83 FR 33817 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 83, Issue 138 (July 18, 2018)
Federal Aviation Administration
Federal Register Volume 83, Issue 138 (July 18, 2018)
| Page Range | 33817-33821 | |
| FR Document | 2018-13362 |
[Federal Register Volume 83, Number 138 (Wednesday, July 18, 2018)] [Rules and Regulations] [Pages 33817-33821] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2018-13362] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2018-0073; Product Identifier 2017-NM-100-AD; Amendment 39-19318; AD 2018-13-06] 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 in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of a certain stringer. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin at the inboard segment of a certain stringer, and repair if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective August 22, 2018. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of August 22, 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 [[Page 33818]] on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-0073. Examining the AD Docket You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018- 0073; 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 98198; 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 February 9, 2018 (83 FR 5738). The NPRM was prompted by reports of fatigue cracking in the lower outboard wing skin at the farthest outboard fastener of the inboard segment of stringer L- 9.5 on airplanes with winglets installed per Supplemental Type Certificate ST01920SE. The NPRM proposed to require repetitive high frequency eddy current (HFEC) inspections for cracking of the lower outboard wing skin at the inboard segment of a certain stringer, and repair if necessary. 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 NPRM and the FAA's response to each comment. Aviation Partners Boeing (APB) concurred with the NPRM. Request To Provide Credit for Previously Approved Repairs All Nippon Airways (ANA) and American Airlines (AAL) asked that credit be given for repair deviations approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) using 8100-9 forms dated after June 15, 2017. ANA stated that Boeing ODAs will be using APB analysis methodology to evaluate and approve the repairs. ANA and AAL stated that Boeing indicated in Multi-Operator Message MOM-MOM- 17-0480-01B, dated August 29, 2017, that repairs approved after June 15, 2017, would be acceptable as alternative methods of compliance (AMOCs) to the final rule if using the referenced service information. Both commenters asked that credit language for those previously approved repairs be added to the content of the proposed AD. We agree with the commenters' requests for the reasons provided. The revised APB analysis methodology was approved by the FAA on June 15, 2017. Therefore, we have added paragraph (i)(2) to this AD to include that approval. Request To Allow Alternative Oversize Fastener Holes AAL asked that we allow oversize fasteners of at least 1/64 inch to be installed at all fastener locations common to inboard stringer L- 9.5. AAL stated that the referenced service information and the APB modification drawing are very restrictive regarding oversize fasteners that are outside of the five critical fasteners at each end of inboard stringer L-9.5. AAL added that hole damage during fastener removal at the existing stringer L-9.5 is common. We do not agree with the commenter's request. This type of deviation would require an engineering evaluation to assess inboard stringer L-9.5 and the skin fastener locations to determine if it is feasible for the oversize fasteners to be installed. However, under the provisions of paragraph (j) of this AD, we will consider requests for approval of an AMOC, if sufficient data are submitted to substantiate that installing 1/64-inch oversize fasteners at all fastener locations common to inboard stringer L-9.5 will provide an acceptable level of safety. We have not changed this AD in this regard. Request To Add Alternative Alodine Type Delta Air Lines (Delta) asked that we add a new paragraph to the proposed AD specifying that Alodine coating ``Bonderite M-CR 600 Aero'' is an acceptable alternative to ``Alodine 600'' coating. Delta stated that APB Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, calls out Alodine 600 in paragraph 2.B.2, ``Parts and Materials Supplied by the Operator,'' and in Drawing 767-9420, Sheet 1, in paragraph 3.B, Part 2, Steps 4 and 5, as an ``RC'' (Required for Compliance) step. Delta noted that the name of the Alodine coating ``Alodine 600'' has been changed to ``Bonderite M-CR 600 Aero.'' Delta added that the FAA issued a Special Airworthiness Information Bulletin (SAIB) that cited an AMOC for the use of Bonderite products. We agree with the commenter's request, for the reason provided. Alodine products made by Henkel manufacturing have been renamed to Bonderite. We issued SAIB HQ-18-09, dated February 5, 2018, which cited the AMOC that allows the use of Henkel Bonderite products as an alternative to Henkel Alodine products. We have revised paragraphs (g)(1)(ii)(A) and (g)(2)(i) of this AD to allow the use of Bonderite M- CR 600 Aero and Bonderite M-CR 600 RTU Aero as an alternative coating. Requests To Clarify Compliance Time Definition United Airlines (UAL) and Delta asked that we clarify the ``Compliance Times'' definition specified in the preamble of the NPRM. The