[Federal Register Volume 68, Number 203 (Tuesday, October 21, 2003)]
[Rules and Regulations]
[Pages 60028-60030]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-26276]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-CE-46-AD; Amendment 39-13342; AD 2003-21-07]
RIN 2120-AA64


Airworthiness Directives; The Cessna Aircraft Company Model 525 
Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain The Cessna Aircraft Company (Cessna) Model 525 airplanes. 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. This AD is the result of analysis that 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. We are issuing this AD to correct this single-point 
failure in the electric pitch trim system, which will result in a 
runaway pitch trim condition where 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.

DATES: 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.

ADDRESSES: Use one of the following to submit comments on this AD:
    [sbull] 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.
    [sbull] By fax: (816) 329-3771.
    [sbull] By e-mail: [email protected]. 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.

FOR FURTHER INFORMATION CONTACT: 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.

SUPPLEMENTARY INFORMATION:
    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.

FAA's Determination and Requirements of the AD

    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.

Compliance Time of This AD

    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-

[[Page 60029]]

usage and low-usage airplanes within a reasonable time period without 
inadvertently grounding any of the affected airplanes.

Comments Invited

    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.

Regulatory Findings

    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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
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:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
1. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2003-21-07 The Cessna Aircraft Company: Amendment 39-13342; Docket 
No. 2003-CE-46-AD.

When Does This AD Become Effective?

    (a) This AD becomes effective on October 22, 2003.

Are Any Other ADs Affected by This Action?

    (b) None.

What Airplanes Are Affected by This AD?

    (c) This AD affects Model 525 airplanes, serial numbers 525-
0001, 525-0002, and 525-0004 through 525-0159, that are certificated 
in any category.

What Is the Unsafe Condition Presented in This AD?

    (d) This AD is the result of analysis that 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. We are issuing this AD to correct this single-point failure 
in the electric pitch trim system, which will result in a runaway 
pitch trim condition where 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 Must I Do To Address This Problem?

    (e) To address this problem, you must accomplish the following:

------------------------------------------------------------------------
                Actions                             Compliance
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(1) Disengage the PITCH TRIM circuit     Within 5 calendar days or 10
 breaker located on the left circuit      hours time-in-service after
 breaker panel. Install a tie strap       October 22, 2003 (the
 (part number (P/N) MS3367-1-4 or         effective date of this AD),
 equivalent part number) on the shaft     whichever occurs first.
 of the PITCH TRIM circuit breaker to
 prevent the circuit breaker from being
 engaged.
(2) Disengage the AP SERVOS circuit      Within 5 calendar days or 10
 breaker located in the right circuit     hours time-in-service after
 breaker panel. Install a tie strap (P/   October 22, 2003 (the
 N MS3367-1-4 or equivalent part          effective date of this AD),
 number) on the shaft of the AP SERVOS    whichever occurs first.
 circuit breaker to prevent the circuit
 breaker from being engaged.
(3) The Minimum Crew portion of Section  Not Applicable.
 II--Operating Limitations of the
 Airplane Flight Manual (AFM) provides
 information on applicable operating
 limitations with the autopilot
 inoperable.
(4) All affected airplanes were          Not Applicable.
 originally equipped with a P/N 6518351-
 3 or P/N 65138351-5 Trim PC Board
 Assembly. If a P/N 6518351-8 Trim PC
 Board Assembly is installed, contact
 the Wichita Aircraft Certification
 Office at the address in paragraph (f)
 of this AD to determine if the
 installed P/N 6518351-8 Trim PC board
 assembly is an alternative method of
 compliance to this AD.
(5) Cessna Citation Alert Service        Not Applicable.
 Letter ASL525-27-02, dated October 10,
 2003, contains information related to
 this subject.
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[[Page 60030]]

What About Alternative Methods of Compliance?

    (f) You may request a different method of compliance or a 
different compliance time for this AD by following the procedures in 
14 CFR 39.13. Send your request to the Manager, Wichita Aircraft 
Certification Office (ACO), FAA. For information on any already 
approved alternative methods of compliance, contact Dan Withers, 
Aerospace Engineer, FAA, Wichita ACO, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209, telephone: (316) 946-4196; facsimile: (316) 
946-4107.

How Do I Get Copies of the Documents Referenced in This AD?

    (g) You may get copies of the document referenced 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 this document at FAA, Central Region, Office 
of the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri 
64106.


    Issued in Kansas City, Missouri, on October 10, 2003.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-26276 Filed 10-20-03; 8:45 am]
BILLING CODE 4910-13-P