Airworthiness Directives:
Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)
Rules and Regulations
Pages 27227-27232
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
FR Doc No: 2011-10685
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD;
Amendment 39-16687; AD 2011-10-06
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 (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:
DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile]
France 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 50). 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 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.
Following the Extended Design Service Goal activities as part of the Structure Task Group for the Airbus A310 program, EASA [European
Aviation Safety Agency] published AD 2007-0053, which replaced DGAC
France AD F-1992-106-132R7.
Since the issuance of AD 2007-0053R1, the thresholds and the intervals of Airbus Service Bulletins (SB) A310-57-2050 and A310-57- 2064 have been updated.
Consequently, this new [EASA] AD takes over the requirements of paragraphs 1.15 and 1.17 of EASA AD 2007-0053R1, which has been revised accordingly * * * and requires the accomplishment of Airbus
SB A310-57-2048 at revision 01.
The unsafe condition is reduced structural integrity of the wings. The required actions are as follows, depending on airplane configuration:
Cold working of trellis boom drainage holes.
Repetitive detailed or rotating probe inspections for cracking in the drain holes on the lower skin panel in the center wing box between frames 42 and 46 and corrective actions if necessary.
Corrective actions include repairing cracking and contacting the FAA or
EASA for repair and doing the repair.
Repetitive eddy current inspections for cracking of the upper corner angle fitting and the vertical tee fitting at left and right frame 40, and corrective actions if necessary. Corrective actions include repairing, replacing the internal angle fitting, and contacting the FAA or EASA for repair and doing the repair.
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 considered the comment received.
Request To Revise Paragraph Header
An anonymous commenter requested that the paragraph reference in the paragraph header between table 5 and paragraph (k) of the NPRM be revised from ``paragraph (h)'' to ``paragraph (j)''. The commenter believed the intent was to reference paragraph (j) of the NPRM.
We agree with the commenter's request. We have revised the paragraph header between table 5 and paragraph (k) of this AD.
Conclusion
We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the
AD with the change described previously. We determined that this change will not
Page 27228
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 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 137 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 $512,380, or $11,645 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: 2011-10-06 Airbus: Amendment 39-16687. Docket No. FAA-2010-1274;
Directorate Identifier 2010-NM-090-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 15, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310-203, -204, -221, -222,
-304, -322, -324, and -325 airplanes, certificated in any category, 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 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.
Cold Working of Trellis Boom Drainage Holes
(g) For Model A310-203, -204, -222, -304, -322 and -324 airplanes, except airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Within the applicable time specified in Table 1 of this AD, cold work the trellis boom drainage holes, in accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007.
Certain compliance times specified in Table 1 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.6 hours; or long range use, AFT exceeding 3.6 hours.
Table 1--Compliance Times for Paragraph (g) of This AD
Airplanes, as identified in Compliance time (whichever occurs later)
Airbus Mandatory Service
Bulletin A310-57-2048,
Revision 01, dated May 22, 2007
Configuration 01 airplanes.. Prior to the
Within 6 months accumulation of
after the effective 31,800 total flight date of this AD. cycles or 63,600 total flight hours, whichever occurs first.
Page 27229
Configuration 02 airplanes.. Prior to the
Within 6 months accumulation of
after the effective 40,000 total flight date of this AD. cycles or 80,000 total flight hours, whichever occurs first.
Configuration 03 short range Prior to the
Within 6 months airplanes.
accumulation of
after the effective 30,950 total flight date of this AD. cycles or 86,750 total flight hours, whichever occurs first.
Configuration 03 long range Prior to the
Within 6 months airplanes.
accumulation of
after the effective 24,100 total flight date of this AD. cycles or 120,600 total flight hours, whichever occurs first.
(1) Airplanes on which Airbus modification 06130 was done in production.
(2) Airplanes on which Airbus Mandatory Service Bulletin A310- 57-2048 was done in service.
(3) Airplanes on which rework of cracked drain holes was done in accordance with Airbus Mandatory Service Bulletin A310-57-2050.
Inspection of Trellis Boom Drainage Holes
(h) For all airplanes: Within the applicable intervals specified in Table 2 of this AD, perform a detailed or rotating probe inspection for cracking in the drain holes on the lower skin panel in the center wing box between frames 42 and 46, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-57-2050, Revision 02, dated August 27, 2009. Repeat the inspections thereafter at intervals not to exceed the applicable times specified in Table 3 of this AD. Certain compliance times specified in Tables 2 and 3 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.6 hours; or long range use, AFT exceeding 3.6 hours.
