TYPE CERTIFICATION DATA SHEET A28NM
<P>TYPE CERTIFICATION DATA SHEET A28NM</P><P>**** Hidden Message *****</P> Page No. 1 2 3 4 5 6 7 8 9 10 11 12 13 14<BR>Rev. No. 6 6 5 5 6 5 5 6 6 5 5 5 5 6<BR>Page No. 15 16 17 18 19 20 21 22<BR>Rev. No. 5 5 5 5 6 5 5 5<BR>DEPARTMENT OF TRANSPORTATION<BR>FEDERAL AVIATION ADMINISTRATION<BR>A28NM<BR>Revision 6<BR>Airbus<BR>A319 Model -111 A320 Model -111<BR>A319 Model -112 A320 Model -211<BR>A319 Model -113 A320 Model -212<BR>A319 Model -114 A320 Model -214<BR>A319 Model -131 A320 Model -231<BR>A319 Model -132 A320 Model -232<BR>A320 Model -233<BR>A321 Model -111<BR>A321 Model -112<BR>A321 Model -131<BR>A321 Model -211<BR>A321 Model -231<BR>September 18, 2002<BR>TYPE CERTIFICATION DATA SHEET A28NM<BR>This Data Sheet which is part of Type Certificate No. A28NM prescribes conditions and limitations under which the product for<BR>which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations.<BR>Type Certificate Holder: Airbus<BR>1, Rond-Point Maurice Bellonte<BR>31707 Blagnac, France<BR>Type Certificate Holder Record Name change from Airbus Industrie to Airbus January 2002<BR>I. Type A319-100 Series Transport Category Airplanes<BR>Model A319-112, Approved August 30, 1996;<BR>Model A319-111, Approved June 20, 1997;<BR>Model A319-113, Approved June 20, 1997;<BR>Model A319-114, Approved June 20, 1997;<BR>Model A319-131, Approved June 20, 1997;<BR>Model A319-132, Approved June 20, 1997;<BR>Engines:<BR>Model A319-111, Two CFMI Model CFM56-5B5 or CFM56-5B5/P jet engines;<BR>Model A319-112, Two CFMI Model CFM56-5B6 or CFM56-5B6/P or CFM56-5B6/2P jet engines;<BR>Model A319-113, Two CFMI Model CFM56-5A4 jet engines;<BR>Model A319-114, Two CFMI Model CFM56-5A5 jet engines;<BR>Model A319-131, Two IAE Model V2522-A5 jet engines;<BR>Model A319-132, Two IAE Model V2524-A5 jet engines;<BR>Fuel:<BR>See Installation Manual - Documents CFM 2026 or IAE-0043<BR>SPECIFICATION<BR>NOMENCLATURE FRANCE U.S.A U.K.<BR>Kerosene MIL-T83133A (JP8)<BR>Air 3405C ASTM D1655 (Jet Al) (Jet A) DERD 2494<BR>Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454<BR>AIR 3407 (TR4) MIL-T 5624 (JP4) DERD 2454<BR>High Flash Point AIR 3404 MIL-T 5624 (JP5) DERD 2452<BR>Additives: See CFMI " Specific Operating Instructions," CMF TPOI-13 or IAE V2500 “Installation and Operating Manual”<BR>IAE-0043, 4. The above mentioned fuels and additives are also suitable for the APU.<BR>A28NM Page 2 of 22<BR>Engine Limits:<BR>CFMI CFM56-5B5 or -<BR>5B5/P<BR>CFMI CFM56-5B6 or -<BR>5B6/P or -5B6/2P<BR>CFMI CFM56-5A4<BR>Engine FAA Data Sheets FAA Data Sheets FAA Data Sheet<BR>Limitation E37NE E38NE E37NE E38NE E28NE<BR>Static Thrust at Sea Level<BR>- Take-off (5 min)** 9 786 daN (22,000 lb) 10 453 daN (23,500 lb) 9 786 daN (22,000 lb)<BR>(Flat rated 30°C)<BR>Maximum Continuous 9 008 daN (20,250 1b) 9 008 daN (20,250 1b) 9 195 daN (20,670 1b)<BR>(Flat rated 25°C)<BR>Maximum Engine Speed<BR>- N1 rpm (%) 5,200 (104) 5,200 (104) 5,100 (102)<BR>- N2 rpm (%) 15,183 (105) 15,183 (105) 15,183 (105)<BR>Max Gas Temperature (°C) Eng. Limit/ ECAM<BR>- Take-off (5 min)** 950 950 915/890<BR>- Max Continuous 915 915 880/855<BR>- Starting * 725 725 725/725<BR>Max Oil Temperature<BR>(supply pump inlet; °C)<BR>- Take-off, Stabilized 140 140 140<BR>- Transient (15 min max) 155 155 155<BR>Min. Press. (PSI) 13 13 13<BR>Approved Oils See SB See SB See SB<BR>CFMI 79-001-0X CFMI 79-001-0X CFMI 79-001-0X<BR>CFMI CFM56-5A5 IAE V2522-A5 IAE V2524-A5<BR>Engine Limitation Data Sheets Data Sheets Data Sheets<BR>E28NE (FAA) E40NE (FAA) E40NE (FAA)<BR>Static Thrust at Sea Level<BR>- Take-off (5 min)** 10 453 daN (23,500 lb) 10 249 daN (23,040 lb) 10 889 daN (24,480 lb)<BR>(Flat rated 30°C)<BR>Maximum Continuous 9 195 daN (20,670 1b) 8 540 daN (19,200 1b) 8 540 daN (19,200 1b)<BR>(Flat rated 25°C)<BR>Maximum Engine Speed<BR>- N1 rpm (%) 5,100 (102) 5,650 (100) 5,650 (100)<BR>- N2 rpm (%) 15,183 (105) 14,950 (100) 14,950 (100)<BR>Max Gas Temperature (°C) Eng. Limit/ ECAM<BR>- Take-off (5 min)** 915/890 645 645<BR>- Max Continuous 880/855 610 610<BR>- Starting * 725/725 650 650<BR>Max Oil Temperature<BR>(supply pump inlet; °C)<BR>- Take-off, Stabilized 140 155 155<BR>- Transient (15 min max) 155 165 165<BR>Min. Press. (PSI) 13 60 60<BR>Approved Oils See SB See Doc IAE 0043 Sec 4.9 See Doc IAE 0043 Sec 4.9<BR>CFMI 79-001-0X (MIL-L-23699) (MIL-L-23699)<BR>* 4 consecutive cycles of 2 minutes each.<BR>** 10 minutes at take-off thrust allowed in case of engine failure (at take off and during go around).<BR>A28NM Page 3 of 22<BR>Airspeed Limits (Indicated Airspeed - IAS - Unless Otherwise Stated:<BR>- Maximum Operating Mach - MMO: 0.82<BR>- Maximum Operating Speed - VMO: 350 kt<BR>- Maneuvering Speed VA: - See Chapter 2.0 of the DGAC-approved Flight Manual<BR>- Extended Flaps/Slats Speed - VFE<BR>Configuration Slats/Flaps VFE (kt)<BR>1 18/0 230 Intermediate<BR>Approach<BR>*18/10 215 Take-off<BR>2 22/15 200 Take-off and<BR>Approach<BR>3 22/20 185 Take-off, Approach, and Landing<BR>Full 27/40 177 Landing<BR>* Auto flap retraction at 210 kt in Take-off configuration.<BR>Landing Gear:<BR>- VLE - Extended: 280 kt/Mach 0.67<BR>- VLO - Extension: 250 kt<BR>- Retraction: 220 kt<BR>Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph)<BR>Maximum Weights:<BR>000 001 002<BR>VARIANT BASIC Mod 25328 Mod 27112<BR>(KG) (LBS) (KG) (LBS) (KG) (LBS)<BR>Max. Take-Off Weight 64,000 141,090 70,000 154,322 75,500 166,447<BR>Max. Landing Weight 61,000 134,480 61,000 134,480 62,500 137,787<BR>Max. Zero Fuel Weight 57,000 125.660 57,000 125,660 58,500 128,969<BR>Minimum Weight:<BR>VARIANT All<BR>Minimum Weight<BR>(KG) (LBS)<BR>35,400 78,042<BR>Minimum Crew:<BR>2 Pilots<BR>Maximum Passengers:<BR>145<BR>Maximum Baggage:<BR>CARGO COMPARTMENT MAXIMUM LOAD<BR>(KG) (LBS)<BR>Forward 2,268 5,000<BR>Aft 3,020 6,660<BR>Rear (Bulk) 1,497 3,300<BR>For the positions and the loading conditions authorized in each position (references of containers, pallets, associated weights),<BR>see Weight and Balance Manual, Ref. 00J080A0001/C1S Chapter 1.10.