ENGINE BLEED AIR SUPPLY SYSTEM - DESCRIPTION AND OPERATION

** ON A/C NOT FOR ALL

1. General
The purpose of the engine bleed air supply system is to:

Select one of the two different compressor stages of the engine HP compressor in agreement with the supplied pressure.
Regulate the bleed air pressure in order to prevent too high pressures.
Regulate the bleed air temperature in order to prevent too high temperatures.

** ON A/C NOT FOR ALL

2. Component Location

Component Location - Cockpit ** ON A/C NOT FOR ALL

Component Location - Avionics Compartment ** ON A/C NOT FOR ALL

Component Location - Engine ** ON A/C NOT FOR ALL

Electrical Schematic - Engine 1 ** ON A/C NOT FOR ALL

Electrical Schematic - Engine 2 ** ON A/C NOT FOR ALL

NOTE: The high pressure (HP) bleed valve, bleed pressure regulator valve (PRV) and intermediate pressure (IP) bleed check valve are buyer-furnished equipment (BFE).

The HP bleed valve is installed on the diffuser case at the 9 o'clock position.
The PRV valve is located downstream of the HP valve and is attached to the 3th and 8th stage bleed air duct (AP62) on the high pressure compressor at the 11 o'clock position.
The IP bleed check valve is installed between the 3th stage bleed air duct (AP60) and the 8th and 11th stage bleed air duct (AP62) at approximately the 10 o'clock position.
The 11th stage compressor bleed air duct (AP61) is R attached to the diffuser case ports at the 8 and 9 o'clock positions.
The 3th stage bleed air duct (AP60) is attached to the R high pressure compressor rear case ports at the 10 and 11 o'clock positions.
The 3th and 8th stage bleed air duct (AP62) is R attached to the IP valve, HP valve, and the PRV at the R 10 o'clock position on the diffuser case.
The HPC bleed air duct (AP63) is attached to the PRV on R the downstream side at the 11 o'clock position on the diffuser case.

FIN	FUNCTIONAL DESIGNATION	PANEL	ZONE	ATA REF
** ON A/C NOT FOR ALL
1HA1	BMC-1	95VU	121	36-11-34
1HA2	BMC-2	96VU	122	36-11-34
6HA1	SENSOR-EXCHANGER OUT TEMP, ENG 1		415	36-11-17
6HA2	SENSOR-EXCHANGER OUT TEMP, ENG 2		425	36-11-17
7HA1	XDCR-BLEED TRANSFER PRESS, ENG 1		471	36-11-15
7HA2	XDCR-BLEED TRANSFER PRESS, ENG 2		481	36-11-15
8HA1	XDCR-BLEED REGULATED PRESS, ENG 1		471	36-11-16
8HA2	XDCR-BLEED REGULATED PRESS, ENG 2		481	36-11-16
9HA1	VALVE-FAN AIR, ENG1		471	36-11-54
9HA2	VALVE-FAN AIR, ENG2		481	36-11-54
4000HA1	VALVE-HP BLEED, ENG 1		453	36-11-51
4000HA2	VALVE-HP BLEED, ENG 2		463	36-11-51
4001HA1	VALVE-BLEED PRESS REG, ENG 1		453	36-11-52
4001HA2	VALVE-BLEED PRESS REG, ENG 2		463	36-11-52
7150HM1	EXCHANGER-BLEED AIR PRECOOL		423	36-11-42
7150HM2	EXCHANGER-BLEED AIR PRECOOL		423	36-11-42

** ON A/C NOT FOR ALL

3. System Description

Pneumatic System - Schematic ** ON A/C NOT FOR ALL

Component Location - Engine ** ON A/C NOT FOR ALL

Air is generally bled from an Intermediate Pressure (IP) stage of the engine High Pressure (HP) compressor to minimize engine pressure losses. This is the normal engine air-bleed configuration.

The IP stage is the 3th HP compressor stage. At low engine speeds, when the pressure from the IP stage is insufficient, air is automatically bled from a higher compressor stage (HP stage). This happens especially at some aircraft holding points and during descent, with engines at idle.

The HP stage is the 8th HP compressor stage. Transfer of bleed air is achieved by means of a pneumatically-operated and electrically commanded butterfly valve, designated HP bleed valve (4000HA).

When the HP bleed valve is closed, air is directly bled from the IP stage through an IP bleed check valve (7110HM), fitted with two flappers.
When the HP bleed valve is open, the HP stage pressure is admitted into the pneumatic ducting and closes the IP bleed check valve. Air is then bled from the HP stage only.
The HP bleed valve operates pneumatically and is electrically controlled.
The bleed pressure regulator valve is installed in the duct downstream of the IP bleed check valve and the HP bleed valve . The bleed pressure regulator valve also operates pneumatically but opening and closing can be controlled by a control solenoid.
Downstream of the PRV, an overpressure valve (OPV) (5HA) is installed to protect the pneumatic system against damage if overpressure occurs. To keep the temperature within the limits, a fan air valve (FAV) (9HA) is installed in the cooling air duct which supplies fan air to the precooler exchanger . The FAV operates pneumatically and is controlled by the BMC which take the data of the Bleed Temperature Sensor (8HA).
Two pressure transducers are installed on a bracket adjacent to the precooler exchanger. One pressure transducer (7HA) is connected with a sense line to the pneumatic duct downstream of the HP bleed valve , the other (8HA) is connected with a sense line to the pneumatic duct downstream of the PRV. An exchanger outlet temperature sensor (6HA) is installed in the elbow of the pneumatic duct in the pylon downstream of the precooler exchanger . Both pressure transducers are connected to the bleed air monitoring computers (BMC) by an electrical cable.
Bleed air at controlled pressure and temperature is supplied through insulated ducts to the user as specified in (SD 36-00-00).

