82 FR 13405 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 47 (March 13, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 47 (March 13, 2017)
| Page Range | 13405-13407 | |
| FR Document | 2017-03032 |
[Federal Register Volume 82, Number 47 (Monday, March 13, 2017)] [Proposed Rules] [Pages 13405-13407] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-03032] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Proposed Rules [[Page 13405]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9572; Directorate Identifier 2016-NM-151-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2014-08- 02 for certain Airbus Model A300 B4-600 and A300 B4-600R series airplanes. AD 2014-08-02 requires modifying the profile of stringer run-outs of both wings, including a high frequency eddy current (HFEC) inspection of the fastener holes for defects, and repairs if necessary. Since we issued AD 2014-08-02, further analysis in the context of widespread fatigue damage (WFD) concluded that a shorter compliance time is necessary to meet specified requirements to address WFD. This proposed AD would retain the actions required by AD 2014-08-02 and would revise the compliance times. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by April 27, 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 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 [email protected]; 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- 9572; 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-2016-9572; Directorate Identifier 2016-NM-151-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 Fatigue damage can occur locally, in small areas or structural design details, or globally, in widespread areas. Multiple-site damage is widespread damage that occurs in a large structural element such as a single rivet line of a lap splice joining two large skin panels. Widespread damage can also occur in multiple elements such as adjacent frames or stringers. Multiple-site damage and multiple-element damage cracks are typically too small initially to be reliably detected with normal inspection methods. Without intervention, these cracks will grow, and eventually compromise the structural integrity of the airplane. This condition is known as widespread fatigue damage. It is associated with general degradation of large areas of structure with similar structural details and stress levels. As an airplane ages, WFD will likely occur, and will certainly occur if the airplane is operated long enough without any intervention. The FAA's WFD final rule (75 FR 69746, November 15, 2010) became effective on January 14, 2011. The WFD rule requires certain actions to prevent structural failure due to WFD throughout the operational life of certain existing transport category airplanes and all of these airplanes that will be certificated in the future. For existing and future airplanes subject to the WFD rule, the rule requires that design approval holders (DAHs) establish a limit of validity (LOV) of the engineering data that support the structural maintenance program. Operators affected by the WFD rule may not fly an airplane beyond its LOV, unless an extended LOV is approved. The WFD rule (75 FR 69746, November 15, 2010) does not require identifying and developing maintenance actions if the DAHs can show that such actions are not necessary to prevent WFD before the airplane reaches the LOV. Many LOVs, however, do depend on accomplishment of future maintenance actions. As stated in the WFD rule, any maintenance actions necessary to reach the LOV will be mandated by airworthiness directives through separate rulemaking actions. [[Page 13406]] In the context of WFD, this action is necessary to enable DAHs to propose LOVs that allow operators the longest operational lives for their airplanes, and still ensure that WFD will not occur. This approach allows for an implementation strategy that provides flexibility to DAHs in determining the timing of service information development (with FAA approval), while providing operators with certainty regarding the LOV applicable to their airplanes. On April 2, 2014, we issued AD 2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014) (``AD 2014-08-02''), for certain Airbus Model A300 B4-600 and A300 B4-600R series airplanes. AD 2014-08-02 was prompted by reports of cracks found in certain bottom wing skin stringers during full-scale fatigue testing and in service. AD 2014-08- 02 requires modifying the profile of stringer run-outs of both wings, including a high frequency eddy current inspection of the fastener holes for defects, and repairs if necessary. We issued AD 2014-08-02 to prevent cracking in the bottom wing skin stringers, which could result in reduced structural integrity of the wings. Since we issued AD 2014-08-02, further analysis in the context of WFD concluded that a shorter compliance time is necessary to meet specified requirements to address WFD. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2016-0174, dated August 30, 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 and A300 B4-600R series airplanes. The MCAI states: During full-scale fatigue testing, cracks were detected in the bottom wing skin stringers at Rib 14. In addition, operators have also reported finding cracks in the same area on in-service aeroplanes. This condition, if not detected and corrected, could impair the structural integrity of the wings. Additional analysis results showed that the improved design of the stringer run-out was necessary for aeroplanes operating beyond the Extended Service Goal 1. To address this unsafe condition, Airbus issued Service Bulletin (SB) A300-57-6046 Revision 01 to provide modification instructions, and EASA issued AD 2013-0008 (later revised) [which corresponds to FAA AD 2014-08-02], to require the removal of the stringer end run- out plate at stringer 19 on the bottom wing skin and a re-profiling modification of the stringers 10, 11, 12, 17 and 19. Since that [EASA] AD was issued, further analysis in the context of Widespread Fatigue Damage (WFD), concluded that a threshold reduction is necessary to meet the WFD requirements. Consequently, Airbus revised SB A300-57-6046 accordingly (now at Revision 03). For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2013-0008R1, which is superseded, but reduces the modification threshold, and introduces a pre-mod High Frequency Eddy Current (HFEC) inspection. 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- 9572. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A300-57-6046, Revision 03, including Appendix 01, dated February 4, 2015. The service information describes procedures to modify the profile of stringer run-outs of both wings, including a HFEC inspection of the fastener holes for defects, and repairs. It also describes new compliance times for completing the modifications. 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. The actions required by AD 2014-08-02, and retained in this proposed AD, take about 63 work-hours per product, at an average labor rate of $85 per work-hour. Required parts cost about $2,360 per product. Based on these figures (accounting for updated work-hour and parts cost estimates), the estimated cost of this proposed AD on U.S. operators is $7,715 per product. We have received no definitive data that would enable us to provide cost estimates for any on-condition actions specified in this proposed AD. We have no way of determining the number of aircraft that might need this repair. 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: [[Page 13407]] Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014), and adding the following new AD: Airbus: Docket No. FAA-2016-9572; Directorate Identifier 2016-NM- 151-AD. (a) Comments Due Date We must receive comments by April 27, 2017. (b) Affected ADs This AD replaces AD 2014-08-02, Amendment 39-17826 (79 FR 21392, April 16, 2014) (``AD 2014-08-02''). (c) Applicability This AD applies to Airbus Model A300-B4-601, B4-603, B4-620, and B4-622 airplanes, and Model A300-B4-605R and B4-622R airplanes, certificated in any category, except airplanes on which Airbus Modification 10324 or 10325 has been embodied in production. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the wing skin stringers are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent cracking in the bottom wing skin stringers, which could result in reduced structural integrity of the wings. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Modification of Rib 14, With Revised Compliance Time and Service Information This paragraph restates the requirements of paragraph (g) of AD 2014-08-02, with revised compliance time and service information. At the time specified in paragraph (g)(1) or (g)(2) of this AD, whichever occurs earlier, modify the profile of stringer run-outs at rib 14 of both wings, including a high frequency eddy current inspection of the fastener holes for defects and all applicable repairs, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-6046, Revision 02, dated June 21, 2013; or Revision 03, including Appendix 01, dated February 4, 2015; except as required by paragraph (h) of this AD. Do all applicable repairs before further flight. As of the effective date of this AD, only Airbus Service Bulletin A300-57-6046, Revision 03, including Appendix 01, dated February 4, 2015, may be used. (1) Before the accumulation of 42,500 total flight cycles, or within 2,000 flight cycles after May 21, 2014 (the effective date of AD 2014-08-02), whichever occurs later. (2) Before the accumulation of 30,000 total flight cycles, or within 2,000 flight cycles after the effective date of this AD, whichever occurs later. (h) Retained Exception to the Service Information, With Revised Service Information This paragraph restates the requirements of paragraph (h) of AD 2014-08-02, with revised service information. (1) Where Airbus Mandatory Service Bulletin A300-57-6046, Revision 02, dated June 21, 2013, specifies to contact Airbus for repair instructions, this AD requires contacting the Manager, ANM- 116, International Branch, Transport Airplane Directorate, FAA, or the European Aviation Safety Agency (EASA) (or its delegated agent) for repair instructions and doing those repairs before further flight. (2) Where Airbus Service Bulletin A300-57-6046, Revision 03, including Appendix 01, dated February 4, 2015, specifies to contact Airbus for appropriate action: Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (j)(2) of this AD. (i) Credit for Previous Actions This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (i)(1), (i)(2), or (i)(3) of this AD. (1) Airbus Service Bulletin A300-57-6046, Revision 01, dated April 18, 2011, which is not incorporated by reference in this AD. (2) Airbus Service Bulletin A300-57-6046, dated January 18, 1994, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A300-57-6046, Revision 02, dated June 21, 2013, which was incorporated by reference in AD 2014-08-02. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; fax 425-227-1149. Information may be emailed to: [email protected]. 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: As of the effective date of this AD, 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): Except as required by paragraph (h) of this AD: 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 Airworthiness Directive 2016-0174, dated August 30, 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-2016-9572. (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 [email protected]; 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 January 12, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-03032 Filed 3-10-17; 8:45 am] BILLING CODE 4910-13-P
![13405
Proposed Rules Federal Register
Vol. 82, No. 47
Monday, March 13, 2017
This section of the FEDERAL REGISTER p.m., Monday through Friday, except will also post a report summarizing each
contains notices to the public of the proposed Federal holidays. substantive verbal contact we receive
issuance of rules and regulations. The For service information identified in about this proposed AD.
