Airworthiness Directives; Airbus Airplanes, 52267-52269 [2014-20937]

Download as PDF Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules emcdonald on DSK67QTVN1PROD with PROPOSALS if those actions were performed before April 23, 2008 (the effective date of AD 2008–06– 18, Amendment 39–15430 (73 FR 14670, March 19, 2008)), using the applicable service information identified in paragraphs (i)(1)(i) through (i)(1)(iv) of this AD, which are not incorporated by reference by this AD. (i) Airbus Service Bulletin A300–57–0177, Revision 03, dated May 29, 2006. (ii) Airbus Service Bulletin A300–57–0177, Revision 04, dated January 5, 2007. (iii) Airbus Service Bulletin A300–57– 6029, Revision 04, dated May 29, 2006. (iv) Airbus Service Bulletin A300–57– 6029, Revision 05, dated October 23, 2006. (2) This paragraph provides credit for actions required by paragraph (g) or (h) of this AD, if those actions were performed before the effective date of this AD, using Airbus Service Bulletin A300–57–6029, Revision 07, dated June 6, 2011, which is not incorporated by reference by 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: 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 425–227–1149. 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. The AMOC approval letter must specifically reference this AD. AMOCs approved previously for AD 2008–06–18, Amendment 39–15430 (73 FR 14670, March 19, 2008) are considered acceptable for 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 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. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120–0056. Public reporting for VerDate Mar<15>2010 16:15 Sep 02, 2014 Jkt 232001 this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES–200. (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) European Aviation Safety Agency Airworthiness Directive 2012–0203, dated October 1, 2012, 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–2014–0618. (2) For service information identified in this AD, contact Airbus SAS Airworthiness Office—EAW, 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 23, 2014. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–20917 Filed 9–2–14; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0589; Directorate Identifier 2014–NM–069–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 A318–111 and –112 airplanes, Model A319, A320, and A321 series airplanes. This proposed AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. This proposed AD would require repetitive inspections of certain forward corner fittings of the pylon aft secondary structures, and corrective actions if necessary. This SUMMARY: PO 00000 Frm 00029 Fmt 4702 Sfmt 4702 52267 proposed AD also provides optional terminating action for the repetitive inspections. We are proposing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. DATES: We must receive comments on this proposed AD by October 20, 2014. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: • 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–2014– 0589; 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. E:\FR\FM\03SEP1.SGM 03SEP1 52268 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules 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–2014–0589; Directorate Identifier 2014–NM–069–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. emcdonald on DSK67QTVN1PROD with PROPOSALS Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2014–0064, dated March 14, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Model A318–111 and –112 airplanes, Model A319 series airplanes, Model A320 series airplanes, and Model A321 series airplanes. The MCAI states: Several operators of A320 family aeroplanes have reported finding cracks on the forward corner fittings of engine pylon aft secondary structures, on the lateral face (lateral panel side). In some cases, these cracks had propagated onto the forward face (Rib 11 side). Investigation results have highlighted that these cracks are initiated by stress corrosion. This condition, if not detected and corrected, could lead to loss (i.e. detachment from the aeroplane) of the lower fairing attachment at Rib 10, and/or loss of the aft fixed fairing with the movable fairing, possibly resulting in * * * [damage to the airplane]. For the reasons described above, this [EASA] AD requires repetitive detailed inspections (DI) of the right hand (RH) Part Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner fittings of engine pylon aft secondary structures (premod 38067 or pre-Airbus Service Bulletin (SB) A320–54–1019) to detect cracks or deformation in the splicing area with corner fitting between Ribs 11–12 and, depending on findings, replacement of the corner fittings. This [EASA] AD also recognizes that replacement of the corner fittings with improved parts (as per Airbus SB A320–54– 1019) constitutes a terminating action for the repetitive DI required by this [EASA] AD. VerDate Mar<15>2010 16:15 Sep 02, 2014 Jkt 232001 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–2014– 0589. Relevant Service Information Airbus has issued Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008; and Service Bulletin A320– 54–1022, Revision 02, dated July 12, 2013. 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 these same type designs. Costs of Compliance We estimate that this proposed AD affects 851 airplanes of U.S. registry. We also estimate that it would take about 30 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 $2,170,050, or $2,550 per product. In addition, we estimate the optional terminating modification would take about 60 work-hours and require parts costing about $932 per product, for a cost of $6,032 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. According to the manufacturer, some of the costs of this proposed AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all costs in our cost estimate. 