(a)  
If the rign pin LE1 cannot easily be put in the rig pin hole, adjust the LE-slat PDU (Ref 27-81-00).

 H.
Put the Airplane Back to Its Usual Condition

 S 865-034
 (1)  
Remove the DO-NOT-CLOSE tags, and close these circuit breakers on the P11 panel:

 (a)  
11B18, WARN ELEX B

 (b)  
11C14, FLAP SLAT ELEC UNIT 2 POWER

 (c)  
ON GUN 006-999;
 11C17, FLAP SLAT SHUTOFF 1

 (d)  
11D31, HYDRAULICS PTU CONT

 (e)  
11G12, FLAP SLAT ELEC UNIT 1 POWER

 (f)  
11G21, FLAP SLAT ELEC UNIT 3 POWER

 (g)  
ON GUN 001-005;
 11H14, FLAP SLAT SHUTOFF 1

 (h)  
11H23, FLAP/SLAT ALTN DR SHUTOFF ARM

 (i)  
11H24, FLAP/SLAT ALTN DR SHUTOFF 2

 (j)  
11J33, WARN ELEX A

 S 865-035
 (2)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P6 panel:

 (a)  
6D20, ALTN SLAT PWR

 (b)  
6D23, ALTN FLAP PWR

 TASK 27-51-00-735-036
 4.  TE Flap System - System Test____________________________
 A. General
 (1)  The TE flap system must be adjusted correctly before the tests that follow are done.
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757
MAINTENANCE MANUAL

 (2)  
ON AIRPLANES WITH A -17 OR LOWER FSEU; FAULT indications are failures the Flap/Slat Electronics Unit finds at the time a BITE test is run.

 (3)  
ON AIRPLANES WITH -32 OR -37 FSEU; PAST FAULT is a failure that occurred before the Flap/Slat Electronic Unit (FSEU) BITE test was run and put in the non-volatile memory. PRESENT FAULT is a failure the FSEU finds at the time a BITE test is run.

 (4)  
ON AIRPLANES WITH -40 FSEU; an EXISTING FAULT is a failure that occurred in the last flight leg. Faults that occurred before the last flight leg can be found in the respective flight leg in the FAULT HISTORY part of the FSEU BITE menu.

 B.
Equipment

 (1)  
TE Flap PDU Lock - B27008-1

 (2)  
Force Gage (0-25 pounds)

 (3)  
TE Flap Torque Tube Clamps from Set B27055-1

 (a)  
Outboard TE Flap Torque Tube Clamp - B27055-2

 (b)  
Inboard TE Flap Torque Tube Clamp - B27055-3

 C.
References

 (1)  
AMM 06-41-00/201, Fuselage Access Doors and Panels

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

 (3)  
AMM 27-81-00/201, Leading Edge Slat System.

 (4)  
AMM 29-11-00/201, Main (Left, Right, and Center) Hydraulic Systems

 D.
Access

 (1)  
Location Zones
 119 Main Equipment Center
 143 Left MLG Wheel Well
 197/198 Wing to Body - Aft Lower Half (Left/Right)
 211/212 Control Cabin - Section 41 (Left/Right)
 567/667 Outboard Aft Flap (Left/Right)

 (2)  
Access Panel
 193BL RAM Air Inlet Actuator Door

 E.
Prepare for the Test

 S 865-171
 (1)  
Supply electrical power (AMM 24-22-00/201).

 S 865-172

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

 S 865-173

 (3)  
Make sure these circuit breakers on the overhead panel, P11, are closed:

 (a)  
EICAS (6 locations)

 (4)  
Open access panel 193BL (AMM 06-41-00/201).

 S 015-174
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757 MAINTENANCE MANUAL
 S 215-175
 (5)  Make sure the flaps and slats are in the fully retracted position with the flap control lever in the zero (FLAPS UP) detent.
　
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