Airworthiness Directives; Airbus Airplanes, 65808-65810 [2012-26198]

Download as PDF 65808 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations accordance with the procedures specified in paragraph (l) of this AD. (j) Repeat ETHF Inspection For airplanes on which any splice repair was required by this AD: Within 30,000 flight cycles after the splice repair, repeat the inspection required by paragraph (g) of this AD for the repaired wing. If no cracking is found on the on the rear spar lower cap of the repaired wing, repeat the inspection on the affected wing rear spar lower cap thereafter at intervals not to exceed 2,550 flight cycles. If any cracking is found during any inspection required by this paragraph, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (g), (h), and (i) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin MD90–57A026, dated February 11, 2010, which is not incorporated by reference in this AD. mstockstill on DSK4VPTVN1PROD with RULES (l) Alternative Methods of Compliance (AMOCs) (1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. (m) Related Information (1) For more information about this AD, contact Roger Durbin, Airframe Branch, ANM–120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, California 90712–4137; phone: (562) 627–5233; fax: (562) 627–5210; email: roger.durbin@faa.gov. (2) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https://www.myboeingfleet.com. (n) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Boeing Alert Service Bulletin MD90– 57A026, Revision 1, dated February 23, 2011. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206–766–5683; Internet https://www.myboeingfleet.com. (4) You may view this service information at FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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/cfr/ibrlocations.html. Issued in Renton, Washington, on October 19, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–26483 Filed 10–30–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0427; Directorate Identifier 2011–NM–202–AD; Amendment 39–17233; AD 2012–21–17] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain Airbus Model A320–214 and –232 airplanes. This AD was prompted by reports that medium-head fasteners were installed in lieu of shear-head fasteners on a certain upper panel, which manufacturer fatigue and damage tolerance analyses demonstrated could have an effect on panel fatigue life. This AD requires repetitive inspections for cracking of certain fasteners, and repairs if necessary. We are issuing this AD to detect and correct such cracking, which SUMMARY: PO 00000 Frm 00036 Fmt 4700 Sfmt 4700 could result in the loss of structural integrity of the airplane. This AD becomes effective December 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 5, 2012. DATES: 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. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; 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 May 8, 2012 (77 FR 26996). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: A problem was reported during the installation of upper panels on Frame 35 in Airbus A320 final assembly line. Investigations revealed that medium head fasteners, Part Number (P/N) EN6114V3, were installed in lieu of shear head fasteners, P/N ASNA2657V3 and ASNA2043V3, which were previously used. Installation of these medium head fasteners leads to a deeper countersink in the panel. Fatigue and damage tolerance analyses were performed, the results of which demonstrated that this installation could have a fatigue impact on two rows of fasteners between stringers (STGR) 5 and 6, and indicated the need for a specific inspection in this area. This condition, if not detected and corrected, could impair the structural integrity of the affected aeroplanes. For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires repetitive special detailed [high frequency eddy current] inspections [for cracking] of the affected fasteners and, depending on findings, the accomplishment of associated corrective actions [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 have considered the comments received. E:\FR\FM\31OCR1.SGM 31OCR1 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations Support for the NPRM (77 FR 26996, May 8, 2012) Mr. Jason Aldrich stated that it appears from the analysis gathered that the repairs/modifications (proposed by the NPRM (77 FR 26996, May 8, 2012)) could significantly reduce potential damage to the airplane, which would directly result in improved safety for persons. Request To Clarify Repair Approval Airbus requested that we revise paragraph (h) of the NPRM (77 FR 26996, May 8, 2012) to clarify that any Repair Approval Sheet (RAS) approved under authority of Airbus Design Organization Approval (DOA) number EASA 21J.031 is acceptable as a repair method for the EASA or its delegated agent. We disagree to change the AD because a change is not necessary. Paragraph (h) of the AD allows repairs approved by EASA or its delegated agent. We understand that Airbus has discretion to provide repair to their operators that meets the certification basis of the airplane and mitigates the unsafe condition addressed in the AD. We have not changed the AD in this regard. mstockstill on DSK4VPTVN1PROD with RULES Request for Terminating Action Airbus requested that we allow a repair performed according to the proposed requirements in paragraph (h) of the NPRM (77 FR 26996, May 8, 2012) as terminating action, as stated in paragraph (3) of EASA Airworthiness Directive 2011–0176, dated September 13, 2011. We disagree to allow repairs as terminating action in this AD. The action identified by EASA in its AD is not necessarily terminating action. Under the provision of paragraph (i) of this AD, we will consider requests for approval of an alternative method of compliance (AMOC) if sufficient data are submitted to substantiate that a proposed repair meets an acceptable level of safety as terminating action for the repetitive inspections. We have not changed the AD in this regard. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD as proposed, except for minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 26996, May 8, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 proposed in the NPRM (77 FR 26996, May 8, 2012). Costs of Compliance We estimate that this AD will affect 44 products of U.S. registry. We also estimate that it will take about 3 workhours 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 $11,220, or $255 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. We have no way of determining the number of products that may need these actions. 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 that 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); 3. Will not affect intrastate aviation in Alaska; and 4. 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. PO 00000 Frm 00037 Fmt 4700 Sfmt 4700 65809 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 (77 FR 26996, May 8, 2012), 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2012–21–17 Airbus: Amendment 39–17233. Docket No. FAA–2012–0427; Directorate Identifier 2011–NM–202–AD. (a) Effective Date This airworthiness directive (AD) becomes effective December 5, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A320– 214 and –232 airplanes; certificated in any category; manufacturer serial numbers 3456, 3503, 3516, 3529, 3591, 3597, 3611, 3631, 3696, 3698, 3714, 3719, 3775, 3777, 3780, 3782, 3786, 3797, 3805, 3812, 3870, 3907, 3909, 3913, 3922, 3929, 3946, 3953, 3975, 3979, 3991, 4010, 4012, 4014, 4027, 4034, 4043, 4046, 4064, 4065, 4084, 4093, 4094, and 4097. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports that medium-head fasteners were installed in lieu of shear-head fasteners on a certain upper E:\FR\FM\31OCR1.SGM 31OCR1 65810 Federal Register / Vol. 77, No. 211 / Wednesday, October 31, 2012 / Rules and Regulations panel, which manufacturer fatigue and damage tolerance analyses demonstrated could have an effect on panel fatigue life. We are issuing this AD to detect and correct such cracking, which could result in the loss of structural integrity of the airplane. (j) Related Information Refer to MCAI EASA Airworthiness Directive 2011–0176, dated September 13, 2011; and Airbus Service Bulletin A320–53– 1244, excluding Appendix 1, dated March 17, 2011; for related information. (f) Compliance (k) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1244, excluding Appendix 1, dated March 17, 2011. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS–EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus. com; Internet http://www.airbus.com. (4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. (5) You may view this 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/cfr/ibr-locations.html. You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Repetitive Inspection Before the accumulation of 35,900 total flight cycles or 88,100 total flight hours, whichever occurs first: Do a high frequency eddy current inspection for cracking of the two rows of six fasteners at frame 35 between stringers 5 and 6 on the left and right sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1244, excluding Appendix 1, dated March 17, 2011. Repeat the inspection thereafter at intervals not to exceed 28,100 flight cycles or 56,300 flight hours, whichever occurs first. (h) Corrective Action If any crack is detected during any inspection required by paragraph (g) of this AD: Before further flight, repair the crack using a method approved by either the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) or its delegated agent. mstockstill on DSK4VPTVN1PROD with RULES (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–1405; fax (425) 227– 1149. Information may be emailed to: 9ANM–116–AMOC–REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate 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. VerDate Mar<15>2010 16:49 Oct 30, 2012 Jkt 229001 Issued in Renton, Washington, on October 16, 2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–26198 Filed 10–30–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0592; Directorate Identifier 2011–NM–253–AD; Amendment 39–17230 AD 2012–21–14] RIN 2120–AA64 Airworthiness Directives; Bombardier, Inc. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are superseding an existing airworthiness directive (AD) for certain Bombardier, Inc. Model CL–600– 2B19 (Regional Jet Series 100 & 440) airplanes. That AD currently requires a one-time inspection of the shafts of the SUMMARY: PO 00000 Frm 00038 Fmt 4700 Sfmt 4700 main landing gear (MLG) side-brace fittings to detect corrosion, and the forward and aft bushings in the lefthand and right-hand MLG side-brace fittings to detect discrepancies. The existing AD also requires corrective and related actions if necessary. This new AD requires repetitive detailed inspections for corrosion and damage of the MLG side-brace fitting, and replacing the side-brace fitting shaft with the re-designed side-brace fitting shaft of the MLG if necessary. This AD also requires eventual replacement of certain side-brace fitting shafts with the re-designed part. Replacement with a redesigned side-brace fitting shaft of the MLG is terminating action for the repetitive inspections. This AD was prompted by reports of failure of the side-brace fitting shaft of the main landing gear (MLG) due to corrosion. We are issuing this AD to prevent fractures of the side-brace fitting shafts of the MLG, and possible collapse of the MLG. DATES: This AD becomes effective December 5, 2012. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 5, 2012. 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: Jeffrey Zimmer, Aerospace Engineer, Airframe and Mechanical Systems Branch, ANE–171, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228– 7306; fax (516) 794–5531. 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 June 12, 2012 (77 FR 34870), and proposed to supersede AD 2004– 22–23, Amendment 39–13851 (69 FR 64856, November 9, 2004). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Due to the failure of the main landing gear (MLG) side brace fitting shaft, caused by corrosion, [Transport Canada Civil Aviation (TCCA)] Airworthiness Directive (AD) CF– 2002–41 was issued to require inspection and E:\FR\FM\31OCR1.SGM 31OCR1