purpose of these notices is to give interested this NPRM, contact Airbus SAS,
persons an opportunity to participate in the Discussion
Airworthiness Office—EAW, 1 Rond
rule making prior to the adoption of the final
Point Maurice Bellonte, 31707 Blagnac Fatigue damage can occur locally, in
rules.
Cedex, France; telephone +33 5 61 93 36 small areas or structural design details,
96; fax +33 5 61 93 44 51; email or globally, in widespread areas.
DEPARTMENT OF TRANSPORTATION account.airworth-eas@airbus.com; Multiple-site damage is widespread
Internet: http://www.airbus.com. You damage that occurs in a large structural
Federal Aviation Administration may view this referenced service element such as a single rivet line of a
information at the FAA, Transport lap splice joining two large skin panels.
14 CFR Part 39 Airplane Directorate, 1601 Lind Avenue Widespread damage can also occur in
SW., Renton, WA. For information on multiple elements such as adjacent
[Docket No. FAA–2016–9572; Directorate
Identifier 2016–NM–151–AD] the availability of this material at the frames or stringers. Multiple-site
FAA, call 425–227–1221. damage and multiple-element damage
RIN 2120–AA64 cracks are typically too small initially to
Examining the AD Docket
be reliably detected with normal
Airworthiness Directives; Airbus You may examine the AD docket on inspection methods. Without
Airplanes the Internet at http:// intervention, these cracks will grow,
AGENCY: Federal Aviation www.regulations.gov by searching for and eventually compromise the
Administration (FAA), DOT. and locating Docket No. FAA–2016– structural integrity of the airplane. This
ACTION: Notice of proposed rulemaking
9572; or in person at the Docket condition is known as widespread
(NPRM). Management Facility between 9 a.m. fatigue damage. It is associated with
and 5 p.m., Monday through Friday, general degradation of large areas of
SUMMARY: We propose to supersede except Federal holidays. The AD docket structure with similar structural details
Airworthiness Directive (AD) 2014–08– contains this proposed AD, the and stress levels. As an airplane ages,
02 for certain Airbus Model A300 B4– regulatory evaluation, any comments WFD will likely occur, and will
600 and A300 B4–600R series airplanes. received, and other information. The certainly occur if the airplane is
AD 2014–08–02 requires modifying the street address for the Docket Operations operated long enough without any
profile of stringer run-outs of both office (telephone 800–647–5527) is in intervention.
