SUPPLEMENTARY INFORMATION:

Discussion

We received reports on two Cessna Models 208 and 208B production airplanes with autopilot heading squawks. Upon investigation by the manufacturer, technicians found in both cases the bridle cable for the autopilot aileron servo was slack, and the swaged ball was unseated from the drum recess.

The cause of the bridle cables going slack was insufficient torque on the bridle cable clamp screws, allowing slippage of the bridle cable clamps on the roll bridle cable. Since the rudder and aileron autopilot interface are similar, the same condition could exist with the yaw bridle cable.

This condition, if not corrected, could result in the swaged ball unseating from the recess in the servo drum and contacting the cable guard pin. This failure could lead to very limited control of the rudder and/or aileron with consequent loss of control.

Relevant Service Information

We reviewed Cessna Aircraft Company Caravan Service Bulletin CAB08-9, dated November 24, 2008. The service information describes procedures for inspecting the bridle cables for looseness, adjusting the bridle cable tension, and tightening the bridle cable clamp screws to the correct torque. The manufacturer intends that the actions specified in the service information adequately address the unsafe condition.

FAA's Determination and Requirements of This AD

We are issuing this AD because we evaluated all the information and determined the unsafe condition described previously is likely to exist or develop on other products of the same type design. This AD requires you to measure the autopilot roll and yaw bridle cable tensions (adjusting as necessary) and to torque the bridle cable clamp screws.

FAA's Determination of the Effective Date

An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because the swaged ball on the bridle cable could unseat from the servo drum and contact the cable guard pin. This failure could lead to very limited control of the rudder and/or aileron. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days.

Comments Invited

This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and an opportunity for public comment. We invite you to send any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under the ADDRESSES section. Include the docket number “FAA-2009-0638; Directorate Identifier 2009-CE-038-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the AD. We will consider all comments received by the closing date and may amend the AD in light of those comments.

We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive concerning this AD.

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on ( printed page 34217) products identified in this rulemaking action.

Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect 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.

For the reasons discussed above, I certify that this AD:

(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.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.

Examining the AD Docket

You may examine the AD docket that contains the AD, the regulatory evaluation, any comments received, and other information on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647-5527) is located at the street address stated in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt.

Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: