(2)
Install hinge fitting to the elevator:
(a)
Place the hinge fitting into the elevator.
(b)
Install hinge bearing bolt, nut and cotter pin.
(3)
Install elevator tab (Ref par. 6).
557
27-31-31 Page 404 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Feb 20/91
D. Install hinge bearing (Airplanes with Composite Elevator Tab)
(1)
Install hinge bearing with grease to the hinge fitting.
(2)
Install hinge fitting to the elevator tab:
(a)
Lubricate the hinge fitting.
(b)
Temporarily install hinge fitting and shims in the elevator tab rear spar.
(c)
Drill holes in shims and hinge fitting to match existing locations in tab.
(d)
Remove the elevator tab and disassemble shims and fittings.
(e)
Install nut plates on the hinge fittings.
(f)
Apply parting agent to elevator tab spar in the fitting area.
(g)
Install shims and fitting with sealant on faying surfaces.
(h)
Install retaining screws and washers.
(i)
Use sealant to seal existing nut plate and apply fillet seal on edge of elevator tab skin and hinge fitting.
(3)
Install elevator tab (Ref par. 6A).
5. Prepare for Installation
A. Accomplish following:
(1)
Remove elevator systems A and B hydraulic power (Ref 27-31-0).
(2)
Check that rigging Pin E-5 is installed in aft control quadrant (Fig. 403).
(3)
Check for allowable wear at elevator tab hinges (Ref 27-31-31 I/C). Check wear at tab pushrod attach points per 27-31-121 I/C.
(4)
Check Fig. 404 for required number of tab adjust weights. Check balance bay No. 2 for number of tab adjust weights installed on lower surface of elevator nose (Fig. 402).
B. On airplanes with metal-fiberglass elevator tab, if a different elevator tab is being installed on the airplane, see Fig. 401 and proceed as follows:
(1)
Remove hinge-retaining screws from upper and lower surfaces of replacement elevator tab at each tab hinge fitting location. Retain tab inboard hinge bolt retainer at upper tab surface.
(2)
Withdraw each tab hinge fitting and assemble to mating hinge fitting at elevator rear spar.
(3)
Install hinge-bearing bolts with bolt heads outboard, at each tab hinge location. Install washers and nuts. Tighten nuts to torque specified in Fig. 401.
CAUTION: LONGER OR SHORTER BOLT CAN NOT BE SUBSTITUTED.
C. On airplanes with metal-fiberglass elevator tab, if a different elevator tab is being installed or if any tab hinge fittings on elevator rear spar were disturbed, check tab to elevator alignment as follows:
(1)
Install tab on hinge fittings at elevator rear spar.
(2)
Check that hinge-retaining screws can be inserted in upper and lower tab surfaces at each tab hinge location.
557
Feb 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 27-31-31 Page 405
G09436
Elevator Tab Adjust Weights Location Diagram 503
27-31-31 Figure 402 Aug 15/76
Page 406
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
(3) If screw holes at any hinge location are misaligned proceed as follows:
(a)
Withdraw hinge retaining screws and remove tab from elevator.
(b)
Back off four-hinge bracket attach bolts common to fitting and rear spar from misaligned tab hinge fitting at elevator rear spar.
(c)
Refit tab to elevator and install hinge retaining screws at all tab hinge locations except at hinge that is misaligned.
(d)
Lightly tap misaligned hinge fitting inboard or outboard until hinge retaining screws can be easily inserted.
(e)
Remove all hinge retaining screws, detach tab from elevator and tighten the four hinge bolts.
6. Install Elevator Tab (Airplanes with Metal-Fiberglass Elevators)
A. Manually rotate all hinge fittings through full travel in both directions and check that movement is smooth and without binding.
B. Install tab on hinge fittings at elevator rear spar. Shim as necessary for snug fit at hinge fitting. Maximum sum total of shims is 0.050 inch. Maximum allowable shim at either surface is 0.050 inch. Maximum allowable gap at one surface is 0.003 inch.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737 AMM 飞机维护手册 飞行操纵 FLIGHT CONTROLS 2(90)
