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A300 · ATA 71 · Power Plant

Power Plant

Draft · under review

This draft is for study only; it is not a maintenance document. Sources: EASA TCDS EASA.A.172 Issue 08 (1 Feb 2026; pp.1, 9, 11, 13, 15, 17, 20, 22, 24, 28, 29, 32, 46, 48, 50, 52, 54, 60, 62, 65 rendered and read visually; every engine-to-model pairing and both thrust tables were read on the rendered page, because `pdftotext -layout` shifts rows in this TCDS), EASA TCDS EASA.IM.E.240 Issue 02 (23 Jul 2024, CF6-80 series; pp.10, 11, 20, 23, 24 rendered and read visually, pp.19, 20 text), EASA TCDS EASA.IM.E.050 Issue 01 (19 Oct 2012, PW4000-94" series; p.6 rendered and read visually, p.11 text), Airbus AC A300-600 "Airplane Characteristics for Airport Planning" Revision 13, Dec 2009 (PDF pp.13-15, 101 text; PDF pp.110-112, 125-133 rendered and read visually), FAA JASC code table (grouping and code description only). Page numbers are the PDF page numbers; they equal the "Page n of N" printed in the two EASA TCDS footers and the printed page in IM.E.050. This chapter covers which engines each A300 model has, the take-off and maximum continuous thrust ratings as printed with their time limits, and the engine data the AC prints for airport planning (danger areas, acoustic protection areas, take-off exhaust velocity contours). The engine itself (sections, dimensions, dry weight) is ATA 72 and is not repeated here (see `internal/taslaklar/a300/72/TASLAK.md`); engine controls and FADEC are ATA 73. Model and engine names are given as printed in each source, units as printed, not converted. The sub-section numbering "71-00" is this site's grouping, following FAA JASC code 7100 "Powerplant System"; neither A.172, the two engine TCDS nor the AC print a "71-00" sub-section numbering for these items; A.172 does cite service bulletins numbered SB A300-71-0011, SB A300-71-0031 and SB 71.014 (quoted below); these are service bulletin numbers, not a sub-section numbering of these items. The AC's own numbers (6.1, 6.3 ...) are the AC's chapter numbers and are not ATA numbers. Only the A300-600 engines of A.172 §15-§19 have engine data sheets read here: CF6-80C2 (IM.E.240) and PW4000-94" (IM.E.050); the JT9D-7R4H1 and the CF6-50 / JT9D-59A engines have no engine data sheet read (see Bekliyor).

A300 B-series and A300-600 · EASA aircraft and engine TCDS and Airbus AC

71-00 General (powerplant system, engine options per model)

  • The FAA JASC table describes code 7100 as "for general reports concerning the powerplant package", the 71 series covering items such as engine cowling, engine mount section, engine fire seals, engine air intake system and engine drains. It is a US reporting taxonomy, not a description of the A300.[1]
  • TCDS A.172 is the aircraft type certificate data sheet "AIRBUS A300, A310, A300-600"; its cover page lists the A300 models. Printed as surrendered (struck through) on the cover: A300 B1, B2-1A, B2-1C, B2K-3C, B2-202, B2-203, B2-320, B4-2C, B4-102, B4-103, B4-120, B4-203, B4-220, C4-203, F4-203. Not marked surrendered: A300 B4-620, B4-601, B4-603, B4-622, C4-620, B4-605R, B4-622R, F4-605R, F4-622R, C4-605R variant F (and the A310 models).[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A300 B4-600 series (§15.2): Model A300 B4-620 two PRATT & WHITNEY JT9D-7R4H1 turbofan engines; B4-601 two GENERAL ELECTRIC CF6-80C2A1; B4-603 two GENERAL ELECTRIC CF6-80C2A3; B4-622 two PRATT & WHITNEY PW 4158.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A300 C4-620 (§16.2): two PRATT & WHITNEY JT9D-7R4H1 turbofan engines.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A300 B4-600R series (§17.2), as printed with the two model labels in the left column: "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)." and "Model A 300 B4-622 R: Two PRATT & WHITNEY PW 4158 turbofan engines". On the rendered page the B4-605 R label sits on the first General Electric line and the B4-622 R label on the PW 4158 line.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A300 F4-600R series (§18.2): Model A300 F4-605 R two GENERAL ELECTRIC CF6-80C2A5 turbofan engines (See Note 3) or two GENERAL ELECTRIC CF6-80C2A5F turbofan engines; Model A300 F4-622 R two PRATT&WHITNEY PW 4158 turbofan engines.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A300 C4-600R series (§19.2): Model A300 C4-605 R Variant F two GENERAL ELECTRIC CF6-80C2A5 turbofan engines.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): Note 3 (as printed): on A300 B4-605R and A300 F4-605R models equipped with GENERAL ELECTRIC CF6-80C2A5 engines, the engine CF6-80C2A3 may be used, with the corresponding revision of the Flight Manual, supplement 11. Note 5 (as printed): on A300 B4-605 R and A300 F4-605 R models, installation of GENERAL ELECTRIC FADEC-equipped CF6-80C2A5F is achieved by modification 8966.[2]
  • A300-600 models: engines as printed (A.172 §15.2-§19.2): A.172 §20.2 states for the A300-600 models: "The engines indicated below can be installed on the different models in the basic version (See definition of each model) or as replacements. For the operating conditions of the aircraft in this case, see the Flight Manual (See Note 3)." The thrust table that follows is headed by engine (see 71-00 thrust ratings), not by aircraft model.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: Every page below carries the "SURRENDERED" stamp and struck-through text in A.172 Issue 08; the entries are listed only as history.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B1 (§2.2): "Two GENERAL ELECTRIC CF6-50A turbofan engines, or CF6-50C turbofan engines after embodiment of SB 71.014.".[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B2-100 series (§3.2), "2 GENERAL ELECTRIC turbofan engines": Model A300 B2-1A CF6 - 50A; Model A300 B2-1C CF6 - 50C or CF6 - 50C2R (See Note 3).[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B2-200 series (§4.2), "2 GENERAL ELECTRIC turbofan engines": Model A300 B2K-3C CF6 - 50C or CF6 - 50C2R (see Note 3); B2-202 CF6 - 50C1; B2-203 CF6 - 50C2 or CF6 - 50C2D (see Note 3).[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B2-320 (§5.2): two PRATT & WHITNEY JT9D-59A turbofan engines.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B4-100 series (§6.2): Model A300 B4-2C 2 GENERAL ELECTRIC CF6 - 50C or CF6 - 50C2R (see Note 3); B4-102 2 GENERAL ELECTRIC CF6 - 50C1; B4-103 2 GENERAL ELECTRIC CF6 - 50C2 or CF6 - 50C2D (see Note 3); B4-120 2 PRATT & WHITNEY JT9D-59A.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 B4-200 series (§7.2): Model A300 B4-203 2 General Electric CF6 50C2 or CF6 - 50C2D (see Note 3); B4-220 2 Pratt & Whitney JT9D-59A.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: A300 C4-203 (§8.2) and A300 F4-203 (§9.2): each "2 GENERAL ELECTRIC CF6 - 50C2 turbofan engines.".[2][2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: §10.15 Note 3 (section 10, all earlier models): after modification 2818 (SB A300-71-0031) and with the corresponding revision of the Flight Manual, the GENERAL ELECTRIC CF6-50C2R engine can be used on A300 B4-2C aircraft models; after modification 7794 (SB A300-72-0004) the CF6-50C2D can be used on A300 B4-103 and A300 B4-203 models.[2]
  • Earlier A300 models (all marked SURRENDERED in A.172): engines as printed: §10.2 introduction (as printed): the engines indicated can be installed on the different models of A300 type aeroplanes as per definition of each model, or as a replacement according to SB A300-71-0011 (General Electric engines); for the operating conditions in that case, see the Flight Manual.[2]

