flightpreparation/limitations if max...

MINIMUM EQUIPMENT LIST

OPERATIONAL PROCEDURES

ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32

Minimum Equipment List A320 Copyright © 2013 Edition 0

32-07-01A Brakes Temperature Indication on the WHEEL SD page

32-07-01B Ident.: MO-32-07-00009012.0003001 / 28 JUN 11

Applicable to: ALL

FLIGHT PREPARATION/LIMITATIONS

The brake energy graph and the brake cooling time table given hereafter permit to determine the

ground brake cooling time.

BRAKE ENERGY GRAPH

If MAX reverser thrust was selected for all reversers during the braking phase:

Enter the brake energy graph: WITH THRUST REVERSERS USE.

If MAX reverser thrust was NOT selected for all reversers during the braking phase:

Enter the brake energy graph: WITHOUT THRUST REVERSERS USE. Determination of the

brake energy accumulated during a REJECTED TAKEOFF (RTO):

‐ Enter with the aircraft takeoff weight (TOW) and with the rejected takeoff speed in kt IAS). ‐ Apply airport pressure altitude, temperature, wind and runway slope corrections.

Determination of the brake energy accumulated during a LANDING:

‐ Enter with the aircraft landing weight, and

‐ Enter with the touch down speed in kt IAS if the autobrake was selected and applied or with

the manual braking speed in kt IAS in the other cases.

‐ Apply airport pressure altitude, temperature, wind and runway slope corrections.

‐ Correct for brake setting with a preselected autobrake setting (LO, MED) or with MAX PEDAL

braking in the other cases.

Note: In the case of a dispatch with one brake inoperative (Refer to Item 32-42-01 Main

Wheel Brake or Refer to Item 32-42-02 Green System Brake), the brake energy

accumulated is increased by 34 %.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


Brake Energy with Thrust Reverser Use



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


Brake Energy without Thrust Reverser Use



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


BRAKE COOLING TIME TABLE

Determination of the brake cooling time: EXAMPLE:

55 152 153 154 155 155 ====> TIME (min) WITHOUT BRAKE COOLING FAN

46 46 46 46 47 ====> TIME (min) WITH BRAKE COOLING FAN

If the Energy and the OAT are not given in the table, use the values given in the next adjacent

column/row.

For Example, with Energy = 78 MJ, and OAT = 15 °C, entering the next adjacent column/row

(Energy = 80 MJ, OAT = 20 °C) gives the following results: ‐ Without brake cooling fan: 189 min

‐ With brake cooling fan: 57 min

Enter the following table with the energy and the OAT to determine the ground brake cooling time.

GROUND BRAKE COOLING TIME (min)

ENERGY

(MJ)

0

OAT (°C) -50

0

0

-40

0

0

-30

0

0

-20

0

0

-10 0

0 0

0 0

10

0

0

20 30

0 0

0 0

40

0

0

50

0

0

55

0

0

5

0 0

0

0

0

0

0

0 0 0

0 0

0

0 0 0

0 0

0

0

0

0

0

0

10

15

0 0

31 9

0

0

35

10

0

0

38

11

4

1

42

12

9 14

3 4

45 48

13 14

19

6

51

15

23 27

7 8

54 57

16 17

31

9

60

18

35

10

62

19

37

11

64

19

20

59 18

62

19

65

19

67

20 70 72

21 22

74

22 77 79

23 24

81

24

83

25

84

25

25

81 24

83

25

85

25

87

26 89 91

27 27

92

28 94 96

28 29

98

29

99

30

100

30

30

35

98 29

11

2 34

99

30

113

34

101

30

115

34

103

31

116

35

104 106

31 32

117 119

35 36

107

32

120

36

109 110

33 33

121 123

36 37

112

34

124

37

113

34

125

38

114

34

126

38

40

124 37

125

37

126

38

127

38 129 130

39 39

131

39 132 133

40 40

134

40

135

41

136

41

45 134

40

135

41

136

41

137

41 139 140

42 42

141

42 142 143

42 43

144

43

145

43

145

44

50 144 43

145

43 146

44 146

44 147 148

44 45 149

45 150 151

45 45 152

46 153

46 153

46 GROUND BRAKE COOLING TIME (min)

ENERGY

(MJ) OAT (°C)

