[Federal Register Volume 67, Number 200 (Wednesday, October 16, 2002)]
[Rules and Regulations]
[Pages 63815-63817]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-26052]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2002-CE-41-AD; Amendment 39-12908; AD 2002-21-02]
RIN 2120-AA64


Airworthiness Directives; Cirrus Design Corporation Model SR20 
and SR22 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 
applies to certain Cirrus Design Corporation (Cirrus) Model SR20 and 
SR22 airplanes. This AD requires you to replace the self-locking 
retaining nut on the roll and yaw trim cartridges with a new self-
locking retaining nut with a higher axial load capability. This AD is 
the result of a report that, during a production flight test, the self-
locking retaining nut on the yaw trim cartridge came off. The actions 
specified by this AD are intended to prevent loss of the self-locking 
retaining nut on the roll and yaw trim cartridges during flight, which 
could result in jamming of the corresponding flight control system. 
Such jamming could lead to loss of control of the airplane.

DATES: This AD becomes effective on November 8, 2002.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the regulation as of 
November 8, 2002.
    The Federal Aviation Administration (FAA) must receive any comments 
on this rule on or before December 10, 2002.

ADDRESSES: Submit comments to FAA, Central Region, Office of the 
Regional Counsel, Attention: Rules Docket No. 2002-CE-41-AD, 901 
Locust, Room 506, Kansas City, Missouri 64106. You may view any 
comments at this location between 8 a.m. and 4 p.m., Monday through 
Friday, except Federal holidays. You may also send comments 
electronically to the following address: [email protected]. 
Comments sent electronically must contain ``Docket No. 2002-CE-41-AD'' 
in the subject line. If you send comments electronically as attached 
electronic files, the files must be formatted in

[[Page 63816]]

Microsoft Word 97 for Windows or ASCII text.
    You may get the service information referenced in this AD from 
Cirrus Design Corporation, 4515 Taylor Circle, Duluth, MN 55811; 
telephone: (218) 727-2737; or electronically at the following address: 
www.cirrusdesign.com/sb. You may view this information at FAA, Central 
Region, Office of the Regional Counsel, Attention: Rules Docket No. 
2002-CE-41-AD, 901 Locust, Room 506, Kansas City, Missouri 64106; or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Gregory J. Michalik, Aerospace 
Engineer, FAA, Chicago Aircraft Certification Office, 2300 East Devon 
Avenue, Des Plaines, IL 60018; telephone: (847) 294-7135; facsimile: 
(847) 294-7834.

SUPPLEMENTARY INFORMATION:

Discussion

What Events Have Caused This AD?

    The FAA received a report that, during a production flight test of 
one of the affected airplanes, the pilot attempted to apply right 
rudder but the control would not move. After investigation of this 
incident, we determined that the self-locking retaining nut on the 
shaft of the yaw trim cartridge came off and caused the yaw trim 
cartridge rod to jam when the right rudder was applied.
    The yaw trim cartridge and the roll trim cartridge use the same 
shaft and self-locking retaining nut. The manufacturer has changed the 
design to include a new self-locking retaining nut with greater locking 
ability.
    There have been no reports of this situation occurring on delivered 
airplanes in over 96,000 hours time-in-service on the fleet.

What Are the Consequences if the Condition Is Not Corrected?

    This condition, if not corrected, could result in loss of the self-
locking retaining nut on the roll and yaw trim cartridges. Such failure 
could lead to jamming of the corresponding flight control and cause 
loss of control of the airplane.

Is There Service Information That Applies to This Subject?

    Cirrus Design Corporation has issued Alert Service Bulletin SB A20-
27-06, Issued: September 20, 2002, and Alert Service Bulletin SB A22-
27-03, Issued: September 20, 2002.
    These service bulletins include procedures for installing a new 
self-locking retaining nut on the roll trim and the yaw trim 
cartridges.

The FAA's Determination and an Explanation of the Provisions of This AD

What Has FAA Decided?

    The FAA has reviewed all available information, including the 
service information referenced above; and determined that:
    --The unsafe condition referenced in this document exists or could 
develop on other Cirrus Model SR20 and SR22 airplanes of the same type 
design;
    --The actions specified in the previously-referenced service 
information (as specified in this AD) should be accomplished on the 
affected airplanes; and
    --AD action should be taken in order to correct this unsafe 
condition.

What Does This AD Require?

    This AD requires you to incorporate the actions in the previously-
referenced service bulletin.
    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.

Will I Have the Opportunity To Comment Prior to the Issuance of the 
Rule?

    Because the unsafe condition described in this document could 
result in loss of flight controls, we find that notice and opportunity 
for public prior comment are impracticable. Therefore, good cause 
exists for making this amendment effective in less than 30 days.

Comments Invited

How Do I Comment on This AD?

    Although this action is in the form of a final rule and was not 
preceded by notice and opportunity for public comment, FAA invites your 
comments on the rule. You may submit whatever written data, views, or 
arguments you choose. You need to include the rule's docket number and 
submit your comments to the address specified under the caption 
ADDRESSES. We will consider all comments received on or before the 
closing date specified above. We may amend this rule in light of 
comments received. Factual information that supports your ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether we need to take additional rulemaking 
action.

