83 FR 11399 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 51 (March 15, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 51 (March 15, 2018)
| Page Range | 11399-11404 | |
| FR Document | 2018-05018 |
[Federal Register Volume 83, Number 51 (Thursday, March 15, 2018)] [Rules and Regulations] [Pages 11399-11404] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-05018] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2017-0695; Product Identifier 2016-NM-173-AD; Amendment 39-19223; AD 2018-06-03] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2009-18-16, which applied to certain Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. AD 2009-18-16 required an inspection for cracking of certain fastener holes on certain frames, and related investigative and corrective actions if necessary; and modification of certain fastener holes. This new AD reduces the compliance times. This AD was prompted by the identification of a structural modification that falls within the scope of the work related to the extension of the service life of the affected airplanes and widespread fatigue damage evaluations. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective April 19, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 19, 2018. ADDRESSES: For service information identified in this final rule, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 [[Page 11400]] South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0695. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0695; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3225. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009) (``AD 2009-18-16''). AD 2009-18-16 applied to certain Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. The NPRM published in the Federal Register on July 14, 2017 (82 FR 32503). We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the airplane. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, has issued EASA AD 2016-0197, dated October 5, 2016 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), for all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. EASA AD 2016-0197 supersedes EASA AD 2008-0212, dated December 4, 2008. EASA AD 2008-0212 was the MCAI referred to in FAA AD 2009-18-16. The new MCAI states: Within the scope of work related to the extension of the service life of A310 design and widespread fatigue damage evaluations, DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD F-2005-078 (EASA approval 2005-3957) [which corresponds to FAA AD 2006-02-06, Amendment 39-14458 (71 FR 3214, January 20, 2006)] to require a structural modification, as defined in Airbus Service Bulletin (SB) A310-53-2124 (Airbus modification 13023), to increase the service life of junctions of center box upper frame bases to upper fuselage arches. The threshold timescales for accomplishment of the tasks as defined in SB A310-53-2124 were refined and reduced. Consequently, EASA issued AD 2007-0238 to require compliance with Revision 01 of SB A310-53-2124 at the reduced compliance times, superseding (the requirements of) DGAC France AD F-2005-078. Subsequently, Airbus identified reference material that was erroneously introduced into Airbus SB A310-53-2124 Revision 01. As a result, the SB instructions could not be accomplished properly. Operators that tried to apply SB A310-53-2124 at Revision 01 had to contact Airbus; see also Airbus SBIT [service bulletin information telex] ref. 914.0135/08, dated 03 March 2008. Consequently, [EASA] AD 2007-0238 was revised to exclude reference to Airbus SB A310-53-2124 Revision 01 and to require accomplishment of the task(s) as described in the original SB A310- 53-2124 instead, although retaining the reduced compliance times introduced by [EASA] AD 2007-0238 at original issue. EASA AD 2008-0212, superseding [EASA] AD 2007-0238R1, was published to refer to Airbus SB A310 53-2124 Revision 02, the corrected version that was used to meet the requirements of this [EASA] AD. Since [EASA] AD 2008-0212 was issued, new investigations in the frame of the Widespread Fatigue Damage campaign induced thresholds reduction, and Airbus issued SB A310-53-2124 Revision 03. For the reason described above, this [EASA] AD retains the requirements of EASA AD 2008-0212, which is superseded, and requires accomplishment of modification(s) within reduced compliance time, as published in Airbus SB A310-53-2124 Revision 03. Required actions include a high frequency eddy current (HFEC) rotating probe inspection for cracking of certain fastener holes on certain frames, and related investigative and corrective actions if necessary; and modification of certain fastener holes. Related investigative actions include an additional HFEC rotating probe inspection for cracking of fastener holes and a check to determine the edge distance of certain holes. Corrective actions include ream out of cracks and repair. You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017- 0695. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comment received on the NPRM and the FAA's response to that comment. Request To Revise the Costs of Compliance FedEx stated that repairs would cost an additional $10,000 per airplane. The commenter noted that 66% of its past accomplishments required additional efforts to incorporate the modification with supplementary repair activities. The commenter suggested that the average cost of compliance would approach $30,000 per airplane. We infer that the commenter is requesting a revision to the costs of compliance in the NPRM. We agree with commenter's request to revise the costs of compliance in this final rule. We have revised the Costs of Compliance section in this final rule accordingly. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD with the change described previously, and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014. This service information describes procedures for a rotating probe inspection for cracking between frame (FR) 43 through FR 46 on the center box, and the cold expansion (modification) of the most fatigue sensitive fastener holes. 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 8 airplanes of U.S. registry. We estimate that it will take about 41 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 $20,180 per product. Based on these figures, we estimate the cost of this AD on U.S. [[Page 11401]] operators to be $189,320, or $23,665 per product. Although we have received no definitive data that will enable us to provide cost estimates for the on-condition actions (i.e., additional inspection and modification for certain airplanes) specified in this AD, we have determined that the total repair costs could be up to $10,000 per product. We have no way of determining the number of aircraft that might need these repairs. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009), and adding the following new AD: 2018-06-03 Airbus: Amendment 39-19223; Docket No. FAA-2017-0695; Product Identifier 2016-NM-173-AD. (a) Effective Date This AD is effective April 19, 2018. (b) Affected ADs This AD replaces AD 2009-18-16, Amendment 39-16012 (74 FR 46342, September 9, 2009) (``AD 2009-18-16''). (c) Applicability This AD applies to Airbus Model A310-203, -204, -221, -222, - 304, -322, -324 and -325 airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Reason This AD was prompted by an evaluation by the design approval holder indicating that the junctions of center box upper frame bases to the upper fuselage arches are subject to widespread fatigue damage and that the compliance threshold for the modification in AD 2009-18-16 should be reduced. We are issuing this AD to prevent fatigue cracking of the frame foot run-outs, which could lead to rupture of the frame foot and cracking in adjacent frames and skin, and which could result in reduced structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Modification of Fastener Holes Except for airplanes modified before the effective date of this AD using the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124: At the times specified in paragraph (g)(1) of this AD but no later than the times specified in paragraph (g)(2) of this AD, do a high frequency eddy current (HFEC) rotating probe inspection for cracking of fastener holes H1 through H29 on frames 43 through 46, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014, except as required by paragraph (h) of this AD. If no cracking is found and the edge distance of the fastener hole is equal to or greater than the distance specified in the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014, before further flight, do the modification (cold expansion) of the affected fastener holes, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014. Do all applicable related investigative and corrective actions before further flight. (1) Inspect at the applicable time specified in table 1 to paragraph (g)(1) of this AD, or within 24 months after the effective date of this AD, whichever occurs later. To establish the average flight time (AFT), take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the AFT per flight cycle. Although the thresholds for Model A310-304, -322, -324, and -325 airplanes are optimized to airplane utilization, an operator can choose to use the thresholds for the other AFT. [[Page 11402]] [GRAPHIC] [TIFF OMITTED] TR15MR18.002 (2) Inspect at the later of the times specified in paragraphs (g)(2)(i) and (g)(2)(ii) of this AD. (i) At the applicable time indicated in table 2 to paragraph (g)(2)(i) of this AD. Airbus Model A310-304, -322, -324, and -325 airplanes with an AFT equal to or less than 3.16 flight hours are short range airplanes. Airbus Model A310-304, -322, -324, and -325 airplanes with an AFT exceeding 3.16 flight hours are long range airplanes. For this paragraph, to establish the average flight time, take the accumulated flight time (counted from the take-off up to the landing) and divide by the number of accumulated flight cycles. This gives the AFT per flight cycle. [[Page 11403]] [GRAPHIC] [TIFF OMITTED] TR15MR18.003 (ii) Within 500 flight cycles or 800 flight hours after October 14, 2009 (the effective date of AD 2009-18-16), whichever occurs first. (h) Service Information Exception Where Airbus Service Bulletin A310-53-2124, Revision 03, dated December 22, 2014, specifies to contact Airbus for appropriate action, and specifies that action as ``RC'' (required for compliance): Before further flight, accomplish corrective actions in accordance with the procedures specified in paragraph (l)(2) of this AD. (i) Airplanes Modified per Revision 01 of the Service Information For airplanes modified before the effective date of this AD using Airbus Service Bulletin A310-53-2124, Revision 01, dated May 3, 2007: Unless already accomplished, before further flight, do applicable corrective actions using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. (j) Additional Inspection and Modification Except as provided by paragraphs (j)(1) and (j)(2) of this AD, as applicable: At the applicable thresholds specified in table 3 to the introductory text of paragraph (j) of this AD, contact the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA for additional inspection and modification instructions. Accomplish those instructions within the compliance times approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. [[Page 11404]] [GRAPHIC] [TIFF OMITTED] TR15MR18.004 (1) For Model A310-203, -204, -221, and -222 airplanes: No additional inspection is required if the inspection and modification specified in Airbus Service Bulletin A310-53-2124 was done after the accumulation of 29,500 flight cycles and 70,900 flight hours since the first flight of the airplane. (2) For Model A310-304, -322, -324, and -325 airplanes: No additional inspection is required if the inspection and modification specified in Airbus Service Bulletin A310-53-2124 was done after the accumulation of 22,600 flight cycles and 69,400 flight hours since the first flight of the airplane. (k) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the Accomplishment Instructions of Airbus Service Bulletin A310-53-2124, dated April 4, 2005; or Airbus Service Bulletin A310-53-2124, Revision 02, dated May 22, 2008. (l) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (m)(2) of this AD. Information may be emailed to: [email protected]. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): Except as provided by paragraph (h) 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. (m) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2016-0197, dated October 5, 2016, for related information. This MCAI may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0695. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone: 206-231-3225. (3) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (n)(3) and (n)(4) of this AD. (n) 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 A310-53-2124, Revision 03, dated December 22, 2014. (ii) Reserved. (3) For service information identified in this AD, contact Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 5 61 93 44 51; email: [email protected]; internet: http://www.airbus.com. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on March 2, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-05018 Filed 3-14-18; 8:45 am] BILLING CODE 4910-13-P
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(d) Subject (2) Before using any approved AMOC, the availability of this material at NARA, call
Air Transport Association (ATA) of notify your appropriate principal inspector, 202–741–6030, or go to: http://
America Code 53, Fuselage. or lacking a principal inspector, the manager www.archives.gov/federal-register/cfr/ibr-
of the local flight standards district office/ locations.html.
(e) Unsafe Condition certificate holding district office.
Issued in Renton, Washington, on March 2,
This AD was prompted by an evaluation by (3) An AMOC that provides an acceptable
2018.
the design approval holder indicating that level of safety may be used for any repair,
modification, or alteration required by this Michael Kaszycki,
the side panel-to-frame attachments and
frames of the aft cargo compartment are AD if it is approved by the Boeing Acting Director, System Oversight Division,
subject to widespread fatigue damage. We are Commercial Airplanes Organization Aircraft Certification Service.
issuing this AD to prevent fatigue cracking at Designation Authorization (ODA) that has [FR Doc. 2018–05015 Filed 3–14–18; 8:45 am]
the attachment points of the side panel-to- been authorized by the Manager, Los Angeles BILLING CODE 4910–13–P
frame attachments of the aft cargo ACO Branch, to make those findings. To be
compartment, which could result in reduced approved, the repair method, modification
structural integrity of the body frames, and deviation, or alteration deviation must meet
consequent rapid decompression of the the certification basis of the airplane, and the
DEPARTMENT OF TRANSPORTATION
airplane. approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(2)
Federal Aviation Administration
(f) Compliance
of this AD: For service information that
Comply with this AD within the contains steps that are labeled as RC, the 14 CFR Part 39
compliance times specified, unless already provisions of paragraphs (j)(4)(i) and (j)(4)(ii) [Docket No. FAA–2017–0695; Product
done. of this AD apply. Identifier 2016–NM–173–AD; Amendment
(g) One-Time General Visual Inspection and (i) The steps labeled as RC, including 39–19223; AD 2018–06–03]
Corrective Actions substeps under an RC step and any figures
identified in an RC step, must be done to RIN 2120–AA64
Except as required by paragraph (h) of this comply with the AD. If a step or substep is
AD: At the applicable times specified in labeled ‘‘RC Exempt,’’ then the RC Airworthiness Directives; Airbus
paragraph 1.E., ‘‘Compliance,’’ of Boeing requirement is removed from that step or Airplanes
Alert Service Bulletin 757–53A0012, substep. An AMOC is required for any
Revision 1, dated January 25, 2017, do all deviations to RC steps, including substeps AGENCY: Federal Aviation
applicable actions identified as ‘‘RC’’ and identified figures. Administration (FAA), Department of
(required for compliance) in, and in (ii) Steps not labeled as RC may be Transportation (DOT).
accordance with, the Accomplishment deviated from using accepted methods in
Instructions of Boeing Alert Service Bulletin ACTION: Final rule.
accordance with the operator’s maintenance
757–53A0012, Revision 1, dated January 25,
or inspection program without obtaining SUMMARY: We are superseding
2017.
approval of an AMOC, provided the RC steps, Airworthiness Directive (AD) 2009–18–
(h) Exceptions to Service Information including substeps and identified figures, can 16, which applied to certain Airbus
Specifications still be done as specified, and the airplane
can be put back in an airworthy condition.
Model A310–203, –204, –221, –222,
(1) For purposes of determining –304, –322, –324, and –325 airplanes.
compliance with the requirements of this AD: (k) Related Information AD 2009–18–16 required an inspection
Where Boeing Alert Service Bulletin 757–
53A0012, Revision 1, dated January 25, 2017,
For more information about this AD, for cracking of certain fastener holes on
contact Peter Jarzomb, Aerospace Engineer, certain frames, and related investigative
uses the phrase ‘‘the Revision 1 date of this
Airframe Section, Los Angeles ACO Branch, and corrective actions if necessary; and
service bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’ FAA, 3960 Paramount Boulevard, Lakewood, modification of certain fastener holes.
(2) Where Boeing Alert Service Bulletin CA 90712–4137; phone: 562–627–5234; fax: This new AD reduces the compliance
757–53A0012, Revision 1, dated January 25, 562–627–5210; email: peter.jarzomb@faa.gov.
times. This AD was prompted by the
2017, specifies contacting Boeing, and (l) Material Incorporated by Reference identification of a structural
specifies that action as RC: This AD requires modification that falls within the scope
(1) The Director of the Federal Register
repair using a method approved in
accordance with the procedures specified in
approved the incorporation by reference of the work related to the extension of
(IBR) of the service information listed in this the service life of the affected airplanes
paragraph (j) of this AD.
paragraph under 5 U.S.C. 552(a) and 1 CFR and widespread fatigue damage
(i) Terminating Action for Inspections part 51. evaluations. We are issuing this AD to
Accomplishment of a modification in (2) You must use this service information address the unsafe condition on these
accordance with the Accomplishment as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
products.
Instructions of Boeing Alert Service Bulletin
757–53A0012, Revision 1, dated January 25, (i) Boeing Alert Service Bulletin 757– DATES: This AD is effective April 19,
2017, terminates the inspections required by 53A0012, Revision 1, dated January 25, 2017. 2018.
paragraph (g) of this AD at the modified (ii) Reserved. The Director of the Federal Register
location only. (3) For service information identified in approved the incorporation by reference
this AD, contact Boeing Commercial
(j) Alternative Methods of Compliance of a certain publication listed in this AD
Airplanes, Attention: Contractual & Data
(AMOCs) Services (C&DS), 2600 Westminster Blvd., as of April 19, 2018.
(1) The Manager, Los Angeles ACO Branch, MC 110–SK57, Seal Beach, CA 90740–5600; ADDRESSES: For service information
FAA, has the authority to approve AMOCs telephone 562–797–1717; internet https:// identified in this final rule, contact
for this AD, if requested using the procedures www.myboeingfleet.com. Airbus SAS, Airworthiness Office—
found in 14 CFR 39.19. In accordance with (4) You may view this service information EAW, 1 Rond Point Maurice Bellonte,
sradovich on DSK3GMQ082PROD with RULES
14 CFR 39.19, send your request to your at the FAA, Transport Standards Branch, 31707 Blagnac Cedex, France;
principal inspector or local Flight Standards 2200 South 216th St., Des Moines, WA. For
telephone: +33 5 61 93 36 96; fax: +33
District Office, as appropriate. If sending information on the availability of this
information directly to the manager of the material at the FAA, call 206–231–3195. 5 61 93 44 51; email: account.airworth-
certification office, send it to the attention of (5) You may view this service information eas@airbus.com; internet: http://
the person identified in paragraph (k) of this that is incorporated by reference at the www.airbus.com. You may view this
AD. Information may be emailed to: 9-ANM- National Archives and Records referenced service information at the
LAACO-AMOC-Requests@faa.gov. Administration (NARA). For information on FAA, Transport Standards Branch, 2200
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South 216th St., Des Moines, WA. For Within the scope of work related to the Comments
information on the availability of this extension of the service life of A310 design
and widespread fatigue damage evaluations, We gave the public the opportunity to
material at the FAA, call 206–231–3195. participate in developing this AD. The
DGAC [Direction Générale de l’Aviation
It is also available on the internet at following presents the comment
Civile] France issued AD F–2005–078 (EASA
http://www.regulations.gov by searching approval 2005–3957) [which corresponds to received on the NPRM and the FAA’s
for and locating Docket No. FAA–2017– FAA AD 2006–02–06, Amendment 39–14458 response to that comment.
0695. (71 FR 3214, January 20, 2006)] to require a
structural modification, as defined in Airbus Request To Revise the Costs of
Examining the AD Docket Service Bulletin (SB) A310–53–2124 (Airbus Compliance
You may examine the AD docket on modification 13023), to increase the service
life of junctions of center box upper frame FedEx stated that repairs would cost
the internet at http://
bases to upper fuselage arches. an additional $10,000 per airplane. The
www.regulations.gov by searching for
The threshold timescales for commenter noted that 66% of its past
and locating Docket No. FAA–2017–
accomplishment of the tasks as defined in SB accomplishments required additional
0695; or in person at the Docket A310–53–2124 were refined and reduced. efforts to incorporate the modification
Management Facility between 9 a.m. Consequently, EASA issued AD 2007–0238 with supplementary repair activities.
and 5 p.m., Monday through Friday, to require compliance with Revision 01 of SB The commenter suggested that the
except Federal holidays. The AD docket A310–53–2124 at the reduced compliance
times, superseding (the requirements of)
average cost of compliance would
contains this AD, the regulatory
DGAC France AD F–2005–078. Subsequently, approach $30,000 per airplane. We infer
evaluation, any comments received, and
Airbus identified reference material that was that the commenter is requesting a
other information. The address for the
erroneously introduced into Airbus SB revision to the costs of compliance in
Docket Office (telephone 800–647–5527)
A310–53–2124 Revision 01. As a result, the the NPRM. We agree with commenter’s
is Docket Management Facility, U.S. SB instructions could not be accomplished request to revise the costs of compliance
Department of Transportation, Docket properly. Operators that tried to apply SB in this final rule. We have revised the
Operations, M–30, West Building A310–53–2124 at Revision 01 had to contact Costs of Compliance section in this final
Ground Floor, Room W12–140, 1200 Airbus; see also Airbus SBIT [service bulletin
rule accordingly.
New Jersey Avenue SE, Washington, DC information telex] ref. 914.0135/08, dated 03
20590. March 2008. Conclusion
Consequently, [EASA] AD 2007–0238 was
FOR FURTHER INFORMATION CONTACT: Dan We reviewed the available data,
revised to exclude reference to Airbus SB
Rodina, Aerospace Engineer, A310–53–2124 Revision 01 and to require including the comment received, and
International Section, Transport accomplishment of the task(s) as described in determined that air safety and the
Standards Branch, FAA, 2200 South the original SB A310–53–2124 instead, public interest require adopting this AD
216th St., Des Moines, WA 98198; although retaining the reduced compliance with the change described previously,
telephone 206–231–3225. times introduced by [EASA] AD 2007–0238 and minor editorial changes. We have
at original issue.
SUPPLEMENTARY INFORMATION:
EASA AD 2008–0212, superseding [EASA]
determined that these minor changes:
AD 2007–0238R1, was published to refer to • Are consistent with the intent that
Discussion
Airbus SB A310 53–2124 Revision 02, the was proposed in the NPRM for
We issued a notice of proposed corrected version that was used to meet the correcting the unsafe condition; and
rulemaking (NPRM) to amend 14 CFR requirements of this [EASA] AD. • Do not add any additional burden
part 39 to supersede AD 2009–18–16, Since [EASA] AD 2008–0212 was issued, upon the public than was already
Amendment 39–16012 (74 FR 46342, new investigations in the frame of the proposed in the NPRM.
