Airworthiness Directives; Airbus Airplanes, 59546-59548 [2016-20699]

Download as PDF 59546 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules vapor seals on the outboard pylons between the strut and aft fairing of the numbers 1 and 4 engines, in accordance with Part 2 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2246, dated February 5, 2016. Repeat the inspection thereafter at intervals not to exceed 1,200 flight cycles. (i) Before the accumulation of 1,800 total flight cycles, or within 1,800 flight cycles after the most recent vapor seal, block seal, and heat shield seal replacement, whichever is later. (ii) Within 6 months after the effective date of this AD. mstockstill on DSK3G9T082PROD with PROPOSALS (h) Replacement If during any inspection required by paragraph (g) of this AD any heat damage of any vapor seal is found: Before further flight, replace the vapor seal, heat shield seal, and block seal with new seals, in accordance with Part 3 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–54A2246, dated February 5, 2016. Repeat the inspection required by paragraph (g) of this AD within 1,800 flight cycles after doing the replacement, and thereafter at intervals not to exceed 1,200 flight cycles. (i) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 manager of the ACO, send it to the attention of the person identified in paragraph (j)(1) of this AD. Information may be emailed to: 9-ANM-Seattle-ACO–AMOCRequests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (j) Related Information (1) For more information about this AD, contact Sue Lucier, Aerospace Engineer, Propulsion Branch, ANM–140S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6438; fax: 425– 917–6590; email: suzanne.lucier@faa.gov. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206– 544–5000, extension 1; fax 206–766–5680; Internet https://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. Issued in Renton, Washington, on August 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20667 Filed 8–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 [Docket No. FAA–2016–9052; Directorate Identifier 2016–NM–080–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 A300 series airplanes; Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. This proposed AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. This proposed AD would require replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. We are proposing this AD to prevent failure of an aft hinge bolt assembly in an NLG aft door while the airplane is in flight, which could lead to an in-flight loss of an NLG aft door, and damage to the airplane. SUMMARY: PO 00000 Frm 00029 Fmt 4702 We must receive comments on this proposed AD by October 14, 2016. 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 NPRM, 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 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. DATES: Sfmt 4702 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 9052; 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: 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. 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–2016–9052; Directorate Identifier 2016–NM–080–AD’’ at the beginning of E:\FR\FM\30AUP1.SGM 30AUP1 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 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 AD 2016–0100, dated May 24, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for all Airbus Model A300 series airplanes; Model A300 B4–600, B4– 600R, and F4–600R series airplanes, and Model A300 C4–605R Variant F airplanes (collectively called Model A300–600 series airplanes); and Model A310 series airplanes. The MCAI states: An occurrence has been reported of failure of a nose landing gear (NLG) door aft hinge bolt assembly, Part Number (P/N) A53612600000. The result of laboratory investigations revealed that the aft hinge bolt rupture was initiated by fatigue crack development in the under head radius of the bolt, due to the lack of radius roll over and in combination with a non-optimised design. This condition, if not detected and corrected, could lead to in-flight loss of an aft NLG door, possibly resulting in damage to the aeroplane and injury to persons on the ground. Prompted by these findings, Airbus developed a new design aft hinge bolt assembly P/N A53612713000, introduced as Airbus modification (mod) 13741, to replace the existing bolt P/N A53612600000. Since the introduction of that mod, additional stress calculations demonstrated that the new bolt assembly, P/N A53612713000, cannot sustain fatigue loads up to the design Limit of Validity (LOV) of the affected aeroplanes. To address this potential unsafe condition, Airbus issued Service Bulletin (SB) A300– 53–0397, SB A310–53–2144 and SB A300– 53–6186, to provide instructions for the repetitive replacement of the affected postmod 13741 P/N A53612713000 aft hinge bolts. For the reasons described above, this [EASA] AD requires the replacement of all P/ N A53612600000 aft hinge bolt assemblies, installed on the left hand (LH) and right hand (RH) NLG aft doors, with post-mod 13741 P/ N A53612713000 aft hinge bolt assemblies, and, subsequently, the implementation of a life limit for those new bolt assemblies. 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–2016– 9052. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. • Airbus Service Bulletin A300–53– 0396, dated November 25, 2015. • Airbus Service Bulletin A300–53– 0397, dated January 18, 2016. • Airbus Service Bulletin A300–53– 6182, dated November 17, 2015. 59547 • Airbus Service Bulletin A300–53– 6186, dated January 18, 2016. • Airbus Service Bulletin A310–53– 2142, dated November 17, 2015. • Airbus Service Bulletin A310–53– 2144, dated January 18, 2016. The service information describes procedures for replacement of the aft hinge bolt assembly in the left and right NLG aft doors, with new aft hinge bolt assemblies. 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. 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 157 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Parts cost Cost per product Cost on U.S. operators Replacement ................................................... mstockstill on DSK3G9T082PROD with PROPOSALS Action 9 work-hours × $85 per hour = $765 ............. $2,000 $2,765 $434,105 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 VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 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: PO 00000 Frm 00030 Fmt 4702 Sfmt 4702 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. E:\FR\FM\30AUP1.SGM 30AUP1 59548 Federal Register / Vol. 81, No. 168 / Tuesday, August 30, 2016 / Proposed Rules 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–2016–9052; Directorate Identifier 2016–NM–080–AD. (a) Comments Due Date We must receive comments by October 14, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Airbus airplanes identified in paragraphs (c)(1) through (c)(6) of this AD, certificated in any category, all manufacturer serial numbers. (1) Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. (2) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. (3) Model A300 B4–605R and B4–622R airplanes. (4) Model A300 F4–605R and F4–622R airplanes. (5) Model A300 C4–605R Variant F airplanes. (6) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of failure of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. We are issuing this AD to prevent failure of an aft hinge bolt assembly in an NLG aft door while the airplane is in flight, which could lead to an in-flight loss of an NLG aft door, and damage to the airplane. mstockstill on DSK3G9T082PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Replace the Aft Hinge Bolt Assemblies Having Part Number (P/N) A53612600000 Before the accumulation of 10,000 total flight cycles since first flight of the airplane, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later, replace each aft hinge bolt assembly having P/N A53612600000 on the left and right NLG aft doors, with a new hinge bolt assembly having P/N A53612713000, in VerDate Sep<11>2014 17:56 Aug 29, 2016 Jkt 238001 accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD. (1) Airbus Service Bulletin A300–53–0396, dated November 25, 2015. (2) Airbus Service Bulletin A310–53–2142, dated November 17, 2015. (3) Airbus Service Bulletin A300–53–6182, dated November 17, 2015. (h) Replace the Aft Hinge Bolt Assemblies Having P/N A53612713000 Within 10,000 flight cycles after modification of an airplane as required by paragraph (g) of this AD, replace each aft hinge bolt assembly having P/N A53612713000 on the left and right aft NLG doors, with a new aft hinge bolt assembly having P/N A53612713000 on the left and right NLG aft doors, in accordance with the Accomplishment Instructions of the applicable service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Repeat the replacement thereafter at intervals not to exceed 10,000 flight cycles. (1) Airbus Service Bulletin A300–53–0397, dated January 18, 2016. (2) Airbus Service Bulletin A310–53–2144, dated January 18, 2016. (3) Airbus Service Bulletin A300–53–6186, dated January 18, 2016. (i) Parts Installation Prohibition (P/N A53612600000) After modification of an airplane NLG aft door as required by paragraph (g) of this AD, do not install an aft hinge bolt assembly having P/N A53612600000 on any NLG aft door of that airplane. (j) Parts Installation Limitation (P/N A53612713000) After removal of an aft hinge bolt assembly having P/N A53612713000 from an airplane aft NLG door, as required by paragraph (h) of this AD, do not install an aft hinge bolt assembly having that part number on any airplane unless it is a new aft hinge bolt assembly. (k) 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. PO 00000 Frm 00031 Fmt 4702 Sfmt 4702 (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) Required for Compliance (RC): If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator’s maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016–0100 dated May 24, 2016, 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– 2016–9052. (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 19, 2016. Dorr M. Anderson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–20699 Filed 8–29–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2014–0923; Directorate Identifier 2014–NM–176–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). AGENCY: E:\FR\FM\30AUP1.SGM 30AUP1

