### 17076 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations

products identified in this rulemaking action. Regulatory Findings

We determined that 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 this AD:

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 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 a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket.
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, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: (800) 647–5527) is provided in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt. 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 AD: 2013–05–19 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39–17391; Docket No. FAA–2012–1031; Directorate Identifier 2012–NE–31–AD.

(a) Effective Date

This airworthiness directive (AD) becomes effective April 24, 2013.

(b) Affected ADs

None.
(c) Applicability

This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611–8 turbofan engines, serial numbers 16245, 16256, 16417, 16418, 16584, 16585, 16639, 16640, 16701, 16702, 16813, 16814, 16853, 16854, 16879, 16880, 16898, 16905, 16906, 16911, 16923, 16935, and 16936, with a date of the last shop visit before December 8,
2006.
(d) Reason

This AD was prompted by a recent quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
(e) Actions and Compliance

Unless already done, for engines with a date of the last shop visit before December 8, 2006, do the following actions:

(1) If engine cycles accumulated since the last engine shop visit is 5,400 cycles or more on the effective date of this AD, inspect the bolts installed in the low-pressure turbine (LPT) stage 1 static seal and high-pressure turbine (HPT) stage 1 air seal support within 100 engine cycles-in-service after the effective date of this AD.

(2) If engine cycles accumulated since the last engine shop visit is fewer than 5,400 cycles on the effective date of this AD, inspect the bolts installed in the LPT stage 1 static seal and HPT stage 1 air seal support before accumulating 5,500 engine cycles since the last engine shop visit.

(3) If you find any broken bolt, brown bolt, or bolt with a rough oxidized surface, then replace all bolts of the inspected engine flange with new bolts before further flight.

(f) Installation Prohibition

After the effective date of this AD, do not install any HPT module and/or LPT module into any engine, or any engine onto an airplane, unless the bolts have been inspected and replaced if necessary, as specified in paragraph (e) of this AD.
(g) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request.

(h) Related Information

(1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238–7199; email: frederick.zink@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012–0163, dated August 28, 2012, and RRD Alert Service Bulletin TAY– 72–A1696, Revision 1, dated June 11, 2012, for related information.

(3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; phone: 49 0 33–7086–1200 (direct 1016); fax: 49 0 33– 7086–1212. You may view this 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. (i) Material Incorporated by Reference

None.

Issued in Burlington, Massachusetts, on March 7, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service.

[FR Doc. 2013–06170 Filed 3–19–13; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0795; Directorate Identifier 2008–SW–53–AD; Amendment 39–**  **17395; AD 2013–05–23]**

**RIN 2120–AA64**

**Airworthiness Directives; Eurocopter France Helicopters** 

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

**ACTION :**  Final rule.

**SUMMARY :**  We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to require a one-time inspection of the main rotor head (MRH) swash-plateupper bearing (bearing) for a nonsmooth point (friction point). This AD was prompted by a report of the premature deterioration of the MRH bearing of the rotating star installed on a Model AS332L1 helicopter. The actions of this AD are intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.

**DATES :**  This AD is effective April 24,

2013.

**ADDRESSES :**  For service information identified in this AD, contact American Eurocopter Corporation, 2701 Forum


### 17077 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations

Drive, Grand Prairie, Texas 75053–4005; telephone (800) 232–0323; or at http:// www.eurocopter.com. You may review 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 :**  Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@faa.gov.

**SUPPLEMENTARY INFORMATION :** 

Discussion

On July 30, 2012, at 77 FR 44509, 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 Eurocopter Model AS332C, L, and L1 helicopters with a certain MRH. That NPRM proposed to require inspecting the MRH bearing for a non-smooth point (friction point), and if there is a friction point in the bearing, then replacing the MRH with an airworthy MRH, or if there is not a friction point in the bearing, then further inspecting the grease expelled from the MRH swash-plate for metal particles. The NPRM also proposed to require that if there is a metal particle in the grease expelled from the MRH swash-plate, replacing the MRH with an airworthy MRH, or if there is not a metal particle in the grease, measuring the force required to rotate the MRH swash-plate and inspecting certain MRH swash-plate assemblies for vertical play in the bearing to determine the airworthiness of the MRH. The proposed requirements were intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Union, issued EASA Emergency AD No. 2008–0172–E, dated September 9, 2008 (EAD No. 2008–0172–E), to correct an unsafe condition for the Eurocopter Model AS 332 C, C1, L, and L1 helicopters, with an MRH, part number (P/N) 332A31–0001–05 or P/N 332A31– 0001–06, having a serial number (S/N) of M172, M216, M261, M308, M547, M677, M811, or M936, and having ‘‘logged less than 275 flight hours since the last overhaul or repair.’’ EASA states that Eurocopter received a report of deterioration of an MRH bearing on an MRH that was installed on an AS 332 L1 helicopter. The AS 332 L1 helicopter had logged 72 flight hours since the last overhaul. EASA states that there was an onset of vibrations in flight and these vibrations were due to premature deterioration of the upper bearing of the MRH swash-plate. They state that this condition, if not corrected, ‘‘could lead to failure of the scissors links and consequently to the control loss 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 44509, July 30, 2012).

FAA’s Determination

These helicopters have been approved by the aviation authority of France and are approved for operation in the United States. Pursuant to our bilateral agreement with France, EASA, its technical representative, has notified us of the unsafe condition described in the EASA AD. We are issuing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other helicopters of these same type designs and that air safety and the public interest require adopting the AD requirements as proposed.

