Airworthiness Directives; The Boeing Company Airplanes, 40511-40514 [2017-17543]

Download as PDF Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods: (k) Related Information • Federal eRulemaking Portal: Go to (1) For more information about this AD, http://www.regulations.gov. Follow the contact Muoi Vuong, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO instructions for submitting comments. Branch, 3960 Paramount Boulevard, • Fax: 202–493–2251. Lakewood, CA 90712–4137; phone: 562–627– • Mail: U.S. Department of 5205; fax: 562–627–5210; email: Transportation, Docket Operations, M– Muoi.Vuong@faa.gov. 30, West Building Ground Floor, Room (2) For service information identified in W12–140, 1200 New Jersey Avenue SE., this AD, contact Boeing Commercial Washington, DC 20590. Airplanes, Attention: Contractual & Data • Hand Delivery: Deliver to Mail Services (C&DS), 2600 Westminster Blvd., MC 110–SK57, Seal Beach, CA 90740–5600; address above between 9 a.m. and 5 telephone 562–797–1717; Internet https:// p.m., Monday through Friday, except www.myboeingfleet.com. You may view this Federal holidays. referenced service information at the FAA, For service information identified in Transport Standards Branch, 1601 Lind this NPRM, contact Boeing Commercial Avenue SW., Renton, WA. For information Airplanes, Attention: Contractual & Data on the availability of this material at the Services (C&DS), 2600 Westminster FAA, call 425–227–1221. Blvd., MC 110–SK57, Seal Beach, CA Issued in Renton, Washington, on August 90740–5600; telephone 562–797–1717; 10, 2017. Internet https:// Dionne Palermo, www.myboeingfleet.com. You may view Acting Director, System Oversight Division, this referenced service information at Aircraft Certification Service. the FAA, Transport Standards Branch, [FR Doc. 2017–17538 Filed 8–24–17; 8:45 am] 1601 Lind Avenue SW., Renton, WA. BILLING CODE 4910–13–P For information on the availability of this material at the FAA, call 425–227– DEPARTMENT OF TRANSPORTATION 1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. Federal Aviation Administration FAA–2017–0779. 14 CFR Part 39 Examining the AD Docket [Docket No. FAA–2017–0779; Product Identifier 2017–NM–040–AD] RIN 2120–AA64 Airworthiness Directives; The Boeing Company Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain The Boeing Company Model 787–8 airplanes. This proposed AD was prompted by reports of degraded bondline performance of co-bonded upper wing stringer-to-skin joints. This proposed AD would require repetitive inspections of certain upper wing stringers for any disbond and corrective actions, if necessary; and a terminating preventative modification of installing disbond arrestment (DBA) fasteners. This proposed AD would also require revising the inspection or maintenance program to incorporate an airworthiness limitation. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by October 10, 2017. pmangrum on DSK3GDR082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0779; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425– 917–6487; fax: 425–917–6590; email: allen.rauschendorfer@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0779; Product Identifier 2017– PO 00000 Frm 00017 Fmt 4702 Sfmt 4702 40511 NM–040–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We have received reports of degraded bond-line performance of co-bonded upper wing stringer-to-skin joints. The co-bonded upper wing stringer-to-skin joints were determined to have degraded bond-line performance due to the exposure of the bond surface with the use of BMS 8–308 peel ply to cure times that exceeded 4 hours at a temperature of 345 degrees Fahrenheit (F) plus or minus 10 F. The upper wing stringer-to-skin joint disbonding can reduce the structural capability to where it cannot sustain limit load, which could adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We have reviewed Boeing Alert Service Bulletin B787–81205– SB570030–00, Issue 001, dated March 17, 2017 (‘‘ASB B787–81205– SB570030–00, Issue 001’’). This service information describes procedures for inspection of certain upper wing stringers for any disbond and repairs; and for a preventative modification which consists of, depending on airplane configuration, applying copper foil to the upper wing at certain stringer and rib bay locations, installing DBA fasteners on the upper flanges of the upper wing stringers at the stringer and rib bay locations, applying cap seals to the DBA fasteners, and applying edge sealant to the stringers at the DBA fastener installation locations. We have also reviewed Airworthiness Limitation (AWL) 57–AWL–13, ‘‘Inspection Requirements for In-Tank Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,’’ of Boeing 787 Special Compliance Items/ Airworthiness Limitations, D011Z009– 03–04, dated February 2017. This service information describes tasks for inspecting in-tank fasteners and edge seals near DBA fastener installations of lightning zone 2. E:\FR\FM\25AUP1.SGM 25AUP1 40512 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 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. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require accomplishing the actions specified in the service information described previously, except as discussed under ‘‘Differences Between this Proposed AD and the Service Information.’’ For information on the procedures and compliance times in ASB B787–81205– SB570030–00, Issue 001, see this service information at http:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0779. This AD requires revisions to certain operator maintenance documents to include new actions (e.g., inspections). Compliance with these actions is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by this proposed AD, the operator may not be able to accomplish the actions described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (l) of this proposed AD. The request should include a description of changes to the required actions that will ensure the continued damage tolerance of the affected structure. The phrase ‘‘corrective actions’’ is used in this proposed AD. Corrective actions correct or address any condition found. Corrective actions in an AD could include, for example, repairs. Differences Between This Proposed AD and the Service Information ASB B787–81205–SB570030–00, Issue 001, specifies to contact the manufacturer for certain instructions, but this proposed AD would require using repair methods, modification deviations, and alteration deviations in one of the following ways: • In accordance with a method that we approve; or • Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Explanation of Applicability In the applicability of this proposed AD, we refer to the airplanes identified in ASB B787–81205–SB570030–00, Issue 001. In addition, we have included line numbers 10, 13, 15, 16, 17, 18, and 19 in the applicability of this proposed AD because those line numbers are included in the applicability for AWL 57–AWL–13. Those line numbers are not listed in ASB B787–81205– SB570030–00, Issue 001, and the actions specified in ASB B787–81205– SB570030–00, Issue 001 are not required for those line numbers because the actions in the service information were completed during production. Costs of Compliance We estimate that this proposed AD affects 24 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Inspection ............................................... 49 work-hours × $85 per hour = $4,165 per inspection cycle. Up to 352 work-hours × $85 per hour = $29,920. 1 work-hour × $85 per hour = $85 ........ Modification ............................................ Maintenance or Inspection Program Revision. pmangrum on DSK3GDR082PROD with PROPOSALS We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. Subtitle VII: Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701: ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 Cost per product Cost on U.S. operators 1,902 $4,165 per inspection cycle. Up to $31,822 ........ $99,960 per inspection cycle. Up to $763,728. 0 $85 ......................... $2,040. Parts cost $0 is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. This proposed AD is issued in accordance with authority delegated by the Executive Director, Aircraft Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance of ADs is normally a function of the Compliance and Airworthiness Division, but during this transition period, the Executive Director has delegated the authority to issue ADs applicable to transport category airplanes to the Director of the System Oversight Division. Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would not have a PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify this proposed regulation: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866, (2) Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979), (3) Will not affect intrastate aviation in Alaska, and (4) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. E:\FR\FM\25AUP1.SGM 25AUP1 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ The Boeing Company: Docket No. FAA– 2017–0779; Product Identifier 2017– NM–040–AD. (a) Comments Due Date We must receive comments by October 10, 2017. (b) Affected ADs None. (c) Applicability This AD applies to The Boeing Company Model 787–8 airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin B787–81205–SB570030–00, Issue 001, dated March 17, 2017 (‘‘ASB B787–81205–SB570030–00, Issue 001’’), and line numbers 10, 13, 15, 16, 17, 18, and 19. (d) Subject Air Transport Association (ATA) of America Code 57; Wings. (e) Unsafe Condition This AD was prompted by reports of degraded bond-line performance of cobonded upper wing stringer-to-skin joints. We are issuing this AD to prevent upper wing stringer-to-skin joint disbonding, which can reduce the structural integrity of the airplane. pmangrum on DSK3GDR082PROD with PROPOSALS (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Inspections and Corrective Actions For airplanes identified in ASB B787– 81205–SB570030–00, Issue 001: Except as specified in paragraph (k)(1) of this AD, at the applicable time specified in paragraph 5., ‘‘Compliance,’’ of ASB B787–81205– SB570030–00, Issue 001: Do an ultrasonic inspection for any disbond on the left side and right side upper wing stringers; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of ASB B787–81205–SB570030– 00, Issue 001, except as specified in paragraph (k)(2) of this AD. Do all applicable corrective actions before further flight. VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 Repeat the inspection of the upper wing stringers thereafter at the applicable intervals specified in paragraph 5., ‘‘Compliance,’’ of ASB B787–81205–SB570030–00, Issue 001 until the actions required by paragraph (j) of this AD are done. (h) Maintenance or Inspection Program Revision (1) For airplanes identified in ASB B787– 81205–SB570030–00, Issue 001: Prior to or concurrently with accomplishing the actions required by paragraph (g) of this AD, revise the inspection or maintenance program, as applicable, to incorporate Airworthiness Limitation (AWL) 57–AWL–13. ‘‘Inspection Requirements for In-Tank Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,’’ of Boeing 787 Special Compliance Items/ Airworthiness Limitations, D011Z009–03–04, dated February 2017. The initial compliance time for accomplishing the tasks specified in AWL 57–AWL–13 is within 24,000 flight cycles or 12 years, whichever occurs first, after accomplishing the actions specified in ASB B787–81205–SB570030–00, Issue 001. (2) For airplanes having line numbers 10, 13, and 15 through 19 inclusive: Within 60 days after the effective date of this AD, revise the inspection or maintenance program, as applicable, to incorporate AWL 57–AWL–13, ‘‘Inspection Requirements for In-Tank Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,’’ of Boeing 787 Special Compliance Items/Airworthiness Limitations, D011Z009–03–04, dated February 2017. The initial compliance time for accomplishing the tasks specified in AWL 57–AWL–13 is prior to the accumulation of 24,000 total flight cycles or within 12 years after the date of issuance of the original airworthiness certificate or date of issuance of the original export certificate of airworthiness, whichever occurs first. (i) No Alternative Actions or Intervals After the action required by paragraph (h) of this AD has been done, no alternative actions (e.g., inspections) or intervals may be used unless the actions or intervals are approved as an AMOC in accordance with the procedures specified in paragraph (l) of this AD. (j) Inspection and Modification For airplanes identified in ASB B787– 81205–SB570030–00, Issue 001, that have not done ‘‘PART 3: PREVENTIVE MODIFICATION’’ of the Accomplishment Instructions of ASB B787–81205–SB570030– 00, Issue 001, at all of the unrepaired areas of the upper wing stringers: At the applicable time specified in paragraph 5., ‘‘Compliance,’’ of ASB B787–81205– SB570030–00, Issue 001, do the actions specified in paragraphs (j)(1) and (j)(2) of this AD, in accordance with the Accomplishment Instructions of ASB B787–81205–SB570030– 00, Issue 001, except as specified in paragraph (k)(2) of this AD. Doing the actions required by this paragraph terminates the repetitive inspections required by paragraph (g) of this AD. (1) Do an ultrasonic inspection for any disbond on the left side and right side upper PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 40513 wing stringers, and do all applicable corrective actions. Do all applicable corrective actions before further flight. (2) Do the preventative modification in accordance with ‘‘PART 3: PREVENTIVE MODIFICATION’’ of the Accomplishment Instructions of ASB B787–81205–SB570030– 00, Issue 001. (k) Exceptions to Service Information (1) Where paragraph 5., ‘‘Compliance,’’ of ASB B787–81205–SB570030–00, Issue 001, specifies a compliance time ‘‘after the Issue 001 date of this service bulletin,’’ this AD requires compliance within the specified compliance time after