80 FR 61327 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 197 (October 13, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 197 (October 13, 2015)
| Page Range | 61327-61330 | |
| FR Document | 2015-25758 |
[Federal Register Volume 80, Number 197 (Tuesday, October 13, 2015)] [Proposed Rules] [Pages 61327-61330] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-25758] ======================================================================== Proposed Rules Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. ======================================================================== Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules [[Page 61327]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to supersede Airworthiness Directive (AD) 2010-04- 03, for all Airbus Model A310 series airplanes. AD 2010-04-03 currently requires accomplishing repetitive detailed visual inspections for cracking around the fastener holes in certain wing top skin panels between the right side and left side of the front and rear spars, and repair if needed. Since we issued AD 2010-04-03, Airbus improved the ultrasonic inspection program to allow earlier crack detection and to extend the repetitive inspection intervals. We have determined these inspections are necessary to address the unsafe condition. This proposed AD would continue to require the repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars, and repair if needed, and would require supplemental repetitive ultrasonic inspections for cracking around the fastener holes in certain wing top skin panels and repair if needed. We are proposing this AD to detect and correct cracking around the fastener holes in certain wing top skin panels between the right side and left side of the front and rear spars, which could result in reduced structural integrity of the airplane. DATES: We must receive comments on this proposed AD by November 27, 2015. ADDRESSES: You may send comments by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed 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. 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. 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-2015- 3985; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion On January 28, 2010, we issued AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010). AD 2010-04-03 requires actions intended to address an unsafe condition on all Airbus Model A310 series airplanes. Since we issued AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010), the manufacturer improved the ultrasonic inspection program to allow earlier crack detection and to extend the repetitive inspection intervals. We have determined these inspections are necessary to address the unsafe condition. The European Aviation Safety Agency, which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2014-0200R1, dated September 19, 2014 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition on all Airbus Model A310 series airplanes. The MCAI states: Following scheduled maintenance, cracks were found around the wing top skin panels fastener holes at Rib 2, between Stringer (STG) 2 and STG14. This condition, if not detected and corrected, could affect the structural integrity of the aeroplane. The General Visual Inspection required by the existing applicable Airworthiness Limitation Items (ALI) tasks may not be adequate to detect these cracks. To address this issue, Airbus developed an inspection programme based on repetitive detailed inspections (DET) to ensure that any visible cracks in the wing top skin panels 1 and 2 along Rib 2 are detected in time and repaired appropriately. EASA issued [EASA] [[Page 61328]] AD 2008-0211 [http://ad.easa.europa.eu/ad/2008-0211] to require implementation of this inspection programme. Since that [EASA] AD was issued, Airbus improved the inspection programme with an ultrasonic inspection to allow earlier crack detection, to subsequently reduce the scope of potential repair action, and to extend the intervals of the repetitive inspections. For the reasons described above, this [EASA] AD [http://ad.easa.europa.eu/ad/2014-0200R1] retains the requirements of EASA AD 2008-0211, which is superseded, and requires supplementary repetitive ultrasonic inspections [for cracking] of the wing top skin panel 1 and 2 between STG2 and STG10 at Rib 2 [and repair if needed]. * * * * * 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- 3985. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information: Airbus Service Bulletin A310-57-2096, dated May 6, 2008, Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010. Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014. This service information describes procedures for detailed visual and ultrasonic inspections for cracking around the fastener holes of the wing top skin panels between the right side and left side of the front and rear spars at certain locations, and repair if needed. 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 of this NPRM. FAA's Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of another country, and is approved for operation in the United States. Pursuant to our bilateral agreement with the State of Design Authority, we have been notified of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all pertinent information and determined an unsafe condition exists and is likely to exist or develop on other products of the same type design. Explanation of ``RC'' Procedures and Tests in Service Information The FAA worked in conjunction with industry, under the Airworthiness Directive Implementation Aviation Rulemaking Committee (ARC), to enhance the AD system. One enhancement was a new process for annotating which procedures and tests in the service information are required for compliance with an AD. Differentiating these procedures and tests from other tasks in the service information is expected to improve an