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Airbus 320 AZUL > LIMITATIONS > Flashcards

LIMITATIONS Flashcards

1
Q

FLIGHT MANEUVERING LOAD ACCELERATION LIMITS

A

Clean configuration……………-1 g to +2.5 g

Other configurations………. 0 g to +2 g

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2
Q

RUNWAY ALTITUDE

A

Runway altitude….9.200 ft

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3
Q

Maximum tailwind for takeoff

A

15 kt

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4
Q

Maximum certified crosswind for takeoff..

A

35 kt (gust included)

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5
Q

Maximum tailwind for landing

A

10 Kt

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6
Q

The maximum wind for passenger door operation is

A

65 k

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7
Q

The maximum wind for FWD and AFT cargo door operation is

A

40 kt (or 50 kt, if the aircraft nose is into the wind, or if the FWD and AFT cargo doors are on the leeward side)

‐ The FWD and AFT cargo doors must be closed before the wind speed exceeds 65 kt

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8
Q

ALTITUDE LIMITATIONS FOR LANDING ON PFC/GROOVED WET RUNWAYS

A

Landing distance reduction associated with Porous Friction Course (PFC)/Grooved wet runways is
applicable only if runway pressure altitude is below 4 000 ft.

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9
Q

COCKPIT WINDOW OPEN MAXIMUM SPEED

A

200 kt

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10
Q

A 321 FLAPS SPEED

A

0 VMO / MMO CRUISE
1 243 kt HOLDING 1
1 + F 225 kt TAKEOFF
2 2 215 kt TAKEOFF/APPROACH
3 3 195 kt TAKEOFF/APPROACH/LANDING
FULL FULL 186 kt LANDING

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11
Q

A 320 FLAPS SPEED

A

0 VMO/MMO CRUISE
1 230 kt HOLDING 1
1 + F 215 kt TAKEOFF
2 2 200 kt TAKEOFF/APPROACH
3 3 185 kt TAKEOFF/APPROACH/LANDING
FULL FULL 177 kt LANDING

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12
Q

MAXIMUM OPERATING SPEED VMO/MMO

A

VMO……………………………………………………………………………………………………………………………. 350 kt
MMO………………………………………………………………………………………………………………………….. M 0.82

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13
Q

MAXIMUM SPEEDS WITH THE LANDING GEAR EXTENDED

A

Maximum speed with the landing gear extended (VLE)…………………………………………..280 kt /M 0.67
Maximum speed at which the landing gear may be extended (VLO extension) …………. 250 kt /M 0.60
Maximum speed at which the landing gear may be retracted (VLO retraction) ………….. 220 kt /M 0.54

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14
Q

MAXIMUM TIRE SPEED

A

Maximum ground speed………………………………………………………………………………………………… 195 kt

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15
Q

MINIMUM CONTROL SPEED FOR LANDING (VMCL)

A

VMCL………………………………………………………………………………………………………………………. 116 kt

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16
Q

WIPERS MAXIMUM OPERATING SPEED

A

230 KT

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17
Q

WEIGHT LIMITATIONS

A

Maximum taxi weight…………………………………………………………………………….. 77 400 kg (170 637 lb)
Maximum takeoff weight (brake release)………………………………………………….. 77 000 kg (169 755 lb)
Maximum landing weight……………………………………………………………………….. 67 400 kg (148 591 lb)
Maximum zero fuel weight………………………………………………………………………64 300 kg (141 757 lb)
Minimum weight………………………………………………………………………………………40 600 kg (89 508 lb)

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18
Q

WEIGHT LIMITATIONS
(PR-YRD, PR-YRE, PR-YRH, PR-YRI, PR-YRJ, PR-YRK, PR-YRT, PR-YRU, PR-YYA, PR-YYB, PR-YYC, PR-YYD, PR-YYE,
PR-YYF, PR-YYG, PR-YYH, PR-YYI, PR-YYJ, PR-YYK, PR-YYL)

A

Maximum taxi weight…………………………………………………………………………….. 79 400 kg (175 047 lb)
Maximum takeoff weight (brake release)………………………………………………….. 79 000 kg (174 165 lb)
Maximum landing weight……………………………………………………………………….. 67 400 kg (148 591 lb)
Maximum zero fuel weight………………………………………………………………………64 300 kg (141 757 lb)
Minimum weight………………………………………………………………………………………40 600 kg (89 508 lb

