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100% found this document useful (2 votes)

805 views884 pages

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A330-200/300

TECHNICAL TRAINING MANUAL

GENERAL FAMILIARIZATION COURSE - T4 (ALL
ENGINES)
PART 2 OUT OF 2

This document must be used for training purposes only

Under no circumstances should this document be used as a reference

It will not be updated.

All rights reserved

No part of this manual may be reproduced in any form,
by photostat, microfilm, retrieval system, or any other means,
without the prior written permission of AIRBUS S.A.S.

A330-200/300 TECHNICAL TRAINING MANUAL

PART 2 OUT OF 2

G6B08031 - G11T4T0

52 Doors System Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . .2

25 Equipment/Furnishings System Presentation (1) . . . . . . . . . . . . .56
35 Oxygen System Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . .116
38 Water and Waste System Presentation (1) . . . . . . . . . . . . . . . . . .140
28 Fuel System Presentation (A330-200) (1) . . . . . . . . . . . . . . . . . .172
28 Fuel System Presentation (A330-300) (1) . . . . . . . . . . . . . . . . . .226
26 Fire Protection SYS Pres. (RR700) (1) . . . . . . . . . . . . . . . . . . . .270
26 Fire Protection System Pres. (GECF6) (1) . . . . . . . . . . . . . . . . .318
26 Fire Protection System Pres. (PW4000) (1) . . . . . . . . . . . . . . . .366
49 APU System Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . .414
70 Power Plant RR Trent 700 Presentation (1) . . . . . . . . . . . . . . . .446
70 Power Plant GE CF6 Presentation (1) . . . . . . . . . . . . . . . . . . . . .512
70 Power Plant PW 4000 Presentation (1) . . . . . . . . . . . . . . . . . . . .576
36 Pneumatic SYS Presentation (RR700) (1) . . . . . . . . . . . . . . . . .640
36 Pneumatic System Presentation (GECF6) (1) . . . . . . . . . . . . . . .658
36 Pneumatic System Presentation (PW4000) (1) . . . . . . . . . . . . . .676
21 Air Conditioning System Presentation (1) . . . . . . . . . . . . . . . . . .694
30 Ice & Rain Protection SYS Pres. (RR700) (1) . . . . . . . . . . . . . .748
30 Ice & Rain Protection SYS Pres. (GECF6) (1) . . . . . . . . . . . . . .786
30 Ice & Rain Protection SYS Pres. (PW4000) (1) . . . . . . . . . . . . .824
00 Circuit Identification Presentation (1) . . . . . . . . . . . . . . . . . . . . .862
05 Time Limits and Maintenance Checks (1) . . . . . . . . . . . . . . . . .876

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

TABLE OF CONTENTS

Jan 15, 2008

Page 1

A330-200/300 TECHNICAL TRAINING MANUAL

52 DOORS SYSTEM PRESENTATION (1)

SYSTEM INTRODUCTION

G6B08031 - G11T4T0 - FM52P7000000001

The doors system has:

- the cabin doors,
- the cockpit door,
- the cargo doors,
- the avionics compartment doors,
- the Doors and Escape Slides Control System (DSCS).
When you operate on the doors system, you must obey all the safety
procedures listed in the AMM.

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A330-200/300 TECHNICAL TRAINING MANUAL

SYSTEM INTRODUCTION
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

52 DOORS SYSTEM PRESENTATION (1)

PASSENGER AND EMERGENCY DOORS (continued)
PASSENGER/EMERGENCY DOORS ATTACHMENTS

G6B08031 - G11T4T0 - FM52P7000000001

The support arm supports the door load. Two guide arms maintain
the door parallel to the fuselage. To prevent the door from moving
when it is in the fully open position, the door stay mechanism locks
the door. It is released by a P/B installed on the support arm.

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52 DOORS SYSTEM PRESENTATION (1)

PASSENGER AND EMERGENCY DOORS (continued)
PASSENGER AND EMERGENCY DOORS EMERGENCY
SYSTEM

G6B08031 - G11T4T0 - FM52P7000000001

The emergency system has:

- an arming lever controlling the girt bar,
- a damper and emergency-operation cylinder,
- an escape slide/raft packed into a container installed at the bottom
of the door.
Disarmed mode selected, the mechanical linkage secures the girt bar
to the door. The damper and emergency-operation cylinder damps the
door movement. Armed mode selected, the arming mechanical linkage
attaches the girt bar to the structure in order to deploy the escape
slide/raft during the opening. The damper and emergency-operation
cylinder opens the door automatically when the handle is raised to let
the escape slide/raft deploy in armed mode.

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A330-200/300 TECHNICAL TRAINING MANUAL

PASSENGER AND EMERGENCY DOORS - PASSENGER AND EMERGENCY DOORS EMERGENCY SYSTEM
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
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52 DOORS SYSTEM PRESENTATION (1)

PASSENGER AND EMERGENCY DOORS (continued)
EMERGENCY EXITS
Emergency exit doors are of the type I and similar to the type A doors
in function but not in design. They are smaller, but still have a locking
system, an emergency system and an indicating system. The structure
and the attachments are similar to the passenger/crew door.
Door locking/unlocking is initiated either from the outer handle or
the inner handle. Only one locking hook is operated. It is the same
type of mechanical linkage as the type A passenger doors.
The emergency system has an arming lever operating a girt via a
mechanical linkage.

G6B08031 - G11T4T0 - FM52P7000000001

NOTE: The escape slide/raft is packed into a container installed at

the bottom of the door.
The damper and emergency-operation cylinder work also as a damper
in disarmed mode or as an emergency-operation cylinder in armed
mode.

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A330-200/300 TECHNICAL TRAINING MANUAL

PASSENGER AND EMERGENCY DOORS - EMERGENCY EXITS

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

52 DOORS SYSTEM PRESENTATION (1)

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52 DOORS SYSTEM PRESENTATION (1)

CARGO DOORS

G6B08031 - G11T4T0 - FM52P7000000001

The aircraft has three cargo compartment doors installed on the lower
right hand side of the fuselage. The three doors give access to the cargo
compartments:
- the FWD and aft doors are hydraulically operated,
- the bulk cargo door is manually operated.

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A330-200/300 TECHNICAL TRAINING MANUAL

CARGO DOORS
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PART 2 OUT OF 2

52 DOORS SYSTEM PRESENTATION (1)

CARGO DOORS (continued)
CARGO DOORS LOCKING AND LATCHING

G6B08031 - G11T4T0 - FM52P7000000001

The door has:

- a locking handle,
- a latching handle.
The locking handle is used for the safety by securing the hooks in the
latched position. It operates a locking shaft, which secures the latching
shaft, when the hooks are engaged with the rollers. When the locking
handle is in the unlocked position it gives access to the latching handle.
Indicator flags extrude from the door skin if the locking system is not
in the fully locked position. A catch pin safeties the latching handle
in the fully latched position. A P/B on the latching handle must be
pressed to release the catch. The cargo door will then leave the fuselage
frame under gravity.

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A330-200/300 TECHNICAL TRAINING MANUAL

CARGO DOORS - CARGO DOORS LOCKING AND LATCHING

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52 DOORS SYSTEM PRESENTATION (1)

CARGO DOORS (continued)
CARGO DOORS HYDRAULIC OPERATION

G6B08031 - G11T4T0 - FM52P7000000001

The cargo compartment door hydraulic system controls the operation

of the FWD and aft cargo compartment doors. The hydraulic system
of each door has a hydraulic actuator and a manual selector valve.
The yellow auxiliary hydraulic system supplies the doors with
hydraulic pressure. For normal operation the yellow electric pump is
used. For the case of electric pump failure or no electric power on the
aircraft a hand pump can be used. A single operator achieves normal
operation; two operators are needed for manual operation. Turning
the manual selector lever to open or close is necessary in both
operating modes. Turning the manual selector lever and the normal
system available will start up the electric pump and the door will
move.

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A330-200/300 TECHNICAL TRAINING MANUAL

CARGO DOORS - CARGO DOORS HYDRAULIC OPERATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

52 DOORS SYSTEM PRESENTATION (1)

CARGO DOORS (continued)
BULK CARGO DOOR LOCKING AND LATCHING

G6B08031 - G11T4T0 - FM52P7000000001

The bulk cargo door has an inner and an outer handle, which operate
the locking mechanism. There is a barrel lock installed at each end of
the locking shaft to lock the door in the fuselage. A balance mechanism
reduces the force, which is necessary to open the door. There is a latch
assembly, which holds it in the fully open position. The locking system
operates also the latching hook. To lock the latching hook in the latch
arrester it is necessary to put the door control handles to the closed
position.

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CARGO DOORS - BULK CARGO DOOR LOCKING AND LATCHING

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52 DOORS SYSTEM PRESENTATION (1)

AVIONICS COMPARTMENT DOORS (continued)
AVIONICS COMPARTMENT DOORS BOTTOM
FUSELAGE

G6B08031 - G11T4T0 - FM52P7000000001

The avionics compartment door is installed in the FWD bottom part

of the fuselage in the pressured area of the aircraft. The door indicating
and warning system sends a signal to the ECAM DOOR/OXY page,
which indicates the state of the avionics access door. The avionics
compartment door gives access to the aircraft through an extendable
ladder. The door can be opened from the outside or from the inside
of the fuselage with outer and inner handles. A compensating
mechanism reduces the force that is necessary to operate the door.

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AVIONICS COMPARTMENT DOORS - AVIONICS COMPARTMENT DOORS BOTTOM FUSELAGE

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52 DOORS SYSTEM PRESENTATION (1)

AVIONICS COMPARTMENT DOORS (continued)
AVIONICS COMPARTMENT DOORS FIXED
PARTITION

G6B08031 - G11T4T0 - FM52P7000000001

The fixed partition door gives access to the avionics compartment

from the FWD cargo compartment. A piano hinge attaches the door
to the fixed partition. The door opens into the avionics compartment.
A handle is located on the avionics compartment side only. A special
key (in the onboard tool kit) opens the door from inside the cargo
compartment.

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AVIONICS COMPARTMENT DOORS - AVIONICS COMPARTMENT DOORS FIXED PARTITION

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52 DOORS SYSTEM PRESENTATION (1)

COCKPIT DOOR

G6B08031 - G11T4T0 - FM52P7000000001

The cockpit door separates the cockpit from the cabin. It is an armored
and bulletproof door made to prevent a hijacking attempt and protect the
flight compartment against an intrusion. A Cockpit Door Locking System
(CDLS) controls its electrical release and prevents an unwanted access
into the cockpit. The door also has a door escape hatch with a
pneumatically operated decompression panel, which opens the hatch
when there is a rapid decompression between the cockpit and the cabin.

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A330-200/300 TECHNICAL TRAINING MANUAL

COCKPIT DOOR
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A330-200/300 TECHNICAL TRAINING MANUAL

52 DOORS SYSTEM PRESENTATION (1)

COCKPIT DOOR (continued)
COCKPIT DOOR LOCK SYSTEM (CDLS)
The CDLS is an electrically operating system for the locking and
unlocking of the cockpit door.
This system is mainly composed of:
- a control unit and its CocKPiT DOOR CONTrol panel, located on
the left-hand side of the overhead panel and a control unit, identical
to the first one, and its CKPT DOOR CONT panel, located on the
right-hand side of the overhead panel,
- the CKPT DOOR panel on the center pedestal with a toggle switch
to control the cockpit door and a fault indicator,

G6B08031 - G11T4T0 - FM52P7000000001

NOTE: The CKPT DOOR panel can be equipped in option with a

CAB ALERT guarded P/B, which alert CKPT crew in case
of hijacking/vandalism in cabin.
- the buzzer on the overhead panel,
- the keypad in the cabin for cockpit access authorization,
- three electrical release strikes,
- an additional CKPT DOOR BacK-UP panel, which is composed of
a LocKinG SYStem switch and a OPEN/FAULT ConTroL P/B
NOTE: The door is always locked when closed and the aircraft is
powered during maintenance activity there is a magnetic
door stop to keep the door fully open.

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A330-200/300 TECHNICAL TRAINING MANUAL

COCKPIT DOOR - COCKPIT DOOR LOCK SYSTEM (CDLS)

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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52 DOORS SYSTEM PRESENTATION (1)

G6B08031 - G11T4T0 - FM52P7000000001

DOORS AND ESCAPE SLIDES CONTROL SYSTEM (DSCS)

The DSCS gives electrical indications related to the condition of the
doors. The DSCS has:
- proximity switches,
- a compensation panel (5062VE),
- a Proximity Switch Control Unit (PSCU),
- an Autonomous Standby Power Supply Unit (ASPSU),
- a pressure switch.
The primary functions of the DSCS are to control:
- door indicating and warning,
- escape slide indicating and warning,
- the residual cabin and cargo compartment pressure detection and
indicating,
- cargo doors electrical control and indicating.
On the ground, with one engine running, the DSCS prevents the
pressurization of the aircraft if:
- a door is not fully closed and locked,
- a sensor is defective.
If a proximity sensor fails during the flight, the aircraft will stay
pressurized.
The compensation panel has one compensation sensor with a set target.
This compensation sensor can be used for a manual override function
when a door closed proximity sensor failed. This function lets dispatch
the aircraft using the Minimum Equipment List (MEL) procedure.

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A330-200/300 TECHNICAL TRAINING MANUAL

DOORS AND ESCAPE SLIDES CONTROL SYSTEM (DSCS)

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52 DOORS SYSTEM PRESENTATION (1)

DOORS AND ESCAPE SLIDES CONTROL SYSTEM (DSCS)
(continued)
PROXIMITY SWITCH CONTROL UNIT (PSCU)

G6B08031 - G11T4T0 - FM52P7000000001

The PSCU has two independent channels supplied by two independent

28V DC busbars:
- the Flight/Ground bus bar,
- the battery bus bar via the ASPSU.
When all doors are closed and locked, the PSCU sends signals to the
Cabin Pressure Controllers (CPCs) so that the cabin can be pressurized.
The ASPSU supplies power for the residual pressure warning system
through the PSCU on a de-powered aircraft. The ASPSU has two
identical and easily removable battery packs and their electronic
control unit. The ASPSU is automatically rechargeable through the
aircraft DC power supply. The switching from aircraft power supply
to ASPSU power supply and vice versa, is fully automatic. The ASPSU
will supply DC power to the residual pressure warning system for
approximately 60 minutes on a de-powered aircraft when the warning
is triggered. An ASPSU test is possible through the Cabin
Intercommunication Data System (CIDS).

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A330-200/300 TECHNICAL TRAINING MANUAL

DOORS AND ESCAPE SLIDES CONTROL SYSTEM (DSCS) - PROXIMITY SWITCH CONTROL UNIT (PSCU)
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

52 DOORS SYSTEM PRESENTATION (1)

CONTROL AND INDICATING (continued)
TYPE I EMERGENCY EXIT DOOR
There is only one mechanical indicator showing the door condition
(LOCKED or UNLOCKED).

G6B08031 - G11T4T0 - FM52P7000000001

NOTE: The red UNLOCKED indication will only be on when the

handle is moved a few degrees during opening and at the
last movement during closing. When the door is open there
is no indication.
All the other indications and warnings are similar to the
passenger/crew door.

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A330-200/300 TECHNICAL TRAINING MANUAL

CONTROL AND INDICATING - TYPE I EMERGENCY EXIT DOOR

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52 DOORS SYSTEM PRESENTATION (1)

CONTROL AND INDICATING (continued)
ECAM DOOR/OXY PAGE

G6B08031 - G11T4T0 - FM52P7000000001

The ECAM DOOR/OXY page monitors the status of all the doors
and the escape slide/slide raft.
The indications on the ECAM page are:
- green when the door is closed and locked,
- amber when the door is unlocked.
The white SLIDE indications on the DOOR/OXY page show that the
slides are armed. When the slide is disarmed on any door no indication
is displayed.

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CONTROL AND INDICATING - ECAM DOOR/OXY PAGE

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MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM52P7000000001

The DSCS can be tested via the MCDU SYSTEM REPORT/TEST pages.
The PSCU has a BITE. The BITE is used for the in-flight monitoring,
on ground trouble shooting and continuous self-testing. All fault data are
transmitted through ARINC 429 buses to the Central Maintenance
Computers (CMCs).
Their functions are to:
- find and indicate faults,
- identify defective electrical components which are Line Replaceable
Units (LRU) for maintenance and trouble-shooting,
- identify defective components that are Shop Replaceable Units (SRU).
The ASPSU also has a BITE used for system test and a battery capacity
test. For these tests, the ASPSU has a test panel with two P/Bs and a
Light Emitting Diode (LED) display.

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MAINTENANCE/TEST FACILITIES
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52 DOORS SYSTEM PRESENTATION (1)

G6B08031 - G11T4T0 - FM52P7000000001

SAFETY PRECAUTIONS
WARNING: WHEN YOU WORK ON THE A/C, MAKE SURE THAT
YOU OBEY ALL THE AMM SAFETY PROCEDURES.
THIS WILL PREVENT INJURY TO PERSONS AND/OR
DAMAGE TO THE A/C.
HERE IS AN OVERVIEW OF THE MAIN SAFETY
PRECAUTIONS ABOUT THE DOORS SYSTEM.
IF THE RED WARNING LIGHT IS FLASHING, DO NOT
OPERATE THE DOOR OPENING HANDLE.
Be careful before opening cabin doors or cargo doors. Make sure that the
red warning light does not flash. If it flashes, that means there is a residual
pressure in the cabin or in cargo compartment, and any door may suddenly
open. It could kill or cause serious injury and damage to the aircraft.
Make sure when you work on a cabin door that the emergency control
handle is in the disarmed position with the safety pin installed.
Check that the percussion lever of the door damper and emergency
operation cylinder is in the disarmed position with the safety pin installed.
Install a safety barrier or an access platform before opening any cabin
door to avoid a fall on the ground.
When opening or closing a cargo door, make sure that the access platform
is at the correct height to avoid damage.
Do not operate a cabin/cargo door if the wind speed is more than 40 kts,
you must close a cabin/cargo door before the wind speed is more than
60 kts to prevent damage to the door or to the aircraft.

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SAFETY PRECAUTIONS
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25 EQUIPMENT/FURNISHINGS SYSTEM PRESENTATION (1)

GENERAL

G6B08031 - G11T4T0 - FM25P9000000001

The equipment and furnishings chapter covers:

- the cockpit,
- the passenger compartment,
- the crew rest compartment,
- the emergency equipment,
- the cargo compartments,
- the miscellaneous compartments.
When you work on aircraft, you must obey all the safety procedures listed
in the Aircraft Maintenance Manual (AMM).

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COCKPIT

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Lining and furnishing panels, which provide flight compartment

decoration, complete the heat and sound insulation. They are easily
removable to give access to the installations they conceal. The cockpit
panels include:
- the overhead panel,
- the glareshield,
- the main instrument panel,
- and the center pedestal.
The linings also give various stowage possibilities.

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COCKPIT (continued)
FLIGHT CREW FOOT WARMERS

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The flight crew foot warmers have heating panels controlled by a

switch located on the CAPT and F/O LighTing panels.

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PASSENGER COMPARTMENT

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The cabin can have three different configurations:

- one first class, one business class and one tourist class,
- one business class and one tourist class,
- one tourist class only.

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PASSENGER COMPARTMENT (continued)
PASSENGER SEATS

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There are three different classes of passenger seats:

- first class,
- business class,
- tourist class.

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PASSENGER COMPARTMENT (continued)
PASSENGER CONTROL UNITS

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The Passenger Control Unit (PCU) is installed in the armrest. The

PCU fulfills the interface between the passenger, the headset, the
video screen and the Digital Seat Electronic Box (DSEB). Under each
passenger seat, there is a DSEB. The DSEB fulfills the interface
between the PCU and the In-Flight Entertainment (IFE) system.

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PASSENGER COMPARTMENT (continued)
CABIN ATTENDANT SEATS

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There are two types of cabin attendant seat, floor-mounted or

wall-mounted, all are folding seats. The floor-mounted cabin attendant
seats are attached to the cabin floor structure (hard point mounted) or
to the seat track. The wall-mounted cabin attendant seats are installed
on:
- the lavatory walls,
- the galley walls,
- the stowage walls.
Depending on the cabin configuration, the number and location of
cabin attendant seats can vary.

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PASSENGER COMPARTMENT (continued)
LAVATORIES

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The lavatories are installed in the cabin for the comfort of the
passengers and the crew. Each lavatory also has a washroom function.
Lavatories can be fixed to the ground by a seat rail or with a hard
point. The number and the location of the lavatories depend on the
aircraft configuration. The forward lavatories are installed in the
forward passenger/crew door area. The middle lavatories are lateral
lavatories, which are installed between the forward and aft
passenger/crew doors areas. The center lavatories are installed where
the mid and aft passenger/crew door areas and the aisles cross. The
aft lavatories are lateral lavatories, which are installed in the aft
passenger/crew door area. A razor socket is installed in each lavatory
and in the crew rest room to supply power for an electrical razor.

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PASSENGER COMPARTMENT (continued)
CABIN PANEL LAYOUT

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The cabin interior has removable panels. The lining design allows
cabin customization. The lower sidewall (Dado) panels are mounted
between the cabin floor and the sidewall panels. They have rapid
decompression panels, which operate during decompression either in
the cabin or in the cargo compartment. The sidewall panels are
mounted on the side of the cabin. They include the window contour.
Inner window panels and sun visors are installed on to the window
frame. The closing cover panels cover the space between the ceiling
panels and the cover light panels. The cover light panels cover the
space between the sidewall panels and the overhead stowage
compartments. The overhead bins or cover plates are removable.
Removable ceiling panels are mounted in the cabin. They are installed
over the full length of the cabin and the utility areas. The cover plates
are installed where there is no overhead stowage compartment installed
along the top.

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PASSENGER COMPARTMENT (continued)
PSU CHANNEL

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The Passenger channel holds the Passenger Service Units (PSUs) to

give service and information to the passengers.
The PSUs are installed in the passenger service channels adjacent to
the emergency oxygen containers. The passenger service channels
are found at the bottom of the overhead stowage compartments above
each seat row. If the center overhead stowage compartments are not
installed, the PSUs are installed in the cabin ceiling. The PSUs have
LED reading lights. You can switch the lights ON or OFF with the
related switch on the PCU in the seat armrest or on the PSU.

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LDMCR COMPARTMENT

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The Lower Deck Mobile Crew Rest (LDMCR) compartment is installed

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BCRC

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The Bulk Crew Rest Compartment (BCRC) is installed in the bulk cargo
compartment. Its size and equipment can be laid out according to the
airline request. A staircase housing is located in the cabin above the
compartment and the exit hatch on the cabin aisle. Lower and upper rest
bunks are installed. Lower bunks without an upper bunk can be used as
seats. Stowage compartments are located in the staircase to store
emergency equipment.

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TYPICAL EMERGENCY EQUIPMENT
COCKPIT EMERGENCY EQUIPMENT

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The standard cockpit emergency equipment components are:

- flash light,
- portable halon fire extinguisher,
- life vest for flight crew,
- Protective Breathing Equipment (PBE),
- crash axe,
- fireproof gloves.

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TYPICAL EMERGENCY EQUIPMENT (continued)
CABIN EMERGENCY EQUIPMENT

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Emergency equipment is kept in different locations in the aircraft with

easy access for immediate use. Typical emergency equipment items
are:
- crash axe,
- life vest,
- megaphone,
- oxygen mask,
- portable oxygen bottle,
- PBE,
- fire extinguisher,
- emergency location transmitter,
- flash light,
- first aid kit and medical kit.
Other items can also be installed, such as blankets, pillows, gloves, a
wheelchair, a dangerous goods kit, a security mirror, a crowbar, a
signaling kit or a baby survival raft.

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LOWER DECK CARGO COMPARTMENT (continued)
LOWER DECK CARGO COMPARTMENT INTERIOR
AND LINING

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The inside of the cargo compartments has:

- floor panels,
- ceiling panels,
- side linings,
- partition walls.
All the linings and panels are sealed to give a fully sealed
compartment. Rapid decompression panels, blow in, blow out panels
are installed in the linings to prevent damage from differential pressure.
In case of decompression in the cabin or in the cargo compartment,
they equalize the pressure in both sections, to avoid damage to the
structure.

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LOWER DECK CARGO COMPARTMENT (continued)
LOWER DECK CLS

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The semi-automatic CLS of the forward and aft cargo compartments

is used to load, unload and move the ULDs. These ULDs can be pallets
or containers of different sizes. One person can operate the CLS. If
there is no electrical power available, it is possible to manually load
or unload. The semi-automatic cargo loading systems of the forward
and the aft lower deck cargo compartments are similar in construction
and work independently. The CLS includes:
- control panel installed adjacent to the cargo compartment door,
- control box,
- Power Drive Units (PDUs),
- proximity switches located on the different latches.
For the powered loading operation, the power switch must be in the
ON position. The AC/DC power is available and the manual doorsill
latch must be in the lowered position. The control panel sends
electrical signals through the control box to the applicable PDUs. The
PDUs move the ULDs in the necessary direction and to their loading
positions. When a ULD is in the correct loading position, you must
lock the latch manually.

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LOWER DECK CARGO COMPARTMENT - LOWER DECK CLS

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AVIONICS COMPARTMENT

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The avionics compartment is located in the underfloor nose section. The

avionics compartment service ladder can be used to enter and leave the
aircraft while performing maintenance procedures. In case of an
emergency on ground, the flight crew can use the service ladder when
they leave the aircraft through the avionics compartment.

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SAFETY PRECAUTIONS

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When you work on aircraft, make sure that you obey all the AMM safety
procedures. This will prevent injury to persons and/or damage to the
aircraft. Here is an overview of the main safety precautions relative to
the equipment & furnishings system. Use only the specified materials
and obey the instructions from the manufacturers. Other materials can
cause damage to the surface protection of the components and the related
area. Before you start working on the escape-slide, make sure that the
door is safetied. This prevents sudden movement of the door and
accidental deployment of the escape-slide, which can cause injury and/or
damage. Before opening the door or the emergency exit, make sure that
the escape-slide system is disarmed and safetied. This will prevent
inadvertent inflation of the slide pack-assembly. Use solvents/cleaning
agents, sealants and other special materials only with a good flow of air
through the work area. Those materials being poisonous, flammable and
skin irritant, put on protective clothing, rubber gloves, goggles and mask.

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GENERAL

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The oxygen system supplies crew and passengers with oxygen in case
of cabin depressurization. The oxygen system has three different
subsystems:
- the crew oxygen system,
- the passenger oxygen system,
- the portable oxygen system.
When you work on aircraft, you must obey all the safety procedures listed
in the AMM.

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COCKPIT CREW OXYGEN SYSTEM
The flight crew oxygen system supplies the flight crew members with
oxygen in the case of loss of cabin pressure altitude or emission of smoke
or toxic gas.

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CREW OXYGEN SUPPLY

The flight crew oxygen is stored in a High Pressure (HP) oxygen
cylinder. This cylinder is located in the avionics compartment and
placed in a cradle. The HP oxygen cylinder can be isolated for
maintenance by a manual ON/OFF valve. The oxygen is supplied to
the flight crew stations through a distribution circuit. HP is reduced
to LP by the pressure regulator/transmitter. LP oxygen flows is
supplied via the LP supply valve to the distribution manifold and
finally to the mask stowage boxes located in the cockpit. Each mask
stowage box has a full face quick donning mask. The LP supply valve
can be switched off from the cockpit for maintenance action as well
as in ground configuration. The system is protected if an overpressure
occurs in a high or low-pressure circuit. The overpressure is vented
overboard. The oxygen pressure condition is indicated on the
DOOR/OXY page of the ECAM system. A test port is used for
distribution leakage tests and a filling port is used for the refilling of
oxygen without removal of the oxygen cylinder.

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CABIN OXYGEN SYSTEM
CHEMICAL OXYGEN SYSTEM
Oxygen masks are released automatically with a cabin depressurization
and an aircraft altitude over 14.000 ft or manually anytime in flight
or on ground via the cockpit oxygen panel or with a manual release
tool. The passenger oxygen system supplies cabin occupants with
oxygen in the case of loss of cabin pressure altitude. The container
doors open electrically. When pulling the mask towards the users face,
the oxygen generator is activated and supplies pure oxygen to the
masks for a limited time. After operation, the system has to be reset
by pushing the OXYGEN TiMeR RESET P/B on the maintenance
panel in order to return the electrical activation system to normal
condition.
The chemical generators are installed in special containers. These
containers are located above the passenger seats, in the lavatories
galleys working areas and at the cabin attendant stations.

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CABIN OXYGEN SYSTEM (continued)

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GASEOUS OXYGEN SYSTEM (OPTIONAL)

The passenger gaseous oxygen system supplies oxygen to each oxygen
container in case of an emergency. The rate of the oxygen flow
depends on the altitude, down to zero at 10.000 ft (3.050 m).
HP oxygen is kept in oxygen cylinder assemblies located behind
sidewall linings in the FWD cargo compartment. The standard system
has 5 oxygen cylinders, plus up to 13 additional oxygen cylinders can
be installed at airline request. When the cabin pressure decreases to
a pressure equivalent to 14.000 ft (4.300 m) the altitude switch closes.
This starts the automatic operation of the oxygen system.
The oxygen regulators open and supply a regulated fllow to the two
main supply lines. The oxygen masks container doors open
pneumatically and the masks fall down. Oxygen only flows to the
masks, which are pulled down. The MASK MANual ON P/B on the
OXYGEN panel can be pushed at any time to manually start the
operation of the oxygen system.
After operation, the system can be reset by pushing the OXYGEN
TMR RESET P/B, this brings the passenger oxygen system back to
the initial configuration and the oxygen regulators will close. The
pressure reducer transmitter and the temperature transducer send
signals to the quantity calculation and control unit. The quantity
calculation and control unit sends a temperature adjusted signal to the
ECAM System Display, which shows the crew the pressure in the
oxygen cylinders. It is also connected to the Central Maintenance
Computer for failures monitoring and system test.

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CONTROL AND INDICATING

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The OXYGEN control panel for crew and passengers, is located on the
cockpit overhead panel. The CREW SUPPLY P/B in OFF position shuts
off the supply from the oxygen cylinder to the crew masks. The MASK
MAN ON P/B electrically controls the opening of the oxygen container
doors. This will be indicated by the SYStem ON light. To reset the
passenger oxygen system the TMR RESET P/B on the maintenance panel
has to be pressed. The P/B also indicates a fault in the system, when the
FAULT light comes in amber.

