A319/A320/A321
TECHNICAL TRAINING MANUAL
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
This document must be used for training purpose only
Under no circumstances should this document be used as a reference.
It will not be updated.
All rights reserved.
No part of this manual may be reproduced in any form,
by photostat, microfilm, retrieval system, or any other means,
without the prior written permission of Airbus Industrie.
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 LANDING GEAR
UFD4200
UFD4200
TABLE OF CONTENTS
Page
GENERAL
** System Presentation (1) ....................... 1
** System Controls & Indicating Present. (1) .... 9
** Wheel Components (3) ........................ 237
** Brake Temperature System Components (3) .... 249
** Brake Cooling System Components (3) ........ 253
LANDING GEAR AND DOORS
** Retraction/Extension Presentation (1) ....... 13
** System Indications (1) ....................... 23
** System Warnings (3) .......................... 27
** System Normal Operation (3) .................. 31
** Free Fall Extension (3) ...................... 47
** Safety Precautions (2) ....................... 57
** Doors Ground Operation (2) ................... 65
** Doors Ground Opening D/O (3) ................. 71
** LGCIU Control Signals (3) .................... 77
** LGCIU Monitoring Interfaces (3) ............. 81
** MLG Description (2) .......................... 87
** MLG Doors Description (2) .................... 97
** NLG Description (2) ......................... 101
** NLG Doors Description (2) ................... 105
** Landing Gear Components (2) ................. 109
** Landing Gear Components (3) ................. 115
NOSE WHEEL STEERING
** System Presentation (1) ..................... 257
** System Description/Operation (3) ........... 261
** ECAM Page Presentation (1) .................. 267
** System Warnings (3) ......................... 271
** Components (2) ............................... 273
** Components (3) ............................... 277
WHEELS AND BRAKES
** Brake System Presentation (1)............... 137
** Brake System Description (3) ................ 151
** Auto-Brake System D/O (3) ................... 155
** Anti-Skid Function (3) ...................... 159
** Brake Hydraulic System Operation (3) ....... 163
** Brake Temperature System Presentation (3) .. 173
** Brake Cooling System Presentation (1) ...... 177
** ECAM Page Presentation (1) .................. 181
** System Warnings (3) ......................... 185
** Normal Braking Components (3)............... 187
** Alternate Braking Components (3) ........... 209
** Parking Brake Components (3) ................ 227
EFFECTIVITY
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BRAKING AND STEERING
** BSCU Control Interfaces (3) ................. 285
** BSCU Architecture & Monitoring INTFC (3) ... 289
TIRE PRESSURE INDICATING
** System Presentation (1) ..................... 295
** System Description/Operation (3) ........... 299
** System Warnings (3) ......................... 303
** Components (3) ............................... 305
MAINTENANCE PRACTICES
** MLG Servicing (3)............................ 313
** MLG Shock Absorber Servicing (3) ........... 319
** Low PRESS Circuit Filling and Bleeding(3) .. 337
** Wheel and Brake R/I (2) ..................... 341
** CFDS Specific Page Presentation (3) ........ 347
32 CONTENTS
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 LANDING GEAR
UFD4200
TABLE OF CONTENTS
Page
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
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32 CONTENTS
Page ii
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 GENERAL SYSTEM PRESENTATION
TMULDG101 LEVEL 1
UFD4200
CONTENTS:
Gear
Extension/Retraction
Brakes
Steering
Self Examination
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32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
GEAR
TMULDG101-T01 LEVEL 1
UFD4200
The landing gear consists of a forward retracting nose
gear and two inboard retracting main gear legs.
Each gear has an oleopneumatic shock absorber and is
equipped with two wheels.
Each main wheel is fitted with anti-skid wheel brakes.
The two-wheel nose gear comprises an oleopneumatic
shock absorber and a nose wheel steering system.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
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32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
EXTENSION/RETRACTION
Gear and doors are electrically controlled and
hydraulically operated by the green hydraulic system.
The hydraulically operated doors open during landing
gear transit.
These doors close each time the landing gear is fully
extended or retracted.
The doors which are fitted to the landing gear struts
are mechanically operated by the gear and close at the
end of gear retraction.
BRAKES
TMULDG101-T02 LEVEL 1
UFD4200
Carbon multidisc brakes are installed on the main gear
wheels.
During take-off, the nose wheels are automatically
centered by means of two centering cams.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
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32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
STEERING
TMULDG101-T03 LEVEL 1
UFD4200
The nose wheel steering system is electrically
controlled and is powered by the green hydraulic
system.
This enables an available powered steering over the
range of 74° below 22 knots.
In addition, the aircraft can be towed or pushed back
to a nose wheel angle of 95° from the aircraft
centerline after inserting a steering pin without any
mechanical disconnection.
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32 LANDING GEAR
LANDING GEAR GENERAL SYSTEM PRESENTATION
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32 LANDING GEAR
SELF EXAMINATION
Which hydraulic system powers normal landing gear
operation ?
A - Green system.
B - Blue system.
C - Yellow system.
TMULDG101 LEVEL 1
UFD4200
Which hydraulic system powers the nose wheel
steering ?
A - Green system.
B - Blue system.
C - Yellow system.
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32 LANDING GEAR
32 - LANDING GEAR
32-00-00 GENERAL LANDING GEAR SYSTEM
CONTROLS AND INDICATING
PRESENTATION
TMULD40ZZ LEVEL 1
UFD4200
CONTENTS:
Landing Gear Panel
Auto Brake Panel
A/SKID & N/W STRG Switch
Triple Indicator
Landing Gear Control Lever
Gravity Extension Crank Handle
Parking Brake Handle
ECAM System Display
Rudder Pedals
Nose Wheel Steering Handle
Brake Fan Control Panel
EFFECTIVITY
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32 LANDING GEAR
GENERAL LANDING GEAR SYSTEM CONTROLS AND INDICATING PRESENTATION
LANDING GEAR PANEL
LANDING GEAR CONTROL LEVER
Two indications are provided for each gear :
- a red "UNLK" light indicates that the
corresponding gear is not locked in the
selected position,
- a green triangle indicates that the related
gear is locked down.
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
AUTO BRAKE PANEL
The three auto brake pushbuttons (LO, MED, MAX) control
the arming of the required deceleration rate.
The "ON" light comes on blue when the related
pushbutton is selected and the system is armed.
The "DECEL" light comes on green when the correct
deceleration is reached.
A/SKID & N/W STRG SWITCH
TMULD40ZZ-T01 LEVEL 1
UFD4200
The A/SKID & N/W STRG switch is normally in the "ON"
position and it is used to isolate anti-skid and nose
wheel steering functions.
When it is set to "OFF", the DC supply of the Braking
and Steering Control Unit (BSCU) is isolated.
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.
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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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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
GENERAL LANDING GEAR SYSTEM CONTROLS AND INDICATING PRESENTATION
EFFECTIVITY
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32 LANDING GEAR
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)
TMULD40ZZ-T01 LEVEL 1
UFD4200
The BRK FAN pushbutton is used to operate the brake
fans when a brake overheat is detected.
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32 LANDING GEAR
32 - LANDING GEAR
32-30-00 LANDING GEAR RETRACTION/EXTENSION
PRESENTATION
TMULDGD05 LEVEL 1
UFD4200
CONTENTS:
Principle
Normal Retraction
Normal Extension
Free Fall Extension
Self Examination
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32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION
TMULDGD05-T01 LEVEL 1
UFD4200
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.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION (PRINCIPLE)
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION
NORMAL RETRACTION
At this stage of the operation, the landing gear is
down and locked.
The aircraft is in flight configuration.
Landing Gear Control and Interface Unit 1 is in
command.
Landing Gear Control and Interface Unit 2 is in
standby.
At each gear UP selection, there is a changeover from
LGCIU 1 to LGCIU 2 (or vice versa).
TMULDGD05-T02 LEVEL 1
UFD4200
Landing gear retraction cycle :
- DOORS OPEN.
- GEAR RETRACTS : When all hydraulic operated
doors are fully open, the
landing gear is controlled to
retract.
- DOORS CLOSE : When all the landing gear is
locked up, the doors are
controlled to close.
The hydraulic supply to the landing gear circuit is
automatically cut off by a safety valve above 260
knots.
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION (NORMAL RETRACTION)
EFFECTIVITY
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ALL
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32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION
NORMAL EXTENSION
All gears are retracted and uplocked, all doors are
closed and uplocked and the safety valve is closed.
At each gear DOWN selection, the safety valve opens
and the LGCIU in command controls the extension
sequence.
TMULDGD05-T03 LEVEL 1
UFD4200
Landing gear extension cycle :
- DOORS OPEN.
- GEAR EXTENDS : When all hydraulic operated
doors are fully open, the
landing gear is controlled to
extend.
- DOORS CLOSE : When all the landing gear is
locked down, the doors are
controlled to close.
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION (NORMAL EXTENSION)
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION
FREE FALL EXTENSION
Rotation of the handle closes the cut out valve and
connects all landing gear hydraulic components to the
return line, and releases door and gear uplocks.
The doors stay open. The main landing gear is locked
down by spring forces. The nose landing gear is locked
down by aerodynamic forces.
Then the landing gear lever must be set to down in
order to switch off the UNLK lights.
TMULDGD05-T04 LEVEL 1
UFD4200
NOTE : As the landing gear system is depressurized and
the nose landing gear doors stay open, the nose
wheel steering is lost.
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TMULDGD05-P04 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION/EXTENSION PRESENTATION (FREE FALL EXTENSION)
EFFECTIVITY
EFFECTIVITY
ALL
32-30-00
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32 LANDING GEAR
SELF EXAMINATION
What controls the landing gear normal operating
sequence ?
A - Either LGCIU in turn.
B - Both LGCIUs simultaneously.
C - The crank handle.
Which unit gives the landing gear position to ECAM
display ?
A - Either LGCIU in turn.
B - Both LGCIUs simultaneously.
C - LGCIU 1 only.
TMULDGD05 LEVEL 1
UFD4200
When does the automatic changeover of the LGCIUs in
control occur?
A - When "DOWN" is selected.
B - When "UP" is selected.
C - When the first engine starts.
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-61-00 LANDING GEAR SYSTEM INDICATIONS
TMULDG501 LEVEL 1
UFD4200
CONTENTS:
Landing Gear System Indicator Panel
ECAM Page
Self Examination
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR SYSTEM INDICATIONS
The landing gear indicator panel indicates the landing
gear positions monitored by Landing Gear Control and
Interface Unit 1 (LGCIU 1).
This indicator has to be used as a back up. The primary
indication system, displayed on the ECAM, receives
data from both LGCIUs.
LANDING GEAR SYSTEM INDICATOR PANEL
L/G DOOR POSITION INDICATIONS
The landing gear door position indications
displayed as shown on the table below.
are
L/G CTL INDICATION
A "L/G CTL" (Landing gear control) indication appears
amber in case of disagreement between the landing gear
lever and landing gear position.
UNLOCK LIGHT
An "UNLK" light is provided for each gear.
It comes on red when the corresponding gear is not
locked in the selected position.
TRIANGLE LIGHT
A green triangle light comes on when the corresponding
gear is locked down.
ECAM PAGE
TMULDG501-T01 LEVEL 1
UFD4200
L/G POSITION INDICATIONS
The different landing gear positions are monitored by
both Landing Gear Control and Interface Units and are
displayed on the WHEEL page as shown on the table
below.
L/G UP LOCK INDICATIONS
The "UP LOCK" indication appears amber if the
respective up lock is engaged when the gear is locked
down.
"UP LOCK" (amber) : In our example the nose gear and
the right main gear up locks are engaged while the
gear is locked down.
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UFD4200
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32 LANDING GEAR
LANDING GEAR SYSTEM INDICATIONS
EFFECTIVITY
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32 LANDING GEAR
SELF EXAMINATION
TMULDG501 LEVEL 1
UFD4200
When does the UNLK light come on ?
A - When the gear and the related doors are
not locked up.
B - When the gear is not locked down.
C - When the gear is not locked in the
selected position.
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-61-00 LANDING GEAR SYSTEM WARNINGS
TMULDA601 LEVEL 3
UFD4200
CONTENTS:
Gear Not Downlocked
Gear Not Down
Shock Absorber Fault
Doors Not Closed
Gear Not Uplocked
Gear Uplock Fault
LGCIU 1 (2) Fault
System Disagree
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
LANDING GEAR SYSTEM WARNINGS
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UFD4200
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32 LANDING GEAR
LANDING GEAR SYSTEM WARNINGS
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TMULDA601 LEVEL 3
UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-31-00 LANDING GEAR NORMAL OPERATION
TMULDGE03 LEVEL 3
UFD4200
CONTENTS:
Extension
Retraction
Self Examination
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
EXTENSION
TMULDGE03-T01 LEVEL 3
UFD4200
DOOR OPENING
When DOWN is selected, the Landing Gear Control and
Interface Unit takes the control of the extension
sequence.
The LGCIU signals the doors to open via selector valves
and the door proximity detectors signal the doors’
fully open position back to the LGCIU in order to
continue the sequence.
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
LANDING GEAR EXTENSION - DOOR OPENING
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
EXTENSION
TMULDGE03-T02 LEVEL 3
UFD4200
GEAR DOWN
When ALL doors are fully open, the LGCIU commands a
gear extension while maintaining the doors "open"
signal.
The gear proximity detectors signal to the LGCIU that
the gears are downlocked.
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32-31-00
Page
Page34
4
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGE03-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR EXTENSION - GEAR DOWN
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page35
5
Nov 30/97
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
EXTENSION
TMULDGE03-T03 LEVEL 3
UFD4200
DOOR CLOSING
When ALL the gear is down and locked, the LGCIU signals
the doors to close and lock stay actuators to
pressurize, while maintaining the gear extended
signal.
Door closing hydraulic pressure is fed to the lock
stay actuators to back up the downlock springs.
Door uplock proximity detectors signal to the LGCIU
that the doors are uplocked.
As the doors begin to close, the LGCIU cancels the
gear extended signal while maintaining the door "close"
signal.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page36
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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TMULDGE03-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR EXTENSION - DOOR CLOSING
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page37
7
Nov 30/97
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
RETRACTION
Setting the landing gear control lever to UP causes
system 1 and 2 changeover. This allows the system which
was previously in standby to control the next
retraction and extension sequence.
Each Landing Gear Control Interface Unit controls one
complete gear cycle: one UP selection and one DOWN
selection.
TMULDGE03-T04 LEVEL 3
UFD4200
DOOR OPENING
The LGCIU must detect all three shock absorbers
extended before allowing the selection of the landing
gear control lever to UP.
The LGCIU signals the doors to open via selector
valves, and the doors proximity detectors signal the
doors’ fully open position back to the LGCIU, in order
to continue the sequence.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page38
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_
TMULDGE03-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION - DOOR OPENING
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page39
9
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
RETRACTION
TMULDGE03-T05 LEVEL 3
UFD4200
GEAR UP
When ALL doors are fully open, the LGCIU signals the
landing gear to raise while maintaining the doors
"open" signal to keep the doors "open" line
pressurized.
The gear uplock proximity detectors signal the LGCIU
that the gear is uplocked.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 40
10
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGE03-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION - GEAR UP
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 41
11
Nov 30/97
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
RETRACTION
TMULDGE03-T06 LEVEL 3
UFD4200
DOOR CLOSING
When ALL the landing gear is up and locked, the LGCIU
signals the doors to close while maintaining landing
gear UP signal to keep the "raise" line pressurized.
Door uplock proximity detectors signal the LGCIU that
the doors are uplocked.
As soon as the last door closes and locks, the LGCIU
cancels the landing gear "raise" signal and maintains
the door close signal as long as the safety valve is
open.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 42
12
Nov 30/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGE03-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION - DOOR CLOSING
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 43
13
Nov 30/97
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR NORMAL OPERATION
RETRACTION
TMULDGE03-T07 LEVEL 3
UFD4200
HYDRAULIC SHUT OFF
Air Data Inertial Reference Units 1 and 3 send a signal
to the safety valve to shut off the hydraulic pressure
to the landing gear system.
When the airspeed is greater than 260 ±5 kts the
hydraulic circuit to the landing gear is depressurized.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 44
14
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TMULDGE03-P07 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR RETRACTION - HYDRAULIC SHUT OFF
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 45
15
Nov 30/97
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
What is the normal retraction sequence?
A - Door open, gear up, door close, cancel
gear up signal.
B - Door open, gear up, door close, maintain
gear up signal.
C - Door open, gear up, door close, cancel
door close signal.
Before the landing gear can be retracted, what must
the LGCIU detect?
A - Three shock absorbers extended.
B - Three shock absorbers compressed.
C - Only one shock absorber extended.
TMULDGE03 LEVEL 3
UFD4200
When is the hydraulic circuit depressurized after
retraction?
A - As soon as the selector lever is moved
to neutral.
B - As soon as the airspeed is greater than
260 ± 5 kts.
C - As soon as the last door is closed.
EFFECTIVITY
EFFECTIVITY
ALL
32-31-00
Page
Page 46
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-33-00 LANDING GEAR AND DOORS - FREE
FALL EXTENSION
TMULDGL02 LEVEL 3
UFD4200
CONTENTS:
General
Initial Configuration
Lever Movement up to 1.5 Turns
Lever Movement between 1.6 and 1.8 Turns
Lever Movement between 1.9 and 3 Turns
Self Examination
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page47
1
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS - FREE FALL EXTENSION
GENERAL
Free fall extension is used either when :
- both LGCIUs have failed,
- green hydraulic low pressure,
- one door cannot be opened hydraulically,
- one gear leg cannot be lowered hydraulically.
If both LGCIUs fail the solenoids are not energized
and the door "close" lines are not pressurized.
If the green hydraulic pressure is low the door "close"
lines are not pressurized.
INITIAL CONFIGURATION
TMULDGL02-T01 LEVEL 3
UFD4200
The safety valve is open and residual pressure supplies
the door "close" line downstream of the selector valve.
Gears and doors are uplocked.
Note that the door bypass valves (1, 2 and 3) are only
operated during ground maintenance.
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page48
2
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGL02-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
FREE FALL EXTENSION - INITIAL CONFIGURATION
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page49
3
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS - FREE FALL EXTENSION
LEVER MOVEMENT UP TO 1.5 TURNS
TMULDGL02-T02 LEVEL 3
UFD4200
Rotating the gravity extension crank handle initially
operates the cut-out valve and both vent valves to
depressurize the system by connecting the entire
landing gear hydraulic system to return.
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page50
4
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGL02-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT UP TO 1.5 TURNS
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page51
5
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS - FREE FALL EXTENSION
LEVER MOVEMENT BETWEEN 1.6 AND 1.8 TURNS
TMULDGL02-T03 LEVEL 3
UFD4200
Then the door uplocks are released.
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page52
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Jan 31/95
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_
TMULDGL02-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT BETWEEN 1.6 AND 1.8 TURNS
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page53
7
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS - FREE FALL EXTENSION
LEVER MOVEMENT BETWEEN 1.9 AND 3 TURNS
Finally the gear uplocks are released and the landing
gear extends by gravity.
TMULDGL02-T04 LEVEL 3
UFD4200
NOTE: Normal landing gear operation is restored by
rotating
the
crank
handle
3
turns
anti-clockwise.
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page54
8
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGL02-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT BETWEEN 1.9 AND 3 TURNS
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page55
9
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
TMULDGL02 LEVEL 3
UFD4200
What happens when the gravity extension crank
handle is rotated?
A - The cut-out and vent valves operate.
B - The safety and cut-out valves operate.
C - The safety and vent valves operate.
EFFECTIVITY
EFFECTIVITY
ALL
32-33-00
Page
Page 56
10
Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 LANDING GEAR SAFETY PRECAUTIONS
TMULDGJ02 LEVEL 2
UFD4200
CONTENTS:
Landing Gear Control Lever
Hydraulic
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page57
1
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS
LANDING GEAR CONTROL LEVER
The lever is locked in the "DOWN" position by an
interlock mechanism as soon as either Landing Gear
Control and Interface Unit (LGCIU) detects any shock
absorber not extended or nose wheels not centered.
TMULDGJ02-T01 LEVEL 2
UFD4200
NOTE : Nose gear shock absorber extended and nose
wheels centered signal comes from the same
proximity detectors.
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page58
2
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGJ02-P01 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - LANDING GEAR CONTROL LEVER
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page59
3
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS
HYDRAULIC
Be sure that all safety precautions are carried out
before working on landing gear :
- wheel chocks are in place,
- hydraulic system is depressurized,
- safety sleeves and safety pins are fitted on
the landing gear and landing gear doors,
- ground door opening handles are in the open
position.
TMULDGJ02-T02 LEVEL 2
UFD4200
MLG AND MLG DOOR SAFETY DEVICES
(see following page).
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page60
4
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGJ02-P02 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - MLG AND MLG DOOR SAFETY DEVICES
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page61
5
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS
HYDRAULIC
TMULDGJ02-T03 LEVEL 2
UFD4200
NLG AND NLG DOOR SAFETY DEVICES
(see following page).
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page62
6
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGJ02-P03 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - NLG AND NLG DOOR SAFETY DEVICES
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page63
7
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TMULDGJ02 LEVEL 2
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page64
8
Oct 31/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 LANDING GEAR DOORS GROUND
OPERATION
TMULDGC03 LEVEL 2
UFD4200
CONTENTS:
Main Landing Gear Door Ground Operation
Nose Landing Gear Doors Ground Operation
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page65
1
Jul 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION
MAIN LANDING GEAR DOOR GROUND OPERATION
The main landing gear doors can be opened on the ground,
for servicing or inspection purposes.
TMULDGC03-T01 LEVEL 2
UFD4200
DOOR OPENING PREPARATION
Precautions have to be taken before the doors are
opened:
Outside,
- ground safeties and main wheel chocks, in
place,
- downlock safety pin, IN.
In the cockpit, put the warning notices on,
- the free fall handle and on the landing gear
control lever,
- make sure that the green hydraulic system is
depressurized.
Outside again,
- make certain that the door travel ranges are clear.
DOOR OPENING
Stand forward of the door. Open, the blue hydraulic
bay servicing panel for the left hand side door or the
yellow hydraulic bay servicing panel for the right
hand side door.
Disengage the safety pin, press the button at the end
of the handle, rotate the handle to the open position.
The door opens by gravity.
Safety it when fully opened.
CAUTION: A SAFETY SLEEVE MUST BE FITTED ON THE ACTUATOR
PISTON ROD IMMEDIATELY AFTER IT HAS BEEN
OPENED ON THE GROUND, AND BEFORE WORKING IN
THE GEAR WELL.
EFFECTIVITY
EFFECTIVITY
ALL
DOOR CLOSING PREPARATION
After servicing, the door can be closed.
Here are the precautions that have to be taken:
In the cockpit,
- landing gear control lever DOWN with the
warning notice in position,
- landing gear free fall crank handle in the
normal position: folded and a warning notice
in position,
- green hydraulic system depressurized.
On the ground,
- make certain that the ground door opening
control handle is locked in the OPEN position,
- remove the safety sleeve from the actuator,
- make certain that the door travel ranges are
clear.
In the cockpit again,
- make sure that the external power is ON,
- pressurize the green hydraulic system,
- check the pressure on the ECAM page.
DOOR CLOSING
On the ground,
- Reposition the ground door opening control
handle in the CLOSED position (the door closes)
and put the safety pin back in position,
- close the access panel.
In the cockpit,
- check that doors are UP and LOCKED, on the
WHEEL ECAM page,
- depressurize the hydraulic systems,
- and remove the warning notices.
32-00-00
Page
Page66
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Jul 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGC03-P01 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION - MAIN LANDING GEAR DOOR GROUND OPERATION
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page67
3
Jul 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION
NOSE LANDING GEAR DOORS GROUND OPERATION
The nose landing gear doors can be opened on the ground,
for servicing or inspection purposes.
TMULDGC03-T02 LEVEL 2
UFD4200
DOORS OPENING PREPARATION
Some precautions have to be taken before the doors are
opened:
Outside,
- ground safeties and nose wheel chocks, in
place,
- downlock safety pin, IN.
In the cockpit,
- put warning notices on the free fall handle
and the landing gear control lever,
- make sure that the green hydraulic system is
depressurized.
Outside again,
- make certain that the door travel ranges are
clear.
DOORS OPENING
Stand AFT of the gear leg.
Disengage the safety pin, press the button at the end
of the handle and rotate the handle to the open
position.
Doors open by gravity.
Lock them with the safety pins.
EFFECTIVITY
EFFECTIVITY
ALL
CAUTION: A SAFETY PIN MUST BE FITTED ON EACH DOOR
IMMEDIATELY AFTER IT HAS BEEN OPENED ON THE
GROUND AND BEFORE WORKING IN THE NOSE GEAR
WELL.
ADJUST THE DOOR POSITION MANUALLY TO EASE THE
INSTALLATION OF THE SAFETY PIN IF NECESSARY.
DOORS CLOSING PREPARATION
After servicing, the doors can be closed, here are
some precautions that have to be taken:
In the cockpit,
- landing gear control lever DOWN with the
warning notice in position,
- landing gear free fall crank handle in the
normal position: folded and the warning notice
in position,
- green hydraulic system depressurized.
On the ground,
- make certain that the ground door opening
control handle is locked in the open position,
- remove the safety pin from the doors,
- make certain that the door travel ranges are
clear.
In the cockpit again,
- make sure that the external power is ON,
- pressurize the green hydraulic system,
- check the pressure on the ECAM page.
32-00-00
Page
Page68
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Jul 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGC03-P02 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION - NOSE LANDING GEAR DOORS GROUND OPERATION
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page69
5
Jul 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION
NOSE LANDING GEAR DOORS GROUND OPERATION (CONTINUED)
TMULDGC03 LEVEL 2
UFD4200
DOORS CLOSING
On the ground,
- reposition the ground door opening control
handle in the CLOSED position (the doors close)
and put the safety pin back in position.
In the cockpit,
- check that doors are UP and LOCKED, on the
WHEEL ECAM page,
- depressurize the hydraulic systems,
- and remove the warning notices.
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page70
6
Jul 31/96
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 LANDING GEAR DOORS GROUND
OPENING DESCRIPTION/OPERATION
TMULDGW01 LEVEL 3
UFD4200
CONTENTS:
General
Main Doors
Nose Doors
Hydraulic Operation
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page71
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Aug 31/96
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_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPENING DESCRIPTION/OPERATION
GENERAL
NOSE DOORS
Each main door and nose door has a ground door opening
system that comprises these primary components :
- a ground door opening control handle,
- a mechanical transmission,
- a by-pass valve,
- a release mechanism in the door uplock.
The control handle has two lockable positions.
When it is set to the "DOOR OPEN" position, it causes
the mechanical system to :
- operate the door by-pass valve,
- release the door from its uplock.
This prevents a hydraulic lock, and allows the
hydraulic fluid to be released from the door actuating
cylinder "DOOR CLOSED" line. The door then moves by
gravity.
The ground opening control handle is located in a
housing in the aft of the nose landing gear bay. This
location places the operator in a safe position with
a clear view of the door travel.
The handle is connected to a lay shaft on the door
by-pass valve and the door uplock on the left hand
side wall of the nose landing gear bay.
TMULDGW01-T01 LEVEL 3
UFD4200
MAIN DOORS
The ground opening control handle is located forward
of the respective main landing gear bay into the
hydraulic compartment. This location places the
operator in a safe position with a clear view of the
door travel.
The handle is connected through a push-pull cable to
the door by-pass valve on the outboard side of the
main landing gear bay.
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page72
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Aug 31/96
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGW01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS GROUND OPENING DESCRIPTION/OPERATION - MAIN DOORS - NOSE DOORS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page73
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR DOORS GROUND OPENING DESCRIPTION/OPERATION
HYDRAULIC OPERATION
TMULDGW01-T02 LEVEL 3
UFD4200
Each by-pass valve has three hydraulic connections
marked A, B and C.
- port A : door open line,
- port B : door close line from the selector
valve,
- port C : door close line to the door actuating
cylinder.
During normal operation of the landing gear, port A
is closed and port B is connected to port C allowing
the respective door actuating cylinder and door uplock
to be operated.
When the ground door opening control handle is
operated, port B is closed and port A is connected to
port C.
A locking plunger in the by-pass valve stops the
movement of the control lever from the "DOOR OPEN" to
the "DOOR CLOSED" position.
Before any selection can be made, a hydraulic pressure
greater than 70 bars (1015 psi) must be supplied to
port B to retract the locking plunger.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR AND DOORS GROUND OPENING DESCRIPTION/OPERATION - HYDRAULIC OPERATION
EFFECTIVITY
EFFECTIVITY
ALL
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TMULDGW01 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-31-00 LANDING GEAR AND DOORS - LGCIU
CONTROL SIGNALS
TMULDGG01 LEVEL 3
UFD4200
CONTENTS:
Up Selection
Down Selection
Door Uplocks
Door Fully Open
Gear Uplocks
Gear Downlocks
Extended or Compressed
Door Selector Valve
Gear Selector Valve
L/G Retraction Interlock Solenoid
LGCIU 2
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - LGCIU CONTROL SIGNALS
UP SELECTION
GEAR DOWNLOCKS
Two UP selection signals which come from the lever,
are sent to the Landing Gear Control Interface Unit
(LGCIU) to initiate the gear retraction sequence.
Three gear downlock signals which come from gear
downlock proximity detectors, are sent to the LGCIU
to indicate whether gears are down and locked, or not.
DOWN SELECTION
EXTENDED OR COMPRESSED
Two DOWN selection signals coming from the lever, are
sent to the LGCIU to initiate the gear extension
sequence.
Three shock-absorber signals which come from the oleo
proximity detectors are sent to the LGCIU to indicate
whether shock-absorbers are compressed, or not.
Note that nose landing gear "flight" information is
given when the gear is extended and wheels are in the
centered position.
DOOR UPLOCKS
Three door uplock signals which come from door uplock
proximity detectors, are sent to the LGCIU to indicate
whether doors are uplocked, or not.
DOOR SELECTOR VALVE
DOOR FULLY OPEN
After analysing all the input signals, the LGCIU sends
two signals to the corresponding solenoid of the door
selector valve according to the position of the gears.
Four door fully open signals (two for nose doors) which
come from the corresponding proximity detectors, are
sent to the LGCIU to indicate whether doors are fully
open, or not.
TMULDGG01-T01 LEVEL 3
UFD4200
GEAR UPLOCKS
Three gear uplock signals which come from gear uplock
proximity detectors, are sent to the LGCIU to indicate
whether gears are uplocked, or not.
EFFECTIVITY
EFFECTIVITY
ALL
GEAR SELECTOR VALVE
After analysing all the input signals, the LGCIU sends
two signals to the corresponding solenoid of the gear
selector valve according to the position of the doors.
L/G RETRACTION INTERLOCK SOLENOID
After analysing all shock absorber signals, the LGCIU
sends a signal to the lever interlock solenoid to
prevent gear retraction if any shock absorber is
compressed.
32-31-00
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LGCIU CONTROL SIGNALS
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - LGCIU CONTROL SIGNALS
LGCIU 2
for
system
TMULDGG01-T01 LEVEL 3
UFD4200
Same control signals for LGCIU 2.
Four signals are used by the LGCIU
selection:
- two for system 1 status,
- two for system 2 status.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-60-00 LANDING GEAR AND DOORS - LGCIU
MONITORING INTERFACES
TMULDGH01 LEVEL 3
UFD4200
CONTENTS:
ARINC and Indicator Panel
Discrete
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - LGCIU MONITORING INTERFACES
ARINC AND INDICATOR PANEL
TMULDGH01-T01 LEVEL 3
UFD4200
After analyzing both gear uplock and downlock signals,
the LGCIU sends up to six signals to the corresponding
lights on the landing gear indicator panel.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LGCIU MONITORING INTERFACES - ARINC AND INDICATOR PANEL
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LGCIU MONITORING INTERFACES - DISCRETE - LANDING GEAR COMPRESSED
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LGCIU MONITORING INTERFACES - DISCRETE
LANDING GEAR EXTENDED - DOWNLOCKED - UPLOCK UNLOCKED
EFFECTIVITY
EFFECTIVITY
ALL
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TMULDGH01 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-11-00 LANDING GEAR AND DOORS - MAIN
LANDING GEAR DESCRIPTION
TMULDAI09 LEVEL 2
UFD4200
CONTENTS:
General
Main Fitting
Sliding Tube/Axle
Actuating Cylinder
Side Stay Assembly
Lock Stay
Lock Stay Actuator
Torque Links/Slave Link
Torque Link Damper
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - MAIN LANDING GEAR DESCRIPTION
GENERAL
TMULDAI09-T01 LEVEL 2
UFD4200
Each Main Landing Gear (MLG) includes these parts:
- a main fitting,
- a sliding tube,
- a shock absorber,
- a retraction actuating cylinder,
- a side stay assembly,
- a lock stay assembly and actuator,
- torque and slave links.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR DESCRIPTION - GENERAL
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - MAIN LANDING GEAR DESCRIPTION
MAIN FITTING
TMULDAI09-T02 LEVEL 2
UFD4200
The main fitting includes:
- the main barrel,
- the drag stay,
- the cross tube,
- the aircraft attachment lugs.
It contains a diaphragm and tube assembly which form
the top of the shock absorber.
A pin connects the diaphragm and the tube assembly.
This pin is located in the two lateral holes in the
main fitting, and contains the shock absorber charging
valve.
A gland housing assembly, at the bottom end of the
main fitting, seals the joint between the main fitting
and the sliding tube.
A spare seal activating valve can isolate the bottom
gland seals if a leak occurs.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR DESCRIPTION - MAIN FITTING
(TOP CHARGING VALVE ASSEMBLY - SPARE SEAL ACTIVATING VALVE)
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - MAIN LANDING GEAR DESCRIPTION
SLIDING TUBE/AXLE
TMULDAI09-T03 LEVEL 2
UFD4200
The sliding tube moves in the main fitting and is a
primary component of the shock absorber.
The axle and the sliding tube are part of same assembly.
The second stage inflation valve of the shock absorber
is on the sliding tube.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR DESCRIPTION - SLIDING TUBE/AXLE
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
LANDING GEAR AND DOORS - MAIN LANDING GEAR DESCRIPTION
ACTUATING CYLINDER
LOCK STAY ACTUATOR
The MLG actuating cylinder is installed on the main
fitting at the piston rod end. Two lugs attach the
body to the wing rear spar.
When it is hydraulically supplied:
- the piston rod extends to retract the MLG,
- the piston rod retracts to extend the MLG.
During MLG extension the two lock stay actuator ports
are open to return; a restritor controls the rate of
MLG extension.
It is pressurized to extend during MLG door closure
until hydraulic pressure on the door close line is
released.
During MLG retraction, the hydraulic fluid retracts
the piston which opens the overcentered lock, to fold
the side stay and the lock stay against the lock
springs.
SIDE STAY ASSEMBLY
The main components of the side stay assembly are:
- a basic side stay,
- a lock stay,
- a lock stay actuator,
- two lock springs,
- the proximity sensors and their related
targets.
The lock springs move the lock stay to an overcenter
position during the extension cycle.
LOCK STAY
The torque links align the main fitting and the sliding
tube, but let vertical movement between the parts
occur.
The slave link is mounted at the rear.
TORQUE LINK DAMPER
The torque link damper is a spring centered, two way
hydraulic unit, which has its own hydraulic reservoir.
Its function is to decrease the landing vibrations
through the torque links.
TMULDAI09-T04 LEVEL 2
UFD4200
The lock stay provides an overcenter stop and a
geometric lock of the landing gear.
TORQUE LINKS/SLAVE LINK
EFFECTIVITY
EFFECTIVITY
ALL
32-11-00
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR DESCRIPTION - ACTUATING CYLINDER - SIDE STAY ASSEMBLY - LOCK STAY
LOCK STAY ACTUATOR - TORQUE LINKS/SLAVE LINK - TORQUE LINK DAMPER
EFFECTIVITY
EFFECTIVITY
ALL
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TMULDAI09 LEVEL 2
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-12-00 LANDING GEAR AND DOORS - MAIN
LANDING GEAR DOORS DESCRIPTION
TMULDCI03 LEVEL 2
UFD4200
CONTENTS:
General
Main Door
Main Landing Gear Door Uplock
Hinged Fairing
Fixed Fairing
EFFECTIVITY
EFFECTIVITY
ALL
32-12-00
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32 LANDING GEAR
LANDING GEAR AND DOORS - MAIN LANDING GEAR DOORS DESCRIPTION
GENERAL
HINGED FAIRING
Each main landing gear is enclosed by one door and two
fairings:
- one main door,
- one hinged fairing,
- one fixed fairing.
The hinged fairing is attached to the wing skin by a
single hinge and to the landing gear by an adjustable
tie rod.
The adjustable tie rod causes the hinged fairing to
follow the landing gear during the landing gear
extension and retraction.
MAIN DOOR
The main door is attached to the fuselage struture by
two hinges and is operated by an hydraulic actuator.
Attached to the forward end of the main door is the
hydraulic actuator and an uplock roller which is used
to keep the main door in the closed position.
Installed on the rear end of the main door are steps,
used for access to the gear well compartment.
Two ramps are installed on the inside of the main door.
These ramps make sure that the gear does not catch on
the main door during a free-fall extension.
Two proximity sensors and targets send the door open
position signal of the main door to the Landing Gear
Control and Interface Units (LGCIUs).
FIXED FAIRING
The fixed fairing is attached to the outboard side of
the landing gear main fitting by two types of
attachment assembly.
Two adjustable studs are installed on the front of the
main fitting.
Three rod ends are installed, one on the front of the
main fitting and two on the rear of the main fitting.
TMULDCI03-T01 LEVEL 2
UFD4200
MAIN LANDING GEAR DOOR UPLOCK
The MLG door uplock is closed mechanically, locking
the door in the closed position, and hydraulically
opened, releasing the door during normal extension and
retraction sequences. The uplock can also be opened
mechanically in free fall extension and ground door
opening.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
MAIN LANDING GEAR DOORS DESCRIPTION
EFFECTIVITY
EFFECTIVITY
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TMULDCI03 LEVEL 2
UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-21-00 LANDING GEAR AND DOORS - NOSE
LANDING GEAR DESCRIPTION
TMULDBI01 LEVEL 2
UFD4200
CONTENTS:
General
Shock Strut Assembly
Shock Absorber
Actuating Cylinder
Drag Strut Assembly
Lockstay Assembly
Lockstay Downlock Actuator
Sliding Tube
Rotating Tube
Torque Link
EFFECTIVITY
EFFECTIVITY
ALL
32-21-00
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32 LANDING GEAR
LANDING GEAR AND DOORS - NOSE LANDING GEAR DESCRIPTION
GENERAL
DRAG STRUT ASSEMBLY
The nose gear retracts forward into the fuselage, and
thus favorably assisted by aerodynamic moments during
gear extension.
The nose gear includes :
- a shock strut assembly,
- a drag strut assembly,
- a lockstay assembly,
- a gear actuating cylinder,
- nose wheel steering system components.
The drag strut assembly consists of a forestay at the
top, a tubular arm at the bottom which are
interconnected by a universal joint. The uplock roller
is installed on the upper hinge pin of the universal
joint.
SHOCK STRUT ASSEMBLY
The shock strut assembly hangs on the structure from
two trunnions. It includes the shock absorber.
SHOCK ABSORBER
TMULDBI01-T01 LEVEL 2
UFD4200
The shock absorber is an integral shock absorber filled
with hydraulic fluid and nitrogen through a single
standard servicing valve at the upper part of the leg.
