(2)
Loosen the heat shield fasteners sufficiently to gain access to the flow passages in the midfairing cavity cross members.
C. Clear Drains (Fig. 601)
(1)
Use 25-35 psig regulated air supply to clear drain line sections.
(a)
Block drain inlet in aft midfairing cavity with plug.
(b)
Apply air pressure to drain line outlet on fixed fairing, while covering pneumatic duct pan assembly drain inlet in forward midfairing with rags to collect debris.
(c)
Remove rags and debris from pneumatic duct pan assembly cavity.
(d)
Plug pneumatic duct pan assembly drain inlet.
(e)
Apply air pressure to drain line outlet on fixed fairing, while covering aft drain inlet with rags to collect debris.
(f)
Remove rags and debris from aft cavity.
(2)
Check for debris clogging flow passages in midfairing cavities cross members. Use air pressure to blow clear if necessary.
(3)
Inspect drain lines for dents or other damage.
D. Return Airplane to Normal
(1)
Check that tools and loose materials are removed and midfairing cavities are free of debris before installing access doors and panels.
CAUTION: TOOLS, LOOSE MATERIAL, AND DEBRIS IN MIDFAIRING CAVITIES MAY BLOCK DRAINS RENDERING DRAIN SYSTEM INEFFECTIVE.
(2)
Install heat shield to firewall.
(3)
Install midfairing access doors and panels.
500
Oct 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 54-10-02 Page 601
Midfairing Drain Locations 500
54-10-02 Figure 601 (Sheet 1) Oct 20/89
Page 602
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Midfairing Drain Locations
Oct 20/89 Figure 601 (Sheet 2) 54-10-02
Page 603
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ENGINE FIREWALL - DESCRIPTION AND OPERATION
1. General
A. Within the engine-to-wing fairing, a vapor-tight stainless steel firewall, and a radiation shield are installed as fire and heat protection. (See figure 1.) An armor plate is installed between nacelle stations 136 through 158 on the firewall.
500 Engine Firewall
Feb 15/68 Figure 1 54-11-0
Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ENGINE COWLING - DESCRIPTION AND OPERATION
1. General
A. The engine cowling consists of a nose dome, a nose cowl, two movable cowls, a fixed upper cowl, and thrust reverser fairings (Fig. 1). Refer to Chapter 54 of the Structural Repair Manual for skin identification.
B. The nose cowl has access openings for inspection and maintenance of the thermal anti-icing duct. The movable cowls have access openings for maintenance of engine accessories.
2. Nose Dome and Nose Cowl
A. The nose dome is mounted on stubs forward of the inlet guide vanes. The nose cowl is attached to the forward flange of the engine inlet case. An acoustical panel, with a drain, is installed on the inside of the nose cowl.
3. Movable Cowls and Fixed Upper Cowls
A. Movable cowls are installed on the left and right side of each engine. The structure of the movable cowl consists of frames and aluminum skin. A fireshield is attached to the upper section of the movable cowl. The movable cowl is mounted on the fixed cowl by means of latches.
(1) The movable cowl has two pressure relief doors. Each door is held by a latch which will yield to excessive pressure inside the cowl and allow the door to open.
B. The structure of the fixed cowl consists of stainless steel skin, frames and support brackets. The fixed cowl is attached to frames on the engine. When the engine is removed, the fixed fairing rests on support fittings attached to the forward engine mount and the engine-to-wing midfairing firewall.
4. Thrust Reverser Fairing
A. The thrust reverser , with associated fairings and doors, is described in Chapter 78, Exhaust.
538
Aug 15/73 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 54-31-0 Page 1
Engine Cowling 540
54-31-0 Figure 1 Nov 01/74
Page 2
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
ENGINE ATTACH FITTINGS - DESCRIPTION AND OPERATION
1. General
A. The engine is attached at the forward end to a steel forging. This steel forging is suspended from wing structure in the following manner: One the inboard side, the steel forging is connected directly to a fitting attached to heavy lower wing skin immediately aft of the wing front spar, and on the outboard side, the steel forging is connected to a fitting attached to the forward side of the wing front spar with an intermediate short link (Fig. 1).
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