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CHAPTER 22
AUTOFLIGHT
CHAPTER
SECTION
SUBJECT CONF PAGE
SUBJECT
AUTOFLIGHT - DDG MAINTENANCE PROCEDURES
22-00-00
MMEL 22-11-1 (DDG) Preparation - Autopilot
Flight Director Computers (AFDC) Inoperative
EFFECT
901
ILF ALL
901
ILF ALL
903
ILF ALL
904
ILF ALL
904
ILF ALL
905
ILF ALL
906
ILF ALL
907
ILF ALL
908
ILF ALL
201
ILF ALL
201
ILF ALL
208
ILF ALL
501
ILF ALL
502
ILF ALL
TASK 22-00-00-040-801
MMEL 22-11-1 (DDG) Restoration - Autopilot
Flight Director Computers (AFDC) Inoperative
TASK 22-00-00-440-801
MMEL 22-11-2 (DDG) Preparation - Autopilot
Backdrive Actuator Systems Inoperative
TASK 22-00-00-040-802
MMEL 22-11-2 (DDG) Restoration - Autopilot
Backdrive Actuator Systems Inoperative
TASK 22-00-00-440-802
MMEL 22-11-6 (DDG) Preparation - Autothrottle
Arm Switches Inoperative
TASK 22-00-00-040-804
MMEL 22-11-6 (DDG) Restoration - Autothrottle
Arm Switches Inoperative
TASK 22-00-00-440-804
MMEL 22-31-2 (DDG) Preparation - Autothrottle
Servomotors (ASM) Inoperative
TASK 22-00-00-040-803
MMEL 22-31-2 (DDG) Restoration - Autothrottle
Servomotors (ASM) Inoperative
TASK 22-00-00-440-803
AUTOPILOT FLIGHT DIRECTOR SYSTEM MAINTENANCE PRACTICES
22-11-00
Autopilot Flight Director System - Deactivation
TASK 22-11-00-040-801
Autopilot Flight Director System - Activation
TASK 22-11-00-440-801
AUTOPILOT FLIGHT DIRECTOR SYSTEM ADJUSTMENT/TEST
22-11-00
Autopilot Flight Director System (AFDS) - System
Test
TASK 22-11-00-730-801
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AUTOFLIGHT
CHAPTER
SECTION
SUBJECT CONF PAGE
SUBJECT
Autopilot Flight Director Computers - System Test
EFFECT
503
ILF ALL
504
ILF ALL
505
ILF ALL
506
ILF ALL
507
ILF ALL
509
ILF ALL
510
ILF ALL
511
ILF ALL
512
ILF ALL
514
ILF ALL
515
ILF ALL
516
ILF ALL
517
ILF ALL
518
ILF ALL
201
ILF ALL
201
ILF ALL
TASK 22-11-00-730-802
Mode Control Panel - System Test
TASK 22-11-00-730-803
TO/GA Switch - System Test
TASK 22-11-00-730-804
Control Column Backdrive - System Test
TASK 22-11-00-730-805
Control Wheel Backdrive - System Test
TASK 22-11-00-730-806
Rudder Pedal Backdrive - System Test
TASK 22-11-00-730-807
ILS Interface - System Test
TASK 22-11-00-730-808
Autopilot Disconnect Warning - System Test
TASK 22-11-00-740-801
Autopilot Flight Director System (AFDS) - System
Configuration
TASK 22-11-00-730-809
ILS Localizer Antenna Switching
TASK 22-11-00-740-802
ILS Glideslope Antenna Switching
TASK 22-11-00-740-803
Autopilot Disengage Bar - Operational Test
TASK 22-11-00-710-801
Autopilot Disconnect Switches - Operational Test
TASK 22-11-00-710-802
TO/GA Switches - Operational Test
TASK 22-11-00-710-803
AUTOPILOT FLIGHT DIRECTOR COMPUTER MAINTENANCE PRACTICES
22-11-01
Autopilot Flight Director Computer Software
Installation
TASK 22-11-01-400-803
22-CONTENTS
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CHAPTER 22
AUTOFLIGHT
CHAPTER
SECTION
SUBJECT CONF PAGE
SUBJECT
AUTOPILOT FLIGHT DIRECTOR COMPUTER REMOVAL/INSTALLATION
22-11-01
Autopilot Flight Director Computer Removal
EFFECT
401
ILF ALL
401
ILF ALL
406
ILF ALL
401
ILF ALL
401
ILF ALL
405
ILF ALL
407
ILF ALL
410
ILF ALL
412
ILF ALL
415
ILF ALL
401
ILF ALL
401
ILF ALL
405
ILF ALL
401
ILF ALL
401
ILF ALL
401
ILF ALL
TASK 22-11-01-000-801
Autopilot Flight Director Computer Installation
TASK 22-11-01-400-801
MODE CONTROL PANEL REMOVAL/INSTALLATION
22-11-02
Mode Control Panel Removal
TASK 22-11-02-000-801
Mode Control Panel Installation
TASK 22-11-02-400-801
Mode Select Switch and Lamp Removal
TASK 22-11-02-000-802
Mode Select Switch and Lamp Installation
TASK 22-11-02-400-802
Mode Control Panel Speed Knob, Heading Knob,
Altitude Knob Removal
TASK 22-11-02-000-803
Mode Control Panel Speed Knob, Heading Knob,
Altitude Knob Installation
TASK 22-11-02-400-803
AUTOPILOT DISCONNECT SWITCH REMOVAL/INSTALLATION
22-11-03
Autopilot Disconnect Switch Removal
TASK 22-11-03-000-801
Autopilot Disconnect Switch Installation
TASK 22-11-03-400-801
TAKEOFF/GO-AROUND SWITCH REMOVAL/INSTALLATION
22-11-04
Takeoff/Go-Around Switch Removal
TASK 22-11-04-000-801
Takeoff/Go-Around Switch Installation
TASK 22-11-04-400-801
22-CONTENTS
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CHAPTER 22
AUTOFLIGHT
CHAPTER
SECTION
SUBJECT CONF PAGE
SUBJECT
CONTROL COLUMN BACKDRIVE ACTUATOR REMOVAL/INSTALLATION
22-11-05
Control Column Backdrive Actuator Removal
EFFECT
401
ILF ALL
401
ILF ALL
408
ILF ALL
401
ILF ALL
401
ILF ALL
407
ILF ALL
401
ILF ALL
401
ILF ALL
407
ILF ALL
501
ILF ALL
501
ILF ALL
502
ILF ALL
503
ILF ALL
504
ILF ALL
505
ILF ALL
TASK 22-11-05-000-801
Control Column Backdrive Actuator Installation
TASK 22-11-05-400-801
CONTROL WHEEL BACKDRIVE ACTUATOR REMOVAL/INSTALLATION
22-11-06
Control Wheel Backdrive Actuator - Removal
TASK 22-11-06-000-801
Control Wheel Backdrive Actuator - Installation
TASK 22-11-06-400-801
RUDDER PEDAL BACKDRIVE ACTUATOR REMOVAL/INSTALLATION
22-11-07
Rudder Pedal Backdrive Actuator Removal
TASK 22-11-07-000-801
Rudder Pedal Backdrive Actuator Installation
TASK 22-11-07-400-801
THRUST MANAGEMENT COMPUTING SYSTEM ADJUSTMENT/TEST
22-31-00
Thrust Management Computing System - System
Test
TASK 22-31-00-730-801
Left TMCF - Autothrottle Servo Loop - System
Test
TASK 22-31-00-730-802
Right TMCF - Autothrottle Servo Loop - System
Test
TASK 22-31-00-730-806
Left TMCF - Autothrottle Switches - LRU
Replacement Test
TASK 22-31-00-730-803
Right TMCF - Autothrottle Switches - LRU
Replacement Test
TASK 22-31-00-730-804
22-CONTENTS
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CHAPTER 22
AUTOFLIGHT
CHAPTER
SECTION
SUBJECT CONF PAGE
SUBJECT
AUTOTHROTTLE SERVO MOTOR REMOVAL/INSTALLATION
22-31-01
Autothrottle Servo Motor Removal
EFFECT
401
ILF ALL
401
ILF ALL
401
ILF ALL
401
ILF ALL
401
ILF ALL
401
ILF ALL
TASK 22-31-01-000-802
Autothrottle Servo Motor Installation
TASK 22-31-01-400-801
AUTOTHROTTLE DISCONNECT SWITCH REMOVAL/INSTALLATION
22-31-02
Autothrottle Disconnect Switch Removal
TASK 22-31-02-000-802
Autothrottle Disconnect Switch Installation
TASK 22-31-02-400-801
22-CONTENTS
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AUTOFLIGHT - DDG MAINTENANCE PROCEDURES
1.
2.
General
A. This procedure has the maintenance tasks for the Master Minimum Equipment List (MMEL)
maintenance requirements as shown in the Dispatch Deviations Guide (DDG). These tasks prepare
the airplane for flight with certain systems/components inoperative.
B.
This procedure also has the tasks that put the airplane back to its usual condition.
C.
These are the tasks for the components in the autoflight system:
(1)
MMEL 22-11-1 (DDG) Preparation - Autopilot Flight Director Computers (AFDC) Inoperative
(2)
MMEL 22-11-1 (DDG) Restoration - Autopilot Flight Director Computers (AFDC) Inoperative
(3)
MMEL 22-11-2 (DDG) Preparation - Autopilot Backdrive Actuator Systems Inoperative
(4)
MMEL 22-11-2 (DDG) Restoration - Autopilot Backdrive Actuator Systems Inoperative
(5)
MMEL 22-11-6 (DDG) Preparation - Autothrottle Arm Switch Inoperative
(6)
MMEL 22-11-6 (DDG) Restoration - Autothrottle Arm Switch Inoperative
(7)
MMEL 22-31-2 (DDG) Preparation - Autothrottle Servomotors (ASM) Inoperative
(8)
MMEL 22-31-2 (DDG) Restoration - Autothrottle Servomotors (ASM) Inoperative
TASK 22-00-00-040-801
MMEL 22-11-1 (DDG) Preparation - Autopilot Flight Director Computers (AFDC) Inoperative
A.
General
(1)
This task contains the maintenance steps which prepare the airplane for flight with the
Autopilot Flight Director Computers (AFDC) inoperative.
(2)
All AFDCs may be inoperative provided approach minimums do not require use of the
associated autopilot.
(3)
One AFDC may be inoperative provided:
(4)
(5)
(a)
Associated AFDC is deactivated.
(b)
Associated AFDC backdrive actuator is deactivated.
Center and one other AFDC may be inoperative provided:
(a)
Associated AFDCs are deactivated.
(b)
For left or right AFDC inoperative, the associated AFDC backdrive actuator is
deactivated.
(c)
Radio altimeter associated with the operative AFDC operates normally.
(d)
Both flap/slat control lanes operate normally.
(e)
All warning electronics system channels operate normally.
All AFDC may be inoperative provided:
(a)
All AFDCs are deactivated.
(b)
Both AFDC backdrive actuators are deactivated.
(c)
Number of flight segments and segment duration is acceptable to flight crew.
(d)
Enroute operations do not require use of the autopilots.
22-00-00
EFFECTIVITY
ILF ALL
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B.
Location Zones
Zone
211
212
C.
Area
Flight Compartment, Left
Flight Compartment, Right
AFDCs Deactivation
SUBTASK 22-00-00-860-001
(1)
If the left AFDC does not operate, then do this step:
(a)
Open these circuit breakers and install safety locks:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
NOTE: The AFDCs are interchangeable. The left AFDC may be moved to the center
position to maintain left backdrive function operational.
SUBTASK 22-00-00-860-002
(2)
If the center AFDC does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
NOTE: The center AFDC does not have an associated backdrive actuator circuit breaker.
SUBTASK 22-00-00-860-003
(3)
If the right AFDC does not operate, then do this step:
(a)
Open these circuit breakers and install safety locks:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
NOTE: The AFDCs are interchangeable. The right AFDC may be moved to the center
position to maintain right backdrive function operational.
SUBTASK 22-00-00-860-009
(4)
If all three AFDCs do not operate, then do these steps:
(a)
Open these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
4
C22601
MCP-L
F
17 C22600
MCP-R
(b)
Close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
4
C22601
MCP-L
F
17 C22600
MCP-R
22-00-00
EFFECTIVITY
ILF ALL
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END OF TASK
TASK 22-00-00-440-801
3.
MMEL 22-11-1 (DDG) Restoration - Autopilot Flight Director Computers (AFDC) Inoperative
A.
General
(1) This task puts the airplane back to its usual condition after operation with the Autopilot Flight
Director Computers (AFDC) inoperative.
B.
References
Reference
22-11-00-730-802
22-11-01-000-801
22-11-01-400-801
Title
Autopilot Flight Director Computers - System Test (P/B 501)
Autopilot Flight Director Computer Removal (P/B 401)
Autopilot Flight Director Computer Installation (P/B 401)
C.
Location Zones
Zone
Area
117
Main Equipment Center, Left
118
Main Equipment Center, Right
211
Flight Compartment, Left
212
Flight Compartment, Right
D.
AFDCs Reactivation
SUBTASK 22-00-00-900-001
(1)
Replace the AFDCs that do not operate. These are the tasks:
· Autopilot Flight Director Computer Removal, TASK 22-11-01-000-801,
· Autopilot Flight Director Computer Installation, TASK 22-11-01-400-801.
SUBTASK 22-00-00-740-001
(2)
If there are more than one AFDCs that do not operate, then do this system test:
(a)
Make sure that these circuit breakers are closed:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
(b)
Do this ground test on the MAT: 22 Autopilot Flight Director System, System Test,
Autopilot Flight Director Computers (TASK 22-11-00-730-802).
1)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
2)
If FAILED shows, select the maintenance message and select MAINTENANCE
MESSAGE DATA or refer to the applicable Maintenance Message Index in the FIM.
END OF TASK
22-00-00
EFFECTIVITY
ILF ALL
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TASK 22-00-00-040-802
4.
MMEL 22-11-2 (DDG) Preparation - Autopilot Backdrive Actuator Systems Inoperative
A.
General
(1) This task contains the maintenance steps which prepare the airplane for flight with the
Autopilot Backdrive Actuator Systems inoperative.
(2)
Both may be inoperative provided approach minimums do not require use of the associated
autopilot.
(3)
One may be inoperative provided:
(4)
B.
(a)
Associated AFDC backdrive actuator is deactivated.
(b)
Opposite AFDC operates normally.
Both may be inoperative provided:
(a)
Both AFDC backdrive actuators are deactivated.
(b)
Number of flight segments and segment duration is acceptable to flight crew.
(c)
Enroute operations do not require use of the autopilots.
Location Zones
Zone
211
212
C.
Area
Flight Compartment, Left
Flight Compartment, Right
Autopilot Backdrive Actuator Systems Deactivation
SUBTASK 22-00-00-860-004
(1)
If the left autopilot backdrive actuator system does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
11
C22607
AFDC BACK DRIVE L
SUBTASK 22-00-00-860-007
(2)
If the right autopilot backdrive actuator system does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
25 C22608
AFDC BACK DRIVE R
END OF TASK
5.
TASK 22-00-00-440-802
MMEL 22-11-2 (DDG) Restoration - Autopilot Backdrive Actuator Systems Inoperative
A.
General
(1)
B.
This task puts the airplane back to its usual condition after operation with the Autopilot
Backdrive Actuator Systems inoperative.
Location Zones
Zone
112
Area
Area Forward of Nose Landing Gear Wheel Well
22-00-00
EFFECTIVITY
ILF ALL
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(Continued)
Zone
115
116
117
118
211
212
C.
Area
Area Outboard and Above Nose Landing Gear Wheel Well, Left
Area Outboard and Above Nose Landing Gear Wheel Well, Right
Main Equipment Center, Left
Main Equipment Center, Right
Flight Compartment, Left
Flight Compartment, Right
Autopilot Backdrive Actuator Systems Reactivation
SUBTASK 22-00-00-860-005
(1)
Remove the safety locks and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
11
C22607
AFDC BACK DRIVE L
F
25 C22608
AFDC BACK DRIVE R
D.
Autopilot Backdrive Actuator Systems Repair
SUBTASK 22-00-00-740-002
(1)
Go to the MAT and find the EICAS status message.
(a)
Find the fault code and the correlated maintenance message numbers on the MAT.
SUBTASK 22-00-00-810-001
(2)
Go to the Fault Code Index in the FIM and find the fault code (the first two digits of the fault
code are the FIM chapter).
(a)
For each correlated maintenance message, find the maintenance message number to
the right side of the fault code.
(b)
Find the task number on the same line as the maintenance message number.
SUBTASK 22-00-00-810-002
(3)
Go to the task in the FIM and do the steps in the task.
END OF TASK
TASK 22-00-00-040-804
6.
MMEL 22-11-6 (DDG) Preparation - Autothrottle Arm Switches Inoperative
A.
General
(1) This task contains the maintenance steps which prepare the airplane for flight with the
Autothrottle Arm Switches inoperative.
(2)
One may be inoperative provided:
(a)
Associated servo motor is deactivated.
ILF 601, 602, 623-632, 650-799
(b)
EEC normal mode operates normally.
(c)
Both thrust levers are manually set for takeoff and go-around thrust.
(d)
Flight remains within 180 minutes of landing at a suitable airport.
ILF ALL
22-00-00
EFFECTIVITY
ILF ALL
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B.
Location Zones
Zone
211
212
C.
Area
Flight Compartment, Left
Flight Compartment, Right
Autothrottle Arm Switches Deactivation
SUBTASK 22-00-00-860-010
(1)
If the left Autothrottle ARM Switch does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
5
C22620
A/T SERVO L
SUBTASK 22-00-00-860-011
(2)
If the right Autothrottle ARM Switch does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
18 C22621
A/T SERVO R
END OF TASK
TASK 22-00-00-440-804
7.
MMEL 22-11-6 (DDG) Restoration - Autothrottle Arm Switches Inoperative
A.
General
(1) This task puts the airplane back to its usual condition after operation with the Autothrottle Arm
Switches inoperative.
B.
References
Reference
22-31-00-730-803
22-31-00-730-804
22-31-01-000-802
22-31-01-400-801
Title
Left TMCF - Autothrottle Switches - LRU Replacement Test
(P/B 501)
Right TMCF - Autothrottle Switches - LRU Replacement Test
(P/B 501)
Autothrottle Servo Motor Removal (P/B 401)
Autothrottle Servo Motor Installation (P/B 401)
C.
Location Zones
Zone
Area
211
Flight Compartment, Left
212
Flight Compartment, Right
D.
Autothrottle Arm Switches Reactivation
SUBTASK 22-00-00-900-003
(1)
Replace the Autothrottle Arm Switches that do not operate. These are the tasks:
· Autothrottle Servo Motor Removal, TASK 22-31-01-000-802,
· Autothrottle Servo Motor Installation, TASK 22-31-01-400-801.
22-00-00
EFFECTIVITY
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SUBTASK 22-00-00-740-004
(2)
If there are more than one Autothrottle Arm Switches that do not operate, then do these system
tests:
(a)
Make sure that these circuit breakers are closed:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
5
C22620
A/T SERVO L
F
18 C22621
A/T SERVO R
(b)
(c)
Do this ground test on the MAT: 22 AIMS - Autothrottle, System Test, Left TMCF Autothrottle Switches (Left TMCF - Autothrottle Switches - LRU Replacement Test,
TASK 22-31-00-730-803).
1)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
2)
If FAILED shows, select the maintenance message and select MAINTENANCE
MESSAGE DATA or refer to the applicable Maintenance Message Index in the FIM.
Do this ground test on the MAT: 22 AIMS - Autothrottle, System Test, Right TMCF Autothrottle Switches (Right TMCF - Autothrottle Switches - LRU Replacement Test,
TASK 22-31-00-730-804).
1)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
2)
If FAILED shows, select the maintenance message and select MAINTENANCE
MESSAGE DATA or refer to the applicable Maintenance Message Index in the FIM.
END OF TASK
TASK 22-00-00-040-803
8.
MMEL 22-31-2 (DDG) Preparation - Autothrottle Servomotors (ASM) Inoperative
A.
General
(1) This task contains the maintenance steps which prepare the airplane for flight with the
Autothrottle Servomotor (ASM) inoperative.
(2)
Both may be inoperative provided:
(a)
Flight remains within 180 minutes of landing at a suitable airport.
ILF 601, 602, 623-632, 650-799
(b)
ECC normal mode operates normally.
ILF ALL
(3)
(4)
One may be inoperative provided:
(a)
Associated servo motor is deactivated.
(b)
Both thrust levers are manually set for takeoff and go-around thrust.
Both may be inoperative provided:
(a)
Both servo motors are deactivated.
(b)
Approach minimums do not require use of the autothrottles.
22-00-00
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B.
Location Zones
Zone
211
212
C.
Area
Flight Compartment, Left
Flight Compartment, Right
ASMs Deactivation
SUBTASK 22-00-00-860-006
(1)
If the left ASM does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
5
C22620
A/T SERVO L
SUBTASK 22-00-00-860-008
(2)
If the right ASM does not operate, then do this step:
(a)
Open this circuit breaker and install safety lock:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
18 C22621
A/T SERVO R
END OF TASK
TASK 22-00-00-440-803
9.
MMEL 22-31-2 (DDG) Restoration - Autothrottle Servomotors (ASM) Inoperative
A.
General
(1) This task puts the airplane back to its usual condition after operation with the Autothrottle
Servomotors (ASM) inoperative.
B.
References
Reference
22-31-00-730-802
22-31-00-730-806
G1: 76-12-01-000-805-H00
G1: 76-12-01-400-804-H00
RR: 76-12-01-000-803-R00
RR: 76-12-01-400-803-R00
Title
Left TMCF - Autothrottle Servo Loop - System Test (P/B 501)
Right TMCF - Autothrottle Servo Loop - System Test (P/B 501)
Autothrottle Servomotor (ASM) and Gearbox Removal (P/B 401)
Autothrottle Servomotor (ASM) and Gearbox Installation
(P/B 401)
Autothrottle Servomotor and Gearbox Removal (P/B 401)
Autothrottle Servomotor and Gearbox Installation (P/B 401)
C.
Location Zones
Zone
Area
211
Flight Compartment, Left
212
Flight Compartment, Right
D.
ASMs Reactivation
SUBTASK 22-00-00-900-002
(1)
Replace the ASMs that do not operate. These are the tasks:
· RR: Autothrottle Servomotor and Gearbox Removal, TASK 76-12-01-000-803-R00 or
G1: Autothrottle Servomotor (ASM) and Gearbox Removal, TASK 76-12-01-000-805-H00,
· RR: Autothrottle Servomotor and Gearbox Installation, TASK 76-12-01-400-803-R00 or
22-00-00
EFFECTIVITY
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G1: Autothrottle Servomotor (ASM) and Gearbox Installation, TASK 76-12-01-400-804-H00.
SUBTASK 22-00-00-740-003
(2)
If there are more than one ASMs that do not operate, then do these system tests:
(a)
Make sure that these circuit breakers are closed:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
5
C22620
A/T SERVO L
F
18 C22621
A/T SERVO R
(b)
(c)
Do this ground test on the MAT: 22 AIMS - Autothrottle, System Test, Left TMCF Autothrottle Servo Loop (TASK 22-31-00-730-802).
1)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
2)
If FAILED shows, select the maintenance message and select MAINTENANCE
MESSAGE DATA or refer to the applicable Maintenance Message Index in the FIM.
Do this ground test on the MAT: 22 AIMS - Autothrottle, System Test, Right TMCF Autothrottle Servo Loop (TASK 22-31-00-730-806).
1)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
2)
If FAILED shows, select the maintenance message and select MAINTENANCE
MESSAGE DATA or refer to the applicable Maintenance Message Index in the FIM.
