5- RUDDER RATE SIGNAL S
. TPI- ,2550-044 :

AP-103F/FD-108 Gulfstream G-159, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 448

Nov 1/68 22-03-00

Pages 401/47, 401/48
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
AhVUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INPICATOR WIRE FUNCTION AMPLIFIER COMPUTER COMPASS POWER MPLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

PRlA-bA b14E-2G 3798-?A AILERON 121A-2

8 J1 52 J1 J1 J2 3Y4C-3
(J1)
J1

.. . .
. . (J1)

.... .. .. RUDDER ENGAGE WLTAGE B

. ... ... RUDDER ENGAGE VOLTAGE C

:
:
:
:
:
: 3 2
27 - GRD
TRIM
SERVO
334C-Z-33E
TRIM
INDICATOR
327D-IW
: 22-
-
: : 5 (Jl)
: . c -+
:
:
COMPASS MON
COMPASS MON +
- :
:
:
30
29
:
--
:
14
30-
17
25
1
:
34 -

33
1c

-+
TRIM TAB MOT CONT

TRIM TAB MOT CONT

: Q
F--
E

: COMPASS DATA X .. . . : 2 GRD : Fi-- TRIM MOTOR GROLND B

. ._ . . D . : 28VDC A

'91 T.1: : COMPASS DATA Y .. .. .. : 3 TRIM ENGAGE VOLTAGE L

. . . TRIM ENGAGE CRCUND M
. . .
1 7 3
: L 1 9
:
:
COMPASS DATA Z
..-. .... 114 *
4
: 99 -
- COMPASS DATA X

: COMPASS FLAG +
-. -. 3 .,
... ...
:
:
50
51 - COMPASS DATA Y
COMPASS DATA Z
30
2Y
15
: COMPASS FLAG - :
:
:
31
32 ...~ ..
lb :
1 b VAC HCG PUR
COMON .
15
l b
. .
20 : 5- HEADING ERROR SYNCHRO C ' : I? ... ..-
21
13
:
:
5 6 HEADING ERROR SYNCHRO H '
5- HEADING RATE G2
:
:
18
19
.. ..
1Y : 5 6 HEADING RATE C2 : 20 .... ...-
.- ..
-
12 : H E MOT CONT C 1 : 21
11 : HDG MOT CONT M I : 12 AIRSPEED

:
11
13
45
4b
47 :
Y
5
:
:
:
:
:
:
:
:
:
:
HEADING DATUM SYNCHRO C '
HEADING DATUM SYNCHRO H '
COURSE DATU4 SYNCHRO C '
COLUSE DATUM SYNCHRO H '
DISTANCE INDICATOR FLAG +
DISTANCE INDICATOR FLAG -
DISTANCE INDICATOR 2 b VAC H
:
:
:
:
:
:
:
:
:
:
:
:
23
33
24
34
:
:
:
OM€_
. :
8bOE-Z
(J1)
9:
1D:
2 :
. .

59
58
bo
- :
.
AIRSPEED SIGNAL
AIRSPEED EXCITATION H
AIRSPEED EXCITATION C
SENSOR
5908-2
J1

48 - : : DISTANCE INDICATOR 2 b VAC C : : : 1:

49J : .. .. ..
50 : : DISTANCE INDICATOR UNITS SYNOlRO x : 2 . : 4 :
51 : DISTANCE INDICATOR UNITS SYNCHRO Y : : : : 3 :
52 : : DISTANCE INDICATOR TENS SYNCHRO X : : : : b :
53 : DISTANCE INDICATOR TENS SYNCHRO Y : : : : 5 :
59 : : DISTANCE INDICATOR HUNDREDS SYNCHRO X : : : 7 :
55
Y8
31
:
:
: 5-
2b VAC COMMAND W R
2b VAC ATTITUDE W R
-
DISTANCE INDICATOR HUNDREDS SYNCHRO Y
12
15
:
:
:
:
:
:
P 8 :

:
33
- 5 b 1 b VAC ATTITUDE PUR COM- l b :
~.
: :
29 : : 19
- 5 VAC LIGHTING PUR <a)
25 :

s
: 2D
:
:
:
5 VAC LIGHTING PWR COM
DC GROUND

- -
115 VAC HEADING PUR
115 VAC ATTITUDE PUR
+28 VDC POWER
- -
20
.
+28 VDC SERVO CLUTCH POWER 20
1-

4 - : 1: 7 5 7
1.I
5-55

:
- ... ..=
-lGRD

.. A
54
5b
:
:

: b

G
. .
... ._ . _ .. ..
..
.. .-_ ...
: GRD :
: bl - CROWD
28 VDC POWER
w
T;;i N

... ..
...
..
...
9 @ b3 -e
.:
RVDDER SERVO POVER
RUDDER SERVO POVER
.. . . @ i-
0- AILERON SERVO POWER
..
.... ....
b l AILERON SERVO PWER V
.. D
I @ b; -e
ELEVATOR SERVO POWER
ELEVATOR SERVO POWER

-
: PITCH STEERING + UP . 3-31 : : G R D W 1 : : GQ*ROWD :
: PITCH STEERING + WWN . 9-21 : RELAY :
: ROLL STEERING + LEFT : 12 31 :
L
K
J -
.
- :
.
-
.
ROLL STEERING + RIGHT
GYRO MODE +
HEADING MOnr +
NAVILOC MODE +
13
: 13
:

r
: 41
: : 4 7
21

: Y b
:y + 4
:L14
.
49
:
.
-
.
:
:
:
:
:
YO
b4
: 47
:
:

GO AROUND MODE +
H APPROACH MODE +
: 45 : f 48 - APPROACH MODE
APPROACH MODE
+
+
:
:
E X l S T R + DN
E X T S T R + UP
:
: 33 i
27
; I
- II
i : ALTITUDE HOLD INTERLOCK . . . A L T I N M HOLD IITERLOCK
I
:
..
.. ._ . .
..
Yb :
.. : bb -
-
ALTITUDE HOLD IYTERLOCX
DISCONNECT SWITCH H
f
.. 39..- 4 5: ALTITUDE
:
:
:
:
b7
4b - DISCONNECT SWITCH C
GLIDE SLOPE MODE +
DISCONNECT
. . : CONTROLLER : SWITCH
: : : 59OA-3A

V
:
:
:
:
ALTITUDE
ALTITUDE
ALTITUDE
ALTITUDE
ALTITUDE
HOLD MODE +
RATE H ' +\
RATE C ' +>
ERROR H ' 4\
ERROR C ' 4 6
:
:
:
:
:
:
:
47-39:
34
14
33
23-27-
-
-
: (J1)
19 :
15 :
l b
Q I
.
.
.
.
41
92
:TP1-2550-044

AP-103F/FD-108 Gulfstream G-159,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 448 (Sheet 2) Pages 401/49, 401/50
 COLLINS
MAINTENANCE
w MANUAL

FLIGHT
ANNUN- CWRSE PEDESTAL DIRECTOR INSTRWT FLIGHT ALTITUDE AUTOPILOT EMRGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER COhPUTER COHTROLLER POWER MPLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J4OX

33lA-bA b14E-2G 3298-?A 39YGlD 5b2AbG 59DA-3A AILERON 121A-2

@ J1 J2 J1 Jl J2 J1 J2 J1A JIB (J1) @ Ji562wJi 34963 J1
(TP) (BP) (TP)(BP) (TP) (BP) (Jl)

. .
12
13
14 -
__C_
: P I T C H BOOTSTRAP TRANSMITTER X
P I T C H BOOTSTRAP TRANSMITTER Y
P I T C H BWTSTRAP TRANSMITTER 2
:
:
:
:
. :.
: :
:
:
39.
Y2-I
9 3 4
.
I
.
43
44
45
-
-
-
ALTITUDE GAIN CHANGE EXCITATION
ALTITUDE GAIN OiANGE NO. 1
ALTITUDE GAIN CHANGE NO. 2
15
l b
2b
27
28
29
30
-
-
_C_
f

I
P I T C H BOOTSTRAP EXCITATION H
P I T C H BOOTSTPAP EXCITATION C
BANK BOOTSTRAP TRANSMITTER X
BANK BOOTSTRAP TRANSMITTER Y
BANK BOOTSTRAP TRANSMITTER 2
BANK BOOTSTFUP EXCITATION H
BANK BOOTSTRAP EXCITATION C
:
:
:
: :
: :
.: .:
1 5 f
:
:
:
3b-l
35
37-D
e
.
:
I
I
I
.
59
18
19 -
25 4-
-
-+
6
COMPUTER MON +
EXT P I T C H STEERIYG A
EXT P I T C H STEERING B
AC PITCH STEERING A
HEADING WARNING DATA X I 2 b -b AC PITCH STEERING B
I HEADING WARNING DATA Y : 27 ++ PROCESSED P I T C H DATA A
HEADING WARNING DATA Z : 28 -6 PmcEsm PITCH DATA B
HEADING WARNING DATA H
HEADING WARNING DATA C
:
:
18
48
I
:
:
I bD -
5 7 -INTERNAL PITCH STEERING OFF
ALT HOLD OFF +
+

--
HEADING WARNING DATA H' 18 -+ ROLL STEERNIG A
. . HEADING WARNING DATA C' 19 -
25
6
-+
ROLL STEERING B
PROCESSED BANK CMD A
.~ 2b -6 PROCESSED BANK ChD B
. . 35 PROCESSED BANK DATA A
3b -b PROCESSED BANK DATA 0
.. .. 55 -+ EXT BANK CM) 0

: PITCH MONITOR +
- : 12 - 12 :
54 -6 EXT BANK CK, A

- --
Q ARM I GLIDE SLOPE ARM. ANN. : b :
GS EXT . GLIDE SLOPE EXT. ANN. f Y2 :
N I L ARM : YAVILOC ARM. ANN. I : b :
N I L CAP . NAVILOC CAPTURE ANN. f 39 :
Q
PWR
GA
ANNUNCIATOR POWER
GO AROUND ANN - f l b : M B C N :
. . : : : R C W
. _ . :
:
:
:
:
:
: 512-4
: (J1)
: MIDDLE MUIKER : 43-4
: : 18 57 -INTERNAL m L L STEERING OFF +
: A P I T C H CONTROL EXC A 21 I wv wv : 51RV-1
: B PITCH m m m L SIGNAL 2Q . . . : RCW CONT : SELF TEST

.. .. ..
: c PITCH m m m L EXC B a22 51RV-1 313N-3 :
. . D (J2) (JZ) :
RELAY

: E TURN c o m m L EXC A 21 :
: F N R N CONTROL EXC B 22 :
: : G TLRN CONTROL SIGNAL 2D :
N I N 1 MOTOR CONTROL VOLTAGE . b2
: P I N T 2bVAC MOTOR EXCITATION C 2Y :
-. ..
: R I N 1 MOTOR RATE SIGNAL J b3
S I N 1 MOTOR SIGNAL C W N . 24
: T 28vDc PANEL L I G H T PUR 0
: u GQOUND GRD :

...... ... .
z
a ENGAGE P U S E f 5b
. .- . -
b DISENGAGE VOLTAGE < 37
.- .
.. (& f ENGAGE READY 55
. ~

ALTITUDE HOLD MODE + 1

. . 38
.. .. .. .. . . .
.- .. . . .
f I HEADING SYNCH CUTOUT 38 : : T R I M INDICATOR:
.. .... ...-
h z z
- :. : . : 327LLlW :
i : 33 +
j .. A
k
. ._.._ ... .. .. : 34
-
..
*
m : E2 I
n
P .f 115 VAC AUTO P I L O T PUR e 53
: @ R
+
.
~. . 9
I :
115 VAC POWER
I N T 2bVAC MOTOR EXCITATION H :
7
23
:
:
5
..- ... t
U
V
W
M
X . .
..
.
.. .
. .
.. .
_
.. . . UNIT
.. .. 345A-W
( m L u
@ :
: YAW D M SU
cc . . .-
..... ..... ....
: b5 ROLL RATE MOTOR (RD
_C__ A
Gym
Dfl
EE
MODE
HEADING MODE . :
8
32
:
f
115 VAC POWER
ROLL RATE EXCITATION c
B
E
... ... ...
FF NAVILOC MODE : 31 _c__ m L L RATE EXCITATION H
GG APPROACH MODE : 29 P ROLL RATE SIGNAL x G
HH MODE VOLTAGE H
. . . -. .- 1TPI-2550-044

AP-103F/FD-108 Gulfstream G-159,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 448 (Sheet 3) Pages 401/51, 401/52
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
ANNUN- COIRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT SENSING EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COWUTER MISC POWER AWLIFIER WIRE FUVCTION SERVOS WIT DISCONNECl J-BOX

8
331A-bA
J1 J2
blSE-2G
J1
3290-7A
J1 J2
344C-1D
J1 J2
SbPA-SG
JIA JIB
43 J l
5b2C-4
Jl
AILERON
34463 345A-40 @
l2U-2
J1
(TP) (BP) (TP)(BP) (TP) (BP) (J1)

21-
22 -PITCH
PITCH DIFFERENTIAL RESOLVER X
DIFFERENTIAL RESOLVER Y : 8 -
- PITCH RATE MOTOR GRD
(PITCH)
A
23-PITCH
24 -PITCH
DIFFERENTIAL RESOLVER Z
DIFFERENTIAL RESOLVER H
:
:
:
10
32 -
-
115 VAC POWER
PITCH RATE EXCITATION C
3
E

2b -
25 -PITCH

-
DIFFERENTIAL RESOLVER C
PITCH DIFFERENTIAL RESOLVER H ' :
31
29 - PITCH RATE EXCITATION H
PITCH RATE SIGNAL X
f
G
27
- PITCH DIFFERENTIAL RESOLVER C '
:@ 28

30
31-
-
29 -BANK
B A M DIFFERENTIAL RESOLVER X
DIFFERENTIAL RESOLVER Y
BANK DIFFERENTIAL RESOLVER Z
BANK DIFFERENTIAL RESOLVER H bb -
-
YAW RATE MOTOR WD
YAW PATE
"..._
BYDO
3326-2
A

Yb

Y?
33
.34
1

2
-
32 -BANK

-
DIFFERENTIAL RESOLVER C
BANK DIFFERENTIAL RESOLVER H '
BANK DIFFERENTIAL RESOLVER C' 3
b

7
1

2
2
3
9
5
10
51
50 P
48
2
- :
115 VAC POWER
YAW RATE EXCITATION C
YAW FATE EXCITATION H
YAW RATE SIGNAL X
1
2
b
B
E
F
G

3 7
49 7 8 3 8 23
50 8 9 4 13 YO
51 19 10 7 15 52
52 15 11 8 l b 58
ID
53 17 14 13 2b
l b
59 35 30 17 2?
55 3b 28 29
37 29 3b
39 38 37
41
YO 5D 38
91 51 Y2
92 52 Y8
43 53 50
44 55 51
Y5 56 52
'tb 5? 53
Y?
Y8
Y9
50
51
52
53
54
55

SYHBOLS USED:
10- THESE LEADS MUST BE W I S T E D AND SHIELDED I F OVER TTO FEET LONG.
S I W I S T E D SHIELDED PAIR 11. C W A R A T O R WARNING RESOLVERS.
SI 12. TOTAL WIRE RUN FROM BUSS TO 121A-2 TO 5bZC-4 TO 33YC-3 ( P I N 8) FOR EACH P R I M SERVO MUST NOT EXCEED 9 5 FEET
SG SHIELD T I E D TO GRDWD AT UNIT I F AWG 20 WIRE I S USED. W E N GREATER THAN 4 5 FEET, INSTALL TERMINALS AT 5b2C-Y MOWT AND RUN AWG 20 WIRE FROM
S1 SINGLE SHIELDED WIRE 5b2C-Y TO TERMINAL AND AWG I b WIRE FROM TERMINAL 344C-3 P I N 8 .
WITH COPIL~TS-FL~GHT
8 ALL 5 1 SHIELDED TIED TO X I ETC.
NOTES
13.
11.
AN ISOLATED MODE SWITCH SI R~OVIDED FOR USE DIRECTOR.
A 12K OHMS 112 WATT 10 RESISTOR I S REQUIRED ON EACH TRIM INDICATOR M3VEMNT. WITH THE TRIM INDICATOR CONNECTIONS
SHOWN THE PRIMARY SERVO CVSTAN SHOULD TLRN CLOCKWISE WHEN VIEWED FROM THE CAPSTAND AND UNDER THE FOLLOWING
AIRCRAFT ATTITUDES:
NOTES:
-
--
AILERON LEFT BANK
1. ALL WIRE SIZES ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY NUWERS I N SQUARES. ELEVATOR PITCH UP
2. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE GROWDED AT THE 51RV-I. MJDDER LEFT YAW
3. JUMPER WIRE FROM J1-2 TO J1-3 OF THE COLUSE INDICATOR SHWLD BE NO LONGER THAN S I X INCHES.
4. A RELAY hUJST BE INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE 51RV-1 W E N 15. POWER FROM A PARTICUAR CIRCUIT BREAKER OR FUSE N4Y PROVIDE POWER FOR W R E MAN ONE EQUIPMNT. THIS WILL BE
THE AUTOPILOT I S ENGAGED. INDICATED N
I m E INTERCONNECT POWER COLW BY A LETTER WITH AN OCTAGON S Y ~ O LAROUND IT. CAPITAL LETTERS FOR
5- THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N THIS DRAWING REFLECTS LOADS AS FOLLOWS: DC AND LOWER CASE LETTERS FOR AC.

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS A - -

28vDC DIMMING CIRCUIT. a - -
W A C D I m T N G CIRCUIT

2 0 0 OHMS
5DD WMS
TO-FROM
GLIDE SLOPE DEVIATION
100 OHMS
2 0 0 OHMS
JUWER
JUWER
BP-43 TO BP-33 OF SIRV-1
TP-8 TO TP-2 AND TP-3 OF 51RV-1
01
c -
C. 0, E 28VDC 5 AMP
28vDC 1 M P e
f
-
b, c. d 115VAC 2 M P
IISVAC 1 AW
A 115VAC 3 AW
500 OHPS GLIDE SLOPE FLAG 2 5 0 OHMS JUWER TP-21 TO TP-2b OF 51RV-1
5000 OHMS VOR/LOC FLAG 250 OHMS JUWER BP-32 TO BP-41 OF SIRV-1 lb. THE GO AROUND RELAY I S USED I N CONJUNCTION WITH THE APPLICABLE FSB FOR WINGS LEVEL, PITCH U p GO *ROUND.
500 OHMS VOR/LOC DEVIATION 2 0 0 OHMS JUWER BP-39 TO BP-30 AND W-98 OF 51RV-1 THE CO AROUND BVlTON IS EFMALLY OPEN AND SHOLLD BE LOCATED ON THE WHEEL I F POSSIBLE- TO DEACTIVATE PROVISION
REMOVE THE RELAY AND CONNECT THOSE WIRES TOGETHER THAT NORMALLY ARE CONNECTED THROUCH THE RELAY CONTACTS W E N
b. THE POWER FOR THE COWASS SYSTEM MVST BE OF THE SAME PHASE AS THE REST OF THE AVIOMATIC FLIGHT CONTROL SYSTEM. RELAY I S DE-ENERGIZED.
7. POWER LEADS DENOTED BY "DIM" SHOULD BE T I E D TO COCKPIT LIGHT DIMMING CIRCUITS. 17. WHEN OPTIONAL 59OA-3A SERVICE 8ULLETlN N0.3 I S INCORPORATED, TUE FOLLOWING INTERCONNECTING WIRINGCUANGES ARE
8. SENSING W I T 345A-4( ) AND RATE GYRO 3326-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE. APPLICABLE'
9. ANNUNCIATORS CHOSEN MUST NOT EXCEED 100 MA. A COMQN c l 8 V D C I S USED FOR ANNUNCIATOR POWER. REMOVE CONNECTION 8ETWEEN Jll8Pl-38 OF THE562C-4 AUTOPILOT AMPLIFIER AND J I - 4 OF THE 614E-2G PEDESTAL CONTROLLER.
REMOVE CONNECTION BETWEEN J I - V OF THE 614E-2G PEDESTAL CONTROLLER 4ND J l 4 l T P ) - 4 7 OF THE 5621-5G
FLIGHT COMPUTER. MAKE CONNECTIONS AS SUOWN BELOW.
PEDESTAL FLIGHT ALTITUDE 4UTOPILOl
CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMPLIFIER
614E-2G 562A-5G 5904-31 562C-4
JI JIA JIB IJII JI JI
lTP1 ISPI ITPI (BPI
v--- PLTITUDE HOLDMODE+--------- 34
ALTITUDEHOLOMODi+ 47-----20------- 38 TPI-2550-044

AP-103F/FD-108 Gulfstream G-159,

M a r 1/73 Interc onne cting Wiring Diagram 22 -0 3-00
Figure 448 (Sheet 4) Pages 401/53, 401/54
 -
a
COLLINS
M.AIIVTENANCE

(To B e Supplied)

Pages 401/57, 401/58; 401/59, 4-01/60; a n d

401/61, 401/62 r e s e r v e d for additional
s h e e t s of figure.

AP-lOSF/FD-108 Nord 2 6 2 , I n t e r c o n n e c t i n g W i r i n g D i a g r a m
F i g u r e 449

May 1/67 22-03-00

Pages 401/55, 401/56
 a
COLLINS
MAISTEIVANCE

Qw MANUAL

WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
ANNUN: COURSE PEDESTAL FLIGHT 8

CIATORS INDICATOR AMPLIFIER COMPUTER AMPLIFIER AILERON DISCONNECT

CONTROLLER DIRECTOR 562A-56
33 I A 6 A 6 14E-2G INDICATOR 3 4 4 C - ID Q 562C-4 334c-3 12 IA-2
G3 JI J2 JI
3296-7A J1 J2 JIA JIB JI JI
(JI) J1
JI
6
52
,-.,
I PITCH ATTITUDE ERROR H'
(TP)
24
(BP) UP1 (BP)
AILERON FIELD NUMBER I A
7
S I
PITCH ATTITUDE ERROR C' 23 28 VDC 8
8 PITCH ATTITUDE SERVO DRIVE M2- 28 AILERON FIELD NUMBER 2 C
9 PITCH ATTITUDE SERVO DRIVE C 27 AILERON SIGNAL C E
IO E PITCH ATTITUDE RATE G2 25 VERT AILERON EXCITATION C F
II ._.
I 1
PITCH ATTITUDE RATE C2 26 REF AILERON POSITION EXCITATION H -
G
I ,,
,-3
MANUAL PITCH COMMAND H ' 36 332D- I 1 AILERON RATE EXCITATION H H
, I
2 \-, MANUAL PITCH COMMAND C' 26 (J1) AILEROY POSITION SIGNAL L
42 V-BAR PITCH COMMAND SERVO DRIVE M I I1 AILEROE SERVO GRD R
43 V-BAR PITCH COMMAND SERVO DRIVE C IO v7
X AILERON RATE SIGNAL S
,-*
, 8 (J2)
44
45
I
I 1
L,
,-,
V-BAR PITCH COMMAND RATE
V-BAR PITCH COMMAND SIG COM 9 KI
P AILERON ENGAGEVOLTAGE A E
40 V-BAR PITCH POS XMTR X 7 AILERON ENGAGE VOLTAGE B F
41
I I
I I
V-BAR PITCH POS XMTR Y 6 u3
W ELEVATOR
3 PITCH ATTITUDE CT X 30 A 334c-3
4 PITCH ATTITUDE CT Y 20 8 (JI)
5 PITCH ATTITUDE CT Z C ELEVATOR FIELD NUMBER I A
17 BANK ATTITUDE CT X 30- D 28 VOC 8
18 BANK ATTITUDE CT Y 20 - E ELEVATOR FIELD NUMBER 2 C
19 BANK ATTITUDE CT Z F ELEVATOR SIGNAL C E
,
3
t-,
20 I BANK ATTITUDE ERROR H' 18 ELEVATOR EXCITATION C F
21
I ,
,_, BANK ATTITUDE ERROR C' I7 ELEVATOR POSITION EXCITATION H - G
22 BANK ATTITUDE SERVO DRIVE M2 22 ELWATOR RATE EXCITATION H - H
23 BANK ATTITUDE SERVO DRIVE C 21 T ELEVATOR POSITION SIGNAL L
,I 1
3
I-\
24 I BANK ATTITUDE RATE G2 19 ELEVATORSERVOGRD R
25 ,_I BANK ATTITUDE RATE C2 - 20 ELEVATOR RATE SIGNAL S
36 V-BAR ROLL COMMAND SERVO DRIVE M2 28 (J2)
37 V-BAR ROLL COMMAND SERVO DRIVE C 27 ELEVATOR ENGAGEVOLTAGE A J
ELEVATOR ENGAGEVOLTAGE B H
38 V-BAR ROLL COMMAND RATE G2 25
i i H G RD RUDDER
39 V-BAR ROLL COMMAND SIG COM 26
34
:.: V-BAR ROLL POS XMTR H I 24 334c-3
I, I
fJ 1)
35 s-, V-BAR ROLL POS XMTR C 1
1 1 5 VAC ATTITUDE POWER
GYRO MON +
5
29
23

I O -N
G
-@
-
Q 67
RUDDER FIELD NUMBER 1
28 VDC
A
B
RUDDER FIELD NUMBER 2 C
31 GYRO HIGH'LEVEL FLAG + 31 NAV
IS- GYRO HIGH L E V E L FLAG - 32 RCVR
RUDDER SIGNAL C E

4
- STEER FLAG - 2 5 1RV- I
45
RUDDER EXCITATION C
RUDDER POSITION EXCITATION H -
F
G
STEER FLAG 2 28 UP) AC RUDDER R A ~ E X C L ? R k 6 0 N H H
16- +28 VDC FLAG POWER 54
%UDDER POSITION SIGNAL L
33 10- GLIDE SLOPE DEV + U P 32 8 0 RUDDER SERVO GRD R
34 II- GLIDE SLOPE DEV + DN 22 9
RUDDER RATE SIGNAL S
35 12 - GLIDE SLOPE LOW L E V E L FLAG + 21
GLIDE SLOPE LOW L E V E L FLAG - 22
RUDDER ENGAGE VOLTAGE
(52)
A B
I1 27
RUDDER ENGAGE VOLTAGE B C
TRIM COUPLER
29 6- VORAOC O N t L E F T 32 - 40 t6lA-1
28 5- VORAOC DEV +RIGHT 22 - 39
9- VORAOC HIGH L E V E L FLAG + I1 -50
ARM UP
TRIM UP
, I
L O CF R E Q V O L T A G E +
COURSERESOLVERH
43 - 38 RELAY GRD
8
I-.
21 TOAIRCRAFT
I I, FAILURE WARNING LIGHT TRIMSYSTEM
Q ',-i :-! COURSE RESOLVER C
COURSE RESOLVER D
23
24
TRIM DN
4 r'
!I 25
RELAY GRD 31
5 LI COURSE RESOLVER E
6 ;-; COURSE RESOLVER F 26
7
4
._, ,
COURSE RESOLVER G 27
31 VORAOC FLAG + 41
32 V O R L O C FLAG - 42
26 TO-FROM ARROW (+TO) 43
27 TO-FROM ARROW (+FROM) 44 TPI-4145-044

AP- 103F/FD- 108 Sabreliner, Interconnecting Wiring Diagram

Aug 1/69 (Sheet 1 of 4) 22-03-00
Figure 450 Pages 401/63, 401/64
 ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MISC POWER AUTOPILOT WIRE FUNCTION SERVOS MISC EMERGENCY J-BOX
ClATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER AILERON DISCONNECT
33 IA-6A 614 E-2G INDICATOR 344C-ID 5 6 2 A -5 6 COMPASS @ 562C-4 334c-3 12 IA-2
329B -7A JI J2 JIA JIB 328A-2A JI JI J1 JI
8 J1 J2 JI JI 52 (TP) (BPI (TP) (BPI (JI) (52) PPI (W
@ GRD GRD 1
I 15 VAC POWER 8
-I+
~

TRIM ENGAGE VOLTAGE -02 L

TRIM ENGAGE GRD 32 M
36- TRIM INPUT DN + 22
35 - TRIM INPUT DN - 24
k E L N A T O R TRIM INDICATOR 34- ELEVATOR TRIM INPUT UP + 11
i ELEVATOR TRIM INDICATOR 33 - ELEVATOR TRIM INPUT UP - 13

8 ;
h
AILERON TRIM INDICATOR
AILERON TRIM INDICATOR
33
34
n, RUDDER TRIM INDICATOR 53
n RUDDER TRIM INDICATOR 52
COMPASS MON - 30 17
COMPASS MON + 29 14- 25
COMPASS DATA X 2

IO* 2 COMPASS DATA Y 3

18
OM PASS z AIRSPEED
Yg
"-t
DATA
11
4
49 -COMPASS DATA X
50 -COMPASS DATA Y
SENSOR
30 COMPASS FLAG + 31 4 590%-2
24 COMPASS FLAG - 32 3 5 I -COMPASS DATA 2 J1
15 2 6 VAC HDG PWR 15 59 AIRSPEED SIGNAL
16 COMMON 16 58 AIRSPEED EXCITATION H
I-,
20 I I HEADING ERROR SYNCHRO C' 17 60 AIRSPEED EXCITATION C
I 1
21 $=* HEADING ERROR SYNCHRO H ' 18 27 G RD
I ,
13 I 4 HEADING RATE G2 19 2 2 -5 D
I 1
14 L_* HEADING RATE C2 20 30 -1 F
12 HDG MOT CONT C1 21
I1 HDG MOT CONT M I 22
4 HEADING DATUM SYNCHRO C' 23
5 HEADING DATUM SYNCHRO H ' 33 DME
12 COURSE DATUM SMYCHRO C' 24 860E-2
13 COURSE DATUM SYNCHRO H' 34 (JI)
45 DISTANCE INDICATOR FLAG + 9
46 DISTANCE INDICATOR FLAG - IO
47 DISTANCE INDICATOR 2 6 VAC C 2
48 ? DISTANCE INDICATOR 26 VAC C 1
GRD -I
49
50 DISTANCE INDICATOR UNITS SYNCHRO X 4 GRD G RD a N
51 DISTANCE INDICATOR UNITS SYNCHRO Y 3 61 -28VOCPOWER
52 DISTANCE INDICATOR TENS SYNCHRO X 6 RUDDERSERVOPOWER
t-,
53 DISTANCE INDICATOR TENS SYNCHRO Y 5 RUDDER SERVO POWER
to:
54 DISTANCE INDICATOR HUNDREDS SYNCHRO X 7 1 AILERON SERVO POWE
55
48
:-:
DISTANCE INDICATOR HUNDREDS SYNCHRO Y
2 6 VAC COMMAND PWR 12
8 rot
s
' I AILERON SERVO POWE
ELEVATOR SERVO POWER W

24
32
33
19-
,-,
, I
2 6 VAC ATTITUDE PWR
2 6 VAC ATTITUDE PWR COM
5 VAC LIGHTING PWR
15
16
-
T
-- ELEVATOR SERVO POWER L

25 20- 5 VAC LIGHTING PWR COM A r- 5 7

DC GRD 1- 1 I I . GRD
1 1 5 VAC HEADING PWR 5 55
I 1 5 VAC ATTITUDE PWR ~ 4- 56 #
- , c
9 + 2 8 VDC POWER 20 54 Q
e + 2 8 VDC SERVO CLUTCH POWER
PITCH STEERING t UP 3 -31
PITCH STEERING + DN 4 -21
ROLL STEERING t L E F T 12 31
ROLL STEERING t RIGHT 13 21 TPI-4145-044

AP- 103F/FD- 108 Sabreliner, Interconnecting Wiring Diagram

Aug 1/69 (Sheet 2 of 4) 22-03-00
Figure 450 Pages 401/65, 401/66
 MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EM ERG E NCY J -BOX
ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGKT
AMPLIFIER COMPUTER ALTITUDE AMPLIFIER AILERON DISCONNECT
CIATORS INDICATOR CONTROLLER DIRECTOR
CONTRQLLER @ 562C-4 334c-3 121A-2
8 33 IA-6A 614E-2G INDICATOR
329B-7A
344C- I D
JI J2
562A-5G
JIA JIB 590A-3A JI J2 (JI) JI
JI J2 JI JI J2
GO AROUND RELAY
L
I( HEADING MODE + 47 60
J NAV/LOC MODE + 46 47
GO AROUND BUTTON I
14
-44 1 GO AROUND MODE + @- - 1
a
APPROACH MODE +
44
APPROACH MODE t -
I
A
-

1
45 48 - APPROACH MODE +
EXT STR t DN
27 3 36 a I
I
I

W
EXT STR t UP
ALTITUDE HOLD INTERLOCK
37

46
ALTITUDE HOLD INTERLOCK
ALTITUDE HOLD INTERLOCK
-
- 0
II

V ALTITUDE HOLD MODE t 47 34Q 66 - DISCONNECT SWITCH H

^ II
v

ALTITUDE RATE H’ ,-I

I I
I 1
34 14 67 - DISCONNECT SWITCH C
P I L O T ~ S ~COPILOT~ST
ALTITUDE RATE C’ ,, 24 15
I \
ALTITUDE ERROR H’ I t 33 16 41 DISCONNECT
ALTITUDE ERROR C’ I # 23 27 42 SWITCH
-ALTITUDE GAIN CHANGE EXCITATION
b-3

12 PITCH BOOTSTRAP TRANSMITTER X 39 43

13 PITCH BOOTSTRAP TRANSMITTER Y 42 44 -ALTITUDE GAIN CHANGE NO. I
14 PITCH BOOTSTRAP TRANSMITTER 2 43 45 -ALTITUDE GAIN CHANGE NO. 2
15 PITCH BOOTSTRAP EXCITATION H 39 45 46 -GLIDE SLOPE MODE t
16 PITCH BOOTSTRAP EXCITATION C 35 GRD
26 BANKBOOTSTRAPTRANSMITTERX 37 G RD
27 BANK BOOTSTRAP TRANSMITTER Y 15 59 -COMPUTER MON +
, , EXT PITCH STEERING A
I8 A

1::
20 BANKBOOTSTRAPTRANSMITTERZ
29 BANK BOOTSTRAP EXCITATION H 19 A EXT PITCH STEERING B
30 BANK BOOTSTRAP EXCITATION C 25 A ,
,\_, AC PITCH STEERING A
16 HEADING WARNING DATA X 40 26 -
,_, AC PITCH STEERING B
35 27 I, ,( PROCESSED PITCH DATA A
@
17 HEADING WARNING DATA Y -

18 HEADING WARNING DATA Z 25 20 A\-, PROCESSED PITCH DATA B

19 HEADING WARNING DATA H 18 57 - INTERNAL PITCH STEERING OFF +
20 HEADING WARNING DATA C 48 60 - A L T HOLD OFF t

I
21 HEADING WARNING DATA H’ 19 18
,-\
, , ROLLSTEERINGA
22 HEADING WARNING DAT C’ 9 19 :-: ROLL STEERING B
49 25 PROCESSED BANK CMD A
I ,
40 26 PROCESSED BANK CMD B
@ 35 35 ,,-,, PROCESSED BANK DATA A
, I
25 36 t-, PROCESSED BANK DATA B
r-,
7 55 EXT BANK CMD B
0I ,t
17 54 ,-, EXT BANK CMD A NAV NAV 51RV-1
PITCH MONITOR t 12- 12 MKR BCN RCVR CONT SELF TEST
GS ARM GLIDE SLOPE ARM. ANN. - 6 RCVR 51RV-1 313N-3 RELAY
GS EXT GLIDE SLOPE EXT. ANN. + 42 512-4 (52) (J2)
N/L ARM N A V A O C ARM. ANN.- 6 (JI)
N/L CAP NAV/LOC CAPTURE ANN. - 39 .-
PNR Q
GS CAP 30 - ANNUNCIATOR POWER
RUNWAY FLAG - 5
GA GO AROUND ANN, - 16
MIDDLE MARKER 43 4
18 57 INTERNAL ROLL STEERING OFF +
A PITCH CONTROL EXC A 21
B PITCH CONTROL SIGNAL 20
C PITCH CONTROL EXC B 22
ENGAGE VOLTAGE
TURN CONTROL EXC A 21 T U I
~

TURNCONTROLEXCB 22
G TURN CONTROL SIGNAL 20
N INT MOTOR CONTROLVOLTAGE 62
INT 26 VAC MOTOR EXCITATION C 24
INT MOTOR RATE SIGNAL 63
S INT MOTOR SIGNAL COMMON 24 T P I -41 45-05 4

AP-103F/FD-108 Sabreliner, Interconnecting

M a r 1/73 Wiring Diagram 22-03-00
Figure 450 (Sheet 3) Pages 401/67, 401/68
 COLLINS
MAINTENANCE
w MANUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER AILERON DISCONNECT
(3
I
33 I A-6A 614E-2G INDICATOR 344C-ID 562A-5G @ 562C-4 334c-3 12 I A - 2
329B-7A JI J2 JIA JIB JI JI (J 1) JI
JI J2 JI (TP) (BP) (TP) (BP)
JI J2 (TP) (BP)

28 VOC PANEL LIGHT PWR

G RD GRD

ENGAGE PULSE 56
b DISENGAGE VOLTAGE 37
ENGAGE READY 55
0 f; ALTITUDE HOLD MODE + 38
HEADING SYNCH CUTOUT 38
P I 15 VAC AUTO PILOT PWR 20 f
9 I 15 VAC POWER 7
INT 26 VAC MOTOR EXCITATION H 23
ENGAGE INTERLOCK 54
-" ,
AILERON CLUTCH VOLTAGE 39 D I
RUDDER CLUTCH VOLTAGE 56 ,I
2 I

M t 2 8 VDC AUTO PILOT PWR R - ,I

^ I

Y
ELEVATOR CLUTCH VOLTAGE
SPARE
39
9
a K

AA
8B SENSING UNIT YAW DAMP SW
cc 345A-48

1
OD GYRO MODE
EE HEADING MODE
FF VOR/LOCMODE @
GG APPROACH MODE
HH MODE VOLTAGE H
-21- PITCH DIFFERENTIAL RESOLVER X 29 ROLL RATE SIGNAL X G
22 - PITCH DIFFERENTIAL RESOLVER Y (PITCH)
23 - PITCH DIFFERENTIAL RESOLVER 2 8- PITCH RATE MOTOR GRD A
24 - PITCH DIFFERENTIAL RESOLVER H IO - 1 1 5 VAC POWER B
25 - PITCH DIFFERENTIAL RESOLVER C 32 - PITCH RATE EXCITATION C E
26 - PITCH DIFFERENTIAL RESOLVER H ' 31 - PITCH RATE EXCITATION H F
27 - PITCH DIFFERENTIAL RESOLVER C' 29 - PITCH RATE SIGNAL X G
Q 28 - PITCH DIFFERENTIAL RESOLVER X YAW RATE
29 - BANK DIFFERENTIAL RESOLVER Y GYRO
30- BANK DIFFERENTIAL RESOLVER 2 332G-2
31- BANK DIFFERENTIAL RESOLVER H 66 YAW RATE MOTOR GRD A
32 - BANK DIFFERENTIAL RESOLVER C IO I 15 VAC POWER B
33 - BANK DIFFERENTIAL RESOLVER H' 51
50
YAW RATE EXCITATION C E
c34- BANK DIFFERENTIAL RESOLVER C' YAW RATE EXCITATION H F
48 YAW RATE SIGNAL X G

T P I - 4 145- 0 5 4

AP-103F/FD-108 Sabreliner, Interconnecting

Mar 1/73 Wiring Diagram 22-03-00
Figure 450 (Sheet 4) Pages 401/69, 401/70
 COLLINS
MAINTENANCE
w MANUAL

NOTES:

A L L WIRE SIZES ARE NO. 2 2 UNLESS DESIGNATED OTHERWISE BY NUMBERS IN SQUARES.

@ SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECENER SHOULD BE GROUNDED A T THE 51RV-I .
@ JUMPER LURE FROM J1-2 TO J1-3 OF THE COURSE INDICATOR SHOULD BE KO LONGER THAN SIX INCHES.
4 A RELAY MUST BE INSTALLED IN THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE 5 1 R V - I WHEN THE
AUTOPILOT IS ENGAGED.

@ THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWING REFLECTS LOADS AS FOLLOWS:
I AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS

2 0 0 OHMS TO-FROM 1 0 0 OHMS JUMPER BP-43 TO BP-33 OF 51RV-I

500 OHMS GLIDE SLOPE POINTER 2 0 0 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 51RV-I

'
5 0 0 OHMS GLIDE SLOPE FLAG 250 OHMS JUMPER TP-21 TO TP-26 OF 5 1 R V - I
500 OHMS LOC FLAG 250 OHMS JUMPER BP-32 TO BP-41 OF 5 1 R V - I
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO BP-30AND BP-48 OF 51RV-I

@ THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL SYSTEM.
@ POWER LEADS DENOTE0 BY "DIM" SHOULD BE TIE0 TO COCKPIT LIGHT DIMMING CIRCUITS.
@ SENSING UNIT 3 4 5 A - 4 ( ) A N 0 RATE GYRO 332G-2 SHOULD BE LOCATED AS CLOSE TOGETHERASPOSSIBLE.
@ ANNUNCIATORS CHOSEN MUST NOT EXCEED 1 0 0 MA. A COMMON +28 VOC IS USED FOR ANNUNCIATOR POWER.
@) THESE LEADS MUST BE TWISTED AN0 SHIELDED I F OVER TWO FEET LONG.

COMPARATOR WARNING RESOLVERS. 00 NOT USE FOR OTHER PURPOSES UNLESS LOADING EFFECT IS EVALUATED.
@ TOTAL WIRE RUN FROM BUSS TO 121A-2 TO 562'2-1 TO 334C-3 (PIN B) FOR EACH PRIMARY SERVO MUST NOT EXCEED 90 FEET I F AWG
2 0 WIRE IS USED. WHEN GREATER THAN 90 FEET, INSTALL TERMINALSAT 5 6 2 C - 4 MOUNT AND RUN AWG 2 0 WIRE FROM 5 6 2 C - 4 TO
TERMINAL AN0 AWG 1 6 WIRE FROM TERMINAL 3 4 4 C - 3 PIN B.

@ AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR.
@ WITH THE TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING LINKS INSTALLED FOR CORRECT SERVO PHASING, THEPRIMARY
SERVO CAPSTAN SHOULD TURN CLOCKWISE WHEN VIEWED FROM THE CAPSTAN AN0 UNDER THE FOLLOWING AIRCRAFT ATTITUDES:

AILERON-LEFT BANK ELEVATOR -PITCH UP RUDDER-RIGHT YAW

@ POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE T H A N ONE EPPT. THIS WILL BE INDICATED IN THE
INTERCONNECT POWER COLUMN B Y A LETTERWITH AN OCTAGON SYMBOLAROUNOIT,CAPITAL LETTERSFDRDCANO LOWERCASE
LETTERS FOR AC.

-
A 2 8 VOC DIMMING CIRCUIT G - 2 8 VOC 1 AMP -
a 5 VAC DIMMING CIRCUIT -
e,h 1 1 5 VAC 1 AMP
B,C,O,E -
2 8 VOC 5 AMP b,c,d - 1 1 5 VAC 2 P.MP -
f 1 1 5 VAC 3 A M P
@ THE GO AROUND RELAY IS INSTALLED I N CONJUNCTION WITH APPLICABLE FSB FOR WINGS LEVEL, PITCH UP GO AROUND. GO AROUND
BUTTON IS NORMALLY OPEN AN0 NORMALLY IS INSTALLED ON CONTROL COLUMN WHEEL. TO DEACTIVATE GO AROUND PROVISION
REMOVE THE RELAY AND CONNECTTHOSEWIRESTOGETHERTHATARECONNECTEO B Y T H E NORMALLYCLOSED CONTACTSOFTHE RELAY.

@) WHEN OPTIONAL 5 9 0 A - 3 h SERVICE BULLETIN NO. 3 IS INCORPORATED, THE FOLLOWING INTERCONNECTING WRING CHANGES ARE
APPLICABLE:
REMOVE CONNECTION BETWEEN J1 (BP)-38 OF THE562C-4 AUTOPILOT A W L I F I E R AND JldOF THE 614E-2G PEDESTAL
CONTROLLER AN0 JlA(TP1-47 OF THE 562A-5G FLIGHT COMPUTER.

MAKE CONNECTIONS AS SHOWN BELOW.

PEDESTAL FLIGHT ALTITUDE AUTOPILOT
CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMPLIFIER
6 1 4E-2G 562A-5G 590A-3A 562C-4
J1 J1A J1B (J1) J 1 J1
I r P ) (BP) I r P ) (BPI
V- - ----ALTITUDE HOLD MODE t - - - - - - - - - - - - -3 4
4 7 - - - - - - - - 2 0 - - - - - - - - - - - - 38
c

ALTITUDE HOLD MODE +

TP1 - 4 1 4 5 - 0 5 4

AP-103F/FD-108 Sabreliner, Interconnecting

Mar 1/73 Wiring Diagram 22-03-00
Figure 450 (Sheet 4A) 401/70A,401/70B
 COLLINS
MAINTENAKCE
w
P I A G G I O PD-808 AP-IOBF F L I G H T CONTROL SYSTEM

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER MISC POWER WLIFIER WIRE FJNCTION SERVOS MISC DISCONNECT JdOX

331A-bA b1YE-2F 329&?A AILERON 121A-?

8 J1 52 Jl J1 J2 3316.3 Jl

-
(Jl)

-
b
7
8

10
9 -
e?-
P I T C H ATTITUDE ERROR

-+
: 5 6 P I T C H ATTITUDE ERROR C'
ATTITUOE SERVO DRIVE M2
PITCH
PITCH
ATTITUDE SERVO DRIVE C
PITCH
ATTITUDE RATE G2
H'

28
27
25
-
-
- :
:
:
BY
23
:
:
:
:
:
:
:
:
:
:
:
:

VERT
13
1Y
-+
+AILERON FIELD N W R 1

AILERON SIGNAL C
AILERON EXCITATION C
A
B
C
E

11-6

Y2
Y3
-
1 -+MANUAL
2 -

Y Y e?-
6
PITCH
ATTITUDE RATE C2
P I T C H COMMAND H '
MANUAL P I T C H COMMAND C'
2b

V-BAR P I T C H COWAND SERVO DRIVE M I a 11

V-SAR P I T C H COMMAND SERVO DRIVE C
:
:

IO - .
3b
2b
:
:
: :

I
REF
: 3320-11
(Jl)

Ii
15 -AILERON
Ib
+
-
!
E
-+
11 -X+
I?
POSITION EXCITATION H
AILERON RATE EXCITATION H
AILERON POSITION SIGNAL
AILERON SERVO GRD
AILERON RATE SIGNAL
G
H
L
R
S

-
V-BAR P I T C H C O W D RATE 8 : '
95 - 6 V-BAR P I T C H COMMAND S I C C O M A 9 : I !Ii
YO -
41 -
3
-
9

-
6
V-BAR P I T 0 1 POS XMTR X
V-BAR P I T C H POS XMTR Y
P I T C H ATTITUDE CT X : 30-A AILERON ENGAGE VOLTAGE
(52)
c

-
Y P I T C H ATTITVDE CT Y : 20-0 AILERON ENGAGE VOLTAGE F
5 P I T C H ATTITUDE CT Z C
17 __C__ BANK ATTITUDE CT X : : 30-D
18 BANK ATTITUDE CT Y : 2 0 - E
19
20 f
BANK ATTITUDE CT 2
5+ BANK ATTITUDE ERROR H ' . . . F ELEVATOR
33Y6.3
2 1 e& BANK ATTITUDE ERROR - C'
- (Jl)

-
:
22
23
:
:
BANK ATTITUDE SERVO DRIVE M2
BANK ATTITUDE SERVO DRIVE C
22
- : : tELEVATOR F I E L D N L M E R 1 A
0
24 e? BANK ATTITUDE - RATE G2 19 : : :
:3i +ELEVATOR F I E L D N U B E R
++ ELEVATOR SIGNAL
-
2 C

-..
--
25 BANK ATTITUDE RATE C2 20 : : : : 13 C E
3b
37 :
V-BAR ROLL COMMAND SERVO DRIVE M2
V-BAR ROLL COMMAND SERVO DRIVE C
28
27
:
..
:
:

..
:
a :
:
:
19
15
lb
- ELEVATOR
ELEVATOR
--.5t ELEVATOR
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION H
F
G
H
38 V-BAR ROLL COMMAND RATE 6 2 : 25 : : : 12 - - - - S t ELEVATOR P O S I T I D N SIGNAL L
39 -6 V-BAR ROLL COMMAND S I G CDM : 2b : : H -GRD : I1 ELEVATOR SERVO GRD R
: a : : :

-
31 V-BAR ROLL PDS XMTR H l 17 - - - - 5 t ELEVATOR RATE SIGNAL S
35 -6 V-BAR ROLL POS XMTR C1 23 : : I G
115 VAC ATTITUOE POWER ; : : :
GYRO MON + 29 : : 1 0 - N
31
:
:
- 18
Y -
GYRO HIGH LEVEL FLAG +
GYRO HIGH LEVEL FLAG
STEER FLAG -
- 31
32
: 2
:
:
:
:
:
:
:
: NAV
ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGAGE VOLTAGE
(J2)
J
H
STEER FLAG : : 28 RCVR
: : : SlRV-1
: lb -t28 M C FLAG POWER I : 54 (TP)
33 : IO -GLIDE SLOPE DEV + W RUWER
3Y : 11 - G L I D E SLOPE OEV + OY . 2 2 - 9 33YC-3
35 : 12 - G L I D E SLOPE LOW LEVEL FLAG + : : : 2 1 (Jl)
3b : 13 - G L I D E
:
SLOPE LOW LEVEL FLAG
G L I D E SLOPE HIGH LEVEL FLAG +
- :
:
:
11-27
: 22 fRUDDER F I E L D N W E R 1
+28 VDC
A
0
: STY- COURSE RESOLVER A
... .. . .. :
(BP)
1E
Y3
fRUDDER F I E L D NUWER 2 C

- RUDDER SIGNAL C E

--
: VORlLOC DEV + LEFT
29
28 :
b
5-
9-
VOR/LOC DEV + RIGHT
+
:
:
:
: -
31-90

11 -
22 39
YY
Y5
-+
RVDDER
RUDDER
EXCITATION C
P O S I T I O N EXCITATION H G

2 :
:
:
: 5TY-
VOWLOC HIGH LEVEL FLAG
LOC FREQ VOLTAGE +
COURSE RESOLVER B
:
:
:
:
:
:
43
:
- 50
38
22
Yb
Y2
Y1
-* RUDDER RATE EXCITATION H
WDDER P O S I T I O N SIGNAL
RUDDER SERVO GRD
H
L
R
: -+
Q 8
3
Y
5
:

:
:
:
:
STY-
: ST+
5-
5 6
COLRSE RESOLVER H
COLRSE RESOLVER C
COLRSE RESOLVER D
COURSE RESOLVER E
. .
:
:
:
:
21
23
24
25
Y7 RUDDER RATE 9 0 1 A L

RVDDER ENGAGE WLTAGE

S
(JZ)
0
RUDDER ENGAGE VOLTAGE C
b f : 5- COURSE RESOLVER F . . : 2b
7 : : S b COURSE RESOLVER G : : : e 7
VORlLOC FLAG +
31
32
2b
:
:
:
VOR/LOC FLAG -
TO-FROM ARROW ( + TO)
: :
:
:
:
Y1
42
Y3
TRIM
COWLER
IblA-1A
27 : TO-FROM ARROW ( + FROM) : : 49
: : : RAD ARMUP m (J1)
Y
: : : ALT TRIM UP w b
: : : 8bOF-1 RELAY GRO u 2

--
: : : (BP) FAILLCIE WARNING L I G H T m 5 TO AIRCRAFT
: + : : ARM DN
w
: @
50 RADIO ALTITUDE FLAG
5 1 __C_ RADIO A L T I T W E FLAG
: 17 -5- + AUX DC ALTITUDE
- : :
:
r
12
u
17
T R I M DN
RELAY GRD
27
29
31
T R I M SYSTEM

: 53 4 4 - -
AUX DC ALTITUDE f
... :
. :
. 'tb GRD GRD 1

.. ... ... @ i 115 VAC POWER

m
8
. . L

-
T R I M ENGAGE VOLTAGE U 20
... .. .....
M
TRIM ENGAGE GRD
- 32

....
: 3b -d+ T R I M INPUT DN 22
.
: k ...
.... ....
.
: 35
3Y -5-
T R I M INPUT DN +
ELEVATOR TRIM INPUT UP - 2Y
11
:
:
j
h ... 33 -5- ELEVATOR TRIM INPUT up t 13
i .._ .. . -33 :
:
... .... ....
-334
m
n
. - : . -
-53
52
:
:

AP-103F/FD-108 Piaggio PD-808, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 451

May 1/67 22 -03-00

Pages 401/71, 401/72
 MAINTEKANCE
COLLINS
wv MANUAL

PIAGGIO PD-808 W-IO3F F L I G H T CONTWL SYSTEM

AUTOPILOT EMERGENCY
AMPLIFIER WIRE FUNCTION
. -_-. ..
FI T C Y T
SERVOS MISC DISCONNECT J-BOX
ANNUN- COURSE PEDESTAL DIRECTOR INSTRWIENT FLIGHT 5bPC-4 AILERON l2lA-2
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER CMUTER COWASS POWER Jl J1 33463 J1
(Jl)
331A-bA b14E-2F 329&7A
Q J1 52 JI J1 J2

.- .. -+
:
:
COMPASS MON
COWWS MON
:
:
30
29-
:
14-
: I?
25 .. ..
9
c 1; . . C M W S DATA X
.. .. .. .: 2 :

'9 I=:1 COWASS DATA Y s3

.. .. .. . :
. .
I1
:El:- .. ...
COMPASS DATA Z - 4
: : : I 1
:
f 49 -
- C W A S S UATA X
. . . :
:
:
:
:
:
:
:
4
3
:
.
:
50
51
-- COWASS N T A Y
COWASS DATA Z
30
: 24
f
:
COMPASS FLAG t
COMPASS FLAG - I 31
3 2 :
:
:
: 27-GRD
:
. .
-
f
: 15 26 VAC H f f i PWR : 15 : : 22- 5 :
: I b . f COWN : l b : : 30- 1 :

.. ..
: 20 : 5- HEADING ERROR SYNCHRO C' f 1 7 : : :
: 21 : 5 6 HEADING ERROR SYNCHRO H' 1 8 : : :
:
:
13
14
:
:
5- HEADING RATE G2
5 6 HEADING RATE C2
.
:
1
2
9
0
:
:
:
: . .
: 12 H f f i MOT CONT C1 : a : :
: I1 Hffi MOT CONT M I : 2 2 : : AIRSPEED
: :

- ..-
: 4 HEADING DATUM SYNCHRO C' 23

12
: 5
:
HEADING D A M SYNQlRO H '
COURSE DATUM SYNOIRO C' I f
: 33
2Y
MK
8bDE-Z
.. SENSOR
59E-2
(JI)
13 COURSE DATUM SYNMRO H ' f 34 (J1) 59 AIRSPEED SIGNAL
. . .
45 f DISTANCE INDICATOR FLAG +
- 58
..
AIRSPEED EXCITATION H

..
4b : DISTANCE INDICATOR FLAG f 10 bO P AIRSPEED EXCITATION C
47 : DISTANCE INDICATOR 2 b VAC H 2
48 f f DISTANCE INDICATOR 2 6 VAC C
. .- .. 1
W--J
50
:
DISTANCE INDICATOR UNITS SYNCHRO X f : : 4 . .
51
52
DISTANCE
DISTANCE
INDICATOR
INDICATOR
UNITS SYNMRO Y
TENS SYNCHRO x
f
f
:
f
t
f
. 3
b . .
. 3 5
54
DISTANCE
DISTANCE
INDICATOR
INDICATOR
TENS SYNCHRO Y
HUNDREDS SYNCHRO X
: . . . 7
. 55
- DISTANCE INDICATOR HUNDREDS SYNCHRO Y
. .. .. .- 8
.. ..
.-
.-
. f .

.-
..
.. .
48
32
33
-
-
e&-
.
2 b VAC COMMAND WR
2 b VAC A T T I T W E PVR
2 b VAC ATTITUDE PWR COM -
.
12
15
lb
...
:
:
:
...-
:
:
:
....
:
:
: :
: .
..
.
..

24
25
.. ..
: 19
20 -55 VAC LIGHTING WR
VAC LIGHTING PWR COM
- . - ce>
-
f

-. . : : DC GRD i- i 4 - i
.-E,
. .
...--
:
.. : :
115 VAC
115 VAC
HEADING PWU
ATTITUDE WR 4 5b .. ..
. 9 +28 M C WYER 4 : 54 ;
.. ..- e tP8 M C SERVO CLUTCH POWER +g : b :
: : .: .: : a, .-
... .... .... ....
.
..
...
..
.--- . . . . . c
: b l - G R
28 M C P O E R
D - p m : N
+
. . ... . RLODER SEW0 POWER

--
S
... .... ... .. @
b3 : 5-RUDER SEW0 P W E R T
..
....- . . .. .._ .. ... . 9 d- 0- AILERON SERVO POWER U

....
@ bl AILERON STRVO POWER V

.- . . . .3.- 3 1 ... .:_ D :

:@ bY
ELEVATOR SERVO POWER
ELEVATOR SERVO POWER
W
X GO W D
. .. P I T C H STEERING + LP - ._ -- -z .

-
: : . _ _ _ . I CnD-I

.. : : PITQl STEERING + & 4-21 : .. ..

.-- : : ROLL STEERING t LEFT
+ RIGHT
: 12 -C 3 1 :
. . : GO AROUND :
. -. L
: ROLL STEERING
GYRO WfS +
f
13
13 -21
41
:
YO :

-...
: :
.. K
J
HEADING M O M t
NAVlLOC MODE +
: 47
: 4b
b't
: Y?
:

. ..- : : 4Y-44 - :

.. .. H
. . APPROACH MODE +
:
:
.

: Y 5
1- Y .

:
d :

: 48 -APPROACH
WPROACH ,MDE
IWE
+
+
v- . I

. . :
:
:
:
EXTSTR+DN
EXT STR + U P
: 27
3 7 7 ; i . - :
.
I
I
ALT HOLD
.. f
.- - w
. . ALTITUDE HOLD INTEWIOCK ALTITUDE lOLD INTERLOQ( - - 1
I
t
... .._ .. . -.- ...
: : Y b : ALTITUDE IMCD I N T E R L O M
... ....- .. : I
.. .. .
-
- 1

... ... .... .. : I

.. .- . :
- bb DISCONNECT SWITCH H
f
39 - 45
. .-
: b? DISONNECI SWITW C
. . : : GLIDE S L W E W E +
.. .. . .
Yb PILOT'S
DISCONNECT
COPILOT'S

.: ::: ALTITUDE :
-. ...
SWITCH
.:
-
CONTROLLER :
.. .. . .
.. -. : ( J 1 ) .
SqDA-3A

.-
.
..
.
V

:
:
:
:
:
:
:
:
A L T I T W E HQD WADE t
ALTITUDE RATE H ' - 5 9
ALTTMERATEC'-/
ALTITUDE ERROR H ' + \
ALT1TU)E ERROR C' -'
I '.
:
:
:
:
. 47-
34
2Y
33-
23-27
- 3Y
I4
15
I b
@ I
:
I
.
*I
42
.

AP-1 OSF/FD-108 Piaggio PD-80 8,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 451 (Sheet 2) Pages 401/73, 401/74
 COLLINS MAIKTENANCE
w MANUAL

PIAGGIO P D - 8 0 8 AP-103F F L I G H T CONTROL SYSTEM

FLIGHT
ANNUN- COLRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTITUDE AUTOPILOT MRENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AHPLIFIER CWUTER CONTROLLER POWER AMPLIFIER WIRE FUHCTION SERVOS MISC DISCONNECT J-BOX

331A-U blYE-ZF 329B-7A AILERON 12lA-2

@ J1

-..
J2

...
J1 J l

12 -
-
J2

PITCH BOOTSTRAP TRANSMITTER X : : : 3 9 : Y3 -

- ALTITUDE GAIN CHANGE EXCITATION
33YC-3
(Jl)
J1

..
..
..
..
13
19

-
-
P I T C H BOOTSTRAP TRANSMITTER Y
PITCH BOOTSTRAP TRANSMITTER 2
P I T C H BOOTSTRAP EXCITATION H
:
.. :.. :
:
w
Y3
:
:
9V
95 - ALTITUDE GAIN CUNGE NO. 1
ALT1TU)E GAIN W G E NO. 2

-
15 __C_
l b P I T C H BOOTSTRAP EXCITATION C : : : 35-
. .
..
..
..
-
..-
2b
27
28
- BANK BOOTSTRAP TRANSMITTER X
BANK BOOTSTRAP TRANSMITTER Y
BANK BOOTSTRAP TRANSMITTER Z
:
: 15
: :
:
37-GRD
.
:
59-COkPuTER
18 *+
M3N +
EXT P I T C H STEERING A

i'" ;
:
:
:
20
21
.
22
.-
t

.
..
29
30

.
.
_C_

.
.
BANK BOOTSTRAP EXCITATION H
BANK BOOTSTRAP EXCITATION C
HEADING WARNING DATA X
HEADING WARHING DATA Y
HEADING WARNING DATA 2
HEADING WARHING DATA H
HEADING WARNING DATA C
HEADING WARNING DATA H'
HEADING WARNING DATA C'
: 18

18
t
I
;
.
t
;
.
19 -b
2?