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4. Interfaces
Pneumatic Interfaces

Fan bypass air
3th stage air at high engine power
8th stage air at low engine power.

** ON A/C NOT FOR ALL

5. Component Description

A. High-Pressure Bleed Valve (HPV) FIN: 4000-HA

High-Pressure Bleed Valve ** ON A/C NOT FOR ALL

(1) The HPV is a butterfly type valve with a diameter of 4 IN. (101.5998 MM) which operates as a shutoff and a PRV. It is electrically controlled to keep it in the closed position, if there is no upstream pressure. A minimum pressure of 15 psig (bar rel.) is necessary to open the valve.

The HPV pneumatically keeps the downstream static pressure to 65 plus or minus 12 psig (bar rel.). If the upstream pressure is over 120 psig (bar rel.), the HPV does not close. It continues to keep the downstream pressure at the same values. The BMC controls the HPV and the PRV to make sure that the HPV will close when the PRV (which can be controlled) is closed.

(2) Detailed Description

High-Pressure Bleed Valve - Schematic ** ON A/C NOT FOR ALL

The HP bleed valve contains three main parts:

A valve body
A pneumatic actuator
A regulator assembly.

(a) Valve body
The valve body is made of Inconel and has a butterfly plate that moves on hybrid ball bearings, on a tilted axis. A pneumatic actuator operates the ball bearings.

(b) Pneumatic assembly
The differential double-effect pneumatic-actuator is made of stainless steel. It has a piston between a closing chamber and an opening chamber. It has a cylinder assembly.

A pressure reducer that supplies a constant pressure to the actuator
An ON/OFF solenoid that lets the regulated pressure go into the opening chamber (solenoid energized) or releases the pressure from the opening chamber (solenoid de-energized). Then the IP pressure is supplied directly to the closing chamber and closes the valve.

(d) Opening/closing

The upstream muscle pressure is applied to the upstream side of the HPV body. The minimum upstream muscle pressure, necessary for the operation of the valve, is 15 psig. When the solenoid is not energized, the HPV is set to the fully closed position. The downstream pressure is applied to the HPV downstream duct and feeds the actuator closing chamber through a sense line.

(3) Controls and Indicating
HP bleed valve operation is pneumatic and electrical. The lower ECAM display unit indicates its position (open or closed) on the BLEED page

ECAM Upper and Lower Display Units ** ON A/C NOT FOR ALL

The two BMCs monitor and command the operation of the HP bleed valve by the control solenoid installed in the body of the valve. They receive and process the signals and transmit the information per data bus by the System Data Acquisition Concentrator (SDAC) to the ECAM system which generates the system display (Ref. AMM D/O 36-20-00-00).

ECAM - Generation ** ON A/C NOT FOR ALL

Additionally, they transmit the information to the Centralized Fault Display Interface Unit (CFDIU). The CFDIU generates maintenance information which is displayed on the Multi Function Control Display Unit (MCDU) if the MCDU MENU is selected.

CFDS Menu ** ON A/C NOT FOR ALL

LAST LEG REPORT Page ** ON A/C NOT FOR ALL

PREVIOUS LEGS REPORT Page ** ON A/C NOT FOR ALL

LRU IDENT Page ** ON A/C NOT FOR ALL

CURRENT STATUS Page ** ON A/C NOT FOR ALL

CLASS 3 FAULT Page ** ON A/C NOT FOR ALL

TEST Page ** ON A/C NOT FOR ALL

B. Bleed-Pressure Regulator Valve (PRV)

Bleed-Pressure Regulator Valve ** ON A/C NOT FOR ALL

(1) The PRV is a butterfly type valve, with a diameter of 4 in. (101.60 mm). It is electrically controlled to be in closed position if there is no upstream pressure. A minimum upstream pressure of 15 psig is necessary to open the valve.

(2) Detailed Description:

Bleed-Pressure Regulator Valve - Schematic ** ON A/C NOT FOR ALL

The valve has these primary parts:

A valve body with a butterfly plate that moves on a hybrid ball bearing, on the slope axis. A pneumatic actuator operates the valve body.
The body of the valve has an upstream pressure tapping that is a part of the valve, which supplies the upstream pressure to the pneumatic actuator. The valve body and the valve shaft are made of inconel. The butterfly plate is made of high-temperature stainless steel.
A differential double-effect pneumatic-actuator with the cylinders and the piston. The cylinders and the piston isolate the opening and closing chambers from the ambient pressure. The pneumatic actuator body is made of stainless steel.
A servo pressure regulator supplies a constant pressure for torque motor modulation.
The PRV is a fireproof valve.

