Honeywell
Commercial Flight Systems Group
Business and Commuter Aviation Systems Division
Honeywell Inc.
Box 29000
Phoenix, Arizona 85038
C-14, C-14A, and C-140
GYROSYN Compass System
Installation and
Maintenance Manual
TITLE PAGE T-1
P\JB. NO. 15·3fH·01
(FORMERLY LJ•1 S-0510)
REVISED 5 NOVE.M8EA 1991
15 DECEMBER 1964
Honeywell
INSTALLATION
& MAINTENANCE
MANUAL
C14tx) COMPASS SYSTEM
IMPORTANT NOTICE
:he ~vionics business units formerly owned by UNISYS Corp. and
1dent1f1ed with the Sperry name or logo have been acquired by
Honeywell Inc. Publications, products, and components marked
or identified herein with the Sperry name or logo are publications,
products. and components of Honeywell Inc. All references to the
Sperry name or logo should be taken as referring to Honeywell Inc.
PROPRIETARY NOTICE
This revised document and the Information disclosed herein are proprietary data of Honeywell Inc.
Neither this document nor the information contained herein shall be used, reproduced, or disclosed
to others without the written authorization of Honeywell Inc., except to the extent required for
installation or maintenance of recipient's equipment.
NOTICE • FREEDOM OF INFORMATION ACT (5 use 552) ANO
OISCLOSURE OF CONFIDENTIAL INFORMATION GENERALLY (18 use 1905)
This revised document is being furnished in confidence by Honeywell Inc. The Information disclosed
herein falls within exemption (b) (4) of s USC 552 anc the prohibitions of 18 use 1905.
SR91
GYROSYN is a ,.giste,-,;i trademark of Honeywell Inc.
TITLE PAGE T-2
Copy,~nt 1991 HontyWell Inc.
All Rlgnl-1 Rese!Wd
RE''IISE0 5 NOVEMBER 091
15 DECEMBER 1'<14
Honeywell
INSTALLATION
& M AINTENANCE
MANUAL
C-14(X) COMPASS SYSTEM
RECORD OF REVISIONS
Upon receipt of a revision, insert the l atest revised pages and dispose of
superseded pages. Enter revi sion number and date, insertion date, and the
incorporator's initials on the Record of Revisions . The typed initials HI are
used when Honeywel l Inc. i s the incorporator.
Revision
Number
Revision
Date
Insertion
Date
1
Feb 15/65
2
Sep 1V68
Nov 8/68
.....!iL
3
May U72
Aug
2on2
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4
May U73
Jun 15n3
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Nov 1004
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15/75
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Nov 5/91
Nov 15/21
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By
Revision
Number
Revision
Date
Insertion
Date
By
.....!iL
Page RR- 1/RR-2
Nov 5/91
U$8 o, d1Sci0$Ure Of 1nform e 1,on or, this pa ge is suo,eet to ftle restnetions on the titte page of ttus docum6nt.
Honeywell
INSTALLATION
& M AINTENANCE
MANUAL
C-140<) COMPASS SYSTEM
LIST Of EFFECTIVE PAGES
Dec
Feb
Sep
May
May
Oct
Original
0
Revision .. 1
Revision
2
Revision
3
Revision .. 4
Revision
5
15/64
15/65
11/68
1/72
1/73
10/74
REVISION
SUBHEADING AND PAGE
Revision
6
Jul 15/75
Revision
7
Feb 1/77
Revision
8 .. Aug 22/77
Revision . . 9
Nov 15/80
Revision . 10
Nov 5/91
SUBHEADING AND PAGE
REVISION
1-22
Title
T- 1
T-2
•
•
10
10
•
10
List of Effective Pages
LEP-1
•
LEP-2
•
10
10
Table of Contents
TC- 1/TC-2
10
Record of Revisions
RR-1/RR-2
•
Introduction
INTR0-1/ I NTR0-2
•
Description and Operation
1-1
1-2
1-3
1-4
1-5
1-6
1-7/1-8
•
F 1-9/1-10
F 1-11/1-12
1-13
1-1 4
1-15
1-23/1-24
F 1-25/1-26
•
Ins ta11 at ion
2-1
2-2
2-3
2-4
2-5
2-6
2-7
9
9
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9
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9
2-8
2-9
10
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9
9
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9
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9
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9
2-10
2-11
2-12
F 2-13/2-14
F 2- 15/2 - 16
F 2-17/2-18
2-19
2-20
2-21
2-22
2-23
2-24
2-25/2-26
9
9
9
•
9
3-2
1-17
1-18
1-19
1-20
1-21
9
9
9
9
9
3-3
3-4
3-5
3-6
3-7
9
10
9
•
Compass Swing Cal ibration
3-1
1-16
9
9
10
10
9
9
9
9
9
9
9
9
9
9
9
9
9
9
• indicates changed, added, or deleted page.
F indicates right foldout page with blank back .
Use Ot disclosure
ot 1ntonnett0n
Page LEP-1
Nov 5/91
on this page is sub;ect to the restnchons on 1he tnte l)llge of t~s documem.
Honeywell
SUBHEADING AND PAGE
REVISION
INSTALLATION
& MAINTENANCE
MANUAL
C-14()() COMPASS SYSTEM
SUBHEADING AND PAGE
REVISION
Compass Swing Calibration (cont)
3-8
3-9/3-10
9
9
Ground Operational Tests
(Ground Check)
4-1
9
4-2
9
Shipping, Handling , and Storage
5-1/5-2
•
10
Use or OlselOsure of ,nfO<mahon
Page LEP-2
Nov 5/91
on this Ptlg9 rs suqec1 10 the res1ne11ons on 1ne t1oe Qage OC this dOCum&m.
Honeywell
TABLE
I
II
I
MANUAL
C-l◄ (X)COMPASS SYSTEM
CONTENTS
Subheading
Section
I
OF
INSTAU.ATION
& MAINTENANCE
DESCRIPTION AND OPERATION
1- 1
1.1 Physical Description
1.2 Component Description
1.3 Functional Operation
1-1
1-5
IV
V
1-21
INSTALLATION
2-1
2.1 General
2-1
2-2
2.2 Mechanical Installation
2.3 Electrical Installation
2.4 Loading and Gradient Characteristics
II I
Page
2-12
2-12
COMPASS SWING CALIBRATION
3-1
GROUND OPERATIONAL TESTS (GROUND CHECK)
4-1
SHIPPING, HANDLING, AND STORAGE
5-1
Page TC-l/TC-2
Nov 5/91
Use or d1scl0s1Jre ol 1ntOrm1110n nn th1, p,ge •s SUbJect to the restneuons on 1t1e 1,ue pag~ or this oocumem
Honeywell
INSTALLATION
& MAINTENANCE
MANUAL
C.!◄ (X)
COMPASS SYSTEM
INTRODUCTION
I
This manual provides general system maintenance and installation instructions for
the C-14, C-14A, and C-140 Gyrosyn® Compass System. The Compass System can
comprise any number of components, providing various level s of capability and
display depending on the user's requirements. (Refer to Section 1.)
This manual provides block diagram information and interconnect diagrams to
permit a general understanding of System interface. Colllllon system maintenance
procedures are not presented in this manual. The best established shop and
flight line practices shoul d be used.
I
Infomation on shipping, handling, and storage of all System collllonents is
contained in Honeywell Pub. No. 09- 1100-01.
Abbreviations used in this manual are defined as follows:
Abbreviation
A/P
CT
ex
FV
FVCT
GRO
POT
SYNC
Definition
Autopilot
Control Transformer
Control Transmitter
Flux Valve
Flux Valve Control Transformer
Ground
Potentiometer
Synchronization
Page INTR0-1/INTR0-2
Nov 5/91
Use or d•sclosu,e ol ,ntormation on thts page ,s subf8CI to the restnct'1ons on !he title page
or
rt11s
csocument
+~t:!.~
A"10,,,C$ DIVISION
lNl'TALLATION
a MAINTENANCE
MANUAL
C-14(XI COMl'ASS SYSTEM
SECTION I
DESCRIPTION ANO OPERATION
1.1 Physical Description
The Conpass System (figure 1-1) uses the horizontal conponent of the earth 's
11111gnetic field to provide
continuoU!I m119netic head ing reference for
4
aircraft navigation. The basic Coq,ass System consists of a directional
gyro, flux valve, colJl)ensator, and an annunciator. Table 1-1 lists the
conponents and part nuni>ers that COIJllrise the Conpass System. The C-14(X)
Directional Gyro is a gyro and synchronizer asseni>ly packaged in a
cylindrical upper housing and a base asseni>ly.
In the C-14 configuration, a gyro and an;,lifier asserooly is contained in the
cylindrical housing mounted on the base. The synchronizer asseni>ly is
contained in the base. In the C-14A configuration, all subasseroolies are
contained in the cylindrical housing and the base is used for support and
mounting. The C-14D confi9Jration is a C-14A with a de static inverter
mounted in the base assembly. The different asseimly and subassembly
combinations are detailed in tables 1-2 and 1-3.
Conponent
Sperry Part No.
