Fuel

Draft · under review

Sources: EASA TCDS EASA.A.172 Issue 08 (1 Feb 2026; PDF pages rendered and read visually for every fuel table), Airbus AC "A300-600 Airplane Characteristics for Airport Planning" Rev 13 (DEC 01/09; chapter 2.1 pages 2 and 2A and chapter 5.4.6 page 7 rendered and read visually), FAA AD 2020-01-15 (85 FR 7655, Federal Register HTML downloaded and read in full), FAA JASC code table (for grouping only). This draft is for study only; it is not a maintenance document. The AD item below is what the AD addresses, not an inspection or maintenance instruction; no interval or compliance time is given. Servicing connection data are airport-planning data, not refuelling instructions. Model names are quoted as printed in each source. The TCDS prints fuel tables per certified model group; no number is carried from one group to another. The sub-section numbers 28-00, 28-10 and 28-40 are this site's grouping, following FAA JASC codes 2800, 2810 and 2840; the TCDS and AC do not use 28-xx numbering for these items, and the AD gives only code 28.

A300 B-series and A300-600 · EASA TCDS, Airbus AC and FAA Airworthiness Directive

28-00 General

EASA TCDS Section 10 (A300 all series, all models except A300 B4-600, C4-600, B4-600R, F4-600R and C4-600R) lists the fuels that may be used as JET A, JET A1, JET B, JP4, JP5, JP8 and N°3-JET, and says they are also suitable for the APU; approved fuel specifications are by reference to the Consumable Material List (CML), which is not available here.^[1]
EASA TCDS Section 20 (A300B4-600, A300C4-600, A300B4-600R, A300F4-600R and A300C4-600R series) lists the fuels as JET A, JET A1, JET B, JP4, JP5, JP8, N°3-JET, TS-1 and RT, also suitable for the APU, with the same CML reference.^[1]
For the A300-600 group, the TCDS lists "Fuel Airworthiness Limitations (ALS Part 5)" among the Airworthiness Limitations Sections; they are "provided in the EASA-approved Airworthiness Limitation Section (ALS) Part 5". The TCDS gives no content of ALS Part 5.^[1]
The TCDS fuel tank names differ by section. Sections 15 and 16 (A300 B4-620, B4-601, B4-603, B4-622 and A300 C4-620): Outer, Inner, Center. Sections 17, 18 and 19 (A300 B4-605R, B4-622R, F4-605R, F4-622R and C4-605R Variant F): Outer, Inner, Center and Trim. Section 6 (B4-100 models): Outer, Inner, Center. Section 2 (B1): Outer, Inner.^{[1][1][1][1][1][1][1]}
The FAA JASC table describes code 2800 as "the units and components storing and delivering fuel to the engine", including integral tank leak detection and sealing.^[2]

28-10 Fuel storage - tank capacities (TCDS EASA.A.172 Issue 08)

