Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 67267 

Mandatory Service Bulletin A330–71–3025, 

excluding Appendices 01 and 02, dated 

January 10, 2011; and the Accomplishment 

Instructions of Rolls-Royce Service Bulletin 

RB.211–71–AG416, excluding Appendix 1, 

dated September 3, 2010. 

(1) If the findings of the inspection are 

within the allowable damage limits, as 

specified in the Accomplishment 

Instructions of Rolls-Royce Service Bulletin 

RB.211–71–AG416, excluding Appendix 1, 

dated September 3, 2010: Do the actions in 

paragraphs (i)(1)(i) and (i)(1)(ii) of this AD. 

(i) Repeat the inspection of the OBA and 

forward bulkhead thereafter at the repeat 

interval specified in Part 3.B. of the 

Accomplishment Instructions of Rolls-Royce 

Service Bulletin RB.211–71–AG416, 

excluding Appendix 1, dated September 3, 

2010. 

(ii) Repeat the inspections specified in 

paragraphs (g) and (h) of this AD thereafter 

at intervals not to exceed 2,500 flight cycles. 

(2) If the findings of the inspection are not 

within the allowable damage limits, as 

specified in the Accomplishment 

Instructions of Rolls-Royce Service Bulletin 

RB.211–71–AG416, excluding Appendix 1, 

dated September 3, 2010: Do the actions in 

paragraphs (i)(2)(i) or (i)(2)(ii) of this AD, as 

applicable. 

(i) If any OBA crack is 22 inches or greater, 

or any forward bulkhead crack is 13 inches 

or greater: Before further flight, replace the 

affected engine air intake cowl with a new or 

serviceable engine air intake cowl, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–71–3025, excluding 

Appendices 01 and 02, dated January 10, 

2011. 

(ii) If any OBA crack is 15 inches or 

greater, but less than 22 inches, or any 

forward bulkhead crack is 9 inches or greater, 

but less than 13 inches: Within 100 flight 

cycles, replace the affected engine air intake 

cowl with a new or serviceable engine air 

intake cowl, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–71–3025, 

excluding Appendices 01 and 02, dated 

January 10, 2011. 

(j) Repetitive Inspections for Replaced 

Engine Air Intake Cowls 

If any engine air intake cowl is replaced in 

accordance with the requirements of this AD 

with an engine air intake cowl that has less 

than 5,000 flight cycles since the engine air 

intake cowl was first installed on an airplane: 

Repeat the inspection required by paragraph 

(g) of this AD thereafter at the compliance 

time specified in paragraph (g)(1) of this AD. 

(1) If any engine air intake cowl is replaced 

in accordance with the requirements of this 

AD with an engine air intake cowl with 5,000 

flight cycles or more since the engine air 

intake cowl was first installed on an airplane: 

Repeat the inspections required by 

paragraphs (g) and (h) of this AD thereafter 

at intervals not to exceed 2,500 flight cycles. 

(2) If any engine air intake cowl is replaced 

in accordance with the requirements of this 

AD with an engine air intake cowl with 5,000 

flight cycles or more since the engine air 

intake cowl was first installed on an airplane: 

Repeat the inspections required by paragraph 

(i) of this AD thereafter at the intervals 

specified in the Accomplishment 

Instructions of Rolls-Royce Service Bulletin 

RB.211–71–AG416, excluding Appendix 1, 

dated September 3, 2010. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(l) Related Information 

Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2011–0062, 

dated April 4, 2011, and the service 

information specified in paragraphs (l)(1) and 

(l)(2) of this AD, for related information. 

(1) Airbus Mandatory Service Bulletin 

A330–71–3025, excluding Appendices 01 

and 02, dated January 10, 2011. 

(2) Rolls-Royce Service Bulletin RB.211– 

71–AG416, excluding Appendix 1, dated 

September 3, 2010. 

(m) 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) Airbus Mandatory Service Bulletin 

A330–71–3025, excluding Appendices 01 

and 02, dated January 10, 2011. 

