Airworthiness Directives; Airbus Airplanes, 23166-23169 [2017-10140]

Download as PDF 23166 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules TABLE 3 TO PARAGRAPH (h) OF THIS AD—COMPLIANCE TIMES FOR INSPECTIONS Repetitive inspection intervals Airplane model Initial inspection FALCON 2000 airplanes ..................... Prior to exceeding 2,000 flight cycles since the airplane’s first flight, or within 1,000 flight cycles after the effective date of this AD, whichever occurs later. Prior to exceeding 1,000 flight cycles since the airplane’s first flight, or within 500 flight cycles after the effective date of this AD, whichever occurs later. FALCON 2000EX airplanes ................ (i) Corrective Action If any discrepancy is found during any inspection required by paragraph (h) of this AD: Before further flight, replace the affected anti-ice piccolo tube with a new or serviceable part, and replace or re-identify the affected wing outboard slat as applicable, in accordance with the Accomplishment Instructions of Dassault Service Bulletin F2000–431, Revision 1, dated June 6, 2016; or Service Bulletin F2000EX–391, Revision 1, dated June 6, 2016; as applicable. (j) Optional Terminating Action Modification of an airplane by installing a new or serviceable anti-ice piccolo tube, and replacing or re-identifying the affected wing outboard slat, terminates the repetitive inspections required by paragraph (h) of this AD, if done in accordance with the Accomplishment Instructions of Dassault Service Bulletin F2000–431, Revision 1, dated June 6, 2016; or Service Bulletin F2000EX–391, Revision 1, dated June 6, 2016; as applicable. nlaroche on DSK30NT082PROD with PROPOSALS (k) Parts Installation Prohibition As of the time specified in paragraph (k)(1) or (k)(2) of this AD, as applicable, no person may install on any airplane an affected antiice piccolo tube or an affected outboard slat. (1) For an airplane that, on the effective date of this AD, has an affected anti-ice piccolo tube or an affected outboard slat installed: Before further flight after modification of that airplane as required by paragraph (i) of this AD. (2) For an airplane that, on the effective date of this AD, does not have an affected anti-ice piccolo tube or an affected outboard slat installed: As of the effective date of this AD. (l) Later-Approved Parts Installation on an airplane of an anti-ice piccolo tube having a part number approved after the effective date of this AD is acceptable for compliance with the requirements of paragraph (i) or paragraph (j) of this AD, as applicable, provided the conditions in paragraphs (l)(1) and (l)(2) of this AD are met. (1) The anti-ice piccolo tube part number must be approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Dassault Aviation’s EASA Design Organization Approval (DOA). (2) The installation of the anti-ice piccolo tube must be accomplished in accordance with a method approved by the Manager, International Branch, ANM–116, Transport VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 Airplane Directorate, FAA; or the EASA; or Dassault Aviation’s EASA DOA. (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 the attention of the person identified in paragraph (n)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOCREQUESTS@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 EASA; or Dassault Aviation’s EASA 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 AD 2016–0149, dated July 25, 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–2017–0475. (2) For more information about this AD, contact Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1137; fax 425–227–1149. (3) For service information identified in this AD, contact Dassault Falcon Jet Corporation, Teterboro Airport, P.O. Box 2000, South Hackensack, NJ 07606; telephone 201–440–6700; Internet http:// www.dassaultfalcon.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. PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 2,000 flight cycles. 1,000 flight cycles. Issued in Renton, Washington, on May 11, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10135 Filed 5–19–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0480; Directorate Identifier 2016–NM–204–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 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 cracking in the door sill area of the aft cargo door. This proposed AD would require repetitive inspections of the aft cargo door lower torsion box area, and corrective actions if necessary. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by July 6, 2017. 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 SUMMARY: E:\FR\FM\22MYP1.SGM 22MYP1 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules 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–2017– 0480; 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–2017–0480; Directorate Identifier 2016–NM–204–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 2016–0241, dated December 6, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus 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: Cracks were found on in-service aeroplane post mod 5438 in the door sill area, from frame (FR) 60 to FR63, including the sill beam flag, lock fitting, door sill web and torsion door panel. Two previous cases with less crack extent were also reported. This condition, if not detected and corrected, could lead to reduced structural integrity of the aeroplane. To address this unsafe condition, Airbus published Inspection Service Bulletin (SB) A310–53–2139 and SB A300–53–6179 to provide inspection instructions for the affected areas. Airbus published also Airbus SB A310–53–2141 and SB A300–53–6181 to provide modification instructions. Further analysis showed that aeroplanes pre-mod 5438, for which one or several lock fittings have been replaced by post mod 10319 lock fittings, could also be affected. Airbus published SB A310–53–2143 and SB 23167 A300–53–6185 to provide inspection instructions. For the reason described above, this [EASA] AD requires repetitive Special Detailed Inspections (SDI) of the aft cargo door lower torsion box area and, depending on findings, accomplishment of applicable corrective action(s). 