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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44900 Federal Register / Vol. 78, No. 143 / Thursday, July 25, 2013 / Proposed Rules 

actuator fuel supply tube with a part 

eligible for installation. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

replacement of the VBV actuator fuel 

supply tube, P/N 2165M22P01, with a 

part eligible for installation. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 59 engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about eight 

hours per engine to replace the VBV 

actuator fuel supply tube. The cost of 

this part is about $14,310. The average 

labor rate is $85 per hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$884,410. 

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. 

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): 

General Electric Company: Docket No. FAA– 

2013–0499; Directorate Identifier 2013– 

NE–20–AD. 

(a) Comments Due Date 

We must receive comments by September 

23, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to General Electric 

Company (GE) GE90–110B1 and –115B 

turbofan engines with variable bypass valve 

(VBV) actuator fuel supply tube, part number 

(P/N) 2165M22P01, installed. 

(d) Unsafe Condition 

This AD was prompted by multiple events 

of a leaking VBV actuator fuel supply tube. 

We are issuing this AD to prevent failure of 

the affected fuel supply tube, fuel leakage, 

engine fire, and damage to the airplane. 

(e) Compliance 

(1) Comply with this AD within the 

compliance times specified, unless already 

done. 

(2) At the next shop visit, after the effective 

date of this AD, replace the VBV actuator fuel 

supply tube, P/N 2165M22P01, with a part 

eligible for installation. 

(f) Definition 

For the purpose of this AD, a shop visit is 

the induction of an engine into the shop for 

maintenance or overhaul. The separation of 

engine flanges solely for the purposes of 

transporting the engine without subsequent 

engine maintenance does not constitute an 

engine shop visit. 

(g) Installation Prohibition 

After the effective date of this AD, do not 

install a VBV actuator fuel supply tube, P/N 

2165M22P01, onto any engine. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures in 14 CFR 39.19 to make your 

request. 

(i) Related Information 

(1) For more information about this AD, 

contact Jason Yang, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: jason.yang@faa.gov. 

(2) For service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, One Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: geae.aoc@ge.com. 

(3) 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 17, 2013. 

Thomas A. Boudreau, 

Acting Directorate Assistant Manager, Engine 

& Propeller Directorate Aircraft Certification 

Service. 

[FR Doc. 2013–17884 Filed 7–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Parts 38 and 284 

[Docket No. RM13–17–000] 

Communication of Operational 

Information Between Natural Gas 

Pipelines and Electric Transmission 

Operators 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Notice of proposed rulemaking. 

SUMMARY: The Federal Energy 

Regulatory Commission (Commission) is 

proposing to revise Parts 38 and 284 of 

the Commission’s regulations to provide 

explicit authority to interstate natural 

gas pipelines and public utilities that 

own, operate, or control facilities used 

for the transmission of electric energy in 

interstate commerce to share nonpublic, operational information with 


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