AD 96-11-12

This amendment adopts a new airworthiness directive (AD) that applies to certain Beech Aircraft Corporation (Beech) Model C90A airplanes equipped with an optional Beech electric trim system or a Collins autopilot system. This action requires modifying the elevator electric trim tab actuator assembly. Failure of the elevator electric trim tab system on a Beech Model C90A prompted the proposed AD action. The actions specified by the proposed AD are intended to prevent possible failure of the elevator electric trim tab system, which, if not detected and corrected, could cause loss of airplane maneuverability and possible loss of control of the airplane.

Final rule

96-11-12 BEECH AIRCRAFT CORPORATION: Amendment 39-9637; Docket No. 95-CE- 82-AD.

Applicability: The following Model C90A Airplanes, certificated in any category, that are equipped with an optional Beech electric trim system or a Collins autopilot system:

(1) Serial numbers LJ-1111 through LJ-1410 that were equipped at manufacture assembly with a pin-type cable guard actuator assembly (P/N 33-524023-51) on the elevator electric trim tab actuator assembly.

(2) All serial numbers (except LJ-1 through LJ-1110) equipped with a pin-type cable guard actuator assembly (P/N 33-524023-51) installed through field approval.

NOTE 1: Steps 1 through 4 of the ACCOMPLISHMENT INSTRUCTIONS section of Beech Service Bulletin (SB) No. 2631, Issued: June 1995, Revised: September 1995, provide procedures for determining which assembly is installed.

NOTE 2: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has beenmodified, 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 (c) 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 follows, unless already accomplished:

1) Within 150 hours time-in-service (TIS) after the effective date of this AD; or

2) Upon installation of an optional Beech elevator electric trim tab system or a Collins autopilot system, whichever occurs first.

To prevent possible failure of the optional Beech electric trim system or the Collins autopilot system, which, if not detected and corrected, could cause loss of airplane maneuverability and possible loss of control of the airplane, accomplish the following:

(a) Modify all elevator electric trim tab actuator assemblies, part number (P/N) 33- 524023-51 to the P/N 33-524023-77 or P/N 33-524023-79 level, by accomplishing the procedures in the ACCOMPLISHMENT INSTRUCTIONS section of Beechcraft Mandatory Service Bulletin SB No. 2631, Issued: June 1995, Revised: September 1995.

(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 initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 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 Aircraft Certification Office.

NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita Aircraft Certification Office.

(d) The modification required by this AD shall be done in accordance with Beechcraft Mandatory Service Bulletin No. 2631, Issued: June 1995, Revised: September 1995. 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 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 CapitolStreet, NW., 7th Floor, suite 700, Washington, DC.

(e) This amendment becomes effective on July 24, 1996.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to Beech Aircraft Corporation (Beech) Model C90A airplanes equipped with an optional Beech electric trim system or a Collins autopilot system was published in the Federal Register on November 28, 1995 (60 FR 58583). The action proposed to require procedures for modifying the elevator electric trim tab actuator assembly. Accomplishment of this action will be in accordance with Beech Service Bulletin (SB) No. 2631, Issued: June 1995, Revised: September 1995.

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 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.

The FAA estimates that 300 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 6 workhours per airplane to accomplish this action, and that the average labor rate is approximately $60 an hour. Parts are estimated to be $160 per airplane. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $156,000 or $520 per airplane. Beech has informed FAA that no parts have been distributed to owners/operators for this modification; therefore, this figure is based on the assumption that no owners/operators have accomplished the proposed inspection and modification.

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.

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