Airworthiness Directives; Airbus Airplanes, 26996-26998 [2012-11023]

Download as PDF 26996 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules (i) Optional Terminating Action DEPARTMENT OF TRANSPORTATION Replacing the titanium seat track bolts with CRES bolts on both the left and right sides of buttock lines 24.75 and 45.50 at Station 727B, and installing a new splice strap P/N 146A5342–26, in accordance with the Accomplishment Instructions of Boeing Special Attention Service Bulletin 737–53– 1296, dated January 11, 2011, terminates the repetitive inspections required by paragraph (h) of this AD. (j) Alternative Methods of Compliance (AMOCs) mstockstill on DSK4VPTVN1PROD with PROPOSALS (1) The Manager, Seattle 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. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (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 Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0427; Directorate Identifier 2011–NM–202–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Airbus Model A320–214 and-232 airplanes. This proposed AD was prompted by reports that medium-head fasteners were installed in lieu of shearhead fasteners on a certain upper panel which manufacturer fatigue and damage tolerance analyses demonstrated could have an affect on panel fatigue life. This proposed AD would require repetitive inspections for cracking of certain fasteners, and repairs if necessary. We are proposing this AD to detect and correct cracking which could result in the loss of structural integrity of the airplane. SUMMARY: We must receive comments on this proposed AD by June 22, 2012. ADDRESSES: You may send comments by any of the following methods: (k) Related Information • Federal eRulemaking Portal: Go to (1) For more information about this AD, https://www.regulations.gov. Follow the contact Patrick Gillespie, Aerospace instructions for submitting comments. Engineer, Cabin Safety and Environmental • Fax: (202) 493–2251. Systems Branch, ANM–150S, FAA, Seattle • Mail: U.S. Department of Aircraft Certification Office (ACO), 1601 Lind Transportation, Docket Operations, Avenue SW., Renton, Washington 98057– M–30, West Building Ground Floor, 3356; phone: 425–917–6429; fax: 425–917– Room W12–140, 1200 New Jersey 6590; email: patrick.gillespie@faa.gov. Avenue SE., Washington, DC 20590. (2) For service information identified in • Hand Delivery: U.S. Department of this AD, contact Boeing Commercial Transportation, Docket Operations, M– Airplanes, Attention: Data & Services 30, West Building Ground Floor, Room Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone W12–140, 1200 New Jersey Avenue SE., 206–544–5000, extension 1; fax 206–766– Washington, DC, between 9 a.m. and 5680; email me.boecom@boeing.com; Internet 5 p.m., Monday through Friday, except https://www.myboeingfleet.com. You may Federal holidays. review copies of the referenced service For service information identified in information at the FAA, Transport Airplane this proposed AD, contact Airbus SAS– Directorate, 1601 Lind Avenue SW., Renton, EAW (Airworthiness Office), 1 Rond Washington. For information on the Point Maurice Bellonte, 31707 Blagnac availability of this material at the FAA, call Cedex, France; telephone +33 5 61 93 36 425–227–1221. 96; fax +33 5 61 93 44 51; email Issued in Renton, Washington, on April 29, account.airworth-eas@airbus.com; 2012. Internet https://www.airbus.com. You Michael Kaszycki, may review copies of the referenced Acting Manager, Transport Airplane service information at the FAA, Directorate, Aircraft Certification Service. Transport Airplane Directorate, 1601 [FR Doc. 2012–11019 Filed 5–7–12; 8:45 am] Lind Avenue SW., Renton, Washington. For information on the availability of BILLING CODE 4910–13–P VerDate Mar<15>2010 16:36 May 07, 2012 Jkt 226001 DATES: PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 this material at the FAA, call 425–227– 1221. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1405; 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–2012–0427; Directorate Identifier 2011–NM–202–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 https:// 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 2011–0176, dated September 13, 2011 (referred to after this as ‘‘the MCAI’’), 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 E:\FR\FM\08MYP1.SGM 08MYP1 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules 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 [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. Relevant Service Information Airbus has issued Service Bulletin A320–53–1244, including Appendix 1, dated March 17, 2011. 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. mstockstill on DSK4VPTVN1PROD with PROPOSALS 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 3 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 $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 proposed 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: VerDate Mar<15>2010 16:36 May 07, 2012 Jkt 226001 26997 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. Airbus: Docket No. FAA–2012–0427; Directorate Identifier 2011–NM–202–AD. 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); 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 proposed AD and placed it in the AD docket. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. 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 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 (a) Comments Due Date We must receive comments by June 22, 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. (e) Reason 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. We are issuing this AD to detect and correct 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 At the later of the times in paragraphs (g)(1) and (g)(2) of this AD: Do a high frequency eddy current inspection for cracking of the 2 rows of 6 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. (1) Before the accumulation of 35,900 total flight cycles or 88,100 total flight hours, whichever occurs first. (2) Within 30 days after the effective date of this AD. (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 E:\FR\FM\08MYP1.SGM 08MYP1 26998 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules 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, Washington 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. Issued in Renton, Washington, on April 29, 2012. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–11023 Filed 5–7–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0428; Directorate Identifier 2011–NM–078–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). mstockstill on DSK4VPTVN1PROD with PROPOSALS AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A330–243, –243F, –342, and –343 airplanes. This proposed AD was prompted by reports of cracking of air intake cowls on Rolls-Royce Trent engines, worn and detached attachment SUMMARY: VerDate Mar<15>2010 16:36 May 07, 2012 Jkt 226001 links, and fractured thermal anti-ice (TAI) piccolo tubes. This proposed AD would require inspecting piccolo tubes, piccolo tube mount links, the aft side of the forward bulkhead, and outer boundary angles (OBA) for cracks, fractures, and broken links, and corrective actions if necessary. We are proposing this AD to prevent degraded structural integrity of the engine nose cowl and a broken piccolo tube, which could lead to in-flight damage of the engine and reduced thermal anti-ice performance. We must receive comments on this proposed AD by June 22, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 W12–140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For Airbus service information identified in this proposed AD, contact Airbus SAS—Airworthiness Office— EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 45 80; email airworthiness.A330A340@airbus.com; Internet https:// www.airbus.com. For Rolls-Royce service information identified in this proposed AD, contact Rolls-Royce Plc, Technical Publications, P.O. Box 31, Derby, DE24 8BJ, United Kingdom; telephone 44 (0) 1332 245882; fax 44 (0) 1332 249936; Internet https://www.RollsRoyce.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. DATES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–1138; 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–2012–0428; Directorate Identifier 2011–NM–078–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 https:// 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 2011–0062, dated April 4, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During shop visit, several primary assembly structures of A330 aeroplanes Trent 700 [engine] air intake cowl have been found with cracks in the forward bulkhead web, web stiffeners and outer boundary angles. Several attachment links have been found severely worn, and some had become detached. In 2 cases, the Thermal Anti Ice (TAI) Piccolo tube was found fractured. Investigations are still ongoing to determine the root cause(s). If not detected and corrected, a broken Piccolo tube in conjunction with forward bulkhead damage could ultimately lead to in flight detachment of the outer barrel, which would constitute an unsafe condition. For the reasons described above, this [EASA] AD requires to perform inspections of RR [Rolls-Royce] Trent 700 [engine] nose cowls and, depending on findings, to do the applicable corrective action(s). These inspections include internal inspection of Piccolo tube, detailed inspection of Piccolo E:\FR\FM\08MYP1.SGM 08MYP1