commenters stated that the initial compliance time is defined as 1,500 flight cycles or 7,500 flight cycles after winglet installation, but it should be 1,500 flight cycles or 7,500 flight hours after winglet installation. The commenters noted that this should be corrected to be consistent with the compliance time specified in the referenced service information. We agree with the commenters that the compliance time definition in the NPRM is inaccurate, and should specify ``The initial compliance time is the later of: 1,500 flight cycles or 7,500 flight hours after winglet installation, whichever occurs first.'' This language provided notice regarding compliance times that were specified in the referenced service information. The compliance time is correct in the referenced service information and does not conflict with this AD. Since that section of the preamble does not reappear in the final rule, no change to this AD is necessary. 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 [[Page 33819]] previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for addressing the unsafe condition; and Do not add any additional burden upon the public than was already proposed in the NPRM. 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 AP767-57-013, Revision 1, dated April 11, 2017. The service information describes procedures for an HFEC inspection for cracking of the lower outboard wing skin at the inboard segment of stringer L-9.5, and on-condition actions that include repetitive HFEC inspections, a preventive modification (repair) that includes installing new stringers, repetitive post-modification (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 -------------------------------------------------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product Cost on U.S. operators -------------------------------------------------------------------------------------------------------------------------------------------------------- HFEC Inspections..................... 1 work-hour x $85 per $0 $85, per inspection $11,900, per inspection cycle. hour = $85, per cycle. inspection cycle. -------------------------------------------------------------------------------------------------------------------------------------------------------- Estimated Costs--On-Condition Actions ---------------------------------------------------------------------------------------------------------------- Action Labor cost Parts cost Cost per product ---------------------------------------------------------------------------------------------------------------- Preventive Modification (Repair).... 50 work-hours x $85 $0 $4,250. per hour = $4,250. Post-modification (repair) 1 work-hour x $85 per 0 $85, per inspection cycle. Inspections. hour = $85, per inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for on-condition repairs that might be necessary as a result of the post-modification (repair) inspections specified in this AD. According to the manufacturer, some of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we have included all available costs in our cost estimate. 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, (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): 2018-13-06 The Boeing Company: Amendment 39-19318; Docket No. FAA- 2018-0073; Product Identifier 2017-NM-100-AD. [[Page 33820]] (a) Effective Date This AD is effective August 22, 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 AP767-57-013, Revision 1, dated April 11, 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 farthest outboard fastener of the inboard segment of stringer L-9.5 on airplanes with winglets installed per Supplemental Type Certificate ST01920SE. 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. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections, Preventive Modification (Repair), Repetitive Post-Modification (Repair) Inspections, and Repair At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, except as required by paragraph (h) of this AD: Do a high frequency eddy current (HFEC) inspection for cracking of the lower outboard wing skin at the inboard segment of stringer L-9.5, in accordance with Part 1 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (1) For airplanes on which ``Condition 1'' is found, as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, during any inspection required by the introductory text of paragraph (g) or paragraph (g)(1)(i) of this AD: Do the actions required by paragraph (g)(1)(i) or (g)(1)(ii) of this AD. (i) Repeat the inspection specified in the introductory text of paragraph (g) of this AD thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. (ii) Do the actions required by paragraphs (g)(1)(ii)(A) and (g)(1)(ii)(B) of this AD: (A) Before further flight, do the preventive modification in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. The use of Alodine 600-RTU, Henkel Bonderite M-CR 600 Aero, or Henkel Bonderite M-CR 600 RTU Aero coating is an acceptable alternative to Alodine 600 coating. Note 1 to paragraph (g)(1)(ii)(A) of this AD: Guidance on identifying alternative Henkel Bonderite Alodine coatings can also be found in Special Airworthiness Information Bulletin (SAIB) HQ-18- 09, dated February 5, 2018. The SAIB may be viewed online at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSAIB.nsf/0/F87909D65FCE4BFA8625822B005AE82A?OpenDocument&Highlight=hq-18-09. (B) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017; and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. (2) For