94-2177. Airworthiness Directives; Pratt & Whitney Canada PW100 Series Turboprop Engines  

  • [Federal Register Volume 59, Number 21 (Tuesday, February 1, 1994)]
    [Unknown Section]
    [Page 0]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 94-2177]
    
    
    [[Page Unknown]]
    
    [Federal Register: February 1, 1994]
    
    
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    DEPARTMENT OF TRANSPORTATION
    14 CFR Part 39
    
    [Docket No. 94-ANE-04; Amendment 39-8808; AD 94-03-02]
    
     
    
    Airworthiness Directives; Pratt & Whitney Canada PW100 Series 
    Turboprop Engines
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule, request for comments.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
    is applicable to Pratt & Whitney Canada PW100 series turboprop engines. 
    This action requires a life limit reduction for affected high pressure 
    turbine (HPT) disks, and establishes a drawdown schedule for disks 
    currently near, at, or greater than the new reduced service life. This 
    amendment is prompted by reports of two HPT disk failures, one of which 
    was uncontained. The actions specified in this AD are intended to 
    prevent an uncontained HPT disk failure and damage to the aircraft.
    
    DATES: Effective February 16, 1994.
        Comments for inclusion in the Rules Docket must be received on or 
    before April 4, 1994.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), New England Region, Office of the Assistant Chief 
    Counsel, Attention: Rules Docket No. 94-ANE-04, 12 New England 
    Executive Park, Burlington, MA 01803-5299.
        The service information referenced in this AD may be obtained from 
    Pratt & Whitney Canada, 1000, Marie-Victorin, Longueuil, Quebec, Canada 
    J4G 1A1. This information may be examined at the FAA, New England 
    Region, Office of the Assistant Chief Counsel, 12 New England Executive 
    Park, Burlington, MA.
    
    FOR FURTHER INFORMATION CONTACT: Marc Bouthillier, Aerospace Engineer, 
    Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
    New England Executive Park, Burlington, MA 01803-5299; telephone (617) 
    238-7135, fax (617) 238-7199.
    
    SUPPLEMENTARY INFORMATION: Transport Canada, which is the airworthiness 
    authority for Canada, recently notified the Federal Aviation 
    Administration (FAA) that an unsafe condition may exist on Pratt & 
    Whitney Canada (PWC) Model PW118, PW118A, PW120, PW120A, PW121, PW123, 
    PW124B, and PW125B turboprop engines. Transport Canada advises that 
    they have received reports of two high pressure turbine (HPT) disk 
    failures in the rim region with subsequent inflight engine shutdowns. 
    Both disks failed at the same location in low cycle fatigue. One event 
    was fully contained within the engine casings; the second event 
    liberated some small debris through the engine nacelle.
        Transport Canada issued AD CF-94-XX, dated January XX, 1994, in 
    order to assure the airworthiness of these PWC PW100 series turboprop 
    engines in Canada.
        This engine model is manufactured in Canada and is type 
    certificated for operation in the United States under the provisions of 
    Section 21.29 of the Federal Aviation Regulations and the applicable 
    bilateral airworthiness agreement. Pursuant to this bilateral 
    airworthiness agreement, Transport Canada has kept the FAA informed of 
    the situation described above. The FAA has examined the findings of 
    Transport Canada, reviewed all available information, and determined 
    that AD action is necessary for products of this type design that are 
    certificated for operation in the United States.
        Since an unsafe condition has been identified that is likely to 
    exist or develop on other PWC PW100 series turboprop engines of the 
    same type design registered in the United States, the proposed AD would 
    require a life limit reduction for affected HPT disks, and establishes 
    a drawdown schedule to manage disks currently near, at, or greater than 
    the new reduced service life, without significant effect on flight 
    safety or economic factors. The FAA has determined that a reduction in 
    cyclic life limit, based on demonstrated crack initiation and 
    propagation rates, would minimize the possibility of a disk failure, 
    and restore the level of safety required at the time of type 
    certification.
        Since a situation exists that requires the immediate adoption of 
    this regulation, it is found that notice and opportunity for prior 
    public comment hereon are impracticable, and that good cause exists for 
    making this amendment effective in less than 30 days.
    
