82 FR 55958 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 226 (November 27, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 226 (November 27, 2017)
| Page Range | 55958-55963 | |
| FR Document | 2017-24502 |
[Federal Register Volume 82, Number 226 (Monday, November 27, 2017)] [Proposed Rules] [Pages 55958-55963] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-24502] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1421; Product Identifier 2014-NM-177-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. ----------------------------------------------------------------------- SUMMARY: We are revising an earlier proposal for certain The Boeing Company Model 767-300 and -300F [[Page 55959]] series airplanes. This action revises the notice of proposed rulemaking (NPRM) by adding new high frequency eddy current (HFEC) inspections for cracking of an expanded area of the lower outboard wing skin for certain airplanes. We are proposing this airworthiness directive (AD) to address the unsafe condition on these products. Since these actions would impose an additional burden over those in the NPRM, we are reopening the comment period to allow the public the chance to comment on these changes. DATES: The comment period for the NPRM published in the Federal Register on June 5, 2015 (80 FR 32066), is reopened. We must receive comments on this SNPRM by January 11, 2018. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. Hand Delivery: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this SNPRM, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; Internet https://www.aviationpartnersboeing.com. You may view this service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Examining the AD Docket You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015- 1421; 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 SNPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-1421; Product Identifier 2014-NM-177-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this SNPRM. We will consider all comments received by the closing date and may amend this SNPRM because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this SNPRM. Discussion We issued an NPRM to amend 14 CFR part 39 by adding an AD that would apply to certain The Boeing Company Model 767-300 and -300F series airplanes. The NPRM published in the Federal Register on June 5, 2015 (80 FR 32066). The NPRM was prompted by reports of fatigue cracking on airplanes with Aviation Partners Boeing winglets installed. The NPRM proposed to require an HFEC inspection for cracking of the lower outboard wing skin, and repair or modification if necessary. The NPRM also proposed to require one of three follow-on actions: repeating the HFEC inspections; modifying certain internal stringers and oversizing and plugging the existing fastener holes of the lower wing; or modifying the external doubler/tripler and doing repetitive post- modification inspections. Actions Since the NPRM Was Issued Since we issued the NPRM, we have determined that new HFEC inspections for cracking of an expanded area of the lower outboard wing skin are necessary to address the identified unsafe condition for certain airplanes. Aviation Partners Boeing (APB) has released Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017. In the NPRM, we refer to APB Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, as the appropriate source of service information for accomplishing the proposed actions. APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, corrects certain errors and omissions that were in the Accomplishment Instructions of APB Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, and provides clarification of certain procedures. APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, also removes all work related to stringer L-6.5 due to recent analysis that the modification was not sufficient to meet the 767 design service objective. In light of this analysis, new repetitive post-modification HFEC inspections have been added for airplanes on which the optional terminating modification of the existing skin or external skin doubler has been done. We have revised this proposed AD to refer to APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, for accomplishing proposed actions for stringer L-9.5. APB has also released Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. APB Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, includes procedures for inspections, repair (modification), and repair of stringer L-6.5 of the lower outboard wing skin (which replace the actions that were removed from APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017). Related Service Information Under 1 CFR Part 51 We reviewed APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. The service information describes procedures for an HFEC inspection for cracking of the external surface of the lower outboard wing skin at stringer L-9.5 and on-condition actions that include repetitive HFEC inspections; modification by oversizing and plugging the existing fastener holes of the wing skin; repair (modification) of the stringer with new stringer; repair (modification) of the stringer with external doubler/tripler; repetitive post-repair inspections for cracking; and repair. We also reviewed APB Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. The service information describes procedures for an HFEC inspection for cracking of the lower outboard wing skin at stringer L-6.5 and on-condition actions that include repetitive HFEC inspections; repair (modification) of the stringer with new stringer; repetitive post-repair [[Page 55960]] HFEC inspections for cracking; and repair. 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. Comments We gave the public the opportunity to participate in developing this proposed AD. We considered the comments received. Request To Clarify Service Information and Actions in the Proposed AD Multiple commenters (United Airlines, Delta Air Lines, American Airlines, Japan Airlines, FedEx, Boeing) requested that the actions specified in APB Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, be revised. Commenters noted that APB Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014, contained multiple errors. United Airlines, Delta Air Lines, American Airlines and Boeing also requested that the actions specified in the proposed AD be revised for clarity because certain language in the proposed AD did not match the language in APB Service Bulletin AP767-57-010, Revision 7, dated November 4, 2014. APB stated APB Service Bulletin AP767-57- 010, Revision 7, dated November 4, 2014, is being revised to include corrections and clarifications and additional work. APB recommend that we refer to updated service information. We acknowledge the commenters' request and have revised this SNPRM to refer to the updated service information in APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, and