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COMPONENT LOCATION

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SAFETY PRECAUTIONS

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When you work on the oxygen system, you must obey all the AMM
safety procedures. This will prevent injury to persons and/or damage to
the aircraft. The main safety precautions relative to the oxygen system
are:
- keep all hydrocarbons (fuels, lubricants, etc) away from all oxygen
sources. Oxygen becomes explosive when in contact with hydrocarbons,
- clean the tools and make sure your hands are clean to prevent
contamination of the oxygen system. Be sure that no unwanted particles
go into the oxygen system as they can cause damage to the system,
- use gloves if you need to touch the oxygen generator. It stays hot for at
least two hours after it stops and can burn you,
- be sure to use or remove generator safety items before removal or
installation of a generator. If a component is not safe, the generators can
cause damage or will not operate,
- do not hold the MASK MAN ON P/B in for more than 5 seconds. This
can cause the relays to become too hot and cause damage,
- make sure that the oxygen masks are packed correctly. If not, it is
possible that they will not fall out correctly in an emergency.

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38 WATER AND WASTE SYSTEM PRESENTATION (1)

SYSTEM INTRODUCTION

G6B08031 - G11T4T0 - FM38P4000000001

The water and waste system has:

- the potable water system, which includes the air supply system,
- the waste disposal system.
The water and waste system is linked to the Central Maintenance System
(CMS) for maintenance functions.

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38 WATER AND WASTE SYSTEM PRESENTATION (1)

POTABLE WATER SYSTEM (continued)
AIR SUPPLY SYSTEM
The potable water system is supplied with pressurized air as follows:
- normal supply from the bleed system (Engines or APU ),
- an electrical compressor will pressurize the potable water system,
mainly on ground when the engines or the APU are not available,
- if none of the above is available, a ground connection can be used
by the maintenance staff.

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38 WATER AND WASTE SYSTEM PRESENTATION (1)

WASTE WATER SYSTEM
DRAIN VALVE
Waste water disposal from the galleys and toilets washbasins is
achieved by gravity and by differential pressure. The drain valves are
installed to prevent leakage of cabin air pressure through the drain
lines.

DRAIN MASTS

G6B08031 - G11T4T0 - FM38P4000000001

The waste water is discharged overboard through two drain masts.

To prevent ice formation, the drain masts are electrically heated.

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COMPONENT LOCATION

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38 WATER AND WASTE SYSTEM PRESENTATION (1)

CONTROL AND INDICATING (continued)
VACUUM TOILETS

G6B08031 - G11T4T0 - FM38P4000000001

A waste quantity transmitter installed at the bottom of each tank gives

information through the VSC for the FAP WATER/WASTE page
quantity indication. A tank full sensor confirms the quantity transmitter
" TANK FULL " signal. On the FAP, when the Water/Waste P/B is
pressed, the WATER/WASTE page is displayed. The waste quantity
of the LH and RH waste holding tanks are shown on the FAP. Status
and fault messages of the water and waste systems are displayed on
a dedicated window.

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CONTROL AND INDICATING - VACUUM TOILETS

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MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM38P4000000001

The VSC sends data faults from the toilet and the potable water systems
to the CMCs. Any system condition that requires special crew actions or
information messages will be displayed on the FAP.

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38 WATER AND WASTE SYSTEM PRESENTATION (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM38P4000000001

When you work on the aircraft, make sure that you obey all the AMM
safety procedures. This will prevent injury to persons and/or damage to
the aircraft. Here is an overview of main safety precautions relative to
the water and waste system. Before you start a task make sure that the
warning notices are in position. When you complete the work procedure,
clean your hands with soap and water. This will prevent infection (toilet
waste is dangerous for health. Do not work on the waste system and the
portable water system at the same time. This will prevent contamination
of the potable water system. When you remove a component of the toilet
waste system, always put it in a plastic bag, then seal the bag. Do not put
documents into the plastic bag. Seal the bag first, then attach the document
to it. When you work on the potable water system make sure that the
equipment you use for the procedure is clean and approved for this system.
If not it can cause contamination. Do not touch the water heater until it
is sufficiently cool to prevent burns when you do the maintenance tasks.

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ENVIRONMENTAL PRECAUTIONS

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Do not discharge products such as oil, fuel, solvent, lubricant either in

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28 FUEL SYSTEM PRESENTATION (A330-200) (1)

GENERAL

G6B08031 - G11T4T0 - FM28P8000000003

The fuel system has different functions, which are:

- storage, venting and scavenge,
- engine feed,
- APU feed,
- main and trim transfers,
- refuel/defuel,
- jettison as an option,
- and the maintenance/test facilities.
When you work on A/C, you must obey all the safety procedures listed
in the AMM.

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TANK VENTING

G6B08031 - G11T4T0 - FM28P8000000003

Each wing tank and the trim tank are vented via dedicated vent pipes
connected to their related vent surge tanks. The center tank is vented
through the left wing vent surge tank. A NACA air intake is mounted on
an access panel on each vent surge tank.

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TANK VENTING
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28 FUEL SYSTEM PRESENTATION (A330-200) (1)

ENGINE FEED

G6B08031 - G11T4T0 - FM28P8000000003

An independent fuel feed system supplies each engine. For each engine,
there are two main fuel pumps, and one stand-by pump. In the normal
configuration the main pumps are running and the stand-by pump is there
as a back up when a main pump has a too low output pressure. A LP
valve isolates its related engine from the fuel supply. The crossfeed system
lets any engine be fed from any tank. It is used to correct fuel imbalance
between tanks or during gravity feeding of the engines.

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ENGINE FEED
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MAIN AND TRIM TRANSFERS

G6B08031 - G11T4T0 - FM28P8000000003

The main transfer system controls the fuel flow from the center tank and
the outer tanks to the two inner tanks for engine feeding. The two transfers
are usually controlled automatically by the FCMCs, but they can be
manually controlled if necessary. The trim transfer system controls the
A/C center of gravity by forward and aft transfers. Trim transfers are
controlled automatically by the FCMCs, but a manual forward transfer
can be initiated from the fuel panel if a failure occurs.

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REFUEL/DEFUEL

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On ground, the A/C can be refueled automatically or manually, defueled

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CONTROL AND INDICATING (continued)
REFUEL/DEFUEL

G6B08031 - G11T4T0 - FM28P8000000003

On ground, the A/C can be refueled automatically or manually,

defueled with pressure or suction, and fuel can be transferred from
tank to tank. Two refuel/defuel couplings are installed in the leading
edge of each wing allowing simultaneous refueling from the right and
the left sides of the A/C. Refueling can be controlled and monitored
from the refuel/defuel panel or optionally from the cockpit. The
FCMCs control the refuel/defuel and transfer operations. The option
for the fuel system, which may be selected by operators is additional
Refuel/Defuel panels located at the LH or/and RH wing leading edge.

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SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM28P8000000003

When you work on A/C, make sure that you obey all the AMM safety
procedures. This will prevent injury to persons and/or damage to the A/C.
Here is an overview of the main safety precautions relative to the fuel
system. Kerosene is poisonous. Do not splash A/C fuel in your eyes,
mouth, nose, and ears or on your skin. Use the approved protective
clothing to prevent personal contamination and formation of static
electricity. Make sure that you have the proper fire fighting equipment
available. Make sure that the safety area is clear and clean. Respect the
safety precautions within the safety distances. Put the NO SMOKING
warning notices around the work area. Ground and bond the A/C.
In the Work area:
- do not use flames which do not have protection and do not use any
material/tool which may cause sparks,
- use only necessary and approved electrical/electronic equipment,
- make sure that the air flow is sufficient to work safely, otherwise use a
respirator,
- do not pull or move metal objects along the ground,
- immediately flush away or remove any fuel leakage.

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GENERAL

G6B08031 - G11T4T0 - FM28P8000000004

The fuel system has different functions, which are:

- storage, venting and scavenge,
- engine feed,
- APU feed,
- main and trim transfers,
- refuel/defuel,
- and the maintenance/test facilities.
When you work on A/C, you must obey all the safety procedures listed
in the AMM.

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28 FUEL SYSTEM PRESENTATION (A330-300) (1)

TANK VENTING

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28 FUEL SYSTEM PRESENTATION (A330-300) (1)

MAIN AND TRIM TRANSFERS

G6B08031 - G11T4T0 - FM28P8000000004

The main transfer system controls the fuel flow from the outer tanks to
the two inner tanks for engine feeding. The transfers are usually controlled
automatically by the FCMCs, but they can be manually controlled if
necessary. The trim transfer system controls the A/C center of gravity
by forward and aft transfers. Trim transfers are controlled automatically
by the FCMCs, but a manual forward transfer can be initiated from the
fuel panel if a failure occurs.

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MAIN AND TRIM TRANSFERS

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28 FUEL SYSTEM PRESENTATION (A330-300) (1)

MAIN AND TRIM TRANSFERS (continued)
MAIN TRANSFERS FROM OUTER TANK TO INNER
TANK

G6B08031 - G11T4T0 - FM28P8000000004

The outer tank to inner tank transfer is controlled automatically by

the FCMC when the fuel quantity decreases in one inner tank to a low
level. The crew can control them manually from the fuel panel. The
system uses gravity to transfer the fuel from the outer tanks to the
inner tanks.
The FCMC opens the valves when the inner tank fuel level is too low.
The FCMC commands the LH and RH inter-tank transfer valves
simultaneously in both wings to keep lateral balance.
Two emergency isolation valves control the fuel flow between the
forward and aft inner tanks. The valves are installed between the aft
and forward inner tanks. During normal operation the emergency
isolation valves are open. The crew has to manually close the
emergency isolation valves to isolate the forward inner tank from the
aft inner tank in case of leak in either the forward or aft inner tank.

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MAIN AND TRIM TRANSFERS (continued)
FORWARD TRIM TRANSFERS

G6B08031 - G11T4T0 - FM28P8000000004

During an automatic forward transfer a trim transfer pump moves fuel

from the trim tank to the inner tanks. The fuel can be transferred to
the inner tanks by the trim transfer pump, through the trim tank
isolation valve, the trim pipe isolation valve and the inner tank inlet
valves. The FCMC opens the inner tank inlet valves. In manual mode,
the AUXiliary FWD transfer valve is also controlled to open.

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MAIN AND TRIM TRANSFERS - FORWARD TRIM TRANSFERS

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REFUEL/DEFUEL

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On ground, the A/C can be refueled automatically or manually, defueled

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CONTROL AND INDICATING (continued)
REFUEL/DEFUEL

G6B08031 - G11T4T0 - FM28P8000000004

On ground, the A/C can be refueled automatically or manually,

defueled with pressure or suction. Fuel can be transferred from tank
to tank. A refuel/defuel coupling is installed in the leading edge of
the RH wing allowing refueling of the A/C. Refueling can be
controlled and monitored from the refuel/defuel panel or optionally
from the cockpit. The FCMCs control the refuel/defuel and transfer
operations. The options for the refuel/defuel system is an additional
coupling on the LH wing leading edge as well as additional
refuel/defuel panels located at the LH or/and RHwing leading edges.

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MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM28P8000000004

Each FCMC has a BITE. The BITE continuously monitors the FCMCs
and fuel system components for failures. It is connected to the Centralized
Maintenance Computers (CMC) and can be interrogated from the MCDU
for fuel data reports or test functions.

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28 FUEL SYSTEM PRESENTATION (A330-300) (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM28P8000000004

When you work on A/C, make sure that you obey to all the AMM safety
procedures. This will prevent injury to persons and/or damage to the A/C.
Here is an overview of the main safety precautions relative to the fuel
system. Kerosene is poisonous. Do not splash A/C fuel in your eyes,
mouth, nose and ears or on your skin. Use the approved protective clothing
to prevent personal contamination and formation of static electricity.
Make sure that you have the proper fire fighting equipment available.
Make sure that the safety area is clear and clean. Respect the safety
precautions within the safety distances. Put the NO SMOKING warning
notices around the work area. Ground and bond the A/C.
In the Work area:
- do not use flames which do not have protection and do not use any
material/tool which may cause sparks,
- use only necessary and approved electrical/electronic equipment,
- make sure that the air flow is sufficient to work safely, otherwise use a
respirator,
- do not pull or move metal objects along the ground,
- immediately flush away or remove any fuel leakage.

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26 FIRE PROTECTION SYS PRES. (RR700) (1)

GENERAL

G6B08031 - G11T4T0 - FM26P8000000003

This chapter includes:

- engine fire detection and extinguishing,
- APU fire detection and extinguishing,
- avionics compartment smoke detection,
- cargo compartments smoke detection and FIRE extinguishing,
- cabin and lavatories smoke detection.
It also includes the Maintenance/Test Facilities function.
When you work on the A/C, you must obey all the safety procedures,
including warnings and cautions listed in the Aircraft Maintenance Manual
(AMM).

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ENGINE FIRE PROTECTION (continued)
CONTROL AND INDICATING

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The overhead ENGine FIRE control panel is used for detection and
extinguishing functions. In addition to these indications on the FIRE
panel, there is the ENG MASTER panel located on the pedestal
including a red FIRE indicator light for each engine.

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ENGINE FIRE PROTECTION (continued)
COMPONENT LOCATION

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Each fire detection loop contains 5 detector elements connected in

parallel. The engine fire extinguishing bottles are located in the pylon.
There are access panels on both sides of the pylon.

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APU FIRE PROTECTION (continued)
CONTROL AND INDICATING

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APU FIRE PROTECTION (continued)
COMPONENT LOCATION

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Each APU fire detection loop is a single detector element installed

around the interior of the APU compartment. The APU engine fire
extinguishing bottle is installed in the aft fuselage forward of the APU
firewall. There is an access panel on the lower fuselage. An
overpressure discharge indicator (red disc) is visible from the outside.
The absence of a red disc indicates a bottle overpressure discharge.

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AVIONICS COMPARTMENT SMOKE DETECTION

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The avionics compartment smoke detection is done by two smoke

detectors installed on the air extraction duct of the ventilation system.
The detectors send signals via a dual loop to the Smoke Detection Control
Unit (SDCU). The SDCU gives aural and visual indications in SMOKE
and FAULT conditions.

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AVIONICS COMPARTMENT SMOKE DETECTION
(continued)
CONTROL AND INDICATING

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Avionics smoke is indicated on the VENTILATION panel in the

cockpit. Pilot action on the VENTILATION panel is required as part
of the AVIONICS SMOKE procedure in flight.
- on the VENTILATION panel, the AVioNiCS SMOKE light comes
on,
- on the EXTRACT P/BSW, the FAULT light comes on.

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CARGO COMPARTMENTS SMOKE PROTECTION

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Each cargo compartment has cavities:

- 2 cavities in the FWD cargo compartment,
- 2 cavities in the AFT cargo compartment,
- 1 cavity in the BULK cargo compartment,
and each cavity holds 2 smoke detectors and a fire extinguishing nozzle.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
SMOKE DETECTION

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The cargo compartments smoke protection is done by two systems:

the cargo smoke detection system and the cargo fire extinguishing
system. Smoke detectors are optical type smoke detectors cells. The
smoke detectors are connected to the SDCU via loop A and loop B.
When the SDCU confirms a smoke detection, it triggers warnings in
the cockpit:
- a Continuous Repetitive Chime (CRC) a MASTER WARNing, and
an EWD fault message through the Flight Warning Computer (FWC),
- on the CARGO SMOKE control panel.
When smoke is detected, isolation valves optionally installed in the
affected compartment will automatically close and the extraction fan
will stop.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
FIRE EXTINGUISHING

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Two fire extinguisher bottles located in the forward cargo compartment

are also used for fire extinguishing in the Lower Deck Cargo
Compartments (LDCCs). Each bottle has two discharge heads, one
dedicated for the forward cargo compartment and one for the
AFT/BULK cargo compartment. The extinguishing agent flows
through rigid pipes and is sprayed out through the extinguisher nozzles
in the forward, aft or bulk compartment.
The fire extinguisher bottles can be discharged from the cockpit by
the CARGO SMOKE panel AGENT P/Bs.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
CONTROL AND INDICATING

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The CARGO SMOKE panel on the overhead is used for detection

and extinguishing functions.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
COMPONENT LOCATION

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Each cargo compartment has 2 smoke detectors in each cavity located

in recessed panels in the compartment ceiling. Two fire extinguisher
bottles are located in the FWD cargo compartment.

