36-PNEUMATIC

A319/A320/A321 TECHNICAL TRAINING MANUAL MECHANICS / ELECTRICS & AVIONICS COURSE 36 PNEUMATIC SYSTEM

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 TRAINING MANUAL MECHANICS / ELECTRICS & AVIONICS COURSE

36 PNEUMATIC SYSTEM

36 PNEUMATIC SYSTEM UFD4200

TABLE OF CONTENTS

Page

System Presentation (1) .......................... 1 System Controls Presentation (1) ................. 7 ECAM Page Presentation (1) ...................... 11 ** Engine Bleed System Description (3) ......... 15 Pneumatic System Warnings (3) ................... 23 APU Bleed Air SPLY/X-Bleed System (3) .......... 27 ** BMC Interfaces (3) ............................ 31 ** Pneumatic Leak Detection System D/O (3) ..... 37 Engine Bleed Air Supply Components (3) ......... 47 ** GND & APU Bleed Air Supply Components (3) ... 61 Leak Detection Components (3) ................... 75

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36 - PNEU PNEUMA MATI TIC C 36-00-0 36-0 0-00 0 SYS SYSTEM TEM PRES PRESENT ENTATI ATION ON CONTENTS: Sources Engine Bleed Air Supply Engine Bleed Valve Overpressure Valve Precooler APU Bleed Ground Air Supply Cross Bleed Valve Leak detection Monitoring Users Self Examination

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SYSTEM PRESENTATION SOURCES

OVERPRESSURE VALVE

The Bleed Air system can be supplied by four different different sources: the engines, the APU and ground cart. APU bleed air supply has priority over engine bleed air supply. On ground, the system may be supplied by a ground cart.

The overpressure valve is positioned downstream downstream of the engine bleed valve to protect the system. The Overpressure valve is pneumatically operated and springloaded open. PRECOOLER

ENGINE BLEED AIR SUPPLY The engine bleed air system system is supplied by one of the two different engine compressor stages: the Intermediate Pressure stage stage or the High Pressure stage. The Intermediate Pressure Pressure (IP) stage is normally used. When the IP pressure is too low (low engine speed), the HP valve pneumatically opens and regulates at 36 psi. The valve is used to connect the HP stage to the engine bleed air system. Note: This valve valve is springload springloaded ed closed closed in the absence absence of upstream pressure. ENGINE BLEED VALVE

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The precooler is a heat exchanger downstream of the engine bleed valve, used to cool the bleed air. A fan air valve regulates the cold air flow flow to the precooler for bleed air temperature control. The Fan Air Valve allows the bleed air temperature to be maintained at 200ºC. It is springloaded closed in the absence of air pressure. APU BLEED The APU bleed air passes through the APU bleed valve which is pneumatically operated and electrically controlled (GARRET) or fuel operated and electrically controlled (APIC). When open, the APU bleed valve has priority over the engine bleed valves, which are automatically controlled to close.

The HP or IP air passes through the engine bleed valve which operates as a pressure regulating and shut-off valve. The Engine Bleed Valve operates pneumatically and regulates the downstream pressure to 44 psi. It is springloaded closed in the absence of upstream pressure.

Note: The APU valve is is springloaded springloaded closed in the absence of air pressure (GARRET) or fuel pressure (APIC).

Note: The closure closure of the the Engine Bleed Valve Valve causes the HP valve to close.

The bleed air system can be supplied by the ground cart.


GROUND AIR SUPPLY

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SYSTEM PRESENTATION CROSS BLEED VALVE

MONITORING

The cross bleed valve, installed in the cross feed line, allows the left and right bleed systems to be interconnected or isolated. The cross bleed valve is electrically controlled by two independent electrical motors. In auto mode, it is controlled to the same position as the APU bleed valve. In manual mode, it is controlled independently independently of APU bleed valve.

Engine bleed pressure, temperature and leak detection are monitored by two bleed monitoring computers:

- In normal configuration, computer 1 monitors the left bleed system and computer computer 2 the right bleed system.

