AD 96-03-03

This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft SA226 and SA227 series airplanes. This action requires replacing the nuts that attach the power control cable to the lever attach point clevis with nuts that have safety wire holes, safety-wiring the power control cable to the lever attach point clevis, inspecting to assure that the power cable is securely attached to the power control cable bracket, and correcting any attachment problems. Reports of power control cable attaching hardware failure on two of the affected airplanes prompted this action. In one of these instances, the power control cable disconnected from the lever attach point clevis, resulting in engine shutdown. The actions specified by this AD are intended to prevent such power control cable disconnection, which could result in engine shutdown and subsequent loss of control of the airplane.

Final rule.

96-03-03 FAIRCHILD AIRCRAFT: Amendment 39-9499; Docket No. 95-CE-17-AD.

Applicability: Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227-TT, SA227-AT, SA227-AC, SA227-BC, SA227-CC, and SA227-DC airplanes (all serial numbers), 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 (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 within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.

To prevent the power control cable from disconnecting from the lever attach point clevis, which could result in engine shutdown and subsequent loss of control of the airplane, accomplish the following:

(a) Replace the nuts that attach the power control cable to the lever attach point clevis with nuts that have safety wire holes, safety-wire the power control cable to the lever attach clevis, inspect to assure that the power cable is securely attached to the power control cable bracket, and correct any attachment problems. Accomplish these actions in accordance with the following service bulletins, as applicable:

(1) Fairchild Service Bulletin (SB) 226-76-009, dated January 6, 1995;

(2) Fairchild SB 227-76-004, dated January 6, 1995; or

(3) Fairchild SB CC7-76-001, dated January 6, 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 compliance time that provides an equivalent level of safety may be approved by the Manager, Fort Worth Airplane Certification Office (ACO), FAA, 2601 Meacham Boulevard, Fort Worth, Texas 76137-0150. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Fort Worth ACO.

NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Fort Worth ACO.

(d) The replacement required by this AD shall be done in accordance with Fairchild Service Bulletin 226-76-009; Fairchild Service Bulletin 227-76-004; or Fairchild Service Bulletin CC7-76-001, all Issued: January 6, 1995, as applicable. 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 Fairchild Aircraft, P.O. Box 790490, San Antonio, Texas 78279-0490. 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., 7th Floor, suite 700, Washington, DC.

(e) This amendment becomes effective on March 15, 1996.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an AD that would apply to certain Fairchild Aircraft SA226 and SA227 series airplanes was published in the Federal Register on July 19, 1995 (60 FR 37037). The action proposed to require replacing the nuts that attach the power control cable to the lever attach point clevis with nuts that have safety wire holes, safety-wiring the power control cable to the lever attach point clevis, inspecting to assure that the power cable is securely attached to the power control cable bracket, and correcting any attachment problems. Accomplishment of the proposed actions would be in accordance with Fairchild Service Bulletin (SB) 226-76-009; Fairchild SB 227-76-004; or Fairchild SB CC7-76-001, all Issued: January 6, 1995, as applicable.

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 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 779 airplanes in the U.S. registry will be affected by this AD, that it will take approximately 4 workhours per airplane to accomplish the required action, and that the average labor rate is approximately $60 an hour. Parts would consist of common hardware and the cost would vary; however, for the purposes of this AD, a figure of $20 is used. Based on these figures, the total cost impact of this AD on U.S. operators is estimated to be $202,540. This figure is based on the assumption that noowner/operator of the affected airplanes has accomplished the required actions. Since parts are obtained locally, the FAA has no readily available means of determining how many owners/operators have incorporated the required actions.

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: