Airworthiness Directives:
Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)
Rules and Regulations
Pages 27220-27227
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
FR Doc No: 2011-10684
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2010-1275; Directorate Identifier 2010-NM-091-AD;
Amendment 39-16688; AD 2011-10-07
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCA I) 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:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued to require a set of inspection- and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation
Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings. We are issuing this AD to require actions to correct the unsafe condition on these products.
DATES: This AD becomes effective June 15, 2011.
The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 15, 2011.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 3, 2011 (76
FR 34). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France Airworthiness Directive (AD) 1992-106-132(B) original issue up to revision 7 was issued to require a set of inspection- and modification tasks which addressed JAR/FAR [Joint Aviation
Regulation/Federal Aviation Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure [FAA AD 98- 26-01 corresponds to DGAC AD 1992-106-132(B)R4, dated June 5, 1996].
Following the Extended Design Service Goal activities as part of the Structure Task Group for the Airbus A310 program, EASA issued AD 2007-0053 which replaced DGAC France AD F-1992-106-132R7. Since the issuance of that AD, the thresholds and the intervals of some Airbus
Service Bulletins (SBs which address structure fatigue related areas on the wing parts), until now part of the requirements of AD 2007- 0053, have been updated.
For the reasons stated above, this new [EASA] AD requires the accomplishment of the structural fatigue-related corrective actions in accordance with the latest revision of these SBs which have been reviewed in the context of the A310 Extended Service Goal activities. Consequently, this new AD supersedes the requirements of paragraphs 1.8, 1.9, 1.10, 1.13, 1.18 of EASA AD 2007-0053, which has been revised accordingly.
The unsafe condition is reduced structural integrity of the wings. The required corrective actions are as follows, depending on airplane configuration:
For certain Model A310-203 and A310-222 airplanes:
Repetitive detailed inspections for cracking of the leading edge access panels around the bolt holes, and repair if necessary.
For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, A310-324, and A310-325 airplanes: Repetitive eddy current inspections to detect cracks in the holes around the overwing refueling aperture at ribs 13-14, and repair if necessary.
For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, A310-324, and A310-325 airplanes: Repetitive external detailed inspections for cracking of the top skin at ribs 13-14, repetitive internal detailed inspections for cracking of stringer 7 and stringer 8 of the overwing refuel aperture, and repair if necessary.
For certain Model A310-203 and A310-222 airplanes:
Repetitive detailed inspections for cracking around the bolts in the wing top skin upper surface of the front spar between rib 7 and rib 28, and repair if necessary.
For certain Model A310-203 and A310-222 airplanes:
Repetitive high frequency eddy current (HFEC) or X-ray inspections to detect cracking of the stringer runouts inboard and outboard of rib 14 at stringers 6, 7, 8, and 9, and repair if necessary.
For certain Model A310-203, A310-204, A310-222, A310-304,
A310-322, and A310-324 airplanes: Repetitive ultrasonic inspections for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, and repair if necessary.
You may obtain further information by examining the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public.
Explanation of Changes to This AD
We have moved the parenthetical information from paragraphs (g),
(i), (j), (o), and (q)(1), (q)(2), and (q)(3) of this AD. Instead, we have provided that information in Note 1, Note 3, Note 4, Note 6, and
Note 8 of this AD.
We have also revised tables 3 and 4 of this AD to refer to Model
``A310-322'' instead of ``A310A-322.'' We inadvertently referred to
``A310A-322'' in the NPRM.
Conclusion
We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these change will not increase the economic burden on any operator or increase the scope of the AD.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in general, agree with their substance. But
Page 27221
we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.
We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect 44 products of U.S. registry.
We also estimate that it will take about 97 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $362,780, or $8,245 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD: 1. Is not a ''significant regulatory action'' under Executive Order 12866; 2. Is not a ''significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly after receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new AD: 2011-10-07 Airbus: Amendment 39-16688. Docket No. FAA-2010-1275;
Directorate Identifier 2010-NM-091-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15, 2011.
Affected ADs
(b) This AD affects AD 90-19-07, Amendment 39-6731 (55 FR 37455,
September 12, 1990); and AD 91-06-18, Amendment 39-6940 (56 FR 10796, March 14, 1991).
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category, all certified models, all serial numbers.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued to require a set of inspection- and modification tasks which addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation
Regulation] 25-571 requirements related to damage-tolerance and fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the actions have already been done.
Restatement of Certain Requirements of AD 98-26-01, Amendment 39-10942
(63 FR 69179, December 16, 1998), With Reduced Compliance Times
Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks at Bolt Holes
(g) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the times specified in paragraph (h) of this AD, perform a detailed visual inspection to detect cracks in the external surface of the wing lower skin around the landing access panel holes of the leading edge, in accordance with the Airbus Service Bulletin A310-57-2002,
Revision 1, dated July 2, 1992; Airbus Service Bulletin A310-57- 2002, Revision 2, dated January 4, 1996; or Airbus Mandatory Service
Bulletin A310-57-2002, Revision 03, dated November 28, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager, International Branch,
ANM-116, FAA, Transport Airplane Directorate, or the Direction
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated agent) or EASA (or its delegated agent). Except as required by paragraph (n) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (g)(1) and (g)(2) of this AD; and thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus
Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 28, 2006. Accomplishment of Airbus Modification 05101 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (n) of this AD are applicable to the new inspections required by paragraph (n) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05101 before the accumulation of 9,400 total flight cycles and 18,800 total flight hours terminates the repetitive inspection requirements of this paragraph.
Note 1: Airbus Service Bulletin A310-57-2003, Revision 03, dated
October 16, 2006, is
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an additional source of guidance for accomplishing Airbus
Modification 05101.
Note 2: As of the effective date of this AD, if Airbus Service
Bulletin A310-57-2003 is done on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours, the actions specified in paragraph (g) of this AD are still required.
(1) Within 3,000 flight cycles after doing the detailed inspection specified in paragraph (g) of this AD.
(2) At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the detailed inspection required by paragraph (g) of this AD.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
(h) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification No. 05101 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2003 has been embodied in service before the accumulation of 9,400 total flight cycles and 18,800 total flight hours: At the earlier of the times specified in paragraphs (h)(1) and (h)(2) of this AD, do the detailed inspection required by paragraph (g) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999 (the effective date of AD 98-26-01, amendment 39-10942), whichever occurs later.
(2) At the later of the times specified in paragraph (h)(2)(i) and (h)(2)(ii) of this AD.
(i) Prior to the accumulation of 9,400 total flight cycles or 18,800 total flight hours, whichever occurs first.
(ii) Within 1,500 flight cycles or 3,000 flight hours, whichever occurs first, after the effective date of this AD.
Inspect Area around Overwing Refueling Aperture at Ribs 13-14
(i) For Model A310-203, A310-204, A310-222, A310-304, A310-322,
A310-324, and A310-325 airplanes that are listed in Airbus Service
Bulletin A310-57-2006, Revision 3, dated May 2, 1996, and are identified as Configuration 1 in Airbus Mandatory Service Bulletin
A310-57-2006, Revision 04, dated May 21, 2007: Prior to the accumulation of 6,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later, perform an eddy current inspection to detect cracks in the holes around the overwing refueling aperture at ribs 13-14, in accordance with Airbus
Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated
May 21, 2007. If any discrepancy is found, prior to further flight, perform follow-on corrective actions, as applicable, in accordance with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007; except where the service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate, or the DGAC (or its delegated agent) or EASA (or its delegated agent). Repeat the inspection specified in this paragraph at the earlier of the times specified in paragraphs (i)(1) and (i)(2) of this AD, and thereafter at intervals not to exceed 2,300 flight cycles or 4,600 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service
Bulletin A310-57-2006, Revision 04, dated May 21, 2007.
Accomplishment of Airbus Modification 05891H5128 terminates the repetitive inspections required by this paragraph.
(1) Within 3,000 flight cycles after doing the last inspection required by paragraph (i) of this AD.
(2) At the later of the times specified in paragraphs (i)(2)(i) and (i)(2)(ii) of this AD.
(i) Within 2,300 flight cycles or 4,600 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (i) of this AD.
(ii) Within 380 flight cycles or 770 flight hours, whichever occurs first, after the effective date of this AD.
Note 3: Airbus Service Bulletin A310-57-2020, Revision 07, dated June 5, 2006, is an additional source of guidance for accomplishing Airbus Modification 05891H5128.
Upper Skin Forward of Front Spar--Inspection for Cracks
(j) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2005 has been done in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the times specified in paragraph (k) of this AD, perform a detailed visual inspection to detect cracks around the bolts in the wing top skin upper surface of the front spar between rib 7 and rib 28, in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-57-2032, Revision 3, dated January 4, 1996; or Airbus
Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. If any discrepancy is found, prior to further flight, repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent).
Except as required by paragraph (p) of this AD, repeat the detailed inspection specified in this paragraph at the earlier of the times specified in paragraphs (j)(1) and (j)(2) of this AD, and thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first. As of the effective date of this AD, use only Airbus Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 1, 2006. Accomplishment of Airbus Modification 05026H0878 before the effective date of this AD terminates the repetitive inspection requirements of this paragraph; however, airplanes identified in paragraph (p) of this AD are applicable to the new inspections required by paragraph (p) of this AD. As of the effective date of this AD: Accomplishment of Airbus Modification 05026H0878 before the accumulation of 10,500 total flight cycles and 21,000 total flight hours terminates the repetitive inspection requirements of this paragraph.
(1) Within 4,500 flight cycles after doing the last inspection required by paragraph (j) of this AD.
(2) At the later of the times specified in paragraphs (j)(2)(i) and (j)(2)(ii) of this AD.
(i) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Note 4: Airbus Service Bulletin A310-57-2005, Revision 03, dated
October 2, 2006, is an additional source of guidance for accomplishing Airbus Modification 05026H0878.
Note 5: As of the effective date of this AD, if Airbus Service
Bulletin A310-57-2005 is done on or after the accumulation of 10,500 total flight cycles or on or after the accumulation of 21,000 total flight hours, the actions specified in paragraph (j) of this AD are still required.
(k) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, except airplanes on which Airbus modification 05026 has been embodied in production, or on which Airbus Service Bulletin A310-57- 2005 has been done in service before the accumulation of 10,500 total flight cycles and 21,000 total flight hours: At the earlier of the times specified in paragraphs (k)(1) and (k)(2) of this AD, do the detailed inspection required by paragraph (j) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,000 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
(i) Prior to the accumulation of 10,500 total flight cycles or 21,000 total flight hours, whichever occurs first.
(ii) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Stringer Flanges at Rib 14 Wing Bottom Skin--Inspect for Cracks
(l) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the compliance time specified in paragraph (m) of this AD, perform a high frequency eddy current (HFEC) or X-ray inspection to detect cracking of the stringer runouts inboard and outboard of rib 14 at stringers 6, 7, 8, and 9, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57- 2038, Revision 2, dated January 4, 1996; or Airbus Mandatory
Page 27223
Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006.
Do the next inspection at the earlier of the times specified in paragraph (l)(1) and (l)(2) of this AD, and repeat the inspection thereafter at intervals not to exceed the applicable times specified in table 1 of this AD. If any crack is detected, prior to further flight, repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or DGAC (or its delegated agent) or EASA (or its delegated agent). As of the effective date of this AD, use only
Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated
October 19, 2006.
(1) Within the applicable interval specified in paragraph 1.B.(5) of Airbus Service Bulletin A310-57-2038, Revision 2, dated
January 4, 1996.
(2) At the later of the times specified in paragraph (l)(2)(i) and (l)(2)(ii) of this AD.
(i) Within the applicable interval specified in table 1 of this
AD after doing the most recent inspection specified in paragraph (l) of this AD.
(ii) Within 1,100 flight cycles or 2,300 flight hours, whichever occurs first, after the effective date of this AD.
Table 1--Repetitive Intervals, Depending on Inspection Type
Repetitive interval (not to
Type of inspection
exceed)
X-Ray.................................. 7,200 flight cycles or 14,500 flight hours, whichever occurs first.
HFEC................................... 9,400 flight cycles or 18,800 flight hours, whichever occurs first.
(m) For Model A310-203 and A310-222 airplanes listed in Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, except airplanes on which Airbus modification 04987 has been done in production: At the earlier of the times specified in paragraphs
(m)(1) and (m)(2) of this AD, perform an inspection required by paragraph (l) of this AD.
(1) Prior to the accumulation of 12,000 total flight cycles, or within 1,500 flight cycles after January 20, 1999, whichever occurs later.
(2) At the later of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of this AD.
(i) Prior to the accumulation of 12,000 total flight cycles or 24,000 total flight hours, whichever occurs first.
(ii) Within 1,100 flight cycles or 2,300 flight hours after the effective date of this AD, whichever occurs first.
New Requirements of This AD
Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks at Bolt Holes--Additional Inspections for Certain Airplanes
(n) For Model A310-203 and A310-222 airplanes, on which Airbus
Service Bulletin A310-57-2003 has been done in service on or after the accumulation of 9,400 total flight cycles or on or after the accumulation of 18,800 total flight hours: Do the inspection required by paragraph (g) of this AD at the later of the times specified in paragraphs (n)(1) and (n)(2) of this AD. Repeat the inspection required by paragraph (g) of this AD thereafter at intervals not to exceed 2,300 flight cycles or 4,700 flight hours, whichever occurs first.
(1) Within 2,300 flight cycles or 4,700 flight hours, whichever occurs first, after doing the most recent detailed inspection required by paragraph (g) of this AD.
(2) Within 1,500 flight cycles or 3,000 flight hours, after the effective date of this AD, whichever occurs first.
Inspect Area Around Overwing Refueling Aperture at Ribs 13-14 for
Additional Airplanes
(o) For Model A310-203, A310-204, A310-222, A310-304, A310-322,
A310-324, and A310-325 airplanes, except for airplanes identified in paragraph (i) of this AD on which Airbus Modification 05891H5128 has not been done: At the applicable compliance time specified in table 2 of this AD, do the applicable actions specified in paragraph
(o)(1) or (o)(2) of this AD, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2006,
Revision 04, dated May 21, 2007. If any cracking is found, before further flight, repair in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2006,
Revision 04, dated May 21, 2007; except where this service bulletin specifies to contact Airbus for repair, before further flight, repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate, or EASA (or its delegated agent). Repeat the inspections thereafter at the applicable interval specified in table 2 of this AD. Certain compliance times specified in table 2 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours. For airplanes identified as Configuration 01 in Airbus Mandatory Service Bulletin
A310-57-2006, Revision 04, dated May 21, 2007, accomplishment of
Airbus Modification 05891H5128 terminates the repetitive inspections required by this paragraph for Configuration 01 airplanes; thereafter do the applicable actions specified in paragraph (o)(2) of this AD at the times specified in table 2 of this AD.
Note 6: Airbus Service Bulletin A310-57-2020, Revision 07, dated
June 5, 2006, is an additional source of guidance for accomplishing
Airbus Modification 05891H5128.
(1) For Configuration 01 airplanes, as identified in Airbus
Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 2007: Do a rotating probe eddy current inspection for cracking in the holes around the overwing refueling aperture at ribs 13-14.
