B767
Páginas: 6 (1262 palabras)
Publicado: 28 de septiembre de 2011
Smartcockpit.com
BOEING 767 SYSTEMS REVIEW
Page 1
HYDRAULICS
1. GENERAL
¡ 3 separate & independent hydraulic systems : - Left Ô powered by 1 Engine pump & 1 Electric pump - Center Ô powered by 2 Electric pumps & 1 Air Driven pump - Right Ô powered by 1 Engine pump & 1 Electric pump ¡ Provide power to the : - Flaps / slats - Landing gear - Tailskid - Nose wheel steering - Brakes -Flight controls - A/P servos ¡ Center hydraulic system provide power (if both Main AC buses are lost) to the Hydraulic Driven Generator (HDG). If required, a Ram Air Turbine (RAT) can provide power to the flight controls portion of the Center hydraulic system (in case of double engine failure)
2. DISTRIBUTION L+C+R
Ô Elevators Ô Rudder Ô Spoilers Ô Stab Trim
L+R
Ô Outboard Ailerons
L only
ÔRudder ratio Ô Left A/P
L+C
Ô Yaw Dampers Ô Elevator Feel Ô Left Inboard aileron
R only
R+C
C only
Ô Tail Skid Ô Flaps & Slats Ô Main Gear Ô Nose gear Ô Nose Wheel Steering Ô Alternate Brakes Ô 5 KVA Gen Ô Center A/P Ô RAT
Ô Right Ô Normal Inboard aileron Brakes Ô Right A/P
3. LEFT AND RIGHT SYSTEMS
¡ Quantity and Refill on EICAS Status display ¡ Independent reservoirs fluidpressurized by bleed air to ensure positive fluid flow. ¡ Each reservoir has a LOW QTY light ¡ Fluid flows through Shutoff valves (SOV) controlled by L & R Engine Fire switches Pulling Fire switch Ô closes the SOV Ô depressurizes the pump ¡ Engine pump = primary power ¡ Electric Demand Pump : Ô in AUTO - starts when pressure is low - Low Pressure only with pump signaled to operate. Ô LEFTinhibited on ground during engine start with only 1 generator (low pressure lights may illuminate)
Copyright © Smartcockpit.com Ludovic ANDRE / version 00
Smartcockpit.com
BOEING 767 SYSTEMS REVIEW
Page 2
4. CENTER SYSTEM
¡ Quantity and refill on EICAS ¡ CENTER system has an independent reservoir pressurized by Bleed air to ensure positive fluid flow ¡ The reservoir has a LOW QTY lightand a Standpipe to maintain a minimum level for operation of : BRAKES & STEERING in the event of a Center system hydraulic leak. ¡ Electric pumps = primary power ¡ N°2 electric pump inhibited with: Ô Only 1 generator operating Ô Both CENTER electric pump switches ON Ô LEFT and RIGHT demand pumps operating ¡ 2 Reserve brake and Steering control valves are automatically activated to allow a reservevolume of hydraulic fluid to be supplied to the CENTER N°1 Electric hydraulic pump : Ô aircraft inflight + CENTER hydraulics quantity level Low Ô SUPPLY valve opens to supply the N°1 pump Ô ISOLATION valve closes Ô ISLN light illuminates to indicate the isolation of the CENTER system. Ô A with failure of the auto system : - RESERVE BKS & STRG ON = pump operates regardless of pump switch position. -VALVE light ON and switch OFF = disagreement with auto isolation feature. switch ON = disagreement with manual selection. ¡ Air demand pump - CENTER system has a bleed air driven hydraulic pump (from the CENTER manifold) which provides hydraulic power when pressure is low or in case of large demand systems (gear, flaps, ground spoilers) - Air Demand Pump selector determines the pump mode ofoperation : Ô AUTO : the air pump operates when pressure is low or in case of large demand systems (gear, flaps, ground spoilers) Ô ON: the pump runs continuously - LOW pump pressure & Air demand pump OVERHEAT are provided. - Hydraulic Driven Generator (HDG) is automatically powered by the CENTER hydraulic system with loss of Main AC busses (in this case, the CENTER Air Demand Pump will operatecontinuously to ensure sufficient sufficient hydraulic pressure to drive the generator (A Extension time for Flaps and Slats is increased). ¡
Ram Air Turbine (RAT) Ô Located on the body fairing aft of the RIGHT main gear Ô Auto deploy with both engines failure & can only be retracted on the ground. Ô Speed should be > 130 kt for adequate power to the flight controls Ô Ram Air Turbine Pressure light...
