(5)  
34-11-00/201, Pitot-Static System

 C.
Prepare for the Tests

 S 865-A94
 (1)  
Supply electrical power (Ref 24-22-00/201).

 S 865-A95

 (2)  
Open these circuit breakers on the overhead panel, P11, and attach DO-NOT-CLOSE tags:

 (a)  
11C6, CSEU 1L AC
 or FLT CONT ELEC 1L AC

 (b)  
11C8, CSEU 2L AC
 or FLT CONT ELEC 2L AC

 (c)  
11G17, CSEU 1R AC
 or FLT CONT ELEC 1R AC

 (d)  
11G27, CSEU 2R AC
 or FLT CONT ELEC 2R AC

 S 015-A96
 WARNING:_______STAY OFF SERVICE ACCESS DOORS 311AL AND 313AL. THE WEIGHT OF A PERSON CAN CAUSE THE SPRING-LOADED LATCHES TO RELEASE. A PERSON CAN BE INJURED IF THEY FALL THROUGH THE OPEN DOOR.
 (3)  Open the access door, 311AL, to the forward stabilizer-compartment (Ref 06-42-00/201).
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757 MAINTENANCE MANUAL
 S 865-A97
 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 PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
 (4)  
Pressurize the right and center hydraulic systems
 (Ref 29-11-00/201).

 D.
Electrical Travel Limits - Operational Test

 S 865-B43
 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 PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR WHEN HYDRAULIC POWER IS SUPPLIED.
 (1)  
Pressurize the left hydraulic system (Ref 29-11-00/201).

 S 215-B44

 (2)  
Make sure the trailing edge flaps and leading edge slats are fully retracted, and the flap lever is in the zero detent (FLAPS UP).

 S 865-B45

 (3)  
Move the captain's stabilizer-trim control-wheel-switches up (airplane nose down) and hold the switches up until the stabilizer stops.

 NOTE: If the stabilizer does not move when you initially move the
____ switches up, move the switches down until the stabilizer is at 4 to 6 units of trim, then move the switches up.
 (a)  Make sure that the stabilizer position indicators on the control stand show 2.75 to 3.25 units of trim.
 S 865-B46
 (4)  
Move the captain's stabilizer-trim control-wheel-switches down (airplane nose up) and hold the switches down until the stabilizer stops.

 (a)  
Make sure that the stabilizer position indicators show 15.0 to

 15.6 units of trim.
 S 865-B47
 (5)  Extend the trailing edge flaps to the 15-unit position
 (Ref 27-51-00).

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A

757
MAINTENANCE MANUAL

 S 865-B48
 (6)  
Do the trailing edge flap system deactivation procedure
 (Ref 27-51-00).

 S 865-B49

 (7)  
Move the captain's stabilizer-trim control-wheel-switches up (airplane nose down) and hold the switches up until the stabilizer stops.

 (a)  
Make sure that the stabilizer position indicators show 0.0 to

 0.5 units of trim.
 S 865-B50
 (8)  
Do the trailing edge flap system activation procedure
 (Ref 27-51-00).

 S 865-B51

 (9)
Move the flaps to the fully retracted position (AMM 27-51-00/201).

 E.
Stabilizer Trim Cutoff Switch Test (Fig 504)

 NOTE: The stabilizer may not be in electrical control range if it
　
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