END OF TASK
22-00-00
EFFECTIVITY
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AUTOPILOT FLIGHT DIRECTOR SYSTEM - MAINTENANCE PRACTICES
1.
2.
General
A. This procedure has these tasks:
(1)
Autopilot Flight Director System Deactivation.
(2)
Autopilot Flight Director System Activation.
TASK 22-11-00-040-801
Autopilot Flight Director System - Deactivation
(Figure 201)
A.
General
(1)
B.
C.
This procedure removes electrical power from the following components of the Autopilot Flight
Director System:
(a)
Autopilot Flight Director Computer.
(b)
Control Column Backdrive Actuator.
(c)
Control Wheel Backdrive Actuator.
(d)
Rudder Backdrive Actuator.
References
Reference
29-11-00-860-808
45-10-00-740-819
Tools/Equipment
Reference
STD-858
Title
Main Hydraulic System Power Removal (P/B 201)
How to Do a Ground Test (P/B 201)
Description
Tag - DO NOT OPERATE
D.
Location Zones
Zone
Area
117
Main Equipment Center, Left
118
Main Equipment Center, Right
211
Flight Compartment, Left
212
Flight Compartment, Right
E.
Procedure
SUBTASK 22-11-00-860-045
WARNING
MAKE SURE THAT THE AREA AROUND THE DOOR FOR THE MAIN
LANDING GEAR IS CLEAR OF PERSONNEL, AND EQUIPMENT. THE DOORS
CLOSE QUICKLY. THIS CAN CAUSE INJURIES TO PERSONNEL, AND
DAMAGE TO EQUIPMENT.
WARNING
KEEP PERSONNEL AND EQUIPMENT AWAY FROM THE AREA AROUND THE
THRUST REVERSERS. THE THRUST REVERSERS EXTEND AND RETRACT
QUICKLY. INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN
OCCUR.
22-11-00
EFFECTIVITY
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(WARNING PRECEDES)
WARNING
(1)
KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL
SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS. THESE
COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
Make sure clearance zones are established at the following areas of flight control surfaces:
(a)
Ailerons
(b)
Rudders
(c)
Elevators
(d)
Flaps
(e)
Slats
(f)
Spoilers
(g)
Landing Gear
(h)
Thrust Reversers
(i)
Drive mechanisms
SUBTASK 22-11-00-020-001
(2)
For the left, center, and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-00-860-048
(3)
Set all the FLT CONTROL HYD VALVE POWER TAIL switches, on the aft Overhead
Maintenance Panel P61, to the SHUT OFF positions.
SUBTASK 22-11-00-860-035
(4)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
21
24
C34630
C22606
C22604
ILS ANT SWITCH C
AFDC WARN
AFDC-C
C34429
ILS L
ILF ALL
A
A
A
ILF 120-199
E
9
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
C34428
ILS R
ILF 120-199
E
22
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
4
C22601
MCP-L
ILF ALL
F
22-11-00
EFFECTIVITY
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(Continued)
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
8
C34629
ILS ANT SWITCH L
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
F
17 C22600
MCP-R
F
21 C34628
ILS ANT SWITCH R
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
SUBTASK 22-11-00-860-036
(5)
Make sure that a DO NOT OPERATE tag, STD-858 is on the captain©s and first officer©s control
wheels.
SUBTASK 22-11-00-860-037
(6)
F.
Set both F/D switches on the Mode Control Panel to OFF and attach a DO NOT OPERATE
tag, STD-858.
Autopilot Flight Director System - Tryout
NOTE: This tryout is to make sure the Autopilot Flight Director System is in a zero energy state.
SUBTASK 22-11-00-860-046
WARNING
MAKE SURE THAT THE AREA AROUND THE DOOR FOR THE MAIN
LANDING GEAR IS CLEAR OF PERSONNEL, AND EQUIPMENT. THE DOORS
CLOSE QUICKLY. THIS CAN CAUSE INJURIES TO PERSONNEL, AND
DAMAGE TO EQUIPMENT.
WARNING
KEEP PERSONNEL AND EQUIPMENT AWAY FROM THE AREA AROUND THE
THRUST REVERSERS. THE THRUST REVERSERS EXTEND AND RETRACT
QUICKLY. INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN
OCCUR.
WARNING
KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL
SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS. THESE
COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
(1)
Make sure clearance zones are established at the following areas of flight control surfaces:
(a)
Ailerons
(b)
Rudders
(c)
Elevators
(d)
Flaps
(e)
Slats
(f)
Spoilers
(g)
Landing Gear
(h)
Thrust Reversers
(i)
Drive mechanisms
22-11-00
EFFECTIVITY
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SUBTASK 22-11-00-860-039
(2)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
21
24
C34630
C22606
C22604
ILS ANT SWITCH C
AFDC WARN
AFDC-C
C34429
ILS L
ILF ALL
A
A
A
ILF 120-199
E
9
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
C34428
ILS R
ILF 120-199
E
22
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
4
8
10
11
17
21
24
25
C22601
C34629
C22603
C22607
C22600
C34628
C22602
C22608
MCP-L
ILS ANT SWITCH L
AFDC-L
AFDC BACK DRIVE L
MCP-R
ILS ANT SWITCH R
AFDC-R
AFDC BACK DRIVE R
ILF ALL
F
F
F
F
F
F
F
F
SUBTASK 22-11-00-860-040
(3)
Make sure that the Mode Control Panel ªA/Pº pushbutton light bars are not lit and that both F/D
switches are set to OFF.
SUBTASK 22-11-00-740-022
(4)
Use a maintenance access terminal (MAT) to do a test of the Autopilot Flight Director
Computers (How to Do a Ground Test, TASK 45-10-00-740-819):
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Autopilot Flight Director Computers
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
22-11-00
EFFECTIVITY
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(c)
1)
CONTINUE
2)
START TEST
When the test is completed, make sure that FAILED shows adjacent to TEST
CONDITION on the MAT.
1)
If FAILED shows, Auto Flight Director System is deactivated.
END OF TASK
22-11-00
EFFECTIVITY
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MODE
CONTROL
PANEL
A
SEE
MAINTENANCE
ACCESSTERMINAL
(MAT)
MAT KEYBOARD
SEE B
FLIGHT COMPARTMENT
A/T ARM
L
R
IAS
IAS
A/P
g
w
F/D ON
OFF
OFF
HDG
MACH
CLB
CON
w
VNAV
A/T
FLCH
g
w
g
w
g
w
V/S
HDG
LNAV
g
w
TRK
V/S
A/P DISENGAGE
A/P
AUTO
25
5
AUTO
ALTITUDE
FPA
SEL
BANK
LIMIT
DOWN
HOLD
g
w
UP
VS/FPA
g
w
g
w
1000
HOLD
g
w
LOC
g
w
F/D ON
APP
g
w
OFF
MODE CONTROLPANEL
A
2404701 S0000555801_V1
Autopilot Flight Director System
Figure 201/22-11-00-990-801 (Sheet 1 of 2)
22-11-00
EFFECTIVITY
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MAT
DISPLAY
BRIGHTNESSKNOB
SELECTION SWITCH
TRACKBALL
B
MAT
DISPLAY
1
SELECTION
SWITCH
BRIGHTNESS
KNOB
TRACKBALL
1
2
PORTRAIT MAT
LANDSCAPEMAT
B
2
2404717 S0000555816_V1
Autopilot Flight Director System
Figure 201/22-11-00-990-801 (Sheet 2 of 2)
22-11-00
EFFECTIVITY
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3.
TASK 22-11-00-440-801
Autopilot Flight Director System - Activation
(Figure 201)
A.
General
(1)
B.
C.
This procedure adds electrical power to the following components of the Autopilot Flight
Director System:
(a)
Autopilot Flight Director Computer.
(b)
Control Column Backdrive Actuator.
(c)
Control Wheel Backdrive Actuator.
(d)
Rudder Backdrive Actuator.
Tools/Equipment
Reference
STD-858
Location Zones
Zone
117
118
211
212
D.
Description
Tag - DO NOT OPERATE
Area
Main Equipment Center, Left
Main Equipment Center, Right
Flight Compartment, Left
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-047
WARNING
MAKE SURE THAT THE AREA AROUND THE DOOR FOR THE MAIN
LANDING GEAR IS CLEAR OF PERSONNEL, AND EQUIPMENT. THE DOORS
CLOSE QUICKLY. THIS CAN CAUSE INJURIES TO PERSONNEL, AND
DAMAGE TO EQUIPMENT.
WARNING
KEEP PERSONNEL AND EQUIPMENT AWAY FROM THE AREA AROUND THE
THRUST REVERSERS. THE THRUST REVERSERS EXTEND AND RETRACT
QUICKLY. INJURIES TO PERSONNEL, AND DAMAGE TO EQUIPMENT CAN
OCCUR.
WARNING
KEEP ALL PERSONS AND EQUIPMENT AWAY FROM THE FLIGHT CONTROL
SURFACES AND THE FLIGHT CONTROL DRIVE MECHANISMS. THESE
COMPONENTS WILL MOVE. THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
(1)
Make sure clearance zones are established at the following areas of flight control surfaces:
(a)
Ailerons
(b)
Rudders
(c)
Elevators
(d)
Flaps
(e)
Slats
(f)
Spoilers
(g)
Landing Gear
22-11-00
EFFECTIVITY
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(h)
Thrust Reversers
(i)
Drive mechanisms
SUBTASK 22-11-00-860-042
(2)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
21
24
C34630
C22606
C22604
ILS ANT SWITCH C
AFDC WARN
AFDC-C
C34429
ILS L
ILF ALL
A
A
A
ILF 120-199
E
9
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
C34428
ILS R
ILF 120-199
E
22
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
4
8
10
11
17
21
24
25
C22601
C34629
C22603
C22607
C22600
C34628
C22602
C22608
MCP-L
ILS ANT SWITCH L
AFDC-L
AFDC BACK DRIVE L
MCP-R
ILS ANT SWITCH R
AFDC-R
AFDC BACK DRIVE R
ILF ALL
F
F
F
F
F
F
F
F
SUBTASK 22-11-00-860-043
(3)
Remove the DO NOT OPERATE tag, STD-858 from the captain©s and first officer©s control
wheels.
SUBTASK 22-11-00-860-044
(4)
Remove the DO NOT OPERATE tag, STD-858 from both F/D switches on the Mode Control
Panel and set the switches to ON.
END OF TASK
22-11-00
EFFECTIVITY
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AUTOPILOT FLIGHT DIRECTOR SYSTEM - ADJUSTMENT/TEST
1.
General
A. This procedure contains scheduled maintenance task data.
B.
This procedure has 15 tasks and these tasks are in the sequence as follows:
(1)
Autopilot Flight Director System (AFDS) - System Test
(a)
(2)
Autopilot Flight Director Computers - System Test
(a)
(3)
This is a special function of the Autopilot Flight Director System. This function allows you
to choose the selected antenna for the ILS localizer signal.
ILS Glideslope Antenna Switching
(a)
(13)
This function lets you do a configuration check of the Autopilot Flight Director Computers
and the Mode Control Panel.
ILS Localizer Antenna Switching
(a)
(12)
This is an interactive test.
Autopilot Flight Director System (AFDS) - System Configuration
(a)
(11)
This is an automatic test.
Autopilot Disconnect Warning - System Test
(a)
(10)
This is an automatic test. The test will not move the rudder pedals if you do not remove
hydraulic power before you do this test.
ILS Interface - System Test
(a)
(9)
This is an automatic test. The test will not move the control wheels if you do not remove
hydraulic power before you do this test.
Rudder Pedal Backdrive - System Test
(a)
(8)
This is an automatic test. The test will not move the control columns if you do not remove
hydraulic power before you do this test.
Control Wheel Backdrive - System Test
(a)
(7)
This is an interactive test.
Control Column Backdrive - System Test
(a)
(6)
This is an interactive test.
TO/GA Switch - System Test
(a)
(5)
This is an automatic test.
Mode Control Panel - System Test
(a)
(4)
This test contains all the AFDS system ground tests.
This is a special function of the Autopilot Flight Director System. This function allows you
to choose the selected antenna for the glideslope signal.
Autopilot Disengage Bar - Operational Test
NOTE: This is a scheduled maintenance task.
(a)
(14)
This is a manual test. .
Autopilot Disconnect Switches - Operational Test
NOTE: This is a scheduled maintenance task.
(a)
This is an interactive test.
22-11-00
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(15)
TO/GA Switches - Operational Test
NOTE: This is a scheduled maintenance task.
(a)
This is an interactive test.
TASK 22-11-00-730-801
2.
Autopilot Flight Director System (AFDS) - System Test
A.
General
(1) This is a system test of the Autopilot Flight Director System (AFDS). The AFDS system test
contains all the system ground tests of the AFDS. This AFDS system test makes sure that the
AFDS is satisfactory.
(2)
B.
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
45-10-00-740-808
Title
How to Use the Central Maintenance Computing System
(P/B 201)
C.
Location Zones
Zone
Area
212
Flight Compartment, Right
D.
Procedure
SUBTASK 22-11-00-740-001
(1)
Do this task: Autopilot Flight Director Computers - System Test, TASK 22-11-00-730-802.
SUBTASK 22-11-00-740-002
(2)
Do this task: Mode Control Panel - System Test, TASK 22-11-00-730-803.
SUBTASK 22-11-00-740-003
(3)
Do this task: TO/GA Switch - System Test, TASK 22-11-00-730-804.
SUBTASK 22-11-00-740-004
(4)
Do this task: Control Column Backdrive - System Test, TASK 22-11-00-730-805.
SUBTASK 22-11-00-740-005
(5)
Do this task: Control Wheel Backdrive - System Test, TASK 22-11-00-730-806.
SUBTASK 22-11-00-740-006
(6)
Do this task: Rudder Pedal Backdrive - System Test, TASK 22-11-00-730-807.
SUBTASK 22-11-00-740-007
(7)
Do this task: ILS Interface - System Test, TASK 22-11-00-730-808.
SUBTASK 22-11-00-740-008
(8)
Do this task: Autopilot Disconnect Warning - System Test, TASK 22-11-00-740-801.
END OF TASK
22-11-00
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3.
TASK 22-11-00-730-802
Autopilot Flight Director Computers - System Test
A.
B.
General
(1) This is an internal function test of the left AFDC, center AFDC, and right AFDC. The test also
makes sure that the left, center, and right AFDC interfaces are satisfactory.
(2)
This is an automatic test. During this test, there is no movement of the flight controls or primary
surfaces.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-001
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-009
(2)
Use a maintenance access terminal (MAT) to do the system test of the Autopilot Flight Director
Computers:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Autopilot Flight Director Computers
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-00
EFFECTIVITY
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TASK 22-11-00-730-803
4.
Mode Control Panel - System Test
A.
B.
General
(1) This is a test of the Mode Control Panel (MCP). This test makes sure that the switch-lights, the
displays, the switches and the selectors on the MCP operate correctly. The test also makes
sure that the interfaces between the MCP and these systems are satisfactory:
(a)
The Autopilot Flight Director Computers
(b)
The Airplane Information Management Systems (AIMS).
(2)
This is an interactive test. During this test, the instructions on the MAT will tell you to operate
all the switches and the selectors on the MCP. Visually monitor the displays on the MCP for the
correct results when you do this test.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-003
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-010
(2)
Use a maintenance access terminal (MAT) to do the system test of the Mode Control Panel:
(a)
(b)
(c)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Mode Control Panel
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
Do the instructions that show on the MAT to complete the test.
1)
Visually monitor the displays on the MCP for the correct results.
a)
If the following message shows after you push the ©VS/FPA© button on the
MCP, push the ©IAS/MACH© button to continue the test.
22-11-00
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ªDescription: This test makes sure the Maintenance Access Terminal is
installed correctly.º
NOTE: If you push ©CONTINUE© on the MAT it will cause the test to fail.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
5.
TASK 22-11-00-730-804
TO/GA Switch - System Test
A.
B.
General
(1) This is a test of the Takeoff/Go-Around (TO/GA) switches and their interfaces with the Autopilot
Flight Director Computers.
(2)
This is an interactive test. During this test, the instructions on the MAT will tell you to operate
the left and right TO/GA switches.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-005
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-860-032
(2)
Make sure that the A/T ARM switches are in the OFF position.
SUBTASK 22-11-00-860-033
(3)
Make sure that the engines are not in operation.
SUBTASK 22-11-00-740-011
(4)
Use a maintenance access terminal (MAT) to do the system test of the TO/GA Switch:
(a)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
22-11-00
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MAKE SURE THAT THE A/T ARM SWITCHES ARE IN THE OFF
POSITION AND THE ENGINES ARE NOT IN OPERATION BEFORE
YOU PUSH THE LEFT OR RIGHT TO/GA SWITCH. IF THE A/T ARM
SWITCHES ARE NOT IN THE OFF POSITION AND THE ENGINES
ARE IN OPERATION AND THE FLAPS ARE NOT IN THE UP
WARNING POSITION, THE AUTOTHROTTLE SERVO MOTORS WILL MOVE
AND THE ENGINES WILL OPERATE AT THE TAKE-OFF THRUST
LEVEL WHEN YOU PUSH THE TO/GA SWITCH. THIS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
(b)
6)
TO/GA Switch
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
Do the instructions that show on the MAT to complete the test.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
TASK 22-11-00-730-805
6.
Control Column Backdrive - System Test
A.
B.
General
(1) This is a test of the left and right control column backdrive actuators. The test makes sure that
the control columns can move through the full range of travel with sufficient rate and torque.
(2)
This is an automatic test. The test will not move the control columns if you do not remove
hydraulic power before you do this test. During this test, the control columns will move.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
29-11-00-860-808
45-10-00-740-808
Title
Supply Electrical Power (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
C.
Location Zones
Zone
Area
212
Flight Compartment, Right
D.
Procedure
SUBTASK 22-11-00-860-007
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
22-11-00
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SUBTASK 22-11-00-860-008
(2)
For the left, center and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-00-740-012
WARNING
(3)
KEEP ALL PERSONS AND EQUIPMENT CLEAR OF THE CAPTAIN©S AND
FIRST OFFICER©S CONTROL COLUMNS. THIS TEST WILL MOVE THE
CONTROL COLUMNS THROUGH THEIR FULL RANGE OF TRAVEL. THIS
CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Use a maintenance access terminal (MAT) to do the system test of the Control Column
Backdrive:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Control Column Backdrive
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
TASK 22-11-00-730-806
7.
Control Wheel Backdrive - System Test
A.
B.
General
(1) This is a test of the left and right control wheel backdrive actuators. The test makes sure that
the control wheels can move through the full range of travel with sufficient rate and torque.
(2)
This is an automatic test. The test will not move the control wheels if you do not remove
hydraulic power before you do this test. During this test, the control wheels will move.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
29-11-00-860-808
Title
Supply Electrical Power (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
22-11-00
EFFECTIVITY
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(Continued)
Reference
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-010
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-860-011
(2)
For the left, center and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-00-740-013
WARNING
(3)
KEEP ALL PERSONS AND EQUIPMENT CLEAR OF THE CAPTAIN©S AND
FIRST OFFICER©S CONTROL WHEELS. THIS TEST WILL MOVE THE
CONTROL WHEELS THROUGH THEIR FULL RANGE OF TRAVEL. THIS CAN
CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Use a maintenance access terminal (MAT) to do the system test of the Control Wheel
Backdrive:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Control Wheel Backdrive
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-00
EFFECTIVITY
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8.
TASK 22-11-00-730-807
Rudder Pedal Backdrive - System Test
A.
B.
General
(1) This is a test of the left and right rudder pedal backdrive actuators. The test makes sure that
the rudder pedals can move through the full range of travel with sufficient rate and torque.
(2)
This is an automatic test. The test will not move the rudder pedals if you do not remove
hydraulic power before you do this test. During this test, the rudder pedals will move.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
29-11-00-860-808
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-013
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-860-014
(2)
For the left, center and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808
SUBTASK 22-11-00-740-014
WARNING
(3)
KEEP ALL PERSONS AND EQUIPMENT CLEAR OF THE CAPTAIN©S AND
FIRST OFFICER©S RUDDER PEDALS. THIS TEST WILL MOVE THE RUDDER
PEDALS THROUGH THEIR FULL RANGE OF TRAVEL. THIS CAN CAUSE
INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Use a maintenance access terminal (MAT) to do the system test of the Rudder Pedal
Backdrive:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Rudder Pedal Backdrive
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
22-11-00
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2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
9.
TASK 22-11-00-730-808
ILS Interface - System Test
A.
General
(1)
B.
This is a test of the ILS interface. This test makes sure that the interfaces to the ILS receivers
and the antenna switches are satisfactory. The test also makes sure that these functions of all
the Autopilot Flight Director Computers (AFDCs) are satisfactory:
(a)
The Localizer antenna switching function
(b)
The Glideslope antenna switching function
(c)
ILS tune inhibit function.
(2)
This is an automatic test. During this test, each AFDC will operate its ILS tune inhibit function,
localizer and glideslope switching functions to make sure that all the ILS interfaces are
satisfactory.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
C.
Location Zones
Zone
Area
212
Flight Compartment, Right
D.
Procedure
SUBTASK 22-11-00-860-016
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-015
(2)
Use a maintenance access terminal (MAT) to do the system test of the ILS Interface:
(a)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
ILS Interface
7)
CONTINUE
22-11-00
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(b)
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
TASK 22-11-00-740-801
10.
Autopilot Disconnect Warning - System Test
A.
General
(1) This is a test of the autopilot disconnect switches and their interfaces to the Autopilot Flight
Director Computers (AFDCs). The test also makes sure that the disconnect warning function
interfaces between the AFDCs and these systems are correct:
(2)
(3)
B.
(a)
The Airplane Information Management Systems (AIMS)
(b)
The Warning Electronic System (WES).
This is an interactive test. During this test, the instructions on the MAT will tell you to operate
the captain©s and first officer©s autopilot disconnect switches. When you do this test, these
indications occur:
(a)
The sound of the aural warning
(b)
The two master warning lights come on
(c)
The "AUTOPILOT DISC" EICAS message shows on the EICAS display.
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-018
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-016
(2)
Use a maintenance access terminal (MAT) to do the system test of the Autopilot Disconnect
Warning:
(a)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
22-11-00
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(b)
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Autopilot Disconnect Warning
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
Do the instructions that show on the MAT to complete the test.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
TASK 22-11-00-730-809
11.
Autopilot Flight Director System (AFDS) - System Configuration
A.
B.
General
(1) The configuration check makes sure that the AFDC has correct software. It will show a failure if
the operational program software (OPS) is not installed.
(2)
The configuration check will show the hardware part number, serial number, program pins and
software part numbers for each of the Autopilot Flight Director Computer (AFDC) installed. It
also shows the configuration data for the mode control panel.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
22-11-01-400-803
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Autopilot Flight Director Computer Software Installation
(P/B 201)
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-020
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
22-11-00
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SUBTASK 22-11-00-750-001
(2)
Use a maintenance access terminal (MAT) to do a system configuration check of the Autopilot
Flight Director System (AFDS):
NOTE: The configuration check will show a failure if the operational program software (OPS)
is not installed. The AFDC must also contain the operational program configuration
(OPC).
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
SYSTEM CONFIGURATION
4)
22 Autopilot Flight Director System
5)
CONTINUE
Make sure that these data show for the Left AFDC, Center AFDC and Right AFDC:
1)
Hardware Part Number (Supplier P/N).
2)
Serial Number (AFDC serial number).
3)
Program Pins:
a)
Ch ID L (For left AFDC only)
b)
Ch ID C (For center AFDC only)
c)
Ch ID R (For right AFDC only)
ILF 104, 105, 107, 118-199
d)
Parity
ILF ALL
4)
Software Part Numbers (Supplier P/N):
a)
Operational Program Software (OPS) Part Number.
b)
Operational Program Configuration (OPC) Part Number.
