Airworthiness Directives; Airbus Airplanes, 19509-19511 [2016-07575]

Download as PDF Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0167, dated July 26, 2013, 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 it in Docket No. FAA–2016–5039. (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 March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–07569 Filed 4–4–16; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION joint, which could reduce the structural integrity of the airframe. DATES: We must receive comments on this proposed AD by May 20, 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. Federal Aviation Administration Examining the AD Docket 14 CFR Part 39 You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2016– 5040; 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: [Docket No. FAA–2016–5040; Directorate Identifier 2013–NM–192–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 series airplanes; and 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). This proposed AD was prompted by the determination that certain existing inspection thresholds and intervals must be reduced. This proposed AD would require repetitive detailed inspections for corrosion, and related investigative and corrective actions if necessary. We are proposing this AD to detect and correct corrosion and cracking on the lower wing root Lhorne on DSK5TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 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. PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 19509 FAA–2016–5040; Directorate Identifier 2013–NM–192–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 2013–0230, dated September 24, 2013 (referred to after this as the Mandatory Continuing Airworthiness Information, or ‘‘the MCAI’’), to correct an unsafe condition for certain Airbus Model A300 and A300–600 series airplanes. The MCAI states: Several cases of corrosion on the lower wing root joint, located in the wing bottom skin inboard and outboard of the external lower surface splice, have been reported by operators. This condition, if not detected and corrected, could affect the structural integrity of the airframe. Prompted by these findings, [Directorate General for Civil Aviation] (DGAC) France issued AD 1997–006–210 [which corresponds to FAA AD 98–21–34, Amendment 39–10842 (63 FR 55524, October 16, 1998)] to require repetitive inspections to detect the presence of corrosion and prevent crack propagation at the wing bottom skin, inboard and outboard of the Rib 1 external lower surface splice, between Frame (FR) 40 and FR47. DGAC France * * * issued [an AD] to expand the choice of applicable Service Bulletins (SB). [The] DGAC France AD * * * was issued to allow A300–600 operators to use Revision 04 of Airbus SB A300–57–6047, converting flight cycles/‘‘Fatigue rating’’ into flight cycles (FC)/flight hours (FH). Subsequently, Airbus modification 10599 was developed to improve the corrosion behaviour of the area. This improvement allowed refining the inspection programme of the A300–600 aeroplane. For postmodification 10599 A300–600 aeroplanes, the application of the Maintenance Review Board Report (MRBR) inspection tasks was deemed sufficient for maintaining an adequate level of safety on these aeroplanes. Consequently, EASA issued AD 2008–0208 [http://ad.easa.europa.eu/blob/easa_ad_ 2008_0208_R2.pdf/AD_2008-0208R2_1] (later revised), retaining the requirements of [a] DGAC France AD * * *, which was superseded, to require the use of Airbus SB A300–57–6047 Revision 05 for the inspections and to exclude post-modification E:\FR\FM\05APP1.SGM 05APP1 19510 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules 10599 A300–600 aeroplanes from the Applicability. Since EASA AD 2008–0208R1 was issued, a fleet survey and updated Fatigue and Damage Tolerance analyses have been performed in order to substantiate the second A300–600 Extended Service Goal (ESG2) exercise. The results of these analyses determined that the threshold and interval must be reduced to allow timely detection of these cracks and the accomplishment of an applicable corrective action. For the reasons described above, this [EASA] AD takes over and retains the requirements for A300 and A300–600 aeroplanes from EASA AD 2008–0208R1 (which has been revised, remaining applicable only to A310 aeroplanes) and requires accomplishment of the inspections within the new thresholds and intervals. Required actions include repetitive detailed inspections for corrosion of the rib 1 external lower surface splice between FR40 and FR47, and repetitive fatigue inspections for cracking of the fasteners and on the surface of the forward and aft lower surface panels if necessary, and corrective actions (including application of new protective coating, removal of corrosion, and measurement of the reworked depth) if necessary. 