APB Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. Request To Allow Previously Approved Repairs American Airlines, APB, and Boeing requested that we give credit for repairs in the subject area that had received 8100-9 approval prior to the effective date of the AD. We agree to give credit for repairs that we have determined will address the identified unsafe condition. We replaced the content of paragraph (i) of the proposed AD (in the NPRM) with new content in this proposed AD to specify that repairs of the lower outboard wing skin done after June 15, 2017, and before the effective date of this AD, that are approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, are approved for the applicable repairs required by paragraphs (g) and (h) of this AD. Request To Allow Previous Modifications Air New Zealand requested that we give credit for accomplishing the proposed modification before the effective date of the AD by adding the required service information to paragraph (i) of the proposed AD, which specifies credit for previous actions. We acknowledge the comment. However, no change to this proposed AD is necessary. Operators who accomplish the actions required by an AD using the required service information before the effective date of an AD are in compliance with the AD. Paragraph (f) of this proposed AD states ``comply with this AD within the compliance times specified, unless already done.'' Credit for previous actions in ADs is used primarily to give credit for earlier revisions of required service information that are also acceptable for compliance if done before the effective date of the AD. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Certain changes described above expand the scope of the NPRM. As a result, we have determined that it is necessary to reopen the comment period to provide additional opportunity for the public to comment on this SNPRM. Proposed Requirements of This SNPRM This SNPRM would require accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed Rule and the Service Information.'' The compliance times vary depending on airplane configuration and inspection area. The shortest initial compliance time is the later of: 1,500 flight cycles or 7,500 flight hours after winglet installation, whichever occurs first; or 18 months after the effective date of the AD. Except for one group of airplanes, the longest initial compliance time is the later of: 7,800 flight cycles or 23,400 flight hours after installation of a certain modification, whichever occurs first; or 18 months after the effective date of the AD. For one group of airplanes, the longest initial compliance time is 29,000 total flight cycles or 111,000 total flight hours, whichever occurs first. The shortest repetitive interval is 1,500 flight cycles or 7,500 flight hours, whichever occurs first. The longest repetitive interval is 12,000 flight cycles or 36,000 flight hours, whichever occurs first. Differences Between Proposed Rule and Service Information APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, and APB Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, specify to contact the manufacturer for instructions on how to repair certain conditions, but this proposed AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes ODA whom we have authorized to make those findings. Table 5a of paragraph 1.E., ``Compliance,'' of APB Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, does not provide a grace period for airplanes that have exceeded a certain compliance time. We have added a grace period of 6 months to paragraph (g)(2) of this proposed AD. Costs of Compliance We estimate that this proposed AD affects 140 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: Estimated Costs--Required Actions ---------------------------------------------------------------------------------------------------------------- Cost per Cost on U.S. Action Labor cost Parts cost product operators ---------------------------------------------------------------------------------------------------------------- HFEC Inspections.................. 6 work-hours x $85 per $0 $510 $71,400 hour = $510. ---------------------------------------------------------------------------------------------------------------- [[Page 55961]] We estimate the following costs to do any necessary on-condition actions that would be required based on the results of the proposed inspection. We have no way of determining the number of aircraft that might need these on-condition actions. Estimated Costs--On-Condition Actions ---------------------------------------------------------------------------------------------------------------- Cost per Action Labor cost Parts cost product ---------------------------------------------------------------------------------------------------------------- Post-repair Inspections.................... 6 work-hours x $85 per hour = $510 $0 $510 per inspection cycle. Repair/Modification........................ 262 work-hours x 85 per hour = 0 22,270 22,270. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for on-condition repairs for the post-repair inspections specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ``Subtitle VII: Aviation Programs'' describes in more detail the scope of the Agency's authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): The Boeing Company: Docket No. FAA-2015-1421; Product Identifier 2014-NM-177-AD. (a) Comments Due Date We must receive comments by January 11, 2018. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 767-300 and -300F series airplanes, certificated in any category, with Aviation Partners Boeing winglets installed; as identified in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and Aviation Partners Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017. (d) Subject Air Transport Association (ATA) of America Code 57, Wings. (e) Unsafe Condition This AD was prompted by reports of fatigue cracking in the lower outboard wing skin at the inboard fastener of stringer L-9.5, and the lower outboard wing skin of stringer L-6.5, on airplanes with winglets installed per Supplemental Type Certificate ST01920SE. We are issuing this AD to prevent fatigue cracking in the lower outboard wing skin, which could result in failure and subsequent separation of the wing and winglet and consequent reduced controllability of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Stringer L-9.5 Inspections, Modification, Repair (Modification), Repetitive Post-Repair Inspections, and Repair (1) For Group 1 and Group 2 airplanes identified in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, except as required by paragraph (j)(1) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin at stringer L-9.5, in accordance with Part 1 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (i) For airplanes on which ``Condition 1'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, during any