82 FR 39520 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 160 (August 21, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 160 (August 21, 2017)
| Page Range | 39520-39523 | |
| FR Document | 2017-17203 |
[Federal Register Volume 82, Number 160 (Monday, August 21, 2017)] [Rules and Regulations] [Pages 39520-39523] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-17203] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0520; Product Identifier 2016-NM-143-AD; Amendment 39-18995; AD 2017-17-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting 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 AD was prompted by reports of cracks initiating at the upper radius of a certain frame and a determination that the current inspection procedure is not reliable in detecting certain cracking of the forward fitting of the frame. This AD requires repetitive inspections to detect cracking of the upper radius of the forward fitting of a certain frame, and related investigative actions and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective September 25, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 25, 2017. ADDRESSES: For service information identified in this final rule, 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 Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0520. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (telephone 800-647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to 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). The NPRM published in the Federal Register on May 31, 2017 (82 FR 24903) (``the NPRM''). The NPRM 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. The NPRM proposed to 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 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. 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] [[Page 39521]] 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 and corrective actions if necessary]. Related investigative actions include an ultrasonic inspection for cracking on the forward face of the forward fitting and a detailed inspection for cracking of the aft fitting around the fasteners. Corrective actions include crack repairs, and modification of the sealing fittings and sealing shims. This 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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 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. Costs of Compliance We estimate that this AD will affect 132 airplanes of U.S. registry. We estimate the following costs to comply with this 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 per $0 $85 per inspection $11,220 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 inspection. We have no way of determining the number of aircraft that might need these repairs: On-Condition Costs ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Related investigative and Corrective 21 work-hours x $85 per hour = $1,835 $3,620 actions. $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 AD is 2120- 0056. The paperwork cost associated with this 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 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. [[Page 39522]] Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will 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 that this AD: 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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): 2017-17-05 Airbus: Amendment 39-18995; Docket No. FAA-2017-0520; Product Identifier 2016-NM-143-AD. (a) Effective Date This AD is effective September 25, 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 occurs 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 Section, Transport Standards Branch, 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 and corrective actions, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (g)(1) or (g)(2) of this AD, and obtain additional corrective action instructions from the Manager, International Section, Transport Standards Branch, 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 Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this [[Page 39523]] 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 Section, 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 Section, Transport Standards Branch, 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: 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 Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425-227-1149. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use this service information as applicable to do the actions required by this AD, unless this AD specifies otherwise. (i) Airbus Service Bulletin A300-53-0246, Revision 08, including Appendix 1, dated April 13, 2016. (ii) Airbus Service Bulletin A300-53-6029, Revision 12, including Appendix 1, dated April 13, 2016. (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. (4) You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on August 8, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-17203 Filed 8-18-17; 8:45 am] BILLING CODE 4910-13-P
![39520 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
Airframe and Mechanical Systems Section, and Model A300 B4–600, B4–600R, and telephone: 425–227–2125; fax: 425–
FAA, New York ACO Branch, 1600 Stewart F4–600R series airplanes, and Model 227–1149.
Avenue, Suite 410, Westbury, NY 11590; A300 C4–605R Variant F airplanes SUPPLEMENTARY INFORMATION:
telephone 516–228–7318; fax 516–794–5531.