owner's/operator's understanding of crucial AD requirements and help provide consistent judgment in AD compliance. The procedures and tests identified as RC (required for compliance) in any service information have a direct effect on detecting, preventing, resolving, or eliminating an identified unsafe condition. As specified in a NOTE under the Accomplishment Instructions of the specified service information, procedures and tests that are identified as RC in any service information must be done to comply with the proposed AD. However, procedures and 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 alternative method of compliance (AMOC), provided the procedures and tests identified as RC can be done and the airplane can be put back in a serviceable condition. Any substitutions or changes to procedures or tests identified as RC will require approval of an AMOC. Costs of Compliance We estimate that this proposed AD affects 13 airplanes of U.S. registry. We also estimate that it would take about 5 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost $0 per product. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $5,525, or $425 per product. We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this AD. 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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) 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010), and adding the following new AD: Airbus: Docket No. FAA-2015-3985; Directorate Identifier 2014-NM- 182-AD. [[Page 61329]] (a) Comments Due Date We must receive comments by November 27, 2015. (b) Affected ADs This AD replaces AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010). (c) Applicability This AD applies to all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes, certificated in any category, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Reason This AD was prompted by cracking around the fastener holes in certain wing top skin panels between the right side and left side of the front and rear spars. This AD was also prompted by the development of an ultrasonic inspection program to allow for earlier crack detection and extend the repetitive inspection intervals. We are issuing this AD to detect and correct cracking around the fastener holes in certain wing top skin panels between the right side and left side of the front and rear spars, 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) Repetitive Inspections Except as required by paragraph (i) of this AD: Within the initial compliance time and thereafter at repetitive intervals specified in paragraphs (h)(1) through (h)(3) of this AD, as applicable, accomplish the actions specified in paragraphs (g)(1) and (g)(2) concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014, except as provided by paragraph (j) of this AD. (1) Accomplish a detailed inspection for cracking around fastener holes in the wing top skin panels 1 and 2, along rib 2 between the front and rear spars on both the left-side and right- side of the fuselage. (2) Accomplish an ultrasonic inspection for cracking around fastener holes in the wing top skin panels 1 and 2, along rib 2, between stringer 2 and stringer 10 on the left-side and right-side of the fuselage. (h) Compliance Times for Airplanes Not Previously Inspected (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraph (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 2,000 flight cycles or 4,100 flight hours, whichever occurs first. (i) Prior to the accumulation of 18,700 flight cycles or 37,400 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (2) For Model A310-304, -322, -324, and -325 airplanes having an average flight time (AFT) of less than 4 hours: Do the actions required by paragraph (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(2)(i) or (h)(2)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 2,000 flight cycles or 5,600 flight hours, whichever occurs first. (i) Prior to the accumulation of 17,300 flight cycles or 48,400 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of equal to or more than 4 hours: Do the actions required by paragraph (g)(1) and (g)(2) of this AD at the later of the times specified in paragraph (h)(3)(i) or (h)(3)(ii) of this AD. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at intervals not to exceed 1,500 flight cycles or 7,500 flight hours, whichever occurs first. (i) Prior to the accumulation of 12,800 flight cycles or 64,300 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (i) Compliance Times of Airplanes Previously Inspected For airplanes previously inspected before the effective date of this AD using Airbus Service Bulletin A310-57-2096, dated May 6, 2008; or Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010: At the applicable compliance times specified in paragraphs (i)(1) through (i)(3) of this AD, accomplish the actions specified in paragraphs (g)(1) and (g)(2) concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD, thereafter at the repetitive intervals specified in paragraphs (h)(1) through (h)(3) of this AD, as applicable. (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraph (g)(1) and (g)(2) of this AD within 3,500 flight hours or 1,700 flight cycles, whichever occurs first since the most recent inspection. (2) For Model A310-304, -322, -324, and -325 airplanes having an AFT of less than 4 hours: Do the actions required by paragraph (g)(1) and (g)(2) of this AD within 4,600 flight hours or 1,600 flight cycles, whichever occurs first since the most recent inspection. (3) For Model A310-304, -322, -324, and -325 airplanes having an AFT of equal to or more than 4 hours: Do the actions required by paragraph (g)(1) and (g)(2) of this AD within 6,100 flight hours or 1,200 flight cycles, whichever occurs first since the most recent inspection. (j) Compliance Times if No Ultrasonic Equipment Is Available If no ultrasonic equipment is available for the