82 FR 26573 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 82, Issue 109 (June 8, 2017)
Federal Aviation Administration
Federal Register Volume 82, Issue 109 (June 8, 2017)
| Page Range | 26573-26576 | |
| FR Document | 2017-11131 |
[Federal Register Volume 82, Number 109 (Thursday, June 8, 2017)] [Rules and Regulations] [Pages 26573-26576] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2017-11131] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-9115; Directorate Identifier 2016-NM-068-AD; Amendment 39-18903; AD 2017-11-04] 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 all The Boeing Company Model 767-200, -300, and -400ER series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that the fuselage skin lap splices are subject to widespread fatigue damage (WFD). This AD requires repetitive inspections to detect any crack in the fuselage skin at the skin lap splices, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective July 13, 2017. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 13, 2017. ADDRESSES: For service information identified in this final rule, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA 90740-5600; telephone: 562-797-1717; Internet: https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016- 9115. 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-2016- 9115; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Docket Management Facility, U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6447; fax: 425-917-6590; 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 all The Boeing Company Model 767-200, -300, and -400ER series airplanes. The NPRM published in the Federal Register on September 28, 2016 (81 FR 66553). The NPRM was prompted by an evaluation by the DAH indicating that the fuselage skin lap splices are subject to WFD. The NPRM proposed to require repetitive inspections to detect any crack in the fuselage skin at the skin lap splices, and repair of any crack found during the inspection. We are issuing this AD to detect and correct cracks at the fuselage skin lap splice, which can rapidly link up, possibly resulting in rapid decompression and loss of structural integrity of the airplane. Comments We gave the public the opportunity to participate in developing this AD. The following presents the comments received on the NPRM and the FAA's response to each comment. Support for the NPRM Boeing and another commenter, Connor Blevins, stated their support for the content of the NPRM. Effect of Winglets on Accomplishment of the Proposed Actions Aviation Partners Boeing stated that accomplishing the Supplemental Type Certificate (STC) ST01920SE does not affect the actions specified in the NPRM. We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as (c)(1) in this AD and added paragraph (c)(2) to state that installation of STC ST01920SE does not affect the ability to accomplish the actions required by this final rule. Therefore, for airplanes on which STC ST01920SE is installed, a ``change in [[Page 26574]] product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. Request for Clarification of Requirements United Airlines (UAL) requested that we clarify whether Boeing Alert Service Bulletin 767-53A0264, Revision 1, dated April 25, 2016 (``ASB 767-53A0264 R1'') or the structural repair manual (SRM) takes precedence for inspection requirements and whether the operator is able to choose which inspection method to utilize. UAL pointed out that Part 3 of ASB 767-53A0264 R1 specifies high frequency eddy current (HFEC) for the initial and repeat inspections, but the corresponding SRM repair provides the option of HFEC or low frequency eddy current inspections. We agree that clarification is necessary. Note (a) of tables 1 through 9 of paragraph 1.E., ``Compliance,'' of ASB 767-53A0264 R1 terminates the AD-mandated inspections for any area under an approved repair. The repairs are evaluated with their own damage tolerance inspection program. The post-repair inspection program is different than the baseline inspections specified in Part 3 of ASB 767-53A0264 R1, and as mentioned previously, post-repair damage tolerance inspections are not required by this AD, but are airworthiness limitation items (ALIs) and are required by maintenance and operational rules. Any deviation from the post-repair ALI inspections requires FAA approval, but does not require an alternative method of compliance (AMOC). We have not revised this AD in this regard. Request for Clarification of Repetitive Inspection Intervals UAL requested that we clarify the repetitive inspection intervals for any Category B repair specified in the SRM and accomplished as specified in Part 8 of ASB 767-53A0264 R1. UAL pointed out that the Part 8 repetitive inspection intervals conflict with the inspection intervals of Category B repairs specified in the SRM. UAL specified that if a repair is accomplished at the times proposed in the NPRM, the repair is already past the initial inspection thresholds specified in the SRM. We agree that there is a conflict between the service information and the Category B repair specified in the SRM, and that clarification is necessary. We have coordinated with Boeing regarding this issue. ASB 767-53A0264 R1 refers to the SRM for these repair instructions. Boeing has revised and published temporary revisions to the SRM that address this issue and these revisions provide an inspection threshold based on flight cycles after repair installation. Additionally, we have revised paragraph (h) of this AD to clarify that the post-repair damage tolerance inspections are not required by this AD, but are ALIs and are required by maintenance and operational rules. Any deviation from the post-repair ALI inspections requires FAA approval, but does not require an AMOC. We have also redesignated subsequent paragraphs accordingly. Conclusion We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this AD with the changes described previously and minor editorial changes. We have determined that these minor changes:Are consistent with the intent that was proposed in the NPRM for correcting 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 AD. Related Service Information Under 1 CFR Part 51 We reviewed Boeing ASB 767-53A0264 R1. The service information describes procedures for repetitive inspections and repair for any crack in the fuselage skin at the skin lap splices. 