83 FR 25885 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 108 (June 5, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 108 (June 5, 2018)
| Page Range | 25885-25891 | |
| FR Document | 2018-11825 |
[Federal Register Volume 83, Number 108 (Tuesday, June 5, 2018)] [Rules and Regulations] [Pages 25885-25891] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-11825] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-1421; Product Identifier 2014-NM-177-AD; Amendment 39-19302; AD 2018-11-14] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 and -300F series airplanes. This AD was prompted by reports of fatigue cracking on airplanes with Aviation Partners Boeing winglets installed. This AD requires high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin, and repair or modification if necessary. This AD also requires 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. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 10, 2018. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of July 10, 2018. ADDRESSES: For service information identified in this final rule, 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, 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-2015- 1421. 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 Docket Operations between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the regulatory evaluation, any comments received, and other information. The address for Docket Operations (phone: 800-647- 5527) is Docket Operations, 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: Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA; phone and fax: 206-231-3528; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (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 a 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. We issued an SNPRM 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 SNPRM published in the Federal Register on November 27, 2017 (82 FR 55958). The SNPRM proposed adding new HFEC inspections for cracking of an expanded area of the lower outboard wing skin for certain airplanes. We are issuing this AD to address 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. Comments We gave the public the opportunity to participate in developing this final rule. The following presents the comments received on the SNPRM and the FAA's response to each comment. One commenter, Matt Leritz, supported the content of the SNRPM. Request To Correct Compliance Time Aviation Partners Boeing (APB) and United Airlines (UAL) asked that we correct the compliance time in paragraphs (h)(2)(ii) and (h)(3)(ii) of the proposed AD (in the SNPRM). The commenters stated that those paragraphs would require the initial post-repair HFEC inspection of the lower wing skin at stringer L-6.5 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. The commenters added that the compliance time for the Part 3 HFEC inspection specified in paragraph 1.E. does not begin after doing the Part 2 repair, but instead begins after the initial issue of the service bulletin (after the effective date of the AD). UAL stated that, as written, this would require doing post-repair inspections on airplanes above the total flight-hour and flight-cycle threshold within 18 months after the effective date of the AD, regardless of if or when the repair was actually done. APB confirmed that the calendar-based compliance time in the referenced service information, for airplanes in Group 1, Configurations 2 and 3, and Groups 2 and 3, should be the same as for airplanes in Group 1, Configuration 1, on which the Part 2 repair has been done. The commenters asked that the compliance time for the Part 3 HFEC inspection be corrected to the following: ``Within 6,000 flight cycles after doing the Part 2 repair, or within 18,000 flight hours since doing the Part 2 repair, whichever occurs first.'' We agree with the commenters' request for the reasons provided. We have added paragraph (j)(3) of this AD to include this compliance-time exception. Request To Remove a Certain Terminating Action Boeing asked that we remove the terminating action sentence at the end of paragraph (g)(2) of the proposed AD (in the SNPRM). Paragraph (g)(2) of the proposed AD (in the SNPRM) applies to Group 3 airplanes with external doublers, and if a crack is found it requires a repair using a method [[Page 25886]] approved by the FAA. That paragraph also specifies that ``[a]n approved repair terminates the repetitive inspections required by paragraph (g)(2) of this AD.'' Boeing stated that any repair for cracks found will require follow-on repetitive inspections, which would be approved as part of the AMOC repair approval process. We agree that the repairs for Group 3 airplanes will have an approved follow-on inspection program, but the repairs may apply to the cracked areas only. We do not agree with removing the terminating action provision because other areas may require the repetitive inspections specified in paragraph (g)(2) of this AD, for which approved terminating action would be appropriate. We have revised that sentence as follows: ``An approved repair terminates the repetitive inspections required by paragraph (g)(2) of this AD for the repaired area only.'' Request To Add Grace Period for Post-Repair (Modification) Inspections American Airlines (AAL), APB, UAL, and Delta Airlines (Delta) asked that we add a grace period for the proposed post-repair (modification) inspections. AAL stated that Table 4 of paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, includes numerous inspections that are due within a specified number of flight hours or flight cycles after previous repair or modification of the airplane. AAL added that since it has completed many repairs and modifications using previous revisions of the referenced service information, there will be airplanes out of compliance with the AD requirements on the effective date because there is no grace period based on the AD due date. APB and Delta stated that paragraph (g) of the proposed AD (in the SNPRM) specifies compliance times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57- 010, Revision 11, dated April 3, 2017, for initial post-repair inspections. APB added that the referenced service information added a flight-hour threshold of 90,000 total flight cycles to the existing flight-cycle threshold of 30,000 total flight cycles for the initial compliance time. APB noted that the grace period published in the referenced service information for airplanes on which the flight-hour or flight-cycle threshold has been reached is set to 18 months after accomplishment of the repair. APB stated that this creates a drop-dead inspection situation for airplanes on which either the flight-hour or flight-cycle threshold has been reached, and on which the Part 8 or Part 11 repair was accomplished over 18 months ago. Delta stated that the compliance table on pages (i) and (ii) of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, should be added to paragraph 1.E., ``Compliance'' and included in the AD. UAL stated that paragraph (g) of the proposed AD (in the SNPRM) would require the repetitive post-repair inspections specified in Parts 9 and 13 of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, in airplane total times or within 18 months after accomplishment of Part 8 and 11 repairs, respectively. UAL is concerned that older airplanes on which the repair was done more than 18 months ago could be out of compliance on the effective date of the AD. UAL noted that the 18-month grace period covers the initial inspection, but does not cover post-repair inspections. UAL suggested that we provide similar relief for airplanes on which the threshold has been exceeded. We do not agree with the commenters' requests to add a grace period. The current revisions of the referenced service information provide a compliance time of 18 months for the initial inspection for all airplanes. The compliance times for certain conditional inspections are in terms of airplane threshold or time since accomplishment of the specified repair or modification. Those previously installed repairs or modifications may have been done using