(3)
Strict clean-up and inspection (using mercury vacuum pump, mercury sniffers, X-ray equipment, etc.), and possible repair, must be made during first airplane service at a main base.
(4)
Reinspect area of spillage and areas below spillage at first overhaul.
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5-51-121 Page 204 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/86
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Oct 20/86 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-121 Page 205
HYDRAULIC FLUID REACTION WITH TITANIUM - CONDITIONAL INSPECTION
1. Hydraulic Fluid Reaction with Titanium
A. General
(1)
At normal ambient temperatures, hydraulic fluid is compatible with titanium. Above 270°F, however, hydraulic fluid becomes acidic and attacks titanium causing corrosion and embrittlement.
(2)
Hydraulic fluid contamination is evidenced by a light glossy brown film, a dull black residue, or a bare surface on painted ducts.
(3)
Metal deterioration is evidenced by a bright etched (rough) surface.
B. Examination of Titanium Parts in Hydraulic Fluid Contamination Areas
(1)
Examine all titanium parts in hydraulic fluid contamination high temperature areas for hydraulic fluid contamination or metal deterioration.
NOTE: Affected parts are the two outlet ducts from the air conditioning air cycle machine compressors in the air conditioning equipment bay area. Refer to Chapter 21 Air Conditioning.
(2)
For cleaning hydraulic fluid contaminated parts, refer to Chapter 51, High Temperature Coating for Titanium.
(3)
Parts showing metal deterioration should be replaced.
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Jun 20/85 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-131 Page 201
CABIN OVERPRESSURIZATION - CONDITIONAL INSPECTION
1. General
A. If cabin overpressurization occurs, (20 psia for oxygen system components and 18 psia for air data units) the following must be accomplished:
(1)
Replace oxygen system continuous flow control units and oxygen diluter demand regulators.
(2)
Check all spare air data units in airplane and air data units with disconnected pitot static lines for damage.
B. Upon completion of replacement and check, systems and components subject to damage due to overpressurization require reactivation or reinstallation and functional testing in compliance with applicable maintenance manual sections.
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Aug 15/69 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 5-51-141 Page 201
EFFECTIVITY
ALL
LIGHTNING STRIKE CONDITION - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)
1. General
A. The airplane has all the necessary and known lightning strike protection measures. Most of the external parts of the airplane are metal structure with sufficient thickness to be resistant to lightning strikes. This metal assembly is its basic protection. The thickness of the metal surface is sufficient to protect the internal spaces from a lightning strike. The metal skin also gives protection from the entrance of electromagnetic energy into the electrical wires of the aircraft. The metal skin does not prevent all electromagnetic energy from going into the electrical wiring; however, it does keep the energy to a satisfactory level. If lightning strikes the airplane, you must fully examine all of the airplane to find the areas of the lightning strike entrance and exit points. When you look at the areas of entrance and exit, examine these areas carefully to find all of the damage that has occurred.
B. Lightning strike entrance and exit points are usually found in Zone 1 (Fig. 201), but also can occur in zones 2 and 3.
C. You can usually find signs of a lightning strike in Zone 1 (Fig. 201). However, lightning strikes can occur to any part of the airplane which includes the fuselage, wing-body fairing, antennas, vertical stabilizer, horizontal stabilizer, and along the wing trailing edge (Zone 2, Fig. 201).
D In metal structures, lightning damage usually shows as pits, burn marks or small circular holes. These holes can be grouped in one location or divided around a large area. Burned or discolored skin also shows lightning strike damage.
E. In composite (non-metallic) structures, solid laminate or honeycomb damage shows as discolored paint. It also shows as burned, punctured, or delaminated skin plies. Damage you can not see can also be there. This damage can extend around the area you can see. Signs of arcing and burning can also occur around the attachments to the supporting structure.
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