AUTOPILOT MODE CONTROL PANEL - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. The autopilot mode control panel is located on the pilot's lightshield. The mode control panel is held in place by four quick release fasteners.
2. Remove Mode Control Panel
A. Open autopilot and panel lights circuit breakers on P6 and P18 panels.
B. Release mode control panel by unlatching quick release fasteners.
C. Withdraw panel from lightshield and disconnect electrical connectors.
3. Install Mode Control Panel
A. Examine electrical connectors for bent or pushed back pins or sockets and repair as required.
B. Connect electrical connectors to mode control panel, position panel in place and latch quick release fasteners.
C. Close autopilot and panel lights circuits breakers.
4. Installation Test
A. Provide electrical power to airplane buses.
B. Pressurize hydraulic system B then apply hydraulic pressure to control surfaces (Ref 29-12).
WARNING: MAKE SURE ALL PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF AILERON, ELEVATOR, SPOILER SPEED BRAKE AND RUDDER SYSTEMS. SURFACES MAY MOVE ABRUPTLY WHEN HYDRAULIC POWER IS APPLIED.
C. Check that flight control B switch is on.
Jun 20/85 22-11-191 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
D. Verify that one yaw damper is engaged.
E. Provide attitude and compass valid signals.
F. Place autopilot stab trim switch on aisle stand to NORMAL position.
G. Engage AIL engage switch.
H. Place navigation (NAV) mode select switch (on autopilot control panel) in VOR/LOC position.
I. Disengage AIL engage switch. Observe that NAV mode select switch returns to MAN position.
J. Engage autopilot.
K. Place pitch mode select switch in ALT HOLD position.
L. Disengage ELEV engage switch. Observe that pitch mode select switch returns to OFF and that ALT HOLD mode cannot be selected.
M. Engage ELEV engage switch and place pitch mode select switch in ALT HOLD position.
N. Remove hydraulic power and restore airplane to normal.
O. Remove electrical power if no longer required.
22-11-191 Feb 20/84 Page 402
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
AILERON POSITION TRANSDUCER - REMOVAL/INSTALLATION
EFFECTIVITY
SD ST-AFK, ST-AFL GJ ALL EXCEPT B-2509 and B-2510
1. General
A. An aileron position transducer is externally mounted between ends of clevis on right end of B aileron power unit and may be installed but not used on A aileron power unit.
B. This procedure covers transformer portion of transducer only. Detail disassembly of the power unit is required to remove the transducer rod (Fig. 401).
2. Remove Transducer Transformer
A. Remove power unit from wheel well area (Ref Chapter 27, Aileron Power Control Unit).
B. Remove mounting bolts and lift transducer transformer from power unit (Fig. 401).
C. Cover all openings.
3. Install Transducer Transformer
A. Verify O-ring is satisfactory or replace.
B. Install transducer transformer (Fig. 401).
C. Install mounting bolts and tighten to 40 to 50 pound-inches.
D. Lockwire bolts.
E. Install aileron power unit (Ref Chapter 27, Aileron Power Unit).
F. Check for leakage and operation of transducer (Ref Aileron Position Transducer -Adjustment/Test).
May 20/82 22-11-231 Page 401
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
H29041
Aileron Position Transducer Installation 500
22-11-231Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 15/67
AILERON POSITION TRANSDUCER -ADJUSTMENT/TEST
EFFECTIVITY
GJ ALL EXCEPT B-2509 and B-2510
1. Aileron Position Transducer Test
A. Prepare to Test Aileron Position Transducer
(1)
Verify control surfaces are free to move.
(2)
Provide ground power to the airplane and energize buses on load control center P6.
(3)
Ensure autopilot circuit breakers, located on load control center P6, are closed.
(4)
Pressurize hydraulic systems A and B (Ref 29-11-0, Maintenance Practices and 29-12-0, Maintenance Practices).
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