Landing Gear Control Components Location 532
32-31-0 Figure 1 Feb 15/73
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500
Apr 15/66 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 32-31-0 Page 3
4. Landing Gear Control Lever
A. The landing gear control lever runs in a guide as the lever is moved up or down. The guide has detents to hold the control lever in any one of three positions, UP, OFF, or DN. To change the control lever position it is necessary to pull out the lever to release a roller on the inner end from the detent.
B. The lock override mechanism enables the inner end of the control lever to be pulled clear of the lock stop when the control lever lock is engaged. The override feature is obtained by making the control lever shaft in two parts, one sliding inside the other. A trigger connected to the inner part, projects through a slot in the underside of the outer shaft. A compression spring between a flange on the inner shaft and the control handle quadrant holds the trigger against the bottom of the slot (Fig. 3). When the control lever is pulled, both the inner and outer shafts move together through the quadrant, until the inner end clears the detent. At this point a stop prevents further movement. To retract the inner end of the lever far enough to pass the lock stop the trigger must be operated. Pulling the trigger telescopes the inner shaft into the lever, the additional retraction of the control lever inner end thus obtained, allows the lever to clear the lock stop.
C. The control lever position switch is mounted in the control lever support channel behind the control lever. The switch is actuated by the inner end of the control lever as it drops into the detent. For more information on the switch, refer to 32-61-0, Gear Position Indicating System.
5. Landing Gear Control Lever Lock System
A. The landing gear control lever lock system prevents the control lever moving past OFF position from DN selection until airplane weight is off landing gear. The control lever lock control consists of a mechanical lock operated by a lock solenoid (Fig. 4). The lock solenoid is controlled by a safety relay operated by solid state circuits through the air safety sensor. The system operates on 28-volt dc power from a circuit breaker on panel P6. The control lever is normally released, only when the solenoid is energized.
B. The landing gear safety relay controls the power for the lock solenoid. The relay is installed in the landing gear electrical module, located in the electrical/electronic compartment. For more information on the relay, refer to 32-09-100.
C. The landing gear air safety proximity switch controls the landing gear relay. When the airplane weight is on the landing gear, the sensor operates through solid state circuits to de-energize the relay. Spoiler linkage, driven by a teleflex cable from the extension and compression movement of the shock strut operates the switch. For more information on the switch, refer to 32-09-200.
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32-31-0 Page 4 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 15/68
500 Landing Gear Control Lever Schematic
Nov 15/66 Figure 3 32-31-0
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
6. Operation
A. When the control lever is pulled, the inner end is raised from a detent to free the lever for movement into another position. Moving the lever up or down rotates a cable drum to operate cables running from a quadrant above the left wheel well ceiling. As the quadrant rotates, it operates the landing gear selector valve on the underside of the ceiling, through a shaft, lever, and an adjustable link. Releasing the landing gear lever when the desired position has been selected, allows the lever end to drop into a detent and so hold the lever in position. In down position, the lever end operates a control lever position switch for the indicating and warning system.
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