Related Service Information

Eurocopter has issued one Emergency Alert Service Bulletin (EASB) with two different numbers, both Revision 0, and both dated September 8, 2008: EASB No. 62.00.73 for Model AS332C, L, and L1 helicopters and non-FAA type certificated Model C1 helicopters; and EASB No. 62.00.30 for non-FAA type certificated Model 532 UC, AC, UL, AL, SC, and UE military helicopters. EASB No. 62.00.73 specifies checking for the absence of a friction point in the MRH bearing. If there is no friction point, EASB No. 62.00.73 specifies checkingthe condition of the grease in the swashplate assembly by lubricating the swashplate, rotating it by hand, and determining if the expelled grease contains traces of metal particles. If the expelled grease does not contain traces of metal particles, EASB No. 62.00.73 specifies checking the swash-plate ‘‘rotation torque’’ using a spring scale. If the rotation torque is less than 5.5 kg, EASB No. 62.00.73 specifies checking the bearing for vertical play. If there is a friction point, the expelled grease contains traces of metal particles, the rotation torque is equal to or greater than 5.5 kg, or there is vertical play in the bearing, EASB No. 62.00.73 specifies removing the MRH and sending it to an approved repair station. EASA classified this EASB as mandatory and issued EAD No. 2008–0172–E to ensure the continued airworthiness of these helicopters.

Differences Between This AD and the EASA AD

The EASA Emergency AD includes Model AS332C1 helicopters. This AD does not include this model helicopter since it is not type certificated in the U.S. The EASA AD does not include S/Ns M561, M859, M935, M938, and M942, whereas this AD does include those S/Ns. The EASA Emergency AD requires operators to comply with the requirements no later than the ‘‘next last flight of the day.’’ Our AD requires the actions to be accomplished within 5 hours TIS. Also, the EASA Emergency AD is applicable to the specified helicopters having logged less than 275 flight hours since the last overhaul or repair, whereas our AD only applies to the specified helicopters having less than 275 hours TIS since the last overhaul of the MRH. Costs of Compliance

We estimate that this AD will affect 6 helicopters of U.S. Registry. We estimate that operators may incur the following costs in order to comply with this AD. It will take approximately 1 work-hour per helicopter to accomplish the inspection of the MRH bearing for afriction point, inspection of the swashplate grease for any metal particles, measurement of the swash-plate force to rotate, and inspection of the bearing for vertical play. It will take approximately 60 work-hours to replace the MRH. These actions will be accomplished atan average labor rate of $85 per workhour. We estimate the parts cost of replacing an MRH will be approximately $20,000. Based on these figures, we estimate the total cost of this


### 17078 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations

AD on U.S. operators is $25,610, assuming that all affected helicopters are inspected and that one MRH in the fleet will need to be replaced.
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 helicopters 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):
2013–05–23 Eurocopter France (Eurocopter): Amendment 39–17395; Docket No. FAA–2012–0795; Directorate Identifier 2008–SW–53–AD.
(a) Applicability

This AD applies to Eurocopter Model AS332C, L, and L1 helicopters with a main rotor head (MRH), part number (P/N) 332A31–0001–05 or P/N 332A31–0001–06, with a serial number (S/N) M172, M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or M942installed; having less than 275 hours time-inservice (TIS) since the last overhaul of the MRH; certificated in any category.

(b) Unsafe Condition

This AD defines the unsafe condition as deterioration of the MRH swash-plate upper bearing (bearing), which could result in overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.

(c) Effective Date

This AD becomes effective April 24, 2013.
(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 5 hours TIS:(1) Inspect the MRH bearing for a nonsmooth point (friction point) by rotating the MRH swash-plate and:

(i) If there is a friction point in the bearing, before further flight, replace the MRH with an airworthy MRH.

(ii) If there is not a friction point in the bearing, lubricate the MRH swash-plate and rotate it until grease is expelled; inspect the expelled grease for metal particles.

(A) If there is a metal particle in the grease, before further flight, replace the MRH with an airworthy MRH.

(B) If there is not a metal particle in the grease, measure the force required to rotate the MRH swash-plate using a spring scale attached to the pitch change rod attachment yokes.

( 1 ) If the force to rotate the MRH swashplate is equal to or greater than 5.5 kg, before further flight, replace the MRH with an airworthy MRH.

( 2) If the force to rotate the MRH swashplate is less than 5.5 kg, inspect the MRH swash-plate assembly for vertical play in the bearing. If there is vertical play in the bearing, before further flight, replace the MRH with an airworthy MRH. (2) Before installing an MRH, P/N 332A31– 0001–05 or P/N 332A31–001–06, with S/N M172, M216, M261, M308, M547, M561, M677, M811, M859, M935, M936, M938, or M942 on any helicopter, inspect the MRH in accordance with paragraph (e)(1) of this AD.
(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Gary Roach, Aviation Safety Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222–5110; email gary.b.roach@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) Additional Information

(1) Eurocopter Emergency Alert Service Bulletin, No. 62.00.73, Revision 0, dated September 8, 2008, which is not incorporated by reference, contains additional information about the subject of this AD. For service information identified in this AD, contact American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053– 4005; telephone (800) 232–0323; or at http://www.eurocopter.com . You may review a copy of the service information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(2) The subject of this AD is addressed in the European Aviation Safety Agency (France) Emergency AD No. 2008–0172–E, dated September 9, 2008.
(h) Subject

Joint Aircraft Service Component (JASC) Code: 6400, Tail Rotor System.

Issued in Fort Worth, Texas, on March 7,

2013. Lance T. Gant, Acting Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–06132 Filed 3–19–13; 8:45 am]

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