81 FR 27986 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 89 (May 9, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 89 (May 9, 2016)
| Page Range | 27986-27989 | |
| FR Document | 2016-10287 |
[Federal Register Volume 81, Number 89 (Monday, May 9, 2016)] [Rules and Regulations] [Pages 27986-27989] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10287] [[Page 27986]] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-134-AD; Amendment 39-18509; AD 2016-09-11] 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, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). This AD requires removing fasteners, doing a rototest inspection of fastener holes, installing new fasteners, oversizing the holes and doing rototest inspections for cracks if necessary, and repairing any cracking that is found. We are issuing this AD to detect and correct cracking on certain holes of certain frames of the CWB that could affect the structural integrity of the airplane. DATES: This AD becomes effective June 13, 2016. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 13, 2016. 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. 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-2015-4808. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-4808; 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 Operations 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. 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, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. The NPRM published in the Federal Register on November 2, 2015 (80 FR 67348) (``the NPRM''). We are issuing this AD to detect and correct cracking on certain holes of certain frames of the CWB, which could affect the structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA Airworthiness Directive 2014-0149, 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 A330-200, -200 Freighter, and -300 series airplanes; and Model A340-200 and -300 series airplanes. The MCAI states: During accomplishment of A330 Airworthiness Limitation Item (ALI) task 57-11-04 on the rear fitting of the Frame (FR) 40 between stringers 38 and 39 on both [left-hand] LH/[right-hand] RH sides, cracks were found on an adjacent hole. After reaming at second oversize of the subject hole, the crack was still present. Other crack findings on this adjacent hole have been reported on A330 and A340-200/300 aeroplanes as a result of sampling inspections. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. For the reasons described above, this [EASA] AD requires removal of the fasteners and repetitive rototest inspections of fastener holes at FR40 vertical web located above Center Wing Box (CWB) lower panel reference and/or below CWB lower panel reference on both sides and, depending on findings, accomplishment of the applicable corrective actions. Note: These holes affected by this [EASA] AD are different from the ones affected by EASA AD 2009-0001 [http://ad.easa.europa.eu/blob/easa_ad_2009_0001.pdf/AD_2009-0001_1]. Required actions also include oversizing certain holes, installing new fasteners, and repairing any cracking that is found. The initial compliance times range from 13,500 to 30,900 flight cycles, or 57,000 to 162,000 flight hours, depending on airplane operation and utilization. The repetitive compliance times are 7,400 flight cycles/ 24,300 flight hours or 5,950 flight cycles/40,400 flight hours from ALI embodiment. 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-2015-4808. Change Made to the Format of Paragraph (g) of This AD At the request of the Office of the Federal Register, we have revised the format of paragraph (g) of this AD by converting the table to text. This change to the format does not affect the requirements of that paragraph. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter, Bowen Gass, supported the NPRM. Conclusion We reviewed the relevant data, considered the comment received, and determined that air safety and the public interest require adopting this AD as proposed except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. The service information describes procedures for removing the fasteners and doing a repetitive rototest inspection of fastener holes at FR40 vertical web on both sides, installing new fasteners in transition fit, and oversizing the holes. Airbus Service Bulletin A330-57-3114, dated March 12, 2013. Airbus Service Bulletin A330-57-3115, dated April 4, 2013. [[Page 27987]] Airbus Service Bulletin A330-57-3116, dated March 12, 2013. Airbus Service Bulletin A340-57-4123, dated March 12, 2013. Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. Airbus Service Bulletin A340-57-4125, dated March 12, 2013. 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 35 airplanes of U.S. registry. We also estimate that it will take about 78 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Required parts will cost about $0 per product. Based on these figures, we estimate the cost of this AD on U.S. operators to be $232,050, per inspection cycle, or $6,630 per product, per inspection cycle. In addition, we estimate that any necessary follow-on actions will take about 98 work-hours and require parts costing $136,400, for a cost of up to $144,730 per product. We have no way of determining the number of aircraft that might need this action. 