[Federal Register Volume 60, Number 44 (Tuesday, March 7, 1995)]
[Rules and Regulations]
[Pages 12406-12407]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-4367]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 94-CE-07-AD; Amendment 39-9162; AD 95-04-10]


Airworthiness Directives; Beech Aircraft Corporation Models 34C, 
T-34C, and T-34C-1 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
applies to certain Beech Aircraft Corporation (Beech) Models 34C, T-
34C, and T-34C-1 airplanes. This action requires replacing the eight 
wing attachment steel bolts and hardware with Inconel bolts and 
hardware. A report of the right lower aft wing attachment nut assembly 
separating in two pieces on a Model T-34C-1 airplane prompted this 
action. The actions specified by this AD are intended to prevent the 
wing from separating from the fuselage because of failure of this 
assembly.

DATES: Effective April 7, 1995.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 7, 1995.

ADDRESSES: Service information that applies to this AD may be obtained 
from the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 
67201-0085. This information may also be examined at the Federal 
Aviation Administration (FAA), Central Region, Office of the Assistant 
Chief Counsel, 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. Larry Engler, Aerospace Engineer, 
Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Mid-
Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4122; 
facsimile (316) 946-4407.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that would apply 
to certain Beech Models 34-C, T-34C, and T-34C-1 airplanes was 
published in the Federal Register on October 25, 1994 (59 FR 53613). 
The action proposed to require replacing the eight wing attachment 
steel bolts and hardware with Inconel bolts and hardware. 
Accomplishment of the proposed replacements would be in accordance with 
Beech Service Bulletin No. 2487, dated August 1993.
    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.
    After careful review of all information related to the subject 
discussed 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 or add any additional 
burden upon the public than was already proposed.
    The compliance time of this AD is presented in calendar time 
instead of hours time-in-service (TIS). The FAA has determined that a 
calendar time compliance is the most desirable method because the 
unsafe condition described by this AD is caused by stress corrosion. 
Stress corrosion initiates as a result of airplane operation, but can 
continue to develop regardless of whether the airplane is in service or 
in storage. Therefore, to ensure that the above-referenced condition is 
detected and corrected on all airplanes within a reasonable period of 
time without inadvertently grounding any airplanes, a compliance 
schedule based upon calendar time instead of hours TIS is required.
    The FAA estimates that 494 airplanes in the U.S. registry will be 
affected by this AD, that it will take approximately 8 workhours per 
airplane to accomplish the required action, and that the average labor 
rate is approximately $60 an hour. Parts cost approximately $800 per 
airplane. Based on these figures, the total cost impact of the AD on 
U.S. operators is estimated to be $632,320. This figure is based on the 
assumption that no affected airplane owner/operator has accomplished 
the required replacement.
    The Beech Aircraft Company has informed the FAA that 89 wing 
attachment assembly kits have been sold. Assuming that each of these 
kits is installed on an affected airplane, this would reduce the cost 
impact of the required AD upon U.S. operators of the affected airplanes 
by $113,920 from $632,320 to $518,400.
    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 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:

95-04-10  Beech Aircraft Corporation: Amendment 39-9162; Docket No. 
94-CE-07-AD.

    Applicability: The following model and serial number airplanes, 
certificated in any [[Page 12407]] category, that have steel wing 
attachment assembly bolts and hardware:

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              Model                            Serial numbers           
------------------------------------------------------------------------
34C..............................  GP-1 through GP-50.                  
T-34C............................  GL-2 through GL-353.                 
T-34C-1..........................  GM-1 through GM-71 and GM-78 through 
                                    GM-98.                              
------------------------------------------------------------------------

    Compliance: Within whichever of the following occurs later, 
unless already accomplished:
     Four years after airplane manufacture;
     Four years after installing a new wing attachment 
assembly; or
     Within the next 30 calendar days after the effective 
date of this AD.

    To prevent the wing from separating from the fuselage because of 
failure of the wing attachment nut assembly, accomplish the following:
    (a) Replace all eight steel wing attach bolts and hardware with 
Inconel bolts and hardware in accordance with the ACCOMPLISHMENT 
INSTRUCTIONS section in Beech Service Bulletin No. 2487, dated August 
19 1993.

    Note 1: Replacing all eight steel wing attach bolts and hardware 
with Inconel bolts and hardware as required by this AD eliminates 
the repetitive inspection requirements of AD 85-22-05, Amendment 39-
5146, for the affected airplanes.

    (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), 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.

    (d) The replacements required by this AD shall be done in 
accordance with Beech Service Bulletin No. 2487, dated August 1993. 
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 Beech Aircraft Corporation, 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.
    (e) This amendment (39-9162) becomes effective on April 7, 1995.

    Issued in Kansas City, Missouri, on February 14, 1995.
Barry D. Clements,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 95-4367 Filed 3-6-95; 8:45 am]
BILLING CODE 4910-13-U