A320 Chapter 32 Landing Gear
A319/A320/A321 TECHNICAL TRAINING MANUAL MECHANICS / ELECTRICS & AVIONICS COURSE 32 LANDING GEAR This document must be
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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
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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 _ MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
32 LANDING GEAR UFD4200
TABLE OF CONTENTS
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UFD4200
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32 CONTENTS
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A319/A320/A321 TECHNICAL TRAINING MANUAL _ 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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LANDING GEAR GENERAL SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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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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LANDING GEAR GENERAL SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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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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LANDING GEAR GENERAL SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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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
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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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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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LANDING GEAR RETRACTION/EXTENSION PRESENTATION (PRINCIPLE) EFFECTIVITY EFFECTIVITY ALL
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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.
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LANDING GEAR RETRACTION/EXTENSION PRESENTATION (NORMAL RETRACTION) EFFECTIVITY EFFECTIVITY ALL
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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.
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LANDING GEAR RETRACTION/EXTENSION PRESENTATION (NORMAL EXTENSION) EFFECTIVITY EFFECTIVITY ALL
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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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LANDING GEAR RETRACTION/EXTENSION PRESENTATION (FREE FALL EXTENSION) EFFECTIVITY EFFECTIVITY ALL
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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.
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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
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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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LANDING GEAR SYSTEM INDICATIONS EFFECTIVITY EFFECTIVITY ALL
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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.
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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
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LANDING GEAR SYSTEM WARNINGS EFFECTIVITY EFFECTIVITY ALL
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LANDING GEAR SYSTEM WARNINGS EFFECTIVITY EFFECTIVITY ALL
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32 - LANDING GEAR 32-31-00 LANDING GEAR NORMAL OPERATION
TMULDGE03 LEVEL 3
UFD4200
CONTENTS: Extension Retraction Self Examination
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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.
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LANDING GEAR EXTENSION - DOOR OPENING EFFECTIVITY EFFECTIVITY ALL
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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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LANDING GEAR EXTENSION - GEAR DOWN EFFECTIVITY EFFECTIVITY ALL
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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.
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LANDING GEAR EXTENSION - DOOR CLOSING EFFECTIVITY EFFECTIVITY ALL
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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.
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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.
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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
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UFD4200
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32 LANDING GEAR
LANDING GEAR RETRACTION - DOOR CLOSING EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
LANDING GEAR RETRACTION - HYDRAULIC SHUT OFF EFFECTIVITY EFFECTIVITY ALL
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32 LANDING GEAR
SELF EXAMINATION What is the normal retraction A - Door open, gear up, gear up signal. B - Door open, gear up, gear up signal. C - Door open, gear up, door close signal.
sequence? door close, cancel door close, maintain door close, cancel
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
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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
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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
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UFD4200
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32 LANDING GEAR
FREE FALL EXTENSION - INITIAL CONFIGURATION EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT UP TO 1.5 TURNS EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT BETWEEN 1.6 AND 1.8 TURNS EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
FREE FALL EXTENSION - LEVER MOVEMENT BETWEEN 1.9 AND 3 TURNS EFFECTIVITY EFFECTIVITY ALL
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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
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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
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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
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32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - LANDING GEAR CONTROL LEVER EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - MLG AND MLG DOOR SAFETY DEVICES EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
LANDING GEAR SAFETY PRECAUTIONS - NLG AND NLG DOOR SAFETY DEVICES EFFECTIVITY EFFECTIVITY ALL
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32 LANDING GEAR
TMULDGJ02 LEVEL 2
UFD4200
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EFFECTIVITY EFFECTIVITY ALL
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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
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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.
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32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION - MAIN LANDING GEAR DOOR GROUND OPERATION EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
LANDING GEAR DOORS GROUND OPERATION - NOSE LANDING GEAR DOORS GROUND OPERATION EFFECTIVITY EFFECTIVITY ALL
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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
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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
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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
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32 LANDING GEAR
LANDING GEAR AND DOORS GROUND OPENING DESCRIPTION/OPERATION - MAIN DOORS - NOSE DOORS EFFECTIVITY EFFECTIVITY ALL
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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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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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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.
