(d)  
To extend the TE flaps independently of the slats, push the arming switch for the flap alternate drive, on the P3 panel, to arm the flap alternate drive (switch light will come on).

 (e)  
To extend the TE flaps and LE slats, push the arming switches for the flap and slat alternate drives on the P3 panel (switch lights will come on).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 01 Page 209 ú Sep 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 (f)  Move the position selector switch for the flap/slat alternate drive, on the P3 panel, to the necessary detent and let the flaps move to the correct position. 1) Look at the L and R needles on the flap position indicator,
 on the P3 panel, to monitor the flap movement.
 2)  If only the flap drive system is armed, the amber LEADING EDGE light, on the P3 panel, will come on and the EICAS screen will show a LE SLAT DISAGREE message.
 (g)  
Remove the electric power if it is not necessary
 (Ref 24-22-00).

 (h)  
If you do work near the flap control surfaces, deactivate the flap drive system.

 S 862-009
 (3)  
Do these steps to retract the TE flaps:

 (a)  
Make sure the position of the TE flaps and the position of the position selector switch for the flap/slat alternate drive, on the P3 panel, are the same.

 (b)  
Supply electrical power (Ref 24-22-00).

 (c)  
Turn the position selector switch for the flap/slat alternate drive, on the P3 panel, to the UP detent and let the flaps move to the fully retracted position.

 (d)  
Turn the position selector switch for the flap/slat alternate drive, on the P3 panel, to the NORM detent.

 (e)  
If only the flap drive system is armed, push the arming switch for the flap alternate drive, on the P3 panel, to disarm the flap alternate drive (switch light will go off).

 (f)  
If the TE flap and LE slat drive systems are armed, push the arming switches for the flap and slat alternate drives on the P3 panel (switch lights will go off).

 (g)  
Remove the electrical power if it is not necessary
 (Ref 24-22-00).

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 01 Page 210 ú Sep 20/90
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757 MAINTENANCE MANUAL
 TRAILING EDGE FLAP SYSTEM - ADJUSTMENT/TEST
___________________________________________
 1.  General_______
 A.  This procedure contains five tasks. The first task is an operational test of the trailing edge (TE) flap system. The second task is an adjustment of the control system for the TE flaps. This adjustment covers components from the flap control lever to the power drive unit (PDU) for the TE flaps. The third task is a system test to make sure the TE flap system is correctly adjusted. The fourth and fifth tasks are included in the third task. Thus, if you do the third task, it is not necessary to do tasks four and five.
 B.  Make sure the inboard and outboard flaps on the trailing edge are installed and adjusted (AMM 27-51-02 and 27-51-14).
 TASK 27-51-00-715-001
 2.  Operational Test of the TE Flap System______________________________________
 A.  General
 (1)  
Make sure the flap-position indicator system is correctly adjusted (AMM 27-58-00/501).

 B.  
References

 (1)  
AMM 20-10-03/401, Control Cables - Removal/Installation

 (2)  
AMM 24-22-00/201, Electrical Power-Control

 (3)  
AMM 29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems

 C.  
Access

 (1)  
Location Zones
 119 Main Equipement Center
 211/212 Control Cabin

 D.  
Prepare for the Test

 S 865-189
 (1)  
Make sure the flaps and slats are in the fully retracted position with the flap control lever in the zero (FLAPS UP) detent.
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 4(127)