Table 2--Compliance Times for Paragraph (h) of This AD
Airplanes, as identified in Compliance time (whichever occurs later)
Airbus Mandatory Service
Bulletin A310-57-2050,
Revision 02, dated August 27, 2009
Configuration 01 airplanes.. Prior to the
Within 1,000 flight accumulation of
cycles or 2,000 17,800 total flight flight hours, cycles or 35,600
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 02 airplanes
Within 32,850 flight Within 1,000 flight on which Airbus Mandatory
cycles or 65,700
cycles or 2,000
Service Bulletin A310-57-
flight hours,
flight hours, 2048 has been done within
whichever occurs
whichever occurs the ``recommended''
first, after
first, after the compliance times specified accomplishing
effective date of in paragraph 1.E.(2),
Airbus Mandatory
this AD.
``Accomplishment
Service Bulletin
Timescale,'' of Airbus
A310-57-2048.
Mandatory Service Bulletin
A310-57-2048, Revision 01, dated May 22, 2007.
Configuration 02 airplanes
Within 8,600 flight Within 1,000 flight on which Airbus Mandatory
cycles or 17,250
cycles or 2,000
Service Bulletin A310-57-
flight hours,
flight hours, 2048 has not been done
whichever occurs
whichever occurs within the ``recommended'' first, after
first, after the compliance times specified accomplishing the
effective date of in paragraph 1.E.(2),
detailed inspection this AD.
``Accomplishment
specified in Airbus
Timescale,'' of Airbus
Mandatory Service
Mandatory Service Bulletin
Bulletin A310-57-
A310-57-2048, Revision 01, 2048; dated May 22, 2007.
OR..................
Within 11,400 flight cycles or 22,800 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus
Mandatory Service
Bulletin A310-57- 2048.
Configuration 03 airplanes.. Prior to the
Within 1,000 flight accumulation of
cycles or 2,000 22,300 total flight flight hours, cycles or 44,550
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 04 airplanes.. Prior to the
Within 1,000 flight accumulation of
cycles or 2,000 41,550 total flight flight hours, cycles or 83,100
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 05 airplanes
Prior to the
Within 1,000 flight on which Airbus Mandatory
accumulation of
cycles or 2,000
Service Bulletin A310-57-
40,000 total flight flight hours, 2048 has been done within
cycles or 80,000
whichever occurs the ``recommended''
total flight hours, first, after the compliance times specified whichever occurs
effective date of in paragraph 1.E.(2),
first.
this AD.
``Accomplishment
Timescale,'' of Airbus
Mandatory Service Bulletin
A310-57-2048, Revision 01, dated May 22, 2007.
Configuration 05 airplanes
Within 10,600 flight Within 1,000 flight on which Airbus Mandatory
cycles or 21,150
cycles or 2,000
Service Bulletin A310-57-
flight hours,
flight hours, 2048 has not been done
whichever occurs
whichever occurs within the ``recommended'' first, after
first, after the compliance times specified accomplishing the
effective date of in paragraph 1.E.(2),
detailed inspection this AD.
``Accomplishment
specified in Airbus
Timescale,'' of Airbus
Mandatory Service
Mandatory Service Bulletin
Bulletin A310-57-
A310-57-2048, Revision 01, 2048; dated May 22, 2007.
OR..................
Within 13,900 flight cycles or 27,800 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus
Mandatory Service
Bulletin A310-57- 2048.
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Configuration 06 short range Prior to the
Within 1,000 flight airplanes.
accumulation of
cycles or 2,800 17,250 total flight flight hours, cycles or 48,400
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 06 long range Prior to the
Within 800 flight airplanes.
accumulation of
cycles or 4,000 13,450 total flight flight hours, cycles or 67,250
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 07 short range Prior to the
Within 1,000 flight airplanes.
accumulation of
cycles or 2,800 32,150 total flight flight hours, cycles or 90,050
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 07 long range Prior to the
Within 800 flight airplanes.
accumulation of
cycles or 4,000 25,050 total flight flight hours, cycles or 125,150
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Configuration 08 short range Prior to the
Within 1,000 flight airplanes on which Airbus
accumulation of
cycles or 2,800
Mandatory Service Bulletin 30,950 total flight flight hours,
A310-57-2048 has been done cycles or 86,750
whichever occurs within the ``recommended'' total flight hours, first, after the compliance times specified whichever occurs
effective date of in paragraph 1.E.(2),
first.
this AD.
``Accomplishment
Timescale,'' of Airbus
Mandatory Service Bulletin
A310-57-2048, Revision 01, dated May 22, 2007.
