Document ID: FAA-2009-1186-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Cessna Aircraft Company (Type Certificate Previously Held by Columbia Aircraft Manufacturing (Previously The Lancair Company))
Posted Date: 2009-12-17T05:00Z

[Federal Register: December 17, 2009 (Volume 74, Number 241)]
[Proposed Rules]               
[Page 66927-66929]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17de09-9]                         

[[Page 66927]]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-1186; Directorate Identifier 2009-CE-065-AD]
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), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2009-09-
09, which applies to certain Cessna Aircraft Company (Cessna) (type 
certificate previously held by Columbia Aircraft Manufacturing 
(previously The Lancair Company)) Models LC40-550FG, LC41-550FG, and 
LC42-550FG airplanes. 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. Since we issued AD 
2009-09-09, Cessna has developed a modification that, when 
incorporated, would terminate the repetitive inspections required by AD 
2009-09-09. The FAA has determined that long-term continued operational 
safety will be better assured by design changes that removed the source 
of the problem, rather than by repetitive inspections or other special 
procedures. Consequently, this proposed AD would retain the inspection 
requirements of AD 2009-09-09 and add a terminating action for the 
inspection requirements. We are proposing 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: We must receive comments on this proposed AD by February 1, 
2010.

ADDRESSES: Use one of the following addresses to comment on this 
proposed 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.
    For service information identified in this proposed AD, contact 
Cessna Aircraft Company, Product Support, P.O. Box 7706; Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax: (316) 942-9006; Internet: 
www.cessna.com.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number, ``FAA-
2009-1186; Directorate Identifier 2009-CE-065-AD'' at the beginning of 
your comments. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the proposed 
AD. We will consider all comments received by the closing date and may 
amend the proposed 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 proposed AD.

Discussion

    We received reports of a cracked lower rudder hinge bracket on two 
Cessna Model LC41-550FG airplanes that caused us to issue AD 2009-09-
09, Amendment 39-15895 (74 FR 19873, April 30, 2009). AD 2009-09-09 
currently requires the following on certain Cessna Models LC40-550FG, 
LC41-550FG, and LC42-550FG airplanes:
     Repetitively inspecting the rudder hinges and the rudder 
hinge brackets for damage; and
     Replacing the rudder hinge and/or rudder hinge bracket if 
damage is found.
    Cessna developed a modification that, when incorporated, would 
eliminate the need for the repetitive inspections required by AD 2009-
09-09. The FAA has determined that long-term continued operational 
safety will be better assured by design changes that removed the source 
of the problem, rather than by repetitive inspections or other special 
procedures.
    This condition, if not corrected, could result in failure of the 
rudder. This failure could lead to loss of control.

Relevant Service Information

    We have reviewed Cessna Single Engine Service Bulletin SB09-27-01, 
Revision 2, dated November 23, 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 incorporating a modification kit that 
will terminate the repetitive inspections.

FAA's Determination and Requirements of the Proposed AD

    We are proposing this AD because we evaluated all information and 
determined the unsafe condition described previously is likely to exist 
or develop on other products of the same type design. This proposed AD 
would supersede AD 2009-09-09 with a new AD that would retain the 
inspection requirements of AD 2009-09-09 and add a terminating action 
for the inspection requirements. This proposed AD would require you to 
use the service information described previously to perform these 
actions.

Costs of Compliance

    We estimate that this proposed AD would affect 535 airplanes in the 
U.S. registry.
    We estimate the following costs to do the proposed inspections:

----------------------------------------------------------------------------------------------------------------
                                                                                  Total cost per   Total cost on
                  Labor cost                               Parts cost                airplane     U.S. operators
----------------------------------------------------------------------------------------------------------------
Inspection with rudder removed: 1.2 work-hours  Not applicable..................             $96         $51,360
 x $80 per hour = $96.

[[Page 66928]]

Inspection without rudder removed: .5 work-     Not applicable..................              40          21,400
 hour x $80 per hour = $40.
----------------------------------------------------------------------------------------------------------------

     We estimate the following costs to do the proposed modification:

------------------------------------------------------------------------
                                                          Total cost per
               Labor cost                   Parts cost       airplane
------------------------------------------------------------------------
For Models LC40-550FG and LC42-550FG                $743            $823
 airplanes: 1 work-hour x $80 per hour =
 $80....................................
For Model LC41-550FG airplanes: 1 work-              803             883
 hour x $80 per hour = $80..............
------------------------------------------------------------------------

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 have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 
regulation:
    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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket that contains the proposed 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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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. 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:

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

Comments Due Date

    (a) We must receive comments on this airworthiness directive 
(AD) action by February 1, 2010.

Affected ADs

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

Applicability

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

------------------------------------------------------------------------
                 Model                             Serial Nos.
------------------------------------------------------------------------
LC40-550FG............................  4001, 4002, and 40004 through
                                         40079.
LC41-550FG............................  41001 through 41569, 41571
                                         through 41800, 411001 through
                                         411087, 411089 through 411110,
                                         411112 through 411138, 411140,
                                         411142, and 411147.
LC42-550FG............................  42001 through 42009, 42011
                                         through 42558, 42560 through
                                         42569, 421001 through 421013,
                                         421015 through 421017, and
                                         421019.
------------------------------------------------------------------------

Subject

    (d) Air Transport Association of America (ATA) 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 actions, 
unless already done:
    (1) Inspect the rudder hinges and rudder hinge brackets for 
damage, i.e., cracking, deformation, and discoloration, following 
Cessna Aircraft Company Single Engine

