98-3637. Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes  

  • [Federal Register Volume 63, Number 31 (Tuesday, February 17, 1998)]
    [Rules and Regulations]
    [Pages 7688-7689]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 98-3637]
    
    
    
    [[Page 7688]]
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 97-CE-45-AD; Amendment 39-10328; AD 98-04-16]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Pilatus Aircraft Ltd. Models PC-12 and 
    PC-12/45 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 certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-
    12/45 airplanes. This AD requires inspecting the aileron tie-rod jam 
    nuts for looseness, tightening any loose jam nuts, and installing a 
    locking sleeve on both ends of the aileron tie-rod in the chain-drive 
    of the aileron system. The AD results from an incident where the 
    aileron tie-rod jam nuts on the chain-drive of the aileron system 
    became loose. This caused a differential of aileron control between the 
    pilot's control wheel and the co-pilot's control wheel. The actions 
    specified by this AD are intended to prevent such aileron control 
    differential caused by the aileron tie-rod jam nuts becoming loose, 
    which could result in loss of aileron control and consequent loss of 
    control of the airplane.
    
    DATES: Effective April 2, 1998.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of April 2, 1998.
    
    ADDRESSES: Service information that applies to this AD may be obtained 
    from Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. This 
    information may also be examined at the Federal Aviation Administration 
    (FAA), Central Region, Office of the Regional Counsel, Attention: Rules 
    Docket No. 97-CE-45-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. Roman T. Gabrys, Aerospace 
    Engineer, Small Airplane Directorate, Airplane Certification Service, 
    FAA, 1201 Walnut, suite 900, Kansas City, Missouri 64106; telephone: 
    (816) 426-6932; facsimile: (816) 426-2169.
    
    SUPPLEMENTARY INFORMATION:
    
    Events Leading to the Issuance of This AD
    
        A proposal to amend part 39 of the Federal Aviation Regulations (14 
    CFR part 39) to include an AD that would apply to certain Pilatus 
    Models PC-12 and PC-12/45 airplanes was published in the Federal 
    Register as a notice of proposed rulemaking (NPRM) on October 6, 1997 
    (62 FR 52055). The NPRM proposed to require inspecting the aileron tie-
    rod jam nuts for looseness, tightening any loose jam nuts, and 
    installing a locking sleeve on both ends of the aileron tie-rod in the 
    chain-drive of the aileron system. Accomplishment of the proposed 
    actions as specified in the NPRM would be in accordance with Pilatus 
    Service Bulletin No. 27-001, dated March 25, 1997.
        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 40 airplanes in the U.S. registry will be 
    affected by this AD, that it will take approximately 5 workhours per 
    airplane to accomplish the required action, and that the average labor 
    rate is approximately $60 an hour. Parts will be provided by the 
    manufacturer at no cost to the owner/operator of the affected 
    airplanes. Based on these figures, the total cost impact of this AD on 
    U.S. operators is estimated to be $12,000, or $300 per airplane.
    
    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.
    
    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:
    
    98-04-16  Pilatus Aircraft Ltd.: Amendment 39-10328; Docket No. 97-
    CE-45-AD.
    
        Applicability: Models PC-12 and PC-12/45 airplanes, serial 
    numbers 101 through 169, certificated in any category.
    
        Note 1: The modification required by this AD is incorporated at 
    manufacture on Models PC-12 and PC-12/45 airplanes, beginning with 
    serial number 170. Airplanes with this modification are not affected 
    by this AD.
    
        Note 2: 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 (d) 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.
    
    
    [[Page 7689]]
    
    
        Compliance: Required as indicated in the body of this AD, unless 
    already accomplished.
        To prevent a differential of aileron control between the pilot's 
    control wheel and the co-pilot's control wheel caused by the aileron 
    tie-rod jam nuts becoming loose, which could result in loss of 
    aileron control and consequent loss of control of the airplane, 
    accomplish the following:
        (a) Within the next 100 hours time-in-service (TIS) after the 
    effective date of this AD, inspect the aileron tie-rod jam nuts for 
    looseness in accordance with the Accomplishment Instructions section 
    of Pilatus Service Bulletin No. 27-001, dated March 25, 1997. Prior 
    to further flight, tighten any loose jam nuts in accordance with the 
    above-referenced service bulletin.
        (b) Within the next 100 hours TIS after the effective date of 
    this AD, install a locking sleeve on both ends of the aileron tie-
    rod in the chain-drive of the aileron system in accordance with the 
    Accomplishment Instructions section of Pilatus Service Bulletin No. 
    27-001, dated March 25, 1997.
        (c) 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.
        (d) An alternative method of compliance or adjustment of the 
    compliance time that provides an equivalent level of safety may be 
    approved by the Manager, Small Airplane Directorate, 1201 Walnut, 
    suite 900, Kansas City, Missouri 64106. The request shall be 
    forwarded through an appropriate FAA Maintenance Inspector, who may 
    add comments and then send it to the Manager, Small Airplane 
    Directorate.
    
        Note 3: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Small Airplane Directorate.
    
        (e) The inspection, tightening, and installation required by 
    this AD shall be done in accordance with Pilatus Service Bulletin 
    No. 27-001, dated March 25, 1997. 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 
    Pilatus Aircraft Ltd., CH-6370 Stans, Switzerland. Copies may be 
    inspected at the FAA, Central Region, Office of the Regional 
    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.
    
        Note 4: The subject of this AD is addressed in Swiss AD HB 97-
    174, dated April 30, 1997.
    
        (f) This amendment (39-10328) becomes effective on April 2, 
    1998.
    
        Issued in Kansas City, Missouri, on February 5, 1998.
    Michael Gallagher,
    Manager, Small Airplane Directorate, Aircraft Certification Service.
    [FR Doc. 98-3637 Filed 2-13-98; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
4/2/1998
Published:
02/17/1998
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
98-3637
Dates:
Effective April 2, 1998.
Pages:
7688-7689 (2 pages)
Docket Numbers:
Docket No. 97-CE-45-AD, Amendment 39-10328, AD 98-04-16
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
98-3637.pdf
CFR: (1)
14 CFR 39.13