82 FR 24903 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 103 (May 31, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 103 (May 31, 2017)
| Page Range | 24903-24906 | |
| FR Document | 2017-10979 |
[Federal Register Volume 82, Number 103 (Wednesday, May 31, 2017)] [Proposed Rules] [Pages 24903-24906] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-10979] [[Page 24903]] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0520; Directorate Identifier 2016-NM-143-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 reports of cracks initiating at the upper radius of frame (FR) 47 and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of FR 47. This proposed AD would require repetitive inspections to detect cracking of the upper radius of the forward fitting of FR 47, and related investigative actions 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 17, 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-2017- 0520; 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-2017-0520; Directorate Identifier 2016-NM-143-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 AD 2016-0150, dated July 25, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all. The MCAI states: During scheduled maintenance inspections on the fuselage, cracks initiating at the upper radius of frame (FR) 47 have been reported on several aeroplanes. Similar damage was also discovered on the A300 fatigue test fuselage. This condition, if not detected and corrected, could reduce the structural integrity of the fuselage. Prompted by these findings, Airbus issued Service Bulletin (SB) A300-53-0246, SB A300-53-6029 and SB A300-53-9014 to provide inspection instructions and, consequently, DGAC France issued AD F- 2006-016 to require repetitive inspections and corrective action. Since that [French] AD was issued, further investigation led to the conclusion that the current ultrasonic inspection performed in accordance with Airbus SB A300-53-0246 Revision 06, or SB A300-53- 6029 Revision 08, or SB A300-53-9014 Revision 01, as applicable, was not reliable to detect deep crack going downward. Consequently, to ensure the crack depth is correctly measured whatever the crack direction, Airbus developed a new nondestructive testing method [eddy current] for this special detailed inspection (SDI) and revised the affected SBs accordingly. For the reasons described above, this [EASA] AD retains the requirements of DGAC France AD F-2006-016, which is superseded, but requires the accomplishment of repetitive SDI to replace the previously required ultrasonic inspections [and related investigative actions and corrective actions if necessary]. Related investigative actions include an ultrasonic inspection for cracking on the forward face of forward fitting and a detailed inspection for cracking of the aft fitting around the fasteners. Corrective actions include crack repairs, modification of the sealing fittings and sealing shims. This proposed AD requires reporting of the inspection results to Airbus. 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-2017-0520. Related Service Information Under 1 CFR Part 51 Airbus has issued Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016 (for Model A300 series airplanes); and Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016 (for Model A300-600 series airplanes). The service information describes procedures for doing an SDI for cracking of the FR 47 forward fitting upper radius on the left- hand and right-hand sides of the fuselage, and related investigative actions and corrective actions. 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. [[Page 24904]] 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 the same type designs. This NPRM would not supersede AD 2007-26-14, Amendment 39-15316 (73 FR 2803, January 16, 2008). Rather, we have determined that a stand- alone AD would be more appropriate to address the changes in the MCAI. This NPRM would require repetitive inspections to detect cracking of the upper radius of the forward fitting of FR 47, and related investigative actions and corrective actions if necessary. Accomplishment of the proposed actions would then terminate all requirements of AD 2007-26-14 for the inspected airplane. Differences Between This Proposed AD and the MCAI or Service Information Although the MCAI and service information allow further flight if cracks are found during accomplishment of the required action, this proposed AD requires that any cracking be repaired before further flight. Costs of Compliance We estimate that this proposed AD affects 132 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........................ 19 work-hours x $85 $0 $1,615 per $213,180 per per hour = $1,615. inspection cycle. inspection cycle. Reporting......................... 1 work-hour x $85 0 $85 per inspection $11,220 per per hour = $85. cycle. inspection cycle. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary related investigative and corrective actions that would be required based on the results of the proposed inspection. We have no way of determining the number of airplanes that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Related investigative and Corrective actions.. 21 work-hours x $85 per hour = $1,835 $3,620 $1,785. ---------------------------------------------------------------------------------------------------------------- Paperwork Reduction Act A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB control number. The control number for the collection of information required by this proposed AD is 2120-0056. The paperwork cost associated with this proposed AD has been detailed in the Costs of Compliance section of this document and includes time for reviewing instructions, as well as completing and reviewing the collection of information. Therefore, all reporting associated with this proposed AD is mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information Collection Clearance Officer, AES-200. 