Single Aisle

TECHNICAL TRAINING MANUAL

GENERAL FAMILIARIZATION COURSE - T4 (CFM 56)
PART 1 OUT OF 2
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 Single Aisle TECHNICAL TRAINING MANUAL

PART 1 OUT OF 2
00 Family Ties Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .2
00 SA Family Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .8
00 Ground Handling (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .58
31 Indicating/Recording System Presentation (1) . . . . . . . . . . . . . . .64
24 Electrical Power System Presentation (1) . . . . . . . . . . . . . . . . . .104
34 ADIRS and STBY Instruments Presentation (1) . . . . . . . . . . . . .130
34 Dependent POS Determining SYS & LAND Aids (1) . . . . . . . .154
34 Independent POS Determining SYS Pres. (1) . . . . . . . . . . . . . . .208
22 Auto Flight System Presentation (1) . . . . . . . . . . . . . . . . . . . . . .236
46 Air Traffic INFO Management SYS Pres. (1) . . . . . . . . . . . . . . .268
23 Communications System Presentation (1) . . . . . . . . . . . . . . . . .284
23 CIDS System Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . .320
33 Lights System Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . .348
51 Structure Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . . . . .378
29 Hydraulic Power System Presentation (1) . . . . . . . . . . . . . . . . . .398
32 Landing Gear Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . . . .416
27 Flight Controls Presentation (1) . . . . . . . . . . . . . . . . . . . . . . . . .440
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00 FAMILY TIES PRESENTATION (1)

For passengers, this means an aircraft that is comfortable and convenient
FAMILY TIES in every class.
The versatility of the single aisle cabin lets operate as to match the market.
Before we design an aircraft, there are a lot of people we listen to:
First, business or economy class layouts as passenger demand requires.
- the businessman is interested in saving time,
On regional flights, this means an equal comfort and useful flexibility
- the cabin crew want the aircraft to be user friendly,
for the airline.
- the ground crew want easy maintenance,
FLEXIBILITY
- the pilot wants the aircraft to be dependable and easy to handle,
The cabin intercommunication system makes it easy to vary cabin
- management are interested in the bottom line and our sales team want
configuration.
an aircraft that can go out and beat the competition with.
With the wide aisle, cabin crew and passengers can move more easily.
So when we have done the listening, we started to design a new generation
A standard A321 with 196 passengers has a turn round time of only 34
150 seat. And what we design has been a great success on original lines
minutes and this reduces to 29 minutes with the wide aisle option, 11
all over the world.
minutes faster than the competition.
With the latest electronics Flight By Wire control and a new approach
EFFICIENCY
to the man machine interface, the A320 really is the state of the art in
When the baggage isn't left behind, the cargo compartments can be
commercial aviation. But to the Airbus Industry approach to the success
unloaded and reloaded well within the passenger turn round time.
is to go further.
70% of A320 users have opted for the containerization system based on
By getting our ideas clear at the design stage we have made the A320
the LD 3 standard. A wise choice when you consider the increasing
the start of a real family.
proportion of an airline income that comes from freight.
For example, to stretch the 150 seat A320 into a 190 seat A321 we have
Although the A321 is only 18% longer than the A320, its underfloor
simply to make local re-enforcements to the wing and center section and
capacity is 40% greater, room for three more containers.
some minor changes to the flight control software. The rest could stay
TECHNOLOGY
virtually the same.
Advanced composite materials and the best aluminum alloys produce a
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The A321 is an A320 with two extra fuselage sections and room for 36
rugged yet light airframe. High structural efficiency directly reduces
more paying customers.
operating costs.
In the same way we have been able to shorten the A320 to create the
The A321 and A319 are assembled in Germany at a purpose built Deutsch
A319, the most economic member of the family.
Airbus plant.
These three aircrafts between them cover the needs of the airlines from
Since potential corrosion problems are addressed at source, structural
124 to 185 seats.
inspection programs are simplified reducing maintenance costs and
This family design makes it easier for an airline to cope with daily or
enhancing resell value.
seasonal variations in traffic and keep maintenance costs down because
More advanced technology can be seen in the wings which are lighter
of the fleet effect.
and optimized for computer control flight. Because of better
COMFORT
The family effect is all the greater because the initial design was right.
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aerodynamics, they made the A320 and the A321 the most fuel efficient Designing a 192/200 seater based on the A320 was a natural step. The
commercial jets on the market. cost effectiveness of the idea is even clearer in market forecast.
RANGE The advent of the A319 is perhaps even more inhibitive. Now airlines
The Airbus A321 cost per passenger mille is by far the lowest in its can adapt a slack operating periods and expand their commercial networks
category. to second relines while keeping the fleet effect.
The A319 has the lowest fuel consumption. The A319 opens up development perspectives for smaller airlines too by
The engines too interface with the flight by wire controls and the autopilot providing them now with a high quality aircraft that would go on being
system. attractive.
The whole family has the same man machine interface. The Primary By founding the first real family of aircraft, Airbus Industry has created
Flight Display alone replaces six conventional electromagnetic a novel concept based on standardization and maximum commonality.
instruments. We have provided the market with three cost effective aircrafts, which
Information is displayed on a six cathode ray tubes when it is needed, operate efficiently together.
thus reducing the crew's workload. This family works as a team.
A major asset of computer-aided design is ease of access to system
operation parameters. This is an advantage for the Centralized Fault
Display System (CFDS), the key to maintenance guidance.
Any failure is analyzed, the faulty component identified, the diagnosis
made, and if necessary the information is transmitted to the ground in
real time for time saving repair.
The A320 family ties really come into their own when it comes to
maintenance. Virtually all despairs, test devices and procedures are
identical. No need for extra stocks or special training or facilities in
service staff are available for the whole family.
FLEET ADVANTAGE
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In terms of maintenance operating A320s, A321s and A319s is the same

as operating a single type. The savings are enormous, common equipment,
common staff.
For cabin crew, the cabin is a just a little longer or shorter.
For pilots the aircraft are virtually the same. They react in the same way
to the same commands. This is true of all Airbus Industry new generation
aircraft from the A319 to the four engine A340.
The simulator is common to the whole family. Basic crew conversion
costs are therefore much lower for airlines, which base their fleets on
Airbus technology. Because the crews can be used on different aircraft,
operations are more flexible and efficient.
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FAMILY TIES

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00 FAMILY TIES PRESENTATION (1)

A320 FAMILY
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A320 FAMILY

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00 SA FAMILY PRESENTATION (1)

AIRCRAFT GENERAL
The Single Aisle is the most advanced family aircraft in service today,
with fly-by-wire flight controls.
The A318, A319, A320 and A321 are twin-engine subsonic medium
range aircraft.
The family offers a choice of engines:
- International Aero Engines and CFM International for the A319, A320
and A321.
- Pratt & Whitney and CFM International for the A318.
AIRCRAFT DIMENSIONS
The picture shows the main dimensions for the A320.
The A318, A319 and A321 have exactly the same dimensions except
that:
- the A318 is 6.12 m (20 ft) shorter and 1.18 m (3ft 10in) higher,
- the A319 is 3.74 m (12ft 3in) shorter,
- the A321 is 6.93 m (22ft 9in) longer.
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AIRCRAFT GENERAL - AIRCRAFT DIMENSIONS

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AIRCRAFT GENERAL - AIRCRAFT DIMENSIONS

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00 SA FAMILY PRESENTATION (1)

AIRCRAFT GENERAL (continued)
FAMILY RANGE
With a Maximum Take-Off Weight (MTOW) of 77 tons (170000 lbs),
the A320 has a range of 3600 Nm as shown above.
- For the A318, with an MTOW of 66 tons (145500 lbs), it is 3900
Nm.
- For the A319, with an MTOW of 68 tons (150000 lbs), it is 4200
Nm.
- For the A321, with an MTOW of 83 tons (183000 lbs), it is 3100
Nm.
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AIRCRAFT GENERAL - FAMILY RANGE

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00 SA FAMILY PRESENTATION (1)

AIRCRAFT GENERAL (continued)
MAXIMUM WEIGHTS AND OPERATING LIMITS
The following picture shows maximum weights and operating limits
for the Single Aisle family aircraft.
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AIRCRAFT GENERAL - MAXIMUM WEIGHTS AND OPERATING LIMITS

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AIRCRAFT GENERAL (continued)
THE CABIN
Cabin seat layout shown in the graphic is the Airbus recommended
seat quantity and pitch based on the design of the airframe. Normally
the Airline, based on needs, modifies these layouts.
The cabin has a maximum of:
- 129 seats for the A318,
- 145 seats for the A319,
- 180 seats for the A320,
- 220 seats for the A321.
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AIRCRAFT GENERAL - THE CABIN

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AIRCRAFT GENERAL (continued)
DOOR HEIGHTS
The following picture shows the different door heights.
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AIRCRAFT GENERAL - DOOR HEIGHTS

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AIRCRAFT GENERAL (continued)
COMPOSITE STRUCTURES
The picture shows the composite structures included in Single Aisle
family aircraft.
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AIRCRAFT GENERAL - COMPOSITE STRUCTURES

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STRUCTURAL BREAKDOWN AND ZONING
In this topic, the fuselage, vertical and horizontal stabilizers, and wings
station numbers are shown.
FUSELAGE
The station (STA) number is the distance in millimeters of the
cross-section from a reference point. The reference (X=0) for all
structural measurements in the X-axis is located 2.54 m (100 in)
forward of the aircraft.
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STRUCTURAL BREAKDOWN AND ZONING - FUSELAGE

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STRUCTURAL BREAKDOWN AND ZONING (continued)
VERTICAL STABILIZER
For the vertical stabilizer the reference station is Z=0 at the vertical
Z-axis. Due to the fin tip extension, the A318 station numbers have
changed. The new rib 12N is on the STA5970.
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STRUCTURAL BREAKDOWN AND ZONING - VERTICAL STABILIZER

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STRUCTURAL BREAKDOWN AND ZONING (continued)
HORIZONTAL STABILIZER
For the horizontal stabilizer the reference station is Y=0 at the
horizontal Y-axis.
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STRUCTURAL BREAKDOWN AND ZONING - HORIZONTAL STABILIZER

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STRUCTURAL BREAKDOWN AND ZONING (continued)
WING
For wings, the reference station is the wing reference axis that is
located at 1868 millimeters (73.54 in) from the aircraft X-axis.
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STRUCTURAL BREAKDOWN AND ZONING - WING

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COCKPIT PRESENTATION
The cockpit has adjustable seats for two crew members, a third occupant
seat and, depending on the configuration a folding seat for a fourth
occupant. Various furnishings and equipment are installed in the cockpit
for the comfort, convenience and safety of the occupants.
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COCKPIT PRESENTATION

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COCKPIT PRESENTATION (continued)
OVERHEAD PANEL
The controls of most aircraft systems are located on the overhead
panel.
The overhead panel is divided into two main sections:
- a FWD section including the system panels,
- an AFT section including mainly the circuit breaker panel.
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COCKPIT PRESENTATION - OVERHEAD PANEL

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COCKPIT PRESENTATION (continued)
GLARESHIELD
The Flight Control Unit (FCU) includes the EFIS controls, and is used
for control and monitoring of the Auto Flight System (AFS). It is
located on the glareshield.
The "Master Warning" and the "Master Caution" lights are also located
on the glareshield.
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COCKPIT PRESENTATION - GLARESHIELD

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COCKPIT PRESENTATION (continued)
MAIN INSTRUMENT PANEL (ENHANCED)
The enhanced single aisle aircraft main instrument panel
instrumentation has been updated. Liquid Crystal Displays (LCDs)
replace the existing CRTs. A single integrated electronic indicator,
the Integrated Standby Instrument System (ISIS) replaces the standby
instrumentation: Standby horizon, Airspeed indicator and Altimeter.
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COCKPIT PRESENTATION - MAIN INSTRUMENT PANEL (ENHANCED)

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COCKPIT PRESENTATION (continued)
CENTER PEDESTAL
The center pedestal ergonomic design of the SA family aircraft gives
the flight crew efficient access to multiple system controls without
compromising safety.
The panels are:
- Switching panel
- ECAM control panel (ECP)
- Multipurpose Control Display Units (MCDU)
- Radio Management Panels (RMPs)
- Audio Control Panels (ACPs)
- Thrust levers and thrust reverser levers
- Pitch trim wheel
- Engine start panel
- Air Traffic Control / Traffic Collision Avoidance System panel
(ATC/TCAS)
- Flap/slat control handle
- Speed brake control panel
- Parking brake control panel
- Cockpit door lock panel
- Landing gear gravity extension handle
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- Printer
- Multifunction disk drive unit
- Pa handset at the rear of the pedestal

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COCKPIT PRESENTATION - CENTER PEDESTAL

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COCKPIT PRESENTATION (continued)
SIDE CONSOLES
The Conventional Aircraft control yoke is noticeably missing in the
Airbus Single Aisle aircraft. The Side Stick Controller (SSC) replaces
the Conventional Aircraft yoke. There is one SSC for each pilot
mounted in the side consoles.
The Aircraft nose wheel is steerable. The flight crew operates the
Nose Wheel Steering (NWS) by using the NWS tillers mounted
outboard of the SSC on the same side console.
Behind the most forward side console are installed several other
compartments along the outboard sides of the cockpit. These side
consoles are used as stowage space for documents, oxygen masks,
fire extinguisher and microphone and headset connections
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COCKPIT PRESENTATION - SIDE CONSOLES

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COCKPIT PHILOSOPHY
Prior to the design of the A320 family aircraft, the designers examined
previous generation aircraft cockpit system indications. A decision was
made on the system indicator lights on the overhead panel that indicator
lights do not come on when systems are in normal operation and there
are no failures.
This ergonomic design enabled the pilots to immediately see when a
system is faulty or has been manually shut off.
Most of the pushbuttons with light have two stable positions: pressed in
and released out, each position is related to a control signal sent to a
system.
Pressed in (recessed):
- normally used system activation (AUTO or ON),
- temporarily used system activation (ON),
- system activated for maintenance operation (ON) or override (OVRD).
Released out (flush with the panel):
- deactivation system (OFF),
- manual activation of a system (ON),
- activation of an alternate system (ALTN).
Some pushbuttons have only one stable position:
- released out.
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When pushed, they send a control signal to the system.

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COCKPIT PHILOSOPHY

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COCKPIT PHILOSOPHY (continued)
PUSHBUTTON COLOR PHILOSOPHY
The pushbuttons light and annunciator lights are in different colors
according to their function.
In normal operation, only green lights and, sometimes, blue lights
come on.
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COCKPIT PHILOSOPHY - PUSHBUTTON COLOR PHILOSOPHY

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GROUND SUPPORT EQUIPMENT AND TOOLS
The World Airlines Technical Operations Glossary (WATOG) definition
of Ground Support Equipment (GSE) is:
equipment required on the ground to support the operation and
maintenance of the aircraft and all its airborne equipment.
Airbus divides GSE into two categories:
- tools,
- standard GSE.
Tools can be split into two categories:
- standard tools,
- specific tools.
STANDARD TOOLS
Standard tools are hand tools such as spanners, sockets, gauges, torque
wrenches...
The specifications (size, range, capacity, accuracy...) are given in the
related Aircraft Maintenance Manual (AMM) task to let operators use
the tool brand of their choice.
Standard tools for Aircraft Maintenance are all in US units.
Metric tools maybe required for shop maintenance.
They are not required for aircraft maintenance but will be required to
maintain Airbus specific tools and, in some cases, for aircraft
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component maintenance in the shop.

