F.  Protective caps and closure for exposed oxygen system tubing
3.  Surface Preparation

A.  Remove external power and place battery switch in OFF position.
B.  Statically ground airplane (Ref 20-40-11, Static Grounding).
C.  If removable drain valves are installed, remove valves before application of BMS 3-23 (Ref 51-41-13).
D.  Vacuum surfaces as necessary to remove excess foreign matter.
E.  Clean surface with perchloroethylene.
NOTE:  Cleaning is required to enhance entry of corrosion preventive compound into surface to be treated and into faying surfaces.
F.  Mask area not to treated using masking tape and paper or plastic film.
G.  Mask disconnected electrical connector to prevent contamination of electrical contacts.
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H.  Do not apply BMS 3-23 corrosion inhibiting compound to actuator rods. BMS 3-23 or any hydrocarbon may cause seals used with Skydrol to swell.
I.  Use caution when applying BMS 3-23 in vicinity of silicone rubber seals or rubber lined clamps such as door and emergency exit hatch seals, grease seals in bearings, liners in hydraulic line or wire clamps.
J.  Oxygen system components must be shielded and protected from direct and indirect contact during application of BMS 3-23 corrosion inhibiting compound on adjacent structure.
WARNING:  CORROSION INHIBITING COMPOUND MUST NOT GET INTO OXYGEN SYSTEM AS MIXTURE IS POTENTIALLY EXPLOSIVE.
K.  Shield (do not mask) control cables, pulleys, teflon bearings and lubricated surfaces from direct application of corrosion inhibiting compound.
4.  Corrosion Inhibiting Compound Application
A.  Provide mechanical ventilation of enclosed areas such as spar cavities and cargo
compartments.

B.  Spray or brush a wet continuous coating of corrosion inhibiting compound on the cleaned surfaces to be treated.
C.  Allow material to remain on surface for a minimum of 30 minutes to aid penetration into faying surfaces.
D.  Allow coating to remain on surface for a minimum of 30 minutes to aid penetration into faying surfaces.
E.  Remove excess material from treated surface using clean wipers. Only a light film is necessary.
NOTE:  Excess material will not aid in additional corrosion protection but is detrimental because of dirt pickup.
F.  Remove all masking tape and protective paper or plastic film installed.
G.  Allow ventilation of enclosed areas to continue until evaporation of volatile solvents is complete before enclosing area.
5.  Corrosion Inhibiting Compound Removal
A.  Corrosion inhibiting compound may bleed through skin fasteners and appear on the airplane exterior as a brown discoloration. The exterior discoloration of excess corrosion compound found elsewhere may be removed by any of the following solvents: Perchlorethylene, Trichlorethane, Naphtha or Stoddard solvent (Ref 20-30-31).
NOTE:  Methyl Ethyl Ketone (MEK) or Acetone is not recommended.
B.  Ventilation requirements stipulated in par. 4 must be adhered to while removing corrosion inhibiting compound.
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FLOOR TRACK CORROSION PREVENTION - MAINTENANCE PRACTICES
1. General

A. This procedure describes steps required to protect floor tracks against corrosion under the galleys, galley work areas, or other limited lengths of track in corrosion prone areas.
2.  Equipment and Materials

A.  Sealant - BMS 5-95, Class B Pressure, Environmental, and Fuel Cavity replaced by BMS 5-125 Type I, Compound, Self Leveling, for fluid drainage (Ref 20-30-11)
B.  Corrosion Preventive Compound - MIL -C-11796, Class 2 (Ref 20-30-21)
C.  Conversion Coating - MIL-C-5541 (Alodine 1200) (Ref 20-30-41)
D.  Tape - Permacel 306 (Ref 20-30-51)
E.  Fiberglass Strip - BMS 8-2 type 35 (Conolite) .035 inch thick, 1.5 inch wide, length as required (Ref 20-30-51)
3.  Protect Floor Tracks Against Corrosion (Fig. 401)
A.  Clean tracks of all contaminants and corrosion products by mechanical means (Ref 20-40-00, Corrosion Prevention Manual).
B.  Brush Alodine 1200 and apply BMS 10-11 epoxy primer on all cleaned exposed areas of track.
C.  Apply leveling compound or sealant on fastener heads if present in cleaned areas of floor track.
　
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