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 332 airplanes of U.S. registry. We estimate the following costs to comply with this AD: Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections...................... 168 work-hours x $0 $14,280 per $4,740,960 per $85 per hour = inspection cycle.. inspection cycle. $14,280 per inspection cycle. ---------------------------------------------------------------------------------------------------------------- The size of the area that requires repair must be determined before material and work-hour costs can be estimated. Additionally, materials for repairs must be supplied by the operator. Therefore, we cannot provide cost estimates for the on-condition actions 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. 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 [[Page 26575]] 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): 2017-11-04 The Boeing Company: Amendment 39-18903; Docket No. FAA- 2016-9115; Directorate Identifier 2016-NM-068-AD. (a) Effective Date This AD is effective July 13, 2017. (b) Affected ADs None. (c) Applicability (1) This AD applies to The Boeing Company Model 767-200, -300, and -400ER series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 767-53A0264, Revision 1, dated April 25, 2016 (``ASB 767-53A0264 R1''). (2) Installation of Supplemental Type Certificate (STC) ST01920SE (http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgstc.nsf/0/59027F43B9A7486E86257B1D006591EE?OpenDocument&Highlight=st01920se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01920SE is installed, a ``change in product'' alternative method of compliance (AMOC) approval request is not necessary to comply with the requirements of 14 CFR 39.17. (d) Subject Air Transport Association (ATA) of America Code 53, Fuselage. (e) Unsafe Condition This AD was prompted by an evaluation by the design approval holder indicating that the fuselage skin lap splices are subject to widespread fatigue damage. We are issuing this AD to detect and correct cracks at the fuselage skin lap splice, which can rapidly link up, possibly resulting in rapid decompression and loss of structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Corrective Actions Except as specified by paragraph (i) of this AD, at the applicable times specified in paragraph 1.E., ``Compliance,'' of ASB 767-53A0264 R1: Do external surface high frequency eddy current (HFEC), internal surface HFEC, and external surface low frequency eddy current inspections, as applicable, to detect cracks in the fuselage skin lap splices, in accordance with the Accomplishment Instructions of ASB 767-53A0264 R1. If any crack is found during any inspection required by this AD, before further flight, repair in accordance with Part 8 of the Accomplishment Instructions of ASB 767-53A0264 R1. Repeat the inspections thereafter at the times specified in paragraph 1.E., ``Compliance,'' of ASB 767-53A0264 R1, as applicable. (h) AD Provisions for Part 26 Supplemental Inspections Repairs identified in Part 8 of ASB 767-53A0264 R1 specify post- modification airworthiness limitation inspections in compliance with 14 CFR 25.571(a)(3) at the modified locations, which support compliance with 14 CFR 121.1109(c)(2) or 129.109(b)(2). As airworthiness limitations, these inspections are required by maintenance and operational rules. It is therefore unnecessary to mandate them in this AD. Deviations from these inspections require FAA approval, but do not require an AMOC. (i) Service Information Exception Where ASB 767-53A0264 R1 specifies a compliance time ``after the original issue date of this service bulletin,'' this AD requires compliance within the specified compliance time after the effective date of this AD. (j) Credit for Previous Actions This paragraph provides credit for the actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 767- 53A0264, dated May 12, 2015. (k) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 ACO, send it to the attention of the person identified in paragraph (l)(1) of this AD. Information may be emailed to: [email protected]. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, 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 specified in paragraph (h) 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. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (l) Related Information (1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle ACO, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6447; fax: 425-917-6590; email: [email protected]. (2) Service information identified in this AD that is not incorporated by reference is available at the addresses specified in paragraphs (m)(3) and (m)(4) of this AD. (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) Boeing Alert Service Bulletin 767-53A0264, Revision 1, dated April 25, 2016. (ii) Reserved. (3) For Boeing service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Contractual & Data Services (C&DS), 2600 Westminster Blvd., MC 110 SK57, Seal Beach, CA 90740-5600; telephone: 562-797-1717; Internet: https://www.myboeingfleet.com. (4) You may view this service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. (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:// [[Page 26576]] www.archives.gov/federal-register/cfr/ibr-locations.html. Issued in Renton, Washington, on May 15, 2017. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2017-11131 Filed 6-7-17; 8:45 am] BILLING CODE 4910-13-P
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(or their delegated agent). You are required DEPARTMENT OF TRANSPORTATION other information. The address for the
to assure the product is airworthy before it Docket Office (phone: 800–647–5527) is
is returned to service. Federal Aviation Administration Docket Management Facility, U.S.
(h) Related Information Department of Transportation, Docket
14 CFR Part 39 Operations, M–30, West Building
Refer to MCAI European Aviation Safety Ground Floor, Room W12–140, 1200
Agency (EASA) AD No. 2017–0024, dated [Docket No. FAA–2016–9115; Directorate
Identifier 2016–NM–068–AD; Amendment New Jersey Avenue SE., Washington,
February 13, 2017, for related information. DC 20590.
39–18903; AD 2017–11–04]
The MCAI can be found in the AD docket on
FOR FURTHER INFORMATION CONTACT:
the Internet at https://www.regulations.gov/ RIN 2120–AA64
Wayne Lockett, Aerospace Engineer,
document?D=FAA-2017-0194-0002.
Airworthiness Directives; The Boeing Airframe Branch, ANM–120S, FAA,
(i) Material Incorporated by Reference Company Airplanes Seattle Aircraft Certification Office
(1) The Director of the Federal Register (ACO), 1601 Lind Avenue SW., Renton,
approved the incorporation by reference AGENCY: Federal Aviation WA 98057–3356; phone: 425–917–6447;
(IBR) of the service information listed in this Administration (FAA), DOT. fax: 425–917–6590; email:
paragraph under 5 U.S.C. 552(a) and 1 CFR ACTION: Final rule. wayne.lockett@faa.gov.
part 51. SUPPLEMENTARY INFORMATION:
(2) You must use this service information SUMMARY: We are adopting a new
airworthiness directive (AD) for all The Discussion
as applicable to do the actions required by
this AD, unless the AD specifies otherwise. Boeing Company Model 767–200, –300, We issued a notice of proposed
(i) Temporary Revision No. 38 to PC–12/ and –400ER series airplanes. This AD rulemaking (NPRM) to amend 14 CFR
47E Pilot’s Operating Handbook, Airplane was prompted by an evaluation by the part 39 by adding an AD that would
Flight Manual 02277, Section 2—Limitations, design approval holder (DAH) apply to all The Boeing Company Model
Report No: 02277, dated February 8, 2017. indicating that the fuselage skin lap 767–200, –300, and –400ER series
(ii) Reserved. splices are subject to widespread fatigue airplanes. The NPRM published in the
(3) For PILATUS AIRCRAFT LTD. service damage (WFD). This AD requires Federal Register on September 28, 2016
information identified in this AD, contact repetitive inspections to detect any (81 FR 66553). The NPRM was
PILATUS AIRCRAFT LTD., Customer crack in the fuselage skin at the skin lap prompted by an evaluation by the DAH
Support PC–12, CH–6371 Stans, Switzerland; splices, and corrective actions if indicating that the fuselage skin lap
phone: +41 41 619 33 33; fax: +41 41 619 73 necessary. We are issuing this AD to splices are subject to WFD. The NPRM
11; email: SupportPC12@pilatus- address the unsafe condition on these proposed to require repetitive
aircraft.com; Internet: www.pilatus- products. inspections to detect any crack in the
aircraft.com. DATES: This AD is effective July 13, fuselage skin at the skin lap splices, and
(4) You may view this service information 2017. repair of any crack found during the
at the FAA, Small Airplane Directorate, 901 The Director of the Federal Register inspection. We are issuing this AD to
Locust, Kansas City, Missouri 64106. For approved the incorporation by reference detect and correct cracks at the fuselage
information on the availability of this of a certain publication listed in this AD skin lap splice, which can rapidly link
material at the FAA, call (816) 329–4148. In as of July 13, 2017. up, possibly resulting in rapid
addition, you can access this service decompression and loss of structural
ADDRESSES: For service information
information on the Internet at http:// integrity of the airplane.
