Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 32353 

identified only on the title page of Chapter 

4. 

(iii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 20, dated April 23, 

2012, of the Cessna Model 560 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(iv) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 13, dated April 23, 

2012, of the Cessna Model 560XL 

Maintenance Manual. The revision level of 

Chapter 4 is identified only on the title page 

of Chapter 4. 

(v) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 30, dated April 23, 

2012, of the Cessna Model 650 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(vi) Subject 4–11–00, Replacement Time 

Limits-General, of Chapter 4, Airworthiness 

Limitations, Revision 4, dated April 23, 2012, 

of the Cessna Model 500/501Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(vii) Subject 4–11–00, Replacement Time 

Limits, of Chapter 4, Airworthiness 

Limitations, Revision 7, dated April 23, 2012, 

of the Cessna Model S550 Maintenance 

Manual. The revision level of Chapter 4 is 

identified only on the title page of Chapter 

4. 

(3) For Cessna service information 

identified in this AD, contact Cessna Aircraft 

Co., P.O. Box 7706, Wichita, KS 67277; 

telephone 316–517–6215; fax 316–517–5802; 

email citationpubs@cessna.textron.com; 

Internet https://www.cessnasupport.com/ 

newlogin.html. 

(4) You may view this service information 

at 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 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–12662 Filed 5–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0426; Directorate 

Identifier 2013–NM–084–AD; Amendment 

39–17463; AD 2013–11–03] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final Rule; Request for 

Comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–215–1A10 

and CL–215–6B11 (CL–215T Variant) 

airplanes. This AD requires repetitive 

detailed inspections for cracking of the 

left-hand (LH) and right-hand (RH) wing 

lower skin, and repair if necessary. This 

AD also provides terminating action for 

the repetitive detailed inspections. This 

AD was prompted by reports of a 

fractured wing lower rear spar cap and 

reinforcing strap. We are issuing this AD 

to detect and correct cracked wing 

structure, which could result in failure 

of the wing. 

DATES: This AD becomes effective June 

14, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 14, 2013. 

We must receive comments on this 

AD by July 15, 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: 

Ricardo Garcia, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office (ACO), 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7331; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Emergency 

Canadian Airworthiness Directive CF– 

2013–11, dated April 17, 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 modifications on a CL– 

215–1A10 aeroplane, an operator discovered 

that the wing lower rear spar cap and 

reinforcing strap were fractured at Wing 

Stations (WS) 49.5 and 50 respectively and 

the rear spar web and wing lower skin were 

also cracked. It is suspected that a crack 

initiated at the wing lower spar cap, leading 

to its failure, the subsequent failure of the 

reinforcing strap and cracking of the spar 

web and wing lower skin. The damage was 

outside of the area addressed by the 

repetitive ultrasonic inspections required by 

AD CF–1992–26R2 [which corresponds to 

FAA AD 2012–11–04, Amendment 39–17067 

(77 FR 32892, June 4, 2012)] and was found 

95 hours air time after the last ultrasonic 

inspection. 

Failure and cracking of the above-noted 

wing structure, if not detected, could result 

in failure of the wing. In order to mitigate the 

unsafe condition, this [Canadian] AD 

mandates a repetitive [detailed] visual 

inspection [for cracking] of the wing lower 

skin until an eddy current inspection [for 

cracking] of the [LH and RH wing lower front 

and rear] spar cap[s] is performed or a 

[detailed] visual inspection [for cracking] of 

the wing structures [i.e., the LH and RH wing 

lower skin, front and rear spar caps, front and 

rear spar webs, and reinforcing straps] is 

performed by removing the fuel bladder[, and 

repair if any cracking is found during any 

inspection]. Transport Canada may mandate 

additional corrective actions pending the 

outcome of the failure investigation and fleet 

findings. The requirements of AD CF–1992– 

26R2 remain applicable. 

The terminating action is doing either a 

detailed inspection for cracking of the 

LH and RH wing lower skin, front and 

rear spar caps, front and rear spar webs, 


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32354 Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 

and reinforcing straps or an optional 

eddy-current inspection for cracking of 

the LH and RH wing lower front and 

rear spar caps and repair if necessary. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Alert 

Service Bulletin 215–A558, dated April 

5, 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 service information specifies to 

contact the manufacturer for 

instructions on how to repair certain 

conditions, but this AD requires 

repairing those conditions using a 

method approved by the FAA or TCCA 

(or its delegated agent). 

Interim Action 

We considered this AD interim action. 

The inspection reports that are required 

by this AD will enable us to obtain 

better insight into the nature, cause, and 

extent of the cracking, and eventually to 

develop final action to address the 

unsafe condition. Once final action has 

been identified, we might consider 

further rulemaking. 

