# TCDS A54NM: Ilyushin Aviation Complex - Type: Type certificate data sheet - Status: Current - Holder: Ilyushin Aviation Complex - Revision: 2 - Revised: November 30, 2006 - Product: Aircraft, Large Airplane - Certification basis: Part 25, Part 34, Part 36 - Data sheet PDF: https://openairdocs.org/files/sha256/14/32/14321f43696ccd1d7a5d5110cd1cea03e85edf7c72addc32711b06736378244c - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BB3F4194CC35B1768625723A00561EB6.0001 - Page: https://openairdocs.org/tcds/A54NM ## Models (1) As the data sheet lists them. - Il-96T (IL-96T) ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A54NM Revision 2 Ilyushin Aviation Complex Ilyushin Model Il-96T November 30, 2006 TYPE CERTIFICATE DATA SHEET NO. A54NM This data sheet which is part of Type Certificate No. A54NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the US Federal Aviation Regulations. Type Certificate Holder Ilyushin Aviation Complex Leningradsky Prospect, 45”G” 12590 Moscow R ussia 1. Model Ilyushin Il-96T (Transport Category Airplane) approved June 2, 1999 Engines 4 Pratt and Whitney PW-2337 turbofan engines. Refer to engine FAA-Type Certificate E17NE. Auxiliary Power Unit One gas turbine engine, Model VSU-10, Series 3, approved for ground use only. Manufactured by Omsk Design Bureau, Russia. Fuel The engines and APU must be operated with fuels and additives in accordance with PW SB No. 2016 (at the latest revision). Fuels RT and TS-1 GOST 10227-86 and fuel additives I, I-M, TGF, and TGF- M may be used in accordance with PW Document IEN No. 94MZ317 dated February 17, 1995. Oil The engines shall be operated with oils specified in PW Service Bulletin No. 238 (at the latest revision). Engine Model PW 2337 Limits Static thrust, sea level 37,530 lb. Maximum permissible rotor speed, rpm: - Low pressure rotor (N1) 4,575 - High pressure rotor (N2) 12,360 - High pressure rotor (N2), 5 seconds, transient 12,445 Maximum permissible turbine exhaust temperature (T4.9), °C/°F - Takeoff (5 minutes) 655/1211 - Takeoff (5 second transient) 670/1238 - Maximum continuous 625/1157 - Maximum continuous, (5 second transient) 640/1184 - At start up, ground 495/923 - At start up, in flight 655/1211 Maximum permissible oil outlet temperature, °C/°F - Continuous operation 163/325 - Transient operation (20 minutes) 177/350 For other limitations refer to engine Data Sheet E17NE Page No. 1 2 3 4 Rev. No. 1 0 0 1 A54NM Page 2 of 4 APU Limits Maximum bleed air flow from driven Compressor, sea level 3.5 kg/sec, not less Maximum load of AC generator (208/120 volts, 400hz ±2%): - 40 kVA during 10 hours duration - 60 kVA during 5 min duration - 80 kVA during 5 seconds duration When the maximum permissible value of either power turbine speed or gas generator speed, or gas temperature, or oil temperature is attained, or oil pressure is decreased below the permissible value (see the maintenance manual for the VSU-10, Section 049.70.30) automatic APU shutdown is provided. Airspeed Limits (I.A.S.) V MO 325 KIAS (600 km/h) M MO 0.84 VA (Maneuvering) See approved airplane flight manual. VFE (Flaps/slats Extended) Flaps/Slats 2°/3° 275 KIAS (510 km/h) 3°/25° 264 KIAS (490 km/h) 10°/25° 243 KIAS (450 km/h) 25°/25° 210 KIAS (390 km/h) 40°/25° 189 KIAS (350 km/h) VLO Extension 325 KIAS (600 km/h) Extension before an emergency descent 325 KIAS (600 km/h) VLE Maximum while extended 325KIAS (600 km/h) Maximum Tire Speed 254 MPH (221 knots, 410 km/h) Datum The aircraft reference zero datum point (QE 0) is located 5.91 in. (150 mm) aft of the fuselage nose cone and on the fuselage centerline. The 0% MAC datum is located 1195.145 in. (29340.7 mm) aft of the reference datum (QE 0). Mean Aerodynamic Chord The MAC length is 261.26 in. (6.636 m) Center of Gravity Limits FWD 10% MAC AFT 34% MAC Leveling Means Measuring marks are provided on the aircraft for leveling. These marks are indicated by special rivets or drillings as shown and described in the Leveling Drawing 1.9625.0011.000.000 with changes 9625.00.035.004.01 and 9625.00.035.002.01. Maximum Weights Max Ramp Weight: 597,440 lb. (271,000 kg) Max Takeoff Weight: 592,240 lb. (270,000 kg) Max Landing Weight: 485,000 lb. (220,000 kg) Max Zero Fuel Weight: 459,430 lb. (208,400 kg) Max Payload 202,390 lb. (92,000 kg) Minimum Crew 2 - Pilot and copilot Temporary Operating Limitation The aircraft must be operated by a flight crew consisting of a pilot and copilot, plus an additional person qualified as pilot in this airplane type, who shall monitor the aircraft performance and warnings. This temporary limitation is explained in the airplane flight manual, and is applicable until verification of the IDS, and ASCS software has been