a version of Aviation Partners Boeing Service Bulletin AP767-57-010 before Revision 11 or alternative method, and may involve deviations, additional repair activity, and previous repairs. Under the provisions of paragraph (k) of this AD, we will consider requests for approval of AMOCs to extend the compliance time if sufficient data are submitted to substantiate that it would provide an acceptable level of safety. We have determined that each situation must be handled separately in the AMOC evaluation. We have not changed this AD in this regard. Request To Add Compliance Tables to Certain Service Information Delta asked that a compliance table be added to Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, for airplanes on which the actions specified in Aviation Partners Boeing Service Bulletin AP767-57-010 have been previously accomplished. Delta noted that page i of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, provides a compliance information table only for Group 3 airplanes; there are no tables for Groups 1 and 2 airplanes. We do not agree with the commenter's request. The compliance information table on page i of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, provides only a description of additional work, if any, necessary based on work accomplished using the previous revision. These tables are reference information only, and do not reflect all the actions required by the AD. The necessary compliance tables are provided in paragraph 1.E., ``Compliance'' of Aviation Partners Boeing Service Bulletin AP767-57- 014, Revision 1, dated April 12, 2017. Therefore, we have not changed this AD in this regard. Request To Clarify Group 4 Airplanes Not Affected UAL asked that we include a clarification in the proposed AD (in the SNPRM) that Group 4 airplanes are not affected. UAL stated that Group 4 airplanes are identified in the effectivity table in paragraph 1.A. of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. UAL noted that an equivalent change to the service information was incorporated during winglet installation with no additional work being necessary. UAL asked that we add paragraph (g)(3) to the AD to clarify that Group 4 airplanes are not affected by the requirements in the AD. We agree with the commenter for the reasons provided. Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, specifies that an equivalent change has been incorporated in APB winglet retrofit kits for Group 4 airplanes, and that no more work is necessary on those airplanes. We have included a clarification in paragraph (g)(3) of this AD that specifies that Group 4 airplanes are not affected by the actions required by paragraph (g) of this AD. Request To Remove an Airplane Having a Certain Line Number FedEx asked that we remove the airplane having line number 1027 from the applicability in the proposed AD (in the SNPRM), or allow Aviation Partners Boeing Service Bulletin AP767-57-012, dated September 2015, as an AMOC. FedEx stated that it will be modifying that airplane by removing the winglets and installing Boeing wing tips in accordance with Aviation Partners Boeing Service Bulletin AP767-57-012, [[Page 25887]] dated September 2015. FedEx anticipated that the modification will be completed prior to the effective date of the AD. FedEx added that the unsafe condition will be addressed when the winglets are removed. We do not agree with the commenter's request. There are many factors that led to the cracking of the lower wing skin, and the additional loading of the winglet is only one of those factors. Other contributory factors are design details with the added internal wing structure, which resulted in shortening the fatigue life of the blended winglet installation. We have not changed this AD in this regard. Request Approval for Alternative Open Hole HFEC Inspection UAL asked that provisions be added to paragraph (g) of the proposed AD (in the SNPRM) to allow an alternative open-hole HFEC inspection procedure to inspect for cracking at the five inboard fastener locations. UAL stated that an open-hole HFEC inspection with the fasteners removed, in accordance with nondestructive test (NDT) Part 6, Chapter 51-00-16, using the same notch sensitivity provides an equivalent crack detection method. UAL added that APB has concurred with the inspection. UAL concluded that it has been performing the optional preventive modification, which trims out the skin containing the five fastener holes, and allows for the open-hole HFEC to be performed easily because the fasteners in the doubler are removed. We do not agree with the commenter's request. Although UAL developed an inspection method that works better for its situation, the HFEC inspection specified in the referenced service information is required by this AD to address all situations. However, under the provisions of paragraph (k) of this AD, we will consider requests for approval of AMOCs if sufficient data are submitted to substantiate that the open-hole HFEC inspection procedure provides an acceptable level of safety. We have not changed this AD in this regard. Request To Clarify Credit for Previously Accomplished Repairs Approved by an Organization Designation Authorization (ODA) All Nippon Airways (ANA), AAL, APB, and Delta asked that we clarify credit in paragraph (i) of the proposed AD (in the SNPRM), for previously accomplished repairs approved by a Boeing ODA prior to June 15, 2017. ANA stated that during discussions with the FAA, it was informed that repair deviations approved by Boeing ODAs prior to the FAA approval of the APB revised fatigue analysis issued on June 15, 2017, and the release of Aviation Partners Boeing Service Bulletins AP767-57- 010, Revision 11, AP767-57-013, Revision 1, and AP767-57-014, Revision 1, do not qualify for AMOC credit to the AD after it is released. ANA added that the proposed AD (in the SNPRM) would provide AMOC credit for repair deviations approved by Boeing ODAs with 8100-9 forms dated after June 15, 2017, because the Boeing ODAs would be using the APB revised fatigue analysis. AAL stated that paragraph (i) of the proposed AD (in the SNPRM) specifies that repairs accomplished before June 15, 2017, and before the AD effective date approved by a Boeing ODA can be considered approved repairs in accordance with paragraphs (g) and (h) of the proposed AD (in the SNPRM). AAL added that Boeing has indicated through Multi-Operator Message MOM-MOM-17-0480-01B that repairs approved prior to June 15, 2017, can be re-evaluated and approved on a new 8100-9 form. AAL noted that the language in paragraph (i) should be clarified to indicate that repairs accomplished prior to June 15, 2017, are also acceptable, as long as they have an 8100-9 approval from a Boeing ODA dated after June 15, 2017. APB requested that we clarify paragraph (i) of the proposed AD (in the SNPRM) to state that accomplishment of previous revisions of Aviation Partners Boeing Service Bulletins AP767-57-010 should be acceptable for credit for previously accomplished repairs and modifications of the lower outboard wing skin. APB stated that after the effective date of the AD, operators that did not seek relief for previously completed actions would need to request approval of AMOCs. Delta stated that paragraph (i) of the proposed AD (in the SNPRM) provides repair approval for repairs of the lower outboard wing skin done after June 15, 2017, and before the effective date of the AD, that are approved by the Boeing ODA authorized by the Manager, Seattle ACO Branch, are approved for the applicable repairs required by paragraphs (g) and (h) of the AD. Delta added that prior to issuance of the referenced service information, both inspection and repair instructions for stringers L-9.5 and L-6.5 were contained in Revisions 1, 2, 4, 6, 7, 8, and 9 of Aviation Partners Boeing Service Bulletin AP767-57-010. Delta added that it has performed many inspections and repairs for stringers L-9.5 and L-6.5 with those revisions. Delta suggested that credit be provided for repairs approved by a Boeing 8100-9 or previously accomplished using Revisions 1, 2, 4, 6, 7, 8, and 9 of Aviation Partners Boeing Service Bulletin