m4d Installation Manual
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Description
M-4D Automatic Flight Control
System
.
3
Avionics Division
Bendix Avionica Division
NOTE
UNUSUAL L OR SPECIAL SERVICEPROBLEMS SPECIALSERVICE ARISE, CONTACT ARISE, IF ANY UNUSUA DEPARTMENT376, BENDIXAVIONICS DIVISION, FIELDSERVICE FIELDSERVICEDEPARTMENT 376, 2100 N.W. 62ND STREET, FORT LAUDERDALE,FLORIDA33310. FLORIDA33310. STREET,FORT EQUIPMENTSHOULDBE RETURNED RNEDTO THEFACTORYFOR THEFACTORYFOR REPAI REPAIR R NO EQUIPMENTSHOULD BERETU UNTIL A RETURNAUTHORIZATION (RA) FORM IS REQUESTED AND REQUESTEDAND RECEIV REC EIVEDFRO EDFROM M THE FAC FACTOR TORY Y SERVIC SERVICE E DEPART DEPARTMEN MENTOF TOF BENDIX AVIONICSDIVISION.
PROPRIETARY
NOTICE
This document contains proprietary information such information may not be disc and discllose sedd to others for any purpose nor used for manufac-
turing purposes
without
written
from THE BENOlX CORPORATION.
permission
Bendix
Avionics Division
M-4D AUTOMATIC To:
Holders
of M-4D Installation
Installation Manual CONTROL
FLIGHT
Manual
SYSTEM
I. B. 20004
REVISION
NO. 2
to INSTALLATION
MANUAL
covering M-4D AUTOMATIC Date of Or Orig igin inal al Date of Revision Date of Revision
Publication No. 1 No. 2
FLIGHT
CONTROL
SYSTEM Dec/72 Aug/74 Oct/75
INSTRUCTIONS: 1.
Replace manual pages listed under REMOVE PAGES with revision under INSERT PAGES as indicated for each manual part below. REMOVE
PAGES
INSERT
i/vi 1-3/1-10 1-13/1-14 1-19 1-20 2-1/2-8 2-13/2-14 2-19/2-20 2-47/2-48 2.
Discard
this instruction
PAGES
i/vi 1-3/1-10 1-13/1-14 1-19 1-20 2-1/2-8 2-13/2-14 2-19/2-20 2-47/2-56 sheet.
pages listed
Bendix Avionica Division M-4D AUTOMATIC
Installation Manual
FLIGHT
SYSTEM
CONTROL
TABLE OF CONTENTS I DESCRIPTION
SECTION
& OPERATION
Paragraph
Page 1-1
1.
General
2.
System
Description
3.
Leading
Particulars
4.
Component Descriptions A. Components Basic
5.
6.
7.
-----------------------------------------------
-- -- --- -- -- -- --- -- -- -- -
Flight
C.
Situation
Display
D.
Compass
System
AccessoryItems Instruments
B.
Items
to AFCS
1-4 1-5
-------------------------------
--------------------------------------
Indicators
(HSI)
1-6
---------------------------
1-6
--------------------------------------
1-7 System
& Compass
Required
General
B.
Instrumentation
C.
4-InchInstruments
D.
3-InchInstruments
E.
3-Inch Attitude
F.
Compass
Installtion
But No Nott Su Supp ppli lied ed
Configurations
A.
Accessories
-
-
-
-
-
-
-
-
-
-
-
1-7
-
1-7
---------------------------
1-8
-------------------------------------
1-8
--------------------------------------------
& Vert Vertic ical al
Reference
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1-9
-------------------------------------
Gyro
System
1-8 1-9
--------------------------------------
1-10
------------------------------------
1-10
--------------------------------------
1-10
----------------------------------------------
A.
System
B.
Flight
C.
GeneralOperatingInstructions
Controls
Annunciators
Director
Controls
(1)
Operating
(2)
AFCS Engage
& Annunciators
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
YAW Damper
Engage
(5)
Basic
Operation
(6)
Command
-------------------------------
---------------------------------
- -- -- --
-
-
1-14
1-16 1-16
-----------------------------
Procedure
-
1-16
- -- -- -- --- -- -- -- -- --- -- -
Procedure
-
1-16
-------------------------------
Procedure
Maneuvers
-
------------------------------
(4)
Attitude
1-10
-----------------------------
Limitations
(3) AFCS Disengage
I.B.20004
1-4
-----------------------------------------
A.
Operation
1-2
--- -- -- -- --- -- --
------------------------------------
Directors
B.
System
1-1
---------------------------------------
--------------------------
1-16 1-17 1-17
i
Revised
Oct 75
Bendix Avionics
Installation
Manual
Division
M-4D AUTOMATIC
CONTROL
FLIGHT
SYSTEM
TABLE OF CONTENTS SECTION I DESCRIPTION
AND OPERATION
Paragraph (7)
Ve:dicalModes
(8)
LateralModes
(9)
Flight Director Flight Director
(10)
1-17
-¯¯¯¯¯¯¯¯¯ -~¯¯--¯¯¯¯ ¯-¯¯¯¯------¯¯¯
1-18
· ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ~¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯ ¯
Operation Adapter Boards
1.
General
2.
Unpacking Pre-Installation A. B.
4.
5.
1-19 1-20
-----------------------------
-------------------------
II INSTALLATION
SECTION
3.
Page
.
¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ~
¯
¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯¯
Check
Installation General
B.
Component
C.
Wiring
Locations
_
_
_
_
_
_
_
-
-
-
_
_
_
_
_
_
_
_
_
_
Check-Out
Manual Electric
D.
Servo Forces
E.
LateralModes
F.
VedicalModes
G.
Flight
H.
Attitude
_
_
_
_
_
_
_
_
_
_
_
_
_
_
-
-
-
-
2-6
----------------------------
2-6 2-6 2-7
-----------------------------------¯¯¯¯
Trim & Engage
Check Logic
------------------------------
2-7
------------------------------
2-10
----------------------------------------
2-11
---------------------------------------
Check-Out
Director
---------------------------------
Gyro Check and Calibration
-
-
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-
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-
-
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-
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-
B.
In-Flight
Instructions Procedures
YAWTrim
-
-
2-12 2-13 2-13
------------------------------------------
Preliminary
2-4 2-5
___ _ __ _
--------------------------------------------
A.
2-1 2-4
Check Calibration------------------------------------------------------------------Check & Calibration--
I. B. 20004
-
2-4
_
_
______
C.
(1)
-
______-
____________________
Preliminay
Flight
_
____- - - - -
B.
7.
_
--_______-_________
General
Pre-Flight
_
2-1
- --- -- -- -- ---
____
A.
6.
Adjust
2-1
¯ ~ ¯ ¯ ¯¯ ¯ ¯~ ¯ ¯
- -- --
______________
A.
¯¯
_____-- -- --- --
2-1
¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ¯¯ ¯ ¯
¯~ ~ ~
¯¯¯¯¯¯
InsenionofBoards Servo Capstan Torque
Post Install
2-1
¯ ~ ¯¯ ¯ ~ ¯ ¯ ¯¯ ¯
2-14 2-14
---------------------------------
2-16
------------------------------------
2-16
----------------------------------------
Revised
Oct/75
il
Bendix Avionics Division M-4D AUTOMATIC
Installation Manual CONTROL
FLIGHT
SYSTEM
TABLE OF CONTENTS II INSTALLATION
SECTION Paragraph
C.
Page ( 2)
Basic
Attitude.
Alt. Hold & Pitch Comm.
(3)
Flight
Director
Adjustments
(4)
Lateral
(5)
Approach
(6)
Go Around Test
(7)
Back-CourseApproachTest
(8)
FlightDirectorTests
Optional (1)
Mode Adjustments
Max.
-
-
-
-
-
-
-
-
-
-
-
-
2-17 2-17
-
--------------------------
& Operation
& Glide Slope Mode Check
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-
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-
-
2-17 2-18 2-19
-----------------------------------
___
___ _ __
______
Method of Se Sett ttiing Attitude
Roll Gyro Sensitivity
____ _
_
__ _ __ _ _
Gyro
_
2-19 2-20
----------------------
2-20
-------------------------------
(2) Pitch Gyro Sensitivity Summary of In-Flight Controller
2-19
_ __ _
__ _
-------------------------------
D.
-
Adjustments
------------------
2-20 2-20
LIST OF FIGURES Page
Figure 1-1
M-4D Automatic
1-2
5485A Flight
1-3
5486A Mode Selector
1-4
5487G Flight
2-1
2268A-1
Servo Capstan
2-2
2268A-1
Capstan
2-3
5485A 5487G Flight
I. B. 20004
Flight
Controller
Control (wo
System Mode Selector)
Annunciator
Controller
-------------------
Assembly Adjustment Torque
--------------------
1-15 2-2
--------------------------
2-3
------------------------
Adjustments
1-15 1-15
--------------------------
(w Mode Selector)
Controller
vi
----------------------
-------------------
2-15
iii
Revised
Oct
Bendix Avionica Division M-4D AUTOMATIC
installation Manual FLIGHT
CONTROL
SYSTEM
LIST OF FIGURES Figure
Page 2-15
2-4
Flight
2-5
Outline,
5487G Flight
Controller
-----------------------
2-21
2-22
2-6
Outline,
5485A Flight
Controller
-----------------------
2-23
2-24
2-7
Outline,
5486A Mode Selector
2-25
2-26
2-8
Outline,
5536F Computer
2-27
2-28
2-9
Outline,
Computer
------------------------
2-29
2-30
2-10
Outline,
3013H Primary
------------------------
2-31
2-32
2-11
Outline
2-33
2-34
2-12
Outline,
2-13
Outline,
2-14
Outline,
2-15
Outline,
2-16
Outline,
2-17
Outline,
2-18
Outline,
2-19 2-21
Outline, AD-854A Trim Adapter M-4D Collins FD-112C or 112V Interface M-4D Collins FD-108 329B-7R Interface
2-22 2-23
M-4D M-4D
Sperry Sperry
2-24
M-4D
2-25
M-4D
King KPI-550 Interface Collins PN-101 Interface
2-26
M-4D
Sperry
2-27
Interconnect
2-20
Controller
3013 JK
Extender
Cable
-------------------------
----------------------------
Shockmount Servo
Primary
-----------------------
Servo
-----------------------
3014D, F, G, H T rriim Servo 2268A-1 Capstan 2179A-CF Attitude Gyro
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
2-36
---------------------------
2-37
----------------------
2203J Altitude Controller 2181D-CF Attitude Gyro
2-38
----------------------
----------------------
4099B Turn and Bank Indicator 4100A Slip-Skid Sensor
------------------
-----------------------
-----------------------
I. B. 20004
2-35
-
HZ-444 HZ-454
Interface Interface
2-39
2-40
2-41
2-42
2-43
2-44
2-45
2-46 2-47
----------------
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2-48 2-49 2-50 2-51
-------------------------
2-52
------------------------
GH-14 Interface M-4D System Diagram,
2-53 2-54
-------------------------
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-
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-
2-55
2-56
iv
75
Revised
Bendix Avionica Division M-4D AUTOMATIC
Oct 75
installation Manual FLIGHT
CONTROL
SYSTEM
LIST OF TABLES Table 1-1
Page 1-2
1-2
Leading Particulars M-4D Basic Component
1-3
Flight
1-4
Situation
1-5
Remote
1-6
Items
1-7
Optional
1-8 1-9
Op Opti tion onal al Inst Instru rume ment ntat atio ionn M-4D System Controls
1-10
M-4D Sy Sysste tem m
1-11
Director Indicator Attitude DH-861A Mo Mode de An Annu nunc ncia iato tors rs
1-12 1-13 2-1
------------------------------------
Description
Director
Indicators Display Indicators
Gyro Compass Required Items
1-4
--------------------------
1-5
---------------------------------
1-6
-------------------------------
System
1-6
-----------------------------
Fo Forr Inst Instal alla lati tion on
1-7
-----------------------------
1-7
------------------------------------------
Configuration
An Annu nunnciat ciator orss
-
-
-
-
-
-
-
-
-
-
-
-
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-
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-
-
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-
-
-
-
1-8 1-10
------------------------------------
1-12
--------------------------------
Gyro Controls
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
-
--
-
-
-
-
1-14 1-14 1-20
--------------------------------
FlightDirectorAdapterBoards Taper Pin Data-----------------------------------------
I. B. 20004
-
-----------------------------
2-6
Revised
v Oct 75
Bendix Avsomca Division M-4D AUTOMATIC
5487G
Installation
-
-
Manual
FLIGHT
CONTROL
SYSTEM
4100A
2203J
1VOO9-5 5536F
3013(
2268A-1
)
I. B. 20004
M-4D Automatic
Flight Control Figure 1-1
3014(
)
System Rëvised
vi Oct/75
Bendix
Installation Manual
Avionica Division
M-4D AUTOMATIC FLIGHT SECTION I DESCRIPTION 1.
