### 60060 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1003; Directorate Identifier 2012–NM–064–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 DHC–8–400 series airplanes. This proposed AD was prompted by reports of engine fire/ overheat detector assemblies advance pneumatic detectors (APDs) failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. This proposed AD would require replacing all three APDs with new detector assemblies. We are proposing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and may influence the pilot to conduct a potentially hazardous ‘‘off-airport’’ landing.

**DATES :**  We must receive comments on this proposed AD by November 16,
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., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375– 4000; fax 416–375–4539; email thd.qseries@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 :**  Mazdak Hobbi, Aerospace Engineer, Propulsion and Services Branch, ANE– 173, FAA, New York Aircraft Certification Office, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7330; 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–2012–1003; Directorate Identifier 2012–NM–064–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–2012–07, dated January 27, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

There have been engine fires on DHC–8 Series 400 aeroplanes, where the ‘‘ENGINE FIRE, CHECK FIRE DETECT’’ warning and ‘‘FUEL OFF’’ handle lights failed to reset and remained illuminated after the fire was extinguished. An investigation has revealed that the existing engine fire/overheat detector assemblies ‘‘Advance Pneumatic Detectors (APD)’’ may fail to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures.

This abnormal condition of a continued engine fire indication in the cockpit, after the actual fire has been extinguished, is misleading and may influence the pilot’s decision to conduct a potentially hazardous ‘‘off-airport’’ landing, which is considered an unsafe condition that warrants mitigating action.

To mitigate this potentially hazardous condition, Bombardier has issued multiple service bulletins (SBs) [Bombardier Service Bulletins 84–26–08, Revision A, dated May 12, 2011; 84–26–09, Revision A, dated May 12, 2011; and 84–26–12, Revision A, dated December 13, 2011] to replace all three affected APDs with new detector assemblies that are not susceptible to the subject diaphragm deformation when exposed to excessive heat. * * *

You may obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

Bombardier, Inc. has issued Service Bulletins 84–26–08, Revision A, dated May 12, 2011; 84–26–09, Revision A, dated May 12, 2011; and 84–26–12, Revision A, dated December 13, 2011. 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 84 products of U.S. registry. We also estimate that it would take about 63 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $5,700 per product. Where the service information lists required parts costs that are covered under warranty, we have assumed that there will be no charge for


### 60061 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules

these parts. As we do not control warranty coverage for affected parties, some parties may incur costs higher than estimated here. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $928,620, or $11,055 per product. 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– 1003; Directorate Identifier 2012–NM– 064–AD.
(a) Comments Due Date

We must receive comments by November 16, 2012.
(b) Affected ADs

None. (c) Applicability

This AD applies to Bombardier, Inc. Model DHC–8–400, –401, and –402 airplanes; certificated in any category; serial numbers 4001 through 4373 inclusive.
(d) Subject

Air Transport Association (ATA) of America Code 26, Fire protection.
(e) Reason

This AD was prompted by reports of engine fire/overheat detector assemblies advance pneumatic detectors (APDs) failing to reset after activation due to permanent deformation of the detector switch diaphragm after being exposed to high temperatures. We are issuing this AD to prevent a continued engine fire indication in the cockpit after the actual fire has been extinguished, which is misleading and may influence the pilot to conduct a potentially hazardous ‘‘off-airport’’ landing.
(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) Installation

Within 6,000 flight hours or 30 months after the effective date of this AD, whichever occurs first, replace the APDs as specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD.

(1) For the nacelle of the engine primary zone: Remove any APD having part number (P/N) 10–1098 and install a new APD having P/N 10–1098–01, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–08, Revision A, dated May 12, 2011.

(2) For the nacelle of the landing gear primary zone: Remove any APD having P/N 10–1097 or 10–1097–01 and install a new APD having P/N 10–1097–02, in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011. (3) For the propeller engine controller: Remove any APD having P/N 10–1096, 10– 1096–01, or 10–1096–02 (serial number is all numeric characters), and install a new APD having P/N 10–1096–02 (serial number is three alpha and four numeric characters), in accordance with the Accomplishment Instructions of Bombardier Service Bulletin 84–26–12, Revision A, dated December 13,
2011.
(h) Credit for Previous Actions

This paragraph provides credit for actions required by paragraph (g) of this AD, if those actions were performed before the effective date of this AD using the service information specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD.

(1) Bombardier Service Bulletin 84–26–08, dated March 11, 2011.

