LIMITACIONES A320 JS

RUNWAY SLOPE. ±2 %. ±3 %. ±1 %. ±1.75 %.

RUNWAY ALTITUDE. 14 100 ft. 8 900 ft. 15 000 ft. 39 800 ft.

NOMINAL RUNWAY WIDTH. 45 m 30 m. 60 m 30 m. 45 m 25 m. 40 m 35 m.

WIND FOR TAKEOFF AND LANDING crosswind (takeoff and landing). 38 kt (gust included). 40 kt (gust included). 35 kt (gust included). 20 kt (gust included).

TAILWIND TAKEOFF. 15 kt. 20 kt. 10 kt. 25 kt.

TAILWIND LANDING. 15 kt. 10 kt. 20 kt. 25 kt.

For landing with a tailwind greater than 10 kt. FLAPS FULL is recommended. FLAPS 3 is recommended. FLAPS 3 only. FLAPS FULL only.

The maximum wind for passenger door operation is. 65 kt. 60 kt. 38 kt. 66 kt.

The FWD and AFT cargo doors must be closed before the wind speed exceeds. 65 kt. 60 kt. 66 kt. 68 kt.

COCKPIT WINDOW OPEN MAXIMUM SPEED. 200 kt. 210 kt. 230 kt. 195 kt.

MAXIMUM FLAPS/SLATS SPEEDS FLAPS 1. 230 kt. 215 kt. 200 kt. 185 kt.

MAXIMUM FLAPS/SLATS SPEEDS FLAPS 1 + F. 215 kt. 230 kt. 200 kt. 216 kt.

MAXIMUM FLAPS/SLATS SPEEDS FLAPS 2. 200 kt. 210 kt. 215 kt. 185 kt.

MAXIMUM FLAPS/SLATS SPEEDS FLAPS 3. 185 kt. 200 kt. 215 kt. 177 kt.

The maximum wind for FWD and AFT cargo door 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 leeward side). 45 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). 40 kt (or 55 kt, if the aircraft nose is into the wind, or if the FWD and AFT cargo doors are on the leeward side). 45 kt (or 55 kt, if the aircraft nose is into the wind, or if the FWD and AFT cargo doors are on the leeward side).

MAXIMUM FLAPS/SLATS SPEEDS FLAPS FULL. 177 kt. 215 kt. 230 kt. 200 kt.

MAXIMUM OPERATING SPEED VMO/MMO. 350 kt M 0.82. 360 kt M 0.82. 350 kt M 0.81. 300 kt M 0.80.

Maximum speed with the landing gear extended (VLE). 280 kt /M 0.67. 250 kt /M 0.60. 230 kt /M 0.54.

Maximum speed at which the landing gear may be extended (VLO extension). 250 kt /M 0.60. 280 kt /M 0.67. 230 kt /M 0.54.

Maximum speed at which the landing gear may be retracted (VLO retraction). 250 kt /M 0.60. 280 kt /M 0.67. 230 kt /M 0.54.

MAXIMUM TIRE SPEED. 190 kt. 195 kt. 200 kt. 197 kt.

MINIMUM CONTROL SPEED FOR LANDING (VMCL). 115 kt / 116 kt. 110 kt / 110 kt. 111 kt / 118 kt. 120 kt / 130 kt.

WIPERS MAXIMUM OPERATING SPEED. 230 kt. 240 kt. 220 kt. 237 kt.

Maximum taxi weight. 77 400 kg (170 637 lb). 77 000 kg (169 755 lb). 67 400 kg (148 591 lb). 64 300 kg (141 757 lb). 40 300 kg (88 847 lb).

Maximum takeoff weight (brake release). 77 400 kg (170 637 lb). 77 000 kg (169 755 lb). 67 400 kg (148 591 lb). 64 300 kg (141 757 lb). 40 300 kg (88 847 lb).

Maximum landing weight. 77 400 kg (170 637 lb). 77 000 kg (169 755 lb). 67 400 kg (148 591 lb). 64 300 kg (141 757 lb). 40 300 kg (88 847 lb).

Maximum zero fuel weight. 77 400 kg (170 637 lb). 77 000 kg (169 755 lb). 67 400 kg (148 591 lb). 64 300 kg (141 757 lb). 40 300 kg (88 847 lb).

Minimum weight. 77 400 kg (170 637 lb). 77 000 kg (169 755 lb). 67 400 kg (148 591 lb). 64 300 kg (141 757 lb). 40 300 kg (88 847 lb).