Directional Gyro (Optional):
C-14 Directional Gyro
C-14A Directional Gyro
C-14D Directional Gyro
2587193-X, -2X, -3X
2587193-4X
4020577-3, -6
2594484
FX-220 Flux Valve
Co11pensator (Optional):
CS-212 Magnetic Co11pensator
CS-412 Dual Remote Compensator
CS-313 Remote Magnetic Com;iensator
AN-140 Annunciator
656767
2593379-1
2586257-1
2503148-2
System Components
Table 1-1
Page 1-1
Nov 15/80
....JLsr=e~v
-,r
INSTALLATION
& MAINTENANCE
Fl,IGHr SYSTEM S
MANUAL
AVt0NJC$ OIVISION
C•14fXJ COMPASS SYSTEM
AN-140
ANNUNCIATOR
CS-212
••GNET,c coC'°"
w
/_,
FX-220
FLUX VALVE
C-14(X)
DIRECTIONAL GYRO
CS--412
D UAL REMOTE
COMPENSATOR
CS-313
REMOTE MAGNETIC
COMPENSATOR
A0-100<
Co111>ass System Co111>onents
Fi gure 1-1
Page 1- 2
Nov 15/80
INSTALLATION
& MAINTENANCE
MANUAL
AYIOIMCS DIYltlON
Asseni>ly
C-14 comeass sistem
2587193-1 [l]
2587193-2 [l]
2587193-3 [l]
2587193-4 [2]
2587193-5 [2]
2587193-6 [2]
2587193- 7 (1)
2587193-21 (1]
2587193- 22 (l]
2587193-23 [l]
2587193-24 (2)
2587193-25 [2]
2587193- 26 [2]
2587193-33 [l]
2587193-36 [2]
C-14(XI COMPASS SVfflM
Subasserri> 1i es
DG 401,
Giro &Amelifier Assi
2585113-1
2585113-2
2585113-3
2585113-4
2585113- 5
2585113- 6
2585113-3
2585113- 1
2585113- 2
2585113-3
2585113- 4
2585113-5
2585113- 6
2585113-13
2585113- 16
Synchronizer
Assi
2587194-901
2587194-901
2587194- 901
2587194- 902
2587194-902
2587194-902
2587194-903
2587194-904
2587194-904
2587194-904
2587194-905
2587194-905
2587194- 905
2587194- 904
2587194-905
Annunciator Part No. 2503148-2 used.
[2] Annunciator in C6, C-6A, C- 60, C-6E, or C- 6H used.
[l)
C- 14 Coffl)ass System
Table 1- 2
Page 1-3
Nov 15/80
...JLst=e~v
- , , - f LIGHTSY'ITPIS
.lWONICS D M -
Assenbly
C- 14A Comeass Sxstem
2587193-41 [2]
2587193-42 [2]
2587193-43 [2]
2587193-44 [3]
2587193- 45 (3)
2587193-46 (3)
2587193-47 (2)
C-14D C0111JJass Ststem
[2]
4020577-3
[2]
4020577 -6
INSTALLATION
• MAINTENANC£
MANUAL
C-1• 1Xl COWAIS SYSTI:M
Subassent>l ies
Giro-Sxnchroni zer Assx
4019190- 1
4019190-2
4019190-3
4019190-4
4019190- 5
4019190-6
4019190- 7
4019190-13
4019190-16
Base Asst
4019759
4019759
4019759
4019759
4019759
4019759
4019759-l
4021979-901 (1]
4021979-901 [l]
[1] Base assembly, Part No. 4021979- 901 i ncl udes a de i nverter circuit.
Part No. 4019759 contai ns no circuitry.
(2] Ann unciator Part No. 2503148- 2 used.
[3J Annuncia t or in C- 6, C- 6A , C- 6D, C- 6E, or C- 6H used .
C- 14A and C- 140 Compass Systems
Table 1-3
Page 1-4
Nov 15/80
+~st~4:V
AVIONICS 01VlS10N
INSTALLATION
a MAINTENANCE
MANUAL
C•14IXI COMPASS SYSTEM
1.2 Component Description
This section provides a brief description, an illustration, leading
particulars, and a block diagram or schematic of each COlft)Onent used in the
System.
The coll1)onents are separated as follows: C-14A and C-140 Directional Gyros,
paragraph 1.2.1; FX-220 Flux Valve and CS-212 Colft)ensator, paragraph 1.2.2;
CS-412 Dual Renote Corrpensator, paragraph 1.2.3; CS-313 Remote ~agnetic
Coll1)ensator, paragraph 1.2.4; and AN-140 Annunciator, paragraph J.2.5.
Page 1-5
Nov 15/80
...JL SPE~Y
- , , - HIGHTSYSTEMS
INSTALLATION
1k MAINTENANCE
MANUAL
C-14IX) COMPASS SYSTEM
AVIONICS DIVISION
1.2.l C- 14A and C-14D Directional Gyros (See figures 1- 2 thru 1-4, and
t~ble 1-4.)
e
!Q
~
2$750
Typical Directi onal Gyro
Figure 1-2
Dirrensions (maxi11UJm):
Length . • • • • • • • • • • • • • • • • • • • • • • • .• • • • • • • • • • • • •• • • • •
Width {C-14A) •• • • • . •• • • •• • • • • • . ••• •• •• • • • •• • • • • ••
Width (C-14D) • •• • ••• •• •• • •• •• ••••••••••••••••• •••
Hei ght • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • • •
9. 03 in.
6.06 in.
Heistit (shock mounts extended
7.50 in.
• . • •• ••• •••• • •• .••••
6.25 in.
7. 22 i n.
(229
( 154
(159
( 183
(190
mm)
mm)
mm)
mm)
mm)
Weight (approximate):
C-14A
C-140
.............................................
•••••• ••• ••• •••• ••• ••••••.•••••••••••••••••.•
4.7 lb (2.13 kg )
6. 7 lb (3.04 kg)
C-14A and C-14D Directional Gyros
Leading Particulars
Table 1- 4
Page 1-6
Nov 15/80
Honeywell
INSTALLATION
& MAINTENANCE
MANUAL
C-14()() COMPASS SYSTEM
Input Power Requirements:
C-14A
............. ...... ..... .... .. .. 115 V, 400 Hz , 40 VA starting,
30 VA running
C-14D .. ........ . ............ ...... . ... . .. .. . 28 V de, 125 Wstarting,
100 Wrunning
C-14D Output Power:
0-22* VA to instrument components
115 V, 400 Hz at IJ2-T
26V, 400 Hz at 1J2-S
3
VA to flux valve
26V, 400 Hz at IJ2-k
0-42* VA to i nstrument components
and heading CX excitation**
SV, 400 Hz at 1J2-W
-2 VA to instrument lighting
Total
SO VA
*Sum of output power from these tvo sources shall not exceed 42 VA .
**Each heading CX requires 4.5 VA excitation.
Gimbal Freedom:
I
Vert ical (Azimuth) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 360 deg
Horizontal (Pitch and Roll) . .. ..• .. ... ........ ..... .. .. .. ... ±85 deg
Slaved accuracy . . . . . . . . . . . . . . . . . . . . . . . . . • . . . . . . . . . . . . . . . . . . . . ±2 deg
Gyro free drift (exclusive of earth rate) .........• ±24 deg/hr (max)
Slaving rate (normal) ....... . .... .. ... . . . .. ... ... 2.5 to 5.0 deg/min
Slew rate (automatic fast or manual) . . . . • . . . . . . . . . . . . . . . • 30 deg/min
Mating Connector
. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . MS3126Fl8-32S
Mounting
Hard Mount
C-14A and C-14D Directional Gyros
Leading Particulars
Table 1-4 (cont)
The C-14( ) Directional Gyro provides three-wire synchro heading
information to various flight instruments, autopilots, and
navigation receivers. A remotely mounted MAG/DG switch controls
compass slaved or nonslaved modes of operation. A remotely mounted
slew switch (INC-DEC) is used to align gyro heading in case of loss
of the slaving amplifier.
Page 1-7/1-8
Nov 5/91
Use Of dlSCIOS.ure
ol antonnation on th,:, page ,s subject 10 the restncuons on
the t1Ue page ot this ooeumant
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Page l -9/1-10
tlov lS/80
-aVIIQT(IIUJlCO'IJ,flO't
{: : }"~·-··""·
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II0.1
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... PA }-ltli.-.11U•IOO..O.-t
r<'a
'"'
C-14A 01rect1orr.al Gyro
Stock Olag..-a u
figure- 1-3
I)
!Q
-~-I----------------{ :: !;~
..""'"t,..
0----~-j -"
I
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}:..--:"U~"O-"O<M"l.lf
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;;.,;.;a4u- - - - -- - - - - --- - - - -- - -- -
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wt'oo.o.loi:
f'OIOtJ
1 n 91,'. ••.., wi•11i
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t,- JW/flll:lld"111 :IUQ00.(,1•0.
HIATII0.4WPJfffl' ....lrJ
II !L ______ _ _
: rJ=:
•
__
___ _
-
_ ________ _JI
L---------------- -- - - - - - - - - - - . 1
C- 140 Sloe\'. Oiagrtni
Figure l-4
Page: 1-11/1- 12
JiO't 15/80
.....-.o ... oo»>Ut
• AA:~•'~"
+~~~,,
AVIOttlCS DIVISION
INSTALLATION
• MAINTI:NANCE
MANUAL
C-14IXI COMPAIS SYSTEM
This page intentionally left blank.
