2017-17096. Airworthiness Directives; The Boeing Company Airplanes  

  • Start Preamble

    AGENCY:

    Federal Aviation Administration (FAA), DOT.

    ACTION:

    Notice of proposed rulemaking (NPRM).

    SUMMARY:

    We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD was prompted by reports of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord. This proposed AD would require repetitive inspections for cracking of the wing upper aft skin, and applicable on-condition actions. We are proposing this AD to address the unsafe condition on these products.

    DATES:

    We must receive comments on this proposed AD by September 29, 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-2017-0772.

    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-2017-0772; 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.

    Start Further Info

    FOR FURTHER INFORMATION CONTACT:

    Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-5210; email: payman.soltani@faa.gov.

    End Further Info End Preamble Start Supplemental Information

    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-2017-0772; Product Identifier 2017-NM-075-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 Start Printed Page 38633all comments received by the closing date and may amend this NPRM 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 a report of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord at wing buttock line (WBL) 172.30 and WBL 197.38. The cracks were found on airplanes with 58,148 to 64,204 total flight hours and 45,512 to 51,409 total flight cycles. This cracking, if not corrected, could result in the inability of a principal structural element to sustain flight load, which could adversely affect the structural integrity of the airplane.

    Related Service Information Under 1 CFR Part 51

    We reviewed Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017. The service information describes procedures for repetitive inspections for cracking of the wing upper aft skin at and forward of the rear spar upper chord, and applicable on-condition actions. 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 accomplishment of the actions identified as “RC” (required for compliance) in the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017, described previously, except for any differences identified as exceptions in the regulatory text of this proposed AD.

    For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-0772.

    Explanation of Applicability

    Model 737 airplanes having line numbers 1 through 291 have a limit of validity (LOV) of 34,000 total flight cycles, and the actions proposed in this NPRM, as specified in Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017, would be required at a compliance time occurring after that LOV. Although operation of an airplane beyond its LOV is prohibited by 14 CFR 121.1115 and 129.115, this NPRM would include those airplanes in the applicability so that these airplanes are tracked in the event the LOV is extended in the future.

    Costs of Compliance

    We estimate that this proposed AD affects 160 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD:

    Estimated Costs

    ActionLabor costParts costCost per productCost on U.S. operators
    Inspection4 work-hours × $85 per hour = $340 per inspection cycle$0$340 per inspection cycle$54,400 per inspection cycle.

    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.

    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

    The Proposed Amendment

    Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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
    Start Printed Page 38634
    [Amended]
    Start Amendment Part

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

    End Amendment Part

    The Boeing Company: Docket No. FAA-2017-0772; Product Identifier 2017-NM-075-AD.

    (a) Comments Due Date

    We must receive comments by September 29, 2017.

    (b) Affected ADs

    None.

    (c) Applicability

    This AD applies to all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes, certificated in any category.

    (d) Subject

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

    (e) Unsafe Condition

    This AD was prompted by reports of crack indications in the right wing upper aft skin, originating from fastener holes common to the rear spar upper chord. We are issuing this AD to detect and correct cracking of the wing upper aft skin, which can lead to the inability of a principal structural element to sustain flight load, and adversely affect the structural integrity of the airplane.

    (f) Compliance

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

    (g) Required Actions

    (1) For airplanes identified as Group 2 in Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017: Except as required by paragraph (h) of this AD, at the applicable times specified in paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017, do all applicable actions identified as “RC” (required for compliance) in, and in accordance with, the Accomplishment Instructions of Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017.

    (2) For airplanes identified as Group 1 in Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017: Within 120 days after the effective date of this AD, inspect the airplane and do all applicable corrective actions using a method approved in accordance with the procedures specified in paragraph (i) of this AD.

    (h) Exceptions to Service Information Specifications

    (1) For purposes of determining compliance with the requirements of this AD, the phrase “the effective date of this AD” may be substituted for “the original issue date of this service bulletin,” as specified in Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017.

    (2) Where Boeing Alert Service Bulletin 737-57A1335, dated May 24, 2017, specifies contacting Boeing, and specifies that action as RC: This AD requires using a method approved in accordance with the procedures specified in paragraph (i) of this AD.

    (i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Los Angeles 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 (j)(1) 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 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 (h)(2) of this AD: For service information that contains steps that are labeled as 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

    (1) For more information about this AD, contact Payman Soltani, Aerospace Engineer, Airframe Section, FAA, Los Angeles ACO Branch, 3960 Paramount Boulevard, Lakewood, CA 90712-4137; phone: 562-627-5313; fax: 562-627-5210; email: payman.soltani@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.

    Start Signature

    Issued in Renton, Washington, on August 4, 2017.

    Jeffrey E. Duven,

    Director, System Oversight Division, Aircraft Certification Service.

    End Signature End Supplemental Information

    [FR Doc. 2017-17096 Filed 8-14-17; 8:45 am]

    BILLING CODE 4910-13-P

Document Information

Published:
08/15/2017
Department:
Federal Aviation Administration
Entry Type:
Proposed Rule
Action:
Notice of proposed rulemaking (NPRM).
Document Number:
2017-17096
Dates:
We must receive comments on this proposed AD by September 29, 2017.
Pages:
38632-38634 (3 pages)
Docket Numbers:
Docket No. FAA-2017-0772, Product Identifier 2017-NM-075-AD
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
Topics:
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety
PDF File:
2017-17096.pdf
Supporting Documents:
» U.S. DOT/FAA - Supporting AD Documents
CFR: (1)
14 CFR 39.13