(ii) Rolls-Royce Service Bulletin RB.211– 

71–AG416, excluding Appendix 1, dated 

September 3, 2010. 

(3) For Airbus service information 

identified in this AD, contact Airbus SAS— 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. 

(4) For Rolls-Royce service information 

identified in this AD, contact Rolls-Royce 

Plc, Technical Publications, P.O. Box 31, 

Derby, DE24 8BJ, United Kingdom; telephone 

44 (0) 1332 245882; fax 44 (0) 1332 249936; 

Internet http://www.Rolls-Royce.com. 

(5) 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. 

(6) 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 October 

26, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26892 Filed 11–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0679; Directorate 

Identifier 2012–NM–063–AD; Amendment 

39–17246; AD 2012–22–10] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, Model CL–600–2D15 

(Regional Jet Series 705) airplanes, 

Model CL–600–2D24 (Regional Jet 

Series 900) airplanes, and Model CL– 

600–2E25 (Regional Jet Series 1000) 

airplanes. This AD was prompted by a 

report that certain wing-to-fuselage 

attachment nuts do not conform to the 

certification design requirements for 

dual locking features. This AD requires 

repetitive inspections to determine that 

cotter pins are installed at affected 

wing-to-fuselage attachment joints and 

replacement if necessary. We are issuing 

this AD to prevent loss of wing-tofuselage attachment joints, which could 

result in the loss of the wing. 


wreier-aviles on DSK5TPTVN1PROD with 
67268 Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 

DATES: This AD becomes effective 

December 14, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 14, 2012. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey Zimmer, Aerospace Engineer, 

Airframe & Mechanical Systems Branch, 

ANE–171, New York Aircraft 

Certification Office (ACO), FAA, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7306; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on July 11, 2012 (77 FR 40826). 

That NPRM proposed to correct an 

unsafe condition for the specified 

products. The Mandatory Continuing 

Airworthiness Information (MCAI) 

states: 

The manufacturer has determined that wingto-fuselage attachment nuts, part number (P/ 

N) SH670–35635–1, SH670–35440–951, 

SH670–35440–3, SH670–35635–1 and 

95136D–2412, installed at six attachment 

joint locations, do not conform to the 

certification design requirements for dual 

locking features. The nuts are not of the selflocking type as required and do not provide 

the frictional thread interference required to 

prevent the nut from backing off the bolt. As 

a result, only a single locking device, the 

cotter pin, is provided at these critical joints. 

In the case where a nut becomes loose, in 

combination with a missing or broken cotter 

pin, the attachment bolt at the wing-tofuselage joint could migrate and fall out. Loss 

of two attachment joints could potentially 

result in the loss of the wing. 

This [Transport Canada Civil Aviation] 

Airworthiness Directive (AD) mandates a 

[repetitive] detailed visual inspection (DVI) 

of each affected wing-to-fuselage attachment 

joint to ensure that a cotter pin is installed. 

The required actions also include 

replacing any missing cotter pin. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

Request for Credit for Previous Actions 

Mesa Airlines requested that 

paragraph (i) of the NPRM (77 FR 40826, 

July 11, 2012), regarding credit for the 

previous actions, be revised to include 

credit for Bombardier Maintenance 

Review Board Report 57–10–305, Task 

000–53–170–501, Detailed Inspection of 

the Wing-to-Fuselage Attachment 

Fittings—FS708.00, FS752.00, and 

FS797.00 at LBL45.0 and RBL45.0, as 

compliance for the initial inspection 

specified in paragraph (g) of the NPRM. 

We disagree with the request to give 

credit for the initial inspection by 

accomplishing the task specified by the 

commenter. The intent of this AD is to 

ensure cotter pin installation, and while 

Task 000–53–170–501 inspects for 

corrosion and general condition of the 

wing attachment fittings, it does not 

specify inspecting the cotter pins. 

