Airworthiness Directives; Airbus Airplanes, 38036-38038 [2015-16165]

Download as PDF 38036 Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules Issued in Renton, Washington, on June 24, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–16155 Filed 7–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–1991; Directorate Identifier 2014–NM–251–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 all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, and –115 airplanes; Model A320–214 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. This proposed AD was prompted by reports of cracked cadmium-plated lock nuts that attach the hinge to the fan cowl door. This proposed AD would require inspecting to determine the serial number of each engine fan cowl door, inspecting for cracking of the hinge lock nuts of any affected door, and replacing the lock nuts if necessary. We are proposing this AD to detect and correct cracking of the hinge lock nuts, which could result in separation of the hinge from the fan cowl door, in-flight loss of the door, and consequent damage to the airplane. DATES: We must receive comments on this proposed AD by August 17, 2015. 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 asabaliauskas on DSK5VPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 21:02 Jul 01, 2015 Jkt 235001 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact the following: For Airbus service information 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 http:// www.airbus.com. For Goodrich service information contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, California, 91910–2098; telephone: 619–691–2719; email: jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs. 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– 1991; 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–2015–1991; Directorate Identifier 2014–NM–251–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:// PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 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 2014–0276, dated December 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A318–111 and –112 airplanes; Model A319–111, –112, and –115 airplanes; Model A320–214 airplanes; and Model A321–111, –112, –211, –212, and –213 airplanes. The MCAI states: In-service findings have been reported of cracked cadmium plated lock nuts. This cracking occurs shortly after installation. Investigation results attribute the cause to an improper manufacturing procedure of the nuts. It was determined that the affected batch of lock nuts was used on the fan cowl to attach hinges to the cowl doors on CFM56–5B engines only. This condition, if not corrected, could lead to separation of the hinge from the fan cowl door, possibly resulting in in-flight loss of a fan cowl door, with consequent damage to the aeroplane and/or injury to persons on the ground. For the reasons describes above, this [EASA] AD required identification of the affected fan cowl doors, a one-time inspection of the fan cowl door hinge nuts and, depending on findings, replacement of the affected nuts. 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– 1991. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A320–71–1062, including Appendix 01, dated July 28, 2014. Goodrich Aerostructures has issued Service Bulletin RA32071–151, dated June 11, 2014. The service information describes procedures for inspection of the hinge nuts of the fan cowl door, and replacement 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 E:\FR\FM\02JYP1.SGM 02JYP1 Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 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 437 airplanes of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $74,290, or $170 per product. We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in this proposed 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. 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 for This Rulemaking Authority: 49 U.S.C. 106(g), 40113, 44701. 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. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS 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: VerDate Sep<11>2014 21:02 Jul 01, 2015 Jkt 235001 § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2015–1991; Directorate Identifier 2014–NM–251–AD. (a) Comments Due Date We must receive comments by August 17, 2015. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any category, all manufacturer serial numbers. (1) Airbus Model A318–111 and –112 airplanes. (2) Airbus Model A319–111, –112, and –115 airplanes. (3) Airbus Model A320–214 airplanes. (4) Airbus Model A321–111, –112, –211, 212, and –213 airplanes. (d) Subject Air Transport Association (ATA) of America Code 71, Powerplant. (e) Reason This AD was prompted by reports of cracked cadmium-plated lock nuts that attach the hinge to the fan cowl door. We are issuing this AD to detect and correct cracking of the hinge lock nuts, which could result in separation of the hinge from the fan cowl door, the in-flight loss of the door, and consequent damage to the airplane. PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 38037 (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspect To Determine