[[Page 66929]]

Service Bulletin SB09-27-01, dated April 13, 2009, or Cessna 
Aircraft Company Single Engine Service Bulletin SB09-27-01, Revision 
2, dated November 23, 2009. Use the compliance times specified in 
the following table:

----------------------------------------------------------------------------------------------------------------
            Condition                        Initial inspection                    Repetitive inspection
----------------------------------------------------------------------------------------------------------------
(i) For airplanes with 25 hours    With the rudder removed and using 10X   Thereafter inspect as follows until
 time-in-service (TIS) or more as   visual magnification, inspect all       the modification required in
 of May 11, 2009 (the effective     three rudder hinges and rudder hinge    paragraph (f)(5) of this AD is done:
 date of AD 2009-09-09):            brackets at whichever of the           (A) Every 25 hours TIS or 3 months,
                                    following occurs first:                 whichever occurs first, without
                                   (A) Within the next 10 hours TIS after   removing the rudder, visually
                                    May 11, 2009 (the effective date of     inspect all three rudder hinges and
                                    AD 2009-09-09); or                      rudder hinge brackets; and
                                   (B) Within the next 30 days after May   (B) Every 50 hours TIS or 6 months,
                                    11, 2009 (the effective date of AD      whichever occurs first, with the
                                    2009-09-09).                            rudder removed and using 10X visual
                                                                            magnification, inspect all three
                                                                            rudder hinges and rudder hinge
                                                                            brackets.
(ii) For airplanes with less than  Without removing the rudder, visually   Thereafter inspect as follows until
 25 hours TIS as of May 11, 2009    inspect all three rudder hinges and     the modification required in
 (the effective date of AD 2009-    rudder hinge brackets, at whichever     paragraph (f)(5) of this AD is done:
 09-09):                            of the following occurs later:         (A) Every 25 hours TIS or 3 months,
                                   (A) Upon accumulating 25 hours TIS; or   whichever occurs first, without
                                   (B) Within the next 10 hours TIS after   removing the rudder, visually
                                    May 11, 2009 (the effective date of     inspect all three rudder hinges and
                                    AD 2009-09-09).                         rudder hinge brackets; and
                                                                           (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) If damage is found on any of the rudder hinges and/or 
rudder hinge brackets during any inspection required in paragraphs 
(f)(1)(i) or (f)(1)(ii) of this AD, before further flight, 
incorporate Cessna Single Engine Modification Kit MK400-27-01, dated 
November 23, 2009, as specified in Cessna Aircraft Company Single 
Engine Service Bulletin SB09-27-01, Revision 2, dated November 23, 
2009. Incorporating Cessna Single Engine Modification Kit MK400-27-
01, dated November 23, 2009, terminates the repetitive inspections 
required in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
    (3) 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) Within the next 24 months after the effective date of this 
AD, incorporate Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009, as specified in Cessna Aircraft Company 
Single Engine Service Bulletin SB09-27-01, Revision 2, dated 
November 23, 2009.
    (i) Incorporating Cessna Single Engine Modification Kit MK400-
27-01, dated November 23, 2009, terminates the repetitive 
inspections required in paragraphs (f)(1)(i) and (f)(1)(ii) of this 
AD.
    (ii) At any time after the initial inspections required in 
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD, you may incorporate 
Cessna Single Engine Modification Kit MK400-27-01, dated November 
23, 2009, to terminate the repetitive inspections required in 
paragraphs (f)(1)(i) and (f)(1)(ii) of this AD.
    (5) For any affected airplane that has Cessna Aircraft Company 
Single Engine Service Bulletin SB09-27-01, Revision 1, dated August 
31, 2009, incorporated, within the next 30 days after the effective 
date of this AD, inspect for proper rudder hinge and rudder bracket 
hardware thread engagement and inspect the rudder travel. Follow the 
Accomplishment Instructions in Cessna Single Engine Modification Kit 
MK400-27-01, dated November 23, 2009, as specified in Cessna 
Aircraft Company Single Engine Service Bulletin SB09-27-01, Revision 
2, dated November 23, 2009.
    (i) During the inspection required in paragraph (f)(5) of this 
AD, if any discrepancies are found in the rudder hinge or rudder 
bracket hardware, before further flight replace the affected 
hardware. Do the replacement following the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009.
    (ii) During the inspection required in paragraph (f)(5) 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, before further flight remove 
the rudder and reinstall it following the Accomplishment 
Instructions in Cessna Single Engine Modification Kit MK400-27-01, 
dated November 23, 2009.
    (iii) After the inspection and any necessary corrective actions 
required in paragraphs (f)(5), (f)(5)(i), and (f)(5)(ii) of this AD, 
incorporation of Cessna Aircraft Company Single Engine Service 
Bulletin SB09-27-01, Revision 1, dated August 31, 2009, terminates 
the repetitive inspections required in paragraphs (f)(1)(i) and 
(f)(1)(ii) of this AD.

Alternative Methods of Compliance (AMOCs)

    (g) 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.
    (h) AMOCs approved for AD 2009-09-09 are approved for this AD.

Related Information

    (i) To get copies of the service information referenced 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 AD docket, go to 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., 
Washington, DC 20590, or on the Internet at http://
www.regulations.gov.

    Issued in Kansas City, Missouri, on December 10, 2009.
Margaret Kline,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E9-29982 Filed 12-16-09; 8:45 am]

BILLING CODE 4910-13-P