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. [[Page 24905]] Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): Airbus: Docket No. FAA-2017-0520; Directorate Identifier 2016-NM- 143-AD. (a) Comments Due Date We must receive comments by July 17, 2017. (b) Affected ADs This AD affects AD 2007-26-14, Amendment 39-15316 (73 FR 2803, January 16, 2008) (``AD 2007-26-14''). (c) Applicability This AD applies to the Airbus airplanes identified in paragraphs (c)(1) through (c)(5) of this AD, certificated in any category, except airplanes that have been repaired as specified in Airbus Service Bulletin A300-53-0370 or Airbus Service Bulletin A300-53- 6144, as applicable. (1) Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 airplanes. (2) Model A300 B4-601, B4-603, B4-620, and B4-622 airplanes. (3) Model A300 B4-605R and B4-622R airplanes. (4) Model A300 F4-605R and F4-622R airplanes. (5) Model A300 C4-605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by reports of cracks initiating at the upper radius of frame (FR) 47 and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of FR 47. We are issuing this AD to detect and correct fatigue cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, which could propagate and result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections Except as required by paragraph (h) of this AD: Before exceeding 10,000 flight cycles since first flight of the airplane or within 30 days after the effective date of this AD, whichever is later, do a special detailed inspection (SDI) for cracking of the FR 47 forward fitting upper radius on the left-hand and right-hand sides of the fuselage, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) and (g)(2) of this AD. Repeat the inspection thereafter at intervals not to exceed 4,150 flight cycles, except as required by paragraph (j) of this AD. (1) Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016. (2) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016. (h) Initial Inspection for Airplanes Previously Inspected For airplanes previously inspected as specified in the applicable Airbus service information specified in paragraphs (h)(1) through (h)(6) of this AD and on which no cracking was found: Within 4,150 flight cycles after the most recent inspection, do the inspection for cracking of the FR 47 forward fitting upper radius required by paragraph (g) of this AD. (1) Airbus Service Bulletin A300-53-0246, Revision 06, dated October 19, 2005. (2) Airbus Service Bulletin A300-53-0246, Revision 07, dated September 9, 2008. (3) Airbus Service Bulletin A300-53-6029, Revision 08, dated October 19, 2005. (4) Airbus Service Bulletin A300-53-6029, Revision 09, dated September 9, 2008. (5) Airbus Service Bulletin A300-53-6029, Revision 10, dated July 9, 2009. (6) Airbus Service Bulletin A300-53-6029, Revision 11, dated September 28, 2009. (i) Inspections for Airplanes With Abnormal Load Events For airplanes on which any crack was found during any inspection done as specified in Airbus Service Bulletin A300-53-0246 or Airbus Service Bulletin A300-53-6029, as applicable, and on which any abnormal load event, such as hard landing or flight in excessive turbulence, occurred within 3 months before the effective date of this AD or occurs on or after the effective date of this AD: Within 3 months after each event, accomplish an SDI for cracking of the FR 47 forward fitting upper radius, left-hand and right-hand sides of the fuselage, in accordance with the applicable Accomplishment Instructions of the Airbus service information specified in paragraphs (g)(1) or (g)(2) of this AD. If, during this 3-month period, another abnormal load event occurs, and if no SDI has yet been accomplished, before further flight after the second event, obtain corrective action instructions from 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), and accomplish those instructions accordingly. (j) Corrective Actions for Airplanes With Cracks If, during any SDI as required by paragraph (g), (h), or (i) of this AD, any crack is found: Before further flight, do the applicable related investigative actions and corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (g)(1) or (g)(2) of this AD, and obtain additional corrective action instructions from the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA, and accomplish those instructions accordingly before further flight. (k) Reporting Submit a report of the findings (both positive and negative) of each SDI inspection required by paragraphs (g), (h), and (i) of this AD to Airbus Service Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), at the applicable time specified in paragraph (k)(1) or (k)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this AD. (l) Terminating Action for AD 2007-26-14 Accomplishing any inspection required by paragraph (g) or (h) of this AD terminates all requirements of AD 2007-26-14 for the inspected airplane. (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: [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: 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 EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Reporting Requirements: A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid OMB Control Number. The OMB Control Number for this information collection is 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: [[Page 24906]] Information Collection Clearance Officer, AES-200. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0150, 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-2017-0520. (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: [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 May 19, 2017. Victor Wicklund, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-10979 Filed 5-30-17; 8:45 am] BILLING CODE 4910-13-P
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DEPARTMENT OF TRANSPORTATION SW., Renton, WA. For information on This condition, if not detected and
the availability of this material at the corrected, could reduce the structural
Federal Aviation Administration FAA, call 425–227–1221. integrity of the fuselage.