(collectively called Model A300–600
(3) Service information identified in this Discussion
AD that is not incorporated by reference is series airplanes). This AD was prompted
available at the addresses specified in by reports of cracks initiating at the We issued a notice of proposed
paragraphs (k)(3) and (k)(4) of this AD. upper radius of a certain frame and a rulemaking (NPRM) to amend 14 CFR
determination that the current part 39 by adding an AD that would
(k) Material Incorporated by Reference
inspection procedure is not reliable in apply to certain Airbus Model A300
(1) The Director of the Federal Register detecting certain cracking of the forward series airplanes; and Model A300 B4–
approved the incorporation by reference 600, B4–600R, and F4–600R series
fitting of the frame. This AD requires
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR repetitive inspections to detect cracking airplanes, and Model A300 C4–605R
part 51. of the upper radius of the forward fitting Variant F airplanes (collectively called
(2) You must use this service information of a certain frame, and related Model A300–600 series airplanes). The
as applicable to do the actions required by investigative actions and corrective NPRM published in the Federal
this AD, unless this AD specifies otherwise. actions if necessary. We are issuing this Register on May 31, 2017 (82 FR 24903)
(i) Bombardier Service Bulletin 605–35– AD to address the unsafe condition on (‘‘the NPRM’’). The NPRM was
003, Revision 02, dated April 18, 2016. these products. prompted by reports of cracks initiating
(ii) Reserved. at the upper radius of frame (FR) 47 and
(3) For service information identified in DATES: This AD is effective September
25, 2017. a determination that the current
this AD, contact Bombardier, Inc., 400 Côte-
Vertu Road West, Dorval, Québec H4S 1Y9, inspection procedure is not reliable in
The Director of the Federal Register detecting certain cracking of the forward
Canada; Widebody Customer Response approved the incorporation by reference
Center North America toll-free telephone 1– fitting of FR 47. The NPRM proposed to
of certain publications listed in this AD require repetitive inspections to detect
866–538–1247 or direct-dial telephone 1–
514–855–2999; fax 514–855–7401; email as of September 25, 2017. cracking of the upper radius of the
ac.yul@aero.bombardier.com; Internet http:// ADDRESSES: For service information forward fitting of FR 47, and related
www.bombardier.com. identified in this final rule, contact investigative actions and corrective
(4) You may view this service information Airbus SAS, Airworthiness Office— actions if necessary. We are issuing this
at the FAA, Transport Standards Branch,
EAW, 1 Rond Point Maurice Bellonte, AD to detect and correct fatigue
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this 31707 Blagnac Cedex, France; cracking of the FR 47 forward fitting
material at the FAA, call 425–227–1221. telephone: +33 5 61 93 36 96; fax: +33 upper radius on the left-hand and right-
(5) You may view this service information 5 61 93 44 51; email: account.airworth- hand sides of the fuselage, which could
that is incorporated by reference at the eas@airbus.com; Internet: http:// propagate and result in reduced
National Archives and Records www.airbus.com. You may view this structural integrity of the airplane.
Administration (NARA). For information on referenced service information at the The European Aviation Safety Agency
the availability of this material at NARA, call FAA, Transport Standards Branch, 1601 (EASA), which is the Technical Agent
202–741–6030, or go to: http:// Lind Avenue SW., Renton, WA. For for the Member States of the European
www.archives.gov/federal-register/cfr/ibr-
information on the availability of this Union, has issued EASA AD 2016–0150,
locations.html.
material at the FAA, call 425–227–1221. dated July 25, 2016 (referred to after this
Issued in Renton, Washington, on August It is also available on the Internet at as the Mandatory Continuing
4, 2017. http://www.regulations.gov by searching Airworthiness Information, or ‘‘the
Jeffrey E. Duven, for and locating Docket No. FAA–2017– MCAI’’), to correct an unsafe condition
Director, System Oversight Division, Aircraft 0520. on all. The MCAI states:
Certification Service.
Examining the AD Docket During scheduled maintenance inspections
[FR Doc. 2017–17086 Filed 8–18–17; 8:45 am] on the fuselage, cracks initiating at the upper
BILLING CODE 4910–13–P You may examine the AD docket on radius of frame (FR) 47 have been reported
the Internet at http:// on several aeroplanes. Similar damage was
www.regulations.gov by searching for also discovered on the A300 fatigue test
DEPARTMENT OF TRANSPORTATION and locating Docket No. FAA–2017– fuselage.
0520; or in person at the Docket This condition, if not detected and
Federal Aviation Administration corrected, could reduce the structural
Management Facility between 9 a.m. integrity of the fuselage.
and 5 p.m., Monday through Friday, Prompted by these findings, Airbus issued
14 CFR Part 39 except Federal holidays. The AD docket Service Bulletin (SB) A300–53–0246, SB
[Docket No. FAA–2017–0520; Product contains this AD, the regulatory A300–53–6029 and SB A300–53–9014 to
Identifier 2016–NM–143–AD; Amendment evaluation, any comments received, and provide inspection instructions and,
39–18995; AD 2017–17–05] other information. The street address for consequently, DGAC France issued AD F–
the Docket Office (telephone 800–647– 2006–016 to require repetitive inspections
RIN 2120–AA64 and corrective action.