(3) Controls and Indicating
The PRV pneumatically controls the downstream pressure to 51 -9 psi or +9 psi (3.52 -0.62 bar or +0.62 bar) for normal bleed operation:

The pressure regulation target is 42 psi (2.90 bar) for the two bleeds in operation or 50 psi (3.45 bar) for one bleed in operation.
For the normal bleed operation the electrical supply to the torque motor will be same as the 42 psi (2.90 bar) of the downstream pressure.

It closes automatically in the cases that follow:

When the torque-motor is not energized
When the torque-motor is energized but without pressure in the valve body
When the overtemperature downstream of the precooler exchanger is 257 -3 deg.C or +3 deg.C (494.6 -5.4 deg.F or +5.4 deg.F) (60 seconds delay)
When the high pressure downstream of the PRV is 57 -3 psi or +3 psi (3.93 -0.21 bar or +0.21 bar) (15 seconds delay)
When there is ambient overheat in the pylon/wing/fuselage ducts adjacent area
APU bleed valve not closed
Related starter valve is not closed
No bleed requirements.

It is controlled in closed position by crew action on:

ENG FIRE pushbutton switch
ENG BLEED pushbutton switch.

The PRV closes pneumatically if there is a risk of opposite flow to the engine. OPV installed downstream of the PRV gives protection to the system against damage if overpressure occurs. The BMC controls the HPV to close position if the PRV is closed or controlled to close. The thermal fuse installed in the valve body causes the valve to close at 450 -25 deg.C or +25 deg.C (842 -45 deg.F or +45 deg.F).

C. Solenoid HP Bleed

(1) Solenoid HP Bleed Override
Not Applicable.

(2) Detailed Description
The PRV contains three main parts:

A valve body
A pneumatic actuator
A regulator assembly.

(a) Regulation
The upstream pressure supplies chamber (1) of the regulator through a jet to control the position of the clapper (2) and maintain constant air pressure in the actuator opening chamber.
The regulator calibration can be modified by the secondary stage of the regulator which is pneumatically connected to the Bleed Pressure regulator valve Control Solenoid according to the air temperature sensed downstream to the PCE. The air pressure in chamber (3) can vary according to an air leakage controlled by the Bleed Pressure Regulator Valve Control Solenoid. As clapper (2) remains in contact with its seat (4), downstream pressure still supplies the actuator closing chamber despite a reduced pressure air value lower than the nominal regulation threshold.
The test intake is used for checking correct valve operation on the ground by directly supplying the regulator.
The downstream pressure supplies the actuator closing chamber through distribution clapper (4). Indeed when downstream pressure reaches the value determined by spring pre-loading.

(b) Opening/Closing
Reduced pressure air supplies chamber (5) of the opening/closing sub assembly though a jet to control the position of clapper (6) against its lower seat position and allow the HP Bleed Valve actuator opening chamber supply with reduced pressure air.
When chamber (5) is vented to ambient the clapper (6) leaves its lower seat position and reduced pressure air is allowed to supply the HP Bleed Valve actuator closing chamber.

(c) Safety devices and indications
A thermal fuse (7) permits to vent to ambient chamber (5) of the opening/closing subassembly. This causes the valve to close.
The PRV is equipped with an upstream pressure test port which permits you to perform an "in situ" test.
A manual override permits you to close the valve mechanically on the ground.

(3) Control and Indicating
PRV operation is pneumatically actuated and electrically commanded. The PRV can be controlled in close position from the AIR COND overhead control panel. The pushbutton switches (ENG 1 (2) BLEED) energize/de-energize the solenoid. The lower ECAM display unit indicates its position on the BLEED page.

ECAM Upper and Lower Display Units ** ON A/C NOT FOR ALL

The two BMCs monitor the operation of the PRV closed/open and regulated pressure level. They receive and process the signals and transmit the information per data bus by the SDAC to the ECAM system which generates the system display (Ref. AMM D/O 36-20-00-00). Additionally, they transmit the information to the CFDIU. The CFDIU generates maintenance information which is displayed on the MCDU if the MCDU MENU is selected.

CFDS Menu ** ON A/C NOT FOR ALL

D. Bleed Pressure Sensor (BPS)

Fan Air Valve Valve ** ON A/C NOT FOR ALL

(1) The bleed pressure sensor (BPS) is a silicon type sensor with integrated interface,temperature compensated, supplied from 28 VDC.

A sense line is installed between the BPS and the pressure tapping which is installed connecting the Pressure Regulated Valve the Intermediate Valve and the Over Pressure Valve.

(2) Function

(a) The Bleed Pressure Sensor Monitoring the pressure and closed loop control, as Overpressure as low pressure.
It is also used to monitoring the position of the switchless OPV.

