83 FR 22362 - Airworthiness Directives; Airbus Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 94 (May 15, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 94 (May 15, 2018)
| Page Range | 22362-22367 | |
| FR Document | 2018-10214 |
[Federal Register Volume 83, Number 94 (Tuesday, May 15, 2018)] [Rules and Regulations] [Pages 22362-22367] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-10214] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0071; Product Identifier 2017-NM-063-AD; Amendment 39-19280; AD 2018-10-05] RIN 2120-AA64 Airworthiness Directives; Airbus Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). [[Page 22363]] ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are superseding Airworthiness Directive (AD) 2016-23-01, which applied to all Airbus Model A310 series airplanes. AD 2016-23-01 required repetitive detailed inspections for cracking around the fastener holes in certain areas of the wing top skin panels, supplemental repetitive ultrasonic inspections for cracking around the fastener holes in certain other areas of the wing top skin panels, and repair if necessary. This AD adds an inspection and modification of the fastener holes of the wing top skin panels at a certain area. This AD also includes terminating action for certain inspections. This AD was prompted by an evaluation by the design approval holder (DAH) which indicates that the wing top skin panel fastener holes at a certain area are also subject to widespread fatigue damage (WFD). We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective June 19, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 19, 2018. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of December 15, 2016 (81 FR 78899, November 10, 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: account.airworth-eas@airbus.com; internet: http://www.airbus.com. You may view this referenced service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0071. 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-2018- 0071; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (telephone 800- 647-5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3225. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016) (``AD 2016-23-01''). AD 2016-23-01 applied to all Airbus Model A310 series airplanes. The NPRM published in the Federal Register on February 8, 2018 (83 FR 5579). The NPRM was prompted by an evaluation done by the DAH which indicates that the wing top skin panel fastener holes at a certain area are subject to WFD. The NPRM would continue to require repetitive detailed inspections for cracking around the fastener holes in certain areas of the wing top skin panels, supplemental repetitive ultrasonic inspections for cracking around the fastener holes in certain other areas of the wing top skin panels, and repair if necessary. The NPRM proposed to add an inspection and modification of the fastener holes of the wing top skin panels at a certain area. The NPRM also includes terminating action for certain inspections. 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 AD 2017-0081, dated May 8, 2017 (referred to after this as the Mandatory Continuing Airworthiness Information, or ``the MCAI''), to correct an unsafe condition for 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 reduce the structural integrity of the aeroplane. To address this issue, Airbus developed an inspection programme, and published Service Bulletin (SB) A310-57-2096, providing instructions for repetitive detailed inspections (DET) to ensure that any visible cracks in the wing top skin panels 1 and 2 along Rib 2 are detected on time and repaired appropriately. Consequently, EASA issued AD 2008-0211 [which corresponds to FAA AD 2010-04-03, Amendment 39-16196 (75 FR 6852, February 12, 2010) (``AD 2010-04- 03)] to require implementation of that inspection programme. After that [EASA] AD was issued, Airbus improved the inspection programme, revising SB A310-57-2096 accordingly, to include a special detailed inspection (SDI), using an ultrasonic method, 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), retaining the requirements of EASA AD 2008-0211, which was superseded, and required supplementary repetitive SDI [for cracking] of the wing top skin panel 1 and 2 between STG2 and STG10 at Rib 2 [and repair if needed], as described in Airbus SB A310-57-2096 Revision 02. Since EASA AD 2014-0200R1 was issued, a Widespread Fatigue Damage (WFD) analysis concluded that the inspection programme had to be extended to include the wing top skin panels at Rib 3 attachments, and Airbus issued SB A310-57-2096 Revision 03 accordingly, to provide the necessary instructions. Consequently, EASA issued [EASA] AD 2016-0005 [which corresponds to FAA AD 2016- 23-01], retaining the requirements of EASA AD 2014-0200R1, which was superseded, and extending the inspection area to include Rib 3. In addition to changes to the inspected area, WFD analysis identified structural modification points for certain fastener holes, located at each attachment from STG2 to STG10, at Ribs 2 and 3 on both wings. Airbus developed modification (mod) 13785 and mod 13786, consisting of an SDI, followed by an oversize of the defined holes on Ribs 2 and 3 on both wings. Airbus issued SB A310-57-2106 and SB A310-57-2107 to provide in-service modification instructions for top skin attachments to Rib 2 and Rib 3 respectively. Accomplishment of these modifications at the specified time will reset the fatigue life of the attachment holes at the top skin attachment to Rib 2 and Rib 3 to the Limit of Validity (LOV). Airbus issued inspection SB A310-57-2096 Revision 04 to account for the inspection requirements post-modification. For the reasons describe above, this [EASA] AD retains the requirements of EASA AD 2016-0005, which is superseded, requires modifications to the top skin attachment holes at Rib 2 and Rib 3, and defines the inspection requirements for Rib 2 and Rib 3 after modification. Modification of the fastener holes at top skin ribs 2 and 3 constitutes terminating action for certain repetitive special detailed inspections. 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-2018-0071. [[Page 22364]] Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. FedEx supported the NPRM. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting this AD as proposed, except for minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. Related Service Information Under 1 CFR Part 51 Airbus has issued the following service information. Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016. 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. Airbus Service Bulletin A310-57-2106, dated November 14, 2016. This service information describes procedures for a special detailed inspection and modification of the fastener holes of wing top skin panels 1 and 2, at rib 2. Airbus Service Bulletin A310-57-2107, dated November 14, 2016. This service information describes procedures for a special detailed inspection and modification of the fastener holes of wing top skin panels 1 and 2, at rib 3. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Costs of Compliance We estimate that this AD affects 8 airplanes of U.S. registry. The actions required by AD 2016-23-01, and retained in this AD, take about 8 work-hours per product, at an average labor rate of $85 per work-hour. Based on these figures, the estimated cost of the actions that are required by AD 2016-23-01 on U.S. operators to be $5,440, or $680 per product. We also estimate that it takes about 95 work-hours per product to comply with the basic requirements of this AD. Required parts will cost about $10,200 per product. 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 $146,200, or $18,275 per product. In addition, we estimate that any necessary modification will take about 40 work-hours and require parts costing $10,000, for a cost of $13,400 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. This AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: 1. Is not a ``significant regulatory action'' under Executive Order 12866; 2. Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD) 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016), and adding the following new AD: 2018-10-05 Airbus: Amendment 39-19280; FAA-2018-0071; Product Identifier 2017-NM-063-AD. (a) Effective Date This AD is effective June 19, 2018. (b) Affected ADs This AD replaces AD 2016-23-01, Amendment 39-18708 (81 FR 78899, November 10, 2016) (``AD 2016-23-01''). (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 an evaluation by the design approval holder (DAH) indicating that the wing top skin panel fastener holes at ribs 2 and 3 are subject to widespread fatigue damage (WFD). 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Retained Repetitive Inspections, With Revised Service Information This paragraph restates the requirements of paragraph (g) of AD 2016-23-01, with revised service information. Except as required by paragraph (i) of this AD: Within [[Page 22365]] 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, or Revision 04, dated December 5, 2016; except as provided by paragraph (j) of this AD. As of the effective date of this AD, use only Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to accomplish the required actions. (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 on the left- and right-hand sides of the fuselage. (h) Retained Compliance Times for Airplanes Not Previously Inspected, With No Changes This paragraph restates the requirements of paragraph (h) of AD 2016-23-01, with no changes. (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 December 15, 2016 (the effective date of AD 2016-23-01). (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 December 15, 2016 (the effective date of AD 2016-23-01). (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 December 15, 2016 (the effective date of AD 2016-23-01). (i) Retained Compliance Times for Airplanes Previously Inspected, With Revised Service Information This paragraph restates the requirements of paragraph (i) of AD 2016-23-01, with revised service information. For airplanes previously inspected before December 15, 2016 (the effective date of AD 2016-23-01), 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) 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, or Revision 04, dated December 5, 2016. As of the effective date of this AD, use only Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016, to accomplish the required actions. 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) Retained Compliance Times if No Ultrasonic Equipment Is Available, With Revised Service Information This paragraph restates the requirements of paragraph (j) of AD 2016-23-01, with revised service information. 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 December 15, 2016 (the effective date of AD 2016-23-01), using the service information identified in paragraph (j)(2)(i), (j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) 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 December 15, 2016 (the effective date of AD 2016-23-01), using the service information identified in paragraph (j)(2)(i), (j)(2)(ii), (j)(2)(iii), or (j)(2)(iv) 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. (iv) Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015. (k) Retained Repair of Cracking, With No Changes This paragraph restates the requirements of paragraph (k) of AD 2016-23-01, with no changes. 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 Section, Transport Standards Branch, FAA; or the European Aviation Safety Agency (EASA); or Airbus's EASA Design Organization Approval (DOA). If approved by the DOA, the approval must include the DOA-authorized signature. 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) Retained Definition of AFT, With No Changes This paragraph restates the requirements of paragraph (l) of AD 2016-23-01, with no changes. 