57
19
25

bO-KTWDOFF+
-+
-+
EXT P I T C H STEERING B
-+
AC P I T C H STEERING A
2 b -bbAC P I T C H STEERING B
++
PROQSSED PITCH DATA A

-
28 -----56 PROCESSED P I T C H DATA B
INTERNU. P I T C H STEERING OFF

EXT ROLL STEERING

EXT ROLL STEERING B
A
+

-
25 PROCESSED B W K OD A
2 b -ebb PROCESSED B M K CmD B
... .. .. -+
.....
35 PROQSSED BAw( DATA A

.. . . 3
55
b
-
+
' U b PROCESSED BMK DATA B
EXT LMNK CMD 0
. . - SY
.. ..
EXT BAM( QID A

--
: P I T C H MONITOR + : 12 12 :

.. ..
GSARM ; GLIDE SLOPE ARM. ANN. : b : :
OS EXT : GLIDE SLOPE EXT. WN. I 9 2 : :

G S W T
.: . .
t 38
.- RUWAY FLAG - . . . . ; 5 : :
.. ...
.. ..- : : : : IKRBCN
.
-
-
: : : :Rcm
GO AROUHD ANN. t lb : 512-Y . .
.
:
.
: M I D D L E W R
: :
: Y3-Y
: : (J1)
. .
: : : 1 8 57 INTERNAL ROLL STEERING OFF +
i PITCH CONTROL EXC A : 21 NAV : 5lRv-1
B P I T C H CMFlROL SIGNAL : 20 CONT : SELFJEST
.. .. .. .. -. ..
C
0
E
P I T C H CONTROL EXC B

TLRN w m m L EXC A
.. .. 21
. 22

:
313N-3 : RELAY

b N R N CONTROL EXC B 22 :
G NRN mmoL SIGNAL 20 :
N I N 1 MOTOR CONTROL VOLTAGE - b2
P I N 1 2 b VAC WTOR EXCITATION C a :
R I N T MOTOR RATE S I G N K : b3
S
T
I N T MOTOR SIGNAL COMQN
28 VDC PANEL L I O H T PYR Q: .-.
:
...
2Y

U
. . GRD
. . .. .. .GQD ... ...
X
:
:
:
Y

a
z . . ENGAGE VWTAGE

ENGAGE PULSE
.. .. .. .. .. ..
T 5
..
6
: b DISENGAGE M L T A G E
ENGAGE READY t
. 37
55
C

..
A L T I M E W D YODE + ... ... ... ... .. T
... 3 ...a
.. .
f
P
HEADING SYNCH CUTOUT
1 1 5 VAC AUTO P I L O T WR- Q
3 8
.. .:.
:

q 1 1 5 VAC P W E R 7
I I N T 2 6 VAC WTOR EXCITATION H 23 :
5
t . . ENGAGE INTERLOCX

U
v
U

X .
..
. . . .. .. . : 53 - YAY D M R ENGAGE KIN + I

..
-
Y SPARE 9 SENSING
2
. .... .... ... .. ... .. UNIT

-
@
. ..
M 33)SWB :
88
cc . . .. .. .. .... .... . (ROLL) : YAW D A W SY

..
} -
b5 ROLL RATE MOTOR GRD A
... ...
..... .
DD 8 115 VAC PCUER B
EE
FF
HEADING M D E
NAVILOC Lwx Q .... ..
..
...
.. .. .. 32
31
ROLL RATE EXCITATION C
ROLL RATE E X C I T A T I Q I H
E

-.. . E SIGN& x
GG APPROACH MOM
.. 29 ROLL RA
...
G

... ... ._
m
. . HOC€ VOLTAGE H
. . .

AP-103 F/ FD- 108 Piaggio PD-8 0 8,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 451 (Sheet 3) Pages 401/75, 401/76
 a
COLLINS
MAINTENANCE
%w MANUAL

PIAGGIO PD-808 W - l D 3 F F L I G H T CONTROL SYSTEM

FLIGHT
AWUN- COCRSE PEDESTAL DIRECTW INSTRMNT FLIGHT AUTOPILOT SENSING EblEffiENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE NNCTLW AMPLIFIER CCWUTER MISC POWER MPLIFIER WIRE FUNCTION SERVOS WIT DISCONNECT J-WX
331A-bA blqE-2F 329817A 3WC-lD 5b2A-50 15 Sb2C-+ AILERON 1 2 M
9 J l 52 J l J1 J2 J1 J2 JlA JIB J1 J1 33Yc-3 33YWB 8 J I
(TP) (e?) (TP)(Bp) (TP) (BP) (J1)

.. .. 21 -
- P I T C H DIFFERENTIAL RESOLVER X . ... .. ._
._ .. . .. . - (PITCH)
.. .. 22
23 -
-
P I T C H DIFFERENTIAL RESOLVER Y
P I T C H DIFFERENTIAL RESOLVER 2 . ..
.. ..
:
:
8
IO -
-
P I T C H RATE MJTOR ORD
115 VAC P W E P
A
0

... ...
2y
-
-
P I T C H DIFFERENTIAL RESOLVER H
.. .
. ... ... : 32
- P I T C H RATE EXCITATION C E

..-
25 P I T C H DIFFERENTIAL RESOLVER C
.._ : 31 P I T C H RATE EKCITATION H F

$1 -
2b PITCH D I F F E R E N T I N ESOLVER H I
-. ... .... ... . ..
: 29 P I T C H RATE SIGNAL X G
27
- PITCH DIFFERENTG RE~MZR c*
.. ..
. 28
- BAM DIFFERENTIAL RESOLYFR X .

-
YAW RATE
29
- BANK DIFFERENTZAL RESOLVER Y .. .. .. . - mm
... ... -
-
: BIN( DIFFERENTIAL RESOLVER 2
..- ...
30 33262
31
- BAM( DIFFERENTIAL RESOLVER H . .. .

-
bb YAW RATE MOTM ORD A
. . .
.. ..
32
33 -
-
BAM( DIFFERENTIAL RESOLVER C
BANK DIFFERENTIAL RESOLVER H' .. .. ... ...
1D
51
115 VAC POWER
YAW RATE EXCITATION C
B

. .
39 B W DIFFEREHTIAL RESOLVER C'
... .- .. 5D YAW RATE EXCITATION H

. . Y8
. . YAW RATE SIGUAL X G

SYWBOLS USED: WHEN OPTlONAL590A.3ASERVlCE BULLETIN NO. 3 I S INCORPORATED,

@ THE FOLLOWING INTERCONNECTING WIRING CHANGES ARE APPLICABLE:
ID. THE 5b2C-Y AND 5 b P k 5 G SHMJLD BE K l W E D AS CLOSE TOOETHER AS POSSIBLE.
S? W I S T E D SHIELDED PAIR-ADJACENT PREFERABLY ON A UJN M3UNT. THESE SIGNAL LEADS MUST BE TWISTED AND WIRED
S4 WIRES AS SHOWN ON DRI\WING POINT TO POINT BETWEEN THE UNITS. THE TWISTED PAIRS SHOULD BE KEPT AS
SG SHIELD T I E D TO GROWD AT U N I T SH&T AS PRACTICAL AND MJST U S 0 BE SHIELDED I F OVER No FEET LONG.
SI SINGLE SHIELDED WIRE 11. CO~PWTOR WARNING RESOLVERS. m
NOT USE FOR OTHER PVIPOSES UNLESS LOADING
' 6 ALL SI SHIELDED T I E D TO X 1 ETC.
NOTES
STY F O W WIRES W I S T E D WITH SHIELD
12.
EFFECT I S EVALUATED.
TOTAL WIRE RUN FROM BUSS TO 111A-Z TO 5 b 2 W TO 3 3 6 3 ( P I N B) FOR EACH
PRIMARY SERVO MJST NOT EXCEED 9D FEET I F AWG 20 WIRE I S USED. YHEN WEATER
MAKE CONNECTIONS ASSHOWN BELOW
PEDESTAL FLiGHT ALTiTUDE AUTOPILOT
CONTROLLER WIRE FUNCTION COMPUTER CONTROLLER AMPLIFIER
l"90 FEET, INSTALL T E W N A L S AT 5 b 2 W mwwT AND R f f l AWG 20 WIRE FROM
NOTES: 5b2C-9 lU TERMINAL AND AWG l b E R E FROM TERMIN4 3YYC-3 P I N 8. G14E-2G 562A.5G 590A.3A 562C.4
13. AN ISOLATED MODE SWITCH I S PROVIDED FOR USE WITH COPILOTS F L I G H T DIRECTOR- Jl JlAJlB fJ11 J1 Jl
1. ALL WIRE S I Z E S ARE NO- 22 M E S S DESIGNATED OTHERWISE BY NLWERS I N SQUARES. 1'). A 1% OHMS 1/2 WATT l D % RESISTOR I S R E W I R E 0 ON EACH T R I M I N D I C A T W MOVEMNT- iTPl [BPI iTP1 (BPI
SHIELDED WIRES ARE GROUNDED AT ONE END ONLY. WITH T R I M INDICATOR CONNECTIONS AS S H W N AND THE REVERSING L I N K S INSTALLED .................
V ALTITUDE HOLD MODE+ ... ... ...................... 34
2. SHIELDS ON THE NAY RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE FOR CORRECT SERVO PHASING 'WE P R I W SERVO UPSTAN SHOUD TLRN CLOCKWISE ALTITUDE HOLD MODE+ 47 .................... 20 ........ ............................. 38
GROLWOED AT THE 5lRV-I. V M N V I E M D FROM lHE W S T M END UNDER M E F O L L W I N G A I R C W T A T T I l W E S :
3.
?.
F O U I WIRES TWISTED WITH SHEILD FOR W A T I B I L I T Y I N FUTURE ARINC INSTALLATIONS.
A RELAY WST BE INSTALLED I N M E AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF
TEST FEATUIE OF T N 5 l R V - 1 W E N THE AUTOPILOT I S ENGAGED.
AILEROW -- RIM1 W K
5. WE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N T H I S DRAWING REFLECTS
LOADS AS FOLLOWS:
ELEVATOR
RWDER - PITCH UP
RIGHT YAW

15- PWER m M A PARTICULAR CIRCUIT WSAKER OR FUSE MAY PROVIDE W E R FOR MORE
AFCS L O M CIRCUIT R E W I R E D LOAD ADDITIONAL LOADS Tnuc ONE EQUIPMENT. -THIS-WILL BE INDICATED 1N-w INTERCONNECT POWER COLM
BY A LETTER WITH AN OCTAGON SlhBoL *ROW0 I T , U P I T A L LETTERS F U ? DC AND LOWER
200 OMS TO-FROM 1DD O M S JUK'ER B P 4 3 TO W-33 OF 5 l R V - 1 CASE LETTERS FOR AC.
500
5DD
M S
MHls
GLIDE SLOPE POINTER
GLIDE SLOPE FLAG
200 Ow
250 OHMS
JWER
JUWER
TP-8 TO TP-2 AND TP-3 OF 51RV-1
TP-21 TO T P d b OF 51RV-1 A - -
28 VDC DIMMING CIRCUIT a - -
5 VDC DIMMING C I R C U f T

-- -
5DD O W LOC FLAG 250 O W JUWER BP-32 TO W d t l OF S I N - 1 b, c. d
5DD 04% CMRSE BAR 200 OMW JUWER BP-39 TO W-3p AND EP-W OF 5lRV-1 0 -
Bo CP DI E 28 VDC 5 W
28VDClAW e
f
g
115 VAC INU
115 VAC 1 NU
115 VAC 3 MP
b. THE P O K R FOR THE COWASS SYSTEM MlST BE OF THE S A M PHASE AS THE REST OF THE
AUTOMATIC F L I O H T CONTROL SYSTEM- Ib. WE GO AROWD RELAY I S INSTALLED FOR WINGS LEVEL, P I T C H U p GO AROUND.
?. POWER LEADS DENOTED BY ''DIM'' SHOULD BE T I E D TO C O W I T L I G H T DIMMING CIRCUITS. GO AROUND W O N I S NCRMALLY W E N AND NORMMLY I S INSTALLED ON CONTROL
8. SENSING W I T 315A-Y( ) AND RATE GYRO 332C-Z S W D BE LOCATED AS CLOSE TOGETHER C O L W W E E L - TO DEACTIVATE GO AROUND PROVISION REKlVE THE RELAY AND
AS POSSIBLE. mNNECT THOSE WIRES TOGETHER TWT ARE CONNECTED BY THE W W L Y CLOSED
9. ANNWCIATORS CHOSEN MJST NOT EXCEED 100 MA. A C W N +18 VDC I S USED FOR CONTACTS OF THE RELAY.
ANNUNCIATOR POWER. ANNUNCIATION VARIES WITH THE PARTICULAR INSTALLATION. 1). EQUIPMENT SHOWN I N MlSC C O L W S MAY NOT HAVE COWLETE WIRING I N F O W T I O N
DEPENDING W O N DESIRED OPERATION. S P E C I F I C ANNUNCIATORS MAY BE DELETED. INDICATED. BEFORE WIRING PPPLICABLE SYSTEM MANUALS FOR M T EQUIPMENT
SHOULD BE CHELYED.
18. PROVISIONS FOR RADIO ALTIMETER (OPTIONAL).

AP-10 3F/FD-108 Piaggio PD-80 8,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 451 (Sheet 4) Pages 401/77, 401/78
 COLLINS
XAISTENASCE
MASUAL

OZARK FH-227 AP-103F

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AhPLIFIER COWUTER MISC POWER AMPLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

331A-bK blYE-2Gl 32%-7M 399C-lD 5bZA-5G AILERON 121A-Z

Q J l J2 J1 J1 J2 J l 52 J1A J I B 339C-3 J1

-
(TP) (BP) (TP)(BP) (J1)

b
7-
8
6
f 5+
P I T C H ATTITUDE ERROR H I -29
P I T C H ATTITUDE ERROR C '
P I T C H ATTITUDE SERVO DRIVE M2
23
28
:
:
:
-
-
:
:
:
:
:
:
i 1Q bz -85~~L~ER
: 5 - +AILERON
FIELD N W E R 1
F I E L D NUWER 2
B
A
C
9 : P I T C H ATTITUDE SERVO DRIVE C- 27 : : : 13 : 5- AILERON SIGNAL C E
10 I 5 7 - P I T C H ATTITUDE RATE G2 25 : : : VERT 19 : AILERON E X C I T A T I O N C
11 : 5 6 P I T C H ATTITUDE RATE C2 2b : : : REF 15 : AILERON P O S I T I O N EXCITATION H G
: 50 4 7 - MANUAL P I T C H COMHAND H ' I 3b : l b . 5 t AILERON RATE EXCITATION H H
: :
-
51 46 MANUAL P I T C H COmMND C ' f 2b 12 : 5 t AILERON P O S I T I O N SIGNAL L
92 f V-BAR P I T C H COMAND SERVO DRIVE M 1 a 11 : : 11-X+ AILERON SERVO GRD R
93 : V-BAR P I T C H COMAND SERVO DRIVE C 10 : : 17 I 5 t AILERON RATE SIGNAL S
94 f 5 7 - V-BAR P I T C H COMAND RATE f E : :
95 : 5 6 V-BAR P I T C H COMAND S I G COM f 9 : :

-
90 : 5 F V - B A R P I T C H POS XVR X f 7 : :
91 f 5 6 V-BAR P I T C H POS XMTR Y f b : : (52)
3 . P I T C H ATTITUDE CT X f 30-0 AILERON ENGAGE VOLTAGE E
9 P I T C H ATTITUDE CT Y : Bo-* AILERON ENGAGE VOLTAGE F
5 P I T C H ATTITUDE CT 2 . . .
17 f BANK ATTITUDE CT X f : 30-0
18 : BANK ATTITUDE Cl Y t t 2 0 -
. . . ELEVATOR
20
21
22
23 - :
I
f
5+ BANK ATTITUDE ERROR H'
5 6 BANK ATTITUDE ERROR C'
BANK ATTITUDE SERVO DRIVE M I - 2 2
S A M ATTITUDE SERVO DRIVE C 21 -
18
17
:
:
:
:
:
:
:
:
:
:
:
:
C- ELEVATOR F I E L D NUMBER 1
33YC-3
(Jl)
A
B
29 -7-
25
3b
37

38
-
-+
:
I
6 6
BANK ATTITUDE PATE 62
BANK ATTITUDE RATE C2
V-BAR ROLL COmAND SERVO DRIVE M2-28
V-BAR ROLL COWND SERVO DRIVE c

V-BAR m L L COWD RATE ~2

19
20

- :
27

2
:
:

._ .. . .
5
:
:
:
:

: :
:
:
:
:
:
:
:

:
-
13 - - - - 5 C ELEVATOR SIGNAL C
19
15 -ELEVATOR
l b
12 MC-
MC-
ELEVATOR EXCITATION C

ELEVATOR
P O S I T I O N EXCITATION H
RATE EXCITATION H
ELEVATOR P O S I T I O N SIGNAL
C
E

G
H
L
39 : 5 6 V-BAR ROLL C W D SG
I CQM : 2 b : : : 11 -+ ELEVATOR SERVO GRD d
3 4 -7- V-BAR ROLL POS XMTR HL : 2 9 : : : 17 MC-ELEVATOR RATE SIGNAL S
35 -

31
:
:
6

- 18
:

9
-
-STEER
V-BAR ROLL POS XMTR C 1
115 VAC ATTITUDE POWER
GYROMON+
Gym HIGH LEVEL FLAG

-
GYRO HIGH LEVEL FLAG
FLAG
+
-
5
29
31
32
:

.
23 :
I
:
;
:
2
:
:
f
:
:
:
:
10
:
:

: NAV
0-

*
:
ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGAGE VOLTAGE
J
H

i:
:
3 -
-
STEER FLAG
STEER FLAG c
2 :
:
I
:
28
:
RCVR
51RV-1

33
: :
l b
10 -
-
+28 M C FLAG POWER
G L I D E SLOPE DEV + W
G L I D E SLOPE DEV + DN
f
:
-
32-0
f 59 (TP)
m :
:
RUDDER
39
. :
11
-
- GLIDE SLOPE LOW LEVEL FLAG +
;a-9 334C-3

-
35 12 : r : 2 1
: 13
:
G L I D E SLOPE LOW LEVEL FLAG
GLIDE SLOPE HIGH LEVEL FLAG +
- :
:
:
11
: 2 2
27
3-- RUDDER F I E L D N L W E R 1
(J1)
A
B
BACX COLRSE 1 f : 5T't COURSE RESOLVER A . I : l b C
: :
b -VORlLOC
: (BP)
RELAY K1 :
DEV + L E F T : . .: 93 :
. 5- RUDDER SIGNAL C E

5 - VORlLOC OEV + L E F T
VORlLOC OEV + RIGHT
:
:
.
:
I
3

22
I
:
:BACX COLRSE
44
95
9b
I
I 5-
RUDDER
RUDDER
RUDDER
EXCITATION C
P O S I T I O N EXCITATION H
RATE EXCITATION H
G
H

:
28

2 .
:
:
f
9
:
-
: -?T5
f 5-
VORlLOC DEV + RIGHT
VORlLOC HIGH LEVEL FLAG
LOC FREQ VOLTAGE +
COURSE RESOLVER B
COURSE RESOLVER H
+
f
. .i
I f
.

f
11
97-
f
-50
2
i!Q
35 RELAY K2 :

1
i
.
92
91
97
f
;
f
5

5
f RUDDER
RUDDER
f RUDDER
P O S I T I O N SIGNAL
SERVO GRD
RATE SIGNAL

RUDDER ENGAGE VOLTAGE

L
R
S
(J2)
B
f 51- COURSE RESOLVER C . . . RUDDER ENGAGE VOLTAGE C
t 57- COURSE RESOLVER D : : I 29
: 5 : f 5 b COURSE RESOLVER E : : I 25
b : f 57- COURSE RESOLVER F f . . 2b
7 : f 5 6 COURSE RESOLVER G f f : 27
: +
:
:
:
31
32
Zb : I
VORlLOC FLAG
VORlLOC FLAG -
TOJROM ARROW (+ TO)
;
:
:
.
.
:
r
:
:
9
9 3
91
2
TRIM
SERVO
334D-2-33D
: 27 : TO-FROM mow (+ FROM) : : : 4 9 (J1)
9b : P I T C H C O W D EXC H f f 5 3 :
97 f P I T C H COMMAND EXC C : f 5 1 :
: : : RAD ALT
:
-. .. : :
:
8bOF-1
(BP)
+
:
:
17-
53-
RADIO
RADIO
ALTITUDE FLAG
ALTITUDE FLAG - :
: I
.
:
:
12
11
B
TRIM
INDICATOR
50
51
:
: 5 6 -
5 7 - + AUX
AUX
DC ALTITUDE
DC ALTITUDE
:

.
I
f
f
._ . . 9 b
:
:
97 : CRD f f X t C R D
28VDC P W E R
EB
A
327D-1W

. ..._ ... . T R I M ENGAGE VOLTAGE L

... T R I M ENGAGE CRD M

-. _ ..
_ ._ . -+
.. . . ._. : 39 M + ELEVATOR T R I M I N P U T LP c-+
._ .- . : 33 -5- ELEVATOR T R I M INPUT L? F--

...
-. .... .._.
:
:
:
33
39
:
:
.
AILERON T R I M INDICATCR
AILERON T R I M INDICATOR ;a
+
..
-. .-. ._
.. :
53
52 .
RUDDER T R I M INDICATOP
RUDDER TRIM INDICATOR -
. .

AP-103F/FD-108 O z a r k FH-227, I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 1 of 4)

Figure 452
Nov 1 / 6 8 22-03-00
P a g e s 401/79, 401180
 a
C 0LLI N S
RIAISTESASCE
MANUAL

FLIGHT
ANNUN- COLRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT MISC AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR U I R E FUNCTION AWLTFIER COWUTER COMPASS @ POWER AMPLIFIER WIRE F'JNCTION SERVOS MISC DISCONNECT J-BOX

331A-bK blYEaG1 329817M 121A-Z

8 J1 J2 J1 J l J2 J1

: 18 HDG MOT CONT C l . 21 : 39 f

: 11 HDG MOT CONT M 1 - 2 2 : : AIRSPEED
: Y HEADING D A N M SYNCHRO C' ; . 2 3 : SENSOR
: 5 HEADING D A N M SYNCHRO H ' . ; 3 3 : 5506-1

13 f . COLRSE D A T W SYNCHRO H ' . . . I _ 59 : AIRSPEED SIGNAL

58 : AIRSPEED EXCITATION H
: : :
-. .. :
8bOE-Z b0 f AIRSPEED E X C I l A T I O N C
(J1)

, -
50 I DISTANCE INDICATOR W I T S SYNCHRO X : . : : 9
51
52
f
:
DISTANCE INDICATOR UNITS SYNCHRO Y
DISTANCE INDICATOR TENS SYNCHRO X
.: . : :
3
b
: .
.::
53 DISTANCE INDICATOR TENS SYNCHRO Y : : 5
59 f : DISTANCE INDICATOR HUNDREDS SYNCHRO X : : 7
.
55
.
f
98 I
DISTANCE INDICATOR HUNDREDS SYNCHRO
2 b VAC C O W D PUR
Y
12 :
:
:
:
:
8
:
32 -7- 2 b VAC ATTITUDE PUR 15 : : :
2Y
25
:
f
33
f
:
f
19
20
-
5 6 2 b VAC A l T I N D E PUR COM-

- 5 VAC LIGHTING PUR

5 VAC LIGHTING PUR COM
lb :
.
.
:
.
.
:
.
. I @ ; ;
: : r 5 7 :
. . :
:
DC GUD
115 VAC HEADING PUR
1-
.
1 A . l
5-55
:
.
BACK COWISE : 115 VAC A T T I N D E PM Y . : 5 b f
+28 VDC PWER- : 59 .
+aVDC E- . . .. ..
._
I SERVO CLUTCH P W R ~ b :
. .. ... ... : 9 :
rn
.- .
. .. ..
- - GRD :
: bl - GRD
28 VDC P W E R
U ' N

. ..
._
.
.._.
..
. .. (? @ b; . SG-
RUDDER SERVO POWER
RUDDER SERVO POWER

_.
.. ... .. . : 9
D
B

:
@ bl
:
:
5-
5 0 -
AILERON SERVO POWER
AILERON SERVO POWER
ELEVATOR SERVO POWER
V
W

:
BACK COURSE MODE +
P I T C H STEERING + Lp f
.
3-31
. 1 9
:
: OGk- io 12 b 4:----5+ ELEVATOR SERVO WWER X

P I T C H STEERING + . . __
-
DN 9-21 : I
.
~ ~~~~~ ~

: ROLL STEERING + LEFT 12 31 :

: ROLL STEERING + RIGHT f 13 21 :
: GYRO MODE + 13 f : 91 : YO :
: HEADING MODE + .. I 9 7 : b9 :
: NAVlLOC MODE + . 9b . . Y?

: BACK COURSE :
:
:
w-9*
19-
- I
:
GO AROUND MODE +
I RELAY K 1
-- :
..
H
. .. APPROACH MODE + .
:
.
45
.
; . 98 - APPROACH K)DE
APPROACH MODE
+
+
: EXT STR+ DN I
I
: EXT STR + UP
A L HOLD
~ I-. I.. i . .
I ALTITUDE HOLD INTERLOCK . . . A L T I N D E HOLD INTERLOCK I ,
I f
: 35 -
- SPEED CONTROL FLAG +
-
...
:

..
...
9b

._ . .
..:. ALTITUDE HOLD INTERLOCK
I

@ i: 99
Y5 -
-
SPEED coma
SPEED CONTROL DEV+
FLAG
FAST
.. .. ..
f~

: bb -
- DISCONNECT SUITCH H
I
I
t
97 SPEED comm DEV + SLOW
:
.. 39 - 95
.-_ ...
:
:
.
b7
Yb - DISCONNECT SWITCH C
GLIDE SLOPE K)DE + PILOT'S
m -F
COPILOT ' s

. 38- R W A Y FLAG - .. . .
DISCONNECT
SUITCH

AP-103F/FD-108 Ozark FH-227, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 452

Nov 1/68 2 2-0 3 -0 0

Pages 401/81, 401/82
 COLLINS
MAINTENANCE
Qv MANUAL

FLIGHT MISC
PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTIWDE AUTOPILOT EMERGENCY
ANNUN- COURSE
MPLIFIER COMPUTER CONTROLLER POWER AMPLIFIER WIRE FUNCTION SERVOS PISC DISCONNECT J-8OX
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION

331A-bK blYE-IG1 329&7M 121A-2

J1
8 J1 52 J1 J1 J2

:
.. : : 20 ALTITUDE HOLD MONITOR +
.. .. ._
... ...
i ALTITUDE HOLD MODE + I
.
r; -
- I
-
:
.
39'Q
. .
-
: ALTITUDE RATE H' 39 1')
: ALTITUDE RATE C' -6 . 29 15
: ALTITUDE ERROR H ' -----5\ : 33 lb : 91
: ALTITUDE ERROR C ' - 5 6 : 23-27 - 92
1 2 -PITCH
13
19
:
:
BOOTSTRAP TRANSMITTER X
PITCH BOOTSTRAP TRANSMITER Y
PITCH BOOTSTRAP TRANSMITER 2
:
:
:
:
:
:
: 3
:
:
9
9
9
2
3
.
f
99 -
Y3 -ALTITUDE

95 -ALTITUDE
GAIN CHANGE EXCITATION
A L T I N D E GAIN alANGE NO. 1
GAIN CHANGE NO. 2
15 : PITCH BOOTSTRAP EXCITATION H : : : 3b-
l b : PITCH BOOTSTRAP EXCITATION C : : : 35-$2
.
2b
27 :
BANK BOOTSTRAP TRANSMITTER X
BANK BOOTSTRAP TRANSMITER Y
BANK BOOTSTRAP TRANSMITER Z
:
15
: :
f
37-GRD
.: 59 - COMPUTER MON +
. . 28 f 18 ----5+ E M PITCH STEERING A

:
29 : BAN( BOOTSTRAP EXCITATION H . 19 -bbE M PITCH STEERING B
:@)
;
30 : BANK BOOTSTRAP EXCITATION C : 15 ---sJ+ AC PITCH STEERING A
. f HEADING WARNING DATA X . 2 b -6 AC PITCH STEERING B
HEADING WARNING DATA Y : 27 4 - PROCESSED PITCH DATA A
.
:
I
:
HEADING WARNING DATA Z
HEADING WARNING DATA H
HEADING WARNING DATA C
18
98
:
f
f
18:
28 -
57
bD:
-
-
6 Pmcsm PITCH DATA B

s+
INTERNAL PITCH :;TEERING OFF
ALT
EXT HOLD
ROLL OFF I G+
STEERN A
+
U
7

i r':
'I" i
: HEADING WARNING DATA H '
: HEADING WARNING DATA C' I iq
25
:
:
5
5-
6 EM mu STEERING
PROCESSED BANK
B
CMD A
@: YO . 2b : S b PROCESSED BANK CMD B
35 : S+ PROCESSED BANK DATA A
: 25 : 3b : S b PROCESSED BANK DATA B
: 7 55 : 5+EXT BANK CMC B
. : 17 : :
f,
: PITCH MONITOR +
- : 12 - 12 :
59 S 6 E X T BANK CMC A

- --
GS ARM : f GLIDE SLOPE ARM. ANN. : b :
GS EXT : : G L I D E SLOPE E M . ANN. : 92 : ALTITUDE M O N I T M POWER
N I L ARM : : NAVILOC ARM. ANN. : ; : b :
N/L CAPT . : : NAVILOC CAPTURE ANN. : : 3 9 :
. . .
PWR
GS CAP1 :
;
:
ANNUNCIATOR POWER
GLIDE SLOPE CAPTURE ANN. - :
. .5 _ .: . :
_
: : : M(R BCN
GA : GO MOUND ANN. - :
. l b
:

.! . .I . .I. .1 1 1 )
:RCM(
: 512-9
- .
: MIDDLE MAFDXER f 93-r
57 . : : l a : INTERNAL ROLL STEERING OFF +
i : PITCH CONTROL EXC A . . . : 21 NAV NAV : 51RV-1
0 . PITCH CONTROL SIGNAL w .~ 20 RCVR CONT : SELF-TEST
C : PITCH CONTROL EXC B . . . f 22
. . . 51RV-1 313N-3 : RELAY
D (52) (J2) :
t : TVRN CONTROL EXC A . . . 21 :
F TURN CONTROL EXC B . . . 22 :
G : N R N CONTROL SIGNAL . . . 20 :
N I N T MOTOR CONTROL VOLTAGE . . . : b2 27 .~
P : I N T 2 b VAC MOTOR EXCITATION C . . . 29 : n :
I (
I
R . I N T MOTOR RATE SIGNAL : b3 I
S : I N 1 MOTOR SIGNAL COmON . . . : 29 55 I (
, -
U
X
GRD
. .-
: f :
.- .GRD
K :

Y : ENGAGE VOLTAGE . . .
7 5 VAC PANEL LIGHT PWR : Q : I U I
a ENGAGE PULSE . . . .. 5b
- b DISENGAGE VOLTAGE . . . 37
ENGAGE READY _ . _ : 55
ALTITUDE HOLD MODE +
. . ..
._ .. . : 38
. .

W R U D E R CLLTCH VOLTAGE . . . 5b : I

: . . . I
M
X
Y
+28 VDC AUTO P I L O T PWR

SPARE
.
..
.
.
.
.-
:
:
53
9
- YAW DMPER ENGAGE MON + ' t
z
AA
88
cc
DD : GYRO M OM
.
..
._
.....
.
.._
.. .
..-_ _
.. .
.. .
.....
.
b5
8
- -
W L L RATE MOTOR CRD
115 VAC POWER
3395A-98
(ROLL)
A
B
@ :
: YAW DAMP SW I s
u 7'
1
EE
FF
GG
HH - :
:
.
HEADING MODE
N A V l L K MODE
APPROACH MODE
MOOE VOLTAGE H
_
...
...
...
...
.
.
.....
.
32
31
29
.
.
.
.
.
m L L RATE EXCITATION
m L L RATE EXCITATION
ROLL RATE SIGNAL x
c
H
E

TPO-5659-044

AP-103F/FD-108 O z a r k FH-227,
Mar 1/73 Inter c o m e cting W i r i n g D i a g r a m 22-03-00
F i g u r e 452 (Sheet 3) Pages 401/83, 401/84
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT MISC
ANNUN- PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT SENSING EMERGENCY
COURSE
CIATORS INDICATOR CONTROLLER AMPLIFIER COMPUTER MISC POWER AMPLIFIEP WIRE FUNCTION SERVOS UNIT DISCONNECT J-BOX
INDICATOR WIRE FUNCTION

Q
331A-bK
J1 J2
b19E-2G1
J1
3298-71
J1 J2
3YYClD
J I J2
5bBA-5.G
J I A JlB
Q J1
5b2C-9
J1
3395A-95 121AJ
J1
(TP) (BP) (TP>(BP) (TP) (BP)
.
: 21-
- P I T C n 2ZFFEREhTIA. RESOCVER X
... .... .... - (PITCH)
:
:
(22
23-
-
P:TCi SIFFEREhTIA- RESOLMR Y
P I T C n DIFFERE\TIA. QESOCMR 2
-. ... ...
:
:
8
10 -
-
PITCH RATE MOTOR GRD
115 VAC POWER
A
B
24
25
8b
-
-
PITCH DIFFERENTIAL RESOLVER P
PITCH DIFFERENTIAL RESOLVER C
PITCH DIFFERENTIAL RESOLVER HI
.._
.
..
.
..
.
:
:
:
32
31 -
29 -
PITCH RATE EXCITATION C
PITCH RATE EXCITATION H
PITCH RATE SIGNAL X
E
F
G
_
. .. ._
- ... ... .._
27- PITCH DIFFERENTIAL RESOLVER C '
88
29
30
-
-
BANK DIFFERENTIAL RESOLVER X
BANK DIFFERENTIAL RESOLVER Y ._
_
.. . .
.. .. . .
YAW RATE
GYRO
3326-2
BANK DIFFERENTIAL RESOLVER 7.
_ :
... ..... ..._.
31- BANK DIFFERENTIAL RESOLVER H f . . bb YAW RATE HDTOR CRD A
10 : 115 VAC POWER B
32-
33
34
-
-
B A t U DIFFERENTIAL RESOLVER C
BANK DIFFERENTIAL RESOLVER H '
BANK DIFFERENTIAL RESOLVER C ' _
_
.
. .
51
50
:
:
YAW RATE EXCITATION C
YAW RATE EXCITATION H
_
.. .. . .. _ 48 : YAW RATE SIGNAL X G
. . .

SYhBDLS USED: @ TOTAL WIRE RUN FROM BUSS TO 121A-2 TO 5 b l C - 9 TO 3346-3 ( P I N 0 ) FOR EACH
PRIMARY SERVO MJST NOT EXCEED 90 I'EET I F AWG 20 WIRE I S USED. WHEN GREATER
SV TWISTED SHIELDED PAIR-ADJACENT THAN 90 FEET, INSTALL TERMINALS A',' 5b2C-9 MOUNT AND RUN AWG 20 WIRE FROM
SA WIRES As SHOWN ON DRAWING 5b2C-Y TO TERMINAL AND AUG I b WIRE FROM TERMINAL 3 4 K - 3 P I N 0.
SG
SI
SHIELD TIED TO G R D ~ N DT; INIT
SINGLE SHIELDED WIRE @ AN ISOLATED MODE SWITCH I S PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR. ,
6 ALL SI SHIELDED T I E D TO X 1 ETC.
NOTES
STY FOUR WIRES TWISTED WITH SHIELD
@ A 7.5K OHMS 1 / 2 WATT 10% RESISTOR I S REQUIRED ON EACH T R I M INDICATOR MOVEMENT.
WITH TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING L I N K S INSTALLED
FOR CORRECT SERVO PHASING THE PRINARY SERVO CAPSTAN SHOULD TURN CLOCKWISE
NOTES: WHEN VIEWED FROM THE CAPSTAN END UNDER THE FOLLOWING AIRCRAFT A T T I T M E S :

ALL WIRE S I Z E S ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY NUMBERS I N SQUARES.

SHIELDED WIRES ARE GROUNDED AT OHE END ONLY.
AILERON
ELEVATOR
-- LEFT BANK
PITCH UP
RUDDER - LEFT YAW
@ SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE
GROUNDED AT THE 51RV-1. Q POWER FROM A PARTICULAR CIRCUIT BFEAKER OR FUSE MAY PROVIDE POWER FOR MORE
THAN ONE EQUIPMENT. T H I S W I L L BE INDICATED I N THE INTERCONNECT POWER COLUMN
FOUR WIRES TWISTED WITH SHEILD FOR COMPATIBILITY I N FUTLRE ARINC INSTALLATIONS. BY A LETTER WITH AN OCTAGON SYMBOL AROUND I T , CAPITAL LETTERS FOR DC AND LOWER
@ CASE LETTERS FOR AC.
A RELAY MUST BE INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF
TEST FEATURE OF THE 51RV-1 WHEN THE AUTOPILOT I S ENGAGED. 0 , CI DI E
G -
-
28VDC SAMP
28 VDC 1 AMP
a -
b , c, d -
5 VDC DIMMING C I R C U I T
115 VAC 2 AMP
Q -
f -
THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N T H I S DPAWING REFLECTS e 115 VAC 1 AMP
LOADS AS FOLLOWS: 1 1 5 VAC 3 AMP

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS

Q THE GO AROUND RELAY I S INSTALLED FOR WINGS LEVEL. P I T C H UP GO AROUND.
GO AROUND BUTTON I S NORMALLY OPEN AND NORMALLY I S INSTALLED ON CONTROL
200 OHMS TO-FROM 1 0 0 OHMS JUPPER BP-93 TO BP-33 OF 51RV-1 COLUMN WHEEL. TO DEACTIVATE GO MOUND PROVISION REMOVE THE RELAY AND
500 OHMS GLIDE SLOPE POINTER 200 OHMS JUMPER TP-8 TO TP-2 AND TP-3 OF 51RV-1 CONNECT THOSE WIRES TOGETHER THAT ARE CONNECTED BY THE NORMALLY CLOSED
500 OHMS GLIDE SLOPE FLAG 250 OHMS JUMPER TP-21 TO TP-Pb OF 51RV-1 CONTACTS OF THE RELAY.
500 OHMS LOC FLAG 250 OHMS JUMPER BP-32 TO BP-91 OF 51RV-1
500 OHMS COURSE BAR 200 OHMS JUMPER BP-39 TO BP-30 AND BP-98 OF S l R V - 1 Q EQUIPMENT SHOWN I N MISC COLMNS MPY NOT HAVE COMPLETE WIRING INFORMATION
INDICATED. BEFORE WIRING APPLICAELE SYSTEM MANUALS FOR THAT EQUIPMENT
@ THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF TAE
AUTOMATIC FLIGHT CONTROL SYSTEM.
SHOULD BE CHECKED.

CONNECTIONS TO TRIM TAB MOTOR CONlROL DEPENDS ON AIRCRAFT RIGGING.

@ POWER LEADS DENOTED BY "DIM" SHOULD BE T I E D TO COCKPIT LIGHT DIMMING CIRCUITS.
PROVISIONS FOR RADIO ALTIMETER (OFTIONAL).
SENSING U N I T 395A-Y( ) AND RATE GYRO 3326-2 SHOULD BE LOCATED AS CLOSE TOGETHER
@ AS POSSIBLE. BACK COLRSE RELAY K 1 I S bPDT OR TWO 9PDT RELAYS. 51 I S SOLENOID HELD
SWITCH MICROSWITCH 5ETl-T OR EQUAL. BACK COURSE ANNUNCIATION I S 28VDC.
@ ANNUNCIATORS CHOSEN M l S T NOT EXCEED 1 0 0 MA. A COMMON + 2 8 VDC I S USED FOR
ANNUNCIATOR POWER. ANNUNCIATION VARIES WITH THE PARTICULAR INSTALLATION. SPEED CONTROL INPUT.
DEPENDING UPON DESIRED OPERATION, S P E C I F I C ANNUNCIATORS MAY BE DELETED.
WHEN O P T I O N A L 5 9 O A - 3 A S E R V I C E B U L L E T I N N O 3 I S I N C O R P O R A T E D , T H E F O L L O W I N G INTERCONNECTING
@ THE 5b2C-9 AND 5b2A-5G SHOULD B E MOUNTED AS CLOSE TOGETHER AS POSSIBLE.
PREFERABLY ON A DUAL MOUNT. THESE SIGNAL LEADS MVST BE TWISTED AND WIRED
WIRING C H A N G E S A R E A P P L I C A B L E
R E M O V E C O N N E C T I O N B E T W E E N J I I B P 1 - 3 8 O F T H E 5 6 2 C - 4 A U T O P I L O T A M P L I F I E R A N D JI-d
POINT TO POINT BETWEEN THE UNITS. THE W I S T E D PAIRS SHOULD BE KEPT AS OF THE 6 1 4 E - 2 0 P E D E S T A L C ( ' N T R 0 L L E . Q R E M O V E C O N N E C T I O N B E T W E E N J I - V OF T H E 6 1 4 E - 2 G
SHORT AS PRACTICAL AND MUST ALSO BE SHIELDED I F OVER TWO FEET LONG. P E D E S T A L C O N T R O L L E R A N D J I A I T P I - 4 7 O F T H E 5621-50 F L I G H T C O M P U T E R .

COMPARATOR WARNING RESOLVERS. W NOT USE FOR OTHER PURPOSES UNLESS LOADING MAKE CONNECTIONS& SHOWN BELOW,
@ EFFECT I S EVALUATED. PEDESTAL FLIGHT ALTITUDE AUTOPILOT
CONTROLLER WIRE F U N C T I O N COMPUTER CONTROLLER AMPLIFIER

614E- 2 G 562A-5G 590A-3A 562C-4

JI JIA JIB (JI) JI JI
I T P ) 13n I T P ) (EP)

V _______ ALTITUDE HOLD M W E

A L T I T U D E HOLD 110DE+47
+ ________34
_____----
20 38
TPO-5 659-044

AP-l03F/ FD- 108 Ozark FH-227,

Mar 1/73 Interconnecting Wiring Diagram 22 -03-00
Figure 452 (Sheet 4) Pages 401/85, 401/86
 COLLINS
iK-IINTENASCE
w MANUAL

AP-IOBF FAIRCHILD F H 4 2 7

FLIGHT
ANNUN- COWSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION MLIFIER COMPUTER MISC POWER AMPLIFIER WIRE FUNCTIOh SERVOS MISC DISCONNECT J-BOX

3 3 l A M blYE-2G 329B-?A 3YYC-lC 5b2A-5G

Q AILERON 121A-Z
8 J1 12 J1 J1 J2 J1 J? J I A J13 33YC-3 J1

b
7 -6
-
e?-
PITCH ATTITUDE ERROR H '
PITCH ATTITUDE ERROR C '
-
-
- 23
(TP) (3P)

24
:
:
(TP)(BP)

:
:
:
:
b; -5 :fER;k

+AILERON
F I E L D NUNBER 1
(Jl)

A
0
8
9 _r__ PITCH ATTITUDE SERVO DRIVE C -
PITCH A T T I T M E SERVO DRIVE M2 28
27
:
:
:
:
:
: 13
: 5
: 5 t - AILERON
FIELC N W R 2
SIGNAL C
C
E

-
ID : 5- PITCH ATTITUDE RATE G2 25 : : : VERT 1Y AILERON EXCITATION C F
11 : 5 6 PITCH A T T I T W E RATE C2 2b : : : REF 15 : AILERON W S I T I O N EXCITATION H G
1 : S?- M N U A L PITCH COMMAND H ' : 3b : 332D-11 lb : St- AILERON RATE EXCITATION H H
2 - 6 MANUAL PITCH COMMWD C ' : 2b : (J1) 12 : 51- AILERON W S I T I O N SIWIAL L
. V-BAR PITCH COMMIND SERVO D R I M MI : : R
Y2
Y3
YY
I V-BAR PITCH C O W N D SERVO DRIVE C t
: 5- V-BAR PITCH C W N D RATE
11
-10 : :
11 X+-
I? : 5+
AILERON
AILERON
SERVO CRD
RATE SIGNAL S

Y5 : 5 6 V-SAR PITCH COMMAND S I C COM

91 -
3
-
Y O -7-

-
6
:
V-BAR PITCH W S XMTR X
V-BAR PITCH ?OS XMTR Y
PITCH ATTITUDE CT X f 30-A AILERON ENGAGE VOLTAGE
(J2)
A.

-
Y PITCH ATTITUDE CT Y r 20-8 AILERON ENGAGE VOLTAGE

l?
5 PITCH ATTITUDE CT Z
BANK A T T I T W E CT X :
. .: 3 .0 - C C

18 BANK ATTITUDE CT Y : : 20-E

-
19 BU4K A T T I T W E CT Z F ELEVATOR
20 e? BANK A T T I-T W E ERROR H ' 33YC-3
.~ . ~

21 -
22
6 BANK A T T I T W E ERROR C'
BANK A T T I T W E SERVO DRIVE M2 -
- 22 : : : +ELEVATOR FIELD N W E R 1
(Jl)
A

25 -
3b -
23 __C_ BANK ATTITUDE SERVO D R I M C
2Y e?-
6
BANK ATTITUDE RATE 6 2
BANK A T T I T W E RATE CZ
V-BAR ROLL COMMAND YRW DRIVE ~2
37 __r_ V-BAR ROLL ComAND SERVO DRIVE C 72 )

3: A?- v-Smm L L CMOuND RATE G2

-
L
21
19
20
:
:
:
28

2;
. . .
:
:
:
:
:

I
:
:
:
:
:

I
a
J -c(

t3 E S T
:
:
:
:
:
13 +C
1Y
15-
lb- t
12 4-
- ELEVATOR
ELEVATOR
ELEVATOR
ELEVATOR
ELEVATOR
SIGhAL C
EXCITATION C
W S I T I O N EXCITATION H
R T E EXCITATION H
W S I T I O N SIGNAL
3
C
E
F
G
H
L
39 : S ~ V - B A R m u ~OMMWD SGI COM : 2b : : H- GRD : 11 - X t ELEVATOR YRVO GW R
3~ e?- V-BAR ROLL POS XMTR ~i - 2 4 : : : I? ++ ELEVATOR RATE SIGNAL s
35 -
6 V-SAR ROLL POS XMTR c i I 2 3 : : C 7 1
: 115 VAC ATTITUDE P W E R - d
: : GYRO MON + 29- 10- N
31 __c_ GYRO HIGH LEVEL FLAG +
:
:

:
18
Y

-
io -
lb
-
-
STEER FLAG
STEER FLAG
-
GYRO HIGH LEVEL FLAG

+28 VDC FLAG POWER

SLOPE DEV + LP
- 31
32

2 - :
:
2

:
f
:
:
:

:
f
28

5Y
:
:
:

:
NAV
RCm
51RV-1
(TP) -
@
ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGLGE VOLTAGE
(52)

33
39
;
. 11 -
-
GLIDE
GLIDE SLOPE DEV + Ctl
:
:
32-8
22-9
RMDER
33YC-3
35
3b
;
:
12
13 - GLIDE SLOPE LOW LEVEL FLAG +
GLIDE SLOPE LOU LEVEL FLAG - f
f
21
22 f WDDER F I E L D NUDBER 1
(J1)
A

-
: GLIDE SLOPE HIGH LEVEL FLAG + : 11-22)
I : S T ' t C O L R Y RESOLVER A I lb
@ bi
9 1 28 VDC F I E L D NLHBER 2
t RUDDER B
C

-
-
: : :
- (BP) 9 3 -f RUDDER SIGNAL C

-
VORlLOC DEV + LEFT
29
28
:

:
b
5
9 - VORlLOC DEV + RIGHT
VORlLOC HIGH LEVEL FLAG + :
:
:
:
32
22
11-50
-')o
39
YY
Y5
Yb -f
RUDDER
RUDDER
RUDDER
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION H
G
H
: LOC FREQ VOLTAGE + : : Y3-338 Y2 --5f RUDER POSITION SIGNAL L
; : 5 T ' t COLRSE RESOLVER B

.
: 22 Yl RUDDER SERVO ORD R
8 : STY- COURSE RESOLVER H : 21 Y? -f RMDER PATE S I G N U s
3 : 5% COURSE RESOLVER C f 23 (52)
Y : S?- COLRSE RESOLVER D 29 RUDDER ENGAGE VOLTAGE
5 I S b COLRSE RESOLVER E : 25 RUDDER ENGAGE VOLTAGE
b : 5- COURSE RESOLVER F : : 2b
- 5& COURSE RESOLVER G . 27
-_
7
.- ..- ..
VORlLOC FLAG -
. . .
: Y2
.. ..
32 - OC
.
...
767-8234
2b TOJROM M O W (+ TO) : Y3
.. .. .. ..-.
27 : TO-FROM ARROW (+ FROM) f YY

. . . ...
.. .. .. . .
. . .

AP-103F/FD-108 Fairchild FH-227, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 453

May 1/67 22 -03-00

Pages 401/87, 401/88
 COLLINS
MAINTENANCE
MANUAL

FLIGHT
ANNW- COLRSE PEDESTAL DIRECTOR INSTRIMNT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER COWUTER COMPASS POWER AWLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

331A4A blYE-ZG 3298-7A 5b2C-Y TRIM 121A-2

8 JI 52 J1 J1 J2 Jl
(TP) (BP)
J l TAB
SERVO
J1

.. . .. . .. . .. 33W-2-330
(J?)
. . . .
.. .. .. ..
.. .. .. ..
.. .. .. ..
. . TRIM
... ._ .. .. INDICATOR
... ... ...
.
.
9 r 1;
.
. :
:
CORASSMON-
CORASS MOW +
CORASS DATA X
1
f

. . . .
30
29-
.
.
-
.. ._
IY-25
.. ..
17

2
GRD
D ;
:

33
:
:
-
f

3Y 4 -
33 -5-
X+ GRD
2 8 W C POWER
TRIM ENGAGE Q1D
TRIM ENGAGE VOLTAGE

TRIM TbE hOT CON7

TRIM T B M)T CONT
AILERON TRIM INDICATOR
m
u
B
A
D

c-• @
F--
3270-1W

L
M

+ -

'9 cI: CORASS DATA Y

._ . . . . : 3 : 39
53
AILERON TRIM INDICATOR
RUDDER TRIM INDICATOR
- w
_C__
+
't c,: CORASS DATA Z
I
- Y
: : : I 1
: 52
.
__r__
19 - RUDDER TRIM INDICITOR P
COWASS DATA X
-
..
:
:
:
:
:
:
Y
3
:
:
50-
51 - COIRASS DATA Y
COWASS DATA Z
C O R I S S FLAG +
-
-
x1 31 : : 27-CRD
: 2'( CORASS FLAG 3 2 : :
: 15 2b VAC HDG PWR f 15 : : 22- 5 :
: Ib COMW : Ib : : 30-1 :
: 20 f 5- HEADING ERROR SYNMRO C: 17 : :
: 21 f 5 b HEADING ERROR SYNMRO H : 1 8 : :
: 13 : 59- HEADING RATE GZ : 1 9 : :
: 1Y f 5 b BEADING RATE C2 . 20 : :
: 12 HDG M T CONT C I . 21 : :
: I1 HDG M)T CONT M I f 2 2 : : AIRSPEED
: Y H U D I N G DATLM SYNMRO C ' I 23 : SENSOR
: 5 HEADING D A T W SYNMRO H ' 33 M 59DB4

;a,
f
12 COLRSE MTLM SYNCHRO C ' : 29 8bOE-? (Jl)
13 COLRSE DATUM SYNCHRO H ' . 3 (J1) 59 . AIRSPEED SIGNAL
.
'(5
Yb
*7
DISTANCE INDICATOR FLAG +
DISTANCE INDICATOR FLAG
DISTANCE INDICATOR 2 b VAC H
- :
9
10
2
58
bo
AIRSPEED EXCITATION H
AIRSPEED EXCITATION C

- :.
.. .. ..
98 D I S T W E INDICATOR 2 b VAC C 1
r9-J F
50 DISTANCE INDICATOR UNITS SYNMRO X : 9
51 DISTANCE INDICATOR W I T S SYNMRO Y ; 3
52 DISTANCE INDICATOR TENS SYNCHRO X ; b
53 DISTANCE INDICATOR TENS SYNCHRO Y : 5
5Y DISTANCE INDICATOR HLNHDREDS SYNMRO X 7
55 DISTANCE INDICATOR HUNDREDS SYNCHRO Y
. . . . 8

Y8
32
33 -b
-
-
2 b VAC C O W N D PWR
2 b VAC A T T I T W E PWR
2 b VAC ATTITUDE RIR CDM -
12
15
l b
_ . .
. .... .... ....
:
:
:
:
:
:
:
:
:
2Y
25
f
f
19
20 - 5 VAC LIGHTING PWR
5 VAC LIGHTING PVR CDM <a>

: 9
e
: :
:
:
DC GRD
115 VAC
115 VAC
+28 M)C
+28 WC
HEADING PVR
A m T V M PWR
F#dER-B-
SERVD UVTM POWER-•
i-
't

.
--d i5 i-rr5-: &

..
55
dD
5Y
..
56

.. =m b :
. q :

._ .. . .. _ : b l - CRD
28 VM: P W E R
w - N
P

.. .._ .. .. RUDDER SERW POWER S

._ . .. . .. T
_.. .. .. U

. . .. ... ... V
W

L
K
:
:
:
:
PITCH STEERING + lU
PITCH STEERING + MI
ROLL STEERING + LEFT
ROLL STEERING + RIGHT
G y m DE +
HEADING MOM +
:
:
13
3-31
Y-21
12
13
:
:
31
21
Y1
Y7
:
:
-
-
-
. YO
bY
:
:
X

1 NAVlLOC M)DE + P Yb : : Y? I
M *ROUND hODE +
I
H APPROACH K I D E +
- APPROACH W E + I

- : 95 f . Y8 APPROACW MWE + f
: EXT STR + DN
3 7 3 :
.. 27
i
I
I
: E M S T R + UP I
ALT HOiD i ALTITUDE HOLD I N T E K O C K r ALTITUDE HOLD INTERLOM 17
_
:
.... .
Yb
.. .
: ALTITUDE HOLD INIERLOCK I

..
... ...
I

..
. . .
: bb -
- DISCONNECT SYITCkI H
I

:
.. .. .. 39- Y5 :
:
f
b7
Yb - DISCONNECT SYITCh C
GLIDE SLOPE K)DE + PILOT'S
T
DISCONNECT
VTa
COPILOT ' 5

. . .. SWITCH

AP-103F/FD-108 Fairchild FH-227, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 453
May 1/67 22 -03-00
Pages 401/89, 401/90
 COLLINS
MAIXTENANCE
MANUAL
WW

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTITUDE AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER CONTROLLER POWER WIRE FUNCTION SERVOS MISC DISCONNECT J-BOX

331A-bA blYE-?G 3290-?A 399C-1D 5b2A-5G 59OA-3A @ 5b2C-9 121A-Z

8 J1 J2 J1 J1 J2 J l
(TP)
J2
(BP)
J l A J1B
(TP)(BP)
(J1) J l
(TP)
J1
(BP)
J1

V
- : ALTITUDE HOLD MODE +
: ALTITUDE RATE H ' 4)
: ALTITUDE RATE C' ---SI : 29-15
: ALTITUDE ERROR H ' +? : 33 -+l b : 91
: .
12
ALTITUDE ERROR C ' +A
PITCH BOOTSTRAP TRANSMITTER X
:
:
23-27
: : 3 9 :
92
93 -
- ALTITUDE GAIN CHANGE EXCITATION
13
19
:
:
PITCH 3OOTSTRAP TRANSMITTER Y
PITCH SOOTSTRAP TRANSMITTER Z .- . ..
:
. .
: : 9 2 : 99
95 - ALTITUDE GAIN CHANGE NO. 1
ALTITUDE GAIN CHANGE NO. 2
15 : PITCH BOOTSTRAP EXCITATION H
l b : PITCH BOOTSTRAP EXCITATION C - . : 35-.
.

--
2b . BANK BOOTSTRAP TRANSMITTER X : : : GRD
27
28
:
.:
BANK BOOTSTRAP TRANSMITTER Y
BANK BOOTSTRAP TRANSMITTER 2
: 15 :
37-
:
. 59
18
-
-+
COMPUTER MON +
EXT PITCH STEERING 4
29 BANK BOOTSTRAP EXCITATION H : 19 -6 EXT PITCH STEEXNG B
30 : BANK BOOTSTRAP EXCITATION C : 25 AC PITCH STEERING A
I flb I : HEADING WARNING DATA X : 2b 4 6AC P I T M STEERING B
: HEADING WARNING DATA Y : 27 -+ PROCESSED PITOrl DATA A
: HEADING WARNING DATA Z : 28 -6 PROCESSED P I T M DATA B
+
: 21 :
:
:
HEADING WARNING DATA H
HEADING WARNING DATA C
HEADING WARNING DATA H '
18
98
:
-
:
:
18
bO
:
-
57 -INTERNAL
S+
PITCH STEERING OFF
ALT HOLD OFF +
EXT ROLL STEERING A
: 22 : : HEADING WARNING DATA C ' 19 : S b EXT ROLL STEERING B
25 : S+ PROCESSED BANK CMD A
8b : S b PROCESSED BANK CMD B
35 : S+ PROCESSED BANK DATA A . -
3b : 5 6 PROCESSED BANK DATA B
- .
PITCH W N I T O R +
;
:
;l,:
- ;: 55
5Y
:
:
5-
5 b
EXT BANK CMD B
EXT BANK CMD A

GS ARM
GS EX?
:
:
:
:
:
GLIDE SLOPE ARM. ANN.
GLIDE SLOPE EXT. ANN.
-- :
:
12
b
52
12
:
: . .
-
N/L ARM
N/L CAPT
:
: :
: NAVlLOC ARM. ANN.
NAVlLOC CPPTVRE ANN. - :
: : 3 9
: b :
:
PWR
GS CAPT : : 38 -RUWAY FLAG -
ANNUNCIATOR POWER

. ._ ._ ._
: : : M(R BCN
: : : RCW
GA GO AROUND A". - :
.. . : (J1)
1b : 512-9 . .
: MIDDLE MARKER : 93-9
. +
A : PITCH CONTROL EXC A _ . . :
: : I 8 57
: 21
INTERNAL ROLL STEERING OFF
NAV NAV : 51RV-I
B : PITCH CONTROL SIGNAL . . . : 80 RCW CONT : SELF-TEST
C
D
: PITCH CONTROL EXC B
.. .. ..
. . .
: 12 51RV-1 313N-3 : RELAY

E TURN CONTROL EXC A . . . 21 :

1 : TURN CONTROL EXC B . . . 88 :
: G : TURN CONTROL SIGNAL . . . 20 :
N : I N T MOTOR CONTROL VOLTAGE . . . : b2
P : I N T 2 b VAC MOTOR EXCITATION C . . . 29 :
R : I N T MOTOR RATE SIGNAL . . . . b3
: s : I N T WTOR SIGNAL COmON . . . :
. 29
.
: T : 28 VDC PANEL LIGHT PWR . . . Q
.. ..: .:.
U GRD : GRD
X
. . A
: Y
2
: ENGAGE VOLTAGE
.
. .
. ..
.
. ~ T U 1
a : ENGAGE PULSE . . . : 5b
: b : DISENGAGE VOLTAGE . . . : 37
: ENGAGE READY . . . : 55
: + _
. . . :
.. . .. .
ALTITUDE HOLD MODE 38
.
_
f : HEADING SYNCH CUTOUT . . . 38 :
P : 115 VAC AUTO P I L O T PWR
9 : 115 VAC POWER . . . 7 :
r : I N T 2 b VAC M T O R EXCITATION H . . . 23
. :
5
t
: ENGAGE INTERLOCK
;. ... .-.. ... - ; - :
59
I
U
V
:
:
AILERON CLUTCH VOLTAGE
ELEVATOR CLUTCH VOLTAGE
. . . 39
.
:
39
D
K
I
I

.... .. ..
w RUDDER CLUTCH VOLTAGE 5b : A
M
X
+28 VDC AUTO P I L O T PWR
.. .. : 53 - YAW DAMPER ENGAGE M3N +
Y : SPARE
. .. .. .. : 9 SENSING
2
. . . . . UNIT

... .._ .. _
AA 3395A-90 @ :
BB (ROLL) : YAW DAMP SW
cc .~ .. .. .. b5 : ROLL RATE MOTOR GRD A
DD : GYRO MODE .. .. .. . 8 . 115 VAC POWER B
EE : HEADING MODE .. .. .. 32 : m u RATE EXCITATION c
FF : NAV/LOC MODE .. ... .._ 31 : ROLL RATE EXCITATION H F
GG : APPROACH MODE .. .. .. 29 : ROLL RATE SIGVAL X G
HH . MODE VOLTAGE H .

