Document ID: FAA-2009-0395-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously The Lancair Company)) Models LC40-550FG, LC41-550FG, and LC42-550FG Airplanes
Posted Date: 2009-04-30T04:00Z

[Federal Register Volume 74, Number 82 (Thursday, April 30, 2009)]
[Rules and Regulations]
[Pages 19873-19876]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-9793]

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  Federal Register / Vol. 74, No. 82 / Thursday, April 30, 2009 / Rules 
and Regulations  

[[Page 19873]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0395; Directorate Identifier 2009-CE-023-AD; 
Amendment 39-15895; AD 2009-09-09]
RIN 2120-AA64

Airworthiness Directives; Cessna Aircraft Company (Type 
Certificate Previously Held by Columbia Aircraft Manufacturing 
(Previously The Lancair Company)) Models LC40-550FG, LC41-550FG, and 
LC42-550FG Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Cessna Aircraft Company (Type Certificate previously held by Columbia 
Aircraft Manufacturing (previously The Lancair Company)) Models LC40-
550FG, LC41-550FG, and LC42-550FG airplanes. This AD requires you to 
repetitively inspect the rudder hinges and the rudder hinge brackets 
for damage, i.e., cracking, deformation, and discoloration. If damage 
is found during any inspection, this AD also requires you to replace 
the damaged rudder hinge and/or rudder hinge bracket. This AD results 
from reports that cracked lower rudder hinge brackets were found on two 
of the affected airplanes. We are issuing this AD to detect and correct 
damage in the rudder hinges and the rudder hinge brackets, which could 
result in failure of the rudder. This failure could lead to loss of 
control.

DATES: This AD becomes effective on May 11, 2009.
    On May 11, 2009, the Director of the Federal Register approved the 
incorporation by reference of certain publications listed in this AD.
    We must receive any comments on this AD by June 29, 2009.

ADDRESSES: Use one of the following addresses to comment on this AD.
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    To get the service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet: 
http://www.cessna.com.
    To view the comments to this AD, go to http://www.regulations.gov. 
The docket number is FAA-2009-0395; Directorate Identifier 2009-CE-023-
AD.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita 
Aircraft Certification Office (ACO), 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107; 
e-mail: gary.park@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We have received reports that a cracked lower rudder hinge bracket 
was found on two Cessna Aircraft Company Model LC41-550FG airplanes.
    One of the airplanes had 106 hours time-in-service (TIS) and the 
rudder hinge was fully fractured. The other airplane had 225 hours TIS 
and the rudder hinge was partially fractured.
    The cracks occurred because of corrosion of the anodized 2024 
aluminum brackets. By design, the bearings are pressed into hinge 
elements and then staked on either side. In the staking process, the 
anodized protection is lost.
    Investigation is ongoing to determine to the best approach to take 
to incorporate a modification or a design change to prevent the rudder 
hinges and the rudder hinge brackets from becoming damaged, i.e., 
cracked, deformed, and discolored.
    This condition, if not corrected, could result in failure of the 
rudder. This failure could lead to loss of control.

Relevant Service Information

    We reviewed Cessna Aircraft Company Single Engine Service Bulletin 
SB09-27-01, dated April 13, 2009. The service information describes 
procedures for repetitively inspecting the rudder hinges and the rudder 
hinge brackets for damage, i.e., cracking, deformation, and 
discoloration. The service information also describes procedures for 
replacing any damaged rudder hinge and/or rudder hinge bracket.

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 
repetitively inspecting the rudder hinges and the rudder hinge brackets 
for damage. If damage is found during any inspection, this AD also 
requires replacing the damaged rudder hinge and/or rudder hinge 
bracket.
    Cessna Aircraft Company is reviewing the information related to the 
occurrences referenced in this AD and may develop a modification that, 
when incorporated, would eliminate the need for the repetitive 
inspections required by this AD. The FAA will review any modification 
that is developed, determine whether it would eliminate the need for 
the requirements of this action, and then determine whether additional 
AD action is necessary.