airplanes on which ``Condition 2'' is found as defined in the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, during any inspection required by the introductory text of paragraph (g) or paragraph (g)(1)(i) of this AD: Do the actions required by paragraph (g)(2)(i) and (g)(2)(ii) of this AD. (i) Before further flight, repair in accordance with Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017. The use of Alodine 600-RTU, Henkel Bonderite M-CR 600 Aero, or Henkel Bonderite M-CR 600 RTU Aero coating is an acceptable alternative to Alodine 600 coating. Note 2 to paragraph (g)(2)(i) of this AD: Guidance on identifying alternative Henkel Bonderite Alodine coatings can also be found in SAIB HQ-18-09, dated February 5, 2018. The SAIB may be viewed online at http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgSAIB.nsf/0/F87909D65FCE4BFA8625822B005AE82A?OpenDocument&Highlight=hq-18-09. (ii) At the applicable time specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017, do an HFEC inspection for cracking, in accordance with Part 3 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017; and repeat the inspection thereafter at the applicable times specified in paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767- 57-013, Revision 1, dated April 11, 2017. (3) If any crack is found during any inspection required by paragraph (g)(1)(ii)(B) or (g)(2)(ii) of this AD, repair before further flight using a method approved in accordance with the procedures specified in paragraph (j) of this AD. Although Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 2017, specifies to contact Boeing for repair instructions, and specifies that action as ``RC'' (Required for Compliance), this AD requires repair as specified in this paragraph. (h) Exception to Service Information Specifications Where paragraph 1.E., ``Compliance,'' of Aviation Partners Boeing Service Bulletin AP767-57-013, Revision 1, dated April 11, 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. (i) Credit for Previous Actions (1) For Group 2 airplanes: This paragraph provides credit for the actions specified in Part 1 and Part 2 of the Accomplishment Instructions of Aviation Partners Boeing Service Bulletin AP767-57- 013, Revision 1, dated April 11, 2017, that are required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Aviation Partners Boeing Service Bulletin AP767-57-013, dated November 30, 2016. (2) Repairs of the lower outboard wing skin approved after June 15, 2017, and before the effective date of this AD, if approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, are approved for the applicable repairs required by paragraph (g) of this AD. (j) 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 (k) 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 Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO Branch, FAA, 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 paragraph (g)(3) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures [[Page 33821]] 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. (k) 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 98198; phone and fax: 206-231-3528; email: [email protected]. (l) 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 AP767-57-013, Revision 1, dated April 11, 2017. (ii) Reserved. (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 June 12, 2018. Michael Kaszycki, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2018-13362 Filed 7-17-18; 8:45 am] BILLING CODE 4910-13-P
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Manager, International Section, Transport as RC may be deviated from using accepted information on the availability of this
Standards Branch, FAA; or the EASA; or methods in accordance with the operator’s material at the FAA, call 206–231–3195.
Airbus’s EASA DOA: Accomplish repetitive maintenance or inspection program without (5) You may view this service information
SDIs within the compliance time defined in obtaining approval of an AMOC, provided that is incorporated by reference at the
those repair instructions for repetitive SDIs. the procedures and tests identified as RC can National Archives and Records
If no compliance time is identified in the be done and the airplane can be put back in Administration (NARA). For information on
repair instructions for repetitive SDIs, an airworthy condition. Any substitutions or the availability of this material at NARA, call
accomplish the repetitive SDIs required by changes to procedures or tests identified as 202–741–6030, or go to: http://
paragraph (i)(2) of this AD at the compliance RC require approval of an AMOC. www.archives.gov/federal-register/cfr/ibr-
times defined in figure 4 to paragraphs (i)(2) (4) Reporting Requirements: A federal locations.html.
and (l) of this AD. agency may not conduct or sponsor, and a
Issued in Des Moines, Washington, on June
(m) No Terminating Action person is not required to respond to, nor
12, 2018.
shall a person be subject to a penalty for
Modification or repair of an airplane, as failure to comply with a collection of Michael Kaszycki,
specified in paragraph (j) or (k) of this AD, information subject to the requirements of Acting Director, System Oversight Division,
does not constitute terminating action for the the Paperwork Reduction Act unless that Aircraft Certification Service.