www.regulations.gov by searching for and identified in this final rule, contact
locating Docket No. FAA–2017–0194. Boeing Commercial Airplanes, Comments
(5) You may view this service information Attention: Contractual & Data Services We gave the public the opportunity to
that is incorporated by reference at the (C&DS), 2600 Westminster Blvd., MC participate in developing this AD. The
National Archives and Records 110 SK57, Seal Beach, CA 90740–5600; following presents the comments
Administration (NARA). For information on telephone: 562–797–1717; Internet: received on the NPRM and the FAA’s
the availability of this material at NARA, call https://www.myboeingfleet.com. You response to each comment.
202–741–6030, or go to: http:// may view this referenced service
www.archives.gov/federal-register/cfr/ibr- information at the FAA, Transport Support for the NPRM
locations.html. Airplane Directorate, 1601 Lind Avenue Boeing and another commenter,
SW., Renton, WA. For information on Connor Blevins, stated their support for
Issued in Kansas City, Missouri, on May
the availability of this material at the the content of the NPRM.
26, 2017.
FAA, call 425–227–1221. It is also
Pat Mullen, available on the Internet at http:// Effect of Winglets on Accomplishment
Acting Manager, Small Airplane Directorate, www.regulations.gov by searching for of the Proposed Actions
Aircraft Certification Service. and locating Docket No. FAA–2016– Aviation Partners Boeing stated that
[FR Doc. 2017–11411 Filed 6–7–17; 8:45 am] 9115. accomplishing the Supplemental Type
BILLING CODE 4910–13–P Certificate (STC) ST01920SE does not
Examining the AD Docket affect the actions specified in the
You may examine the AD docket on NPRM.
the Internet at http:// We concur with the commenter. We
asabaliauskas on DSKBBXCHB2PROD with RULES
www.regulations.gov by searching for have redesignated paragraph (c) of the
and locating Docket No. FAA–2016– proposed AD as (c)(1) in this AD and
9115; or in person at the Docket added paragraph (c)(2) to state that
Management Facility between 9 a.m. installation of STC ST01920SE does not
and 5 p.m., Monday through Friday, affect the ability to accomplish the
except Federal holidays. The AD docket actions required by this final rule.
contains this AD, the regulatory Therefore, for airplanes on which STC
evaluation, any comments received, and ST01920SE is installed, a ‘‘change in
VerDate Sep<11>2014 16:16 Jun 07, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\08JNR1.SGM 08JNR1](https://thefederalregister.org/doc/82_FR_26682/page/1.svg)
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under the criteria of the Regulatory (f) Compliance (3) An AMOC that provides an acceptable
Flexibility Act. Comply with this AD within the level of safety may be used for any repair,
compliance times specified, unless already modification, or alteration required by this
List of Subjects in 14 CFR Part 39 done. AD if it is approved by the Boeing
Commercial Airplanes Organization
Air transportation, Aircraft, Aviation (g) Repetitive Inspections and Corrective Designation Authorization (ODA) that has
safety, Incorporation by reference, Actions been authorized by the Manager, Seattle
Safety. Except as specified by paragraph (i) of this ACO, to make those findings. To be
AD, at the applicable times specified in approved, the repair method, modification
Adoption of the Amendment paragraph 1.E., ‘‘Compliance,’’ of ASB 767– deviation, or alteration deviation must meet
53A0264 R1: Do external surface high the certification basis of the airplane, and the
Accordingly, under the authority frequency eddy current (HFEC), internal approval must specifically refer to this AD.
