H26807
Control Cabin Window Inner Pane Chip Identification 500
56-11-0 Figure 201 Feb 20/87
Page 204
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
500 Glass Cockpit Window Cross Section of Edge Showing Vinyl Interlayer Cracking
Oct 20/91 Figure 202 (Sheet 1) 56-11-0
Page 205
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Glass Cockpit Window Cross Section of Edge Showing Vinyl Interlayer Cracking 500
56-11-0 Figure 202 (Sheet 2) Oct 20/91
Page 206
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
G. The vinyl interlayer core ply is susceptible to cracking and shrinking. Vinyl interlayer cracks or tears occur most often in the upper aft and lower inboard corners of the No. 1 window. Vinyl cracks can occur at the edge of the slip panes or the separator material anywhere around any glass cockpit window. The cracks usually appear as a thick or broken line or as hash marks in the vinyl interlayer along the edge of the slip panes or the separator material. Usually, but not always, the cracks will be perpendicular to the inner and outer panes and have depth which can be detected. Do not confuse vinyl cracks with wrinkles in the slip pane material. Windows that develop cracks in the vinyl interlayer should be replaced. The vinyl core is required for fail-safe capability should the structural inner glass pane crack.
500
Oct 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 56-11-0 Page 207
FIXED CONTROL CABIN WINDOWS - APPROVED REPAIRS
1. General
A. Aerodynamic smoother (sealant), installed around all control cabin windows, is subject to erosion and cracking and must be maintained in good condition to ensure longest possible window life.
B. Fairing compound is installed on the window frames of control cabin windows No. 1, 4 and 5. Whenever the fairing compound is cracked, chipped, broken or damaged in any way, the fairing compound should be repaired before installation of the window.
NOTE: An exception is local crushing of the fairing compound, around the ends of the spacers installed with the window assembly; this condition does not require repair.
2. Aerodynamic Smoother (Sealant) - Approved Repairs
A. Equipment and Materials
(1)
Masking Tape - No. 221 (Ref 20-30-51)
(2)
Aliphatic Naphtha - TT-N-95A, Type II (Ref 20-30-31)
NOTE: Freon-TF may be used in lieu of aliphatic naphtha for general cleaning of windows.
(3)
Polysulfide Sealant (Preferred for longer life) - PR 1425 (Ref 20-30-11)
(4)
Polysulfide Sealant (Alternate) - Pro Seal 860 class B (Ref 20-30-11)
(5)
Polysulfide Sealant (Alternate) - BMS 5-26 (Ref 20-30-11)
(6)
Polysulfide Sealant (Alternate) - BMS 5-79 (Ref 20-30-11)
(7)
Cheesecloth -lint- and oil-free
(8)
Spatula
(9)
Sealant Gun -Semco Model 250
B. Repair Aerodynamic Smoother (Sealant)
(1)
Check that power is OFF in window heating circuit.
WARNING: OUTPUT VOLTAGE OF AUTOTRANSFORMER RANGES FROM 250 TO 350 VOLTS. BE CAREFUL WHEN WORKING ON CONTROL CABIN WINDOWS.
(2)
Remove all sealant that is cracked, eroded or not bonded to glass.
CAUTION: USE PLASTIC TOOLS ONLY TO PRECLUDE SCRATCH DAMAGE.
(3)
Clean remaining sealant and adjacent window and frame with cheesecloth wetted with aliphatic naphtha.
(4)
Apply masking tape on glass and window frame where sealant is to be applied.
(5)
Mix sealant according to manufacturer's instructions.
(6)
Inject sealant with sealant gun to completely fill gap between frame and glass and to provide a small excess. Use care and proceed slowly to prevent voids or entrapment of air in sealant.
NOTE: Refer to par. 1. General concerning sealant to be used.
(7)
Smooth and shape excess sealant with spatula or by hand to shape shown in Fig. 801 and 802.
(8)
Removing masking tape before sealant skins over or begins to set.
(9)
Allow sealant to cure per Fig. 803.
CAUTION: WET CHEESECLOTH ONLY. EXCESS SOLVENT COULD PENETRATE WINDSHIELD LAMINATIONS, CAUSING DAMAGE.
500
May 01/01 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 56-11-0 Page 801
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