CONTROL
SYSTEM
AND OPERATION
General The M-4D is an integrated
Control System(AFCS) consisting of a full As i t i s c o m bination of sensors, system. a such, servos, guidance displays, mode selector and a central computer which performs It is designed for use in medium to heavier the necessary flight computations. weight twin engine aircraft, both piston and turbine. The system provides either with th simu simult ltan aneo eous us full full au auto topi pilo lott control of the aircraft wi flight director monitoring or manual control in response to flight director displayed steering commands. The yaw axis can be engaged independently of roll and pitch for use as a yaw damper. The roll axis contains a full-time command modifier for smooth control. Automatic
three-axis autopilot and flight director
2.
System
Flight
Description
The system
maximu mum m allows a wide range of component selection resulting in maxi flexibility. Power requirements for the basic components are 115 vac, 400 Hz, 25 va and 4.2 amps at 28 vdc. which consists of nine Heart of the system is the type 5536F Computer-Amplifier plug-in modules, one of which is peculiar to a particular aircraft type installation an andd an anot othe herr which relates to a specific type flight director installation. The flig:ht director can be omitted if operational considerations or cockpit spac spacee li limi mita tati tion onss preclude its use. The 5536F combines inputs from gyro sensors, control panel, heading and radio electrical commands to the control surface servos sourced to deliver appropriate and to flight director instrumentation. It is mounted on a type 1VOO9-05 shockmount which also contains a relay for primary power application the roll and pitch servos. Type 3013( ) Primary Servos (three per aircraft) control power application to the All primary servos are aircraft surface by means of magnetic powder clutches. 2268A-1 assembled to a type Capstan which connects the servo output pinion with aircraft cable rigging. The capstan contains an adjustable slip clutch which the pre-set is for each aircraft axis by the installer. Servo is used to activate an elevator trim tab control to relieve long-term aerodynamic loading and generally assist in smoother operation of the elevator surface without requiring large amounts of power from the primary servo. Its operation is either automatic, using the composite pitch error signal from the 5536F or both automatic and manual if an optional manual electric trim adapter is utilized.
Type 3014(
) Trim
Therequires 2203J Altitude Controller co cont ntaain inss It a barometric input isandrequired which supplies the altitude error signal.
I. B. 20004
operate logic in altitude pick-off hold function. toengage the system and a differential
Revised
1-1 Aug/74
Bendix
Avionics Division M-4D AUTOMATIC
2.
Installati Manual FLIGHT
n
CONTROL
SYSTEM
Operation of the yaw axis requires inputs from type 4099B Turn and Bank Indicator (panel-mounted) and type 4100A Slip-Skid Sensor. These units provide yawing rate and and acce accele lera rati tion on rope perr cha harrac acte teri rist stic icss for processing signals respectively, with the pro Computer-Amplifier by the 5536F and thence to the yaw primary servo. or if a The controls for the M-4D AFCS are located on type 5487G Flight Controller controller-mode split selector is desired, then the 5487G functions are split into two In either case, the units, the 5485A Flight Controller with 5486A Mode Selector. total number of controls and indicators is the same. The split configuration is advantageous where panel space is at a premium or crew dut dutie iess dicta tatte an alternate location. The function of each control and indicator is discussed elsewhere in this manual. A source of vertical reference information is required and can be either a remote vertical gyro or a panel mounted gyro. A variety of system configurations are com4 o r 3 i n c h available utilizing either A selection of instruments instruments. pletes the M-4D AFCS. (See Paragraph 6, System Configurations) 3.
Particulars
Leading
1-1 describes
Table
the various
characteristics
of
CHARACTERISTICS TSO Compliance Flight
the M-4D AFCS. DESCRIPTION
C9c, C52a
References
Roll,
Pitch
Attitude Gyro.
Yaw
Rate Gyro (Located in Turn and Bank Indicator) and Slip-Skid Sensor.
Altitude
Barometric aneroid pressure, Controller sensing Altitude
Heading
Directional
Enroute
VHF NAV system
Approach Synchroniz ation
type
Gyro, Slaved
ILS, VOR or Area
or Area Nav Computer Nav Nav Co Comp mput uter er
Flight attitude maintained after autopilot engaged. Assumes wings level attitude upon engagement of autopilot.
Pitch Roll
Rudder
Yaw
streamlined.
Servo Drives Power
I. B. 20004
Source
D-c motoclutches. r geared powder Leading Particulars Table 1-1 (Sheet 1 of 3)
to input of magnetic
1-2 Aug/74
Revised
Bendix
Avionics Division
M-4D AUTOMATIC
3.
Installation Manual FLIGHT
SYSTEM
CONTROL
CHARACTERISTICS
DESCRIPTION
Power
Control
Magnetic powder of operation.
Power
Application
C able drive clutch.
clutch for either
drum with
direction
torque limiting
Follow-Ups
Surface
Pitch,
Roll,
Automatic
Rate: outputs proportional to rate of displacement of control surface. Negative fee feedb dbaack pro roppor orti tion onaal to servo speed.
Yaw
Trim Elevator trim by trim servo.
Pitch Vo Volt ltag agee
tabs automatically
115 vac 400 Hz single nominal
Re Requ quiireme rement ntss
phase
operated
and 28 vde
Characteristics
Flight
Stability of Attitude Control Directional Stability Maximum
degree degree
±1/2 ±1/2
of Altitude
Control
smooth air smooth air; ±1 degree
moderate turbulence feet maximum and level flight
±20
deviation
Roll Angle
Turn Knob Heading,
Capture
Track
Angle
Roll Trim
Correction
Maximum
Pitch Angle
Pitch Knob Altitude
and GS Modes
to 30 degrees to 22 degrees to 12 degrees to ±5 degrees
to to
±20
degrees
±20
degrees
115 vac and 28 vde
Power Standby
18.0va
1.3 amps
A/P Engage (Single-Axis) Hardover
25 va
4. 2 amps
25 va
7. 2 amps
LB
KG
5536F Computer 1VOO9-05 Shockmount
6. 6 2. 2
3, 0 1, 0
5487G
2.1
Weight
I. B. 20004
in straight
Flight
Controller
Leading Particulars Table 1-1 (Sheet 2 of 3)
,95
Revised
1-3 Oct/75
Bendix
Avsonica Davasion -
-
-
M-4D
3.
-
-
AUTOMATIC
Installation Manual
FLIGHT
CONTROL
CHARACTERISTICS Weight
DESCRIPTION
(cont'd)
5485A Flight
Controller
5486A M ode SelecServo tor 3013H Primary 3013J/K Primary Servo 2268A-1 Capstan 3014D-2|F-2/G-2/H-2/J-2/K-2 L-2 Trim Servo AD-854A Trim Adapter 2203 203J Al Alttit itud udee Controller 4099B Turn and Bank Indicator 4100A Slip-Skid Sensor 2181D-CF Attitude Gyro 2179A-CF Attitude Gyro VG-865A Remote Vertical Gyro
4.
Component
Descriptions
SYSTEM
LB
KG
1. 3
0, 60
1.1 4.75 6. 6 1. 1 3. 8
0,50 2,16 2, 99 0, 50 1, 73
1. 2 2. 5 2.1 0. 75 3. 7 2. 9 6. 0
0, 55 1, 13 0,95 0, 34 1, 70 1, 30 2, 73
Leading Particulars Table 1-1 (Sheet 3 of 3)
Table 1-2 list basic items in the M-4D AFCS. Table 1-3 lists optional flight directors. Table 1-4 lists optional situation display instruments [formerly known as horizontal 1-5 instruments lists items in the remote gyro compass situation (HSI)]. Table system.
A.
Components
TYPE NUMBER
5536F
Basic
to AFCS DESCRIPTION
PART NUMBER 4000495-8501
Computer-Amplifier
4007263-05XX
Calibration
Board
for 5536F.
D epends on aircraft See service bulletin M4D-001.
type.
1VOO9-05
1VOO9-05
Computer
5487G
4000493-8501
Flight
5485A
4000507-8501
5486A
4000494-8501
Flight Controller (without Selector/Annunciators) Mode Selector/Annunciator
3013H
4000523-8501
Primary
3013J
4009506-8501
3013K
4009506-8502
Optional low speed primary servo disconnect containing clutch when AFCS not in use Same as 3013H except contains disconnect clutch
I. B. 20004
Shockmount
Controller
M-4D Basic Component Description Table 1-2 (Sheet 1 of 2)
Servo
Mode
(3 per aircraft)
Revised
Oct
Bendix
Installation Manuat
AViOniCS
Division
M-4D AUTOMATIC
4.
FLIGHT
CONTROL
SYSTEM
TYPE NUMBER
PART
2268A-1
4006451-0501
Capstan
3014D-2
4000524-8505
Trim
Servo,
low speed 40 in/lb
3014F-2 3014G-2
4000524-8506 4000524-8507
Trim Trim
Servo, Servo,
low speed 20 in/lb high speed 40 in/lb
3014H-2
4000524-8508
Trim
Servo,
medium
speed 55 in/lb
3014J-2
4000524-8509
Trim
Servo,
medium
speed
3014K-2
4000524-8510
Trim
Servo,
medium
speed 32 in/lb
3014L-2
4000524-8511
Trim
Servo,
high speed 40 in/lb
AD-854A
4000589-5401
2203J
4000225-8502
4099B
4000784-8501
4099B
4000784-8502
Adapter, manual electric Altitude Controller sensor Turn and Bank Indicator except 5 volt lighting Same as
4099B
4100A
4000784-8503 4000780-8501
Same as except Slip-Skid Sensor
2181D-CF
4000627-8101
28 vde Attitude Gyro. For use in systems requiring flight director capability.
2181D-CF
4000627-8103
2179A-CF
4000474-8506
but but desi design gned ed for Same as panel mounting. Vacuum-driven Attitude Gyro. For use in flight ht dire direct ctor or capability systems not requiring flig
2179A-CF
4000474-8507
VG-865A
Same as mounting
4000650-6501
Remote
20 in/lb
-
-80
-8501
28 volt lighting not
-8°
-8101
-8506
but designed for
-8
panel
Vertical Gyro. ARINC outputs. ReDH-861A m o v e d w h e n Flight 3-wire Director ARINC used or other flight directors having 407 outputs Table
Flight
(3 per aircraft)
Trim
M-4D Basic B.
DESCRIPTION
NUMBER
Compo mponent Description 1-2 (Sheet 2 of 2)
Directors
TYPE NUMBER
PART
DH-861A
4000369-8501
4 Flight Director displaying computed commands and attitude information.
DH-866A
4000843-6601
Same as above plus glideslope,
NUMBER
DESCRIPTION
localizer
steering
and
inclinometer.
I. B. 20004
Flight Director Indicators Table 1-3 (Sheet 1 of 2)
1-5 Revised Oct/75
Bendix Avionica
instalation Manual
Division
M-4D AUTOMATIC
4. B
FLIGHT
TYPE NUMBER
PART NUMBER
DH-841C
4000512-4101
DH-841C
4000512-4103
CONTROL
SYSTEM
DESCRIPTION self co cont ntai ainned Attitude-Gyro, 3 sel 28 vde power. fligh lightt dire direct ctor or.. same as but designed panel mounting -40
for
-8°
DH-841A
4000184-8503
3 self contained Attitude Gyro, flight director. vacuum power.
DH-841A
4000184-8504
Same as panel mount -80
but designed
for 8°
Flight Director Indicators Table 1-3 (Sheet 2 of 2) C.
Situation
Display
TYPE NUMBER
Indicators
(HSI)
PART NUMBER
DESCRIPTION
IN-863A
4000458-6301
4 HSI. AFOS coupling and bootstrap heading outputs standard. Requires ARINC XYZ heading input, 26 vac power.
IN-863A
4000458-6302
Same as
IN-863A
4000458-6303
Same as pointer colors
IN-831A
4000172-8502
3 HSI with AFCS coupling.
IN-831A
4000172-8503
Same as with bo boot otst stra rapp but with heading output added.
-6301
Table
Compass
TYPE
Indicators 1-4
System
NUMBER
PART NUMBER
SG-832B
4000099-8504
FX-833A
4000191-8501
EC-834A
4000202-8501
IN-835 A
4000192-8501
I. B. 20004
for bezel color except for bezel and
except
-8502
Situation Display D.
-6301
Remote
Gyro Compass Table 1-5
DESCRIPTION Slaved ed Dir Directi ection onaal Remote Slav with shockmount Flux Sensor Magnetic Error Slaving Meter
Gyro,
Corrector
System 1-6
Revised Oct/75
Bendix Avsonaca Division -
.
Installation Manual
M-4D AUTOMATIC F LIGHT CONTROL 5.
Items
Accessory
PART NUMBER
DESCRIPTION cocKpit kit. coContains Switch & switches, Connector coil mounted rd and deall cals associated with installation of basic AFCS Contains mating connectors for any aircraft. Connectors and other basic AFCS components. hardware supplied with instruments are not included. comkit. Contains mechanical STC Installation ponents, servo mounts and instructions to marry M·-4D AFCS to aircraft type. For use when installing system in an existing aircraft model. Whe henn av avai aila labl blee from Bendix, a unique part number is assigned for each aircraft type.
4007265-0501
-
SYSTEM
-
-
Items
RequirTable ed for1-6Installation DESCRIPTION
PART NUMBER 4006591-0502
comManual electric trim kit kit pr prov oviide dess necessary ponents and cockpit switches to actuate the 3014( ) trim servo.
4006315-0501
Trim indicator kit (rudder & aileron) provides coinponents & meters to monitor forces necessary exerted by yaw & rpfl servos.
4003134-0001
Shim for mounting 2181D-CF,
-8°
or DH-841(
version of 2179D-CF ) attitude gyro.
or
Optional Items Table 1-7 A.
Instruments
an andd Magn gnet etiic
Compass Sy Sysstems tems
Insstall In tallat atio ionn
Accessories
Various mounting clamps and bezels are available for the DH-841( ), DH-861A, IN-863A and IN-831A. relating to the IN-831A and SG-832B, refer For information 860-840 refer to I. B. 2864-( ). to I. B. 2830-1. For the series of instruments, B.
Items
Required
But Not Supplied
Power Source harness. Interconnect
L B. 20004
1-7
Revised
Bendix Avionica Division M-4D AUTOMATIC 6.
System A.
Instaffation Manual FLIGHT
CONTROL
SYSTEM
Configurations
General The AFCS can be configured with various instruments, control panels and servos. Generally the selection of primary and trim servos is a function of the aerodynamic loading on the surface to be controlled and the desired control or STC (supplemental characteristics. The TC (type certificate) type certificate) for a particular aircraft type will specify the servos to be used together with break-away torque settings and cable tensions for any cables connected to the servo capstan. constants for smooth servo operation are preset on Electrical type. the 5536 536F cali calibr brat atio ionn board for a particular aircraft
B.
Where desirable, lightt Co Cont ntro rolller can be split into the functions of the 5487G Fligh in a aircraft e a c h m o u n t e d different The 5485A Flight two groups, location. Controller would then contain autopilot and yaw axis engage switches, turn knob, The 5486A Mode Selector contains the mode pitch control and trim meter. and and an annu nunc ncia iato tors rs for all lateral and longitudinal modes such as altitude selectors hold or VOR navigation. & Vertical Reference Instrumentation The M-4D AFCS allows for customer selection of flight director display instruments and associated horizontal situation displays. Selection of these instruments will determine the vertical reference for the system. which can be expanded almost infinitely Basically there are five configurations as long as the vertical and heading references supply the required outputs or can be transformed to same. See figure 2-27 for option block diagrams. Table 1-8 details
the basic configurations.
REQUIREMENT 4
SUPPLEMENTARY
Instruments DH-861A IN 863A
Use adapter board P/N 4007262-0501 Remote Vertical Gyro with 200 mv/degree required (Bendix VG-865A or equal).
-
IN- 866A 3
Instruments
Use adapter board P/N 4007713-0501 Vertical Gyro.
with above
with
Flight Director DH-841A or C IN 831A -
Optional
I.B.
INFORMATION
Use DH-841 to 5536F.
Adapter
Instrumentation Configuration Table 1-8 (Sheet 1 of 2)
board P/N 4007264-0501
Oct/75
20004
1-8
Bendix Avuonics Division -
M-4D AUTOMATIC
6. C.
-
Installation Manual
FLIGHT
CONTROL
SYSTEM
4-Inch
Instruments The DH-866A Flight Director Indicator is a four-inch primary flight instrument designed for use in heavy twin and turboprop aircraft. The panelmouunt mo nteed mul multi tipu purrpo posse provides aircraft attitude and computed instrument flight path information. This indicator is designed for use in conjunction with the Bendix M-4D Flight Control System or an equivalent. include the following: Additional functions and optional configurations (1) Glideslope deviation is displayed by a meter driven pointer read against a fixed vertical scale. The meter is controlled by signals from the navigation receiver. (2)
deviation is displayed by a meter driven pointer read against a fixe xedd hor oriizonta ntal scale. The meter is controlled by signals from the Localizer
navigation
receiver.
driven pointer to the ground during the final phases
(3)
Radio altitude (optional) is presented indicate actua tual aircraft height above (200 ft) of the approach.
(4)
An inclinometer is externally mounted to indicate aircraft slip or skid. The inclinometer is adjustable to compensate for installation tilt. The A TT flag denotes a malfunction in the pitch or roll servos or the aircraft vertical gyro.
(5)
by a meter
to warn the pilot of
(6)
A flight director invalid command
(7)
A PITCH TRIM knob manually adjusts the attitude sphere in pilot eye level and for changes in aircraft for variations
attitude.
(8)
warning flag (FD) comes bar indications.
into view
to compensate cruise
An ATT TEST/FD ON switch inputs fixed signals which produces a pitch up and roll right display serving as a visual performance/confidence check of the attitude servos. The flight director is functional and the command bars are operational with the switch in the FD ON position.
The DH-861A is a 4-inch instrument with single-cue comp mput uted ed display of co It contains mode annunciators steering commands and attitude information. d/or long longit ituudina dinall mode selections. Additional which light to display lateral and/or go-around mode operation and minimum descent altitude, annunciators advise altimeter A remot mote equipment is available. the latter for use if radio vertical gyro, which also supplies attitude information, is required when using DH-861A. the It must have XYZ synchro outputs per ARINC 407. D.
3-Inch
Instruments
The DH-841 is a 3-inch self-contained attitude gyro with flig flight ht dire direct ctor or capability. It is designed for panel mounting and requires 20 vac power
I. B. 20004
display for the
1-9
Revised
Oct/75
Bendix Avionica Division M-4D
6.D.
AUTOMATIC
installation
Manual
FLIGHT
CONTROL
SYSTEM
synchro pick-offs
to the AF CS. Either vacuum which supply attitude information (DH-841A) or electric (DH-841C) models are available. Electric models operate from 28 vde with a built-in power converter providing the vac to accelerate the 0° panel mounting. gyro wheel. The DH-841( ) Models are available for or -8°
supplies attitude flig rehfteredi ncrect ector basic AFCS plus a visual and single-cue display. igh dire or to the
attitude
display
Displa layy In Inddicat icator or.. Companion to the DH-841( ) is the 3-inch, IN-831A, Situation Disp and radio signals and selects It provides readout of magnetic compass information radio courses or headings for coupling to the AFCS in a similar manner as the IN-863A. Additional information on the DH-841( ) may be found in I. B. 2864-2 and The IN-831A is further treated in Inst I. B. 2864-5. Instal alla lati tion on Manual I. B. 2830-1. E.
3-Inch Attitude
Gyro
The 2179A-CF (vacuum driven) or 2181D-CF (electrically driven) attitude gyros for pitch and roll information provide a visual and electrical reference for capability. systems not requiring flight director F.
Compass
System
I. B. 2830-1 provides additional details associated error corrector flux sensor, 7.
on the SG-832B directional and slaving meter,
gyro and its
Operation A.
System
Controls
& Annunciators
Tables 1-7, 1-8, 1-9 and 1-10 list the basic controls and annunciators associated with the M-4D Automatic Flight Control System. See figures 1-2, 1-3 and 1-4 for flight controller configurations and control location. CONTROL
LOCATION
FUNCTION
CONTROL
5487G or 5485A
AP
Engages AFCS by ap appplyi lying power to all primary servos and pitch trim servo. Annunciator shows ON status. Aircraft attains wings level attitude and the pitch attitude that exists at time of engagement
5487G or 5485A
YAW
Engages YAW axis servo only. shows ON status. Annunciator
5487G or 5485A
PITCH
This control is spring-loaded to position. When center (neutral) activated it commands desired pitch attitude pitch proof airc aircra raft ftmaximum. R ate of cto han±20 ge degrees
M-4D System Controls Table 1-9 (Sheet 1 of 3)
1--10
I. B. 20004
Revised
Aug/74
Bendië Aviomcs Division .
.
M-4D AUTOMATIC
7. A. CONTROL
LOCATION
Installation
Manual
-
FLIGHT
CONTROL
SYSTEM FUNCTION
CONTROL
portional to rate of movement of pitch control (variable rate pitch command). any existing Activation releases
5487G or 5485A (cont'd)
5487G or 5485A
TEST
5487G or 5485A
DIM
5487G or 5485A
ROLL TRIM
longitudinal modes (ALT, GS or GA). Activation of this button checks all annunciators on 5487G, 5485A and 5486A. If not already illuminated due to mode selection, they will light in response to TEST button. This control does not engage or disengage any axis or any operating mode. associDims all panel annunciators ated with 5487G, 5485A and 5486A. Allows pilot adjustment of out-oftrim condition in roll axis with AFCS engaged. Should not be used with any lateral control
5487G or 5485A
ELEV
5487G or 5485A
TURN
m odeof s center engaged detent. or with TURN out
Before engagement, meter indicates status of AFCS pitch signal relative to pitch axis of aircraft. It should always be near center as the M-4D has automatic pitch synchronization. After engagement, meter indicates force required by primary servo to hold aircraft in desired pitch attitude. Commands
not initially
AFCS
Cockpit
MASTER
either
12 or 24 degrees
of
bank angle at detents. other lateral modes.
Releases any AFCS will engage with T URN knob
off center. Applies 115 vac and 28 vde power AFCS control circuitry.
to
Control
Wheel
A/P REL or F/C REL
Provides for instant disengagement of all servos coupled to aircraft control AP ON and/or YAW ON surfaces. lamps extinguish.
Control
Wheel
SYNC
Disengages pitch axis when pressed to allow pilot to perform vertical maneuver using control column. Button is released on completion of maneuver and pitch axis re-engages to maintain new attitude. Also resynes flight command TheGA SYNC director cancels ALT or button GS, bar. mode.
I. B. 20004
M-4D System Controls (Table 1-9 (Sheet 2 of 3)
1-11
Revised
Aug/74
Bendix Avionics Division
Installation Manual
M-4D AUTOMATIC FIAGHT CONTROL
7.A. CONTROL Throttle Control
LOCATION
CONTROL
FUNCTION
go-around mode for missed approaches. Preset pitch up command
GA
or Wheel
Initiates
inserted, engaged. settings.
Control Wheel
SYSTEM
other vertical modes disPilot must adjust power
Activates pitch trim servo when manual electric trim used. Activation disengages roll and pitch axis.
TRIM
M-4D System Controls (Table 1-9 (Sheet 3 of 3) NOTE:
controls select lateral gu guid idan ance following ce co comm mman ands ds selection for both AFCS and flight director. and Ifvertical AFCS is not engaged, the pilot must manually satisfy the command Annunciators operate in identical fashion either with indication. mode
The
or without
CONTROL LOCATION 5487G or 5486A
AFCS engagement.
CONTROL HDG
ANNUNCIATOR(S) HDG ON
FUNCTION
Commands air irccraft to follow or turn to heading selected by associated instrument heading selector knob.
5487G or 5486A
ALT
ALT ON
5487G or 5486A
NAV
NAV ON RNAV ON
mainaircraft Commands tain altitude existing toat time of ALT mode selection.
Couples system to output of associated VOR receiver or Aircraft RNAV computer.
performs standard 4Πinterand then cept if necessary. tracks course selected by CRSS selec CR electtor on associated instrument or computed by RNAV system. If RNAV is operating, RNAV and NAV AutoON lamps illuminate. matic locked glide out. slope engage M-4D System Annunciators Table 1-10 (Sheet 1 of 2) I. B. 20004
1-12
Revised
Aug/74
Bendix Avionica Division M-4D AUTOMATIC FLIGHT
7. A. CONTROL
Installation Manuai
LOCATION
5487G or 54 5 486A
CONTROL APPR
CONTROL
. ANNUNCIATOR(S) APPR ON RNAV ON
SYSTEM
FUNCTION systems tightly to Couples to ILS, VOR, or RNAV
allow precise intercept & tracking during approach Use CRS conditions. selector on associated instrument to establish course (or computed RNAV Also in this mode, course). glide slope information is sensed at beam threshold and is presented as an ARM indication on an adjacent light. If RNAV operating, RNAV and APPR ON lights illuminate.
5487G or 5486A
REV
REV ON APPR ON
Provides for back-course approaches or outbound tracking of front course by reversing polarity of localizer and course signals to AFCS. Glide slope will not arm in this Use CRS selector mode. in associated instrument to establish course.
5487G or 5486A
GS
GS ON
The ARM annunciation occurs in APPR mode if
GS ARM
intercept below signalbeam has center andisthe been present for approx. 20 seconds. Automatic glide slop slopee en enggag ageement ment will occur as the aircraft flies into beam center. The GS ON lamp will illuminate and ALT (if activated) and ARM lamps will extinguish. Manual glide slope may be activated when in any mode except go around. M-4D Sy Syst stem em An Annnun uncciato iatorrs Table 1-10 (Sheet 2 of 2)
I. B. 20004
Benclix Avionics Division -
M-4D AUTOMATIC
B.
Flight
Director
Director covered
CONTROL
Controls
-Installation Manual
-
FLIGHT
CONTROL
& Annunciators
Horizon Indicator DH-841A, DH-841C, more thoroughly in I. B. 2864-2, -5,
LOCATION
SYSTEM
-1,
DH-861A and DH-866A are, and I. B. 2866 respectively.
CONTROL
FUNCTION
DH-861A
PITCH TRIM
Adjust pitch axis attitude
DH-861A
FD ON (and off)
Activates
command
bar circuitry.
Cockpit (used with DH-841 only)
FD ON
Activates
command
dot circuitry,
Cockpit
Parallax
Adjust command viewing angle.
Pull To Cage
Neutralizes tumbled attitude gyro. For emergency use only. Activation disengages AFCS.
Pitch Adjust
Adjusts
2181D-CF
DH-841C, DH-841,
2179,
2181
Director
Indicator/Attitude Table 1-11
for pilot
pit pitch refer eferen ence ce..
Gyro Controls
ANNUNCIATOR
FUNCTION
HDG
Illuminates
when HDG mode selected
control panel.
V- L
on AFCS
when APPR, REV, or NAV Illuminates selected on AFCS control panel, Illuminates when go-around button depressed.
GA
I. B. 20004
bars
of sphere.
Illuminates on system
MDA
Illuminates to indicate MDA (Minimum provides altitude) when radio altimeter
GYRO
Operates with remote vertical gyro to indicate lack of gyro power or improper erection.
CMPT
Indicates AFCS computer (5536F) inoperative or low ac power from aircraft supply.
ALT
when ALT is selected Illuminates control panel. DH-861A
simultaneous control panel.
with GS EN ENG lamp
GS ENG
Mode Annunciators Table 1-12
decision signal.
on AFCS
1.--14
Revised
Oct/75
Bendix
Installation Manual
Avionics Division
M-4D AUTOMATIC FLIGHT
CONTROL SYSTEM DN
AP
,TURN
-
R
L
---
ROLL TRIM
P
ELEV YAW ON
TEST 5485A Flight
HDG ON
NAV
Controller
Figure
APPR
RNV ON RNV ON
DI M
UP
(w/o Mode Selector) 1-2
REV
GS
ALT
ON
ARM ON
ON
GS AR. ON
ALT
5486A Mo Mode de Se Sele lect ctor or/A /Ann nnun unci ciat ator or Figure
HDG ON
NAV APPR RN'v ON RN'. CN
1-3
REV ON
ON
DN AP
L,TURN'R
e a.
ELEV
ROLLTRIM
p I
CT
YAW
H
TEST
L B. 20004
5487G Flight
Controller Figure
DIM
(w Mode Selector) 1-4
UP
1-15
Aug/74
Bendix Avionica Division
Installation
Manual
M-4D AUTOMATIC FLIGHT
C.
General Operating (1)
Operating
Limitations
the AFCS, the following operational
See figures
(4)
precaution
THE AFCS SHOULD BE OPERATED IN ACCORDANCE WITH THE APPROVED FLIGHT MANUAL SUPPLEMENT.
CAUTION:
(3)
SYSTEM
Instructions
Fshould or safebe oobserved: peration of
(2)
CONTROL
1-2,
AFCS Engage
1-3 and 1-4 for operating
controls
and annunciators.
Procedure
(a)
Manually trim controls during
(b )
Close the AFCS master
(c)
Check that the TURN command
(d)
push the Observing that the ELEV trim meter needle is centered, AP button on the flight controller. AP and YAW lamps will go on if engagement occurs.
(e)
Use
(f)
The automatic pitch trim will keep the aircraft trimmed in axis and functions whenever the AFCS is engaged.
the aircraft
engagement
switch.
the ROLL TRIM control required. as
AFCS Disengage
the aircraft
in all axes and monitor procedures.
on
knob is in
the center
the flight controller
(detent) position.
to level the wings the pitch
Procedure
(a)
Check the aircraft trim and monitor the controls prior to disengagement. The automatic pitch trim assures that the aircraft will be properly trimmed in the pitch axis at the pitch attitude existing when the system is engaged.
(b)
Disengage the system A/P Release switch.
(c)
The system may also be disengaged by placing the system master switch to OFF . as it However, this method is not recommended results in loss of the automatic pitch synchronization feature.
Yaw Damper (a)
Engage
by pressing
and releasing
the wheel-mounted
Procedure
Manually about yaw trim axis. rudder
and aileron
for zero
turn rate and acceleration
1-16
I. B. 20004
Aug/74
Revised
Bendix Installation Avionics Manual Division M-4D AUTOMATIC FLIGHT CONTROL
7. C.(4)
(5)
(b)
Press
(c)
If full AFCS is later engaged,
YAW button.
SYSTEM
ON lamp will illuminate
as engagement
occurs.
YAW lamp will remain ON.
Basic Attitude Operation
After AF any of the mode selector AFCS CS en enggag ageement ment but prior to depressing buttons, the AFCS stabilizes the aircraft in a wings level condition at the pitch attitude that existed at time of engagement. (6)
Command Maneuvers tedd by a turn maneuver may be execute rotating the TURN knob in the direction of the desired turn. Any lateral mode is disengaged by the overiding action of the turn knob. The first 12 degrees. The detent position produces a bank angle of approximately Maxisecond position produces a bank angle of approximately 25 degrees. aircraft function of particular mum AFCS bank angle is set At any time AFCS is engaged,
type.
as a
may be executed at any time by rotating the spring-loaded rate of aircraft response, pitch knob. Rate of control moveme mennt determines similar to hand-flying the aircraft in that a sudden movement of the control yoke would produce a faster change in pitch attitude than a slow, deliberate Movement of the PITCH knob from the center position distype movement. engages any vertical mode that may exist.
A pitch maneuver
A cha hannge in pitch attitude may also be accomplished by moving the control column in the desired direction while simultaneously pressing the SYNC button on the control wheel. This disengages the pitch axis and allows lows direct pilot control of the elevator surface until such time as the desired attitude is attained. The SYN SYNC C butto buttonn is then released and the pitch a-us titu tudde change nge in this manner re-engages to maintain this attitude. An atti also cancels any existing
(7) Vertical
vertical
mode.
Modes
Altitude hold, Glide slope beam tracking or Go-Around can be selected. In ALT mode, the system is coupled to a barometric maintain altitude existing at time of mode selection.
slopee en enga gage geme ment nt Glide slop as indicated below. (a)
System
is automatic
tracking localizer
(b) Glide slope signal present
I. B. 20004
sensing
device
to
when wh en se seve vera rall conditions are satisfied
beam inbound in APPR mode. for 20 seco seconnds minimum.
1-17
Revised
Aug/74
Bendix
Installation Manual
Avionics Division M-4D AUTOMATIC
7. C. (7)
CONTROL
FLIGHT
(c)
Glide slope interception
(d)
R-NAV lamp must be extinguished.
from below beam center.
the GS ARM have been satisfied, lamp illuminates and automatic engagement (GS ON will subsequently occur when the glide slope beam center is intercepted. When activated, ALT mode will be automatically released. Maximum pitch/angle is limited to 20°. approximately When
the above mentioned
SYSTEM
conditions
Manual G. S. can be selected by simply pressing the GS mode button. or GA (go-around). Glide slope acquisition is locked out during REV (reverse) operation can be initiated if the system is in APPR or REV mode. the GA button releases GS or ALT modes and causes the aircraft to assume a climb-out pitch-up condition to a deg egrree dependent on fixed calibration constants related to type of aircraft. This climb-out attitude is approximately 6 to 8 degrees. The AFCS remains coupled to the beam until another mode is selected. Go-around Pressing
GA (go-around) may be cancelled by selecting ALT mode, pressing SYNC button on the control wheel or actuating the PITCH command. (8)
Lateral
the
Modes
of four lateral modes is available, heading (HDG), NAV, (APPR) and REVERSE COURSE (REV). Modes are interlocked so that selection of any mode cancels the existing mode. HDG may be used in conjunction with NAV, APPR, or REV for variable-angle intercept discussed. to be subs subseq eque uent ntly ly A selection APPROACH
to intercept and hold the heading sethe IN-831A or IN-863A. One degree of will yield one degree of bank bank angle up to a maximum of 22
Heading mode will cause the aircraft lected on an as asso soci ciat ated ed HSI such as error heading degrees.
for intercept and tracking of VOR signals or RNAV computations. The aircraft will turn to an intercept angle of 45 degr degree ees. s. After being estabBank angle limit during beam intercept is ±22 degrees. lished on the desired course, the system reverts to a tracking mode wherein posssibl siblee to maintain course beam error integration techniques make it po cross-wind under or engine out conditions. Maximum bank angle is reNAV mode provides
duced to ±10 degrees while tracking. This value assures a smooth passage Courses are selected on the associated HSI or over the VOR station. computed by the RNAV system in resp espon onsse to VOR and DME information. of a new course
Acquisition
selector
on
can be accomplished
the HSI to the desired
by rotating
the CRS
course.
