Airworthiness Directives: Airbus Model A300 B2 and A300 B4 Series Airplanes et al.
Federal Register: November 18, 2009 (Volume 74, Number 221)
Proposed Rules
Page 59483-59488
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
DOCID:fr18no09-13
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration 14 CFR Part 39
Docket No. FAA-2009-1067; Directorate Identifier 2009-NM-071-AD
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series
Airplanes; A300 B4-600, B4-600R, and F4-600R Series Airplanes; and
Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series
Airplanes)
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 that would supersede an existing AD. 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:
Following the occurrence of cracks on the MLG [main landing gear] rib 5 RH [right-hand] and LH [left-hand] attachment fitting lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) [parallel to part of FAA AD 2006-12- 13] was issued to require repetitive inspections and, as terminating action * * *[.]
Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300-600 type aeroplanes on which the terminating action * * * [was] embodied. This condition, if not corrected, could affect the structural integrity of those aeroplanes.
* * * * *
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 January 4, 2010.
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 or 425-227-1152.
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-2009-1067;
Directorate Identifier 2009-NM-071-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 have lengthened the 30-day comment period for proposed ADs that address MCAI originated by aviation authorities of other countries to provide adequate time for interested parties to submit comments. The comment period for these proposed ADs is now typically 45 days, which is consistent with the comment period for domestic transport ADs.
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
On May 31, 2006, we issued AD 2006-12-13, Amendment 39-14639 (71 FR 33994, June 13, 2006). That AD required actions intended to address an unsafe condition on the products listed above.
Since we issued AD 2006-12-13, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European
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Community, has issued EASA Airworthiness Directive 2009-0081, dated
April 6, 2009 (referred to after this as ``the MCAI''), to correct an unsafe condition for the specified products. The MCAI states:
Following the occurrence of cracks on the MLG [main landing gear] rib 5 RH [right-hand] and LH [left-hand] attachment fitting lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) [parallel to part of FAA AD 2006-12- 13] was issued to require repetitive inspections and, as terminating action, the embodiment of Airbus Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300-600 type aeroplanes on which the terminating action SBs were embodied.
This condition, if not corrected, could affect the structural integrity of those aeroplanes.
To address and correct this condition, Airbus developed an inspection programme for aeroplanes modified in accordance with SB
A300-57-0235 or A300-57-6088. This inspection programme was required to be implemented by DGAC France AD F-2005-113, original issue and later revision 1 [parallel to part of FAA AD 2006-12-13].
A new EASA AD 2008-0111, superseding DGAC France AD F-2005- 113R1, was issued to reduce the applicability. For aeroplanes already compliant with DGAC France AD F-2005-113R1, no further action was required.
Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection programmes of SB A300-57A0246 and SB A300-57A6101 to introduce repetitive inspections including a new inspection technique for holes 47 and 54 and to reduce inspections threshold and intervals from 700 Flight Cycles (FC) to 400 FC until a revised terminating action is made available.
Required actions include contacting Airbus for repair instructions, if necessary, and doing the repair. You may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A300-57A0246, including Appendixes 1 and 2, Revision 03, dated March 11, 2009; and
Mandatory Service Bulletin A300-57A6101, including Appendixes 1 and 2,
Revision 03, dated March 11, 2009. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI.
Changes to Existing AD
This proposed AD would retain certain requirements of AD 2006-12- 13. Since AD 2006-12-13 was issued, the AD format has been revised, and certain paragraphs have been rearranged. As a result, the corresponding paragraph identifiers have changed in this proposed AD, as listed in the following table:
Revised Paragraph Identifiers
Corresponding requirement in
Requirement in AD 2006-12-13
this proposed AD
Paragraph (e)........................... paragraph (f).
Paragraph (f)........................... paragraph (g).
Paragraph (g)........................... paragraph (h).
Paragraph (h)........................... paragraph (i).
Paragraph (i)........................... paragraph (j).
Paragraph (j)........................... paragraph (k).
Paragraph (k)........................... paragraph (l).
Paragraph (l)........................... paragraph (m).