E. Differential Pressure Sensor (DPS)

(1) The DPS is a silicon type sensor with integrated interface (output voltage), temperature compensated, supplied from 28 VDC.

(a) The flow detection differential pressure sensor is connect by two sense lines:

One is tapped upstream of the precooler.
The other one is downstream of the precooler.

(2) Function
The function of the DPs is monitor the pressure, control the PRV position and make sure that no reverso flow occur.

F. Bleed Temperature Sensor (BTS)

(1) The BTS is a dual element immersion type with two electrical connectors, each sensing element is of the 2-wire type.

Engraved marking must be visible when the sensor is installed, two faces have to be engraved to allow visibility on all installations.
The wiring connected to channel A of the BTS is fully segregated from the wiring connected to channel B this means that the wiring passed thought different connectors all the way through from the BTS to BMC.

(2) Function

Bleed air temperature regulation control and monitoring (low and high temperature warning).

G. Overpressure Valve (OPV)

Overpressure Valve (OPV) ** ON A/C NOT FOR ALL

(1) The OPV is a pneumatic butterfly shut-off valve, spring loaded open. The OPV have a one effect pneumatic actuator and an overpressure clapper valve

The overpressure clapper supplies the closing chamber of the actuator in case of bleed overpressure. Due to differential areas inside this clapper.
The OPV reopening only for pressure significantly lower than the overpressure setting.

(2) Detailed Description

Overpressure Valve (OPV) - Schematic ** ON A/C NOT FOR ALL

(a) The OPV contains two main parts:

A valve body
An actuator assembly.

(b) Pressure working:

To closure between 75 psi (5.1711 bar) and 85 psi (5.8605 bar), closing time 4 sec.
To re-opening between 43 psi (2.9647 bar) and 59 psi (4.0679 bar), time < 2 sec.

(3) Controls and Indicating
OPV operation is fully pneumatic. It cannot be controlled from the cockpit.

H. Bleed Air Precooler Exchanger

Bleed Air Precooler Exchange ** ON A/C NOT FOR ALL

(1) The precooler is a compact plate and fin heat exchange cross flow type that have one path on both cold and hot air sides.

(2) Detailed Description

(a) Function
The precooler assures cooling of the hot air bled from the engine compressors by a heat exchange process using cold air from the engine fan. (a) Main Components:

A core made of 29 cold flow layers and 28 hot flow layers
Hot inlet and outlet headers
Mixer at PCE hot side outletside
Cold inlet and outlet flanges
4 shock absorbers to let thermal expansion of the PCE

I. Fan Air Valve (FAV)

Fan Air Valve (FAV) ** ON A/C NOT FOR ALL

Fan Air Valve Valve ** ON A/C NOT FOR ALL

(1) The FAV is a 6 in. dia. butterfly-type valve, normally spring - loaded closed in the absence of pressure. A minimum upstream pressure of 8 psig is necessary to open the valve. The FAV regulates the downstream precooler exchanger temperature to 200 plus or minus 15 deg.C (27 deg.F).

(2) Detailed description
The FAV contains these primary parts:

A FAV body
A rod
A FAV actuator.

(a) Regulation
A bleed temperature sensor is installed downstream of the precooler exchanger. The bleed temperature sensor senses the hot air temperature and sends a pressure signal to the valve related to the precooler cooling air. The FAV butterfly changes its position from fully closed to fully open to keep the temperature value of bleed air in limits.
The pressure in the cylinder is controlled by the pneumatic servo regulator and the torque-motor controlled servo-valve.
The servo-valve controls the leakage of the cylinder pressure overboard. The muscle pressure is supplied to the regulator by a pneumatic connection from the downstream of the hot side of the precooler.
The FAV body goes to the full closed position without the muscle pressure.
The FAV body goes to the fully open position with the muscle pressure but without the current on the torque motor.

(b) Safety devices and indications
The FAV has a test port which is used to do the "in situ" test.
A manual override controls the valve mechanically to close it on the ground. A thermal fuse installed on the valve body closes the valve if the nacelle temperature gets to a value of 450 -25 DEG.C or +25 DEG.C (842 -45 DEG.F or +45 DEG.F)

J. Bleed Manifold Pressure Sensor (BMPS)

(1) Function
The BMPS is a silicon type sensor with integrated interface, temperature compensated, supplied from 28VDC.
The BMPS is connected by a pneumatic sense line to pressure tapping on the bleed T-Ducts, upstream the pressure regulating valve.

K. Bleed Monitor Control (BMC)

(1) The BMC is a 2 MCU ARINC 600 controller embedding two channels:

Digital control channel (CHA)
Hardware safety channel (CHB)

CHA is a full digital channel embedding all the control and monitoring functions to meet system requirements.
CHB is a fully hardware part able to detect the system overtemperature. This detection is fully independent from software part.

L. -

(1) BMC internal archiquecture

(a) CHA is a digital board embedding:

1 A microcontroller and associated peripherals

2 I/O necessary for the control of the system and interface with other aircraft systems:

Discrete inputs/outputs
Analogue inputs
Leak detection loop inputs
Torque motor/solenoid for electro-pneumatic valves
Arinc I/O for communication with A/C systems.

