### 49394 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules

Issued in Kansas City, Missouri, on August 9, 2012. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–20107 Filed 8–15–12; 8:45 am]

**BILLING CODE 4910–13–C**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0806; Directorate Identifier 2012–NM–022–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, –401, and –402 airplanes. This proposedAD was prompted by reports of an inservice incident where the propeller deicing system became unavailable due to burnt/chafed wires within the alternating current contractor box (ACCB). This proposed AD would require inspection for chafing, damage, and loose wiring within an ACCB and repair if necessary; and would require rework and re-identification of the wiring installation within each ACCB. We are proposing this AD to detect and correct damaged, chafed, or loose wiring within an ACCB, which could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pilot probe heater, engine intake heater, or propeller de-icing system, and subsequently adversely affect the airplane’s flight characteristics in icing conditions.

**DATES :**  We must receive comments on this proposed AD by October 1, 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, 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 :**  Assata Dessaline, Aerospace Engineer, Avionics and Flight Test Branch, ANE– 172, FAA, New York Aircraft Certification Office (ACO), 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone (516) 228–7301; 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–2012–0806; Directorate Identifier 2012–NM–022–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–2012–03, dated January 11, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states:

There has been one (1) reported in-service incident where the propeller de-icing system became unavailable due to burnt/chafed wires within the Alternating Current Contactor Box (ACCB). There has also been a number of additional minor events of wires found chafed within ACCBs.

An investigation revealed that inadequate clearance between the wires and metallic structure within the ACCB could cause chafed wires.

Damaged, chafed or loose wiring within an ACCB could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pitot probe heater, engine intake heater or propeller de-icing system. Loss of one of these systems could adversely affect the aeroplane’s flight characteristics in icing conditions.

This [TCCA] Airworthiness Directive (AD) mandates the [visual] inspection [for damaged, chafed, and loose wiring within an ACCB and replace if necessary] and rectification [rework] of the wiring installation within each ACCB.

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

Relevant Service Information

Bombardier, Inc. has issued the following service bulletins:

• Bombardier Service Bulletin 84–24– 47, Revision A, dated September 14,
2011.

• Bombardier Service Bulletin 84–24– 48, Revision A, dated September 14,
2011.

• Bombardier Service Bulletin 84–24– 49, Revision A, dated September 14,
2011.

• Bombardier Service Bulletin 84–24– 50, Revision A, dated September 14,
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


### 49395 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules

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 83 products of U.S. registry. We also estimate that it would take about 7 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 $49,385, or $595 per product.

In addition, we estimate that any necessary follow-on actions would take about 2 work-hours and require parts costing $0, for a cost of $170 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.

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– 0806; Directorate Identifier 2012–NM– 022–AD.
(a) Comments Due Date

We must receive comments by October 1,
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 and subsequent.
(d) Subject

Air Transport Association (ATA) of America Code 24: Electrical Power.

(e) Reason

This AD was prompted by reports of an inservice incident where the propeller de-icing system became unavailable due to burnt/ chafed wires within the alternating current contractor box (ACCB) due to inadequate clearance. We are issuing this AD to detect and correct damaged, chafed, or loose wiring within an ACCB, which could affect the operation of the windshield heater, ice detector, angle of attack (AOA) vane heater, pilot probe heater, engine intake heater, or propeller de-icing system, and subsequently adversely affect the airplane’s flight characteristics in icing conditions.
(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

For serial numbers 4001 through 4354 and 4356 through 4366: Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first: Do a general visual inspection for chafing, damage, and insulation damage, and rework the wiring within the ACCB, in accordance with the Accomplishment Instructions in the applicable Bombardier service bulletins specified in paragraphs (g)(1) through (g)(4) of this AD. If any chafing, damage, or insulation damage is found, before further flight, replace the damaged wiring, in accordance with the Accomplishment Instructions of the applicable Bombardier service bulletins specified in paragraphs (g)(1) through (g)(4) of this AD.

(1) Bombardier Service Bulletin 84–24–47, Revision A, dated September 14, 2011.

(2) Bombardier Service Bulletin 84–24–48, Revision A, dated September 14, 2011.

(3) Bombardier Service Bulletin 84–24–49, Revision A, dated September 14, 2011.

(4) Bombardier Service Bulletin 84–24–50, Revision A, dated September 14, 2011.
(h) Parts Installation Prohibition

As of the effective date of this AD, no person may install an ACCB having the combination of part numbers (P/N) and series specified in paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of this AD on any airplane.

(1) P/N 1152130–6, series 1, 2, and 4. (2) P/N 1152148–6, series 1, 2, 4, and 5. (3) P/N 1152090–6, series 1, 2, and 4. (4) P/N 1152124–6, series 1, 2, 4, and 5.
(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 the applicable service bulletins specified in paragraphs (i)(1) through (i)(4) of this AD.

(1) Bombardier Service Bulletin 84–24–47, dated April 26, 2011.

(2) Bombardier Service Bulletin 84–24–48, dated April 26, 2011.

(3) Bombardier Service Bulletin 84–24–49, dated April 26, 2011.

(4) Bombardier Service Bulletin 84–24–50, dated April 26, 2011.
(j) 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, New York 11590; telephone 516–228–7300; fax 516– 794–5531. Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager


### 49396 Federal Register / Vol. 77, No. 159 / Thursday, August 16, 2012 / Proposed Rules

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–2012–03, dated January 11, 2012, and the service information specified in paragraphs (k)(1)(i) through (k)(1)(iv) of this AD, for related information.

(i) Bombardier Service Bulletin 84–24–47, Revision A, dated September 14, 2011.

(ii) Bombardier Service Bulletin 84–24–48, Revision A, dated September 14, 2011.

(iii) Bombardier Service Bulletin 84–24–49, Revision A, dated September 14, 2011.

(iv) Bombardier Service Bulletin 84–24–50, Revision A, dated September 14, 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; 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 August 3, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–20110 Filed 8–15–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0809; Directorate Identifier 2011–NM–135–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 supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 757 airplanes equipped with Rolls-Royce RB211–535E engines. The existing AD currently requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. The existing AD also provides for an optional terminating modification for the repetitive inspections. Since we issued the existing AD, we have received reports of incorrectly installed washers under the attachment bolts of the aft hinge fittings of the thrust reversers. For certain airplanes, this proposed AD would add a one-time inspection of the washers installed under the attachment bolts of the aft hinge fittings for correct installation sequence, and reinstallation if necessary. This proposed AD also adds an option for installing a redesigned aft hinge fitting with the trim already done, instead of trimming an existing or new hinge fitting, which is included in the existing optional terminating modification. We are proposing this AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could result in structural damage to the airplane.

**DATES :**  We must receive comments on this proposed AD by October 1, 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, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124– 2207; telephone 206–544–5000, extension 1; fax 206–766–5680; 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, 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 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 :**  Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: 425– 917–6440; fax: 425–917–6590; email: nancy.marsh@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–2012–0809; Directorate Identifier 2011–NM–135–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 June 8, 2008, we issued AD 2008– 13–20, Amendment 39–15583 (73 FR 37786, July 2, 2008), for certain Model757 airplanes equipped with RollsRoyce RB211–535E engines. That AD requires repetitive inspections for signs of damage of the aft hinge fittings and attachment bolts of the thrust reversers, and related investigative and corrective actions if necessary. That AD also provides for an optional terminating modification for the repetitive inspections. That AD resulted from reports of several incidents of bolt failure at the aft hinge fittings of the thrust reversers due to, among other things, high operational loads. We issued that AD to prevent failure of the attachment bolts and consequent separation of a thrust reverser from the airplane during flight, which could