the effective date of this AD. (2) Although ASB B787–81205–SB570030– 00, Issue 001, specifies to contact Boeing for repair instructions, and specifies that action as ‘‘RC’’ (Required for Compliance), this AD requires repair before further flight using a method approved in accordance with the procedures specified in paragraph (l) of this AD. (l) 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 (m)(1) of this AD. Information may be emailed to: 9ANM-Seattle-ACO-AMOC-Requests@faa.gov. (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, 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 (k)(2) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (l)(4)(i) and (l)(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 E:\FR\FM\25AUP1.SGM 25AUP1 40514 Federal Register / Vol. 82, No. 164 / Friday, August 25, 2017 / Proposed Rules 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. (m) Related Information (1) For more information about this AD, contact Allen Rauschendorfer, Aerospace Engineer, Airframe Branch, FAA, Seattle ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917– 6487; fax: 425–917–6590; email: allen.rauschendorfer@faa.gov. (2) For 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. You may view this referenced service information at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. Issued in Renton, Washington, on August 9, 2017. Dionne Palermo, Acting Director, System Oversight Division, Aircraft Certification Service. [FR Doc. 2017–17543 Filed 8–24–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0719; Product Identifier 2017–NE–22–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Division Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Pratt & Whitney Division (PW) PW4074, PW4074D, PW4077, PW4077D, PW4084D, PW4090, and PW4090–3 turbofan engines. This proposed AD was prompted by the discovery of multiple cracked outer diffuser cases. This proposed AD would require initial and repetitive inspections to detect cracks in the outer diffuser case and removal from service of cases that fail inspection. We are proposing this AD to address the unsafe condition on these products. DATES: We must receive comments on this proposed AD by September 25, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR pmangrum on DSK3GDR082PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 14:55 Aug 24, 2017 Jkt 241001 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact Pratt & Whitney Division, 400 Main St., East Hartford, CT 06118; phone: 800–565–0140; fax: 860–565–5442. You may view this service information at the FAA, Engine and Propeller Standards Branch, Policy and Innovation Division, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. 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–2017– 0719; 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 NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer, FAA, ECO Branch, Compliance and Airworthiness Division,1200 District Avenue, Burlington, MA 01803; phone: 781–238–7105; fax: 781–238–7199; email: jo-ann.theriault@faa.gov. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0719; Directorate Identifier 2017– NE–22–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. PO 00000 Frm 00020 Fmt 4702 Sfmt 4702 We will post all comments we receive, without change, to http:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We were notified of the discovery of multiple cracked outer diffuser cases. This proposed AD requires initial and repetitive inspections to detect cracks in the outer diffuser case and removal from service of cases that fail inspection. This condition, if not corrected, could result in failure of the outer diffuser case, uncontained case release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed PW Service Bulletin (SB) No. PW4G–112–A72–347, dated March, 31, 2017. This PW SB provides guidance on performing outer diffuser case fluorescent penetrant inspections (FPI). 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. Other Related Service Information We reviewed PW4000 Series (112 Inch) Engine Cleaning, Inspection and Repair (CIR) Manual, Part Number 51A750, Revision Number 74, section 72–41–13, Inspection/Check-02, dated July 15, 2017. This manual section provides guidance on performing the high sensitivity FPI of the outer diffuser case at piece-part exposure. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require initial and repetitive inspections to detect cracks in the outer diffuser case and removal from service of cases that fail inspection. Costs of Compliance We estimate that this proposed AD affects 121 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: E:\FR\FM\25AUP1.SGM 25AUP1