It also includes the two centering cams which return
the wheels to the centered position when the gear is
extended.
ACTUATING CYLINDER
The actuating cylinder operates the nose gear during
retraction and extension sequences.
EFFECTIVITY
EFFECTIVITY
ALL
LOCKSTAY ASSEMBLY
The lockstay assembly provides an overcentered stop
and a geometric lock of the nose gear. It includes
both systems downlock proximity detectors.
On the ground, a safety pin locks the two arms of the
lockstay.
LOCKSTAY DOWNLOCK ACTUATOR
The downlock actuator locks and unlocks both brace
assemblies of the lockstay. It is assisted by two
springs.
SLIDING TUBE
The sliding tube includes the wheel axle. It is
inclined 9 degrees forward, this design allows the
wheels to return freely to the centered position.
The two system proximity detectors provide signals for
both gear extended and wheel centered positions.
The towing lug is designed to shear if the towing load
is more than the limit.
32-21-00
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE LANDING GEAR DESCRIPTION - LOCKSTAY ASSEMBLY
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR AND DOORS - NOSE LANDING GEAR DESCRIPTION
ROTATING TUBE
The rotating tube is inside the shock strut. It is
equipped with a pinion which transmits steering orders
from the steering actuating cylinder to the wheels.
TORQUE LINK
TMULDBI01 LEVEL 2
UFD4200
The torque link is installed on the rear. It connects
the sliding tube to the rotating tube.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-22-00 LANDING GEAR AND DOORS - NOSE
LANDING GEAR DOORS DESCRIPTION
TMULDDI01 LEVEL 2
UFD4200
CONTENTS:
General
Main Doors
Proximity Detectors
Aft Doors
Leg Door
EFFECTIVITY
EFFECTIVITY
ALL
32-22-00
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32 LANDING GEAR
LANDING GEAR AND DOORS - NOSE LANDING GEAR DOORS DESCRIPTION
GENERAL
LEG DOOR
The doors of the nose landing gear include:
- two main doors,
- two aft doors,
- one leg door.
The leg door is attached to the rear part of the gear
leg.
When the gear is retracted, this door closes off the
area through which the drag strut passes when the gear
is extended.
MAIN DOORS
The two main doors are hydraulically operated. These
two doors are connected mechanically to the aircraft
by a linkage which has two control rods connected to
the same bellcrank.
This bellcrank is installed at the roof of the landing
gear well and is operated by one double-acting
actuator.
An uplock assembly latches the doors in the closed
position.
PROXIMITY DETECTORS
TMULDDI01-T01 LEVEL 2
UFD4200
Two proximity detectors per door provide a signal it
is in the open position (one per system).
The doors must be in this position to permit the gear
to operate.
AFT DOORS
The two aft doors are symmetrical and connected by an
adjustable rod to the gear leg.
These doors close the aft part of the nose gear well
when the gear is retracted.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
NOSE LANDING GEAR DOORS DESCRIPTION
EFFECTIVITY
EFFECTIVITY
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TMULDDI01 LEVEL 2
UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-00-00 LANDING GEAR COMPONENTS
TMULD1I02 LEVEL 2
UFD4200
CONTENTS:
NLG Shock Absorber
MLG Shock Absorber
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR COMPONENTS
NLG SHOCK ABSORBER
LOCATION
ZONE: 711
TMULD1I02-T01 LEVEL 2
UFD4200
DESCRIPTION
The shock absorber is of the single chamber type
without a separator piston and is double acting.
The shock absorber is filled with hydraulic fluid and
nitrogen through a single standard servicing valve in
the upper part of the leg. Calibration of the metering
devices in the shock absorber is the same for the
different versions of the aircraft.
Holes are included in the leg to show possible leaks
from the dynamic seal of the shock absorber.
It is possible to remove the shock absorber without
drainage of the hydraulic fluid.
A placard bonded to the leg shows the filling curves.
The shock absorber includes 2 centering cams, the lower
cam is part of the plunger tube and the upper cam is
part of the sliding tube. When the shock absorber is
fully extended the pressure of the nitrogen causes the
cams to engage. The wheels then return automatically
to the center position.
EFFECTIVITY
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - NLG SHOCK ABSORBER - CENTERING CAM
EFFECTIVITY
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32 LANDING GEAR
LANDING GEAR COMPONENTS
MLG SHOCK ABSORBER
LOCATION
ZONE: 731, 741
TMULD1I02-T02 LEVEL 2
UFD4200
DESCRIPTION
The shock absorber is a telescopic oleo-pneumatic unit
which includes the sliding tube. It is installed in
the main fitting to transmit the landing, take off and
taxiing loads to the wing.
When the shock absorber is compressed, the load is
transmitted to the hydraulic fluid and nitrogen gas.
The shock absorber is a 2 stage unit and contains four
chambers:
- a first stage gas chamber contains gas at a
low pressure and hydraulic fluid,
- a recoil chamber that contains hydraulic fluid,
- a compression chamber that contains hydraulic
fluid,
- a 2nd stage gas chamber that contains gas at
a high pressure.
Primary control of the shock absorber recoil is:
- the fluid flow from the recoil chamber into
the gas chamber,
- the fluid flow from the gas chamber into
the compression chamber.
EFFECTIVITY
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TMULD1I02-P02 LEVEL 2
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - MLG SHOCK ABSORBER
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
TMULD1I02 LEVEL 2
UFD4200
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EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-00-00 LANDING GEAR COMPONENTS
TMULD2I01 LEVEL 3
UFD4200
CONTENTS:
LGCIU
Proximity Detectors
Safety Valve
Selector Valve Manifold
Hydraulic Fuses
MLG Actuating Cylinder
MLG Uplock Box
MLG Door Actuating Cylinder
MLG Door Uplock Box
NLG Actuating Cylinder
NLG Uplock Box
NLG Door Actuating Cylinder
NLG Door Uplock Box
Cut-Out Valve
Vent Valves
Door Bypass Valves
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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32 LANDING GEAR
LANDING GEAR COMPONENTS
LGCIU
PROXIMITY DETECTORS
IDENTIFICATION
FIN: 5GA1 (LGCIU1), 5GA2 (LGCIU2)
IDENTIFICATION
FIN: See table
LOCATION
ZONE: 121 (LGCIU1), Rack 93VU
122 (LGCIU2), Rack 94VU
DESCRIPTION
The proximity detector consists of:
- a proximity sensor,
- a sensor target.
The proximity sensor uses the variable reluctance
principle and operates on the detection of ferrous
metals. In this application the ferrous metal sensor
target supplies the electrical signal.
As the sensor target moves into or out of the proximity
sensor’s actuation area it causes a change in the
proximity sensor’s electrical property.
DESCRIPTION
Each Landing Gear Control and Interface Unit (LGCIU)
consists of an ARINC 600 4 MCU (Modular Concept Unit)
case that contains:
- 7 Printed Circuit Boards (PCU),
- an On Board Replaceable Memory Module (OBRM),
- a Power Supply Unit (PSU).
TMULD2I01-T01 LEVEL 3
UFD4200
BE CAREFUL: If the aircraft is electrically supplied
and a piece of ferrous metal is set on the
proximity sensor, a flight configuration
can be read by its associated system.
EFFECTIVITY
EFFECTIVITY
ALL
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TMULD2I01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - LGCIU - PROXIMITY DETECTORS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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117
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32 LANDING GEAR
LANDING GEAR COMPONENTS
SAFETY VALVE
IDENTIFICATION
FIN: 49GA
LOCATION
ZONE: 148
DESCRIPTION
The safety valve is a single solenoid valve that
operates independently of the LGCIUs.
TMULD2I01-T02 LEVEL 3
UFD4200
CUT-VIEW
Solenoid Energized:
When energized, the safety valve is open.
Solenoid De-energized:
When de-energized, the safety valve shuts off the
hydraulic pressure to the landing gear system when the
airspeed signal from ADIRU 1 and 3 is greater than
260 ±5 kts.
EFFECTIVITY
EFFECTIVITY
ALL
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TMULD2I01-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - LANDING GEAR SAFETY VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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119
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32 LANDING GEAR
SELECTOR VALVE MANIFOLD
HYDRAULIC FUSES
IDENTIFICATION
FIN: 2524GM
IDENTIFICATION
FIN: 2629GM, 2630GM
LOCATION
ZONE: 148
LOCATION
ZONE: 148
DESCRIPTION
The selector valve manifold assembly consists of:
- a manifold block, equipped with hydraulic pipe
connections, a restrictor valve and a check
valve,
- a landing gear selector valve,
- a landing gear door selector valve.
Each valve has two operating solenoids. Each solenoid
has two coil windings, one for each of the landing
gear control sub-systems.
Weight: 7,09 kg (15.62 lb).
DESCRIPTION
Hydraulic fuses are installed in the open and close
lines between the nose landing gear door actuator and
the landing gear door selector valve. They close the
line in case of leakage downstream in case of a flow
rate equal to or greater than 11 l/mn (2.91 USgal/mn).
The hydraulic fuse is reset by depressurizing the green
system reservoir or by opening the bleed screw.
TMULD2I01-T03 LEVEL 3
UFD4200
LANDING GEAR COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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120
Page
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TMULD2I01-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - HYDRAULIC FUSES - SELECTOR VALVE MANIFOLD
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
121
Page
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32 LANDING GEAR
MLG ACTUATING CYLINDER
MLG UPLOCK BOX
IDENTIFICATION
FIN: 2503GM (LH), 2504GM (RH)
IDENTIFICATION
FIN: 2509GM (LH), 2510GM (RH)
LOCATION
ZONE: 731 , 741
LOCATION
ZONE: 147, 148
DESCRIPTION
Identical for left-hand and right-hand installation.
Weight: 29,8 kg (67.71 lb).
DESCRIPTION
The uplock is hung in the same for both the left or
right-hand installations.
The same applies for the left-hand and right-hand
actuators.
Weight: 4,722 kg (10.412 lb).
TMULD2I01-T04 LEVEL 3
UFD4200
LANDING GEAR COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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122
Page
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TMULD2I01-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - MLG ACTUATING CYLINDER - MLG UPLOCK BOX
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
123
Page
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32 LANDING GEAR
MLG DOOR ACTUATING CYLINDER
MLG DOOR UPLOCK BOX
IDENTIFICATION
FIN: 2523GM (LH), 2522GM (RH)
IDENTIFICATION
FIN: 2521GM (LH), 2520GM (RH)
LOCATION
ZONE: 147, 148
LOCATION
ZONE: 147, 148
DESCRIPTION
The actuator is suitable for left-hand and right-hand
installations.
Weight: 6,601 kg (14.553 lb).
DESCRIPTION
The uplock box is suitable for left-hand and right-hand
installations.
Weight: 4,38 kg (9.65 lb).
TMULD2I01-T05 LEVEL 3
UFD4200
LANDING GEAR COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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Page124
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TMULD2I01-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - MLG DOOR ACTUATING CYLINDER - MLG DOOR UPLOCK BOX
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page125
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32 LANDING GEAR
NLG ACTUATING CYLINDER
NLG UPLOCK BOX
IDENTIFICATION
FIN: 2527GM
IDENTIFICATION
FIN: 2530GM
LOCATION
ZONE: 711
LOCATION
ZONE: 123
TMULD2I01-T06 LEVEL 3
UFD4200
LANDING GEAR COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page126
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TMULD2I01-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - NLG ACTUATING CYLINDER - NLG UPLOCK BOX
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page127
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32 LANDING GEAR
NLG DOOR ACTUATING CYLINDER
NLG DOOR UPLOCK BOX
IDENTIFICATION
FIN: 2531GM
IDENTIFICATION
FIN: 2534GM
LOCATION
ZONE: 123
LOCATION
ZONE: 123
TMULD2I01-T07 LEVEL 3
UFD4200
LANDING GEAR COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page128
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TMULD2I01-P07 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - NLG DOOR ACTUATING CYLINDER - NLG DOOR UPLOCK BOX
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page129
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32 LANDING GEAR
LANDING GEAR COMPONENTS
CUT-OUT VALVE
IDENTIFICATION
FIN: 2515GM
LOCATION
ZONE: 147
TMULD2I01-T08 LEVEL 3
UFD4200
DESCRIPTION
Shuts off the high pressure supply and connects the
entire landing gear hydraulic system to the return
circuit during free fall extension.
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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TMULD2I01-P08 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - CUT-OUT VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
Page
Page131
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS
VENT VALVES
IDENTIFICATION
FIN: 2532GM (NLG), 2516GM (MLG)
LOCATION
ZONE: 124, 148
TMULD2I01-T09 LEVEL 3
UFD4200
DESCRIPTION
There are two identical mechanically operated vent
valves in the landing gear free fall extension system.
During landing gear free fall extension, operation of
the vent valve connects door close and gear raise lines
to the return circuit.
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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TMULD2I01-P09 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - VENT VALVES
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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32 LANDING GEAR
LANDING GEAR COMPONENTS
DOOR BYPASS VALVES
IDENTIFICATION
FIN: 2533GM (NLG), 2517GM (LH), 2518GM (RH)
LOCATION
ZONE: 123, 147, 148
TMULD2I01-T10 LEVEL 3
UFD4200
DESCRIPTION
Each bypass valve isolates its corresponding door
hydraulic actuator from the landing gear hydraulic
supply during ground opening of landing gear door(s).
Weight: 0,88 kg (1.94 lb).
EFFECTIVITY
EFFECTIVITY
ALL
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TMULD2I01-P10 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LANDING GEAR COMPONENTS - DOOR BYPASS VALVES
EFFECTIVITY
EFFECTIVITY
ALL
32-00-00
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32 LANDING GEAR
TMULD2I01 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-40-00 WHEELS AND BRAKES - BRAKE SYSTEM
PRESENTATION
TMULDZ101 LEVEL 1
UFD4200
CONTENTS:
Normal Braking
Normal Braking by Auto Brake
Manual Normal Braking
Inflight Braking
Parking Brake
Alternate Braking with Anti-Skid
Alternate Braking without Anti-Skid
Self Examination
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKE - BRAKES SYSTEM PRESENTATION
The four braking modes available depend on :
- the hydraulic system,
- the position of the A/SKID & N/W STRG switch
and PARKING BRK control switch.
NORMAL BRAKING
Before landing, the crew can select one of the AUTO
BRAKE modes to obtain the optimal deceleration rate
compatible with the length of the runway.
Before take-off, MAX mode must be selected in case of
an aborted take-off.
When a pushbutton deceleration rate is selected, the
"ON" light comes on blue to indicate the positive
arming of the auto brake mode.
Braking begins when ground spoilers deployment orders
are present.
The Braking and Steering Control Unit (BSCU) energizes
the selector valve allowing green pressure to supply
the brakes through the automatic selector and normal
servovalves.
The automatic reversible selector, when powered by the
green hydraulic system cuts the yellow one.
Depending on the deceleration rate and the anti-skid
regulation, the BSCU regulates the pressure delivered
to each brake through the normally open normal
servovalves.
Wheels rotation speed and ADIRU data are supplied to
the BSCU for braking and anti-skid computation.
When the aircraft deceleration reaches a given value,
the "DECEL" green light comes on.
TMULDZ101-T01 LEVEL 1
UFD4200
Normal braking is obtained when :
- the green high hydraulic pressure is available,
- the A/SKID & N/W STRG switch is in the "ON"
position,
- the PARKING BRK control switch is in the "OFF"
position.
Electrical control is obtained :
- through the pedals,
- automatically : on the ground by the auto brake
system or in flight when the landing gear
control lever is set to "UP".
No indicator of normal brake pressure is used.
NORMAL BRAKING BY AUTO BRAKE
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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TMULDZ101-P01 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - NORMAL BRAKING BY AUTOBRAKE
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM PRESENTATION
MANUAL NORMAL BRAKING
TMULDZ101-T02 LEVEL 1
UFD4200
Electrical braking orders are sent by the pedals to
the Braking and Steering Control Unit (BSCU).
The BSCU energizes the selector valve allowing green
pressure to supply the brakes through the automatic
selector and normal servovalves.
The automatic reversible selector, when powered by the
green hydraulic system cuts the yellow one.
Depending on manual braking orders and anti-skid
regulation, the BSCU regulates the pressure delivered
to each brake through the normally open servovalves.
Wheel rotation speed, braking pressure and ADIRU data
are supplied to the BSCU for braking and anti-skid
computation.
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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Page
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TMULDZ101-P02 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - MANUAL NORMAL BRAKING
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
Page
141
Page
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM PRESENTATION
INFLIGHT BRAKING
TMULDZ101-T03 LEVEL 1
UFD4200
In order to stop the main landing gear wheels rotation
before entry into the landing gear bay, a preprogrammed
brake pressure is released to the normal brakes.
When the landing gear control lever is set to "UP",
the BSCU opens the selector valve and energizes the
servovalves.
The brake pressure is released either when the nose
gear is no longer downlocked or three seconds after
the "UP" selection.
Furthermore, nose wheels are mechanically braked at
the end of the gear retraction cycle using brake bands.
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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TMULDZ101-P03 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - INFLIGHT BRAKING
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM PRESENTATION
PARKING BRAKE
TMULDZ101-T04 LEVEL 1
UFD4200
The parking brake system is hydraulically supplied
either by yellow high pressure or by an accumulator
of 12 hours autonomy.
The system needs either DC ground/flight bus or hot
bus 1 electrical supply and uses segregated wiring
routes.
When the parking brake system is activated, all other
braking modes become electrically and hydraulically
inoperative.
Note that, as normal braking and auxiliary low pressure
control systems are not available, an ultimate
emergency braking can be ensured by means of the
parking brake system.
PARKING BRAKE OFF
When the parking brake handle is lifted and turned to
"OFF", the parking brake control valve is energized
on the opposite way, the parking brake is reset and
all the other braking modes are restored.
The yellow brake accumulator can be pressurized by
pressing the yellow electrical pump pushbutton switch.
PARKING BRAKE ON
When the parking brake handle is lifted and turned to
"ON", the parking brake control valve is energized.
The BSCU is informed that the parking brake system is
on, which deactivates the other braking modes.
Yellow pressure passes through the parking brake
control valve and reaches the dual shuttle valve.
The dual shuttle valve moves, allowing alternate system
circuit to be supplied by the parking brake system.
Brakes are supplied through the normally open alternate
servovalves.
The pressure delivered to the left hand and right hand
brakes as well as the brake accumulator pressure are
indicated on the yellow pressure triple indicator.
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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Page
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TMULDZ101-P04 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - PARKING BRAKE
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
Page
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Page
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32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM PRESENTATION
ALTERNATE BRAKING WITH ANTI-SKID
TMULDZ101-T05 LEVEL 1
UFD4200
The alternate braking with anti-skid associates the
yellow high pressure with the anti-skid regulation.
This mode is automatically obtained :
- in case of green pressure loss,
- if a failure occurs on the normal braking system
during operation or BSCU BITE test.
As the normal system becomes inoperative, the alternate
braking circuit is pressurized through the automatic
selector.
Orders are entered by the pedals and transmitted
through an auxiliary low pressure control system to
the dual valve.
The dual valve regulates the yellow braking pressure.
The BSCU ensures the anti-skid regulation by
controlling the normally open alternate servovalves.
The braking pressure is read on the ACCU/PRESS triple
indicator.
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
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TMULDZ101-P05 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - ALTERNATE BRAKING WITH ANTI-SKID
EFFECTIVITY
EFFECTIVITY
ALL
ALL
32-40-00
Page
Page147
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32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM PRESENTATION
ALTERNATE BRAKING WITHOUT ANTI-SKID
TMULDZ101-T06 LEVEL 1
UFD4200
Alternate braking without anti-skid is different from
alternate braking with anti-skid in that there is no
anti-skid regulation.
The anti-skid regulation can be disconnected :
- either electrically (A/SKID & N/W STRG switch
set to "OFF" or power supply failure),
- or hydraulically if the brake yellow pressure
accumulator only supplies the brakes.
