95-7784. Airworthiness Directives; Beech Aircraft Corporation Model 1900D Airplanes  

  • [Federal Register Volume 60, Number 61 (Thursday, March 30, 1995)]
    [Rules and Regulations]
    [Pages 16366-16367]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 95-7784]
    
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 95-CE-15-AD; Amendment 39-9184; AD 95-02-17]
    
    
    Airworthiness Directives; Beech Aircraft Corporation Model 1900D 
    Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule; request for comments.
    
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    SUMMARY: This document publishes in the Federal Register an amendment 
    adopting Airworthiness Directive (AD) 95-02-17, which was sent 
    previously to known U.S. owners and operators of certain Beech Aircraft 
    Corporation Model 1900D airplanes. This AD requires inspecting (one-
    time) the elevator trim tab control cables at the top of the vertical 
    stabilizer to ensure that cables (at the left, right, and crossover 
    pulleys) are correctly routed around the pulleys, within the cable 
    guide pins, and are not contacting any structure; and replacing any 
    cable that is incorrectly routed or chafed. The actions specified by 
    this AD are intended to prevent in-flight separation of the elevator 
    trim tab control cable caused by misrouting, which could result in loss 
    of control of the airplane.
    
    DATES: Effective April 17, 1995, to all persons except those to whom it 
    was made immediately effective by priority letter AD 95-02-17, issued 
    January 25, 1995, which contained the requirements of this amendment.
        Comments for inclusion in the Rules Docket must be received on or 
    before June 16, 1995.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Central Region, Office of the Assistant Chief 
    Counsel, Attention: Rules Docket 95-CE-15-AD, Room 1558, 601 E. 12th 
    Street, Kansas City, Missouri 64106.
        Information that relates to this AD may be examined at the Rules 
    Docket at the address above.
    
    FOR FURTHER INFORMATION CONTACT: Mr. Steven E. Potter, Wichita Aircraft 
    Certification Office, FAA, 1801 Airport Road, Mid-Continent Airport, 
    Wichita, Kansas 67209; telephone (316) 946-4124; facsimile (316) 946-
    4407.
    
    SUPPLEMENTARY INFORMATION: The FAA has received a report of an in-
    flight separation of the elevator trim tab control (``nose up'' and 
    ``nose down'') cable on a Beech Model 1900D airplane. The reported 
    cable separation prevented the airplane flight crew from using manual 
    and electrical nose up trim, and the flight crew experienced high 
    elevator ``nose down'' control forces. The flight crew was then able to 
    land the airplane without further incident.
        Investigation of this incident showed that the elevator trim tab 
    control cable had separated in the vicinity of its guide pulley, which 
    is located at the top of the vertical stabilizer. The cable had been 
    routed outside the lower cable pulley guard pin instead of under the 
    guard pin. The routing configuration caused the cable to rub against 
    the stabilizer rib, resulting in cable separation.
        Since an unsafe condition has been identified that is likely to 
    exist or develop in other Beech Model 1900D airplanes of the same type 
    design, the FAA issued priority letter AD 95-02-17 on January 25, 1995, 
    to prevent in-flight separation of the elevator trim tab control cable 
    caused by misrouting, which could result in loss of control of the 
    airplane. The AD requires inspecting (one-time) the elevator trim tab 
    control cables at the top of the vertical stabilizer to ensure that 
    cables (at the left, right, and crossover pulleys) are correctly routed 
    around the pulleys, within the cable guide pins, and are not contacting 
    any structure; and replacing any cable that is incorrectly routed or 
    chafed. Accomplishment of the required actions is in accordance with 
    the Beech 1900D Maintenance Manual, part number 129-590000-15A11, 
    Chapters 5-20-07, page 203; 6-40-00, page 3; 6-50-00, page 16; and 27-
    30-04, pages 202 and 203.
        Since it was found that immediate corrective action was required, 
    notice and opportunity for prior public comment thereon were 
    impracticable and contrary to the public interest, and good cause 
    existed to make AD 95-02-17 effective immediately by individual letters 
    issued on January 25, 1995, to known U.S. operators of certain Beech 
    Model 1900D airplanes. These conditions still exist, and the AD is 
    hereby published in the Federal Register as an amendment to section 
    39.13 of the Federal Aviation Regulations (14 CFR 39.13) to make it 
    effective as to all persons.
    
