AIRBUS SA Fami!

y to A319′ A320′ A321 PWl100G‐ Tl+T2

A319′ A320′ A321
TP REV 6
TECHNICAL
36-PNEUMATIC

36 Pneumatic System Presentation― PVVl100G … 2

Pneumauc System component Locatton(PW l100G)…
……… … 16
Engine Bleed System Descr plon(PVVl100G) … … … 26
BMC interfaces(NEO)… ………… …………………………… ……… 42

:l:」 罷 け 謀 濾 漁 31i『 Rttc騨 需 々Pwiィ 66ё た IM 54

LEAP) _ … …… … … … … …………… ………… …… … 60
Pneumalc System Line Maintenance(PWl100G) … ………62

TABLE OF CONTENTS Page 1

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OAIRBUS SA Fam‖ yto A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAININC MANUAL

36 PNEUMATIC SYSTEM PRESENTATION. PWI IOOG

SYSTEM INTRODUCTION
TheAirbus SingleAisle family pneumatic system supplies High Pressure
(HP) air for:
- Air conditioning,
- Wing ice protection,
- Water Tank pressudzation,
- Hydraulic reservoir pressudzation,
- Engine starting,
- Fuel tank inerting system.
High Pressure air can be supplied from three sources:
- The Engine Bleed system,
- The APU,
- A HP Ground Air source.
The pneumatic system operates electro-pneumatically and is controlled
and monitored by 2 Bleed Monitoring Computers (BMC I & 2).
There is one BMC for each engine bleed system.
Both BMCs exchange data.
ln this NEO configuration, one BMC can control & monitor both sides
when the other BMC fails.

Ul\.|36P2000000004 003 - 36 Pneumatic System Presentation- PW1100G page2

A AIRBUS SAS 2014 All rights rcsetued. Confidential and proprietary documen{

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AIRBUS SA Fam‖ yto A319′ A320′ A321 PW4100G‐ Tl+T2
A319′ A320′ A321 36-PNEUMATIC
TECHN,CAL TRAINING MANUAL

AlR WINC ICE ENGINE FuEL TANK

CONDIT10NING PROTECT10N P思議鵬 N限 蹴 員
淵。N
STARTING INERTINC

０ １ １ １ １ １■Ｊ月ロ
HP GROUND CART

SYSTEM INTRODUCT10N

UM36PZ000000004 003-36 Pneumatc System Presentaton‐ PVVイ 400C Page 3

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OA:RBUS SA Familyto A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

36 PNEUMATIC SYSTEM PRESENTAT10N― PW l100G

SYSTEM INTRODUCTION (continued) APU BLEED/EXTERNAL AIR
The left and right bleed systems are connected by a crossbleed duct.
ENGINE BLEED A Crossbleed Valve is used for their interconnection or isolation.
The Engine Bleed Air is pressure and temperature regulated before it The APU is mainly used for bleed air supply on the ground for air
supplies the pneumatic system. conditioning and for engine start.
Air is bled from an Intermediate Pressure (lP) stage (HP3) or the HP8 But APU BLEED air can also be used in flight, but limited in altirude.
stage with the High Pressure Valve (HPV) which is used for the The APU bleed supply is connected to the left side of rhe crossbleed
pneumatic regulation. duct.
The IP check valve gives protection to the IP stage from reverse flow On the ground, an HP Ground cart can be connected to the left side
when the HP valve is open. pneumatic system. The Crossbleed valve has to be opened to supply
the right side.
NOTE: Note: The Engine BleedAir System (EBAS) uses
electro-pneumatic valves.
The HP bleed is only used when the engines are at low power and for
engine effrciency the High PressureValve (HPV) is kept closed during
cruise.
The Pressure RegulatingValve (PRV) regulates the bleed airpressure.
The PRV is used as a protective shut off valve when the parameters
are abnormal. In case of EBAS electdcal failure, the PRV operates
in back-up pneumatic mode.
An Overpressure Valve (OPV) is installed downstream ofthe bleed
valve to give protection to the system if an oveqrressure condition
occurs. On this PW Engine the OPV is installed in the engine core.
The Fan Air Valve (FAV) modulates Fan discharge air through an
air-to-air heat exchanger called "Precooler" to reduce the Bleed
temperature.
BMCs are Dual Channel computers. Each BMC channelA is a full
digital channel embedding all the control and monitoring functions.
Channel B is a hardware part and back-up channel able to detect
system ovenemperature.
For the monitoring, the BMCs read pressure transducers (upstream /
downstream ofthe PRV), Precooler Differential Pressure and
downstream temperature with the Bleed Temperature Sensor (BTS).

U
Page 4
@ AIRBUS SAS 2014 Att tights reseued. Confidenfial and propietary document.

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SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
36-PNEUMATIC

Ａ
︲
Ｒ
¨
APU HP CROuND HYDRAULIC WATER TANK PACK 2
RESERVOIR
BLEED IIr csAs
WAi

蜘 SWlTCH(。 PS) .

IPCV Hpz
HYDRAULiC
→ RESERVOIR

HP8

ENG l ENG 2
SYSTEM INTRODUCT10N― ENGINE BLEED&APU BLEED/EXTERNAL AIR

UM36PZ000000004 003‐ 36 Pneumatc System P「 esentat on‐ PWl100G Page 5

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g/ ATRBUS SA Family to A319′ A320′ A321 PWl100C‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAININC MANUAL
36-PNEUMATIC

36 PNEUMATIC SYSTEM PRESENTATION- PWI lOOG

SYSTEM INTRODUCTION (continued)

LEAK DETECTION
Leak detection loops are installed along the hot air supply ducts of
the pneumatic system. The loops are made of multiple sensing
elements connected in series to the BMCs Overheat Detection System
(oHDS).
If a leak is detected, a signal is sent to the BMC I or 2 which
automatically isolates the affected area by closing the crossbleed valve
and shutting offthe engine bleed on the affected side.
The leak detection system is organized into three loops. Here are the
loops and the protected areas: - Pylon: dual loop from the precooler
to the wing leading edge.
- Wing: dual loop from wing leading edge, including the wing air inlet
supply, and belly fairing (cross bleed duct, pack supply ducts and
APU forward supply duct).
- APU: single loop at APU aft supply duct (left hand side ofthe
fuselage) from APU firewall to wheel well area.

UM36PZ000000004 003‐ 36 Pneumauc System PresentaJon― PVV1100G Page 6

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O AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100G・ Tl+T2
TP REV 6
A319′ A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAINING MANUAL

CHECK VALVE

ヽ ‐ PVLON
LEFT WINC ・ コ
●●●●●●

R:GHT VV:NG
APU ―・藤 ヽ ‐
一 ― ,一 ・・―

SYSTEM INTRODUCT10N― LEAK DETECT10N

UM36PZ000000004 003-36 Pneumatic System Presentation‐ PvVl100G Page 7

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 SA Fam‖ y to A319′ A320′ A321 PWl100G・ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

36 PNEUMATIC SYSTEM PRESENTATION― PWl100G

CONTROL&INDICATING
This scction is rclatcd to the control pancls and indications for thc
pncumatic system

CONTROL PANEL
Controls forthe pneumatic systcm arc palt ofthc AIR COND pancl
and are opcratcd flom thc ovcrhcad panel

UM36PZ000000004 003-36 Pneumatic System Presentation― PWl100G Pago 8

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AIRBuS SA Fam‖ y to A319′ A320/A321 PWl100G‐ Tl,T2
A319′ A320′ A321 TP REV 6
T匡 CHNICAL TRAINING MANUAL
36‐ PNEUMATIC

CONTROL&INDiCATING― CONTROL PANEL

UM36PZ000000004 003‐ 36 Pneumatic System Presentat on― PWl100G Page 9

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TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

36 PNEUMATIC SYSTEM PRESENTAT10N― Pヽ V H 00G

CONTROL&INDICATING(continued)
ECAM INDICAT10N
Thc pncumatic systcm indications arc displaycd On thc lo、 vcr palt or
thc ECAヽ 4 BLEED pagc:
‐HPV PRV poshions with dcHvcrcd blccd prcssurc and tcmpcraturc,
―APU blccd and crossblccd status

U
Page 10
@ AIRBUS SAS 2014 All rights rcseNod. Contidential and prcpietary document.