<BR>A28NM Page 4 of 22<BR>Fuel Capacity (0.8 kg/liter)<BR>3-Tank Airplane<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,609 4,124 58.9 15.6<BR>(12,487) (27,531) (47.1) (103.9)<BR>Center 8,250 2,179 23.2 6.5<BR>(6,600) (14,551) (18.6) (41.0)<BR>TOTAL 23,859 6,303 82.1 20.8<BR>(19,087) (42,082) (65.7) (144.9)<BR>4 to 9-Tank Airplane<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>TOTAL<BR>3-Tank 23,859 6,303 82.1 20.8<BR>Airplane (19,087) (42,082) (65.7) (144.9)<BR>ACT 1 3,121 824 17 4.3<BR>(2,497) (5,505) (13.6) (28.8)<BR>TOTAL<BR>4-Tank 26,980 7,128 99.1 25.1<BR>Airplane (21,584) (47,587) (79.3) (173.7)<BR>ACT 2 3,121 824 17 4.3<BR>(2,497) (5,505) (13.6) (28.8)<BR>TOTAL<BR>5-Tank 30,101 7,952 116.1 29.4<BR>Airplane (24,081) (53,092) (92.9) (202.5)<BR>ACT 3 2,186 577 22 5.6<BR>(1,749) (3,855) (17.6) (37.4)<BR>TOTAL<BR>6-Tank 32,287 8,530 138.1 35.0<BR>Airplane (25,830) (56,947) (110.5) (239.9)<BR>ACT 4 2,186 577 22 5.6<BR>(1,749) (3,855) (17.6) (37.4)<BR>TOTAL<BR>7-Tank 34,473 9,107 160.1 40.6<BR>Airplane (27,579) (60,803) (128.1) (277.3)<BR>ACT 5 3,046 804 12 3.1<BR>(2,437) (5,372) (9.6) (20.6)<BR>TOTAL<BR>8-Tank 37,519 9,912 172.1 43.7<BR>Airplane (30,016) (66,176) (137.7) (297.9)<BR>ACT 6 3,121 824 17 4.3<BR>(2,497) (5,505) (13.6) (28.8)<BR>TOTAL<BR>9-Tank 40,640 10,737 189.1 48.0<BR>Airplane (32,513) (71,681) (151.3) (326.7)<BR>Oil Capacity<BR>CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters).<BR>IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters)<BR>Maximum Operating Altitude:<BR>- 41,000 feet (12,600 m) clean if modification 28162 is embodied.<BR>- 39,800 feet (12,200 m) clean if modification 30748 is embodied.<BR>- 39,100 feet (12,000 m) clean.<BR>- 20,000 feet (6,500 m) Slats/Flaps extended.<BR>A28NM Page 5 of 22<BR>Equipment:<BR>The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraft for<BR>certification.<BR>Equipment approved for installation are listed in the definition of the reference model and the modifications applicable to it.<BR>Refer to Type Certification Standard Equipment Lists:<BR>-00J000A0012/C0S for A319-111 Model<BR>-00J000A0004/C0S for A319-112 Model<BR>-00J000A0113/C0S for A319-113 Model<BR>-00J000A0114/C0S for A319-114 Model<BR>-00J000A0131/C0S for A319-131 Model<BR>-00J000A0132/C0S for A319-132 Model<BR>Refer to Note 4 for list of A319 airplane model FAA Type Definitions.<BR>Serial Numbers Eligible:<BR>A319 aircraft, all series, all models, are produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to<BR>Airbus.<BR>A German Export Certificate of Airworthiness endorsed as noted under “Import Requirement,” must be submitted for each<BR>individual aircraft for which application for U.S. certification is made.<BR>Import Requirements:<BR>A FAA Standard Airworthiness Certificate may be issued on the basis of a German Export Certificate of Airworthiness, signed<BR>by a representative of the Luftfahrt-Bundesamt (LBA) of Germany, containing the following statement: “The Airplane covered<BR>by this certificate has been examined, tested, and found to conform to the Type Design approved under Type Certificate No.<BR>A28NM and to be in condition for safe operation.”<BR>The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of<BR>manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated<BR>under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections<BR>21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require<BR>certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical<BR>way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type<BR>design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness<BR>Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.<BR>Certification Basis:<BR>a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto.<BR>b.1 Plus the following sections of Part 25 as amended by amendments 25-1 through:<BR>-25-58 (Section 25.812(e))<BR>-25-63 (Section 25.25 (a)(3))<BR>-25-67 (Section 25.807 (c)(7))<BR>(Applied per FAA derivative aircraft policy – reference FAA order 8110.4A)<BR>b.2 Airbus elected to comply with the following sections of Part FAR 25 through Amendment 86:<BR>25.305(d), 25.321(c)/(d), 25.331(a)/(d), 25.333(a)/(c),25.335(d), 25.341,<BR>25.343 (b)(1)(ii), 25.345(a)/(c), 25.349(b), 25.351(b),25.371, 25.373(a),<BR>25.391(e), 25.427, 25.445(a), 25.571(b)(2)/(b)(3), 25.1517.<BR>b.3 Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR<BR>paragraphs 25.562(c)(5), (c)(6) do not apply.<BR>c. Part 34 of the FAR effective Sept. 10, 1990, including amendment 34-1.<BR>d. Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto.<BR>e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the<BR>Federal Register as follows:<BR>(1) January 27, 1989:<BR>- Electronic Flight Controls<BR>- Active Controls<BR>- Engine Controls and Monitoring<BR>- Protection from Lightning and Unwanted Effects of Radio Frequency<BR>- (RF) Energy<BR>- Flight Characteristics<BR>- Flight Envelope Protection<BR>- Side Stick Controllers<BR>- Flight Recorder<BR>A28NM Page 6 of 22<BR>(2) June 9, 1989:<BR>- Computerized AFM<BR>f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and<BR>AC 120-28c.<BR>For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for<BR>automatic landing and by AC 25.1329-1A for cruise.<BR>Use of JAR AWO where applicable to the requirements above, is acceptable.<BR>g. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:<BR>- 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected takeoff and landing performance<BR>- 25.783(f) for passenger doors<BR>- 25.807(c) for maximum passenger capacity<BR>- 25.813(a) emergency exit access for a single 13 inch aisle<BR>- 25.933(a), 25.1309(b) for thrust reversing system<BR>- 25.811(e)(3) Type III emergency exit marking.<BR>h. Optional Requirements elected:<BR>- 25.801 for ditching<BR>- 25.1419 for icing<BR>Note 1 - Weight and Balance<BR>a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated<BR>empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,<BR>except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"<BR>contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or<BR>refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage<BR>compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in<BR>the passenger compartment.<BR>b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear<BR>retraction and movement of crew and passengers from their assigned positions.<BR>c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty<BR>weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.<BR>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<BR>critical flight attitude, including the unusable tank fuel as defined by FAR part 25.959. (The usable fuel in the crossfeed<BR>manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct<BR>weight and CG for take-off.)<BR>e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as<BR>defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be<BR>accounted for separately.<BR>f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the<BR>tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only<BR>the usable oil for which the tanks must be placarded.<BR>Note 2:<BR>The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is<BR>considered equivalent to "FAA-approved".)<BR>Note 3:<BR>Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness<BR>Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.<BR>A28NM Page 7 of 22<BR>Note 4:<BR>The A319 basic definition for U.S. import certification is contained in the following documents:<BR>-AI/EA-S 413.0969/96 for A319-111 model<BR>-AI/EA-S 413.1012/96 for A319-112 model<BR>-AI/EA-S 413.3100/96 (Mod 25699 supplement) for A319-112 model<BR>-AI/EA-S 413.2504/96 for A319-113 model<BR>-AI/EA-S 413.2505/96 for A319-114 model<BR>-AI/EA-S 413.0393/97 for A319-131 model<BR>-AI/EA-S 413.0396/97 for A319-132 model<BR>Note 5:<BR>Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89<BR>“Certification Maintenance Requirements (FAA version)” (CMR).<BR>Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/<BR>95A.0252/96 “Airworthiness Limitation Items”. This document is not applicable to the A319 for Corporate Jet<BR>use, but rather Airbus document AI/SE-M2/95A-1038/99 “Airworthiness Limitation Items”.<BR>Note 6:<BR>If modification 25469 or 26968 is embodied on models with CFM engines, the airplane is qualified for CAT III B precision<BR>approach. This does not constitute operational approval.<BR>Note 7:<BR>Modification 25303 (for CFM engine) or 25302 (for IAE engine) are part of the FAA Type Design and shall be implemented on<BR>any A319 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness can be issued.<BR>Note 8:<BR>If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine<BR>denomination changes to /P.<BR>CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.<BR>Note 9:<BR>If Modification 26716 or 26717 is embodied on models with IAE engines, the airplane is qualified for CAT III B precision<BR>approach. This does not constitute operational approval.<BR>Note 10:<BR>The type design definitions and certification standard equipment lists as referenced in Note 4 are complemented by document<BR>00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution” and document 00J000A0067/C0S “A319-111/112<BR>ATC Transponder Type Standard Evolution”.<BR>Note 11:<BR>A319 for Corporate Jet use are defined through the following set of modifications:<BR>- Modification 28238 (0 to 6 ACTs)<BR>- Modification 28162 (extension of flight envelope up to 41,000 ft)<BR>- Modification 28342 (modification of CG limits)<BR>Note 12:<BR>On A319 for Corporate Jet use, the certification of installing up to six Additional Center Tanks (ACT) in bulk version is defined<BR>by modification 28238. The approval together with structural and system provisions was subject of compliance demonstrated to<BR>Advisory Circular AC 25-8.<BR>Note 13:<BR>On A319 for Corporate Jet use, exemptions to the following paragraphs of the FAR have been granted when the airplane is not<BR>operated for hire or for public transport<BR>(Granted APR 9, 2001, Exemption No. 7489):<BR>25.785(h)(2) Flight Attendant seat locations which do not provide for direct view of the cabin<BR>25.807(d)(7) Distance between exits<BR>25.813(e) Installation of Interior Doors in between passenger compartments<BR>A28NM Page 8 of 22<BR>Note 14:<BR>If modification 26610 is embodied on A319-112 airplanes, the engine performance and gaseous emission levels are improved.<BR>The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).<BR>CFM56-5B6/P engine can be intermixed with CFM56-5B6/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft<BR>(AFM Supplement).<BR>II. Type A320-100/200 Series Transport Category Airplanes<BR>Model A320-111, Approved December 15, 1988<BR>Model A320-211, Approved December 15, 1988;<BR>Model A320-231, Approved July 6, 1989;<BR>Model A320-212, Approved November 26, 1990;<BR>Model A320-232, Approved November 12, 1993;<BR>Model A320-233, Approved November 17, 1995;<BR>Model A320-214, Approved December 12, 1996.<BR>Engines:<BR>Model A320-111, Two CFMI Model CFM-56-5A1 jet engines;<BR>Model A320-211, Two CFMI Model CFM-56-5A1 jet engines;<BR>Model A320-212, Two CFMI Model CFM56-5A3 jet engines;<BR>Model A320-214, Two CFMI Model CFM56-5B4 or CFM56-5B4/P or CFM56-5B4/2P jet engines;<BR>Model A320-231, Two IAE Model V2500-A1 jet engines;<BR>Model A320-232, Two IAE Model V2527–A5 jet engines;<BR>Model A320-233, Two IAE Model V2527E–A5 jet engines;<BR>Fuel:<BR>See Installation Manual - Documents CFM 2026 or IAE-0043<BR>SPECIFICATION<BR>NOMENCLATURE FRANCE U.S.A U.K.<BR>Kerosene Air 3405C ASTM D 1655 (JET A1) (JET A) DERD 2494<BR>Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454<BR>Air 3407 (TR4) MIL-T 5624 (JP4) DERD 2454<BR>High Flash Point Air 3404 MIL-T 5624 (JP5) DERD 2452<BR>Additives: See CFMI “Specific Operating Instructions”, CFM TPOI-13 or IAE V2500 “Installation and Operation Manual”<BR>IAE-0043, 4.5. The above mentioned fuels and additives are also suitable for the APU.<BR>Engine Limits:<BR>CFMI CFM56-<BR>5A1<BR>CFMI CFM56-<BR>5A3<BR>CFMI CFM56-<BR>5B4 or -5B4/P or<BR>–5B4/2P<BR>IAE V2500-A1 IAE V2527-A5<BR>or V2527E-A5<BR>Engine Limitation Data Sheets Data Sheets Data Sheets Data Sheets Data Sheets<BR>E28NE (FAA) E28NE (FAA) E37NE E38NE FAA E31NE (FAA) E40NE (FAA)<BR>Static Thrust at Sea<BR>Level<BR>- Take-off (5 min)**<BR>(Flat rated 30°C)<BR>11 120 daN<BR>(25,000 lb)<BR>11 787 daN<BR>(26,500 lb)<BR>12 010 daN<BR>(27,000 lb)<BR>11 030 daN<BR>(24,800 lb)<BR>11 030 daN<BR>(24,800 lb)<BR>- Maximum Continuous<BR>(Flat rated 25°C)<BR>10 542 daN<BR>(23,600 lb)<BR>10 542 daN<BR>(23,600 lb)<BR>10 840daN<BR>(24,370 lb)<BR>9 890 daN<BR>(22,240lb)<BR>9 890 daN<BR>(22,240lb)<BR>Maximum Engine<BR>Speed<BR>- N1 rpm (%) 5,100 (102) 5,100 (102) 5,200 (104) 5,465 (100) 5,650 (100)<BR>- N2 rpm (%) 15,183(105) 15,183(105) 15,183(105) 14,915(100) 14,950(100)<BR>Eng. limit/<BR>Max Gas Temp.(°C) ECAM<BR>- Take-off (5 min)** 890 915/890 950 635 645<BR>- Max Continuous 855 880/855 915 610 610<BR>- Starting* 725 725/725 725 635 650<BR>A28NM Page 9 of 22<BR>Maximum Oil Temp.<BR>(Supply Pump Inlet; °C)<BR>-Takeoff, Stabilized 140 140 140 155 155<BR>-Transient<BR>(15 min max)<BR>155 155 155 165 165<BR>Min. Press. (PSI) 13 13 13 60 60<BR>Approved oils See SB See SB See SB See doc IAE See doc IAE<BR>CFMI 79-001-<BR>0X<BR>CFMI 79-001-<BR>0X<BR>CFMI 79-001-0X 0043 (MIL-L<BR>23699)<BR>0043 (MIL-L<BR>23699)<BR>* 4 consecutive cycles of 2 minutes each.