Page 1-13
Nov 15/80
+~st~;t,,
AV10NtCI O C -
INSTALLATION
& MAINTENANCE
MANUAL
C•14 1XI COMPASS SYSTEM
1.2.2 FX-220 Flux Valve and CS-212 Coq>ensator (See f igures 1-5 and 1-6,
and tables 1-5 and 1-6. )
COMPENSATOR
FLUX VALVE
FX- 220 Flux Valve and CS-212 ColTlJensator
Figure 1-5
Dimensions (rraxi111Jm):
Bowl diameter • . • • •••..• • ...•.•• • • • •••••••..• . • 3.58 in. (90.93 11111)
Mounting flange diameter •••••••••••••••••••••• 4.78 in. (121.4 mm)
Hei ~t ........ ... ...... · • · · · · • • • • • • • • • • • • • • • • • 2.88 in. (73.15 mm)
Weight (maximum)
Power Requirerrents
Mounting
••. • ••• •• .•••••. .••• ..•.•.••• ••• • • • ••
1.5 lb (0.68 kg)
•••••••••••••••••••••••••••.•••• 26 V, 400 Hz, 1.1 VA
•••••••••••••••••••••••••• Nonmagnetic machine screws, 6-40 by
3/8 i n. round head, Sperry Part No. 319011
FX-220 Flux Va l ve Leading Particulars
Table 1-5
Page 1-14
Nov 15/80
+~~'!""
A - 1 IIIVI-
INSTALLATION
• MAINTENANCE
MANUAL
C•14(l() COMPASS IYIT!M
Dilrensions (approximate):
Length
Width
Height
........................................
.........................................
....•...........................•.•.•...
3.88 in. (98,5 mm)
2,88 in. (73,2 11111)
0,75 in. (19.1 11111)
Weight (naxinum) ••• ••• ••• • •••••••••••••••••••••••• 0.25 lb (0.113 kg)
Mount in9
····································
Hard Mount to Flux Valve
CS-212 Corrpensator Leading Particulars
Table 1-6
The flux valve detects the magnitude and direct ion of the earth's
magnetic field and converts it to elect rical information which is
used to align the directional gyro to magnetic north.
The nagnetfc co°"ensator consists of two sets of adjustable permanent
bar nagnets which are used to CO!ll)ensate the flux valve for the effects
of magnetizable material in the aircraft structure.
LI
------F
SHIELD
111:a
FX-220 Flux Valve Schematic
Figure 1- 6
Page 1-15
Nov 15/80
+~st~=<¥
&YIONJCS OIVl.s&ON
INSTALLATION
& MAINTENANCE
MANUAL
C-14(XI COMPASS SYSTEM
1.2.3 CS-412 Remote Compensator (See figures 1-7 and 1-8, and table 1-7.)
CS-412 Remote Compensator
Figure 1-7
Dimensions (maximum):
length .•........•. .. ..................•........
Width ••. ••.•. ••••.•.•.•••• ••••.•. ..•.•.•. ....•
Height
.•..•. ... ... ...•... ..•.•. ... . .••... .. . ••
Weight (maximum)
Power Requirenents
5.62in. (142.7nvn)
2.56· in. (65.0 mm)
2.99 i n. (75.9 rrvn)
•••••••••••••••••••••• . •••••••••••••• • 1.0 lb (0.45 kg}
••••••••.•••••••••••.•••••••••.• 26 V, 400 Hz, 2.5 VA
Hating Connectors:
Jl
J2
••.••• •.• •.••••.••.••.••.••••••. .•• ••••.••.••••.
MS3126F14-19SX
MS3126Fl4-19SY
CS-412 Remote Compensator Leading Particulars
Table 1-7
Page 1-16
Nov 15/80
INSTALLATION
• MAINTENANCE
MANUAL
+~sSt~=t-r
C•141Xl COMPASS SYSTEM
AVIOtllCS DMSION
The CS-412 Dual Remote COff1)ensator co.,.,ensates the flux valves by
inserting small de currents to cancel the errors caused by aircraft
magnetic disturbances.
SCREWDRIVER
ADIUSTMENTS
r----,
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REGULATtD
De POWl!II
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VAi.YE
CT
TMl DU4L REMOTE COMPENSATOR CONTAINS TWO IDENTICAL COMPUIISI.TlON
CIRCUITS. CUICUITRY AND CONNECTIONS SHOWN ARE FOR THE NUMBER ONE
SYSTOf THROUGH CONNECTOR J1. CIRCUITRY FOi! THE NUMIER TWO SYSTEM
IS IDENTICAL TO SY$TEM NUMBER ONE. EXCtn CO"INECTIONS ARE MA.DE
fHROUGH CONNECTOR J:t.
CS-412 Dual Remote Compensator Block Diagram
Figure 1-8
Page 1-17
Nov 15/80
INSTALLATION
• MAINTENANCE
MANUAL
-.v10MtC$ DtV1~
Cl◄IXI COMPASS SYSTEM
1.2.4 CS-313 Remote Coni>ensator (See f1!J)res 1-9 and } 10. and table 1•8,}
5
CS- 313 Remote Compensator
Figure 1- 9
Di mensions (maximum):
Length
Width
Height
Weight
............................................
.... ... .... .. ...•.•......•.........• .. .......
4.78 in. (121.4 mm)
5.75 in. (146.1 rrm)
1.87 in. (47 . 5 mm}
.............................................
(maximum) ...........................................
Power Requirements
••• • •••• •••••• •••• •• ••• .•. •• •• • ••
1. 5 1b (680 g)
115 V, 400 Hz, 1.75 VA
Inputs (maxi11Um):
Coriolis Signal • •• • , •••••• • •••••• ••• • •• •••••.•• •• ••• • ••• 8.2 V, 400 Hz
Heading Signal ••• •• •• ••• •• .• • . • •..•• ••• .•••• •. • •••• •• •• • 50 mV, 800 Hz
Outputs:
One-cycle Error Correction • .. •• • ••. •••. •. .• . •. . ••• .• ••••. t8 to 12 deg
Index Error Correction ...• . .• • • •• •. • ••• • ••• • •••• •• ••••• •••.·• 2 deg min
Two-cycle Error Correction . •• •• •. •• .•••• •• • • . . •• •• •• • •••• • t l.4 deg min
Coriolis Error Correction •••••••••• •• •.••• • ••• •••••• •••••• 1000 kn max
Ooppler Vari able Resistor Excitation •••• •••• •••••• • •• 26 t 2 V, 400 Hz
Mating Connector ••.•• • • ••• •••• •• ••••••• . • • •• . ••••• •• •• • Cannon K03-19-20SW
Mounting
• . • . . . . . . . . . . . . . . . . . • . . . . . • . . . • .• • . . . . . . . . . . • . . . . . •
CS- 313 Remote Co111>ensator
Leading Particulars
Table 1- 8
Unit Fasteners
Page 1- 18
Nov 15/80
+~~l~-<Y
AVIONICS OIVISIO<I
INSTALLATION
• MAINTENANCE
MANUAL
C.l4 CXI COMPASS SYSTEM
The remte co~ensator co,rpensates the FX- 220 Flux Valve by inserting small
de cur rents to cancel the errors caused by magnet ic disturbances•
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Figure 1-10
Page 1- 19
Nov 15/80
+~!t~;ey
AVIONICS D<YISION
INSTALLATION
• MA.INffNANCE
MANUAL
C•141Xl COMPASS SYSTEM
1.2.s AN-140 Annunciator (See fi~re 1-11. )
35229
AN-140 Annunciator
Figure 1-11
The annunciator is a null microa1T111eter which ioonitors the output of the
slaving amplifier of the gyro and alf4)1ifier asserrbly. The arrangement of
the annunciator is such that, when the system is synchronized, the meter
will be in the center (null position). When the gyro heading output is
less than the magnetic heading, the pointer of the annunciator is to the
left ( +) of its center (synchronized) position. When t he pointer is to
the right (e) of its center position, the gyro heading output is greater
than the magnetic heading.
With directional gyros, Part No. 2587193-1, -2, -3, -7, -21, -22, - 23,
-33, -41, -42, -43, -47, and 4020577-3, the annunciator is a col"f1)onent of
the system. With directional gyros Part No. 2587193-4, -5, -6, -24, -25,
-25, -36 , -44, -45 , -46, and 4020577-6, the annunciator in the C-6
indicator is used as the system annunciator. C-6 indicators used with the
Corrpass System are the C-6, C-6A, C-60, C-6E, and C-6H.
Page 1-20
Nov 15/80
+~st~4;T'
AVIOIMC$ DIVISION
INSTALLATION
• MAINTENANCE
MANUAL
C-14CX) COMPASS SYSTEM
1.3 Functional Operation
This paragraph contains the theory of operation for the Compass System,
Compass System Signal Flow Diagraa1 (figure 1-12) provides a general
understanding of the system and i ts major signal flow and connections.
NOTE:
Figure 1-12 shows a C-14A Directional Gyro, Part No, 2587193-43, and
a CS-412 Dual Remote Compensator for descriptive purposes.
Configuration differences are discussed in the text.
Basic power for the system is the 115-volt, 400-Hz input to the C-14A
Directional Gyro. This provides internal power for the gyro and a 26-volt
ac power output for the flux valve and CS-412 Dual Remote Compensator.
The C-140 Directional Gyros, Part No. 4020577-3 and -6, contain a de static
inverter in the base .assembly that provides ac inputs to the gyro
synchronizer 4019190-13, -16 and the other . external system components.
The flux valve senses the horizontal component of the earth's magnet ic
field. Using the 26-volt ac reference signal it provides an output signa l
I magnetic field. This signal
that represents aircraft heading in the earths
wi l l provide a conmand to keep the rotor spin axis of the gyro al ign ed to
magnetic north in the slaved mode.
The CS-412 Dual Remote Compensator compensates the flux valve for
single-cycle error (hard-iron effects) by inducing small de currents into
the flux valve coils to correct for errors caused by ferrous metal in the
aircraft. The procedure for adjusting this level of compensation is
discussed i n Section Ill.