- If one Bleed Monitoring Computer fails, the remaining BMC is able to monitor both bleed systems (except for Pylon leak and APU leak detection).

LEAK DETECTION USERS A leak detection system is provided to detect overheat overheat in the vicinity of hot air ducts, in the pylons, wings and fuselage. The leak detection system monitors the following zones:

- Wing and packs: ensured by a double loop of sensing elements. The left loops also monitor bleed ducts up to cross bleed valve and APU check valve. The right loops also monitor bleed ducts ducts up to cross bleed valve.

- Pylons: ensured by a single loop with one sensing element.

The pneumatic system different users. The users are:

-

supplies

pressurized

air

to

the engine start system, the wing ant-ice system, the air conditioning pack, the water tank pressurization,

and

hydraulic

reservoir

- the AFT cargo heating (Optional), - the nacelle anti-ice valve (CFM only).

- APU bleed duct (from APU bleed valve to check 1 L E V E L

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valve): ensured by a single loop of sensing elements.

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SELF EXAMINATION Does the APU bleed valve opening have priority over the engine bleed valves opening ? A - YES. B - NO.

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36 - PNEU PNEUMA MATI TIC C 36-00-0 36-0 0-00 0 SYS SYSTEM TEM CONTROL CONTROLS S PRESENTAT PRESENTATION ION CONTENTS: Engine Bleed Valve Pushbutton APU Bleed Valve Pushbutton Cross Bleed Valve Selector

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SYSTEM CONTROLS PRESENTATION ENGINE BLEED VALVE PUSHBUTTON

CROSS BLEED VALVE SELECTOR

When pressed in, the related engine bleed valve valve opens, provided the engine is running, the APU bleed not ON and no fault is detected (by its Bleed Monitoring Computer). When released out, the related related bleed valve and HP valve are closed. The HP valve opens if the bleed bleed pressure is less than 36 psi.

In AUTO, the cross bleed valve takes configuration as the APU bleed valve (closed (closed When OPEN is selected, the cross bleed controlled to open. When SHUT is selected, the cross bleed controlled to close.

the same or open). valve is valve

is

NOTE: If SHUT is is selected selected and the APU bleed bleed valve valve is open, only engine 2 bleed valve is open.

APU BLEED VALVE PUSHBUTTON When pressed in, the APU bleed valve opens provided the APU is running and no leak is detected by BMC1. When released out, the APU bleed valve is closed. NOTE: When the APU bleed bleed valve is open, open, the X bleed valve is open and both engine bleed valves are closed, provided X bleed valve selector at AUTO.

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36 - PNE PNEUM UMAT ATIC IC 36-20-0 36-2 0-00 0 ECA ECAM M PAGE PAGE PRESEN PRESENTAT TATION ION CONTENTS: Sources Engine and APU Bleed Valves Engine HP Valve Cross Bleed Valve Ducts Bleed Air Parameters

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ECAM PAGE PRESENTATION SOURCES

DUCTS

Engine symbol 1 or 2 is amber when the corresponding engine is stopped. It becomes white when engine is running. The green ground symbol and the white GND indication are displayed when the aircraft is on ground, independently of ground cart connection. The white HP, IP and APU indications are always displayed.

The ducts are represented by green lines when corresponding valves valves are open, and become amber or are not displayed when the valves are closed.

ENGINE AND APU BLEED VALVES Green is used when the engine bleed valve position corresponds to the required position, and amber in case of disagreement. The APU bleed bleed valve is green in line when open, and green cross line when closed. The engine bleed valve symbol is replaced by XX when information is not valid. The APU bleed valve is displayed when APU is running; it is not displayed when APU MASTER SW is set to OFF.