NOTE: If there is no OPC installed, then 0000-000-000-00 will show.
c)
Flight Test Data (FTD) Part Number.
NOTE: The Flight Test Data is a file that can be installed to cause specific
internal AFDC parameters to be transmitted on a dedicated 429 output
bus from the AFDC. It will not normally be used for in service flights. If
there is no FTD file installed, then this entry will not show on the MAT.
d)
(c)
If the part numbers are incorrect, do this task: Autopilot Flight Director
Computer Software Installation, TASK 22-11-01-400-803.
Make sure that these data show for the Mode Control Panel:
1)
LRU Part Number (Supplier P/N).
2)
Serial Number (Supplier P/N).
ILF 104, 105, 107, 118-199, 601, 602, 623-632
3)
Program pin:
a)
A-3 Dig Mach
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ILF 104, 105, 107, 118-199, 601, 602, 623-632 (Continued)
b)
B-3 Dig Mach
ILF ALL
(d)
Select GO BACK to remove the configuration display.
END OF TASK
TASK 22-11-00-740-802
12.
ILS Localizer Antenna Switching
A.
General
(1) The ILS Localizer Antenna Switching is not a test. It is an AFDS special function. This function
lets you select the localizer antenna or the VOR antenna for troubleshooting of the Instrument
Landing System. It has no PASSED/FAILED indication. There are no EICAS messages.
(2)
B.
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
24-22-00-860-805
45-10-00-740-808
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
C.
Location Zones
Zone
Area
212
Flight Compartment, Right
D.
Procedure
SUBTASK 22-11-00-860-022
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-017
(2)
Use a maintenance access terminal (MAT) to do the ILS Localizer Antenna Switching:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
OTHER FUNCTIONS
3)
SPECIAL FUNCTIONS
4)
22 Autopilot Flight Director System
5)
ILS Localizer Antenna Switching
6)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START FUNCTION
(c)
Do the instructions that show on the MAT to select the localizer Antenna or the VOR
antenna.
(d)
Make this selection on the MAT to put the ILS localizer antenna back to its usual
condition (localizer antenna):
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1)
STOP FUNCTION
END OF TASK
TASK 22-11-00-740-803
13.
ILS Glideslope Antenna Switching
A.
General
(1) The ILS Glideslope Antenna Switching is not a test. It is an AFDS special function. This
function lets you select the track antenna or the capture antenna for troubleshooting of the
Instrument Landing System. It has no PASSED/FAILED indication. There are no EICAS
messages.
B.
References
Reference
24-22-00-860-805
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-024
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-018
(2)
Use a maintenance access terminal (MAT) to do the ILS Glideslope Antenna Switching:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
OTHER FUNCTIONS
3)
SPECIAL FUNCTIONS
4)
22 Autopilot Flight Director System
5)
ILS Glideslope Antenna Switching
6)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START FUNCTION
(c)
Do the instructions that show on the MAT to select the track antenna or the capture
antenna.
(d)
Make this selection on the MAT to put the ILS glideslope antenna back to its usual
condition (track antenna):
1)
STOP FUNCTION
END OF TASK
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TASK 22-11-00-710-801
14.
Autopilot Disengage Bar - Operational Test
A.
References
Reference
24-22-00-860-805
34-21-00-820-801
B.
Location Zones
Zone
211
212
C.
Title
Supply Electrical Power (P/B 201)
Air Data Inertial Reference Unit - Alignment (P/B 201)
Area
Flight Compartment, Left
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-026
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-980-001
(2)
Do these steps to engage the autopilot:
(a)
Make sure that the airplane is on the ground.
ILF 104, 105, 107, 118-199, 601, 602, 623-632; ILF 650-799 POST SB 777-22A0024
(b)
Make sure that the flaps are retracted.
ILF ALL
(c)
Do this task: Air Data Inertial Reference Unit - Alignment, TASK 34-21-00-820-801.
(d)
Push the autopilot (A/P) engage switch on the mode control panel (MCP) to engage the
autopilot.
SUBTASK 22-11-00-980-002
(3)
Do these steps to disengage the autopilot:
(a)
Put the autopilot disengage bar (on the MCP) in the down position to disengage the
autopilot.
(b)
Make sure that these indications occur:
1)
The sound of the autopilot disconnect aural warning
2)
The two master warning lights come on
3)
The "AUTOPILOT DISC" EICAS message shows on the EICAS display.
(c)
Push the captain©s or first officer©s autopilot disconnect switch (on the control wheel) to
stop the autopilot disconnect aural warning.
(d)
Make sure that the two master warning lights go off.
(e)
Make sure that the "AUTOPILOT DISC" EICAS message does not show on the EICAS
display.
SUBTASK 22-11-00-740-019
(4)
Look at the Line Maintenance, Existing Flight Deck Effects display on the MAT for the
22-13404 maintenance message.
(a)
Make sure that the maintenance message shows ACTIVE on the MAT.
(b)
Select the maintenance message and select MAINTENANCE MESSAGE DATA to make
sure that all AFDCs show the fault.
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(c)
Put the autopilot disengage bar in the up position.
1)
(d)
Make sure that the MAT shows NOT ACTIVE for the maintenance message.
Set the ADIRU switch on the overhead panel (P5) to OFF.
END OF TASK
15.
TASK 22-11-00-710-802
Autopilot Disconnect Switches - Operational Test
A.
General
(1) A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
B.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-028
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-020
(2)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the Autopilot
Disconnect Switch:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
Autopilot Disconnect Switch
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
Do the instructions that show on the MAT to complete the test.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-00
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TASK 22-11-00-710-803
16.
TO/GA Switches - Operational Test
NOTE: This procedure is a scheduled maintenance task.
A.
General
(1) A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
B.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Location Zones
Zone
212
D.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Right
Procedure
SUBTASK 22-11-00-860-030
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-00-740-021
(2)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the TO/GA
Switch:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
TO/GA Switch
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
Do the instructions that show on the MAT to complete the test.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-00
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AUTOPILOT FLIGHT DIRECTOR COMPUTER - MAINTENANCE PRACTICES
1.
TASK 22-11-01-400-803
Autopilot Flight Director Computer Software Installation
A.
General
(1) This procedure tells you how to install software in the Autopilot Flight Director Computer
(AFDC). The AFDC must contain these pieces of software:
(a)
The names of the two software parts loaded into each AFDC follow:
AFDC Operational Program Software (OPS)
REF: AIPC 46-00-00-22D.
AFDC Operational Program Configuration (OPC)
REF: AIPC 46-00-00-22C.
Using the names, the two specific software part numbers for an aircraft can be identified
in the Illustrated Parts Catalog (IPC).
(2)
You can install the software in any sequence, but it is best to install the OPS before you install
the OPC.
(3)
To read about the conditions and times necessary for software installation, do this task:
On-Airplane Software Installation, TASK 20-15-11-400-801.
(4)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
(5)
If you do not know if the AFDC needs new software, you can first do the software configuration
check. It will save time if you only install software when the software is missing or the part
number is incorrect. You can find the software configuration check in this task: Autopilot Flight
Director Computer Installation, TASK 22-11-01-400-801.
ILF 626-632, 650-799; ILF 601, 602, 623-625 POST SB 777-45-0015
(6)
You can use the Ground Support Equipment (GSE)-Laptop, maintenance device, SPL-5704,
as an alternative to the Portable Maintenance Access Terminal (PMAT) in this task.
NOTE: The GSE-Laptop and the PMAT are equivalent for all of the PMAT functions that you
will use in this task.
ILF ALL
(7)
You can install the software from disks, the Maintenance Access Terminal (MAT) hard drive or
the PMAT hard drive (if available). It is recommended that you install software from the MAT or
PMAT hard drive. To install new software on the MAT or PMAT hard drive, do this task: How to
Add Software to the Hard Drive, TASK 45-10-00-860-812.
NOTE: When new software is installed in the AFDC, the load process first erases the old
software and then installs the new software. If you install software directly to the AFDC
from a faulty disk, the load process may erase the old software and then fail, so that
no software is installed. If you install a faulty disk to the MAT or PMAT hard drive, the
load may fail, but you will not erase the software from the AFDC.
(a)
It is recommended that you remove old software part numbers from the MAT or PMAT
hard drive after new software is installed. To remove software from the hard drive, do this
task: How to Remove Software from the Hard Drive, TASK 45-10-00-860-813.
22-11-01
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(8)
B.
Before you can install software, the airplane must be on the ground with the engines off, and
the autopilot must not be engaged.
References
Reference
20-15-11-400-801
22-11-01-400-801
24-22-00-860-805
45-10-00-740-808
Title
On-Airplane Software Installation (P/B 201)
Autopilot Flight Director Computer Installation (P/B 401)
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
How to Add Software to the Hard Drive (P/B 201)
How to Remove Software from the Hard Drive (P/B 201)
Aircraft Illustrated Parts Catalog
Aircraft Illustrated Parts Catalog
45-10-00-860-812
45-10-00-860-813
AIPC 46-00-00-22C
AIPC 46-00-00-22D
C.
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
SPL-5704
Description
Device - Maintenance
777-300, -300ER
Part #: G45004-1 Supplier: 81205
Part #: G45004-2 Supplier: 81205
Part #: G45004-3 Supplier: 81205
Opt Part #: G45002-20 Supplier: 81205
Opt Part #: G45002-25 Supplier: 81205
Opt Part #: G45002-29 Supplier: 81205
Opt Part #: J45001-1 Supplier: 81205
Opt Part #: J45003-1 Supplier: 81205
D.
Location Zones
Zone
Area
212
Flight Compartment, Right
E.
Procedure
SUBTASK 22-11-01-860-012
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-01-420-003
(2)
Use a maintenance access terminal (MAT or PMAT) to install software in the AFDC:
NOTE: Make sure you know the correct software part number for the AFDC before you select
the software part number on the display. For the AFDC to be an approved installation,
the correct software must be installed.
(a)
If the software is on a disk, put the correct disk in the disk drive.
(b)
Make these selections on the MAT:
(c)
1)
ONBOARD MAINTENANCE
2)
EXTENDED MAINTENANCE
3)
DATA LOAD
Make these selections to select the component that will receive the software:
22-11-01
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(d)
(e)
1)
SELECT DESTINATION
2)
22 Autopilot Flight Director System
3)
Autopilot Flight Director Computer (Left, Center, or Right)
4)
CONTINUE
Make these selections to select the source of the software:
1)
SELECT SOURCE
2)
Select the source of the software (if Disk Drive is the only selection, it is
automatically selected).
3)
Select the correct software part number from the display.
4)
CONTINUE
Select START to start the software installation.
NOTE: During the installation of new software for the left, center and right AFDCs, an
AFDC status message will show on the Engine Indication and Crew Alerting
System (EICAS) display. The AFDC has a built-in monitor which causes an AFDC
status message to show when an AFDC has a different software part number
from the other two. However, after the software installation for the last AFDC, no
AFDC status message will show.
(f)
When the software installation is completed, make sure the correct software part number
shows on the display.
(g)
If the software part number shows on the display, select CONTINUE to remove the
configuration display. Do not do the steps that follow.
(h)
If the software part number does not show on the display, make these selections on the
MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
SYSTEM CONFIGURATION
4)
22 Autopilot Flight Director System
5)
CONTINUE
(i)
Find Autopilot Flight Director Computer (Left, Center, or Right) on the display and make
sure that the software part numbers are correct.
(j)
Select GO BACK to remove the configuration display.
NOTE: If the other computers (left, right, center) need to have software loaded, do this
task again.
END OF TASK
22-11-01
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AUTOPILOT FLIGHT DIRECTOR COMPUTER - REMOVAL/INSTALLATION
1.
2.
General
A. This procedure has these tasks:
(1)
The removal of an autopilot flight director computer (AFDC).
(2)
The installation of an autopilot flight director computer.
(a)
The installation test has the configuration check which makes sure that the AFDC has
correct software.
(b)
The configuration check will show a failure if the operational program software (OPS) is
not installed.
B.
You can find the three AFDCs in the main equipment center. The left AFDC (M22101) is on the No. 3
shelf of the E1 electronics equipment rack (E1-3). The center AFDC (M22301) is on the No. 1 shelf
of the E4 electronics equipment rack (E4-1). The right AFDC (M22201) is on the No. 5 shelf of the
E2 electronics equipment rack (E2-5).
C.
The removal and installation tasks are the same for the left AFDC, center AFDC and right AFDC.
TASK 22-11-01-000-801
Autopilot Flight Director Computer Removal
(Figure 401)
NOTE: This procedure is a scheduled maintenance task.
A.
References
Reference
06-41-00-800-801
20-10-01-000-801
B.
Location Zones
Zone
117
118
211
212
C.
Area
Main Equipment Center, Left
Main Equipment Center, Right
Flight Compartment, Left
Flight Compartment, Right
Access Panels
Number
117AL
D.
Title
Finding an Access Door or Panel on the Fuselage (P/B 201)
E/E Box Removal (P/B 401)
Name/Location
Main Equipment Center Access Door
Removal Procedure
SUBTASK 22-11-01-860-001
(1)
Open this circuit breaker and install safety tag:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
21 C22606
AFDC WARN
SUBTASK 22-11-01-860-002
(2)
For the left AFDC;
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(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
E
9
C34429
ILS L
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
8
10
11
C34629
C22603
C22607
ILS ANT SWITCH L
AFDC-L
AFDC BACK DRIVE L
ILF ALL
F
F
F
SUBTASK 22-11-01-860-003
(3)
For the right AFDC;
(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
E
22
C34428
ILS R
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
21
24
25
C34628
C22602
C22608
ILS ANT SWITCH R
AFDC-R
AFDC BACK DRIVE R
ILF ALL
F
F
F
SUBTASK 22-11-01-860-004
(4)
For the center AFDC;
(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
24
C34630
C22604
ILS ANT SWITCH C
AFDC-C
ILF ALL
A
A
SUBTASK 22-11-01-010-001
(5)
To get to the main equipment center, open this access panel:
(TASK 06-41-00-800-801)
Number
Name/Location
117AL
Main Equipment Center Access Door
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SUBTASK 22-11-01-020-001
CAUTION
(6)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON
THE AFDC. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE AFDC.
To remove the AFDC [1], do this task: E/E Box Removal, TASK 20-10-01-000-801.
END OF TASK
22-11-01
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ELECTRONIC
EQUIPMENT
RACKS, E1,E2
A
ELECTRONIC
EQUIPMENT
RACKS, E3,E4
B
MAIN EQUIPMENT
CENTER
ACCESS DOOR,
117AL
RIGHT AUTOPILOT
FLIGHT DIRECTOR
COMPUTER (E2-5)
LEFT AUTOPILOT
LIGHT DIRECTOR
COMPUTER (E1-3)
C
FWD
C
ELECTRONIC EQUIPMENT RACKS, E1,E2
A
C36234 S0006404555_V2
Autopilot Flight Director Computer Installation
Figure 401/22-11-01-990-802 (Sheet 1 of 2)
22-11-01
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CENTER AUTOPILOT
FLIGHT DIRECTOR
COMPUTER
(E4-1)
C
FW
D
ELECTRONIC EQUIPMENT RACKS, E3, E4
B
AFDC-770
[1] AUTOPILOT FLIGHT DIRECTOR COMPUTER
C
C36305 S0006404556_V2
Autopilot Flight Director Computer Installation
Figure 401/22-11-01-990-802 (Sheet 2 of 2)
22-11-01
EFFECTIVITY
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3.
TASK 22-11-01-400-801
Autopilot Flight Director Computer Installation
(Figure 401)
NOTE: This procedure is a scheduled maintenance task.
A.
General
(1)
B.
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
06-41-00-800-801
20-10-01-400-801
22-11-01-400-803
24-22-00-860-805
45-10-00-740-808
C.
Title
Finding an Access Door or Panel on the Fuselage (P/B 201)
E/E Box Installation (P/B 401)
Autopilot Flight Director Computer Software Installation
(P/B 201)
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Expendables/Parts
AMM Item
Description
1
AFDC
AIPC Reference
AIPC Effectivity
22-11-01-01-008
22-11-01-02-005
ILF ALL
ILF 104, 105, 107,
118-199, 601, 602,
623-625
ILF 626-632, 650-799
22-11-01-02-008
D.
Location Zones
Zone
Area
117
Main Equipment Center, Left
118
Main Equipment Center, Right
211
Flight Compartment, Left
212
Flight Compartment, Right
E.
Access Panels
Number
Name/Location
117AL
Main Equipment Center Access Door
F.
Installation Procedure
SUBTASK 22-11-01-860-005
(1)
Make sure that this circuit breaker is open and has safety tag:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
21 C22606
AFDC WARN
SUBTASK 22-11-01-860-006
(2)
For the left AFDC;
22-11-01
EFFECTIVITY
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(a)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
E
9
C34429
ILS L
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
8
10
11
C34629
C22603
C22607
ILS ANT SWITCH L
AFDC-L
AFDC BACK DRIVE L
ILF ALL
F
F
F
SUBTASK 22-11-01-860-007
(3)
For the right AFDC;
(a)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
E
22
C34428
ILS R
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
21
24
25
C34628
C22602
C22608
ILS ANT SWITCH R
AFDC-R
AFDC BACK DRIVE R
ILF ALL
F
F
F
SUBTASK 22-11-01-860-008
(4)
For the center AFDC;
(a)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
24
C34630
C22604
ILS ANT SWITCH C
AFDC-C
ILF ALL
A
A
SUBTASK 22-11-01-420-001
CAUTION
(5)
DO NOT TOUCH THE CONNECTOR PINS OR OTHER CONDUCTORS ON
THE AFDC. IF YOU TOUCH THESE CONDUCTORS, ELECTROSTATIC
DISCHARGE CAN CAUSE DAMAGE TO THE AFDC.
To install the AFDC [1], do this task: E/E Box Installation, TASK 20-10-01-400-801.
22-11-01
EFFECTIVITY
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SUBTASK 22-11-01-410-001
(6)
Close this access panel:
(TASK 06-41-00-800-801)
Number
117AL
Name/Location
Main Equipment Center Access Door
SUBTASK 22-11-01-860-009
(7)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
ILF 120-199
A
9
C34430
ILS C
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
A
9
C34427
MMR C
10
21
24
C34630
C22606
C22604
ILS ANT SWITCH C
AFDC WARN
AFDC-C
C34429
ILS L
ILF ALL
A
A
A
ILF 120-199
E
9
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
9
C34426
MMR L
C34428
ILS R
ILF 120-199
E
22
ILF 104, 105, 107, 118, 119, 601, 602, 623-632, 650-799
E
22
C34425
MMR R
8
10
11
21
24
25
C34629
C22603
C22607
C34628
C22602
C22608
ILS ANT SWITCH L
AFDC-L
AFDC BACK DRIVE L
ILS ANT SWITCH R
AFDC-R
AFDC BACK DRIVE R
ILF ALL
F
F
F
F
F
F
G.
Installation Test
SUBTASK 22-11-01-860-010
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-01-750-001
(2)
Use a maintenance access terminal (MAT) to do a software configuration check of the Autopilot
Flight Director Computer (AFDC):
NOTE: The configuration check will show a failure if the operational program software (OPS)
is not installed. The AFDC must also contain the operational program configuration
(OPC).
(a)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
22-11-01
EFFECTIVITY
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3)
SYSTEM CONFIGURATION
4)
22 Autopilot Flight Director System
5)
CONTINUE
(b)
Find Autopilot Flight Director Computer (Left, Center, or Right) on the display and make
sure that the software part numbers are correct.
(c)
Select GO BACK to remove the configuration display.
SUBTASK 22-11-01-420-002
(3)
If the part numbers are incorrect, install software in the Autopilot Flight Director Computer (Left,
Center, or Right), do this task: Autopilot Flight Director Computer Software Installation,
TASK 22-11-01-400-803.
SUBTASK 22-11-01-740-001
(4)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the Autopilot
Flight Director Computer:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
Autopilot Flight Director Computer (left, center, right)
7)
CONTINUE
Do the instructions that show on the MAT and make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-01
EFFECTIVITY
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MODE CONTROL PANEL - REMOVAL/INSTALLATION
1.
General
A. This procedure has these tasks:
(1)
A removal of the Mode Control Panel (MCP).
(2)
An installation of the MCP.
(3)
A removal of a mode select switch and/or a lamp for the mode select switch.
(4)
An installation of a mode select switch and/or a lamp for the mode select switch.
B.
The MCP is in the center of the glareshield, P55, in the flight compartment.
C.
The MCP is installed on supports in the glareshield structure. Captive screws attach the MCP to the
glareshield supports. There are three electrical connectors at the rear of the MCP. An opening at the
rear of the MCP automatically connects with the equipment cooling system when the panel is
installed.
TASK 22-11-02-000-801
2.
Mode Control Panel Removal
(Figure 401)
NOTE: This procedure is a scheduled maintenance task.
A.
References
Reference
20-41-01-000-802
20-41-01-000-803
B.
Location Zones
Zone
211
212
C.
Title
Conductive Dust Cap and Connector Cover Installation
(P/B 201)
ESDS Handling for Metal Encased Unit Removal (P/B 201)
Area
Flight Compartment, Left
Flight Compartment, Right
Mode Control Panel Removal
SUBTASK 22-11-02-860-001
(1)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-860-007
(2)
On the Overhead Panel, P5, set the MASTER BRIGHT switch to off.
SUBTASK 22-11-02-860-002
(3)
On the Overhead Panel, P5, turn the outer knob of the GLARESHIELD PNL/FLOOD control
fully counterclockwise.
22-11-02
EFFECTIVITY
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SUBTASK 22-11-02-910-001
CAUTION
(4)
DO NOT TOUCH THE MCP BEFORE YOU DO THE PROCEDURE FOR
DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE.
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE MCP.
Before you touch the MCP [1], do this task: ESDS Handling for Metal Encased Unit Removal,
TASK 20-41-01-000-803.
SUBTASK 22-11-02-020-001
(5)
Remove the MCP [1]:
(a)
Loosen the four captive screws [2] on the bottom of the MCP supports in the glareshield
that attach to the MCP [1].
CAREFULLY MOVE THE MCP OUT FROM ITS SUPPORTS IN THE
GLARESHIELD TO PREVENT FORCE ON THE ELECTRICAL CABLES.
DAMAGE TO THE ELECTRICAL CABLES COULD OCCUR IF YOU PUT
TOO MUCH FORCE ON THEM.
CAUTION
(b)
Move the MCP [1] out from its supports in the glareshield until you can get access to the
electrical connectors at the rear of the MCP unit.
WARNING
BE CAREFUL WHEN YOU PUT YOUR HAND BEHIND THE MODE
CONTROL PANEL. THE SCREW HEADS ADJACENT TO THE
CONNECTOR CAN CUT YOUR HAND.
(c)
Disconnect the electrical connectors.
(d)
Remove the MCP [1] from its supports in the glareshield.
(e)
Do this task: Conductive Dust Cap and Connector Cover Installation,
TASK 20-41-01-000-802.
END OF TASK
22-11-02
EFFECTIVITY
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MODE
CONTROL
PANEL
A
GLARESHIELD
B
FLIGHT COMPARTMENT
A/T ARM
L
IAS
IAS
A/P
g
w
F/D ON
OFF
HDG
MACH
V/S
TRK
ALTITUD E
FPA
R
C LB
C ON
w
VNAV
A/T
FLCH
g
w
g
w
g
w
V/S
HDG
LNAV
g
w
OFF
5
AUTO
A/P DISENGAGE
A/P
AUTO
25
SEL
BANK
LIM IT
LOC
DOW N
g
w
HOLD
g
w
g
w
1000
VS/FPA
UP
g
w
HOLD
g
w
F/D ON
APP
g
w
OFF
MODE CONTROL PANEL
A
C38997 S0006404562_V2
Mode Control Panel Installation
Figure 401/22-11-02-990-801 (Sheet 1 of 2)
22-11-02
EFFECTIVITY
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[1] MODE CONTROL
PANEL
[2] CAPTIVE
SCREWS
GLARESHIELD
(BOTTOM VIEW)
B
C39320 S0006404563_V2
Mode Control Panel Installation
Figure 401/22-11-02-990-801 (Sheet 2 of 2)
22-11-02
EFFECTIVITY
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3.
