95-4124. Airworthiness Directives; Teledyne Continental Motors IO-346, IO- 520, and IO-550 Series Reciprocating Engines  

  • [Federal Register Volume 60, Number 37 (Friday, February 24, 1995)]
    [Rules and Regulations]
    [Pages 10308-10310]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 95-4124]
    
    
    
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    DEPARTMENT OF TRANSPORTATION
    14 CFR Part 39
    
    [Docket No. 94-ANE-57; Amendment 39-9150; AD 95-03-14]
    
    
    Airworthiness Directives; Teledyne Continental Motors IO-346, IO-
    520, and IO-550 Series Reciprocating Engines
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This amendment supersedes an existing airworthiness directive 
    (AD), applicable to certain Teledyne Continental Motors (TCM) IO-346, 
    IO-520, and IO-550 series reciprocating engines, that currently 
    requires initial and repetitive inspections of the engine mount 
    brackets for cracks, and if found cracked, replacement with improved 
    design engine mount brackets. All engine mount brackets require 
    replacement with improved design engine mount brackets at the next 
    engine removal after the effective date of that airworthiness directive 
    (AD). This amendment clarifies the identification procedures to 
    determine which engine mount brackets must be inspected. This amendment 
    is prompted by reports that the engine mount bracket part numbers, 
    which are ink stamped, can be easily obliterated. The actions specified 
    by this AD are intended to prevent engine separation from the aircraft 
    due to cracks in the engine mount brackets.
    
    DATES: Effective March 13, 1995.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of March 13, 1995.
        Comments for inclusion in the Rules Docket must be received on or 
    before April 25, 1995.
    
    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-57, 12 New England 
    Executive Park, Burlington, MA 01803-5299.
        The service information referenced in this AD may be obtained from 
    Teledyne Continental Motors, P.O. Box 90, Mobile, AL 36601; telephone 
    (334) 438-3411. This information may be examined at the FAA, New 
    England Region, Office of the Assistant Chief Counsel, Burlington, MA; 
    or at the Office of the Federal Register, 800 North Capitol Street, 
    NW., suite 700, Washington, DC.
    
    FOR FURTHER INFORMATION CONTACT: Jerry Robinette, Aerospace Engineer, 
    Atlanta Aircraft Certification Office, FAA, Small Airplane Directorate, 
    Campus Building, 1701 Columbia Ave., Suite 2-160, College Park, GA 
    30337-2748; telephone (404) 305-7371, fax (404) 305-7348.
    
    SUPPLEMENTARY INFORMATION: On April 19, 1994, the Federal Aviation 
    Administration (FAA) issued airworthiness directive (AD) 94-09-07, 
    Amendment 39-8896 (59 FR 23148, May 5, 1994), applicable to certain 
    Teledyne Continental Motors (TCM) IO-346, IO-520, and IO-550 series 
    reciprocating engines, to require initial and repetitive dye penetrant 
    inspections for cracks in certain lower left engine mount brackets, 
    Part Number (P/N) 630695. If the lower left engine mount bracket is 
    found cracked, that AD requires replacing both the lower left and lower 
    right engine mount brackets with improved design engine mount brackets, 
    P/N 653306 and 653305, respectively. If a crack is not detected, the 
    lower left engine mount bracket requires repetitive inspections at 
    intervals not to exceed 500 hours time in service (TIS) until the next 
    engine removal, at which time engine mount brackets, P/N 630694 and 
    630695, are replaced with improved design engine mount brackets, P/N 
    653306 and 653305. Installation of these improved design engine mount 
    brackets constitutes terminating action to the inspection requirements 
    of that AD. That action was prompted by reports of cracks in engine 
    mount brackets on engines that have completed at least one overhaul 
    cycle. That condition, if not corrected, could result in engine 
    separation from the aircraft due to cracks in the engine mount 
    brackets.
        Since the issuance of that AD, the FAA has received reports of 
    difficulty in identifying the engine mount brackets that must be 
    inspected. The P/N is ink-stamped on the part and is quite easily 
    obliterated. The problem arises when the Casting Number (C/N), which is 
    different from the P/N, is mistaken for the P/N, and the AD is 
    incorrectly believed to not apply.
        The FAA has reviewed and approved the technical contents of TCM 
    Mandatory Service Bulletin (MSB) No. MSB94-9, dated October 21, 1994, 
    that provides positive identification of affected engine mount brackets 
    that require inspection, and replacement, if necessary.
        Since an unsafe condition has been identified that is likely to 
    exist or develop on other engines of this same type design, this AD 
    supersedes AD 94-09-07 to clarify the identification procedures to 
    determine which engine mount brackets must be inspected. The actions 
    are required to be accomplished in accordance with the MSB described 
    previously.
        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-57.'' 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 
    [[Page 10309]] 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, 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. 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 removing Amendment 39-8896 (59 FR 
    23148, May 5, 1994), and by adding a new airworthiness directive, 
    Amendment 39-9150, to read as follows:
    