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 PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 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. 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. Amend § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2014–0589; Directorate Identifier 2014–NM–069–AD. E:\FR\FM\03SEP1.SGM 03SEP1 Federal Register / Vol. 79, No. 170 / Wednesday, September 3, 2014 / Proposed Rules (a) Comments Due Date We must receive comments by October 20, 2014. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(4) of this AD, certificated in any category, except for airplanes on which Airbus Modification 33844, or Modification 33847, as applicable, has been embodied in production. (1) Airbus Model A318–111 and –112 airplanes. (2) Airbus Model A319–111, –112, –113, –114, –115, –131, –132, and –133 airplanes. (3) Airbus Model A320–211, –212, –214, –231, –232, and –233 airplanes. (4) Airbus Model A321–111, –112, –131, –211, –212, –213, –231, and –232 airplanes. (d) Subject Air Transport Association (ATA) of America Code 54, Nacelles/pylons. (e) Reason This AD was prompted by reports of cracks on the forward corner fittings of engine pylon aft secondary structures. We are issuing this AD to detect and correct detachment of the lower fairing attachment and/or loss of the aft fixed fairing with the movable fairing from the airplane in flight, which could result in damage to the airplane. emcdonald on DSK67QTVN1PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections At the latest of the times specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking of forward corner fittings having part number (P/N) D54530014201 (right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon aft secondary structures, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–54–1022, Revision 02, dated July 12, 2013, except as provided by paragraph (j) of this AD. Repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 22,500 flight hours, whichever occurs first. Accomplishment of the actions required by paragraph (i) of this AD terminates the actions required by this paragraph. (1) Within 15,000 flight cycles or 22,500 flight hours, whichever occurs first since first flight of the airplane. (2) Within 5,000 flight cycles or 7,500 flight hours after the effective date of this AD, without exceeding 40,750 flight cycles or 60,750 flight hours, whichever occurs first since first flight of the airplane. (3) Within 750 flight cycles or 750 flight hours, whichever occurs first after the effective date of this AD. (h) Related Investigative and Corrective Actions If any crack is found on the corner fittings of a pylon during any inspection required by VerDate Mar<15>2010 16:15 Sep 02, 2014 Jkt 232001 paragraph (g) of this AD: Before further flight, do a detailed inspection for cracking of the lower and medium spars, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–54–1022, Revision 02, dated July 12, 2013. (1) If any damage 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 Airbus’s EASA Design Organization Approval (DOA). (2) If no damage is found: Within 5,000 flight cycles or 7,500 flight hours, whichever occurs first after the detailed inspection specified in paragraph (h) of this AD, modify the airplane, in accordance with the Accomplishment Instructions of Service Bulletin A320–54–1019, Revision 01, dated April 10, 2008. (i) Optional Terminating Action Modification of an airplane by installation of corner fittings having P/N D0041092120000 RH and P/N D0041092120100 LH on both pylons, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 54–1019, Revision 01, dated April 10, 2008, constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD. (j) Parts Installation Exception Airplanes on which Airbus Modification 38067 (installation of new corner fittings) has been embodied in production, and airplanes already modified in service as described in Airbus Service Bulletin A320–54–1019, are not affected by the requirements of paragraph (g) of this AD, provided that no corner fittings having P/N D54530014201 RH or P/N D54530014200 LH have been installed since first flight of the airplane, or since modification, as applicable. (k) Parts Installation Prohibition (1) As of the effective date of this AD, for airplanes on which Airbus Modification 38067 has been embodied in production on both pylons, and for airplanes previously modified in service as described in Airbus Service Bulletin A320–54–1019: Do not install any corner fittings having P/N D54530014201 RH or P/N D54530014200 LH. (2) After modification as required by paragraph (h) of this AD, or after optional modification as specified in paragraph (i) of this AD, as applicable: Do not install any corner fittings having P/N D54530014201 RH or P/N D54530014200 LH. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (h) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A320–54–1022, dated July 7, 2009; or Airbus Service Bulletin A320–54–1022, Revision 01, dated September 29, 2011; which are not incorporated by reference in this AD. (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1405; fax 425–227–1149. Information may be emailed to: 9-ANM-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. 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 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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0064, dated March 14, 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– 2014–0589. (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 22, 2014. Kevin Hull, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2014–20937 Filed 9–2–14; 8:45 am] BILLING CODE 4910–13–P (m) Other FAA AD Provisions The following provisions also apply to this AD: PO 00000 Frm 00031 Fmt 4702 Sfmt 9990 52269 E:\FR\FM\03SEP1.SGM 03SEP1