initial or second inspection required by paragraph (g) or (h) of this AD, accomplish the detailed inspection specified in paragraph (g)(1) of this AD, within the applicable compliance times specified in paragraphs (j)(1) and (j)(2) of this AD. After accomplishing the detailed inspection, do the inspections specified in paragraphs (g)(1) and (g)(2) of this AD at the applicable compliance times specified by paragraphs (i)(1) through (i)(3) of this AD. Subsequently, repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable repetitive intervals specified in paragraphs (h)(1) through (h)(3) of this AD. (1) For airplanes not previously inspected before the effective date of this AD: Do the actions required by paragraph (g)(1) of this AD within the initial compliance time specified by paragraphs (h)(1) through (h)(3) of this AD, as applicable. (2) For airplanes previously inspected before the effective date of this AD using the service information identified in paragraph (j)(2)(i), (j)(2)(ii), or (j)(2)(iii) of this AD: Do the actions required by paragraph (g)(1) of this AD within the applicable compliance times specified in paragraphs (i)(1) through (i)(3) of this AD. (i) Airbus Service Bulletin A310-57-2096, dated May 6, 2008. (ii) Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010. (iii) Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014. (k) Repair of Cracking If any cracking is found during any inspection required by paragraphs (g), (h), (i), or (j) of this AD, before further flight, repair the cracking 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). (l) Terminating Action for Certain Repetitive Inspections Accomplishment of a repair using the service information identified in paragraph (l)(1), (l)(2), or (l)(3) of this AD, constitutes terminating action for the requirements of paragraph (g) of this AD, only for the repaired areas of the airplane. (1) Airbus Service Bulletin A310-57-2096, dated May 6, 2008. (2) Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010. (3) Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014. (m) Definition of Average Flight Time (AFT) For the purposes of this AD, the AFT should be established as specified in paragraphs (m)(1), (m)(2), and (m)(3) of this AD for the determination of the compliance times. (1) The inspection threshold is defined as the total flight hours accumulated (counted from take-off to touch-down), divided by the total number of flight cycles accumulated at the effective date of this AD. (2) The initial inspection interval is defined as the total flight hours accumulated divided by the total number of flight cycles accumulated at the time of the initial inspection threshold. [[Page 61330]] (3) The second inspection interval is defined as the total flight hours accumulated divided by the total number of flight cycles accumulated between the initial and second threshold. (n) Credit for Previous Actions This paragraph provides credit for 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 A310-57- 2096, dated May 6, 2008; or Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010. (o) 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: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057- 3356; telephone 425-227-2125; 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: 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 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): 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 a serviceable condition. Any substitutions or changes to procedures or tests identified as RC require approval of an AMOC. (p) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2014-0200R1, dated September 19, 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-2015-3985. (2) 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. 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. Issued in Renton, Washington, on September 28, 2015. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2015-25758 Filed 10-9-15; 8:45 am] BILLING CODE 4910-13-P
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Proposed Rules Federal Register
Vol. 80, No. 197
Tuesday, October 13, 2015
This section of the FEDERAL REGISTER ADDRESSES: You may send comments by this proposed AD. Send your comments
contains notices to the public of the proposed any of the following methods: to an address listed under the
issuance of rules and regulations. The • Federal eRulemaking Portal: Go to ADDRESSES section. Include ‘‘Docket No.
purpose of these notices is to give interested http://www.regulations.gov. Follow the FAA–2015–3985; Directorate Identifier
persons an opportunity to participate in the instructions for submitting comments. 2014–NM–182–AD’’ at the beginning of
rule making prior to the adoption of the final
• Fax: 202–493–2251. your comments. We specifically invite
rules.
• Mail: U.S. Department of comments on the overall regulatory,
Transportation, Docket Operations, M– economic, environmental, and energy
DEPARTMENT OF TRANSPORTATION 30, West Building Ground Floor, Room aspects of this proposed AD. We will
W12–140, 1200 New Jersey Avenue SE., consider all comments received by the
Federal Aviation Administration Washington, DC 20590. closing date and may amend this
• Hand Delivery: U.S. Department of proposed AD based on those comments.
14 CFR Part 39 Transportation, Docket Operations, M– We will post all comments we
30, West Building Ground Floor, Room receive, without change, to http://
[Docket No. FAA–2015–3985; Directorate W12–140, 1200 New Jersey Avenue SE., www.regulations.gov, including any
Identifier 2014–NM–182–AD] Washington, DC, between 9 a.m. and 5 personal information you provide. We
p.m., Monday through Friday, except will also post a report summarizing each
RIN 2120–AA64
Federal holidays. substantive verbal contact we receive
Airworthiness Directives; Airbus For service information identified in about this proposed AD.