71-00 Take-off thrust and maximum continuous thrust, as printed

  • Time limits and conditions are in the next section. Take-off values are for 5 minutes as printed in the row or column label of each table; the 10-minute case is not a separate row in any of these tables; the footnotes and notes that give it are in the next section.[2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: Table heading: "Static thrust at sea level (daN)*", rows "Take-off (5 mn)** (lbs)" and "Max continuous (lbs)"; each cell prints the value in daN followed by the value in lbs in brackets. On the rendered page the row labels are not on the same lines as the values, so the assignment of the upper and lower value in a column to take-off and maximum continuous is by order; the printed pounds figures agree with those of the engine TCDS below for CF6-80C2A1, CF6-80C2A5 / A5F and PW 4158, for CF6-80C2A3 only the upper value (58 950) does (see the comparison below), and no engine TCDS was read for the column printed "JT9D-7RH1", so its assignment rests on order alone.[2][3][4]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: GENERAL ELECTRIC (DATA SHEET E13NE, FICHE DGAC M.IM 13) CF6-80C2A1: take-off 25 740 (57 860), maximum continuous 23 750 (53 390). CF6-80C2A3: take-off 26 220 (58 950), maximum continuous 23 920 (53 780). CF6-80C2A5 / CF6-80C2A5F (one shared column): take-off 26 734 (60 100), maximum continuous 25 003 (56 210).[2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: PRATT & WHITNEY (DATA SHEET E3N3, FICHE DGAC M.IM 6) engine printed "JT9D-7RH1": take-off 24 920 (56 000), maximum continuous 22 250 (50 000).[2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: PRATT & WHITNEY (DATA SHEET E24NE, FICHE DGAC M.IM 18) PW 4158: take-off 25 800 (58 000), maximum continuous 22 054 (49 580).[2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: The same table prints the Pratt & Whitney JT9D engine as "JT9D-7RH1", while §15.2 and §16.2 print "JT9D-7R4H1"; the spellings differ in the source and are not reconciled here.[2][2][2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: Footnote * (as printed): "Standard conditions (ISA : 15° C - 1013,2 mbar) and up to temperatures indicated in DGAC "Fiche de Caractéristiques Moteur" which also precises the thrust measurement conditions.".[2]
  • A.172 §20.2 table (A300-600 models), static thrust at sea level, as printed: The table also prints "Approved oils" entries (a specification reference); oil belongs to ATA 79 and is not used here.[2]
  • Engine TCDS ratings (kN and lbf, or daN and lbs, as printed): IM.E.240 §6 "Ratings", heading "Thrust kN (lbf)", columns "Take-off (5 minutes)" and "Maximum Continuous". Rows read on the rendered pages: C2A1 take-off 257.374 (57860), maximum continuous 237.490 (53390); C2A3 take-off 262.223 (58950), maximum continuous 243.718 (54790); C2A5 take-off 267.338 (60100), maximum continuous 250.034 (56210); C2A5F take-off 267.338 (60100), maximum continuous 250.034 (56210). Row labels are printed as "C2A1", "C2A3" etc. in the table, under the document's "CF6-80 series" heading.[3]
  • Engine TCDS ratings (kN and lbf, or daN and lbs, as printed): IM.E.050 §5 "Ratings (Static Thrust at Sea Level, see Notes 1 and 2)": PW4158 take-off (5 minutes) 25800 daN (58000 lbs)**, maximum continuous 22054 daN (49580 lbs)**; the footnote "**" reads "Flat-rated to 30°C". The table is for the PW4000-94" series; its other rows are other models.[4]
  • Engine TCDS ratings (kN and lbf, or daN and lbs, as printed): Comparison A.172 vs engine TCDS: the lbs/lbf values agree for CF6-80C2A1 (57 860 / 53 390), CF6-80C2A3 take-off (58 950), CF6-80C2A5 and A5F (60 100 / 56 210) and PW 4158 (58 000 / 49 580). They differ for the CF6-80C2A3 maximum continuous: A.172 prints 23 920 daN (53 780 lbs), IM.E.240 prints 243.718 kN (54790 lbf). The comparison is of the printed pounds figures only (A.172 labels them "lbs", IM.E.240 "lbf"); the daN and kN figures are not compared here. Both values are reported; the difference is not explained in either source.[2][3]
  • Engine TCDS ratings (kN and lbf, or daN and lbs, as printed): Within IM.E.240 two different "takeoff" numbers are printed per engine: the §6 ratings above (CF6-80C2A1 57860 lbf) and, in Note 13, "takeoff ideal thrust rating" values: CF6-80C2A1 "59,000 pounds", CF6-80C2A3 "60,200 ideal", CF6-80C2A5 "61,300 ideal", CF6-80C2A5F "61,300 ideal". The TCDS does not say why the numbers differ; they are reported as printed.[3][3]
  • Surrendered A300 models: A.172 §10.2 table, as printed: Heading "THRUST", engines GENERAL ELECTRIC (DATA SHEET E23EA - FICHE DGAC M.IM7) in columns "CF6-50C / CF6-50C2R", "CF6-50C1", "CF6-50C2 / CF6-50C2D", and PRATT & WITHNEY (DATA SHEET E3NE - FICHE DGAC M.IM6) "JT9D-59A"; a further header cell before the first General Electric column is blank and its value cells are blank. Rows: "Static Thrust at sea level (daN)*", "Take-off (5 mn up to 30° C 30.5° C for the 50A)**", "Max continuous (up to 30° C)". The page is stamped SURRENDERED.[2][2]
  • Surrendered A300 models: A.172 §10.2 table, as printed: Take-off values as printed: 22 400 (CF6-50C / CF6-50C2R), 23 050 (CF6-50C1), 23 050 (CF6-50C2 / CF6-50C2D), 23 015 (JT9D-59A). Maximum continuous: 20 600, 20 600, 20 600 and 19 920 (JT9D-59A), in the same column order.[2]
  • Surrendered A300 models: A.172 §10.2 table, as printed: The Pratt & Whitney column heading prints "WITHNEY" (a misprint of the company name), kept as printed.[2]

