35752 Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 

(e) Unsafe Condition 

This AD was prompted by reports of 

hydraulic fluid contamination (including 

contamination caused by hydraulic fluid in 

its liquid, vapor, and/or solid (coked) form) 

found in the strut forward dry bay. We are 

issuing this AD to detect and correct 

hydraulic fluid contamination of the strut 

forward dry bay, which could result in 

hydrogen embrittlement of the titanium 

forward engine mount bulkhead fittings, and 

consequent inability of the fittings to carry 

engine loads, resulting in engine loss. 

Hydraulic embrittlement also could cause a 

through-crack formation across the fittings 

through which an engine fire could breach 

into the strut, resulting in an uncontained 

strut fire. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

Except as provided by paragraph (h)(1) of 

this AD, at the times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Special 

Attention Service Bulletin 777–54–0028, 

dated May 25, 2012: Do a general visual 

inspection for hydraulic fluid contamination 

(including contamination caused by 

hydraulic fluid in its liquid, vapor, and/or 

solid (coked) form) of the interior of the strut 

forward dry bay, and do all applicable related 

investigative and corrective actions 

(including checking drain lines for blockage 

due to hydraulic fluid coking, and cleaning 

or replacing drain lines to allow drainage) if 

necessary, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–54– 

0028, dated May 25, 2012, except as required 

by paragraph (h)(2) of this AD. Repeat the 

inspection thereafter at the times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 777–54– 

0028, dated May 25, 2012. Except as required 

by paragraph (h)(3) of this AD, do all 

applicable related investigative and 

corrective actions at the times specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Special Attention Service Bulletin 777–54– 

0028, dated May 25, 2012. 

(h) Exceptions to the Service Information 

(1) Where the Compliance time column of 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Service Bulletin 777–54–0028, dated May 25, 

2012, refers to the compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 777–54–0028, dated May 25, 2012, 

specifies to contact Boeing for repair: Except 

as required by paragraph (h)(3) of this AD, at 

the applicable times specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Special 

Attention Service Bulletin 777–54–0028, 

dated May 25, 2012, repair, using a method 

approved in accordance with the procedures 

specified in paragraph (i) of this AD. 

(3) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

777–54–0028, dated May 25, 2012, specifies 

a compliance time of ‘‘within 25 flight-cycles 

or 10 days, whichever occurs first,’’ this AD 

requires compliance within 25 flight cycles 

or 10 days after the most recent inspection 

required by paragraph (g) of this AD, 

whichever occurs first. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(j) Related Information 

For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 777–54–0028, dated May 25, 2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P. O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on May 24, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–13294 Filed 6–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0458; Directorate 

Identifier 2013–NE–19–AD; Amendment 

39–17480; AD 2013–12–03] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Deutschland Ltd & Co KG Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Rolls-Royce Deutschland Ltd & Co KG 

(RRD) BR700–725A1–12 turbofan 

engines with fuel pump tube part 

number FW64852 installed. This AD 

requires removal of the affected fuel 

pump tube and its replacement with a 

part eligible for installation. This AD 

was prompted by the discovery that 

cracks have occurred in the affected fuel 

pump tube between the fuel metering 

unit and the main fuel pump. We are 

issuing this AD to prevent loss of fuel 

supply to the engine, which could result 

in in-flight engine shutdown of one or 

more engines, loss of thrust control and 

damage to the airplane. 

DATES: This AD becomes effective June 

14, 2013. 

We must receive comments on this 

AD by July 29, 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: 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. 

mstockstill on DSK4VPTVN1PROD with RULES

Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 35753 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact, contact Rolls-Royce 

Deutschland Ltd & Co KG, Eschenweg 

11, Dahlewitz, 15827 BlankenfeldeMahlow, Germany; phone: 49 0 33– 

7086–1883; fax: 49 0 33–7086–3276. 

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. 

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 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: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0110, 

dated May 24, 2013, a Mandatory 

Continuing Airworthiness Information 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Cracks have occurred in the Spill Return to 

Fuel Pump Tube between the Fuel Metering 

Unit (FMU) and the main fuel pump. This 

resulted in fuel leaks. This condition, if not 

corrected, could lead to loss of engine fuel 

supply, likely resulting in uncommanded inflight shut down and consequent reduced 

control of the aeroplane. 

We are issuing this AD to prevent loss 

of fuel supply to the engine, which 

could result in in-flight engine 

shutdown of one or more engines, loss 

of thrust control and damage to the 

airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Relevant Service Information 

RRD has issued Service Bulletin SB– 

BR700–73–101847, dated May 17, 2013. 

The actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of Germany, 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 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 

products of the same type design. This 

AD requires removal of affected fuel 

pump tube and its replacement with a 

part eligible for installation. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because of the short compliance 

time requirement. Therefore, we find 

that notice and opportunity for public 

comment before issuing this AD are 

impracticable and that good cause exists 

for making this amendment effective in 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2013–0458; 

Directorate Identifier 2013–NE–19–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 with FAA 

personnel concerning this 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 review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 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); and 

(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. 

mstockstill on DSK4VPTVN1PROD with RULES

35754 Federal Register / Vol. 78, No. 115 / Friday, June 14, 2013 / Rules and Regulations 

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: 

2013–12–03 Rolls-Royce Deutschland Ltd & 

Co KG (Formerly Rolls-Royce 

Deutschland GmbH, formerly BMW 

Rolls-Royce GmbH): Amendment 39– 

17480; Docket No. FAA–2013–0458; 

Directorate Identifier 2013–NE–19–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective June 14, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce 

Deutschland Ltd & Co KG (RRD) BR700– 

725A1–12 turbofan engines with fuel pump 

tube part number (P/N) FW64852 installed. 

