TYPE CERTIFICATION DATA SHEET A28NM

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TYPE CERTIFICATION DATA SHEET A28NM

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Rev. No. 5 5 5 5 6 5 5 5
DEPARTMENT OF TRANSPORTATION
FEDERAL AVIATION ADMINISTRATION
A28NM
Revision 6
Airbus
A319 Model -111 A320 Model -111
A319 Model -112 A320 Model -211
A319 Model -113 A320 Model -212
A319 Model -114 A320 Model -214
A319 Model -131 A320 Model -231
A319 Model -132 A320 Model -232
A320 Model -233
A321 Model -111
A321 Model -112
A321 Model -131
A321 Model -211
A321 Model -231
September 18, 2002
TYPE CERTIFICATION DATA SHEET A28NM
This Data Sheet which is part of Type Certificate No. A28NM prescribes conditions and limitations under which the product for
which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.
Type Certificate Holder: Airbus
1, Rond-Point Maurice Bellonte
31707 Blagnac, France
Type Certificate Holder Record Name change from Airbus Industrie to Airbus January 2002
I. Type A319-100 Series Transport Category Airplanes
Model A319-112, Approved August 30, 1996;
Model A319-111, Approved June 20, 1997;
Model A319-113, Approved June 20, 1997;
Model A319-114, Approved June 20, 1997;
Model A319-131, Approved June 20, 1997;
Model A319-132, Approved June 20, 1997;
Engines:
Model A319-111, Two CFMI Model CFM56-5B5 or CFM56-5B5/P jet engines;
Model A319-112, Two CFMI Model CFM56-5B6 or CFM56-5B6/P or CFM56-5B6/2P jet engines;
Model A319-113, Two CFMI Model CFM56-5A4 jet engines;
Model A319-114, Two CFMI Model CFM56-5A5 jet engines;
Model A319-131, Two IAE Model V2522-A5 jet engines;
Model A319-132, Two IAE Model V2524-A5 jet engines;
Fuel:
See Installation Manual - Documents CFM 2026 or IAE-0043
SPECIFICATION
NOMENCLATURE FRANCE U.S.A U.K.
Kerosene MIL-T83133A (JP8)
Air 3405C ASTM D1655 (Jet Al) (Jet A) DERD 2494
Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454
AIR 3407 (TR4) MIL-T 5624 (JP4) DERD 2454
High Flash Point AIR 3404 MIL-T 5624 (JP5) DERD 2452
Additives: See CFMI " Specific Operating Instructions," CMF TPOI-13 or IAE V2500 “Installation and Operating Manual”
IAE-0043, 4. The above mentioned fuels and additives are also suitable for the APU.
A28NM Page 2 of 22
Engine Limits:
CFMI CFM56-5B5 or -
5B5/P
CFMI CFM56-5B6 or -
5B6/P or -5B6/2P
CFMI CFM56-5A4
Engine FAA Data Sheets FAA Data Sheets FAA Data Sheet
Limitation E37NE E38NE E37NE E38NE E28NE
Static Thrust at Sea Level
- Take-off (5 min)** 9 786 daN (22,000 lb) 10 453 daN (23,500 lb) 9 786 daN (22,000 lb)
(Flat rated 30°C)
Maximum Continuous 9 008 daN (20,250 1b) 9 008 daN (20,250 1b) 9 195 daN (20,670 1b)
(Flat rated 25°C)
Maximum Engine Speed
- N1 rpm (%) 5,200 (104) 5,200 (104) 5,100 (102)
- N2 rpm (%) 15,183 (105) 15,183 (105) 15,183 (105)
Max Gas Temperature (°C) Eng. Limit/ ECAM
- Take-off (5 min)** 950 950 915/890
- Max Continuous 915 915 880/855
- Starting * 725 725 725/725
Max Oil Temperature
(supply pump inlet; °C)
- Take-off, Stabilized 140 140 140
- Transient (15 min max) 155 155 155
Min. Press. (PSI) 13 13 13
Approved Oils See SB See SB See SB
CFMI 79-001-0X CFMI 79-001-0X CFMI 79-001-0X
CFMI CFM56-5A5 IAE V2522-A5 IAE V2524-A5
Engine Limitation Data Sheets Data Sheets Data Sheets
E28NE (FAA) E40NE (FAA) E40NE (FAA)
Static Thrust at Sea Level
- Take-off (5 min)** 10 453 daN (23,500 lb) 10 249 daN (23,040 lb) 10 889 daN (24,480 lb)
(Flat rated 30°C)
Maximum Continuous 9 195 daN (20,670 1b) 8 540 daN (19,200 1b) 8 540 daN (19,200 1b)
(Flat rated 25°C)
Maximum Engine Speed
- N1 rpm (%) 5,100 (102) 5,650 (100) 5,650 (100)
- N2 rpm (%) 15,183 (105) 14,950 (100) 14,950 (100)
Max Gas Temperature (°C) Eng. Limit/ ECAM
- Take-off (5 min)** 915/890 645 645
- Max Continuous 880/855 610 610
- Starting * 725/725 650 650
Max Oil Temperature
(supply pump inlet; °C)
- Take-off, Stabilized 140 155 155
- Transient (15 min max) 155 165 165
Min. Press. (PSI) 13 60 60
Approved Oils See SB See Doc IAE 0043 Sec 4.9 See Doc IAE 0043 Sec 4.9
CFMI 79-001-0X (MIL-L-23699) (MIL-L-23699)
* 4 consecutive cycles of 2 minutes each.