repetitive inspections required by this AD, collection of information displays a current [FR Doc. 2018–13802 Filed 7–17–18; 8:45 am]
unless it is specified otherwise in a repair valid OMB Control Number. The OMB
method approved by the Manager, BILLING CODE 4910–13–P
Control Number for this information
International Section, Transport Standards collection is 2120–0056. Public reporting for
Branch, FAA; or the EASA; or Airbus’s EASA this collection of information is estimated to
DOA. If approved by the DOA, the approval be approximately 1 work-hour per response,
DEPARTMENT OF TRANSPORTATION
must include the DOA-authorized signature. including the time for reviewing instructions,
completing and reviewing the collection of
Federal Aviation Administration
(n) Reporting Requirement
information. All responses to this collection
Submit a report of the positive findings of 14 CFR Part 39
of information are mandatory. Comments
the inspections required by paragraphs (i)
and (j) of this AD to ‘‘Airbus Service Bulletin concerning the accuracy of this burden and [Docket No. FAA–2018–0073; Product
Reporting Online Application’’ on Airbus suggestions for reducing the burden should Identifier 2017–NM–100–AD; Amendment
World (https://w3.airbus.com/), at the be directed to the FAA at 800 Independence 39–19318; AD 2018–13–06]
applicable time specified in paragraph (n)(1) Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, RIN 2120–AA64
or (n)(2) of this AD.
(1) If the inspection was done on or after AES–200.
the effective date of this AD: Report within
Airworthiness Directives; The Boeing
(p) Related Information
30 days after that inspection. Company Airplanes
(1) Refer to Mandatory Continuing
(2) If the inspection was done before the AGENCY: Federal Aviation
Airworthiness Information (MCAI) EASA AD
effective date of this AD: Report within 30
days after the effective date of this AD. 2017–0099, dated June 8, 2017, for related Administration (FAA), DOT.
information. This MCAI may be found in the ACTION: Final rule.
(o) Other FAA AD Provisions AD docket on the internet at http://
(1) Alternative Methods of Compliance www.regulations.gov by searching for and SUMMARY: We are adopting a new
(AMOCs): The Manager, International locating Docket No. FAA–2017–1102. airworthiness directive (AD) for certain
Section, Transport Standards Branch, FAA, (2) For more information about this AD, The Boeing Company Model 767–300
has the authority to approve AMOCs for this contact Sanjay Ralhan, Aerospace Engineer, and –300F series airplanes. This AD was
AD, if requested using the procedures found International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
prompted by reports of fatigue cracking
in 14 CFR 39.19. In accordance with 14 CFR in the lower outboard wing skin at the
39.19, send your request to your principal Moines, WA 98198; telephone and fax 206–
inspector or local Flight Standards District 231–3223. farthest outboard fastener of the inboard
Office, as appropriate. If sending information (3) Service information identified in this segment of a certain stringer. This AD
directly to the manager of the International AD that is not incorporated by reference is requires repetitive high frequency eddy
Section, send it to the attention of the person available at the addresses specified in current (HFEC) inspections for cracking
identified in paragraph (p)(2) of this AD. paragraphs (q)(3) and (q)(4) of this AD. of the lower outboard wing skin at the
Information may be emailed to: 9-ANM-116- (q) Material Incorporated by Reference inboard segment of a certain stringer,
AMOC-REQUESTS@faa.gov. Before using and repair if necessary. We are issuing
any approved AMOC, notify your appropriate (1) The Director of the Federal Register
approved the incorporation by reference this AD to address the unsafe condition
principal inspector, or lacking a principal
inspector, the manager of the local flight (IBR) of the service information listed in this on these products.
standards district office/certificate holding paragraph under 5 U.S.C. 552(a) and 1 CFR DATES: This AD is effective August 22,
district office. part 51. 2018.
(2) Contacting the Manufacturer: As of the (2) You must use this service information The Director of the Federal Register
effective date of this AD, for any requirement as applicable to do the actions required by approved the incorporation by reference
in this AD to obtain corrective actions from this AD, unless this AD specifies otherwise. of a certain publication listed in this AD
a manufacturer, the action must be (i) Airbus Service Bulletin A320–57–1178,
Revision 03, including only Appendix 03,
as of August 22, 2018.