BOEING 767 SYSTEMS REVIEW
Page 1
HYDRAULICS
1. GENERAL
¡ 3 separate & independent hydraulic systems : - Left Ô powered by 1 Engine pump & 1 Electric pump - Center Ô powered by 2 Electric pumps & 1 Air Driven pump - Right Ô powered by 1 Engine pump & 1 Electric pump ¡ Provide power to the : - Flaps / slats - Landing gear - Tailskid - Nose wheel steering - Brakes -Flight controls - A/P servos ¡ Center hydraulic system provide power (if both Main AC buses are lost) to the Hydraulic Driven Generator (HDG). If required, a Ram Air Turbine (RAT) can provide power to the flight controls portion of the Center hydraulic system (in case of double engine failure)
2. DISTRIBUTION L+C+R
Ô Elevators Ô Rudder Ô Spoilers Ô Stab Trim
L+R
Ô Outboard Ailerons
L only
ÔRudder ratio Ô Left A/P
L+C
Ô Yaw Dampers Ô Elevator Feel Ô Left Inboard aileron
R only
R+C
C only
Ô Tail Skid Ô Flaps & Slats Ô Main Gear Ô Nose gear Ô Nose Wheel Steering Ô Alternate Brakes Ô 5 KVA Gen Ô Center A/P Ô RAT
Ô Right Ô Normal Inboard aileron Brakes Ô Right A/P
3. LEFT AND RIGHT SYSTEMS
¡ Quantity and Refill on EICAS Status display ¡ Independent reservoirs fluidpressurized by bleed air to ensure positive fluid flow. ¡ Each reservoir has a LOW QTY light ¡ Fluid flows through Shutoff valves (SOV) controlled by L & R Engine Fire switches Pulling Fire switch Ô closes the SOV Ô depressurizes the pump ¡ Engine pump = primary power ¡ Electric Demand Pump : Ô in AUTO - starts when pressure is low - Low Pressure only with pump signaled to operate. Ô LEFTinhibited on ground during engine start with only 1 generator (low pressure lights may illuminate)
Copyright © Smartcockpit.com Ludovic ANDRE / version 00
Smartcockpit.com
BOEING 767 SYSTEMS REVIEW
Page 2
4. CENTER SYSTEM
¡ Quantity and refill on EICAS ¡ CENTER system has an independent reservoir pressurized by Bleed air to ensure positive fluid flow ¡ The reservoir has a LOW QTY lightand a Standpipe to maintain a minimum level for operation of : BRAKES & STEERING in the event of a Center system hydraulic leak. ¡ Electric pumps = primary power ¡ N°2 electric pump inhibited with: Ô Only 1 generator operating Ô Both CENTER electric pump switches ON Ô LEFT and RIGHT demand pumps operating ¡ 2 Reserve brake and Steering control valves are automatically activated to allow a reservevolume of hydraulic fluid to be supplied to the CENTER N°1 Electric hydraulic pump : Ô aircraft inflight + CENTER hydraulics quantity level Low Ô SUPPLY valve opens to supply the N°1 pump Ô ISOLATION valve closes Ô ISLN light illuminates to indicate the isolation of the CENTER system. Ô A with failure of the auto system : - RESERVE BKS & STRG ON = pump operates regardless of pump switch position. -VALVE light ON and switch OFF = disagreement with auto isolation feature. switch ON = disagreement with manual selection. ¡ Air demand pump - CENTER system has a bleed air driven hydraulic pump (from the CENTER manifold) which provides hydraulic power when pressure is low or in case of large demand systems (gear, flaps, ground spoilers) - Air Demand Pump selector determines the pump mode ofoperation : Ô AUTO : the air pump operates when pressure is low or in case of large demand systems (gear, flaps, ground spoilers) Ô ON: the pump runs continuously - LOW pump pressure & Air demand pump OVERHEAT are provided. - Hydraulic Driven Generator (HDG) is automatically powered by the CENTER hydraulic system with loss of Main AC busses (in this case, the CENTER Air Demand Pump will operatecontinuously to ensure sufficient sufficient hydraulic pressure to drive the generator (A Extension time for Flaps and Slats is increased). ¡
Ram Air Turbine (RAT) Ô Located on the body fairing aft of the RIGHT main gear Ô Auto deploy with both engines failure & can only be retracted on the ground. Ô Speed should be > 130 kt for adequate power to the flight controls Ô Ram Air Turbine Pressure light...
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