Prompted by these findings, Airbus issued
14 CFR Part 39 Examining the AD Docket Service Bulletin (SB) A300–53–0246, SB
You may examine the AD docket on A300–53–6029 and SB A300–53–9014 to
[Docket No. FAA–2017–0520; Directorate
the Internet at http:// provide inspection instructions and,
Identifier 2016–NM–143–AD]
www.regulations.gov by searching for consequently, DGAC France issued AD F–
RIN 2120–AA64 and locating Docket No. FAA–2017– 2006–016 to require repetitive inspections
0520; or in person at the Docket and corrective action.
Airworthiness Directives; Airbus Management Facility between 9 a.m. Since that [French] AD was issued, further
Airplanes and 5 p.m., Monday through Friday, investigation led to the conclusion that the
AGENCY: Federal Aviation except Federal holidays. The AD docket current ultrasonic inspection performed in
contains this proposed AD, the accordance with Airbus SB A300–53–0246
Administration (FAA), DOT.
regulatory evaluation, any comments Revision 06, or SB A300–53–6029 Revision
ACTION: Notice of proposed rulemaking 08, or SB A300–53–9014 Revision 01, as
received, and other information. The
(NPRM). applicable, was not reliable to detect deep
street address for the Docket Operations
SUMMARY: We propose to adopt a new office (telephone: 800–647–5527) is in crack going downward.
airworthiness directive (AD) for certain the ADDRESSES section. Comments will Consequently, to ensure the crack depth is
be available in the AD docket shortly correctly measured whatever the crack
Airbus Model A300 series airplanes;
after receipt. direction, Airbus developed a new
and Model A300 B4–600, B4–600R, and
nondestructive testing method [eddy current]
F4–600R series airplanes, and Model FOR FURTHER INFORMATION CONTACT: Dan
for this special detailed inspection (SDI) and
A300 C4–605R Variant F airplanes Rodina, Aerospace Engineer,
revised the affected SBs accordingly.
(collectively called Model A300–600 International Branch, ANM–116,
For the reasons described above, this
series airplanes). This proposed AD was Transport Airplane Directorate, FAA,
[EASA] AD retains the requirements of DGAC
prompted by reports of cracks initiating 1601 Lind Avenue SW., Renton, WA
France AD F–2006–016, which is
at the upper radius of frame (FR) 47 and 98057–3356; telephone: 425–227–2125; superseded, but requires the accomplishment
a determination that the current fax: 425–227–1149. of repetitive SDI to replace the previously
inspection procedure is not reliable in SUPPLEMENTARY INFORMATION: required ultrasonic inspections [and related
detecting certain cracking of the forward investigative actions and corrective actions if
Comments Invited
fitting of FR 47. This proposed AD necessary].
would require repetitive inspections to We invite you to send any written
detect cracking of the upper radius of relevant data, views, or arguments about Related investigative actions include
the forward fitting of FR 47, and related this proposed AD. Send your comments an ultrasonic inspection for cracking on
investigative actions and corrective to an address listed under the the forward face of forward fitting and
actions if necessary. We are proposing ADDRESSES section. Include ‘‘Docket No. a detailed inspection for cracking of the
this AD to address the unsafe condition FAA–2017–0520; Directorate Identifier aft fitting around the fasteners.
on these products. 2016–NM–143–AD’’ at the beginning of Corrective actions include crack repairs,
DATES: We must receive comments on your comments. We specifically invite modification of the sealing fittings and
this proposed AD by July 17, 2017. comments on the overall regulatory, sealing shims. This proposed AD
economic, environmental, and energy requires reporting of the inspection
ADDRESSES: You may send comments,
aspects of this proposed AD. We will results to Airbus. You may examine the
using the procedures found in 14 CFR
consider all comments received by the MCAI in the AD docket on the Internet
11.43 and 11.45, by any of the following
closing date and may amend this at http://www.regulations.gov by
methods:
proposed AD based on those comments. searching for and locating Docket No.
