AD 95-04-10

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.

Final rule.

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 category, that have steel wing attachment assembly bolts and hardware:

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 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 becomes effective on April 7, 1995.

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 theseminor 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 doesnot 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.

Section 39.13 - [AMENDED]
2. Section 39.13 is amended by adding a new airworthiness directive to read as follows: