24340 Federal Register / Vol. 78, No. 80 / Thursday, April 25, 2013 / Rules and Regulations 

21, 2011, as revised by Boeing Service 

Bulletin 737–53–1312, Revision 1, dated 

March 14, 2012, except as required by 

paragraph (k) of this AD: Do an external 

detailed inspection and an external 

nondestructive inspection (a medium 

frequency eddy current (MFEC), magneto 

optic imager (MOI), C-scan, or ultrasonic 

phased array (UTPA) inspection) for cracking 

in the fuselage skin along the chem-mill steps 

at certain locations specified in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1312, dated October 21, 2011, as revised 

by Boeing Service Bulletin 737–53–1312, 

Revision 1, dated March 14, 2012. Repeat the 

inspections thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 737–53–1312, dated 

October 21, 2011, as revised by Boeing 

Service Bulletin 737–53–1312, Revision 1, 

dated March 14, 2012. 

(h) Inspections of Shear Wrinkle Areas 

For Group 1 airplanes as identified in 

Boeing Service Bulletin 737–53–1312, dated 

October 21, 2011, as revised by Boeing 

Service Bulletin 737–53–1312, Revision 1, 

dated March 14, 2012: At the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 737–53–1312, dated 

October 21, 2011, as revised by Boeing 

Service Bulletin 737–53–1312, Revision 1, 

dated March 14, 2012, except as required by 

paragraph (k) of this AD, do an external 

detailed inspection and an external 

nondestructive inspection (MFEC, MOI, Cscan, or UTPA) for cracking in the fuselage 

skin along the chem-mill steps at certain 

shear wrinkle locations specified in, and in 

accordance with, the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1312, dated October 21, 2011, as revised 

by Boeing Service Bulletin 737–53–1312, 

Revision 1, dated March 14, 2012. Repeat the 

inspections thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 737–53–1312, dated 

October 21, 2011, as revised by Boeing 

Service Bulletin 737–53–1312, Revision 1, 

dated March 14, 2012. 

(i) Repair 

If any cracking is found during any 

inspection required by either paragraph (g) or 

(h) of this AD, before further flight, repair the 

cracking using a method approved in 

accordance with the procedures specified in 

paragraph (m) of this AD. Accomplishing the 

repair approved in accordance with the 

procedures specified in paragraph (m) of this 

AD terminates the repetitive inspection 

requirement for that area under the repair 

only. 

(j) Optional Terminating Modification 

Modification of an inspection area 

specified in paragraph (g) of this AD, 

including doing an external detailed 

inspection and an external nondestructive 

inspection (MFEC, MOI, C-scan, or UTPA) for 

cracking of the area to be modified, and a 

high frequency eddy current inspection of all 

existing holes for cracking as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

53–1312, dated October 21, 2011, as revised 

by Boeing Service Bulletin 737–53–1312, 

Revision 1, dated March 14, 2012, terminates 

the repetitive inspections required by 

paragraph (g) of this AD for that modified 

area only. If any cracking is found during any 

inspection described by this paragraph, 

before further flight, repair the cracking using 

a method approved in accordance with the 

procedures specified in paragraph (m) of this 

AD. 

(k) Service Bulletin Exception 

Boeing Service Bulletin 737–53–1312, 

dated October 21, 2011, as revised by Boeing 

Service Bulletin 737–53–1312, Revision 1, 

dated March 14, 2012, specifies compliance 

times ‘‘after the original issue date of this 

service bulletin.’’ However, this AD requires 

compliance within the specified compliance 

times ‘‘after the effective date of this AD.’’ 

(l) Post-Modification Inspections 

The post-modification inspections 

specified in Tables 3 and 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1312, dated October 21, 2011, as 

revised by Boeing Service Bulletin 737–53– 

1312, Revision 1, dated March 14, 2012, are 

not required by this AD. 

Note 1 to paragraph (l) of this AD: The 

damage tolerance inspections specified in 

Tables 3 and 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1312, dated October 21, 2011, as 

revised by Boeing Service Bulletin 737–53– 

1312, Revision 1, dated March 14, 2012, may 

be used in support of compliance with 

section 121.1109(c)(2) or 129.109(b)(2) of the 

Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 14 CFR 129.109(b)(2)). The 

actions specified in Part 5 of the 

Accomplishment Instructions and 

corresponding figures of Boeing Service 

Bulletin 737–53–1312, dated October 21, 

2011, as revised by Boeing Service Bulletin 

737–53–1312, Revision 1, dated March 14, 

2012, are not required by this AD. 

(m) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle 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. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6447; fax: (425) 917–6590; 

email: Wayne.Lockett@faa.gov. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Service Bulletin 737–53–1312, 

dated October 21, 2011. 

(ii) Boeing Service Bulletin 737–53–1312, 

Revision 1, dated March 14, 2012. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 view this 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 Renton, Washington, on April 4, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08996 Filed 4–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0330; Directorate 

Identifier 2013–NM–051–AD; Amendment 

39–17427; AD 2013–08–10] 

RIN 2120–AA64 

Airworthiness Directives; Kelowna 

Flightcraft R & D Ltd. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 80 / Thursday, April 25, 2013 / Rules and Regulations 24341 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Tracor (Convair) Model 340 and 440 

airplanes and certain Military Model C– 

131B, C–131D, C–131E, and C131F/ 

R4Y–1 airplanes. This AD requires 

repetitive inspections of the lower skin 

of the wings for cracking around the 

inboard side of the wing station (WS) 6 

and 7 access panel doubler fingers and 

between stringers 5 and 11; repetitive 

inspections of the lower skin of the 

wings for cracking around stringers 6, 8, 

and 10, and around the WS 6 and WS 

7 access panel doubler fingers; and 

repair if necessary. This AD was 

prompted by a report of a crack found 

on the lower skin of the right-hand wing 

between WS 5 and WS 6. We are issuing 

this AD to detect and correct fatigue 

cracking of the lower skin of the wings, 

which could result in reduced structural 

integrity of the wings. 

DATES: This AD becomes effective May 

10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 10, 2013. 

We must receive comments on this 

AD by June 10, 2013. 

ADDRESSES: You may send comments 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, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office 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 Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone (516) 228–7306; 

fax (516) 794–5531; email: 

jeffrey.zimmer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Emergency Airworthiness Directive CF– 

2013–04, dated February 14, 2013 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

While performing a corrosion inspection of 

the wing internal structures, an operator 

discovered a crack of significant length 

between Wing Station (WS) 5 and 6, on the 

right hand wing lower skin of a Convair 580 

aeroplane. Although an investigation is still 

ongoing to determine the cause, the crack 

appears to originate from a fastener located 

at the wing skin to wing access door doubler 

attachment. 

Previous repetitive external inspections of 

the wing lower skin in accordance with 

Structurally Significant Detail (SSD) 57–1–4, 

that was mandated by FAA AD 92–06–06, 

[Amendment 39–8186 (57 FR 9382, March 

18, 1992)], did not detect the crack because 

the location of the crack is covered by the 

nacelle drag angle. 

Cracking of the wing lower skin at a fatigue 

critical area, if not detected, could 

compromise the structural integrity of the 

wing. This [TCCA] AD mandates internal 

visual and eddy current inspections to detect 

cracking of the wing lower skin to mitigate 

this unsafe condition. Transport Canada may 

mandate additional corrective actions [repair] 

pending the outcome of the failure 

investigation and fleet findings. 

The visual and eddy current inspections 

mandated by this [TCCA] AD are considered 

as Alternative Means of Compliance (AMOC) 

to the SSD 57–1–4 inspection that was 

mandated by FAA AD 92–06–06, for the 

locations addressed by the visual and eddy 

current inspections. 