1-18
I. B. 20004
Revised
Aug/74
Bendix Installatian Avionics Manual Division M-4D AUTOMATIC FLIGHT CONTROL
7. C. (8)
SYSTEM
APPR mode is similar to NAV except that the overall response to beam errors is more sensitive to insure tight tracking. During IL ILSS ap appr proa oach ches es,, to ARM and automatically engage the glide slope ecessar ssaryy this mode is nece mode mo de pr preevi viou oussly discussed. REV mode will cause reversal of course and localizer beam inputs in order to allow outbound tracking of localizer front course or back-course tracking. Glide slope will not arm in this mode. In this mode, both APPR and REV lamps light simultaneously. In NAV, APPR, or REV mode, beam interception depressing degrees is possible by simultaneously REV. Initially, although both mode selectors are in HDG mode at the heading selected on the HSI. the capture threshold, the HDG lamp automatically aircraft performs a standard intercept of selected or computed RNAV course. (9)
Flight
Director
at angles greater than 45 HDG and NAV, APPR, or lighted, the system operates As the aircraft appr pproac oaches hes extinguishes the and localizer, omni radial
Operation
With the AFCS engaged, the flight director is essentially a monitoring After engagement and FD operative, the AFCS will direct instrument. the aircraft and the command bars will simultaneously display commands to which. the autopilot will respond to bring the command indicators back to center.
the flight director
function switched off, (FD on-off knob on DH-861A and DH-866A or external on-off switch with DH-841) the indicator functions solely as a basic attitude reference.
With
For flight director only operation, trim the aircraft for desired attitude. Turn FD switch to ON. Select desired mode on AFCS control panel. bolic air irccraft Manually fly the aircraft to center the wing tips of the symbol type. The symbolic on the command dots or bars depending on instrument aircraft must be flown into the command bars. To resync the command indication for a new pitch attitude, move control column in desired direction SYNC NC butt button on.. Release SYNC button when while simultaneously pressing SY Go-around mode command dots, or bars, are centered at desired attitude. provided system is in APPR is also operative in FD (flight director) or REV mode.
I B. 20004
1-19
Revised
Bendix Aveonics Division ·
M-4D AUTOMATIC
7. C. (10)
-
Installation Manual
FLIGHT
CONTROL
SYSTEM
Table 1-13 describes the available flight director adapter boards to accommodate a variety of flight director systems. Figures 2-20 2-26 show interconnect diagrams between the Bendix M-4D through and various type flight director systems.
PART NUMBER
NAME/FUNCTION
4007431-0501
to convert three-wire synchro type to a two-wire EI pick-off type (used with VG-865A).
4007262-0501
Used with Bendix DH-861
4007463-0501
Used with Collins
4007264-0501
Used with Bendix DH-841
gyro.
4007266-0501
Used with Sperry
HZ-444
gyro.
4007266-0502 4007266-0503
Used with Sperry
HZ-454 gyro. GH-14 gyro.
4007713-0501
Used with Bendix Director
Gyro adapter
Used with Sperry
Flight Director Adapter Table 1-13
I. B. 20004
329B7-R,
Boards
gyro. FD-108,
Horizon
and FD-112C/V.
DH-866A.
Oct/75
Revised
1-20
Oct/75
Bendix Avionics Division .
-
-
Installation Manual
M-4D AUTOMATIC FLIGHT
CONTROL
SYSTEM
SECTION II INSTALLATION 1.
General contains information for the installation of the M-40 Automatic Flight Included are equipment outline drawings and a system interconnector STC (supplemental type ing drawing. These, together with the TC (type certificate) installation is begun. A certificate) drawing should be reviewed before installation and ground series of post-installation in-flight included both is to verify checks, the functionality of the completed installation. This section
Control System.
2.
Unpacking Open shipping cartons and careUse care when unpacking M-4D AFCS components. Check contents to insure all items have been included. fully remove all items.
3.
Inspect the items been damaged in
thoroughly as soon as possible after delivery. If any equipment has transp nsport ortati ation on carrier. transit, report the extent of damage to the tra
Pre-Installation
Check
The units of the M-4D AFCS. have been factory tested immediately prior to shipment. No electrical bench check is required upon receipt of equipment except or mechanical as noted below.
A.
Insertion (1)
B.
of Calibration
and Flight
Director
Boards
Remove dust cover from 5536F Computer-Amplifier and insert the approboard into the rear slot. Part number 4007263-( priate F9 calibration ) is spe peccifie ifiedd on the drawing supplied with the installation kit as appli pplica cabl blee for the particular aircraft type and model. See service bulletin M4D-001.
(2)
the appropriate F1 Flight Director Adaptor Board into the front slot according to the flight director horizon indicator usage as described in Seee pa para ragr grap aphh check out procedure. table 1-13. Se 5. G for post installation
( 3)
board must be tested and R9055 adjusted in accordance The calibration 4. J. or 4. K. , of I. B. 20004A. Part 2, Section II, paragraph
Insert
2268A-1 Capstan (1)
Torque
with
Adjustment
to installation, each 2268A-1 Capstan must be adjusted for a breakaway torque setting as indicated on the installation kit drawing for the specific aircraft type involved. This requires the following tools: Prior
g-1
I. B. 20004
Revised
Oct/75
Bendix Avionica Division M-4D AUTOMATIC
3. B. (1)
(2)
Installat Manual
on
F LIGHT CONTROL
SYSTEM
Adjusting Gear Adjusting Block Torque Wrenches 1/4 Dowel Pin
Bendix #95629 Bendix #95628 Locally supplied Locally supplied
1 &1/4Wr Hex Wren ench ch Socket
Locally
0-200 lbs.
supplied
Remove 3 screws holding capstan guard to capstan mounting plate and withdraw guard from plate. The capstan output gear, pulley and clutch will now slide off the shaft of the capstan mounting plate as a unit. See figure 2-1. e
CAPSTAN MOUNTINGOUTLA
GEAR
PULLEY CLUTCH PLATE SP SPRI RING NG WASHE ASHER R TORQUE ADJUST NUT CAPSTAN GUARD M20420I4
CAPSCREW
2268A-1 Servo Capstan Figure 2-1 (3)
Mount the capstan slip clutch to the adjusting block #95628 as indicated in that figure. figure 2-2 and adjust per directions
(4)
All
I. B. 20004
in
differ eren entt three capstans are to be adjusted. Since each may have a diff i t i s mark i t i s torque setting, important to the axis upon which to be used.
Revised
2-2 Oct/75
Bendix
Installation
Avionics Division
M-4D AUTOMATIC
Manual
FLIGHT
CONTROL
DOWEL EL PIN -ANI2272\ I /4 DOW LOCALLY SUPPLIED
SYSTEM
I-l/4
AND D WREN WRENCH CH HEX SOCKET AN
TORQUE WRENCH
SLIP CLUTCH ADJUSTING BLOCK-
95628 (PART OF 96g6 ASSEMBLY) MOUNTING FOR 1/4 -2ONC SCREWS ON BOTTOM -3
CAPSTAN SLIP CLUTCH WITH TORQUE ADJUST NUT SLIP CLU CLUTCH TCH ADJUST ADJUSTING ING GEAR -NO.95629
M2042OI5
DIRECTIONSCLAMP IN VISE ADJU ING BL K WORK VI . PLACE BENCH AND AN D TO SE SECU CURE RE CL BY INTO BOLT ADJUAD STIJUST NGSTIN BLGOCBLOC K OCK CLUT UTCH CH OR FROM FROM TURN TURNIN ING G SE. SETTINGCAPSTAN DOWELCLUTCH PIN THROU HROUGH GH HOLE HOLE ON DIAM DIAMET ETER ER OF CA CAPS PSTA TAN N DRUM DRUM.. LOOS LOOSEN EN CAP SCREW AND TO TORQ RQUE UE ADJU ADJUST ST NUT. ADJUST TORQUE SLIPPAGE OF CLUTCH BY TIGHTENING OR LOO LOOSEN SENING ING TORQUE TORQUE TORQ RQUE UE VALU VALUES ES REQUIRED, SEE SEE INST INSTAL ALLA LATI TION ON ADJUSTING NUT WITH SOCKET WRENCH FOR TO DRAWINGSUPPLIED WITH INSTALLATION KIT. CHECK AD ADJU JUST STME MENT NT WITH WITH TORQ TORQUE UE WREN WRENCH CH,, ON OBTAINING DESIRED SLIPPAGE SETTING, SECURE ADJUSTMENT BY TIGHTENING CAP SCREW ON TORQUE ADJUST NUT.
2268A-1
Capstan
Torque
Adjustment
I. B. 20004
Figure
2-2 2-3
Bendix
Installation Manual
Avionica Division M-4D AUTOMATIC 4.
FLIGHT
CONTROL
SYSTEM
Installation A.
General The location,
orientation
and mounting
support
structure
for
the M-4D Automatic
Flight ystem is determined of aaircraft in which by system is the type by TC obtained installed.ControTlhe Sapproved installation is covered by the airframe manufacturer or an STC obtained from the FAA by Bendix Avionics or other authorized agency. Installation installation kits supplied by Bendix Avionics will prov proviide inst nstru ruct ctio ionns for mounting locations of all system components plus special brackets, pulleys and other items necessary to complete the installation in a specific type aircraft. Items such as aircraft wiring harness, cable clamps and standard aircraft electrical components are not supplied. B.
Component (1)
Locations
Computer-Amplifier The computer-amplifier
mounts directly into its own shockmount and is The shockclamps affixed to the shockmount. mount, mounts in a location depentogether with the computer-amplifier, dent on the particular aircraft type.
secured by two hold-down
(2)
Flight
Controller
is dependent upon the The choice of mounting locations for the flight controller The 5485A and aircraft type, and the type of flight controller to be installed. 5486A are designed to be mounted by quarter-turn fasteners into an ARINCtype mounting, which must be provided by the installing agency. The 5487G rewhich is supplied along with the appropriate quires a supporting dust structure, kit. The aircraft for cover in the STC installation connector the interwiring 5487G is supplied as part of the dust cover. The aircraft interwiring connector for the 5485A and 5486A are supplied in the switch and connector kit. (3)
Primary
Servos
With Capstans
procedures for the roll, pitch and yaw primary servos together with their respective cable drive drum (capstan) assemblies are determined aircraft installation. Detailed instructions by the particular cable tensions, clutch settings, etc. , and other pertinent data concerning for installing the servos are included in the installation kit. The installation
(4)
Pitch Trim
Servo
The installation procedure for the pitch trim servo is determined Detailed instructions particular aircraft installation. concerning tensions, etc. , are included in the system installation kit. (5)
Slip/Skid
by the cable
Sensor
The slip/skid sensor is mounted to the aircraft frame forward generally, nose, Mounting in the aircraft along the centerline
of in
the fire wall, the nose 2-4
I. B. 20004
Revised
Oct/75
Bendix Avionica Division M-4D AUTOMATIC
4.B. (5)
is recommended are included in (6)
Altitude
as
the
Installation
Manual FLIGHT
the best location.
syst system em
in inssta tall llat atiion
CONTROL
Deta Detail iled ed
kit.
SYSTEM
ins nsta tall llat atio ionn
instructions
Controller
The exact mounting location of the altitude controller is dependent upon the particular type of ai airc rcra raft ft.. it is mounted near the static Generally, De Dettaile ailedd inst nstall allat atio ionn instructions are included in the system ports. installation kit. Instruments
(7)
The following instruments the installation kit:
are panel-mounted
2179A-CF or 2181D-CF DH-841A or C DH-861A or DH-866A IN-863A or IN-831A 4099B
and will be so specified
in
Attitude Director Director
Gyro Horizon Horizon Situation Display Indicator Turn and Ban Bank Ind ndiica cato torr
Outline drawings of the 4099B, 2179A-CF and 2181D-CF are included in this manual. Refer to I. B. 2864-( ) or 2863 for additional information on the 860-840 series instruments. information Refer to I. B. 2830-1 for installation on IN-831A. kit will call out all approved instruments The ST C installation and the HorizonDH-866A. specific covers locations aircraft. B . 2 8 6 6 Director their in a I. Miscellaneous
(8)
Controls
Other associated controls such as AFCS RELEASE, GO-AROUND and Manual Electric Trim Switch (if used) will be mounted on the control wheel, throttle or specific location called out in the ST STC C inst instal alla lati tion on drawing. C.