-50 -40 -30 -20 -10 0 10 20 30 40 50 55



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


55

60

152

46

160

48

153 154

46 46

160 161

48 48

155

46

162

49

155

47

163

49

156

47

164

49

157 158

47 47

164 165

49 50

159 160

48 48

166 167

50 50

160 161

48 48

167 168

50 50

65 167

50 167 168

50 50

169

51

170

51

170

51 171 172

51 52

172 173

52 52

174 174

52 52

70

75

173

52

179

54

174 174

52 52

180 180

54 54

175

53

181

54

176

53

182

54

176

53

182

55

177 178

53 53

183 183

55 55

178 179

54 54

184 185

55 55

180 180

54 54

185 186

56 56

80

85

185

55

190

57

185 186

56 56

190 191

57 57

186

56

191

57

187

56

192

58

188

56

193

58

188 189

56 57

193 194

58 58

189 190

57 57

194 195

58 58

190 191

57 57

195 196

59 59

90 195

58 195 196

59 59

196

59

197

59

197

59 198 198

59 60

199 199

60 60

200 200

60 60

95

100

199

60

204

61

200 200

60 60

204 205

61 61

201

60

205

62

201

60

206

62

202

61

206

62

202 203

61 61

207 207

62 62

203 204

61 61

208 208

62 62

204 205

61 61

208 209

63 63

105 208

62 208 209

63 63

209

63

210

63

210

63 211 211

63 63

212 212

63 64

212 213

64 64

110 212

64 212 213

64 64

213

64

214

64

214

64 215 215

64 64

215 216

65 65

216 216

65 65

115

120

216

65

219

66

216 217

65 65

220 220

66 66

217

65

221

66

217

65

221

66

218

65

221

66

218 219

65 66

222 222

67 67

219 219

66 66

222 223

67 67

220 220

66 66

223 223

67 67

A320 Messier/Goodrich - 03.01.05 - F476021.txt



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


AFTER ENGINE START

In the case of a false BRAKES HOT alert displayed on the EWD:

EMER CANC pb................................................................................................................. Press

Note: In the case of a false BRAKES HOT alert due to a faulty BTMU or a faulty BSCU, the

"T.O CONFIG NORMAL” line will not replace the "T.O CONFIG . . TEST" line in the T.O

MEMO. Consider normal configuration for takeoff provided that no alert was displayed

during the T.O CONFIG TEST.

CAUTION: The T.O CONFIG TEST pb must be maintained pressed to check that there is no

alert.

32-07-03A L/G Doors Position Indication on the WHEEL SD page

Ident.: MO-32-07-00009013.0001001 / 28 JUN 11

Applicable to: ALL

IN FLIGHT

MAX SPEED....................................................................................................... 250 kt or M 0.60

32-31-01A Landing Gear Control and Interface Unit (LGCIU)

Ident.: MO-32-31-00008975.0002001 / 28 JUN 11

Applicable to: ALL

DURING COCKPIT PREPARATION

HYDRAULIC/LGCIU/SYS2 (121VU Q35) C/B......................................................................PULL

The following table gives the consequences on the systems affected when the LGCIU 2 is

inoperative and above mentioned C/B is pulled.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


SYSTEMS CONSEQUENCES PROCEDURE

AVNCS VENT

(on ground)

HYD

(on ground)

TPIS

• The system remains in closed circuit

configuration.

• The ground cooling system is

inoperative.

The PTU runs after the first engine start until

the second engine is started.