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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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32 LANDING GEAR
LGCIU MONITORING INTERFACES - ARINC AND INDICATOR PANEL EFFECTIVITY EFFECTIVITY ALL
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LGCIU MONITORING INTERFACES - DISCRETE - LANDING GEAR COMPRESSED EFFECTIVITY EFFECTIVITY ALL
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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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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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32 LANDING GEAR
MAIN LANDING GEAR DESCRIPTION - GENERAL EFFECTIVITY EFFECTIVITY ALL
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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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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.
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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
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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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UFD4200
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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
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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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UFD4200
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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
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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.
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NOSE LANDING GEAR DESCRIPTION - LOCKSTAY ASSEMBLY EFFECTIVITY EFFECTIVITY ALL
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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.
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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
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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.
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NOSE LANDING GEAR DOORS DESCRIPTION EFFECTIVITY EFFECTIVITY ALL
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TMULDDI01 LEVEL 2
UFD4200
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32 - LANDING GEAR 32-00-00 LANDING GEAR COMPONENTS
TMULD1I02 LEVEL 2
UFD4200
CONTENTS: NLG Shock Absorber MLG Shock Absorber
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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.
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LANDING GEAR COMPONENTS - NLG SHOCK ABSORBER - CENTERING CAM EFFECTIVITY EFFECTIVITY ALL
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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.
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LANDING GEAR COMPONENTS - MLG SHOCK ABSORBER EFFECTIVITY EFFECTIVITY ALL
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TMULD1I02 LEVEL 2
UFD4200
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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
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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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LANDING GEAR COMPONENTS - LGCIU - PROXIMITY DETECTORS EFFECTIVITY EFFECTIVITY ALL
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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.
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LANDING GEAR COMPONENTS - LANDING GEAR SAFETY VALVE EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
LANDING GEAR COMPONENTS - HYDRAULIC FUSES - SELECTOR VALVE MANIFOLD EFFECTIVITY EFFECTIVITY ALL
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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
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LANDING GEAR COMPONENTS - MLG ACTUATING CYLINDER - MLG UPLOCK BOX EFFECTIVITY EFFECTIVITY ALL
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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
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LANDING GEAR COMPONENTS - MLG DOOR ACTUATING CYLINDER - MLG DOOR UPLOCK BOX EFFECTIVITY EFFECTIVITY ALL
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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
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LANDING GEAR COMPONENTS - NLG ACTUATING CYLINDER - NLG UPLOCK BOX EFFECTIVITY EFFECTIVITY ALL
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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
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LANDING GEAR COMPONENTS - NLG DOOR ACTUATING CYLINDER - NLG DOOR UPLOCK BOX EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
LANDING GEAR COMPONENTS - CUT-OUT VALVE EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
LANDING GEAR COMPONENTS - VENT VALVES EFFECTIVITY EFFECTIVITY ALL
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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).
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32 LANDING GEAR
LANDING GEAR COMPONENTS - DOOR BYPASS VALVES EFFECTIVITY EFFECTIVITY ALL
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TMULD2I01 LEVEL 3
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
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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
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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
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - NORMAL BRAKING BY AUTOBRAKE EFFECTIVITY EFFECTIVITY ALL ALL
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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.
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - MANUAL NORMAL BRAKING EFFECTIVITY EFFECTIVITY ALL ALL
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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.
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - INFLIGHT BRAKING EFFECTIVITY EFFECTIVITY ALL ALL
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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.
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - PARKING BRAKE EFFECTIVITY EFFECTIVITY ALL ALL
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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.
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - ALTERNATE BRAKING WITH ANTI-SKID EFFECTIVITY EFFECTIVITY ALL ALL
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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.
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32 LANDING GEAR
BRAKE SYSTEM PRESENTATION - ALTERNATE BRAKING WITHOUT ANTI-SKID EFFECTIVITY EFFECTIVITY ALL ALL
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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. the parking brake be hydraulically powered ? - Only by yellow high pressure. - Only by the brake accumulator. - Either by yellow high pressure or by the brake accumulator.
TMULDZ101 LEVEL 1
UFD4200
How can A B C
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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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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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32 LANDING GEAR
BRAKE SYSTEM DESCRIPTION EFFECTIVITY EFFECTIVITY ALL
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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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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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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.
EFFECTIVITY EFFECTIVITY ALL
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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32 LANDING GEAR
AUTO BRAKE SYSTEM DESCRIPTION/OPERATION EFFECTIVITY EFFECTIVITY ALL
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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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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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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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SELF EXAMINATION When does A B C -
the BSCU provide anti-skid control? During normal and alternate braking. Only during normal braking. 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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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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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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BRAKE HYDRAULIC SYSTEM OPERATION - NORMAL BRAKING EFFECTIVITY EFFECTIVITY ALL
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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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BRAKE HYDRAULIC SYSTEM OPERATION - ALTERNATE BRAKING WITH ANTI-SKID EFFECTIVITY EFFECTIVITY ALL
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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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BRAKE HYDRAULIC SYSTEM OPERATION - ALTERNATE BRAKING WITHOUT ANTI-SKID EFFECTIVITY EFFECTIVITY ALL
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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.
EFFECTIVITY EFFECTIVITY ALL
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BRAKE HYDRAULIC SYSTEM OPERATION - PARKING BRAKE EFFECTIVITY EFFECTIVITY ALL
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SELF EXAMINATION What is A B C
the purpose of the hydraulic fuses? - To stop the flow in case of leakage. - To shut off the return lines. - 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.
EFFECTIVITY EFFECTIVITY ALL
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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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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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BRAKE TEMPERATURE SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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UFD4200
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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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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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BRAKE COOLING SYSTEM PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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TMULDWW01 LEVEL 1
UFD4200
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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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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.
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WHEEL AND BRAKE ECAM PAGE PRESENTATION EFFECTIVITY EFFECTIVITY ALL
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TMULDA4ZZ LEVEL 1
UFD4200
THIS PAGE INTENTIONALLY LEFT BLANK
EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
WHEEL AND BRAKE SYSTEM WARNINGS EFFECTIVITY EFFECTIVITY ALL
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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)
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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.
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NORMAL BRAKING COMPONENTS - BSCU EFFECTIVITY EFFECTIVITY ALL
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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
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NORMAL BRAKING COMPONENTS - BRAKE SELECTOR VALVE - FILTER EFFECTIVITY EFFECTIVITY ALL
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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.
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NORMAL BRAKING COMPONENTS - AUTOMATIC SELECTOR EFFECTIVITY EFFECTIVITY ALL
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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.
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NORMAL BRAKING COMPONENTS - AUTOMATIC SELECTOR CROSS SECTION EFFECTIVITY EFFECTIVITY ALL
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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.
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NORMAL BRAKING COMPONENTS - THROTTLE VALVE EFFECTIVITY EFFECTIVITY ALL
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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
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NORMAL BRAKING COMPONENTS - MANIFOLD NORMAL BRAKE SERVOVALVES - NORMAL BRAKE SERVOVALVES EFFECTIVITY EFFECTIVITY ALL
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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
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NORMAL BRAKING COMPONENTS - NORMAL BRAKE SERVOVALVES CROSS SECTION EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
NORMAL BRAKING COMPONENTS - PRESSURE TRANSDUCERS - HYDRAULIC FUSES EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BRAKE PEDAL TRANSMITTER UNIT EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
NORMAL BRAKING COMPONENTS - BRAKE BELTS EFFECTIVITY EFFECTIVITY ALL
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TMULDBXZZ LEVEL 3
UFD4200
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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
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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
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32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - HYDRAULIC RESERVOIR - MASTER CYLINDERS EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE DUAL VALVE EFFECTIVITY EFFECTIVITY ALL
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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
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE DUAL VALVE CROSS SECTION EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - MANIFOLD BRAKE ALTERNATE SERVOVALVES EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - ALTERNATE SERVOVALVES EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - BRAKING PRESSURE TRANSDUCERS EFFECTIVITY EFFECTIVITY ALL
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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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UFD4200
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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
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
ALTERNATE BRAKING COMPONENTS - HYDRAULIC PRESSURE TRANSDUCER - RELIEF VALVE EFFECTIVITY EFFECTIVITY ALL
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TMULDDX09 LEVEL 3
UFD4200
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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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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
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32 LANDING GEAR
PARKING BRAKE COMPONENTS - ACCUMULATOR - PRESSURE GAGE - CHARGING VALVE EFFECTIVITY EFFECTIVITY ALL
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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.