completed and the AFM limitation has been removed. Maximum Cabin Crew Four persons Page 3 of 4 A54NM Type of Baggage Compartment Class "E" Compartment (main deck cargo compartment) Class “E” Compartments (below the floor) Maximum Cargo Total of 202,820.96 lbs. (92,000 kg) on the main deck compartment - 59,523.54 lbs. (27,000 kg) in the forward lower compartment - 46,296.09 lbs. (21,000 kg) in the aft lower compartment - Maximum. floor loading = 82 lb./ft2 on the main deck Fuel Capacity 116,300 kg maximum, when γ = 0.775 254,672.6 lbs (115, 520 kg) usable Oil Capacity Oil capacity per Engine MAX OIL TANK MIN OIL TANK US Gallons 7.0 1.2 Liters 26.5 4.56 Maximum Operating Altitude 43,000 ft. (13,100 m) Control Surface Movements Wing Flaps 2°, 3°, 10°, 25°, and 40 ° Ailerons 31° up ( ±1.5°), 16° down (+1°, -1.5°) Elevator 17.5° up (+1.5°, -1°), 10° down (+2°, -0.5°) Stabilizer 12° nose up (+12’, -30’), 2° nose down ( ±12’) Rudder 27 ° right (-1°), 27° left (-1°) Serial Numbers S/N 976693201001T and subsequent. Import Requirements To be considered eligible for operation in the United States, each aircraft manufactured under this type certificate must be accompanied by a certificate of airworthiness for export or certifying statement endorsed by the exporting foreign civil airworthiness authority which states (in the English language): This aircraft conforms to its U.S. Type Design (Type Certificate No. A54NM) and is in a condition for safe operation. Certification Basis 14 CFR part 25 Effective February 1, 1965, including Amendments 25-1 through 25- 81. In addition, Ilyushin has elected to comply with Part 25 of the FAR as amended by Amendments 25-83 through 86. Special Conditions: - No. 25-ANM-135, “Ground Loads and Conditions for Central Landing Gear” - No. 25-ANM-135, “Design Maneuver Requirements - No. 25-ANM-135, “Effect of Flight Control Systems on Structure - No. 25-ANM-135, “High intensity Radiated Fields” Exemptions: - No. 6011 for FAR 25.571(e), Bird Strike Speed - No. 6754, Hydraulic Systems No. 6877, Partial Grant for Floor Warpage Test Requirements A54NM Page 4 of 4 Equivalent Level of Safety Findings: - Checked Maneuver Loads (FAR 25.331(c)(2)) - Premium Selection of Materials (FAR 25.603, 25.613) - Flap Gust Conditions (FAR 25.345) - Aircraft Pressurization Outflow and Safety Valves (FAR 25.841) - Unique Aural Overspeed Warning (FAR 25.1303(c)(1)) Optional Requirements complied with: - FAR 25.1419 Icing Environmental Standards complied with: - FAR Part 36 effective December 1, 1969, including Amendments 36-1 through 36-21. - FAR Part 34 effective September 10, 1990, including Amendment 34-1 Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see the Certification Basis) must be installed in the aircraft. The lists of all equipment as well as optional approved equipment are contained in the document: Type Design Definition Document No. Reg.W.9625.00.00183.872 (Master Drawing List) Airplane Flight Manual Aviation Register approved Airplane Flight Manual No. 9625 AFM, original issue, approved June 2, 1999 Service Information Service bulletins, repair instructions (letters, drawings, specifications, forms used for transmitting repair descriptions, etc.), structural repair manuals, airplane flight manuals, vendor manuals, and overhaul and maintenance manuals that are published in the English language and indicate applicability to the U.S. approved type designs included in this Type Certificate and that include a statement ”AR Approved” are accepted by the FAA and are considered ”FAA Approved.” NOTES NOTE 1. Current weight and balance report including a list of equipment included in certificated empty weight, and loading instructions when necessary must be provided for each aircraft at its delivery. For further information see Il-96T Weight & Balance Manual dated March 30, 1998 NOTE 2. Airworthiness Limitations including structural inspections and retirement times for safe-life parts are listed in Ilyushin Airworthiness Limitations Document N9625-701 CD dated November 4, 1998. NOTE 3. Certification Maintenance Requirements (CMR) are listed in the Il-96T CMR Document. Dated November 30, 1998 NOTE 4. Compliance with the optional ditching requirements of FAR 25.801, FAR 25.1411, and FAR 25.1415 has been shown. NOTE 5. FAA Certificate of Airworthiness is not to be issued until the Instructions for Continued Airworthiness, as defined in 14 CFR 25.1529 and Appendix H, have been approved. Contact the Seattle Aircraft Evaluation Group for information. NOTE 6. A FAA Certificate of Airworthiness is not to be issued until compliance is found to SFAR 88. ...END... ``` ## ADs None name its models. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.