inspection required by paragraph (g)(1) or (g)(1)(i)(A) of this AD: Do the applicable actions required by paragraph (g)(1)(i)(A), (g)(1)(i)(B), (g)(1)(i)(C), or (g)(1)(i)(D) of this AD. (A) Repeat the inspection specified in paragraph (g)(1) of this AD thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017. (B) Do the applicable actions required by paragraphs (g)(1)(i)(B)(1), (g)(1)(i)(B)(2), and (g)(1)(i)(B)(3) of this AD. (1) Before further flight, do actions (modifications and repair (modification)) in [[Page 55962]] accordance with Part 2, Part 3, Part 4, and Part 5, as applicable, of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) For airplanes on which the repair (modification) specified in Part 5 of Aviation Partners Boeing Service Bulletin AP767-57-010 was done: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 12 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(i)(B)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (C) Do the actions required by paragraphs (g)(1)(i)(C)(1) and (g)(1)(i)(C)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(i)(C)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 9 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(i)(C)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (D) Do the actions required by paragraphs (g)(1)(i)(D)(1) and (g)(1)(i)(D)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(i)(D)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 11 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 13 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(i)(D)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (ii) For airplanes on which ``Condition 2'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, during any inspection required by paragraph (g)(1) or (g)(1)(i)(A) of this AD: Do the actions required by paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this AD. (A) Do the actions required by paragraphs (g)(1)(ii)(A)(1) and (g)(1)(ii)(A)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(ii)(A)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 9 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(ii)(A)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (B) Do the actions required by paragraphs (g)(1)(ii)(B)(1) and (g)(1)(ii)(B)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(ii)(B)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 11 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 13 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(ii)(B)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (iii) For airplanes on which ``Condition 3'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, during the actions specified in paragraph (g)(1)(i)(B)(1) of this AD: Do the actions required by paragraph (g)(1)(iii)(A) or (g)(1)(iii)(B) of this AD. (A) Do the actions required by paragraphs (g)(1)(iii)(A)(1) and (g)(1)(iii)(A)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(iii)(A)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 8 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 9 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(iii)(A)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (B) Do the actions required by paragraphs (g)(1)(iii)(B)(1) and (g)(1)(iii)(B)(2) of this AD, and do all applicable actions required by paragraph (g)(1)(iii)(B)(3) of this AD. (1) Before further flight, repair (modify) in accordance with Part 11 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (2) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-010, Revision 11, dated April 3, 2017, do a post-repair HFEC inspection for cracking, in accordance with Part 13 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017; and repeat the inspection thereafter at the applicable times specified in in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(iii)(B)(2) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (iv) For airplanes on which ``Condition 4'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, during any action specified in paragraph (g)(1)(i)(C)(1), (g)(1)(i)(D)(1), (g)(1)(ii)(A)(1), (g)(1)(ii)(B)(1), (g)(1)(iii)(A)(1), and (g)(1)(iii)(B)(1) of this AD: Repair before further flight using a method approved in accordance with the [[Page 55963]] procedures specified in paragraph (k) of this AD. (2) For Group 3 airplanes identified in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, or within 6 months after the effective date of this AD, whichever occurs later, do an HFEC inspection for cracking of the lower outboard wing skin at stringer L-9.5, in accordance with Part 7 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. Repeat the inspection thereafter at the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. If any cracking is found during any inspection, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. An approved repair terminates the repetitive inspections required by paragraph (g)(2) of this AD. (h) Repetitive Stringer L-6.5 Inspections, Repair (Modification), Repetitive Post-Repair Inspections, and Repair (1) For airplanes identified in Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017: At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, except as required by paragraph (j)(2) of this AD: Do an HFEC inspection for cracking of stringer L-6.5 of the lower outboard wing skin, in accordance with Part 1 of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. If no cracking is found, repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, except as provided by paragraph (h)(3) of this AD. (2) If any crack is found during any inspection required by paragraph (h)(1) of this AD, do the actions required by paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, and do all applicable actions required by paragraph (h)(2)(iii) of this AD. (i) Before further flight, repair (modify) stringer L-6.5, in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. (ii) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017, except as required by paragraph (j)(2) of this AD, do an HFEC post-repair inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 014, Revision 1, dated April 12, 2017, and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017. (iii) If any crack is found during any inspection required by paragraph (h)(2)(ii) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (3) As an option to the repetitive inspections required by paragraph (h)(1) of this AD, do the actions required by paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, and do all applicable actions required by paragraph (h)(3)(iii) of this AD. (i) Before further flight after accomplishing the most recent inspection required by paragraph (h)(1) of this AD, repair (modify) stringer L-6.5, in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 014, Revision 1, dated April 12, 2017. (ii) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017, except as required by paragraph (j)(2) of this AD, do a post-repair HFEC inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 014, Revision 1, dated April 12, 2017, and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-014, Revision 1, dated April 12, 2017. (iii) If any crack is found during any inspection required by paragraph (h)(3)(ii) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (k) of this AD. (i) Repair Approval Repairs of the lower outboard wing skin done after June 15, 2017, and before the effective date of this AD, that are approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, are approved for the applicable repairs required by paragraphs (g) and (h) of this AD. (j) Exceptions to Service Information Specifications (1) Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, specifies a compliance time of ``after the issue date of Revision 11 of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, specifies a compliance time of ``after the initial issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle ACO 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 manager of the certification office, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: [email protected]. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes ODA that has been authorized by the Manager, Seattle ACO Branch, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraphs (g)(1)(i)(B)(3), (g)(1)(i)(C)(3), (g)(1)(i)(D)(3), (g)(1)(ii)(A)(3), (g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3), (g)(1)(iii)(B)(3), (g)(1)(iv), (g)(2), (h)(2)(iii), and (h)(3)(iii) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (k)(4)(i) and (k)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled ``RC Exempt,'' then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled 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 RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425- 917-6450; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Aviation Partners Boeing, 2811 S. 102nd Street, Suite 200, Seattle, WA 98168; telephone 206-762-1171; Internet https://www.aviationpartnersboeing.com. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on November 3, 2017. Jeffrey E. Duven, Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017-24502 Filed 11-24-17; 8:45 am] BILLING CODE 4910-13-P
![55958 Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules
paragraph (g) of this AD: Within 24 months required by this paragraph, does not those procedures and tests must be done to
after the effective date of this AD, modify the constitute terminating action for the comply with this AD; any procedures or tests
repair using a method approved by the repetitive inspections required by paragraph that are not identified as RC are
Manager, International Section, Transport (g) of this AD for that airplane, as applicable, recommended. Those procedures and tests
Standards Branch FAA; or EASA; or Airbus’s unless specified otherwise in the that are not identified as RC may be deviated
EASA DOA. If approved by the DOA, the instructions. from using accepted methods in accordance
approval must include the DOA-authorized with the operator’s maintenance or
signature. (o) Terminating Action for ALI Tasks
inspection program without obtaining
(1) Accomplishment of an inspection as approval of an AMOC, provided the
(k) Optional Terminating Action for required by paragraph (g) of this AD or procedures and tests identified as RC can be
Airplanes Post-Modification 20416 or Post- instructions as required by paragraph (l) of done and the airplane can be put back in an
Modification 21999 this AD, as applicable, constitutes airworthy condition. Any substitutions or
Modification of an airplane post- terminating action for the inspection changes to procedures or tests identified as
modification 20416 or post-modification requirements of ALI task 531110, for that RC require approval of an AMOC.
21999 in accordance with the airplane.
Accomplishment Instructions of Airbus (2) Modification of the two upper rows of (s) Related Information
Service Bulletin A320–53–1295, including fasteners of the crossbeam splicing at FR16 (1) Refer to Mandatory Continuing
Appendixes 01 and 02, dated June 29, 2015, and FR20 on both LH and RH sides of an Airworthiness Information (MCAI) EASA
constitutes terminating action for the airplane, in accordance with the Airworthiness Directive 2016–0139, dated
repetitive inspections required by paragraph Accomplishment Instructions of Airbus July 14, 2016, for related information. This
(g) of this AD for that airplane. Service Bulletin A320–53–1295, including MCAI may be found in the AD docket on the
Appendixes 01 and 02, dated June 29, 2015, Internet at http://www.regulations.gov by
(l) Post-Repair Actions for Certain Airplanes as specified in paragraphs (k) and (m) of this searching for and locating Docket No. FAA–
For an airplane that has been inspected per AD, constitutes terminating action for the 2017–1093.
ALI task 531110 and repaired before the inspection requirements of ALI task 531110, (2) For more information about this AD,
effective date of this AD using the for those holes for that airplane. contact Sanjay Ralhan, Aerospace Engineer,
instructions in an Airbus Repair Design International Section, Transport Standards
Approval Sheet (RDAS): Within 30 days after (p) No Reporting Requirement
Branch, FAA, 1601 Lind Avenue SW.,
the effective date of this AD, contact the Although Airbus Service Bulletin A320– Renton, WA 98057–3356; telephone 425–
Manager, International Section, Transport 53–1286, Revision 01, dated December 22, 227–1405; fax 425–227–1149.
Standards Branch, FAA; or EASA; or 2015, specifies to submit certain information (3) For service information identified in
Airbus’s EASA DOA for instructions and to the manufacturer, and specifies that action this AD, contact Airbus, Airworthiness
accomplish those instructions accordingly. If as ‘‘RC’’ (Required for Compliance), this AD Office—EIAS, 1 Rond Point Maurice
approved by the DOA, the approval must does not include that requirement. Bellonte, 31707 Blagnac Cedex, France;
include the DOA-authorized signature. telephone +33 5 61 93 36 96; fax +33 5 61
(q) Credit for Previous Actions
Accomplishment of the instructions required 93 44 51; email account.airworth-eas@
by this paragraph, does not constitute This paragraph provides credit for actions
required by paragraph (g) and (h) of this AD, airbus.com; Internet http://www.airbus.com.
terminating action for the repetitive
if those actions were performed before the You may view this service information at the
inspections required by paragraph (g) of this
effective date of this AD using Airbus Service FAA, Transport Standards Branch, 1601 Lind
AD for that airplane, unless specified
Bulletin A320–53–1286, dated June 29, 2015. Avenue SW., Renton, WA. For information
otherwise in the instructions.
on the availability of this material at the
(m) Partial Terminating Action for Airplanes (r) Other FAA AD Provisions FAA, call 425–227–1221.