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AUXILIARY AREAS SMOKE DETECTION
VCC AND IFEC SMOKE DETECTION

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The Video Control Center (VCC) includes 2 smoke detectors on the

extraction air duct, connected to the SDCU. The In-Flight
Entertainment Center (IFEC) includes 2 smoke detectors on the
extraction air duct, connected to the SDCU.

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OPTIONS

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There are some options, which may be selected by operators and which
require fire protection:
- the Flight Crew Rest Compartment (FCRC), installed behind the cockpit,
- the Lower Deck Mobile Crew Rest (LD-MCR) and its associated
staircase housing.

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OPTIONS (continued)
FCRC SMOKE DETECTION

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If installed the FCRC includes a smoke detector connected to the

SDCU.

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OPTIONS (continued)
LD-MCR SMOKE DETECTION

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The LD-MCR smoke detection system operates independently from

the other aircraft smoke detection systems and has 5 smoke detectors
and a crew rest smoke detection control unit. The crew rest smoke
detection control unit transmits a smoke alarm signal to the SDCU
and the SDCU sends a smoke alarm signal to the Ventilation Controller
(VC), the FWC and the CIDS. The staircase housing will have one
smoke detector connected to the SDCU.

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MAINTENANCE/TEST FACILITIES

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Each fire protection system computer has a BITE that tests, manages and
records failures to help maintenance operations.

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SAFETY PRECAUTIONS

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When you work on the A/C, make sure that you obey all the AMM safety
procedures. This will prevent injury to persons and/or damage to the A/C.
Here is an overview of the main safety precautions relative to the fire
protection system. Make sure that there is good airflow through the
working area: fumes from a discharged fire extinguisher bottle can cause
injury to persons. Install or remove the fire detector elements carefully.
You can easily cause damage to them. Move a filled fire extinguisher
bottle carefully: A heavy shock or damage to the frangible disc can cause
unwanted discharge and seriously injure persons who are in the proximity.

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GENERAL

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This chapter includes:

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ENGINE FIRE PROTECTION

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ENGINE FIRE PROTECTION (continued)
CONTROL AND INDICATING

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ENGINE FIRE PROTECTION (continued)
COMPONENT LOCATION

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Each fire detection loop contains 4 detector elements connected in

parallel. The engine fire extinguishing bottles are located in the pylon.
There are access panels on both sides of the pylon.

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APU FIRE PROTECTION

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AVIONICS COMPARTMENT SMOKE DETECTION

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The avionics compartment smoke detection is done by two smoke

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AVIONICS COMPARTMENT SMOKE DETECTION
(continued)
COMPONENT LOCATION

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The two smoke detectors are located in the FWD cargo compartment
in the ventilation extraction duct.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
SMOKE DETECTION

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The cargo compartments smoke protection is done by two systems:

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
CONTROL AND INDICATING

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The CARGO SMOKE panel on the overhead is used for detection

and extinguishing functions.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
COMPONENT LOCATION

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Each cargo compartment has 2 smoke detectors in each cavity located

in recessed panels in the compartment ceiling. Two fire extinguisher
bottles are located in the FWD cargo compartment.

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AUXILIARY AREAS SMOKE DETECTION
VCC AND IFEC SMOKE DETECTION

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The Video Control Center (VCC) includes 2 smoke detectors on the

extraction air duct, connected to the SDCU. The In-Flight
Entertainment Center (IFEC) includes 2 smoke detectors on the
extraction air duct, connected to the SDCU.

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SDCU.

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OPTIONS - FCRC SMOKE DETECTION

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26 FIRE PROTECTION SYSTEM PRES. (GECF6) (1)

OPTIONS (continued)
LD-MCR SMOKE DETECTION

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The LD-MCR smoke detection system operates independently from

the other aircraft smoke detection systems and has 5 smoke detectors
and a crew rest smoke detection control unit. The crew rest smoke
detection control unit transmits a smoke alarm signal to the SDCU
and the SDCU sends a smoke alarm signal to the Ventilation Controller
(VC), the FWC and the CIDS. The associated staircase housing will
have one smoke detector connected to the SDCU.

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26 FIRE PROTECTION SYSTEM PRES. (GECF6) (1)

OPTIONS (continued)
LD-MCR FIRE EXTINGUISHING

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MAINTENANCE/TEST FACILITIES

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

GENERAL

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This chapter includes:

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GENERAL
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ENGINE FIRE PROTECTION

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ENGINE FIRE PROTECTION

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ENGINE FIRE PROTECTION (continued)
COMPONENT LOCATION

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Each fire detection loop contains 3 detector elements connected in

parallel. The engine fire extinguishing bottles are located in the pylon.
There are access panels on both sides of the pylon.

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APU FIRE PROTECTION

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

AVIONICS COMPARTMENT SMOKE DETECTION

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The avionics compartment smoke detection is done by two smoke

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

AVIONICS COMPARTMENT SMOKE DETECTION
(continued)
COMPONENT LOCATION

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The two smoke detectors are located in the FWD cargo compartment
in the ventilation extraction duct.

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
SMOKE DETECTION

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The cargo compartments smoke protection is done by two systems:

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
CONTROL AND INDICATING

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The CARGO SMOKE panel on the overhead is used for detection

and extinguishing functions.

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CARGO COMPARTMENTS SMOKE PROTECTION
(continued)
COMPONENT LOCATION

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Each cargo compartment has 2 smoke detectors in each cavity located

in recessed panels in the compartment ceiling. Two fire extinguisher
bottles are located in the FWD cargo compartment.

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CABIN AND LAVATORIES FIRE PROTECTION

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AUXILIARY AREAS SMOKE DETECTION
VCC AND IFEC SMOKE DETECTION

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The Video Control Center (VCC) includes 2 smoke detectors on the

extraction air duct, connected to the SDCU. The In-Flight
Entertainment Center (IFEC) includes 2 smoke detectors on the
extraction air duct, connected to the SDCU.

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SDCU.

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OPTIONS - FCRC SMOKE DETECTION

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OPTIONS (continued)
LD-MCR SMOKE DETECTION

G6B08031 - G11T4T0 - FM26P8000000005

The LD-MCR smoke detection system operates independently from

the other aircraft smoke detection systems and has 5 smoke detectors
and a crew rest smoke detection control unit. The crew rest smoke
detection control unit transmits a smoke alarm signal to the SDCU
and the SDCU sends a smoke alarm signal to the Ventilation Controller
(VC), the FWC and the CIDS. The associated staircase housing will
have one smoke detector connected to the SDCU.

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26 FIRE PROTECTION SYSTEM PRES. (PW4000) (1)

OPTIONS (continued)
LD-MCR FIRE EXTINGUISHING

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MAINTENANCE/TEST FACILITIES

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49 APU SYSTEM PRESENTATION (1)

GENERAL

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The Auxiliary Power Unit (APU) is a constant-speed gas turbine engine.

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CONTROL AND INDICATING
This section will highlight the control panels and indications for the APU.

CONTROL PANELS

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The controls used to operate the APU are:

- the APU MASTER SWitch and START P/BSW, on the APU control
panel,
- the APU fire controls, on the APU fire panel.

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CONTROL AND INDICATING - CONTROL PANELS

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49 APU SYSTEM PRESENTATION (1)

CONTROL AND INDICATING (continued)
EXTERNAL CONTROLS

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It is possible to do an emergency shut down of the APU from either

the REFUEL/DEFUEL panel or the EXTERNAL PWR panel by
lifting the guard and pushing either the APU EMERGENCY P/BSW
or the APU SHUT OFF P/BSW.

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CONTROL AND INDICATING - EXTERNAL CONTROLS

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COMPONENT LOCATION
The APU is installed in the tail section of the fuselage.

ENGINE VIEW

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The left and right hand sides of the APU are shown.

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COMPONENT LOCATION - ENGINE VIEW

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49 APU SYSTEM PRESENTATION (1)

COMPONENT LOCATION (continued)
OIL

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The oil, contained in the gearbox sump, is used to lubricate, to clean

and to cool the APU bearings and the accessory gearbox. The oil cools
and lubricates the gearbox mounted AC generator. The oil system has
a lubrication module for distribution, filtration, scavenging, and oil
cooler.

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COMPONENT LOCATION - OIL

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COMPONENT LOCATION (continued)
AIR

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The main role of the APU air system is to supply pressurized air to
the A/C pneumatic system. This is achieved by the APU load
compressor. The ECB controls and operates the bleed valve for air
supply. The ECB also controls and operates the IGVs for flow
regulation, and the surge control valve for surge protection.

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COMPONENT LOCATION - AIR

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COMPONENT LOCATION (continued)
ECB

G6B08031 - G11T4T0 - FM49P3000000001

The ECB is in the bulk cargo compartment on the Right Hand side.
A Data Memory Module (DMM) is installed on the Left Hand side
of the APU.

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COMPONENT LOCATION - ECB

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MAINTENANCE/TEST FACILITIES

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The Central Maintenance Computers (CMCs) let the maintenance crew

analyze failure data present in the ECB BITE via the Multipurpose Control
& Display Units (MCDUs).

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49 APU SYSTEM PRESENTATION (1)

SAFETY PRECAUTIONS

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ENVIRONMENTAL PRECAUTIONS
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A330-200/300 TECHNICAL TRAINING MANUAL

70 POWER PLANT RR TRENT 700 PRESENTATION (1)

POWERPLANT INTRODUCTION

G6B08031 - G11T4T0 - FM70PB000000071

The Rolls-Royce RB211-Trent 772 series engine is an axial flow, triple

spool, high bypass-ratio, turbo-fan engine. The RR RB-211Trent 772
powers the A330 aircraft and produces approximately 71.000 lbf. of
thrust.

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POWERPLANT INSTALLATION

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The powerplant installation includes the engine inlet, the engine assembly,
the exhaust common nozzle assembly, the fan cowls and thrust reverser
assemblies. The FORWARD and AFT engine mounts attach the engine
to the aircraft pylon and support the weight of the engine and transmit
thrust loads to the aircraft structure.

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MODULAR ENGINE DESIGN

G6B08031 - G11T4T0 - FM70PB000000071

The RR RB-211Trent 772 is designed using a modular concept. The

modules may be replaced independently to reduce the time required to
return the engine into service. The modules are:
- module 01: LP compressor rotor,
- module 02: IP (Intermediate Pressure) compressor,
- module 03: Intermediate case,
- module 04: HP system (this includes the HP compressor, the combustion
system and the HP turbine),
- module 05: IP turbine,
- module 06: External gearbox,
- module 07: LP compressor case,
- module 08: LP turbine.

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MODULAR ENGINE DESIGN

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MODULAR ENGINE DESIGN (continued)
IP ROTOR

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The IP rotor has an 8-stage IP compressor driven by a single-stage IP

turbine. The IP compressor supplies primary airflow to the
high-pressure compressor for combustion. The speed of the IP rotor
is indicated on the ECAM as N2.
1 ball and 2 roller bearings support the IP rotor and are lubricated and
cooled. The Intermediate case is the location for the forward engine
mount.

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MODULAR ENGINE DESIGN (continued)
HP ROTOR

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The HP rotor is made of a 6-stage HP compressor driven by a

single-stage HP turbine. The HP compressor is also the source of
customer bleed air. The speed of the HP rotor is indicated on the
ECAM as N3. The HP rotor is supported by 1 ball and 1 roller bearing,
which are lubricated and cooled.
The annular combustion chamber is installed between the HP
compressor and HP turbine. It has ports for 24 fuel nozzles and 2
igniter plugs.

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MODULAR ENGINE DESIGN - HP ROTOR

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MODULAR ENGINE DESIGN (continued)
ACCESSORY DRIVE

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The external gearbox is attached to the bottom of the LP compressor

case and is driven by the HP rotor through an internal gearbox. The
fuel pump, oil pump assembly, hydraulic pumps, Integrated Drive
Generator (IDG) and the Electronic Engine Controller (EEC)
Dedicated Alternator are all attached to and driven by the external
gearbox.
The starter is also attached to the external gearbox. During engine
starting, the starter rotates the HP compressor through the external
and internal gearboxes.

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communication with the EEC (thrust lever position, air data, ECAM
Primary indications, etc.) is direct to and from the applicable systems
and controls. Non-essential communication (autothrust, Central
Maintenance System (CMS), etc) is routed through the Engine Interface
and Vibration Monitoring Unit (EIVMU) of each engine. The EIVMUs
interface with various aircraft circuits and systems. The data is then
transmitted in a single stream to each EEC channel.
Engine vibration monitoring is also accomplished by the EIVMU. Each
EIVMU collects vibration data from the vibration sensor on the engine.
The vibration information is displayed on the ECAM and is also available
through the CMS for troubleshooting.

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ENGINE FUEL SYSTEM

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The engine fuel system is designed to supply metered fuel to the

combustion chamber according to the engine power demand. The fuel
system is also used to cool the engine oil and supply servo pressure to
operate valves and actuators.
The Engine Electronic Controller (EEC) controls the operation of the
engine fuel system. The EEC also monitors the system for normal
operation and ECAM fuel flow indication.

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ENGINE FUEL SYSTEM

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OIL SYSTEM

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The primary function of the oil system is to supply sufficient oil at the
correct temperature and pressure to the engine internal drives, gears and
bearings for lubrication, to decrease temperature and keep wear to a
minimum. The oil system is also designed to heat the fuel to prevent fuel
icing.

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IP & HP BLEED VALVES

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Seven bleed valves are installed around the IP and HP compressor. Four
IP bleed valves are installed on and around the compressor intermediate
case and aligned with stage 8 of the IP compressor. Three HP bleed valves
are installed at the front of the combustion outer case and aligned with
stage 3 of the HP compressor. Two HP bleed valves, HP3.3 and HP3.2,
are installed at the top right and bottom right of the case. The third one,
HP3.1, is installed at the bottom left of the case.
These valves are operated by servo (muscle) air pressure from the HP
compressor third stage (HP3). The servo pressure to operate each bleed
valve is controlled through the bleed valve solenoid unit based upon
signals from the EEC.

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IP & HP BLEED VALVES

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IGNITION AND STARTING SYSTEM

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The Engine Electronic Controller (EEC) selects engine starting, motoring

and ignition sequences according to digital command inputs from the
Engine Interface and Vibration Monitoring Unit (EIVMU). To achieve
these functions, the following sub-systems are combined:
- starting,
- fuel,
- ignition.

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IGNITION AND STARTING SYSTEM

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THRUST REVERSER SYSTEM

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CONTROL AND INDICATING
CONTROL PANELS

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The engines are controlled by throttle control levers, which are

installed on the center pedestal. They can only be moved manually.
To select reverse thrust operation, each throttle control lever includes
a reverse thrust control lever. This lever is also used to increase engine
power in reverse.
Autothrust mode is the most efficient mode of operation in flight.
When active, the autothrust can be disconnected using the two
instinctive disconnect pushbuttons. These 2 red buttons are installed
on the outside of each throttle control lever. This allows the engines
to be controlled in manual thrust mode.
The controls for engine starting and shut down are installed on the
center pedestal just behind the throttle control levers. The engine
MAN START switches are installed on the overhead panel. These
switches are used to initiate an engine manual start procedure. They
are also used to initiate an engine dry or wet motoring procedure. The
N1 mode switches are used to switch the primary engine control
parameter to N1 if the normal EPR control fails.