Brake pressure has to be limited by the pilot to avoid
wheel locking using ACCU/PRESS triple indicator.
With the accumulator pressure only, a maximum of 7
full brake pedal applications can be performed.
EFFECTIVITY
EFFECTIVITY
ALL
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDZ101-P06 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - ALTERNATE BRAKING WITHOUT ANTI-SKID
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
Which hydraulic system powers normal braking ?
A - Green system.
B - Yellow system.
C - Blue system.
How is inflight braking initiated ?
A - By setting the landing lever to the UP
position.
B - By shock absorber extension.
C - By auto brake deactivation.
In case of normal braking system failure, how is
alternate braking applied ?
A - Automatically when the selector valve is
de-energized.
B - Automatically through the automatic
selector.
C - As soon as the brake pedals are pressed
in.
TMULDZ101 LEVEL 1
UFD4200
How can the parking brake be hydraulically powered ?
A - Only by yellow high pressure.
B - Only by the brake accumulator.
C - Either by yellow high pressure or by the
brake accumulator.
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-40-00 WHEELS AND BRAKES - BRAKE SYSTEM
DESCRIPTION
TMULDZZ02 LEVEL 3
UFD4200
CONTENTS:
Pedals
Brake Pedals XMTR Unit
BSCU
Selector Valve
Normal Servovalve
Wheels
Automatic Selector
Auxiliary Low Pressure Control System
Dual Valve
Dual Shuttle Valve
Alternate Servovalve
Parking Brake Control Valve
Parking Brake Operated Valve
Accumulator
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Sep 30/98
A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TMULDZZ02-T01 LEVEL 3
UFD4200
WHEELS AND BRAKES - BRAKE SYSTEM DESCRIPTION
PEDALS
WHEELS
The pedals give mechanical inputs to the brake pedal
transmitter unit for manual normal braking and to the
auxiliary low pressure control system for alternate
braking.
Each main wheel is equipped with multidisc carbon
brakes.
Each main wheel rotation speed given by a tachometer
is fed back to the BSCU for anti-skid computation.
BRAKE PEDALS XMTR UNIT
AUTOMATIC SELECTOR
The brake pedal transmitter unit transforms the
mechanical input from the right and left pedals into
electrical signals which are sent to the BSCU.
The automatic selector allows the pressurization of
either normal brake systems or alternate brake systems
and preferential supply to the normal system.
BSCU
AUXILIARY LOW PRESSURE CONTROL SYSTEM
The Braking and Steering Control Unit (BSCU) controls
normal braking, auto braking as well as anti-skid
operation during normal and alternate braking.
The auxiliary low pressure control system transforms
the mechanical input from the left and right pedals
into hydraulic pressure which controls the dual valve.
SELECTOR VALVE
DUAL VALVE
The selector valve is an on/off valve. When normal
braking is applied, the BSCU first energizes the
selector valve, this allows full green pressure to
supply the normal servovalves.
The dual valve allows the operation of the alternate
braking system.
NORMAL SERVOVALVES
The dual shuttle valve selects either the alternate
braking system or the parking brake system.
DUAL SHUTTLE VALVE
The normal servovalve has a dual function: it regulates
braking pressure, which depends on BSCU braking orders,
and anti-skid control pressure delivered to the brakes.
They are located on the main landing gear strut.
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Sep 30/98
A319/A320/A321 TECHNICAL TRAINING MANUAL
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TMULDZZ02-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SYSTEM DESCRIPTION
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32 LANDING GEAR
WHEELS AND BRAKES - BRAKE SYSTEM DESCRIPTION
ALTERNATE SERVOVALVES
The alternate servovalves regulate only the anti-skid
control pressure.
They are located on the rear pressure bulkhead above
the main landing gear strut.
PARKING BRAKE CONTROL VALVE
The parking brake electrical control valve is operated
by the parking brake handle. It deactivates anti-skid
and braking modes.
PARKING BRAKE OPERATED VALVE
The parking brake operated valve shuts off supply to
the alternate brake system to prevent leakage through
the dual valve.
ACCUMULATOR
TMULDZZ02-T01 LEVEL 3
UFD4200
The accumulator is only used for braking. It is either
pressurized by the yellow hydraulic system or by the
yellow electric pump.
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-42-00 WHEELS AND BRAKES - AUTO BRAKE
SYSTEM DESCRIPTION/OPERATION
TMULDG902 LEVEL 3
UFD4200
CONTENTS:
Auto Brake Modes
ADIRS
A/SKID & N/W STRG Switch
Arming
Activation
Disarming
Self Examination
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32 LANDING GEAR
WHEELS AND BRAKES - AUTO BRAKE SYSTEM DESCRIPTION/OPERATION
AUTO BRAKE MODES
ARMING
The AUTO BRK panel is used to select the desired
deceleration rate of the system.
MAX mode is normally selected for take-off: In the
event of an aborted take-off, maximum braking pressure
is sent to the normal servovalves as soon as ground
spoilers deployment order is present.
MED or LO modes are selected for landing: Progressive
pressure is sent to the brakes, for respectively 2 or4
seconds after the ground spoilers deployment order.
The auto brake system is armed if one of the three
mode pushbuttons (LO, MED or MAX) is pressed in and
the following conditions are met:
- Green pressure available.
- Anti-skid electrically powered.
- No failure in the normal braking system.
The ON light comes on blue when the corresponding rate
is armed.
ADIRS
The Air Data Inertial Reference System (ADIRS) signals
the aircraft deceleration rate to the Braking and
Steering Control Unit (BSCU) to be compared with the
selected deceleration mode for braking computation.
TMULDG902-T01 LEVEL 3
UFD4200
A/SKID & N/W STRG SWITCH
The A/SKID & N/W STRG switch activates the anti-skid
system and enables auto brake arming.
ON: Anti-skid and nose wheel steering are available
and auto brake can be armed provided the green pressure
is valid.
If green pressure drops:
- Yellow pressure takes over automatically,
anti-skid is available and nose wheel steering
is lost.
- Auto brake cannot be armed.
OFF: Anti-skid, nose wheel steering and auto brake are
lost.
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ACTIVATION
The automatic braking system is activated by 2 of the
3 ground spoiler extension signals coming from the
Spoiler Elevator Computers (SECs).
The DECEL light comes on green when actual aircraft
deceleration is 80 % of selected rate (LO and MED
modes) or 0.27 g (MAX mode).
DISARMING
The auto brake is disarmed by:
- Releasing the selected pushbutton out or,
- Loss of one or more arming conditions or,
- Applying sufficient force to the pedals when
auto brake is operating.
- Ground spoiler retraction.
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Sep 30/98
A319/A320/A321 TECHNICAL TRAINING MANUAL
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TMULDG902-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
AUTO BRAKE SYSTEM DESCRIPTION/OPERATION
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Sep 30/98
A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
In which mode is progressive pressure sent to the
brakes, 2 seconds after ground spoiler deployment:
A - MAX mode.
B - MED mode.
C - LO mode.
TMULDG902 LEVEL 3
UFD4200
What are the auto brake arming conditions?
A - An AUTO BRK pushbutton pressed in, green
pressure and anti-skid powered and no
failure in normal braking system.
B - An AUTO BRK pushbutton pressed in,
yellow pressure and anti-skid powered
and no failure in normal braking system.
C - An AUTO BRK pushbutton pressed in, green
pressure and anti-skid deactivated and
no failure in normal braking system.
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-42-00 WHEELS AND BRAKES - ANTI-SKID
FUNCTION
TMULD2004 LEVEL 3
UFD4200
CONTENTS:
Purpose
BSCU
Principle
Regulation
Servovalves
ADIRU
Self Examination
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ANTI-SKID FUNCTION
PURPOSE
REGULATION
The anti-skid system gives the maximum braking
efficiency as it keeps each individual wheel at the
maximum deceleration rate avoiding a skidding
configuration.
The operational amplifier compares the calculated
reference speed with the speed of the decelerating
wheel.
The operational amplifier supplies numerical values
which are converted into current to supply the coil
of the normal and alternate servovalves in use to
ensure the anti-skid function.
BSCU
TMULD2004-T01 LEVEL 3
UFD4200
The Braking and Steering Control Unit (BSCU) provides
anti-skid control during normal and alternate braking
by either system 1 or 2 of the BSCU.
System 1 and 2 have independent power supplies, and
at each energization, the first system supplied takes
control.
If the two systems are supplied simultaneously system 1
has priority and system 2 is in standby.
SERVOVALVES
The normal and alternate servovalves are identical but
connected differently to the BSCU.
While the two coils of the normal servovalve are
connected to system 1 and 2 respectively, only one
coil of the alternate servovalve is used.
PRINCIPLE
ADIRU
The speed of each main gear wheel, given by a
tachometer, is compared with the aircraft speed
supplied by the Air Data Inertial Reference Units.
A reference speed is determined by the BSCU from the
longitudinal deceleration given by Air Data Inertial
Reference Units 1, 2 or 3 (ADIRU).
When the speed of a wheel decreases below 0.87 times
the reference speed, brake release orders are given
to that wheel to maintain the wheel deceleration rate
at that value.
The required reference speed during braking is directly
obtained from the average between the values from the
three Air Data Inertial Reference Units (ADIRUs).
In case the ADIRU data is not valid, the reference
speed is equal to the maximum of either main landing
gear wheel speeds. Aircraft deceleration is limited
to 1.7 m/s2 (5.6 ft/s2).
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Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULD2004-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ANTI-SKID FUNCTION
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Jan 31/95
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
When does the BSCU provide anti-skid control?
A - During normal and alternate braking.
B - Only during normal braking.
C - When the auto brake system has failed.
TMULD2004 LEVEL 3
UFD4200
What happens when a wheel speed decreases below
0.87 times the reference speed?
A - A brake release order is given to the
wheels of the same gear.
B - A brake release order is given to the
related wheel.
C - A brake release order is given to all
wheels.
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-40-00 WHEELS AND BRAKES - BRAKE
HYDRAULIC SYSTEM OPERATION
TMULDGT05 LEVEL 3
UFD4200
CONTENTS:
Normal Braking
Alternate Braking with Anti-Skid
Alternate Braking without Anti-Skid
Parking Brake
Self Examination
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Sep 30/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE HYDRAULIC SYSTEM OPERATION
NORMAL BRAKING
The hydraulic braking operation is identical for
automatic braking, manual braking and inflight
braking.
Note that during inflight braking, anti-skid function
is inhibited by the BSCU.
Normal braking and anti-skid regulation are
electrically controlled by the Braking and Steering
Control Unit.
OPERATION:
The selector valve is energized.
The automatic selector ensures the segregation of the
two hydraulic systems and preferential supply of the
normal braking system.
The throttle valve decreases the movement speed of the
automatic selector when the brake selector valve is
de-energized.
The normal brake servovalves supply a pressure which
depends on the control current delivered by the BSCU.
The manifold comprises the two servovalves, the two
pressure transducers and the two hydraulic fuses.
The hydraulic fuse stops the flow in the line in case
of leakage.
Note that during the normal braking the automatic
selector connects the alternate system to the yellow
return manifold.
During manual braking, the master cylinders provide
an artificial feel at the pedals.
The brake system is ready to be supplied by the
alternate system in case of normal braking failure.
TMULDGT05-T01 LEVEL 3
UFD4200
The hydraulic braking architecture is shown with all
components. Note that only their main functions are
shown.
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGT05-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE HYDRAULIC SYSTEM OPERATION - NORMAL BRAKING
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE HYDRAULIC SYSTEM OPERATION
ALTERNATE BRAKING WITH ANTI-SKID
The alternate braking with anti-skid associates yellow
high pressure with anti-skid regulation.
TMULDGT05-T02 LEVEL 3
UFD4200
OPERATION:
The orders are entered through the pedals and an
auxiliary low pressure hydraulic system transmits the
orders via the master cylinders, to control the
distribution dual valve.
The pressure from the dual valve is delivered to the
brakes through the dual shuttle valve and the alternate
servovalves. It is indicated on the yellow pressure
triple indicator.
The alternate brake servovalve manifold comprises two
alternate servovalves and two hydraulic fuses.
The BSCU ensures the anti-skid regulation by
controlling the related servovalve.
The hydraulic fuse stops the flow in the line in case
of leakage.
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGT05-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE HYDRAULIC SYSTEM OPERATION - ALTERNATE BRAKING WITH ANTI-SKID
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE HYDRAULIC SYSTEM OPERATION
ALTERNATE BRAKING WITHOUT ANTI-SKID
In case of alternate braking without antiskid the
brakes are supplied either by the yellow high pressure
or the brake accumulator.
When yellow high pressure is available, the brakes are
supplied through the alternate system and the return
lines are connected to the yellow return manifold.
When the brakes are only supplied by the brake
accumulator the return lines are shut off by the
automatic selector.
TMULDGT05-T03 LEVEL 3
UFD4200
OPERATION:
The orders are entered through the pedals only and an
auxiliary low pressure hydraulic system transmits the
orders via the master cylinders, to control the
distribution dual valve.
The pressure from the dual valve is delivered to the
brakes through the dual shuttle valve and the alternate
servovalves. It is indicated on the yellow pressure
triple indicator.
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Sep 30/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGT05-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE HYDRAULIC SYSTEM OPERATION - ALTERNATE BRAKING WITHOUT ANTI-SKID
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE HYDRAULIC SYSTEM OPERATION
PARKING BRAKE
The brakes are supplied either by the yellow high
pressure manifold or the brake accumulator.
TMULDGT05-T04 LEVEL 3
UFD4200
OPERATION:
When the parking brake handle is set to the "ON"
position, all the other braking modes and the anti-skid
system are deactivated and all the return lines are
shut off.
The parking brake electrical control valve comprises
one electrical linear transmitter which operates the
hydromechanical valve and a pressure limiter for the
dual shuttle valve supply.
The secondary slide valve of the automatic selector
isolates the return lines of the alternate brake
servovalves to prevent fluid leakage to the yellow
reservoir.
The parking brake operated valve shuts off the supply
to the alternate system to prevent leakage through the
dual valve.
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDGT05-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE HYDRAULIC SYSTEM OPERATION - PARKING BRAKE
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Sep 30/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SELF EXAMINATION
What is the purpose of the hydraulic fuses?
A - To stop the flow in case of leakage.
B - To shut off the return lines.
C - To separate the Normal from the
Alternate Servovalves.
Are the return lines shut off when the parking
brake is applied?
A - No, they are always open.
B - Yes, by the Automatic Selector.
C - Yes, when braking is supplied by the
accumulator only.
TMULDGT05 LEVEL 3
UFD4200
Which component gives priority to the green
hydraulic system?
A - Brake Selector Valve.
B - Throttle Valve.
C - Automatic Selector.
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-47-00 WHEELS AND BRAKES - BRAKE
TEMPERATURE SYSTEM PRESENTATION
TMULDGOZZ LEVEL 1
UFD4200
CONTENTS:
Purpose
Temperature Sensor
Brake Temperature Monitoring Unit (BTMU)
Braking and Steering Control Unit (BSCU)
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - BRAKE TEMPERATURE SYSTEM PRESENTATION
PURPOSE
The system measures the brake temperature and indicates
the values on the lower display unit of the ECAM.
A warning is generated when the brake temperature
threshold is exceeded.
TEMPERATURE SENSOR
Brake temperature is measured by one chromel-alumel
thermocouple per brake.
BRAKE TEMPERATURE MONITORING UNIT
The Brake Temperature Monitoring Unit (BTMU) is
equipped with two printed circuits to process the data
from the thermocouples.
After processing, the BTMU delivers a voltage which
varies between 1V and 9V corresponding to a temperature
range of 0 to 1000°C.
TMULDGOZZ-T01 LEVEL 1
UFD4200
BRAKING AND STEERING CONTROL UNIT
The Braking and Steering Control Unit (BSCU) changes
analog signals from the monitoring unit into digital
signals for temperature indication on the lower ECAM
display unit.
The amber HOT light on the optional BRK FAN pushbutton
comes on when the temperature threshold of any brake
is reached.
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_
TMULDGOZZ-P01 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE TEMPERATURE SYSTEM PRESENTATION
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32 LANDING GEAR
TMULDGOZZ LEVEL 1
UFD4200
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-48-00 BRAKE COOLING SYSTEM PRESENTATION
TMULDWW01 LEVEL 1
UFD4200
CONTENTS
Purpose
Control and Logic
Brake Fans
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE COOLING SYSTEM PRESENTATION
PURPOSE
The brake fan system allows the brakes to be cooled
in a short time period.
CONTROL AND LOGIC
The BRK FAN pushbutton is used to operate the fan when
the landing gear is downlocked.
BRAKE FANS
TMULDWW01-T01 LEVEL 1
UFD4200
The impeller creates a flow of air from the heat pack
to the exterior through the debris guard.
Each fan includes a three phase type motor, an impeller
and a shroud with a debris guard.
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TMULDWW01-P01 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE COOLING SYSTEM PRESENTATION
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32 LANDING GEAR
TMULDWW01 LEVEL 1
UFD4200
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-42-00 WHEEL AND BRAKE ECAM PAGE
PRESENTATION
TMULDA4ZZ LEVEL 1
UFD4200
CONTENTS:
Wheel/Brake Release Indications
Anti-Skid Indication
Auto Brake Indications
Alternate Braking Indication
Brake Temperature Indications
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A319/A320/A321 TECHNICAL TRAINING MANUAL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE ECAM PAGE PRESENTATION
The ECAM WHEEL page displays landing gear and door
positions, as well as brake and steering indications.
WHEEL/BRAKE RELEASE INDICATIONS
BRAKE TEMPERATURE INDICATIONS
The various brake temperature indications
displayed as shown on the table below.
are
The wheel and brake release indications are displayed
as shown on the table below.
ANTI-SKID INDICATION
"A/SKID" indication appears amber in case of failure
of Braking and Steering Control Unit system 1 and
system 2 or when the anti-skid and nose wheel steering
switch (A/SKID & N/W STRG) is set to "OFF".
AUTO BRAKE INDICATIONS
TMULDA4ZZ-T01 LEVEL 1
UFD4200
"AUTO BRK" (Green) : Steady when auto brake is armed.
Flashing for 10 sec after auto
brake disengagement.
"AUTO BRK" (Amber) : If arming conditions are not met.
If a failure occurs with the
system armed.
"MED", "LO" or "MAX" (Green) : Selected auto brake
rate.
ALTERNATE BRAKING INDICATION
"ALTN BRK" indication appears if the braking system
is in alternate mode.
During normal braking operation, if a master lever is
set to OFF, normal braking is momentarily lost and
alternate braking becomes operative.
This to avoid any jerks during braking when the
electrical generator is shut down.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
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Page
2
Oct 31/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDA4ZZ-P01 LEVEL 1
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE ECAM PAGE PRESENTATION
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
183
Page
3
Oct 31/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TMULDA4ZZ LEVEL 1
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
184
Page
4
Oct 31/97
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-42-00 WHEEL AND BRAKE SYSTEM WARNINGS
TMULDB6ZZ LEVEL 3
UFD4200
CONTENTS:
Config Parking Brake ON
Brakes Hot
Auto Brake Fault
Anti Skid NWS Fault
Anti Skid/NWS Off
Hydraulic Selector Valve Fault
Braking And Steering Control Unit System 1 (2) Fault
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
185
Page
1
Sep 30/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDB6ZZ-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE SYSTEM WARNINGS
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
186
Page
2
Sep 30/99
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-42-00 NORMAL BRAKING COMPONENTS
TMULDBXZZ LEVEL 3
UFD4200
CONTENTS:
BSCU
Brake Selector Valve
Filter
Automatic Selector
Throttle Valve
Manifold Normal Brake Servovalves
Normal Brake Servovalves
Pressure Transducers
Hydraulic Fuses
Brake Pedal Transmitter Unit
Brake Belts (optional)
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
187
Page
1
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A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
BSCU
IDENTIFICATION
FIN: 10GG
LOCATION
ZONE: 122, Rack 94VU
TMULDBXZZ-T01 LEVEL 3
UFD4200
DESCRIPTION
The Braking and Steering Control Unit (BSCU) consists
of:
- four power supply units grouped two by two,
- two identical sets of three boards which form
systems 1 and 2, each board is connected to an
On-Board Reprogrammable Module (OBRM),
- a rear interface in the form of two
U-shaped boards (around the connector)
comprises the lightning protection and the
switching assemblies.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
188
Page
2
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BSCU
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
189
Page
3
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE SELECTOR VALVE
FILTER
IDENTIFICATION
FIN: 23GG
IDENTIFICATION
FIN: 2584GM
LOCATION
ZONE: 146
LOCATION
ZONE: 146
DESCRIPTION
The selector valve directs normal hydraulic pressure
(green system) through the automatic selector to the
normal brake servovalve manifold.