5527) is Docket Management Facility,
Since that [French] AD was issued, further
Airworthiness Directives; Airbus U.S. Department of Transportation, investigation led to the conclusion that the
Airplanes Docket Operations, M–30, West current ultrasonic inspection performed in
Building Ground Floor, Room W12–140, accordance with Airbus SB A300–53–0246
AGENCY: Federal Aviation
sradovich on DSK3GMQ082PROD with RULES
1200 New Jersey Avenue SE., Revision 06, or SB A300–53–6029 Revision
Administration (FAA), Department of Washington, DC 20590. 08, or SB A300–53–9014 Revision 01, as
Transportation (DOT). applicable, was not reliable to detect deep
ACTION: Final rule. FOR FURTHER INFORMATION CONTACT: Dan
crack going downward.
Rodina, Aerospace Engineer, Consequently, to ensure the crack depth is
SUMMARY: We are adopting a new International Section, Transport correctly measured whatever the crack
airworthiness directive (AD) for certain Standards Branch, FAA, 1601 Lind direction, Airbus developed a new
Airbus Model A300 series airplanes; Avenue SW., Renton, WA 98057–3356; nondestructive testing method [eddy current]
VerDate Sep<11>2014 16:12 Aug 18, 2017 Jkt 241001 PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 E:\FR\FM\21AUR1.SGM 21AUR1](https://thefederalregister.org/doc/82_FR_39680/page/1.svg)
![Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39521
for this special detailed inspection (SDI) and Comments including Appendix 1, dated April 13,
revised the affected SBs accordingly. 2016 (for Model A300 series airplanes);
We gave the public the opportunity to
For the reasons described above, this and Airbus Service Bulletin A300–53–
participate in developing this AD. We
[EASA] AD retains the requirements of DGAC 6029, Revision 12, including Appendix
received no comments on the NPRM or
France AD F–2006–016, which is 1, dated April 13, 2016 (for Model
on the determination of the cost to the
superseded, but requires the accomplishment A300–600 series airplanes). The service
public.
of repetitive SDI to replace the previously
information describes procedures for
required ultrasonic inspections [and related Conclusion
doing an SDI for cracking of the FR 47
investigative and corrective actions if We reviewed the relevant data and
necessary].
forward fitting upper radius on the left-
determined that air safety and the hand and right-hand sides of the
Related investigative actions include an public interest require adopting this AD fuselage, and related investigative and
ultrasonic inspection for cracking on the as proposed except for minor editorial corrective actions. This service
forward face of the forward fitting and changes. We have determined that these information is reasonably available
minor changes:
a detailed inspection for cracking of the • Are consistent with the intent that because the interested parties have
aft fitting around the fasteners. was proposed in the NPRM for access to it through their normal course
Corrective actions include crack repairs, correcting the unsafe condition; and of business or by the means identified
and modification of the sealing fittings • Do not add any additional burden in the ADDRESSES section.
and sealing shims. This AD requires upon the public than was already
reporting of the inspection results to Costs of Compliance
proposed in the NPRM.
Airbus. You may examine the MCAI in We estimate that this AD will affect
the AD docket on the Internet at http:// Related Service Information Under 1
CFR Part 51 132 airplanes of U.S. registry.
www.regulations.gov by searching for
and locating Docket No. FAA–2017– Airbus has issued Airbus Service We estimate the following costs to
0520. Bulletin A300–53–0246, Revision 08, comply with this AD:
ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspection ............ 19 work-hours × $85 per hour = $0 $1,615 per inspection cycle ......... $213,180 per inspection cycle.
$1,615.
Reporting ............. 1 work-hour × $85 per hour = $85 $0 $85 per inspection cycle .............. $11,220 per inspection cycle.