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 
rudder failure could lead to loss of control. 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.

[[Page 19874]]

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-2009-0395; 
Directorate Identifier 2009-CE-023-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 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 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. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2009-09-09 Cessna Aircraft Company (Type Certificate previously held 
by Columbia Aircraft Manufacturing (previously The Lancair 
Company)): Amendment 39-15895; Docket No. FAA-2009-0395; Directorate 
Identifier 2009-CE-023-AD.

Effective Date

    (a) This AD becomes effective on May 11, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the following airplane models and serial 
numbers that are certificated in any category:

------------------------------------------------------------------------
                Model                             Serial Nos.
------------------------------------------------------------------------
LC40-550FG..........................  40001 through 40079.
LC41-550FG..........................  41001 through 41800, 411001 and
                                       subsequent.
LC42-550FG..........................  42001 through 42569, 421001 and
                                       subsequent.
------------------------------------------------------------------------

Unsafe Condition

    (d) This AD is the result of reports that cracked lower rudder 
hinge brackets were found on two of the affected airplanes. We are 
issuing this AD to detect and correct damage, i.e., cracking, 
deformation, and discoloration, in the rudder hinges and the rudder 
hinge brackets, which could result in failure of the rudder. This 
failure could lead to loss of control.

Compliance

    (e) To address this problem, you must do the following per 
Cessna Aircraft Company Single Engine Service Bulletin SB09-27-01, 
dated April 13, 2009, unless already done:

----------------------------------------------------------------------------------------------------------------
                Condition                             Initial inspection                Repetitive inspection
----------------------------------------------------------------------------------------------------------------
(1) For airplanes with 25 hours time-in-   With the rudder removed and using 10X     Thereafter inspect as
 service (TIS) or more as of May 11, 2009   visual magnification, inspect all three   follows:
 (the effective date of this AD):           rudder hinges and rudder hinge brackets  (A) Every 25 hours TIS or 3
                                            for damage, i.e., cracking,               months, whichever occurs
                                            deformation, and discoloration, at        first, without removing
                                            whichever of the following occurs         the rudder, visually
                                            first:                                    inspect all three rudder
                                           (i) Within the next 10 hours TIS after     hinges and rudder hinge
                                            May 11, 2009 (the effective date of       brackets for damage; and
                                            this AD); or                             (B) Every 50 hours TIS or 6
                                           (ii) Within the next 30 days after May     months, whichever occurs
                                            11, 2009 (the effective date of this      first, with the rudder
                                            AD).                                      removed and using 10X
                                                                                      visual magnification,
                                                                                      inspect all three rudder
                                                                                      hinges and rudder hinge
                                                                                      brackets for damage.

[[Page 19875]]

 
(2) For airplanes with less than 25 hours  Without removing the rudder, visually     Thereafter inspect as
 TIS as of May 11, 2009 (the effective      inspect all three rudder hinges and       follows:
 date of this AD):                          rudder hinge brackets for damage, at     (A) Every 25 hours TIS or 3
                                            whichever of the following occurs         months, whichever occurs
                                            later:                                    first, without removing
                                           (i) Upon accumulating 25 hours TIS; or     the rudder, visually
                                           (ii) Within the next 10 hours TIS after    inspect all three rudder
                                            May 11, 2009 (the effective date of       hinges and rudder hinge
                                            this AD).                                 brackets for damage.
                                                                                     (B) Every 50 hours TIS or 6
                                                                                      months, whichever occurs
                                                                                      first, with the rudder
                                                                                      removed and using 10X
                                                                                      visual magnification,
                                                                                      inspect all three rudder
                                                                                      hinges and rudder hinge
                                                                                      brackets for damage.
----------------------------------------------------------------------------------------------------------------

