Airbus A320. AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE PLANNING (2016-2023)

@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

WEATHER RADAR

EMERGENCY STATIC PROBE

AOA SENSOR(3) STBY

ATC(4)

VHF(1)

GPS(2)

AOA SENSOR(1)

VHF(3)

GPS(1)

ELT

TCAS TOP

LOC

GLIDE

RADIO ALTIMETER(2)

DME(1)

TAT PROBE

MARKER

RADIO ALTIMETER(1)

PITOT PROBE(3)

TCAS BOTTOM

VHF(2)

PITOT PROBE(1)

ATC(1)

DME(2)

STATIC PROBE(1)

STATIC PROBE(2)

VOR

EMERGENCY STATIC PROBE

ATC(3)

ADF(1)

AOA SENSOR(2)

TAT PROBE

PITOT PROBE(2)

ATC(2)

STATIC PROBE(1)

STATIC PROBE(2)

NOTE: DEPENDING ON AIRCRAFT CONFIGURATION

N_AC_021100_1_0030101_01_00

Antennas and Probes

Location

FIGURE-2-11-0-991-003-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

2-12-0

Power Plant

**ON A/C A320-200 A320neo

Auxiliary Power Unit

General

The APU is installed at the rear part of the fuselage in the tail cone. An air intake system with a

flap-type door is installed in front of the APU compartment. The exhaust gases pass overboard at the

end of the fuselage cone.

Controls and Indication

The primary APU controls and indications are installed on the overhead panel, on the center pedestal

and on the center instrument panel. Additionally, an external APU panel is installed on the nose

landing gear to initiate an APU emergency shutdown.

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

FR77

FR87

A B

Z310

FR70

UPPER

FIREWALL

FRONT

FR80

FIREWALL

FIREWALL RH

LOUVER LH

CUT OUT SEALED WITH

LABYRINTH GASKET

RH ACCESS DOOR

316AR

REAR

FIREWALL

FR84

CUT OUT SEALED WITH

LABYRINTH GASKET

AIR INTAKE FIXED

ON ACCESS DOOR

NOTE:

LH ACCESS DOOR 315AL NOT SHOWN FOR CLARITY.

N_AC_021200_1_0050101_01_01

Auxiliary Power Unit

Access Doors

FIGURE-2-12-0-991-005-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

FIRE OVERHEAT DETECTOR

APU

APU SUSPENSION

(7 RODS)

GENERATOR

FIRE EXTINGUISHING BOTTLE

BLEED AIR LINE

FR87

EXHAUST

MUFFLER

APU SUSPENSION

(7 RODS)

FR84

OIL COOLER OUTLET

AIR INTAKE DUCT

APU−FUEL−LINE

FR80

FRONT FIRE

WALL

AIR INTAKE HOUSING

FR78

FR77

DIVERTER

N_AC_021200_1_0060101_01_01

Auxiliary Power Unit

General Layout

FIGURE-2-12-0-991-006-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

Engine and Nacelle

**ON A/C A320-200

Engine and Nacelle - CFM Engine

Engine

The engine is a dual-rotor, variable stator, high bypass ratio turbo fan power plant for subsonic

services. The principal modules of the engine are:

low pressure compressor (fan stator and fan rotor)

high pressure compressor

turbine frame

combustion chamber

high pressure turbine

low pressure turbine

accessory drives (gear box).

The 9 stage high pressure compressor is driven by 1 stage high pressure turbine, and the

integrated front fan and booster is driven by 4 stage low pressure turbine. An annular combustor

converts fuel and compressor discharge air into energy to provide engine thrust part through

primary exhaust and to drive the turbines. The accessory drive system extracts energy from the

high pressure rotor to drive the engine accessories and the engine mounted aircraft accessories.

Reverse thrust for braking the aircraft after landing is supplied by an integrated system which

acts on the fan discharge airflow.

Nacelle

The cowls enclose the periphery of the engine so as to form the engine nacelle. Each engine is

housed in a nacelle suspended from a pylon attached to the wing lower surface. The nacelle

consists of the demountable powerplant, the fan cowls and the thrust reverser cowls.

The nacelle installation is designed to provide cooling and ventilation air for engine accessories

mounted along the fan and core casing. The nacelle provides:

protection for the engine and the accessories

airflow around the engine during its operation

lighting protection

HIRF and EMI attenuation.

