Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 40823 

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. 

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 airworthiness 

directive (AD): 

Pratt & Whitney Division: Docket No. FAA– 

2012–0546; Directorate Identifier 2012– 

NE–15–AD. 

(a) Comments Due Date 

We must receive comments by September 

10, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Pratt & Whitney 

PW4050, PW4052, PW4056, PW4060, 

PW4060A, PW4060C, PW4062, PW4062A, 

PW4152, PW4156, PW4156A, PW4158, 

PW4160, PW4460, PW4462, and PW4650 

turbofan engines, including models with any 

dash number suffix, with 3rd stage LPT duct 

segments P/N 50N095; 50N095–001; 50N235; 

50N235–001; 50N494–01; 50N494–001; 

50N495–01; or 50N495–001, installed. 

(d) Unsafe Condition 

This AD was prompted by 16 reports of 

damaged or failed 3rd stage low-pressure 

turbine (LPT) duct segments. We are issuing 

this AD to prevent failure of the 3rd stage 

LPT duct segments, which could lead to LPT 

rotor damage, uncontained engine failure, 

and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(f) 3rd Stage LPT Duct Segments Removal 

From Service 

At the next piece-part exposure after the 

effective date of this AD, remove from service 

3rd stage LPT duct segments, P/Ns 50N095; 

50N095–001; 50N235; 50N235–001; 50N494– 

01; 50N494–001; 50N495–01; and 50N495– 

001. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install into any engine any 3rd stage LPT 

duct segment, P/N 50N095; 50N095–001; 

50N235; 50N235–001; 50N494–01; 50N494– 

001; 50N495–01; or 50N495–001, that is at 

piece-part exposure. 

(h) Definition 

For the purpose of this AD, piece-part 

exposure is when the 3rd stage LPT duct 

segment is removed from the engine and 

completely disassembled. 

(i) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(j) Related Information 

(1) Pratt & Whitney Engine-Duct Segment, 

Third Stage LPT Assembly Service Bulletin 

(SB) No. PW4ENG 72–488, Revision 3, dated 

August 13, 2009. 

(2) For more information about this AD, 

contact James Gray, Aerospace Engineer, 

Engine & Propeller Directorate, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7742; fax: 781–238– 

7199; email: james.e.gray@faa.gov. 

(3) For service information identified in 

this AD, contact Pratt & Whitney, 400 Main 

St., East Hartford, CT 06108; phone: 860– 

565–8770; fax: 860–565–4503. You may 

review copies of the service information at 

the FAA, Engine & Propeller Directorate, 12 

New England Executive Park, Burlington, 

MA. For information on the availability of 

this material at the FAA, call 781–238–7125. 

Issued in Burlington, Massachusetts, on 

July 2, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–16857 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–2012–0150; Directorate 

Identifier 2011–NM–234–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all Airbus Model A318 series 

airplanes, Airbus Model A319 series 

airplanes, Airbus Model A320 series 

airplanes, and Airbus Model A321 

series airplanes. That NPRM proposed 

an inspection to determine if certain 

angle of attack (AOA) probes are 

installed, and replacing the affected 

AOA probe if necessary. That NPRM 

was prompted by reports of oil residue 

between the stator and the rotor parts of 

the position resolvers of the AOA vane, 

which was a result of incorrect removal 

of the machining oil during the 

manufacturing process of the AOA 

resolvers. This action revises that NPRM 

by including an inspection to determine 

if certain other AOA probes are 

installed, and replacing the affected 

probes. We are proposing this AD to 

prevent erroneous AOA information and 

consequent delayed or non-activation of 

the AOA protection systems which, 

during flight at a high angle of attack, 

could result in reduced control of the 

airplane. Since these actions impose an 

additional burden over that proposed in 

the NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this proposed AD by August 27, 2012. 


erowe on DSK2VPTVN1PROD with PROPOSALS-1
40824 Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 

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 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.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For 

Thales Avionics service information 

identified in this proposed 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. 

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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

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–2012–0150; Directorate Identifier 

2011–NM–234–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 

We proposed to amend 14 CFR part 

39 with an earlier NPRM for the 

specified products, which was 

published in the Federal Register on 

February 23, 2012 (77 FR 10693). That 

earlier NPRM proposed to require 

actions intended to address the unsafe 

condition for the products listed above. 

Since that NPRM (77 FR 10693, 

February 23, 2012) was issued, we have 

determined that certain other AOA 

probes need to be inspected in order to 

address the identified unsafe condition. 

Comments 

We gave the public the opportunity to 

comment on the previous NPRM (77 FR 

10693, February 23, 2012). The 

following presents the comments 

received on the previous NPRM and the 

FAA’s response to each comment. 

Request To Include Other AOA Probes 

Airbus stated that certain Thales AOA 

probes, part number (P/N) C16291AB, 

have been modified in accordance with 

Thales Avionics Service Bulletin 

C16291A–34–007, August 27, 2009, 

without incorporating Thales Avionics 

Service Bulletin C16291A–34–007, 

Revision 01, dated December 3, 2009. 