AP-103F/FD-108 Fairchild FH-227,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 453 (Sheet 3) Pages 401/91, 401/92
 e
COLLINS MAINTENANCE
wv MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRVMENT FLIGHT AUTOPILOT SENSING EMERGEN-
CIATORS INDICATOR CONT2OLLER INDICATOR WIRE FUNCTION AWLIFIER COMPUTER MISC POWER A W L I FI
ER WIRE FUNCTION SERVOS UNIT DISCONNECT J-BOX

Q
331A-bA
J1 52
b1YEaG
J1
329B-7A
J l 52
Q J l
5b2C-Y
J l 33Y5A-YB @
121A-2
Jl
(IP) (BP)
$1 -
- PITCH DIFFERENTIAL RESOLVER X . .-
- (PITCH)
22
23 -
-
PITW
PITW
DIFFERELTIAL RESOLVER Y
DIFFEREhTIAL RESOLVER 2
:
:
8
IO-
-
P I T C H RATE MOTOR GRD
115 VAC WWER
A
8

. .
2+
25 -
26 -PITCH
PITCH
PITCd
DIFFEREhTIAL E S O - V E R !4
DIFFERENTIAL RESOLVER C
DIFFERENTIAL RESOLVER H '
:
:
.
:
32
31
29
-
.-
PITCH R AE EXCITATION C
P I T C H RATE EXCITATION H
PITCH RATE SIGNAL X
E
F
G
27 - P I T C H DIFFERENTIAL RESOLVER C '
.- .. UTE
.-. ...
28 -BANK DIFFERENTIAL RESOLVER X YAW
29 -BANK
30-
31-
32 -
-
33 -BANK
3Y
BANK
BANK
BANK

BANK
DIFFERENTIAL RESOLVER Y
DIFFERENTIAL RESOLVER 2
DIFFERENTIAL RESOLVER H
DIFFERENTIAL RESCLVER C
DIFFERENTIAL RESOLVER H'
DIFFERENTIAL RESOLVER C'
10
-15
..
bb P
-
-
..-
YAW RATE MOTOR GRD
115 VAC PWER
YAW RATE EXCITATION C
50 P YAW RATE EXCITATION H
GYRO
332-
A
8
E

Y8
. .
YAW RATE SIGNAL X G

SYMBOLS USED:
11. CCWARATOR WARNING RESa.VERS. Do NOT USE FOR OTHER P W O S E S UNLESS LOADING
51 TWISTED W I E L D E D PAIR-ADJACENT EFFECT-. - - A L-
IS.N U.
T E_
D ...
Sd WIRES AS SHOWN ON DRAWING 12. TOTAL W I R E R I N FRM BUSS TO 12lA-2 TO 5 6 2 W TO 3 3 Y C 3 ( P I N 8 ) FOR EACH
SG SHIELD T I E D TO QK)WAT U N I T P R I M M Y SERVO W S T NOT EXCEED 90 FEET I F AWG 20 WIRE I S USED. WHEN GREATER
S1 SINGLE SHIELDED WIRE THAN 90 FEET, INSTALL TERMINALS AT 5 b 2 C - 1 MMNT AND RVN AWG 20 WIRE FROM
8 ALL 51 Y l I E L D E D T I E D TO X 1 ETC.
NOTES
ST't F W R WIRES TWISTED WITH SHIELD
13.
1Y.
562C-Y TO TERMINAL AND AWG l b WIRE FROM TEPMINAL 3 Y Y G 3 P I N 8.
AN S ICA
ITED Mors SWITCH SI PROVIDED FOR USE WTIH COPILOTS FLIGHT DIRECTOR.
A 12K O M 1I2 WATT 10% RESISTOR I S REQUIRED ON EAGi TRIM INDICATOR MOVEENT.
WITH TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING L I N K S INSTALLED
NOTES: FOR CWRECT Y R V O PHASIYG THE P R W Y SERVO CAPSTAN S H W L D Tw(N CLOCKWISE
W E N VIEWED FROM iM CA'STAN END WDER THE F O L L W I N G AIRQUFT A T T I T W E S :
1. ALL WIRE S I Z E S ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY W E R S I N SQUARES.
SHIELDED WIRES ARE GROUNDED AT W E END ONLY- AILERON -- LEFT B W K
MAKE CONNECTIONS AS SHOWN BELOW.
2.

3.
SHIELDS ON THE NAV FfSOLVER LEADS F R M THE NAVIGATION RECEIVER SHWLD BE
...... AT THE
GRaUNDED - .
5lRV-1.
_-.
FOUR WIRES TWISTED WITH SHEILD FOR C O W A T I B I L I T Y I N FUTURE ARINC INSTALLATIONS.
ELEVATOR
RVDDUI - P I T U i Up
LEFT YAW PEDESTAL
CONTROLLER WIRE FUNCTION
FLIGHT
COMPUTER
ALTITUDE
CONTROLLER
AUTOPILOI'
AMPLIFIER
4. A RELAY W S T BE INSTALLED I N THE A I R Q I A F T JUNCTION BOX TO E L I M I N A T E THE SELF 15. WMR FROM A PARTICULAR C I R C U I T BREAKER OR FUSE MAY PROVIDE POWER FOR MORE
TEST F E A N R E OF THE 5 l R V - 1 WHEN THE AUTOPILOT I S ENGASED. S14E.ZG 562A-5G SQOA.3A 562C.4
THAN ONE EWIPMENT. T U S WILL BE INDICATED I N THE INTERCONNECT POWER C O L M 1 J l A J l B Illi Jl il
5. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N T H I S ERAWING REFLECTS BY A LETTER WITH AN OCT4GON SYMBOL AROUND I T , CAPITAL LETTERS FOR DC AND LOWER ITP! IBP! ITP! lBP1
LOADS AS FOLLOWS: UJE LElTERS FOR AC.
V ................. P L T TUDE )(CLD ),!@DE+ ...............
AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS A - -
28 W C D I M I N S CIRCUIT 1 - -
5 VDC DIhMING CIRCUIT
AL' 'rLi1:: HOLD ODE^ ,; ......................
...34
20. ................................... 38

200 OHMS
500 OHMS
TO-FROM
GLIDE SLOPE POINTER
100 O W
200 OHMS
JWER
JWER
W-Y3 TO W-33 OF SIRV-1
TP-8 TO TP-2 AND T P J OF 5 l R V - 1
G -
BI C, DI E 28 W C 5 A W
1 8 W C l M --
b. c , d 115 VAC 2 AR
e 11s VK 1 M
f 115 VAC 3 hW
500 oIy4s GLIDE SLOPE FLAG 250 OHMS JLWER TP-21 TO TP-3 OF 5 l R V - 1
500 OHMS LOC FLAG 250 OMIS JWER W-32 TO W 4 1 OF 5 l R V - 1 lb. THE GO AROCHD RELAY I S INSTALLED FOR WINGS LEVEL, P I T W U p GO AROUND.
500 OHMS COURSE BAR 200 OHMS JLWER 8P-39 TO W-30 AND W 4 8 OF 51RV-1 GO AROUHD BUTTON I S H M W U L Y W E N AND NORMKLY I S INSTALLED ON CONTROL
COLM MEL. TO DEACTIVATE GO A R O M PROVISION REMOVE THE RELAY AND
b. THE POWER FOR THE COMPASS SYSTEM WST BE OF THE S M E P W E AS THE REST OF THE CONNECT M S E WIRES TOQTHER T H I T AQE CONNECTED BY THE NORMALLY U O S E D
AUTOMATIC FLIGHT CONTROL SYSTEM. CONTACTS OF TIE RELAY.
7. WVZR LEADS DENOTED BY "DIM" S W D BE T I E D TO C O W I T L I G H T DIMMING CIRCUITS. 17 I EQUIPMENT YHWN I N M S C COLUMS MAY NOT HAVE W L E T E WIRING INFORMATION
8. SENSING U N I T 39SA-Y( ) AND RATE G Y M 332- SHCUD BE LOCATED AS CLOSE TOGETHER INDICATED. BEFORE WIRIYG W L I C A B L E SYSTEM W U A L S FOR THAT EQUIPMENT
AS POSSIBLE. YKHLD BE OIEQ(ED.
9. ANNUNCIATORS CHOSEN W S T NOT EXCEED 100 MA. A C O M N +28 VDC I S USED FOR 18. CONNECTIONS TO TRIM TAB MOTOR CONTROL DEPENDS ON AIRCRAFT RIGGING.
ANNUNCIATOR WER. A " U N C I A T 1 O N VARIES WITH THE PARTICILAR INSTALLATIOH- 19. PROVISIONS FOR W I O ALTIMETER (OPTIONAL).
DEPENDING WON DESIRED OPERATION. S P E C I F I C ANNUNCIATORS MAY BE DELETED.
10. THE 5b2C-Y AND 562A-SG S H W L D BE M O W E D AS U O S E TOGETHER AS POSSIBLE,
PREFERABLY ON A WAL MOUNT. THESE SIGNAL LEADS W S T BE TWISTED AND WIRED
POINT TO POINT BETWEEN M UNITS. THE TWISTED PAIRS S W L D BE KEPT AS
SHORT AS PRACTICAL AND W S T ALSO BE SHIELDED I F OVER TWO FEET LONG. THE
WIRING SHOULD BE POINT TO POINT.

AP-103F/FD-108 Fairchild FH-227,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 453 (Sheet 4) Pages 401/93, 401/94
 a
COLLINS
MAINTENANCE
MAKUAL

FLIGHT
W- COVlSE PEDESTAL DIRECTCR INSTRVIENT FLIGHT AUTOPILOT EIERGEW
CIATDRS INDICATOR CONTROLLER INDICATOR YTRE FUNCTION MPLIFIER CWPUTER MISC POWER ALPLIFTER WIRE FUNCTION SERVOS MISC DISCONNECT JdoX

@
331A-M
J1 J2
blH-2F
J1 J1 J2
Q J1
5b2C-Y
J1
ULERON
331C-3
l 2 l M
J l

-
(Jl)

b -+ PITCH A T T I M E EmOR H' -

- 2* 1s : : +AILERON F I E L D ".MER 1 A
? ----c---5bP I T C H
8

-
9 -PITCH
10 -+
PITCH
ATTITUDE ERRW. C '

ATTXTUDE SERYO DRIVE C

ATTXTLOE M E G2
-
-
A T T I T W E SERVO W I V E M2
23
28
27
:
:
:
:
:
:
:
:
:
:
:
:
Q
-
1 3 --cb+AILERON
l- AILERON FIELD H U M R 2
S I W L C
I)
C
E

-
PITCH 25 VERT 1+ AILERON EXCITATION C F
11-b- 2b : : : REF

-
PITCH A T T I M E RATE C2 15 AILERON P O S I T I O N EXCITATION H G
1 -+ M A L P I T M COmAND H ' : 3b : 3320-11 l b -+ AILERON RATE E X C I T A T I O N H H
2 MANUM P I T M CC*MHD C ' : 2b : (Jl) 1 2 --c--.5+ AILERON POSITION S I W L L
12 V - 8 u 1 P I T C H C W D SERVO W I V E - M 11 : : 11- l
- AILERON SERVO gK) R
*3 V-BAR P I T C H C W D SERVO W I V E C IO : : 17 -+ AILERON PATE SIGNAL S
9'4 -+ 8 . -

-
V 4 M P I T C H C Q l l u l l D RATE
1 5 - b V 4 M
-+
PITCH COMMD SIC C
v 4 M P I T C H POS m x
O M A 9 ; i

-
10
11-
& v a P I T C H POS m Y (J2)

-
3 P I T C H A T T I l W E CT X f 30-A AILERON ENGAGE VOLTAGE n

*5 P I T C H ATTXTl.DE CT Y 20-B AILERON EN6AGE M L T A G E

-
f

-
P I T C H A T T I T W E CT 2 C
l? M W A T T I M E CT X : 30-D
18 CAM A T T I T W E CT Y : 20-E ELEVATOR
l q
20
21
- MH( A T T X N D E CT 2
BANK A H I T I D E ERROR H '
CAM A T T X M E E m C'
-
. . .
E+ t ELEVATOR FIELD W R 1
33YC-3
(Jl)

-
22 BAlK A T T I M E SERVO W I V E M2 22 : : : b! 28yDc B
A
i
- :
23-BM A T T I T W E SERVO W I V E C-21 : 2 4 1 tELEVATOR F I E L D NVlbER 2 C
-+
29 BAHK A T T I M E RATE W 19 : : :
-
-
1 3 35+ ELEVATOR SIGNAL C
: ..5& : : :

-
25 MH( A T T I M E RATE C2 20 l* ELEVATOR EXCITATION C F
3b V 4 M ROLL C M M W D SERVO W I V E M2
-- 28 : : 15 - E L E V A T O R
-+
POSITION EXCITATION H G

- .. .. ..
37 V e ROLL co)*uND SERVO ORIVE C 27 : : I b ELEVATOR RATE E X C I T A T I O N H H
12 -+ ELEVATOR P O S I T I O N SIGNAL L
38 -+ V - ( u R ROLL COMM)(D RATE G2 25 : : ERECT: 11 ELEVATOR SERVO -1 R
ROLL COlMD S I G M - 2 b : : DRC" RATE S I G M L S

--
39-V- l? -2- ELEVATOR
3 V - M R ROLL POS Ml'R H 1 . 2* : : 7 F
35

31
:
:
-
-
- 18
1
V B A R ROLL POS

GYROMoN+

STEER FLAG
STEER F L M
--
m

GYRO HIGH LEVEL FLAG

GYRO HIGH L E E L FLAG
c1
l l N A C A T T I T W E PWER

+
-
29
31
32
f

22
-8
2

:
:
2
3

:
:
:
: :

10
:
:
:
N

NAV
RCVR
E L N A T O R ENGAGE WLTAGE
ELEVATOR ENGAGE WLTAOE
(J2)
A

33
:
:
l b
10
-
- +28 W C FLAG POWER
G L I D E SLOPE DEV + Ip
: : : SlRV-1

3
35
3b
;
:
:
12
13
-
11- G L I D E

- am SLW
SLOPE DEV + DN
LW LEVEL FLAG +
W I D E SLOPE LW LEVEL F U G -
: 22-9
:
:
21
22
am SLOPE HGI H LEVEL FLAG + : 11-27

a b -
- VORlLOC DEV +
LEFT
I I I
:
:
32 - Y O
(EP)

28
:
5
9 -
-
WRAOC DEV +
RIGHT

-
VORlLOC HIGH LEVEL FLAG +
:
:
22-39
11 - 50 RUDDER

8
: 38

: 5-
R W A Y FLAG
LOC FREQ VOLTA6E
COlRSE RESOLVER H
+
- 5
f
:
+3
f
- 38
21
331c3
(J1)

1 f 5- COCRSE RESOLVER A : 20

o;
: 5-
: 5-
COCRSE RESOLVER B :
:
22
23
bi E- +RWDER F I E L D N W E R 1 i

-
COCRSE RESOLVER C
: 5- COlRSE RESOLVER D . 2* @ 28 W C B
5 -' M S E RESOLVER E : 25 +RUDDER F I E L D NVOBER 2 C
-+

-
b : 5- COCRSE RESOLVER F : 2b 13 RUODER SIGNAL c E
C O I R S RESWKR G : 27

--
-' 1* RUDDER E X C I T A T I O N C r
95 W D E R POSITION E X C I T A T I W H G
1 b ----.c-.5+ RUDER RATE E X C I T A T I O N H H
t2 -+ RUDDER POSITION S I W L
91 RUDDER S E R W 6RD a
Y? RATE SGNAL S
.. .- .. RUDER
(J2)

... .... ...- RUDDER E M A G E VOLTAGE

RUDDER ENGAGE VOLTAGE
i
C

. . .
.*. .-. ... TRIM YRYO
331D-2-330 ( J I )
k EL TRIM : 31 -C T R I M TbB D T COHT
: j EL TRIM : 33 --++
T R I M TbB D T CON1
767-'8235-001

AP-103F/FD-108 Beech King Air, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 454

May 1/67 22-03-00

Pages 401/95 , 401/96
 COLLINS
MAINTENANCE
MANUAL
QW

AUTOPILOT E)IERXNCY
MPLIFIER WIRE FUNCTION SEWS MSC DISCOMECT JdoX
FLIGHT
WW- COlRSE PEMSTAL DIRECTOR INSTRlMNT FLIGHT AILERON 12lM
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION 33163 J I
(J1)
331AAA blYE-ZF 3298-7A
Jl J2 J l JI J 1
1
... ..
.
.... ... ... ... .
....
.: .-: :.. : U-Gm
...
:
...
:
..
: 3 1
. .: .:
-...
: : 11-5
-.. . . - .
. : 30-1 .. ..
. . .
:
:
:
:
COWUSMN
CMRASSMN+ .
-0
3
19- I Y - I? 25 . .
9 t 1 : : . .. C O W U S DATA X
. . . . .
+2
... ...
X': TRIM M)TOR GROUlD
18WC
B
A
.. ..
CORUS DATA Y
.. .. .. .. -.9
+ 3
.. .. T R I M ENGAGE WXTAGE
TRIM ENGAGE CROWD
D
t
L
M

... ..
.. .. COhpASS DATA 2
: : : : IIi :
.
Y9
.
-
- M U S DATA X

. .. . . .. :
:
:
: :
:
:
:
3
+
4
i .
:
50
51 - COWASS DATA Y
CDWASS DATA 2

.... ..
+
30
:
:
24
15
COWASS FLAG
M A S S FLAG -
2 b V K Hffi PWR
.
.
.
3

I
3
1

s
9
:
:
:
:
:
: :
:
:
..
:
:
l b
20 : 5-
COmC)N
WADING E a SYNCtRO C '
.. I
I
?
b :
:
:
:
:
:
... ..
:
:
21
13
:
f
5 6 HEADING ERROR SYNORO H '
5- HEADING RATE G I
.
.
l
I s
a
: :
: : :
: ... ..-
. a : :
. .
...
: 14 *' WEADING RATE C2 :
: 12 HCG M T CON1 C l . a : : :
: 11 H f f i M T CON1 M 1 . 2 1 : : :
... AIRSPEED

11
13
95
:
: 5
.
Y f HEADING DAM swum cn
HEADING DATUM SYNCHRO H '
COUISE D A M SYNCHRO C'
CDUISE MlW SYNMRO H '
DISTANCE INDICATOR FLAG +
-
:
:
f
:
..
23
33mtE:
ZY
3Y
:
8bDE-Z
(Jl)
9 :
59
58 P
-
...
A
.-
...
I R S
.
P
AIRSPEED SIGNAL
E E D EXCITATION H
SENSOR
59062
J1

... ...
Yb DISTANQ INDICAXHI FLAG ID : bD AIRSPEED EXCITATION C
Y? DISTANCE INDICATOR 2 6 VAC H ; a: * .
Y8
W--I
- :
: .. .. DISTANCE INDICATOR 2 b VAC C
. . . :. 1:
.
50 DISTANCE INDICATOR UNITS SYNORO X : : Y :
51 DISTANCE INDICATOR W I T S SYNCHW Y
DISTANCE INDICATOR TENS SYNCHRO X
.. :
.
3 :
b :
52
53 DISTWCE INDICATOR TENS SYNCHRD Y
DISTANQ INDICATOR HWOREDS SYNMRO X
. .. 5 :
7 :
5Y f
55
.. :
... -8
9
OISTANQ INDICATOR W E D S S Y N W -Y
2b V K C O W R P
b
- I1 : : :
8:
:
.. : : : :
..
32 1 b VAC A T T I M E PVR 15
.
n
33-62b
-
-
VAC AlTIME PWR CW-lb : : : :
--. ....
-v
: 19 5 VAC LIGHTING RIR a
; 80 5 VAC LIGHTING PbR OM .
25. .: : : DC GmWD i - i L I i : :
... .. .. ..
.. ...
: : 115 VAC WEADING PbR 5 -c 55 b : :
: : I15 VAC A T T I M E PbR Y 5b C
. . 9 +28 VDC P W E R 4
- 4 .. 5Y : 0
G : :

...
: :
..
e
.
--. .
.
+28 VDC S EW CLUTCH PWER ~

.: . . . . h b :
.. ...
-*q :

....
: : :
... ....
:Gm QXKHD

...
..
. .....
. .. .. .. ... : bi-18 wc POWER
- T :
..
RUXlER YRVO M E R
.. .. .... ... .
. .
...~ .. ...
..
.. .. ..
... ...
.. .. @@b
@ b 3 -0- RWMR SEW0 POWER
(c AILERON SERVO m w E R -- E
10
.
. . . .... .. .. .. .. .. D
i d - AILERON SERVO PWER
ELEVATOR SERVO M E R
p
& .
. 63 M W D
RELAY

.. .. PITCH STEERING + LP :
I @b; -0- ELEVATOR SERVO POWER a :
: : :
. .
-
3-31 tRD- 1 :
: : PITCH STEERING + W Y N . *-e1 : :
.. .. :
: :
: ROLL STEERING + LEFT
ROLL STEERING + RIGHT
.
:
12- 31
13 -C 21
:
:
. ..
f

.~
-
.

: : L GYKI MODE + 13 Yl YO :
HEADING MODE +
:

...
:

.
:
...
:

.
K
J
...
.
.
..-
VORlLOC MODE +
.
I
.
;c:,t
f
:
Y?
Yb

;
bY
~.
I
.
*>
:
.
co *R owm DM +-
i fi'
6 A

I+=
I
: : i I

...-
+ APPROAOl l a x +
... ..- .. .. APPROACH MODE
: : 9 5 . f 48 APPROACH MODE +
I

.. .- : : EXT STR + DN f 1?-l : : ... I

- - : : E X 1 STR + LP : 3?-1 : : -:I
ALT HOLD
...
:
...
..
W
..
.
-
...
ALTITUDE HOLD INTERLOCU
..
:
..
: Y
..
b .
.. .. : bb
-- MTINDE HOLD INTERLOO(
ALTITUDE HOLD INTERLOU
DISCONNECT SWITCH H - I
I

...
...
..-
..... .
..
.
.
..
.
:
:
:
:
:
:
39-
:
:
Y5
>
: ALTITUDE
:
:
:
:
....
b?
Yb
..
- DISCONNECT SWITCH C
GLIDE SLOPE M)KE + PILOT 0s
01

DISCONNECT SWITCH
COPILOT'S
:
.. .. .- . .: .: : CONTROLLER : ..

.
..
..
..
..
.
....
..
.-
V
.
:
:
:
:
..

:
.
.-
:
:
:
ALTITUDE
ALTITUDE
ALTITUDE
ALTITUDE
ALTINDE
HOLD MODE +
RATE H' +P
RATE C ' 4 6
ERROR H ' 4 9
ERROR C ' 4 6
:
: :
f
:
:
f
r
3Y
21
33
z3-
:
Y7-3Y:
-
--e9
: 59OA-3A
: (JI)
1Y :
1s :
Ib
27 .
i ..
:

:
-
...
*I
'12
.
...
.
767-82i5-001

A P - 1 0 3 F l F D - 1 0 8 Beech King A i r ,
Mar 1/73 Interconnecting W i r i n g D i a g r a m 22-03-00
F i g u r e 454 (Sheet 2) Pages 401/97, 401/98
 a
COLLINS MAINTENANCE
w MANUAL

FLIGHT
ANNUN- C M S t PEDESTAL DIRECTOR INSTRUMENT FLIGHT ALTITUM AUTOPILOT ENRGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTIOh AHPLIFIER COWUTER CONTROLLER POWER WLIFIER WIRE FUNCTION SERVOS MISC DISCONNECT J-WX

331A-bA blYE-?F 3298-7A AILERON 121A-Z

8 41 J2 J I JI J2 33963 J1

12 : P I T C H SOOTSTRAP TRANSMITTER X : 39 z . Y3 -
- ALTITUDE G A I N CHANGE E X C I T A T I O N
13
19
15
Ib
2b
27
:
:
:

:
:
;
P I T C H EOOTSTRAP TRANSMITTER Y
P I T C H BOOTSTRAP TRANSMITTER Z
PITCH BOOTSTRAP EXCITATION n
P I T C H BOOTSTRAP E X C I T A T I O N C
BANK BOOTSTRAP TRANSMITTER X
0ANK BOOTSTRAP TRAkSMITTER Y
:
..
:
..
:
:
:
;
:
92 <
93
3bz-B
35
37
-
- GRD
GRC
59
:
I
:
YY
+5 -ALTITUDE
A L T I T U M G A I N CWANGE NO. I
G A I N MANGE NO. 2

-CEXTW UPTI ET CRH STEERING

+
m)N
28
29
:
:
BANK BOOTSTRAP TRAUSMITTER Z
BANK BOOTSTRAP E X C I T A T I O N H
I8 .
:
19 - 6
-* EXT P I T C H STEERING B
A

30 ; BANK BOOTSTRAP E X C I T A T I O N C : 725 AC P I T C H STEERING A

--
: 2b - - S b AC P I T C H STEERING B

-
AEADING WARhING DATA X
-+

--
HEADING WARNING CATA Y . 21 PROCESSED P I T C H DATA A
HEADING WARNING DATA Z : 28 -5 6PROCESSED P I T C H DATA B
: +
HEACING WARNING OATA H
HEADING WARNING DATA C
HEADING WARNING CATA H '
:
:
18
YB
:
: :
: -
W bO
18
57
-
INTERNAL P I T C H STEERING OFF
ALT HOLD OFF +
EXT ROLL STEERING A
HEADING WARNING DATA C '
: -
19 -b

-
25 -+
EXT m L L STEERING
PROCESSED BANK CMC A
E

I '
:
: -
Zb -
35
36 -b
6
-+
PROCESSED BANK 0.0 B
PROCESSED BANK DATA A
PROCESSED BANK DATA B
, '
: -
55 ---r------5* EXT BANK 0.0 B
59 - 6 EXT E W K CMD A
P I T C H MOkITOR + : I? - 12 :
CS ARM : GLIDE SLOPE ARM. ANN. - . b :
GS t X T : G L I D t SLOPE EXT. ANR. - : Y2 :
N I L ARM ; NAV/LOC ARM. ANN. - : : b :
N I L CAP1 : NAVILOC CAPTWE ANh. -
PUR ANNUNCIATOR POWER
-
GA <
GS CAP1 :
GO AROUNL ANN
G S CAP ANI* - :
:
:
lb
5
:
:
:
:
MKR 8CK
RCVR
5 124
~.~
: : : (JI)
MIDDLE VARKER . 13-9
: : 1 8 , : 51 INTERNAL mLL 5 ' I N G OFF +
A P I T C H CONTROL EXC A . 21 RCVR
NAV NAV
CONT : 51RV-I
B P I T C H COkTROL SiGNAL . 20 SELF T E S l
C P I T C H COhTKOL EXC B .. .. .. : 22 51RV-1 313N-3 : RELAY
L. . . . (J2) (J2) :
TURN CONTROL EXC A . . . 21 ; 19
E T W h CONTROL EXC B . . . 22 :
G TURh COkTROL S I G h A L . . . 20 :
h I N T MOTOR COhTROL VOLTAGE. . . . f b2
P I N T 2bVAC IOTOR E X C I T A T I O h C . . . 2+ :
F I N T MOTOR RATE SIGNAL . . . . b3
S I N T W T O R SIGNAL COMMON . . . : 2Y
T 26VDC PAkEL L I G H T PUR
GROUNC . .. .. ..
X . . .
Y ENGAGE VOLTAGE .. .. ..
z . . .
2 ENGAGE P U L S t . . . : Sb
DISLNGAGE VOLTAGE . . . : 37
ENGAGt READY . . . : 55 A

49; ALTITUDE HOLU MODE + . . . : 38

HEADING SYNCH CUTOLlT . . . 38 : . .
AILERON T R I M 33 :
AILERON T R I M . . . 3Y :
n RUCDER T R I M . . . 53 :
RUDDER T R I M 52 :
3 . . . 9
7 115 VAC POWER 1 :
r I N T 2bVAC MOTOR L X C I T A T I O N 84 23 :
_ . ENGAGE INTERLOCK
5
t .. .. .. i
J AILERON CLVTCH VOLTAGE 39 I
V ELEVATOR CLUTCH VOLTAGE . . . . 39
w RUDDER CLUTCH VOLTAGL . . . 56 ,
M
x
Y
m v D c AUTO PLIOT

SPARE
PWR
..
..
..
..
..
..
:
:
53
9
- YAW D W E R ENGAGE M3N t
SENSING
2 .. . . W I T I
AA .. ... ... 3Y5A-9B @ :
88 .. . . (ROLL) : YAW D M SW
cc . .. .. : A
DO GYRO MODE .. ... ...
b5
8 .
ROLL W T E W T C R GRD
115 VAC POWER
..
EE
FF
HEADING MODE
NAVILOC m)DE .. ... ... 32
31
:
.
ROLL RATE E X C I T A T I O N C
ROLL FATE E X C I T A T I O N H
E
F
GG WPROACH WDE .. ... ... 29 ; ROLL RATE SIGNAL X G
.. .
Yri MoDt VOLTAGL n
. . ..
. ..
.
767-8235-001

AP-103F/FD-108 Beech King A i r ,

M a r 1/73 Interconnecting W i r i n g D i a g r a m 22-03-00
F i g u r e 454 (Sheet 3) Pages 401/99, 401/100
 a
COLLINS MAINTENANCE
w MANUAL

FLIGHT
UMII- CwRtE PEISTAL DIRECTOR ALIIOPILOT E*ERQycI
CIATORS IWICATOR MTROLLER IWICATOR WIRE FU(cT1ON msc PWER ULIFIER DISCOmECT

Q
33-
J1 J2
blW-2F
J l
r n ? A
J1 J2
Q J l
5bzc-l
Jl
LlM
Jl
flP) (PI
.. . .
PITCH DIFFERENTIAL RESOLVER X
RESOLVER Y ..
... ... ... : -
- P I T c n RATE LOTOR w
(PITOI)
A

... ...
PITCH DIFFERENTIAL 8
PITCH
PITCH
DIFFERENTIAL
DIFFERENTIAL
RESOLHR
RESOLVER
2
R
. . .
:
:
10
32 -
-
115 VAC KIVER
P I T O I RATE EXCITATION C
B
E
PITCH
PITCH
DIFFERENTIAL
DIFFERENTIAL
RESOLHR
RESOLVER
C
R'
..... ..... .....
:
:
31
n - P I T C H RATE EXCITATION H
P I T C H RATE S I W x
f
G

-
PITCH DIFFERENTIAL RESOLVER C'
DAM DIFFERENTIAL =saw x
.. .. .. IAm IUTE
eANK DIFFERENTIAL RESOLVER Y
. ... ...
-
s*R)
Iw( DIFFERENTIAL RESOLVER 2
... 33-

-
YW RATE mow. m
. D A M DIFFERENTIAL RESOLVER H A
.... ....
. . DAM OIFFERENTIAL R Y X V E R C
DAM D I F F E R E h T I A L R E Y X K R H ' ... IO
51
115 VAC POKR
YAU RATE EXCITATION C
B
E
DAM DIFFERENTIAL REYLVER C '
... ..... .....
50 YAW RATE EXCITATION H
x
F

--
RAD ?8 YAW RATE S I % G
..
: . . . . STW WEAR P I L O T ' S w. PAWL
: Y
50
51
: l? -5+
RADIO A L T I M E FLAG
RADIO A L T I T -
+
FLAG
AUX DC A L T I T W E
-
+ : 12

: 53 4 b AUX DC K T I T W E : ?b

nr#KS VSED: 10. THE s2w NID s m - 5 6 SHCUD I MTED AS aoy TOETIER AS COSSIDLE, PFEFERAKY ON A CUM m. THESE
S I W M LEADS NJST BE TWISTED UO WIRED POINT TO P O I N T B E W N THE W I T S . TWISTED P A I R S Y M U O DE KEPT
SV N I S T E D SHIELDED P A I R 4 J A C E N T AS SKFIT AS P R A C T I O L IWD U T ALSO I SHIELDED I F O W 3 TW) FEET L W .
M WIRES AS U(0vN ON CRAVING 11. ColPMATOR U A M I f f i RESOLW3S. W NOT USE FOR O W R P W S E S U L E S S LOADING EFFECT I S EVMVATED.
56 S H I E L D T I E D TO Q)OU(D AT W I T 12. TOTK WIRE RIM FROM U S TO 10lA-Z TO 5 b 2 W TO 339- ( P I N B) FOR EAOI P R I M M Y SERW lUST WT EXCEED
51 SINGLE W I E L D E D WIRE 0 FEET I F AYG 20 VLE I S UED. W E N GREATER Tw)( 90 FEET, I N S T A L L T E W W S AT S c X 4 *ou(I W RUN
ALL S1 SHIELDED T I E D TO X l ETC. Sl'V FOIR WIRES TWISTED WITH SHIELD AVC 20 WIRE FROM 5- TO m N A L W D AYC l b WIRE FROM TOIIW 3WG3 P I N B.
E3 mEs u.
I?.
W ISOLATED loC€ S K T O I I S PROVIDED FOR USE WITH COPILOTS R I M DIRECTOR.
WITH T R I M INDICATOR WNNECTIORS AS y(GIw YK, THE RESERVING L I W S I M S T M L E D FOR m
CAM SERW WSTM YRUD n m awsE mcc VIMD FFKW M WSTW END UDER THE FOLLOVING - IA
C l SERVO RusIffi TIE

AHINDES:

mns:
1. ML WIRE S I Z E S ME W. 22 M E S S E S I W T E D OMERUIY BY W R S I N W I R E S . SHIELDED WIRES ARE W D E D
ELEVATOR
RIE€€R
-
AILERON - R I W T W
P I T O I lP
-RIWTYW
AT o(E END M Y .
2. SHIELDS ON TIE NAV R E S O L H R LEADS FROM THE NAVIGATION R E C E I K R S W U D BE QIOU(OED AT THE 5lRV-1. 15. POYER FROM A pmncu.m CR
I CUT
I CRWER OR FUSE RAY F W ~WYER
E FOR IRE TWI( O(E EWICIENT. THS
I WILL
3. FOIR WIRES M S T E D WITH SHIELD fOR C O P A T M I L I T Y I N FUtlRE ARINC I N S T K L A T I W S . BE INDICATED I N TIE I h l E R Q w * E C T K M R QKW BY A LETTER WITH NI OCTCOON S T # o c ylow I T . C l p I T A L LETTERS
?. A R L A Y NJST IINSTALLED I N "I€ U W T J W C T I O N E 4 X TO E L I M I N A T E M SELF TEST FEATIRE OF l7E S n V - 1 FOR DC YY) LOYER UY LETTERS FOR AC.

5.
W E N Tl€ M W I L O T I S E W D .
M * I I I C W T I C F L I G H T CONTROL SYSTEM AS C O l Y C T E D I N THIS W I N G R F L E C T S LOADS AS FOLLWS: A - -
28 VDC D I W N 6 C I R C U I T a - -
5 VDC D I W N G C I R C U I T

-- -
BI C. D, E ?8 W 5 AR b. C. d 115 VAC 1 M P
Ycs LOAD CIRCUIT REQUIRED L W D ADDITIQUL LOADS G-28VDC1 W e a 115 VAC 1 MP
f iis VAC 3 AR
m-fwu ID0 w J U C E R B P 4 3 TO W-33 OF 5lRV-1
S L I D E SLOPE P O 1 m 2 M oH(s X I + E R lP-8 TO lP-2 UO lP-3 OF 51RV-1 lb. M W MWND R L A Y I S I I K T M L E D FOR VI1165 L E K L . P I T O I lP GO *Roue. 64 AROUO BWrCU I S m L Y OPEN
OLIDE SLOPE FLS 250 OHllS J U P E R lPp-21 TO lP-2b OF S l R V - 1 UO -LY I S I M S T k L E D ON cQ(TRy C O L U N U E E L . 'TO C€ACTIVATE W *ROW PROVISICU P€WK TIE RELAY
LOC FLAG 250 ocls J U l P E R BP-32 TO BPp-ll OF 5 l R V - 1 YY) COWlECT MOSE YWES ToQlHER l W T UE C O M C T R , BY T)(E m L Y CLOSED C W T K T S OF TIE RELAY.
COIRSE @M 2w (m6 A W E R Bp-39 TO BP-30 AND BP-W OF 51RV-I l?. EWICIENT woyll N
I MIS CULM MY m i WE OMJLETE WRIM IYORUTION INDICATED. F
IORE naffi
Y P L I W E SYSTEM Y l l W L S FOR THIT E W I R I E N T W Q U D ICCEQED.
L. TIE COKR FOR Tl€ co(cASS SYSTEM W S T BE OF TIE S Y E PHASE AS THE REST OF THE A U T Q A T I C F L I G H T COWTROL 18. OMIYECTIONS TO nm TM MOTOR OJNIFSL WENDS ON AIRQWT RG
IN
IG.
SYSTEM. 19. P R O V I S I W S FOR M I 0 MTIIIETER ( O P T I O Y L ) .
?. P O E R LEADS DENOTED BT "DIM" YKXLD BE T I E D TO C O W I T L I G H T D I U N G CIRCUITS.
20. W H E N O P T I O N A L 5 9 O A - 3 1 SERVICE B U L L E T I N N 0 . 3 I S INCORPORATED,
8. P I K I N G W I T 37%-W ) AND RATE GYRJ 33- WahD I LOCATED AS CLOSE TOOEWER AS POSSIBLE.
T H E F O L L O W I N G INTERCONNECTING WIRING C H A N G E S ARE A P P L I C A B L E :
9. Y Y U I C I A T O R S M S E N Us1 NDT EXCEED 100 MA. A toll))( +28 M C I S USED FOR ANNLNCIATOR PWER. MMCIATION
V I R I E S WITH T I L P A R T I C U A R I N S T A L L A T I O * . D E C E W I N C Leo)( = S I R E D O e E R A T I f f l . S P E C I F I C W C I A T O R S MAY I
DELETED. R E M O V E CONNECTION B E T W E E N J I ( B P ) - 3 8 OF T H E 5 6 2 C - 4 AUTO-
P I L O T A M P L I F I E R A N D JI-d O F T H E 614E-ZG P E D E S T A L C O Y T R O L -
L E R . R E M O V E C W N E C T I O N B E T W E E N JI-V O F T H E 6 1 4 E - 2 6 P E D E S T A L
CONTROLLER AN0 JIA(TP1-47 OF T H E 5 6 2 A - 5 6 F L I G H T COMPUTER.

M A K E C O N N E C T I O N S A S SHOWN.

PEDESTAL FLIGHT ALTITUDE AUTOPILOT

CONTROLLER WIRE F U N C T I O N C O M P U T E R C O N T R O L L E R AMPLIFIER
614E-26 562A-50 590A-3A 562C-4
JI J I A JIB (JI) J I JI
(TP) (BP) (TP) (BPI

V---- ALTITUDE HOLD MODE+---.-------- 34

ALTITUDE HOLD M ODEC47 - ----- -- 20 ------ -------- 38

AP-103F/FD-108 Beech King Air,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 454 (Sheet 4) Pages 401/101, 401/102
 dh
COLLINS
MAIIVTENANCE
ww MAIYUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER DISCONNECT

0 INDICATOR @ 562C-4 I 2 IA-2

33 I A-6A 6 14E-2G 3296-7A 344C-IO 562A-56
JI J2 J I JI 32 JI J2 J I A JIB
JI
(TP) (BPXTP) (BP)

,-. EXT STEERING A

18 I 1
IC; I EXT STEERING B
1-1
25 I PROCESSED BANKCMD A
PROCESSED BANK CMD B
PROCESSED B A N K D A T A A
PROCESSED B A N K D A T A B
EXT BANK CMD B
EXT BANK CMD A

MKR BCN NAV NAV S LRV- I

RCVR RCVR CONT SELF TEST
512-4 51RV-I 313N-3
(Jl) RELAY
MIDDLE MARKER 43 4 (J2) (J2)
18 57 INTERNAL ROLL STEERING OFF t
A PITCH CONTROL EXC A 21
B PITCH CONTROL SIGNAL 20
C PITCH CONTROL EXC B 22 14
E TURNCONTROLEXCA 21 L -,
F
G
TURNCONTROLEXCB
TURN CONTROL SIGNAL
22
20
jt
54 1
N
P
INT MOTORCONTROLVOLTAGE
INT 2 6 VAC MOTOR EXCITATION C 24
62
n -
R INT MOTOR RATE SIGNAL 63 it
S INT MOTOR SIGNAL COMMON 24
T 2 8 VDC PANEL LIGHT PWR 4 :;:@
1 :,,
U GROUND GRD K A
Y ENGAGE VOLTAGE
a ENGAGE PULSE 56
5 DISENGAGE VOLTAGE 37
-

AILERON CLUTCH VOLTAGE 9 ‘

-
20
U
ELEVATORCLUTCHVOLTAGE J9
-
20
v
-
RUDDER CLUTCH VOLTAGE -6 20

2
W A

M t 2 8 VDC AUTO PILOT PWR

53 YAW DAMPER ENGAGE M D N t

YAW CAMP SW

TPI-3123- 044

M a r 1/73 AP-103F Aerocommander 1121 J e t ,

Interconnecting Wiring Diagram 22-03-00
Figure 455 (Sheet 1 of 4) Pages 401/103, 401/104
 e
COLLINS
JI.AISTEN.4SCE
3IASUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER VERT AMPLIFIER DISCONNECT
INDICATOR REF AILERON
@ 331A-6A 6 I4E-2G 329B-7A 3 4 4 C - ID 562A-5G 332D-1 I @ 562C-4 334c-3 121A-2
JI J2 JI JI J2 JI J2 J I A J I B IJ I) JI JI (J I) JI
(TP) (BP) (TP) (BP) (TP) (BP)

A
@ (- MANUAL PITCH COMMAND H '
MANUAL PITCH COMMAND C'
36
26 El 2 8 VOC B
C
HEADING DATUM SYNCHRO C' 23
HEADING DATUM SYNCHRO H' 33 E
COURSE DATUM SYNCHRO C'
COURSE DATUM SYNCHRO H'
PITCH ATTITUDE CT X
24
34
30
a
A 16
AILERON
AILERON
AILERON
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION H
-
F
G
H
PITCH ATTITUDE CT Y B-2 12 7 AILERON POSITION SIGNAL L
PITCH ATTITUDE CT Z C I1 ?. AILERON SERVO GRD R
BANK ATTITUDE CT X 30-D 17 :! AILERON RATE SIGNAL S
BANK ATTITUDE CT Y 20-E (J2)
BANK ATTITUDE CT Z F 37 AILERON ENGAGE VOLTAGE A E
DD GYRO MODE 27 AILERON ENGAGE VOLTAGE B F
EE HEADING MODE ,'I 28 ELEVATOR
334c-3
FF NAV/LOC MODE
GG APPROACH MODE Q :7 (JI)
HH
@)
MODE VOLTAGE H
STEERFLAG t
+28 VDC FLAG POWER
28
54 a
3 ELEVATOR FIELD NUMBER I

ELEVATOR FIELD NUMBER 2

A
B
C
EXT STR t ON
EXT STR t UP
K
j 3 FAST
ERECT
15
ELEVATOR EXCITATION C
ELEVATOR POSITION EXCITATION H -G
E
F

H
G
16- ELEVATOR RATE EXCITATION H -H

I 15 VAC ATTITUDE POWER - d

ELEVATOR POSITION SIGNAL
ELEVATORSERVOGRO
L
R
GYRO MON t I O -N
17 ,_, ELEVATOR RATE SIGNAL S
NAV
(J2)
RCVR A J
ELEVATOR ENGAGEVOLTAGE
5 IRV- I ELEVATOR ENGAGEVOLTAGE B H
(TP)
GLIDE SLOPE DEV t UP -3 8 Q
SLIDE SLOPE OEV +ON 22 9
GLIDE SLOPE LOW LEVEL FLAG t 21
GLIDE SLOPE LOW LEVEL FLAG - 72
Q6
=
:E
RUDDER FIELD NUMBER 1
28 VDC
A
B
GLIDE SLOPE HIGH LEVEL FLAG t I 1 3 7
RUDDER FIELD NUMBER 2 C
(B P)
VOR/LOC DEV t LEFT 32-0
' RUDDER SIGNAL C E

GS CAP
VOR/LOC DEV +RIGHT
VOR/LOC HIGH LEVEL FLAG t
RUNWAY FLAG - 5
22-39
I 1-50 i i 4
42
46 , . t

'
RUDDER
RUDDER
RUDDER
RUDDER
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
-G
H
L
F

+
LOC FREQVOLTAGE 43-38
COMPASS
320A-2A 41
47 + ~ ~ ~
R
~S
(J2)
~ ~ ~ ~ A L

JI J2 RUDDER ENGAGE VOLTAGE A B

27-GRD RUDDER ENGAGEVOLTAGE B C
COMPASS MON - 30 17
COMPASS MDN t 29 - - 25
PITCH STEERING t UP 31 -9" -11 COMPASS DATA X
PITCH STEERING t DOWN 21 4 50- COMPASS DATA Y
ROLL STEERING t LEFT 31 3 51- COMPASS DATA Z
ROLL STEERING t RIGHT 21 54 AIRSPEED SIGNAL
PITCH MONITOR t 12 12 58 AIRSPEED EXCITATION H
GS ARM GLIDE SLOPE ARM. ANN. - 6 60 AIRSPEED EXCITATION C
GS EXT GLIDE SLOPE EXT. ANN. - 42
N/L ARM NAV/LOC ARM. ANN. - 6
N/L CAP NAV/LOC CAPTURE ANN. - 39
PWR
GA
ANNUNCIATOR POWER
GO AROUb!3 ANN - 16
(9
TPI-3123-044
43 Y SPARE 9

AP-103F Aerocommander 1 1 2 1 J e t , Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 455

Nov 1/68 22 -03-00

Pages 401/105, 401/1'06
 COLLINS
MMAINTEIVANCE
MANUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MISC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER DISCONNECT
6 I4E-2G INDICATOR
8 331A-6A 3298-7A Q TRIM
121A-2
JI
JI J2 JI JI J2 COUPLER
I 6 IA- IA
(J I)
k ELEVATOR TRIM INDICATOR 34 ,-s 1-1
TRIM UP t 13
3 L 1

+
33
j ELEVATOR TRIM INDICATOR \ f TRIM UP- 'J I ' 11
GRD 5) TRIM COUPLER GROUND , I I
I
h I 15AC 'a' 8
5 VAC LIGHTING PWR
5 VAC LLGHTING PWR COM L o _ TRIM ENGAGE VOLTAGE
TRIM ENGAGE GROUND
L
M
DC GROUND 67 GRD
FAILURE WARNING LIGHT
I 15 VAC HEADING PWR ~
5 b 35 ;<1, TRIM DN t
36 \I TRIM DN-
I 15 VAC ATTITUDE PWR 56 ARM UP
9 t 2 8 VDC POWER 54 TRIM UP
TRIM ON 29
e t 2 8 V D C S E R V O C L U T C H POWER 6 ARM ON 27
DN RELAY GRD 31
-9
UP RELAY GRD
GROUND
2 8 VDC POWER
RUDDERSERVD POWER
RUDDERSERVO POWER
AILERON SERVO POWER
AILERON SERVO POWER
ELEVATORSERVO POWER
ELEVATORSERVO POWER
"X @
L GO AROUND RELAY
GYRO MODE t 41 40
K HEADING MODE t
- - 1 I
47 64
J VOR/LOC MODE t
44
14
-
46
44 - 17
GO AROUND MODE t

H APPROACH MODE t APPROACH MODE t

48
W ALTITUDE HOLD INTERLOCK
45 APPROACH MODE t
ALTITUDE HOLD INTERLOCK ,.
"
I

1- ALTITUDE HOLD INTERLOCK

66 DISCONNECT SWITCH H "
A

DISCONNECT SWITCH C
PILOT'S COPILOT'S
1- 7- GLIDE SLOPE MODE t
DISCONNECT
ALTITUDE
SWITCH
CONTROLLER
590A-3A
(J 1 )
v ALTITUDE HOLD MODE t 47 34@
ALTITUDE RATE H' 34 14
ALTITUDE RATE C' 24 15
ALTITUDE ERROR H ' 33 16 41
ALTITUDE ERROR C' 23 27 42
ALTITUDE GAIN CHANGE EXCITATION
7- -- ALTITUDE GAIN CHANGE NO. I
43 45 ALTITUDE GAIN CHANGE NO. 2
36 @
3 a - G R D
37 GRD
15 59- COMPUTER MON t
I-
19 18 I , EXT PITCH STEERING A
9 19 .,-_.
"
\
EXT PITCH STEERING A
49 25- AC PITCH STEERING A
I ,
40 26 AC PITCH STEERING B
35 27
1-1
I , PROCESSED PITCH DATA A
25 28 ., PROCESSED PITCH DATA B
18 57 INTERNAL PITCH STEERING OFF t
TPI -3123 -044
48 -6 ALT HOLD OFF t

A P-103F Aero commander 1121 J et,

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 455 (Sheet 3) Pages 401/107, 401/108
 a
COLLINS
MAINTENANCE
wlv MANUAL

ANNUN- COURSE PEDESTAL FLIGHT WIRE FUNCTION INSTRUMENT FLIGHT MlSC POWER AUTOPILOT WIRE FUNCTION SERVOS MlSC EMERGENCY J-BOX
CIATORS INDICATOR CONTROLLER DIRECTOR AMPLIFIER COMPUTER AMPLIFIER SENSING DISCONNECT
33 I A - 6 A 614E-2G INDICATOR 344C-IO 562A-5G 562C-4 UNIT @ I 2 IA-2
@ JI J2 JI 3298-7A JI J2 JIA JIB
J1 JI
345A-48
JI J2 JI
(TP) (BP) (TP) (BP) (ROLL)
(TP) (BPI

ROLL RATE MOTOR GRD PA

" I I 5 VAC POWER B
-- ROLL RATE EXCITATION C E
31 ROLL RATE EXCITATION H F
ROLL RATE SIGNAL X G
(PITCH)
-8 PITCH RATE MOTOR GRD A
IO- I 1 5 VAC POWER B
32 - PITCH'RATE EXCITATION C E
31- PITCH RATE EXCITATION H F
29- PITCH RATE SIGNAL X G
YAW RATE
GYRO
3326-2
66 YAW RATE MOTOR GRO A
IO I 1 5 VAC POWER 8
YAW RATE EXCITATION C E
_-
48
YAW RATE EXCITATION H F
YAW RATE SIGNAL X G
SYMBOLS USED:

0 NOTES
NOTES:
I . A L L W I R E SIZES ARE NO. 22 UNLESS DESIGNATED OTHERWISE B Y NUMBERS IN SQUARES. 14. POWER FROM A PARTlCULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT.
2 . SHIELDS ONTHENAVRESOLVER LEADS FROMTHE NAVIGATIONRECEIVERSHOULD B E G R O U N O E D A T T H E 5 I R V - I . THIS W I L L BE INDICATED IN THE INTERCONNECT POWER COLUMN B Y A LETTER WITH AN OCTAGON SYMBOL AROUND
3. THIS INTERCONNECT IS FOR USE IN INSTALLATIONS WHERE A SEPARATE FLIGHT DIRECTOR IS INSTALLED. IT. CAPITAL LETTERS FOR DC AN0 LOWER CASE LETTERS FOR AC.
CONNECTIONS TO THE RESPECTIVE COMMAND SOURCES INDICATED ARE REQUIRED FOR F U L L SYSTEM OPERATION.
4. A RELAY MUST BE INSTALLED IN THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF TEST FEATURE OF THE 5 1 R V - I WHEN
-
A 28 VDC DIMMING CIRCUIT -
a 5 VAC DIMMING CIRCUIT

THE AUTOPILOT IS ENGAGED.

B,C,D,E -
28 VDC 5 AMP b,C,d -1 1 5 VAC 2 AMP
5. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED IN THIS DRAWING REFLECTS LOADS AS FOLLOWS:
-
G 28 VDC I AMP e,h -I I 5 V A C I AMP
f - 115VAC3AMP
AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS
15. THE GO AROUND RELAY IS USED IN CONJUNCTION WITH APPLICABLE FSB FOR WINGS LEVEL, PITCH UP GO AROUND.
NONE TO-FROM IO0 OHMS DEPENDENT ON FLIGHT DIRECTOR INSTALLED GO AROUND BUTTON IS NORMALLY OPEN AND SHOULD BE LOCATED ON THE WHEEL IF POSSIBLE. TO DEACTIVATE
10,000 OHMS GLIDE SLOPE POINTER 2 0 0 OHMS GO AROUND PROVlSIDN,REMDVETHERELAYAND CDNNECTTHOSEWIRESTDGETHERTHATARECONNECTEDTO
NONE GLIDE SLOPE FLAG 250 OHMS THENORMALLYCLOSED CONTACTSDFTHEREPLAY.
NONE LOC FLAG 2 5 0 OHMS
10,000 OHMS COURSE BAR 200 OHMS 16. WHEN OPTIONAL 590A-3A SERVICE BULLETIN NO. 3 IS INCORPORATED, THE FOLLOWING INTERCONNECTING WiRING CHANGES ARE APPLICABLE:
REM5VE CONNECTION BETWEEN J l ( B P p 3 8 OF THE 562C-4 AUTOPILOT AMPLIFIER AND J1-d OF THE 614E-2G PEDESTAL CONTROLLER.
6. THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL SYSTEM.
REMOVE CONNECTION BETWEEN J l - V OF THE 614E-2G PEDESTAL CONTROLLER AND J l A ( T P F 4 7 OF THE 562A-5G FLIGHT COMPUTER.
7. POWER LEADS DENOTED B Y "DIM" SHOULD B E TIE0 TO COCKPIT LIGHT DIMMING CIRCUITS.
8. SENSING UNIT 3 4 5 A - 4 ()AND RATE GYRO 332G-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE. MAKE CONNECTIONS AS SHOWV BELOW.
9. THESE LEADS MUST BE TWISTED AN0 SHIELDED IF OVER TWO FEET LONG.
PEDESTAL FLIGHT ALTITUDE AUTOPILOT
I O . T H E 5 6 2 C 4 A N D T H E 5 6 2 A - 5 6 S H O U L O BEMOUNTEDAS CLOSETOGETHER AS POSSIBLE,PREFERABLYONADUALMOUNT.
CONTROLLER M R E FUNCTION COMPUTER CONTROLLER AMPLIFIER
THESE SIGNAL LEADS MUST BE TWISTED AND WIRED POINT TO POINT BETWEEN THE UNITS. THE TWISTED PAIRS SHOULD
BE AS SHORTAS PRACTICAL AND MUST ALSO BESHIELOEDIFDVER TWOFEET LONG. 614E-2G 562A-5G 590A-3A 562C-4
I I. TOTAL WIRE RUN FROM BUSS TO 12 I A - 2 TO 562C-4 TO 3 M C - 3 (PIN B ) FOR EACH PRIMARY SERVO MUST NOT EXCEED 90 FEET J1 JIA JlB (JI) J1 J1
IF AWG 2 0 WIRE IS USED. WHEN GREATER THAN 90 FEET, INSTALL TERMINALS AT 5 6 2 C - 4 MOUNT AND RUN AWG 20 WIRE FROM (TP) (BP) (TP) (BPI
5 6 2 C - 4 TO TERMINAL AND AWG I 6 WIRE FROM TERMINAL 3 4 4 C - 3 PIN B. V ------------ALTITUDE HOLD MI3DE t -------e 34
12. AN ISOLATED MODE SWITCH IS PROVIDED FOR USE WITH COPILOTS FLIGHT DIRECTOR. ALTITUDE HOLD MODE+47-- ------ 20 -----------_---- 38
13. WITH THE TRIM INDICATOR CONNECTIONS SHOWN, THE PRIMARY SERVO CAPSTAN SHOULD TURN CLOCKWISE WHEN VIEWED FROM THE
CAPSTAN EN0 UNDERTHEFOLLOWINGAIRCRAFTATTITUDES:

AILERON-RIGHT TURN
ELEVATDR-PITCH UP
TPI-3123-044
RUDDER-LEFT YAW

AP- 1 03F Ae rocommander 1121J et,

Mar 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 455 (Sheet 4) Pages 401/109, 401/110
 COLLINS
MAINTEKVANCE

FLIGHT
AMUN- COLRY PEDESTK DIRECTOR INSTMMNT FLIGHT AUTOPILOT EIIERGENCY
DISCONNECT
CIATORS INDICATOR CONTROLLER INDICATOR AWLIFIER COWUrER MISC PWER AWLIFIER WIW N N C T I O N SERVOS MISC J a X

-
0
331-
J1, ,52
blW-ZG
Jl
32-?A
J1 J2
31YC-10
Jl J2
5b2A-5G
J1A J l B
43 Jl
5b2W
Jl
AILERON
331GU
12u3
J l
(TP) (BP) (TP)(BP) (TP) (BP) (J1)
b
7
-
-
-+ PITCH
PITCH
A T T I T I X H ERROR H'
A T T I T L E ERROR C '
-
-
-
-
A T T I T W E SERVO D R I V E 112
23
:
:
:
:
:
:
:

-
+AILERON
*
VOC
+
28
FIELD W R 1

F I E L D WIBER 2
A
B

-
8 PITCH 28 AILERON C
9 PITCH A T T I W SERVO DRIVE C 27 : : 13-+ AILERON SIGNAL C E
10 25 : : 1Y

-
PITCH A l T I T W E RATE 6 2 VERT AILERON EXCITATIW C
11 PITCH A T T I T W E RATE C 2 2b : : 15 AILERON P O S I T I O N EXCITATION H G

-
REF
1 W A L P I T C H COL+MD H ' : 3 b 332611 I b --cb+AILERON RATE EXCITATION H H
2 Mwu P I T C H -0 C' : 2b (J1) 12e+ AILERON P O S I T I O N SIGNAL L
12 V - B A R P I T C H coyMI(D S EW W I V E M1- 11 : 11-+ AILERON SERVO GRD R
't3 __C_ V-BAR P I T C H COWUM) SERVO W I V E C 10 : 17 -----c-5+ AILERON RATE SIGNAL S
e+

-
't't V-BAR P I T C H C o m A H D RATE 8 :
15 V m P I T C H COmAHD S I G COLl- 9 :

-
10 -W V - o * R P I T C H POS M f R X 7 :
1- V-BAR P I T C H POS Wrf?Y b : (J2)

-
3 P I T C H ATTITWE '3 X : 30- AILERON ENGAGE VOLTAGE E
1 P I T C H AlTITVDE CT Y : 20 f B AILERON ENGAGE VOLTAGE F
5
17-Mm
P I T C H A H I T W E CT 2
ATTITUDE CT X : 30 - C
0

-
18 Mm A R W CT Y : 20- E
19 MHK A T T I T W E CT 2 F ELEVATOR
20
21 -6
Bw A T T I M E ERROR H'
Bw ATTITWE ERROR C '
MHK A T T I T W E SERYD D R I V E ME -
-
18
17
:
:
:
:
:
:
:
:
: E+ +ELEVATOR F I E L O HUB=
3310%
(J1)
A

-
22 22 @bi 28 VDC 1
:I
23
2't -W
25 -b
-
-
Bw A T T I T W E SERVO DRIVE C
BAHK A l T I T W E RATE 6 2
BAm A R T W E RATE C2
21
19
20
:
:
:
:
:
:
:
:
: 13
Y 1

-
-+
+ELEVATOR F I E L D NWBER 2
B
C
E

-
ELEVATOR SIGNAL C
36 V-BAR ROLL COL+MD SERVO DRIVE h2 28 : : 1Y ELEVATOR EXCITATIOH C
37 V W ROLL C W D SERVO DRIVE C 27 : : J 15 - E L E V A T O R POSITION EXCITATION H G
: : : f N C I F L T ~ l b *+ ELEVATOR RATE EXCITATION H H
38 V4L*R ROLL COmAHD RATE G
.2 25 : : 12 ++ELEVATOR P O S I T I O N SIG". L
39-V-
-+
ROLL C O W S I G CUM-2b
WS XJ4lR H I : a :
: :
:
H-CAD 11
17
-*
-+
ELEVATOR
ELEVATOR
SERVO GRD
RATE SIGHAL
R
S

- -
31 V-BAR ROLL
35-6v-B*R ROLL POS mCl : 23 : :
I G
: 115 VAC A T
T I M E POWER
: GIRoMDN+ 29 . . 10. N
31
:
:
- 18
GYRO HIGH LEVEL FLAG +
GIRo HIGH LEVEL FLAG
9-STEERFLS-
- 31
32 :
2
:
:
:
: NAV
:
ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGAGE VOLTAGE
(J2)
J
H

i c;:-
-
STEER FLAG
STEER FLAG +
22
-8
: : :
RCVR
5lRV-1

- e 8 VDC FLAG POWER : 5Y (TP)

-
--
33 : 10 G L I M SLOPE DEV UP+ : 32-0 @
3Y
35
36
:
:
:
- 11
12
13 -
G L I D E SLOPE DEV DN+
G L I D E SLOPE LOU LEVEL FLAG
G L I D E SLOPE LW LEVEL FLAG -
+
f 22-9
:
:
21
22
: GLIDE SLOPE u a i LEVEL FLAG + 11 27

.. ..
1 f STY- C M R S E WSOLVER A : l b

29 b -
- VORlLOC DEV LEFT+ :
:
32 - 4 0
(BP)

28
:
5
9 - VORILOC DEV + RIGHT
VORlLOC HIGH LEIlEL FLAG
LOC FREQ WTAQ +
+
: 22-39
: 11-
: 't3
50
38 -
2 : 52)-COLRSE RESOLVER B 22 .
0 ; ST+ W E RESOLVER H 21 .
3 : 5-COLRSE RESOLVER C :
*
b
: S+ COLRSE RESOLVER D
: S b CULRSE RESOLVER E
23
.: 29
25
b : 5+CNRSE RESOLVER F : : 2b
sb C M R S E RESOLVER G : 27
31
32
26
VORlLOC FLAG +
W l L O C FLAG -
T O - F R W ARROW C + TO)
:
.
:
91
12
'13
TRIM
COCPLER
lb1A-IA
27 TO- *FIROW (+ FROM) I 49 (J1)
: : : R A D mup
: : : ALT TRIM W

.. :..
: :
:
8bOF-1
(BP)
RELAY GRD
F A I L L R E WARNING L I M
. .
i 8 50I J7-

-.-.
-5-RADIO
RID10 A L T I M E FLAG
N T I T U O E FLAG -
+
:
.
12
11
AFnW 27
5
29
TRIM
TO AIRCRAFT
SYSTEM

51
f
: -
+ AU4 DC A L T I T I X H
AUX DC K T I T W E
... ... .:..
17
Yb r.
RELAY GRD
Qu)
VAC PWER
115
Y
31
1
8
INDICATOR

...
.. . pJ
.._
T R I M ENGAGE VOLTAGE 20 L

. ... .
. -
T R I M ENGAGE GRD 32 M
: 35 -dY- T R I M I N P U T ON 22

...
..
.--
..
...-
...
..
....
:
:
:
33
39
- 3b
33 -C
31
+*
T R I M I N P U T DN
ELEVATOR R I M I I P U T IS
ELEVATOR TRIM I W U T up
AILERON TRIM INDICATOR
AILERON T R I M INDICATOR
+
-
+
2Y
1-
1
3
- -
+

I @
.. . _ TPI-2551+44

AP-103F/FD-108 Falcon (2-Axis), Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 456

Nov 1/68 22 -03-00

Pages 401/111, 401/112
 COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION MPLIFIER COWUTER COMPASS POWER AMPLIFIER WIRE N N C T I M j SERVOS MISC DISCONNECT J-BOX

331A-bA blYE-ZG 329B-7A 3YYClD 5b2A-5G 3 2 8 A d A @@ 5b2C-4 AILERON 121A-Z

Q J1 J2 J1 J1 52 J1 J2 J1A J I B ( J l ) (J2) J l Jl 33YC3A
(J1)
Jl

. . : :
:
COWASSMON-
COMPASSMON+
.
f
30
29-lY-25
. 17
:

;E,: i: COWASS DATA X

.. ... ... .::
f . . 2 :
. .
'9 c1; .. .. ._ - . .
:
. . COWASS DATA Y
. 3

. . .
'fc:l COWASS DATA Z - Y
: : : : 1 1
:
. 99 -
- COWASS DATA X

- .
COWASS FLAG + :
.
:
.. .. ..
: : : Y
3
:
:
50
51 - COWASS DATA Y
COWASS D4TA Z
30
:
:
2Y
15
f COMPASS FLAG -
2 b VAC H f f i P M
f
31

15
:
3 2 : :
: . : 22-
:
5
2?-Q1D

:
: l b : COmON I l b : : 30- 1 :
: 20 : SP- HEADING ERROR SYNCHRO C ' . 1 7 : : :
: 21 I I 5 b HEADING ERROR SYNCHRO H'- 18 : : :
-

-
: 13 ; 5+ HEADING RATE 62 1 9 : : :
: 19 : 5 6 HEADING RATE CZ . P o : :
: 12 Hffi MOT CONT C l 21 : .- :
. .
-
: 11 H f f i MOT CONT M 1 2 2 : : AIRSPEED
: + : HEADING DATUM SYNCHRO C' 23 : SENSOR
.
:
12
13
45
Yb
Y?
-
5
:
I

:
~
HEADING D A N M SYNCHRO H'
COLRSE D A T W SYNCHRO C'
COLRSE D A M SYNCHRC H '
DISTANCE INDICATOR FLAG + P
DISTANCE INDICATOR FLAG
DISTANCE INDICATOR 2 b VAC H
-
; 3 3
; 29

:
DME
8bOE-2
: 34 ( J l )
9
10
2
.
.
.
59
58
bD

.
- .
.
.
AIRSPEED SIGNAL
AIRSPEED EXCITATION H
AIRSPEED EXCITATION C
59ow
(Jl)

'(8
U S A :
:
.
:
.
DISTANCE INDICATOR 2 b VAC C 1
._ . _. .
50 I DISTANCE INDICATOR W I T S SYNCHRO X . f . i Y
51 : : DISTANCE INDICATOR UNITS SYNCHRO Y I 3
52 f f DISTANCE INDICATOR TENS SYNCHRO X .. , : f f b . .
53
5Y
f
.
DISTANCE
DISTANCE
INDICATOR
INDICATOR
TENS SYNCHRO Y
HMDREDS SYNCHRO X f I :
5
? . .
55 f : DISTANCE INDICATOR HMDREDS SYNCHRO Y . : ; 8
. . ..
:
..:_ ..: . .:. .
. . .

