Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules 44897 

before collecting data from the public. It is 

our understanding that before a federal 

agency can require or request information 

from the public, the agency must (1) seek 

public comment on the proposed collections, 

and (2) submit the proposed collections for 

review and approval by OMB. Based on 

published guidance from the Executive 

Branch, it appears that the regular review and 

approval process can take anywhere from 6– 

9 months from the date the process is 

initiated by the agency. 

The rulemaking requested in this petition 

appears to involve the collection of 

information subject to PRA requirements. For 

the reasons stated above, however, a delay of 

up to 9 months after the initiation of the 

rulemaking will cause harm to manufacturers 

and consumers that can and must be avoided. 

Under certain circumstances, an agency 

may obtain expedited or ‘‘emergency’’ OMB 

review of an information collection request. 

The regulations applicable to a request for 

emergency processing are set forth in 5 CFR 

§ 1320.13 and state, in relevant part: 

(a) Any such request shall be accompanied 

by a written determination that: 

(1) The collection of information: 

(i) Is needed prior to the expiration of time 

periods established under this Part; and 

(ii) Is essential to the mission of the 

agency; and 

(2) The agency cannot reasonably comply 

with the normal clearance procedures under 

this Part because: 

(i) Public harm is reasonably likely to 

result if normal clearance procedures are 

followed; (or) 

(ii) An unanticipated event has occurred; 

. . . 

The circumstances described in this 

petition meet the requirements for expedited 

emergency review. Collecting EER 

information is based on regional standards 

that include minimum EER standards for 

CACs installed in the Southwestern Region. 

Collection of EER information, therefore, is 

essential to DOE’s ability to effectively 

enforce compliance with regional EER 

standards, and to provide complete 

information for the public to use in 

evaluating the energy efficiency of a covered 

product or covered equipment. [subsection 

(a)(1)(ii).] 

EER information must be collected and 

published in CCMS/CCD before completion 

of normal clearance procedures or significant 

public harm to manufacturers and consumers 

is likely to result. [subsection (a) (1) (ii), and 

(2)(i).] In addition, the adoption of 

regulations by the California Energy 

Commission applicable to higher efficiency 

CACs installed on or after January 1, 2014 

may be regarded as an unanticipated event in 

light of the January 1, 2015 effective date for 

regional standards under federal law. 

[subsection (a)(2)(ii)]. The voluntary 

collection of EER information under the 

emergency procedure would place no 

additional burden on manufacturers, because 

they already have and maintain the EER 

information which is derived from the ‘‘A’’ 

test required under existing certification and 

compliance regulations. 

Very truly yours, 

HOWE, ANDERSON & STEYER, P.C. 

Richard A. Steyer 

Attorney for First Co. 

cc: Ashley Armstrong, DOE, Laura Barhydt, 

DOE, First Co. 

[FR Doc. 2013–17894 Filed 7–24–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0381; Directorate 

Identifier 2013–NE–16–AD] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft 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 

Turbomeca S.A. Arrius 2B1, 2B1A, 2B2, 

and 2K1 turboshaft engines. This 

proposed AD was prompted by in-flight 

shutdowns caused by interrupted fuel 

supply at the hydro-mechanical 

metering unit (HMU). This proposed AD 

would require initial and repetitive 

inspections of the HMU high pressure 

pump drive gear shaft splines, cleaning 

and inspections of the sleeve assembly 

splines, and replacement of the HMU if 

it fails inspection. We are proposing this 

AD to prevent in-flight shutdown and 

damage to the engine. 

DATES: We must receive comments on 

this proposed AD by September 23, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 

00; telex: 570 042; fax: 33 (0)5 59 74 45 

15. 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; 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 proposed AD, the 

mandatory continuing airworthiness 

information (MCAI), the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION 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. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0381; Directorate Identifier 

2013–NE–16–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 based on 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 AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may view the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2013– 


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44898 Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules 

0082, dated April 2, 2013, referred to 

hereinafter as ‘‘the MCAI’’, to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A number of in-flight shutdown 

occurrences have been reported for Arrius 2 

engines. The results of the technical 

investigations concluded that these events 

were caused by deterioration of the splines 

on the high pressure (HP)/low pressure (LP) 

pump assembly drive shaft of the hydromechanical metering unit (HMU), which 

eventually interrupted the fuel supply to the 

engine. 

This condition, if not detected and 

corrected, could lead to further cases of 

engine in-flight shutdown, possibly resulting 

in forced landing. 

To address these occurrences, Turbomeca 

published Service Bulletin (SB) No. SB 319 

73 2825, which provides inspection 

instructions. After that SB was issued, further 

similar occurrences prompted Turbomeca to 

perform a new assessment of the issue. As a 

result, it was determined that repetitive 

inspections of the HMU, including an 

additional inspection of the sleeve assembly, 

was necessary to address the issue. Those 

instructions are provided in Turbomeca 

Mandatory SB (MSB) No. SB 319 73 2825 

version G. 

For the reasons described above, this AD 

requires repetitive inspections of drive gear 

shaft splines of the HP pump, and depending 

on findings, accomplishment of applicable 

corrective actions. 

You may obtain further information by 

examining the MCAI in the AD docket. 

We are proposing this AD to prevent inflight shutdown and damage to the 

engine. 

Relevant Service Information 

Turbomeca S.A. has issued 

Mandatory Service Bulletin No. SB 319 

73 2825, Version G, dated January 24, 

2013. The service information describes 

procedures for correcting the unsafe 

condition described in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of France, and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with the European 

Community, EASA has 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 provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

proposed AD would require initial and 

repetitive inspections and cleaning of 

the HMU high pressure pump drive gear 

shaft splines, cleaning and inspections 

of the sleeve assembly splines, and 

replacement of the HMU if it fails 

inspection. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 162 engines installed on 

helicopters of U.S. registry. We also 

estimate that it would take about one 

hour per engine to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Required parts cost about 

$753 per engine. Based on these figures, 

we estimate the cost of the proposed AD 

on U.S. operators to be $135,756. 

