Airbus 36 A300 A310 Pneumatics

MTT M540000 / R3.3 01AUG01MTT M540000 / R3.3 01AUG01For Training Purposes OnlyFor Training Purposes Only

ATA 36ATA 36A300/A310A300/A310

36-36-11

ATA 36ATA 36PneumaticsPneumatics


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Air Supply System


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•

• Pressurization System without Jet Pump SupplyPressurization System without Jet Pump Supply

A300 / Some A310 Pneumatic System – General Schematic - GE CF6 Engine


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•A310 Pneumatic System - General Schematic - PW JT9D Engines


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Engine Air Bleed - Typical Schematic for GE and PW Engines


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A300 Pneumatic System Electrical Power Supply – Typical Layout


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Bleed Air Supply System – Nacelle and Pylon Component Locations

GE CF6-80C2A5FEngine 1

A 3 0 0 S H O W N


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36-36-88

A310 Pneumatic System - Nacelle and Pylon Component Locations

PW JT9D-7R4 PW JT9D-7R4 Engine 1Engine 1

A310 SHOWN


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A310/A310 Pneumatic System – Air Bleed System Components and Location


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Electronic Rack 90VUElectronic Rack 90VU

ENGINE 2

ENGINE 1

AvionicsAvionicsBayBay

FWDFWD

A300/A310 Pneumatic System Controllers and 103VU Relay Panel - Location


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A300 Air Bleed System Panel Locations – Controls and Indicating


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COMPT TEMP/AIR BLEED Panels 436 / 437 VU

436VU

437VU


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A300/A310 AIR BLEED Panel 436VU – Bleed Valve Indications


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A300/A310 AIR BLEED Panel 436VU – X FEED (Crossfeed) Control and Indicating


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A300/A310 ECAM System – ECAM Control Panel and RH ECAM Display

ECAM CONTROL PANEL

RH ECAM


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A300/A310 RH ECAM Display Unit – AIR BLEED Page


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A300 HP Valve - Manual Override/Visual Position Indicator


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PW JT9-7R4 Engine 1PW JT9-7R4 Engine 1

A310 Pneumatic System High Pressure (HP) Bleed Valve FIN DV225 (DV226)


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JT9D-7R4 EngineJT9D-7R4 Engine

A310 Pneumatic System - High Pressure (HP) Valve - Installation Features


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GE CF6-80C2A5F EngineGE CF6-80C2A5F EngineOne Valve per EngineOne Valve per EngineEngine 1 - FIN A004Engine 1 - FIN A004Engine 2 - FIN B004Engine 2 - FIN B004

*IP - Intermediate Pressure*IP - Intermediate Pressure *IP*IP

A300 Pneumatic System - 8th Stage Check Valve FIN A004 (B004) - Installation


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PW JT9D-7R4 EnginePW JT9D-7R4 EngineTwo Valves per EngineTwo Valves per Engine

Engine 1 - FIN B004Engine 1 - FIN B004Engine 2 - FIN D004Engine 2 - FIN D004

A310 Pneumatic System - 8th Stage Check Valves - Component Installation


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A300 Pneumatic System - Bleed Valve (Pressure Regulating and Shutoff/PRSOV)


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A300 Pneumatic System - Bleed Air Valve FIN DV224 (Eng 1/2) - Component Installation

GE CF6-80C2A5F

ENGINE


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A310 Bleed Air System - Bleed and Pressure Regulator Shutoff Valve - Component Features



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A310 Bleed Air System - Bleed and Pressure Regulator Shutoff Valve - Component Installation


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A310 Bleed Air System - Bleed and Pressure Regulator Shutoff Valve - Lockout and Filters


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A310 - Bleed Air System Overpressure Valve (OPV) - Component Installation

PW JT9D-7R4 Engine


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Engine Bleed Air System - Over Pressure Valve (OPV) - Schematic and Features


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A300/A310 Bleed Air System - Overpressure Valve - Component Installation

GE CF6-80A3 ENGINE ANDGE CF6-80C2A5F ENGINE


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A300 Bleed Air System - Fan Air Valve (FAV) FIN 51HA (52HA) - Component ValveIdentification Names