** 10 minutes at take-off thrust allowed in case of engine failure (at take off and during go around).
A28NM Page 3 of 22
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 22/15 200 Take-off and
Approach
3 22/20 185 Take-off, Approach, and Landing
Full 27/40 177 Landing
* Auto flap retraction at 210 kt in Take-off configuration.
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)
Maximum Weights:
000 001 002
VARIANT BASIC Mod 25328 Mod 27112
(KG) (LBS) (KG) (LBS) (KG) (LBS)
Max. Take-Off Weight 64,000 141,090 70,000 154,322 75,500 166,447
Max. Landing Weight 61,000 134,480 61,000 134,480 62,500 137,787
Max. Zero Fuel Weight 57,000 125.660 57,000 125,660 58,500 128,969
Minimum Weight:
VARIANT All
Minimum Weight
(KG) (LBS)
35,400 78,042
Minimum Crew:
2 Pilots
Maximum Passengers:
145
Maximum Baggage:
CARGO COMPARTMENT MAXIMUM LOAD
(KG) (LBS)
Forward 2,268 5,000
Aft 3,020 6,660
Rear (Bulk) 1,497 3,300
For the positions and the loading conditions authorized in each position (references of containers, pallets, associated weights),
see Weight and Balance Manual, Ref. 00J080A0001/C1S Chapter 1.10.
A28NM Page 4 of 22
Fuel Capacity (0.8 kg/liter)
3-Tank Airplane
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,609 4,124 58.9 15.6
(12,487) (27,531) (47.1) (103.9)
Center 8,250 2,179 23.2 6.5
(6,600) (14,551) (18.6) (41.0)
TOTAL 23,859 6,303 82.1 20.8
(19,087) (42,082) (65.7) (144.9)
4 to 9-Tank Airplane
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
TOTAL
3-Tank 23,859 6,303 82.1 20.8
Airplane (19,087) (42,082) (65.7) (144.9)
ACT 1 3,121 824 17 4.3
(2,497) (5,505) (13.6) (28.8)
TOTAL
4-Tank 26,980 7,128 99.1 25.1
Airplane (21,584) (47,587) (79.3) (173.7)
ACT 2 3,121 824 17 4.3
(2,497) (5,505) (13.6) (28.8)
TOTAL
5-Tank 30,101 7,952 116.1 29.4
Airplane (24,081) (53,092) (92.9) (202.5)
ACT 3 2,186 577 22 5.6
(1,749) (3,855) (17.6) (37.4)
TOTAL
6-Tank 32,287 8,530 138.1 35.0
Airplane (25,830) (56,947) (110.5) (239.9)
ACT 4 2,186 577 22 5.6
(1,749) (3,855) (17.6) (37.4)
TOTAL
7-Tank 34,473 9,107 160.1 40.6
Airplane (27,579) (60,803) (128.1) (277.3)
ACT 5 3,046 804 12 3.1
(2,437) (5,372) (9.6) (20.6)
TOTAL
8-Tank 37,519 9,912 172.1 43.7
Airplane (30,016) (66,176) (137.7) (297.9)
ACT 6 3,121 824 17 4.3
(2,497) (5,505) (13.6) (28.8)
TOTAL
9-Tank 40,640 10,737 189.1 48.0
Airplane (32,513) (71,681) (151.3) (326.7)
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:
- 41,000 feet (12,600 m) clean if modification 28162 is embodied.
- 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.
A28NM Page 5 of 22
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 modifications applicable to it.
Refer to Type Certification Standard Equipment Lists:
-00J000A0012/C0S for A319-111 Model
-00J000A0004/C0S for A319-112 Model
-00J000A0113/C0S for A319-113 Model
-00J000A0114/C0S for A319-114 Model
-00J000A0131/C0S for A319-131 Model
-00J000A0132/C0S for A319-132 Model
Refer to Note 4 for list of A319 airplane model FAA Type Definitions.
Serial Numbers Eligible:
A319 aircraft, all series, all models, are produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to
Airbus.
A German Export Certificate of Airworthiness endorsed as noted under “Import Requirement,” must be submitted for each
individual aircraft for which application for U.S. certification is made.
Import Requirements:
A FAA Standard Airworthiness Certificate may be issued on the basis of a German Export Certificate of Airworthiness, signed
by a representative of the Luftfahrt-Bundesamt (LBA) of Germany, containing the following statement: “The Airplane covered
by this certificate has been examined, tested, and found to conform to the Type Design approved under Type Certificate No.
A28NM and to be in condition for safe operation.”
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of
manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated
under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections
21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require
certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical
way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type
design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness
Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.
Certification Basis:
a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto.
b.1 Plus the following sections of Part 25 as amended by amendments 25-1 through:
-25-58 (Section 25.812(e))
-25-63 (Section 25.25 (a)(3))
-25-67 (Section 25.807 (c)(7))
(Applied per FAA derivative aircraft policy – reference FAA order 8110.4A)
b.2 Airbus elected to comply with the following sections of Part FAR 25 through Amendment 86:
25.305(d), 25.321(c)/(d), 25.331(a)/(d), 25.333(a)/(c),25.335(d), 25.341,
25.343 (b)(1)(ii), 25.345(a)/(c), 25.349(b), 25.351(b),25.371, 25.373(a),
25.391(e), 25.427, 25.445(a), 25.571(b)(2)/(b)(3), 25.1517.
b.3 Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR
paragraphs 25.562(c)(5), (c)(6) do not apply.
c. Part 34 of the FAR effective Sept. 10, 1990, including amendment 34-1.
d. Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto.
e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the
Federal Register as follows:
(1) January 27, 1989:
- Electronic Flight Controls
- Active Controls
- Engine Controls and Monitoring
- Protection from Lightning and Unwanted Effects of Radio Frequency
- (RF) Energy
- Flight Characteristics
- Flight Envelope Protection
- Side Stick Controllers
- Flight Recorder
A28NM Page 6 of 22
(2) June 9, 1989:
- Computerized AFM
f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and
AC 120-28c.
For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for
automatic landing and by AC 25.1329-1A for cruise.
Use of JAR AWO where applicable to the requirements above, is acceptable.
g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:
- 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected takeoff and landing performance
- 25.783(f) for passenger doors
- 25.807(c) for maximum passenger capacity
- 25.813(a) emergency exit access for a single 13 inch aisle
- 25.933(a), 25.1309(b) for thrust reversing system
- 25.811(e)(3) Type III emergency exit marking.
h. Optional Requirements elected:
- 25.801 for ditching
- 25.1419 for icing
Note 1 - Weight and Balance
a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated
empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,
except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"
contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or
refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage
compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in
the passenger compartment.
b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear
retraction and movement of crew and passengers from their assigned positions.
c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty
weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.
d. System fuel is the weight of all fuel required to fill a lines and tanks up to zero-fuel point on the fuel gauges in the most
critical flight attitude, including the unusable tank fuel as defined by FAR part 25.959. (The usable fuel in the crossfeed
manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct
weight and CG for take-off.)
e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as
defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be
accounted for separately.
f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the
tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only
the usable oil for which the tanks must be placarded.
Note 2:
The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is
considered equivalent to "FAA-approved".)
Note 3:
Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness
Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.
A28NM Page 7 of 22
Note 4:
The A319 basic definition for U.S. import certification is contained in the following documents:
-AI/EA-S 413.0969/96 for A319-111 model
-AI/EA-S 413.1012/96 for A319-112 model
-AI/EA-S 413.3100/96 (Mod 25699 supplement) for A319-112 model
-AI/EA-S 413.2504/96 for A319-113 model
-AI/EA-S 413.2505/96 for A319-114 model
-AI/EA-S 413.0393/97 for A319-131 model
-AI/EA-S 413.0396/97 for A319-132 model
Note 5:
Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89
“Certification Maintenance Requirements (FAA version)” (CMR).
Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/
95A.0252/96 “Airworthiness Limitation Items”. This document is not applicable to the A319 for Corporate Jet
use, but rather Airbus document AI/SE-M2/95A-1038/99 “Airworthiness Limitation Items”.
Note 6:
If modification 25469 or 26968 is embodied on models with CFM engines, the airplane is qualified for CAT III B precision
approach. This does not constitute operational approval.
Note 7:
Modification 25303 (for CFM engine) or 25302 (for IAE engine) are part of the FAA Type Design and shall be implemented on
any A319 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness can be issued.
Note 8:
If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine
denomination changes to /P.
CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.
Note 9:
If Modification 26716 or 26717 is embodied on models with IAE engines, the airplane is qualified for CAT III B precision
approach. This does not constitute operational approval.
Note 10:
The type design definitions and certification standard equipment lists as referenced in Note 4 are complemented by document
00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution” and document 00J000A0067/C0S “A319-111/112
ATC Transponder Type Standard Evolution”.
Note 11:
A319 for Corporate Jet use are defined through the following set of modifications:
- Modification 28238 (0 to 6 ACTs)
- Modification 28162 (extension of flight envelope up to 41,000 ft)
- Modification 28342 (modification of CG limits)
Note 12:
On A319 for Corporate Jet use, the certification of installing up to six Additional Center Tanks (ACT) in bulk version is defined
by modification 28238. The approval together with structural and system provisions was subject of compliance demonstrated to
Advisory Circular AC 25-8.