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 because an operator discovered that 

the wing lower rear spar cap and 

reinforcing strap were fractured at WS 

49.5 and 50 respectively, and that the 

rear spar web and wing lower skin were 

also cracked. Failure and cracking of the 

wing structure, if not detected, could 

result in failure of the wing. 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–2013–0426; 

Directorate Identifier 2013–NM–084– 

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 5 

products of U.S. registry. We also 

estimate that it will take up to 20 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 $8,500, or $1,700 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: 

2013–11–03 Bombardier, Inc.: Amendment 

39–17463. Docket No. FAA–2013–0426; 

Directorate Identifier 2013–NM–084–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 14, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–215–1A10 airplanes, serial numbers (S/ 

Ns) 1001 through 1125 inclusive; and Model 

CL–215–6B11 (CL–215T Variant) airplanes, 

S/Ns 1056 through 1125 inclusive; 

certificated in any category. 


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Federal Register / Vol. 78, No. 104 / Thursday, May 30, 2013 / Rules and Regulations 32355 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57; Wings. 

(e) Reason 

This AD was prompted by reports of a 

fractured wing lower rear spar cap and 

reinforcing strap. We are issuing this AD to 

detect and correct cracked wing structure, 

which could result in failure of the wing. 

(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) Inspection and Repair 

Within 10 flight hours after the effective 

date of this AD, do a detailed inspection for 

cracking of the left-hand (LH) and right-hand 

(RH) wing lower skin between wing stations 

(WS) 45.00 and 51.00, in accordance with 

Part A of Bombardier Alert Service Bulletin 

215–A558, dated April 5, 2013. Repeat the 

inspection thereafter at intervals not to 

exceed 25 flight hours, until the inspection 

specified in paragraph (h)(1) or (h)(2) of this 

AD has been accomplished. If any cracking 

is found during the inspection required by 

paragraph (g) of this AD, before further flight, 

repair the crack using a method approved by 

the Manager, New York Aircraft Certification 

Office (ACO), FAA; or Transport Canada 

Civil Aviation (TCCA) (or its delegated 

agent). 

(h) Optional Terminating Actions 

(1) Accomplishing a one-time detailed 

inspection for cracking of the LH and RH 

wing lower skin, front and rear spar caps, 

front and rear spar webs, and reinforcing 

straps, in accordance with Part B of 

Bombardier Alert Service Bulletin 215–A558, 

dated April 5, 2013, terminates the actions 

required by paragraph (g) of this AD. If any 

cracking is found during the one-time 

detailed inspection, before further flight, 

repair the crack using a method approved by 

the Manager, New York ACO, FAA; or TCCA 

(or its delegated agent). 

(2) Accomplishing a one-time eddy current 

inspection for cracking of the LH and RH 

wing lower front and rear spar caps, in 

accordance with paragraph 3.B. and 

paragraphs 4. through 9. (Part C–1), and 

paragraphs 10. through 16. (Part C–2), of 

Bombardier Alert Service Bulletin 215–A558, 

dated April 5, 2013, terminates the actions 

required by paragraph (g) of this AD. If any 

cracking is found during the one-time eddy 

current inspection, before further flight, 

repair the crack using a method approved by 

the Manager, New York ACO, FAA; or TCCA 

(or its delegated agent). 

(i) Reporting Requirement 

Submit a report of the crack findings of the 

inspections specified in paragraphs (g), 

(h)(1), and (h)(2) of this AD to Bombardier 

Aerospace Specialized and Amphibious 

Aircraft Technical Support at email: 

mtl.saa.tech.support@aero.bombardier.com. 

Submit the report at the applicable time 

specified in paragraph (i)(1) or (i)(2) of this 

AD. The report must include the inspection 

results, a description of any discrepancies 

found, the airplane serial number, and the 

number of landings and flight hours on the 

airplane. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 14 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 14 days after the effective date of this 

AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York ACO, 

ANE–170, 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. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information Canadian 

Emergency Airworthiness Directive CF– 

2013–11, dated April 17, 2013; and 

Bombardier Alert Service Bulletin 215–A558, 

dated April 5, 2013; for related information. 

(l) 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) Bombardier Alert Service Bulletin 215– 

A558, dated April 5, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.com. 

(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 May 17, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–12615 Filed 5–29–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0793; Airspace 

Docket No. 12–ANE–14] 

Establishment of Class E Airspace; 

Bass Harbor, ME 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action establishes Class 

E Airspace at Bass Harbor, ME, to 

accommodate a new Area Navigation 

(RNAV) Global Positioning System 

(GPS) special Standard Instrument 

Approach Procedure (SIAP) serving 

Bass Harbor Heliport. This action 

enhances the safety and airspace 

management of Instrument Flight Rules 

(IFR) operations within the National 

Airspace System. Also, geographic 

coordinates are corrected under their 

proper heading. 

DATES: Effective 0901 UTC, August 22, 

2013. The Director of the Federal 


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