W DOC AIRBUS | MMEL OPS PROC

Main Wheel Brake

32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
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.
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN ONE BRAKE IS INOPERATIVE
RUNWAY LENGTH (m)CONFIGURATION
1+F23
ΔWkg (lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔWkg (lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔWkg (lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)
1500 3500
( 7700 )
 11 3 3 3500
( 7700 )
 11 3 3 3000
( 6600 )
 9 3 3
2000 3500
( 7700 )
 11 3 3 3500
( 7700 )
 11 3 3 3000
( 6600 )
 10 4 4
2500 7000
( 15500 )
 13 4 4 5000
( 11000 )
 12 5 5 3000
( 6600 )
 14 5 5
3000 9000
( 19900 )
 19 7 7 5500
( 12200 )
 22 8 8 3000
( 6600 )
 20 8 8
3500 10000
( 22100 )
 20 8 8 6500
( 14400 )
 22 9 9 3500
( 7700 )
 24 9 9
4000 and above 10000
( 22100 )
 18 8 8 6500
( 14400 )
 21 9 9 3500
( 7700 )
 22 9 9
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 3000 kg ( 6600 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).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (see Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.20.
- 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
The autobrake function, even if available, must not be used.
32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
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.
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN ONE BRAKE IS INOPERATIVE
RUNWAY LENGTH (m)CONFIGURATION
1+F23
ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)
1500
2600 / 5800
7 2 2
2600 / 5800
7 2 2
2600 / 5800
7 2 2
2000
2600 / 5800
7 6 6
2000 / 4500
7 3 3
1800 / 4000
8 4 4
2500
2400 / 5300
11 5 5
2200 / 4900
11 6 6
1800 / 4000
9 5 5
3000
3600 / 8000
22 11 11
3000 / 6700
21 11 11
3600 / 8000
17 14 14
3500
3400 / 7500
22 12 12
4400 / 9800
19 18 18
4400 / 9800
18 17 17
4000 and above
5200 / 11500
20 20 20
5200 / 11500
18 18 18
2800 / 6200
17 16 16
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 3000 kg ( 6600 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).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (see Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
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
The autobrake function, even if available, must not be used.
32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
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.
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN ONE BRAKE IS INOPERATIVE
RUNWAY LENGTH (m)CONFIGURATION
1+F23
ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)
1500
2400 / 5200
8 2 2
2400 / 5200
8 2 2
2400 / 5200
7 6 6
2000
2600 / 5700
7 6 6
1800 / 3900
7 5 5
1600 / 3500
7 4 4
2500
2200 / 4800
10 5 5
1800 / 3900
9 5 5
1800 / 3900
8 5 5
3000
3800 / 8300
22 11 11
3400 / 7400
21 12 12
3800 / 8300
15 13 13
3500
3200 / 7000
22 12 12
7800 / 17100
15 13 13
6800 / 14900
12 10 10
4000 and above
5000 / 11000
21 19 19
5800 / 12700
18 18 18
2000 / 4400
13 12 12
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 3000 kg ( 6600 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).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (see Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
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
The autobrake function, even if available, must not be used.
32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
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.
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN ONE BRAKE IS INOPERATIVE
RUNWAY LENGTH (m)CONFIGURATION
1+F23
ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)ΔW (kg/lb)ΔV1 (kt)ΔVR (kt)ΔV2 (kt)
1500
2700 / 5900
7 2 2
3200 / 7000
8 3 3
3000 / 6600
8 2 2
2000
3600 / 7900
8 2 2
3800 / 8300
8 3 3
3100 / 6800
8 3 3
2500
5600 / 12300
16 5 5
5100 / 11200
15 5 5
4800 / 10500
16 5 5
3000
9900 / 21800
16 10 10
7200 / 15800
17 7 7
5100 / 11200
21 8 8
3500
9300 / 20500
17 15 15
7400 / 16300
19 19 19
6800 / 14900
20 14 14
4000 and above
9800 / 21600
15 13 13
7200 / 15800
20 21 21
6500 / 14300
19 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 3000 kg ( 6600 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).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation (see Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.20.
- 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
The autobrake function, even if available, must not be used.
32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
Maximum landing capability is CAT 3 Single.
Takeoff performance computation:
The takeoff and landing performance must be determined by using OCTOPUS program or other equivalent program with present failure case taken into account.
Launch PEP.
Landing performance computation
Multiply the landing distances by 1.20.
- For takeoff
The autobrake function, even if available, must not be used.
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
The autobrake function, even if available, must not be used.
32-42-01AMain Wheel Brake
Applicable to: -
- Flight preparation/limitations
Maximum landing capability is CAT 3 Single.
Takeoff performance computation:
The takeoff and landing performance must be determined by using OCTOPUS program or other equivalent program with present failure case taken into account.
Launch PEP.
Landing performance computation
Multiply the landing distances by 1.30.
- For takeoff
The autobrake function, even if available, must not be used.
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
The autobrake function, even if available, must not be used.
"WTRUIB" 2025