AD 96-13-11: Structural Integrity for Airbus A300 Model B2-1A, A300 Model B2-1C and 5 more

Effective: August 9, 1996
Published: July 5, 1996 · 61 FR 35122–35125
Superseded by: AD2007-04-11
Models: A300 Model B2-1A, A300 Model B2-1C, A300 Model B2-203, A300 Model B2K-3C, A300 Model B4-103, A300 Model B4-203, A300 Model B4-2C
Product: Aircraft · Large airplane
Amendment: 39-9679
Docket: 94-NM-102-AD
Issued as: Final rule

Unofficial copy of the text in the FAA’s Dynamic Regulatory System. Only the govinfo PDF is the legal edition. DRS record last changed August 7, 2025.

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Summary

This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B2, B4-100, and B4-200 series airplanes, that currently requires supplemental structural inspections to detect fatigue cracking, and repair of cracked structure. This amendment requires revising the supplemental structural inspection (SSID) program by changing some of the inspection techniques, changing some of the thresholds and intervals for inspections, expanding the area to be inspected for some of the inspections, and revising the Fleet Leader Program. This amendment is prompted by a review of recent service history and reports received from the current SSID program required by the existing AD. The actions specified by this AD are intended to prevent reduced structural integrity of these airplanes due to fatigue cracking.

The airworthiness directive

96-13-11 AIRBUS INDUSTRIE: Amendment 39-9679. Docket 94-NM-102-AD. Supersedes AD 93-01-24, Amendment 39-8478.

Applicability: All Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 series airplanes, and Model A300 B4-2C, B4-103, and B4-203 series airplanes; certificated in any category.

NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (m) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Compliance: Required as indicated, unless accomplished previously.

To prevent reduced structural integrity of these airplanes due to fatigue cracking, accomplish the following:

(a) Within one year after March 9, 1993 (the effective date of AD 93-01-24, amendment 39-8478), incorporate a revision into the FAA-approved maintenance inspection program that provides for supplemental maintenance inspections, modifications, repair, or replacement of the significant structural details (SSD) and significant structural items (SSI) specified in "Airbus Industrie A300 Supplemental Structural Inspection Document" (SSID), dated September 1989 (hereafter referred to as "the SSID").

(b) Within one year after the effective date of this AD, replace the revision of the FAA-approved maintenance program required by paragraph (a) of this AD with the inspections, inspection intervals, repairs, and replacements defined in "Airbus Industrie A300 Supplemental Structural Inspection Document" (SSID), Revision 2, dated June 1994 (hereafter referred to as "Revision 2 of the SSID"). Accomplish the actions specified in the service bulletins identified in Section 6, "SB Reference List," Revision 2 of the SSID, at the times specified in those service bulletins. The actions are to be accomplished in accordance with those service bulletins.

(1) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, "SB Reference List," Revision 2 of the SSID: Accomplish the actions specified in those service bulletins within the grace period specified in that service bulletin. The grace period is to be measured from the effective date of this AD.

(2) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, "SB Reference List," Revision 2 of the SSID, and a grace period is not specified in that service bulletin: Accomplish the actions specified in that service bulletins within 1,500 flight cycles after the effective date of this AD.

(c) If any cracked structure is detected during the inspections required by either paragraph (a) or (b) of this AD, prior to further flight, permanently repair the cracked structure in accordance with either paragraph (c)(1), (c)(2), or (c)(3) of this AD.

NOTE 2: A permanent repair is defined as a repair that meets the certification basis of the airplane, and does not require additional modification at a later date.

(1) The service bulletins listed in Section 6, "SB Reference List," of the SSID [for airplanes that are currently being inspected in accordance with paragraph (a) of this AD]; or in accordance with a method approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate, if a permanent repair is not specified in any of these service bulletins. Or

(2) The service bulletins listed in Section 6, "SB Reference List," of Revision 2 of the SSID [for airplanes that are currently being inspected in accordance with paragraph (b) of this AD]; or in accordance with a method approved by the Manager, Standardization Branch, ANM-113, if a permanent repair is not specified in any of these service bulletins. Or

(3) Other permanent repair data meeting the certification basis of the airplane which is approved by the Manager, Standardization Branch, ANM-113, or by the Direction G n rale de l'Aviation Civile (DGAC) of France.

(d) For airplanes identified as Fleet Leader Program (FLP) in Section 5, "Fleet Leader Program," of the SSID or Revision 2 of the SSID: Inspect according to the instructions and intervals specified in paragraph 4.4, "Adjustment of Inspection Requirements and DSG," of Section 4, or Section 9, as applicable, of the SSID [for airplanes inspected in accordance with paragraph (a) of this AD], or Revision 2 of the SSID [for airplanes inspected in accordance with paragraph (b) of this AD], for each SSD.(e) For the purpose of accomplishing paragraphs (d), (f), (g), and (i) of this AD, operators shall not use paragraph 6.2, "Complete RR Method," of Section 9 of the SSID to calculate inspection thresholds and intervals.

(f) For Model A300-B2 and B2K-3C series airplanes: For any SSD that has exceeded the values of the threshold specified in paragraph 6, "Inspection Threshold and Intervals," Section 9 of the SSID, inspect at the time specified in either paragraph (f)(1) or (f)(2) of this AD, as applicable.