Agencies

[Federal Register Volume 79, Number 170 (Wednesday, September 3, 2014)]
[Proposed Rules]
[Pages 52267-52269]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-20937]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0589; Directorate Identifier 2014-NM-069-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 A318-111 and -112 airplanes, Model A319, A320, and 
A321 series airplanes. This proposed AD was prompted by reports of 
cracks on the forward corner fittings of engine pylon aft secondary 
structures. This proposed AD would require repetitive inspections of 
certain forward corner fittings of the pylon aft secondary structures, 
and corrective actions if necessary. This proposed AD also provides 
optional terminating action for the repetitive inspections. We are 
proposing this AD to detect and correct detachment of the lower fairing 
attachment and/or loss of the aft fixed fairing with the movable 
fairing from the airplane in flight, which could result in damage to 
the airplane.

DATES: We must receive comments on this proposed AD by October 20, 
2014.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     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-2014-
0589; 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.

[[Page 52268]]


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-2014-0589; 
Directorate Identifier 2014-NM-069-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 Community, has issued EASA 
Airworthiness Directive 2014-0064, dated March 14, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Model A318-
111 and -112 airplanes, Model A319 series airplanes, Model A320 series 
airplanes, and Model A321 series airplanes. The MCAI states:

    Several operators of A320 family aeroplanes have reported 
finding cracks on the forward corner fittings of engine pylon aft 
secondary structures, on the lateral face (lateral panel side). In 
some cases, these cracks had propagated onto the forward face (Rib 
11 side). Investigation results have highlighted that these cracks 
are initiated by stress corrosion.
    This condition, if not detected and corrected, could lead to 
loss (i.e. detachment from the aeroplane) of the lower fairing 
attachment at Rib 10, and/or loss of the aft fixed fairing with the 
movable fairing, possibly resulting in * * * [damage to the 
airplane].
    For the reasons described above, this [EASA] AD requires 
repetitive detailed inspections (DI) of the right hand (RH) Part 
Number (P/N) D54530014201 and left hand (LH) P/N D54530014200 corner 
fittings of engine pylon aft secondary structures (pre-mod 38067 or 
pre-Airbus Service Bulletin (SB) A320-54-1019) to detect cracks or 
deformation in the splicing area with corner fitting between Ribs 
11-12 and, depending on findings, replacement of the corner 
fittings.
    This [EASA] AD also recognizes that replacement of the corner 
fittings with improved parts (as per Airbus SB A320-54-1019) 
constitutes a terminating action for the repetitive DI required by 
this [EASA] AD.

    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-2014-
0589.

Relevant Service Information

    Airbus has issued Service Bulletin A320-54-1019, Revision 01, dated 
April 10, 2008; and Service Bulletin A320-54-1022, Revision 02, dated 
July 12, 2013. 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 these 
same type designs.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We also estimate that it would take about 30 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 $2,170,050, or 
$2,550 per product.
    In addition, we estimate the optional terminating modification 
would take about 60 work-hours and require parts costing about $932 per 
product, for a cost of $6,032 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.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

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]

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2. Amend Sec.  39.13 by adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2014-0589; Directorate Identifier 2014-NM-
069-AD.

