Skip to Content

Rule

Airworthiness Directives; The Boeing Company Airplanes

Comments on this document are being accepted at Regulations.gov. Submit a formal comment

Document Details

Information about this document as published in the Federal Register.

Enhanced Content

Relevant information about this document from Regulations.gov provides additional context. This information is not part of the official Federal Register document.

Published Document

This document has been published in the Federal Register. Use the PDF linked in the document sidebar for the official electronic format.

Start Preamble

AGENCY:

Federal Aviation Administration (FAA), DOT.

ACTION:

Final rule.

SUMMARY:

We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 and -200PF series airplanes. This AD was prompted by an evaluation by the design approval holder (DAH) indicating that certain areas of the frame webs are subject to widespread fatigue damage (WFD). This AD requires inspections of the frame webs for any crack of any open coordinating holes, tooling holes, and insulation blanket attachment holes; repair if necessary; and modification of the frame webs at all open hole locations, which would terminate the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.

DATES:

This AD is effective July 25, 2017.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of July 25, 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 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-2016-9502.

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-2016-9502; 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 final rule, 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.

Start Further Info

FOR FURTHER INFORMATION CONTACT:

Muoi Vuong, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office (ACO), 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5205; fax: 562-627-5210; email: muoi.vuong@faa.gov.

End Further Info End Preamble Start Supplemental Information

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 757-200 and -200PF series airplanes. The NPRM published in the Federal Register on December 20, 2016 (81 FR 92742) (“the NPRM”). The NPRM was prompted by an evaluation by the DAH indicating that certain areas of the frame webs are subject to WFD. The NPRM proposed to require high frequency eddy current (HFEC) inspections of the frame webs for any crack in any open coordinating holes, tooling holes, and insulation blanket attachment holes; repair if necessary; and modification of the frame webs at all open hole locations, which would terminate the repetitive inspections. We are issuing this AD to prevent fatigue cracking that could result in reduced structural integrity of the airplane.

Comments

We gave the public the opportunity to participate in developing this AD. We have considered the comments received. Boeing Commercial Airplanes, FedEx, and United Airlines supported the NPRM.

Effect of Winglets on Accomplishment of the Proposed Actions

Aviation Partners Boeing stated that accomplishing the supplemental type certificate (STC) ST01518SE does not affect the actions specified in the proposed AD.

We concur with the commenter. We have redesignated paragraph (c) of the proposed AD as paragraph (c)(1) of this AD and added paragraph (c)(2) to this AD to state that installation of STC ST01518SE does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE 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.

Additional Change to Proposed AD

We have revised paragraph (g) of this AD to specify all compliance times, rather than referring to the service information because a certain compliance time specified in the service information is relative to the issue date of the service information. For this AD, that compliance time is relative to the effective date of this AD.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting this final rule with the changes described previously, and minor editorial changes. We have determined that these minor changes:

  • Are consistent with the intent that was proposed in the NPRM for correcting the unsafe condition; andStart Printed Page 27971
  • 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 Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016. The service information describes procedures for performing repetitive HFEC inspections of the frame webs for any crack of any open coordinating holes, tooling holes, and insulation blanket attachment holes; and modifying the frame webs between stringers S-20 and S-25. 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 74 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:

Estimated Costs

ActionLabor costParts costCost per productCost on U.S. operators
HFEC inspection68 work-hours × $85 per hour = $5,780 per inspection cycle$0$5,780 per inspection cycle$427,720 per inspection cycle.
Modification1 work-hour × $85 per hour = $851 08585.
1 Parts supplied by the operator.

We have received no definitive data that would enable us to 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 under the criteria of the Regulatory Flexibility Act.

Start List of Subjects

List of Subjects in 14 CFR Part 39

  • Air transportation
  • Aircraft
  • Aviation safety
  • Incorporation by reference
  • Safety
End List of Subjects

Adoption of the Amendment

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

Start Part

PART 39—AIRWORTHINESS DIRECTIVES

End Part Start Amendment Part

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

End Amendment Part Start Authority

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

End Authority
[Amended]
Start Amendment Part

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

End Amendment Part

2017-12-14 The Boeing Company: Amendment 39-18929; Docket No. FAA-2016-9502; Directorate Identifier 2016-NM-128-AD.

(a) Effective Date

This AD is effective July 25, 2017.

(b) Affected ADs

None.

(c) Applicability

(1) This AD applies to The Boeing Company Model 757-200 and -200PF series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016.

(2) Installation of Supplemental Type Certificate (STC) ST01518SE (http://rgl.faa.gov/​Regulatory_​and_​Guidance_​Library/​rgSTC.nsf/​0/​38B606833BBD98B386257FAA00602538?​OpenDocument&​Highlight=​st01518se) does not affect the ability to accomplish the actions required by this AD. Therefore, for airplanes on which STC ST01518SE 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 (DAH) indicating that the frame webs between stringers S-20 and S-25 on the left side and right side, from station (STA) 440 to STA 820 and from STA 1300 to STA 1701, are subject to widespread fatigue damage (WFD). We are issuing this AD to prevent fatigue cracking that could result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Repetitive High Frequency Eddy Current (HFEC) Inspections of the Frame Webs

Before the accumulation of 28,000 total flight cycles, or within 3,000 flight cycles after the effective date of this AD, whichever occurs later, do an HFEC inspection of the frame webs for any crack in any open coordinating holes, tooling holes, and insulation blanket attachment holes, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016. If any cracking is found, repair before further flight Start Printed Page 27972using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Repeat the inspection at intervals not to exceed 12,000 flight cycles.

(h) Modification of the Frame Webs

Before the accumulation of 59,000 total flight cycles, modify the frame webs at all open hole locations, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 757-53A0103, dated June 22, 2016. Accomplishment of this modification terminates the repetitive inspection requirements of paragraph (g) of this AD at the modified locations only.

(i) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Los Angeles 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 (j) of this AD. Information may be emailed to 9-ANM-LAACO-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, Los Angeles 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 required by paragraph (g) of this AD: For service information that contains steps that are labeled as Required for Compliance (RC), the provisions of paragraphs (i)(4)(i) and (i)(4)(ii) of this AD apply.

(i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. If a step or substep is labeled “RC Exempt,” then the RC requirement is removed from that step or substep. An AMOC is required for any deviations to RC steps, including substeps and identified figures.

(ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition.

(j) Related Information

For more information about this AD, contact Muoi Vuong, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles ACO, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5205; fax: 562-627-5210; email: muoi.vuong@faa.gov.

(k) 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 757-53A0103, dated June 22, 2016.

(ii) Reserved.

(3) 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.

(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://www.archives.gov/​federal-register/​cfr/​ibr-locations.html.

Start Signature

Issued in Renton, Washington, on June 7, 2017.

Michael Kaszycki,

Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

End Signature End Supplemental Information

[FR Doc. 2017-12397 Filed 6-19-17; 8:45 am]

BILLING CODE 4910-13-P