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OA:RBuS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2

TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

PRESSuRE ANO
TEMPERATURE
lNDICAT10NS

BLEED VALVE
POSlT10N

SD
CONTROL&INDICATING‐ ECAM INDICAT10N

UM36PZ000000004 003-36 PneumaJc System P「 osentation― PVVl100G Page ll

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O AIRBUS SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319/A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

36 PNEUMATIC SYSTEM PRESENTAT10N― PWl100G

MAINTENANCE/TEST FACILITIES
Using thc Multipurpose COntrol and Display Unit(MCDU),you Can
have access to thc Ccntralizcd Fault Display Systcm(CFDS)fault
mcssagcs oftlnc PNEUMATIC systcm BMCl and BMC2 Built ln Tcst
Equipmcnt(BITE)is standard″ pc l

UM36PZ000000004 003‐ 36 Pneumatc System Presentaton‐ PVVl100G Page 12

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A319′ A320′ A321
TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

■ ロ セ ■ ●

Ｅ ■ ■ ■ ■ 目
―

ａ
MAINTENANCE/TEST FACILITIES

UM36PZ000000004 003-36 Pneumat c System Presenlation― PWl100C Page 13

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 AIRBuS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
A319/A320′A321 36-PNEUMATIC

36 PNEUMATIC SYSTEM PRESENTATION- PWI lOOG

SAFETY PRECAUTIONS
When you do work on the aircraft, make surc that you obey all the Aircraft
Maintenance Manual (AMM) safety procedures. This will prevent injury
to people and / or damage to the aircraf't. Here is an overview ofthe main
safety precautions related to the pneumatic system.
Make sure that the pneumatic system is depressurized before you stan
the work. HP air can cause unwanted pressurization ofthe aircraft, and
injury to personnel.
Be careful when you do work on the engine components immediately
after the engine shutdown. The engine components can stay hot for one
hour

UM36PZ000000004 003‐ 36 Pnoumatc System Presentaton‐ PVVイ 400G Page 14

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O AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100C‐ 71+T2
TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

Ａ
塾〇〇
PNEUMAT:C SYSTEM MuST
BE DEPRESSuRレ ED
WARN:"0

EIEED A A A

︵
∪Ｔ
16・ c

帥館
￨ cメ ぐ ヽ H
120・ 、

il倉 ￨[
:

LO 、 HI
ξ

t
驀

SAFETY PRECAUT10NS

UM36PZ000000004 003-36 Pneumatic System Presentat on― PWl100G Page 15

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OA:RBuS SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

PNEUMATIC SYSTEM COMPONENT LOCATION

But APU BLEED air can also be used in flight, in relation to the
SYSTEM OVERVIEW altitude. The altitude can be different for each aircraft. These altitude
The Pneumatic system is used to supply High Pressure (HP) air for air
limits are givcn by the manufacturer. The APU bleed supply is
connected to the left side ofthe crossbleed duct.
conditioning, pressu zation, Fuel Tank Inerting System (FTIS), engine
On the ground, a IIP ground power unit can be connected to the left
start and anti-icing. HP air can be supplied from the two engines, the
side pneumatic system. The ght side can be supplied by opening thc
APU or an extemal ground source.
crossbleed valve.
ENGINE BLEED
The engine bleed air is pressure regulated and temperature controlled
belore it supplies the aircraft pneumatic system.
Air is bled from the engine High Pressure Compressor (HPC) stages:
HP3 via an Intermediate Pressure Check Valve (IPCV) and HP8 via
the HP Valve (HPV).
The High Pressure BleedValve (HPV) supplies airto the system when
the engine is at low power When the Intermediate Pressure (lP) bleed
is sufficient. the HPV closes.
The bleed valves are electro-pneumatically controlled.
The Pressure RegulatingValve (PRV) installed downstream the IPCV
and HPV regulates the bleed pressure.
Each Bleed Monitoring Computer (BMC) controls and monitors its
engine bleed system and the opposite.
An Overpressure Valve (OPV) is installed downstream from the bleed
valve as a protection ofthe system ifthe pressure is too high.
The engine bleed air is tempemture regulated. The hot bleed air goes
through an air-to-air heat exchanger called Precooler Fan discharge
air, modulated by the Fan Air Valve (FAV), is blown across the
precooler to keep the temperature within limits.

APU BLEED/EXTERNAL AIR

The left and right bleed systems are connected by a crossbleed duct.
A Crossbleed valve is used for their interconnection or isolation.
The APU can also be used for bleed air supply. This is usually done
on the ground for air conditioning and for engine start.

UM36C2COMPLOC02 003‐ Pneumalc System Component Localon(PW`イ 00C) Page 16

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SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2

A319′ A320′ A321
TP REV 6
TECHNICAL TRAININC MANUAL
36-PNEUMATIC

APU HP GROUND HYDRAULIC AtR wATER TANK PACK 2

RESERV01R
WAl
35.* L".o"

饉 W:NG X BLEED
VAい ノE

PYLON
D,S

HYDRAuLIC
→ RESERVOIR

HP8

ENC l ENC 2
SYSTEM OVERVIEヽ V‐ ENGINE BLEED&APU BLEED/EXTllRNAL AIR

UM36C2COMPし OC02 003-PneumaJc System CompOnent Localon(PW l100G) Page 17

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◎ ス′ dο cυ meη ι
OAIRBuS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321
36-PNEUMATIC

PNEUMATIC SYSTEM COMPONENT LOCATION

SYSTEM OVERVIEW (continued)

LEAK DETECTION
Leak detection loops are installed along the hot air supply ducts of
the pneumatic system and are connected to the BMCs. The leak
detection system is organized into three loops. Here are the loops and
the protected areas: - PYLON:the precooler outlet area,
- WING: wing leading edge and belly fairing,
- APU: APU aft supply duct (left hand side ofthe fuselage) from APU
firewall to wheel well area.

UM36C2COMPLOC02_003‐ PneumaJc System Component Localon(PW l100C)

OA′ RBυ S Sス S20,44″ rlgわ a′ and proprleraγ dOct7層 eη ι Page 18
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O AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100G・ Tl+T2
TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

//

CROSS BLEED VALVE

CHECК VALVE

PYLON
LEFT W:NC ・ ■口饉口●●●
R:GHT WiN0
APU ― ―・―・― ―・― ―

SYSTEM OVERVIEW― LEAK DETECT10N

UM36C2COMPLOC02 003‐ Pneumalc System COmpOnent Localon(PW l100C) Page 19

0ス ′
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@AIRBUS SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
36-PNEUMATIC

PNEUMATIC SYSTEM COMPONENT LOCATION

COMPONENT LOCAT10N
The primary COmponcnts ofthc pneumatic systcm arc insta■ cd on the
cngincs and in the pylons

PRESSURE REGULAT10N COMPONENTS

Thc prcssurc rcgulation componcnts on thc cngincs arc the:
‐Engine HPv
‐Enginc BLEED PS、
‐OPv
‐Bleed MOnitoing Prcssurc Scnsor(BMPS),
―Blccd Prcssurc Scnsor(BPS),
‐Dimerential Pressure Sensor(DPS)
To gct acccss,opcn thc right ran c。 、
vl and thrust rcvcrscr cowl

UM36C2COMPLOC02 003‐ Pneumalc System CompOnent Localon(PW l100G) Page 20

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@AIRBUS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
36‐ PNEUMATIC

ヽ
い

OVERPRESSuRE
VALVE(OPV)

HiGH PRESSuRE
VALVE(HPV〕
COMPONENT LOCAT10N― PRESSURE REGULAT10N COMPONENTS

υM36C2COMPLOC02 003-Pneumalo System Component Localon(PW l100G) Page 21

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 A:RBUS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321
36-PNEUMATIC

PNEUMATIC SYSTEM COMPONENT LOCAT10N

COMPONENT LOCATION(coninued)
TEⅣIPERATURE REGULAT10N COⅣ IPONENTS
Thc tcmpcraturc rcgulation compOnents arc in thc pylonsi
thc iS,
‐the Precoolcr,
―thc Blccd Tcmpclatulc Scnsor(BTS)

UM36C2COMPLOC02 003-Pneumalc System Component Loca輛 on(PW,100C) Page 22

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qiAmBUS SA Fam‖ y to A319′A320′ A321 PWl100G・ Tl+T2
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TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