<BR>** 10 minute at take-off thrust allowed in case of engine failure (at take-off and during go-around)<BR>Airspeed Limits (Indicated Airspeed - IAS - Unless otherwise Stated:<BR>- Maximum Operating Mach - MMO: 0.82<BR>- Maximum Operating Speed - VMO: 350 kt<BR>- Maneuvering Speed VA: - See Chapter 2.0 of the DGAC-approved Flight Manual<BR>- Extended Flaps/Slats Speed - VFE<BR>Configuration Slats/Flaps VFE (Kt)<BR>1 18/0 230 Intermediate<BR>Approach<BR>*18/10 215 Take-off<BR>2 22/15 200 Take-off and<BR>Approach<BR>3 22/20 185 Take-off,<BR>Approach, and<BR>Landing<BR>Full 27/35 177 Landing<BR>* Auto flap retraction at 210 kt in Take-off configuration.<BR>Landing Gear:<BR>- VLE - Extended 280 Kt/Mach 0.67<BR>- VLO - Extension 250 kt<BR>- Retraction 220 kt<BR>Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph)<BR>Minimum Control Speed:<BR>A320-100:<BR>- VMCA (Air): 105 kt<BR>- VMCG (Ground): 102 kt (all config.)<BR>A320-200:<BR>- VMCA (Air) and VMCG (Ground): See TAB program issue M or N with associated A/C performances module<BR>Maximum Weights:<BR>A320-100:<BR>000<BR>VARIANT (BASIC)<BR>(KG) (LBS)<BR>Max. Ramp Weight 68,400 150,820<BR>Max. Take-off Weight 68,000 149,940<BR>Max. Landing Weight 63,000 138,915<BR>Max. Zero Fuel Weight 59,000 130,100<BR>A28NM Page 10 of 22<BR>A320-200:<BR>FAA Approved<BR>Weight Variants<BR>000<BR>BASIC<BR>001 003 007 008 009 010 011 012 013 014<BR>A320-211 YES YES YES YES YES YES YES YES YES<BR>A320-212 YES YES YES YES YES YES YES YES YES YES<BR>A320-214 YES YES YES YES YES YES YES YES YES YES<BR>A320-231 YES YES YES YES YES YES YES YES YES<BR>A320-232 YES YES YES YES YES YES YES YES YES YES<BR>A320-233 YES YES YES YES YES YES YES YES YES YES<BR>VARIANT 000<BR>BASIC<BR>001 003 007 008 009 010 011 012 013 014<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>(KG)<BR>(LBS)<BR>Max. Ramp<BR>Weight<BR>73900<BR>162949<BR>68400<BR>150822<BR>75900<BR>167360<BR>77400<BR>170667<BR>73900<BR>162950<BR>75900<BR>167360<BR>77400<BR>170667<BR>75900<BR>167360<BR>77400<BR>170667<BR>71900<BR>158512<BR>73900<BR>162949<BR>Max. Takeoff<BR>Weight<BR>73500<BR>162068<BR>68000<BR>149940<BR>75500<BR>166478<BR>77000<BR>169785<BR>73500<BR>162068<BR>75500<BR>166478<BR>77000<BR>169785<BR>75500<BR>166478<BR>77000<BR>169785<BR>71500<BR>157631<BR>73500<BR>162068<BR>Max.<BR>Landing<BR>Weight<BR>64500<BR>142223<BR>64500<BR>142223<BR>64500<BR>142223<BR>64500<BR>142223<BR>64500<BR>142223<BR>64500<BR>142223<BR>64500<BR>142223<BR>66000<BR>145505<BR>66000<BR>145505<BR>64500<BR>142223<BR>64500<BR>142223<BR>Max. Zero<BR>Fuel<BR>Weight<BR>60500<BR>133403<BR>60500<BR>133403<BR>60500<BR>133403<BR>60500<BR>133403<BR>61000<BR>134505<BR>61000<BR>134505<BR>61000<BR>134505<BR>62500<BR>137789<BR>62500<BR>137789<BR>61000<BR>134505<BR>61500<BR>135584<BR>Minimum Weight:<BR>A320-100:<BR>VARIANT 000<BR>(BASIC)<BR>(KG) (LBS)<BR>Minimum Weight 36,750 81,030<BR>A320-200:<BR>VARIANT All<BR>(KG) (LBS)<BR>Minimum Weight 37,230 82,080<BR>Minimum Crew:<BR>2 Pilots<BR>Maximum Passengers:<BR>179<BR>Maximum Baggage:<BR>CARGO COMPARTMENT MAXIMUM LOAD<BR>(KG) (LBS)<BR>Forward 3,402 7,500<BR>Aft 4,536 10,000<BR>Rear (Bulk) 1,497 3,300<BR>For the positions and the loading conditions authorized in each position (references of containers, pallets, and associated<BR>weights), see Weight and Balance Manual, ref. 00D080A0001/C1S Chapter 1.10.<BR>A28NM Page 11 of 22<BR>Fuel Capacity (0.8 kg/liter):<BR>A320-100:<BR>2-Tank Airplane<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,843 4,185 57.3 15.1<BR>(12,674) (27,946) (45.8) (101.0)<BR>Total 15,843 4,185 57.3 15.1<BR>(12,674) (27,946) (45.8) (101.0)<BR>3-Tank Airplane<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,843 4,185 58.9 15.6<BR>(12,674) (27,946) (47.1) (103.9)<BR>Center 8,250 2,179 23.2 6.1<BR>(6,600) (14,484) (19.6) (43.2)<BR>TOTAL 24,093 6,364 82.1 21.7<BR>(19,274) (42,430) (65.7) (147.1)<BR>A320-200:<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,609 4,124 58.9 15.6<BR>(12,487) (27,534) (47.1) (103.9)<BR>Center 8,250 2,179 23.2 6.5<BR>(6,600) (14,484) (19.6) (41.0)<BR>TOTAL 23,859 6,304 82.1 20.8<BR>(19,087) (42,087) (65.7) (144.9)<BR>Oil Capacity:<BR>CFMI CFM56-5A/5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters).<BR>IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters)<BR>Maximum Operating Altitude:<BR>- 39,800 feet (12,200 m) clean if modification 30748 is embodied.<BR>- 39,100 feet (12,000 m) clean.<BR>- 20,000 feet (6,500 m) Slats/Flaps extended.<BR>Equipment:<BR>The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraft for<BR>certification.<BR>Equipment approved for installation are listed in the definition of the reference model and the modification applicable to it.<BR>Refer to Type Certification Standard Equipment List 00D000A0101/C1S.<BR>Refer Note 4 for list of A320 airplane model FAA Type Definitions.<BR>Serial Numbers Eligible:<BR>A320 aircraft, all series, all models, are produced in Blagnac (France) under approval P09 or F.G.035 issued by DGAC to<BR>Airbus.<BR>A French "Certificat de Navigabilite pour Exportation," endorsed as noted under "Import Requirement," must be submitted for<BR>each individual aircraft for which application for U.S. certification is made.<BR>A28NM Page 12 of 22<BR>Import Requirements:<BR>A FAA Standard Airworthiness Certificate may be issued on the basis of a French "Certificat de Navigabilite pour Exportation,"<BR>signed by a representative of the Direction Generale de 1'Aviation Civile (DGAC) of France, containing the following statement:<BR>"The Airplane covered by this certificate has been examined, tested, and found to conform to the Type Design approved under<BR>Type Certificate No. A28NM and to be in condition for safe operation."<BR>The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of<BR>manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated<BR>under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections<BR>21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require<BR>certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical<BR>way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type<BR>design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness<BR>Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.