• Time limitations on ground for ELEC PWR

supply:

‐ OAT ≤ 43 °C: No Limitation

‐ 44 °C ≤ OAT ≤ 52 °C: 3 h

‐ OAT ≥ 53 °C: 30 min

• Check that the air conditioning system is

operative.

The BLUE ELEC PUMP FAULT light and the

YELLOW ENG 2 PUMP FAULT light come on

when engines are off.

The WHEEL TYRE LO PR alert threshold is

set to flight level.

ATC 2

(on ground)

LIGHTS

The ATC 2 is not inhibited.

The strobe lights are not inhibited on

ground when set to AUTO.

On ground, set the ATC selector to SYS 1.

On ground, set the STROBE sw to OFF.

On ground, with flaps retracted, logo lights do

not come on.

The taxi light, the runway turn-off light, and the

takeoff light are inoperative on ground and in

flight.

ELEC

(on ground)

When only the APU generator or the GPU supplies the aircraft, the main galleys are not

supplied.

SYSTEMS CONSEQUENCES PROCEDURE

ENG 2

(on ground)

The FADEC supply is continuously on.

The automatic start abort is inoperative. Use the MAN START procedure.

The minimum idle is inoperative when

slats/flaps are extended. Ground

Refer to OpsProc 73-20-05A Minimum Idle on

When FLX TO is selected, MCT thrust is

set.

Use the TOGA for takeoff.

The thrust reverser is inoperative. Refer to OpsProc 78-30-01A Thrust Reverser

The BUMP function is inoperative. Do not use the BUMP function.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


SLATS (on ground)

AIR COND (on

ground)

The slats are slow from 1 to 0.

Both air conditioning packs ram air inlet do

not

Close.

WING A ICE

(on ground)

On ground, when set to ON, the WING A

ICE valve do not close at the end of the test

sequence (30 s).

The WING A.ICE OPEN ON GND alert will be

displayed on the EWD.

ADIRU and AVNCS

VENT alert WATER

SERVICING (on

ground)

The horn and the light are inoperative.

The preselect water servicing is inoperative.

CARGO DOOR

(FWD and AFT)

RECORDERS (on

ground)

Only the manual control is operative.

The CVR test and the CVR erase functions

are inoperative. The CVR and the DFDR do

not stop after engine shutdown.

BRAKES (on

ground) AIRSTAIRS

The brakes cooling is inoperative.

The air stairs cannot be extended.

WEIGHT AND

BALANCE

SYSTEM ECAM

(in flight and on

ground)

The WBS is inoperative.

IN FLIGHT

In the case of loss of the LGCIU 1: AP and FD are lost. Maximum landing capability is CAT 1.

32-31-02A Landing Gear Retracting System

Ident.: MO-32-31-00008977.0001001 / 28 JUN 11

Applicable to: ALL

Refer to FCOM/PRO-SPO-25-FLIGHT WITH GEAR DOWN.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-32-02A LGCIU 2 RH L/G Shock Absorber Proximity Detector

Ident.: MO-32-32-00008978.0002001 / 28 JUN 11

Applicable to: ALL

GENERAL INFORMATION SYSTEMS CONSEQUENCES PROCEDURES

PITOTS

(on ground)

AVNCS VENT (on ground)

The F/O pitot is set to high heating level when the EXT PWR pb-sw is set to OFF.

• The system remains in the closed circuit

configuration.

• The ground cooling system is inoperative.

Keep the EXT PWR pb-sw set to ON until the

engine start.

• Time limitations on ground for ELEC PWR

supply:

‐ OAT ≤ 43 °C: No limitation

‐ OAT = 52 °C: 3 h

‐ OAT = 61 °C: 30 min

• Check that the air conditioning system is

operative. ADIRU and AVNCS

VENT alert (on

ground)

The horn and the light are inoperative.

HYD alerts

(on ground)

The BLUE ELEC PUMP FAULT light and the YELLOW ENG 2 PUMP FAULT light come on

when engines are off.

