HORIZONTAL STABILIZER REAR SPAR
REAR SIDE AFT SPAR
ELEVATORS

HORIZONTAL STABILIZER SKIN AT REAR
SPAR
VERTICAL STABILIZER

METHOD OF BMS-3 APPLICATION
TO PREVENT OR RETARD FILIFORM CORROSION, APPLY TO RIVET HEADS AND PANEL EDGES WHERE THE PAINT SYSTEM HAS CRACKED OR FLAKED. WIPE OFF EXCESS.
APPLY TO ENTIRE TRUSS STRUCTURE.
APPLY TO ALL INSPAR STRUCTURE OF HORIZONTAL STABILIZER FROM ROOT TO TIP.
SPRAY FORWARD SIDE OF REAR SPAR WITH PARTICULAR ATTENTION TO UPPER AND LOWER SPAR CHORD. ACCESS IS THROUGH FRONT SPAR AFTER REMOVING LEADING EDGE (REF 27-41-21). REQUIRES EXTENSION TUBE FOR SPRAYING.
APPLY TO ENTIRE REAR SPAR CAVITY WITH PARTICULAR ATTENTION TO ATTACHMENT POINTS AND FAYING SURFACES. INCLUDE ACTUATOR CAVITY.
APPLY TO ATTACHMENT POINTS AND EXPOSED PORTIONS OF FRONT SPAR AND REAR SPAR. APPLY TO BALANCE PANELS.
APPLY TO FASTENER HEADS AND SKIN JOINT AT REAR SPAR - UPPER AND LOWER SURFACES. WIPE OFF EXCESS.
APPLY TO REAR SPAR CAVITY WITH PARTICULAR ATTENTION TO RUDDER HINGE POINTS AND FAYING SURFACES. REMOVE ACCESS PANELS AT BASE OF VERTICAL FIN (REF 12-31-51) AND APPLY TO CLOSEOUT PANEL AND FORWARD AND AFT FIN ATTACHMENT FITTINGS. APPLY TO ALL INSPAR STRUCTURE OF VERTICAL STABILIZER FROM ROOT TO TIP.
APPLY TO AREA BETWEEN CLOSURE ANGLES OF FIN TO BODY INTERSECTION.
Jan 20/82 51-21-91
Page 705
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

DESCRIPTION OF AREA
RUDDERS

RAM AIR DUCTS (SEE BBL 70.5 BELOW)
UPPER AND LOWER WING JOINTS AT BBL 70.5
WING REAR SPAR
FRONT SPAR

DRY BAY AREAS (INSPAR)
WING SKIN UPPER AND LOWER SURFACES & STRUCTURE
METHOD OF BMS 3-23 APPLICATION
APPLY TO EXPOSED PORTIONS OF FRONT SPAR AND RUDDER HINGE POINTS.
APPLY LIGHT SPRAY OF BMS 3-23 TO LOWER WING SKIN SURFACE WITH PARTICULAR ATTENTION TO FASTENER. HEADS AND SKIN JOINTS. WIPE OFF
EXCESS. 
 CAUTION:  APPLICATION SHOULD BE KEPT TO A MINIMUM SO THAT BMS 3-23 IS NOT FORCED INTO HEAT EXCHANGER. 

REMOVE FAIRINGS. APPLY LIBERALLY TO ALL SURFACES WITH PARTICULAR ATTENTION TO FASTENER HEADS AND FAYING SURFACES.
OPEN ACCESS DOOR ON INBOARD SIDE OF BBL
70.5 JOINT AND SPRAY ALL METAL SURFACES IN CAVITY CONTAINING RAM AIR DUCT.
SPRAY ENTIRE REAR SPAR AREA WITH PARTICULAR ATTENTION TO SPAR CHORDS TO WEB JOINT AND OTHER FAYING SURFACES.
APPLY TO ENTIRE FRONT SPAR AREA WITH PARTICULAR ATTENTION TO SPAR CHORDS TO WEB JOINT AND OTHER FAYING SURFACES. LOCALLY SHIELD DUCTING AND WIRING WHILE BMS 3-23 IS BEING APPLIED.
SPRAY DRY BAY AREAS (INSPAR) INCLUDING
INSPAR AREA OUTBOARD OF SURGE TANK.
APPLY LOCALLY TO DETERIORATED PAINT THAT EXHIBITS CORROSION AROUND FASTENER HEADS. PERMIT BMS 3-23 TO PENETRATE AROUND FASTENER HEADS FOR APPROXIMATELY 30 MINUTES, THEN WIPE OFF EXCESS WITH SOLVENT.
STRUCTURE COVERED BY WING TO BODY FAIRING EXCEPT UPPER AND LOWER WING/BODY SPLICE AREAS.
51-21-91 Jan 20/82
Page 706

BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

DESCRIPTION OF AREA
WING CENTER SECTION UPPER AND LOWER SURFACES
FUEL TANK FLAP TRACKS
FLAP TRACK FITTINGS
ENGINE FITTINGS
FLAPS
ANTENNAS OUTBD WING CAVITY NACELLE

METHOD OF BMS 3-23 APPLICATION
APPLY TO UPPER AND LOWER SURFACES WITH PARTICULAR ATTENTION TO FASTENER HEADS, JOINTS AND FAYING SURFACES.
APPLY TO ENTIRE SURFACE.

SPRAY FLAP TRACK FASTENERS AND CONNECTION POINTS.
APPLY TO EXTERIOR OF FLAP TRACK SUPPORT FITTINGS AT WBL 254 AND WBL 353, LH AND RH INCLUDING EDGE OF FAYING SURFACE.
APPLY TO EXTERIOR OF ENGINE THRUST FITTING AT WBL 183, WBL 199 AND ENGINE MOUNT FITTING AT WBL 183, LH AND RH, INCLUDING EDGE OF FAYING
SURFACE. 
 CAUTION:  AS A FIRE SAFETY PRECAUTION, THE MATERIAL SHOULD BE KEPT AWAY FROM SURFACES THAT WILL ATTAIN 300°F OR MORE IN SERVICE. THE DRY FILM FLASH POINT IS 500°F. 

REMOVE ACCESS PANELS (REF CHAPTER 12) ON TOP OF MID FLAPS THAT EXPOSE THE FLAP CARRIAGE SPINDLE. APPLY BMS 3-23 TO THE SPINDLE BEARINGS AND SURROUNDING STRUCTURE.
SPRAY TRACK WELLS IN AFT EDGE OF MID FLAP.
SPRAY FULL INTERIOR SURFACE OF FLAP TRACKS.
APPLY BMS 3-23 BETWEEN ANTENNAS AND STRUCTURE UPON INSTALLATION OF ANTENNAS.
SPRAY ENTIRE INTERIOR SURFACE OF WING CAVITY AFT OF REAR SPAR BETWEEN WBL 525 AND WBL 546.
APPLY TO NOSE COWL COVERED BY FORWARD FAIRING.
APPLY TO INNER SURFACE OF FORWARD FAIRING.
Oct 20/85 51-21-91
Page 707
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

2.  Equipment and Materials

A.  Corrosion Inhibiting Compound - BMS 3-23 (Ref 20-30-21)
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 結構 STRUCTURES(23)