NAVAIR 01.Fl4AAD-1
CHAPTER 1
Aircraft and Engine
1.1 AIRCRAFT
The F-14D aircraft is a supersonic, two-place, twinengine,
swing-wing, air-superiority tighter designed
and manufactured by Grumman Aerospace Corporation.
In addition to its primaty tighter role, carrying
missiles (Sparrow and/or Sidewinder) and an internal
ZO-mm gun, the aircraft is designed for fleet air defense
(Phoenix missiles) and ground attack (conventional ordnance)
missions. Armament and peculiar auxiliaries
used only during secondary missions are installed in
low-drag, external configurations. Mission versatility
and tactical flexibility are enhanced through independent
operational capability or integration under existing
tactical data systems.
The forward fuselage, containing the flightcrew and
electronic equipment, projects forward from midfuselage
and wing glove. Outboard pivots in the highly
swept wing glove support the movable wing panels,
whichi ncotporatein tegralf uelc ells andf ull-spanl eadingedge
slats and trailing-edge flaps for supplemental lift
control. In flight, the wings may be varied in sweep,
area, camber, and aspect ratio by selection of any
leading-edge sweep angle between 20” and 68”. Wing
sweep can be automatically or manually controlled to
optimize performance and thereby enhance aircraft versatility.
Separate variable-geometry air inlets, offset
from the fuselage in the glove, direct primary airflow to
two Fl lo-GE-400 dual-axial compressor, turbofan engines
equipped with afterburners for thrust augmentation.
The displaced engine nacelles extend rearward to
the tail section, supporting the twin vertical tails, horizontal
tails, and ventral fins. The middle and aft fuselage,
which contains the main fuel cells, tapers off in
deptht o the rear where it accommodatesth e speedbrake
surfaces and arresting hook. All control surfaces are
positioned by irreversible hydraulic actuators to provide
desiredc ontrol effectivenesst hroughoutt he flight envelope.
Stability augmentationf eaturesi n the flight control
system enhance flight characteristics and thereby provide
a more stablea nd maneuverablew eaponsd elivery
platform. The tricycle-type, forward-retracting landing
geari s designedf or nosegeacr atapultl aunch and carrier
landings. Missiles and external stores are carried from
eight hardpoint stations on the center fuselage between
the nacelles and under the nacelles and wing glove; no
stores are carried on the movable portion of the wing.
The fuel system incorporates both in-flight and singlepoint
ground refueling capabilities. Aircraft general dimensions
are shown in Figure l-l. FO-1 shows the
general placement of components within the aircraft. A
summary of aircraft limitations and characteristics are
shown in Figure 1-2. Refer to Chapter 4 for detailed
information.
1.1.1 Aircraft Weight. The basic weight of the aircraft
is approximately 43,735 pounds, which includes
trapped fuel, oil gun, and pylons. Consult the applicable
Handbook of Weight and Balance (NAVAIR Ol-lB-40)
for the exact weight of any series aircraft.
1.1.2 Cockpit. The aircraft accommodates a twomain
crew that consists of a pilot and RIO in a tandem
seating arrangement. To maximize external field of
view, stations within the tandem cockpit are prominently
located atop the forward fuselage and enclosed by a
single clamshell canopy. Integral boarding provisions to
the cockpit and aircraft top deck are on the left side of
the fuselage. Each crew station incorporates a rocket
ejection seat that is vertically adjustable for crew accommodation
A single environmental control system provides
conditioned air to the cockpit and electronic bays
for pressurization and air-conditioning. Oxygen for
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