Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations 29863 

to assure the product is airworthy before it 

is returned to service. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2011–0051, dated March 22, 2011; and 

Fokker MCNO MCNO–F100–057, dated 

December 17, 2010; for related information. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the following service information 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(i) Fokker Manual Change Notification— 

Operational Documentation MCNO–F100– 

057, dated December 17, 2010. 

(3) For service information identified in 

this AD, contact Fokker Services B.V., 

Technical Services Dept., P.O. Box 231, 2150 

AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; email technicalservices.

fokkerservices@stork.com; Internet http:// 

www.myfokkerfleet.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(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 Renton, Washington, on May 9, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11954 Filed 5–18–12; 8:45 am] 

BILLING CODE 4910–13–P 

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. 

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 FAAapproved 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: 

• 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 AD, contact Cessna Aircraft 

Company, Customer Support Service, 

P.O. Box 7706, Wichita, Kansas 67277; 

telephone: (316) 517–5800; fax (316) 

517–7271; Internet: 

www.cessnasupport.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 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: WICHITACOS@FAA.GOV. 

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 


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29864 Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations 

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 http:// 

www.regulations.gov, 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

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Internal and external inspection of 

the left and right wing lower main 

spar caps for cracks.

From 3 to 6 work-hours 

× $85 per hour = 

From $255 to $510.

Not applicable ............... From $255 to $510 ....... From $934,575 to 

$1,869,150. 

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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 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, 


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Federal Register / Vol. 77, No. 98 / Monday, May 21, 2012 / Rules and Regulations 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 timein-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: WICHITACOS@FAA.GOV. 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, sightseeing, 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: WICHITA– 

COS@FAA.GOV. 

(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: 

www.cessnasupport.com. 

(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: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

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 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2011–0608; Airspace 

Docket No. 11–ASW–6] 

Amendment of Class E Airspace; 

Leesville, LA 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action amends Class E 

airspace at Leesville, LA. Additional 

controlled airspace is necessary to 


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