[Federal Register Volume 68, Number 219 (Thursday, November 13, 2003)]
[Rules and Regulations]
[Pages 64266-64268]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-28166]



[[Page 64266]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2003-NM-225-AD; Amendment 39-13365; AD 2003-23-02]
RIN 2120-AA64


Airworthiness Directives; Cessna Model 560 Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to certain Cessna Model 560 airplanes. This action 
requires disengaging and tie-strapping the pitch trim and autopilot 
servo (servo 1) circuit breakers. This action also provides an optional 
inspection and follow-on actions that, if accomplished, terminates the 
requirement to disengage and tie-strap those circuit breakers. This 
action is necessary to prevent a single-point failure in the trim 
system from causing a runaway trim condition that the pilot may be 
unable to stop by using the autopilot-disconnect switch. This condition 
could result in loss of control of the airplane. This action is 
intended to address the identified unsafe condition.

DATES: Effective November 28, 2003.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 28, 2003.
    Comments for inclusion in the Rules Docket must be received on or 
before January 12, 2004.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2003-NM-225-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9 a.m. and 3 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2003-NM-225-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 or 2000 or 
ASCII text.
    The service information referenced in this AD may be obtained from 
Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. This 
information may be examined at the FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington; at the FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 
North Capitol Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Bryan Easterwood, Aerospace Engineer, 
Systems and Equipment Branch, ACE-116W, FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas 67209; telephone (316) 946-4132; fax (316) 
946-4107.

SUPPLEMENTARY INFORMATION: The FAA has received a report of an accident 
involving a Cessna Model 525 airplane. The pilot reported a problem 
with the trim system and was forced to ditch the airplane in the water 
near Coupeville, Washington. Although the final investigation by the 
National Transportation Safety Board is not complete, investigation 
revealed a discrepancy that could allow single-wire shorting to 28 
volts or the failure of a relay in the trim system such that the relay 
contacts remain closed. In addition, the pilot may be unable to stop 
the runaway trim condition by pressing the red autopilot-disconnect 
switch located on the control wheel, due to the design of the trim 
system on a certain serial number range of airplanes. A runaway trim 
condition that the pilot is unable to stop by using the autopilot-
disconnect switch could result in loss of control of the airplane.
    The design of the trim system on certain Cessna Model 560 airplanes 
is the same as that on certain Cessna Model 525 airplanes. Therefore, 
Model 560 airplanes may be subject to the same unsafe condition.

Explanation of Relevant Service Information

    We have reviewed and approved Cessna Alert Service Letter ASL560-
27-10, dated October 10, 2003. Among other actions, that service letter 
describes procedures for disengaging the pitch trim and autopilot (AP) 
servo (servo 1) circuit breakers and tie-strapping those circuit 
breakers so that they may not be engaged. Accomplishment of these 
actions specified in the service letter is intended to adequately 
address the identified unsafe condition.
    Cessna Alert Service Letter ASL560-27-10 also describes procedures 
for an inspection to determine the part number of the installed trim pc 
board assembly, and follow-on actions. The follow-on actions include 
replacement of the assembly with an improved assembly and installation 
of an extension cap on the pitch trim circuit breaker, as applicable. 
Once the inspection and applicable follow-on actions have been 
accomplished, the tie straps on the pitch trim and AP servo circuit 
breakers may be removed and those circuit breakers may be re-engaged.

Explanation of the Requirements of the Rule

    Since an unsafe condition has been identified that is likely to 
exist or develop on other airplanes of the same type design registered 
in the United States, this AD requires disengaging and tie-strapping 
the pitch trim and AP servo circuit breakers. This AD also provides for 
an optional inspection and follow-on actions that terminates the 
requirement for disengaging and tie-strapping those circuit breakers. 
These actions must be accomplished per the service letter described 
previously, except as discussed below.

Differences Between This AD and Service Letter

    Although the service letter requires that the disengaging and tie-
strapping of the pitch trim and AP servo circuit breakers be 
accomplished upon receipt of the service letter, this AD allows 
accomplishment of these actions within 5 days or 10 hours time-in-
service after the effective date of this AD, whichever is first. We 
find that such a compliance time represents an appropriate compliance 
time for affected airplanes to continue to operate without compromising 
safety.
    Although the service letter is effective for certain Model 560 
airplanes having serial numbers 0260 through 0538 inclusive, this AD is 
applicable to certain Model 560 airplanes having serial numbers 0260 
through 0396 inclusive. While the discrepancy that could allow a 
single-point failure in the trim system, causing a runaway trim 
condition, may occur on any airplane having a serial number in the 
range 0260 through 0538 inclusive, on airplanes having serial numbers 
0397 through 0538 inclusive, the pilot would be able to stop the 
runaway trim condition by pressing the red autopilot-disconnect switch 
located on the control wheel. Therefore, we have determined that an 
acceptable level of safety exists on airplanes having serial numbers 
0397 through 0538 inclusive, and it is not

[[Page 64267]]

necessary to require disengaging and tie-strapping of the pitch trim 
and AP servo circuit breakers on these airplanes at this time.
    Although the Accomplishment Instructions of the service letter 
describe procedures for sending a maintenance transaction report to the 
manufacturer, this AD does not require this action.

Interim Action

    We consider this proposed AD interim action. We are currently 
considering requiring the optional terminating action provided in this 
AD--inspection of the trim pc board assembly and follow-on actions, 
which would eliminate the need for the tie straps on the pitch trim and 
AP servo circuit breakers, and would allow those circuit breakers to be 
re-engaged. However, the planned compliance time for such actions would 
likely allow enough time to provide notice and opportunity for prior 
public comment on the merits of those actions.

Determination of Rule's Effective Date

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment hereon are impracticable, and that good cause exists for 
making this amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications shall identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Submit comments using the following format:
    [sbull] Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
    [sbull] For each issue, state what specific change to the AD is 
being requested.
    [sbull] Include justification (e.g., reasons or data) for each 
request.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this rule must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2003-NM-225-AD.'' The postcard will be date stamped 
and returned to the commenter.

Regulatory Impact

    The regulations adopted herein 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. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and that it is not a ``significant regulatory 
action'' under Executive Order 12866. It has been determined further 
that this action involves an emergency regulation under DOT Regulatory 
Policies and Procedures (44 FR 11034, February 26, 1979). If it is 
determined that this emergency regulation otherwise would be 
significant under DOT Regulatory Policies and Procedures, a final 
regulatory evaluation will be prepared and placed in the Rules Docket. 
A copy of it, if filed, may be obtained from 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

0
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

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
2. Section 39.13 is amended by adding the following new airworthiness 
directive:

2003-23-02 Cessna Aircraft Company: Amendment 39-13365. Docket 2003-
NM-225-AD.

    Applicability: Model 560 airplanes, having serial numbers 0260 
through 0396 inclusive, certificated in any category; except those 
on which Cessna Service Bulletin 560-34-93, dated March 16, 2001, 
has been accomplished.
    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent a single-point failure in the trim system from 
causing a runaway trim condition that the pilot may be unable to 
stop by using the autopilot disconnect switch, which could result in 
loss of control of the airplane, accomplish the following:

Disengaging and Tie-Strapping Circuit Breakers

    (a) Within 5 days or 10 hours time-in-service after the 
effective date of this AD, whichever is first: Disengage the PITCH 
TRIM circuit breaker on the left circuit breaker panel and the SERVO 
1 circuit breaker on the right circuit breaker panel, and install 
tie straps on those circuit breakers, per paragraphs 1.A. and 1.B. 
of the Accomplishment Instructions of Cessna Alert Service Letter 
ASL560-27-10, dated October 10, 2003.

Optional Inspection and Corrective Actions

    (b) Accomplishment of the inspection of the trim pc board 
assembly to determine the part number of the assembly and all 
applicable follow-on actions; per paragraphs 2.A., 2.B., and 2.C. of 
the Accomplishment Instructions of Cessna Alert Service Letter 
ASL560-27-10, dated October 10, 2003; terminates the requirements of 
paragraph (a) of this AD. Once the inspection and applicable follow-
on actions have been accomplished, the tie straps on the pitch trim 
and autopilot servo circuit breakers may be removed and those 
circuit breakers may be re-engaged.

Parts Installation

    (c) As of the effective date of this AD, no person may install a 
trim pc board assembly having part number 6518351-3 or -5 on any 
airplane.

Alternative Methods of Compliance

    (d) In accordance with 14 CFR 39.19, the Manager, Wichita 
Aircraft Certification Office (ACO), FAA, is authorized to approve 
alternative methods of compliance for this AD.

Incorporation by Reference

    (e) The actions shall be done in accordance with Cessna Alert 
Service Letter ASL560-27-

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10, dated October 10, 2003. 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 
Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. Copies 
may be inspected at the FAA, Transport Airplane Directorate, 1601 
Lind Avenue, SW., Renton, Washington; at the FAA, Wichita Aircraft 
Certification Office, 1801 Airport Road, Room 100, Mid-Continent 
Airport, Wichita, Kansas; or at the Office of the Federal Register, 
800 North Capitol Street, NW., suite 700, Washington, DC.

Effective Date

    (f) This amendment becomes effective on November 28, 2003.

    Issued in Renton, Washington, on November 4, 2003.
Ali Bahrami,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 03-28166 Filed 11-12-03; 8:45 am]
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