We have also revised paragraph (i) of this NPRM to clarify the compliance times for airplanes that have not had the modification required by paragraph (i) of this NPRM accomplished before July 18, 2006. We added the phrase, ``Except as required by paragraph (l) of this AD,'' to paragraph (i) of this NPRM. We have determined that this change will neither increase the economic burden on any operator nor increase the scope of the AD.
We have also revised paragraph (o) of this AD to specify that no reporting is required.
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 155 products of U.S. registry.
The actions that are required by AD 2006-12-13 and retained in this proposed AD take about 76 work-hours per product, at an average labor rate of $80 per work hour. Required parts cost about $10,270 per product. Based on these figures, the estimated cost of the currently required actions is $16,350 per product.
We estimate that it would take about 3 work-hours per product to comply with the new basic requirements of this proposed AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $37,200, or $240 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,
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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 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.
Sec. 39.13 [Amended] 2. The FAA amends Sec. 39.13 by removing Amendment 39-14639 (71 FR 33994, June 13, 2006) and adding the following new AD:
Airbus: Docket No. FAA-2009-1067; Directorate Identifier 2009-NM- 071-AD.
Comments Due Date
(a) We must receive comments by January 4, 2010.
Affected ADs
(b) The proposed AD supersedes AD 2006-12-13, Amendment 39- 14639.
Applicability
(c) This AD applies to the airplanes, certificated in any category, identified in paragraph (c)(1) and (c)(2) of this AD; except airplanes on which Airbus Modification 11912 or 11932 has been installed.
(1) Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and
B4-203 airplanes.
(2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R,
B4-622R, and F4-605R airplanes.
Subject
(d) Air Transport Association (ATA) of America Code 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI) states:
Following the occurrence of cracks on the MLG [main landing gear] rib 5 RH [right-hand] and LH [left-hand] attachment fitting lower flanges, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation
Civile] France AD 2003-318(B) [parallel to part of FAA AD 2006-12- 13] was issued to require repetitive inspections and, as terminating action, the embodiment of Airbus Service Bulletins (SB) A300-57-0235 and A300-57-6088 * * *.
Subsequently, new cases of cracks were discovered during scheduled maintenance checks by operators of A300B4 and A300-600 type aeroplanes on which the terminating action SB's were embodied.
This condition, if not corrected, could affect the structural integrity of those aeroplanes.
To address and correct this condition, Airbus developed an inspection programme for aeroplanes modified in accordance with SB
A300-57-0235 or A300-57-6088. This inspection programme was required to be implemented by DGAC France AD F-2005-113, original issue and later revision 1 [parallel to part of FAA AD 2006-12-13].
A new EASA [European Aviation Safety Agency] AD 2008-0111, superseding DGAC France AD F-2005-113R1, was issued to reduce the applicability. For aeroplanes already compliant with DGAC France AD
F-2005-113R1, no further action was required.
Since EASA AD 2008-0111 issuance, Airbus reviewed the inspection programmes of SB A300-57A0246 and SB A300-57A6101 to introduce repetitive inspections including a new inspection technique for holes 47 and 54 and to reduce inspections threshold and intervals from 700 Flight Cycles (FC) to 400 FC until a revised terminating action is made available.
Required actions include contacting Airbus for repair instructions, if necessary, and doing the repair.
Restatement of Requirements of AD 2000-05-07:
(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.
Repetitive Inspections
(g) Perform a detailed inspection and a high-frequency eddy current (HFEC) inspection to detect cracks in Gear Rib 5 of the main landing gear (MLG) attachment fittings at the lower flange, in accordance with the Accomplishment Instructions of any applicable service bulletin listed in Table 1 and Table 2 of this AD, at the time specified in paragraph (g)(1) or (g)(2) of this AD. After April 12, 2000 (the effective date of AD 2000-05-07, amendment 39-11616), only the service bulletins listed in Table 2 of this AD may be used.
Repeat the inspections thereafter at intervals not to exceed 1,500 flight cycles, until the actions specified in paragraph (i), (j), or
(l) of this AD are accomplished.
Table 1--Revision 01 of Service Bulletins
Airbus Service Bulletin-- Revision
Model--
level--
Dated--
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6087............
01 March 11, 1998.
B4-605R, B4-622R, F4-605R, F4-622R, and A300 C4-605R Variant F airplanes.