Agencies

[Federal Register Volume 82, Number 164 (Friday, August 25, 2017)]
[Proposed Rules]
[Pages 40511-40514]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-17543]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0779; Product Identifier 2017-NM-040-AD]
RIN 2120-AA64


Airworthiness Directives; The Boeing Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain The Boeing Company Model 787-8 airplanes. This proposed AD was 
prompted by reports of degraded bond-line performance of co-bonded 
upper wing stringer-to-skin joints. This proposed AD would require 
repetitive inspections of certain upper wing stringers for any disbond 
and corrective actions, if necessary; and a terminating preventative 
modification of installing disbond arrestment (DBA) fasteners. This 
proposed AD would also require revising the inspection or maintenance 
program to incorporate an airworthiness limitation. We are proposing 
this AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by October 10, 
2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, 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 
Standards Branch, 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-2017-0779.

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-2017-
0779; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street address for the Docket 
Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Allen Rauschendorfer, Aerospace 
Engineer, Airframe Branch, FAA, Seattle ACO Branch, 1601 Lind Avenue 
SW., Renton, WA 98057-3356; phone: 425-917-6487; fax: 425-917-6590; 
email: allen.rauschendorfer@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0779; 
Product Identifier 2017-NM-040-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD because of those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    We have received reports of degraded bond-line performance of co-
bonded upper wing stringer-to-skin joints. The co-bonded upper wing 
stringer-to-skin joints were determined to have degraded bond-line 
performance due to the exposure of the bond surface with the use of BMS 
8-308 peel ply to cure times that exceeded 4 hours at a temperature of 
345 degrees Fahrenheit (F) plus or minus 10 F. The upper wing stringer-
to-skin joint disbonding can reduce the structural capability to where 
it cannot sustain limit load, which could adversely affect the 
structural integrity of the airplane.

Related Service Information Under 1 CFR Part 51

    We have reviewed Boeing Alert Service Bulletin B787-81205-SB570030-
00, Issue 001, dated March 17, 2017 (``ASB B787-81205-SB570030-00, 
Issue 001''). This service information describes procedures for 
inspection of certain upper wing stringers for any disbond and repairs; 
and for a preventative modification which consists of, depending on 
airplane configuration, applying copper foil to the upper wing at 
certain stringer and rib bay locations, installing DBA fasteners on the 
upper flanges of the upper wing stringers at the stringer and rib bay 
locations, applying cap seals to the DBA fasteners, and applying edge 
sealant to the stringers at the DBA fastener installation locations.
    We have also reviewed Airworthiness Limitation (AWL) 57-AWL-13, 
``Inspection Requirements for In-Tank Fasteners and Edge Seal near 
Disbond Arrestment (DBA) Fastener Installations of Lightning Zone 2,'' 
of Boeing 787 Special Compliance Items/Airworthiness Limitations, 
D011Z009-03-04, dated February 2017. This service information describes 
tasks for inspecting in-tank fasteners and edge seals near DBA fastener 
installations of lightning zone 2.

[[Page 40512]]

    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.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require accomplishing the actions specified 
in the service information described previously, except as discussed 
under ``Differences Between this Proposed AD and the Service 
Information.'' For information on the procedures and compliance times 
in ASB B787-81205-SB570030-00, Issue 001, see this service information 
at http://www.regulations.gov by searching for and locating Docket No. 
FAA-2017-0779.
    This AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections). Compliance with 
these actions is required by 14 CFR 91.403(c). For airplanes that have 
been previously modified, altered, or repaired in the areas addressed 
by this proposed AD, the operator may not be able to accomplish the 
actions described in the revisions. In this situation, to comply with 
14 CFR 91.403(c), the operator must request approval for an alternative 
method of compliance according to paragraph (l) of this proposed AD. 
The request should include a description of changes to the required 
actions that will ensure the continued damage tolerance of the affected 
structure.
    The phrase ``corrective actions'' is used in this proposed AD. 
Corrective actions correct or address any condition found. Corrective 
actions in an AD could include, for example, repairs.

