曝光台 注意防骗
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may be observed through an access door on the
underside of the aft fuselage.
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The ground test mode incorporates a solenoid
valve that allows the BFCM to pressurize
the entire combined hydraulic system. If
thec ombineda ndb rakea ccumulatorsa re not
fully charged (brake pressure indicator at top
of green), or if the combined system is not
fully serviced, the reservoir will be depleted
and the motor will cavitate and overheat.
This could result in motor failure prior to
activation of the thermal cutoff switch.
In the low-speedm ode, the systemc an operatein definitely
and should be used for maximum range and endurance.
Emergency power (high mode) provides a
maximum unloaded horizontal tail deflection rate approximately
one fourth of that available from a full powered
hydraulic system (IO’ per second vice 36O per
second). The maximum deflection rate available will
decreasea s airloads increase.
2-75 ORIGINAL
NAVAIR Ol-Fl4AAD-1
Prolonged use (approximately 8 minutes cumulative
time) of the BFCM in the high
mode may result in a failure of the BFCM.
2.17 PNEUMATIC POWER SUPPLY SYSTEMS
The pneumatic power supply systems consist of three
independents, toredp neumaticp ressures ourcesf or normal
and auxiliary operation of the canopy and for emergency
extension of the landing gear. The high-pressure
bottles for normal canopy operation and emergency
landing gear extension are ground-charged through a
common filter connection in the nose wheelwell to 3,000
psi at 70 “F ambient temperature.I ndividual bottle pressurei
s registeredo n separateg augeso n the right sideo f
the nosew heelwell. An auxiliary canopy-openN z bottle,
filter valve, and gauge is on the turtleback behind the
cockpit to allow opening the canopy from the cockpit or
ground.C hargesm ay be compresseda ir; however,p ressurizeddrynitrogenispreferredbecauseofitslowmoisture
content and inert properties.
2.17.1 Normal Canopy Control. The bottle that
suppliesapressurizedchargfeo rnormaloperation ofthe
canopy is on the right side of the forward fuselage,
inboard of the air refuel probe cavity. Expenditure of
bottle pressure for normal operation of the canopy is
controlled by three (pilot, RIO, and ground) canopy
control handles. A fully charged bottle provides approximately
10 complete cycles (open and close) of the
canopy before reaching the minimum operating pressure
of 225 psi.
2.17.2 Auxiliary Canopy Open Control. The auxiliaty
canopy air bottle supplies a pneumatic charge to
translatet he canopy aft so that the counter-poisea ction
of the canopy actuator facilitates opening. It is on the
turtleback behind the canopy hinge line.
Activation of the auxiliary mode can be effected from
either of the three (pilot, RIO, or ground) canopy control
handles. After activation of the auxiliary open mode, the
control system will not return to the normal mode of
operation (canopy will lower but will not translate forward)
until the auxiliary selector valve on the aft canopy
deck is manually reset (lever in vertical position). Servicing
of the auxiliary canopy air bottle is through the
small access panel immediately behind the canopy on
the turtleback. The reservoir is normally serviced to
3,000p si at 70 ‘F ambientt emperature.A fully charged
bottle provides more than 20 operations in the auxiliary
open mode. Minimum preflight pressure is 800 psi.
2.17.3 Emergency Gear Extension. Tbebottlethat
supplies the pneumatic force for a single emergency
extension of the landing gear is on the right side of the
nose wheelwell. Expenditure of bottle pressure is controlled
by a twist-pull operation of the landing gear
handle. Minimum bottle pressure for accomplishing
emergency extension of the gear to the down-andlocked
condition is 1,800 psi. Normal preflight bottle
pressure is 3,000 psi at 70 “F.
Note
Emergency extension of the landing gear
shall be logged in the Maintenance Action
Form (OPNAV Form 3760-2).
Once the landing gear is extended by
emergency means, it cannot be retracted
while airborne and must be reset by maintenance
personnel.
Use of emergency gear extension results
in loss of nosewheel steering.
2.18. MISSION COMPUTER SYSTEM
The MCS consists of two AN/AYK-14 digital computer
(MC1 and MC2) and the dual redundant MILSTD-
1553B buses. The MCS is operated at 16 MHz
clock speed to perform 1 million instructions per second
using up to I megabyte of memory. The 1553B bus
system in the F-14D uses time division multiplexing
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F-14D 飞行手册 Flight Manual 1(100)