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GROUND SUPPORT EQUIPMENT AND TOOLS - STANDARD TOOLS

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GROUND SUPPORT EQUIPMENT AND TOOLS (continued)
SPECIFIC TOOLS
Specific tools are tools designed by Airbus or by its vendors to carry
out given maintenance tasks on the aircraft or one of its components.
All maintenance tools for "on - aircraft" maintenance such as the
AMM, Trouble Shooting Manual (TSM)... and for "off - aircraft"
maintenance such as the Component Maintenance Manual (CMM)
are found in the Support Equipment Summary (SES) document.
The SES covers all Airbus aircraft types and all associated
documentation.
If a tool does not appear in the SES it is not a tool for Airbus aircraft
or equipment.
All specific tools called up for "on - aircraft" maintenance in the AMM
and the TSM are illustrated in the Tool Equipment Manual (TEM).
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GROUND SUPPORT EQUIPMENT AND TOOLS - SPECIFIC TOOLS

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GROUND SUPPORT EQUIPMENT AND TOOLS (continued)
STANDARD GSE
Airbus considers as standard GSE any GSE which is not designed for
a specific aircraft type, but it can/could be used on a number of
different aircraft types.
Standard GSE includes, but is not limited: tow bars, axle/wheel change
jacks, tripod maintenance jacks, access platforms, hydraulic ground
carts, electrical power units, etc...
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GROUND SUPPORT EQUIPMENT AND TOOLS - STANDARD GSE

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JACKING
Three jacking points, when equipped with jacking pads, are used to lift
the aircraft. The forward point "A" is located forward of the nose landing
gear. The points "B" and "C" are located outboard of the engine pylon.
. A safety jack positioned at the rear of the aircraft prevents the aircraft
from tipping up.
The open air jacking operation is limited if the wind velocity exceeds
permissible values which depend on aircraft gross weight and center of
gravity position.
In any condition, the aircraft must be pointed upwind.
The three jacks have to be operated together.
The aircraft has to be lifted so that the landing gear can be operated in
the "landing gear shock absorbers deflated, flat tyres" configuration.
As soon as the jacking operation is finished, position the safety jack at
the tail.
Jacking pads have to be used under the jacking points to spread the loads.
To make sure that excessive side loads are not placed on the jacks and
on the aircraft structure, a quick leveling check must be carried out during
the jacking operation.
The aircraft attitude monitor is located in the refuel/defuel control panel
recess.
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The "D4" position corresponds to a longitudinal angle of 0 degree and a

lateral angle of 0 degree.

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JACKING

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TOWING
Towing: you can tow the aircraft by the nose landing gear or the main
landing gear. You can also tow the aircraft with deflated tires.
Towing operation, whether push back or pull, requires a good team
co-operation.
Some airlines have two different types of towing procedures in use:
- maintenance towing,
- transportation servicing towing.
Maintenance towing procedures are laid down in the applicable AMM -
Chapter 09.
Transportation servicing towing procedures are published in the applicable
ramp operation manuals.
The major differences between the two are that transportation services
only get involved with moving aircraft on ramps for positioning or
dispatch pushback.
When they are handling the towing operation, they require either a pilot
or qualified maintenance man on the aircraft brakes.
On the other hand, maintenance personnel is involved in moving aircraft
in abnormal situation such as aircraft stuck in mud, towing with flat tires,
engines removal, etc., as well as routine towing to gates.
Because of the hazards that may be involved in the towing operation,
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major precautions taken have been gathered together and are listed under
paragraph "General Towing Precaution".
Caution and warnings are repeated as necessary in the particular step of
the towing operation to which they apply.

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TOWING

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SAFETY ITEMS
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
The following terms are used in the AMM and are defined as follows:

WARNING: call attention to the use of material, processes, methods,

procedures or limits, which must be followed precisely to
avoid injury or death to persons.

CAUTION: call attention to methods and procedures, which must be

followed to avoid damage to equipment.
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SAFETY ITEMS

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SERVICING POINTS
The ground service connections layout is the same on the AIRBUS A318
and A319.The main difference between A320 and A321 servicing point
is a second potable water draining panel in the center of the A/C on the
A320.
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SERVICING POINTS

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A/C SERVICING ARRANGEMENT
The graphic shows the access to the aircraft by various servicing
equipment. The A318 fuselage is shorter than the rest of the single aisle
aircraft. Due to the removal of 2.39 meters or 1.5 frames of the forward
fuselage, the aft edge of the forward cargo compartment door now is in
close proximity to the engine air intake nose cowl. When using a self
propelled conveyor belt, there is a possibility of structural damage to the
nose cowl because of the clearance.

NOTE: Note: The use of a self-propelled conveyor belt is not

recommended by Airbus.
The main difference between the A318/A319 and the A320/A321
servicing arrangement is that the A320 and A321 can have a bulk loader
on the bulk cargo door.
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A/C SERVICING ARRANGEMENT

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TURNING RADII
The different turning radii are shown on a steering diagram. "Y" is the
distance between the centerline of the A/C longitudinal axis (X-axis) and
the theoretical center of turn for turning radius. "A" matches the minimum
turning width for a 180 turn. "Y, A" and the radii "R3, R4, R5 and R6"
values depend on two parameters: effective turn angle and steering angle.
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TURNING RADII

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ELECTRONIC INSTRUMENT SYSTEM
The Single Aisle aircraft cockpit instrumentation information is displayed
on six display units. These display units are part of the Electronic
Instrument System (EIS).
The EIS is separated into two subsystems:
- Electronic Flight Instrument System (EFIS),
- Electronic Centralized Aircraft Monitoring (ECAM).
The four EFIS displays (2 for each flight crew member) give to the flight
crew all the basic flight parameters. The ECAM system gives to the flight
crew aircraft system displays, faults, checklists and the aircraft operational
status.
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ELECTRONIC INSTRUMENT SYSTEM

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ELECTRONIC INSTRUMENT SYSTEM (continued)
ECAM
The System Data Acquisition Concentrators (SDACs) receive data
from the A/C systems and sends it to the Display Management
Computers (DMCs) for display on the ECAM display units.

NOTE: Note: DMC 1 supplies both ECAM displays and DMC 2 is

also a backup for ECAM displays.
The DMCs acquire data and transmit it to the Display Units (DUs),
which generate the images. Under normal circumstances:
- DMC 1 supplies both ECAM display,
- DMC 2 and 3 are available as a backup.
The Flight Warning Computers (FWCs), heart of the ECAM system,
receive data from:
- the A/C systems to generate red warnings,
- the SDACs to generate amber cautions.
The FWCs then supply:
- the DMCs for the display of alert messages,
- the attention getters,
- the loudspeakers with aural alerts and synthetic voice messages.
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ELECTRONIC INSTRUMENT SYSTEM - ECAM

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ELECTRONIC INSTRUMENT SYSTEM (continued)
ECAM CONTROL AND INDICATING
The EWD is divided into two main parts:
- the upper area is used to display the main engine parameters, the
Fuel On Board (FOB) and the slat/flap position,
- the lower area is used for warning, caution and memo messages.
The SD is divided into two areas:
- the upper part is used to display the various system pages, diagrams
of the A/C systems,
- the lower part is used to display permanent data.
Below the ECAM displays, on the center pedestal, there is the ECAM
control panel. The two control knobs on the LH side are used to adjust
the brightness of the two ECAM screens and to turn them off. The
P/Bs on the RH side are mainly used to:
- display any of the system pages or the STATUS page,
- clear or recall a warning or caution message.
An A/C STATUS page may be also displayed on the SD to give an
operational status of the A/C. When things are not normal the STATUS
page displays:
- operational data on the LH side,
- INOPerative SYStem on the RH side.
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In front of each pilot, there are two attention getters, a red MASTER
WARNing and an amber MASTER CAUTion. As a further means of
getting the attention, there is a loudspeaker on each side of the cockpit
for aural alerts and synthetic voice messages.

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ELECTRONIC INSTRUMENT SYSTEM - ECAM CONTROL AND INDICATING

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ELECTRONIC INSTRUMENT SYSTEM (continued)
EFIS
For the EFIS displays, data from the Air Data and Inertial Reference
System (ADIRS) plus navigation data from the Flight Management
and Guidance System (FMGS) is fed directly to the DMCs.
The DMCs then process the data and generate the images to display.
Under normal circumstances:
- DMC 1 supplies the CAPT EFIS displays,
- DMC 2 supplies the F/O EFIS displays,
- DMC 3 is available as a backup.
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ELECTRONIC INSTRUMENT SYSTEM - EFIS

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ELECTRONIC INSTRUMENT SYSTEM (continued)
EFIS CONTROL AND INDICATING
Flight parameters are displayed on the PFDs while navigation data is
displayed on the NDs.
Outboard of the PFDs, there are control knobs to adjust the brightness
of the associated PFD and ND, and to turn the displays off.
Two EFIS control panels are used to select what is displayed on the
EFIS screens. The EFIS control panels are divided into two sections,
one section associated with the PFD and the other one with the ND.
Just below the ECAM screens, on the center pedestal, there is a
switching panel with, on the right, 2 rotary selectors to restore data
to the EFIS and ECAM displays in abnormal operation.
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ELECTRONIC INSTRUMENT SYSTEM - EFIS CONTROL AND INDICATING

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CLOCK
A single electrical clock gives the Universal Time Coordinated (UTC)
and date as time references for the crew and all peripheral systems. The
other functions available for crew are Elapsed Time (ET) and
chronometer. The clock can be synchronized with satellite GPS time.
The time is also displayed at the bottom of the SD.
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CLOCK

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CENTRALIZED FAULT DISPLAY SYSTEM
The Centralized Fault Display Interface Unit (CFDIU) centralizes and
memorizes all information concerning A/C system failures. Reading or
printing of the failure information is done in the cockpit with any MCDU
or the printer. Most A/C system computers have a BITE. The BITE
permanently monitors the system operation. When a failure is detected,
it is stored in the BITE memory and is transmitted to the CFDIU. The
ECAM, which generate warning and status messages, delivers these data
to the CFDIU as well.
The failure information is available in various reports. The reading of
the failure information is made from two different MCDU menus
depending on if the A/C is in flight or on ground. The SYSTEM
REPORT/TEST function is available on ground only. It enables a dialogue
between the CFDIU and a system computer. The SYSTEM
REPORT/TEST menu page presents the list of all the systems connected
to the CFDIU, in ATA chapter order.
The maintenance Post Flight Report (PFR) can only be printed on ground.
It summarizes and displays the list of the ECAM warning messages and
the fault messages that occurred during the last flight, with the associated
time, flight phase and ATA reference. It helps the maintenance crew to
make a correlation for easier troubleshooting.
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CENTRALIZED FAULT DISPLAY SYSTEM

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CENTRALIZED FAULT DISPLAY SYSTEM

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AIRMAN (OPTION)
AIRMAN is a ground-based software dedicated to the identification and
the management of unscheduled maintenance.
AIRMAN receives and analyses the aircraft status information generated
by the Onboard Maintenance System (OMS) and also e-logbook data.
The information is automatically transmitted to the ground by the aircraft's
communication system.
These information sources are synthesized, combined with Airbus's and
the Airline's own technical documentation and presented through a
user-friendly interface. Aircraft status information is sent to AIRMAN
while the aircraft is both in flight and on ground. Message analysis also
takes place in real-time.
These capabilities maximize the time available for appropriate
maintenance actions to be determined and preparations to be made.
AIRMAN is capable of analyzing an aircraft's fault history and
consequently identifying and prioritizing preventive maintenance actions.
The aircraft maintenance philosophy is based on the following steps:
- fault detection made by the computers BITEs
- cockpit effects as flags on Display Units, and warning generated by the
Flight Warning System (FWS)
- centralization and correlation by the Onboard Maintenance System
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(OMS) of BITE faults, cockpit effects and related maintenance procedures

generation of Post Flight Report (PFR)
- fault event data reporting through the eLogbook
- fault event data and reports transmission to AIRMAN for maintenance
support on ground

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AIRMAN (OPTION)

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AIRMAN (OPTION)

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AIRMAN (OPTION) (continued)
ELOGBOOK
The eLogbook is the main communication means for aircraft
operational staff. It enables the flight crew and the technical staff to
be aware of the aircraft status, to enter aircraft defect and to report
maintenance and servicing actions.
The eLogbook lets the flight crew:
o consult the Logbook status
o accept / create a new flight
o report aircraft defects
o hand over to maintenance
The maintenance staff uses the eLogbook to:
o consult the aircraft status
o report aircraft defects
o report corrective or scheduled maintenance actions
o report servicing actions
o build the Certificate of Release into Service (CRS) of the aircraft
Finally the cabin crew can also use the eLogbook to:
o consult the aircraft status
o inform the flight crew about regulatory cabin defects
o report none regulatory cabin defects
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The eLogbook runs on a fully stand-alone laptop and is not connected

to the aircraft. The eLogbook is stowed in the cockpit by the flight
crew.

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AIRMAN (OPTION) - ELOGBOOK

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AIRMAN (OPTION) - ELOGBOOK

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DIGITAL FLIGHT DATA RECORDING
The Flight Data Interface and Management Unit (FDIMU) has two
primary functions. The first of which is the Flight Data Interface Unit
(FDIU) function.
To fulfill the mandatory requirements of crash recording, the FDIU
acquires and formats various critical flight parameters and system data
before supplying the Solid State Flight Data Recorder (SSFDR).
The linear accelerometer measures the acceleration of the A/C in all three
axes. The System Data Acquisition Concentrator (SDAC) digitizes the
analog signal of the linear accelerometer and sends it to the FDIU.
For maintenance and performance purposes, the optional Quick Access
Recorder (QAR) records the same parameters as the SSFDR. The
operation of the SSFDR is automatic.
On the overhead panel, there is a GrouND ConTroL P/B located on the
ReCorDeR panel. This P/B lets the SSFDR be supplied when the A/C is
on ground for preflight checks before engine start or for test and
maintenance purposes. On the center pedestal, there is a Digital Flight
Data Recorder (DFDR) EVENT P/B, which can be used to set an event
mark on the SSFDR memory.
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DIGITAL FLIGHT DATA RECORDING

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AIRCRAFT INTEGRATED DATA SYSTEM
The main functions of the Aircraft Integrated Data System (AIDS) are
to monitor engine condition, APU condition and A/C performance, and
to provide trouble shooting assistance. The second main function of the
FDIMU is the DMU function which houses the Aircraft Integrated Data
System (AIDS).
The Data Management Unit (DMU) is the heart of the AIDS. It fulfils
the following functions:
- collection, processing and recording of various A/C parameters,
including the mandatory parameters given by the FDIU. The recording
is made in an internal memory of the DMU and on an optional external
recorder called Digital AIDS Recorder (DAR),
- generate various reports according to defined conditions. These reports
are stored in a non-volatile memory of the DMU.
A data loader is used to upload programmed data into the DMU and to
download recorded DMU data on a floppy disk for on ground analysis.
The printer is used to print reports generated by the DMU.
The printer can be automatically controlled by the DMU, manually
controlled from the MCDU or using the AIDS PRINT P/B on the center
pedestal.
The FDMIU has a PCMCIA card slot to upload DMU software and
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download DMU data.

In the A/C, two MCDUs are connected to the DMU.
To initiate communication with the AIDS via either MCDU, the user has
to press the AIDS line select key from the MCDU MENU page. The
AIDS MCDU menu page is then displayed.
Some of the AIDS functions, including real time parameter read out, may
be controlled from this menu.

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AIRCRAFT INTEGRATED DATA SYSTEM

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ON BOARD MAINTENANCE FACILITIES
In this graphic all the indicating/recording systems can be seen together.
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ON BOARD MAINTENANCE FACILITIES

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COMPONENT LOCATION
The EIS and the Centralized Fault Display System (CFDS) computers
are located in the aft avionics rack.
The DFDRS and AIDS computers are located in the aft avionics rack.
Concerning the QAR/DAR, there are several vendors of optical disk
storage media. The recorder is then called Optical QAR/DAR
(OQAR/ODAR).
Also there is a version from Teledyne that is equipped with a GSM
module for data transmission called WQAR (Wireless GroundLink QAR).
The FDIMU computer is located in the aft avionics rack.
The SSFDR is installed, just above the Cockpit Voice Recorder (CVR),
in an unpressurized area of the rear fuselage.
The SSFDR stores, in a solid state memory located in a crash and fire
protected housing, the data of the last 25 hours collected by the FDIU.
The linear accelerometer is near the A/C center of gravity.
It sends the accelerations according to the 3 axis (pitch, roll and yaw) to
the DFDRS.
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COMPONENT LOCATION

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COMPONENT LOCATION

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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
Using the MCDU, you can have access to the CFDS fault messages of
all the indicating/recording systems.
Specific BITE tests are available as well.
ECAM 1 and 2 gives access to FWC 1/2, SDAC 1/2 and ECAM control
panel.
EIS 1 gives access to DMC 1, PFD 1, ND 1, Upper ECAM and Lower
ECAM.
EIS 2 gives access to DMC 2, PFD 2 and ND 2.
EIS 3 gives access to DMC 3.
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SAFETY PRECAUTIONS
Make sure that you obey all the Aircraft Maintenance Manual (AMM)
safety procedures during some Indicating test due to weather radar
operation.
Make sure that:
- all persons are more than 5 meters away from the weather radar antenna
in the area made by an arc of 135 degrees on each side of the A/C
centerline,
- all objects and obstacles are more than 5 meters away from the antenna
in the area made by an arc of 90 degrees on each side of the A/C
centerline.
Stop the fuel tanker 60 meters from the A/C nose while the weather radar
operates. Do not operate the fuel tanker/pump until you stop the operation
of the weather radar.
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24 ELECTRICAL POWER SYSTEM PRESENTATION (1)

have to give priorities to the different power sources in supplying the bus
GENERAL bars.
AC 1 and AC 2 buses are supplied in priority by their own side generator,
There are two identical engine driven generators called Integrated Drive
then the external power, then the APU generator and then by the opposite
Generators (IDGs). They are used as the main power source to supply
generator.
the A/C electrical network.
The IDG basically contains, in a common housing, a generator and a
Constant Speed Drive (CSD). The CSD gives a constant input speed to
the generator, which is required for a constant output frequency.
Each generator supplies 115V 400Hz AC to its own bus:
- generator 1 supplies AC bus 1,
- generator 2 supplies AC bus 2.
This supply is known as split operation, which means that the AC power
sources are never connected in parallel.
Each AC bus supplies a Transformer Rectifier (TR):
- AC bus 1 supplies TR 1,
- AC bus 2 supplies TR 2.
The TRs convert 115V AC into 28V DC to supply their associated DC
buses, DC 1 and DC 2.
DC bus 1 then supplies the DC BAT bus.
The DC battery bus can charge the batteries or receive power from the
batteries as a backup supply, if no other power sources are available.
The electrical system also includes two ESSential (ESS) Buses. One is
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the AC ESS bus fed by AC bus 1 and the other is the DC ESS bus fed
by DC bus 1. These buses are used to supply the most critical A/C
systems.
This is the basic electrical system. We will now introduce some other
components, which also supply the system.
The entire electrical network can also be supplied by the APU generator.
On the ground, the aircraft electrical network can be supplied by an
external power source.
Any one of the power sources can supply the entire electrical network.
As no parallel connection is allowed on this A/C (split operation), we

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GENERAL

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GENERAL (continued)
ABNORMAL CONFIGURATION
The electrical system has an ESS TR, which supplies the DC ESS
Bus in abnormal or emergency configuration.
In abnormal configuration (loss of TR1 or TR2) the ESS TR is
supplied by the AC ESS Bus.
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GENERAL - ABNORMAL CONFIGURATION

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GENERAL (continued)
EMERGENCY CONFIGURATION
In the event of emergency operation, the Emergency Generator (EMER
GEN) supplies the A/C with electrical power. The EMER GEN needs
hydraulic power to operate. This hydraulic power to drive the EMER
GEN is supplied by the Blue Hydraulic system via the Ram Air
Turbine (RAT). The RAT is located in the belly fairing and extends
automatically when AC BUS 1 and 2 have no voltage supply.
The RAT is in the belly fairing and extends automatically in case of
loss of AC BUS 1 and 2. Then, the EMER GEN supplies the DC ESS
through AC ESS directly TR. In emergency configuration (loss of AC
BUS 1 and AC BUS 2), the EMER GEN supplies the ESS TR.
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GENERAL - EMERGENCY CONFIGURATION

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GENERAL (continued)
BATTERY ONLY CONFIGURATION
In emergency configuration with emergency generator not available,
BAT 1 supplies the AC ESS BUS via the static inverter and BAT 2
supplies the DC ESS BUS.
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GENERAL - BATTERY ONLY CONFIGURATION

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CONTROL AND INDICATING/PANEL LOCATION
The ELEC panel is installed on the overhead panel.
For emergency cases, there is an EMER ELEC PWR panel on the LH
side of the overhead panel.
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CONTROL AND INDICATING/PANEL LOCATION
(continued)
MAIN PANEL/ECAM PAGE
The ECAM Electric System page shows all relevant data with regard
to the entire A/C Electrical Power Generation and Distribution
systems. The System page shown here is a normal configuration with
main generators supplying the network.
The battery voltage can be monitored either on the overhead panel or
the ECAM page. Each battery is controlled by a P/B Switch (SW).
Both main generators and the APU generator are controlled by their
related P/B SW.
The external power is also controlled by a P/B SW.
The AC ESS FEED P/B SW lets the pilots change the supply to the
AC ESS bus from AC bus 1 to AC bus 2.
When the BUS TIE P/B SW is in AUTO position, it lets the opening
or closing of the bus tie contactors in order to supply the AC 1 and
AC 2 buses according to the power supply priorities.
When OFF, both bus tie contactors open to isolate one side of the
network from the other (e.g.: smoke configuration).
In case of failure, the IDG P/B SWs disconnect the IDG from the
engine gearbox.
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The GALY & CAB P/B SW lets galleys and some sub-buses be
manually shed.
The COMMERCIAL P/B SW is used for the shedding of all
commercial loads including the GALY & CAB related buses.

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CONTROL AND INDICATING/PANEL LOCATION - MAIN PANEL/ECAM PAGE

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CONTROL AND INDICATING/PANEL LOCATION
(continued)
EMERGENCY PANEL
The EMER GEN TEST P/B is used on ground to test the EMERgency
GENerator or the Static Inverter.
In avionics smoke condition, the GEN 1 LINE P/B disconnects the
generator 1 from the busbar but the generator remains exited to supply
some fuel pumps.
When AC BUS 1 and 2 are no longer supplied, the RAT will extend
automatically to pressurize the blue hydraulic system, which powers
the EMER GEN, if the A/C speed is sufficient.

WARNING: ACTIVATION OF THE RED GUARDED MAN ON

PUSHBUTTON ON THE GROUND OR IN FLIGHT
WILL EXTEND THE RAM AIR TURBINE (RAT),
EVEN ON COLD AIRCRAFT.
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CONTROL AND INDICATING/PANEL LOCATION - EMERGENCY PANEL

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COMPONENT LOCATION
The AC generators provide a 115 VAC, 3-phase, 400 Hz AC supply. The
IDGs and the APU have a nominal 90 kVA power whereas the EMER
GEN has a 5 kVA output.
The static inverter converts the direct current from battery 1 into an AC
current if no other source is available.
The Battery Charge Limiters (BCLs) control the battery coupling and
uncoupling to the DC BATTERY BUS to ensure battery charging and
protection. Each battery is rated at 24 V with a capacity of 23 Ah. All
TRs are identical and interchangeable.
In the Electrical Power Generation System (EPGS), the GAPCU controls
the APU GEN and the external power. The Generator Control Units
(GCUs) protect and control the A/C network and generators and display
the AC electrical power parameters on ECAM. The main C/B panels are
located in the cockpit.
The ESS TR is identical to TR 1 and TR 2. It converts 115 VAC to 28
VDC at a rate of 200 A. The EMER GCU connects the EMER GEN to
the ESS network, if all conditions are met.
The Ground Power Control Panel and the external power receptacle are
installed in front of the nose landing gear. On this panel, 2 Lights indicate
the Ground Power Unit availability (AVAIL light) and connection to the
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A/C network (NOT IN USE light). The Ground Power Unit should supply
400 Hz 3 phase 115 VAC rated at 90 kVA minimum.
The MAINTenance BUS SW, located on the forward cabin Circuit
Breaker (C/B) panel, lets the AC and DC service buses be supplied
without energizing the whole A/C electrical network.
The aft cabin C/B panel contains only C/Bs.

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COMPONENT LOCATION

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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
The GAPCU is the interface between the GCUs and the Centralized Fault
Display Interface Unit (CFDIU) for test purposes and fault reporting on
the MCDUs. Both the BCLs and the EMER GCU communicate with the
CFDIU for the same purposes. The TRs are connected to the CFDIU so
that they can be reset via the MCDU.
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SAFETY PRECAUTIONS
When you do any maintenance task on the electrical system, make sure
that no AC or DC power source is connected to the aircraft electrical
circuits.
Before De-energizing aircraft electrics or before doing the Static Inverter
test, tell all personnel on the aircraft that the lights will go out.
Some components are heavy. You must make sure that you can hold the
component before its removal/installation. If it falls, it can cause injury
to personnel and damage to the equipment.
Dangerous arcing can occur if external power (GPU or Gate power) is
energized when trying to connect power to the aircraft. Make sure that
external power source is de-energized before connecting.
Components can remain hot for one hour following engine shutdown.
Be careful as hot parts and hot oil can cause injury and burn your eyes
and skin. Use protective clothing as oil products are poisonous.
ENVIRONMENTAL PRECAUTIONS
Turn-off unused ground service equipment (GPU, Air conditioning
cart, etc...) if no work is being done or nobody is present on the
aircraft.
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SAFETY PRECAUTIONS - ENVIRONMENTAL PRECAUTIONS

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GENERAL SYSTEM
The Airbus Single Aisle aircraft family includes several different types
of navigation systems, each used for particular functions. The systems
will be explained in separate groups based on their functions. These
functions are broken down into 4 main groups. They will be presented
in separate modules:
- Air Data/Inertial Reference System (ADIRS) and standby instruments,
- dependent position determining systems,
- landing aids,
- independent position determining systems.
There are several subsystems within each group.
The first group includes:
- Air Data Inertial Reference Units (ADIRUs),
- Standby Instruments,
- Digital Distance and Radio Magnetic Indicator (DDRMI),
- Integrated Standby Instrument System (ISIS).
The second group (dependent position determining systems) includes:
- GPS,
- ATC/Traffic Alert and Collision Avoidance System (TCAS),
- DME,
- ADF,
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- VOR.
The third group (landing aids) includes:
- ILS,
- marker receivers.
The fourth group (independent position determining systems) includes:
- Ground Proximity Warning System (GPWS),
- RAs,
- Weather Radar (WXR) and Predictive Windshear (PWS).

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AIR DATA/INERTIAL REFERENCE SYSTEM
The aircraft has three identical and interchangeable ADIRUs.
Each ADIRU combines computers that carry out two functions in a single
unit with a shared power supply. Those computers are:
- an Air Data Reference (ADR) unit,
- a strapdown Inertial Reference (IR) unit, using laser gyros and
accelerometers.
The ADR and IR systems of each ADIRU operate independently, and
failure of one system does not affect the other one.
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AIR DATA/INERTIAL REFERENCE SYSTEM (continued)
AIR DATA INPUTS
The ADIRS systems have peripheral components connected to the
LRUs. These components are an integral part of the Air Data
portion. The components are:
- pitot probes,
- static ports,
- Angle of Attack Sensors (AOA),
- Total Air Temperature Sensor (TAT).
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AIR DATA/INERTIAL REFERENCE SYSTEM (continued)
AIR DATA SECTION
The ADR part supplies various air data parameters to the EFIS
instruments and other users:
- airspeed, mach number, barometric altitude to the PFD and overspeed
to the Flight Warning Computer (FWC),
- TAT, Static Air Temperature (SAT), and AOA sensors to other
indicators and users.
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AIR DATA/INERTIAL REFERENCE SYSTEM (continued)
INERTIAL REFERENCE SECTION
The IR part of the ADIRU uses laser gyros and accelerometers. They
give inertial data to the EFIS, Flight Management and Guidance
Computers (FMGCs) and other users. Each ADIRU provides:
- attitude, heading, Vertical Speed (V/S), flight path vector to the PFD,
- heading, ground speed to the ND,
- IR position to FMGCs for A/C position computation. This
information is available on the MCDU DATA page.
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AIR DATA/INERTIAL REFERENCE SYSTEM (continued)
ADIRS CONTROL AND INDICATING
The three ADIRUs are controlled through the single ADIRS Mode
Selector Unit (MSU) located on the overhead panel.
The initialization of the ADIRUs is normally done through either one
of the two MCDUs installed on the center pedestal.
The Digital Distance Radio Magnetic Indicator (DDRMI) is installed
on the main instrument panel below the standby instruments.
It supplies digital DME distance information, as well as heading
coming from ADIRS, and VOR/ADF bearing information.
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AIR DATA/INERTIAL REFERENCE SYSTEM (continued)
PFD AND ND INDICATING
ADIRU 1 supplies the CAPT PFD and ND, and ADIRU 2 supplies
the F/O PFD and ND.
ADIRU 3 is used as a hot spare, and can be switched via the switching
panel to replace either ADIRU 1 or ADIRU 2.
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STANDBY INSTRUMENTS
In case of EFIS system failures, the standby instruments can be used.
There are 3 conventional standby instruments, installed on the instrument
panel:
- airspeed indicator,
- altimeter,
- horizon.
The standby compass is installed just below the overhead panel.
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STANDBY INSTRUMENTS

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INTEGRATED STANDBY INSTRUMENT SYSTEM (Option)
The enhanced standby instrument, called ISIS (Integrated Standby
Instrument System), is installed on the instrument panel near the ECAM.
It replaces the 3 conventional standby instruments. The inputs to the
airspeed indication and the altimeter come directly from the air sources
(standby pitot probe and static ports). The standby horizon is
self-contained. ISIS is also capable of displaying heading and ILS
information. The standby compass is installed just below the overhead
panel.
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INTEGRATED STANDBY INSTRUMENT SYSTEM (OPTION)

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COMPONENT LOCATION
Here is the location of the 3 ADIRUs.
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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
All the navigation systems can be tested from the MCDUs except the
ISIS.
ISIS tests and OTHER DATA are accomplished directly from the unit
itself.
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MAINTENANCE/TEST FACILITIES

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SAFETY PRECAUTIONS
When you work on A/C, make sure that you obey all the Aircraft
Maintenance Manual (AMM) procedures. This will prevent injury to
persons and/or damage to the A/C.
Before you do the test of the probes, remove the protective covers. Do
not continue the test for more than one minute to prevent damage.
Do not touch the probes immediately after the test, they are hot.
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SAFETY PRECAUTIONS

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LANDING AIDS
The navigation systems that require external inputs of the aircraft to
operate are: the landing aids systems, the dependent position determining
systems and the Head-Up Display (HUD) system. They include:
- ILS,
- marker system,
- GPS,
- ATC/Traffic Collision Avoidance System (TCAS)/Traffic and Terrain
Collision Avoidance System (T2CAS) as option,
- DME,
- ADF,
- VOR.
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LANDING AIDS

