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[Federal Register Volume 76, Number 25 (Monday, February 7, 2011)]
[Rules and Regulations]
[Pages 6525-6529]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2008]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD; 
Amendment 39-16588; AD 2011-03-04]
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.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. AD 2009-09-09 currently requires 
repetitive inspections of the rudder hinges and the rudder hinge 
brackets for damage, i.e., cracking, deformation, and discoloration. If 
damage is found during any inspection, AD 2009-09-09 also requires 
replacing the damaged rudder hinge and/or rudder hinge bracket. This 
new AD retains the inspection requirements of AD 2009-09-09, adds 
airplanes to the Applicability section, and adds a terminating action 
for the repetitive inspection requirements. This AD resulted from the 
manufacturer developing a modification that terminates the repetitive 
inspections and from the manufacture adding airplane serial numbers 
into the Applicability section. 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 is effective March 14, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of March 14, 
2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 11, 2009 
(74 FR 19873, April 30, 2009).

ADDRESSES: 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. You may review copies of the referenced service 
information at the FAA, Small Airplane Directorate, 901 Locust, Kansas 
City, Missouri 64106. For information on the availability of this 
material at the FAA, call (816) 329-4148.

Examining the AD Docket

    You may examine the AD docket 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 AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The address for the 
Docket Office (phone: 800-647-5527) is Document Management Facility, 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200

[[Page 6526]]

New Jersey Avenue SE., Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Gary Park, Aerospace Engineer, Wichita 
Aircraft Certification Office, FAA, 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 issued a supplemental notice of proposed rulemaking (SNPRM) to 
amend 14 CFR part 39 to supersede AD 2009-09-09, Amendment 39-15895 (74 
FR 19873, April 30, 2009). That AD applies to the specified products. 
The SNPRM published in the Federal Register on October 27, 2010 (75 FR 
66009). That SNPRM proposed to retain the inspection requirements of AD 
2009-09-09, add airplanes to the Applicability section, and add a 
terminating action for the repetitive inspection requirements using 
revised service information.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the SNPRM or on the determination 
of the cost to the public.

Conclusion

    We reviewed the relevant data and determined that air safety and 
the public interest require adopting the AD as proposed except for 
minor editorial changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
SNPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the SNPRM.

Costs of Compliance

    We estimate that this proposed AD affects 790 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this AD:

                                                                     Estimated Costs
--------------------------------------------------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product             Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Inspecting the rudder hinges and     1.5 work-hours x $85 per     Not applicable........  $127.50 per            $72,675 per inspection cycle.
 rudder hinge brackets for damage     hour = $127.50 per                                   inspection cycle.
 with rudder removed (affects 570     inspection cycle.
 airplanes).
Inspecting the rudder hinges and     .5 work-hour x $85 per hour  Not applicable........  $42.50 per inspection  $24,225 per inspection cycle.
 rudder hinge brackets for damage     = $42.50 per inspection                              cycle.
 without rudder removed (affects      cycle.
 570 airplanes).
Incorporating the modification kit   1 work-hour x $85 per hour   $739..................  $824.................  $203,528.
 for Models LC40-550FG and LC42-      = $85.
 550FG airplanes (affects 247
 airplanes).
Incorporating the modification kit   1 work-hour x $85 per hour   $848..................  $933.................  $487,959.
 for Model LC41-550FG airplanes       = $85.
 (affects 523 airplanes).
Inspecting the rudder hinge and the  .5 work-hour x $85 per hour  Not applicable........  $42.50...............  $850.
 rudder brackets attachment           = $42.50.
 hardware for correct thread
 engagement (affects 20 airplanes).
Inspecting the rudder travel         1 work-hour x $85 per hour   Not applicable........  $85..................  $1,700.
 (affects 20 airplanes).              = $85.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary repairs that 
will be required based on the results of the inspection of the rudder 
hinge and the rudder brackets attachment hardware for correct thread 
engagement and the rudder travel. We have no way of determining the 
number of aircraft that might need these repairs:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Repair the rudder hinge and the rudder          .5 work-hour x $85 per hour =                $14          $56.50
 brackets attachment hardware thread             $42.50.
 engagement (could affect 20 airplanes).
Repair the rudder travel (could affect 20       .5 work-hour x $85 per hour =                 14           56.50
 airplanes).                                     $42.50.
----------------------------------------------------------------------------------------------------------------

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.