AP767-57-010. Delta added that AMOCs will have to be obtained for each approved 8100-9 if no credit is provided. We agree to clarify the language in paragraph (i) of this AD to include certain language provided by the commenters' for the reasons provided. We have clarified the language in paragraph (i) of this AD by adding that the ODA repairs approved after June 15, 2017, and before the effective date of this AD, will have post-installation inspection requirements in lieu of the post-inspection instructions specified 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. Request To Correct Error in Service Information APB and UAL asked that we correct an error specified in Part 13 of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. APB and UAL stated that paragraphs (g)(1)(i)(D)(2), (g)(1)(ii)(B)(2), and (g)(1)(iii)(B)(2) of the proposed AD (in the SNPRM) would require the post-repair HFEC inspection in accordance with Part 13 of the referenced service information. UAL stated that Part 13, Step 1.d., specifies repeating the Part 9 HFEC inspection; however, it should specify repeating the Part 13 HFEC inspection because Part 9 applies to airplanes without the stringer replacement. UAL noted that the paragraphs in the proposed AD (in the SNPRM) correctly specify repeating the Part 13 HFEC inspection. UAL added that the steps in the referenced service information are listed as RC (required for compliance), and must be done to comply with the AD. We agree that the error exists in the service information. We have added an exception in paragraph (j)(4) of this AD that specifies repeating the Part 13 HFEC inspection instead of the Part 9 inspection. Request To Provide Credit for Previous Service Information AAL, UAL, and United Parcel Service (UPS) asked that we provide credit for doing the modification required by paragraph (i) of the proposed AD (in the SNPRM) using previous revisions of the referenced service information. UAL and UPS noted that paragraph (i) of the [[Page 25888]] proposed AD (in the NPRM), which provided credit for previous actions using previous revisions of the referenced service information, was deleted in the SNPRM. We do not agree with the commenters' requests. No credit is given for previously installed repairs or modifications due to each situation being unique; therefore, a re-evaluation will have to be done and may involve additional work for certain airplanes. Under the provisions of paragraph (k) of this AD, we will consider requests for approval of AMOCs if sufficient data are submitted to substantiate that work done using previous revisions of the service information provides an acceptable level of safety. We have not changed this AD in this regard. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the SNPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the SNPRM. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this final rule. 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, and 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 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. Costs of Compliance We estimate that this AD affects 140 airplanes of U.S. registry. We estimate the following costs to comply with this 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. ---------------------------------------------------------------------------------------------------------------- We estimate the following costs to do any necessary on-condition actions that would be required based on the results of the 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 = $0 $510 $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 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 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 and associated appliances to the Director of the System Oversight Division. Regulatory Findings 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, [[Page 25889]] (2) Is not a ``significant rule'' under 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 adding the following new airworthiness directive (AD): 2018-11-14 The Boeing Company: Amendment 39-19302; Docket No. FAA- 2015-1421; Product Identifier 2014-NM-177-AD. (a) Effective Date This AD is effective July 10, 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 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 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 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)(4) of this AD. (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- [[Page 25890]] 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 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 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)(4) of this AD. (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 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 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)(4) of this AD. (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 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 for the repaired area only. (3) Group 4 airplanes identified in Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, are not affected by the actions required by paragraph (g) 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) Except as required by paragraph (j)(3) of this AD: 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) Except as required by paragraph (j)(3) of this AD: At the applicable time specified [[Page 25891]] 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 that were approved after June 15, 2017, and before the effective date of this AD, 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. The ODA repairs will have post-installation inspection requirements in lieu of the post-inspection instructions specified 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. (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 ``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 ``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. (3) For Condition 1 and Condition 2 airplanes: Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017, specifies a compliance time for accomplishing the Part 3 HFEC inspection of 18 months ``after the initial issue date of this service bulletin,'' the required compliance time is 6,000 flight cycles or 18,000 flight hours, whichever occurs first, after doing the Part 2 repair. (4) For airplanes on which a stringer L-9.5 replacement was accomplished per Part 11 of Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017: Where Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017, specifies repeating the post-repair HFEC inspection ``in Part 9,'' this AD requires repeating the post-repair HFEC inspection in Part 13. (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) 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 For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA; phone and fax: 206-231-3528; email: [email protected]. (m) 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 the AD specifies otherwise. (i) Aviation Partners Boeing Service Bulletin AP767-57-010, Revision 11, dated April 3, 2017. (ii) Aviation Partners Boeing Service Bulletin AP767-57-014, Revision 1, dated April 12, 2017. (3) 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. (4) You may view this service information at the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines, WA. For information on the availability of this material at the FAA, call 206-231-3195. (5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Des Moines, Washington, on May 21, 2018. James Cashdollar, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-11825 Filed 6-4-18; 8:45 am] BILLING CODE 4910-13-P
![Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations 25885
Issued in Des Moines, Washington, on May for and locating Docket No. FAA–2015– and winglet and consequent reduced
18, 2018. 1421. controllability of the airplane.
Michael Kaszycki,
Examining the AD Docket Comments
Acting Director, System Oversight Division,
Aircraft Certification Service. You may examine the AD docket on We gave the public the opportunity to
[FR Doc. 2018–11414 Filed 6–4–18; 8:45 am] the internet at http:// participate in developing this final rule.