Engine and Nacelle - IAE Engine

A. Engine

The engine is a two spool, axial flow, high bypass ratio turbofan powerplant for subsonic sevice.

The main modules of the engine are:

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

low pressure compressor (fan and booster) assembly

LP compressor/intermediate case

No. 4 bearing and combustion section

high pressure compressor

HP turbine section

LP turbine section

accessory drives (gear box).

The four stage Low Pressure Compressor (LPC) is driven by a five stage Low Pressure Turbine

(LPT) and the ten stage High Pressure Compressor (HPC) by a two stage High Pressure

Turbine (HPT). The HPT also drives a gearbox which, in turn drives the engines and aircraft

mounted accessories. The two shafts are supported by five main bearings.

The V2500 incorporates a Full Authority Digital Engine Control (FADEC) which governs all

engine functions, including power management. Reverse thrust for braking the aircraft after

landing is supplied by an integrated system which acts on the fan discharge airflow.

Nacelle

The cowls enclose the periphery of the engine so as to form the engine nacelle. Each engine is

housed in a nacelle suspended from a pylon attached below the wing.

The nacelle installation is designed to provide cooling and ventilation air for engine accessories

mounted along the fan and core casing. The nacelle provides:

protection for the engine and the accessories

airflow around the engine during its operation

lighting protection

HIRF and EMI attenuation.

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

2 943 mm

(115.87 in)

2 600 mm

(102.36 in)

1 125 mm

TURBINE

(44.28 in)

COMPRESSOR

FRAME

FAN AND BOOSTER

FWD HOISTING

COMBUSTOR

POINT

FWD

HANDLING

POINT

1 820 mm

TURBINE

(71.65 in)

AFT HANDLING

AND HANDLING

AGB

TGB

POINT

ACCESSORY

DIA 986 mm

DRIVE

(38.82 in)

2 145 mm

(84.45 in)

FWD

1 130 mm

(44.49 in)

989 mm

(38.94 in)

1 978 mm

(77.87 in)

N_AC_021200_1_0270101_01_00

Power Plant Handling

Major Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-027-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

DISTANCE FROM

0.33 m

THE NOSE

(1.1 ft)

11 m

0.93 m

1.3 m

1.2 m

(36.1 ft)

(3.1 ft)

(4.3 ft)

(3.9 ft)

PRIMARY

NOZZLE

6°

2.3 m

1.6 m

(7.5 ft)

(5.2 ft)

CENTERBODY

2.1 m

(6.9 ft)

ENGINE AIR

0.57 m

INLET COWL

FAN COWL

(1.9 ft)

FAN

REVERSER

A A

1.9 m

2.07 m

1.8 m

(6.2 ft)

(6.8 ft)

(5.9 ft)

1.2 m

(3.9 ft)

BLOCKER DOOR

EXTENDED

B B

C C

D D

N_AC_021200_1_0280101_01_00

Power Plant Handling

Major Dimensions - CFM56 Series Engine

FIGURE-2-12-0-991-028-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

3.7 m

(12.1 ft)

3.3 m

(10.8 ft)

1 m

(3.3 ft)

0.9 m

(3 ft)

1 m

35°

0.7 m

(3.3 ft)

45°

0.56 m

(2.3 ft)

(1.8 ft)

GROUND

CAUTION

DO NOT ACTUATE SLATS:

− WITH THRUST REVERSER COWLS 45° OPEN POSITION

− WITH BLOCKER DOORS OPEN AND THRUST REVERSER

COWLS AT 35° AND 45° OPEN POSITION

NOTE: APPROXIMATE DIMENSIONS

N_AC_021200_1_0300101_01_00

Power Plant Handling

Thrust Reverser Cowls - CFM56 Series Engine

FIGURE-2-12-0-991-030-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

3 101 mm

(122.1 in)

TURBINE

FRAME

TURBINE

COMBUSTOR

FAN AND BOOSTER

COMPRESSOR

TURBINE

1 715 mm

(67.5 in)

1 067 mm

(42.0 in)

ACCESSORY

DRIVE

FWD

N_AC_021200_1_0310101_01_00

Power Plant Handling

Major Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-031-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

DISTANCE FROM

THE NOSE

11.12 m

5.25 m

(36.5 ft)

(17.23 ft)

0.5°

6°

1.50 m

(4.95 ft)

5.26 m

(17.27 ft)

PPS

COMPONENT

INLET

A−A

2.01

6.58

0.99

3.25

1.10

3.63

1.41

4.62

ATTACH FLG

TORQUE BOX

B−B

2.01

6.58

1.00

3.29

1.11

3.64

2.59

8.50

"V" BLADE

COMB. CHAMBER

C−C

1.98

6.50

0.97

3.19

1.07

3.52

3.26

10.70

ENTRY FLG

COMB. CHAMBER

D−D

1.93

6.32

0.93

3.06

1.03

3.39

3.63

11.90

EXIT FLG

TECH FLG

E−E

1.64

5.38

0.78

2.57

0.86

2.83

4.60

15.10

TURB. EXIT CASE

AFT END

F−F

1.24

4.07

0.60

1.96

0.64

2.11

−−−−

CNA

N_AC_021200_1_0320101_01_00

Power Plant Handling

Major Dimensions - IAE V2500 Series Engine

FIGURE-2-12-0-991-032-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

FWD VIEW

2 m

(6.6 ft)

WL100

CLOSED

3.9 m

(12.8 ft)

WL100

FAN COWL

OPEN 50°

1.6 m

(5.2 ft)

1.2 m

(3.9 ft)

0.67 m

(2.2 ft)

GROUND

NOTE: APPROXIMATE DIMENSIONS

N_AC_021200_1_0330101_01_00

Power Plant Handling

Fan Cowls - IAE V2500 Series Engine

FIGURE-2-12-0-991-033-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

AFT VIEW

2 m

(6.6 ft)

WL100

CLOSED

3.6 m

(11.8 ft)

WL100

0.9 m

(3 ft)

THRUST REVERSER

OPEN 45°

1.1 m

(3.6 ft)

1 m

(3.3 ft)

0.67 m

(2.2 ft)

NOTE: APPROXIMATE DIMENSIONS

N_AC_021200_1_0340101_01_00

Power Plant Handling

Thrust Reverser Halves - IAE V2500 Series Engine

FIGURE-2-12-0-991-034-A01

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May 01/16

2-12-0

@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320neo

FAN COWL THRUST

NOSE COWL

REVERSER

PRIMARY

NOZZLE

PLUG

0.46 m

(1.51 ft)

0.66 m

(2.17 ft)

1.46 m

1.53 m

1.44 m

(4.79 ft)

(5.02 ft)

(4.72 ft)

FWD

2.60 m

(8.53 ft)

2.67 m

(8.76 ft)

0.46 m

(1.51 ft)

N_AC_021200_1_0460101_01_00

Power Plant Handling

Major Dimensions - PW 1100G Engine

FIGURE-2-12-0-991-046-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320neo

43°

45°

1: THRUST REVERSER

OPEN

POSITION

MIN.

MAX.

4.26 m

0.80 m

0.90 m

43°

(13.98 ft)

(2.62 ft)

(2.95 ft)

SEE AC SECTION

2−3−0

4.33 m

0.84 m

0.95 m

45°

(14.21 ft)

(2.76 ft)

(3.12 ft)

NOTE:

B AND C DEPENDING ON AIRCRAFT CONFIGURATION.

N_AC_021200_1_0480101_01_00

Power Plant Handling

Thrust Reverser Halves - PW 1100G Engine

FIGURE-2-12-0-991-048-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320neo

3548 mm

(139.68 in)

3327 mm

(130.98 in)

1352 mm

(53.23 in)

FAN AND

BOOSTER

COMPRESSOR

FWD

COMBUSTOR

HANDLING

TURBINE

POINT

FRAME

DIA 1084 mm

(42.68 in)

AGB TGB

TURBINE

ACCESSORY

DRIVE

2152 mm

(84.72 in)

FWD

2242 mm

(88.27 in)

1165 mm

(45.87 in)

1236 mm

(48.66 in)

2487 mm

(97.91 in)

N_AC_021200_1_0540101_01_00

Power Plant Handling

Major Dimensions - CFM LEAP-1A Engine

FIGURE-2-12-0-991-054-A01

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320neo

THRUST

NOSE COWL

FAN COWL

REVERSER

PRIMARY

NOZZLE

PLUG

0.98 m

(3.22 ft)

0.49 m

(1.61 ft)

0.67 m

(2.20 ft)

1.58 m

1.98 m

(5.18 ft)

(6.50 ft)

0.23 m

(0.75 ft)

FWD

2.52 m

(8.27 ft)

2.60 m

(8.53 ft)

0.46 m

(1.51 ft)

N_AC_021200_1_0550101_01_00

Power Plant Handling

Major Dimensions - CFM LEAP-1A Engine

FIGURE-2-12-0-991-055-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

2-13-0

Leveling, Symmetry and Alignment

**ON A/C A320-200 A320neo

Leveling, Symmetry and Alignment

Quick Leveling

There are three alternative procedures to level the aircraft:

Quick leveling procedure with Air Data/Inertial Reference Unit (ADIRU).