71-00 Rating conditions and time limits, as printed

  • A.172 §20.2 footnote **: "10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) in accordance with DGAC "Fiche de Caractéristiques Moteur"." The take-off row of the same table is labelled "Take-off (5 mn)".[2]
  • A.172 §10.2 footnote **, for the surrendered models: "10 minutes at take-off thrust allowed only in case of engine failure (at take-off or during go-around) (see letter SGAC N° 1623 DTA/SDT/M of March 7, 1974 for GENERAL ELECTRIC engines, DGAC letter referenced 54 326 SFACT/TC of December 21, 1979 for PRATT & WHITNEY engines)." The surrendered-model table labels take-off "5 mn up to 30° C 30.5° C for the 50A" (two lines in the cell).[2]
  • IM.E.240 Note 3 (CF6-80 series): "Take off rating is limited to a continuous period of not more than 5 minutes except in the event of a power unit having failed or been shut down when a continuous period of not more than 10 minutes is allowed.".[3]
  • IM.E.050 Note 2 (PW4000-94" series): "The normal 5 minute takeoff limit may be extended to 10 minutes for engine out contingency." The wording differs from the two sources above; it is reported as printed.[4]
  • IM.E.240 Note 4, flat rating ambient temperature, read on the rendered table (columns "Take-off" and "Maximum Continuous"): C2A1 30°C (86°F) and 25°C (77°F); C2A3 30°C (86°F) and 25°C (77°F); C2A5 30°C (86°F) and 25°C (77°F); C2A5F 30°C (86°F) and 25°C (77°F). On the rendered page the row C2A2 prints 44°C (111°F) for take-off; the text-extracted version places 33.3°C on the C2A2 line and 44°C on the C2B1 line, so it shifts rows and was not used.[3]
  • IM.E.050: the PW4158 take-off and maximum continuous values carry the footnote "**: Flat-rated to 30°C".[4]
  • IM.E.240 Note 2, conditions on which the engine ratings are based (as printed): fan inlet air at 15°C (59°F) and 14.69 psia (29.92 in. hg.) abs, zero humidity; ideal engine inlet (100% bellmouth recovery); no external air bleed or accessory drive power for aircraft accessories; turbine temperature and engine rotor speed limits not exceeded; with a flight exhaust system definition listed per model.[3]
  • IM.E.050 Note 1: "The Sea Level Static Ratings are ideal and based on ICAO Standard Atmosphere conditions, a Pratt & Whitney hardwall bellmouth inlet, no fan or compressor air bleed or load on accessory drives, an exhaust system having no internal pressure or external scrubbing losses, and fan duct and primary nozzle velocity coefficients equal to 1.0.".[4]