    Comments Invited
    
        Although this action is in the form of a final rule that involves 
    requirements affecting immediate flight safety and, thus, was not 
    preceded by notice and opportunity to 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 above. 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 No. 95-CE-15-AD.'' 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 [[Page 16367]] 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 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 adding a new airworthiness directive 
    to read as follows:
    
    95-02-17 Beech Aircraft Corporation: Amendment 39-9184; Docket No. 
    95-CE-15-AD.
    
        Applicability: Model 1900D airplanes, serial numbers UE-1 
    through UE-131, certificated in any category.
    
        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 use the authority 
    provided in paragraph (c) of this AD to request approval from the 
    FAA. This approval may address either no action, if the current 
    configuration eliminates the unsafe condition, or different actions 
    necessary to address the unsafe condition described in this AD. Such 
    a request should include an assessment of the effect of the changed 
    configuration on the unsafe condition addressed by this AD. In no 
    case does the presence of any modification, alteration, or repair 
    remove any aircraft from the applicability of this AD.
    
        Compliance: Required prior to further flight after the effective 
    date of this AD, unless already accomplished.
        To prevent in-flight separation of the elevator trim tab control 
    cable, which could lead to loss of control of the airplane, 
    accomplish the following:
        (a) In accordance with Beech 1900D Maintenance Manual, part 
    number 129-590000-15A11, Chapters 5-20-07, page 203; 6-40-00, page 
    3; 6-50-00, page 16; and 27-30-04, pages 202 and 203:
        (1) Remove access panel Number 333ATC, which is located on the 
    top surface of the horizontal stabilizer, to gain access to the 
    elevator trim tab cable, guides, and pulleys;
        (2) Inspect the cable routing to ensure that cables (at the 
    left, right, and crossover pulleys) are correctly routed around the 
    pulleys, within the cable guide pins, and are not contacting any 
    structure; and
        (3) Replace any cable that is incorrectly routed (cable that 
    does not meet the criteria above in paragraph (a)(2) of this AD) or 
    is chafed.
    
        Note 2: The procedures listed in Beech Communique 1900D-112, 
    dated January 1995, ``Inspection of Elevator Trim Tab Control 
    Cables'', are similar to those included in this priority letter AD. 
    Complying with all procedures in Beech Communique 1900D-112 is 
    considered equivalent to the requirements of paragraphs (a)(1), 
    (a)(2), and (a)(3) of this AD, and is considered ``unless already 
    accomplished'' for this portion of the AD.
    
        Note 3: The compliance time specified in this AD takes 
    precedence over that specified in Beech Communique 1900D-112, dated 
    January 1995, ``Inspection of Elevator Trim Tab Control Cables''.
    
        (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, Wichita Aircraft Certification Office 
    (ACO), FAA, 1801 Airport Road, Mid-Continent Airport, Wichita, 
    Kansas 67209. The request shall be forwarded through an appropriate 
    FAA Maintenance Inspector, who may add comments and then send it to 
    the Manager, Wichita ACO.
    
        Note 4: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Wichita ACO.
    
        (d) Information that relates to this AD may be examined at the 
    FAA, Central Region, Office of the Assistant Chief Counsel, Room 
    1558, 601 E. 12th Street, Kansas City, Missouri 64106.
        (e) This amendment (39-9184) becomes effective on April 17, 
    1995, to all persons except those persons to whom it was made 
    immediately effective by priority letter AD 95-02-17, issued January 
    25, 1995, which contained the requirements of this amendment.
    
        Issued in Kansas City, Missouri, on March 24, 1995.
    Dwight A. Young,
    Acting Manager, Small Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 95-7784 Filed 3-29-95; 8:45 am]
    BILLING CODE 4910-13-U
    
    

Document Information

Effective Date:
4/17/1995
Published:
03/30/1995
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
95-7784
Dates:
Effective April 17, 1995, to all persons except those to whom it was made immediately effective by priority letter AD 95-02-17, issued January 25, 1995, which contained the requirements of this amendment.
Pages:
16366-16367 (2 pages)
Docket Numbers:
Docket No. 95-CE-15-AD, Amendment 39-9184, AD 95-02-17
PDF File:
95-7784.pdf
CFR: (1)
14 CFR 39.13