We infer that Airbus is requesting that 

we change the previous NPRM (77 FR 

10693, February 23, 2012) to include an 

inspection of those AOA probes. 

We agree with Airbus’ request. The 

AOA probes may have the same unsafe 

condition found in AOA probe P/N 

C16291AA. We have determined that 

those discrepant AOA probes, P/N 

C16291AB, must also be replaced. We 

have added new paragraph (g)(2) of this 

supplemental NPRM to address the 

identified unsafe condition on those 

AOA probes. 

Request To Refer to the Latest Service 

Information 

Airbus and United Airlines requested 

that the previous NPRM (77 FR 10693, 

February 23, 2012) reference Thales 

Avionics Service Bulletin C16291A–34– 

007, Revision 02, dated December 16, 

2011, as a means of compliance. 

We agree to refer to the latest revision 

of this service information. Thales 

Avionics has issued Service Bulletin 

C16291A–34–007, Revision 03, dated 

April 10, 2012. We have revised this 

supplemental NPRM accordingly. 

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. 

Certain changes described above 

expand the scope of the earlier NPRM 

(77 FR 10693, February 23, 2012). As a 

result, we have determined that it is 

necessary to reopen the comment period 

to provide additional opportunity for 

the public to comment on this proposed 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 755 products of U.S. 

registry. We also estimate that it would 

take about 2 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 

$128,350, or $170 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 3 work-hours and require parts 

costing $0, for a cost of $255 per 

product. 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. 


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Federal Register / Vol. 77, No. 133 / Wednesday, July 11, 2012 / Proposed Rules 40825 

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: 

Airbus: Docket No. FAA–2012–0150; 

Directorate Identifier 2011–NM–234–AD. 

(a) Comments Due Date 

We must receive comments by August 27, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 34: Navigation. 

(e) Reason 

This AD was prompted by reports of oil 

residue between the stator and the rotor parts 

of the position resolvers of the angle of attack 

(AOA) vane, which was a result of incorrect 

removal of the machining oil during the 

manufacturing process of the AOA resolvers. 

We are issuing this AD to prevent erroneous 

AOA information and consequent delayed or 

non-activation of the AOA protection 

systems which, during flight at a high angle 

of attack, could result in reduced control of 

the airplane. 

(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 

Within 12 months after the effective date 

of this AD, except as provided by paragraph 

(h) of this AD: Do the inspections in 

paragraphs (g)(1) and (g)(2) of this AD. 

(1) Inspect to determine the part number 

(P/N) and serial number of each Thales 

Avionics AOA probe, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, excluding 

Appendix 01, dated January 29, 2010. If any 

probe is found having P/N C16291AA and 

having a serial number listed in Thales 

Avionics Service Bulletin C16291A–34–007, 

Revision 03, dated April 10, 2012: Within 12 

months after the effective date of this AD, 

replace the AOA probe, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A320–34–1452, excluding 

Appendix 01, dated January 29, 2010. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number and serial number of the 

installed AOA probes can be conclusively 

determined from that review. 

(2) Inspect to determine the part number 

and serial number of each Thales Avionics 

AOA probe, in accordance with paragraph 

3.C.1.a. of the Accomplishment Instructions 

of Airbus Service Bulletin A320–34–1452, 

excluding Appendix 01, dated January 29, 

2010. If any probe is found having P/N 

C16291AB, on which Thales Avionics 

Service Bulletin C16291A–34–009, Revision 

1, dated January 7, 2010, has been 

incorporated, and on which Thales Avionics 

Service Bulletin C16291A–34–007, Revision 

01, dated December 3, 2009, has not been 

incorporated: Within 12 months after the 

effective date of this AD, replace the AOA 

probe, in accordance with a method 

approved by the Manager, International 

Branch, ANM–116, FAA, or EASA (or its 

delegated agent). A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number of the 

installed AOA probes can be conclusively 

determined from that review. 

(h) Exception 

For any airplane on which Airbus 

modification 150006 (installation of Thales 

Avionics AOA probes P/N C16291AB) or 

modification 26934 (installation of Goodrich 

AOA probes P/N 0861ED) has been embodied 

in production, and on which no AOA probe 

replacement has been made since first flight: 

The actions specified in paragraph (g) of this 

AD are not required. 

(i) Parts Installation Limitations 

(1) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AA, having a serial 

number listed in Thales Avionics Service 

Bulletin C16291A–34–007, Revision 03, 

dated April 10, 2012, on any airplane, unless 

that Thales Avionics probe has been 

inspected, re-identified and tested, in 

accordance with the Accomplishment 

Instructions of Thales Avionics Service 

Bulletin C16291A–34–007, Revision 03, 

dated April 10, 2012. 

(2) As of the effective date of this AD, no 

person may install a Thales Avionics AOA 

probe, P/N C16291AB, on which Thales 

Avionics Service Bulletin C16291A–34–009, 

dated September 10, 2009, has been 

incorporated, and on which Thales Avionics 

Service Bulletin C16291A–34–007, Revision 

01, dated December 3, 2009, has not been 

incorporated. 

(j) 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: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; 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. 


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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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