71-00 Powerplant installation items in the A.172 certification basis

  • A.172 §20.1 item g (as printed): "For A300 B4-622, A300 B4-622 R and A300 F4-622 R models equipped with PW engines, a special condition relative to the Full Authority Digital Engine Control (DGAC letter 53517 SFACT/TC) CRI S15 – A/C Powered by P4000 engines – FADEC.".[2]
  • Item h: "For A300 B4-605 R and A300 F4-605 R models equipped with General Electric CF6-80C2A5F engines, a special condition relative to the Full Authority Digital Engine Control (DGAC letter 940849-SFACT/N.AT) CRI P1 - FADEC.".[2]
  • Item k: "For aircraft equipped with PW engines, the embodiment of modification related to Third Line of Defence installation (mod .12261 for PW JTP or mod. 12262 for PW4000) amend the French German certification basis as follows: - Equivalent Safety Finding P-4 related to thrust reverser in-flight deployment is applicable." The TCDS does not say here what the "Third Line of Defence" installation consists of.[2]

71-00 Airport planning engine data (Airbus AC A300-600, chapter 6.0)

  • The AC states its purpose as providing "the necessary data needed by airport operators and airlines for the planning of airport facilities" for "the A300--600 basic versions" (as printed). Chapter 6 is described as containing "data and safety/environmental precautions related to engine and APU operation on the ground", covering "contour size and shape of the jet engine exhaust velocities and temperature" and "noise data". The revision on the cover transmittal pages is Revision 13, DEC 01/09; individual drawing pages carry earlier footers, noted below.[5][5]
  • Chapter 6.0 contents (PDF p.101, DEC 01/09): 6.1 Jet Engine Exhaust Velocities And Temperatures (6.1.1 and 6.1.2 breakaway power, 6.1.3 and 6.1.4 take-off power, 6.1.5 and 6.1.6 idle power, each velocity then temperature), 6.2 Airport and Community Noise, 6.3 Danger Areas of the Engines (6.3.1 ground idle, 6.3.2 take-off, 6.3.3 acoustic protection areas, 6.3.4 APU exhaust gas temperature and velocity). The page defines: "Breakaway Power means the minimum power necessary for the aircraft to be able to start moving.".[5]
  • Each drawing is given for one engine type, named in its caption: "PW JT9D-7R4H1 ENGINE", "GE CF6-80C2 ENGINE", "PW 4000 ENGINE" or, on the two DEC 01/09 pages (6.3.1 page 3 and 6.3.3 page 3), "PW4000 Engine" (spellings as printed in the captions). All captions add "MODEL A300-600" except those two DEC 01/09 pages, which carry "A300-600" only in the page header. The captions do not name an individual A300-600 model.[5][5][5][5]
  • Danger areas, ground idle (AC 6.3.1): PW JT9D-7R4H1 engine (Chapter 6.3.1 page 1, Oct 01/87): legend entries "INLET SUNCTION DANGER AREA GROUND IDLE" (spelling as printed), "ENTRY CORRIDOR", "EXHAUST WAKE DANGER". Printed on the drawing: "20 ft / 6.1 m" on a leader line to the stippled inlet area, "5 ft. / 1.5 m" on a dimension at the left engine, "TO 55 m/180 ft. AFT FAN NOZZLE" along the edge of the exhaust wake area, and "30°" across the rear of that area. The page does not say in words what the 20 ft and 5 ft dimensions measure.[5]
  • Danger areas, ground idle (AC 6.3.1): GE CF6-80C2 engine (page 2, Oct 01/87): legend entries "INTAKE SUCTION DANGER AREA GROUND IDLE", "ENTRY CORRIDOR", "SET WAKE AREA" (as printed; the take-off page below prints "JET WAKE AREA"). Printed: "25 ft / 7,6 m" on a leader line to the stippled intake area, "5 Ft" over "1 5 m" at the left engine (no decimal point is visible in the scan), "TO 54,8 m/180 ft AFT FAN NOZZLE" and "30°". The page does not say in words what the 25 ft and 5 ft dimensions measure.[5]
  • Danger areas, ground idle (AC 6.3.1): PW 4000 engine (page 3, DEC 01/09): legend entries "REVERSE THRUST DANGER AREA" and "EXHAUST DANGER AREA", with the label "AT IDLE". Printed: "72 ft / 22 m" on a leader line to each of the two stippled areas, "TO 162 ft AT 34 mph" and "TO 50 m AT 54.4 Kph" beside the exhaust area, and "30°". The metric and US values are as printed; the page does not say in words what the 72 ft dimension measures.[5]
  • Danger areas, take-off (AC 6.3.2): PW JT9D-7R4H1 engine (Chapter 6.3.2 page 1, Oct 01/87): legend "INLET SUCTION DANGER AREA TAKE OFF THRUST" and "EXHAUST WAKE DANGER". Printed: "50 ft. / 15.2 m" on a leader line to the stippled inlet area, "6 ft. / 1.8 m" at the left engine, "TO 275 m/900 ft. AFT FAN COWL" along the exhaust wake area, "40°" across its rear.[5]