WING A/ICE

(on ground)

The wing anti-ice is not inhibited.

On ground, do not set the WING ANTI ICE pb-sw to ON for more that 30 s. If required, set

it to ON just before takeoff.

TPIS

(on ground)

The WHEEL TYRE LO PR alert threshold is set to flight level.

ATC 2

(on ground)

LIGHTS

(on ground)

The ATC 2 is not inhibited.

The strobe lights are not inhibited.

On ground, set the ATC selector to SYS 1.

On ground, set the STROBE sw to OFF.

On ground, with flaps retracted, the logo lights

do not come on.

ELEC When only the APU generator or GPU supplies

(on ground) the aircraft, the main galleys are not supplied.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


SYSTEMS CONSEQUENCES PROCEDURES

The FADEC supply is continuously on.

ENG 2

(on ground)

The automatic start abort is inoperative. Use the MAN START procedure.

The minimum idle is inoperative.

When FLX TO is selected, MCT thrust is set.

Refer to OpsProc 73-20-05A Minimum Idle on

Ground

Use the TOGA for takeoff.

The thrust Reverser is inoperative. Refer to OpsProc 78-30-01A Thrust Reverser

The BUMP function is inoperative. Do not use the BUMP function.

SLATS (on ground) CARGO DOOROnly the

manual control is

operative.

(on ground)

The slats are slow from

1 to 0.

AIR COND (on ground) not close.

WATERThe preselect

water servicing is

inoperative.

SERVICING

(on ground)

The air conditioning pack 2 ram air inlet

does

AIRSTAIRS (on

ground) The CVR

test and the CVR erase

functions are

inoperative. The CVR

and the DFDR do not

stop after engine

shutdown.

The airstairs cannot be extended.

RECORDERS

ECAM position

indications associated

with the (in flight

and LGCIU 2 are

displayed XX.

on The L/G LGCIU 2 FAULT alert is displayed on the EWD.

• On the WHEEL SD page, the landing gear



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-32-03A LGCIU 2 LH L/G Shock Absorber Proximity Detector

Ident.: MO-32-32-00008988.0001001 / 28 JUN 11

Applicable to: MSN 0342

GENERAL INFORMATION



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-32-08A LGCIU 2 RH L/G Up Lock Proximity Detector

Ident.: MO-32-32-00008993.0004001 / 05 OCT 10

Applicable to: MSN 0112-0189


ENG 2

(on ground)

REVERSER 2 is displayed in the INOP SYS

column on the STATUS SD page.

The thrust Reverser 2 is still operative.

The minimum idle on ground is inoperative

when slats/flaps are extended.

ECAM

(in flight and

on ground)

For WHEEL SD page and ECAM alert Refer to Item 32-31-01 Landing Gear Control and

Interface Unit (LGCIU) "ECAM" line.

32-32-08A LGCIU 2 RH L/G Up Lock Proximity Detector

Ident.: MO-32-32-00008993.0001001 / 05 OCT 10


GENERAL INFORMATION

SYSTEMS CONSEQUENCES PROCEDURES

ECAM

(in flight and

on ground)



32-32-09A LGCIU 2 LH L/G Up Lock Proximity Detector

Ident.: MO-32-32-00008994.0004001 / 17 SEP 10

Applicable to: MSN 0112-0189 SYSTEMS CONSEQUENCES PROCEDURES

REVERSER 2 is displayed in the INOP SYS ENG 2 column on the STATUS SD page.

(on ground) The minimum idle on ground is inoperative



ECAM (in flight and

on ground)





ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-32-09A LGCIU 2 LH L/G Up Lock Proximity Detector

Ident.: MO-32-32-00008994.0001001 / 04 OCT 10


32-32-10A LGCIU 2 Nose L/G Up Lock Proximity Detector

Ident.: MO-32-32-00009002.0004001 / 28 JUN 11

Applicable to: MSN 0112-0189, 0438


REVERSER 2 is displayed in the INOP SYS

ENG 2 column on the STATUS SD page.

