82 FR 18547 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 75 (April 20, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 75 (April 20, 2017)
| Page Range | 18547-18550 | |
| FR Document | 2017-06712 |
[Federal Register Volume 82, Number 75 (Thursday, April 20, 2017)] [Rules and Regulations] [Pages 18547-18550] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-06712] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. ======================================================================== Federal Register / Vol. 82, No. 75 / Thursday, April 20, 2017 / Rules and Regulations [[Page 18547]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD; Amendment 39-18845; AD 2017-07-07] 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 A330-200, A330-300, A340-200, and A340-300 series airplanes. This AD was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. This AD requires repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective May 25, 2017. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of May 25, 2017. 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 [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9192. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9192; 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: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 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 A330- 200, A330-300, A340-200, and A340-300 series airplanes. The NPRM published in the Federal Register on October 25, 2016 (81 FR 73357) (``the NPRM''). The NPRM was prompted by a report of cracking at fastener holes located at a certain frame on the lower shell panel junction. The NPRM proposed to require repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct cracking at frame 40 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 Airworthiness Directive 2014-0136, dated June 13, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for certain Airbus Model A330, A340-200, and A340-300 series airplanes. The MCAI states: During A330/A340 aeroplanes full scale fatigue test specimen in the FR40-to-fuselage skin panel junction, fatigue damage has been found. Corrective actions consisted of the following actions: --In-service installation of an internal reinforcing strap on related junction required by DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC)] France AD 1999-448-126(B) and [DGAC France] AD 2001-070(B), --retrofit improvement of internal reinforcing strap fatigue life through recommended Airbus Service Bulletin (SB) A330-53-3145, and --new design in production through Airbus modification 44360. The aeroplanes listed in the Applicability section of this [EASA] AD are all aeroplanes post-mod 44360 and pre-mod 55792 (fuselage reinforcement at FR40 in production). Recently, during embodiment of a FR40 web repair on an A330 aeroplane and during FR40 keel beam fitting replacement on an A340 aeroplane, the internal strap was removed and rototest inspection was performed on several holes. Cracks were found on both left-hand (LH) and right-hand (RH) sides on internal strap, or butt strap, or keel beam fitting, or forward fitting FR40 flange. This condition, if not detected and corrected, could lead to crack propagation, possibly resulting in reduced structural integrity of the fuselage. For the reasons described above, this [EASA] AD requires repetitive rototest inspections of 10 fastener holes located at FR40 lower shell panel junction on both LH and RH sides, and, depending on findings, accomplishment of the applicable corrective actions [which include oversizing, installing fasteners and repair; and accomplishment of applicable related investigative actions, which include a rototest inspection for cracking after oversizing]. 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 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-2016-9192. [[Page 18548]] Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM from a single commenter, and the FAA's response to that comment. Request To Refer to Revised Service Information Delta Airlines (DAL) requested that we revise paragraphs (g), (g)(1), and (g)(2) of the proposed AD to refer to Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016. DAL also asked that credit be given in paragraph (h)(1) of the proposed AD for previously accomplished actions using Airbus Service Bulletin A330-53- 3215, Revision 01, dated April 17, 2014. DAL stated that if the Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, Revision 01, dated April 17, 2014, are used, operators may incorrectly reference kit part numbers in their instructions and would then need to submit a request for approval of an alternative method of compliance for the replaced part. We agree with the commenter's request to refer to Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016. Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, has also been issued. No additional work is required by Airbus Service Bulletins A330-53-3215, Revision 02; and A340-53-4215, Revision 02, both dated November 23, 2016; the revised service information merely corrects typographical errors and contains minor editorial changes. We have revised the Related Service Information under 1 CFR part 51 section of this final rule and paragraphs (g), (g)(1), and (g)(2) of this AD to refer to Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; and Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016. We have also revised paragraph (h)(1) of this AD to provide credit for actions accomplished prior to the effective date of this AD using Airbus Service Bulletin A330-53- 3215, Revision 01, dated April 17, 2014; and Airbus Service Bulletin A340-53-4215, Revision 01, dated April 17, 2014. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD with 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. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information Under 1 CFR Part 51 We reviewed Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; and Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016. The 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 41 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs -------------------------------------------------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- Inspection........................... 41 work-hours x $85 per hour $0 $3,485 $142,885 per inspection cycle. = $3,485 per inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary repairs that are required based on the results of the required 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 ---------------------------------------------------------------------------------------------------------------- Repair.................................... 46 work-hours x $85 per hour = $4,186 $8,096 $3,910. ---------------------------------------------------------------------------------------------------------------- Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this 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: [[Page 18549]] 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): 2017-07-07 Airbus: Amendment 39-18845; Docket No. FAA-2016-9192; Directorate Identifier 2016-NM-038-AD. (a) Effective Date This AD is effective May 25, 2017. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD, having serial numbers 0176 through 0915 inclusive. (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342, and -343 airplanes. (2) Airbus Model A340-211, -212, -213, -311, -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) Repetitive Inspections and Related Investigative and Corrective Actions Within the compliance times defined in table 1 to the introductory text of paragraph (g) of this AD, and, thereafter, at intervals not to exceed the compliance times defined in Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, depending on airplane utilization and configuration: Accomplish a special detailed inspection of fastener holes located at FR40 lower shell panel junction on both left-hand (LH) and right-side (RH) sides, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable. Table 1 to the Introductory Text of Paragraph (g) of this AD--Compliance Time for Initial Inspection ------------------------------------------------------------------------ Compliance time (whichever occurs later, A or B) ------------------------------------------------------------------------ A...................................... Before exceeding the compliance time ``threshold'' defined in table 1 of Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, depending on airplane utilization and configuration and to be counted from airplane first flight B...................................... For Model A330 airplanes: Within 2,400 flight cycles or 24 months, whichever occurs first after the effective date of this AD For Model A340 airplanes: Within 1,300 flight cycles or 24 months, whichever occurs first after the effective date of this AD ------------------------------------------------------------------------ (1) If, during any inspection required by the introductory text of paragraph (g) 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 Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016; as applicable, except where Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, specifies to contact Airbus for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair before further flight using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). (2) If, during any inspection required by the introductory text of paragraph (g) of this AD, the hole diameter is not within tolerance of the transition fit as nominal, or first oversize, or second oversize, or next nominal, as applicable, and Airbus Service Bulletin A330-53-3215, Revision 02, dated November 23, 2016; or Airbus Service Bulletin A340-53-4215, Revision 02, dated November 23, 2016, specifies to contact Airbus for repair instructions, and specifies that action as ``RC'' (Required for Compliance), before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA. (3) Accomplishment of corrective actions, as required by paragraph (g)(1) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD. (4) Accomplishment of a repair on an airplane, as required by paragraph (g)(2) of this AD, does not constitute terminating action for the repetitive inspections required by the introductory text of paragraph (g) of this AD for that airplane, unless the method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA indicates otherwise. (h) Credit for Previous Actions (1) This paragraph provides credit for inspections required by the introductory text of paragraph (g) of this AD and the related investigative and corrective actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using Airbus Service Bulletin A330-53-3215, dated June 21, 2013; or Revision 01, dated April 17, 2014; or Airbus Service Bulletin A340-53-4215, dated June 21, 2013; or Revision 01, dated April 17, 2014; as applicable. (2) This paragraph provides credit for the inspections and corrective actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Airbus Technical Disposition (TD) Reference LR57D11023360, Issue B, dated July 12, 2011. (i) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate [[Page 18550]] principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: For any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the 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) and (g)(2) of this AD: If any service information contains procedures or tests that are identified as RC, those procedures and tests must be done to comply with this AD; any procedures or tests that are not identified as RC are recommended. Those procedures and tests that are not identified as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the procedures and tests identified as RC can be done and the airplane can be put back in an airworthy condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (j) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0136, dated June 13, 2014, for related information. This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-9192. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (k)(3) and (k)(4) of this AD. (k) 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 02, dated November 23, 2016. (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 [email protected]; Internet http://www.airbus.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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 March 28, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-06712 Filed 4-19-17; 8:45 am] BILLING CODE 4910-13-P
![18547
Rules and Regulations Federal Register
Vol. 82, No. 75
Thursday, April 20, 2017
This section of the FEDERAL REGISTER at http://www.regulations.gov by an unsafe condition for certain Airbus
contains regulatory documents having general searching for and locating Docket No. Model A330, A340–200, and A340–300
applicability and legal effect, most of which FAA–2016–9192. series airplanes. The MCAI states:
are keyed to and codified in the Code of
Federal Regulations, which is published under Examining the AD Docket During A330/A340 aeroplanes full scale
50 titles pursuant to 44 U.S.C. 1510. fatigue test specimen in the FR40-to-fuselage
You may examine the AD docket on skin panel junction, fatigue damage has been
The Code of Federal Regulations is sold by the Internet at http:// found. Corrective actions consisted of the
the Superintendent of Documents. www.regulations.gov by searching for following actions:
and locating Docket No. FAA–2016– —In-service installation of an internal
9192; or in person at the Docket reinforcing strap on related junction
DEPARTMENT OF TRANSPORTATION Management Facility between 9 a.m. required by DGAC [Direction Générale de
and 5 p.m., Monday through Friday, l’Aviation Civile (DGAC)] France AD 1999–
Federal Aviation Administration except Federal holidays. The AD docket 448–126(B) and [DGAC France] AD 2001–
contains this AD, the regulatory 070(B),
14 CFR Part 39 evaluation, any comments received, and —retrofit improvement of internal reinforcing
[Docket No. FAA–2016–9192; Directorate other information. The street address for strap fatigue life through recommended
Identifier 2016–NM–038–AD; Amendment the Docket Office (telephone 800–647– Airbus Service Bulletin (SB) A330–53–
39–18845; AD 2017–07–07] 5527) is Docket Management Facility, 3145, and
U.S. Department of Transportation, —new design in production through Airbus
RIN 2120–AA64 modification 44360.
Docket Operations, M–30, West
Building Ground Floor, Room W12–140, The aeroplanes listed in the Applicability
Airworthiness Directives; Airbus section of this [EASA] AD are all aeroplanes
Airplanes 1200 New Jersey Avenue SE.,
post-mod 44360 and pre-mod 55792 (fuselage
Washington, DC 20590. reinforcement at FR40 in production).
AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT: Recently, during embodiment of a FR40
Administration (FAA), Department of Vladimir Ulyanov, Aerospace Engineer, web repair on an A330 aeroplane and during
Transportation (DOT). International Branch, ANM–116, FR40 keel beam fitting replacement on an
ACTION: Final rule. Transport Airplane Directorate, FAA, A340 aeroplane, the internal strap was
1601 Lind Avenue SW., Renton, WA removed and rototest inspection was
SUMMARY: We are adopting a new 98057–3356; telephone 425–227–1138; performed on several holes.
airworthiness directive (AD) for certain fax 425–227–1149. Cracks were found on both left-hand (LH)
Airbus Model A330–200, A330–300, and right-hand (RH) sides on internal strap,
SUPPLEMENTARY INFORMATION:
A340–200, and A340–300 series or butt strap, or keel beam fitting, or forward
airplanes. This AD was prompted by a Discussion fitting FR40 flange.
report of cracking at fastener holes This condition, if not detected and
We issued a notice of proposed corrected, could lead to crack propagation,
located at a certain frame on the lower rulemaking (NPRM) to amend 14 CFR
shell panel junction. This AD requires possibly resulting in reduced structural
part 39 by adding an AD that would integrity of the fuselage.
repetitive inspections of certain fastener apply to certain Airbus Model A330– For the reasons described above, this
holes, and related investigative and 200, A330–300, A340–200, and A340– [EASA] AD requires repetitive rototest
corrective actions if necessary. We are 300 series airplanes. The NPRM inspections of 10 fastener holes located at
issuing this AD to address the unsafe published in the Federal Register on FR40 lower shell panel junction on both LH
condition on these products. October 25, 2016 (81 FR 73357) (‘‘the and RH sides, and, depending on findings,
DATES: This AD is effective May 25, NPRM’’). The NPRM was prompted by accomplishment of the applicable corrective
2017. actions [which include oversizing, installing
a report of cracking at fastener holes
The Director of the Federal Register fasteners and repair; and accomplishment of
located at a certain frame on the lower applicable related investigative actions,
approved the incorporation by reference shell panel junction. The NPRM which include a rototest inspection for
of certain publications listed in this AD proposed to require repetitive cracking after oversizing].
as of May 25, 2017. inspections of certain fastener holes,
ADDRESSES: For service information and related investigative and corrective The compliance time ranges between
identified in this final rule, contact actions if necessary. We are issuing this 20,000 flight cycles or 65,400 flight
Airbus SAS, Airworthiness Office— AD to detect and correct cracking at hours and 20,800 flight cycles or 68,300
EAL, 1 Rond Point Maurice Bellonte, frame 40 on the lower shell panel flight hours, depending on airplane
31707 Blagnac Cedex, France; telephone junction; such cracking could lead to utilization and configuration. The
+33 5 61 93 36 96; fax +33 5 61 93 45 reduced structural integrity of the repetitive inspection interval ranges
80; email airworthiness.A330-A340@ fuselage. between 14,000 flight cycles or 95,200
airbus.com; Internet http:// The European Aviation Safety Agency flight hours and 24,600 flight cycles or
pmangrum on DSK3GDR082PROD with RULES
www.airbus.com. You may view this (EASA), which is the Technical Agent 98,700 flight hours, depending on
referenced service information at the for the Member States of the European airplane configuration. You may
FAA, Transport Airplane Directorate, Union, has issued EASA Airworthiness examine the MCAI in the AD docket on
1601 Lind Avenue SW., Renton, WA. Directive 2014–0136, dated June 13, the Internet at http://
For information on the availability of 2014 (referred to after this as the www.regulations.gov by searching for
this material at the FAA, call 425–227– Mandatory Continuing Airworthiness and locating Docket No. FAA–2016–
1221. It is also available on the Internet Information, or ‘‘the MCAI’’), to correct 9192.
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![Federal Register / Vol. 82, No. 75 / Thursday, April 20, 2017 / Rules and Regulations 18549
1. Is not a ‘‘significant regulatory (g) Repetitive Inspections and Related (2) If, during any inspection required by
action’’ under Executive Order 12866; Investigative and Corrective Actions the introductory text of paragraph (g) of this
2. Is not a ‘‘significant rule’’ under the Within the compliance times defined in AD, the hole diameter is not within tolerance
DOT Regulatory Policies and Procedures table 1 to the introductory text of paragraph of the transition fit as nominal, or first
(g) of this AD, and, thereafter, at intervals not oversize, or second oversize, or next nominal,
(44 FR 11034, February 26, 1979);
to exceed the compliance times defined in as applicable, and Airbus Service Bulletin
3. Will not affect intrastate aviation in A330–53–3215, Revision 02, dated November
Alaska; and Airbus Service Bulletin A330–53–3215,
Revision 02, dated November 23, 2016; or 23, 2016; or Airbus Service Bulletin A340–
4. Will not have a significant 53–4215, Revision 02, dated November 23,
Airbus Service Bulletin A340–53–4215,
economic impact, positive or negative, Revision 02, dated November 23, 2016; as 2016, specifies to contact Airbus for repair
on a substantial number of small entities applicable, depending on airplane utilization instructions, and specifies that action as
under the criteria of the Regulatory and configuration: Accomplish a special ‘‘RC’’ (Required for Compliance), before
Flexibility Act. detailed inspection of fastener holes located further flight, repair using a method
at FR40 lower shell panel junction on both approved by the Manager, International
List of Subjects in 14 CFR Part 39 left-hand (LH) and right-side (RH) sides, in Branch, ANM–116, Transport Airplane
Air transportation, Aircraft, Aviation accordance with the Accomplishment Directorate, FAA; or EASA; or Airbus’s EASA
safety, Incorporation by reference, Instructions of Airbus Service Bulletin A330– DOA.
53–3215, Revision 02, dated November 23, (3) Accomplishment of corrective actions,
Safety.
