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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration (FAA), DOT.
 ACTION: Notice of proposed rulemaking (NPRM).
 SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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 Générale 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. The proposed AD would require actions that are intended to address the unsafe condition described in the MCAI.
 DATES: We must receive comments on this proposed AD by February 17, 2011.
 ADDRESSES: You may send comments by any of the following methods: *Federal eRulemaking Portal:*
                         Go to 
                        *http://www.regulations.gov.*
                         Follow the instructions for submitting comments.
                    *Fax:*
                         (202) 493-2251.
                    *Mail:*
                         U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC 20590.
                    *Hand Delivery:*
                         U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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.*
                         You may review copies of the referenced 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. 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 this proposed AD, 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.
 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: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the 
                    **ADDRESSES**
                     section. Include “Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to 
                    *http://www.regulations.gov,*
                     including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2009-0057, dated March 13, 2009 (referred to after this as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states: DGAC [Direction Générale de l'Aviation Civile] France AD 1992-106-132(B) original 
                        ( print page 51)
                        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 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. Other Relevant Rulemaking We are considering issuing three other NPRMs related to this NPRM: Directorate Identifier 2010-NM-092-AD. That NPRM proposes to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16, 1998), to continue to require certain actions specified in that AD. However, that NPRM does not restate paragraphs (p) and (r) of AD 98-26-01. Instead, certain requirements of paragraphs (p) and (r) of that AD are included in this NPRM, Directorate Identifier 2010-NM-090-AD.
                Directorate Identifiers 2010-NM-089-AD and 2010-NM-091-AD. Both of these NPRMs include the requirements of certain other paragraphs of AD 98-26-01. Relevant Service Information Airbus has issued the service bulletins listed in the table that follows: Table—Service Information
Service bulletin
Revision
DateAirbus Mandatory Service Bulletin A310-57-2048
01
May 22, 2007.Airbus Mandatory Service Bulletin A310-57-2050, including Appendix 01
02
August 27, 2009.Airbus Mandatory Service Bulletin A310-57-2064, including Appendix 1
02
December 21, 2007.
 The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. 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 proposed different actions in this AD from those in the MCAI in order to follow FAA policies. Any such differences are highlighted in a Note within the proposed AD. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 44 products of U.S. registry. We also estimate that it would take about 137 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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 
                    ( print page 52)
                    this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Incorporation by reference
Safety
 The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: Authority:
                        49 U.S.C. 106(g), 40113, 44701. § 39.13
  2. The FAA amends § 39.13 by adding the following new AD: **Airbus:**
                                 Docket No. FAA-2010-1274; Directorate Identifier 2010-NM-090-AD. Comments Due Date (a) We must receive comments by February 17, 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 Générale 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. * * *. 
 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 Airbus mandatory service bulletin A310-57-2048, revision 01, dated May 22, 2007
Compliance time (whichever occurs later)Configuration 01 airplanes
Prior to the accumulation of 31,800 total flight cycles or 63,600 total flight hours, whichever occurs first
Within 6 months after the effective date of this AD.Configuration 02 airplanes
Prior to the accumulation of 40,000 total flight cycles or 80,000 total flight hours, whichever occurs first
Within 6 months after the effective date of this AD.Configuration 03 short range airplanes
Prior to the accumulation of 30,950 total flight cycles or 86,750 total flight hours, whichever occurs first
Within 6 months after the effective date of this AD.Configuration 03 long range airplanes
Prior to the accumulation of 24,100 total flight cycles or 120,600 total flight hours, whichever occurs first
Within 6 months after the effective date of this AD.
 (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 Airbus mandatory service bulletin A310-57-2050, revision 02, dated August 27, 2009
Compliance time (whichever occurs later)Configuration 01 airplanes
Prior to the accumulation of 17,800 total flight cycles or 35,600 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.( print page 53)Airplanes, as identified in Airbus mandatory service bulletin A310-57-2050, revision 02, dated August 27, 2009
Compliance time (whichever occurs later)Configuration 02 airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Within 32,850 flight cycles or 65,700 flight hours, whichever occurs first, after accomplishing Airbus Mandatory Service Bulletin A310-57-2048
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 02 airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has not been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Within 8,600 flight cycles or 17,250 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310-57-2048;
                                     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
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 03 airplanes
Prior to the accumulation of 22,300 total flight cycles or 44,550 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 04 airplanes
Prior to the accumulation of 41,550 total flight cycles or 83,100 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 05 airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Prior to the accumulation of 40,000 total flight cycles or 80,000 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 05 airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has not been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Within 10,600 flight cycles or 21,150 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310-57-2048;
                                     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
Within 1,000 flight cycles or 2,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 06 short range airplanes
Prior to the accumulation of 17,250 total flight cycles or 48,400 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD.Configuration 06 long range airplanes
Prior to the accumulation of 13,450 total flight cycles or 67,250 total flight hours, whichever occurs first
Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 07 short range airplanes
Prior to the accumulation of 32,150 total flight cycles or 90,050 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD.Configuration 07 long range airplanes
Prior to the accumulation of 25,050 total flight cycles or 125,150 total flight hours, whichever occurs first
Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 08 short range airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Prior to the accumulation of 30,950 total flight cycles or 86,750 total flight hours, whichever occurs first
Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD.( print page 54)Airplanes, as identified in Airbus mandatory service bulletin A310-57-2050, revision 02, dated August 27, 2009
Compliance time (whichever occurs later)Configuration 08 short range airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has not been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Within 8,200 flight cycles or 23,000 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310-57-2048;
                                     OR 
                                     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
Within 1,000 flight cycles or 2,800 flight hours, whichever occurs first, after the effective date of this AD.Configuration 08 long range airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Prior to the accumulation of 24,100 total flight cycles or 120,600 total flight hours, whichever occurs first
Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD.Configuration 08 long range airplanes on which Airbus Mandatory Service Bulletin A310-57-2048 has not been done within the “recommended” compliance times specified in paragraph 1.E.(2), “Accomplishment Timescale,” of Airbus Mandatory Service Bulletin A310-57-2048, Revision 01, dated May 22, 2007
Within 6,400 flight cycles or 31,950 flight hours, whichever occurs first, after accomplishing the detailed inspection specified in Airbus Mandatory Service Bulletin A310-57-2048;
                                     OR 
                                     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
Within 800 flight cycles or 4,000 flight hours, whichever occurs first, after the effective date of this AD.