(2) For Configuration 02 through 06 airplanes, as identified in
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated
May 21, 2007: Do an external detailed inspection for cracking of the top skin at ribs 13-14, and an internal detailed inspection for cracking of string 7 and string 8 of the overwing refuel aperture.
Table 2--Compliance Times for Configuration 01 Through 06 Airplanes
Airplanes as Identified in Airbus
Compliance time (whichever occurs later)
Repetitive interval
Mandatory Service Bulletin A310-57-
(not to exceed) 2006, revision 04, dated May 21, 2007
Configuration 01 airplanes........... Prior to the
Within 380 flight
2,300 flight cycles or accumulation of 6,000 cycles or 770 flight
4,600 flight hours, total flight cycles.
hours, whichever
whichever occurs occurs first, after
first. the effective date of this AD.
Configuration 02 airplanes........... Within 30,900 flight
Within 1,500 flight
11,300 flight cycles or cycles or 61,900
cycles or 18 months,
22,600 flight hours, flight hours,
whichever occurs
whichever occurs whichever occurs
first, after the
first. first, after
effective date of this accomplishing Airbus
AD.
Service Bulletin A310- 57-2020.
Configuration 03 airplanes........... Within 30,900 flight
Within 1,500 flight
12,000 flight cycles or cycles or 61,900
cycles or 18 months,
24,000 flight hours, flight hours,
whichever occurs
whichever occurs whichever occurs
first, after the
first. first, after Airbus
effective date of this
Modification
AD. 05891H5128 is done or
Airbus Service
Bulletin A310-57-2020 is accomplished.
Page 27224
Configuration 04 and 05 short range
Before the accumulation Within 1,500 flight
12,000 flight cycles or airplanes.
of 25,900 total flight cycles or 18 months,
33,600 flight hours, cycles or 72,500 total whichever occurs
whichever occurs flight hours,
first, after the
first. whichever occurs first. effective date of this
AD.
Configuration 04 and 05 long range
Before the accumulation Within 1,500 flight
9,400 flight cycles or airplanes.
of 18,800 total flight cycles or 18 months,
47,200 flight hours, cycles or 94,200 total whichever occurs
whichever occurs flight hours,
first, after the
first. whichever occurs first. effective date of this
AD.
Configuration 06..................... Before the accumulation Within 1,500 flight
12,000 flight cycles or of 30,900 total flight cycles or 18 months,
24,000 flight hours, cycles or 61,900 total whichever occurs
whichever occurs flight hours,
first, after the
first. whichever occurs first. effective date of this
AD.
Upper Skin Forward of Front Spar--Inspection for Cracks--Additional
Inspections for Certain Airplanes
(p) For Model A310-203 and A310-222 airplanes on which Airbus
Service Bulletin A310-57-2005 has been done in service on or after the accumulation of 10,500 total flight cycles or on or after 21,000 total flight hours: Do the inspection required by paragraph (j) of this AD at the later of the times specified in paragraphs (p)(1) and
(p)(2) of this AD. Repeat the inspection specified in paragraph (j) of this AD thereafter at intervals not to exceed 3,900 flight cycles or 7,900 flight hours, whichever occurs first.
(1) Within 3,900 flight cycles or 7,900 flight hours, whichever occurs first, after doing the most recent inspection required by paragraph (j) of this AD.
(2) Within 850 flight cycles or 1,700 flight hours, whichever occurs first, after the effective date of this AD.
Inspection of Rear Spar at Selected Bolt Locations for Attachment of
Main landing Gear Forward Pick-Up Fitting
(q) For Model A310-203, A310-204, A310-222, A310-304, A310-322, and A310-324 airplanes, except airplanes on which Airbus modification 07601 has been done in production: Do the applicable actions specified in paragraphs (q)(1), (q)(2), and (q)(3) of this
AD. If any cracking is found during any inspection, before further flight, repair in accordance with a method approved by either the
Manager, International Branch, ANM-116, FAA, Transport Airplane
Directorate, or EASA (or its delegated agent).