2016; or Airbus Service Bulletin A340–53– as required by paragraph (g)(1) of this AD,
Adoption of the Amendment 4215, Revision 02, dated November 23, 2016; does not constitute terminating action for the
as applicable. repetitive inspections required by the
Accordingly, under the authority introductory text of paragraph (g) of this AD.
delegated to me by the Administrator, (4) Accomplishment of a repair on an
the FAA amends 14 CFR part 39 as TABLE 1 TO THE INTRODUCTORY TEXT
airplane, as required by paragraph (g)(2) of
follows: OF PARAGRAPH (g) OF THIS AD— this AD, does not constitute terminating
Compliance Time for Initial Inspec- action for the repetitive inspections required
PART 39—AIRWORTHINESS tion by the introductory text of paragraph (g) of
DIRECTIVES this AD for that airplane, unless the method
Compliance time (whichever approved by the Manager, International
■ 1. The authority citation for part 39 occurs later, A or B) Branch, ANM–116, Transport Airplane
continues to read as follows: Directorate, FAA; or EASA; or Airbus’s EASA
A ........... Before exceeding the compliance DOA indicates otherwise.
Authority: 49 U.S.C. 106(g), 40113, 44701. time ‘‘threshold’’ defined in table
1 of Airbus Service Bulletin (h) Credit for Previous Actions
§ 39.13 [Amended]
A330–53–3215, Revision 02, (1) This paragraph provides credit for
■ 2. The FAA amends § 39.13 by adding dated November 23, 2016; or inspections required by the introductory text
the following new airworthiness Airbus Service Bulletin A340– of paragraph (g) of this AD and the related
directive (AD): 53–4215, Revision 02, dated investigative and corrective actions required
November 23, 2016; as applica- by paragraph (g)(1) of this AD, if those
2017–07–07 Airbus: Amendment 39–18845; ble, depending on airplane utili- actions were performed before the effective
Docket No. FAA–2016–9192; Directorate zation and configuration and to date of this AD using Airbus Service Bulletin
Identifier 2016–NM–038–AD. be counted from airplane first A330–53–3215, dated June 21, 2013; or
(a) Effective Date flight Revision 01, dated April 17, 2014; or Airbus
B ........... For Model A330 airplanes: Within Service Bulletin A340–53–4215, dated June
This AD is effective May 25, 2017.
2,400 flight cycles or 24 months, 21, 2013; or Revision 01, dated April 17,
(b) Affected ADs whichever occurs first after the 2014; as applicable.
None. effective date of this AD (2) This paragraph provides credit for the
For Model A340 airplanes: Within inspections and corrective actions required
(c) Applicability 1,300 flight cycles or 24 months, by paragraph (g) of this AD, if those actions
This AD applies to the airplanes, whichever occurs first after the were performed before the effective date of
certificated in any category, identified in effective date of this AD this AD using Airbus Technical Disposition
paragraphs (c)(1) and (c)(2) of this AD, having (TD) Reference LR57D11023360, Issue B,
serial numbers 0176 through 0915 inclusive. (1) If, during any inspection required by dated July 12, 2011.
(1) Airbus Model A330–201, –202, –203, the introductory text of paragraph (g) of this
(i) Other FAA AD Provisions
–223, –243, –301, –302, –303, –321, –322, AD, any crack is detected, before further
–323, –341, –342, and –343 airplanes. flight, accomplish all applicable related The following provisions also apply to this
(2) Airbus Model A340–211, –212, –213, investigative and corrective actions, in AD:
–311, –312, and –313 airplanes. accordance with the Accomplishment (1) Alternative Methods of Compliance
Instructions of Airbus Service Bulletin A330– (AMOCs): The Manager, International
(d) Subject 53–3215, Revision 02, dated November 23, Branch, ANM–116, Transport Airplane
Air Transport Association (ATA) of 2016; or Airbus Service Bulletin A340–53– Directorate, FAA, has the authority to
America Code 53, Fuselage. 4215, Revision 02, dated November 23, 2016; approve AMOCs for this AD, if requested
as applicable, except where Airbus Service using the procedures found in 14 CFR 39.19.
