81 FR 78899 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 218 (November 10, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 218 (November 10, 2016)
| Page Range | 78899-78902 | |
| FR Document | 2016-26810 |
[Federal Register Volume 81, Number 218 (Thursday, November 10, 2016)] [Rules and Regulations] [Pages 78899-78902] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-26810] ======================================================================== Rules and Regulations Federal Register ________________________________________________________________________ This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. ======================================================================== Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / Rules and Regulations [[Page 78899]] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD; Amendment 39-18708; AD 2016-23-01] 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) 2010-04-03 for all Airbus Model A310 series airplanes. AD 2010-04-03 required accomplishing repetitive detailed inspections for cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, and repair if necessary. This new AD continues to require the repetitive detailed inspections, and also requires supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at ribs 2 and 3, and repair if necessary. This AD was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, which could result in reduced structural integrity of the airplane. DATES: This AD is effective December 15, 2016. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 15, 2016. 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 3985. 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 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 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: Discussion We issued a supplemental notice of proposed rulemaking (SNPRM) to amend 14 CFR part 39 to supersede AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010) (``AD 2010-04-03''). AD 2010-04-03 applied to all Airbus Model A310 series airplanes. The SNPRM published in the Federal Register on July 11, 2016 (81 FR 44812) (``the SNPRM''). We preceded the SNPRM with a notice of proposed rulemaking (NPRM) that published in the Federal Register on October 13, 2015 (80 FR 61327) (``the NPRM''). The NPRM was prompted by development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. The NPRM proposed to retain the requirements of AD 2010-04-03, and proposed to require supplemental repetitive ultrasonic inspections for cracking around the fastener holes in wing top skin panels 1 and 2 at rib 2, and repair if necessary. The SNPRM proposed to expand the inspection area to include rib 3 due to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking around the fastener holes, 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 Airworthiness Directive 2016-0005, dated January 7, 2016 (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 AD 2008- 0211 to require implementation of this inspection programme. After 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. Consequently, EASA issued AD 2014-0200 (later revised), superseding [EASA] AD 2008-0211, retaining its requirements, and to require 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]. Since EASA AD 2014-0020R1 was issued, a widespread fatigue damage analysis concluded that the inspection programme has to be extended to include the wing top skin panels at Rib 3 attachments. For the reasons described above, this [EASA] AD [[Page 78900]] retains the requirements of EASA AD 2014-0200R1, which is superseded, and extends the inspection area to include Rib 3. 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the SNPRM or on the determination of the cost to the public. Clarification of Requirements We have clarified the terminating action sentence in paragraph (k) of this AD by adding a reference to paragraph (g) of this AD. We have clarified the average flight time in paragraph (l)(3) of this AD for subsequent inspections after the second inspection interval. Conclusion We reviewed the relevant data and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. Related Service Information Under 1 CFR part 51 Airbus has issued Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015. This service information describes procedures for detailed and ultrasonic inspections for cracking around the fastener holes of wing top skin panels 1 and 2, at ribs 2 and 3, on the left- and right-hand sides of the fuselage. 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 28 airplanes of U.S. registry. We also estimate that it takes about 8 work-hours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD on U.S. operators to be $19,040, or $680 per product. We estimate that it takes about 15 work-hours per product to do any necessary on-condition actions that are required based on the results of the inspections. Required parts will cost about $10,000 per product. We have no way of determining the number of aircraft that might need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs,'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in ``Subtitle VII, Part A, Subpart III, Section 44701: General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010), and adding the following new AD: 2016-23-01 Airbus: Amendment 39-18708; Docket No. FAA-2015-3985; Directorate Identifier 2014-NM-182-AD. (a) Effective Date This AD is effective December 15, 2016. (b) Affected ADs This AD replaces AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010) (``AD 2010-04-03''). (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 the development of an ultrasonic inspection program to allow for earlier crack detection and extended repetitive inspection intervals. We are issuing this AD to detect and correct fatigue cracking around the fastener holes in certain wing top skin panels between the front and rear spars on the left- and right-hand sides of the fuselage, 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 the 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) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015, except as provided by paragraph (j) of this AD. (1) Accomplish a detailed inspection for cracking around the fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 3, between the front and rear spars on the left- and right-hand sides of the fuselage. (2) Accomplish an ultrasonic inspection for cracking around the fastener holes in the wing top skin panels 1 and 2, along ribs 2 and 3, between stringer (STG) 2 and STG10 [[Page 78901]] on the left- and right-hand sides 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 paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(1)(i) and (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 paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(2)(i) and (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 paragraphs (g)(1) and (g)(2) of this AD at the later of the times specified in paragraphs (h)(3)(i) and (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 for 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; Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010; or Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014: At the applicable compliance times specified in paragraphs (i)(1), (i)(2), and (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 03, dated June 30, 2015. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the repetitive intervals specified in paragraphs (h)(1), (h)(2), and (h)(3) of this AD, as applicable. (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (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 paragraphs (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 paragraphs (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), (i)(2), and (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), (h)(2), and (h)(3) of this AD. (1) For airplanes not 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 initial compliance time specified by paragraphs (h)(1), (h)(2), and (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), (i)(2), and (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 paragraph (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). Accomplishing the repair specified in this paragraph terminates the repetitive inspections required by paragraph (g), (h), (i), or (j) of this AD, as applicable, for the repaired area only. (l) Definition of Average Flight Time (AFT) For the purposes of this AD, the AFT should be established as specified in paragraphs (l)(1), (l)(2), and (l)(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. (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 inspection threshold. For all inspection intervals onwards, the average flight time is the flight hours divided by the flight cycles accumulated between the last two inspections. (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g)(1) of this AD, if those actions were performed before the effective date of this AD using the applicable service information identified in paragraph (m)(1), (m)(2), or (m)(3) of this AD. (1) Airbus Service Bulletin A310-57-2096, dated May 6, 2008, which was incorporated by reference in AD 2010-04-03. (2) Airbus Service Bulletin A310-57-2096, Revision 01, dated August 5, 2010, which is not incorporated by reference in this AD. (3) Airbus Service Bulletin A310-57-2096, Revision 02, dated March 5, 2014, which is not incorporated by reference in this AD. (n) 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. [[Page 78902]] (3) Required for Compliance (RC): Except as required by paragraph (k) 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. (o) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA Airworthiness Directive 2016-0005, dated January 7, 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-2015-3985. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (p)(4) and (p)(5) of this AD. (p) 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. (3) The following service information was approved for IBR on December 15, 2016. (i) Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015. (ii) Reserved. (4) 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. (5) 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. (6) 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 October 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-26810 Filed 11-9-16; 8:45 am] BILLING CODE 4910-13-P
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Rules and Regulations Federal Register
Vol. 81, No. 218
Thursday, November 10, 2016
This section of the FEDERAL REGISTER ADDRESSES: For service information NPRM was prompted by development of
contains regulatory documents having general identified in this final rule, contact an ultrasonic inspection program to
applicability and legal effect, most of which Airbus SAS, Airworthiness Office— allow for earlier crack detection and
are keyed to and codified in the Code of EAW, 1 Rond Point Maurice Bellonte, extended repetitive inspection intervals.
Federal Regulations, which is published under 31707 Blagnac Cedex, France; telephone The NPRM proposed to retain the
50 titles pursuant to 44 U.S.C. 1510.
+33 5 61 93 36 96; fax +33 5 61 93 44 requirements of AD 2010–04–03, and
The Code of Federal Regulations is sold by 51; email account.airworth-eas@ proposed to require supplemental
the Superintendent of Documents. Prices of airbus.com; Internet http:// repetitive ultrasonic inspections for
new books are listed in the first FEDERAL www.airbus.com. You may view this cracking around the fastener holes in
REGISTER issue of each week. referenced service information at the wing top skin panels 1 and 2 at rib 2,
FAA, Transport Airplane Directorate, and repair if necessary. The SNPRM
1601 Lind Avenue SW., Renton, WA. proposed to expand the inspection area
DEPARTMENT OF TRANSPORTATION For information on the availability of to include rib 3 due to widespread
this material at the FAA, call 425–227– fatigue damage. We are issuing this AD
Federal Aviation Administration 1221. It is also available on the Internet to detect and correct fatigue cracking
at http://www.regulations.gov by around the fastener holes, which could
14 CFR Part 39 searching for and locating Docket No. result in reduced structural integrity of
FAA–2015–3985. the airplane.