  • Danger areas, take-off (AC 6.3.2): GE CF6-80C2 engine (page 2, Oct 01/87): legend "INTAKE SUCTION DANGER AREA TAKEOFF THRUST" and "JET WAKE AREA". Printed: "54.13 ft. / 16.50 m" on a leader line to the stippled intake area, "5 ft. / 1.5 m" at the left engine, "TO 275 m/900 ft AFT FAN COWL", "40°".[5]
  • Danger areas, take-off (AC 6.3.2): PW 4000 engine (page 3, Aug 31/88): the only legend entry is "INLET SUCTION DANGER AREA TAKE-OFF THRUST"; no exhaust area is drawn on this page. Printed: "50 Ft / 15.2 m" on a leader line to the stippled area and "6 Ft / 1.8 m" at the left engine.[5]
  • Acoustic protection areas (AC 6.3.3): PW JT9D-7R4H1 engine (Chapter 6.3.3 page 1, Oct 01/87): table "POWER SETTING / RADIUS X / RADIUS Y" as printed: GROUND IDLE 75 Ft (23 m) and 100 Ft (30 m); BREAK AWAY 90 Ft (27 m) and 115 Ft (35 m); TAKE-OFF 125 Ft (38 m) and 200 Ft (60 m). The drawing marks two concentric areas with lines labelled X and Y; printed warnings: "EAR PROTECTION REQUIRED WITHIN THIS AERA" (spelling as printed) and "PROLONGED EXPOSURE OF ONE HOUR EVEN WITH EAR PROTECTION CAN CAUSE EAR DAMAGE".[5]
  • Acoustic protection areas (AC 6.3.3): GE CF6-80C2 engine (page 2, Jun 01/98): table as printed: GROUND IDLE 23m (75ft) and 30m (100ft); BREAK AWAY 30m (100ft) and 46m (150ft); TAKE-OFF 30m (100ft) and 61m (200ft). Printed note: "BASED ON UNINSTALLED ENGINE". Two warnings are printed: "EAR PROTECTION REQUIRED WITHIN THIS AREA" (spelled "AREA" on this page) and the exposure warning, with "PROLONGER" (as printed).[5]
  • Acoustic protection areas (AC 6.3.3): PW 4000 engine (page 3, DEC 01/09): table as printed: GROUND IDLE 75 ft (23 m) and 100 ft (30 m); BREAK AWAY 90 ft (27 m) and 115 ft (35 m); TAKE-OFF 125 ft (38 m) and 200 ft (60 m), the same figures as on the JT9D-7R4H1 page. Two warnings are printed: "EAR PROTECTION REQUIRED WITHIN THIS AREA." and "PROLONGED EXPOSURE OF ONE HOUR EVEN WITH EAR PROTECTION CAN CAUSE EAR DAMAGE.".[5][5]
  • Acoustic protection areas (AC 6.3.3): Against the JT9D-7R4H1 and PW 4000 pages for the same power setting, the GE page prints a different X at break away (30m (100ft) against 90 ft (27 m)) and at take-off (30m (100ft) against 125 ft (38 m)), and a different Y at break away (46m (150ft) against 115 ft (35 m)). At take-off Y is 200 ft on all three pages, but the metric figure is 61m on the GE page and 60 m on the other two. These are different engine types and the AC does not compare them.[5][5][5]
  • Exhaust velocity contours, take-off power (AC 6.1.3): PW JT9D-7R4H1 engine (Chapter 6.1.3 page 1, Oct 01/87): elevation and plan views with a distance scale in FEET (-100 to 200) and METERS (-30 to 61). Contour labels 341, 205, 136 and 68. Printed note: "ALL VELOCITY VALUES ARE IN STATUTE MILES PER HOUR TAKE OF POWER - SEA LEVEL STATIC ZERO WIND STANDARD DAY - ZERO RAMP GRADIENT ENGINE TYPE." ("TAKE OF" as printed) and "45.520 POUNDS OF THRUST" with "CONVERSION FACTOR 1 MPH = 1.6Km/h". A.172 §20.2 prints take-off thrust 24 920 daN (56 000 lbs) for the engine it names "JT9D-7RH1" (the AC caption names "JT9D-7R4H1"; see the spelling note above); the AC page does not say how its "45.520 POUNDS OF THRUST" relates to that rating, and the two numbers differ as printed.[5][2]
  • Exhaust velocity contours, take-off power (AC 6.1.3): GE CF6-80C2 engine (page 2, Oct 01/87): one chart, "VELOCITY ~ KNOTS (km/hr)", contour labels 400 (741), 300 (556), 200 (372), 100 (185), 50 (93) and 35 (65); horizontal axis "DISTANCE AFT OF FAN NOZZLE EXIT ~ FEET (m)" from 0 to 400 (121.9), vertical axis "VERTICAL DISTANCE FROM CENTERLINE ~ FEET (m)" up to 40 (12.2) each side, with "PROJECTED ENGINE CL" and "GROUND PLANE" marked. This page is in knots, the other two take-off pages in miles per hour.[5]
  • Exhaust velocity contours, take-off power (AC 6.1.3): PW 4000 engine (page 3, Aug 31/88): elevation and plan views, contour labels 682MPH, 477MPH, 341MPH, 204MPH, 102MPH, 68MPH and 34MPH "TO720FT" ("TO 720 FT (216m)" on the plan view), scale FEET -100 to 200 and METERS -30 to 61. Printed note: "ALL VELOCITY VALUES ARE IN STATUTE MILES PER HOUR. TAKEOFF POWER – SAE LEVEL STATIC, ZERO WIND STANDARD DAY, ZERO RAMP GRADIENT ENGINE TYPE." ("SAE" as printed) and "CONVERSION FACTOR 1 MPH = 1.6 km/h".[5]