Wiring (1)
General STC STC in inst stal alla lati tion on drawings for unit location and system interwiring 2-27 The inter(figure in this manual) before fabrication of cable harness. conmattion for various optional instruments, wiring drawing includes informa trollers and servo configurations. Use only that portion of the interwiring related to the specific components are Mating connectors to be installed. switch (P/N an andd co conn nnec ecto torr kit part of 4007265-0501). Review
2-5
I B. 20004
Revised
Oct
Bendix Avionica Division M-4D AUTOMATIC
4. C. (2)
Taper
Installation Manual FLIGHT
CONTROL
SYSTEM
Pi Pinn Inst Instal alla lati tion on
The mating connector for the computer-amplifier is ph phys ysic ical ally ly a part of the 1V009-0 5 shocktnount. This mount is supplied less the taper pins that insert into the connector receptacles on the shockrnount. The taper pins (18 and 22 AWG) are supplied as part of the switch and connector kit (P/N 4007265-0501). After establishing the proper fit and length of the After this has harness, the taper pins should be connected to the harness. been done, proper taper pin insertion into the receptacles at the rear of computer-amplifier the shockmount must be carried out. Special tools are required to perform the procedures The tool and taper pins correctly. are available from the factory and are listed below in Table 2-1. WIRE SIZE
TAPER BENDIX NO. 24055-04LP 24055-02 LP
18 ga 22 ga 18/22 ga
NO. AMP NO. 41652 41649
18/22 ga
AMP NO.
TOOLS
DESCRIPTION
47043 47042 380518-3
Pin Crimping Pin Crimping Pin Pin Inser nserti tion on
380305-1
Pin Pin Ex Exttract ractio ionn
Taper Pin Data Table 2-1
5.
Post-Installation A.
Check Out
General
for ground testing the system after installation This section provides procedures in the aircraft. No spe peccia iall test equipment is required except that a usable VOR (A simu simula lato torr may be substituted and/or glide slope signal should be present. if check-out of these functions is to be completed on the ground). has been confirmed It is assumed that interwiring supplying the correct voltages. B.
are
Preliminary (1)
Close all circuit breakers associated with (4.5 to 5.0 in Hg) if using air drivenattitude master
(2)
I.B.
and all power sources
switch.
the system. gyros.
Provide vacuum Activate AFCS
DH-8441( ), DH-861A or convenCheck for gyro erection as ind ndiica cate tedd on DH-8 tional attitude gyro. On the DH-861A, GYRO flag and CMPT flag should disappear. The flight director command bars or dots should also be out of view at this time.
2-6
/75
20004
Revised
Aug/74
Bendix Avionica Division
Installation Manual
1VÏ-4D AUTOMATIC FLIGHT
5.B.
(3)
CONTROL
SYSTEM
Check that HDG flag disappears
muth card on IN-831A or IN-863A and azimut within minutes slaves to a i r c r a f t h e a d i n g two m a x i m u m : c alibration fast of SG-832B compass system is treated in I. B. 2830-1.
(4)
alll an annu nunc ncia iato tors rs Check that al command knob is centered.
(5)
On
on AFCS controller
are extinguished
and
the turn
the DH-861A or DH-866A, turn FD ON-OFF
switch to ON po posi siti tion on.. With ON-OFF panel mounted FD switch to O N p o s i t i o n . T h e set ) indication (Bars or Dots) should appear on the flight director
the DH-841( command indicator.
In all subsequent tests exéept manual electric trim, command indication may be evaluated simultaneously trolled surface command as follows.
the flight director
with AFCS con-
control If aft, then aircraft. director should movecolumn comthe ma manntest d icalls ndicatiofor n the fly down above tothego symbolic the flight A command will cause the control column to move forward and the command indication to go below the symbolic aircraft on the flight director display. a roll right command will cause the control wheel to turn clockSimilarly, wise and the command indication to call for a right turn. After completion of the combined AFCS system is evaluated with AFCS disengaged. C.
Manual
Trim
Electric
aircraft
Check
Center
(2)
Operate elevator trim switch on control column to DN. Aircraft elevator trim indicator should move downward and aircraft trim control wheel should move in the down direction.
(3)
Operate
elevator
elevator
trim tab.
(1)
trim switch to UP.
should move upwards,
UP di dire rect ctio ion. n. (4)
D.
tests, the flight director
Operate
trim switch to recenter
Servo Forces NOTE: (1)
and aircraft
and Engage
Aircraft elevator trim indicator trim control wheel should rotate in an
trim control
a nd
trim indicator.
Logic
If 3013J or 3013K Servo is used omit step (b).
Pitch (a)
Check
that ELEV trim meter on AFCS controller
is centered.
I. B. 20004
2-7
Aug|74
Revised
Bendix Avsonica Davasion -
.
-
-
-
Installation
Manual
M-4D AUTOMATIC F LIGHT CONTROL
5. D. (1)
(2)
SYSTEM
(b )
Pull control column back, check that ELEV trim meter deflects down. Push column forward, check ELEV trim meter deflects upward. Meter should ould retur turn to center when column is stationary.
(c)
Press
(d)
Manually overpower pitch. Observe that AF CS opposes the movement and aircraft pitch trim wheel runs in opposite direction; i.e., pulling column back should result in nose down trim. Repeat test for both directions of column movement. ELEV trim meter will also deflect in a direction opposing the overpower.
(e)
Activate Pitch knob on AFCS controller in the DOWN direction. The control colum olumnn sho should uld move smoothly forward and the pitch trim When pitch knob released, wheel should move in a nose down direction. control column should ould retur turn to near original position. Repeat test for UP direction of AFCS controller pitch knob.
(f)
AP ON annunciator Activate manual electric trim switch (if installed). should extinguish. No opposition to roll or pitch control movements shou hould be enc ncoounte ntered.
AP button on AF AFCS CS co cont ntro roll ller er.. annunciators should illuminate.
AP ON and YAW ON
Roll NOTE: Proper phasing of velocity generator is checked in (b). However, ileron on trim indicator is installed, reversed velocity generators if no ailer ontrol ol respon ponse and instability when the control wheel cause rough contr should be at rest. (a)
control wheel to the neutral position for for ai aile lero rons ns.. If 3013J or 3013K Servo is used omit step (b).
Set aircraft :
(b)
check for zero indication If AFCS alleron trini indicator is installed, (adjust roll trim if necessary). Turn control wheel clockwise and note trim indicator moves counterclockwise. Repeat by turning wheel and note that trim indicator mo counterclockwise move vess cl cloc ockw kwis ise. e.
(c)
AP button on AFCS controller. should illuminate.
(d)
TRIM co cont ntrrol on AFCS panel by adjusting for Check action of ROLL TRIM control wheel rotation off center and then re-centering.
Press
AP ON and YAW ON annunciators
2-8
I.B.
20004
Revised Aug/74
Bendix Avionics Division
Installation
Manual
M-4D AUTOMATIC FLIGHT
5. D. (2)
CONTROL
(e)
Observe AFCS opposes the movement. Manually overpower ROLL. meter Aileron trim (if (if in inst stal alle led) d) will also deflect in a direction opposing the movement. Repeat test for both directions of control wheel movement.
(f)
Actuate TURN knob on AFCS control panel for a right turn. Repeat for left Wheel should smoothly rotate to the right.
(g) Center
TURN knob in its zero detent
to center.
(h)
(3)
position.
Control
turn.
Wheel should return
operate A/P Release switch on pilot's control wheel. AP Momentarily No further and YAW ON annunciators on controller should extinguish. felt. opposition to control movements should be
Yaw NOTE:
(a)
phasintrim g ofinvelocity is checked in (b). IProper f no rudder dicator generator is installed, output a reversed velocity generator shows up as rough control response and instability around neutral position.
Set rudder NOTE:
pedals
manually
to neutral position for rudder.
If 3013J or 3013K Servo is used omit step (b).
(b)
If AFCS trim indicator installed, check for zero indication, then press left rudder pedal and note trim indicator moves clockwise. Repeat Trim indicator should move counterclockwise. test for right rudder.
(c)
Press YAW button on AFCS controller. illuminate.
(d)
Manually overpower movements.
(e)
Momentarily
should
guish.
(4)
SYSTEM
rudder
YAW ON annunciator
in both both dire direct ctio ions ns..
Observe
operate AP Release button on control wheel. be felt to rudder foot pressure. YAW Annunciator
should
AFCS opposes No op oppo posi siti tion on
should extin-
(f)
AP ON and YAW ON annunciators Press AP button on controller. illuminate. Opposition to rudder pedal pressure should be felt.
(g)
Physically move 4099B Turn and Bank Indicator (which houses Yaw Rate Yaw w move moveme ment nt proGyro) and observe corrective rudder action. Left Ya vice-versa. duces right rudder correction and
Pitch Sync Button
(a) With AP engaged gradually
(b)
Depress
an andd airc aircra raft ft on ground, elevator show some slight deflection from center.
SYNC button on yoke.
ELEV
trim meter will
trim meter should re-center.
should
I.B.
20004
Revised
2-9 Au /74
Bendix Installation Avionica Manual Division M-4D AUTOMATIC FLIGHT CONTROL
5.D.(4) (c)
If the ELEV trim meter does not center, RDO55 on the 5538F computer calibration board F9 must be set. After depressing the SYNC button, if the ELEV trim meter gives a down deflection, R9055 should be adju adjust sted ed CCW. If the ELEV trim meter gives an up deflection, R9055 should be adjusted CW for a center needle. After adjustment, retest of the SYNC nece cesssary sary button is ne to confirm centering.
by The computer can be made accessible, if necessary utilizing a pair of adapter cables from the shockmount Cables to be wired pin-to-pin to the computer. on mating 24049-0007 connectors P/N (Wi Winc nchhest ester #XM #XMRA66 RA66PP-72 7244) and P/N 24049-0004 (Winchester #XMRA66SA-723).
NOTE:
CARE MUST BE TAKEN TO ADA PT P1 TO J1 AND P2 TO J2 WITH CORRECT PIN ALIGNMENT.
CAUTION:
R9055 can also be adjusted on the bench by referring I. B. 20004A, Section II, paragraph 4. H. (3).
NOTE: E.
Lateral (1)
(2)
SYSTEM
to
Modes Heading
to aircraft
heading.
(a)
Rotate
HDG knob on HSI
(b)
Press
HDG button on controller.
(c)
Rotate HDG knob to should rotate right.
(d)
Rotate HDG knob to aircraft should rotate left.
(e)
Move mode TURN should f the knob odniseAnFgCagSe coanstroellveirdencoeudt oby detent position. annunciator HDG HDGcenter on the controller extinguishing.
(f)
Reset
TURN knob
NAV and APPR
HDG lamp should
then illuminate.
aircraft heading plus 10 degrees.
Control wheel
heading minus 10 degrees.
Control wheel
to the center detent position.
and REV Modes
(a)
Press NAV button. Set CRS select on HSI to aircraft heading. HDG annunciator should extinguish. should illuminate.
(b)
Rotate CRS seleot should rotate right.
to aircraft
(c)
Rotate
to aircraft heading minus 10 degrees.
(d)
wheel should rotate left. Check that NAV mode disengages detent.
CRS select
heading plus 10 degrees.
if
turn knob
moved
Control Control
from center
It wheel
I. B. 20004
Revised
2-10 Aug/74
Bendix
Avionica -
Division
-
Installation
Manual
M-4D AUTOMATIC FLIGHT
5.E.(2)
CONTROL
SYSTEM
(e)
Tune in NAV receiver for a local VOR channel or use simulator Check NAV flag on HSI is out of sight. radio test signal.
(f)
Rotate
CRS knob for a TO indication
on HSI and full scale
for
deflection
deviation bar. Engage NAV function. ourrse deviation bar on (g) Control wheel should rotate in direction of cou left de defl flec ecti tion on of course deviation bar control wheel turns HSI; i. e. left for a left bank. of course
,
F.
(2)
bar on HSI.
Repeat
(i)
Press guish.
(j)
houuld illu illumi mina nate te.. Press REV butto utton. n. APPR and REV annunciators sho Repeat tests (b) through (h) except note that in steps (b) and (c) CRS select After tuning in the acts to rotate control wheel in an opposite direction. NAV station, steps and (h) will result in control wheel rotation away from course deviation(g)har if using IN-831A or IN-863A. GS ARM annunciator should never illuminate in REV mode.