It is energized for normal braking purposes.
DESCRIPTION
A filter with a filtering capability of 15 microns
absolute is installed between the delivery port of the
selector valve and the automatic selector.
The purpose of this filter is to protect the supply
of the normal servovalves downstream of the selector
valve.
TMULDBXZZ-T02 LEVEL 3
UFD4200
NORMAL BRAKING COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
190
Page
4
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BRAKE SELECTOR VALVE - FILTER
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
191
Page
5
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
AUTOMATIC SELECTOR
IDENTIFICATION
FIN: 2576GM
LOCATION
ZONE: 148
TMULDBXZZ-T03 LEVEL 3
UFD4200
DESCRIPTION
The automatic selector supplies the brake system with
either the green (normal braking) or yellow (alternate
braking/parking brake) pressure.
Under normal operating conditions it allows the green
hydraulic fluid to flow to the brakes and maintains
the yellow hydraulic pressure on standby status.
Should the green pressure drop below a predetermined
value, the selector automatically cuts off the green
supply and opens the passage to the yellow pressure.
In addition, it shuts off the yellow system from the
return line for parking brake application.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
192
Page
6
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - AUTOMATIC SELECTOR
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
193
Page
7
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
AUTOMATIC SELECTOR (CONTINUED)
TMULDBXZZ-T04 LEVEL 3
UFD4200
CROSS SECTION
The automatic selector includes a primary stage which
selects the system.
It also includes a secondary stage used to cut off the
return from the servovalves of the alternate system.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
194
Page
8
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - AUTOMATIC SELECTOR CROSS SECTION
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
195
Page
9
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
THROTTLE VALVE
IDENTIFICATION
FIN: 2581GM
LOCATION
ZONE: 148
TMULDBXZZ-T05 LEVEL 3
UFD4200
DESCRIPTION
The throttle valve is installed on the green supply
port (A) of the automatic selector.
It decreases the speed of movement of the main slide
valve of the selector when the brake selector valve
is de-energized.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page196
10
Jun 30/00
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_
TMULDBXZZ-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - THROTTLE VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page197
11
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
MANIFOLD NORMAL BRAKE SERVOVALVES
NORMAL BRAKE SERVOVALVES
IDENTIFICATION
FIN: 2613GM (LH), 2612GM (RH)
IDENTIFICATION
FIN: 15GG (WHEEL 1), 17GG (WHEEL 2), 16GG (WHEEL 3),
18GG (WHEEL 4)
LOCATION
ZONE: 731, 741
DESCRIPTION
There are four servovalves, one for each brake.
The brake servovalve supplies a pressure inversely
proportional to the current which passes through the
control coil used.
TMULDBXZZ-T06 LEVEL 3
UFD4200
DESCRIPTION
The manifold is equipped with two servovalves, two
pressure transducers, two hydraulic fuses and one
filter on the supply line of the manifold.
LOCATION
ZONE: 731, 741
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page198
12
Jun 30/00
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_
TMULDBXZZ-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - MANIFOLD NORMAL BRAKE SERVOVALVES - NORMAL BRAKE SERVOVALVES
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page199
13
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
NORMAL BRAKE SERVOVALVES (CONTINUED)
TMULDBXZZ-T07 LEVEL 3
UFD4200
CROSS SECTION
The current of the control coil in use (either system
1 or 2) moves a flapper located between two jets.
This modifies the sections of the fluid passage at the
jets, and consequently the pressure in the control
chambers of the slide valve.
With zero current, the supplied pressure is equal to
the pressure supplied to the servovalve.
If there is no supply pressure, the servovalve connects
the brake to the reservoir return system.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page200
14
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P07 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - NORMAL BRAKE SERVOVALVES CROSS SECTION
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page201
15
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
PRESSURE TRANSDUCERS
HYDRAULIC FUSES
IDENTIFICATION
FIN: 11GG (WHEEL 1), 13GG (WHEEL 2),
12GG (WHEEL 3), 14GG (WHEEL 4)
IDENTIFICATION
FIN: 2618GM (WHEEL 1), 2616GM (WHEEL 2),
2617GM (WHEEL 3), 2619GM (WHEEL 4)
LOCATION
ZONE: 731, 741
LOCATION
ZONE: 731, 741
DESCRIPTION
The normal brake pressure transducers are installed
on the manifold of the normal brake servovalve, one
downstream of each servovalve.
The integrated-logic transducer supplies a DC voltage
between 1 and 5V for a pressure between 0 and 3000 psi
(206 bars).
The zero has been shifted to enable BITE testing.
DESCRIPTION
A hydraulic fuse, installed between the brake
servovalve and the brake, stops the flow in the line
if the leakage exceeds 1.32 U.S. gal/mn (5 l/mn).
The valve is reset when you depressurize the hydraulic
systems and when you open the bleed screw.
TMULDBXZZ-T08 LEVEL 3
UFD4200
NORMAL BRAKING COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page202
16
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P08 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - PRESSURE TRANSDUCERS - HYDRAULIC FUSES
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page203
17
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
BRAKE PEDAL TRANSMITTER UNIT
IDENTIFICATION
FIN: 9GG
LOCATION
ZONE: 121
TMULDBXZZ-T09 LEVEL 3
UFD4200
DESCRIPTION
The brake pedal transmitter unit transforms the pedal
input into four identical electrical voltages per side
which are sent to the BSCU for selector valve
energization.
Any overtravel is absorbed by the spring rods which
actuate the levers of the transmitter unit.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page204
18
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P09 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BRAKE PEDAL TRANSMITTER UNIT
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page205
19
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS
BRAKE BELTS (OPTIONAL)
LOCATION
ZONE: 124
DESCRIPTION
Brake belts stop the nose gear wheels at the end of
the gear retraction cycle.
TMULDBXZZ-T10 LEVEL 3
UFD4200
NOTE: Depending on the aircraft configuration, brake
bands are removed and optionally re-installed.
When removed, there will be no braking of the
nose wheels which shall be allowed to spin down
naturally.
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page206
20
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDBXZZ-P10 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BRAKE BELTS
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page207
21
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TMULDBXZZ LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
32-42-00
Page
Page208
22
Jun 30/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-43-00 WHEELS AND BRAKES - ALTERNATE
BRAKING COMPONENTS
TMULDDX09 LEVEL 3
UFD4200
CONTENTS:
Hydraulic Reservoir
Master Cylinders
Alternate Dual Valve
Manifold Brake Alternate Servovalves
Alternate Servovalves
Braking Pressure Transducers
Hydraulic Fuses
Hydraulic Pressure Transducer
Relief Valve
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
209
Page
1
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
HYDRAULIC RESERVOIR
MASTER CYLINDERS
IDENTIFICATION
FIN: 2624GM
IDENTIFICATION
FIN: 2625GM (LH), 2626GM (RH)
LOCATION
ZONE: 122
LOCATION
ZONE: 122
DESCRIPTION
The brake control hydraulic reservoir supplies the
master cylinders of the alternate system with hydraulic
fluid to permit volume changes of the fluid and
compensate possible leakages.
The reservoir is slightly pressurized by a spring
loaded piston: 22 psi (1,5 bar).
Capacity: 3.05 cu. in. (50 cm3).
DESCRIPTION
There is one master cylinder for the LH side and one
for the RH side.
They are used to control the distribution dual valve
of the alternate brake system by displacement of fluid.
They also give artificial feel at the pedals by means
of an internal spring and the load resulting from the
pressure increase in the control circuit.
TMULDDX09-T01 LEVEL 3
UFD4200
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
210
Page
2
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDDX09-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - HYDRAULIC RESERVOIR - MASTER CYLINDERS
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
211
Page
3
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
ALTERNATE DUAL VALVE
IDENTIFICATION
FIN: 2577GM
LOCATION
ZONE: 148
TMULDDX09-T02 LEVEL 3
UFD4200
DESCRIPTION
The alternate dual valve includes two independent
pressure-reducing valves, one for each main gear.
A master cylinder operates each valve.
A transparent drain tube connected to the cover of the
dual valve is used to check for possible presence of
water.
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
212
Page
4
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDDX09-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE DUAL VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
213
Page
5
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
ALTERNATE DUAL VALVE CROSS SECTION
PEDAL RELEASED
Each pressure reducing valve includes a control piston
which operates a distribution slide valve through a
spring R1 and a rocker arm.
When the pedal is released, the yellow pressure at A
is shut off and the brake port C is connected to the
reservoir return B.
TMULDDX09-T03 LEVEL 3
UFD4200
PEDAL DEPRESSED/PRESSURE INCREASING
When the pedal is pushed in, the volume of fluid moved
by the master cylinder causes the displacement of the
piston which then operates the rocker arm and the slide
valve: B is shut off and the pressure port A is
connected to the brake port C.
PEDAL DEPRESSED/PRESSURE REGULATION
In balanced state, the pressure supplied is in
proportion to the compression of the spring R1 and
consequently to the displacement of the control piston.
The pressure increases in the control line as a result
of the compression of the return springs of the control
piston.
The delivery pressure depends on the control piston
travel and the control pressure.
Maximum pressure delivered: 2537 psi (175 bars).
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
214
Page
6
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDDX09-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE DUAL VALVE CROSS SECTION
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
215
Page
7
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
MANIFOLD BRAKE ALTERNATE SERVOVALVES
IDENTIFICATION
FIN: 2615GM (LH), 2614GM (RH)
LOCATION
ZONE: 571, 671
TMULDDX09-T04 LEVEL 3
UFD4200
DESCRIPTION
The manifold is equipped with two servovalves, two
hydraulic fuses and one filter on the supply line of
the manifold.
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
216
Page
8
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDDX09-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - MANIFOLD BRAKE ALTERNATE SERVOVALVES
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
217
Page
9
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
ALTERNATE SERVOVALVES
IDENTIFICATION
FIN: 41GG (Wheel 1), 43GG (Wheel 2), 40GG (Wheel 3),
42GG (Wheel 4)
LOCATION
ZONE: 571 (Wheel 1 & 2), 671 (Wheel 3 & 4)
TMULDDX09-T05 LEVEL 3
UFD4200
DESCRIPTION
Only one coil is used for anti-skid control by system
1 and 2 (pins E and F are not used).
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
Page218
10
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
TMULDDX09-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE SERVOVALVES
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
Page219
11
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
BRAKING PRESSURE TRANSDUCERS
IDENTIFICATION
FIN: 62GG (RH MLG), 63GG (LH MLG)
LOCATION
ZONE: 146
TMULDDX09-T06 LEVEL 3
UFD4200
DESCRIPTION
Two pressure transducers measure the pressure supplied
either by the alternate brake distribution dual valve
or the parking brake pressure limiter.
The pressure transducers send the information to the
Brake Yellow Pressure Triple Indicator in the cockpit.
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
Page220
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Aug 31/00
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_
TMULDDX09-P06 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - BRAKING PRESSURE TRANSDUCERS
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
Page221
13
Aug 31/00
A319/A320/A321 TECHNICAL TRAINING MANUAL
_
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
HYDRAULIC FUSES
IDENTIFICATION
FIN: 2620GM (WHEEL 1), 2622GM (WHEEL 2),
2623GM (WHEEL 3), 2621GM (WHEEL 4)
LOCATION
ZONE: 571 (Wheel 1 & 2), 671 (Wheel 3 & 4)
TMULDDX09-T07 LEVEL 3
UFD4200
DESCRIPTION
A hydraulic fuse, installed between the brake
servovalve and the brake, stops the flow in the line
if the leakage exceeds 1.32 U.S. gal/mn (5 l/mn).
The valve is reset when you depressurize the hydraulic
reservoir and when you open the bleed screw.
EFFECTIVITY
EFFECTIVITY
ALL
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TMULDDX09-P07 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - HYDRAULIC FUSES
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
HYDRAULIC PRESSURE TRANSDUCER
RELIEF VALVE
IDENTIFICATION
FIN: 3068GN
IDENTIFICATION
FIN: 3067GM
LOCATION
ZONE: 148
LOCATION
ZONE: 148
DESCRIPTION
The transducer is made of two main sections. The first
section has the pressure-sensing element. It includes
a diaphragm which is under hydraulic pressure. The
diaphragm causes a piezoresistive sensing element to
operate on the Wheatstone bridge principle, according
to the pressure applied.
The transducer is a sealed unit and no maintenance is
necessary or possible.
The pressure transducer sends hydraulic pressure data
to the Brake Yellow Pressure Triple Indicator for
accumulator pressure indication.
DESCRIPTION
The hydraulic thermal-pressure relief valve is
calibrated at 3436 psi (237 bars).
It can be manually activated for accumulator
depressurization.
TMULDDX09-T08 LEVEL 3
UFD4200
WHEELS AND BRAKES - ALTERNATE BRAKING COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-43-00
Page
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TMULDDX09-P08 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - HYDRAULIC PRESSURE TRANSDUCER - RELIEF VALVE
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
TMULDDX09 LEVEL 3
UFD4200
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EFFECTIVITY
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ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-45-00 WHEELS AND BRAKES - PARKING
BRAKE COMPONENTS
TMULDEX02 LEVEL 3
UFD4200
CONTENTS:
Accumulator
Pressure Gage
Charging Valve
Parking Brake Electrical Control Valve
Parking Brake Operated Valve
Dual Shuttle Valve
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
WHEELS AND BRAKES - PARKING BRAKE COMPONENTS
ACCUMULATOR
CHARGING VALVE
IDENTIFICATION
FIN: 2582GM
IDENTIFICATION
FIN: 2586GM
LOCATION
ZONE: 148
LOCATION
ZONE: 148
DESCRIPTION
The brake yellow pressure accumulator is either
pressurized by the hydraulic system or by the yellow
electric pump.
Filling pressure:
- 1450 psi at 60°F (100 bars at 20°C).
Volume of fluid:
- 164.8 cu.in. (2700 cm3), filled with nitrogen.
DESCRIPTION
The accumulator is equipped with a charging valve for
nitrogen refilling if necessary.
PRESSURE GAGE
IDENTIFICATION
FIN: 2585GM
TMULDEX02-T01 LEVEL 3
UFD4200
LOCATION
ZONE: 148
DESCRIPTION
The pressure
pressure.
gage
EFFECTIVITY
EFFECTIVITY
ALL
indicates
the
actual
nitrogen
32-45-00
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
PARKING BRAKE COMPONENTS - ACCUMULATOR - PRESSURE GAGE - CHARGING VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-45-00
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32 LANDING GEAR
WHEELS AND BRAKES - PARKING BRAKE COMPONENTS
PARKING BRAKE ELECTRICAL CONTROL VALVE
IDENTIFICATION
FIN: 72GG
LOCATION
ZONE: 148
DESCRIPTION
The parking-brake electrical control-valve comprises:
- a linear transmitter which operates the
hydromechanical valve,
- a pressure limiter for the dual shuttle valve
supply,
- a replaceable desiccant cartridge,
- two thermal fuses.
TMULDEX02-T02 LEVEL 3
UFD4200
THERMAL FUSES
A thermal fuse protects each linear transmitter coil
from overheat.
It is possible to reset the fuse after removal of the
transparent cover.
DESICCANT CARTRIDGE
A replaceable desiccant cartridge indicates the
humidity conditions. The cartridge is blue and becomes
pink when in contact with water.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
PARKING BRAKE COMPONENTS - PARKING BRAKE ELECTRICAL CONTROL VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-45-00
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32 LANDING GEAR
WHEELS AND BRAKES - PARKING BRAKE COMPONENTS
PARKING BRAKE OPERATED VALVE
IDENTIFICATION
FIN: 2579GM
LOCATION
ZONE: 148
TMULDEX02-T03 LEVEL 3
UFD4200
DESCRIPTION
The parking brake operated valve, installed between
the brake automatic selector and the dual valve, shuts
off supply to the alternate brake system to prevent
leakage through the distribution dual valve.
Parking brake pressure is delivered through port C.
Pressure from the automatic selector is delivered
through port A.
Port B is connected to the dual valve.
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
PARKING BRAKE COMPONENTS - PARKING BRAKE OPERATED VALVE
EFFECTIVITY
EFFECTIVITY
ALL
32-45-00
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233
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32 LANDING GEAR
WHEELS AND BRAKES - PARKING BRAKE COMPONENTS
DUAL SHUTTLE VALVE
IDENTIFICATION
FIN: 2578GM
LOCATION
ZONE: 148
TMULDEX02-T04 LEVEL 3
UFD4200
DESCRIPTION
The dual shuttle valve includes two valves, one for
each main gear, installed in a single block adjacent
to the alternate brake distribution dual valve.
Each valve is used to select either the alternate
system (E or/and D) (spring biased position) or the
parking brake system (A), to supply the corresponding
gear (C or/and B).
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
PARKING BRAKE COMPONENTS - DUAL SHUTTLE VALVE
EFFECTIVITY
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32 LANDING GEAR
TMULDEX02 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-40-00 WHEEL AND BRAKE COMPONENTS
TMULDJX04 LEVEL 3
UFD4200
CONTENTS:
Main Landing Gear Wheels
Main Landing Gear Tires
Carbon Brakes
Tachometers
Main Landing Gear Drive Tachometers
Axle Wheel Adapter Sleeves
Nose Landing Gear Wheels
Nose Landing Gear Tires
Nose Landing Gear Axle Sleeves
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR WHEELS
MAIN LANDING GEAR TIRES
IDENTIFICATION
FIN: 2651GM (WHEEL 1), 2649GM (WHEEL 2),
2652GM (WHEEL 3), 2650GM (WHEEL 4)
IDENTIFICATION
FIN: 2647GM (WHEEL 1), 2645GM (WHEEL 2),
2648GM (WHEEL 3), 2646GM (WHEEL 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
DESCRIPTION
The MLG wheels consist of two forged light alloy
half-wheels attached together with high-tensile steel
bolts and self-locking nuts.
An O-ring seal is put between the two half-wheels.
The wheel is equipped with :
- one standard inflating valve,
- one bolt which you can replace by a valve with
an incorporated pressure indicator (PSI type).
- six fuse plugs deflate the tire in the event
of excessive brake overheat and thus protect
against tire burst because of excessive
pressure.
Melting point of the fuse plug:
• first set, inside keys, 300°C (572°F),
• second set, on wheel web, 183°C (361°F).
TRAINING INFORMATION POINTS
Always use the appropriate tires on the wheels.
The Braking and Steering Control Unit is set to use
one diameter of main gear tire only (Refer to AMM).
WARNING: THE WHEEL TIRE ASSEMBLY WEIGHS APPROXIMATELY
61 KG (133 LB). BE CAREFUL WHEN YOU INSTALL
IT TO PREVENT INJURY TO PERSONS OR DAMAGE TO
THE WHEEL OR AXLE.