The directional gyro receives an input fran the flux valve through the flux
valve control transfonner (FVCT) (B2) i n Part No. 2587193-1 thru 3, -7, -21
thru -23, 33, -41, thru -43, and -47 , and Part No. 4020577-3 units, and
through the FVCT in the C-6 indicator in Part No. 2587193-4 thru -6, -24
thru -26, -36, -44 thru -46, and 4020577-6 units. The output from the FVCT
is tuned to 800 Hz and applied to the slaving 11111pl ifier. The slaving
amplifier output is then applied to the precession coils in the gyro and to
the annunciator.
The Compass System may be operated in either the slaved or free gyro mode.
In the slaved mode of operation, the di rect ional gyro is slaved to a
position relative to the magnetic heading reference as supplied by the flux
valve and the compensator. In the free mode of operation, magnetic
infonnat ion fran the flux valve and canpensator is disabled in the gyro and
no slaving is perfonned. The directional gyro provides compass info nnat ion
as a product of the position of the aircraft with reference to the position
of the unslaved gyro. As no slaving is performed, the displayed heading
infonnat ion is subject to error as the result of free gyro drift.
Page 1-21
Nov 15/80
+~s~V
AVIOPOCS D4VISt0N
INSTALLATION
& MAINTENANCE
MANUAL
C-141XI COMPASS SYSTEM
The C~ass System ; s operated in the free gyro mode by removing the
connection between pins E and G on connector lJl Of the d1rect1onal gyro.
Usually an operational switch is installed between pins E and G. When pins
E and Gare open circuited, the slaving system is made inoperative.
If the SLAVED-FREE switch is not used, a jumper wire R11St be inserted
to connect pin E of connector lJl to pin G of connector lJl. The
system then operates in the slaved mode at all times.
Slaving of the directional gyro is accomplished by supplying current flow
through precession coils affecting the sensitive axis of the gyro. The
MANUAi. SYNCHRONIZATION switch is used to engage fast slaving of the
directional gyro. When fast slaving is engaged, the slaving rate is
increased from approximately 3.5 degrees per minute to approximately 40
degrees per minute. Once engaged, fast slaving continues until the coffl)ass
card of the HSI indicates within 4 degrees of actual heading, at which time
the normal slaving rate is reestablished. Fast slaving is autoll'atically
initiated during the start-up initialization cycle.
NOTE:
Directional gyro, Part No. 2587193-47, contains a circuit (Ml) that
allows the manual fast sync. switch wiper to be grounded externally
instead of being connected back to the unit connector pin lPl-A as
required in all other C-14, A or D units.
During operation of the directional gyro, any of the following conditions
will cause a loss of the 0G valid signal and allow relay K2 to deenergize.
(a) Low voltage to the directional gyro power supply
(b)
Improper wheel speed of the spin motor
(c) Fast sync (manual synchronization)
The directional gyro provides three-wire co111>ass information from an ARINC
heading synchro transmitter No. 1 (83) and uses it to move the HSI c~ass
card to the proper heading.
Additional heading information outputs are available through a second
identical heading transmitter (84) or a clutched potentiometer depending
upon dash number. Heading transmitter CX No. 2 provides additional
three-wire (ARINC) heading information while the clutched potentiometer
provides an automatic pilot heading hold function. The clutched
potentiometer consists of a 5k-ohm potentiometer with a sensitivity of 2.5
volts per degree and a clutch which is geared to the output axis of the
gyro. The clutch requires 28 volts de excitation and the potentiometer
requires 100 volts de excitation. The potentiometer provides a linear
output proportional to gyro rotation up to ±20 degrees. The arm of the
Page 1-22
Nov 15/80
INSTALLATION
It MAINTENANCE
MANUAL
AVIONIC$ Orv1S10N
C-1'1X) COMl'ASS SYSTEM
potentiometer is spring loaded so that when the clutch is disengaged the arm
will return to the center (null} position.
The system configurations are as
follows:
C-14, C-14A, C-140
Directional Gyro
Part No.
Contents
2587193-1, -21, and -41
Heading Transmitter No. I (83)
Flux Valve Control Transformer (B2)
2587193-2 , -22, and -42
Heading Transmitter No. 1 (83)
Clutched Potentiometer (84)
Flux Valve Control Transformer (82)
2587193-3, -7, - 23, -33,
-43, -47, and 4020577-3
Heading Transmitter No. 1 {B3)
Heading Transmitter No. 2 (B4)
Flux Valve Control Transformer (82)
2587193-4, -24, and -44*
Heading Transmitter No. 1 (83)
2587193-5, -25, and -45*
Heading Transmitter No. 1 (B3)
Clutched Potentiometer {B4)
2587193-6, -26 , -36, -46,
and 4020577-6*
Heading Transmitter No. 1 (BJ)
Heading Transmitter No. 2 (84)
'"The flux valve control transformer 1n the external C-6 1nd1cator 1s used
in these configur ations .
Synchronization between the flux valve and the actual head ing of the
aircraft is indicated by an external sync annunciator or by the compass
synchronization annunciator of the HSI. When the+ is in view on the
annunciator, the compass card is rotating in the counterclcokwise direction
(actual heading greater than indicated) . When the • is in view, the colJl)ass
card is rotating in the clockwise direction (actual headi ng less than
indicated). When synchronized, the annunciator slowly oscillates between
the + and the •·
Page 1-23/1-24
Nov 15/80
INSTALLA'JION
Honeywell
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..JLSPE~Y
,r
INSTALLATION
& MAINTENANCE
H IGHT SYSTEMS
MANUAL
AVIONICS OIVISION
C-14(X I COMPASS SYSTEM
SECTION II
INSTALLATION
2.1
General
This section provides information for installing and interconnecting
co111>onents that COfllJrise the ColJl)ass System. This section has been divided
into the following three subsections: Paragraph 2. 2, Mechanical
Installation, contains informat ion on how and where to mount each component
in the aircraft; Paragraph 2.3, Electrical Installation, contains general
electrical installation data and the point-to-point wiring interconnects;
Paragraph 2.4, Loading/Gradient Character isti cs, contains input/output signal
data for each colJl)onent of the system.
A list of system components and their mating connectors is provided in Table
2- 1.
COl11)onent
C-14 Directional Gyro
C- 14A Directional Gyro
C-14D Directional Gyro
FX- 220 Flux Valve
CS-412 Dual Remote
Compensator
CS-313 Remote Magnetic
Compensator
Sperry
Part No.
Connector
Designation
Hating
Connector
lJl
MS3126Fl8-32S
lJl
1J2
MS3126F18-32S
MS3126F20-41S
5Jl
5J2
3Jl
MS3126Fl4-19SX
MS3126F14-19SY
Cannon Part No.
K03- 19- 20SW
2587193-X,
- 2X, - 3X
2587193-4X
4D20577-3, -6
2594484
2593379- 1
2586257- 1
Mating Connectors
Table 2-1
Page 2-1
Nov 15/80
+~!t~:.?,'
AYt0NtC$ OfV1S.ON
INSTALLATION
& MAINTENANCE
MANUAL
C-14(X> COMPASS SYSTEM
2.2 Mechanical Installation
This paragraph contains information on how and where to mount each cofll)onent
of the Cofll)ass System. Cofll)onents are separated as follows:
C-14(X) Directional Gyros, paragraph 2.2.l;
FX-220 Flux Valve and CS-212 Cofll)ensator, paragraph 2.2.2;
CS-412 Dual Remote Cofll)ensator, paragraph 2,2,3;
CS- 313 Remote Magnet ic Cofll)ensator, paragraph 2.2,4; and,
AN-140 Annunciator, paragraph 2,2.5.
2.2.1 C-14(X) Directional Gyro
(a) Location
Locate the units near and preferably forward of the aircraft's most
aft CG position. Laterally they should be placed within 2 feet of the
aircraft's vertical plane of syflllletry and vert ically they should be
placed within 5 feet of the fuselage reference plane.
(b) Mounting
Mount the gyros rigidly to the aircraft primary structure in the
fuselage, using the mounting holes in the gyro base. See figures 2-1
thru 2-3 for mounting.
NOTE: In dual C-14 installations, the directional gyro should be
mounted so that both spin axes are aligned parallel. This will
be accofllllished when both units are mounted with their
connectors pointing in the same direction. This alignment is
necessary to minimize differences between the two cofll)ass
heading outputs during turns, These differences between the
dual systems are attributed to gimbal error.
CAUTION:
MOUNTING THE DIRECTIOllAL GYRO IN ANY LOCATION SUBJECT TO
EXCESSIVE STRUCTURAL FLEXURE OR VIBRATION MAY IMPAIR
INSTRUMENT OPERATION AND SHORTEN GYRO LIFE. IT IS
RECOMNOED THAT THEY BE MOUNTED IN A LOCATION WHERE
VIBRATION DOES NOT EXCEED 0,5 g AT ANY FREQUENCY,
Page 2-2
Nov 15/80
+~~~~'('(
INSTALLATION
& MAINTENANCE
MANUAL
C•14 !Xl COMPASS SYSTEM
AVIONICS DIVJS'O"I
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1. ~ DENOTES APPAOX. CENTEA OF GRAVITY.
2. APPROXIMATE WEIGHT $ ,5 LBS,
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E2H7U:).C(R)
Outline and Installation of C-14 Directional Gyro,
Part No. 2587 193- 1 thru -7, -21 thru - 26, -33, and -36
Figu re 2-1
Page 2-3
Nov 15/80
+~s~'!"(Y
INSTALLATION
& MAINTENANCE
MANUAL
C-14()(1 COMPASS SYSTEM
AVtONtCS DIVISION
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Outline and Installation of C-14A Directional Gyro,
Part No. 2587193-41 thru -47
Figure 2-2
Page 2-4
Nov 15/80
_JLs;pe~v
,r
INSTALLATION
& MAINTENANCE
FllGHT SYSTEMS
MANUAL
AvtON1CS OfVISION
C•14IX) COMPASS SYSTEM
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2. APPAOX IMATE WEIGHT 6 . 7 L8S.