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– 5040. Related Rulemaking AD 98–21–34, Amendment 39–10842 (63 FR 55524, October 16, 1998) (‘‘AD 98–21–34’’), applies to all Model A300, A300–600, and A310 series airplanes. This NPRM proposes to apply to only certain Model A300 and A300–600 series airplanes. The actions in this proposed AD are the same as those required by AD 98–21–34, but with certain revised compliance times. Accomplishment of the initial inspection specified in this proposed AD would terminate the repetitive inspection requirements of AD 98–21– 34 for the affected airplanes. Certain modified Model A300–600 series airplanes would not be subject to the inspection requirements of this AD, and would no longer be subject to the repetitive inspection requirements of AD 98–21–34. Lhorne on DSK5TPTVN1PROD with PROPOSALS Related Service Information Under 1 CFR Part 51 We reviewed Service Bulletin A300– 57–0204, Revision 01, dated April 2, 1999; and Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011. This service information describes procedures for repetitive detailed inspections for corrosion of the rib 1 external lower VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 surface splice between FR40 and FR47, repetitive fatigue inspections for cracking of the fasteners and on the surface of the forward and aft lower surface panels if necessary, and corrective actions (including application of new protective coating, removal of corrosion, and measurement of the reworked depth) 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. 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 29 airplanes of U.S. registry. We also estimate that it would take about 8 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $19,270, or $680 per product. In addition, we estimate that any necessary follow-on actions would take about 8 work-hours, for a cost of $680 per product. We have no way of determining the number of aircraft that might need these actions. 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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Airbus: Docket No. FAA–2016–5040; Directorate Identifier 2013–NM–192–AD. (a) Comments Due Date We must receive comments by May 20, 2016. (b) Affected ADs This AD affects AD 98–21–34, Amendment 39–10842 (63 FR 55524, October 16, 1998) (‘‘AD 98–21–34’’). (c) Applicability This AD applies to all Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. E:\FR\FM\05APP1.SGM 05APP1 Federal Register / Vol. 81, No. 65 / Tuesday, April 5, 2016 / Proposed Rules (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, B4–622, B4–605R, B4–622R, F4–605R, F4– 622R, and C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by the determination that certain existing inspection thresholds and intervals must be reduced. We are issuing this AD to detect and correct corrosion and cracking on the lower wing root joint, which could reduce the structural integrity of the airframe. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Airplanes Excluded From Requirements of This AD and AD 98–21–34 For airplanes identified in paragraph (c)(2) of this AD on which Airbus modification 10599 has been incorporated: (1) No action is required by this AD; and (2) As of the effective date of this AD, the actions specified in AD 98–21–34 are no longer required. Lhorne on DSK5TPTVN1PROD with PROPOSALS (h) Inspection and Corrective Actions Within 60 months since the airplane’s first flight, or within 60 months since accomplishment of the last inspection specified in Airbus Service Bulletin A300– 57–0204 or A300–57–6047, whichever occurs later: Do a detailed inspection for corrosion of the rib 1 external lower surface splice between frame (FR)40 and FR47, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– 57–0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011; as applicable. Repeat the