(1)
Location Zones
211/212 Control Cabin
C.
Install the Position Indicator (Fig. 401)
S 424-010
(1)
Set the position indicator in the control stand.
S 434-011
(2)
Connect the electrical connector to the position indicator.
S 434-012
(3)
Install the screws to attach the position indicator to the control stand.
S 414-013
(4)
Install the access panel on the side of the control stand.
D.
Position Indicator Test
S 864-014
(1)
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the overhead panel, P11:
(a)
11B19, STAB TRIM ALT (IF INSTALLED)
(b)
11C12, STAB TRIM SHUTOFF LIGHT
(c)
11C13, STAB TRIM SHUTOFF RIGHT
(d)
11H10, STAB TRIM LEFT POS IND
or STAB TRIM POS IND L
(e)
11H11 or 11C05, STAB TRIM CONT L
(f)
11H19, STAB TRIM POS IND RIGHT
(g)
11H20, STAB TRIM CONT R
S 864-015
(2) Put the RIGHT and CENTER STAB TRIM SHUTOFF valve switches on the control stand panel, P10, to the NORM position.
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MAINTENANCE MANUAL
S 864-016
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. INJURIES TO PERSONS OR DAMAGE TO EQUIPMENT CAN OCCUR
WHEN HYDRAULIC POWER IS SUPPLIED.
(3)
Pressurize the right and center hydraulic systems (Ref 29-11-00).
S 864-018
(4)
AIRPLANES WITH STAB TRIM LEVERS ON THE CONTROL STAND; use the STAB TRIM levers to move the stabilizer to the APL NOSE DN and APL NOSE UP travel limits.
S 214-019
(5)
Make sure the position indicators follow the stabilizer movement correctly through its full travel range.
S 864-020
(6)
AIRPLANES WITH ALTERNATE STAB TRIM SWITCHES ON THE CONTROL STAND; use the alternate stabilizer trim switches to move the stabilizer to the APL NOSE DN and APL NOSE UP travel limits.
S 214-021
(7)
Make sure the position indicators follow the stabilizer movement correctly through its full travel range.
S 864-022
(8)
Move the stabilizer to its neutral position.
S 214-023
(9)
Make sure the position indicators show 4 units of trim (neutral position).
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E. Put the Airplane Back to Its Usual Condition
S 864-024
(1)
Remove the power from the right and center hydraulic systems (Ref 29-11-00).
S 864-025
(2)
Remove electrical power if it is not necessary (Ref 24-22-00).
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TRAILING EDGE FLAP SYSTEM - DESCRIPTION AND OPERATION
_____________________________________________________
1. General_______
A. Introduction (Fig. 1, Fig. 2)
(1)
The trailing edge flaps provide extra aircraft lift during takeoff and landing. When extended the flaps operate in conjunction with leading edge slats to effectively increase camber and area of the wings.
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