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A300 · ATA 53 · Fuselage

Fuselage

Draft · under review

This draft is for study only; it is not a maintenance document. Sources: FAA AD 2020-21-04 (85 FR 64955, 14 Oct 2020) and FAA AD 2019-12-04 (84 FR 31710, 3 Jul 2019), both downloaded from govinfo.gov and read as literal Federal Register text (page numbers are Federal Register pages); Airbus AC A300-600 "Airplane Characteristics for Airport Planning" Revision 13, Dec 2009 (PDF p.22 is an image page; PDF pp.18-20 have a text layer whose table rows come out of order; all four pages were rendered and read visually); FAA JASC code table (grouping and code description only; printed page = PDF page minus 7). Page numbers for the AC are PDF page numbers, with the printed chapter and page given beside them. Model names are given as each source prints them. The heading "53-00" is this site's grouping, following FAA JASC chapter 53 "Fuselage" with code 5300 "Fuselage Structure (General)"; neither the ADs nor the AC pages read print a "53-xx" sub-section numbering for these items. The only "53" the ADs print is the "Air Transport Association (ATA) of America Code 53, Fuselage" subject line of AD 2020-21-04. No licensed manual and no TCDS table was used. The ADs are described only as to what they address; this draft gives no compliance times and no inspection procedures.

A300 and A300-600 models named per source · FAA Airworthiness Directives and Airbus AC

53-00 Fuselage structure: general

  • The FAA JASC table describes code 5300 as reports of structural units and associated components and members which make up the compartments for crew, passengers, equipment and cargo (the text also mentions the envelope and gondola of airships). It is an FAA code table, not a description of the A300.[1]
  • JASC splits the 53 series into, among others, 5311 Fuselage Main, Frame ("the main fuselage frames"; associated attach fittings are said to be covered in JASC code 5320), 5315 Fuselage Main, Floor Beam, 5330 Fuselage Main, Plate/Skin ("the exterior covering of the fuselage including access covers") and 5340 Fuselage Main, Attach Fittings ("the fittings on the fuselage used for the attachment of doors, wings, stabilizers, landing gear, engine and rotor pylons, and the support of equipment within the fuselage").[1]

53-00 Main deck cargo crossbeams, FR48 to FR54 (AD 2020-21-04)

  • Applicability: AD 2020-21-04 "applies to Airbus SAS Model A300 F4-605R and F4-622R airplanes, certificated in any category, as identified in" EASA AD 2020-0050, dated March 9, 2020, corrected March 11, 2020.[2]
  • Applicability: The AD's summary and discussion say "certain Airbus SAS Model A300 F4-600R series airplanes", while the applicability paragraph names only F4-605R and F4-622R; the two wordings differ, and the applicability paragraph is the one used here.[2][2]
  • Applicability: The AD gives its subject as "Air Transport Association (ATA) of America Code 53, Fuselage".[2]
  • What the AD addresses: The AD was prompted by "a report of damaged main deck cargo crossbeams on the right-hand side, between certain frame locations".[2][2]
  • What the AD addresses: The FAA states it issued the AD "to address damaged main deck cargo crossbeams, which could adversely affect the structural integrity of the airplane".[2][2]
  • What the AD addresses: The AD requires, as the AD summarises it, repetitive detailed inspections of the affected main deck cargo crossbeams for any damage and, depending on findings, applicable corrective actions as specified in EASA AD 2020-0050, which the AD incorporates by reference.[2][2]
  • What the AD addresses: The AD's description of EASA AD 2020-0050 says that AD "describes procedures for repetitive detailed inspections of the affected main deck cargo crossbeams from frame (FR) 48 to FR54 for any damage (including bent, curved, and cracked crossbeams), corrective actions, and terminating actions".[2]
  • What the AD addresses: Per the same description, the corrective actions include detailed inspections of the right-hand and left-hand crossbeams and lugs for damage (including buckling and cracking) and for the correct diameter of the lug/crossbeam holes, repair, and replacement of damaged crossbeams; optional terminating actions include replacement of crossbeams with "reinforced machined crossbeams".[2]
  • What the AD addresses: The AD also contains a reporting provision: inspection results are to be reported to Airbus.[2]
  • What the AD addresses: A commenter (UPS) said the unsafe condition was discovered as a result of tasks in the Airbus A300-600 Maintenance Planning Document; this is the commenter's statement as the AD reports it, not an FAA finding.[2]

Cross-reference, not grouped under 53-00: FR47 angle fitting (AD 2019-12-04, coded ATA 57 by the AD)