(2) CHB is an analogue board embedding full hardware electrical protection functions (EPF).

these EPFs are based on a hardware comparator whose output is activated as soon as associated input sensor reached a critical threshold.

M. IP Bleed Check Valve

(1) The IP bleed check valve prevents diffuser bleed air from flowing into the mid-stage bleed duct when the HP bleed valve is open.

(2) The IP bleed check valve is a split flapper-type one way valve. At low power settings, when the HP bleed valve is open, the IP bleed check valve prevents 8th stage bleed air from flowing back into the mid-stage duct. At higher power settings the HP bleed valve will close allowing 3th stage air to open the IP bleed check valve and supply the aircraft pneumatic system through the bleed pressure regulator valve.

N. Bleed Air Ducts

(1) The bleed air ducts collect the 3th and 8th stage compressor bleed air for distribution to the aircraft Environment Control System (ECS).

(2) The bleed air ducts are formed and bent metal ducts with specially-made flanges that attach to the engine and the valves.

(3) The 8th stage bleed air duct and the 8th and 11th stage air duct have gimbal joints as part of their assembly. This feature is for removal of the engine bleed air supply system valves without removing adjacent ducts.

(4) The 3th and 8th stage air duct (AP62) has a sensor line fitting.

(5) The 8th stage bleed air duct has a pressurization line fitting used for the hydraulic reservoir pressurization.

(6) The bleed-air ducts are line replaceable units.

** ON A/C NOT FOR ALL

6. Power Supply

Electrical Schematic - Engine 1 ** ON A/C NOT FOR ALL

Electrical Schematic - Engine 2 ** ON A/C NOT FOR ALL

-------------------------------------------------------------------------------

BUSBAR VOLTAGE FUNCTIONS ATA NO.

AND POWER

SUPPLY

-------------------------------------------------------------------------------

801PP 28 VDC ESS Power Supply to :

Bleed Air Monitoring Computer 1 (BMC 1) 36-11-00

Relay ENG 1 BLEED LAMP TEST AND INTERFC 36-20-00

Pressure Transducers 36-21-00

202PP 28 VDC NORM Power Supply to :

Bleed Air Monitoring Computer 2 (BMC 2) 36-11-00

Relay ENG 2 BLEED LAMP TEST AND INTERFC 36-20-00

Pressure Transducers 36-21-00

801PP 28 VDC ESS Power Supply to :

Bleed Air Monitoring Computer 1 (BMC 1) 36-11-00

ENG 1 BLEED Pushbutton Switch 36-20-00

ENG 1 FIRE Handle 26-00-00

202PP 28 VDC NORM Power Supply to :

Bleed Air Monitoring Computer 2 (BMC 2) 36-11-00

ENG 2 BLEED Pushbutton Switch 36-20-00

ENG 2 FIRE Handle 26-00-00

** ON A/C NOT FOR ALL

7. Operation

A. Function

The bleed systems of engine 1 and engine 2 are almost the same and operate independently.
Air is tapped from the intermediate HP compressor-stage through the IP bleed check-valve (IPCV) or from the high HP compressor-stage through the HPV related to the engine speed.
An IP port pressure is not sufficient when the engine speed is low, specially during the aircraft decent with the engine at idle. The air is automatically bled from the HP port (high pressure on stage 8) through the HPV and the IPCV is closed to prevent the air recirculation.
The engine bleed air is in the normal configuration when the engine speed is high. The air is bled from the IP port (intermediate pressure on stage 3) through the IPCV and the HPV closes.
The PRV controls the bleed air pressure to a standard value downstream of the HPV and IPCV. A solenoid is installed downstream of the precooler exchanger to control the PRV in the closed position. The PRV is connected to the HPV by a sense line. The PRV and the HPV are vented and closed at the same time when the PRV is controlled to the OFF position.
An OPV is installed downstream of the PRV to prevent ducting damage caused by an incorrect control of the PRV (high pressure). The OPV will close when the downstream PRV pressure gets the OPV closing value.
The pressure regulated air goes to the other systems through the bleed-air precooler exchanger where it is cooled. The bleed temperature sensor controls the FAV to adjust the cold airflow from the engine fan. This cold airflow cools the pressure regulated air.

B. Fault Detection and Monitoring of the System
The monitoring system detects failures and abnormal operation of the engine bleed air supply system. It warns the crew and transmits the relevant information to the upper and lower ECAM display units. Additionally the MASTER CAUT light comes on and a single chime sounds. The system also enables abnormal operation and failure to be detected during flight in order to facilitate replacement on the ground of faulty components (Line Replaceable Units, LRU).

An exchanger outlet temperature sensor monitors the precooler outlet temperature.
Two pressure transducers monitor the air pressure available in circuit.

(1) The two BMCs monitor the electrical signals from the switchless system of the valves, the temperature at the precooler outlet, the transferred and the regulated pressures. Additionally, they monitor ambient overheat in pylons, wings and the fuselage (Ref. AMM D/O 36-22-00-00).

