Airworthiness Directives; Airbus Airplanes, 63270-63272 [2012-25461]

Download as PDF 63270 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2012–1071; Directorate Identifier 2012–NM–070–AD. (a) Comments Due Date We must receive comments by November 30, 2012. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A310– 203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 71; Powerplant. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 (e) Reason This AD was prompted by a report of an analysis that demonstrated a reduced fatigue life for the side link bolts, center sway link bolts, and thrust link bolts on the forward engine mounts. We are issuing this AD to prevent deterioration of the structural integrity of the bolts, which could result in possible damage to an engine or wing. (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) Actions Within 18 months after the effective date of this AD, replace all side link bolts on left hand (LH) and right hand (RH) side of the engines, and all center sway link bolts and thrust link bolts of both engines, having any part number (P/N) identified in paragraphs VerDate Mar<15>2010 15:10 Oct 15, 2012 Jkt 229001 (g)(1) through (g)(6) of this AD, with new bolts having the same part number, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A310–71–2037, including Appendices 01 and 02, dated September 30, 2011. Repeat the bolt replacements thereafter at intervals not exceeding 134 months. (1) P/N 9021M88P01 (2) P/N 9021M88P02 (3) P/N 9205M81P01 (4) P/N 9021M88P03 (5) P/N 9021M88P04 (6) P/N 9205M82P01 (h) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone (425) 227–2125; fax (425) 227– 1147. 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. (i) Related Information (1) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2012–0056, dated April 3, 2012; and Airbus Mandatory Service Bulletin A310–71–2037, including Appendices 01 and 02, dated September 30, 2011; for related information. (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email account.airwortheas@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, WA. For information on the availability of this material at the FAA, call 425–227–1221. PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 Issued in Renton, Washington, on October 4, 2012. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–25458 Filed 10–15–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–1076; Directorate Identifier 2011–NM–274–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, –232 and –233; and Model A321–211, –213, and –231 airplanes. This proposed AD was prompted by a report of a missing fastener between certain stringers of the fuselage frame which connects the frame to a tee. This proposed AD would require a rototest inspection and modification or repair of the fuselage frame at the affected area. We are proposing this AD to detect and correct cracking in the fuselage that could result in reduced structural integrity of the airplane. SUMMARY: We must receive comments on this proposed AD by November 30, 2012. DATES: 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, Airworthiness Office—EAS, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 ADDRESSES: E:\FR\FM\16OCP1.SGM 16OCP1 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules 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, WA. 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, WA 98057–3356; telephone (425) 227–1405; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 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–2012–1076; Directorate Identifier 2011–NM–274–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 aviation authority for the Member States of the European Community, has issued EASA Airworthiness Directive 2011–0229, dated December 6, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During a quality check in production of an A320 family aeroplane, it was discovered VerDate Mar<15>2010 15:10 Oct 15, 2012 Jkt 229001 that a fastener was missing at [frame] FR 24 between stringer (STRG) 25 and STRG 26 on the right-hand (RH) side. The purpose of the missing fastener, a 4 [millimeter] mm diameter aluminum rivet, Part Number (P/N) ASNA2050DXJ040, is to connect the FR 24 to the FR 24 Tee. The hole where the fastener was missing was not drilled. Further investigations revealed that the drilling was missing on the milling grid used for frame assembly of a limited group of aeroplanes. This condition, if not corrected, could impair the structural integrity of the affected aeroplanes. For the reasons described above, this [EASA] AD requires a special detailed inspection (SDI) [rototest inspection for cracking] of the affected area, and the accomplishment of the associated corrective actions [modification and/or repair]. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Service Bulletin A320–53–1247, including Appendix 01, dated July 15, 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 111 products of U.S. registry. We also estimate that it would take about 6 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 $56,610, or $510 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 PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 63271 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. E:\FR\FM\16OCP1.SGM 16OCP1 63272 § 39.13 Federal Register / Vol. 77, No. 200 / Tuesday, October 16, 2012 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2012–1076; Directorate Identifier 2011–NM–274–AD. (a) Comments Due Date We must receive comments by November 30, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A320– 214, –232, and –233; and Model A321–211, –213, and –231 airplanes; certificated in any category; manufacturer serial numbers 4338, 4371, 4374, 4375, 4377, 4381 through 4384 inclusive, 4386, 4387, 4388, 4390 through 4402 inclusive, 4404 through 4409 inclusive, 4411 through 4417 inclusive, 4419, 4420, 4421, 4423, 4424, 4426, 4429 through 4436 inclusive, 4438 through 4443 inclusive, 4445 through 4450 inclusive, 4453, 4454, 4456 through 4469 inclusive, 4471, 4472, 4474 through 4481 inclusive, 4483 through 4498 inclusive, 4500, 4504, 4505, 4506, and 4509. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of a missing fastener between certain stringers of the fuselage frame which connects the frame to a tee. We are issuing this AD to detect and correct cracking in the fuselage that could result in reduced structural integrity of the airplane. pmangrum on DSK3VPTVN1PROD with PROPOSALS-1 (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) Inspection Before the accumulation of 24,000 total flight cycles since first flight of the airplane, or within 30 days after the effective date of this AD, whichever occurs later: Do a rototest inspection for cracking of the two adjacent fastener holes at fuselage frame (FR) 24 between stringer 25 and stringer 26 righthand side, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–53–1247, excluding Appendix 01, dated July 15, 2011. (1) If, during the rototest inspection required by paragraph (g) of this AD, any crack is found, before further flight, repair using 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). (2) If, during the rototest inspection required by paragraph (g) of this AD, no crack is found, before the accumulation of 24,000 total flight cycles since first flight of the airplane, or within 30 days after the effective date of this AD, whichever occurs later, modify fuselage frame FR 24 between stringer 25 and stringer 26 right-hand side, in VerDate Mar<15>2010 15:10 Oct 15, 2012 Jkt 229001 accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1247, excluding Appendix 01, dated July 15, 2011. DEPARTMENT OF TRANSPORTATION (h) Other FAA AD Provisions 14 CFR Part 39 The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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. [Docket No. FAA–2012–1077; Directorate Identifier 2012–NM–146–AD] (i) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2011–0229, dated December 6, 2011; and Airbus Service Bulletin A320–53–1247, excluding Appendix 01, dated July 15, 2011. (2) For service information identified in this AD, contact Airbus, Airworthiness Office—EAS, 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, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on October 5, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–25461 Filed 10–15–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 Federal Aviation Administration RIN 2120–AA64 Airworthiness Directives; Embraer S.A. Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain Embraer S.A. Model ERJ 170 and ERJ 190 airplanes. This proposed AD was prompted by a report that high rate discharge (HRD) bottle explosive cartridges of a cargo compartment fire extinguisher system were swapped between the forward and aft cargo compartments. Additional investigation also revealed the possibility of swapping between the electrical connectors of the HRD and low rate discharge (LRD) bottles, and a rotated installation of the HRD bottle. Improper assembly of the fire extinguishing bottle might cause the extinguishing agent to be discharged toward the unselected cargo compartment rather than toward the cargo compartment with fire. This proposed AD would require an inspection of the HRD bottle for correct installation and to determine if the pressure switch is in the correct position, and re-installation if necessary; an inspection of the HRD and LRD bottle discharge heads to determine the part number and replacement if necessary; and, for certain airplanes, an inspection to determine the part numbers of the HRD and LRD electrical connectors, and relocation if necessary. We are proposing this AD to prevent the inability of the fire extinguishing system to suppress fire. DATES: We must receive comments on this proposed AD by November 30, 2012. SUMMARY: 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– ADDRESSES: E:\FR\FM\16OCP1.SGM 16OCP1