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Ambient Air to PrecoolerAmbient Air to Precooler(Heat Exchanger)(Heat Exchanger)

NOTE:NOTE:FAV - On AircraftFAV - On Aircraft

N650FE to N653FEN650FE to N653FE

A300 Bleed Air System - Fan Air Valve (FAV) - Component Features

GE CF6-80C2A5F ENGINE


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A300 Bleed Air System - Fan Air Valve (FAV) - Mechanical Lockout and Test Port



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FAV Air FilterFAV Air FilterFAV Engine 1 - FIN 51 HAFAV Engine 1 - FIN 51 HAFAV Engine 2 - FIN 52 HAFAV Engine 2 - FIN 52 HA

A300 Engine Bleed Air System - Fan Air Valve (FAV) - Filter Element



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AircraftAircraftConfiguration 01Configuration 01

A310 Fan Air Valve (FAV) FIN 51HA (52HA) - General View



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PlugPlug

GasketGasket

SpringSpring

FilterFilter

A310 Bleed Air System - Fan Air Valve (FAV) - Air Filter Element

Aircraft Configuration 02Aircraft Configuration 02

PW JT9D-7R4 Engine


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A300/A310 Bleed Air System - Cooling Air Inlet Duct to Precooler Base Unit

NOTE

COOLING AIR EXTRACTED

FROM FAN AIR STREAMTO THE FAN AIR VALVE(FAV) IS DUCTED TO THEPRECOOLER BASE UNIT.

COOL FAN AIR ISDIRECTED THROUGH THEBLEED AIR SYSTEMPRECOOLER UNIT FORCOOLING HOT BLEED AIRFOR PNEUMATIC USERS.

THE USED COOLING AIR ISDIRECTED OVER BOARDON TOP OF THE PYLONASSEMBLY TO LOUVEREDPANEL ASSEMBLY.


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A300/A310 Pneumatic Bleed Air System Precooler - Component Installation


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Regulator PressureRegulator Pressure Sensor Sensor

High StageHigh StagePressure SensorPressure Sensor

A300/A310 Pneumatic System - Sensors - Component Location


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A300/A310 Wing-to-Pylon Connection - Component Installation and Sensors

PRECOOLER TEMPERATURECONTROL SENSOR

FIN 53HA (54HA)

PRECOOLER OUTLETTEMPERATURE SENSOR

FIN 4HX (5HX)


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A300/A310 Pneumatic System - Pressure Sensors - Pylon Location

RegulatorRegulator Pressure Sensor Pressure SensorFIN 49HA (50HA)FIN 49HA (50HA)

UPPER UNITUPPER UNIT

A300 SHOWN

High StageHigh StagePressure SensorPressure SensorFIN 47HA (48HA)FIN 47HA (48HA)

LOWER UNITLOWER UNIT


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RegulatorRegulatorPressure SensorPressure Sensor

High StageHigh StagePressure SensorPressure Sensor

PRECOOLER OUTLETTEMPERATURE SENSOR4HX (5HX)

A310 Pneumatic System - Pressure Sensors - Installation of Sensors


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Warning Logic - Engine Bleed Air WarningWarning Logic - Engine Bleed Air WarningDepicted below are various warnings displayed in the Flight Deck in the event a fault occurs in the aircraft pneumaticDepicted below are various warnings displayed in the Flight Deck in the event a fault occurs in the aircraft pneumaticsystem. Also graphically shown are the various flight phases at which warnings will or will not be shown.system. Also graphically shown are the various flight phases at which warnings will or will not be shown.

Warning Logic - JT9D Engine Bleed Air System


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WLDPWLDP

A310 PW JT9D-7R4 Engine Bleed Air Warning Logic - Configuration 01


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Warning Logic - Engine Bleed Air WarningWarning Logic - Engine Bleed Air WarningDepicted below are various warnings displayed in the Flight Deck in the event a fault occurs in the aircraft pneumaticDepicted below are various warnings displayed in the Flight Deck in the event a fault occurs in the aircraft pneumaticsystem. Also graphically shown are the various flight phases at which warnings will or will not be shown.system. Also graphically shown are the various flight phases at which warnings will or will not be shown.