BLEED AIR PARAMETERS PARAMETERS Bleed temperature and pressure are shown in the shaded boxes; they are green when normal, amber when out of limits. Bleed pressure parameter becomes amber if lower than 4 psi or in case of overpressure detected by BMC (above 57 psi). Temperature parameter becomes amber in case of overheat detection by BMC. Overheat is detected if temperature exceeds:

- 290°C for more than 5 sec or, - 270°C for more than 15 sec or, - 257°C for more than 55 sec.

ENGINE HP VALVE

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The engine HP VALVE is displayed cross line when closed, and in line when open. Green is used when HP valve position corresponds to the required position, and amber in case of disagreement. The engine HP valve symbol is replaced by XX when HP valve information is not valid CROSS BLEED VALVE The cross-bleed valve is displayed in line when open, and cross line when closed.


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36 - PNEU PNEUMA MATI TIC C 36-10-0 36-1 0-00 0 ENG ENGINE INE BLEED BLEED SYSTEM SYSTEM DESCRIPT DESCRIPTION ION CONTENTS: General HPV HPV IPC IPC PRV/CTS OPV OPV Pr Pt FAV/CT Precooler Heat Exchanger Outlet Temperature Sensor (T) Self Examination

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ENGINE BLEED SYSTEM DESCRIPTION GENERAL

IPC IPC

The engine air bleed pressure is pneumatically regulated by the High Pressure Valve (HPV) when air is supplied by the HP stage or by the Pressure Regulating Valve (PRV) (PRV) when the air is supplied by the IP stage. The pressure regulation system is monitored by two BMCs.

The Intermediate Pressure Pressure Check Valve protects the IP stage from reverse flow when the High Pressure Valve is open.

HPV HPV The switching between Intermediate Pressure (IP) and High Pressure (HP) is achieved pneumatically pneumatically when the IP stage pressure is not sufficient. The HPV pneumatically regulates the air supply between 8 to 36 psi. The HPV is forced closed when the PRV is closed via the PRV/HPV sense line. In flight, the EEC (Engine Electronic Controller) maintains the HPV closed. It vents the HPV-PRV sense line when :

-

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engine is above idle (PS3 > 110 110 PSI) Wing Anti-Ice OFF Altitude over 15000 ft

Normal pack configuration. When one of the four conditions conditions is no longer met, the solenoid is de-energized and the opening of the HPV is no longer inhibited.


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ENGINE BLEED SYSTEM DESCRIPTION


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ENGINE BLEED SYSTEM DESCRIPTION PRV/CTS The PRV pneumatically regulates the bleed pressure around 44 psi. A thermal fuse causes the valve to close in case of engine fire (450°C). The PRV is pneumatically controlled by an external servo-control, the Bleed Pressure Regulated Valve Control Solenoid (CTS), located downstream from the precooler. The CTS operates in two modes, pneumatically and electrically, causing a partial or complete closure of the PRV. Pneumatic mode:

The solenoid is automatically energized by the BMC in the following cases:

- Overtemperature downstream of the precooler (the heat exchanger outlet temperature sensor T senses a temperature above 257°C.

- Overpressure

downstream of the PRV (the pressure regulated transducer Pt senses a pressure greater than 57 psi).

- Leak detection in pylon/wing/fuselage ducts surrounding areas.

- APU bleed valve not closed. Corresponding starter valve not closed. - Corresponding

- Temperature

limitation downstream of the precooler by means of the CTS thermostat. When the temperature increases and reaches 235°C, the PRV downstream pressure is progressively reduced up to 17,5 psi when the temperature gets higher than 245°C. Reverse flow protection by closing the PRV when a ∆P between the precooler outlet and the PRV inlet is detected. Electrical mode: (PRV shut-off function through the CTS solenoid energization) 3 L E V E L

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- Eng. Bleed P/B selected "OFF". - Eng. Fire P/B selected on.

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ENGINE BLEED SYSTEM DESCRIPTION


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ENGINE BLEED SYSTEM DESCRIPTION OPV OPV

PRECOOLER

The OverPressure Valve (OPV), normally open, pneumatically closes. The OPV starts to close at 75 psi. It is fully closed at 85 psi and opens again at 35 psi.

