Airworthiness Directives; Airbus Airplanes, 74597-74599 [2014-29174]

Download as PDF Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations and Soundness Act, 12 U.S.C. 4567(a), through increased charges or fees, or decreased premiums, or in any other manner, to the originators of mortgages purchased or securitized by the Enterprise. (b) Enforcement. Compliance by each Enterprise with the foregoing prohibition shall be enforced under subpart 3 of part B of the Safety and Soundness Act, 12 U.S.C. 4581–89. only to the Enterprises, which are not small entities for purposes of the Regulatory Flexibility Act. List of Subjects in 12 CFR Part 1251 Administrative practice and procedure, Capital Magnet Fund, Government-sponsored enterprises, Housing Trust Fund, Reporting and recordkeeping requirements. Authority and Issuance Accordingly, for the reasons stated in the Supplementary Information, under the authority of 12 U.S.C. 4567, the Federal Housing Finance Agency amends Chapter XII of Title 12 of the Code of Federal Regulations, as follows: CHAPTER XII—FEDERAL HOUSING FINANCE AGENCY § 1251.4 Submission of information. The Director may issue guidance, orders, or notices on compliance with section 1337 and this part by the Enterprises, which may include information submissions by the Enterprises. SUBCHAPTER C—ENTERPRISES 1. Add part 1251 to Subchapter C to read as follows: Dated: December 10, 2014. Melvin L. Watt, Director, Federal Housing Finance Agency. [FR Doc. 2014–29345 Filed 12–15–14; 8:45 am] ■ BILLING CODE 8070–01–P PART 1251—CONTRIBUTIONS TO THE HOUSING TRUST AND CAPITAL MAGNET FUNDS Sec. 1251.1 Purpose. 1251.2 Definitions. 1251.3 Prohibition on pass-through of cost of allocation; enforcement. 1251.4 Submission of information. Authority: 12 U.S.C. 1452(c), 1718(b), 4511(b), 4513(a), 4514(a), 4526(a), and 4567. § 1251.1 Purpose. The purpose of this part is to implement a prohibition against an Enterprise redirecting the cost of any allocation to the Housing Trust Fund or the Capital Magnet Fund to originators of mortgages purchased or securitized by an Enterprise. § 1251.2 Definitions. tkelley on DSK3SPTVN1PROD with RULES The following definitions apply to the terms used in and related specifically to this part. Definitions of other terms may be found in 12 CFR part 1201, General Definitions Applying to All Federal Housing Finance Agency Regulations: Capital Magnet Fund means that Fund established at section 1339(a) of the Safety and Soundness Act, 12 U.S.C. 4569(a). Housing Trust Fund means that Fund established by section 1338(a) of the Safety and Soundness Act, 12 U.S.C. 4568(a). § 1251.3 Prohibition on pass-through of cost of allocation; enforcement. (a) In general. No Enterprise shall redirect or pass through the cost of any allocation to the Housing Trust Fund or the Capital Magnet Fund required pursuant to section 1337(a) of the Safety VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0453; Directorate Identifier 2013–NM–205–AD; Amendment 39–18049; AD 2014–25–07] 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 A320–211, –212, –214, –231, –232, and –233 airplanes. This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during fullscale fatigue testing. This AD requires repetitive inspections for cracking of both sides of the splice plate of that frame butt joint crossing area, and corrective action if necessary. This AD also provides for an optional modification, which terminates the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR 47 butt joint crossing area, which could result in reduced structural integrity of the airplane. DATES: This AD becomes effective January 20, 2015. The Director of the Federal Register approved the incorporation by reference SUMMARY: PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 74597 of certain publications listed in this AD as of January 20, 2015. ADDRESSES: You may examine the AD docket on the Internet at https://www. regulations.gov/#!docketDetail;D=FAA2014-0453 or in person at the Docket Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 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 view this 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. FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–227–1405; fax: 425–227–1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Airbus Model A320– 211, –212, –214, –231, –232, and –233 airplanes. The NPRM published in the Federal Register on July 18, 2014 (79 FR 41940). The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2013–0203, dated September 6, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. The MCAI states: During the full scale fatigue test on A320– 200, cracks were reported at the splice plate of the frame (FR) 47 butt joint crossing area, both sides. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. Prompted by these findings, Airbus developed Mod 31012 and introduced this on the production line to modify the current 2 fastener row butt joint into a 3 fastener row butt joint to prevent further damage. For inservice aeroplanes, a corresponding modification was developed and published E:\FR\FM\16DER1.SGM 16DER1 74598 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations as Airbus Service Bulletin (SB) A320–53– 1271. For the reason described above, this [EASA] AD requires repetitive special detailed inspections (SDI) of the splice plate of the FR47 butt joint crossing area and, depending on findings, accomplishment of applicable corrective action(s). You may examine the MCAI in the AD docket on the Internet at https:// www.regulations.gov/#!documentDetail; D=FAA-2014-0453-0002. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM (79 FR 41940, July 18, 2014) and the FAA’s response. Request to Extend the Compliance Time Allegiant Air, LLC asked that we extend the threshold for the initial inspection for the airplanes identified in paragraph (g)(3) of the proposed AD (79 FR 41940, July 18, 2014) to 44,000 flight cycles or 88,000 flight hours, whichever occurs first. Allegiant Air asserted that an equivalent level of safety would be maintained by extending the compliance time as proposed. Allegiant Air noted that paragraph (g)(2) of the proposed AD specified a threshold of 45,000 total flight cycles or 91,000 total flight hours, whichever occurs first. We do not agree with the commenter’s request to extend the compliance time. We infer that Allegiant Air, LLC expected 44,000 total flight cycles or 88,000 total flight hours to be the threshold for crack growth propagation based on full-scale fatigue testing; however, Allegiant Air, LLC did not provide data to support this inference. Based on our risk assessment, taking into consideration the worldwide fleet utilization, as well as fatigue and crack growth analysis, we have determined that the compliance time