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A310 PW JT9D-7R4 Engine Bleed Air Warning Logic - Configuration 01

WLDPWLDP


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FWDFWD

GE CF6-80C2A5F EngineGE CF6-80C2A5F Engine

FIN T603 -FIN T603 -Engine 1/2Engine 1/2

FADECFADEC

A300 Pneumatic System - High Stage Temperature Sensor (T3) - Component Location


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A310 Pneumatic System - High Stage Temperature Sensor - Component Installation

PW JT9D-7R4 ENGINEPW JT9D-7R4 ENGINE


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A300 BLEED AIR SYSTEM - 14th Stage Manifold - Component Installation

GE CF6-80C2A5F ENGINEENGINE NUMBER 1


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A300 BLEED AIR SYSTEM - 8th Stage Manifold - Component Installation



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To Left Hand side ofTo Left Hand side ofEngine to PRSOVEngine to PRSOV

(Bleed Valve(Bleed Valve))

A310 BLEED AIR SYSTEM- Low Pressure Bleed Air Check Valve and Duct Assembly Component Installation

PW JT9D-7R4 ENGINE


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From 8 th StageEngine Port(RH Side of

Engine)

To Precooler(Heat Exchanger)

Air Flow

StarterAir Duct

AirFlow

PS4 Air

PS4 Air

15th Stage(PS4 Air) Air

Flow In

**8th StageAir Flow In

*Bleed Air Port forHydraulic ReservoirSystem- Engine 1 only- Engine 2 Plug inserted in port hole.

A310 BLEED AIR SYSTEM - 8th and 15th Stage Collector Duct Assembly - Component Installation

PW JT9D-7R4 ENGINE


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A310 BLEED AIR SYSTEM - Left 8th Stage Low Pressure Bleed and Duct AssemblyComponent Installation

PW JT9D-7R4 ENGINE


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88thth/15/15thth

Stage AirStage AirFlow OutFlow Out

Air Flow to PrecoolerAir Flow to Precooler

Air Flow OutAir Flow Out

A310 BLEED AIR SYSTEM - Bleed Air Pressure Regulator Valve Outlet Duct AssemblyComponent Installation

PW JT9D-7R4 ENGINE

PRSOV

PRSOV = PRESSUREREGULATING SHUT OFF

VALVE


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DiffuserDiffuserSectionSection

**PS4 AirPS4 AirFlow OutFlow Out

**

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**

A310 BLEED AIR SYSTEM - 15th State High Pressure Manifold - Component Installation

PW JT9D-7R4 ENGINE


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A300/A310 Pneumatic Bleed Air Duct - Clamp Location and Features (Typical)

WING FRONT SPAR AREA


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A300/A310 Bleed Air Duct - Clamp Installation and Duct Alignment


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Some A310 Pneumatic System Controller / GE CF6-80A3 and PWJT9D-7R4 Engines - (Front Face Labels - BITE Check)

FIN 41HA (42HA)FIN 41HA (42HA


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A300 / Some A310 Pneumatic System Controller - Front Face

FIN 41HA (42HA)


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or PW Engineor PW Engine

A300 / Some A310 Pneumatic Controller - Initiated Built-In-Test Flow Diagram

FIN 41HA (42HA)


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A300 / Some A310 Pneumatic Controller - Initiated Built-In-Test Flow Diagram 1

FIN 41HA (42HA)


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A300/A310 APU Bleed Air System - Flight Deck Controls and Indications

AIR BLEED PANEL 436VU


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A300/A310 APU Bleed Air System - Component Location in Fuselage


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Only on some A310s

A300/A310 Pneumatic System – High Pressure (HP) Ground Connectors – Component Location

A310 SHOWN


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A300/A310 APU Bleed Air and Crossfeed - Schematic


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A300/A310 Bleed Air System – Crossfeed (X-FEED) Valve FIN 16HV – Component Location


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A300/A310 Bleed Air System – Crossfeed Valve (X-FEED) FIN 16HV – Component Installation


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Located in Bulk CargoLocated in Bulk CargoBay Area – Above andBay Area – Above andAft of Bulk Cargo DoorAft of Bulk Cargo Door