wings, including a high frequency eddy the ADDRESSES section. Comments will The FAA’s WFD final rule (75 FR
current (HFEC) inspection of the be available in the AD docket shortly 69746, November 15, 2010) became
fastener holes for defects, and repairs if after receipt. effective on January 14, 2011. The WFD
necessary. Since we issued AD 2014– FOR FURTHER INFORMATION CONTACT: Dan rule requires certain actions to prevent
08–02, further analysis in the context of Rodina, Aerospace Engineer, structural failure due to WFD
widespread fatigue damage (WFD) International Branch, ANM–116, throughout the operational life of
concluded that a shorter compliance Transport Airplane Directorate, FAA, certain existing transport category
time is necessary to meet specified 1601 Lind Avenue SW., Renton, WA airplanes and all of these airplanes that
requirements to address WFD. This 98057–3356; telephone 425–227–2125; will be certificated in the future. For
proposed AD would retain the actions fax 425–227–1149. existing and future airplanes subject to
required by AD 2014–08–02 and would SUPPLEMENTARY INFORMATION: the WFD rule, the rule requires that
revise the compliance times. We are design approval holders (DAHs)
proposing this AD to address the unsafe Comments Invited establish a limit of validity (LOV) of the
condition on these products. We invite you to send any written engineering data that support the
DATES: We must receive comments on relevant data, views, or arguments about structural maintenance program.
this proposed AD by April 27, 2017. this proposed AD. Send your comments Operators affected by the WFD rule may
ADDRESSES: You may send comments, to an address listed under the not fly an airplane beyond its LOV,
using the procedures found in 14 CFR ADDRESSES section. Include ‘‘Docket No. unless an extended LOV is approved.
11.43 and 11.45, by any of the following FAA–2016–9572; Directorate Identifier The WFD rule (75 FR 69746,
methods: 2016–NM–151–AD’’ at the beginning of November 15, 2010) does not require
• Federal eRulemaking Portal: Go to your comments. We specifically invite identifying and developing maintenance
http://www.regulations.gov. Follow the comments on the overall regulatory, actions if the DAHs can show that such
instructions for submitting comments. economic, environmental, and energy actions are not necessary to prevent
jstallworth on DSK7TPTVN1PROD with PROPOSALS
• Fax: 202–493–2251. aspects of this proposed AD. We will WFD before the airplane reaches the
• Mail: U.S. Department of consider all comments received by the LOV. Many LOVs, however, do depend
Transportation, Docket Operations, M– closing date and may amend this on accomplishment of future
30, West Building Ground Floor, Room proposed AD based on those comments. maintenance actions. As stated in the
W12–140, 1200 New Jersey Avenue SE., We will post all comments we WFD rule, any maintenance actions
Washington, DC 20590. receive, without change, to http:// necessary to reach the LOV will be
• Hand Delivery: Deliver to Mail www.regulations.gov, including any mandated by airworthiness directives
address above between 9 a.m. and 5 personal information you provide. We through separate rulemaking actions.
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![13406 Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Proposed Rules
In the context of WFD, this action is Damage (WFD), concluded that a threshold no way of determining the number of
necessary to enable DAHs to propose reduction is necessary to meet the WFD aircraft that might need this repair.
LOVs that allow operators the longest requirements. Consequently, Airbus revised
SB A300–57–6046 accordingly (now at Authority for This Rulemaking
operational lives for their airplanes, and
Revision 03). Title 49 of the United States Code
still ensure that WFD will not occur. For the reasons described above, this
This approach allows for an specifies the FAA’s authority to issue
[EASA] AD retains the requirements of EASA
implementation strategy that provides AD 2013–0008R1, which is superseded, but
rules on aviation safety. Subtitle I,
flexibility to DAHs in determining the reduces the modification threshold, and section 106, describes the authority of
timing of service information introduces a pre-mod High Frequency Eddy the FAA Administrator. ‘‘Subtitle VII:
development (with FAA approval), Current (HFEC) inspection. Aviation Programs,’’ describes in more
while providing operators with certainty detail the scope of the Agency’s
You may examine the MCAI in the authority.