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. [[Page 22366]] (m) New Requirements of This AD: Rib 2 Inspection and Modification At the compliance time specified in paragraph (n) of this AD, as applicable, accomplish the actions specified in paragraphs (m)(1) and (m)(2) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2106, dated November 14, 2016. (1) Accomplish a special detailed inspection to determine the diameter of the fastener holes in the wing top skin panels 1 and 2, at rib 2 of both wings. (2) Modify the fastener holes. (n) New Compliance Times for Rib 2 Inspection and Modification (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(1)(i) and (n)(1)(ii) of this AD. (i) Prior to the accumulation of 40,000 flight cycles or 93,300 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 AFT of less than 4 hours: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(2)(i) and (n)(2)(ii) of this AD. (i) Prior to the accumulation of 40,000 flight cycles or 116,000 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 4 hours or more: Do the actions required by paragraphs (m)(1) and (m)(2) of this AD at the later of the times specified in paragraphs (n)(3)(i) and (n)(3)(ii) of this AD. (i) Prior to the accumulation of 30,000 flight cycles or 150,000 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (o) New Requirements of This AD: Rib 3 Inspection and Modification At the compliance time specified in paragraph (p) of this AD, as applicable, accomplish the actions specified in paragraphs (o)(1) and (o)(2) of this AD concurrently and in sequence, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A310-57-2107, dated November 14, 2016. (1) Accomplish a special detailed inspection to determine the diameter of the fastener holes in the wing top skin panels 1 and 2, at rib 3 of both wings. (2) Modify the fastener holes. (p) New Compliance Times for Rib 3 Inspection and Modification (1) For Model A310-203, -204, -221, and -222 airplanes: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(1)(i) and (p)(1)(ii) of this AD. (i) Prior to the accumulation of 46,400 flight cycles or 92,900 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 AFT of less than 4 hours: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(2)(i) and (p)(2)(ii) of this AD. (i) Prior to the accumulation of 45,400 flight cycles or 127,300 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 4 hours or more: Do the actions required by paragraphs (o)(1) and (o)(2) of this AD at the later of the times specified in paragraphs (p)(3)(i) and (p)(3)(ii) of this AD. (i) Prior to the accumulation of 33,800 flight cycles or 169,000 flight hours since first flight of the airplane, whichever occurs first. (ii) Within 30 days after the effective date of this AD. (q) New Corrective Actions If any cracking is found during any inspection required by paragraph (m), (n), (o), or (p) of this AD, before further flight, repair the cracking using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. 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. (r) New Terminating Actions (1) Accomplishment of the modification specified in paragraph (m) of this AD constitutes terminating action for the repetitive special detailed inspections required by paragraph (g)(2) of this AD for the modified fastener holes at top skin rib 2 for that airplane. After modification, the un-modified fastener holes at top skin rib 2 between the front and rear spars remain subject to the repetitive inspections required by paragraph (g)(1) of this AD. (2) Accomplishment of the modification specified in paragraph (o) of this AD constitutes terminating action for the repetitive special detailed inspections required by paragraph (g)(2) of this AD for the modified fastener holes at top skin rib 3 for that airplane. After modification, the un-modified fastener holes at top skin rib 3 between the front and rear spars remain subject to the repetitive inspection required by paragraph (g)(1) of this AD. (s) Other FAA AD Provisions (1) Alternative Methods of Compliance (AMOCs): The Manager, International Section, Transport Standards Branch, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Section, send it to the attention of the person identified in paragraph (t)(2) of this AD. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (2) Contacting the Manufacturer: As of the effective date of this AD, for any requirement in this AD to obtain corrective actions from a manufacturer, the action must be accomplished using a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature. (3) Required for Compliance (RC): 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. (t) Related Information (1) Refer to Mandatory Continuing Airworthiness Information (MCAI) EASA AD 2017-0081, dated May 8, 2017, 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-2018-0071. (2) For more information about this AD, contact Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3225. (u) 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 June 19, 2018. (i) Airbus Service Bulletin A310-57-2096, Revision 04, dated December 5, 2016. (ii) Airbus Service Bulletin A310-57-2106, dated November 14, 2016. (iii) Airbus Service Bulletin A310-57-2107, dated November 14, 2016. (4) The following service information was approved for IBR on December 15, 2016 (81 FR 78899, November 10, 2016). (i) Airbus Service Bulletin A310-57-2096, Revision 03, dated June 30, 2015. [[Page 22367]] (ii) Reserved. (5) 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: account.airworth-eas@airbus.com; internet: http://www.airbus.com. (6) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (7) 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 Des Moines, Washington, on May 7, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-10214 Filed 5-14-18; 8:45 am] BILLING CODE 4910-13-P
![22362 Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
PART 39—AIRWORTHINESS 2017, specifies contacting Boeing, and or inspection program without obtaining
DIRECTIVES specifies that action as RC: This AD requires approval of an AMOC, provided the RC steps,
repair using a method approved in including substeps and identified figures, can
■ 1. The authority citation for part 39 accordance with the procedures specified in still be done as specified, and the airplane
continues to read as follows: paragraph (j) of this AD. can be put back in an airworthy condition.
(3) Where the Condition column of Table
Authority: 49 U.S.C. 106(g), 40113, 44701. 3 in paragraph 1.E., ‘‘Compliance,’’ of Boeing (k) Related Information
Special Attention Service Bulletin 747–35– For more information about this AD,
§ 39.13 [Amended] contact Susan L. Monroe, Aerospace
2134, dated November 22, 2017, specifies
■ 2. The FAA amends § 39.13 by adding ‘‘all airplanes,’’ for this AD, the Condition Engineer, Cabin Safety and Environmental
the following new airworthiness column of Table 3 is ‘‘airplanes on which one Systems Section, FAA, Seattle ACO Branch,
directive (AD): or more hose assemblies were replaced or 2200 South 216th St., Des Moines, WA
disconnected.’’ 98198; phone and fax: 206–231–3570; email:
2018–09–12 The Boeing Company: susan.l.monroe@faa.gov.
