Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 11719 

interface, which could result in reduced 

structural integrity of the airframe. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection With Reduced 

Compliance Times and Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (f)(1) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008), with reduced compliance times and 

revised service information. For Airbus 

Model A330–200 series airplanes, as 

identified in paragraph (c) of this AD, on 

which Modification 45012 has been 

embodied in production: Within the 

applicable compliance times specified in 

paragraphs (g)(1), (g)(2), (g)(3), and (g)(4) of 

this AD, do the HFEC inspection for cracking, 

and corrective actions as applicable; and 

modify the upper shell structure of the 

fuselage; in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–53–3152, 

Revision 3, dated December 22, 2011. Do all 

applicable corrective actions before further 

flight. 

(1) For airplanes pre-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD. 

(i) Prior to 24,400 total flight cycles or 

85,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(2) For airplanes pre-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Prior to 18,900 total flight cycles or 

122,900 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 25,400 

total flight cycles. 

(3) For airplanes post-modification 48827 

with short range utilization: At the later of 

the times specified in paragraph (g)(3)(i) or 

(g)(3)(ii) of this AD. 

(i) Prior to 16,400 total flight cycles or 

57,400 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(4) For airplanes post-modification 48827 

with long range utilization: At the later of the 

times specified in paragraph (g)(4)(i) or 

(g)(4)(ii) of this AD. 

(i) Prior to 12,700 total flight cycles or 

82,700 total flight hours, whichever occurs 

first. 

(ii) Within 12 months after the effective 

date of this AD without exceeding 17,100 

total flight cycles or 94,700 total flight hours, 

whichever occurs first. 

(h) Retained Modification With Revised 

Formatting 

This paragraph restates the requirements of 

paragraph (f)(2) of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008). For Airbus Model A330–200 and 

A340–300 series airplanes as identified in 

paragraph (c) of this AD, on which 

Modification 45012 has not been embodied 

in production: At the later of the compliance 

times specified in paragraphs (h)(1) and 

(h)(2) of this AD, modify the upper shell 

structure of the fuselage, in accordance with 

the Accomplishment Instructions of Airbus 

Service Bulletin A330–53–3157 or Airbus 

Service Bulletin A340–53–4163, both dated 

July 5, 2006, as applicable. 

(1) For the airplanes identified in 

paragraphs (h)(1)(i) and (h)(1)(ii) of this AD. 

(i) For Model A330–200 series airplanes, 

prior to 6,600 total flight cycles. 

(ii) For Model A340–300 series airplanes, 

prior to 14,000 total flight cycles. 

(2) Within 90 days after August 21, 2008 

(the effective date of AD 2008–14–17, 

Amendment 39–15612 (73 FR 40958, July 17, 

2008)). 

(i) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the service information 

specified in paragraph (i)(1), (i)(2), or (i)(3) of 

this AD. 

(1) Airbus Mandatory Service Bulletin 

A330–53–3152, dated April 10, 2007. 

(2) Airbus Mandatory Service Bulletin 

A330–53–3152, Revision 1, dated May 5, 

2009. 

(3) Airbus Mandatory Service Bulletin 

A330–53–3152, Revision 2, dated July 27, 

2011. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1138; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer, use these actions if they are 

FAA-approved. Corrective actions are 

considered FAA-approved if they were 

approved by the State of Design Authority (or 

its delegated agent, or by the DAH with a 

State of Design Authority’s design 

organization approval, as applicable). You 

are required to ensure the product is 

airworthy before it is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0158, dated July 22, 2013, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0121. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.com. You may 

view this service information at the 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. 

Issued in Renton, Washington, on February 

14, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–04501 Filed 2–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0953; Directorate 

Identifier 2013–NE–32–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc 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 

Rolls-Royce plc (RR) RB211 Trent 875– 

17, 877–17, 884–17, 884B–17, 892–17, 

892B–17, and 895–17 turbofan engines. 

The proposed AD was prompted by 

thin-walled low pressure (LP) turbine 

bearing support and exhaust case 

assemblies having been delivered into 

service. This proposed AD would 

require inspection of the affected LP 

turbine bearing support and exhaust 

case assembly and, if necessary, its 

replacement with a part eligible for 

installation. We are proposing this AD 

to prevent failure of the LP turbine 

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11720 Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 

bearing support and exhaust case 

assembly, which could lead to engine 

separation and damage to the airplane. 

DATES: We must receive comments on 

this proposed AD by May 2, 2014. 

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 proposed AD, contact Rolls-Royce 

plc, Corporate Communications, P.O. 

Box 31, Derby, England, DE248BJ; 

phone: 011–44–1332–242424; fax: 011– 

44–1332–249936; email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp; Web site: https:// 

www.aeromanager.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–2013– 

0953; 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: 

Eugene Triozzi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7148; fax: 781–238– 

7199; email: eugene.triozzi@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–2013–0953; Directorate Identifier 

2013–NE–32–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 review 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– 

0223, dated September 19, 2013 

(referred to hereinafter as ‘‘the MCAI’’), 

to correct an unsafe condition for the 

specified products. The MCAI states: 

Rolls-Royce has identified that limitations 

in the drawing definition for the Trent 800 

low pressure (LP) Turbine Bearing Support 

and Exhaust Case assembly (EIPC 72–52–51, 

03–300, also known as the Tail Bearing 

Housing or TBH) may have resulted in thin 

wall section parts being delivered into 

service. Further analysis has concluded that 

under certain circumstances, the structural 

integrity of a thin walled part may be 

insufficient to withstand a fan blade failure 

event. 

This condition, if not detected and 

corrected, could, in case of fan blade failure, 

lead to a loss of integrity of the TBH and 

leave the engine unsupported at the rear 

mount, possibly resulting in damage to, or 

reduced control of, the aeroplane. 