(e) Reason Bulletin A330–53–3215, Revision 02, dated In accordance with 14 CFR 39.19, send your
This AD was prompted by a report of November 23, 2016; or Airbus Service request to your principal inspector or local
cracking at fastener holes located at frame Bulletin A340–53–4215, Revision 02, dated Flight Standards District Office, as
(FR) 40 on the lower shell panel junction. We November 23, 2016, specifies to contact appropriate. If sending information directly
are issuing this AD to detect and correct Airbus for repair instructions, and specifies to the International Branch, send it to ATTN:
pmangrum on DSK3GDR082PROD with RULES
cracking at FR40 on the lower shell panel that action as ‘‘RC’’ (Required for Vladimir Ulyanov, Aerospace Engineer,
junction; such cracking could lead to reduced Compliance), this AD requires repair before International Branch, ANM–116, Transport
structural integrity of the fuselage. further flight using a method approved by the Airplane Directorate, FAA, 1601 Lind
Manager, International Branch, ANM–116, Avenue SW., Renton, WA 98057–3356;
(f) Compliance Transport Airplane Directorate, FAA; or the telephone 425–227–1138; fax 425–227–1149.
Comply with this AD within the European Aviation Safety Agency (EASA); or Information may be emailed to: 9-ANM-116-
compliance times specified, unless already Airbus’s EASA Design Organization AMOC-REQUESTS@faa.gov. Before using
done. Approval (DOA). any approved AMOC, notify your appropriate
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![18550 Federal Register / Vol. 82, No. 75 / Thursday, April 20, 2017 / Rules and Regulations
principal inspector, or lacking a principal 202–741–6030, or go to: http:// FOR FURTHER INFORMATION CONTACT: Tom
inspector, the manager of the local flight www.archives.gov/federal-register/cfr/ibr- Clark, Federal Aviation Administration,
standards district office/certificate holding locations.html. Operations Support Group, Western
district office.
Issued in Renton, Washington, on March Service Center, 1601 Lind Avenue SW.,
(2) Contacting the Manufacturer: For any
28, 2017. Renton, WA 98057; telephone (425)
requirement in this AD to obtain corrective
actions from a manufacturer, the action must Michael Kaszycki, 203–4511.
be accomplished using a method approved Acting Manager, Transport Airplane
SUPPLEMENTARY INFORMATION:
by the Manager, International Branch, ANM– Directorate, Aircraft Certification Service.
116, Transport Airplane Directorate, FAA; or [FR Doc. 2017–06712 Filed 4–19–17; 8:45 am] Authority for This Rulemaking
the EASA; or Airbus’s EASA DOA. If BILLING CODE 4910–13–P
approved by the DOA, the approval must The FAA’s authority to issue rules
include the DOA-authorized signature. regarding aviation safety is found in
(3) Required for Compliance (RC): Except Title 49 of the United States Code.
DEPARTMENT OF TRANSPORTATION
as required by paragraphs (g)(1) and (g)(2) of Subtitle I, Section 106 describes the
this AD: If any service information contains
Federal Aviation Administration authority of the FAA Administrator.
procedures or tests that are identified as RC,
those procedures and tests must be done to Subtitle VII, Aviation Programs,
comply with this AD; any procedures or tests 14 CFR Part 71 describes in more detail the scope of the
that are not identified as RC are [Docket No. FAA–2016–9286; Airspace
agency’s authority. This rulemaking is
recommended. Those procedures and tests Docket No. 16–ANM–13] promulgated under the authority
that are not identified as RC may be deviated described in Subtitle VII, Part A,
from using accepted methods in accordance Establishment of Class E Airspace, Subpart I, Section 40103. Under that
with the operator’s maintenance or section, the FAA is charged with
inspection program without obtaining
Denver, CO
approval of an AMOC, provided the
prescribing regulations to assign the use
AGENCY: Federal Aviation of airspace necessary to ensure the
procedures and tests identified as RC can be Administration (FAA), DOT.
done and the airplane can be put back in an safety of aircraft and the efficient use of
airworthy condition. Any substitutions or ACTION: Final rule. airspace. This regulation is within the
changes to procedures or tests identified as scope of that authority as it establishes
RC require approval of an AMOC. SUMMARY: This action establishes Class Class E en route airspace at Denver Air
E en route airspace extending upward Route Traffic Control Center, Denver,
(j) Related Information from 1,200 feet above the surface to
(1) Refer to Mandatory Continuing
CO to ensure controlled airspace exists
accommodate instrument flight rules
Airworthiness Information (MCAI) EASA in those areas where the Federal airway
(IFR) aircraft under control of the
Airworthiness Directive 2014–0136, dated structure is inadequate.