Therefore, the cotter pins could be 

missed during the inspection in Task 

000–53–170–501. We have not changed 

the AD in this regard. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

40826, July 11, 2012) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 40826, 

July 11, 2012). 

Costs of Compliance 

We estimate that this AD will affect 

366 products of U.S. registry. We also 

estimate that it will take about 5 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 $155,550, or $425 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. We have no way 

of determining the number of products 

that may need these actions. 

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. 

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 the NPRM (77 FR 40826, July 

11, 2012), 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. 

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, 


wreier-aviles on DSK5TPTVN1PROD with 
Federal Register / Vol. 77, No. 218 / Friday, November 9, 2012 / Rules and Regulations 67269 

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: 

2012–22–10 Bombardier, Inc.: Amendment 

39–17246. Docket No. FAA–2012–0679; 

Directorate Identifier 2012–NM–063–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective December 14, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Bombardier, Inc. Model 

CL–600–2C10 (Regional Jet Series 700, 701, 

& 702) airplanes, serial numbers 10002 

through 10999 inclusive; Model CL–600– 

2D15 (Regional Jet Series 705) and CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15001 through 15990 

inclusive; and Model CL–600–2E25 (Regional 

Jet Series 1000) airplanes, serial numbers 

19001 through 19990 inclusive; certificated 

in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report that 

certain wing-to-fuselage attachment nuts do 

not conform to the certification design 

requirements for dual locking features. We 

are issuing this AD to prevent loss of wingto-fuselage attachment joints, which could 

result in the loss 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) Repetitive Detailed Inspection 

Within 3,000 flight hours or 18 months 

after the effective date of this AD, whichever 

occurs first: Perform a detailed inspection of 

each affected wing-to-fuselage attachment 

joint, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–53–042, Revision A, 

dated April 27, 2012. Repeat the inspection 

thereafter at intervals not to exceed 6,600 

flight hours. 

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

compliance time in this AD differs from the 

recommended compliance time specified in 

Bombardier Service Bulletin 670BA–53–042, 

Revision A, dated April 27, 2012. 

(h) Corrective Action 

If any cotter pin is found missing during 

any inspection required by paragraph (g) of 

this AD: Before further flight, replace any 

missing cotter pin using a method approved 

by either the Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA; 

or Transport Canada Civil Aviation (or its 

delegated agent). 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 670BA–53–042, dated 

December 21, 2011, which is not 

incorporated by reference in 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 manager of the ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

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. 

(k) Related Information 

(1) Refer to MCAI Canadian Airworthiness 

Directive CF–2012–10, dated March 12, 2012; 

and Bombardier Service Bulletin 670BA–53– 

042, Revision A, dated April 27, 2012; for 

related information. 

(2) For Bombardier service information 

identified in this AD, contact Bombardier, 

Inc., 400 Coˆte-Vertu 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. 

(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 Service Bulletin 670BA–53– 

042, Revision A, dated April 27, 2012. 

(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 October 

24, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–26961 Filed 11–8–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 400 

[Docket No. FAA–2012–0318; Amdt. No. 

400–4] 

RIN 2120–AK16 

Voluntary Licensing of Amateur 

Rocket Operations; Withdrawal 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Direct Final rule, withdrawal. 

SUMMARY: The FAA is withdrawing a 

previously published direct final rule 

that would have allowed launch 

operators that conduct certain amateur 

rocket launches to voluntarily apply for 

a commercial space transportation 

license or experimental permit. The 

FAA is withdrawing this action because 

of the adverse comments it received. 

DATES: The direct final rule published 

on August 22, 2012, at 77 FR 50584 is 

withdrawn, effective November 8, 2012. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact Shirley McBride, Senior 

Transportation Industry Analyst, Office 

of Commercial Space Transportation, 

Regulations and Analysis Division, 

Federal Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone (202) 

267–7470; facsimile (202) 267–5463; 


wreier-aviles on DSK5TPTVN1PROD with