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

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

 (4)  
AMM 32-00-15/201, Landing Gear Door Locks

 B.
Access

 (1)  
Location Zones 119 Main Equipment Center 211/212 Control Cabin - Section 41 (Left/Right)

 (2)  
Access Panel
 119BL E/E Access Door

 C.
Prepare for the Test

 (1)  
Supply electrical power (AMM 24-22-00/201).

 S 865-208

 (2)  
Put the EICAS computer switch on the EICAS DISPLAY select-panel, P9, to L.

 S 865-209

 (3)  
Make sure the six EICAS circuit breakers on the overhead panel, P11, are closed.

 S 865-207
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 02 Page 555 ú Jan 20/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
757 MAINTENANCE MANUAL
 S 215-211
 (4)  Make sure the flaps and slats are in the fully retracted position with the flap control lever in the zero (FLAPS UP) detent.
 S 865-212
 WARNING: KEEP PERSONS AND EQUIPMENT AWAY FROM ALL CONTROL SURFACES WHEN
_______ HYDRAULIC POWER IS SUPPLIED. AILERONS, ELEVATORS, RUDDER, FLAPS, SLATS, SPOILERS, AND STABILIZER ARE FULLY POWERED SURFACES. INJURY TO A PERSON OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
 (5)  
Pressurize the left hydraulic system (AMM 29-11-00/201).

 D.
TE-Flap Load Relief System - Test

 S 865-194
 (1)  
Move the flap control lever to the 30-unit detent, and let the TE flaps and LE slats fully extend.

 S 865-195

 (2)  
Open this circuit breaker on the P11 panel and attach DO-NOT-CLOSE tag:

 (a)  
11J18, FLAP LOAD RELIEF

 S 865-196
 (3)  Push and hold the FLA TEST switch (Fig. 501).
 NOTE: The FLA TEST switch is near the E/E bay access panel.
____
 S 215-197
 (4)  
Make sure the EICAS message, FLAP LD RELIEF, does show on the display unit and the TRAILING EDGE light is on.

 S 865-198

 (5)  
Release the FLA TEST switch.

 S 215-199

 (6)  
Make sure the EICAS message, FLAP LD RELIEF, does not show on the display unit and the TRAILING EDGE light is off.

 S 865-200

 (7)  
Remove the DO-NOT-CLOSE tag and close this circuit breaker on the P11 panel:

 (a)  
11J18, FLAP LOAD RELIEF

 S 215-201
 (8)
Push and hold the FLA TEST switch and do the checks that follow:

 (a)
Make sure the TE flaps move to the 25-unit position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-51-00
 ALL  ú ú 02 Page 556 ú Jan 28/02
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757 MAINTENANCE MANUAL
 (b)  Make sure the L and R needles, on the flap position indicator, are in the tolerance band for the 25-unit position.
 S 215-202
 (9)  
Release the FLA TEST switch and do the checks that follow:

 (a)  
Make sure the TE flaps go to the 30-unit position.

 (b)  
Make sure the position indicator needles are in the tolerance band for the 30-unit position.

 S 215-203
 (10)
 Make sure the EICAS messages, FLAP/SLAT ELEC or FLAP ISLN VAL, do not show on the status display.

 S 215-204

 (11)
 Make sure the messages, FLAP/SLAT ELEC, FLAP ISLN VAL, or a FLAP/SLAT BITE, do not show on the ECS/MSG display.

 S 865-205

 (12)
 Move the flap control lever to the zero (FLAPS UP) detent, and let the TE flaps and LE slats fully retract.

 E.
Put the Airplane Back to Its Usual Condition

 S 865-143
 (1)  
　
中國(guó)航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：757 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 4(152)