|
曝光台 注意防骗 网曝天猫店富美金盛家居专营店坑蒙拐骗欺诈消费者
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
LANDING GEAR POSITION AND WARNING SYSTEM (CONT'D) Landing Gear Warning Logic Primary Mode
ANY GEAR NOT SERVICEABLE
AND DOWN AND LOCKED RADALT
GF1510_037
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
LANDING GEAR
LANDING GEAR POSITION AND WARNING SYSTEM (CONT'D) Landing Gear Warning Logic (Cont’d) Secondary Mode
Volume 2 Flight Crew Operating Manual Rev 2A, Apr 11, 2005
LANDING GEAR
LANDING GEAR POSITION AND WARNING SYSTEM (CONT'D)
Gear Warning Horn “MUTED”Switch
A “MUTED”switch is located on the landing gear control panel. It is used to disable the gear warning horn under certain airplane configurations with both radio altimeters inoperative. The “MUTED”switch is inoperative with at least one radio altimeter valid.
GF1510_014
The gear warning horn is not mutable under any of the following conditions:
.
When activated by flap position.
.
Both throttles at idle.
.
Radio altimeter(s) valid.
The landing gear warning horn function is restored after it has been muted if any of the following conditions are met:
.
Both throttles are advanced above idle.
.
All the landing gears are down and locked.
.
Flaps are commanded to 30°.
Rev 2A, Apr 11, 2005 Flight Crew Operating Manual Volume 2
LANDING GEAR
RETRACTION AND EXTENSION SYSTEM
Normal retraction and extension of the landing gear is initiated by landing gear control lever selection. The retraction or extension signal is sent to the LGECU which monitors various landing gear proximity sensing inputs and weight-on-wheels (WOW) inputs. If the correct parameters are met, the LGECU sequentially energizes the appropriate selector valves to retract or extend the landing gear using No. 2 and No. 3 hydraulic system pressures.
Landing Gear Retraction
For landing gear retraction, once the airplane is airborne (example: weight-off-wheels, nose wheel centered) the LGECU commands and monitors the following events:
. Landing gear control lever solenoid downlock releases to permit up selection of the landing gear control lever.
IN TRANSIT
GF1510_015
.
The door selector valve is energized and No. 3 hydraulic system powers all door uplocks and door actuators.
.
When the doors indicate open, the nose landing gear and main landing gear selector valves are energized.
.
No. 3 hydraulic system releases the respective downlocks and completely retracts the nose landing gear (extension/retraction actuator). No. 2 hydraulic system will power the main extension/retraction actuators and completely retracts the main landing gear assemblies. The side brace actuator is energized only to disengage the internal downlocks during retraction.
中国公务机网 www.gongwuji.com
公务机翻译 www.aviation.cn
本文链接地址：庞巴迪环球5000公务机机组操作手册 Bombardier Global-起落架(8)
| 