[Docket No. FAA–2015–3985; Directorate The European Aviation Safety Agency
Identifier 2014–NM–182–AD; Amendment Examining the AD Docket (EASA), which is the Technical Agent
39–18708; AD 2016–23–01]
You may examine the AD docket on for the Member States of the European
the Internet at Union, has issued EASA Airworthiness
RIN 2120–AA64 http://www.regulations.gov by searching Directive 2016–0005, dated January 7,
Airworthiness Directives; Airbus for and locating Docket No. FAA–2015– 2016 (referred to after this as the
Airplanes 3985; or in person at the Docket Mandatory Continuing Airworthiness
Management Facility between 9 a.m. Information, or ‘‘the MCAI’’), to correct
AGENCY: Federal Aviation and 5 p.m., Monday through Friday, an unsafe condition on all Airbus Model
Administration (FAA), Department of except Federal holidays. The AD docket A310 series airplanes. The MCAI states:
Transportation (DOT). contains this AD, the regulatory Following scheduled maintenance, cracks
ACTION: Final rule. evaluation, any comments received, and were found around the wing top skin panels
other information. The address for the fastener holes at Rib 2, between Stringer
SUMMARY: We are superseding Docket Office (telephone 800–647–5527) (STG) 2 and STG14.
Airworthiness Directive (AD) 2010–04– is Docket Management Facility, U.S. This condition, if not detected and
03 for all Airbus Model A310 series Department of Transportation, Docket corrected, could affect the structural integrity
airplanes. AD 2010–04–03 required Operations, M–30, West Building of the aeroplane. The General Visual
Inspection required by the existing
accomplishing repetitive detailed Ground Floor, Room W12–140, 1200 applicable Airworthiness Limitation Items
inspections for cracking around the New Jersey Avenue SE., Washington, (ALI) tasks may not be adequate to detect
fastener holes in certain wing top skin DC 20590. these cracks.
panels between the front and rear spars FOR FURTHER INFORMATION CONTACT: Dan To address this issue, Airbus developed an
on the left- and right-hand sides of the Rodina, Aerospace Engineer, inspection programme based on repetitive
fuselage, and repair if necessary. This International Branch, ANM–116, detailed inspections (DET) to ensure that any
new AD continues to require the visible cracks in the wing top skin panels 1
Transport Airplane Directorate, FAA, and 2 along Rib 2 are detected in time and
repetitive detailed inspections, and also 1601 Lind Avenue SW., Renton, WA repaired appropriately. EASA issued AD
requires supplemental repetitive 98057–3356; telephone 425–227–2125; 2008–0211 to require implementation of this
ultrasonic inspections for cracking fax 425–227–1149. inspection programme.
around the fastener holes in wing top SUPPLEMENTARY INFORMATION: After that [EASA] AD was issued, Airbus
skin panels 1 and 2 at ribs 2 and 3, and improved the inspection programme with an
repair if necessary. This AD was Discussion ultrasonic inspection to allow earlier crack
prompted by development of an We issued a supplemental notice of detection, to subsequently reduce the scope
ultrasonic inspection program to allow of potential repair action, and to extend the
proposed rulemaking (SNPRM) to intervals of the repetitive inspections.
for earlier crack detection and extended amend 14 CFR part 39 to supersede AD Consequently, EASA issued AD 2014–0200
repetitive inspection intervals. We are 2010–04–03, Amendment 39–16196 (75 (later revised), superseding [EASA] AD 2008–
issuing this AD to detect and correct FR 6852, February 12, 2010) (‘‘AD 2010– 0211, retaining its requirements, and to
fatigue cracking around the fastener 04–03’’). AD 2010–04–03 applied to all require supplementary repetitive ultrasonic
asabaliauskas on DSK3SPTVN1PROD with RULES
holes, which could result in reduced Airbus Model A310 series airplanes. inspections [for cracking] of the wing top
structural integrity of the airplane. The SNPRM published in the Federal skin panel 1 and 2 between STG2 and STG10
DATES: This AD is effective December Register on July 11, 2016 (81 FR 44812) at Rib 2 [and repair if needed].
Since EASA AD 2014–0020R1 was issued,
15, 2016. (‘‘the SNPRM’’). We preceded the a widespread fatigue damage analysis
The Director of the Federal Register SNPRM with a notice of proposed concluded that the inspection programme
approved the incorporation by reference rulemaking (NPRM) that published in has to be extended to include the wing top
of a certain publication listed in this AD the Federal Register on October 13, skin panels at Rib 3 attachments. For the
as of December 15, 2016. 2015 (80 FR 61327) (‘‘the NPRM’’). The reasons described above, this [EASA] AD
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retains the requirements of EASA AD 2014– necessary on-condition actions that are PART 39—AIRWORTHINESS
0200R1, which is superseded, and extends required based on the results of the DIRECTIVES
the inspection area to include Rib 3. inspections. Required parts will cost
You may examine the MCAI in the about $10,000 per product. We have no ■ 1. The authority citation for part 39
AD docket on the Internet at http:// way of determining the number of continues to read as follows:
www.regulations.gov by searching for aircraft that might need these actions. Authority: 49 U.S.C. 106(g), 40113, 44701.
