99-32507. Airworthiness Directives; Boeing Model 767 Series Airplanes  

  • [Federal Register Volume 64, Number 243 (Monday, December 20, 1999)]
    [Rules and Regulations]
    [Pages 71006-71007]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 99-32507]
    
    
    
    [[Page 71006]]
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 97-NM-186-AD; Amendment 39-11468; AD 99-26-09]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Boeing Model 767 Series Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD), 
    applicable to certain Boeing Model 767 series airplanes, that requires 
    repetitive inspections to ensure the proper condition of the engine 
    thrust link components, and follow-on corrective action, if necessary; 
    and replacement of the end cap assembly with an improved assembly. Such 
    replacement, when accomplished, terminates the repetitive inspections. 
    This amendment is prompted by a report of fatigue cracking of end cap 
    bolts caused by improper installation. The actions specified by this AD 
    are intended to prevent failure of the end cap assembly, which could 
    lead to separation of the engine from the airplane in the event of a 
    primary thrust linkage failure.
    
    DATES: Effective January 24, 2000.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of January 24, 2000.
    
    ADDRESSES: The service information referenced in this AD may be 
    obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, 
    Washington 98124-2207. This information may be examined at the Federal 
    Aviation Administration (FAA), Transport Airplane Directorate, Rules 
    Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of 
    the Federal Register, 800 North Capitol Street, NW., suite 700, 
    Washington, DC.
    
    FOR FURTHER INFORMATION CONTACT: James G. Rehrl, Aerospace Engineer, 
    Airframe Branch, ANM-120S, FAA, Transport Airplane Directorate, Seattle 
    Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
    Washington 98055-4056; telephone (425) 227-2783; fax (425) 227-1181.
    
    SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
    Aviation Regulations (14 CFR part 39) to include an airworthiness 
    directive (AD) that is applicable to certain Boeing Model 767 series 
    airplanes was published as a supplemental notice of proposed rulemaking 
    (NPRM) in the Federal Register on October 21, 1999 (64 FR 56709). That 
    action proposed to require repetitive inspections to ensure the proper 
    condition of the engine thrust link components, and follow-on 
    corrective action, if necessary; and replacement of the end cap 
    assembly with an improved assembly. Such replacement, when 
    accomplished, terminates the repetitive inspections. That action also 
    revises the proposed rule by adding a repair requirement and by 
    clarifying the type of inspection and terminology used in describing 
    the parts to be inspected.
    
    Comments
    
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. Due consideration has been given to 
    the single comment received.
        The Air Transport Association of America (ATA), on behalf of its 
    members, supports the proposed rule. The ATA states that responding 
    members indicated that they had no comment or no objection to the 
    proposed rule.
    
    Conclusion
    
        After careful review of the available data, including the comment 
    noted above, the FAA has determined that air safety and the public 
    interest require the adoption of the rule as proposed.
    
    Cost Impact
    
        There are approximately 239 Model 767 series airplanes of the 
    affected design in the worldwide fleet. The FAA estimates that 96 
    airplanes of U.S. registry will be affected by this AD, that it will 
    take approximately 37 work hours per airplane (18.5 work hours per 
    engine) to accomplish the required inspections, and that the average 
    labor rate is $60 per work hour. Based on these figures, the cost 
    impact of this AD on U.S. operators is estimated to be $213,120, or 
    $2,220 per airplane, per inspection cycle.
        It will take approximately 135 work hours per airplane (67.5 work 
    hours per engine) to accomplish the required replacement of the forward 
    engine mount end cap and bolts, at an average labor rate of $60 per 
    work hour. Required parts will cost approximately $1,000 per airplane. 
    Based on these figures, the cost impact of the AD on U.S. operators is 
    estimated to be $873,600, or $9,100 per airplane.
        The cost impact figures discussed above are based on assumptions 
    that no operator has yet accomplished any of the requirements of this 
    AD action, and that no operator would accomplish those actions in the 
    future if this AD were not adopted.
    
    Regulatory Impact
    
        The regulations adopted herein will not have substantial direct 
    effects 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. Therefore, in 
    accordance with Executive Order 12612, it is determined that this final 
    rule does not have sufficient federalism implications to warrant the 
    preparation of a Federalism Assessment.
        For the reasons discussed above, I certify that this action (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); and (3) 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. A final evaluation has been prepared for this action 
    and it is contained in the Rules Docket. A copy of it may be obtained 
    from the Rules Docket at the location provided under the caption 
    ADDRESSES.
    
    List of Subjects in 14 CFR Part 39
    
        Air transportation, Aircraft, Aviation safety, Incorporation by 
    reference, Safety.
    
    Adoption of the Amendment
    
        Accordingly, pursuant to the authority delegated to me by the 
    Administrator, the Federal Aviation Administration amends part 39 of 
    the Federal Aviation Regulations (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.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by adding the following new 
    airworthiness directive:
    
    99-26-09 Boeing: Amendment 39-11468. Docket 97-NM-186-AD.
    
        Applicability: Model 767 series airplanes, powered by Pratt & 
    Whitney Model JT9D or Model PW4000 series engines, as listed in 
    Boeing Alert Service Bulletin 767-71A0087, dated October 10, 1996; 
    certificated in any category.
    
        Note 1: This AD applies to each airplane identified in the 
    preceding applicability provision, regardless of whether it has been
    
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    modified, altered, or repaired in the area subject to the 
    requirements of this AD. For airplanes that have been modified, 
    altered, or repaired so that the performance of the requirements of 
    this AD is affected, the owner/operator must request approval for an 
    alternative method of compliance in accordance with paragraph (e) of 
    this AD. The request should include an assessment of the effect of 
    the modification, alteration, or repair on the unsafe condition 
    addressed by this AD; and, if the unsafe condition has not been 
    eliminated, the request should include specific proposed actions to 
    address it.
    