<BR>Certification Basis<BR>a. Part 25 of the FAR effective February 1, 1965, including Amendments 25-1 through 25-56 thereto.<BR>b. Special Federal Aviation Regulation (SFAR) No.27 effective February 1, 1974, including Amendments 27-1 through<BR>27-5.<BR>c. Part 36 of the FAR effective December 1, 1969, including Amendments 36-1 through 36-12.<BR>d. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the<BR>Federal Register, as follows:<BR>(1) January 27, 1989:<BR>- Electronic Flight Controls<BR>- Active Controls<BR>- Engine Controls and Monitoring<BR>- Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy<BR>- Flight Characteristics<BR>- Flight Envelope Protection<BR>- Side Stick Controllers<BR>- Flight Recorder.<BR>(2) June 9, 1989:<BR>- Computerized Airplane Flight Manual<BR>e. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC<BR>120-28c.<BR>For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for<BR>automatic landing and by AC 25.1329-1A for cruise.<BR>Use of JAR AWO where applicable to the requirements above, is acceptable.<BR>f. The following paragraphs of the FAR have been complied with through equivalent safety demonstrations:<BR>- 25.783(e) for cargo doors<BR>- 25.783(f) for passenger doors and bulk cargo door<BR>- 25.813(c) for emergency exit access<BR>- 25.811(e)(3) Type III emergency exit marking.<BR>g. Optional Requirements elected:<BR>- 25.801 for ditching.<BR>- 25.1419 for icing.<BR>Note 1 - Weight and Balance<BR>a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated<BR>empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,<BR>except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"<BR>contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or<BR>refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage<BR>compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in<BR>the passenger compartment.<BR>A28NM Page 13 of 22<BR>b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear<BR>retraction and movement of crew and passengers from their assigned positions.<BR>c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty<BR>weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.<BR>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<BR>critical flight attitude, including the unusable tank fuel as defined by FAR part 26.959. (The usable fuel in the crossfeed<BR>manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct<BR>weight and CG for take-off.)<BR>e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as<BR>defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be<BR>accounted for separately.<BR>f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the<BR>tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only<BR>the usable oil for which the tanks must be placarded.<BR>Note 2:<BR>The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is<BR>considered equivalent to "FAA-approved".)<BR>Note 3:<BR>Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness<BR>Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.<BR>Note 4:<BR>The A320 basic definition for U.S. import certification is contained in the following documents:<BR>- AI/A 414.282/88 for the A320 Models -111 and -211<BR>- AI/EA-A 413.628/89 for the A320 Model -231<BR>- AI/EA-A 412.1631/90 for the A320 Model -212<BR>- AI/EA-A 414.0665/93 for the A320 Model -232<BR>- AI/EA-S 413.2143/95 for the A320 Model -233<BR>- AI/EA-S 413.0150/95 for the A320 Model -214<BR>- AI/EA-S 413.3004/96 (supplement) for the A320 Model -214.<BR>Note 5:<BR>Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89<BR>“Certification Maintenance Requirements (FAA version)” (CMR).<BR>Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/<BR>95A.0252/96 “Airworthiness Limitation Items”.<BR>Note 6:<BR>If modification 20758 is embodied, the airplane is certified for CAT III B precision approach (fail operational) and landing. This<BR>does not constitute an operational approval.<BR>Note 7:<BR>All Models of A320 airplanes manufactured after January 1, 1997 must have either modification 25302 (for IAE engines) or<BR>25303 (for CFM engines) installed, before the individual U.S. standard Certificate of Airworthiness can be issued.<BR>Note 8:<BR>If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine<BR>denomination changes to /P.<BR>CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.<BR>A28NM Page 14 of 22<BR>Note 9:<BR>If modification 26610 is embodied on A320-214 airplanes, the engine performance and gaseous emission levels are improved.<BR>The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).<BR>CFM56-5B4/P engine can be intermixed with CFM56-5B4/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft<BR>(AFM Supplement).<BR>Note 10:<BR>For A320-200 series airplanes with OCTOPUS Airplane Flight Manual, Airbus elected to comply with Part 25 Amendment 25-<BR>92.<BR>III. Type A321-100/200 Series Transport Category Airplanes<BR>Model A321-111, Approved December 20, 1995;<BR>Model A321-112, Approved December 20, 1995;<BR>Model A321-131, Approved December 20, 1995;<BR>Model A321-211, Approved September 18, 1997;<BR>Model A321-231, Approved September 18, 1997:<BR>Engines:<BR>Model A321-111, Two CFMI Model CFM56-5B1 or CFM56-5B1/P or CFM56-5B1/2P jet engines;<BR>Model A321-112, Two CFMI Model CFM56-5B2 or CFM56-5B2/P jet engines;<BR>Model A321-131, Two IAE Model V2530-A5 jet engines<BR>Model A321-211, Two CFMI Model CFM56-5B3/P or CFM56-5B3/2P jet engines<BR>Model A321-231, Two IAE Model V2533-A5 jet engines<BR>See Note 14 for description of “P” engine designations<BR>Fuel:<BR>See Installation Manual - Documents CFM 2026 or IAE-0043<BR>SPECIFICATION<BR>NOMENCLATURE FRANCE U.S.A U.K.<BR>Kerosene MIL-T83133A (JP8)<BR>Air 3405C ASTM D 1655 (JET A1) (JET A) DERD 2494<BR>Wide Cut Air 3407 ASTM D 1655 (JET B) DERD 2454<BR>Air 3407 (TR4) MIL-T 5624 (JP4) DERD 2454<BR>High Flash Point Air 3404 MIL-T 5624 (JP5) DERD 2452<BR>Additives: See CFMI "Specific Operating Instructions," CFM TPOI-13 or IAE V2500 “Installation and Operating Manual”<BR>IAE-0043, 4.5. The above mentioned fuels and additives are also suitable for the APU.