AD 2003-21-07

This AD becomes effective on October 22, 2003.

The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulation as of October 22, 2003.

We must receive any comments on this AD by December 15, 2003.

Use one of the following to submit comments on this AD:

• By mail: FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-46-AD, 901 Locust, Room 506, Kansas City, Missouri 64106.

• By fax: (816) 329-3771.

• By e-mail: 9-ACE-7-Docket@faa.gov. Comments sent electronically must contain “Docket No. 2003-CE-46-AD” in the subject line. If you send comments electronically as attached electronic files, the files must be formatted in Microsoft Word 97 for Windows or ASCII.

You may get the service information identified in this AD from The Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517-6000; facsimile: (316) 517-8500.

You may view the AD docket at FAA, Central Region, Office of the Regional Counsel, Attention: Rules Docket No. 2003-CE-46-AD, 901 Locust, Room 506, Kansas City, Missouri 64106. Office hours are 8 a.m. to 4 p.m., Monday through Friday, except Federal holidays.

Dan Withers, Aerospace Engineer, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209, telephone: (316) 946-4196; facsimile: (316) 946-4107.

What events have caused this AD? The FAA has received a report of an accident involving a Cessna Model 525 airplane where the pilot ditched the airplane in the water off the coast near Coupeville, Washington. The pilot reported a problem with the pitch trim system.

Although the final investigation by the National Transportation Safety Board (NTSB) is not complete, Cessna and FAA analysis reveals the potential for a single-wire shorting to 28 volts or a failure of a relay in the electric pitch trim system such that the relay contacts remain closed and also precludes disconnect of the pitch trim using the control wheel autopilot/trim disconnect switch.

What are the consequences if the condition is not corrected? Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.

Is there service information that applies to this subject? Cessna has issued Citation Alert Service Letter ASL525-27-02, dated October 10, 2003.

What are the provisions of this service information? The service bulletin includes (as well as other information) procedures for disengaging and tie strapping the pitch trim and autopilot servo circuit breakers.

What has FAA decided? We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design.

Since the unsafe condition described previously is likely to exist or develop on other Cessna Model 525 airplanes of the same type design, this AD is being issued to correct a single-point failure in the pitch trim system, which could result in a runaway pitch trim condition where that the pilot could not disconnect using the control wheel autopilot/trim disconnect switch. Failure of the electric trim system would result in a large pitch mistrim and would cause excessive control forces that the pilot could not overcome.

What does this AD require? This AD requires you to disengage the pitch trim circuit breaker and AP servo circuit breaker and then tie strap each of them to prevent them from being engaged.

In preparation of this rule, we contacted type clubs and aircraft operators to obtain technical information and information on operational and economic impacts. We did not receive any information through these contacts. If received, we would have included, in the rulemaking docket, a discussion of any information that may have influenced this action.

How does the revision to 14 CFR part 39 affect this AD? On July 10, 2002, we published a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs FAA's AD system. This regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material previously was included in each individual AD. Since this material is included in 14 CFR part 39, we will not include it in future AD actions.

What would be the compliance time of this AD? The compliance time of this AD is within 5 days or 10 hours time-in-service after October 22, 2003 (the effective date of this AD), whichever occurs first.

Why is the compliance time of this AD presented in both hours TIS and calendar time? The unsafe condition on these airplanes is not a result of the number of times the airplane is operated. The FAA is establishing the compliance time in both hours TIS and calendar time (with the prevalent being that which occurs first).

This would assure that the unsafe condition is addressed on both high- usage and low-usage airplanes within a reasonable time period without inadvertently grounding any of the affected airplanes.

Will I have the opportunity to comment prior to the issuance of the rule? This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include “AD Docket No. 2003-CE-46-AD” in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will date-stamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us through a nonwritten communication, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments.

Will this AD impact various entities? We have 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.

Will this AD involve a significant rule or regulatory action? 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 the 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include “AD Docket No. 2003-CE-46-AD” in your request.

Accordingly, under 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:

1. The authority citation for part 39 continues to read as follows:

1. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):