99-15775. Airworthiness Directives; Boeing Model 727 Series Airplanes  

  • [Federal Register Volume 64, Number 120 (Wednesday, June 23, 1999)]
    [Rules and Regulations]
    [Pages 33394-33397]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 99-15775]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 99-NM-121-AD; Amendment 39-11199; AD 99-12-52]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Boeing Model 727 Series Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This document publishes in the Federal Register an amendment 
    adopting Airworthiness Directive (AD) T99-12-52 that was sent 
    previously to all known U.S. owners and operators of all Boeing Model 
    727 series airplanes by individual telegrams. This AD requires a boost 
    pump dry bay inspection to detect leakage of fuel through an arced-
    through conduit, and corrective action, as necessary. This AD also 
    requires repetitive detailed visual inspections of the in-tank fuel 
    boost pump wiring to detect chafing of the wire insulation, evidence of 
    electrical arcing, or arc-through of the conduit wall on Model 727 
    series airplanes, and applicable corrective action; and installation of 
    sleeving over the in-tank fuel boost pump wires as a method to protect 
    the wiring from chafing. This action is prompted by reports of severe 
    wear of in-tank fuel boost pump wiring, and arc-through of the 
    surrounding conduit on two Model 727 series airplanes. The actions 
    specified by this AD are intended to prevent fuel tank explosion 
    resulting from arc-through of the fuel boost pump wiring conduits.
    
    DATES: Effective June 28, 1999, to all persons except those persons to 
    whom
    
    [[Page 33395]]
    
    it was made immediately effective by telegraphic AD T99-12-52, issued 
    May 24, 1999, which contained the requirements of this amendment.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of June 28, 1999.
        Comments for inclusion in the Rules Docket must be received on or 
    before August 23, 1999.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Transport Airplane Directorate, ANM-114, 
    Attention: Rules Docket No. 99-NM-121-AD, 1601 Lind Avenue, SW., 
    Renton, Washington 98055-4056.
        The applicable service information may be obtained from Boeing 
    Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124-
    2207. This information may be examined 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.
    
    FOR FURTHER INFORMATION CONTACT: Jon Regimbal, Aerospace Engineer, 
    Propulsion Branch, ANM-140S, FAA, Transport Airplane Directorate, 
    Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, 
    Washington 98055-4056; telephone (425) 227-2687; fax (425) 227-1181.
    
    SUPPLEMENTARY INFORMATION:
    
    Issuance of Telegraphic AD T99-12-51
    
        On May 21, 1999, the FAA issued telegraphic AD T99-12-51, which is 
    applicable to all Boeing Model 727 series airplanes, to require a boost 
    pump dry bay inspection to detect leakage of fuel through an arced-
    through conduit, and corrective action, as necessary.
        Telegraphic AD T99-12-51 was prompted by reports of severe wear of 
    the in-tank fuel boost pump wiring, and arc-through of the surrounding 
    conduit on two Model 727 series airplanes that had accumulated in 
    excess of 50,000 total flight hours. The wear and arc-through condition 
    of the conduit surrounding the in-tank fuel boost pump wiring has been 
    attributed to chafing between the in-tank fuel boost pump wiring and 
    the wall of the surrounding conduit, exposing the electrical conductor 
    of the boost pump power wire and placing it in contact with the 
    aluminum wall of the conduit, resulting in arc-through of the conduit 
    wall. Arc-through of the conduit presents an ignition source inside the 
    fuel tank. In addition, the resultant hole in the conduit provides a 
    path for fuel to leak from the fuel tank. The actions required by 
    telegraphic AD T99-12-51 were intended to detect and correct fuel boost 
    pump wiring conduits which have experienced severe chafing and 
    electrical arcing, resulting in burn-through of the conduit. This 
    condition, if not corrected, could result in ignition of fuel vapors in 
    a fuel tank, and a fuel tank explosion.
    