The precooler is an air to air heat exchanger.

Pr A transducer, connected to the Bleed Monitoring Computer, reads the regulated pressure downstream from the PRV. This pressure is indicated on the ECAM.

HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T) The Heat Exchanger Outlet Temperature Sensor, connected to both Bleed Monitoring Computers, reads the regulated temperature downstream from the precooler. This temperature is indicated indicated on the ECAM and used to monitor the system.

Pt A transducer, connected to the Bleed Monitoring Computer, reads the transferred pressure downstream from the HPV. This pressure is used to monitor PRV and HPV. FAV/CT

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The Fan Air Valve (FAV) pneumatically regulates the fan air flow to the precooler for bleed air temperature temperature regulation (200°C). The FAV is pneumatically controlled by an external servo-control: the Fan Air Valve Control Thermostat (CT), located downstream from the precooler. A thermal fuse installed in the valve body closes the valve if a temperature of 450°C is reached.


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SELF EXAMINATION What is the purpose of IP/HP switching ? A - To regulate the output pressure, depending on Fan Air Valve position. B - To keep air bleed at a sufficient pressure at low engine speed. C - To regulate the output temperature, depending on the configuration of users. What is the purpose of the CTS ? A - To send a pneumatic signal to the OPV, in case of overpressure. B - To send a pneumatic signal to regulate or shut-off the PRV. What is the purpose of the CT ? A - To send a pneumatic signal to control the FAV. B - To send a pneumatic signal to the OPV in case of overpressure. C - To send a pneumatic signal to control the PRV.

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36 - PNEU PNEUMA MATI TIC C 36-20-0 36-2 0-00 0 PNE PNEUMA UMATIC TIC SYSTEM SYSTEM WARNI WARNINGS NGS CONTENTS: Engine 1 (2) Bleed Abnormal Pressure Engine 1 (2) Bleed Low Temperature X Bleed Fault Engine 1 (2) HP Valve Fault Bleed Monitoring Fault Left (Right) Wing Leak Detection Fault Eng 1 (2) Bleed Fault Left (Right) Wing Leak Engine 1 (2) Bleed Leak Engine 1 (2) Bleed not closed Bleed 1 (2) OFF APU Bleed Fault APU Bleed Leak.

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36 - PNEU PNEUMA MATI TIC C SYST SYSTEM EM 36-12-0 36-1 2-00 0 APU BLEED BLEED AIR AIR SUPPLY SUPPLY / X-BLEE X-BLEED D SYSTEM CONTENTS: APU Bleed X-Bleed System HP Ground Connection Self Examination

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APU BLEED AIR SUPPLY / X-BLEED SYSTEM APU BLEED The pneumatic system can be supplied supplied by APU bleed air through the APU bleed valve provided the APU is running.

The position of the valve is controlled controlled by the X-BLEED selector (SHUT or OPEN) on the overhead panel. It is operated by two electrical motors:

- the primary motor is used for AUTO mode, controlled by the - the position of the valve is controlled BMC according to APU bleed configuration,

The APU bleed valve (GARRET) is electrically controlled and pneumatically operated by a Solenoid. It is springloaded closed in absence of air pressure. NOTE: NOTE : Thi This s valve valve is of the the ON/OFF ON/OFF type. type. The APU bleed valve (APIC) is electrically controlled controlled and fuel operated by a ServoValve. The ECB monitors the fuel muscle pressure which which closes or opens the APU bleed valve. X-BLEED SYSTEM The X-BLEED valve permits the isolation or interconnection of the left and right bleed systems. OPEN Manual control is used for:

- the secondary motor is used to override the AUTO mode. HP GROUND CONNECTION The pneumatic system may be supplied supplied by a ground cart. The supply duct is located to the left of the cross bleed valve. Only the left-hand bleed system is supplied. When the X-BLEED selector is in the OPEN position, position, the ground air supply will be available to start ENG2.

the air

- cross supply of the packs, - engine crossbleed start (on ground only), - engine bleed air failure in icing conditions for wing anti-ice supply, 3 L E V E L

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- ENG2 start from ground cart supply. SHUT Manual control is used for closure of the valve. The X-Bleed valve is an electrically controlled shut-off valve.