TASK 22-11-02-400-801
Mode Control Panel Installation
(Figure 401)
NOTE: This procedure is a scheduled maintenance task.
A.
B.
C.
General
(1)
The installation test makes sure that the mode control panel is installed correctly.
(2)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
20-41-01-400-803
45-10-00-740-808
Title
ESDS Handling for Metal Encased Unit Installation (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Expendables/Parts
AMM Item
Description
1
MCP
AIPC Reference
22-11-02-10-005
22-11-02-10-450
D.
Location Zones
Zone
211
212
E.
AIPC Effectivity
ILF 104, 105, 107,
118-199, 601, 602,
625-628, 631, 650-799
ILF ALL
Area
Flight Compartment, Left
Flight Compartment, Right
Mode Control Panel Installation
SUBTASK 22-11-02-860-003
(1)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-910-002
CAUTION
(2)
DO NOT TOUCH THE MCP BEFORE YOU DO THE PROCEDURE FOR
DEVICES THAT ARE SENSITIVE TO ELECTROSTATIC DISCHARGE.
ELECTROSTATIC DISCHARGE CAN CAUSE DAMAGE TO THE MCP.
Before you touch the MCP [1], do this task: ESDS Handling for Metal Encased Unit Installation,
TASK 20-41-01-400-803.
SUBTASK 22-11-02-420-001
(3)
Install the MCP [1]:
22-11-02
EFFECTIVITY
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MAKE SURE THE COVER FOR THE AIR INLET ON THE REAR OF THE
MCP IS REMOVED. DAMAGE TO EQUIPMENT COULD OCCUR IF THIS
OPENING IS BLOCKED.
CAUTION
(a)
Make sure the cover for the air inlet on the rear of the MCP [1] is removed.
MAKE SURE THAT THE AIR OUTLET AT THE REAR OF THE MCP
SUPPORTS IN THE GLARESHIELD IS CLEAR OF BLOCKAGE.
EQUIPMENT DAMAGE COULD OCCUR IF THIS OPENING IS BLOCKED.
CAUTION
(b)
Make sure the air outlet at the rear of the supports in the glareshield is clear of blockage.
(c)
Remove the protective covers from the electrical connectors.
(d)
Examine the electrical connectors for bent or broken pins, dirt, and damage.
CAREFULLY PUT THE MCP INTO ITS SUPPORTS IN THE GLARESHIELD
TO PREVENT FORCE ON THE ELECTRICAL CABLES. DAMAGE TO
ELECTRICAL CABLES COULD OCCUR IF YOU PUT TOO MUCH FORCE
PUT ON THEM.
CAUTION
(e)
Move the MCP [1] on to its supports in the glareshield until the electrical connectors can
connect to the rear of the MCP.
WARNING
BE CAREFUL WHEN YOU PUT YOUR HAND BEHIND THE MODE
CONTROL PANEL. THE SCREW HEADS ADJACENT TO THE
CONNECTOR CAN CUT YOUR HAND.
(f)
Connect the electrical connectors.
(g)
Move the MCP [1] into its installed position.
(h)
Tighten the four captive screws [2] on the bottom of the MCP supports in the glareshield.
SUBTASK 22-11-02-860-004
(4)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
F.
Mode Control Panel Installation Test
SUBTASK 22-11-02-860-008
(1)
On the Overhead Panel, P5, set the MASTER BRIGHT switch to on.
SUBTASK 22-11-02-860-009
(2)
Turn the outer knob of the MASTER BRIGHT control switch approximately to the middle
position.
SUBTASK 22-11-02-860-010
(3)
On the Overhead Panel, P5, turn the outer knob of the GLARESHIELD PNL/FLOOD control
approximately to the middle position.
22-11-02
EFFECTIVITY
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SUBTASK 22-11-02-710-001
(4)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the MCP:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
Mode Control Panel
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
4.
TASK 22-11-02-000-802
Mode Select Switch and Lamp Removal
(Figure 402)
A.
General
(1) This task has steps to remove a mode select switch and to remove a lamp for the mode select
switch.
B.
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
COM-1611
C.
Description
Extractor - Lens Module, Mode Select Switch
777-300, -300ER
Part #: 50445 Supplier: 08719
Location Zones
Zone
211
212
Area
Flight Compartment, Left
Flight Compartment, Right
22-11-02
EFFECTIVITY
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D.
Removal Procedure
SUBTASK 22-11-02-860-011
(1)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-860-012
(2)
On the Overhead Panel, P5, set the MASTER BRIGHT switch to off.
SUBTASK 22-11-02-860-013
(3)
On the Overhead Panel, P5, turn the outer knob of the GLARESHIELD PNL/FLOOD control
fully counterclockwise.
SUBTASK 22-11-02-020-002
(4)
To remove a lamp, do these step:
(a)
Use the lamp mode control switch lens module extractor, COM-1611 (or your fingernails)
in the grooves at the sides of the lens module to pull the lens module out.
NOTE: The lens module is now held by two pins at the end of the bail plates (one on
each side).
(b)
Use the lamp mode control switch lens module extractor, COM-1611 (or your fingernails)
to remove the lens module from the bail plate if it is necessary.
(c)
To remove a lamp, pull the lamp out of the rear of the lens module.
NOTE: The top two incandescent lamps are replaceable. The bottom two LEDs are not
replaceable except for the CLB-CON lens module. For the CLB-CON lens
module, the bottom two incandescent lamps are also replaceable.
SUBTASK 22-11-02-020-003
(5)
To remove the switch, do these steps:
(a)
Turn the jackscrew counterclockwise until it stops.
NOTE: There are two jackscrews in the switch module. One is at the top and the other is
at the bottom behind the mating plate for the lens module.
(b)
Pull the switch module out from the case.
END OF TASK
22-11-02
EFFECTIVITY
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MPC FRONT PANEL
SWITCH
MODULE
SPACER
BAIL PLATES
CASE
LAMP
(4 LOCATIONS)
1
LENS
MODULE
PINS
MODE SELECT SWITCH
1
THE JACKSCREWS ARE IN THE SWITCH
MODULE. ONE IS AT THE TOP AND THE
OTHER IS AT THE BOTTOM BEHIND THE
MATING PLATE FOR THE LENS MODULE.
F36049 S0006404566_V2
Mode Select Switch Removal/Installation
Figure 402/22-11-02-990-802
22-11-02
EFFECTIVITY
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5.
TASK 22-11-02-400-802
Mode Select Switch and Lamp Installation
(Figure 402)
A.
B.
C.
General
(1)
This task has steps to install a mode select switch and to install a lamp for the mode select
switch.
(2)
The installation test makes sure that the switch-lights and the switches on the MCP operate
correctly.
(3)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808
References
Reference
24-22-00-860-805
45-10-00-740-808
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
COM-1611
D.
Description
Extractor - Lens Module, Mode Select Switch
777-300, -300ER
Part #: 50445 Supplier: 08719
Location Zones
Zone
211
212
E.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Area
Flight Compartment, Left
Flight Compartment, Right
Installation Procedure
SUBTASK 22-11-02-860-014
(1)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-420-002
(2)
To install the switch, do these steps:
(a)
Turn the jackscrews counterclockwise until the jackscrew stops before you install the
switch module.
(b)
Move the spacer to the front flange of the switch module.
22-11-02
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(c)
Push the switch module into the case.
NOTE: Put the side that has the word "TOP" in the up position.
CAUTION
(d)
DO NOT USE THE JACKSCREWS TO PULL THE SWITCH MODULE INTO
ITS POSITION. THIS CAN CAUSE DAMAGE TO THE SWITCH MODULE
AND CASE.
Push the switch module with your finger while you lightly turn the jackscrews clockwise.
1)
Continue to push the switch module and turn the jackscrews clockwise until the
jackscrews are tight.
SUBTASK 22-11-02-420-003
(3)
To install the lamp, do these steps:
(a)
Put the lamp into the rear of the lens module.
(b)
Make sure the part number of the lamp is 685 or equivalent.
SUBTASK 22-11-02-420-004
(4)
To install the lens module, do these steps:
(a)
Use the lamp mode control switch lens module extractor, COM-1611 (or your fingernails)
to install the lens module to the bail plates.
(b)
Push the lens module into the switch module.
NOTE: Make sure that the side that has the word "TOP" is in the up position.
SUBTASK 22-11-02-860-015
(5)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
F.
Installation Test
SUBTASK 22-11-02-860-016
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-02-860-017
(2)
On the Overhead Panel, P5, set the MASTER BRIGHT switch to on.
SUBTASK 22-11-02-860-018
(3)
Turn the outer knob of the MASTER BRIGHT control switch approximately to the middle
position.
SUBTASK 22-11-02-860-019
(4)
On the Overhead Panel, P5, turn the outer knob of the GLARESHIELD PNL/FLOOD control
approximately to the middle position.
SUBTASK 22-11-02-710-002
(5)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the MCP:
(a)
Make these selections on the MAT:
22-11-02
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(b)
(c)
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
SYSTEM TEST
6)
Mode Control Panel
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
Do the instructions that show on the MAT to complete the test.
1)
Visually monitor the displays on the MCP for the correct results.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
TASK 22-11-02-000-803
6.
Mode Control Panel Speed Knob, Heading Knob, Altitude Knob Removal
(Figure 403)
A.
General
(1) This task has steps to remove a Heading, Speed, or an Altitude knob.
B.
Location Zones
Zone
Area
211
Flight Compartment, Left
212
Flight Compartment, Right
C.
Removal Procedure
SUBTASK 22-11-02-860-020
(1)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-020-004
(2)
To remove the Speed Indicator Control Knob [7], do these steps:
(a)
Loosen the two Speed Control Screws [3] on the Speed Indicator Control Knob [7].
(b)
Remove the Speed Indicator Control Knob [7] by pulling on it.
22-11-02
EFFECTIVITY
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SUBTASK 22-11-02-020-005
(3)
To remove the Altitude Indicator Control Knob [6], do these steps:
(a)
Loosen the two Altitude Control Screws [2] on the Altitude Indicator Control Knob [6].
(b)
Remove the Altitude Indicator Control Knob [6] by pulling on it.
SUBTASK 22-11-02-020-006
(4)
To remove the Heading Indicator Control Knob [9], do these steps:
(a)
Loosen the two Push Button Screws [4] on the Push Button [8].
(b)
Remove the Push Button [8] by pulling on it.
(c)
Loosen the two Heading Control Screws [5] on the Heading Indicator Control Knob [9].
(d)
Remove the Heading Indicator Control Knob [9] by pulling on it.
END OF TASK
22-11-02
EFFECTIVITY
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[3]
SPEED
INDICATOR SCREW
(2 LOCATIONS)
[5]
[4]
PUSH BUTTON
HEADING SCREW
(2 LOCATIONS)
HEADING
INDICATOR SCREW
(2 LOCATIONS)
[11]
BLANK
LIMIT
SHAFT
IA
SA
RM
IA
S
F/ D
SHAFT
MAC
H
OF
F
A/ T
ON
HD
G
OFF
FL C
N
TRK
V/
S
PPA
5
AUT
O
25
BAN
K
UNI
T
HOL
D
AL
TI
TU
DE
VS/
F
DOW
N
100
UP
[7]
SPEED
INDICATOR [9]
KNOB
[8]
[2]
ALTITUDE
INDICATOR SCREW [6]
(2 LOCATIONS)
APP
0
F/ D
HEADING
INDICATOR
KNOB
PUSH
BUTTON
L OC
HOL
D
AUT
O
ON
SHAFT
OFF
[10]
ALTITUDE
RATE
ALTITUDE
INDICATOR
KNOB
U91329 S0000220297_V1
Speed Knob, Heading Knob, Altitude Knob Removal/Installation
Figure 403/22-11-02-990-803
22-11-02
EFFECTIVITY
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7.
TASK 22-11-02-400-803
Mode Control Panel Speed Knob, Heading Knob, Altitude Knob Installation
(Figure 403)
A.
General
(1) This task has steps to install a Heading, Speed or an Altitude knob.
B.
Location Zones
Zone
211
212
C.
Area
Flight Compartment, Left
Flight Compartment, Right
Installation Procedure
SUBTASK 22-11-02-860-021
(1)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-420-005
(2)
To install the Altitude Indicator Control Knob [6], do these steps:
(a)
Install the Altitude Indicator Control Knob [6] on the shaft of the Altitude Rate Switch [10].
(b)
Make sure there is a clearance of .030 +/- .010 inch between the two knobs.
(c)
Tighten the Altitude Indicator Control Knob [6] with two Altitude Control Screws [2].
(d)
Make sure to tighten the screws to 3.5 in-lbs min.
SUBTASK 22-11-02-420-006
(3)
To install the Speed Indicator Control Knob [7] do these steps:
(a)
Install the Speed Indicator Control Knob [7] onto the indicator shaft.
(b)
Make sure there is a clearance of .030 +/- .010 inch between the bottom face of the knob
and the top face of the light panel.
(c)
Tighten the Speed Indicator Control Knob [7] with two Speed Control Screws [3].
(d)
Make sure to tighten the screws to 3.5 in-lbs min.
SUBTASK 22-11-02-420-007
(4)
To install the Heading Indicator Control Knob [9], do these steps:
(a)
Align Heading Indicator Control Knob [9] with switch flats of Bank Limit Switch [11].
(b)
Push on the Heading Indicator Control Knob [9].
(c)
Tighten the Heading Indicator Control Knob [9] with two Heading Control Screws [5].
(d)
Make sure to tighten the screws to 3.5 in-lbs min.
(e)
Install Push Button [8] on shaft of Bank Limit Switch [11] so it has full travel.
(f)
Tighten with two Push Button Screws [4].
(g)
Make sure to tighten the screws to 3.5 in-lbs min.
22-11-02
EFFECTIVITY
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SUBTASK 22-11-02-420-008
(5)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
24 C22604
AFDC-C
F
10 C22603
AFDC-L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
SUBTASK 22-11-02-420-009
(6)
Do this task to test the knobs:
(a)
Rotate the knobs back and fourth.
(b)
Make sure the window change as knobs rotated.
SUBTASK 22-11-02-420-010
(7)
Put the airplane back to it usual condition.
END OF TASK
22-11-02
EFFECTIVITY
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AUTOPILOT DISCONNECT SWITCH - REMOVAL/INSTALLATION
1.
2.
General
A. This procedure has these tasks:
(1)
The removal of an autopilot disconnect switch.
(2)
The installation of an autopilot disconnect switch.
B.
You can find the two autopilot disconnect switches (S22001 and S22002) on each outboard horn of
the pilots© control wheels. The switch is a single action, multipole, button type. A switch plate holds
the switch in its position.
C.
The removal and installation tasks are the same for the two autopilot disconnect switches.
TASK 22-11-03-000-801
Autopilot Disconnect Switch Removal
(Figure 401)
A.
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
COM-1113
B.
Location Zones
Zone
211
212
C.
Description
Tool - Wire Insertion and Extraction
777-300, -300ER
Part #: M15570-20 Supplier: 00779
Area
Flight Compartment, Left
Flight Compartment, Right
Removal Procedure
SUBTASK 22-11-03-860-001
(1)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
21 C22606
AFDC WARN
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
SUBTASK 22-11-03-020-001
(2)
Remove the autopilot disconnect switch [5]:
(a)
Move the approach plate [10] until you can get access to the screw [8] and screw [9] on
the medallion [7].
(b)
Remove the screw [8] and screw [9] on the medallion [7].
22-11-03
EFFECTIVITY
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1)
Remove the medallion [7] and the approach plate [10].
NOTE: The medallion is part of the approach plate.
(c)
Remove the wire guard assembly [6].
(d)
For stabilizer trim autopilot wire connector with quick disconnect type.
1)
(e)
Disconnect the wires on the autopilot disengage switch side of the wire connectors
in the center of the control wheel.
Use (Table 401) for switch part number 721101A1-2 or (Table 402) for switch part number
SW43896-2.
NOTE: There are two equivalent switches you can use for the autopilot disconnect
function. The switches have different part numbers and some different wire
colors.
NOTE: The wires on the 721101A1-2 switch are white. The switch wire labels are
stamped onto the wires. The wires on the SW43896-2 switch each have a
different color.
NOTE: In the AIRPLANE WIRE COLOR column of the table, the second color is for the
stripe on the wire.
Table 401/22-11-03-993-802 Wire Labels and Colors for Switch 721101A1-2
SWITCH WIRE LABEL
AIRPLANE WIRE COLOR
BRN
White/Black
YEL
White/Violet
GRN
White/Orange
BKB
White/Brown
BKY
White/Green
BKA
Black/Yellow
BLU
Black/Green
BKG
Black/White
Table 402/22-11-03-993-803 Wire Labels and Colors for Switch SW43896-2
SWITCH WIRE COLOR
AIRPLANE WIRE COLOR
BROWN
White/Black
YELLOW
White/Violet
GREEN
White/Orange
BLACK
White/Brown
ORANGE
White/Green
WHITE
Black/Yellow
BLUE
Black/Green
GRAY
Black/White
1)
Use the extraction wire insertion and extraction tool, COM-1113 to disconnect the
eight wires on the autopilot disengage switch side of the wire connectors in the
center of the control wheel.
22-11-03
EFFECTIVITY
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(f)
Attach one end of the threading wire around the eight wires that connect to the autopilot
disconnect switch [5].
NOTE: For the threading wire, you can use a 30-inch length of standard wire (No. 18 to
20 gage, without insulation).
(g)
Remove the nut [1] on the outboard horn of the control wheel.
(h)
Remove the screw [2] and screws [3] on the plate [4].
1)
Remove the plate [4].
(i)
Remove the autopilot disconnect switch [5] through the plate hole.
(j)
Pull the eight wires through the control wheel horn slowly until the threading wire shows.
NOTE: Pull until approximately 3 inches of the threading wire comes out of the control
wheel horn. Do not remove the threading wire. It is necessary to use this
threading wire for the installation.
(k)
Remove the eight wires from the threading wire.
END OF TASK
22-11-03
EFFECTIVITY
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[2] SCREW
[3] SCREW
CONTROL WHEEL
A
FLIGHT COMPARTMENT
[4] PLATE
[1] NUT
[5] AUTOPILOT
DISCONNECT
SWITCH
[10] APPROACH
PLATE
[9] SCREW
[6] WIRE GUARD
ASSEMBLY
[8] SCREW
STABILIZER TRIM
AUTOPILOT WIRE
CONNECTORS
[7] MEDALLION
CONTROL WHEEL
A
C48897 S0006404573_V3
Autopilot Disconnect Switch Installation
Figure 401/22-11-03-990-801
22-11-03
EFFECTIVITY
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3.
TASK 22-11-03-400-801
Autopilot Disconnect Switch Installation
(Figure 401)
A.
General
(1) A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808
B.
References
Reference
24-22-00-860-805
45-10-00-740-808
C.
Title
Supply Electrical Power (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
COM-1113
D.
Description
Tool - Wire Insertion and Extraction
777-300, -300ER
Part #: M15570-20 Supplier: 00779
Expendables/Parts
AMM Item
Description
5
Autopilot disconnect switch
AIPC Reference
AIPC Effectivity
22-11-03-01-020
ILF 601, 602, 623-632,
650-799
ILF 104, 105, 107,
118-199
27-11-01-01-055
E.
Location Zones
Zone
211
212
F.
Area
Flight Compartment, Left
Flight Compartment, Right
Installation Procedure
SUBTASK 22-11-03-860-002
(1)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
21 C22606
AFDC WARN
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
22-11-03
EFFECTIVITY
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SUBTASK 22-11-03-420-001
(2)
Install the autopilot disconnect switch [5]:
(a)
Make sure that the threading wire is in the control wheel horn and the two ends of the
threading wire show.
(b)
Pull the eight wires through the plate [4] hole.
(c)
Attach the end of the threading wire that comes out of the control wheel horn around the
eight wires.
(d)
Pull the eight wires down through the control wheel horn with the opposite end of the
threading wire.
(e)
Put the autopilot disconnect switch [5] in its position.
1)
(f)
Install the nut [1].
Hold the plate [4] in its position.
1)
Install the screw [2] and screws [3].
(g)
Remove the threading wire from the eight wires.
(h)
For stabilizer trim autopilot wire connectors with quick disconnect.
1)
(i)
Connect the quick disconnect on the autopilot disengage switch side to the
connectors in the center of the control wheel.
For switch part number 721101A1±2 or SW43896±2.
1)
Use the insertion wire insertion and extraction tool, COM-1113 to connect the eight
wires to the wire connectors in the center of the control wheel
(Table 401),(Table 402).
NOTE: There are two equivalent switches you can use for the autopilot disconnect
function. The switches have different part numbers and some different wire
colors.
NOTE: The wires on the 721101A1-2 switch are white. The switch wire labels are
stamped onto the wires. The wires on the SW43896-2 switch each have a
different color.
NOTE: In the AIRPLANE WIRE COLOR column of the table, the second color is for
the stripe on the wire.
Table 403/22-11-03-993-804 Wire Labels and Colors for Switch 721101A1-2
SWITCH WIRE LABEL
AIRPLANE WIRE COLOR
BRN
White/Black
YEL
White/Violet
GRN
White/Orange
BKB
White/Brown
BKY
White/Green
BKA
Black/Yellow
BLU
Black/Green
BKG
Black/White
22-11-03
EFFECTIVITY
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Table 404/22-11-03-993-805 Wire Labels and Colors for Switch SW43896-2
SWITCH WIRE COLOR
AIRPLANE WIRE COLOR
BROWN
White/Black
YELLOW
White/Violet
GREEN
White/Orange
BLACK
White/Brown
ORANGE
White/Green
WHITE
Black/Yellow
BLUE
Black/Green
GRAY
Black/White
(j)
Install the wire guard assembly [6].
(k)
Put the approach plate [10] in its position.
NOTE: The medallion [7] is part of the approach plate.
1)
Install the screw [8] and screw [9].
SUBTASK 22-11-03-860-003
(3)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
A
21 C22606
AFDC WARN
A
24 C22604
AFDC-C
F
4
C22601
MCP-L
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
F
17 C22600
MCP-R
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
G.
Installation Test
SUBTASK 22-11-03-860-004
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-03-740-001
(2)
Use a maintenance access terminal (MAT) to do the LRU replacement test of the autopilot
disconnect switch:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TESTS
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
Autopilot Disconnect Switch
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
22-11-03
EFFECTIVITY
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1)
CONTINUE
2)
START TEST
(c)
Do the instructions that show on the MAT to complete the test.
(d)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(e)
If FAILED shows, refer to the applicable Maintenance Message Index in the FIM or select
the maintenance message and select MAINTENANCE MESSAGE DATA.
END OF TASK
22-11-03
EFFECTIVITY
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TAKEOFF/GO-AROUND SWITCH - REMOVAL/INSTALLATION
1.
2.
General
A. This procedure has these tasks:
(1)
The removal of a Takeoff/Go-Around Switch.
(2)
The installation of a Takeoff/Go-Around Switch.
TASK 22-11-04-000-801
Takeoff/Go-Around Switch Removal
A.
References
Reference
G1: 76-12-03-000-804-H00
RR: 76-12-03-000-803-R00
B.
