99-183. Airworthiness Directives; Boeing Model 727 Series Airplanes  

  • [Federal Register Volume 64, Number 4 (Thursday, January 7, 1999)]
    [Rules and Regulations]
    [Pages 989-991]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 99-183]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 96-NM-263-AD; Amendment 39-10983; AD 98-11-03 R1]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Boeing Model 727 Series Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; correction.
    
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    SUMMARY: This amendment corrects information in an existing 
    airworthiness directive (AD), applicable to certain Boeing Model 727 
    series airplanes, that currently requires that the FAA-approved 
    maintenance inspection program be revised to include inspections that 
    will give no less than the required damage tolerance rating for each 
    Structural Significant Item (SSI), and repair of cracked structure. The 
    actions specified in that AD are intended to ensure the continued 
    structural integrity of the entire Boeing Model 727 fleet. This 
    amendment corrects the requirements of the current AD by allowing 
    operators not to change their programs if they determine that the 
    existing inspections are effective for the new or affected SSI. This 
    amendment is prompted by a review of the requirements of the existing 
    AD.
    
    DATES: Effective June 23, 1998.
        The incorporation by reference of a certain publication, as listed 
    in the regulations, was approved previously by the Director of the 
    Federal Register as of June 23, 1998 (63 FR 27455, May 19, 1998).
    
    FOR FURTHER INFORMATION CONTACT: Walter Sippel, Aerospace Engineer, 
    Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office, 
    1601 Lind Avenue, SW., Washington; telephone (425) 227-2774; fax (425) 
    227-1181.
    
    SUPPLEMENTARY INFORMATION: On May 12, 1998, the FAA issued AD 98-11-03, 
    amendment 39-10530 (63 FR 27455, May 19, 1998), which is applicable to 
    certain Boeing Model 727 series airplanes. That AD requires that the 
    FAA-approved maintenance inspection program be revised to include 
    inspections that will give no less than the required damage tolerance 
    rating for each Structural Significant Item (SSI), and repair of 
    cracked structure. That action was prompted by a structural re-
    evaluation by the manufacturer that identified additional structural 
    elements where, if damage were to occur, supplemental inspections may 
    be required for timely detection. The actions required by that AD are 
    intended to ensure the continued structural integrity of the entire 
    Boeing Model 727 fleet.
        AD 98-11-03 contains provisions regarding when operators must 
    revise their maintenance or inspection program to address SSI's that 
    are created or affected by repairs and design changes. As discussed in 
    the preamble to the final rule, the FAA intended that such revisions be 
    made only if a damage tolerance assessment indicates that such a change 
    is necessary because existing inspections are ineffective for the SSI. 
    Paragraph (d)(1) of the AD, applicable to repairs and design changes 
    accomplished prior to the effective date of the AD, properly states the 
    FAA's intent. However, the FAA inadvertently omitted a comparable 
    provision in paragraph (g), which applies to repairs and design changes 
    accomplished after the effective date of the AD. As adopted, paragraph 
    (g) requires that operators revise their maintenance programs following 
    repairs and design changes, regardless of whether a damage tolerance 
    assessment indicates that the existing applicable inspection continue 
    to be effective. Therefore, consistent with the FAA's intent, this 
    correction is necessary to allow operators not to change their programs 
    if they determine that the existing inspections are effective for the 
    new or affected SSI.
        Action is taken herein to correct these requirements of AD 98-11-03 
    and to correctly add the AD as an amendment to section 39.13 of the 
    Federal Aviation Regulations (14 CFR 39.13).
        The final rule is being reprinted in its entirety for the 
    convenience of affected operators. The effective date remains June 23, 
    1998.
        Since this action only corrects a current requirement, it has no 
    adverse economic impact and imposes no additional burden on any person. 
    Therefore, notice and public procedures hereon are unnecessary.
    
    List of Subjects in 14 CFR Part 39
    
        Air transportation, Aircraft, Aviation safety, Incorporation by 
    reference, Safety.
    
    [[Page 990]]
    
    Adoption of the Correction
    
        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 removing amendment 39-10530 (63 FR 
    27455, May 19, 1998), and by adding a new airworthiness directive (AD), 
    amendment 39-10983, to read as follows:
    
    98-11-03 R1  Boeing: Amendment 39-10983. Docket 96-NM-263-AD. 
    Revises AD 98-11-03: Amendment 39-10530.
    
