NOTE: NAS679C(-)W nuts are low permeability (nonmagnetic).
(6)
Install retaining angle bolts (14, Detail B). Maintain minimum gap requirements between bolts and windshield (Section B-B, Fig. 401). Tighten nuts 72 to 88 pound-inches.
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56-11-11 Page 408 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/92
CAUTION: NUMBER 1 WINDOW INNER PANE CAN BE CRACKED IF MINIMUM GAP BETWEEN RETAINING ANGLE BOLT AND WINDOW PANE IS NOT MAINTAINED.
NOTE: Adjacent sliding window must be open to permit insertion of special retaining angle bolts (14, Detail B, Fig. 401) attaching window retaining angle (15) and doubler (13) along aft edge of window (1) to window frame post (12). These bolts should be installed while window is retained by one finger-tight bolt in each remote corner, thus allowing some shift for proper alignment and easy installation of remaining bolts.
(7)
Tighten attaching nuts up finger-tight at first and then, using a staggered sequence (diagonally back and forth across window in a criss-cross pattern), tighten each nut to correct torque value. (See Fig. 403 for typical nut torque sequence and Fig. 401 for torque values).
(8)
Install checknut (19, Detail C, Fig. 401).
NOTE: Pressurized flight tends to bed any newly installed fixed window down in frame. As a result, after initial pressurization if leakage occurs, attaching nuts should be checked. Any loose nut should be retightened to a torque of not more than 5 pound-inches with checknuts removed. Damage can result if this torque is exceeded. Replace and tighten checknuts, while attaching nuts are being held. After this occasion, no further retightening should ever be done unless water or air leaks occur, in which case, retightening of attaching nuts should again be limited to a torque of 5 pound-inches. For self-locking attaching nuts, 5 pound-inches is the torque above run-on torque for nut.
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Jun 20/92 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 56-11-11 Page 409
Window No. 1 Retaining Bolt Torque Sequence 500
56-11-11 Figure 403 Feb 20/89
Page 410
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
C. Apply masking tape over outside gap between window and skins to prevent contamination prior to filling with nylon cord and smoother.
D. Remove strip of masking tape immediately over gap at outside edge of window. This can be done with a sharp knife so as to leave strips of masking tape protecting the edges of the gap.
E. Insert a clean, dry nylon cord, slightly longer than window perimeter, in bottom of gap at outside edge of window. The two ends should meet in the upper aft corner of the window frame and overlap approximately 0.5 inch.
NOTE: To ease insertion of cord, stretch it slightly and tamp down into gap with a spatula if necessary.
F. On PPG and Sierracin windows with Z-Channel strip, check resistance between Z-Channel and structure. If resistance is greater than one ohm, install wire mesh between Z-Channel and structure. Wire mesh may be added to all airplanes in lieu of the resistance check.
(1)
Remove paint from edge of frame structure where wire mesh contacts (4 places, one in middle of each side).
(2)
Refinish with chemical film treatment (alodine or Iredite).
(3)
Install 2 to 3 inch length of aluminum wire mesh near middle of each side of window in gap between Z-Channel and structure.
G. Inject aerodynamic smoother into the gap by means of a flow gun or with a spatula until the gap is completely filled. Do not trap air under the smoother. Apply smoother over bumper strip or Z-channel to overlap glass surface 0.15 ±0.03 inch.
(1) If airplane must be dipatched prior to sealant cure completion, cover sealant with Scotch Cal Tape. Remove tape when cure is complete.
CAUTION: SMOOTHER IS AVAILABLE WITH SEVERAL WORK LIVES TO SUIT A VARIETY OF JOBS. STEPS F, G, AND H, MUST BE COMPLETED DURING WORK LIFE SELECTED.
H. Remove excess filler, while still wet, with a tool until just level with the masking tape.
CAUTION: DO NOT ABRADE METAL OR GLASS SURFACES.
I. Remove masking tape from edges of gap and protective cover from outside surface of window. Smoother material lifting at edges of the gap can be smoothed over with a tool.
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Feb 20/91 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 56-11-11 Page 411
7. Restore Airplane to Normal Configuration
A. Connect power leads to window bus bar terminals.
CAUTION: CHECK THAT THE TRANSFORMER TAPS CONNECTED TO THE LEADS MATCH THE WINDOW RESISTANCE (REF 30-41-21 A/T). IMPROPER CONNECTION CAN CAUSE DAMAGE TO WINDOW OR HEATING CIRCUIT.
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