• Federal eRulemaking Portal: Go to We will post all comments we
http://www.regulations.gov. Follow the FAA–2017–0520.
receive, without change, to http://
instructions for submitting comments. www.regulations.gov, including any Related Service Information Under 1
• Fax: 202–493–2251. CFR Part 51
personal information you provide. We
• Mail: U.S. Department of
will also post a report summarizing each
Transportation, Docket Operations, M– Airbus has issued Airbus Service
substantive verbal contact we receive
30, West Building Ground Floor, Room Bulletin A300–53–0246, Revision 08,
about this proposed AD.
W12–140, 1200 New Jersey Avenue SE., including Appendix 1, dated April 13,
Washington, DC 20590. Discussion 2016 (for Model A300 series airplanes);
• Hand Delivery: Deliver to Mail The European Aviation Safety Agency and Airbus Service Bulletin A300–53–
address above between 9 a.m. and 5 (EASA), which is the Technical Agent 6029, Revision 12, including Appendix
p.m., Monday through Friday, except for the Member States of the European 1, dated April 13, 2016 (for Model
Federal holidays. Union, has issued EASA AD 2016–0150, A300–600 series airplanes). The service
For service information identified in dated July 25, 2016 (referred to after this information describes procedures for
this NPRM, contact Airbus SAS, as the Mandatory Continuing doing an SDI for cracking of the FR 47
Airworthiness Office—EAW, 1 Rond Airworthiness Information, or ‘‘the forward fitting upper radius on the left-
nlaroche on DSK30NT082PROD with PROPOSALS
Point Maurice Bellonte, 31707 Blagnac MCAI’’), to correct an unsafe condition hand and right-hand sides of the
Cedex, France; telephone: +33 5 61 93 on all. The MCAI states: fuselage, and related investigative
36 96; fax: +33 5 61 93 44 51; email: actions and corrective actions. This
account.airworth-eas@airbus.com; During scheduled maintenance inspections service information is reasonably
on the fuselage, cracks initiating at the upper
Internet: http://www.airbus.com. You radius of frame (FR) 47 have been reported available because the interested parties
may view this referenced service on several aeroplanes. Similar damage was have access to it through their normal
information at the FAA, Transport also discovered on the A300 fatigue test course of business or by the means
Airplane Directorate, 1601 Lind Avenue fuselage. identified in the ADDRESSES section.
VerDate Sep<11>2014 14:38 May 30, 2017 Jkt 241001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\31MYP1.SGM 31MYP1](https://thefederalregister.org/doc/82_FR_25006/page/1.svg)
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§ 39.13 [Amended] (2) Airbus Service Bulletin A300–53–6029, (k) Reporting
■ 2. The FAA amends § 39.13 by adding Revision 12, including Appendix 1, dated Submit a report of the findings (both
the following new airworthiness April 13, 2016. positive and negative) of each SDI inspection
directive (AD): (h) Initial Inspection for Airplanes required by paragraphs (g), (h), and (i) of this
Previously Inspected AD to Airbus Service Bulletin Reporting
Airbus: Docket No. FAA–2017–0520; Online Application on Airbus World (https://
Directorate Identifier 2016–NM–143–AD. For airplanes previously inspected as w3.airbus.com/), at the applicable time
(a) Comments Due Date specified in the applicable Airbus service specified in paragraph (k)(1) or (k)(2) of this
information specified in paragraphs (h)(1) AD.
We must receive comments by July 17, through (h)(6) of this AD and on which no
2017. (1) If the inspection was done on or after
cracking was found: Within 4,150 flight the effective date of this AD: Submit the
(b) Affected ADs cycles after the most recent inspection, do report within 30 days after the inspection.
This AD affects AD 2007–26–14, the inspection for cracking of the FR 47 (2) If the inspection was done before the
Amendment 39–15316 (73 FR 2803, January forward fitting upper radius required by effective date of this AD: Submit the report
16, 2008) (‘‘AD 2007–26–14’’). paragraph (g) of this AD. within 30 days after the effective date of this
(1) Airbus Service Bulletin A300–53–0246, AD.
(c) Applicability Revision 06, dated October 19, 2005. (l) Terminating Action for AD 2007–26–14
This AD applies to the Airbus airplanes (2) Airbus Service Bulletin A300–53–0246,
identified in paragraphs (c)(1) through (c)(5) Revision 07, dated September 9, 2008. Accomplishing any inspection required by
of this AD, certificated in any category, (3) Airbus Service Bulletin A300–53–6029, paragraph (g) or (h) of this AD terminates all
except airplanes that have been repaired as requirements of AD 2007–26–14 for the
Revision 08, dated October 19, 2005.
specified in Airbus Service Bulletin A300– inspected airplane.