Note 13:
On A319 for Corporate Jet use, exemptions to the following paragraphs of the FAR have been granted when the airplane is not
operated for hire or for public transport
(Granted APR 9, 2001, Exemption No. 7489):
25.785(h)(2) Flight Attendant seat locations which do not provide for direct view of the cabin
25.807(d)(7) Distance between exits
25.813(e) Installation of Interior Doors in between passenger compartments
A28NM Page 8 of 22
Note 14:
If modification 26610 is embodied on A319-112 airplanes, the engine performance and gaseous emission levels are improved.
The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).
CFM56-5B6/P engine can be intermixed with CFM56-5B6/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft
(AFM Supplement).
II. Type A320-100/200 Series Transport Category Airplanes
Model A320-111, Approved December 15, 1988
Model A320-211, Approved December 15, 1988;
Model A320-231, Approved July 6, 1989;
Model A320-212, Approved November 26, 1990;
Model A320-232, Approved November 12, 1993;
Model A320-233, Approved November 17, 1995;
Model A320-214, Approved December 12, 1996.
Engines:
Model A320-111, Two CFMI Model CFM-56-5A1 jet engines;
Model A320-211, Two CFMI Model CFM-56-5A1 jet engines;
Model A320-212, Two CFMI Model CFM56-5A3 jet engines;
Model A320-214, Two CFMI Model CFM56-5B4 or CFM56-5B4/P or CFM56-5B4/2P jet engines;
Model A320-231, Two IAE Model V2500-A1 jet engines;
Model A320-232, Two IAE Model V2527–A5 jet engines;
Model A320-233, Two IAE Model V2527E–A5 jet engines;
Fuel:
See Installation Manual - Documents CFM 2026 or IAE-0043
SPECIFICATION
NOMENCLATURE FRANCE U.S.A U.K.
Kerosene Air 3405C ASTM D 1655 (JET A1) (JET A) DERD 2494
Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454
Air 3407 (TR4) MIL-T 5624 (JP4) DERD 2454
High Flash Point Air 3404 MIL-T 5624 (JP5) DERD 2452
Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13 or IAE V2500 “Installation and Operation Manual”
IAE-0043, 4.5. The above mentioned fuels and additives are also suitable for the APU.
Engine Limits:
CFMI CFM56-
5A1
CFMI CFM56-
5A3
CFMI CFM56-
5B4 or -5B4/P or
–5B4/2P
IAE V2500-A1 IAE V2527-A5
or V2527E-A5
Engine Limitation Data Sheets Data Sheets Data Sheets Data Sheets Data Sheets
E28NE (FAA) E28NE (FAA) E37NE E38NE FAA E31NE (FAA) E40NE (FAA)
Static Thrust at Sea
Level
- Take-off (5 min)**
(Flat rated 30°C)
11 120 daN
(25,000 lb)
11 787 daN
(26,500 lb)
12 010 daN
(27,000 lb)
11 030 daN
(24,800 lb)
11 030 daN
(24,800 lb)
- Maximum Continuous
(Flat rated 25°C)
10 542 daN
(23,600 lb)
10 542 daN
(23,600 lb)
10 840daN
(24,370 lb)
9 890 daN
(22,240lb)
9 890 daN
(22,240lb)
Maximum Engine
Speed
- N1 rpm (%) 5,100 (102) 5,100 (102) 5,200 (104) 5,465 (100) 5,650 (100)
- N2 rpm (%) 15,183(105) 15,183(105) 15,183(105) 14,915(100) 14,950(100)
Eng. limit/
Max Gas Temp.(°C) ECAM
- Take-off (5 min)** 890 915/890 950 635 645
- Max Continuous 855 880/855 915 610 610
- Starting* 725 725/725 725 635 650
A28NM Page 9 of 22
Maximum Oil Temp.
(Supply Pump Inlet; °C)
-Takeoff, Stabilized 140 140 140 155 155
-Transient
(15 min max)
155 155 155 165 165
Min. Press. (PSI) 13 13 13 60 60
Approved oils See SB See SB See SB See doc IAE See doc IAE
CFMI 79-001-
0X
CFMI 79-001-
0X
CFMI 79-001-0X 0043 (MIL-L
23699)
0043 (MIL-L
23699)
* 4 consecutive cycles of 2 minutes each.
** 10 minute at take-off thrust allowed in case of engine failure (at take-off and 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 22/15 200 Take-off and
Approach
3 22/20 185 Take-off,
Approach, and
Landing
Full 27/35 177 Landing
* Auto flap retraction at 210 kt in Take-off configuration.
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:
A320-100:
- VMCA (Air): 105 kt
- VMCG (Ground): 102 kt (all config.)