Airplanes this proposed AD, contact Airbus SAS,
Discussion
Airworthiness Office—EAW, 1 Rond
AGENCY: Federal Aviation Point Maurice Bellonte, 31707 Blagnac On January 28, 2010, we issued AD
Administration (FAA), DOT. Cedex, France; telephone +33 5 61 93 36 2010–04–03, Amendment 39–16196 (75
ACTION: Notice of proposed rulemaking 96; fax +33 5 61 93 44 51; email FR 6852, February 12, 2010). AD 2010–
(NPRM). account.airworth-eas@airbus.com; 04–03 requires actions intended to
Internet http://www.airbus.com. You address an unsafe condition on all
SUMMARY: We propose to supersede may view this referenced service Airbus Model A310 series airplanes.
Airworthiness Directive (AD) 2010–04– information at the FAA, Transport Since we issued AD 2010–04–03,
03, for all Airbus Model A310 series Airplane Directorate, 1601 Lind Avenue Amendment 39–16196 (75 FR 6852,
airplanes. AD 2010–04–03 currently SW., Renton, WA. For information on February 12, 2010), the manufacturer
requires accomplishing repetitive the availability of this material at the improved the ultrasonic inspection
detailed visual inspections for cracking FAA, call 425–227–1221. program to allow earlier crack detection
around the fastener holes in certain and to extend the repetitive inspection
wing top skin panels between the right Examining the AD Docket intervals. We have determined these
side and left side of the front and rear You may examine the AD docket on inspections are necessary to address the
spars, and repair if needed. Since we the Internet at http:// unsafe condition.
issued AD 2010–04–03, Airbus www.regulations.gov by searching for The European Aviation Safety
improved the ultrasonic inspection and locating Docket No. FAA–2015– Agency, which is the Technical Agent
program to allow earlier crack detection 3985; or in person at the Docket for the Member States of the European
and to extend the repetitive inspection Management Facility between 9 a.m. Community, has issued EASA
intervals. We have determined these and 5 p.m., Monday through Friday, Airworthiness Directive 2014–0200R1,
inspections are necessary to address the except Federal holidays. The AD docket dated September 19, 2014 (referred to
unsafe condition. This proposed AD contains this proposed AD, the after this as the Mandatory Continuing
would continue to require the repetitive regulatory evaluation, any comments Airworthiness Information, or ‘‘the
detailed inspections for cracking around received, and other information. The MCAI’’), to correct an unsafe condition
the fastener holes in certain wing top street address for the Docket Operations on all Airbus Model A310 series
skin panels between the front and rear office (telephone 800–647–5527) is in airplanes. The MCAI states:
spars, and repair if needed, and would the ADDRESSES section. Comments will Following scheduled maintenance, cracks
require supplemental repetitive be available in the AD docket shortly were found around the wing top skin panels
ultrasonic inspections for cracking after receipt. fastener holes at Rib 2, between Stringer
around the fastener holes in certain (STG) 2 and STG14.
FOR FURTHER INFORMATION CONTACT: Dan
This condition, if not detected and
wing top skin panels and repair if Rodina, Aerospace Engineer, corrected, could affect the structural integrity
needed. We are proposing this AD to International Branch, ANM–116, of the aeroplane. The General Visual
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
detect and correct cracking around the Transport Airplane Directorate, FAA, Inspection required by the existing
fastener holes in certain wing top skin 1601 Lind Avenue SW., Renton, WA applicable Airworthiness Limitation Items
panels between the right side and left 98057–3356; telephone 425–227–2125; (ALI) tasks may not be adequate to detect
side of the front and rear spars, which fax 425–227–1149. these cracks.
could result in reduced structural To address this issue, Airbus developed an
SUPPLEMENTARY INFORMATION: inspection programme based on repetitive
integrity of the airplane.