A300 B2 and A300 B4 series airplanes. A300-57-0234............
01 March 11, 1998.
Table 2--Other Revisions of Service Bulletins
Airbus Service
Model--
Bulletin--
Revision level--
Dated--
A300 B4-601, B4-603, B4-620, B4-
A300-57A6087......... 02, including
June 24, 1999. 622, B4-605R, B4-622R, F4-605R,
Appendix 01.
F4-622R, and A300 C4-605R Variant
F airplanes. 03, including
May 19, 2000.
Appendix 01. 04, including
February 19, 2002.
Appendix 01.
A300 B2 and A300 B4 series
A300-57A0234......... 02.................. June 24, 1999. airplanes. 03, including
September 2, 1999.
Appendix 01. 04, including
May 19, 2000.
Appendix 01. 05, including
February 19, 2002.
Appendix 01.
(1) For airplanes that have accumulated 20,000 or more total flight cycles as of March 9, 1998 (the effective date of AD 98-03- 06, amendment 39-10298): Inspect within 500 flight cycles after
March 9, 1998.
(2) For airplanes that have accumulated less than 20,000 total flight cycles as of March 9, 1998: Inspect prior to the accumulation of 18,000 total flight cycles, or within 1,500 flight cycles after
March 9, 1998, whichever occurs later.
Note 1: For the purposes of this AD, a detailed inspection is defined as: ``An
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intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.''
Note 2: Accomplishment of the initial detailed and HFEC inspections in accordance with Airbus Service Bulletin A300-57A0234 or A300-57A6087, both dated August 5, 1997, as applicable, is considered acceptable for compliance with the initial inspections required by paragraph (g) of this AD.
Repair for Any Crack Found During Inspections Required by Paragraph (g) of This AD
(h) If any crack is detected during any inspection required by paragraph (g) of this AD, prior to further flight, accomplish the requirements of paragraph (h)(1) or (h)(2) of this AD, as applicable.
(1) If a crack is detected at one hole only, and the crack does not extend out of the spotface of the hole, repair in accordance with the Accomplishment Instructions of the applicable service bulletin in Table 2 of this AD.
(2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA, or the
European Aviation Safety Agency (EASA) (or its delegated agent).
Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD
(i) Except as required by paragraph (l) of this AD, prior to the accumulation of 21,000 total flight cycles, or within 2 years after
October 20, 1999 (the effective date of AD 99-19-26, amendment 39- 11313), whichever occurs later: Modify Gear Rib 5 of the MLG attachment fittings at the lower flange in accordance with the
Accomplishment Instructions of the applicable service bulletin in
Table 3 of this AD. After July 18, 2006 (the effective date of AD 2006-12-13), only Revision 04 of Airbus Service Bulletin A300-57- 6088, and Revisions 04 and 05 of Airbus Service Bulletin A300-57- 0235 may be used. Accomplishment of this modification constitutes terminating action for the repetitive inspection requirements of paragraphs (g) and (j) of this AD.
Table 3--Service Bulletins for Terminating Modification
Airbus Service
Model--
Bulletin--
Revision level--
Dated--
A300 B4-601, B4-603, B4-620, B4-
A300-57-6088......... 01, including
February 1, 1999. 622, B4-605R, B4-622R, F4-605R,
Appendix 01.
F4-622R, and A300 C4-605R Variant
F airplanes. 02.................. September 5, 2002 04.................. December 3, 2003.
A300 B2 and A300 B4 series
A300-57-0235......... 01, including
February 1, 1999. airplanes.
Appendix 01. 03.................. September 5, 2002 04.................. March 13, 2003. 05.................. December 3, 2003.
Note 3: Accomplishment of the modification required by paragraph
(i) of this AD prior to April 12, 2000, in accordance with Airbus
Service Bulletin A300-57-6088 or A300-57-0235, both dated August 5, 1998; as applicable; is acceptable for compliance with the requirements of that paragraph.