3. DIM ENSIONS IN PARENTHESES ARE IN
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Outline and Installation of C-14D Directional Gyro,
Part No. 4020577-3 and -6
Figure 2- 3
Page 2-5
Nov 15/80
+~!.~"'
AVIONICS DIVISION
INSTALLATION
II MAINTENANCE
MANUAL
C-14(XI COMPASS SYSTEM
2.2.2 FX-220 Flux Valve and CS-212 Compensator
(a)
Location
The flux valve should be located as far as Possible from all sources
of local magnetic disturbances, such as electrical cables, engines
and magnetic materials. Generally, the best location is in the outer
wing panel, as near the wing tip as possible. Where a wing
installat ion is not feasible, an alternate location in the tail may
be satisfactory.
To detennine a suitable location for the flux valve, place an
uncompensated magnetic compass in each of the Possible locations for
an installation, then turn the aircraft to each of the four cardinal
headings, noting amount of error at locations. While detennining
location, simulate as nearly as possible actual flight conditions by
operating engines, electrical systems, radio equipment, and
accessories. Select location offering least magnetic error.
(b) Mounting
The flux valve should be mounted to a suitable bracket or frame which
is rigidly attached to the aircraft structure such that the flux valve
mounting flange is parallel within 2 degrees of the level flight
attitude on the aircraft.
The bracket used for mounting the flux valve should be of 202-T4
aluminum alloy or its equivalent, with a minimum thickness of 1/16
inch. rt should be reinforced by ribs, flanges, or angles such that
local aircraft structure vibration will not be amplified by more than
15 percent at any frequency experienced or the flux valve will not be
subjected to more than 3 g's acceleration, whichever is smaller. The
mounting flange of the flux va he is not to be considered as adding
to the rigidity of the bracket.
NOTE: If an MC-1 or MC-2 Magnetic Compass Calibrator Set is to be
used for calibration of the Compass System, the flux valve
should be mounted with a 7-inch minimum diameter access hole
directly over the top mount or directly under the bottom mount.
The flux valve top or bottom should be within 3 inches of the
access hole. A 7-inch square access plate is recommended for
mounting in the vertical stabilizer. The nearest edge of the
flux valve should be within 3 inches of the access plate, and
the top of the flux valve should be a minimum of 3-1/2 inches
below the top of the access hole to facilitate use of optical
alignment gear.
The mounting surface should be laid out as shown in figure 2-4.
\-lhenever possible, the unit shoul d be top mounted; that is, with the
mounting flange of the flux valve above the surface of the mounting
bracket. The single drilled hole, shown on the centerline of the
cutout drawing, should face in the direction of f l ight of the
aircraft, and the centerline should be parallel the longitudinal axis
of the a i rcraft.
Page 2-6
Nov 15/80
+~.5~4!'1'
AVIONICS DIYIIIOII
INSTALLATION
• MAINTENANCE
MANUAL
C-141XI COMPASS SYSTEM
Fasten the flux valve to the mounting braclcet with three 6-40 by 3/8
inch (0,138 dial) round head, nonmagnetic machine screws, Sperry Part
No, 319011, The screws are supplied with the flux valve. r~orarily
align the valve parallel to the longitudinal axis of the aircraft;
elongated holes in the flange are provided for making this alignment.
2,2,2
(c) Adjustnents
Refer to Sect ion III for adjustnent procedures,
NOTE: Before adjustnents can be made, all C0"'1onents of the Co""ass
System111Jst be installed,
If the performance of the flux valve is faulty ~lhile checking for
magnetic deviation, index error, or proper C0"'1ensation, it should be
replaced with another unit.
CAUTION:
(d)
DO NOT USE A DC OHMTER ACROSS ANY TERMINALS OF THE FLUX
VALVE. CHECK THE CONTINUITY WITH CONTINUITY CHECKER Tl00870
ONLY,
CS-212 Co""ensator Mounting
The CS-212 Magnet ic COfll)ensator is mounted on top of the flux valve
and is held in pl ace by six screws, which are suppl ied with the flux
valve. See figure 2-4.
Page 2-7
Nov 15/80
.JL.sr=E~Y
,r
INSTALLATION
& MAINTENANCE
FUGHT SVST£M$
MANUAL
AVIONIC$ OIYISION
C-141Xl COMPASS SYSTEM
HUSTIC $TO, NUTS. CAT. NO,
Mf'WA1-t0(QUAUY SrAC:f O ON
f;.(IQ O IA AS SM0w"I
16-«tTHO>
......
10T1'OM U ,N fl._ MOUNTING
816-48-53
Outline and Installation of FX- 220 Flux Valve
and CS-212 Coa;:iensator
Figure 2- 4
Page 2-8
Nov 15/80
FUGHT SYSlEMS
INSTALLATION
& MAINTENANCE
MANUAL
AYt()NtCS orv•SIOH
C•14IXI COMPASS SYSTEM
..JLsr-,E~V
,r
2.2.3 CS-412 Dual Remote Compensator
(a) Location
The recofll11ended location for the unit is i n the cockpit area or
adjacent to it so that adjustments can be made while viewing the
indicators on the instrument panel. Allow enough room in the location
chosen to facilitate rerrova l of the cover. The unit may be mount ed in
allY position.
(b) Mounting
Mount the unit rigidly to the aircraft structure. using the mounting
holes in its base plate. See figure 2-5.
CAUTION:
MOUNTING THE UNIT IN ANY LOCATION SUBJECT TO EXCESSIVE
STRUCTURAL FLEXURE OR VIBRATION MAY IMPAIR INSTRUMENT
OPERATION AND SHORTEN EQUIPMENT LIFE. IT IS RECOMMENDED
THAT THE UNIT BE MOUNTED I N A LOCATION WHERE VIBRATI ON DOES
NOT EXCEED 0.5 g AT ANY FREQUENCY.
(c) Adjustments
Refer to Section III for adjustment procedures.
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Out line and Installation of
Dua l Remote Corrpensator
Fi gure 2- 5
CS-4 12
Page 2- 9
Nov 15/80
+~5~4:Y
AVIONICS D4'11110N
IWTALLATION
•MAtNTINANCE
MANUAL
C-141XI COMPASS SYSTEM
2.2.4 CS-313 Remote Magnetic C~ensator
(a)
Location
The reco11111ended location for the unit is in the cockpit area or
adjacent to it so that adjustnents can be made during a COlllJaSs swing.
Allow enough room in the location chosen to facilitate removal of the
cover and ensure uniJl'1aired operation of controls physically and
visually. If MC-1 or MC-2 electrica l co~ass swing is anticipated,
allow sufficient space for connection to panel connector.
(b) Mounting
Mount the unit rigidly to the aircraft structure, us ing unit dzus
fasteners. See figure 2-6.
CAUTION: fi()UNTING THE UNIT IN ANY LOCATION SUBJECT TO EXCESSIVE
STRUCTURAL FLEXURE OR VIBRATION HAY IMPAIR INSTRUMENT
OPERATION AND SHORTEN EQUIPMENT LIFE. IT IS RECOMMENDED
THAT THE UNIT BE MOUNTED IN A LOCATION WHERE VIBRATION ODES
NOT EXCEED 0.5 g AT ANY FREQUENCY.
(c) Adjustments
Refer to Section III for adjustment procedures.
0
S.00
NOTE:
ALL OIMENSIOl<S AA[ IN INCHES.
Outline and Installation of
CS-313 Remote Magnetic Compensator
Figure 2-6
Page 2-10
Nov 15/80
INSTALLATION
• MAINTENANCE
MANUAL
c.1,00 COMPASS SYSTEM
2.2 . 5 AN-140 Annunciator
(a) Location
The annunciator should be 1110unted on the i nstrument panel and should
be easily seen by the pilot at all times.
(b)
Mount ing
See figure 2-7.
1.2Sf MAX
1··-nur.s-.:M
N:lll'TIVE
f£,WINAI.. M.,iKfO
..........
#u ..,
WUIIE MAX
4 SLOTS.,. Al'A,tT, ,040
DEEP X ,OIJ WIDE
Outl i ne and Installation of AN-140 Annunciator
(null-meter), Part No. 2503148-2
Figure 2-7
Page 2-11
Nov
15/80
+~st~'(,,
AVIONICS DIVISION
tNSTALLATION
a MAINTENANCE
MANUAL
C-14IX) COWASS 5Y$TEM
2.3 Electrical Installation
This paragraph contains the electrical interconnect data required for
instal lation of the C014(X) Compass Systen. Refer to figure 2-8, 2-9, or
2-10 for appropriate interconnect data.
2.4 Loading and Gradient Characterisics
This paragraph contains loading and gradient characteristics for the input
and output signals of each component of the Compass System. Component
infonnation is as fo llows:
C-14A Directional Gyro, table 2-2 ;
C-14D Directional Gyro, table 2-3;
FX-220 Flux Valve, table 2-4,
CS-412 Dual Remote Compensator, table 2-5, and,
CS-313 Remote Magnetic Compensator, table 2-6.
Page 2-12
Nov 15/80
INS'TALLAftON
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Page 2- 17/2· 18
Nov S/ 91
- - 0,0, ' " ' lol!o l"'9f 1t1 'ha cloc:u-
+~st!~"'
AVIONICS DIVIS10H
TITLE:
1.