.
98
.
. 2 b VAC C O W D PM 12
. .: .: :. . .
.
32
33 -6
.. -
S I L Z b VAC A T T I N D E PM
2 b VAC ATTITUDE PbU COM - 1s
l b
:
:
. . .
:
: :'
: :
:
. .
2y 19
- 5 VAC LIGHTING PVR
. _ . ,@ :

-
25 : 20 5 VAC LIGHTING PM COM
. .
:
:
:
DCORD
115 VAC HEADING PVR 5 -c 55
. .
: 115 VAC ATTINUDE PWR Y 5b
- 9 + I 8 VDC POWER
. i 5Y . . .
.. .. ... ..... .....
..... .
e +28 VDC SERVO CLUTCH POWER b :
9 : . -
r;
;l
.
. . _
.. .. . ORD ORD N

. .. : bl- 28 VDC POWER

RUOMR SERVO WMR

..
:
:
..
:
:
P I T C H STEERING + UP
PITCH STEERING + DN
ROLL STEERING + LEFT
. .. .. ..
:
..
3-31 :
9-21
-:
12 -C 31
D
B

QLD-1
@
@
b3 -0-

#
:
. .:
bY -- 5- RUDDER SERVO
AILERON
b l -c-5+ AILERON SERVO POYER
ELEVATOR SERVO WWER
ELEVATOR SERVO POWER
SERVOPOWER
PWER

: GO AROUND
GO ARQWD
RELAY
: @
: R(KL
..~ . . + RIGHT
STEERING .. 13 .
_ 21 : BUTSON
. :.
~~ ~ ~~

L i GYROMODE + 13 Y1 YD :
K HEADING MODE + Y? bY :
J
. . NAVlLOC MODE +
:
:
: YY-44
. Yb - : . 97

. . : : l Y 4 :
..
H
.
:
APPROACH MOM+

EXTSTR+DN
: : Y 5 - f Y8 - APPROACH MODE
APPROACH MODE
+
+
: : EXTSTR+UP . . : I
C T HOLD- W ALTITUDE HOLD INTERLOCK . . . ALTITUDE H)LD I N T E R L O C K M C I
-~. . .. .:.. Yb.-. :... .. ... ...
ALTITUDE HOLD INTERLOCK
: I
..
.- .-. ... .. .. . - . - . : bb -
- DISCONNECT SWITCH H
.. . . . .
.-
: b? DISCONNECT SWITCH C
. . . .. . .:.. 39- ... 95:..A L T I.N M .
: Yb GLIDE SLOPE K)DE + PILOT'S
DISCWNECT
. .
. ... ... : CONTROLLER :
.. .. SWITCH
:
. . . . .: 5 9 0 A J A
i :TPI-2551-044
V
..
:
-
..
:
..
ALTITUDE HOLD MODE +
ALTITUDE RATE H'+V
ALTITUDE RATE C ' -C
ALTITUDE ERROR H' I
ALTITUDE ERROR C ' I 6
?
) : : I( : ; r
.. 2Y3334 --r-
. 23 -c 2?
--r- 15
11
f

lb
Q
- ..
f
f
..
91
Y2

A P- 103F/ FD- 108 Falcon (2-Axis),

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 456 (Sheet 2) Pages 401/113, 401/114
 a
COLLINS
MAINTENANCE
ww MANUAL

FLIGHT
ANNUN- COURSE PEDESTAL DIRECTOR INSTRRUMENT FLIGHT ALTITUDE AUTOPILOT EMZRGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION MLIFIER WUTER CONTROLLER POWER AMPLIFIER WIRE N h C T I O N SERVOS MISC DISCONNECT J-BOX

331A-bA blYE-2G 3298-?A AILERON 12lA-2

Q J1 J2 J1 J1 52 33%-3A J1

-
(Jl)

12 I PIT- SCOTSTRAP TRANSMITTER X : : : 3 9 .. Y3 - ALTITUDE GAIN CMNGE EXCITATION

13 : P I T h BOOTSTRAP TRPJISMITTER Y : : : w - YY-
- ALTITUDE GAIN CHANGE NO. 1
l'?
15
lb
2b
27
28
29
-
-
.
_C_

:
PITCrl BOOTSTRAP TRANSMITTER 2
P I T C n BOOTSTRAP EXCITATION rl
P I T C h BOOTSTRAP EXCITATION C
BANK BOOTSTRAP TRAhSMITTER X
BAM BOOTSTRAP TRANSMITTER Y
BANK BOOTSTRAP TRANSMITTER Z
BAW( BOOTSTRAP EXCITATION H
:
:
:
:
:
:
:
:
:
:
:
:
9 3
3b-@
35-
37-GRD
i
.
I
15

59
18
i

19 -
-
-+
ALTITUDE GAIN CiANGE NO. 2

COMPUTER MON +
EXT P I T C H STEERING A
6 EXT P I T C H STEERING B
30 : BANK BOOTSTRAP EXCITATION C I 25 AC P I T C H STEERING A
HEADING WARNING DATA X . 2b -e AC PITCH STEERING B
: HEADING WARNING DATA Y 27 -+ PROCESSED P I T C H DATA A
H E M I N G YARNING DATA Z
HEADING YARNING DATA H
HEADING YARNING DATA C
:
:
18
48
:
: . -
:
: 57
bo
-
- - - - S b PROCESSED PITCH DATA B
28
INTERNAL PITCH STEERING OFF
ALT HOLD OFF +
+
:
HEADING WARNING DATA H '
HEADING WARNING DATA C' . . ._ -+.
18
19
5- EXT ROLL STEERING
EXT ROLL STEERN IG
A
B
25 S+ PROCESSED BANK CMD A
. 2b 5 6 P R O C E S S E D BANK 0110 B
35 I 5- PROCESSED BANK DATA A
3b : 5 b PROCESSED BANK DATA B
55 . 5- EXT BANK CMD B

. . +
: : c17
- .
5Y -b
. EXT BANK CMD A
P I T C H MONITOR
- : 12 12 :
.. ..
- --
Gs ARM : GLIDE SLOPE ARM. ANN. f b :
GS EXT I GLIDE SLOPE EXT. ANN. f Y2 :
N I L ARM : : NAVlLOC ARM. ANN. I b :
N I L CAPT I NAVILOC WTURE ANN. : 39 :
FWR
GS CAPT
:
. :
f
38 - RWYAY FLAG -
ANNWCIATOR POWER

.: ..: .:. :.. .

' : 5 :
MRBCN

GA GO M Q W D ANN- - :

:
:
:
:
lb
:
:
: RCVR
: 512-9
: (J1)
: : MIDDLE W E R - 4 3 - 9
: l a 57 : : . N
I TERNAL ROLL STEERING OFF +
AB P I T C H CONTROL EXC A
P I T C H CONTROL SIGNAL
I
I
21
20
NAV
RCVR
NAV
CONT
:
:
51RV-1
SELF-TEST
. ... ... ... .. . .
C P I T C H CONTROL EXC B 3 22 51RV-1 3131-3 : RELAY
D (J2) (J2) :
E TLRN CONTROL EXC A 21 : 19
k CONTROL EXC B E 22 : L . 1
I
G N R N CONTROL SIGNAL 20 :
N I N T MOTOR CONTROL VOLTAGE . b2 59
n :
I
I &
P I N T 2b VAC WTOR EXCITATION C 2Y : I
R I N T WTOR RATE SIGNAL b3
I
S INT MOTOR SIGNAL MM4ON . 2Y 55 14
I 28 M C PANEL L I G H T PYR K :
U
Y
GRD GRD
. .. .- ..
. . .
. I

.. .. .
Y ENGAGE VOLTAGE
z .
a ENGAGE PULSE : 5b
b DISENGAGE VOLTAGE : 37
:
@ I ENGAGE READY
.. 55

. .... .... .... .

ALTITUDE HOLD MODE + 38
. .
f HEADING SYNCH CUTOUT 38 :
P : 1 1 5 VAC AUTO P I L O T PWR-
9 f 1 1 5 VAC FWER 7 :
r I N T 2b VAC MOTOR EXCITATION H 23 :
5
t . - ENGAGE INTERLOCK
. ... ... ... . -
c : 59

U : AILERON CLUTCH VOLTAGE 39

V ELEVATOR CLUTCH VOLTAGE : 39
W RWDER CLUTCH VOLTAGE 5b
M
X
+28 VDC AUTO P I L O T PWR
..
.
... ... . : 53 - YAW D M E R ENGAGE M3N +
... ... ...
- Y SPARE
.. 9 SENSING

M
z
ea
cc
. ._
..
..
... .
..
... .
..
..
.
b5 -
-
.
ROLL PATE WTOR GRD
33Y5A-W
(ROLL)
A
@ :
: YAY D A W SY

DD
EE
FF
GG
HH
GYRO MODE
HEADING WDE
NAVILOC W E
APPROACH MODE
MODE VOLTAGE H
. ....
..
....
.
.
..
.
.
..
... - .
8
32
31
29 - 115 VAC POWER
mu PATE EXCITATION
ROLL MTEEXCITATION
ROLL RATE SIGNAL X
c
H
B
E
F
G : TPI-2551-044

AP-103F/FD-l08 Falcon (2-Axis),

M a r 1/73 Interconnecting Wiring Diagram 22-03-00
Figure 456 (Sheet 3) Pages 401/115, 401/116
 ANNUN-
CIATORS
COURSE
INDICATOR

331A-bA
PEDESTAL
CONTROLLER

blYE-2G
FLIGHT
DIRECTOR
INDICATOR

3298-?A
-
a
COLLINS

WIRE FUNCTION
MAINTEIVANCE
MANUAL

INSTRUMENT
AMPLIFIER
FLIGHT
COMPUTER MISC POWER
AUTOPILOT
AMPLIFIER WIRE FUNCTION SERVOS

AILERON
SENSING
UNIT
EMERGENCY
DISCONNECT

121A-2
J-BOX

8 J1 52 J1 J1 J2 @ 33YC-3A
(J1)
3395A-YB 8 J1

. .
: 8 -
- P I T C H RATE MOTOR 6RD
(PITCH)
A
:
:
10
32 -
-
1 1 5 VAC POWER
P I T C H RATE EXCITATION C
B
E
:
:
31
29 - P I T C H RATE EXCITATITTON H
P I T C H RATE SIGNAL X
F
G

-
.. .. YAW PATE
GVM
332G-z

-
bb YAW RATE MOTOR GRD A
10 : 115 VAC POWER B
51 __C___ YAW PATE EXCITATION C
50 I YAW RATE EXCITATION H F
Y8 YAW MTE SIGNAL X G

SYMBOLS USED: 7. POMR LEADS DENOTED BY "DIM" SHOULD BE T I E D TO C O W P I T L I G H T DIMMING CIRCUITS.

8. SENSING W I T 3 1 ( 5 k Y ( ) AND RATE GYRO 3326-2 SHCULD BE LOCATED AS CLOSE TCGETHER
SP TWISTED SHIELDED PAIR-ADJACENT . POSSIBLE.
AS ......_ .
SI WIRES AS SHOWN ON DRAWING 9. ANNUNCIATORS CHOSEN MJST NOT EXCEED 100 MA. A C O M N +a8 VDC I S USED FOR
SG SHIELD T I E D TO GROUND AT U N I T ANNUHCIATOR POWER. ANNUNCIATION VARIES WITH THE P A R T I C U A R INSTALLATION.
51 SINGLE SHIELDED WIRE DEPENDING UPON DESIRED OPERATION, S P E C I F I C ANNUNCIATORS M Y BE DELETED.

8 ALL S1 SHIELDED T I E D TO X I ETC-

NOTES
STY FOUR WIRES W I S T E D WITH SHIELD 10. THE 5b2C-'I AND 5b2A-5G SHOUD Bc' WUNTED AS CLOSE TOGETHER AS POSSIBLE,
PREFERABLY ON A W A L MOUNT.
POINT TO POINT BEWEEN THE UNITS.
M S E SIGNAL LEADS MJST BE W I S T E D AND WIRED
THE W I S T E D PAIRS SHWLD BE KEPT AS
S M T AS PRACTICAL AND MJST A L S I BE SHIELDED I F O M R WO FEET LONG.
NOTES: 11. COWARATOR WARNING ESOLVERS. [x) NOT USE FOR OTHER PUIPOSES UNLESS LOADING
EFFECT I S EVALUATED.
1. ALL WIRE S I Z E S ARE NO. 82 UNLESS DESIGNATED OTHERWISE BY NVIBERS I N SQUARES. 12. TOTAL WIRE RW FROM BUSS TO Elk2 TO SbaC-Y TO 33YC-3 ( P I N 8) FOR EACH
SHIELDED WIRES ARE GROWDED AT ONE END ONLY. PRIMARY SERVO MJST NOT EXCEED 90 FEET I F AWG 80 WIRE I S USED. WHEN GREATER
2. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE THAN 90 FEET, INSTALL T E M I N A L S AT 5 b P W MOWT AND RVN AWG 2 0 WIRE FROM
GROWDED AT T e 51RV-1. 5b2C-4 TO TERMINAL AND AWG l b WIRE FROM TERMINAL 3Y'tC-3 P I N 8.
3. FOUR WIRES W I S T E D WITH SHEILD FOR C O W A T I B I L I T Y I N FUTVRE ARINC INSTALLATIONS. 13. AN ISOLATED MODE SWITCH I S PROVIDED FOR USE WITH COPILOTS F L I G H T DIRECTOR.
Y. A RELAY W S T BE INSTALLED I N THE AIRCRAFT JUNCTION BOX TO ELIMINATE THE SELF 19. WITH TRIM INDICATOR CONNECTIONS AS SHWN AND THE REVERSING L I N K S INSTALLED
TEST F E A N R E OF THE 5 l R V - 1 WHEN THE AUTOPILOT I S ENGAGED. FOR CORRECT SERVO PHASING THE PRIMARY SERVO U P S T A N SHOULD TtRN CLOCKWISE
5. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N T H I S DRAWING REFLECTS WHEN VIEWED FROM THE CAPSTAN END UNDER THE FOLLOWING A I R Q W T ATTITLQES:
LOADS AS FOLLOWS:

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS

AILERON
ELEVATOR
-- RIGHT BANK
P I T C H DOWN

200 OHMS TO-FROM 1DD OHMS JUWER BP-93 TO BP-33 OF 51RV-1 15. POWER FROM A P A R T I C U A R C I R C U I T MEAKER OR FUSE M Y PROVIDE POWER FOR mxlE
500 OHMS GLIDE SLOPE POINTER 200 OHMS JUWER T P 4 TO TP-2 AND TP-3 OF 51RV-1 THAN ONE EQUIPMENT. THS
I WILL aE INDICATED N
I THE INTERCONNECT POWER COLLW
500 OHMS GLIDE SLOPE FLAG 85D OHMS JUWER TP-21 TO T P d b OF 51RV-1 BY A LETTER WITH AN OCTAGON SYM)OL AROUND I T . CAPITAL LETTERS FOR DC AND LOWER
500 OHMS LOC FLAG 250 OHMS JUWER BP-32 TO B P - Y 1 OF 51RV-1 U S E LETTERS FOR AC.
500 OHMS COURSE BAR 200 OHMS JUWER W-39 TO BP-30 AND BP&8 OF 51RV-1
- - -
-- - -
A 88 VDC DIMMING CIRCUIT a 5 VDC D I W N G C I R C U I T
b. THE POWER FOR T I E COWASS SYSTEM W S T BE OF THE SAME PHASE AS THE REST OF THE
AUTOMATIC FLIGHT CONTROL SYSTEM- G -
8, CI D, E 28 VDC 5 M p
2 8 V D C l M
b, c , d 1 1 5 VAC 2 *Lp
e g 11s YAC i u p
f i i s VAC 3 ~p
lb. THE GO AROUND RELAY I S INSTALLED FOR WINGS LEVEL, PITCH UP GO AROUND.
GO MOUND W T O N IS NORMALLY OPEN AND HORMULY IS INSTALLED ON CONTROL
COLVMN WHEEL- TO DEACTIVATE GO AROUND PROVISION REMOM THE RELAY AND
CONNECT THOSE VIRES TOGETHER THAT ARE CONNECTED BY THE N W L Y CLOSED
CONTACTS OF TCE RELAY.
n. EQUIPMENT SMDWN I N MISC COLUmS M Y NOT H AM W L E T E WIRING INFORMATION
INDICATED. BEFORE WIRING APPLICABLE SYSTEM MANUALS FOR THAT EQUIPMENT
SH0U.D BE CHEWED.
18. CONNECTIONS TO T R I M TAB MOTOR CON% DEPENDS ON AIRCRAFT RIGGING.
19. PROVISIONS FOR RADIO ALTIMETER (OPTIONAL).
20. A PAIR OF 112 WATT 10
21. WHEN O P T I O N A L 5 9 0 A - 3 A SERVICE B U L L E T I N N 0 . 3 IS I N C O R W R A T E O , THE FOLLOWING
I N T E R C O N N E C T I N G WIRING CHANGES ARE A P P L I C A B L E
REMOVE C O N N E C T I O N B E T W E E N J I ( B P ) - 3 8 OF T H E 5 6 2 C - 4 A U T O P I L O T
A M P L I F I E R AND J I - d OF T H E 6 1 4 E - 2 0 P E D E S T A L CONTROLLER. REMOVE
CONNECTION BETWEEN JI-V OF T H E 6 1 4 E - 2 G P E D E S T A L CONTROLLER
A N D JIA(TP!-47 O F THE 5 6 2 A - 5 0 FLIGHT COMPUTER.
M A K E C O N N E C T I O N S A S SHOWN BELOW.

614E-20 562A-50 59OA-3A 562C-4

JI JIA JIB (JI) JI JI
(TP) (BPI (TP) (BP)
V. A L T I T U D E HOLD MODE + ________ 3 4
A L T I T U D E HOLDMODE +47 20 ___----
-- --- 38

T P I - 2551-044

AP-103F/FD-108 Falcon (2-Axis),

M a r 1/73 Interconnecting Wiring Diagram 22 -0 3- 00
Figure 456 (Sheet 4) Pages 401/117, 401/118
 COLLINS
MAISTESASCE
MANUAL

A?-103F/FD-108 INTERCONNECT4FB-320

772-0830-001

FLIGHT
A"- U)WtSE PEDESTAL DIRECTOR INSTRVMENT FLIGHT AUTOPILOT EMERGENCY
CIATORS INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER COW'LVER MISC POWER MLIFIER WIRE FLWCTIDN SERVOS msc DISCONNECT

*+
33lA-bA blYE-?G 329B-7A 399'2-10 5b2A-5G
@ 5b2C-'I AILERON 121A-2
8 J1 J2 J1 J1 J2 J1
(TP)
J2
(BP)
J l A J1B
(TP)(BP)
J l
(TP) (BP)
J l 33YC-3
(J1)
Jl

-
b
7
8

ID
9
- :
:

:
5?- P I T C H ATTITUDE ERROR H '
5 6 P I T C H ATTITUDE ERROR C' -
-
-
P I T C H A T T I T M E SERVO DRIVE M2
P I T C H ATTITUDE SERVO DRIVE C
: S ' t P I T C H ATTITUDE RATE G2
2Y
23
28
2?
25
:
:
:
:
:
:
:
:
:
:
:
:
:
:
: VERT
:Q
b:
13
19
: 5-
AILERON F I E L D NWIBER 1
*28 vcc
AILERON
AILERON
AILERON
F I E L D NLWER 2
SIGNAL C
EXCITATION C
A
B
C
E

11

92
Y3
1

-
2 e&

Y Y -?-
: 5 6 P I T C H A T T I T U M RATE C2
5 - MANUAL PITCH C U W D H '
MANUAL PITCH C O W D C '
V-BAR PITCH COMMAND SERVO DRIVE M1
V-BAR P I T O I C O W D SERVO DRIVE C
V-0AR PITCH C O W D RATE
- .
2b :
:
:
11
10
8
3b
2b
:

:
:
: :
:
: 3320-11
:
:
:
(J1)
REF

:Ii
i
15
Ib

11
17
-+
12 -+AILERON

-+
: X+
AILERON
AILERON
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
AILERON SERVO GRD
AILERON RATE SIGNAL
G
H
I
R
s
95 -

91 -
3 -
&
YO -7-

- 6
V - B M PITCH M W D SIG C
V-BAR PITCH POS XMTR X
V-BAR PITCH POS XNTR Y
P I T C H A T T I T U M CT X
O M A 9

: 30-A
: :

AILERON ENGAGE VOLTAGE

(J2)
E

17
I8
19
4
5

- :

:
P I T C H AlTITUDE CT Y
P I T C H ATTITUDE CT 2
BANK ATTITUDE CT X
BANK A T T I T U M CT Y
BANK A T T I T W P CT 2
:
. 20-5

.
.
30-D
2 0 - E
C

F
AILERON ENGAGE VOLTAGE

ELEVATOR
F

21 -

-
20 e?-

-
22 -BANK
6
BANK A T T I T M E ERROR H '
BANK ATTITUDE ERROR C '
-
-
A T T I T W E SERVO DRIVE MP 22 . ' '
E+
+-ELEVATOR F I E L D NUbSER 1
33YC-3
(J1)

-
23 B W K ATTITUDE SERVO DRIVE C @bi 28 VDC B
A
29 e?- BANK ATTITUDE RATE G2 19 . . . t ELEVATOR F I E L D NUh6ER 2 C
25 - 6 BANK ATTITLOE PATE C2 : 13
-
-
ELEVATOR SIGNAL C
3b
37

38 e?-
39 - 6
V-BAR ROLL C O M N D SERVO DRIVE W
V-BAR ROLL COMND

V-BAR ROLL CDMND

V-BAR ROLL C O W D
RATE GZ
SG
I COM
.
:
2
28
SERVO DRIVE c ----c- 27
.
2b
5
:
:
. :.
:
:
:
:

:
a

K
H
3
-
.AS;
ERECT
GRD
:
:
:
:
:
1Y
15
l b
12 4
11
-+
ELEVATOR
ELEVATOR
ELEVATOR
- ELEVATOR
-e ELEVATOR
EXCITATION C
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
SERVO GRD
F
G
H
L
R
3~ -FL v - 8 ~ROLL POS XMTR ~i : 2 9 : : : 17 -+ ELEVATOR RATE SIGNAL S
35 -

31
:
:
-
6 V-BAR ROLL POS XMTR c i

-
-
18
9
1 1 5 VAC ATTITUDE POWER
GYRO hQN +

- --
GYRO HIGH LEVEL FLAG +
GYRO HIGH LEVEL FLAG
STEER FLAG
-
:

29
31
32
.
23

:
:
:
2
:

:
:
:
:
10
:
:
:

.
17.
N
:

NAV
ELEVATOR ENGAGE VOLTAGE
ELEVATOR ENGAGE VOLTAGE
(J2)

H
J

i: El? -
-+28
STEER FLAG
STEER FLAG + . . 2

: :
28
:
RCVR
51RV-1

33 -
11 -
10
VDC FLAG POWER
GLIDE SLOPE DEV + LP
5Y (TP)
RWDER
34 :
- GLIDE SLOPE M V + CU : 22-9 33YC-3

--
: GLIDE SLOPE LOW LEVEL FLAG +
13 - -
35 12 : : : 21 (Jl)
3b

1
:

: ST+-

-
GLIDE SLOPE LOW LEVEL FLAG

COLRSE RESOLVER A

--
GLIDE SLOPE HIGH LEVEL FLAG +
:
.
:
:
.
11-
.
:
.

:
:
2 2
27
lb
b:9 E
1
fRUDDER
f 28 VDC
fRLODER
F I E L D NUMER 1

FIELD NUeER 2
A
B
C

--
(BP) Y3 RWMR SIGNAL C E
29 . VORILOC DEV + LEFT
: b . 32 -90 Y9 RUDDER EXCITATIOM C F
: VORILDC DEV + RIGHT5- : :
28 :
: 9
LOC FREQ VOLTAGE +
-
VOR/LOC HIGH LEVEL FLAG + t
:
:
:
22-39
11
93-
50
38
Y5
Yb -
Y2
f
RWDER
RWDER
RMDER
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGN&
G
H
L
2 : S T C COLRSE RESOLVER B : : . 2 2 91 RUDDER SERVO CRD R
8 : S T C COLRSE RESOLVER H : 21 97 RWDER RATE SIGNAL S
3 : S T C COURSE RESOLVER C : : . 2 3 (52)
9 : : 5 7 - CDLUSE RESOLVER D : 29 RUDDER ENGIGE VOLTAGE
5 : 5 6 COURSE RESOLVER E : : : 25 RWDER ENGAGE VOLTAGE
b . : 5?- COLRSE RESOLVER F : : : 2b
7 : : S b CDLRSE RESOLVER G : : : 2)
VDRILDC FLAG + : : :
31
32
2b
PVORlLOC FLAG
: TO-FROM mmw (+ TO)
- : :
:
:
41
92
93
TRIM
COLPLER
1blA-1A
27 : TO-FROM ARROW (+ FROM)
..: :
...
..
: w (Jl)
.. . ..
ARMUP
TRIM LP
.. ... ... RELAY GRD

--
. FAILURE WARNING L I W T
.. .. .. ARM Mi
TRIM DN 29
.... ... ... RELAY CRD 31 INDICATOR

... .. .. CRD 327D-1W

. . 115 VAC POWER
m
8

... .. .. T R I M ENCAGE VOLTAGE u 20

.
... ..
. .
.. : 3b -+
TRIM ENGAGE GRD
TRIM INPUT DN - 32
22
.. .. : 35 -Y- TRIM INPUT DN +
-+ 2Y
+
..
..
.
... ...
. :
:
39 4- ELEVATOR TRIM INPUT LP
33 ..-5+ ELEVATOR TRIM INPUT W
1-
13- -
... ... ...
33 AILERON TRIM INDICATOR
39 AILERON TRIM INDICATOR ' Q
.. .
.
.. ..
..
..
..
53
52 .
RUDDER TRIM INDICATOR
RWDER TRIM INDICATOR :a

AP-103F/FD-108 HFB-320, Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 457
May 1/67 22 -03-00
Pages 401/119, 401/120
 COLLIKS
MAINTEYANCE
MANUAL

LP-103FIFD-108 INTERCONNECT4FE-320

??2-0830-001

FLIGHT
ANW- COURSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT AUTOPILOT E M 1RGENCY
CIATORS INDICATOR CONTROLLER INDICATOR W I R E FUNCTION AWLIFIER COWUTER MISC PWER AWLIFIER WIRE FUNCTION SERVOS MISC D I S CONNECT
' J4OX

331A-bA LlIEdG 3290-?A BYYC-lD 5b2A-5G AILERON 12 l A 4

Q J l J2 JI J I 52 J1
(TP)
52
(BP)
J l A JIB
(TP)(BP)
339c-3
(J1)
J l

: : : COWASS
. .
... ... :
:
328A;
(J1) (J2)
:
:
COWASS MON
COWASS MON +
COWASS DATA X
- .
:
30
29
..
-
.. ..
- :
19
: 1)
25
: 2 :
. . .
'9 r= :l COWASS DATA Y .. ... ... : 3 :
.
. . .
--
-
COWASS DATA 2 -Y :
: : : 1 1 . 99 COWASS DATA X

: COMPASS FLAG + :
:
: :
:
:
. :-
:
i L
3
- : - 50
51
COWASS DATA Y
COWASS DATA Z
30
:
:
2Y
15
C W A S S FLAG
2b VAC HDG PUR
- :
:
31
3
15 :
2 : :
:

:
2?

22- 5
GRt

:
: lb COWN .: l b : : 30- 1 :
: 20 : 5?- HEADING EF(R0R SYNCHRO C ' 1 7 : :
: 21 : 5 6 HEADING ERROR SYNMRO H ' . 18 : :
: 13 : 5- HEADING RATE G2 . 19 : :
: 1Y : 5 6 HEADING RATE C2 . a : :
: 12 HDG LOT CONT C l : 2 1 : :
: 11 : HDG MOT CONT M l : 2 2 : : AIRSPEED
: Y HEADING DATUM SYNCHRO C' : : 2 3 : SENSOR
: 5 HEADING DATUM SYNMRO H ' : ; 33 O M 5908-2
12 COURSE DATUM SYNCHRO C ' : : 2Y 8bOE-2 (J1)
13 : COCRSE DATUM SYNCHRO H ' : . 39 (Jl) 59 . AIRSPEED SIGNAL
Y5 DISTANCE INDICATOR FLAG t .: : : 9 56 . AIRSPEED EXCITATION H
Yb DISTANCE INDICATOR FLAG - : : : l o bo . AIRSPEED EXCITATION J
Y? DISTANCE INDICATOR 2b VAC H : : : 2
Y8 - f DISTANCE INDICATOR 2 b VAC C : : : I
Y9 --I : .. .. ..
50 DISTANCE INDICATOR UNITS SYNCHRO X . . . .
51 DISTANCE INDICATOR UNITS SYNCHRO Y : : . : 3
52 DISTANCE INDICATOR TENS SYNCHRO x : : : : b
53 DISTANCE INDICATOR TENS SYNCHRO Y : . . .
59 . DISTANCE INDICATOR HUNDREDS SYNCHRO X : : : ?
55 DISTANCE INDICATOR HUNDREDS SYNCHRO Y
..
: :
. :
. 8

Y8
32
33 -
6
-
e?-
2b VAC C O W 0 PWR
2b VAC ATTITUOE PWR

- 2b VAC ATTITUDE PWR COM -

12
15
lb
:
:
:
..
..
:
:
:
..
...
:
:
:
..
...

2Y
25 :
:
:
19
20 - 5 VAC LIGHTING PWR
5 VAC LIGHTING PUR COM .3 5 .; . : Q
; - ;
DC GRD
115 VAC HEADING PUR : 5-55 :
115 VAC A T T I T U M PUR Y : : 5 b :
9 +26 VDC POWER : 54 :
e + 2 8 VDC SERVO CLLirCH POWER 4 . .. .. .
...
b :

... ... .. : C
- ? 9 :

...
..
...
..
...
.
c .
R
:
D
b l - P GRD
28 VOC POWER
RUDDER SERVO POWER
..
..
.. .. O. @ b3 : S t c RUJDER SERW POWER
i I*
.. ... ... 0: @)
a .
b l
:
:
5-
5-
AILERON SERVO POWER
AILERON SERVO POWER
.. ... ... : D : ELEVATOR SERVO POWER W

L
K
P I T C H STEERING + Up
P I T C H STEERING + DN
ROLL STEERING + LEFT
ROLL STEERING + RIGHT
GYRO MODE +
HEADING LODE +
.
:
13
12
13
.
3-31
Y--21

.
:
- ; Y7
.

:
31
21
Y l
.
:
:
:
:
:
GRD -
Lto
bY
: @ bY
1 :

:
:
-+ ELEVATOR SERVO POWER X

J NAVtLOC LODE + : : Y b : : Y7
: YY--sY - : GO M U N D hQDE + I ! l i I
: 1 r - I : : I
H APPROACH MODE + . . . APPROACH MODE +

EXT STR + DN
: Y5 : : Y8 - APPROACrl hQDE +
I

I
EXT STR + U p I
ALT HOLD : ~ T I T U D E HOLD INTERLOCK . . . ALTITUDE HOLD INTERLOCK I
I
:
.. Yb
.. :.. ALTITUDE HOLD INTERLOCU
I
.. ... ...
...
.
.. ..
. .
: bb -
- DISCONNECT SWITCH L(
I
I
t
:
..
39-Y5
.. ..
:
:
.
b?
Lib - DISCONNECT SWITCH C
GLIDE SLOPE MODE +
DISCONNECT
COP1L O T

SWITCH

AP-103F/FD-108 HFB-320, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 457
May 1/67 22 -03-00
Pages 401/121, 401/122
 a MAINTESANCE
COLLINS

v MANUAL

F L I W
INSTWCENT FLIGHT AUTOPILOT
AYUI- COURSE PEDESTAL DIECTOR
UATQIS INOIUTOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER COWUTER MISC POWER MLIFIER WIRE FUNCTION SERVOS msc J&X

UWI blYE-ZG 32-X ULERY

Q Jl K J1 J l J2 35%-3
(Jl)
.: .: : ALTITUDE
: CONTROLLER :
.. ..
V
:
ALTITUDE HOLD W D E +
A L T I T M E RATE H ' -9
ALTITUDE RATE C '
:

: 3Y
: 2Y
:
: Y7-
: (J1)
34
19
15
-
: 59DA-3E

-
-
-
: ALTITUDE ERROR H ' - - 5 V : 33 lb : 91

12 __C_
: ALTITUDE ERROR C' +&
P I T C H BOOTSTRAP TRANSMITTER X
: 2 3 --?- 27
: : : 3 9
:
:
:
92
Y3 -
- ALTITUDE GAIN CHANGE EXCITATION
ALTITVOE GAIN CHANGE NO. 1
13 P I T C H BOOTSTRAP TRANSMITTER Y :
.. :
.. :
.9 2 YY
-
-
14 __C_ P I T C H BOOTSTRAP TRANSMITTER 2 95 ALTITUDE GAIN CHANGE NO. 2
15 -PITCH BOOTSTRAP EXCITATION H

-
l b -PITCH BOOTSTRAP EXCITATION C : : : 35-
2b __C_
27
28
BANK BOOTSTRAP TRANSMITTER X
BANK BOOTSTRAP TRANSMIlTER Y
BANK BOOTSTRAP TRANSMITTER 2
: : : 37- CRD :
:
;
59
18
- COWUTER M)H +
EXT P I T M STEERING A
29 BANK BOOTSTRAP EXCITATION H : 19 46EXT P I T C H STEERING B
30 _I_c_ BANK BOOTSTRAP EXCITATION C : 25 -6- AC P I T C H STEERING A
HEADING WARNING DATA X : 2b - - b eAC P I T C H STEERING B
:

-
HEADING WARNING DATA Y 2? PROCESSED P I T C H DATA A
.
iQ 19
HEADING WARNING DATA 2
HEADING WARNING DATA H
HEADING W*FblING DATA C
:
:
18
Y8
:
:
:
:
57
bo
-
28 -bbPROCESSED P I T C H DATA B

- INTERNAL P I T C H STEERING OFF

ALT HOLD OFF +
+
HEADING WARNING DATA H ' 18 -+ EXT ROLL STEERING A
HEADING WARNING DATA C' 19 EM ROLL STEERN IG B
2s -+ P m C E s s E o BANK CM) A
2 b -b PROCESSED BANK CM, E
35 PROCESSED BANK DATA A
3b -6 PROCESSED BANK DATA B
55 -+ EXT BANK CM, B

P I T C H MONITOR +
- : 12 - 12 :
5Y -6 EXT BANK CM) A

- --
GSARM : GLIDE SLOPE ARM. ANN. . b :
GS EXT : GLIDE SLOPE EXT. ANN. : Y2 :
N I L ARM : NAVILOC ARM. A". : b :
NIL UPT : NAVILOC W T U R E ANN. : 35 :
PUR
G S W T : : 38 -
R W A Y FLAG -
ANNUNCIATOR PMIER
:
._ 5.. : . .
: : : M(R BCN

-
-
: : : RCVR
GA GO AROfflD ANN. : lb : 512-Y
: : : (J1)
: MIDDLE MAQKER ; Y3-Y
: : 18 57 N
I TERNAL mu STEERING OFF +
i P I T C H CONTROL EXC A : 21 NAV NAV : 51RV-1
B P I T M CONTROL SIGNAL : 20 RCVR CON1 : SELF-TEST
P I T C H CONTROL EXC B : :
C
D .. .- .. 22 5lRV-1
(J2)
3131-3
(52) :
RELAY

E TURN CONTROL EXC A . . . 21 : 19

F TURN CONTROL EXC B 22 : L :
G TURN CONTFSL SIGNAL 20 : I
N I N T M,TOR CONTROL VOLTAGE : b2 5Y
P I N T 2b VAC MOTOR EXCITATION C a : n : 14
R I N T 1IX)TOR RATE SIGNAL : b3 I
S
T
I N 1 WTOR S I G N A C O M N
28 VDC PANEL L I G H T PWR . . . : 29 55
K :
1
I
I
I
U
X
GRD
.. .. .. GRD
: Q i,
.. .. .. r
Y ENGAGE VOLTAGE
7 T U
a ENGAGE P U S € ; 5b
b DISENGAGE VOLTAGE : 37
C ENGAGE READY : 55
d ALTITUDE HOcD W E + .. .. .. : 38
.. .. ..
f HEADING SYNW CLTOLT 38 :
P 115 VAC AUTO P I L O T PWR
q 115 VAC POWER 7 :
I I N T 2 b VAC WTOR EXCITATION H 23 :
5 ENGAGE INTERLOCK
t
U AILERON CLUTCH VOLTAGE
V
w
M
X
Y
2
AA ... .
...
.
...
BB . : YAW D A W SW U

AP-103F/FD-108 HFB-320, Interconnecting Wiring Diagram (Sheet 3 of 4)

Figure 457
May 1/67 22 -03-00
Pages 401/123, 401/124
 COLLINS
M.AISTENASCE
MIANYUAL

FLIGHT
"- QXRY PEESTAL DIRECTOR
bATo(rs 1NDICATOR CONTROLLER INDICATOR WIRE FwcTION WIRE FUKi'iON
33- bllf-?G 329b7A
8 J1 J2 Jl J1 J2

SENSING
: : WIT
3315A-W
ROLL RATE IQTOR GRO (mu)
cc
DD
EE
FF
GG
HH
HEADING MODE
NAVILOC MDM
APPROACH mDE
IQM MCTAGE H
.-.

-.-.
..
.
.
...
..
...
.
b5
8
32
31
29
- 1 1 5 VAC POWER
ROLL RATE EXCITATION C
ROLL RATE EXCITATION H
ROCL RATE SIGNAL x
A
B
E
F
G

-1 - . ... - (PITCH)
21
128 -
-
PITCH
PITCH
DIFFERENTIAL RESOLVER X
DIFFERENTIAL RESOLVER Y -.- . ...
.
:
:
8
in -
-
PITCH RATE
115 VAC POWER
mice GRC A
0
: 23
29 -
25-PITCH
PITCH
PITCH
DIFFERENTIAL RESOLVER 2
D I F F E R E N T I M RESOLVER H
D I F F E E N T I A L ESOLVER C
:
:
:
38
31 -
29 - P I T C H
P I T C H RATE EXCITATICN C
P I T C H RATE EXCITATION H
RATE SIGNAL x
E
F
G
2b-
-
-
P I T C H DIFFERENTIAL RESOLVER H '
-. ..

-
27 P I T C H DIFFERENTIAL R E Y X V E R C ' YAW RATE
28
- BANK DIFFERENTIAL RESOLVER X .. .. olm
: i :
:
29
30 -
-
BANK DIFFERENTIAL E M L V
DU~K DIFFERENTIAL
~~

RESOLVERz
~.E R Y
... ..- bb YAW RATE miou GRD - 332w
A
:
:
31
38 -
-
B W K DIFVEREhTIAL RESOLVER n
BWK D I F F E E N T I A . RESOLVER C . . .. in
51
11s VAC FWER
YAW RATE EXCITATION C
B
E
,
, 3 Y -BWK D I F F E R E h T I A L RESOLVER C'
: 33 DIFFERENTIAL RESOLVER PI' 50 YAW RATE EXCITATION H
.. ..
BAH(
: YAW RATE SIGN# X - G

.. ..

symas USED: l't. WIRING TU T R I M INDICATORS U I D I b l A - U YLn = W I R E REVERSING DEPENDING upoI(

SERVO INSTALLATION. CONSULT # - 1 0 3 F MAINTENANCE W A L FOR S P E C I F I C INFORMTION.
SV N I S T E D SHIELDED P A I R 4 J A C E N T WITH T R I M I N D I C A T M I W M E C T I O N S AS SHOW AND THE REVERSING L I N K S INSTALLED
SA WIRES AS SHOWN ON WAWING FOR C ~ C SERVO
T PHASING THE FRIUIRY SERM CAPSTAN WD nm aocxwzx
SG SHIELD T I E D TO GWWD AT U N I T WHEN V I M D F R o l l THE W S T b A EYD W R THE F O L L W I N G AIRCRAFT ATTITUDES:
51 SINGLE SHIELDED WIRE
ALL 51 SHIELDED T I E D TO XI. ETC. STY FOV( WIRES TYISTED WITH SHIELD AILEROW -- RIQITCM
ELEVATOR
RUXXR - PITCH U p
RIGHTIW

WTES: 15. P W E R FROM A PARTIQLAR C I R C U I ' WEAKER OR FUSE MAY PROVIDE PWER FOR hFXE
M A N M E EWIPMENT. T H I S WILL BE I N D I C A T E 0 I N THE INTERCONNECT POWER COL
W
1. ALL WIRE S I Z E S ARE HO. 22 LHLESS DESIGNATED OTHERWISE BY N U B E R S I N SQUARES. BY A L E l l E R WITH AN IEXA6011 S Y Y M L ARM*ID I T , U P I T A L LETTERS FOR DC IWD L W E R
SHIELDED WIRES ARE CROWDED AT ONE END ONLY. M E LElTERS FOR AC.
2. SHIELDS ON THE NAV RESOLVER LEADS FROM THE N A V I G A T I W RECEIVER SHOUD BE
GROWDID AT THE 5LRV-1. A - -
28 Mc D I M l I f f i CIRCUIT - -
a 5 W D I M I f f i CIRCUIT
3.
9.
FOCR WIRES m1sm WITH SHEILD FOR WATIBILIPI I FUTUFE ARINC INSTALLATIONS.
N
A RELAY W T BE I N S T K L E D I N W AIRCRAFT JUNCTION BOX TU E L I M I N A T E THE SELF
TEST FEATURE OF THE 5lW-1 WEN THE AUTOPILOT I S ENGAGED.
G -
8, CI De E 28 VDC 5 UP
28 VDC 1 AW e-g
f --
b, C, d 1 1 5 VAC 2 ALP
1 1 5 VAC 1 MI
115 VAC 3 NR
5. THE AUTOMATIC FLIGHT &TWL SYSTEM AS CONNECTED I N T H I S DRAWING REFLECTS lb. THE GO AROUHD RELAY I S INSTALLED FOR WINGS LEVEL. P I T C H U p GO W M D .
LOADS AS FOLLOWS: GO M N D BUTTON I S H O M L Y OPEN AND NORMKLY I S INSTALLED ON CONTROL
COLUW4 WEL. TO M A C T I V A T E Go AROU(0 P R O V I S I W REIQVE THE RELAY AND
AFCS LOAD CIRCVIT FSQLIRED LOAD ADDITIONAL LOADS CONNECT MSE WIRES TOETHER niAT NE CONNECTED BY THE W W L Y a o m
CONTACTS OF THE RELAY
zoo OHMS TO-FROM in0 o w JWER w a 3 TO w-33 OF SLRV-i 17. E Q U I P h E N l SHOWN I N MISC C O L W S MAY HOT HAVE COWLETE WIRIHG I N F O R M T I O N
5nn OHMS am SLOPE POINTER Zoo OHMS JWER TP-E TO T P - ~AND TP-3 OF s 1 R v - i INDICATED. BEFORE WIRING A P P L l U g L E SYSTEM W S FOR THAT E Q L I P E N T
500 OHMS GLIDE SLOPE FLAG 250 OHMS JWER T P - ~TO T P OF~ m v - 1 SHCULD
-. _ BE
.. . --
- CHEMED.
-.
SOD OHllS LOC FLAG 850 OHMS J U P E R EP-32 TO E W t 1 OF 5 l R V - 1 18. CONNECTIONS TO TRIM TAB MOTOR CONTROL DEPENDS ON AIRCRAFT RIGGING-
5 0 0 OHMS COWS€ BAR 2nn OHMS JWER w-39 TO w-30 AMD w a 8 OF smv-1 19. PROVISIONS FOR RADIO ALTIMETER (OPTIONAL).
20. A P A I R OF 4 WATT 1 0 % RESISTORS SHOULD BE SELECTED TO GIVE FULL SCALE T R I M
INDICATOR MOVEMENTWEN CONTROLS ARE OVERPWERED UNTIL SERVO aum SLIPS.
THE RESISTANCE SWD BE SPLIT WTIH ONE HALF ON EACH SD IE OF TRM
I INDICATOR
MOVEMENT. THE TOTAL VALUE OF BOTH RESISTORS SHOULD BE GREATER THIN W OWN.
; U N I T 315A-W ) AND RATE GYFS 3
AS POSSIBLE.
9. U I N W C I A T C R S CHOSEN MOT HOT EXCEED 100 MA. A CUmoH + 8 8 VOC I S USED FOR
W W C I A T O R WVER- AW(UNC1ATION VARIES WITH THE P A R T I C U A R INSTALLATION.
DEPENDING UPON OESIRED OPERATIONr S P E C I F I C ANNUNCIATOPS MAY M DELETED.
10. THE 5b2C-Y AND 5 6 U - 5 G SHDUD BE W T E D AS CLOSE XXETHER AS POSSIBLE.
PREFERABLY ON A WAL MOWT. THESE SIGNAL LEADS MJST BE N I S T E D AND WIRED
POINT TO P O I N T BETYEEN THE W I T S . THE N I S T E D PAIRS SHOUD BE KEPT AS
SHW~T AS PRACTIUL AND MJST ALSO BE SHIELDED F I OVER NO FEET LONG.
11. COWUUTOR W W I N G RESOLVERS. W NOT USE FOR OTHER P U P O S E S UNLESS LOADING
EFFECT I S EVALUATED.
12. TOTAL WIRE RH FROM BUSS TO 121A-2 TO 5 b X 4 TO 33YC-3 ( P I N 5 ) FOR EAOl
P R I M SERVO MOT NOT EXCEED 90 FEET I F AWG 2 0 WIRE I S USED. WEN GREATER
THAN qn FEET, N ISTALL TERMINALS AT s b 2 c - Y WUNT AND RUN AWG 20 WRI E FROM
Sb2C-9 TO TERMINAL AND AWG l b WIRE FROM T E M N A L 399C-3 P I N 5.
13. AH ISOLATED M 3 M SWITCH IS PROVIDED FOR USE WITH COPILOTS F L I G H T DIRECTOR.

AP-103F/FD-108 HFB-320, I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 4 of 4)

F i g u r e 457

May 1/67 22 -03-00

P a g e s 401/125, 401/126
 COLLINS
RIAINTESANCE
MANUAL

AP-lD3FIFD-IO8G WITH 34YC-IF

MASTER I RE+
FLIGHT
ANNUN- COLRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT MODE
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COMPUTER COUPLER MISC MISC POWER
SERVCis
@ 331A-bA blYE-?G 329B-?C AWLIFIER
AUTOPILOT WIRE FUNCTION EMERGENCY
AILERON MISC DISCONNECT

--
J1 J2 J1 J l 52
33YC-3 121A-2
J1 J2
. . . . . . . . .

--
.. .. .. b PITCH A T T I T W E ERROR H '
.. .. ..
.. ... ...
7 -6- PITCH ATTITUDE ERROR C '
-
- bz
AILERON F I E L D NUMBER -1
28 W C
-
A
0
:
:

i
8 : PITCH ATTITLDE SERVO DRIVE I42 26 : : : :
.. .. .. 9 : PITCH ATTITUDE SERVO DRIVE C 25 : : : : : 5 1 1- AILEROtI F I E L D NUbBER 2 C :
.. 13 : 51- AILEROh SIGNAL C
- E :
.. ..
10 P I T C H ATTITUDE RATE G2 : 2 3 : : : :
.. 11 PITCH ATTITUDE RATE C2 : 2 * : : : : 14 : AILEROh EXCITATION C
- F :
... ...

--
.. .
25 4 - BANK ATTITUDE RATE C2 : 3 * : : : : 15 AILERQE
-
POSITION EXCITATION H G :
..
..
.
...
..
.
...
..
. 2 9 -6-
23 :
BANK ATTITUDE RATE G2
BANK ATTITUDE SERVO DRIVE C -
: 3 3

- 35
:
:
:
:
:
:
:
:
l b
12
11
:
:
:
5 r
51
-
xk-
AILERON
AILEROh
AILERON
POSITION SIGNAL
SERVO GRD
-
RATE EXCITATION H H
L
R :
:
:

...
22 -r--BANK ATTITUDE SERVO DRIVE M2 3b : : : :
.. ..

