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

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 turbine 

wheel, part number (P/N) 23065818, and 4thstage turbine wheel, P/N 23055944, installed. 

(d) Unsafe Condition 

This AD was prompted by investigations 

that 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. We 

are 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 


rmajette on DSK2VPTVN1PROD with RULES
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 


rmajette on DSK2VPTVN1PROD with RULES
Federal Register / Vol. 79, No. 191 / Thursday, October 2, 2014 / Proposed Rules 59467 

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. 


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