Agencies

[Federal Register Volume 77, Number 89 (Tuesday, May 8, 2012)]
[Proposed Rules]
[Pages 26996-26998]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-11023]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0427; Directorate Identifier 2011-NM-202-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A320-214 and-232 airplanes. This proposed 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 affect 
on panel fatigue life. This proposed AD would require repetitive 
inspections for cracking of certain fasteners, and repairs if 
necessary. We are proposing this AD to detect and correct cracking 
which could result in the loss of structural integrity of the airplane.

DATES: We must receive comments on this proposed AD by June 22, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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 W12-140, 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; email account.airworth-eas@airbus.com; Internet https://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 https://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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1405; 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-2012-0427; 
Directorate Identifier 2011-NM-202-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 https://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 2011-0176, dated September 13, 2011 (referred 
to after this as ``the MCAI''), 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

[[Page 26997]]

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 [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.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1244, including Appendix 
1, dated March 17, 2011. 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.

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 3 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 $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 proposed 
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 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);
    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 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 adding the following new AD:

Airbus: Docket No. FAA-2012-0427; Directorate Identifier 2011-NM-
202-AD.

(a) Comments Due Date

    We must receive comments by June 22, 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 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 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

    At the later of the times in paragraphs (g)(1) and (g)(2) of 
this AD: Do a high frequency eddy current inspection for cracking of 
the 2 rows of 6 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.
    (1) Before the accumulation of 35,900 total flight cycles or 
88,100 total flight hours, whichever occurs first.
    (2) Within 30 days after the effective date of this AD.

(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

[[Page 26998]]

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, Washington 
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.


    Issued in Renton, Washington, on April 29, 2012.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-11023 Filed 5-7-12; 8:45 am]
BILLING CODE 4910-13-P
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