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A300 · ATA 72 · Engine

Engine

Draft · under review

Sources: EASA TCDS EASA.A.172 Issue 08 (1 Feb 2026; pp.1, 7, 9, 11, 13, 15, 17, 20, 22, 24, 28, 29, 46, 48, 50, 52, 54, 62, 65 read as text, pp.7, 28, 50 and 62 also rendered and read visually), EASA TCDS EASA.IM.E.240 Issue 02 (23 Jul 2024, CF6-80 series; pp.1-4, 6, 9-12, 19, 22-25 read, pp.9, 10, 12 and 24 rendered and read visually), EASA TCDS EASA.IM.E.050 Issue 01 (19 Oct 2012, PW4000-94" series; pp.1, 3, 5, 6, 10 read, pp.6 and 10 rendered and read visually), FAA JASC code table (grouping and code descriptions only). This draft is for study only; it is not a maintenance document. It describes the engines themselves (ATA 72). Thrust rating tables and the powerplant installation are ATA 71 and are not written here; the engine types per A300 model are listed under 72-00 only to identify the engines concerned, and the thrust figures in the IM.E.240 Note 13 model differences are quoted only as part of that text; control system and fuel (ATA 73) and oil (ATA 79) are not covered. Model names and engine names are given as printed in each source, except that the spaces some A.172 lines print inside a name (for example "CF6 - 50C2", "CF6 50C2", "A300 F4-605 R") are closed up outside quotation marks. The aircraft-to-engine statements come only from TCDS A.172; the engine descriptions come only from the engine TCDS. IM.E.240 names no aircraft model; IM.E.050 names the Airbus aircraft only in the column heading "A300-600/A310" of its section V table, beside columns for B747-400, B767-200/300 and MD-11, and prints "Boeing 747" and "Boeing 767" in its ratings table. No description is carried from one engine model, one aircraft model or one engine family to another unless the source states it. The sub-section numbers 72-00, 72-30 and 72-50 are this site's grouping, following FAA JASC codes 7200, 7230 and 7250; neither of the two engine TCDS nor A.172 prints 72-xx numbering for these items.

A300 B-series and A300-600 engines · EASA aircraft and engine TCDS

72-00 General (engine models and what each source covers)