OHDS PYLON′ VVING

ZONE F INTERFACE

Ｗ
Ш

Ｂ
Ｍ Ｂ
Ｐ Ｓ
Ｓ
FIREWALL PYLON′ ENCINE FAV

Ｐ
lNTERFACE ACTUATOR
PRESSuRE PORT FOR FAV
MuSCLE PRESSuRE
BLEED A!R
OUTLET
FAN AIR
OuTLET

′
 ノ
PRESSuRE
PORT FOR OPS
BMPS: Aleed Monrloring Pressure S€nsor
BPSr Blaed Pressure Sensor
BLEED AIR DPS: Difrerentral Pr€ssure sensor
FAN AIR
INLET INLET OHDS: OverHcat Detection System
PCE: Precooler Erchanger

COMPONENT LOCAT10N‐ TEMPERATURE REGULAT10N COMPONENTS

UM36C2COMPLOC02 003‐ Pneumalc System cOmpOnent Localon(PW l100C) Pago 23

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OAIRBUS SA Fami:y to A319′ A320′ A321 PWl100G・ Tl+T2
A319′ A320′ A321 36-PNEUMATIC

PNEUMATIC SYSTEM COMPONENT LOCATION

COMPONENT LOCATION (continued)
OTHER COMPONENTS
The Crossbleed valve is in the forward section ofthe lower fuselage
belly fairing area.
The access to the HP ground connector is through a small aqcess door
on lhe lower fuselage belly fairing.
The APU bleed valve is on the APU.
The APU supply duct is installed along the Ieft hand side ofthe
fuselage to the wheel well area and is connected to the crossbleed
duct in the forward belly fairing area.

UM36C2COMPLOC02 003-PneumaJc System Component Loca,on(PW`100G) Page 24

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&ArRBUs SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

APU COMP

APU SuPPLY DuCT ヽ

APU 8LEED VAIVE

CROSSBLEED
VALVE

COMPONENT LOCAT10N‐ OTHER COMPONENTS

UM36C2COMPLOC02 003‐ Pneumalc System Component Localon(PW l100C) Page 25

0 4rR3υ S Sス S20,イ ス″rlghrs resen/ed Conndenrfa′ and ρrop″ erary docυηeni
O AIRBuS SA Fam‖ y to A319′A320′ A321 PWl100C‐ ■1+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

ENGINE BLEED SYSTEM DESCRIPT10N

B2SCOPE

CAUT10N:MODULE TACGED B2 SCOPE

BE Aヽ VARE THAT ONLY AV10NICSノ ELECTRICAL TOPICS
SHOULD BE LEARNED FOR A T2 COURSE
GENERAL
Thc Enginc BleedAir System(EBAS)supphCS prcssurc and temperaturc
rcgulatcd airflow from each enginc lo thc air system users
During nomal opcration,cach cngine bleed systcm is isolatcd from
adlaccnt system by the Crossbleed valvc;cxccpt dunng 2nd enginc
starting using air blcd from lst startcd cngine,CrOssblccd valvc opcncd
or undcr APU Blccd
Thc prcssure regulatiOn system is controncd and monitored by two Blccd
Monio‖ ng Computcrs(BMCS)
As compared to A320 CEO,
t

hc NEO engine has higher blccd air tcmpcratures during

H
igh Prcssurc(HP)Operation,lower air prcssurc during lntemediatc
Prcssurc(IP)
0
pcration,lower fan prcssurcs for cOOling air flo、 v
S

upply and limited space for installation duc to ne、 v pylon cOnnguration
T
O
achicve bcttcr pcrfonnancc rcquircmcnts a ncw clcctro― pncumatic blecd
air systcm is dcsigncd for A320 NEO

UM36DlPW4100004_003-Engine Bleed System Desclplon(PWl100G) Page 26

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AIRBUS SA Fam‖ y to A319/A320′ A321 PWl100C‐ Tl+T2
A319′A320′ A321
TP REV 6
TECHNICAL TRAINING MANUAL
36‐ PNEUMATIC

EBAS 4 ￨

ENG 2
BLEED A:R SYSTEM.
EBAS 2
:
l

l
1

PREC00LER ― ―
r―
― ― ― ― ―

―― ― ¨― ― ―
r―

TEMPE‐ TEMPE‐

¨
RATURE RATURE

¨
SFNSOR SCNSOR

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FUNCT10N

CHA
LH MAlN
CH A
国 iCH A
LHIBACKUP
CH A
MAIN
CTL

ENG l
lP3 HP8
￨ ￨ l

PWl100■ M [__¨ ______ト

￢ :

B2SCOPE&GENERAL

UM36DlPVV1100004_003-Engine Blood System Descriplon(PWl100C) Page 27

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O AIRBUS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

ENGINE BLEED SYSTEM DESCRIPTION

BMC
Normally BMC I Channel A does all the control and monitoring ofthe
LH EBAS and BMC 2 Channel A the RH EBAS.
Each BMC channel A controls torque-motor and solenoid for the
electro-pneumatic valves, monitors sensors. As both BMC interface, each
one is capable to control both sides.
The channel B is a fully hardware part able to detect the system
overtemperature: Electrical Protection Function (EPS). This detection is
fully independent from software part.
Each BMC reports the failures independently ofeach other

UM36DlPVVl100004_003‐ Engine Bleed System Descr plon(PVVl100C) Page 28

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SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAININC MANUAL
36‐ PNEUMATIC

TO THE uSERS )

￨と BLEED易 ‖ξξtsTEM l

I EBes z
￨

t_ ￨

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TEMPE‐

呻
RATURE

¨
SENSOR

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PWl100」 M

BM(

UM36DlPWl100004_003-Engine Bieed System Descriplon(PWl100C) Page 29

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9,ArRBus SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

ENGINE BLEED SYSTEM DESCRIPTION

HPC

HP VALVE (HPV)
The engine air bleed pressure is pneumatically regulated by the HP
Valve (HPV) when air is supplied by the High Pressure Compressor
(HPC) stage or directly by the Pressurc Regulating Valve (PRV) when
the air is supplied by the Intermediate Pressure (lP) HPC stage.
- Intermediate-pressure service port: lP is defined by HP3.
High-pressure service pon: HP is defined by HP8.
The HPV lets air to be bled from the

ngine HP stage at lower power settings.

I
t is a pressure regulating and
S

hut-offvalve with a butterfly

c
losure elemen(. lt regulates thc pressure ofthe bleed air between l5
and 65 psig. With the Solenoid energized, the minimum upsteam
muscle pressure needed to operate the valve is l5 psig. When the
solenoid is not energized, the HPV is commanded to the full closed
position.
When the solenoid is energized but without pressure in the valve body,
the HPV stays closed.
The HPV is forced to close when the PRV is closed. The valve has a
manual ovenide and test port for pneumatic test in-situ.

IP CHECK VALVE (IPCV)

An lntermediate Pressure Check Valve (IPCV) lets air to be bled from
the engine tP stage. It is closed when air is bled from HP stage. The
purpose ofthis IPCV is to allow the flow from IP stage and avoid the
reverse flow from either the HP port or the pneumatic manifold.

UM36DlPWl100004_003‐ Eng ne B eed System Desc百 plon(PWl100G) Page 30

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OAIRBuS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′A320′ A321
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

い旧
TO THE uSERS
ENG 2
BLEED A:R SYSTEM
EBAS 2

ｒ ｌ ｌ ｌ ■ ︱ ︱ ︱
PREC00LER

TEMPビ ‐ TEMPЁ

¨
RATORE RATuRE

¨
SENSOR SENSOR

Ｗ¨
1画

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T0
SAV‐
HDW HOW
ELEC ELEC

一
PROTECT PROTECT

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FUNCT10N FU"CT1011

¨一
︲
ｃ
Ｈ
Ａ¨
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CH A CH A CH A
LH MAIN
CTL
BMCl

‖P(― ヽLVE(HPV)&IP(1‖ 1(Kヽり

HPヽ ち ヽLV E(IPCV)

UM36D Page 31
OAiRAUS SAS 2074 All tights Bseved. Confidential and prcNietary document.
OAIRBuS SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′A320′ A321
TECHNICAL TRAININC MANUAL
36-PNEUMATIC

ENGINE BLEED SYSTEM DESCRIPTION

PRESSURE REGULATING VALVE (PRV)

The Pressure RegulatingValve (PRV) is a 4 inch diameter butterfly valve,

installed downslream ofthe IPCV and HPV.
It regulates the pressure ofthe bleed air at 42 ,t 2 psig in normal dual
bleed operation (50 + 2 psig in single bleed operation).
Its setting is modulated by the electric command on the torque-motor.
When the torque-motor is de-energized, the PRV is commanded to the
full closed position.
When the torque-motor is energized but without pressure, the PRV stays
qlosed.
With the torque-motor energized, the minimum upsteam muscle pressure
needcd to operate the valve is 15 psig.
The PRV operates as a shut offvalve when abnormal conditions occur.
The valve has a manual overide and test port for pneumatic test in-situ.

