83 FR 33821 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 138 (July 18, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 138 (July 18, 2018)
| Page Range | 33821-33825 | |
| FR Document | 2018-13220 |
[Federal Register Volume 83, Number 138 (Wednesday, July 18, 2018)] [Rules and Regulations] [Pages 33821-33825] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-13220] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD; Amendment 39-19312; AD 2018-12-08] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2017-07-07, which applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes. AD 2017-07-07 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This AD retains the requirements of AD 2017-07-07 and expands the applicability. This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 22, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 22, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0111. 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-2018- 0111; 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 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: Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017) (``AD 2017-07-07''). AD 2017-07-07 applied to certain Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes with manufacturer serial numbers (MSN) 0176 through 0915 inclusive. The NPRM published in the Federal Register on February 20, 2018 (83 FR 7117). The NPRM was prompted by a report of cracking at fastener holes located at frame FR40 on the lower shell panel junction. The NPRM proposed to retain the requirements of AD 2017-07-07 and expand the applicability. We are issuing this AD to detect and correct cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2017-0063, dated April 12, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330-200, A330- 300, and A340-200 series airplanes, and Model A340-312 and -313 airplanes. The MCAI states: During full scale fatigue test of the Frame (FR) 40 to fuselage skin panel junction, fatigue damage was found. Corrective actions consisted of in-service installation of an internal reinforcing strap on the related junction, as currently required by DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France AD 1999-448-126(B), which refers to Airbus Service Bulletin (SB) A340- 53-4104 Revision 02, and [DGAC] AD 2001-070(B), which refers to Airbus SB A330-53-3093 Revision 04; retrofit improvement of internal reinforcing strap fatigue life through recommended Airbus SB A330- 53-3145; and [[Page 33822]] introducing a design improvement in production through Airbus mod 44360. After those actions were implemented, cracks were found on both left-hand (LH) and right-hand (RH) sides on internal strap, butt strap, keel beam fitting, or forward fitting FR40 flange. These findings were made during embodiment of a FR40 web repair on an A330 aeroplane, and during keel beam replacement on an A340 aeroplane, where the internal strap was removed and a special detailed inspection (SDI) was performed on several holes. This condition, if not detected and corrected, could affect the structural integrity of the centre fuselage of the aeroplane. Prompted by these findings, Airbus issued SB A330-53-3215 and SB A340-53-4215, providing inspection instructions. Consequently, EASA issued AD 2014-0136 [which corresponds to FAA AD 2017-07-07] to require repetitive SDI (rototest) of 10 fastener holes located at the FR40 lower shell panel junction on both LH and RH sides and, depending on findings, accomplishment of applicable corrective action(s). Since that [EASA] AD was issued, prompted by the results of complementary fatigue analyses, it was determined that post-mod 55792 aeroplanes could be also affected by crack initiation and propagation at this area of the fuselage. These analyses demonstrated that post-mod 55792 aeroplanes must follow the same maintenance program as aeroplanes in post-mod 55306 and pre-mod 55792 configuration. Consequently, Airbus published SB A330-53-3215 Revision 02 and SB A340-53-4215 Revision 02 to expand the Effectivity accordingly. For the reasons described above, this [EASA] AD retains the requirements of EASA AD 2014-0136, which is superseded, which now also apply to aeroplanes in post-mod 55792 configuration [the applicability identifies airplanes in post-mod 44360 configuration]. AD 2017-07-07 includes Model A340-211 airplanes in its applicability. Airbus Model A340-211 airplanes are not identified in the applicability of this AD because those airplanes are not affected by the identified unsafe condition. All of those airplanes are in the pre-Airbus modification 44360 configuration. The MCAI also does not include Model A340-211 airplanes in its applicability. The compliance time ranges between 20,000 flight cycles or 65,400 flight hours and 20,800 flight cycles or 68,300 flight hours, depending on airplane utilization and configuration. The repetitive inspection interval ranges between 14,000 flight cycles or 95,200 flight hours and 24,600 flight cycles or 98,700 flight hours, depending on airplane utilization and configuration. 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-2018-0111. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. Kenneth Ciallella supported the NPRM. Explanation of Changes Made to This AD We have revised this AD to refer to Airbus Service Bulletin A330- 53-3215, Revision 03, dated January 22, 2018, as the appropriate source of service information for the required actions. This service information incorporates minor editorial changes which have no effect on airplanes that have incorporated prior revisions of this service information. We have revised table 1 to paragraph (g)(1) of this AD and paragraphs (g), (g)(1), (g)(2), (h), (h)(1), (h)(2), and (i) of this AD to specify Airbus Service Bulletin A330-53-3215, Revision 03, dated January 22, 2018, as the appropriate source of service information for accomplishing the required actions in those paragraphs. We have revised paragraph (j) of this AD to give credit for using Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016, to accomplish the required actions before the effective date of this AD. Conclusion We reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting this AD as proposed except for the changes described previously and 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 A330-53-3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3'') and Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016. This service information describes procedures for repetitive rototest inspections of certain fastener holes, and related investigative and corrective actions if necessary. These documents are distinct since they apply to different airplane models. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 99 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs for Required Actions ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- 42 work-hours x $85 per hour = $3,570........................ $0 $3,570 $353,430 ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that would be required based on the results of the required inspections. We have no way of determining the number of aircraft that might need these repairs: Estimated Costs of On-Condition Actions ------------------------------------------------------------------------ Cost per Labor cost Parts cost product ------------------------------------------------------------------------ 46 work-hours x $85 per hour = $3,910. $2,358 $6,268 ------------------------------------------------------------------------ [[Page 33823]] 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. 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 removing Airworthiness Directive (AD) 2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017), and adding the following new AD: 2018-12-08 Airbus: Amendment 39-19312; Docket No. FAA-2018-0111; Product Identifier 2017-NM-059-AD. (a) Effective Date This AD is effective August 22, 2018. (b) Affected ADs This AD replaces AD 2017-07-07, Amendment 39-18845 (82 FR 18547, April 20, 2017) (``AD 2017-07-07''). (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, all manufacturer serial numbers on which Airbus Modification 44360 has been embodied in production. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-212, -213, -312, and -313 airplanes. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by a report of cracking at fastener holes located at frame (FR) 40 on the lower shell panel junction. We are issuing this AD to detect and correct cracking at FR40 on the lower shell panel junction; such cracking could lead to reduced structural integrity of the fuselage. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Compliance Times for the Actions Required by Paragraph (h) of This AD Accomplish the actions required by paragraph (h) of this AD at the times specified in paragraphs (g)(1) and (g)(2) of this AD, as applicable. (1) For airplanes having serial numbers 0176 through 0915 inclusive: Within the compliance times defined in table 1 to paragraph (g)(1) of this AD, and, thereafter, at intervals not to exceed the compliance times defined in Airbus Service Bulletin A330- 53-3215, Revision 03, dated January 22, 2018 (``A330-53-3215, R3''); or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016 (``A340-53-4215, R2''); as applicable, depending on airplane utilization and configuration. As of the effective date of this AD, where paragraph 1.E. ``Compliance,'' of A330-53-3215, R3 specifies weight variant (WV) 050 in the condition column of table 1, configuration 003, for the purposes of this AD, WV060 and WV080 are also included. [[Page 33824]] [GRAPHIC] [TIFF OMITTED] TR18JY18.000 (2) For all airplanes except those identified in paragraph (g)(1) of this AD: Before exceeding the applicable compliance time ``threshold'' defined in paragraph 1.E., ``Compliance,'' of A330-53- 3215, R3; or A340-53-4215, R2; as applicable, depending on airplane utilization and configuration and to be counted from airplane first flight, and, thereafter, at intervals not to exceed the compliance times specified in paragraph 1.E., ``Compliance'' of A330-53-3215, R3; or A340-53-4215, R2; as applicable, depending on airplane utilization and configuration. Where paragraph 1.E. ``Compliance,'' of A330-53-3215, R3 specifies weight variant WV050 in the condition column of table 1, configuration 003, for the purposes of this AD, WV060 and WV080 are also included. (h) Repetitive Inspections