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LANDING AIDS (continued)
ILS AND MARKER SYSTEM
The ILS sends to the flight crew or Autopilot (AP) signals for optimum
descent path for landing. The ILS signal reception is done in part by
the Multi-Mode Receiver (MMR). The system provides lateral
guidance and vertical guidance to the aircraft approaching the runway.
The marker beacon system is a radio navigation aid that, in conjunction
with an instrument landing system, indicates the distance between the
A/C and the runway threshold. The marker function is done inside
the VOR receivers, but it is only active in VOR 1. There are three
types of marker beacons on an ILS:
- the outer marker,
- the middle marker,
- the inner marker.
When the aircraft goes over the beacons, the marker beacon
information is displayed flashing on the PFDs, with related audio
signals.
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LANDING AIDS - ILS AND MARKER SYSTEM

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LANDING AIDS (continued)
LANDING AIDS CONTROL AND INDICATING
The ILS information is displayed on the PFDs as 2 scales. One
horizontal scale for the localizer signal and one vertical scale for the
Glide Slope (G/S) signal.
Note that for redundancy:
- ILS 1 is displayed on PFD 1 and ND 2,
- ILS 2 is displayed on PFD 2 and ND 1.
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LANDING AIDS - LANDING AIDS CONTROL AND INDICATING

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LANDING AIDS (continued)
HEAD-UP DISPLAY (OPTION)
The HUD is an optional flying aid system, which gives to the pilot
an image superimposed on the outside world in his field of view. This
aid is based on the principle of symbol projection on an external
combiner, mainly composed of a flat sheet of glass.
The objectives of the HUD are :
- to supply guidance information on the ground, at take-off and landing
in conditions of reduced visibility;
- to give information to the pilot for visual approach on airfields
without Instrument Landing System (ILS);
- to monitor the automatic approach operations.
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LANDING AIDS - HEAD-UP DISPLAY (OPTION)

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LANDING AIDS (continued)
HEAD-UP DISPLAY CONTROL
The HUD system is composed of one HUD set (giving head up data
for the CAPT).
The HUD is composed of one Head-Up Computer (HUDC), one
Head-Up Projection Unit (HPU), one Head-Up Combiner Unit (HCU),
one Personalization Memory Module (PMM) and one HUD Control
Panel.
The HUDC is located in the avionics bay 82VU.
It is used:
- to centralize the source data from the aircraft systems,
- to send the necessary data to the HPU.
The HPU is located inside the cockpit above the Captain.
It is used to generate the image to project towards the HCU. The
generated image is sent to the HCU by the HPU optical lenses.
The HCU is located inside the cockpit in front of the Captain forward
field of view.
It is used to reflect the image projected by the HPU towards the pilot
while the forward field of view remains visible through the combiner.
The HCU can take two positions (operational or retracted) by means
of a declutching handle, located on its right (left) hand side.
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The PMM is a memory module used to store the HPU installation

adjustment (Contains data specific to the A/C particular installation,
eg correction of error in X/Y positioning ).
One HUD Control Panel on 131VU in the cockpit left hand side is
composed of:
- A HUD potentiometer used to switch ON/OFF the HUD,
- A DECLUTTER pushbutton switch used to change the display,
- And an X WIND switch also used to change the display.

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LANDING AIDS - HEAD-UP DISPLAY CONTROL

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LANDING AIDS (continued)
HCU DISPLAY
According to the flight configuration, different displays can be shown
to the pilot.
The HUD image is divided into ten areas, which show indications
related to:
- attitude, guidance and radio height,
- heading,
- ground roll information,
- mach/ILS data,
- air speed,
- Flight Mode Annunciator (FMA),
- system messages,
- vertical speed,
- altitude,
- approach trajectory deviation.
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LANDING AIDS - HCU DISPLAY

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LANDING AIDS (continued)
EXAMPLE OF HUD USE
Film on HUD use
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LANDING AIDS - EXAMPLE OF HUD USE

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RADIO NAVIGATION SYSTEM
The A/C has the following equipment installed:
- two VOR/marker receivers,
- two DMEs interrogators,
- two MMRs: ILS and GPS,
- two ADFs receivers.
NORMAL TUNING
The Flight Management and Guidance Computers (FMGCs) contain
the navigation computer function that calculates the aircraft position.
The FMGCs tune the radio navigation receivers automatically and
use the navigation info from these receivers for display and also in
background for A/C position computation. The Jeppesen database is
loaded in the FMGCs. This information includes: station identifiers,
and specific information (frequency, identification and coordinates)
about the station.
Access to the MCDU RADIO NAV page lets the crew manually tune
the radio navigation receivers, via the FMGCs for display. Manual
tuning overrides automatic tuning.
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RADIO NAVIGATION SYSTEM - NORMAL TUNING

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RADIO NAVIGATION SYSTEM (continued)
BACKUP TUNING
Radio Management Panel (RMP) 1 and 2 are capable of tuning the
own side Navigation receivers in backup mode if both FMGCs have
failed or both MCDUs have failed and manual tuning is needed by
the crew.
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RADIO NAVIGATION SYSTEM - BACKUP TUNING

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RADIO NAVIGATION SYSTEM (continued)
RADIO NAVIGATION CONTROL and INDICATING
The EFIS control panel mode switches control what type of
information is shown to the flight crew on the ND. They are located
on both sides of the glareshield. The toggle switches on the EFIS
control panel enable the display of the VOR or ILS pointers on the
ND. RMPs are located on the center pedestal.
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RADIO NAVIGATION SYSTEM (continued)
ND MODES
There are five different ND modes that can be selected via the EFIS
control panels. These modes are the PLAN, ARC, NAV, VOR, and
ILS modes.
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RADIO NAVIGATION SYSTEM - ND MODES

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MMR (GPS PART) SYSTEM
The GPS receiver uses data sent by 24 satellites.
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MMR (GPS PART) SYSTEM

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MMR (GPS PART) SYSTEM (continued)
NETWORK ARCHITECTURE
GPS data may be processed and used by anyone. The satellite system
transmits precise phase, and time signals. These signals are decoded,
synchronized and triangulated by the receivers.
There are four monitor stations:
- Hawaii,
- Ascension Island,
- Diego Garcia,
- Kwajelein.
There is also a master control station at Colorado Springs. The master
control station transmits orbital decay information (Ephemerid data)
back to the satellite so that these distance errors can be compensated
for the user receiver. The system gives accurate positional altitude
and time information. This information is supplied to the FMGCs for
aircraft present position calculation.
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MMR (GPS PART) SYSTEM - NETWORK ARCHITECTURE

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MMR (GPS PART) SYSTEM (continued)
GPS CONTROL AND INDICATING
The GPS data is accessible on the MCDU. Selecting DATA page P/B
on the MCDU and then the GPS monitor line select key, will give the
information related to the GPS receivers.
GPS when receiving adequate signals to calculate a present position
will be annotated at the bottom of the ND. This is displayed as "GPS
PRIMARY".
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MMR (GPS PART) SYSTEM - GPS CONTROL AND INDICATING

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ATC/TCAS SYSTEM
The Single Aisle family has two ATC transponders, which respond to
the ATC secondary surveillance radar and TCAS (or T2CAS option)
interrogations.
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ATC/TCAS SYSTEM

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ATC/TCAS SYSTEM (continued)
TCAS PRINCIPLE
The TCAS gives traffic information and warnings of potential conflicts
to the crew, with vertical avoidance instructions. TCAS can only
detect and indicate intruders that have at least one operative ATC
transponder.
The Traffic and Terrain Collision Avoidance System (T2CAS) is a
combination of two functions in a single line replaceable unit (LRU).
The Terrain Awareness and Warning System (TAWS) of the T2CAS
is the part of the T2CAS that ensures the EGPWS functions. The
Traffic Collision avoidance System (TCAS) part of the T2CAS is the
part that ensures the same functions as the TCAS.
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ATC/TCAS SYSTEM (continued)
ATC/TCAS SYSTEM
In normal operation Air Data Reference (ADR) 1 supplies barometric
information to ATC 1, ADR 2 supplies ATC 2.
The ATC transponder is an integral part of the ATC radar beacon
system. The transponder is interrogated by the ground station and
replies with a series of pulses. These reply pulses are coded to supply
identification MODE A and altitude reporting MODE C, and selective
call and flight data MODE S on the Air Traffic Controllers (ATCs)
radar scope.
This information enables the controller to distinguish the A/C and to
maintain effective ground surveillance of the air traffic.
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ATC/TCAS SYSTEM (continued)
ATC/TCAS CONTROL AND INDICATING
The single control panel on the center pedestal is used for the controls
of the ATC and TCAS (or T2CAS) systems.
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ATC/TCAS SYSTEM (continued)
TCAS INDICATING
Here are the different indications that are given by the TCAS (or
T2CAS) computer linked to audio warnings.
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COMPONENT LOCATION
Let's see the location of the different navigation systems LRUs.
The radio navigation receiver antennae are located on the upper and lower
fuselage:
- DME,
- ATC,
- ADF,
- VOR,
- MMR.
The radio navigation receiver antennae are located on the upper and lower
fuselage:
-TCAS (or T2CAS),
- Enhanced Ground Proximity Warning System (EGPWS).
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COMPONENT LOCATION

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COMPONENT LOCATION (continued)
NAVIGATION ANTENNAS LOCATION (1/3)
The MMR, ADF and VOR antennae are installed on the upper and
lower portion of the fuselage.
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COMPONENT LOCATION - NAVIGATION ANTENNAS LOCATION (1/3)

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COMPONENT LOCATION (continued)
NAVIGATION ANTENNAS LOCATION (2/3)
The marker antenna and DME antennae are installed on the lower
portion of the fuselage. There are also two TCAS (or T2CAS)
antennae, (1 at the top, 1 at the bottom).
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COMPONENT LOCATION - NAVIGATION ANTENNAS LOCATION (2/3)

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COMPONENT LOCATION (continued)
NAVIGATION ANTENNAE LOCATION (3/3)
The four ATCs antennae are located on the upper and lower portion
of the fuselage.
The G/S and Localizer (LOC) dual antennae are located in the radome.
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COMPONENT LOCATION - NAVIGATION ANTENNAE LOCATION (3/3)

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MAINTENANCE/TEST FACILITIES
All navigation systems can be tested from the MCDUs.
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SUMMARY
This picture lists the navigation systems that are installed on the Single
Aisle A/C.
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SUMMARY

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34 INDEPENDENT POS DETERMINING SYS PRES. (1)

GENERAL
The Independent Position determining systems include:
- Enhanced Ground Proximity Warning System (EGPWS) or Traffic and
Terrain Collision Avoidance System (T2CAS) as option,
- Radio Altimeters (RAs),
- Weather Radar (WXR) and Predictive Windshear (PWS).
These systems do not rely on external sources to provide the flight crew
with position determination.
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GENERAL

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EGPWS
The purpose of the EGPWS is to generate aural and visual warnings if
the A/C adopts a potentially hazardous configuration of Controlled Flight
Into Terrain (CFIT).
This system has five basic Enhanced Ground Proximity Warning System
(EGPWS) modes and has 2 TERRAIN modes called TERRAIN Clearance
Function (TCF) and the TERRAIN Awareness and Display (TAD).
As an option, the T2CAS can replace the EGPWS.
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EGPWS

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EGPWS (continued)
SYSTEM ARCHITECTURE
The EGPWS computer (or T2CAS computer as an option) processes
the data from:
- RA 1,
- Air Data/Inertial Reference Unit (ADIRU) 1,
- Multi-Mode Receiver (MMR) 1 (Instrument Landing System (ILS)
part),
- Flight Management and Guidance Computer (FMGC) 1,
- Landing Gear Control and Interface Unit (LGCIU) 1,
- WXR/PWS (for ND image source selection between both systems).
The Traffic Collision avoidance System (TCAS) part of the T2CAS
is the part that ensures the TCAS functions.
The Terrain Awareness and Warning System (TAWS) of the T2CAS
is the part of the T2CAS that ensures the EGPWS functions such as:
- basic TAWS modes base on Radio Altitude (RA),
- predictive TAWS modes: Collision Prediction and Alerting (CPA)
function and Terrain Hazard Display (THD) which provides a
forward-looking terrain alerting capability.
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EGPWS - SYSTEM ARCHITECTURE

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EGPWS (continued)
GPWS PANEL
The GPWS/T2CAS control panel is located on the overhead panel
and enables the deactivation of:
- TERRAIN mode,
- complete or partial basic EGPWS mode in specific approach
configuration.
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EGPWS (continued)
CONTROL AND INDICATING
EGPWS and T2CAS have the same visual warnings, that are shown
on the instrument panels. The systems can be tested by pressing either
of the PULL UP/GPWS P/BSW.
In addition, two loudspeakers installed on each lower side of the main
panel broadcast EGPWS/T2CAS aural warnings, even if loudspeaker
knobs are turned off.
Terrain information will be automatically displayed on the ND if there
is any danger within the proximity of the A/C. The terrain elevation
surrounding the A/C is color coded. The TERRain ON ND P/B is
used to display the terrain information on the ND all the time on
request.
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RADIO ALTIMETER
The RAs supply accurate measurement of the A/C height above the
ground during initial climb, landing and approach phases.
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RADIO ALTIMETER (continued)
CONTROL AND INDICATING
RA data is supplied to several users and is displayed on both PFDs at
all times below 2500 feet Above Ground Level (AGL).
In normal operation, the RA 1 height is displayed on the CAPT PFD
and RA 2 height on the F/O PFD.
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RADIO ALTIMETER - CONTROL AND INDICATING

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34 INDEPENDENT POS DETERMINING SYS PRES. (1)

WXR/PWS
WXR is installed to detect precipitation. The displayed returns are shown
on the ND.
The weather radar supplies PWS detection. A wind shear event is a sudden
change of wind speed and/or direction over a short distance with a
downwards and/or upwards movement of the air very dangerous during
take off and approach phases.
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WXR/PWS

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WXR/PWS (continued)
WXR/PWS PANEL
The WXR control panel is installed on the center pedestal. The
information is displayed on the CAPT or F/O ND.

CAUTION: when the WXR is "ON":

- personnel should not be within 5 meters of the radome,
- no metallic obstacle should be within 5 meters,
- no refueling within 60 meters.
The multiscan is a radar function that displays all significant weather
at all ranges, at all aircraft altitudes, and at all times on a display that
is essentially clutter-free, without the need for pilot to input tilt or
gain settings. The multiscan function optimizes weather detection and
minimizes ground clutter.
The weather radar can operate in autotilt mode (automatic tilt angle):
the use of the automatic tilt function is recommended in WX and
TURB modes. The autotilt function uses the terrain altitude
information of the EGPWS. Based on the aircraft altitude above the
terrain and on terrain conditions in the area, the EGPWS determines
the optimum tilt angle for the radar
Automatic tilt is selected by setting the MULTISCAN SW to AUTO
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on the weather radar control unit.

- switch to AUTO: Tilt setting for weather scans is automatic,
- switch to MAN: Tilt is controlled with the manual tilt control knob.