The TCDS prints a volumic mass for each table. Volumes in litres are as printed; no conversion is done here. A300 B1 and B4-100 tables are printed on pages marked "SURRENDERED" in the TCDS; the A300-600 tables are not marked.^[1]
A300-600 group (volumic mass 0.8 kg/litre as printed): A300 B4-620, B4-601, B4-603, B4-622 (Section 15): unusable fuel Outer 12 kg (15 l), Inner 130 kg (163 l), Center 48 kg (60 l), TOTAL 190 kg (238 l); usable fuel Outer 7 408 kg (9 260 l), Inner 28 112 kg (35 140 l), Center 14 080 kg (17 600 l), TOTAL 49 600 kg (62 000 l). The TCDS adds that for aircraft fitted with Additional Centre Tank, see Note 1.^[1][1]
A300-600 group (volumic mass 0.8 kg/litre as printed): A300 C4-620 (Section 16): the same table values as the group above (TOTAL usable 49 600 kg, 62 000 l; TOTAL unusable 190 kg, 238 l), with the same Additional Centre Tank reference.^[1][1]
A300-600 group (volumic mass 0.8 kg/litre as printed): A300 B4-605R, B4-622R (Section 17): unusable fuel Outer 12 kg (15 l), Inner 130 kg (163 l), Center 48 kg (60 l), Trim 32 kg (40 l), TOTAL 222 kg (278 l); usable fuel Outer 7 408 kg (9 260 l), Inner 28 112 kg (35 140 l), Center 14 080 kg (17 600 l), Trim 4 920 kg (6 150 l), TOTAL 54 520 kg (68 150 l).^[1][1]
A300-600 group (volumic mass 0.8 kg/litre as printed): A300 F4-605R, F4-622R (Section 18): the same table values as the B4-605R/B4-622R group, with Center and Trim marked "(*) See Note 6". Note 6 reads: "For A300 F4-605 R weight variant 06 & 09 and A300 F4-622R weight variant 09, following limitations apply:" followed by two listed items, "centre and trim fuel tanks deactivated" and "maximum authorized altitude 35.000 ft.".^[1][1][1]
A300-600 group (volumic mass 0.8 kg/litre as printed): A300 C4-605R Variant F (Section 19): the same table values as the B4-605R/B4-622R group (TOTAL usable 54 520 kg, 68 150 l; TOTAL unusable 222 kg, 278 l).^[1][1]
A300-600 group (volumic mass 0.8 kg/litre as printed): Additional centre tanks (ACT): the TCDS Note 1 says modifications 5498, 5499, 5470 and 5471 install additional centre tanks in the aft cargo compartment. Two tanks are listed, ACT 1 and ACT 2, each with unusable fuel 93 kg (117 l) and usable fuel 5 600 kg (7 000 l). The TCDS refers to the corresponding revision of the EASA-approved Aeroplane Flight Manual for limitations and procedures.^[1]
A300 B-series groups printed here (volumic mass as printed): A300 B4-2C, B4-102, B4-103, B4-120 (Section 6; volumic mass printed as 0,782 kg/litre): unusable fuel Outer 12 kg, Inner 130 kg, Center 48 kg, TOTAL 190 kg. Usable fuel is given with "Normal preselected refuelling" and "Refuelling with high level shut off" columns, without and with SB n° 28.0021 (modification 1664): without it, normal preselected Outer 7 000 / Inner 27 000 / Center 11 000 / TOTAL 45 000 kg and high level shut off TOTAL 45 434 kg (58 100 l); with it, normal preselected Outer 7 000 / Inner 27 000 / Center 13 500 / TOTAL 47 500 kg and high level shut off TOTAL 48 484 kg (62 000 l). The table footnote reads "(1) See Note 6".^[1][1]
A300 B-series groups printed here (volumic mass as printed): A300 B1 (Section 2; volumic mass 0.782 kg/litre): unusable fuel Outer 12 kg, Inner 40 kg, TOTAL 52 kg; usable fuel normal preselected refuelling Outer 7 000, Inner 27 000, TOTAL 34 000 kg; refuelling with high level shut off TOTAL 34 408 kg (44 000 l).^[1][1]
A300 B-series groups printed here (volumic mass as printed): For the A300 B4-100 series, the TCDS describes the essential difference from the A300 B2-100 series as including "the addition of a fuel tank in the wing centre box".^[1]

28-10 Fuel storage - airport-planning data (Airbus AC A300-600)

The AC chapters quoted here are headed A300-600 and cover the versions printed in its tables. The AC uses d = 0.785 for kilograms, the TCDS uses 0.8 for the same A300-600 groups, so the printed kilogram values differ; litres are compared below.^[3]
AC chapter 2.1 page 2 gives usable fuel capacity for A300B4-600 WV000 (Basic) and WV008 as 62 000 - 76 400 l (16 380 - 20 184 US gal; 48 670 - 59 974 kg at d = 0.785), with note (2) "ACT only for WV000 with PW JT9D engine". For A300C4-600 PAX WV000 and A300C4-600 FREIGHT WV000 it gives 62 000 l (16 380 US gal; 48 670 kg).^[3]
AC chapter 2.1 page 2A gives usable fuel capacity for A300B4-600R WV000 (Basic), WV001, WV002 and WV003 as 68 160 l (18 008 US gal; 53 505 kg at d = 0.785).^[3]
Litres compared: the AC figure of 62 000 l (A300C4-600, and the lower figure for A300B4-600) is the same number as the TCDS litre total for the A300 B4-620/601/603/622 group (62 000 l). The AC figure of 68 160 l for A300B4-600R WV000 to WV003 is 10 l more than the TCDS litre total for the A300 B4-605R/B4-622R group (68 150 l); neither document explains the difference, and both are given here as printed.^[1][1][3]
The AC glossary defines "Usable Fuel" as "Fuel available for aircraft propulsion".^[3]

28-10 Fuel storage - ground fuel connections (Airbus AC A300-600, chapter 5.4.6)