TMULDJX04-T01 LEVEL 3
UFD4200
WHEEL AND BRAKE COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - MAIN LANDING GEAR WHEELS
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
Page
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32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS
CARBON BRAKES
IDENTIFICATION
FIN: 2643GM (WHEEL 1), 2641GM (WHEEL 2),
2644GM (WHEEL 3), 2642GM (WHEEL 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
TMULDJX04-T02 LEVEL 3
UFD4200
DESCRIPTION
Each brake includes:
- a piston housing,
- a carbon heat pack.
The piston housing has:
- two independent hydraulic sets (normal and
alternate) of 7 pistons,
- a bleeder for each of the two systems,
- a half self-sealing coupling for each system,
- a torque tube,
- two wear indicators for the heat pack,
- a brake temperature sensor.
Three bolts and nine pins attach the brake to the axle
flange of the landing gear.
Brake weight: 67 kg (147 lb).
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - CARBON BRAKES
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS
CARBON BRAKES (CONTINUED)
BLEED VALVES
(see following page).
TMULDJX04-T03 LEVEL 3
UFD4200
WEAR PIN INDICATORS
Two wear pins give a visual indication of the overall
wear of the heat pack without removal (Parking brake
applied).
For the minimum length X of the wear pin indicator
refer to the AMM.
EFFECTIVITY
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TMULDJX04-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - BLEED VALVES - WEAR PIN INDICATORS
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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32 LANDING GEAR
TACHOMETERS
MAIN LANDING GEAR DRIVE TACHOMETERS
IDENTIFICATION
FIN: 19GG (WHEEL 1), 21GG (WHEEL 2),
20GG (WHEEL 3), 22GG (WHEEL 4)
IDENTIFICATION
FIN: 2681GM (WHEEL 1), 2680GM (WHEEL 2),
2679GM (WHEEL 3), 2678GM (WHEEL 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
DESCRIPTION
The tachometers send wheel speed information.
Each tachometer has two 200 tooth rings:
- 1 stationary ring associated to a coil and a
permanent magnet,
- 1 ring driven by the wheel.
The rotation of the wheel causes variations in the
induction frequency which are proportional to the
angular speed (Frequency = 200 x angular speed).
The variable frequency voltage supplied by the
tachometer is sent to the Braking/Steering Control
Unit (BSCU).
AXLE WHEEL ADAPTER SLEEVES
IDENTIFICATION
FIN: 2634GM (WHEEL 1), 2633GM (WHEEL 2),
2632GM (WHEEL 3), 2631GM (WHEEL 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
TRAINING INFORMATION POINT
Each wheel is installed on the axle with an axle sleeve.
CAUTION : WHEN YOU INSTALL THE SLEEVE, DO NOT FORGET
TO TURN IT IN ORDER TO INSERT THE LOCATING
PEGS IN THE AXLE KEYWAYS, THEN PUT THE
RETAINER IN ITS GROOVE.
TMULDJX04-T04 LEVEL 3
UFD4200
WHEEL AND BRAKE COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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TMULDJX04-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - TACHOMETERS - MLG DRIVE TACHOMETERS - AXLE SLEEVES
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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32 LANDING GEAR
NOSE LANDING GEAR WHEELS
NOSE LANDING GEAR TIRES
IDENTIFICATION
FIN: 2659GM (WHEEL 9), 2660GM (WHEEL 10)
IDENTIFICATION
FIN: 2635GM (WHEEL 9), 2636GM (WHEEL 10)
LOCATION
ZONE: 711
LOCATION
ZONE: 711
DESCRIPTION
The wheels consist of two forged half-wheels made of
light alloy.
They are attached together with bolts and self-locking
nuts.
An O-ring seal is put between the two half-wheels.
The wheels have 3 ports which are equipped with :
- one standard inflating valve,
- one overpressure relief valve,
- one bolt which you can replace by a valve with
an incorporated pressure indicator (PSI type).
Wheel weight: 15.95 kg (35 lbs), including hub cap.
TRAINING INFORMATION POINT
Always use the appropriate tires on the wheels.
AXLE SLEEVES
LOCATION
ZONE: 711
TRAINING INFORMATION POINT
Each NLG wheel is installed on the axle with an axle
sleeve.
TMULDJX04-T05 LEVEL 3
UFD4200
WHEEL AND BRAKE COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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TMULDJX04-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - NLG WHEELS - AXLE SLEEVES
EFFECTIVITY
EFFECTIVITY
ALL
32-40-00
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32 LANDING GEAR
TMULDJX04 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-47-00 WHEELS AND BRAKES - BRAKE
TEMPERATURE SYSTEM COMPONENTS
TMULDIX01 LEVEL 3
UFD4200
CONTENTS:
BTMUs
Temperature Sensors
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
BTMUs
TEMPERATURE SENSORS
IDENTIFICATION
FIN: 3GW, 2GW
IDENTIFICATION
FIN: 7GW, 5GW, 4GW, 6GW
LOCALISATION
ZONE: 731, 741
LOCALISATION
ZONE: 731, 731, 741, 741
COMPONENT DESCRIPTION
The Brake Temperature Monitoring Unit (BTMU) is
equipped with two printed circuits required to:
- process the data from the temperature sensor,
- compensate the thermocouple cold junction.
There is one BTMU per main gear.
COMPONENT DESCRIPTION
Each brake is equipped with a temperature sensor which
is of the chromel-alumel thermocouple type.
It delivers a voltage which is proportional to the
temperature difference between the cold junction and
the hot junction.
TMULDIX01-T01 LEVEL 3
UFD4200
WHEELS AND BRAKES - BRAKE TEMPERATURE SYSTEM COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-47-00
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TMULDIX01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE TEMPERATURE SYSTEM COMPONENTS - BTMUs - TEMPERATURE SENSORS
EFFECTIVITY
EFFECTIVITY
ALL
32-47-00
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32 LANDING GEAR
TMULDIX01 LEVEL 3
UFD4200
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EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-48-00 WHEELS AND BRAKES - BRAKE
COOLING SYSTEM COMPONENTS
TMULDFX01 LEVEL 3
UFD4200
CONTENTS
Fan Motor
Impeller
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
FAN MOTOR
IMPELLER
IDENTIFICATION
FIN: 7GS (WHEEL 1), 9GS (WHEEL 2), 8GS (WHEEL 3),
10GS (WHEEL 4)
IDENTIFICATION
FIN: 2789GM (WHEEL 1), 2790GM (WHEEL 2),
2791GM (WHEEL 3), 2792GM (WHEEL 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
LOCATION
ZONE: 731 (WHEEL 1 & 2), 741 (WHEEL 3 & 4)
DESCRIPTION
The three phase fan motor is installed in the wheel
axle, where an adaptor assembly holds it in position.
Note that the tachometer drive shaft passes through
the hollow shaft of the fan motor and the shroud drives
the tachometer.
DESCRIPTION
The impeller creates a flow of air from the heat pack
to the exterior through the debris guard.
TMULDFX01-T01 LEVEL 3
UFD4200
WHEELS AND BRAKES - BRAKE COOLING SYSTEM COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
32-48-00
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TMULDFX01-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKE COOLING SYSTEM COMPONENTS - FAN MOTOR - IMPELLER
EFFECTIVITY
EFFECTIVITY
ALL
32-48-00
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32 LANDING GEAR
TMULDFX01 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-51-00 NOSE WHEEL STEERING SYSTEM
PRESENTATION
TMULD1003 LEVEL 1
UFD4200
CONTENTS:
Controls
Pedals
Disconnect Pushbutton
BSCU
Activation
Towing Control Lever
Self Examination
EFFECTIVITY
EFFECTIVITY
ALL
32-51-00
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32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM PRESENTATION
The nose wheel steering system is hydraulically powered
and controlled by an electrical servomechanism from
the cockpit via the Braking and Steering Control Unit
(BSCU).
CONTROLS
Steering is controlled by two handwheels and the rudder
pedals depending on aircraft speed. Their signals are
algebraically
added
if
they
are
operated
simultaneously.
Steering angle speed limitation shown on the schematic
below.
PEDALS
Steering orders from the pedals are sent to the BSCU,
via the Elevator Aileron Computer which also receives
autopilot steering signals.
The resulting signal is algebraically added to the
handwheel signals in the BSCU.
ACTIVATION
Steering signals are sent to the hydraulic block when
the arming conditions are met.
The steering hydraulic block is powered by green
pressure if the nose gear doors are closed.
NOTE: Steering is lost after gear gravity extension
as the doors remain open.
TOWING CONTROL LEVER
A lever on the towing electrical box located on the
nose landing gear enables the steering system to be
deactivated for towing purposes.
With the control lever in towing position:
- The maximum towing angle is ± 95°,
- The ECAM MEMO DISPLAY shows N WHEEL STEER
DISC in green, which changes to amber if
one engine is running.
DISCONNECT PUSHBUTTON
TMULD1003-T01 LEVEL 1
UFD4200
When a rudder pedal disconnect pushbutton is pressed
in, nose wheel steering by the pedals is disconnected.
NOTE: The disconnect pushbuttons are also used during
rudder ground check.
BSCU
The A/SKID & N/W STRG switch enables electrical power
supply of the BSCU which computes the steering orders.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM PRESENTATION
EFFECTIVITY
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32 LANDING GEAR
SELF EXAMINATION
What is the maximum nose wheel steering angle
obtained by the handwheels?
A - ± 6°.
B - ± 74°.
C - ± 95°.
TMULD1003 LEVEL 1
UFD4200
Is nose wheel steering available after a landing
gear gravity extension ?
A - Yes.
B - No.
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-51-00 NOSE WHEEL STEERING SYSTEM
DESCRIPTION/OPERATION
TMULDGS04 LEVEL 3
UFD4200
CONTENTS:
Rotating Joint
Selector Valve
Check Valve/Filter
Servovalve
Adjustable Diaphragm
Check Valves
Bypass Valve
Anti-Shimmy Valves
Steering Actuator
Accumulator
Bleed Screw
Operation
Self Examination
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NOSE WHEEL STEERING SYSTEM DESCRIPTION/OPERATION
ROTATING JOINT
CHECK VALVES
The rotating joint is installed co-axially with respect
to the landing gear retraction axis and provides
hydraulic power supply when the gear is extended.
When the gear starts to retract, the rotating joint
cuts the hydraulic power supply.
Two check valves ensure the distribution of fluid from
the accumulator to the chamber of the steering actuator.
SELECTOR VALVE
When the selector valve is energized the pressure is
applied to the servovalve via the slaved valve.
BYPASS VALVE
The bypass valve interconnects the two chambers of the steering
actuator in the event of hydraulic system depressurization.
The bypass valve opens if the pressure exceeds 273 bars
(4000 psi).
ANTI-SHIMMY VALVES
CHECK VALVE/FILTER
There is one anti-shimmy valve per steering actuator chamber.
A 40 micron filter and a check valve are installed in
the hydraulic power supply line.
SERVOVALVE
TMULDGS04-T01 LEVEL 3
UFD4200
The servovalve is of the deflection-jet type. It is
equipped with a Linear Variable Differential
Transducer (LVDT) sensor which detects the position
of the slide valve.
The LVDT provides position feedback for the steering
control.
ADJUSTABLE DIAPHRAGM
The ajustable diaphragms are used to adjust the flow
to each actuating cylinder chamber and consequently
the wheel steering speed.
STEERING ACTUATOR
The steering actuator drives the rotating tube, which
is part of the nose landing gear structure, via a
rack-and-pinion assembly.
ACCUMULATOR
The anti-shimmy accumulator supplies pressurized fluid
in case of cavitation in one of the two chambers of
the steering actuator.
The accumulator can supply fluid pressurized up to 15
bars (220 psi).
BLEED SCREW
A bleed screw allows bleeding and depressurization of
the hydraulic block.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM DESCRIPTION/OPERATION - DESCRIPTION
EFFECTIVITY
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NOSE WHEEL STEERING SYSTEM DESCRIPTION/OPERATION
OPERATION
TMULDGS04-T02 LEVEL 3
UFD4200
When the nose gear is extended and the nose gear doors
are closed, the hydraulic block is pressurized.
When the MLG is compressed, both chambers of the
steering actuator are supplied and the nose wheels
servoed to an angle of 0º.
Depending on the BSCU reference speed and the nose
wheel steering orders, the nose wheels are steered.
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM DESCRIPTION/OPERATION - OPERATION
EFFECTIVITY
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SELF EXAMINATION
What is the purpose of the accumulator?
A - To compensate a complete pressure loss.
B - To dampen rapid movements.
C - To supply hydraulic pressure in case of
cavitation.
What is the purpose of the bypass valve?
A - To interconnect the two chambers of the
steering actuator.
B - To apply hydraulic pressure to the
servovalve.
C - To bypass the servovalve in case of BSCU
failure.
TMULDGS04 LEVEL 3
UFD4200
What are the adjustable diaphragms used for?
A - To ensure self centering of the nose
gear.
B - To adjust the nose wheel steering speed.
C - To adjust the rate of depressurization
in the hydraulic block.
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-42-00 NOSE WHEEL STEERING ECAM PAGE
PRESENTATION
TMULDB401 LEVEL 1
UFD4200
CONTENTS:
Steering Indication
EFFECTIVITY
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NOSE WHEEL STEERING ECAM PAGE PRESENTATION
The ECAM WHEEL page displays landing gear and door
positions, as well as brake and steering indications.
STEERING INDICATION
TMULDB401-T01 LEVEL 1
UFD4200
The "STEERING" indication appears amber in case of
green hydraulic failure, nose wheel steering failure
or when the anti-skid and nose wheel steering (A/SKID
& N/W STRG) switch is set to "OFF".
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING ECAM PAGE PRESENTATION
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-42-00 NOSE WHEEL STEERING SYSTEM
WARNINGS
TMULDC601 LEVEL 3
UFD4200
CONTENTS:
ANTI SKID/NWS Fault
ANTI SKID/NWS Off
Hyd Sel Fault
BSCU Sys 1 (2) Fault
N.W. Steer Fault
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM WARNINGS
EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-51-00 NOSE WHEEL STEERING SYSTEM
COMPONENTS
TMULDKX02 LEVEL 2
UFD4200
CONTENTS:
Electrical Box
EFFECTIVITY
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NOSE WHEEL STEERING SYSTEM COMPONENTS
ELECTRICAL BOX
IDENTIFICATION
FIN: 5GC
LOCATION
ZONE: 711
TMULDKX02-T01 LEVEL 2
UFD4200
DESCRIPTION
The electrical box is used to disengage the steering
control system when the aircraft is being towed. In
the disengaged position the handle must be secured by
a pin.
In addition, a light indicates when the PARKING BRAKE
is set to the "ON" position. A LIGHT TEST pushbutton
allows this light to be tested.
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM COMPONENTS - ELECTRICAL BOX
EFFECTIVITY
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TMULDKX02 LEVEL 2
UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-51-00 NOSE WHEEL STEERING SYSTEM
COMPONENTS
TMULDLX02 LEVEL 3
UFD4200
CONTENTS:
BSCU
Handwheel Transmitter Unit
Feedback Sensors
Hydraulic Control Unit
Rotating Joint
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
BSCU
HANDWHEEL TRANSMITTER UNIT
IDENTIFICATION
FIN: 10GG
IDENTIFICATION
FIN: 1GC, 2GC
LOCATION
ZONE: 122
LOCATION
ZONE: 211, 212
DESCRIPTION
The Braking and Steering Control Unit (BSCU) consists
of:
- four power supply units grouped two by two,
- two identical sets of three boards which form
the systems 1 and 2, each board is connected
to an On-Board Reprogrammable Module (OBRM),
- a rear interface in the form of two U-shaped
boards (around the connector) comprises the
lightning protection and the switching
assemblies.
DESCRIPTION
Each handwheel activates a transmitter unit with
4 potentiometers.
In addition, it includes a pushbutton switch for the
disconnection of the nose wheel steering control
through the rudder pedals.
TMULDLX02-T01 LEVEL 3
UFD4200
NOSE WHEEL STEERING SYSTEM COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM COMPONENTS - BSCU - HANDWHEEL TRANSMITTER UNIT
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
FEEDBACK SENSORS
HYDRAULIC CONTROL UNIT
IDENTIFICATION
FIN: 3GC, 4GC
IDENTIFICATION
FIN: 6GC
LOCATION
ZONE: 711
LOCATION
ZONE: 711
DESCRIPTION
The nose wheel steering feedback sensor is of the
Rotary Variable Differential Transducer (RVDT) type.
It consists of a reduction gearbox and a sensor box.
The sensor box transmits the rotating tube position
to the sensor box which sends information to the BSCU
for steering position monitoring.
The knob, with an internal lockpin, locks the gearbox
in the neutral position (0 degree) before installation
of the sensor box.
DESCRIPTION
The hydraulic control unit mainly consists of:
- a selector valve,
- a servovalve,
- an accumulator,
- a filter and valves.
It is hydraulically supplied from the nose landing
gear doors close line, through the rotating joint, and
electrically connected to the BSCU.
It supplies the steering cylinders according to the
electrical signals.
TMULDLX02-T02 LEVEL 3
UFD4200
NOSE WHEEL STEERING SYSTEM COMPONENTS
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM COMPONENTS - FEEDBACK SENSORS - HYDRAULIC CONTROL UNIT
EFFECTIVITY
EFFECTIVITY
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NOSE WHEEL STEERING SYSTEM COMPONENTS
ROTATING JOINT
IDENTIFICATION
FIN:2526GM (NLG LEG ASSY)
LOCATION
ZONE: 711
TMULDLX02-T03 LEVEL 3
UFD4200
DESCRIPTION
The rotating joint mainly consists of:
- a fixed part fitted with a liner and a lever
for the attachment to the aircraft structure,
- a moving part fitted with a shaft and a plate
for the attachment to the NLG leg hinge pin.
It supplies the steering hydraulic control unit when
the leg is downlocked and stops the fluid flow when
the leg is in another position.
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NOSE WHEEL STEERING SYSTEM COMPONENTS - ROTATING JOINT
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-42-00 BRAKING AND STEERING - BSCU
CONTROL INTERFACES
TMULDGV0C LEVEL 3
UFD4200
CONTENTS:
ADIRUs
SECs
LGCIUs
ELACs
BTMUs
Tachometers
LGCIUs
Pack Controllers
EFFECTIVITY
EFFECTIVITY
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BRAKING AND STEERING - BSCU CONTROL INTERFACES
ADIRUs
TACHOMETERS
The aircraft reference speed for nose wheel steering
and anti-skid functions is obtained by processing the
inertial deceleration from the Air Data Inertial
Reference Units (ADIRUs).
Tachometers send wheel speed values to the BSCU
enabling reference speed computation and also to the
Spoiler Elevator Computers for ground spoilers
extension logic.
SECs
LGCIUs
Two of the three ground spoilers extended signals
coming from the Spoiler Elevator Computers (SECs) must
be present to enable automatic braking.
Landing Gear Control and Interface Units receive wheel
speed indications.
These signals are used for BITE inhibition.
LGCIUs
PACK CONTROLLERS
Inputs from both Landing Gear Control and Interface
Units (LGCIUs) serve for braking and nose wheel
steering functions control logic.
After wheel speed computation the BSCU energizes wheel
speed relays.
The latter send a signal to the Pack Controllers for
pack ram air inlet operation during take-off and
landing phases.
ELACs
The link between the BSCU and the Elevator Aileron
Computer (ELAC) serves for nose wheel steering purposes
with orders coming from rudder pedals and autopilot.
TMULDGV0C-T01 LEVEL 3
UFD4200
BTMUs
The BSCU changes analog signals from the Brake
Temperature Monitoring Units (BTMUs) into digital ones
for temperature indication on the lower ECAM display
unit.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BRAKING AND STEERING - BSCU CONTROL INTERFACES
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-42-00 BRAKING AND STEERING - BSCU
ARCHITECTURE AND MONITORING
INTERFACES
TMULDGUZZ LEVEL 3
UFD4200
CONTENTS:
Architecture
Monitoring
EFFECTIVITY
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32 LANDING GEAR
BRAKING AND STEERING - BSCU ARCHITECTURE AND MONITORING INTERFACES
ARCHITECTURE
TMULDGUZZ-T01 LEVEL 3
UFD4200
The Braking/Steering Control Unit (BSCU) is made up
of two identical sets of three boards which form the
systems 1 and 2.
