1. OA[RBUS SA Fam‖ y to A319′A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES‐ ENGINES
TP REV 6
A319′ A320′A321
TECHNICAL TRAINING MANUAL
POWER PLANT DRAIN PRESENTATION
PYLON & ENGINE DRAINS
The fluids from the engine and pylon exit the nacelle through a drain
mast.
The drains system provides a controlled leak path exit to the 6 o'clock
position ofthe nacelle for hydraulic, oil and fuel systems.
The drains system is comprised ofthe upper pylon drains hoses, lower
drains through the nacelle bifurcation and the scupper drains assembly
attached to the fan case providing drainage for the oil reservoir
At the lower bifurcation, lateral, core and aft suppon for the l0 drains
tubes is provided through the mid-clamp support attached to the Nacelle
Anti-Icing (NAl) flag and through the latch beam seal interface.
UM7,PlPWl100005 003‐ Power Plant Drain Presentation
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OA:RBuS SA Fam‖ y to A319′A320′ A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′A321
TECHNICAL TRAINING MANUAL
TP REV 6
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HPC: High Pressure Compressor
IDG: lntegrated Drive Generator
IFPC: lntegrated Fuel Pump and Conlrol
LPC: Low Pressure Compressor
PMA: Permanent Magnet Alternator
SVA: Stato. Vane Actuator
PYLON&ENGINE DRAINS
UM71P4PWl100G05 003‐ Power Plant Drain P「osentation Page 53
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3. OA:RBuS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
POWER PLANT DRAIN PRESENTAIION
DRAIN MAST
At the 6 o'clock position an aerodynamic drain mast protrudes below the
nacelle surface. The dmin mast also has exit holes on the sides and bottom
surface which are identified to enable trouble shooting ofthe leaking
components.
UM71PlP'Vl100005 003‑Power Plant Drain Presentalon Page 54
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4. OA:RBUS
A319′ A3207A321
TECHNICAL TRAINING MANUAL
SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
BLEED―ACT
DRAWING V:EW
FROM RIGHT SIDE
HPC-SVA: High Pressure Compressor - Stator Vane Actuator
IDG: Integrated D,ive cenerator
IFPC: lnteqrateal Fuel Pumo and Control
Page 55
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5. O AIRBUS SA Fam‖ y to A319′A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
TP REV 6
POWER PLANT INSTALLATION D/O
INLET COWL
The inlet cowl is composed ofan inner barrel, outer banel, forward
bulkhead, aft bulkhead and a nose lip.
The inner banel has acoustic liners for noise suppression. It also
accommodates the T2 probe.
The outer barrel has a small flush inlet vent scoop located at 12 o'clock
position to provide ram air for fan compartment cooling. lt also has
Nacelle Anti lce Exhaust Pons at the 6 o'clock position.
The inner and outer barrels are made ofcomposite material.
The forward and aft bulkhead provides support and dgidity to the
structure.
The inlet lip is made ofa single piece aluminium alloy for engine anti-ice
purpose.
It includes installation of interphortejack for sewice interphone.
For renoval and installation, the inlet cowl is attached to the enginc at
the attach ring with 40 bolts.
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ilrr All(E US SA Fam‖ y to A319′A320′A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′A321
TECHNICAL TRAINING MANUAL
TP REV 6
lNLET Lip FAN COMPARTMENT
C00L:NG VENT
FAN COMPARTMENT
;NLET VENT SCOOP
OUTER BARREL
lNNER BARREL
A'ACH RING
THERMAL ANT:‐ lCE
(TA:)DuCT
cOpynghted by unled TechnoloOtes CO子 POratlon ̲Prall&Whitlney Division 利[R,9hls Reserved
INLET COWL
THERMAL ANTIJCE
DuCT VENT
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7. O AIRBUS SA Fam‖ y to A319′A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES‐ ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
POWER PLANT INSTALLATION D/O
AIR INTAKE FUNCTIONS
The main function ofthe inlet cowl is to guide the airflow into the ergine
inlet and to permit an aerodynamic airflow over the outer surface ofthe
engine.