Chapter 5.4.6 "Fuel System", model A300-600, page 7 (footer Oct 30/94), lists the following connections with distance aft of nose, distance from airplane centreline and mean height from ground, as printed (metres, with feet-inches in brackets):^[3]
Two standard 2 1/2 in. connections, ISO R45 Specification: 24.31 m (79-9) aft of nose, 11.84 m (38-10) right-hand side, left-hand side cell blank, mean height 4.26 m (13-11).^[3]
Two service connections (gravity feed): 24.95 m (81-10) aft of nose, 12.35 m (40-6) on each of the RH and LH sides, mean height 4.72 m (15-5).^[3]
Two further service connections (gravity feed): 31.02 m (101-9) aft of nose, 20.39 m (66-11) on each of the RH and LH sides, mean height 5.27 m (17-3).^[3]
The same page gives a flow rate of 1475 litres/min (325 Imp. gal/min; 390 US gal/min) per connection and a maximum pressure of 50 psig (3.45 bars). The page does not say to which of the connection rows the flow rate and pressure refer, beyond "per connection"; see Bekliyor.^[3]
The AC servicing symbol list defines "F" as "REFUELING VEHICLE" for the A300-600 and A300C4-600 servicing diagrams.^[3]
The FAA JASC table lists typical parts of code 2810 Fuel Storage as including filler cap, filler neck, vent line, vent valve, drain valve, filler adapter, fueling panel and tank interconnect lines. This is a US reporting taxonomy, not a description of the A300.^[2]

28-40 Fuel indicating - FQIS centre tank (FAA AD 2020-01-15)

FAA AD 2020-01-15 (85 FR 7655, Federal Register 11 Feb 2020, effective 17 March 2020) gives its subject as "Air Transport Association (ATA) of America Code 28, Fuel".^[4]
Applicability as printed: (1) Model A300 B4-601, B4-603, B4-620 and B4-622; (2) A300 B4-605R and B4-622R; (3) A300 F4-605R and F4-622R; (4) A300 C4-605R Variant F; (5) A310-304, -322, -324 and -325. Among A300 models the AD lists only these; no A300 B2/B4 (non-600) model is listed, and A300 C4-620 (TCDS Section 16) is not listed either.^[4][1]
The Summary groups Model A300 B4-600, B4-600R, and F4-600R series airplanes and Model A300 C4-605R Variant F airplanes as "collectively called Model A300-600 series airplanes".^[4]
The AD addresses ignition sources inside the center fuel tank, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.^[4][4]
The AD says it was prompted by the FAA's analysis of the fuel system reviews on these models conducted by the manufacturer.^[4][4]
Paragraph (g) of the AD concerns a modification of the FQIS to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions.^[4]
For airplanes used exclusively for cargo operations, the AD provides alternative actions that concern (a) the fault codes stored in the fuel quantity indicating (FQI) computer and a BITE check (check of built-in test equipment) of that computer, and (b) separation of FQIS wiring that runs between the FQI computer and the center fuel tank wall penetrations, including any circuits that might pass through a main fuel tank, from other airplane wiring that is not intrinsically safe. This describes what the AD addresses, not a procedure.^[4]
Parts and locations named in the AD: FQIS, FQI computer, center fuel tank, center fuel tank wall penetrations, main fuel tank (as a route for circuits), and wiring that is not intrinsically safe.^[4]
In its comment responses the AD states that the FAA considers the center wing fuel tanks of Model A300-600 and Model A310 airplanes as high-flammability exposure time fuel tanks, and that therefore the criteria for an unsafe condition are met as described in FAA Policy Memorandum ANM100-2003-112-15.^[4]
The AD records that Airbus and EASA noted differences between EASA's risk assessment policy and that of the FAA, and that EASA, based on its own criteria, concluded there is no unsafe condition. The FAA writes that it "infers that the commenters would like the NPRM withdrawn" and disagrees with this proposal. Under a separate comment heading, Airbus, with A4A/CAA and UPS, requested that the FAA withdraw the NPRM.^[4]
The AD names no Airbus service bulletin: it says Airbus was developing inspection and modification service bulletins that were not yet approved or available, and that the FAA could consider them later as an alternative method of compliance. The AD's material incorporated by reference is "None".^[4][4]