accomplished using a method approved by
the Manager, International Section, Transport both dated November 29, 2016. ADDRESSES: For service information
Standards Branch, FAA; or the EASA; or (ii) Airbus Service Bulletin A320–57–1200, identified in this final rule, contact
Airbus’s EASA DOA. If approved by the dated November 20, 2015. Aviation Partners Boeing, 2811 S 102nd
DOA, the approval must include the DOA- (3) For service information identified in Street, Suite 200, Seattle, WA 98168;
authorized signature. this AD, contact Airbus, Airworthiness telephone 206–762–1171; internet
(3) Required for Compliance (RC): Except Office—EIAS, Rond-Point Emile Dewoitine https://www.aviationpartners
amozie on DSK3GDR082PROD with RULES
as specified in paragraph (k) of this AD, if No: 2, 31700 Blagnac Cedex, France;
boeing.com. You may view this service
any service information contains procedures telephone +33 5 61 93 36 96; fax +33 5 61
or tests that are identified as RC, those 93 44 51; email account.airworth-eas@ information at the FAA, Transport
procedures and tests must be done to comply airbus.com; internet http://www.airbus.com. Standards Branch, 2200 South 216th St.,
with this AD; any procedures or tests that are (4) You may view this service information Des Moines, WA. For information on the
not identified as RC are recommended. Those at the FAA, Transport Standards Branch, availability of this material at the FAA,
procedures and tests that are not identified 2200 South 216th St., Des Moines, WA. For call 206–231–3195. It is also available
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previously and minor editorial changes. Related Service Information Under 1 modification (repair) HFEC inspections
We have determined that these minor CFR Part 51 for cracking, and repair. This service
changes: We reviewed APB Service Bulletin information is reasonably available
• Are consistent with the intent that AP767–57–013, Revision 1, dated April because the interested parties have
was proposed in the NPRM for 11, 2017. The service information access to it through their normal course
addressing the unsafe condition; and describes procedures for an HFEC of business or by the means identified
• Do not add any additional burden inspection for cracking of the lower in the ADDRESSES section.
upon the public than was already outboard wing skin at the inboard Costs of Compliance
proposed in the NPRM. segment of stringer L–9.5, and on-
We also determined that these condition actions that include repetitive We estimate that this AD affects 140
changes will not increase the economic HFEC inspections, a preventive airplanes of U.S. registry. We estimate
burden on any operator or increase the modification (repair) that includes the following costs to comply with this
scope of this final rule. installing new stringers, repetitive post- AD:
ESTIMATED COSTS—REQUIRED ACTIONS
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
HFEC Inspections .................. 1 work-hour × $85 per hour = $0 $85, per inspection cycle ...... $11,900, per inspection cycle.
$85, per inspection cycle.
ESTIMATED COSTS—ON-CONDITION ACTIONS
Cost per
Action Labor cost Parts cost product
Preventive Modification (Repair) ............................ 50 work-hours × $85 per hour = $4,250 ................ $0 $4,250.
Post-modification (repair) Inspections .................... 1 work-hour × $85 per hour = $85, per inspection 0 $85, per inspection
cycle. cycle.
We have received no definitive data products identified in this rulemaking (4) Will not have a significant
that would enable us to provide cost action. economic impact, positive or negative,
estimates for on-condition repairs that This AD is issued in accordance with on a substantial number of small entities
might be necessary as a result of the authority delegated by the Executive under the criteria of the Regulatory
post-modification (repair) inspections Director, Aircraft Certification Service, Flexibility Act.
specified in this AD. as authorized by FAA Order 8000.51C.
According to the manufacturer, some In accordance with that order, issuance List of Subjects in 14 CFR Part 39
of the costs of this AD may be covered of ADs is normally a function of the Air transportation, Aircraft, Aviation
under warranty, thereby reducing the Compliance and Airworthiness
cost impact on affected individuals. We safety, Incorporation by reference,
Division, but during this transition Safety.
do not control warranty coverage for period, the Executive Director has
affected individuals. As a result, we delegated the authority to issue ADs Adoption of the Amendment
have included all available costs in our applicable to transport category
cost estimate. airplanes and associated appliances to Accordingly, under the authority
Authority for This Rulemaking the Director of the System Oversight delegated to me by the Administrator,
Division. the FAA amends 14 CFR part 39 as
Title 49 of the United States Code follows:
specifies the FAA’s authority to issue Regulatory Findings
rules on aviation safety. Subtitle I, This AD will not have federalism PART 39—AIRWORTHINESS
section 106, describes the authority of implications under Executive Order DIRECTIVES
the FAA Administrator. Subtitle VII: 13132. This AD will not have a
Aviation Programs, describes in more substantial direct effect on the States, on ■ 1. The authority citation for part 39
detail the scope of the Agency’s the relationship between the national continues to read as follows:
authority. government and the States, or on the
We are issuing this rulemaking under Authority: 49 U.S.C. 106(g), 40113, 44701.
distribution of power and
the authority described in Subtitle VII,
responsibilities among the various § 39.13 [Amended]
Part A, Subpart III, Section 44701:
levels of government.