Kaynaklar

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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.53 (PDF p.60). 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; §15.2 p.46; §16.2 p.48; §17.2 p.50; §18.2 p.52; §19.2 p.54; §20.15 Notes 3, 5 p.65; §20.2 p.62; pp.9-24, 28-29; §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; §10.15 Note 3 p.32; §10.2 p.28; p.29; §10.2 p.29; §20.1 item g p.60; §20.1 item h p.60; §20.1 item k p.60. 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) — §6 pp.10-11; §6 p.11; §VI Note 13 pp.23-24; §VI Note 3 p.20; §VI Note 4 p.20; §VI Note 2 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) — §5 p.6; §VI Note 2 p.11; §VI Note 1 p.11. 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
  5. Airbus AC A300-600 — Aircraft Characteristics, Airport and Maintenance Planning, Revision 13 (2009-12-01) — §1.1 p.1 (PDF p.13); §1.2 p.2 (PDF p.15); §6.0 p.1 (PDF p.101); §6.1.3 pp.1-3 (PDF pp.110-112); §6.3.1 pp.1-3 (PDF pp.125-127); §6.3.2 pp.1-3 (PDF pp.128-130); §6.3.3 pp.1-3 (PDF pp.131-133); §6.3.1 p.1 (PDF p.125); §6.3.1 p.2 (PDF p.126); §6.3.1 p.3 (PDF p.127); §6.3.2 p.1 (PDF p.128); §6.3.2 p.2 (PDF p.129); §6.3.2 p.3 (PDF p.130); §6.3.3 p.1 (PDF p.131); §6.3.3 p.2 (PDF p.132); §6.3.3 p.3 (PDF p.133); p.1 (PDF p.131); p.3 (PDF p.133); §6.1.3 p.1 (PDF p.110); §6.1.3 p.2 (PDF p.111); §6.1.3 p.3 (PDF p.112). https://www.aircraft.airbus.com/sites/default/files/2023-02/Airbus-Commercial-Aircraft-AC-A300-600-Dec-2009.pdf · erişim 2026-11-10

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