### 68055 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations

(3) Fokker Report, SE–623, Fokker 70/100 Airworthiness Limitation Items and Safe Life Items, Issue 8, dated December 20, 2010.

(4) Goodrich Service Bulletin 41000–32– 29, dated November 10, 2010.
(o) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(3) The following service information was approved for IBR on December 20, 2012.

(i) Fokker Service Bulletin SBF100–32– 161, dated April 7, 2011.

(ii) Fokker Report, SE–623, Fokker 70/100 Airworthiness Limitation Items and Safe Life Items, Issue 8, dated December 20, 2010.

(iii) Goodrich Service Bulletin 41000–32– 29, dated November 10, 2010.

(4) The following service information was approved for IBR on March 22, 2011 (76 FR 8618, February 15, 2011).

(i) Fokker Service Bulletin SBF100–32– 158, dated October 2, 2009.

(ii) Reserved. (5) For service information identified in this AD, contact Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands; telephone +31 (0)252–627–350; fax +31 (0)252–627–211; email technicalservices.fokkerservices@stork.com;
Internet http://www.myfokkerfleet.com. For Goodrich Corporation service information identified in this AD, contact Goodrich, 1400 South Service Road, West Oakville, L6L 5Y7, Ontario, Canada, telephone +1–905–827– 7777; fax +1–905–825–1583; Internet http:// www.goodrich.com/TechPubs.

(6) You may review copies of the 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.

(7) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Renton, Washington, on October
24, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–26781 Filed 11–14–12; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0530; Directorate Identifier 2011–SW–075–AD; Amendment**  **39–17247; AD 2012–22–11]**

**RIN 2120–AA64**

**Airworthiness Directives; Bell Helicopter Textron Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Bell Helicopter Textron (BHT) Model 412, 412EP, and 412CF helicopters. This AD requires a repetitive inspection of the collective lever for a crack, and if there is a crack, before further flight, replacing the collective lever with an airworthy collective lever. This AD was prompted by a reported failure of a collective lever. The actions are intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective December 20, 2012.

The Director of the Federal Register approved the incorporation by reference of certain documents listed in this AD as of December 20, 2012.

**ADDRESSES :**  For service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101; telephone (817) 280–3391; fax (817) 280–6466; or
at http://www.bellcustomer.com/files/. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas
76137.

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 AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. **FOR FURTHER INFORMATION CONTACT :**  Martin Crane, Aerospace Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5170; email martin.r.crane@faa.gov.
**SUPPLEMENTARY INFORMATION :** 

Discussion

On May 22, 2012, at 77 FR 30232, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to certain serial-numbered BHT Model 412, 412EP, and 412CF helicopters with a collective lever, part number (P/N) 412–010–408–101. That NPRM proposed to require within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS, cleaning the collective lever and inspecting it for cracks with a 10X or higher power magnifying glass. If there is a crack in the collective lever paint finish, the NPRM proposed to require removing the collective lever from the swashplate and performing a fluorescent penetrant inspection, and if there is a crack in the collective lever, before further flight, replacing the collective lever with an airworthy collective lever. The proposed requirements were intended to detect a crack in the collective lever, which could lead to failure of the collective lever and subsequent loss of control of the helicopter.

Comments

We gave the public the opportunity to participate in developing this AD, but we did not receive any comments on the NPRM (77 FR 30232, May 22, 2012).

FAA’s Determination

We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

We reviewed Bell Helicopter Alert Service Bulletin (ASB) No. 412–11–148 and ASB No. 412CF–11–47, both Revision A, and both dated December 12, 2011, which describe procedures for repetitively inspecting the collective lever with a magnifying glass and a strong light source and, if necessary, a fluorescent penetrant inspection. If there is a crack, the ASBs require replacing the collective lever.


### 68056 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations

Differences Between This AD and the Service Information

The BHT ASBs require compliance within 100 hours of flight time for the initial inspection; this AD requires compliance within 25 hours TIS or 30 days, whichever occurs first. If there is a crack, the BHT ASBs require reporting the defect to Bell Product Support Engineering; this AD does not. The BHT ASBs allow a portion of the collective lever to be inspected by a mirror and light only without a magnifying glass; this AD requires using a 10X or higher power magnifying glass for the entire inspection. Costs of Compliance

We estimate that this AD will affect 83 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. Inspecting the collective lever requires one work-hour at an average labor rate of $85 per work-hour, for a cost per helicopter of $85 and a total cost to the U.S. operator fleet of $7,055 per inspection cycle. Replacing a cracked collective lever requires 10 work-hours at an average labor rate of $85 per work-hour and required parts will cost $12,883, for a total cost of $13,733 per helicopter. 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

This AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

(2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; 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 an economic evaluation of the estimated costs to comply with this 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. Adoption of the Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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):
2012–22–11 Bell Helicopter Textron: Amendment 39–17247; Docket No. FAA–2012–0530; Directorate Identifier 2011–SW–075–AD.
(a) Applicability

This AD applies to Model 412 and 412EP helicopters, serial numbers (S/N) 33001 through 33213, 34001 through 34036, and 36001 and higher; and Model 412CF helicopters, S/N 46400 and higher; with a collective lever part number (P/N) 412–010– 408–101 installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as a cracked collective lever, which could result in failure of the collective lever and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective December 20,
2012. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time. (e) Required Actions Within 25 hours time-in-service (TIS) or 30 days, whichever occurs first, and thereafter at intervals not to exceed 100 hours TIS:

(1) Using cleaning compound (C–318) or equivalent, thoroughly clean the collective lever.

