97-6539. Airworthiness Directives; Raytheon Aircraft Company (Formerly Beech Aircraft Corporation) Model 76 Airplanes  

  • [Federal Register Volume 62, Number 53 (Wednesday, March 19, 1997)]
    [Rules and Regulations]
    [Pages 12949-12951]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 97-6539]
    
    
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    DEPARTMENT OF TRANSPORTATION
    
    Federal Aviation Administration
    
    14 CFR Part 39
    
    [Docket No. 94-CE-34-AD; Amendment 39-9967; AD 97-06-10]
    RIN 2120-AA64
    
    
    Airworthiness Directives; Raytheon Aircraft Company (Formerly 
    Beech Aircraft Corporation) Model 76 Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
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    SUMMARY: This amendment supersedes Airworthiness Directive (AD) 91-14-
    14, which currently requires repetitively inspecting the main landing 
    gear (MLG) ``A'' frame assemblies for cracks on Raytheon Aircraft 
    Company (Raytheon) Model 76 airplanes (formerly referred to as Beech 
    Model 76 airplanes), and replacing any assembly found cracked. AD 91-
    14-14 resulted from reports of fatigue cracks developing on the MLG 
    ``A'' frame assemblies of the affected airplanes. Raytheon has 
    developed improved design MLG ``A'' frame assemblies, and the Federal 
    Aviation Administration (FAA) has determined that Model 76 airplanes 
    with an improved design ``A'' frame assembly installed on both the left 
    and right MLG should be exempt from AD 91-14-14. This action retains 
    the requirement of repetitively inspecting the MLG ``A'' frame 
    assemblies for cracks and replacing any cracked ``A'' frame assembly 
    only for those Model 76 airplanes that do not have the improved design 
    parts installed. The actions specified by this AD are intended to 
    prevent MLG failure because of a cracked ``A'' frame assembly, which 
    could result in loss of control of the airplane during landing 
    operations.
    
    DATES: Effective May 16, 1997.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of May 16, 1997.
    
    ADDRESSES: Service information that applies to this AD may be obtained 
    from the Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-
    0085. This information may also be examined at the FAA, Central Region, 
    Office of the Assistant Chief Counsel, Attention: Rules Docket No. 94-
    CE-34-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.
    
    
    [[Page 12950]]
    
    
    FOR FURTHER INFORMATION CONTACT: Mr. Larry Engler, Aerospace Safety 
    Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport 
    Road, Mid-Continent Airport, Wichita, Kansas 67209; telephone (316) 
    946-4122; facsimile (316) 946-4407.
    
    SUPPLEMENTARY INFORMATION:
    
    Events Leading to the Issuance of the 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 Raytheon Model 76 
    airplanes (formerly referred to as Beech Model 76 airplanes) was 
    published in the Federal Register as a notice of proposed rulemaking 
    (NPRM) on October 18, 1996 (61 FR 54368). The NPRM proposed to 
    supersede AD 91-14-14 with a new AD that would retain the requirement 
    of repetitively inspecting the MLG ``A'' frame assemblies for cracks 
    and replacing any part found cracked, but would exempt those airplanes 
    with both a P/N 105-810023-75 (left) and P/N 105-810023-76 (right) MLG 
    ``A'' frame assembly installed. Accomplishment of the proposed 
    repetitive inspections as specified in the NPRM would be in accordance 
    with Raytheon Mandatory Service Bulletin No. 2361, Revision III, dated 
    June 1996.
        The NPRM was the result of Raytheon developing improved design MLG 
    ``A'' frame assemblies, and the FAA determining that Model 76 airplanes 
    with an improved design ``A'' frame assembly installed on both the left 
    and right MLG should be exempt from AD 91-14-14.
        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 437 airplanes in the U.S. registry will be 
    affected by this AD, that it will take approximately 2 workhours per 
    airplane to accomplish the required action, and that the average labor 
    rate is approximately $60 an hour. Based on these figures, the total 
    cost impact of the AD on U.S. operators is estimated to be $52,440. 
    These figures only take into account the cost of the required initial 
    inspection; repetitive inspection costs and costs for replacing any 
    cracked MLG ``A'' frame assemblies are not included in these figures.
        The FAA has no way of determining how many airplanes will have 
    cracked MLG ``A'' frame assemblies or how many repetitive inspections 
    each affected owner/operator will incur over the life of the airplane.
        The only difference between this AD and AD 91-14-14 is that this AD 
    exempts airplanes with the improved MLG ``A'' frame assemblies 
    installed. Therefore, the cost impact of this AD is less than that 
    already required by AD 91-14-14 because the FAA believes that some 
    airplanes will have the improved MLG ``A'' frame assemblies installed.
    