  • The FAA JASC table describes code 7200 as "the units and components which are used to induce and convert fuel-air mixture into power, and transmit power to the propeller shaft (if any) and accessory drives", for general engine reports. It is a US reporting taxonomy, not a description of the A300.[1]
  • TCDS A.172 is the aircraft type certificate data sheet for "AIRBUS A300, A310, A300-600"; it lists in each model's section the engine types for that model. It states after the thrust tables "Other powerplant limitations: see corresponding engine Type Certificate Data Sheets." (§10.2) and "Other powerplant limitations: see corresponding engine Type Certificate Data Sheet." (§20.2).[2][2][2]
  • A300 B4-600 series (A.172 §15.2, p.46), as printed: A300 B4-620 two PRATT & WHITNEY JT9D-7R4H1; A300 B4-601 two GENERAL ELECTRIC CF6-80C2A1; A300 B4-603 two GENERAL ELECTRIC CF6-80C2A3; A300 B4-622 two PRATT & WHITNEY PW 4158.[2]
  • A300 C4-620 (A.172 §16.2, p.48): two PRATT & WHITNEY JT9D-7R4H1.[2]
  • A300 B4-600R series (A.172 §17.2, p.50), as printed, each model label on the same line as the first of its engine entries: "Model A 300 B4-605 R: Two GENERAL ELECTRIC CF6-80C2A5 or CF6-80C2A3 turbofan engines (See Note 3), or Two GENERAL ELECTRIC CF6-80C2A5F turbofan engines (See Note 5)."; "Model A 300 B4-622 R: Two PRATT & WHITNEY PW 4158 turbofan engines". The ETOPS table of the same TCDS lists A300 B4-605R with GE CF6-80C2A5 and with GE CF6-80C2A5F, and A300 B4-622R with PW 4158.[2][2]
  • A300 F4-600R series (A.172 §18.2, p.52): A300 F4-605R two GENERAL ELECTRIC CF6-80C2A5 (See Note 3) or two CF6-80C2A5F; A300 F4-622R two PRATT&WHITNEY PW 4158.[2]
  • A300 C4-605R Variant F (A.172 §19.2, p.54): two GENERAL ELECTRIC CF6-80C2A5.[2]
  • A.172 Note 3 (p.65): on A300 B4-605R and F4-605R models equipped with CF6-80C2A5, the CF6-80C2A3 may be used, with the corresponding revision of the Flight Manual, supplement 11. Note 5 (p.65): on A300 B4-605R and F4-605R, installation of the FADEC-equipped CF6-80C2A5F is achieved by modification 8966.[2]
  • A.172 §20.2 (p.62) prints the engine data sheet references for the A300-600 engines as: GENERAL ELECTRIC DATA SHEET E13NE (FICHE DGAC M.IM 13) for CF6-80C2A1, CF6-80C2A3 and CF6-80C2A5/CF6-80C2A5F; PRATT & WHITNEY DATA SHEET E3N3 (FICHE DGAC M.IM 6) for "JT9D-7RH1"; PRATT & WHITNEY DATA SHEET E24NE (FICHE DGAC M.IM 18) for PW 4158. The same table prints the JT9D engine as "JT9D-7RH1", while §15.2 and §16.2 print "JT9D-7R4H1"; the two spellings differ in the source and are not reconciled here.[2][2][2]
  • The earlier A300 models (B1, B2-1A, B2-1C, B2K-3C, B2-202, B2-203, B2-320, B4-2C/-102/-103/-120/-203/-220, C4-203, F4-203) are marked "(surrendered)" on the A.172 cover page, and §10.2 (p.28) carries a "SURRENDERED" stamp. Their engines as printed: CF6-50A (B1, B2-1A), CF6-50C or CF6-50C2R (B2-1C, B2K-3C, B4-2C), CF6-50C1 (B2-202, B4-102), CF6-50C2 or CF6-50C2D (B2-203, B4-103, B4-203), JT9D-59A (B2-320, B4-120, B4-220), CF6-50C2 (C4-203, F4-203); B1 also "CF6-50C turbofan engines after embodiment of SB 71.014". No engine TCDS for the CF6-50 or JT9D-59A was read, so these engines are listed only as names (see Bekliyor).[2][2][2][2][2][2][2][2][2][2]
  • Only the A300-600 engines of A.172 §15-§19 that have an engine TCDS read here are described below: the CF6-80C2 models (EASA TCDS IM.E.240) and the PW 4158 (EASA TCDS IM.E.050). The JT9D-7R4H1 has no engine TCDS read (see Bekliyor).[2][2][2][2][2][2][2][2][2][2]
  • CF6-80C2 (A300 B4-601, B4-603, B4-605R, F4-605R, C4-605R Variant F as listed in A.172) - EASA TCDS IM.E.240: IM.E.240 is the data sheet "GENERAL ELECTRIC COMPANY CF6-80 series"; its model list includes CF6-80C2A1, -80C2A3, -80C2A5 and -80C2A5F (the models A.172 names for the A300-600) among others. Its certification basis section states "See FAA TCDS E13NE", the same number A.172 §20.2 prints as the GENERAL ELECTRIC data sheet for these engines.[3][3][2]
  • CF6-80C2 (A300 B4-601, B4-603, B4-605R, F4-605R, C4-605R Variant F as listed in A.172) - EASA TCDS IM.E.240: The Manufacturer entry lists GE Aviation and Safran Aircraft Engines (formerly SNECMA), the latter with a reference to Note 12.[3]
  • CF6-80C2 (A300 B4-601, B4-603, B4-605R, F4-605R, C4-605R Variant F as listed in A.172) - EASA TCDS IM.E.240: Model differences as printed in Note 13 (p.23-24): CF6-80C2A1 "Basic model (takeoff ideal thrust rating: 59,000 pounds)"; CF6-80C2A3 "Same as 80C2A1, except higher takeoff thrust rating (60,200 ideal). Corresponding PMC and MEC changes."; CF6-80C2A5 "Same as 80C2A1, except higher takeoff thrust rating (61,300 ideal). Corresponding PMC and MEC changes. Minor HPT and LPT hardware changes"; CF6-80C2A5F "Same as 80C2A1, except higher takeoff thrust rating (61,300 ideal). Minor HPT and LPT hardware changes. Incorporates Full Authority Digital Engine Control (FADEC), modulated active clearance control for the HPT and LPT, modulated bore cooling. Minor airframe related hardware changes, and added servo fuel heating system.".[3]
  • CF6-80C2 (A300 B4-601, B4-603, B4-605R, F4-605R, C4-605R Variant F as listed in A.172) - EASA TCDS IM.E.240: Note 14 (p.25) lists CF6-80C2A5 and CF6-80C2A5F among the models that "require the incorporation of" General Electric CF6-80C2 Service Bulletins 72-201, 72-222, 72-240, 72-241, 72-248, 72-255, 72-268, 77-005 and 77-006. This only reports the TCDS statement; no content of those bulletins was read.[3]
  • 72-30 Compressor section (CF6-80C2, PW4000-94): The FAA JASC table describes code 7230 as the engine section where incoming air is compressed, including (typical parts) fan blades; this is a US reporting taxonomy.[1]
  • 72-30 Compressor section (CF6-80C2, PW4000-94): CF6-80C2 series (the series description in IM.E.240 §III.2 lists CF6-80C2A1, A3, A5 and A5F among its models): "Dual rotor, axial flow high bypass turbofan. The 14-stage compressor is driven by a 2-stage high pressure turbine and the integrated front fan and low-pressure compressor are driven by a 5-stage low pressure turbine.".[3]
  • 72-30 Compressor section (CF6-80C2, PW4000-94): PW4000-94" series (the TCDS names PW4158 among its models; the description is given once for the series, not per model): "Axial airflow, dual-spool, turbofan, single-stage fan, 4-stage low pressure compressor, 11-stage high pressure compressor, annular combustor, 2-stage high pressure turbine, 4-stage low pressure turbine.".[4][4]
  • 72-50 Turbine section (CF6-80C2, PW4000-94): The FAA JASC table describes code 7250 as the engine section containing the turbine disc and associated nozzles and cases; a US reporting taxonomy.[1]
  • 72-50 Turbine section (CF6-80C2, PW4000-94): Turbine stage counts are in the descriptions quoted under 72-30: CF6-80C2 series 2-stage high pressure turbine and 5-stage low pressure turbine; PW4000-94" series 2-stage high pressure turbine and 4-stage low pressure turbine.[3][4]