    Issuance of Telegraphic AD T99-12-52
    
        On May 24, 1999, the FAA issued telegraphic AD T99-12-52, 
    applicable to all Model 727 series airplanes, which superseded 
    telegraphic AD T99-12-51 to continue to require a boost pump dry bay 
    inspection to detect leakage of fuel through an arced-through conduit, 
    and corrective action, as necessary.
        Telegraphic AD T99-12-52 adds a requirement for repetitive detailed 
    visual inspections of the in-tank fuel boost pump wiring to detect 
    chafing of the wire insulation, evidence of electrical arcing, or arc-
    through of the conduit wall on Model 727 series airplanes, and 
    applicable corrective action. In addition, this telegraphic AD requires 
    installation of sleeving over the in-tank fuel boost pump wires as a 
    method to protect the wiring from chafing. If the initial inspection of 
    the wiring is performed before the inspection of the fuel boost pump 
    dry bay for fuel leaks, the inspection of the fuel boost pump dry bay 
    for fuel leaks is not required.
        Telegraphic AD T99-12-52 was prompted by the same reports that are 
    described in the Summary of this AD and in telegraphic AD T99-12-51.
    
    Explanation of Relevant Service Information
    
        The FAA has reviewed and approved Boeing Alert Service Bulletin 
    727-28A0126, dated May 24, 1999, which describes procedures for 
    performing a boost pump dry bay inspection to detect leakage of fuel 
    through an arced-through conduit. That alert service bulletin also 
    describes procedures for performing detailed inspections of the in-tank 
    fuel boost pump wire bundles, installing wire bundle sleeving, 
    replacing the conduit if fuel leakage is detected, and performing 
    applicable corrective actions. In addition, the alert service bulletin 
    describes procedures for performing leak checks of the replaced conduit 
    and installing the new fuel boost pump wire.
    
    Explanation of Requirements of the Rule
    
        Since the unsafe condition described is likely to exist or develop 
    on other airplanes of the same type design, the FAA issued telegraphic 
    AD T99-12-52 to prevent fuel tank explosion resulting from arc-through 
    of the fuel boost pump wiring conduits. This AD supersedes telegraphic 
    AD T99-12-51 to continue to require a boost pump dry bay inspection to 
    detect leakage of fuel through an arced-through conduit, and corrective 
    action, as necessary. This AD adds a requirement for repetitive 
    detailed visual inspections of the in-tank fuel boost pump wiring to 
    detect chafing of the wire insulation, evidence of electrical arcing, 
    or arc-through of the conduit wall on Model 727 series airplanes, and 
    applicable corrective action. In addition, this AD requires 
    installation of sleeving over the in-tank fuel boost pump wires as a 
    method to protect the wiring from chafing. If the initial inspection of 
    the wiring is performed before the inspection of the boost pump dry bay 
    for fuel leaks, the inspection of the fuel boost pump dry bay for fuel 
    leaks is not required.
        Except as described in the ``Differences'' paragraph below, the 
    actions are required to be accomplished in accordance with Boeing All 
    Operator Message (AOM) M-7200-99-04035, dated May 21, 1999, (for the 
    boost pump dry bay inspection), and Boeing Alert Service Bulletin 727-
    28A0126, dated May 24, 1999, (for the boost pump dry bay inspection and 
    the wiring inspection).
    
    Differences Between This AD and the Service Information
    
        Although the Boeing AOM describes general procedures for inspecting 
    the fuel boost pump wire bundles and installing new fuel boost pump 
    wire bundles and sleeving, the FAA considers that use of the more 
    specific instructions included in Boeing Alert Service Bulletin 727-
    28A0126, dated May 24, 1999, is necessary to ensure that the wire 
    inspections are performed properly.
        However, if the wire bundle inspection or wire bundle replacement 
    has been accomplished in accordance with the Boeing AOM, these actions 
    may provide the basis for an alternative method of compliance as 
    provided in paragraph (l) of this AD.
        Since it was found that immediate corrective action was required, 
    notice and opportunity for prior public comment thereon were 
    impracticable and contrary to the public interest, and good cause 
    existed to make the AD effective immediately by individual telegrams 
    issued on May 24, 1999, to all known U.S. owners and operators of all 
    Model 727 series airplanes. These conditions still exist, and the AD is 
    hereby published in the Federal
    
    [[Page 33396]]
    
    Register as an amendment to section 39.13 of the Federal Aviation 
    Regulations (14 CFR 39.13) to make it effective to all persons.
    