(on ground) The minimum idle on ground is inoperative



ECAM For WHEEL SD page and ECAM alert Refer to Item 32-31-01 Landing Gear Control and

(in flight and Interface Unit (LGCIU) "ECAM" line.

on ground)

32-32-10A LGCIU 2 Nose L/G Up Lock Proximity Detector

Ident.: MO-32-32-00009002.0001001 / 04 OCT 10


GENERAL INFORMATION



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-42-01A Main Wheel Brake

Ident.: MO-32-42-00009004.0229001 / 18 JUL 12 Applicable to: MSN 0112, 0342


Maximum landing capability is CAT 3 Single.

The following penalties may be used for takeoff and landing performance determination if no takeoff

and landing data (predetermined by using OCTOPUS program or other equivalent program with

present failure case) is available.

Takeoff performance computation:

The method explained hereafter allows the determination of the MTOW and associated

speeds (V1, VR, V2), by applying decrements on the MTOW and associated speeds

computed in normal conditions (i.e. all systems operative). The method is based on the use

of RTOW charts established at optimum V2/VS, optimum V1/VR, minimum V1.

WARNING ‐ Do not use this method with takeoff charts computed with other conditions.

‐ Do not use this method for takeoff with tailwind.

‐ Do not use this method for takeoff on wet or contaminated runways.

How to proceed ?

‐ Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW

and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the

case of headwind (the method does not take into account the headwind benefit on takeoff

performance).

‐ Apply the QNH and/or bleed corrections, if any, to determine the MTOW.

‐ Enter the following table to determine the MTOW and speed decrements.

‐ Applying these decrements, calculate the MTOW and associated speeds corresponding to

the actual temperature.

CAUTION Do not extrapolate below the shortest runway length provided by the table.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN ONE BRAKE IS INOPERATIVE

CONFIGURATION

RUNWAY 1+F 2 3

LENGTH (m) ΔW (kg/lb) ΔV1 ΔVR

(kt) (kt)

ΔV2

(kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

1 500 2 600/5 800

2 000 2 800/6 200

7 2

7 2

2

2

2 600/5 800

2 600/5 800

7

7

2 2

2 2

2 400/5 300

2 600/5 800

7

7

2 2

2 2

2 500 4 000/8 900 12 4 4 3 800/8 400 10 4 4 2 600/5 800 11 5 5


CONFIGURATION

RUNWAY 1+F 2 3

LENGTH (m) ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

3 000 6 800/15 000

3 500 8 200/18 100

18

16

8 8

12 12

5 800/12 800

7 000/15 500

18

17

8 8

13 13

4 400/9 800

4 400/9 800

22

20

10 10

14 14

4 000 and 8 200/18 100 above

17

15 15

6 600/14 600

18

17 17

5 200/11 500

20

17 17

If the actual TOW is lower than the MTOW calculated using above method:

The speeds determined without failure and associated with the actual TOW may be retained

provided that they are all lower than the speeds calculated using above method.

Check that the corrected V1 is equal to or above the minimum V1 value shown on the RTOW

chart (due to VMCG limitation).

If the corrected V1 is lower than the minimum V1: Take this last value as V1.

Further decrease the weight by 3 000 kg (6 600 lb) per kt difference between both values.

Check that the corrected VR is equal to or above the minimum VR value shown on the

RTOW chart (due to VMCA limitation).



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


If the corrected VR is lower than the minimum VR:

Takeoff cannot be performed using this method.


chart (due to VMCA limitation).

If the corrected V2 is lower than the minimum V2:


Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (see

Refer to FCOM/PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).



Landing performance computation: Multiply the landing distances by 1.25.

FOR TAKEOFF

The autobrake function, even if available, must not be used.

