Airworthiness Directive · Amendment 39-18605 · Time limits/maintenance checks
Airbus Airplanes
This AD applies to Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all manufacturer serial numbers.
We are superseding Airworthiness Directive (AD) 2007-21-14 R1 for all Airbus Model A310 series airplanes. AD 2007-21-14 R1 required revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This new AD requires revising the maintenance program or inspection program to incorporate revised fuel maintenance and inspection tasks. This AD was prompted by the issuance of more restrictive maintenance requirements and/or airworthiness limitations by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors caused by latent failures, alterations, repairs, or maintenance actions, could result in fuel tank explosions and consequent loss of the airplane.
This paragraph restates the requirements of paragraph (f) of AD 2007-21-14 R1, with no changes. Within 3 months after November 20, 2007 (the effective date of AD 2007-21-14, Amendment 39-15232, (72 FR 58499, October 16, 2007) (“AD 2007-21-14”)), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the European Aviation Safety Agency (EASA) on July 6, 2007), Section 1, “Maintenance/Inspection Tasks.” For all tasks identified in Section 1 of Document 95A.1930/05, Issue 2, dated May 11, 2007, the initial compliance times start from the later of the times specified in paragraphs (g)(1) and (g)(2) of this AD, and the repetitive inspections must be accomplished thereafter at the intervals specified in Section 1 of Document 95A.1930/05, except as provided by paragraph (h) of this AD.
(1) November 20, 2007 (the effective date of AD 2007-21-14).
(2) The date of issuance of the original French standard airworthiness certificate or the date of issuance of the original French export certificate of airworthiness.
Note 1 to paragraph (g) of this AD: Airbus Operator Information Telex SE 999.0079/07, Revision 01, dated August 14, 2007, identifies the applicable sections of the Airbus A310 Airplane Maintenance Manual necessary for accomplishing the tasks specified in Section 1 of Document 95A.1930/05.
This paragraph restates the requirements of paragraph (g) of AD 2007-21-14 R1, with no changes. For Task 28-18-00-03-1 identified in Section 1 of Document 95A.1930/05, “Maintenance/Inspection Tasks,” of Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007): The initial compliance time is the later of the times specified in paragraphs (h)(1) and (h)(2) of this AD. Thereafter, Task 28-18-00-03-1 identified in Section 1 of Document 95A.1930/05, “Maintenance/Inspection Tasks,” of Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007), must be accomplished at the repetitive interval specified in Section 1 of Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007).
(1) Prior to the accumulation of 40,000 total flight hours.
(2) Within 72 months or 20,000 flight hours after November 20, 2007 (the effective date of AD 2007-21-14), whichever occurs first.
This paragraph restates the requirements of paragraph (h) of AD 2007-21-14 R1, with no changes. Within 12 months after November 20, 2007 (the effective date of AD 2007-21-14), revise the ALS of the Instructions for Continued Airworthiness to incorporate Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, dated May 31, 2006, as defined in Airbus A310 Fuel Airworthiness Limitations, Document 95A.1930/05, Issue 2, dated May 11, 2007 (approved by the EASA on July 6, 2007), Section 2, “Critical Design Configuration Control Limitations.”
This paragraph restates the requirements of paragraph (i) of AD 2007-21-14 R1, with a new paragraph reference. Except as provided by paragraphs (k) and (m)(1) of this AD: After accomplishing the actions specified in paragraphs (g) and (i) of this AD, no alternative inspections, inspection intervals, or CDCCLs may be used.
Within 3 months after the effective date of this AD, revise the maintenance or inspection program, as applicable, by incorporating the airworthiness limitations as specified in Airbus A310 Airworthiness Limitations Section (ALS) Part 5—Fuel Airworthiness Limitations, Revision 00, dated May 27, 2014. The initial compliance times for the actions specified Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, Revision 00, dated May 27, 2014, are at the later of the times specified in Airbus A310 ALS Part 5—Fuel Airworthiness Limitations, Revision 00, dated May 27, 2014, or within 3 months after the effective date of this AD, whichever occurs later. Accomplishing the revision required by this paragraph terminates the actions required by paragraphs (g) through (i) of this AD.
After the maintenance or inspection program has been revised as required by paragraph (k) of this AD, no alternative actions (e.g., inspections), intervals, and/or CDCCLs may be used unless the actions, intervals, and/or CDCCLs are approved as an alternative method of compliance (AMOC) in accordance with the procedures specified in paragraph (m)(1) of this AD.
