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庞巴迪挑战者300公务机机组操作手册 Bombardier Challenger-飞机概述 Airplane General(3)

时间:2011-11-01 13:03来源:蓝天飞行翻译 作者:公务机
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Components And Operation ......................................................................................01-05-12

EICAS Messages................................................................................................................01-05-13

Sep 14/2005 Flight Crew Operating Manual Volume 2 REV 4 CSP 100-6
01-00-01

The Challenger 300 aircraft, manufactured by Bombardier Aerospace, is an all metal, pressurized, low-wing, turbofan-powered monoplane. The high-aspect ratio, fully cantilevered, swept-back wings with winglets are of conventional riveted construction except for the upper section of the winglets, which utilize full-depth honeycomb core bonded to the outer skin. The fuselage is of semimonocoque construction and utilizes a constant circular cross-sectional shape fuselage.
Thrust is provided by two pod-mounted AS907 turbofan engines manufactured by Honeywell. Independent fuel systems supply fuel to the engines with fuel storage provided in wing tanks. Engine-driven hydraulic pumps provide hydraulic pow-er for braking, extending or retracting the landing gear, nosewheel steering, wing flaps, spoilers, thrust reversers, elevator, and rudder. The landing gear system is a fully retractable tricycle-type trailing link landing gear with dual main gear wheels, nosewheel steering, and a brake-by-wire brake control/anti-skid braking system.
The ailerons are manually controlled, and the elevator and rudder are controlled via hydraulic actuators. An electrically actuated trim tab is installed on the left aileron to provide lateral trim. Longitudinal trim is accomplished by changing the incidence of the horizontal stabilizer with an electrically operated linear actuator. Rudder trim is accomplished via an elec-tromechanical actuator which moves the rudder surface independent of the rudder pedal position. Aircraft air-conditioning systems which include an air-cycle machine, provide heating, cooling, and pressurization for the cockpit, passenger compartment, and lavatory.
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
01-02-01

AIRCRAFT DIMENSION SCHEMATIC


NOTES
Measurement at manufacturer

 

23 ft 9 in
(7.24 m)
CFO0101002_015
Volume 2 Flight Crew Operating Manual Sep 13/2004 CSP 100-6 REV 1
01-02-02


1 20 ft
(6.1 m) 6 ft 3 in
2 ft 6 in (1.89 m) (0.76 m)
4 ft 3 in
(1.3 m) 61 ft 1 in
(18.62 m) 68 ft 8 in
(20.92 m)

 

NOTES
Measurement at manufacturer empty weight.


CFO0101002_016
Sep 13/2004 Flight Crew Operating Manual Volume 2 REV 1 CSP 100-6
01-02-03

AIRCRAFT DIMENSION SCHEMATIC (Cont)

6.1 ft
(1.9 m)
5.1 ft
(1.6 m)
7.2 ft
(2.2 m)
PASSENGER COMPARTMENT DIMENSIONS 
LENGTH  28 ft 7 in  8.71 m 
WIDTH (FLOOR LINE)  5 ft 1 in  1.55 m 
 
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