Not yet covered

System description of the A300 B2/B4 and A300-600 fuel systems (tank layout, pumps, valves, crossfeed, transfer, jettison/dump, vent system, fuel feed to engines and APU, refuel/defuel panel, trim tank transfer): no Level 1 source found; the TCDS gives capacities, fuel types and the notes quoted above, without describing these systems, and the AC gives airport-planning data. FQIS description (probes, FQI computer, BITE, indicators) beyond the AD wording: no Level 1 description found. TCDS fuel tables of the A300 B2 and later B-series groups (Sections 3, 4, 5, 7, 8, 9: B2-1A/1C, B2K-3C/B2-202/B2-203, B2-320, B4-203/B4-220, C4-203, F4-203; PDF pp.12, 14, 16, 21, 23, 25): not read in this draft; page images exist but were not checked. TCDS Section 6 table footnote "(1) See Note 6" for the B4-100 group: section 6.7 refers to the "A300 All series, all models" chapter, whose Note 6 (p.33) concerns aircraft identified by the letters FF and does not mention SB n° 28.0021 or modification 1664. Note 5 of that chapter (p.33) names modification 1664 among those separately defining aircraft embodying modification 2599. The TCDS does not say what SB n° 28.0021 (modification 1664) changes; the footnote is quoted only. TCDS Note 1 (additional centre tanks, mods 5498/5499/5470/5471) does not say which models can carry them or how many tanks a given aircraft has; only ACT 1 and ACT 2 values are printed. AC chapter 2.1 page 2B (A300B4-600R WV004 to WV010) was not read visually; only WV000 to WV003 (page 2A) are quoted. AC chapter 5.4: page numbers run through the whole chapter, and page 7 (PDF p.83) is the only page of section 5.4.6 (page 6 is 5.4.5, page 8 is 5.4.7). Page 1 (5.4.1, PDF p.77) lists symbols "FUEL GRAVITY FILLING" (H) and "FUEL PRESSURE FILLING" (L). The 5.4.2 drawing on page 2 (PDF p.78) places the H and L symbols on both wings, while the page 7 table gives a position for the two 2 1/2 in. connections on the right-hand side only, with the left-hand side cell blank; the AC does not explain this. Page 7 does not say which tank each gravity-feed connection serves. AC chapter 5.2/5.3 turnaround charts (refuelling time and vehicle positions) are image pages and were not read. Maximum fuel imbalance, fuel temperature limits, ALS Part 5 content, and fuel limits in the Flight Manual: not in the sources read. Other FAA or EASA ADs on A300 ATA 28 (the survey lists only AD 2020-01-15): no search beyond the survey was done in this draft; EASA ADs incorporated by the FAA could not be searched. A310 items in AD 2020-01-15 are outside this chapter.

Kaynaklar

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EASA TCDS EASA.A.172 — Airbus A300, A310, A300-600, Issue 08 (2026-02-01) — §10.4 p.29; §20.4 p.63; §20.11 p.64; §15.6 p.47; §16.6 p.49; §17.6 p.51; §18.6 p.53; §19.6 p.55; §6.6 p.19; §2.6 p.10; §15.1 p.46; §16.1 p.48; §17.1 p.50; §18.1 p.52; §20.15 Note 6 p.65; §19.1 p.54; §20.15 Note 1 pp.64-65; §6.1 p.17; §2.1 p.9; §6 p.17. https://www.easa.europa.eu/en/downloads/17110/en · erişim 2026-11-10
FAA Joint Aircraft System/Component (JASC) Code Table and Definitions, Information last updated October 27, 2008 (2008-10-27) — p.20. https://www.faa.gov/sites/faa.gov/files/JASC_Code.pdf · erişim 2026-11-10
Airbus AC A300-600 — Aircraft Characteristics, Airport and Maintenance Planning, Revision 13 (2009-12-01) — §2.1 p.2 (PDF p.18); §2.1 p.2A (PDF p.19); §2.1 pp.2, 2A; §2.1 p.1 (PDF p.17); §5.4.6 p.7 (PDF p.83); §5.1 p.1 (PDF p.72). https://www.aircraft.airbus.com/sites/default/files/2023-02/Airbus-Commercial-Aircraft-AC-A300-600-Dec-2009.pdf · erişim 2026-11-10
FAA AD 2020-01-15 — Airbus SAS airplanes (A300-600 included), Issue 85 FR 7655 (2020-02-11) — §(d) p.7661; §(c) p.7661; Summary p.7655; Discussion p.7655; §(e) p.7661; §(g) p.7661; §(h) p.7661; §(g)-(h) p.7661; Comments p.7658; Comments pp.7656-7657; Comments pp.7658-7659; §(k) p.7661. https://www.govinfo.gov/content/pkg/FR-2020-02-11/html/2020-02512.htm · erişim 2026-11-09

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