Comments Invited detailed inspections (DET) to ensure that any
DATES: We must receive comments on visible cracks in the wing top skin panels 1
this proposed AD by November 27, We invite you to send any written and 2 along Rib 2 are detected in time and
2015. relevant data, views, or arguments about repaired appropriately. EASA issued [EASA]
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![61328 Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules
AD 2008-0211 [http://ad.easa.europa.eu/ad/ Directive Implementation Aviation We are issuing this rulemaking under
2008-0211] to require implementation of this Rulemaking Committee (ARC), to the authority described in ‘‘Subtitle VII,
inspection programme. enhance the AD system. One Part A, Subpart III, Section 44701:
Since that [EASA] AD was issued, Airbus enhancement was a new process for General requirements.’’ Under that
improved the inspection programme with an
ultrasonic inspection to allow earlier crack
annotating which procedures and tests section, Congress charges the FAA with
detection, to subsequently reduce the scope in the service information are required promoting safe flight of civil aircraft in
of potential repair action, and to extend the for compliance with an AD. air commerce by prescribing regulations
intervals of the repetitive inspections. Differentiating these procedures and for practices, methods, and procedures
For the reasons described above, this tests from other tasks in the service the Administrator finds necessary for
[EASA] AD [http://ad.easa.europa.eu/ad/ information is expected to improve an safety in air commerce. This regulation
2014-0200R1] retains the requirements of owner’s/operator’s understanding of is within the scope of that authority
EASA AD 2008–0211, which is superseded, crucial AD requirements and help because it addresses an unsafe condition
and requires supplementary repetitive provide consistent judgment in AD that is likely to exist or develop on
ultrasonic inspections [for cracking] of the
wing top skin panel 1 and 2 between STG2
compliance. The procedures and tests products identified in this rulemaking
and STG10 at Rib 2 [and repair if needed]. identified as RC (required for action.
compliance) in any service information
* * * * * Regulatory Findings
have a direct effect on detecting,
You may examine the MCAI in the AD preventing, resolving, or eliminating an We determined that this proposed AD
docket on the Internet at http:// identified unsafe condition. would not have federalism implications
www.regulations.gov by searching for As specified in a NOTE under the under Executive Order 13132. This
and locating Docket No. FAA–2015– Accomplishment Instructions of the proposed AD would not have a
3985. specified service information, substantial direct effect on the States, on
Related Service Information Under 1 procedures and tests that are identified the relationship between the national
CFR Part 51 as RC in any service information must Government and the States, or on the
be done to comply with the proposed distribution of power and
Airbus has issued the following AD. However, procedures and tests that responsibilities among the various
service information: are not identified as RC are levels of government.
• Airbus Service Bulletin A310–57–
recommended. Those procedures and For the reasons discussed above, I
2096, dated May 6, 2008,
tests that are not identified as RC may certify this proposed regulation:
• Airbus Service Bulletin A310–57–
2096, Revision 01, dated August 5, be deviated from using accepted 1. Is not a ‘‘significant regulatory
2010. methods in accordance with the action’’ under Executive Order 12866;
• Airbus Service Bulletin A310–57– operator’s maintenance or inspection 2. Is not a ‘‘significant rule’’ under the
2096, Revision 02, dated March 5, 2014. program without obtaining approval of DOT Regulatory Policies and Procedures
an alternative method of compliance (44 FR 11034, February 26, 1979);
This service information describes
(AMOC), provided the procedures and 3. Will not affect intrastate aviation in
procedures for detailed visual and
tests identified as RC can be done and Alaska; and
ultrasonic inspections for cracking
the airplane can be put back in a 4. Will not have a significant
around the fastener holes of the wing
serviceable condition. Any substitutions economic impact, positive or negative,
top skin panels between the right side
or changes to procedures or tests on a substantial number of small entities
and left side of the front and rear spars
identified as RC will require approval of under the criteria of the Regulatory
at certain locations, and repair if
an AMOC. Flexibility Act.
needed. This service information is
reasonably available because the Costs of Compliance List of Subjects in 14 CFR Part 39
interested parties have access to it
We estimate that this proposed AD Air transportation, Aircraft, Aviation
through their normal course of business
affects 13 airplanes of U.S. registry. safety, Incorporation by reference,
or by the means identified in the
ADDRESSES section of this NPRM.
