### 66205 Federal Register / Vol. 76, No. 207 / Wednesday, October 26, 2011 / Proposed Rules

Subject

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

Reason

(e) The mandatory continuing airworthiness information (MCAI) states: During pre-delivery inspections and test flights, several short circuit events were reported, one of which resulted in smoke in the cockpit. There were no in-service incidents. Investigations have identified three conditions affecting the wiring of Circuit Breaker Panels * * * and Junction Boxes * * *, which would lead to short circuiting:

If not corrected, these conditions could result in arcing, damage to adjacent structure, smoke in the cockpit, or loss of system redundancies.

Compliance

(f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.

Inspections, Bus Bar Actions, and Corrective
Actions

(g) For airplanes having serial numbers 5701 through 5752, 5754 through 5775, 5777, 5780 through 5781, 5783 through 5790, 5792, 5794 through 5796, 5798, 5801, and 5804: Within 800 flight hours after the effective date of this AD, do the actions in paragraph (g)(1), (g)(2), and (g)(3) of this AD, in accordance with the Accomplishment Instructions of the Bombardier Service Bulletin 605–24–004, dated January 18, 2010.

(1) Do a detailed inspection in CBP–1 for loose lugs and for crimped lugs that have any of the conditions specified in step 2.B.(9)(d) of Bombardier Service Bulletin 605–24–004, dated January 18, 2010. Before further flight, replace all loose lugs and all crimped lugs in CBP–1 that have any of the conditions specified in step 2.B.(9)(d) of Bombardier Service Bulletin 605–24–004, dated January
18, 2010.

(2) Relocate or replace the CBP–1 bus bars as applicable.

(3) Do a general visual inspection for foreign object damage (FOD). If any FOD is found: Before further flight, remove the FOD.

(h) For airplanes having serial numbers 5701 through 5752, 5754 through 5756, 5758 through 5775, 5779, 5781, 5788, 5789, 5792, 5795, 5798, 5801, and 5804: Within 800 flight hours after the effective date of this AD, do the actions in paragraph (h)(1) and (h)(2) of this AD, in accordance with the Accomplishment Instructions of the Bombardier Service Bulletin 605–24–002, dated December 7, 2009.

(1) Do a detailed inspection for loose lugs and for crimped lugs that have any of the conditions specified in step 2.B.(2)(d) of Bombardier Service Bulletin 605–24–002, dated December 7, 2009, in CBP–2, CBP–3, CBP–4, JB17, and JB18. Before further flight, replace all loose lugs and all crimped lugs that have any of the conditions specified in step 2.B.(2)(d) of Bombardier Service Bulletin 605–24–002, dated December 7, 2009, in CBP–2, CBP–3, CBP–4, JB17, and JB18. (2) Do a general visual inspection for FOD. If any FOD is found: Before further flight,
remove the FOD.

FAA AD Differences

Note 1: This AD differs from the MCAI
and/or service information as follows: The Accomplishment Instructions of Bombardier Service Bulletin 605–24–002, dated December 7, 2009, does not specify corrective action for the general visual inspection for FOD. This AD requires removing any FOD discovered during the general visual inspection.

Other FAA AD Provisions

(i) The following provisions also apply to
this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to ATTN: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 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.

Related Information

(j) Refer to MCAI Canadian Airworthiness Directive CF–2010–25, dated August 3, 2010;
and Bombardier Service Bulletin 605–24– 002, dated December 07, 2009; and Bombardier Service Bulletin 605–24–004, dated January 18, 2010; for related
information.

Issued in Renton, Washington, on October

17, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2011–27653 Filed 10–25–11; 8:45 am]

**BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION** 

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0517; Directorate Identifier 2009–SW–73–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Sikorsky Aircraft Corporation Model S–76A**  **Helicopters**

**AGENCY :**  Federal Aviation Administration, DOT.

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

**SUMMARY :**  This document proposes adopting a new airworthiness directive (AD) for the Sikorsky Aircraft Corporation (Sikorsky) Model S–76A helicopters. This proposal would require modifying the electric rotor brake (ERB). Thereafter, the AD would also require inserting changes to the ‘‘Normal Procedures’’ and ‘‘Emergency Procedures’’ sections of the Rotorcraft Flight Manual (RFM), which revises the information of the basic RFM when the ERB is installed. This proposal is prompted by a reported incident of a fire occurring in an ERB installed on a Model S–76A helicopter. The actions specified by this proposed AD are intended to prevent overheating of the ERB assembly, ignition of the ERB hydraulic fluid, a fire in the main gearbox area, and subsequent loss of control of the helicopter.