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–2017– 0480. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A300–53–6185, dated February 11, 2016; and Service Bulletin A310–53– 2143, dated February 11, 2016; which describe, among other actions, repetitive inspections of the aft cargo door sill area for cracking. These documents are distinct since they apply to different airplane models. 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 18 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Labor cost Inspection ............................... nlaroche on DSK30NT082PROD with PROPOSALS Action 12 work-hours × $85 per hour = $1,020 per inspection cycle. We have received no definitive data that would enable us to provide a cost estimate for the on-condition corrective actions specified in this proposed AD. VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 Parts cost Cost per product $0 Cost on U.S. operators $1,020 per inspection cycle ... $18,360 per inspection cycle. 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: PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 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: E:\FR\FM\22MYP1.SGM 22MYP1 23168 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules 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 (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 (2) Model A300 B4–605R and B4–622R airplanes. (3) Model A300 F4–605R and F4–622R airplanes. (4) Model A300 C4–605R Variant F airplanes. (5) Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2017–0480; Directorate Identifier 2016–NM–204–AD. (a) Comments Due Date We must receive comments by July 6, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated in any category; except those on which Airbus Modification 5438 was embodied in production. (1) Model A300 B4–601, B4–603, B4–620, and B4–622 airplanes. This AD was prompted by cracking in the door sill area of the aft cargo door. We are issuing this AD to detect and correct cracking of the door sill area of the aft cargo; such cracking could adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Within the applicable compliance time specified in table 1 to paragraph (g) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the door sill area (including the sill beam flag, lock fitting, door sill web, and torsion door panel) of the aft cargo door lower torsion box area, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 53–6185, dated February 11, 2016; or Service Bulletin A310–53–2143, dated February 11, 2016; as applicable. Repeat the HFEC inspection thereafter at intervals not to exceed 15,100 flight cycles. TABLE 1 TO PARAGRAPH (g) OF THIS AD—INITIAL INSPECTION Airplane configuration Compliance time Repaired (date known), post-Airbus Modification 10319 lock fittings installed using Airbus Structural Repair Manual (SRM) Task 51–72–00. Repaired (no record, date unknown), post-Airbus Modification 10319 lock fittings installed using Airbus SRM Task 51–72–00. Non-repaired airplane, or airplane repaired with pre-Airbus Modification 10319 lock fittings using Airbus SRM Task 51–72–00. Before exceeding 25,800 flight cycles since the lock fitting replacement. Before exceeding 25,800 flight cycles from November 1, 1996. No inspection required. nlaroche on DSK30NT082PROD with PROPOSALS (h) Corrective Action (i) Terminating Action If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–53–6185, dated February 11, 2016; or Service Bulletin A310– 53–2143, dated February 11, 2016; as applicable; except, where Airbus Service Bulletin A300–53–6185, dated February 11, 2016; or Service Bulletin A310–53–2143, dated February 11, 2016; specifies to contact Airbus for appropriate action, and specifies that action as ‘‘RC’’ (Required for Compliance), before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (j)(2) of this AD. Repair of an airplane as required by paragraph (h) of this AD constitutes terminating action for the repetitive inspections required by paragraph (g) of this AD for that airplane. VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 (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 PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 to the manager of the International Branch, send it to the attention of the person identified in paragraph (k)(2) of this AD. Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). If approved by E:\FR\FM\22MYP1.SGM 22MYP1 Federal Register / Vol. 82, No. 97 / Monday, May 22, 2017 / Proposed Rules nlaroche on DSK30NT082PROD with PROPOSALS 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. VerDate Sep<11>2014 12:41 May 19, 2017 Jkt 241001 (k) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016–0241, dated December 6, 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–2017–0480. (2) For more information about this AD, 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. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office—EAW, 1 Rond Point Maurice PO 00000 Frm 00017 Fmt 4702 Sfmt 9990 23169 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 May 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017–10140 Filed 5–19–17; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\22MYP1.SGM 22MYP1