Agencies

[Federal Register Volume 77, Number 200 (Tuesday, October 16, 2012)]
[Proposed Rules]
[Pages 63270-63272]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-25461]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1076; Directorate Identifier 2011-NM-274-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, -232 and -233; and Model A321-211, -213, 
and -231 airplanes. This proposed AD was prompted by a report of a 
missing fastener between certain stringers of the fuselage frame which 
connects the frame to a tee. This proposed AD would require a rototest 
inspection and modification or repair of the fuselage frame at the 
affected area. We are proposing this AD to detect and correct cracking 
in the fuselage that could result in reduced structural integrity of 
the airplane.

DATES: We must receive comments on this proposed AD by November 30, 
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, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36

[[Page 63271]]

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, WA. 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, WA 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-2012-1076; 
Directorate Identifier 2011-NM-274-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 aviation 
authority for the Member States of the European Community, has issued 
EASA Airworthiness Directive 2011-0229, dated December 6, 2011 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

During a quality check in production of an A320 family aeroplane, it 
was discovered that a fastener was missing at [frame] FR 24 between 
stringer (STRG) 25 and STRG 26 on the right-hand (RH) side. The 
purpose of the missing fastener, a 4 [millimeter] mm diameter 
aluminum rivet, Part Number (P/N) ASNA2050DXJ040, is to connect the 
FR 24 to the FR 24 Tee. The hole where the fastener was missing was 
not drilled.

Further investigations revealed that the drilling was missing on the 
milling grid used for frame assembly of a limited group of 
aeroplanes.

This condition, if not corrected, could impair the structural 
integrity of the affected aeroplanes.

For the reasons described above, this [EASA] AD requires a special 
detailed inspection (SDI) [rototest inspection for cracking] of the 
affected area, and the accomplishment of the associated corrective 
actions [modification and/or repair].

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Service Bulletin A320-53-1247, including Appendix 
01, dated July 15, 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 111 products of U.S. registry. We also estimate that 
it would take about 6 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 $56,610, or $510 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.

[[Page 63272]]

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

Airbus: Docket No. FAA-2012-1076; Directorate Identifier 2011-NM-
274-AD.

(a) Comments Due Date

    We must receive comments by November 30, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-214, -232, and -233; and 
Model A321-211, -213, and -231 airplanes; certificated in any 
category; manufacturer serial numbers 4338, 4371, 4374, 4375, 4377, 
4381 through 4384 inclusive, 4386, 4387, 4388, 4390 through 4402 
inclusive, 4404 through 4409 inclusive, 4411 through 4417 inclusive, 
4419, 4420, 4421, 4423, 4424, 4426, 4429 through 4436 inclusive, 
4438 through 4443 inclusive, 4445 through 4450 inclusive, 4453, 
4454, 4456 through 4469 inclusive, 4471, 4472, 4474 through 4481 
inclusive, 4483 through 4498 inclusive, 4500, 4504, 4505, 4506, and 
4509.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a missing fastener between 
certain stringers of the fuselage frame which connects the frame to 
a tee. We are issuing this AD to detect and correct cracking in the 
fuselage that could result in reduced 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) Inspection

    Before the accumulation of 24,000 total flight cycles since 
first flight of the airplane, or within 30 days after the effective 
date of this AD, whichever occurs later: Do a rototest inspection 
for cracking of the two adjacent fastener holes at fuselage frame 
(FR) 24 between stringer 25 and stringer 26 right-hand side, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1247, excluding Appendix 01, dated July 15, 2011.
    (1) If, during the rototest inspection required by paragraph (g) 
of this AD, any crack is found, before further flight, repair using 
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).
    (2) If, during the rototest inspection required by paragraph (g) 
of this AD, no crack is found, before the accumulation of 24,000 
total flight cycles since first flight of the airplane, or within 30 
days after the effective date of this AD, whichever occurs later, 
modify fuselage frame FR 24 between stringer 25 and stringer 26 
right-hand side, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-53-1247, excluding Appendix 01, 
dated July 15, 2011.

(h) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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.

(i) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2011-0229, dated December 6, 
2011; and Airbus Service Bulletin A320-53-1247, excluding Appendix 
01, dated July 15, 2011.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EAS, 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, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on October 5, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2012-25461 Filed 10-15-12; 8:45 am]
BILLING CODE 4910-13-P
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