(1) For airplanes inspected in accordance with paragraph (a) of this AD: Inspect within 2,000 landings after March 9, 1993, in accordance with the SSID. Or

(2) For airplanes inspected in accordance with paragraph (b) of this AD: Inspect within 2,000 landings after the effective date of this AD, in accordance with Revision 2 of the SSID.

(g) For Model A300-B4 series airplanes: For any SSD that has exceeded the values of the threshold specified in paragraph 6, "Inspection Threshold and Intervals," Section 9 of the SSID, inspect at the time specified in either paragraph (g)(1) or (g)(2) of this AD, as applicable.

(1) For airplanes inspected in accordance with paragraph (a) of this AD: Inspect within 1,500 landings after March 9, 1993 [the effective date of AD 93-01-24, amendment 39-8478]. Or

(2) For airplanes inspected in accordance with paragraph (b) of this AD: Inspect within 1,500 landings after the effective date of this AD.

(h) For airplanes identified as FLP in Section 5, "Fleet Leader Program," of the SSID or Revision 2 of the SSID: Within one year after the effective date of this AD, apply the basic requirements given in Revision 2 of the SSID.

(i) For airplanes that are subject to the requirements of paragraph (b) of this AD, and have exceeded the initial inspection threshold specified in paragraph 4.4, "Adjustment of Inspection Requirements and DSG," of Section 4, or paragraph 6, "Inspection Threshold and Intervals," of Section 9, for each SSD: Perform the initial inspection prior to the accumulation of the number of flight cycles specified in paragraph 7, "Additional Information," Section 9, of Revision 2 of the SSID.

NOTE 3: Fatigue ratings are not applicable to these allowances; therefore, no adjustment is required.

NOTE 4: Paragraph (i) of this AD provides the "grace" periods for those airplanes that are new to the FLP or that have newly added or revised SSID requirements in accordance with paragraph (b) of this AD.

(j) The grace period provided by paragraph (i) of this AD is also applicable to the thresholds and/or repeat intervals for each SSD for which the inspection interval or threshold was reduced in accordance with the requirements of paragraph (b) of this AD.

(k) For FLP airplanes identified in Section 5, "Fleet Leader Program," of the SSID or Revision 2 of the SSID that are listed in Section 7, "SSI Limitation List," of the SSID [for airplanes that are currently being inspected in accordance with paragraph (a) of this AD], or Revision 2 of the SSID [for airplanes that are currently being inspected in accordance with paragraph (b) of this AD]: Inspect at intervals not to exceed the interval specified for each SSI, in accordance with the values given in Section 7, "SSI Limitation List," of the SSID or Revision 2 of the SSID, as applicable.

(l) For all airplanes: All inspection results, positive or negative, must be reported to Airbus Industrie in accordance with either paragraph (l)(1) or (l)(2) of this AD, as applicable. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.

(1) For FLP airplanes, identified in Section 5, "Fleet Leader Program," of the SSID or Revision 2 of the SSID: Submit reports in accordance with the instructionsin paragraph 5.2, "SSIP Inspection Reporting," of Section 5, and paragraph 7.1, "General," of Section 7 of the SSID [for airplanes that are currently being inspected in accordance with paragraph (a) of this AD]; or Revision 2 of the SSID [for airplanes inspected in accordance with paragraph (b) of this AD].

(2) For all airplanes that are subject to Section 6, "SB Reference List," of the SSID: Submit reports in accordance with the instructions in the applicable service bulletins identified in Section 6 of the SSID [for airplanes that are currently being inspected in accordance with paragraph (a) of this AD]; or Revision 2 of the SSID [for airplanes that are currently being inspected in accordance with paragraph (b) of this AD].

(m) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submittheir requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113.

NOTE 5: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113.

NOTE 6: Alternative methods of compliance previously granted for AD 93-01-24, amendment 39-8478, continue to be considered as acceptable alternative methods of compliance with this amendment.

(n) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.

(o) The actions shall be done in accordance with Airbus Industrie Supplemental Structural Inspection Document (SSID), dated September 1989; or Airbus Industrie A300 SSID, Revision 2, dated June 1994, as applicable. Airbus Industrie SSID, Revision 2, dated June 1994, contains the following list of effective pages:

Page Number Revision Level Shown on Page Date Shown on Page Record of Revision 2 JUN94 Section 0

O-LEP 1 2 JUN94 O-TOC 1 2 JUN94 Section 1

1-LEP 1 2 JUN94 1-TOC 1 1 MAR93 1 1 MAR93 2, 3 2 JUN94 Section 2

2-LEP 1 2 JUN94 2-TOC 1 1 MAR93 1, 2 1 MAR93 3 2 JUN94 Section 3

3-LEP 1 2 JUN94 3-TOC 1 2 JUN94 1, 2 2 JUN94 Section 4

4-LEP 1 1 MAR93 4-TOC 1 1 MAR93 1-3, 7-9, 11-16, 19, 1 MAR93 24-38, 40-46

4-6, 10, 17, 18, 20-23 0 SEP89 39

Page Number Revision Level Shown on Page Date Shown on Page Section 5

5-LEP 1 2 JUN94 5-TOC 1 2 JUN94 1-48 2 JUN94 Section 6

6-LEP 1 2 JUN94 6-TOC 1 1 MAR93 1 1 MAR93 2-4 2 JUN94 Section 7

7-LEP 1 1 MAR93 7-TOC 1 1 MAR93 1-10 1 MAR93 Section 8

8-LEP 1 1 MAR93 8-TOC 1 1 MAR93 1-5 1 MAR93