and locating Docket No. FAA–2015– Authority for This Rulemaking
3985. § 39.13 [Amended]
Title 49 of the United States Code ■ 2. The FAA amends § 39.13 by
Comments
specifies the FAA’s authority to issue removing Airworthiness Directive (AD)
We gave the public the opportunity to rules on aviation safety. Subtitle I, 2010–04–03, Amendment 39–16196 (75
participate in developing this AD. We section 106, describes the authority of FR 6852, February 12, 2010), and adding
received no comments on the SNPRM or the FAA Administrator. ‘‘Subtitle VII: the following new AD:
on the determination of the cost to the Aviation Programs,’’ describes in more 2016–23–01 Airbus: Amendment 39–18708;
public. detail the scope of the Agency’s Docket No. FAA–2015–3985; Directorate
Clarification of Requirements authority. Identifier 2014–NM–182–AD.
We are issuing this rulemaking under (a) Effective Date
We have clarified the terminating the authority described in ‘‘Subtitle VII,
action sentence in paragraph (k) of this This AD is effective December 15, 2016.
Part A, Subpart III, Section 44701:
AD by adding a reference to paragraph General requirements.’’ Under that (b) Affected ADs
(g) of this AD. section, Congress charges the FAA with This AD replaces AD 2010–04–03,
We have clarified the average flight Amendment 39–16196 (75 FR 6852, February
promoting safe flight of civil aircraft in
time in paragraph (l)(3) of this AD for 12, 2010) (‘‘AD 2010–04–03’’).
air commerce by prescribing regulations
subsequent inspections after the second
for practices, methods, and procedures (c) Applicability
inspection interval.
the Administrator finds necessary for This AD applies to all Airbus Model A310–
Conclusion safety in air commerce. This regulation 203, –204, –221, –222, –304, –322, –324, and
We reviewed the relevant data and is within the scope of that authority –325 airplanes, certificated in any category,
determined that air safety and the because it addresses an unsafe condition all manufacturer serial numbers.
public interest require adopting this AD that is likely to exist or develop on (d) Subject
with the changes described previously products identified in this rulemaking
action. Air Transport Association (ATA) of
and minor editorial changes. We have America Code 57, Wings.
determined that these minor changes: Regulatory Findings (e) Reason
• Are consistent with the intent that
was proposed in the SNPRM for We determined that this AD will not This AD was prompted by the
correcting the unsafe condition; and have federalism implications under development of an ultrasonic inspection
Executive Order 13132. This AD will program to allow for earlier crack detection
• Do not add any additional burden
not have a substantial direct effect on and extended repetitive inspection intervals.
upon the public than was already We are issuing this AD to detect and correct
proposed in the SNPRM. the States, on the relationship between
fatigue cracking around the fastener holes in
the national government and the States, certain wing top skin panels between the
Related Service Information Under 1 or on the distribution of power and front and rear spars on the left- and right-
CFR part 51 responsibilities among the various hand sides of the fuselage, which could
Airbus has issued Service Bulletin levels of government. result in reduced structural integrity of the
A310–57–2096, Revision 03, dated June For the reasons discussed above, I airplane.
30, 2015. This service information certify that this AD: (f) Compliance
describes procedures for detailed and 1. Is not a ‘‘significant regulatory Comply with this AD within the
ultrasonic inspections for cracking action’’ under Executive Order 12866; compliance times specified, unless already
around the fastener holes of wing top 2. Is not a ‘‘significant rule’’ under the done.
skin panels 1 and 2, at ribs 2 and 3, on DOT Regulatory Policies and Procedures (g) Repetitive Inspections
the left- and right-hand sides of the (44 FR 11034, February 26, 1979);
fuselage. This service information is Except as required by paragraph (i) of this
3. Will not affect intrastate aviation in AD: Within the initial compliance time and
reasonably available because the
Alaska; and thereafter at the repetitive intervals specified
interested parties have access to it
4. Will not have a significant in paragraphs (h)(1) through (h)(3) of this AD,
through their normal course of business as applicable, accomplish the actions
or by the means identified in the economic impact, positive or negative,
on a substantial number of small entities specified in paragraphs (g)(1) and (g)(2) of
ADDRESSES section. this AD concurrently and in sequence, in
under the criteria of the Regulatory accordance with the Accomplishment
Costs of Compliance Flexibility Act. Instructions of Airbus Service Bulletin A310–
We estimate that this AD affects 28 List of Subjects in 14 CFR Part 39 57–2096, Revision 03, dated June 30, 2015,
airplanes of U.S. registry. except as provided by paragraph (j) of this
We also estimate that it takes about 8 Air transportation, Aircraft, Aviation AD.