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APU BLEED AIR SUPPLY / X-BLEED SYSTEM - APU BLEED


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SELF EXAMINATION With the X-BLEED selector at AUTO and air supplied by ENG1 ONLY, the X-BLEED valve : A - Does not receive any order. B - Is automatically controlled to open. C - Is controlled to close. How does the GARRET APU Bleed valve operate ? A - As a regulating valve. B - As an ON/OFF valve. C - A and B. How does the APIC APU Bleed valve operate ? A - Pneumatically. B - Fuel operated

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36 - PNEU PNEUMA MATI TIC C 36-11 3611-3 -34 4 BMC BMC INTERFA INTERFACE CES S CONTENTS: Inputs Outputs

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BMC INTERFACES INPUTS Each Bleed Monitoring Computer has three types of inputs:

- DIGITAL INPUTS via ARINC 429 buses, from opposite BMC, corresponding EIU and CFDIU.

- ANALOG INPUTS from the bleed sensors. - DISCRETE INPUTS from valve position switches, BMC and overhead panel. 28 Volts Direct Current power is supplied for energization of the Bleed Pressure Regulated Valve Control Solenoid (CTS).

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BMC INTERFACES OUTPUTS Each Bleed outputs:

Monitoring

Computer

has

two

types

of

- DIGITAL OUTPUTS via ARINC 429 buses to the SDACs (for ECAM warnings and indications), the CFDIUs (for maintenance purposes), and the opposite BMC (for bleed monitoring purposes).

- DISCRETE OUTPUTS to APU Electronic Control Box for APU availability, to overhead panel for bleed faults, to Cross Bleed Valve, CTS and Zone Controller. NOTE: In case of BMC failure, failure, the monit monitoring oring of main parameters (HPV and PRV, Heat Exchanger Outlet Temperature Sensor, Pr) is kept, but the automatic control of the PRV is lost.

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36 - LEAK LEAK D DET ETEC ECTI TION ON 36-22 3622-0 -00 0 LEAK LEAK DETECT DETECTIO ION N CONTENTS: Routing Warning Logic Fault Logic Leak Consequence Self Examination

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LEAK DETECTION ROUTING The leak detection system is used to detect leaks in the vicinity of the packs, wings, pylons and APU hot air ducts. Each wing is monitored by a double loop. The pylon and APU hot air ducts are monitored by a single loop. A continuous monitoring system detects ambient overheat in the vicinity of the hot air ducts. Protected areas: Double loop for:

- RH wing and pack 2 - LH wing, pack 1 and mid fuselage APU duct. Single loop for:

- LH and RH pylons - Aft fuselage APU duct NOTE: Each loop loop consists consists of sensing elements connected in series.

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LEAK DETECTION - ROUTING


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LEAK DETECTION WARNING LOGIC Both Bleed Monitoring Computers receive signals from the leak detection loops. They exchange data via ARINC bus for the wing double loop detection. NOTE: NOTE : The wing wing loops loops A are connected connected to Bleed Bleed Monitoring Computer 1 (BMC 1) and wing loops B to BMC 2. The crosstalk bus allows wing leak warnings to be activated through an AND logic. The APU loop is connected to BMC 1 only. The pylon loop is connected to the related related BMC.

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LEAK DETECTION - WARNING LOGIC


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LEAK DETECTION FAULT LOGIC The engine bleed fault light comes on when a leak is detected by the wing loops A and B or by the pylon loop. The APU bleed fault light comes on when an APU duct leak is detected. If one BMC is failed, the adjacent BMC takes over monitoring of the bleed system and ensures the following ECAM warnings:

- overpress - overtemp - wing leak Nevertheless the associated FAULT light on the AIR COND panel is lost, and the associated BLEED VALVE does not close automatically. ENG BLEED LEAK warning is lost for the associated engine as well as APU BLEED LEAK warning if BMC 1 is failed.

