(2) Adjust autobrake off ramp switch as follows:
(a)
Move speed brake lever aft until open circuit is obtained between common and normally open contacts of switch. Check that speed brake lever is 3.28-3.84 inches aft from down and locked detent.
(b)
Adjust switch as required, bending switch actuator tab if necessary. Tighten adjustment nuts.
D. Test speed brake arming and autobrake off ramp switches as follows:
(1) Test speed brake arming switch.
NOTE: Weight of airplane must be on the landing gear for this test.
(a)
Provide electrical power.
(b)
Provide system A hydraulic power (Ref 27-62-0, Maintenance Practices).
(c)
Place both inboard and outboard antiskid switches to ON. Switches are located on center instrument panel.
(d)
On circuit breaker panel P6 ensure that the following circuit breakers are closed: INDICATOR LIGHTS FLIGHT CONTROL VALVES SPOILER SHUTOFF VALVES AUTO SPEED BRAKE ALL ANTISKID
(e)
Place engines No. 1 and 2 thrust levers in idle position.
(f)
Place speed brake control lever in ARMED position. Check that ARMED light on center panel comes on.
(g)
Move speed brake control lever forward to DOWN position and check that ARMED light goes off.
(h)
Remove system A hydraulic power (Ref 27-62-0).
(i)
Remove electrical power if no longer required.
(2) Test autobrake off ramp switch:
(a)
Connect ohmmeter across common and normally open contacts on switch.
(b)
Move speed brake lever aft until open circuit is obtained. Check that speed brake lever is 3.28-3.84 inches aft from down and locked detent.
(c)
Remove ohmmeter and return speed brake lever to down and locked detent.
501
May 15/78 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-62-111 Page 403
LEADING EDGE FLAP AND SLAT CONTROL SYSTEM - DESCRIPTION AND OPERATION
1. General
A. High lift leading edge devices are used in combination with the trailing edge flaps to allow airplane operation from short runways. The use of leading edge devices allows a change in wing camber which greatly increases lift. The leading edge lift devices consist of four Krueger flaps and six slats. (See figure 1.)
B. Three leading edge slats are installed outboard of the engine and two leading edge flaps are installed inboard of the engine on each wing. The slats and flaps are numbered from left to right as shown in figure 1. Leading edge slats 1 through 6 are actuated by a three-position hydraulic actuator . If hydraulic pressure is low, a blocking valve will create a hydraulic lock that prevents actuator movement. This locking action will hold the slat in the position at which the loss of hydraulic pressure occurs. Each leading edge flap is actuated by a two-position hydraulic actuator. The flap actuator will also lock in position if hydraulic pressure is low. Locking the actuators prevents blowback of the flaps and slats if hydraulic pressure is lost during takeoff or landing. Restrictors installed in the flap and slat actuator hydraulic pressure lines limit the actuating speed of the leading edge devices.
C. The leading edge flaps and slats are normally powered by hydraulic system A. A three-position, spool type control valve is operated by the flap control unit. The control valve ports hydraulic fluid to the leading edge flap and slat actuators. When the trailing edge flaps are between up and 10 units, the control valve ports pressure to fully extend the leading edge flaps and extend all leading edge slats to the intermediate position. When the trailing edge flaps are positioned to 10 units or more, the control valve ports pressure to fully extend all leading edge slats.
D. On flap retraction, all leading edge flaps and slats remain fully extended until the trailing edge flaps are retracted to less than 10-unit extension. Between 10 units and up, all leading edge slats retract to their intermediate positions, and all leading edge flaps remain fully extended. When the trailing edge flaps reach the fully retracted position, all leading edge flaps and slats move to the fully retracted position. Control lever movement toward the up detent is stopped momentarily at the 1-unit position by a gate on the flap control quadrant.
531
May 15/71 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-81-0 Page 1
G41314G41343 G41352G41361
Leading Edge Flap and slat Control System Component Location 521
27-81-0 Figure 1 (Sheet 1) May 15/71
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
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