Amendment 39–19269; Docket No. (i) Parts Installation Prohibition
FAA–2018–0362; Product Identifier As of the effective date of this AD, no (l) Material Incorporated by Reference
2018–NM–020–AD. person may install, on any airplane, the hose (1) The Director of the Federal Register
(a) Effective Date assembly part numbers identified as approved the incorporation by reference
‘‘Removed hose assembly part numbers’’ in (IBR) of the service information listed in this
This AD is effective May 30, 2018. paragraph under 5 U.S.C. 552(a) and 1 CFR
Table 3, ‘‘Hose Assembly Replacement,’’ of
(b) Affected ADs Boeing Special Attention Service Bulletin part 51.
747–35–2134, dated November 22, 2017, in (2) You must use this service information
None.
the locations for hose assembly installation as applicable to do the actions required by
(c) Applicability as identified in Figures 1 through 14 of this AD, unless the AD specifies otherwise.
This AD applies to The Boeing Company Boeing Special Attention Service Bulletin (i) Boeing Special Attention Service
Model 747–200B, 747–300, and 747–400 747–35–2134, dated November 22, 2017. Bulletin 747–35–2134, dated November 22,
series airplanes, certificated in any category, 2017.
(j) Alternative Methods of Compliance (ii) Reserved.
as identified in Boeing Special Attention (AMOCs)
Service Bulletin 747–35–2134, dated (3) For service information identified in
November 22, 2017. (1) The Manager, Seattle ACO Branch, this AD, contact Boeing Commercial
FAA, has the authority to approve AMOCs Airplanes, Attention: Contractual & Data
(d) Subject for this AD, if requested using the procedures Services (C&DS), 2600 Westminster Blvd.,
Air Transport Association (ATA) of found in 14 CFR 39.19. In accordance with MC 110–SK57, Seal Beach, CA 90740–5600;
America Code 35, Oxygen. 14 CFR 39.19, send your request to your telephone 562–797–1717; internet https://
principal inspector or local Flight Standards www.myboeingfleet.com.
(e) Unsafe Condition District Office, as appropriate. If sending (4) You may view this service information
This AD was prompted by reports of low- information directly to the manager of the at the FAA, Transport Standards Branch,
pressure flex-hoses of the flightcrew oxygen certification office, send it to the attention of 2200 South 216th St., Des Moines, WA. For
system that burned through due to the person identified in paragraph (k) of this information on the availability of this
inadvertent electrical current from a short AD. Information may be emailed to: 9-ANM- material at the FAA, call 206–231–3195.
circuit. We are issuing this AD to prevent Seattle-ACO-AMOC-Requests@faa.gov. (5) You may view this service information
electrical current from passing through the (2) Before using any approved AMOC, that is incorporated by reference at the
low-pressure oxygen flex-hoses in the notify your appropriate principal inspector, National Archives and Records
gaseous passenger oxygen system, which can or lacking a principal inspector, the manager Administration (NARA). For information on
cause the flex-hoses to melt or burn, and a of the local flight standards district office/ the availability of this material at NARA, call
consequent oxygen-fed fire in the passenger certificate holding district office. 202–741–6030, or go to: http://
cabin. (3) An AMOC that provides an acceptable www.archives.gov/federal-register/cfr/ibr-
(f) Compliance level of safety may be used for any repair, locations.html.
modification, or alteration required by this
Comply with this AD within the Issued in Des Moines, Washington, on
AD if it is approved by the Boeing
compliance times specified, unless already April 27, 2018.
Commercial Airplanes Organization
done. Michael Kaszycki,
Designation Authorization (ODA) that has
(g) Required Actions been authorized by the Manager, Seattle ACO Acting Director, System Oversight Division,
Branch, to make those findings. To be Aircraft Certification Service.
Except as required by paragraph (h) of this
AD: At the applicable times specified in approved, the repair method, modification [FR Doc. 2018–09865 Filed 5–14–18; 8:45 am]
paragraph 1.E., ‘‘Compliance,’’ of Boeing deviation, or alteration deviation must meet BILLING CODE 4910–13–P
Special Attention Service Bulletin 747–35– the certification basis of the airplane, and the
2134, dated November 22, 2017, do all approval must specifically refer to this AD.
applicable actions identified as ‘‘RC’’ (4) Except as required by paragraph (h)(2)
DEPARTMENT OF TRANSPORTATION
(required for compliance) in, and in of this AD: For service information that
accordance with, the Accomplishment contains steps that are labeled as Required
Federal Aviation Administration
Instructions of Boeing Special Attention for Compliance (RC), the provisions of
Service Bulletin 747–35–2134, dated paragraphs (j)(4)(i) and (j)(4)(ii) of this AD
apply. 14 CFR Part 39
November 22, 2017.
