C.
Procedure
S 865-060
(1)
Do a check of the input to the rudder power control unit (AMM 27-21-00/501).
S 865-061
(2)
If a small rudder trim input is necessary (0.2 to 0.3 units) and the system is correctly adjusted, put the rudder trim at the center:
(a)
Set the rudder trim knob at the position necessary for a straight flight (in a range of 0.2 to 0.3 unit).
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL
_______ CONTROL SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDERS, ELEVATORS, TRAILING EDGE FLAPS, LEADING EDGE FLAPS AND SLATS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY TO PERSONS OR DAMAGE TO EQUIPMENT.
(b)
Pressurize hydraulic systems A and B (AMM 27-21-00/201).
(c)
Loosen two index plate bolts from the tail cone.
S 865-049
(3)
Put the index plate at a position where the two sides of rudder trailing edge are in the width of the tab on the index plate.
S 435-050
(4)
Tighten the index plate bolts.
S 865-085
(5)
Set the rudder trim knob to zero.
S 825-052
(6)
Adjust the input of the main and standby power control units to align the rudder with the new index position (AMM 27-21-00/501).
TASK 27-09-71-865-053
9. Rudder Standby Power Discrepancy Correction___________________________________________
A. References
(1) AMM 27-21-00/501, Rudder and Rudder Trim Control System
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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
B. Access
(1)
Location Zone
706 Vertical Stabilizer
708 Rudder
C.
Procedure
S 865-086
(1) Do a check of the input to the rudder standby power control unit (AMM 27-21-00/501).
TASK 27-09-71-865-055
10. Elevator Power Off Discrepancy Correction_________________________________________
A. References
(1)
AMM 27-31-00/501, Elevator and Tab Control System
B.
Access
(1)
Location Zone
711 Elevator and Tab, LH
712 Elevator and Tab, RH
C.
Procedure
S 865-058
(1)
Do a check of the adjustment of the elevator and tab control system (AMM 27-31-00/501).
S 715-059
(2)
Do the elevator power off flight test (AMM 27-31-00/501).
TASK 27-09-71-865-057
11. Leading Edge Slat Trailing Edge Clearance Mismatch Record_________________________________________________________
A. Access
(1)
Location Zone 302 Wing Outboard Leading Edge with Slats, LH 402 Wing Outboard Leading Edge with Slats, RH
B.
Procedure
S 225-056
(1) Make sure the clearances of the leading edge slat trailing edge are as specified (Fig. 506).
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A 737-300/400/500MAINTENANCE MANUAL
SLAT SYMMETRY
TE CLEARANCE
1 TE CLEARANCE
1 TE CLEARANCE
1
SLAT 1 __________ SLAT 2 __________ SLAT 3 __________
SLAT 6 __________ SLAT 5 __________ SLAT 4 __________
DIFFERENCE __________ (0.25 INCH)DIFFERENCE __________ (0.25 INCH) DIFFERENCE __________ (0.25 INCH)
THE CLEARANCE OF THE LEADING EDGE SLAT IS MEASURED FROM THE TE OF A SLAT
(IN THE FULLY EXTENDED POSITION) TO THE FIXED LEADING EDGE SKIN.
THE TE CLEARANCE AT EQUIVALENT ENDS OF THE OPPOSITE SLATS WILL BE
SYMMETRICAL TO A LIMIT OF 0.25 INCH.
Leading Edge Symmetry Mismatch
Figure 506
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