asabaliauskas on DSK3SPTVN1PROD with RULES
work-hours per product to comply with safety, Incorporation by reference, (1) Accomplish a detailed inspection for
the basic requirements of this AD. The Safety. cracking around the fastener holes in the
wing top skin panels 1 and 2, along ribs 2
average labor rate is $85 per work-hour. Adoption of the Amendment and 3, between the front and rear spars on
Based on these figures, we estimate the the left- and right-hand sides of the fuselage.
cost of this AD on U.S. operators to be Accordingly, under the authority (2) Accomplish an ultrasonic inspection for
$19,040, or $680 per product. delegated to me by the Administrator, cracking around the fastener holes in the
We estimate that it takes about 15 the FAA amends 14 CFR part 39 as wing top skin panels 1 and 2, along ribs 2
work-hours per product to do any follows: and 3, between stringer (STG) 2 and STG10
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![78902 Federal Register / Vol. 81, No. 218 / Thursday, November 10, 2016 / Rules and Regulations
(3) Required for Compliance (RC): Except DEPARTMENT OF TRANSPORTATION federal_register/code_of_federal-
as required by paragraph (k) of this AD, if any regulations/ibr_locations.html.
service information contains procedures or Federal Aviation Administration FAA Order 7400.11, Airspace
tests that are identified as RC, those Designations and Reporting Points, is
procedures and tests must be done to comply 14 CFR Part 71 published yearly and effective on
with this AD; any procedures or tests that are
September 15.
not identified as RC are recommended. Those [Docket No. FAA–2016–6985; Airspace
procedures and tests that are not identified Docket No. 16–AGL–16] FOR FURTHER INFORMATION CONTACT:
as RC may be deviated from using accepted Jeffrey Claypool, Federal Aviation
methods in accordance with the operator’s Amendment of Class E Airspace for Administration, Operations Support
maintenance or inspection program without the Following Illinois Towns; Carmi, IL; Group, Central Service Center, 10101
obtaining approval of an AMOC, provided De Kalb, IL; Harrisburg, IL; Kewanee, Hillwood Parkway, Fort Worth, TX,
the procedures and tests identified as RC can IL; Litchfield, IL; Paris, IL; and 76177; telephone (817) 222–5711.
be done and the airplane can be put back in Taylorville, IL SUPPLEMENTARY INFORMATION:
an airworthy condition. Any substitutions or
changes to procedures or tests identified as AGENCY: Federal Aviation Authority for This Rulemaking
RC require approval of an AMOC. Administration (FAA), DOT. The FAA’s authority to issue rules
(o) Related Information ACTION: Final rule. regarding aviation safety is found in
(1) Refer to Mandatory Continuing Title 49 of the United States Code.
SUMMARY: This action modifies Class E
Airworthiness Information (MCAI) EASA Subtitle I, Section 106 describes the
airspace extending upward from 700
Airworthiness Directive 2016–0005, dated authority of the FAA Administrator.
January 7, 2016, for related information. This feet above the surface at Carmi
Subtitle VII, Aviation Programs,
MCAI may be found in the AD docket on the Municipal Airport, Carmi, IL; De Kalb
describes in more detail the scope of the
Internet at http://www.regulations.gov by Taylor Municipal Airport, De Kalb, IL;
agency’s authority. This rulemaking is
searching for and locating Docket No. FAA– Harrisburg-Raleigh Airport, Harrisburg,
promulgated under the authority
2015–3985. IL; Kewanne Municipal Airport,
described in Subtitle VII, Part A,
(2) Service information identified in this Kewanne, IL; Litchfield Municipal
AD that is not incorporated by reference is Subpart I, Section 40103. Under that
Airport, Litchfield, IL; Edgar County
available at the addresses specified in section, the FAA is charged with
Airport, Paris, IL; and Taylorville
paragraphs (p)(4) and (p)(5) of this AD. prescribing regulations to assign the use
Municipal Airport, Taylorville, IL.
