DOC AIRBUS | MMEL OPS PROCSpoilers 1 and 2
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
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: |
|
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 TWO PAIRS OF SPOILERS
ARE INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| 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 | 400 / 900 | 1 | 0 | 0 | 400 / 900 | 1 | 0 | 0 | 500 / 1100 | 1 | 0 | 0 |
| 2000 | 500 / 1100 | 1 | 0 | 0 | 500 / 1100 | 1 | 0 | 0 | 500 / 1100 | 2 | 1 | 1 |
| 2500 | 500 /1 100 | 1 | 0 | 0 | 500 / 1100 | 2 | 1 | 1 | 500 / 1100 | 3 | 1 | 1 |
| 3000 | 500 / 1100 | 2 | 1 | 1 | 500 / 1100 | 3 | 2 | 2 | 500 / 1100 | 3 | 2 | 2 |
| 3500 | 1000 / 2200 | 3 | 2 | 2 | 900 / 2000 | 3 | 3 | 3 | 500 / 1100 | 3 | 2 | 2 |
| 4000 and above | 1000 / 2200 | 3 | 2 | 3 | 900 / 2000 | 3 | 3 | 3 | 500 / 1100 | 3 | 2 | 2 |
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 ( 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 1.05.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
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: |
|
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 TWO PAIRS OF SPOILERS
ARE INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| 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 | 1400 / 3100 | 3 | 1 | 1 | 1400 / 3100 | 4 | 3 | 3 | 1000 / 2300 | 4 | 2 | 2 |
| 2000 | 1000 / 2300 | 3 | 2 | 2 | 1000 / 2300 | 3 | 2 | 2 | 1200 / 2700 | 4 | 3 | 3 |
| 2500 | 1000 / 2300 | 2 | 1 | 1 | 800 / 1800 | 3 | 2 | 2 | 1000 / 2300 | 4 | 3 | 3 |
| 3000 | 800 / 1800 | 3 | 2 | 2 | 800 / 1800 | 4 | 3 | 3 | 600 / 1400 | 5 | 4 | 4 |
| 3500 | 800 / 1800 | 4 | 3 | 3 | 600 / 1400 | 4 | 3 | 3 | 400 / 900 | 4 | 3 | 3 |
| 4000 and above | 800 / 1800 | 4 | 3 | 3 | 600 / 1400 | 4 | 4 | 4 | 200 / 500 | 0 | 1 | 1 |
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 ( 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 1.15.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
Takeoff performance computation:
The takeoff 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 1.05.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1.
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
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: |
|
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 TWO PAIRS OF SPOILERS
ARE INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| 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 | 1400 / 3000 | 3 | 2 | 2 | 1000 / 2200 | 4 | 3 | 3 | 1000 / 2200 | 4 | 2 | 2 |
| 2000 | 1000 / 2200 | 3 | 2 | 2 | 800 / 1700 | 3 | 2 | 2 | 1200 / 2600 | 4 | 3 | 3 |
| 2500 | 800 / 1700 | 2 | 1 | 1 | 800 / 1700 | 3 | 2 | 2 | 1000 / 2200 | 3 | 2 | 2 |
| 3000 | 800 / 1700 | 4 | 3 | 3 | 800 / 1700 | 4 | 3 | 3 | 800 / 1700 | 4 | 3 | 3 |
| 3500 | 800 / 1700 | 4 | 3 | 3 | 600 / 1300 | 5 | 4 | 4 | 400 / 800 | 4 | 3 | 3 |
| 4000 and above | 800 / 1700 | 5 | 3 | 3 | 800 / 1700 | 4 | 6 | 6 | 200 / 400 | 0 | 2 | 2 |
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 ( 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.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
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: |
|
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 TWO PAIRS OF SPOILERS
ARE INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| 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 | 1400 / 3000 | 3 | 1 | 1 | 1300 / 2800 | 3 | 1 | 1 | 1300 / 2800 | 2 | 1 | 1 |
| 2000 | 1900 / 4100 | 2 | 0 | 0 | 1300 / 2800 | 1 | 0 | 0 | 1000 / 2200 | 1 | 0 | 0 |
| 2500 | 1000 / 2200 | 2 | 1 | 1 | 1200 / 2600 | 2 | 1 | 1 | 1100 / 2400 | 2 | 1 | 1 |
| 3000 | 1300 / 2800 | 4 | 4 | 4 | 1300 / 2800 | 4 | 3 | 3 | 1000 / 2200 | 4 | 3 | 3 |
| 3500 | 1700 / 3700 | 7 | 6 | 6 | 1000 / 2200 | 4 | 3 | 3 | 900 / 1900 | 5 | 3 | 3 |
| 4000 and above | 900 / 1900 | 4 | 2 | 2 | 900 / 1900 | 4 | 3 | 3 | 800 / 1700 | 5 | 3 | 3 |
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 ( 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 1.10.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
Takeoff performance computation:
The takeoff 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 1.10.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1
| 27-64-04A | Spoilers 1 and 2 |
|---|
Applicable to: -
- Flight preparation/limitations
Takeoff performance computation:
The takeoff 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.
- During cockpit preparation
- SEC 3 pb-swOFF
- FLIGHT CONTROLS/SEC3/SPLY (121VU Q19) C/BPull
- In flight
In the case of further failure of SEC 1 and SEC 2:
- Autoland is not permitted.
- Disengage the AP at 500 ft RA before landing in direct law. As soon as the AP is disengaged when the three SECs are failed, it cannot be engaged again.
- Maximum landing capability is CAT 1