Configuration 08 short range Within 8,200 flight Within 1,000 flight airplanes on which Airbus
cycles or 23,000
cycles or 2,800
Mandatory Service Bulletin flight hours,
flight hours,
A310-57-2048 has not been
whichever occurs
whichever occurs done within the
first, after
first, after the
``recommended'' compliance accomplishing the
effective date of times specified in
detailed inspection this AD. paragraph 1.E.(2),
specified in Airbus
``Accomplishment
Mandatory Service
Timescale,'' of Airbus
Bulletin A310-57-
Mandatory Service Bulletin 2048;
A310-57-2048, Revision 01, OR.................. dated May 22, 2007.
Within 10,800 flight cycles or 30,300 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus
Mandatory Service
Bulletin A310-57- 2048.
Configuration 08 long range Prior to the
Within 800 flight airplanes on which Airbus
accumulation of
cycles or 4,000
Mandatory Service Bulletin 24,100 total flight flight hours,
A310-57-2048 has been done cycles or 120,600
whichever occurs within the ``recommended'' total flight hours, first, after the compliance times specified whichever occurs
effective date of in paragraph 1.E.(2),
first.
this AD.
``Accomplishment
Timescale,'' of Airbus
Mandatory Service Bulletin
A310-57-2048, Revision 01, dated May 22, 2007.
Configuration 08 long range Within 6,400 flight Within 800 flight airplanes on which Airbus
cycles or 31,950
cycles or 4,000
Mandatory Service Bulletin flight hours,
flight hours,
A310-57-2048 has not been
whichever occurs
whichever occurs done within the
first, after
first, after the
``recommended'' compliance accomplishing the
effective date of times specified in
detailed inspection this AD. paragraph 1.E.(2),
specified in Airbus
``Accomplishment
Mandatory Service
Timescale,'' of Airbus
Bulletin A310-57-
Mandatory Service Bulletin 2048;
A310-57-2048, Revision 01, OR.................. dated May 22, 2007.
Within 8,400 flight cycles or 42,150 flight hours, whichever occurs first, after accomplishing the rotating probe inspection specified in Airbus
Mandatory Service
Bulletin A310-57- 2048.
Table 3--Repetitive Intervals for Paragraph (h) of This AD, Depending on
Most Recent Inspection Type
Airplanes, as identified in
Type of
Airbus Mandatory Service
inspection done
Bulletin A310-57-2050,
during most
Repetitive interval
Revision 02, dated August 27,
recent
(not to exceed) 2009
inspection
Configuration 01 and 02
Detailed
8,600 flight cycles airplanes.
inspection.
or 17,250 flight hours, whichever occurs first.
Rotating probe
11,400 flight cycles inspection.
or 22,800 flight hours, whichever occurs first.
Configurations 03, 04, and 05 Detailed
10,600 flight cycles airplanes.
inspection.
or 21,150 flight hours, whichever occurs first.
Rotating probe
13,900 flight cycles inspection.
or 27,800 flight hours, whichever occurs first.
Configurations 06, 07, and 08 Detailed
8,200 flight cycles short range airplanes.
inspection.
or 23,000 flight hours, whichever occurs first.
Rotating probe
10,800 flight cycles inspection.
or 30,300 flight hours, whichever occurs first.
Configurations 06, 07, and 08 Detailed
6,400 flight cycles long range airplanes.
inspection.
or 31,950 flight hours, whichever occurs first.
Page 27231
Rotating probe
8,400 flight cycles inspection.
or 42,150 flight hours, whichever occurs first.
Corrective Actions for Paragraph (h) of This AD
(i) If any cracking is found during any inspection required by paragraph (h) of this AD, before further flight, do all applicable corrective actions, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2050,
Revision 02, dated August 27, 2009; except where the service bulletin specifies to contact Airbus, before further flight, repair in accordance with a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate, or European Aviation Safety Agency (EASA) (or its delegated agent).
Inspection of Fuselage Frame 40 Upper Corner Fitting
(j) For all airplanes: Within the applicable time specified in
Table 4 of this AD, perform an eddy current inspection for cracking of the upper corner fitting at left and right frame 40, in accordance with the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A310-57-2064, Revision 02, dated December 21, 2007.
Repeat the inspections thereafter at intervals not to exceed the applicable times specified in Table 5 of this AD. Certain compliance times specified in Tables 4 and 5 of this AD are applicable to short range use, average flight time (AFT) equal to or less than 3.23 hours; or long range use, AFT exceeding 3.23 hours.