BILLING CODE 4910–13–P www.regulations.gov by searching for The following presents the comments
and locating Docket No. FAA–2015– received on the SNPRM and the FAA’s
1421; or in person at Docket Operations response to each comment. One
DEPARTMENT OF TRANSPORTATION between 9 a.m. and 5 p.m., Monday commenter, Matt Leritz, supported the
through Friday, except Federal holidays. content of the SNRPM.
Federal Aviation Administration The AD docket contains this final rule, Request To Correct Compliance Time
the regulatory evaluation, any
14 CFR Part 39 comments received, and other Aviation Partners Boeing (APB) and
information. The address for Docket United Airlines (UAL) asked that we
[Docket No. FAA–2015–1421; Product Operations (phone: 800–647–5527) is correct the compliance time in
Identifier 2014–NM–177–AD; Amendment Docket Operations, U.S. Department of paragraphs (h)(2)(ii) and (h)(3)(ii) of the
39–19302; AD 2018–11–14]
Transportation, Docket Operations, M– proposed AD (in the SNPRM). The
30, West Building Ground Floor, Room commenters stated that those
RIN 2120–AA64 paragraphs would require the initial
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590. post-repair HFEC inspection of the
Airworthiness Directives; The Boeing lower wing skin at stringer L–6.5 at the
Company Airplanes FOR FURTHER INFORMATION CONTACT:
applicable time specified in paragraph
Allen Rauschendorfer, Aerospace 1.E., ‘‘Compliance,’’ of Aviation Partners
AGENCY: Federal Aviation Engineer, Airframe Section, FAA,
Administration (FAA), DOT. Boeing Service Bulletin AP767–57–014,
Seattle ACO Branch, 2200 South 216th Revision 1, dated April 12, 2017. The
ACTION: Final rule. St., Des Moines, WA; phone and fax: commenters added that the compliance
206–231–3528; email: time for the Part 3 HFEC inspection
SUMMARY: We are adopting a new
allen.rauschendorfer@faa.gov. specified in paragraph 1.E. does not
airworthiness directive (AD) for certain
The Boeing Company Model 767–300 SUPPLEMENTARY INFORMATION: begin after doing the Part 2 repair, but
and –300F series airplanes. This AD was Discussion instead begins after the initial issue of
prompted by reports of fatigue cracking the service bulletin (after the effective
on airplanes with Aviation Partners We issued a notice of proposed date of the AD). UAL stated that, as
Boeing winglets installed. This AD rulemaking (NPRM) to amend 14 CFR written, this would require doing post-
requires high frequency eddy current part 39 by adding an AD that would repair inspections on airplanes above
(HFEC) inspections for cracking of the apply to certain The Boeing Company the total flight-hour and flight-cycle
lower outboard wing skin, and repair or Model 767–300 and –300F series threshold within 18 months after the
modification if necessary. This AD also airplanes. The NPRM published in the effective date of the AD, regardless of if
requires one of three follow-on actions: Federal Register on June 5, 2015 (80 FR or when the repair was actually done.
Repeating the HFEC inspections, 32066). The NPRM was prompted by APB confirmed that the calendar-based
modifying certain internal stringers and reports of fatigue cracking on airplanes compliance time in the referenced
oversizing and plugging the existing with Aviation Partners Boeing winglets service information, for airplanes in
fastener holes of the lower wing, or installed. The NPRM proposed to Group 1, Configurations 2 and 3, and
modifying the external doubler/tripler require a HFEC inspection for cracking Groups 2 and 3, should be the same as
and doing repetitive post-modification of the lower outboard wing skin, and for airplanes in Group 1, Configuration
inspections. We are issuing this AD to repair or modification if necessary. The 1, on which the Part 2 repair has been
address the unsafe condition on these NPRM also proposed to require one of done. The commenters asked that the
products. three follow-on actions: Repeating the compliance time for the Part 3 HFEC
HFEC inspections, modifying certain inspection be corrected to the following:
DATES: This AD is effective July 10, internal stringers and oversizing and ‘‘Within 6,000 flight cycles after doing
2018. plugging the existing fastener holes of the Part 2 repair, or within 18,000 flight
The Director of the Federal Register the lower wing, or modifying the hours since doing the Part 2 repair,
approved the incorporation by reference external doubler/tripler and doing whichever occurs first.’’
of certain publications listed in this AD repetitive post-modification inspections. We agree with the commenters’
as of July 10, 2018. We issued an SNPRM to amend 14 request for the reasons provided. We
ADDRESSES: For service information CFR part 39 by adding an AD that have added paragraph (j)(3) of this AD
identified in this final rule, contact would apply to certain The Boeing to include this compliance-time
Aviation Partners Boeing, 2811 S. 102nd Company Model 767–300 and –300F exception.
Street, Suite 200, Seattle, WA 98168; series airplanes. The SNPRM published
telephone 206–762–1171; in the Federal Register on November 27, Request To Remove a Certain
internet https:// 2017 (82 FR 55958). The SNPRM Terminating Action
www.aviationpartnersboeing.com. You proposed adding new HFEC inspections Boeing asked that we remove the
may view this service information at the for cracking of an expanded area of the terminating action sentence at the end
amozie on DSK3GDR082PROD with RULES
FAA, Transport Standards Branch, 2200 lower outboard wing skin for certain of paragraph (g)(2) of the proposed AD
South 216th St., Des Moines, WA. For airplanes. (in the SNPRM). Paragraph (g)(2) of the
information on the availability of this We are issuing this AD to address proposed AD (in the SNPRM) applies to
material at the FAA, call 206–231–3195. fatigue cracking in the lower outboard Group 3 airplanes with external
It is also available on the internet at wing skin, which could result in failure doublers, and if a crack is found it
http://www.regulations.gov by searching and subsequent separation of the wing requires a repair using a method
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![25886 Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations
approved by the FAA. That paragraph cycle threshold has been reached, and Service Bulletin AP767–57–014,
also specifies that ‘‘[a]n approved repair on which the Part 8 or Part 11 repair Revision 1, dated April 12, 2017,
terminates the repetitive inspections was accomplished over 18 months ago. provides a compliance information table
required by paragraph (g)(2) of this AD.’’ Delta stated that the compliance table only for Group 3 airplanes; there are no
Boeing stated that any repair for cracks on pages (i) and (ii) of Aviation Partners tables for Groups 1 and 2 airplanes.