**DATES :**  Comments must be received on or before December 27, 2011.

**ADDRESSES :**  Use one of the following addresses to submit comments on this proposed AD:

• 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

You may get the service information identified in this proposed AD from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, e-mail address:


### 66206 Federal Register / Vol. 76, No. 207 / Wednesday, October 26, 2011 / Proposed Rules

tsslibrary@sikorsky.com, or at http:// www.sikorsky.com.

**FOR FURTHER INFORMATION CONTACT :**  Caspar Wang, Aviation Safety Engineer, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7799, fax (781) 238–7170.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption

**ADDRESSES** . Include the docket number ‘‘FAA–2010–0517, Directorate Identifier 2009–SW–73–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed rulemaking. Using the search function of our docket Web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78).
Examining the Docket

You may examine the docket that contains the proposed AD, any comments, and other information 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 Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

Discussion

A number of service documents and ADs have been issued relating to the ERB on these and similar model helicopters. AD 82–17–03, issued July 30, 1982 (47 FR 35469, August 16, 1982), requires a puck-to-disc inspection of rotor brake, part number (P/N) 76363–09101–101, and modification of the ERB system including, among other modifications, installation of a warning relay by following Sikorsky Customer Service Bulletin No. 76–66–10B, dated November 25, 1981. AD 2003–04–15, issued February 14, 2003 (68 FR 8994, February 27, 2003), requires inspecting certain rotor brake discs for cracks that resulted from improper heat treating of the disc. This document proposes adopting a new AD for the Sikorsky Model S–76A helicopters with a different part-numbered ERB. This proposal would require, within 120 days, modifying the ERB by installing and operationally testing the parts contained in an ERB warning relay kit (P/N 76070–55023–011), an ERB circuit modification kit (P/N 76070–55033– 012), and an ERB modification kit (P/N 76070–55207–011) for helicopters with ERB, P/N 76363–09100–012. This proposal is prompted by a reported incident of a fire occurring in an ERB installed on a Model S–76A helicopter in Brazil. The actions specified by this proposed AD are intended to prevent overheating of the ERB assembly, ignition of the ERB hydraulic fluid, a fire in the main gearbox area, and subsequent loss of control of the helicopter.

We have reviewed the following documents from Sikorsky:

• Customer Service Bulletin No. 76– 66–10B, Revision 1, pages 2–8, dated July 30, 1981, and Revision 2, pages 1 and 9–13 dated November 25, 1981 (CSB), specifies installing an ERB warning relay kit;

• Customer Service Notice 76–113, dated June 1, 1983 (CSN), which specifies installing an ERB circuit breaker and modification kit; and

• ASB No. 76–66–48B, Revision B, dated July 8, 2009, which specifies a one-time installation of an ERB modification kit containing two other kits and several modifications.

• RFM Supplement No. 41, dated September 6, 2005, which revises the information in the basic RFM normal and emergency procedures sections when the ERB system is modified.

This unsafe condition is likely to exist or develop on other helicopters of the same type design. Therefore, the proposed AD would require modifying the ERB by installing the parts contained in a warning relay system modification kit, part number (P/N) 76070–55023–011; a circuit modification kit, P/N 76070–55033–012; and a manifold, relay box, junction box, right-hand relay panel, and wiring harness modification kit, P/N 76070– 55207–011. The proposed AD would also require operationally testing the ERB system after each modification. The proposed AD would also require inserting changes contained in a supplement into the RFM.

These actions would be required to be accomplished in accordance with specified portions of the service information described previously.

We estimate that this proposed AD would affect 180 helicopters of U.S. registry. It would take about 38 work hours per helicopter to perform the modifications and operational tests at an average labor rate of $85 per work hour. Required parts would cost $13,300 per helicopter. Based on these figures, we estimate the total cost impact of the proposed AD on U.S. operators would be $2,975,400 for the fleet.
Regulatory Findings

We have determined that this proposed AD would not have federalism implications under Executive Order 13132. Additionally, 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 that the 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); and

3. 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 draft economic evaluation of the estimated costs to comply with this proposed AD. See the AD docket to examine the draft economic evaluation.
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


### 66207 Federal Register / Vol. 76, No. 207 / Wednesday, October 26, 2011 / Proposed Rules

because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
The Proposed Amendment

Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend part 39 of the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive (AD) to read as follows:
Sikorsky Aircraft Corporation: Docket No. FAA–2010–0517; Directorate Identifier
2009–SW–73–AD. Applicability: Model S–76A helicopters, with an electric rotor brake (ERB), part number (P/N) 76363–09100–012, installed, certificated in any category.

