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the low drag and pitching moments required for
high-speed cruise. The leading edge is swept at 11
degrees and is protected by pneumatic de-ice boots.
Three degrees dihedral contributes to lateral stability.
Each half of the wing is constructed of three monolithic
spars, meaning each spar assembly, including spar
caps, webs, and rib stiffeners, is machined from a single
piece of aluminum. The spars are then spliced at the
centerline of the airplane. Control surfaces on each wing
include an aileron, flap, and upper and lower surface
speed brakes. The left-hand aileron incorporates a trim
tab. All fuel is carried inside the wing.
Located on the wing tips are LED navigation and anticollision
strobe lights, and static wicks. Aluminum fairings
blend the wing with the fuselage. High intensity discharge
(HID) landing/taxi lights are located below the
fuselage in the belly fairing.
Limit Speeds
VMO Sea Level to 27,120 ft (8,266 m) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS (463 km/hr, 288 mph)
MMO 27,120 ft (8,266 m) and above . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . Mach 0.63 (indicated)
Flap Extension Speeds
VFE 0° to Takeoff/Approach Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (343 km/hr, 213 mph)
VFE Takeoff/Approach to Landing Extension . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 150 KIAS (278 km/hr, 173 mph)
Landing Gear Operating and Extended Speeds
VLO (retracting) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 185 KIAS (343 km/hr, 213 mph)
VLO (extending) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS (463 km/hr, 288 mph)
VLE . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 250 KIAS (463 km/hr, 288 mph)
8
September 2006
The empennage section is a T-tail design consisting of
aluminum monolithic spars, aluminum skins, and a composite
fairing. Composite strakes are mounted on the tailcone.
The one-piece, fixed horizontal stabilizer has two
elevators, each with trim tabs, and a 27 degree leading
edge sweep. The vertical stabilizer is swept 52 degrees
at the leading edge and has a single rudder with one trim
tab. A red LED ground recognition light is mounted on the
top. Both the vertical and the horizontal stabilizers are
protected from ice by pneumatic de-ice boots.
6. EMPENNAGE
7 . LANDING GEAR
Each main gear is a trailing link, single wheel, air/oil
shock assembly that retracts inboard into the wing with
a partial coverage door. The nose gear is a single wheel
assembly that retracts forward into the fuselage and,
when retracted, is fully enclosed by two doors. The landing
gear retraction system is electrically controlled and
hydraulically actuated. Once retracted it is secured by
up-locks. The landing gear may be extended and flown
at speeds up to VMO or 250 KIAS. To retract the gear, airspeed
must be at or below 185 KIAS. Emergency landing
gear extension is accomplished by manual release of
the uplocks for free fall followed by use of the pneumatic
blow-down system.
Steering is mechanically controlled through the rudder
pedals and stabilized with an internal shimmy damper. The
nose gear tire is chined for water and slush deflection.
Dual rotor steel disc brakes are installed on the main
gear wheels. Toe pressure on the rudder pedals is
mechanically transferred to the brake metering valve to
provide normal powered braking. Digital antiskid protection
is available for speeds above 10 knots. Power to the
system is supplied by an electric motor-driven hydraulic
pump and accumulator. A pneumatic bottle system in the
nose with a pilot operated valve handle under the instrument
panel serves as back-up for the brakes. The parking
brakes are toe pedal actuated while pulling a cockpit
handle to trap pressure on the brake assemblies.
8 . P OWERPLANTS
Two Pratt & Whitney Canada PW615F turbofan engines
are installed on the Mustang, one on each side of the
rear fuselage in easily accessible nacelles. This engine
is a 2.8 to one bypass ratio, counter-rotating twin-spool
design with 3 compression stages and 2 turbine stages.
It produces 1,460 pounds (6.49 kN) of thrust at sea level
static conditions, flat rated up to 77°F (25°C). A forced
exhaust mixer improves fuel burn and reduces noise.
Expected intervals for major maintenance are 1,750
hours for HSI and 3,500 hours for overhaul. Engine indications
　
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本文鏈接地址：Specification & Description(5)