Title
Takeoff and Go-Around Switch Removal (P/B 401)
Takeoff and Go-Around Switch Removal (P/B 401)
Removal Procedure
SUBTASK 22-11-04-020-001
(1)
To remove the Takeoff/Go-Around Switch, do this task: RR: Takeoff and Go-Around Switch
Removal, TASK 76-12-03-000-803-R00 or G1: Takeoff and Go-Around Switch Removal,
TASK 76-12-03-000-804-H00.
END OF TASK
3.
TASK 22-11-04-400-801
Takeoff/Go-Around Switch Installation
A.
References
Reference
G1: 76-12-03-400-804-H00
RR: 76-12-03-400-803-R00
B.
Title
Takeoff and Go-Around Switch Installation (P/B 401)
Takeoff and Go-Around Switch Installation (P/B 401)
Installation Procedure
SUBTASK 22-11-04-420-001
(1)
To install the Takeoff/Go-Around Switch, do this task: RR: Takeoff and Go-Around Switch
Installation, TASK 76-12-03-400-803-R00 or G1: Takeoff and Go-Around Switch Installation,
TASK 76-12-03-400-804-H00.
END OF TASK
22-11-04
EFFECTIVITY
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CONTROL COLUMN BACKDRIVE ACTUATOR - REMOVAL/INSTALLATION
1.
2.
General
A. This procedure has these tasks:
(1)
The removal of a control column backdrive actuator.
(2)
The installation of a control column backdrive actuator.
B.
You can get access to the control column backdrive actuators through the forward access door,
112AL. There are two control column backdrive actuators directly above the forward access door.
You can find the left control column backdrive actuator (M22102) on the left side of the area above
the forward access door. You can find the right control column backdrive actuator (M22202) on the
right side of the area above the access door.
C.
Mounting bolts attach the control column backdrive actuator to the airplane structure. The output
crank of the control column backdrive actuator attaches to a control rod. An electrical cable is also
attached to the control column backdrive actuator.
TASK 22-11-05-000-801
Control Column Backdrive Actuator Removal
(Figure 401)
A.
References
Reference
06-41-00-800-801
29-11-00-860-808
B.
Title
Finding an Access Door or Panel on the Fuselage (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
Consumable Materials
Reference
Description
G00472
Twine - Impregnated Fibrous, Lacing And
Tying
C.
Location Zones
Zone
Area
112
Area Forward of Nose Landing Gear Wheel Well
D.
Access Panels
Number
112AL
E.
Specification
MIL-T-713
Name/Location
Forward Access Door
Removal Procedure
SUBTASK 22-11-05-020-001
(1)
For the left, center, and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-05-860-011
(2)
Set all the FLT CONTROL HYD VALVE POWER TAIL switches, on the aft Overhead
Maintenance Panel P61, to the SHUT OFF positions.
SUBTASK 22-11-05-860-001
(3)
For the left control column backdrive actuator:
22-11-05
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(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
SUBTASK 22-11-05-860-002
(4)
For the right control column backdrive actuator:
(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
SUBTASK 22-11-05-860-003
(5)
Attach DO-NOT-OPERATE tags to the two control columns.
SUBTASK 22-11-05-010-001
(6)
Open this access panel, do this task:
(TASK 06-41-00-800-801)
Number
Name/Location
112AL
Forward Access Door
SUBTASK 22-11-05-020-002
(7)
Remove the control column backdrive actuator [13]:
(a)
Disconnect the electrical connector [1] from the electrical panel.
NOTE: The electrical connector on the actuator side is not a removable connector and it
should stay connected to the actuator.
(b)
Put protective covers on the electrical connector [1].
(c)
For the left control column backdrive actuator [13], do these steps to remove the
electrical cable [14]:
(d)
1)
Make a note of the sequence of the clamps in the left inboard clamp assembly [9].
2)
Remove the screw [4] and washer [3] that attach the inboard clamp [2] to the
structure.
3)
Remove the clamp [2] from the electrical cable [14].
4)
Make a note of the sequence of the clamps in the left outboard clamp
assembly [10].
5)
Identify the electrical cable [14] and clamp [2] at the left outboard clamp
assembly [10].
6)
Use a piece of twine, G00472 to temporarily attach the other cables in the left
outboard clamp assembly [10] to an adjacent structure to keep them together.
7)
Remove the screw [4] and washer [3] that attach the left outboard clamp
assembly [10] to the structure.
8)
Remove the clamp [2] from the electrical cable [14].
For the right control column backdrive actuator [13], do these steps to remove the
electrical cable [14]:
22-11-05
EFFECTIVITY
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1)
Make a note of the sequence of the clamps in the right inboard clamp
assembly [11].
2)
Remove the screw [4] and washer [3] that attach the right inboard clamp
assembly [11] to the structure.
3)
Remove the clamp [2] from the electrical cable [14].
4)
Make a note of the sequence of the clamps and spacers in the right outboard clamp
assembly [12].
5)
Identify the electrical cable [14] and clamp [2] at the right outboard clamp
assembly [12].
6)
Use a piece of twine, G00472 to temporarily attach the other cables in the right
outboard clamp assembly [12] to an adjacent structure to keep them together.
7)
Remove the screw [8], washer [3], spacer [5], spacer [6] and spacer [7] that attach
the right outboard clamp assembly [12] to the structure.
NOTE: The spacer [5], spacer [6] and spacer [7] are loose and can fall out.
8)
Remove the clamp [2] from the electrical cable [14].
(e)
Remove the bolt [15], washer [18], and nut [19] that attach the control rod [17] to the
output crank [16] of the control column backdrive actuator [13].
(f)
Remove the loose end of the control rod [17].
(g)
Hold the control column backdrive actuator [13] in its position.
(h)
Remove the mounting bolts [15], washers [20], and nuts [19] that attach the control
column backdrive actuator [13] to the mounting structure.
(i)
Remove the control column backdrive actuator [13].
END OF TASK
22-11-05
EFFECTIVITY
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LEFT AND RIGHT
CONTROL COLUMN
BACKDRIVE ACTUATORS
A
FORWARD ACCESS
DOOR, 112AL
CONTROL COLUMN
BACKDRIVE ACTUATOR
B
FORWARD
ACCESS DOOR
FW
D
AREA ABOVE THE FORWARD ACCESS DOOR
A
E10145 S0006404582_V2
Control Column Backdrive Actuator Installation
Figure 401/22-11-05-990-801 (Sheet 1 of 4)
22-11-05
EFFECTIVITY
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INBOARD
CLAMP
OUTBOARD
CLAMP
D
C
[1] ELECTRICAL
CONNECTOR
CONTROL
COLUMN
BACKDRIVE
ACTUATOR
E
FWD
LEFT CONTROL COLUMN BACKDRIVE ACTUATOR
(RIGHT CONTROL COLUMN BACKDRIVE ACTUATOR IS OPPOSITE)
B
E10148 S0006404583_V2
Control Column Backdrive Actuator Installation
Figure 401/22-11-05-990-801 (Sheet 2 of 4)
22-11-05
EFFECTIVITY
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[5] SPACER
[6] SPACER
[2] CLAMP
[7] SPACER
[2] CLAMP
[3] WASHER
[3] WASHER
[4] SCREW
[8] SCREW
[10] LEFT OUTBOARD
CLAMP ASSEMBLY
[12] RIGHT OUTBOARD
CLAMP ASSEMBLY
C
C
[2] CLAMP
[2] CLAMP
[3] WASHER
[4] SCREW
[3] WASHER
[4] SCREW
[9] LEFT INBOARD
CLAMP ASSEMBLY
[11] RIGHT INBOARD
CLAMP ASSEMBLY
D
D
E10150 S0006404584_V2
Control Column Backdrive Actuator Installation
Figure 401/22-11-05-990-801 (Sheet 3 of 4)
22-11-05
EFFECTIVITY
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[13] CONTROL
COLUMN
BACKDRIVE
ACTUATOR
[14] ELECTRICAL
CABLE
[15] BOLT
(4 LOCATIONS)
[16] OUTPUT
CRANK
[17] CONTROL
ROD
[20] WASHER
(4 LOCATIONS)
[19] NUT
(4 LOCATIONS)
[18] WASHER
(2 LOCATIONS)
[15] BOLT
(2 LOCATIONS)
FW
[19] NUT
(2 LOCATIONS)
D
CONTROL COLUMN BACKDRIVE ACTUATOR
E
E10149 S0006404585_V2
Control Column Backdrive Actuator Installation
Figure 401/22-11-05-990-801 (Sheet 4 of 4)
22-11-05
EFFECTIVITY
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3.
TASK 22-11-05-400-801
Control Column Backdrive Actuator Installation
(Figure 401)
A.
B.
General
(1)
The control column backdrive actuator test makes sure that the control column backdrive
actuator (left or right) is installed correctly. The test also makes sure that the control columns
can move through their full range of travel with sufficient rate and torque.
(2)
A maintenance access terminal is necessary for this procedure. For instructions on how to use
a maintenance access terminal, do this task: How to Use the Central Maintenance Computing
System, TASK 45-10-00-740-808.
References
Reference
06-41-00-800-801
24-22-00-860-805
29-11-00-860-808
45-10-00-740-808
C.
D.
Consumable Materials
Reference
Description
G00472
Twine - Impregnated Fibrous, Lacing And
Tying
Area
Area Forward of Nose Landing Gear Wheel Well
Flight Compartment, Left
Flight Compartment, Right
Access Panels
Number
112AL
F.
Specification
MIL-T-713
Location Zones
Zone
112
211
212
E.
Title
Finding an Access Door or Panel on the Fuselage (P/B 201)
Supply Electrical Power (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
How to Use the Central Maintenance Computing System
(P/B 201)
Name/Location
Forward Access Door
Installation Procedure
SUBTASK 22-11-05-000-001
(1)
If the power is not removed from the left, center, and right hydraulic systems, do this task: Main
Hydraulic System Power Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-05-860-012
(2)
Make sure that all the FLT CONTROL HYD VALVE POWER TAIL switches, on the aft
Overhead Maintenance Panel P61, are in the SHUT OFF positions.
SUBTASK 22-11-05-860-004
(3)
For the left control column backdrive actuator:
(a)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
22-11-05
EFFECTIVITY
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SUBTASK 22-11-05-860-005
(4)
For the right control column backdrive actuator:
(a)
Make sure that these circuit breakers are open and have safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
SUBTASK 22-11-05-860-006
(5)
Make sure that DO-NOT-OPERATE tags are on the two control columns.
SUBTASK 22-11-05-400-001
(6)
Install the control column backdrive actuator [13]:
(a)
Hold the control column backdrive actuator [13] in the correct position for the installation.
(b)
Install the mounting bolts [15], washers [20], and nuts [19] to the mounting structure of
the control column backdrive actuator [13].
(c)
Do an inspection check of the mechanical linkage of the control column backdrive
actuator [13]:
(d)
1)
Examine the control rod [17] for worn areas, bends, cracks, or corrosion.
2)
Examine the control rod [17] bearings for worn areas.
3)
If the condition of the control rod [17] is not satisfactory, replace the control rod [17]:
a)
Remove the bolt [15], washer [18] and nut [19] that attach the other end of the
control rod [17].
b)
Hold the replacement control rod [17] in its position.
c)
Install the bolt [15], washer [18] and nut [19].
Connect the control rod [17] to the output crank [16].
NOTE: Make sure that the output crank is in the down position when you connect the
control rod [17].
1)
Install the bolt [15], washer [18] and nut [19].
(e)
Remove the protective covers from the electrical connector [1].
(f)
Examine the electrical connector [1] for bent or broken pins, dirt and damage.
(g)
For the left control column backdrive actuator [13], install the electrical cable [14]:
(h)
1)
Connect the electrical connector [1].
2)
Install the inboard clamp [2] on the electrical cable [14].
3)
Put the inboard clamps and washer [3] on the screw [4] in the correct sequence.
4)
Attach the left inboard clamp assembly [9] to the structure with the screw [4].
5)
Install the outboard clamp [2] on the electrical cable [14].
6)
Put the outboard clamps and washer [3] on the screw [4] in the correct sequence.
7)
Attach the left outboard clamp assembly [10] to the structure with the screw [4].
8)
Remove the twine, G00472.
For the right control column backdrive actuator [13], install the electrical cable [14]:
1)
Connect the electrical connector [1].
2)
Install the inboard clamp [2] on the electrical cable [14].
22-11-05
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3)
Put the inboard clamps and washer [3] on the screw [4] in the correct sequence.
4)
Attach the right inboard clamp assembly [11] to the structure with the screw [4].
5)
Install the outboard clamp [2] on the electrical cable [14].
6)
Put the outboard clamps, spacer [5], spacer [6], spacer [7] and washer [3] on the
screw [4] in the correct sequence.
7)
Attach the right outboard clamp assembly [12] to the structure with the screw [8].
8)
Remove the twine, G00472.
SUBTASK 22-11-05-410-001
(7)
Close this access panel, do this task:
(TASK 06-41-00-800-801)
Number
112AL
Name/Location
Forward Access Door
SUBTASK 22-11-05-860-007
(8)
Remove the D0-NOT-OPERATE tags from the two control columns.
SUBTASK 22-11-05-860-008
(9)
For the left control column backdrive actuator:
(a)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
SUBTASK 22-11-05-860-009
(10)
For the right control column backdrive actuator:
(a)
Remove the safety tags and close these circuit breakers:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
G.
Installation Test
SUBTASK 22-11-05-860-013
(1)
Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
SUBTASK 22-11-05-860-016
(2)
Set all the FLT CONTROL HYD VALVE POWER TAIL switches, on the aft Overhead
Maintenance Panel P61, to the NORM positions.
SUBTASK 22-11-05-860-017
(3)
Make sure that the right and center stab trim cut-out switches on the control stand are in the
NORMAL position.
22-11-05
EFFECTIVITY
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SUBTASK 22-11-05-710-001
WARNING
(4)
KEEP ALL PERSONS AND EQUIPMENT CLEAR OF THE CAPTAIN©S AND
FIRST OFFICER©S CONTROL COLUMNS. THIS TEST WILL MOVE THE
CONTROL COLUMNS THROUGH THEIR FULL RANGE OF TRAVEL. THIS
CAN CAUSE INJURIES TO PERSONS AND DAMAGE TO EQUIPMENT.
Use a maintenance access terminal (MAT) to do the LRU replacement test of the left (right)
Control Column Backdrive Actuator:
(a)
(b)
Make these selections on the MAT:
1)
ONBOARD MAINTENANCE
2)
LINE MAINTENANCE
3)
GROUND TEST
4)
22 Autopilot Flight Director System
5)
LRU REPLACEMENT TEST
6)
Control Column Backdrive Actuator (left, right)
7)
CONTINUE
Do the instructions that show on the MAT and then make these selections:
1)
CONTINUE
2)
START TEST
(c)
When the test is completed, make sure that PASSED shows adjacent to TEST
CONDITION on the MAT.
(d)
If FAILED shows, refer to applicable Maintenance Message Index in the FIM or select the
maintenance message and select MAINTENANCE MESSAGE DATA.
SUBTASK 22-11-05-420-001
(5)
Put the airplane back to its usual condition.
END OF TASK
22-11-05
EFFECTIVITY
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CONTROL WHEEL BACKDRIVE ACTUATOR - REMOVAL/INSTALLATION
1.
2.
General
A. This procedure has these tasks:
(1)
The removal of a control wheel backdrive actuator.
(2)
The installation of a control wheel backdrive actuator.
B.
You can get access to the control wheel backdrive actuators through the electrical/electronics
access door, 117AL. Go forward to the area above the nose landing gear wheel well. There are two
control wheel backdrive actuators. You can find the left control wheel backdrive actuator (M22103)
on the left side of the area above the nose landing gear wheel well. You can find the right control
wheel backdrive actuator (M22203) on the right side of the area above the nose wheel landing gear
wheel well.
C.
Mounting bolts attach the control wheel backdrive actuator to the airplane structure. The output
crank of the control wheel backdrive actuator attaches to the control rod. An electrical cable is also
attached to the control wheel backdrive actuator.
TASK 22-11-06-000-801
Control Wheel Backdrive Actuator - Removal
(Figure 401)
A.
References
Reference
06-41-00-800-801
29-11-00-860-808
Title
Finding an Access Door or Panel on the Fuselage (P/B 201)
Main Hydraulic System Power Removal (P/B 201)
B.
Location Zones
Zone
Area
115
Area Outboard and Above Nose Landing Gear Wheel Well, Left
116
Area Outboard and Above Nose Landing Gear Wheel Well, Right
117
Main Equipment Center, Left
118
Main Equipment Center, Right
C.
Access Panels
Number
117AL
D.
Name/Location
Main Equipment Center Access Door
Removal Procedure
SUBTASK 22-11-06-020-001
(1)
For the left, center, and right hydraulic systems, do this task: Main Hydraulic System Power
Removal, TASK 29-11-00-860-808.
SUBTASK 22-11-06-860-011
(2)
Set all the FLT CONTROL HYD VALVE POWER WING switches, on the aft Overhead
Maintenance Panel P61, to the SHUT OFF positions.
SUBTASK 22-11-06-860-001
(3)
For the left control wheel backdrive actuator;
22-11-06
EFFECTIVITY
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(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
10 C22603
AFDC-L
F
11
C22607
AFDC BACK DRIVE L
SUBTASK 22-11-06-860-002
(4)
For the right control wheel backdrive actuator;
(a)
Open these circuit breakers and install safety tags:
Overhead Circuit Breaker Panel, P11
Row
Col Number
Name
F
24 C22602
AFDC-R
F
25 C22608
AFDC BACK DRIVE R
SUBTASK 22-11-06-860-003
(5)
Attach DO-NOT-OPERATE tags to the two control wheels.
SUBTASK 22-11-06-010-001
(6)
Open this access panel:
(TASK 06-41-00-800-801)
Number
Name/Location
117AL
Main Equipment Center Access Door
(a)
Go forward to the area above the nose wheel landing gear wheel well.
SUBTASK 22-11-06-020-002
(7)
Remove the control wheel backdrive actuator [1]:
(a)
Disconnect the electrical connector [6].
NOTE: The electrical connector on the actuator side is not a removable connector and it
should stay connected to the actuator.
(b)
Put protective covers on the electrical connector [6].
(c)
Remove the electrical cable [3]:
1)
Remove the screw [12] or screw [14], and washer [11] that attach the clamp [10] or
clamp [15] to the structure.
2)
If necessary, remove the strap [16] from the electrical cable [3] on the right
backdrive actuator [1].
3)
Remove the clamp [10] or clamp [15] from the electrical cable [3].
(d)
Remove the bolt [2] or bolt [13], washer [4], and nut [5] that attach the control rod [7] to
the output crank [8] of the control wheel backdrive actuator [1].
(e)
Remove the loose end of the control rod [7].
(f)
Hold the control wheel backdrive actuator [1] in its position.
(g)
Remove the mounting bolts [9], washers [4], and nuts [5] that attach the control wheel
backdrive actuator [1] to the mounting structure.
(h)
Remove the control wheel backdrive actuator [1].
END OF TASK
22-11-06
EFFECTIVITY
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RIGHT SIDE OF
THE WHEEL WELL
B
LEFT SIDE OF
THE WHEEL WELL
A
MAIN EQUIPMENT
CENTER ACCESS
DOOR, 117AL
LEFT CONTROL WHEEL
BACKDRIVE ACTUATOR
C
LEFT SIDE OF THE WHEEL WELL
A
C34514 S0006404590_V2
Control Wheel Backdrive Actuator Installation
Figure 401/22-11-06-990-801 (Sheet 1 of 4)
22-11-06
EFFECTIVITY
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RIGHT CONTROL WHEEL
BACKDRIVE ACTUATOR
D
FWD
RIGHT SIDE OF THE WHEEL WELL
B
C34551 S0006404591_V3
Control Wheel Backdrive Actuator Installation
Figure 401/22-11-06-990-801 (Sheet 2 of 4)
22-11-06
EFFECTIVITY
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PARKING WITH ENGINES REMOVED - MAINTENANCE PRACTICES
1.
General
KEEP THE CENTER OF GRAVITY (CG) AT THE SPECIFIED LIMITS SHOWN
IN FIGURE 201. THIS MUST BE DONE DURING ALL GROUND MOVEMENTS
AND MAINTENANCE. LOOK AT ALL UNUSUAL CONDITIONS TO MAKE SURE
THE CENTER OF GRAVITY DOES NOT MOVE TOO FAR AFT.
CAUTION
A.
When one or both engines are removed, make sure that the airplane center of gravity limitations are
in the SAFE ZONE as shown in (Figure 201).
NOTE: When it is necessary, use accepted weight and balance procedures to keep the airplane
center of gravity below the GROUND STABILITY MARGIN line.
2.
TASK 10-11-04-580-801
Park the Airplane with the Engines Removed
A.
References
Reference
10-11-01-580-804
B.
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
SPL-13522
Description
Adapter - Engine Ballast
777-300, -300ER
Part #: J10007-1 Supplier: 81205
Adapter - Engine Ballast (777 Trent 800)
777-300
Part #: J10007-3 Supplier: 81205
Ballast - Engine Weight
777-300, -300ER
Part #: J10007-5 Supplier: 81205
SPL-13524
SPL-13526
C.
Location Zones
Zone
100
200
D.
Title
Park the Airplane (Normal Parking) (P/B 201)
Area
Lower Half of Fuselage
Upper Half of Fuselage
Procedure
SUBTASK 10-11-04-840-001
ILF 104, 105, 107, 118-199
(1) Use ballast adapter, SPL-13524 and ballast, SPL-13526 to apply ballast that is necessary
during the engine removal and installation.
10-11-04
EFFECTIVITY
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ILF 601, 602, 623-632, 650-799
(2)
Use ballast adapter, SPL-13522 and ballast, SPL-13526 to apply ballast that is necessary
during the engine removal and installation.
ILF ALL
SUBTASK 10-11-04-860-001
(3)
Make sure the airplane center of gravity is below the specified GROUND STABILITY MARGIN
line (Figure 201).
SUBTASK 10-11-04-550-001
(4)
Do these steps to prepare the pylons of the aircraft for storage:
(a)
Cap and stow all fuel lines, hydraulic lines and wire bundles.
(b)
Cover exposed metal surfaces on the pylon with a moisture barrier.
(c)
Provide suitable drains in the moisture barrier to make sure water drains.
(d)
Use a desiccant in the moisture barrier to keep a low humidity around the pylon.
SUBTASK 10-11-04-580-001
(5)
Do this task: Park the Airplane (Normal Parking), TASK 10-11-01-580-804.
END OF TASK
10-11-04
EFFECTIVITY
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TIPPING OF THE 777 AIRPLANE
THE CHART BELOW SHOWS THE 777-300 TIPPING LIMITS. THE ABSOLUTE TIPPING LIMIT IS THE MLG
CENTERLINE AT B.S. 1343.7. THE GROUND STABILITY MARGIN LINE REPRESENTS
THE ABSOLUTE TIPPING LIMIT FOR FACTORS SUCH AS TOWING FORCES, RAMP SLOPE AND WIND.
