Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules 61363 

Rolls-Royce Alert Service Bulletin (ASB) No. 

RB.211 72–AG272. 

Repeat Inspection Requirements 

(2) At each engine shop visit after 

accumulating 1,500 cycles since the last 

inspection of the LP turbine stage 1, 2 and 

3 discs, repeat the inspections specified in 

paragraph (e)(1) of this AD. 

Remove Cracked Discs 

(3) If you find cracks, remove the disc from 

service. 

Definitions 

(f) For the purpose of this AD, 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 does not constitute an engine 

shop visit. 

FAA AD Differences 

(g) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and or service information as follows 

in that while the MCAI compliance requires 

action at a current shop visit, this AD 

requires compliance at the next shop visit 

after the effective date of this AD. 

Other FAA AD Provisions 

(h) Alternative Methods of Compliance 

(AMOCs): The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(i) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2009–0244, 

dated November 9, 2009, and Rolls-Royce plc 

ASB No. RB.211–72–AG272 for related 

information. Contact Rolls-Royce plc., P.O. 

Box 31, Derby, DE24 8BJ, United Kingdom; 

phone: 011 44 1332 242424, fax: 011 44 1332 

249936; e-mail: tech.help@rolls-royce.com, 

for a copy of this service information or 

download the publication from https:// 

www.aeromanager.com. 

(j) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: ian.dargin@faa.gov; telephone (781) 

238–7178; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

September 27, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–24887 Filed 10–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0993; Directorate 

Identifier 2010–NE–08–AD] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–524 Series, –535 Series, 

RB211 Trent 700 Series, and RB211 

Trent 800 Series 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 the 

products listed above. This proposed 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued 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: 

Cracking has been found on the inner wall 

between intermediate dilution chutes on a 

total of five front combustion liners of the 

standard corresponding to Rolls-Royce 

RB211 Service Bulletin No. 72–D133. The 

lives of two of these liners were confirmed 

to be below the currently valid borescope 

inspection interval. Ultimately, crack 

propagation could result in hot gas breakout 

with potential of downstream component 

distress and multiple turbine blade release 

beyond containment capabilities of the 

engine casings. Thus, cracking of this nature 

constitutes a potentially unsafe condition. 

Since Rolls-Royce Service Bulletin No. 72– 

E902 introduces further developments of 

Rolls-Royce RB211 Service Bulletin No. 72– 

D133, engines incorporating Rolls-Royce 

RB211 Service Bulletin No. 72–E902 are also 

considered to be potentially affected and are 

therefore included in the applicability of this 

AD. 

We are proposing this AD to detect 

cracks in the front combustion liner, 

which could result in hot section 

distress, uncontained multiple blade 

release and possible damage to the 

aircraft. 

DATES: We must receive comments on 

this proposed AD by November 19, 

2010. 

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. 

Contact Rolls-Royce plc, P.O. Box 31, 

Derby, DE24 8BJ, United Kingdom; 

telephone: 011–44–1332–242424; fax: 

011–44–1332–249936 for the service 

information identified in this proposed 

AD. 

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 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (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: Ian 

Dargin, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: ian.dargin@faa.gov; telephone 

(781) 238–7178; fax (781) 238–7199. 

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–2010–0993; Directorate Identifier 

2010–NE–08–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.). 


hsrobinson on DSK69SOYB1PROD with PROPOSALS-1
61364 Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules 

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 

Airworthiness Directive 2009–0243R1, 

dated November 26, 2009 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

Cracking has been found on the inner wall 

between intermediate dilution chutes on a 

total of five front combustion liners of the 

standard corresponding to Rolls-Royce 

RB211 Service Bulletin No. 72–D133. The 

lives of two of these liners were confirmed 

to be below the currently valid borescope 

inspection interval. Ultimately, crack 

propagation could result in hot gas breakout 

with potential of downstream component 

distress and multiple turbine blade release 

beyond containment capabilities of the 

engine casings. Thus, cracking of this nature 

constitutes a potentially unsafe condition. 

Since Rolls-Royce Service Bulletin No. 72– 

E902 introduces further developments of 

Rolls-Royce RB211 Service Bulletin No. 72– 

D133, engines incorporating Rolls-Royce 

RB211 Service Bulletin No. 72–E902 are also 

considered to be potentially affected and are 

therefore included in the applicability of this 

AD. 

