曝光臺 注意防騙 網(wǎng)曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費(fèi)者

O.  On inboard flap, check that phenolic rub strip on nacelle fairing closure door contacts lower surface of hinge flap for its entire length. If adjustment is necessary loosen nut on pivot bolt located on the forward end of the closure door and rotate eccentric bushing to obtain contact. If necessary rotate eccentric one notch to align notch in eccentric with roll pin.
P.  On inboard hinged flap, check that gap between nacelle fairing closure door and nacelle fairing side wall is 0.02 inch minimum throughout flap travel. If not, add washer at forward pivot to obtain clearance.
Q.  On inboard hinged flap, check that clearance between nacelle fairing closure door and guide on foreflap torque tube is 0.12 inch minimum throughout flap travel. If not, loosen bolt and reposition serrated slotted guide to obtain required clearance.
R.  On outboard hinged flap, adjust seal and seal support between hinged flap and wing trailing edge lower panel per detail D, Fig. 401.
S.  Fill gap between support fitting and upper skin with sealant.
T.  Remove system A hydraulic power (Ref 27-51-0).
501 
27-51-51 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 20/89 

HINGED FLAP - INSPECTION/CHECK
1.  General
A.  This data consists of illustrations and wear limits charts. There will be no procedure given in this section for gaining access to, or removing and replacing the component after inspection for wear. Refer to Component - Removal/Inspection for this information.
2.  Hinged Flap Wear Limits

G13105 G13132
501  Hinged Flap Wear Limits 
Feb 01/75  Figure 601 (Sheet 1)  27-51-51 
Page 601 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Hinged Flap -Wear Limits  501 
27-51-51  Figure 601 (Sheet 2)  Feb 01/75 
Page 602 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

AFTFLAP ACTUATING MECHANISM BOOM - REMOVAL/INSTALLATION
1.  Equipment and Materials
A.  Rigging Pins - F-5 and F-6, 0.248 +0.000/-0.002 inch diameter, 3.7 +0.25-inches long
(MS20392-3)

NOTE: Rigging pins are a part of kit F70207-61, or -84.
B.  Protective cover - to fit aftflap
C.  Support - to support aftflap (with protective cover)
D.  Grease - MIL-G-23827 (Ref 20-30-21)
2.  Remove Aftflap Actuating Mechanism Boom
A.  Remove inboard flap track fairing (Ref 27-51-141 R/I).
B.  Provide system A hydraulic power (Ref 27-51-0 MP).
C.  Position flap control lever at 0-unit detent.
D.  Install rigging pins F-5 and F-6 in boom to trap boom roller between pins (Fig. 401).
E.  Remove system A hydraulic power (Ref 27-51-0 MP).
F.  Install protective cover on aftflap and position support under flap so that aftflap will not move when boom is disconnected.
G.  Install cable clamps on boom cables where they pass through midflap end rib. This will maintain some tension on cables in midflap to keep cables in proper drum grooves.
H.  Remove rigging pins F-5 and F-6.
I.  Remove bolt to disconnect boom from structure.
J.  Loosen cable adjusting nuts and disconnect cables from boom cable fittings.
K.  Pull boom aft and off of boom roller.
587 
Feb 20/88  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-61 Page 401 

G13164F96157 G42460
Aft Flap Actuating Mechanism Boom Installation  500 
27-51-61  Figure 401 (Sheet 1)  Aug 15/72 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

589  Aft Flap Actuating Mechanism Boom Installation 
Nov 15/80  Figure 401 (Sheet 2)  27-51-61 
Page 403 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

Aft Flap Actuating Mechanism Boom Installation  500 
27-51-61  Figure 401 (Sheet 3)  Aug 15/72 
Page 404 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

3. Install Aftflap Actuating Mechanism Boom
A.  Extend trailing edge flaps.
B.  Disconnect both rods from inboard flap aft segment.
C.  Disconnect boom assembly forward end.
D.  Position boom aft of boom roller and roll boom forward onto roller (Fig. 401). Partially retract trailing edge flaps sufficiently for clearance to move boom assembly.
E.  Make sure that cables are properly positioned in pulleys and cable ends are connected to boom cable sockets.
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊 飛行操縱 FLIGHT CONTROLS 3(18)