‘‘General requirements.’’ Under that ■ 2. The FAA amends § 39.13 by adding
section, Congress charges the FAA with For the reasons discussed above, I
certify that this AD: the following new airworthiness
promoting safe flight of civil aircraft in
(1) Is not a ‘‘significant regulatory directive (AD):
air commerce by prescribing regulations
amozie on DSK3GDR082PROD with RULES
for practices, methods, and procedures action’’ under Executive Order 12866, 2018–13–06 The Boeing Company:
the Administrator finds necessary for (2) Is not a ‘‘significant rule’’ under Amendment 39–19318; Docket No.
safety in air commerce. This regulation DOT Regulatory Policies and Procedures FAA–2018–0073; Product Identifier
is within the scope of that authority (44 FR 11034, February 26, 1979), 2017–NM–100–AD.
because it addresses an unsafe condition (3) Will not affect intrastate aviation
that is likely to exist or develop on in Alaska, and
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![Federal Register / Vol. 83, No. 138 / Wednesday, July 18, 2018 / Rules and Regulations 33821
identified in an RC step, must be done to DEPARTMENT OF TRANSPORTATION except Federal holidays. The AD docket
comply with the AD. If a step or substep is contains this AD, the regulatory
labeled ‘‘RC Exempt,’’ then the RC Federal Aviation Administration evaluation, any comments received, and
requirement is removed from that step or other information. The address for the
substep. An AMOC is required for any 14 CFR Part 39 Docket Office (telephone: 800–647–
deviations to RC steps, including substeps 5527) is Docket Management Facility,
[Docket No. FAA–2018–0111; Product
and identified figures. U.S. Department of Transportation,
Identifier 2017–NM–059–AD; Amendment
(ii) Steps not labeled as RC may be 39–19312; AD 2018–12–08] Docket Operations, M–30, West
deviated from using accepted methods in Building Ground Floor, Room W12–140,
accordance with the operator’s maintenance RIN 2120–AA64
1200 New Jersey Avenue SE,
or inspection program without obtaining Washington, DC 20590.
approval of an AMOC, provided the RC steps, Airworthiness Directives; Airbus
Airplanes FOR FURTHER INFORMATION CONTACT:
including substeps and identified figures, can
Vladimir Ulyanov, Aerospace Engineer,
still be done as specified, and the airplane AGENCY: Federal Aviation International Section, Transport
can be put back in an airworthy condition. Administration (FAA), Department of Standards Branch, FAA, 2200 South
(k) Related Information Transportation (DOT). 216th St., Des Moines, WA 98198;
For more information about this AD, ACTION: Final rule. telephone and fax: 206–231–3229.
contact Allen Rauschendorfer, Aerospace SUPPLEMENTARY INFORMATION:
Engineer, Airframe Section, FAA, Seattle
SUMMARY: We are superseding
Airworthiness Directive (AD) 2017–07– Discussion
ACO Branch, 2200 South 216th St., Des
Moines, WA 98198; phone and fax: 206–231–
07, which applied to certain Airbus We issued a notice of proposed
3528; email: allen.rauschendorfer@faa.gov. Model A330–200, A330–300, A340–200, rulemaking (NPRM) to amend 14 CFR
and A340–300 series airplanes. AD part 39 to supersede AD 2017–07–07,
(l) Material Incorporated by Reference 2017–07–07 required repetitive Amendment 39–18845 (82 FR 18547,
(1) The Director of the Federal Register inspections of certain fastener holes, April 20, 2017) (‘‘AD 2017–07–07’’). AD
approved the incorporation by reference and related investigative and corrective 2017–07–07 applied to certain Airbus
(IBR) of the service information listed in this actions if necessary. This AD retains the Model A330–200, A330–300, A340–200,
paragraph under 5 U.S.C. 552(a) and 1 CFR requirements of AD 2017–07–07 and and A340–300 series airplanes with
part 51. expands the applicability. This AD was manufacturer serial numbers (MSN)
(2) You must use this service information prompted by a report of cracking at 0176 through 0915 inclusive. The
as applicable to do the actions required by fastener holes located at frame (FR) 40 NPRM published in the Federal
this AD, unless the AD specifies otherwise. on the lower shell panel junction. We Register on February 20, 2018 (83 FR
(i) Aviation Partners Boeing Service are issuing this AD to address the unsafe 7117). The NPRM was prompted by a
Bulletin AP767–57–013, Revision 1, dated condition on these products. report of cracking at fastener holes
April 11, 2017. DATES: This AD is effective August 22, located at frame FR40 on the lower shell
(ii) Reserved. 2018. panel junction. The NPRM proposed to
(3) For service information identified in The Director of the Federal Register retain the requirements of AD 2017–07–
this AD, contact Aviation Partners Boeing, approved the incorporation by reference 07 and expand the applicability. We are
2811 S 102nd Street, Suite 200, Seattle, WA of certain publications listed in this AD issuing this AD to detect and correct
98168; telephone 206–762–1171; internet as of August 22, 2018. cracking at FR40 on the lower shell
https://www.aviationpartnersboeing.com.
