Airworthiness Directive · Amendment 39-16698 · Airbus Model A300 and A310 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Airbus Model A300 and A310 Series Airplanes, and Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)
Superseded. A later AD replaced this one: AD 2017-04-05. Comply with the one in force.
This AD applies to all Airbus model airplanes identified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in any category.
(1) Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 airplanes.
(2) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes.
(3) Models A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-622R airplanes, and Model A300 C4-605R Variant F airplanes.
Note 1: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (t)(1) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529-1.
We are superseding three existing airworthiness directives (ADs) that apply to the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Within one year after August 9, 1996 (the effective date of AD 96-13-11), replace the revision of the maintenance program with the inspections, inspection intervals, repairs, and replacements defined in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994. Accomplish the actions specified in the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994, at the times specified in those service bulletins. The actions are to be accomplished in accordance with those service bulletins. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph.
(1) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994: Accomplish the actions specified in those service bulletins within the grace period specified in those service bulletins. The grace period is to be measured from August 9, 1996.
(2) For airplanes that have exceeded the threshold specified in any of the service bulletins identified in Section 6, “SB Reference List,″ in Airbus Industrie A300 Supplemental Structural Inspection Document, Revision 2, dated June 1994, and a grace period is not specified in that service bulletin: Accomplish the actions specified in that service bulletin within 1,500 flight cycles after August 9, 1996.
For airplanes identified in paragraph (c)(1) of this AD: Within 12 months after April 3, 2007 (the effective date of AD 2007-04-11), replace the revision of the maintenance program required by paragraph (g) of this AD with the supplemental structural inspections, inspection intervals, and repairs defined in Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 Temporary Revision (TR) 3.1, dated April 2006. Accomplish the actions specified in Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006, at the times specified in that ALI, except as provided by paragraph (i) of this AD. The actions must be accomplished in accordance with Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph.
(i) For airplanes identified in paragraph (c)(1) of this AD that have exceeded the threshold or intervals specified in the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, for the application tolerance on the first interval for new and revised requirements and have exceeded 50 percent of the intervals specified in sections D and E of Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005: Do the actions within 6 months after April 3, 2007.
Damaged, cracked, or corroded structure detected during any inspection done in accordance with the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, must be repaired, before further flight, in accordance with Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1, dated April 2006, except as provided by paragraph (k) of this AD; or other data meeting the certification basis of the airplane which is approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or by the European Aviation Safety Agency (EASA) (or its delegated agent).
(k) Where the Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies contacting Airbus for appropriate action: Before further flight, repair the damaged, cracked, or corroded structure using a method approved by either the Manager, International Branch, ANM-116; or the EASA (or its delegated agent).
Although Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies to do a “Sampling Concept″ in section B, this AD prohibits the use of such a sampling program and requires all affected airplanes of the fleet to be inspected.
Although Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, specifies to submit certain information to the manufacturer, this AD does not include that requirement.
For airplanes identified in paragraph (c)(3) of this AD: Within 3 months after October 31, 2007 (the effective date AD 2007-20-03), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006. The tolerance (grace period) for compliance (specified in paragraph 2 of Section B—Program Rules) with Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006, is within 2,000 flight cycles after October 31, 2007, provided that none of the following is exceeded. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph.
(1) Thresholds or intervals in the operator's current approved maintenance schedule that are taken from a previous ALI issue, if existing, and are higher than or equal to those given in Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006.
(2) 8 months after October 31, 2007.
(3) 50 percent of the intervals given in Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006.
(4) Any application tolerance given in the task description of Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006.
For airplanes identified in paragraph (c)(2) of this AD: Within 3 months after January 14, 2008 (the effective date of AD 2007-25-02), do the actions specified in paragraphs (o)(1) and (o)(2) of this AD. Accomplishing the initial ALI tasks required by paragraph (s) of this AD terminates the actions required by this paragraph.
(1) Revise the ALS of the ICA to incorporate the structural inspections and inspection intervals defined in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006 (approved by the EASA on May 31, 2006). Accomplish the actions specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, at the times specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, except as provided by paragraph (p) of this AD. Thereafter, except as provided by paragraphs (o)(2) and (t)(1) of this AD, no alternative structural inspection intervals may be approved. The actions specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be accomplished in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006.
(2) Revise the ALS of the ICA to incorporate the new and revised structural inspections and inspection intervals defined in Airbus Temporary Revision (TR) 6.1, dated November 2006 (approved by the EASA on December 12, 2006), to Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006. Thereafter, except as provided by paragraph (t)(1) of this AD, no alternative structural inspection intervals may be approved.
The tolerance (grace period) for compliance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, is within 1,500 flight cycles after January 14, 2008, provided that none of the following is exceeded.
(1) Thresholds or intervals in the operator's current approved maintenance schedule that are taken from a previous ALI issue, if existing, and are higher than or equal to those given in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006.
(2) 18 months after January 14, 2008.
(3) 50 percent of the intervals given in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006.
(4) Any application tolerance specified in Section D of Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006.
Damaged, cracked, or corroded structure detected during any inspection done in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be repaired, before further flight, in accordance with Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006; or in accordance with other data meeting the certification basis of the airplane that has been approved by either the Manager, International Branch, ANM-116, or the EASA (or its delegated agent). Where Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, specifies to contact Airbus for appropriate action: Before further flight, repair the damaged, cracked, or corroded structure using a method approved by either the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).
If any damage that exceeds the allowable limits specified in Airbus A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, is detected during any inspection required by this AD: At the applicable time specified in paragraph (r)(1) or (r)(2) of this AD, submit a report of the finding to Airbus, Customer Service Directorate, Attn: Department Manager Maintenance Engineering, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; e-mail: sched.maint@airbus.com. The report must include the ALI task reference, airplane serial number, the number of flight cycles and flight hours on the airplane, identification of the affected structure, location and description of the finding including its size and orientation, and the circumstance of detection and inspection method used.
(1) If the inspection was done after January 14, 2008: Submit the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to January 14, 2008: Submit the report within 30 days after January 14, 2008.
Within 3 months after the effective date of this AD: Revise the maintenance program to incorporate the structural inspections and inspection intervals defined in the applicable ALI document listed in Table 1 of this AD. Thereafter, except as provided by paragraph (t)(1) of this AD, no alternative structural inspections and inspection intervals may be approved. The actions must be accomplished in accordance with the applicable issue of the ALI. The initial ALI tasks must be done at the times specified in the applicable ALI document listed in Table 1 of this AD. Accomplishing the applicable initial ALI tasks constitutes terminating action for the requirements of paragraphs (g) through (r) of this AD for that airplane only.
| Model | Document | Issue | Date |
|---|---|---|---|
| A300 | Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/95A.1308/07 | 4 | June 2008. |
| A310 | Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 | 7 | June 2008. |
| A300-600 | Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07 | 12 | June 2008. |
Note 2: This AD differs from the MCAI and/or service information as follows: Where the MCAI includes a compliance time of “from the effective date of this AD,″ we have determined that a compliance time of “within 3 months after the effective date of this AD″ is appropriate. The manufacturer and EASA agree with this difference in compliance time.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
