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(PSEU) which monitors various landing gear proximity sensing inputs and weight-on-wheels
inputs. If the correct parameters are met, the PSEU energizes a selector valve to retract or
extend the landing gear using hydraulic system No. 3 pressure.
The landing gear control handle is equipped with a solenoid lock which prevents an up
selection of the landing gear control handle with the aircraft on the ground. In the event of a
solenoid lock malfunction, a downlock release on the landing gear control panel, permits up
selection of the landing gear control handle by overriding the solenoid lock.
Retraction and extension of each landing gear is driven by a retract/extend actuator. An
auxiliary actuator, powered by hydraulic system No. 2 provides a backup means of
extending the main landing gear.
Tension springs assisted by a downlock actuator ensure that the main gear locks in the
down position. The lock is released at the start of the retraction cycle. An uplock assembly
locks the main gear in the retracted position. An uplock release actuator releases the uplock
assembly at the start of the extension cycle.
The nose landing gear locks in both the extended or retracted positions with a
spring-loaded, over-centre type locking mechanism. A lock actuator moves the locking
mechanism out of the over-center condition at the beginning of each cycle.
.
Vol. 1 16--20--2
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Main Landing Gear
Figure 16---20---1
MAIN LANDING GEAR
WHEEL BIN
LOCK ACTUATOR
DOWNLOCK
MECHANISM
MAIN LANDING GEAR
UPLOCK ASSEMBLY
RETRACT
ACTUATOR
AUXILIARY
ACTUATOR
SHOCK STRUT
ASSEMBLY
MAIN LANDING
GEAR DOOR
SHIMMY DAMPER
TORQUE
LINK ASSEMBLY
Outboard tire removed for clarity.
Brake assembly not shown.
NOTE
Vol. 1 16--20--3
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Nose Landing Gear
Figure 16---20---2
FORWARD
DOOR
SPIN DOWN
ASSEMBLY
LOCK
ACTUATOR
AFT
DOOR
TORQUE
LINK
ASSY
SHOCK STRUT
ASSEMBLY
STEERING
ACTUATOR
DRAG
BRACE
FORWARD
DOOR
RETRACT
ACTUATOR
Vol. 1 16--20--4
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
Landing Gear Retraction and Extension --- Schematic
Figure 16---20---3
ACCUMULATOR
NO.2 HYDRAULIC
SYSTEM
LANDING GEAR
MANUAL RELEASE
HANDLE
NO.2 HYDRAULIC
SYSTEM
LANDING GEAR
SELECTOR VALVE
LANDING GEAR
BYPASS VALVE
ACCUMULATOR
LH MAIN GEAR
RETRACT
ACTUATOR
LH MAIN GEAR
UPLOCK
LH MAIN GEAR
LOCK ACTUATOR
LH MAIN GEAR
AUXILIARY
ACTUATOR
DOWNLOCK
ASSIT
VALVE
RH MAIN GEAR
RETRACT
ACTUATOR
RH MAIN GEAR
UPLOCK
RH MAIN GEAR
LOCK ACTUATOR
RH MAIN GEAR
AUXILIARY
ACTUATOR
NLG RETRACT
ACTUATOR
NLG LOCK
ACTUATOR
NLG MANUAL
RELEASE
ACTUATOR
PSEU
RETURN
EICAS
Vol. 1 16--20--5
LANDING GEAR
Nose and Main Landing Gear REV 3, May 03/05
Flight Crew Operating Manual
CSP C--013--067
For landing gear retraction:
Once the aircraft is airborne, with no weight-on-wheels signal, the PSEU commands
and monitors the following events:
S The landing gear control handle solenoid downlock is released to permit UP
selection of the landing gear control handle.
S The landing gear selector valve energizes the nose and main landing gear
retract/extend actuators, releases the downlocks and retracts the landing gear.
Hydraulic pressure from the landing gear up line is routed to activate the brake
control valves to stop main wheel rotation. The tire spin--down assembly in the nose
landing gear bay stops nose wheel rotation.
S Uplocks are engaged to secure the landing gears in the retracted position.
For landing gear extension:
The PSEU commands and monitors the following events:
S The landing gear control handle is manually selected to the DN position.
S The landing gear selector valve energizes the nose and main landing gear
retract/extend actuators, releases the uplocks and extends the landing gear.
S Downlocks are engaged to secure the landing gear in the extended position.
To prevent the landing gear from retracting when the aircraft is on the ground, ground lock
　
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