(b)
Make sure the yellow STAB TRIM light on the pilots' overhead panel, P5, is off.
(c)
Move the trim switches on the control wheel in the down direction.
(d)
Make sure the STAB TRIM light on the pilots' overhead panel, P5, comes on.
(e)
Make sure the EICAS message, STAB TRIM, shows on the top display.
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757
MAINTENANCE MANUAL
(f)
Set the R STAB TRIM switch on the pilots' aft control stand, P8, to the NORM position.
(g)
Push the RESET switch on the right SAM module in the main equipment center.
(h)
Move the trim switches on the control wheel in the down direction.
(i)
Make sure the STAB TRIM light on the pilots' overhead panel, P5, goes off.
(j)
Make sure the EICAS message, STAB TRIM, does not show on the top display.
(k)
Close these circuit breakers on the overhead circuit breaker panel, P11: 1) 11C6, CSEU 1L AC or FLT CONT ELEC 1L AC 2) 11C8, CSEU 2L AC or FLT CONT ELEC 2L AC
S 712-040
(5)
Do the procedure, MCDP Ground Test 65 - Stab Trim (AMM 22-00-02/201), to do a test of the interface between the SAM module and the flight control computer.
S 442-041
(6)
Do the activation procedure for the spoilers if you did the deactivation procedure (Ref 27-61-00).
H.
Do a Test of the Rudder Ratio Changer Module
S 712-042
(1)
Do a test of the rudder ratio changer module (Ref 27-21-00).
I.
Put the Airplane Back to Its Usual Position
(1)
Remove electrical power if it is not necessary (Ref 24-22-00).
S 862-043
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757 MAINTENANCE MANUAL
AILERON AND AILERON TRIM CONTROL SYSTEM - DESCRIPTION AND OPERATION
___________________________________________________________________
1. General (Fig. 1, 5)_______
A. The ailerons, assisted by the spoilers (Ref 27-61-00, Description and Operation), provide lateral control of the airplane. There are two ailerons; one at the outboard trailing edge of each wing. Each aileron is moved by two power control actuators (PCAs) which move the aileron up and down.
B. Control wheels in the flight deck regulate aileron movement. The control wheels actuate cables which in turn actuate the PCAs. The PCAs are powered by separate hydraulic systems to allow aileron control in the event of a single hydraulic failure.
C. The autopilot system (Ref 22-13-00, Description and Operation) controls the ailerons electrically. Autopilot commands actuate the PCAs and back-drive the control wheels.
D. The aileron trim system operates the ailerons and control wheels electrically to adjust the ailerons to a neutral or trimmed (wings level) position. The trim indicator on the control wheels shows the degree of trim.
2. Component Details_________________
A. Lateral Control Wheel (Fig. 2)
_____________________
(1)
The control wheel drives a drum at the base of the control column to operate the aileron system. The bus force limiter links the captain's and first officer's control drums to ensure symmetrical input. Control wheel rotation actuates cables which run aft to lateral control mechanisms in the left and right main gear wheel wells.
(2)
Control wheel travel is |82.5° to the left and right of the control wheel neutral position. Maximum corresponding aileron travel is 21° up and 21° down for about 55° control wheel travel. The remaining 30° of travel drive the spoiler RVDT units. An autopilot disconnect button is located on the control wheel. The aileron trim indicator is on the top of the control wheel.
B.
Aileron Control Drum and Bus Force Limiter Assembly (Fig. 2)
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