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off wheels provides a redundant and automatic transfer
of the control valve to the extend position. With weight
off wheels, the NOSE STRUT switch is inoperative.
2.127 ORIGINAL
NAVAIR 0%MUAD-I
NOMENCLATURE
0
NOSE STRUT switch
0 LAUNCH BAR advisory
light
@ LAUNCH BAR switch
ORIGINAL
FUNCTION
EXTD - Hydraulic pressure causes strut to extend. Combined hydraulic
system must be pressurized before switch is activated on external
power. Launch bar is lifted into the up-lock position by torque arms
as strut extends 14 inches.
OFF - Spring-loaded return position.
KNEEL Nose strut transfer control valve releases pressure In the shock
strut, which strokes 14 inches. Combined hydraulic system must be
pressurized before switch is active on external power. Launch bar
uplock can be released manually to allow bar to lower to deck, or
by turning nosewheel 3~10’.
illuminates under the following conditions:
Weight On Wheels
l Aircraft kneeled, throttles less than MIL (goes out when throttles are
advanced to MIL to provide lights out criterion for catapult launch).
l Launch bar not up and locked (normal operation)
Weight Off Wheels (mhiblts nosegear retraction)
l Launch bar not up and locked
l Nosewheel not within &IV of center
l Nose strut not fully extended
ABORT -Enables pilot to disengage the launch bar from the catapult while
remaining at MIL power and in the kneel position.
NORM Allows launch bar to be lowered.
Figure 2-73. Launch Bar Controls
2-128
2.28.2 Launch Bar. Thelaunchbarisattachedtothe
nosegeara nd servesa s the tow link for catapulting the
aircrafi (see Figure Z-74). With the nose strut extended,
the launch bar is held in the retracted position. The
launch bar can be lowered by kneeling the aircraft and
turning the nosewheel greater than ilOo from the centered
position. The launch bar can also be lowered by
the deck crew with no pilot action after the aircraft has
been kneeled. A proximity sensing switch on the uplock
detects the latch out of the locked position and ilhuninates
the LAUNCH BAR advisory light (see Figure
2-73). Ears on the head of the launch bar engage under
the lip of the catapult lead-in track and the head serves
as a guide to steer the nosewheel on the catapult track
and engage the shuttle. For an abort, the launch bar
cannot be raised until the shuttle is disengaged.
2.28.2.1 LAUNCH BAR Light. ‘Ihe LAUNCH BAR
advisory light is interlocked to go off whenboth throttles
are at MIL even though the launch bar position and
mechanismr emain unchanged,th is action is effectedt o
establish a “lights out” criterion for launch. The light
circuit is disabledw ith nosegeaur p andl ocked. A pilotcontrolled
LAUNCH BAR switch is installed that enables
the pilot to disengage the launch bar from the
catapult while remaining at MB. power and in the kneel
position. This switch is on the pilot left vertical console.
To avoid damage to the launch bar retract
mechanism, do not set the LAUNCH BAR
switch to ABORT with the nosewheel deflected
off center.
After the catapult launch stroke, extension of the strut
mechanically cams the launch bar up to the retractedand-
lockedp osition. If the launch bar is not engagedin
the uplock with weight off wheels, the LAUNCH BAR
advisory light will illuminate and nosegear retraction
will be electrically inhibited.
2.28.3 Holdback Fitting. The holdback fitting is
provided on the nose strut for insertion of the holdback
bar. A groundcrewman must manually attach the bar
before the aimrat? is taxied into the catapult lead track.
The holdback bar is reusable and provides for repeated
releasesa t a tow force of 76,000 pounds.F orce greater
than this on launch causes the holdback bar to release
the aircraft holdback fitting.
Single-engine,h igh-powert umup operationsc an use
the holdback fitting to attach aircraft restraining hardware
to deck-securedfi ttings. Prior to the application of
NAVAIR 0%Fl4AAD-1
single-engine high power, the nose strut should be
kneeled and slack taken out of the holdback mechanism,
otherwise dynamic loads may exceed mechanism design
strength conditions.
2.29 ARRESTING HOOK SYSTEM
The arresting hook installation consists of a stinger
tailhook and associatedc ontrol mechanism mountad to
the underside of the center fuselage. The hook shank is
free to pivot up and down at its attachment point. A
pneumatic dashpot preloads the hook down to minimize
hook bounce on contact with the deck. The hook shank
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F-14D 飞行手册 Flight Manual 1(128)