Table 4--Compliance Times for Paragraph (j) of This AD
Airplane configurations
Compliance time identified in Airbus
(whichever occurs later)
Mandatory Service Bulletin
A310-57-2064, Revision 02, dated December 21, 2007
Model A310-203, -204, -221, Prior to the
Within 1,300 flight and -222 airplanes
accumulation of
cycles or 2,700 identified as Configuration 15,100 total flight flight hours, 01.
cycles or 30,300
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Model A310-203, -204, -221, Prior to the
Within 1,300 flight and -222 airplanes
accumulation of
cycles or 2,700 identified as
21,400 total flight flight hours,
Configurations 02 and 03.
cycles or 42,800
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Model A310-304, -322, -324, Prior to the
Within 600 flight and -325 short range
accumulation of
cycles or 1,800 airplanes identified as
14,700 total flight flight hours,
Configuration 01.
cycles or 41,300
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Model A310-304, -322, -324, Prior to the
Within 600 flight and -325 short range
accumulation of
cycles or 1,800 airplanes identified as
20,700 total flight flight hours,
Configurations 02 and 03.
cycles or 58,300
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Model A310-304, -322, -324, Prior to the
Within 500 flight and -325 long range
accumulation of
cycles or 2,650 airplanes identified as
12,800 total flight flight hours,
Configuration 01.
cycles or 64,000
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Model A310-304, -322, -324, Prior to the
Within 500 flight and -325 long range
accumulation of
cycles or 2,650 airplanes identified as
18,000 total flight flight hours,
Configurations 02 and 03.
cycles or 90,400
whichever occurs total flight hours, first, after the whichever occurs
effective date of first.
this AD.
Table 5--Repetitive Intervals for Paragraph (j) of This AD
Repetitive interval (not to
Airplanes
exceed)
Model A310-203, -204, -221, and -222
8,750 flight cycles or 17,550 airplanes.
flight hours, whichever occurs first.
Model A310-304, -322, -324, and -325
5,800 flight cycles or 16,300 short range airplanes.
flight hours, whichever occurs first.
Model A310-304, -322, -324, and -325
4,800 flight cycles or 24,050 long range airplanes.
flight hours, whichever occurs first.
Corrective Actions for Paragraph (j) of This AD
(k) If, during any inspection required by paragraph (j) of this
AD, any crack is found, prior to further flight, do all applicable corrective actions, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A310-57-2064,
Revision 02, dated December 21, 2007; except where the service bulletin specifies to contact Airbus, 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).
Credit for Actions Accomplished in Accordance With Previous Service
Information
(l) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2048, dated April 23, 1990, are considered acceptable for compliance with the corresponding action specified in paragraph (g) of this AD.
(m) Actions accomplished before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2050, dated April 23, 1990; or Airbus Mandatory Service Bulletin A310-57-2050,
Revision 01, dated May 22, 2007; are considered acceptable for compliance with the corresponding actions specified in paragraphs
(h) and (i) of this AD.
(n) Actions done before the effective date of this AD in accordance with Airbus Service Bulletin A310-57-2064, dated August 24, 1995; or, Airbus Mandatory Service Bulletin A310-57-2064,
Revision 01, dated January 5, 2001; are acceptable for compliance with the corresponding actions specified in paragraphs (j) and (k) of this AD.
Page 27232
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information as follows: No Differences.
Other FAA AD Provisions
(o) 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, or if sending information directly to the International Branch, send it to ATTN: 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.
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.
(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
(p) Refer to MCAI EASA Airworthiness Directive 2009-0057, dated
March 13, 2009, and the service bulletins listed in Table 6 of this
AD, for related information.
Table 6--Service Information
Service Bulletin
Revision
Date
Airbus Mandatory Service
01 May 22, 2007.
Bulletin A310-57-2048.
Airbus Mandatory Service
02 August 27, 2009.
Bulletin A310-57-2050.
Airbus Mandatory Service
02 December 21, 2007.
Bulletin A310-57-2064.
Material Incorporated by Reference
(q) You must use the applicable service information contained in
Table 7 of this AD to do the actions required by this AD, unless the
AD specifies otherwise.
Table 7--All Material Incorporated by Reference
Service Bulletin
Revision
Date
Airbus Mandatory Service
01 May 22, 2007.
Bulletin A310-57-2048.
Airbus Mandatory Service
02 August 27, 2009.
Bulletin A310-57-2050, excluding Appendix 01.
Airbus Mandatory Service
02 December 21, 2007.
Bulletin A310-57-2064, excluding Appendix 1.
(1) The Director of the Federal Register approved the incorporation by reference of the service information under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) 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.
(3) 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.
(4) 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. 2011-10685 Filed 5-10-11; 8:45 am
BILLING CODE 4910-13-P