found will require follow-on repetitive Boeing Service Bulletin AP767–57–010, We do not agree with the commenter’s
inspections, which would be approved Revision 11, dated April 3, 2017, should request. The compliance information
as part of the AMOC repair approval be added to paragraph 1.E., table on page i of Aviation Partners
process. ‘‘Compliance’’ and included in the AD. Boeing Service Bulletin AP767–57–014,
We agree that the repairs for Group 3 UAL stated that paragraph (g) of the Revision 1, dated April 12, 2017,
airplanes will have an approved follow- proposed AD (in the SNPRM) would provides only a description of
on inspection program, but the repairs require the repetitive post-repair additional work, if any, necessary based
may apply to the cracked areas only. We inspections specified in Parts 9 and 13 on work accomplished using the
do not agree with removing the of Aviation Partners Boeing Service previous revision. These tables are
terminating action provision because Bulletin AP767–57–010, Revision 11, reference information only, and do not
other areas may require the repetitive dated April 3, 2017, in airplane total reflect all the actions required by the
inspections specified in paragraph (g)(2) times or within 18 months after AD. The necessary compliance tables
of this AD, for which approved accomplishment of Part 8 and 11 are provided in paragraph 1.E.,
terminating action would be repairs, respectively. UAL is concerned ‘‘Compliance’’ of Aviation Partners
appropriate. We have revised that that older airplanes on which the repair Boeing Service Bulletin AP767–57–014,
sentence as follows: ‘‘An approved was done more than 18 months ago Revision 1, dated April 12, 2017.
repair terminates the repetitive could be out of compliance on the Therefore, we have not changed this AD
inspections required by paragraph (g)(2) effective date of the AD. UAL noted that in this regard.
of this AD for the repaired area only.’’ the 18-month grace period covers the
Request To Clarify Group 4 Airplanes
initial inspection, but does not cover
Request To Add Grace Period for Post- Not Affected
post-repair inspections. UAL suggested
Repair (Modification) Inspections UAL asked that we include a
that we provide similar relief for
American Airlines (AAL), APB, UAL, airplanes on which the threshold has clarification in the proposed AD (in the
and Delta Airlines (Delta) asked that we been exceeded. SNPRM) that Group 4 airplanes are not
add a grace period for the proposed We do not agree with the commenters’ affected. UAL stated that Group 4
post-repair (modification) inspections. requests to add a grace period. The airplanes are identified in the effectivity
AAL stated that Table 4 of paragraph current revisions of the referenced table in paragraph 1.A. of Aviation
1.E., ‘‘Compliance,’’ of Aviation Partners service information provide a Partners Boeing Service Bulletin
Boeing Service Bulletin AP767–57–010, compliance time of 18 months for the AP767–57–010, Revision 11, dated
Revision 11, dated April 3, 2017, initial inspection for all airplanes. The April 3, 2017. UAL noted that an
includes numerous inspections that are compliance times for certain conditional equivalent change to the service
due within a specified number of flight inspections are in terms of airplane information was incorporated during
hours or flight cycles after previous threshold or time since accomplishment winglet installation with no additional
repair or modification of the airplane. of the specified repair or modification. work being necessary. UAL asked that
AAL added that since it has completed Those previously installed repairs or we add paragraph (g)(3) to the AD to
many repairs and modifications using modifications may have been done clarify that Group 4 airplanes are not
previous revisions of the referenced using a version of Aviation Partners affected by the requirements in the AD.
service information, there will be Boeing Service Bulletin AP767–57–010 We agree with the commenter for the
airplanes out of compliance with the AD before Revision 11 or alternative reasons provided. Aviation Partners
requirements on the effective date method, and may involve deviations, Boeing Service Bulletin AP767–57–010,
because there is no grace period based additional repair activity, and previous Revision 11, dated April 3, 2017,
on the AD due date. repairs. Under the provisions of specifies that an equivalent change has
APB and Delta stated that paragraph paragraph (k) of this AD, we will been incorporated in APB winglet
(g) of the proposed AD (in the SNPRM) consider requests for approval of retrofit kits for Group 4 airplanes, and
specifies compliance times specified in AMOCs to extend the compliance time that no more work is necessary on those
paragraph 1.E., ‘‘Compliance,’’ of if sufficient data are submitted to airplanes. We have included a
Aviation Partners Boeing Service substantiate that it would provide an clarification in paragraph (g)(3) of this
Bulletin AP767–57–010, Revision 11, acceptable level of safety. We have AD that specifies that Group 4 airplanes
dated April 3, 2017, for initial post- determined that each situation must be are not affected by the actions required
repair inspections. APB added that the handled separately in the AMOC by paragraph (g) of this AD.
referenced service information added a evaluation. We have not changed this
flight-hour threshold of 90,000 total Request To Remove an Airplane Having
AD in this regard.
flight cycles to the existing flight-cycle a Certain Line Number
threshold of 30,000 total flight cycles for Request To Add Compliance Tables to FedEx asked that we remove the
the initial compliance time. APB noted Certain Service Information airplane having line number 1027 from
that the grace period published in the Delta asked that a compliance table be the applicability in the proposed AD (in
referenced service information for added to Aviation Partners Boeing the SNPRM), or allow Aviation Partners
airplanes on which the flight-hour or Service Bulletin AP767–57–014, Boeing Service Bulletin AP767–57–012,
amozie on DSK3GDR082PROD with RULES
flight-cycle threshold has been reached Revision 1, dated April 12, 2017, for dated September 2015, as an AMOC.