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CONTROL AND INDICATING (continued)
ECAM ENGINE INDICATIONS

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The engine primary parameters are permanently displayed on the

upper ECAM Engine/Warning Display. The engine secondary
parameters are shown on the lower ECAM ENGINE page when it is
selected or displayed automatically during an engine start or a fault.
Bleed pressure, Starter valve position and ignition are displayed during
engine start only. Some engine parameters are permanently displayed
on the CRUISE page in flight.

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COMPONENT LOCATION (continued)
STARTING

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Two ignition exciter units are installed on the fan case, on the left
hand side. The starter air valve is found on the fan case, on the left
hand side. The starter is attached to the front face of the external
gearbox and also on the left hand side.

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COMPONENT LOCATION - STARTING

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COMPONENT LOCATION (continued)
AIR

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The main functions of the engine air systems are compressor control,
and turbine clearance control. The EEC controls both systems.
The VSV system and the IP/HP Compressor Bleed Valves are the
primary compressor control systems. These systems let the engine
operate efficiently during starting, acceleration and deceleration:
- 2 fuel-powered actuators operate the VSV system installed on either
side of the compressor case which move the variable inlet guide vanes
and the first 2 rows of the intermediate pressure compressor stator
vanes.
- the solenoids control and operate with high air pressure the IP and
HP Bleed valves . There are four IP8 (intermediate compressor stage
8) and three HP3 (high pressure compressor stage 3) bleed valves
found on the engine.
The Turbine Impingement Cooling (TIC) system increases engine
efficiency by controlling turbine blade tip clearances. The TIC valve
is operated by high-pressure air and controls the supply of fan air to
the IP and LP turbine case manifolds to keep the case temperatures
within limits and to control the IP turbine blade tip clearances.

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COMPONENT LOCATION (continued)
THRUST REVERSER

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The Isolation Control Unit is installed on the pylon and the Direction
Control Unit is installed in the front face of the RH side thrust reverser
half.
The thrust reverser operating components for each side are installed
in the front face of each thrust reverser half.

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MAINTENANCE/TEST FACILITIES

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On the maintenance panel, the ENG FADEC GND PWR is used to supply
the FADEC system for maintenance tasks, when the engines are not
running. The MCDU is used to get access to the CMS f tests and for
troubleshooting monitored components (computers, sensors, actuators).

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SAFETY PRECAUTIONS
When you work on aircraft, make sure that you obey all the AMM safety
procedures. This will prevent injury to personnel and/or damage to the
aircraft. Here is an overview of the main safety precautions related to the
engines:
- make sure that all engine danger areas are as clear as possible to prevent
damage to the engine, the aircraft or personnel in the area,
- make sure that you have fire-fighting equipment available,
- do not try to stop the fan from turning by hand,
- after engine shutdown, let the oil tank pressure bleed off a minimum of
5 minutes before you remove the tank filler cap. If you do not, pressurized
oil can spray out of the tank and cause dangerous burns,
- the engine ignition system is an electrical system with high energy. Do
not do maintenance on the ignition system while operating the engine.
There is a danger of serious electrical shock. Make sure that the engine
shutdown occurred a minimum of 5 minutes before you proceed,
- make sure that the thrust reverser is deactivated during maintenance. If
not, the thrust reverser can operate accidentally and cause injury to
personnel and/or damage to the reverser.
When opening the engine cowls:
- respect the wind limitations and the opening/closing sequence,
- always secure cowls with the hold-open rods,
- make sure that the slats are retracted and install a warning notice to
prevent slat operation.

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STORAGE AND PRESERVATION
Storage and preservation procedures must be applied for engines being
not operated for a period of time according to the AMM. The preservation
procedures protect the engine against corrosion, liquid and debris entering
the engine, and atmospheric conditions during period of inactivity.

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CAUTION: under no circumstances shall preservative oil or equivalent

be sprayed into the engine inlet, core compressor or turbine,
or engine exhaust. Dirt particles on wet blades and vanes
may adversely affect engine performance during subsequent
operation.

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STORAGE AND PRESERVATION

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ENVIRONMENTAL PRECAUTIONS

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Do not discharge products such as oil, fuel, solvent, lubricant either in

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POWERPLANT INTRODUCTION

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The CF6-80E1 series engine is an axial flow, dual spool, high

bypass-ratio, and turbo-fan engine. The CF6-80E1 powers the A330
aircraft and produces, depending on the version, 70.000 lbf or 72.000 lbf
of maximum thrust.

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POWERPLANT INSTALLATION

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The powerplant installation includes the engine inlet, the engine assembly,
the exhaust, fan cowls and thrust reverser assemblies. The engine is
attached to the aircraft pylon by the FWD and AFT engine mounts, which
support the weight of the engine and transmit thrust loads to the aircraft
structure.

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MODULAR CONCEPT

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The CF6-80E1 engine is designed using a modular concept. For ease of

maintenance and quicker return-to-service, the engine is built up with
the following main modules:
- fan and LP compressor module (includes forward fan and booster (LP
compressor)),
- HP compressor module,
- High Pressure Turbine (HPT) module,
- Low Pressure Turbine (LPT) module,
- transfer and accessory drive module (includes transfer and accessory
gearboxes).

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MODULAR CONCEPT (continued)
HP ROTOR

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The HP rotor is made of a 14-stage HP compressor driven by a 2-stage

HP turbine. The HP compressor is also the source of customer bleed
air. The HP rotor is supported by roller and ball bearings, which are
lubricated and cooled. The speed of the HP rotor is indicated on the
ECAM as N2. The N2 speed indication is given by the N2 speed
sensor installed on the forward right side of the accessory gearbox,
inboard of the HydroMechanical Unit (HMU), and connected to the
ECU
The annular combustion chamber is located between the HP
compressor and HP turbine. It has ports for 30 fuel nozzles and 2
igniter plugs.

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MODULAR CONCEPT - HP ROTOR

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MODULAR CONCEPT (continued)
TRANSFER AND ACCESSORY GEARBOXES

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The accessory gearbox is located at the bottom of the HP compressor

case and is driven by the HP rotor through the transfer gearbox.
The HydroMechanical Unit (HMU), fuel pump, oil lube and scavenge
pumps, hydraulic pumps, Integrated Drive Generator (IDG) and the
Full Authority Digital Engine Control (FADEC) Permanent Magnet
Alternator (PMA) are all attached to and driven by the accessory
gearbox. The starter is also attached to the accessory gearbox. During
engine starting, the starter rotates the HP compressor through both
gearboxes.

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communication with the ECU (thrust lever position, air data, ECAM
Primary indications, etc.) is direct to and from the applicable systems
and controls. Non-essential communication (autothrust, Central
Maintenance System (CMS), etc) is routed through the Engine Interface
and Vibration Monitoring Unit (EIVMU) of each engine. The EIVMU's
interface with various aircraft circuits and systems. The data is then
transmitted in a single stream to each ECU channel.
Engine vibration monitoring is also accomplished by the EIVMU. Each
EIVMU collects vibration data from 2 vibration sensors on the engine.
The vibration information is displayed on the ECAM and is also available
through the CMS for troubleshooting.

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OIL SYSTEM

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The engine oil system is a full flow recirculatory system monitored by

the ECU. It must provide adequate lubrication and cooling for all engine
bearings and gears.
The oil pick-up at oil tank is pressurized by the oil pump and supplied
to the Servo Fuel Heater and Main Fuel/Oil Heat Exchanger (FOHE).
The oil is thus pressurized and cooled before reaching the internal drive
gears and bearings. Oil is then returned to the oil tank by several scavenge
lines, each one being connected to a dedicated scavenge pump. Scavenged
oil is passing through a scavenge filter before returning into the oil tank.

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COOLING AND SEALING SYSTEM (continued)
ENGINE INTERNAL AIR SYSTEM

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The internal air system has the following subsystems:

- propulsion airflow (secondary and primary flows) for the cooling
of several systems,
- forward and aft bearing sump pressurizing air for sealing,
- internal thrust balancing air that prevents overloading of the thrust
bearings.

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COOLING AND SEALING SYSTEM (continued)
ENGINE EXTERNAL AIR SYSTEM

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The external air system has the following subsystems:

- Core compartment cooling, located on the upper left hand side and
around the HP compressor. It cools the core compartment airspace.
- High-Pressure and Low-Pressure Turbine Active Clearance Control
provided by fan discharge air to cool and shrink. The flow rate is
controlled by the Electronic Control Unit (ECU) and the Hydro
Mechanical Unit (HMU) according to engine operating conditions.
- Integrated Drive Generator (IDG) cooling system located along the
HP compressor and accessory gearbox. It cools the IDG oil.
- Bore cooling, attached to the aft fan case. It cools the HP compressor
rotor.

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AIRFLOW CONTROL SYSTEM

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At lower speeds, the engine compressor airflow becomes unstable

specially during acceleration, deceleration and transient.
It is therefore necessary to have an airflow control system to provide a
stable airflow during starting and low speed operations.
The airflow control has two systems: Variable Bleed Valve (VBV) and
Variable Stator Vane (VSV) system. Both systems are controlled by the
Electronic Control Unit (ECU).

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AIRFLOW CONTROL SYSTEM

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THRUST CONTROL SYSTEM

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The engine thrust is controlled under the management of the Electronic

Control Unit (ECU). The main thrust parameter is the N1 speed.
The engine thrust can be set:
- manually from the throttle control lever or,
- automatically from the Auto Flight System (AFS).
The engine thrust parameters are displayed on the ECAM.

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THRUST CONTROL SYSTEM

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CONTROL AND INDICATING (continued)
ECAM ENGINE INDICATIONS

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The engine primary parameters are permanently displayed on the

upper ECAM Engine/Warning Display (EWD). The engine secondary
parameters are shown on the lower ECAM System Display (SD)
ENGINE page when it is selected or displayed automatically during
an engine start or a fault. Bleed pressure, Starter valve position and
ignition are displayed during engine start only. Some engine
parameters are permanently displayed on the CRUISE page in flight.

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COMPONENT LOCATION (continued)
STARTING

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Two ignition exciter units are located on the fan case, on the left hand
side. The air starter and starter air valve are located on the gearbox
aft face.

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COMPONENT LOCATION - STARTING

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COMPONENT LOCATION (continued)
AIR

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COMPONENT LOCATION (continued)
THRUST REVERSER

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The thrust reverser operating components for each side are located in
the front face of the left and right thrust reverser cowl structure:
- CDU,
- upper and lower ball-screw actuators,
- Thrust Reverser Pressurizing Valve (TRPV),
- Thrust Reverser Directional Valve (TRDV),
- disk brake.

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COMPONENT LOCATION - THRUST REVERSER

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MAINTENANCE/TEST FACILITIES

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On the maintenance panel, the ENG FADEC GND PWR is used to supply
the FADEC system for maintenance tasks, when the engines are not
running. The MCDU is used for the access to the CMS to make the tests
and for troubleshooting monitored components (computers, sensors,
actuators).

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SAFETY PRECAUTIONS
When you work on aircraft, make sure that you obey all the AMM safety
procedures. This will prevent injury to personnel and/or damage to the
aircraft. Here is an overview of the main safety precautions related to the
engines:
- make sure that all engine danger areas are as clear as possible to prevent
damage to the engine, the aircraft or personnel in the area,
- make sure that you have fire-fighting equipment available,
- do not try to stop the fan from turning by hand,
- after engine shutdown, let the oil tank pressure bleed off a minimum of
5 minutes before you remove the tank filler cap. If you do not, pressurized
oil can spray out of the tank and cause dangerous burns,
- the engine ignition system is an electrical system with high energy. Do
not do maintenance on the ignition system while operating the engine.
There is a danger of serious electrical shock. Make sure that the engine
shutdown occurred a minimum of 5 minutes before you proceed:
- make sure that the thrust reverser is deactivated during maintenance. If
not, the thrust reverser can operate accidentally and cause injury to
personnel and/or damage to the reverser.
When opening the engine cowls:
- respect the wind limitations and the opening/closing sequence,
- always secure cowls with the hold-open rods.

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WARNING: ALL SAFETY PRECAUTIONS MUST BE APPLIED.

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ENVIRONMENTAL PRECAUTIONS
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POWERPLANT INTRODUCTION

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BASIC ENGINE DESIGN

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The PW-4168 engine is designed around the following basic sections:

- fan and booster Low Pressure Compressor (LPC),
- High Pressure Compressor (HPC),
- combustion chamber,
- High Pressure Turbine (HPT),
- Low Pressure Turbine (LPT),
- accessory drive section (main and transfer/angle gearboxes).

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BASIC ENGINE DESIGN

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BASIC ENGINE DESIGN (continued)
HP ROTOR

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The High Pressure (HP) rotor is made of an 11-stage HP compressor

driven by a 2-stage HP turbine. The speed of the HP rotor is indicated
on the ECAM as N2. The HPC is also the source of customer bleed
air. The HP rotor is supported by 1 ball and 1 roller bearing, which
are lubricated and cooled. The annular combustion chamber is located
between the HPC and HPT. It is equipped with ports for 24 fuel
nozzles and 2 igniter plugs.The engine N2 speed output is produced
from a winding of the PMA.

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BASIC ENGINE DESIGN - HP ROTOR

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FADEC
In order to increase engine reliability and efficiency, the Full Authority
Digital Engine Control (FADEC) system provides full range of engine
control to achieve steady state and transient engine performances when
operated in combination with aircraft subsystems. Each engine is
controlled by an Electronic Engine Control (EEC), which is a dual channel
computer located on the engine fan case. The EEC controls the engine
during start and all operations. It manages engine thrust and protects
against over speed and over temperature by controlling the engine
subsystems. The EEC also monitors all engine subsystems and sensors
for failure. When the engine is running, power for FADEC operation is
provided by a dual-output FADEC PMA.
The FADEC system consists of the EEC and the following peripherals:
- FMU,
- FADEC PMA,
- compressor control systems (Variable Bleed Valve (VBV), Variable
Stator Vane (VSV), 2.9 Bleed),
- Turbine Case Cooling system (TCC),
- Start system (starter shutoff valve, ignition exciters),
- thrust reverser system,
- IDG cooling system,
- engine sensors,
- electrical harnesses.

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FADEC
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EIVMU

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The EEC interfaces with various aircraft systems. Essential

communication with the EEC (thrust lever position, air data, ECAM
Primary indications, etc.) is direct to and from the applicable systems
and controls. Non-essential communication (A/THR, Central Maintenance
System (CMS), etc) is routed through the Engine Interface and Vibration
Monitoring Unit (EIVMU) of each engine. The EIVMUs interface with
various aircraft circuits and systems. The data is then transmitted in a
single stream to each EEC channel.
Engine vibration monitoring is also accomplished by the EIVMU. Each
EIVMU collects vibration data from 2 vibration sensors on the engine.
The vibration information is displayed on the ECAM and is also available
through the CMS for troubleshooting.

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EIVMU
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OIL SYSTEM

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The engine oil system has three sub-systems: the engine oil distribution
system, the engine oil scavenge system and the engine breather
system.The self-contained oil system lubricates, cleans and cools the
engine gears, bearings and accessories. It removes air from the system
and vents it overboard.

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OIL SYSTEM
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COOLING AND SEALING SYSTEM (continued)
ENGINE BEARING COOLING SYSTEM

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The engine bearing cooling system is used to remove excess heat from
the number 3 bearing compartment.

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COOLING AND SEALING SYSTEM - ENGINE BEARING COOLING SYSTEM

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AIRFLOW CONTROL SYSTEM

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The compressor control system gives a better compressor stability during

engine starting, transient, and reverse thrust operations.
The two subsystems including the compressor control system, are the
compressor stator vane control system and the compressor bleed control
system.
The Electronic Engine Control (EEC), controls these systems.