    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 USC 106(g), 40113, 44701.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by removing Airworthiness Directive 
    (AD) 91-14-14, Amendment 39-7055 (56 FR 29173, June 26, 1991), and by 
    adding a new AD to read as follows:
    
    97-06-10  Raytheon Aircraft Company (formerly Beech Aircraft 
    Corporation): Amendment 39-9967; Docket No. 94-CE-34-AD. Supersedes 
    AD 91-14-14, Amendment 39-7055.
    
        Applicability: Model 76 airplanes (serial numbers ME-1 through 
    ME-437), certificated in any category, that do not have both a part 
    number (P/N) 105-810023-75 (left) and P/N 105-810023-76 (right) main 
    landing gear (MLG) ``A'' frame assembly installed.
    
        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 initally within the next 50 hours time-in-
    service (TIS) after the effective date of this AD, unless already 
    accomplished (compliance with AD 91-14-14), and thereafter at 
    intervals not to exceed 100 hours TIS .
        To prevent MLG failure because of a cracked ``A'' frame 
    assembly, which could result in loss of control of the airplane 
    during landing operations, accomplish the following:
        (a) Inspect, using both visual and dye penetrant methods, both 
    the left and right MLG ``A'' frame assemblies for cracks in 
    accordance with the ACCOMPLISHMENT INSTRUCTIONS section of Raytheon 
    Mandatory Service Bulletin No. 2361, Revision III, dated June 1996. 
    Pay particular attention to the tips of the gussets and the small 
    corrosion treatment hole adjacent to the gusset.
        (b) If any MLG ``A'' frame assembly is found cracked during any 
    inspection required by this AD, prior to further flight, replace the 
    assembly with one of the following in accordance with Chapter 32 of 
    the Raytheon Model 76 Maintenance Manual:
        (1) A new MLG ``A'' frame assembly with the same P/N as that 
    found cracked. The 100-hour TIS repetitive inspection requirement 
    still applies when this design ``A'' frame is installed.
        (2) A P/N 105-810023-75 (left) or P/N 105-810023-76 (right) main 
    MLG ``A'' frame
    
    [[Page 12951]]
    
    assembly, as applicable. Repetitive inspections are no longer 
    required on an MLG ``A'' frame assembly incorporating this design 
    configuration. Repetitive inspections are still required on an MLG 
    ``A'' frame assembly if it does not incorporate this improved design 
    configuration.
        (c) Installing both P/N 105-810023-75 (left) and P/N 105-810023-
    76 (right) MLG ``A'' frame assemblies eliminates the repetitive 
    inspection requirement of this AD.
        (d) 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.
        (e) 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), 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 2: Information concerning the existence of approved 
    alternative methods of compliance with this AD, if any, may be 
    obtained from the Wichita ACO.
    
        (f) The inspection required by this AD shall be done in 
    accordance with Raytheon Mandatory Service Bulletin No. 2361, 
    Revision III, dated June 1996. 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 
    Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201-0085. 
    Copies may be inspected at the FAA, Central Region, Office of the 
    Assistant Chief 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 (39-9967) supersedes AD 91-14-14, Amendment 
    39-7055.
        (h) This amendment (39-9967) becomes effective on May 16, 1997. 
    Issued in Kansas City, Missouri, on March 6, 1997.
    Michael Gallagher,
    Manager, Small Airplane Directorate, Aircraft Certification Service.
    [FR Doc. 97-6539 Filed 3-18-97; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
5/16/1997
Published:
03/19/1997
Department:
Federal Aviation Administration
Entry Type:
Rule
Action:
Final rule.
Document Number:
97-6539
Dates:
Effective May 16, 1997.
Pages:
12949-12951 (3 pages)
Docket Numbers:
Docket No. 94-CE-34-AD, Amendment 39-9967, AD 97-06-10
RINs:
2120-AA64: Airworthiness Directives
RIN Links:
https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
PDF File:
97-6539.pdf
CFR: (1)
14 CFR 39.13