[[Page 6527]]

Regulatory Findings

    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.
    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),
    (3) Will not affect intrastate aviation in Alaska, and
    (4) 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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

    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 removing Airworthiness Directive (AD) 
2009-09-09, Amendment 39-15895 (74 FR 19873, April 30, 2009), and 
adding the following new AD:

2011-03-04 Cessna Aircraft Company (Type Certificate Previously Held 
by Columbia Aircraft Manufacturing (Previously The Lancair 
Company)): Amendment 39-16588; Docket No. FAA-2009-1186; Directorate 
Identifier 2009-CE-065-AD.

Effective Date

    (a) This airworthiness directive (AD) is effective March 14, 
2011.

Affected ADs

    (b) This AD supersedes AD 2009-09-09, Amendment 39-15895.

Applicability

    (c) This AD applies to the following Cessna Aircraft Company 
(type certificate previously held by Columbia Aircraft Manufacturing 
(previously The Lancair Company)) airplane models and serial numbers 
that are certificated in any category:

                            Group 1 Airplanes
------------------------------------------------------------------------
               Model                             Serial Nos.
------------------------------------------------------------------------
LC40-550FG (300)..................  40001, 40002, and 40004 through
                                     40079.
LC41-550FG (400)..................  41001 through 41569, 41571 through
                                     41800, 411001 through 411087,
                                     411089 through 411110, 411112
                                     through 411138, 411140, 411142, and
                                     411147.
LC42-550FG (350)..................  42001 through 42009, 42011 through
                                     42558, 42560 through 42569, 421001
                                     through 421013, 421015 through
                                     421017, and 421019.
------------------------------------------------------------------------

                            Group 2 Airplanes
------------------------------------------------------------------------
               Model                             Serial Nos.
------------------------------------------------------------------------
LC41-550FG (400)..................  41570, 411088, 411111, 411139,
                                     411141, 411143 through 411146, and
                                     411148 through 411153.
LC42-550FG (350)..................  42010, 42559, 421014, 421018, and
                                     421020.
------------------------------------------------------------------------

Subject

    (d) Joint Aircraft System Component (JASC)/Air Transport 
Association (ATA) of America Code 55, Stabilizers.

Unsafe Condition

    (e) This AD is the result of reports received of a cracked lower 
rudder hinge bracket 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

    (f) To address this problem, you must do the following, unless 
already done:
    (1) For Group 1 airplanes specified in paragraph (c) of this AD: 
Using the compliance times specified in table 1 of this AD, inspect 
the rudder hinges and rudder hinge brackets for damage, i.e., 
cracking, deformation, and discoloration. Do the inspections 
following Cessna Single Engine Service Bulletin SB09-27-01, dated 
April 13, 2009; Cessna Single Engine Service Bulletin SB09-27-01, 
Revision 2, dated November 23, 2009; or Cessna Single Engine Service 
Bulletin SB09-27-01, Revision 3, dated July 20, 2010.

[[Page 6528]]