-
: : 17 : 5+ AILEROII RATE SIGNAL s :
.... ....
21 BANK ATTITUDE ERROR C ' : 3 1 : :

...
. ... ... 20
. . BANK QTTITUDE ERROR H ' : 3 2 : : : :
: : : :
.. ..
BANK ATTITUDE MON H : 3
.. .. .. 32 : 7 2 b VAC ATTITUDE PWR : 5 : : : : QI
.. ... ... VERT

... .. ..
33
. .
: 18
2 b VAC PWR COM
GYRO HIGH LEVEL FLAG +
-
GYRO HIGH LEVEL FLAG -
: 5 1
: 29
: 3 0
:

:
10
:

:
- :
:
:
:
:
:
REF
332D-1 1 : AILEROII ENGAGE VOLTAGE
AILEROt ENGAGE VOLTAGE
I ;
: B
. .. .. 31 7
. . GYRO LOW LEVEL FLAG + : Y e : : : :
J1
.. ..
. .
.. .. .. GYRO MON + : Y o : : : : N
.. .. .. 3 : : PITCH ATTITUDE CT X : : 3 0 : . : A ELEVATOR
33YC-3
::: : :
.. .. ..
Y
5
PITCH ATTITUDE CT Y
PITCH ATTITUDE CT Z
: : 2 0
.
:
. . . . .
0
C (J1) ( J 2 )
.. .. .. 17 BANK ATTITUDE CT X . . :
. 3 .0 . :
. .: n ELEVATOR F I E L D NUMBER I -A :
.. ... ...
~~~

: 18 BANK ATTITUDE CT Y : : : 2 0 : : E 28 W C
-B :
...
-
ELEVATOR F I E L D NUMBER 2 C :
... ...
:
.. 19
.. : L .
.. BANK ATTITUDE CT Z
. . . . . .
... .. .. .. .. ..
115 VAC POWER
AC GROUND .. .. .. .
. .
. .. H
-
ELEVATCIR
ELEVATC'R
SIGNAL C
EXCITATION C --
E
F
:
:
. . . : 12 PITCH ATTITUDE X (BOOTSTRAP) : : : : : 5 3 15 ELEVATOR
-
POSITION EXCITATION G :
.. .. .. : 13-PITCH ATTITUDE Y (BOOTSTRAP) : . : : 5 * 1b ---St
12 - t
ELEVATOR
ELEVATOR
RATE EXCITATION H
POSITION SIGNAL -
H
L
:
:
:
:PITCH:
:SYNC : : ..
:
.. ..
1Y 7 PITCH ATTITUDE 2 (BOOTSTRAP) : : : : : 5 5
11 -x+_ ELEVATOR SERVO GRD R :
.. .. .. P I T C H COMMAND H ' : : 3b-15 :
l? -+ ELEVATCIR RATE SIGNAL s :
.... ...
:BUTTON : PITCH COMMAND C ' : : 2b-lb :
: 15 7 2 b VAC A T T I T W E P W E R .
: 53-5 .
i li i : l b -C-- 2 b VAC PWR COM : : 51-2) . ... ..
..
:.=s o.: I. .f
..
.
..
i .i
..
PITCH SYNC MAN
PITCH STEER + UP : 5-31
: :
:
3 0
:
:
:
PITCH STEER + WWN

- :m
: : : : ELEVATOR ENGAGE VOLTAGE : A J
. .. ..
9-21
.
-
... .... ROLL STEER + LEFT 10 : : 31 : :u . ELEVATOR ENGAGE VOLTAGE :
. B
. H

... . . . . ROLL STEER + RIGHT 1 1 . : 2 1 : :

. .
...
- ... ...
: : : : :
...
49 7 V-BAR ROLL POS XMTR Z 58
..
--
: 39 V-BAR ROLL XMTR X . b D : : : :
..
..
...
..
:
:
3 b ---r---V-BAR ROLL COWAND SERVO DRIVE M2
37 : V-BAR ROLL COMMAND SERVO DRIVE C - -
b2
b3
:
:
:
:
:
:
:
: ... ...

-- -
.. : 38 -+ V-BAR ROLL COWAND RATE G2 b l : : : :
... : 39 V-BAR ROLL COMMAND S I G COM 59
. . : :
.. .. ..: :
.. ... ...
... :
:
35 7
Y5
V-BAR ROLL POSITION Y
V-BAR PITCH COMMAND S I G COM 54 - .
: : :
.
: :
.. ..
... ... : YY V-BAE PITCH COMAND RATE G2 b2 - : : : : : ... ...
... ... : YB 7 V-BAR PITCH COMMAND SERVO DRIVE C bY : : : : : .. ..
.. ..
. .
-
: Y2 7 V-BAR PITCH COMMAND SERVO DRIVE M2b3 : : : : :
: 41 : V-BAR PITCH POSIOFF-SCALE B I A S b l : - .
: : : :
. .
... ... .. .. .. . .. .. .. .. ..
... ..
:
:
YO :
XMTR 2
V-BAR PITCH POS XMTR X -
b o : :
:
: : :
RUDDER
. .
.. ... ..
98
.. ..
2 b VAC C O W N D PWR b ? :
. :
. . . ..: .:. 33YC-3
STEER FLAG -
.. ..
:
. .: Y-. PITCH COMPUTER K I N +
. b Y
: :
:
12 - 12
: :
:
:
: NAY RCVR @ RUDDER F I E L D NUHBER 1 - ...
P
... ... :
..
: Ib-
.. .. STEER FLAG + . . : 38 : : 51RV-1 : 18 VDC
RUDDER F I E L D NUMBER 2 -eC
33 : : : 10 -GLIDE
COWAND SERVO MONITOR
SLOPE DEV + UP
. 11 -b- GLIDE SLOPE DEV + WWN
:
: :
b5-28
3 2 :
:
: :
: (TP)
8 ($ RUDDER SIGNAL C E

-B
YY RUDDER EXCITATION C F
3Y : : : . 2 2 : : : 9
..
35
36
. .:
: : : 12 4
... ...: 13-...
--GLIDE SLOPE LOW LEVEL FLAG
GLIDE SLOPE LOW LEVEL FLAG
+
-
+
.
.
.
.
.
.
.
.
.
.
.
.
21
22 Yb
42 .
5+
5+
RUDDER
RUDDER
RUDDER
POSITION EXCITATION H
RATE EXCITATION H
POSITION SIGNAL
-
- H
L
. . . . .
GLIDE SLOPE HIGH LEVEL FLAG
.:. :
.. 11
.. :
.. ..: .:. 2?
Y1 : x+ RUDDER SERVO GRD R
. . .. .. .. .. .. .. .. .. .. Y? . 53- RUDER RATE SIGNAL s
1
.. .
.. .. ..: .:. 5T-
: COURSE RSVR A .. ... ... ... ...~. ... Ib
RUDDER ENGAGE VOLTAGE
. IRPl I
-COLRSE RSVR B
~~ ~~

. . . . . . RUDDER ENGAGE VOLTAGE

:
:
:
:
:
: STY
: STY
: STY
-
-
COLRSE RSVR C
COVRSE RSW H
.
.
.
.
.
.
.
.
.
.
.
.
22
23
21
:5 - 9 COLRSE RSVR D . . . . . . 29
: 5 : : 5 6 - COURSE RSVR E . . . . . . 25
: b : : -S COVRSE RSVR F . . . . . . 2b
: 7 : : 5 6 - COURSE R S W G . . . . . . 2?
-
FROM + TO . . . . . .
:
:
:
2b
2?
:
:
. . . . .
TO
TO -
FROM + FROM
+
.
.
.
.
.
.
.
.
. .
. .
Y3
YY

:
:
31
32
29
:
:
VORILOC LOW LEVEL FLAG
VCWLOC LOW LEVEL FLAG
VOR/LOC DEV + LEFT +
- .
:
.
:
.
: :
.
: 11-
. .
Y1
Y2
YO
:
. 28
. .. :
VORILOC DEV + RIGHT
VORILOC DEV + L E F T
: : : : : 10-339
. : b I
- : : 32-11 .~:
. .. ..
-
.

-...
~~

VOR/LOC DEV + RIGHT

.-
: : 5 : : 22-110 :
.. .. : : 9 VORILOC H I LEVEL FLAG l? : : 11 : : 50
... . ..
. . . ... ... LOC FREQUENCY
28 W C NAV REC POWER .. .. :
.. Y3-19-
.. .. .. 38
37
: TO NAV
REC PWR

777-2 563 -001

AP-103F/FD-l08G M a s t e r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 1 of 4)
F i g u r e 458
1/67 22 -03 -00
Pages 401/127, 401/128
 c OLLIIV s hIAISTENASCE
MANUAL

FLIGHT SERVOS
AhNW- COURSE PEDESTAL DIRECTOR INSTQUMENT FLIGHT MODE mISC MISC POWiR AUTOPILOT EMERGENCY
C A T O R INDICATOR CONTROLLER INDICATOR WIRE F L M T I O N AMPLIFIER COMPUTER COUPLER NAY RCVR AMPLIFIER WIRE FUNCTIOh RLDDER WISC CISCONNECT

@ 331A-bA tlSE-?G 32%-7C 39YC-1F 5t2A-5G 5b2C-Y 33YC-3 12lA-2

J1A J 1 3 J l A J13 J l JI J1 J2
J1 JZ J1 J1 J2 (TP) (3P) (-9) (3P) (TP) (3P)
.. ... ... .. .. .. VOR SELF TEST DISABLE . . .. .. : :
.. .. .. ... ... .. VOR SELF TEST DISABLE .. .. . . :
1-
15 -1 9 NAV CONT
3133-3 :
.. ...
5Y
. . ..
..
.. VOR SELF TEST DISABLE .
. .
. .
..
.
..
: 98 -55 (J2) '
. .
: BACK:
:
: COLRSE
: .. ... ... VOR SELF TEST DISABLE
VOR SELF TEST DISAOLE . . . . :
:
90
l b
: K Q
n
r
: : AIRSPEED :
:A:: . .. .. VOR SELF TLST DISABLE . . .. .. : 2 L :
.. ..: SENSOR
. ..
1.
.. . .
@. [ -. : :.
BACK COLRSE MODE I N P U T . : : : : 1 3 59002
. .. .. .. .. .. .. .. .. .. .. J1
. . . BACK COLRSE INTERLOCK : : : : : 1 2 59 : AIRSPEED SIGNAL . .

. . . . . .. .. .. .. .. .. (J1) : . .
95 : . . . DISTANCE SHUTTER + . . . . . . 9 . .
Yb : . . . DISTANCE SHUTTER - . . . . . . 10 .
..
..
..
97 : . . . DISTANCE RECEIVERS 2 t VAC HCT : : ; : : : 2
98 -: .. .. .. DISTANCE RECEIVERS 2 5 VAC GRD .. : : : : : 1 . .
w J: . . . DISTANCE RECEIVERS Z COMMON . .. .. .. .. .. .. ..
50 : . . . DISTANCE RECEIVER U Y I T S X . . . . . . . .
51 : . . . DISTANCE RECEIVER U S I T S Y . . . . . . 3 ... ...
52 : . . . DISTANCE RECEIVER TENS X . . . . . . b .. ..
53 ; . . . DISTANCE RECEIVER TENS Y . . . . . . 5
5Y . . . . DISTANCE RECEIVER WNDQEDS X . . . . . . 7 . .
.. . ..
.. ... ...
DISTANCE RECEIVER HUNDREDS Y
.. .
: :
. .
:
.
:
8
COMPASS : . .
.. .. .. : : : : 328A2A : ... ...
.. . . J2)
. .
COWPASS HEADING X .. .. .. .. .. .. 2
. .
. . . . . . . . . . .
COMPASS HEADING Y .. . . . . . 3 . .
. . . . .. .. .. .. .. .. .. . .. ..
.. . .
.. .. .. COMPASS HEADING Z
.. .. .. .. .. : * :
. .
... ... ... 1 1 5 VAC POWER ..
. ..
.
.. .. .. 28 M C POWER : : : : : : 2b
. .
.. .. .. GROUND : : : : : : 2 ) ; ; GRD
. . . COMPASS MONITOR I : 3q-lY-25 : : ... ...
HEADING DATUM H ' : . : : : b 1 1 : : : 49 COMPASS DATA X
: Y . . .. HEADING DATUH C ' . . . . . ? 9 : : . 50 COMPASS DATA Y . .
. . .. . .
.. .. .. ... .. HEADING DATUH H '
HEADING DATUIl C '
. 51 COMPASS DATA Z
... ...
. . . .. .. HEADING DATUM LOAD RES ( 1 C K ) . . .
13 . . . . COLRSE DATUII H' PILOTS coPILois
12

30
. .
. .
. .
.

:
29
21 :
...
..
.
.
...
..
.
.

:
..
...

.
:-S
. COLC(SE DATLW C '
COLRSE DATUM H '
COLRSE DATUII C'
COURSE DATUII LOAD RES ( I C K )

COMPASS FLAG -
COMPASS LOW LEVEL FLAG +

A Z I M U T i CARD ERROR CT r l ' : 1 3 : : :

AUTOPI LOT DISENGAGE

AUTOPILOT DISENGAGE
-- DISENGAGE
BUTTON
L
.
..
.
.
.
..
.
.
DISENGAGE
BUrTON
I

20 : : : 5- AZIMUTA CARD ERROR CT C ' : 1 2 : : : : ... ...

13 : : : 5- AZIMUTH CARD RATE G2 . l Y : : : :
1Y
11
12
:
.
.
.
.
:
.
: 5-

.
AZIMUTH CARD RATE C2
AZIMUTH CARD SERVO D R I M M1
AZIMUTH CARD SERVO DRIVE C 1
-
- lb
17 :
:
:
:
:
:
:
:
:
:
:
:
:
:
SENSING
UNIT
?+SA-YB
15 . . . 2 t VAC HEADING PWR . 5 2 : : : : : : (ROLL)
l b . . . 2 t VAC POWER COM . S i : : : : b5 : ROLL RPTE WTOR GRD A
... ... ... ..
..
.
..
.
..
.
..
.
..
.
.. 8 . 115 VAC POWER . . B
.. .. .. .. ... ... ... .. ..
32 . m u RATE EXCTIATOI N c . . E
. . . . . . ._ ROLL RATE EXCITATION H . . F
. .. .. . . . . .. .. C'Q . m L L RPTE SIGNAL x G
... .. .. . .
..
..
..
..
..
..
'
I
1 UA:I3 ALTIMETE? :
. .
: (PITCH)

: 50 : RADIO ALTITUDE +
..
.
..
.
..
.
..
.
..
.
..
.
&F-1
(Pl5)
22
339H-( )
:
:
:
:
-8
10
32
-
PITCH RATE WTOR WD

-
115 VAC POWER
PITCH FATE EXCITATION C .
. .
.
A
B
E
. - . . . . . . - . .
:
:
..
51

.. : 17-
..
RADIO ALTITUDE
?ACIO ALTITUDE MONITOR t ..
..
..
..
..
..
..
..
..
..
..
..
23
12
:
:
31
29 -
PITCH FATE EXCITATION H
PITCH KATE SIGNAL X ..
. ..
.
F
G
.. .. .. ..
.. .. .. . ... ... ... ... ... : : YAW RATE
.. ... ... ALTITUDE EX? OVEiiRIDE 2C0 F T : . : @ ; :
:
:
:
GYRO
3326-1
.. .. .. ?UNWAY SYMBOL 230 F i ALT T R I P Yt
: :
:
L l
:
:
: : : tu YAW : RATE MOTOR GRD . . A
... .. .. MIDDLE VARKER TRIP *3-29
.. .. .. :
.. :
.. :
.. 1s 115 . VAC POWER . . B
.. .. .. A i T @ ; 51 YAW : RATE EXCITATION C .. .. E
:
.. : : : : : SEVSOR : 5G YAW . R A l E EXCITATION H F
.. . . . . .. .. .. .. .. 543A-3E : 9h PYAW RATE SIGNAL X . . G
. . . ALTITUDE ERROR H ' : : 3 3 : : : 15 P Yl : .. ...
. .. .. .
v .. ..: :
..
ALTITUDE E9ROR C '
ALTITUDE HOLD MODE INPUT
ALTITUDE dOLD VODE (SENSOR)
:
.
:
:
:
:
2 3
:
:
:
:
:
:
: c g
'ic-33Y
: 2) Y2 :

.
.. .
.
.. .. .. ALTITUDE HOLD MODE : : 'i7- 27 : . .
.

-
w
..
: : ALTITUDE INTERLOCK . : : . : ? a .
.. ...
. ALTITLlDE ISTERLOCK : : 'it-39 : . .
...
..
.
...
..
. ..
..
ALTITUDE OFF
GS ON
115 VAC POWER
:
Y'i
..
..
- :
-
... ... ...
' 1 8 :
39 95
: 3 3

...
3
.. 3b 4 . 4b
.
...
. .
.
...
... ... . . . .. .
AC GROUW
. ... ... ... ... 37
39
: SRD
-- 93 ALTITUDE GAIN CbAVGE i X C I T A T I O N .: .:
. . .. .. .. .
.. *? : Y9 ALTITUDE GAIN CHWGE NO. 1 .. ..
. . . . . . 93 . Y5 ALTITUDE GAIN CHANGE NO. ? 777-2563-001

AP-103F/FD-l08G M a s t e r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 2 of 4)
Figwe- 458
M a y 1/67 22 -03-00
P a g e s 401/129, 401/130
 a
COLLINS
MAINTESANCE
v

FLIGHT SERVOS
ANNLN- CWRSE PEDESTAL DIRECTOR INSTRMNT FLIGHT MODE AUTOPILOT EMRGENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FVICTION ARLIFIER CCWUTER mwm MISC MISC POWER WLIFIER tIIRE FUNCTIOh RUoW MISC DISCONNECT

@ 331A-bA LIYE-ZG 3290-7C 3YYC-1F 5b2A-5G IblE-1 33YC-3 121A-2

J I A JIB J1A J1B J1A J I B Jl J2
J1 JZ J1 J l J2 (TP) (BP) (TP) (BP) (TP)(BP)
... ... ... ..
.. .. .. : : : : : : M A R K Q : : ...
.....
.. .. .. .. ... ... .. .
...
.
...
.
...
.
...
.
... : ..
..
BCN

. .. .. .. .. ... ... RECV : ...

..
.
.. .. . .. . ... ... ... ......
.. ... ... .. ..
..
..
.. ..
..
.
..
..
.
...
...
.
.
.
...
..
..
.
...
..
.
1 1 5 VAC HEADING PWR
115 VAC ATTITUDE PUR
115 VAC COWAND PUR GROUND :
. .
.=: N

-- ---I'
115 VAC RUNWAY PWR 28 VDC POWER P
.. ... ... .. . .. 115 VAC PUR CON RUDDE? SERVO POWER S
. . . . .. .. . . . . . . RUDDER SERVO POWER T
*'. . . 53 DC GROUND - l-l-2b : GRD
.. ... ... e-----+- : 28 VDC POWER : . : : : 2 5 AILERON SERVO POWER
Q Q
:
.
-2Y
.
:
. g :
: 19
: 25 VDC POWER (REG)
5 VACIDC LIGHTING
:
.
.
:
.
59-ZY
. . . .
: i
D
bl .
-
AILER>N SERVO POWER
ELEVATOR SERVO POWER
.. ... . . .. .. .. i .
o? ( &
: 20-
..
:
..
25 :
. ... .. ..
5 VACIDC COM
. : bY ELEVATOR SERVO POWER
... ...
20 X
. . .. ... .... .... : I @ ; i .. ..
.. .. .. ...
: : : :
... ... ... . . .. ..
.. . . .. . -
-
.
: GA:
: BUTTON
:I:
....
:

.P o .. .
.

~..
:
:
.
..
..
..
. .
... ... ..
...
.
..
...
.
..
MIDE++ ROLL
GO AROUND MON
GO AROUND MIDE + PITCH
G3 AROUND EXC
GO AROUND ACTUATE
EXTERNAL STEER + DOWN
.
42-
:.
. . .
..
..

. .
.:

:.
. .
: 2 9
-!J;
4Y

:
- .
:
. . :

:
GRD

$
1

b
:

:
TRIM ENGAGE VOLTAGE
TRIM ENGAGE GROUND
lRIM
COUPLER :
IbU-AA
(JIB
20
K :
:

:
: L
.. . .. .. .. EXTERNAL STEER + LP ; ; ;;I;; ; . . M

... ... ... ... . . .

-
.
.. .. .. .. ... ... GYRO MODE
HEADING MODE
:
:
:
:
:
:
91-20
97-21
:
:
-YO
-bY
:
: : : TRIM
.. .. .. .. .. .. N I L MODE : : : Yb-22 : : Y? : : INDICATOR :
... ... ... . .. .. APPROACH MODE : :
- 3 - - 59 Y8 :
. . : 32)D-IW
.. .. .. L : : GYRO MODE . . : : : 2 0
: : : : : : : 2 1 115 VAC PGlER
... ... ...
K
J : :
HEADING MODE
N I L MODE : : : : : 2 2
0
. :
.
. . . H
.. : : APPROACH MODE .. :. : : : 2 3 : GRD GROMD 1 :
. . . . . ... . .. .. .. .. : 3+----51c TRIM TAB MOT CONT +-1
... ... ... .. .. ... ... ... ... ... ... :
... ...
3 3 4 - TRIM TAB MOT CONT -31 E
.. .. .. .. . . . 33 :
.. .. .. .. .. ... .. ..
AILERDN TRIM INDICATOR

.. .. .. .. ... ... .. ..
..
..
. .
3Y _r__ AILERON TRIM INDICATOR
:
.::
---+ + A

.. .. .. .. . . . . . .. ..
52 RUDDER TRIH. INDICATOR

.. .. . .. .. - 53 . RUDDER TRIM INDICATOR R

...
N I L ARM .. ... ... - : TRIM INWT m +
- 2L :
..... ..... ...
N I L CAPTURE
GS ARM
..
.. .
...
:
: .
... -
:
: b-36
: 3 9 - 3 :
: ..
:
..
3 5 ' 4 9 - TRIM INWT Ly

... ... ... . : -- : :

.. ..
GS CAPTURE 8-3)
. . GS EXTENSION
. . .. ..
. . : .. : 92- 38 : RELAY BPD
-
..
GO AROUND : : lb-33 :
.*
-
-
.
- .
N/L ARM ANNUNCIATOR +
.
N I L CAPNRE ANNUNCIATOR +
.
. .
.
. .
:
.
:
: :
: 3 7
38 ... ...
.*
** P
: :
GS ARM ANNUNCIATOR +
.
GS CAPTLRE ANNUNCIATOR +
GS EXTENSION ANNUNCIATOR +
. .
.
. :.
. :
:
:
:
:
.
: + I @ :
: Y 2
S L A T Qo
-
. -
.

..
' 0 P
..: : : ..
GO AROUND ANNUNCIATOR
:
. - : : :
: 9 3
: Y 4 .. ..
-* P A L T I T W E ANNUNCIATOR .. :
.
:
.
: : Y o -.. ...
. . BACK COURSE ANNUNCIATOR +
.~
..
: : Y5 . .
ANNUNCIATOR BUS
.
:
.- : : : 1 9 : : E
... ...
... ... OUT OF VIEW B I A S
.... 2 0
..- - : :
. :
. : P b
. I

. .
: RATE OF TURN DEV + . . .. ..
... . .
.... .... ... ...
OF TURN D N +
:-PATE
:
:
...
RATE OF TURN FLAG +
..
..
SENSOR :
..
-
- - .. ..
.... ....
PATE OF TLRN FLAG
.. .. . . -.- .. ..
... CORLTER MINT
. .
...
.<

.. .. 1 9 : : : _I. . 18 EXT PITCH STEERING A

.. ..
.. .. .. ...
9 . :
-. r
-. 5- 19 EXT PITCH STEERING 8
. . .~
..
9 9
Y o
:
: : .
-5 25 AC PITCH STEERING A
.... ...
...
... 5- 2b AC P I T C n STEERING B
-.
..... .. .- 3 6 . : I 6
- 27 PROCESSED PITCH DATA A
.. . . -
.. .. . . .
PROCESSED PITCH DATA 0
INTERHAL PITCH STEERING OFF + : :
... ... ..~ . : 24 : : bo ALT HOLD OFF + . ..
... .
...
.. .. 19 : : sv 18 : EXT ROLL STEERING A ... ...
. .. .. 9 : :
:
SA 19 : EXT ROLL STEERING B .. ..
... ... ... .- Y9
YO
f
: :
59 25
SA 2b
:
:
PROCESSED BANK CMP A
PROCESSED BANK KW B . .
.. .. .. 35 : : sv 35 : PROCESSED BANK DATA A . .
... .
... 25 : : Sb 36 : PROCFSSED BANK DATA B ... ...
.. .
... .. 1) : : sv 59 : EXT BANK OH) A . .
... . ..
.~ ..
.
18
7 :
:
:
:
SA 55
57
:
:
EXT BANK CMD B
INTERNAL ROLL STEERING OFF +
. .
: : 777-2563-001

AP-103F/FD-l08G M a s t e r y I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 3 of 4 )
F i g u r e 458

M a y 1/67 22 -03-00
P a g e s 401/131 401/132
 COLLINS
MAIKTEIVANCE

FLIGHT SERVOS
A!INUN- COLRSE PEDESTAL DIRECTOR INSTRUMENT FLIGHT MODE AUTOPILOT
EMRGENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER COWUTER COWLER MISC MISC POWER AMPLIFIER WIRE FUNCTIOh MISC DISCONNECT

331A-bA blYE2G 3290-7C 349C-1F 5b2A-5G IblE-1 512C-9 121A-2

J1A J1B J1A J I B J1A J I B J1 J1 *I
J l 52 Jl J l J2 (TP) (BPI ( T P I ( B P ) ( T P ) (BP) (TPI (BP)

A : : PITCH CONTROL EXC A . . . . . . : 21

B : : PITCH CONTROL SIGNAL . . . . . . . 20
c : : PITCH CONTROL EXC B . .. .. .. .. ... . 22
D : : .
E : : TURN CONTROL EXC A . . . . . . 21 :
b : : TLRN CONTROL EXC B . . . . . . ?2 :
G : : TURN CONTROL SIGNAL . . . . . . ?(I :
N : : I N T MOTOR CONTROL VOLTAGE . . . . . . : b2
P
R
s
:
:
:
:
:
:
I N T 2b VAC MOTOR EXCITATION C
I N T MOTOR FATE SIGNAL
I N T MOTOR SIGNAL C O W N
:
.
.
:
.
.
.
.
.
.
.
.
.
.
.
.
.
:
-
19

:
b3
29
:

T . : 28 VDC PANEL LIGHT PUR . . . . . .

U
x
:
:
:
:
GROUND
..
. ..
. ..
.
.
..
.
..
.
..
: : . : : :
Y
z : :
ENGAGE VOLTAGE
.. .. .. .. 3 ..1 :
..
a : : ENGAGE PULSE . . . . . : 56
b : : DISENGAGE VOLTAGE . . . . . . : 37
c : : ENGAGE READY . . . . . : 55
d . : ALTITUDE HOLD MODE + . . . . . . . 38
f : : HEADING SYNCH CUTOUT . . . . . . 3E :
P : - . . . . . . : Q
9 : : 115 VAC POWER . . . . . . ? :
r : : I N T 2 b VAC MOTOR EXCITATION H : : : .. . . 23 :
5 : : ENGAGE INTERLOCK .. .. .. .. .. .. . 59
t : : . . . . . . k
u : : AILERON CLUTCH VOLTAGE . . . . . .
v : : ELEVATOR CLUTCH VOLTAGE . . . . . .
w : : RUDDER CLUTCH VOLTAGE . . . . . .
.. .. .. .. .. ..
M
x
:
:
:
:
c 2 8 VDC AUTO P I L O T PWR
.
..
. . . . . : 53 - YAW DAWER ENGAGL MON +
!
.. i i SPARE
.. .. .. .. .. : 5

.. ... ... ... .. .. .. .. ..

.. .. . . . ... ... ...
.. .. .. ... ... ... . .
..
... .... .... .. .. .. ... ... ... .. ..
. . ... ... ...
.. . . ... ... ... Ykrn DMW sw
. . ... ..
. .. .. .. ... ... ...

SYhBOLS USED: 10. ANNUNCIATION VARIES WITH THE PARTICULAR INSTALLATION. I N T H I S INTERCONNECT ANNUNCIATION I S
28 VDC: OTHER OPTIONS MAY BE PROVIDED.
SV W I S T E D SHIELDED PAIR-ADJACENT
SA WIRES AS SHOWN ON ERAWING 11. THE 5b2C-9 AND Sb2A-5G SHOULD BE MOUNTED AS CLOSE TOGETHER AS POSSIBLE, PREFERABLY ON A DUAL
SG SHIELD T I E D TO GROUND AT U N I T MOUNT. THESE SIGNAL LEADS MUST BE TWISTED AND WIRED POINT TO POINT BETWEEN THE UNITS. THE
W I S T E D PAIRS SHOULD OE KEPT AS SHORT AS PRACTICAL AND MUST BE SHIELDED I F OVER WO FEET LONG.

12. TOTAL WIRE W N FROM BUS TO 1 2 1 A - 2 TO 5 b X - Y TO 33YC-3 ( P I N 0 ) FOR EACH PRIMARY SERVO MJST NOT
EXCEED 4 5 FEET I F AWG 20 WIRE I S USED. WHEN GREATER THAN 95 FEET, INSTALL TERMINALS AT 5b2C-4
MOUNT AND RUN AWG 2 0 WIRE FROM 5b2C-Y TO TERMINAL 3YYC-3 P I N 0.
NOTES :
ii. POWER FROM A PARTICULAR CIRCUIT BREAKER OR FUSE MAY PROVIDE POWER FOR W R E THAN ONE EQUIPMENT.
1. REFER TO W E I N D I V I D U A L INSTALLATION MANUALS FOR COWLETE INSTALLATION INFORMATION. T H I S WILL BE INDICATED I N THE INTERCONNECT POWER C O L W BY A LETTER WITH AN OCTAGON S Y m O L AROUND
I T , CAPITAL LETTERS FOR DC AND LOWER CASE LETTERS FOR AC.
2. SPEED DISPLAY I S COVERED BY A REMOVABLE MASK.
A. 0
.. C -
. G.. I. .
.. 0.
-
28 M C 5 M a. b. ., m - 1 1 5 V
c , d , e, f -
~
900 HZ 1 A W
3.

Y.
ALL WIRE SIZES M E NO. 22 UNLESS DESIGNATED OTHERWISE BY NUh8ERS I N SQUARES.

SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE GROUNDED AT THE 51RV-I.
SHIELDED WIRES ARE GROMDED AT ONE END ONLY. E
F -
2 8 M C ANNUN D I M E R
28VDC PANEL L I T E S
H - I W
g
k
- SVAC D I M E R
11% 400 H Z 2

- 115 VAC 400 HZ 3 AMP

~ h p

5. FOWI WIRES W I S T E D WITH SHIELD FOR C O M P A T I B I L I l Y I N FUTURE ARINC INSTALLATIONS. i't. WITH TRIM INDICATOR CQNNECTIONS AS SHOWN AND THE REVERSING L I N K S INSTALLED FOR CORRECT SERVO
PHASING THE PRIHARY SERVO CAPSTAN SHOULD N R N CLOCKWISE WHEN VIEWED FROM THE CAPSTAN END UNDER
b. m E AUTOMATC
I FLIGHT CONTROL SYSTEM AS CONNECTED IN mIs DRAWN
IG REFLECTS LOADS AS FOLLOWS: M E FOLLOWING AIRCRAFT ATTITUDES:

AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS AILERON

ELEVATOR
-- RIGHT BANK
PITCH Up
200 OHMS TO-FROM 100 OHMS JUWER BP-Y3 TO BP-33 OF 51RV-1 RUDDER - RIGHT YAW
500 OHMS GLIDE SLOPE POINTER 200 OH!6 JUWER TP-8 TO TP-? AND TP-3 OF 51RV-1
SOD OHM GLIDE SLOPE FLAG 250 OHMS JUMPER T P - Z I TO T P 2 b OF 51RV-1 15. YAW DAWER SWITCH AND BACK COLUSE SWITCH ARE SOLENOID HELD K,ICROSWITCH bET1-T AND 5ET1-T OR
500 OHMS LO€ FLAG 250 OHMS JUWER BP-32 TO BP-41 OF 5 l R V - 1 EQUIVALENT RESPECTIVELY.
500 OHMS COURSE BAR 200 OHMS JUWER BP-39 TO BP-30 AND BP-98 OF 51RV-1
lb. THE GA BUTTON WILL NORMALLY E LOCATED ON THE CONTROL WHEEL.
?. THE POWER FOR THE COWASS SYSTEM WJST BE OF THE SAUE PHASE AS THE REST OF THE ALITOMATIC FLIGHT CONTROL SYSTEM.
17. OPTIONAL CROSSOVER SWITCHING OF STEERING INFORMATION MAY BE PROVIDED BY USING ALTEIWATE WIRING
8. POWER LEADS D E N T E D BY "DIM" SHOULD BE T I E D TO COCKPIT L I G H T DIMMING CIRCUITS. AS S H W N I N COLLINS LXAWING ?72-Y523-001.

5. SENSING U N I T 39SA-4( ) AND RATE GYRO 3326-2 SHOULD BE LOCATE0 AS CLOSE TOGETHER AS POSSIBLE. 18. A PAIR OF 1/2 WATT 1 O X RESISTORS SHOULD BE SELECTED TO GIVE FULL SCALE TRIM INDICATOR MOVEMNT
WHEN CONTROLS ARE OVERPOWERED U N T I L SERVO L U T W SLIPS. THE RESISTANCE SHOULD BE S P L I T WITH
HALF ON EACH S I D E OF T R I M INDICATOR M O V E M i T . THE TOTAL RESISTANCE V A L E SHOULD BE GREATER THAN
5K OHMS.

19. A L T I N D E T R I P POINT I S NORMALLY ADJUSTED TO 200 FEET BUT MAY BE AT A DIFFERENT ALTITUDE I F
DESIRED. CONSULT AL-IO1 SYSTEM MAINTENANCE MANUAL FOR S P E C I F I C ADJUSTMNT PROCEMRES AND FOR
N T I N D E T R I P WIRING INFORMATIOH. 777-2563-001

AP-103F/FD-l08G M a s t e r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 4 of 4 )
F i g u r e 458
M a y 1/67 22-03-00
Pages 401/133, 401/134
 a
COLLINS
MAIIVTEKANCE
MANUAL

FLIGHT
IVIIUN- COURSE PEDESTAL DIRECTOR 1NSTRUMEt;T FLIGHT MOLE SERVOS
CIATOR INDICATOR CONTROLLER ILDICATOR WIRE FUI~CTIOII AMPLIFIER CO~IPCTER COUPLE:! MISC m c PCW~ AUTOPILOT EMERGENCY
AMPI T r T P 9 WIRE FUhCTIOti AILERON MISC DISCONNECT
@ 331A-bA blYE-ZG 3290-80 3YYC-1F 5b2ASG 1blE-1
J l A J15 JlA JlO J1A J L 33YC-3A 121A-2

..
. . .
J1

.
.... ..... .....
32

.
J1

:
:
J1

52
b
-
52

:
J3

:S+
PITCrl ATTITUDE MOh H
PITCH ATTITUDE ERROR H '
(TP) (BP)

: z t :
. 2 2
(TP) (BP) (TP) ( 3 P )

:
:
:
:
:
:
:
: :
bz=@z 5 1 51-
AILERON
26 M C
FIELD NUNbEH 1

-ec
-A
J1 J2

:
:

... ... ...

:
:
7
8-
: :sL- PITCH ATTITUDE ERROR C'
PITCH ATTITUDE SERVO c a m MZ -
-
: 2 1
2b
:
:
:
:
:
:
:
: 13 .
.
51-
AILERON
AILERON
FIPL) NUWER 2
SIGhRL C
- E
:
:
..
.. ... ...
:
:
-9
10 : :s e
PITCri ATTITUDE SERVO D R I M C
PITCH ATTITUDE RATE G2 : 2 3
25 :
I :
: :
:
:
:
14
15 .
AILEROK
AILERON
EXCITATIOti C

--
POSITIOtI EXCITATI0I.I H
F
G
:
:
..

...
...
.
.
... ...
.. ..
. .
. .
... ...
:
:
:
:
:
:
11
25
29
23
2 2
21-se
-
:
:
:

.
:S b
: sv-
:S b

:
PITCH ATTITUDE RATE C2
BANK ATTITUDE RATE C2
8A14K ATTITUDE RATE G2
BANK ATTITUDE SEW0 RIM C
BANK ATTITUDE SERVO D R I M M2
BANK ATTITUDE ERROR C'
- : a
: 3 Y
. 3 3

: 3 1
35
3b
I
:
:
:
:
:
:
:
:
:
:
:
:
:
I
:
:
:
:
:
:
:
:
:
lb
12
11x
-1-
l i -1s-
..
.
:
:

..
.
S+
s+
AILERON
AILEROI?
AILERON
AILERON
SERVC GRC
RATE SIGNAL
-
PATE EXCITATION H
POSITIOI. SIGNAL

-s.
H
L
R

... ....
:

:
:
:

.. . .
.. ..
:
:
20 : :5 6 BANK ATTITUDE ERROR H ' : 3 2 :
:
:
:
:
:
:
:
.. .. .. ..
. ... ...
5 Y : : BANK ATTITUDE MON H . 3 8
. .
... I I ;
-
: 32 : : 7 2b VAC ATTITUDE PWR : 53 : : : : V E i T Q I AILEROt; ENGAGE VOLTAGE
... . . ... ...
..... .....
: 33 : : " 2b VAC PWR COM : 5 1 : : : : REF : :
GYRO HIGH LEVEL FLAG + . .. ..
AILERON ENGAGE WLTAGE
. B.
....
..
. .
... ...
:
:
:
: : 33-
.. .. .. ..
: 18-

3 : : ' :
GYRO HIGH LEVEL FLAG
GYRO MOL +
PITCH ATTITUDE CT X
- . 3 0
: YO
29

: : 3 0 :
- :
10
:
:
:

:
:
:

:
332D-11
J1
N
A
:
:
:
:
..
..
..
..
.. ..
ELEVATOR
33YC-3A
:

... ... ... .. .. ~~ ~

.. .. ..
:
:
: 1)
9-e
5 :
:
:
:
;
C
PITCH ATTITUDE CT Y
PITCH ATTITUDE CT Z
5At.K ATTITUDE CT X
:

:
.
:

:
.
2 0
.
:

. 3 0
.
:
.
:
:
.
:
0
C
D
:

: biEE ELEVATOR FIELD NUMBER 1

.....M C
28
- ( J l ) (J2)

0
A :
:
..
. ... ... : *-81 BANK ATTITUDE CT Y : : : 2 c : . E : ELEVATOR F1E.D NUWER 2 -C
-
'
.. ... ... . . . . . .
.. .. ..
: 1 9 : :
.. .. .. ..
. . .. ..
BANK ATTITUDE CT Z
115 VAC POWER .. .. .. .. .. .. L
-
9 :
:
13++
lY -
-
ELEVATOR SIGhAL C

-G
. AC GROUND G
-i 0 : 15 ELEVATOir
-
FOSITIOh EXCITATIOI.
.. .. ..
- : :
:

:
:
:
12
13
PITCH ATTITUDE X (BOOTSTRAP)
PITCH ATTITUDE Y (BOOTSTRAP)
PITCI! ATTITUDE Z (BOOTSTRAP)
:
:
:
:
:
:
:
:
:
:
: 5 3
. 5 Y
:
:
lb-S2--
1 2 4 -
ELEVATOR
ELEVATOQ
RATE EXCITATIOI: H
P0S:TIOt. SIG!.AL - H
L
:PITCH:
. ..l Y .. .. : 5 5 : 11-x+ ELEVATOR SERVO GRC
:SYNC : :
.. . .. ..
PITCH COMMMC H ' : : 3b-15 : :
-
1i-s+
:BUTTON : PITCH COMMAND C ' : : 2b-lb : .. ..
y:
r. . .
.. . .
:
:
..
15
lb -
. .. ..
.
.. .. ..
2b VAC ATTITUDE POWER
2b VAC PUR COM
PITCI! srlrc VAN
P I T C h STEER + UP
:
.
.
:
:
:
: 53-5
: 51-2i
: : 3 c :
..
..
.
..
..
.
.
...
.
.. ..
.. ..
..
.
... ... .. ..
. .
PITCH STEiR + WWI.
ROLL STEER + LEFT 13-31
:
:
5-31
Y-21
:
:
:
:
:
:
:Q
:
i I
> :
..
.
..
.
ELEVATOR ENGAGE VOLTAGE
ELEVATOR E:WrGE VOLTAGE
J
ti

... .. .. .. .. .. ..

-
-
ROLL STEER c RIGHT 11-21 : :
. . : Ls-i V-BAR ROLL POS XMTR I : :
.. .. .. : s o I :
.. ..
:
-
3Y V-BAR ROLL POS XMTR X : b 3 : : : :
. . .
..
..
. .
.
...
.
.
...
:
:
:
3b
3)
38 : :s
e
V-DAR ROLL COMMAND SERVO CRIVE C
V 4 A R ROLL COWWND RATE G2
-
V-BAR ROLL COMMAND SERVO CRIVE MZ -L- b2

- b3
b l
:
:
:
:
:
:
:
:
:
:
:
:
.
..
.
..
: 39 : :5 6 v-LAR ROLL CO1IYIIAt:D S I G COM- 55 : : : :
.. ... . -
...
-
:se
..
.. .
. .
:
:
Y5
YY
:
: :5 6
V-BAK PITCH COIWNC S I 5 COM
V-BAR P:TCH C0WMI.C RATE G 2 - 59
b2
:
:
:
:
:
:
:
:
:
:

. . ... ... : 93- v-am PITCII COMMAIC SERVO CHIVE c bY : : : : :

... ... ...

: Y2 V-BAR PITCH CO!4Ml\NC SERVO DRIVE '12b3 : : : : :

..
:
.. .. .. ..
Y1- V-BAR PITCH POSIOFF-SCALi YIAS
XMTR Z
- ..
b l :
.. :
.. :
.. :
.. :
..
.. ... ... : Yo- V-BAR PITCH POS XMTR X - b o : : : : : . .
.. .. .. : Y8 : f : 2 b VAC COMMAIID PWR b ? : : : : : RUUDER
.. : : : 35+ 2b VAC COMMAND PWR COM - 5 Y : : : : : 33YC-3
.. ... ... :
. . : .9- . STEER FLAG - . b Y : : : : (J1) (JZ)
.. ..
..
..
..
PITCH COMPUTER MON + : : 12 -
12 : : kAV RCVR RUCDE:! F I E L L :IVWER 1 - A :
. .. .. .. ..
: : 3- STEER FLAG + . : : 38 : : 5lRV-1 : 2s vcc 5 .

:
:
33
3Y
:
.
:
:
: l o
: 11-
: :
COMMAI.ID SERVO MONITOR
GLIDE SLOPE DEV + Up
GLIDE SLOPE DEV + WWh
: b5-
. : 3 2 :
: . 2 2
28

:
:
:
:
:
:
:
(TP)
8
9
0; : Y
13 -s+
$9
l

:
:
:
35 . : : 1 2 : 7 GLICE SLOPE LOW LEVEL FLAG +
- : : : : : . 21 : Y5 . RUUi:ii POSITI01. EXCITATIOI.
--Gii

.. 3b
.. ..: :
.. .. : 1 ..3 .. : ' GLIUE SLOPE LOW LEVEL FLAG
GLIDE SLOPE HIGH LEVEL FLAG +
: : : : :
.
:
.
22 : Lib -S+ RUCLER RATE EXCITATIOh d
-LR
.. .. .. ..
: : : -s+
... .. .. : 11 27 :
.. . . . . . $2 RUDLER POSITI38: SIGllAL
. . .. .. .. .. .. ... ... ... ... ... Y 1 -x+
Y i+s-
RilDCER
RUUCCk
SERVO GRb
k A T i SiGhAL
:

.. . .
:
.. ..1 :
.. :
.. ..
:
..
: STY-
..
COURSE RSVR A
. ... ... ... ... ... lb :
: i
;q
1DP) i J D C i 3 tl.GAG: VLLTAGE
: : : S T Y - COURSE RSVR E . . . . . . 22 : % & E K EI\GAGI VOLTAGE 3 C
: 5 T Y - COURSE RSVR C . . . . . . 23 : ,. ..
: : : S T Y - COURSE RSVR H . . . . . . 21 : . .
: Y : : : : . s v - COURSE RSVR D . . . . . . ZY ... ..
: 5 : : : : . S b COURSE RSVR E . . . . . . 25 : .. ...
: b : . . : s- .
COURSE RSVR F . . . . . . 2b : .
.. .
..
: 7 -56 COURSE RSVR G . . . . . . 27 :
: 2b . . . . . TO - FROM + TO . . . . . . Y3 : . .
: 27 : . . . .
. . . .
TO - FROM + FHOM . . . . . . YY .
..
.
:
:
31
32
:
. . . . . .
VORILOC LOW LEVEL FLAG
v o w L o c LOW LEVEL FLAG
+
- .
.
.
.
.
.
.
.
.
.
.
.
Yl
Y2
:
.
....
: 29 : . . . . VOR/LOC CEV t LEFT + . . : . . 1 1 - YO
.
. ..
:
.. 28
.. VOR/LOC DEV + RIGHT . : : : : 1c- 30, :
VOR/LOC DEV + L t F T 7-32-11 : . .
.. . VOHILOC U t V + RIGHT 8-22-13 : . .
...
..
..
. ..
.
...
..
..
..
.
..
..
.
..
..
.
..
..
.
VORILOC 4 1 LEVEL FLAG
LL'C FkCCJE:rCY
ZoVOC NAV REC POYc%
l?-ll
Y3
. -
. . .-
. . .- -
.
Y3
. .
:
I=
.
.
5J
3h
37
: TO >.AV
REC PUR
...
..
...
..

AP-lOSF/FD-l09G Falcon (3-Axis), Interconnecting Wiring Diagram (Sheet 1 of 4)

Figure 459

May 1/67 22-03-00

Pages 401/135, 401/136
 a MAINTEKAKCE
COLLINS
wv

FLIGHl
WNUN- COLRSE PEDESTAL DIRECTOR INSTRUWNT FLIGHT MODE AUTOPILOT
CIATOR INDICATOR COI.TROLLER INDICATOR
I(IT AIRSPEED EMERGENCY
WIRE FUNCTION AMPLIFiER COWUTER COWLER NAV R M HAV #YIT POWER WLIFIER WIRE FUNCTIOI# DISCOlrlNECT
@ 331A-U LlYE-BG 329B-8G 34YC-IF 5b2A-5G IblE-1 SIN-1 313JJ L21A-2
JlA JIC J l A J1B J l A J1S JI
J1 J2 J l J1 J2 33 (TP) (BP) (TP) (BP) (TP) (BP) (TP)
.. .. .. .. .. .. .
.. : : : :
: 1-19
.. .. .. .. .. .. VW SELF TEST DISABLE
. . . .
.. .. .. .. .. .. ... VOR SELF TEST DISABLE : : : : : 15- 59
.. .. .. ..
: : : : : *a- 55
Ka:
[!
.. .. .. .. VOR SELF TEST DISABLE
. . . . . . . .
.
: JACK: : VOR SELF TEST DISABLE : * 9 :
. . . . voa SELF TEST DISAJLE : : : : : l b n . .
: COURSE :
VOR SELF TEST LISADLE .. .. .. .. r 2 - . L .. .. :
:
:
:
AiRSPiiL
SEhSOR
iv: ZACK COLRSE MOCE 11;PUT
.. .. .. .. .. 13
..
.. .. : : 5403-2
0:
. .. . : : J1

.. .. ... . .
SACK COUKSE IhTERLOCK : : : : : 1 2 59 : AIRSPEED SIGXAL
DME Q :I @
. . .
. . .. .. .. .. .. SACK COURSE EXC .
.
.
. 29 - 25 :
58 : AIHSPtEC EXCITAT:OII i . .
.. .
SACK COURSE M03E bo : AIRS Pi B 0 E X C I T A T 3 , C
... ... . .. . . . . . ... .. .
.. ... ...
: : : UbOE-2 :
.. . . . . . . . .
. . . . ...
(J1) :
: . . . . . LISTANCE SHUTTER + . . . . . . 9 : ..
:
95
Yb . . . . . DISTANCE SdUTTER - . . . . . . 10 :
. . ..... ...
. . . . . : : :
...
: Y7 : CISTAACE RECEIVERS 2bVAC HOT f 2 :
. .. .. .. .. : : : : : 1 : .. .. .... ...
DISTANCE RECEIVERS 2bVAC GRD
:
:
Y8
9s-J: DISTAhCE KECEIVERS Z COMMON .. .. .. .. .. ..
: 50 : . . . . DISTAhCE RECEIVER UNITS X . . . . . . 4 .. ..
: 51 : . . . DISTAhCE
DISTANCE
RECEIVER UNITS Y
RECEIVER TENS X
.
.
.
.
.
.
.
.
.
. .
. 3
t
:
: . .
: 52 :
: 53 : . . . . 3ISTAIICE RECEIVER TENS Y . . . . . . 5 : . .
. . . . . ... ....
: 59 : CISTAhCE RECEIVER HUNDREDS X : : : : : 7 :
: : . . . DISTAhCE RECEIVER HUNDREDS Y : : : : . 8 :
. . ..
.. .
55 f
.. . . .. ... ... ... :@ .
... ... ... ...
: : : COMPASS :
... ... .. .. .. : : : : : : 328A-2A : .. ..
. .. .. . . . . : : (J1) (J2) :
. . . .
: 9-1 - .. .. .. .. COMPASS HEADING X :
.. .. : :
.. :
.. :
.. :
.. .:. .2 . :
... ... ... ....
: : 1 7 2 . . . .
: 10-2 - -.. .. - ..- .. COMPASS HEADING Y .
.. :
..
:
..
:
..
:. :
..
. i I
.. .. .. . .. .
: : 18J .
.-.
.
..
.
.-
.
. Z .. P .
.
: ... ... ... ...
.. .. .. .. .. .. ..
: 11-3 - COWASS HEADING Y

... ... ... ...

.
.. .. ... ...
~

: : 1 9 3 0 .
. . .
... .
...
.
... ... .
..
.
.. ..
1 1 5 VAC POWER
.
:
:
:
:
:
:
:
:
:
:
32
2b
:
:
:
: 8 .. ..
. .
-
28VDC POWER
.. . ... . .
..
GROUND : : : : : 27 : : GRD
. .. .. .. .. .. ..COMPASS MONITOR + 39 19-25 : : . .
: : 5 . . . .HEADING DATUM H ' . : : : : t 11 : : . YS COMPASS DATA X ... ...
: : ' I
... ... ... ...
HEADING DATLM C' : .- - ... ...

-
. . . : : : ? 9 : : : 50 COMPASS CATA Y
... ... ... ... ... :
..
;
HEADING DATUM H ' 33-b 3 51 COmWASS CATA Z
. . . . . .. ..
:
.. ..
13
..
:
.
.
.
.
.
.
.
.
HEADING DATUM C'
HEADING DATUM LOAD RES ( 1 0 K )
COWSE D A T W H '
:
:
:
:
:
:
: .
: 17
: 9
: :
. . I. i ..
. ... . .
.. ..
:
..
12
. .:
.. .
..
.
...
.
...
COURSE DATUM C' . : . : . 8
... ...
..
.
..
..
..
..
..
.. ..
.
..
.
..
.
COWSE DATim H '
COURSE DATUM C'
COURSE DATUM LOAD RES (10K)
:
.
..
:
..
.
:
.
: 3*-9
2*-1:]
.
i. i :
.
bb
.
- AUTOPILOT DISEhGAGL T-
: 30 : . . . . COMPASS LOW LEVEL FLAG + . Y ? : : 5 : b7 .. ..
:
:
: BY
: 21
. . . .
: :
COWASS FLAG
: .se AZIMUTH CARD ERROR CT H '
- : I 1
: I 3
:
:
:
:
1
:
3 :
:
AUTOPILOT DISENGAGE
.. ..
: : 20 : : :sL- A Z I M U M CARD EmOR CT C' : : : : .~ ... . ... ..
..
; . 1 2
.
-
: : 13 : : : :se AZIMUTH CARD RATE G2 . l Y : : : : . .
. . ..: .-
-
: : 14 : : 5 6 AZIMUTH CARD PATE C2 : 1 5 : : : : : : SENSING
: : 11 . . . . : : : :
: : 12 . . . .
A Z I n u m CARD SERVO DRIVE MI
AZIMUTH CARD SERVO DRWE C 1
17
It : : : : ... ...
5 :
:
:
:
@;IT
3Y5A-YC
: : 15 . . . . 2 b VAC HEADING PWR . 5 2 : : : : . . : :
: : lb . . . . 2b VAC POWER COM : : : : . . .
(....
ROLL1

... ... .. . 5 4 b5 ROLL RATE MOTOR LRL: A

.. : : :lo-?- RUNWAY LOC POS XMTR -X 2 8 : : : : : 8 : 115 V4C POWER . . 3
.. .. .. : : : 11-* RUlvWAY LOC POS XMTR -Y 2 7 : : : : : 32 : ROLL RATE EXCITATIO?l C . . E
.. .. .
.. .. ...
:
:
:
:
:
:
: 12-L-
: 13-
: lli-
RUNWAY LOC POS YMTR -Z
RUWAY LOC SERVO DRIVE M2
RUNWAY LOC SERVO DRIVE C
-2
-
2 2

2Y
3 :
:

:
:
:
:
:
:
:
:
:
:
:
:
:
31
24
.. ..:
ROLL RATE EXCITAlIO'. ii
m L L RATE SIGI~AL x
.
.
.
.
.
. F
G
.. .. . .. ..
.. .. ... : : : 15+ RUNWAY LOC RATE G2 2 t : : : : : :
.
:
.
(PITCH)

... ...
. .
...
..
:
:
:
:
:
:
: lb+
: 5-
: Y-
RUNWAY LOC PATE C2
RUNWAY ALT SERVO DRIVE C -
-
2 5
3 Y :
: :
:
:
:
:
:
:
: :
: -8
10 -
-
PITCH RATE WTOK GRD
1 1 5 VAC POWER .
.
.
.
A
B

..... ....- ... : :

RUNWAY ALT SERVO DRIVE Y2
: 7 s - RUNWAY ALT RATE C2
3
3 5 :
3 : :
:
:
:
:
:
:
:
:
.
32
31 -
-
PITCH RATE EXCITATION C
PITCH RATE EXCITATIOI, ii .
.
.
.
E
F

.. ... .
...
:
:
:
:
:
: b S 6 RUNWAY ALT PATE G2
: 1-+ RUNdAY ALT POS Y4TR X
RUNWAY ALT POS zmm Y
-
-
3
3 8 :
b : :
:
:
:
:
:
:
:
.
29
.
PITCH RATE SIGNAL X
. . G

.. ..
... ...
..
...
:
:
:
: 2-*
: 3-6- RUNWAY ALT POS WTR Z - 3 7 :
3 2 :
:
:
:
:
:
:
:
: .
..
.
..
:
:
:
:
YAW RATE
GYRO

.. .. ...
:
:
:
:
: 8-+
: 9-e-
2 b VAC RUNWAY PWR
2b VAC RUNWAY PWR COM - 5
5
3
1
:
:
:
:
:
:
:
:
:
: bb : YAW RATE MOTOR GW
:
.
.
:
.
.
3326-2
A
. ..
,
.. .. ..
:
:
.. ..
:
:
: 17-
: 18-
..
WNWAY FLAG +
RUNWAY FLAG
.. - Y9
Y8
. :
:
. .
:
:
:
.
:
.
:
:
.
: 1 RADIO ALTIMETER
: O 8 b O F - 1 339H-( )
:
:
:
10
51
:
:
.
115
YAW
VAC POWER
RATE EXCITATIOI: C .
. .
.
B
E
. . .. .. .. .. ... ; I I ; 1 1
(PlB) 50 YAW RATE MCITATION ti
.
F
.. ..
.. .. ... .. .. .. ..
RADIO ALTITUDE +
RADIO ALTITUDE - Y . : : : :
22
23
:
:
YLi
.. .:. YAW RATE SIGNAL X
... ... G

.. .. ...
R W I O ALTITUDE W N I T O R + 1
.
Y :
. .
: :
. .
:
.
: 12 : ... .
.. .... ...
.
.....
.. .. : : : 37- MDA LIGHT COhTROL E :
... ..
... : . . . . . . ....
..
: : 3b- MDA LIGHT TEST : GRD
.. .. : : : 38- MOA LIGHT EXCITATION . . . . . . .. ...
.. .. .. .. .. .. ..
: 0
. . . ALTITUDE EXT OVERRIDE : : Y 1 : : :
.. ..
... ... ... ... ... ... ... RUNWAY SYMBOL 200 F T ALT TRIP
MIDDLE MRKER TRIP
Yb
Y3-29
. : :
:
:
:
:
: . .
.
.
.
.

AP-103F/FD-l09G Falcon (3-Axis), I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 2 of 4 )

F i g u r e 459

May 1/67 22 -03-00

Pages 401/137, 401/138
 a
COLLINS
hlAINTENAIVCE
Qw MANUAL

FLIGHT
ANNLII- COURSE PEDESTAL DIRECTOR INSTRUMiRT FLIGHT MODE Y T AUTOPILOT EMERGENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION NRLIFIER COLPUTER COUPLER PNW MISC POWER MLIFIER WIRE FUNCTIOII MIX MISC DISCONNECT

@ 33lA-M blYE-PG 3298-8G 349C-1F 5bZA-5G IblE-1 59OAJE 562C-Y 121A-2

J l A J1B J l A JIB J l A J1B Jl J1
J1 JB J l JI J2 53 (TP) (BPI (TP) ( W ) (TP) ( 3 P ) (TP) (BP)
.. .. .. .. ... . ..
.. .. .
...
.
...
.
...
.
...
.
... Q : .. ... .. ...
...
:
.. .. .. .. ... ...
... ... ... . .
. . . .. .. .. . .. .. .. .. .. .. ..
..
..
.
...
.
...
.. . . ... ALTITUDE ERROR H '
ALTITUDE ERROR C'
:
:
:
:
3
2
3
3
:
:
:
:
.
:
lb
27
:
:
: Y l .
... ...
... ... ... i. . I .I .I ALTITUDE HOLD MODE I N P L i l :
. :
. : : . 5 3 .. ...
.. .. .. .. .. .. .. ALTITUDE W L D MODE (SENSOR)
ALTITUDE HOLD MODE : : 97-27
: : 1'9-39
:
: .. .
.
.. ... ... ; .. .. I ..I .I. ALTITUDE INTERLOCK : : : : : 3 9 . .
. . .. . .
..
. . - .-
ALTITUDE INTERLOCK : : Yb-39 :
... .. .. ..
.-
.. . . ALTITUDE OFF : : -8
$ 33 .. .
.. ... ... . . .
. . . GS Clu Y'1
. . 39 '15 3'1 :
. Yb
. ... ....
. .. .. .. . . . . .. .. .. .. .. .. .
.. ... ... ... .. .
115 VAC POVER 3b
..
.
..
.
..
.. .. .. ..
AC GROUt.0
.. .. .. .. ... ... 37 __t_ GRD

.. ..
:
. ... ... ... ... ...
39 : : Y3 ALTITUDE GAIN OiAlrGE EXCITATION
. .:
.. ... ... ... ..
.
..
.
..
. .. . . . . .
Y2
93
:
..
YY
Lis
ALTITUDE G A I h WANGE NO. 1
ALTITUDE G A I h CHNiGE hC. 2 . .
.. .. .. .. .. .. .. .. .. . .
..
7 :
.. ..: .:. ..: ..: MARKQ:
... . .
.. ... .. ... .. .. .. BCN :
... ...
.. ... ... .. ... ... ... : : : : : : R E C V :
.. ... .. .. ...
...
: :
.. .. . . . .: :
. v 3. :
. . . Y
..
.. ... ... .. .. .. .. . .
.. .. .. . . . . 115 VAC HEADING PWR :
55-55 : :
-0 , : c
... ..
. . .
... ... ... ... 1 1 5 VAC ATTITUDE PWR :
5b-5b
: E : : :
... .." ... .. .. .. 115 VAC COMAND PWR b 5 .
U . . . .
@ - . e GRD GROUND : N
.
.
.
.
.
.. ..
.
.. .. ..
115 VAC RUNWAY PWR
I15 VAC PWR COM
5 b .
57 57
.. - -
. . . .
.
.. . :T: .. 57 : : : GRD A
: b l 28 VDC POWER
RUDDER SERVO POiER :
:E:
P
S
.. .. ..
~

; ----
b3 : RUDDER SERVO POWER :
*' .. .. T
.. .: .: : : : Y1- 3c GROU?ID : l-f-1-2b : GRD
.. ... ... e-lb-
g : : :
28 VDC POkER P
2 5 VVC POVER (REG)
25 AILEROt. SERVO POWER
AILEROh SERVO POWER
: 2'1 : : : 19- 5 VAClDC LIGATING ELEVATOR SERVO POWER k'
:
...
25
.
...
:
.
...
:
:
: 20-
: '15-
5 VAClDC COM
SPEED COMMAND DEV + FAST IIIGH LEVE
ELEVATofS SERVO POIIER
.. .. 2 0 . X

. : : '17- SPEED COMMAND DEV + SLOW COM .. ...

.. .. .. : : 35- SPEED COhMAND FLAG HIGH LEVEL + .
. .
.. .. .. : : 99- SPEED COWWND FLAG COvl . .
: GA: .. .. .. .. GO AROUIiD MOh + :
: SUTTON
:
: .. .. .. .. GO AROUND MODE + ROLL
TRIM
ILIA-IA :
COUPLER :
: L :: . . . . GO AROUND MODE + PITCH
:II I : - : . . . GO AROUND EXC
.. (J1) :
. .. ~~.
.
- .. .~ .. ~ .. ~ .
GO AROUND ACTUATE : : : : .
. 2 Y. .. TRIM ENGAGE VOLTAGc - 21) : L
.. . .. .. .. .. EXTERNAL STEER + DOWN
; TRIM EI.GAGt GROdIiD 32 : M
.. .. ... .. .. .. .... EXTERhiAL STEER + up j $ 7 ; :. .: .
.
.
. .
.
.
.
.. .. .. . . .
.. .. ..
GYRO MODE : : : Lil-20 :
. ..
. .
.. .. .. .. .. .. .. HEADING MODE
i r l t MODE
:
:
:
:
: Y7-221
: 'tb-22
:
.
YO
b'1
:
:
. .
.. ..
.. ..
...
...
L
K
. .
:
:
:
:
..
:
:
APPROACH MODE
GYRO MODE
HEADING MODE
: : Li5-23
:
: :
:
:
..
:
:
.
2 0
2 1
:

: h
-
. .
: '17
Yil
. x+ 115 VAC POW&
:
:
6 :
:
:
IhDICATOR
TRIK
327D-1W
:
:

. .. . .
.. . ... J : : : N l L MODE : :
..
: : .
:.
2 2
:
. .
1 :
.. .. .. H
.. .. : ..: ..: APPROACH MODE : : :
. . . 2 3
. GRD
: 3 3 4 -
GROUND
TRIM IIIPUT LP - 11 _yvI_ +
.. . . . . ... . . . . .
.. ..
.. ..
. ...
..
.. .. .. . ... ... ... ... ... : 3 4 - TaIR! I l P U T dP + 1 3 v - E
i
.. .. ..
33 :
. . ... .. .. .. .. .. 3Li :
AILEROh
AILEhO.'. TKI!6
X I Y Il.;ICATCS
II.>ICATOK =:A@
..
. . . .. . . . . . .
... ... .. ... ... ...
.. .. .. .. .. .. .. 52
53 :
RUDDER T21.'8, 1IiC:CATOk
RUDDEF. T R V Ih5;CATOA
. ... ...
... ... ... ... h / L ARM -
... .. .. . . .
.. N/L CAPTURE -
:
:
:
:
:
:
b-32
39-3'1
:
:
:
:
35-8-
3b-8-
.. . . .. . GS ARM - : : b-3b : . .
. . . . . . . GS CAPTURE - .. ..
... ... ... .. .. .. .. GS EXTENSIOli -
: : 8-37 :
. .
...-
.. ..- .-.
. .
.. .. .. ..
. . . .
GO AROUND -
N l L ARM Ai<hUhICATOR +
:
:
.
:
:
:
92-38
lb-33
:
: .
.
.
.
..
: : : 3 7
. . l i l L CAPTURE AhllUNCIATOR + : : : : : 3 8 . .
P
- - . . . . GS ARY ASNUIIIICATOR + . : : : : * I @ ; . .
GS CAPTURE AIINUI~CIATOR+ : : : . : Y 2
. . . . . . GS EXTEl6IOIU AIhUNCIATOR + . : : : : Y 3 .. ..
.. . .. . : : : 3 Y GO AROUND AIdNUIvCIATOR : : : : : w . . ..
...
. .
.. .. .. .. ..
ALTITUDE ANNUNCIATOR
LACK COURSE AI.NUNCIATOR +
.
.
:
:
:
.
:
.
: Y o
. . . ....
.
.
..
. Y 5
.. . .
.. ... ... ... ... ... AIIIIUNCIATOR GUS : : : : 19. :
.. .. .. .
..
...
. ..
..
..
. ... ... ... 99 -
-
OUT OF VIEV C I A 8
TC RATE
2
:
0 :
:
:
:
:
:
I 3 b
: : .
.. .
..
... . .. .. ... ... 50
- ,+X : : : : : : ..
..
..
..
... ... .
.. .. ..
51 RATE OF TURV FLAG +
- RATE OF TURN FLAG -
SEliSOR .
.. :
.. ..
: :
..
:
.. ..
:
. . .. ..
... ... ... ... . . 52
. ... ... : : 1 5 : . . : 59 . .
. :
.
:
:
1 9
4
.
:
:
1 :
: 5':
- ' :
. 18
19 ... .
..
. . :7 : ... ...
i Q Y 0
: . 3
' 1 9 .

5 :
; ;: :I :l. :
;7 :
25
2b
27
.. ..
: : 2 5 : : : ZL : 28 ... ...
: : I D : : : : 57
. .
.:. .:. :
: 1 9
: 2 9
:
.
: sv 18
: bo
: EXT ROLL STEERI~G A . .
: : : 9 : : SA 19 : EXT ROLL STEER1l.G 5 ... ...
.. ..
:
.. :Q:s
.. 35
i i:
:
sv 25
SA 2 b
sv 35
:
:
:
PROCESSEi 3AIJi: CRP A
PROCESSEL 6AIdK CNP B
PRCCESSE; YAlrK jATA A
.
.
.
.
.. .. : 2 5 : : SA 3b : PROCESSEC BAliK 3ATA 5 . .
: : : I ? : : SV 5'1 : EXT IIAliK CY,D A .. ...
.. .. : 7 : : SI 55 :
~~

EXT DAhK CN2 5 .

. : : 1 i . : 57 : INTERNAL ROLL STEERIhG OFF t : :

AP-103F/FD-l09G Falcon (3-Axis), Interconnecting Wiring Diagram (Sheet 3 of 4)

Figure 459
May 1/67 22 -03-00
Pages 401/139, 401/140
 COLLINS
MAIYTENANCE
MAYUUAL

FLIGHT
WNUN- COURSE P E D E n A L DIRECTOR INSTRUMNT FLIGHT MODE AUTOPILOT EMRGENCY
C I A T M INDICATOR CONTROLLER INDICATOR WIRE FUNCTION M L I F I E R COMPUTER COWLER MISC MISC POWER AWLIFIER WIRE FUKCTIOh MIS MISC DISCONNECT
@ 331h-M LlYE-ZG 3298-80 39YC-lF 5b2A-5G IblE-1
J1A J1E 121A-2
J1A J l S J1A J16
J1 J2 J1 J l JZ 53 (TP) (Bp) (TP) (BP) (TP) (BP)
.. .. ..
. . . A : : :
... .. .. 3 : : :
... .... .... c
D
.
:
:
:
:
:
.. . . E . : :
.. ... ... I. : . :
.. .. .. G : : :
.. ... ... . . . . .
.. .. .. P : : .
... ... ... s . : :
... ... ... 1 : : :
.. . . . . . .
.. ... ... x : : :
.. . .. .. ..
. .. . z . . .
.. .. ... a . : :
.. .. .. b . : I
.. .. .. c : : .
.. .. .. d . : .
.. .. .. f . : :
.. .. .. p : : .
q . : :
.. .. .. . : :
... ... ...
r
5 : : :
.. .. .. t : : :
... .. .. u : : :
.. .. .. v
w
. : :
: : :
.. . . . : :
..
..
... ...
. .
M
x : : : .. .. .. .. .. .. : 53 - YAW DAMPER EhGAGE Wh + . .
... ... ... . . . : 9 : : I
.. ..
SPARE
... ... ... .. .. I :
i. i_ I.
..
.. ... ...
!
..
.. ... ... ... .. .. .. . . . . . ..... ..
...
.. .. .. .. .. .. .. .. ... ... ... ... ... ..
.
..
. .. . : YAW D A W SW
.. ... ... . .. .. .. .. .. .. .. .. .. ... ....
..
..
..
... ...
.. ..
..
...
..
.
..
..
..
..
. .
..
..
..
..
...
...
.
...
...
.
...
...
.
...
... ...
. .
... ...
.
.
..
.
.
.. . .
w
. . . . . .
m.
REVISION A - 9.
POWER LEADS DENOTED BY "DIM*# Y~WD E TE
IC TO COCKPIT LIGHT DM
IN
IG

SEI6ING U N I T 345A-'t( ) M D RATE GYRO 33%-2 SHOULC BE LOCATED A s CLOSE TOGETHER AS POSSIBLE.
CIRCUITS.

RUN GA AhNUN TO 3298-8G J3-39. 10. ANNUNCIATION VARIES WITH WE PiRTICULAR IhSTALLATION. I h THIS INTERCONNECT ANNUNCIATION I S
CORRECT DISENGAGE 5b2C-Y TP-b? TO SP-h?. 2 8 VDCi OTHER OPTIONS M Y BE PFOVIDED.
CORRECT N I L SbZC-'k TP-Y? TO Bp-4).
115V POWER CORRECTED k TO bl9E-2( ) ; J1-D 11. THE 5b2C-Y AI4D 5b2A-5G SHOULC LE MOUivTED AS CLOSE TOGETHER AS POSSIBLE, PREFERABLY ON A DUAL
AND 59DA-38; J l - 3 6 TO b. M3UNT. THESE SIGNAL LEADS MUS1 BE TWISTED AND WIRED POINT TO POINT BEWEEN THE UNITS. THE
CORRECT NOTE b FOR LOADING EFFECTS TRL11-25-bb TWISTED PAIRS SHOULD BE KEPT A! M O R T AS PRACTICAL MID W S T BE SHIELDED I F OVER TWO FEET LONG.

REVISION B - 12. TOTAL WIRE RUN FROM BUSS TO 12;A-2 TO 5b2C-+ TO 334C-3 ( P I N 0 ) FOR EACH PRIMARY SERVO MUST NOT
EXCEED 95 FEET I F AWG 20 YRE IS USEi. VHEli GREATER THAN 95 FEET, INSTALL TERMINALS AT 5b2C-Y
CHANGE NOTE 1 2 TO Y 5 FEET INSTEAD OF 90 FEET. TRL2-1Y-b? WUNT AN$ KUIl AWG 20 WIRE FROM 5b2C-Y TO TERMINAL 39YC-3 P I N 3.

SYhBOLS USED: 13. POWER FROM A PARTICULAR CIRCUIi BREAKER OR FUSY ,MY PROVIDE POWER FOR WRE THAN OflE EPUIPMENT.
THIS WILL BE INDICATED IN TIC ?KTERCOhflECT POWER C O L W BY A LETTER WITH AN OCTAGOh SYWOL AROUNC
SI W I S T E D SHIELDED PAIR-ADJACEhT I T . CAPITAL LETTERS FOR DC PirC LOWER CASE LETTERS FOR At.
SA WIRES AS SHOWN ON DRAWING
SG SHIELD TIED TO GROUND AT UNIT A, B I CI D. G
- -2 8 vC.C 5 MlF -
a, b , m m v WOHZ 1w
- WAC D I M -R
51 SINGLE SHIELDED WIRE t znvcc ANW DIMER C, d, e, f , h 11% Y O 0 HZ 2A,W
X I ALL SI SHIELDED TIEC TO X 1 ETC. F - 28VDC PANEL LIGHTS
STY FOUR WIRES W I S T E D WITH SHIELC
0 NOTES
-
i 2tlVDC 2 M P k - 115V LIOOHZ 3AMp

1 9 1 WIT4 TiiiM IirDiCATGR CO:!tlcCiiOh: AS SHOWh A h 0 THE REVERSING LINKS INSTALLED FOR CORRECT SERVO
NOTES: PdASING, TiiE PRIMARY SERVO CAPlTAlr SHOULD TURN CLOCKWISE WHEN VIEWED FROM THE CAPSTAN
END &DER THE FOLLOWING AIRCRAI'T ATTITUDES:
1. REFER TO THE INDIVIDUAL INSTALLATIOR W U A L S FOR COWLETE INSTALLATIOh INFORVATION.
AILERON - RIGHT BANK

--
2. SPEED DISPLAY I S COVERED BY A REMOVABLE MASK. ELEVATOR PITCH UP
RUODER RIGHT YAW
3. ALL WIRE SIZES,ARE NO. 22 LlNLESS DESIGNATED OTHERWISE BY NUMBERS I K SQUARES. SHIELDED WIRES PjlE GROUIIDE? AT ONE END ONLY.
15. YAir DAMPER SWITCrI AIC bACK OISUISE SYITCri ARE SOLZIIOID HELD MICROSWITCIIES bET1-T AND SETI-T
'k. SHIELDS ON THE NAV RESOLVER LEADS FROW, THE 1hAVIGATION RECEIVER SHOULD 5E GROUNDED AT THE SlRV-1. 0:. EOUIVALEIiT RESPECTIVELY.

5. FOUR WIRES W I S T E D WITH SHIELD FOR C O W A T I B I L I T Y I N FUTURE ARINC INSTALLATIONS. lii. THE GA 6UTTOI.l WILL 1:ORMALLY JE LOCATES. 01: TAE COhTROL WHEEL.

b. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED 114 THIS DRAWIhiG REFLECTS LOADS AS FOLLOWS: l?. OPTIOI*AL CROSSOVER SWITCtiI:.G 01: STEERING I:uFOREWTION MAY BE PROVIDED BY USING ALTERNATE
YIR1I.G AS SHOW. I t s C0LL:I.S Dr4A:II.G 7?2-4523-001.
AFCS LOAD CIRCUIT REQUIREC LOAD ALUITIO1.AL LOADS
18. ALTITLIDE TRIP POlNT I S INORMALLY ACJUSTE3 TO 20: FEET W T A DIFFERENT TRIP POINT MAY BE SELECTED
200 OHMS TO-FROM 100 OHMS JUMPER BP-43 TO 8P-33 OF 5lRV-1 I F ZESIRED. CONSULT AL-101 SY jTE:' ~AII.ITENA'lCE LU1:UAL FOR SPECIFIC ADJUSTMEliT PROCEWRES AND FOR
500 oms GLIDE SLOPE POIhlTEY 2OC OhMS JUM'ER TP-8 TO TP-2 A1.D TP-3 OF 51RV-1 ALTiTJDE TRIP W R I h G INFORMATION.
500 OHMS GLIDE SLOPE FLAG 25G OHMS JUMPER TP-21 TO TP-2b OF SIRV-1
1 0 0 0 OHMS LOC FLAG 250 OHMS JUWER w - 3 2 TO ~ ~ - 4TO1 ~ ~ - 3OF 1 5 i a v - i
1000 OHMS COLRSE BAR 200 011m uwia BP-39 TO bP-99 OF siav-1

?. THE POWER FOR THE COMPASS SYSTEM MUST BE OF THE SMlE PHASE AS TiiE R E S T OF THE AUiOMATiC FLIGHT C O h i W L SYSTEM.

AP-103F/FD-l09G Falcon (3-Axis), Interconnecting Wiring Diagram (Sheet 4 of 4)

Figure 459

May 1/67 22 -03 -00

Pages 401/141,401/142
 a
COLLINS
MAINTENANCE
ww MANUAL

?72-Y52b401
YRVOS
FLIGHT ALITWILOT EMRCENCY
UINUI- COURSE PEDESTU DIRECTOR INSTRUMNT FLIGHT MODE MLIFIER WIRE FUNCTION AILERON MISC DISCONNECT
CIATOY INDICATOR CONTROLLER INDICATOR WIRE FUNCTION MLIFIER COWUTER COWLER MISC MISC POWER
SbPC4 33%-3 121A-2
@ 33lA-bA bIYE-2F 32-G 3YYC-IF 5b2A-50 IblE-1 J1 J1 J1 J2
J U JIB JIA JIB J l A JIB (TP) (W)
J1 52 J1 J I 52 J3 (Tp) (BPI (Tp) (BPI (TP) ( W )

*E AILERON FIELD N M E R I - :

-
A
t 28 wc
.. .. .-
bz
- B :

..... ... ..-

52 : : PITCH A T T I T M E MON H : a 8 : : : : AILERON FIELD N W E R 2 C :
.. .. -?-b
7-b
PITCH ATTITUDE EFfWR H '
PITCH ATTITUDE ERROR C'
: 2 2
21
:
:
:
:
:
:
:
:
13 --tdt AILERON
1Y AILERON
SIGNAL C
EXCITATIOll C--
E
F
:
:
.... .... .... -8 PITCH ATTITUDE SERVO DRIVE M2 _C 2b : : : : 15 : AILERON
-
POSITION EXCITATION H G :
SERVO rnm
-
-
-9 PITCH ATTITWE 52- t - - - -c : : : : l b-
k AILERON RATE EXCITATION H H :
.. .. .. 10 : .5?- PITCH A D I T W E RATE GO . 2 3 : : : : + I2 AILERON . POSITION S I G N U L :

.....
..
.. ..
....
.-.
..
....
.-.
I1 W
25

--
2Y -&-

22
21 w
-
e
:

. .
:5e
b PITCH ATTITUDE RATE C2-
BANK ATTITUDE RATE C2
B M ATTITUDE RATE GZ
BW( ATTITUDE SERVO cum c
RANK ATTITUDE SERVO W I V E M I
B W K A T T I W E EmOR C'
-
-
: 3 *
33
2Y

35
3b
31
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
11
...
17

.
:

...
AILERON
5 t AILERON
..
..
.
...
SERVO CRD
RATE SIGN4L -.. R
S :
. ...
.-. ...
:

.. .. .. : : : :
-.. ...

--
20 -b B M ATTITUDE ERROR H'-X AILEROII ENGAGE VOLTAGE : A E

.. ..
5Y -cr- : :
... ... F

-
BANK ATTITUDE KXI H . 3 8 : : AILERON ENGAGE MLTAGE : B
... .
..
..
. 32 : : "
: 1:
2 b VAC ATTITUDE PWR .. 5 531 : : : : VERTQI I
... ..
.....
33 Bb VAC PdR COM : : : : REF :
: : 33- GYRO HIGH LEVEL FLAG + ... :
. .. .... - 29 10 : : 332D-11 : ELEVATOR

.... . . . .
: 18 GYRO HIGH LEVEL FLAG 30 : : : : Jl : 33YC-3

..
-
..
GYRO MQN + : Y o : : -. . N :
i bq$z - (J1) ( 5 2 ) :

-
3 : .: PITCH A T T I T W E CT X : I O : . : A : ELEVATOR FIELO N W E R 1 A :
.. .... ...- *-5 .-. -.. -
: . 28MC 0 :
... : I:
PITCH A T T I N U E CT Y
PITCH A T T I T W E CT Z . . E .o .
. 0
c
:
: : + $ 1 ELEVATOR FIELD N W E R 2 C :

.. ..
. ..- I?
I8
: :.: BANK ATTITUDE CT X
B M ATTITUDE CT Y .
: 3 0 ;
:
:
.
D : :
: -
-
13-t
1Y
ELEVATOR
EL5VATOR
SIGNU C
EXCITATION C - E
F
:
:

-
: 2 0 E :
.. .. ...
19
. . . BANK ATTITWE CT Z .. .. .. .. .. ... : 15 ELEVATDR
-
POSITION EXCITATION- G :

... ... .. .. .. .. 115 VAC POWER

AC G?OUND ... .
..
.
..
.
..
.
.. .. H-
:
:
lb++
E-+
ELEVATOR
ELEVATOR -
RATE EXCITATION H
POSITION SIGNAL
H
L
:
:
.
12
.. . .. .
PITCH ATTITUDE X (BOOTSTRAP)
PITCH ATTITUOE Y IDCOTSTRAP)
:
. : : : :
: ; :
.
53
54
:
:
..
Il-x2--
I?-+
.
ELEVATOR
ELEVATOR
SEW0 GRD
RATE SIGNAL -S.. R
.
:
:
.... ..-- ..-..
-
PITCH ATTITUDE Z ( B O O T S W ) : 55
.. .. .
._
PITCH C W N D H '
. .. 36-15
: : ...
15 : :
PITCH C W O C'
2 b VAC A T T I T W E POWER
2b-lb
: 53-5
:
.. .. . .
. . : 51 .. ..

--
I b : : 2 b VAC WR COM 2? ELEVATOR ENGAGE VOLTAGE : A J
..... .: 5-31. . .: 30. :. .. ELEVATOR ENGAGE VOLTAGE
..
:
..
B H
PITCH STEER + UP
.... .... .. ...
PITCH STEER + W Y N
ROLL STEER + LEFT
: Y-221 :
.. .. ... ... ...
-
10 31
.. .. ..- -
....-
ROLL STEER + RIGHT 11 21
.. .. .. ...
. . . . V-BAR ROLL POS mTR 2 58 : :
... ...
: : V-BAR ROLL POS XNTR x : :
... ... ..
-
3Y : b O
V-SAR ROLL COWUND SERVO DRIVE M2 +b 2 .. ..
... ..
- : :
.. ..
3b
: : .. ..
.. . ...
37 V 4 A R ROLL COWUKD SERVO W I V E C- b3 : :
38 : :5 e V-BAFI ROLL COUU4NO RATE G2 b l : :
... ... ..
.. .. .~.
. ..
.. ..
39 : :5 6 V..I)AR ROLL COWND SG I COM
- 59 : :
...
- .. . ..
: :s e
95 V-OAR PITCH C O W N D SIG COM 59
- : : :
.. . .
. ...
YY : :; V-BAR PITCH C W D RATE 0 2 b2
.... : : :
.. .. .....
.-.
: : :
..
-
Y3 V-BAR PITCH CGWAND SERVO DRIVE C bY : :
+2 V4AR PITCH C O W D SERVO DRIVE M2b3 : .. : :
.. ... ..
..
.. .. .. .. .. .. ..*I ..: .:. V-BAR
XMTR z . . .: :. . .
PITCH POWOFF-SCALE B I A S - b l :
.. ...
: YO V-BAR PITCH POS XMTR X - : . . . .
b o . .
RUDDER
33YC-3
. . .
.. .. ..
:
:
Y8
:
: : ?
: 39-h
Zb VAC COMMND PYR

-
2b VAC COhWAND P M COM-
b ?
59
:
:
:
:
:
:
:
: :
:
E= RUDDER FIELD W m € R I - ( J l ) (52)
A :
:

..
-
.. .. wc
.. . . .:. ..: ..Y- .. S E E R FLAG . b Y : : : : b i 28
- 9 :

-
..~. PITCH CODPUTER MON + : : 12- 12 : : NAY k V U 0;: 4 1 + RUDDER FIELD NUMLIER 2 C :
. . . : : 3- STEER FLAG + . . : 38 : : 51RV-1 Y3 . 5+ RUDDER SIGtlAL C E :

- -
: : : :
: 33 : : ID
CCWAND SERVO MONITOR
GLIDE SLOPE DEV + UP
: b5
: 3 2
28
:
:
:
:
:
(TP)
8 ($ YY . RUDDER
RUDDER
EXCITATIOI: C

-
POSITION EXCITATION It
F
G
:
:
:
:
:
39
35
:
:
:
;
: I1
: 12
: 13
GLIDE SLOPE OEV + WWN
G L I M SLOPE LOU LEVEL FLAG +
-
:
.
:
.
. . .
2 2
:
:
:
:
:
. .
:
;
9
21
.
:
Yb
Y2
91
:
:
I
5+
5+
"-
RUDDER
RUDDER
RUDDER
POSITIOL SIGNAL
SERVO GRD
-
RATE EXCITATIM: H H

R
L
:
:
:
.. ..
3b
.:. GLIDE SLOPE LOU LEVEL FLAG
GLIDE SLOPE HIGH LEVEL FLAG +
22 :
. .. .. :
... : :
... ... :
... :
.
. . 11. .:
:
.: .: 2? : 47
..
:
..
5+ RlDDER RATE SIGNAI.
.5 :
.
. . .. ... ... ... ... ... .. ... RUDDER ENGAGE VOLTAGE I ; B
i. I. . .: .: sT+
. MLRSE RSVR A . . . . . . l b .. .. RUDDER ENGAGE VOLTAGE :
.. D
.. C
. . : : : : : : (BPI . ...
. . . . . . .. ... .
..-
. T + MLRSE RSVR B 22

(3:-9 .: .
.T't
T+
COLRSE RSVR C
COURSE RSVR H ... ... ... ... ... 23
21
....
.
... ...
..
..
..
: : :5?- COLRSE RSVR D
.. . .
2Y
..
5
- b
: : : 5 6 COLRSE RSVR E
.5- COURSE RSVR F .
. -
. . .
25
2b ... .. ... ....
5 - 7
2b :
b COLRSE RSVR G
TO -
FROM + TO
.. .. .. .. . . . . 2?
93 .. . ..
.. . .
.
2) . TO -
FROM + FROM . . . . . YY .. .. ... ...
31
2
:
:
VORlLOC LOU LEVEL FLAG
VORlLOC LOW LEVEL FLAG
+
- .. .. .. .. .. .. Y1
112 .
.. .
.. . .-
29
28
:
:
.
..
. . .
.. .. ..
VORlLOC DEV + LEFT +
VORlLOC DEV + RIGUT
.: .
.
:
:
:
:
:
:
11-YO ..
..
.
...
. .
. .

--
10-339
.. .. .. . ..
... ... .... VOWLOC DEV LEFT + 7-32-11 : . .
.. .. VOHlLOC DCV + RIGllT .. .. . .
.. .... .. ..
8-22-lD :
. .
.. . .
. . ..
. ... .
..
.
..
VORlLOC H I LtVEL FLAG
LOC FREPUEhCY
28VDC NAV REC POWER
l?-ll
YD
. . . Y3
.
:
. . -3?38 -
19
: 5u

- TO NAV
REC PUR TPI-2831-044

A P - 1 0 3 F / F D - l 0 9 G King A i r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 1 of 4)
F i g u r e 460

Nov 1/68 22 -03 -00

Pages 401/143, 401/144
 a
COLLINS
MAINTENANCE
MASUAL

-
FLIGKT
Wuc COWS€ PEDESTK DIRECTOR INSTRUEWT FLIQlT mDE SERVOS
CIATOR INDICATOR COWTROLLER 1)LDICATQI YCLIFIER C
R
- COtRER MY ULSC FWER AUTOPILOT EMERGENCY
AWLIFIER WIRE N t CTIOII A I L t RON MISC DISCONNECT
IO 33- b l - 3 3 m l F 562- IblE-1
J U JlB 33YC-3 lE1A-2
J U JlB J U JlB
JI 52
J 1 J2 J1 JI J2 J3 ITP) (Bp) (TP) ( W ) (TP) (e+)
NAV RCVR
5lRV-1
..... ... .. .. ... ... (TP)
.. .. .. ..
.. . .. .. . . VOR SELF TEST DISABLE :
.. :
.. ..: ..: : 1 - 19 NAV CONT :
.. ... . .. ..
.
. .. ,.
. .. .. .. ... VOR SELF TEST DISABLE
.. .. .. ..
: 15-
- 5Y 3135-3 :
.. ... ...
: SACK: :
.. .. .. ..
VOR SELF TEST DISA5LE
VOR SELF TEST DISABLE : : : :
: +a
: Y s
55
:
(52)
K Q :
:
.. .
..
: COURSE : : : : : .. .. : :
.. .. .. ..
VOR SELF TEST DISABLE : l b - n AIRSPEED
.. ... : : SENSOR
.. ... ... ...
VOR SELF TEST DISABLE
BACK COWLSE WDE INPUT
:
:
..
:
:
:
:
.. .. .. ..
:
:
: B : L :
..
..
: 1 3 : : 5908-2
. .. : : J1
.. .. .. . B A U I COURSE IIITERLOCK : : : I 1 2 59 : AIRSPEEO SIGNAL . .
. .
.. .. .. .
. ... BACK COLRSE EXC . . . . . 58 : AIHSPEED EXCITATIOII H
.. .. ..
. .
...
.
... ...
BACK COLRSE MODE :
:
:
:
:
:
29-25
: :
:
: .
~~

8b(lE-ZV
bD
..
:
...
AIRSPEED EXCITATIOX C
..
.. ..
..
. . : : : : : (J1) :
~~~~