This AD requires a change to the initial 

and repeat borescope inspection intervals for 

the front combustion liner. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Rolls-Royce plc has issued Alert 

Service Bulletin RB.211–72–AF458, 

Revision 4, dated March 9, 2009. 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 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 United 

Kingdom, 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 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other products of the 

same type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 239 products of U.S. 

registry. We also estimate that it would 

take about 1.5 work-hours per product 

to comply with this proposed AD. The 

average labor rate is $85 per work-hour. 

No parts are required so parts would 

cost about $0 per product. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$30,473. 

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); and 

3. 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 AD: 

Rolls-Royce plc: Docket No. FAA–2010– 

0993; Directorate Identifier 2010–NE– 

08–AD. 

Comments Due Date 

(a) We must receive comments by 

November 19, 2010. 

Affected Airworthiness Directives (ADs) 

(b) None. 

Applicability 

(c) This AD applies to Rolls-Royce (RR) 

engine models RB211–524G2–T–19, RB211– 

524G3–T–19, RB211–524H2–T–19, RB211– 

524H–T–36, RB211–535E4–37, RB211– 

535E4–B–37, RB211–535E4–C–37, RB211– 

535E4–B–75, RB211 Trent 768–60, RB211 

Trent 772–60, RB211 Trent 772B–60, RB211– 

Trent 892–17, RB211–Trent 884–17, RB211– 

Trent 884B–17, RB211–Trent 877–17, 

RB211–Trent 875–17, RB211–Trent 892–17, 

RB211–Trent 892B–17 and RB211–Trent 

895–17 engines, that incorporate RR Service 

Bulletins (SBs) RB.211–72–D133 or RB.211– 

72–E902. These engines are installed on, but 

not limited to Airbus A330 series airplanes; 

Boeing 747–400 series, 757 series, 767 series, 

and 777 series airplanes; and Tupolev Tu204 

series airplanes. 

Reason 

(d) This AD results from: 

Cracking has been found on the inner wall 

between intermediate dilution chutes on a 

total of five front combustion liners of the 

standard corresponding to Rolls-Royce 

RB211 Service Bulletin No. 72–D133. The 

lives of two of these liners were confirmed 

to be below the currently valid borescope 

inspection interval. Ultimately, crack 

propagation could result in hot gas breakout 

with potential of downstream component 

distress and multiple turbine blade release 

beyond containment capabilities of the 

engine casings. Thus, cracking of this nature 

constitutes a potentially unsafe condition. 

Since Rolls-Royce Service Bulletin No. 72– 

E902 introduces further developments of 

Rolls-Royce RB211 Service Bulletin No. 72– 

D133, engines incorporating Rolls-Royce 

RB211 Service Bulletin No. 72–E902 are also 

considered to be potentially affected and are 


hsrobinson on DSK69SOYB1PROD with PROPOSALS-1
Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules 61365 

therefore included in the applicability of this 

AD. 

We are issuing this AD to detect cracks in 

the front combustion liner, which could 

result in hot section distress, uncontained 

multiple blade release and possible damage 

to the aircraft. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

Inspection 

(f) Perform a borescope inspection as 

specified in section 3. Accomplishment 

instructions, subsection A. Borescope 

Inspection of Rolls-Royce RB211 Alert 

Service Bulletin (ASB) RB.211–72–AF458 

Revision 4, dated March 9, 2009, before the 

limits specified below: 

Initial Inspection 

(1) If the engine has a combustion liner 

installed with: 

(i) A LIFE on the effective date of this AD, 

that is equal to or greater than the initial 

inspection threshold specified in column (b) 

in Table 1 of this AD, or 

(ii) A LIFE on the effective date of this AD, 

that is not known, carry out the action 

specified in paragraph (f) of this AD within 

250 cycles after the effective date of this AD. 

(iii) A LIFE on the effective date of this AD, 

that is less than the initial inspection 

threshold specified in column (b) of Table 1 

of this AD, perform the borescope inspection 

before the LIFE exceeds the limit specified in 

column (c) of Table 1 of this AD. 

Repeat Inspection 

(2) Thereafter, repeat the borescope 

inspection at intervals not to exceed the 

cycles specified in column (d) of Table 1 or 

this AD. 

TABLE 1—INITIAL INSPECTION THRESHOLDS AND LIMITS

Column (a) Column (b) Column (c) Column (d) 

Engine Model Initial inspection threshold 

Initial inspection limit if 

LIFE is less than the initial 

inspection threshold 

Repeat inspection interval 

(i) RB211–524G2–T–19, 524G3–T–19 and 524H2–T–19 1,150 cycles ..................... 1,400 cycles ..................... 1,400 cycles. 

