40826 Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 

(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 European Aviation 

Safety Agency Airworthiness Directive 2011– 

0203, dated October 13, 2011, and the service 

information specified in paragraphs (k)(1)(i) 

and (k)(1)(ii) of this AD, for related 

information. 

(i) Airbus Service Bulletin A320–34–1452, 

excluding Appendix 01, dated January 29, 

2010. 

(ii) Thales Avionics Service Bulletin 

C16291A–34–007, Revision 03, dated April 

10, 2012. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For Thales Avionics service 

information identified in this AD, contact 

Thales Avionics, Retrofit Manager, 105, 

Avenue du Ge ́ne ́ral Eisenhower, BP 63647, 

31036 Toulouse Cedex 1, France; telephone 

+33 5 61 19 76 95; fax +33 5 61 19 68 20; 

email retrofit.ata@fr.thalesgroup.com; 

Internet http://www.thalesgroup.com/ 

aerospace. You may review copies of the 

referenced 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. 

Issued in Renton, Washington, on July 5, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16970 Filed 7–10–12; 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] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt 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 proposed AD was 

prompted by a report that certain wingto-fuselage attachment nuts do not 

conform to the certification design 

requirements for dual locking features. 

This proposed AD would require 

repetitive inspections to determine that 

cotter pins are installed at affected 

wing-to-fuselage attachment joints and 

replacement if necessary. We are 

proposing this AD to prevent loss of 

wing-to-fuselage attachment joints, 

which could result in the loss of the 

wing. 

DATES: We must receive comments on 

this proposed AD by August 27, 2012. 

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. 

For service information identified in 

this proposed 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. You may 

review copies of the referenced 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. 

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 proposed 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 & 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0679; Directorate Identifier 

2012–NM–063–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 proposed AD. 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2012–10, 

dated March 12, 2012 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

The manufacturer has determined that 

wing-to-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 [TCCA] Airworthiness Directive (AD) 

mandates a [repetitive] detailed visual 

inspection (DVI) of each affected wing-tofuselage attachment joint to ensure that a 

cotter pin is installed. 

The required actions also include 

replacing any missing cotter pin. You 


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Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 40827 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Bombardier, Inc. has issued Service 

Bulletin 670BA–53–042, Revision A, 

dated April 27, 2012. 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 Proposed 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 proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 366 products of U.S. 

registry. We also estimate that it would 

take about 5 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on 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 proposed 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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: 

Bombardier, Inc.: Docket No. FAA–2012– 

0679; Directorate Identifier 2012–NM– 

063–AD. 

(a) Comments Due Date 

We must receive comments by August 27, 

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. 

(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 


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40828 Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 

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 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. You may review 

copies of the referenced 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. 

Issued in Renton, Washington, on June 29, 

2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–16960 Filed 7–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0680; Directorate 

Identifier 2011–NM–247–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model DC–10–10 

and MD–10–10F airplanes. This 

proposed AD was prompted by a report 

that the safe life limit on certain main 

landing gear (MLG) upper torque link 

bolts is reduced significantly due to 

incorrect fabrication. This proposed AD 

would require replacing certain MLG 

upper torque link bolts with a new or 

serviceable part. We are proposing this 

AD to prevent damage to the MLG and 

consequent damage to airplane 

structure, which could adversely affect 

the airplane’s continued safe flight and 

landing. 

DATES: We must receive comments on 

this proposed AD by August 27, 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: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced 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. 

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 proposed 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: 

Nenita Odesa, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: (562) 627–5234; 

fax: (562) 627–5210; email: 

nenita.odesa@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2012–0680; Directorate Identifier 2011– 

NM–247–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

We have received a report that the 

safe life limit on certain MLG upper 

torque link bolts is reduced significantly 

due to incorrect fabrication. This 

condition, if not corrected, could result 

in damage to the MLG and consequent 

damage to airplane structure, which 

could adversely affect the airplane’s 

continued safe flight and landing. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin DC10–32A260, dated 

September 30, 2011. The service 

information describes procedures for 

replacing certain MLG upper torque link 

bolts with a new or serviceable part. 

Explanation of Proposed Compliance 

Time 

Boeing Alert Service Bulletin DC10– 

32A260, dated September 30, 2011, 

specifies a compliance time of ‘‘before 

further flight or before 6,590 flight 

cycles from installation,’’ for replacing 

the MLG upper torque link bolt. This 

proposed AD would change the 

compliance time to ‘‘within 6,590 flight 

cycles from bolt installation or within 

180 days after the effective date of this 

AD, whichever occurs later.’’ We have 

determined that this compliance time 

would provide adequate time for the 

actions to be done without grounding 

airplanes. 

FAA’s Determination 

We are proposing 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. 


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