When the engine anti icing is selected to ON from the cockpit overhead
panel, hot bleed air from the engine is ducted to the cowl nose lip to
prevent ice build-up. The hot air enters to the inlet Iip through a dedicated
duct at the 4 o'clock position in the outerbulkhead. The airthen exhausts
overboard through a flush exit ports at the 6 o'clock position in the outer
barrel.
The outer barrel has an impregnated copper screen layer for protection
against lightning stdke.
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OA:RBuS
A319′ A320/A321
TECHNICAL TRAINING MANUAL
SA Family to A319′ A320′A321 PWl1000‐ Tl●T2
70‐ STANDARD PRATICES‐ ENGINES
TP REV 6
NOZZLE7BULKHEAD
FWD」 0:NT
NAi SYSTEM
INLET EAl
SYSTEM
lNLET′ENCINE EAl
lNTERFACE
CoPy● ghted by unted Technol● 9ies COrpoは lon‐ Pratt e whittney D■ isOn利IR● htS Reserved
AIR INTAKE FtJNCT10NS
UM7101PWl100G05 003‐ Powor Plantlnsla‖ alon D′ 0
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9. A AlRBvs SA Fam‖ y to A319′A320′A321 PWl100C‐ Tl+T2
70‑STANDARD PRATICES‐ ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANuAL
POWER PLANT INSTALLATION D/O
FAN COWL DOORS
There are two fan cowl doors to enclose the fan case and provide
aerodynamic smoothness around the engine.
They are attached to the pylon by three hinges with hinge pins.
The door assembly is latched along the bottom centcrline by three latches.
These latches have a mounting mechanism and visual indicators to ensure
that they are properly secured.
Proximity sensors are installed on each latch which sends its position
signal to the Engine lnterface Unit (EIU) for generating necessary
waming.
The door can be opened manually. Each door is provided with 2 telescopic
hold open rods, for opening.
The fan cowl door rests on 4 axial locators, when closed.
It also has hoist points, for removal and installation.
Acrodynamic strakes are mounted on the fan cowls to improve aircraft
performance during manoeuvres.
Access doors on the LH side fan cowl door facilitates engine oil servicing
and the Thrust reverser Hydraulic Control Unit (HCU) de-activation
without opening the fan cowl.
A vent g ll near the 6 o' clock position permits the air to escape out in
case ofdamage ofthe anti-ice duct. The same is used for draining any
fluids in and around the fan case.
UM71DlPW1400G05 003‑Power Plantinsta‖ atlon D′O Page 60
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O AIRBUS SA Family to A319′ A320′ A321 PWl100G‐ Tl,T2
70‑STANDARD PRATICES― ENGINES
H!NGES VV!TH HINCE PIN(3)
01L TANK
ACCESS DOOR
HOLD OPEN
RODS(HOR)
AX:AL LOCATOR(4) OUTLET VENT′
PRESSuRE REL:EF
Copy■ 9hted by Unted￢∝hnolo91es CorpOmtlon ‐
Pratt&VVhlltney Division A‖ R19hts Reserved
RヽN COヽVL D00RS
UM71DlPWl100G05 003‐ Power Plant insta‖ alon D′ O Page 61
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11. A:RBUS
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
SA Fam‖ y to A319′A320′ A321 PWl100G‐ ■
1+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
POWER PLANT INSTALLATION D/O
THRUST REVERSER COWL DOORS
The thrust reverser cowl doors (or "C" Ducts) are in two halves. Each
half includes one translating sleeves, two actuators, five blocke$ doors
and cascades.
The thrust reverser cowls provide a smooth air flow around the engine
area and enclose the engine core components, gear boxes and pipelines.
Each half is supported by 3 hinges at the pylon. The assembly is latched
along the bottom centerline by seven latches.
Each half is provided with:
- Hoist points to install a handling sling for removal and installation,
- I opening actuator operated extemally using a hydraulic hand pump
for opening the thrust reve$er cowl for maintenance
- I hold open rod mounted on the fan case for opening.
