96-28164. Airworthiness Directives; Aerospace Technologies of Australia Pty Ltd. (Formerly Government Aircraft Factory) Models N22B, N24A, and N22S Airplanes  

  • [Federal Register Volume 61, Number 219 (Tuesday, November 12, 1996)]
    [Rules and Regulations]
    [Pages 57993-57994]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 96-28164]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 95-CE-103-AD; Amendment 39-9808; AD 96-23-03]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Aerospace Technologies of Australia Pty 
    Ltd. (Formerly Government Aircraft Factory) Models N22B, N24A, and N22S 
    Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
    applies to Aerospace Technologies of Australia Pty Ltd. (ASTA) Models 
    N22B, N24A, and N22S airplanes that are not equipped with a part number 
    (P/N) 1E/N-12-57 fuselage stub fin plate (MOD N759). This action 
    requires replacing the existing fuselage stub fin plate with one of 
    improved design, P/N 1E/N-12-57. This action results from several 
    reports of cracks along the forward flange of the fuselage stub fin 
    plate in the area of Rib Water Line (WL) 138.87. The actions specified 
    by this AD are intended to prevent structural failure of the fuselage 
    area caused by a cracked stub fin plate, which could result in loss of 
    control of the airplane.
    
    DATES: Effective December 23, 1996.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of December 23, 1996.
    
    ADDRESSES: Service information that applies to this AD may be obtained 
    from Aerospace Technologies of Australia Pty Ltd., ASTA DEFENCE, 
    Private Bag No. 4, Beach Road Lara 3212, Victoria, Australia. This 
    information may also be examined at the Federal Aviation Administration 
    (FAA), Central Region, Office of the Assistant Chief Counsel, 
    Attention: Rules Docket 95-CE-103-AD, Room 1558, 601 E. 12th Street, 
    Kansas City, Missouri 64106; or at the Office of the Federal Register, 
    800 North Capitol Street, NW., suite 700, Washington, DC.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Ron Atmur, Aerospace Engineer, 
    FAA, Los Angeles Aircraft Certification Office, 3960 Paramount 
    Boulevard., Lakewood, California 90712; telephone (310) 627-5224; 
    facsimile (310) 627-5210.
    
    SUPPLEMENTARY INFORMATION:
    
    Events Leading to the AD
    
        A proposal to amend part 39 of the Federal Aviation Regulations (14 
    CFR part 39) to include an AD that would apply to ASTA Models N22B, 
    N24A, and N22S airplanes that are not equipped with a part number (P/N) 
    1E/N-12-57 fuselage stub fin plate (MOD N759) was published in the 
    Federal Register on July 8, 1996 (61 FR 35693). The action proposed to 
    require replacing the existing fuselage stub fin plate with one of 
    improved design, P/N 1E/N-12-57. Accomplishment of the proposed 
    installation as specified in the notice of proposed rulemaking (NPRM) 
    would be in accordance with Nomad Service Bulletin ANMD-53-13, Revision 
    3, dated October 24, 1995.
        The NPRM was the result of several reports of cracks along the 
    forward flange of the fuselage stub fin plate in the area of Rib Water 
    Line (WL) 138.87.
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. No comments were received on the 
    proposed rule or the FAA's determination of the cost to the public.
    
    The FAA's Determination
    
        After careful review of all available information related to the 
    subject presented above, the FAA has determined that air safety and the 
    public interest require the adoption of the rule as proposed except for 
    minor editorial corrections. The FAA has determined that these minor 
    corrections will not change the meaning of the AD and will not add any 
    additional burden upon the public than was already proposed.
    
    Cost Impact
    
        The FAA estimates that 15 airplanes in the U.S. registry will be 
    affected by this AD, that it will take approximately 22 workhours per 
    airplane to accomplish the required action, and that the average labor 
    rate is approximately $60 an hour. Parts cost approximately $150 per 
    airplane. Based on these figures, the total cost impact of the AD on 
    U.S. operators is estimated to be $22,050 or $1,470 per airplane. This 
    figure is based on the assumption that no affected owner/operator of 
    the affected airplanes has accomplished the required replacement.
        ASTA has informed the FAA that it has no records of parts 
    distribution. The FAA believes that several of the affected airplanes 
    already have the required replacement incorporated, which would reduce 
    the cost impact upon the public.
    
    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 copy of the final evaluation prepared for this 
    action is contained in the Rules Docket. A copy of it may be obtained 
    by contacting the Rules Docket at the location provided under the 
    caption ADDRESSES.
    
    [[Page 57994]]
    
    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 a new airworthiness directive 
    (AD) to read as follows:
    
    96-23-03  Aerospace Technologies of Australia Pty Ltd.: Amendment 
    39-9808; Docket No. 95-CE-103-AD.
    
        Applicability: Models N22B, N24A, and N22S airplanes (all serial 
    numbers), certificated in any category, that are not equipped with a 
    part number (P/N) 1E/N-12-57 fuselage stub fin plate (MOD N759).
    
        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 (c) 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 within the next 100 hours time-in-service 
    after the effective date of this AD, unless already accomplished.
        To prevent structural failure of the fuselage area caused by a 
    cracked stub fin plate, which could result in loss of control of the 
    airplane, accomplish the following:
        (a) Replace the fuselage stub fin plate with one of improved 
    design, P/N 1E/N-12-57 (MOD N759), in accordance with the 
    ACCOMPLISHMENT INSTRUCTIONS section of Nomad Service Bulletin ANMD-
    53-13, Revision 3, dated October 24, 1995.
        (b) 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.
        (c) An alternative method of compliance or adjustment of the 
    compliance time that provides an equivalent level of safety may be 
    approved by the Manager, FAA, Los Angeles Aircraft Certification 
    Office (ACO), 3960 Paramount Boulevard, Lakewood, California 90712. 
    The request shall be forwarded through an appropriate FAA 
    Maintenance Inspector, who may add comments and then send it to the 
    Manager, Los Angeles ACO.
    
        Note 2: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Los Angeles ACO.
    
        (d) The replacement required by this AD shall be done in 
    accordance with Nomad Service Bulletin ANMD-53-13, Revision 3, dated 
    October 24, 1995. 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 Aerospace 
    Technologies of Australia Pty Ltd., ASTA DEFENCE, Private Bag No. 4, 
    Beach Road Lara 3212, Victoria, Australia. Copies may be inspected 
    at the FAA, Central Region, Office of the Assistant Chief Counsel, 
    Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the 
    Office of the Federal Register, 800 North Capitol Street, NW., suite 
    700, Washington, DC.
        (e) This amendment (39-9808) becomes effective on December 23, 
    1996.
    
        Issued in Kansas City, Missouri, on October 28, 1996.
    John R. Colomy,
    Acting Manager, Small Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 96-28164 Filed 11-8-96; 8:45 am]
    BILLING CODE 4910-13-P
    
    
    

Document Information

Effective Date:
12/23/1996
Published:
11/12/1996
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
96-28164
Dates:
Effective December 23, 1996.
Pages:
57993-57994 (2 pages)
Docket Numbers:
Docket No. 95-CE-103-AD, Amendment 39-9808, AD 96-23-03
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
96-28164.pdf
CFR: (1)
14 CFR 39.13