This condition, if not addressed, may 

allow failure of the LP turbine bearing 

support and exhaust case assembly, 

which could lead to engine separation 

and damage to the airplane. You may 

examine the MCAI in the AD docket on 

the Internet at http:// 

www.regulations.gov by searching for 

and locating it in Docket No. FAA– 

2013–0953. 

Relevant Service Information 

RR has issued Alert Service Bulletin 

(ASB) No. RB.211–72–AG644, dated 

April 30, 2013. The ASB provides 

guidance for rework or inspection of the 

LP turbine bearing support and exhaust 

case assembly. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of the United 

Kingdom 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 inspection 

of the affected LP turbine bearing 

support and exhaust case assembly and, 

if necessary, its replacement with a part 

eligible for installation. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 110 engines installed 

on airplanes of U.S. registry. We also 

estimate that it would take about 1 hour 

per product to comply with this 

proposed AD. The average labor rate is 

$85 per hour. Required parts cost about 

$9,250. Based on these figures, we 

estimate the cost of the proposed AD on 

U.S. operators to be $92,600. 

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. 

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Federal Register / Vol. 79, No. 41 / Monday, March 3, 2014 / Proposed Rules 11721 

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. Amend § 39.13 by adding the 

following new airworthiness directive 

(AD): 

Rolls-Royce plc: Docket No. FAA–2013– 

0953; Directorate Identifier 2013–NE– 

32–AD. 

(a) Comments Due Date 

We must receive comments by May 2, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Rolls-Royce plc (RR) 

RB211 Trent 875–17, 877–17, 884–17, 884B– 

17, 892–17, 892B–17, and 895–17 turbofan 

engines, except those that have been 

reworked in accordance with RR Service 

Bulletin (SB) RB.211–72–G604, dated March 

18, 2013. 

(d) Reason 

This AD was prompted by identification by 

RR of limitations in the drawing definition 

for the Trent 800 low pressure (LP) turbine 

bearing support and exhaust case assembly 

which resulted in thin wall section parts 

being delivered into service. We are issuing 

this AD to prevent failure of the LP turbine 

bearing support and exhaust case assembly, 

which could lead to engine separation and 

damage to the airplane. 

(e) Actions and Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) For engines that have an LP turbine 

bearing support and exhaust case assembly 

identified by part number (P/N) and serial 

number (S/N) in Table 1 to paragraph (e) of 

this AD, installed, at the next engine shop 

visit after the effective date of this AD, but 

not later than June 30, 2017, replace the 

assembly with one that is eligible for 

installation. 

(2) For engines with an LP turbine bearing 

support and exhaust case assembly not 

identified by P/N and S/N in Table 1 to 

paragraph (e) of this AD, installed, at the next 

piece part exposure of the LP turbine bearing 

support and exhaust case assembly after the 

effective date of AD: 

(i) Inspect the hub to conical panel weld 

line thickness using paragraphs 3.B.(3)(a) 

through 3.B.(3)(d)(iii) of RR Alert Service 

Bulletin (ASB) RB.211–72–AG644, dated 

April 30, 2013; and 

(ii) Inspect the hub to conical panel flange 

thickness using paragraphs 3.B.(4)(a) through 

3.B.(4)(c)(v) of RR ASB RB.211–72–AG644, 

dated April 30, 2013. 

(iii) If the LP turbine bearing support and 

exhaust case assembly does not pass the 

inspections required by paragraphs (e)(2)(i) 

and (e)(2)(ii) of this AD, replace the LP 

turbine bearing support and exhaust case 

assembly with one that is eligible for 

installation. 

TABLE 1 TO PARAGRAPH (e)—LP TURBINE BEARING SUPPORT AND EXHAUST CASE ASSEMBLY P/NS AND

S/NS

P/N S/N 

FK31446 118–01 

FK31446 209–01 

FK31446 216–01 

FK31446 232–01 

FK32232 113–01 

FK32085 268–01 

FK32085 269–01 

FK31446 022–01 

FK31446 028–01 

(f) Definitions 

The following definitions apply for the 

purpose of this AD: 

(1) An LP turbine bearing support and 

exhaust case assembly is eligible for 

installation if it has passed the inspections of 

paragraphs (e)(2)(i) and (e)(2)(ii) of this AD; 

or has been reworked in accordance with RR 

Service Bulletin (SB) RB.211–72–G604, dated 

March 18, 2013. 

(2) ‘‘Piece part exposure’’ occurs whenever 

the LP turbine bearing support and exhaust 

case assembly is sufficiently exposed to do 

the inspections required by paragraphs 

(e)(2)(i) and (e)(2)(ii) of this AD. 

(3) An ‘‘engine shop visit’’ is the induction 

of an engine into the shop for maintenance 

involving the separation of pairs of major 

mating engine flanges, except that the 

separation of engine flanges solely for the 

purposes of transportation without 

subsequent engine maintenance is not an 

engine shop visit. 

(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 Eugene Triozzi, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7148; fax: 781–238–7199; 

email: eugene.triozzi@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2013–0223, dated 

September 19, 2013, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2013–0953. 

(3) RR SB No. RB.211–72–G604, dated 

March 18, 2013, which is not incorporated by 

reference in this AD, can be obtained from 

Rolls-Royce plc using the contact information 

in paragraph (h)(4) of this AD. 

(4) For service information identified in 

this AD, contact Rolls-Royce plc, Corporate 

Communications, P.O. Box 31, Derby, 

England, DE248BJ; phone: 011–44–1332– 

242424; fax: 011–44–1332–249936; email: 

http://www.rolls-royce.com/contact/ 

civil_team.jsp; Web site: https:// 

www.aeromanager.com. 

(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 

February 20, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–04350 Filed 2–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

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