(2) Bombardier Service Bulletin 84–26–09, dated March 11, 2011.

(3) Bombardier Service Bulletin 84–26–12, dated October 12, 2011.
(i) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office (ACO), ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, NY 11590; telephone 516–228–7300; fax 516–794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.
(j) Related Information

(1) Refer to MCAI Transport Canada Civil Aviation Airworthiness Directive CF–2012– 07, dated January 27, 2012; and the service bulletins identified in paragraphs (j)(1)(i), (j)(1)(ii), and (j)(1)(iii) of this AD; for related information.

(i) Bombardier Service Bulletin 84–26–08, Revision A, dated May 12, 2011.

(ii) Bombardier Service Bulletin 84–26–09, Revision A, dated May 12, 2011.

(iii) Bombardier Service Bulletin 84–26–12, Revision A, dated December 13, 2011.

(2) For service information identified in this AD, contact Bombardier, Inc., Q-Series Technical Help Desk, 123 Garratt Boulevard, Toronto, Ontario M3K 1Y5, Canada; telephone 416–375–4000; fax 416–375–4539;


### 60062 Federal Register / Vol. 77, No. 191 / Tuesday, October 2, 2012 / Proposed Rules

email thd.qseries@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 September 21, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–24174 Filed 10–1–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1052; Directorate Identifier 2012–CE–014–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Cessna Aircraft Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede an existing airworthiness directive (AD) that applies to certain Cessna Aircraft Company (Cessna) Models 172R, 172S, 182S, 182T, T182T, 206H, and T206H airplanes. The existing AD currently requires an inspection of the engine oil pressure switch and, if applicable, replacement of the engine oil pressure switch. Since we issued that AD, we have received new reports of internal failure of the engine oil pressure switch, which could result in complete loss of engine oil with consequent partial or complete loss of engine power or fire. This proposed AD would increase theapplicability of the AD and place a lifelimit of 3,000 hours time-in-service on the engine oil pressure switch, requiring replacement when the engine oil pressure switch reaches its life limit. We are proposing this AD to correct the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by November 16,
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 Cessna Aircraft Company, Product Support, P.O. Box 7706, Wichita, Kansas 67277; telephone: (316) 517–5800; fax (316) 942–9006; Internet: www.cessna.com/customer-service/technicalpublications.html. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148. 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 :**  Jeff Janusz, Sr. Propulsion Engineer, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Wichita, KS 67209; phone: (316) 946–4148; fax: (316) 946– 4107; email: jeff.janusz@faa.gov.

**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–2012–1052; Directorate Identifier 2012–CE–014–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 On February 11, 2000, we issued AD 2000–04–01, amendment 39–11583 (65 FR 8649, February 22, 2000), for certain Cessna Aircraft Company Models 172R, 172S, 182S, 206H, and T206H airplanes. That AD requires inspection of the engine oil pressure switch to determineif the engine oil pressure switch is partnumber (P/N) 77041 or P/N 83278 and replacement of any P/N 77041 engine oil pressure switch with a P/N 83278 engine oil pressure switch. That AD resulted from reports of failure of the engine oil pressure switch diaphragm. We issued that AD to prevent loss of engine oil through the failure of the engine oil pressure switch diaphragm, which could result in partial or complete loss of engine power. Actions Since Existing AD Was Issued

Since we issued AD 2000–04–01, amendment 39–11583 (65 FR 8649, February 22, 2000), we have received new reports of internal failure of the engine oil pressure switch, which could result in complete loss of engine oil with consequent partial or complete loss of engine power or fire.

Relevant Service Information

We reviewed Cessna Service Bulletin 07–79–01, dated January 29, 2007. The service information describes procedures for replacement of the engine oil pressure switch.

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 these same type designs. Proposed AD Requirements

This proposed AD would retain none of the requirements of AD 2000–04–01, amendment 39–11583 (65 FR 8649, February 22, 2000). This proposed AD would increase the applicability statement of the existing AD and require an inspection of the engine oil pressure switch with replacement of the engine oil pressure switch when it reaches its life limit of 3,000 hours time-in-service. We are proposing this AD to correct the unsafe condition on these products. Differences Between the Proposed AD and the Service Information

Applicability in this proposed AD has been expanded to include additional airplane serial numbers. Costs of Compliance

We estimate that this proposed AD affects 6,155 airplanes of U.S. registry.