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handle can be used to assist in stowing the ladder by releasing the handle and pushing the ladder to
the stowed position and pushing the stow assist handle to the closed (stowed) position and releasing it.
With electrical power on the aircraft, a LADDER caution comes on whenever the proximity switch in
the aft portion of the ladder well is not actuated. With the ladder stowed and the 3 latches locked, the
LADDER caution goes out.
The ladder is extended remotely by opening the ground power receptacle door and holding the
ladder remote release switch (lower switch) to the down (DEPLOY) position. The three latches are
opened by a battery powered actuator. The ladder drops to the open position while being restrained
from free falling by a dampening strut (drop time approximately 3 to 4 seconds). All other procedures
for securing the ladder are the same as manual opening.
2.15.2.1 Ladder Remote Release Switch. The external ladder remote release switch is located inside
the external power receptacle (door 9) on the left side of the aircraft below the canopy and LEX. The
switch is lever locked and spring loaded to the UP position. Switch positions are:
UP Removes electrical power from the unlock actuators which allows the ladder to lock
when it is manually stowed.
DEPLOY Applies electrical power to the three unlock actuators which unlocks the actuators
so the ladder can free fall. The switch must be pulled out and down and held in
DEPLOY until the actuators are unlocked.
WARNING
Due to the close proximity of the ladder remote release switch and the
external canopy switch, positive switch identification is required to
prevent inadvertently lowering the canopy and injuring personnel egressing
the aircraft.
A1-F18EA-NFM-000
I-2-109 ORIGINAL
2.15.3 Ejection Seat. The SJU-17 (V)1/A and 2/A NACES (Navy Aircrew Common Ejection Seat)
are ballistic catapult/rocket systems that provide the pilot with a quick, safe, and positive means of
escape from the aircraft. See Ejection Seat, foldout section, for ejection seat illustrations. The seat
system includes an initiation system which, after jettisoning the canopy and positioning the occupant
for ejection, fires the telescopic seat catapult. Canopy breakers on the top of the seat give capability of
ejecting through the canopy. As the seat departs the aircraft and the catapult reaches the end of the
stroke a rocket motor on the bottom of the seat is fired. The thrust of the rocket motor sustains the
thrust of the catapult to eject the seat to a height sufficient for parachute deployment even if ejection
is initiated at zero speed, zero altitude in a substantially level attitude.
NOTE
Safe escape is provided for most combinations of aircraft altitude,
speed, attitude, and flight path within the envelope of 0 to 600 KCAS
airspeed and 0 to 50,000 feet altitude.
2.15.3.1 SJU-17(V) 1/A and 2/A NACES Seat. Timing of all events after rocket motor initiation is
controlled by the electronic sequencer which utilizes altitude, acceleration, and airspeed information to
automatically control drogue and parachute deployment and seat/man separation throughout the
ejection seat's operational envelope. In the event of partial or total failure of the electronic sequencer,
a four second mechanical delay initiates a barostatic release unit which will free the occupant from the
seat and deploy the parachute between 14,000 and 16,000 feet MSL if the ejection occurred in or above
this altitude range. The emergency barostatic release unit operates immediately after the four second
delay if the ejection occurred below 14,000 feet MSL. An emergency restraint release (manual override)
Figure 2-33. Boarding Ladder
A1-F18EA-NFM-000
I-2-110 ORIGINAL
system provides a backup in the event of failure of the barostatic release unit. The seat is stabilized and
the forward speed retarded by a drogue chute attached to the top and bottom of the seat. The
parachute deployment rocket is automatically fired to withdraw the parachute from deployment bag.
Full canopy inflation is inhibited until the g forces are sufficiently reduced to minimize opening shock.
There are five modes of operation. See figure 2-34 for parameters that determine the mode of operation
and the corresponding parachute deployment and drogue chute release times. At high altitude the
drogue chute deploys to decelerate and stabilize the seat. The seat falls drogue retarded to 18,000 feet
MSL where the drogue is released, the main parachute is deployed, and seat/man separation occurs. At
medium altitude, (between 18,000 and 8,000 feet MSL), and at low altitude (below 8,000 feet MSL)
parachute deployment is automatically delayed from 0.45 to 2.90 seconds (depending upon airspeed
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(88)