Note 7: For Model A310-304, A310-322, and A310-324 airplanes on which Airbus modification 07601 has been done, guidance for post- modification inspections can be found in Structure Significant Item
(SSI) 57.21.16 of the Maintenance Review Board Document (MRBD).
(1) For airplanes on which Airbus Modification 07925H1113 and
Modification 11578H5436 have not been done: At the applicable time specified in table 3 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service
Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 3 of this AD until Airbus Modification 07925H1113 or 11578H5436 has been done. After doing Airbus Modification 07925H1113 or 11578H5436 do the applicable actions specified in paragraph
(q)(2) or (q)(3) of this AD at the times specified in paragraph
(q)(2) or (q)(3) of this AD, as applicable. Certain compliance times specified in table 3 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Note 8: Airbus Service Bulletin A310-57-2049, Revision 6, dated
November 26, 1997, is an additional source of guidance for accomplishing Airbus Modification 07925H1113. Airbus Service
Bulletin A310-57-2074, Revision 03, dated July 3, 2006, is an additional source of guidance for accomplishing Airbus Modification 11578H5436.
Table 3--Compliance Times for Airplanes Pre-Mod 07925 and Pre-Mod 11578
Airplanes
Compliance time (whichever occurs later)
Repetitive interval
(not to exceed)
Model A310-203, A310-204, and A310-
Prior to the
Within 750 flight
2,800 flight cycles or 222 airplanes.
accumulation of 9,800 cycles or 1,500 flight 5,700 flight hours, total flight cycles or hours, whichever
whichever occurs 19,600 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310-
Prior to the
Within 750 flight
2,400 flight cycles or 324 short range airplanes.
accumulation of 7,100 cycles or 1,500 flight 6,900 flight hours, total flight cycles or hours, whichever
whichever occurs 20,100 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310-
Prior to the
Within 750 flight
1,900 flight cycles or 324 long range airplanes.
accumulation of 5,700 cycles or 1,500 flight 9,800 flight hours, total flight cycles or hours, whichever
whichever occurs 28,600 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
(2) For airplanes on which Airbus Modification 07925H1113 has been done: At the applicable time specified in table 4 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated
December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 4 of this AD. Certain compliance times specified in table 4 of this AD are applicable to short range use,
AFT equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Page 27225
Table 4--Compliance Times for Airplanes Post-Mod 07925
--
--
--
--
Airplanes
Compliance time (whichever occurs later)
Repetitive interval
(not to exceed)
Model A310-203, A310-204, and A310-
Prior to the
Within 750 flight
9,400 flight cycles or 222 airplanes.
accumulation of 14,700 cycles or 1,500 flight 18,900 flight hours, total flight cycles or hours, whichever
whichever occurs 29,400 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310-
Prior to the
Within 750 flight
5,000 flight cycles or 324 short range airplanes.
accumulation of 11,900 cycles or 1,500 flight 14,000 flight hours, total flight cycles or hours, whichever
whichever occurs 33,500 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
Model A310-304, A310-322, and A310-
Prior to the
Within 750 flight
4,000 flight cycles or 324 long range airplanes.
accumulation of 9,500 cycles or 1,500 flight 20,000 flight hours, total flight cycles or hours, whichever
whichever occurs 47,700 total flight
occurs first, after
first. hours, whichever
the effective date of occurs first.
this AD.
(3) For airplanes on which Airbus Modification 11578H5436 has been done: At the applicable time specified in table 5 of this AD, perform an ultrasonic inspection for cracking in certain bolt holes where the main landing gear forward pick-up fitting is attached to the rear spar, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated
December 1, 2006. Repeat the inspection thereafter at the applicable interval specified in table 5 of this AD. Certain compliance times specified in table 5 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 4.0 hours, or long range use, AFT exceeding 4.0 hours.