        Compliance: Required as indicated, unless accomplished 
    previously.
        To prevent possible separation of the engine from the airplane 
    in the event of a primary thrust linkage failure, accomplish the 
    following:
    
    Initial and Repetitive Inspections
    
        (a) For Groups 1 and 2 airplanes: Accomplish paragraphs (a)(1), 
    (a)(2), and (a)(3) of this AD, as applicable, in accordance with 
    Boeing Alert Service Bulletin 767-71A0087, dated October 10, 1996.
        (1) Within 500 flight hours or 300 flight cycles after the 
    effective date of this AD, whichever occurs later: Accomplish Work 
    Package 1 (a detailed visual inspection of the forward engine mount 
    to ensure that the thrust link, evener bar, associated lugs, and 
    attaching hardware are firmly attached). Thereafter, repeat Work 
    Package 1 at the intervals specified in the alert service bulletin 
    until the requirements of either paragraph (a)(2) or (a)(3) of this 
    AD are accomplished.
    
        Note 2: For the purposes of this AD, a detailed visual 
    inspection is defined as: ``An intensive visual examination of a 
    specific structural area, system, installation, or assembly to 
    detect damage, failure, or irregularity. Available lighting is 
    normally supplemented with a direct source of good lighting at an 
    intensity deemed appropriate by the inspector. Inspection aids such 
    as mirrors, magnifying lenses, etc. may be used. Surface cleaning 
    and elaborate access procedures may be required.''
    
        (2) Prior to the accumulation of 16,000 total flight cycles on 
    any engine or within 500 flight hours or 300 flight cycles after the 
    effective date of this AD, whichever occurs later: Accomplish Work 
    Package 2 (non-destructive test inspection of the forward engine 
    mount to ensure the proper condition of the engine thrust link 
    components). Thereafter, repeat Work Package 2 on that engine at the 
    intervals specified in the alert service bulletin until the 
    requirements of paragraph (a)(3) of this AD are accomplished. 
    Accomplishment of Work Package 2 constitutes terminating action for 
    the repetitive inspections required by paragraph (a)(1) of this AD 
    for that engine.
    
    Replacement and Terminating Action
    
        (3) Within 3 years after the effective date of this AD: 
    Accomplish Work Package 3 (end cap and bolt replacement of the 
    forward engine mount). Accomplishment of Work Package 3 constitutes 
    terminating action for the requirements of this AD for Groups 1 and 
    2 airplanes.
        (b) For Group 3 airplanes: Within 3 years after the effective 
    date of this AD, accomplish Work Package 4 (bolt replacement) in 
    accordance with Boeing Alert Service Bulletin 767-71A0087, dated 
    October 10, 1996.
    
    Repair and Replacement Action
    
        (c) For all airplanes: If any discrepancy (including an 
    improperly installed or damaged engine thrust link component) is 
    found during any inspection required by this AD, prior to further 
    flight, accomplish the actions required by paragraphs (c)(1) and 
    (c)(2) of this AD.
        (1) Repair any discrepancies in accordance with a method 
    approved by the Manager, Seattle Aircraft Certification Office 
    (ACO), FAA, Transport Airplane Directorate. For a repair method to 
    be approved by the Manager, Seattle ACO, as required by this 
    paragraph, the Manager's approval letter must specifically reference 
    this AD.
        (2) Accomplish Work Package 3 in accordance with Boeing Alert 
    Service Bulletin 767-71A0087, dated October 10, 1996.
    
    Spares
    
        (d) As of the effective date of this AD, no person shall install 
    a forward engine mount end cap having part number 310T3026-1 on any 
    airplane.
    
    Alternative Method of Compliance
    
        (e) An alternative method of compliance or adjustment of the 
    compliance time that provides an acceptable level of safety may be 
    used if approved by the Manager, Seattle ACO. Operators shall submit 
    their requests through an appropriate FAA Principal Maintenance 
    Inspector, who may add comments and then send it to the Manager, 
    Seattle ACO.
    
        Note 3: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Seattle ACO.
    
    Special Flight Permits
    
        (f) Special flight permits may be issued in accordance with 
    Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
    21.197 and 21.199) to operate the airplane to a location where the 
    requirements of this AD can be accomplished.
    
    Incorporation by Reference
    
        (g) Except as provided by paragraph (c)(1) of this AD, the 
    actions shall be done in accordance with Boeing Alert Service 
    Bulletin 767-71A0087, dated October 10, 1996. This incorporation by 
    reference was approved by the Director of the Federal Register in 
    accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be 
    obtained from Boeing Commercial Airplane Group, P.O. Box 3707, 
    Seattle, Washington 98124-2207. Copies may be inspected at the FAA, 
    Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
    Washington; or at the Office of the Federal Register, 800 North 
    Capitol Street, NW., suite 700, Washington, DC.
        (h) This amendment becomes effective on January 24, 2000.
    
        Issued in Renton, Washington, on December 9, 1999.
    D.L. Riggin,
    Acting Manager, Transport Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 99-32507 Filed 12-17-99; 8:45 am]
    BILLING CODE 4910-13-P
    
    
    

Document Information

Effective Date:
1/24/2000
Published:
12/20/1999
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
99-32507
Dates:
Effective January 24, 2000.
Pages:
71006-71007 (2 pages)
Docket Numbers:
Docket No. 97-NM-186-AD, Amendment 39-11468, AD 99-26-09
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
99-32507.pdf
CFR: (1)
14 CFR 39.13