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19
Q

WEIGHT LIMITATIONS (PR-YJA, PR-YJB, PR-YJC, PR-YJD, PR-YJE, PR-YJF)

A

Maximum taxi weight…………………………………………………………………………….. 93 900 kg (207 014 lb)
Maximum takeoff weight (brake release)………………………………………………….. 93 500 kg (206 132 lb)
Maximum landing weight……………………………………………………………………….. 79 200 kg (174 606 lb)
Maximum zero fuel weight………………………………………………………………………75 600 kg (166 669 lb)
Minimum weight……………………………………………………………………………………. 46 600 kg(102 736 lb)

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20
Q

APU BLEED USE WITH HP AIR START UNIT

A

The flight crew must not use bleed air from the APU BLEED and from the HP Air Start Unit at the
same time, to prevent any adverse effect on the Bleed Air System

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21
Q

CABIN PRESSURE

A

Maximum positive differential pressure………………………………………………………………………….. 9.0 PSI
Maximum negative differential pressure…………………………………………………………………………-1.0 PSI
Safety relief valve setting…………………………………………………………………………………………….. 8.6 PSI

22
Q

AUTO PILOT

A

At takeoff 100 ft AGL and at least 5 s after liftoff

In approach with FINAL APP, V/S or FPA mode 250 ft AGL

In circling approach 500 ft AGL for aircraft category C (600 ft AGL for
aircraft category D).

ILS/MLS approach when CAT1 is displayed on the FMA 160 ft AGL

ILS/MLS approach when CAT2 or CAT3 (single or dual) is
displayed on the FMA is 0 ft AGL if autoland

After a manual go-around 100 ft AGL

In all other phases 500 ft. The AP or FD in OP DES or DES mode can be used in approach. However, its use is only permitted if the FCU selected
altitude is set to, or above, the higher of the two: MDA/MDH or 500 ft AGL

23
Q

ILS CATEGORY II

A

Minimum decision height…100 ft

At least one autopilot must be engaged in APPR mode, and CAT 2 or CAT 3 SINGLE or CAT 3
DUAL must be displayed on the FMA.
For manual landing, AP should be disconnected no later than 80 ft AGL

24
Q

MAXIMUM WIND CONDITIONS FOR ILS/MLS  CAT II OR CAT III AND FOR GLS  CAT I

airbus 321

A

Headwind : 15 kt
Tailwind : 10 kt
Crosswind : 10 kt

25
Q

MAXIMUM WIND CONDITIONS FOR ILS/MLS  CAT II OR CAT III AND FOR GLS  CAT I

airbus 320

A

Headwind : 30 kt
Tailwind : 10 kt
Crosswind : 20 kt (15 kt for automatic rollout with OEI)

26
Q

APU START

A

After three consecutive APU start attempts, the flight crew must wait 60 min before a new start
attempt

27
Q

APU START/SHUTDOWN DURING REFUELING/DEFUELING

A

During refuel/defuel procedures, APU starts or shutdown are permitted with the following restrictions:
‐ If the APU failed to start or following an automatic APU shutdown, do not start the APU
‐ If a fuel spill occurs, perform a normal APU shutdown.

28
Q

APU LIMITATIONS

A

START & ELEC POWER = NO LIMITATION

Max altitude to assist engine start=20.000ft

Max altitude for air conditioning and pressurization (single pack operation)=20.000ft

Max altitude for air conditioning and pressurization (dual pack operation)= 15.000ft.

Use of APU bleed air for wing anti-ice= NOT PERMMIT.

29
Q

OIL QUANTITY

A

The minimum oil quantity is the highest value of:
‐ 10.6 qt, or
‐ 8.9 qt + estimated consumption.
Maximum estimated consumption = 0.45 qt/h.

