505 A/P Elevator Actuator Linkage Wear Limits
Oct 20/89 Figure 601 (Sheet 1) 22-11-261
Page 601
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
A/P Elevator Actuator Linkage Wear Limits 500
22-11-261 Figure 601 (Sheet 2) Oct 20/86
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 A/P Elevator Actuator Linkage Wear LimitsOct 20/86 Figure 601 (Sheet 3) 22-11-261 Page 603/604BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON POSITION SENSOR - REMOVAL/INSTALLATION
EFFECTIVITY
SA ZS-SIA and on SD ST-AIB and on WA N235WA-N241WA GJ B-2509 and B-2510
1. General (Fig. 401)
A. The aileron position sensor is mounted on the left aileron torque tube and forward wall of the main wheel well adjacent to the autopilot actuators (Ref Chapter 27, Aileron and Aileron Trim Control System).
2. Remove Sensor
A. Open autopilot AC circuit breakers on P6 and P18 load control centers.
B. Open tire burst protection screens in left main wheel well (Ref Chapter 27, Tire Burst Screen Doors - Maintenance Practices).
C. Disconnect sensor electrical connectors.
D. Loosen screw in sensor crank and remove crank from sensor.
E. Loosen screw in sensor clamp and remove sensor.
3. Install Sensor
A. Set ailerons and aileron trim to 0 units.
B. Align index marks on sensor housing and sensor shaft.
C. Install sensor in clamp and crank with index mark aligned with slot in crank.
CAUTION: ENSURE THAT AUTOPILOT AILERON POSITION SENSOR ROD IS CORRECTLY ORIENTED AS SHOWN IN FIG. 401.
D. Tighten screws in sensor clamp and crank 8-12 lb-in.
E. Adjust aileron position sensor (Ref Aileron Position Sensor - Adjustment/Test).
F. Replace tire burst protection screens.
May 01/01 22-11-291 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H19362
Aileron Position Sensor Installation 580
22-11-291Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Nov 15/79
AILERON POSITION SENSOR -ADJUSTMENT/TEST
EFFECTIVITY
SA ZS-SIA and on GJ B-2509 and B-2510
1. Aileron Position Sensor Adjustment
A. General
(1) The autopilot system and all aileron rigging must be fully adjusted before the sensor can be adjusted (Ref Chapter 27, Aileron and Aileron Trim Control -Adjustment/Test). The tire burst protection screens must be folded out of the way (Ref Chapter 27, Tire Burst Screen Doors -Maintenance Practices).
B. Equipment and Materials
(1)
VTVM -Hewlett Packard, Model 410C.
(2)
Test Set -Autopilot Elevator/Rudder/Aileron Control Unit -P/N F80217-125
C. Prepare to Adjust
(1)
Provide electrical and hydraulic power.
(2)
Position hydraulic system A and B switches on P5 panel to OFF and open FLT CONT SYS circuit breaker on P6 load control center.
WARNING: PRESSURIZING HYDRAULIC SYSTEMS WILL SUPPLY POWER TO RUDDER, AILERON, ELEVATOR, SPOILER AND SPEED BRAKE SYSTEMS. CARE SHOULD BE TAKEN TO ISOLATE OR TAG SYSTEMS NOT BEING TESTED TO PREVENT INJURY TO PERSONNEL OR DAMAGE TO AIRPLANE AND EQUIPMENT.
(3)
Open autopilot circuit breakers on P6 and P18 load control centers.
(4)
Set ailerons and aileron trim to 0.
(5)
Connect power cable between test set and D152 electronic equipment rack service outlet.
(6)
Disconnect D1827 (A system) and D1691 (B system) connectors from autopilot actuators; connect tester A to actuator A and tester B to actuator B.
(7)
Connect VTVM to LVDT FEEDBACK J10A and J11A on test set (A system).
(8)
Disconnect airplane wiring from position sensors and connect test cables between A sensor and tester A and B sensor and tester B.
(9)
Set switches on test set as follows (A system):
(a)
LVDT FEEDBACK switches A ON, B ON.
(b)
LVDT EXCITATION switches A ON, B ON.
(c)
NSS EXCITATION switches A ON, B OFF.
(d)
NSS FEEDBACK switches A and B OFF.
(e)
SOLENOID EXCITATION switches PISTON and ENGAGE A ON, B ON.
(f)
CURRENT SELECT switches to A T-VALVE.
(g)
A & B SOLENOIDS switches to A NORMAL, B NORMAL, and ON.
(h)
ACTUATOR SELECT switch (S-12) to A and B COMMON.
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