Airworthiness Directives; Airbus Airplanes, 51968-51970 [2015-21098]

Download as PDF 51968 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules (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. 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 removing Amendment 39–17986 (79 FR 60329, October 7, 2014), and adding the following new AD: ■ Pacific Aerospace Limited: Docket No. FAA– 2015–3620; Directorate Identifier 2015– CE–029–AD. (a) Comments Due Date We must receive comments by October 13, 2015. (b) Affected ADs This AD supersedes AD 2014–20–13, Amendment 39–17986 (79 FR 60329, October 7, 2014). (c) Applicability This AD applies to Pacific Aerospace Limited Model 750XL airplanes, all serial numbers through XL–193, XL–195, and XL– 197, certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 53: Fuselage. rmajette on DSK2VPTVN1PROD with PROPOSALS (e) Reason This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as fatigue cracks on the fin forward pickup plates. We are issuing this AD to detect and correct cracked fin forward pickup plates to prevent failure of the fin forward pickup plates, which could result in reduced control. (f) Actions and Compliance Unless already done, do the actions in paragraphs (f)(1) through (f)(4) of this AD: (1) Within the next 150 hours time-inservice (TIS) after the effective date of this AD, reduce the fin forward pickup bolt torque following the procedures in section 1.D., paragraphs A. 1) and A. 2) of the PLANNING INFORMATION in Pacific VerDate Sep<11>2014 14:07 Aug 26, 2015 Jkt 235001 Aerospace Limited Mandatory Service Bulletin PACSB/XL/068, Issue 5, dated June 29, 2015. (2) At or before reaching 2,000 hours total time-in-service (TTIS) or within the next 150 hours TIS after the effective date of this AD, whichever occurs later, and repetitively thereafter at intervals not to exceed 600 hours TIS or 12 months, whichever occurs first, do a detailed visual inspection and liquid penetrant inspection of the fin forward pickup plates for any evidence of cracking. Do the inspections following the procedures in sections 2.A. and 2.B. of the ACCOMPLISHMENT INSTRUCTIONS in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/XL/068, Issue 5, dated June 29, 2015. (3) If cracks are found during any inspection required in paragraph (f)(2) of this AD, before further flight, replace the fin forward pickup plates with new fin forward pickup plates, part number (P/N) 11–03375– 1. Do the replacement following the procedures in section 2.C. of the ACCOMPLISHMENT INSTRUCTIONS in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/XL/068, Issue 5, dated June 29, 2015. This replacement terminates the repetitive inspections required in paragraph (f)(2) of this AD. (4) If no cracks are found during any inspection required in paragraph (f)(2) of this AD, at or before reaching 6,000 hours TTIS or within the next 600 hours TIS after the effective date of this AD, whichever occurs later, replace the fin forward pickup plates, P/N 11–10281–1, with P/N 11–03375–1. Do the replacement following the procedures in section 2.D. of the ACCOMPLISHMENT INSTRUCTIONS in Pacific Aerospace Limited Mandatory Service Bulletin PACSB/ XL/068, Issue 5, dated June 29, 2015. This replacement terminates the repetitive inspections required in paragraph (f)(2) of this AD . (g) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4146; fax: (816) 329–4090; email: karl.schletzbaum@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. (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. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 (h) Related Information Refer to MCAI Civil Aviation Authority (CAA) AD DCA/750XL/18A, dated August 4, 2015, for related information. You may examine the MCAI on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015–3620. For service information related to this AD, contact Pacific Aerospace Limited, Airport Road, Hamilton, Private Bag 3027, Hamilton 3240, New Zealand, phone: +64 7 843 6144; fax: +64 7 843 6134; email: pacific@ aerospace.co.nz; Internet: www.aerospace.co.nz. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. Issued in Kansas City, Missouri, on August 14, 2015. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–21097 Filed 8–26–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–3148; Directorate Identifier 2014–NM–254–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 A320–212, –214, –232, and –233 airplanes. This proposed AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame. This proposed AD would require repetitive low frequency eddy current inspections or repetitive high frequency eddy current inspections of this area, and repair if necessary. The repair terminates the repetitive inspections. We are proposing this AD to detect and correct any cracking of the pocket radius, which could lead to in-flight decompression of the airplane and possible injury to the passengers. DATES: We must receive comments on this proposed AD by October 13, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: SUMMARY: E:\FR\FM\27AUP1.SGM 27AUP1 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 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—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 http://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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3148; 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 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: rmajette on DSK2VPTVN1PROD with PROPOSALS 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–2015–3148; Directorate Identifier 2014–NM–254–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy VerDate Sep<11>2014 14:07 Aug 26, 2015 Jkt 235001 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 http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014–0278, dated December 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A320–212, -214, -232, and -233 airplanes. The MCAI states: An operator reported finding a crack during an inspection in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A53N007–14. What was found, a 170 mm through-thickness crack in the pocket radius between frame 36 and 37 above stringer 6 on left hand (LH) side lap joint, was not the aim of the AOT inspection. Prior to this finding, the operator reported noise in the affected area during several weeks. This condition, if not detected and corrected, could lead to in-flight decompression of the aeroplane, possibly resulting in injury to occupants. To address this unsafe condition, Airbus published AOT A53N009–14 to provide inspection and repair instructions to detect and prevent crack propagation. EASA decided to agree on a sampling inspection to determine whether additional aeroplanes need to be inspected. For the reasons described above, this [EASA] AD requires, for the selected aeroplanes, repetitive Low Frequency Eddy Current (LFEC) or High Frequency Eddy Current (HFEC) inspections of the pocket radii [for cracks] located between fuselage frames 35 and 40, above stringer 6 on both LH and right hand (RH) sides and, depending on findings, accomplishment of repair instructions. This [EASA] AD is considered an interim action and further [EASA] AD action may follow. You may examine the MCAI in the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 3148. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Alert Operators Transmission A53N009–14, dated December 17, 2014. The service information describes procedures for repetitive inspections of the pocket radii PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 51969 located between fuselage frames 35 and 40, above stringer 6 on both the left- and right-hand sides, and repair if necessary. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section of this NPRM. 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 We estimate that this proposed AD affects 1 airplane 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 this proposed AD on U.S. operators to be $255, 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. 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. E:\FR\FM\27AUP1.SGM 27AUP1 51970 Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / Proposed Rules 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. 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 airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–3148; Directorate Identifier 2014–NM–254–AD. (a) Comments Due Date We must receive comments by October 13, 2015. rmajette on DSK2VPTVN1PROD with PROPOSALS (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A320– 212 airplanes having manufacturer serial number (MSN) 1011; Airbus Model A320– 214 airplanes having MSNs 1009, 1026 and 1030; Airbus Model A320–232 airplanes having MSN 0977; and Airbus Model A320– 233 airplanes having MSNs 1007 and 1013, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. VerDate Sep<11>2014 14:07 Aug 26, 2015 Jkt 235001 (e) Reason This AD was prompted by a report of a crack found during an inspection of the pocket radius of the fuselage frame. We are issuing this AD to detect and correct any cracking of the pocket radius, which could lead to in-flight decompression of the airplane and possible injury to the passengers. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections (1) Within 750 flight cycles or 4 months, whichever occurs first after the effective date of this AD: Do a low frequency eddy current (LFEC) inspection or a high frequency eddy current (HFEC) inspection for cracking of the pocket radii located between fuselage frames 35 and 40, above stringer 6 on both the leftand right-hand sides, in accordance with the instructions of Airbus Alert Operators Transmission (AOT) A53N009–14, dated December 17, 2014. Repeat the inspection, thereafter, at intervals not to exceed the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD. (i) For the LFEC inspection performed on the outside: Repeat the inspection at intervals not to exceed 1,000 flight cycles. (ii) For the HFEC inspection performed on the inside: Repeat the inspection at intervals not to exceed 2,000 flight cycles. (h) Corrective Action If, during any inspection required by paragraph (g) of this AD, any crack is found, before further flight, accomplish the repair in accordance with the instructions of Airbus AOT A53N009–14, dated December 17, 2014; except if the crack is beyond the structural repair manual limits as specified in Airbus AOT A53N009–14, dated December 17, 2014, 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). (i) Terminating Action Repair of an airplane as required by paragraph (h) of this AD terminates the repetitive inspections required by paragraph (g) of this AD for the repaired area only. (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, 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; PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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) 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 EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0278, dated December 19, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2015–3148. (2) 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 http://www.airbus.com. 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. Issued in Renton, Washington, on August 19, 2015. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–21098 Filed 8–26–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2015–3322; Airspace Docket No. 15–ANM–16] Proposed Establishment of Class E Airspace; Vancouver, WA Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to establish Class E surface area airspace at Pearson Field, Vancouver, WA, to accommodate existing Standard Instrument Approach Procedures (SIAPs) at the airport. The FAA is taking this action to enhance the safety and SUMMARY: E:\FR\FM\27AUP1.SGM 27AUP1