    95-03-14  Teledyne Continental Motors: Amendment 39-9150. Docket 94-
    ANE-57. Supersedes AD 94-09-07, Amendment 39-8896.
    
        Applicability: Teledyne Continental Motors (TCM) engine models 
    IO-346A, IO-346B, IO-520C, IO-520CB, and IO-550C; rebuilt engine 
    model IO-520C with serial numbers (S/N) 287051-R and lower; rebuilt 
    engine model IO-520CB with S/N 282226-R and lower; rebuilt engine 
    model IO-550C with S/N 271742-R and lower; and all factory 
    overhauled IO-520C, IO-520CB, and IO-550C engines with a build date 
    prior to August 6, 1992. These engines are installed on but not 
    limited to Beech model A23, A23A, 95-C55, 95-C55A, D55, D55A, E55, 
    E55A, 58, and 58A airplanes.
        Compliance: Required as indicated, unless accomplished 
    previously.
        To prevent engine separation from the aircraft due to cracks in 
    the engine mount brackets, accomplish the following:
        (a) For engines with engine mount brackets that have completed 
    at least one engine overhaul or rebuild cycle, or have accumulated 
    2,500 or more hours time in service (TIS) on the effective date of 
    this airworthiness directive (AD), inspect the lower left engine 
    mount bracket, Part Number (P/N) 630695 or Casting Number (C/N) 
    630724, for cracks using the dye penetrant techniques specified in 
    this paragraph and in accordance with TCM Mandatory Service Bulletin 
    (MSB) No. MSB94-9, dated October 21, 1994, within the next 50 hours 
    TIS after the effective date of this AD.
    
        Note 1: TCM MSB No. MSB94-9, dated October 21, 1994, differs 
    from TCM MSB No. M92-13, dated September 4, 1992, which was 
    referenced in AD 94-09-07, only in clarification of part 
    identification by utilizing a cross reference table for P/N and C/N.
        Note 2: The P/N is ink stamped on the part and may not be 
    visible. The engine mount bracket can be identified by the C/N which 
    is cast in the engine mount bracket.
    
        (1) Perform the dye penetrant inspection as follows:
    
        Note: Military Specification MIL-I-6866 and American Society of 
    Testing Materials specifications ASTM E1417-93 and E165-9 contain 
    additional information on dye penetrant inspection processes.
    
        (i) Preparation: clean and dry all parts in such a manner as to 
    leave the surfaces free from grease, oil, soaps, alkalies, and other 
    substances which would interfere with inspection. Vapor degreasing 
    is generally suitable for this purpose.
        (ii) Penetrant Application Procedure: after preparation, spray 
    or brush the parts with the penetrant, and allow to stand for not 
    less than 5 minutes. The effectiveness of the penetrant increases if 
    left standing for a longer time, as the penetrant will reach finer 
    discontinuities.
        (iii) Penetrant Cleaning: clean the parts thoroughly using a 
    medium which will remove penetrant from the surfaces of parts; wash 
    with water when the penetrant is water soluble. When other than 
    water soluble penetrants are used, the penetrant shall be removed 
    with a suitable cleaner. Avoid excessive cleaning which would remove 
    the penetrant from discontinuities.
        (iv) Drying: dry the parts as thoroughly as possible. Drying of 
    parts may be accomplished by evaporation at room temperature or by 
    placing the parts in a circulating warm air oven or in the air 
    stream of a hot air dryer. Avoid excessive drying time or drying 
    temperatures above 75 deg.C (165 deg.F) to prevent excessive 
    evaporation of the penetrant. If heat is used for drying parts, cool 
    parts to approximately 50 deg.C (120 deg.F) before proceeding to the 
    developing procedure.
        (v) Developing: apply the developer to the dry parts as lightly 
    and as evenly as possible, using as thin a coating of developer as 
    is possible. A translucent film is adequate. Mix wet developer by 
    agitation immediately prior to applying it. After applying the 
    developer, take care that no penetrant indication is disturbed or 
    obliterated in subsequent handling.
        (vi) Examination: examine the developed penetrant indications in 
    accordance with the dye penetrant manufacturer's instructions. 
    Examine parts for indications of discontinuities open to the 
    surface.
        (vii) Final cleaning: clean the parts following the inspection 
    to remove penetrant and developer.
    