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: 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): 2016-09-11 Airbus: Amendment 39-18509. Docket No. FAA-2015-4808; Directorate Identifier 2014-NM-134-AD. (a) Effective Date This AD becomes effective June 13, 2016. (b) Affected ADs None. (c) Applicability This AD applies to the airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers, except those on which Airbus Modification (Mod) 55792 or Mod 55306 has been embodied in production, and except those on which Airbus Repair Instruction R57115092 has been embodied in service on both right-hand (RH) and left-hand (LH) sides. (1) Airbus Model A330-201, -202, -203, -223, -223F, -243 -243F, -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 57, Wings. (e) Reason This AD was prompted by reports that cracks were found on an adjacent hole of certain frames of the center wing box (CWB). We are issuing this AD to detect and correct cracking on certain holes of the CWB, which could affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspection Do a rototest inspection of the fastener holes at the frame (FR) 40 vertical web, on both sides, as specified in paragraphs (g)(1) through (g)(6) of this AD, except as required by paragraph (k) of this AD. (1) For Model A330-300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(1)(i) and (g)(1)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A330-57-3114, dated March 12, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (2) For Model A330-200 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (3) For Model A330-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(3)(i) and (g)(3)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (ii) Within 2,400 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (4) For Model A340-200 and -300 series airplanes in pre-mod 44360 configuration: At the later of the times specified in paragraphs (g)(4)(i) and (g)(4)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4123, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance'' of Airbus [[Page 27988]] Service Bulletin A330-57-4123, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (5) For Model A340-200 and -300 series airplanes in pre-mod 55306 and pre-mod 55792 configuration: At the later of the times specified in paragraphs (g)(5)(i) and (g)(5)(ii) of this AD, inspect above the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (6) For Model A340-200 and -300 series airplanes in post-mod 44360 and pre-mod 49202 configuration: At the later of the times specified in paragraphs (g)(6)(i) and (g)(6)(ii) of this AD, inspect below the CWB lower panel reference, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (i) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (ii) Within 1,300 flight cycles or 24 months after the effective date of this AD, whichever occurs first. (h) Follow-on Actions: No Cracking If no crack is found during any inspection required by paragraph (g) of this AD, do the actions specified in paragraphs (h)(1) and (h)(2) of this AD. (1) Before further flight, install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (2) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ``Compliance,'' of the applicable service information identified in paragraph (g) of this AD. (i) Follow-on Actions for Crack Findings If any crack is found during any inspection required by paragraph (g) of this AD: Before further flight, oversize the holes to the first oversize in comparison with the current hole diameter, and do a rototest inspection for cracks, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (1) If no cracking is found during the rototest inspection required by paragraph (i) of this AD, do the actions specified in paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. (i) Before further flight: Install new fasteners in the transition fit, in accordance with the Accomplishment Instructions of the applicable service information identified in paragraph (g) of this AD. (ii) Repeat the inspection required by paragraph (g) of this AD thereafter at the applicable time identified in paragraph 1.E., ``Compliance,'' of the applicable service information identified in paragraph (g) of this AD. (2) If cracking is found during the rototest inspection required by paragraph (i) of this AD: Before further flight, repair 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). (j) Terminating Action Specifications Accomplishment of the initial and repetitive inspections required by this AD terminates accomplishment of Airworthiness Limitation Items Tasks 57-11-04 and 57-11-02 of the Airworthiness Limitation Section (ALS) Part 2, Damage Tolerant Airworthiness Limitation Items (DT ALI). (1) Installation of new fasteners, as specified in paragraph (h)(1) of this AD, does not terminate the repetitive inspections required by paragraph (g) of this AD. (2) Accomplishment of the corrective actions specified in the introductory text of paragraph (i) and paragraph (i)(1) of this AD does not terminate the repetitive inspections required by paragraph (g) of this AD. (3) Accomplishment of the repair specified in paragraph (i)(2) of this AD does not terminate repetitive inspections required by paragraph (g) of this AD, unless the approved repair method specifies otherwise. (k) Exceptions to Service Information (1) If the applicable service information identified in paragraph (g) of this AD specifies contacting Airbus for appropriate action: Before further flight, repair using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA DOA. (2) Where paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraph (g) of this AD specifies a compliance time in terms of a ``Threshold'' and ``Grace Period,'' this AD requires compliance at the later of the applicable