Agencies

[Federal Register Volume 81, Number 168 (Tuesday, August 30, 2016)]
[Proposed Rules]
[Pages 59546-59548]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-20699]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9052; Directorate Identifier 2016-NM-080-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 A300 series airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model A300 C4-605R Variant F airplanes 
(collectively called Model A300-600 series airplanes); and Model A310 
series airplanes. This proposed AD was prompted by reports of failure 
of an aft hinge bolt assembly in the nose landing gear (NLG) aft doors. 
This proposed AD would require replacement of the aft hinge bolt 
assembly in the left and right NLG aft doors, with new aft hinge bolt 
assemblies. We are proposing this AD to prevent failure of an aft hinge 
bolt assembly in an NLG aft door while the airplane is in flight, which 
could lead to an in-flight loss of an NLG aft door, and damage to the 
airplane.

DATES: We must receive comments on this proposed AD by October 14, 
2016.

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 NPRM, 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 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-2016-
9052; 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: 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.

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-2016-9052; 
Directorate Identifier 2016-NM-080-AD'' at the beginning of

[[Page 59547]]

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 AD 
2016-0100, dated May 24, 2016 (referred to after this as the Mandatory 
Continuing Airworthiness Information, or ``the MCAI''), to correct an 
unsafe condition for all Airbus Model A300 series airplanes; Model A300 
B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R 
Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Model A310 series airplanes. The MCAI states:

    An occurrence has been reported of failure of a nose landing 
gear (NLG) door aft hinge bolt assembly, Part Number (P/N) 
A53612600000. The result of laboratory investigations revealed that 
the aft hinge bolt rupture was initiated by fatigue crack 
development in the under head radius of the bolt, due to the lack of 
radius roll over and in combination with a non-optimised design.
    This condition, if not detected and corrected, could lead to in-
flight loss of an aft NLG door, possibly resulting in damage to the 
aeroplane and injury to persons on the ground.
    Prompted by these findings, Airbus developed a new design aft 
hinge bolt assembly P/N A53612713000, introduced as Airbus 
modification (mod) 13741, to replace the existing bolt P/N 
A53612600000. Since the introduction of that mod, additional stress 
calculations demonstrated that the new bolt assembly, P/N 
A53612713000, cannot sustain fatigue loads up to the design Limit of 
Validity (LOV) of the affected aeroplanes.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A300-53-0397, SB A310-53-2144 and SB A300-53-
6186, to provide instructions for the repetitive replacement of the 
affected post-mod 13741 P/N A53612713000 aft hinge bolts.
    For the reasons described above, this [EASA] AD requires the 
replacement of all P/N A53612600000 aft hinge bolt assemblies, 
installed on the left hand (LH) and right hand (RH) NLG aft doors, 
with post-mod 13741 P/N A53612713000 aft hinge bolt assemblies, and, 
subsequently, the implementation of a life limit for those new bolt 
assemblies.

    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-2016-
9052.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Airbus Service Bulletin A300-53-0396, dated November 25, 
2015.
     Airbus Service Bulletin A300-53-0397, dated January 18, 
2016.
     Airbus Service Bulletin A300-53-6182, dated November 17, 
2015.
     Airbus Service Bulletin A300-53-6186, dated January 18, 
2016.
     Airbus Service Bulletin A310-53-2142, dated November 17, 
2015.
     Airbus Service Bulletin A310-53-2144, dated January 18, 
2016.

The service information describes procedures for replacement of the aft 
hinge bolt assembly in the left and right NLG aft doors, with new aft 
hinge bolt assemblies.
    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.

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 157 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per      Cost on  U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Replacement.........................  9 work-hours x $85 per           $2,000           $2,765         $434,105
                                       hour = $765.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 59548]]

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-2016-9052; Directorate Identifier 2016-NM-
080-AD.

(a) Comments Due Date

    We must receive comments by October 14, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1) through (c)(6) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and 
B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (3) Model A300 B4-605R and B4-622R airplanes.
    (4) Model A300 F4-605R and F4-622R airplanes.
    (5) Model A300 C4-605R Variant F airplanes.
    (6) Model A310-203, -204, -221, -222, -304, -322, -324, and -325 
airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of failure of an aft hinge bolt 
assembly in the nose landing gear (NLG) aft doors. We are issuing 
this AD to prevent failure of an aft hinge bolt assembly in an NLG 
aft door while the airplane is in flight, which could lead to an in-
flight loss of an NLG aft door, and damage to the airplane.

(f) Compliance

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

(g) Replace the Aft Hinge Bolt Assemblies Having Part Number (P/N) 
A53612600000

    Before the accumulation of 10,000 total flight cycles since 
first flight of the airplane, or within 2,000 flight cycles after 
the effective date of this AD, whichever occurs later, replace each 
aft hinge bolt assembly having P/N A53612600000 on the left and 
right NLG aft doors, with a new hinge bolt assembly having P/N 
A53612713000, in accordance with the Accomplishment Instructions of 
the applicable service information identified in paragraph (g)(1), 
(g)(2), or (g)(3) of this AD.
    (1) Airbus Service Bulletin A300-53-0396, dated November 25, 
2015.
    (2) Airbus Service Bulletin A310-53-2142, dated November 17, 
2015.
    (3) Airbus Service Bulletin A300-53-6182, dated November 17, 
2015.

(h) Replace the Aft Hinge Bolt Assemblies Having P/N A53612713000

    Within 10,000 flight cycles after modification of an airplane as 
required by paragraph (g) of this AD, replace each aft hinge bolt 
assembly having P/N A53612713000 on the left and right aft NLG 
doors, with a new aft hinge bolt assembly having P/N A53612713000 on 
the left and right NLG aft doors, in accordance with the 
Accomplishment Instructions of the applicable service information 
specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD. Repeat 
the replacement thereafter at intervals not to exceed 10,000 flight 
cycles.
    (1) Airbus Service Bulletin A300-53-0397, dated January 18, 
2016.
    (2) Airbus Service Bulletin A310-53-2144, dated January 18, 
2016.
    (3) Airbus Service Bulletin A300-53-6186, dated January 18, 
2016.

(i) Parts Installation Prohibition (P/N A53612600000)

    After modification of an airplane NLG aft door as required by 
paragraph (g) of this AD, do not install an aft hinge bolt assembly 
having P/N A53612600000 on any NLG aft door of that airplane.

(j) Parts Installation Limitation (P/N A53612713000)

    After removal of an aft hinge bolt assembly having P/N 
A53612713000 from an airplane aft NLG door, as required by paragraph 
(h) of this AD, do not install an aft hinge bolt assembly having 
that part number on any airplane unless it is a new aft hinge bolt 
assembly.

(k) 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-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(l) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2016-0100 dated May 24, 2016, 
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-2016-9052.
    (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 19, 2016.
Dorr M. Anderson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-20699 Filed 8-29-16; 8:45 am]
 BILLING CODE 4910-13-P