<BR>Engine Limits<BR>CFMI CFM56-5B1 or -5B1/P<BR>or –5B1/2P<BR>CFMI CFM56-5B2 or -5B2/P CFMI CFM56-5B3/P<BR>or –5B3/2P<BR>Engine Limitation Data Sheets Data Sheets Data Sheets<BR>E37NE E38NE (FAA) E37NE E38NE (FAA) E37NE E38NE (FAA)<BR>Static Thrust at Sea Level<BR>- Take-off (5 min)** 13 344 daN (30,000 lb) 13 789 daN (31 000 lb) 14 234 daN (32,000 lb)<BR>(Flat rated 30°C)<BR>Maximum Continuous 12 940 daN (29,090 1b) 12 940 daN (29,090 1b) 12940 daN (29,090 lb)<BR>(Flat rated 25°C)<BR>Maximum Engine Speed<BR>- N1 rpm (%) 5,200 (104) 5,200 (104) 5,200 (104)<BR>- N2 rpm (%) 15,183 (105) 15,183 (105) 15,183 (105)<BR>Max Gas Temperature<BR>(°C)<BR>- Take-off (5 min)** 950 950 950<BR>- Max Continuous 915 915 915<BR>- Starting * 725 725 725<BR>A28NM Page 15 of 22<BR>Max Oil Temperature<BR>(Supply Pump Inlet; °C)<BR>- Take-off, Stabilized 140 140 140<BR>- Transient (15 min max) 155 155 155<BR>Min. Press. (PSI) 13 13 13<BR>Approved Oils See SB CFMI 79-001-OX See SB CFMI 79-001-OX See SB CFMI 79-001-OX<BR>IAE V2530-A5 IAE V2533-A5<BR>Engine Limitation Data Sheets E40NE (FAA) Data Sheets E40NE (FAA)<BR>Static Thrust at Sea Level<BR>- Take-off (5 min)** 13 300 daN (29,900 lb) 14 055 daN (31,600 lb)<BR>(Flat rated 30°C)<BR>Maximum Continuous 11 988 daN (26,950 1b) 11 988 daN (26,950 lb)<BR>(Flat rated 25°C)<BR>Maximum Engine Speed<BR>- N1 rpm (%) 5,650 (100) 5,650 (100)<BR>- N2 rpm (%) 14,950 (100) 14,950 (100)<BR>Maximum Gas Temperature (°C)<BR>- Take-off (5 min)** 645 645<BR>- Max Continuous 610 610<BR>- Starting * 650 650<BR>Maximum Oil Temperature<BR>(Supply Pump Inlet; °C)<BR>- Take-off, Stabilized 155 155<BR>- Transient (15 min max) 165 165<BR>Min. Press. (PSI) 60 60<BR>Approved Oils See Doc IAE 0043 Sec 4.9 See Doc IAE 0043 Sec 4.9<BR>(MIL-L-23699) (MIL-L-23699)<BR>* 4 Consecutive cycles of 2 minutes each.<BR>**10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around)<BR>Airspeed Limits (Indicated Airspeed - IAS - Unless otherwise Stated:<BR>- Maximum Operating Mach - MMO: 0.82<BR>- Maximum Operating Speed - VMO: 350 kt<BR>- Maneuvering Speed VA: - See Chapter 2.0 of the DGAC-approved Flight Manual<BR>- Extended Flaps/Slats Speed - VFE<BR>Configuration Slats/Flaps VFE (Kt)<BR>1 18/0 230** Intermediate Approach<BR>18/10 215** Take-off<BR>2 22/14 205 Take-off and Approach<BR>215*<BR>3 22/21 195 Take-off, Approach, and<BR>Landing<BR>Full 27/25 190 Landing<BR>* See Note 12<BR>** See Note 18<BR>Landing Gear:<BR>- VLE - Extended: 280 Kt/Mach 0.67<BR>- VLO - Extension: 250 kt<BR>- Retraction: 220 kt<BR>Tire Limit Speed (Ground Speed) = 195.5 kt (225 mph)<BR>Minimum Control Speed:<BR>- VMCA (Air): 105 kt<BR>- VMCG (Ground): 102 kt (all config.)<BR>A28NM Page 16 of 22<BR>Maximum Weights:<BR>A321-100:<BR>000 002 003<BR>VARIANT BASIC Mod 24178 Mod 24899<BR>(KG) (LBS) (KG) (LBS) (KG) (LBS)<BR>Max. Take-off Weight 83,000 182,983 83,000 182,983 85,000 187,391<BR>Max. Landing Weight 73,500 162,040 74,500 164,243 74,500 164,243<BR>Max. Zero Fuel Weight 69,500 153,220 70,500 155,424 70,500 155,424<BR>A321-200:<BR>000 001<BR>VARIANT BASIC Mod 28960<BR>(KG) (LBS) (KG) (LBS)<BR>Max. Take-off Weight 89,000 196,210 93,000 205,027<BR>Max. Landing Weight 75,500 166,448 77,800 171,517<BR>Max. Zero Fuel Weight 71,500 157,629 73,800 162,699<BR>Minimum Weight:<BR>VARIANT All<BR>(KG) (LBS)<BR>Minimum Weight 47,500 104,718<BR>Minimum Crew:<BR>2 Pilots<BR>Maximum Passengers:<BR>220<BR>Maximum Baggage:<BR>CARGO COMPARTMENT MAXIMUM LOAD<BR>(KG) (LBS)<BR>Forward 5,670 12,500<BR>Aft 5,670 12,500<BR>Rear (Bulk) 1,497 3,300<BR>For the positions and the loading conditions authorized in each position (references of containers, pallets, and associated<BR>weights), see Weight and Balance Manual, ref. 00E080A0001/C1S Chapter 1.10.<BR>Fuel Capacity (0.8 kg/liter):<BR>A321-100 and A321-200:<BR>3-Tank Airplane<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,500 4,094 22.6 6<BR>(12,400) (27,331) (18) (39.6)<BR>Center 8,200 2,166 23.2 6.1<BR>(6,560) (14,460) (18.6) (40.97)<BR>TOTAL 23,700 6,260 45.8 12.1<BR>(18,960) (41,791) (36.6) (80.62)<BR>A28NM Page 17 of 22<BR>A321-200:<BR>4-Tank Airplane (high pressure ACT system)<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>Wing 15,500 4,094 22.6 6<BR>(12,400) (27,331) (18) (39.6)<BR>Center 8,200 2,166 23.2 6.1<BR>(6,560) (14,460) (18.6) (40.97)<BR>ACT 2,900 766 17 4.5<BR>(2,320) (5,114) (13.6) (29.96)<BR>TOTAL 26,600 7,026 62.8 16.6<BR>(21,280) (46,905) (50.2) (110.58)<BR>4 to 5-Tank Airplane<BR>(low pressure ACT system)<BR>Tank Usable Fuel Unusable Fuel<BR>Liters (kgs) Gallons (lbs) Liters (Kgs) Gallons (lbs)<BR>TOTAL<BR>3-Tank 23,700 6,260 45.8 12.1<BR>Airplane (18,960) (41,791) (36.6) (80.62)<BR>ACT 1 2,992 790 17 4.5<BR>(2,393) (5,274) (13.6) (29.96)<BR>TOTAL<BR>4-Tank 26,692 7,050 62.8 16.6<BR>Airplane (21,353) (47,065) (50.2) (110.58)<BR>ACT 2 2,992 790 17 4.5<BR>(2,393) (5,274) (13.6) (29.96)<BR>TOTAL<BR>5-Tank 29,684 7,840 79.8 21.1<BR>Airplane (23,746) (52,339) (63.8) (140.54)<BR>Oil Capacity:<BR>CFMI CFM56-5B - Engine Oil Capacity, 10 quarts/engine (9.46 liters).<BR>IAE V2500-A5 - Engine Oil Capacity, 7 quarts/engine (6.6 liters)<BR>Maximum Operating Altitude:<BR>- 39,800 feet (12,200 m) clean if modification 30748 is embodied.<BR>- 39,100 feet (12,000 m) clean.<BR>- 20,000 feet (6,500 m) Slats/Flaps extended.<BR>Equipment:<BR>The basic equipment as prescribed in the airworthiness regulations (see certification basis) must be installed in the aircraft for<BR>certification. Equipment approved for installation are listed in the definition of the reference model and the modification<BR>applicable to it. Refer to Type Certification Standard Equipment Schedule Lists:<BR>- 00E000A0007/C1S for A321-111 Model<BR>- 00E000A0006/C1S for A321-112 Model<BR>- 00E000A0004/COS for A321-131 Model<BR>- 00E000A0211/COS for A321-211 Model<BR>- 00E000A0231/COS for A321-231 Model<BR>Refer to Note 4 for list of A321 airplane model FAA Type Definitions.<BR>Serial Numbers Eligible:<BR>A321 Aircraft, all series, all models, are produced in Hamburg (Germany) under approval LBA.G.0009 or I-A9 issued by LBA to<BR>Airbus.<BR>A German Export Certificate of Airworthiness endorsed as noted under “Import Requirement”, must be submitted for each<BR>individual aircraft for which application for U.S. certification is made.<BR>A28NM Page 18 of 22<BR>Import Requirements:<BR>A FAA Standard Airworthiness Certificate may be issued on the basis of a German Export Certificate of Airworthiness, signed<BR>by a representative of the Luftfahrt-Bundesamt (LBA) of Germany, containing the following statement: “The airplane covered by<BR>this certificate has been examined, tested, and found to conform to the type design approved under Type Certificate No. A28NM<BR>and to be in condition for safe operation.”