threshold and grace period. (3) Where paragraph 1.E., ``Compliance,'' of the applicable service information specified in paragraph (g) of this AD specifies a threshold as ``before next flight,'' this AD requires compliance before the next flight after the applicable finding. (l) Credit for Previous Actions This paragraph provides credit for actions required by paragraphs (g) and (i) of this AD, if those actions were performed before the effective date of this AD using the applicable service information specified in paragraph (l)(1), (l)(2), (l)(3), (l)(4), (l)(5), (l)(6), (l)(7), (l)(8), or (l)(9) of this AD. This service information is not incorporated by reference in this AD. (1) Airbus Technical Disposition LR57D11023270, Issue B, dated July 12, 2011. (2) Airbus Technical Disposition LR57D11029171, Issue B, dated September 6, 2011. (3) Airbus Technical Disposition LR57D11029173, Issue B, dated September 6, 2011. (4) Airbus Technical Disposition LR57D11030741, Issue B, dated September 22, 2011. (5) Airbus Technical Disposition LR57D11029170, Issue C, dated September 6, 2011. (6) Airbus Technical Disposition LR57D11023714, Issue B, dated July 12, 2011. (7) Airbus Technical Disposition LR57D11029172, Issue B, dated September 6, 2011. (8) Airbus Technical Disposition LR57D11030740, Issue C, dated September 22, 2011. (9) Airbus Service Bulletin A340-57-4124, dated April 4, 2013. (m) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it to 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 principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. The AMOC approval letter must specifically reference this AD. (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. (n) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0149, 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-2015-4808. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (o)(3) and (o)(4) of this AD. (o) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this [[Page 27989]] 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 A330-57-3114, dated March 12, 2013. (ii) Airbus Service Bulletin A330-57-3115, dated April 4, 2013. (iii) Airbus Service Bulletin A330-57-3116, dated March 12, 2013. (iv) Airbus Service Bulletin A340-57-4123, dated March 12, 2013. (v) Airbus Service Bulletin A340-57-4124, Revision 01, dated August 22, 2013. (vi) Airbus Service Bulletin A340-57-4125, dated March 12, 2013. (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 April 21, 2016. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10287 Filed 5-6-16; 8:45 am] BILLING CODE 4910-13-P
![27986 Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations
DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket findings, accomplishment of the applicable
contains this AD, the regulatory corrective actions.
Federal Aviation Administration evaluation, any comments received, and Note: These holes affected by this [EASA]
other information. The street address for AD are different from the ones affected by
14 CFR Part 39 EASA AD 2009–0001 [http://ad.easa.europa.
the Docket Operations office (telephone eu/blob/easa_ad_2009_0001.pdf/AD_2009-
[Docket No. FAA–2015–4808; Directorate 800–647–5527) is Docket Management 0001_1].
Identifier 2014–NM–134–AD; Amendment Facility, U.S. Department of
Transportation, Docket Operations, M– Required actions also include
39–18509; AD 2016–09–11]
30, West Building Ground Floor, Room oversizing certain holes, installing new
RIN 2120–AA64 fasteners, and repairing any cracking
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC. that is found. The initial compliance
Airworthiness Directives; Airbus times range from 13,500 to 30,900 flight
Airplanes FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer, cycles, or 57,000 to 162,000 flight hours,
AGENCY: Federal Aviation International Branch, ANM–116, depending on airplane operation and
Administration (FAA), Department of Transport Airplane Directorate, FAA, utilization. The repetitive compliance
Transportation (DOT). 1601 Lind Avenue SW., Renton, WA times are 7,400 flight cycles/24,300
98057–3356; telephone 425–227–1138; flight hours or 5,950 flight cycles/40,400
ACTION: Final rule.
fax 425–227–1149. flight hours from ALI embodiment. You
SUMMARY: We are adopting a new may examine the MCAI in the AD
SUPPLEMENTARY INFORMATION:
airworthiness directive (AD) for certain docket on the Internet at http://
Airbus Model A330–200, –200 Discussion www.regulations.gov by searching for
Freighter, and –300 series airplanes; and We issued a notice of proposed and locating Docket No. FAA–2015–
Model A340–200 and –300 series rulemaking (NPRM) to amend 14 CFR 4808.
airplanes. This AD was prompted by part 39 by adding an AD that would Change Made to the Format of
reports that cracks were found on an apply to certain Airbus Model A330– Paragraph (g) of This AD
adjacent hole of certain frames of the 200, –200 Freighter, and –300 series
center wing box (CWB). This AD At the request of the Office of the
airplanes; and Model A340–200 and
requires removing fasteners, doing a Federal Register, we have revised the
–300 series airplanes. The NPRM
rototest inspection of fastener holes, format of paragraph (g) of this AD by
published in the Federal Register on
installing new fasteners, oversizing the converting the table to text. This change
November 2, 2015 (80 FR 67348) (‘‘the
holes and doing rototest inspections for to the format does not affect the
NPRM’’). We are issuing this AD to
cracks if necessary, and repairing any requirements of that paragraph.
detect and correct cracking on certain
cracking that is found. We are issuing holes of certain frames of the CWB, Comments
this AD to detect and correct cracking which could affect the structural
on certain holes of certain frames of the We gave the public the opportunity to
integrity of the airplane. participate in developing this AD. We
CWB that could affect the structural The European Aviation Safety Agency
integrity of the airplane. considered the comment received. The
(EASA), which is the Technical Agent
commenter, Bowen Gass, supported the
DATES: This AD becomes effective June for the Member States of the European
NPRM.
13, 2016. Union, has issued EASA Airworthiness
The Director of the Federal Register Directive 2014–0149, dated June 13, Conclusion
approved the incorporation by reference 2014 (referred to after this as the We reviewed the relevant data,
of certain publications listed in this AD Mandatory Continuing Airworthiness considered the comment received, and
as of June 13, 2016. Information, or ‘‘the MCAI’’), to correct determined that air safety and the
ADDRESSES: For service information an unsafe condition for certain Airbus public interest require adopting this AD
identified in this final rule, contact Model A330–200, –200 Freighter, and as proposed except for minor editorial
Airbus SAS, Airworthiness Office— –300 series airplanes; and Model A340– changes. We have determined that these
EAL, 1 Rond Point Maurice Bellonte, 200 and –300 series airplanes. The minor changes:
31707 Blagnac Cedex, France; telephone MCAI states: • Are consistent with the intent that
+33 5 61 93 36 96; fax +33 5 61 93 45 During accomplishment of A330 was proposed in the NPRM for
80; email airworthiness.A330-A340@ Airworthiness Limitation Item (ALI) task 57– correcting the unsafe condition; and
airbus.com; Internet http:// 11–04 on the rear fitting of the Frame (FR) • Do not add any additional burden
www.airbus.com. For information on the 40 between stringers 38 and 39 on both [left- upon the public than was already
availability of this material at the FAA, hand] LH/[right-hand] RH sides, cracks were
proposed in the NPRM.
found on an adjacent hole. After reaming at
call 425–227–1221. It is also available second oversize of the subject hole, the crack Related Service Information Under 1
on the Internet at http:// was still present. CFR Part 51
www.regulations.gov by searching for Other crack findings on this adjacent hole
and locating Docket No. FAA–2015– have been reported on A330 and A340–200/ Airbus has issued the following
4808. 300 aeroplanes as a result of sampling service information. The service
inspections. information describes procedures for
Examining the AD Docket This condition, if not detected and removing the fasteners and doing a
You may examine the AD docket on corrected, could affect the structural integrity repetitive rototest inspection of fastener
mstockstill on DSK3G9T082PROD with RULES
the Internet at http:// of the aeroplane. holes at FR40 vertical web on both
www.regulations.gov at http:// For the reasons described above, this
sides, installing new fasteners in
[EASA] AD requires removal of the fasteners
www.regulations.gov by searching for and repetitive rototest inspections of fastener transition fit, and oversizing the holes.
and locating Docket No. FAA–2015– holes at FR40 vertical web located above • Airbus Service Bulletin A330–57–
4808; or in person at the Docket Center Wing Box (CWB) lower panel 3114, dated March 12, 2013.
Management Facility between 9 a.m. reference and/or below CWB lower panel • Airbus Service Bulletin A330–57–
and 5 p.m., Monday through Friday, reference on both sides and, depending on 3115, dated April 4, 2013.
VerDate Sep<11>2014 16:15 May 06, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\09MYR1.SGM 09MYR1](https://thefederalregister.org/doc/81_FR_28075/page/1.svg)
![Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 27987
• Airbus Service Bulletin A330–57– responsibilities among the various (e) Reason
3116, dated March 12, 2013. levels of government. This AD was prompted by reports that
• Airbus Service Bulletin A340–57– For the reasons discussed above, I cracks were found on an adjacent hole of
4123, dated March 12, 2013. certify that this AD: certain frames of the center wing box (CWB).
• Airbus Service Bulletin A340–57– We are issuing this AD to detect and correct
1. Is not a ‘‘significant regulatory cracking on certain holes of the CWB, which
4124, Revision 01, dated August 22,
action’’ under Executive Order 12866; could affect the structural integrity of the
2013.