We also estimate that it would take Safety.
about 5 work-hours per product to
FAA’s Determination and Requirements comply with the basic requirements of The Proposed Amendment
of This Proposed AD this proposed AD. The average labor Accordingly, under the authority
This product has been approved by rate is $85 per work-hour. Required delegated to me by the Administrator,
the aviation authority of another parts would cost $0 per product. Based the FAA proposes to amend 14 CFR part
country, and is approved for operation on these figures, we estimate the cost of 39 as follows:
in the United States. Pursuant to our this proposed AD on U.S. operators to
bilateral agreement with the State of be $5,525, or $425 per product. PART 39—AIRWORTHINESS
Design Authority, we have been notified We have received no definitive data DIRECTIVES
of the unsafe condition described in the that would enable us to provide cost
estimates for the on-condition actions ■ 1. The authority citation for part 39
MCAI and service information
specified in this AD. continues to read as follows:
referenced above. We are proposing this
AD because we evaluated all pertinent Authority: 49 U.S.C. 106(g), 40113, 44701.
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Authority for This Rulemaking
information and determined an unsafe § 39.13 [Amended]
condition exists and is likely to exist or Title 49 of the United States Code
develop on other products of the same specifies the FAA’s authority to issue ■ 2. The FAA amends § 39.13 by
type design. rules on aviation safety. Subtitle I, removing Airworthiness Directive (AD)
section 106, describes the authority of 2010–04–03, Amendment 39–16196 (75
Explanation of ‘‘RC’’ Procedures and the FAA Administrator. ‘‘Subtitle VII: FR 6852, February 12, 2010), and adding
Tests in Service Information Aviation Programs,’’ describes in more the following new AD:
The FAA worked in conjunction with detail the scope of the Agency’s Airbus: Docket No. FAA–2015–3985;
industry, under the Airworthiness authority. Directorate Identifier 2014–NM–182–AD.
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![61330 Federal Register / Vol. 80, No. 197 / Tuesday, October 13, 2015 / Proposed Rules
(3) The second inspection interval is by searching for and locating Docket No. Ground Floor, Room W12–140,
defined as the total flight hours accumulated FAA–2015–3985. Washington, DC 20590–0001.
divided by the total number of flight cycles (2) For service information identified in • Hand Delivery: Deliver to Mail
accumulated between the initial and second this AD, contact Airbus SAS, Airworthiness
address above between 9 a.m. and 5
threshold. Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; p.m., Monday through Friday, except
(n) Credit for Previous Actions telephone +33 5 61 93 36 96; fax +33 5 61 Federal holidays.
This paragraph provides credit for actions 93 44 51; email account.airworth-eas@ • Fax: 202–493–2251.
required by paragraph (g)(1) of this AD, if airbus.com; Internet http://www.airbus.com. For service information identified in
those actions were performed before the You may view this service information at the this proposed AD, contact Dowty
effective date of this AD using Airbus Service FAA, Transport Airplane Directorate, 1601 Propellers, 114 Powers Court, Sterling,
Bulletin A310–57–2096, dated May 6, 2008; Lind Avenue SW., Renton, WA. For VA 20166; phone: 703–421–4434; fax:
or Airbus Service Bulletin A310–57–2096, information on the availability of this 703–450–0087; email:
Revision 01, dated August 5, 2010. material at the FAA, call 425–227–1221.
technicalsupport@dowty.com; Internet:
(o) Other FAA AD Provisions Issued in Renton, Washington, on www.http://dowty.com/services/repair-
The following provisions also apply to this September 28, 2015. and-overhaul. You may view this
AD: Michael Kaszycki, service information at the FAA, Engine
(1) Alternative Methods of Compliance Acting Manager, Transport Airplane & Propeller Directorate, 12 New England
(AMOCs): The Manager, International Directorate, Aircraft Certification Service. Executive Park, Burlington, MA. For
Branch, ANM–116, Transport Airplane [FR Doc. 2015–25758 Filed 10–9–15; 8:45 am] information on the availability of this
Directorate, FAA, has the authority to material at the FAA, call 781–238–7125.