Restatement of Requirements of AD 2006-12-13:
Additional Repetitive Inspections
(j) For airplanes on which the modification specified in paragraph (i) or (l) of this AD has not been done before July 18, 2006 (the effective date of AD 2006-12-13, amendment 39-14639), perform a detailed and an HFEC inspection to detect cracks of the lower flange of Gear Rib 5 of the MLG at holes 43, 47, 48, 49, 50, 52, and 54, in accordance with the applicable service bulletin listed in Table 4 of this AD. Perform the inspections at the applicable time specified in paragraph (j)(1), (j)(2), (j)(3), or
(j(4) of this AD. Repeat the inspections thereafter at intervals not to exceed 700 flight cycles until the terminating modification required by paragraph (l) of this AD is accomplished. Accomplishment of the inspections per paragraph (j) of this AD terminates the inspection requirements of paragraph (g) of this AD.
Table 4--Service Bulletins for Repetitive Inspections
Airbus Service
Model--
Bulletin--
Revision level--
Dated--
A300 B4-601, B4-603, B4-620, B4-
A300-57A6087......... 04, including
February 19, 2002. 622, B4-605R, B4-622R, F4-605R,
Appendix 01.
F4-622R, and C4-605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, A300-57A0234......... 05, including
February 19, 2002.
B4-2C, B4-103, and B4-203
Appendix 01. airplanes.
(1) For Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes; Model A300 B4-601, B4-603, B4-620, B4-622, B4- 605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; and Model C4-605R Variant F airplanes that have accumulated 18,000 or more total flight cycles as of July 18, 2006: Within 700 flight cycles after July 18, 2006.
(2) For Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 airplanes that have accumulated less than 18,000 total flight cycles as of
July 18, 2006: Prior to the accumulation of 18,000 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later.
(3) For Model A300 B4-2C, B4-103, and B4-203 airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 14,500 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later.
(4) For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4- 622R, F4-605R, F4-622R, and C4-605R Variant F airplanes that have accumulated less than 18,000 total flight cycles as of July 18, 2006: Prior to the accumulation of 11,600 total flight cycles, or within 700 flight cycles after July 18, 2006, whichever occurs later.
Crack Repair
(k) If any crack is detected during any inspection required by paragraph (j) of this AD, prior to further flight, accomplish the requirements of paragraphs (k)(1) and (k)(2) of this AD, as applicable.
(1) If a crack is detected at only one hole, and the crack does not extend out of the
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spotface of the hole, repair in accordance with Airbus Service
Bulletin A300-57A0234, Revision 05, including Appendix 01, dated
February 19, 2002 (for Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- 2C, B4-103, and B4-203 airplanes); or A300-57A6087, Revision 04, including Appendix 01, dated February 19, 2002 (for Model A300 B4- 601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and
C4-605R airplanes); as applicable.
(2) If a crack is detected at more than one hole, or if any crack at any hole extends out of the spotface of the hole, repair in accordance with a method approved by the Manager, International
Branch, ANM-116, or the EASA (or its delegated agent).
Terminating Modification for Repetitive Inspections Required by
Paragraphs (g) and (j) of This AD for Certain Airplanes
(l) For airplanes on which the terminating modification in paragraph (i) of this AD has not been accomplished before July 18, 2006: At the earlier of the times specified in paragraphs (l)(1) and
(l)(2) of this AD, modify Gear Rib 5 of the MLG attachment fittings at the lower flange. Except as provided by paragraph (m) of this AD, do the modification in accordance with the applicable service bulletin in Table 5 of this AD. This action terminates the repetitive inspections requirements of paragraphs (g) and (j) of this AD.
(1) Prior to the accumulation of 21,000 total flight cycles, or within 2 years after October 20, 1999, whichever is later.
(2) Within 16 months after July 18, 2006.
Table 5--Service Bulletins for Terminating Modification
Airbus Service Bulletin-- Revision
Model--
level--
Dated--
A300 B4-601, B4-603, B4-620, B4-622, A300-57-6088............
04 December 3, 2003.
B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes.
A300 B2-1A, B2-1C, B2K-3C, B2-203, B4- A300-57-0235............
04 March 13, 2003. 2C, B4-103, and B4-203 airplanes. 05 December 3, 2003.
(m) Where the applicable service bulletin in paragraph (l) of this AD specifies to contact Airbus for modification instructions; or if there is a previously installed repair at any of the affected fastener holes; or if a crack is found when accomplishing the modification: Prior to further flight, modify in accordance with a method approved by the Manager, International Branch, ANM-116, or the EASA (or its delegated agent).