specified in paragraph (g)(3) of this AD will ensure an acceptable level of safety and allow the inspections to be done in a timely manner. However, under the provisions of paragraph (j) of this AD, we may approve requests for adjustments to the compliance time if data are submitted to substantiate that such an adjustment would provide an acceptable level of safety. We have not changed this final rule in this regard. tkelley on DSK3SPTVN1PROD with RULES Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes: VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 • Are consistent with the intent that was proposed in the NPRM (79 FR 41940, July 18, 2014) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (79 FR 41940, July 18, 2014). Costs of Compliance We estimate that this AD affects 229 airplanes of U.S. registry. We also estimate that it will take about 98 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 on U.S. operators to be $1,907,570, or $8,330 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. In addition, we estimate that any necessary follow-on actions take about 100 work-hours and require parts costing $1,150, for a cost of $9,650 per product. We have no way of determining the number of aircraft that might 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: PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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. Examining the AD Docket You may examine the AD docket on the Internet at https://www.regulations. gov/#!docketDetail;D=FAA-2014-0453; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this 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. 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 airworthiness directive (AD): ■ 2014–25–07 Airbus: Amendment 39–18049. Docket No. FAA–2014–0453; Directorate Identifier 2013–NM–205–AD. (a) Effective Date This AD becomes effective January 20, 2015. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A320– 211, –212, –214, –231, –232, and –233 airplanes, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification 31012 has been embodied in production. E:\FR\FM\16DER1.SGM 16DER1 Federal Register / Vol. 79, No. 241 / Tuesday, December 16, 2014 / Rules and Regulations (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking at the splice plate of the frame (FR) 47 butt joint crossing area found during fullscale fatigue testing. We are issuing this AD to detect and correct fatigue cracking of the splice plate of the FR47 butt joint crossing area, which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. tkelley on DSK3SPTVN1PROD with RULES (g) Repetitive Inspections At the applicable time specified in paragraph (g)(1), (g)(2), or (g)(3) of this AD: Do a special detailed inspection (rototest) for cracking of both sides of the splice plate of the FR47 butt joint crossing area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 53–1260, dated December 19, 2012. Repeat the inspection thereafter at intervals not to exceed 14,800 flight cycles or 29,600 flight hours, whichever occurs first. (1) For airplanes that, as of the effective date of this AD, have accumulated 44,000 or more total flight cycles or 88,000 or more total flight hours since first flight of the airplane: Do the inspection within 1,500 flight cycles or 3,000 flight hours after the effective date of this AD, whichever occurs first. (2) For airplanes that, as of the effective date of this AD, have accumulated 27,700 or more total flight cycles or 55,400 or more total flight hours, but fewer than 44,000 total flight cycles or 88,000 total flight hours since first flight of the airplane: Do the inspection within 3,000 flight cycles or 6,000 flight hours after the effective date of this AD, without exceeding 45,500 total flight cycles or 91,000 total flight hours since first flight of the airplane, whichever occurs first. (3) For airplanes that, as of the effective date of this AD, have accumulated fewer than 27,700 total flight cycles and less than 55,400 total flight hours since first flight of the airplane: Do the inspection before the accumulation of 30,700 total flight cycles or 61,400 total flight hours since first flight of the airplane, whichever occurs first. (h) Corrective Action If any crack is found during any inspection required by this AD: 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 Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOAauthorized signature. (i) Optional Modification Accomplishing the modification of the splice plate of the FR47 butt joint in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– VerDate Sep<11>2014 16:25 Dec 15, 2014 Jkt 235001 53–1271, dated December 18, 2012, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD. (j) 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; phone: 425–227–1405; fax: 425–227–1149. Information may be emailed to: 9-ANM-116AMOC-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. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0203, dated September 6, 2013, for related information. This MCAI may be found in the AD docket on the Internet at https://www.regulations. gov/#!documentDetail;D=FAA-2014-04530002. (l) 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 this AD specifies otherwise. (i) Airbus Service Bulletin A320–53–1260, dated December 19, 2012. (ii) Airbus Service Bulletin A320–53–1271, dated December 18, 2012. (3) For service information identified in this AD, contact Airbus, Airworthiness Office—EIAS, 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. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 74599 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: https://www.archives. gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on December 3, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–29174 Filed 12–15–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0257; Directorate Identifier 2014–NM–012–AD; Amendment 39–18051; AD 2014–25–09] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes. This AD was prompted by reports of fatigue cracking in the skin assembly and bear strap of the aft lower corner of the forward airstair stowage doorway. This AD requires repetitive inspections for cracking of the skin assembly and bear strap of the forward airstair stowage doorway; post-repair and post-modification inspections for certain airplanes; and related investigative and corrective actions, if necessary. This AD also provides optional terminating actions for certain inspections. We are issuing this AD to detect and correct fatigue cracking, which could result in rapid loss of cabin pressure. DATES: This AD is effective January 20, 2015. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of January 20, 2015. ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// SUMMARY: E:\FR\FM\16DER1.SGM 16DER1

