(q) If power control unit input rod required a coarse adjustment, the neutral shift sensor must be readjusted per Chapter 22, Elevator Neutral Shift Sensor -A/T.
(4) Adjust Neutral Shift Input Rods
(a)
Remove elevator systems A and B hydraulic power per 27-31-0 and check that horizontal stabilizer B dimension is set at 41.57 士0.04 inches.
(b)
Ensure that mach trim actuator is set in null position (Ref 27-31-0, MP).
(c)
Check for 1.25 士0.03-inch dimension between centerline of neutral shift crank and vertical bulkhead (View 1, Fig. 507). If required dimension does not exist, adjust per the following steps:
(d)
Disconnect feel and centering unit output rod from aft control quadrant crank.
(e)
Break lockwire from checknuts at aft end of both neutral shift input rods and back off index washer and checknut. Remove aft mounting bolts and detach rods from neutral shift crank.
(f)
Adjust length of left neutral shift input rod until 1.25士0.03-inch dimension is obtained between centerline of neutral shift crank and aft side of vertical bulkhead. Alternately rotate rod end fitting, and insert mounting bolt, until dimension is obtained.
(g)
Adjust other neutral shift input rod until mounting bolt can be easily installed. Tighten rod end checknuts on both rods and lockwire.
(h)
Attach input rods to neutral shift crank.
(i)
Adjust feel and centering unit output rod per par. C.(5).
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G08809
Feel and Centering Unit Input and Output Rod Adjustment 551
27-31-0 Figure 507 Oct 20/84
Page 516
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(5) Adjust Feel and Centering Unit Output Rod
(a)
Remove elevator systems A and B hydraulic power per 27-31-0, MP and check that horizontal stabilizer B dimension is set at 41.57 士0.05 inches.
(b)
Set mach trim actuator in null position (Ref 27-31-0, MP).
(c)
Install rigging pin E-5 in aft control quadrant.
(d)
Loosen two checknuts on feel and centering unit output rod (Fig. 507).
(e)
Remove locknut from bolt assembly and detach output rod from aft control quadrant crank by removing bolt assembly.
(f)
Check relationship between bolt hole in output rod and bolt hole in aft control quadrant crank.
(g)
If mismatch is greater than 0.06 inch, rotate clevis in sleeve 1/2 turn and/or sleeve in rod 1/2 turn (coarse adjustment). Repeat, if required, to reduce mismatch to below
0.06 inch.
NOTE: Always turn clevis and sleeve in the same direction, keeping number of threads exposed approximately equal in both parts.
(h)
If mismatch is less than 0.06 inch, rotate sleeve until bolt can be easily installed (fine adjustment).
(i)
Install bolt assembly and tighten outer bolt 75 to 85 pound-inches torque, then install locknut over end of inner bolt and tighten 15 to 20 pound-inches.
CAUTION: AFTER SETTING TORQUE ON LOCKNUT, DO NOT ATTEMPT TO RESET TORQUE ON OUTER BOLT.
(j)
Check output rod for minimum thread engagement. Combined number of threads visible on clevis and sleeve shall not exceed 27.
(k)
Remove rigging pin E-5.
(l)
If feel and centering unit output rod required a coarse adjustment, adjust neutral shift sensor per Chapter 22, Elevator Neutral Shift Sensor - A/T.
500
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(6) Adjust Elevator Tab Pushrods (Airplanes with Metal-Fiberglass Elevators)
NOTE: Measure tab position from inboard edge of trailing edge.
(a)
Remove elevator systems A and B hydraulic power (Ref 27-31-0 MP).
(b)
Check that horizontal stabilizer B dimension is set at 41.57 士0.05 inches and that mach trim actuator is in null position per 27-31-0 MP.
(c)
Hold elevator trailing edge in line with index on tail cone within 0.04 inch and check that both elevator tabs are displaced 0.22士0.01 inch up from elevator trailing edge. If this condition is not met, adjust tab pushrods per following steps (d) thru (u).
(d)
Remove lower inboard hinge cover located on lower forward inboard edge of elevator by removing 19 bolts (Fig. 508).
(d1) Remove lower aerodynamic seal located on lower aft edge of horizontal stabilizer by removing attach bolts (Fig. 508). It is not necessary to remove all bolts in order to access tab pushrods. 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 2(66)