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AIRFLOW CONTROL SYSTEM

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THRUST CONTROL SYSTEM

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The engine thrust is controlled under the management of the Electronic

Engine Control (EEC).
The engine thrust can be set:
- manually from the throttle control lever or,
- automatically from the Auto Flight System (AFS).
The engine thrust parameters are displayed on the ECAM.

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THRUST CONTROL SYSTEM

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THRUST REVERSER SYSTEM

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CONTROLS AND INDICATING (continued)
ECAM ENGINE INDICATIONS

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The engine primary parameters are permanently displayed on the

upper ECAM EWD. The engine secondary parameters are shown on
the lower ECAM SD ENGINE page when it is selected or displayed
automatically during an engine start or a fault. Bleed pressure, Starter
valve position and ignition are displayed during engine start only.
Some engine parameters are permanently displayed on the CRUISE
page in flight.

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CONTROLS AND INDICATING - ECAM ENGINE INDICATIONS

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COMPONENT LOCATION (continued)
STARTING

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Two ignition exciter units are located on the HPC case, on the right
hand side. The air starter and starter air valve are located on the
gearbox aft face, on the right hand side.

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COMPONENT LOCATION - STARTING

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COMPONENT LOCATION (continued)
AIR

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The main functions of the engine air systems are compressor control,
and Turbine Case Cooling (TCC) (clearance control).
The VBV system and the VSV system are the primary compressor
control systems. The VBV system is operated by a fuel-powered
actuator located on the left hand side of the compressor case. The
actuator opens and closes the annular bleed valve located around the
fan case. The VSV system is operated by 2 fuel-powered actuators
located on either side of the compressor case, which move the variable
inlet guide vanes and the first 3 rows of HP stator vanes. The left and
right Start/Stability 2.9 Bleed valves are open during engine start and
during engine transient conditions. The 2.5 bleed system is used to
control LPC discharge airflow.
The TCC system increases engine efficiency by controlling turbine
blade tip clearances. The fuel-powered TCC actuator controls the low
pressure and HPT valves to fan air to cool the cases.
The 2.5 bleed valve actuator is located on the LH compressor case.

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COMPONENT LOCATION - AIR

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COMPONENT LOCATION - AIR

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COMPONENT LOCATION (continued)
THRUST REVERSER

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With the exception of the isolation valve located in the pylon, the
thrust reverser operating components for each side are located on the
front face of the left and right thrust reverser cowl structure. The
Directional valve is located on the RH side.

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MAINTENANCE/TEST FACILITIES

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On the maintenance panel, the ENG FADEC GND PWR is used to supply
the FADEC system for maintenance purposes, when the engines are not
running. The MCDU is used to access the CMS to perform tests and for
troubleshooting monitored components (computers, sensors, actuators).

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SAFETY PRECAUTIONS
When you work on aircraft, make sure that you obey all the Aircraft
Maintenance Manual (AMM) safety procedures. This will prevent injury
to personnel and/or damage to the aircraft. Here is an overview of the
main safety precautions related to the engines:
- make sure that all engine danger areas are as clear as possible to prevent
damage to the engine, the aircraft or personnel in the area,
- make sure that you have fire-fighting equipment available,
- do not try to stop the fan from turning by hand,
- after engine shutdown, let the oil tank pressure bleed off a minimum of
5 minutes before you remove the tank filler cap. If you do not, pressurized
oil can spray out of the tank and cause dangerous burns,
- the engine ignition system is an electrical system with high energy. Do
not do maintenance on the ignition system while operating the engine.
There is a danger of serious electrical shock. Make sure that the engine
shutdown occurred a minimum of 5 minutes before you proceed,
- make sure that the thrust reverser is deactivated during maintenance. If
not, the thrust reverser can operate accidentally and cause injury to
personnel and/or damage to the reverser.
When opening the engine cowls:
- respect the wind limitations and the opening/closing sequence,
- always secure cowls with the hold-open rods.

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WARNING: ALL SAFETY PRECAUTIONS MUST BE APPLIED.

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

GENERAL

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The pneumatic system is used to supply air to various A/C systems. This
module describes:
- the system sources and users,
- the engine, APU and HP Ground Unit bleed air management system,
- the leak detection system,
- the control and indicating,
- the maintenance and test facilities.
When you work on A/C, you must obey all the safety procedures listed
in the AMM.

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SOURCES AND USERS
The pneumatic system may be supplied with High Pressure (HP) bleed
air from 3 types of sources:
- ground cart,
- APU,
- engines.
The bleed air is distributed to the different users via a distribution and
supply ducting network. These users are:
- the water system pressurization,
- the hydraulic reservoir pressurization,
- the wing anti-icing system,
- the engines starting systems,
- the packs bay ventilation system,
- the air conditioning packs,
The pneumatic system operates pneumatically and is monitored by two
Bleed Monitoring Computers (BMCs) one, two.
There is one BMC for each engine bleed system. Both BMCs exchange
data. If one BMC fails, the other BMC takes over most of its monitoring
functions.

(OPV) is installed downstream from the bleed valve to protect the

system in case of overpressure.
The temperature of the engine bleed air is regulated to a maximum
value. The hot bleed air goes through an air-to-air heat exchanger
called the precooler. Fan discharge air modulated by the Fan Air Valve
(FAV), blows across the precooler to maintain the temperature within
limits.

APU BLEED/HP GROUND UNIT BLEED

A crossbleed duct connects the left and right bleed systems. A
crossbleed valve enables 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. However, APU
BLEED air could also be used in flight, depending on altitude. The
APU bleed supply is connected to the left side of the crossbleed duct.
On the ground, a HP ground power unit can be connected to the left
side pneumatic system. The right side may be supplied by opening
the crossbleed valve.

G6B08031 - G11T4T0 - FM36P5000000003

ENGINE BLEED
The engine bleed air is pressure and temperature regulated prior to
supplying the pneumatic system. Air is bled from the Intermediate
Pressure Compressor (IPC) stage or the High Pressure Compressor
(HPC) stage.
The HP bleed is only used when the engines are at low power. Once
the IP bleed is sufficient, the High Pressure Valve (HPV) closes.
All the engine bleed air is supplied to the pneumatic system through
the main engine BLEED valve (or Pressure Regulating Valve (PRV)),
which acts as a shut off and overall system pressure regulating valve.
Each BMC monitors system pressure and will shut down the engine
bleed in case of excessive pressure. In addition, an overpressure valve
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SOURCES AND USERS - ENGINE BLEED & APU BLEED/HP GROUND UNIT BLEED
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
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LEAK DETECTION

G6B08031 - G11T4T0 - FM36P5000000003

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. A dual loop detection system is installed in the wings,
the mid fuselage above the air conditioning packs area and on the APU
bleed duct. Two loops A and B are routed in parallel along the air ducts.
An "AND" logic ensures the interconnection of the loops in the BMCs
to prevent spurious warnings. In each engine pylon, a single detection
loop ensures the leak detection.
The leak detection loops are connected to the BMCs. If a leak is detected,
a signal is sent to the BMC one, or two, which automatically isolates the
affected area, triggers a warning signal to the ECAM system through the
System Data Acquisition Concentrator (SDAC) and sends a fault message
to the Central Maintenance Computer (CMC).

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LEAK DETECTION
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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

CONTROL AND INDICATING
This section highlights the control panels and indications for the
pneumatic system.

CONTROL PANEL

G6B08031 - G11T4T0 - FM36P5000000003

Controls for the pneumatic system are part of the AIR COND panel,
located on the overhead panel.

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PART 2 OUT OF 2

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CONTROL AND INDICATING - CONTROL PANEL

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PART 2 OUT OF 2

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

CONTROL AND INDICATING (continued)
ECAM INDICATION

G6B08031 - G11T4T0 - FM36P5000000003

The pneumatic system indications are displayed on the lower part of

the ECAM BLEED page.

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PART 2 OUT OF 2

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Page 648

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CONTROL AND INDICATING - ECAM INDICATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

COMPONENT LOCATION
The main components of the pneumatic system are located on the engines
and in the pylons.

ENGINE BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000003

The IPC, the High Pressure Valve (HPV), the PRV, the FAV are
located on the engine. The OPV and the precooler are located in the
pylon.

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PART 2 OUT OF 2

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COMPONENT LOCATION - ENGINE BLEED COMPONENTS

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PART 2 OUT OF 2

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

COMPONENT LOCATION (continued)
APU AND X BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000003

The crossbleed valve is located in the forward section of the lower

fuselage belly fairing area. Get access to the HP ground connector
through a small access door located on the lower fuselage belly fairing.
The APU bleed valve is located on the APU.

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PART 2 OUT OF 2

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COMPONENT LOCATION - APU AND X BLEED COMPONENTS

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM36P5000000003

The CMCs let the maintenance crew read the failure data in the BMCs
BITE via the MCDUs.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

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MAINTENANCE/TEST FACILITIES
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

36 PNEUMATIC SYS PRESENTATION (RR700) (1)

Jan 15, 2008

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36 PNEUMATIC SYS PRESENTATION (RR700) (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM36P5000000003

A330-200/300 TECHNICAL TRAINING MANUAL

36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

SOURCES AND USERS

G6B08031 - G11T4T0 - FM36P5000000004

The pneumatic system may be supplied with High Pressure (HP) bleed
air from 3 types of sources:
- ground cart,
- APU,
- engines.
The bleed air is distributed to the different users via a distribution and
supply ducting network. These users are:
- the water system pressurization,
- the hydraulic reservoir pressurization,
- the wing anti-icing system,
- the engines starting systems,
- the packs bay ventilation system,
- the air conditioning packs,
- the thrust reverser system.
The pneumatic system operates pneumatically and is monitored by two
Bleed Monitoring Computers (BMCs) one, two.
There is one BMC for each engine bleed system. Both BMCs exchange
data. If one BMC fails, the other BMC takes over most of its monitoring
functions.

bleed in case of excessive pressure. In addition, an overpressure valve

A330-200/300 TECHNICAL TRAINING MANUAL

36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

CONTROL AND INDICATING
This section highlights the control panels and indications for the
pneumatic system.

CONTROL PANEL

G6B08031 - G11T4T0 - FM36P5000000004

Controls for the pneumatic system are part of the AIR COND panel,
located on the overhead panel.

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PART 2 OUT OF 2

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Page 664

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CONTROL AND INDICATING - CONTROL PANEL

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PART 2 OUT OF 2

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36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

CONTROL AND INDICATING (continued)
ECAM INDICATION

G6B08031 - G11T4T0 - FM36P5000000004

The pneumatic system indications are displayed on the lower part of

the ECAM BLEED page.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

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CONTROL AND INDICATING - ECAM INDICATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

COMPONENT LOCATION
The main components of the pneumatic system are located on the engines
and in the pylons.

ENGINE BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000004

The IPC, the High Pressure Valve (HPV), the PRV, the FAV are
located on the engine. The OPV and the precooler are located in the
pylon.

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PART 2 OUT OF 2

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COMPONENT LOCATION - ENGINE BLEED COMPONENTS

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PART 2 OUT OF 2

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36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

COMPONENT LOCATION (continued)
APU AND X BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000004

The crossbleed valve is located in the forward section of the lower

fuselage belly fairing area. Get access to the HP ground connector
through a small access door located on the lower fuselage belly fairing.
The APU bleed valve is located on the APU.

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PART 2 OUT OF 2

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COMPONENT LOCATION - APU AND X BLEED COMPONENTS

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

Jan 15, 2008

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36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM36P5000000004

The CMCs let the maintenance crew read the failure data in the BMCs
BITE via the MCDUs.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

Jan 15, 2008

Page 672

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MAINTENANCE/TEST FACILITIES
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PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

Jan 15, 2008

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36 PNEUMATIC SYSTEM PRESENTATION (GECF6) (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM36P5000000004

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

CONTROL AND INDICATING
This section highlights the control panels and indications for the
pneumatic system.

CONTROL PANEL

G6B08031 - G11T4T0 - FM36P5000000005

Controls for the pneumatic system are part of the AIR COND panel,
located on the overhead panel.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

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Page 682

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CONTROL AND INDICATING - CONTROL PANEL

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

CONTROL AND INDICATING (continued)
ECAM INDICATION

G6B08031 - G11T4T0 - FM36P5000000005

The pneumatic system indications are displayed on the lower part of

the ECAM BLEED page.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

Page 684

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CONTROL AND INDICATING - ECAM INDICATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

COMPONENT LOCATION
The main components of the pneumatic system are located on the engines
and in the pylons.

ENGINE BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000005

The IPC, the High Pressure Valve (HPV), the PRV, the FAV are
located on the engine. The OPV and the precooler are located in the
pylon.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

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COMPONENT LOCATION - ENGINE BLEED COMPONENTS

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

COMPONENT LOCATION (continued)
APU AND X BLEED COMPONENTS

G6B08031 - G11T4T0 - FM36P5000000005

The crossbleed valve is located in the forward section of the lower

fuselage belly fairing area. Get access to the HP ground connector
through a small access door located on the lower fuselage belly fairing.
The APU bleed valve is located on the APU.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

Page 688

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COMPONENT LOCATION - APU AND X BLEED COMPONENTS

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

Page 689

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM36P5000000005

The CMCs let the maintenance crew read the failure data in the BMCs
BITE via the MCDUs.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

Jan 15, 2008

Page 690

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MAINTENANCE/TEST FACILITIES
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

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Jan 15, 2008

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36 PNEUMATIC SYSTEM PRESENTATION (PW4000) (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM36P5000000005

When you work on A/C, make sure that you obey all the AMM safety
procedures. This will prevent injury to persons and/or damage to the A/C.
Here is an overview of the main safety precautions relative to the
pneumatic system.
Make sure that the pneumatic system is depressurized before starting the
work as pressurized air can cause unwanted pressurization of the A/C,
and injury to personnel.
Parts can be hot for 1 hour after engine shutdown. Do not touch them
until they are sufficiently cool.

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SAFETY PRECAUTIONS
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PART 2 OUT OF 2

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

GENERAL

G6B08031 - G11T4T0 - FM21PA000000001

The air conditioning system maintains the air in the pressurized fuselage
areas at the correct level of pressure, temperature and freshness. The
pressurized areas are:
- the cockpit,
- the 6 zones of the passenger cabin,
- the lavatories and galleys areas,
- the crew rest compartments, when installed,
- the avionics compartment,
- the FWD, AFT and BULK cargo compartments.
The air conditioning system also carries out the ventilation of the air
conditioning bay, which is a non-pressurized area
Air supply comes from the pneumatic system. Then, air is regulated in
temperature by the temperature regulation sub-system. Correct level of
air freshness in the pressurized areas and proper ventilation of the avionics
equipment are done by the ventilation sub-system. The pressurization
sub-system makes sure that the cabin altitude complies with crew and
passengers comfort.