inspection thereafter at intervals not to exceed 60 months. Accomplishment of the initial inspection required by this paragraph terminates the requirements of AD 98–21–34 for Model A300 and A300–600 series airplanes. (i) Corrective Actions for Corrosion If any corrosion is found during any inspection required by paragraph (h) of this AD, do the actions specified in paragraph (i)(1) and (i)(2) of this AD. (1) Before further flight, do all applicable corrective actions in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300–57–0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(1) of this AD. (2) At the applicable time specified in paragraph (i)(2)(i) or (i)(2)(ii) of this AD, except as required by paragraph (j)(2) of this AD: Do fatigue inspections to detect cracks of the fasteners and on the surface of the forward and aft lower surface panels, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300– VerDate Sep<11>2014 13:17 Apr 04, 2016 Jkt 238001 57–0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011; as applicable. Repeat the fatigue inspections thereafter at the applicable interval specified in paragraph B.(5) of Airbus Service Bulletin A300–57–0204, Revision 01, dated April 2, 1999; or Figure A–FBGAA, Sheet 01, of Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011; as applicable; except as required by paragraph (j)(2) of this AD. If any cracking is found during any fatigue inspection required by this paragraph: Before further flight, repair using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus’s EASA Design Organization Approval (DOA). (i) For Model A300 series airplanes: Do the initial inspection at the applicable time specified in paragraph B.(5) of Airbus Service Bulletin A300–57–0204, Revision 01, dated April 2, 1999. (ii) For Model A300–600 series airplanes: Do the initial inspection at the later of the times specified in paragraphs (i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD. (A) At the applicable time specified in Figure A–FBGAA, Sheet 01, of Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011. (B) Within 500 flight cycles or 1,050 flight hours after the effective date of this AD, whichever occurs first, without exceeding the time specified in paragraph (i)(2)(ii)(A) of this AD. (j) Exceptions to Service Bulletin Specifications (1) Where Airbus Service Bulletin A300– 57–0204, Revision 01, dated April 2, 1999; or Airbus Service Bulletin A300–57–6047, Revision 06, dated October 17, 2011; specifies to contact Airbus for appropriate corrective action, this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (2) Where Airbus Service Bulletin A300– 57–6047, Revision 06, dated October 17, 2011, specifies to contact Airbus for the appropriate threshold or repetitive interval, this AD requires that the compliance time be determined using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or EASA; or Airbus’s EASA DOA. (k) Calculating Average Flight Time (AFT) The accumulated flight hours (counted from the takeoff up to the landing) divided by the number of accumulated flight cycles is the AFT per flight cycle. (l) Credit for Previous Actions This paragraph provides credit for the inspections and corrective actions required by paragraphs (h) and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraphs (l)(1) through (l)(3) of this AD. (1) Airbus Service Bulletin A300–57–6047, Revision 02, dated April 2, 1999, which is not incorporated by reference in this AD. PO 00000 Frm 00012 Fmt 4702 Sfmt 9990 19511 (2) Airbus Service Bulletin A300–57–6047, Revision 03, dated September 28, 1999, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A300–57–6047, Revision 05, dated May 27, 2008, which is not incorporated by reference in this AD. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: 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: 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 actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM– 116, Transport Airplane Directorate, FAA; or the EASA; or Airbus’s EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2013–0230, dated September 24, 2013, 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–2016–5040. (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 March 24, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016–07575 Filed 4–4–16; 8:45 am] BILLING CODE 4910–13–P E:\FR\FM\05APP1.SGM 05APP1