A320-200:
- VMCA (Air) and VMCG (Ground): See TAB program issue M or N with associated A/C performances module
Maximum Weights:
A320-100:
000
VARIANT (BASIC)
(KG) (LBS)
Max. Ramp Weight 68,400 150,820
Max. Take-off Weight 68,000 149,940
Max. Landing Weight 63,000 138,915
Max. Zero Fuel Weight 59,000 130,100
A28NM Page 10 of 22
A320-200:
FAA Approved
Weight Variants
000
BASIC
001 003 007 008 009 010 011 012 013 014
A320-211 YES YES YES YES YES YES YES YES YES
A320-212 YES YES YES YES YES YES YES YES YES YES
A320-214 YES YES YES YES YES YES YES YES YES YES
A320-231 YES YES YES YES YES YES YES YES YES
A320-232 YES YES YES YES YES YES YES YES YES YES
A320-233 YES YES YES YES YES YES YES YES YES YES
VARIANT 000
BASIC
001 003 007 008 009 010 011 012 013 014
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
(KG)
(LBS)
Max. Ramp
Weight
73900
162949
68400
150822
75900
167360
77400
170667
73900
162950
75900
167360
77400
170667
75900
167360
77400
170667
71900
158512
73900
162949
Max. Takeoff
Weight
73500
162068
68000
149940
75500
166478
77000
169785
73500
162068
75500
166478
77000
169785
75500
166478
77000
169785
71500
157631
73500
162068
Max.
Landing
Weight
64500
142223
64500
142223
64500
142223
64500
142223
64500
142223
64500
142223
64500
142223
66000
145505
66000
145505
64500
142223
64500
142223
Max. Zero
Fuel
Weight
60500
133403
60500
133403
60500
133403
60500
133403
61000
134505
61000
134505
61000
134505
62500
137789
62500
137789
61000
134505
61500
135584
Minimum Weight:
A320-100:
VARIANT 000
(BASIC)
(KG) (LBS)
Minimum Weight 36,750 81,030
A320-200:
VARIANT All
(KG) (LBS)
Minimum Weight 37,230 82,080
Minimum Crew:
2 Pilots
Maximum Passengers:
179
Maximum Baggage:
CARGO COMPARTMENT MAXIMUM LOAD
(KG) (LBS)
Forward 3,402 7,500
Aft 4,536 10,000
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. 00D080A0001/C1S Chapter 1.10.
A28NM Page 11 of 22
Fuel Capacity (0.8 kg/liter):
A320-100:
2-Tank Airplane
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,843 4,185 57.3 15.1
(12,674) (27,946) (45.8) (101.0)
Total 15,843 4,185 57.3 15.1
(12,674) (27,946) (45.8) (101.0)
3-Tank Airplane
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,843 4,185 58.9 15.6
(12,674) (27,946) (47.1) (103.9)
Center 8,250 2,179 23.2 6.1
(6,600) (14,484) (19.6) (43.2)
TOTAL 24,093 6,364 82.1 21.7
(19,274) (42,430) (65.7) (147.1)
A320-200:
Tank Usable Fuel Unusable Fuel
Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)
Wing 15,609 4,124 58.9 15.6
(12,487) (27,534) (47.1) (103.9)
Center 8,250 2,179 23.2 6.5
(6,600) (14,484) (19.6) (41.0)
TOTAL 23,859 6,304 82.1 20.8
(19,087) (42,087) (65.7) (144.9)
Oil Capacity:
CFMI CFM56-5A/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 applicable to it.
Refer to Type Certification Standard Equipment List 00D000A0101/C1S.
Refer Note 4 for list of A320 airplane model FAA Type Definitions.
Serial Numbers Eligible:
A320 aircraft, all series, all models, are produced in Blagnac (France) under approval P09 or F.G.035 issued by DGAC to
Airbus.
A French "Certificat de Navigabilite pour Exportation," endorsed as noted under "Import Requirement," must be submitted for
each individual aircraft for which application for U.S. certification is made.
A28NM Page 12 of 22
Import Requirements:
A FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation,"
signed by a representative of the Direction Generale de 1'Aviation Civile (DGAC) of France, containing the following statement:
"The Airplane covered by this certificate has been examined, tested, and found to conform to the Type Design approved under
Type Certificate No. A28NM and to be in condition for safe operation."
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of
manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated
under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections
21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require
certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical
way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type
design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness
Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.
Certification Basis
a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto.
b. Special Federal Aviation Regulation (SFAR) No.27 effective February 1, 1974, including Amendments 27-1 through
27-5.
c. Part 36 of the FAR effective December 1, 1969, including Amendments 36-1 through 36-12.
d. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the
Federal Register, as follows:
(1) January 27, 1989:
- Electronic Flight Controls
- Active Controls
- Engine Controls and Monitoring
- Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy
- Flight Characteristics
- Flight Envelope Protection
- Side Stick Controllers
- Flight Recorder.
(2) June 9, 1989:
- Computerized Airplane Flight Manual
e. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC
120-28c.
For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for
automatic landing and by AC 25.1329-1A for cruise.
Use of JAR AWO where applicable to the requirements above, is acceptable.
f. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:
- 25.783(e) for cargo doors
- 25.783(f) for passenger doors and bulk cargo door
- 25.813(c) for emergency exit access
- 25.811(e)(3) Type III emergency exit marking.
g. Optional Requirements elected:
- 25.801 for ditching.
- 25.1419 for icing.
Note 1 - Weight and Balance
a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated
empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,
except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"
contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or
refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage
compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in
the passenger compartment.
