99-13875. Airworthiness Directives; Cessna Aircraft Company Model 402C Airplanes  

  • [Federal Register Volume 64, Number 106 (Thursday, June 3, 1999)]
    [Rules and Regulations]
    [Pages 29781-29783]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 99-13875]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 99-CE-21-AD; Amendment 39-11184; AD 99-11-13]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Cessna Aircraft Company Model 402C 
    Airplanes
    
    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 
    applies to certain Cessna Aircraft Company (Cessna) Model 402C 
    airplanes. This AD requires inspecting the forward, aft, and auxiliary 
    wing spars for cracks; repairing any cracks found; and reporting the 
    results of the inspection to the Federal Aviation Administration (FAA). 
    This AD is the result of an accident of one of the affected airplanes 
    where the right-hand wing failed just inboard of the nacelle at Wing 
    Station (WS) 87. Investigation of this accident revealed fatigue 
    cracking of the forward main spar that initiated at the edge of the 
    front spar forward lower spar cap. The actions specified by this AD are 
    intended to detect and correct any cracks in the forward, aft, and 
    auxiliary wing spars, which could result in reduced or loss of control 
    of the airplane.
    
    DATES: Effective June 21, 1999.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of June 21, 1999.
        Comments for inclusion in the Rules Docket must be received on or 
    before July 23, 1999.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Central Region, Office of the Regional Counsel, 
    Attention: Rules Docket No. 99-CE-21-AD, Room 1558, 601 E. 12th Street, 
    Kansas City, Missouri 64106.
        Service information that applies to this AD may be obtained from 
    the Cessna Aircraft Company, P. O. Box 7706, Wichita, Kansas 67277; 
    telephone: (316) 941-7550, facsimile: (316) 942-9008. This information 
    may also be examined at the Federal Aviation Administration (FAA), 
    Central Region, Office of the Regional Counsel, Attention: Rules Docket 
    No. 99-CE-21-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. Eual Conditt, Aerospace Engineer, 
    FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 
    100, Mid-Continent Airport, Wichita, Kansas 67209, telephone: (316) 
    946-4128; facsimile: (316) 946-4407.
    
    SUPPLEMENTARY INFORMATION:
    
    Discussion
    
        The FAA has received a report of an accident on a Cessna Model 402C 
    airplane where the right-hand wing failed just inboard of the nacelle 
    at Wing Station (WS) 87 during a normal descent. Investigation of this 
    accident revealed fatigue cracking of the forward main spar that 
    initiated at the edge of the front spar forward lower spar cap.
        The airplane involved in the above-referenced accident had 
    accumulated over 20,000 hours time-in-service (TIS). Analysis shows 
    that the fatigue cracks could propagate after 10,000 hours TIS. 
    Information available to the FAA shows that a large percentage of the 
    Cessna Model 402C airplane fleet has already accumulated 10,000 hours 
    TIS.
    
    Relevant Service Information
    
        Cessna has issued Service Bulletin MEB99-3, dated May 6, 1999, 
    which includes procedures for conducting an internal and external 
    inspection of the forward, aft, and auxiliary wing spars for cracks.
    
    The FAA's Determination
    
        After examining the circumstances and reviewing all available 
    information related to the incidents described above, including the 
    relevant service information, the FAA has determined that:
    
    --In order to detect cracking on Cessna Model 402C airplanes, an 
    external and internal inspection of the forward, aft, and auxiliary 
    wing spars for cracks should be accomplished upon accumulating 10,000 
    hours total TIS on the airplane or within the next 25 hours TIS for 
    those airplanes having already accumulated 10,000 hours TIS; and
    --AD action should be taken to assure that these inspections are 
    accomplished.
    
    Explanation of the Provisions of the AD
    
        Since an unsafe condition has been identified that is likely to 
    exist or develop in other Cessna Model 402C airplanes of the same type 
    design, this AD requires inspecting the forward, aft, and auxiliary 
    wing spars for cracks; repairing any cracks found; and reporting the 
    results of the inspection to the FAA.
        Accomplishment of the inspections as specified in this AD is 
    required in accordance with Cessna Service Bulletin MEB99-3, dated May 
    6, 1999. The repair, if necessary, is required in accordance with an 
    FAA-approved repair scheme.
    
    Possible Follow-Up AD Action
    
        The FAA is requiring a reporting requirement of the inspection 
    results in order to analyze the situation and determine whether 
    repetitive inspections of the wing spars are necessary. The FAA will 
    review all information received and will then determine whether 
    additional AD action is necessary.
    
    [[Page 29782]]
    
    Determination of the Effective Date of the AD
    
        Since a situation (possible loss of control of the airplane caused 
    by a cracked wing spar) exists that requires the immediate adoption of 
    this regulation, it is found that notice and opportunity for public 
    prior 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 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 rule must submit a self-addressed, 
    stamped postcard on which the following statement is made: ``Comments 
    to Docket No. 99-CE-21-AD.'' The postcard will be date stamped and 
    returned to the commenter.
    