regarding the LOV applicable to their AD docket on the Internet at http://
airplanes. We are issuing this rulemaking under
www.regulations.gov by searching for the authority described in ‘‘Subtitle VII,
On April 2, 2014, we issued AD 2014–
and locating Docket No. FAA–2016– Part A, Subpart III, Section 44701:
08–02, Amendment 39–17826 (79 FR
9572. General requirements.’’ Under that
21392, April 16, 2014) (‘‘AD 2014–08–
02’’), for certain Airbus Model A300 B4– Related Service Information Under 1 section, Congress charges the FAA with
600 and A300 B4–600R series airplanes. CFR Part 51 promoting safe flight of civil aircraft in
AD 2014–08–02 was prompted by air commerce by prescribing regulations
Airbus has issued Service Bulletin for practices, methods, and procedures
reports of cracks found in certain A300–57–6046, Revision 03, including
bottom wing skin stringers during full- the Administrator finds necessary for
Appendix 01, dated February 4, 2015. safety in air commerce. This regulation
scale fatigue testing and in service. AD The service information describes
2014–08–02 requires modifying the is within the scope of that authority
procedures to modify the profile of because it addresses an unsafe condition
profile of stringer run-outs of both stringer run-outs of both wings,
wings, including a high frequency eddy that is likely to exist or develop on
including a HFEC inspection of the products identified in this rulemaking
current inspection of the fastener holes fastener holes for defects, and repairs. It
for defects, and repairs if necessary. We action.
also describes new compliance times for
issued AD 2014–08–02 to prevent completing the modifications. This Regulatory Findings
cracking in the bottom wing skin service information is reasonably
stringers, which could result in reduced We determined that this proposed AD
available because the interested parties would not have federalism implications
structural integrity of the wings. have access to it through their normal
Since we issued AD 2014–08–02, under Executive Order 13132. This
course of business or by the means proposed AD would not have a
further analysis in the context of WFD
identified in the ADDRESSES section. substantial direct effect on the States, on
concluded that a shorter compliance
time is necessary to meet specified FAA’s Determination and Requirements the relationship between the national
requirements to address WFD. of This Proposed AD Government and the States, or on the
The European Aviation Safety Agency distribution of power and
This product has been approved by responsibilities among the various
(EASA), which is the Technical Agent
the aviation authority of another levels of government.
for the Member States of the European
country, and is approved for operation For the reasons discussed above, I
Union, has issued EASA Airworthiness
in the United States. Pursuant to our certify this proposed regulation:
Directive 2016–0174, dated August 30,
bilateral agreement with the State of 1. Is not a ‘‘significant regulatory
2016 (referred to after this as the
Design Authority, we have been notified action’’ under Executive Order 12866;
Mandatory Continuing Airworthiness
of the unsafe condition described in the 2. Is not a ‘‘significant rule’’ under the
Information, or ‘‘the MCAI’’), to correct
MCAI and service information DOT Regulatory Policies and Procedures
an unsafe condition for certain Airbus
referenced above. We are proposing this (44 FR 11034, February 26, 1979);
Model A300 B4–600 and A300 B4–600R
AD because we evaluated all pertinent 3. Will not affect intrastate aviation in
series airplanes. The MCAI states:
information and determined an unsafe Alaska; and
During full-scale fatigue testing, cracks condition exists and is likely to exist or 4. Will not have a significant
were detected in the bottom wing skin develop on other products of these same economic impact, positive or negative,
stringers at Rib 14. In addition, operators on a substantial number of small entities
have also reported finding cracks in the same type designs.
area on in-service aeroplanes. under the criteria of the Regulatory
Costs of Compliance Flexibility Act.
This condition, if not detected and
corrected, could impair the structural We estimate that this proposed AD List of Subjects in 14 CFR Part 39
integrity of the wings. affects 29 airplanes of U.S. registry.
Additional analysis results showed that the The actions required by AD 2014–08– Air transportation, Aircraft, Aviation
improved design of the stringer run-out was 02, and retained in this proposed AD, safety, Incorporation by reference,
necessary for aeroplanes operating beyond Safety.
take about 63 work-hours per product,
the Extended Service Goal 1.
To address this unsafe condition, Airbus at an average labor rate of $85 per work- The Proposed Amendment
issued Service Bulletin (SB) A300–57–6046 hour. Required parts cost about $2,360
Accordingly, under the authority
Revision 01 to provide modification per product. Based on these figures
jstallworth on DSK7TPTVN1PROD with PROPOSALS
delegated to me by the Administrator,
instructions, and EASA issued AD 2013– (accounting for updated work-hour and
0008 (later revised) [which corresponds to the FAA proposes to amend 14 CFR part
parts cost estimates), the estimated cost
FAA AD 2014–08–02], to require the removal 39 as follows:
of this proposed AD on U.S. operators
of the stringer end run-out plate at stringer is $7,715 per product.