  • This AD names frame (FR) 47 and angle fittings but states its own subject as ATA 57; it is recorded here only as a cross-reference. This draft does not recode it; where it is treated is left to the Director (see Bekliyor).[3]
  • AD 2019-12-04 gives its subject as "Air Transport Association (ATA) of America Code 57, Wings".[3]
  • Applicability as printed: "Airbus SAS Model A300 B4-603, B4-620, B4-622, B4-605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes, certificated in any category, as identified in" EASA AD 2018-0229, dated October 23, 2018.[3]
  • The AD was prompted by reports of cracking of the frame (FR) 47 angle fitting; the FAA states it issued the AD to address that cracking, "which could result in reduced structural integrity of the airplane".[3]
  • The summary names, depending on airplane configuration, "a modification of certain angle fitting attachment holes" and repetitive inspections for cracking of certain holes of the internal lower angle fitting web, certain holes of the internal lower angle fitting horizontal splicing, the aft bottom panel and a certain junction area; and, for certain airplanes, repetitive inspections for cracking of certain holes of the center wing box (CWB) lower angle fittings and the CWB lower panel.[3]
  • The EASA text quoted in the AD says cracks were found on "CWB FR47 angle fittings" and that, later, cracks "were reportedly found on the horizontal flange of the FR47 internal corner angle fitting".[3]
  • The EASA text quoted in the AD names Airbus service bulletins A300-57-6049, A300-57-6050 and A300-57-6086 as prompted by the cracks, and A300-57-6113 as a "(recommended) modification".[3]

53-00 Fuselage and cargo volumes (AC chapter 2.1) and the "DIA." dimension on the front view (AC chapter 2.2)

  • Chapter 2.1 page 2 (DEC 01/09; PDF p.18) is headed with versions A300B4-600 (WV000 (Basic), WV008) and A300C4-600 PAX and FREIGHT (WV000 (Basic)); pages 2A (PDF p.19) and 2B (PDF p.20) are headed A300B4-600R (WV000 (Basic), WV001, WV002, WV003 on 2A; WV004, WV005, WV007, WV008, WV010 on 2B).[4]
  • Pressurized fuselage volume (A/C non equipped), as printed: 860 m3 and 30 370 ft3, for every version column on pp.2, 2A and 2B.[4]
  • Passenger compartment volume, as printed: 574 m3 (20 270 ft3) for A300B4-600 and A300C4-600 PAX; 540 m3 (19 069 ft3) for A300C4-600 FREIGHT; 574 m3 (20 270 ft3) for all A300B4-600R columns.[4]
  • Cockpit volume, as printed: 12 m3 (424 ft3) for every column.[4]
  • Usable cargo compartment volume, as printed: 158.54 m3 (5 602 ft3) for every column on the three pages.[4]
  • Footnote (1) on each of the three pages gives the volumes of the cargo compartments as: Fwd Cargo Compartment 76.51 m3 (2 702 ft3); Aft Cargo Hold Compartment 61.03 m3 (2 155 ft3); Bulk Cargo Compartment 21 m3 (742 ft3).[4]
  • The three metric footnote values add up to the printed 158.54 m3; the three ft3 values add up to 5 599 ft3, which differs from the printed 5 602 ft3 (printed as is).[4]
  • Chapter 2.2 page 2 (Oct 30/94; PDF p.22) shows the airplane in side and front view; next to the fuselage cross-section in the front view the drawing prints "DIA. 5.64 m" and "DIA. 18 ft 6 in." The drawing carries no text label naming the fuselage on that dimension.[4]

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.40 (PDF p.47); p.40-41 (PDF pp.47-48). https://www.faa.gov/sites/faa.gov/files/JASC_Code.pdf · erişim 2026-11-10
  2. FAA AD 2020-21-04 — Airbus SAS airplanes (A300-600 included), Issue 85 FR 64955 (2020-10-14) — para (c) p.64957; Summary p.64955; para (d) p.64957; para (e) p.64957; Discussion p.64955; para (g) p.64957; Related IBR Material p.64956; para (h)(3) p.64957; Comments p.64955. https://www.govinfo.gov/content/pkg/FR-2020-10-14/html/2020-22622.htm · erişim 2026-11-10
  3. FAA AD 2019-12-04 — Airbus SAS airplanes (A300-600 included), Issue 84 FR 31710 (2019-07-03) — para (d) p.31712; para (c) p.31712; para (e) p.31712; Summary p.31710; Discussion p.31710. https://www.govinfo.gov/content/pkg/FR-2019-07-03/html/2019-14152.htm · erişim 2026-11-10
  4. Airbus AC A300-600 — Aircraft Characteristics, Airport and Maintenance Planning, Revision 13 (2009-12-01) — §2.1 pp.2, 2A, 2B (PDF pp.18-20); §2.1 p.2 (PDF p.18); §2.2 p.2 (PDF p.22). 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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