Quick leveling procedure with a spirit level in the passenger compartment.

Quick leveling procedure with a spirit level in the FWD cargo compartment.

Precise Leveling

For precise leveling, it is necessary to install sighting rods in the receptacles located under the

fuselage (points 11 and 12 for longitudinal leveling) and under the wings (points 2LH and 2RH for

lateral leveling) and use a sighting tube. With the aircraft on jacks, adjust the jacks until the

reference marks on the sighting rods are aligned in the sighting plane (aircraft level).

Symmetry and Alignment Check

Possible deformation of the aircraft is measured by photogrammetry.

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

2-14-0

Jacking

**ON A/C A320-200 A320neo

Jacking for Maintenance

Aircraft Jacking Points for Maintenance

General

(1) The A320 can be jacked:

At not more than 59 000 kg (130 073 lb),

Within the limits of the permissible wind speed when the aircraft is not in a closed

environment.

Primary Jacking Points

(1) The aircraft is provided with three primary jacking points:

One located under the forward fuselage (FR8),

Two located under the wings (one under each wing, located at the intersection of RIB9

and the datum of the rear spar).

(2) Three jack adapters are used as intermediary parts between the aircraft and the jacks:

One male spherical jack adapter of 19 mm (0.75 in) radius, forming part of the aircraft

structure (FR8),

Two wing jack pads (one attached to each wing at RIB9 with 2 bolts) for the location

of the jack adaptor.

Wing jack pads are ground equipment.

Auxiliary Jacking Points (Safety Stay)

(1) When the aircraft is on jacks, it is recommended that a safety stay be placed under the

fuselage, between FR73 and FR74, to prevent tail tipping caused by accidental

displacement of the center of gravity.

(2) The safety stay must not be used to lift the aircraft.

(3) A male spherical ball pad with a 19 mm (0.75 in) radius, forming part of the aircraft

structure, is provided for using the safety stay.

Jacks and Safety Stay

A. Jack Design

(1) The maximum permitted loads given in the table in FIGURE 2-14-0-991-030-A are the

maximum loads applicable on jack fittings.

(2) In the fully retracted position (jack stroke at minimum), the height of the jack is such that

the jack may be placed beneath the aircraft in the most adverse conditions, namely, tires

deflated and shock absorbers depressurized. In addition, there must be a clearance of

approximately 50 mm (1.97 in) between the aircraft jacking point and the jack upper end.

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

(3) The lifting jack stroke enables the aircraft to be jacked up so that the fuselage longitudinal

datum line (aircraft center line) is parallel to the ground, with a clearance of 100 mm (3.94

in) between the main landing gear wheels and the ground. This enables the landing gear

extension/retraction tests to be performed.

Shoring Cradles

When it is necessary to support the aircraft in order to relieve the loads on the structure to do

modifications or major work, shoring cradles shall be placed under each wing and the fuselage as

necessary.

NOTE : The aircraft must not be lifted or supported by the wings or fuselage alone without

adequate support of the other.

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@A320

AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

WING JACKING

POINT

RIB9

FR74

FR73

FR8

FWD JACKING

SAFETY

POINT

STAY

B’

RIB9

WING JACKING

POINT

MAXIMUM

LOAD ELIGIBLE

daN

FORWARD FUSELAGE

2.74

8.99

6 800

JACKING POINT

17.56

57.61

6.50

21.33

28 500

WING JACKING

POINT

B’

17.56

57.61

−6.50

−21.33

28 500

SAFETY STAY

32.57

106.86

2 000

NOTE:

SAFETY STAY IS NOT USED FOR JACKING.