We estimate the following costs to do required based on the results of the determining the number of aircraft that
any necessary related investigative and inspection. We have no way of might need these repairs:
corrective actions that would be
ON-CONDITION COSTS
Cost per
Action Labor cost Parts cost product
Related investigative and Corrective actions ............... 21 work-hours × $85 per hour = $1,785 ...................... $1,835 $3,620
Paperwork Reduction Act should be directed to the FAA at 800 the Administrator finds necessary for
Independence Ave. SW., Washington, safety in air commerce. This regulation
A federal agency may not conduct or
DC 20591, ATTN: Information is within the scope of that authority
sponsor, and a person is not required to
Collection Clearance Officer, AES–200. because it addresses an unsafe condition
respond to, nor shall a person be subject
to penalty for failure to comply with a Authority for This Rulemaking that is likely to exist or develop on
collection of information subject to the products identified in this rulemaking
requirements of the Paperwork Title 49 of the United States Code action.
Reduction Act unless that collection of specifies the FAA’s authority to issue This AD is issued in accordance with
information displays a current valid rules on aviation safety. Subtitle I, authority delegated by the Executive
OMB control number. The control section 106, describes the authority of Director, Aircraft Certification Service,
number for the collection of information the FAA Administrator. ‘‘Subtitle VII:
as authorized by FAA Order 8000.51C.
required by this AD is 2120–0056. The Aviation Programs,’’ describes in more
In accordance with that order, issuance
paperwork cost associated with this AD detail the scope of the Agency’s
authority. of ADs is normally a function of the
has been detailed in the Costs of Compliance and Airworthiness
Compliance section of this document We are issuing this rulemaking under Division, but during this transition
sradovich on DSK3GMQ082PROD with RULES
and includes time for reviewing the authority described in ‘‘Subtitle VII, period, the Executive Director has
instructions, as well as completing and Part A, Subpart III, Section 44701: delegated the authority to issue ADs
reviewing the collection of information. General requirements.’’ Under that
applicable to transport category
Therefore, all reporting associated with section, Congress charges the FAA with
airplanes to the Director of the System
this AD is mandatory. Comments promoting safe flight of civil aircraft in
Oversight Division.
concerning the accuracy of this burden air commerce by prescribing regulations
and suggestions for reducing the burden for practices, methods, and procedures
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![39522 Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations
Regulatory Findings (3) Model A300 B4–605R and B4–622R (i) Inspections for Airplanes With Abnormal
airplanes. Load Events
We determined that this AD will not (4) Model A300 F4–605R and F4–622R
have federalism implications under For airplanes on which any crack was
airplanes. found during any inspection done as
Executive Order 13132. This AD will (5) Model A300 C4–605R Variant F specified in Airbus Service Bulletin A300–
not have a substantial direct effect on airplanes. 53–0246 or Airbus Service Bulletin A300–
the States, on the relationship between 53–6029, as applicable, and on which any
the national government and the States, (d) Subject
abnormal load event, such as hard landing or
or on the distribution of power and Air Transport Association (ATA) of flight in excessive turbulence, occurred
responsibilities among the various America Code 53, Fuselage. within 3 months before the effective date of
levels of government. (e) Reason this AD or occurs on or after the effective
For the reasons discussed above, I date of this AD: Within 3 months after each
This AD was prompted by reports of cracks event, accomplish an SDI for cracking of the
certify that this AD:
initiating at the upper radius of frame (FR) FR 47 forward fitting upper radius, left-hand
1. Is not a ‘‘significant regulatory
47 and a determination that the current and right-hand sides of the fuselage, in
action’’ under Executive Order 12866; inspection procedure is not reliable in
2. Is not a ‘‘significant rule’’ under the accordance with the applicable
detecting certain cracking of the forward Accomplishment Instructions of the Airbus
DOT Regulatory Policies and Procedures fitting of FR 47. We are issuing this AD to service information specified in paragraphs
(44 FR 11034, February 26, 1979); detect and correct fatigue cracking of the FR (g)(1) or (g)(2) of this AD. If, during this 3-
3. Will not affect intrastate aviation in 47 forward fitting upper radius on the left- month period, another abnormal load event
Alaska; and hand and right-hand sides of the fuselage, occurs, and if no SDI has yet been
4. Will not have a significant which could propagate and result in reduced accomplished, before further flight after the
economic impact, positive or negative, structural integrity of the airplane. second event, obtain corrective action
on a substantial number of small entities instructions from the Manager, International
(f) Compliance
under the criteria of the Regulatory Section, Transport Standards Branch, FAA;
Flexibility Act. Comply with this AD within the or the European Aviation Safety Agency
compliance times specified, unless already (EASA); or Airbus’s EASA Design
List of Subjects in 14 CFR Part 39 done. Organization Approval (DOA), and
Air transportation, Aircraft, Aviation accomplish those instructions accordingly.
