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A300 · ATA 57 · Wings

Wings

Draft · under review

This draft is for study only; it is not a maintenance document. Sources: FAA AD 2022-11-01 (87 FR 32292, 31 May 2022), FAA AD 2019-12-04 (84 FR 31710, 3 Jul 2019) and FAA AD 2019-14-08 (84 FR 45065, 28 Aug 2019), all three downloaded from govinfo.gov on 2026-11-10 and read as literal Federal Register text (page numbers are Federal Register pages); FAA JASC code table (grouping and code description only; printed page = PDF page minus 7, both given). Model names are given as each source prints them; nothing said about one model is extended to the family. The heading "57-00" is this site's grouping, following FAA JASC chapter 57 "Wings" with code 5700 "Wing Structure"; none of the three ADs prints a "57-xx" sub-section numbering. The only ATA statements the ADs print are their "Subject" paragraphs: Code 57, Wings for AD 2022-11-01 and AD 2019-12-04, and Code 24, Electrical power for AD 2019-14-08. No licensed manual, no TCDS table and no Airbus AC page was used. The ADs are described only as to what they address; this draft gives no compliance times and no inspection procedures. Where the AD quotes or reports EASA text, the bullet says so.

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

57-00 Wing structure: general

  • The FAA JASC table describes code 5700 as reports pertaining to the center wing and outer wing structural units and associated components and members which support the aircraft in flight, to be used for general reports of the primary wing structure. It is an FAA code table, not a description of the A300.[1]
  • JASC splits the 57 series into, among others, 5711 Wing Spar, 5712 Wing, Rib/Bulkhead, 5713 Wing, Longeron/Stringer, 5714 Wing, Center Box ("the center wing box structure"), 5730 Wing, Plate/Skin and 5743 Wing, Landing Gear Attach Fittings ("the fittings on the wing used for attachment to the landing gear").[1]
  • JASC also lists 5751 Ailerons, 5753 Trailing Edge Flaps, 5754 Leading Edge Devices, 5755 Spoilers and 5797 Wing System Wiring under code 57.[1]

57-00 Main landing gear (MLG) support rib 5 lower flange (AD 2022-11-01)

  • Applicability: The AD's summary says it concerns "certain Airbus SAS Model A300 series airplanes, Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes)".[2]
  • Applicability: Applicability paragraph (c), as printed: "This AD applies to the Airbus SAS airplanes, certificated in any category, without Airbus modification 11912 and identified in figure 1 to paragraph (c) of this AD." The figure is a graphic (TIFF) that the govinfo text file does not show, so the airplanes it identifies were not read here.[2]
  • Applicability: The AD's background says EASA AD 2021-0190 (dated August 17, 2021) concerns "certain Airbus SAS Model A300, A300-600, and A300-600ST airplanes"; the FAA states that Model A300-600ST airplanes are not certificated by the FAA and are not included on the U.S. type certificate data sheet, so the AD does not include them in its applicability.[2]
  • Applicability: The AD gives its subject as "Air Transport Association (ATA) of America Code 57, Wings".[2]
  • What the AD addresses: The AD was prompted by "reports of cracking in the main landing gear (MLG) support rib 5 lower flange, inboard and outboard of Rib 5, on the right-hand and left-hand sides".[2]
  • What the AD addresses: The FAA states it issued the AD "to address cracking of the MLG support rib 5 lower flange", a condition that "if not detected and corrected, could affect the structural integrity of the airplane".[2][2]
  • What the AD addresses: The AD's summary describes the requirement as a one-time detailed inspection (DET) of the affected area and applicable corrective actions, as specified in EASA AD 2021-0190, which the AD incorporates by reference.[2][2]
  • What the AD addresses: The AD's description of EASA AD 2021-0190 says that AD "specifies procedures for a DET of the affected area, a one-time fluorescent penetrant inspection (FPI) around some fastener holes in the affected area, and applicable corrective action(s) including crack repair".[2]
  • What the AD addresses: The AD's cost section refers to replacing "any cracked rib" as an on-condition action that "would be required based on the results of any required actions and repair status".[2]
  • What the AD addresses: A commenter (FedEx) said it had airplanes with fasteners different from those specified in a required for compliance (RC) step in Airbus Alert Operators Transmission (AOT) A57W017-21, which the AD says is referred to in EASA AD 2021-0190; this is the commenter's statement as the AD reports it. The FAA concurred with the request and, in paragraph (i)(1)(ii), approved two Airbus Statements of Airworthiness Compliance (ASAC) as alternative methods of compliance for the corresponding provisions of this AD, for the airplanes identified in those ASACs only.[2][2]

57-00 FR47 angle fitting, center wing box (CWB) lower angle fittings and lower panel (AD 2019-12-04)