A300/A310 APU Bleed Air – Component Location in Fuselage

APU ECB UNIT


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A300/A310 APU Bleed Air System – Bleed (Load Control) Valve FIN 66KD - General Features


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A300 / Some A310 APU Bleed Air System – Check Valve FIN 360022 – Component Installation

NOTESOME A310 HAVE SIX

(PIE CUT SHAPE) FLAPPER TYPECHECK VALVE COMPONENT UNITS

WITH SPRINGS TO RESEAT FLAPPERUNDER NO PNEUMATIC LOAD

CONDITIONS

DOUBLE FLAPPERTYPE CHECK

VALVE


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NACA = National Advisory Committee ofNACA = National Advisory Committee ofAeronautics U. S. A.Aeronautics U. S. A.

- Now NASA Since 1958.- Now NASA Since 1958.

A300/A310 Wing Leading Edge Air Cooling Area (Slat Number 1 Area)- General Features


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A300/A310 Pneumatic System - Overheat Detection Controllers - Component Location


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A300/Some A310s Maintenance Panel 472VU - AIR BLEED & COMPT TEMP Test Panel


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A300/A310 Air Bleed - Monitoring and Bleed Fault Test - Flight Deck Configurations

MAINTENANCE PANEL 471VU


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A300/A310 Air Bleed System - Manifold Air Leak Test Panel



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A300/A310 Pneumatic System - Control and Indicating - Location

COMPT TEMP PANEL 437VU


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A300/A310 Pneumatic System - Bleed Air Pressure Indication - Overhead Panel 437VU

COMPT TEMP PANEL 437VU


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A300/A310 PRECOOLER OUTLET TEMP - SCHEMATIC



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A300/A310 Manifold Air Leak Detection - Controls and Indications - Location


90VU ELECTRONIC RACK


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A300/A310 Pneumatic System - Overheat Detection Controller FIN 12HF/13HF - Location

90VU ELECTRONIC RACK


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A300/A310 Manifold Air Leak Detection - Detection Loops Layout


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A300/A310 GE/PW Engine Pylon Overheat Detection - Component Location

ENGINE 1 PYLON - INBRD SIDE

ENGINE 2 PYLON - OUTBRD SIDE

204 DEGREES C

SINGLE LOOP


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A300/A310 Wing Overheat Detection - Loop Sections Layout

A300 SHOWN

ALL AREAS SHOWN -124 DEGREES C

DOUBLE LOOPS


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A300/A310 Pneumatic System - Overheat Sensing Elements - Location in Fuselage

A310 SHOWN

ALL AREAS SHOWN - 124 DEGREES C

DOUBLE LOOPS


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A300/A310 Aft Fuselage Overheat Detection - Overheat Sensing Elements

154 DEGREE CSINGLE LOOP

124 DEGREE C SINGLE LOOP


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A300/A310 Manifold Air Leak Detection - Ambient Overheat Detection Loop

GROMMET


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NOTENOTESome A310 have Master Caution Lights and other A310 haveSome A310 have Master Caution Lights and other A310 have

WLDP (WARNING LIGHT DISPLAY PANEL)WLDP (WARNING LIGHT DISPLAY PANEL)

A300/A310 Pneumatic System - Manifold Leak Detection - Schematic


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GE CF6-80C2A5F (FADEC Engine)GE CF6-80C2A5F (FADEC Engine)

A300/A310 Engine Bleed System - Troubleshooting Guidelines and Information


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A300/A310 Engine Bleed System - Troubleshooting Guidelines and Information


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A300 Engine Bleed Air System - Troubleshooting Guidelines and Component Location


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A310 Bleed Air Pneumatic Controller FIN 41HA (42HA) - BITE Test


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A300/A310 Bleed Air Pneumatic Controller FIN 41HA (42HA) - BITE Sequence


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Warning Logic - Pneumatic System

Depicted below are various warnings displayed in the flight deck in the event a fault occurs in theaircraft Pneumatic System. Also graphically shown are the various Flight Phases at which warningswill or will not be shown.


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Warning Logic - Pneumatic System


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THIS PAGE INTENTIONALLY

LEFT BLANK

ATA 36 - END

COURSE CODE - M450000

Airbus 36 A300 A310 Pneumatics

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