N_AC_021400_1_0300101_01_02

Jacking for Maintenance

Jacking Point Locations

FIGURE-2-14-0-991-030-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

WING JACK PAD

LOWER SURFACE

POINT BB’ DETAIL

RIB9INTERSECTION WITH REAR

SPAR DATUM

Z−828.35

Z−895

SPHERICAL RADIUS

32 mm (1.26 in)

NOTE:

TYPICAL

N_AC_021400_1_0320101_01_01

Jacking for Maintenance

Wing Jacking Points

FIGURE-2-14-0-991-032-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

FR73 FR74

FR8

FUSELAGE

DATUM LINE

FORWARD JACK

WING JACK

SAFETY STAY N

RIB9

WING JACK

FORWARD WING JACK

JACK

TYPICAL JACK INSTALLATION SHOWN

DISTANCE BETWEEN

JACKING/SAFETY POINTS

AND THE GROUND

CONFIGURATION

DESCRIPTION

(FORWARD

(WING

(SAFETY

JACK)

STAY)

− NLG SHOCK ABSORBER DEFLATED AND

NLG TIRES FLAT

1 588 mm

3 113 mm

3 656 mm

− MLG STANDARD TIRES, WITH STANDARD

(62.52 in)

(122.56 in)

(143.00 in)

SHOCK ABSORBERS

− AIRCRAFT ON WHEELS

TIRES FLAT

1 660 mm

2 735 mm

2 834 mm

SHOCK ABSORBERS DEFLATED

(65.35 in)

(107.68 in)

(111.57 in)

STANDARD TIRES

1 880 mm

3 112 mm

3 364 mm

STANDARD SHOCK ABSORBERS

(74.02 in)

(122.52 in)

(132.44 in)

STANDARD TIRES

−AIRCRAFT ON JACKS

MLG SHOCK ABSORBERS EXTENDED WITH

2 554 mm

3 655 mm

3 779 mm

(FORWARD JACK AND

WHEEL CLEARANCE OF 120 mm (4.72 in)

(100.55 in)

(143.90 in)

(148.78 in)

WING JACKS)

FOR MLG RETRACTION OR EXTENSION

− FUSELAGE DATUM LINE

PARALLEL TO THE GROUND

STANDARD TIRES

MLG SHOCK ABSORBERS EXTENDED WITH

3 204 mm

4 305 mm

4 429 mm

WHEEL CLEARANCE OF 770 mm (30.31 in)

(126.14 in)

(169.49 in)

(174.37 in)

FOR REPLACEMENT OF THE MLG

− AIRCRAFT ON FORWARD

STANDARD TIRES

JACK

NLG SHOCK ABSORBERS EXTENDED WITH

2 387 mm

2 854 mm

−MLG WHEELS ON THE

WHEEL CLEARANCE OF 60 mm (2.36 in)

(93.98 in)

(112.36 in)

GROUND

FOR NLG RETRACTION OR EXTENSION

NOTE:

THE SAFETY STAY IS NOT USED FOR JACKING.

N_AC_021400_1_0340101_01_02

Jacking for Maintenance

Jacking Design

FIGURE-2-14-0-991-034-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT FORWARD

FUSELAGE JACKING POINT

1000 kg

CG 15 %

MAX PERMISSIBLE LOAD

6.93

CG 25 %

CG 35 %

CG 45 %

1000 kg

1000 lb

110

121

132

143

154

165

A/C WEIGHT

NOTE: AS AN EXAMPLE ASSUME THAT THE AIRCRAFT HAS A GROSS WEIGHT

OF 66 000 kg AND THE CENTER OF GRAVITY (CG) IS AT 25 %. THUS THE

FORCE AT THE FORWARD FUSELAGE JACKING POINT IS 5 300 kg.

N_AC_021400_1_0350101_01_00

Loads at the Aircraft Jacking Points

Forward Fuselage Jacking Point - Twin Wheel/Bogie

FIGURE-2-14-0-991-035-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT WING JACKING POINT AT

STA4067/ FR8

1000 kg

CG 45 %

CG 35 %

CG 25 %

CG 15 %

MAX PERMISSIBLE LOAD

29.06

EXAMPLE:

GROSS WT: 60 000 kg

CG 25 %

FORCE AT EACH WING

JACKING POINT 27 350 kg

1000 kg

1000 lb

110

121

132

143

154

165

A/C WEIGHT

N_AC_021400_1_0360101_01_00

Loads at the Aircraft Jacking Points

Wing Jacking Point Rib 8 - Twin Wheel/Bogie

FIGURE-2-14-0-991-036-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

FR73/FR74

(SAFETY STAY)

FR64

FR63

FR42

RIB4

RIB22

RIB13

FR33

FR15

NOTE: THE SHORING CRADLE MUST BE INSTALLED AT THE EXACT LOCATION OF THE FRAME.