.. . .. ..
. . . . . . . .. ...
-
6C
DISTANCESHUTTER I 9
.- . . . . . DISTANCESHUTTER . 10 . . . . .
-... .
...
DISTANCERECEIVERS 2bVAC HOT : : : : : : 2
: : :
DISTAlICE
RECEIVERS ZbVAC GRD : : I
.. 1
.. .. .. .. .. ..
-- .- . . . . DISTANCE
DISTANCE
RECEIVERS Z COhWN
RECEIVER UNITS X . . . . . . 4 .. ....
91
. . . . DISTANCERECEIVER UNITS Y . 3 . . . . . ... ..
__ -.: . . . . .
DISTANCERECEIVER TENS X b . . . . . . ... ... ...
. .
93
. . . . DISTANCERECEIVER TENS Y p . 5 . . .
SY .- .- . ... ... .. .
...
DISTANCERECEIVER HUNDREDS X I : : - 7
-. .:.
55 ... .
...
.
...
.
... DISTANCERECEIVER HUNDREDS Y : : : : : I
.. 8
.. .. .. .. ..
... : : COMPASS 0 .. .. . .
.. .. ... ... ... .. .. ... ..
.. .. .. ...
: : : : : : 328A-2A
. . .
..
: : (J1) (52)
9-1
: I? -
- ..
I .: .: .. COWASS HEADING X
i. : . i. i . i . i . :. . ?. ...
. ..- .. .
....
- :. .. : ..: ..: . . .. .. .. . . . 3. .. .... ...
...
10-2 COMPASS HEADING Y s
: 18J . . . . . . . . . .. .. ..
7
... :.. .:. :.. .. :. .. .
.: ...
11-3 : : : : C W A S S HEADING Z Y
: 19- :
.. .. : ..: .:. .. .. .
....
.. .. ..
. .
.. .. .. .. .. .. 115 VAC POWER . . . .
.. ... ..
..
... ... ..
. ... ... ...
28VDC POWER
GROUhD
:
:
:
:
:
:
:
:
:
:
:
:
2b
2 7 : . .
: 5 . . . . COMPASS MONITOR + : 39-1Iy-225 : : . . ... ...
.. HEADING DATUM H' : : : : b 11 : : : Y9 COMPASS DATA X
.. ..
....
: Y
.... .. .... .... .... HEADING DATUM C' .. .:
. .
: : I ?
.
Y : : . 50 CSMPASS DATA Y
.. ...
. . ..
13
. .
:
.
. ..
:
...
:
.
..
I
HEADING DATUM H '
HEADING DATUM C'
HEWING DATUM LOAD RES (1OK)
COURSE DATUM n'
:
:
: :
:
:
:
:
:
.
33-b
l :
:
a - ? I?
] ;
: 9
:
3

.; I
: ;
. I
I

..
.
51

.
..
COWASS DATA Z

PILOTS
. ..
COPILOTS
.. :..
12 . . : : COURSE DATUM C' . : : : : 8 .. .. DISENGAGE DISENGAGE
. .
: : : : COUilSE D A T W H'
.. .:.
: : 3Y-q
i .. .. BUTTON 3UTrON

..
:
.
.. ... .:..
.: 1 COURSE D A T W C'
COURSE DATUM LOAD HES (10K) .. .. :
: : 1 s : : bb - AUTOPILOT DISENGAGE
COMPASS LOW LEVEL FLAG + .
30
. . . - : Y, ? : : 5
..
b?
..
-
BY COMPASS FLAG : I 1 : : 1 3 : AUTOPILOT DISENGAGE
81 : : :s* AZIMUTH CARD ERROR CT H ' . 1 3 : : : : .. . -... ....
~.

- ..
: ::ts+ AZIMUTH CARD EmOR CT C' : : : :
20
13 : : :5+ AZIMUTH CARD RATE GZ
. 1 2
: 1 Y : : : : .
1Y
11 . . . .
. 5 6 AZIMUTH CARD RATE CB
AZIMUTH CARD SERVO DRIVE M I
: 1 5
l?
:
:
:
:
:
:
:
:
..
..
.
...
:
:
:
:
SENSING
UNIT
12 . . . . AZIMUTH CARD SERVO DRIVE C1- lb : : : :
.. ... : : 3Y5A-W Q
15 Bb VAC HEADING PYR . 5 2 : : : : . : : (ROLL)
lb 2b VAC POWER COM : S Y : : : : b5 . ROLL RATE IOTDR GRI . . A
:
:
:
:
:
: 1 0 4
:11+
: 1B+
RUNWAY LOC POS W T R X-
RUhYAY LOC WS XMTR Y - 2?
2 8 :
:
:
:
:
:
:
:
:
:
8
32
:
.
115 VAC POWER
ROLL RATE EXCITATICN C
.
.
.
.
B
E

.. .. .. ..
: RUNWAY LOC POS WTR Z- 22 : : : : : 31 : ROLL RATE EXCITATICN H F
: : RUNWAY LOC SERVO DRIVE M2- 2 3 : ..
: :
: 13-
:19- RUfNAY LDC SERVO D R I M C - 2 Y : : : : :
29
.
. .
ROLL PATE PGNAL X
. .
-
G

... ... :
:
:
:
:
:
: 1 5 4
: 1b-b-
RUNWAY LOC RATE G2
RUWAY LOC RATE CZ
-
2
2
b :
5 :
:
:
:
:
:
:
:
: : 8 -
- -
PITCH PATE IQTOR GRO
.I . . . . .L P. T T N I
. . A

..... ..... : :
: 5-
: Y-
RUIiWAY ALT SERVO DRIVE C
RUWAY ALT SERVO m x v E ~2 - 3Y
3 3 :
: :
:
:
:
:
:
:
:
:
:
10
P -
-
115 VAC WYER
PITCH RATE EXCITATION C . .
B

..~
. ..
:
:
:
:
:
:
?S+
b S b
RUWAY ALT RATE C2
RUfNAY U T RATE G2 3
3 5 :
b :
:
:
:
:
:
:
:
:
:
:
..
31
29
..
- PITCH RATE EXCITATION H
PITCH RATE SIGNAL X
-..~ .. G
.. .- :
.. ...
: : l+ RUWAY ALT POS M R X-38 : : : : :
... ....
. . . 2 -e RUNVAY ALTPOS XMTRY-3) : :
. .. .. . : : :
.
: : YAW RATE

... ...
c-.v...
... .. 3 - e RUWAY ALT POS XIlTR 2- 32 : .
! :
. m
. 8 4 I b VAC RUMWAY PWR 5 3 : : : : : . . : : 33262
.... .... .. .. 9-6.
- 2b VAC RWWAY PWR COM-
RUWAY FLAG +
51 : : : : : bb YAY RATE MOTOR GRD A

. . ...
.. 17
- - Y S : : : : : 1 RADIO ALTIMETER 10 :
.
115 VAC POWER
. .
B

..... .....
18 R W A Y FLAG : : : : 339;d ) YAW RATE EXCITATION C
... ... Y
:
8 :
: : : : :
OSbO;-l
(pmi :
51
50 : YAW RATE &CITATION H . .
. : ...
.... .... ~.
.. ...
RADIO A L T I M E +
RAUIO A L T I M E - 5
4
:
: : :
:
:
:
:
E2
23
:
:
Y8
..
.
YAW RATE SIGNAL X
..
.
~. .
..
.. G
.. .. ....
..- _ ~
RADIO ALTITUDE MONITOR +
... ... ... ... 37 -
- MDA LIGHT CONTKOL R
I Y : : : : : 12

. . . . i.
~

.. .. .... ...
. . .. 36
-
.... .... ... 38 hOA LIGHT EXCITATION . . ... ...
.-.
.
...
...
: :
... ...
A L T I M E EXT OVERRIDE : : * 1 :
. .
.. .. .. RWYAY SYMBOL 200 F T U T TRIP Yb : : : I : .. ..-
. . MIDDLE MRKER TRIP Y3-224 : : : . .
TPI-2831-044

AP-103F/FD-l09G King A i r , Interconnecting W i r i n g D i a g r a m (Sheet 2 of 4)

Figure 460

Nov 1/68 22-03-00

Pages 401/145, 401/146
 a
COLLINS
JIAINTESASCE
MANUAL

FLIGHT SERVOS
ANNUK- COWSE PEDESTU DIRECTOR II4STRUMENT FLIGHT MODE AUTOPILOT EMERGENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AAVLIFIER COM'UTER COWLI,R MISC MISC POWER MLIFIER WIRE FUNCTION AILERON MISC DISCONNECT

ID 331A-M blYE-ZF 3298-80 33YC-3 121A-2

JI J2
J1 J2 Jl J l J2 53
.. .... . . . . ... ...
.:. : : :
.... .... .... .... ....
: : A L T O :
..
.. .. ... .
...
.
...
.
.... .. SENSOR :
.. ..
..
. ...
... ...
590A-3E :
.. .. .. .. ALTITUDE ERROR H' : : 3 3 . : : :
. . . : : a . : :
Ib I Y1
... ..
.... ... v
ALTITUDE ERROR C'
..
27
..:. Y2
.. . ....
.: .:.
: : : ALTITUDE HOLD MODE INPUT : : : 5 0
.. . . . I
... .
....- .. ... ... ... ALTITUDE HOLD 14DE (SENSOR) : : YD-3Y :
.. ..
. ..
.. w
ALTITUDE IWLD MODE
. :
Y?--f-27
. :
:
... ....
... ...
... ... ... ...
: : : ALTITUDE INTERLOCK : 3 9
.... .... ... .
... .... . ..
.. ... ... ...
ALTITUDE INTERLOCK
ALTITUDE OFF
GS ON YY
:
:
... -
... ... - ...-
:
:

.. ..
+
Yb-

39
a
Y5
: :
39 :
.
3
.
33

...
..
: Yb
..
. ... .....-
. .
.
.
. ..
.
..
...
..
...
..
...
115 VAC POh'ER
AC GROUIID ..
.. . . . . . .. ..
... ...
. .
... ...
.
...
37
39
- : : Y3
. ALTITUDE GAIN CHANGE EXCITATION
..:
. .-
.:.
.. ..
.. .. .. .. .. .. .. .. ...
Y2 : : YY ALTITUDE GAIN CHANGE NO. 1
.. .. .
.. .. .. ....
Y3 : Y5 ALTITUDE GAIN CHANGE NO. 2
.. .. .. . . . .. :.. ..:
:
.. ..:
:
.:. NARKQI I ... .. ..
. . . .. . . BCli :
..
... ... ... ... .. .. :
:
: : : :
:
:
:
R E C V : .
...~ .. ... ...
.. .. .. ..
.. .. .. : .. + ..3 :
.. .. .. Y
.. ... ...
. . .. ...
.. ..
..... .. .. ... 115 VAC HEADING PWR
. .-
... ..
. .
.
.
.
. 115
115
VAC
VAC
ATTITUDE PWR
CO,WND PWR ....
.. . .
.. .. ... . .. ..
115 VAC
-..
RUMIAY PWR 28 VDC POWER
: w:. P

.. .
. .: -. . .. .. ..
115 VAC PWR COM
.. .. .. .. .. .. ..
RUWER SERVO POWER
RUDDER SERVO POWER :
:
.E S
T

... ... ...

-- .
:

-
:+1-

:
. . .
2Y
--- . . .
19
DC GiOUND
2 8 W C POWER
2 5 VDC POWER (REG)
.
:
1-1-2b

:
:
5Y-2Y
: : : 2 5
:
:
.
GRD
D C
bl
. .
: AILERON SERVO POWER
ELEVATOR I R V O POWER
v = i
....
:

...
.
..
..
.
..
25 -t-

..... - .
..
.....
20
: Y5
: Y7
: 35 -
-
SPEED COsWAND DEV + FAST HIGH LEVEL:
SPEED COW4AND M V L SLOW COM
SPEED COmAND FLAG HIGH LEVEL +
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:@
:
j
.. ..
ELEVATOR SERVO POWER .
...
... ...
20 X

... .. ..
: Y9 SPEED COM!AND FLAG COM
GO AROUND MON +
.. .
: GA: :
: BUTTON : .. .. .. GO AROUND MODE + ROLL ..
TRIM :
.A . .. .. GO ARDUIID MODE + PITCH . . .
SERVO
332C-2JIF
:

:
... ... .. I.... .~
..
..
.
.
...
..
.
...
GO .AROUND EXC
GO AROUND ACTUATE
EXTERNAL STEER + WWN .
.
..
.
.
.
:
.
:
.
29 ..
b

.
:
.
.. TRIX ENGAGE VOLTAGE
(J1)
D
:
: L

... .. .. .. . . EXTERhAL STEER + Up

2?-: :
. . :
.. .. TRIP1 Et:GAGE GROUND E . M

... ... ... ...

: : 37-:
. .. GYRO MODE : : : Y1-20 : YO :
.. .. .. .. .. .. HEADING MODE : : : Y7-221 :
.
bY :
. . . N I L MODE
. : : : Yb-22 Y? :
... ... ... APPROACH MOOE
GYRO MODE
, 1 :2 - : 5
. :
9
. : : 2 0 . 98
.
. . . . . . K A D I N G MODE . . : : - 2 1
.. .. 28 W C POWER i
_. .-.
.. . . . . . : . :
..... .....
N I L WDE : 2 2
.. .- .- APPROACH MDDE . : : : . 2 3 : GRD . . GROUtIU B
.. ELEVATOR TRIM INDICATOR . . . . . . : 33-+ rnm MOTOR C O ~ T R O L C
... . . . . . . . .
..... .....
ELEVATOR TRIM INDICATOR : 3y-Y- TRIM MOTOR CONTROL F

...
AILERON TRIM INDICATOR . . . . . . 33 :
AILERON TRIM INDICATOR . . . . . . 3Y :
. . . . . . . . .
... ... ... . . . RUDDER TRIM INDICATOR
RUDDER TRIM INDICATOR . . . . .
52
53
.
:
:
.
.. . .
..
..
...
..
...
..
:
:
:
:
:
:
NILMM-
N I L CAPTURE
-
- :
:
:
I
:
:
b-32
35-39
:
: .
...
.
...
..
..
.
...
.
...
:
:
:
:
:
:
:
:
GS APM
GS CAPTLRE -- :
:
:
:
b-3b
8-37
:
: .. ..
: : : : GS EXTENSION
- : : 92-3311 :
.. ...
...
-0 .-
.
:
-
: : :
:
:
:
:
GO AROUND
N I L ARM ANNUNICATOR +
b1IL CAPTWE AtIfIUlICIATOR + .
:
:
:
:
.
I : :
lb-33
:
.
.
.
. 3 7
:
... ..
'.. .
'* :
:
:
:
:
:
. :
: :
: GS ARM Al4UI4ICATOR +
GS CAPTURE ANNUIICIATOR +
.
: : : :
. 3 8
i Y l
: Y 2
@ i i ...
..
..
.
..
... .
'8 :
-
:
..
:
-
:
:
: :

. .: .: :.
-
: : :
: 34
GS EXTENS1014 WNUNCIATOR +
GO AROUND ANNUIJCIATOR
ALTITUDE ANNUNCIATOR
BACK COLHSE ANhiUNCIATOR +
.
:
:
:
:
:
:
:
:
. .
.
:
:
. Y 3
: Y Y
: Y o ....
...
...
..
.
...
..
' 0
.. .. : . 4 5
.. .. .. .
...
: : : : ANNUfrCIATOR BUS : : : : 1 9 :

... .. ..
: : : :
- OUT OF VIEW BIAS
PATE OF TURN DEV +
20 : : : . O b
.. ..
..
... ... ...
:
:
:
:
: 49
: 50 - RATE OF TURN DEV +
PATE OF TURN FLAG +
TO RATE :
OF TURN :
:
:
:
:
:
:
:
:
:
:
... ..
.. - -
: : SENSOR : : : :
.. ...
.
...
. :
. ... ... . :
: 51-
: 52 RATE OF TURN FLAG .. .. .. .:. .. :
.. . .-
. ... ..
..... .....
: : 1 5 : : : : 59 COWUTER MINT

.. . . . . : : 1 9 : : . I. . 18 E X l PITCH STEERING A
.. . . . : : q . : : : 19 EXT PITCH STEERING B
... ... . .. .
-'

.. .. .. .. 9 9 . . . 57 . 25 AC PITCH STEERIlJG A
. . .. .. .. ; @ ; ; : . .I :.
.... ....
: 2b AC PITCH STEERING B
... .. .. .. ..
-
2, : 2) PROCESSED PITCH DATA A
. . .
-c: PROCESSED PITCH IATA B
... .... .... . . : .: .: .
:
:
:
:
:
2
l a
5 :
: : :
28
57 INTERNAL PITCH STEERING OFF +
ALT HOLD OFF +
... . . .. .. .. .. : : : : a : bD

... ...
: .
.. . . . :
.. :
. : 1 9 SV IS : EXT ROLL STEERING A
.-
. .. .. .... .... .... . .. : 9 : : SI 19, : EXT ROLL STEERN
IG B

....
...
... ...
. . ..
...
.
...
.
...
.
.... .:.
. .
:q:;
.. 35
i: i:
. .
sv 25
S.3 2b
sv 35
:
:
:
PROCESSED 0ANK WP A
PROCESSED W K OV 0
PWCESSED BANK DATA A

.... .... ... : 2 5 S.3 3b : PROCESSED BANK DATA 3

.. . . . ..
: ..
: : 1 7 : . sv 5Y : ZXT BANK ccm A
. . .. . . . ..
. .. .. .. .. : ? . : 5.3 55 : EXT BANK CWJ B
: l a . : -57 : INTERNAL ROLL STEERIIIG OFF +
TPI-2811-044

AP-103F/FD-l09G King A i r , Interconnecting W i r i n g D i a g r a m (Sheet 3 of 4)

Fimre 460
Nov 1/68 22 -03-00
Pages 401/147, 401/148
 COLLINS
MAINTENANCE
MANUAL

FLIGHT SERVOS
NINUN- COURSE PEDESTAL DIRECTOR INSTRLUENT FLIGHT MODE A
AUTOPILOT
WLIFIER EMEROENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AMPLIFIER CWUTER COLPLER MISC MISC POWER WIRE N N C T m t l AILER0I.I MISC DISCONNECT
331A-b.4 LIYE-ZF 329B-EG 3YYC-lF 5b2A-5G IblE-1 5b2C-4 33YC-3 121A-Z
J I A JIB JIA JIB J I A JIB J1 J l J I 52
J l 52 J l J1 JZ J3 (TP) (Bp) (TP) (Bp) (TP) (BP) (TP) (BP)

.
.
.
.
A : : . PITCH CONTROL EXC A . . . . . . . 21 ... ...
. .
B : : : PITCH CONTROL SIGNAL . . . . . . . 20 ... ...
... ...
C I : : PITCH CONTROL EXC B
.. ..
.
..
.
...
. ..
..
. ..
.
22
.. .. ..
.... ....
D : : :
.. .. E : : : NRN miimoL EXC A . . . . . . ' 2 1 :
.. . F :
.
: : TURh CONTKOL EXC 9 . . . . . . 22 :
. . . . . . .... ....
f .

. G : : TURN CONTROL SIGI.AL 20 :

... ... N : : . I N T MOTOR CONTROL VOLTAGE . . . . . : b2
.. ... P : . : I H T 2bVAC MOTOR EXCITATION C : : f : : : 29 : .. ..
.. . : : . . . . . . . .
..... .....
R
.
.. .. S . f :
I N T MOTOR RATE SIGNAL
I N T WTOR SIGtlAL COIMOII . . . . . . :
:
b3
2Y
. . . . . . . .. .
..
T : : 2 8 M C PANEL LIGHT PWR
... ... . . . . . . . . -.. ...
. . x
U : : CROUND
. . . . . . ... .. . .
..... .....
: : : : , :
Y
z
.: :
:
:
:
ENGAGE VOLTAGE .
..
:.
. ..
: .
..
3
..
1
..
: .
..
.
.. -.. ...
. .
.. ..
.. ..
a ' : : : ENGAGE PULSE .
.
.
.
. . . .
. . . . : 5b ... ...
... ...
b : : : DISENGAGE VOLTAGE
. . . . . . : 3) .. ..
c :
. : :
: : ENGAGE READY
. . . . . . : 55 .. ..
-.. ...
d
.. .. f : : :
A L T I M E HOLD MODE + : 38

.... ....
HEADING S I K H CUTOUT 38 :

.. ..
p : : : 115 VAC AUTO PILOT P W i 7 - m !
. . f
. . . I.
! : a .. .. .. ..
.-~.
: @
- .-.
Y
q : : : 115 VAC POWER ? : ~.
. . r : : : I N T 2bVAC MOTOR EXCITATION H : : - .- . . 23 :
.. . .. .. .. .. .
+
- 5
. . ENGAGE INTERLOCK 5Y k
... ...
t
U
:
:
:
:
:
: AILERON CLUTCH VOLTAGE .. ... .. .. . .. : Q .
E
.
39.
.
. .
.
i
... ... v
W
:
:
:
:
:
:
ELEVATOR CLUTCH VOLTAGE
RUDDER CLUTCH VOLTAGE . . . . . . 39:
56 . . . 20 A
I
.~
... ...
. . M
x
:
:
:
:
:
:
+ 2 8 M C AUTO PILOT PWR
... ... ... ... ... ... - .. ..
I

.. .. Y : SPARE
... ... ... ... . ..
:
.
53
.
YAW DAMPER ENCAGE MON +
.~. .. I I t
..... .. .. ..
I

....
f : 9
... ..-
..._ ... . ... . ... ... ... .. ... ..
.. ....
... ....
.. .. .. . . . .. ... ... ...
.... .... ....
:
... ... ...
YAW DAMP SW

.... ....
. .
... ... .. . .-...
.. .. .- . .- .-. .. ...
... ... .
..
.. .. .. -. .. ..
.. .. .. ...
.
... ... ... ..
.
... ...
. . . . . . . . . . .. . . . -

IO. ANNUNCIATION VARIES w m THE PARTICULAR INSTALLATION. N

I mxs INTERCONNECT ANNUNCIATION IS
SYhBOLS USED: 2 8 WC; OTMR OPTIONS HAY BE PROVIDED.

11. THE 5b2C-Y AND 5b2A-SG SHOULD BE MOUNTED AS CLOSE TCGETHER AS POSSIBLE, PREFERABLY ON A DUAL
MNT. M E S E SIGNAL LEADS M I S T BE TYISTED AND WIRED POINT TO POINT BETYEEN THE UNITS. THE
TYISTED PAIRS WOULD BE KEPT AS WORT AS PRACTICAL AND MJST BE SHIELDED I F OVER TWO FEET LONG.

12. TOTAL W I F S RUN FRMn BUSS TO 121A-Z TO 5b2C-Y TO 3 3 9 6 3 ( P I N 8) FOR EACH P R I M M SERVO MJST NOT
EXCEED 90 FEET I F AWG 20 WIRE I S USED. W E N GREATER THAN 90 FEET. INSTALL T E M I N A L S AT 5b2C-Y
hYKNT AND R I N AWG 20 WIRE FROM Sb2C-Y TO TEFMNAL 3YYC-3 P I N 8 .

13. POWER FROM A PhQTICULhQ CIRCUIT BREAKER OR FUSE M Y PROVIDE POWER FOR MORE T H u l ONE EQUIPMENT-
ilOTES: THIS WILL BE INDICATED I N THE INTERCONNECT POWER COLWN BY A LETTER WITH AN OCTAGON SYMSOL AROUlD
I T . CAPITAL LETTERS FOR DC AND LOWER CASE LETTERS FOR AC.
1.
2.
REFER TO THE ItiCIVIDUAL IISTALLATION MAIJUALS FOR COKBLETE INSTALLATION INFORMATION.

SPEED DISPLAY I S MVERED BY A REMOVmLE M S K . --

A - 8, CI De Gr I - 28 VDC 5 AMP a, b, C, -
11% YO0 H.7 2 *MI
c, d, e. f.- 115V YO0 HZ 2 AhP
3. ALL WIRE SIZES ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY NVnaERS I N SQUARES. SHIELDED WIRES ARE GROUNDED AT ONE END ONLY.
E
F
28v3c M N W D I M R
PBVDC PANEL L I T E S
H - 2 M
-
k -
g 5 VAC D I M R
115 VAC YO0 HZ 3 AMP
4. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD BE GROUNDED AT THE 51RV-I. 19. WITH TRIM INDICATOR CMINECTIONS AS SHOWN AND THE REVERSING LINKS INSTALLED FOR CORRECT SERVO
PHASING TI€ P U I t M Y SERVO CAPSTAN SHOULD W N CLOMWISE WHEN VIEWED FROM THE W S T A N END UIi9ER
5. FOLU WIRES TdISTEO WITH SHIELC FOR C O I C A T I B I L I P I I N F U m E ARINC INSTALLATIONS. THE FOLLOWING AIRCRAFT ATTITUDES:

---
b. THE AUTOMATIC FLIGHT COIlTROL SYSTEM AS CONNECTED I N THIS DRAWIKG REFLECTS LOADS AS FOLLOWS: AILERON LEFT BANK
ELEVATOR PITCH WWN
AFCS LOAD CIRCUIT REQUIRED LOAD ADDITIONAL LOADS RUDDER RIGHT YAW
200 OHMS TO-FROM 100 OMS15 JUMPER DP-Y3 TO CP-33 OF 51RV-1 15. YAW DAMPER SWITCH AND BACK COURSE SWITCH ARE SOLENOID HELD MICROSWITCH bET1-T NiD SET1-T OR
500 OHMS GLIDE SLOPE POINTER 200 OHMS JUMPER TP-3 TO TP-2 AND TP-3 OF 51RV-1 EQUIVALENT RESPECTIVELY.
500 oms GLIDE SLOPE FLAG 250 omis JUWER TP-21 TO TP-2b OF 51RV-1
500 OHMS LOC FLAG 250 0w.u JUHPER W-32 TO BP-Yl OF 51RV-1 lb. THE GA BUTTON WILL NORMALLY BE LOCATED ON THE CONTROL WHEEL.
500 oms COLRSE BAR 250 OHMS JUHPER BP-39 TO Bp-30 AND Bp-Y8 OF 51RV-1
l?. OPTIONAL GQSSOVER SWITCHING OF STEERING INFORMATION MAY BE PROVIDED BY USING ALTERWTE WIRING
7. THE POWER FOR mc COMPASS SYSTEM MJST BE OF THE SAME PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL SYSTEM. AS SHOWtI I N COLLINS CCUWING ??2-'t523-001.
8. POWER LEADS DENOTED BY "GIM" SHOULD BE TIED TO COCKPIT LIGHT D I W N G CIRCUITS. 18. A PAIR OF 112 WATT 10%RESISTORS SHOLLD BE SELECTED TO GIVE FULL SCALE TRIM INDICATOR MOVEMNT
WHEN CONTROLS ARE OVEFBOYERED UNTIL SERVO CLUTCH SLIPS. lHC RESISTANCE SHOUD BE S P L I T WITH
9. SENSING W I T 395A-Y( ) AND RATE GYRO 332C-2 SHOULD BE LOCATED AS CLOSE TCGETHER AS POSSIBLE. HALF ON EACH SIDE OF TRIM INDICATOR MOVENENT. THE TOTAL R E S I S T M E VALUE SHOULD BE GREATER THAN
a: was.

AP-103F/FD-l09G King A i r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 4 of 4)

F i g u r e 460

Nov 1 / 6 8 22 -03-00
Pages 401/149, 401/150
 a
COLLINS
MAIKTEKAKCE
MANUAL

AP-103FIFD-IOSG A E R O C O W E R 1121 JET

772-9527-DO1

FLIGHT SERVOS
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMNT FLIGHT MODE AUTOPILOT EMERGENCY
CIATOR INDICATOR CQNTROLLER INDICATOR WIRE FUNCTION MLIFIER COWJTER COUPLER MISC MISC POWER AMPLIFIER WIRE FUNCTION AILERON MISC DISCONNECT
@ 331A-bA LIYE-IF 329B-8G 3YYClF 5b2A-5G IblE-1 339c-3 121A-2
JlA J I B J I A J1B J1A J1B J1 J2
J1 J2 J1 J1 J2 J3 (TP) (E?) (TP) (BP) (TP) ( W )

52 : : : 2 8 : : : :
b; -E :;LERF -
F I E L D NUM8ER 1
PlTCH A T T I N D E MON H
-
- +
b : :5+ PITCH ATTITUDE ERROR H ' ; 2 2 : : : :

-
AILERON FIELD NUMBER 2
7 . I 5 6 PITCH ATTITUDE ERROR C' : : : :
-8
-9
PITCH ATTITUDE SERVO DRIVE M2
: 2 1
2b : : : :
13
19
:
.
51- AILERON
AILERON
SIGNAL C
EXCITATION C --
10 ; : 5-
PITCH ATTITUDE SERVO DRIVE C
PITCH ATTITUDE RATE G2 . 2 3
25 :
:
:
:
:
:
:
:
15
l b
:
: 51-
AILERON
AILERON -
POSITIOii EXCITATION H

-
RATE EXCITATIOI: H

-
I1 : : S b PITCH A V I T U D E RATE C2 : 2 * : : : : 12 : 51- AILERON POSITION SIGNAL
25 : : 59- BANK A T T I N D E RATE C2 : : : :
: 3 9 11X +- AILERON SERVO GRG
-
-
29 : : 5 6 BANK ATTITUDE RATE 0 2 ; 3 3 : : : : :
23 : . BANK A T T I N D E SERVO DRIVE C 35 : : : :
17
. . 51- AILERON RATE SIGNAL

22 : BANK ATTITUDE SERVO DRIVE ,he : : : : . .

I
21 : :5* BANK ATTITUDE ERROR C' - 3 1
36
: : : : .. ...
20 .
. 5 6 BANK ATTITUDE ERROR H ' : : : : ... ..

--
I 3 2
5Y : . BANK ATTITUDE MON H - 3 8 : : : : AILEROh ENGAGE VOLTAGE
32 : I : 2 b VAC ATTITUDE PWR I 53 : : : : VEbTQ .. .. AILERON ENGAGE VOLTAGE
33 : : A : : : : .. .
- ..
2 b VAC Ph'R COM . 5 1 REF
: : 33- GYRO HIGH LEVEL FLAG + .. . .
. . .
: 18 GYRO HIGH LEVEL FLAG - . 3 0
29
:
10
:
:
:
:
:
3320-11
J1
... .... ELEVATOK :

,iE-S
GYRO MON + : y o ; ; : : N 33YC-3
3 . : : PITCH ATTITUDE CT X A . .
Y V X - PITCH ATTITUDE CT Y
z
. .
.
?
3
O
0
f
.

. . . .
I

..
:
: B 1 :::TOR -
F I E L D IiUhEER 1
( J l ) (J2)
A :
:

..
5 I ; ' PITCH ATTITUDE CT Z C
1 7 :
18
: .
BANK ATTITUDE CT X
: : : : BANK ATTITUDE CT Y
. : . 3 0
.. .. . .
; D : Y 1 S+ ELEVATOR -
F I E L D NUWER 2
0
C
:
:
: 2 0 ; : E : 1 3 -S+
- ELEVATOR SIGkAL C
- E :

-
. . .. .. ... -
: : : BANK ATTITUDE CT 2
19
.. .. .. .. ..
F : lli ELEVATOR EXCITATIOh C
- F :
.. .. ... .. ... .. ..
115 VAC POWER G- : 15 ELEVATOR POSITIOIi EXCITATION G :
: . -
..
. ... :
: : :
12
AC GROUND
PITCH A T T I N D E X (BOOTSTRAP) :
.
I : 53
:
:
lb-+
12-52-
ELEVATOR
ELEVATOR -
RATE EXCITATIOh H
POSITIOIi SIGNAL
H
L
:
:
:PITCH:
:SYNC :
:
:
: 13
I * : :
: : :
PITCH ATTITUDE Y ( B W T S T W P )
PITCH ATTITUDE Z (BOOTSTRAP)
PITCH COMMAND H ' :
:
:
:
: .
36-18
.
:
:
I
.
5Y
55
:
:
:
.
ll--xt
17-2-
.
ELEVATOR
ELEVATOR
SERVO GRD
RATE SIGhAL -.. R
S
:
:
..
. .
~~

-.
:BUTON : : : : PITCH COMMAND C' : : 2b-lb :
: I :
:J-: :
:
:
1 5 .-.r--C 2 6 VAC ATTITUDE POWER
l b : : 2 b VAC PWR COM
.
: 53-5
: 51
.
27
... ...
-I-"; i. : PITCH SYNC W . . I : 3 0 : ELEVATOR ENGAGE VOLTAGE : A J
: : : : PITCH STEER + UP :

-
: 5-31 :
.. .. ... .....
ELEVATOK ENGAGE VOLTAGE : B H
.. . : : : : PITCH STEER + WWN : : : I@
.. .. ... ...
9-21
. ... ...
: : : : ROLL STEER + LEFT 10 : 3 1 . : : ...
...
..
..
..
.. ...
..
.
..
..
..
...
.
:
:
:
:
:
:
Y9
3Y
36
37
: : :

: I
-
: I 5-
ROLL STEER + RIGHT
V 4 A R ROLL POS XMTR Z
V S A R ROLL POS XMTR X
I1
- 5 8
. b o
V-SAR ROLL C O W N D SERVO DRIVE M2 +b 2
V-BAR ROLL COMMAND SERVO DRIVE C -r- b3
-.
: : 21
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
.. ..
..
...
..
... ...
....
..-
.

-
38 V-SAR ROLL COWAND RATE G2 b l : : : :
. . 8: i i
...... ..- : : -5t- V-BAR ROLL COMMAND S I G COM- : :
39
. . .. . ... ...-
: 95 I : 57- V - E M PITCH COMMAND S I 0 COM- 59
- ..
..
.
... ... :
:
99
Y3
-
: : 5 6 V-BAR PITCH COMMAND RATE G2 b? :
:
:
:
:
:
:
:
:
:
..
-
V-BAR PITCH COMMAND SERVO DRIVE C bY
.. .. . ..
... ... -.
: 92 V-BAR PITCH COMMAND SERVO DRIVE M2b3 : : : : :
. . . . ..
: $1 : V-BAR PITCH POS/OFF-SCPLE B I A S b l : : :
.. .. .. ..: ..: .. ..
.
..
.. .. .
..
:
:
90
Y8 : 7 .
XMTR z
V-BAR PITCH POS M R X
2 b VAC COWAND PWR
-.
b o :
b 7 :
:
: :
: :
:
:
:
RUDDER
33YC-3
. .
..
. .. ... :
:
: : 39 -& 2 b VAC COMMAND PWR COM-
: 9- STEER FLAG - 5 9 :
- b Y
:
:
:
:
:
:
:
:
i E *
z - (J1) ( J 2 ) :

-
:
: : : : PITCH COMPUTER MON + : : : : NAV &@i RUDDER FIELD W E R 1 A

..
.
.. ..
. . :
:
: 3-
: : :
STEER FLAG +
COMMAND SERVO MONITOR : b5-28
1 2 - 12
: 38 :
:
:
:
51RV-1
(TP)
:
93
9 1

s+
28 VDC
RUDDER
RUDDER
F I E L D NUMBER 2
SIGNAL C
- 0
C
E
:
:
:
GLIDE SLOPE DEV + UP -. -.
:
:
33
39
;
I
: : IO-
: 11 GLIDE SLOPE DEV + WWN
GLIDE SLOPE LOW LEVEL FLAG +
.
.
:
:
3
2 2
2
:
:

. . . . .
: I
.
8
9
@
.
YY
Y5
-+
:
:
RUDDER
RUDDER
EXCITATIOh C '
-
-
POSITION EXCITATIOh H
F
G
:
:
:
. 3.b I.
:
35 :
:
: 12-
: 13- GLIDE SLOPE LOW LEVEL FLAG - . . . . .
21
22
:
:
Yb
92 : 5+-
RUDDER
RUDDER
RATE EXCITATION H
-
W S I T I O N SIGNAL
H
L
:
:
.. .. .. ... ... ... ...
: : : : GLIDE SLOPE HIGH LEVEL FLAG + : : 11
.. .. .. .. ..-.
I .. 27 ' *-19 RUDDER SERVO GRD R :

. . . . . . . .. .. .. .. .. ... 97
... .... s+ RUDDER RATE SIGNAL .. :..
s

.. ..1 :..
:
. . .: .6PC .. .- .. .- .. .. .. .
...
COURSE RSVR A Ib : RUDDER ENGAGE VOLTAGE : A B
..
;@; .. ...-
( E ? ) : RUDDER ENGAGE VXTAGE : B C
: rSPC COURSE RSVR B 22 : .. ..
f; : .. . ..
.....
I ST'!- COURSE RSVR C 23
. .ST+
.
COURSE RSVR H .
. . .
. . . . 21 : .. .. ..
:
:
Y
5
;
.
:
:
5- COURSE RSVR D
: 5 6 COURSE RSVR E .... .. .. .. ..
29
25
:
: ... .. .... ..
..
: b ; ; : 5- COURSE RSVR F 2b : .
. . . . . . ~. . .. .... ...-
: 7 : : I -' COURSE RSVR G 27 :
: 2b : : --
FROM + TO . . . . . :
... ... ..
TO Y3
: 27 : : . . . . . . ...
....-
TO FROM+ FROM lili :
: 31
.. : .
I
: 7 VORlLOC LOW LEVEL FLAG +
- . . . 91 : ... . ..
: 32 : A
. VOR/LOC LOW LEVEL FLAG 42 :
... .... ...
. .. .. :.
VORlLOC DEV + LEFT c
: 29 : 11-90 :
. . -.... ....
.... ..-.~...
: 28
: : : :
VORlLOC DEV + RIGHT
VORlLOC E V + LEFT
: l o - 3 9 :
... .. .
...
7-32-11 :
.. -... .-.
.... . .... ... -:. .-:: .:.: ..
: : VORlLOC E V + RIGHT
VORlLOC H I LEVEL FLAG
8
17-11
. . 22-
-10
: .-
:
50 :
.
.. ..
. ..-
.. ... .. : : :
:
:
LOC FREQUENCY
28VDC NAV REC POWER
. O Y
.. .. ..
Y3
.. .. ..
19 38
37 __c
: TO NAV
. F f c PYR

AP-103F/FD-l09G Aerocommander 1121 Jet Interconnecting

Wiring Diagram (Sheet 1 of 4)
Figure 461
May 1/67 22 -03-00
Pages 401/151 401/152
 ANNUN- COLRSE

@ 331A-M
PEDESTAL DIRECTOR
CIATOR I N D I C A T W CONTROLLER INDICATOR

b14E-2F
__
. _. . .
FI TCUT

32-80
-
COLLINS

WIRE NhlCTION
MAISTENASCE
IllANUAL

INSTRUMENT
URLIFIER
FLIGHT
COMPUTER
MODE
COLPLER

IblE-1
J l A J1B
MISC

NAV RCMl
5lRV-1
MISC POWER
AUTOPILOT
MPLIFIER

5bEC-C
J1 J1
WIRE FUNCTION
SERVOS

AILERON

3r)c-3
J1 J2
MISC
EMERGENCY
DISCONNECT

121A9

.. .. ..
Jl
.. .. ..
J2
..
J1
. . .
J1
. . . JZ 53
... .... ... ....
(TP) (E?) (TP) (TP)
. (Bp)
.
.. ... ... ... .. .. .. ..
: 1-
-19 NAV CONT
... ..-
. . .
: BACK: :
.-
.
._ . . . .
. . . .. . .
. .
:
:
I
I5
48
99
- 54
55
:
313J-3
(J2)
K A .. ..
. COURSE :
~~ ~

: : : : VOR SECF TEST DiiABLE : : : : : l b

. .