A28NM Page 13 of 22
b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear
retraction and movement of crew and passengers from their assigned positions.
c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty
weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.
d. System fuel is the weight of all fuel required to fill a lines and tanks up to zero-fuel point on the fuel gauges in the most
critical flight attitude, including the unusable tank fuel as defined by FAR part 26.959. (The usable fuel in the crossfeed
manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct
weight and CG for take-off.)
e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as
defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be
accounted for separately.
f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the
tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only
the usable oil for which the tanks must be placarded.
Note 2:
The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is
considered equivalent to "FAA-approved".)
Note 3:
Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness
Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.
Note 4:
The A320 basic definition for U.S. import certification is contained in the following documents:
- AI/A 414.282/88 for the A320 Models -111 and -211
- AI/EA-A 413.628/89 for the A320 Model -231
- AI/EA-A 412.1631/90 for the A320 Model -212
- AI/EA-A 414.0665/93 for the A320 Model -232
- AI/EA-S 413.2143/95 for the A320 Model -233
- AI/EA-S 413.0150/95 for the A320 Model -214
- AI/EA-S 413.3004/96 (supplement) for the A320 Model -214.
Note 5:
Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89
“Certification Maintenance Requirements (FAA version)” (CMR).
Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/
95A.0252/96 “Airworthiness Limitation Items”.
Note 6:
If modification 20758 is embodied, the airplane is certified for CAT III B precision approach (fail operational) and landing. This
does not constitute an operational approval.
Note 7:
All Models of A320 airplanes manufactured after January 1, 1997 must have either modification 25302 (for IAE engines) or
25303 (for CFM engines) installed, before the individual U.S. standard Certificate of Airworthiness can be issued.
Note 8:
If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine
denomination changes to /P.
CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.
A28NM Page 14 of 22
Note 9:
If modification 26610 is embodied on A320-214 airplanes, the engine performance and gaseous emission levels are improved.
The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).
CFM56-5B4/P engine can be intermixed with CFM56-5B4/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft
(AFM Supplement).
Note 10:
For A320-200 series airplanes with OCTOPUS Airplane Flight Manual, Airbus elected to comply with Part 25 Amendment 25-
92.
III. Type A321-100/200 Series Transport Category Airplanes
Model A321-111, Approved December 20, 1995;
Model A321-112, Approved December 20, 1995;
Model A321-131, Approved December 20, 1995;
Model A321-211, Approved September 18, 1997;
Model A321-231, Approved September 18, 1997:
Engines:
Model A321-111, Two CFMI Model CFM56-5B1 or CFM56-5B1/P or CFM56-5B1/2P jet engines;
Model A321-112, Two CFMI Model CFM56-5B2 or CFM56-5B2/P jet engines;
Model A321-131, Two IAE Model V2530-A5 jet engines
Model A321-211, Two CFMI Model CFM56-5B3/P or CFM56-5B3/2P jet engines
Model A321-231, Two IAE Model V2533-A5 jet engines
See Note 14 for description of “P” engine designations
Fuel:
See Installation Manual - Documents CFM 2026 or IAE-0043
SPECIFICATION
NOMENCLATURE FRANCE U.S.A U.K.
Kerosene MIL-T83133A (JP8)
Air 3405C ASTM D 1655 (JET A1) (JET A) DERD 2494
Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454
Air 3407 (TR4) MIL-T 5624 (JP4) DERD 2454
High Flash Point Air 3404 MIL-T 5624 (JP5) DERD 2452
Additives: See CFMI "Specific Operating Instructions," CFM TPOI-13 or IAE V2500 “Installation and Operating Manual”
IAE-0043, 4.5. The above mentioned fuels and additives are also suitable for the APU.
Engine Limits
CFMI CFM56-5B1 or -5B1/P
or –5B1/2P
CFMI CFM56-5B2 or -5B2/P CFMI CFM56-5B3/P
or –5B3/2P
Engine Limitation Data Sheets Data Sheets Data Sheets
E37NE E38NE (FAA) E37NE E38NE (FAA) E37NE E38NE (FAA)
Static Thrust at Sea Level
- Take-off (5 min)** 13 344 daN (30,000 lb) 13 789 daN (31 000 lb) 14 234 daN (32,000 lb)
(Flat rated 30°C)
Maximum Continuous 12 940 daN (29,090 1b) 12 940 daN (29,090 1b) 12940 daN (29,090 lb)
(Flat rated 25°C)
Maximum Engine Speed
- N1 rpm (%) 5,200 (104) 5,200 (104) 5,200 (104)
- N2 rpm (%) 15,183 (105) 15,183 (105) 15,183 (105)
Max Gas Temperature
(°C)
- Take-off (5 min)** 950 950 950
- Max Continuous 915 915 915
- Starting * 725 725 725
A28NM Page 15 of 22
Max Oil Temperature
(Supply Pump Inlet; °C)
- Take-off, Stabilized 140 140 140
- Transient (15 min max) 155 155 155
Min. Press. (PSI) 13 13 13
Approved Oils See SB CFMI 79-001-OX See SB CFMI 79-001-OX See SB CFMI 79-001-OX
IAE V2530-A5 IAE V2533-A5
Engine Limitation Data Sheets E40NE (FAA) Data Sheets E40NE (FAA)
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
applicable to it. Refer to Type Certification Standard Equipment Schedule Lists:
- 00E000A0007/C1S for A321-111 Model
- 00E000A0006/C1S for A321-112 Model
- 00E000A0004/COS for A321-131 Model
- 00E000A0211/COS for A321-211 Model
- 00E000A0231/COS for A321-231 Model
Refer to Note 4 for list of A321 airplane model FAA Type Definitions.