N_AC_021400_1_0370101_01_00

Jacking for Maintenance

Location of Shoring Cradles

FIGURE-2-14-0-991-037-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

Jacking of the Landing Gear

General

Landing gear jacking will be required to lift the landing gear wheels off the ground.

NOTE : You can lift the aircraft at Maximum Ramp Weight (MRW).

NOTE : The load at each jacking position is the load required to give a 25.4 mm (1 in) clearance

between the ground and the tire.

Main Gear Jacking (Twin Wheel)

The main gears are normally jacked up by placing a jack directly under the ball pad.

The ball spherical radius is 19 mm (0.75 in).

It is also possible to jack the main gear using a cantilever jack.

**ON A/C A320-200

Main Gear Jacking (4-Wheel Bogie)

The fore and aft pairs of MLG wheels can be jacked by placing a jack directly under the ball pads

located at each end of the bogie beam.

The ball spherical radius is 19 mm (0.75 in).

The leading dimensions and environmental distances of these jacking points are shown on FIGURE

2-14-0-991-048-A, FIGURE 2-14-0-991-049-A and FIGURE 2-14-0-991-050-A.

The reactions at each of the jacking points are shown on the graph FIGURE 2-14-0-991-051-A.

**ON A/C A320-200 A320neo

Nose Gear Jacking

For nose gear jacking, a 19 mm (0.75 in) radius ball pad is fitted under the lower end of the shock-

absorber sliding tube. Jacking can be accomplished either by placing a jack directly under the ball

pad, or using an adapter fitting provided with an identical ball pad.

Page 11

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

49 x 19 R20

600 mm

(23.62 in)

FULLY

EXTENDED

45 x 16 R20

200 mm

218 mm

25 mm

38 mm

552 mm

(7.87 in)

(8.58 in)

(1 in)

(1.5 in)

(21.73 in)

FULLY

DIA. BALL

RETRACTED

180 mm

INFLATED TIRES

(7.09 in)

ON THE RIM

FLAT TIRES

NOTE: TWIN WHEEL TRACK IS 927 mm (36.5 in).

THE FLAT TIRES VIEW SHOWS THE MINIMUM HEIGHT TO ENGAGE JACK WITH 2 FLAT TIRES.

THE INFLATED TIRES VIEW SHOWS THE JACKING HEIGHT TO GIVE 25 mm (1 in)

CLEARANCE BETWEEN THE TIRE AND GROUND.

N_AC_021400_1_0450101_01_00

Jacking of the Landing Gear

MLG Jacking Point Location - Twin Wheels

FIGURE-2-14-0-991-045-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

643 mm

(25.32 in)

MLG TIRE 49 x 19 R20

CANTILEVER

ARM

552 mm

(21.73 in)

25 mm

FWD

(1 in)

TWIN WHEEL TRACK

927 mm

(36.5 in)

DOUBLE FLAT MLG TIRES

218 mm (8.58 in)

(180 mm (7.09 in)

ON RIM)

409 mm

FORK

(16.1 in)

25 mm

1 620 mm

25 mm

MIN

APPROX

MIN

(1 in)

(63.78 in)

(1 in)

CONTOUR OF TIRES ON GROUND

N_AC_021400_1_0460101_01_00

Jacking of the Landing Gear

MLG Jacking with Cantilever Jack - Twin Wheels

FIGURE-2-14-0-991-046-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT MLG

JACKING POINT

1 000 kg

CG 40 %

CG 30 %

CG 25 %

CG 20 %

CG 17 %

A/C WEIGHT

1 000 kg

1 000 lb

100

110

120

130

140

150

160

170

180

N_AC_021400_1_0470101_01_00

Jacking of the Landing Gear

Loads at MLG Jacking Points - Twin Wheels

FIGURE-2-14-0-991-047-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

FRONT WHEELS JACKED UP

MAX DIAMETER

915 mm (36.02 in)

REAR WHEELS JACKED UP

MAX DIAMETER

915 mm (36.02 in)

FLAT TIRE DIMENSIONS

780 mm

(30.71 in)

140 mm

(5.51 in)

330 mm

(12.99 in)

1 230 mm

(48.43 in)