OVERPRESSURE VALVE (OPV)

The C)verpressure Valve (OPV) downstream ofthe PRV in the engine
core, protects the system against damage ifoverpressure occurs.
It operates pneumatically. The OPV, normally in springJoaded open
position will be fully closed ifbleed pressure reaches 90 psig.
The valve has a manual override and test port for pneumatic test
in-situ.

U
Page 32
O A/RAUS SAS 20',4,All rights rcserved. Conlidential and prcNietary document.

ヽ１ ′
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SA Familyto A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
TECHNICAL TRAINING MAN∪ AL
36-PNEUMATIC

一
  Ｍ    一
TO THE USERS
ENG 2

EBAS 2

PREC00LER

PRESSURE REGULATING VALVE(PRV)― ()VERPRESSUREくヽ LVE(OPV)

UM3604PVVl100004 003-Engine Bieed System Desclplon(PWl100G) Page 33

0ス IR3υ S SИ S 20′ イス″ ed Cο ηrldenfla′ and proprlera″ dOcυ ηθη′
"Is reSe″
“
OAttBuS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl● T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

ENGINE BLEED SYSTEM DESCRIPTION

PRESSURE SENSORS
BLEED MONITORINC PRESSURE SENSOR(BMPS)
Thc Blccd Monitoring Pressure Scnsor(BM PS)iS uSCd to pcrlorn
blccd polt s、 vitching function it is also uscd to cstimatc thc position
ofthe HPV buttcrny and lo monitorthc HPV and the PRV

BLEED PRESSURE SENSOR(BPS)

Thc Blccd Prcssurc Scnsor(BPS)iS inStaned downstrcam thc PRヽ 4
1t providcs to BMC thc acmal blccd air pressurc dclivcrcd through
thc PRヽ 4 This scnsoris also used by thc BNIC ror systcm monitoring
(。 VCrprcssurc and low prcssurc alanlls)and tO mon■ Orthc pOsi10n
ofthc OPV buttcrny

DIFFERENTIAL PRESSURE SENSOR(DPS)

Thc D
l

fFcrcnial Plcssure Sensor(DPS)cnSurcs thc rcvcrsc■ ow protcclon

by scnsing thc difFcrcntial prcssurc bct、 vccn Precooler hOt sidc inlct
and outlct it also providcs to thc Bヽ 4C an indication orthc PRV and
OPV posltiOn

U)- Page 34
@ AIRBUS SAS 2014 All rights reserved. Confidential and proprietary documenL

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ヽ１ ︰′
 、 ノ

ヽ１ノ

ヽ ノ
・
  一

O AIRBUS SA Fami!y to A319′ A320′ A321 PWl100G‐ Tl+T2

TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL

TO THE USERS
ll
ENG 2

¨    一
l
EBAS 2
:_

PREC00LER ¨
:『
●￨‐ ●● ￨ : 1 1

Ｃ
Ｈ
Ａ
田ｍ
[
CH A
Ｎ

PRESSURE SENSORS― BLEED MONITORING PRESSURE SENSOR(BMPS)… DIFFERENTIAL PRESSURE SENSOR(DPS)

UM36DlPVV`100004_003‐ Engine Bleed System DescnptiOn(PWl100G) Page 35

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"ο
(/ ATRBUS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAININC MANUAL
36-PNEUMATIC

ENGINE BLEED SYSTEM DESCRIPTION

BLEED TEMPERATURE SENSOR (BTS)
The dual Bleed Temperature Sensor (BTS) installed downstream the
Precooler provides to the BMC the actual EBAS temperature.
The BMC uses EBAS temperature to position the Fan Air Valve (FAV).
The wiring connected to channel A ofthe BTS is fully segregated from
the wiring connected to channel B.
Both BMCs interchange temperature measurements and can carry out
both sides temperature regulation.
This dual sensor is also used by the BMCs for system monitoring
(overtemperature and low temperature alarms).

NOTE: Channel B ofone BMC is connected to Channel A of the other

BMC, so that in case of loss of temperature monitoring and
control in Channel A ofone side, the opposite controller can
take over control ofthe whole EBAS.

UM36D4PVVイ 400G04_003-Eng ne Bleed System DescHplon(PVVイ 400G) Page 36

0ス ′RBυ S S4S 20チ イス″″夕,rs rese″ oこ Confldenlla′ and prOprlerar/dOCυ mena
、ノ

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@ArRBUs SA Fam‖ y to A319′ A320′ A321 PWl100C・ Tl+T2
TP REV 6
A3197A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAINING MANUAL

TO THE uSERS
1

ENG 2 1
J
BLEED A:R SYSTEM I
l

PREC00LER
i r 1-― ―――――――■――――――――■ :

: 〕 l ￨― ― ―― ― ― ― ― ¨ ― ― ― ― ― ― ― ‐11
「
: : [

[ :
: :

BLEED TEMPERATURE SENSOR(BTS)

U
@ AIRBUS SAS 2014 All tights rcseNed. Confidential and proryielary document.
O AIRBUS SA Family to A319′ A320′ A321 PW1100G‐ Tl+T2 TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANuAL

ENGINE BLEED SYSTEM DESCRIPT10N

TEMPERATURE REGULAT10N
FAN AIR VALVE(Rミ )
The FAV pneumatica‖ y rcgulatcs thc fan ailno、 v to thc Prccoolcr for
blccd air telnperature regulation
Thc FAV buttcrny valvc acmator rOdヽ adlusted by the BMC vね a
torquc motor scP/o― control depending on BTS input
Thc BMC sct pointis 200° C(392° F)in nonllal opcrations and 160° C
(320° F)in Climb and H。 ld with 2 bleeds andヽ Ving Anti‐ Icc(WAl)
ofF
ヽ
Vith nO clcctrical po、 vcr and cnough musclc pressure,thc FAV valvc
is ftllly opcn
Thc valvc has a tcst por fOr pncumatic tcstin‐ situ

PREC00LER EXCHANGER
Thc Prccoolcr is a stainlcss steel and nickcl anoy ai「 to‐ air hcat
cxchangcr
lt cools do、 vn thc llot air supplicd f10m thc cnginc HP comprcssor
stagc by a hcat cxchangc proccss、 vith cooling n。 、
v taken frolll the
cnginc ran

UM36DlPWl100G04_003-Engine Bieed System Desclplon(PVVl100G) Page 38

0ハ ′
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9iATRBUS SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319′A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAININC MANUAL

TO THE USERS

1_

200° C(392・ F)

PREC00LER

HP3 HP3 :

■P∵ ■ ,
,

i I
‐

TEMPERATURE REGULAT10N― FAN AIR VAし ヽ/E(「 tV)&PREC00LER EXCHANGER

UM36DlPWl100004_003‐ Engine Bleed System Descriplon(PWl100G) Page 39

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@,alRBUS SA Familyto A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321
TECHNICAL TRAINlNG MANUAL
36-PNEUMATIC

ENGINE BLEED SYSTEM DESCRIPTION

PROTECTION― ISOLAT10N
Thc PP/opcratcs as a shut― ofF valvc ltis commandcd lo c10sc in thc
fo‖ O、ving cOnditions:
-Ovcr‐ tcmpcraturc downstrcam ofthc Prcc001cr(BTS)
257° C(495° F)く T 270° C(518° F)during 55s,
270° C(518° F)く T 290° C(554° F)for 15s,
T>290° C(554° F)for 5s
-Ovcrprcssurc do、 vnstrcam oFthc PRV>60■ 3 psig at BPS,
―Enginc arc(conscqucnce ofcrew action on thc ENG FIRE P/B),
‐Lcak dctcction in py10n/、 ving76,sclagc ducts surrounding arcas,
―APU blccd valvc not closcd`と APU BLEED P/B sclcctcd:
Dcpcnding on thc Crossfeed Blecd Valvc(CBV)positiOn,only onc PRV
(lert cnginc PRV if CBV is closcd)Or bOth(if XBICCd is opcn)
―Rcvcrsc flow dctcctcd by DPS,
‐ENG BLEED P/B selcctcd OFF or ENG notrunning,
―Associatcd Starcr Air Valvc(SAV)not C10SCd,
―HPV fdilcd opcn,
―Dual BTS channcls failed

