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时间:2011-03-30 10:22来源:蓝天飞行翻译 作者:航空
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25-00-11 Page 222  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/76 


CAUTION:  EXTREME CARE SHOULD BE TAKEN TO AVOID OVERHEATING NYLON PART DURING BUFFING OPERATION. BURNISHING OF THE PART WILL RESULT AND CAUSE DISCOLORATION.
(4)  
Removal of Mold Lines

(a)  
Mold lines shall be removed, using a small disc sander (No. 400 or finer sandpaper).

(b)  
Mold lines shall be sanded away, using very light pressure.

CAUTION:  CARE MUST BE TAKEN NOT TO SAND INTO PARTS MOLDED SURFACE.

(c)  
Procedure outlined in (3) (d) shall be used if polishing is required.

 

(5)  
Removal of Gate Flash


NOTE:  Gate flash is that excess of material which usually remains on any injection molded part after part has been ejected from mold and sprue and runners have been removed.
(a)  
A small amount of flash shall be removed, using procedure outlined in (4) (a).

(b)  
A large amount of flash shall be removed, using a spindle shaper.

(c)  
After removing gate flash with spindle shaper, shaper marks shall be removed, using No. 400 wet or dry sandpaper (sand dry).

(d)  
Surface gloss shall be restored using Learock Type BS-30 or Type B-815 buffing compound.


Aug 15/76  25-00-11
Page 223
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

N.  Repair Method No. 12
(1) 
 General

(a)  See Repair Method No. 12 (patching), except that vinyl for repairing vinyl-aluminum laminates shall be obtained from scrap vinyl-aluminum materials as follows:

(2)  
Equipment and Materials

(a)  
X-Acto knife

(b)  
Scrap material

(c) 
 Heat 1amp

(d) 
 Soldering iron

 

(3)  
Repair: (Patching of Munster Textural Vinyl-Aluminum Laminate)

(a)
Using an X-Acto Knife, cut a square of vinyl in scrap vinyl-aluminum material.

NOTE:  This square shall be larger than damaged area in order that a cupcake patch may be made as in Repair Method 6.

(b)  
Heat shall be applied locally to metal side of laminate opposite square cut in vinyl, using a heat lamp, soldering iron, or other heating device.

(c)  
When laminate has heated up, knife blade or other similar tool shall be used to lift out square of vinyl material.

CAUTION:  EXERCISE CAUTION WHEN REMOVING VINYL AS IT WILL STRETCH VERY EASILY RESULTING IN TEXTURE DISTORTION.

(d)  
When patch material has been removed from scrap aluminum laminate, proceed with patch repair, Method No. 6.

 


O.  Repair Method No. 13
(1) 
 General

(a)  This method describes the procedures used to repair holes which completely penetrate vinyl-aluminum panels.

(2)  
Equipment and Materials

(a) 
 Drill

(b)  
Adhesive, Eastman 910

(c)  
Backing Plate, Aluminum

(d)  
Epibond No. 126

(e)  
Ferro No. 7005 White (Titanium Dioxide Pigment)

(f) 
 Calcium Carbonate

(g)  
Glass Cloth, Volan No. 128

(h)  
Mylar Film

(i)  
Resin

(j)  
Hardener, HN 9812

 


25-00-11  Aug 15/76
Page 224
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

(3)  Repair: (Holes in Vinyl-Aluminum Panels)
(a)  Repair of holes less than 1/2 inch in diameter in solid colored or silk screened vinyl-aluminum panels. 1) Damaged area shall be made circular and uniform in size, using a drill or other
suitable tool. Remove all burrs. 2) A piece of embossed mylar shall be taped tightly over hole in decorative (vinyl) side of laminate. 3) Accurately weigh and thoroughly mix the following materials:
10.0 parts by weight - Epibond 126
6.5 parts by weight - HN 9812 Hardener
1.5 parts by weight - Ferro No. 7005 White Titanium Dioxide Pigment
1.5 parts by weight - Calcium Carbonate 4) From non-decorative (aluminum ) side of panel, sufficient resin shall be applied
to fill damaged area.
5)  Resin shall be swept and faired to panel contour.
6)  A piece of Volan No. 128 glass cloth, approximately 1/4 to 1/2 inch larger than
diameter of hole, shall be impregnated with above mixture.
7)  Impregnated glass cloth shall be placed over hole on non-decorative (aluminum)
side of panel. Sweep glass down tightly over hole and onto panel. 8) Resin shall be allowed to cure eight hours at 70°F or two hours at 120°F. 9) After cure, mylar film shall be stripped from resin.
 
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