(i) The steps labeled as RC, including [Docket No. FAA–2018–0071; Product
(h) Exception to Service Information substeps under an RC step and any figures Identifier 2017–NM–063–AD; Amendment
Specifications identified in an RC step, must be done to 39–19280; AD 2018–10–05]
(1) For purposes of determining comply with the AD. If a step or substep is
compliance with the requirements of this AD: labeled ‘‘RC Exempt,’’ then the RC RIN 2120–AA64
daltland on DSKBBV9HB2PROD with RULES
Where Boeing Special Attention Service requirement is removed from that step or
Bulletin 747–35–2134, dated November 22, substep. An AMOC is required for any Airworthiness Directives; Airbus
2017, uses the phrase ‘‘the original issue date deviations to RC steps, including substeps Airplanes
of this service bulletin,’’ this AD requires and identified figures.
using ‘‘the effective date of this AD.’’ (ii) Steps not labeled as RC may be AGENCY: Federal Aviation
(2) Where Boeing Special Attention Service deviated from using accepted methods in Administration (FAA), Department of
Bulletin 747–35–2134, dated November 22, accordance with the operator’s maintenance Transportation (DOT).
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![Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22363
ACTION: Final rule. is Docket Management Facility, U.S. cracks in the wing top skin panels 1 and 2
Department of Transportation, Docket along Rib 2 are detected on time and repaired
SUMMARY: We are superseding Operations, M–30, West Building appropriately. Consequently, EASA issued
Airworthiness Directive (AD) 2016–23– Ground Floor, Room W12–140, 1200 AD 2008–0211 [which corresponds to FAA
01, which applied to all Airbus Model AD 2010–04–03, Amendment 39–16196 (75
New Jersey Avenue SE, Washington, DC FR 6852, February 12, 2010) (‘‘AD 2010–04–
A310 series airplanes. AD 2016–23–01 20590.
required repetitive detailed inspections 03)] to require implementation of that
FOR FURTHER INFORMATION CONTACT: Dan inspection programme.
for cracking around the fastener holes in
Rodina, Aerospace Engineer, After that [EASA] AD was issued, Airbus
certain areas of the wing top skin improved the inspection programme, revising
panels, supplemental repetitive International Section, Transport
Standards Branch, FAA, 2200 South SB A310–57–2096 accordingly, to include a
ultrasonic inspections for cracking special detailed inspection (SDI), using an
around the fastener holes in certain 216th St., Des Moines, WA 98198;
ultrasonic method, to allow earlier crack
other areas of the wing top skin panels, telephone and fax: 206–231–3225.
detection, to subsequently reduce the scope
and repair if necessary. This AD adds an SUPPLEMENTARY INFORMATION: of potential repair action, and to extend the
inspection and modification of the Discussion intervals of the repetitive inspections.
fastener holes of the wing top skin Consequently, EASA issued AD 2014–0200
panels at a certain area. This AD also We issued a notice of proposed (later revised), retaining the requirements of
includes terminating action for certain rulemaking (NPRM) to amend 14 CFR EASA AD 2008–0211, which was
inspections. This AD was prompted by part 39 to supersede AD 2016–23–01, superseded, and required supplementary
Amendment 39–18708 (81 FR 78899, repetitive SDI [for cracking] of the wing top
an evaluation by the design approval skin panel 1 and 2 between STG2 and STG10
holder (DAH) which indicates that the November 10, 2016) (‘‘AD 2016–23–
01’’). AD 2016–23–01 applied to all at Rib 2 [and repair if needed], as described
wing top skin panel fastener holes at a in Airbus SB A310–57–2096 Revision 02.
certain area are also subject to Airbus Model A310 series airplanes. Since EASA AD 2014–0200R1 was issued,
widespread fatigue damage (WFD). We The NPRM published in the Federal a Widespread Fatigue Damage (WFD)
are issuing this AD to address the unsafe Register on February 8, 2018 (83 FR analysis concluded that the inspection
condition on these products. 5579). The NPRM was prompted by an programme had to be extended to include the
evaluation done by the DAH which wing top skin panels at Rib 3 attachments,
DATES: This AD is effective June 19,
2018. indicates that the wing top skin panel and Airbus issued SB A310–57–2096
fastener holes at a certain area are Revision 03 accordingly, to provide the
The Director of the Federal Register necessary instructions. Consequently, EASA
approved the incorporation by reference subject to WFD. The NPRM would
continue to require repetitive detailed issued [EASA] AD 2016–0005 [which
of certain publications listed in this AD corresponds to FAA AD 2016–23–01],
as of June 19, 2018. inspections for cracking around the retaining the requirements of EASA AD
The Director of the Federal Register fastener holes in certain areas of the 2014–0200R1, which was superseded, and
approved the incorporation by reference wing top skin panels, supplemental extending the inspection area to include
of a certain other publication listed in repetitive ultrasonic inspections for Rib 3.
this AD as of December 15, 2016 (81 FR cracking around the fastener holes in In addition to changes to the inspected
78899, November 10, 2016). certain other areas of the wing top skin area, WFD analysis identified structural
panels, and repair if necessary. The modification points for certain fastener holes,
ADDRESSES: For service information
NPRM proposed to add an inspection located at each attachment from STG2 to
identified in this final rule, contact STG10, at Ribs 2 and 3 on both wings.