UM36DlPWl100004 003-Engine B eed System Descttplon(PVVl100C) Page 40

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"eη

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A319′ A320′ A321
SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

TO THE uSeRS

PREC00LER

¨
¨Ｓ
Ｅ
Ｎ
Ｓ
。
Ｒ
Ｗ
   
 ЮＷ

F:RE P′ B
LEAK
APU BLEED
ENC NO RUN
ENG BLEED P′ 8 0FF
SAV NOT CLOSED
REVERSE FLOW DPS
HPV FAILED OPEN
DUAL BTS CHANNEL FAILED

PROTECIT10N‐ ISOLAT10N

U page 41
@ A/RBUS SAS 2014 All tights reseNed. Contidential and propietary documen[
 AIRBUS SA Fam‖ y to A319/A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321
36-PNEUMATIC

BMC TNTERTACES (PWl 100G)

BMC
The pneumatic system uses 2 identical controllers with a microprocessor
and command channelA and a back-up channel B. Each channel is
supplied by a different 28V DC bus bar
Both Bleed Monitoring Computers (BMCs) will work as
MASTER-/SLAVE so long as the ARINC429 cross communication is
working properly.
lf one ARINC429 bus is lost from one BMC to the other. the BMC
receiving no data will take over control and would inform to the opposite
BMC.

UM36F1000000003 003‐ BMC interFaces(NEO) Page 42

0/1′ R3υ S Sス S20′ イス″rlgars resθ ″ed Cο ηndenlra′ and ρrop77eraγ dOcυ ηθη′

ヽ︰′
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ヽ１′
&,ArRBUs SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

801PP
Ess Bus

ACSC:Air Conditioning system Contro‖ er CMD:Command Elu: Engine lnterlace Unit

APU:Auxl,ary POwer unit CTRLi Control PRV: Pressur€ R€guhnng Valve
BPS:Bleed Pressure Sensor ●LRB:Data Lcading Routing Box SOAC: Systcm Dala Acquasilion Conccntralor
8TSi Bleed Temperature Sensor DMu:Data Management unit
CFDiU:Centralized Fault Disp:ay interface unit ECB:Electro口 ,c Control Box

BM(1

UM36F1000000003 003-BMC interfaces(NEO) Page 43

0A′ R3υ S SAS 20′ イス″71gわ rs rese″ ed Conrldθ η″a′ and ρrOprletar/dOCυ ment
O AIRBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 1 36-PNEUMATIC

BMC TNTERFACES (PWl 100G)

EIU
The Propulsion Control System (PCS) informs both BMCs via both
Engine Interface Units (EIUs) when engines start/run.
The Electronic Engine Conkol (EEC) will need information relative to
the Aircraft Environmental Control System (ECS) from the EtU ARINC
data bus as system bleed pressure, bleed and anti-ice configuration.
The ElUs receive positions ofENG BLEED P/Bs ON, APU BLEED P/B
OFF, Crossbleed valve status.

UM36F1000000003 003‐ BMC nterfaces(NEO) Page 44

04′ R3υ S SAS 20′ イス″rlgわ rs resen/oこ ゎ′and ρroprlera″ dο cυ menl
Cο ηrldeη ι

〕
 、１ノ

ヽ１ ′
OAIRBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

Bleed Monitoring Bleed Monitoring

Computer(BMC)1 Computer (BMC) 2
001 PP
ESS BuS CH‐ A CH -A

P′ esws

ACSC: Air Conditionang System Controller CMO: Command EIU: Engine lnterface Unit
APU: Auriliary Power Unit CTRL:Cont.ol PRV: Pressurc Retulalrng Valve
BPS: Bleed Pressure S€nsor DLRE: oata Loading Routing 8ox SDAC' Syslem Data Acquisilion Concenlralor
8TS: Bleed Temperature Sensor DMt,: Deta Mahagement unat
CFOIU: Centralized Faull Display lntenace Unir ECB: Electron,c Conlrol Box

EIU

UM36F1000000003 003‐ BMC nteraces(NEO) Page 45

04′ RBυ S SAS 20′ イス″rlghts reseryed Conrldenrfa′ and proprletar/dOoumo″ ′
OAIRBUS SA FammytO A319′ A320′ A321 PWl100G・ Tl+T2
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

BMC INTERFACES(Pu/1looG)
DATA LOADING
vccn thc onboard
The up and do、 vn data loading system is an intcrface be●
computcrs as BMCs and thc ground‐ basc data proccssing stations
For data loading purposcs,thc BMC i Channcl A is conncctcd to Data
Loading Routing Box(DLRB)Thc BMC 2 Channel A will bc loadcd
through BMC I Channel A Thc BMC 2 will bctlploadcd thlough thc
crosstalk bus from thc BMC l once thc Bヽ lC l has been ftllly uploaded
flom thc data loader

UM36F4000000003 003-BMC interfaces(NEO)

Page 46
0 AIR3υ S Sス S20イ イス〃rlghts/ese2od Cο η a″ d prOpη eraγ dOcψ ηe″ ι
"denrra′
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Al贈 騰US SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAINING MANUAL 36-PNEUMATIC

301PP
Ess Bus

ACSC:A r Conditioning system Contro ler CMDi Command Elu: Engine lnierlace Uoit
APU:Aux,お ary POwer unit CTRL:Control PRV: Pressurc Regulating Vatve
BPS:Bleed Pressure Sensor Oし RB:Data Loading Routing Box SDAC: System OalB Acquisilion Concentrator
BTS:Bleed Temperature Sens。「 DMU:Data Management un"
CFDlU:Centralized Fault Dispiay interrace un t ECB:Electronic Controt Box

DATA LOADING

UM36F1000000003 003-BMC Interfaces(NEO)

Page 47
0ス ′
R3υ S SAS 20′ イス″r1911rs resen/ed Cο ηrldeη lla′ aη σρroprjelaγ docυ ηeη r
O AIRBUS SA Fami!y to A319′ A320′ A321 PWl100C‐ Tl+T2
A319′ A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAINING MANUAL

BMC INTERFACES (PWl 100G)

ACSC
The BMC inform the Air Conditioning System Controller (ACSC) on
the precooler outlet temperatue for pack flow calculation. The bleed
pressure Sensor (BPS) and the wired Crossbleed valve position are used
for Pack hlet Pr€ssure Sensor (PIPS) monitoring.
The BMC send a discrete input ofits Pressure Regulating Valve (PRV)
position.
Another discrete signal informs about the precooler delivered bleed
pressure.
The ACSCs input the BMCs for Pack l12 P/B SW position, Pack Inlet
Pressure and wing anti-ice valves position.

UM36F1000000003 003‐ BMC lnterFaces(NEO) Page 48

0A′ RBυ S S/1S20,イ ス″rlghrs rese″ θd Cο ηndentra′ and proprlela″ dooυ ηent

ヽ １ ／
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ヽ１ ノ
OAIRBUS SA Fami!y to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

Bleed Monitoring
Computer (BMC) I
801PP
ESS BuS CH.A

P′ 日SWs

12く L PRVく 60 PSi 12く R PRVく 60 PSl

APU Vに V CTRL i CMD

APU VLV` POS

ACSC: Air Condtoning Syslem Controller CMDiCommand EIU: Engan. lnlerface Unil
APU: Auxiliary Power Unit CTRL:Control PRV: Pressure Regulaling Valve
BPS: Bleecl Pressure Sensor DLRB:Data Loading Rouun9 8ox SDAC: System Data Acquisilion Concentrator
8TS: Bleed Temp€ralure Sensor DMu:Data management unit
CFOIU: Cenlralized Fault Display lnterlace Unat ECB:Electronic Control Box

ACS(1

UM36F1000000003 003‐ BMC lnterFaces(NEO) Page 49

0/11R3υ S Sス S20イ イス″rlgars resθ ′
νθd Conrldearla′ and ρroprletar/dOCumθ ′1
QrNnaus ￨
SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAINING MANUAL

BMC INTERFACES(PⅥ /1100G)

DTSPI,AY

The BMCs I and 2 tmnsmitARINC signals to the System Data

Acquisition Concentmtor (SDAC) for monitoring, fault indication,
waming and data recording purposes by the Flight Waming Computer
(FWC), Electronic Instrument System (EIS) and Digital Flight Data
Recording System (DFDRS).
The Centralized Fault Display Interface Unit (CFDIU) is connected to
the BITE ofthe BMCs to centralize the pneumatic system data for
maintenance via the Multipurpose Control and Display Units (MCDUs),
printer and Aircraft Communication Addressing and Reporting System
(ACARS).