-
: : : : VOR Y L F TEST DISABLE : : : : : 2 : L :
. . . . : aACK COURSE MDDE INPUT
..
:
..
:
..
:
..
:
..
: 1 3
.. . . . . . .
iL : BACK COURSE INTERLOCK .. :. .: :. .: 1 2. 59 . AIRSPEED SIGNAL
:
9 .
... ... ....
..
I BACK COURSE EXC 0 58 AIRSPEED EXCITATION H
. .
-
: : : :
. . .. .. .. ..
BACK COURSE MDDE
.. ... ... ... ...
: 29-25 : 4 E Q ;
..
bO
..
I AIRSPEED EXCITATION C
. .
. . . . . SHUTTER +
.
.. .. ... .
.. .. . . .
8bOE-2
(Jl)
:
: ...
..
..-
.. .... ....
45
Yb
f DISTANCE
DISTANCESHUTTER -
9
10
:
: ... .....
. ?
. .. ..
.. .- ..
.....
Y? DISTANCERECEIVERS 2bVAC -TO
H 2 :
48 -: f DISTANCERECEIVERS 2bVAC R D P . .
.. .. ..
1 :
.. .. .. ... ... ...
u9-I:
.. : : : : DISTANCERECEIVERS Z COMMN
.. ..
. . . . . . .. . .. ..
..
50 : DISTANCERECEIVER UNITS X P Y :
51 : DISTANCERECEIVER UNITS Y P 3 : . . . .. ..
52 .. DISTANCERECEIVER TENS X b :
..
. ..
... ... ...
53
59 : :
DISTANCE
DISTANCE
RECEIVER TENS Y P
RECEIVER HUNDREDS X
5
?
:
: ... .. .. ..
.... ....
55 :
... ... ... ... : DISTANCERECEIVER HUNDREDS Y
I
8 :
I I I .. ... .. ..
. . .. .. .. .. : : : :
..
:
COWASS :
:
.. .. .. .
...~ . .
....
: 328AdA
. . . . : :
... ... .. ..(J1) (52) :
... ... ... ... ...
9-1 - ..: ._ .I. . .
f f COWASS HEADING X
..
: 2 :
.. .. ..~ .
: n2
.. .. .: 3... .. .. .. ... ...- .. ..
... ...
10-2
: 18 J
- I
.. ..I ..: :.. COWASS HEADING Y
. . . ..
:
- ..: ..: .. . Y
...
. . ... ... -.... .....
.. ... -.. ... .. .....
11-3 I f COWASS HEADING Z Z :
: 19 2 .
.. ..- -
.. .. .. .. . . . .. ..
...
: : : : 115 VAC POWER
... ... :
:
:
:
:
:
:
:
2 8 W C POWER
ROUND .. .. .. .. -72 .. . .. ..
.
: : : : COMPASS MONITOR + : : 25 :: 39-1Y : . . .... ....
.. .:
~~

. : 5 ' : : HEADING D A M H . b 11 f : : 49 COMPASS DATA X

:
. 4. .. .. .. .. HEADING D A M C' . . . ? 4 : : : 50 COMPASS DATA Y ... ...
HEADING DATUM H '
... ... : : : : HEADING DATUM C '
:
.. 51
.. COMPASS DATA Z
.
. ..
: :
: . .: :. :
HEADING D A M LOAD RES (IOK)
. . : . ... ..
....
13 COURSE DATUM H' : 9 PILOTS COPILOTS
12
. . : :
:
COURSE DATUM C '
. .. 8 ... DISENGAGE DISENGAGE

.. ...
: : : COURSEDANMH'
. .
: 3Y-
i .. .. BUTON BUTTON
:
:
:
:
:
:
:
:
COLRSE DATUM C '
COURSE DATUM LOAD RES (10K)
COWASS LOW LEVEL FLAG +
. .
:
:
2 4 - q ;
: I s . : bb - AUTOPILOT DISENGAGE - I L -
. .
30
: 24
:
. . . . :
COMPASS FLAG - : Y ?
: I 1
:
:
:
:
5
13
:
f
:
.
b?

...
AUTOPILOT DISENGAGE
.. ..
...
: 21 : I : : ST- AZIMUTH CARD ERROR CT H ' : 1 3 : : : :
: 20
:
:
:
:
:
13
14
11
12
15
:

. . .
. .
:
:
f S b AZIMUTH CARD ERROR CT C '
: S+
:
:
:
AZIMUTH CARD RATE G2
AZIMUTH CARD RATE C2
AZIMUTH CARD SERVO DRIVE M I
AZUnUTH CARD SERM DRIVE Cl-lb
2b VAC HEADING PWR
- :
. 1 4
. I 5
I?
: 5 2
l B :
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
..
..
..
..
.
..
..
...
..
.
:
:
:
:
. .
:
:
:
:
SENSING
UNIT
345A-YB
(ROLL)
8
:
... ..
..~
l b

.
:
:
:
:
:
:
2 b VAC POWER COM
1 0 4 RUWAY LOC POS %hTR X
ll+ RUWAY LOC POS X6T.R Y
-
- 28
2?
: 5 4
:
:
:
:
:
:
:
:
:
:
:
:
:
:
b5
8
32
:
.
.
m L L RATE MOTOR ISD
115 VAC POWER
ROLL RATE E X C I T K I O N C . .
A
8

.. ..
.... ....
:
:
:
:
:
:
:
:
:
13
14-
-
12 -& RUWAY LOC POS X6T.R -Z
RUNWAY LOC SERVO DRIVE M2
RUWAY LOC SERVO DRIVE C-
- 22
2 3 :
24
:

:
:
:
:
:
:
:
:
:
:
:
:
:
31
...
29
...
ROLL RATE EXCITATION H
ROLL RATE SIGNAL X .
.
.
.
F
G

.... .... : : : 1 5 4 R W A Y LOC RATE 02 2 b : : : : : . .. : : (PITCH)

: : : : : : : . .
.... .... : : :
l b -& RUWAY LOC RATE CB
5- RJWAY K T S E R V O DRIVE C-3Y
2 5 :
: : : : :
:
:
8-
10 -
- 115 VAC POWER -
PITCH RATE MOTOR GRD
.
.
.
.
A
0

... ...
:
. .: .:
:
: : 4-
7 S+
RVWAY ALT SERVO W I V E M2-33
RUWAY ALTRATE C 1 3 5 :
: :
: :
: :
: *
: :
:
32
31 -
-
PITCH RATE EXCITATION C
PITCH PATE EXCITATION H . .
E
F
... ... b S b R W A Y ALTRATE G2 3 b : : : : :
.:. 29.. PITCH RATE SIGNAL X
.. .. G

.... ...-
:
:
:
: :
: :
:
1 4 RUWAYUTPOSX4TRX-38
2 -X- RUWAY ALT POS M T R Y - 37
:
:
:
:
' : :
:
:
:
:
:
:
:
:
.. -
..~ .. :
:
:
:
YAW RATE

.... .... :
:
: :
3 4 - RJWAY ALT POS %KTU-Z
8 4 2b VAC RUWAY PWR
3 1 :
5 3 : : : : : . . . .
GYRO

: : : : : : : :

.. ._ . . .-
9-6. 2b VAC RJWAY RIR COM-51 bb YAW
... ... :
-: : 17 RUNWAY FLAG +
- 4 9 : : : - -
I I
1 RADIO ALTIMETER : 10 . 115
.. ..
: : : 18 R W A Y FLAG : : : O8bOi-l > : YAW
. 48 339:-( 51

..... .....
: : : : : : (PlB) : 50 : YAW
: : : .
:
:
: : :
RADIO ALTITUDE+
RADIO U T I N D E - -
5
4
: : : : : 22
23
:
: ..
48
... ...
YAW

... ... : : : :
- RADIO ALTITUDE KINITOR + 1 Y . : : : ; 12 :
.. ....
.... .... : : : 37 MDA LIGHT CONTROL E :
..... ...-
.... ...-
. .
:
:
:
:
:
:
:
:
: 3b-
: 38-
: :
: :
MDA LIGHT TEST
MDA LIGHT EXCI
ALTITUDE EXT OVERRIDE 200 F l
RUWAY SYhBOL 200 F T ALT TRIP Yb
: :
:
91
.
f
:
I
f
f
:
..*.@I i *. -I
: : : : MIDDLE MARKER TRIP 43-29 : : : i s

AP-103F/FD-l09G Aerocommander 1121 J e t , Interconnecting

Wiring Diagram (Sheet 2 of 4)
Figure 461

May 1/67 22-03-00

Pages 401/153, 401/154
ANNLRi- COLRSE

@ 331A-bA
FLIGHT
PEDESTAL DIRECTOR
CIATOR INDICATOR CONTROLLER INDICATOR

bl'tE-ZF 3298-86
WIRE FUNCTION
-
a
COLLINS

INSTRUMEhT
MLIFIER

3YYC-Y
J1A J l B
.
tTp) (BP)
R.IAINTEKANCE
MANUAL

. :. .: .:. ..: ..:

:
.
FLIGHT
COMPUTER

5b2A-5G
J1A J l B
.
(TP) t.BP)
.
MODE
COLPLW

IblE-1
J1A J1B
(rp)
. (sp)
.
MTSC

A
SENSCR-
590A-3E
L T
MISC

:
~
:
:
POWER
AUTOPILOT
MLIFIER

5b2C-L)
J1
...
(Tp)
.
Jl
..
tap)

..
WIRE FUNCTION
SERVOS

AILERON

33Yc-3
J1
..
...
...
J2
.
...
...
MISC
EMERGENCY

DISCONNECT

l2lA-Z

..... .. . .- A L T I N D E ERWR H ' : : 33- l b : Y1

. ...- ....
...
V-
...
- M R T U D E ERROR C'
ALTITUDE HOLD MODE INPLIT
:
.. ..
: 2
:
3

:
.
.
:
. 5 D
: 27 f
...
:
..
92
...
.
~. ..
...
..
...
...
: :

--
ALTITUDE HOLD MODE (SENSOR) 90-33y
. .. .. . . ..
- : : :

-
A L T I N D E HOLD MODE Y7-27
.. .. ..
~

-W ALTITUDE INTERLOCK . : 35 .. .. . .
ALTITUDE INTERLOCK : : Yb-319 : . .. ... ...
A L T I N D E OFF : : Y8 33 . . ... ..
- Y 5.. ..
.. .. ..-~ ... .:.
... ...
GS ON YY 39 3Y Yb
115 VAC POWER
... ... 3b . B
. ..
AC GROUND .. .. ... .. 37 . .
.. .. ... .... .... .... 39 : Y3 ALTITUDE GAIN WAhGE EXCITATIOI; :
... .:..
.. .. . . . .
92 :
..
YY ALTITUDE G A L CHANGE NO. 1
.. ..
.. .... 43
.. .
Y5 ALTITUDE GAIII CHANGE NO- 2
... .. ... ....
.
..
.
... f .

.. RECV ; .. .. ..
.. .. .: .. ... ...
.
...
.
...
.
.
..
115 VAC HEADING PWR
115 VAC ATTITUDE PWR.
..
: 55
b: 5 b
:
..
-
.. ..
-
+ 3

@-
55
5
:
. .
9 :

..
.
..
...
..
...
..-
.. : . : : I . :p-J: i

-- - -
115 VAC COMMAND PWR b 5 : GRD : GROUND :
.. .. 115 VAC RUNWAY PWR 5 b . : : . : : bl 28 M C POWER . . P
... ...
yB-;
g 3 : .
-
115 VAC PWR COM
DC GROUND
. . . .. .. 57-57-57
. : : f GRU
..
b3
..
:
RUDDER SERVO POWER
RUDDER SERVO POWER
S
1
'8 - . l-1-2b : :
GRD
..
..- e
9 :
lb
: :
28 M C POWER
25 VDC POWER (REG) :
. . . : 25
5Y-24 :
: .
@ Q .
b l
.: AILEROh SERVO POWER
AILERON SERVO POWER
. . . .
-
~

..-
: 24 19 5 VACIDC LIGHTING U ELEVATOR SERVO POkER W
:
.. 25 : . 20 5 VACIDC COM u :. b4 ELEVATOR SERVO POWER .. .. 20 X
.. ..
- i
: : Y5- SPEED COWAND DEV + FAST HIGH LEVEL: :
. . : : : :
... .. : : 97 SPEED COHMAND DEV + SLOW COM : : : : : @ i I . .
.. ... : : 35- SPEED C O W D FLAG HIGH LEVEL + :
.. .. . . . ..
: : : :
. .
'!-Ji- ... ...
: : 49 SPEED COMnWD FLAG COM : GRD 1 :
: GA :
MODE++ ; ; i .. ..
TRIM :

. =
: BUTTON : : : :
: co
M AROUND MON ROLL COUPLER :
: 1: : : : : Go AROUND MODE + PITCH 92- YY 35
. . .
. 1blA-lA :
;
..
..
c GO AROUND E
Go AROUND ACNATE
EXTERNAL STEER + WWN
:
: .-X .. . . :. a+.C I b
....
:
.
...
TRIM ENGAGE VOLTAGE - (J1)
20
:
: L

.. ... . . . .
: : : : TRIM ENGAGE GROUND 32
..
: M

. : : : :
EXTERNAL STEER + UP
GYROMODE : : : Y1-20 :
.
YO
.
: ..
.. ... : : : : HEADING MODE : : : Y7-21 : bY : .
.
.
.
.. .. : : : : N I L MODE : : : Yb-22 : 47 :
.. . .
. ..
: : : : APPROACH MOM : : Y5-23 :
L : : : GYRO W D E : 2D ..: 98
.. .. ..
..~ . K : : : HEADING MODE : . : 2 1 : Q
.. .. X+ 115 VAC POWER a :
.... .... J . : : N I L MODE : . . :22 . . .
. . . .: 23. . .
.. .. H
j : : :
P APPROACH MODE
ELEVATOR TRIM INDICATOR
: GRD
:
.
GROUND
33 ----S+ TRIM INPUT UP
-+
- 1
13
:
:

.. ..
k . : : ELEVATOR TRIM INDICATOR 39 TRIM INPUT LP + 11 :
. . . . . ... ...
... ...
h : : I AILERON TRIM INDICATOR 33 : f .

.. ..
1 : : : AILERON TRIM INDICATOR 3Y :
.. C..
n : : : RUDDER TRIM I N D I 4 T O R M 52 :
.. .. m .---.r-.cr- RUDDER TRIM INDICATOR . . . . 53 : . .
.. .. -+
- --
: : : : NILARM- : : : b-32 : : 35 TRIM INPUT DN + 2Y :
.. ..
... ...
:
:
: : :
: : :
N I L CAPTURE
GS ARM
:
:
:
:
:
b-3b
39-34 :
:
:
. 3b -'t
. TRIM INPUT DN
ARMUP
-
.. ..
--
: : : : GS CAPTURE : : 8-37 : TRIM LP
. . .. ..
.. ..
: : : : :
.. .. .. .. GS EXTENSION
GO AROUND
:
:
:
:
Y2-38
lb-33 : .. ..
*. N I L APJI ANNUNICATOR +

....-
-c : : : : : . 3 7
: : . . : . N I L C A P W E ANNUNCIATOR + - : : -. ...
'8
.I - - I GS ARM ANNUNICATOR +
: 3 8
... .. RELAY GRD
GS CAPTURE ANNUNCIATOR + :
...
8' : : : : : Y 2
GS EXTENSION ANNUNCIATOR + . ..
.. .. ..
9'
: : : 3Y GO MOUND ANNUNCIATOR - . .: :
:
: Y Y
Y3
. .
-
: ALTITUDE ANNUNCIATOR
JAW COLRSE ANNUNCIATOR +
:
:
: . . Y O
... ..
: : : ANNUNCIATOR BUS :
2-45
: : : 19-
...
. ..
: : : OUT OF VIEW B I A S 2 0 . : . : 3b
... ...
.
: : 99-
: : 50
R A T E O F TLUN
RATE OF TURN
OF TLRN FLAG +
- RAT^
TO PATE :
OF TURN :
1 ;. 1. :
:
:
.. .. .. :..
:
:
I
:
I
:
..
..
...
..
- . . . .
: : 51- SENSOR
.
: : 52-
. .
PATE OF TVRN FLAG . .

-
: :
... . . -.. ... 1
1 9 :
5 :
: : ..:: 59

.. .. .. : :
18

...
.... .... 5 : -s-
.
19

.. .. .. i. Q.
4
YO r n
25
2b
5 q :7

.. ... ... ... ... 35 E

2 5 . . : -' :
27
28
..
...
.. ..
. . ... .... 1 8 : : : : 57 OFF +

. ..._ ... .
... ..
:
: 1 9
: a : :
S? 1 8
bO
: . . EXT mi; STEERN
IG A

.. ... .. : 9 : : SI 19 : EXT ROLL STEERING B

..- ... .. ..... @;; i :t S? 25 : PROCESSED BANK W A

-.... .... SI 2b : PROCESSED BANK CW B

. .
....- .... . .... .:: 321 557 : S? 35 : PROCESSED BANK DATA A

.. ...
:: :. SI 3b : PROCESSED BANK DATA B

.. .. - : 7 S? 5Y : EXT BANK CK, A

.. .. .. . :18 . :
SI 55
-557
:
:
EXT BANK CMD B
IhTERNAL ROLL STEERING OFF +

AP-103F/FD-l09G A e r o c o m m a n d e r 1 1 2 1 Jet, Interconnecting

W i r i n g D i a g r a m (Sheet 3 of 4)
May 1/67 F i g u r e 461 22 -03-00
Pages 401/155, 401/156
ANNW-
FLIGHT
PEDESTAL DIRECTOR
C I A T W INDICATOR CONTROLLER INDICATOR

331A-bA

11 12
blYE-ZF

J1 J1
32-86

J2 53
W I R E FUNCTION
-
a
COLLINS

INSTRLWENT
MLIFIER

394C-lF
J l A J1B
MAIYTENANCE
MANUAL

(TP) (BP) (TP) (BP)

FLIGHT
COhPUTER

5b2A-5G
JIA JIB
M3DE
COWLER

IblE-1
JIA JIB
(TP) (BP)
MISC MISC POWER
AUTOPILOT
MLIFIER

5b2C-'4
J l
(TP)
J l
(Bp)
YIPS NNCTION
SERVOS

AILEM

334c-3
J l J2
MISC
EMZffiENCI
DISCONNECT

121A-2

- A
:. ._ . . P I T M CONTROL EXC A .
. . .
.
. . .
. .
. : 21 .. ..
. -
0 P I T W CONTROL S I G W L : 20
-.-. ....
I

: : : .. .. ..
.. .. .. . .
D
. . .
. -... ....
.. ..
E : : . N R N CONTROL EXC A 21 :
F : : : N R N CONTROL EXC B . . 22 : ... ...
G . : . TURN CONTROL SIGNAL . . . . . . . 23 :
... .
. . -. -. .- . ..
I N T MOTOR CONTROL VOLTAGE
.. :.. ..: :.. ... .
. : 62
... .....
D TNT ObVAC M T O R EXCITATION C 2u :
R : . . I N T MOTOR RATE SIGNAL
. . . . .
.. : b3
..
s
T
u
: : ;
: . :
. : :
I N T MOTOR SIWAL C O W N
28VDC PANEL LIGHT PWR
GROUND
. . . . .
.. .. . . .
.
.
l
.
o GRD
, .
. 2'1
. ..
...
..
...
x : : : . . .. .. .. .. . . .. ...
. . . . .. :. ..
...
ENGAGE VOLTAGE
2 : : : . . ..: .
.. 3 ..1 :
.. ...
a : : : ENGAGE PULSE' . . . . . . . Sb
b : : : DISENGAGE VOLTAGE . . . . . . . 37 .. ..
c : : : ENGAGE READY . . . . . . . 55 . .
d : : : ALTITUDE HOLD MOOE + . . . . . . f 3s ... ...
f : : : HEADING SYNCH CUTOUT . . . . . . 3a
. :
.
P : : : : : 1 : : : ; @ ... ...
9 : : : 115 VAC POWER . . . . . . ; I ... ..
r I : . I N T 2bVAC MOTOR EXCITATION H : . : : : : r 23 :
. ...
: : : :
.. ... .. .. ... ...
5 ENGAGE INTERLOCK 59
t : : :
~ ~ ~~

. . . . . I i
__I

. . I
u
v
. : :
: : :
AILERON C L n W VOLTAGE
ELEVATOR CLUTCH VOLTAGE
. . . . . .
p
39_ . c
. . . . . .
39
> . .
w : : : RUDDER CLUTCH VOLTAGE 5 ib : . . . . . .
M : : : + P a m c AUTO PILOT PWR: . .. .. . . .. .. .. .. . . d
x : : : 13 . .
YAK DA'IPch ElqGAGi !CI. + . . . . . . . - .. .. I
t
! SPARE -q .. . . . . .
.. ..i ..i i.
. .. ... ... ... ... ... .
..
.
.. . .
.. . . _.. . .. .. .. .. .. .. . . . . 1
.. .._ .. .. .. .. . .
.. .. : YAW DAMP SV
.. . . .. .. .
.. .. . . . .. ..
.
..
. . . . ...
.. .. .. .. . .. .. . .. .. . . ... ...
.. . . .. .. . . . . .
. ... ... ..
. . . . . ... ...

SYhBOLS USED:

S? TWISTED SHIELDED PAIR-ADJACENT

SA WIRES AS SHOWN ON DRA\<ING
SG SHIELD TEID To QIOUND AT UNTI
S1 SINGLE SHIELDED WIRE

8
XI ALL S 1 SHIELDED TIED TO X I ETC.
Z;~WR
IES TWSI TED wIm SHIELD

NOTES:

1. REFER TO THE INDIVIDUAL INSTALLATION MANUALS FOR COMPLETE INSTALLATIOI; iNFC

2- SPEED DISPLAY I S COVERED BY A REMOVABLE M S K .

A , t31 C, G. G
L - - 2 b VLC
26VDC Al.irdI, C1:IMih
5 AMP a , b, c . -11% i j c ZI 1 k*IP
c , (i, e , =, 11- i i w Y X hi 2 AMP
- -
3- ALL WIRE SIZES ARE IO. 22 UNLESS DESIGNATED OTHERWISE 5Y IhUWERS 11: S P U M E S . Sk1ZLL.C
F 2EVUC P A l i i L LITES
8 5 - 2 W
9
k - 5 VAC C I M I C R
115 VAC '130 nZ 3 &YP
'4. SHIELDS ON THE NAV RESOLVER LEADS FROM TiiE IKAVIGATIOI~RYCEIVER SHOULL 3C G 1Y. SIITti TRIIV IliDICATOR CCl.htCTIOlrS 5 SHOWh A I 2 THE KtViFSI1;G LINKS I I l S T A L L i D FCR CORRECT SERVL
PhASIlvG T t r i PRIMARY SERVC CWSTA SHOULD TJRI. CLOCKWISE WHEII VIEWED FROM TLiE CAPSTAlr El?; L t h k
5. FOUR WIRES TWISTED uim SHIELD FOR COWAT~ILITY I:; FUTUR; AR
NIC II~STALLATIOLS. Thc FOLLOWIhG AIiiCkAFT ATTITUDES
b. THE AUOMATIC FLIGHT COKTROL SYSTEM AS CC;C.LCTEI> I:.
T'iIS 3 CTS LSA"S AS FCLLO::S: AILEROI.
ELEVATOR
-- RIGliT LIAIJK
PITCH UP
AFCS LOAD CIRCUIT REQUIRE5 LOA5 ;,L-IT:O,.AL LXCS RUCDEli - LEFT YAh
200 OHMS TO-FROM 130 owls 15. YAW D A W S SWITCi AliC UACK COURSE SWITCH ARE SOLEkOI5 HELD MICROSWITCH bET1-T AND SET1-T OR
500 OHMS GLIDE SLOPE POINTER 200 OHMS E0UIVALEI.T RESPECTIVELY.
500 O M S GLIDE SLOPE FLAG 250 OHhlS
500 OHMS LOC FLAG 250 OHMS lb. M E GA WJTTCI. U I L L IiORlMLLY 3C LOCAlEL' O h THE COhTROL WHEEL.
500 OHMS COURSE BAR 250 OHMS
17. OPTIOhAL CROSSOVER SYITCt.IhG OF STEERIkG IlIFORMATIOh WY BE PROVICED BY USIICG ALTERNATE WIRING
?- THE POWER FMI THE COMPASS SYSTEM W S T BE OF THE SIVIIE PHASE AS T I E REST OF i r i E AJTOIMTIC FLIGUT CONTROL SYSTEM. AS ShCYt. 1I.i COLLIlrS DRAWING ?72-'1523-301.
8. POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT L I G n T LI":\II~G CIRCXTS. 18. ALTITUDE TRIP P O I h T I S NORMALLY ADJUSTEC TO 230 FEET GUT A DIFFERENT TRIP POINT MAY SE SELECTED
I F DESIRED. COkSULT AL-IO1 SYSTEiI i,lAi!~T€P.A:,CE 14ALUAL FOR SPECIFIC ACJUSTi4El.T PROCEGURLS AND FOR
9. SENSING UNIT 3'45A-'+( ) bND PATE GYRO BOG-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE. ALTITUDE TRIP WIRING INFORMATIOI7. 772-.m7-00,

AP-103F/FD-l09G Aerocommander 1121 J e t , Interconnecting

Wiring Diagram (Sheet 4 of 4)
Figure 461

May 1/67 22-03-00

Pages 401/157, 401/158
 COLLINS
MAINTENANCE
Qw MANUAL

FLIGHT
ANNUN- CWRSE PEDESTAL DRI ECTOR INSTRLMNT FLIGHT MODE YRMS
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER CORLmR COCPLER MISC MISC POWER AUTWILOT EMRGENCY
NWLIFIER WIRE FUNCTTON AILEROH MISC DISCONNECT
@ 331AAA bIYE-% 3298-86 3YYClF 5bOA-SG IbIE-1
JlA JIB J l A JlB J I A JIB 5b2C-Y 33*03 121A-Z
Jl J2

-
Jl J2 Jl J1 J2 J3 (TP) (BP) (TP) (BP) ( T p ) (BP) Jl Jl
(Tp) (BP)
.. .. .. -
.. .. ..
..
..
..
.
.
...
...
.
.
...
...
.
...
:
:
:
:
:
:
5

7-b
-8
-9
b+-

ID-+
2 : :
PITCH ATTITUDE M3N H
PITCH A T T I M E ERROR H '
PITCH A T T I N D E E m C'
PITCH ATTITUDE YRVO DRIVE b?
PITCH A T T I T W E Y R V O DRIVE C
PITCH A T T I T W E RATE G2 P 23
-
. 2 8
22
21
2b
T 25
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
b! +* '

13 -cbt
1Y -
t AILERON FIELD N W R
+ AILERON

AILERON
AILERON
1
28 wc FIELD NLWER 2

SIGNAL C
EXCITATION C-
--
- A
0
c
E
F
:
:
:
:
:

- -
15 _c__ AILERON POSITION EXCITATION H G :
...
.-.
.
...
.
..
..
..
:
:
:
I1 -tf56 PITCH A T T I N D E RATE C2
25-F
24
BANK ATTITUDE RATE C2
: I 5 6 BANK ATTITUDE RATE G2
. 2 Y
. 3 Y
. 3 3
:
:
:
:
:
:
:
:
:
:
:
:
Ib -
I2
t
-+
-+
AILERON
AILEROH -
RATE EXCITATION H
POSITION S I G N 4
H
L
:
:

-
11 AILERON SERVC ORD R :
. . . ..-+ ..
...~..
: 23 BANK ATTITUDE SERVO DRIVE C : : : : 5 :

-
35 17
.. : 22 -cc- BANK ATTITUDE SERVO DRIVE M2 73b : : : :
. .
AILERON RATE SIGNAL
.-. ...
.. .. ..

- .. .. ... ...
: 21-F BANK ATTITUDE ERROR C'-31 : : : :
.. .. .. : 20 : : 5 6 BANK ATTITUDE ERROR H ' Y : : : :
. . . .
..
...
..
..
..
.
. .
... ...
. .
... ...
... ...
:
:
:
:
5Y
32
33

.:. .. .. ..
: : :

: : 33-
: 18-
BANK A T T I N D E K)N H
2 b VAC ATTITUDE PUR
2 b VAC PUR COM
GYRO HIGH LEVEL FLAG +
mm HIGH LEVEL FLAG
Gym MON +
- --
. 3 8
53
. 5 1
29
. 3 0
: Y o
:
:
:

:
.
IC
:
:
:

:
: .
:
:
:
:
:
:
:
:
:
:
:
I
VERTQ
REF
3320-11
J1
N
:
I
:
:
...

.
..
..
.. ..
..
.-
..
...
AILERON ENGAGE VOLTAGE
AILERON ENGACE YKTAGE
:

.. ..
:

ELEVATOR
A
B
E
F

.. .. .-
. .
: 3- P I T M ATTITUDE CT X : 3 0 . : : A :
-. . 33YC-3
..
.. ... ...
.. ..
:
:
*Y-
5 .
PITCH ATTITUDE CT Y
: > PITCH A T T I T W E CT Z
. . a
.
:
. . . .
: :
.
0
c
:
: ELEVATOR -
FIELD NUlBER 1
( J 1 ) (JI)
A :

...
.
.. ..
. .
:
:
17 : : . : BAHK ATTITUDE CT X
18-e BANK A T T I N D E CT Y
: .
: :
: 3 D
: 2 0
.. . . . . .
:
:
.
:
D
E
: 28VDC
ELEVATOR -
FIELD NUIBER 2
0
C
:
:
.. .. ..
:
. 19
... .. ... ...
: : ; BANK ATTITUDE CT 2
... ... ... ... ...
:
-
13-----52-- ELEVATOR SIGNAL C
-
-
E :'

- - :
.. 115 VAC POWER
. G- : I Y ELEVATOR EXCITATION C F

...
.
... ...
.. ..
:
:
1 2 : :
13
AC OROUND
PITCH ATTITUDE X (BOOTSTRAP)
PITCH ATTITUDE Y (BOOTSTRIP)
. . . . .
.
.
.
53
59
H- :
:
:
15
lb-2-
1 2 4 +
ELEVATOR
ELEVATOR
ELEVATOR
RATE EXCITATION H
POSITION SIGNAL
-
POSITION EXCITATION

-
G
H
L
:
:
:

. :
.. .. .. ..
-
:PITCH: : : 1Y- PITCH ATTITUDE Z (BWTSTRAP) . 5 5 : 11-xt ELEVATOR SERVO GPD R :
:
:SYNC :
:WTTON : .. .. .. .. PITCH COMMAND H ' :
:
: 3b-15 :
:
:
. 17-+
. ELEVATOR RATE SIGNAL 5
. .
:

:
PITCH COmAND C '
:
: 2b-
: 53-5 .
Ib
... .. ...
...
...
15 2 b VAC ATTITUDE POWER
' x i : : I b : : 2 b VAC PUR COM .
: 51-27 . .. . .
' d . i .j ; . i i i ; PITCH SYNC MAN . 30 : .. ...
PITCH STEER + LP
-.. I ;
.. . .
... ...
.. .. .. ..
.. .,. .. .. PITCH STEER + DOWN
:
:
5-31
4-21
:
:
:
:
:
:Q i I ....
ELEVATOR ENGAGE VOLTAGE
: H-8
... ...
J

-
ELEVATOR ENGAGE VOLTAGE
.
... ..~. .. .. .. .. m u STEER + LEFT
ROLL STEER + RIGHT
10 : : 31 :
:
:
: -. . .... ....
.. . . m u PDS ~ T 2R
1 1 : : 2 1
: : . .
... ...
: 99- MAR . 5 8 : :
.. . .
- . .
-
V-BAR ROLL POS XMTR x
... ...
-
: 39 . b o : : : :
.. : : : . . f
. .
.
.... ...
3 b : . V-BAR ROLL COWAND SERVO DRIVE M2 b2 : :
.. .. .. ... ...
-
: 3 ? : : V-BAR ROLL C O W D SERVO DRIVE C b3 : : : :
.. .. .. : 38-F V-BAR ROLL C M N D RATE G2 bl : : : :
.. . ..
.. .. .. ....
f .

..
: 39 : : 5 b V-BAR ROLL C W D SG
I COM 59 : : : :
... .... ...
...
.... ...
. : Y5-P V-BAR PITCH CohmwD S I 0 COM- 59
- : : : : :
...
.. ... ...
: YY : : 5 6 V-BAR PITCH C W N D RATE G2 b2 : : : : :
... .. ..
..
: : : : : ..
.....
-3
9 V-BAR PITCH COmAND SERVO DRIVE C bY :

..
..
..
..
..
.
...
..
..
.
...

..
...
..
..
.
...

..
:
:
.
:
:
:
Y 2 : :

._ . . . .
9 1 : .

YO
98
:
- V-BAR PITCH C W D SERVO D R I M h e b 3
V-BAR PITCH POSlOFF-SCALE B I A S

: : :
: 39-t-
mTR z
bl

V-BAR PITCH POS XMTR X

2 b VAC ComAND PUR

-
2b VAC C W D PUR COM -
-.
-.
:
:
b
b
:
:

5Y
:
:
o
?
:
:
:
.. ..
:
:
:
:
:
:
..
:
:
..
:
:
:
:
:
..
:
:
:
..
..
..
...
...
..-
..
.
. ...
.. ..
RLDDER
33YC-3

..
:
..
:
..
Y-
..
STEER FLAG . b Y : :
- 12
: :
- (Jl) (J2)
..
-
.. .. PITCH COMPUTER M3N + : : 12 : : NAV RCW QI RUDDER F I E L D Y W R 1 A :

:
:
:
.

..:
. .
33
3
35
3b
...
.
:
:
.
.
:
...
. :

..
: 3-
. . . .
.lo-
: 11
. . :e l :
: 13
... ...
- ...
STEER FLAG +
C W N D SERVO MONITOR
GLIDE SLOPE DEV + LP
GLIDE SLOPE M V + DOWN
G L I M SLOPE L W LEVEL FLAG +
GLIDE SLOPE LOU LEVEL FLAG
GLIDE SLOPE HIGH LEVEL FLAG +
-
.:

:
:
b5-
:
:

.:
3
2
:

:
.
2
2
38
28

:
r

. .
:
:
:
:
:
:
:
.
.. ..:
5lRV-1
(TP)
8
9
21
22
0;
.
:

:
:
Y3
YY
45
Yb
-
-+
ti+
-+
28 VDC-
RVDDER F I E L D MMBER 2
RVDMR SIGNAL C
RUDDER EXCITATION C
RUDDER P O S I T I W EXCITATION H-
RVDDER RATE EXCITATION H
-
-
-
0
C
E
F
G
H
:

:
:
:

:
:
.. . . .. . . . ...
:
.. 11
.. :
.. .. .. 27 : 92 RVDDER W S I T I 9 N SIGNAL L :
. ..
RWDER SERVO GRD R :
.. .. ..
- 1Y
. . . . . . . . ~.
Y? -+ RUWER RATE S K I N U 5
. :
.. .. .. .. .. .. ... ... .
:@a .:
: 1 : STY- COURSE RSVR A lb
. . . .. . . I
.
. . . . . . . (E?) :
. . RLODER ENGAGE VOLTAGE : A B
: :
i ;
%T+
+ST+
COLRSE R S W B
COURSE RSVR C
22
21 : -. -. RVDDER ENGAGE MLTAGE
..-. ....
: E i C

.. .. .. .. . .. .. .
:
:
%T+ COURSE RSVR H
.
21 :
. ..- -.. ...
:
:
Y
5
:
:
T 5 F COURSE RSVR D
: S b C M S E RSVR E . . . . . .
2Y
25
:
: ... ... ... ...
. . . . . . .. ..
... ...
: b . : : S F COURSE RSVR F 2b :
. . : . . . . . .
:
:
?
2b
:
: TO --
: S b CDURSE RSVR G
FROM + TO + . . .
. . . . . .
27
43
:
: ..
..
.. ~.
... ...
: 27 : TO FROM + FROM YY
.. .. ..
:
:
31
32
:
:
.
VCWLOC LOU LEVEL FLAG
VORlLOC LOU LEVEL FLAG -
+
. . . . .
91
Y2
:
: .
..
.
.. ... ...
: 29
.
VORlLOC DEV + LEFT + 11 - Y O :
.. ... ... ...
-.
.. .. .. ..
-- -
: VORlLOC DEV + RIGHT :
.. .. .. ...
28 10- 39

... .. .. ... ... ... ...

VORlLOC DEV + LEFT 7 : ; 32 11 :
. .. .. ..
... ...
. . .. . . . VORlLOC DEV + RIGHT 8-82-10
. : I1 : : :
... ....
. . . Y .3 . 1.9 -38
.. ... ... ... ... ...
VORlLOC H I LEVEL FLAG 17 50
... ...
.. . . .. LOC FREQUENCY
PPVDC HAV REC mum
YO
37
: TO NAV
REC PVR ... ..

AP-103F/FD-l09G G u l f s t r e a m I, I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 1 of 4)
F i g u r e 462

Mav 1/67
Y .
22-03-00
P a g e s 401/159, 401/160
 a
COLLINS
MAISTENANCE
w MANUAL

F L I M SERVOS
ANW- CMRSE PEDESTAL DIRECTOR I N S M Y T FLIGHT W E AUTOPILOT ElERGEHCl
CIATOR INOHCATOR COUfROLLER INDICATOR WIFf "CnW MLIFIER COWUlER COLPLER MISC LUX POYER MPLIFIEU V I E FUNCTION NLERON MISC DISCONNECT
@ 331A-M blYE-ZG 3298-86 3WC-W SbU-5G IblE-1 NAV RCMI 562M 33u-3 1 2 W
JlA JIB AIA JIB J l A JiB 51RV-1 J1 J1 J2
. J!
. . J?
.. .._
J+
. .J+ JS J! tsp)
...
tep,
...
CTp'tep) (Tp)
. . .: (W)
-
-
(T) trp) (
... .
...
... ... ... .-~. ..
1 19 NAV CONT :
. .. _ VOR SELF TEST DISABLE
. ..
.-
VOR SELF TEST DISABLE 15 :
. . . . ._ . . . .
. . . . ... .. ..
54 313J-3

..
VOR SELF TEST DISABLE : Y8- 55 (52) :
: BACK: : VOR SELF TEST DISABLE . . . .
: COURSE : VOR SELF TEST DISABLE
VOR SELF TEST DISABLE
.
..
"-Pi
..
. ... ... : b-l
: 2 - L :
:
:
:
:
AIRSPEED
SENSOR
:
.. .. .. .. .. ..
BACK COURSE MODE INPUT : I : : : 1 3 : 59oe-z

BACK COURSE INTERLOCK-

- . . .. .. . 12
. -
M;IECi)-: -y m
59 -
- AIRSPEED SIGNAL
:
.
. .
:
.
J1

.. .. . . . . BACK COURSE EXC

: : : :
58
bD - AIRSPEED EXCITATION H

.... ....
BACK C a R S E MODE 29-25 AIRSPEED EXCITATION- C
.
. .
. .. .. .. .. : : : : : : 8bDE-2- :

. . . . :
.
:
.
:
.
:
.
:
.
:
.
(Jl)
... ...
Y5
Yb
Y?
:
:
: . . .
DISTANCE
DISTANCE
DISTANCE
SHUTTER +
SHUTTER -
RECEIVERS 2bVAC HOT p
. 10
2
. . . . .
9
.... ....
... ... ... ... .. ... .. .. .. ... .
- .. ...
YB -: DISTANCE RECEIVERS 2bVAC GRD : : f : : 1
-T :
...
Y9 DISTANCE RECEIVERS Z COMK)N
50 : DISTANCE RECEIVER UNITS X . . . . .
Y
. . . . .
.
.. ..
51
52
: DISTANCE
DISTUCE
RECEIVER UNITS Y
RECEIVER TENS X
3
. . . . .
b
.... ....
53 :
. . . . DISTANCE RECEIVER TENS Y 5 . . . .
5Y .
. . . .
DISTANCE RECEIVER HUNDREDS X : : : : : 7 ..
..... ..... ..... .....
:
.
.... :a
55 DISTANCE RECEIVER HUNDREDS Y : f : f : 8

...
: : : : : COMPASS

.. . . .
: : : : : :
..
328AdA
.. .. ..
..-. ..-. .-._
- : : ( J l ) (52)
9-1
.. COMPASS HEADING X . : : : : . .
. 2
. . . . .
. . .
: 17 --T
10-2
: 18
-
-
..
.- .:_ .-. . -.. . COMPASS HEADING Y .
.. :.
.
... :.. .. :..
..: 3.. :..
:
11-3
.. ..- ..- .-. C W A S S HEADING Z
.. .. .. .. .: + :
:
. :.
: 19 2
.. .. .. ... ... ..-
.. .. .-. .. .. .. 115 VAC POWER . .- - .
... . .. .. .. . . ,
... . . . . . . ,. . . . .
28VDC POWER
-.
. . .. .. ... ... ... GROUND . -.. ...
COWASS MONITOR + : 3
9
-
14
-
2
5 : :
: 5 . . . HEADING D A W H ' . : 2 : : b l l : : f 9 . COWASS DATA X
.... ....
... ... . . . . .. ..
... ...
: Y HEADING D A M C' : : . ? Y : : f 50 COWASS DATA Y

.. .. .. .. HEADING D A M H ' . : 33-b . 3

I
-
I I
.. 51
. COWASS DATA Z .. ..
.. ..
..... ...
HEADING DATLU C' : : : 23-71; :
. . .. .. .. .. HEADING D A M LOAD RES (10K) : : : : 17 : : : :
13 :
. COURSE DATUM H' . . : : : 9 .. PILOTS COPILOTS
.... .... . . .
... ...
12 COURSE DATUM C '
... ...
: : 8 DISENGAGE DISENGAGE

-
: : : : COURSE DATUM H' BUTTON BUTTON
: : : : .. .. -
-
COURSE DATUM C'
. .
.~ 1 -
: . . : : : :
:
COURSE DATUM LOAD RES (10K)
COhPASS LOW LEVEL FLAG +
: bb AUTOPILOT DISENGAGE
.~. .
30
- .
47 5 :
:
:
..
b7

.... ... ...

2Y
... ...
COMPASS FLAG 11 13 AUTOPILOT DISENGAGE
: : :s+ AZIMUTH CARD ERROR CT H'

-
21 13
20 _ . . S b A Z I W T H CARD ERROR CT C' . 12 .- . .
13 . : : :s+ AZIMUTH CARD RATE G2 . 1Y . . .
. .
.
1Y : : :s+ A Z I W T H CARD RATE C2 : 15 ... ... : : SENSING
11
12
AZIMUTH CARD SERVO D R I M M I
AZIMUTH CAW SERVO DRIVE C1-lb
17
... ....
:
:
:
:
UNIT
395A-W @
15 2b VAC HEADING PWR 52 . I . I. . .
. l R a.
LL>
. . . f
.
lb 2b VAC POWER COM
t o 4 RUNWAY LOC POS XMlR X -
- 28
: 5Y
:
b5
8 .
ROLL RATE M T D R GRD
115 VAC POWEE
A
B
11 -n- RUNWAY LOC POS W T R Y
-
12 -I+ RUNWAY LOC POS XMTR Z -
-
2?
22
:
:
32
31 :
ROLL RATE EXCITATION C
m L L RATE EXCITATION H
13
1Y -
+
RUNWAY LOC SERVO DRIVE M2
RUNWAY LOC SERVO DRIVE C - 23
2Y
:
: .
.-. .
.-
29
.
I :
..
ROLL RATE SIGNAL X
.- ..
. .
G

...
15 RUNWAY LOC RATE G2 2b : : : (PITCH)
..
l b -& RUNWAY LOC RATE C2
5- RUNWAY ALT SERVO DRIVE C -
-
25
34
:
: .... ....
:
: 10
-8
-
-
PITCH RATE MOTOR GRD
115 VAC PWER
. .
A
B
9-
7 s+
RUNYAY ALT SERVO DRIVE U2
RUNWAY ALT RATE C2
33
35
:
: ..
..
..
.
:
:
32
31 -
-
PITCH RATE EXCITATION C
PITCH RATE EXCITATION H
E
F
b S b RUNWAY N T RATE G2 3b :
.
: 29
. PITCH RATE SIGNAL X
. .. G
4 RUNWAY ALT POS XMSR X-
- 38 :
. .
....
. . .
. .

-
1
RUNWAY ALT ws m Y
- .. ...
.....
2* 37 : : : YAW RATE
3-+ RUNWAY ALT POS XhTR Z 32 : . .. .. : : OIRO

:
-
. .-
17
18

:
8 4 - 2b VAC RUWAY PUR
9 - b 2b VAC RUNWAY FWR COM
RUNWAY FLAG +
RUWAY FLAG

RADIO ALTITUDE +
-
-
- 53
51
Y9
Y8
. ..
5
:
:
:
:

: f .
-
.-
:
:
:
.-
.-
..
:
:
:
.-
.-
1 RADIO ALTIMETER
08bOF-1
(PlB)
22
339H4 )
:
:
:
:
bb
10
51
50
.

..-
Y8
- .
:
....
YAW
115
YAW
YAW
YAW
RATE MOTCU Q(D
VAC POWER
RATE EXCITATION C
RATE EXCITATION H
RATE SIGNAL X
:

.
..
:

.
..
332c-2
A
B
E

G
:
:
:
:
RADIO ALT1TU)E
RADIO ALTITUDE MONITOR + 1
Y
Y
:
:
:
: : : .
23
12 .
:
.. .. . .
.. ..
: 37- hOA LIGHT CONTROL . . . . . . : ; I . .-
. . . . . . .. ...
: 3b-
: 38-
: :
MDA LIGHT TEST
MDA LIGHT EXCITATION
A L T I N D E E X 1 OVERRIDE 200 F T :
.: .
41
.:
.
.: .:
. .
.. : GRD
B
..
~.
..
...
..
.....
-..
..
.
. ..
: : RUNWAY SYMBOL 200 F T ALT TRIP Yb : :
: : MIDDLE MARKER TRIP 93-29 : : : . .

AP-103F/FD-l09G Gulfstream I, Interconnecting Wiring Diagram (Sheet 2 of 4)

Figure 462

May 1/67 22-03-00

Pages 401/161, 401/162
 COLLINS
MAINTENANCE
MANUAL

FLIGHT
ANNUN- COWSE PEDESTAL DIRECTOR INSTRLWNT FLIGHT KME SERVOS
AUTOPILOT
CIATOR INDICATDR CONTROLLER INDICATOR WIRE FUNCTION WLIFIER CWUTER COLPLER MISC MISC WYER MLIFXER EMRGENCY
WIRE N K T I O N AILERON MISC DISCONNECT
@ 331A-M blVEdG 3298-8G IYVC-IF 5b2A-5G IblE-1 SbZC-V
JIA JIB J I A 110 JlA JIB 3%3 121A-2
JI JI
JIJ2 J I Jl J2 J5 11 JZ
.. .. .. .. .. .. (TP)
.. (Bp)
.. (TP) (Bp) (TP) (Bp)
.. .. .. .. ALT . (TP) tap)
. .
.. .. .. ..
I
.. .. . ..
.. .. .. .. :
..
:
.. ..: :
.. ..: . :.. Sih;OQV
... .
.
.
.
.
.. .. .. .. A-TITUDE E?RCR 4 ' : : 3 3 : : :
590A-3E
lb
:
: Y1
. ..
.. .. . . .. .. .. : . .
.. .. v
ALTITJDE ERROR C' : : 2 3 : : : 27 Y2
.. .: .: :
. ALTITUDE HOLD MODt i h P U T :
.. :
.. : : . 5 3

..
..
..
..
..
..
*
.. ..
.
:.
. ..
.
.
:
.. ALTITUDE HOLD W O E [SENSOR)
ALTITUDE YOLD MODE
ALTITUDE INTERLOCK
:
:
.
:
Y?
:
:
- :

:
Y0-39
27 : .
.
.
.
..
: 3 9
.. ..
.. .. .. ... ALT:TUDE INTERLOCK : : Yb-39 :

-
.. .. .. .. ALTITUDE OFC : : YB : . 33
GS ON . Y
.. .. .. .. ..
.. .. . . ..
1 1 5 VAC POWER
AC GROUND .. ... ... ... 3
I?
;
-g I
. .
.. .. . .. .. .. : :
.
.. .. 39
Y2 :
'13
?Y
ALTITUDE GAIN CHANGE E%CITATIOh
ALTITUDE GAIN W N G E NO. I . .:
.. .. : Lis ALTITUDE GAIN CHANGE NO. 2 . .
. .. Y3
Q . .
.. .. .. .. MARK : .. ..
... . ...
BCti :
... ..
.. .. .. RECV :
. .. .. . .
.. .. .. .. :
..
:
.. 9
..3 :
.. ..: :
.. k
. .
.. .. .. . . .
.. .. .. ... 1 1 5 VAC HEADING PWR
1 1 5 VAC ATTITUDE PWR
:
:
55-55
5 b V - b :
. :
: - - : c . .
.. .. ... ... .
..
..
...
..
.
..
115 VAC C O W A N D PUR
1 1 5 VAC RUNWAY PUR
b 5 : . : : . : e GRD
: bl -
... .. .. ... 1 1 5 VAC PWR COM

--...
.. .. .. .. .. .. .. .
~

b3
.. :. .
- .
U-ql- DC GROUNC i---f-I-?b GRD

. .. ..
. .
e-lb-
g : : :
28 V D C POWER :
.
:
.
: . : 2 5 : B C :
:
AILERON SERVO POWER
AILERON SERVO POWER
:
:
:
:
I
2
b I J
V
: 2k : : . 1 9 -
25 VDC POWER (REG)
5 VACIDC L I G H T i h G
5'1 2Y : b l
ELEVATOR SERVO POWER : . I-0 :b : Y
: 25 : : : 20- 5 VACIDC COM ELEVATOR SERVO POWER : : 2- 0 : x
... ..
.
..
.
: : 95-
.
.. ... ... :
:
: Y?-
: 35-
. . .. .. : : Y9- . . . . . .
: GA: : .. .. .. ..
: SUTTOh : .. ... ... ...
.. . . .
..
3399-2-330
. . .i
il: . . . . (J1) :
.. .. . .. ... ... ... GO AROUND ACT TRIM ENGAGE VOLTAGE D : L
.
.. . .. . TRIM ENGAGE GROUND E . n,
. .
.. .. . .
... .. . .
. ..
..
.. ..
. .. .. .. .. : :
: INDICATOR
TRIM
. L : : : . : 327D-lw
.. .. i
.. .. K
J
:
: : .
: : HEADING MODE 28 VDC POWER
. .:
... ..
. H
.. . . . : : : WOUND 0 1
.. .. .. ..
.. .. ... ... ... ... . .. .. ..
TRIM MOTOR CONTROL F-+

...
TRIM MOTOR CONTROL
E - - . . u - - - C
. . .. ... ... ... .. ..
. .. .. @
=IA
.. .. .. ... ... ... .. .. AILERON T R I l INDICATOR
.. .. . .. .. . . AILEROh TRIM NDICATOR
.. .. . . . . .. ... ... ... RUDDER T R W INDICATOR
RUDDER TRIM INDICATOR
uh-
-*R
.
..
.
.. ..
.. ... ... ... N I L ARM - - : b-32 :
.. .. ..
..
N I L CAPTURE : 39-39 :
.. .. -
.. .. .. ... ... ... GS ARM b-3b :
..
..
..
..
...
. ..
.. .. ..
.. ..
GS CAPTLRE
GS EXTENSION
GO AROUND -
-- 6-31
'42
Ib
-
- 3E
33
:
:
:
0. . I N I L ARM ANNUNICATOR +
N I L CAPTURE ANNUNCIATOR +
GS ARM ANNUNICATOR +
GS CAPTLRE ANNUNCIATOR t
... ... . . . . GS EXTENSION ANNUNCIATOR +
.. : : : 3'1- SO AROUND ANNUNCIATOR
. . . . . . ALTITUDE ANNUNCIATOR
: .
**
.. . .. .. .
...
. 3ACK COURSE ANNUNCIA
..
.
.. .. .. ....
..
..
...
. .
.. .
.. : Y9 -
-
.. .. ... ... :
:
50
51 -
... ... ... .. .. . : 52 - M T E OF TURN FLAG - J .. .. .. .. .. .. .. ..
. .. . . . . 1 5 : . . . 59 COWUTER M4NT
... . .. .. .. . .
. .. . . .. ... 1 9 : :
:
:
:
<.
A: :
18 i X T PITCH STEERING A
EXT PITCH STEERING 5
... ...
9 : iq
. . Y 9 f : : -8- 25 AC PITCH STEERING A
. .. : Q '10: : : 5:. . 2b AC PITCri STEERING 0
... ..
. .. .
. . 3 5 : : : : 27 PROCESSED PITCH DATA A
.
..
..
.. ... .. .
. . . 25 : -. .
9 ,
i
: : 28 PROCESSED P:TCH DATA B
. . .
. . ... ... .. . .. .. 1 : 6 : : 2 9: :
: :
.
57
bD
INTERNAL PITCH STEERING OFF +
ALT HOLD OFF t
.. .. . . .. . . : : sv
... ... ..
: 1 9 : 18 : E X T m L L STEERING A
.. .. . ... ... : 9 . : : SA 1 9 : EXT m L L STEERING B
.. .. . ..
... ...
.
... . . ... i i: : sv 25 : PROCESSED BANK W A

. . . ... . ..
. . @:;
... .... :
: SA 2b
sv
: PROCESSED 0ANK CWP B
PROCESSED BANK l3TA A
.. ..
35 : 35 :
.. .. .. . . . : PROCESSED SANK DATA B
... ... ..
.. .. : 2 5 : SI 3b :
. .. .. : I 7 : : : sv 5Y : EXT BANK O l l D A
..
..
..
..
.
..
. .
. . ..
. .. .. : 7 : : : SA 55 : EXT BANK CUD 3
. . . . . : 1 8 : : 57 : INTERNAL ROLL STEERING OFF +

AP-103F/FD-l09G G u l f s t r e a m I, I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 3 of 4)
F i g u r e 462
May 1/67 22-03-00
Pages 401/163, 401/164
 COLLINS
MAINTENANCE
w
FLIGHT
ANNUII- W S E PEDESTU DIRECTOR SERVOS
INSTWENT FLIGHT WD€ AUTOPILOT EERbENCY
CIATOR INDICATOR COHTROLLER I N D I U T O R Nmnw COMIVlER
WIRE MPLIFIER COUPLER USC USC POWER *RCIFIER WIRE NHCTION ULERDN usc DISCONNECT
331- b11)E-X 32-
33YC-3 l2lA-z
JI J2 JI Jl J2 J3 JI J2

. . . . . .. . . . 2D . . .
PITCH CONTROL SIGNAL
... ..
c
D
:
:
:
:
:
:
PITCH CONTROL EXC B
...
... ... ... ...
. 22. ... f

.... .....
E - - - N R N CONTROL EXC A .
. . . 21 . : .
F f f : TLUN CONTROL EXC B . . . . 22 : -.. -..
.
c . - .- .- TURN CONTROL SIGNAL . . . . . . 20 :
... -
....-
N : - - I N T MOTOR CONTROL VOLTAGE . . . . . . : b2

. . . . .
I N T BbVAC WTOR EXCITATION C 7
I N T WTOR RATE SIGNAL . . . . . .
2Y
: b3
:
.... ...
I ; . . I N T MOTOR SIGNAL C W N . . . . .
. . . . . . I @ ... 29...
: ... .
..
.....
28VDC PANEL LIGHT PUR
. . . . GROUND .. .. .. .. .. .. : GRD
.... ..-- ...
x : : : . . . . . .
Y I . : ENGAGE VOLTAGE f r ~ ~
.. .. .. .. .. ..
3 1 : ..
.. ... . .
.. ....
ENGAGE PULSE . . . . . . . 5b
....
.....
DISENGAGE VOLTAGE . . . . . . 37
. . . . ENGAGE READY . 55 ..
d - - - ALTITUDE H M D MODE + .
. . . .
.
. . .
f .
38
. ... ..
HEADING SYNCH CLllOvl
115 VAC AUTO PILOT PUR
115 VAC POWER
- g . . .
. . . . . .
.. ..:
38
@
7 :
. .
--. ...
I N T 2bVAC MOTOR EXCITATION H : : . . : 23 :
.t .. .. .-
f
. .
. . . ENGAGE INTERLOCK
. . . . . .. . .. .. .. .. - : 5Y

. . . .
AILERON CLUTCH VOLTAGE
ELEVATOR CLUTCH VOLTAGE
c . . >
. . . . . .
: G

. . . . . MJDDER CLUTCH V O . L . . T . A G E T
.x . :. .: .: . +28VDC AUTO PILOT PUR
.. .. .. .. .. ..
,
... .... .... .... SPARE
.... ... ... .... .... ... . .
.. .. ... ... .. .. ... .~
. .
.. ... ... ... .... .. .. .. .. .. ..~
.
.
.. .
.. . .
.. .. ... . ...
... ...
... ... ...
. . .... .. ...
.~
.. ..
.... .... .... .
..
. . . . ..
. ... ... . . .
..

io. ANNUNCIATION VARIES WITH THE PARTICULAR INSTALLATION. I N THIS INTERCONNECT ANNUNCIATION I S
28 VDC; OTHER OPTIONS MAY BE PROVIDED.
SYhSOLS USED:
11. m E 5b2C-Y AND 5b2A-5G SHWLD BE MOUNTED AS CLOSE TOGETHER AS POSSIBLE, PREFERABLY ON A DUAL
SV TWISTED SHIELDED PAIR-ADJACENT WUNT. THESE SIGNAL LEADS MJST BE TWISTED AND WIRED POINT TO POINT BETWEEN THE UNITS. THE
SI WIRES AS SHOWN ON DRAWING TWISTED PAIRS SHOULD BE KEPT AS SHORT AS PRACTICAL AND MJST BE SHIELDED I F OVER TWO FEET LONG-
SG SHIELD TIED TO OROUND AT UNIT
SI SINGLE SHIELDED WIRE 12. TOTAL WIRE RUN FROM BUSS TO 121A-2 TO 5b2C-9 TO 33'tC-3 (PIN B) FOR EACH PRIMIRY SERVO K I S T NOT
XI ALL 51 SHIELDED TIED TO X 1 ETC. EXCEED 90 FEET I F A f f i 20 IIIRE I S USED. WHEN GREATER THW QD FEET, INSTALL TERMINALS AT 5b2C-Y
STY FOUR WIRES TWISTED WITH SHIELD WUNT AND RUN AWG 2D WIRE FROM Sb2C-Y TO TERMINAL WtC-3 P I N B.
0 NOTES
POWER FROM A PARTICULAR C R C U I T BREAKER OR FUSE MAY PROVIDE POWER FOR MORE THAN ONE EQUIPMENT-
13.
mis WILL BE NIDCIATED I THE INTERCONNECT
N POWER CDLW BY A LETTER wIm AN OCTAMN SYMSDL AROUND
NOTES: I T . CAPITAL LETTERS FOR DC AND LOWER CRSE LETTERS FOR AC.