(d) Reason 

This AD was prompted by the discovery 

that cracks have occurred in the affected fuel 

pump tube between the fuel metering unit 

and the main fuel pump. We are issuing this 

AD to prevent loss of fuel supply to the 

engine, which could result in in-flight engine 

shutdown of one or more engines, loss of 

thrust control and damage to the airplane. 

(e) Actions and Compliance 

Unless already done, within 15 days after 

the effective date of the AD, remove fuel 

pump tube P/N FW64852 and replace with 

a part eligible for installation. Guidance on 

removing the affected fuel pump tube can be 

found in RRD Service Bulletin SB–BR700– 

73–101847, dated May 17, 2013. 

(f) Installation Prohibition 

After the effective date of this AD, do not 

install fuel pump tube P/N FW64852 onto 

any engine or install an engine with fuel 

pump tube P/N FW64852 onto any aircraft. 

(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, 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 2013–0110, dated May 24, 2013, 

and Rolls-Royce Deutschland Ltd & Co KG 

Service Bulletin No. SB–BR700–73–101847, 

dated May 17, 2013, 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 

33–7086–1883; fax: 49 0 33–7086–3276. 

(4) 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 

June 10, 2013. 

Colleen M. D’Alessandro, 

Assistant Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–14035 Filed 6–13–13; 8:45 am] 

BILLING CODE 4910–13–P 

PENSION BENEFIT GUARANTY 

CORPORATION 

29 CFR Parts 4022 and 4044 

Allocation of Assets in SingleEmployer Plans; Benefits Payable in 

Terminated Single-Employer Plans; 

Interest Assumptions for Valuing and 

Paying Benefits 

AGENCY: Pension Benefit Guaranty 

Corporation. 

ACTION: Final rule. 

SUMMARY: This final rule amends the 

Pension Benefit Guaranty Corporation’s 

regulations on Benefits Payable in 

Terminated Single-Employer Plans and 

Allocation of Assets in Single-Employer 

Plans to prescribe interest assumptions 

under the benefit payments regulation 

for valuation dates in July 2013 and 

interest assumptions under the asset 

allocation regulation for valuation dates 

in the third quarter of 2013. The interest 

assumptions are used for valuing and 

paying benefits under terminating 

single-employer plans covered by the 

pension insurance system administered 

by PBGC. 

DATES: Effective July 1, 2013. 

FOR FURTHER INFORMATION CONTACT: 

Catherine B. Klion 

(Klion.Catherine@PBGC.gov), Assistant 

General Counsel for Regulatory Affairs, 

Pension Benefit Guaranty Corporation, 

1200 K Street NW., Washington, DC 

20005, 202–326–4024. (TTY/TDD users 

may call the Federal relay service toll 

free at 1–800–877–8339 and ask to be 

connected to 202–326–4024.) 

SUPPLEMENTARY INFORMATION: PBGC’s 

regulations on Allocation of Assets in 

Single-Employer Plans (29 CFR Part 

4044) and Benefits Payable in 

Terminated Single-Employer Plans (29 

CFR Part 4022) prescribe actuarial 

assumptions—including interest 

assumptions—for valuing and paying 

plan benefits under terminating singleemployer plans covered by title IV of 

the Employee Retirement Income 

Security Act of 1974. The interest 

assumptions in the regulations are also 

published on PBGC’s Web site (http:// 

www.pbgc.gov). 

The interest assumptions in Appendix 

B to Part 4044 are used to value benefits 

for allocation purposes under ERISA 

section 4044. PBGC uses the interest 

assumptions in Appendix B to Part 4022 

to determine whether a benefit is 

payable as a lump sum and to determine 

the amount to pay. Appendix C to Part 

4022 contains interest assumptions for 

private-sector pension practitioners to 

refer to if they wish to use lump-sum 

interest rates determined using PBGC’s 

historical methodology. Currently, the 

rates in Appendices B and C of the 

benefit payment regulation are the same. 

The interest assumptions are intended 

to reflect current conditions in the 

financial and annuity markets. 

Assumptions under the asset allocation 

regulation are updated quarterly; 

assumptions under the benefit payments 

regulation are updated monthly. This 

final rule updates the benefit payments 

interest assumptions for July 2013 and 

updates the asset allocation interest 

assumptions for the third quarter (July 

through September) of 2013. 

The third quarter 2013 interest 

assumptions under the allocation 

regulation will be 2.60 percent for the 

first 20 years following the valuation 

date and 3.43 percent thereafter. In 

comparison with the interest 

assumptions in effect for the second 

quarter of 2013, these interest 

assumptions represent no change in the 

select period (the period during which 

the select rate (the initial rate) applies), 

an increase of 0.10 percent in the select 

rate, and an increase of 0.23 percent in 

the ultimate rate (the final rate). 

The July 2013 interest assumptions 

under the benefit payments regulation 

will be 1.25 percent for the period 

during which a benefit is in pay status 

and 4.00 percent during any years 

preceding the benefit’s placement in pay 

status. In comparison with the interest 

assumptions in effect for June 2013, 

these interest assumptions represent an 

increase of 0.50 percent in the 

immediate annuity rate and are 

otherwise unchanged. 

mstockstill on DSK4VPTVN1PROD with RULES