(g) Repetitive Inspections
safety, Incorporation by reference, (j) Corrective Actions for Airplanes With
Except as required by paragraph (h) of this
Safety. AD: Before exceeding 10,000 flight cycles Cracks
Adoption of the Amendment since first flight of the airplane or within 30 If, during any SDI as required by paragraph
days after the effective date of this AD, (g), (h), or (i) of this AD, any crack is found:
Accordingly, under the authority whichever occurs later, do a special detailed Before further flight, do the applicable
delegated to me by the Administrator, inspection (SDI) for cracking of the FR 47 related investigative and corrective actions,
the FAA amends 14 CFR part 39 as forward fitting upper radius on the left-hand in accordance with the Accomplishment
follows: and right-hand sides of the fuselage, in Instructions of the applicable Airbus service
accordance with the Accomplishment information specified in paragraph (g)(1) or
PART 39—AIRWORTHINESS Instructions of the applicable Airbus service (g)(2) of this AD, and obtain additional
DIRECTIVES information specified in paragraphs (g)(1) corrective action instructions from the
and (g)(2) of this AD. Repeat the inspection Manager, International Section, Transport
■ 1. The authority citation for part 39 thereafter at intervals not to exceed 4,150 Standards Branch, FAA; or EASA; or
continues to read as follows: flight cycles, except as required by paragraph Airbus’s EASA DOA, and accomplish those
(j) of this AD. instructions accordingly before further flight.
Authority: 49 U.S.C. 106(g), 40113, 44701.
(1) Airbus Service Bulletin A300–53–0246, (k) Reporting
§ 39.13 [Amended] Revision 08, including Appendix 1, dated
Submit a report of the findings (both
■ 2. The FAA amends § 39.13 by adding April 13, 2016.
positive and negative) of each SDI inspection
(2) Airbus Service Bulletin A300–53–6029,
the following new airworthiness required by paragraphs (g), (h), and (i) of this
Revision 12, including Appendix 1, dated AD to Airbus Service Bulletin Reporting
directive (AD): April 13, 2016. Online Application on Airbus World (https://
2017–17–05 Airbus: Amendment 39–18995; w3.airbus.com/), at the applicable time
Docket No. FAA–2017–0520; Product (h) Initial Inspection for Airplanes
Previously Inspected specified in paragraph (k)(1) or (k)(2) of this
Identifier 2016–NM–143–AD.
AD.
For airplanes previously inspected as
(a) Effective Date (1) If the inspection was done on or after
specified in the applicable Airbus service
This AD is effective September 25, 2017. the effective date of this AD: Submit the
information specified in paragraphs (h)(1) report within 30 days after the inspection.
(b) Affected ADs through (h)(6) of this AD and on which no (2) If the inspection was done before the
cracking was found: Within 4,150 flight effective date of this AD: Submit the report
This AD affects AD 2007–26–14, cycles after the most recent inspection, do
Amendment 39–15316 (73 FR 2803, January within 30 days after the effective date of this
the inspection for cracking of the FR 47 AD.
16, 2008) (‘‘AD 2007–26–14’’).
forward fitting upper radius required by
(c) Applicability paragraph (g) of this AD. (l) Terminating Action for AD 2007–26–14
This AD applies to the Airbus airplanes (1) Airbus Service Bulletin A300–53–0246, Accomplishing any inspection required by
identified in paragraphs (c)(1) through (c)(5) Revision 06, dated October 19, 2005. paragraph (g) or (h) of this AD terminates all
of this AD, certificated in any category, (2) Airbus Service Bulletin A300–53–0246, requirements of AD 2007–26–14 for the
except airplanes that have been repaired as Revision 07, dated September 9, 2008. inspected airplane.