delegated to me by the Administrator, surface HFEC, and external surface low (4) Except as specified in paragraph (h) of
the FAA amends 14 CFR part 39 as frequency eddy current inspections, as this AD: For service information that
follows: applicable, to detect cracks in the fuselage contains steps that are labeled as Required
skin lap splices, in accordance with the for Compliance (RC), the provisions of
PART 39—AIRWORTHINESS Accomplishment Instructions of ASB 767– paragraphs (k)(4)(i) and (k)(4)(ii) of this AD
DIRECTIVES 53A0264 R1. If any crack is found during any apply.
inspection required by this AD, before further (i) The steps labeled as RC, including
flight, repair in accordance with Part 8 of the substeps under an RC step and any figures
■ 1. The authority citation for part 39 Accomplishment Instructions of ASB 767– identified in an RC step, must be done to
continues to read as follows: 53A0264 R1. Repeat the inspections comply with the AD. An AMOC is required
Authority: 49 U.S.C. 106(g), 40113, 44701. thereafter at the times specified in paragraph for any deviations to RC steps, including
1.E., ‘‘Compliance,’’ of ASB 767–53A0264 substeps and identified figures.
§ 39.13 [Amended] R1, as applicable. (ii) Steps not labeled as RC may be
(h) AD Provisions for Part 26 Supplemental deviated from using accepted methods in
■ 2. The FAA amends § 39.13 by adding accordance with the operator’s maintenance
Inspections
the following new airworthiness or inspection program without obtaining
directive (AD): Repairs identified in Part 8 of ASB 767– approval of an AMOC, provided the RC steps,
53A0264 R1 specify post-modification including substeps and identified figures, can
2017–11–04 The Boeing Company: airworthiness limitation inspections in still be done as specified, and the airplane
Amendment 39–18903; Docket No. compliance with 14 CFR 25.571(a)(3) at the can be put back in an airworthy condition.
FAA–2016–9115; Directorate Identifier modified locations, which support
2016–NM–068–AD. compliance with 14 CFR 121.1109(c)(2) or (l) Related Information
129.109(b)(2). As airworthiness limitations, (1) For more information about this AD,
(a) Effective Date these inspections are required by contact Wayne Lockett, Aerospace Engineer,
This AD is effective July 13, 2017. maintenance and operational rules. It is Airframe Branch, ANM–120S, FAA, Seattle
therefore unnecessary to mandate them in ACO, 1601 Lind Avenue SW., Renton, WA
(b) Affected ADs
this AD. Deviations from these inspections 98057–3356; phone: 425–917–6447; fax: 425–
None. require FAA approval, but do not require an 917–6590; email: wayne.lockett@faa.gov.
AMOC. (2) Service information identified in this
(c) Applicability
(1) This AD applies to The Boeing (i) Service Information Exception AD that is not incorporated by reference is
available at the addresses specified in
Company Model 767–200, –300, and –400ER Where ASB 767–53A0264 R1 specifies a
paragraphs (m)(3) and (m)(4) of this AD.
series airplanes, certificated in any category, compliance time ‘‘after the original issue date
as identified in Boeing Alert Service Bulletin of this service bulletin,’’ this AD requires (m) Material Incorporated by Reference
767–53A0264, Revision 1, dated April 25, compliance within the specified compliance
(1) The Director of the Federal Register
2016 (‘‘ASB 767–53A0264 R1’’). time after the effective date of this AD.
approved the incorporation by reference
(2) Installation of Supplemental Type (j) Credit for Previous Actions (IBR) of the service information listed in this
Certificate (STC) ST01920SE (http:// paragraph under 5 U.S.C. 552(a) and 1 CFR
rgl.faa.gov/Regulatory_and_Guidance_ This paragraph provides credit for the
actions required by paragraph (g) of this AD, part 51.
Library/rgstc.nsf/0/59027F43B9A7486E (2) You must use this service information
86257B1D006591EE?Open if those actions were performed before the
effective date of this AD using Boeing Alert as applicable to do the actions required by
Document&Highlight=st01920se) does not this AD, unless the AD specifies otherwise.
Service Bulletin 767–53A0264, dated May
affect the ability to accomplish the actions (i) Boeing Alert Service Bulletin 767–
12, 2015.
required by this AD. Therefore, for airplanes 53A0264, Revision 1, dated April 25, 2016.
on which STC ST01920SE is installed, a (k) Alternative Methods of Compliance (ii) Reserved.