    Explanation of Changes Made to the Final Rule
    
        The FAA has determined that reference to a certain paragraph that 
    was included in the ``Differences'' paragraph and in NOTE 1 of 
    Telegraph AD T99-12-52 is incorrect. The FAA has revised this AD to 
    correctly reference paragraph (l) instead of paragraph (e).
    
    Interim Action
    
        In the preamble to AD T99-12-51, the FAA indicated that the actions 
    required by that AD were considered ``interim action'' and that further 
    rulemaking action was being considered. The FAA now has determined that 
    further rulemaking action is indeed necessary, and this AD follows from 
    that determination.
    
    Comments Invited
    
        Although this action is in the form of a final rule that involves 
    requirements affecting flight safety and, thus, was not preceded by 
    notice and an opportunity for public comment, comments are invited on 
    this rule. Interested persons are invited to comment on this rule by 
    submitting such written data, views, or arguments as they may desire. 
    Communications shall identify the Rules Docket number and be submitted 
    in triplicate to the address specified under the caption ADDRESSES. All 
    communications received on or before the closing date for comments will 
    be considered, and this rule may be amended in light of the comments 
    received. Factual information that supports the commenter's ideas and 
    suggestions is extremely helpful in evaluating the effectiveness of the 
    AD action and determining whether additional rulemaking action would be 
    needed.
        Comments are specifically invited on the overall regulatory, 
    economic, environmental, and energy aspects of the rule that might 
    suggest a need to modify the rule. All comments submitted will be 
    available, both before and after the closing date for comments, in the 
    Rules Docket for examination by interested persons. A report that 
    summarizes each FAA-public contact concerned with the substance of this 
    AD will be filed in the Rules Docket.
        Commenters wishing the FAA to acknowledge receipt of their comments 
    submitted in response to this rule must submit a self-addressed, 
    stamped postcard on which the following statement is made: ``Comments 
    to Docket Number 99-NM-121-AD.'' The postcard will be date stamped and 
    returned to the commenter.
    
    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.
        The FAA has determined that this regulation is an emergency 
    regulation that must be issued immediately to correct an unsafe 
    condition in aircraft, and that it is not a ``significant regulatory 
    action'' under Executive Order 12866. It has been determined further 
    that this action involves an emergency regulation under DOT Regulatory 
    Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
    determined that this emergency regulation otherwise would be 
    significant under DOT Regulatory Policies and Procedures, a final 
    regulatory evaluation will be prepared and placed in the Rules Docket. 
    A copy of it, if filed, 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:
    
    99-12-52  Boeing: Amendment 39-11199. Docket 99-NM-121-AD. 
    Supersedes Telegraphic AD T99-12-51.
    
        Applicability: All Model 727 series airplanes, certificated in 
    any category.
    
        Note 1: This AD applies to each airplane identified in the 
    preceding applicability provision, regardless of whether it has been 
    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 (l) 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 fuel tank explosion resulting from arc-through of the 
    fuel boost pump wiring conduits, accomplish the following:
        (a) For airplanes with 50,000 or more total flight hours as of 
    the date of receipt of AD T99-12-51, within 5 days after the 
    effective date of this AD, accomplish the requirements of paragraph 
    (c) of this AD.
        (b) For airplanes with less than 50,000 total flight hours as of 
    the date of receipt of AD T99-12-51, prior to the accumulation of 
    30,000 total flight hours, or within 10 days after receipt of this 
    AD, whichever occurs later, accomplish the requirements of paragraph 
    (c) of this AD.
    