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LEAK DETECTION - FAULT LOGIC


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LEAK DETECTION LEAK CONSEQUENCE A detected leak will close associated valves, valves, as shown on this table. These valves are automatically automatically controlled to close if they were open. NOTE: APU and X Bleed valves do not close during Main Main Engine Start.

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LEAK DETECTION - LEAK CONSEQUENCE


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SELF EXAMINATION Which of the following are maintained by a double loop detection system ? A - The LH and RH wing ducts, packs and mid fuselage APU duct. B - The pylon. C - A and B. What happens in case of BMC 1 failure ? A - BMC 2 ensures the complete leak detection. B - BMC 2 ensures its wing leak detection. C - The leak detection is completely lost.

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36 - PNEU PNEUMA MATI TIC C SYST SYSTEM EM 36-11-0 36-1 1-00 0 ENGINE ENGINE BLEED BLEED AIR SUPP SUPPLY LY COMPONENTS CONTENTS: High Pressure Valve (HPV) HPV Closure Control Solenoid Solenoid Pressure Regulating Valve (PRV) Bleed Pressure Regulated Valve Control Solenoid (CTS) Precooler Fan air Valve (FAV) Fan Air Valve Control Thermostat (CT) Intermediate Pressure Check Valve (IPC) Overpressure Valve (OPV) Regulated Pressure (Pr) Transferred Pressure (Pt) Heat Exchanger Outlet Temperature Sensor (T) Bleed Monitoring Computer (BMC)

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ENGINE BLEED AIR SUPPLY COMPONENTS HIGH PRESSURE VALVE (HPV)

HIGH CLOSURE CONTROL SOLENOID

IDENTIFICATION FIN: 4000HA1, 4000HA2

IDENTIFICATION FIN: 4029KS

LOCATION ZONE: 450, 460


COMPONENT DESCRIPTION The valve is spring loaded closed.

COMPONENT DESCRIPTION It controls the HPV to close upon EEC command.

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ENGINE BLEED AIR SUPPLY COMPONENTS - HPV - HPV CLOSURE CONTROL SOLENOID EFFECTIVITY EFFECTIVITY ALL

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ENGINE BLEED AIR SUPPLY COMPONENTS PRESSURE REGULATING VALVE (PRV)

BLEED PRESSURE REGULATED VALVE CONTROL SOLENOID (CTS)





COMPONENT DESCRIPTION The valve is spring loaded closed.

COMPONENT DESCRIPTION Three functions:

- PRV electrical shut off (Solenoid) - Temperature Limitation - Reverse flow inhibition

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ENGINE BLEED AIR SUPPLY COMPONENTS - PRV - CTS EFFECTIVITY EFFECTIVITY ALL

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ENGINE BLEED AIR SUPPLY COMPONENTS PRECOOLER

FAN AIR VALVE CONTROL THERMOSTAT (CT)

IDENTIFICATION FIN: 7150HM1, 7150HM2




COMPONENT DESCRIPTION Single cross pass heat exchanger.

COMPONENT DESCRIPTION It is pneumatically coupled to the Fan Air Valve to control it open if the temperature downstream of the precooler exceeds 200°C ( 392°F ).

FAN AIR VALVE (FAV) IDENTIFICATION FIN: 9HA1, 9HA2 LOCATION ZONE: 453, 463 COMPONENT DESCRIPTION The valve is spring loaded closed.

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ENGINE BLEED AIR SUPPLY COMPONENTS - PRECOOLER - FAV - CT EFFECTIVITY EFFECTIVITY ALL

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36 PNEUMATIC SYSTEM

ENGINE BLEED AIR SUPPLY COMPONENTS INTERMEDIATE PRESSURE CHECK VALVE (IPC)

OVERPRESSURE VALVE (OPV)




LOCATION ZONE: 453, 563 COMPONENT DESCRIPTION The valve is spring loaded open.