    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.
        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 (otherwise, an evaluation is 
    not required). A copy of it, if filed, may be obtained from the Rules 
    Docket.
    
    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:
    
    99-11-13  Cessna Aircraft Company: Amendment 39-11184; Docket No. 
    99-CE-21-AD.
        Applicability: Model 402C airplanes, serial numbers 689; 
    402C0001 through 402C0125; 402C0201 through 402C0355; 402C0401 
    through 402C0528; 402C0601 through 402C0653; and 402C0801 through 
    402C1020, 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 request approval for an 
    alternative method of compliance in accordance with paragraph (e) 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 as indicated in the body of this AD, unless 
    already accomplished.
    
        Note 2: The compliance times specified in Cessna Service 
    Bulletin MEB99-3, dated May 6, 1999, are different than those 
    required by this AD. The compliance times of this AD take precedence 
    over those specified in the service bulletin.
    
        To detect and correct any cracks in the forward, aft, and 
    auxiliary wing spars, which could result in reduced or loss of 
    control of the airplane, accomplish the following:
        (a) Upon accumulating 10,000 hours total time-in-service (TIS) 
    on the airplane or within the next 25 hours TIS after the effective 
    date of this AD, whichever occurs later, accomplish the external and 
    internal inspection of the forward, aft, and auxiliary wing spars 
    for cracks, in accordance with the ACCOMPLISHMENT INSTRUCTIONS 
    section of Cessna Service Bulletin MEB99-3, dated May 6, 1999.
        (b) If any crack(s) is/are found on any forward, aft, or 
    auxiliary wing spar during the inspections required by paragraph (a) 
    of this AD, prior to further flight, accomplish the following:
        (1) Obtain an FAA-approved repair scheme from the Cessna 
    Aircraft Company, P. O. Box 7706, Wichita, Kansas 67277; telephone: 
    (316) 941-7550, facsimile: (316) 942-9008; and
        (2) Incorporate this repair scheme.
        (c) If any crack(s) is/are found during the inspections required 
    by paragraph (a) of this AD, submit a report of inspection findings 
    to the Manager, Wichita Aircraft Certification Office (ACO), 1801 
    Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 
    67209; facsimile: (316) 946-4407; at the applicable time specified 
    in paragraph (c)(1) or (c)(2) of this AD. The report must include 
    the results of the findings, a description of any cracking found, a 
    description of any previous wing repairs or modifications, the 
    airplane serial number, and the total number of hours TIS on the 
    airplane. The ``Lower Wing Spars and Skin Inspection Report'' 
    included as page 6 of Cessna Service Bulletin MEB99-3, dated May 6, 
    1999, may be utilized for this reporting requirement. Information 
    collection requirements contained in this regulation have been 
    approved by the Office of Management and Budget (OMB) under the 
    provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et 
    seq.) and have been assigned OMB Control Number 2120-0056.
        (1) For airplanes on which the inspections are accomplished 
    after the effective date of this AD: Submit the report within 10 
    days after performing the inspection required by paragraph (a) of 
    this AD.
        (2) For airplanes on which the inspections have already been 
    accomplished prior to the effective date of this AD: Submit the 
    report within 10 days after the effective date of this AD, unless 
    already accomplished.
        (d) Special flight permits may be issued in accordance with 
    Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
    21.197 and 21.199) to operate the airplane to a
    
    [[Page 29783]]
    
    location where the requirements of this AD can be accomplished.
        (e) An alternative method of compliance or adjustment of the 
    compliance times that provides an equivalent level of safety may be 
    approved by the Manager, Wichita Aircraft Certification Office 
    (ACO), 1801 Airport Road, Room 100, 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 3: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Wichita ACO.
    
        (f) The inspections required by this AD shall be done in 
    accordance with Cessna Service Bulletin MEB99-3, dated May 6, 1999. 
    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 the Cessna Aircraft Company, P. O. 
    Box 7706, Wichita, Kansas 67277. 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.
        (g) This amendment becomes effective on June 21, 1999.
    
        Issued in Kansas City, Missouri, on May 21, 1999.
    Michael K. Dahl,
    Acting Manager, Small Airplane Directorate.
    [FR Doc. 99-13875 Filed 6-2-99; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
6/21/1999
Published:
06/03/1999
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
99-13875
Dates:
Effective June 21, 1999.
Pages:
29781-29783 (3 pages)
Docket Numbers:
Docket No. 99-CE-21-AD, Amendment 39-11184, AD 99-11-13
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
99-13875.pdf
CFR: (1)
14 CFR 39.13