‘‘change in product’’ alternative method of (AMOCs) (3) For Boeing service information
compliance (AMOC) approval request is not (1) The Manager, Seattle Aircraft identified in this AD, contact Boeing
necessary to comply with the requirements of Certification Office (ACO), FAA, has the Commercial Airplanes, Attention:
14 CFR 39.17. authority to approve AMOCs for this AD, if Contractual & Data Services (C&DS), 2600
requested using the procedures found in 14 Westminster Blvd., MC 110 SK57, Seal
(d) Subject
CFR 39.19. In accordance with 14 CFR 39.19, Beach, CA 90740–5600; telephone: 562–797–
Air Transport Association (ATA) of send your request to your principal inspector 1717; Internet: https://
America Code 53, Fuselage. or local Flight Standards District Office, as www.myboeingfleet.com.
appropriate. If sending information directly (4) You may view this service information
(e) Unsafe Condition
to the manager of the ACO, send it to the at the FAA, Transport Airplane Directorate,
asabaliauskas on DSKBBXCHB2PROD with RULES
This AD was prompted by an evaluation by attention of the person identified in 1601 Lind Avenue SW., Renton, WA. For
the design approval holder indicating that paragraph (l)(1) of this AD. Information may information on the availability of this
the fuselage skin lap splices are subject to be emailed to: 9-ANM-Seattle-ACO-AMOC- material at the FAA, call 425–227–1221.
widespread fatigue damage. We are issuing Requests@faa.gov. (5) You may view this service information
this AD to detect and correct cracks at the (2) Before using any approved AMOC, that is incorporated by reference at the
fuselage skin lap splice, which can rapidly notify your appropriate principal inspector, National Archives and Records
link up, possibly resulting in rapid or lacking a principal inspector, the manager Administration (NARA). For information on
decompression and loss of structural of the local flight standards district office/ the availability of this material at NARA, call
integrity of the airplane. certificate holding district office. 202–741–6030, or go to: http://
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![26576 Federal Register / Vol. 82, No. 109 / Thursday, June 8, 2017 / Rules and Regulations
www.archives.gov/federal-register/cfr/ibr- p.m., Monday through Friday, except loss of the inboard flap. Continued safe
locations.html. Federal holidays. flight and landing could be adversely
Issued in Renton, Washington, on May 15, For service information identified in affected after the departure of a flap
2017. this final rule, contact Boeing during takeoff or landing. We are
Michael Kaszycki, Commercial Airplanes, Attention: issuing this AD to correct the unsafe
Acting Manager, Transport Airplane Contractual & Data Services (C&DS), condition on these products.
Directorate, Aircraft Certification Service. 2600 Westminster Blvd., MC 110–SK57,
Related Service Information Under 1
[FR Doc. 2017–11131 Filed 6–7–17; 8:45 am] Seal Beach, CA 90740–5600; telephone
CFR Part 51
BILLING CODE 4910–13–P
562–797–1717; Internet https://
www.myboeingfleet.com. You may view We reviewed Boeing Alert Service
this referenced service information at Bulletin 767–57A0134, dated May 27,
DEPARTMENT OF TRANSPORTATION the FAA, Transport Airplane 2016. The service information describes
Directorate, 1601 Lind Avenue SW., procedures for repetitive inspections for
Federal Aviation Administration Renton, WA. For information on the damage caused by interference between
availability of this material at the FAA, the 6–9 drive arm assembly and the 4–
14 CFR Part 39 call 425–227–1221. It is also available 5 actuator crank arm assembly on the
on the Internet at http:// inboard flap outboard support assembly
[Docket No. FAA–2017–0531; Directorate
Identifier 2016–NM–178–AD; Amendment www.regulations.gov by searching for number 3 and number 6, and related
39–18916; AD 2017–12–01] and locating Docket No. FAA–2017– investigative and corrective actions.