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32 LANDING GEAR
PARKING BRAKE COMPONENTS - PARKING BRAKE ELECTRICAL CONTROL VALVE EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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32 LANDING GEAR
PARKING BRAKE COMPONENTS - PARKING BRAKE OPERATED VALVE EFFECTIVITY EFFECTIVITY ALL
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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 ALL
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32 LANDING GEAR
PARKING BRAKE COMPONENTS - DUAL SHUTTLE VALVE EFFECTIVITY EFFECTIVITY ALL
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TMULDEX02 LEVEL 3
UFD4200
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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 EFFECTIVITY ALL
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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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32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - MAIN LANDING GEAR WHEELS EFFECTIVITY EFFECTIVITY ALL
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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 ALL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - CARBON BRAKES EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - BLEED VALVES - WEAR PIN INDICATORS EFFECTIVITY EFFECTIVITY ALL
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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
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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - TACHOMETERS - MLG DRIVE TACHOMETERS - AXLE SLEEVES EFFECTIVITY EFFECTIVITY ALL
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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
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
WHEEL AND BRAKE COMPONENTS - NLG WHEELS - AXLE SLEEVES EFFECTIVITY EFFECTIVITY ALL
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TMULDJX04 LEVEL 3
UFD4200
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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
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32 LANDING GEAR
BRAKE TEMPERATURE SYSTEM COMPONENTS - BTMUs - TEMPERATURE SENSORS EFFECTIVITY EFFECTIVITY ALL
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TMULDIX01 LEVEL 3
UFD4200
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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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32 LANDING GEAR
BRAKE COOLING SYSTEM COMPONENTS - FAN MOTOR - IMPELLER EFFECTIVITY EFFECTIVITY ALL
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TMULDFX01 LEVEL 3
UFD4200
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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
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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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SELF EXAMINATION What is the obtained by A - ± B - ± C - ±
maximum nose wheel steering angle the handwheels? 6°. 74°. 95°.
TMULD1003 LEVEL 1
UFD4200
Is nose wheel steering available after a landing gear gravity extension ? A - Yes. B - No.
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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.
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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.
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SELF EXAMINATION What is A B C
the purpose of the accumulator? - To compensate a complete pressure loss. - To dampen rapid movements. - 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.
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32 - LANDING GEAR 32-42-00 NOSE WHEEL STEERING ECAM PAGE PRESENTATION
TMULDB401 LEVEL 1
UFD4200
CONTENTS: Steering Indication
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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".
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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
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32 - LANDING GEAR 32-51-00 NOSE WHEEL STEERING SYSTEM COMPONENTS
TMULDKX02 LEVEL 2
UFD4200
CONTENTS: Electrical Box
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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.
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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
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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
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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
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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.
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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
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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
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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.
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32 - LANDING GEAR 32-42-00 BRAKING AND STEERING - BSCU ARCHITECTURE AND MONITORING INTERFACES
TMULDGUZZ LEVEL 3
UFD4200
CONTENTS: Architecture Monitoring
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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.
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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.
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TMULD1Q04 LEVEL 1
UFD4200
CONTENTS: Function Description Self Examination
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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).
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SELF EXAMINATION Tire Pressure Indication displayed ? a tire and brake indicator. ECAM. indication.
TMULD1Q04 LEVEL 1
UFD4200
Where is the A - On B - On C - No
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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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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
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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.
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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
EFFECTIVITY EFFECTIVITY ALL
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MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM WARNINGS EFFECTIVITY EFFECTIVITY ALL
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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
EFFECTIVITY EFFECTIVITY ALL
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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.