BY ENSURING THAT THE AIRPLANE WEIGHT AND C.G. DURING MAINTENANCE OPERATIONS IS BELOW THIS
LINE, A TIPPING SITUATION WILL BE AVOIDED
777-300
GROUND STABILITY MARGIN (AFT GROUND LIMITS)
SHORT TERM MAINTENANCE AND ENGINE REMOVAL CONDITIONS
% MAC
66.62
1360
TIPPING (BS 1343.3)
59.43
EXTREME CAUTION ZONE
(ALLOW FOR RAMP SLOPE, WIND, AND SUBSEQUENT
REMOVAL/INSTALLATION OF HEAVY ITEMS, AND PERSONNEL
IN AIRPLANE)
1320
1 ENGINE REMOVAL
655,100 LB
1340
663,000 LB
52.25
AFT OPERATING
(BS 1297.0)
1300
45.07
BS 1292.0
BS 1280.0
1280
37.89
SAFE ZONE
FOR ONE ENGINE
REMOVAL
GROUND STABILITY MARGIN
FOR ONE ENGINE REMOVAL
CONSIDERATION PRIOR TO
ENGINE REMOVAL
1260
MTW 662,000 LB
AIRPLANE CENTER OF GRAVITY PRIOR TO ONE ENGINE REMOVAL (BODY STATION AND % MAC)
BS
30.71
23.53
1240
200
250
300
350
400
450
500
550
600
650
700
AIRPLANE GROSS WEIGHT PRIOR TO ONE ENGINE REMOVAL (THOUSAND POUNDS)
G97611 S0006399263_V3
Airplane Center of Gravity Limitations with Engine(s) Removed
Figure 201/10-11-04-990-801 (Sheet 1 of 2)
10-11-04
EFFECTIVITY
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777-300
GROUND STABILITY MARGIN (AFT GROUND LIMITS)
SHORT TERM MAINTENANCE AND ENGINE REMOVAL CONDITIONS
BS
1360
% MAC
66.62
TIPPING (BS 1343.3)
59.43
1340
EXTREME CAUTION ZONE
(ALLOW FOR RAMP SLOPE, WIND,
AND SUBSEQUENT REMOVAL/INSTALLATION
OF HEAVY ITEMS, AND PERSONNEL INAIRPLANE)
52.25
AFT OPERATING
(BS 1297.0)
1300
655,100 LB
1320
663,000 LB
45.07
BS 1292.0
GROUND STABILITY MARGIN
FOR TWO ENGINE REMOVAL
CONSIDERATION PRIOR TO
ENGINE REMOVAL
1280
37.89
BS 1280.0
SAFE ZONE
FOR TWO ENGINE
REMOVAL
2 ENGINE REMOVAL
1260
30.71
MTW 662,000 LB
AIRPLANE CENTER OF GRAVITY PRIOR TO ONE ENGINE REMOVAL (BODY STATION AND % MAC)
TIPPING OF THE 777 AIRPLANE
THE CHART BELOW SHOWS THE 777-300 TIPPING LIMITS. THE ABSOLUTE TIPPING LIMIT IS THE MLG
CENTERLINE AT B.S. 1343.7. THE GROUND STABILITY MARGIN LINE REPRESENTS
THE ABSOLUTE TIPPING LIMIT FOR FACTORS SUCH AS TOWING FORCES, RAMP SLOPE AND WIND.
BY ENSURING THAT THE AIRPLANE WEIGHT AND C.G. DURING MAINTENANCE OPERATIONS IS BELOW THIS
LINE, A TIPPING SITUATION WILL BE AVOIDED
23.53
1240
200
250
300
350
400
450
500
550
600
650
700
AIRPLANE GROSS WEIGHT PRIOR TO TWO ENGINE REMOVAL (THOUSAND POUNDS)
G97820 S0006399266_V3
Airplane Center of Gravity Limitations with Engine(s) Removed
Figure 201/10-11-04-990-801 (Sheet 2 of 2)
10-11-04
EFFECTIVITY
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CHOCK INSTALLATION
1.
General
A. This procedure has the instructions for the installation of chocks for these conditions:
B.
(1)
Winds or wind gusts to a maximum of 35 knots (40 mph) (65 km/hr).
(2)
Winds of more than 35 knots (40 mph) (65 km/hr).
This procedure does not have instructions for the installation of chocks during engine operation.
(1)
2.
For the instructions for the installation of chocks during engine operation, see this task:
RR: Procedures to Prepare the Engine for Operation, TASK 71-00-00-800-821-R00 or
G1: Engine Operation Preparation, TASK 71-00-00-800-834-H00.
TASK 10-11-05-500-801
Chock Installation in Winds or Wind Gusts to a Maximum of 35 Knots
(Figure 201)
A.
General
(1) This procedure has the instructions for the installation of chocks in winds or wind gusts to a
maximum of 35 knots (40 mph) (65 km/hr).
(a)
B.
It is not mandatory to install chocks on the tires of the nose landing gear.
References
Reference
32-00-50-040-801
C.
Title
Main Landing Gear Steering System Deactivation (P/B 201)
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
SPL-1499
D.
Description
Pin - Lock, NLG Towing Lever
777-300, -300ER
Part #: A09003-2 Supplier: 81205
Opt Part #: A09003-1 Supplier: 81205
Procedure
SUBTASK 10-11-05-480-001
(1)
If you install chocks to the nose landing gear tires, do these steps to deactivate the nose
landing gear steering:
(a)
Move the towing lever, on the forward side of the nose landing gear, to the TOW position.
NOTE: This isolates the steering system for the nose landing gear from hydraulic power.
WARNING
(b)
ONLY USE THE CORRECT PIN FOR THE AIRPLANE MODEL. IF YOU
USE AN INCORRECT PIN, THE HYDRAULIC STEERING CAN OPERATE.
THIS CAN CAUSE INJURIES TO PERSONNEL AND DAMAGE TO
EQUIPMENT.
Install the NLG towing lever pin, SPL-1499, through the towing lever to hold the lever in
the towing position.
10-11-05
EFFECTIVITY
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SUBTASK 10-11-05-480-002
WARNING
(2)
MAKE SURE THE MAIN LANDING GEAR STEERING SYSTEM IS ISOLATED
FROM HYDRAULIC POWER BEFORE YOU DO WORK NEAR THE TIRES,
WHEELS, OR BRAKES. IF YOU DO NOT DO THIS, THE AFT AXLES CAN
AUTOMATICALLY TURN. THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
Deactivate the main landing gear steering system. To deactivate it, do this task: Main Landing
Gear Steering System Deactivation, TASK 32-00-50-040-801.
SUBTASK 10-11-05-580-001
(3)
Put chocks forward and aft of the inboard (or outboard) set of tires of each main landing gear.
NOTE: It is not mandatory to install chocks on both the inboard and outboard set of tires.
(a)
If the ramp does not slope, do the steps that follow.
1)
Put the aft nose landing gear chocks approximately 2 in. (51 mm) from the tires, if
you will install chocks to the nose landing gear tires.
NOTE: When a load is added to the airplane, the tires can prevent the removal of
the chocks if you install them nearer to the tire.
2)
Put the main landing gear chocks approximately 2 in. (51 mm) from the tires.
NOTE: When a load is added to the airplane, the tires can prevent the removal of
the chocks if you install them nearer to the tire.
(b)
If the ramp slopes, do the steps that follow.
1)
Put the chocks that are down from the nose landing gear and main landing gear
tires such that they touch the tires.
2)
Put the chocks up from the nose landing gear and main landing gear tires
approximately 2 in. (51 mm) from the tires.
END OF TASK
10-11-05
EFFECTIVITY
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F
W
D
NOSE LANDING
GEAR TRUCK
1
MAIN LANDING
GEAR TRUCK
2
MAIN LANDING
GEAR TRUCK
2
INBD
INBD
LEGEND:
RECOMMENDED CHOCKS
OPTIONAL CHOCKS
1
OPTIONAL TO CHOCK NOSE LANDING GEAR TIRES.
2
CHOCK THE FORWARD AND AFT TIRES ON EITHER THE INBOARD SIDE OR THE OUTBOARD SIDE OF
EACH MAIN LANDING GEAR TRUCK.
2029652 S0000405148_V2
Chock Installation in Winds or Wind Gusts up to 35 Knots
Figure 201/10-11-05-990-801
10-11-05
EFFECTIVITY
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3.
TASK 10-11-05-500-802
Chock Installation in Winds of More than 35 Knots
(Figure 202)
A.
General
(1)
B.
C.
This procedure has the instructions for chock installation when the wind is more than 35 knots
(40 mph) (65 km/hr).
References
Reference
32-00-50-040-801
Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference
SPL-1499
D.
Title
Main Landing Gear Steering System Deactivation (P/B 201)
Description
Pin - Lock, NLG Towing Lever
777-300, -300ER
Part #: A09003-2 Supplier: 81205
Opt Part #: A09003-1 Supplier: 81205
Procedure
SUBTASK 10-11-05-860-001
(1)
Move the towing lever, on the forward side of the nose landing gear, to the TOW position.
NOTE: This isolates the steering system for the nose landing gear from hydraulic power.
SUBTASK 10-11-05-480-003
WARNING
(2)
ONLY USE THE CORRECT PIN FOR THE AIRPLANE MODEL. IF YOU USE AN
INCORRECT PIN, THE HYDRAULIC STEERING CAN OPERATE. THIS CAN
CAUSE INJURIES TO PERSONNEL AND DAMAGE TO EQUIPMENT.
Install the NLG towing lever pin, SPL-1499, through the towing lever to hold the lever in the
towing position.
SUBTASK 10-11-05-480-004
WARNING
(3)
MAKE SURE THE MAIN LANDING GEAR STEERING SYSTEM IS ISOLATED
FROM HYDRAULIC POWER BEFORE YOU DO WORK NEAR THE TIRES,
WHEELS, OR BRAKES. IF YOU DO NOT DO THIS, THE AFT AXLES CAN
AUTOMATICALLY TURN. THIS CAN CAUSE INJURIES TO PERSONS AND
DAMAGE TO EQUIPMENT.
Deactivate the main landing gear steering system. To deactivate it, do this task: Main Landing
Gear Steering System Deactivation, TASK 32-00-50-040-801.
SUBTASK 10-11-05-580-002
(4)
Do these steps when the wind will be more than 35 knots (40 mph) (65 km/hr).
(a)
Put chocks forward and aft of the inboard and outboard set of tires on each main landing
gear.
1)
If the ramp does not slope, do the steps that follow.
10-11-05
EFFECTIVITY
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a)
Put the main landing gear chocks approximately 2 in. (51 mm) from the tires.
NOTE: When a load is added to the airplane, the tires can prevent the
removal of the chocks if you install them nearer to the tire.
2)
(b)
If the ramp slopes, do the steps that follow.
a)
Put the chocks that are down from the main landing gear tires such that they
touch the tires.
b)
Put the chocks up from the main landing gear tires approximately 2 in.
(51 mm) from the tires.
Put chocks forward and aft of the tires on the nose landing gear.
1)
If the ramp does not slope, do the steps that follow.
a)
Put the nose landing gear chocks approximately 2 in. (51 mm) from the tires.
NOTE: When a load is added to the airplane, the tires can prevent the
removal of the chocks if you install them nearer to the tire.
2)
If the ramp slopes, do the steps that follow.
a)
Put the chocks that are down from the nose landing gear tires such that they
touch the tires.
b)
Put the chocks up from the nose landing gear tires approximately 2 in.
(51 mm) from the tires.
SUBTASK 10-11-05-080-001
(5)
Remove the NLG towing lever pin, SPL-1499, after the chocks are installed.
END OF TASK
10-11-05
EFFECTIVITY
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F
W
D
NOSE LANDING
GEAR TRUCK
MAIN LANDING
GEAR TRUCK
MAIN LANDING
GEAR TRUCK
INBD
INBD
2029659 S0000405149_V2
Chock Installation in Winds of More than 35 Knots
Figure 202/10-11-05-990-802
10-11-05
EFFECTIVITY
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Active Storage
1.
General
A. This procedure can be used up to 90 days of active storage.
B.
During Active Storage, aircraft systems are visited frequently for inspection, operation, engine runs,
etc. to minimize the work required to restore the airplane to flight ready status.
C.
This procedure contains these tasks:
(1)
Prepare for Active Storage
(2)
Service and Protection on 7 Day (1 Week) Cycle
(3)
Service and Protection on 14 Day (2 Week) Cycle
(4)
Service and Protection on 30 Day (1 Month) Cycle
(5)
Service and Protection on 60 Day (2 Month) Cycle
(6)
Put the Airplane Back to A Serviceable Condition after Storage
TASK 10-11-07-600-801
2.
Preparation for Active Storage
A.
General:
(1) Do this procedure to prepare the airplane for active storage.
(2)
The following airplane Active Storage preparation Quick Check table is to be used only for
reference and for a quick review of what is in the procedure:
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 201 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks, and steps
within the procedure. The table can help the mechanic understand quickly what is
necessary to put an airplane into a storage condition.
Table 201/10-11-07-993-802
ACTIVE STORAGE PREPARATION PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
• Tow or taxi the airplane into the correct position for parking
All
• Install covers on the openings, vents and scoops of the airplane
• Prepare to park the airplane to park it in the high winds if there will be high
winds.
10-11-07
EFFECTIVITY
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Table 201/10-11-07-993-802 (Continued)
ACTIVE STORAGE PREPARATION PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
• Wash the airplane
• Examine the airplane to check for corrosion, obvious damage
EXTERNAL SURFACES
(FUSELAGE, WING, HORIZONTAL
AND VERTICAL STABILIZERS)
• Check the installation and condition of all covers
• Open all structural drain holes
• Close all doors and hatches when airplane is unattended
• Remove snow if more than 8 inches accumulate
• Stow all leading edge flaps, slats, trailing edge flaps and spoilers in the
stowed position.
Do this steps:
• Check the tire pressure
• Service the struts and check for leaks
LANDING GEAR, TIRES
• Put wheel chocks forward and aft of the wheels
• Install brake/wheel/tire covers which are opaque to keep weathering to a
minimum
• Disconnect torsion link and protect exposed bearings.
Do these steps:
• Put greater than 10% fuel capacity (approximately 20%) into the fuel tanks
FUEL
• Drain water (sumps and surge tanks)
• Cover each vent opening and jettison nozzle.
Do these steps:
• Install airplane static ground
ELECTRICAL/ELECTRONIC
• Open circuit breakers
• Position necessary switches to "OFF"
• Apply electrical power to all electrical/electronic equipment for a minimum of
2 hours.
Do these steps:
FLIGHT COMPARTMENT
• Drain water from pitot and static system
• Wash and cover flight compartment windows.
Do these steps:
AIR CONDITIONING
• Operate air conditioning packs for a minimum of 5 minutes
• Close outflow valves.
AVIONICS & FLIGHT CONTROLS
Do this step:
• Put flaps/slats in Full Up position.
10-11-07
EFFECTIVITY
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Table 201/10-11-07-993-802 (Continued)
ACTIVE STORAGE PREPARATION PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
• Close window shades
• Empty all waste containers
EQUIPMENT AND FURNISHINGS
• Check galleys and toilets
• Disarm escape slides
• Open interior doors for ventilation
• Maintain relative humidity below 70%.
Do these steps:
• Drain potable water
WATER AND WASTE
• Disinfect potable water system
• Drain and flush waste storage tanks
• Deactivate toilets and sinks.
Do this step:
NITROGEN GENERATING
SYSTEM
• Cover the dedicated ram inlet and outlet.
Do these steps:
• Check for leaks
HYDRAULIC
• Service all systems
• Fill all pump gearboxes
• Cover ADU turbine exhaust ports.
B.
References
Reference
09-11-00 P/B 201
10-11-03 P/B 201
12-11-02 P/B 301
12-13-05-610-801
12-14-01-600-803
12-14-01-616-802
12-15-03 P/B 301
12-15-04-610-802
12-17-01 P/B 301
12-17-01-610-801
12-25-01-100-801
20-41-00-910-801
21-00-00-800-803
24-22-00 P/B 201
27-51-00-860-805
Title
TOWING - MAINTENANCE PRACTICES
PARKING IN HIGH WINDS - MAINTENANCE PRACTICES
FUEL SUMP - OPERATION
Add Oil to the Air-Driven Pump (ADP) Turbine Gearbox
Assembly (TGA) (P/B 301)
Potable Water System - Drain (P/B 301)
Potable Water System - Drain (P/B 301)
LANDING GEAR TIRE - SERVICING
Brake Accumulator Servicing (P/B 301)
WASTE TANK - SERVICING
Waste Tank Servicing (P/B 301)
Clean (Wet Wash) the External Surfaces of the Airplane
(P/B 301)
Static Grounding (P/B 201)
Supply Conditioned Air with a Cooling Pack (P/B 201)
AC GENERATION AND BUS CONTROL - MAINTENANCE
PRACTICES
Retract the Trailing Edge Flaps (P/B 201)
10-11-07
EFFECTIVITY
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(Continued)
Reference
27-81-00-860-805
32-11-25-200-802
34-11-00-170-802
38-10-00-600-801
51-03-01-200-801
C.
Consumable Materials
Reference
G00034
Description
Cotton Wiper - Process Cleaning Absorbent
Wiper (Cheesecloth, Gauze)
Tape - Yellow Vinyl Adhesive, Scotch Brand
No.471, 1.5 Inches (38.1 mm) Wide
G02219
D.
Title
Retract the Leading Edge Slats (P/B 201)
Main Landing Gear Shock Strut Seal Leakage Check (P/B 601)
Static and Total Air Pressure System - Servicing (P/B 301)
Potable Water System - Disinfectant (P/B 201)
Drain Valve Inspection (P/B 601)
Specification
BMS15-5 Class A
Preparation
SUBTASK 10-11-07-600-001
CAUTION
(1)
YOU MUST MAKE SURE THAT EACH LANDING GEAR TRUCK IS STRAIGHT
BEFORE YOU PARK THE AIRPLANE. IF THE TRUCKS ARE NOT STRAIGHT,
TORSIONAL LOADS CAN REMAIN AT EACH TRUCK. THIS CONDITION CAN
CAUSE A LEAK AT THE SHOCK STRUT SEAL.
Tow or taxi the airplane into the correct position for parking (PAGEBLOCK 09-11-00/201).
SUBTASK 10-11-07-550-002
(2)
Install covers on openings, vents and scoops on the airplane to keep out unwanted materials
(for example; dirt, dust, debris, ice snow, and volcanic ash).
SUBTASK 10-11-07-600-002
(3)
E.
When or where high wind conditions can exist, prepare the airplane for parking in high wind
conditions (PAGEBLOCK 10-11-03/201
Electrical/Electronic Systems Deactivation
SUBTASK 10-11-07-910-001
(1)
Ground the airplane to an approved ground (TASK 20-41-00-910-801).
SUBTASK 10-11-07-840-001
(2)
Put necessary switches in the OFF position.
SUBTASK 10-11-07-840-002
(3)
Open the circuit breakers for all electrical/electronic components that have been removed from
the airplane.
SUBTASK 10-11-07-620-001
(4)
F.
Supply the electrical power to all electrical/electronic equipment for a minimum of 2 hours
(PAGEBLOCK 24-22-00/201).
External surfaces
SUBTASK 10-11-07-160-001
(1)
Wash and dry the airplane, if necessary (TASK 12-25-01-100-801).
SUBTASK 10-11-07-210-001
(2)
Do a visual check of all external surfaces for corrosion or obvious damage.
10-11-07
EFFECTIVITY
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SUBTASK 10-11-07-211-001
(3)
Make sure all of the structural drain holes are open (TASK 51-03-01-200-801).
NOTE: An airplane removed from service can contain accumulated ice or moisture
condensation.
SUBTASK 10-11-07-620-002
(4)
Make sure that unattended doors and hatches are closed.
SUBTASK 10-11-07-610-001
(5)
Remove snow from the flight control surfaces when 8 in. (20 cm) or more has accumulated.
SUBTASK 10-11-07-620-003
G.
(6)
Retract the Leading Edge (LE) flaps to the FULL UP position (TASK 27-81-00-860-805).
(7)
Retract the Trailing Edge (TE) flaps to the FULL UP position (TASK 27-51-00-860-805).
Air Conditioning System Deactivation
SUBTASK 10-11-07-620-004
H.
(1)
Seal the external openings to the air conditioning system.
(2)
Operate air conditioning packs for a minimum of 5 minutes (TASK 21-00-00-800-803).
Equipment/Furnishings Deactivation
SUBTASK 10-11-07-840-003
(1)
Close the window shades.
SUBTASK 10-11-07-610-002
(2)
Make sure all the tray carriers and waste containers are empty and clean, do this task (Waste
Tank Servicing, TASK 12-17-01-610-801).
SUBTASK 10-11-07-210-002
(3)
Make sure the galleys and toilets are in good condition.
SUBTASK 10-11-07-020-001
(4)
Open the cabinets, closets, and interior doors to supply ventilation and to prevent mildew.
SUBTASK 10-11-07-020-002
(5)
Make sure the humidity is below 70 percent.
NOTE: If the humidity reaches 70 percent or higher, remove the seats and carpet in the flight
compartment and the passenger compartment after 30 days, or take corrective action
to reduce the humidity.
SUBTASK 10-11-07-550-001
(6)
I.
Make sure all escape slide girt bars are properly stowed in the hooks on the escape slide
packs.
Flight Compartment Deactivation
SUBTASK 10-11-07-211-002
(1)
Make sure the pitot-static systems are drained (TASK 34-11-00-170-802).
NOTE: The drains are in the lower sections 41, 42, and 46. There are 27 drains.
SUBTASK 10-11-07-160-002
(2)
Clean and cover flight compartment windows.
10-11-07
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J.
Fuel System Deactivation
SUBTASK 10-11-07-610-003
(1)
Keep sufficient fuel quantities to cover the hydraulic heat exchangers during and after the
engine run plus the additional fuel necessary to operate the engines.
SUBTASK 10-11-07-610-004
(2)
Drain all the water from the fuel tanks, the surge tanks, the stabilizer drip pan, and the boost
pumps. After 24 hours drain again (PAGEBLOCK 12-11-02/301).
SUBTASK 10-11-07-620-005
(3)
Cover each vent opening and jettison nozzle with cotton wiper, G00034 using Scotch Brand
No.471 tape, G02219. Attach red flags to each installation.
NOTE: Put covers on each vent opening with cotton wiper, G00034 to make sure insects do
not go into the vents.
K.
Hydraulic System Deactivation
SUBTASK 10-11-07-211-003
(1)
Do a check of the hydraulic system for leaks and make repairs, if necessary.
SUBTASK 10-11-07-610-005
(2)
Service the hydraulic reservoirs and accumulators (TASK 12-15-04-610-802).
SUBTASK 10-11-07-610-006
(3)
Fill the hydraulic pump gearbox pneumatic drive with oil (TASK 12-13-05-610-801).
SUBTASK 10-11-07-620-006
(4)
L.
Put a cover on the turbine exhaust port of the hydraulic pump.
Landing Gear Deactivation
SUBTASK 10-11-07-200-001
(1)
Check of shock strut inflation and check for leaks, do this task (TASK 32-11-25-200-802).
SUBTASK 10-11-07-610-007
(2)
M.
Make sure the tire pressure is not less than 30 psi (207 kPa) below the serviceable inflation
pressure (PAGEBLOCK 12-15-03/301).
Water and Waste Deactivation
SUBTASK 10-11-07-610-008
(1)
Drain the portable water system (TASK 12-14-01-600-803 or TASK 12-14-01-616-802).
SUBTASK 10-11-07-160-003
(2)
Disinfect the potable water system (TASK 38-10-00-600-801).
SUBTASK 10-11-07-610-009
(3)
Drain and flush all of the toilet tanks (PAGEBLOCK 12-17-01/301).
SUBTASK 10-11-07-210-003
(4)
N.
Make sure all of the tanks are empty (PAGEBLOCK 12-17-01/301).
Nitrogen Generating System
SUBTASK 10-11-07-840-004
(1)
Cover the dedicated ram inlet and outlet.
END OF TASK
10-11-07
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3.
TASK 10-11-07-600-802
Service and Protection on 7 Day (1 Week) Cycle
A.
General
(1) Do this procedure every 7 days during Active Storage.
(2)
The following airplane Active Storage Quick Check table is to be used only for reference and
for a quick review of what is in the procedure:
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 202 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks and subtasks
within the procedure. The table was created to help the mechanic understand quickly
what is necessary to put an airplane into a storage condition.
Table 202/10-11-07-993-803
7-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do this step:
• Check the installation and condition of all covers.
