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Static Thrust at Sea Level
- Take-off (5 min)** 13 300 daN (29,900 lb) 14 055 daN (31,600 lb)
(Flat rated 30°C)
Maximum Continuous 11 988 daN (26,950 1b) 11 988 daN (26,950 lb)
(Flat rated 25°C)
Maximum Engine Speed
- N1 rpm (%) 5,650 (100) 5,650 (100)
- N2 rpm (%) 14,950 (100) 14,950 (100)
Maximum Gas Temperature (°C)
- Take-off (5 min)** 645 645
- Max Continuous 610 610
- Starting * 650 650
Maximum Oil Temperature
(Supply Pump Inlet; °C)
- Take-off, Stabilized 155 155
- Transient (15 min max) 165 165
Min. Press. (PSI) 60 60
Approved Oils See Doc IAE 0043 Sec 4.9 See Doc IAE 0043 Sec 4.9
(MIL-L-23699) (MIL-L-23699)
* 4 Consecutive cycles of 2 minutes each.
**10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around)
Airspeed Limits (Indicated Airspeed - IAS - Unless otherwise Stated:
- Maximum Operating Mach - MMO: 0.82
- Maximum Operating Speed - VMO: 350 kt
- Maneuvering Speed VA: - See Chapter 2.0 of the DGAC-approved Flight Manual
- Extended Flaps/Slats Speed - VFE
Configuration Slats/Flaps VFE (Kt)
1 18/0 230** Intermediate Approach
18/10 215** Take-off
2 22/14 205 Take-off and Approach
215*
3 22/21 195 Take-off, Approach, and
Landing
Full 27/25 190 Landing
* See Note 12
** See Note 18
Landing Gear:
- VLE - Extended: 280 Kt/Mach 0.67
- VLO - Extension: 250 kt
- Retraction: 220 kt
Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph)
Minimum Control Speed:
- VMCA (Air): 105 kt
- VMCG (Ground): 102 kt (all config.)
A28NM Page 16 of 22
Maximum Weights:
A321-100:
000 002 003
VARIANT BASIC Mod 24178 Mod 24899
(KG) (LBS) (KG) (LBS) (KG) (LBS)
Max. Take-off Weight 83,000 182,983 83,000 182,983 85,000 187,391
Max. Landing Weight 73,500 162,040 74,500 164,243 74,500 164,243
Max. Zero Fuel Weight 69,500 153,220 70,500 155,424 70,500 155,424
A321-200:
000 001
VARIANT BASIC Mod 28960
(KG) (LBS) (KG) (LBS)
Max. Take-off Weight 89,000 196,210 93,000 205,027
Max. Landing Weight 75,500 166,448 77,800 171,517
Max. Zero Fuel Weight 71,500 157,629 73,800 162,699
Minimum Weight:
VARIANT All
(KG) (LBS)
Minimum Weight 47,500 104,718
Minimum Crew:
2 Pilots
Maximum Passengers:
220
Maximum Baggage:
CARGO COMPARTMENT MAXIMUM LOAD
(KG) (LBS)
Forward 5,670 12,500
Aft 5,670 12,500
Rear (Bulk) 1,497 3,300
For the positions and the loading conditions authorized in each position (references of containers, pallets, and associated
weights), see Weight and Balance Manual, ref. 00E080A0001/C1S Chapter 1.10.
Fuel Capacity (0.8 kg/liter):
A321-100 and A321-200:
3-Tank Airplane
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,500 4,094 22.6 6
(12,400) (27,331) (18) (39.6)
Center 8,200 2,166 23.2 6.1
(6,560) (14,460) (18.6) (40.97)
TOTAL 23,700 6,260 45.8 12.1
(18,960) (41,791) (36.6) (80.62)
A28NM Page 17 of 22
A321-200:
4-Tank Airplane (high pressure ACT system)
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,500 4,094 22.6 6
(12,400) (27,331) (18) (39.6)
Center 8,200 2,166 23.2 6.1
(6,560) (14,460) (18.6) (40.97)
ACT 2,900 766 17 4.5
(2,320) (5,114) (13.6) (29.96)
TOTAL 26,600 7,026 62.8 16.6
(21,280) (46,905) (50.2) (110.58)
4 to 5-Tank Airplane
(low pressure ACT system)
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
TOTAL
3-Tank 23,700 6,260 45.8 12.1
Airplane (18,960) (41,791) (36.6) (80.62)
ACT 1 2,992 790 17 4.5
(2,393) (5,274) (13.6) (29.96)
TOTAL
4-Tank 26,692 7,050 62.8 16.6
Airplane (21,353) (47,065) (50.2) (110.58)
ACT 2 2,992 790 17 4.5
(2,393) (5,274) (13.6) (29.96)
TOTAL
5-Tank 29,684 7,840 79.8 21.1
Airplane (23,746) (52,339) (63.8) (140.54)
Oil Capacity:
CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters).
IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters)
Maximum Operating Altitude:
- 39,800 feet (12,200 m) clean if modification 30748 is embodied.
- 39,100 feet (12,000 m) clean.
- 20,000 feet (6,500 m) Slats/Flaps extended.
Equipment:
The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraft for
certification. Equipment approved for installation are listed in the definition of the reference model and the modification
　
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