INSTALLATION
& MAINTENANCE
MANUAL
C-14(XI COMPASS SYSTEM
Loading and gradient characteristics for the C-14A Directional Gyro, Part
No. 2587193-4X.
QUALIFICATIONS
1.1 Technical Standard Order - The C-14A is qualified to TSO-C6c.
1.2 Other Qualification Tests - The C-14A is also qualified to SAE 399A.
2.
2.1
POWER
Input Power
The aircraft ac power supply must be 115 + 5 volts at 400 + 20 Hz, single
phase sine wave (51 maxi,rum harmonic distorti on). Alll)litude modulation of
the power supply for all load conditions shall not exceed 2 percent at aey
frequency. (Percent modulation is defined as one-half of the peak-to-peak
modulation envelope di vided by the carrier amplitude, multiplied by one
hundred.) Within the power supply's load rating, its output iffl)edance shal l
be less than 0.3 ohm for sinusoidal load variations at all frequencies below
10 Hz.
Maximum starting power required i s 40 VA.
Maximum runni ng power required is 30 VA.
2.2 Output Power - The following outputs are available for external power
requirements.
26 volts, 400 Hz, 26 VA; pins lJl-S to lJl-T (Lo)
5 volts, 400 Hz, 6 VA; pins lJl-W to lJI-T (Lo)
3.
INPUT SIGNALS/COMMANDS
3.I Slave-Free Switch - In the free mode, it removes slaving conmand by opening
lJl-G t o lJl-E. In the slave mode, it closes the circuit between lJl-G and
lJ l-E.
3.2 External Synchronizat ion Swi t ch - With the Slave-Free switch in the Free
position, moving this center off switch to the INCREASE (+) posi t ion
connects lJl-f to lJl-A. This causes the compass card to rotate
counterc lockwise. Moving this switch to the DECREASE (e ) pos ition connects
lJl-g to lJl-A. This causes the COl!lJass card to rotate clockwise. With the
Slave-Free switch i n the Slave posit ion, moving this switch in either
direction (+) or ( e) engages the fast slave mode.
C-14A Directional Gyro
Loading and Gradient Characteristics
Table 2-2
Page 2-19
Nov 15/80
..JLSPe~v
- , , - FLIGHT SYSTEMS
AVtONICS IMY'ISIOH
4.
INSTALLATION
• MAINT£NANCE
MANUAL
C-l◄ CXI
COMPASs SYSTEM
OUTPUT SIGNALS
4. 1 Heading Synchro Transmitter No. l (B3) provides continuous heading data
throusjlout 360 de~rees of heading change. The output is on pins L, M, K of
lJl (ARING 407 (XJ , (Y), (Z), respectively) with 11.8 volts leg-to- leg which
represents a nominal sensitivity of 200 mV per degree.
Loading characteristics are:
DC Resistance± 15% - Rotor = 16 ohms; S~ator = 5 ohms
Impedance t 15% - Zso: 23 ohms at 70°; Zro ~ 150 ohms at 78°
Maxi mum load is three AY- 500 (222 + j 470) synchro loads.
4.2 Heading Synchro Transmitter No. 2 (B4) (Applicable to -43 , - 46 , and -47 uni ts
only).
Exactly same characteristics as Heading Synchro No. 1. The No. 2 t r ansmitter
is driven by an antibacklash gear for use wit h the Sper ry autopilot
appl ication.
4. 3 Clutched Potentiometer (B4) (Applicable to -42 and - 45 units only).
The clutched potentiometer cons ists of a 5k-ohm potentiometer with a
sensitivity of 2.5 volts per degree and a clutch which is geared to the
output axis of the gyro. The clutch r equires 28 vo l ts de excitation and the
potentiometer requi res 100 vol t s de excitat ion. The potentiomet er provi des a
li near output proportional to gyro rotation up t o a maximum of +20 degrees.
The arm of the potentiometer is spri ng l oaded so that when the clutch is
di sengaged the arm will return to the center (null) position.
4.4 Monitor Interlock
Two sets of relay contacts are controlled by the gyro monitor. Pins lJl -h
and lJl- j are used with the autopilot. Pins lJl- c, d, e are used for f l ight
directors or i nstruments. When the gyro n~nitor is valid, pins lJl-h and j
and also pi ns lJ l-d and e are closed.
4.5 Sync Annunciator
The output from lJl pins U and Vis capable of driving only ONE sync
annunciator with the fol l owing characteristics:
DC Resistance= 250 ohms
Meter Movenent 250-0- 250 microamps
C-14A Directional Gyro
Loading and Gradient Character istics
Table 2- 2 (cont)
Page 2-20
Nov 15/80
+~~.t!~Y
AvtONICS OIVISION
TITLE:
-
INSTALLATION
• MAINTENANCE
MANUAL
C·14(Xl COMPASS SYSTEM
Loading and gradient character! st 1cs for the C-140 Direct ion al Gyro, Part
No. 4020577-3 and -6.
1. QUALIFICATIONS
1.1 Technical Standard Order - The C-140 is qualified to TSO-C6c.
1.2 Other Qualification Tests - The C-14D is also qualified to SAE 399A.
2.
2.1
POWER
Input Power
The aircraft de power supply must be 22 to 29,5 volts de. Ripple amplitude
shall not exceed 2.0 volts peak. The 28-volt de input shall be connected to
pins 1J2-C (+) and 1J2-B (-).
Maximum startin9 power required is 125 watts.
Maximum runnng power required is LOO watts.
2.2 Output Power - The following outputs are available for external power
requirements:
115 V, 400 Hz at 1J2-T •••••.•• 0 to 22* VA to instrument canponents
26 V, 400 Hz at 1J2-S •••.••.•••••• 3 VA to flux valve
26 V, 400 Hz at 1J2-k .••••••.•• 0 to 42* VA to instrument canponents
and heading CS excitation**
5 V, 400 Hz at 1J2-W .••••.••.••••••• 5 VA to i nstrument lighting
Tocal
50 VA
*Sum of output power fran these two sources shall not exceed 42 VA.
**Each heading CX requires 4.5 VA excitation.
3.
INPUT SIGNALS/COl'flANDS
3.1 Slave-Free Switch - In the free mode, it renoves slaving command by opening
1J2-G to 1J2-E. In the slave mode, it closes the circuit between 1J2-G and
1J2-E.
3.2 External Synchronization Switch - With the Slave-Free switch in the Free
position, moving this center off switch to the INCREASE (+) position
connects 1J2-n to 1J2-p. This causes the compass card to· rotate
counterclockwise. Moving this switch to the DECREASE (e) position connects
1J2- n to 1J2-m. This causes the compass card to rotate clockwi se. With the
Slave-Free switch in the Slave position, moving this switch in either
direction(+) or(•) engages the fast slave mode.
C-140 Directional Gyro
Loading and Gradient Characteristics
Table 2-3
Page 2-21
llov 15/80
..JL.SPe~v
1r
FLIGHT SYSTt:MS
AVtONICS OIVISJON
4.
4.1
INSTALLATION
& MAINTENANCE
MANUAL
c.,14(X) COMPASS SYSTEM
OUTPUT SIGNALS
Headi ng Synchro Transmitter No. l provides continuous heading data throughout
360 de~rees of heading change. The output is on pins L, M, K of 1J2 (ARlNC
407 (X), (Y), (Z), respective ly) with 11.8 volts leg-to-leg which represents
a nominal sensitivity of 200 mV per degree.
Loading characteristics are:
DC Resistance+ 15%
Rotor = !€"°ohms
Stator= 5 ohms
Impedance + 15%
Z = 23 ohms at 70°
Z~~ = 150 ohms at 78°
Maximum load is three AY-SOO (222 + j470) synchro loads.
4.2 Heading Synchro Transmitter No. 2
Exactly same characteristics as Heading Synchro No. 1. The No. 2 transmitter
is driven by an ant ibacklash gear for use with the Sperry autopilot
app 1i caU on.
4.3 Monitor Interlock
Two sets of relay contacts are controlled by the gyro monitor. Pins 1J2-h,
i, and j are used with the autopilot. Pins c, d, and e are used for fl i ght
director s or instruments. When the gyro monitor is valid, pins 1J2-h and j
and also pins lJ2-d and e are closed.
4.4
Sync Annunciator
The output from 1J2 pins U and V is capab 1e of driving only ONE sync
annunciator with t he fol l™ing characteristics:
DC Resistance = 250 ohms
Meter Mo ve,aent 250-0-250 mi croafll)s
C-14D Directional Gyro
Loading and Gradient Characteristics
Table 2-3 (cont)
Page 2-22
Nov 15/80
+~~!~:;a,'
AVIONICS OMSION
INSTALLATION
• MAINTENANCE
MANUAL
C:.14CXI COMPASS SVSTEM
TITLE: Loading and gradient characteristics for FX-220 Flux Valve, P~rt No.
2594484.
l.
QUALIFICATIONS
1.1 Technical Standard Order - The flux valve conforms to TS0-C6c.
2.
POWER
The aircraft ac power supply must be 115 + 5 volts at 400 + 20 Hz, single
phase sine wave (SS maximum harmonic distortion). Ampl i tude modulation of the
power supply for all load conditions shall not exceed 2 percent at any
frequency. (Percent modulation is defined as one-half of the peak-to-peak
modulation envelope divided by the carrier affl)litude, irultiplied by one
hundred.) Within the power supply's load rating, its output impedance shall
be less than 0,3 ohm for sinusoidal load variations at all frequencies below
10 Hz.
Power consumnption, 26V, 400 Hz for the flux valve is 1.1 VA.