If the above method was used for takeoff performance computation:

Perform the takeoff using full thrust (TOGA).

In the case of engine failure at takeoff:

Retract the landing gear when positive climb.

Vibrations may occur during 1 or 2 min after the retraction of the landing gear.

If both engines are operative:

Keep the landing gear down for 1 min.

FOR LANDING




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32



Ident.: MO-32-42-00009004.0130001 / 18 JUL 12












WARNING: ‐ Do not use this method with takeoff charts computed with other conditions.



How to proceed ?

‐ Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW and

associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the case of

headwind (the method does not take into account the headwind benefit on takeoff

performance).





CAUTION: Do not extrapolate below the shortest runway length provided by the table.



ATA 32 LANDING GEAR

AIRBUS A320

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CONFIGURATION

RUNWAY

1+F 2 3

LENGTH (m) ΔW (kg/lb) ΔV1 ΔVR

(kt) (kt)

ΔV2

(kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

1 500 2 600/5 800

2 000 2 800/6 200

7 2

7 2

2

2

2 600/5 800

2 600/5 800

7

7

2 2

2 2

2 400/5 300

2 600/5 800

7

7

2 2

2 2

2 500 4 000/8 900 12 4 4 3 800/8 400 10 4 4 2 600/5 800 11 5 5


CONFIGURATION

RUNWAY 1+F 2 3


(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

3 000 6 800/15 000

3 500 8 200/18 100

18

16

8 8

12 12

5 800/12 800

7 000/15 500

18

17

8 8

13 13

4 400/9 800

4 400/9 800

22

20

10 10

14 14

4 000 and 8 200/18 100

above

17

15 15

6 600/14 600

18

17 17

5 200/11 500

20

17 17




Check that the corrected V1 is equal to or above the minimum V1 value shown on the RTOW chart

(due to VMCG limitation).


Further decrease the weight by 3 000 kg (6 600 lb) per kt difference between both values. Check

that the corrected VR is equal to or above the minimum VR value shown on the RTOW chart

(due to VMCA limitation).





ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


Check that the corrected V2 is equal to or above the minimum V2 value shown on the RTOW chart

(due to VMCA limitation).



Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (Refer to

FCOM/PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).




FOR TAKEOFF







If both engines are operative:

Keep the landing gear down for 1 min.

FOR LANDING




ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32



Ident.: MO-32-42-00009004.0130001 / 18 JUL 12 Applicable to: MSN 0189











WARNING: ‐ Do not use this method with takeoff charts computed with other conditions.



How to proceed ?

‐ Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW

and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the

case of headwind (the method does not take into account the headwind benefit on takeoff

performance).





CAUTION: Do not extrapolate below the shortest runway length provided by the table.



ATA 32 LANDING GEAR

AIRBUS A320

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CONFIGURATION

RUNWAY 1+F 2 3


(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

ΔW (kg/lb) ΔV1

(kt)

ΔVR ΔV2

(kt) (kt)

1 500 3 000/6 700

2 000 3 200/7 100

7

8

3 3

3 3

2 600/5 800

3 000/6 700

7

7

2 2

2 2

2 400/5 300

3 000/6 700

7

7

2 2

3 3

2 500 5 200/11 500 14 4 4 4 800/10 600 13 5 5 4 600/10 200 13 5 5

3 000 9 400/20 800 16 9 9 5 600/12 400 18 6 6 7 000/15 500 19 11 11

3 500 9 200/20 300 16 11 11 7 500/16 600 16 11 11 8 000/17 700 18 16 16

4 000 and 9 500/21 000 above

15

13 13 7 600/16 800 16

15 15 8 600/19 000 16

14 14





chart (due to VMCG limitation).


Further decrease the weight by 3 000 kg (6 600 lb) per kt difference between both values.

Check that the corrected VR is equal to or above the minimum VR value shown on the RTOW









ATA 32 LANDING GEAR

AIRBUS A320

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Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (Refer to

FCOM/PER-TOF-TOD-25-20 MINIMUM V2 LIMITED BY VMU/VMCA (KT IAS)).




