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

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.


### 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.


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

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.


### 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 wasprompted 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 Co ˆ te-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 duallocking 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 cotterpin, 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 visualinspection (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