F. Make sure the bolt threads and nut threads are free of grease. Tighten nuts on inboard side 440 to 650 pound-inches.
G. Make sure the bolt threads and nut threads are free of grease. Tighten nuts on outboard side 350 to 900 pound-inches and install cotter pin.
H. Install nuts, washers, and bolts securing forward ends of thrust links to forward engine mount. Tighten nuts 630 to 950 pound-inches. If required, tighten nuts at aft ends 630 to 950 pound-inches.
I. Install detector support bracket on forward engine mount.
J. Install seals between firewall and forward engine mount (AMM 51-31-0/201).
5. Restore Airplane to Normal
A. Install engine (AMM 71-00/401).
B. Install access panels.
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C21513 F59600
501 No. 2 Engine Shown, No. 1 Opposite
May 01/01 Forward Engine Mount Installation 54-41-11
Figure 401 (Sheet 1) Page 403
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Forward Engine Mount Installation 500
54-41-11 Figure 401 (Sheet 2) May 01/99
Page 404
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
FIBER WASHER - REMOVAL/INSTALLATION
1. Equipment and Materials
A. Adhesive - BMS 5-14, Synthetic Rubber Buna N Cement
2. Remove Asbestos Fiber Washer (Fig. 401)
A. After power plant is removed, remove aft vibration isolator (Ref 71-21-11 R/I).
B. Remove asbestos fiber (hex) washer from firewall pan.
NOTE: Asbestos fiber (hex) washer is cemented to firewall pan with BMS 5-14 adhesive.
3. Install Asbestos Fiber Washer (Fig. 401)
A. Check that overall dimension across flanges of hex-head flap track bushings is 4.72 +0.02/-
0.02 inches. Adjust bushings (using a wrench on each bushing) as required.
B. Clean firewall pan in area where asbestos fiber (hex) washer is to be installed per Overhaul Manual, 20-50-12, Application of Adhesives.
C. Cement asbestos fiber (hex) washer to firewall pan over hex flats of each bushing per Overhaul Manual, 20-50-12, Application of Adhesives.
D. Check again dimension obtained in step 3.A. except this time measure overall dimension across asbestos fiber (hex) washers. Trim asbestos fiber (hex) washers equally as necessary.
NOTE: Asbestos fiber (hex) washer is manufactured thicker than bushing head to assure complete coverage of bushing head under adverse tolerance stackup. Asbestos fiber (hex) washer may be trimmed back to allow proper installation; however, do not trim past a point flush top of bushing heads.
E. Install aft vibration isolator (Ref 71-21-11 R/I).
500
Sep 20/81 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 54-41-21 Page 401
E38916 E39039 E39107
Fiber Washer Installation 501
54-41-21 Page 402 Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/94
501 Fiber Washer Installation
Aug 01/94 Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 54-41-21 Page 403
Fiber Washer Installation 501
54-41-21 Page 404 Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Aug 01/94
ENGINE-TO-WING FAIRING - DESCRIPTION AND OPERATION
1, General
A. The engine-to-wing fairing is an aerodynamic titanium cover between the engine and the wing (Fig. 1). The fairing is divided into an aft fairing, a midfairing and a forward fairing. The removable aft fairing is cantilevered aft from thje wing rear spar. The midfairing is attached to the lower wing skin between the wing front and rear spars by means of angles. The forward fairing is removable and is attached to the forward end of the midfairing and the top side of the nose cowl by means of latches.
B. On airplanes without a honeycomb energy absorber on the aft mount, a red stripe is installed at the aft end of the aft fairing. The red stripe will come in to view is there is a structural failure at the aft engine mount allowing the nacelle to say.
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