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. 25 min without air conditioning supply. The lack of fresh air supply will significantly reduce the cabin’s air quality. 33 min without air conditioning supply. The lack of fresh air supply will significantly reduce the cabin’s air quality. 15 min without air conditioning supply. The lack of fresh air supply will significantly reduce the cabin’s air quality.

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

AVIONICS VENTILATION // OAT ≤ 49 °C. No limitation. 2 h. 1 h. 0.5 h.

AVIONICS VENTILATION // 49 °C < OAT ≤ 55 °C. No limitation. 2 h. 1 h. 0.5 h.

AVIONICS VENTILATION // 60 °C < OAT ≤ 64 °C. No limitation. 2 h. 1 h. 0.5 h.

AVIONICS VENTILATION // 55 °C < OAT ≤ 60 °C. No limitation. 2 h. 1 h. 0.5 h.

Maximum positive differential pressure. 9.0 PSI. -1.0 PSI. 8.6 PSI.

Maximum negative differential pressure. 9.0 PSI. -1.0 PSI. 8.6 PSI.

Safety relief valve setting. 9.0 PSI. -1.0 PSI. 8.6 PSI.

AUTOPILOT FUNCTION At takeoff. 250 ft AGL and at least 5 s after liftoff. 160 ft AGL and at least 5 s after liftoff. 100 ft AGL and at least 5 s after liftoff. 200 ft AGL and at least 5 s after liftoff.

AUTOPILOT FUNCTION In approach with F-G/S  mode. 200 ft AGL. 250 ft AGL. 100 ft AGL. 160 ft AGL.

AUTOPILOT FUNCTION In approach with FINAL APP, V/S or FPA mode. 200 ft AGL. 250 ft AGL. 100 ft AGL. 160 ft AGL.

In circling approach. 200 ft AGL. 1000 ft AGL for aircraft category C (600 ft AGL for aircraft category D). 250 ft AGL for aircraft category C (600 ft AGL for aircraft category D). 500 ft AGL for aircraft category C (600 ft AGL for aircraft category D).

AUTOPILOT FUNCTION ILS/MLS  approach when CAT1 is displayed on the FMA. 160 ft AGL. 50 ft AGL if autoland. 260 ft AGL. 0 ft AGL if autoland.

AUTOPILOT FUNCTION LS/MLS  approach when CAT2 or CAT3 SINGLE or CAT3 DUAL is displayed on the FMA. 160 ft AGL. 0 ft AGL if autoland. 50 ft AGL.

AUTOPILOT FUNCTION GLS  approach when CAT1 is displayed on the FMA. 250 ft AGL. 0 ft AGL if autoland. 160 ft AGL.

AUTOPILOT FUNCTION GLS  approach when AUTO LAND is displayed on the FMA. 200 ft AGL. 0 ft AGL if autoland. 160 ft AGL. 0 ft AGL if autoland.

AUTOPILOT FUNCTION LPV approach (with SLS  ) when APPR1 is displayed on the FMA. 160 ft AGL. 0 ft AGL if autoland. 250 ft AGL.

AUTOPILOT FUNCTION After a manual go-around. 200 ft AGL. 100 ft AGL. 160 ft AGL.

AUTOPILOT FUNCTION In all other phases. 160 ft AGL. 100 ft AGL. 500 ft AGL. 250 ft AGL. 200 ft AGL.

ILS CATEGORY II Minimum decision height. 100 ft. 50 ft. 80 ft. 160 ft.

ILS CATEGORY III FAIL PASSIVE (SINGLE) Minimum decision height. 100 ft. 50 ft. 80 ft. 160 ft.

ILS CATEGORY III FAIL OPERATIONAL (DUAL) Alert height. 100 ft AGL. 75 ft AGL. 150 ft AGL. 200 ft AGL.

ILS CATEGORY III FAIL OPERATIONAL (DUAL) CAT III without DH: Minimum Runway Visual Range. 100 ft AGL. 75 ft AGL. 150 ft AGL. 200 ft AGL.

MAXIMUM WIND CONDITIONS FOR ILS/MLS  CAT II OR CAT III AND FOR GLS  CAT I. Headwind : 20 kt Tailwind : 30 kt Crosswind : 10 kt (15 kt for automatic rollout with OEI). Headwind : 30 kt Tailwind : 10 kt Crosswind : 20 kt (15 kt for automatic rollout with OEI). Headwind : 10 kt Tailwind : 20 kt Crosswind : 30 kt (15 kt for automatic rollout with OEI).