υM36F1000000003 003‐ BMC lnterfacos(NEO) Page 50

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A319′ A320′ A321 TP REV 6
TCCHNICAL TRAINING MANUAL
36-PNEUMATIC

ComputeF(BMC)1 Computer ([
804PP
ESS BuS CH‐ A clt -A

P′ 8SWs

島 ,理
12く L PRVく 60 PSI 12く R PRVく 60 PSi

APu VLV CTRL l CMD

APU VLV , POS

CH・ B

ACSCr Air Condilioning System Controtter CMD:Command EIU: Engrne lnt€rtace Unit
APU: Auiliary Power unil CTRL: Control PRV: Pressure Regulating Valve
BPS: Ble€d Pressu.e s.nsor DLRB: Data Loadin! Routing 8ox SOAC: Sysi€m Oata Acquis(ion Concentrator
8TS: Eleed Temperature Sensor DMU: oata lvlanagemcnt unit
CFDllr: Centralized Fault Oisp,ay lnte.face Unit EcB: Electronic contrct Bor

DISPLAY

UM36F1000000003 003‐ BMC lnterfaces(NEO) Page 51

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 AIRBUS SA FammytO A319′ A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 TP REV 6
36-PNEUMATIC

BMC TNTERFACES (PWl 100G)

APU
The APU/Electronic Control Box (ECB) system sends to the Engine
Bleed Air System EBAS/BMC the information about APU bleed valve
position in order to command the PRV to close when APU BLEED P/B
is ON.
The EBAS transmits to the ECB information related to the APU Bleed
Valve open Command in order to provide APU Bleed valve control in
when APU flow is required.

UM36F1000000003 003-BMC nterraces(NEO) Page 52

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TP REV 6
A319′ A320′ A321 36‐ PNEUMATIC
TECHNICAL

Bleed Monitoring
Computer (BMC) 2
”Ｂ

P′ BSWs

P′ BSWS
VALVES
SCNSORS
8PS‐ BTS

ACSC:Air Conditioning system cOntro‖ er CMD:Command EIU: Engan€ lnlerface Unrt

APU:Auxliary Power unit CTRL: Control PRV: Pressure Regulalrng Valve
BPS:Bleed Pressure Sensor OLRB: Data Loading Routing Box SDAC: System Data Acquis on Concentrator
BTS:Bieed Temperature Sensor oMlJ: oata Managehent unlt
CFDlU:Centralized Fault Oisplay interrace unit EC8: Electronic Control Box

APU

UM36F1000000003 003-8MC nterfaces(NEO) Page 53

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@,AtRBUs SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
36-PNEUMATlC

PNEUMATIC LEAK DETECTION SYSTEM D/O

ROUTING
The leak detection system is used to detect leaks in the vicinity ofthe
packs, wings, pylons and APU hot air ducts.
There are two independent loops as redundancy in both pylons and both
wing sides.
The APU hot air duct is monitored by a single loop.
Protected areas with double loop for:
- Engine I and Engine 2 pylons,
- RH wing and pack 2,
- LH wing, pack I and mid fuselage APU duct.
Protected areas with single loop for:
- APU duct.

NOTE: Each loop consists ofsensing elements connected in series.

Both extremities ofthe overheat detection loop are connected
to the BMC.
For CFM LEAP only, thc Engine Nacelle Corc Temperature sensor
measures the temperature within the core cowling near the ECS ducting.
This signal is used to indicate an undercowl leak (overheat and./or burst
duct events).

UM36D4000000003 002‐
― Pneumalo Leak Deteclon System D/0(NEO) Page 54
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@AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100G・ Tl+T2
TP REV 6
A319′A320′ A321
TECHNICAL TRAININC MANuAL
36-PNEUMATIC

On CFM LEAP ohly

ll Corc Tenp.rotur. s.nsor

CROSSBLEED
VALVE

BLEED PRESSuRE BLEED PRESSURE

RECULATED VALVE REGULATED VALVE

APU BLEED
CHECK VALVE

DETEcl■ ON LOOPS
n‐ ………… ⅢDoub!e204° C(399° F)
Pyl●
Lり illg L pack Ⅲ ・ bOuble 124° C(255° F) APU 8LEED
一 LOAD VALVE
R wing R Pack・ “DOub!・ 124° C(255° F)
APυ Sing:● 124° C(255° F)

BLEED DUCTS

ROUTIN(i

UM36D4000000003 002‐ Pneumalc Leak Deteclon System D′ 0(NEO) Page 55

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9, AIRBU$ SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
36-PNEUMATIC

PNEUMATIC LEAK DETECTION SYSTEM D/O

DETECTION LOGIC
Both Bleed Monitoring Computers (BMCs) permanently receive signals
from the leak detection loops primarily tested at power-up.
They exchange data via an ARINC bus for the double loop detection.
Each BMC channel A normally controls its side engine bleed air system,
so monitors the OverHeat Detection System (OHDS).

NOTE: The wing and pylon loops A are connected to one BMC and
wing and pylon loops B to the other BMC.
The crosstalk bus allows wing leak wamings to be activated
through an AND logic. The APU loop is connected to BMC I
only.

UM36D4000000003 002-Pneumauc Leak Detection System D′ 0(NEO) Page 56

0ハ ′R3υ S SAS 20,`ス ″rlgゎ ls resen/ed Cο ηrldeη lla′ and proprerar/dOCυ ″θηr

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OAIRBUS SA Fammyto A319′ A320′ A321 PWl100G‐ Tl● T2
A319′ A320′ A321 36‐ PNEUMATIC
TECHNICAL TRAINING MANUAL

Bleed Monitoring Compute. (BMC) 1

DETECT10N LOCIC

UM36D4000000003 002-Pneumalc Leak Deteclon system D′ 0(NEO) Page 57

@ AIRBUS SAS 2014 All tights reseNed. Conlidential and proprietary documenL
O AIRBuS SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A3197A320′A321 36-PNEUMATIC
TECHNICAL TRAINING MANυ AL

PNEUMATIC LEAK DETECTION SYSTEM D/O

WARNING CONSEQUENCES NOTE: ApU and cross bleed (X-BLEED) valves do not close rluring
Main Engine start (MES)'
The ENG BLEED FAULT light comes on when a leak is detected by the
wing loops A and B or by the pylon loops A and B.
For CFM LEAP Engine only, it illuminates ifFan Duct Burst is detected.
The APU BLEED FAULT light comes on when an APU duct leak is
detected.
When an overheat condition is detected by both loops, the following
ale(s are generated for the affected zone:
- AIR ENG l(2) LEAK for a leak/overheat detected in the Pylons,
- AIR L(R) WING LEAK for a leak/overheat detected in the Wings,
- AIR APU LEAK for a lealdoverheat detected in the APU line,
- AIR APU LEAK IAPU LEAK FED BY ENC] for a leak/overheat
detected in the APU line and the leak is automatically isolated.
A new waming alert has been introduced on the A320neo, the AIR
BLEED LEAK to isolate a bleed leak in the opposite pylon to the
operative bleed with manually open Crossbleed Valve.
Thc failurc ofa single loop for Pylon or Wing is idcntified by a
MAINTENANCE message displayed on the STATUS SD page.
Dual engine loop failure is identified by the AIR ENG l(2) LEAK DET
FAULT and is NO GO.
lfone BMC is failed, the other BMC takes over monitoring ofthe bleed
syst€m and triggers the ECAM wamings.
The aircraft dispatch is for l0 days with the BMC I inoperative for
non-ETOPS operations provided that the Engine I Bleed Air System
(EBAS I ) is considered inoperative and the APU leak detection loop is
considered inoperative.

LEAK CONSEQUENCE
A detected leak will close associated valves.as shown on the table.
These valves are automatically controlled to close ifthey were open.

