(b)
Set the FLT CONTROL A switch to STDBY RUD.
1) Make sure the LOW PRESSURE light comes on.
2) AIRPLANES POST-SB 27-1252;
Make sure the STBY RUD ON light comes on.
(c)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P6 Circuit Breaker Panel: 1) NO. 2 GEN BUS -STBY HYD PUMP (ALT) 2) NO. 1 GEN BUS -STBY HYD PUMP NORMAL
(d)
Make sure the LOW PRESSURE light goes off.
(e)
Set the FLT CONTROL A switch to ON.
1) Make sure the LOW PRESSURE light is off.
2) AIRPLANES POST-SB 27-1252;
Make sure the STBY RUD ON light goes off.
(9)
Do a test of the YAW DAMPER light on the P5-3 module.
(a)
Make sure the FLT CONTROL B switch is ON.
(b)
Turn the YAW DAMPER switch to OFF.
1) Make sure the YAW DAMPER light comes on.
(c)
Turn the YAW DAMPER switch to ON.
1) Make sure the YAW DAMPER light goes off.
(10)
Do a test of the FLT CONTROL and SPOILER switches.
(a)
Operate the aileron control wheel, control column, and rudder pedal sets. 1) Make sure the ailerons, rudder, elevators, and spoilers operate satisfactory.
(b)
Set the FLT CONTROL A and B switches and the SPOILER A and B switches to OFF. 1) Make sure the two LOW PRESSURE lights come on. 2) Make sure the spoilers do not operate.
(c)
Set the FLT CONTROL A and B switches and the SPOILER A and B switches to ON. 1) Make sure the two LOW PRESSURE lights go off.
(11)
Do a test of the alternate leading edge flaps and slats system.
(a)
Set the FLT CONTROL B switch to STDBY RUD 1) Make sure the LOW PRESSURE light comes on momentarily then goes off. 2) AIRPLANES POST-SB 27-1252;
Make sure the STBY RUD ON light comes on.
(b)
Make sure that the flap control lever is in the FLAP UP detent.
(c)
Set the ALTERNATE FLAPS arm switch to ARM.
1) Make sure that the leading edge flaps and slats do not extend.
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27-09-45 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/03
WARNING: MAKE SURE THAT PERSONS OR EQUIPMENT ARE CLEAR OF THE LEADING EDGE FLAPS AND SLATS. THE LEADING EDGE CONTROL SURFACES WILL EXTEND. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
CAUTION: MAKE SURE THAT THE INBOARD FAN DUCT COWL AND THE THRUST REVERSERS ARE CLOSED OR COMPLETELY REMOVED BEFORE YOU EXTEND THE LEADING EDGE FLAPS. THERE IS NOT SUFFICIENT CLEARANCE FOR THE LEADING EDGE FLAPS TO EXTEND IF THE INBOARD FAN DUCT COWL AND THE THRUST REVERSER ARE IN THE OPEN POSITION. THIS CAN CAUSE DAMAGE TO EQUIPMENT.
CAUTION: MAKE SURE THAT THE ALTERNATE FLAP DRIVE UNIT IS LIMITED TO 4 MINUTES OPERATION AND 25 MINUTES OFF. FAILURE TO DO THIS CAN CAUSE DAMAGE TO THE DRIVE UNIT.
(d)
Set the ALTERNATE FLAPS position switch to DOWN.
1) Make sure that the leading edge flaps and slats operate satisfactory.
(e)
Set the ALTERNATE FLAPS position switch to UP.
1) Make sure the leading edge flaps and slats operate satisfactory.
(f)
Set the ALTERNATE FLAPS arm switch to OFF.
1) Make sure that the leading edge flaps and slats fully retract.
2) Make sure that the trailing edge flaps fully retract.
(g)
Set the FLT CONTROL B switch to OFF
1) AIRPLANES POST-SB 27-1252;
Make sure the STBY RUD ON light goes off.
(h)
Set the ALTERNATE FLAPS arm switch to ARM.
1) Make sure that the leading edge flaps and slats do not extend.
(i)
Set the ALTERNATE FLAPS arm switch to OFF.
(j)
Set the FLT CONTROL B switch to ON.
(12)
Remove electrical power if it is not necessary (AMM 24-22-0/201).
(13)
Remove hydraulic power if it is not necessary (AMM 27-21-0/201).
500
May 01/03 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-09-45 Page 405
CONTROL CABLE SYSTEMS - DESCRIPTION AND OPERATION
1. General
A. The primary function of the control cables in the flight control systems is to transmit the pilots' control inputs to the affected control surfaces. The control cables ar e made from 7 x 7 and 7 x 19 carbon steel flexible wire. A typical control cable system terminates at a drum or quadrant by means of swaged terminals and has turnbuckles to allow tensioning the cable to the proper rigging load. Long cable runs are supported by idler pulleys. Air seals are used to reduce pressure loss when cables are routed through pressure bulkheads.
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本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(17)