Are There Any Specific Portions of the AD I Should Pay Attention to?

    We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. You may view all comments we receive 
before and after the closing date of the rule in the Rules Docket. We 
will file a report in the Rules Docket that summarizes each FAA contact 
with the public that concerns the substantive parts of this AD.

How Can I Be Sure FAA Receives My Comment?

    If you want us to acknowledge the receipt of your written comments, 
you must include a self-addressed, stamped postcard. On the postcard, 
write ``Comments to Docket No. 2002-CE-41-AD.'' We will date stamp and 
mail the postcard back to you.

Regulatory Impact

Does This AD Impact Various Entities?

    These regulations 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, FAA has determined that this 
final rule does not have federalism implications under Executive Order 
13132.

Does This AD Involve a Significant Rule or Regulatory Action?

    We have determined that this regulation is an emergency regulation 
that must be issued immediately to correct an unsafe condition in 
aircraft, and 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 (otherwise, an evaluation is 
not required). A copy of it, if filed, may be obtained from the Rules 
Docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 63817]]

Adoption of the Amendment

    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

    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]

    2. FAA amends Sec.  39.13 by adding a new airworthiness directive 
(AD) to read as follows:

2002-21-02 Cirrus Design Corporation: Amendment 39-12908; Docket No. 
2002-CE-41-AD.

    (a) What airplanes are affected by this AD? This AD applies to 
the following airplane models and serial numbers that are 
certificated in any category:

------------------------------------------------------------------------
  Model                           Serial numbers
------------------------------------------------------------------------
   SR20   1005 through 1241, except 1235, 1237, and 1238.
   SR22   0002 through 0333, except 0309, 0322, 0323, and 0328.
------------------------------------------------------------------------

    (b) Who must comply with this AD? Anyone who wishes to operate 
any of the airplanes identified in paragraph (a) of this AD must 
comply with this AD.
    (c) What problem does this AD address? The actions specified by 
this AD are intended to prevent loss of the self-locking retaining 
nut on the roll and yaw trim cartridges during flight, which could 
result in jamming of the corresponding flight control system. Such 
jamming could lead to loss of control of the airplane.
    (d) What must I do to address this problem? To address this 
problem, you must accomplish the following actions:

------------------------------------------------------------------------
           Actions                 Compliance            Procedures
------------------------------------------------------------------------
(1) Replace the self-locking  Within the next 10    In accordance with
 retaining nut on the yaw      hours time-in-        Cirrus Alert
 trim cartridge and the roll   service after         Service Bulletin SB
 trim cartridge with a new     November 8, 2002      A20-27-06, Issued:
 self-locking retaining nut,   (the effective date   September 20, 2002,
 part number MS21044N3.        of this AD), unless   and Cirrus Alert
                               already               Service Bulletin SB
                               accomplished.         A22-27-03, Issued:
                                                     September 20, 2002,
                                                     as applicable.
 
(2) Do not install any self-  As of November 8,     Not applicable.
 locking retaining nut on      2002 (the effective
 the yaw trim cartridge or     date of this AD).
 the roll trim cartridge
 that is not part number
 MS21044N3.
------------------------------------------------------------------------

    (e) Can I comply with this AD in any other way? You may use an 
alternative method of compliance or adjust the compliance time if:
    (1) Your alternative method of compliance provides an equivalent 
level of safety; and
    (2) The Manager, Chicago Aircraft Certification Office (ACO), 
approves your alternative. Submit your request through an FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Chicago ACO.

    Note: This AD applies to each airplane identified in paragraph 
(a) of this AD, 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 (e) 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 you have not eliminated the unsafe condition, specific 
actions you propose to address it.

    (f) Where can I get information about any already-approved 
alternative methods of compliance? Contact Gregory J. Michalik, 
Aerospace Engineer, FAA, Chicago ACO, 2300 East Devon Avenue, Des 
Plaines, IL 60018; telephone: (847) 294-7135; facsimile: (847) 294-
7834.
    (g) What if I need to fly the airplane to another location to 
comply with this AD? The FAA can issue a special flight permit under 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate your airplane to a location where 
you can accomplish the requirements of this AD.
    (h) Are any service bulletins incorporated into this AD by 
reference? Actions required by this AD must be done in accordance 
with in Cirrus Alert Service Bulletin SB A20-27-06, Issued: 
September 20, 2002, and Cirrus Alert Service Bulletin SB A22-27-03, 
Issued: September 20, 2002. The Director of the Federal Register 
approved this incorporation by reference under 5 U.S.C. 552(a) and 1 
CFR part 51. You can get copies from Cirrus Design Corporation, 4515 
Taylor Circle, Duluth, MN 55811; telephone: (218) 727-2737; or 
electronically at the following address: www.cirrusdesign.com/sb. 
You may view this information at FAA, Central Region, Office of the 
Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri, or at 
the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.
    (i) When does this amendment become effective? This amendment 
becomes effective on November 8, 2002.

    Issued in Kansas City, Missouri, on October 7, 2002.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-26052 Filed 10-15-02; 8:45 am]
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