Serial Number Within 24 months after the effective date of this AD: Inspect to determine if any fan cowl door has a serial number 10029001 through 11092003 inclusive, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–71–1062, dated July 28, 2014; or Goodrich Aerostructures Service Bulletin RA32071– 151, dated June 11, 2014. A review of airplane maintenance records is acceptable in lieu of the inspection required by this paragraph, provided those records can be relied upon for that purpose and the serial number can be positively identified by that review. (h) Inspection and Replacement For any fan cowl door having any serial number identified in paragraph (g) of this AD: Within 24 months after the effective date of this AD, do a detailed inspection for cracking of the hinge lock nuts of the door, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320– 71–1062, dated July 28, 2014; or Goodrich Aerostructures Service Bulletin RA32071– 151, dated June 11, 2014. If any crack is found, before further flight, replace each cracked hinge lock nut, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320–71–1062, dated July 28, 2014; or Goodrich Aerostructures Service Bulletin RA32071–151, dated June 11, 2014. (i) Special Flight Permits Special flight permits, as described in Section 21.197 and Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199), are not allowed. (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; telephone: 425–227–1405; fax: 425–227– 1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective E:\FR\FM\02JYP1.SGM 02JYP1 38038 Federal Register / Vol. 80, No. 127 / Thursday, July 2, 2015 / Proposed Rules 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 (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014–0276, 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–2015–1991. (2) For Airbus service information 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. (3) For Goodrich service information contact Goodrich Aerostructures, 850 Lagoon Drive, Chula Vista, California, 91910–2098; telephone: 619–691–2719; email: jan.lewis@ goodrich.com; Internet: http:// www.goodrich.com/TechPubs. (4) 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. Issued in Renton, Washington, on June 24, 2015. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015–16165 Filed 7–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2455; Directorate Identifier 2014–NM–180–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). asabaliauskas on DSK5VPTVN1PROD with PROPOSALS AGENCY: We propose to supersede Airworthiness Directive (AD) 2008–26– 07, which applies to all McDonnell Douglas Model DC–8–11, DC–8–12, DC– 8–21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, DC–8–42, and DC–8–43 airplanes; Model DC–8–50 series airplanes; Model DC–8F–54 and DC– 8F–55 airplanes; Model DC–8–60 series SUMMARY: VerDate Sep<11>2014 21:02 Jul 01, 2015 Jkt 235001 airplanes; Model DC–8–60F series airplanes; Model DC–8–70 series airplanes; and Model DC–8–70F series airplanes. AD 2008–26–07 currently requires repetitive inspections of the lower skin and stringers at certain stations, and corrective actions if necessary. This proposed AD is intended to complete certain mandated programs intended to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This proposed AD would also require an eddy current high frequency (ETHF) inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive eddy current low frequency (ETLF) inspections around the fasteners for any crack; and corrective actions if necessary. We are proposing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane. DATES: We must receive comments on this proposed AD by August 17, 2015. 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800–0019, Long Beach, CA 90846–0001; telephone 206–544–5000, extension 2; fax 206– 766–5683; Internet https:// www.myboeingfleet.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. It is also available on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2015– 2455. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 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– 2455; 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 Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Chandra Ramdoss, Aerospace Engineer, Airframe Branch, ANM–120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712–4137; telephone: 562–627–5239; fax: 562–627–5210; email: Chandraduth.Ramdoss@faa.gov. 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–2015–2455; Directorate Identifier 2014–NM–180–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 because of 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 On December 12, 2008, we issued AD 2008–26–07, Amendment 39–15773 (73 FR 78946, December 24, 2008), for all McDonnell Douglas Model DC–8–11, DC–8–12, DC–8–21, DC–8–31, DC–8–32, DC–8–33, DC–8–41, DC–8–42, and DC– 8–43 airplanes; Model DC–8–50 series airplanes; Model DC–8F–54 and DC– 8F–55 airplanes; Model DC–8–60 series airplanes; Model DC–8–60F series airplanes; Model DC–8–70 series airplanes; and Model DC–8–70F series airplanes. AD 2008–26–07 requires repetitive inspections of the lower skin and stringers at stations Xw=408 and Xw=-408, and corrective actions if E:\FR\FM\02JYP1.SGM 02JYP1