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ENGINE BLEED AIR SUPPLY COMPONENTS - IPC - OPV EFFECTIVITY EFFECTIVITY ALL

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ENGINE BLEED AIR SUPPLY COMPONENTS REGULATED PRESSURE (Pr)

HEAT EXCHANGER OUTLET TEMPERATURE SENSOR (T)





COMPONENT DESCRIPTION It is connected to both BMCs for pressure indication and system fault monitoring purposes. It is also connected by a sense line to the duct downstream of the PRV.

COMPONENT DESCRIPTION It is connected to both BMCs for temperature indication (ECAM) and FAULT logic. It also monitors the temperature downstream of the precooler.

TRANSFERRED PRESSURE (Pt) IDENTIFICATION FIN: 7HA1, 7HA2 LOCATION ZONE: 415, 425

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0 0 2 4 D F U

COMPONENT DESCRIPTION It is connected to its dedicated BMC for faulty component identification in case of failure. It is also connected by a sense line to the duct downstream of the HP bleed valve. It gives the transferred relative static pressure.

5 0 T 5 0 H E N P U M T


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ENGINE BLEED AIR SUPPLY COMPONENTS - Pr - Pt - T EFFECTIVITY EFFECTIVITY ALL

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ENGINE BLEED AIR SUPPLY COMPONENTS BLEED MONITORING COMPUTER (BMC) IDENTIFICATION FIN: 1HA1, 1HA2 LOCATION ZONE: 121, 122 COMPONENT DESCRIPTION It monitors and controls the engine bleed system. At each power-up, a test of the BMC and of the leak detection system is done.

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6 0 T 5 0 H E N P U M T


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6 0 P 5 0 H E N P U M T

ENGINE BLEED AIR SUPPLY COMPONENTS - BMC EFFECTIVITY EFFECTIVITY ALL

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5 0 H E N P U M T


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36 - PNEU PNEUMA MATI TIC C SYST SYSTEM EM 36-12-0 36-1 2-00 0 GND AND AND APU BLEE BLEED D AIR SUPP SUPPLY LY COMPONENTS CONTENTS: APU Bleed Valve (GTCP 36-300) APU Bleed Valve (APIC) APU Bleed Valve (GTCP 131-9A) X Bleed Valve APU Bleed Check Valve HP Ground Connector

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GND AND APU BLEED AIR SUPPLY COMPONENTS APU BLEED VALVE (GTCP 36-300) IDENTIFICATION FIN: 4005KM LOCATION ZONE: 310 COMPONENT DESCRIPTION Spring loaded closed

3 L E V E L

0 0 2 4 D F U

1 0 T 1 0 I E N P U M T


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0 0 2 4 D F U

1 0 P 1 0 I E N P U M T

GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (GTCP 36-300)


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36 PNEUMATIC SYSTEM

GND AND APU BLEED AIR SUPPLY COMPONENTS APU BLEED VALVE (APIC) IDENTIFICATION FIN: 110KD LOCATION ZONE: 316 COMPONENT DESCRIPTION The Bleed Control Valve is located on the right lower part of the APU at the scroll outlet. It delivers air to the aircraft while avoiding load compressor surge.

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2 0 T 1 0 I E N P U M T


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3 L E V E L

0 0 2 4 D F U

2 0 P 1 0 I E N P U M T

GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (APIC)


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GND AND APU BLEED AIR SUPPLY COMPONENTS APU BLEED VALVE (GTCP 131-9A) IDENTIFICATION FIN: TBD LOCATION ZONE: 316 COMPONENT DESCRIPTION Spring loaded closed.