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 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 proposed 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. 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Turbomeca S.A.: Docket No. FAA–2013– 

0381; Directorate Identifier 2013–NE– 

16–AD. 

(a) Comments Due Date 

We must receive comments by September 

23, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Turbomeca S.A. 

Arrius 2B1, 2B1A, 2B2, and 2K1 turboshaft 

engines. 

(d) Reason 

This AD was prompted by in-flight 

shutdowns caused by interrupted fuel supply 

at the hydro-mechanical metering unit 

(HMU). We are issuing this AD to prevent inflight shutdown and damage to the engine. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(f) Initial Visual Inspection for HMUs Not 

Previously Inspected 

(1) On the effective date of this AD, for 

those HMUs that have not previously been 

inspected per Turbomeca Mandatory Service 

Bulletin (MSB) No. SB 319 73 2825, Version 

G, dated January 24, 2013, or earlier versions; 

perform an initial visual inspection of HMU 

aft splines of the high pressure pump for 

wear, corrosion, scaling, or cracks, and clean 

and inspect the sleeve assembly splines for 

wear, corrosion, scaling, or cracks, at the 

following: 

(i) For HMUs that have accumulated more 

than 150 operating hours (OHs) since new or 

since last overhaul, within 50 HMU OHs after 

effective date of this AD. 

(ii) For HMUs that have accumulated 150 

or fewer OHs since new or since last 

overhaul, before exceeding 200 HMU OHs. 


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Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules 44899 

(g) Initial Visual Inspection for HMUs That 

Have Been Previously Inspected 

(1) On the effective date of this AD, for 

those HMUs that have been previously 

inspected per Turbomeca MSB No. SB 319 73 

2825, Version G, dated January 24, 2013, or 

earlier versions; perform a visual inspection 

of HMU aft splines of the high pressure 

pump for wear, corrosion, scaling, or cracks, 

and clean and inspect the sleeve assembly 

splines for wear, corrosion, scaling, or cracks, 

at the following: 

(i) For HMUs that have accumulated 300 

OHs or more since last inspection, within 

200 HMU OHs after effective date of this AD. 

(ii) For HMUs that have accumulated fewer 

than 300 OHs since last inspection, before 

exceeding 500 HMU OHs. 

(h) Repetitive Visual Inspections of HMUs 

(1) Thereafter, repetitively visually inspect 

the HMU aft splines of the high pressure 

pump, and clean and inspect the sleeve 

assembly splines for wear, corrosion, scaling, 

or cracks, at intervals not to exceed 500 HMU 

OHs. 

(2) If, during any initial or repetitive 

inspection required by this AD, an HMU does 

not pass inspection, then before further 

flight, replace the sleeve assembly on the 

affected high pressure pump drive gear shaft 

or replace the affected HMU. 

(i) Installation Prohibition 

After the effective date of this AD, do not 

install any engine on any helicopter unless 

the HMU was inspected as required by this 

AD. 

(j) 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. 

(k) 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; 

email: frederick.zink@faa.gov; phone: 781– 

238–7779; fax: 781–238–7199. 

(2) Refer to European Aviation Safety 

Agency, AD 2013–0082, dated April 2, 2013, 

for more information. You may examine the 

AD on the Internet at http:// 

www.regulations.gov. 

(3) Turbomeca MSB No. SB 319 73 2825, 

Version G, dated January 24, 2013, which is 

not incorporated by reference in this AD, can 

be obtained from Turbomeca, S.A. using the 

contact information in paragraph (k)(4) of 

this AD. 

(4) For service information identified in 

this AD, contact Turbomeca, S.A., 40220 

Tarnos, France; phone: 33 (0)5 59 74 40 00; 

telex: 570 042; fax: 33 (0)5 59 74 45 15. 

(5) 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. 

Issued in Burlington, Massachusetts, on 

July 18, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–17864 Filed 7–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0499; Directorate 

Identifier 2013–NE–20–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company 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 certain 

General Electric Company (GE) GE90– 

110B1 and –115B turbofan engines. This 

proposed AD was prompted by multiple 

events of a leaking variable bypass valve 

(VBV) actuator fuel supply tube. This 

proposed AD would require 

replacement of this VBV actuator fuel 

supply tube with a part eligible for 

installation. We are proposing this AD 

to prevent failure of the affected fuel 

supply tube, fuel leakage, engine fire, 

and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by September 23, 

2013. 

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 proposed AD, contact General 

Electric Company, GE Aviation, Room 

285, One Neumann Way, Cincinnati, 

OH 45215; phone: 513–552–3272; 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; 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: 

Jason Yang, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7747; fax: 781–238– 

7199; email: jason.yang@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– 

2013–0499; Directorate Identifier 2013– 

NE–20–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 multiple reports of 

a leaking VBV actuator fuel supply tube, 

part number (P/N) 2165M22P01, 

installed on GE90–110B1 and –115B 

turbofan engines. One of the leaks led to 

an under cowl engine fire. The vibratory 

excitation frequency of this VBV 

actuator fuel supply tube mode shape is 

within the frequency range generated by 

the engine during cruise. Because the 

tube’s end weld is a high stress 

concentration location, the tube can and 

has cracked in this area and eventually 

failed due to high-cycle fatigue. This 

proposed AD, therefore, requires 

replacement of the affected VBV 


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