Agencies

[Federal Register Volume 80, Number 127 (Thursday, July 2, 2015)]
[Proposed Rules]
[Pages 38036-38038]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16165]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-1991; Directorate Identifier 2014-NM-251-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 all 
Airbus Model A318-111 and -112 airplanes; Model A319-111, -112, and -
115 airplanes; Model A320-214 airplanes; and Model A321-111, -112, -
211, -212, and -213 airplanes. This proposed AD was prompted by reports 
of cracked cadmium-plated lock nuts that attach the hinge to the fan 
cowl door. This proposed AD would require inspecting to determine the 
serial number of each engine fan cowl door, inspecting for cracking of 
the hinge lock nuts of any affected door, and replacing the lock nuts 
if necessary. We are proposing this AD to detect and correct cracking 
of the hinge lock nuts, which could result in separation of the hinge 
from the fan cowl door, in-flight loss of the door, and consequent 
damage to the airplane.

DATES: We must receive comments on this proposed AD by August 17, 2015.

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 the 
following:
    For Airbus service information 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.
    For Goodrich service information contact Goodrich Aerostructures, 
850 Lagoon Drive, Chula Vista, California, 91910-2098; telephone: 619-
691-2719; email: jan.lewis@goodrich.com; Internet: http://www.goodrich.com/TechPubs.
    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-
1991; 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-2015-1991; 
Directorate Identifier 2014-NM-251-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 2014-0276, dated December 19, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318-111 and -112 airplanes; Model A319-111, -112, and -115 airplanes; 
Model A320-214 airplanes; and Model A321-111, -112, -211, -212, and -
213 airplanes. The MCAI states:

    In-service findings have been reported of cracked cadmium plated 
lock nuts. This cracking occurs shortly after installation. 
Investigation results attribute the cause to an improper 
manufacturing procedure of the nuts. It was determined that the 
affected batch of lock nuts was used on the fan cowl to attach 
hinges to the cowl doors on CFM56-5B engines only.
    This condition, if not corrected, could lead to separation of 
the hinge from the fan cowl door, possibly resulting in in-flight 
loss of a fan cowl door, with consequent damage to the aeroplane 
and/or injury to persons on the ground.
    For the reasons describes above, this [EASA] AD required 
identification of the affected fan cowl doors, a one-time inspection 
of the fan cowl door hinge nuts and, depending on findings, 
replacement of the affected nuts.

    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-
1991.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-71-1062, including Appendix 
01, dated July 28, 2014. Goodrich Aerostructures has issued Service 
Bulletin RA32071-151, dated June 11, 2014. The service information 
describes procedures for inspection of the hinge nuts of the fan cowl 
door, and replacement 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

[[Page 38037]]

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 437 airplanes of U.S. 
registry.
    We also estimate that it would take about 2 work-hours per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Required parts would cost about $0 per 
product. Based on these figures, we estimate the cost of this proposed 
AD on U.S. operators to be $74,290, or $170 per product.
    We have received no definitive data that would enable us to provide 
a cost estimate 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.

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-2015-1991; Directorate Identifier 2014-NM-
251-AD.

(a) Comments Due Date

    We must receive comments by August 17, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, certificated in any 
category, all manufacturer serial numbers.
    (1) Airbus Model A318-111 and -112 airplanes.
    (2) Airbus Model A319-111, -112, and -115 airplanes.
    (3) Airbus Model A320-214 airplanes.
    (4) Airbus Model A321-111, -112, -211, 212, and -213 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 71, Powerplant.

(e) Reason

    This AD was prompted by reports of cracked cadmium-plated lock 
nuts that attach the hinge to the fan cowl door. We are issuing this 
AD to detect and correct cracking of the hinge lock nuts, which 
could result in separation of the hinge from the fan cowl door, the 
in-flight loss of the door, and consequent damage to the airplane.

(f) Compliance

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

(g) Inspect To Determine Serial Number

    Within 24 months after the effective date of this AD: Inspect to 
determine if any fan cowl door has a serial number 10029001 through 
11092003 inclusive, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28, 
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated 
June 11, 2014. A review of airplane maintenance records is 
acceptable in lieu of the inspection required by this paragraph, 
provided those records can be relied upon for that purpose and the 
serial number can be positively identified by that review.

(h) Inspection and Replacement

    For any fan cowl door having any serial number identified in 
paragraph (g) of this AD: Within 24 months after the effective date 
of this AD, do a detailed inspection for cracking of the hinge lock 
nuts of the door, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-71-1062, dated July 28, 2014; or 
Goodrich Aerostructures Service Bulletin RA32071-151, dated June 11, 
2014. If any crack is found, before further flight, replace each 
cracked hinge lock nut, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-71-1062, dated July 28, 
2014; or Goodrich Aerostructures Service Bulletin RA32071-151, dated 
June 11, 2014.

(i) Special Flight Permits

    Special flight permits, as described in Section 21.197 and 
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197 
and 21.199), are not allowed.

(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; 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

[[Page 38038]]

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

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0276, 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-2015-1991.
    (2) For Airbus service information 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.
    (3) For Goodrich service information contact Goodrich 
Aerostructures, 850 Lagoon Drive, Chula Vista, California, 91910-
2098; telephone: 619-691-2719; email: jan.lewis@goodrich.com; 
Internet: http://www.goodrich.com/TechPubs.
    (4) 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.

    Issued in Renton, Washington, on June 24, 2015.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2015-16165 Filed 7-1-15; 8:45 am]
BILLING CODE 4910-13-P