Airbus SAS, Airworthiness Office— and modification of the fastener holes of
Airbus developed modification (mod)
EAW, 1 Rond Point Maurice Bellonte, the wing top skin panels at a certain 13785 and mod 13786, consisting of an SDI,
31707 Blagnac Cedex, France; area. The NPRM also includes followed by an oversize of the defined holes
telephone: +33 5 61 93 36 96; fax: +33 terminating action for certain on Ribs 2 and 3 on both wings. Airbus issued
5 61 93 44 51; email: account.airworth- inspections. We are issuing this AD to SB A310–57–2106 and SB A310–57–2107 to
eas@airbus.com; internet: http:// detect and correct fatigue cracking provide in-service modification instructions
www.airbus.com. You may view this around the fastener holes, which could for top skin attachments to Rib 2 and Rib 3
result in reduced structural integrity of respectively. Accomplishment of these
referenced service information at the modifications at the specified time will reset
FAA, Transport Standards Branch, 2200 the airplane.
The European Aviation Safety Agency the fatigue life of the attachment holes at the
South 216th St., Des Moines, WA. For top skin attachment to Rib 2 and Rib 3 to the
information on the availability of this (EASA), which is the Technical Agent
Limit of Validity (LOV). Airbus issued
material at the FAA, call 206–231–3195. for the Member States of the European inspection SB A310–57–2096 Revision 04 to
It is also available on the internet at Union, has issued EASA AD 2017–0081, account for the inspection requirements post-
http://www.regulations.gov by searching dated May 8, 2017 (referred to after this modification.
for and locating Docket No. FAA–2018– as the Mandatory Continuing For the reasons describe above, this
0071. Airworthiness Information, or ‘‘the [EASA] AD retains the requirements of EASA
MCAI’’), to correct an unsafe condition AD 2016–0005, which is superseded,
Examining the AD Docket for all Airbus Model A310 series requires modifications to the top skin
airplanes. The MCAI states: attachment holes at Rib 2 and Rib 3, and
You may examine the AD docket on defines the inspection requirements for Rib 2
the internet at http:// Following scheduled maintenance, cracks and Rib 3 after modification.
www.regulations.gov by searching for were found around the wing top skin panels
and locating Docket No. FAA–2018– fastener holes at Rib 2, between Stringer Modification of the fastener holes at
0071; or in person at the Docket (STG) 2 and STG14. top skin ribs 2 and 3 constitutes
Management Facility between 9 a.m. This condition, if not detected and terminating action for certain repetitive
daltland on DSKBBV9HB2PROD with RULES
and 5 p.m., Monday through Friday, corrected, could reduce the structural special detailed inspections. You may
integrity of the aeroplane.
except Federal holidays. The AD docket To address this issue, Airbus developed an
examine the MCAI in the AD docket on
contains this AD, the regulatory inspection programme, and published the internet at http://
evaluation, any comments received, and Service Bulletin (SB) A310–57–2096, www.regulations.gov by searching for
other information. The address for the providing instructions for repetitive detailed and locating Docket No. FAA–2018–
Docket Office (telephone 800–647–5527) inspections (DET) to ensure that any visible 0071.
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![22364 Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations
Comments $85 per work-hour. Based on these 4. Will not have a significant
We gave the public the opportunity to figures, we estimate the cost of this AD economic impact, positive or negative,
participate in developing this AD. We on U.S. operators to be $146,200, or on a substantial number of small entities
considered the comment received. $18,275 per product. under the criteria of the Regulatory
FedEx supported the NPRM. In addition, we estimate that any Flexibility Act.
necessary modification will take about
Conclusion List of Subjects in 14 CFR Part 39
40 work-hours and require parts costing
We reviewed the available data, $10,000, for a cost of $13,400 per Air transportation, Aircraft, Aviation
including the comment received, and product. We have no way of safety, Incorporation by reference,
determined that air safety and the determining the number of aircraft that Safety.
public interest require adopting this AD might need these actions. Adoption of the Amendment
as proposed, except for minor editorial Authority for This Rulemaking Accordingly, under the authority
changes. We have determined that these
Title 49 of the United States Code delegated to me by the Administrator,
minor changes:
specifies the FAA’s authority to issue the FAA amends 14 CFR part 39 as
• Are consistent with the intent that
rules on aviation safety. Subtitle I, follows:
was proposed in the NPRM for
correcting the unsafe condition; and section 106, describes the authority of
PART 39—AIRWORTHINESS
• Do not add any additional burden the FAA Administrator. Subtitle VII:
DIRECTIVES
upon the public than was already Aviation Programs, describes in more
proposed in the NPRM. detail the scope of the Agency’s ■ 1. The authority citation for part 39
authority. continues to read as follows:
Related Service Information Under We are issuing this rulemaking under
1 CFR Part 51 the authority described in Subtitle VII, Authority: 49 U.S.C. 106(g), 40113, 44701.
Airbus has issued the following Part A, Subpart III, Section 44701: § 39.13 [Amended]
service information. ‘‘General requirements.’’ Under that
• Airbus Service Bulletin A310–57– section, Congress charges the FAA with ■ 2. The FAA amends § 39.13 by
2096, Revision 04, dated December 5, promoting safe flight of civil aircraft in removing Airworthiness Directive (AD)
2016. This service information describes air commerce by prescribing regulations 2016–23–01, Amendment 39–18708 (81
procedures for detailed and ultrasonic for practices, methods, and procedures FR 78899, November 10, 2016), and
inspections for cracking around the the Administrator finds necessary for adding the following new AD:
fastener holes of wing top skin panels 1 safety in air commerce. This regulation 2018–10–05 Airbus: Amendment 39–19280;
and 2, at ribs 2 and 3, on the left- and is within the scope of that authority FAA–2018–0071; Product Identifier
right-hand sides of the fuselage. because it addresses an unsafe condition 2017–NM–063–AD.
