(d)
Insert rigging pin R-5 in feel and centering unit output crank. Rigging pin shall enter easily without movement of output crank.
(e)
Check alignment of index mark on standby actuator valve input crank and center mark on actuator body. 1) If marks align, proceed to step (h). 2) If marks do not align but misalignment is less than 0.02 inch, proceed to step (f). 3) If marks do not align and misalignment is more than 0.02 inch, proceed to
step (g).
(f)
Adjust control rod (fine adjustment) as follows: 1) Loosen both checknuts on rod assembly and back them off a few turns. 2) Turn tube until index marks align. One full turn at tube moves index mark
approximately 0.006 inch.
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3) Tighten both checknuts.
4) Proceed to step (h).
(g) Adjust control rod (coarse adjustment) as follows: 1) Position flight control switches A and B on forward overhead panel to OFF.
CAUTION: HYDRAULIC POWER MUST BE OFF FOR THIS PROCEDURE.
2) Loosen both checknuts on rod assembly.
3) Remove bolt connecting aft end of rod to actuator.
4) Turn aft rod end and tube together and/or aft rod end alone in the same
direction. Half a turn of one rod end moves index mark approximately 0.015
inch. 5) Install clevis bolt at aft end of rod. 6) Position flight control switches A and B to ON. 7) Repeat fine adjustment starting at step (b).
(h)
Check for minimum thread engagement on rod. Rod end threads must be visible through inspection holes in tube at both ends.
(i)
Remove rigging pin R-5.
(j)
Restore airplane to normal hydraulic configuration. Refer to 27-21-0.
(k)
Test rudder and rudder trim control system per paragraph 2.
2. Rudder and Rudder Trim Control System Test
A. General
(1)
The test may be performed without removing components, breaking into hydraulic systems, or using rigging pins.
(2)
Refer to figure 506 for method of measuring large and small rudder travel. Left and right rudder travel measurements when testing rudder are made with respect to left aft corner of indicator on index tab and lower inboard corner of rudder trailing edge.
(3)
The rudder and rudder trim control system must be completely installed and rigged prior to test.
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WARNING: RUDDER, ELEVATOR, AND AILERONS ARE FULLY POWERED SYSTEMS. ALL THREE SYSTEMS ARE POWERED SIMULTANEOUSLY. CHECK TO ENSURE THAT PERSONNEL AND OBSTRUCTIONS ARE CLEAR OF ALL CONTROL SURFACES BEFORE TURNING POWER ON. ALSO THE RUDDER, RUDDER PEDALS, AND RUDDER TRIM KNOB SHOULD BE IN NEUTRAL AND ALL RIGGING PINS AND OTHER OBSTRUCTIONS REMOVED FROM THE SYSTEM BEFORE TURNING POWER ON.
PRECAUTIONS SHOULD BE TAKEN TO PREVENT INADVERTENT APPLICATION OF HYDRAULIC POWER DURING THE POWER OFF PORTIONS OF THIS TEST.
CAUTION: WHEN MOVING RUDDER SURFACE BY EXTERNAL FORCE ALWAYS USE LOADING BLOCK TO PREVENT DAMAGE TO RUDDER. APPLY EXTERNAL FORCE APPROXIMATELY 46.9 INCHES FROM RUDDER HINGE LINE BETWEEN RUDDER STATIONS 13.33 and 31.65. DO NOT EXCEED A LOAD OF 50 POUNDS ON RUDDER AT ANY TIME.
(4) Rudder neutral position is defined as the position at which both sides of rudder trailing edge are within width of tab on rudder index plate (Fig. 506) and when rudder pedals are adjusted per step 1.C.(3).
B. Equipment and Materials
(1)
Rudder Loading Block and Dial Indicator
(a)
Loading block to distribute loads over a minimum of 5 square inches of rudder trailing edge. Suggested loading block: 0.125 inch thick (minimum) by 3 inches by 3 inches approximately. Wood or fiberglass, suitably padded to prevent skin damage.
(b)
Dial indicator with a minimum range of 0.00 to 0.04 inch plus mounting stand for measuring small rudder movements. Measuring point shall be approximately 46 inches from rudder hinge line at lower end of trailing edge.
(2)
Rudder Pedal Force Check Tool - F80212-19 (Preferred) or F80212-1 (Optional)
(3)
Scale - 0 to 2 feed, graduated in inches, tenths and hundredths of an inch
(4)
Rudder Trim Knob Torque Adapter -SE27-2011
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C. Test Rudder and Rudder Trim Control System
(1)
Test rudder pedal adjustment and rudder pedal limit travel.
(a) 中國航空網 www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(114)
