### 59465 Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules

Rolls-Royce Corporation (Type Certificate Previously Held by Allison Engine Company and Allison Gas Turbine Division of General Motors): Docket No. FAA–2011–0961; Directorate Identifier 2011–NE–22–AD.
(a) Comments Due Date

The FAA must receive comments on this AD action by December 1, 2014.
(b) Affected ADs

This AD supersedes AD 2012–14–06, Amendment 39–17120 (77 FR 40479, July 10, 2012).
(c) Applicability

This AD applies to Rolls-Royce Corporation (RRC) 250–B17, –B17B, –B17C, –B17D, –B17E, –B17F, –B17F/1, –B17F/2 turboprop engines; and RRC 250–C20, –C20B, –C20F, –C20J, –C20R, –C20R/1,– C20R/2, –C20R/4, –C20S and –C20W turboshaft engines with 3rd-stage turbinewheel, part number (P/N) 23065818, and 4thstage turbine wheel, P/N 23055944, installed.
(d) Unsafe Condition

This AD was prompted by investigationsthat revealed that not all 3rd-stage and 4thstage turbine wheel blade failures were identified by the one-time inspections required by AD 2012–14–06, Amendment 39–17120 (77 FR 40479, July 10, 2012). We determined that to address the unsafe condition, repetitive inspections are required, triggered by hours since last inspection (HSLI) or any hot start event. Weare issuing this AD to prevent failure of 3rdstage and 4th-stage turbine wheel blades, which could cause engine failure and damage to the aircraft.
(e) Compliance

Comply with this AD within the compliance times specified, unless already done. After the effective date of this AD:

(1) Within 1,750 HSLI, remove the affected turbine wheels and perform a visual inspection and a fluorescent-penetrant inspection (FPI) on the removed turbine wheels for cracks at the trailing edge of the turbine blades near the fillet at the rim.

(2) Any time there is a hot start, immediately perform a visual inspection and an FPI on the affected turbine wheels for cracks at the trailing edge of the turbine blades, near the fillet at the rim.

(3) Any time the power turbine is disassembled, perform a visual inspection and an FPI on the affected turbine wheels for cracks at the trailing edge of the turbine blades, near the fillet at the rim.

(4) Thereafter, re-inspect every 1,750 HSLI. (5) Do not return to service any turbine wheels that have cracks detected.

(f) Definition

For the purpose of this AD, an engine hot start is any time the turbine temperature exceeds 1,490 °F for 10 seconds or more, or exceeds 1,700 °F for any duration.
(g) Alternative Methods of Compliance (AMOCs)

The Manager, Chicago Aircraft Certification Office, may approve AMOCs for 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 John Tallarovic, Aerospace Engineer, Chicago Aircraft Certification Office, FAA, 2300 E. Devon Ave., Des Plaines, IL 60018; phone: 847–294–8180; fax: 847–294–7834; email: john.m.tallarovic@faa.gov

.

(2) RRC Alert Commercial Engine Bulletin (CEB) No. CEB–A–1407, Revision 3, dated May 19, 2014, and CEB No. CEB–A–72–4098, Revision 3, dated May 19, 2014 (combined into one document), which are not incorporated by reference in this AD, can be obtained from RRC, using the contact information in paragraph (h)(3) of this AD.

(3) For service information identified in this AD, contact Rolls-Royce Corporation Customer Support, 450 South Meridian Street, Indianapolis, IN 46225–1103; phone: 888–255–4766 or 317–230–2720; email: helicoptercustsupp@rolls-royce.com ; Internet: www.rolls-royce.com

.

(4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803. For information on the availability of this material at the FAA, call
781–238–7125.

Issued in Burlington, Massachusetts, on September 23, 2014. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2014–23553 Filed 10–1–14; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0759; Directorate Identifier 2014–CE–028–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; Alpha Aviation Concept Limited Airplanes** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for certain Alpha Aviation Concept Limited Model R2160 airplanes. This proposed AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as paint adherence defects inside the engine air intake box and cohesion defects inside the laminated ducting from the filter to the air intake box. We are issuing this proposed AD to require actions to address the unsafe condition on these products.

**DATES :**  We must receive comments on this proposed AD by November 17,
2014.

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

For service information identified in this proposed AD, contact Alpha Aviation, 59 Hautapu Road, RD 1, Cambridge 3493, New Zealand; telephone: +64 7 827 0528; fax: +64 7 929 2878; Internet: www.alphaaviation.co.nz. You may review this 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 by searching for and locating Docket No. FAA–2014– 0759; 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 (telephone (800) 647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; phone: (816) 329–4123; fax: (816) 329– 4090; email: karl.schletzbaum@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about


### 59466 Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules

this proposed AD. Send your comments to an address listed under the

**ADDRESSES** section. Include ‘‘Docket No. FAA–2014–0759; Directorate Identifier 2014–CE–028–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:// 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

The Civil Aviation Authority (CAA), which is the aviation authority for New Zealand, has issued AD DCA/R2000/ 25A, dated August 28, 2014 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for Alpha Aviation Concept Limited Model R2160 airplanes and was based on mandatory continuing airworthiness information originated by an aviation authority of another country. The MCAI states:

To prevent loss of engine power due to a possible paint adherence defect inside the engine air intake box, accomplish the following:

Inspect the engine air intake box (including the deflection flap) and the engine air intake ducting (include the area downstream of the filter) per Alpha Aviation Service Bulletin No. AA–SB–71–007 dated August 2014 or later approved revisions.