1. REFER TO THE INDIVIDUAL INSTALLATION MANUALS FOR COWLETE INSTALLATION INFORMITION. A,

-- 8, Cr D. G - 28 VDC 5 AMP a , b, C, -
11%'Y O 0 HZ 1 AM'

2. SPEED DISPLAY I S COVERED BY A REMOVNLE MASK.

E
F
H -
28VDC ANNUN D I M R
28VDC PANEL LITES
B A W
-
c , d , e, f, h- 115V +DO HZ 2 AW
k -
g 5 VAC D I M R
115 VAC YOD HZ 3 AM'
3. ALL WIRE SIZES ARE NO. 22 UNLESS DESIGNATED OTHERWISE BY NUHBERS I N SPUPSIES. SHIELDED WIRES ARE GROUNDED AT ONE END ONLY.
1Y. WITH TRIM INDICATOR CONNECTIONS AS SHOWN AND THE REVERSING LINKS INSTALLED FOR CORRECT SERVO
8. SHIELDS ON THE NAV RESOLVER LEADS FROM THE NAVIGATION RECEIVER SHOULD E€ GQOWDED AT THE 51RV-1. PHASING THE PRIMARY SERVO CAPSTAN SHOULD TURN QOCKWISE WHEN VIEWED FROM THE CAPSTAN END UNDER
THE FOLLOWING AIRCRAFT ARITUDES:
5. FOUR WIRES W I S T E D WITH SHIELD FOR C O W A T I B I L I T Y I N FURRE ARINC INSTALLATIONS.
AILERON -- LEFT BANK
b. THE AUTOMATIC FLIGHT CONTROL SYSTEM AS CONNECTED I N THIS DRAWING REFLECTS LOADS AS FOLLOWS:

AFCS LOAD CIRCUIT REQUIRED LOAD AWITIONAL LOADS

ELEVATOR
MJDDER - PITCH DOWN
RIGHT YAW

15. YAW D M E R SWITCH AND BAO: COLC(SE SWITCH ARE SOLENOID HELD MICROSWITCH bETI-T AND SETI-T OR
200 O W TO-FRQM 100 OHMS JUWER BP-'t3TO BP-33 OF 51RV-I EQUIVALENT RESPECTIVELY.
500 OHMS GLIDE SLOPE POINTER 200 OHMS JUWER TP-8 TO TP-2 AND TP-3 OF 51RV-I
500 OHMS GLIDE SLOPE FLAG 250 OHMS JUWER TP-21 TO TP-Zb OF 51RV-1 lb. THE GA WTTON WILL NoRMIII..Y BE LOCATED ON THE CONTROL WHEEL.
500 onus LOC FLAG 250 O W JUWER W-32 TO B P - Y l OF 51RV-1
500 OHMS COURSE BAR 250 OHMS JUhPER W-34 TO BP-30 AND BP-Y8 OF 51RV-1 17. OPTIONAL CROSSOVER SWITCHING OF STEERING INFORMATION MAY BE PROVIDED BY USING ALTERNATE WIRING
AS SHWN I N COLLINS DRAWING 7?2-+52>DDl.
?- THE POWER FOR THE COWASS SYSTEM MJST BE OF THE S M PHASE AS THE REST OF THE AUTOMATIC FLIGHT CONTROL SYSTEM.
18. A PAIR OF 112 WATl 10% RESISTORS SHOULD BE SELECTED TO GIVE FULL SCALE TRIM INDICATOR MOVEhENT
8. POWER LEADS DENOTED BY "DIM" SHOULD BE TIED TO COCKPIT LIGHT DIMMING CIRCUITS. WHEN CONTROLS ARE OVERPOKRED UNTIL SERVO CLUTCH SLIPS. THE RESISTANCE SHOUD BE SPLIT WITH
HALF ON EACH SIDE OF TRIM INDICATOR WVEMNT. THE TOTAL RESISTANCE VAL* SHOULD BE GREATER THAN
4. SENSING W I T 3+5A-Y( ) AND RATE U R O 3320-2 SHOULD BE LOCATED AS CLOSE TOGETHER AS POSSIBLE. 5K O W .

19. ALTITUDE TRIP POINT I S N W L Y ADJUSTED TO 200 FEET BLT A DIFFERENT TRIP W I N T MAY BE SELECTED
I S DESIRED. CONSULT AL-1'31 SYSTEM MINTENANCE MANUAL FOR SPECIFIC ADJUSTMENT PROCEWRES AND FOR
ALTITUDE TRIP WIRING INFORMATION.

AP-103F/FD-l09G G u l f s t r e a m I, I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 4 of 4)
F i g u r e 462

May 1/67 22-03-00

P a g e s 401/165, 401/166
 a
COLLINS
MAISTEKANCE
w MAKUAL

77H6.3402
FLIGHT SERVOS
ANNUN- C O W PEDESTAL DIRECTOR INSTRUMNT FLIGHT MODE AUTOPILOT EEffiENCY
CIATOR INDICATOR CONTROLLER INDICATOR WIRE FUNCTION 4HPLIFIER COWLTER COUPLER MISC MTSC POWER MLIFIER WIRE N Y C T I O N AILERON MISC DISCONNECT

@ 331A-bA blSE2G 329&8G 3YYC-lF 5b2A-5G IblE-1 33YC-3 l2lA-2

J I A J1B J1A J l B J1A J1B

-
J1 52
J1 K JI J1 J2 J3 (TP) (W) (TP) (BP) (Tf') (BP)

-E -
. . .
. . .
...
.. ... ..
.
....
.
.
....
.
..
:
:
:
:
:
52
b?
--
7-6
-8
-9
P I T M ATTIT.DE KUI H
P I T M ATTITUDE ERROR H
P I T M ATTITUDE ERROR C' -
-
'

-
PITCH A T T I T W E SERVO D R I M M-26
PITCH ATTITUDE SERVO DRIVE C
V
1 2 8
2
21
25
2
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
b!

13
1Y
15
- :
:
5+
AILERON
28 VDC
AILERON
AILERON
AILERON
AILERON
FIELD NUMBER 1

FIELD NUMBER 2
SIGNAL C
EXCITATION C
-c
-
--
PCSITION EXCITATION H
A
6

E
F
G
:
:
:
:

:
:
: : : : : Ib : S+ ALIERON RATE EXCITATION
- n H :

-
10-?- PITCH ATTITUDE RATE G2 23
... ... ....
-+

-
: 11-6 P I T M ATTITUDE RATE C2 29 : : : : 12 AILERON PCSITIOli SIGNAL L :
: 25-P- BANK ATTITUDE RATE C2-39 : : : : 11 -+ AILERON S E W 0 GQD R :
.. : 29-6 BANK ATTITUDE RATE G2-33 : : : : 17
... 51- AILERON W T E SIGNAL 5 :
.... ....
..
..
. ..... ..... :
:
23-
22
BWK ATTITUDE SERVO D U M C
BANK ATTITUDE SERVO WJM M2
35
36
:
:
:
:
:
:
:
:
.
.
.
. . .

-
: : : : :
.. . .
... ... .. ..
f 21-?- BANI( ATTITUDE ERROR C' ___.C_ 31
. : 2D-b BANK ATTITUDEERROR H ' P - 2 : : : :
... ..
..
.
..
..
.
.. ....
..
:
:
:
:
:
59 -cc- BANK ATTITUDE MON H
-Y
33
: : 33-
: 18-
2b VAC ATTITUDE PWR
2b VAC PWR CDM
I H LEVEL FLAG +
tym
HG
GYRO HIGH LEVEL FLAG - -- ; 5 1
38
I
53

29
39
:
:
:

:
IO
:
:
:

:
:
:
:
:
:
:
:
:
:
:
M,TQ
REF
332~-ii
J1
I
:
:
:
..
..
..
...
..
..
AILEROh ENGAGE VOLTAGE
AILERON ENGAGE VOLTAGE
I ;
: B
-.. ...
:
i
F

-
ELEVATOR
.. .. .. : i : : GYRO MON + : 9 0 . : f : N
. . 3 3-
. 9c3 --
... ...- .
...
: 3- PITCH ATTITUDE CT X . . m : : : A :
bjE-S+- (J1) ( J 2 )

- i -
: 9x- P I T M ATTITUDE CT Y i . 2 0 : : : 0 : 5;EYEIELD NUMBER I A :
: PITCH A T T I T W E CT 2 c :
.. .. .. -5 0 :
.. .. . : 17 BANK ATTITUDE CT X . 3 0
. : f 0 : : Y 1 ELEVATOR F X L D N W E R -2 C :

...- - -
: 18-)k- BANK A T T I N M CT Y P O P E : : 13 4+ELEVATOR SZGNAL C E :
.. .. -
. . . .
- -
: BWK ATTITUDE CT 2 F : : :
19
.. .. .. .. .. .. 19 ELEVATOR EXC1TATIOf.I C F
. . .
.... .... .,.. . . . .
:
115 VAC POWER
AC CROWD
12 --c--c P I T W A T T I T M X (6WTSTP.W)
. . . .. .. ..
: 53
G-
-H
:
:
:
15
l b -52-
ELEVATOR
ELEVATOR
12 A+ ELEVATOR
POSITION EXCITATION
RhTE EXCITATION H
POSITION SIGNAL
-
-
G
H
L :
:
:
.:PITCH:. .: : 13 P I T M ATTITUDE Y (BCQTSTW)
. . . .
. 5Y : 11. -* ELEVATOR SCRVO G?D R :

-
: : :
... ... ... ...
19 P I T M ATTITUDE 2 (BOOTSTRAP) 55
.. ..-
17 ----5+ ELEVATOR RATE SIGNAL 5
... :
...
:sulk : : P I T M C O W D H' : : 3b-15 :
.. -.. ...
L .:. ; ::
:
..
:WITON P1TC-I C O W D C' : : 2b-lb :
15 --cc 2b VAC ATTITUDE POWER
Ib Ob VAC PWR COM
: 53-5
: 51-27 ... . . .
.. . ;.
: : . : a :
. .. ._ . . ... ...
PITCH SYNC h W ELEVATOR ENGAGE VOLTAGE : A J

. .
. . - .. ..
"+

.. .. .. ..
. I
PITCH STEER + W
P I T Q I STEER + WWN
:
:
5-31
4-21
:
:
:
:
: .
:
i I .. ....
ELEVATOR ENGAGE VOLTAGE
..:. ...
B H

. . . ROLL STEER + LEFT 10 : . 3 1

.. .-
...
.
. I

... ... ...

ROLL STEER + R I Q I T 1 1 : : 2 1 : :
. . ..
..
.
-...
:
.. ..
. .
... ..
....~...
:
:
:
:
:
19-
3-

37-
3 . :

38-9-
39-b
V-BAR ROLL POS XMlR 2
V-BAR m u POS XM~R x
V 4 A R ROLL C D W D SERVO D R I M hy Z b2
V-BAR ROLL C O W D SERVO DRIVE C
V-BAR ROLL M W D RATE G2-bl
W A R ROLL COWND SG I COM-
-
-
. 5 8
: b D

b3

59
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
..
..
...

.
...
...
..
.
..
..
-....
..
.
...
...
.. .
...
-
..
.. .. .. :
:
95-P-
YY-6
V-BAR PITCH C O W 0 S I C COM
V-BAR PITCH C O W D RATE G2 -59
b2
:
:
:
:
:
:
:
:
:
: ... ... ... ...
.. ... . ..
- -~.
: : : : :
. : 43- V-BAR PITCH C O W D SERVO D R I M C b9

-
.. .. -.-.
...~ ....
: : : :

.-..
. .~
. .
:
:
. . . .
92
91-
V-BAR PITCH C O W D SERVO DfUK M b 3
V-BAR PITCH POS/OFF-SCALE BIAS bl - .. : :
..
:
:
.. .. ..
:
..
:
..
.
..
.. .- : 90
XMTR 2
V-BAR PITCH PO5 XMTR X- b0 : : : : : .. .. RUDDER
.. .. .. : 98 2b VAC C O W D PWR b 7 : : : : : 339c-3
.. ... ... : : : 39+
-
2b VAC C O M D PWR COM- 59 : : : : :
-
-
( J I ) (J2)

.- 38 bi E+
. . . . . . .
: : STEER FLAG bY : : : : % RUDDER FIELD WhBER 1 :

-
9- A
I @
f

-
.. ... ..- :
-. ._
:
. . ..
3-
P I T M COWUTER MON +
STEER FLAG +
: 12 12 :
:
:
:
NAV ;CW
51RV-1 : Y 1
?a VDC
h RUDDER FIELD N W E R 2 - B
C
:
:

-
. +
: 33 : : IO
C O W N D SERVO MONITOR
GLIDE SLOPE DEV + LP
: b5-28
: 3 2 :
:
:
:
:
(TP)
8 a; Y3
99
RUDDER S I G M L C
RUDDER EXCITATION C
n-
E
F
:
:
:
:
39
3 5 :
a
: :
:
11 -c.6 GLIDE SLOPE DEV + WWN
I2 -c-9- GLIDE SLOPE L W L E M L FLAG +
-
. : 2 2 : : :
21 :
YS
9b -+
RUDDER POSITION EXCITATION
RWDER RATE EXCITATION H -
-
G
H
:
:
.-
:
. :. . . . .
: 13 GLIDE SLOPE LOW LEVEL FLAG 22 92 f 5% RWDER P O S I T I W SIGNAL L :

..1. :.. GLIDE SLOPE HIGH L E M L FLAG +

.: ;. : R :
.:
Y1
.: . . .. .. :
. 11
. f
. 27 RUDDER SERVO G?D
s :
cspc
Y7 %
-
.. .. RVDDER RATE S I W A L
. . . :
. .
COURSE RSVR A 9 16
. . .: . (BP) . . . . .-. .. W D E R ENGAGE VOLTAGE AB B
.
:@; i :
f
epc
rspc
+STY-
COUISE

COURSE
mu
RSVR H
s
...... 22
.. .. . . .. .. 21
-..
.. .....
RUDER ENGAGE VOLTAGE C

:
:
9
5
:
:
: 69- COURSE RSVR D
f S b COURSE Rsw E
29
25 . .
: b : f-5- COURSE EM1 F 2b
:
:
:
7
26
27
:
.. TO
TO
--
: 5 6 COURSE RSVR
FRMn +
G
TO
FROM + FROM
27
43
YY
m / L O C L W L M L FLAG + 91
VOR/LOC LOW LEVEL FLAG - .
92
. .
.
.
:
-.
28
.
.
:
.
.
.
.
.
. .
_ -
WR/LOC DEV + LEFT +
M R / L O C DEV + RIGHT
:
.
32 - 11
11-
10 - 40
39 .
.. ..-.
..... ..- ... ....- ..... ..... W R l L O C D N + LEFT 7 : . :

-
... VOR/LOC DEV + RIGHT -
. .
8-22-10
:
:
.. ..
.. -3738 -:
W W L O C H I LEVEL FLAG 17 . I 1 f : 50
..- ... ... ... ... ...
.. LOC FREQUENCY
..
YO :
.. ..
f 43-
.. .. 19 TO NAV .. ..
. . . 28VDC NAV REC POWER REC PWR . .

AP-103F/FD-l09G S a b r e l i n e r , Interconnecting W i r i n g D i a g r a m (Sheet 1 of 4)

F i g u r e 463

May 1/67 22 -03-00

Pages 401/167, 401/168
 COLLINS
3IAINTENAIVCE
MASUAL

FLIGHT SERVOS
ANNUN- COURSE PEDESTAL DIRECTOR INSTRUMNT FLIGHT MODE AUTOPILOT EMERGENCY
CIATOR INDICATOR CONmOLLER INDICATOR WIRE FUNCTION AhPLIFIER COWUTER COUPLER MISC MISC POWER AMPLIFIER WIRE FUIXTIO:v AILERON MISC DISCOhNECT

@ 331A-bA b19E-BG 3898-80 399C-1F 5b2A-5G 1blE-1 33YC-3 121A-2

J 1 A J1D J1A J 1 3 J1A J 1 3 J1 J2
J1 JZ J1 J1 52 53 (TP) (W) ( T P ) (BP) ( T P I (BP)
NAV RCVR
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. . . . -
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(TP)
19 PJAV CONT :
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.. ... ... ... VOR SELF TEST DISABLE .
.
.
.
.
.
.
.
: 15
. . . . 54 313J-3 :
:
.. ... ... . VOR SELF TEST DISASLE : 98- 55 (J2)
. .
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.
:
.
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VOR SELF TEST DISASLE

AACK COURSE INTERLOCK

YACK COURSE EXC
JACK COURSE K)DE
: : :
JACK COURSE MODE INPUT P 1 3
: : 2 -
..
:
.
..
..
:
..
..
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AIRSPEED SlGNAL
AIRSPEEC EVCITATIOh Ii
AIRSPEEC EXCITATIOI. C
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:
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..
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.
..
SENSOR
5908-2
J1

.. ... ... . . . .. .. . . . . .
8bSE-2
(J1)
:
: . .
: 45 : DISTANCE StIUTTER + . . . . . . 9 .. ..
: Yb : . . . DISTANCE SHUTTER - . . . . . . 1C . .
:
:
$7 :
48 -:
. . . . DISTANCE RECEIVERS 2bVAC HOT :
:
:
:
: : : : 2 .. ..
wJ: .. .. .. ..
DISTANCE RECEIVERS 2bVAC GRC
.. .. ..: :
.. ..: :
.. 1 :
. .
:
: 50 :
DISTANCE
DISTANCE
RECEIVERS Z COMMON
RECEIVER UNITS X . . . . . . 9
. . .. ..
: 51 : DISTANCE RECEIVER UNITS Y . . . . . . .
..
:
:
52
53
:
: . . .
DISTAhCE
DISTANCE
RECEIVER TENS X
RECEIVER TENS Y
.. .
.
.
.
.
.
.
.
.
.
b
5
.
... ...
: 5Y : DISTANCE RECEIVER HUNDREDS X : : . . : : ?
. .
:
..: 55
...
:
... . . . . DISTANCE RECEIVER HUNDREDS Y : : : : :

... .. .. ... ... ... ...

:
.. :
..
:
..
:
..
:
.. .
i Q COh'iASS
328AdA
:
: .... ....
. . . . . . . : : : : : : (J1) (J2) :
..
. ...
: 9-1 - :
.. .. : ..: ..: COWASS HEADING X .. .. .. .. ... .. :
.. ..2 :
.. . .
: : l?J . . . . .
: 10-2 -2 :
.. .. : ..: ..: COMPASS HEADING Y .. .. .. .. .. . . .: .3 :
.. ..
. .. ... ...
. . . . . . . .
:
: 11-3
: 1 8
- :
.. .: .: .: COMPASS HEADING Z .. .. .. .. .. .. : 9 : . .
... ... ... .. .. .. .. . . . ..
:
.
...
: 1 9 2
.
.. ... ... .. .. .. .. ;i+@ ... ..

-
115 VAC POWER
. ... ... ... .. .. .. 2 8 ° K POWER . . . . ..: ..
: .
... ... ... .. .. . .
.. .. .. .. ..
WOUND : : : : : : 27 . :
.. . . . COWASS hDNITOR c : 39-19-25 : : . .
.. ...
....
: : 5 HEADING DATUM H ' : : : : : b 11 : : : 4s COMPASS DATA X
..: ..: *.
. ... ... ... ...
HEADING DATUM C' :
:
:
:
:
:
: : 7
.
4 : : I 5a
51
COMPASS DATA Y
COMPASS De14 Z
...

-
dEADING DATUM H ' 33-$ 3
... ... ... .. . . . . .: i i. ; ; ... ...
. . . . .. .. .. dEADING DATUM C'
IIEADING DATUM LOAD RES (10K)
:
. . :
:
2 3 - 7
: 1
] :
7 : . . .
: 13 : COURSE DATUM H' : : : : : q PILOTS COPILOTS
:
. 12
. . .. .. .. .. COURSE DATUM C'
COURSE DATUM / I '
:
:
:
:
:
: 34-q
: : 8
. .. .. DISENGAGE
BUTTOtl
DISENGAGE
BUTTO!.
...
.
...
.
...
.
...
.
COURSE DATUIA C'
COURSE DATUM LOAD RES (10K)
..
:
..
:
.
:
24-
: 1
E 1 1
E :
i : bb -AUTOPILOT JISEhGAGE . .
. . . . COWASS LOW LEVEL FLAG + : * 7 : : 5 : : b? . .
:
:
:
:
29
21
. . .
:
.
:5?-
COWASS FLAG -
AZIMUTI< CARD ERROR CT H'
. 11
: 1 3
:
I :
: 13
: I
:
. . AUTOPILOT >ISENGAGi
. .
. .
:
:
:
:
20
13 : : :
:5 6
: S F
AZIMUTH CARD ERROR CT C'
A Z I L l U T CARD RATE G2
: 1 2
: 1 4
:
:
:
:
:
:
:
: .. .. . .
: : 19 : : : :-SA- AZIblUTk CARD RATE C2 : E : : : : : : SENSING

:
:
: :
: 12
: 15
11
. . . .
AZIMUilI CARD SERVO > R I M Kl
AZ1MUT.i CARD SERVO DRIVE C l
2b VAC HEADING PWR
-
__f_

: 5 2
17
lb
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
UhIT
395A-90
(ROLL)
@
: : lb . . . . 2 6 VAC POWER COW : 5 * : : : : b5 ROLL RATE K)TOH GR2 . . A
... .. . .
..
.
...
..
:
:
:
:
: 1 0 4
: ll--)c
RUfI!IAY LOC POS W T R -X
RUKWAY LOC POS XKTR Y -
-
22
27
:
:
.
:
:
..
:
:
..
:
:
..
:
.:.
6
32
:
:
.
115 VAC P O K R
ROLL PATE IXCITATIO?. C .
.
.
.
E

...
.. ... ...
:
:
:
:
:
:
: 12+
:
:
13-
lli-
RUNWAY LOC POS W T R Z
RUNWAY LOC SERVO D R I M M B
RUNVAY LOC SERVO DRIVE C
-
-
22
23
24
:
:
:
:
:
:
:
:
:
:
31
29 :
ROLL PATE IXCITATIOI. d
ROLL RAT= SIGNAL X
..
. .
F
G

.. ... ... : : : 1 5 4 RUNWAY LOC RATE G2 Z b : : : : : : : (PITCrl)

: : . .
..
. ..
..
..
.. :
:
:
:
:
:
:
lb+
5-
RUNWAY LOC RATE C2
RUNWAY ALT SERVO DRIVE C -
-
2
3Li
5 :
: : :
:
:
:
:
:
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-8
:1 -
32 -
PITCH PATE M T O R GRi.
115 VAC POdEH .
.
.
.
A

-.
.. ... ... :
:
:
:
:
:
:
:
4-
7s-
b S 6
RUNkAY ALT SERVO DRIVE H2
RUNWAY ALT RATE C2
RUNWAY ALT RATE G2
3
3 5 :
3
:

b :
:
:
:
:
:
:
:
:
:
:
:
:
:
:
:
31
29
-
-
PITCH PATE EXCITATIO~I C
PITCH RATE EXCITATIOIv H
PITCH RATE SIG:,hL X
.
.
.
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. . . : : : 1 4 RUNWAY ALT POS XlLTR -X 36 : : : : : .. ..
.. .. .. -3
.
. ..
.
..
. :
:
:
:
:
:
2-x-
3+
RUNk'AY ALT POS XYTR Y
RUNWAY ALT POS n l T R Z - 32
7 :
:
:
:
:
:
:
:
:
:
:
:
:
:
YAV ?ATE
GYRC
... ... ...
:
:
:
:
:
: 9
8 4
4
2 b VAC RUNWAY PWR
2 6 VAC RUNWAY PWR COW -5 3 51
:
:
:
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:
:
:
:
:
: bb . YAW PATE ,WTOR Gi1D
:
.
:
.
31dG-2
A
.. . . : : : 17- RUII'dAY FLAG + Li9 : : : : : @ RADIO ALTIVLTER : li . 115 VAC PCivEH
... ... ..
...
:
.. :
.. .. ..
: 1E- RUNkAY FLAG - 48
. : : : : : %OF-1 33H-( ) : 51 . YAk' RATE EXCITATIOI. C . .
.. .. .. .. .. .. .. (P1B) :
-./
>L . YA!? RATE EXCITATIO~T : . .
... . .. .. . . .
. . . RADIO ALTITUDE + 5 : : : : : 22 Lib : YAL' RATE S:G:.AL X
... .
..
.. .. . .. ... ... ... RADIO ALTITUDE - 9 : : : : : 23 :
.. .
.. ... ... . RADIO ALTITUDE WONITOR + 1 * : : : : : 12
.. ...
.. . : : : 37- MDA LIGHT CONTROL . . . . . . : E
.. . .. : : : 3b- MDA LIGHT TEST . . . . . . .. ..
.. .. .. : : : 38- MDA LIGHT EXCITATION . . . . . . .. ..
. .. .. .. .. ..
-.. .. .. ... ... ... ...
ALTITUDE E X I OVERRIDE : : * 1 : : :
.. ..
. .. .. .. . . .
RUNWAY SYMBOL 290 FT ALT T R I P
!4133LE MARKER T R I P
Yb
y3-29
: : :
:
:
:
:
: .. ..

A P - 1 0 3 F / F D - l 0 9 G S a b r e l i n e r , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 2 of 4)
F i g u r e 463

May 1/67 22 -03-00

Pages 401/169, 401/170
 COLLIN s
MAIETENANCE
w MANUAL

FLIGHT SERVOS
ANNUI- CWAY PEDESTK DIRECTOR INSTRUMENT FLIGHT NODE AUTOPILOT EMERGENCY
CIATOR INOICATOR CONTROLLER INDICATOR WIRE FUNCTION AWLIFIER COWUTER COW'LER MISC MISC POWER AWLIFIER WIRE FUNCTIOh AILERON MISC DISCONNECT

@ 301- blYE-ZG 3898-80 IYYC-1F 5b2A-5G IblE-1 5b2C-4 339c-3 121A-Z

JIA JIB J I A J1B J 1 A JIB J1 Jl J1 JB
J1 52 J1 J1 J2 J3 (TP) ( W ) (TP) (e?)(TP) ( W ) (TP) (e?)
.. . . .. .. .. .. . .. .. .. .. .. . .
.. .. .. .. .. .. ..
ALTQ: :
.. ..
... ... ... ... ... ... ...
: : : :
:
: : SENSOR :
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.. .. .
: : : : : 590A-3E
. .
..
. .. .. . .. .. .. ALTITUDE ERROR H '
ALTITUDE ERROR C'
:
:
:
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3
2
3
3
:
:
:
: :
: lb
2? :
:
:
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.. ...
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... ... ... ...
ALTITUDE HOLD NODE INPCrr
ALTITUDE HOLD NODE (SENSOR) .. .. : : 'io-3Y . .
. . . . ALTITUDE HOLD NODE : : Y?-27 : . .
. .
w.. .. .. ..
-
: : : ALTITUDE INTERLOCK f : : : : 3 9
. .
ALTITUDE INTERLOCK : : Yb-39 :
...
... .
..
...
.
..
...
..
...
.
ALTITUDE OFF
GS ON
115 VAC POWER
:
YY
..
..
-. .- .
.. .. ..
: Y E
39
:
Y5
: 3 3

...
. 3Y
.
... 3b :
: 4b
.
..
.
.
.
..
.
.
.. .. .. .. .. AC GROUND
. .. .. .. . . 3? __r_
... ... . . . . . . . . .. . 39 : 'i3 .............
... . . .. .. .. .. .. Y2 : YY ALTITUDE @ I N CHANGE hi0. 1
.. .. .. .. .. .. .. . . . . . Y3 : Y5 ALTITUDE GAII, CHAlIGt
.. .. .. ... .. .. .. :
.. :
.. ..: :
.. ..: : MARKQI 1
. ... ... .. .. .. ..
...
BCN :
.. . . . : : : : : : . .
.. ... ... . .... .... .... : :
R E C V :
.. ..
.. .. .. .. .. ..
: : ' i 3 : Y
.. . . ... .. ..
.. ... ... . ...
.
...
. .
... 115 VAC HEADING PWR
.
..
.
..
. . . ... .. .. .. 115 VAC ATTITUDE PWR
.. .. .. .. 115 VAC COWdAND PYR GROUIIC : : E .
... ... ... .. ... ... ... 115 VAC RUNWAY PWR a; v j c PCI.:K . . P
..
.
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..
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..
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.
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I15 VAC PWR COM
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2 8 VDC POWER
..
:
.
..
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:
..
:
..
:
..
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..
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PRD
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RUCCEF: S E K K P W i h
HUDCEK siavo POWER

AILEROI. SERVO PCLER

8
I

-
--f-
. . .. : 2 5 VDC POWER (REG) : : 54-2Zy : b l : AILEROI. SEFiVO POWER

-
9 : :
. . . . . .
:
:
..
29
25
.
:
:
.
: 19
: 20
5 VAClDC LIGHTING
5 VAC/DC COM .
SPEED C O M N D DEV + FAST HIGH L E M L :
. . - . . = . -
0 :
: bS - ELiVATCR SCRVC POWE:?
. .
-
: : Y5 : : : : :
..
..
...
..
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..
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: 35
SPEED COMMAND DEV + SLOW COM
SPEED COmAND FLAG HIGH L E M L +
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.
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:
:
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-
; .
.
.
.
.
.
. . .
..: ..: 99.. .. SPEED COMAND FLAG COM
. .. : GRD 1 .
: GA:
:
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:BUTTON
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. . . . . .
.. .. ... ... . . GO AROUND MODE++ ROLL
AROWD h13N
GO AROUND NODE + P I T M Y2
:.
-'i-J;
- .:
YY 35
i TRIM
COUPLER
lirlA-lA
:
:
:
I. d _.
r - .- GO AROUND EXC . . . . . . : Q ; I (J1) :
. . . . .
... ... ... GO AROuIlD ACTUATE : : : : : 2 Y TRIX ENGAGE VOLTAGL 20 L
... ... ... . . .
... EXTERNAL STEER + WWN
; ; TRIhl EhGAGL GfiOUhC 32 : Irl
.. .. .. ... ... ... EXTERNAL STEER + U p $ 2 ; :. .: .. ..
.. .. ... -... ..
.
..
. .
..
GYRO NODE : : : 41-20 :
:
10 : .
.
.
.
... ... ... ...
HEADING MODE : : : Y7-21 bt :
.. .. .. N I L NODE : : : Yb-22 : 1? : : : mrx
. .. .. . . . .
.
APPROACH NODE :
.. :.
: Y5-23 :
- w-
- : : INDICATOR :
... ... tym NODE
: : : : : : 2 0 : : 327D-1W :

-
L
.. . . K : : : HEADING MODE . .
- : 21 : h : x c 115 VAC POWER 5
.
:
.
.. ... ... J : f : N/L NODE 2 : : : : 2 2
.. . . ..-
. . . . . H
.. ..: ..: :.. APPROACH NODE
..
..
.
... ...
.:
...
.:
...
2 3
.
...
: GRD
:
:
33-8s-
3 9 4 s -
GROUNL
TRIM IIIPUT UP
TRIM ISPLIT UP +
- 1
11
13--E
:
+
.
.. ..
.
..
.
.
.
.
.
.
. 33
39 :
: AILERON TRIM INUICATOR
AILEROh TRIM IXDICATOR --A
+ Q r
.. .. .. . . . . .. . . .. .. .. 52 : RUDDER TR1:l IllDICATOK
'.':
...
.
.. ..
.. .. .... .... ...
.
...
.
N/L ARM - : :
. .
:
.
b-32
.
:
. 53
:
:
35-s-
RUDDER TRIn INDICATOK
TRIM INPUT DN + 22 :
- R

.. .. .. ... ..
..
..
..
..
.. N/L CAPTURE- : : : 39-339 : : 3b-c TRIir, INPUT Dii -
. ... ... .. - - .. .. : ARM UP
... ... ...
GS ARK b-3b
.. .. .. ..
--
GS CAPTURE 8-37 : TRxE.1 LIP
.. .. .. .. .. ..
..
.... GS EXlENSION : : Y2-38 : RELAY GRD
. .. .. . . . . GO AROUND : : lb-33 :
- . N/L ARM ANNUNICATOR + . .
.. : : f 3 i ARM m U N
- N I L CAPTLRE ANNUNCIATOR + :

... . . .
: : : : : 3 8 TRIM GKD
RELAY W'h'li
- . GS ARM ANNUNICATOR + : : : : :41@):
~ - GS CAPTLRE ANNUNCIATOR + : : : . f 4 2
. ..
cs EXTENSION ANNUNCIATOR + .
.. .. .. : : : 3 Y GO AROUND ANNUNCIATOR
:
.
:
:
:
:
:
:
:
f 4 Y
Y 3
. . .. ..
ALTITUDE ANNUNCIATOR : : : : : r c
.* : : BACK COLRSi ANNUNCIATOR + : :-95 ... ...
.. .. : : : E
.. ..
ANNUNCIATOR BUS : 19.
. . O U T OF VIEW B I A S 20 : :
. .. . . ..
: 3 b :
.. ..
1
RATE OF TURN DEV + RIGIiT TO RATE :
' : u9-
. . .
. . . ... .. ..
RATE OF TURN DEV + RIG;(T OF TUKI
RATE OF TURI. FLAG + SE!1SCR
:
:
: : : :
.. ... ... ... ...
:
... ....
.. .. .
... . .. RATE OF TURI. FLAG - . . . . . . .
...
. .. .. .. .. ..
: : 1 5 : : : . 59 COMPUTER M3NT ... ...
.. ... .. .. .. ...
: : :: :
.. .
. : 1 5 : 18 EXT P I T C t i STEERIRG A
..' .. ..
... .. .. ... : : 9 : : : SA : 19 EXT PITCH SSEERIhG E
.. .. . .
..
..
.
... ...
.. ..
.. .. ..
...
..
...
i: 6: K35 x 1
Y Q . . . .,. . 25
% : 2b AC PITCH STEERING D: I
AC PITCH S E E R I N G A
... ...
... ... .. .. 7 27 PROCESSEL PITCH DATA A
.. .. .. .. f

.. .
. : : 25 E . 28-PROCESSEL PITCH DATA ; B
.. .. ... .. .. .. ... : : 1 n . : : . 57 INTERNAL PITCH STEERING OFF + :
.. :..
... ... .. .. .. ... ...
: : : : a : : bD ALT HOLD OCF +
.. ... ... ... ... .. ..
: I : i s : : sv 1 b : EXT m u STEERING A
. . .. ..
..
.. .... .... ... ... ..
...
.... .. ..
: 9
' 9 9
f
:
:
:
Sb 19
sv 2 1
:
:
EXT ROLL STEERIXG 3
PROCESSEC YATilK C W A .
.. ...
.. .. . :
..
sc. 2ir
...
: : @ Y O : PROCESSEL 3ANK CVP Y
.. .. . .. .. . .
... ... .. ... . 3 5 : : SP 31 : PROCESSEC 3UIK DATA A
.. . . . ... : 2 5 .. ..
.. ... ... . . ... . ... 2
:
:
.
SA 3b : PROCESSED SAhK DATA 3
.
. . . . . . .. .. . .. ..
.
..
: 1 7
: ? : :
S? 54
S I 55
:
:
EXT BANK CV,D A
EXT BAIiK C W 3 .. ...
.. .. .. . .. . .. .. . : : 1 E : : 57 : 1NTER:iAL R I L L S T E K I N G OFF + : :
I

- Diagram
AP-103F/FD-l09G Sabreliner, Interconnecting Wiring - (Sheet 3 of 4)
May 1/67 Figure 463 22 -03-00
Pages 401/171, 401/172
 a
COLLINS
MAINTENANCE
w MANUAL

FLIGLtT SERVOS
MINUN- COIRSE PEDESTAL DIRECTOR INSTRUMNT FLIGHT MODE AUTOPILOT EMRGENCY
CIATOR INDICATOR CONTROLLER ItICICATOR WIRE FUNCTION WLIFIER COMPUTER COUPLER MISC MISC POWER AWLIFIER WIRE FUNCTION AILEROh MIX DISCONNECT

331A-U bIYE-2G 3296-SG 3YYC-IF 5bZA-SG IblE-1 5b2C-Y 33YC-3 121A-2

JlA JIB JlA JlB J1A JL2 JI Jl J1 J2
J1 J2 J1 J1 32 J3 (TP) (BP) (TP) (3P) ( T P ) ( B P ) (TP) (8P)

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Y
.
.
.
. ..
.
.
.
..
.
.
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.
.
..
.
.
..
.
.
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.
.
.
.
.
.
.
.
.
-
.
.
21
23
22
.
..
.
...
.
.. .. .. .. . .
~

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..
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F
:
:
:
:
:
:
TURll CC:.T;IOL EXC A
TdRh CO!,TROL EXC 3
.
.
.
.
.
.
.
.
.
.
.
.
21
22
:
: . ...
G : : : TURli COI.T?OL S1GI.AL . . . . . . ci. : . .
N : : : 1:;T MOTOR CO!.TROL VOLTAGE . . . . . . . b2 . .
P : : : I N ? 2LVAC MOTOR EXCITATIOII C . . . . . . 2, : .. ..
.
R : : : 1i.T '.1OTO9 RATE SIG:.AL . . . . . . . b3
.. .
I b l T WTOR SIGI.AL COlfMOii . . . . . . . 2Y . .
2UVOC PA:lEL LIGYT PI!R . . . . . . . .
. . GROUND .. .. .. .. .. .. .. ..
x z : : . . . . . .
Y : : : ENGAGE VOLTAG;
z : . : . . . . . .
" . . . ENGAGE PULSE
5 : : : CISElrGAGE VOLTAGE
c : : : ENGAGE READY
d : : : ALTITUDE dOLL' MODE +

115 VAC PO\!Ek

. . . .
t : : :
u - :
v : : :

. . .
x : : :
'I . . .
.. ... ... ...
..
.. ... ... ...
. . . .
.. . . .
.. ... ... ... . . . . .
. .. .. .. . .. . . . . .
... ... ...
.
. . .. . . . .
.

10.
SY,%OLS USED:

SI TYISTED SHIELCEC PAIR-ADJACi:.7 11.

SI WIRES AS SdOWh ON DRAVIlvG
SG SHIELD T I E L TO GROUKD AT UI:lT
81 SINGLZ SHIELCE; WIRE
XI ALL 5 1 SHIELCEL T I E L TO X 1 I T C . 12.
STL) FOUR 'WIRES TJISTEC WIT!; SHICL:
0 :lOTES

13.
NOTES:

1.

2.
REFER TO THE II;CIVI3UAL 1I.STALLATIOt. \'AI.UALS FOR COhiPLETE IISTALLATIO:.

SPEE; 3ISPLAY I S COVEREL bY A REMOVULE .WSK.

II.FCR:AATIO!I.
a , b,
c, d ,
C, - 119 Y O 0 HZ 1 AMP
f , P, - 1 1 5 V Y33 :iz e AXP
E,
4 - 5 VAC D I W C R
3. ALL WIRE SIZES ARE KO. 22 UNLCSS >ESiGi.ATED OTiERWISC AY :IUI.IDERS I;r SQUAKES. SilIELDi: l I R E S A k i G2OUl.i& AT 0i:E E : . i OXLY. 1. - 115 V K 935 HZ 3 AP.P

9. SHIELDS O h THE NAV RESOLVER L E K S FR0l.l TnE %hVIGATIOI. RECEIVER SHOULC 3E GR0UI:DEC AT THE Slav-1. li. WITH TRI:l 1:rCICkTOR CO:,:.ECTIOt:S ilS SAC,::, Aj.3 T, i R3ERSI::G L I I l K S 1:;STALLEC FO': CORRECT SCRVQ
PHAS1t.G TdE PRIMPjiY SEZVO CAPSTA:. SHOLL; TJR:. CLOCI:\IISE ):HE:; VIEWE: F?OY TliE CAPSTAb END LI'.LER
5. FOUR !IIRES TWISTED WITH SHIELC FOR C O I O P A T I S I L I N Ili FUTURE ARINC I:lSTALL,$TIOt.S. W E F0LLCVIi.G A I R C W F T PSTITUCES:

-
b.

AFCS LOAD
THE AUTOMATIC FLIGHT COI:TROL SYSTil.', AS COIlliECTED II? T l i i S DRh\!ING 3EFLiCTS L G A E A S FOLLOWS:

CIRCUIT REQUIRED LOAC ACDITIOhAL LOADS

AILERO:.
ELEVATOR
RUDDER
-- LEFT SA
PITC~ 3
LEFT YA:r

200 OHMS TO-FROI 1LO OHMS JUMPER 3 P 4 3 TO 3P-33 OF 51RV-I 15. YAW 3AKPER SWITCH a,; 3ACl( COURS: S,;:TC,I ARE SOLE ,010 IiELD M1CRQYd:TC:' 6ETl-T AI<D SET1-T OR
5 0 0 OHMS GLIDE SLOPE POINTER 203 OHhIS JUMPER TP-8 TO TP-2 A X 0 TP-3 OF SIRV-1 ZCJIVALENT RESPECTI'XLY.
500 OHMS GLIDE SLOPE FLAG 2 5 0 OHMS JUMPER TP-21 TO TP-2b OF 51RV-I
530 OHMS LOC FLAG 250 OHfIlS JUMPER DP-32 TO BPY-I OF SIRV-I lb. THE GA 3UTTO:. WILL IIORf4ALLY 3i LLCATEL 0:.TiIE COi,TROL WHEEL.
SO0 OHMS COLRSE 3AR 253 OHMS JUWER DP-39 TO 3P-30 AflD 3 P 4 8 DF 51RV-1
I?. OPTIOllAL CROSSOVER N I T RItlG 1SFORSAT;OI~ MAY BE PROVIDCL BY USIPiG ALTERNATE WIRI!.G
?. THE POWER FOR THE COMPASS SYSTEM VIUST dE OF THE SAME PYASE A S THE REST OF TiIE AUTOMTIC FLIGHT COf.:ROL 8YSTE:l. COLL1:vS C 2 A
A S SHOW!, I:. -351.

6. POWER LEADS DENOTED BY "3Ibi" SHOULC 5E TIED TO COCKPIT L I G i i T DI:R*UlvG CIRCUITS. 16. ULC 3E SELECTED TO GIVE F d L L SCALE TRIM IIIDICATOR MOVEMENT
SERVO CLUTC:-' SLIPS. THE XESiSTAtiCE SHOULD E.E S P L I T Y I T i
9. S E X I N G U N I T 3Y5A-Y( ) Ah3 RATE GYRO 3326-2 SHOUL: DE LOCATED AS CLOSE TOGEiiiER A S POSSIBLE. :lDViMc:.T. THE TOTAL RESISTANCE V A L U SHOULL 2C GREATER TtlAl:
SK OHMS.
19. MTITULSTRIP mmr SI )(ORULLY ADJUSTED TO ZM FEET WT A DIFFERENT TRIP mItn
M Y DE SELECTED I F DESIRED- CONSULT AL-101 SYSTEM U N T E W C E W W FOR
SPECIFIC ADJVSTLENTPROQRRES WD FOR bATINDE TRIP WIRING INFQUUTIW.

AP-103F/FD-l09G Sabreliner, Interconnecting Wiring Diagram (Sheet 4 of 4)

Figure 463
May 1/67 22-03-00
Pages 401/173, 401/174
 COLLINS
MAINTENANCE
MANUAL

??2453O-ml
FLIGHT
ANNW- COLRSE PEDESTAL DIRECTOR INSTRLWENT FLIGiiT MODE SER\ OS
CIATDR INDICATOR CONTROLLER INDICATOR HIRE FUNCTION MPLIFIER COWLITER COWLER MISC MISC POWER AUTOPILOT HIRE FUNCTION EMERGENCY
AWLIFIER A I L I RON MISC DISCONNECT
@ 331AM b1YE-2G 3298-86 3YYC-IF SbZA-SG IblE-I
JIA JIB JIA JIB JIA JIB SblC-Y 33PC-3 121A-2
J1 JZ Jl J1 J 2 J3 (TP) (BP) (TP) ( B P I (TP) (BP) J1 J2
J l J1
(TP) (BP)
. .
... ..... ... ... ...
-
. 2 5 PITCH ATTITUDE W N H : 28
.. ' . AILERON FIELD NUMBER -
1
. . b : r5Q-
PITCH ATTITUDE ERROR H ' 22
... ... ... =b:&E: +
-
.. ..
5 1 28 M C
7-t PITCH ATTITUDE ERROR C ' : 21 .
. .... .. .. .. .. AILERON FIELD NUhBER 2

.....
-8 PITCH ATTITUDE SERVO DRIVE M2 2b

.
-9 PITCH ATTITUDE SERVO DRIVE C- 25 .. .. .. ..
13
lli
:
.
5 e AILERON
AILERON
SIGNAL C
EXCITATION C -
... ...
10 -Q- PITCH ATTITUDE RATE G2 :
.
23
... ... ... .. 15 . AILERON
-
POSITION EXCITATION H -
.
I1 -6
25 -?-
PITCH ATTITUDE RATE C2
BANK ATTITUDE RATE CZ .
2Y
39 .. .. .. ... Ib .
.
5+ AILERON
-
RATE EXCITATION H
.. .. . . . . . 12 5+ AILERON POSITION SIGNAL
... .. .. .. -
-
2Y -t- BANK A R I T U D E RATE G2 33 I1 x+
- AILERON SERVO G9D
... .
..
23
22
: .
:
BANK A T T I T U M SERVO DRIVE c
.
BANK ATTITUDE SERVO DRIVE M2
__f_ 35
3b .. ... ... ... 17 . 5+ AILERON RATE SIGNAL
.. .. .. .. ..
.. .... 2 1 -7-
BO - 6
BANK ATTITUDE ERROR C'
BANK ATTITUDE ERROR H ' :
. 31
32 .. .. .. ..
... .... 5Y : .
BANK ATTITUDE W N H . 38 .. .. .. ..
- I
: . 2b VAC ATTITUDE PUR
.....
Q
....
3 2 .
33 : . I 2b VAC PUR COM
:
.
53
51 .. .. .. ..
VERT
REF :
AILERON ENGAGE VOLTAGE
AILERON ENGAGE VOLTAGE
: : 33- GYRO HIGH LEVEL FLAG + :
.. .. : 18 - :
29 -10
.. .. ..: .:. 3320-11 :
:
: : :
GYRO HIGH LEVEL FLAG
GYRO MON + : Y
30
o : .- .- . JI
... ..
. 3 : : 7 PITCH ATTITUDE CT X . : 3 0 . : :
N
A
:
:
I

.. .. 4
5
: .
PITCH ATTITUDE CT Y
PITCH ATTITUDE CT Z
: : 2 0
.
:
. .
:
.
: 0
c
:
: - L.
.. .. ELEVATOR F I E L D NUWER I
.. . : : : D :
... -
17- BANK ATTITUDE CT X : 3 0
: . . : : e o . :
... 18 BANK ATTITUDE CT Y E : ELEVATOR F I E L D NUWER 2
.. .. .. .. .. .. .
. 19 : : A BANK ATTITUDE CT Z
... ELEVATOR SIGNAL C
-
-
: : : 115 VAC POWER
. .. .. . . .. . ELEVATOR EXCITATSON C
-
..
- -
: : : AC GQOUND
. . . . :
ELEVATOR POSIT1)N EXCITATION
.. .. 12
13 :
PITCH ATTITUDE X (BOOTSTRAP)
.
PITCH ATTITUDE Y (BOOTSTRAP)
:
:
:
: . :
: 5 3
: 5 Y
ELEVATOR
ELEVATOR -
RATE EXCITATION H
P O S I T I I k SIGNAL
. .
:PITCH:
:SYNC :
:BUTTON
1Y
: :
: :
:
:
PITCH ATTITUDE Z (BOOTSTRAP)
PITCH COWAND H '
PITCH COUUAND C '
:
:
:
:
3b-15
Ib---?-Ib
55
:
:
ELEVATOR
ELEVATOR
SERVO jRD
RATE SlGNAL -
:L: 15 : .
2b VAC ATTITUOE POWER : .53-5
: I I :
A .. : I b : . 2b VAC PUR COM . . : 51-27
: . : :
. . .. .. .. ..
PITCH SYNC WAN : : 3 0 :

.. PITCH STEER + UP

-
: 5-31 : : : ELEVATOR ENGAGE VOLTAGE
.. : : : : PITCH STEER + WUN : 9-21 : : :Q ELEVATOR ENGAGE VOLTAGE
.. ... : : : : ROLL STEER + LEFT -OI 31 : :
. .. : : : : ROLL STEER + RIGHT 11 : : :
....
- 8 1
... V-BAR ROLL POS XMTR z

-
: 49 . 5 8 : : : :
.. .
..
: 3~ : V-BAR ROLL POS XMTR x : b o : : : :
: .
.. ..
: 3b V-BAR ROLL C O M N D SERVO DRIVE M2 b2 : : : :
: 3 ? . .
... ...
V-BAR ROLL C O W D SERVO W I V E C --?- b3 : : : :
: 38 : : 5- V-BAR ROLL C O M N D RATE G2- bl : : : :
.
..
.. : 39 : ;; V-814R ROLL C O W 0 S I C COM-
- 59 : : : :

.. ..
...
...
...

..
..
...
.
.
.. :
:
:
:
Y5 -?-
Y Y -b
Y3
Y2
.. .. .. ..
: YI
-
:

-
V-BAR PITCH C O M N D S I C COM
V-BAR PITCH COhMAND RATE G2
.
V-BAR PITCH COWAND SERVO DRIVE M2b3
V-BAR PITCH POSlOFF-SCALE B I A S
XMTR
.. -
Z
59
b2
V-BAR PITCH C O M N D SERVO DRIVE C by
-
- ..
b l
:
:
:
:
:
..
:
:
:
:
:
..
:
:
:
:
:
..
:
:
:
:
:
..
:
:
:
:
:
..

-
. . . : YQ : . V-BAR PITCH PO5 XWR X- bO : : : : :
: Y8 : : 7 2b VAC COKMAND PHR b ? : : : : :
. .. .. : 39-L-
..
. .. ..
:
:
:
: Y STEER FLAG -
2b VAC COWAND PUR CDM- 5Y
: b Y
: :
:
:
:
:
:
:
:
- 12 - (,

-
: : : : PITCH C W U T E R hY)N + : : : :

-
12 NAV RCVR
-. ... .. . . RUDDER FIELD NUBER I

:
.. .
33
.
..
:
:
: 3
: : :
: 10 e
STEER FLAG +
COMXAND SERVO MONITOR
GLIDE SLOPE DEV + UP
:
-
b5-
. 3 2
38
28
:
:
:
:
:
:
:
51RV-I
(TP)
8
28 MC-
WDDER
RUDDER
-
F I E L D NUd3ER 2
SIGNAL C
: 39 : I1 GLIDE SLOPE DEV + DOWN . 2 2 : . : 9
: 35 . . 12 t4- GLIDE SLOPE LOU LEVEL FLAG + . : -. .. .- . 21
RUODER EXCITAT1)N C
-
:
... .. ...
3b : 13 GLIDE SLOPE LOU LEVEL FLAG
GLIDE SLOPE HIGH LEVEL FLAG +
- . . . . 22
RUDDER
RUDDER RATE EXCrTATIOh H-
POSITION EXCITATION H

-
.. .. :
. . : : :
. . :
.. :
.. ..
il ;
.. ..: .:. 2) RUDDER POSITION SIGNAL
... .. .. .
. . . .. . . .. .. .. .. .. .. RUDDER
RUDDER
SERVO CRJ
RATE SIGsIAL
:
.. 1 :
.. ..: ..: .4. T C COLRSE RSVR A . . . . . .
.. ..
Ib
: : : : : : (BP) RLDDER ENGAGE VOLTAGE i B
: 2 : : S T C COLRSE RSVR B 22 . . . . RUDDER ENGAGE VILTAGE B C
;Q; . : 4T+ COLRSE R S M C . 23 . . . .
: rSTe COURSE RSVR H . 21 . . . .
: Y . : : :-SQ- COLRSE RSYR 0 . 2Y . . . .
: 5 : : . :5 6 COURSE RSVR E . 25 . . . .
: b : : : : 57- COLRSE RSVR F . . 2b . . . .
. . . . .
--
: 7 . : : 5 6 COLRSE RSVR G q 2)
: 26 : : . TO FROM + TO . . Y3 . . . .
: 27 . TO FROM + FROM .. ..
YLt .. . . .
: 31 : : : 7 VORlLOC LOU LEVEL FLAG t P Y1 . .
: 38 : : L VORlLOC LOW LEVEL FLAG - . . 42 . . . .
:
:
29 . . . : :
.
VORlLOC DEV + LEFT +
VORlLOC OEV + RIGHT p
: ..
: : : ll-YD
. . . -
.. .. ..: 28 : 10 39

--
VORlLOC DEV + LEFT
.. . . : : : : 7-32-11 :
.. ... ...
-
: : : : VORlLOC OEV + RIGHT 8-22-10 :
: : : : VORlLOC H I LEVEL FLAG -71 11 : : 50
. . .
..
.
..
.
..
.
:
..
::
.. .. ..
: LOC FREQUENCY
28VDC NAY REC POWER
YO
..VB 19
.. 7u
._
37
.
.. .. .. ..- TO NAY
REC PUR

AP-103F/FD-l09G F - 2 7 J , I n t e r c o n n e c t i n g W i r i n g D i a g r a m (Sheet 1 of 4)
F i g u r e 464

May 1/67 22 -03-00

Pages 401/175, 401/176
 COLLINS
MAIKTENAKCE
MANUAL

FLIWT
.
IWNVH- CRRY P E M S T M DIRECTOR INSTRWNT FLIGHT NX€ SERWS
CIATOR I W D I U T W CONTROLLER INDICATOR WIRE NUCTIW WLIFIER COlRITER ODLPLER MlSC MISC P M R Em-
WIE " C n O N AILERO( MISC DISaMCT
@ 331- CIW-Hj 32-6
33903 12-

.
JI
...
52
...
J1 JI JZ J3
.. .. .. .. - .. .-,.. J1
...
J2
...
..

:r1 I
. I . ,

: : : : VOR SELF TEST DISABLE : :

1 19 NAV CONT
.. . ... ..
. . .. : : : : VCR SELF TEST DISABLE :
. :
. :
.
:
.
: 15- 59 3131-3 :
..: ... ..
.. ..: ..: .:.
: VOR SELF TEST DISABLE
.
. .. .. ..
: Y8-
: Y 4 - K @ :
55 (J2) :
: .
: BACK:
: COURSE
:
: . . . . VOR SELF TEST DISABLE
VOR SELF TEST DISABLE
.: : : : : l b n . . : : AIRSPEED :
VDR SELF TEST DISABLE .. : : : 2 : L : ... ... : : SENSOR

0:I . . . :
. T U BACK PCOLRSEN MODE I
. . ..
.
..
. . 13
. . . : : 59CB-2

i'
: : Jl
. 12 . .
.. . . .. .. ..
:
...
BACK COURSE INTERLOCK
B A M COURSE EXC
.
. .. .
:
:
. . .
:
; $ .) ; ; . 59 . AIRSPEED SIGNAL
AIRSPEED EXCITATION H
. .
. .. .. . .
BACK COLRSE MODE
..:
29-25 DMEQ :
.. .. AIRSPEED EXCITATION C
... ...
.. .. .. .. ..
: : : : : 8bCE-2 :
. . . . . . . (Jl) : .. .
:
:
Y5
Yb :
.
: :
DISTANCE
DISTANCE
SHUllER +
SKITTER - . . . . .
9
1c
:
:
..
...
..... ..
...
..:
...
: : . . . . 2 :
... .... .. ...
Y? DISTANCE RECEIVERS 2bVAC HOT
:
:
YS - :
. . .: .. DISTANCE RECEIVERS 2bVAC GRD
RECEIVERS Z COMK)N
:
. :
.
:
.
:
.
:
.
:
.
1 :
.
... ...
u9J: DISTANCE
: so .: : DISTANCE RECEIVER UNITS X .
.
.
.
.
.
.
.
.
.
.
.
Y : ... ...
:
:
51
52 .
: : DISTANCE
DISTANCE
RECEIVER UNITS Y
RECEIVER TENS X . . . . . .
3
b :
:
.... ..
.. .. ..
. . . . . . . . .
: 53 : :
.
DISTANCE RECEIVER TENS Y 5 :
.. ..
... ...
: 59 : : :
..
DISTANCE RECEIVER HUNDREDS X :
..
:
..
: :
.. ..
:
.
:
.
7 :
.. ..
.. ..
:
. . .: 55
.. .. : ..: DISTANCE RECEIVER HUNDREDS Y 8 :
.. .
... ... ... . ... ... ...
. . . . . : :Q COMPASS :
.. .. ...
...
..
. . . ... . . .
:
:
:
:
:
:
:
:
:
:
:
:
328A-2A
( J l ) (J2)
:
: .. ... ... ... ..
- . .. .. .. ..
:
:
9-1
: 1 7 2
:
.. .. ..: :
.:. COMPASS HEADING X
.. . .
:
.. .. .. : :
..: 2
.. .. :
... ... .. ..
:
:
10-2 -
: 1 8 2 .. .. :
:
... :
.. COMPASS HEADING Y
... ..
.
.. .. :. :.
. . . . ..
:
.. ..
3 :
.. .. . .
. . . . . . .. .. ... ..
... ...
... .. .... .... ..... ..... .
: COMPASS HEADING Z : Y :
1-3
.. . . ..:. ..:. ..
... ....
:
. .: 19J
.
.. ..
: : : : 115 VAC POWER 3i-g
.. .. .. . . . . . .
... ... ... ... .. .. : :
: : : : 28VDC POWER Zb
.. . . GROUND . . 2) : ; .. . ... ...
. .. .. . . . . COWASS MONITOR + : 39-1Y- 25 : : . .. .. ..
.. .
...
: : 5 : : HEADING DATUM H' : . : : : b 11 : : : Y9 COWASS DATA X
... ...: 4...
: : HEADING DATUM C' :
. :
. : : : ?
.
Y : : :
-
50 COWASS DATA Y
.... ..
..
.
..
.
..
.
:
:
..
:
:
.. .. ..
:
:
:
:
HEADING D A N M H '
HEADING DATUM C'
HEADING DATUM LOAD RES (1DK)
:
..
:
..
:
:
:
3 3 - b
+?]I
: 1 ? :
3
i
.
i. ;. ; ;. 51
;
..
COWASS DATA Z

. .
: 13 . . . . : COURSE DATUM H' . : . : . 9 . PILOTS COPILOTS :
. .
: 12
.. : COURSE D A M C ' : : : : : s
. . DISENGAGE DISENGAGE :
. . ... ... .
'1 j
..
:
:
:
.
..
.
30
: 2Y
: 21
..
.
:
:
:
:
:
:
:

:
:
:
:
:

:
:
:
:
:
:
: 5?-
COLRSE D A N M H '
COURSE DATUM C'
COLRSE D A M LOAD RES (10K)
COWASS LOW LEVEL FLAG +
COWASS FLAG -
AZIMUTH CARD ERROR CT H '
-
-
:

.
13
:
97
11
;
:
:
:
:
:
;;:
:
:
:
1 s
5
13
:
:
:
:
:
j
: b?
.
:

.
..
bb
.
:

...
- AUTOPILOT DISENGAGE

AUTOPILOT DISENGAGE
BUTTON

-
T
.
..
.
..
BUTTON
T

... ...
-
: : 20 : : : : :
... ...
AZIMUTH CARD ERROR CT C ' 2 1 2
: : 13 : : : $?- AZIMUTH CARD RATE G2 : l Y : : : :
:
: : 1Y : : :5 6 A Z I W T H CARD WTE C2 . 1 5 : : : :
.. ...
:
:
SENSING
: : 11 AZIMUTH CARD SERVO DRIVE M I l? : : : :
.. . :
:
:
UNIT
:
:
: 12
: 15
: : AZIWTH CARD SERVO DRIVE C1-lb
2 b VAC HEADING PUR . 5 2
:
:
:
:
:
:
:
: .. .. : :
345A-YB
(ROLL)
. . .
-
: : l b : 2 b VAC POWER COM . 5 Y : : : : : b5