Limits Flashcards
Flight Maneuvering Load Acceleration Limits
Clean configuration -1 g to +2.5 g
Other configurations 0 g to +2 g
Environmental Envelope
41450ft
Minimum TAT
Minimum TAT -53 °C
Runway Slope
Runway slope (mean) ±2 %
Runway altitude
Runway altitude 12 500 ft
Nominal Runway Width
Nominal Runway Width 45 m
Maximum demonstrated crosswind
Maximum demonstrated crosswind (takeoff and landing) 40 kt (gust included)
Maximum tailwind for takeoff
Maximum tailwind for takeoff 15 kt
Maximum tailwind for landing
Maximum tailwind for landing at or below 11 000 ft 15 kt
Maximum tailwind for landing above 11 000 ft 10 kt
FLAPS FULL NOTE
For landing with a tailwind greater than 10 kt, FLAPS FULL is recommended.
Wind limitations for passenger and cargo doors operation
The following are the wind limitations for passenger and cargo doors operation:
The maximum wind for passenger door operation is 40 kt (or 50 kt , if the aircraft nose is into the wind).
The maximum wind for FWD and AFT cargo doors operation is 40 kt (or 50 kt , if the aircraft nose is into the wind, or if the FWD and AFT cargo doors are on the downwind side of the aircraft).
The passenger, FWD and AFT cargo doors must be closed before the wind speed exceeds 60 kt.
Maximum Crosswind
Dry
Damp
Wet
Standing water
Maximum Crosswind
Dry …………………… 40kts
Damp …………….… 40kts
Wet ………………..… 40kts
Standing water … 20kts
Cockpit Window Open Maximum Speed
Maximum speed 230 kt
Maximum Flaps/Slats Speeds
1 ……. 240kts
1+F … 215kts
2* ….. 205kts
2 ……. 196kts
3 ……. 186kts
Full … 180kts
Maximum Operating Speed VMO/MMO
.86
330kts
Maximum Speeds with the Landing Gear Extended
Maximum speed with landing gear extended (VLE) 250 kt/0.55
Maximum speed with the landing gear operating - extension and retraction (VLO) 250 kt/0.55
Maximum speed for landing gear gravity extension (VLE/VLO) 200 kt
Maximum Tire Speed
Maximum ground speed 204 kt
Minimum Control Speed Landing
VMCL (IAS) 118 kt
Wipers Maximum Operating Speed
Maximum speed 230 kt
Weight Limitations A330-300 series
Maximum taxi weight …………………………….233 900 kg (515 661 lb)
Maximum takeoff weight (brake release) 233 000 kg (513 676 lb)
Maximum landing weight ………………………187 000 kg (412 264 lb)
Maximum zero fuel weight………………………175 000 kg (385 808 lb)
Minimum weight ……………………………………..121 000 kg (266 760 lb)
Weight Limitations VH-EBA to EBD
Maximum taxi weight ………………………………233 900 kg (515 661 lb)
Maximum takeoff weight (brake release) …233 000 kg (513 676 lb)
Maximum landing weight ………………………..180 000 kg (396 831 lb)
Maximum zero fuel weight ………………………168 000 kg (370 376 lb)
Minimum weight ………………………………………116 000 kg (255 737 lb)
Weight Limitations VH-EBE to EBG, VH-EBJ to EBL
Maximum taxi weight ………………………………233 900 kg (515 661 lb)
Maximum takeoff weight (brake release) …233 000 kg (513 676 lb)
Maximum landing weight …………………………182 000 kg (401 241 lb)
Maximum zero fuel weight ……………………….170 000 kg (374 785 lb)
Minimum weight ……………………………………….116 000 kg (255 737 lb)
Weight Limitations VH-EBM to EBS, VH-EBV
Maximum taxi weight …………………………………238 900 kg (526 684 lb)
Maximum takeoff weight (brake release)…….238 000 kg (524 700 lb)
Maximum landing weight ……………………………182 000 kg (401 241 lb)
Maximum zero fuel weight ………………………….168 000 kg (370 376 lb)
Minimum weight ………………………………………….116 000 kg (255 737 lb)
Without air conditioning supply
With passengers on board, it is not recommended to exceed 20 min without air conditioning supply. The lack of fresh air supply will significantly reduce the cabin’s air quality.
Cabin Pressure
Maximum positive differential pressure 9.25 PSI
Maximum negative differential pressure -1.0 PSI
Safety relief valve setting 8.85 PSI
Packs Use with LP Air Conditioning Unit
The flight crew must not use conditioned air from the packs and from the LP Air Conditioning Unit at the same time, to prevent any adverse effect on the Air Conditioning system.