• Airbus Service Bulletin A310–57– that is likely to exist or develop on (a) Effective Date
2106, dated November 14, 2016. This products identified in this rulemaking This AD is effective June 19, 2018.
service information describes action.
procedures for a special detailed This AD is issued in accordance with (b) Affected ADs
inspection and modification of the authority delegated by the Executive This AD replaces AD 2016–23–01,
fastener holes of wing top skin panels 1 Director, Aircraft Certification Service, Amendment 39–18708 (81 FR 78899,
and 2, at rib 2. as authorized by FAA Order 8000.51C. November 10, 2016) (‘‘AD 2016–23–01’’).
• Airbus Service Bulletin A310–57– In accordance with that order, issuance (c) Applicability
2107, dated November 14, 2016. This of ADs is normally a function of the This AD applies to all Airbus Model A310–
service information describes Compliance and Airworthiness 203, –204, –221, –222, –304, –322, –324, and
procedures for a special detailed Division, but during this transition –325 airplanes, certificated in any category,
inspection and modification of the period, the Executive Director has all manufacturer serial numbers.
fastener holes of wing top skin panels 1 delegated the authority to issue ADs (d) Subject
and 2, at rib 3. applicable to transport category
Air Transport Association (ATA) of
This service information is reasonably airplanes to the Director of the System America Code 57, Wings.
available because the interested parties Oversight Division.
have access to it through their normal (e) Reason
course of business or by the means Regulatory Findings This AD was prompted by an evaluation by
identified in the ADDRESSES section. We determined that this AD will not the design approval holder (DAH) indicating
have federalism implications under that the wing top skin panel fastener holes
Costs of Compliance Executive Order 13132. This AD will at ribs 2 and 3 are subject to widespread
We estimate that this AD affects 8 not have a substantial direct effect on fatigue damage (WFD). We are issuing this
airplanes of U.S. registry. AD to detect and correct fatigue cracking
the States, on the relationship between
The actions required by AD 2016–23– around the fastener holes, which could result
the national government and the States, in reduced structural integrity of the
01, and retained in this AD, take about or on the distribution of power and airplane.
8 work-hours per product, at an average responsibilities among the various
labor rate of $85 per work-hour. Based levels of government. (f) Compliance
on these figures, the estimated cost of For the reasons discussed above, I Comply with this AD within the
the actions that are required by AD certify that this AD: compliance times specified, unless already
done.
daltland on DSKBBV9HB2PROD with RULES
2016–23–01 on U.S. operators to be 1. Is not a ‘‘significant regulatory
$5,440, or $680 per product. action’’ under Executive Order 12866; (g) Retained Repetitive Inspections, With
We also estimate that it takes about 95 2. Is not a ‘‘significant rule’’ under the Revised Service Information
work-hours per product to comply with DOT Regulatory Policies and Procedures This paragraph restates the requirements of
the basic requirements of this AD. (44 FR 11034, February 26, 1979); paragraph (g) of AD 2016–23–01, with
Required parts will cost about $10,200 3. Will not affect intrastate aviation in revised service information. Except as
per product. The average labor rate is Alaska; and required by paragraph (i) of this AD: Within
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![Federal Register / Vol. 83, No. 94 / Tuesday, May 15, 2018 / Rules and Regulations 22367
(ii) Reserved. Program provides a statutory death law enforcement officers; a prosecutor
(5) For service information identified in benefit to certain survivors of public and former claims attorney, and two
this AD, contact Airbus SAS, Airworthiness safety officers who are fatally injured in members of Congress. OJP received
Office—EAW, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
the line of duty, disability benefits to input from a total of 7 commenters on
telephone: +33 5 61 93 36 96; fax: +33 5 61 public safety officers catastrophically the first proposed rule, and 8
93 44 51; email: account.airworth-eas@ injured in the line of duty, and commenters on the second rule.
airbus.com; internet: http://www.airbus.com. education benefits to certain of the After careful consideration and
(6) You may view this service information survivors and family members of the analysis of all comments received, OJP
at the FAA, Transport Standards Branch, foregoing public safety officers. Under has made amendments that are
2200 South 216th St., Des Moines, WA. For the Program, claims are filed with, and incorporated into this consolidated final
information on the availability of this
adjudicated by, the Office of Justice rule. The final rule also contains a few
material at the FAA, call 206–231–3195.