19 on the bottom wing skin and a re-profiling PART 39—AIRWORTHINESS
modification of the stringers 10, 11, 12, 17 We have received no definitive data DIRECTIVES
and 19. that would enable us to provide cost
Since that [EASA] AD was issued, further estimates for any on-condition actions ■ 1. The authority citation for part 39
analysis in the context of Widespread Fatigue specified in this proposed AD. We have continues to read as follows:
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![Federal Register / Vol. 82, No. 47 / Monday, March 13, 2017 / Proposed Rules 13407
Authority: 49 U.S.C. 106(g), 40113, 44701. after the effective date of this AD, whichever the European Aviation Safety Agency
occurs later. (EASA); or Airbus’s EASA Design
§ 39.13 [Amended] Organization Approval (DOA). If approved by
(h) Retained Exception to the Service
■ 2. The FAA amends § 39.13 by the DOA, the approval must include the
Information, With Revised Service
removing Airworthiness Directive (AD) DOA-authorized signature.
Information
2014–08–02, Amendment 39–17826 (79 (3) Required for Compliance (RC): Except
This paragraph restates the requirements of as required by paragraph (h) of this AD: If
FR 21392, April 16, 2014), and adding paragraph (h) of AD 2014–08–02, with any service information contains procedures
the following new AD: revised service information. or tests that are identified as RC, those
Airbus: Docket No. FAA–2016–9572; (1) Where Airbus Mandatory Service procedures and tests must be done to comply
Directorate Identifier 2016–NM–151–AD. Bulletin A300–57–6046, Revision 02, dated with this AD; any procedures or tests that are
June 21, 2013, specifies to contact Airbus for not identified as RC are recommended. Those
(a) Comments Due Date repair instructions, this AD requires procedures and tests that are not identified
We must receive comments by April 27, contacting the Manager, ANM–116, as RC may be deviated from using accepted
2017. International Branch, Transport Airplane methods in accordance with the operator’s
Directorate, FAA, or the European Aviation maintenance or inspection program without
(b) Affected ADs Safety Agency (EASA) (or its delegated agent) obtaining approval of an AMOC, provided
This AD replaces AD 2014–08–02, for repair instructions and doing those the procedures and tests identified as RC can
Amendment 39–17826 (79 FR 21392, April repairs before further flight. be done and the airplane can be put back in
16, 2014) (‘‘AD 2014–08–02’’). (2) Where Airbus Service Bulletin A300– an airworthy condition. Any substitutions or
(c) Applicability 57–6046, Revision 03, including Appendix changes to procedures or tests identified as
01, dated February 4, 2015, specifies to RC require approval of an AMOC.
This AD applies to Airbus Model A300– contact Airbus for appropriate action: Before
B4–601, B4–603, B4–620, and B4–622 further flight, accomplish corrective actions (k) Related Information
airplanes, and Model A300–B4–605R and in accordance with the procedures specified
B4–622R airplanes, certificated in any (1) Refer to Mandatory Continuing
in paragraph (j)(2) of this AD. Airworthiness Information (MCAI) EASA
category, except airplanes on which Airbus
Modification 10324 or 10325 has been (i) Credit for Previous Actions Airworthiness Directive 2016–0174, dated
embodied in production. August 30, 2016, for related information.
This paragraph provides credit for actions
This MCAI may be found in the AD docket
(d) Subject required by paragraph (g) of this AD, if those
on the Internet at http://www.regulations.gov
actions were performed before the effective
Air Transport Association (ATA) of by searching for and locating Docket No.
date of this AD using the service information
America Code 57, Wings. FAA–2016–9572.
specified in paragraph (i)(1), (i)(2), or (i)(3) of
(2) For service information identified in
(e) Reason this AD.
this AD, contact Airbus SAS, Airworthiness
(1) Airbus Service Bulletin A300–57–6046,
This AD was prompted by an evaluation by Office—EAW, 1 Rond Point Maurice
Revision 01, dated April 18, 2011, which is
the design approval holder (DAH) indicating Bellonte, 31707 Blagnac Cedex, France;
not incorporated by reference in this AD.