2. Is not a ‘‘significant rule’’ under the airplane.
• Airbus Service Bulletin A340–57–
4125, dated March 12, 2013. DOT Regulatory Policies and Procedures (f) Compliance
This service information is reasonably (44 FR 11034, February 26, 1979); Comply with this AD within the
available because the interested parties 3. Will not affect intrastate aviation in compliance times specified, unless already
have access to it through their normal Alaska; and done.
course of business or by the means 4. Will not have a significant (g) Inspection
identified in the ADDRESSES section. economic impact, positive or negative, Do a rototest inspection of the fastener
Costs of Compliance on a substantial number of small entities holes at the frame (FR) 40 vertical web, on
under the criteria of the Regulatory both sides, as specified in paragraphs (g)(1)
We estimate that this AD affects 35 Flexibility Act. through (g)(6) of this AD, except as required
airplanes of U.S. registry. by paragraph (k) of this AD.
We also estimate that it will take List of Subjects in 14 CFR Part 39 (1) For Model A330–300 series airplanes in
about 78 work-hours per product to pre-mod 44360 configuration: At the later of
Air transportation, Aircraft, Aviation the times specified in paragraphs (g)(1)(i) and
comply with the basic requirements of safety, Incorporation by reference,
this AD. The average labor rate is $85 (g)(1)(ii) of this AD, inspect below the CWB
Safety. lower panel reference, in accordance with the
per work-hour. Required parts will cost Accomplishment Instructions of Airbus
about $0 per product. Based on these Adoption of the Amendment Service Bulletin A330–57–3114, dated March
figures, we estimate the cost of this AD 12, 2013.
Accordingly, under the authority
on U.S. operators to be $232,050, per (i) At the applicable time specified in
delegated to me by the Administrator,
inspection cycle, or $6,630 per product, paragraph 1.E., ‘‘Compliance’’ of Airbus
the FAA amends 14 CFR part 39 as Service Bulletin A330–57–3114, dated March
per inspection cycle.
follows: 12, 2013.
In addition, we estimate that any
necessary follow-on actions will take (ii) Within 2,400 flight cycles or 24 months
PART 39—AIRWORTHINESS after the effective date of this AD, whichever
about 98 work-hours and require parts DIRECTIVES occurs first.
costing $136,400, for a cost of up to (2) For Model A330–200 series airplanes in
$144,730 per product. We have no way ■ 1. The authority citation for part 39 post-mod 44360 and pre-mod 49202
of determining the number of aircraft continues to read as follows: configuration: At the later of the times
that might need this action. specified in paragraphs (g)(2)(i) and (g)(2)(ii)
Authority: 49 U.S.C. 106(g), 40113, 44701. of this AD, inspect below the CWB lower
Authority for This Rulemaking panel reference, in accordance with the
§ 39.13 [Amended] Accomplishment Instructions of Airbus
Title 49 of the United States Code
specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by adding Service Bulletin A330–57–3116, dated March
12, 2013.
rules on aviation safety. Subtitle I, the following new airworthiness
(i) At the applicable time specified in
section 106, describes the authority of directive (AD): paragraph 1.E., ‘‘Compliance,’’ of Airbus
the FAA Administrator. ‘‘Subtitle VII: 2016–09–11 Airbus: Amendment 39–18509. Service Bulletin A330–57–3116, dated March
Aviation Programs,’’ describes in more Docket No. FAA–2015–4808; Directorate 12, 2013.
detail the scope of the Agency’s Identifier 2014–NM–134–AD. (ii) Within 2,400 flight cycles or 24 months
authority. after the effective date of this AD, whichever
(a) Effective Date occurs first.
We are issuing this rulemaking under
This AD becomes effective June 13, 2016. (3) For Model A330–200 and –300 series
the authority described in ‘‘Subtitle VII,
airplanes in pre-mod 55306 and pre-mod
Part A, Subpart III, Section 44701: (b) Affected ADs 55792 configuration: At the later of the times
General requirements.’’ Under that None. specified in paragraphs (g)(3)(i) and (g)(3)(ii)
section, Congress charges the FAA with of this AD, inspect above the CWB lower
promoting safe flight of civil aircraft in (c) Applicability panel reference, in accordance with the
air commerce by prescribing regulations This AD applies to the airplanes identified Accomplishment Instructions of Airbus
for practices, methods, and procedures in paragraphs (c)(1) and (c)(2) of this AD, Service Bulletin A330–57–3115, dated April
the Administrator finds necessary for certificated in any category, all manufacturer 4, 2013.