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GENERAL
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

21 AIR CONDITIONING SYSTEM PRESENTATION (1)

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

G6B08031 - G11T4T0 - FM21PA000000001

TEMPERATURE CONTROL AND RE-CIRCULATION

Bleed air coming from the pneumatic system is first regulated in flow by
two pack flow control valves controlled by the Pack Controllers (PCs)
according to flow demand inputs received from the AIR panel and the
Zone Controller (ZC).
Bleed air is then delivered to two independent air conditioning packs,
which ensure basic temperature regulation. Each air conditioning pack
mainly has an Air Cycle Machine (ACM) and heat exchangers using ram
air flowing through ram air inlet and ram air outlet flaps. Pack temperature
regulation is controlled by the related PC according to a temperature
demand computed by the ZC based upon inputs received from the AIR
panel and the Flight Attendant Panel (FAP).
The cooled fresh air is then fed into a mixer unit.
On ground, a ground cart supplies preconditioned air through Low
Pressure (LP) ground connectors. In flight, if both packs are inoperative,
an emergency ram air inlet will help to maintain air supply to the cabin.
The emergency ram air supply is directly controlled from the AIR panel.
Fine temperature adjustment of air distributed in the pressurized zones
is obtained by controlling the amount of hot air added to the air coming
from the mixer unit. This air temperature adjustment is done under the
control of the ZC according to the temperature demand inputs received
from the AIR panel and the FAP.
A part of cabin air is re-circulated by re-circulation fans through
re-circulation valves in order to limit the bleed air demand on the engines.
This re-circulated air is mixed with fresh air coming from the air
conditioning packs into the mixer unit. Re-circulated air is also used for
avionics ventilation. The re-circulation fans and valves are controlled by
the Ventilation Controller (VC). The re-circulation fans can be manually
switched off from the VENTILATION panel.

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TEMPERATURE CONTROL AND RE-CIRCULATION

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PART 2 OUT OF 2

21 AIR CONDITIONING SYSTEM PRESENTATION (1)

AIR DISTRIBUTION AND VENTILATION (continued)
COCKPIT SIDE WINDOWS AIR OUTLET ELECTRICAL
HEATING (OPTIONAL)

G6B08031 - G11T4T0 - FM21PA000000001

To improve the pilot's comfort, additional heating for cockpit

side-window air outlet is installed. Cockpit temperature-regulated air
supply is heated using two electrical heaters: one for the captain, the
other for the First Officer (F/O). Temperature control is achieved via
the overhead panel rotary selector.

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

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AIR DISTRIBUTION AND VENTILATION - COCKPIT SIDE WINDOWS AIR OUTLET ELECTRICAL HEATING (OPTIONAL)
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

21 AIR CONDITIONING SYSTEM PRESENTATION (1)

AIR DISTRIBUTION AND VENTILATION (continued)
AVIONICS COMPT VENTILATION

G6B08031 - G11T4T0 - FM21PA000000001

The two re-circulation fans used for cabin air re-circulation are also
used as blower fans for the avionics equipment ventilation. The system
carries out proper ventilation of the rack equipment and various panels
in order to avoid any overheat condition. It operates continuously
whenever aircraft electrical power is available. An extract fan extracts
the air from the avionics equipment ventilation. Air is discharged
either overboard through the overboard valve or under the cargo floor
through the underfloor valve. When the overboard valve is open, the
underfloor valve is closed and vice versa. The Avionics Equipment
Ventilation Computer (AEVC) controls and monitors the avionics
ventilation system. A manual override is possible from the
VENTILATION panel.

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PART 2 OUT OF 2

21 AIR CONDITIONING SYSTEM PRESENTATION (1)

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AIR DISTRIBUTION AND VENTILATION - AVIONICS COMPT VENTILATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

21 AIR CONDITIONING SYSTEM PRESENTATION (1)

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

AIR DISTRIBUTION AND VENTILATION (continued)
AVIONICS COMPT GROUND REFRIGERATION UNIT
(OPTIONAL)

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The Ground Refrigeration Unit (GRU) supplies additional cooling to

the avionics compartment when the aircraft is on the ground under
high ambient temperature conditions. The system only works with air
conditioning Packs selected off. The GRU cools the air coming from
the cabin air re-circulation system before sending it to distribution
into the avionics compartment and the cockpit panels. The system
comprises a GRU, a fan and a skin valve. The system is monitored
and controlled by the AEVC and may be manually controlled from
the VENTILATION panel.

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AIR DISTRIBUTION AND VENTILATION - AVIONICS COMPT GROUND REFRIGERATION UNIT (OPTIONAL)
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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

AIR DISTRIBUTION AND VENTILATION (continued)
AIR CONDITIONING COMPARTMENT VENTILATION

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The air conditioning bay is ventilated by external air to maintain

temperature compatible with structure constraints in the relevant area.
On ground, when the air conditioning packs operate, a turbofan boosts
the air into the ventilation circuit. In flight, the ventilation is done by
ram air from NACA air inlet. The system is monitored by the AEVC.

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AIR DISTRIBUTION AND VENTILATION - AIR CONDITIONING COMPARTMENT VENTILATION

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PRESSURIZATION

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The pressurization system makes sure that cabin altitude is safe and
compatible with crew and passenger comfort. The cabin pressurization
is done by controlling the amount of cabin air discharged overboard
through two outflow valves located on the lower part of the aircraft
fuselage. The system is controlled automatically by the Cabin Pressure
Controllers (CPCs), or manually from the CABIN PRESS panel.
When the aircraft is on ground, the Residual Pressure Control Unit
(RPCU) forces both outflow valves to move to the fully open position,
overriding the automatic control from CPCs and the manual control as
well. This is to prevent any violent door opening in case of residual cabin
pressure.
Three safety valves are installed at the rear pressure bulkhead to prevent
excessive positive or negative differential pressure. Due to the large
volume of the fuselage, one negative-pressure relief valve helps the safety
valves to prevent negative differential pressure.

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PRESSURIZATION
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AFT CARGO COMPT VENTILATION SYSTEM
(OPTIONAL)

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The AFT cargo compartment ventilation system is based on an extraction

system using cabin air with an extract fan related to isolation valves. The
AFT cargo compartment ventilation is controlled and monitored through
the VC.

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AFT CARGO COMPT VENTILATION SYSTEM (OPTIONAL)

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

CREW REST COMPARTMENT (OPTIONAL)
LD-MCR COMPARTMENT VENTILATION AND
HEATING

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The Lower Deck Mobile Crew Rest compartment (LD-MCR) gets

fresh air from the mixer unit through a dedicated air duct and the
LD-MCR isolation valve. This air comes from the air supply duct of
cabin areas 5 and 6. The air is then extracted from the LD-MCR
through a grid located in the ceiling of the staircase housing, which
is connected to the Lavatory and Galley air extraction system. The
LD-MCR isolation valve is controlled and monitored by the VC. The
isolation valve is automatically closed in case the access hatch is not
in the fully open position, or if smoke is detected in the LD-MCR or
in the aft/bulk cargo compartment. The LD-MCR has a separate
temperature controller and temperature selector that adjust the
compartment temperature between 20C and 25C by the use of an
electrical air-heater. This heating function is not available when the
aircraft is on ground.

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CREW REST COMPARTMENT (OPTIONAL) - LD-MCR COMPARTMENT VENTILATION AND HEATING

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

CREW REST COMPARTMENT (OPTIONAL) (continued)
FLIGHT CREW REST COMPT VENTILATION AND
HEATING

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Conditioned air coming from the mixer unit ventilates the Flight Crew
Rest Compartment (FCRC). The FCRC is also heated by its own
heating system. The heating system has an electrical heater, a
temperature controller, a temperature sensor and a temperature selector.
The temperature sensor and the temperature selector are installed on
the service panel.
According to the customer choice, the heater and the temperature
controller can be either located between the frame 23 and 24 for the
option 1 or just in the ceiling of the FCRC for the option 2.

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CREW REST COMPARTMENT (OPTIONAL) - FLIGHT CREW REST COMPT VENTILATION AND HEATING
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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

CONTROL AND INDICATING
This section will highlight the control panels and indications for the air
conditioning system.

TEMPERATURE CONTROL AND RE-CIRCULATION

CONTROL PANELS

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The pilot uses the AIR COND on the overhead panel to control the
air conditioning system. This panel contains the PACK switches, the
zone temperature selectors, the PACK FLOW control, the HOT AIR
control switches, and the RAM AIR control switch. On the overhead,
the VENTILATION panel contains the CAB FANS pushbutton switch.
The switch is used to select the re-circulation fans OFF.
At the purser station, the Flight Attendant Panel (FAP) is used to
modify the temperature selected in the cockpit by +/- 3 Celsius for
each cabin zone.
In option, and according to customer demand, an additional CREW
HEATER temperature selector can be installed on the AIR COND
panel. As well as, Additional Attendant Panels (AAPs) can be installed
in the passenger cabin.

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CONTROL AND INDICATING - TEMPERATURE CONTROL AND RE-CIRCULATION CONTROL PANELS

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CONTROL AND INDICATING (continued)
TEMPERATURE CONTROL AND RE-CIRCULATION,
ECAM PAGES

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Basic temperature regulation is accomplished by the Packs. Pack

parameters, such as Pack flow and Pack discharge temperature are
found on the upper section of the ECAM BLEED page. Fine
temperature adjustment is accomplished by trimming hot air from the
hot manifolds. Temperature data, hot air valves, hot air shut off valve
and trim air shut off valve positions are displayed on the ECAM
COND page. Zone temperatures are also displayed on the ECAM
CRUISE page.

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CONTROL AND INDICATING - TEMPERATURE CONTROL AND RE-CIRCULATION, ECAM PAGES

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CONTROL AND INDICATING (continued)

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CONTROL AND INDICATING (continued)
VENTILATION ECAM PAGES

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A section of the ECAM CAB PRESS page displays avionics

equipment ventilation system information. The overboard extract
valve and the GRU skin valve position are displayed on this page.
The indications linked to the FWD, AFT and bulk cargo compartments
are displayed on the ECAM COND page. The ambient temperatures
in the FWD, AFT and the bulk cargo compartment are also displayed
on the ECAM CRUISE page.

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CONTROL AND INDICATING - VENTILATION ECAM PAGES

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CONTROL AND INDICATING (continued)
PRESSURIZATION CONTROL PANEL AND ECAM
PAGES

G6B08031 - G11T4T0 - FM21PA000000001

The CABIN PRESSure control panel is installed on the overhead

panel. The panel includes both automatic and manual pressurization
controls. The MODE SELect switch lets the system be used in
automatic, or in manual mode in case of failure of the automatic
function. When the manual mode is selected, the MANual Vertical
Speed (V/S) ConTroL switch is used to directly control the outflow
valve (indirectly, the cabin rate of climb).
The guarded DITCHING switch is used to close all lower fuselage
valves so that the A/C can be sealed in the unlikely event of a ditching.
The crew can monitor all cabin pressure functions on the ECAM
CABin PRESSure page. Some of the pressurization parameters are
also displayed on the ECAM CRUISE page.

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CONTROL AND INDICATING - PRESSURIZATION CONTROL PANEL AND ECAM PAGES

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

COMPONENT LOCATION (continued)
CABIN AIR DISTRIBUTION AND BULK CARGO
COMPT COMPONENT LOCATION

G6B08031 - G11T4T0 - FM21PA000000001

The cabin air is distributed through cabin air outlets located above
the hatracks and through individual fresh-air outlet panel.
The cabin air is then distributed in the cargo compartment at DADO
panels floor level. The isolation valves, extract fan and fan heater of
the bulk cargo compartment ventilation and heating systems are located
behind the compartment sidewall panels. Grills protect the air inlets
and outlets.

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COMPONENT LOCATION - CABIN AIR DISTRIBUTION AND BULK CARGO COMPT COMPONENT LOCATION
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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

COMPONENT LOCATION (continued)
AVIONICS EQUIPMENT VENT AND AIR COND COMPT
VENTILATION COMPONENT LOCATION

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On ground, the air is extracted from the avionics compartment by the

extraction fan and is discharged overboard through the overboard
extract valve. In flight, the extraction air is discharged through the
underfloor extract valve in the bilge area of the FWD cargo
compartment before being discharge overboard through the FWD
outflow valve.
The air conditioning compartment ventilation system uses a turbofan
on ground and a NACA air inlet in flight.

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COMPONENT LOCATION - AVIONICS EQUIPMENT VENT AND AIR COND COMPT VENTILATION COMPONENT LOCATION
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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

COMPONENT LOCATION (continued)
PRESSURIZATION COMPONENT LOCATION

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Pressurization is achieved by the use of a dual gate type outflow valve.

Three electrical motors operate the outflow valves: two for automatic
mode and one for manual mode.
The RPCU is installed on the RH side of the avionics compartment.

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COMPONENT LOCATION - PRESSURIZATION COMPONENT LOCATION

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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

MAINTENANCE/TEST FACILITIES

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The Central Maintenance Computers (CMCs) will help the maintenance

crew to analyze the BITE from the various air conditioning computers
by using the Multipurpose Control and Display Unit (MCDUs).
All fans monitored by the VC have a common fan FAULT light due to
overheat displayed on the AIR OVHT COND FANS RESET P/BSW on
the maintenance panel.

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MAINTENANCE/TEST FACILITIES
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21 AIR CONDITIONING SYSTEM PRESENTATION (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM21PA000000001

When you work on the air conditioning system, make sure that you obey
all the Aircraft Maintenance Manual (AMM) safety procedures. This will
prevent injury to persons and/or damage to the aircraft. Here is an
overview of the main safety procedures relative to the air conditioning
system.
Do not touch A/C components until they are sufficiently cool to prevent
burns.
Keep away from the moving parts of the outflow valves, and the ram air
inlet and outlet flaps when you operate or test the valves and the flaps to
avoid injury to persons.

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SAFETY PRECAUTIONS
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30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

GENERAL

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The Ice and Rain Protection System lets the aircraft operate without
restriction in icing conditions or heavy rain. Hot air or electrical heating
protects critical areas of the aircraft. The different sub systems of the Ice
and Rain Protection System are:
- wing ice protection,
- engine air intake ice protection,
- probe ice protection,
- windshield anti-icing, defogging and rain protection,
- potable and waste water ice protection,
- escape slide locking mechanism ice protection,
- ice detection,
- maintenance/test facilities.
When you work on aircraft, you must obey all the safety procedures listed
in the AMM.

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GENERAL
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WING ICE PROTECTION

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During icing conditions, hot air is supplied by the pneumatic system to

the four outboard slats to raise the temperature. Bleed air is supplied to
each wing through two Wing Anti Ice (WAI) valves, one for the slat
number four and one for slats number five, six and seven.
If a failure occurs in the wing ice protection system:
- the Zone Controller (ZC) sends the failure data to the Central
Maintenance Computer (CMC),
- the System Data Acquisition Concentrator (SDAC) sends data to the
ECAM.

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WING ICE PROTECTION

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30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

WING ICE PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000003

The inner and outer wing anti-ice valves are installed on the stable
leading edges of the wings.

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WING ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
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30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

ENGINE AIR INTAKE ICE PROTECTION (continued)
CONTROL AND INDICATING

G6B08031 - G11T4T0 - FM30P9000000003

The controls for the engine anti-ice system are located on the overhead
panel. Each engine anti-ice valve is controlled manually by a dedicated
P/BSW on the ANTI ICE panel. A MEMO appears on the EWD when
the engine anti-ice is selected. In case of abnormal operation, the
FAULT light comes on, on the related P/BSW.

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ENGINE AIR INTAKE ICE PROTECTION - CONTROL AND INDICATING

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30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

PROBE ICE PROTECTION

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The static ports, Angle Of Attack (AOA), pitot and Total Air Temperature
(TAT) probes are electrically heated to prevent ice formation. The
Captain, the First Officer and standby probe heating systems are
independent. Each one has one Probe Heat Computer (PHC), which
controls probe and static port heating. The standby system has no TAT
probe. The PROBE/WINDOW HEAT P/BSW overrides the automatic
operation. On ground, pitot heating is reduced and TAT heating is cut
off.