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COMPONENT LOCATION
Here is the location of the:
- EGPWS computer or T2CAS computer,
- WXR computer.
The RAs are located in the aft cargo compartment.
The various antennae are located on the lower portion of the fuselage.
The WXR antenna is located in the radome.
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COMPONENT LOCATION

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COMPONENT LOCATION

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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
All navigation systems can be tested from the MCDUs.
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34 INDEPENDENT POS DETERMINING SYS PRES. (1)

SAFETY PRECAUTIONS
When you work on A/C, make sure that you obey all the Aircraft
Maintenance Manual (AMM) procedures. This will prevent injury to
persons and/or damage to the A/C.
Make sure that:
- all persons are more than 5 meters (16.4 feet) away from the antenna,
- nobody is in the area made by an arc of 135 degrees on each side of the
A/C centerline.
Make sure that there is no sign of corrosion or damage and no foreign
objects in the test equipment.
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22 AUTO FLIGHT SYSTEM PRESENTATION (1)

GENERAL
The Auto Flight System (AFS) is divided into four main parts:
- Flight Management (FM),
- Flight Guidance (FG),
- Flight Augmentation,
- Fault Isolation and Detection System (FIDS).
The first two functions are accomplished by the Flight Management and
Guidance Computers (FMGCs). The other two functions are accomplished
by the Flight Augmentation Computers (FACs).
The AFS calculates the position of the aircraft using several aircraft
sensors.
In addition, the system has the capability of storing flight plans in its
memory, which are predetermined by the airline. A flight plan describes
a complete flight from departure to arrival, it includes vertical information
and all intermediate waypoints. Knowing the position of the aircraft and
the desired flight plan (chosen by the pilot), the AFS is able to compute
the orders sent to the flight controls and engines so that the aircraft can
follow the flight plan.
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GENERAL

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GENERAL

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FLIGHT MANAGEMENT/FLIGHT GUIDANCE
The FM part has several functions linked to the flight plan such as lateral
and vertical guidance associated with performance computation.
The FG part has 3 functions:
- Autopilot (AP),
- Flight Director (FD),
- Autothrust (A/THR).
The FMGC functions, FM and FG are controlled from the MCDUs and
the Flight Control Unit (FCU).
Basically, the MCDUs provide the long term interface between the crew
and the FMGCs (e.g. flight plan selection and modification) while the
FCU provides the short term interface (e.g. engagement of the autopilot,
flight director and A/THR functions).
Besides the MCDUs and the FCU, the main displays presenting Flight
Management and Guidance information are the EFIS displays.
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FLIGHT MANAGEMENT/FLIGHT GUIDANCE (continued)
AUTOPILOT/FLIGHT DIRECTOR
The main AP and FD functions are:
- stabilization of the aircraft around its center of gravity when the
AP/FD system holds vertical speed or flight path angle and heading
or track,
- acquisition and holding of a flight path,
- guidance of the aircraft after take off,
- automatic landing and go around.
The AP function gives orders to control:
- the position of the control surfaces on the three axes (pitch, roll and
yaw),
- the nose wheel steering.
The FD function generates optimum guidance orders used in manual
controls. The FD is also used to monitor the AP when it is engaged.
The FD symbols are displayed on the PFDs.
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FLIGHT MANAGEMENT/FLIGHT GUIDANCE - AUTOPILOT/FLIGHT DIRECTOR

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FLIGHT MANAGEMENT/FLIGHT GUIDANCE (continued)
AUTOTHRUST
The A/THR system fulfills the following functions through the control
of the thrust:
- speed or mach hold (either FMGCs computed or from throttle levers
position),
- thrust hold (either FMGS computed or from throttle lever position),
- thrust reduction during descent and during flare in final approach,
- protection against insufficient speed linked to excessive angle of
attack.
To fulfill the A/THR functions, the FMGCs communicate with the
Full Authority Digital Engine Control (FADEC) via the FCU and the
Engine Interface Units (EIUs).
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FLIGHT AUGMENTATION
The flight augmentation part fulfills the following functions:
- rudder trim,
- yaw damper,
- rudder travel limitation,
- flight envelope protection,
- FIDS.
For flight envelope protection, the FAC computes:
- the various speeds for aircraft operation (e.g. flaps limit speed),
- the excessive angle of attack and windshear detection,
- the low energy warning, indicating to the crew that the aircraft is quickly
decelerating and that thrust will have to be increased to recover a positive
flight path angle through pitch control.
The FIDS function is only active in FAC 1. FAC 1 is connected to the
BITE of all the AFS computers and communicates to the Centralized
Fault Display System (CFDS).
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FLIGHT AUGMENTATION

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PANEL LOCATION/CONTROL AND INDICATING
The different panels used for AFS control and indicating are described
in this topic.
MCDUs
Two MCDUs are located on the center pedestal.
The MCDU is the primary entry/display interface between the pilot
and the FM part of the FMGC.
The MCDUs exchange information not directly but via the FMGCs.
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PANEL LOCATION/CONTROL AND INDICATING - MCDUS

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
FLIGHT CONTROL UNIT
A FCU is installed on the glareshield.
The FCU front face includes an AFS control panel between two EFIS
control panels.
The AFS control panel allows and displays the AP and A/THR
engagement, and the selection of guidance modes and flight
parameters.
Each pilot has an EFIS control panel to select the display on his related
EFIS screens.
Speed, lateral guidance and level change can be selected by the pilot
after a "pull" action or managed by the flight management after a
"push" action. In that case, the parameter window shows dashes (- -
- -) and a white dot will indicate that the reference is managed.
An exception to this rule is when the V/S - FPA knob is pushed, a
level off is immediately commanded.
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PANEL LOCATION/CONTROL AND INDICATING - FLIGHT CONTROL UNIT

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
EFIS DISPLAYS
Four EFIS displays, i.e. two PFDs and two NDs, are located on the
main instrument panel.
Flight parameters are displayed on the PFDs while the flight plan and
navigation data are displayed on the NDs.
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PANEL LOCATION/CONTROL AND INDICATING
(continued)
PRIMARY FLIGHT DISPLAY
As the main guidance instrument, the PFD displays various speeds
and reference parameters used for short term flight guidance.
The Flight Mode Annunciator (FMA) is the top part of the PFD and
indicates:
- the AP, FD and A/THR engagement status,
- the AP/FD and A/THR modes,
- the landing category.
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PANEL LOCATION/CONTROL AND INDICATING - PRIMARY FLIGHT DISPLAY

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
SIDE STICKS
Two side sticks are respectively located on the CAPT lateral panel
and F/O lateral panel.
When the AP is engaged, the side sticks are locked in the neutral
position, by solenoids.
The AP is disengaged, and the side sticks become free, when the red
TAKEOVER & PRIORITY pushbutton on any side stick is pressed
or when a force above a certain threshold is applied on any side stick.
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PANEL LOCATION/CONTROL AND INDICATING - SIDE STICKS

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
THROTTLE LEVERS
The engines are manually controlled by throttle levers, which are
located on the center pedestal, or automatically controlled by the
A/THR system. Two red INSTINCTIVE DISCONNECT pushbuttons,
located on the throttle levers, allow the A/THR function to be
disengaged (push either one). Note that the throttle levers never move
automatically.
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PANEL LOCATION/CONTROL AND INDICATING
(continued)
FLIGHT CONTROL PANELS
On the two flight control (FLT CTL) panels, located on the overhead
panel, there is a pushbutton to respectively disengage FAC 1 and 2.
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PANEL LOCATION/CONTROL AND INDICATING - FLIGHT CONTROL PANELS

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COMPONENT LOCATION
The AFS computers are located in the aft avionics rack (80VU).
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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
Using the MCDU, you can have access to the CFDS fault messages of
the AFS.
The BITE of each AFS computer including FCU and MCDUs, can be
interrogated via the FAC 1. AFS TEST and LAND TEST can be launched
from the MCDUs.
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MAINTENANCE/TEST FACILITIES

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SAFETY PRECAUTIONS
Make sure that all circuits in maintenance are isolated before you apply
electrical power to the aircraft.
Before you pressurize/depressurize a hydraulic system:
- make sure that the travel ranges of the flight control surfaces are clear,
- check that the Flap/Slat lever agrees with the actual flap and slat surface
position,
- make sure that the Speed brake Selector is retracted and disarmed.
Put safety devices and warning notices before you start a task on or near:
- the flight controls,
- the flight control surfaces,
- the landing gear and the related doors,
- components that move.
Put warning notices in the cockpit to identify systems undergoing
maintenance work.
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SAFETY PRECAUTIONS

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46 AIR TRAFFIC INFO MANAGEMENT SYS PRES. (1)

GENERAL
The Air Traffic Information Management System (ATIMS) complies
with the future developments of the Communication, Navigation,
Surveillance and Air Traffic Management (ATM) also known as Future
Air Navigation System (FANS). It covers the evolution of the way the
airspace will be used in the years to come.
It will be used in different operational environments and is designed to
be easily configured to the airlines needs.
ATIMS enables data-link communication: VHF Data Radio (VDR), HF
Data Radio (HFDR) and SATCOM (if installed) and the exchange of
complex data or specific reports between the aircraft and the ground
centers:
- controller pilot data-link communications (HF voice in backup) for air
traffic management,
- automatic reporting (position, intention) for air traffic surveillance,
- specific airline/aircraft communications (operational control) to improve
airline operational costs and flexibility.
Standard AOC functionalities are basically provided but airlines can
customize these functions and the way they are accessed by the crew.
On the ground, the different existing networks dispatch the messages.
These networks are operated by private companies such as ARINC, SITA
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and others, which are known as service providers.

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GENERAL

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GENERAL (continued)
PRE-FANS, FANS
There are three stages of FANS development.
- Pre-FANS (Communications (COM) and AOC functions),
- FANS A (pre-FANS + ATC functions) and
- FANS B (FANS A + improved ground network + Traffic Alert and
Collision Avoidance System (TCAS)).
Today, the pre-FANS allow the AOC function.
It provides the crew with Aircraft Communication Addressing and
Reporting System (ACARS) equivalent functions and more, as for
instance:
- NOtice To AirMen (NOTAM), weather, winds aloft requests,
- free text message exchanges,
- diversion, delay, refueling, flight reports,
- aircraft data from Centralized Fault Display System (CFDS), Aircraft
Integrated Data System (AIDS), cabin terminal...etc.
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GENERAL - PRE-FANS, FANS

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ARCHITECTURE
The ATIMS pre-FANS configuration mainly has an Air Traffic Service
Unit (ATSU).
The ATSU is used:
- to manage communications (air/ground data-links),
- to manage applications (on board data routing).
The ATSU is configured in pre-FANS to do:
- the management of air/ground communication,
- Airline Operational Control applications.
The communication devices include:
- the SATCOM, if installed,
- the VDR
- the HF.
The Pre FANS crew interfaces include:
- the ECAM, and,
- the MCDU.
For FANS-A and FANS-B equipped aircraft there are:
- two Data Communication Display Units (DCDUs),
- two attention getter pushbuttons, marked "ATC MSG",
- the MCDU "ATC COM" key operative.
The ATSU manages the communication message exchanges to and from
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the peripheral computers (on-board routing function).

The software is uploaded in the ATSU by means of the Multipurpose
Disk Driver Unit (MDDU) or the Portable Data Loader (PDL).

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ARCHITECTURE

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PANEL LOCATION/CONTROL AND INDICATING
We will now have a look at the control and indicating of the system.
PRE-FANS
The ATSU line key from the MCDU MENU gives access to:
- AOC MENU line key and,
- COMM line key.
MCDU "ATC COM" key is inoperative.
The COMM line key gives access to the COMM MENU, which is
used for the management and control of the air/ground router.
The AOC line key gives access to the AOC MENU page, which is
used for the management of AOC functions (equivalent to ACARS
functions).
The content of this menu depends on the AOC applications selected
by the airline.
Messages related to the pre-FANS status are displayed on the EWD.
The "ATC MSG" pushbutton is inoperative.
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PANEL LOCATION/CONTROL AND INDICATING - PRE-FANS

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
FANS
In FANS configuration the "ATC MENU" prompt is available to get
access to ATC pages. The "ATC COMM" key gives the same access
but as a shortcut.
Two attention getter pushbuttons are operative and indicate ATC
incoming messages.
Two DCDUs give full time accessibility and readability for messages
exchanged with the ATC and both crew, which require only limited
head-down time.
Text messages instead of voice communication reduce the risk of
misunderstanding.

NOTE: Note: The DCDUs are the interfaces for ATC messages
only.
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PANEL LOCATION/CONTROL AND INDICATING - FANS

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PANEL LOCATION/CONTROL AND INDICATING
(continued)
MCDU MENU
The COMM MENU is used for communication settings, as selection
of the Service provider and frequency.
The AOC MENU line key gives access to the AOC MENU which is
equivalent to ACARS functions.
The content of this menu depends on the AOC applications selected
by the airline.
The ATC MENU gives access to the least frequent ATC operations,
which are:
- data entry for message preparation,
- access to previously exchanged messages (MSG LOG).
Note that the ATC COMM key has the same functions as ATC MENU
but provides quick access to the page whatever the MCDU menus
displayed.
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PANEL LOCATION/CONTROL AND INDICATING - MCDU MENU

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COMPONENT LOCATION
The ATSU is in the 81VU in the avionics compartment.
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COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
The ATIMS BITE information and test request are available through
MCDU menus which communicate with the ATSU BITE.
The ATIMS maintenance menu is accessible using the "ATIMS" prompt
from the COM SYSTEM REPORT/TEST page.
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MAINTENANCE/TEST FACILITIES

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23 COMMUNICATIONS SYSTEM PRESENTATION (1)

GENERAL
The single aisle aircraft communication system has two sub-systems:
- radio communication,
- on-board communication.
The radio communication systems are used for communications to and
from the aircraft.
The on-board internal communication system is divided into 4 functions:
- service interphone (on ground only) for maintenance technician
communication with cockpit or cabin thanks to several jack connectors
around the A/C.
- Flight interphone for cockpit internal communication and also with the
ground mechanic,
- Passenger Address (PA) from the cockpit or from cabin crew stations
for passenger announcements,
- cabin interphone for cabin crew or cabin crew/pilots communication.
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GENERAL

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GENERAL

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GENERAL

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RADIO COMMUNICATION SYSTEM
The radio communications system lets the crew communicate with ground
stations and to other aircrafts through VHF Data Radio (VDR), High
Frequency Data Radio (HFDR) and SATCOM if installed.
The VHF transceivers are identical and interchangeable, as are the HF
transceivers. VDR 1 and VDR 2 are normally used by the flight crew for
voice communications. VDR 3 is used for Aircraft Communication
Addressing and Reporting System (ACARS) functions, and is used as
back-up voice communications in case of system 1 or 2 failure.
The HF transceivers are used when the aircraft is beyond the useful range
of the VHF radios.
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RADIO COMMUNICATION SYSTEM

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RADIO COMMUNICATIONS CONTROL AND INDICATING
RMP
The Radio Management Panels (RMPs) give the capability of tuning
all communication radios. The frequencies are tuned by using the 2
concentric knobs.
There are two RMPs located on the center pedestal and a third optional
one on the overhead panel.
Any RMP can tune any communication radio but each one is normally
dedicated to a particular radio.
- RMP 1 is dedicated to VDR 1,
- RMP 2 is dedicated to VDR 2,
- RMP 3 is dedicated to VDR 3 and HF 1/HF 2 (if installed).
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RADIO COMMUNICATIONS CONTROL AND INDICATING - RMP

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RADIO COMMUNICATIONS CONTROL AND INDICATING
(continued)
ACP
There are three Audio Control Panels (ACPs), each one is located
close to a RMP. The ACPs allow for audio channel selection for both
transmission and reception. Additionally, the ACP provides individual
volume control for reception channels. ACP 1 is dedicated to the
captain and ACP 2 is dedicated to the F/O. Both ACPs 1 and 2 are
located on the center pedestal left and right respectively. A third
optional ACP is located on overhead panel and is dedicated for a third
occupant and may be used as a back up for captain or first officer in
case of failure.
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RADIO COMMUNICATIONS CONTROL AND INDICATING - ACP