FOR TAKEOFF







If both engines are operative: Keep the landing gear down for 1 min.

FOR LANDING


32-42-02A Green System Brake

Ident.: MO-32-42-00009005.0001001 / 11 MAR 10

Applicable to: ALL

Refer to OpsProc 32-42-01A Main Wheel Brake.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-42-05A AUTO/BRK Function

Ident.: MO-32-42-00009006.0001001 / 11 MAR 10

Applicable to: ALL


Maximum landing capability is CAT 3 SINGLE.

BEFORE TAKEOFF

When T.O MEMO is displayed on the EWD, disregard the line:

AUTO BRK....................................................................................................................... MAX (blue)

32-47-01A Brake Temperature Monitoring Unit (BTMU)

Ident.: MO-32-47-00009008.0001001 / 28 JUN 11

Applicable to: ALL

DURING PRELIMINARY COCKPIT PREPARATION

HYDRAULIC/BRK/TEMP/DET/UNIT (121VU M26 or M37) C/B................................................PULL

Determine brake cooling time (Refer to OpsProc 32-07-01A (B) Brakes Temperature Indication on

the WHEEL SD page).

32-51-01A Nose Wheel Steering Control System

Ident.: MO-32-51-00009009.0001001 / 28 JUN 11


GENERAL INFORMATION

The electrical and hydraulic control of NWS is inoperative. Do not reset the WHEEL N.W. STEER

FAULT alert with A/SKID & N/W STRG selector. The WHEEL N.W. STEER FAULT alert indicates

that no hydraulic pressure is applied on the NWS actuator.


Dispatch is not permitted from (or to) contaminated runways. Maximum crosswind component for

takeoff and landing: 20 kt. Maximum landing capability is CAT 3 SINGLE.

Note: the automatic roll out is not permitted (Refer to QRH/OPS Required Equipment for

CAT2 and CAT3).



ATA 32 LANDING GEAR

AIRBUS A320

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For operations with crosswind component above 5 kt:

Reduce maximum takeoff performance limiting weight by 1 000 kg (2 200 lb)

DURING TAXI

Taxiing Procedure:

‐ Avoid high thrust settings, taxi speed limited to 20 kt.

‐ Check brakes temperature (if available) before takeoff.

If necessary, set the BRAKES FAN pb-sw to ON.

‐ Minimum speed of 5 kt is required to initiate a turn.

‐ Apply asymmetrical thrust in straight taxi to compensate crosswind and differential braking for taxi

and line up as required.

‐ Avoid sharp turns and use maximum width of the runway.

‐ Do not apply too high asymmetrical thrust to avoid that nose landing gear get stuck to full travel

(90 °) (in that case release the aircraft by towing).

FOR TAKEOFF

In the case of crosswind component above 5 kt:

‐ Set full nose down elevator till 80 kt regardless of the aircraft loading.

‐ Apply N1 = 50 % on the brakes

‐ Release the brakes, and smoothly apply takeoff power

‐ Use asymmetric braking, if required, to keep on runway center-line until directional control is

available by use of rudder.

‐ Release stick progressively to reach neutral at about 100 kt.

FOR LANDING

Do not use autobrake for landing.


‐ Aircraft lateral control is achieved with the rudder until slowing to approximately 50 kt IAS.

‐ Upon reaching 50 kt IAS use differential braking to achieve taxi speed as required.

AFTER LANDING

Disengage AP at touchdown when autoland is performed.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


32-51-01A Nose Wheel Steering Control System

Ident.: MO-32-51-00009009.0006001 / 28 JUN 11

Applicable to: MSN 0112-0189

GENERAL INFORMATION

The electrical and hydraulic control of NWS is inoperative. Do not reset the WHEEL N/W STRG

FAULT alert with A/SKID & N/W STRG selector. The WHEEL N/W STRG FAULT alert indicates

that no hydraulic pressure is applied on the NWS actuator.