Agencies

[Federal Register Volume 81, Number 65 (Tuesday, April 5, 2016)]
[Proposed Rules]
[Pages 19509-19511]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-07575]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-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 series airplanes; and 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). This 
proposed AD was prompted by the determination that certain existing 
inspection thresholds and intervals must be reduced. This proposed AD 
would require repetitive detailed inspections for corrosion, and 
related investigative and corrective actions if necessary. We are 
proposing this AD to detect and correct corrosion and cracking on the 
lower wing root joint, which could reduce the structural integrity of 
the airframe.

DATES: We must receive comments on this proposed AD by May 20, 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-
5040; 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-2016-5040; 
Directorate Identifier 2013-NM-192-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 2013-0230, dated September 24, 2013 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 and A300-600 series airplanes. The MCAI states:

    Several cases of corrosion on the lower wing root joint, located 
in the wing bottom skin inboard and outboard of the external lower 
surface splice, have been reported by operators.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    Prompted by these findings, [Directorate General for Civil 
Aviation] (DGAC) France issued AD 1997-006-210 [which corresponds to 
FAA AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998)] 
to require repetitive inspections to detect the presence of 
corrosion and prevent crack propagation at the wing bottom skin, 
inboard and outboard of the Rib 1 external lower surface splice, 
between Frame (FR) 40 and FR47.
    DGAC France * * * issued [an AD] to expand the choice of 
applicable Service Bulletins (SB). [The] DGAC France AD * * * was 
issued to allow A300-600 operators to use Revision 04 of Airbus SB 
A300-57-6047, converting flight cycles/``Fatigue rating'' into 
flight cycles (FC)/flight hours (FH).
    Subsequently, Airbus modification 10599 was developed to improve 
the corrosion behaviour of the area. This improvement allowed 
refining the inspection programme of the A300-600 aeroplane. For 
post-modification 10599 A300-600 aeroplanes, the application of the 
Maintenance Review Board Report (MRBR) inspection tasks was deemed 
sufficient for maintaining an adequate level of safety on these 
aeroplanes.
    Consequently, EASA issued AD 2008-0208 [http://ad.easa.europa.eu/blob/easa_ad_2008_0208_R2.pdf/AD_2008-0208R2_1] 
(later revised), retaining the requirements of [a] DGAC France AD * 
* *, which was superseded, to require the use of Airbus SB A300-57-
6047 Revision 05 for the inspections and to exclude post-
modification

[[Page 19510]]

10599 A300-600 aeroplanes from the Applicability.
    Since EASA AD 2008-0208R1 was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of these analyses determined that the 
threshold and interval must be reduced to allow timely detection of 
these cracks and the accomplishment of an applicable corrective 
action.
    For the reasons described above, this [EASA] AD takes over and 
retains the requirements for A300 and A300-600 aeroplanes from EASA 
AD 2008-0208R1 (which has been revised, remaining applicable only to 
A310 aeroplanes) and requires accomplishment of the inspections 
within the new thresholds and intervals.

    Required actions include repetitive detailed inspections for 
corrosion of the rib 1 external lower surface splice between FR40 and 
FR47, and repetitive fatigue inspections for cracking of the fasteners 
and on the surface of the forward and aft lower surface panels if 
necessary, and corrective actions (including application of new 
protective coating, removal of corrosion, and measurement of the 
reworked depth) if necessary. 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-2016-5040.

Related Rulemaking

    AD 98-21-34, Amendment 39-10842 (63 FR 55524, October 16, 1998) 
(``AD 98-21-34''), applies to all Model A300, A300-600, and A310 series 
airplanes. This NPRM proposes to apply to only certain Model A300 and 
A300-600 series airplanes. The actions in this proposed AD are the same 
as those required by AD 98-21-34, but with certain revised compliance 
times. Accomplishment of the initial inspection specified in this 
proposed AD would terminate the repetitive inspection requirements of 
AD 98-21-34 for the affected airplanes. Certain modified Model A300-600 
series airplanes would not be subject to the inspection requirements of 
this AD, and would no longer be subject to the repetitive inspection 
requirements of AD 98-21-34.

Related Service Information Under 1 CFR Part 51

    We reviewed Service Bulletin A300-57-0204, Revision 01, dated April 
2, 1999; and Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011. This service information describes procedures for 
repetitive detailed inspections for corrosion of the rib 1 external 
lower surface splice between FR40 and FR47, repetitive fatigue 
inspections for cracking of the fasteners and on the surface of the 
forward and aft lower surface panels if necessary, and corrective 
actions (including application of new protective coating, removal of 
corrosion, and measurement of the reworked depth) 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.

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 29 airplanes of U.S. 
registry. We also estimate that it would take about 8 work-hours per 
product to comply with the basic requirements of this proposed AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of this proposed AD on U.S. operators to be $19,270, 
or $680 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours, for a cost of $680 per product. We have no way 
of determining the number of aircraft that might need these actions.

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-2016-5040; Directorate Identifier 2013-NM-
192-AD.

(a) Comments Due Date

    We must receive comments by May 20, 2016.

(b) Affected ADs

    This AD affects AD 98-21-34, Amendment 39-10842 (63 FR 55524, 
October 16, 1998) (``AD 98-21-34'').

(c) Applicability

    This AD applies to all Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.

[[Page 19511]]

    (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, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by the determination that certain existing 
inspection thresholds and intervals must be reduced. We are issuing 
this AD to detect and correct corrosion and cracking on the lower 
wing root joint, which could reduce the structural integrity of the 
airframe.