serial numbers, except those on which (i) At the applicable time specified in
safety in air commerce. This regulation
Airbus Modification (Mod) 55792 or Mod paragraph 1.E., ‘‘Compliance’’ of Airbus
is within the scope of that authority 55306 has been embodied in production, and Service Bulletin A330–57–3115, dated April
because it addresses an unsafe condition except those on which Airbus Repair 4, 2013.
that is likely to exist or develop on Instruction R57115092 has been embodied in (ii) Within 2,400 flight cycles or 24 months
products identified in this rulemaking service on both right-hand (RH) and left-hand after the effective date of this AD, whichever
action. (LH) sides. occurs first.
(1) Airbus Model A330–201, –202, –203, (4) For Model A340–200 and –300 series
Regulatory Findings –223, –223F, –243 –243F, –301, –302, –303, airplanes in pre-mod 44360 configuration: At
mstockstill on DSK3G9T082PROD with RULES
We determined that this AD will not –321, –322, –323, –341, –342, and –343 the later of the times specified in paragraphs
have federalism implications under airplanes. (g)(4)(i) and (g)(4)(ii) of this AD, inspect
(2) Airbus Model A340–211, –212, –213, below the CWB lower panel reference, in
Executive Order 13132. This AD will accordance with the Accomplishment
–311, –312, and –313 airplanes.
not have a substantial direct effect on Instructions of Airbus Service Bulletin A340–
the States, on the relationship between (d) Subject 57–4123, dated March 12, 2013.
the national government and the States, Air Transport Association (ATA) of (i) At the applicable time specified in
or on the distribution of power and America Code 57, Wings. paragraph 1.E., ‘‘Compliance’’ of Airbus
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![Federal Register / Vol. 81, No. 89 / Monday, May 9, 2016 / Rules and Regulations 27989
paragraph under 5 U.S.C. 552(a) and 1 CFR and right-side upper frames, and repair Discussion
part 51. (including open hole high frequency
(2) You must use this service information We issued a notice of proposed
eddy current (HFEC) inspections for rulemaking (NPRM) to amend 14 CFR
as applicable to do the actions required by
cracking of fastener holes) if necessary. part 39 by adding an AD that would
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A330–57–3114, This AD also provides an optional apply to certain The Boeing Company
dated March 12, 2013. preventive modification, which Model 737–300, –400, and –500 series
(ii) Airbus Service Bulletin A330–57–3115, terminates the repetitive inspections at airplanes. The NPRM published in the
dated April 4, 2013. the modified location. We are issuing Federal Register on February 24, 2015
(iii) Airbus Service Bulletin A330–57– this AD to detect and correct fatigue (80 FR 9667) (‘‘the NPRM’’). The NPRM
3116, dated March 12, 2013. cracking of the upper frame, which can was prompted by reports of fatigue
(iv) Airbus Service Bulletin A340–57– grow in size and result in a severed
4123, dated March 12, 2013. cracking found at the left-side and right-
frame, leading to rapid decompression side upper frame, at a certain area. The
(v) Airbus Service Bulletin A340–57–4124,
Revision 01, dated August 22, 2013. and consequent reduced structural NPRM proposed to require repetitive
(vi) Airbus Service Bulletin A340–57– integrity of the airplane. MFEC inspections for cracking of the
4125, dated March 12, 2013. DATES: This AD is effective June 13, left-side and right-side upper frames,
(3) For service information identified in 2016. and repair (including open hole HFEC
this AD, contact Airbus SAS, Airworthiness The Director of the Federal Register inspections for cracking of fastener
Office—EAL, 1 Rond Point Maurice Bellonte, holes) if necessary. The NPRM also
31707 Blagnac Cedex, France; telephone +33
approved the incorporation by reference
of a certain publication listed in this AD provided an optional preventative
5 61 93 36 96; fax +33 5 61 93 45 80; email
as of June 13, 2016. modification that would terminate the
airworthiness.A330-A340@airbus.com;
Internet http://www.airbus.com. repetitive inspections at the modified
ADDRESSES: For service information
(4) You may view this service information location. We are issuing this AD to
identified in this AD, contact Boeing
at the FAA, Transport Airplane Directorate, detect and correct fatigue cracking of the
Commercial Airplanes, Attention: Data upper frame, which can grow in size
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
& Services Management, P.O. Box 3707, and result in a severed frame, leading to
material at the FAA, call 425–227–1221. MC 2H–65, Seattle, WA 98124–2207; rapid decompression and consequent
(5) You may view this service information telephone 206–544–5000, extension 1; reduced structural integrity of the
that is incorporated by reference at the fax 206–766–5680; Internet https:// airplane.