EXTERNAL SURFACES
(FUSELAGE, WING,
HORIZONTAL AND
VERTICAL STABILIZERS)
Do these steps as needed:
• Close all doors and hatches when airplane is unattended
• Remove snow if more than 8 inches accumulate
• Stow all leading edge flaps, slats, trailing edge flaps and spoilers in the stowed
position.
Do this step:
LANDING GEAR, TIRES
• Check the tire pressure
• Check the tire for flat spots.
Do this step:
• Drain water (sumps and surge tanks).
FUEL
Do these steps as needed:
• Put greater than 10% fuel capacity (approximately 20%) into the fuel tanks.
Do this step:
ELECTRICAL/ELECTRONIC
• Apply electrical power to all electrical/electronic equipment for a minimum of 2
hours.
Do these steps:
AIR CONDITIONING
• Operate air conditioning packs for a minimum of 5 minutes.
Do these steps as needed:
• Close the outflow valves.
AVIONICS & FLIGHT
CONTROLS
Do these steps as needed:
• Put flaps/slats in full up position.
10-11-07
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B.
References
Reference
05-51-54-210-801
09-11-04-580-801
12-11-02 P/B 301
12-15-03 P/B 301
21-00-00-800-803
21-31-00
24-22-00 P/B 201
27-51-00 P/B 201
27-51-00-860-805
27-81-00 P/B 201
27-81-00-860-805
32-45-04-700-801
C.
Title
Flat Spotted Tire Conditional Inspection (P/B 201)
Tow the Airplane With Flat Tire(s) (P/B 201)
FUEL SUMP - OPERATION
LANDING GEAR TIRE - SERVICING
Supply Conditioned Air with a Cooling Pack (P/B 201)
CABIN PRESSURE CONTROL SYSTEM
AC GENERATION AND BUS CONTROL - MAINTENANCE
PRACTICES
TRAILING EDGE FLAP SYSTEM - MAINTENANCE
PRACTICES
Retract the Trailing Edge Flaps (P/B 201)
LEADING EDGE SLAT SYSTEM - MAINTENANCE
PRACTICES
Retract the Leading Edge Slats (P/B 201)
Tires Inspection (P/B 601)
External Surfaces
SUBTASK 10-11-07-610-010
(1)
Make sure all protective coverings are installed correctly. Reinstall the protective coverings
where required.
SUBTASK 10-11-07-610-011
(2)
D.
Do these steps if they are necessary:
(a)
Make sure to close all doors and hatches when airplane is unattended.
(b)
Remove snow if there is more than 8 inches accumulate.
(c)
Stow all leading edge flaps, slats, trailing edge flaps and spoilers in the stowed position
(PAGEBLOCK 27-51-00/201, PAGEBLOCK 27-81-00/201).
Keep The Landing Gear Serviceable
SUBTASK 10-11-07-211-004
(1)
Check the tire for flat spots (TASK 32-45-04-700-801).
(a)
Rotate the tires or tow the airplane a short distance (TASK 09-11-04-580-801).
1)
If there are flat spots on the tires, then find the cause (TASK 05-51-54-210-801).
SUBTASK 10-11-07-620-007
(2)
E.
Make sure the tire pressure is not less than 15 psi (103 kPa) below the serviceable inflation
pressure (PAGEBLOCK 12-15-03/301).
Fuel
SUBTASK 10-11-07-610-012
(1)
Drain all the water from the fuel tanks, the surge tanks, the stabilizer drip pan, and the boost
pumps (PAGEBLOCK 12-11-02/301).
SUBTASK 10-11-07-610-013
(2)
Do this step if it is necessary:
(a)
Keep sufficient fuel quantities to cover the hydraulic heat exchangers during and after the
engine run plus the additional fuel necessary to operate the engines.
10-11-07
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F.
Electrical/Electronic
SUBTASK 10-11-07-610-014
(1)
G.
Supply the electrical power to all electrical/electronic equipment for a minimum of 2 hours
(PAGEBLOCK 24-22-00/201).
Air Conditioning
SUBTASK 10-11-07-620-008
(1)
Operate air conditioning packs for a minimum of 5 minutes (TASK 21-00-00-800-803).
SUBTASK 10-11-07-620-009
(2)
Do this step if it is necessary:
(a)
H.
Make sure to close the outflow valves (CABIN PRESSURE CONTROL SYSTEM,
SUBJECT 21-31-00).
Avionics & Flight Controls
SUBTASK 10-11-07-620-010
(1)
Do this step as needed:
(a)
Retract the LE flaps to the FULL UP position (TASK 27-81-00-860-805).
(b)
Retract the TE flaps to the FULL UP position (TASK 27-51-00-860-805).
END OF TASK
TASK 10-11-07-600-803
4.
Service and Protection on 14 Day (2 Week) Cycle
A.
General
(1) Do this procedure every 14 days during Active Storage in addition to the procedure at 7 day
intervals (TASK 10-11-07-600-802).
(2)
The following airplane Active Storage Quick Check table is to be used only for reference and
for a quick review of what is in the procedure:
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 203 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks and subtasks
within the procedure. The table was created to help the mechanic understand quickly
what is necessary to put an airplane into a storage condition.
Table 203/10-11-07-993-805
14-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
All
ABBREVIATED PROCEDURE
Do all steps from 7 day cycle task.
10-11-07
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Table 203/10-11-07-993-805 (Continued)
14-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
• Wash the airplane
• Examine the airplane to check for corrosion, obvious damage
EXTERNAL SURFACES
(FUSELAGE, WING,
HORIZONTAL AND
VERTICAL STABILIZERS)
• Open all structural drain holes
Do these steps as needed:
• Close all doors and hatches when airplane is unattended
• Remove snow if more than 8 inches accumulate
• Stow all leading edge flaps, slats, trailing edge flaps and spoilers in the stowed
position
Do this step:
LANDING GEAR, TIRES
• Service the struts and check for leaks
FUEL
Do this step as needed:
• Put greater than 10% fuel capacity (approximately 20%) into the fuel tanks
ELECTRICAL/ELECTRONIC
AIR CONDITIONING
Do this step:
• Make sure that battery is fully charged.
Do this step as needed:
• Close outflow valves
Do this step:
AVIONICS & FLIGHT
CONTROLS
• Power-up all avionics and move all flight control surfaces
Do this step as needed:
• Put flaps/slats in full up position
B.
References
Reference
12-25-01-100-801
21-31-00
27-51-00-860-804
27-51-00-860-805
27-81-00-860-804
27-81-00-860-805
51-03-01-200-801
C.
Title
Clean (Wet Wash) the External Surfaces of the Airplane
(P/B 301)
CABIN PRESSURE CONTROL SYSTEM
Extend the Trailing Edge Flaps (P/B 201)
Retract the Trailing Edge Flaps (P/B 201)
Extend the Leading Edge Slats (P/B 201)
Retract the Leading Edge Slats (P/B 201)
Drain Valve Inspection (P/B 601)
Preparation
SUBTASK 10-11-07-610-016
(1)
D.
Do this task: (Service and Protection on 7 Day (1 Week) Cycle, TASK 10-11-07-600-802).
External Surfaces
SUBTASK 10-11-07-160-004
(1)
Wash and dry the airplane if necessary (TASK 12-25-01-100-801).
10-11-07
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SUBTASK 10-11-07-210-004
(2)
Do a visual check of all external surfaces for corrosion or obvious damage.
SUBTASK 10-11-07-211-005
(3)
Make sure that all of the structural drain holes are open (TASK 51-03-01-200-801).
SUBTASK 10-11-07-610-017
(4)
E.
Do these steps, if necessary:
(a)
Make sure that unattended doors and hatches are closed.
(b)
If 8 or more inches of snow collects on the flight control surfaces, remove the snow.
Keep the landing gear serviceable
SUBTASK 10-11-07-610-018
(1)
F.
Clean and oil shock-strut and steering-cylinder pistons if they are not protected with covers.
Fuel
SUBTASK 10-11-07-610-019
(1)
Do this step, if necessary:
(a)
G.
Keep sufficient fuel quantities to cover the hydraulic heat exchangers during and after the
engine run plus the additional fuel necessary to operate the engines.
Electrical/Electronic
SUBTASK 10-11-07-200-002
(1)
H.
Make sure the primary battery is in the charged condition.
Air Conditioning
SUBTASK 10-11-07-610-020
(1)
Do this step, if necessary:
(a)
I.
Make sure you close the outflow valves (CABIN PRESSURE CONTROL SYSTEM,
SUBJECT 21-31-00).
Avionics and Flight Control
SUBTASK 10-11-07-610-021
(1)
Supply the power to all Avionics systems and move all flight control surfaces.
(2)
Move the trailing edge flaps until the flaps complete three full cycles of travel.
(3)
Move the leading edge flaps until the flaps complete three full cycles of travel.
(4)
Move the stabilizer trim until you complete one full cycle of travel.
(5)
Move the rudder trim until you complete one full cycle of travel.
(6)
Move the aileron trim until you complete one full cycle of travel.
(7)
Move the elevators until you complete three full cycles of travel.
(8)
Move the rudder until you complete three full cycles of travel.
(9)
Move the ailerons until you complete three full cycles of travel.
(10)
Operate the rudder ratio changer actuators until you complete three full cycles of travel. Return
the actuators to their initial position.
(11)
Do this task to extend the Trailing Edge (TE) flaps (TASK 27-51-00-860-804).
(12)
Do this task to retract the TE flaps to the FULL UP position (TASK 27-51-00-860-805).
(13)
Do this task to extend the Leading Edge (LE) flaps (TASK 27-81-00-860-804).
10-11-07
EFFECTIVITY
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(14)
Do this task to retract the LE flaps to the FULL UP position (TASK 27-81-00-860-805).
END OF TASK
5.
TASK 10-11-07-600-804
Service and Protection on 30 Day (1 Month) Cycle
A.
General
(1)
Do this procedure every 30 days during Active Storage in addition to the procedures at 7 day
intervals (TASK 10-11-07-600-802) and 14 day intervals (TASK 10-11-07-600-803).
(2)
The following airplane Active Storage Quick Check table is to be used only for reference and
for a quick review of what is in the procedure:
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 204 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks and subtasks
within the procedure. The table was created to help the mechanic understand quickly
what is necessary to put an airplane into a storage condition.
Table 204/10-11-07-993-806
30-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
All
• Do all steps from 7 day cycle task.
• Do all steps from 14 day cycle task.
EXTERNAL SURFACES
(FUSELAGE, WING,
HORIZONTAL AND
VERTICAL STABILIZERS)
Do these steps as needed:
• Close all doors and hatches when airplane is unattended
• Remove snow if more than 8 inches accumulate
• Stow all leading edge flaps, slats, trailing edge flaps and spoilers in the stowed
position
LANDING GEAR, TIRES
FUEL
Do this step:
• Lubricate the wheel bearings
Do this step as needed:
• Put greater than 10% fuel capacity (approximately 20%) into the fuel tanks
APU
Do these steps:
• Do the APU preservation
• Operate the APU
• Shutdown the APU
AIR CONDITIONING
Do this step as needed:
• Close outflow valves
10-11-07
EFFECTIVITY
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Table 204/10-11-07-993-806 (Continued)
30-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
AVIONICS & FLIGHT
CONTROLS
ABBREVIATED PROCEDURE
Do this step as needed:
• Put flaps/slats in full up position
Do these step:
• Do the engine preservation
• Operate the Engines
POWER PLANT
• Operate the AC packs
• Shutdown the Engines
• Operate the Thrust Reversers
B.
References
Reference
21-00-00-800-803
21-31-00
27-51-00-860-804
27-51-00-860-805
27-81-00-860-804
27-81-00-860-805
49-11-00-860-804
49-11-00-860-805
G1: 71-00-00-800-806-H01
G1: 71-00-00-800-837-H00
G1: 78-31-00-710-823-H00
RR: 71-00-00-800-824-R00
RR: 71-00-00-800-826-R00
RR: 78-31-00-710-813-R00
C.
Title
Supply Conditioned Air with a Cooling Pack (P/B 201)
CABIN PRESSURE CONTROL SYSTEM
Extend the Trailing Edge Flaps (P/B 201)
Retract the Trailing Edge Flaps (P/B 201)
Extend the Leading Edge Slats (P/B 201)
Retract the Leading Edge Slats (P/B 201)
APU Starting and Operation (P/B 201)
APU Usual Shutdown (P/B 201)
Engine Manual Start (P/B 201)
Usual Engine Stop (P/B 201)
Thrust Reverser - Operational Test (Engine In Operation)
(P/B 501)
Start the Engine Procedure (Manual Start) (P/B 201)
Stop the Engine Procedure (Usual Engine Stop) (P/B 201)
Thrust Reverser - Operational Test (Engine In Operation)
(P/B 501)
Preparation
SUBTASK 10-11-07-610-022
(1)
Do this task: (Service and Protection on 7 Day (1 Week) Cycle, TASK 10-11-07-600-802).
SUBTASK 10-11-07-610-023
(2)
Do this task: (Service and Protection on 14 Day (2 Week) Cycle, TASK 10-11-07-600-803).
SUBTASK 10-11-07-000-001
(3)
D.
Remove all covers, screens, taped covers, and then replace after engine run.
External Surfaces
SUBTASK 10-11-07-610-024
(1)
Do these steps as needed:
(a)
Make sure that unattended doors and hatches are closed.
(b)
Remove snow from the flight control surfaces when 8 in. (20 cm) or more has
accumulated.
10-11-07
EFFECTIVITY
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E.
Keep the landing gear serviceable
SUBTASK 10-11-07-640-001
(1)
F.
Lubricate the wheel bearings.
Fuel
SUBTASK 10-11-07-610-025
(1)
Do this step as needed:
(a)
G.
Keep sufficient fuel quantities to cover the hydraulic heat exchangers during and after the
engine run plus the additional fuel necessary to operate the engines.
APU
SUBTASK 10-11-07-610-026
(1)
H.
Do the APU preservation
(a)
Operate APU for a minimum of 5 minutes (TASK 49-11-00-860-804).
(b)
Shut down the APU (TASK 49-11-00-860-805).
Air Conditioning
SUBTASK 10-11-07-610-027
(1)
Do this step as needed:
(a)
I.
Make sure to close the outflow valves (CABIN PRESSURE CONTROL SYSTEM,
SUBJECT 21-31-00).
Avionics and Flight Control
SUBTASK 10-11-07-610-028
J.
(1)
Supply the power to all Avionics systems and move all flight control surfaces.
(2)
Move the trailing edge flaps until the flaps complete three full movements of travel.
(3)
Move the leading edge flaps until the flaps complete three full movements of travel.
(4)
Move the stabilizer trim until you complete one full movement of travel.
(5)
Move the rudder trim until you complete one full movement of travel.
(6)
Move the aileron trim until you complete one full movement of travel.
(7)
Move the elevators until you complete three full movements of travel.
(8)
Move the rudder until you complete three full movements of travel.
(9)
Move the ailerons until you complete three full movements of travel.
(10)
Operate the rudder ratio changer actuators until you complete three full strokes and put the
actuators to their initial position.
(11)
Do this task to extend the Trailing Edge (TE) flaps (TASK 27-51-00-860-804).
(12)
Do this task to retract the TE flaps to the FULL UP position (TASK 27-51-00-860-805).
(13)
Do this task to extend the Leading Edge (LE) flaps (TASK 27-81-00-860-804).
(14)
Do this task to retract the LE flaps to the FULL UP position (TASK 27-81-00-860-805).
Power Plant
SUBTASK 10-11-07-610-029
(1)
Do the engine preservation procedures:
ILF 601, 602, 623-632, 650-799
(a)
Operate each engine (G1: TASK 71-00-00-800-806-H01).
10-11-07
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ILF 104, 105, 107, 118-199
(b)
Operate each engine (RR: TASK 71-00-00-800-824-R00).
ILF ALL
(c)
Operate the Air Conditioning (A/C) packs during engine operation
(TASK 21-00-00-800-803).
(d)
Do the engine shutdown procedure (RR: TASK 71-00-00-800-826-R00 or
G1: TASK 71-00-00-800-837-H00).
ILF 601, 602, 623-632, 650-799
(2)
Operate the thrust reversers (G1: TASK 78-31-00-710-823-H00).
ILF 104, 105, 107, 118-199
(3)
Operate the thrust reversers (RR: TASK 78-31-00-710-813-R00).
ILF ALL
END OF TASK
TASK 10-11-07-600-805
6.
Service and Protection on 60 Day (2 Month) Cycle
A.
General
(1) Do this procedure every 60 days during Active Storage in addition to the procedures at 7 day
intervals (TASK 10-11-07-600-802) , 14 day intervals (TASK 10-11-07-600-803) and 30 day
intervals TASK 10-11-07-600-804
(2)
The following airplane Active Storage Quick Check table is to be used only for reference and
for a quick review of what is in the procedure:
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 205 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks and subtasks
within the procedure. The table was created to help the mechanic understand quickly
what is necessary to put an airplane into a storage condition.
Table 205/10-11-07-993-807
60-DAY ACTIVE STORAGE PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Do these steps:
• Do all steps from 7 day cycle task.
All
• Do all steps from 14 day cycle task.
• Do all steps from 30 day cycle task.
B.
Preparation
SUBTASK 10-11-07-610-030
(1)
Do this task: (Service and Protection on 7 Day (1 Week) Cycle, TASK 10-11-07-600-802).
10-11-07
EFFECTIVITY
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SUBTASK 10-11-07-610-031
(2)
Do this task: (Service and Protection on 14 Day (2 Week) Cycle, TASK 10-11-07-600-803).
SUBTASK 10-11-07-610-032
(3)
Do this task: (Service and Protection on 30 Day (1 Month) Cycle, TASK 10-11-07-600-804).
END OF TASK
7.
TASK 10-11-07-630-801
Put the Airplane Back to a Serviceable Condition After Storage
A.
General
(1) This procedure gives the steps to return the airplane to a serviceable condition after Active
Storage (AS).
(2)
The airplane Active Storage depreservation quick check table that follows is a reference or
quick review only. It shows only a summary of the many tasks in this procedure.
WARNING
(a)
THE QUICK CHECK TABLE IS NOT A SUBSTITUTE FOR FOLLOWING
THE COMPLETE PROCEDURE WHICH CONTAINS WARNINGS,
CAUTIONS, TASKS, AND DETAILED INSTRUCTIONS. FAILURE TO
FOLLOW THE COMPLETE PROCEDURE CAN RESULT IN INJURIES TO
PERSONNEL AND DAMAGE TO THE AIRPLANE AND EQUIPMENT.
Table 206 below is for a Quick Check to show what is necessary when you do the
preservation to an airplane. This data is in direct relationship with the tasks and steps
within the procedure. The table helps the mechanic understand quickly what is necessary
to put an airplane into a storage condition.
Table 206/10-11-07-993-804
ACTIVE STORAGE DEPRESERVATION PROCEDURE ± QUICK CHECK
AIRPLANE AREA
ABBREVIATED PROCEDURE
Prepare the airplane for return to service (Park the Airplane (Normal
Parking), TASK 10-11-01-580-804). *[1]
All
Do these steps:
EXTERNAL SURFACES
(FUSELAGE, WING,
HORIZONTAL AND VERTICAL
STABILIZERS)
• Examine to check for corrosion, obvious damage
• Remove all covers.
Do this step if needed:
• Remove snow if more than 8 in. (20 cm) has accumulated.
LANDING GEAR, TIRES
Do this step:
• Check tire pressures.
Do this step:
FUEL
• Test for fuel contamination and treat, if necessary.
Do these steps:
ELECTRICAL/ELECTRONIC
• Remove static ground
• Close open circuit breakers
• Position switches to “ON”.
10-11-07
EFFECTIVITY
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Table 206/10-11-07-993-804 (Continued)
ACTIVE STORAGE DEPRESERVATION PROCEDURE ± QUICK CHECK
AIRPLANE AREA
FLIGHT COMPARTMENT
AIR CONDITIONING
EQUIPMENT AND
FURNISHINGS
ABBREVIATED PROCEDURE
Do this step:
• Remove window cover.
Do this step:
• Do the de-preservation procedure to the air conditioning systems.
Do these steps:
• Service fire extinguishers
• Open shades.
Do these steps:
• Drain potable water
WATER AND WASTE
• Disinfect potable water system
• Drain and flush waste storage tanks
• Reactivate toilets and sinks.
Do these steps:
• Engine fire extinguishing systems
FIRE PROTECTION
• APU fire extinguishing systems
• Fire extinguisher bottles
• Smoke detectors.
Do these steps:
NITROGEN GENERATING
SYSTEM
• Remove cover from dedicated ram inlet and outlet
• Perform leak check
• Perform electrical and system IBIT test.
Do these steps:
• Remove the covers from the turbine exhaust ports of the air driven hydraulic
pump port
• Clean grease off all actuators
• Pressurize hydraulic system
• Check hydraulic system components
HYDRAULIC
• Hydraulic system component leak check
• Check hydraulic system low pressure warning lights
• Clean and put a protective coating on actuator rods and slide valves
• Remove ground lock pins
• Move the landing gears fully
• Service all systems
• Replace hydraulic system filters.
*[1]
Do only the steps in the procedure that follows these words: “Put the Airplane Back In Its Usual Condition for Return
to Service.”
10-11-07
EFFECTIVITY
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B.
References
Reference
05-51-28-210-801
07-11-01-580-804
07-11-01-580-805
10-11-01-580-804
12-15-03 P/B 301
12-15-04-610-802
12-15-09-610-802
20-41-00-910-801
26-10-00-710-802
26-11-00-710-801
26-14-30-740-803
26-15-00-710-801
26-22-00-730-801
28-10-00-200-801
29-11-00 P/B 201
29-11-00-710-801
29-11-00-710-802
29-11-00-710-803
29-11-00-710-804
29-11-00-730-801
29-33-00-730-801
32-00-30-480-801
32-30-01-720-801
32-30-01-720-803
32-45-01-000-801
32-45-01-400-801
32-45-02-000-801
32-45-02-400-801
38-10-00-440-801
38-32-00-420-801
47-00-00-790-801
47-00-00-910-803
G1: 71-00-00-800-806-H01
Title
Ice or Snow Conditional Inspection (P/B 201)
Lift the Airplane with Jacks (P/B 201)
Lower the Airplane Off of the Jacks (P/B 201)
Park the Airplane (Normal Parking) (P/B 201)
LANDING GEAR TIRE - SERVICING
Brake Accumulator Servicing (P/B 301)
Brake Surge Accumulator Servicing (P/B 301)
Static Grounding (P/B 201)
FIRE/OVHT Operational Test (P/B 501)
Engine Fire Detection Operational Test (P/B 501)
Overhead Flight Crew Rest Smoke Detection Operational Test
(P/B 501)
APU Fire Detection Operational Test (P/B 501)
APU Fire Extinguishing System Test (P/B 501)
Detection Test for Microbial Growth (P/B 201)
MAIN (LEFT, RIGHT, AND CENTER) HYDRAULIC SYSTEMS MAINTENANCE PRACTICES
Engine-Driven Pump (EDP) - Operational Test (P/B 501)
Air-Driven Pump (ADP) Assembly - Functional Test (P/B 501)
Center System Alternating Current Motor Pumps (ACMP) Operational Test (P/B 501)
Hydraulic Interface Module (HYDIM) - Operational Test
(P/B 501)
Left and Right System Alternating Current Motor Pumps
(ACMP) - Operational Test (P/B 501)
Hydraulic Fluid Quantity Indicating System - System Test
(P/B 501)
Landing Gear Downlock Pins Installation (P/B 201)
Main Landing Gear Extension and Retraction System Functional Test (Airplane on the Jacks) (P/B 501)
Nose Landing Gear Extension and Retraction System Functional Test (Airplane on the Jacks) (P/B 501)
Main Landing Gear Wheel and Tire Assembly Removal
(P/B 401)
Main Landing Gear Wheel and Tire Assembly Installation
(P/B 401)
Nose Landing Gear Wheel and Tire Assembly Removal
(P/B 401)
Nose Landing Gear Wheel and Tire Assembly Installation
(P/B 401)
Potable Water System - Activation (P/B 201)
Toilet Activation (P/B 201)
Leak Check of the Nitrogen Generation System (P/B 601)
Ground Operation of the Nitrogen Generation System (P/B 201)
Engine Manual Start (P/B 201)
10-11-07
EFFECTIVITY
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(Continued)
Reference
G1: 71-00-00-800-837-H00
G1: 78-31-00-710-823-H00
RR: 71-00-00-800-824-R00
RR: 71-00-00-800-826-R00
RR: 78-31-00-710-813-R00
C.