<BR>The U.S. airworthiness certification basis for aircraft type certificated under FAR Section 21.29 and exported by the country of<BR>manufacture is FAR Sections 21.183(c) or 21.185(c). The U.S. airworthiness certification basis for aircraft type certificated<BR>under FAR Section 21.29 exported from countries other than the country manufacture (e.g., third party country) is FAR Sections<BR>21.183(d) or 21.185(b). Notwithstanding that FAR section 21.183(d) and 25.185(b) do not specifically address or require<BR>certification by the foreign civil airworthiness authority of the country of manufacture, such certification is the only practical<BR>way for an applicant to show, and the Federal Aviation Administration (FAA) to find conformity to the FAA-approved type<BR>design and condition for safe operation. Additional guidance is contained in FAA advisory Circular 21-23, Airworthiness<BR>Certification of Civil Aircraft, Engines, Propellers, and Related Products Imported into the United States.<BR>Certification Basis (A321-100 and A321-200)<BR>a. Part 25 of the FAR effective February 1, 1965, including amendments 25-1 through 25-56 thereto.<BR>b.1. Plus the following sections of Part 25 as amended by amendments 25-1 through:<BR>- 25-58 (Section 25.812(e))<BR>- 25-63 (Section 25.25(a)(3))<BR>- 25-67 (Section 25.807(c)(7))<BR>- 25-70 (Section 25.1411(a)(2))<BR>(Applied per FAA derivative aircraft policy – reference FAA order 8110.4A)<BR>b.2. Airbus elected to comply with portions of FAR 25.562, Amendment 64, for the passenger seats only. FAR<BR>paragraphs 25.562(c)(5) and 25.562(c)(6) do not apply.<BR>c. Part 34 of the FAR effective September 10, 1960, including amendments 34-1.<BR>d. Part 36 of the FAR effective December 1, 1965, including amendments 36-1 through 36-20 thereto.<BR>e. FAA Special Conditions issued for the A320 in accordance with Section 21.16 of the FAR and published in the<BR>Federal Register as follows:<BR>1) January 27, 1989:<BR>- Electronic Flight Controls<BR>- Active Controls<BR>- Engine Controls and Monitoring<BR>- Protection from Lightning and Unwanted Effects of Radio Frequency (RF) Energy<BR>- Flight Characteristics<BR>- Flight Envelope Protection<BR>- Side Stick Controllers<BR>- Flight Recorder.<BR>(2) June 9, 1989<BR>- Computerized Airplane Flight Manual<BR>f. For precision approach and landing, the applicable technical requirements are complemented by AC 120-29 and AC<BR>120-28c.<BR>For the automatic flight control system, the applicable technical requirements are complemented by AC 20-57A for<BR>automatic landing and by AC 25.1329-1A for cruise.<BR>Use of JAR AWO where applicable to the requirements above, is acceptable.<BR>g. The following sections of the FAR have been complied with through equivalent safety demonstrations in addition to<BR>the equivalent safety findings applicable from the original A320 certification basis:<BR>- 25.101, 25.105, 25.109, 25.113, 25.115, 25.735, for rejected take-off and landing performance<BR>- 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<BR>criteria<BR>-25.783(e) bulk cargo door<BR>- 25.783(f) for passenger doors<BR>- 25.807(c) for maximum passenger capacity<BR>- 25.933(a) for thrust reversing system.<BR>h. Optional requirements elected:<BR>- 25.801 for ditching.<BR>- 25.1419 for icing.<BR>A28NM Page 19 of 22<BR>Note 1 - Weight and Balance<BR>a. Current weight and balance report including list of equipment, entitled "Aircraft Inspection Report" included in certificated<BR>empty weight, and loading instructions, must be in each aircraft at the time of original certification and at all times thereafter,<BR>except in the case of operators having an approved weight control system. Airbus report, " Weight and Balance Manual,"<BR>contains loading information for each airplane and interior arrangement configuration as delivered. This report contains, or<BR>refers to, information relative to location of all passengers and crew member seats, location and capacity of all cargo and baggage<BR>compartments, buffets, storage spaces and coat rooms, location and capacity of lounges, lavatories, and the required placards in<BR>the passenger compartment.<BR>b. The airplane must be loaded so that the CG is within specified limits at all times, considering fuel loading usage, gear<BR>retraction and movement of crew and passengers from their assigned positions.<BR>c. The weights of system fuel and oil, as defined below, and hydraulic fluid, all of which must be included in the airplane empty<BR>weight, are listed for each airplane in the Weight and Balance Manual specified in paragraph a. above.<BR>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<BR>critical flight attitude, including the unusable tank fuel as defined by FAR part 26.959. (The usable fuel in the crossfeed<BR>manifold lines, manifolds, and engine that is not part of the system fuel must be included in the total usable fuel to obtain correct<BR>weight and CG for take-off.)<BR>e. The unusable fuel is that amount of fuel in the tanks which is unavailable to the engines under critical flight conditions as<BR>defined in FAR Part 25.959. This "unusable" fuel is included in System Fuel as indicated in paragraph d. above, and need not be<BR>accounted for separately.<BR>f. System oil is the weight of all remaining in the engine, constant speed drive, lines, and tanks after subtracting the oil in the<BR>tanks which is above the standpipe (zero gauge) levels. The engine oil capacities shown elsewhere in this data sheet include only<BR>the usable oil for which the tanks must be placarded.<BR>Note 2:<BR>The aircraft must be operated in accordance with the DGAC-approved FAA Airplane Flight Manual. ("DGAC-approved" is<BR>considered equivalent to "FAA-approved".)<BR>Note 3:<BR>Life limitations are provided in the A319/A320/A321 Maintenance Planning Document, Section 9 “Airworthiness<BR>Limitation Section”, Sub-Sections 9-1-2 and 9-1-3 - Approved by DGAC.<BR>Note 4:<BR>The A321 basic definition for U.S. import certification is contained in the following documents:<BR>- 00E000A0010/C11 for A321-111 model<BR>- 00E000A0011/C11 for A321-112 model<BR>- 00E000A0012/C11 for A321-131 model<BR>- AI/EA-S 413.3365/96 (supplement) for A321-111/112/131 models<BR>- AI/EA-S 413.0401/97 for A321-211 model<BR>- AI/EA-S 413.0399/97 for A321-231 model.<BR>Note 5:<BR>Maintenance criteria to comply with certification requirements for systems are given in Airbus Document AI/ST4/955.061/89<BR>“Certification Maintenance Requirements (FAA version)” (CMR).