Post-Modification 20416 or Post- The following provisions also apply to this Issued in Renton, Washington, on
Modification 21999 AD: November 7, 2017.
For an airplane post-modification 20416 or (1) Alternative Methods of Compliance Dionne Palermo,
post-modification 21999, modification in (AMOCs): The Manager, International
Section, Transport Standards Branch, FAA, Acting Director, System Oversight Division,
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320– has the authority to approve AMOCs for this Aircraft Certification Service.
53–1295, including Appendixes 01 and 02, AD, if requested using the procedures found [FR Doc. 2017–25252 Filed 11–24–17; 8:45 am]
dated June 29, 2015, for the applicable in 14 CFR 39.19. In accordance with 14 CFR BILLING CODE 4910–13–P
fastener holes, where no damage or cracks 39.19, send your request to your principal
were detected (i.e., those not repaired) during inspector or local Flight Standards District
the latest inspection as required by paragraph Office, as appropriate. If sending information DEPARTMENT OF TRANSPORTATION
(g) of this AD, constitutes terminating action directly to the manager of the International
for the repetitive inspections of those fastener Section, send it to the attention of the person Federal Aviation Administration
holes as required by paragraph (g) of this AD identified in paragraph (s)(2) of this AD.
for that airplane. Information may be emailed to: 9-ANM-116-
AMOC-REQUESTS@faa.gov. Before using 14 CFR Part 39
(n) Actions for Airplanes With Certain any approved AMOC, notify your appropriate
Repairs [Docket No. FAA–2015–1421; Product
principal inspector, or lacking a principal
Identifier 2014–NM–177–AD]
For an airplane that has been repaired inspector, the manager of the local flight
before the effective date of this AD in the standards district office/certificate holding RIN 2120–AA64
areas described in this AD using the district office.
instructions in an Airbus RDAS unrelated to (2) Contacting the Manufacturer: For any Airworthiness Directives; The Boeing
ALI task 531110: Before exceeding the requirement in this AD to obtain corrective Company Airplanes
compliance times specified in table 1 to actions from a manufacturer, the action must
pmangrum on DSK3GDR082PROD with PROPOSALS1
paragraph (g) of this AD or table 2 to be accomplished using a method approved AGENCY: Federal Aviation
paragraph (g) of this AD, as applicable, by the Manager, International Section, Administration (FAA), DOT.
contact the Manager, International Section, Transport Standards Branch, FAA; or EASA;
Transport Standards Branch, FAA; or EASA; or Airbus’s EASA DOA. If approved by the ACTION: Supplemental notice of
or Airbus’s EASA DOA for corrective action DOA, the approval must include the DOA- proposed rulemaking (SNPRM);
instructions and accomplish those authorized signature. reopening of comment period.
instructions accordingly. If approved by the (3) Required for Compliance (RC): Except
DOA, the approval must include the DOA- as required by paragraphs (h)(1) and (p) of SUMMARY: We are revising an earlier
authorized signature. Accomplishment of this AD: If any service information contains proposal for certain The Boeing
corrective action(s) on an airplane, as procedures or tests that are identified as RC, Company Model 767–300 and –300F
VerDate Sep<11>2014 15:12 Nov 24, 2017 Jkt 244001 PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 E:\FR\FM\27NOP1.SGM 27NOP1](https://thefederalregister.org/doc/82_FR_56184/page/1.svg)
![Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules 55961
We estimate the following costs to do of the proposed inspection. We have no aircraft that might need these on-
any necessary on-condition actions that way of determining the number of condition actions.
would be required based on the results
ESTIMATED COSTS—ON-CONDITION ACTIONS
Cost per
Action Labor cost Parts cost product
Post-repair Inspections .................... 6 work-hours × $85 per hour = $510 per inspection cycle ....................... $0 $510
Repair/Modification .......................... 262 work-hours × 85 per hour = 22,270 ................................................... 0 22,270
We have received no definitive data For the reasons discussed above, I (d) Subject
that would enable us to provide cost certify this proposed regulation: Air Transport Association (ATA) of
estimates for on-condition repairs for (1) Is not a ‘‘significant regulatory America Code 57, Wings.