(7) You may view this service information Programs (OJP) of the U.S. Department clarifying changes to provisions in the
that is incorporated by reference at the of Justice. The regulations for the PSOB proposed rule where there were some
National Archives and Records Program are codified at 28 CFR part 32. previously unnoticed ambiguities, or
Administration (NARA). For information on where the language was more complex
the availability of this material at NARA, call I. Executive Summary
than necessary. A summary overview of
202–741–6030, or go to: http:// A. Purpose of the Regulatory Action the changes made by the final rule
www.archives.gov/federal-register/cfr/ibr- follows below, with a more complete
locations.html. OJP published two proposed rules for
the PSOB Program, one on July 15, discussion (below that) of the provisions
Issued in Des Moines, Washington, on May of the rule, the public comments
7, 2018.
2016, 81 FR 46019 (‘‘PSOB I’’), and the
other on August 22, 2016, 81 FR 57348 received on the proposed rule, the
Michael Kaszycki, Department’s response, and the final
(‘‘PSOB II’’). PSOB I primarily focused
Acting Director, System Oversight Division, changes incorporated into the final rule.
on certain changes needed to implement
Aircraft Certification Service. Pursuant to 34 U.S.C. 10287, this final
statutory changes made by the Dale
[FR Doc. 2018–10214 Filed 5–14–18; 8:45 am]
Long Act (affecting members of rescue rule is intended (insofar as consistent
BILLING CODE 4910–13–P
squad and ambulance crews, as well as with law) to be effective and applicable
provisions related to certain heart to all claims from and after the effective
attack/stroke/vascular rupture cases), date hereof, whether pending (in any
DEPARTMENT OF JUSTICE and also to align the workings of the stage) as of that date or subsequently
PSOB Program with certain provisions filed.
28 CFR Part 32 under the World Trade Center (WTC) B. Summary of the Major Changes in the
[Docket No.: OJP (BJA) 1722] Health Program, as well as with the Final Rule
RIN 1121–AA85
September 11th Victim Compensation
Fund (VCF). PSOB II was to implement The final rule makes the following
recent statutory changes, address some conforming changes required by the
Public Safety Officers’ Benefits
gaps in the regulations, and to improve Dale Long Public Safety Officers’
Program
the efficiency of the PSOB Program Benefits Improvement Act of 2012 (Dale
AGENCY: Office of Justice Programs, claims process. Long Act), Public Law 112–239, which,
Department of Justice. During the comment periods, OJP among other things, added (as codified
ACTION: Final rule. received comments on its proposed at 34 U.S.C. 10282(9)(D)) as a new
rules from various parties. After further category of public safety officer—‘‘a
SUMMARY: This final rule finalizes two review of the proposed rules and careful member of a rescue squad or ambulance
proposed rules in order to update and consideration and analysis of all crew who, as authorized or licensed by
improve the regulations of the Office of comments on both proposed rules, OJP law and by the applicable agency or
Justice Programs (OJP) implementing has made amendments that are entity, is engaging in rescue activity or
the Public Safety Officers’ Benefits incorporated into this final rule. In in the provision of emergency medical
(PSOB) Program, in order to incorporate addition, the final rule includes a services’’. The following changes
several statutory changes enacted in technical change necessitated by the implement the inclusion of the new
recent years, address some gaps in the newly-enacted provisions of the Public category of public safety officer by the
regulations, and improve the efficiency Safety Officers’ Benefits Improvement following revisions and additions to the
of the PSOB Program claims process. Act of 2017, Public Law 115–36, 131 PSOB regulations:
After careful consideration and analysis Stat. 841 (June 2, 2017). The final rule • Revise definition of Employed by a
of the public comments on both also includes (non-substantive) changes public agency;
proposed rules, the final rule to myriad cross-references to statutory • Revise definition of Line of duty
incorporates a number of changes as provisions, referred to in the activity or action to align with statutory
discussed below. regulations, that—effective September 1, inclusion of members of rescue squads
DATES: This rule is effective June 14, 2017—were reclassified by the Law and ambulance crews;
2018, except for amendatory Revision Counsel of the House of • Revise definition of Officially
instructions 10 (amending 28 CFR Representatives from title 42 of the U.S. recognized or designated public
32.12), 17 (amending 28 CFR 32.22), and Code to title 34 of the U.S. Code. employee member of a squad or crew;
32 (amending 28 CFR 32.53), which are During the comment period, OJP • Add a definition for Officially
effective June 14, 2020. received comments on its proposed recognized or designated volunteer
daltland on DSKBBV9HB2PROD with RULES
FOR FURTHER INFORMATION CONTACT: rules from a number of interested member of a squad or crew;
Hope Janke, Bureau of Justice parties: Various national police-, fire-, • Revise definition of Official training
Assistance; Telephone: (202) 514–6278, and rescue associations and unions; a program of public agency;
or toll-free at (888) 744–6513. foundation supporting 9/11 responders; • Remove definition of Public
SUPPLEMENTARY INFORMATION: The an organization that provides support employee member of a squad or crew,
Public Safety Officers’ Benefits (PSOB) and assistance to the survivors of fallen and
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Document Created: 2018-05-15 00:33:04
Document Modified: 2018-05-15 00:33:04
| 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 June 19, 2018. | |
| Contact | Dan Rodina, Aerospace Engineer, International Section, Transport Standards Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone and fax: 206-231-3225. | |
| FR Citation | 83 FR 22362 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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