Table 5--Compliance Times for Airplanes Post-Mod 11578
Airplanes
Compliance time (whichever occurs later)
Repetitive interval
(not to exceed)
Model A310-203, A310-204, and A310-
Within 29,600 flight
Within 750 flight
9,400 flight cycles or 222 airplanes.
cycles or 59,200
cycles or 1,500 flight 18,900 flight hours, flight hours,
hours, whichever
whichever occurs whichever occurs
occurs first, after
first. first, after Airbus
the effective date of
Modification
this AD. 11578H5436 has been done.
Model A310-304, A310-322, and A310-
Within 24,200 flight
Within 750 flight
5,000 flight cycles or 324 short range airplanes.
cycles or 67,900
cycles or 1,500 flight 14,000 flight hours, flight hours,
hours, whichever
whichever occurs whichever occurs
occurs first, after
first. first, after Airbus
the effective date of
Modification
this AD. 11578H5436 has been done.
Model A310-304, A310-322, and A310-
Within 19,300 flight
Within 750 flight
4,000 flight cycles or 324 long range airplanes.
cycles or 96,800
cycles or 1,500 flight 20,000 flight hours, flight hours,
hours, whichever
whichever occurs whichever occurs
occurs first, after
first. first, after Airbus
the effective date of
Modification
this AD. 11578H5436 has been done.
Credit for Actions Accomplished in Accordance With Previous Service
Information
(r) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, are acceptable for compliance with the corresponding actions specified in paragraph (l) of this AD.
(s) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999, are acceptable for compliance with the corresponding actions specified in paragraph (q) of this AD.
Terminating Action for Paragraph (a) of AD 90-19-07
(t) Accomplishing an inspection in accordance with Airbus
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, or
Revision 03, dated September 4, 1998; or Airbus Mandatory Service
Bulletin A310-57-2038, Revision 04, dated October 19, 2006; terminates the requirements of paragraph (a) of AD 90-19-07.
Note 9: Airbus Service Bulletin A310-57-2038, Revision 2, dated
January 4, 1996; and Airbus Mandatory Service Bulletin A310-57-2038,
Revision 04, dated October 19, 2006; are referred to in paragraph
(l) of this AD. Airbus Service Bulletin A310-57-2038, Revision 03, dated September 4, 1998, is referred to in paragraph (r) of this AD.
Terminating Action for AD 91-06-18
(u) Accomplishing an inspection in accordance with Airbus
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated
October 16, 1996; Airbus Service Bulletin A310-57-2046, Revision 07, dated April 2, 1999; or Airbus Mandatory Service Bulletin A310-57- 2046, Revision 08, dated December 1, 2006; terminates the requirements of AD 91-06-18.
Note 10: Airbus Mandatory Service Bulletin A310-57-2046,
Revision 08, dated December 1, 2006, is referred to in paragraph (q) of this AD. Airbus Service Bulletin A310-57-2046, Revision 07, dated
April 2, 1999, is referred to in paragraph (s) of this AD. Airbus
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, as revised by Airbus Service Bulletin Change Notice 4A, dated
October 16, 1996, is referred to in paragraph (n) of AD 98-26-01.
FAA AD Differences
Note 11: This AD differs from the MCAI and/or service information as follows:
Although the MCAI or service information allows further flight after cracks are found during compliance with the required action, paragraph (j) of this AD requires that you repair the crack(s) before further flight.
Other FAA AD Provisions
(v) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, Transport
Page 27226
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify your principal inspector or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD. AMOCs approved previously in accordance with AD 98-26-01, are approved as
AMOCs for the corresponding provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
Related Information
(w) Refer to MCAI EASA Airworthiness Directive 2007-0242, dated
September 4, 2007, and the Airbus service bulletins listed in table 6 of this AD for related information.
Table 6--Related Service Information
Service Bulletin
Revision
Date
Airbus Mandatory Service Bulletin A310- 03.......................... November 28, 2006. 57-2002.
Airbus Mandatory Service Bulletin A310- 04.......................... May 21, 2007. 57-2006.