of airspace necessary to ensure the
(p) Material Incorporated by Reference Decommissioning of non-directional
safety of aircraft and the efficient use of
(1) The Director of the Federal Register radio beacons (NDB), cancellation of
airspace. This regulation is within the
approved the incorporation by reference NDB approaches, or implementation of
scope of that authority as it amends
(IBR) of the service information listed in this area navigation (RNAV) procedures
Class E airspace at Carmi Municipal
paragraph under 5 U.S.C. 552(a) and 1 CFR have made this action necessary for the
Airport, Carmi, IL; De Kalb Taylor
part 51. safety and management of Instrument
Municipal Airport, De Kalb, IL;
(2) You must use this service information Flight Rules (IFR) operations at the
as applicable to do the actions required by Harrisburg-Raleigh Airport, Harrisburg,
above airports. This action also updates
this AD, unless this AD specifies otherwise. IL; Kewanne Municipal Airport,
the geographic coordinates of Carmi
(3) The following service information was Kewanne, IL; Litchfield Municipal
Municipal Airport, De Kalb Taylor
approved for IBR on December 15, 2016. Airport, Litchfield, IL; Edgar County
Municipal Airport, Harrisburg-Raleigh
(i) Airbus Service Bulletin A310–57–2096, Airport, Paris, IL; and Taylorville
Airport, Litchfield Municipal Airport,
Revision 03, dated June 30, 2015. Municipal Airport, Taylorville, IL.
(ii) Reserved.
Edgar County Airport, and Taylorville
(4) For service information identified in Municipal Airport to coincide with the History
this AD, contact Airbus SAS, Airworthiness FAA’s aeronautical database. On July 1, 2016, the FAA published
Office—EAW, 1 Rond Point Maurice DATES: Effective 0901 UTC, March 2, in the Federal Register a notice of
Bellonte, 31707 Blagnac Cedex, France; 2017. The Director of the Federal proposed rulemaking (NPRM), (81 FR
telephone +33 5 61 93 36 96; fax +33 5 61 Register approves this incorporation by 43124) Docket No. FAA–2016–6985, to
93 44 51; email account.airworth-eas@ reference action under Title 1, Code of
airbus.com; Internet http://www.airbus.com.
modify Class E airspace at Carmi
Federal Regulations, part 51, subject to Municipal Airport, Carmi, IL; De Kalb
(5) You may view this service information
the annual revision of FAA Order Taylor Municipal Airport, De Kalb, IL;
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
7400.11 and publication of conforming Harrisburg-Raleigh Airport, Harrisburg,
information on the availability of this amendments. IL; Kewanne Municipal Airport,
material at the FAA, call 425–227–1221. ADDRESSES: FAA Order 7400.11A, Kewanne, IL; Litchfield Municipal
(6) You may view this service information Airspace Designations and Reporting Airport, Litchfield, IL; Edgar County
that is incorporated by reference at the Points, and subsequent amendments can Airport, Paris, IL; and Taylorville
National Archives and Records be viewed online at http://www.faa.gov/ Municipal Airport, Taylorville, IL.
Administration (NARA). For information on air_traffic/publications/. For further Interested parties were invited to
the availability of this material at NARA, call information, you can contact the participate in this rulemaking effort by
202–741–6030, or go to: http://
Airspace Policy Group, Federal Aviation submitting written comments on the
www.archives.gov/federal-register/cfr/ibr-
locations.html.
Administration, 800 Independence proposal to the FAA. No comments
asabaliauskas on DSK3SPTVN1PROD with RULES
Avenue SW., Washington, DC 20591; were received. The FAA discovered a
Issued in Renton, Washington, on October telephone: 202–267–8783. The Order is typographical error in the geographic
28, 2016. also available for inspection at the coordinate of Harrisburg-Raleigh Airport
Dionne Palermo, National Archives and Records which has been corrected in this action.
Acting Manager, Transport Airplane Administration (NARA). For Class E airspace designations are
Directorate, Aircraft Certification Service. information on the availability of FAA published in paragraph 6005 of FAA
[FR Doc. 2016–26810 Filed 11–9–16; 8:45 am] Order 7400.11A at NARA, call 202–741– Order 7400.11A, dated August 3, 2016,
BILLING CODE 4910–13–P 6030, or go to http://www.archives.gov/ and effective September 15, 2016, which
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Document Created: 2016-11-10 01:44:09
Document Modified: 2016-11-10 01:44:09
| 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 December 15, 2016. | |
| 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 | 81 FR 78899 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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