27-51-10
ALL ú ú 01 Page 601 ú Oct 10/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
SEE A
OUTBOARD FLAP CONTROL MODULE
MODULE FLAP CONTROL
CONTROL MODULE INBOARD FLAP
POWER PACKAGE INBOARD FLAP OUTBOARD FLAP POWER PACKAGE
CONTROL VALVE STEM 1. BEARING/ BUSHING A A
CRANK
A-A BUSHING/BOLT2. A INBOARD FLAP POWER PACKAGE (OUTBOARD PACKAGE EQUIVALENT)
Flap Control Module Wear Limits
Figure 601 (Sheet 1)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-10
ALL ú ú 01 Page 602 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
INDEX NO. 1 PART NAME DIM. BEARING ID (cm)(cm) 0.4370 0.4380 INCHES MINIMUM MAXIMUM INCHES DESIGN LIMITS DIAMETER (1.1125)(1.1100) (cm) 0.4425 PERMITTED DIMENSION INCHES WEAR WEAR LIMITS (1.1240) 0.007 (cm) MAXIMUM DIAMETER CLEARANCE INCHES X PART WORN REPLACE REPAIR INSTRPART WORN REPAIR
BUSHING OD 0.4345 0.4355 (1.1062)(1.1036) 0.4300 (1.0922) (0.018) X
2 BOLT BUSHING ID OD 0.2495 0.2485 0.2510 0.2495 (0.6337)(0.6312) (0.6375)(0.6337) 0.2535 0.2475 (0.6287) (0.6439) 0.004 (0.010) X
X
Flap Control Module Wear Limits
Figure 601 (Sheet 2)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-10
ALL ú ú 01 Page 603 ú Jun 18/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
L33987
A
747-400 MAINTENANCE MANUAL
HIGH LIFT CONTROL SYSTEM - ADJUSTMENT/TEST
__________________________________________
1. General_______
A. There are two tasks in this procedure. There are tasks for the operational test of the leading edge (LE) and trailing edge (TE) flap primary electrical control systems and the alternate electrical control system.
B. The primary electrical system controls the LE and TE flaps through the flap control lever. A "FLAPS PRIMARY" caution message will be shown on the EICAS to show that the primary electrical system is in control.
C. The alternate system is an open loop system that controls the LE and TE flaps independently of the flap control units (FCUs) with the electric motors. The alternate system is controlled by a pushbutton ALTN FLAPS ARM switch and a rotary ALTN FLAPS EXT/RET switch on the P2-3 Pilot's Center Panel. A "FLAPS CONTROL" caution message will be shown on the EICAS to show that the alternate system is in control. In the alternate mode, the limit switches on the TE Power Drive Units control the sequence of the LE flaps during retraction. The inboard PDU controls the group B LE flaps and the outboard PDU controls the group A LE flaps.
D. For the LE flap system to operate, it is necessary that the TE flaps are serviceable.
TASK 27-51-11-705-026
2. Primary Electric Operational Test - LE and TE Flap Systems__________________________________________________________
A. General
(1)
The primary electrical system controls the LE and TE flaps through the flap control lever. A "FLAPS PRIMARY" caution message will be shown on the EICAS to show that the primary electrical system is in control.
B.
References
(1)
24-22-00/201, Manual Control
(2)
29-11-00/201, Main Hydraulic Supply System
(3)
36-00-00/201, Pneumatic System
C.
Access
(1)
Location Zone
221 Control Cabin, LH
222 Control Cabin, RH
D.
Prepare for the Test
(1)
Supply electrical power (Ref 24-22-00/201).
S 865-002
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：747-400 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 4(152)