Airbus Mandatory Service Bulletin A310- 04.......................... December 1, 2006. 57-2032.
Airbus Mandatory Service Bulletin A310- 04.......................... October 19, 2006. 57-2038.
Airbus Mandatory Service Bulletin A310- 08.......................... December 1, 2006. 57-2046.
Airbus Service Bulletin A310-57-2038.... 2........................... January 4, 1996.
Airbus Service Bulletin A310-57-2038.... 03.......................... September 4, 1998
Airbus Service Bulletin A310-57-2046.... 4........................... October 16, 1996.
Airbus Service Bulletin A310-57-2046.... 07.......................... April 2, 1999.
Airbus Service Bulletin A310-57-2046,
Original.................... October 16, 1996.
Change Notice 4A.
Material Incorporated by Reference
(x) You must use the service bulletins contained in table 7 of this AD to do the actions required by this AD, unless the AD specifies otherwise. If you accomplish the optional terminating actions specified by this AD, you must use the service information contained in table 7 of this AD to perform those actions unless the
AD specifies otherwise.
Table 7--All Material Incorporated by Reference
Required/optional
Service Bulletin
Revision
Date
action
Airbus Mandatory Service Bulletin
03...................... November 28, 2006...... Required.
A310-57-2002.
Airbus Mandatory Service Bulletin
04...................... May 21, 2007........... Required.
A310-57-2006.
Airbus Mandatory Service Bulletin
04...................... December 1, 2006....... Required.
A310-57-2032.
Airbus Mandatory Service Bulletin
04...................... October 19, 2006....... Required and optional.
A310-57-2038.
Airbus Mandatory Service Bulletin
08...................... December 1, 2006....... Required and optional.
A310-57-2046.
Airbus Service Bulletin A310-57-2038 2....................... January 4, 1996........ Optional.
Airbus Service Bulletin A310-57-2038 03...................... September 4, 1998...... Optional.
Airbus Service Bulletin A310-57-2046 4....................... October 16, 1996....... Optional.
Airbus Service Bulletin A310-57-2046 07...................... April 2, 1999.......... Optional.
Airbus Service Bulletin A310-57-
Original................ October 16, 1996....... Optional. 2046, Change Notice 4A.
(1) The Director of the Federal Register approved the incorporation by reference of the service information contained in table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 8--New Material Incorporated by Reference
Service Bulletin
Revision
Date
Airbus Mandatory Service Bulletin A310-57-2002.
03 November 28, 2006.
Airbus Mandatory Service Bulletin A310-57-2006.
04 May 21, 2007.
Airbus Mandatory Service Bulletin A310-57-2032.
04 December 1, 2006.
Airbus Mandatory Service Bulletin A310-57-2038.
04 October 19, 2006.
Airbus Mandatory Service Bulletin A310-57-2046.
08 December 1, 2006.
Airbus Service Bulletin A310-57-2038...........
03 September 4, 1998.
Airbus Service Bulletin A310-57-2046...........
07 April 2, 1999.
(2) The Director of the Federal Register previously approved the incorporation by reference of the service information contained in table 9 of this AD on January 20, 1999 (63 FR 69179, December 16, 1998).
Page 27227
Table 9--Material Previously Incorporated by Reference
Service Bulletin
Revision
Date
Airbus Service Bulletin A310-57-2038.... 2........................... January 4, 1996.
Airbus Service Bulletin A310-57-2046.... 4........................... October 16, 1996.
Airbus Service Bulletin A310-57-2046,
Original.................... October 16, 1996.
Change Notice 4A.
(3) For service information identified in this AD, contact
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail account.airworth-eas@airbus.com;
Internet http://www.airbus.com.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at the FAA, call 425-227-1221.
(5) You may also review copies of the service information that is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
FR Doc. 2011-10684 Filed 5-10-11; 8:45 am
BILLING CODE 4910-13-P
