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TRIPLE INDICATOR
The triple indicator displays the yellow brake
accumulator pressure.
It also displays the yellow braking pressure delivered
to the left and right hand brakes.
LANDING GEAR CONTROL LEVER
The landing gear lever must be pulled before selecting
one of the two possible positions.
When the landing gear is not downlocked in landing
configuration, the red arrow of the control lever comes
on.
GRAVITY EXTENSION CRANK HANDLE
When the normal extension system fails, the gear can
be extended by gravity.
The crank handle must be pulled, then rotated three
turns clockwise.
PARKING BRAKE HANDLE
When the parking brake handle is pulled and turned to
the "ON" position, yellow pressure is applied to the
brakes.
CAUTION : No progressive pressure can be applied using
the parking brake system.
As long as the parking brake handle is "ON",
brake pressure is not necessarily applied
due to limited autonomy of the system
accumulator.
ECAM SYSTEM DISPLAY
The ECAM "WHEEL" page displays landing gear and door
positions, as well as braking and steering indications.
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EFFECTIVITY 32-00-00 Page 2
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 32 LANDING GEAR
UF94200
EFFECTIVITY Page 10
ALL
GENERAL LANDING GEAR SYSTEM CONTROLS AND INDICATING PRESENTATION
TMULD40ZZ-P01 LEVEL 1
EFFECTIVITY 32-00-00 Page 3
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_A319/A320/A321 TECHNICAL TRAINING MANUAL
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EFFECTIVITY Page 11
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GENERAL LANDING GEAR SYSTEM CONTROLS AND INDICATING PRESENTATION
RUDDER PEDALS
Manual Braking is provided by the Captain and First
Officer brake pedals.
Nose wheel steering is also provided by the Captain
and First Officer rudder pedals.
NOSE WHEEL STEERING HANDLE
The steering handwheels control the nose wheel steering
angle up to 74° in either direction.
On each handwheel, a rudder pedal disconnect pushbutton
allows the rudder pedal steering orders to be
disconnected.
BRAKE FAN CONTROL PANEL (OPTIONAL)
The BRK FAN pushbutton is used to operate the brake
fans when a brake overheat is detected.
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EFFECTIVITY 32-00-00 Page 4
Oct 31/97
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 32 LANDING GEAR
UF94200
EFFECTIVITY Page 12
ALL
32 - LANDING GEAR
32-30-00 LANDING GEAR RETRACTION/EXTENSION
PRESENTATION
CONTENTS:
Principle
Normal Retraction
Normal Extension
Free Fall Extension
Self Examination
TMULDGD05 LEVEL 1
EFFECTIVITY 32-30-00 Page 1
Nov 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 32 LANDING GEAR
UF94200
EFFECTIVITY Page 13
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LANDING GEAR RETRACTION/EXTENSION PRESENTATION
PRINCIPLE
Gear and door sequencing is electrically controlled
by Landing Gear Control and Interface Units (LGCIU) 1
and 2.
Each Landing Gear Control Interface Unit in turn
controls a complete gear cycle : one "UP" selection
and one "DOWN" selection.
They switch over automatically at each retraction
cycle, or in case of sequencing system failure.
The gear up and down positions and the door close and
open positions are monitored by duplicated detectors.
An interlock mechanism prevents unsafe retraction by
locking the lever in the "DOWN" position when any shock
absorber is not extended.
NOTE : The nose wheel is automatically centered by a
cam when the shock absorber is extended.
The two systems are electrically segregated with
different connections on the related selector valves.
The landing gear is powered by the green hydraulic
system. In case of failure, the gear can be extended
mechanically from the cockpit by means of a gravity
extension crank handle.
The safety valve cuts landing gear hydraulic supply
in normal landing gear retraction/extension ; the
cut-out valve cuts landing gear hydraulic supply in
free fall extension.
LGCIU 1 provides gear positions to the landing gear
indicator panel.
LGCIU 1 and 2 provide gear and door positions to the
ECAM system.
Other aircraft systems are linked to the LGCIUs for
"flight/ground" signals.
TMULDGD05-T01 LEVEL 1
EFFECTIVITY 32-30-00 Page 2
Nov 30/98
_A319/A320/A321 TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE 32 LANDING GEAR
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