Vertical (1)
test for opposite deflection of course deviation
(h)
APPR button. APPR ON should illuminate. NAV should extin(b) through (h) for this condition. Repeat paragraphs
Modes
Altitude ALT button on AFCS controller.
ALT ON should illuminate.
(a)
Press
(b)
Activate PITCH knob on AFCS controller for UP condition. should extinguish and pitch trim wheel runs up.
ALT
Glide Slope (a)
Set H in Aselect PPR mode the the SI. system Set CRS to aircand raft center headingthe . course deviation bar on
(b)
signaal, gener nerate a full up glide slope command. With a glide slope test sign annunciator i l l u m i n ate after approximately 20 seconds. should GS ARM GS flag on HSI should disappear.
(c)
Turn off glide slope test signal. GSARM annunciator should extinguish and conditions illuminate annunciator after these should are satisfied. ON GS
(d)
Turn glide slope test signal on and check control same direction as glide slope deviation needle.
(e)
Glide slope can be engaged at any time, except while in Go-Around, by pressing will illuminate. momentarily the GS button. GS ON annunciator
column deflects in
2-11
I. B. 20004
Aug/74
Bendix Avionica Division M-4D AUTOMATIC
5. F. (3)
Instaflation Manual FLIGHT
CONTROL
SYSTEM
Go-Around (a)
With APPR and GS modes engaged, press the throttle or control wheel (provided as part mounted GA button. The GA annunciator of othe herw rwiisemovpanel The should illuminate. should should extinguish. conDH-861A trol columonr ot e AFTmounted) . GS annunciator A PP PPR R an annnun unccia iato torr should remain on.
G.
Flight
the HDG knob on HSI to aircraft
heading plus 10 degrees.
(b)
Set
(c)
Check that HDG ON annunciator Press the HDG button on controller. annu nunnci ciat ator or ex extting ngui uish shes es.. illuminates and APPR an
(d)
Control
(e)
GA annunciator Select ALT mode. ator should illuminate.
(f)
Momentarily pressandA/P controextinguish. l wheel. switchonshould ALT release YAW annunciators ON, HDG
Director
wheel
turns to the right. and ALT annunci-
should extinguish
AP ON,
Check-Out
the flight director
(1)
Assuming autopilot functions display may now be evaluated
(2)
The AP ON annunciator
(3)
Rotate
(4)
ComPress Pitch SYNC button after DOWN and UP commands displayed. mand mand ind ndic icat atio ionn should center within 3 seconds. Hold SYNC button until it does.
(5)
degr gree ees. s. Depress HDG HDG knob on HSI to aircraft heading plus 10 de Command indication should be a right turn. Repeat button on controller. for aircraft heading minus 10°. Command indication should be a left turn. On DH-861A, HDG annunciator will be illuminated.
(6)
Set HDG on HSI
all operates satisfactorily, in FD only mode.
should be off(AP disengaged)
PITCH knob for UP and DOWN commands. should move up and down respectively.
during Flight
the following checks.
Director
commands
Rotate
flight.
to aircraft
heading.
Command
indication
should be level
(7)
Select ALT and APPR modes on controller. HDG annunciators should will illuminate. Set extinguish. On DH-861A, ALT and V-L annunciators CRSS selec CR electo torr on HSI to aircraft heading plus 10 degrees. Command indication should be a right turn with no up or down command.
(8)
Press GA button. ALT mode annunciator indication should be up with a right turn,
should extinguish.
Command
I. B. 20004
2-12 Aug/74
Revised
Bendix Avionics Division
M-4D AUTOMATIC
5. G. (9) (10) H.
Installation Manual .
FLIGHT
CONTROL
SYSTEM
Press ALT and momentarily move TURN knob out of center and APPR should extinguish and ALT annunciator illuminate. vell fli ligh ght. t. indication should call for leve Rotate optional cockpit of command indication.
mounted
parallax
pot
detent. GA Director
to check vertical
deflection
Attitude Gyro Check and Calibration
the gyro sensitivity
is not equal to 100 mv/degree, R115 PITCH GYRO GAIN adjust sted ed (see figure 2-3). and R131 ROLL GYRO GAIN must be adju If
(1)
Remove Flight and reconnect,
(2)
Engage
(3)
Rotate
5485A or 5487G from the instrument using the extender cable (see figure 2-4).
Controller
panel
AP (AFCS).
attitude gyro 10 degrees up and down in the pitch axis.
Note
the
Note
the
(4)
level indication null voltage With an ac voltmeter connected to pin 4 on the extender cable, adjust R115 PITCH GYRO GAIN for 1. O vrms voltage change for a 10 degree
(5)
attitude change. Rotate attitude gyro 10 degrees level indication null voltage.
.
With the voltmeter connected to pin 1 on the extender R131 ROLL GYRO GAIN for 1. O vrms voltage change attitude change.
(7)
Turn AP Master in paragraph
Pre-Flight NOTE:
the roll axis.
(6)
and controller NOTE: An optional 6.
right and left in
in
switch off, remove extender the instrument panel.
method 7. C.
of adjusting ,
following.
cable, adjust for 10 degree
cable and reinstall
the gyro
the attitude gyro levels is outlined
Check Refer
forr ad addi diti tion onal al operating to Pilots Handbook fo
flight check.
information
prior
to first
A.
With gyros erected (engines running if necessary for vacuum) place the AFCS The GYRO and CMPT flags on the DH-861A master switch to the ON position. should be out of view.
B.
After pressing
AP button, move the control column fore and aft (from a neutral The position) while observing the ELEV trim meter on the flight controller. moveneedle should deflect to the direction opposite to that of control column ment; i. e. , with column moved forward for a nose-down attitude of aircraft, The aircraft pitch trim wheel should pointer should deflect up, and vice versa. in a dire direct ctio ionn opposite to that of the column. run during column movement,
2-13
I. B. 20004
Revised
Aug/74
Bendix Avionics Division -
Installation Manual
M-4D AUTOMATIC FLIGHT
6.
7.
-
CONTROL
SYSTEM
C.
Opposition from the Apply manual overpower force to the controls in each axis. Oppowheel control should be felt during overpower in the roll and pitch axis. sition from the rudder pedals should be felt when force is applied to right or left rudder.
D.
While making a right or left turn when taxiing the aircraft, check for corresponding rudder control pedal opposition for yaw axis damping check.
E.
Press and release should be observed.
F.
re-trim elevator control surface before due to the operation of automatic pitch trim during necessary Set HDG on the HSI for the desired climb out heading.
G.
Check that Turn the FD switch to the ON position. on flight director indication come into view. Turn
switch.
No op oppo posi siti tion on
Check and manually
from the controls
take--off. This is the preflight check.
the command bars or dots the FD switch to the of offf po posi siti tion on..
Check & Calibration
Flight A.
the A/P Release
Preliminary (1)
Instructions
Pre-Flight
Requirements
To Enablë
Fli Fligh ghtt
Adj Adjust ustment mentss
The following flight adjustments must be made on the 5487G or 5485A in order to match the unit to the installation or in some cases to individual preference. gain, course gain, flight director roll trim. flight Heading director pitch trim, yaw trim. maximum pitch rate, and turn command max bank angle adjustments are within the flight controller (5487G or 5485A). When on
the ground,
jackscrew);
remove connect extender
the 5487G from its dust cover (by turning
cable between
controller
connector
and dust
cover co-pilots connector; position contr5485A and route cable adjustments to permit fasteners; loosenDzus from If using oller Controller, seat. remove controller are accessible through with dust cover on (adjustments dust cover), connect extender cable in similar manner to controller 5487G.
flig ight ht cont contro roll ller er adjustments See Figures 2-3 and 2-4 for location of fl on con-troller 5485A or 5487G and fabrication of extender cable. The extender cable is shown for field-fabrication. Th Thee sug sugge gessted ted length of 3 feet may be altered if desired, and may be used with either controller. Prior to flight, perform pre-flight check for paragraph 6 and review basic per section I of this manual and the Pilots Handbook. operating procedure
I. B. 20004
Revised
2-14
Aug/74
Benclix Avionica Division
Installation Manual
M-4D AUTOMATIC F LIGHT CONTROL
SYSTEM
I
M204ÊOf6 Flight
Controller Figure
Adjustments
2-3
BENDIX PN 24213-0002 CANNON PN DD-50S -C33
BENDIX PN 24149-0005 CANNONPN DD-50P -C33
I
NOTE: WARE ALL PINS ONE-TO-ONE , e.g. Ji-I TO PI-I ETCUSE #22 AWG WIRE, WIRE, APPROX 3 FEET. J I M2042Ol7
SC ..,
PI
Flight
I. B. 20004
Controller Figure
Extender 2-4
Cable
2-15 Aug 74
Bendix Avionics Division
Installation Manual
M-4D AUTOMATIC FLIGHT
7.A. (2)
Cockpit Do's and Dont's
CONTROL
For Optimum
SYSTEM
Performance DO
DON'T Engagetrim AFCS (a) pitch indicwith ator either extreme. (b) Engage out first
aircraft.
at
the AFCS withtrimming the
(c) Engage any late terral function tionss without first centering the roll axis with the roll trim knob on the flight controller. AFCS
Wiaseit for indicator otherw h in direction aircraft will ptoitccenter, of indi indica cato tor. r. Trim utent.
the aircraft
prior
to engage-
Center roll axis directly after AFCS engagement using roll trim on fligh lightt
controller.
AFCS without
(d) Retrim engaged. any lateralthe modes with
Trim modes
engaged. the
(e) Hold pressure in the pitch axis on the control column.
Keep your hand relaxed on the control column when it's necessary for your hand to be there such as prior to disengagement on final approach. Should you hol hold sl sliight ght pressure, the AFCS will sense this and oppose you by retrimming to compensate for the pres-
any lateral
sure.
B.
Retrim aircraft AFCS engaged.
(g)
Operate your M-4D AFCS its performance indicates for need maintenance.
In-Flight NOTE: ( 1)
with the
(f)
Trim
aircraft
with AFCS disengaged.
Perform periodic maintenance per Manual I. B. 20004A. Maintenance
Procedures See figure
2-3 for adjustments
referred
to in this paragraph.
YAW TRIM Adjust With aircraft manually trimmed for straight and level flight, press YAW button on flig flight ht controller. Note ball on Turn and Bank Indícator is centered. If not, reset YAW TRIM pot. As a final check, disengage and re-engage several times. There should be no transients on the rudder pedals. Adjust YAW TRIM until any transient is minimized.
2-16
I. B. 20004
Revised
Aug/74
Bendix Avionica Division 7.B. (2)
Basic
Installation Manual
M-4D AUTOMATIC
FLIGHT
Operation,
Altitude
Attitude
CONTROL
SYSTEM
Hold & Pitcly Command
Adjust
vel fli ligh ghtt, press manually trimmed for straight and level AP ON indicates AFCS engaged. There should be no engagement transient. Adjust, if necessary, the roll trim knob on AFCS AF CS con onttro rolller for a wings level condition.
(a)
With aircraft A/P button.
overpower the AFCS alternately for pitch-up and pitchThe aircraft down conditions. should always return to level flight. The ELEV trim meter should indicate in an opp ppos osit itee direction to any manual force applied to the control column. Trim should run to oppose the force.
(b) Momentarily
(c)
AFCS momentarily level flight.
Overpower
turn to
in roll.
The aircraft
should always re-
(d) Use PITCH knob to set 500 FPM rate of climb. Check that knob introduces changes smoothly and with a rate rate pr prop opor orti tion onat atee to amount of knob rotation. (e) In 500 FPM climb at a noted altitude, Check that overshoot does not exceed
press ALT button on co cont ntro roll ller er.. 75 feet (approximately).
(f) Quickly override AFCS to introduce 500 FPM rate of descent, then release control column. returns to original altitude. Check that aircraft
(g)
Rotate PITCH Adjust PITCH is preset and response can
knob rapidly for CLIMB condition. ALT will disengage. RATE MAX pot for desired response. A maximum limit cannot be exceeded by adjustment, however, the rate of be reduced as desired.
and hold pitch SYNC button on control wheel and at same time, pull control column for a climb attitude. After attitude is established, release SYNC button. Aircraft should maintain climb attitude.