(2) The two BMCs transmit data through the SDAC to the ECAM system which generates the indications on the system page. The indications are:

Pressure
Temperature
Position of the main valves (PRV, HP Bleed Valve, Crossbleed valve and APU BLEED valve).

The two BMCs signal directly to the AIR COND overhead control panel the ENG 1 (2) BLEED FAULT signal.

(3) The two BMCs trigger a warning in case of:

Overpressure/low pressure
Overtemperature/low temperature
Ambient overheat.

(4) The two BMCs control the closure of the PRV (during warning, engine start, APU bleed) automatic mode of Crossbleed valve and APU bleed valve opening availability.

(5) The two BMCs monitor the correct operation of the whole system and detect abnormal function of an item. They send this data to the Centralized Fault Display System (CFDS) (Maintenance Computer).

NOTE: All the class 1, 2 and 3 maintenance messages transmitted from the two BMCs are listed in the INDEX of the TSM.

** ON A/C NOT FOR ALL

8. BMC Parameter List

A. Data Bus from EIU

(1) Discrete word

----------------------------------------------------------------------------

! KEY: (e) !

! SDI = 01 or 11 from EIU1 !

! SDI = 10 or 00 from EIU2 !

!--------------------------------------------------------------------------!

! LABEL ! SDI ! BIT ! REFRESH ! PARAMETER !STATUS 0!STATUS 1! COMMENTS !

! ! ! ! RATE (ms) ! DEFINITION ! ! ! !

!-------!-----!-----!-----------!------------!--------!--------!-----------!

! 270 ! (e) ! 13 ! 250 max ! ENGINE !CLOSED ! NOT !USED BLEED !

! ! ! ! ! STARTER ! !CLOSED !PRESSURE !

! ! ! ! ! VALVE ! ! !REGULATOR !

! ! ! ! ! POSITION ! ! !VALVE FOR !

! ! ! ! ! ! ! !CONTROL !

----------------------------------------------------------------------------

! KEY: !

! SDI = 01 from EIU1 !

! SDI = 10 from EIU2 !

!--------------------------------------------------------------------------!

! LABEL ! BIT ! REFRESH ! PARAMETER ! STATUS 0!STATUS 1! COMMENTS !

! ! ! RATE (ms)! DEFINITION ! ! ! !

!-------!-------!----------!---------------!---------!--------!------------!

! ! 11 ! ! OIL LOW PRESS ! !DETECTED! !

! ! ! ! ! !(Eng ! !

! ! ! ! ! ! Not ! !

! ! ! ! ! !Running)! !

! 032 !-------! 125 max !---------------!---------!--------!------------!

! ! 13 ! !VALVE CLOSURE ! ! !FOR CROSS- !

! ! ! !For ENG START ! NO ! YES !BLEED VALVE !

! ! ! ! DEMAND ! ! !CTL AND APU !

! ! ! ! ! ! !ENABLE !

! !-------!----------!---------------!---------!--------!------------!

! ! 19 ! ! CFM 56 FAMILY ! !SELECTED! !

!--------------------------------------------------------------------------!

! ! 17 ! ! LH MAIN ! !COMPRES-! !

! ! ! ! LANDING GEAR ! !SED ! !

! ! ! ! ! ! ! USED FOR !

! ! ! ! ! ! ! TEST !

! ! ! 80 max ! ! ! ! INHIBITION !

! 031 !-------! !---------------!---------!--------! AND !

! ! 18 ! !RH MAIN ! !COMPRES-! LOW TEMP !

! ! ! !LANDING GEAR ! !SED ! !

! ! ! ! ! ! ! !

! !-------! !---------------!---------!--------!------------!

! ! 29 ! ! WAI P/B ! ! OFF ! LOW TEMP !

! ! ! ! ! !SELECTED! !

----------------------------------------------------------------------------

B. Data Bus from EIU

(1) Numerical word

----------------------------------------------------------------------------

! KEY: (e) (k) !

! SDI = 01 or 11 from EIU1 SDI = 01 from EIU1 !

! SDI = 10 or 00 from EIU2 SDI = 10 from EIU2 !

!--------------------------------------------------------------------------!

!LABEL!SDI!PARAMETER!BINARY! REFRESH !NUMBER OF!OPERATING!RESOLUTION! UNIT !

! ! ! DEFINI- !RANGE ! RATE !SIGNIFI- !RANGE !(approx) ! !

! ! ! TION ! ! (ms) !CANT BITS!Min/Max ! ! !

!-----!---!---------!------!---------!---------!---------!----------!------!

! 114 ! ! PO ! 32 ! 250 max ! 14 ! 2/20 ! 0,002 ! !

!-----!(e)!---------------------------------------------------------! PSIA !

! 264 ! ! PS3 ! 512 ! 125 max ! 14 ! 2/450 ! 0,03 ! !

!-----!---!---------!------!---------!---------!---------!----------!------!