N_AC_021400_1_0500101_01_00

Jacking of the Landing Gear

MLG Jacking Point Location Bogie

FIGURE-2-14-0-991-050-A01

Page 17

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

LOAD AT MLG

JACKING POINT

1 000 kg

CG 40 %

CG 30 %

CG 25 %

CG 20 %

CG 17 %

A/C WEIGHT

1 000 kg

1 000 lb

100

110

120

130

140

150

160

170

180

NOTE: LOADS GIVEN ARE THOSE AT EACH BOGIE BEAM

JACKING POINT (FRONT AND REAR)

N_AC_021400_1_0510101_01_00

Jacking of the Landing Gear

Loads at MLG Jacking Points - Bogie Version

FIGURE-2-14-0-991-051-A01

Page 18

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT MLG

JACKING POINT

1 000 kg

KEY:−

37.5% CG

33.0% CG

28.0% CG

17.0% CG

x1 000 kg

100

110

120

130

140

150

160

170

180

x1 000 lb

AIRCRAFT WEIGHT

N_AC_021400_1_0520101_01_00

Jacking of the Landing Gear

Loads at MLG Jacking Points - 77 000 kg

FIGURE-2-14-0-991-052-A01

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

40 mm

128 mm

25 mm

38 mm

326 mm

APPROX

(1.57 in)

(5.06 in)

(1 in)

(1.5 in)

(12.83 in)

DIA. BALL

SAE AS 33559

FWD

500 mm (19.69 in)

264 mm MIN (10.39 in)

289 mm MAX (11.38 in)

198 mm

(7.8 in)

FLAT TIRES

INFLATED TIRES

NOTE:

THE FLAT TIRES VIEW SHOWS THE MINIMUM HEIGHT TO ENGAGE JACK WITH 2 FLAT TIRES.

THE INFLATED TIRES VIEW SHOWS THE JACKING HEIGHT TO GIVE 25 mm (1 in)

CLEARANCE BETWEEN THE TIRE AND GROUND.

N_AC_021400_1_0530101_01_00

Jacking of the Landing Gear

NLG Jacking - Point Location

FIGURE-2-14-0-991-053-A01

Page 20

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT NLG

JACKING POINT

1 000 kg

AIRCRAFT WEIGHT

x 1 000 kg

120

130

140

150

160

170

180

190

200

x 1 000 lb

N_AC_021400_1_0540101_01_00

Jacking of the Landing Gear

Loads at NLG Jacking Points

FIGURE-2-14-0-991-054-A01

Page 21

May 01/16

2-14-0

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200 A320neo

LOAD AT NLG

JACKING POINT

1 000 kg

KEY:−

17.0% CG

28.0% CG

33.0% CG

37.5% CG

AIRCRAFT WEIGHT

x 1 000 kg

100

110

120

130

140

150

160

170

180

x 1 000 lb

N_AC_021400_1_0550101_01_00

Jacking of the Landing Gear

Loads at NLG Jacking Points - 77 000 kg

FIGURE-2-14-0-991-055-A01

Page 22

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

AIRCRAFT PERFORMANCE

3-1-0

General Information

**ON A/C A320-200 A320neo

General Information

Standard day temperatures for the altitudes shown are tabulated below:

Standard Day Temperatures for the Altitudes

Altitude

Standard Day Temperature

FEET

METERS

˚F

˚C

59.0

15.0

2 000

610

51.9

11.1

4 000

1 220

44.7

7.1

6 000

1 830

37.6

3.1

8 000

2 440

30.5

-0.8

Page 1

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3-1-0

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AIRCRAFT CHARACTERISTICS - AIRPORT AND MAINTENANCE PLANNING

**ON A/C A320-200

NOTE: THESE CURVES ARE GIVEN FOR INFORMATION ONLY

THE APPROVED VALUES ARE STATED IN THE "OPERATING

MANUALS" SPECIFIC TO THE AIRLINE OPERATING THE AIRCRAFT.

1 000 kg

1 000 lb

110

230

100

220

210

200

190

180

170

160

150

140

130

120

110

1 000 ft

RUNWAY LENGTH

1 000 m

N_AC_030301_1_0050101_01_01

Take-Off Weight Limitation - ISA Conditions

CFM56 Series Engine

FIGURE-3-3-1-991-005-A01

Page 2

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Airbus A320. AIRCRAFT CHARACTERISTICS AIRPORT AND MAINTENANCE PLANNING (2016-2023) - page 3