Trailing Edge Flap System Component Location
Figure 2 (Sheet 3)
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-00
ALL ú ú 01 Page 5 ú Apr 10/89
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
WARNING:_______DO NOT USE THESE VALUES (UNITS) FOR RIGGING PURPOSES. THESE VALUES ARE FOR REFERENCE USE ONLY. YOU MUST USE THE APPROPRIATE MAINTENANCE MANUAL PROCEDURE TO RIG THE TRAILING EDGE FLAPS.
C. The table that follows shows the upper and lower Trailing Edge flap position output range for each detent setting. The Inboard and Outboard values are shown.
NOTE: The values can be seen on the Flight Controls EICAS Maintenance
____ Page. The values from each of the three Flap Control Units (FCU's) can be seen independently if you supply power to each FCU separately. If you supply power to all three FCU's, the EICAS display will show the Center FCU flap position values.
~...................................................
| DETENT | INBOARD | OUTBOARD | |
| POSITION | FLAP | FLAP | THRESHOLD |
.....................................................
| UP | - 0.15 | - 0.15 | LOWER |
| | 0.16 | 0.16 | UPPER |
.....................................................
| 1 | - 0.15 | - 0.15 | LOWER |
| | 0.16 | 0.16 | UPPER |
.....................................................
| 5 | 4.84 | 4.84 | LOWER |
| | 6.42 | 6.13 | UPPER |
.....................................................
| 10 | 8.76 | 8.87 | LOWER |
| | 11.69 | 11.86 | UPPER |
.....................................................
| 20 | 18.24 | 18.11 | LOWER |
| | 21.99 | 22.28 | UPPER |
.....................................................
| 25 | 22.98 | 22.71 | LOWER |
| | 26.31 | 26.69 | UPPER |
.....................................................
| 30 | 28.69 | 28.31 | LOWER |
| | 31.32 | 31.70 | UPPER |
2............…............…............…............1
3. Flap Control Units (Fig. 2)__________________
A. The three Flap Control Units (FCU's) provide control, protection, and indication for the trailing edge and leading edge flaps. The FCU's also process position indication signals for the horizontal stabilizer (Ref 27-48-00). The FCU's are located in the main electrical/electronic equipment center, with the left FCU on the E1-2 shelf and the center and right FCU's on the E2-2 shelf. The FCU's are powered by the Flight Controls Electronics Power Supply Modules (Ref 27-09-00).
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú
27-51-00
ALL ú ú 01 Page 6 ú Oct 10/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
747-400
MAINTENANCE MANUAL
B. Each FCU receives inputs from the following sources:
(1)
Flap lever RVDT assembly
(2)
Alternate flaps ARM switch and EXT/RET switch
(3)
RVDT transmitters at TE flap actuator, power packages, and
transmissions
(4)
Primary and alternate air/ground relay system
(5)
Left and right Air Data Computers
(6)
Engine 1 and 4 demand pressure and EDP pressure switches
(7)
Engine 1 and 4 Hydraulic Discrete Interface circuit cards
(8)
Central Maintenance Computer System
C.
The inputs are processed independently by each FCU to generate output signals to the flap actuator, flap alternate electric motors, flap position and failure indication displays, leading edge flap power drive units and other airplane user systems. Only one FCU at a time is enabled to command a change in flap position for a given group of flaps (TE outboard, TE inboard, LE group A, LE group B). All automatic flap control functions will operate with one, two, or three FCU's operational.
D.
The FCU in control operates in primary hydraulic mode or primary electric mode to command a change in flap position. Normally, flaps are moved in primary hydraulic mode. If no movement with a group of flaps under hydraulic power is detected, the FCU automatically switches to primary electric mode for that group of flaps. In primary electric mode, the flaps are commanded by the FCU to move under electric motor power. If alternate flaps are selected from the flight deck, the FCU control outputs are disabled and the electric drive motors for all flaps are under direct manual control.
中國航空網 m.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 4(40)