        Applicability: All Model 727 series airplanes, certificated in 
    any category.
        Compliance: Required as indicated, unless accomplished 
    previously.
        To ensure the continued structural integrity of the entire 
    Boeing Model 727 fleet, accomplish the following:
    
        Note 1: Where there are differences between the AD and the 
    Supplemental Structural Inspection Document, the AD prevails.
    
        (a) For airplanes listed in Section 3.0 of Boeing Document No. 
    D6-48040-1, ``Supplemental Structural Inspection Document'' (SSID), 
    Revision E, dated June 21, 1983: Within 12 months after November 1, 
    1984 (the effective date of AD 84-21-05, amendment 39-4920), 
    incorporate a revision into the FAA-approved maintenance inspection 
    program which provides no less than the required damage tolerance 
    rating (DTR) for each Structural Significant Item (SSI) listed in 
    that document. (The required DTR value for each SSI is listed in the 
    document.) The revision to the maintenance program shall include and 
    shall be implemented in accordance with the procedures in Sections 
    5.0 and 6.0 of the SSID. This revision shall be deleted following 
    accomplishment of the requirements of paragraph (b) of this AD.
    
        Note 2: For the purposes of this AD, an SSI is defined as a 
    principal structural element that could fail and consequently reduce 
    the structural integrity of the airplane.
    
        (b) Prior to reaching the threshold specified in paragraph (c) 
    of this AD, or within 12 months after the effective date of this AD, 
    whichever occurs later, incorporate a revision into the FAA-approved 
    maintenance or inspection program that provides no less than the 
    required DTR for each SSI listed in Boeing Document No. D6-48040-1, 
    Volumes 1 and 2, ``Supplemental Structural Inspection Document'' 
    (SSID), Revision H, dated June 1994 (hereinafter referred to as 
    ``Revision H''). (The required DTR value for each SSI is listed in 
    the document.) Except as provided to the contrary in paragraphs (c), 
    (d), and (g) of this AD, the revision to the maintenance or 
    inspection program shall include and shall be implemented in 
    accordance with the procedures in Section 5.0, ``Damage Tolerance 
    Rating (DTR) System Application'' and Section 6.0, ``SSI Discrepancy 
    Reporting'' of Revision H. Upon incorporation of the revision 
    required by this paragraph, the revision required by paragraph (a) 
    of this AD may be deleted.
        (c) Except as provided in paragraph (d), (e), or (g) of this AD, 
    perform an inspection to detect cracks in all structure identified 
    in Revision H at the time specified in paragraph (c)(1) or (c)(2) of 
    this AD, as applicable.
        (1) For Model 727-100C and 727-200F series airplanes: Inspect 
    prior to the accumulation of 46,000 total flight cycles, or within 
    3,000 flight cycles measured from the date 12 months after the 
    effective date of this AD, whichever occurs later.
    
        Note 3: The requirements specified by paragraph (c)(1) of this 
    AD only apply to airplanes listed as 727-100C and 727-200F on the 
    type certificate data sheet. Paragraph (c)(1) does not apply to 
    airplanes that have been modified from a passenger configuration to 
    an all-cargo configuration by supplemental type certificate (STC). 
    Paragraphs (c)(2) and (d) apply to those airplanes.
    
        (2) For all airplanes, except for those airplanes identified in 
    paragraph (c)(1) of this AD: Inspect prior to the accumulation of 
    55,000 total flight cycles, or within 3,000 flight cycles measured 
    from the date 12 months after the effective date of this AD, 
    whichever occurs later.
    
        Note 4: Notwithstanding the provisions of paragraphs 5.1.1, 
    5.1.2, 5.1.6(e), 5.1.11, 5.1.12, 5.1.13, 5.2, 5.2.1, 5.2.2, 5.2.3, 
    and 5.2.4 of the General Instructions of Revision H, which would 
    permit operators to perform fleet and rotational sampling 
    inspections, to perform inspections on less than whole airplane 
    fleet sizes and to perform inspections on substitute airplanes, this 
    AD requires that all airplanes that exceed the threshold be 
    inspected in accordance with Revision H.
    
        Note 5: Once the initial inspection has been performed, 
    operators are required to perform repetitive inspections at the 
    intervals specified in Revision H in order to remain in compliance 
    with their maintenance or inspection programs, as revised in 
    accordance with paragraph (b) of this AD.
    