Serial Numbers Eligible:
A321 Aircraft, all series, all models, are produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to
Airbus.
A German Export Certificate of Airworthiness endorsed as noted under “Import Requirement”, must be submitted for each
individual aircraft for which application for U.S. certification is made.
A28NM Page 18 of 22
Import Requirements:
A FAA Standard Airworthiness Certificate may be issued on the basis of a German Export Certificate of Airworthiness, signed
by a representative of the Luftfahrt-Bundesamt (LBA) of Germany, containing the following statement: “The airplane covered by
this certificate has been examined, tested, and found to conform to the type design approved under Type Certificate No. A28NM
and to be in condition for safe operation.”
The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of
manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated
under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections
21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require
certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical
way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type
design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness
Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.
Certification Basis (A321-100 and A321-200)
a. Part 25 of the FAR effective February 1, 1965, including amendments 25-1 through 25-56 thereto.
b.1. Plus the following sections of Part 25 as amended by amendments 25-1 through:
- 25-58 (Section 25.812(e))
- 25-63 (Section 25.25(a)(3))
- 25-67 (Section 25.807(c)(7))
- 25-70 (Section 25.1411(a)(2))
(Applied per FAA derivative aircraft policy – reference FAA order 8110.4A)
b.2. Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR
paragraphs 25.562(c)(5) and 25.562(c)(6) do not apply.
c. Part 34 of the FAR effective September 10, 1960, including amendments 34-1.
d. Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto.
e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the
Federal Register as follows:
1) January 27, 1989:
- Electronic Flight Controls
- Active Controls
- Engine Controls and Monitoring
- Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy
- Flight Characteristics
- Flight Envelope Protection
- Side Stick Controllers
- Flight Recorder.
(2) June 9, 1989
- Computerized Airplane Flight Manual
f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC
120-28c.
For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for
automatic landing and by AC 25.1329-1A for cruise.
Use of JAR AWO where applicable to the requirements above, is acceptable.
g. The following sections of the FAR have been complied with through equivalent safety demonstrations in addition to
the equivalent safety findings applicable from the original A320 certification basis:
- 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected take-off and landing performance
- 25.305, 25.331, 25.333, 25.335, 25.341, 25.345, 25.349, 25.351, 25.371, 25.373, 25.391, 25.427, for design gust
criteria
-25.783(e) bulk cargo door
- 25.783(f) for passenger doors
- 25.807(c) for maximum passenger capacity
- 25.933(a) for thrust reversing system.
h. Optional requirements elected:
- 25.801 for ditching.
- 25.1419 for icing.
A28NM Page 19 of 22
Note 1 - Weight and Balance
a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated
empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,
except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"
contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or
refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage
compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in
the passenger compartment.
b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear
retraction and movement of crew and passengers from their assigned positions.
c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty
weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.
d. System fuel is the weight of all fuel required to fill a lines and tanks up to zero-fuel point on the fuel gauges in the most
critical flight attitude, including the unusable tank fuel as defined by FAR part 26.959. (The usable fuel in the crossfeed
manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct
weight and CG for take-off.)
e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as
defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be
accounted for separately.
f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the
tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only
the usable oil for which the tanks must be placarded.
Note 2:
The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is
considered equivalent to "FAA-approved".)
Note 3:
Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness
Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.
Note 4:
The A321 basic definition for U.S. import certification is contained in the following documents:
- 00E000A0010/C11 for A321-111 model
- 00E000A0011/C11 for A321-112 model
- 00E000A0012/C11 for A321-131 model
- AI/EA-S 413.3365/96 (supplement) for A321-111/112/131 models
- AI/EA-S 413.0401/97 for A321-211 model
- AI/EA-S 413.0399/97 for A321-231 model.
Note 5:
Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89
“Certification Maintenance Requirements (FAA version)” (CMR).
Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/
95A.0252/96 “Airworthiness Limitation Items”.
Note 6:
Door 2 and/or Door 3 may be derated to Type III.
Note 7:
If modifications 24173 and 22853 are embodied on models with IAE engines, the aircraft is qualified for Cat II precision
approach. This does not constitute operational approval.
A28NM Page 20 of 22
Note 8:
If modification 24064 is embodied on models with CFM engines, the aircraft is qualified for Cat III precision approach. This
does not constitute operational approval.
Note 9:
If modification 24066 is embodied on models with IAE engines, the aircraft is qualified for Cat III precision approach. This does
not constitute operational approval.
Note 10:
If modification 25199 is embodied on models with CFM engines, the aircraft is qualified for Cat III B precision approach. This
does not constitute operational approval.