(4) Airbus Service Bulletin A300–53–6029,
53–0370 or Airbus Service Bulletin A300– Revision 09, dated September 9, 2008. (m) Other FAA AD Provisions
53–6144, as applicable. (5) Airbus Service Bulletin A300–53–6029,
(1) Model A300 B2–1A, B2–1C, B2K–3C, The following provisions also apply to this
Revision 10, dated July 9, 2009. AD:
B2–203, B4–2C, B4–103, and B4–203
(6) Airbus Service Bulletin A300–53–6029, (1) Alternative Methods of Compliance
airplanes.
(2) Model A300 B4–601, B4–603, B4–620, Revision 11, dated September 28, 2009. (AMOCs): The Manager, International
and B4–622 airplanes. Branch, ANM–116, Transport Airplane
(i) Inspections for Airplanes With Abnormal
(3) Model A300 B4–605R and B4–622R Directorate, FAA, has the authority to
Load Events
airplanes. approve AMOCs for this AD, if requested
(4) Model A300 F4–605R and F4–622R For airplanes on which any crack was using the procedures found in 14 CFR 39.19.
airplanes. found during any inspection done as In accordance with 14 CFR 39.19, send your
(5) Model A300 C4–605R Variant F specified in Airbus Service Bulletin A300– request to your principal inspector or local
airplanes. 53–0246 or Airbus Service Bulletin A300– Flight Standards District Office, as
53–6029, as applicable, and on which any appropriate. If sending information directly
(d) Subject abnormal load event, such as hard landing or to the International Branch, send it to the
Air Transport Association (ATA) of flight in excessive turbulence, occurred attention of the person identified in
America Code 53, Fuselage. within 3 months before the effective date of paragraph (n)(2) of this AD. Information may
this AD or occurs on or after the effective be emailed to: 9–ANM–116–AMOC–
(e) Reason
date of this AD: Within 3 months after each REQUESTS@faa.gov. Before using any
This AD was prompted by reports of cracks event, accomplish an SDI for cracking of the approved AMOC, notify your appropriate
initiating at the upper radius of frame (FR) FR 47 forward fitting upper radius, left-hand principal inspector, or lacking a principal
47 and a determination that the current inspector, the manager of the local flight
and right-hand sides of the fuselage, in
inspection procedure is not reliable in standards district office/certificate holding
detecting certain cracking of the forward accordance with the applicable
Accomplishment Instructions of the Airbus district office.
fitting of FR 47. We are issuing this AD to (2) Contacting the Manufacturer: For any
detect and correct fatigue cracking of the FR service information specified in paragraphs
(g)(1) or (g)(2) of this AD. If, during this 3- requirement in this AD to obtain corrective
47 forward fitting upper radius on the left- actions from a manufacturer, the action must
hand and right-hand sides of the fuselage, month period, another abnormal load event
be accomplished using a method approved
which could propagate and result in reduced occurs, and if no SDI has yet been
by the Manager, International Branch, ANM–
structural integrity of the airplane. accomplished, before further flight after the
116, Transport Airplane Directorate, FAA; or
second event, obtain corrective action
(f) Compliance EASA; or Airbus’s EASA DOA. If approved
instructions from the Manager, International by the DOA, the approval must include the
Comply with this AD within the Branch, ANM–116, Transport Airplane
compliance times specified, unless already DOA-authorized signature.