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ON-BOARD COMMUNICATIONS
Of the four on-board communication systems, two Cabin
Intercommunications Data System (CIDS) directors control three of the
four functions. The CIDS directors manage the following on-board
communication functions:
- PA system for passenger announcements (from the cockpit or from
cabin crew stations),
- cabin interphone system for crew communication (cabin together or
with cockpit),
- service interphone.
The CIDS directors do not manage the flight interphone.
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ON-BOARD COMMUNICATIONS

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ON-BOARD COMMUNICATION CONTROL AND
INDICATING
ACP
The ACPs also give to the flight crew the ability to communicate with
ground personnel and cabin crew and annunciate calls to the flight
deck.
Calls to the flight deck can be made from any of the cabin attendant
handsets. Mechanic calls can also be made from the External Power
Panel. This will cause a buzzer to sound and a CALL light to come
on, on the ACPs.
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ON-BOARD COMMUNICATION CONTROL AND INDICATING - ACP

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ON-BOARD COMMUNICATION CONTROL AND
INDICATING (continued)
FLIGHT INTERPHONE
This system allows the flight crew members to communicate among
themselves and through a jack on the external power panel (108VU)
with the ground mechanic.
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ON-BOARD COMMUNICATION CONTROL AND INDICATING - FLIGHT INTERPHONE

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ON-BOARD COMMUNICATION CONTROL AND
INDICATING (continued)
AMU
The heart of the audio system is the Audio Management Unit (AMU).
It routes the signals generated by the crew and directs the signals to
and from the appropriate radio or interphone system.
The AMU has a decoding unit called Selective Calling (SELCAL).
It lets aural and visual indications on the ACP with an amber CALL
indication to alert the flight crew for calls from ground stations. When
the PA function is used from cockpit the audio signal is routed via
the AMU to the CIDS director and from the director to the Decoder
Encoder Units (DEUs) for distribution in the cabin.
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ON-BOARD COMMUNICATION CONTROL AND INDICATING - AMU

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ON-BOARD COMMUNICATION CONTROL AND
INDICATING (continued)
CALLS PANEL
The CALL panel lets the cockpit crew gain the attention of a ground
mechanic or the cabin crew by triggering visual and audio signals.
For mechanic call the horn will sound, for cabin crew a high low
chime will be broadcast on respective areas.
The EVAC panel is located on the overhead panel in the cockpit. It
allows the evacuation command to be activated from the cockpit only
or from the cockpit and the purser station.
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ON-BOARD COMMUNICATION CONTROL AND INDICATING - CALLS PANEL

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COMPONENT LOCATION
Several peripherals and acoustic equipment are installed in the cockpit.
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COMPONENT LOCATION

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COMPONENT LOCATION (continued)
ANTENNAS
All the antennae are located on the outer skin of the aircraft except
the HF antenna located behind the leading edge of the vertical
stabilizer.
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COMPONENT LOCATION - ANTENNAS

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23 COMMUNICATIONS SYSTEM PRESENTATION (1)

COMPONENT LOCATION (continued)
TRANSCEIVERS, AMU, SELCAL CODE PANEL
The SELCAL panel, AMU, HF and VHF Line Replaceable Units
(LRUs) are located in the aft avionics compartment.
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COMPONENT LOCATION - TRANSCEIVERS, AMU, SELCAL CODE PANEL

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COMPONENT LOCATION (continued)
SATCOM (OPTION)
The SATellite COMmunication system (SATCOM) is composed of
the Satellite Data Unit (SDU),
The SATCOM is a multi channel aviation satellite communication
system. It supplies worldwide mobile radio communications that can
handle voice and Data. The SDU is located in the aft avionics rack
80VU. The function is selected through the ACP.
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COMPONENT LOCATION - SATCOM (OPTION)

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SOLID STATE COCKPIT VOICE RECORDER-SSCVR
The cockpit voice recorder records the last 2 hours of the flight crew
conversations and communications and aural warnings. It records
automatically in flight and on ground when at least 1 engine is running
and for 5 minutes after the last engine is shut down and also 5 minutes
after aircraft energization.

SSCVR CONTROL AND INDICATING

The Cockpit Voice Recorder (CVR) control panel gives CVR controls
for manual erasure and test of the recording.
The CVR microphone is located at the bottom of the overhead panel.
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SOLID STATE COCKPIT VOICE RECORDER-SSCVR & SSCVR CONTROL AND INDICATING

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SSCVR COMPONENT LOCATION
The CVR is located in the rear fuselage.
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SSCVR COMPONENT LOCATION

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MAINTENANCE/TEST FACILITIES
All the communication sub-systems can be tested through the MCDU
except the CVR system.
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MAINTENANCE/TEST FACILITIES

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23 COMMUNICATIONS SYSTEM PRESENTATION (1)

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 persons and/or damage to aircraft. Here is an
overview of main safety precautions related to the communications
system.
Make sure that all circuits in maintenance are isolated before you apply
electrical power to the aircraft. Unwanted electrical power can be
dangerous.
Although the HF antenna is mounted under the leading edge of the vertical
stabilizer, the RF energy generated during transmissions can cause an
explosion during refueling. DO NOT TRANSMIT during refueling.
When working on the aircraft make sure that you focus on the tasks.
Interruptions can lead to errors. These errors can lead to an accident. To
avoid these interruptions it is prudent to advise the flight crew, ground
crew and cabin crew of your progress. This will relieve anxiety of the
passengers, and crew members. They will not interrupt you as often,
leaving you the time to focus on your tasks.
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SAFETY PRECAUTIONS

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GENERAL
The Cabin Intercommunication Data System (CIDS) is used for the control
and management of all the cabin systems presented in the graphic.
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GENERAL

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CABIN INTERCOMMUNICATION DATA SYSTEM
The CIDS includes two directors, a touch-screen Flight Attendant Panel
(FAP), and the DEUs. The touch screen FAP controls and indicates the
status of the CIDS. Integrated within the FAP are Cabin Assignment
Module (CAM), On Board Replaceable Module (OBRM) and Prerecorded
Announcement and Music (PRAM) in flash card format.
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CABIN INTERCOMMUNICATION DATA SYSTEM

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PASSENGER ENTERTAINMENT AND SIGNS
"No smoking" and "fasten seat belt" signs are controlled from the cockpit.
The FAP audio page provides controls and displays for the Pre-Recorded
Announcement And Boarding Music (PRAM). The PRAM can be a flash
card type, directly plugged into the FAP. An audio cassette/compact disc
audio reproducer can also be installed.
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PASSENGER ENTERTAINMENT AND SIGNS

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EVACUATION COMMAND SYSTEM
The emergency evacuation command may be activated from the cockpit,
from the purser station, and optionally from the Additional Attendant
Panel (AAP).
The EVAC signal can be reset from cockpit, FAP, AAP.
On the FAP, EVAC CMD and EVAC RESET P/Bs are located on the
hard key panel to be available at any time irregardless of the FAP page
presented.
On the EVAC panel located in the cockpit, the CAPT/CAPT & PURS
selector switch, selects who is able to activate an EVAC ALERT.
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EVACUATION COMMAND SYSTEM

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EVACUATION COMMAND SYSTEM

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23 CIDS SYSTEM PRESENTATION (1)

AIRCRAFT DATA MANAGEMENT
In the CIDS, the FAP displays the current cabin status on the CABIN
STATUS page. The CIDS and related cabin systems are controlled and
monitored from the FAP by its associated page.
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AIRCRAFT DATA MANAGEMENT

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CONTROL AND INDICATING
In this topic are described the purser station, the cabin crew station, and
the area call panel.
PURSER STATION
The purser station is equipped with the FAP.
In the CIDS system, the functions are ensured by:
- the FAP for monitoring, control and testing,
- the MCDU for testing interface.
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CONTROL AND INDICATING - PURSER STATION

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CONTROL AND INDICATING (continued)
CABIN CREW STATION
Each crew station is equipped with:
- a handset,
- an Additional Attendant Panel (AAP),
- an Attendant Indication Panel (AIP),
- a switch panel, installed adjacent to the middle RH (A321) and exit
RH (A318/319/320) attendant station.
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CONTROL AND INDICATING - CABIN CREW STATION

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CONTROL AND INDICATING (continued)
AREA CALL PANEL
The Area Call Panel (ACP) indicates:
- crew calls (pink steady or flashing),
- passenger call (blue steady),
- lavatory call (amber steady),
- lavatory smoke detection (amber flashing).
The ACPs are installed in the cabin ceiling at both ends of the
passenger compartment.
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CONTROL AND INDICATING - AREA CALL PANEL

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COMPONENT LOCATION
CIDS DIRECTORS
The main components of the CIDS are the directors. Director 1 is
active and director 2 is in hot standby, in normal operation.
In addition to the functions already listed, the directors manage the
Vacuum System Control (VSC) function and the Smoke Detection
Function (SDF).
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COMPONENT LOCATION - CIDS DIRECTORS

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COMPONENT LOCATION (continued)
PASSENGER ENTERTAINMENT SYSTEM
The passenger entertainment system is composed of the audio
reproducer, the Digital Interface Unit (DIU) and the main multiplexer.
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COMPONENT LOCATION - PASSENGER ENTERTAINMENT SYSTEM

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COMPONENT LOCATION (continued)
DECODER/ENCODER UNITS
DEUs type A and B are located behind the ceiling panels. The number
of DEUs installed depends on fuselage length and configuration of
passenger entertainment systems. On the A321 for example, up to 32
DEU-A and 8 DEU-B may be installed. DEUs type A are not
interchangeable with DEUs type B.
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COMPONENT LOCATION - DECODER/ENCODER UNITS

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MAINTENANCE/TEST FACILITIES
The CFDS CIDS MENU page is accessible from the MCDU and from
the FAP.
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MAINTENANCE/TEST FACILITIES

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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 persons and/or damage to aircraft. Here is an
overview of main safety precautions relative to the CIDS system.
Make sure that all circuits in maintenance are isolated before you apply
electrical power to the aircraft. Unwanted electrical power can be
dangerous.

NOTE: Note: You must be careful when you open the panels 2000VU
or 2001VU as these are in a high voltage area.
Make sure that the warning notices are in position.
When you finish the work make sure that the work area is clean and clear
of tools and other items.
Do not touch the lamp glass with your fingers. The oils from your skin
will quickly cause deterioration of the lamp. If you accidentally touch
the lamp glass, clean it with a lint-free cloth.
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33 LIGHTS SYSTEM PRESENTATION (1)

GENERAL
The lighting system includes:
- cockpit lighting,
- cabin lighting and signs,
- emergency lighting,
- cargo and service compartment lighting,
- exterior lighting.
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COCKPIT LIGHTS SYSTEM
The cockpit lighting system include:
- panel and instrument lighting,
- general cockpit lighting (dome light),
- ambient lighting.
COCKPIT LIGHTS CONTROL
The cockpit panels and instrument lighting controls are located:
- on three different panels,
- and underneath the glareshield.
The Captain and First Officer reading lights contain a potentiometer
for brightness control and a slider for beam control.
The internal light panel contains the controls for the overhead panel
integral lighting, standby compass integral light, the dome lights, and
the annunciator lights.
Two potentiometers underneath the glareshield control the integral
lighting of the glareshield and Flight Control Unit (FCU) displays.
The FLOOD LT potentiometers control the flood lights of their
respective areas and the INTEG LT potentiometer, the main panel
and pedestal lighting.
The side console light controls are on panels located on the left and
right sides of the main instrument panel.
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COCKPIT LIGHTS SYSTEM - COCKPIT LIGHTS CONTROL

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COCKPIT LIGHTS SYSTEM (continued)
COCKPIT LIGHTS
The ambient lighting is supplied by:
- two reading lights installed on each side of the upper part of the
overhead panel. Each reading light potentiometer controls the
brightness of the corresponding supplementary reading light.
- Side console lights bring light to:
- the side consoles,
- briefcase areas,
- the floor around the pilot seats.
- Two map lights are also installed, one on each side of the cockpit.
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COCKPIT LIGHTS SYSTEM - COCKPIT LIGHTS

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CABIN LIGHTS
CABIN LIGHTS THROUGH CIDS
Various cabin light and sign systems are controlled, tested, and
monitored by the Cabin Intercommunication Data System (CIDS).
The CIDS includes two directors, the Flight Attendant Panel (FAP),
and the DEUs. The touch screen FAP controls and indicates the status
of the CIDS. Integrated within the FAP are Cabin Assignment Module
(CAM), On Board Replaceable Module (OBRM) and Prerecorded
Announcement and Music (PRAM) in flash card format.
The director communicates through Decoder Encoder Units (DEUs)
with the cabin, passenger and crew systems.
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CABIN LIGHTS - CABIN LIGHTS THROUGH CIDS

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CABIN LIGHTS (continued)
CABIN LIGHTS AND SIGNS
The CIDS controls and monitors the cabin lights through the FAP.
The CIDS also controls:
- the passenger lighted signs,
- the passenger reading lights,
- the passenger calls.
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CABIN LIGHTS - CABIN LIGHTS AND SIGNS

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CABIN LIGHTS (continued)
PURSER STATION
The FAP is located at the purser station. The FAP display structure
is made of different pages related to the different systems connected
to the CIDS.
The FAP is used for monitoring, control and testing. The MCDU
provides a testing interface.
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CABIN LIGHTS - PURSER STATION

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EMERGENCY LIGHTS
Emergency lights are installed in the cabin and on the exterior fuselage
for overwing emergency exits.
The cabin emergency lights are lamps located on the cabin ceiling panels.
In order to provide sufficient lighting of the aisle, exits and emergency
exits, lights are installed on the left aisle seats and near the passenger
doors and wing exits.
The exterior emergency lights come on automatically whenever the escape
slide is deployed. The lights are supplied from the cabin emergency power
supply units.
CONTROL AND INDICATING
The emergency-lighting system can be controlled by the control switch
EMER EXIT LT installed on the overhead cockpit control panel.
The red EMERgency pushbutton has the same function as the cockpit
EMER EXIT LT switch in the ON position.
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EMERGENCY LIGHTS (continued)
COMPONENT LOCATION
Emergency lights in the cabin include EMERGENCY EXIT signs,
Ceiling EMERGENCY lights, ESCAPE PATH lighting, The
emergency lights are supplied by several Emergency Power Supply
Units (EPSUs).
Housed in the fuselage, there are 4 exterior emergency lights. These
lights are automatically activated when an overwing emergency exit
door is opened in the armed configuration. The lights come on all
along the escape route leading to the aft wing slide. Each escape slide
has integrated lighting strips.
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CARGO AND SERVICE COMPARTMENT LIGHTS
The graphic shows the different cargo and avionics compartment lights.
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CARGO AND SERVICE COMPARTMENT LIGHTS

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33 LIGHTS SYSTEM PRESENTATION (1)

EXTERIOR LIGHTS
CONTROLS
The controls for all external lights are on the EXT LT panel located
on the overhead panel.
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EXTERIOR LIGHTS (continued)
COMPONENT LOCATION
The exterior lighting system include:
- taxi, turn off lights,
- navigation, strobe, beacon, wing lights,
- take off and landing lights.
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MAINTENANCE/TEST FACILITIES
The CIDS related lights system can be monitored and tested via the
MCDU.
The CIDS BITE is accessible from the MCDU through the Centralized
Fault Display Interface Unit (CFDIU) or from the FAP, like it is possible
on the MCDU in the cockpit. This page is protected by a password.
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MAINTENANCE/TEST FACILITIES

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Do not touch the strobe lights for at least 5 minutes after operation. The
SAFETY PRECAUTIONS strobe light will still be hot. Use gloves when removing lamps, oils from
your skin can deteriorate the life of the bulbs.
When you work on the lights system, make sure that you obey all the
Be careful if you touch the strobe light with the cover removed and the
Aircraft maintenance Manual (AMM) safety procedures. This will prevent
power on. Some components have dangerous voltages.
injury to persons and/or damage to the aircraft. Here is an overview of
main safety precautions related to the lights system.
Isolate the electrical circuits from the related equipment and the
environment to prevent injury to persons and/or aircraft damage.
Do not disconnect the electrical connections for at least two minutes after
you de-energize the electrical circuits.
When you change a lamp, do not touch the glass with your fingers. The
oils from your skin will quickly cause deterioration of the lamp. If you
accidentally touch the lamp glass, clean it with a lint-free cloth.
Do not look directly towards the lights without eyes protection. Their
intensity can be high enough to cause permanent damage to your eyes.
Make sure that there are no signs of fuel contamination in the landing
light assembly. If you find fuel contamination, no person must operate
the landing light until:
- you repair the fuel leak,
- you replace the landing light assembly.
If you do not obey this precaution, ignition of the remaining fuel in the
landing light can occur.
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Put the safety devices and the warning notices in position before you start
a task on or near:
- the flight controls,
- the flight control surfaces,
- the landing gear and the related doors,
- components that move.
Do not remove a strobe light for at least ten minutes after you de-energize
the electrical circuits. The high voltage electrical current in the capacitor
of the strobe light is dangerous.