sradovich on DSK3GMQ082PROD with RULES
specified in Airbus Service Bulletin A300– (3) Airbus Service Bulletin A300–53–6029,
Revision 08, dated October 19, 2005. (m) Other FAA AD Provisions
53–0370; or Airbus Service Bulletin A300–
53–6144, as applicable. (4) Airbus Service Bulletin A300–53–6029, The following provisions also apply to this
(1) Model A300 B2–1A, B2–1C, B2K–3C, Revision 09, dated September 9, 2008. AD:
B2–203, B4–2C, B4–103, and B4–203 (5) Airbus Service Bulletin A300–53–6029, (1) Alternative Methods of Compliance
airplanes. Revision 10, dated July 9, 2009. (AMOCs): The Manager, International
(2) Model A300 B4–601, B4–603, B4–620, (6) Airbus Service Bulletin A300–53–6029, Section, Transport Standards Branch, FAA,
and B4–622 airplanes. Revision 11, dated September 28, 2009. has the authority to approve AMOCs for this
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![Federal Register / Vol. 82, No. 160 / Monday, August 21, 2017 / Rules and Regulations 39523
AD, if requested using the procedures found (ii) Airbus Service Bulletin A300–53–6029, Helicopters, Inc., Attn: Customer
in 14 CFR 39.19. In accordance with 14 CFR Revision 12, including Appendix 1, dated Support Division, 4555 E. McDowell
39.19, send your request to your principal April 13, 2016. Rd., Mail Stop M615, Mesa, AZ 85215–
inspector or local Flight Standards District (3) For service information identified in
9734; telephone 1–800–388–3378; fax
Office, as appropriate. If sending information this AD, contact Airbus SAS, Airworthiness
Office—EAW, 1 Rond Point Maurice 480–346–6813; or at http://
directly to the International Section, send it
to the attention of the person identified in Bellonte, 31707 Blagnac Cedex, France; www.mdhelicopters.com. You may
paragraph (n)(2) of this AD. Information may telephone: +33 5 61 93 36 96; fax: +33 5 61 review the referenced service
be emailed to: 9-ANM-116-AMOC- 93 44 51; email: account.airworth-eas@ information at the FAA, Office of the
REQUESTS@faa.gov. Before using any airbus.com; Internet: http://www.airbus.com. Regional Counsel, Southwest Region,
approved AMOC, notify your appropriate (4) You may view this service information 10101 Hillwood Pkwy, Room 6N–321,
principal inspector, or lacking a principal at the FAA, Transport Standards Branch, Fort Worth, TX 76177. It is also
inspector, the manager of the local flight 1601 Lind Avenue SW., Renton, WA. For available on the Internet at http://
standards district office/certificate holding information on the availability of this
www.regulations.gov by searching for
district office. material at the FAA, call 425–227–1221.
(5) You may view this service information and locating Docket No. FAA–2017–
(2) Contacting the Manufacturer: For any 0270.
requirement in this AD to obtain corrective that is incorporated by reference at the
actions from a manufacturer, the action must National Archives and Records Examining the AD Docket
be accomplished using a method approved Administration (NARA). For information on
the availability of this material at NARA, call You may examine the AD docket on
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
202–741–6030, or go to: http:// the Internet at http://
www.archives.gov/federal-register/cfr/ibr- www.regulations.gov in Docket No.
or Airbus’s EASA DOA. If approved by the
locations.html. FAA–2017–0270; or in person at the
DOA, the approval must include the DOA-
authorized signature. Issued in Renton, Washington, on August Docket Management Facility between 9
(3) Reporting Requirements: A federal 8, 2017. a.m. and 5 p.m., Monday through
agency may not conduct or sponsor, and a Dionne Palermo, Friday, except Federal holidays. The AD
person is not required to respond to, nor Acting Director, System Oversight Division, docket contains this AD, any
shall a person be subject to a penalty for Aircraft Certification Service. incorporated-by-reference information,
failure to comply with a collection of the economic evaluation, any comments
[FR Doc. 2017–17203 Filed 8–18–17; 8:45 am]
information subject to the requirements of
BILLING CODE 4910–13–P
received, and other information. The
the Paperwork Reduction Act unless that
collection of information displays a current address for the Docket Office (phone:
valid OMB Control Number. The OMB 800–647–5527) is Document
Control Number for this information DEPARTMENT OF TRANSPORTATION Management Facility, U.S. Department
collection is 2120–0056. Public reporting for of Transportation, Docket Operations,
this collection of information is estimated to Federal Aviation Administration M–30, West Building Ground Floor,
be approximately 5 minutes per response, Room W12–140, 1200 New Jersey
including the time for reviewing instructions, 14 CFR Part 39 Avenue SE., Washington, DC 20590.