and Related Investigative and Corrective Actions At the applicable compliance times specified in paragraph (g) of this AD: Accomplish a special detailed inspection of the 10 fastener holes located at FR40 lower shell panel junction on both left-hand and right-hand sides, in accordance with the Accomplishment Instructions of A330-53-3215, R3; or A340-53-4215, R2; as applicable. (1) If, during any inspection required by the introductory text of paragraph (h) of this AD, any crack is detected, before further flight, accomplish all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of A330-53-3215, R3; or A340-53-4215, R2; as applicable, except where A330-53-3215, R3; or A340-53-4215, R2; specifies to contact Airbus for repair instructions, and specifies that action as ``RC,'' this AD requires repair before further flight using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (2) If, during any inspection required by the introductory text of paragraph (h) of this AD, the diameter of a fastener hole is found to be outside the tolerances of the transition fit as specified in A330-53-3215, R3; or A340-53-4215, R2; as applicable; and A330-53-3215, R3; or A340-53-4215, R2; specifies to contact Airbus for repair instructions, and specifies that action as ``RC,'' before further flight, repair 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) Accomplishment of corrective actions, as required by paragraph (h)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD. (4) Accomplishment of a repair on an airplane, as required by paragraph (h)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (h) of this AD for that airplane, unless the method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA indicates otherwise. (i) No Reporting Requirement Although A330-53-3215, R3 and A340-53-4215, R2, specify to submit certain information to the manufacturer, and specify that action as ``RC,'' this AD does not include that requirement. (j) Credit for Previous Actions This paragraph provides credit for the inspections required by the introductory text of (h) of this AD and the related investigative and corrective actions required by paragraph (h)(1) of this AD, if those actions were performed before May 25, 2017 (the effective date of AD 2017-07-07), using Airbus Service Bulletin A330-53-3215, dated June 21, 2013; or Revision 01, dated April 17, 2014; or Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated April 17, 2014; as applicable. (k) 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 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 (l)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International 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) Required for Compliance (RC): Except as required by paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (i) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an [[Page 33825]] airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (l) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0063, dated April 12, 2017, 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-2018-0111. (2) For more information about this AD, contact Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (m) 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 A330-53-3215, Revision 03, dated January 22, 2018. (ii) Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 45 80; email: airworthiness.A330-A340@airbus.com; internet: http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (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 Des Moines, Washington, on June 6, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-13220 Filed 7-17-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33821
identified in an RC step, must be done to DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket
comply with the AD. If a step or substep is contains this AD, the regulatory
labeled ‘‘RC Exempt,’’ then the RC Federal Aviation Administration evaluation, any comments received, and
requirement is removed from that step or other information. The address for the
substep. An AMOC is required for any 14 CFR Part 39 Docket Office (telephone: 800–647–
deviations to RC steps, including substeps 5527) is Docket Management Facility,
[Docket No. FAA–2018–0111; Product
and identified figures. U.S. Department of Transportation,
Identifier 2017–NM–059–AD; Amendment
(ii) Steps not labeled as RC may be 39–19312; AD 2018–12–08] Docket Operations, M–30, West
deviated from using accepted methods in Building Ground Floor, Room W12–140,
accordance with the operator’s maintenance RIN 2120–AA64
1200 New Jersey Avenue SE,
or inspection program without obtaining Washington, DC 20590.
approval of an AMOC, provided the RC steps, Airworthiness Directives; Airbus
Airplanes FOR FURTHER INFORMATION CONTACT:
including substeps and identified figures, can
Vladimir Ulyanov, Aerospace Engineer,
still be done as specified, and the airplane AGENCY: Federal Aviation International Section, Transport
can be put back in an airworthy condition. Administration (FAA), Department of Standards Branch, FAA, 2200 South
(k) Related Information Transportation (DOT). 216th St., Des Moines, WA 98198;
For more information about this AD, ACTION: Final rule. telephone and fax: 206–231–3229.