At each energization the system supplied first takes
control.
If there is a disagreement between the control and the
monitoring channels, the corresponding system is
disengaged and the system in standby takes over.
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BSCU ARCHITECTURE AND MONITORING INTERFACES - ARCHITECTURE
EFFECTIVITY
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BRAKING AND STEERING - BSCU ARCHITECTURE AND MONITORING INTERFACES
MONITORING
CFDIU
The BSCU sends BITE data to the Centralized Fault
Display System (CFDS) by a bi-directional ARINC 429
link. This link permits transmission of the failure
messages.
SDAC
The System Data Acquisition Concentrators (SDACs)
receive ARINC 429 bus signals for acquirement and
processing of all the data necessary for the generation
of warnings.
FDIU
The Flight Data Interface Unit collects braking system
data (braking pressure, braking pedal position,
autobrake status) in order to send them to the flight
data recorder.
TMULDGUZZ-T02 LEVEL 3
UFD4200
DMU
The Display Management Unit receives maintenance data
for reports used in preventive maintenance. The Display
Management Unit (DMU) is a computer of the Aircraft
Integrated Data System (AIDS)(as an option, AIDS may
not be installed).
FMGC
The BSCU sends 4 availability discretes to the Flight
Management and Guidance Computers (FMGCs). This is to
meet the safety requirements of a category 3B landing.
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
BSCU ARCHITECTURE AND MONITORING INTERFACES - MONITORING
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-49-00 TIRE PRESSURE INDICATING SYSTEM
PRESENTATION
TMULD1Q04 LEVEL 1
UFD4200
CONTENTS:
Function
Description
Self Examination
EFFECTIVITY
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32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM PRESENTATION
FUNCTION
The function of the Tire Pressure Indicating System
is to supply:
- pressure information, for each tire, to be
displayed on the ECAM,
- warnings when pressure in one or more tires
does not agree with the specified pressure.
The warning functions of the system are as follows:
- to show that the absolute pressure of any tire
is lower than a given value,
- to tell the flight crew when the pressure
difference between 2 tires installed on the
same wheel axle is above a given value,
The indication becomes amber in case of abnormal
pressure.
TMULD1Q04-T01 LEVEL 1
UFD4200
DESCRIPTION
The Tire Pressure Indicating System has a sensor and
a transmitter for each wheel, and includes a computer:
the Tire Pressure Indicating Unit (TPIU).
The system includes:
- a sensor which measures the pressure of each
tire,
- a rotating mechanism which transmits the
electrical pressure signal from the wheel to
the wheel axle.It includes a rotating
transformer and an integrated electronic
module,
- a computer TPIU (Tire Pressure Indicating
Unit).
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM PRESENTATION
EFFECTIVITY
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32 LANDING GEAR
SELF EXAMINATION
TMULD1Q04 LEVEL 1
UFD4200
Where is the Tire Pressure Indication displayed ?
A - On a tire and brake indicator.
B - On ECAM.
C - No indication.
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32 LANDING GEAR
32 - LANDING GEAR
32-49-00 TIRE PRESSURE INDICATING SYSTEM
DESCRIPTION/OPERATION
TMULDGQ04 LEVEL 3
UFD4200
CONTENTS:
Purpose
Pressure Transducer
Rotating Mechanism
Electronic Module
Rotating Transformer
Detection Unit
Interfaces
Self Examination
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32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM DESCRIPTION/OPERATION
PURPOSE
ROTATING TRANSFORMER
The Tire Pressure Indicating System (TPIS)
continuously monitors the absolute pressure of each
individual tire and provides cockpit indications and
warnings.
The rotating transformer transmits the tire pressure
value from the wheel to the detection unit.
PRESSURE TRANSDUCER
The detection unit comprises a microprocessor which
provides data processing and distribution of each tire
pressure including normal and abnormal pressure
signals for ECAM indication and CFDS monitoring.
The TPIS detection unit permanently performs a test
of the unit itself, the rotating mechanism and the
pressure transducer. The test is only stopped for data
processing and distribution.
A pressure transducer installed in the wheel rim
measures the pressure of each tire.
The pressure transducer gives a DC signal from 0 to
100mV in proportion to the pressure.
ROTATING MECHANISM
The rotaring mechanism serves to transmit the tire
pressure signal from the wheel to the axle.
The rotating transformer also provides the necessary
power supply for the electronic module and the pressure
transducer in form of a 3125Hz signal.
TMULDGQ04-T01 LEVEL 3
UFD4200
ELECTRONIC MODULE
DETECTION UNIT
INTERFACES
The signal from the Landing Gear Control and Interface
Unit (LGCIU) is used to change the tire pressure
threshold for on ground or in flight warnings.
Note that tire pressure warnings are only memorized
by the BITE when at least one engine is running to
prevent false warnings during wheel change.
The integrated electronic module amplifies the signal
from the pressure transducer and changes the voltage
into frequency by means of a converter.
The voltage to frequency converter gives a signal which
varies from 50 to 100kHz for a pressure range from 0
to 300psi.
EFFECTIVITY
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TMULDGQ04-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM DESCRIPTION/OPERATION
EFFECTIVITY
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32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM DESCRIPTION/OPERATION
SELF EXAMINATION
What signal is delivered by the pressure transducer?
A - A DC signal which depends on the tire
pressure.
B - A frequency signal which depends on the
tire pressure.
C - A pneumatic signal equal to the tire
pressure.
TMULDGQ04 LEVEL 3
UFD4200
What is the rotating mechanism used for?
A - To change the pressure voltage into a
frequency signal.
B - To transmit the tire pressure signal
from the wheel to the axle.
C - To perform the permanent test of the
system.
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32 LANDING GEAR
32 - LANDING GEAR
32-49-00 TIRE PRESSURE INDICATING SYSTEM
WARNINGS
TMULDBQ04 LEVEL 3
UFD4200
CONTENTS:
Tire Lo Pr
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TMULDBQ04-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM WARNINGS
EFFECTIVITY
EFFECTIVITY
ALL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-49-00 TIRE PRESSURE INDICATING SYSTEM
COMPONENTS
TMULDHX04 LEVEL 3
UFD4200
CONTENTS:
Tire Pressure Indicating Unit
MLG Transmission Unit
MLG Pressure Transducer
NLG Transmission Unit
NLG Pressure Transducer
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32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM COMPONENTS
TIRE PRESSURE INDICATING UNIT
IDENTIFICATION
FIN: 2GV
LOCATION
ZONE: 122
TMULDHX04-T01 LEVEL 3
UFD4200
COMPONENT DESCRIPTION
The TPIS detection unit is of the 3 Modular Concept
Unit (MCU) size and is connected to the aircraft wiring
through an ARINC 600 connector, size 1.
The detection unit performs a permanent test which is
only stopped for processing of the following three
functions :
- pressure measurement,
- data distribution,
- maintenance.
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TMULDHX04-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM COMPONENTS - TIRE PRESSURE INDICATING UNIT
EFFECTIVITY
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32 LANDING GEAR
MLG TRANSMISSION UNIT
MLG PRESSURE TRANSDUCER
IDENTIFICATION
FIN: 7GV (WHEEL 1), 9GV (WHEEL 2), 6GV (WHEEL 3),
8GV (WHEEL 4)
IDENTIFICATION
FIN: 13GV (WHEEL 1), 15GV (WHEEL 2), 12GV (WHEEL 3),
14GV (WHEEL 4)
LOCATION
ZONE: 731 (LH MLG), 741 (RH MLG)
LOCATION
ZONE: 731 (LH MLG), 741 (RH MLG)
COMPONENT DESCRIPTION
The rotating mechanism includes :
- a rotating transformer which transmits the
electrical power (3125Hz signal) to supply the
electronic circuits and the pressure transducer
installed on the wheel. It transmits also the
tire pressure value from the wheel to the axle.
The frequency varies from 50kHz to 100kHz.
- an integrated electronic module which amplifies
the DC signal from the pressure transducer and
converts the voltage into frequency (50kHz to
100kHz range), before the signal is applied to
the rotating transformer.
COMPONENT DESCRIPTION
The pressure transducer is installed in a support
attached to the wheel rim. It is of the piezoresistive
strain-gage type. An external voltage source supplies
this transducer which gives a DC signal from 0 to 100mV
in proportion to the pressure. A four-wire, shielded
and twisted cable is connected to the rotating
mechanism.
TMULDHX04-T02 LEVEL 3
UFD4200
TIRE PRESSURE INDICATING SYSTEM COMPONENTS
EFFECTIVITY
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TMULDHX04-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TPIS COMPONENTS - MLG TRANSMISSION UNIT - MLG PRESSURE TRANSDUCER
EFFECTIVITY
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32 LANDING GEAR
NLG TRANSMISSION UNIT
NLG PRESSURE TRANSDUCER
IDENTIFICATION
FIN: 4GV (WHEEL 9), 5GV (WHEEL 10)
IDENTIFICATION
FIN: 10GV (WHEEL 9), 11GV (WHEEL 10)
LOCATION
ZONE: 711
LOCATION
ZONE: 711
TMULDHX04-T03 LEVEL 3
UFD4200
TIRE PRESSURE INDICATING SYSTEM COMPONENTS
EFFECTIVITY
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TMULDHX04-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TPIS COMPONENTS - NLG TRANSMISSION UNIT - NLG PRESSURE TRANSDUCER
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
TMULDHX04 LEVEL 3
UFD4200
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 MAIN LANDING GEAR SERVICING
TMULDTT05 LEVEL 3
UFD4200
CONTENTS:
Spare Seal Activating Valve
Torque Link Damper
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR SERVICING
SPARE SEAL ACTIVATING VALVE
DESCRIPTION
Each main landing gear fitting has a spare seal
activating valve. The activating valve is on the barrel
of the main fitting, adjacent to the gland housing
assembly. This valve can isolate the bottom gland seals
if a leak occurs from that position.
TMULDTT05-T01 LEVEL 3
UFD4200
OPERATION
Under normal conditions the valve stem of the spare
activating valve is screwed out, with the ball away
from its seat. Fluid pressure in the shock absorber
is felt equally on both sides of the upper seal in the
lower bearing sub-assembly, but only one side of the
lower seal. Therefore, the lower seal is subjected to
pressure differentials.
If a leak occurs at the lower bearing housing,
indicated by the presence of hydraulic fluid on the
sliding tube, the fault may be expected to be from the
lower seal.
The cap screw, an indicator, must be removed and the
valve stem screwed on to seat the ball. This action
isolates the lower seal from hydraulic pressure, which
effectively stops the leak, and transfers the pressure
differential to the upper seal.
EFFECTIVITY
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TMULDTT05-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR SERVICING - SPARE SEAL ACTIVATING VALVE
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR SERVICING
TORQUE LINK DAMPER
TMULDTT05-T02 LEVEL 3
UFD4200
DESCRIPTION
The torque link damper is a spring centered, two way
hydraulic unit, which has its own pressurized hydraulic
reservoir. Its function is to decrease the landing
vibrations through the torque links.
The hydraulic fluid contents of the damper are shown
by the extension of the reservoir when it is
pressurized. When the contents are correct, the "FULL"
and "REFILL" level indications are in view.
- Remove the hydraulic rig and bleed tube, then
check for leakage over the next 3 minutes at
the same time ensuring the reservoir can
remains above the "FULL" line.
- Finally open the bleed plug slowly until
reservoir can is level with the "FULL"
line, then close and lock the bleed and cap
assemblies.
REPLENISHMENT
The torque link damper must be fitted in accordance
with AMM 12-12-00, but we will consider the general
outline of the task:
- First remove the cap assembly from the check
valve, and bleed screw from the bleed plug,
then attach a hydraulic charging rig, using a
connector, to the check valve.
- Next fit a plastic tube, which is SKYDROL
compatible, to the bleed plug, this is to
collect expelled fluid, so place the free end
of the plastic tube into a suitable container.
- Using the hydraulic rig, apply a pressure of
2.42 to 2.75 bars (35.1 to 39.9 psi) and open
the bleed plug until an air free flow of fluid
is obtained.
- Increase the pressure to between 2.75 and 3.45
bars (39.9 and 50 psi) and close the bleed
plug, the reservoir can should rise slightly
above the "FULL" line (approximately 2.5 mm/0.1
inch).
EFFECTIVITY
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TMULDTT05-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR SERVICING - TORQUE LINK DAMPER
EFFECTIVITY
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32 LANDING GEAR
TMULDTT05 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 - LANDING GEAR
32-00-00 MAIN LANDING GEAR SHOCK ABSORBER
SERVICING
TMULDGA06 LEVEL 3
UFD4200
CONTENTS:
General
Servicing Procedures
Nitrogen Filling of the MLG Two-Stage Shock Absorber
Pressure/Extension Graph - Values of the Film
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
GENERAL
TMULDGA06-T01 LEVEL 3
UFD4200
PA is the pressure measured at the top charging valve
(valve A).
PB is the pressure measured at the bottom charging
valve (valve B).
H is the height of the shock aborber measured as shown
bellow.
EFFECTIVITY
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TMULDGA06-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
GENERAL - TOP CHARGING VALVE - BOTTOM CHARGING VALVE - H MEASUREMENT
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
SERVICING PROCEDURES
Inspection of the MLG Shock Absorber Before Flight
TMULDGA06-T02 LEVEL 3
UFD4200
Check Charge and Nitrogen Filling of the MLG Two-Stage
Shock Absorber
EFFECTIVITY
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TMULDGA06-P02 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SERVICING PROCEDURES
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
SERVICING PROCEDURES
TMULDGA06-T03 LEVEL 3
UFD4200
Nitrogen Filling of the MLG Two-Stage Shock Absorber
(metric units)
EFFECTIVITY
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TMULDGA06-P03 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SERVICING PROCEDURES - NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER (metric units)
EFFECTIVITY
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
SERVICING PROCEDURES
TMULDGA06-T04 LEVEL 3
UFD4200
Nitrogen Filling of the MLG Two-Stage Shock Absorber
(US units)
EFFECTIVITY
EFFECTIVITY
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TMULDGA06-P04 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
SERVICING PROCEDURES - NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER (US units)
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
TMULDGA06-T05 LEVEL 3
UFD4200
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER
This film includes several procedures or parts of
procedures of the shock absorber servicing:
- Check Charge Pressure of the Main Landing Gear
Shock Absorber,
- Visual Inspection of the Main Landing Gear
Two-Stage Shock Absorber for Leakage of
Hydraulic Fluid,
- Nitrogen Filling of the Main Landing Gear
Two-Stage Shock Absorber (Aircraft on the
Ground).
The values of some parameters such as temperature,
pressure, etc, have to be recorded to perform this
procedure. Depending on the value obtained, some parts
must or must not be done, referring to the Aircraft
Maintenance Manual.
Of course, when you will effectively do it, you will
have to adapt your actions to the values you will
obtain. In no case, can the values used in this film
be used as a reference.
WARNING: PUT THE SAFETY DEVICES AND THE WARNING NOTICES
IN POSITION BEFORE YOU START A TASK ON OR
NEAR:
- THE FLIGHT CONTROLS,
- THE FLIGHT CONTROL SURFACES,
- THE LANDING GEAR AND THE RELATED DOORS,
- ANY COMPONENTS THAT MOVE.
MAKE SURE THAT THE GROUND SAFETY-LOCKS ARE
IN POSITION ON THE LANDING GEAR.
EFFECTIVITY
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Note that it is recommended that you wait a minimum
of ten minutes after taxiing or towing before you carry
out this procedure. This will allow to get a stable
temperature and a more accurate value of the shock
absorber extension and pressures.
During this procedure, actions will be made on the top
charging valve (also called valve A), and on the bottom
charging valve (also called valve B).
A placard located underneath the top charging valve
gives you a summary of the information necessary to
perform this procedure.
It consists of:
- a gear schematic which shows you where you have
to measure the height H,
- a summarized actions list which presents the
main points necessary to perform the dedicated
procedures,
- DIAGRAM 1 which allows you to find a target
value H depending on the measured temperature
and the pressure on the top charging valve,
- DIAGRAM 2 which gives the same information,
but for a different step of the procedure,
- DIAGRAM 3 enables you to find the position
of a point determined by the temperature
and the pressure values in relation to a
graph line.
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TMULDGA06-P05 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER - SHOCK ABSORBER SCHEMATIC
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER
(cont’d)
TMULDGA06-T06 LEVEL 3
UFD4200
PREPARATION
In the cockpit,
make sure that the landing gear control lever is in
the DOWN position and put a warning notice in position
to tell people not to operate the landing gear.
On the outside,
- make sure that the wheel chocks are in position
on the main landing gear, but do not put a
chock on the nose wheel,
- put a warning notice in position to tell persons
not to operate the landing gear doors,
- put the access platform in position below the
applicable shock absorber.
Before filling with nitrogen, examine the gland housing
of the shock absorber for leakage of hydraulic fluid.
In case of leakage, refer to your AMM to troubleshoot.
PROCEDURE
Measure and record dimension H, H = 89 mm (3.50 in).
Measure and record the temperature of the MLG adjacent
to the top charging valve, T = 10ºC (50ºF).
Put the standard charging equipment into position.
On the top charging valve:
- remove the blanking cap,
- on the charging equipment, make sure that the
control valves are closed,
- and connect the filling hose.
Do the same on the bottom charging valve.
CAUTION: MAKE SURE THAT YOU USE A GAGE WITH THE
SPECIFIED PRESSURE RANGE.
EFFECTIVITY
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On the top charging valve:
- slowly open it,
- read and record the pressure shown on the
pressure gage, PA = 79 bar (1150 psi),
- and then close it.
Do the same on the bottom charging valve, PB = 75 bar
(1090 psi).
Using DIAGRAM 1, find the dimension HA for the pressure
at the top charging valve and the measured temperature,
HA = 141mm (5.6 in) (1).
As the condition H = HA ± 15mm (0.6 in) is not fulfilled
we have to do the Nitrogen Filling of the MLG Two-Stage
Shock Absorber.
The pressure at the bottom charging valve must be
between 13.8 and 20.7 bar (200 and 300 psi) above the
pressure at the top charging valve,
PA + 13.8 bar < PB < PA + 20.7 bar.
This is to ensure that the floating piston is at the
top of the bottom chamber (key point in case of
restart).
To perform this condition, we are going to pressurize
the bottom chamber.
WARNING: DO NOT PUT COMPRESSED GAS IN CONTACT WITH
YOUR SKIN. THE GAS CAN GO THROUGH THE SKIN
AND CAUSE BUBBLES IN THE BLOOD. THIS COULD
CAUSE DEATH.
MAKE SURE THAT THE AREA AROUND THE AIRCRAFT
IS CLEAR OF PERSONS AND EQUIPMENT. WHEN YOU
PRESSURIZE OR DEPRESSURIZE THE SHOCK
ABSORBER, WITH THE AIRCRAFT WEIGHT ON THE
GROUND, THE AIRCRAFT WILL MOVE.
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER
(cont’d)
TMULDGA06-T06 LEVEL 3
UFD4200
CAUTION: ALWAYS ADD NITROGEN SLOWLY WHEN YOU
PRESSURIZE THE SHOCK ABSORBER. IF YOU ADD
NITROGEN TOO QUICKLY, THE TEMPERATURE WILL
INCREASE AND HAVE AN EFFECT ON THE SHOCK
ABSORBER PRESSURE.
FILLING
On the bottom charging valve:
- the nitrogen supply being open, open the bottom
charging valve,
- open the control supply valve slowly to add
nitrogen to the bottom chamber, PB = 98 bar
(1420 psi),
- close the bottom charging valve.
Wait ten minutes and make sure that the pressure
condition is fulfilled. The bottom chamber pressure
is still the same, PB = 98 bar (1420 psi).