Directorate, FAA; or the European Aviation (3) Reporting Requirements: A federal
done. Safety Agency (EASA); or Airbus’s EASA agency may not conduct or sponsor, and a
(g) Repetitive Inspections Design Organization Approval (DOA), and person is not required to respond to, nor
accomplish those instructions accordingly. shall a person be subject to a penalty for
Except as required by paragraph (h) of this
AD: Before exceeding 10,000 flight cycles (j) Corrective Actions for Airplanes With failure to comply with a collection of
since first flight of the airplane or within 30 Cracks information subject to the requirements of
days after the effective date of this AD, the Paperwork Reduction Act unless that
If, during any SDI as required by paragraph collection of information displays a current
whichever is later, do a special detailed
inspection (SDI) for cracking of the FR 47 (g), (h), or (i) of this AD, any crack is found: valid OMB Control Number. The OMB
forward fitting upper radius on the left-hand Before further flight, do the applicable Control Number for this information
and right-hand sides of the fuselage, in related investigative actions and corrective collection is 2120–0056. Public reporting for
accordance with the Accomplishment actions, in accordance with the this collection of information is estimated to
nlaroche on DSK30NT082PROD with PROPOSALS
Instructions of the applicable Airbus service Accomplishment Instructions of the be approximately 5 minutes per response,
information specified in paragraphs (g)(1) applicable Airbus service information including the time for reviewing instructions,
and (g)(2) of this AD. Repeat the inspection specified in paragraphs (g)(1) or (g)(2) of this completing and reviewing the collection of
thereafter at intervals not to exceed 4,150 AD, and obtain additional corrective action information. All responses to this collection
flight cycles, except as required by paragraph instructions from the Manager, International of information are mandatory. Comments
(j) of this AD. Branch, ANM–116, Transport Airplane concerning the accuracy of this burden and
(1) Airbus Service Bulletin A300–53–0246, Directorate, FAA; or EASA; or Airbus’s EASA suggestions for reducing the burden should
Revision 08, including Appendix 1, dated DOA, and accomplish those instructions be directed to the FAA at: 800 Independence
April 13, 2016. accordingly before further flight. Ave. SW., Washington, DC 20591, Attn:
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![24906 Federal Register / Vol. 82, No. 103 / Wednesday, May 31, 2017 / Proposed Rules
Information Collection Clearance Officer, must be replaced, and certain SUPPLEMENTARY INFORMATION:
AES–200. compliance times must be reduced. This
Comments Invited
(n) Related Information proposed AD would require identifying
the serial number and part number of We invite you to send any written
(1) Refer to Mandatory Continuing
the MLG rear hinge pins, and replacing relevant data, views, or arguments about
Airworthiness Information (MCAI) EASA AD
2016–0150, dated July 25, 2016, for related pins if necessary. We are proposing this this proposed AD. Send your comments
information. This MCAI may be found in the AD to address the unsafe condition on to an address listed under the
AD docket on the Internet at http:// these products. ADDRESSES section. Include ‘‘Docket No.
www.regulations.gov by searching for and DATES: We must receive comments on FAA–2017–0516; Directorate Identifier
locating Docket No. FAA–2017–0520. this proposed AD by July 17, 2017. 2016–NM–125–AD’’ at the beginning of
(2) For more information about this AD, your comments. We specifically invite
ADDRESSES: You may send comments,
contact Dan Rodina, Aerospace Engineer, comments on the overall regulatory,
International Branch, ANM–116, Transport using the procedures found in 14 CFR
11.43 and 11.45, by any of the following economic, environmental, and energy
Airplane Directorate, FAA, 1601 Lind
methods: aspects of this proposed AD. We will
Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–2125; fax: 425–227– • Federal eRulemaking Portal: Go to consider all comments received by the
1149. http://www.regulations.gov. Follow the closing date and may amend this
(3) For service information identified in instructions for submitting comments. proposed AD based on those comments.
this AD, contact Airbus SAS, Airworthiness • Fax: 202–493–2251. We will post all comments we
Office—EAW, 1 Rond Point Maurice • Mail: U.S. Department of receive, without change, to http://
Bellonte, 31707 Blagnac Cedex, France; Transportation, Docket Operations, M– www.regulations.gov, including any
telephone: +33 5 61 93 36 96; fax: +33 5 61 30, West Building Ground Floor, Room personal information you provide. We
93 44 51; email: account.airworth-eas@ W12–140, 1200 New Jersey Avenue SE., will also post a report summarizing each
airbus.com; Internet: http://www.airbus.com. substantive verbal contact we receive
Washington, DC 20590.
You may view this service information at the
• Hand Delivery: U.S. Department of about this proposed AD.
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For Transportation, Docket Operations, M–
Discussion
information on the availability of this 30, West Building Ground Floor, Room
material at the FAA, call 425–227–1221. W12–140, 1200 New Jersey Avenue SE., On November 12, 2015, we issued AD
Washington, DC, between 9 a.m. and 5 2015–23–12, Amendment 39–18329 (80
Issued in Renton, Washington, on May 19,
p.m., Monday through Friday, except FR 73096, November 24, 2015) (‘‘AD
2017.