0531. This service information is reasonably
RIN 2120–AA64 available because the interested parties
Examining the AD Docket have access to it through their normal
Airworthiness Directives; The Boeing course of business or by the means
You may examine the AD docket on
Company Airplanes identified in the ADDRESSES section.
the Internet at http://
AGENCY: Federal Aviation www.regulations.gov by searching for FAA’s Determination
Administration (FAA), DOT. and locating Docket No. FAA–2017–
0531; or in person at the Docket We are issuing this AD because we
ACTION: Final rule; request for
Management Facility between 9 a.m. evaluated all the relevant information
comments.
and 5 p.m., Monday through Friday, and determined the unsafe condition
SUMMARY: We are adopting a new except Federal holidays. The AD docket described previously is likely to exist or
airworthiness directive (AD) for certain contains this AD, the regulatory develop in other products of the same
The Boeing Company Model 767–200 evaluation, any comments received, and type design.
series airplanes. This AD requires other information. The street address for AD Requirements
repetitive inspections for damage of a the Docket Office (phone: 800–647–
certain drive arm assembly, and related 5527) is in the ADDRESSES section. This AD requires accomplishing the
investigative and corrective actions if Comments will be available in the AD actions specified in the service
necessary. This AD was prompted by a docket shortly after receipt. information described previously,
report indicating that during an except as discussed under ‘‘Differences
FOR FURTHER INFORMATION CONTACT:
inspection associated with a flap, the Between this AD and the Service
Wayne Lockett, Aerospace Engineer, Information.’’ For information on the
extend overtravel stops on an actuator Airframe Branch, ANM–120S, FAA,
crank arm assembly were making procedures and compliance times, see
Seattle Aircraft Certification Office this service information at http://
contact with an adjacent drive arm (ACO), 1601 Lind Avenue SW., Renton,
assembly when the flaps were retracted. www.regulations.gov by searching for
WA 98057–3356; phone: 425–917–6447; and locating Docket No. FAA–2017–
We are issuing this AD to address the fax: 425–917–6590; email:
unsafe condition on these products. 0531.
wayne.lockett@faa.gov. The phrase ‘‘related investigative
DATES: This AD is effective June 23, SUPPLEMENTARY INFORMATION: actions’’ is used in this AD. Related
2017. investigative actions are follow-on
The Director of the Federal Register Discussion
actions that (1) are related to the
approved the incorporation by reference We have received a report indicating primary action, and (2) further
of a certain publication listed in this AD that during an inspection of the investigate the nature of any condition
as of June 23, 2017. outboard support assembly number 3 of found. Related investigative actions in
We must receive comments on this the inboard flap of the left wing, an an AD could include, for example,
AD by July 24, 2017. operator observed that the extend inspections.
ADDRESSES: You may send comments, overtravel stops on the 4–5 actuator The phrase ‘‘corrective actions’’ is
using the procedures found in 14 CFR crank arm assembly were making used in this AD. Corrective actions
11.43 and 11.45, by any of the following contact with the adjacent 6–9 drive arm correct or address any condition found.
methods: assembly when the flaps were totally Corrective actions in an AD could
• Federal eRulemaking Portal: Go to retracted. The problem occurred with include, for example, repairs.
http://www.regulations.gov. Follow the the installation of 767–400ER flaps,
instructions for submitting comments. modified as specified in supplemental Differences Between This AD and the
asabaliauskas on DSKBBXCHB2PROD with RULES
• Fax: 202–493–2251. type certificate (STC) ST01329WI–D, on Service Information
• Mail: U.S. Department of 767–200 airplanes. This condition, if Boeing Alert Service Bulletin 767–
Transportation, Docket Operations, not corrected, could result in 57A0134, dated May 27, 2016, specifies
M–30, West Building Ground Floor, interference between the 6–9 drive arm to contact the manufacturer for certain
Room W12–140, 1200 New Jersey assembly and the 4–5 actuator crank instructions, but this AD would require
Avenue SE., Washington, DC 20590. arm assembly, which causes a fatigue using repair methods, modification
• Hand Delivery: Deliver to Mail load on the 5–7 link that could result in deviations, and alteration deviations in
address above between 9 a.m. and 5 failure of the 5–7 link and subsequent one of the following ways:
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Document Created: 2018-11-14 10:06:50
Document Modified: 2018-11-14 10:06:50
| 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 13, 2017. | |
| Contact | Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6447; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 82 FR 26573 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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