        (d) For airplanes on which the structure identified in Revision 
    H has been physically altered in accordance with an STC prior to the 
    effective date of this AD: Accomplish the requirements specified in 
    paragraph (d)(1) or (d)(2) of this AD.
        (1) Within 18 months after the effective date of this AD, assess 
    the damage tolerance characteristics of each SSI created or affected 
    by each STC to determine the effectiveness of the applicable 
    Revision H inspection for each SSI and, if not effective, revise the 
    FAA-approved maintenance or inspection program to include an 
    inspection method for each new or affected SSI, and to include the 
    compliance times for initial and repetitive accomplishment of each 
    inspection. Following accomplishment of the revision and within the 
    compliance times established, perform an inspection to detect cracks 
    in the structure affected by any design change or repair, in 
    accordance with the new inspection method. The new inspection method 
    and the compliance times shall be approved by the Manager, Seattle 
    Aircraft Certification Office (ACO), FAA, Transport Airplane 
    Directorate.
    
        Note 6: For purposes of this AD, an SSI is ``affected'' if it 
    has been physically altered or repaired, or if the loads acting on 
    the SSI have been increased or redistributed. The effectiveness of 
    the applicable inspection method and compliance time should be 
    determined based on a damage tolerance assessment methodology, such 
    as that described in FAA Advisory Circular AC No. 91-56, Change 2, 
    dated April 15, 1983.
    
        (2) Accomplish paragraphs (d)(2)(i), (d)(2)(ii), and (d)(2)(iii) 
    of this AD.
        (i) Within 18 months after the effective date of this AD, submit 
    a plan that describes a methodology for accomplishing the 
    requirements of paragraph (d)(1) of this AD to the Manager, Seattle 
    ACO, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; fax (425) 
    227-1181.
    
        Note 7: The plan should include a detailed description of the 
    STC; methodology for identifying new or affected SSI's; method for 
    developing loads and validating the analysis; methodology for 
    evaluating and analyzing the damage tolerance characteristics of 
    each new or affected SSI; and proposed inspection method. The plan 
    would not need to include all of these elements if the operator can 
    otherwise demonstrate that its plan will enable the operator to 
    comply with paragraph (d)(2)(iii) of this AD.
    
        (ii) Within 18 months after the effective date of this AD, 
    perform a detailed visual inspection in accordance with a method 
    approved by the Manager, Seattle ACO to detect cracks in all 
    structure identified in Revision H that has been altered by an STC.
        (A) If no crack is detected, repeat the detailed visual 
    inspection thereafter at intervals not to exceed 18 months.
        (B) If any crack is detected, prior to further flight, repair it 
    in accordance with a method approved by the Manager, Seattle ACO.
        (iii) Within 48 months after the effective date of this AD, 
    revise the FAA-approved maintenance or inspection program to include 
    an inspection method for each new or affected SSI, and to include 
    the compliance times for initial and repetitive accomplishment of 
    each inspection. The inspection methods and the compliance times 
    shall be approved by the Manager, Seattle ACO. Accomplishment of the 
    actions specified in this paragraph constitutes terminating action 
    for the repetitive inspection requirements of paragraph 
    (d)(2)(ii)(A) of this AD.
    
        Note 8: Notwithstanding the provisions of paragraphs 5.1.17 and 
    5.1.18 of the General Instructions of Revision H, which would permit 
    deletions of modified, altered, or repaired structure from the SSIP, 
    the inspection of SSI's that are modified, altered, or repaired 
    shall be done in accordance with
    
    [[Page 991]]
    
    a method approved by the Manager, Seattle ACO.
    
        (e) For airplanes on which the structure identified in Revision 
    H has been repaired or physically altered by any design change other 
    than an STC identified in paragraph (d), prior to the effective date 
    of this AD: At the time of the first inspection of each SSI after 
    the effective date of this AD in accordance with Revision H, 
    identify each repair or design change to that SSI. Within 12 months 
    after such identification, assess the damage tolerance 
    characteristics of each SSI created or affected by each repair or 
    design change to determine the effectiveness of the applicable SSID 
    inspection for each SSI and, if not effective, revise the FAA-
    approved maintenance or inspection program to include an inspection 
    method and compliance times for each new or affected SSI. The new 
    inspection method and the compliance times shall be approved by the 
    Manager, Seattle ACO.
    