Dispatch is not permitted from (or to) contaminated runways.

Maximum crosswind component for takeoff and landing: 20 kt.

Maximum landing capability is CAT 3 SINGLE.

Note: the automatic roll out is not permitted (Refer to QRH/OPS Required Equipment for

CAT2 and CAT3).

For operations with crosswind component above 5 kt:

Reduce maximum takeoff performance limiting weight by 1 000 kg (2 200 lb).

DURING TAXI

Taxiing Procedure:

‐ Avoid high thrust settings, taxi speed limited to 20 kt.

‐ Check brakes temperature (if available) before takeoff.

If necessary, set the BRAKES FAN pb-sw to ON.

‐ Minimum speed of 5 kt is required to initiate a turn.

‐ Apply asymmetrical thrust in straight taxi to compensate crosswind and differential braking

for taxi and line up as required.

‐ Avoid sharp turns and use maximum width of the runway.

‐ Do not apply too high asymmetrical thrust to avoid that nose landing gear get stuck to full

travel (90 °) (in that case release the aircraft by towing).

FOR TAKEOFF


‐ Set full nose down elevator till 80 kt regardless of the aircraft loading.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


‐ Apply N1 = 50 % on the brakes

‐ Release the brakes, and smoothly apply takeoff power

‐ Use asymmetric braking, if required, to keep on runway center-line until directional control is

available by use of rudder.

‐ Release stick progressively to reach neutral at about 100 kt.

FOR LANDING

Do not use autobrake for landing.


‐ Aircraft lateral control is achieved with the rudder until slowing to approximately 50 kt IAS.

‐ Upon reaching 50 kt IAS use differential braking to achieve taxi speed as required.

AFTER LANDING

Disengage AP at touchdown when autoland is performed.

32-51-02A Rudder PEDALS DISC pb

Ident.: MO-32-51-00012799.0001001 / 17 SEP 10

Applicable to: ALL

The purpose of the procedure is to explain how to perform the flight control check with one or both

PEDALS DISC pb failed in the released position. GENERAL INFORMATION

When the disconnection is not possible on one side:

The flight control check can be performed on the operative side.

When the disconnection is not possible on both sides:

The flight control check must be performed while aircraft is stopped.

Note: it is not necessary to set the A/SKID & N/W STRG sw to OFF.

32-51-03A NWS Electrical Deactivation Box (towing mode is not

available when the lever is in the TOWING position)

Ident.: MO-32-51-00009010.0001001 / 17 SEP 10

Applicable to: ALL

BEFORE CONVENTIONAL OR TOWLESS PUSHBACK

A/SKID & N/W STRG selector.................................................................................................... OFF



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


AFTER PUSHBACK

A/SKID & N/W STRG selector...................................................................................................... ON

32-51-03B NWS Electrical Deactivation Box (NWS Electrical Deactivation

Box deactivated)

Ident.: MO-32-51-00012592.0001001 / 17 SEP 10

Applicable to: ALL

BEFORE CONVENTIONAL OR TOWLESS PUSHBACK

A/SKID & N/W STRG selector.................................................................................................... OFF

As a result of the NWS electrical box deactivation, the parking brake light on that box will not be

available.

The parking brake setting must be verbally confirmed between the flight crew and the

ground personnel before pushback.

AFTER PUSHBACK

A/SKID & N/W STRG selector...................................................................................................... ON

32-51-04A PARKING BRAKE light on the NWS Electrical Deactivation Box

Ident.: MO-32-51-00009011.0001001 / 17 SEP 10

Applicable to: ALL

BEFORE PUSHBACK

The parking brake setting must be verbally confirmed between the flight crew and the ground

personnel.



ATA 32 LANDING GEAR

AIRBUS A320

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CAA-01 ATA 32


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