Airworthiness Directives; Rolls-Royce plc RB211-524 Series, -535 Series, RB211 Trent 700 Series, and RB211 Trent 800 Series Turbofan Engines, 61363-61365 [2010-24888]

Download as PDF Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules Rolls-Royce Alert Service Bulletin (ASB) No. RB.211 72–AG272. DEPARTMENT OF TRANSPORTATION Repeat Inspection Requirements Federal Aviation Administration (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. 14 CFR Part 39 Remove Cracked Discs Airworthiness Directives; Rolls-Royce plc RB211–524 Series, –535 Series, RB211 Trent 700 Series, and RB211 Trent 800 Series Turbofan Engines [Docket No. FAA–2010–0993; Directorate Identifier 2010–NE–08–AD] RIN 2120–AA64 (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 hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 (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 VerDate Mar<15>2010 18:28 Oct 04, 2010 Jkt 223001 Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: 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: SUMMARY: 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. We must receive comments on this proposed AD by November 19, 2010. DATES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 ADDRESSES: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 61363 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 https:// 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 https:// 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.). E:\FR\FM\05OCP1.SGM 05OCP1 61364 Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules Costs of Compliance 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: 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 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. 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. You may obtain further information by examining the MCAI in the AD docket. Regulatory Findings 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. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 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. VerDate Mar<15>2010 18:28 Oct 04, 2010 Jkt 223001 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 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 E:\FR\FM\05OCP1.SGM 05OCP1 61365 Federal Register / Vol. 75, No. 192 / Tuesday, October 5, 2010 / Proposed Rules 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 (ii) RB211–524H–T–36 ....................................................... (iii) RB211–535E4–37, E4–B–37 and E4–C–37 ................ (iv) RB211–535E4–B–75 .................................................... (v) RB211–Trent 768–60, 772–60 and 772B–60 ............... (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. 1,150 cycles ..................... 550 cycles ........................ 550 cycles ........................ 550 cycles ........................ 1,250 cycles ..................... 750 cycles ........................ 1,400 cycles ..................... 800 cycles ........................ 800 cycles ........................ 800 cycles ........................ 1,500 cycles ..................... 1,000 cycles ..................... 1,400 cycles. 800 cycles. 800 cycles. 800 cycles. 1,500 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. (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 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. DEPARTMENT OF ENERGY Federal Energy Regulatory Commission 18 CFR Part 260 (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. hsrobinson on DSK69SOYB1PROD with PROPOSALS-1 Other FAA AD Provisions [Docket No. RM07–9–003] 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. VerDate Mar<15>2010 18:28 Oct 04, 2010 Jkt 223001 Revisions to Forms, Statements, and Reporting Requirements for Natural Gas Pipelines September 24, 2010. Federal Energy Regulatory Commission. ACTION: Notice of Proposed Rulemaking; notice providing for reply comments. AGENCY: On June 17, 2010, the Commission issued a Notice of Proposed Rulemaking proposing to SUMMARY: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 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: https:// 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., E:\FR\FM\05OCP1.SGM 05OCP1

Agencies

[Federal Register Volume 75, Number 192 (Tuesday, October 5, 2010)]
[Proposed Rules]
[Pages 61363-61365]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-24888]

-----------------------------------------------------------------------

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 https://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 https://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 https://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.).

[[Page 61364]]

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:

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.

Sec. 39.13 [Amended]

2. The FAA amends Sec. 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:

[[Page 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)
--------------------------------------------------------------------------------------------------------------------------------------------------------
Initial inspection limit if LIFE is
Engine Model Initial inspection threshold less than the initial inspection Repeat inspection interval
threshold
--------------------------------------------------------------------------------------------------------------------------------------------------------
(i) RB211-524G2-T-19, 524G3-T-19 1,150 cycles.......................... 1,400 cycles......................... 1,400 cycles.
and 524H2-T-19.
(ii) RB211-524H-T-36.............. 550 cycles............................ 800 cycles........................... 800 cycles.
(iii) RB211-535E4-37, E4-B-37 and 550 cycles............................ 800 cycles........................... 800 cycles.
E4-C-37.
(iv) RB211-535E4-B-75............. 550 cycles............................ 800 cycles........................... 800 cycles.
(v) RB211-Trent 768-60, 772-60 and 1,250 cycles.......................... 1,500 cycles......................... 1,500 cycles.
772B-60.
(vi) RB211-Trent 892-17, RB211- 750 cycles............................ 1,000 cycles......................... 1,000 cycles.
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.
--------------------------------------------------------------------------------------------------------------------------------------------------------

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 Rolls-Royce 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; e-mail: 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

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