Maximum Wind Conditions for ILS CAT II or CAT III and for GLS@ CAT I
Headwind : 35 kt
Tailwind : 10 kt
Crosswind : 20 kt
Consecutive APU start attempts
After three consecutive APU start attempts, the flight crew must wait 60 min before a new start attempt.
APU rotor speed
Maximum N speed 107 %
APU EGT limits
Maximum EGT for APU start 1 250 °C
Maximum EGT for APU running 650 °C
APU bleed limits
Max altitude to assist engine start 20 000 ft
Max altitude for air conditioning and pressurization (single pack operation) 22 500 ft
Max altitude for air conditioning and pressurization (dual pack operation) 17 500 ft
Use of APU bleed air for wing anti-ice is not permitted.
Thrust Setting/EGT Limits
Takeoff(1) and Go-around
All engines operative 5 min 975 °C
One engine inoperative 10 min 975 °C
Maximum Continuous Thrust (MCT) Not limited 940 °C
Starting
On ground 750 °C
In flight 975 °C
Shaft Speeds
Maximum N1 115.5 %
Note:
The N1 limit depends on the ambient conditions and on the configuration of the engine air bleed.
These parameters may limit N1 to a value that is less than the above-mentioned N1 value.
Maximum N2 113 %
Oil temp
Maximum continuous temperature 160 °C
Maximum transient temperature (15 min) 175 °C
Minimum starting temperature -40 °C
Oil quantity
Minimum oil quantity 12 qt + estimated consumption
Average estimated consumption = 0.56 qt/h,
Engine operation with engine oil consumption above 0.56 qt/h and up to 0.87 qt/h is allowed, provided that the engine oil consumption enables fulfillment of the mission.
Starter
A standard automatic start that includes up to three start attempts, is considered one cycle
For ground starts (automatic or manual), a 30 s pause per minute of operation is required between successive cycles
A 10 min cooling period is required, subsequent to two failed cycles, before each subsequent cycle
The starter must not be run when N2 is above 30 %
Reverse Thrust
Selection of the reverse thrust is prohibited in flight.
Backing the aircraft with reverse thrust is not permitted.
Maximum reverse should not be used below 70 kt. Idle reverse is permitted down to aircraft stop.
Maximum Altitude Flaps/Slats Extended
Maximum operating altitude with slats and/or flaps extended 20 000 ft
Fuel Temperature
Minimum fuel temperature :
The highest of freezing point +3 °C or -54 °C, in inner tank.
Freezing point in outer or trim tank.
JET A -40 °C
JET A1 -47 °C
Minimum Fuel Quantity for Takeoff
Minimum fuel quantity for takeoff 5 200 kg (11 461 lb)
The ECAM alerts that are related to fuel low level in the wing tanks (FUEL WING TK LO LVL, etc.) must not appear for takeoff.
Definition of Icing Conditions
Icing conditions exist when the OAT (on ground or after takeoff) or the TAT (in flight) is at or below 10 °C and visible moisture in any form is present (such as clouds, fog with visibility of 1 sm (1 600 m) or less, rain, snow, sleet or ice crystals).
Icing conditions also exist when the OAT on the ground and for takeoff is at or below 10 °C and operating on ramps, taxiways or runways where surface snow, standing water or slush may be ingested by the engines, or freeze on engines, nacelles or engine sensor probes.
Brake Temperature
Maximum brake temperature for takeoff (brake fans@ off) 300 °C
Taxi with Deflated or Damaged Tires
To vacate the runway or taxi at low speed with tire(s) deflated (not damaged), all of the following limitations apply:
If maximum one tire per gear is deflated (consider three gears)
Maximum taxi speed during turn 7 kt
If two tires are deflated on the same main gear (maximum one main gear)
Maximum taxi speed 3 kt
Maximum NWS angle 30 °
In addition, if tire damage is suspected, the flight crew must ask for an aircraft inspection prior to vacate the runway or taxi. If the ground crew suspects that a tire burst may damage the landing gear, maintenance action is due.
Turbulence penetration A330-300
M 0.78
260kts above F200
240kts below F200
Turbulence penetration A330-200
M 0.80
260kts above F200
240kts below F200
Barometric reference and altitude indications
The maximum difference is:
±20 ft between both PFDs
And depending on the aircraft configuration:
±60 ft between ISIS and PFDs, or
±300 ft between mechanical standby altimeter and PFDs.
A330-200 CWT residual fuel
A330-200 CWT residual fuel amounts less than or equal to 750 kg are acceptable, provided:
Performance and structural weight limitations are not exceeded.
Fuel in the CWT is considered unusable and remaining fuel is assessed sufficient. If useable fuel is insufficient, ensure the fuel quantity is increased to a sufficient amount.