                  Table 1--Inspection Compliance Times
------------------------------------------------------------------------
                               Initially inspect .  Repetitively inspect
          Condition                    . .                  . . .
------------------------------------------------------------------------
(i) For airplanes with 25     With the rudder       Thereafter inspect
 hours time-in-service (TIS)   removed and using     as follows until
 or more as of May 11, 2009    10X visual            the modification
 (the effective date of AD     magnification,        required in
 2009-09-09).                  inspect all three     paragraph (f)(5) of
                               rudder hinges and     this AD is done:
                               rudder hinge         (A) Every 25 hours
                               brackets at           TIS or 3 months,
                               whichever of the      whichever occurs
                               following occurs      first, without
                               first                 removing the
                              (A) Within the next    rudder, visually
                               10 hours TIS after    inspect all three
                               May 11, 2009 (the     rudder hinges and
                               effective date of     rudder hinge
                               AD 2009-09-09); or.   brackets; and
                              (B) Within the next   (B) Every 50 hours
                               30 days after May     TIS or 6 months,
                               11, 2009 (the         whichever occurs
                               effective date of     first, with the
                               AD 009-09-09).        rudder removed and
                                                     using 10X visual
                                                     magnification,
                                                     inspect all three
                                                     rudder hinges and
                                                     rudder hinge
                                                     brackets.
(ii) For airplanes with less  Without removing the  Thereafter inspect
 than 25 hours TIS as of May   rudder, visually      as follows until
 11, 2009 (the effective       inspect all three     the modification
 date of AD 2009-09-09).       rudder hinges and     required in
                               rudder hinge          paragraph (f)(5) of
                               brackets, at          this AD is done:
                               whichever of the     (A) Every 25 hours
                               following occurs      TIS or 3 months,
                               later.                whichever occurs
                              (A) Upon               first, without
                               accumulating 25       removing the
                               hours TIS; or.        rudder, visually
                              (B) Within the next    inspect all three
                               10 hours TIS after    rudder hinges and
                               May 11, 2009 (the     rudder hinge
                               effective date of     brackets; and
                               AD 2009-09-09).      (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.
------------------------------------------------------------------------

     (2) For Group 1 airplanes specified in paragraph (c) of this 
AD: Before further flight after any inspection required in 
paragraphs (f)(1)(i) or (f)(1)(ii) of this AD in which damage is 
found on any of the rudder hinges and/or rudder hinge brackets, 
incorporate Cessna Single Engine Modification Kit MK400-27-01, dated 
November 23, 2009; or Cessna Single Engine Modification Kit MK400-
27-01A dated July 20, 2010, as specified in Cessna Single Engine 
Service Bulletin SB09-27-01, Revision 2, dated November 23, 2009; 
and Cessna Single Engine Service Bulletin SB09-27-01, Revision 3, 
dated July 20, 2010. Incorporating either Modification Kit MK400-27-
01 or Modification Kit MK400-27-01A, terminates the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (3) For Group 1 airplanes specified in paragraph (c) of this AD: 
If the repetitive inspections required in paragraphs (f)(1)(i) and 
(f)(1)(ii) 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.
    (4) For Group 1 airplanes specified in paragraph (c) of this AD: 
Within the next 24 months after March 14, 2011 (the effective date 
of this AD), incorporate Cessna Single Engine Modification Kit 
MK400-27-01, dated November 23, 2009; or Cessna Single Engine 
Modification Kit MK400-27-01A, dated July 20, 2010, as specified in 
Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated 
November 23, 2009; and Cessna Single Engine Service Bulletin SB09-
27-01, Revision 3, dated July 20, 2010, unless already done as 
specified in paragraph (f)(2) of this AD. Incorporating either 
Modification Kit MK400-27-01 or Modification Kit MK400-27-01A, 
terminates the repetitive inspections required in paragraphs 
(f)(1)(i) and (f)(1)(ii) of this AD.
    (5) For Group 1 airplanes specified in paragraph (c) of this AD: 
At any time after the initial inspections required in paragraphs 
(f)(1)(i) and (f)(1)(ii) of this AD, as long as no damage is found, 
and no later than the compliance time specified in paragraph (f)(4) 
of this AD, you may incorporate Cessna Single Engine Modification 
Kit MK400-27-01, dated November 23, 2009; or Cessna Single Engine 
Modification Kit MK400-27-01A, dated July 20, 2010, as specified in 
Cessna Single Engine Service Bulletin SB09-27-01, Revision 2, dated 
November 23, 2009; and Cessna Single Engine Service Bulletin SB09-
27-01, Revision 3, dated July 20, 2010, to terminate the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (6) For any Group 1 airplane with Cessna Single Engine Service 
Bulletin SB09-27-01, Revision 1, dated August 31, 2009, already 
incorporated and for all Group 2 airplanes: Within the next 30 days 
after March 14, 2011 (the effective date of this AD), inspect for 
proper rudder hinge and rudder bracket hardware thread engagement 
and inspect the rudder travel. Do these inspections following the 
Accomplishment Instructions in Cessna Single Engine Modification Kit 
MK400-27-01, dated November 23, 2009; or the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01A, 
dated July 20, 2010.
    (i) Before further flight after the inspection required in 
paragraph (f)(6) of this AD, if any discrepancies are found in the 
rudder hinge or rudder bracket hardware, replace the affected 
hardware. Do the replacements following the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009; or the Accomplishment Instructions in 
Cessna Single Engine Modification Kit MK400-27-01A, dated July 20, 
2010.
    (ii) Before further flight after the inspection required in 
paragraph (f)(6) of this AD, if the rudder travel is outside the 
limits specified in the Accomplishment Instructions in Cessna Single 
Engine Modification Kit MK400-27-01, dated November 23, 2009; or the 
Accomplishment Instructions in Cessna Single Engine Modification Kit 
MK400-27-01A, dated July 20, 2010, reinstall the rudder following 
the Accomplishment Instructions in either Cessna Single Engine 
Modification Kit MK400-27-01, dated November 23, 2009; or Cessna 
Single Engine Modification Kit MK400-27-01A, dated July 20, 2010.
    (iii) After the inspection and any necessary corrective actions 
required in paragraphs (f)(6), (f)(6)(i), and (f)(6)(ii) of this AD, 
no further action is required.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (g) For all airplanes specified in paragraph (c) of this AD: As 
of March 14, 2011 (the effective date of this AD), if Cessna Single 
Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 
2009, has already been incorporated, no further action is required.