Agencies

[Federal Register Volume 82, Number 97 (Monday, May 22, 2017)]
[Proposed Rules]
[Pages 23166-23169]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10140]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0480; Directorate Identifier 2016-NM-204-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 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 cracking in the door sill 
area of the aft cargo door. This proposed AD would require repetitive 
inspections of the aft cargo door lower torsion box area, and 
corrective actions if necessary. We are proposing this AD to address 
the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by July 6, 2017.

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

[[Page 23167]]

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-2017-
0480; 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-2017-0480; 
Directorate Identifier 2016-NM-204-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 2016-0241, dated December 6, 2016 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus 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:

    Cracks were found on in-service aeroplane post mod 5438 in the 
door sill area, from frame (FR) 60 to FR63, including the sill beam 
flag, lock fitting, door sill web and torsion door panel. Two 
previous cases with less crack extent were also reported.
    This condition, if not detected and corrected, could lead to 
reduced structural integrity of the aeroplane.
    To address this unsafe condition, Airbus published Inspection 
Service Bulletin (SB) A310-53-2139 and SB A300-53-6179 to provide 
inspection instructions for the affected areas. Airbus published 
also Airbus SB A310-53-2141 and SB A300-53-6181 to provide 
modification instructions.
    Further analysis showed that aeroplanes pre-mod 5438, for which 
one or several lock fittings have been replaced by post mod 10319 
lock fittings, could also be affected. Airbus published SB A310-53-
2143 and SB A300-53-6185 to provide inspection instructions.
    For the reason described above, this [EASA] AD requires 
repetitive Special Detailed Inspections (SDI) of the aft cargo door 
lower torsion box area and, depending on findings, accomplishment of 
applicable corrective action(s).

    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-2017-
0480.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-53-6185, dated February 
11, 2016; and Service Bulletin A310-53-2143, dated February 11, 2016; 
which describe, among other actions, repetitive inspections of the aft 
cargo door sill area for cracking. These documents are distinct since 
they apply to different airplane models. 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 18 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
              Action                    Labor cost        Parts cost      Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.......................  12 work-hours x $85              $0  $1,020 per           $18,360 per
                                    per hour = $1,020                    inspection cycle.    inspection cycle.
                                    per inspection
                                    cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition corrective 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:

[[Page 23168]]

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-2017-0480; Directorate Identifier 2016-NM-
204-AD.

(a) Comments Due Date

    We must receive comments by July 6, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD; certificated 
in any category; except those on which Airbus Modification 5438 was 
embodied in production.
    (1) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes.
    (2) Model A300 B4-605R and B4-622R airplanes.
    (3) Model A300 F4-605R and F4-622R airplanes.
    (4) Model A300 C4-605R Variant F airplanes.
    (5) 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 cracking in the door sill area of the 
aft cargo door. We are issuing this AD to detect and correct 
cracking of the door sill area of the aft cargo; such cracking could 
adversely affect the structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive Inspections

    Within the applicable compliance time specified in table 1 to 
paragraph (g) of this AD: Do a high frequency eddy current (HFEC) 
inspection for cracking of the door sill area (including the sill 
beam flag, lock fitting, door sill web, and torsion door panel) of 
the aft cargo door lower torsion box area, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A300-53-6185, 
dated February 11, 2016; or Service Bulletin A310-53-2143, dated 
February 11, 2016; as applicable. Repeat the HFEC inspection 
thereafter at intervals not to exceed 15,100 flight cycles.

         Table 1 to Paragraph (g) of This AD--Initial Inspection
------------------------------------------------------------------------
         Airplane configuration                  Compliance time
------------------------------------------------------------------------
Repaired (date known), post-Airbus       Before exceeding 25,800 flight
 Modification 10319 lock fittings         cycles since the lock fitting
 installed using Airbus Structural        replacement.
 Repair Manual (SRM) Task 51-72-00.
Repaired (no record, date unknown),      Before exceeding 25,800 flight
 post-Airbus Modification 10319 lock      cycles from November 1, 1996.
 fittings installed using Airbus SRM
 Task 51-72-00.
Non-repaired airplane, or airplane       No inspection required.
 repaired with pre-Airbus Modification
 10319 lock fittings using Airbus SRM
 Task 51-72-00.
------------------------------------------------------------------------

(h) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) of this AD: Before further flight, repair in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-53-6185, dated February 11, 2016; or Service Bulletin 
A310-53-2143, dated February 11, 2016; as applicable; except, where 
Airbus Service Bulletin A300-53-6185, dated February 11, 2016; or 
Service Bulletin A310-53-2143, dated February 11, 2016; specifies to 
contact Airbus for appropriate action, and specifies that action as 
``RC'' (Required for Compliance), before further flight, accomplish 
corrective actions in accordance with the procedures specified in 
paragraph (j)(2) of this AD.

(i) Terminating Action

    Repair of an airplane as required by paragraph (h) of this AD 
constitutes terminating action for the repetitive inspections 
required by paragraph (g) of this AD for that airplane.

(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 manager of the International Branch, send it to the 
attention of the person identified in paragraph (k)(2) of this AD. 
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

[[Page 23169]]

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.

(k) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0241, dated December 6, 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-2017-0480.
    (2) For more information about this AD, 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.
    (3) 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 May 12, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-10140 Filed 5-19-17; 8:45 am]
BILLING CODE 4910-13-P