    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 should 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 notice must submit a self-addressed, 
    stamped postcard on which the following statement is made: ``Comments 
    to Docket Number 94-ANE-04.'' The postcard will be date stamped and 
    returned to the commenter.
        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 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, Safety.
    
    Adoption of the Amendment
    
        Accordingly, pursuant to the authority delegated to me by the 
    Administrator, the Federal Aviation Administration amends 14 CFR part 
    39 of the Federal Aviation Regulations as follows:
    
    PART 39--AIRWORTHINESS DIRECTIVES
    
        1. The authority citation for part 39 continues to read as follows:
    
        Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
    106(g); and 14 CFR 11.89.
    
    
    Sec. 39.13  [AMENDED]
    
        2. Section 39.13 is amended by adding the following new 
    airworthiness directive:
    
    94-03-02 Pratt & Whitney Canada: Amendment 39-8808. Docket 94-ANE-
    04.
        Applicability: Pratt & Whitney Canada (PWC) Model PW118, PW118A, 
    PW120, PW120A, PW121, PW123, PW124B, and PW125B turboprop engines, 
    installed on but not limited to Dehavilland DHC-8 series, Embraer 
    EMB-120 series, ATR-42 and -72 series, Fokker 50 series, Canadair 
    Models CL-215T and 415, Dornier 328 series, British Aerospace ATP 
    series, and XAC Y7-200A aircraft.
        Compliance: Required as indicated, unless accomplished 
    previously.
        To prevent an uncontained HPT disk failure and damage to the 
    aircraft, accomplish the following:
        (a) Remove from service high pressure turbine (HPT) disks, part 
    numbers (P/N) 3035711 and 3038411, and replace with a serviceable 
    part in accordance with the following schedule, based on cycles in 
    service (CIS) on the effective date of this airworthiness directive 
    (AD):
        (1) For disks with 13,000 or more CIS, remove within the next 
    1,000 CIS after the effective date of this AD, but not to exceed 
    15,000 total CIS.
        (2) For disks with 12,000 or more CIS, but less than 13,000 CIS, 
    remove within the next 1,250 CIS, but not to exceed 14,000 total 
    CIS.
        (3) For disks with 10,000 or more CIS, but less than 12,000 CIS, 
    remove within the next 1,750 CIS, but not to exceed 13,250 total 
    CIS.
        (4) For disks with 8,000 or more CIS, but less than 10,000 CIS, 
    remove within the next 2,500 CIS, but not to exceed 12,000 total 
    CIS.
        (5) For disks with less than 8,000 CIS, remove at or prior to 
    accumulating 10,000 total CIS.
        (b) This AD establishes a new service cycle life limit for HPT 
    disks, P/N 3035711 and 3038411, of 10,000 total CIS.
    
        Note: Further information on the life limit reduction for 
    affected HPT disks can be found in PWC Service Information Letter 
    No. 307, dated December 17, 1993.
    
        (c) 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, Engine Certification Office. The 
    request should be forwarded through an appropriate FAA Principal 
    Maintenance Inspector, who may add comments and then send it to the 
    Manager, Engine Certification Office.
    
        Note: Information concerning the existence of approved 
    alternative methods of compliance with this airworthiness directive, 
    if any, may be obtained from the Engine Certification Office.
    
        (d) Special flight permits may be issued in accordance with FAR 
    21.197 and 21.199 to operate the aircraft to a location where the 
    requirements of this AD can be accomplished.
        (e) This amendment becomes effective on February 16, 1994.
    
        Issued in Burlington, Massachusetts, on January 24, 1994.
    Jay J. Pardee,
    Manager, Engine and Propeller Directorate, Aircraft Certification 
    Service.
    [FR Doc. 94-2177 Filed 1-31-94; 8:45 am]
    BILLING CODE 4910-13-P
    
    
    

Document Information

Effective Date:
2/16/1994
Published:
02/01/1994
Department:
Transportation Department
Entry Type:
Uncategorized Document
Action:
Final rule, request for comments.
Document Number:
94-2177
Dates:
Effective February 16, 1994.
Pages:
0-0 (1 pages)
Docket Numbers:
Federal Register: February 1, 1994, Docket No. 94-ANE-04, Amendment 39-8808, AD 94-03-02
CFR: (1)
14 CFR 39.13