AD 2012-10-04

[Federal Register Volume 77, Number 98 (Monday, May 21, 2012)]
[Rules and Regulations]
[Pages 29863-29865]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2012-11944]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0534; Directorate Identifier 2012-CE-015-AD; 
Amendment 39-17053; AD 2012-10-04]
RIN 2120-AA64


Airworthiness Directives; Cessna Aircraft Company Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Cessna Aircraft Company Models 210G, T210G, 210H, T210H, 210J, T210J, 
210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N, 210R, T210R, 
and P210R airplanes. This AD requires an inspection(s) of the left and 
right wing lower main spar caps for cracks and either replacing cracked 
wing lower main spar caps, wing spars, or wings (as applicable) with 
serviceable spar caps, spars, or wings that are found free of cracks or 
incorporating an FAA-approved modification. This AD also requires 
reporting the results of the inspections to the FAA. This AD was 
prompted by reports of cracks found in the wing lower main spar caps on 
the above-referenced airplanes with cantilever metal wings. We are 
issuing this AD to correct the unsafe condition on these products.

DATES: This AD is effective June 5, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of June 5, 2012.
    We must receive comments on this AD by July 5, 2012.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 AD, contact Cessna 
Aircraft Company, Customer Support Service, P.O. Box 7706, Wichita, 
Kansas 67277; telephone: (316) 517-5800; fax (316) 517-7271; Internet: 
<a href="http://www.cessnasupport.com">www.cessnasupport.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 street address for 
the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Gary D. Park, Aerospace Engineer, 
Wichita Aircraft Certification Office, (ACO), FAA, 1801 Airport Road, 
Wichita, KS 67209; phone: (316) 946-4123; fax: (316) 946-4107; email: 
<a href="/cdn-cgi/l/email-protection#91c6d8d2d9d8c5d0bcd2dec2d1d7d0d0bfd6dec7"><span class="__cf_email__" data-cfemail="14435d575c5d405539575b47545255553a535b42">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We received reports of cracks found in the wing lower main spar 
caps on Cessna Aircraft Company Models 210G, T210G, 210H, T210H, 210J, 
T210J, 210K, T210K, 210L, T210L, 210M, T210M, 210N, T210N, P210N, 210R, 
T210R, and P210R airplanes with cantilever metal wings. The reports 
include a wing lower main spar cap that was completely severed with the 
skin split. This condition, if not corrected, could result in 
structural failure of the wing with consequent loss of control.

Relevant Service Information

    We reviewed Cessna Aircraft Company Single Engine Service Letter 
SEL-57-01, Revision 1, dated May 9, 2012. The service letter describes 
procedures for visually inspecting the right and left lower main spar 
caps for cracks and replacing the spar cap, wing spar, or wing, as 
applicable.

FAA's Determination

    We are issuing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

AD Requirements

    This AD requires a one-time internal (for all airplanes) and 
external (for certain airplanes) visual inspection of the left and 
right wing lower main spar caps for cracks and either replacing cracked 
wing lower main spar caps, wing spars, or wings, or incorporating an 
FAA-approved modification. This AD also requires reporting the results 
of the inspections to the FAA, Wichita ACO.

Interim Action

    We consider this AD interim action. We are requiring inspection(s) 
of the left and right wing lower main spar caps with a report to the 
FAA of the results. We will work with the type certificate

[[Page 29864]]

holder to evaluate that information to determine repetitive inspection 
intervals and subsequent terminating action. Based on this evaluation, 
we may initiate further rulemaking action to address the unsafe 
condition identified in this AD.

FAA's Justification and 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 
cracks in the wing lower main spar caps could result in structural 
failure of the wing during flight with consequent loss of control. 
Therefore, we find that notice and opportunity for prior public comment 
are impracticable and that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include the docket number FAA-2012-0534 and 
Directorate Identifier 2012-CE-015-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this AD. We will 
consider all comments received by the closing date and may amend this 
AD because of those comments.
    We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this AD.

Costs of Compliance

    We estimate that this AD affects 3,665 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                   Labor cost          Parts cost       Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Internal and external inspection  From 3 to 6 work-   Not applicable....  From $255 to $510.  From $934,575 to
 of the left and right wing        hours x $85 per                                             $1,869,150.
 lower main spar caps for cracks.  hour = From $255
                                   to $510.
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    Currently, there is no FAA-approved modification for a cracked wing 
lower main spar cap. If cracks are found during the inspections 
required by this AD, further flight is prohibited until an FAA-approved 
modification is incorporated or the cracked wing lower main spar cap is 
replaced with a serviceable spar cap, wing spar, or wing (as 
applicable) if one is available. The FAA does not have availability and 
cost information on serviceable spar caps, wing spars, or wings. 
Therefore, at this time, the FAA has no way of determining any on-
condition costs associated with replacing or modifying cracked wing 
lower main spar caps.

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

    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 adding the following new airworthiness 
directive (AD):

2012-10-04 Cessna Aircraft Company (Cessna): Amendment 39-17053; 
Docket No. FAA-2012-0534; Directorate Identifier 2012-CE-015-AD.

(a) Effective Date

    This AD is effective June 5, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the following Cessna model airplanes listed 
in paragraphs (c)(1) through (c)(13) of this AD, certificated in any 
category:
    (1) 210G: Serial numbers (S/Ns) 21058819 through 21058936,
    (2) T210G: S/Ns T210-0198 through T210-0307,
    (3) 210H: S/Ns 21058937 through 21059061,
    (4) T210H: S/Ns T210-0308 through T210-0392,
    (5) 210J: S/Ns 21059062 through 21059199,
    (6) T210J: S/Ns 21058140, and T210-0393 through T210-0454,
    (7) 210K and T210K: S/Ns 21059200 through 21059502,
    (8) 210L and T210L: S/Ns 21059503 through 21061041, and 21061043 
through 21061573,

[[Page 29865]]

    (9) 210M and T210M: S/Ns 21061042, 21061574 through 21062954,
    (10) 210N and T210N: S/Ns 21062955 through 21064897,
    (11) P210N: S/Ns P21000001 through P21000834,
    (12) 210R and T210R: S/Ns 21064898 through 21065009, and
    (13) P210R: S/Ns P21000835 through P21000874.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 57, Wings.

(e) Unsafe Condition

    This AD was prompted by reports of cracks found in the wing 
lower main spar caps on the affected airplanes with cantilever metal 
wings. We are issuing this AD to prevent structural failure of the 
wing with consequent loss of control.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Inspection of the Left Wing and the Right Wing

    (1) For airplanes with 10,000 hours time-in-service (TIS) or 
more as of June 5, 2012, (the effective date of this AD), do the 
following in accordance with Cessna Single Engine Service Letter 
SEL-57-01, Revision 1, dated May 9, 2012:
    (i) Before further flight after June 5, 2012 (the effective date 
of this AD), do an external visual inspection of the outer skin 
underneath the main spar cap fitting between wing station (WS) 25.25 
and WS 45.00 for cracks.
    (ii) If no cracks are found during the inspection required in 
paragraph (g)(1)(i) of this AD, within the next 5 hours TIS after 
June 5, 2012 (the effective date of this AD), do an internal visual 
inspection of the wing lower main spar caps between WS 25.25 and WS 
45.00 for cracks.
    (2) For airplanes with 5,000 hours TIS or more, but less than 
10,000 hours TIS as of June 5, 2012 (the effective date of this AD), 
within the next 25 hours TIS after June 5, 2012 (the effective date 
of this AD), do an internal visual inspection of the wing lower main 
spar caps between WS 25.25 and WS 45.00 for cracks in accordance 
with Cessna Single Engine Service Letter SEL-57-01, Revision 1, 
dated May 9, 2012.
    (3) For airplanes with less than 5,000 TIS as of June 5, 2012 
(the effective date of this AD), when the airplane reaches 5,000 
hours TIS or within the next 25 hours TIS after June 5, 2012 (the 
effective date of this AD), whichever occurs later, do an internal 
visual inspection of the wing lower main spar caps between WS 25.25 
and WS 45.00 for cracks in accordance with Cessna Single Engine 
Service Letter SEL-57-01, Revision 1, dated May 9, 2012.