Denver Air Route Traffic Control Center
June 13, 2014, for related information. This (ARTCC), Denver, CO. Establishment of
MCAI may be found in the AD docket on the
History
Internet at http://www.regulations.gov by
this airspace area is necessary to ensure
controlled airspace exists in those areas On November 16, 2016, the FAA
searching for and locating Docket No. FAA–
2016–9192. where the Federal airway structure is published in the Federal Register (81
(2) Service information identified in this inadequate. FR 80620) Docket FAA–2016–9286 a
AD that is not incorporated by reference is notice of proposed rulemaking to
DATES: Effective 0901 UTC, June 22, establish Class E en route airspace
available at the addresses specified in
paragraphs (k)(3) and (k)(4) of this AD.
2017. The Director of the Federal extending upward from 1,200 feet above
Register approves this incorporation by the surface at Denver, CO. Interested
(k) Material Incorporated by Reference reference action under Title 1, Code of parties were invited to participate in
(1) The Director of the Federal Register Federal Regulations, part 51, subject to
approved the incorporation by reference
this rulemaking effort by submitting
the annual revision of FAA Order
(IBR) of the service information listed in this written comments on the proposal to the
7400.11 and publication of conforming
paragraph under 5 U.S.C. 552(a) and 1 CFR FAA. No comments were received.
amendments.
part 51. Class E airspace designations are
(2) You must use this service information ADDRESSES: FAA Order 7400.11A,
Airspace Designations and Reporting published in paragraph 6006 of FAA
as applicable to do the actions required by
Points, and subsequent amendments can Order 7400.11A, dated August 3, 2016,
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–53–3215, be viewed online at http://www.faa.gov/ and effective September 15, 2016, which
Revision 02, dated November 23, 2016. air_traffic/publications/. For further is incorporated by reference in 14 CFR
(ii) Airbus Service Bulletin A340–53–4215, information, you can contact the part 71.1. The Class E airspace
Revision 02, dated November 23, 2016. Airspace Policy Group, Federal Aviation designation listed in this document will
(3) For service information identified in Administration, 800 Independence be published subsequently in the Order.
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
Avenue SW., Washington, DC 20591; Availability and Summary of
31707 Blagnac Cedex, France; telephone +33 telephone: 202–267–8783. The Order is Documents for Incorporation by
5 61 93 36 96; fax +33 5 61 93 45 80; email also available for inspection at the Reference
airworthiness.A330-A340@airbus.com; National Archives and Records
Internet http://www.airbus.com. Administration (NARA). For This document amends FAA Order
(4) You may view this service information information on the availability of this 7400.11A, Airspace Designations and
at the FAA, Transport Airplane Directorate, material at NARA, call 202–741–6030, Reporting Points, dated August 3, 2016,
pmangrum on DSK3GDR082PROD with RULES
1601 Lind Avenue SW., Renton, WA. For or go to http://www.archives.gov/ and effective September 15, 2016. FAA
information on the availability of this federal_register/code_of_federal- Order 7400.11A is publicly available as
material at the FAA, call 425–227–1221.
(5) You may view this service information
regulations/ibr_locations.html. listed in the ADDRESSES section of this
that is incorporated by reference at the FAA Order 7400.11, Airspace document. FAA Order 7400.11A lists
National Archives and Records Designations and Reporting Points, is Class A, B, C, D, and E airspace areas,
Administration (NARA). For information on published yearly and effective on air traffic service routes, and reporting
the availability of this material at NARA, call September 15. points.
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Document Created: 2017-04-20 01:42:19
Document Modified: 2017-04-20 01:42:19
| 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 May 25, 2017. | |
| Contact | Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. | |
| FR Citation | 82 FR 18547 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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