Agencies

[Federal Register Volume 79, Number 241 (Tuesday, December 16, 2014)]
[Rules and Regulations]
[Pages 74597-74599]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-29174]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0453; Directorate Identifier 2013-NM-205-AD; 
Amendment 39-18049; AD 2014-25-07]
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 A320-211, -212, -214, -231, -232, and -233 airplanes. This 
AD was prompted by a report of cracking at the splice plate of the 
frame (FR) 47 butt joint crossing area found during full-scale fatigue 
testing. This AD requires repetitive inspections for cracking of both 
sides of the splice plate of that frame butt joint crossing area, and 
corrective action if necessary. This AD also provides for an optional 
modification, which terminates the repetitive inspections. We are 
issuing this AD to detect and correct fatigue cracking of the splice 
plate of the FR 47 butt joint crossing area, which could result in 
reduced structural integrity of the airplane.

DATES: This AD becomes effective January 20, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 20, 
2015.

ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0453 or in person at the 
Docket Management Facility, U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC.
    For service information identified in this AD, contact Airbus, 
Airworthiness Office--EIAS, 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 view this 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.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-227-1405; fax: 
425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to certain Airbus Model A320-
211, -212, -214, -231, -232, and -233 airplanes. The NPRM published in 
the Federal Register on July 18, 2014 (79 FR 41940).
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2013-0203, dated September 6, 2013 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-211, -212, -214, -231, -232, and -233 airplanes. The MCAI states:

    During the full scale fatigue test on A320-200, cracks were 
reported at the splice plate of the frame (FR) 47 butt joint 
crossing area, both sides.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    Prompted by these findings, Airbus developed Mod 31012 and 
introduced this on the production line to modify the current 2 
fastener row butt joint into a 3 fastener row butt joint to prevent 
further damage. For in-service aeroplanes, a corresponding 
modification was developed and published

[[Page 74598]]

as Airbus Service Bulletin (SB) A320-53-1271.
    For the reason described above, this [EASA] AD requires 
repetitive special detailed inspections (SDI) of the splice plate of 
the FR47 butt joint crossing area and, depending on findings, 
accomplishment of applicable corrective action(s).

    You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-0453-0002.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comment received on the NPRM (79 FR 
41940, July 18, 2014) and the FAA's response.