! 316 !(k)! OIL TEMP!2048 ! 125 max ! 12 ! -60 to ! 0,5 ! °C !

! ! ! ! ! ! ! +250 ! ! !

-------------------------------------------------------------------------!

C. Output Data Bus from CFDIU (Numerical word)

----------------------------------------------------------------------------

! KEY: !

! SDI = 00 for BMC1 and BMC2 !

! SDI = 01 for BMC1 !

! SDI = 10 for BMC2 !

!--------------------------------------------------------------------------!

! LABEL ! SDI ! PARAMETER DEFINITION ! FORMAT ! REFRESH ! COMMENTS !

! ! ! ! ! RATE (ms)! !

!-------!-------!----------------------!--------!----------!---------------!

! 125 ! 00 ! GMT ! BCD ! 1000 ! !

!-------!-------!----------------------!--------!----------! SEE ARINC 429 !

! 260 ! 00 ! DATE ! BCD ! 1000 ! !

!-------!-------!----------------------!--------!----------!---------------!

! 233 ! ! ! ISO NOT! ! !

! 234 ! 00 ! FLIGHT NUMBER ! EQUAL ! 4000 ! !

! 235 ! ! ! TO 5 ! ! !

! 236 ! ! ! ! ! !

!-------!-------!----------------------!--------!----------! !

! 227 ! 01/10 ! BITE COMMAND CONTROL ! BCD ! 120 ! !

!-------!-------!----------------------!--------!----------! SEE ABD 0018 !

! 301 ! ! ! ISO NOT! ! !

! 302 ! ! AIRCRAFT IDENTIFIER ! EQUAL ! 4000 ! !

! 303 ! ! ! TO 5 ! ! !

! 304 ! ! ! ! ! !

!-------!-------!----------------------!--------!----------! !

! 126 ! 00 ! FLIGHT PHASE ! BNR ! 1000 ! !

!-------!-------!----------------------!--------!----------! !

! 155 ! 00 !AIRCRAFT CONFIGURATION!DISCRETE! 1000 ! !

! ! ! WORD ! WORD ! ! !

----------------------------------------------------------------------------

! KEY: (c) SDI=01 for BMC1 or 10 for BMC2 !

! (d) Used by SDAC1 or SDAC2 for "SYSTEM PAGES" !

! (h) Emission only by BMC2 - (i) Emission only by BMC1 !

! (e) SDI=01 from EIU1 and SDI=10 from BMC2 !

!--------------------------------------------------------------------------!

!LABEL!SDI!PARAMETER!FORMAT!UPD/MSEC ! SIG !OPER RANGE!RESOLUTION! UNIT !

! ! ! DEF ! !MIN/MAX ! BIT !MIN/MAX ! ! !

!-----!---!---------!------!---------!--------!----------!----------!------!

! 141 !(c)!ENG1 PRE-! ! ! ! ! ! !

! (d) ! !COOLER ! BNR ! 125/250 ! 10 ! 0/+512 ! 0,5 ! °C !

! ! !EXCHANGER! ! ! ! ! ! !

! ! !OUTLET ! ! ! ! ! ! !

! ! !TEMPERA- ! ! ! ! ! ! !

! ! !TURE ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 143 !(c)!ENG1 PRE-! ! ! ! ! ! !

! (d) ! !COOLER ! BNR ! 125/250 ! 10 ! 0/ 512 ! 0,5 ! PSIG !

! ! !EXCHANGER! ! ! ! ! ! !

! ! !INLET ! ! ! ! ! ! !

! ! !PRESSURE ! ! ! ! ! ! !

! ! ! (PR1) ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 140 !(c)!ENG2 PRE-! ! ! ! ! ! !

! (d) ! !COOLER ! BNR ! 125/250 ! 10 ! 0/+512 ! 0,5 ! °C !

! ! !EXCHANGER! ! ! ! ! ! !

! ! !OUTLET ! ! ! ! ! ! !

! ! !TEMPERA- ! ! ! ! ! ! !

! ! !TURE(PR1)! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 142 !(c)!ENG2 PRE-! ! ! ! ! ! !

! (d) ! !COOLER ! BNR ! 125/250 ! 10 ! 0/ 512 ! 0,5 ! PSIG !

! ! !EXCHANGER! ! ! ! ! ! !

! ! !OUTLET ! ! ! ! ! ! !

! ! !PRESSURE ! ! ! ! ! ! !

! ! ! (PR2) ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 151 !01 !ENG1 ! ! ! ! ! ! !

! (i) ! !TRANSFER-! BNR ! 125/250 ! 10 ! 0/ 512 ! 0,5 ! PSIG !

! ! !RED PRES-! ! ! ! ! ! !

! ! !SURE ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 153 !01 !ENG1 HIGH! ! ! ! ! ! !

! (i) ! !PRESSURE ! BNR ! 125/250 ! ! SAME AS PS3 ! PSIG !

! ! !STAGE ! ! ! ! ! ! !

! ! !OUTLET ! ! ! ! ! ! !

! ! !PRESSURE ! ! ! ! ! ! !