UM36D4000000003 002‐ Pneumauc Leak Deteolon System D′ 0(NEO) Page 58

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Q;atnsus SA Fami:y to A319′ A320′ A321 PWl100G‐ Tl+T2

TP REV 6
A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

WARN工 NC MESSACES:
Rctcted す
o leak:

▲ / ▼ Relo,ed to o,her foi:ures(c g OVerheat′ overpressurc ):

Eお

`1 1LEEd STARI
WARN工 NC MESSA● [S:
Rclotedす o lcck:

36 22 01 1 pybn teakDet∝ tbn System

WARNINe MESSA● E(ι FM LEAP onlソ (★ )):

362201E
Rebted to Fcn Ouct Burst:

, 2

MlEl be opo-dtve

ME Fi,txe ol otF bop & olp or 000, pla.r s irfialed ry a MANI EN/tlCE
DEssag€ @b|,edo,r r,,e SIAIUS SD p6ge
M.btun J640{,lrf SIEEO fd,{0lIEN rt C€Uessage

M,NIMUM EQUIPMENT LIST(MEL)

FNG l FAじ LT ENG 2 FAULT APU LEAκ

■YPに OF FAILURE (PYLON LEAK OR (PVLON LEAК OR (EXCEPT DuRING
ENG X
HOT AIR LEAK
LH WlNG LEAK) RH WINC LEAК } ENO[NE STAR■ )

PRV l ‐PRV 2
AUTOMAT!C RESPONSE7 ANT:■ CE VALVE l ‐ANTllCE VALVE 2
‐APU 8LEED VALVE
‐
PRV X
APu BLEED VALVE
VALVE CLOSuRE X BLEED VALVE(llt AuTO) ‐X BLEED VALVE“ N Au70)
‐X BLEED VALVF(,N AUTO)
(aV。 ￨● 。penin9 XBlood Valvo)
APU BLEED VALV嘔

VARNING
ヽ CONSEQUENCES― LEAK CONSEQUENCE

UM36D4000000003 002‐ Pneumalc Leak Deteclon system D′ 0(NEO) Page 59

0ス IRBυ S MS 20′ イス″rrghrs rese″ ed Conた 0"tla′ and ρroprlerar/dOcυ mena
OA:RBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321
36-PNEUMATIC

PNEUMATIC SYSTEM CONTROL AND INDICATING(3)(PW l100G/CFM LEAPlA)

Pneumatic System― Ceneral(2)

HP Cround Cart Bleed Supply(2)

APU Bleed Supply(2)

APU Bleed leak(3)

Engine Bleed supply(2)

Engine Bleed― HP/1P Switching(3)

Engine l Bleed Fauit(HPV Stuck OPEN)(3)

M/ing Bleed leak(3)

UM36:ILEVEL0301 001-Pneumauc System Controi and lndicaang(Pvvl100G′ CFM LEAP) Page 60

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 AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100G‐ ■1+T2
A319′ A320′ A321
TP REV 6
TECHNICAL
36-PNEUMATIC

THIS PACEINTENT10NALLY LEFT BLANK

UM36 1LEVEL0301 001‐ Pneumalc System cOntroland lnd calng(PWl100G′ CFM LEAP) Page 61
0ス ′RBυ S SAS 20イ イス″77gわ ts resen/oこ Cο ηndonlla′ and ρゅprlela″ docυ
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C AIRBけ S SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2
36-PNEUMATIC

PNEUMATIC SYSTEM LINE MAINTENANCE (PWl l00G)

power setting and to open the Crossbleed valve in order to supply
MEL ITEMS both sides from the opposite EBAS which is operative.

EBAS MEL
The aircraft dispatch is for l0 days with the Engine Bleed Supply
System inoperative on one side provided that:
- The associated bleed is isolated by setting the ENG BLEED P/BSW
to OFF.
- The X-BLEED valve is manually open to supply both sides,
- The speed brakes are operative.
For an Extended Range Twin Engined Aircraft Operations (ETOPS)
flight, Auxiliary Power Unit (APU) Bleed should be available.
One Engine BleedAir System (EBAS) remaining available, it supplies
both sides for Wing Anti-lce (WAI) and air conditioning.
However, there is limitation on ,A320 NEO compared to ,A.320 CEO
due to lower capacity of the heat exchanger in case ofsingle bleed
operations.

NOTE: Only one PACK can be supplied. Thercfore, the associated

operational procedure will ask to switch one PACK off.
HPV FAILURE
Failed closed High Pressure Valve (HPV) can lead to low bleed
pressure or low bleed temperature when engine is at low power settings
(in idle or in holding conditions).
HPV failed in open position, leads to Bleed overpressure or Bleed
overtemperature identified by AIR ENG l(2) BLEED FAULT.
ln case of failure ofone HPV the aircraft can be dispatched for t0
days with the valve secured closed.
The consequence ofhaving the HPV secursd closed is that the bleed
air from the lntermediate Pressure (lP) port will be insufficient at low
engine power settings (taxi, descent, holding). That is the reason why
the crew procedure requests to switch offthe associated EBAS at low

UM36BA000000002 003-Pneumalc System Line Ma ntenance(PWl100G) Page 62

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,'9.A|RBUS
SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAININC MANUAL
36‐ PNEUMATIC

HPV FAILED CLOSED: HPV FAILED OPEN:

36‐ 11‐ 07 1 Enqine B:oed HP VaNo

36‐ 11‐ 07A Associated bleod considorod inoperative

Repair interval Nbr inslalled Nbr required Placard

C 1 No
One may be inoperalive in lhe cbsed position p.ovded thal lhe associated engine t{eed air
supply syslem rs cmsdered rnoperatve.
Rd€' b ll€Jn '$.1141 Lngie Ale€d Ar Stlfly Spt€,n

36‐ 11‐ 07B HP valvo wcurod in tho closod position

Repair interval Nbr insta‖ ed Nbr requrred Placard

C 1 No
(o)(m) One may be rnoperatre provited that
'l The aflecled eognc bleed HP vahrc i3 seolred an the dGed positon and
)
2) The opposite engrne bleed suppty system is operalrve

(OI R断け。OpsPr∝ 36,7‐ θ73[mtte aldHP yJ婢 、

1

J● ‐1′ ‐
け υOXχ χ ｀｀
(m)′ daroAMM 、
ス     Ａ

low enginc POWer se十 十ings, affected side ENa BLEED P/B is set十 o OFF ond X BLEED selector is sef to OPEN.
higher power settings′ offected side[卜 ↓O BLEED P/B is sett bock ON and X BLEED sclccfor is sct to AUTO.

NIEL ITEMS― EBASヽ 4EL&HPV FAILURE

UM36BA000000002 003‐ Pneumatc System Lino Maintenanco(PWl100G) Page 63

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&,AlnBUs SA Fammyto A319′ A320′ A321 PWl1000・ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAININC MANUAL

PNEUMATIC SYSTEM LINE MAINTENANCE(PWl100G)

MELITEMS(continued)
BLEED VALVE DEACTIVAT10N
In casc of failulc,Prcssure Rclief Valvc(PRV)and HPV havclo bc
dcactivated CLOSED for dispatch undcr Minimun,Equipmcnt List
(MEL)
Thc dcactivation proccdure is thc samc for both valvcsi
―makc surc pncumatic systcm in not prcssurizcd,BLEED switchcs
OFR
‐dcactivatc thc thrust reverscl.
―open thc RH fan and rcvcrscr cowis,
‐movc thc manual ovcrridc to thc CLOSED positlon,
―sccurc in CLOSED position with iocking pin,
―closc co、 vlings,
‐rcactivatc thc thrust reversen

U Page 64
@ AIRBUS SAS 2014 All tights rcserved. Confidential and proprietary document_

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)

O AIRBuS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2

TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

ELECTRIC

０
Ｃ Ｐ
Ｋ Ｉ
︲ Ｎ
Ｎ
Ｇ
CONNECTOR
MANUAL
OVERRlDE

TORoUE PNEUMATIC
MOTOR CONNECTOR

LOCK!NG NAME
PIN PLATE

lSOLAT10N PRESSURE
PLATE REDuCER

TEST
PORT CLOCKING
DEVlCE
VALVE
BODY

PRESSURE REGULATING HIGH PRESSuRE

VALVE(PRV) VALVE{HPV)

IDENT:F:CAT10N PLATE

LOCK:NC P:N
ITEMS― BLEED VALVE DEACTIN AT10N

UM36BA000000002 003‐ Pneumalc System Line Maintenance(PWl100G) Page 65

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,'g ATRBUS
SA Fam‖ y to A319′ A320′ A321 PWl100C‐ Tl+T2
A319′ A320′ A321 TP REV 6
TECHNICAL TRAINING MANUAL
36-PNEUMATIC

PNEUMATIC SYSTEM LINE MAINTENANCE (PWl IOOG)

MEL ITEMS (continued)
WING LEAK DETECTION
The WING leak detection is a dual-loop system. To generate a WING
LEAK waming, both A and B loops have to detect the oyerheat. For
dispatch, WING leak detection must be operational (at least one loop)
on each wing. tf a single loop fails, the MAINTENANCE message
AIR BLEED wiU be displayed on the STATUS page associated with
a Centralized Fault Display System (CFDS) message L(R) WING
LOOP (INOP). The aircraft may be dispatched per MEL with the
MAINTENANCE message displayed.
For troubleshooting it is important to understand that the WING
detection elements monitor much more than just the wings alone.
The protected areas are:
- wing leading edge (wing anti-ice supply duct),
- air conditioning compartment - belly fairing - (pack supply,
crossbleed manifold, APU supply, ground air supply),
- APU forward supply duct (from the APU check valve through the
wheel well).