contact Allen Rauschendorfer, Aerospace SUPPLEMENTARY INFORMATION:
Engineer, Airframe Section, FAA, Seattle
SUMMARY: We are superseding
Airworthiness Directive (AD) 2017–07– Discussion
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
07, which applied to certain Airbus We issued a notice of proposed
3528; email: allen.rauschendorfer@faa.gov. Model A330–200, A330–300, A340–200, rulemaking (NPRM) to amend 14 CFR
and A340–300 series airplanes. AD part 39 to supersede AD 2017–07–07,
(l) Material Incorporated by Reference 2017–07–07 required repetitive Amendment 39–18845 (82 FR 18547,
(1) The Director of the Federal Register inspections of certain fastener holes, April 20, 2017) (‘‘AD 2017–07–07’’). AD
approved the incorporation by reference and related investigative and corrective 2017–07–07 applied to certain Airbus
(IBR) of the service information listed in this actions if necessary. This AD retains the Model A330–200, A330–300, A340–200,
paragraph under 5 U.S.C. 552(a) and 1 CFR requirements of AD 2017–07–07 and and A340–300 series airplanes with
part 51. expands the applicability. This AD was manufacturer serial numbers (MSN)
(2) You must use this service information prompted by a report of cracking at 0176 through 0915 inclusive. The
as applicable to do the actions required by fastener holes located at frame (FR) 40 NPRM published in the Federal
this AD, unless the AD specifies otherwise. on the lower shell panel junction. We Register on February 20, 2018 (83 FR
(i) Aviation Partners Boeing Service are issuing this AD to address the unsafe 7117). The NPRM was prompted by a
Bulletin AP767–57–013, Revision 1, dated condition on these products. report of cracking at fastener holes
April 11, 2017. DATES: This AD is effective August 22, located at frame FR40 on the lower shell
(ii) Reserved. 2018. panel junction. The NPRM proposed to
(3) For service information identified in The Director of the Federal Register retain the requirements of AD 2017–07–
this AD, contact Aviation Partners Boeing, approved the incorporation by reference 07 and expand the applicability. We are
2811 S 102nd Street, Suite 200, Seattle, WA of certain publications listed in this AD issuing this AD to detect and correct
98168; telephone 206–762–1171; internet as of August 22, 2018. cracking at FR40 on the lower shell
https://www.aviationpartnersboeing.com.
ADDRESSES: For service information panel junction; such cracking could lead
(4) You may view this service information
identified in this final rule, contact to reduced structural integrity of the
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For Airbus SAS, Airworthiness Office— fuselage.
information on the availability of this EAL, 1 Rond Point Maurice Bellonte, The European Aviation Safety Agency
material at the FAA, call 206–231–3195. 31707 Blagnac Cedex, France; (EASA), which is the Technical Agent
(5) You may view this service information telephone: +33 5 61 93 36 96; fax: +33 for the Member States of the European
that is incorporated by reference at the 5 61 93 45 80; email: Union, has issued EASA AD 2017–0063,
National Archives and Records airworthiness.A330-A340@airbus.com; dated April 12, 2017 (referred to after
Administration (NARA). For information on internet: http://www.airbus.com. You this as the Mandatory Continuing
the availability of this material at NARA, call may view this referenced service Airworthiness Information, or ‘‘the
202–741–6030, or go to: http:// information at the FAA, Transport MCAI’’), to correct an unsafe condition
www.archives.gov/federal-register/cfr/ibr- Standards Branch, 2200 South 216th St., for certain Airbus Model A330–200,
locations.html. Des Moines, WA. For information on the A330–300, and A340–200 series
availability of this material at the FAA, airplanes, and Model A340–312 and
Issued in Des Moines, Washington, on June –313 airplanes. The MCAI states:
call 206–231–3195. It is also available
12, 2018.
on the internet at http:// During full scale fatigue test of the Frame
Michael Kaszycki, www.regulations.gov by searching for (FR) 40 to fuselage skin panel junction,
Acting Director, System Oversight Division, and locating Docket No. FAA–2018– fatigue damage was found. Corrective actions
Aircraft Certification Service. 0111. consisted of in-service installation of an
[FR Doc. 2018–13362 Filed 7–17–18; 8:45 am] internal reinforcing strap on the related
Examining the AD Docket junction, as currently required by DGAC
BILLING CODE 4910–13–P
You may examine the AD docket on [Direction Générale de l’Aviation Civile]
amozie on DSK3GDR082PROD with RULES
the internet at http:// France AD 1999–448–126(B), which refers to
Airbus Service Bulletin (SB) A340–53–4104
www.regulations.gov by searching for Revision 02, and [DGAC] AD 2001–070(B),
and locating Docket No. FAA–2018– which refers to Airbus SB A330–53–3093
0111; or in person at the Docket Revision 04; retrofit improvement of internal
Management Facility between 9 a.m. reinforcing strap fatigue life through
and 5 p.m., Monday through Friday, recommended Airbus SB A330–53–3145; and
VerDate Sep<11>2014 17:26 Jul 17, 2018 Jkt 244001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\18JYR1.SGM 18JYR1](https://thefederalregister.org/doc/83_FR_33959/page/1.svg)
![33822 Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations
introducing a design improvement in condition. All of those airplanes are in We have revised paragraph (j) of this
production through Airbus mod 44360. the pre-Airbus modification 44360 AD to give credit for using Airbus
After those actions were implemented, configuration. The MCAI also does not Service Bulletin A330–53–3215,
cracks were found on both left-hand (LH) and
right-hand (RH) sides on internal strap, butt
include Model A340–211 airplanes in Revision 02, dated November 23, 2016,
strap, keel beam fitting, or forward fitting its applicability. to accomplish the required actions
FR40 flange. These findings were made The compliance time ranges between before the effective date of this AD.