Corrective action includes repairing any 

cracking of the lower skin of the wings. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Kelowna Flightcraft Ltd. has issued 

Service Bulletin 340–57–001, dated 

February 12, 2013. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the AD and the 

MCAI or Service Information 

The MCAI and Kelowna Flightcraft 

Service Bulletin 340–57–001, dated 

February 12, 2013, specify that 

operators with a damage rate factor 

(DRF) must divide 1,000 flight hours by 

their DRF to get the repetitive 

inspection interval. However, there are 

no U.S.-registered airplanes that have a 

DRF; therefore, this AD requires that the 

repetitive inspections be done at 

intervals not to exceed 1,000 flight 

hours. 

The MCAI and Kelowna Flightcraft 

Service Bulletin 340–57–001, dated 

February 12, 2013, do not contain 

instructions to repair certain cracking 

conditions; however, this AD requires 

repairing those conditions using a 

method approved by either the Manager, 

New York Aircraft Certification Office 

(ACO), FAA; or TCCA (or its delegated 

agent). 

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 based on the manufacturer’s 

engineering analysis of the structural 

failure condition and flight hours/cycles 

on the affected fleet, which showed that 

certain areas of the lower skin of the 

wings must be inspected for fatigue 

cracking. Such fatigue cracking could 

result in reduced structural integrity of 

the wings. 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. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2013–0330; 


wreier-aviles on DSK5TPTVN1PROD with RULES
24342 Federal Register / Vol. 78, No. 80 / Thursday, April 25, 2013 / Rules and Regulations 

Directorate Identifier 2013–NM–051– 

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 will affect 

70 products of U.S. registry. We also 

estimate that it will take about 6 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate the 

cost of this AD to the U.S. operators to 

be $35,700, or $510 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in 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 the 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 AD: 

2013–08–10 Kelowna Flightcraft R & D 

Ltd.: Amendment 39–17427. Docket 

No. FAA–2013–0330; Directorate 

Identifier 2013–NM–051–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective May 10, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Tracor (Convair) Model 

340 and 440 airplanes, including airplanes 

modified by Supplemental Type Certificates 

(STC) SA1096WE http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rgstc.nsf/

0/BAB5BE3241FF1FD085256CC

10080DDDC?OpenDocument&

Highlight=sa1096we (commonly referred to 

as Model 640 airplanes), STC SA6088NM 

http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/

BEFFE27E85EAFF918625771

4007C8B4B?OpenDocument&

Highlight=sa6088nm (commonly referred to 

as Model 5800 airplanes), and STC SA4–1100 

http://rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/

AFD81364EE6A3EAC85256C

C2000C5CC2?OpenDocument&

Highlight=sa4-1100 (commonly referred to as 

Model 580 airplanes) and Military Model C– 

131B, C–131D, C–131E, and C131F/R4Y–1 

airplanes; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by a report of a 

crack found on the lower skin of the righthand (RH) wing between wing station (WS) 

5 and 6. We are issuing this AD to detect and 

correct fatigue cracking of the lower skin of 

the wings, which could result in reduced 

structural integrity of the wings. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Detailed Inspections 

Within 20 flight hours after the effective 

date of this AD: Do a one-time detailed 

inspection for cracking of the lower skin of 

the left-hand (LH) and RH wings around the 

inboard side of the WS 6 and WS 7 access 

panel doubler fingers and between stringers 

5 and 11, in accordance with the 

Accomplishment Instructions of Kelowna 

Flightcraft Service Bulletin 340–57–001, 

dated February 12, 2013. Repeat the 

inspection thereafter at intervals not to 

exceed 1,000 flight hours. 

(h) Repetitive Eddy Current Inspections 

Within 100 flight hours after the effective 

date of this AD: Do an eddy current 

inspection for cracking of the lower skin of 

the LH and RH wings for cracking around 

stringers 6, 8, and 10, and around the WS 6 

and WS 7 access panel doubler fingers, in 

accordance with the Accomplishment 

Instructions of Kelowna Flightcraft Service 

Bulletin 340–57–001, dated February 12, 

2013. Repeat the inspection thereafter at 

intervals not to exceed 1,000 flight hours. 