Note 11:
If modification 25200 is embodied on models with IAE engines, the aircraft is qualified for Cat III B precision approach. This
does not constitute operational approval.
Note 12:
If FWC Standard D2 and FAC standard BAM 0510 are fitted on A321 aircraft, VFE speed in configuration 2 is increased from
205kts to 215kts (as identified by speed limitation placard installed by modification 24641).
Note 13:
Modifications 25302 (for IAE engine) and 25303 (for CFM engine) are part of the FAA Type Design, and shall be implemented
on any A321 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness be issued.
Note 14:
If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine
denomination changes to /P.
CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.
Note 15:
On the series A321-200, one Additional Center Tank (ACT) in bulk version is defined by modification 25453 (high pressure
system). Its approval together with structural and system provisions was subject of compliance demonstrated to Advisory
Circular (AC) 25-8.
Note 16:
The type design definitions and certification standard equipment lists as referenced in Note 4 above are complemented by
document 00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution”.
Note 17:
On the series A321-200, one or two Additional Center Tanks (ACT) in bulk version are defined by modification 30422 (low
pressure system). Their approval together with structural and system provisions was subject of compliance demonstrated to AC
25-8.
Note 18:
On the series A321-200, Weight Variant 001, VFE speed in Configuration 1 is increased from 230 to 235 kts, and in
Configuration 1+F increased from 215 to 225 kts (as identified by speed limitation placard installed by modification 28960).
Note 19:
If modification 26610 is embodied on A321-111airplanes, the engine performance and gaseous emission levels are improved.
The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).
CFM56-5B1/P engine can be intermixed with CFM56-5B1/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft
(AFM Supplement).
Note 20:
If modification 27640 is embodied on A321-211airplanes, the engine performance and gaseous emission levels are improved.
The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).
CFM56-5B3/P engine can be intermixed with CFM56-5B3/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft
(AFM Supplement).
A28NM Page 21 of 22
DATA PERTINENT TO ALL MODELS
Auxiliary Power Unit (APU)
GARRETT AIRESEARCH GTCP 36-300(A) (Standard)
(Specification 31-5306B)
APIC APS 3200 (Option - Mod 22562)
(Specification ESR 0802, Rev A)
AlliedSignal 131-9[A] (Option – Mod 25888)
(Specification 4900 M1E 03 19 01)
APU Limits:
GTCP 36-300 (A)
- Maximum Allowable Speed 69,204 rpm (107 %)
- Maximum Gas Temperature
at turbine outlet (ISA + 35°C)
rated output 638°C
overtemp. shutdown 711°C
Maximum on starting 1038°C
APS 3200
- Maximum Rotor Speed 49,300 rpm (105 %)
- Maximum EGT 742°C
- Maximum for Start 900°C at altitudes below 25000 ft
982°C at altitudes below 25000 ft
131-9[A]
- Maximum Allowable Speed Nominal 51,728 rpm (106 %)
Overshoot 53,875 rpm (110 %)
- Maximum Gas Temperature
at turbine outlet 675°C
rated output (ISA + 23°C) 585°C
overtemp. shutdown (ISA) 706°C
maximum on starting (ISA) 1080°C below 35000 ft,
1108°C above 35000 ft
(ISA + 40°C) 1090°C below 35000 ft,
1120°C above 35000 ft
APU Approved oils:
See GARRETT Report GT-7800 or in conformity with MIL-L-IAS, MIL-L23699 or DERD 2487 for the GTCP 36-300, Usable
Capacity: 5.8 liters
See APIC Maintenance Manual for approved oils for the APS 3200
See Model Specification 31-12048A-3B for Allied Signal 131-9[A]
Center of Gravity Range (% Mean Aerodynamic Chord):
See DGAC-Approved Airplane Flight Manual, U.S. Version.
Hydraulic Fluids:
- Type IV - Specification NSA 30.7110.
- Capacity (Reservoirs and Systems):
System Liters Gallons
Green 100 26
Yellow 75 20
Blue 60 16
Pressure: 3000 ± 200 PSI (207 ± 4 bar)
A28NM Page 22 of 22
Tires:
- See Airbus Service Bulletin (SB) A320-32-1007
Datum:
Station 0 (100 inches forward of fuselage nose).
Reference Mean Aerodynamic Chord (MAC):
165.10 inches / 4.1935 m (leading edge of MAC: Sta. 700.85 inches).
Leveling Means:
Clinometer on the cabin seat track rails.
Service Information:
- Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals,
which contain a statement that the document DGAC-approved, are accepted by the FAA and are considered FAA approved.
These approvals pertain to the type design only. The reference to service bulletins includes any type of service instructions
(letters, repair approvals, etc.). The reference to DGAC-approved includes findings made by DGAC designees and/or design
organizations which are equally as acceptable as those made directly by the DGAC.
- Other available service documents for the Airbus include:
a. Illustrated Parts Catalog
b. Wiring Diagram Manual
c. Maintenance Manual
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TYPE CERTIFICATION DATA SHEET A28NM