during embodiment of a FR40 web repair on 20,000 flight cycles or 65,400 flight
Conclusion
an A330 aeroplane, and during keel beam hours and 20,800 flight cycles or 68,300
replacement on an A340 aeroplane, where flight hours, depending on airplane We reviewed the available data,
the internal strap was removed and a special utilization and configuration. The including the comments received, and
detailed inspection (SDI) was performed on repetitive inspection interval ranges determined that air safety and the
several holes.
This condition, if not detected and between 14,000 flight cycles or 95,200 public interest require adopting this AD
corrected, could affect the structural integrity flight hours and 24,600 flight cycles or as proposed except for the changes
of the centre fuselage of the aeroplane. 98,700 flight hours, depending on described previously and minor
Prompted by these findings, Airbus issued airplane utilization and configuration. editorial changes. We have determined
SB A330–53–3215 and SB A340–53–4215, You may examine the MCAI in the AD that these minor changes:
providing inspection instructions. docket on the internet at http:// • Are consistent with the intent that
Consequently, EASA issued AD 2014–0136 www.regulations.gov by searching for was proposed in the NPRM for
[which corresponds to FAA AD 2017–07–07]
and locating Docket No. FAA–2018– correcting the unsafe condition; and
to require repetitive SDI (rototest) of 10
fastener holes located at the FR40 lower shell 0111. • Do not add any additional burden
panel junction on both LH and RH sides and, upon the public than was already
Comments
depending on findings, accomplishment of proposed in the NPRM.
applicable corrective action(s). We gave the public the opportunity to
Since that [EASA] AD was issued, participate in developing this AD. We Related Service Information Under 1
prompted by the results of complementary considered the comment received. CFR Part 51
fatigue analyses, it was determined that post- Kenneth Ciallella supported the NPRM. Airbus has issued Airbus Service
mod 55792 aeroplanes could be also affected
Bulletin A330–53–3215, Revision 03,
by crack initiation and propagation at this Explanation of Changes Made to This
area of the fuselage. These analyses dated January 22, 2018 (‘‘A330–53–
AD
demonstrated that post-mod 55792 3215, R3’’) and Airbus Service Bulletin
aeroplanes must follow the same We have revised this AD to refer to A340–53–4215, Revision 02, dated
maintenance program as aeroplanes in post- Airbus Service Bulletin A330–53–3215, November 23, 2016. This service
mod 55306 and pre-mod 55792 Revision 03, dated January 22, 2018, as information describes procedures for
configuration. Consequently, Airbus the appropriate source of service repetitive rototest inspections of certain
published SB A330–53–3215 Revision 02 and information for the required actions. fastener holes, and related investigative
SB A340–53–4215 Revision 02 to expand the This service information incorporates
Effectivity accordingly. and corrective actions if necessary.
For the reasons described above, this minor editorial changes which have no These documents are distinct since they
[EASA] AD retains the requirements of EASA effect on airplanes that have apply to different airplane models. This
AD 2014–0136, which is superseded, which incorporated prior revisions of this service information is reasonably
now also apply to aeroplanes in post-mod service information. We have revised available because the interested parties
55792 configuration [the applicability table 1 to paragraph (g)(1) of this AD have access to it through their normal
identifies airplanes in post-mod 44360 and paragraphs (g), (g)(1), (g)(2), (h), course of business or by the means
configuration]. (h)(1), (h)(2), and (i) of this AD to identified in the ADDRESSES section.