BILLING CODE 4910–13–P
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19. Examining the AD Docket
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local DEPARTMENT OF TRANSPORTATION You may examine the AD docket on
Flight Standards District Office, as the Internet at http://
appropriate. If sending information directly Federal Aviation Administration www.regulations.gov by searching for
to the International Branch, send it to ATTN: and locating Docket No. FAA–2015–
Dan Rodina, Aerospace Engineer, 14 CFR Part 39 3661; or in person at the Docket
International Branch, ANM–116, Transport [Docket No. FAA–2015–3661; Directorate Operations office between 9 a.m. and 5
Airplane Directorate, FAA, 1601 Lind Identifier 2015–NE–24–AD] p.m., Monday through Friday, except
Avenue SW., Renton, WA 98057–3356; Federal holidays. The AD docket
telephone 425–227–2125; fax 425–227–1149. RIN 2120–AA64 contains this proposed AD, the
Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using Airworthiness Directives; Dowty mandatory continuing airworthiness
any approved AMOC, notify your appropriate Propellers Constant Speed Propellers information (MCAI), the regulatory
principal inspector, or lacking a principal evaluation, any comments received, and
inspector, the manager of the local flight AGENCY: Federal Aviation other information. The address for the
standards district office/certificate holding Administration (FAA), DOT. Docket Office (phone: 800–647–5527) is
district office. The AMOC approval letter ACTION: Notice of proposed rulemaking in the ADDRESSES section. Comments
must specifically reference this AD. (NPRM). will be available in the AD docket
(2) Contacting the Manufacturer: As of the shortly after receipt.
effective date of this AD, for any requirement SUMMARY: We propose to adopt a new
in this AD to obtain corrective actions from FOR FURTHER INFORMATION CONTACT:
airworthiness directive (AD) for certain Michael Schwetz, Aerospace Engineer,
a manufacturer, the action must be
Dowty Propellers R352/6–123–F/1, Boston Aircraft Certification Office,
accomplished using a method approved by
the Manager, International Branch, ANM– R352/6–123–F/2, and R410/6–123–F/35 FAA, Engine & Propeller Directorate, 12
116, Transport Airplane Directorate, FAA; or model propellers. This proposed AD New England Executive Park,
the EASA; or Airbus’s EASA DOA. If was prompted by reports of dowel hole Burlington, MA 01803; phone: 781–
approved by the DOA, the approval must cracks in the face of the rear hub half. 238–7761; fax 781–238–7170; email:
include the DOA-authorized signature. This proposed AD would require a michael.schwetz@faa.gov.
(3) Required for Compliance (RC): If any records review to determine repair
service information contains procedures or SUPPLEMENTARY INFORMATION:
status and marking the affected
tests that are identified as RC, those propeller hubs as required. This Comments Invited
procedures and tests must be done to comply
proposed AD would also require
with this AD; any procedures or tests that are We invite you to send any written
not identified as RC are recommended. Those installing dowel hole liners as
relevant data, views, or arguments about
procedures and tests that are not identified necessary. We are proposing this AD to
this NPRM. Send your comments to an
as RC may be deviated from using accepted prevent loss of structural integrity of the
address listed under the ADDRESSES
methods in accordance with the operator’s propeller hub, which could result in
section. Include ‘‘Docket No. FAA–
maintenance or inspection program without damage to the propeller and damage to
obtaining approval of an AMOC, provided 2015–3661; Directorate Identifier 2015–
the airplane.
the procedures and tests identified as RC can NE–24–AD’’ at the beginning of your
DATES: We must receive comments on comments. We specifically invite
be done and the airplane can be put back in
a serviceable condition. Any substitutions or
this proposed AD by December 14, comments on the overall regulatory,
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
changes to procedures or tests identified as 2015. economic, environmental, and energy
RC require approval of an AMOC. ADDRESSES: You may send comments by aspects of this NPRM. We will consider
(p) Related Information any of the following methods: all comments received by the closing
• Federal eRulemaking Portal: Go to date and may amend this NPRM based
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA http://www.regulations.gov. Follow the on those comments.
Airworthiness Directive 2014–0200R1, dated instructions for submitting comments. We will post all comments we
September 19, 2014, for related information. • Mail: Docket Management Facility, receive, without change, to http://
This MCAI may be found in the AD docket U.S. Department of Transportation, 1200 www.regulations.gov, including any
on the Internet at http://www.regulations.gov New Jersey Avenue SE., West Building personal information you provide. We
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Document Created: 2018-02-27 08:48:21
Document Modified: 2018-02-27 08:48:21
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by November 27, 2015. | |
| Contact | Dan Rodina, Aerospace Engineer, International Branch, ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; fax 425-227-1149. | |
| FR Citation | 80 FR 61327 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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