(i) Repair 

If any cracking is found during any 

inspection required by paragraph (g) or (h) of 

this AD: Before further flight, repair using a 

method approved by either the Manager, 

New York Aircraft Certification Office (ACO), 

FAA; or Transport Canada Civil Aviation 

(TCCA) (or its delegated agent). 

(j) Method of Compliance 

The inspections required by this AD are 

approved as a method of compliance to the 

structurally significant detail (SSD) 57–1–4 

inspection required by AD 92–06–06, 

Amendment 39–8186 (57 FR 9382, March 18, 

1992), for only the locations addressed by the 

detailed and eddy current inspections 

specified in paragraphs (g) and (h) of this AD. 

Inspections at all other locations addressed 

by SSD 57–1–4 remain applicable. 

(k) Reporting 

Submit a report of the findings (both 

positive and negative) of each inspection 

required by paragraphs (g) and (h) of this AD 

to Kelowna Flightcraft Convair Division, 

5655 Airport Way, Kelowna, Canada BC, V1V 

1S1; telephone (250) 807–5416; fax (250) 

765–7140; email 

matt_palmberg@flghtcraft.ca; at the 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 80 / Thursday, April 25, 2013 / Rules and Regulations 24343 

applicable time specified in paragraph (k)(1) 

or (k)(2) of this AD. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York 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 ACO send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone 516–228–7300; fax 

516–794–5531. 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. The AMOC approval letter must 

specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: 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. 

(m) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Emergency Airworthiness Directive CF– 

2013–04, dated February 14, 2013; and 

Kelowna Flightcraft Service Bulletin 340–57– 

001, dated February 12, 2013; for related 

information. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Kelowna Flightcraft Service Bulletin 

340–57–001, dated February 12, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Kelowna Flightcraft Ltd., 

5655 Airport Way, Kelowna, BC Canada, V1V 

1S1; telephone (250) 807–5416; fax (250) 

765–7140; Internet http://www.flightcraft.ca/ 

convair.asp. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this 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/ibrlocations.html. 

Issued in Renton, Washington, on April 8, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08987 Filed 4–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0880; Directorate 

Identifier 2012–CE–004–AD; Amendment 

39–17422; AD 2013–08–05] 

RIN 2120–AA64 

Airworthiness Directives; Cessna 

Aircraft Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Cessna Aircraft Company (Cessna) 

Model 525 airplanes equipped with 

certain part number (P/N) air 

conditioning (A/C) compressor motors. 

This AD was prompted by reports of 

smoke and/or fire in the tailcone caused 

by brushes wearing beyond their limits 

on the A/C motor. This AD requires 

inspection of the number of hours on 

the A/C compressor hour meter, 

inspection of the logbook, replacement 

of the brushes on certain P/N A/C 

compressor motors or deactivation of 

the A/C system until replacement of the 

brushes, and reporting of airplane 

information related to the replacement 

of the brushes. We are issuing this AD 

to correct the unsafe condition on these 

products. 

DATES: This AD is effective May 30, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 30, 2013. 

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; email: 

customercare@cessna.textron.com; 

Internet: 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 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Christine Abraham, Aerospace Engineer, 

Wichita Aircraft Certification Office, 

FAA, 1801 Airport Road, Room 100, 

Wichita, Kansas 67209; phone: (316) 

946–4165; fax: (316) 946–4107; email: 

christine.abraham@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to include an 

airworthiness directive (AD) that would 

apply to the specified products. That 

SNPRM published in the Federal 

Register on December 6, 2012 (77 FR 

72778). The original NPRM (77 FR 

50644, August 22, 2012) proposed to 

require inspection of the number of 

hours on the A/C compressor hour 

meter, inspection of the logbook, and 


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