Federal holidays. 2015–23–12’’), for all ATR—GIE Avions
Victor Wicklund,
For service information identified in de Transport Régional Model ATR42
Acting Manager, Transport Airplane this NPRM, contact ATR—GIE Avions and ATR72 airplanes. AD 2015–23–12
Directorate, Aircraft Certification Service. de Transport Régional, 1, Allée Pierre was prompted by new occurrences of
[FR Doc. 2017–10979 Filed 5–30–17; 8:45 am] Nadot, 31712 Blagnac Cedex, France; certain cracked MLG rear hinge pins.
BILLING CODE 4910–13–P telephone +33 (0) 5 62 21 62 21; fax +33 AD 2015–23–12 requires identifying the
(0) 5 62 21 67 18; email serial number and part number of the
continued.airworthiness@atr.fr; Internet MLG rear hinge pins, and replacing pins
DEPARTMENT OF TRANSPORTATION http://www.aerochain.com. You may or the MLG if necessary. We issued AD
view this referenced service information 2015–23–12 to detect and correct
Federal Aviation Administration
at the FAA, Transport Airplane cracked rear hinge pins, which could
Directorate, 1601 Lind Avenue SW., lead to MLG structural failure, possibly
14 CFR Part 39
Renton, WA. For information on the resulting in collapse of the MLG and
[Docket No. FAA–2017–0516; Directorate availability of this material at the FAA, consequent injury to the occupants of
Identifier 2016–NM–125–AD] call 425–227–1221. the airplane.
RIN 2120–AA64 Examining the AD Docket Since we issued AD 2015–23–12, we
have received a new report of a cracked
Airworthiness Directives; ATR—GIE You may examine the AD docket on MLG hinge pin having P/N D62055 on
Avions de Transport Régional the Internet at http:// a Model ATR42 airplane. We have
Airplanes www.regulations.gov by searching for determined that certain additional MLG
and locating Docket No. FAA–2017– hinge pins must be replaced, and certain
AGENCY: Federal Aviation 0516; or in person at the Docket compliance times must be reduced.
Administration (FAA), DOT. Management Facility between 9 a.m. The European Aviation Safety Agency
ACTION: Notice of proposed rulemaking and 5 p.m., Monday through Friday, (EASA), which is the Technical Agent
(NPRM). except Federal holidays. The AD docket for the Member States of the European
contains this proposed AD, the Union, has issued EASA Airworthiness
SUMMARY: We propose to supersede regulatory evaluation, any comments Directive 2016–0135, dated July 8, 2016
Airworthiness Directive (AD) 2015–23– received, and other information. The (referred to after this as the Mandatory
12, for all ATR—GIE Avions de street address for the Docket Operations Continuing Airworthiness Information,
Transport Régional Model ATR42 and office (telephone 800–647–5527) is in or ‘‘the MCAI’’), to correct an unsafe
ATR72 airplanes. AD 2015–23–12 the ADDRESSES section. Comments will condition for all ATR—GIE Avions de
currently requires identifying the serial be available in the AD docket shortly Transport Régional Model ATR42 and
nlaroche on DSK30NT082PROD with PROPOSALS
number and part number of the main after receipt. ATR72 airplanes. The MCAI states:
landing gear (MLG) rear hinge pins, and FOR FURTHER INFORMATION CONTACT:
replacing pins or the MLG if necessary. Prompted by cases of rupture of main
Shahram Daneshmandi, Aerospace
landing gear (MLG) rear hinge pin part
Since we issued AD 2015–23–12, we Engineer, International Branch, ANM– number (P/N) D61000 encountered in service
have received a new report of a certain 116, Transport Airplane Directorate, in 1994 and 1996, DGAC [Direction Générale
cracked MLG hinge pin on a Model FAA, 1601 Lind Avenue SW., Renton, de l’Aviation Civile] France issued AD 96–
ATR42 airplane. We have determined WA 98057–3356; telephone 425–227– 131–064 (B) for ATR42 aeroplanes and AD
that certain additional MLG hinge pins 1112; fax 425–227–1149. 96–096–029 (B) for ATR72 aeroplanes to
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Document Created: 2017-05-31 05:59:46
Document Modified: 2017-05-31 05:59:46
| 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 July 17, 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 24903 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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