[[Page 52269]]

(a) Comments Due Date

    We must receive comments by October 20, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except for airplanes on which Airbus Modification 33844, or 
Modification 33847, as applicable, has been embodied in production.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 54, Nacelles/
pylons.

(e) Reason

    This AD was prompted by reports of cracks on the forward corner 
fittings of engine pylon aft secondary structures. We are issuing 
this AD to detect and correct detachment of the lower fairing 
attachment and/or loss of the aft fixed fairing with the movable 
fairing from the airplane in flight, which could result in damage to 
the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    At the latest of the times specified in paragraphs (g)(1), 
(g)(2), and (g)(3) of this AD: Do a detailed inspection for cracking 
of forward corner fittings having part number (P/N) D54530014201 
(right-hand (RH)) and P/N D54530014200 (left-hand (LH)) of the pylon 
aft secondary structures, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-54-1022, Revision 02, 
dated July 12, 2013, except as provided by paragraph (j) of this AD. 
Repeat the inspection thereafter at intervals not to exceed 15,000 
flight cycles or 22,500 flight hours, whichever occurs first. 
Accomplishment of the actions required by paragraph (i) of this AD 
terminates the actions required by this paragraph.
    (1) Within 15,000 flight cycles or 22,500 flight hours, 
whichever occurs first since first flight of the airplane.
    (2) Within 5,000 flight cycles or 7,500 flight hours after the 
effective date of this AD, without exceeding 40,750 flight cycles or 
60,750 flight hours, whichever occurs first since first flight of 
the airplane.
    (3) Within 750 flight cycles or 750 flight hours, whichever 
occurs first after the effective date of this AD.

 (h) Related Investigative and Corrective Actions

    If any crack is found on the corner fittings of a pylon during 
any inspection required by paragraph (g) of this AD: Before further 
flight, do a detailed inspection for cracking of the lower and 
medium spars, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-54-1022, Revision 02, dated July 12, 
2013.
    (1) If any damage 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 Airbus's EASA Design Organization Approval (DOA).
    (2) If no damage is found: Within 5,000 flight cycles or 7,500 
flight hours, whichever occurs first after the detailed inspection 
specified in paragraph (h) of this AD, modify the airplane, in 
accordance with the Accomplishment Instructions of Service Bulletin 
A320-54-1019, Revision 01, dated April 10, 2008.

(i) Optional Terminating Action

    Modification of an airplane by installation of corner fittings 
having P/N D0041092120000 RH and P/N D0041092120100 LH on both 
pylons, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-54-1019, Revision 01, dated April 10, 2008, 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD.

(j) Parts Installation Exception

    Airplanes on which Airbus Modification 38067 (installation of 
new corner fittings) has been embodied in production, and airplanes 
already modified in service as described in Airbus Service Bulletin 
A320-54-1019, are not affected by the requirements of paragraph (g) 
of this AD, provided that no corner fittings having P/N D54530014201 
RH or P/N D54530014200 LH have been installed since first flight of 
the airplane, or since modification, as applicable.

(k) Parts Installation Prohibition

    (1) As of the effective date of this AD, for airplanes on which 
Airbus Modification 38067 has been embodied in production on both 
pylons, and for airplanes previously modified in service as 
described in Airbus Service Bulletin A320-54-1019: Do not install 
any corner fittings having P/N D54530014201 RH or P/N D54530014200 
LH.
    (2) After modification as required by paragraph (h) of this AD, 
or after optional modification as specified in paragraph (i) of this 
AD, as applicable: Do not install any corner fittings having P/N 
D54530014201 RH or P/N D54530014200 LH.

(l) Credit for Previous Actions

    This paragraph provides credit for actions required by 
paragraphs (g) and (h) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-54-1022, dated July 7, 2009; or Airbus Service Bulletin A320-
54-1022, Revision 01, dated September 29, 2011; which are not 
incorporated by reference in this AD.

(m) Other FAA AD Provisions

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

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0064, dated March 14, 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-2014-0589.
    (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 22, 2014.
Kevin Hull,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-20937 Filed 9-2-14; 8:45 am]
BILLING CODE 4910-13-P