that the wing skin stringers are subject to telephone +33 5 61 93 36 96; fax +33 5 61
(2) Airbus Service Bulletin A300–57–6046,
widespread fatigue damage (WFD). We are 93 44 51; email account.airworth-eas@
dated January 18, 1994, which is not
issuing this AD to prevent cracking in the airbus.com; Internet: http://www.airbus.com.
incorporated by reference in this AD.
bottom wing skin stringers, which could You may view this service information at the
(3) Airbus Service Bulletin A300–57–6046,
result in reduced structural integrity of the FAA, Transport Airplane Directorate, 1601
wings. Revision 02, dated June 21, 2013, which was
incorporated by reference in AD 2014–08–02. Lind Avenue SW., Renton, WA. For
(f) Compliance information on the availability of this
(j) Other FAA AD Provisions material at the FAA, call 425–227–1221.
Comply with this AD within the
compliance times specified, unless already The following provisions also apply to this Issued in Renton, Washington, on January
done. AD: 12, 2017.
(1) Alternative Methods of Compliance Michael Kaszycki,
(g) Retained Modification of Rib 14, With (AMOCs): The Manager, International
Revised Compliance Time and Service Branch, ANM–116, Transport Airplane Acting Manager, Transport Airplane
Information Directorate, FAA, has the authority to Directorate, Aircraft Certification Service.
This paragraph restates the requirements of approve AMOCs for this AD, if requested [FR Doc. 2017–03032 Filed 3–10–17; 8:45 am]
paragraph (g) of AD 2014–08–02, with using the procedures found in 14 CFR 39.19. BILLING CODE 4910–13–P
revised compliance time and service In accordance with 14 CFR 39.19, send your
information. At the time specified in request to your principal inspector or local
paragraph (g)(1) or (g)(2) of this AD, Flight Standards District Office, as DEPARTMENT OF TRANSPORTATION
whichever occurs earlier, modify the profile appropriate. If sending information directly
of stringer run-outs at rib 14 of both wings, to the International Branch, send it to ATTN: Federal Aviation Administration
including a high frequency eddy current Dan Rodina, Aerospace Engineer,
inspection of the fastener holes for defects International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind 14 CFR Part 71
and all applicable repairs, in accordance with
the Accomplishment Instructions of Airbus Avenue SW., Renton, WA 98057–3356; [Docket No. FAA–2016–9476; Airspace
Service Bulletin A300–57–6046, Revision 02, telephone 425–227–2125; fax 425–227–1149. Docket No. 16–AWP–28]
dated June 21, 2013; or Revision 03, Information may be emailed to: 9-ANM-116-
including Appendix 01, dated February 4, AMOC-REQUESTS@faa.gov. Before using Proposed Establishment of Class E
2015; except as required by paragraph (h) of any approved AMOC, notify your appropriate Airspace, Sacramento, CA
this AD. Do all applicable repairs before principal inspector, or lacking a principal
further flight. As of the effective date of this inspector, the manager of the local flight AGENCY: Federal Aviation
jstallworth on DSK7TPTVN1PROD with PROPOSALS
AD, only Airbus Service Bulletin A300–57– standards district office/certificate holding Administration (FAA), DOT.
6046, Revision 03, including Appendix 01, district office.
(2) Contacting the Manufacturer: As of the ACTION: Notice of Proposed Rulemaking
dated February 4, 2015, may be used.
(1) Before the accumulation of 42,500 total effective date of this AD, for any requirement (NPRM).
flight cycles, or within 2,000 flight cycles in this AD to obtain corrective actions from
after May 21, 2014 (the effective date of AD a manufacturer, the action must be SUMMARY: This action proposes to
2014–08–02), whichever occurs later. accomplished using a method approved by establish Class E en route airspace
(2) Before the accumulation of 30,000 total the Manager, International Branch, ANM– extending upward from 1,200 feet above
flight cycles, or within 2,000 flight cycles 116, Transport Airplane Directorate, FAA; or the surface to accommodate Instrument
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Document Created: 2018-02-01 14:57:33
Document Modified: 2018-02-01 14:57:33
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by April 27, 2017. | |
| 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. | |
| FR Citation | 82 FR 13405 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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