 Table 3—Repetitive Intervals for Paragraph (h) of This AD, Depending on Most Recent Inspection Type
Airplanes, as identified in Airbus
                                     mandatory service bulletin A310-57-2050, revision 02, dated August 27, 2009
Type of inspection done during most recent inspection
Repetitive interval 
                                     (not to exceed)Configuration 01 and 02 airplanes
Detailed inspection
8,600 flight cycles or 17,250 flight hours, whichever occurs first.Rotating probe inspection
11,400 flight cycles or 22,800 flight hours, whichever occurs first.Configurations 03, 04, and 05 airplanes
Detailed inspection
10,600 flight cycles or 21,150 flight hours, whichever occurs first.Rotating probe inspection
13,900 flight cycles or 27,800 flight hours, whichever occurs first.Configurations 06, 07, and 08 short range airplanes
Detailed inspection
8,200 flight cycles or 23,000 flight hours, whichever occurs first.Rotating probe inspection
10,800 flight cycles or 30,300 flight hours, whichever occurs first.Configurations 06, 07, and 08 long range airplanes
Detailed inspection
6,400 flight cycles or 31,950 flight hours, whichever occurs first.Rotating probe inspection
8,400 flight cycles 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 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 identified in Airbus mandatory service bulletin A310-57-2064, revision 02, dated December 21, 2007
Compliance time (whichever occurs later)Model A310-203, -204, -221, and -222 airplanes identified as Configuration 01
Prior to the accumulation of 15,100 total flight cycles or 30,300 total flight hours, whichever occurs first
Within 1,300 flight cycles or 2,700 flight hours, whichever occurs first, after the effective date of this AD.Model A310-203, -204, -221, and -222 airplanes identified as Configurations 02 and 03
Prior to the accumulation of 21,400 total flight cycles or 42,800 total flight hours, whichever occurs first
Within 1,300 flight cycles or 2,700 flight hours, whichever occurs first, after the effective date of this AD.Model A310-304, -322, -324, and -325 short range airplanes identified as Configuration 01
Prior to the accumulation of 14,700 total flight cycles or 41,300 total flight hours, whichever occurs first
Within 600 flight cycles or 1,800 flight hours, whichever occurs first, after the effective date of this AD.Model A310-304, -322, -324, and -325 short range airplanes identified as Configurations 02 and 03
Prior to the accumulation of 20,700 total flight cycles or 58,300 total flight hours, whichever occurs first
Within 600 flight cycles or 1,800 flight hours, whichever occurs first, after the effective date of this AD.Model A310-304, -322, -324, and -325 long range airplanes identified as Configuration 01
Prior to the accumulation of 12,800 total flight cycles or 64,000 total flight hours, whichever occurs first
Within 500 flight cycles or 2,650 flight hours, whichever occurs first, after the effective date of this AD.Model A310-304, -322, -324, and -325 long range airplanes identified as Configurations 02 and 03
Prior to the accumulation of 18,000 total flight cycles or 90,400 total flight hours, whichever occurs first
Within 500 flight cycles or 2,650 flight hours, whichever occurs first, after the effective date of this AD.
 Table 5—Repetitive Intervals for Paragraph (j) of This AD
Airplanes
Repetitive interval 
                                     (not to exceed)Model A310-203, -204, -221, and -222 airplanes
8,750 flight cycles or 17,550 flight hours, whichever occurs first.Model A310-304, -322, -324, and -325 short range airplanes
5,800 flight cycles or 16,300 flight hours, whichever occurs first.Model A310-304, -322, -324, and -325 long range airplanes
4,800 flight cycles or 24,050 flight hours, whichever occurs first.
 Corrective Actions for Paragraph (h) 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 Revision 01, dated January 5, 2001; are acceptable for compliance with the corresponding actions specified in paragraphs (j) and (k) of this AD. 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. Send information 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. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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. (3) 
                                *Reporting Requirements:*
                                 For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 
                                *et seq.*), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120-0056. 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
DateAirbus Mandatory Service Bulletin A310-57-2048
01
May 22, 2007.Airbus Mandatory Service Bulletin A31-57-2050
02
August 27, 2009.( print page 56)Airbus Mandatory Service Bulletin A310-57-2064
02
December 21, 2007.
 Issued in Renton, Washington on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.


[FR Doc. 2010-32992 Filed 12-30-10; 8:45 am] BILLING CODE 4910-13-P