FX-220 Flux Valve
Loading and Gradient Characteristics
Table 2-4
Page 2-23
Nov 15/80
..JLSPe~v
- , , - - FLIGHT SYSTEM$
AVH)trUCS DCVISION
TITLE:
1.
INSTALLATION
• MAINTENANCE
MANUAL
C-141Xl COMPASS SYSTEM
Loading and gradient characteristics for CS-412 Dual Remote Compensator,
Part No. 2593379-1.
QUALIFICATIONS
1.1 Technical Standard Order - The dual remote compensator confonns to TSO-C6c.
2.
POWER
The aircraft ac power supply must be 115 + 5 volts at 400 + 20 Hz, single
phase sine wave {Si maximum harmonic distortion). Amplitude modulation of the
power supply for all load conditions shall not exceed 2 percent at any
frequency. {Percent modulation is defined as one-half of the peak-to-peak
modulation envelope divided by the carrier ampl i tude, multiplied by one
hundred.) Within the power supply's load rating, its output impedance shall
be less than 0.3 ohm for sinusoidal load variations at all frequencies below
10 Hz.
Power consumption, 26V, 400 Hz is 2.5 VA.
CS-412 Dual Remote Compensator
Loading and Gradient Characteristics
Table 2-5
Page 2-24
Nov 15/80
1~~~~~"'
AV1ONICS DMStON
TITLE:
-
INSTALLATION
• MAINTENANCE
MANUAL
C,t41XI COMPASS SYS'nM
Loading and gradient characteristics for CS-313 Remote Magnetic
Compensator, Part No. 2586257-1.
1. QUALIFICATIONS
1.1 Technical Stan·dard Order - The remote magnetic canpensator confonns to
TSO-C6c.
2.
POWER
The aircraft ac power supply must be 115 + 5 volts at 400 + 20 Hz, single
phase sine wave (5% maximun hannonic distortion). Ampl itude modulation of the
power supply for all load conditions shall not exceed 2 percent at aey
frequency. (Percent modulation is defined as one-half of the peak-to-peak
modulation envelope divided by the carrier amplitude, multiplied by one
hundred.) Within the power supply's load rating, its output impedance shall
be less than 0.3 ohm for sinusoidal load variations at all frequencies below
10 Hz.
Power consumption, 26V, 400 Hz is 1.75 VA.
CS-313 Remote Magnetic Compensator
Loading and Gradient Characteristi cs
Table 2-6
Page 2-25/2-26
Nov 15/80
+~~!~°'.,,
AV.ONICS DIVISION
INSTALLATION
• MAINTENANCE
MANUAL
C-14CXI COMPASS SYSTEM
SECTION III
COfll'ASS SWING CALIBRATION
3.1 General
This section contains the procedures necessary to ensure that the Compass
System is operating properly when instal led in the aircraft, and the
procedures requi red to perfonn a canpass swing calibration. This
calibration should be perfonned after installation of the equipment in the
aircraft prior to actual flight use of the aircraft and thereafter only when
necessary to maintain desired heading accuracy, and when a system component
is changed.
3.2 Compass Swing and Adjustment
3.2,l Flux Valve Index Error Adjustment
NOTIS:
1.
When perfonning a compass swing, the aircraft should be in its
nonnal flight position with the electrical system and radio
equipment operating. The engines need not be running during
this adjustment, unless their operation affects the heading
indication of the flux valve.
2. On initial compass swing, the compensator adj ustment
potentiometers should be set to approximate center position.
3. The Sperry MC-1, MC-IM, or MC-1 Magnetic Compass Calibrator Set
can be used for index error and canpensator adjustments instead
of procedures provided below.
3.2.2 Energize t he Compass System and allow several minutes for the gyro to reach
operating speed and for the system to slave to the magnetic heading.
3.2.3 Position the aircraft on a canpass rose and turn it to each of the four
cardinal headings.
3.2.4 Allowing suff icient time for the heading indicator to settle, record the
differences in readings between the heading indicator and the compass rose
at each cardinal heading as plus or minus, dependi ng on whether the dial
readings are greater or less than the compass rose readings.
NOTE:
Instead of the canpass rose, a magnetic sighting compass may be
used. To take a reading, the compass is located at a considerable
distance fore and aft of the aircraft and is moved back and forth
from the line of sight coinciding with the plane extended
centerline. When a sight is taken facing aft, 180 degrees must be
added or subtracted from the sighting compass reading. When facing
fore, the compass reads directly.
3.2.5 Add the err ors algebraical ly and divide by four.
error.
The result is the index
Page 3•1
Nov 15/80
+~~t~-<'1'
AVIOHlCS OJVISIOft
INSTALLATION
• MAINTENANCE
MANUAL
C•14CXI COMPASS SYSTEM
3.2.6 Loosen the screws holding the flux valve flange to its mounting surface
and rotate the flange of the unit to cancel out the index error. If the
error is positive, the flange should be rotated in the counterclockwise
direction (giving a minus reading on the flange) as observed fran above
the unit.
3.2.7 If the error is negative, rotate the flange in the clockwise direction
(giving a plus reading on the flange). The amount of rotation should
equal the index error.
3•.2. 8 Tighten the mounting screws and recheck the readings at the four cardi na 1
headings . Recalculate the index error to make sure it is near zero.
3.2.9 If the index error is not zero, readjust the flux valve flange until this
error is cancelled.
3.2.10 Any remaining errors in excess of ±1 degree which are caused by
extraneous magnetic fields should be counteracted by readjusting the
canpensator.
Page 3-2
Nov 15/80
+~st~-<V
AVIONICS DIVISION
INSTALLATION
• MAINTENAN<:£
MANUAL
C-141XI COM'ASS SYSTEM
3.3 CS-412 Dual Remote Compensator Adjustments
!!Qm:
l,
The CS-412 Dual Remote Compensator is a dual corrpensator used
with dual compass systems. The following adjustment .procedures
are required for each corrpass system.
2,
Before making the following adjustments to the corrpensator,
perform flux valve index error adjustment.
3.
The MC-1, MC-lM, or MC-2 Magnetic Compass Calibrator Set can be
used for conpensator adjustment in lieu of the procedure
provided be 1ow.
3.3.1 Remove the conpensator cover.
3.3.2 Make sure compensation potentiorreters are in their center position.
3.3.3 Using a cofll)ass rose, place the aircraft on a north heading and allow
COfll)aSS dial to settle.
3,3.4 Cofll)ensate for any difference between actual heading and corrpass dial
indication by loosening locking nut and adjusting N-S {North-South)
potentiometer on conpensator. Tighten locking nut.
3.3.5 Place the aircraft on an east heading and allow corrpass dial to settle.
3.3.6 COlll)ensate for any difference between actual heading and colll)ass dial
indication by loosening tocking nut and adjusting E-W {East-West)
potentiometer on compensator. Tighten locking nut,
3.3.7 Place the aircraft on a sout h heading and allow co111>ass dial to settle.
3.3.8 COITl)ensate for half of any difference between actual heading and colll)ass
dial indication by loosening locking nut and adjusting N-S potentiometer on
COfll)ensator. Tighten locking nut.
3.3.9 Place the aircraft on a 11est heading and allow cofll)ass dial to settle,
3.3.10 Compensate for half of any difference bet ween actual heading and compass
dial indicat ion by loosen ing l ocking nut and adjusting E-W potentiometer
on cofll)ensator. Tighten tocki ng nut.
3.3.11 The co1Tpensator should now be fully adjusted for proper compensat i on. As
a check, swing the aircraft on JO-degree increments and note readi ngs on
compass dial. All readings shoul d be within l degree of the act ua l
heading. If errors are greater than 1 degree, repeat index error
adjustn~nt and above adjust ments for greater accuracy.
Page 3-3
Nov 15/80
FLIGKJ' SVSTDIS
INSTALLATION
• MAINTENANCE
MANUAL
AVIONICS DIVISION
C-1'lXI COMPASS SYSTEM
..JLSPE~V
,r
3.4 CS-313 Remote Magnetic Compensator Adjustment
3.4.1 General
After the remote colJl)ensator has been installed, it must be adjusted t o
provide proper colJl)ensation to the aircraft co1Tpass system. Adjustments
may be most conveniently made while using an MC-1 or MC-2 Magnetic Compass
Calibrator Set. The magnetic COIJllass calibrator set can be connected to
the remote magnetic corrpensator through connector 3J2 and will provide the
effect of positioning the aircraft on various compass headings without
actually moving the aircraft. If the magnetic corrpass calibrator set is
not used, the aircraft must be accurately positioned on a cof11)ass rose to
each of the headings noted in the following procedures.
NOTES:
1.
When performing a corrpass swing, the aircraft should be in its
normal flight posit ion with the electrical system and radio
equipment operating. The· engines need not be running during
this adjustment, unless their operation affects the heading
i ndi cation of the flux valve.
2.
The terms "aircraft heading" and "actual heading" will be used
throughout this procedure to indicate the aircraft directions
obta i ned either by simulation using the MC-1 or MC-2 Magnetic
Corrpass Calibrator Set or by actual rotation of the aircraft on
a corrpass rose. Throughout this procedure, errors will be
defined as positive if the indicated heading (as read on the
aircraft compass system ) is greater than the actual heading and
negative if the indicated heading is less tha.n the actual
heading.
3.