(ii) RB211–524H–T–36 ....................................................... 550 cycles ........................ 800 cycles ........................ 800 cycles. 

(iii) RB211–535E4–37, E4–B–37 and E4–C–37 ................ 550 cycles ........................ 800 cycles ........................ 800 cycles. 

(iv) RB211–535E4–B–75 .................................................... 550 cycles ........................ 800 cycles ........................ 800 cycles. 

(v) RB211–Trent 768–60, 772–60 and 772B–60 ............... 1,250 cycles ..................... 1,500 cycles ..................... 1,500 cycles. 

(vi) RB211–Trent 892–17, RB211–Trent 884–17, RB211– 

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

875–17, RB211–Trent 892B–17 and RB211–Trent 

895–17 engines.

750 cycles ........................ 1,000 cycles ..................... 1,000 cycles. 

Definitions 

(g) This AD defines LIFE as the lowest of: 

(1) The number of cycles-since-new of the 

combustion liner, or 

(2) The number of cycles-in-service (CIS) 

since replacement of the inner wall, or 

(3) The number of CIS since the 

combustion liner was last inspected in 

accordance with section 3. Accomplishment 

instructions, subsection A. Borescope 

Inspection of Rolls-Royce RB211 Series 

Propulsion System Series Non-Modification 

Service Bulletin No. RB.211–72–AF458 

Revision 2, dated December 21, 2007. 

FAA AD Differences 

(h) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) and or service information in that the 

MCAI AD applies to the RB211 Trent 772C– 

60 engine, which isn’t type certificated in the 

United States. 

Other FAA AD Provisions 

(i) Alternative Methods of Compliance 

(AMOCs): The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Refer to MCAI European Aviation Safety 

Agency Airworthiness Directive 2009– 

0243R1, dated November 26, 2009, and RollsRoyce ASB RB.211–72–AF458, Revision 4, 

dated March 9, 2009, for related information. 

Contact Rolls-Royce plc, P.O. Box 31, Derby, 

DE24 8BJ, United Kingdom; telephone: 011– 

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

for a copy of this service information. 

(k) Contact Ian Dargin, Aerospace Engineer, 

Engine Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; email: ian.dargin@faa.gov; telephone (781) 

238–7178; fax (781) 238–7199, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

September 27, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–24888 Filed 10–4–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF ENERGY 

Federal Energy Regulatory 

Commission 

18 CFR Part 260 

[Docket No. RM07–9–003] 

Revisions to Forms, Statements, and 

Reporting Requirements for Natural 

Gas Pipelines 

September 24, 2010. 

AGENCY: Federal Energy Regulatory 

Commission. 

ACTION: Notice of Proposed Rulemaking; 

notice providing for reply comments. 

SUMMARY: On June 17, 2010, the 

Commission issued a Notice of 

Proposed Rulemaking proposing to 

revise certain financial reporting forms 

required to be filed by natural gas 

companies (FERC Form Nos. 2, 2–A, 

and 3–Q). The Commission is providing 

interested parties an opportunity to file 

reply comments on the Notice of 

Proposed Rulemaking. 

DATES: Reply comments are due October 

25, 2010. 

ADDRESSES: You may submit reply 

comments, identified by Docket No. 

RM07–9–003, by any of the following 

methods: 

• Agency Web Site: http:// 

www.ferc.gov. Documents created 

electronically using word processing 

software should be filed in native 

applications or print-to-PDF format and 

not in a scanned format. 

• Mail/Hand Delivery: Commenters 

unable to file comments electronically 

must mail or hand deliver an original 

and 14 copies of their comments to: 

Federal Energy Regulatory Commission, 

Office of the Secretary, 888 First Street, 

NE., Washington, DC 20426. 

FOR FURTHER INFORMATION CONTACT: 

Brian Holmes (Technical Information), 

Office of Enforcement, Federal Energy 

Regulatory Commission, 888 First 

Street, NE., Washington, DC 20426, 

Telephone: (202) 502–6008, E-mail: 

brian.holmes@ferc.gov. 

Robert Sheldon (Technical Information), 

Office of Energy Market Regulation, 

Federal Energy Regulatory 

Commission, 888 First Street, NE., 


hsrobinson on DSK69SOYB1PROD with PROPOSALS-1