APU START After _____ consecutive APU start attempts, the flight crew must wait _______ min before a new start attempt. 3 // 60 Min. 3 //30 Min. 5 // 60 Min. 5 // 30 Min.

ROTOR SPEED Maximum N speed. 107 %. 109 %. 106 %. 108 %.

EGT Maximum EGT for APU start (below 35 000 ft). 1 090 °C. 1 120 °C. 675 °C.

EGT Maximum EGT for APU start (above 35 000 ft). 1 090 °C. 1 120 °C. 675 °C.

EGT Maximum EGT for APU running. 1 090 °C. 1 120 °C. 675 °C.

APU BLEED Max altitude to assist engine start. 22 500 ft. 20 000 ft. 15 000FT.

APU BLEED Max altitude for air conditioning and pressurization (single pack operation). 22 500 ft. 20 000 ft. 15 000 ft.

APU BLEED Max altitude for air conditioning and pressurization (dual pack operation). 22 500 ft. 20 000 ft. 15 000 ft.

Use of APU bleed air for wing anti-ice is. not permitted. permitted.

THRUST SETTING/EGT LIMITS Takeoff(1) and Go-around All engines operative. 5 min // 1 083 °C. 10 min // 1 083 °C. 5 min // 1 043 °C. Not limited // 610 °C.

THRUST SETTING/EGT LIMITS Takeoff(1) and Go-around One engine inoperative. 5 min // 1 083 °C. 10 min // 1 083 °C. 5 min // 1 043 °C. Not limited // 610 °C.

Maximum Continuous Thrust (MCT). 5 min // 1 083 °C. 10 min // 1 083 °C. 5 min // 1 043 °C. Not limited // 610 °C.

THRUST SETTING/EGT LIMITS // Starting On ground. 1 083 °C. 1 043 °C. Not limited.

THRUST SETTING/EGT LIMITS // Starting In flight. 1 083 °C. 1 043 °C. Not limited.

ENGINES SHAFT SPEEDS // Maximum N1 in normal operation. 100 %. 105 %. 107 %.

ENGINES SHAFT SPEEDS // Maximum N2 in normal operation. 100 %. 105 %. 107 %.

ENGINES SHAFT SPEEDS // Maximum N2 permitted. 100 %. 105 %. 107 %.

ENGINES OIL TEMPERATURE // Maximum temperature. 165 °C. 151 °C. 141 °C.

ENGINES OIL TEMPERATURE // Minimum starting temperature. -40 °C. -50 °C. -30 °C. -45 °C.

ENGINES OIL TEMPERATURE // Minimum temperature before takeoff. 52 °C. 60 °C. 40 °C. 51 °C.

ENGINES OIL QUANTITY // OAT below -30 °C. 16.5 qt. 18.5 qt. 14.5 qt. 15.5 qt.

ENGINES MINIMUM OIL PRESSURE // Minimum oil pressure. 65 PSI. 270 PSI. 60 PSI. 55 PSI.

ENGINES MAXIMUM OIL PRESSURE // Maximum oil pressure. 65 PSI. 270 PSI. 60 PSI. 55 PSI.

ENGINES STARTER // A standard automatic start that includes up to ____ start attempts, is considered one cycle. 2. 4. 5. 3.

ENGINES STARTER // For ground starts (automatic or manual), a ____ s pause is required between successive cycles. 35 s. 40 s. 30 s. 55 s.

ENGINES STARTER A _____ min cooling period is required, subsequent to ____ failed cycles, or _____ min of continuous or cumulated crank. 15min // 3 cycles // 15 min. 20min // 3 cycles // 20 min. 10min // 2 cycles // 15 min. 15min // 3 cycles // 10 min.

ENGINES STARTER The starter must not be run when N2 is above ____ %. 20 %. 25 %. 30 %. 15 %.

ENGINES REVERSE THRUST // Maximum reverse should not be used below ____ kt. Idle reverse is permitted down to aircraft stop. 70 kt. 60 kt. 80 kt. 75 kt.

SOFT GO-AROUND // The use of GA SOFT mode is ____ with one engine inoperative. prohibited. permitted.