Agencies

[Federal Register Volume 80, Number 166 (Thursday, August 27, 2015)]
[Proposed Rules]
[Pages 51968-51970]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21098]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-3148; Directorate Identifier 2014-NM-254-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 A320-212, -214, -232, and -233 airplanes. This 
proposed AD was prompted by a report of a crack found during an 
inspection of the pocket radius of the fuselage frame. This proposed AD 
would require repetitive low frequency eddy current inspections or 
repetitive high frequency eddy current inspections of this area, and 
repair if necessary. The repair terminates the repetitive inspections. 
We are proposing this AD to detect and correct any cracking of the 
pocket radius, which could lead to in-flight decompression of the 
airplane and possible injury to the passengers.

DATES: We must receive comments on this proposed AD by October 13, 
2015.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:

[[Page 51969]]

     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 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--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 http://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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3148; 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 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-2015-3148; 
Directorate Identifier 2014-NM-254-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 http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0278, dated December 19, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A320-212, -214, -232, and -233 airplanes. The MCAI states:

    An operator reported finding a crack during an inspection in 
accordance with the instructions of Airbus Alert Operators 
Transmission (AOT) A53N007-14. What was found, a 170 mm through-
thickness crack in the pocket radius between frame 36 and 37 above 
stringer 6 on left hand (LH) side lap joint, was not the aim of the 
AOT inspection. Prior to this finding, the operator reported noise 
in the affected area during several weeks.
    This condition, if not detected and corrected, could lead to in-
flight decompression of the aeroplane, possibly resulting in injury 
to occupants.
    To address this unsafe condition, Airbus published AOT A53N009-
14 to provide inspection and repair instructions to detect and 
prevent crack propagation.
    EASA decided to agree on a sampling inspection to determine 
whether additional aeroplanes need to be inspected.
    For the reasons described above, this [EASA] AD requires, for 
the selected aeroplanes, repetitive Low Frequency Eddy Current 
(LFEC) or High Frequency Eddy Current (HFEC) inspections of the 
pocket radii [for cracks] located between fuselage frames 35 and 40, 
above stringer 6 on both LH and right hand (RH) sides and, depending 
on findings, accomplishment of repair instructions.
    This [EASA] AD is considered an interim action and further 
[EASA] AD action may follow.

    You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
3148.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Alert Operators Transmission A53N009-14, dated 
December 17, 2014. The service information describes procedures for 
repetitive inspections of the pocket radii located between fuselage 
frames 35 and 40, above stringer 6 on both the left- and right-hand 
sides, and repair if necessary. This service information is reasonably 
available because the interested parties have access to it through 
their normal course of business or by the means identified in the 
ADDRESSES section of this NPRM.

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

    We estimate that this proposed AD affects 1 airplane 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 this proposed AD on U.S. operators to be $255, 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.

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.

[[Page 51970]]

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.

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

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):

Airbus: Docket No. FAA-2015-3148; Directorate Identifier 2014-NM-
254-AD.

(a) Comments Due Date

    We must receive comments by October 13, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A320-212 airplanes having 
manufacturer serial number (MSN) 1011; Airbus Model A320-214 
airplanes having MSNs 1009, 1026 and 1030; Airbus Model A320-232 
airplanes having MSN 0977; and Airbus Model A320-233 airplanes 
having MSNs 1007 and 1013, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by a report of a crack found during an 
inspection of the pocket radius of the fuselage frame. We are 
issuing this AD to detect and correct any cracking of the pocket 
radius, which could lead to in-flight decompression of the airplane 
and possible injury to the passengers.

(f) Compliance

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

(g) Repetitive Inspections

    (1) Within 750 flight cycles or 4 months, whichever occurs first 
after the effective date of this AD: Do a low frequency eddy current 
(LFEC) inspection or a high frequency eddy current (HFEC) inspection 
for cracking of the pocket radii located between fuselage frames 35 
and 40, above stringer 6 on both the left- and right-hand sides, in 
accordance with the instructions of Airbus Alert Operators 
Transmission (AOT) A53N009-14, dated December 17, 2014. Repeat the 
inspection, thereafter, at intervals not to exceed the times 
specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD.
    (i) For the LFEC inspection performed on the outside: Repeat the 
inspection at intervals not to exceed 1,000 flight cycles.
    (ii) For the HFEC inspection performed on the inside: Repeat the 
inspection at intervals not to exceed 2,000 flight cycles.

(h) Corrective Action

    If, during any inspection required by paragraph (g) of this AD, 
any crack is found, before further flight, accomplish the repair in 
accordance with the instructions of Airbus AOT A53N009-14, dated 
December 17, 2014; except if the crack is beyond the structural 
repair manual limits as specified in Airbus AOT A53N009-14, dated 
December 17, 2014, 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).

(i) Terminating Action

    Repair of an airplane as required by paragraph (h) of this AD 
terminates the repetitive inspections required by paragraph (g) of 
this AD for the repaired area only.

(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, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) 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 EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

 (k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0278, dated December 19, 
2014, for related information. This MCAI may be found in the AD 
docket on the Internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2015-3148.
    (2) 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 http://www.airbus.com. 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.

    Issued in Renton, Washington, on August 19, 2015.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-21098 Filed 8-26-15; 8:45 am]
 BILLING CODE 4910-13-P