EFFECTIVITY EFFECTIVITY ALL
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32 LANDING GEAR
TIRE PRESSURE INDICATING SYSTEM COMPONENTS - TIRE PRESSURE INDICATING UNIT EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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32 LANDING GEAR
TPIS COMPONENTS - MLG TRANSMISSION UNIT - MLG PRESSURE TRANSDUCER EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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32 LANDING GEAR
TPIS COMPONENTS - NLG TRANSMISSION UNIT - NLG PRESSURE TRANSDUCER EFFECTIVITY EFFECTIVITY ALL
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TMULDHX04 LEVEL 3
UFD4200
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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 EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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32 LANDING GEAR
MAIN LANDING GEAR SERVICING - SPARE SEAL ACTIVATING VALVE EFFECTIVITY EFFECTIVITY ALL
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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).
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32 LANDING GEAR
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TMULDTT05 LEVEL 3
UFD4200
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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
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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.
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32 LANDING GEAR
GENERAL - TOP CHARGING VALVE - BOTTOM CHARGING VALVE - H MEASUREMENT EFFECTIVITY EFFECTIVITY ALL
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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
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32 LANDING GEAR
SERVICING PROCEDURES EFFECTIVITY EFFECTIVITY ALL
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MAIN LANDING GEAR SHOCK ABSORBER SERVICING SERVICING PROCEDURES
TMULDGA06-T03 LEVEL 3
UFD4200
Nitrogen Filling of the MLG Two-Stage Shock Absorber (metric units)
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32 LANDING GEAR
SERVICING PROCEDURES - NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER (metric units) EFFECTIVITY EFFECTIVITY ALL
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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 ALL
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32 LANDING GEAR
SERVICING PROCEDURES - NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER (US units) EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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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UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
NITROGEN FILLING OF THE MLG TWO-STAGE SHOCK ABSORBER - SHOCK ABSORBER SCHEMATIC EFFECTIVITY EFFECTIVITY ALL
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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 EFFECTIVITY ALL
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 ALL
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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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 HA = 141 mm (4) PA = 92 bar HA = 119 mm (5) PA = 86 bar HA = 125 mm
(1150 psi), T = 10ºC (50ºF) (5.6 in) (1330 psi), T = 11ºC (52ºF) (4.7 in) (1250 psi), T = 11ºC (52ºF) (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)
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32 LANDING GEAR
PRESSURE/EXTENSION GRAGH - VALUES OF THE FILM EFFECTIVITY EFFECTIVITY ALL
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TMULDGA06 LEVEL 3
UFD4200
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32 - LANDING GEAR 32-43-00 LOW PRESSURE CIRCUIT FILLING AND BLEEDING
TMULDGM01 LEVEL 3
UFD4200
CONTENTS: Precautions Procedure
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LOW PRESSURE CIRCUIT FILLING AND BLEEDING PRECAUTIONS Aircraft configuration: All safety precautions are fulfilled (Refer to AMM). PROCEDURE
- Yellow hydraulic circuit and brake accumulator -
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-
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).
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- 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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TMULDGM01-P01 LEVEL 3
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32 LANDING GEAR
LOW PRESSURE CIRCUIT FILLING AND BLEEDING EFFECTIVITY EFFECTIVITY ALL
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UFD4200
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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.
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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
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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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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.
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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
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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.
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TMULDGRZZ-P01 LEVEL 3
UFD4200
MECHANICS / ELECTRICS & AVIONICS COURSE
32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - LGCIU 1 EFFECTIVITY EFFECTIVITY ALL
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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 ALL
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TMULDGRZZ-P02 LEVEL 3
UFD4200
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - BSCU A EFFECTIVITY EFFECTIVITY ALL
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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 ALL
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TMULDGRZZ-P03 LEVEL 3
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32 LANDING GEAR
CFDS SPECIFIC PAGE PRESENTATION - TPIS EFFECTIVITY EFFECTIVITY ALL
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TMULDGRZZ LEVEL 3
UFD4200
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