<BR>Maintenance criteria to comply with certification requirements for structure are given in Airbus Document AI/SEM4/<BR>95A.0252/96 “Airworthiness Limitation Items”.<BR>Note 6:<BR>Door 2 and/or Door 3 may be derated to Type III.<BR>Note 7:<BR>If modifications 24173 and 22853 are embodied on models with IAE engines, the aircraft is qualified for Cat II precision<BR>approach. This does not constitute operational approval.<BR>A28NM Page 20 of 22<BR>Note 8:<BR>If modification 24064 is embodied on models with CFM engines, the aircraft is qualified for Cat III precision approach. This<BR>does not constitute operational approval.<BR>Note 9:<BR>If modification 24066 is embodied on models with IAE engines, the aircraft is qualified for Cat III precision approach. This does<BR>not constitute operational approval.<BR>Note 10:<BR>If modification 25199 is embodied on models with CFM engines, the aircraft is qualified for Cat III B precision approach. This<BR>does not constitute operational approval.<BR>Note 11:<BR>If modification 25200 is embodied on models with IAE engines, the aircraft is qualified for Cat III B precision approach. This<BR>does not constitute operational approval.<BR>Note 12:<BR>If FWC Standard D2 and FAC standard BAM 0510 are fitted on A321 aircraft, VFE speed in configuration 2 is increased from<BR>205kts to 215kts (as identified by speed limitation placard installed by modification 24641).<BR>Note 13:<BR>Modifications 25302 (for IAE engine) and 25303 (for CFM engine) are part of the FAA Type Design, and shall be implemented<BR>on any A321 aircraft entered on the U.S. register, before the individual U.S. standard Certificate of Airworthiness be issued.<BR>Note 14:<BR>If modification 25800 is embodied on models with CFM56-5B engines, the engine performance is improved. The engine<BR>denomination changes to /P.<BR>CFM56-5B/”non-P” engine can be intermixed with CFM56-5B/P engine on the same aircraft.<BR>Note 15:<BR>On the series A321-200, one Additional Center Tank (ACT) in bulk version is defined by modification 25453 (high pressure<BR>system). Its approval together with structural and system provisions was subject of compliance demonstrated to Advisory<BR>Circular (AC) 25-8.<BR>Note 16:<BR>The type design definitions and certification standard equipment lists as referenced in Note 4 above are complemented by<BR>document 00D000A0546/C0S “A319-100/A321-200 FMGC Type Standard Evolution”.<BR>Note 17:<BR>On the series A321-200, one or two Additional Center Tanks (ACT) in bulk version are defined by modification 30422 (low<BR>pressure system). Their approval together with structural and system provisions was subject of compliance demonstrated to AC<BR>25-8.<BR>Note 18:<BR>On the series A321-200, Weight Variant 001, VFE speed in Configuration 1 is increased from 230 to 235 kts, and in<BR>Configuration 1+F increased from 215 to 225 kts (as identified by speed limitation placard installed by modification 28960).<BR>Note 19:<BR>If modification 26610 is embodied on A321-111airplanes, the engine performance and gaseous emission levels are improved.<BR>The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).<BR>CFM56-5B1/P engine can be intermixed with CFM56-5B1/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft<BR>(AFM Supplement).<BR>Note 20:<BR>If modification 27640 is embodied on A321-211airplanes, the engine performance and gaseous emission levels are improved.<BR>The engine denomination changes to /2P (DAC IIC Dual Annual Combustor).<BR>CFM56-5B3/P engine can be intermixed with CFM56-5B3/2P (DAC IIC Dual Annual Combustor) engine on the same aircraft<BR>(AFM Supplement).<BR>A28NM Page 21 of 22<BR>DATA PERTINENT TO ALL MODELS<BR>Auxiliary Power Unit (APU)<BR>GARRETT AIRESEARCH GTCP 36-300(A) (Standard)<BR>(Specification 31-5306B)<BR>APIC APS 3200 (Option - Mod 22562)<BR>(Specification ESR 0802, Rev A)<BR>AlliedSignal 131-9 (Option – Mod 25888)<BR>(Specification 4900 M1E 03 19 01)<BR>APU Limits:<BR>GTCP 36-300 (A)<BR>- Maximum Allowable Speed 69,204 rpm (107 %)<BR>- Maximum Gas Temperature<BR>at turbine outlet (ISA + 35°C)<BR>rated output 638°C<BR>overtemp. shutdown 711°C<BR>Maximum on starting 1038°C<BR>APS 3200<BR>- Maximum Rotor Speed 49,300 rpm (105 %)<BR>- Maximum EGT 742°C<BR>- Maximum for Start 900°C at altitudes below 25000 ft<BR>982°C at altitudes below 25000 ft<BR>131-9<BR>- Maximum Allowable Speed Nominal 51,728 rpm (106 %)<BR>Overshoot 53,875 rpm (110 %)<BR>- Maximum Gas Temperature<BR>at turbine outlet 675°C<BR>rated output (ISA + 23°C) 585°C<BR>overtemp. shutdown (ISA) 706°C<BR>maximum on starting (ISA) 1080°C below 35000 ft,<BR>1108°C above 35000 ft<BR>(ISA + 40°C) 1090°C below 35000 ft,<BR>1120°C above 35000 ft<BR>APU Approved oils:<BR>See GARRETT Report GT-7800 or in conformity with MIL-L-IAS, MIL-L23699 or DERD 2487 for the GTCP 36-300, Usable<BR>Capacity: 5.8 liters<BR>See APIC Maintenance Manual for approved oils for the APS 3200<BR>See Model Specification 31-12048A-3B for Allied Signal 131-9<BR>Center of Gravity Range (% Mean Aerodynamic Chord):<BR>See DGAC-Approved Airplane Flight Manual, U.S. Version.<BR>Hydraulic Fluids:<BR>- Type IV - Specification NSA 30.7110.<BR>- Capacity (Reservoirs and Systems):<BR>System Liters Gallons<BR>Green 100 26<BR>Yellow 75 20<BR>Blue 60 16<BR>Pressure: 3000 ± 200 PSI (207 ± 4 bar)<BR>A28NM Page 22 of 22<BR>Tires:<BR>- See Airbus Service Bulletin (SB) A320-32-1007<BR>Datum:<BR>Station 0 (100 inches forward of fuselage nose).<BR>Reference Mean Aerodynamic Chord (MAC):<BR>165.10 inches / 4.1935 m (leading edge of MAC: Sta. 700.85 inches).<BR>Leveling Means:<BR>Clinometer on the cabin seat track rails.<BR>Service Information:<BR>- Service bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and overhaul and maintenance manuals,<BR>which contain a statement that the document DGAC-approved, are accepted by the FAA and are considered FAA approved.<BR>These approvals pertain to the type design only. The reference to service bulletins includes any type of service instructions<BR>(letters, repair approvals, etc.). The reference to DGAC-approved includes findings made by DGAC designees and/or design<BR>organizations which are equally as acceptable as those made directly by the DGAC.<BR>- Other available service documents for the Airbus include:<BR>a. Illustrated Parts Catalog<BR>b. Wiring Diagram Manual<BR>c. Maintenance Manual<BR>-----END---- TYPE CERTIFICATION DATA SHEET A28NM
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