Agencies

[Federal Register Volume 77, Number 211 (Wednesday, October 31, 2012)]
[Rules and Regulations]
[Pages 65808-65810]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-26198]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0427; Directorate Identifier 2011-NM-202-AD; 
Amendment 39-17233; AD 2012-21-17]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A320-214 and -232 airplanes. This AD was prompted by 
reports that medium-head fasteners were installed in lieu of shear-head 
fasteners on a certain upper panel, which manufacturer fatigue and 
damage tolerance analyses demonstrated could have an effect on panel 
fatigue life. This AD requires repetitive inspections for cracking of 
certain fasteners, and repairs if necessary. We are issuing this AD to 
detect and correct such cracking, which could result in the loss of 
structural integrity of the airplane.

DATES: This AD becomes effective December 5, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 5, 
2012.

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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405; 
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 May 8, 2012 (77 FR 
26996). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    A problem was reported during the installation of upper panels 
on Frame 35 in Airbus A320 final assembly line. Investigations 
revealed that medium head fasteners, Part Number (P/N) EN6114V3, 
were installed in lieu of shear head fasteners, P/N ASNA2657V3 and 
ASNA2043V3, which were previously used. Installation of these medium 
head fasteners leads to a deeper countersink in the panel. Fatigue 
and damage tolerance analyses were performed, the results of which 
demonstrated that this installation could have a fatigue impact on 
two rows of fasteners between stringers (STGR) 5 and 6, and 
indicated the need for a specific inspection in this area.
    This condition, if not detected and corrected, could impair the 
structural integrity of the affected aeroplanes.
    For the reasons described above, this [European Aviation Safety 
Agency (EASA)] AD requires repetitive special detailed [high 
frequency eddy current] inspections [for cracking] of the affected 
fasteners and, depending on findings, the accomplishment of 
associated corrective actions [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 have considered the comments received.

[[Page 65809]]

Support for the NPRM (77 FR 26996, May 8, 2012)

    Mr. Jason Aldrich stated that it appears from the analysis gathered 
that the repairs/modifications (proposed by the NPRM (77 FR 26996, May 
8, 2012)) could significantly reduce potential damage to the airplane, 
which would directly result in improved safety for persons.