  • Applicability: Paragraph (c), as printed: "This AD applies to 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 European Aviation Safety Agency (EASA) AD 2018-0229, dated October 23, 2018".[3]
  • Applicability: The AD gives its subject as "Air Transport Association (ATA) of America Code 57, Wings".[3]
  • Applicability: The AD supersedes AD 2018-19-18, which, as the summary prints it, applied to certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F airplanes; and Model A300 F4-605R airplanes. The summary says the new AD "expands the applicability".[3]
  • What the AD addresses: The AD was prompted by "reports of cracking of the frame (FR) 47 angle fitting"; the FAA states it issued the AD "to address cracking of the FR47 angle fitting, which could result in reduced structural integrity of the airplane".[3]
  • What the AD addresses: 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]
  • What the AD addresses: The AD's description of EASA AD 2018-0229 lists, among the procedures: a modification of the angle fitting attachment holes; inspection of certain holes of the internal lower angle fitting web; inspection of certain holes of the internal lower angle fitting horizontal splicing; inspection of the aft bottom panel; inspection of "the FR47/Rib 1 junction area"; inspection of certain holes of the CWB lower angle fittings; inspection of the CWB lower panel; and corrective actions.[3]
  • What the AD addresses: Per the same description, the corrective actions include a rotating probe inspection for cracking, replacing damaged fasteners, reaming and drilling holes, installing the next nominal fastener for oversized bore holes, and repairing cracks.[3]
  • What the AD addresses: The EASA text quoted in the AD (the MCAI) says that cracks were found on "CWB FR47 angle fittings", and that these cracks "if not detected and corrected, could affect the structural integrity of the CWB of the aeroplane".[3]
  • What the AD addresses: The same EASA text says that, later, cracks "were reportedly found on the horizontal flange of the FR47 internal corner angle fitting".[3]
  • What the AD addresses: The same EASA text names Airbus service bulletins A300-57-6049, A300-57-6050 and A300-57-6086 as prompted by the cracks, A300-57-6113 as a "new (recommended) modification" and A300-57-6119 and A300-57-6121 as further Airbus publications; it also mentions earlier EASA and DGAC France ADs, including one "to require CWB FR47 angle fittings inspections for A300 F4-608ST aeroplanes", a model that paragraph (c) of this FAA AD does not name.[3][3]
  • What the AD addresses: The EASA text says that EASA AD 2018-0229 "expands the Applicability (Group 3) to include post-mod 12171 and post-mod 12249 aeroplanes" and (in the bracketed words of the FAA's quotation) requires sending inspection results to Airbus.[3]
  • What the AD addresses: A commenter (UPS) said that post-modification 12171 and 12249 airplanes have not had any crack findings in service; this is the commenter's statement as the AD reports it, not an FAA finding.[3]

Cross-reference, not grouped under 57-00: wing leading and trailing edge wiring bundles (AD 2019-14-08, coded ATA 24 by the AD)

  • This AD concerns wiring in the wings but states its own subject as ATA 24; 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).[4]
  • AD 2019-14-08 gives its subject as "Air Transport Association (ATA) of America Code 24, Electrical power".[4]
  • Applicability as printed: Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes; Model A300 B4-605R and B4-622R airplanes; Model A300 F4-605R and F4-622R airplanes; Model A300 C4-605R Variant F airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, "certificated in any category".[4]
  • Paragraph (e) says the AD was prompted by "reports of insufficient clearance for the electrical wiring bundles in the leading and trailing edges of the right-hand (RH) and left-hand (LH) wings"; the summary says it "was prompted by reports of missing installation information for certain airplanes" (the two statements differ and are given as printed); the FAA states it issued the AD to address insufficient clearance between wing structures and electrical wiring, "which could lead to chafing damage and arcing, possibly resulting in an on-board fire".[4][4][4]
  • The summary says the AD supersedes AD 2016-07-22, which "required modifying the electrical routing installation at the right-hand (RH) and left-hand (LH) wings to achieve a minimum distance between wiring bundles and surrounding structures", and that, "for certain airplanes", the new AD adds a requirement to further modify the electrical installations in both wings, as specified in EASA AD 2019-0014.[4]
  • The AD's Related IBR Material paragraph says EASA AD 2019-0014 "describes procedures for modifying the electrical installations in both wings (RH and LH)".[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.46 (PDF p.53); p.46-47 (PDF pp.53-54); p.47-48 (PDF pp.54-55). https://www.faa.gov/sites/faa.gov/files/JASC_Code.pdf · erişim 2026-11-10
  2. FAA AD 2022-11-01 — Airbus SAS airplanes (A300-600 included), Issue 87 FR 32292 (2022-05-31) — Summary p.32292; para (c) pp.32293-32294; Background p.32292; para (d) p.32294; para (e) p.32294; para (g) p.32294; Related Service Information p.32293; Costs of Compliance p.32293; Comments pp.32292-32293; para (i)(1)(ii) p.32294. https://www.govinfo.gov/content/pkg/FR-2022-05-31/html/2022-11538.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 (c) p.31712; para (d) p.31712; Summary p.31710; para (e) p.31712; Related IBR Material p.31711; Discussion p.31710; Discussion pp.31710-31711; Discussion p.31711; Comments p.31711. https://www.govinfo.gov/content/pkg/FR-2019-07-03/html/2019-14152.htm · erişim 2026-11-10
  4. FAA AD 2019-14-08 — Airbus SAS airplanes (A300-600 included), Issue 84 FR 45065 (2019-08-28) — para (d) p.45067; para (c) p.45067; para (e) p.45067; Summary p.45065; Discussion p.45066; Related IBR Material p.45066. https://www.govinfo.gov/content/pkg/FR-2019-08-28/html/2019-18518.htm · erişim 2026-11-10

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