Differences Between This Proposed AD and the Service Information

    ASB B787-81205-SB570030-00, Issue 001, specifies to contact the 
manufacturer for certain instructions, but this proposed AD would 
require using repair methods, modification deviations, and alteration 
deviations in one of the following ways:
     In accordance with a method that we approve; or
     Using data that meet the certification basis of the 
airplane, and that have been approved by the Boeing Commercial 
Airplanes Organization Designation Authorization (ODA) whom we have 
authorized to make those findings.

Explanation of Applicability

    In the applicability of this proposed AD, we refer to the airplanes 
identified in ASB B787-81205-SB570030-00, Issue 001. In addition, we 
have included line numbers 10, 13, 15, 16, 17, 18, and 19 in the 
applicability of this proposed AD because those line numbers are 
included in the applicability for AWL 57-AWL-13. Those line numbers are 
not listed in ASB B787-81205-SB570030-00, Issue 001, and the actions 
specified in ASB B787-81205-SB570030-00, Issue 001 are not required for 
those line numbers because the actions in the service information were 
completed during production.

Costs of Compliance

    We estimate that this proposed AD affects 24 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection.....................  49 work-hours x $85 per              $0  $4,165 per          $99,960 per
                                  hour = $4,165 per                        inspection cycle.   inspection cycle.
                                  inspection cycle.
Modification...................  Up to 352 work-hours x            1,902  Up to $31,822.....  Up to $763,728.
                                  $85 per hour = $29,920.
Maintenance or Inspection        1 work-hour x $85 per                 0  $85...............  $2,040.
 Program Revision.                hour = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This proposed AD is issued in accordance with authority delegated 
by the Executive Director, Aircraft Certification Service, as 
authorized by FAA Order 8000.51C. In accordance with that order, 
issuance of ADs is normally a function of the Compliance and 
Airworthiness Division, but during this transition period, the 
Executive Director has delegated the authority to issue ADs applicable 
to transport category airplanes to the Director of the System Oversight 
Division.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

[[Page 40513]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13   [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

The Boeing Company: Docket No. FAA-2017-0779; Product Identifier 
2017-NM-040-AD.

(a) Comments Due Date

    We must receive comments by October 10, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to The Boeing Company Model 787-8 airplanes, 
certificated in any category, as identified in Boeing Alert Service 
Bulletin B787-81205-SB570030-00, Issue 001, dated March 17, 2017 
(``ASB B787-81205-SB570030-00, Issue 001''), and line numbers 10, 
13, 15, 16, 17, 18, and 19.

(d) Subject

    Air Transport Association (ATA) of America Code 57; Wings.

(e) Unsafe Condition

    This AD was prompted by reports of degraded bond-line 
performance of co-bonded upper wing stringer-to-skin joints. We are 
issuing this AD to prevent upper wing stringer-to-skin joint 
disbonding, which can reduce the structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspections and Corrective Actions

    For airplanes identified in ASB B787-81205-SB570030-00, Issue 
001: Except as specified in paragraph (k)(1) of this AD, at the 
applicable time specified in paragraph 5., ``Compliance,'' of ASB 
B787-81205-SB570030-00, Issue 001: Do an ultrasonic inspection for 
any disbond on the left side and right side upper wing stringers; 
and do all applicable corrective actions; in accordance with the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, except as specified in paragraph (k)(2) of this AD. Do all 
applicable corrective actions before further flight. Repeat the 
inspection of the upper wing stringers thereafter at the applicable 
intervals specified in paragraph 5., ``Compliance,'' of ASB B787-
81205-SB570030-00, Issue 001 until the actions required by paragraph 
(j) of this AD are done.