AD 2017–07–07 includes Model specify Airbus Service Bulletin A330–
A340–211 airplanes in its applicability. 53–3215, Revision 03, dated January 22, Costs of Compliance
Airbus Model A340–211 airplanes are 2018, as the appropriate source of We estimate that this AD affects 99
not identified in the applicability of this service information for accomplishing airplanes of U.S. registry. We estimate
AD because those airplanes are not the required actions in those the following costs to comply with this
affected by the identified unsafe paragraphs. AD:
ESTIMATED COSTS FOR REQUIRED ACTIONS
Cost per Cost on U.S.
Labor cost Parts cost product operators
42 work-hours × $85 per hour = $3,570 ..................................................................................... $0 $3,570 $353,430
We estimate the following costs to do required based on the results of the of determining the number of aircraft
any necessary repairs that would be required inspections. We have no way that might need these repairs:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Cost per
amozie on DSK3GDR082PROD with RULES
Labor cost Parts cost product
46 work-hours × $85 per hour = $3,910 ................................................................................................................. $2,358 $6,268
VerDate Sep<11>2014 17:26 Jul 17, 2018 Jkt 244001 PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 E:\FR\FM\18JYR1.SGM 18JYR1](https://thefederalregister.org/doc/83_FR_33959/page/2.svg)
![Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33823
Authority for This Rulemaking 1. Is not a ‘‘significant regulatory paragraphs (c)(1) and (c)(2) of this AD, all
action’’ under Executive Order 12866; manufacturer serial numbers on which
Title 49 of the United States Code
2. Is not a ‘‘significant rule’’ under the Airbus Modification 44360 has been
specifies the FAA’s authority to issue
DOT Regulatory Policies and Procedures embodied in production.
rules on aviation safety. Subtitle I,
(44 FR 11034, February 26, 1979); (1) Airbus Model A330–201, –202, –203,
section 106, describes the authority of
3. Will not affect intrastate aviation in –223, –243, –301, –302, –303, –321, –322,
the FAA Administrator. Subtitle VII:
Alaska; and –323, –341, –342, and –343 airplanes.
Aviation Programs, describes in more
4. Will not have a significant (2) Airbus Model A340–212, –213, –312,
detail the scope of the Agency’s and –313 airplanes.
authority. economic impact, positive or negative,
We are issuing this rulemaking under on a substantial number of small entities (d) Subject
the authority described in Subtitle VII, under the criteria of the Regulatory
Flexibility Act. Air Transport Association (ATA) of
Part A, Subpart III, Section 44701: America Code 53, Fuselage.
‘‘General requirements.’’ Under that List of Subjects in 14 CFR Part 39
section, Congress charges the FAA with (e) Reason
Air transportation, Aircraft, Aviation
promoting safe flight of civil aircraft in This AD was prompted by a report of
safety, Incorporation by reference,
air commerce by prescribing regulations cracking at fastener holes located at frame
Safety.
for practices, methods, and procedures (FR) 40 on the lower shell panel junction. We
the Administrator finds necessary for Adoption of the Amendment are issuing this AD to detect and correct
safety in air commerce. This regulation Accordingly, under the authority cracking at FR40 on the lower shell panel
is within the scope of that authority delegated to me by the Administrator, junction; such cracking could lead to reduced
because it addresses an unsafe condition structural integrity of the fuselage.
the FAA amends 14 CFR part 39 as
that is likely to exist or develop on follows: (f) Compliance
products identified in this rulemaking
action. Comply with this AD within the
PART 39—AIRWORTHINESS
This AD is issued in accordance with compliance times specified, unless already
DIRECTIVES
authority delegated by the Executive done.
Director, Aircraft Certification Service, ■ 1. The authority citation for part 39 (g) Compliance Times for the Actions
as authorized by FAA Order 8000.51C. continues to read as follows: Required by Paragraph (h) of This AD
In accordance with that order, issuance Authority: 49 U.S.C. 106(g), 40113, 44701. Accomplish the actions required by
of ADs is normally a function of the paragraph (h) of this AD at the times
Compliance and Airworthiness § 39.13 [Amended]
specified in paragraphs (g)(1) and (g)(2) of
Division, but during this transition ■ 2. The FAA amends § 39.13 by this AD, as applicable.