ADDRESSES: For service information panel junction; such cracking could lead
(4) You may view this service information
identified in this final rule, contact to reduced structural integrity of the
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For Airbus SAS, Airworthiness Office— fuselage.
information on the availability of this EAL, 1 Rond Point Maurice Bellonte, The European Aviation Safety Agency
material at the FAA, call 206–231–3195. 31707 Blagnac Cedex, France; (EASA), which is the Technical Agent
(5) You may view this service information telephone: +33 5 61 93 36 96; fax: +33 for the Member States of the European
that is incorporated by reference at the 5 61 93 45 80; email: Union, has issued EASA AD 2017–0063,
National Archives and Records airworthiness.A330-A340@airbus.com; dated April 12, 2017 (referred to after
Administration (NARA). For information on internet: http://www.airbus.com. You this as the Mandatory Continuing
the availability of this material at NARA, call may view this referenced service Airworthiness Information, or ‘‘the
202–741–6030, or go to: http:// information at the FAA, Transport MCAI’’), to correct an unsafe condition
www.archives.gov/federal-register/cfr/ibr- Standards Branch, 2200 South 216th St., for certain Airbus Model A330–200,
locations.html. Des Moines, WA. For information on the A330–300, and A340–200 series
availability of this material at the FAA, airplanes, and Model A340–312 and
Issued in Des Moines, Washington, on June –313 airplanes. The MCAI states:
call 206–231–3195. It is also available
12, 2018.
on the internet at http:// During full scale fatigue test of the Frame
Michael Kaszycki, www.regulations.gov by searching for (FR) 40 to fuselage skin panel junction,
Acting Director, System Oversight Division, and locating Docket No. FAA–2018– fatigue damage was found. Corrective actions
Aircraft Certification Service. 0111. consisted of in-service installation of an
[FR Doc. 2018–13362 Filed 7–17–18; 8:45 am] internal reinforcing strap on the related
Examining the AD Docket junction, as currently required by DGAC
BILLING CODE 4910–13–P
You may examine the AD docket on [Direction Générale de l’Aviation Civile]
amozie on DSK3GDR082PROD with RULES
the internet at http:// France AD 1999–448–126(B), which refers to
Airbus Service Bulletin (SB) A340–53–4104
www.regulations.gov by searching for Revision 02, and [DGAC] AD 2001–070(B),
and locating Docket No. FAA–2018– which refers to Airbus SB A330–53–3093
0111; or in person at the Docket Revision 04; retrofit improvement of internal
Management Facility between 9 a.m. reinforcing strap fatigue life through
and 5 p.m., Monday through Friday, recommended Airbus SB A330–53–3145; and
VerDate Sep<11>2014 17:26 Jul 17, 2018 Jkt 244001 PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 E:\FR\FM\18JYR1.SGM 18JYR1](https://thefederalregister.org/doc/83_FR_33955/page/5.svg)
Document Created: 2018-11-06 10:24:39
Document Modified: 2018-11-06 10:24:39
| 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 August 22, 2018. | |
| Contact | Allen Rauschendorfer, Aerospace Engineer, Airframe Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206-231-3528; email: [email protected] | |
| FR Citation | 83 FR 33817 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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