Check the pressure of the top chamber too:
- slowly open the top charging valve,
- read and record the pressure shown on the
pressure gage, PA = 92 bar (1330 psi),
- and then close it.
As the pressure condition is NOT fulfilled
(PA + 13.8 bar < PB < PA + 20.7 bar), we have to increase
the pressure in the bottom chamber by adding nitrogen.
On the bottom charging valve:
- the bottom charging valve being open, open the
control supply valve slowly to add nitrogen to
the bottom chamber, PB = 112 bar (1620 psi),
- and close the bottom charging valve.
EFFECTIVITY
EFFECTIVITY
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Wait ten minutes and make sure that the pressure
condition between the two chambers is fulfilled,
PA = 92 bar (1330 psi), PB = 112 bar (1620 psi). The
pressure condition is fulfilled.
The nitrogen pressure being released, read and write
down the temperature again, T = 11ºC (52ºF), as well
as the dimension H, H = 123 mm (4.8 in).
Make sure that the difference in pressure at the top
charging valve and the bottom charging valve is more
than 10.7 bar (155 psi),
PB > PA + 10.7 bar,
this condition being enough at this point.
Using DIAGRAM 2, find the dimension HA for the pressure
and the temperature at the top charging valve,
HA = 140 mm (5.5 in) (2).
Dimension H must be the same as HA, ± 1mm (0.6 in).
Depending on whether H, is higher or lower than the
value of HA found on DIAGRAM 2, we have respectively
to remove or add nitrogen from the top chamber.
As H is lower than the value of H found on DIAGRAM 2
we have to add nitrogen to the top chamber.
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
TMULDGA06-T06 LEVEL 3
UFD4200
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER
(cont’d)
To do that:
- open the top charging valve,
- the nitrogen supply being open, slowly open
the control valve to add nitrogen; as soon as
the shock absorber moves, close the control
valve,
- after 5 minutes, measure the temperature,
T = 11ºC (52ºF), and the pressure at the top
charging valve, PA = 92 bar (1330 psi),
- using DIAGRAM 2, find the dimension HA required
for these conditions, HA = 140 mm (5.5 in),
- slowly open the control valve to add nitrogen
to obtain the same dimension H as we found
before, H = HA ± 1mm (0.6 in).
After 5 minutes, open the top and the bottom charging
valves.
Read and write down:
- pressures, PA = 92 bar (1330 psi),
PB = 112 bar (1620 psi),
- the temperature, T = 11ºC (52ºF),
- the dimension H, H = 139 mm (5.5 in).
Using the pressure and the temperature find the correct
dimension H in DIAGRAM 2 and make sure that this value
is equal to the previous measured value, ± 1mm (0.6
in).
Make sure that the difference in pressure at the top
charging valve and the bottom charging valve is still
more than 10.7 bar (155 psi), PB > PA + 10.7 bar.
Close the top and the bottom charging valves.
EFFECTIVITY
EFFECTIVITY
ALL
Now, depending on if the pressure and temperature of
the top charging valve is either, on or below, or above
the graph line on DIAGRAM 3 (3), there are two
possibilities.
In our case, as PA is above the graph line, we have
to carry out the following steps:
- using DIAGRAM 1, find the dimension HA for the
pressure at the top charging valve and the
measured temperature, HA = 119 mm (4.7 in) (4),
- open the bottom charging valve,
- slowly open the control valve to remove
nitrogen and immediately the dimension H starts
to change, close the control valve,
- after 5 minutes, open the top charging valve,
and read and record the pressure, PA = 86 bar
(1250 psi), and the temperature, T = 11ºC
(52ºF),
- using DIAGRAM 1, find the dimension H that you
need for the above conditions, HA = 125 mm (4.9
in) (5),
- slowly open the control valve to remove
nitrogen from the bottom charging valve until
the dimension H is the same as the dimension
H found in DIAGRAM 1, ± 1 mm (0.6 in),
- close the bottom charging valve.
After 5 minutes, check the pressures:
- open the top charging valve, read and write
down the pressure, PA = 86 bar (1250 psi), and
then close it,
- open the bottom charging valve, read and
write down the pressure, PB = 85 bar (1230
psi), and then close it.
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER
(cont’d)
TMULDGA06-T06 LEVEL 3
UFD4200
Make sure that the pressure at the top and bottom
charging valves are the same, ± 1.5 bar (22 psi). If
not, you have to do the procedure again starting from
the step where the floating piston must be moved to
the top of the bottom chamber.
CLOSE-UP
Release the nitrogen pressure.
On the bottom charging valve:
- torque the valve to the preset value,
- remove the charging equipment,
- use SPECIAL MATERIALS to do a leak check of
the valve,
- install the blanking cap.
Remove the thermometer.
On the top charging valve:
- do the same as on the bottom charging valve.
Remove the access platform.
Examine the gland seal of the shock absorber for signs
of oil leaks.
Remove the ground support and maintenance equipment,
the special and standard tools and all other items.
Remove the warning equipment and notices.
Make sure that the work area is clean and clear of
tools and other items.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
MAIN LANDING GEAR SHOCK ABSORBER SERVICING
PRESSURE/EXTENSION GRAPH - VALUES OF THE FILM
Find below the points noticed during the film in their
chronological order.
DIAGRAM 1
(1) PA = 79 bar (1150 psi), T = 10ºC (50ºF)
HA = 141 mm (5.6 in)
(4) PA = 92 bar (1330 psi), T = 11ºC (52ºF)
HA = 119 mm (4.7 in)
(5) PA = 86 bar (1250 psi), T = 11ºC (52ºF)
HA = 125 mm (4.9 in)
DIAGRAM 2
(2) PA = 92 bar (1330 psi), T = 11ºC (52ºF)
HA = 140 mm (5.5 in)
TMULDGA06-T07 LEVEL 3
UFD4200
DIAGRAM 3
(3) PA = 92 bar (1330 psi)
EFFECTIVITY
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UFD4200
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32 LANDING GEAR
PRESSURE/EXTENSION GRAGH - VALUES OF THE FILM
EFFECTIVITY
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TMULDGA06 LEVEL 3
UFD4200
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32 LANDING GEAR
32 - LANDING GEAR
32-43-00 LOW PRESSURE CIRCUIT FILLING AND
BLEEDING
TMULDGM01 LEVEL 3
UFD4200
CONTENTS:
Precautions
Procedure
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
LOW PRESSURE CIRCUIT FILLING AND BLEEDING
PRECAUTIONS
Aircraft configuration: All safety precautions are
fulfilled (Refer to AMM).
PROCEDURE
- Yellow hydraulic circuit and brake accumulator
-
-
-
TMULDGM01-T01 LEVEL 3
UFD4200
-
-
are depressurized.
Use de-aerated hydraulic fluid.
Disconnect hydraulic hoses from the master
cylinders and connect master cylinders to
hydraulic fluid recovery containers with vinyl
tubing.
Open bleeder J, bleeder K remains closed.
Fill the system with the hand pump until the
fluid flows from the vinyl pipe and there are
no air bubbles. Make sure that the supply
pressure is no more than 15 bars (217.6 psi).
Close the bleeder J, open the bleeder K and
carry out the same procedure.
Connect hydraulic hoses to the base of the left
and the right master cylinders.
Connect the vinyl tubing to the reservoir
bleeder (do not unscrew the bleeder).
Open the bleeders J and K of the dual valve
and continue to fill until the fluid which
flows from the reservoir bleeder is free of
air bubbles.
Check that the reservoir is full (indicator
fully extended to the stop position).
EFFECTIVITY
EFFECTIVITY
ALL
- Open the reservoir bleeder to adjust the level
of the fluid in the reservoir to normal (the
piston is level with the green band).
- Close the supply valves of the dual valve.
- Close the bleeders on the dual valve and
reservoir.
- With the yellow hydraulic system
pressurized and the pressure of the green
hydraulic system depressurized push in the
pedals and check that the pressure value
shown on the brake yellow pressure triple
indicator is correct.
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
LOW PRESSURE CIRCUIT FILLING AND BLEEDING
EFFECTIVITY
EFFECTIVITY
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TMULDGM01 LEVEL 3
UFD4200
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EFFECTIVITY
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32 LANDING GEAR
32 - LANDING GEAR
32-41-00 WHEEL AND BRAKE
REMOVAL/INSTALLATION
TMULDVV0B LEVEL 2
UFD4200
CONTENTS:
MLG Wheel and Brake Removal/Installation
NLG Wheel Removal/Installation
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
WHEEL AND BRAKE REMOVAL/INSTALLATION
MLG WHEEL AND BRAKE REMOVAL/INSTALLATION
TMULDVV0B-T01 LEVEL 2
UFD4200
GENERAL
This procedure includes removal/installation
operations of the following components/systems:
- brake fan (optional),
- Tire Pressure Indicating System (optional),
- ABS wheel and brake.
Even if your aircraft is not equipped with one or both
optional systems or this type of wheel and brake, the
procedure remains the same.
PREPARATION
Outside,
- make sure that the landing gear safety devices
are in position,
- as well as the wheel chocks.
In the cockpit,
- open, safety and tag the TPIS and the brake
fans circuit breakers,
- put warning notices on the free fall control
handle and on the landing gear control lever,
- set the parking brake to OFF,
- make sure that the pressure is off and the brake
fan pushbutton is set to off.
Outside again,
- put the jack in position,
- make sure that the dome correctly engages,
- lift the landing gear.
EFFECTIVITY
EFFECTIVITY
ALL
WHEEL REMOVAL
- Fully deflate the tire if it must be changed.
- Remove the guard assembly attached by means of
6 screws.
- Remove the lock wire.
- Insert a tool to lock the impeller and unscrew
the nut.
- Remove the impeller.
- Remove the shroud fixed by 2 screws.
- Disconnect the TPIS sensor connector from the
rotating transformer. Note that the TPIS sensor
must be removed from the wheel if it is changed.
- Remove the "V" clamp and the shroud support.
- Discard the cotterpins, loosen and remove the
2 locking bolts.
- Loosen the wheel nut using the torque adaptor
and remove it.
- Install the propely greased protection tool.
- Using a specific tool, remove the wheel.
BRAKE REMOVAL
- Disconnect the self-sealing couplings.
- Disconnect the brake temperature sensor.
- Using an adaptor, loosen and remove the three
nuts and washers.
- The protective tool being installed on the
axle, remove the wheel.
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32 LANDING GEAR
TMULDVV0B-T01 LEVEL 2
UFD4200
WHEEL AND BRAKE REMOVAL/INSTALLATION
MLG WHEEL AND BRAKE REMOVAL/INSTALLATION (CONTINUED)
- Install the locking nuts with the head of the
BRAKE INSTALLATION
- Remove the protective tool, clean and grease
the axle.
- The protective tool being fitted, install the
brake unit.
- Make sure that the studs engage correctly on
the axle.
- Install the 3 washers and nuts.
- Adjust the torquemeter value and torque the 3
nuts.
- Connect the brake temperature sensor.
- Reconnect the self-sealing couplings.
- Remove the protection devices.
-
WHEEL INSTALLATION
- Make sure that the driving keys on the brake
rotor are correctly aligned.
- The axle protective tool being fitted, install
the wheel with the tool.
- Remove the protection device.
- Install the axle nut.
- Adjust the torque meter to the pre-torque value
and apply it to the nut while turning the wheel.
- Prevent the rotation of the wheel and loosen
the nut.
- Adjust the torque meter to the torque value.
- Torque the axle nut.
- Tighten it until the holes in the nut are
aligned with the holes in the axle.
EFFECTIVITY
EFFECTIVITY
ALL
-
screws facing the axle.
Fit the washers an the nuts.
Tighten the nut.
Safety the locking nuts with splitpins.
Install the shroud support centered by a
centering pin and tighten the "V" clamp.
Reconnect the TPIS sensor plug.
Install the shroud with the 2 srews.
Align the splined driving shaft with the
impeller.
Install the impeller, prevent its rotation and
tighten the nut.
Safety the nut with lockwire.
Install the guard on the tachometer drive
shaft and fit it with the 4 screws.
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32 LANDING GEAR
WHEEL AND BRAKE REMOVAL/INSTALLATION
TMULDVV0B-T01 LEVEL 2
UFD4200
MLG WHEEL AND BRAKE REMOVAL/INSTALLATION (CONTINUED)
CLOSE-UP
- Make sure that the area is clean. Lower the
landing gear, the tire pressure being
previously checked and adjusted.
- Carefully remove the jack from the landing gear
dome.
In the cockpit,
- remove the tags and close the circuit breakers,
- select the ECAM HYDraulic page,
- pressurize the green hydraulic system,
- press the braking pedals.
Outside,
- check the forward coupling for any leakage.
In the cockpit,
- apply the parking brake and check the pressure
on the triple gage indicator.
Outside,
- check the rear coupling for any leakage,
In the cockpit,
- depressurize the hydraulic systems,
- select the ECAM WHEEL page,
- check the brake temperature and tire pressure
for correct indication,
- select the brake fans ON.
Outside,
- check the brake fans for correct operation.
In the cockpit,
- select the brake fans off and remove the
warning notices.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
WHEEL AND BRAKE REMOVAL/INSTALLATION
NLG WHEEL AND BRAKE REMOVAL/INSTALLATION
TMULDVV0B-T01 LEVEL 2
UFD4200
PREPARATION
Outside,
- make sure that the safety locks and wheel chocks
are in position on the landing gear.
In the cockpit,
- open, safety and tag the TPIS circuit breaker,
- put warning notices on the free fall and landing
gear control handles,
- select the parking brake OFF.
Outside again,
- put the jack in position,
- make sure that the dome correctly engages,
- lift the landing gear
- fully deflate the tire.
WHEEL REMOVAL
- Cut and remove the lock wire.
- Remove the 3 srews and washers and remove the
hubcap.
- Remove the grommet and disconnect the TPIS
sensor plug from the rotating transducer. Note
that the sensor has to be removed from the
wheel and refitted on the new wheel.
- Remove and discard the cotterpins.
- Remove the 2 locking nuts.
- Remove the axle nut with the torque adaptor.
- Install the properly greased protection tool.
- Remove the wheel.
- Attach a correctly filled-in label on it.
EFFECTIVITY
EFFECTIVITY
ALL
WHEEL INSTALLATION
- Install the protection tool if removed.
- Correctly grease the axle.
- Install the wheel.
- Remove the protection tool.
- Install the nut.
- Adjust the torque meter to the pre-torque value
and apply it to the nut while turning the wheel.
- Prevent the wheel from rotating and loosen the
nut.
- Adjust the torque meter to the correct value.
- Torque the nut.
- Tighten until the locking bolt holes are
aligned.
- Install the locking bolt with the head of the
screw facing the axle.
- Fit the washers and nuts.
- Safety the locking nuts with split pins.
- Connect the TPIS sensor to the rotating
transducer.
- Re-install the grommet.
- Put the hubcap in position.
- Install the 3 washers and screws.
- Safety the 3 srews with lockwire.
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32 LANDING GEAR
WHEEL AND BRAKE REMOVAL/INSTALLATION
NLG WHEEL AND BRAKE REMOVAL/INSTALLATION (CONTINUED)
TMULDVV0B-T01 LEVEL 2
UFD4200
CLOSE-UP
Outside,
- make sure that the working area is clean,
- lower the gear, the tire pressure being
previously checked and ajusted,
- carefully remove the jack from the dome,
- put the chocks back in position.
In the cockpit,
- remove the tag and close the TPIS circuit
breaker,
- remove the safety warnings,
- select the WHEEL ECAM page,
- check the pressure for correct indication.
EFFECTIVITY
EFFECTIVITY
ALL
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32 LANDING GEAR
32 - LANDING GEAR
32-00-00 CFDS SPECIFIC PAGE PRESENTATION
TMULDGRZZ LEVEL 3
UFD4200
CONTENTS:
LGCIU 1
BSCU A
TPIS
EFFECTIVITY
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32 LANDING GEAR
GENERAL
LGCIU 1
LGCIU 1 and LGCIU 2 have the same functions, thus only
LGCIU 1 is shown on the MCDU.
BSCU A and BSCU B have the same functions, thus only
BSCU A is shown on the MCDU.
The Tire Pressure Indicating System is provided as an
option.
On the SYSTEM REPORT/TEST L/G menu page, the "TPIS"
line is always displayed, even if this system is not
fitted on the aircraft.
LANDING GEAR SIMULATION
The landing gear simulation function is an aid for the
maintenance technicians during trouble shooting and
the maintenance tasks.
With this function it is not necessary to:
- lift the aircraft on jacks (to operate the
proximity sensors on the gear),
- operate the landing gear.
During the simulation of a landing gear configuration
the:
- BITE causes the LGCIU to supply output data
that agrees with the simulated configuration,
- ARINC 429 and discrete signals go to the
applicable interface systems.
Two examples have been chosen:
NOSE LANDING GEAR
- Aircraft position: nose landing gear is
compressed and downlocked.
- Via the MCDU: nose landing gear extended or
uplocked can be simulated.
LH + RH MAIN LANDING GEAR
- Aircraft position: Main gear is compressed and
downlocked.
- Via the MCDU: Main gear extended or uplocked
can be simulated.
TMULDGRZZ-T01 LEVEL 3
UFD4200
CFDS SPECIFIC PAGE PRESENTATION
NOTE: Using the RETURN line key allows the landing
gear system to be reconfigured to the normal
position.
EFFECTIVITY
EFFECTIVITY
ALL
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UFD4200
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - LGCIU 1
EFFECTIVITY
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION
BSCU A
NOTE: STEERING DATA function access is only available
with BSCU standard 8.
PIN-PROG SELECTION
As braking and anti-skid computation depend on tire
diameter, if, for any reason you have to use a
compatible BSCU from another aircraft, some actions
must be done (refer to AMM).
This function is used after removal/installation of
the BSCU. Its purpose is to adapt the BSCU
pin-programming to the aircraft pin-programming.
At the end of menu mode, the system must be set to
"OFF" then to "ON" to be correctly reset using the
A/SKID & N/W STRG switch.
Moreover, the pin-programming modification must also
be performed on the second BSCU system.
Displayed data
- SELV ORDER = selector valve status (OPEN or
CLOSED).
- SSV CURRENT = servovalve current comprised
between -10mA and +10mA.
- STEER ORDER = commanded steering angle.
- CAPT ANGLE = CAPT steering handwheel angle.
- FO
ANGLE = F/O steering handwheel angle.
- PEDAL ANGLE = ELAC angle.
- NWS ANGLE3GC= RVDT COM angle.
- SSV SPOOL
= LVDT spool position comprised
between -0.6 mm and +0.6 mm.
The REFRESH key is used to refresh the values of the
nose wheel steering parameters, as required.
TMULDGRZZ-T02 LEVEL 3
UFD4200
NOTES: The pin-programming reference can be checked
using system 1 and 2 LRU IDENTIFICATION pages.
PIN-PROG SELECTION menu pages can be slightly
different depending on if BSCU standard 7 or
BSCU standard 8 is installed. Whatever your
configuration is, the principle remians the
same.
STEERING DATA
STEERING DATA function displays in real time and clear
language some parameters of the nose wheel steering
system.
This
function
allows
any
possible
malfunctioning of this system to be identified in case
of a non axial roll-out.
EFFECTIVITY
EFFECTIVITY
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - BSCU A
EFFECTIVITY
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION
TPIS
REF PRESSURE
This item displays the values of the landing gear wheel
reference pressures wired at the rear of the computer
by pin programming.
TMULDGRZZ-T03 LEVEL 3
UFD4200
GROUND FAULTS
This mode gives all class 1, 2 and 3 faults that have
occured on the ground with a memory capacity of 3
faults maximum during the last 64 flights.
EFFECTIVITY
EFFECTIVITY
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - TPIS
EFFECTIVITY
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TMULDGRZZ LEVEL 3
UFD4200
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