If any defects are found, replace affected parts per SB No. AA–SB–71–007 before further flight. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0759.

Relevant Service Information

Alpha Aviation Concept Limited has issued Alpha Aviation Service Bulletin AA–SB–71–007, Revision 0, dated August 2014. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of the 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 this State of Design Authority, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Costs of Compliance

We estimate that this proposed AD will affect 10 products of U.S. registry. We also estimate that it would take about 1 work-hour 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 $850, or $85 per product.

In addition, we estimate that any necessary follow-on actions would take about 6 work-hours and require parts costing $1,000, for a cost of $1,510 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. 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. Amend § 39.13 by adding the following new AD:
Alpha Aviation Concept Limited: Docket No. FAA–2014–0759; Directorate Identifier 2014–CE–028–AD.
(a) Comments Due Date

We must receive comments by November 17, 2014.
(b) Affected ADs

None. (c) Applicability

This AD applies to Alpha Aviation Concept Limited Model R2160 airplanes, serial numbers 001 to 378, certificated in any category. (d) Subject

Air Transport Association of America (ATA) Code 73: Engine Fuel & Control.
(e) Reason

This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as paint adherence defects inside the engine air intake box and cohesion defects inside the laminated ducting from the filter to the air intake box. We are issuing this proposed AD to prevent paint defects from entering the engine which could cause loss of power.
(f) Actions and Compliance

Unless already done, do the actions in paragraphs (f)(1) through (f)(4) of this AD: (1) Within the next 100 hours time-in-service (TIS) after the effective date of this AD and repetitively thereafter every 100 hours TIS, inspect any painted engine air intake box (including the deflection flap) and the air


### 59467 Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules

intake ducting (including the area downstream of the filter) for paint adherence defects such as peeling, blistering, or bubbling following Alpha Aviation Service Bulletin (SB) No. AA–SB–71–007, Revision 0, dated August 2014.

(2) If any defects are found during the inspection required in paragraph (f)(1) of this AD, before further flight, replace the affected parts with airworthy parts following Alpha Aviation Service Bulletin No. AA–SB–71– 007, Revision 0, dated August 2014.

(3) As of the effective date of this AD, only install new unpainted steel assembly air intake boxes.

(4) The replacement of defective parts is not a terminating action to the repetitive inspection of painted engine intake components required in paragraph (f)(1) of this AD.
(g) Other FAA AD Provisions

The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, Standards Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; phone: (816) 329–4123; fax: (816) 329–4090; email: karl.schletzbaum@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO.

(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.

(h) Related Information

Refer to MCAI Civil Aviation Authority (CAA) AD DCA/R2000/25A, dated August 28, 2014, for related information. You may examine the MCAI on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA–2014–0759. For service information related to this AD, contact Alpha Aviation, 59 Hautapu Road, RD 1, Cambridge 3493, New Zealand; telephone: +64 7 827 0528; fax: +64 7 929 2878; Internet: www.alphaaviation.co.nz. You may review this 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.

Issued in Kansas City, Missouri, on September 26, 2014. Kelly A. Broadway, Acting Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2014–23554 Filed 10–1–14; 8:45 am]

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

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2014–0521; Directorate Identifier 2014–NE–11–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; CFM International S.A. Turbofan Engines** 

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

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

**SUMMARY :**  We propose to adopt a new airworthiness directive (AD) for all CFM International (CFM) S.A. CFM56–7B series turbofan engines. This proposed AD was prompted by a dual engine thrust instability event that resulted in the overspeed and in-flight shutdown (IFSD) of one engine. This proposed AD would require modification of the engine by removing full authority digital engine control (FADEC) software, version 7BV4 or earlier, installed in the electronic engine controls (EECs) on CFM56–7B engines. We are proposing this AD to prevent a thrust instability event, which could lead to overspeed and IFSD of one or more engines, loss of thrust control, damage to the engine, and damage to the airplane.

**DATES :**  We must receive comments on this proposed AD by December 1, 2014.

**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 AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877–432–3272; fax: 877– 432–3329; email: geae.aoc@ge.com. 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. Examining the AD Docket You may examine the AD docket on the Internet at http:// www.regulations.gov by searching for and locating Docket No. FAA–2014– 0521; 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 :**  Barbara Caufield, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7146; fax: 781–238– 7199; email: barbara.caufield@faa.gov.

**SUPPLEMENTARY INFORMATION :** 
Comments Invited

We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the **ADDRESSES** section. Include ‘‘Docket No. FAA– 2014–0521; Directorate Identifier 2014– NE–11–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

We have received reports of dual engine thrust instability events on CFM56–7B turbofan engines that resulted in overspeed and IFSD of one engine. These resulted from water-borne fuel contamination of the fuel supply causing a lag in the response of the control valve in the fuel metering unit (FMU). CFM has improved its FADEC software to help prevent the lag in the response of the FMU control valve, thereby mitigating these thrust instability events. This condition, if not corrected, could lead to overspeed and IFSD of one or more engines, loss of thrust control, damage to the engine, and damage to the airplane.