Alternative Methods of Compliance (AMOCs)

    (h)(1) 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. In accordance with 14 
CFR 39.19, send your request to your principal inspector or local 
Flight Standards District Office, as appropriate. If sending 
information directly to the manager of the ACO, send it to the 
attention of the person identified in the Related Information 
section of this AD.
    (2) Before using any approved AMOC, notify your Principal 
Maintenance Inspector or Principal Avionics Inspector, as 
appropriate, or lacking a principal inspector, your local Flight 
Standards District Office.
    (3) AMOCs approved for AD 2009-09-09 are approved for this AD.

Related Information

    (i) For more information about this AD, contact Gary Park, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Room 100, 
Wichita, Kansas 67209; telephone: (316) 946-4123; fax: (316) 946-
4107; e-mail: gary.park@faa.gov.

Material Incorporated by Reference

    (j) You must use Cessna Single Engine Service Bulletin SB09-27-
01, dated April 13, 2009; Cessna Single Engine Service Bulletin 
SB09-27-01, Revision 2, dated November 23, 2009; Cessna Single 
Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010;

[[Page 6529]]

Cessna Single Engine Modification Kit MK400-27-01, dated November 
23, 2009; and Cessna Single Engine Modification Kit MK400-27-01A, 
dated July 20, 2010, 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 Cessna Single Engine Service Bulletin 
SB09-27-01, Revision 2, dated November 23, 2009; and Cessna Single 
Engine Service Bulletin SB09-27-01, Revision 3, dated July 20, 2010; 
Cessna Single Engine Modification Kit MK400-27-01, dated November 
23, 2009; and Cessna Single Engine Modification Kit MK400-27-01A, 
dated July 20, 2010, under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) The Director of the Federal Register previously approved the 
incorporation by reference of Cessna Single Engine Service Bulletin 
SB09-27-01, dated April 13, 2009, on May 11, 2009 (74 FR 19873, 
April 30, 2009).
    (3) 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.
    (4) You may review copies of the service information at the FAA, 
Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. 
For information on the availability of this material at the FAA, 
call 816-329-4148.
    (5) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Kansas City, Missouri, on January 25, 2011.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-2008 Filed 2-4-11; 8:45 am]
BILLING CODE 4910-13-P
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