September 9, 2009) (‘‘AD 2009–18–16’’). Widespread Fatigue Damage campaign
AD 2009–18–16 applied to certain induced thresholds reduction, and Airbus Related Service Information Under 1
issued SB A310–53–2124 Revision 03. CFR Part 51
Airbus Model A310–203, –204, –221, For the reason described above, this
–222, –304, –322, –324, and –325 [EASA] AD retains the requirements of EASA Airbus has issued Service Bulletin
airplanes. The NPRM published in the AD 2008–0212, which is superseded, and A310–53–2124, Revision 03, dated
Federal Register on July 14, 2017 (82 FR requires accomplishment of modification(s) December 22, 2014. This service
32503). We are issuing this AD to within reduced compliance time, as information describes procedures for a
prevent fatigue cracking of the frame published in Airbus SB A310–53–2124 rotating probe inspection for cracking
foot run-outs, which could lead to Revision 03. between frame (FR) 43 through FR 46 on
rupture of the frame foot and cracking Required actions include a high the center box, and the cold expansion
in adjacent frames and skin, and which frequency eddy current (HFEC) rotating (modification) of the most fatigue
could result in reduced structural probe inspection for cracking of certain sensitive fastener holes. This service
integrity of the airplane. fastener holes on certain frames, and information is reasonably available
The European Aviation Safety Agency related investigative and corrective because the interested parties have
(EASA), which is the Technical Agent actions if necessary; and modification of access to it through their normal course
for the Member States of the European certain fastener holes. Related of business or by the means identified
Union, has issued EASA AD 2016–0197, investigative actions include an in the ADDRESSES section.
dated October 5, 2016 (referred to after additional HFEC rotating probe
this as the Mandatory Continuing Costs of Compliance
inspection for cracking of fastener holes
Airworthiness Information, or ‘‘the and a check to determine the edge We estimate that this AD affects 8
MCAI’’), for all Airbus Model A310– distance of certain holes. Corrective airplanes of U.S. registry.
sradovich on DSK3GMQ082PROD with RULES
203, –204, –221, –222, –304, –322, –324, actions include ream out of cracks and We estimate that it will take about 41
and –325 airplanes. EASA AD 2016– repair. work-hours per product to comply with
0197 supersedes EASA AD 2008–0212, You may examine the MCAI in the the basic requirements of this AD. The
dated December 4, 2008. EASA AD AD docket on the internet at http:// average labor rate is $85 per work-hour.
2008–0212 was the MCAI referred to in www.regulations.gov by searching for Required parts will cost about $20,180
FAA AD 2009–18–16. The new MCAI and locating Docket No. FAA–2017– per product. Based on these figures, we
states: 0695. estimate the cost of this AD on U.S.
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![Federal Register / Vol. 83, No. 51 / Thursday, March 15, 2018 / Rules and Regulations 11401
operators to be $189,320, or $23,665 per responsibilities among the various (e) Reason
product. levels of government. This AD was prompted by an evaluation by
Although we have received no For the reasons discussed above, I the design approval holder indicating that
definitive data that will enable us to certify that this AD: the junctions of center box upper frame bases
provide cost estimates for the on- 1. Is not a ‘‘significant regulatory to the upper fuselage arches are subject to
condition actions (i.e., additional action’’ under Executive Order 12866; widespread fatigue damage and that the
inspection and modification for certain 2. Is not a ‘‘significant rule’’ under the compliance threshold for the modification in
airplanes) specified in this AD, we have DOT Regulatory Policies and Procedures AD 2009–18–16 should be reduced. We are
determined that the total repair costs (44 FR 11034, February 26, 1979); issuing this AD to prevent fatigue cracking of
could be up to $10,000 per product. We 3. Will not affect intrastate aviation in the frame foot run-outs, which could lead to
Alaska; and rupture of the frame foot and cracking in
have no way of determining the number
4. Will not have a significant adjacent frames and skin, and which could
of aircraft that might need these repairs. result in reduced structural integrity of the
economic impact, positive or negative,
Authority for This Rulemaking on a substantial number of small entities airplane.