     (3) If damage is found on any of the rudder hinges and/or 
rudder hinge brackets during any inspection required in paragraphs 
(e)(1) or (e)(2), before further flight, replace the damaged rudder 
hinges and/or rudder hinge brackets with new parts and inspect 
following the Repetitive Inspection procedures specified in 
paragraphs (e)(1) or (e)(2) of this AD.
    (4) If the repetitive inspections required in paragraphs (e)(1) 
and (e)(2) of this AD become due at the same time, credit for both 
inspections will be given by doing the rudder removal and 10X visual 
inspection.
    (5) Use the form (Figure 1 of this AD) to report the results of 
the following inspections required in this AD to the FAA at the 
address specified in paragraph (f) of this AD:
    (i) Initial inspections required in paragraphs (e)(1) and (e)(2) 
of this AD, report within 10 days after the inspection or within 10 
days of May 11, 2009 (after the effective date of this AD), 
whichever occurs later.
    (ii) Repetitive inspections required in paragraphs (e)(1) and 
(e)(2) of this AD ONLY if cracks are found, report within 10 days 
after the inspection.
    (iii) The Office of Management and Budget (OMB) approved the 
information collection requirements contained in this regulation 
under the provisions of the Paperwork Reduction Act of 1980 (44 
U.S.C. 3501 et seq.) and assigned OMB Control Number 2120-0056.

------------------------------------------------------------------------
 
------------------------------------------------------------------------
                     AD 2009-09-09 Inspection Report
------------------------------------------------------------------------
Airplane Model
------------------------------------------------------------------------
Airplane Serial Number
------------------------------------------------------------------------
Airplane Tach Hours at Time of
 Inspection
------------------------------------------------------------------------
Is Upper Rudder Bracket Damaged?    No                 Yes, describe
                                                        extent of damage
------------------------------------------------------------------------
Is Middle Rudder Bracket Damaged?   No                 Yes, describe
                                                        extent of damage
------------------------------------------------------------------------
Is the Lower Rudder Bracket         No                 Yes, describe
 Damaged? (Models LC40-550FG &                          extent of damage
 LC42-550FG only)
------------------------------------------------------------------------
Is Lower Rudder Hinge Damaged?      No                 Yes, describe
 (Model LC40-550FG)                                     extend of damage
------------------------------------------------------------------------
Were any other discrepancies
 noticed during the inspection?
------------------------------------------------------------------------
Name:
------------------------------------------------------------------------
Telephone and/or e-mail address:
------------------------------------------------------------------------
Date:
------------------------------------------------------------------------
    Send report to: Gary Park, Aerospace Engineer, ACE-118W, Wichita
    Aircraft Certification Office (ACO), 1801 Airport Road, Room 100,
 Wichita, Kansas 67209; fax: (316) 946-4107; e-mail: gary.park@faa.gov.
                                Figure 1
------------------------------------------------------------------------

Alternative Methods of Compliance (AMOCs)

    (f) The Manager, Wichita Aircraft Certification Office (ACO), 
FAA, has the authority to approve AMOCs for this AD, if requested 
using the procedures found in 14 CFR 39.19. Send information to 
Attn: Gary Park, Aerospace Engineer, ACE-118W, Wichita Aircraft 
Certification Office (ACO), 1801 Airport Road, Room 100, Wichita, 
Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-4107; e-
mail: gary.park@faa.gov. Before using any airplane to which the AMOC 
applies, notify your appropriate principal inspector (PI) in the FAA 
Flight Standards District Office (FSDO), or lacking a PI, your local 
FSDO.

Material Incorporated by Reference

    (g) You must use Cessna Aircraft Company Single Engine Service 
Bulletin SB09-27-01, dated April 13, 2009, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; 
Internet: http://www.cessna.com.
    (3) You may review copies of the service information 
incorporated by reference for this AD at the FAA, Central Region, 
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 
64106. For information on the availability of this material at the 
Central Region, call (816) 329-3768.
    (4) You may also review copies of the service information 
incorporated by reference for this AD at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

[[Page 19876]]

    Issued in Kansas City, Missouri, on April 23, 2009.
Scott A. Horn,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-9793 Filed 4-29-09; 8:45 am]
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