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fioin either cockpit or tium external controls on
each side of the foselage. An internal control handle in
each cockpit (Figure 2-125) is on the forward right side
of each flightcmw instrument panel and is painted yeilow
and black for ease of identification. To activate the
jettison control handle, squeeze the bmer face of the
handle and then pull.
The length ofpull is approximately one-half to threequarter
inch, and the handle comes tkee of the aircraft
when actuated. Pulling either CANOPY JBTTISON
handle actuatesa n initiator that ignites the canopys eparationc
hargea nd actuatest he canopyg asg eneratorT. he
canopy separation charge ignites the expanding,
shielded, mild-detonating cord lines, routed through the
canopy sill hooks, breaking the sill hook tinngiile bolt.
This allows the hooks to rotate upward, releasing the
canopy. The canopy gas generator produces highpressure
gas that forces the canopy hydraulic actuator
shaft upward, ballistically removing the canopy.
ORIGINAL
Ejection through the canopy can result in injury and
is provided only as a backup method, therefore, the
canopy is jettisoned as part of the normal ejection soquence.
An upward pull on the ejection seat firing handle
jettisons the canopy prior to ejection.
2.37.1.4.1 External Canopy Jettison Handles.
There are two external emergency jettison handles
located on the lower left and right t%selageb elow
the pilot cockpit, appropriately marked for rescue.
Opening either access door and pulling the T-handle
tires an initiator that detonates the canopy separation
charge and actuates the canopy gas generator. The sequence
is the same as when the cockpit handles are
pulled. The jettison control handles require squeezing
the inner face of the handle and then pulling for actuation.
The length of pull is approximately one-half to
three-quarterin ch and the T-handle comes Bee on the
aircraft when actuated. Refer to Chapter 12 for canopy
external jettisoning procedures.
2.38 EJECTION SYSTEM
The aircraft is equipped with an automatic electronically
sequencedc ommand escapes ystemi ncorporating
two Navy aircrew common ejection seat (SJU-17(V)
3/A (pilot) and SJU-17(V) 4/A (RIO)) rocket-assisted
ejection seats. Both seats are identical in operation and
differ only in nozzle direction of their lateral thrust motors,
which provide a divergent ejection trajectory away
from the aircratt path. When either crewmember initiates
the command escape system, the canopy is ballistically
jettisoned and each cmwmember is ejected in a
preset-times equenceT. be RIO is ejectedt o the left and
the pilot to the right.
Safe escape is provided for most combinations of
aim&I altitude, speed, attitude, and flightpatb within an
envelope from zero airspeed, zero altitude in a substantially
level attitude to a maximum speed of 600 KCAS
between zero altitude and 50,000 feet. Preflight procedures
are shown in Chapter 7 of this manual; ejection
procedures are discussed in Chapter 16. Ejection sequence
is illustrated in FO-16 and FO-17.
Loose gear in the cockpit is a FOD and missile
hazard, especially during carrier operations,
maneuvering flight, or ejection
sequellces.Crariageofgearthatcannotbecontained
in the wckpit stomge wmparmledlt shall
bek ept to a minimum consistenwt ith mission
requirements and the mission environment
NAVAlR 0%F14AAD1
2.38.1 Ejection Seat. The NACES seat (Figure
2-126) is provided with a rocket-deployed 6.5 meter
(20-foot), aeroconical, steerable parachute that is
packed with a ribbon extraction drogue in a container
behind the seat occupant’s head. The seat bucket holds
the smvival kit and also has the seat tiring handle and
other operating controls. The parachute risers attach to
the crewmember’st orso harnessb y meanso f seawateractivated
release switches. Normal ejection includes
canopy jettison before the seats are catapulted out of the
cockpit; however, the parachute container is fitted with
canopy penetratora. This permits a backup ejection
through the canopy after a time delay in the event of
safe-and-arm unit failure or failure of the canopy to
separatet? om the aircraft.
After ejection has been initiated, two pitot heads
mounted next to the parachute container are deployed.
Airspeed and altitude are provided to the batteryoperatede
lectronics equencemr ounted under the parachute
container. The sequencer, which also receives
static pressure, uses the information to determine the
proper sequencingo f deployment of the seatd mgue and
　
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