SPOILER CONTROL PACKAGE QUADRANT
WING REAR SPAR
RIG PIN A/S-18,A/S-20, A/S-22 OR A/S-23
POSITION TRANSMITTTER SPOILER NO. 12 ONLY
FWD
EXAMPLE OF OUTBOARD FLIGHT SPOILERS NO. 1,3,10, AND 12
A

Flight Spoiler Control Package - Rig Pin Locations
Figure 503 (Sheet 1)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-61-00
 ALL  ú ú 01 Page 512 ú Jun 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

TRAILING EDGE
REAR SPAR
SPOILER CONTROL PACKAGE

SPOILER ACTUATOR QUADRANT AND RATIO CHANGER (LINKAGE)
SPOILER CONTROL CABLES
INBOARD FLIGHT SPOILER RIG PINS NO. A/S-19 AND A/S-21
INBD FWD
RATIO CHANGER ACTUATOR
INBOARD FLIGHT SPOILER NO. 8 (SPOILER NO. 5 EQUIVALENT)
B
Flight Spoiler Control Package - Rig Pin Locations
Figure 503 (Sheet 2)

EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-61-00
 ALL  ú ú 01 Page 513 ú Jun 10/91
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

 S 835-118
 (12)
 If the tension is not in the limits or you installed new cables, adjust the tension:

 (a)  
Adjust the tension to |5 pounds (2.27kg) of the tension shown for the ambient temperature (Fig. 501).

 (b)  
With the trim and feel mechanism centered and rig pin A/S-2 installed, make sure you can easily install the rig pins A/S-4, A/S-5, and A/S-18 thru A/S-23.

 (c)  
Remove all of the rig pins.

 (d)  
Do this task: "Turnbuckle Locking Clips Installation" (AMM 20-11-02/401).

 S 865-037
 (13)
 Do this task: "Remove Hydraulic Power" (AMM 29-11-00/201).

 S 865-038

 (14)
 Do this task: "Remove Electrical Power" (AMM 24-22-00/201).

 H.
Examine the Clearance Between the Spoilers and the Flaps

 NOTE: The airplane must be on its landing gear when you measure this
____
 clearance.

 S 865-039
 WARNING: OPEN THE CIRCUIT BREAKERS TO PREVENT THE SPOILER RETRACTION.
_______ IF YOU USE THE SPEED BRAKE CONTROL LEVER TO LIFT THE SPOILERS, AND IF YOU RELEASE THE PRESSURE IN HYDRAULIC SYSTEMS NO. 1 AND 4, THE SPOILERS WILL RETRACT AUTOMATICALLY. THIS CAN CAUSE INJURY TO PERSONS.
 (1)  
Open these circuit breakers and attach DO-NOT-CLOSE tags:

 (a)  
P7, Overhead Circuit Breaker Panel
 1) 7G6, SPEED BRAKE AUTO CONT

 S 865-040
 (2)  
Do this task: "Supply Electrical Power" (AMM 24-22-00/201).

 (3)  
Do this task: "Supply Hydraulic Power" (AMM 29-11-00/201).

 (4)
Put the speed brake lever in the UP position to lift the spoilers.

 S 865-041
 S 865-042
 NOTE: With the spoilers up, the trailing edge flaps will not touch
____
 the spoilers during the retraction.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-61-00
 ALL  ú ú 03 Page 514 ú Feb 18/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL

A
A B
B
OUTBOARD 45` FLIGHT SPOILER TO FLAP MINIMUMSEE B
SPOILER
MIDFLAP CLEARANCE 0.02 TO 0.16 INCH
(0.50 TO 4.06 mm) WITH SPOILER FULLY RETRACTED 1
NOTE:  THE AIRPLANE MUST BE SUPPORTED ON ITS LANDING GEAR WHEN YOU MEASURE THIS CLEARANCE.
1 THE SPOILER PANELS ARE NOT FLAT.
FWD MEASURE THE CLEARANCE AT THE NEAREST
CONTROL PACKAGE INPUT POINT. THERE IS NO MAXIMUM CLEARANCE
SEE A ARM ROD ASSEMBLY BECAUSE OTHER PARTS OF THE PANEL CAN HAVE A GREATER CLEARANCE. AFTER THE
FIRST SPOILER CYCLE AFTER THE ADJUSTMENT, THE MINIMUM CLEARANCE MUST BE 0.02 TO 0.16
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 6(36)