Request to Extend the Compliance Time

    Allegiant Air, LLC asked that we extend the threshold for the 
initial inspection for the airplanes identified in paragraph (g)(3) of 
the proposed AD (79 FR 41940, July 18, 2014) to 44,000 flight cycles or 
88,000 flight hours, whichever occurs first. Allegiant Air asserted 
that an equivalent level of safety would be maintained by extending the 
compliance time as proposed. Allegiant Air noted that paragraph (g)(2) 
of the proposed AD specified a threshold of 45,000 total flight cycles 
or 91,000 total flight hours, whichever occurs first.
    We do not agree with the commenter's request to extend the 
compliance time. We infer that Allegiant Air, LLC expected 44,000 total 
flight cycles or 88,000 total flight hours to be the threshold for 
crack growth propagation based on full-scale fatigue testing; however, 
Allegiant Air, LLC did not provide data to support this inference. 
Based on our risk assessment, taking into consideration the worldwide 
fleet utilization, as well as fatigue and crack growth analysis, we 
have determined that the compliance time specified in paragraph (g)(3) 
of this AD will ensure an acceptable level of safety and allow the 
inspections to be done in a timely manner. However, under the 
provisions of paragraph (j) of this AD, we may approve requests for 
adjustments to the compliance time if data are submitted to 
substantiate that such an adjustment would provide an acceptable level 
of safety. We have not changed this final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this 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 (79 FR 41940, July 18, 2014) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (79 FR 41940, July 18, 2014).

Costs of Compliance

    We estimate that this AD affects 229 airplanes of U.S. registry.
    We also estimate that it will take about 98 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 on U.S. operators to be $1,907,570, or $8,330 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.
    In addition, we estimate that any necessary follow-on actions take 
about 100 work-hours and require parts costing $1,150, for a cost of 
$9,650 per product. We have no way of determining the number of 
aircraft that might 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2014-0453; or in person at the 
Docket Management Facility between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this 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.

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 airworthiness 
directive (AD):

2014-25-07 Airbus: Amendment 39-18049. Docket No. FAA-2014-0453; 
Directorate Identifier 2013-NM-205-AD.

(a) Effective Date

    This AD becomes effective January 20, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-211, -212, -214, -231, -
232, and -233 airplanes, certificated in any category, all 
manufacturer serial numbers, except those on which Airbus 
Modification 31012 has been embodied in production.

[[Page 74599]]

(d) Subject

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

(e) Reason

    This AD was prompted by a report of cracking at the splice plate 
of the frame (FR) 47 butt joint crossing area found during full-
scale fatigue testing. We are issuing this AD to detect and correct 
fatigue cracking of the splice plate of the FR47 butt joint crossing 
area, which could result in reduced structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Repetitive Inspections

    At the applicable time specified in paragraph (g)(1), (g)(2), or 
(g)(3) of this AD: Do a special detailed inspection (rototest) for 
cracking of both sides of the splice plate of the FR47 butt joint 
crossing area, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1260, dated December 19, 2012. 
Repeat the inspection thereafter at intervals not to exceed 14,800 
flight cycles or 29,600 flight hours, whichever occurs first.
    (1) For airplanes that, as of the effective date of this AD, 
have accumulated 44,000 or more total flight cycles or 88,000 or 
more total flight hours since first flight of the airplane: Do the 
inspection within 1,500 flight cycles or 3,000 flight hours after 
the effective date of this AD, whichever occurs first.
    (2) For airplanes that, as of the effective date of this AD, 
have accumulated 27,700 or more total flight cycles or 55,400 or 
more total flight hours, but fewer than 44,000 total flight cycles 
or 88,000 total flight hours since first flight of the airplane: Do 
the inspection within 3,000 flight cycles or 6,000 flight hours 
after the effective date of this AD, without exceeding 45,500 total 
flight cycles or 91,000 total flight hours since first flight of the 
airplane, whichever occurs first.
    (3) For airplanes that, as of the effective date of this AD, 
have accumulated fewer than 27,700 total flight cycles and less than 
55,400 total flight hours since first flight of the airplane: Do the 
inspection before the accumulation of 30,700 total flight cycles or 
61,400 total flight hours since first flight of the airplane, 
whichever occurs first.

(h) Corrective Action

    If any crack is found during any inspection required by this AD: 
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 
Airbus's EASA Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.

(i) Optional Modification

    Accomplishing the modification of the splice plate of the FR47 
butt joint in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1271, dated December 18, 2012, 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD.

(j) 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; phone: 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.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2013-0203, dated September 6, 2013, for 
related information. This MCAI may be found in the AD docket on the 
Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2014-
0453-0002.

(l) 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 this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-53-1260, dated December 19, 
2012.
    (ii) Airbus Service Bulletin A320-53-1271, dated December 18, 
2012.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 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.
    (4) You may view this 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on December 3, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-29174 Filed 12-15-14; 8:45 am]
BILLING CODE 4910-13-P

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