(2) Using a 10X or higher power magnifying glass, inspect the collective lever in the areas shown in Figure 1 of Bell Helicopter Textron Alert Service Bulletin (ASB) 412–11–148, Revision A, dated December 12, 2011 or Bell Helicopter Textron ASB 412CF–11–47, Revision A, dated December 12, 2011, as appropriate for your model helicopter.

(3) If there is a crack in the paint, remove the collective lever from the swashplate assembly.

(i) Remove paint and primer from the area around the crack.

(ii) Fluorescent penetrant inspect the area of the crack.

(4) If there is a crack in the collective lever, before further flight, replace the collective lever with an airworthy collective lever.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Martin Crane, Aerospace Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222–5170, email martin.r.crane@faa.gov.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(g) Subject

Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor.
(h) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Bell Helicopter Textron Alert Service Bulletin No. 412–11–148, Revision A, dated December 12, 2011.

(ii) Bell Helicopter Textron Alert Service Bulletin No. 412CF–11–47, Revision A, dated December 12, 2011.

(3) For Bell Helicopter service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101, telephone (817) 280–3391, fax (817) 280–6466, or at http:// www.bellcustomer.com/files/.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For


### 68057 Federal Register / Vol. 77, No. 221 / Thursday, November 15, 2012 / Rules and Regulations

information on the availability of this material at the FAA, call (817) 222–5110.

(5) You may view this service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741–6030, or go to: http://www.archives.gov/federal-register/cfr/ibrlocations.html.

Issued in Fort Worth, Texas, on October 26,
2012. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–27059 Filed 11–14–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0340; Directorate Identifier 2011–SW–073–AD; Amendment**  **39–17250; AD 2012–22–13]**

**RIN 2120–AA64**

**Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for certain Sikorsky Aircraft Corporation (Sikorsky) Model S–76C helicopters. This AD requires installing an improved throttle stop and a wider trigger on the engine control levers (ECL). This AD was prompted by a bird-strike to the windshield that resulted in unintended movement of the engine control levers from the forward position and towards the flight-idle position, which reduced power on both engines. These actions are intended to prevent unintended movement of the ECLs, resulting in main rotor speed decay and subsequent loss of control of the aircraft.

**DATES :**  This AD is effective December 20, 2012.

The Director of the Federal Register approved the incorporation by reference of a certain document listed in this AD as of December 20, 2012.

**ADDRESSES :**  For service information identified in this AD, contact Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone (203) 383–4866, email address tsslibrary@sikorsky.com,
or at http://www.sikorsky.com. You may review a copy of the referenced service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

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 AD, any incorporated-by-reference service information, the economic evaluation, any comments received, and other information. The street address for the Docket Operations Office (phone: 800– 647–5527) is U.S. Department of Transportation, Docket Operations Office, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590.

**FOR FURTHER INFORMATION CONTACT :**  Kirk Gustafson, Aerospace Engineer, FAA, Boston Aircraft Certification Office, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7190; email kirk.gustafson@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On March 29, 2012, at 77 FR 18969, the Federal Register published our notice of proposed rulemaking (NPRM), which proposed to amend 14 CFR part 39 to include an AD that would apply to Sikorsky Model S–76C helicopters with serial numbers 760506 and 760607 through 760812. That NPRM proposed to require within 6 months after the effective date of the AD, installing an improved throttle stop and a wider trigger on each ECL as specified in Sikorsky Alert Service Bulletin (ASB) No. 76–76–6A, Revision A, dated May 18, 2011.

The proposed requirements were intended to prevent unintended in-flight movement of the ECLs from the normal ‘‘FLY’’ position towards the ‘‘IDLE’’ position, which significantly reduces engine power, resulting in an unrecoverable loss of main rotor speed and subsequent loss of control of the helicopter.

Comments

Two commenters, one anonymous and one from the National Transportation Safety Board, commented that they support the NPRM (77 FR 18969, March 29, 2012).

FAA’s Determination

We have reviewed the relevant information and determined that an unsafe condition exists and is likely to exist or develop on other products of the same type design and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

We reviewed ASB 76–76–6A, which describes procedures for partially disassembling the engine control quadrant assembly, removing the existing throttle stop, and installing a new airworthy throttle stop. The ASB also describes procedures to remove the existing trigger assembly from each ECL and install a new airworthy wide trigger assembly. Costs of Compliance

We estimate that this AD will affect 52 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. To replace the engine control lever stop and trigger assemblies will require 2 work-hours at an average labor cost of $85 per hour. Required parts will cost about $939. Based upon these costs, we estimate a total cost of $1,109 per helicopter and a total cost of $57,668 for the entire U.S. operator fleet. 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

This AD will not have federalism implications under Executive Order 13132. This AD will 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 this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866;