National Archives and Records www.myboeingfleet.com. You may view
Administration (NARA). For information on this referenced service information at Comments
the availability of this material at NARA, call the FAA, Transport Airplane We gave the public the opportunity to
202–741–6030, or go to: http://www.archives. Directorate, 1601 Lind Avenue SW.,
gov/federal-register/cfr/ibr-locations.html.
participate in developing this AD. The
Renton, WA. For information on the following presents the comments
Issued in Renton, Washington, on April 21, availability of this material at the FAA, received on the NPRM and the FAA’s
2016. call 425–227–1221. It is also available response to each comment.
Michael Kaszycki, on the Internet at http://
Acting Manager, Transport Airplane www.regulations.gov by searching for Requests To Clarify Compliance Time
Directorate, Aircraft Certification Service. and locating Docket No. FAA–2015– Europe Airpost and Boeing requested
[FR Doc. 2016–10287 Filed 5–6–16; 8:45 am] 0264. that we revise the NPRM to clarify the
BILLING CODE 4910–13–P ‘‘Condition’’ column of table 1 of
Examining the AD Docket paragraph 1.E., ‘‘Compliance,’’ of Boeing
You may examine the AD docket on Alert Service Bulletin 737–53A1339,
DEPARTMENT OF TRANSPORTATION the Internet at http:// dated August 12, 2014, which specifies
www.regulations.gov by searching for airplanes with certain flight cycles ‘‘on
Federal Aviation Administration and locating Docket No. FAA–2015– the original issue date of this service
0246; or in person at the Docket bulletin.’’ The commenters questioned
14 CFR Part 39 Management Facility between 9 a.m. whether the corresponding compliance
[Docket No. FAA–2015–0246; Directorate and 5 p.m., Monday through Friday, time should be ‘‘on the effective date of
Identifier 2014–NM–187–AD; Amendment except Federal holidays. The AD docket the AD.’’
39–18511; AD 2016–09–13] contains this AD, the regulatory For the reasons suggested by both
evaluation, any comments received, and commenters, we agree to add paragraph
RIN 2120–AA64 (i)(3) to this AD to state that the
other information. The address for the
Docket Office (phone: 800–647–5527) is corresponding reference point is on the
Airworthiness Directives; The Boeing
Docket Management Facility, U.S. effective date of this AD, and we have
Company Airplanes
Department of Transportation, Docket included reference to paragraph (i)(3) in
AGENCY: Federal Aviation Operations, M–30, West Building all appropriate paragraphs in this AD.
Administration (FAA), DOT. Ground Floor, Room W12–140, 1200 Request for Clarify Inspection
ACTION: Final rule. New Jersey Avenue SE., Washington, Requirements
DC 20590.
SUMMARY: We are adopting a new Boeing requested that we revise
airworthiness directive (AD) for certain FOR FURTHER INFORMATION CONTACT: paragraph (g) of the proposed AD to
The Boeing Company Model 737–300, Galib Abumeri, Aerospace Engineer, address the inspection requirements in
mstockstill on DSK3G9T082PROD with RULES
–400, and –500 series airplanes. This Airframe Branch, ANM–120L, FAA, Los areas of an existing repair to eliminate
AD was prompted by reports of fatigue Angeles Aircraft Certification Office cracking approved by a Boeing
cracking found at the left-side and right- (ACO), 3960 Paramount Boulevard, Organization Designation Authorization
side upper frames, at a certain area. This Lakewood, California 90712–4137; (ODA) via FAA Form 8100–9. Boeing
AD requires repetitive medium phone: 562–627–5324; fax: 562–627– explained that this condition is
frequency eddy current (MFEC) 5210; email: galib.abumeri@faa.gov. addressed in note (c) of table 1 of
inspections for cracking of the left-side SUPPLEMENTARY INFORMATION: paragraph 1.E., ‘‘Compliance,’’ of Boeing
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Document Created: 2018-02-07 14:49:48
Document Modified: 2018-02-07 14:49:48
| 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 becomes effective June 13, 2016. | |
| 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 | 81 FR 27986 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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