MAXIMUM ALTITUDE FLAPS/SLATS EXTENDED. 20 000 ft. 22 500 ft. 15 000 ft. 25 000 ft.

FUEL TEMPERATURE // JET A1 MINI. -43 °C. 55 °C. -40 °C. 50 °C.

FUEL TEMPERATURE // JET A1 MAXI. -43 °C. 55 °C. -40 °C. 50 °C.

FUEL IMBALANCE AT TAKEOFF // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) 3 000 kg (6 613 lb). 500 kg (1 102 lb). 1 050 kg (2 314 lb). 1 450 kg (3 196 lb).

FUEL IMBALANCE AT TAKEOFF // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) FULL -. 500 kg (1 102 lb). 1 050 kg (2 314 lb). 1 450 kg (3 196 lb).

FUEL IMBALANCE AT TAKEOFF // OUTER TANKS (INNER TANKS BALANCED) Maximum Asymmetry. 370 kg (815 lb). 380 kg (815 lb). 360 kg (815 lb).

FUEL IMBALANCE AT TAKEOFF // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) 1 450 kg (3 196 lb). 500 kg (1 102 lb). 1 050 kg (2 314 lb). 1 450 kg (3 196 lb).

FUEL IMBALANCE IN FLIGHT AND AT LANDING // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) 4 300 kg (9 479 lb). 1 600 kg (3 527 lb). 1 500 kg (3 306 lb). 2 250 kg (4 960 lb).

FUEL IMBALANCE IN FLIGHT AND AT LANDING // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) FULL. 1 600 kg (3 527 lb). 1 500 kg (3 306 lb). 2 250 kg (4 960 lb).

FUEL IMBALANCE IN FLIGHT AND AT LANDING // INNER TANKS (OUTER TANKS BALANCED) (((Tank Fuel Quantity (Heavier Tank) // Maximum Asymmetry))) 2 250 kg (4 960 lb). 1 600 kg (3 527 lb). 1 500 kg (3 306 lb). 2 250 kg (4 960 lb).

FUEL IMBALANCE IN FLIGHT AND AT LANDING // INNER TANKS (OUTER TANKS BALANCED) Maximum Asymmetry. 690 kg (1 521 lb). 680 kg (1 521 lb). 670 kg (1 521 lb).

MINIMUM FUEL QUANTITY FOR TAKEOFF. 1 500 kg (3 307 lb). 1 600 kg (3 307 lb). 2 000 kg (3 307 lb). 1 800 kg (3 307 lb).

Maximum brake temperature for takeoff (brake fans  off). 300 °C. 350 °C. 150 °C. 310 °C.

Maximum NWS angle. ±85 °. ±95 °. ±75 °. ±90 °.

‐ If maximum one tire per gear is deflated (consider three gears) Maximum taxi speed during turn. 7 kt. 3 kt. 10 kt.

‐ If two tires are deflated on the same main gear (maximum one main gear) Maximum taxi speed. 3 kt. 7 kt. 10 kt.

TAXI WITH DEFLATED OR DAMAGED TIRES ‐ For the nosewheel steering (NWS) angle Maximum NWS angle. 30 °. 35 °. 40 °. 60 °.

MINIMUM FLIGHT CREW OXYGEN PRESSURE. 800 PSI. 780 PSI. 800 PSI. 800 PSI.

Minimum Bottle Pressure to Cover: During emergency descent for all flight crewmembers and observers for _____ min. 22 min. 15 min. 20 min. 98 min.

Minimum Bottle Pressure to Cover: During cruise at FL 100 for two flight crewmembers for _____ min. 98 min. 99 min. 97 min. 96 min.

• Protection against smoke with 100 % oxygen for all flight crewmembers and observers during ______ min at 8 000 ft cabin altitude. 15 min. 25 min. 20 min. 22 min.

FUEL ON BOARD FOB after refueling // Abnormal difference above // Up to 6 t (13 200 lb). 400 kg (900 lb). 500 kg (1 100 lb). 600 kg (1 300 lb).

FUEL ON BOARD FOB after refueling // Abnormal difference above // Between 6 t (13 200 lb) and 12 t (26 500 lb). 400 kg (900 lb). 500 kg (1 100 lb). 600 kg (1 300 lb).

FUEL ON BOARD FOB after refueling // Abnormal difference above // More than 12 t (26 500 lb). 400 kg (900 lb). 500 kg (1 100 lb). 600 kg (1 300 lb).