UM36BA000000002 003‐ Pneumalc System L ne Ma ntenance(PVV1400G) Page 66

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OAIRBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2 TP REV 6

A319′A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

APU BLEED
CHECK VALVE

W,NO LEAK
DETECT10N L00P

FuSELAGE LEFT SlDE{AFT BELLY FA:R:NG)

W:NG LEADING EDGE

The WIN6 leok detection elements monitor more

thon the wings olone.
The protected oreos ore :
- Wing leodi4g adge (wing onti-ice supply),
- Air conditioning compartment (pack supply,
crossblced monifold, APU supply, ground oir supply)
- APU supply duci (from the APU check volvc
through thc whccl wcll).

A:R CONDIT10NINC COMPARTMENT

MELITEMS― WIN(〕 LEAK DETECT10N

UM36BA000000002 003-Pneumatic System Line Maintenanco(PVVl100C) Page 67

0ス IR3υ S MS 20,4A″ ″gゎ rS rese′ ved Con″ dentla′ andprop″ eraγ docunen`
 AlttBUS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
A349′ A320′ A321 TP REV 6
TECHNICAL TRAINING MANUAL
￨

36-PNEUMATIC

PNEUMATIC SYSTEM LINE MAINTENANCE (PWI IOOG)

MAINTENANCE TIPS
CTDS
CFDS menus for all failure reports and interactive mode displays are
generated by the Bleed Monito ng Computer (BMC) itself.
In normal mode, the BITE transmits maintenance messages (Standard
A type l) for detection results on level of:
- OverHeat Detection System (OHDS),
- Valves.
- Precooler.
- Sensors,
- Extemal communication.
- Intemal communication.
- BMC (Hardware and Software).
The electrical test verifies the EBAS following f'unctions:
- Central Processing Unit (CPU) (microprocessor, RAM, ROM),
- discrete outputs,
- leak detection loops and interfaces,
- discrete and analog inputs,
- digital lnputs/Outputs,
- torque motors, solenoid,
- pressure sensors failures,
- temperature sensors failures,
- valves.
The pressure sensor drift test shall detect any pressure dritt in
Differential Pressure Sensor (DPS) and/or Bleed Pressure Sensor
(BPS).
Electrical Protection System (EPS) conesponds to the channel B
Electrical Protection Function (EPF) test.
The repons menu displays the status in real time for all the system.

UM36BA000000002 003-Pneumalc System L ne Maintenance(PW4100C) Page 68

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94AIRBUS SA Family to A319′ A320′ A321 PWl100C‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

‐ ‐ ‐ ‐ 饉 ‐ 範 ‐ ‐ 璽 Electrical Tes,p● ssibie if:

´■ ■ 日 ■ ■ ■
―A/ι on groond AND
瞥￨こ BMC, : 4フ
■ ■ ■ ■ ■ ■

―Engines OFF AN0

- APυ no十 bleeding AND
■ ■ ― HP“ nol bleeding
■ 目
腱 ■
■ ■
Th. Pr.ssur€ Drift T.st
目 ■ shdll d.t ct ony pr.ssurc
■ ￨■ drift ih DPS ondlor 8PS.

皿 皿 ‐ 璽 ‐ 饉 ‐ ‐ ロ
“
■ 日 日 ■ 日 ■

自 ■ 目 ■ ■一

目 日 ■ ■ ■ ■
■
■
目 APs: Bl..d Pr.ssure scnso.
■ CBV: Cross Blcld Valvc
OPs: D,ff.r.nnal Pr.ssur. Sensor
EPF: Ehcirical Prot.ctaon Fu.crion
日

機 ‐
FAV: Fan Air Valve
日 HPGC: Hrgh PrlssurG cround
，

メ
LRU: Liltc R.plac.ablc Unil
PRV: Pressurc R.lief Valv€

ヽ4AINTENANCE TIPS‐ CFDS

UM36BA000000002 003-Pneumalc System Line Ma ntenance(PW4100G) Page 69

0ハ ′
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 AIRBUS SA Fam“ y to A319′ A320′ A321 PWl100C‐ Tl+T2
A319′A320′ A321
36-PNEUMATIC

PNEUMATIC SYSTEM LINE MAINTENANCE (PWI IOOG)

MAINTENANCE TIPS (continued)
TEST SET
The Test Set P,N 98L36103002000 is available to assisr in
troubleshooting the pneumatic system. The test set enables calibrated
pressure to be applied to individual valves, components and isolated
parts ofthe system to check for normal operation and sense line
integrity (i.e.: PRV HPV, Overpressure Valve (OPV), Fan Air Valve
(FAV), BIeed Pressure Regulated Transducer...).

UM36BA000000002 003-Pneumalc System L ne Maintenance(PVV'100G)

Page 70
R3υ S SAS 20′ イス″/1gわ ′
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 、１ノ

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ヽ ノ
O AIRBuS SA Fam‖ y to A319′ A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANuAL

一
   
  峰
”一
OVERPRESSURE
VALVE(OPV)

SENSE LINES

PRESSURE FUNCT10NNAL TEST OF THE

RECULAT:NG PRESSuRE REGULATING VALVE(PRV)
VALVE(PRⅥ PYLON W:TH THE TEST SET P′ N98L36103002000
lNTERFACE
Ｓ Ｅ
Ａ Ｒ
Ｖ Ｆ

一Ｅ
Ｎ
Ｔ

Ａ
Ｃ

!P CHECK
VALVE
HIGH
PRESSuRE
VALVE(HPVl
lP: lntcrmcdiat. Pr.ssu..
SAV: St.at.r Aar Valv.

MAINTFNAN(lF TIPS― TEST SET

UM36BA000000002_003‐ Pneumalc System Line Ma ntenanco(PWl100G) Page 71

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TP REV 6
A319′ A320′ A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

PNEUMATTC SYSTEM LrNE MATNTENANCE (pwl100G)

MAINTENANCE TIPS (continued)
ENGINE START WITH GROUND AIR
To perlbrm an engine start with ground air, the connection is locatcd
on the lower fuselage. The access door is on the belly fairing.
During a ground air start, the crossbleed valve must be operated
manually. For safety, it is recommended to use the ground air supply
to start the first engine. Then disconnect the ground air supply and
perform a crossbleed stafi for the second engine.
On the ECAM BLEED page, the GND indication DOES NOT indicate
ground air supply connected or available. This indication appears
when the aircraft is on the ground to show that the ground air is
directly supplied to the LEFT side ofthe system only. The left bleed
system pressure indicator will indicate pressure when the ground air
is supplied.

UM36BA000000002 003-Pneumalc System L ne Ma ntenance(PWl100G) Page 72

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OA:RBuS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
TP REV 6
A319′ A320/A321 36-PNEUMATIC
TECHNICAL TRAINING MANUAL

19∝
昨肝
Ю92
HP GROUND AIR
CONNECTOR

NIAINTENANCE TIPS― ENGINE START WITH GROUND AIR

UM36BA000000002 003-Pneuma,c System L ne Maintenance(PVVl100G) Page 73

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 ‐
薇 A[RBUS
O AIRBUS SAS 2015. All rights reserved.
Confi dential and proprietary document.

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