30
Q

STARTER

A

‐ A standard automatic start that includes up to three start attempts, is considered one cycle
‐ For ground starts (automatic or manual), a 60 s pause is required between successive cycles
‐ A 15 min cooling period is required, subsequent to three failed cycles
‐ The starter must not be run when N2 is above 63 %

31
Q

MAXIMUM ALTITUDE FLAPS/SLATS EXTENDED

A

Maximum operating altitude with slats and/or flaps extended…………………………………………..20 000 ft

32
Q

FUEL IMBALANCE AT TAKEOFF

A

Tank Fuel Quantity (Heavier Tank) Maximum Asymmetry
Full 500 kg (1 102 lb)
3 000 kg (6 613 lb) 1 050 kg (2 314 lb)
1 450 kg (3 196 lb) 1 450 kg (3 196 lb)

33
Q

FUEL IMBALANCE IN FLIGHT AND AT LANDING

A

Tank Fuel Quantity (Heavier Tank) Maximum Asymmetry
Full 1 500 kg (3 306 lb)
4 300 kg (9 479 lb) 1 600 kg (3 527 lb)
2 250 kg (4 960 lb) 2 250 kg (4 960 lb)

34
Q

OUTER TANKS

A

Maximum Asymmetry 690 kg (1 521 lb)

35
Q

MAXIMUM ALLOWED FUEL IMBALANCE AIRBUS 321

A

Tank Fuel Quantity (Heavier Tank) Maximum Asymmetry
Full 400 kg (882 lb)
3 000 kg (6 614 lb) 400 kg (882 lb)
700 kg (1 543 lb) 700 kg (1 543 lb)

36
Q

FUEL IMBALANCE IN FLIGHT AND AT LANDING AIRBUS 321

A

Tank Fuel Quantity(Heavier Tank) Maximum Asymmetry
Full 1 320 kg (2 910 lb)
4 000 kg (8 818 lb) 1 450 kg (3 196 lb)
2 350 kg (5 180 lb) 2 350 kg (5 180 lb)

37
Q

MINIMUM FUEL QUANTITY FOR TAKEOFF

A

Minimum fuel quantity for takeoff…………………………………………………………………..1 500 kg

38
Q

DEFINITION OF ICING CONDITIONS

A

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)

39
Q

DEFINITION OF SEVERE ICE ACCRETION

A

Ice accretion is considered severe when the ice accumulation on the airframe reaches approximately
5 mm (0.2 in) thick or more

40
Q

RAIN REPELLENT

A

The flight crew should only use the rain repellent in the case of moderate to heavy rain

41
Q

BRAKE TEMPERATURE

A

Maximum brake temperature for takeoff (brake fans  off)….300 °C
BRAKE FANS ON…….150 C

42
Q

TAXI WITH DEFLATED OR DAMAGED TIRES

A

‐ 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
‐ For the nosewheel steering (NWS) angle
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.

43
Q

IR GROUND ALIGNMENT

A

Ground alignment of the IRS is possible in latitudes between 73 ° North and 73 ° South

44
Q

Takeoff is not recommended on the following runway conditions:

A

‐ Wet ice
‐ Water on top of Compacted Snow
‐ Dry Snow or Wet Snow over Ice

45
Q

AVIONICS VENTILATION

A

OAT ≤ 49 °C No limitation
49 °C < OAT ≤ 55 °C 2 h
55 °C < OAT ≤ 60 °C 1 h
60 °C < OAT ≤ 64 °C 0.5 h

46
Q

DEGRADED SITUATION GPS

A

If GPS PRIMARY LOST is displayed on the PFD, the navigation accuracy remains sufficient
for RNP operations provided that, the RNP value is checked or entered on the MCDU and HIGH
ACCURACY is displayed.

47
Q

ENGINE TEMPERATURES

A

MAX EGT

Start (ground) 750 C
Start (in flight) 875 C

TO & GA 1060 C
MCT 1025

48
Q

OIL TEMP

A

Maximum continuous temperature…140 °C

Maximum transient temperature(15 min) 155 °C

Minimum starting temperature… -40 °C

Minimum temperature before takeoff… 19 °C

49
Q

FLEX TAKEOFF

A

FLEX takeoff is not permitted on contaminated runways.

50
Q

SOFT GO-AROUND

A

The use of soft go-around is prohibited with one engine inoperative

51
Q

SHAFT SPEEDS MAX N1 & N2 %

A

Maximum N1 = 101 %
Maximum N2 = 116.5 %

Airbus 320 AZUL (3 decks)

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