72-00 Engine dimensions and dry weight, as printed (units as printed, not converted)

  • CF6-80C2 series, overall length 4273.8 mm (168.26 in), for all CF6-80C2 models in the table. Overall width and height are given in groups. Group listing CF6-80C2A1, -80C2A2, -80C2B1, -80C2B4, -80C2A3, -80C2B2, -80C2B6, -80C2A5, -80C2A8: width 2669.5 mm (105.10 in), height 2691.6 mm (105.97 in). Group listing CF6-80C2B1F, -B2F, -B4F, -B6F, -D1F, -B1F1, -B3F, -A5F, -B7F, -B5F, -B8F: width 2830.1 mm (111.42 in), height 2691.6 mm (105.97 in). The table is read visually: 2830.1 sits in the Overall Width column and the height cell is one cell spanning both groups.[3]
  • CF6-80C2 dry weight as printed: series row listing CF6-80C2A1, -A2, -A3, -A5, -A8: 4300.1 kg (9480 lbs). CF6-80C2A5F appears twice in the same table: in the series row (with B1F, B2F, B4F, B6F, D1F, B1F1, B3F, B7F, B5F, B8F) at 4440.7 kg (9790 lbs), and in its own row at 4472.4 kg (9860 lbs). The two values for CF6-80C2A5F differ within the source; neither is selected here.[3]
  • Note 1: "Dry weight includes basic engine accessories & optional equipment as listed in the manufacturer's engine specifications, including condition monitoring instrumentation sensors.".[3]
  • PW4000-94" series, one set of values printed for the series: overall length 3.90 m (153.6 inches), overall height 2.48 m (97.5 inches); no overall width is printed. Dry weight 4272.84 kg (9420 lbs); "Weight of basic engine includes all essential accessories, but excludes starter, exhaust nozzle and power source for the ignition system." The TCDS does not say whether the values apply to every model of the series including PW4158.[4]
  • The values for CF6-80C2 and PW4000-94" are not compared with each other, and neither is attributed to an aircraft model.[4]

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  1. FAA Joint Aircraft System/Component (JASC) Code Table and Definitions, Information last updated October 27, 2008 (2008-10-27) — p.54 (PDF p.61). https://www.faa.gov/sites/faa.gov/files/JASC_Code.pdf · erişim 2026-11-10
  2. EASA TCDS EASA.A.172 — Airbus A300, A310, A300-600, Issue 08 (2026-02-01) — p.1; p.29 (§10.2); p.62 (§20.2); §15.2 p.46; §16.2 p.48; §17.2 p.50; §1 ETOPS table p.7; §18.2 p.52; §19.2 p.54; §20.15 Notes 3, 5 p.65; §20.2 p.62; §2.2 p.9; §3.2 p.11; §4.2 p.13; §5.2 p.15; §6.2 p.17; §7.2 p.20; §8.2 p.22; §9.2 p.24; §10.2 p.28. https://www.easa.europa.eu/en/downloads/17110/en · erişim 2026-11-10
  3. EASA TCDS EASA.IM.E.240 — GE CF6-80A / CF6-80C series engines, Issue 02 (2024-07-23) — §I.1 p.4; §II.1 p.6; §I.3 p.4; §VI Note 13 pp.23-24; §VI Note 14 p.25; §III.2 p.9; §III.4 p.10; §III.5 p.10; §VI Note 1 p.19. https://www.easa.europa.eu/en/downloads/136365/en · erişim 2026-11-10
  4. EASA TCDS EASA.IM.E.050 — Pratt & Whitney PW4000-94 series engines, Issue 01 (2012-10-19) — §I.1 p.3; §III.2 p.5; §III.3-4 p.6. https://www.easa.europa.eu/sites/default/files/dfu/EASA-TCDS-E.050_(IM)_Pratt_and_Whitney_PW4000--94_series_engines-01-19102012.pdf · erişim 2026-11-10

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