period, the Executive Director has removing Airworthiness Directive (AD) (1) For airplanes having serial numbers
delegated the authority to issue ADs 2017–07–07, Amendment 39–18845 (82 0176 through 0915 inclusive: Within the
applicable to transport category FR 18547, April 20, 2017), and adding compliance times defined in table 1 to
airplanes to the Director of the System the following new AD: paragraph (g)(1) of this AD, and, thereafter,
Oversight Division. at intervals not to exceed the compliance
2018–12–08 Airbus: Amendment 39–19312;
Regulatory Findings Docket No. FAA–2018–0111; Product times defined in Airbus Service Bulletin
Identifier 2017–NM–059–AD. A330–53–3215, Revision 03, dated January
We determined that this AD will not 22, 2018 (‘‘A330–53–3215, R3’’); or Airbus
have federalism implications under (a) Effective Date Service Bulletin A340–53–4215, Revision 02,
Executive Order 13132. This AD will This AD is effective August 22, 2018. dated November 23, 2016 (‘‘A340–53–4215,
not have a substantial direct effect on R2’’); as applicable, depending on airplane
(b) Affected ADs
the States, on the relationship between utilization and configuration. As of the
the national government and the States, This AD replaces AD 2017–07–07,
effective date of this AD, where paragraph
Amendment 39–18845 (82 FR 18547, April
or on the distribution of power and 1.E. ‘‘Compliance,’’ of A330–53–3215, R3
20, 2017) (‘‘AD 2017–07–07’’).
responsibilities among the various specifies weight variant (WV) 050 in the
levels of government. (c) Applicability condition column of table 1, configuration
For the reasons discussed above, I This AD applies to the airplanes, 003, for the purposes of this AD, WV060 and
certify that this AD: certificated in any category, identified in WV080 are also included.
amozie on DSK3GDR082PROD with RULES
VerDate Sep<11>2014 17:26 Jul 17, 2018 Jkt 244001 PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 E:\FR\FM\18JYR1.SGM 18JYR1](https://thefederalregister.org/doc/83_FR_33959/page/3.svg)
![Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33825
airworthy condition. Any substitutions or DEPARTMENT OF THE INTERIOR B. Regulatory Flexibility Act
changes to procedures or tests identified as
This rule will not have a significant
RC require approval of an AMOC. Bureau of Indian Affairs economic effect on a substantial number
(l) Related Information [189A2100DD/AAKC001030/ of small entities under the Regulatory
(1) Refer to Mandatory Continuing A0A501010.999900 253G] Flexibility Act (RFA) (5 U.S.C. 601 et
Airworthiness Information (MCAI) EASA AD seq.). The rule is administrative in
25 CFR Part 83 nature and affects only a mailing
2017–0063, dated April 12, 2017, for related
information. This MCAI may be found in the RIN 1076–AF41
address.
AD docket on the internet at http:// C. Small Business Regulatory
www.regulations.gov by searching for and Change of Address; Office of Federal Enforcement Fairness Act
locating Docket No. FAA–2018–0111. Acknowledgment
(2) For more information about this AD,
This rule is not a major rule under 5
contact Vladimir Ulyanov, Aerospace AGENCY: Bureau of Indian Affairs, U.S.C. 804(2), the Small Business
Engineer, International Section, Transport Interior. Regulatory Enforcement Fairness Act. It
Standards Branch, FAA, 2200 South 216th ACTION: Final rule; technical will not result in the expenditure by
St., Des Moines, WA 98198; telephone and amendment. State, local, or tribal governments, in the
fax: 206–231–3229. aggregate, or by the private sector of
(3) Service information identified in this SUMMARY: The Bureau of Indian Affairs $100 million or more in any one year.
AD that is not incorporated by reference is (BIA) is amending its regulations to The rule’s requirements will not result
available at the addresses specified in reflect a change of address for the Office in a major increase in costs or prices for
paragraphs (m)(3) and (m)(4) of this AD. of Federal Acknowledgment. This rule consumers, individual industries,
is a technical amendment that corrects Federal, State, or local government
(m) Material Incorporated by Reference the address for filing petitions for agencies, or geographic regions. Nor will
(1) The Director of the Federal Register Federal acknowledgment as an Indian this rule have significant adverse effects
approved the incorporation by reference Tribe. on competition, employment,
(IBR) of the service information listed in this DATES: Effective July 18, 2018. investment, productivity, innovation, or
paragraph under 5 U.S.C. 552(a) and 1 CFR the ability of the U.S.-based enterprises
FOR FURTHER INFORMATION CONTACT:
part 51. to compete with foreign-based
(2) You must use this service information Elizabeth Appel, Director, Office of enterprises.