completing and reviewing the collection of
[Docket No. FAA–2017–0270; Product FOR FURTHER INFORMATION CONTACT: Eric
information. All responses to this collection
of information are mandatory. Comments Identifier 2016–SW–032–AD; Amendment Schrieber, Aviation Safety Engineer, Los
concerning the accuracy of this burden and 39–18993; AD 2017–17–03] Angeles ACO Branch, Compliance and
suggestions for reducing the burden should RIN 2120–AA64
Airworthiness Division, FAA, 3960
be directed to the FAA at: 800 Independence Paramount Blvd., Lakewood, California
Ave. SW., Washington, DC 20591, Attn: Airworthiness Directives; MD 90712; telephone (562) 627–5348; email
Information Collection Clearance Officer, Helicopters, Inc., Helicopters eric.schrieber@faa.gov.
AES–200. SUPPLEMENTARY INFORMATION:
(n) Related Information
AGENCY: Federal Aviation
Administration (FAA), DOT. Discussion
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD ACTION: Final rule. We issued a notice of proposed
2016–0150, dated July 25, 2016, for related rulemaking (NPRM) to amend 14 CFR
SUMMARY: We are superseding part 39 to remove AD 2014–16–01,
information. This MCAI may be found in the
AD docket on the Internet at http:// Airworthiness Directive (AD) 2014–16– Amendment 39–17925 (79 FR 45322,
www.regulations.gov by searching for and 01 for MD Helicopters, Inc. (MDHI), August 5, 2014) and add a new AD. AD
locating Docket No. FAA–2017–0520. Model MD900 helicopters. AD 2014– 2014–16–01 applied to MDHI Model
(2) For more information about this AD, 16–01 required an eddy current MD900 helicopters, serial numbers 900–
contact Dan Rodina, Aerospace Engineer, inspection of the main rotor upper hub 00008 through 900–00140, with an
International Section, Transport Standards assembly (upper hub) for a crack. This
Branch, FAA, 1601 Lind Avenue SW.,
upper hub part number (P/N)
AD requires additional inspections and 900R2101006–105, –107, –109, or –111
Renton, WA 98057–3356; telephone: 425– replacing the fillet seal. This AD was
227–2125; fax: 425–227–1149. installed. AD 2014–16–01 required eddy
prompted by three additional reports of current inspecting the upper hub and
(o) Material Incorporated by Reference upper hub cracks. The actions of this replacing it if there is a crack. The
(1) The Director of the Federal Register AD are intended to prevent an unsafe NPRM published in the Federal
approved the incorporation by reference condition on these products. Register on April 3, 2017 (82 FR 16138).
(IBR) of the service information listed in this DATES: This AD is effective September The NPRM was prompted by reports
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paragraph under 5 U.S.C. 552(a) and 1 CFR 25, 2017. of three additional cracks found in the
part 51. The Director of the Federal Register
(2) You must use this service information
MD900 fleet. These cracks were not
approved the incorporation by reference discovered by the one-time eddy current
as applicable to do the actions required by
of a certain publication listed in this AD inspection required by AD 2014–16–01,
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A300–53–0246, as of September 25, 2017. but were found during regular
Revision 08, including Appendix 1, dated ADDRESSES: For service information maintenance of the upper hub. The
April 13, 2016. identified in this final rule, contact MD NPRM proposed to require for MDHI
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Document Created: 2017-08-19 00:44:43
Document Modified: 2017-08-19 00:44:43
| 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 | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective September 25, 2017. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone: 425-227-2125; fax: 425- 227-1149. | |
| FR Citation | 82 FR 39520 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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