is set to 18 months after airplanes on which the actions specified FedEx stated that it will be modifying
accomplishment of the repair. APB in Aviation Partners Boeing Service that airplane by removing the winglets
stated that this creates a drop-dead Bulletin AP767–57–010 have been and installing Boeing wing tips in
inspection situation for airplanes on previously accomplished. Delta noted accordance with Aviation Partners
which either the flight-hour or flight- that page i of Aviation Partners Boeing Boeing Service Bulletin AP767–57–012,
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![Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations 25889
(2) Is not a ‘‘significant rule’’ under (f) Compliance (1) Before further flight, repair (modify) in
DOT Regulatory Policies and Procedures Comply with this AD within the accordance with Part 8 of the
(44 FR 11034, February 26, 1979), compliance times specified, unless already Accomplishment Instructions of Aviation
done. Partners Boeing Service Bulletin AP767–57–
(3) Will not affect intrastate aviation 010, Revision 11, dated April 3, 2017.
in Alaska, and (g) Repetitive Stringer L–9.5 Inspections, (2) At the applicable time specified in
(4) Will not have a significant Modification, Repair (Modification), paragraph 1.E., ‘‘Compliance,’’ of Aviation
economic impact, positive or negative, Repetitive Post-Repair Inspections, and Partners Boeing Service Bulletin AP767–57–
on a substantial number of small entities Repair 010, Revision 11, dated April 3, 2017, do a
under the criteria of the Regulatory (1) For Group 1 and Group 2 airplanes post-repair HFEC inspection for cracking, in
Flexibility Act. identified in Aviation Partners Boeing accordance with Part 9 of the
Service Bulletin AP767–57–010, Revision 11, Accomplishment Instructions of Aviation
List of Subjects in 14 CFR Part 39 dated April 3, 2017: At the applicable time Partners Boeing Service Bulletin AP767–57–
specified in paragraph 1.E., ‘‘Compliance,’’ of 010, Revision 11, dated April 3, 2017; and
Air transportation, Aircraft, Aviation Aviation Partners Boeing Service Bulletin repeat the inspection thereafter at the
safety, Incorporation by reference, AP767–57–010, Revision 11, dated April 3, applicable times specified in paragraph 1.E.,
Safety. 2017, except as required by paragraph (j)(1) ‘‘Compliance,’’ of Aviation Partners Boeing
of this AD: Do a high frequency eddy current Service Bulletin AP767–57–010, Revision 11,
Adoption of the Amendment dated April 3, 2017.
(HFEC) inspection for cracking of the lower
Accordingly, under the authority outboard wing skin at stringer L–9.5, in (3) If any crack is found during any
accordance with Part 1 of the inspection required by paragraph
delegated to me by the Administrator, (g)(1)(i)(C)(2) of this AD, repair before further
the FAA amends 14 CFR part 39 as Accomplishment Instructions of Aviation
Partners Boeing Service Bulletin AP767–57– flight using a method approved in
follows: accordance with the procedures specified in
010, Revision 11, dated April 3, 2017.
(i) For airplanes on which ‘‘Condition 1’’ paragraph (k) of this AD.
PART 39—AIRWORTHINESS is found, as defined in the Accomplishment (D) Do the actions required by paragraphs
DIRECTIVES Instructions of Aviation Partners Boeing (g)(1)(i)(D)(1) and (g)(1)(i)(D)(2) of this AD,
Service Bulletin AP767–57–010, Revision 11, and do all applicable actions required by
■ 1. The authority citation for part 39 dated April 3, 2017, during any inspection paragraph (g)(1)(i)(D)(3) of this AD.
continues to read as follows: required by paragraph (g)(1) or (g)(1)(i)(A) of (1) Before further flight, repair (modify) in
this AD: Do the applicable actions required accordance with Part 11 of the
Authority: 49 U.S.C. 106(g), 40113, 44701.
by paragraph (g)(1)(i)(A), (g)(1)(i)(B), Accomplishment Instructions of Aviation
§ 39.13 [Amended] (g)(1)(i)(C), or (g)(1)(i)(D) of this AD. Partners Boeing Service Bulletin AP767–57–
(A) Repeat the inspection specified in 010, Revision 11, dated April 3, 2017.
■ 2. The FAA amends § 39.13 by adding paragraph (g)(1) of this AD thereafter at the (2) At the applicable time specified in
the following new airworthiness applicable times specified in paragraph 1.E., paragraph 1.E., ‘‘Compliance,’’ of Aviation
directive (AD): ‘‘Compliance,’’ of Aviation Partners Boeing Partners Boeing Service Bulletin AP767–57–
Service Bulletin AP767–57–010, Revision 11, 010, Revision 11, dated April 3, 2017, do a
2018–11–14 The Boeing Company: post-repair HFEC inspection for cracking, in
dated April 3, 2017.
Amendment 39–19302; Docket No. accordance with Part 13 of the
(B) Do the applicable actions required by
FAA–2015–1421; Product Identifier Accomplishment Instructions of Aviation
paragraphs (g)(1)(i)(B)(1), (g)(1)(i)(B)(2), and
2014–NM–177–AD. Partners Boeing Service Bulletin AP767–57–
(g)(1)(i)(B)(3) of this AD.
(a) Effective Date (1) Before further flight, do actions 010, Revision 11, dated April 3, 2017; and
(modifications and repair (modification)) in repeat the inspection thereafter at the
This AD is effective July 10, 2018.
accordance with Part 2, Part 3, Part 4, and applicable times specified in paragraph 1.E.,
(b) Affected ADs Part 5, as applicable, of the Accomplishment ‘‘Compliance,’’ of Aviation Partners Boeing
None. Instructions of Aviation Partners Boeing Service Bulletin AP767–57–010, Revision 11,
Service Bulletin AP767–57–010, Revision 11, dated April 3, 2017; except as required by
(c) Applicability dated April 3, 2017. paragraph (j)(4) of this AD.