UM71D̀PVVl100G05 003‑Power Plantlnstalalon D′ 0 Page 62
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O AIRBUS SA Fam‖ yto A319′ A320′A321 pwl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A3201A321
TECHNICAL TRAINING MANUAL
TRANSLAT!NC SLEEVE
(R:GHT HAND)
INNER FIXED STRuCTURE
HYDRAUL:C PUMP QU:CK
D:SCONNECT(QD}
BLOCKER D00RS
CASCADES
Copylghted by un tel T∝hnolo9bs ColIЮ rat10n ‐
Pratt a vvhittney Division 肉I R19hts Reserved
THRUST REVERSER COWL D00RS
UM71DlPWl100005 003‑Power Plantinstalalon D′ 0 Page 63
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13. OA:RBuS SA Fami:y to A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
TP REV 6
A319′ A320′ A321
TECHNICAL TRAINING MANUAL
POWER PLANT INSTALLATION D/O
EXHAUST NOZZLE
The exhaust nozzle is formed by the center bodies and nozzle assembly.
The annular passage between the exhaust nozzles and the centcrbodies
provide a smooth exit ofthe exhaust gas flow.
The lire seal fingers (turkey feathers) at the top ofthe exhaust nozzle
prevents any flame from entering the core compartment area in the event
offire.
The centerbody also accommodates the drain outlet to expel hazardous
fluids and vapors. These drains are located at the 6 o'clock position on
the tbrward and aft center bodies.
UMア イ
D4PVVl100G05 003‑Power Plantinsta‖ alon D′ 0 Page 64
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14. OAIRBUS
A319′A320′ A321
TECHNICAL TRAINING MANUAL
SA Family to A319′ A320′ A321 PWl100G‐ Tl+T2
70‐ STANDARD PRATICES― ENGINES
TP REV 6
FlRE SEAL F:NCERS
AFT CENTERBODY
EXHAuST NOZZLE
FWD CENTERBODY
CoPyhghted by United Technolo9ies COrporalon ‐
Pratl&Whittney Division 肉I Rlghts Reserved
EXHAUST NOZZLE
UM71DlPWl100005 003‑Power Plantlnsta‖ a on D′ 0 Pago 65
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15. &,ATRBUS SA Fam‖ yto A319′ A320′ A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′ A321
TECHNICAL TRAININC MANUAL
TP REV 6
POWER PLANT INSTALLAIION D/O
ENGINE MOUNTS
The engine is mounted to the pylon by the forward and all mounts. They
transfer the engine and thrust loads.
The forward mount assembly bears the engine thrust, vertiqal and laterul
loads. The forward mount is attached to the engine at the Compressor
lntermediate Case at l2 o'clock position. The forward mount is attached
to the pylon by the help of four attachment bolts.
The thrust link assemblies attached to the forward mount take the lateral
loads. Thcy are attached to the forward mount through a balance beam.
They are attached to the Compressor lntermediate Case at 09:30 and
02:30 position.
The aft mount assembly bears the engine venical and radial loads. It is
attached to the engine at the Turbine Exhaust Case (TEC) at l2 o' clock
position. lt is attached to the pylon by four bolts.
UM7,DlPVVl100G05 003‐ Powor Plantlnsla‖ aJon D′ 0
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C AIRBuS SA Family to A319′ A320′A321 PWl100G‐ Tl+T2
70‑STANDARD PRATICES― ENGINES
A319′ A320′A321
TECHNICAL TRAINING MANUAL
TP REV 6
FORWARD MOuNT
COMPRESSOR
INTERMED:ATE
CASE(CiC)
Copylghted by united Technol● lles Corpo日 lon― Pratt&ヽVhitlney D vis on A‖ R9htS Reserved
ENGINE MOUNTS
UM71DlPVVl100G05 003‐ Powe「 Plantlnsta lanon D′ 0
@ AIRBUS SAS 2014 All tights resoMed. Confidential and propietary documenf
Page 67
REAR MOUNT