        Note 9: For the purposes of this AD, a design change is defined 
    as any modification, alteration, or change to operating limitations.
    
        (f) Except as provided in paragraph (d)(2)(ii)(B) of this AD, 
    cracked structure found during any inspection required by this AD 
    shall be repaired, prior to further flight, in accordance with an 
    FAA-approved method.
        (g) For airplanes on which the structure identified in Revision 
    H is affected by any design change (including STC's) or repair that 
    is accomplished after the effective date of this AD: Within 12 
    months after that modification, alteration, or repair, assess the 
    damage tolerance characteristics of each SSI created or affected by 
    each repair or design change to determine the effectiveness of the 
    applicable SSID inspection for each SSI and, if not effective, 
    revise the FAA-approved maintenance or inspection program to include 
    an inspection method and compliance times for each new or affected 
    SSI, and to include the compliance times for initial and repetitive 
    accomplishment of each inspection. The new inspection method and the 
    compliance times shall be approved by the Manager, Seattle ACO.
    
        Note 10: Notwithstanding the provisions of paragraphs 5.1.17 and 
    5.1.18 of the General Instructions of Revision H, which would permit 
    deletions of modified, altered, or repaired structure from the SIP, 
    the inspection of SSI's that are modified, altered, or repaired 
    shall be done in accordance with a method approved by the Manager, 
    Seattle ACO.
    
        (h) Before any airplane that is subject to this AD and that has 
    exceeded the applicable compliance times specified in paragraph (c) 
    of this AD can be added to an air carrier's operations 
    specifications, a program for the accomplishment of the inspections 
    required by this AD must be established in accordance with paragraph 
    (h)(1) or (h)(2) of this AD, as applicable.
        (1) For airplanes that have been inspected in accordance with 
    this AD, the inspection of each SSI must be accomplished by the new 
    operator in accordance with the previous operator's schedule and 
    inspection method, or the new operator's schedule and inspection 
    method, whichever would result in the earlier accomplishment date 
    for that SSI inspection. The compliance time for accomplishment of 
    this inspection must be measured from the last inspection 
    accomplished by the previous operator. After each inspection has 
    been performed once, each subsequent inspection must be performed in 
    accordance with the new operator's schedule and inspection method.
        (2) For airplanes that have not been inspected in accordance 
    with this AD, the inspection of each SSI required by this AD must be 
    accomplished either prior to adding the airplane to the air 
    carrier's operations specification, or in accordance with a schedule 
    and an inspection method approved by the Manager, Seattle ACO. After 
    each inspection has been performed once, each subsequent inspection 
    must be performed in accordance with the new operator's schedule.
        (i)(1) 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 11: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Seattle ACO.
    
        (2) Alternative methods of compliance, approved previously in 
    accordance with AD 84-21-05, amendment 39-4920, are not considered 
    to be approved as alternative methods of compliance with this AD.
        (j) 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.
        (k) The actions specified in paragraphs (b) and (c) shall be 
    done in accordance with Boeing Document No. D6-48040-1, Volumes 1 
    and 2, ``Supplemental Structural Inspection Document'' (SSID), 
    Revision H, dated June 1994, which contains the following list of 
    effective pages:
    
    ------------------------------------------------------------------------
             Page number shown on page          Revision level shown on page
    ------------------------------------------------------------------------
    List of Active Pages......................  H
      Pages 1 thru 17.2
    ------------------------------------------------------------------------
    
        (Note: The issue date of Revision H is indicated only on the 
    title page; no other page of the document is dated.). This 
    incorporation by reference was approved previously by the Director 
    of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 
    CFR part 51, as of June 23, 1998 (63 FR 27455, May 19, 1998). 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.
    
        (l) The effective date of this amendment remains June 23, 1998.
    
        Issued in Renton, Washington, on December 30, 1998.
    Darrell M. Pederson,
    Acting Manager, Transport Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 99-183 Filed 1-6-99; 8:45 am]
    BILLING CODE 4910-13-P
    
    
    

Document Information

Effective Date:
6/23/1998
Published:
01/07/1999
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; correction.
Document Number:
99-183
Dates:
Effective June 23, 1998.
Pages:
989-991 (3 pages)
Docket Numbers:
Docket No. 96-NM-263-AD, Amendment 39-10983, AD 98-11-03 R1
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
99-183.pdf
CFR: (1)
14 CFR 39.13