! ! !(PS3-P0) ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 152 !10 !ENG2 ! ! ! ! ! ! !

! (h) ! !TRANSFER-! BNR ! 125/250 ! 10 ! 0/ 512 ! 0,5 ! PSIG !

! ! !RED ! ! ! ! ! ! !

! ! !PRESSURE ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 154 !10 !ENG2 HIGH! ! ! ! ! ! !

! (h) ! !PRESSURE ! BNR ! 125/250 ! ! SAME AS PS3 ! PSIG !

! ! !STAGE ! ! ! ! ! ! !

! ! !OUTLET ! ! ! ! ! ! !

! ! !PRESSURE ! ! ! ! ! ! !

! ! !(PS3-P0) ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 377 !(c)!EQUIP- ! ! ! ! ! ! !

! ! !MENT ! BCD ! 125/250 ! ! ! ! NONE !

! ! !IDENTI- ! ! ! ! ! ! !

! ! !FICATION ! ! ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 356 !(c)!MAINTE- ! ISO !NORMAL ! ! ! ! !

! ! !NANCE ! NOT !MODE 50/ ! ! ! ! NONE !

! ! !DATA ! EQUAL!250 MENU ! ! ! ! !

! ! ! ! TO 5 !MODE SEE ! ! ! ! !

! ! ! ! !ABD0018 ! ! ! ! !

!-----!---!---------------------------------------------------------!------!

! 316 !(e)! OIL ! ! ! ! -60 ! ! !

! ! ! TEMP ! BNR ! 125/250 ! 12 ! to ! 0,5 ! °C !

! ! ! ! ! ! ! +250 ! ! !

!-----!---!---------------------------------------------------------!------!

! 322 !(e)! NACELLE ! ! ! ! -55 ! ! !

! ! ! TEMP ! BNR ! 125/250 ! 10 ! to ! 0,5 ! °C !

! ! ! ! ! ! ! +330 ! ! !

----------------------------------------------------------------------------

** ON A/C NOT FOR ALL

9. -

A. Data Bus from Valves of EBAS

(1) Data Table to Engine 1

-------------------------------------------------

!LABEL! BIT !PARAMETER ! Status ! Status !

!67/01! !DEFINITION ! 0 ! 1 !

!-----!-----!-----------!-------------!---------!

! ! 11 ! Eng1 OPV !Fully open !Not fully!

! ! ! position ! !open !

!-----!-----!-----------!-------------!---------!

! ! 14 ! OPEN Eng1 ! Open !Not open !

! ! !FAV command! ! !

!-----!-----!-----------!-------------!---------!

! ! 15 ! Eng1 HPV !Fully closed !Not fully!

! ! ! position ! !closed !

!-----!-----!-----------!-------------!---------!

! ! 16 ! OPEN Eng2 ! Open !Not open !

! ! !FAV command! ! !

!-----!-----!-----------!-------------!---------!

! ! 17 ! Eng1 PRV !Fully closed !Not fully!

! ! ! position ! !closed !

-------------------------------------------------

(2) Data Table to Engine 2

-------------------------------------------------

!LABEL! BIT !PARAMETER ! Status ! Status !

!66/01! !DEFINITION ! 0 ! 1 !

!-----!-----!-----------!-------------!---------!

! ! 11 ! Eng2 OPV !Fully open !Not fully!

! ! ! position ! !open !

!-----!-----!-----------!-------------!---------!

! ! 14 ! OPEN Eng1 ! Open !Not open !

! ! !FAV command! ! !

!-----!-----!-----------!-------------!---------!

! ! 15 ! Eng2 HPV !Fully closed !Not fully!

! ! ! position ! !closed !

!-----!-----!-----------!-------------!---------!

! ! 16 ! OPEN Eng2 ! Open !Not open !

! ! !FAV command! ! !

!-----!-----!-----------!-------------!---------!

! ! 17 ! Eng1 PRV !Fully closed !Not fully!

! ! ! position ! !closed !

-------------------------------------------------

** ON A/C NOT FOR ALL

10. BMC Power-up Test

A. Conditions of Power-up Test Initialization

(1) How long the computer must be de-energized:

1 sec.

(2) A/C configuration :

Same configuration as the A/C on ground.

B. Progress of Power-up Test

(1) Duration:

22 sec.

(2) Cockpit repercussions directly linked to power-up test accomplishment (some other repercussions may occur depending on the A/C configuration but these can be disregarded):

ECAM BLEED page:
* BLEED temperature indication reset to 0 deg
ENG 1 (2) BLEED and APU BLEED pushbutton:
* Light flashing.

C. Results of power-up test

(1) Test pass:

None.

(2) Test failed:

None because the opposite BMC is taking over the functions of the faulty one, use CFDS.

NOTE: If both BMC have failed, the following messages are displayed:

ECAM warning:
* BLEED MONITORING FAULT
ECAM BLEED page:
* XX are displayed in place of temperature, pressure indication and valves position.

[Rev.10 from 2021] 2026.04.01 01:05:55 UTC