(5)
Loosely install eleven bolts (5) up through forward end of balance panel (3), idler hinge seal (10) and idler hinge (9).
(6)
Ensure idler hinge seal remains slack for any elevator position, then tighten bolts.
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27-31-41 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/01
CAUTION: WHEN CONNECTING BALANCE PANEL TO IDLER HINGE, ENSURE IDLER HINGE IS DEFLECTED DOWNWARD FROM STABILIZER SUPPORT BEAM.
D. Install bulb seals (2) at inboard and outboard ends of balance panel (3) as follows:
(1)
Loosely install bolts up through bulb seal and balance panel.
(2)
Airplanes with composite elevators, install each bulb seal with a clearance of 0.02 ±0.01 inch between seal and rib.
(3)
Airplanes with fiberglass aluminum elevators,install each bulb seal with a clearance of
0.02 +0.01 inch between seal and stabilizer trailing edge rib (1).
(4)
Maintain 0.20 inch gap between forward end of balance panel bulb seal (2) and aft end of idler hinge flat seal (7).
NOTE: If necessary, loosen idler hinge flat seal bolts and reposition flat seal to obtain gap, then repeat steps 5.B.(2) and (3).
(5)
Tighten balance panel bulb seal bolts.
E. Remove rigging pin E-5 from aft control quadrant.
F. Perform test procedure (Ref 27-31-41 A/T).
G. Close or replace all access doors and panels.
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Apr 01/97 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-41 Page 405
ELEVATOR BALANCE PANELS - ADJUSTMENT/TEST
1. Elevator Balance Panels Test
A. Equipment and Materials
(1)
Trammel Bar - F80055-1, or equivalent
(2)
Spring scale - 0- to 15-pound capability, graduated in 1-pound increments
(3)
Loading block - 17 inches long, 2 x 4 wood block or equivalent
(4)
Scale - 0 to 2 feet, graduated in inches and tenths of an inch
(5)
Scale - 0 to 6 inches, graduated in tenths and hundredths of an inch
B. Prepare for Test
(1)
Remove elevator systems A and B hydraulic power. Refer to 27-31-0, Elevator and Tab Control System - Maintenance Practices.
(2)
Set horizontal stabilizer B dimension at 41.57 (+ 0.05) inches, using trammel bar. (See figure 501.)
(3)
Rotate control columns fully forward and secure in this position. Tag the columns.
(4)
Remove bolts securing aft end of each elevator control pushrod to its respective elevator. (See figure 502.)
CAUTION: DO NOT PERMIT INNER RACE OF ELEVATOR MAST FITTING CRANK BEARING TO ROTATE TO A POSITION WHERE ROLLERS MAY DROP OUT THROUGH HOLE IN INNER RACE.
(5)
Rotate control columns fully aft to withdraw each elevator control pushrod clevis from the elevator lugs. When column aft stops are contacted, secure control columns in this position. Tag the columns.
C. Test Elevator Balance Panels
(1) Measure breakaway forces required to move elevator. Use spring scale and a loading block and apply force to elevator rear spar adjacent to elevator inboard rib.
(a)
Move elevators by hand until trailing edges align with index marks on tail cone, then release. (See detail A, figure 502.)
(b)
If the right elevator moves after releasing it at the neutral position (index mark), record the maximum force required to slowly move it back to the neutral position. Record the force at the time the elevator reaches the neutral position. Record the difference between these two forces.
(c)
If right elevator trailing edge remains at the index mark, measure force required to move trailing edge up to 2.0 (± 1.0) inches from index mark. Add this force to force required to move trailing edge down 2.0 (± 1.0) inches from index mark. Record sum of these two forces.
(d)
If the left elevator moves after releasing it at the neutral position (index mark), record the maximum force required to slowly move it back to the neutral position. Record the force at the time the elevator reaches the neutral position. Record the difference between these two forces.
(e)
If left elevator trailing edge remains at index mark, measure force required to move trailing edge up 2.0 (± 1.0) inches from index mark. Add this force to force required to move trailing edge down 2.0 (± 1.0) inches from index mark. Record sum of these two forces.
(f)
The forces recorded in steps (b), (c), (d), or (e) shall not exceed 1 pound.
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Feb 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-41 Page 501
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