The follow·ing procedures assume the use of a magnetic co111>ass
calibrator set and adjustment for each error is described
separately. If the aircraft is to be swung on a con1>ass rose,
it will be possible to combine adjustments to reduce the number
of times the a i rcraft must be repositioned,
3.4.2 Remove cover from colJl)ensator.
Page 3-4
Nov 15/80
INSTAl.LATIDII
• MAINTl:N'INCE
MANUAL
+~~l~:.:v
C•14 1X) CQMPAII SYSTIM
A'tlOIOC$ OMSION
3. 4.3 Before starting adjustment procedures, set c~ensator controls as
foll CM S:
The midrange of the N-5 and E-W coopensators is obtained when minirum de
voltage is developed across the appropriate test jack and pin F of
connector 3J2,
3.4.4
Index Error Adjus t ment
To determine the i ndex error, set the aircraft heading to 0, 90, 180, and
270 degrees, In turn, all owing the Co!!l>ass System to synchronize and
stabilize for l mi nute at each heading. Record the difference between the
indicated headings (as read on the aircraft Coq,ass System) and the actual
heading.
Error
Record headi ng errors
at each heading in
chart at right ...... .
Headi ng
• -
o•
90°
180°
270°
Add each
col urm of errors . .. ..
Add the sum of the two
colunns algebraica l ly ••
Divide al gebraic sum by
4 to obtain index error . •• •
Sum
Algebraic Sum
Index Error
Page 3-5
Nov 15/80
+~~t~-<Y
AVIONICS DMSIOf<
INSTALLATION
• MAINTENAllila
MANUAL
C•140CI COMPASS SYSTEM
Rotate the INDEX control until the indicated heading changes by the amount
of the index error. If the index error is negative. rotate the INDEX
control clockwise. If the index error is positive. rotate the I NDEX
control counterclockwise. Lock the INDEX control.
u,oc
3.4.5
+
Permanent Magnet (One-Cycle) Error Adjustment
To determine the permanent magnet error. set the aircraft heading too.
90, 180, and 270 degrees, in turn, allowing the COIT'pass System to
synchronize and stabi lize for l minute at each heading. Record the
difference between the indicated headings (as read on the aircraft Compass
System) and the actual headings.
Co~ute the north-south error as follows:
N-S Error= Error (0° Heading) - Error (180° Heading)
2
To correct for this error . set the aircraft heading to O degree and adjust
the N-S co~ensator until the heading indi cation is increased (negative
N-S error) or decreased (positive N-S error ) by the amount of the
north-south error. Tighten lock.
Co~ute the east-west error as follows:
E-W Error= Error (90° Headiny) - Error (270° Heading)
2
To correct for this error, set the aircraft heading to 90 degrees and
adjust the E-W co~ensator until the heading indication is increased
(negative E- l~ error) or decreased (positive E-W error) by the amount of
the east-west error. Tighten lock.
,,,_.
I-W
~:~.
'/,,, .......,.
;-o• ••n
Page 3-6
Nov 15/80
+~!t~'<Y
AVIONICS OfvtSION
INSTALLATION
& MAINTENANCE
MANUAL
C•14lXI COMPAi$ SYSTEM
3.4.6 Transmission Error Adjustment
To detennine the transmission (two-cycle) error compensation required, the
residual error in the Compass System 111.1st be determined by means of an
eight heading compass swing,
Set the aircraft heading to 0, 45, 90, 135 , 180, 225, 270, and 315 degrees.
in turn, allowing the Compass System to synchronize and stabilize for 1
minute at each heading, Record the difference between the indicated
headings (as read on the aircraft Compass System) and the actual heading.
Compute the D and E coefficients which detennine the di rection and
magnitude of the transmission error as follows:
D • 1/4 [Error (45° Heading) - Error (135° Heading)+ Error
(225° Heading) - Error (315° Heading)]
E = 1/4 [Error (0° Heading) - Error (90° Heading) + Error
( 180° Heading) - Error (270° !leading)]
The direction and magnitude of the transmission error may be obtained fr~n
these O and E coefficients by either of the following two methods:
1.
Compute the direction and magnitude of the transmission error as
fol lows:
1
Direction of error~ 1/2 tan" o/E
Magnitude of error=
Vo2 + t2
Page 3-7
Nov 15/80
+~st~-<'1'
AVIONICS OIVIStON
2.
INSTALLATION
& MAINTENANCE
MANUAL
C•141XI COMPASS SYSTEM
Scale the direction and magnitude of the transmission error from graph
as follows:
Draw a line between the value of Don the D and D' scales. Draw a line
between t he value of Eon the E and E' scales. At the intersection of
the two li nes, read the magnitude of the error on the circular sca le.
Draw a line from the or igin to the intersection of the lines just
drawn. Read the directions of the error on the polar scale. EXA!f>LE:
If D = +0.6 degree and E = - 0 . 8 degree, magnitude is 1.0 degree and
direction is 71 degrees .
_,..,.
NII
CICCIIH
o
-o.s•
"
..,,s.
E
ftlf'"* <W 1,
-IO
•s
•o.s•
•o
"
••
10
•
••
I)' 0
-o.s·
-~-I
...,.
..
to
0
0
I)
'"
ITO
IOO
I%$
I SO
~
140
-o.s·
l4S
Page 3-8
Nov 15/80
+~sl~~,,
AVIONICS DIVIStON
INSTALLATION
& MAINTENANCE
MANUAL
C-14IXI COMPASS SYSTEM
Set the TRANSMISSION knob for the direction of the transmission error
co111puted or scaled above. Tighten lock •
•
2,
Set the aircraft heading as close as possible to the setting on the
TRANSMISSION knob, Rotate the TRANSMISSION magnitude control
clockwise until the heading indicated on the aircraft Compass System
is decreased by the magnitude of the error. Tighten lock.
3.4.7 Final Check
As a final check of the accuracy of the instal led remote compensator, set
the aircraft to 24 headings in 15-degree increments starting with O
degree, allowing the Conl)ass System to synchronize and stabilize for l
minute at each heading. Record the error at each heading.
If errors are within ±1 degree, replace front cover on the co"1)ensator.
If errors are not within specified limits, touch up of sone of the
compensator adj us trnents may be required.
Page 3-9/3-10
Nov 15/80
+~!~~~,,
AVIONICS DIYISI~
INSTALLATION
• MAINnNANCE
MANUAL
C-l4(Xl COM'ASS SYSTEM
SECTION IV
GROUND OPERATIONAL TESTS {GROUND CHECK)
4.1 General
This section describes procedures for checking the COlll>ass System for correct
installation and proper operation of all corriionents in the system.
4.2 Compass System Checkout Procedure
4.2.l Set the FREE/SLAVED (OG/HAG) switch in the SLAVED (MAG) position.
Apply power to system,
4.2.2 After the aircraft power has been applied for a minimum of 3 minutes the
Horizontal Situation Indicator (HSI) OFF flag shall be out of view, the
synchronization annunciator shall indicate a null, and the compass
indication on the HSI shall be synchronized to magnetic heading and shall
agree with actual heading.
4.2.3 Rotate the pilot's directional gyro (DG No. l) in a cct1 direction as viewed
from the top. The heading indication on the HSI shall decrease and the
synchronization annunciator shall indicate a cross (+).
4.2.4 Rotate the DG in a cw direction as viewed from the top. The heading
indication on the HSI shall increase and the synchronization annunciator
shall indicate a dot (e). Return the DG to its normal position.
4.2.5 Set the FREE/SLAVED (DG/HAG) switch in the FREE (DG) position.
synchronization annunciator shall indicate a null.
The
4.2,6 Set the MANUAL SYNC switch in the cross (+) (INC] position. The compass
card on the HSI shall slowly rotate ccw (increasing heading).
4.2.7
Set the MANUAL SYNC switch in the dot (•) (DEC] position.
on the HSI shall slowly rotate cw (decreasing heading).
The compass card
4.2.8 With the FREE/SLAVED (DG/MAG) switch in the FREE (DG) position, use the
MANUAL SYNC switch to rotate the compass card on the HSI to obtain a
headi ng indication of 20 degrees less than actual magnetic heading of
aircraft (towards e). Return the FREE/SLAVED (DG/MAG) . switch to the SLAVED
(MAG) position. The synchronization annunciator shall i ndicate a cross
( +).
4.2.9 Monentarily set the MANUAL SYNC switch in the cross (+) [INC] position.
The Compass System shall engage the fast slave mode (HSI COMP flag in view)
and remain in the fast slave mode until the compass card is with in a few
degrees of the magnetic heading. When the system switches to s l ow slave
mode, all flags should retract.
Page 4-1
Nov 15/80
+~~;ey
AYIOMICSDMSION
INSTALLATION
I MAINTENANCE
MANUAL
t-1'(Xl COMPASS SYST£M
4.2.10 With FREE/SLAVED (DG/HAG) switch in the FREE (DG) position, use the MANUAL
SYNC switch to rotate the co~ass card to obtain a heading indication of
10 degrees more than magnetic heading (towards+). Return the FREE/SLAVED
(DG/MAG) switch to SLAVED (HAG) position. The synchronization annunciator
on the HSI shall indicate a dot (1), The con-.iass cards shall slowly
synchronize to the magnetic heading, at whi ch time the synchronization
annunciator shall indicate a null .
4.2.11
If applicable. repeat tests 4.2,1 tnru 4.2,lD for copilot's Cofll)ass
System.
Page 4-2
Nov lS/80
Honeywell
INSTALLATION
& MAINTENANCE
MANUAL
C-14(X) COMPASS SYSTEM
SECTION V
SHIPPING, HANDLING, AND STORAGE
I
Refer to manual, Honeywell Pub. No. 09-1100-01, for detailed procedures for
preparing all System components for storage or shipment .
Page 5-1/5-2
Nov 5/91
Use O' disclosure of •nform•tion on this page 1$ sub,ect to
th(j re$tr1ctt0ns
on the 11Ue page ot thts document