Lockheed C-5M, Техническое руководство

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1.5.5.14 Airplane Surfaces.
During freezing weather, movement along the top surfaces of the airplane may be hazardous
due to frost or ice patches which may not be visible. Remove frost and ice in accordance with paragraph title Anti-Icing,
Deicing, and Snow and Frost Removal.
1.5.5.15 Flight Control Surfaces.
a. To minimize entry of frozen precipitation, always fair the
À
ight control surfaces after completion of maintenance
functions and ensure access panels are secured.
b. Remove all snow and ice from
À
ight control surfaces in accordance with paragraph titled Anti-Icing, Deicing, and
Snow and Frost Removal.
When operating the wing
À
aps, closely observe the
À
ap position indicator for
À
ap movement. If the
À
aps stall due
to ice or snow deposits, immediately return the
À
ap control handle to the position where movement was started.
Failure to comply may result in damage to components.
c. During checkout operations in freezing weather, carefully cycle the
À
ight controls a sufficient number of times to
ensure surface movement is not hampered by ice or snow deposits that are not readily visible.
1.5.5.16 Angle-of Attack Vanes. During freezing weather, check the angle-of-attack vanes for ice. Remove ice forma-
tions with integral heaters.
1.5.5.17 Landing Gear.
a. Gear retraction/extension times will be slower after overnight soak temperatures of -20 °F (-29 °C) and lower.
b. Following exposure to very cold ambient temperatures, the initial kneeling operation may result in slow movement of
the main landing gears. The kneeling operation should be continued if all main landing gear are kneeling and adequate
airplane-to-ground clearance is maintained. Prior to kneeling, self-warming of the MLG may be accompanied by
individually kneeling the gear to a counter reading of approximately 75 and then unkneeling.
c. During unkneeling after exposure to very cold ambient temperatures, individual landing gear may stall due to the
increased friction. The unkneeling operation should be continued as long as adequate airplane-to-ground clearance is
maintained. The stalled gear should resume operation as the load is relieved by the other landing gear unkneeling.
1.5.5.18 Logic Circuitry Control Units for Retraction Functions. After the airplane has been subjected to cold soaks of
10 hours or more at ground ambient temperatures that are at or below -25 °F (-32 °C), logic circuitry control units
(integrated circuitry) for retraction functions may operate erratically. These control units should be preheated for 20 to 30
minutes before any kneeling operation, ground retraction test, or taxi-out for takeoff. Alternatively, these units may be
warmed by heating of their compartments either from external heaters or the airplane environmental subsystem. Warm air
applied directly to the units should be no more than about 100 °F (38 °C) to avoid excessive heating. Even after proper
external warming of the control units, adverse affects from the cold may remain.
1.5.5.19 Visor Locks.
After cold soaks (-40 °F/-40 °C and below) some locking pins of the visor locks may not fully
retract. Prior to attempting to raise visor, operate locks by using manual controls and check that all locking pins retract.
Cycle lock and unlock manual controls if required.
1.5.5.20 Fire Detectors.
After overnight cold soaks at temperatures below 0 °F (-18 °C), sluggish or erratic response can
be expected in the course of the
¿
re detector checks. Several attempts may be required to obtain a normal check.
1.5.5.21 Fuel Quantity Indicators.
On AF83-1285, AF68-0216, and AF69-0024, the fuel quantity indicators may not test
properly until the
À
ight station has warmed. On AF83-1285 and up, after cold soak at temperatures from -70 °F to 4 °F (-57
°C to -16 °C), fuel quantity LCD displays may be sluggish for 1 to 3 minutes after power has been applied to the airplane.
TO 1C-5M-2-1
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