Request To Clarify Repair Approval

    Airbus requested that we revise paragraph (h) of the NPRM (77 FR 
26996, May 8, 2012) to clarify that any Repair Approval Sheet (RAS) 
approved under authority of Airbus Design Organization Approval (DOA) 
number EASA 21J.031 is acceptable as a repair method for the EASA or 
its delegated agent.
    We disagree to change the AD because a change is not necessary. 
Paragraph (h) of the AD allows repairs approved by EASA or its 
delegated agent. We understand that Airbus has discretion to provide 
repair to their operators that meets the certification basis of the 
airplane and mitigates the unsafe condition addressed in the AD. We 
have not changed the AD in this regard.

Request for Terminating Action

    Airbus requested that we allow a repair performed according to the 
proposed requirements in paragraph (h) of the NPRM (77 FR 26996, May 8, 
2012) as terminating action, as stated in paragraph (3) of EASA 
Airworthiness Directive 2011-0176, dated September 13, 2011.
    We disagree to allow repairs as terminating action in this AD. The 
action identified by EASA in its AD is not necessarily terminating 
action. Under the provision of paragraph (i) of this AD, we will 
consider requests for approval of an alternative method of compliance 
(AMOC) if sufficient data are submitted to substantiate that a proposed 
repair meets an acceptable level of safety as terminating action for 
the repetitive inspections. We have not changed the AD in this regard.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD as proposed, except for minor editorial changes. We have 
determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 26996, May 8, 2012) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 26996, May 8, 2012).

Costs of Compliance

    We estimate that this AD will affect 44 products of U.S. registry. 
We also estimate that it will take about 3 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 $11,220, or $255 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this AD. We 
have no way of determining the number of products that may need these 
actions.

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 that 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);
    3. Will not affect intrastate aviation in Alaska; and
    4. 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 (77 FR 26996, May 8, 2012), 
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:

2012-21-17 Airbus: Amendment 39-17233. Docket No. FAA-2012-0427; 
Directorate Identifier 2011-NM-202-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective December 5, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-214 and -232 airplanes; 
certificated in any category; manufacturer serial numbers 3456, 
3503, 3516, 3529, 3591, 3597, 3611, 3631, 3696, 3698, 3714, 3719, 
3775, 3777, 3780, 3782, 3786, 3797, 3805, 3812, 3870, 3907, 3909, 
3913, 3922, 3929, 3946, 3953, 3975, 3979, 3991, 4010, 4012, 4014, 
4027, 4034, 4043, 4046, 4064, 4065, 4084, 4093, 4094, and 4097.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports that medium-head fasteners were 
installed in lieu of shear-head fasteners on a certain upper

[[Page 65810]]

panel, which manufacturer fatigue and damage tolerance analyses 
demonstrated could have an effect on panel fatigue life. We are 
issuing this AD to detect and correct such cracking, which could 
result in the loss of structural integrity of the airplane.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Repetitive Inspection

    Before the accumulation of 35,900 total flight cycles or 88,100 
total flight hours, whichever occurs first: Do a high frequency eddy 
current inspection for cracking of the two rows of six fasteners at 
frame 35 between stringers 5 and 6 on the left and right sides, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1244, excluding Appendix 1, dated March 17, 2011. 
Repeat the inspection thereafter at intervals not to exceed 28,100 
flight cycles or 56,300 flight hours, whichever occurs first.

(h) Corrective Action

    If any crack is detected during any inspection required by 
paragraph (g) of this AD: Before further flight, repair the crack 
using a method approved by either the Manager, International Branch, 
ANM-116, Transport Airplane Directorate, FAA; or the European 
Aviation Safety Agency (EASA) or its delegated agent.

(i) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227-1405; fax (425) 227-1149. Information may 
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate 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.

(j) Related Information

    Refer to MCAI EASA Airworthiness Directive 2011-0176, dated 
September 13, 2011; and Airbus Service Bulletin A320-53-1244, 
excluding Appendix 1, dated March 17, 2011; for related information.

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Service Bulletin A320-53-1244, excluding Appendix 1, 
dated March 17, 2011.
    (ii) Reserved.
    (3) For service information identified in this AD, contact 
Airbus SAS-EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (4) You may review copies of the service information at the FAA, 
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, 
call 425-227-1221.
    (5) You may view this 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/cfr/ibr-locations.html.

    Issued in Renton, Washington, on October 16, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-26198 Filed 10-30-12; 8:45 am]
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