        Note 1: Caution: because of differences among penetrants, take 
    care to ensure that the final cleaner, the penetrant, the penetrant 
    remover, and the developer are suitable for use with each other.
        Note 2: Caution: all penetrant materials should be kept as free 
    from moisture as possible.
        Note 3: Caution: most penetrants, cleaning agents, and developer 
    suspensions are low flash point material; use caution to prevent 
    fires.
    
        (2) If no crack is detected, inspect in accordance with 
    paragraph (a) of this AD at intervals not to exceed 500 hours TIS 
    since the last inspection.
        (3) If a crack is detected, prior to further flight replace both 
    the lower left engine mount bracket, P/N 630695 or C/N 630724, and 
    lower right engine mount bracket, P/N 630694 or C/N 630723, with 
    improved design engine mount brackets, P/N 653306 or C/N 653299, and 
    P/N 653305 or C/N 653298, respectively.
        (b) For all engines, replace both the lower left engine mount 
    bracket, P/N 630695 or PC/N 630724, and lower right engine mount 
    bracket, P/N 630694 or C/N 630723, with improved design engine mount 
    brackets, PP/N 653306 or C/N 653299, and P/N 653305 or C/N 653298, 
    respectively, at the next engine removal after the effective date of 
    this AD.
        (c) Installation of the improved design engine mount brackets, 
    P/N 653306 or C/N 653299, and P/N 653305 or C/N 653298, constitutes 
    terminating action to the inspection requirements of this AD.
        (d) 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, Atlanta Aircraft Certification 
    Office. The request should be forwarded through an appropriate FAA 
    Maintenance Inspector, who may add comments and then send it to the 
    Manager, Atlanta Aircraft Certification Office.
    
        Note: Information concerning the existence of approved 
    alternative methods of compliance with this airworthiness directive, 
    if any, may be obtained from the Atlanta Aircraft Certification 
    Office.
    
        (e) 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 aircraft to a location where 
    the inspection may be performed. [[Page 10310]] 
        (f) The inspections and replacement shall be done in accordance 
    with the following service document:
    
    ------------------------------------------------------------------------
                   Document No.                 Pages           Date        
    ------------------------------------------------------------------------
    TCM MSB No. MSB94-9......................      1-2  Oct. 21, 1994.      
    Total pages: 2.                                                         
    ------------------------------------------------------------------------
    
    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 Teledyne Continental Motors, P.O. 
    Box 90, Mobile, AL 36601; telephone (334) 438-3411. Copies may be 
    inspected at the FAA, New England Region, Office of the Assistant 
    Chief Counsel, 12 New England Executive Park, Burlington, MA; or at 
    the Office of the Federal Register, 800 North Capitol Street NW., 
    suite 700, Washington, DC.
        (g) This amendment becomes effective on March 13, 1995.
    
        Issued in Burlington, Massachusetts, on February 8, 1995.
    James C. Jones,
    Acting Manager, Engine and Propeller Directorate, Aircraft 
    Certification Service.
    [FR Doc. 95-4124 Filed 2-23-95; 8:45 am]
    BILLING CODE 4910-13-P
    
    

Document Information

Effective Date:
3/13/1995
Published:
02/24/1995
Department:
Transportation Department
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
95-4124
Dates:
Effective March 13, 1995.
Pages:
10308-10310 (3 pages)
Docket Numbers:
Docket No. 94-ANE-57, Amendment 39-9150, AD 95-03-14
PDF File:
95-4124.pdf
CFR: (1)
14 CFR 39.13