|
Jetstream 31
The
Jetstream 31 is a product of BAE
Systems.
On March 28th, 1980 – the First
flight of the BAe Jetstream 31 prototype took place.
The Jetstream 31 offers the largest cabin in the 19-seat class of aircraft
and has been proven to be both safe and economical in worldwide operation.
The aircraft is flying throughout the world in 18/19 seat Commuter, 8-12
seat Corporate Shuttle, Air Ambulance and other Special Role Configurations.
The aircraft is a fast, reliable turboprop airliner designed with passenger
comfort in mind.
During
our production of Northwestern Air
Lease a multitude
of the Jetstreams on
board systems are reviewed. Below is
an overview.
Introduction
The Jetstream 31 is a light transport aircraft powered by two
Garrett TPE 331-10 turbo-propeller units. The aircraft is an
all-metal low
wing monoplane with a pressurized cabin, tricycle landing gear, steerable
nose wheels and hydraulic brakes. Conventional mechanically operated
flying controls, control the aircraft in pitch roll and yaw. At the
trailing
edge of the wings double-slotted flaps are attached.
Fuselage
The Flight deck has accommodation for a crew of two. A bulkhead
separates crew and passenger compartments. In the left side of
the fuselage,
at the rear, is the crew/passenger entrance door which, when opened,
is
also the entrance stairs. In the right side, mid-way along the
fuselage, is a hatch providing overwing emergency escape. At
the rear of the
passenger compartment is a baggage area, this area ends with a
pressure bulkhead.
The aircraft is fitted with a baggage pod, which can hold up to
435 pounds of cargo.
Wings
The wing is constructed with front, center main and rear spars,
chordwise ribs and skin stiffened by stringers. The underside
of the wing holds
the retracted landing gear. The trailing edge flaps are double
slotted and as in most traditional aircraft, the ailerons are
located outboard
of the flaps. Normal operation of the flaps is achieved through
electrical control by a flap selector and hydraulic power from
the engine driven
pumps. Vertical and horizontal stabilizers hold both the single
piece rudder and dual elevators. During the production our pilots
will
review these systems and explain the Jetstreams automatic flap
DUMP position
on landing.
Electrical
Electrical power is supplied by two engine-mounted starter/generators
and with two batteries for essential supply during failure
conditions and engine starting. Ground power may be used for
starting.
Fire Protection
The fire protection system provides the means to detect and
extinguish a fire in the engine nacelles. A smoke detection
system is located
in the rear baggage area. Aural and visual indications are
provided to alert
the flight crew to excessive temperature conditions. Four
fire extinguisher bottles, two per engine, mounted in the landing
gear bays are electrically
discharged from the flight deck.
Stall protection
The left and right stall warning systems consist of a vane
and stickshaker. The wing-mounted vane identifies an approach
to
the stall and warns
the crew by activating the related stickshaker and audio
warning (horn). The stickpusher is operated by hydraulic
pressure,
which automatically
moves the elevators into an aircraft nose down position.
Fuel System
An integral tank of 192 gal (230.6 U.S. gal) is located
in each wing. Normal fuel supply is left tank to left
engine and right
tank to
right engine. The left and right supplies can be interconnected
for crossfeeding.
Hydraulic Power
Normal hydraulic power is provided by a single hydraulic
system. Emergency power is available. Normal pressure
of 2000 p.s.i.
is provided by two
engine driven pumps for operation of the stick pusher,
nosewheel steering, gear and flaps, and the supply
pressure to the
normal and emergency
braking systems. A hand pump with an emergency selector
at NORMAL provides system
pressure when the engines are not running.
Ice and Rain Protection
The ice and rain protection system comprises:
- Wing and tail leading edge de-icing
- Engine anti-icing with continuous ignition
- Propeller anti-icing
- Windshield heating and demisting
- Windshield rain removal
- Stall vane and pitot heating
- Elevator horn anti-icing
Landing Gear
The aircraft has tricycle landing gear consisting of
a twin wheeled nose gear and single wheel main
gears. Retraction
and extension
of the gear
is hydraulically powered. The nose gear is hydraulically
steered and disc brakes are fitted to the main
wheels.
Emergency Equipment
Flight compartment
-Smoke goggles
-Quick donning oxygen masks
-Portable oxygen bottle
-BCF fire extinguisher
Passenger compartment
-First aid kit
-BCF fire extinguisher
-Therapeutic oxygen masks
-Emergency lighting
-
DIMENSIONS:
-
Wing span: 52 ft 0 in / 15.85 m
-
Length: 47 ft 1.5 in / 14.36 m
-
Height: 17 ft 8 in / 5.38 m
WEIGHTS:
-
Max. Takeoff Weight
(MTOW): 15,322 lbs / 6,900 kg
-
Max. landing weight
(MLW): 14,900 lbs / 6,759 kg
-
Max. Zero Fuel Weight
(MZFW): 14,300 lbs / 6,486 kg
-
Operating Empty
Weight (OEW): 10,200 lbs / 4,626 kg
-
Maximum Payload:
4,100 lbs / 1,860 kg
-
Maximum Fuel Capacity:
3,024 lbs / 1,372 kg
-
PERFORMANCE:
-
Maximum Cruise Speed: 255 kts
-
Range with 17 Pax Load: 297 NM
-
Range with 60% Load Factor: 980 NM
-
Typical Fuel Burn: 562 lb/hr / 255 kg/hr
-
Maximum Cruise Altitude: 25,000 ft
|