(h) Maintenance or Inspection Program Revision

    (1) For airplanes identified in ASB B787-81205-SB570030-00, 
Issue 001: Prior to or concurrently with accomplishing the actions 
required by paragraph (g) of this AD, revise the inspection or 
maintenance program, as applicable, to incorporate Airworthiness 
Limitation (AWL) 57-AWL-13. ``Inspection Requirements for In-Tank 
Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener 
Installations of Lightning Zone 2,'' of Boeing 787 Special 
Compliance Items/Airworthiness Limitations, D011Z009-03-04, dated 
February 2017. The initial compliance time for accomplishing the 
tasks specified in AWL 57-AWL-13 is within 24,000 flight cycles or 
12 years, whichever occurs first, after accomplishing the actions 
specified in ASB B787-81205-SB570030-00, Issue 001.
    (2) For airplanes having line numbers 10, 13, and 15 through 19 
inclusive: Within 60 days after the effective date of this AD, 
revise the inspection or maintenance program, as applicable, to 
incorporate AWL 57-AWL-13, ``Inspection Requirements for In-Tank 
Fasteners and Edge Seal near Disbond Arrestment (DBA) Fastener 
Installations of Lightning Zone 2,'' of Boeing 787 Special 
Compliance Items/Airworthiness Limitations, D011Z009-03-04, dated 
February 2017. The initial compliance time for accomplishing the 
tasks specified in AWL 57-AWL-13 is prior to the accumulation of 
24,000 total flight cycles or within 12 years after the date of 
issuance of the original airworthiness certificate or date of 
issuance of the original export certificate of airworthiness, 
whichever occurs first.

(i) No Alternative Actions or Intervals

    After the action required by paragraph (h) of this AD has been 
done, no alternative actions (e.g., inspections) or intervals may be 
used unless the actions or intervals are approved as an AMOC in 
accordance with the procedures specified in paragraph (l) of this 
AD.

(j) Inspection and Modification

    For airplanes identified in ASB B787-81205-SB570030-00, Issue 
001, that have not done ``PART 3: PREVENTIVE MODIFICATION'' of the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, at all of the unrepaired areas of the upper wing stringers: At 
the applicable time specified in paragraph 5., ``Compliance,'' of 
ASB B787-81205-SB570030-00, Issue 001, do the actions specified in 
paragraphs (j)(1) and (j)(2) of this AD, in accordance with the 
Accomplishment Instructions of ASB B787-81205-SB570030-00, Issue 
001, except as specified in paragraph (k)(2) of this AD. Doing the 
actions required by this paragraph terminates the repetitive 
inspections required by paragraph (g) of this AD.
    (1) Do an ultrasonic inspection for any disbond on the left side 
and right side upper wing stringers, and do all applicable 
corrective actions. Do all applicable corrective actions before 
further flight.
    (2) Do the preventative modification in accordance with ``PART 
3: PREVENTIVE MODIFICATION'' of the Accomplishment Instructions of 
ASB B787-81205-SB570030-00, Issue 001.

(k) Exceptions to Service Information

    (1) Where paragraph 5., ``Compliance,'' of ASB B787-81205-
SB570030-00, Issue 001, specifies a compliance time ``after the 
Issue 001 date of this service bulletin,'' this AD requires 
compliance within the specified compliance time after the effective 
date of this AD.
    (2) Although ASB B787-81205-SB570030-00, Issue 001, specifies to 
contact Boeing for repair instructions, and specifies that action as 
``RC'' (Required for Compliance), this AD requires repair before 
further flight using a method approved in accordance with the 
procedures specified in paragraph (l) of this AD.

(l) 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 (m)(1) of this AD. Information may be 
emailed to: 9-ANM-Seattle-ACO-AMOC-Requests@faa.gov.
    (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, 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 (k)(2) of this AD: For 
service information that contains steps that are labeled as Required 
for Compliance (RC), the provisions of paragraphs (l)(4)(i) and 
(l)(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

[[Page 40514]]

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.

(m) Related Information

    (1) For more information about this AD, contact Allen 
Rauschendorfer, Aerospace Engineer, Airframe Branch, FAA, Seattle 
ACO Branch, 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-
917-6487; fax: 425-917-6590; email: allen.rauschendorfer@faa.gov.
    (2) For 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. You may view this referenced service 
information at the FAA, Transport Standards Branch, 1601 Lind Avenue 
SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on August 9, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-17543 Filed 8-24-17; 8:45 am]
 BILLING CODE 4910-13-P