Title 49 of the United States Code under the criteria of the Regulatory (f) Compliance
specifies the FAA’s authority to issue Flexibility Act. Comply with this AD within the
rules on aviation safety. Subtitle I, List of Subjects in 14 CFR Part 39 compliance times specified, unless already
section 106, describes the authority of done.
the FAA Administrator. ‘‘Subtitle VII: Air transportation, Aircraft, Aviation
safety, Incorporation by reference, (g) Inspections and Modification of Fastener
Aviation Programs,’’ describes in more Holes
detail the scope of the Agency’s Safety.
authority. Except for airplanes modified before the
Adoption of the Amendment
We are issuing this rulemaking under effective date of this AD using the
Accordingly, under the authority Accomplishment Instructions of Airbus
the authority described in ‘‘Subtitle VII,
delegated to me by the Administrator, Service Bulletin A310–53–2124: At the times
Part A, Subpart III, Section 44701:
the FAA amends 14 CFR part 39 as specified in paragraph (g)(1) of this AD but
General requirements.’’ Under that no later than the times specified in paragraph
follows:
section, Congress charges the FAA with (g)(2) of this AD, do a high frequency eddy
promoting safe flight of civil aircraft in PART 39—AIRWORTHINESS current (HFEC) rotating probe inspection for
air commerce by prescribing regulations DIRECTIVES cracking of fastener holes H1 through H29 on
for practices, methods, and procedures frames 43 through 46, and do all applicable
the Administrator finds necessary for ■ 1. The authority citation for part 39 related investigative and corrective actions,
safety in air commerce. This regulation continues to read as follows: in accordance with the Accomplishment
is within the scope of that authority Authority: 49 U.S.C. 106(g), 40113, 44701. Instructions of Airbus Service Bulletin A310–
because it addresses an unsafe condition 53–2124, Revision 03, dated December 22,
that is likely to exist or develop on § 39.13 [Amended] 2014, except as required by paragraph (h) of
products identified in this rulemaking this AD. If no cracking is found and the edge
■ 2. The FAA amends § 39.13 by distance of the fastener hole is equal to or
action. removing Airworthiness Directive (AD)
This AD is issued in accordance with greater than the distance specified in the
2009–18–16, Amendment 39–16012 (74 Accomplishment Instructions of Airbus
authority delegated by the Executive FR 46342, September 9, 2009), and Service Bulletin A310–53–2124, Revision 03,
Director, Aircraft Certification Service, adding the following new AD: dated December 22, 2014, before further
as authorized by FAA Order 8000.51C. flight, do the modification (cold expansion)
2018–06–03 Airbus: Amendment 39–19223;
In accordance with that order, issuance Docket No. FAA–2017–0695; Product of the affected fastener holes, in accordance
of ADs is normally a function of the Identifier 2016–NM–173–AD. with the Accomplishment Instructions of
Compliance and Airworthiness Airbus Service Bulletin A310–53–2124,
Division, but during this transition (a) Effective Date Revision 03, dated December 22, 2014. Do all
period, the Executive Director has This AD is effective April 19, 2018. applicable related investigative and
delegated the authority to issue ADs (b) Affected ADs corrective actions before further flight.
applicable to transport category (1) Inspect at the applicable time specified
This AD replaces AD 2009–18–16, in table 1 to paragraph (g)(1) of this AD, or
airplanes to the Director of the System Amendment 39–16012 (74 FR 46342,
Oversight Division. within 24 months after the effective date of
September 9, 2009) (‘‘AD 2009–18–16’’). this AD, whichever occurs later. To establish
Regulatory Findings (c) Applicability the average flight time (AFT), take the
This AD applies to Airbus Model A310– accumulated flight time (counted from the
We determined that this AD will not
203, –204, –221, –222, –304, –322, –324 and take-off up to the landing) and divide by the
have federalism implications under number of accumulated flight cycles. This
Executive Order 13132. This AD will –325 airplanes; certificated in any category;
all serial numbers. gives the AFT per flight cycle. Although the
not have a substantial direct effect on thresholds for Model A310–304, –322, –324,
the States, on the relationship between (d) Subject and –325 airplanes are optimized to airplane
the national government and the States, Air Transport Association (ATA) of utilization, an operator can choose to use the
or on the distribution of power and America Code 53, Fuselage. thresholds for the other AFT.
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Document Created: 2018-03-15 02:37:32
Document Modified: 2018-03-15 02:37:32
| 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 April 19, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 206-231-3225. | |
| FR Citation | 83 FR 11399 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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