(f) Compliance

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

(g) Airplanes Excluded From Requirements of This AD and AD 98-21-34

    For airplanes identified in paragraph (c)(2) of this AD on which 
Airbus modification 10599 has been incorporated:
    (1) No action is required by this AD; and
    (2) As of the effective date of this AD, the actions specified 
in AD 98-21-34 are no longer required.

(h) Inspection and Corrective Actions

    Within 60 months since the airplane's first flight, or within 60 
months since accomplishment of the last inspection specified in 
Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever 
occurs later: Do a detailed inspection for corrosion of the rib 1 
external lower surface splice between frame (FR)40 and FR47, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed 60 months. Accomplishment of the initial inspection required 
by this paragraph terminates the requirements of AD 98-21-34 for 
Model A300 and A300-600 series airplanes.

(i) Corrective Actions for Corrosion

    If any corrosion is found during any inspection required by 
paragraph (h) of this AD, do the actions specified in paragraph 
(i)(1) and (i)(2) of this AD.
    (1) Before further flight, do all applicable corrective actions 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable; except as required by paragraph (j)(1) of this AD.
    (2) At the applicable time specified in paragraph (i)(2)(i) or 
(i)(2)(ii) of this AD, except as required by paragraph (j)(2) of 
this AD: Do fatigue inspections to detect cracks of the fasteners 
and on the surface of the forward and aft lower surface panels, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable. Repeat the fatigue inspections thereafter at the 
applicable interval specified in paragraph B.(5) of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Figure 
A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-57-6047, Revision 
06, dated October 17, 2011; as applicable; except as required by 
paragraph (j)(2) of this AD. If any cracking is found during any 
fatigue inspection required by this paragraph: Before further 
flight, repair using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 
European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA).
    (i) For Model A300 series airplanes: Do the initial inspection 
at the applicable time specified in paragraph B.(5) of Airbus 
Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999.
    (ii) For Model A300-600 series airplanes: Do the initial 
inspection at the later of the times specified in paragraphs 
(i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
    (A) At the applicable time specified in Figure A-FBGAA, Sheet 
01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011.
    (B) Within 500 flight cycles or 1,050 flight hours after the 
effective date of this AD, whichever occurs first, without exceeding 
the time specified in paragraph (i)(2)(ii)(A) of this AD.

(j) Exceptions to Service Bulletin Specifications

    (1) Where Airbus Service Bulletin A300-57-0204, Revision 01, 
dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, 
Revision 06, dated October 17, 2011; specifies to contact Airbus for 
appropriate corrective action, this AD requires repair before 
further flight using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA.
    (2) Where Airbus Service Bulletin A300-57-6047, Revision 06, 
dated October 17, 2011, specifies to contact Airbus for the 
appropriate threshold or repetitive interval, this AD requires that 
the compliance time be determined using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Calculating Average Flight Time (AFT)

    The accumulated flight hours (counted from the takeoff up to the 
landing) divided by the number of accumulated flight cycles is the 
AFT per flight cycle.

(l) Credit for Previous Actions

    This paragraph provides credit for the inspections and 
corrective actions required by paragraphs (h) and (i) of this AD, if 
those actions were performed before the effective date of this AD 
using the applicable service information specified in paragraphs 
(l)(1) through (l)(3) of this AD.
    (1) Airbus Service Bulletin A300-57-6047, Revision 02, dated 
April 2, 1999, which is not incorporated by reference in this AD.
    (2) Airbus Service Bulletin A300-57-6047, Revision 03, dated 
September 28, 1999, which is not incorporated by reference in this 
AD.
    (3) Airbus Service Bulletin A300-57-6047, Revision 05, dated May 
27, 2008, which is not incorporated by reference in this AD.

(m) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it to ATTN: 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. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; 
or Airbus's EASA DOA. If approved by the DOA, the approval must 
include the DOA-authorized signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2013-0230, dated September 24, 
2013, 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-2016-5040.
    (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 March 24, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07575 Filed 4-4-16; 8:45 am]
BILLING CODE 4910-13-P