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SAFETY PRECAUTIONS

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51 STRUCTURE PRESENTATION (1)

STRUCTURE DESIGN PRINCIPLES
Four typical principles are used in the aircraft design:
- for the fuselage, the skin is attached to the frames and stiffened by
stringers,
- for the boxes, the skins stiffened with stiffeners are attached to spars
and ribs,
- the composite parts could be monolithic or sandwich construction.
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STRUCTURE DESIGN PRINCIPLES

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STRUCTURE ATA BREAKDOWN
The structure of the aircraft is broken down as follows:
ATA 52 for the doors,
ATA 53 for the fuselage,
ATA 54 for the pylons,
ATA 55 for the stabilizers,
ATA 56 for the windows,
ATA 57 for the wings.
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STRUCTURE ATA BREAKDOWN

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DOORS
The passenger/crew doors and the emergency exit doors are of same
aluminum alloy design comprising skins, edge members, horizontal beams
and vertical frames.
There are three cargo compartment doors installed on the right side of
the fuselage. The forward and the aft cargo doors are also aluminum alloy
structures consisting of skins, edge members, corner pieces, horizontal
beams and vertical frames.
The bulk cargo door is of plug type design opening inside the fuselage.
The primary structure comprise skins, edge members and horizontal
beams both being made from aluminum alloy.
The main landing gear doors are located in the lower part of the center
fuselage.
They have:
- two main doors, hinged to the two longitudinal boxes of the keel beam,
- two hinged door,
- and two leg fairing doors.
All doors are of composite construction, including carbon fiber skins.
The nose landing gear doors have two forward doors, two aft doors and
one fixed door. The fixed door is made of aluminum alloy, theother doors
are made ofsandwich type CFRP composite
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DOORS

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FUSELAGE
Within the technical documentation the fuselage is divided into five main
parts which are also divided into sections mainly for production purpose:
- the nose forward fuselage covered by chapter 53-10-00 and containing
sections 11 and 12,
- the forward fuselage covered by chapter 53-20-00 and containing the
sections 13, or 13/14, depending on A/C model,
- the center fuselage covered by chapter 53-30-00 which is also the section
15/21,
- the rear fuselage covered by chapter 53-40-00 and containing the
sections 16, 17 and 18,
- the rear/cone fuselage covered by chapter 53-50-00 and containing the
sections 19 and the tail cone, section 19.1.
The A321, A320, A319 and A318 have the same fuselage sections. The
A321 is a stretched version of the A320 with 8 frames added FWD of
the center section and 5 frames added AFT of the center section.
The A319 is a shortened version of the A320 with 3 frames removed
FWD of the center section and 4 frames removed AFT the of the center
section.
The A318 is a shortened version of the A319 with 1.5 frames removed
FWD of the center section and 3 frames removed AFT of the center
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section.

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FUSELAGE

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PYLONS
The pylon box is the primary structure of the pylon. The secondary
structure comprises the forward, the lower and the aft fairings and the
pylon to wing center fillets.
The pylon box is an assembly of titanium alloy and steel parts which
includes spars, ribs, side panels, engine attachment, pylon to wing
attachment fittings.
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PYLONS

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STABILIZERS - HORIZONTAL STABILIZER &
ELEVATORS
The horizontal stabilizer main structure includes center joint and two
outer spar boxes.
On each side, the horizontal stabilizer also includes a leading edge, a
trailing edge structure, both being mainly made from Carbon Fiber
Reinforced Plastic (CFRP) and a tip which is made of aluminum alloy.
The elevators are basically CFRP structure including top and bottom skin
panels, ribs and front spar. The hinge and actuator fittings and the trailing
edge profile are from aluminum alloy.
The vertical stabilizer structure has:
- the main spar box,
- the leading edge,
- the tip,
- and the trailing edge.
The main box is an assembly of CFRP ribs, spars and side panels.
The vertical stabilizer structure has also:
- a leading edge made of Glass Fiber Reinforced Plastic (GFRP),
- a tip made from aluminum alloy,
- a trailing edge structure made of aluminum alloy,
- and trailing edge panels made of CFRP.
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The rudder structure has:

- two side panels made of CFRP,
- a front spar made of CFRP,
- leading edge panels made of CFRP,
- hinge and actuator fittings made of aluminum alloy,
- and the trailing edge profile made of aluminum alloy.

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STABILIZERS - HORIZONTAL STABILIZER & ELEVATORS

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WINDOWS
The ATA 56 chapter describes the cockpit, cabin and door windows.
The cockpit windows include the windshield, the sliding windows and
the side fixed windows.
The cabin windows include an inner and an outer pane installed in a seal.
This assembly is installed in the window frame from inside the fuselage
and held in position by a retainer ring
The door windows are of the same design principle as for the cabin
windows.
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WINDOWS

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WINGS FIXED PARTITION
The wings consist in a center wing box which is installed in the center
fuselage section and which provides the cantilever attachment of the outer
wings. The center wing box is an assembly of aluminum alloy parts,
located between frames 36 and 42. Each outer wing has a main box (outer
wing box), which is the main load carrying structure. The main box
supports a fixed leading edge structure, a fixed trailing edge structure
and a wing tip.
The fixed leading edge structure has leading edge ribs, attached to the
main box front spar, and which support the "D-nose" structure.
The fixed trailing edge structure includes hinge fittings and actuator
fittings for the movable surfaces, and intermediate ribs. The access panels
are made of CFRP.
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WINGS FIXED PARTITION

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WINGS MOVABLE SURFACE
Each outer wing is fitted with:
- five slats made of aluminum alloy,
- an inboard flap and an outboard flap with a CFRP structure and a
sandwich aluminum trailing edge structure,
- five CFRP spoilers,
- and one aileron, mainly made from CFRP.
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WINGS MOVABLE SURFACE

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51 STRUCTURE PRESENTATION (1)

COMPOSITE APPLICATIONS
The illustration shows the main application of composite materials on
A320 (same materials for other aircrafts).
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COMPOSITE APPLICATIONS

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29 HYDRAULIC POWER SYSTEM PRESENTATION (1)

Blue and yellow pumps are interchangeable.
SYSTEM INTRODUCTION In an emergency, the blue system can be pressurized by the Ram Air
Turbine (RAT).
The aircraft has three independent hydraulic systems:
The RAT is deployed automatically or manually. It pressurizes the blue
- green,
hydraulic system at 2500 psi. It can be retracted on ground only, following
- yellow,
a specific maintenance procedure.
- blue.
The three hydraulic systems supply hydraulic power at 3000 psi to the
users:
- flight controls,
- landing gear,
- brakes,
- nose wheel steering,
- cargo doors,
- thrust reverser operation,
- Constant Speed Motor / Generator (CSM/G).
Hydraulic fluid cannot be transferred from one system to another.
A reservoir in each hydraulic system is pressurized with air to prevent
cavitation.
The green and yellow hydraulic systems are each pressurized by an Engine
Driven Pump (EDP) 1 and 2.
The yellow hydraulic system can also be pressurized by an electric pump.
It is mainly used on ground for maintenance and cargo door operation.
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If no electric power is available, a hand pump in the yellow system can

be used to operate the cargo doors.
A Power Transfer Unit (PTU) enables the green system to be pressurized
by the yellow system and vice versa. It transfers the hydraulic power but
does not transfer the hydraulic fluid.
Fire shut-off valves are located between the reservoirs and the EDPs.
They isolate the systems in case of an engine fire.
The blue hydraulic system is pressurized by an electric pump.
The electric pump is the main pump for the blue system.
It starts running at first engine start or it can be manually activated on
ground for maintenance purpose.
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SYSTEM INTRODUCTION

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29 HYDRAULIC POWER SYSTEM PRESENTATION (1)

ECAM HYDRAULIC PAGE
The items displayed on the ECAM hydraulic page are:
- reservoirs,
- fire shut-off valves,
- pumps,
- RAT,
- PTU,
- pressure indications.
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ECAM HYDRAULIC PAGE

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PANEL LOCATION
On the ENG FIRE panel (20VU), the fire shut-off valve pushbuttons
ENG 1 (2) released out will close the fire shut-off valves.
The EDPs, electric pumps, PTU and the RAT are operated from the HYD
control panel and monitored on the HYD ECAM page.
The blue electric pump can also be operated on ground for maintenance
purpose by the BLUE PUMP OVRD push button on the HYD
maintenance panel.
The hydraulic leak measurement system is used for maintenance purpose
only.
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PANEL LOCATION

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COMPONENT LOCATION
PTU/ELEC PUMPS/RAT
The PTU is located in the main landing gear bay. The blue electric
pump and the RAT are located in the blue hydraulic bay and the yellow
electric pump is located in the yellow hydraulic bay.
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COMPONENT LOCATION - PTU/ELEC PUMPS/RAT

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COMPONENT LOCATION (continued)
ENGINE PUMP
The EDPs 1 and 2 are located on the accessory gearbox of engine 1
(EDP 1 green system) and engine 2 (EDP 2 yellow system).
RESERVOIR
The green reservoir is located inside the main landing gear bay. The
blue reservoir is located aft of the main landing gear bay on the LH
side. The yellow reservoir is located inside the yellow hydraulic bay.
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COMPONENT LOCATION - ENGINE PUMP & RESERVOIR

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COMPONENT LOCATION (continued)
SERVICING PANELS
The hydraulic servicing panels are located aft of the main landing
gear bay; the green and the blue panels on the LH side, and the yellow
panel on the RH side.
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COMPONENT LOCATION - SERVICING PANELS

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29 HYDRAULIC POWER SYSTEM PRESENTATION (1)

SAFETY PRECAUTIONS
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. Her is an overview of main safety precautions relative to the
Hydraulic Power System.
Make sure that the hydraulic system you work on is isolated before you
pressurize the other hydraulic systems.
Make sure that the travel ranges of the flight controls are clear. Movement
of the flight controls can cause injury to persons and/or damage to the
aircraft.
Do not get hydraulic fluid or hot gas from hydraulic reservoir on your
body. Use protective clothing to prevent risk of poisoning and burns. Use
solvents, cleaning agents, sealants and other special materials in a
ventilated area. To prevent inadvertent breathing or contact with your
body, use applicable gloves, eye protections and face mask.
Install safety devices and warning before working on or near landing
gear and related doors.
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SAFETY PRECAUTIONS

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29 HYDRAULIC POWER SYSTEM PRESENTATION (1)

SAFETY PRECAUTIONS (continued)
RAT
Activation of the RAT MAN ON switch on the ground or in flight
will extend the RAT. Install the safety device when you work near
the RAT.
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SAFETY PRECAUTIONS - RAT

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29 HYDRAULIC POWER SYSTEM PRESENTATION (1)

ENVIRONMENTAL PRECAUTIONS
Do not discharge products such as oil, fuel, solvent, lubricant either in
trash bins, soil or into the water network (drains, gutters, rain water, waste
water, etc...).
Sort waste fluids and use specific waste disposal containers.
Each product must be stored in an appropriate and specific cabinet or
room such as a fire-resistant and sealed cupboard.
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ENVIRONMENTAL PRECAUTIONS

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32 LANDING GEAR PRESENTATION (1)

LANDING GEAR
The A320 aircraft family has a LH and RH dual wheel Main Landing
Gear (MLG) and a dual wheel Nose Landing Gear (NLG).
The MLG retracts inboard into the MLG wheel well and the NLG retracts
forward into the NLG wheel well. The Landing Gears (L/Gs) are
hydraulically operated and electrically controlled. Each L/G has
hydraulically and mechanically operated doors. Each L/G has a shock
absorber.
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LANDING GEAR

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32 LANDING GEAR PRESENTATION (1)

LANDING GEAR (continued)
LANDING GEAR DOORS
Doors are hydraulically operated and electrically controlled.
The mechanically operated doors are linked to the L/G struts and
moves with the gear.
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LANDING GEAR - LANDING GEAR DOORS

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32 LANDING GEAR PRESENTATION (1)

LANDING GEAR (continued)
WHEELS AND BRAKES
The MLG have:
- wheels,
- carbon brakes,
- brake fans (optional),
- Tire Pressure Indicating System (TPIS) sensor (optional),
- gear jacking pad for wheel change.
The NLG has:
- a Nose Wheel Steering (N/WS) system,
- a jacking pad for wheel change,
- a TPIS sensor (optional).
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LANDING GEAR - WHEELS AND BRAKES

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32 LANDING GEAR PRESENTATION (1)

LANDING GEAR EXTENSION AND RETRACTION
The L/G extension and retraction is controlled from the L/G control lever
located in the cockpit.
The gear up and down sequence is controlled by two computers called
Landing Gear Control and Interface Unit (LGCIU) 1 and 2. Only one
LGCIU is in command while the other LGCIU is in standby. With any
up selection the LGCIU in command will change and control a complete
gear cycle.
The gear up and down position and the door close and open position are
monitored by proximity detectors.
In case of failure of a LGCIU or a proximity detector, the other LGCIU
will be in command.
An interlock mechanism prevents unsafe retraction by locking the control
lever in the down position when any shock absorber is not extended.
The Nose Wheel (N/W) is automatically centered when the shock absorber
is extended.
The L/G is powered by the green hydraulic system. At high air speed a
safety valve cuts hydraulic supply to the L/G system.
In case of failure, the gear can be extended mechanically from the cockpit
by means of a free fall extension handle. During free fall extension, a
cut-out valve will close to cut the L/G hydraulic supply.
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LANDING GEAR EXTENSION AND RETRACTION

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32 LANDING GEAR PRESENTATION (1)