the post-repair inspections specified in action’’ under Executive Order 12866,
(e) Unsafe Condition
this proposed AD. (2) Is not a ‘‘significant rule’’ under
the DOT Regulatory Policies and This AD was prompted by reports of
Authority for This Rulemaking Procedures (44 FR 11034, February 26, fatigue cracking in the lower outboard wing
skin at the inboard fastener of stringer L–9.5,
Title 49 of the United States Code 1979), and the lower outboard wing skin of stringer
specifies the FAA’s authority to issue (3) Will not affect intrastate aviation L–6.5, on airplanes with winglets installed
rules on aviation safety. Subtitle I, in Alaska, and per Supplemental Type Certificate
(4) Will not have a significant ST01920SE. We are issuing this AD to
section 106, describes the authority of
economic impact, positive or negative, prevent fatigue cracking in the lower
the FAA Administrator. ‘‘Subtitle VII:
on a substantial number of small entities outboard wing skin, which could result in
Aviation Programs’’ describes in more
under the criteria of the Regulatory failure and subsequent separation of the wing
detail the scope of the Agency’s and winglet and consequent reduced
Flexibility Act.
authority. controllability of the airplane.
We are issuing this rulemaking under List of Subjects in 14 CFR Part 39
(f) Compliance
the authority described in Subtitle VII, Air transportation, Aircraft, Aviation
Part A, Subpart III, Section 44701: Comply with this AD within the
safety, Incorporation by reference,
compliance times specified, unless already
‘‘General requirements.’’ Under that Safety. done.
section, Congress charges the FAA with
promoting safe flight of civil aircraft in The Proposed Amendment (g) Repetitive Stringer L–9.5 Inspections,
air commerce by prescribing regulations Accordingly, under the authority Modification, Repair (Modification),
for practices, methods, and procedures delegated to me by the Administrator, Repetitive Post-Repair Inspections, and
the FAA proposes to amend 14 CFR part Repair
the Administrator finds necessary for
safety in air commerce. This regulation 39 as follows: (1) For Group 1 and Group 2 airplanes
is within the scope of that authority identified in Aviation Partners Boeing
PART 39—AIRWORTHINESS Service Bulletin AP767–57–010, Revision 11,
because it addresses an unsafe condition
DIRECTIVES dated April 3, 2017: At the applicable time
that is likely to exist or develop on specified in paragraph 1.E., ‘‘Compliance,’’ of
products identified in this rulemaking ■ 1. The authority citation for part 39 Aviation Partners Boeing Service Bulletin
action. continues to read as follows: AP767–57–010, Revision 11, dated April 3,
This proposed AD is issued in 2017, except as required by paragraph (j)(1)
Authority: 49 U.S.C. 106(g), 40113, 44701. of this AD: Do a high frequency eddy current
accordance with authority delegated by
the Executive Director, Aircraft (HFEC) inspection for cracking of the lower
§ 39.13 [Amended]
outboard wing skin at stringer L–9.5, in
Certification Service, as authorized by ■ 2. The FAA amends § 39.13 by adding accordance with Part 1 of the
FAA Order 8000.51C. In accordance the following new airworthiness Accomplishment Instructions of Aviation
with that order, issuance of ADs is directive (AD): Partners Boeing Service Bulletin AP767–57–
normally a function of the Compliance 010, Revision 11, dated April 3, 2017.
The Boeing Company: Docket No. FAA–
and Airworthiness Division, but during 2015–1421; Product Identifier 2014–NM– (i) For airplanes on which ‘‘Condition 1’’
this transition period, the Executive 177–AD. is found, as defined in the Accomplishment
Director has delegated the authority to Instructions of Aviation Partners Boeing
issue ADs applicable to transport (a) Comments Due Date Service Bulletin AP767–57–010, Revision 11,
category airplanes to the Director of the We must receive comments by January 11, dated April 3, 2017, during any inspection
2018. required by paragraph (g)(1) or (g)(1)(i)(A) of
System Oversight Division. this AD: Do the applicable actions required
Regulatory Findings (b) Affected ADs by paragraph (g)(1)(i)(A), (g)(1)(i)(B),
None. (g)(1)(i)(C), or (g)(1)(i)(D) of this AD.
We determined that this proposed AD (A) Repeat the inspection specified in
(c) Applicability
pmangrum on DSK3GDR082PROD with PROPOSALS1
would not have federalism implications paragraph (g)(1) of this AD thereafter at the
under Executive Order 13132. This This AD applies to The Boeing Company applicable times specified in paragraph 1.E.,
proposed AD would not have a Model 767–300 and –300F series airplanes, ‘‘Compliance,’’ of Aviation Partners Boeing
substantial direct effect on the States, on certificated in any category, with Aviation Service Bulletin AP767–57–010, Revision 11,
Partners Boeing winglets installed; as dated April 3, 2017.
the relationship between the national identified in Aviation Partners Boeing (B) Do the applicable actions required by
Government and the States, or on the Service Bulletin AP767–57–010, Revision 11, paragraphs (g)(1)(i)(B)(1), (g)(1)(i)(B)(2), and
distribution of power and dated April 3, 2017; and Aviation Partners (g)(1)(i)(B)(3) of this AD.