This AD applies to The Boeing Company (2) For airplanes on which the repair (3) If any crack is found during any
Model 767–300 and –300F series airplanes, (modification) specified in Part 5 of Aviation inspection required by paragraph
certificated in any category, with Aviation Partners Boeing Service Bulletin AP767–57– (g)(1)(i)(D)(2) of this AD, repair before further
Partners Boeing winglets installed; as 010 was done: At the applicable time flight using a method approved in
identified in Aviation Partners Boeing specified in paragraph 1.E., ‘‘Compliance,’’ of accordance with the procedures specified in
Service Bulletin AP767–57–010, Revision 11, Aviation Partners Boeing Service Bulletin paragraph (k) of this AD.
dated April 3, 2017; and Aviation Partners AP767–57–010, Revision 11, dated April 3, (ii) For airplanes on which ‘‘Condition 2’’
Boeing Service Bulletin AP767–57–014, 2017, do a post-repair HFEC inspection for is found, as defined in the Accomplishment
Revision 1, dated April 12, 2017. cracking, in accordance with Part 12 of the Instructions of Aviation Partners Boeing
Accomplishment Instructions of Aviation Service Bulletin AP767–57–010, Revision 11,
(d) Subject Partners Boeing Service Bulletin AP767–57– dated April 3, 2017, during any inspection
Air Transport Association (ATA) of 010, Revision 11, dated April 3, 2017; and required by paragraph (g)(1) or (g)(1)(i)(A) of
America Code 57, Wings. repeat the inspection thereafter at the this AD: Do the actions required by
applicable times specified in paragraph 1.E., paragraph (g)(1)(ii)(A) or (g)(1)(ii)(B) of this
(e) Unsafe Condition ‘‘Compliance,’’ of Aviation Partners Boeing AD.
This AD was prompted by reports of Service Bulletin AP767–57–010, Revision 11, (A) Do the actions required by paragraphs
fatigue cracking in the lower outboard wing dated April 3, 2017. (g)(1)(ii)(A)(1) and (g)(1)(ii)(A)(2) of this AD,
skin at the inboard fastener of stringer L–9.5, (3) If any crack is found during any and do all applicable actions required by
and the lower outboard wing skin of stringer inspection required by paragraph paragraph (g)(1)(ii)(A)(3) of this AD.
L–6.5, on airplanes with winglets installed (g)(1)(i)(B)(2) of this AD, repair before further (1) Before further flight, repair (modify) in
amozie on DSK3GDR082PROD with RULES
per Supplemental Type Certificate flight using a method approved in accordance with Part 8 of the
ST01920SE. We are issuing this AD to accordance with the procedures specified in Accomplishment Instructions of Aviation
prevent fatigue cracking in the lower paragraph (k) of this AD. Partners Boeing Service Bulletin AP767–57–
outboard wing skin, which could result in (C) Do the actions required by paragraphs 010, Revision 11, dated April 3, 2017.
failure and subsequent separation of the wing (g)(1)(i)(C)(1) and (g)(1)(i)(C)(2) of this AD, (2) At the applicable time specified in
and winglet and consequent reduced and do all applicable actions required by paragraph 1.E., ‘‘Compliance,’’ of Aviation
controllability of the airplane. paragraph (g)(1)(i)(C)(3) of this AD. Partners Boeing Service Bulletin AP767–57–
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![Federal Register / Vol. 83, No. 108 / Tuesday, June 5, 2018 / Rules and Regulations 25891
in paragraph 1.E., ‘‘Compliance,’’ of Aviation AD requires repeating the post-repair HFEC (i) Aviation Partners Boeing Service
Partners Boeing Service Bulletin AP767–57– inspection in Part 13. Bulletin AP767–57–010, Revision 11, dated
014, Revision 1, dated April 12, 2017, except April 3, 2017.
(k) Alternative Methods of Compliance (ii) Aviation Partners Boeing Service
as required by paragraph (j)(2) of this AD, do
(AMOCs) Bulletin AP767–57–014, Revision 1, dated
a post-repair HFEC inspection for cracking,
in accordance with Part 3 of the (1) The Manager, Seattle ACO Branch, April 12, 2017.
Accomplishment Instructions of Aviation FAA, has the authority to approve AMOCs (3) For service information identified in
Partners Boeing Service Bulletin AP767–57– for this AD, if requested using the procedures this AD, contact Aviation Partners Boeing,
014, Revision 1, dated April 12, 2017, and found in 14 CFR 39.19. In accordance with 2811 S. 102nd Street, Suite 200, Seattle, WA
repeat the inspection thereafter at the 14 CFR 39.19, send your request to your 98168; telephone 206–762–1171; internet
applicable times specified in paragraph 1.E., principal inspector or local Flight Standards https://www.aviationpartnersboeing.com.
‘‘Compliance,’’ of Aviation Partners Boeing District Office, as appropriate. If sending (4) You may view this service information
Service Bulletin AP767–57–014, Revision 1, information directly to the manager of the at the FAA, Transport Standards Branch,
dated April 12, 2017. certification office, send it to the attention of 2200 South 216th St., Des Moines, WA. For
(iii) If any crack is found during any the person identified in paragraph (l) of this information on the availability of this
inspection required by paragraph (h)(3)(ii) of AD. Information may be emailed to: 9-ANM- material at the FAA, call 206–231–3195.
this AD, repair before further flight using a Seattle-ACO-AMOC-Requests@faa.gov. (5) You may view this service information
method approved in accordance with the (2) Before using any approved AMOC, that is incorporated by reference at the
procedures specified in paragraph (k) of this notify your appropriate principal inspector, National Archives and Records
AD. or lacking a principal inspector, the manager Administration (NARA). For information on
of the local flight standards district office/ the availability of this material at NARA, call
(i) Repair Approval certificate holding district office. 202–741–6030, or go to: http://
Repairs of the lower outboard wing skin (3) An AMOC that provides an acceptable www.archives.gov/federal-register/cfr/ibr-
that were approved after June 15, 2017, and level of safety may be used for any repair, locations.html.
before the effective date of this AD, by the modification, or alteration required by this
AD if it is approved by the Boeing Issued in Des Moines, Washington, on May
Boeing Commercial Airplanes Organization 21, 2018.