Depending on the deceleration rate and the A/SKID regulation, the
BRAKING BSCU regulates the pressure delivered to each brake trough the normal
servo valves.
There are two braking modes:
When the aircraft deceleration reaches a given value, the DECELerate
- normal braking,
green light on the L/G panel comes on.
- alternate braking.
In order to stop the MLG wheels rotation before entry into the L/G
The normal braking system is powered by the green hydraulic system.
bay, a programmed brake pressure is sent to the normal brakes during
The alternate brake system is powered by the yellow hydraulic system
gear retraction.
and backed up by a brake accumulator.
Optionally, the N/Ws are mechanically braked at the end of the gear
All braking functions are controlled by the Braking/Steering Control Unit
cycle using brake bands.
(BSCU).
When there is no braking order, the servo valve is fully closed.
These functions are:
- normal and alternate braking, ALTERNATE BRAKING
- Anti-Skid (A/SKID) control, The alternate brake system is powered by the yellow hydraulic system
- auto braking, and backed up by a brake accumulator.
- brake temperature indication. The alternate braking with A/SKID or without A/SKID is electrically
NORMAL BRAKING controlled by the Alternate Braking Control Unit (ABCU); but the
BSCU supplies the A/SKID orders to the ABCU.
In manual normal braking, electrical braking orders are sent by the
The ABCU becomes active when the normal brake system is faulty
brake pedals to the BSCU. The BSCU energizes the normal brake
and/or low hydraulic pressure in the green system. The information
selector valve allowing green pressure to supply the brakes trough the
comes from the BSCU.
automatic selector and normal servo valves.
Braking inputs are given by the brake pedals and transmitted through
Depending on manual braking orders and A/SKID regulation, the
the Alternate Brake Pedal Transmitter Unit to the ABCU which will
BSCU regulates the pressure delivered to each brake through the
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control the braking pressure.

normal servo valves.
The braking data are sent to the BSCU for calculating the A/SKID
Wheel rotating speed from the tachometer, aircraft speed data and
protection.
braking pressure are supplied to the BSCU for braking and A/SKID
The braking pressure is read on the triple indicator.
computation.
The A/SKID regulation is disconnected, either electrically by setting
Before landing, the crew can select one of the auto brake modes
OFF the A/SKID & N/W STeeRinG switch, BSCU failure or hydraulic
MAXimum, MEDium or LOw, to obtain the optimal deceleration rate
low pressure in the green and yellow hydraulic system (brakes being
compatible with the length of the runway.
supplied by the brake accumulator only).
Before take-off, MAXimum mode must be selected in case of an
The pilot must refer to the triple pressure indicator to limit brake
aborted take-off.
pressure in order to avoid locking a wheel. Nevertheless in that case
Braking starts when the ground spoilers deploy.
the brake pressure is limited to max 1000PSI by the ABCU.
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With the accumulator pressure only, a maximum of 7 full brake pedal
applications can be done.
PARKING BRAKE
The parking brake system is supplied either by the yellow hydraulic
pressure or by the brake accumulator. When the parking brake is set,
the brakes are supplied by the yellow system pressure or by the brake
accumulator through the shuttle valve.
Putting ON the parking brake, the other braking modes and the
A/SKID system are deactivated.
With the parking brake handle in ON position, the parking brake
control valve is open and the yellow pressure goes through the parking
brake control valve, reaching the dual shuttle valves. The BSCU and
ABCU will deactivate the other braking modes.
The pressure delivered to the LH and RH brakes as well as the brake
accumulator pressure are indicated on the triple pressure indicator.
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BRAKING - NORMAL BRAKING ... PARKING BRAKE

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32 LANDING GEAR PRESENTATION (1)

STEERING
The steering system uses the yellow hydraulic system to operate a steering
actuating cylinder, which changes the direction of the NLG wheels.
The steering system is controlled by the BSCU, which receives order
from:
- the steering hand wheels (orders added algebraically),
- the rudder pedals,
- the autopilot.
The BSCU transforms the orders into N/WS angle. That angle has the
following limits:
- Ruder pedals: max 6 degrees,
- Hand wheels: max 74 degrees.
The steering system receives hydraulic pressure in the following
conditions:
- A/SKID & N/W STeeRinG switch in ON,
- towing control lever in normal position,
- at least one ENG MASTER switch ON,
- aircraft is on ground.
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STEERING

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32 LANDING GEAR PRESENTATION (1)

CONTROL AND INDICATING
This section will highlight the control panels and indications for the
landing gear system.
LANDING GEAR / BRAKES CONTROL AND
INDICATING
Cockpit panel location:
- L/G control lever,
- L/G gravity extension handle,
- L/G panel which includes:
- L/G position indication panel,
- auto brake mode selection panel,
- brake fan indication/selection panel, and
- A/SKID & N/W STeeRinG selector.
- ECAM WHEEL page.
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CONTROL AND INDICATING - LANDING GEAR / BRAKES CONTROL AND INDICATING

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32 LANDING GEAR PRESENTATION (1)

CONTROL AND INDICATING (continued)
INDICATOR, PARKING BRAKE HANDLE, RUDDER
PEDALS
Cockpit panel location:
- triple pressure indicator for brake accumulator pressure and
alternate/parking brake pressure,
- parking brake selector,
- rudder/brake pedals.
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CONTROL AND INDICATING - INDICATOR, PARKING BRAKE HANDLE, RUDDER PEDALS

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32 LANDING GEAR PRESENTATION (1)

CONTROL AND INDICATING (continued)
NOSE WHEEL STEERING
N/WS control:
- rudder/steering pedals,
- N/WS hand wheels.
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CONTROL AND INDICATING - NOSE WHEEL STEERING

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32 LANDING GEAR PRESENTATION (1)

COMPONENT LOCATION
The L/G computers are located in the forward avionics bay.
Note that the Tire Pressure Indication Unit (TPIU) is an option.
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COMPONENT LOCATION

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32 LANDING GEAR PRESENTATION (1)

SAFETY PRECAUTIONS
When you work on the L/G system, 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 L/G system.
When you perform any maintenance task, make sure that all circuits are
isolated. Unwanted electrical or hydraulic power can be dangerous.
Make sure that the L/G ground safety locks are installed.
Let the brakes and the wheels become cool before you go near the L/G.
Do not apply a liquid or gas fire extinguisher directly on a hot wheel or
brake unit. This could cause an explosion.
Use only nitrogen for tire inflation. If the brakes overheat, other gases
can cause an explosion.
During L/G servicing, do not let high pressure gas get in contact with
your skin. Gas bubbles in your blood can kill you.
Make sure that the controls agree with the position of the items they
operate before you pressurize a hydraulic system.
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SAFETY PRECAUTIONS

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27 FLIGHT CONTROLS PRESENTATION (1)

Roll orders and speed brake orders are added with priority given to
INTRODUCTION the roll function.
All flight control surfaces are made of composite materials except for GROUND SPOILERS
the slats which are made of aluminum alloy. The ground spoiler function is used to destroy the lift during landing
All flight control surfaces are electrically controlled and hydraulically and in case of aborted take-off. All spoiler panels are used.
operated.
As a back-up, the stabilizer and rudder is mechanically controlled and HIGH LIFT
hydraulically operated. The high lift function is achieved by slats and flaps.
Pilots use side sticks to fly the aircraft in pitch and roll. There are two flaps, inboard and outboard, and five slats on each wing,
numbered from wing root to wing tip.
FLIGHT CONTROL SURFACES The A321 is equipped with double slotted flaps.
The control is achieved through the following conventional surfaces. AILERON DROOP
PITCH The aileron droop function increases the lift on the part of the wing
Pitch control is achieved by two elevators and the Trimmable which is not equipped which flaps.
Horizontal Stabilizer (THS). The ailerons are deflected downwards when the flaps are extended.
Elevators are used for short-term activity.
The THS is used for long-term activity.
ROLL
Roll control is achieved by one aileron and spoilers 2 to 5 on each
wing, numbered from wing root to wing tip.
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YAW
Yaw control is fulfilled by the rudder.
The rudder is used during cross wind take-off and landing, and in case
of engine failure (thrust asymmetry).
The yaw damper function controls the rudder for Dutch roll damping
and turn coordination.
SPEED BRAKES
The speed brake function is used in flight to increase the aircraft drag.
Spoilers 2 to 4 are used.

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INTRODUCTION & FLIGHT CONTROL SURFACES

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The rudder trim RESET switch resets the trim position to zero.
CONTROLS The rudder trim indicator displays rudder trim position in degrees.
All the controls for the flight controls are located in the cockpit. FLAP CONTROL LEVER
SIDE STICK The flap control lever selects simultaneous operation of slat and flap.
It has five positions.
The two side sticks are used for manual pitch and roll control.
They are spring loaded to neutral position.
Each side stick has a push button used for autopilot disconnection and
to take priority over the other side stick.
SPEED BRAKE LEVER
The speed brake lever controls the position of the speed brake surfaces
and pre selection of the ground spoiler function.
For the speed brake function, the lever has to be pushed down and
placed in the required position.
To arm the ground spoilers for automatic extension, the lever must
be pulled UP when in the retracted position.
THS CONTROL
The THS is automatically trimmed during flight.
After touch down, the THS is automatically trimmed to neutral
position.
The THS mechanical control is used to set the pitch trim before
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take-off or when the automatic pitch trim is not available.

Trim position is indicated in degrees on a scale adjacent to each trim
wheel.
RUDDER PEDALS
Two sets of pedals enable the rudder mechanical control.
The pedals can be individually adjusted.
RUDDER TRIM
The rudder trim control switch operates the electrical trim actuator to
move the rudder to a new neutral position.

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CONTROLS - SIDE STICK ... FLAP CONTROL LEVER

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INDICATING
All the indications for the flight controls are located in the cockpit.
FLIGHT CONTROL PANELS
The computer push buttons are used to energize, de-energize and reset
the flight control computers.
FAULT or OFF can be indicated.
SIDE STICK PRIORITY LIGHTS
The side stick priority lights in front of each pilot, indicate who has
taken and who has lost priority.
ECAM PAGES
The flight control system uses three ECAM pages:
- Flight control ECAM page for primary surface indication,
- WHEEL ECAM page for ground spoiler indication,
- Engine/Warning Display for slat/flap indication.
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INDICATING - FLIGHT CONTROL PANELS ... ECAM PAGES

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FLY BY WIRE PRINCIPLE
The pilots use the side sticks to fly the aircraft in pitch and roll (and in
yaw indirectly through turn coordination).
Computers interpret the pilot's inputs and move the flight control surfaces
to follow their orders.
However, regardless of the pilot's inputs, the computer prevents:
- excessive maneuvers,
- flight outside the safe flight envelope.
Autopilot commands are given directly to the computers.
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FLY BY WIRE PRINCIPLE

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FLIGHT CONTROLS ARCHITECTURE
A computer arrangement permanently controls and monitors the flight
control surfaces, it also records and stores faults.
This arrangement includes:
- 2 Elevator Aileron Computers (ELAC) for pitch and roll control,
- 3 Spoiler Elevator Computers (SEC) for pitch and roll control,
- 2 Flight Augmentation Computers (FAC) for yaw control,
- 2 Flight Control Data Concentrators (FCDC) for indication and
maintenance tests,
- 2 Flight Management Guidance Computer (FMGC) for autopilot
commands,
- 2 Slat Flap Control Computers (SFCC) for slat and flap control.
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FLIGHT CONTROLS ARCHITECTURE

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SURFACES
All the flight control surfaces are hydraulically operated by actuators
which receive electrical signals from the computers. The rudder and the
Trimmable Horizontal Stabilizer (THS) can also be mechanically
controlled.
ACTUATORS
All the actuators are hydraulically powered by one of the three
hydraulic circuits, except the rudder trim actuator, the rudder travel
limitation actuator and the THS servo-motors which are electrically
driven.
COMPUTERS
The relationship between actuators and computers is indicated on the
schematic. The left or right elevator actuators are connected to two
computers, one ELevator Aileron Computer (ELAC) and one Spoiler
Elevator Computer (SEC).
ACTIVE SERVO CONTROLS
There are two servo controls for each aileron, for each elevator and
for the yaw damping function. In normal configuration, one servo
control actuates the surface. It is called active servo control. The
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second, which follows the surface deflection, is in damping mode.

When only the mechanical control of the pitch trim is available (all
computers inop), the centering mode is applied to the elevators. The
actuators are hydraulically maintained in neutral position.
RECONFIGURATION PRIORITIES
In normal configuration, the following computers ensure the servoloop
control. The arrows indicate the actuation reconfiguration priorities
in case of computer failure or loss of hydraulic circuits.

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SURFACES - ACTUATORS ... RECONFIGURATION PRIORITIES

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FLIGHT CONTROL LAWS
The Electrical Flight Control System (EFCS) computers convert pilot
inputs into aircraft control objectives.
The computers calculate the control laws that are used to compute the
surface deflections.
The system has a high degree of redundancy and it will reconfigure itself
when failures occur.
NORMAL LAW
In normal condition, the normal law is used to compute the surface
deflection orders.
Normal laws provide full flight phase envelope protection. This means
that the aircraft will be protected from excessive maneuvers during
all flight phases.
ALTERNATE LAW
The alternate law is automatically introduced as soon as the normal
law is lost due to system failures.
The alternate law gives reduced protection.
DIRECT LAW
The direct law is automatically introduced when further failures occur.
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In direct law all protections are lost. There is a direct relationship

between the side stick orders and the surface.
The direct law is automatically activated on ground.

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FLIGHT CONTROL LAWS - NORMAL LAW ... DIRECT LAW

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MECHANICAL BACK-UP
The mechanical back-up lets the aircraft be controlled during a temporary
complete loss of electrical power or flight controls computers.
Longitudinal control is achieved using the trim wheels to control the
THS, as the elevators are kept at zero deflection.
Lateral control is achieved from the rudder pedals.
Hydraulic power is still needed to operate the surfaces of the THS and
the Rudder.
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MECHANICAL BACK-UP

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SLAT AND FLAP SYSTEM
The slats and flaps are electrically controlled and hydraulically operated.
Two SFCCs ensure control and monitoring. Each computer has one slat
and one flap channel.
The slat and flap systems are similar.
Each system is driven by a Power Control Unit (PCU) with two hydraulic
motors coupled by a differential gearbox.
Then torque shafts and gearboxes transmit the mechanical power to the
actuators which drive the surfaces.
Each motor is powered by a different hydraulic system and has its own
valve block and Pressure Off Brake (POB).
Valve blocks control the direction of rotation and the speed of their related
PCU output shaft.
The POB locks the transmission when the slat and flap surfaces have
reached the selected position or if hydraulic power fails.
Wing Tip Brakes (WTBs) are provided in order to stop and lock the
system when major failures are detected. They are hydraulically activated
and can only be reset on ground.
Position Pick-Off Units (PPUs) send slat and flap position feedback to
the SFCCs and ECAM.
Flap sensors installed between inboard and outboard flaps inhibit further
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flap operation when a flap attachment failure is detected.

The signal is sent to the SFCCs via the Landing Gear Control and
Interface Units (LGCIU)
To prevent an aircraft stall, slats cannot be fully retracted at high angles
of attack or low speeds (Alpha/speed lock function).

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SLAT AND FLAP SYSTEM

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COMPUTERS
All the flight control computers are located in the avionics compartment.
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COMPUTERS

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ACTUATORS
The Aileron surface is powered by two servo controls.
Each Spoiler surface is powered by a single servo control.
The Flaps and Slats surfaces are powered by their dedicated PCU.
The Rudder surface is powered by 3 servo controls.
The THS is moved by one actuator.
The Elevator surface is powered by two servo controls.
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ACTUATORS

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ACTUATORS

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MAINTENANCE TEST FACILITIES
All computers in the flight control systems can be tested via the MCDU.
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MAINTENANCE TEST FACILITIES

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SAFETY PRECAUTIONS
When you work on flight controls, make sure that you obey all the AMM
safety procedures. This will prevent injury to persons and /or damage to
the aircraft.
Put safety devices and warning notices in position before you start a task
on or near flight controls.
Make sure that the controls agree with the position of the flight control
surfaces before you pressurize hydraulic system.
Make sure that the travel ranges of the flight control surfaces are clear.
Movement of flight controls can cause injury to persons and/or damage
to the aircraft.
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SAFETY PRECAUTIONS

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SAFETY PRECAUTIONS (continued)
DYNAMIC TESTS
When you perform operational tests, the flight control surfaces move.
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SAFETY PRECAUTIONS - DYNAMIC TESTS

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