D.
Title
Usual Engine Stop (P/B 201)
Thrust Reverser - Operational Test (Engine In Operation)
(P/B 501)
Start the Engine Procedure (Manual Start) (P/B 201)
Stop the Engine Procedure (Usual Engine Stop) (P/B 201)
Thrust Reverser - Operational Test (Engine In Operation)
(P/B 501)
Consumable Materials
Reference
Description
D00054
Fluid - Hydraulic Assembly Lubricant - MCS
352B (Formerly Monsanto MCS 352B)
D00233
Grease - Aircraft, General Purpose, Wide
Temperature - Mobil 28
D00378
Grease - Aircraft, General Purpose, Wide
Temperature - Aeroshell 22
G00034
Cotton Wiper - Process Cleaning Absorbent
Wiper (Cheesecloth, Gauze)
Specification
MIL-PRF-81322
MIL-PRF-81322
BMS15-5 Class A
Preparation
SUBTASK 10-11-07-580-001
(1)
Prepare the airplane for return to service (Park the Airplane (Normal Parking),
TASK 10-11-01-580-804).
(a)
Do only the steps of that procedure that follow these words: “Put the Airplane Back In Its
Usual Condition for Return to Service.”
SUBTASK 10-11-07-630-002
(2)
E.
Prepare the fire protection systems.
(a)
Make sure that the engine fire detection system is serviceable. Do this task:
(TASK 26-11-00-710-801).
(b)
Make sure the APU fire detection system is serviceable. Do this task:
(TASK 26-15-00-710-801).
(c)
Examine the smoke detectors and air sample tubing for blockage, dust, insects or other
contamination.
(d)
Do a test of the smoke detection system. Do this task: (TASK 26-10-00-710-802).
Prepare to Operate the Airplane
SUBTASK 10-11-07-210-005
(1)
Do a general visual check of all external surfaces for corrosion or obvious damage.
SUBTASK 10-11-07-630-004
(2)
Remove the tape and covers from all of the doors, access panels and windows.
(3)
Remove the cotton wiper, G00034, red flags, and tape from all of the vent and openings.
(4)
Remove the flight compartment window covers.
SUBTASK 10-11-07-660-001
(5)
Do a snow and ice conditions inspection, if necessary (TASK 05-51-28-210-801).
10-11-07
EFFECTIVITY
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SUBTASK 10-11-07-610-033
(6)
Inflate the tires to the correct pressures (PAGEBLOCK 12-15-03/301).
(7)
If the airplane has been in Active Storage for over 60 days, examine the wheel bearing
surfaces for fretting as follows:
(a)
Jack the airplane((TASK 07-11-01-580-804).
(b)
Remove the wheels (TASK 32-45-01-000-801 or TASK 32-45-02-000-801).
1)
Inspect wheel bearings, including the bearing cups, for damage or corrosion.
2)
Apply Aeroshell 22 grease, D00378 or Mobil 28 grease, D00233 to the wheel
bearings.
(c)
Install the wheels (TASK 32-45-01-400-801 or TASK 32-45-02-400-801).
(d)
Lower the airplane and remove the jacks (TASK 07-11-01-580-805).
SUBTASK 10-11-07-210-006
(8)
If airplane has been in active storage for more than 30 days, test for microbial growth in the
fuel tanks. Do this task: (TASK 28-10-00-200-801).
SUBTASK 10-11-07-840-005
(9)
Remove the airplane static ground when airplane is prepared to be moved
(TASK 20-41-00-910-801).
SUBTASK 10-11-07-860-001
(10)
Make sure that all circuit breakers are closed.
SUBTASK 10-11-07-840-006
(11)
Set the necessary switches to the ON position.
SUBTASK 10-11-07-880-001
(12)
Open the external openings to the air conditioning system, if sealed.
SUBTASK 10-11-07-860-002
(13)
Open the window shades.
SUBTASK 10-11-07-440-001
(14)
Do the toilet and sink activation procedure (TASK 38-32-00-420-801).
SUBTASK 10-11-07-440-002
(15)
Do the portable water system activation procedure (TASK 38-10-00-440-801).
SUBTASK 10-11-07-710-001
(16)
Do the Auxiliary Power Unit (APU) fire extinguishing system operation test
(TASK 26-22-00-730-801).
SUBTASK 10-11-07-710-002
(17)
Do the engine fire and overheat detection system operation test (TASK 26-10-00-710-802).
ILF 650-799
SUBTASK 10-11-07-710-004
(18)
Do the operations test of the Overhead Flight Crew Rest (OFCR) smoke detectors
(TASK 26-14-30-740-803).
ILF ALL
SUBTASK 10-11-07-730-001
(19)
Do the Nitrogen Generating System activation procedures as follows.
(a)
Remove the covers from the dedicated ram inlet and outlet.
10-11-07
EFFECTIVITY
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(b)
Perform leak check (TASK 47-00-00-790-801).
(c)
Perform electrical and system test (TASK 47-00-00-910-803).
SUBTASK 10-11-07-630-005
(20)
Prepare hydraulic to operate the airplane:
(a)
Remove the unwanted grease from all actuators.
NOTE: Do this for grease that was applied during airplane preservation and subsequent
active storage.
(b)
Before you pressurize the airplane hydraulic systems, do the steps that follow:
MAKE SURE THAT ALL PERSONS AND EQUIPMENT ARE CLEAR
OF THE LANDING GEAR DOORS. THE QUICK MOVEMENT OF THE
DOORS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO
WARNING EQUIPMENT.
1)
Install the landing gear downlock pins (TASK 32-00-30-480-801).
2)
Make sure the landing gear control handle in the first officer's instrument panel is in
the DOWN position.
(c)
Pressurize the hydraulic systems. Do a check of the system for leaks
(PAGEBLOCK 29-11-00/201).
(d)
Do the operation tests that follow:
(e)
(f)
1)
Engine Driven Pump (EDP) operational test (TASK 29-11-00-710-801).
2)
Air Driven Pump (ADP) functional test (TASK 29-11-00-710-802).
3)
AC Motor Pump (ACMP) operational tests for left, right and center
(TASK 29-11-00-710-803) and (TASK 29-11-00-730-801).
4)
Hydraulic Interface Module (HYDIM) operational test (TASK 29-11-00-710-804).
5)
Hydraulic Fluid Quantity Indicating System (HYQIS) self test
(TASK 29-33-00-730-801).
Service the hydraulic system accumulators:
1)
Do this task: (Brake Accumulator Servicing, TASK 12-15-04-610-802).
2)
Do this task: (Brake Surge Accumulator Servicing, TASK 12-15-09-610-802).
Do a visual check of hydraulic system low pressure warning lights.
SUBTASK 10-11-07-610-034
(21)
If the airplane was stored for more than 60 days, clean and apply a layer of MCS 352B fluid,
D00054 to all of the finished surfaces on the actuator rods and the valve slides which are open
to the outside air.
SUBTASK 10-11-07-440-003
(22)
Retract and extend the landing gears:
(a)
Operate the main landing gear. Do this task: (TASK 32-30-01-720-801).
(b)
Operate the nose landing gear. Do this task: (TASK 32-30-01-720-803).
SUBTASK 10-11-07-210-007
(23)
Open engine fan, thrust reverser, and core cowl panels. Examine for fluid contamination,
corrosion, or other problems.
(a)
Clean the area if necessary.
(b)
Close, and latch the cowls correctly.
10-11-07
EFFECTIVITY
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SUBTASK 10-11-07-440-004
ILF 601, 602, 623-632, 650-799
(24)
Do this task to operate the engine (G1: TASK 71-00-00-800-806-H01).
ILF 104, 105, 107, 118-199
(25)
Do this task to operate the engine (RR: TASK 71-00-00-800-824-R00).
ILF ALL
(26)
Do this task to shutdown the engine (RR: TASK 71-00-00-800-826-R00 or
G1: TASK 71-00-00-800-837-H00).
ILF 601, 602, 623-632, 650-799
(27)
Operate the thrust reversers (G1: TASK 78-31-00-710-823-H00).
ILF 104, 105, 107, 118-199
(28) Operate the thrust reversers (RR: TASK 78-31-00-710-813-R00).
END OF TASK
10-11-07
EFFECTIVITY
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ACTIVE STORAGE
ILF
ILF
1.
ILF
General
A. This procedure contains these tasks:
ILF
(1)
Active Storage - Maintenance Practices.
ILF
(2)
Active Storage (Hot Weather) - Maintenance Practices
ILF
ILF
ILF
B.
The engine, thrust reverser and APU checks are completed each 30 day interval that the airplane is
in Active Storage. All other checks are at an interval of 7 days that the airplane is parked in Active
Storage.
ILF
C.
When in Active Storage, the airplane can be back to usual operation in 4-6 hours.
ILF
TASK 10-11-94-550-801
Active Storage - Maintenance Practices
ILF
ILF
2.
A.
General
(1) Do this task: Park the Airplane (Normal Parking), TASK 10-11-01-580-804 before you park the
aircraft in active storage.
B.
References
ILF
ILF
ILF
ILF
ILF
ILF
Reference
10-11-01-580-804
12-11-02-680-801
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
12-12-01-610-801
12-13
12-15-11 P/B 301
21-00-00-800-803
21-00-00-800-804
21-31-00-700-806-001
24-22-00-860-805
24-22-00-860-806
27-51-00-860-804
27-51-00-860-805
27-81-00-860-804
27-81-00-860-805
28-10-00-200-801
28-10-00-600-802
29-11-00-860-801
32-00-40 P/B 201
36-00-00-860-801
36-00-00-860-802
49-11-00-620-801
G1: 71-00-00-700-813-H01
Title
Park the Airplane (Normal Parking) (P/B 201)
Fuel Tank Sump Drain Valve - Water Removal/Sampling
(P/B 301)
Hydraulic Reservoir Fluid Level Check (P/B 301)
OIL SERVICING
LANDING GEAR SHOCK STRUT FLUID - SERVICING
Supply Conditioned Air with a Cooling Pack (P/B 201)
Remove Conditioned Air Supplied by a Cooling Pack (P/B 201)
Cabin Pressure Control System - System Test (P/B 501)
Supply Electrical Power (P/B 201)
Remove Electrical Power (P/B 201)
Extend the Trailing Edge Flaps (P/B 201)
Retract the Trailing Edge Flaps (P/B 201)
Extend the Leading Edge Slats (P/B 201)
Retract the Leading Edge Slats (P/B 201)
Detection Test for Microbial Growth (P/B 201)
Biocide Treatment of Fuel Tanks - Metered Injection Cart
(P/B 201)
Main Hydraulic System Pressurization (P/B 201)
LANDING GEAR GROUND DOOR RELEASE SYSTEM MAINTENANCE PRACTICES
Depressurize the Pneumatic System (P/B 201)
Pressurize the Pneumatic System (P/B 201)
APU Preservation - Mild Environment (P/B 201)
Test No. 14 - Engine Fuel Driven Actuator Test (MAT Initiated
Test) (P/B 501)
10-11-94
EFFECTIVITY
ILF 104, 105, 107, 118-199, 601, 602, 623-632
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(Continued)
Reference
G1: 71-00-00-700-814-H01
ILF
ILF
ILF
G1: 71-00-00-800-805-H01
G1: 71-00-00-800-837-H00
G1: 71-00-03-600-806-H01
RR: 71-00-00-800-823-R00
RR: 71-00-00-800-826-R00
ILF
ILF
ILF
ILF
ILF
ILF
C.
Consumable Materials
Reference
G00034
ILF
ILF
ILF
G02321
Description
Cotton Wiper - Process Cleaning Absorbent
Wiper (Cheesecloth, Gauze)
Additive, Fuel - Biobor JF
Fuel - Turbine, Aviation (Grades JP-4, JP-5,
JP-5/JP-8ST)
Tape - Vinyl
G02347
Biocide - Fuel - Kathon FP1.5
G00452
G02272
ILF
ILF
ILF
ILF
Title
Test No. 15 - Engine Air Driven Actuator Test (MAT Initiated
Test) (P/B 501)
Engine Automatic Start (P/B 201)
Usual Engine Stop (P/B 201)
Depreservation of An Installed Engine (P/B 201)
Start the Engine Procedure (Automatic Start) (P/B 201)
Stop the Engine Procedure (Usual Engine Stop) (P/B 201)
ILF
ILF
ILF
D.
Specification
BMS15-5 Class A
MIL-DTL-5624
BAC5034-4 Type VII
Class 1
Procedure
ILF
SUBTASK 10-11-94-610-001
ILF
(1)
General Servicing:
ILF
(a)
Do this task: Hydraulic Reservoir Fluid Level Check, TASK 12-12-01-610-801.
ILF
ILF
(b)
Do this task: LANDING GEAR SHOCK STRUT FLUID - SERVICING,
PAGEBLOCK 12-15-11/301.
ILF
ILF
(c)
Do this task: LANDING GEAR GROUND DOOR RELEASE SYSTEM - MAINTENANCE
PRACTICES, PAGEBLOCK 32-00-40/201
ILF
(d)
Clean the chrome of the landing gear when necessary.
ILF
(e)
Use OIL SERVICING, SECTION 12-13 to service the engine oil, IDG oil, APU oil, and
hydraulic oil when necessary between engine runs.
ILF
ILF
SUBTASK 10-11-94-580-001
ILF
(2)
Wheels:
ILF
ILF
(a)
Tow the aircraft (sufficient to turn the wheels a minimum of 2 full turns). Do this task:
Maintenance Towing, AMM Task 09-11-00-580-801.
ILF
(b)
Move all flight control surfaces through their full movement of travel:
ILF
ILF
1)
Pressurize the main hydraulic system. Do this task: Main Hydraulic System
Pressurization, TASK 29-11-00-860-801.
ILF
ILF
2)
Extend the trailing edge flaps. Do this task: Extend the Trailing Edge Flaps,
TASK 27-51-00-860-804.
ILF
ILF
3)
Retract the trailing edge flaps. Do this task: Retract the Trailing Edge Flaps,
TASK 27-51-00-860-805.
ILF
ILF
4)
Extend the leading edge slats. Do this task: Extend the Leading Edge Slats,
TASK 27-81-00-860-804.
10-11-94
EFFECTIVITY
ILF 104, 105, 107, 118-199, 601, 602, 623-632
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5)
ILF
ILF
Retract the leading edge slats. Do this task: Retract the Leading Edge Slats,
TASK 27-81-00-860-805.
ILF
SUBTASK 10-11-94-810-001
ILF
(3)
Electrical/Electronic:
ILF
(a)
Supply electrical power. Do this task: Supply Electrical Power, TASK 24-22-00-860-805.
ILF
(b)
Use the correct FIM tasks to examine possible flight deck effects (FDEs).
NOTE: 90 minutes are necessary for the batteries to charge.
ILF
(c)
ILF
ILF
Remove electrical power after 2 hours. Do this task: Remove Electrical Power,
TASK 24-22-00-860-806.
ILF
SUBTASK 10-11-94-700-001
ILF
(4)
Air Conditioning Operational Test:
(a)
ILF
ILF
Pressurize the pneumatic system. Do this task: Pressurize the Pneumatic System,
TASK 36-00-00-860-802.
NOTE: Use the engines or the APU to pressurize the pneumatic system.
ILF
ILF
ILF
(b)
Supply conditioned air with a cooling pack. Do this task: Supply Conditioned Air with a
Cooling Pack, TASK 21-00-00-800-803.
ILF
(c)
Operate the air conditioning packs for 10 minutes.
ILF
(d)
Remove conditioned air supplied by a cooling pack. Do this task: Remove Conditioned
Air Supplied by a Cooling Pack, TASK 21-00-00-800-804.
(e)
Depressurize the pneumatic system. Do this task: Depressurize the Pneumatic System,
TASK 36-00-00-860-801.
(f)
Close the outflow valves of the cabin pressure control system. Do this task: Cabin
Pressure Control System - System Test, TASK 21-31-00-700-806-001.
ILF
ILF
ILF
ILF
ILF
ILF
SUBTASK 10-11-94-670-001
ILF
(5)
Potable Water System:
ILF
ILF
NOTE: There are two procedures for the potable water system. You can do the most
applicable procedure.
ILF
(a)
Procedure 1:
1)
ILF
On the first day that the aircraft is in storage:
ILF
a)
Remove the water filters.
ILF
b)
Disinfect the potable water. This is at an interval of 21 days.
NOTE: For procedure 1, use the 21 day interval on this index.
ILF
2)
ILF
ILF
ILF
(b)
Install new water filters when the aircraft is out of storage.
Procedure 2:
1)
On the first day that the aircraft is in storage:
ILF
a)
Remove the water filters.
ILF
b)
Fully drain the potable water.
ILF
ILF
2)
Install new water filters when the aircraft is out of storage.
NOTE: The water is serviced in the preflight servicing.
10-11-94
EFFECTIVITY
ILF 104, 105, 107, 118-199, 601, 602, 623-632
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AIRCRAFT MAINTENANCE MANUAL
ILF
SUBTASK 10-11-94-620-001
WARNING
DO NOT BREATHE FUMES FROM THE BIOCIDE FUEL ADDITIVE, OR
TOUCH IT. READ THE MATERIAL SAFETY DATA SHEET (MSDS) FROM THE
MANUFACTURER OF THE ADDITIVE. THE ADDITIVE CAN CAUSE INJURIES
TO PERSONNEL, AND HEALTH PROBLEMS.
CAUTION
DO NOT ADD MORE THAN THE MAXIMUM CONCENTRATION OF BIOCIDE.
IF THE BIOCIDE CONCENTRATION IS HIGHER THAN THE MAXIMUM LIMIT,
DAMAGE TO THE ENGINES CAN OCCUR.
ILF
ILF
ILF
ILF
ILF
ILF
ILF
ILF
(6)
Fuel System:
(a)
ILF
Fill or keep all of the wing fuel tanks to more than 10% of the capacity.
1)
ILF
ILF
Make sure that there is biocide in the fuel. Do this task: Biocide Treatment of Fuel
Tanks - Metered Injection Cart, TASK 28-10-00-600-802.
ILF
ILF
ILF
ILF
NOTE: The fuel must contain 270 parts per million by weight of Biobor JF additive,
G00452, or 100 parts per million by volume of Kathon FP1.5 biocide,
G02347. The approved procedure to mix the additive is by metered
injection into fuel flow.
ILF
NOTE: Military fuels (fuel, G02272, fuel, G02272 and fuel, G02272) contain Biobor
JF additive, G00452 additive and no additional Biobor JF additive, G00452
is required.
ILF
ILF
(b)
ILF
ILF
Drain all water that collects in the sumps of the fuel and the surge tanks. Do this task:
Fuel Tank Sump Drain Valve - Water Removal/Sampling, TASK 12-11-02-680-801.
NOTE: After 24 hours drain the water again. This will prevent corrosion in the areas
where water collects.
ILF
ILF
(c)
ILF
ILF
Cover each fuel vent opening with cotton wiper, G00034 and use tape, G02321. Put
covers on each vent with cheesecloth to make sure that insects do not go into the vents.
1)
ILF
(d)
ILF
Attach red flags to each installation.
Look for signs of fuel leakage in the areas that follow:
NOTE: A maximum of ten drops of fuel (while in storage) during a 24 hour period is
permitted.
ILF
ILF
ILF
1)
The APU fuel shroud.
ILF
2)
The center dry bay drain (if there is a center dry bay) at the fuel drain mast.
NOTE: This is located along the keel beam forward of the aft edge of the main
landing gear door.
ILF
ILF
(e)
ILF
ILF
Collect a sample of fuel for a microbiological contamination analysis. Do this task:
Detection Test for Microbial Growth, TASK 28-10-00-200-801.
ILF
SUBTASK 10-11-94-200-001
ILF
(7)
APU and Engines:
ILF
ILF
NOTE: The engine, thrust reverser and APU checks are completed each 30 days that the
airplane is in Active Storage.
ILF
ILF
(a)
ILF
ILF
For APU preservation, do this task: APU Preservation - Mild Environment,
TASK 49-11-00-620-801.
NOTE: No-load operation of the APU at an interval of approximately 2 months can
prevent preservation.
10-11-94
EFFECTIVITY
ILF 104, 105, 107, 118-199, 601, 602, 623-632
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ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
Page 204
Sep 05/2017
777-200/300
AIRCRAFT MAINTENANCE MANUAL
(b)
ILF
ILF
For B777 with Trent 800 engines and thrust reverser at an interval of 30 days:
1)
Start the engine and let it operate at ground idle for 5 minutes. Do this task:
RR: Start the Engine Procedure (Automatic Start), TASK 71-00-00-800-823-R00 or
G1: Engine Automatic Start, TASK 71-00-00-800-805-H01.
2)
Stop the engine. Do this task: RR: Stop the Engine Procedure (Usual Engine Stop),
TASK 71-00-00-800-826-R00 or G1: Usual Engine Stop,
TASK 71-00-00-800-837-H00.
ILF
ILF
ILF
ILF
ILF
a)
ILF
ILF
You can do the thrust reverser deployment and stowage test (Task
78–31–00–740–802–A01) before you stop the engine.
ILF 601, 602, 623-632
ILF
(c)
ILF
ILF
For B777 with GE90 extended preservation procedure at an interval of 30 days:
1)
Do steps 1-7 G1: Depreservation of An Installed Engine,
TASK 71-00-03-600-806-H01.
2)
Do this task: G1: Test No. 14 - Engine Fuel Driven Actuator Test (MAT Initiated
Test), TASK 71-00-00-700-813-H01.
3)
Do this task: G1: Test No. 15 - Engine Air Driven Actuator Test (MAT Initiated Test),
TASK 71-00-00-700-814-H01.
ILF
ILF
ILF
ILF
ILF
ILF
ILF 104, 105, 107, 118-199, 601, 602, 623-632
ILF
SUBTASK 10-11-94-580-002
ILF
(8)
Park the Airplane:
(a)
ILF
Do this task: Park the Airplane (Normal Parking), TASK 10-11-01-580-804.
ILF
END OF TASK
ILF
ILF
ILF
3.
TASK 10-11-94-550-802
Active Storage (Hot Weather) - Maintenance Practices
A.
(1)
ILF
ILF
General
B.
This task includes the steps to park the airplane in an Active Storage condition in hot weather.
Procedure
ILF
SUBTASK 10-11-94-800-001
ILF
(1)
Limit the heat to the inside of the cabin and the electronics:
ILF
(a)
Lower the window revels throughout the cabin.
ILF
(b)
Open cabin doors.
ILF
(2)
Do this task: Active Storage - Maintenance Practices, TASK 10-11-94-550-801.
ILF
END OF TASK
10-11-94
EFFECTIVITY
ILF 104, 105, 107, 118-199, 601, 602, 623-632
D633W101-ILF2
ECCN 9E991 BOEING PROPRIETARY - Copyright © Unpublished Work - See title page for details
Page 205
Sep 05/2017
CHAPTER
22
AUTOFLIGHT
PJW