(h) Press
(3)
Flight (a)
Director
Adjustments
With the aircraft in straight and level flight under AFCS control (engage ALT and HDG modes), adjust if necessary FD PITCH TRIM pot to align fl flig ight ht dire direct ctor or indication with symbolic airplane.
(b) At this time, the FD ROLL TRIM pot can also be adjusted the command indication. necessary) ( 4)
Lateral (a)
Mode Adjustments
After quired), degrees
establishing
to level (if
and Operation
level flight with AFCS engaged
(use roll
trim as re-
selercigt ht HoDfGprm Adjust HDG bug on HSI for a heading esoednet . heading. to
10
I.B.
2-17
20004
Bendix
Installation
Avionica Division M-4D AUTOMATIC
7. B. (4)
Manual
FLIGHT
CONTROL
SYSTEM
(b) Aircraft
should bank 10 degrees in direction of selected HEADING GAIN pot so 10 degrees of heading difference degree bank angle.
heading. Adjust in a 10
results
that the aircraft rolls out on selected heading without overshoot. HDG should disengage and (d) Rotate TURN knob to furthest right detent. (c)
Check
aircraft
should bank approximately 25 de degr greees. es. angle. bank max
Adjust
MAX pot for desired (e)
(5)
TURN COMM
Set system to NAV mode with selected course far enough from present Aircraft should establish position to insure full-scale needle deflection. a course to intercept the omni radial. Adjust COURSE GAIN pot if to insure a 45 degree intercept angle. necessary
and Glide Slope Mode Check
Approach
the station in the HDG mode, tune in the localizer
(a) While approaching
and set the CRS knob to the published runway inbound heading. will illu illumi mina nate te.. (b) Press the REV button. The APPR ON and REV ON lights will The aircraft should intercept and track the localizer outbound. (c)
Descend
(d)
Press
(e)
Set
(f)
localizer
to desired
outbound.
ALT
altitude using the PITCH knob while tracking the
to maintain
altitude.
the HDG knob to the procedure-turn
posi siti tion on for When in po will turn to
aircraft
outbound heading.
the procedure turn, press the HDG button. the procedure-turn outbound heading.
procedure rotating the HDG knob. turn by (g) aContinue ircraft heading by more than 150 degrees.
(h) When the aircraft heading is within 90 degrees course, press the APPR button. The aircraft lizer inbound at 45 degrees. (i)
the
of the localizer inbound will will inter nterce cept pt the loca-
the aircraft is established on course and tracking the localizer inbound, the glide slope mask should be out of view and the glide slope When
pointer
(j)
Do not lead
The
Establish etc.).
deflected
full scale
the aircraft
in
upwards.
GS AR ARM M an annu nunc ncia iato torr
the approach configuration
will illuminate.
(such as gear,
flaps,
(k) When the aircraft intercepts the glide slope, the glide slope pointer will will ex exttingu inguiish and be centered, the GS ARM and ALT ON annunciators will GS ON will illuminate. AFCS will now track GS signal.
I.B.
2-18 Aug/74
20004
Bendix
Installation Manual
Avionics Division
M-4D AUTOMATIC
7. B. (5) (1)
Set
and complete
Go-Around
SYSTEM
CONTROL
the HDG knob to the go-around
(m) Whe henn de desi sire redd,
(6)
FLIGHT
heading.
press the A/P RELEASE the lan anddin ingg vi visu sual ally ly..
switch
on
the control wheel
Test
(a) On an ILS approach when in the APPR or REV modes, press the GA (GoAround) button. The aircraft will assume a pitch-up attitude, and track the localizer during climb-out. In addition, the GA annunciator will illuminate. Missed approach heading may be activated by pressing HDG button. Aircraft will continue in a GA mode climb-out attitude. (b) Apply climb power and follow standard (c)
(d) (7)
climb-out
To esta establ blis ishh a new pitch attitude, rotate the PITCH knob and set in the desired rate of climb or use SYNC button and manually set desired rate column. of climb with control When at the desired altitude press ALT button for altitude hold.
Back-Course
Approach
(a) Tune the localizer
the CRS knob.
Test
and set in the published
(b) Engage the HDG mode. Steer the aircraft back-course heading with the HDG knob. (c)
procedures.
or de depa part rtur uree
Press nate. When
front course
heading
to within 90 de deggrees rees
with of
the
the APPR and REV ON buttons will illumiThe aircraft will turn to intercept the localizer back-course beam. the backcourse beam is intercepted, the aircraft will track the the REV button.
Both
localizer.
(8)
the rate of descent with the PITCH knob and power settings, the pre-landing checklist.
(d)
Control complete
( e)
When desired, press the A/P RELEASE switch and complete or execute a Go-Around procedure. visually,
Flight
Director
and
the landing
Test
the appropriate mode button on the controller; but do and press, NOT engage the AFCS. The flight director command will display the commands to the pilot for manual flying of the aircraft.
(a) Select,
Transition
director
flig ighht di dire rect ctor or pressing only to cthe ombiAP ned button flight on the controller and (b) AFCS operation from requires only
to engage the AFCS.
(c)
For AFCS operation
only,
set FD ON--OFF switch
to OFF position.
Revised
I. B. 20004
Aug/74
Bendix Avionica Division -
-
M-4D AUTOMATIC
C.
Optional
.
FLIGHT
Method of Setting Attitude
NOTE: (1)
Installation Manual
-
CONTROL
SYSTEM
Gyro
adju just stme ment nts. s. to figure 2-3 for location of ad
Refer
Roll Gyro Sensitivity (a) With aircraft manually trimmed for straight and level flight, press A/P button. Adjust ROLL TRIM for wings level, set HDG select to 90° off course and press HDG button on the controller,
(b) Adjust R131 ROLL GYRO GAIN for 22° bank angle. 45° error of at least during this adjustment.
(2)
Set HDG select to 90° in opposite direction and check bank angle. Readjust R131 as necessary to maintain bank angles of 22° ±2° in both directions.
(d)
Disengage detent.
heading by momentarily
the roll command
switching
out of
Pitch Gyro Sensitivity Hold
PITCH
Summary
the
up or down. Adjust R115 knob at full displacement 20° ±2° attitude up or down. of GYRO GAIN for maximum PITCH
of In--Flight
Adjustments
Controller Circuit Designation
Function
JD JD
heading
(c)
(a) D.
Maintain
Adjustment
w Trim
R126
Minimum
tch Rate Max
R116
Desired
Pitch Trim oll Trim
R125 R123
FD command FD command
R131
22 ±2° Bank angle
Xoll Gyro Gain h Gyro Gain Gain
Heading
urn Comm Max Course
Gain
:
R115
\Î
«
R113 R132 R112
transient
pitch rate at max command satisfied satisfied
in level flight in level flight
20 ±2° Max pitch attitude 10° Bank for 10° Hdg. error 25° Approx. in full turn command 45° Intercept with full Nav deflection
R121 PITCH COMM TRIM is adjusted with Part 3, Section
rudder
II, paragraph
on
3. M.
the bench in accordance
2-19
I. B. 20004
Revised
m
O
g
.
o
I
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M
1 8 0 4
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5
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5
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2
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2-20 Aug/74
I
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,
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5
L
1
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m
0 0 5
M O 2
Bendix
Avionics Division
Installation Manual
M-4D AUTOMATIC FLIGHT
-
CONTROL
62DO13G Outline,
Computer
Shockmount
SYSTEM
I. B. 20004
Figure
2-9
2-29/2-30
Revised Aug/74
A
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Bendix · Avionics Division ·
Instaliation Manual
·
M-4D AUTOMATIC FLIGHT
FD-II2C OR FD-112VIND. J2
DAT.
PI I
\
Y
5485A OR 54870
5536F Jl
X X HDG.
SYSTEM
CONTROL
H' s
.
|
20 VAC
P4
P2
|
TBI 8
GND
14
VDAC
YX COURSE DAT.
H' 0
(+LT ROLL CMD +RT (+UP PITCH CMD +DN
--
36
T -
U
35 38
F k
I
37
28+DC TOTEST PUSHTOTEST PUSH
Kl 3
ATTITRUODLE
ROLL VERT. GYRO X AA y 9
PITCH ATTITUDE|
+28DC
Sl FCSMASTER FCS MASTER
I
F.D. ENGAGE
|
ON 57 C OFF FDON/0FF SW. FDON/0FF
Y
22
=
I
X
23
31 COMPUTERFLAG
4000672E
NOTES. l. 2.
MUSTBE ALLAC MUST BEOF THESAMEREF. THESAMEREF. PHASE. 4000511 REF: BENDIXDRW DRW4000511 COLLINSOHMAN. MAN.PP/N 622 57 001, 523-0764978-00IllA
3.
BEN BENOIX OIXM40 M40 COMPUT COMPUTER ER5536F 5536F REQUIRESFD BOARD PN 40007463-0501. BOARDPN
PITCH
M-4D
Collins
I. B. 20004
FD-112C or 112V Interface Figure 2-20
Revised
Bendix Avionics Division ·
-
M-4D AUTOMATIC
33\A-6A
Installation Manual
FLIGHT
CONTROL
5536 F VOO9-05
HDG
H
5
DAT
C X
4 I
Y
2
SYSTEM
6
I 75K TBI
FROM FDIO8 FSY EM
P4
14
12
CDRS
z
SYSTEM
li
I
329 B-7R
332D-I I
PITCHATT
26VAC GND Z
LOCDEV
6VAC
a
ND
+RIGHT
5
+LEFT
NOTES:
NAV+ LEFT
2.
EX-LOC REV.
ALLACM ALLACMUST USTBEO BEOFTH FTHESA ESAMER MEREF. EF.PHA PHASE SE OH.MAN REFERENCEOLLiNS298-7R OH. MAN PIN 523-0763457-10\lI3 BENDIXDRAWING BENDIX DRAWING4000511
3.
BENDIXM4DCOMPUTER BENDIXM4D 536F REQUIRES COMPUTER536F ED. BOAR BOARD D P/N4007463-0501
I.
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l
150MVI, +RIGHT
ROLLCMO 150MV/ PITCHCMD PITCHCMD
NAV+ RIGHT
38
-
+00WN LL
37
C MAND
SI FCSMASTER OF OFFF CC
ON 2 OFF FDON/0FF
39
4000672F
M-4D/Co11ins
FD-108/329B-7R
2-47 Oct/75
I. B. 20004
Interface
2-21
Figure
Revised
2-48 Oct/75
Bendix Avionics Division
Installation IVianual .
·
-
M-4D AUTOMATIC
FLIGHT
SYSTEM
CONTROL
5536F C3Pl PITCH CMD + P
HZ 444 P
Pl
37
I
38
PITCHCMD q F/D WARNING HH -
-
P2
ACFT GND.4
P
I
35
R0ll CMD +
s
RDB CMD CMD
l
36
X
54
NOTES
D WARNING FX LOC REV
RFVCRS GND
NV
G
C2P2 RD 444
L
ALLAC MUS MUST T BEO BEOFF THESAME REF. PHASE
2.
REF:BEN BENDIX DIX DRW 4000511 SPERRY MAINT MAN15-3321-01
3.
BENDIX M4DCOMPUTER M4DCOMPUTER536F 536F
-
35
5485A
54876
¯
P4
CPP1 RD-444 COURSE H DATUM C
27 C ? TARSYN444 27
ROLL u ATTITUDE 5 -
26 23
P1TCH CC ATTITUDE
SI-2
VERT OYRO
TB3-2
INTERLOCK R
Cl ClP3 P3 TA TARS RSYN YN 444 INTERLC INTERLC
A/P
I
51
ON
+28
FD
ON/00FFF SW.
4000672D 4000672D
M-4D
39
4. 5.
REQUIRESFDBOARD4007266-0501 OPTl0NAL PARAL PARALLEXADJUSTPOT LEXADJUSTPOT IS NOT TO BEUSE BEUSEDON DON HZ444 (REE4000Sill HDGANDCRSCTMUSTBE HDGANDCRSCTMUST WIREDFOR300MV/0 BEWIREDFOR300MV/0 SENSITIVITYPERSPERRYMANUAL5-332l-Ol
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