ELEVATOR HINGES -ADJUSTMENT/TEST
EFFECTIVITY
Airplanes with Aluminum/Fiberglass Elevators
1. Elevator Hinges Test
A. Equipment and Materials
(1)
Trammel Bar - F80055-1
(2)
Spring scale - 0- to 15-pound capability, graduated in 1-pound increments
(3)
Loading block - 17 inches long, 2 x 4 wood block
(4)
Scale - 0 to 6 inches
B. Prepare for Test
(1)
Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(2)
Set horizontal stabilizer B dimensions at 41.57 +0.05 inches, using trammel bar (Fig. 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 (Fig. 502).
(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 Hinges
(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 (Detail A, Fig. 502).
Jun 20/90 27-31-21 Page 501
(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.
G42332G09435
Stabilizer Trim Jackscrew Setting 500
27-31-21 Figure 501 Feb 20/93
Page 502
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Elevator Control Pushrod Attachment
Nov 15/67 Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-21 Page 503
(g) Move each elevator by hand through full travel in both directions. Movement shall be smooth and without binding.
D. Restore Airplane to Original Configuration
(1) Connect each elevator control pushrod to its respective elevator as follows:
(a)
Ensure both elevators are positioned with trailing edge fully down.
(b)
Release the control columns. Slowly rotate control columns fully forward and secure in this position. Tag the columns.
CAUTION: PROVIDE ASSISTANCE AT EACH ELEVATOR TO GUIDE ELEVATOR CONTROL PUSHROD CLEVIS ONTO ELEVATOR LUG AS CONTROL COLUMNS ARE ROTATED.
(c)
Connect each elevator control pushrod to its respective elevator. Install each mounting bolt with head facing inboard. Tighten first locknut to 500-600 pound-inches, then tighten second locknut to 150-220 pound-inches.
CAUTION: AFTER SETTING TORQUE ON SECOND LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON FIRST LOCKNUT.
(2)
Release control columns and allow columns to return to neutral position.
(3)
Restore airplane to normal hydraulic configuration. Refer to 27-31-0.
500
27-31-21 Page 504 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 15/73
ELEVATOR TABS - REMOVAL/INSTALLATION
1. General
A. The elevator tabs are balanced into the elevator system by adding or removing tab adjust weights on the elevator nose in balance bay No. 2 (Fig. 402). The number of adjust weights required is a function of tab part number and tab weight. The data plate on each tab is stamped with the tab weight. When replacing an elevator tab, the number of tab weights installed on the elevator nose must agree with the number called for in Fig. 404. If data plate is missing or if tab weight is changed (due to structural changes or repainting), check Chapter 51 of the Structural Repair Manual for tab adjust weight requirement.
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本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(88)