(h) Corrective Action

    If cracks are found during the inspections required in 
paragraphs (g)(1)(i), (g)(1)(ii), (g)(2), or (g)(3) of this AD, 
before further flight after the inspection in which cracks are 
found, either replace the cracked part (spar cap, wing spar, or 
wing, as applicable) with a serviceable part that is found free of 
cracks or modify the spar cap, wing spar, or wing (as applicable) 
following a procedure approved for this AD by the FAA, Wichita 
Aircraft Certification Office (ACO).

(i) Reporting Requirement

    Within 10 days after each inspection or 10 days after June 5, 
2012 (the effective date of this AD), whichever occurs later, report 
the results of the inspections to the FAA, Wichita ACO, Attn: Gary 
D. Park, Aerospace Engineer, 1801 Airport Road, Room 100; fax: (316) 
946-4107; email: <a href="/cdn-cgi/l/email-protection#8ddac4cec5c4d9cca0cec2decdcbcccca3cac2db"><span class="__cf_email__" data-cfemail="a2f5ebe1eaebf6e38fe1edf1e2e4e3e38ce5edf4">[email&#160;protected]</span></a>. Include the following 
information in addition to the undated Attachment (titled Wing Lower 
Main Spar Cap Inspection Report) to Cessna Single Engine Service 
Letter SEL-57-01, Revision 1, dated May 9, 2012. Please identify AD 
2012-10-04 in the subject line if submitted through email.
    (1) Hours TIS at time of inspection.
    (2) Installed wing modifications.
    (3) Approved gross weight increases.
    (4) Extended low altitude operations (i.e., pipe line survey, 
surface spotting, sight-seeing, etc.)
    (5) A description of any cracks detected.

(j) Credit for Actions Accomplished in Accordance With Previous Service 
Information

    This paragraph provides credit for the actions required in 
paragraphs (g) and (h) of this AD if already done before June 5, 
2012 (the effective date of this AD) following Cessna Single Engine 
Service Letter SEL-57-01, dated April 27, 2012.

(k) Paperwork Reduction Act Burden Statement

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to a penalty 
for failure to comply with a collection of information subject to 
the requirements of the Paperwork Reduction Act unless that 
collection of information displays a current valid OMB Control 
Number. The OMB Control Number for this information collection is 
2120-0056. Public reporting for this collection of information is 
estimated to be approximately 5 minutes per response, including the 
time for reviewing instructions, completing and reviewing the 
collection of information. All responses to this collection of 
information are mandatory. Comments concerning the accuracy of this 
burden and suggestions for reducing the burden should be directed to 
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: 
Information Collection Clearance Officer, AES-200.

(l) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Wichita 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 appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(m) Related Information

    For more information about this AD, contact Gary D. Park, 
Aerospace Engineer, Wichita ACO, FAA, 1801 Airport Road, Wichita, KS 
67209; phone: (316) 946-4123; fax: (316) 946-4107; email: <a href="/cdn-cgi/l/email-protection#62352b212a2b36234f212d31222423234c252d34"><span class="__cf_email__" data-cfemail="a1f6e8e2e9e8f5e08ce2eef2e1e7e0e08fe6eef7">[email&#160;protected]</span></a>.

(n) Material Incorporated by Reference

    (1) You must use Cessna Single Engine Service Letter SEL-57-01, 
Revision 1, dated May 9, 2012, (includes the undated Attachment 
titled Wing Lower Main Spar Cap Inspection Report) to do the actions 
required by this AD, unless the AD specifies otherwise. The Director 
of the Federal Register approved the incorporation by reference 
(IBR) under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Cessna Aircraft Company, Customer Support Service, P.O. Box 7706, 
Wichita, Kansas 67277; telephone: (316) 517-5800; fax (316) 517-
7271; Internet: <a href="http://www.cessnasupport.com">www.cessnasupport.com</a>.
    (3) 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.
    (4) 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 NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr_locations.html">http://www.archives.gov/federal-register/cfr/ibr_locations.html</a>.

    Issued in Kansas City, Missouri, on May 11, 2012.
John Colomy,
Acting Manager, Small Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-11944 Filed 5-18-12; 8:45 am]
BILLING CODE 4910-13-P