(e)
Polish with the air-driven sander/polisher as follows:
NOTE: Polish the airplane surface first with Schaffner No. 521 white bar compound.
Polish with the Schaffner No. 521 white bar compound until all of the gray
undercast is removed. Then apply the No. 4094 green coloring bar
compound.
Always clean the surface with solvent before you change to a different bar
compound.
1) Remove the dried polish material from the buffer wheel with a wheel rasp or a
coarse file.
2) Apply the applicable polishing compound to the buffer wheel.
3) Hold the buffer wheel parallel to the direction that you polish.
4) Polish in the forward-to-aft direction.
5) Use sufficient pressure to remove the stains and scratches.
6) Move the buffer wheel in the correct direction to keep the finish in a good
condition.
7) Apply the applicable polishing compound to the buffer wheel frequently.
8) Remove the dried polish material from buffer wheel frequently.
9) Remove the dried polish material from the airplane surface with the wipers and
solvents.
NOTE: Put the solvent on the heavy polish material to make it soft before you wipe it off.
10) Do the “Clean the External Surfaces of the Airplane” procedure in the polished
area.
11) Put some water on the surface, and make sure the water becomes drops.
12) If the surface was conversion coated before it was polished, apply Alodine 1000
with a swab, cloth, or sponge (Ref. 51-21-41).
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(3) PROCEDURE III - Polish the surface to repair damage that penetrates the clad aluminum.
NOTE: There is a test in PROCEDURE II to find if a scratch penetrates the clad aluminum.
(a)
Use the soft wipers to clean the damaged area.
NOTE: Wipe the damaged area carefully to prevent scratches.
(b)
Remove the burr edge as follows: 1) Apply the lubricant to the burnishing tool. 2) Move the burnishing tool in the direction of the scratch so that the clad
aluminum material is moved into the defective area.
NOTE: Keep the area that you burnish to a minimum.
3) Move the burnishing tool on the repaired area so the area has a smooth surface, and so the stress is applied on a large area. 4) If the burnished area blends in with the adjacent surface, no further work is necessary. 5) If the burnished area does not blend in with the adjacent surface, continue as shown in PROCEDURE II.
E. Put the Airplane Back In Its usual Condition
WARNING: FAILURE TO REMOVE COVERS FROM PITOT PROBES BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION: REMOVE ALL COVERS. ENGINES SHOULD NOT BE OPERATED WITH COVERS IN PLACE BECAUSE THE COVERS CAN COME OFF AND DAMAGE THE ENGINES.
(1)
Remove covers from the following components:
(a)
Pitot probes
(b)
Engine inlet and turbine exhaust
(c)
Brakes
(d)
Tires
(2)
Remove the ‘PITOT PROBES COVERED” tag from the left control wheel in the flight deck.
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May 01/98 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 12-40-0 Page 223
WARNING: FAILURE TO REMOVE BARRICADE TAPE AND VINYL ADHESIVE TAPE FROM STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED-SENSING AND ALTITUDE-SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION: REMOVE ALL BARRICADE TAPE, COVERS, POLYETHYLENE SHEET AND VINYL ADHESIVE TAPE. ENGINES SHOULD NOT BE OPERATED WITH COVERS IN PLACE BECAUSE THE COVERS CAN COME OFF AND DAMAGE THE ENGINES.
(3)
Remove all barricade tape, covers, polyethylene sheet and vinyl adhesive tape from the following openings:
(a)
Static Ports
1) Inspect each static port and if necessary, use naphtha or equivalent, and a clean dry rag to remove all tape residue, dirt and other contaminates around the static port.
(b)
Surge tank and fuel tank vents
(c)
APU exhaust duct outlet port
(d)
APU oil cooling air exhaust port
(e)
Equipment cooling ground supply valve port
(f)
Overboard exhaust valve port
(g)
Smoke clearance valve port
(h)
Ram air inlet and outlet doors
(i)
Outflow valve
(4)
Remove the “STATIC PORTS COVERED” tag from the left control wheel in the flight deck.
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