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PROBE ICE PROTECTION

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WINDSHIELD ANTI-ICING

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Windshields and side windows are electrically heated to maintain clear

visibility in icing or misting conditions. Windshields are de-iced and side
windows are dimisted. The windshield heating operates at low power on
ground and at full power in flight. Heating is automatically initiated at
engine 2 or 3 start-up. The PROBE/WINDOW HEAT P/BSW overrides
the automatic operation. Two fully independent Window Heat Computers
(WHCs), one on each side, carry out the heat system monitoring and the
overheat protection of their respective windshield and windows.

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WINDSHIELD ANTI-ICING
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WINDSHIELD ANTI-ICING (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000003

The WHCs are installed in the avionics compartment:

- WHC 1 LH side (CAPT side),
- WHC 2 RH side (F/O side).

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WINDSHIELD ANTI-ICING - COMPONENT LOCATION

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RAIN PROTECTION

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Rain removal from the windshield is done by two independent wipers

and in heavy rain, by a rain repellent system. These systems are controlled
from the overhead panel. The rain repellent fluid (FORALKYL 2211) is
discharged onto the left or right windshield from a pressurized canister
installed at the rear of the cockpit. The rain repellent system is inhibited
on the ground when the engines are not running.

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RAIN PROTECTION
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POTABLE AND WASTE WATER ICE PROTECTION

G6B08031 - G11T4T0 - FM30P9000000003

An automatic water ice protection system is installed to prevent ice

formation in flight or on ground at freezing temperature on the following
lines:
- the potable water,
- the waste water,
- the water servicing panels,
- the drain masts.
Heating of these water lines is controlled and monitored by two Ice
Protection Control Units (IPCUs) based upon information received from
temperature sensors installed on these lines. One IPCU controls the lines
of the aircraft forward section, the second one the lines of the aft section.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 772

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

POTABLE AND WASTE WATER ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 773

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

POTABLE AND WASTE WATER ICE PROTECTION
(continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000003

One IPCU is installed in the avionics compartment, the other one is

in the AFT cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 774

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

POTABLE AND WASTE WATER ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 775

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

ESCAPE SLIDE LOCKING MECHANISM ICE
PROTECTION

G6B08031 - G11T4T0 - FM30P9000000003

An electrical ice protection system prevents ice accretion on the Slide

Attachment Fittings (SAFs) during flight that could lead to escape slide
disarming difficulties on ground at door opening. Each passenger/crew
door has two heated SAFs. On the A340-600, the overwing-emergency
exits have no heated SAFs. The heating elements located in the related
locking plate are powered automatically when icing conditions are
detected, if the escape slide is armed. The system is controlled and
monitored by two IPCUs, one for doors 1 and 2 (LH and RH) and one
for doors 3 and 4 (LH and RH).

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 776

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

ESCAPE SLIDE LOCKING MECHANISM ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 777

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

ESCAPE SLIDE LOCKING MECHANISM ICE
PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000003

One IPCU is installed in the avionics compartment; the other one is

installed in the bulk cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 778

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

ESCAPE SLIDE LOCKING MECHANISM ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 779

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

ICE DETECTION

G6B08031 - G11T4T0 - FM30P9000000003

An external visual ice indicator with an integrated light is installed

between both windshields to be visible from the CAPT and F/O sides.
This indicator light comes on from the ICE INDicator & STandBY
COMPASS selector switch on the INTerior LighT panel. In icing
conditions, the ice accretion on the indicator prevents the integrated light
to be visible from the cockpit.
In addition, a dual advisory ice detection system is installed to give:
- a better detection of icing conditions,
- fuel saving by cutting off the anti-icing systems when the latter is no
longer necessary.
The dual advisory ice detection system is made of two ice detectors
installed on the skin of the aircraft and directly connected to the FWC to
send warning messages to the crew on the EWD. Two levels of detections
are given:
- ICE DETECTED used for the selection of engine anti-ice,
- SEVERE ICE DETECTED used for the selection of wing anti-ice.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 780

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

ICE DETECTION
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 781

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

MAINTENANCE/TEST FACILITIES

G6B08031 - G11T4T0 - FM30P9000000003

The WHCs, the PHCs, the ice detector system, and the ZC are connected
to the CMCs for maintenance tasks. The IPCUs are also connected to the
CMCs but via the Cabin Intercommunication Data System (CIDS).

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 782

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

MAINTENANCE/TEST FACILITIES
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

Jan 15, 2008

Page 783

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (RR700) (1)

SAFETY PRECAUTIONS

G6B08031 - G11T4T0 - FM30P9000000003

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

WING ICE PROTECTION (continued)
CONTROL AND INDICATING

G6B08031 - G11T4T0 - FM30P9000000004

The control for the WAI system is located on the overhead ANTI ICE
panel. A MEMO appears on the EWD when the WAI is selected. The
FAULT light comes on in case of abnormal operation. The WAI
system operates in flight only, but the system can be tested on ground.
The WAI valve position indication is available on the BLEED page
when the system is selected.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 790

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

WING ICE PROTECTION - CONTROL AND INDICATING

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

ENGINE AIR INTAKE ICE PROTECTION

G6B08031 - G11T4T0 - FM30P9000000004

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 794

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

ENGINE AIR INTAKE ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 795

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

ENGINE AIR INTAKE ICE PROTECTION (continued)
CONTROL AND INDICATING

G6B08031 - G11T4T0 - FM30P9000000004

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 796

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

ENGINE AIR INTAKE ICE PROTECTION - CONTROL AND INDICATING

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

PROBE ICE PROTECTION

G6B08031 - G11T4T0 - FM30P9000000004

The static probes, Angle Of Attack (AOA), pitot and Total Air
Temperature (TAT) sensors are electrically heated to prevent ice
formation. The Captain, the First Officer and standby probe heating
systems are independent. Each one has one Probe Heat Computer (PHC),
which controls probe and static port heating. The standby system has no
TAT probe. The PROBE/WINDOW HEAT P/BSW overrides the
automatic operation. On ground, pitot heating is reduced and TAT heating
is cut off.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 800

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

PROBE ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 801

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

PROBE ICE PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000004

The probe ice protection system has 3 systems:

- pilot system,
- first officer system,
- stand-by system.
Each system has its related probes, located on the LH and RH FWD
fuselage and, its own computer installed on the LH and RH side of
the avionics compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 802

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

PROBE ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 803

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

WINDSHIELD ANTI-ICING

G6B08031 - G11T4T0 - FM30P9000000004

Windshields and side windows are electrically heated to maintain clear

visibility in icing or misting conditions. Windshields are de-iced and side
windows are dimisted. The windshield heating operates at low power on
ground and at full power in flight. The PROBE/WINDOW HEAT P/BSW
overrides the automatic operation. Two fully independent Window Heat
Computers (WHCs), one on each side, carry out the heat system
monitoring and the overheat protection of their respective windshield
and windows.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 804

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

WINDSHIELD ANTI-ICING
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 805

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

WINDSHIELD ANTI-ICING (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000004

The WHCs are installed in the avionics compartment:

- WHC 1 LH side (CAPT side),
- WHC 2 RH side (F/O side).

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 806

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

WINDSHIELD ANTI-ICING - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 807

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

RAIN PROTECTION

G6B08031 - G11T4T0 - FM30P9000000004

Rain removal from the windshield is done by two independent wipers

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 808

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

POTABLE AND WASTE WATER ICE PROTECTION
(continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000004

One IPCU is installed in the avionics compartment, the other one is

in the AFT cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 812

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

POTABLE AND WASTE WATER ICE PROTECTION - COMPONENT LOCATION

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

ESCAPE SLIDE LOCKING MECHANISM ICE
PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000004

One IPCU is installed in the avionics compartment; the other one is

installed in the bulk cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 816

G6B08031 - G11T4T0 - FM30P9000000004

A330-200/300 TECHNICAL TRAINING MANUAL

ESCAPE SLIDE LOCKING MECHANISM ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

Jan 15, 2008

Page 817

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (GECF6) (1)

ICE DETECTION

GENERAL

G6B08031 - G11T4T0 - FM30P9000000005

The Ice and Rain Protection System lets the aircraft operate without
restriction in icing conditions or heavy rain. Hot air or electrical heating
protect critical areas of the aircraft. The different sub systems of the Ice
and Rain Protection System are:
- wing ice protection,
- engine air intake ice protection,
- probe ice protection,
- windshield anti-icing, defogging and rain protection,
- potable and waste water ice protection,
- escape slide locking mechanism ice protection,
- ice detection,
When you work on aircraft, you must obey all the safety procedures listed
in the AMM.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 824

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

WING ICE PROTECTION (continued)
CONTROL AND INDICATING

G6B08031 - G11T4T0 - FM30P9000000005

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 828

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

WING ICE PROTECTION - CONTROL AND INDICATING

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

ENGINE AIR INTAKE ICE PROTECTION

G6B08031 - G11T4T0 - FM30P9000000005

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 832

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

ENGINE AIR INTAKE ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 833

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

ENGINE AIR INTAKE ICE PROTECTION (continued)
CONTROL AND INDICATING

G6B08031 - G11T4T0 - FM30P9000000005

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 834

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

ENGINE AIR INTAKE ICE PROTECTION - CONTROL AND INDICATING

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

PROBE ICE PROTECTION

G6B08031 - G11T4T0 - FM30P9000000005

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 838

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

PROBE ICE PROTECTION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 839

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

PROBE ICE PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000005

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 840

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

PROBE ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 841

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

WINDSHIELD ANTI-ICING

G6B08031 - G11T4T0 - FM30P9000000005

Ice protection for windshield and demisting for windows is electrically

achieved. Two independent Window Heat Computers (WHCs), one for
each side, monitor and control the heaters. They include an overheat
protection. Window heating system is automatically or manually
controlled. In case of severe icing conditions on ground, automatic
operation can be overridden with the PROBE/WINDOW HEAT P/BSW.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 842

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

WINDSHIELD ANTI-ICING
GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 843

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

WINDSHIELD ANTI-ICING (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000005

The WHCs are installed in the avionics compartment:

- WHC 1 LH side (CAPT side)?
- WHC 2 RH side (F/O side).

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 844

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

WINDSHIELD ANTI-ICING - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 845

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

RAIN PROTECTION

G6B08031 - G11T4T0 - FM30P9000000005

Rain removal from the windshield is done by two independent wipers

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 846

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

POTABLE AND WASTE WATER ICE PROTECTION
(continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000005

One IPCU is installed in the avionics compartment, the other one is

in the AFT cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 850

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

POTABLE AND WASTE WATER ICE PROTECTION - COMPONENT LOCATION

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

ESCAPE SLIDE LOCKING MECHANISM ICE
PROTECTION (continued)
COMPONENT LOCATION

G6B08031 - G11T4T0 - FM30P9000000005

One IPCU is installed in the avionics compartment; the other one is

installed in the bulk cargo compartment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 854

G6B08031 - G11T4T0 - FM30P9000000005

A330-200/300 TECHNICAL TRAINING MANUAL

ESCAPE SLIDE LOCKING MECHANISM ICE PROTECTION - COMPONENT LOCATION

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

Jan 15, 2008

Page 855

A330-200/300 TECHNICAL TRAINING MANUAL

30 ICE & RAIN PROTECTION SYS PRES. (PW4000) (1)

ICE DETECTION

FIN PRESENTATION

G6B08031 - G11T4T0 - FM01P1000000002

Equipment on the A/C is identified by a unique identifier designated the

G6B08031 - G11T4T0 - FM01P1000000002

For electrical equipment (any component with an electrical

connection), the prefix (sequence number) will be below 5000. Here
is an example for the electrical and electro-mechanical
systems/circuits.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

00 CIRCUIT IDENTIFICATION PRESENTATION (1)

Jan 15, 2008

Page 866

G6B08031 - G11T4T0 - FM01P1000000002

A330-200/300 TECHNICAL TRAINING MANUAL

FIN PRESENTATION - ELECTRICAL EQUIPMENT

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)
PART 2 OUT OF 2

00 CIRCUIT IDENTIFICATION PRESENTATION (1)

FIN PRESENTATION (continued)
MECHANICAL EQUIPMENT

G6B08031 - G11T4T0 - FM01P1000000002

For mechanical equipment (without electrical connection), the prefix

will be above 5000. Here is an example for the mechanical equipment.

GENERAL FAMILIARIZATION COURSE - T4 (ALL ENGINES)

PART 2 OUT OF 2

00 CIRCUIT IDENTIFICATION PRESENTATION (1)

Jan 15, 2008

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FIN PRESENTATION - MECHANICAL EQUIPMENT

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FIN PRESENTATION (continued)
FICTITIOUS COMPONENTS

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All components, not specifically related to a circuit, are identified by

the fictitious circuit letter V. The circuit letter defines the type of
component. The panels and racks are identified by the letters VU or
VE.

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PLACARDS

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As a general rule, operating or installation instructions, directional

movement instructions, servicing, part or position identifications,
rescue and evacuation instructions and safety precautions shall be marked
with placards, nameplates stencils or markings. Here are various
examples:
- safety placard,
- fin placard,
- component placard,
- operational placard.

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PLACARDS
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05 TIME LIMITS AND MAINTENANCE CHECKS (1)

SCHEDULED / UNSCHEDULED MAINTENANCE CHECKS
IN THE AMM / MPD
This chapter includes the following sections:
- scheduled maintenance tasks and checks,
- unscheduled maintenance checks.

SCHEDULED MAINTENANCE TASKS & CHECKS - IN

MPD
This Chapter 05-20-00 "Life Limits and Maintenance Checks" is now
covered in the Maintenance Planning Document (MPD).
The MPD is the repository document for all repetitive scheduled
maintenance tasks promulgated by Airworthiness Directives (AD/CN),
All Operator Telex (AOT), Inspection Service Bulletins (ISB), Service
Information Letters (SIL), and Modifications (MOD/SB) and analyzed
under the Maintenance Review Board (MRB).

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UN-SCHEDULED MAINTENANCE - IN AMM SECTION

05-50-00
This Chapter 05-50-00 includes the maintenance checks that you must
do when a flight crew report shows abnormal flight conditions.
Such maintenance actions are divided into two categories of
information:
- inspections,
- checks.

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SCHEDULED / UNSCHEDULED MAINTENANCE CHECKS IN THE AMM / MPD - SCHEDULED MAINTENANCE TASKS & CHECKS IN MPD & UN-SCHEDULED MAINTENANCE - IN AMM SECTION 05-50-00
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SCHEDULED REPETITIVE REQUIREMENTS THROUGH

MPD
The main objective of the MPD document is to provide maintenance
planning information necessary for each operator to develop a customized
maintenance program.
MPD reflects all repetitive scheduled maintenance tasks promulgated by
AD/CN, AOT, ISB, SIL, and MOD/SB and analyzed under the MRB.
A typical scheduled repetitive task (Integrated Drive Generator (IDG)
scavenge filter) is listed with the following data:
- the threshold interval, source document, cross-references to other
manuals or documents (Aircraft Maintenance Manual (AMM) and SIL),
- Man Hours required to accomplish the work,
- the applicability in this Envelope document.
Note the Zonal inspection, requested by C CHECK interval, on the tension
of the fan cowl latches, the AOT, AMM and SIL cross-referenced.
Some maintenance tasks have a higher ranking of requirement, when the
maintenance requirement is identified as:
- "Airworthiness Limitations Item" (ALI) or "Life limit parts",
- "Certification Maintenance Requirements" (CMR).
The approved document MRB REPORT Appendix 1 lists all these
airworthiness approved issues, the ALIs and CMRs.
The MPD details these airworthiness related items in the "Time controlled
Items" and "Life Limits" sections.
It is the responsibility of each operator to adjust his own maintenance
program in accordance with his National Authority.

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