as applicable to do the actions required by Regulatory Affairs & Collaborative
this AD, unless this AD specifies otherwise. Action, (202) 273–4680; D. Unfunded Mandates Reform Act
(i) Airbus Service Bulletin A330–53–3215, elizabeth.appel@bia.gov. This rule does not impose an
Revision 03, dated January 22, 2018. SUPPLEMENTARY INFORMATION: This rule unfunded mandate on State, local, or
(ii) Airbus Service Bulletin A340–53–4215, updates the address for the Office of Tribal governments or the private sector
Revision 02, dated November 23, 2016. Federal Acknowledgment to reflect the of more than $100 million per year. The
(3) For service information identified in office’s change in location. rule does not have a significant or
this AD, contact Airbus SAS, Airworthiness unique effect on State, local, or Tribal
Procedural Requirements
Office—EAL, 1 Rond Point Maurice Bellonte, governments or the private sector. A
31707 Blagnac Cedex, France; telephone: +33 A. Regulatory Planning and Review statement containing the information
5 61 93 36 96; fax: +33 5 61 93 45 80; email: (E.O. 12866 and 13563) required by the Unfunded Mandates
airworthiness.A330-A340@airbus.com; Reform Act (2 U.S.C. 1531 et seq.) is not
Executive Order (E.O.) 12866 provides
internet: http://www.airbus.com. required.
that the Office of Information and
(4) You may view this service information
Regulatory Affairs (OIRA) at the Office E. Takings (E.O. 12630)
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
of Management and Budget (OMB) will Under the criteria in Executive Order
information on the availability of this
review all significant rules. OIRA has 12630, this rule does not affect
material at the FAA, call 206–231–3195. determined that this rule is not individual property rights protected by
(5) You may view this service information significant. the Fifth Amendment nor does it
that is incorporated by reference at the E.O. 13563 reaffirms the principles of involve a compensable ‘‘taking.’’ A
National Archives and Records E.O. 12866 while calling for takings implication assessment is
Administration (NARA). For information on improvements in the nation’s regulatory therefore not required.
the availability of this material at NARA, call system to promote predictability, to
202–741–6030, or go to: http:// reduce uncertainty, and to use the best, F. Federalism (E.O. 13132)
www.archives.gov/federal-register/cfr/ibr- most innovative, and least burdensome Under the criteria in Executive Order
locations.html. tools for achieving regulatory ends. The 13132, this rule has no substantial direct
E.O. directs agencies to consider effect on the States, on the relationship
Issued in Des Moines, Washington, on June regulatory approaches that reduce
6, 2018.
between the national government and
burdens and maintain flexibility and the States, or on the distribution of
Michael Kaszycki, freedom of choice for the public where power and responsibilities among the
Acting Director, System Oversight Division, these approaches are relevant, feasible, various levels of government. This rule
Aircraft Certification Service. and consistent with regulatory corrects a mailing address.
[FR Doc. 2018–13220 Filed 7–17–18; 8:45 am] objectives. E.O. 13563 emphasizes
further that regulations must be based G. Civil Justice Reform (E.O. 12988)
amozie on DSK3GDR082PROD with RULES
BILLING CODE 4910–13–P
on the best available science and that This rule complies with the
the rulemaking process must allow for requirements of Executive Order 12988.
public participation and an open Specifically, this rule meets the criteria
exchange of ideas. The Department has of section 3(a) requiring all regulations
developed this rule in a manner be reviewed to eliminate errors and
consistent with these requirements. ambiguity and be written to minimize
VerDate Sep<11>2014 17:26 Jul 17, 2018 Jkt 244001 PO 00000 Frm 00031 Fmt 4700 Sfmt 4700 E:\FR\FM\18JYR1.SGM 18JYR1](https://thefederalregister.org/doc/83_FR_33959/page/5.svg)
Document Created: 2018-11-06 10:25:03
Document Modified: 2018-11-06 10:25:03
| 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 August 22, 2018. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3229. | |
| FR Citation | 83 FR 33821 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
2024 Federal Register | Disclaimer | Privacy Policy
USC | CFR | eCFR