Actions Accomplished per Previous Issues of Service Bulletins
(n) Actions accomplished before July 18, 2006, in accordance with the service bulletins listed in Table 6 of this AD, are considered acceptable for compliance with the corresponding action specified in paragraphs (g) through (m) of this AD.
Table 6--Previous Issues of Service Bulletins
Airbus Service Bulletin--
Revision level--
Dated--
A300-57-0235............................ 02, including Appendix 01...... September 27, 1999. 03............................. September 5, 2002.
A300-57-6088............................ 02............................. September 5, 2000. 03............................. March 13, 2003.
No Reporting
(o) Although the service bulletins identified in Tables 1, 2, 3, 4, 5, and 6 of this AD specify to submit certain information to the manufacturer, this AD does not include such a requirement.
New Requirements of This AD
(p) Unless already done, do the following actions.
(1) At the applicable time specified in paragraph (p)(2) of this
AD, perform a detailed inspection for cracking at the locations specified in paragraphs (p)(1)(i), (p)(1)(ii), and (p)(1)(iii) of this AD, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A300-57A0246, Revision 03, dated
March 11, 2009; or Airbus Mandatory Service Bulletin A300-57A6101,
Revision 03, dated March 11, 2009, as applicable.
(i) The bottom flange and vertical web in the area between the wing rear spar/gear rib 5 attachment and the forward reaction-rod pick-up lug.
(ii) On the inboard side, around the fastener holes at locations 43, 47 to 50, 52, and 54.
(iii) On the outboard side, the lower flange, the vertical web and around the fastener holes at locations 43, 47 to 50, 52 and 54.
(2) Do the inspection required by paragraph (p)(1) of this AD at the later of the times in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD.
(i) Within 400 flight cycles after the accomplishment of the actions required by paragraph (i) or (l) of this AD, as applicable.
(ii) Within 400 flight cycles or 4 months after the effective date of this AD, whichever occurs first.
(3) If no cracking is detected during the inspection required by paragraph (p)(1) of this AD, before further flight, perform a fluorescent penetrant inspection (FPI) at holes location 47 and 54, in the right-hand and left-hand MLG rib 5 attachment fitting lower flange, in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A300-57A0246, Revision 03, dated March 11, 2009; or Airbus Mandatory Service Bulletin A300-57A6101,
Revision 03, dated March 11, 2009; as applicable.
(4) Thereafter, at intervals not to exceed 400 flight cycles, repeat the detailed and FPI inspections, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A300-57A0246, Revision 03, dated March 11, 2009; or Airbus Mandatory
Service Bulletin A300-57A6101, Revision 03, dated March 11, 2009; as applicable.
(5) If any crack is detected during any of the inspections required by paragraphs (p)(1), (p)(3), and (p)(4) of this AD, before further flight, contact Airbus for a repair solution, and do the repair.
FAA AD Differences
Note 4: This AD differs from the MCAI and/or service information as follows: No differences.
Other FAA AD Provisions
(q) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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
Page 59488
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.
Related Information
(r) Refer to MCAI EASA Airworthiness Directive 2009-0081, dated
April 6, 2009, and the service information in Table 7 of this AD.
Table 7--Service Information
Airbus Service Information--
Revision level--
Dated--
Service Bulletin A300-57-0235........... 04............................. March 13, 2003. 05............................. December 3, 2003.
Service Bulletin A300-57-6088........... 04............................. December 3, 2003.
Service Bulletin A300-57A0234........... 02............................. June 24, 1999. 03, including Appendix 01...... September 2, 1999. 04, including Appendix 01...... May 19, 2000. 05, including Appendix 01...... February 19, 2002.
Service Bulletin A300-57A6087........... 02, including Appendix 01...... June 24, 1999. 03, including Appendix 01...... May 19, 2000. 04, including Appendix 01...... February 19, 2002.
Mandatory Service Bulletin A300-57A0246. 03............................. March 11, 2009.
Mandatory Service Bulletin A300-57A6101. 03............................. March 11, 2009
Issued in Renton, Washington, on November 6, 2009.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
FR Doc. E9-27631 Filed 11-17-09; 8:45 am
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