    Initial Inspection and Corrective Action
    
        (c) Except as provided in paragraphs (d) and (e) of this AD, 
    perform a boost pump dry bay inspection and applicable follow-on 
    corrective actions, in accordance with steps 1 through 6 of the 
    ``Boost Pump Dry Bay Inspection,'' specified in Boeing All Operator 
    Message M-7200-99-04035, dated May 21, 1999, or in accordance with 
    Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999.
        (d) For airplanes on which the actions specified in step 5-E-<3> 
    of Boeing All Operator Message M-7200-99-04035, dated May 21, 1999, 
    are accomplished, the fuel tank in which the conduit has been 
    replaced must be refueled prior to accomplishing step 6.
        (e) Accomplishment of the requirements of paragraph (c) of this 
    AD is not required if the requirements of paragraph (i) of this AD 
    are accomplished within the times specified in paragraph (a) or (b) 
    of this AD, as applicable.
    
    New Requirements of This AD
    
        (f) For airplanes with 50,000 or more total flight hours as of 
    the effective date of this AD, within 20 days after the effective 
    date of this AD, accomplish the requirements of paragraph (i) of 
    this AD.
        (g) For airplanes with less than 50,000 total flight hours, but 
    more than 30,000 total flight hours, as of the effective date of 
    this AD, within 30 days after the effective date of this AD, 
    accomplish the requirements of paragraph (i) of this AD.
        (h) For airplanes with 30,000 total flight hours or fewer, as of 
    the effective date of this AD, within 90 days after the effective 
    date of this AD, accomplish the requirements of paragraph (i) of 
    this AD.
    
    [[Page 33397]]
    
    Detailed Visual Inspection, Corrective Action, and Installation
    
        (i) Perform a detailed visual inspection of the in-tank fuel 
    boost pump wire bundles, and applicable corrective actions; and, 
    except as provided in paragraph (j) of this AD, install sleeving 
    over the wire bundles; in accordance with Boeing Alert Service 
    Bulletin 727-28A0126, dated May 24, 1999.
    
        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 
    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.
    
    Installation: Possible Deferral
    
        (j) Installation of sleeving over the wire bundles, as required 
    by paragraph (i) of this AD, may be deferred if, within 18 months or 
    6,000 flight hours, whichever occurs first, after accomplishment of 
    the inspection and applicable corrective actions required by 
    paragraph (i), the following actions are accomplished: Perform a 
    detailed visual inspection of the in-tank fuel boost pump wire 
    bundles, and applicable corrective actions; and install sleeving 
    over the wire bundles; in accordance with Boeing Alert Service 
    Bulletin 727-28A0126, dated May 24, 1999.
    
    Repetitive Inspections and Corrective Actions
    
        (k) Repeat the detailed visual inspection and applicable 
    corrective actions required by paragraphs (i) and (j) of this AD at 
    intervals not to exceed 30,000 flight hours.
    
    Alternative Methods of Compliance
    
        (l) 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 Aircraft Certification 
    Office (ACO), FAA, Transport Airplane Directorate. 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
    
        (m) Special flight permits may be issued in accordance with 
    sections 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
    
        (n) The actions shall be done in accordance with Boeing All 
    Operator Message (AOM) M-7200-99-04035, dated May 21, 1999, or 
    Boeing Alert Service Bulletin 727-28A0126, dated May 24, 1999, as 
    applicable. 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.
        (o) This amendment becomes effective on June 28, 1999, to all 
    persons except those persons to whom it was made immediately 
    effective by telegraphic AD T99-12-52, issued on May 24, 1999, which 
    contained the requirements of this amendment.
    
        Issued in Renton, Washington, on June 15, 1999.
    Kalene C. Yanamura,
    Acting Manager, Transport Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 99-15775 Filed 6-22-99; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
6/28/1999
Published:
06/23/1999
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
99-15775
Dates:
Effective June 28, 1999, to all persons except those persons to whom it was made immediately effective by telegraphic AD T99-12-52, issued May 24, 1999, which contained the requirements of this amendment.
Pages:
33394-33397 (4 pages)
Docket Numbers:
Docket No. 99-NM-121-AD, Amendment 39-11199, AD 99-12-52
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
99-15775.pdf
CFR: (1)
14 CFR 39.13