responsibilities among the various Boeing Service Bulletin AP767–57–014, (1) Before further flight, do actions
levels of government. Revision 1, dated April 12, 2017. (modifications and repair (modification)) in
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![Federal Register / Vol. 82, No. 226 / Monday, November 27, 2017 / Proposed Rules 55963
procedures specified in paragraph (k) of this (iii) If any crack is found during any 14 CFR 39.19, send your request to your
AD. inspection required by paragraph (h)(2)(ii) of principal inspector or local Flight Standards
(2) For Group 3 airplanes identified in this AD, repair before further flight using a District Office, as appropriate. If sending
Aviation Partners Boeing Service Bulletin method approved in accordance with the information directly to the manager of the
AP767–57–010, Revision 11, dated April 3, procedures specified in paragraph (k) of this certification office, send it to the attention of
2017: At the applicable time specified in AD. the person identified in paragraph (l)(1) of
paragraph 1.E., ‘‘Compliance,’’ of Aviation (3) As an option to the repetitive this AD. Information may be emailed to: 9–
Partners Boeing Service Bulletin AP767–57– inspections required by paragraph (h)(1) of ANM-Seattle-ACO-AMOC-Requests@faa.gov.
010, Revision 11, dated April 3, 2017, or this AD, do the actions required by (2) Before using any approved AMOC,
within 6 months after the effective date of paragraphs (h)(3)(i) and (h)(3)(ii) of this AD, notify your appropriate principal inspector,
this AD, whichever occurs later, do an HFEC and do all applicable actions required by or lacking a principal inspector, the manager
inspection for cracking of the lower outboard paragraph (h)(3)(iii) of this AD. of the local flight standards district office/
wing skin at stringer L–9.5, in accordance (i) Before further flight after accomplishing certificate holding district office.
with Part 7 of the Accomplishment the most recent inspection required by (3) An AMOC that provides an acceptable
Instructions of Aviation Partners Boeing paragraph (h)(1) of this AD, repair (modify) level of safety may be used for any repair,
Service Bulletin AP767–57–010, Revision 11, stringer L–6.5, in accordance with Part 2 of modification, or alteration required by this
dated April 3, 2017. Repeat the inspection the Accomplishment Instructions of Aviation AD if it is approved by the Boeing
thereafter at the applicable time specified in Partners Boeing Service Bulletin AP767–57– Commercial Airplanes ODA that has been
paragraph 1.E., ‘‘Compliance,’’ of Aviation 014, Revision 1, dated April 12, 2017. authorized by the Manager, Seattle ACO
Partners Boeing Service Bulletin AP767–57– (ii) At the applicable time specified in Branch, to make those findings. To be
010, Revision 11, dated April 3, 2017. If any paragraph 1.E., ‘‘Compliance,’’ of Aviation approved, the repair method, modification
cracking is found during any inspection, Partners Boeing Service Bulletin AP767–57– deviation, or alteration deviation must meet
repair before further flight using a method 014, Revision 1, dated April 12, 2017, except the certification basis of the airplane, and the
approved in accordance with the procedures as required by paragraph (j)(2) of this AD, do approval must specifically refer to this AD.
specified in paragraph (k) of this AD. An a post-repair HFEC inspection for cracking, (4) Except as required by paragraphs
approved repair terminates the repetitive in accordance with Part 3 of the (g)(1)(i)(B)(3), (g)(1)(i)(C)(3), (g)(1)(i)(D)(3),
inspections required by paragraph (g)(2) of Accomplishment Instructions of Aviation (g)(1)(ii)(A)(3), (g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3),
this AD. Partners Boeing Service Bulletin AP767–57– (g)(1)(iii)(B)(3), (g)(1)(iv), (g)(2), (h)(2)(iii),
014, Revision 1, dated April 12, 2017, and and (h)(3)(iii) of this AD: For service
(h) Repetitive Stringer L–6.5 Inspections, information that contains steps that are
Repair (Modification), Repetitive Post- repeat the inspection thereafter at the
applicable times specified in paragraph 1.E., labeled as Required for Compliance (RC), the
Repair Inspections, and Repair provisions of paragraphs (k)(4)(i) and
‘‘Compliance,’’ of Aviation Partners Boeing
(1) For airplanes identified in Boeing Service Bulletin AP767–57–014, Revision 1, (k)(4)(ii) of this AD apply.
Service Bulletin AP767–57–014, Revision 1, dated April 12, 2017. (i) The steps labeled as RC, including
dated April 12, 2017: At the applicable time (iii) If any crack is found during any substeps under an RC step and any figures
specified in paragraph 1.E., ‘‘Compliance,’’ of inspection required by paragraph (h)(3)(ii) of identified in an RC step, must be done to
Aviation Partners Boeing Service Bulletin this AD, repair before further flight using a comply with the AD. If a step or substep is
AP767–57–014, Revision 1, dated April 12, method approved in accordance with the labeled ‘‘RC Exempt,’’ then the RC
2017, except as required by paragraph (j)(2) procedures specified in paragraph (k) of this requirement is removed from that step or
of this AD: Do an HFEC inspection for AD. substep. An AMOC is required for any
cracking of stringer L–6.5 of the lower deviations to RC steps, including substeps
outboard wing skin, in accordance with Part (i) Repair Approval and identified figures.