Compliance: Required as indicated, unless accomplished previously.

To prevent overheating of the ERB assembly, ignition of the ERB hydraulic fluid, fire in the main gearbox area, and subsequent loss of control of the helicopter, do the following:

(a) Within 120 days, modify the ERB by installing:

(1) Warning relay system parts contained in modification kit, part number (P/N) 76070–55023–011, and operationally testing the ERB system in accordance with paragraphs 2.A. through 2.F., of Sikorsky Customer Service Bulletin No. 76–66–10B, Revision 1 (pages 2 through 8), dated July 30, 1981, and Revision 2, (pages 1 and 9 through 13) dated November 25, 1981;

(2) Circuit breaker and diodes contained in ERB circuit modification kit, P/N 76070– 55033–012, and operationally testing the ERB system in accordance with paragraph B. through F. of Sikorsky Customer Service Notice 76–113, dated June 1, 1983; and

(3) Manifold, relay box, junction box, righthand relay panel, and wiring harness parts contained in ERB modification kit, P/N 76070–55207–011, and operationally testing the ERB system in accordance with paragraphs 3.B. through 3.I. of the Accomplishment Instructions of Sikorsky Alert Service Bulletin No. 76–66–48B, Revision B, dated July 8, 2009.

(b) After accomplishing paragraph (a) of this AD, insert into the Sikorsky Rotorcraft Flight Manual (RFM) the changes to the ‘‘Normal Procedures (Part I, Section II)’’ and ‘‘Emergency Procedures (Part 1, Section III)’’ contained in Sikorsky RFM, Supplement No. 41, dated September 6, 2005.

(c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Boston Aircraft Certification Office, FAA, ATTN: Caspar Wang, Aviation Safety Engineer, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7799, fax (781) 238–7170, for information about previously approved alternative methods of compliance.

(d) The Joint Aircraft System/Component (JASC) Code is 6321: Main Rotor Brake.

Issued in Fort Worth, Texas, on October 7,

2011. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2011–27659 Filed 10–25–11; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2011–1115; Directorate Identifier 2010–SW–011–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model**  **S–92A Helicopters**

**AGENCY :**  Federal Aviation Administration, DOT.

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

**SUMMARY :**  This document proposes adopting a new airworthiness directive (AD) for the Sikorsky Model S–92A helicopters. This proposal would require revising the Operating Limitations section of the Sikorsky Model S–92A Rotorcraft Flight Manual (RFM). This proposal is prompted by the manufacturer’s analysis of engine data that revealed the data was inaccurate in dealing with available above specification engine power margin. The actions specified by this proposed AD are intended to prevent the use of inaccurate engine performance data in calculating maximum gross weight by revising the Operating Limitations section of the
RFM.

**DATES :**  Comments must be received on or before December 27, 2011.

**ADDRESSES :**  Use one of the following addresses to submit comments on this proposed AD:

• 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 20590, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

**FOR FURTHER INFORMATION CONTACT :**  John Coffey, Aviation Safety Engineer, Boston Aircraft Certification Office, 12 New England Executive Park, Burlington, MA 01803, telephone (781) 238–7173, fax (781) 238–7170.

**SUPPLEMENTARY INFORMATION :** 

Comments Invited

We invite you to submit any written data, views, or arguments regarding this proposed AD. Send your comments to the address listed under the caption

**ADDRESSES** . Include the docket number ‘‘FAA–2011–1115, Directorate Identifier 2010–SW–011–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 with FAA personnel concerning this proposed rulemaking. Using the search function of our docket web site, you can find and read the comments to any of our dockets, including the name of the individual who sent or signed the comment. You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78).
Examining the Docket

You may examine the docket that contains the proposed AD, any comments, and other information 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 Docket Operations office (telephone (800) 647–5527) is located in Room W12–140 on the ground floor of the West Building at the street address stated in the **ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.