Designation Authorization (ODA) that has Commercial Airplanes ODA that has been
authorized by the Manager, Seattle ACO James Cashdollar,
been authorized by the Manager, Seattle ACO
Branch, are approved for the applicable Branch, to make those findings. To be Acting Director, System Oversight Division,
repairs required by paragraphs (g) and (h) of approved, the repair method, modification Aircraft Certification Service.
this AD. The ODA repairs will have post- deviation, or alteration deviation must meet [FR Doc. 2018–11825 Filed 6–4–18; 8:45 am]
installation inspection requirements in lieu the certification basis of the airplane, and the
BILLING CODE 4910–13–P
of the post-inspection instructions specified approval must specifically refer to this AD.
in Aviation Partners Boeing Service Bulletin (4) Except as required by paragraphs
(g)(1)(i)(B)(3), (g)(1)(i)(C)(3), (g)(1)(i)(D)(3),
AP767–57–010, Revision 11, dated April 3, DEPARTMENT OF TRANSPORTATION
(g)(1)(ii)(A)(3), (g)(1)(ii)(B)(3), (g)(1)(iii)(A)(3),
2017; and Aviation Partners Boeing Service
(g)(1)(iii)(B)(3), (g)(1)(iv), (g)(2), (h)(2)(iii),
Bulletin AP767–57–014, Revision 1, dated Federal Aviation Administration
and (h)(3)(iii) of this AD: For service
April 12, 2017.
information that contains steps that are
(j) Exceptions to Service Information labeled as Required for Compliance (RC), the 14 CFR Part 39
Specifications provisions of paragraphs (k)(4)(i) and
(k)(4)(ii) of this AD apply. [Docket No. FAA–2017–1099; Product
(1) Where paragraph 1.E., ‘‘Compliance,’’ of Identifier 2017–NM–093–AD; Amendment
Aviation Partners Boeing Service Bulletin (i) The steps labeled as RC, including
substeps under an RC step and any figures 39–19296; AD 2018–11–08]
AP767–57–010, Revision 11, dated April 3,
identified in an RC step, must be done to RIN 2120–AA64
2017, specifies a compliance time ‘‘after the
comply with the AD. If a step or substep is
issue date of Revision 11 of this service
labeled ‘‘RC Exempt,’’ then the RC Airworthiness Directives; The Boeing
bulletin,’’ this AD requires compliance
requirement is removed from that step or Company Airplanes
within the specified compliance time after
substep. An AMOC is required for any
the effective date of this AD.
(2) Where paragraph 1.E., ‘‘Compliance,’’ of
deviations to RC steps, including substeps AGENCY: Federal Aviation
and identified figures. Administration (FAA), DOT.
Aviation Partners Boeing Service Bulletin
(ii) Steps not labeled as RC may be ACTION: Final rule.
AP767–57–014, Revision 1, dated April 12,
deviated from using accepted methods in
2017, specifies a compliance time ‘‘after the accordance with the operator’s maintenance
initial issue date of this service bulletin,’’ this SUMMARY: We are adopting a new
or inspection program without obtaining airworthiness directive (AD) for certain
AD requires compliance within the specified approval of an AMOC, provided the RC steps,
compliance time after the effective date of including substeps and identified figures, can
The Boeing Company Model 767–200
this AD. still be done as specified, and the airplane and –300 series airplanes. This AD was
(3) For Condition 1 and Condition 2 can be put back in an airworthy condition. prompted by a report of two cracks at
airplanes: Where paragraph 1.E., a certain frame inner chord. This AD
‘‘Compliance,’’ of Aviation Partners Boeing (l) Related Information
requires a detailed inspection for any
Service Bulletin AP767–57–014, Revision 1, For more information about this AD,
dated April 12, 2017, specifies a compliance
material review board (MRB) filler
contact Allen Rauschendorfer, Aerospace installed in the area from the frame web
time for accomplishing the Part 3 HFEC Engineer, Airframe Section, FAA, Seattle
inspection of 18 months ‘‘after the initial ACO Branch, 2200 South 216th St., Des
to the stub-beam fitting at certain
issue date of this service bulletin,’’ the Moines, WA; phone and fax: 206–231–3528; stations to determine if the filler extends
required compliance time is 6,000 flight email: allen.rauschendorfer@faa.gov. above the frame-to-stub-beam joint, and
cycles or 18,000 flight hours, whichever applicable on-condition actions. We are
occurs first, after doing the Part 2 repair. (m) Material Incorporated by Reference
issuing this AD to address the unsafe
(4) For airplanes on which a stringer L–9.5 (1) The Director of the Federal Register condition on these products.
amozie on DSK3GDR082PROD with RULES
replacement was accomplished per Part 11 of approved the incorporation by reference
DATES: This AD is effective July 10,
Aviation Partners Boeing Service Bulletin (IBR) of the service information listed in this
AP767–57–010, Revision 11, dated April 3, paragraph under 5 U.S.C. 552(a) and 1 CFR 2018.
2017: Where Aviation Partners Boeing part 51. The Director of the Federal Register
Service Bulletin AP767–57–010, Revision 11, (2) You must use this service information approved the incorporation by reference
dated April 3, 2017, specifies repeating the as applicable to do the actions required by of a certain publication listed in this AD
post-repair HFEC inspection ‘‘in Part 9,’’ this this AD, unless the AD specifies otherwise. as of July 10, 2018.
VerDate Sep<11>2014 16:50 Jun 04, 2018 Jkt 244001 PO 00000 Frm 00011 Fmt 4700 Sfmt 4700 E:\FR\FM\05JNR1.SGM 05JNR1](https://thefederalregister.org/doc/83_FR_25993/page/7.svg)
Document Created: 2018-11-02 11:47:17
Document Modified: 2018-11-02 11:47:17
| 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 July 10, 2018. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA; phone and fax: 206-231-3528; email: [email protected] | |
| FR Citation | 83 FR 25885 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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