1 of Aviation Partners Boeing Service Repairs of the lower outboard wing skin (ii) Steps not labeled as RC may be
Bulletin AP767–57–014, Revision 1, dated done after June 15, 2017, and before the deviated from using accepted methods in
April 12, 2017. If no cracking is found, repeat effective date of this AD, that are approved accordance with the operator’s maintenance
the inspection thereafter at the applicable by the Boeing Commercial Airplanes or inspection program without obtaining
times specified in paragraph 1.E., Organization Designation Authorization approval of an AMOC, provided the RC steps,
‘‘Compliance,’’ of Aviation Partners Boeing (ODA) that has been authorized by the including substeps and identified figures, can
Service Bulletin AP767–57–014, Revision 1, Manager, Seattle ACO Branch, are approved still be done as specified, and the airplane
dated April 12, 2017, except as provided by for the applicable repairs required by can be put back in an airworthy condition.
paragraph (h)(3) of this AD. paragraphs (g) and (h) of this AD. (l) Related Information
(2) If any crack is found during any
inspection required by paragraph (h)(1) of (j) Exceptions to Service Information (1) For more information about this AD,
this AD, do the actions required by Specifications contact Allen Rauschendorfer, Aerospace
paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, (1) Where paragraph 1.E., ‘‘Compliance,’’ of Engineer, Airframe Section, FAA, Seattle
and do all applicable actions required by Aviation Partners Boeing Service Bulletin ACO Branch, 1601 Lind Avenue SW.,
paragraph (h)(2)(iii) of this AD. AP767–57–010, Revision 11, dated April 3, Renton, WA 98057–3356; phone: 425–917–
(i) Before further flight, repair (modify) 2017, specifies a compliance time of ‘‘after 6450; fax: 425–917–6590; email:
stringer L–6.5, in accordance with Part 2 of allen.rauschendorfer@faa.gov.
the issue date of Revision 11 of this service
the Accomplishment Instructions of Aviation (2) For service information identified in
bulletin,’’ this AD requires compliance
Partners Boeing Service Bulletin AP767–57– this AD, contact Aviation Partners Boeing,
within the specified compliance time after
014, Revision 1, dated April 12, 2017. 2811 S. 102nd Street, Suite 200, Seattle, WA
the effective date of this AD.
(ii) At the applicable time specified in 98168; telephone 206–762–1171; Internet
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
paragraph 1.E., ‘‘Compliance,’’ of Aviation https://www.aviationpartnersboeing.com.
Aviation Partners Boeing Service Bulletin
Partners Boeing Service Bulletin AP767–57– You may view this referenced service
AP767–57–014, Revision 1, dated April 12,
014, Revision 1, dated April 12, 2017, except information at the FAA, Transport Standards
2017, specifies a compliance time of ‘‘after
as required by paragraph (j)(2) of this AD, do Branch, 1601 Lind Avenue SW., Renton, WA.
the initial issue date of this service bulletin,’’
For information on the availability of this
pmangrum on DSK3GDR082PROD with PROPOSALS1
an HFEC post-repair inspection for cracking, this AD requires compliance within the
in accordance with Part 3 of the material at the FAA, call 425–227–1221.
specified compliance time after the effective
Accomplishment Instructions of Aviation date of this AD. Issued in Renton, Washington, on
Partners Boeing Service Bulletin AP767–57– November 3, 2017.
014, Revision 1, dated April 12, 2017, and (k) Alternative Methods of Compliance
(AMOCs) Jeffrey E. Duven,
repeat the inspection thereafter at the
Director, System Oversight Division, Aircraft
applicable times specified in paragraph 1.E., (1) The Manager, Seattle ACO Branch,
Certification Service.
‘‘Compliance,’’ of Aviation Partners Boeing FAA, has the authority to approve AMOCs
Service Bulletin AP767–57–014, Revision 1, for this AD, if requested using the procedures [FR Doc. 2017–24502 Filed 11–24–17; 8:45 am]
dated April 12, 2017. found in 14 CFR 39.19. In accordance with BILLING CODE 4910–13–P
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Document Created: 2017-11-25 01:09:04
Document Modified: 2017-11-25 01:09:04
| 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 | Proposed Rules | |
| Action | Supplemental notice of proposed rulemaking (SNPRM); reopening of comment period. | |
| Dates | The comment period for the NPRM published in the Federal Register on June 5, 2015 (80 FR 32066), is reopened. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6450; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 82 FR 55958 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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