3 L E V E L

0 0 2 4 D F U

3 0 T 1 0 I E N P U M T


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3 L E V E L

0 0 2 4 D F U

3 0 P 1 0 I E N P U M T

GND AND APU BLEED AIR SUPPLY COMPONENTS - APU BLEED VALVE (GTCP 131-9A)


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GND AND APU BLEED AIR SUPPLY COMPONENTS X BLEED VALVE IDENTIFICATION FIN: 6HV LOCATION ZONE: 192 COMPONENT DESCRIPTION For safety reasons, the valve is equipped with two electric motors which can both actuate the butterfly in opening or closing directions. A brake system locks the valve in position when electrical power is cut off.

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4 0 P 1 0 I E N P U M T

GND AND APU BLEED AIR SUPPLY COMPONENTS - X BLEED VALVE


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GND AND APU BLEED AIR SUPPLY COMPONENTS APU BLEED CHECK VALVE IDENTIFICATION FIN: 7260HM LOCATION ZONE: 150 COMPONENT DESCRIPTION The APU bleed check valve is of the flapper type. It protects the APU from reverse flow when another source is supplying Bleed air at a higher pressure.

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5 0 T 1 0 I E N P U M T


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GND AND APU BLEED AIR SUPPLY COMPONENTS HP GROUND CONNECTOR IDENTIFICATION FIN: 7300HM LOCATION ZONE: 191 COMPONENT DESCRIPTION The HP ground connector contains contains a check valve of the flapper type and a built-in nipple. A duct connects the HP ground connector with the crossfeed duct on the left hand side of the cross bleed valve.

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GND AND APU BLEED AIR SUPPLY COMPONENTS - HP GROUND CONNECTOR


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36 - PNEU PNEUMA MATI TIC C SYST SYSTEM EM 36-22-0 36-2 2-00 0 PNEUMA PNEUMATIC TIC LEAK LEAK DETECT DETECTION ION COMPONENTS CONTENTS: Wing Leak Detection Element Pylon Detection Element APU Detection Element

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PNEUMATIC LEAK DETECTION COMPONENTS WING LEAK DETECTION ELEMENT IDENTIFICATION FIN: 21HF → 79HF LOCATION ZONE: COMPONENT DESCRIPTION Installed in each wing along the forward face of the front spar and in the mid fuselage along the hot air ducts. Triggering signal: Temperature > 124°C. Sensing elements mounted in series with connecting cables where necessary. At the alarm temperature, the impedance between the solid nickle conductor and the outer tubing decreases decreases suddenly, the center conductor grounds and gives an alarm signal to the BMC.

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1 0 P 1 0 K E N P U M T

PNEUMATIC LEAK DETECTION COMPONENTS - WING LEAK DETECTION ELEMENT


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PNEUMATIC LEAK DETECTION COMPONENTS PYLON DETECTION ELEMENT IDENTIFICATION FIN: 1HF1, 1HF2 LOCATION ZONE: 410, 420 COMPONENT DESCRIPTION Located at the outlet of the pylon ventilation duct. Triggering signal: Temperature > 204°C. Only one sensing element. At the alarm temperature, the impedance between the solid nickle conductor and the outer tubing decreases decreases suddenly, the center conductor grounds and gives an alarm signal to the BMC.

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2 0 P 1 0 K E N P U M T

PNEUMATIC LEAK DETECTION COMPONENTS - PYLON DETECTION ELEMENT


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PNEUMATIC LEAK DETECTION COMPONENTS APU DETECTION ELEMENT IDENTIFICATION FIN: 11HF → 20 HF LOCATION ZONE: APU duct COMPONENT DESCRIPTION Installed between check valve and APU compartment Triggering signal: Temperature > 124°C. Sensing elements mounted in series. At the alarm temperature, the impedance between the solid nickle conductor and the outer tubing decreases decreases suddenly, the center conductor grounds and gives an alarm signal to the BMC.

3 L E V E L

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3 0 T 1 0 K E N P U M T


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3 0 P 1 0 K E N P U M T

PNEUMATIC LEAK DETECTION COMPONENTS - APU DETECTION ELEMENT


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