Airworthiness Directives; Rolls-Royce plc RB211-524 Series Turbofan Engines, 46550-46552 [E8-18102]

Download as PDF 46550 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–0036; Directorate Identifier 2007–NE–22–AD; Amendment 39– 15636; AD 2008–16–18] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce plc RB211–524 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: Recently an RB211 HP turbine disc has been found with a crack which had propagated further than expected from the risk model that was used to establish the original inspection. We are issuing this AD to detect cracks that could cause the high pressure (HP) turbine disc to fail and result in uncontained failure of the engine. DATES: This AD becomes effective September 15, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of September 15, 2008. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: jlentini on PROD1PC65 with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 24, 2007 (72 FR VerDate Aug<31>2005 15:34 Aug 08, 2008 Jkt 214001 60293). That NPRM proposed to correct an unsafe condition for the specified products. The Civil Aviation Authority (CAA), which is the aviation authority for the United Kingdom, has issued United Kingdom Airworthiness Directive G–2006–0002, dated February 13, 2006, to correct an unsafe condition for the specified products. The CAA AD states: A population of HP turbine discs that were manufactured between 1989–1999 and which were subject to possible machining anomalies, were believed to have an increased chance of suffering from cooling air hole cracking, compared to the general fleet population of HP turbine discs. As a result of this risk, Rolls-Royce issued NonModification Service Bulletin (NMSB) 72– C816, recommending in-service inspections of the subject discs. Recently an RB211 HP turbine disc has been found with a crack which had propagated further than expected from the risk model that was used to establish the original inspection defined in the above NMSB; This has led to the need for a revision of the original inspection requirements. An HP turbine disc fracture would be uncontained and create a potential unsafe condition. Accordingly, this AD introduces revised inspection requirements to reflect the increased risk of HP turbine disc cracking and potential disc fracture. You may obtain further information by examining the CAA AD in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. The commenter supports the NPRM. Editorial Change for Clarity We changed the paragraph layering in paragraph (e) of the regulatory text to clarify the requirements for disks that have a serial number in Table 1 of this AD and disks that don’t have a serial number in Table 1 of this AD. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 72 engines of U.S. registry. We also estimate that it will take about 10 workhours per product to comply with this AD. The average labor rate is $80 per work-hour. Required parts will cost about $15,000 per product. Based on these figures, we estimate the total cost PO 00000 Frm 00022 Fmt 4700 Sfmt 4700 of the proposed AD to U.S. operators to be $1,137,600. Our cost estimate is exclusive of possible warranty coverage. 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 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 AD and placed it in the AD docket. 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 AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is provided in the ADDRESSES section. Comments will be E:\FR\FM\11AUR1.SGM 11AUR1 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: I PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: I Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–16–18 Rolls-Royce plc: Amendment 39–15636. Docket No. FAA–2007–0036; Directorate Identifier 2007–NE–22–AD. Effective Date (a) This airworthiness directive (AD) becomes effective September 15, 2008. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce (RR) RB211–524 series turbofan engines with certain high pressure (HP) turbine discs installed. These engines are installed on, but not limited to, Boeing 747 series and 767 series airplanes and Lockheed L1011 series airplanes. Reason (d) Recently an RB211 HP turbine disc has been found with a crack which had propagated further than expected from the risk model that was used to establish the original inspection. We are issuing this AD to detect cracks that could cause the HP turbine disc to fail and result in uncontained failure of the engine. jlentini on PROD1PC65 with RULES Actions and Compliance (e) Unless already done, do the following actions. (1) Carry out the eddy current inspection as detailed in Section 3—Accomplishment Instructions of Rolls-Royce NMSB RB.211– 72–AE718, dated January 24, 2006. (2) Carry out the eddy current inspection in accordance with the following schedule: (i) The HP disc serial numbers listed in Table 1 are to be inspected as follows: TABLE 1—HP DISC SERIAL NUMBERS BY PART NUMBER Part No. Serial No. UL29473 ........... UL29473 ........... VerDate Aug<31>2005 LAQDY6043 LAQDY6048 15:34 Aug 08, 2008 Jkt 214001 TABLE 1—HP DISC SERIAL NUMBERS BY PART NUMBER—Continued Part No. UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29473 UL29472 UL29472 UL29472 UL29472 UL29472 UL29472 UL29472 UL24994 UL24994 UL24994 UL24994 UL24994 UL24994 UL24994 UL24994 UL24994 UL23166 UL23166 UL23166 UL23166 FK24790 FK24790 Serial No. ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... ........... LAQDY6079 LDRCZ10057 LDRCZ10264 LDRCZ10415 LDRCZ11402 LDRCZ11425 LDRCZ11497 LDRCZ11663 LDRCZ11679 LDRCZ12301 LDRCZ12308 LDRCZ12316 LDRCZ12319 LQDY6957 LQDY9075 LQDY9084 LQDY9557 LQDY9906 LQDY9956 LQDY9970 LQDY9985 LQDY9125 LQDY9554 LQDY9582 LQDY9895 LQDY9910 LQDY9947 LQDY9960 LQDY6777 LQDY6792 LQDY6859 LQDY6860 LQDY6866 LQDY6869 LQDY6934 LQDY6946 LQDY6963 LQDY6745 LQDY6846 LQDY6848 LQDY6954 LDRCZ12492 LDRCZ12694 (A) For all RB211–524 engine marks except RB211–524D4 variants: (1) If the HP turbine disc cycles are greater than 6150 cycles since new on the effective date of this AD, inspect the HP turbine disc within 500 cycles after the effective date of this AD. (2) If the HP turbine disc cycles are less than 6150 cycles since new on the effective date of this AD, inspect the disc by whichever is the soonest of the conditions below: (i) Prior to reaching 6650 cycles since new. The HP turbine disc life at inspection must be greater than 700 cycles since new. (ii) At next shop visit where the HP turbine rotor is removed from the Combustor Outer Case and the HP turbine disc life is greater than 700 cycles since new. If a HP turbine disc that meets these cyclic life criteria is currently at shop visit, and if, at the effective date of this Airworthiness Directive, it has not yet been reinstalled into the Combustion Outer Case, then the HP turbine disc must be inspected in accordance with the requirements of this Airworthiness Directive at the current shop visit. PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 46551 (B) For all RB211–524D4 engine mark variants: (1) If the HP turbine disc cycles are greater than 5000 cycles since new on the effective date of this AD, inspect the HP turbine disc within 500 cycles after the effective date of this AD. (2) If the HP turbine disc cycles were less than 5000 cycles since new on the effective date of this AD, inspect the HP turbine disc by whichever is the soonest of the conditions below: (i) Prior to reaching 5500 cycles since new. The HP turbine disc life at inspection must be greater than 700 cycles since new. (ii) At the next shop visit where the HP turbine rotor is removed from the Combustor Outer Case and the HP turbine disc life is greater than 700 cycles since new. If a HP turbine disc that meets these cyclic life criteria is currently at shop visit, and if, at the effective date of this Airworthiness Directive, it has not yet been reinstalled into the Combustion Outer Case, then the HP turbine disc must be inspected in accordance with the requirements of this Airworthiness Directive at the current shop visit. (ii) For all other HP turbine discs specified in the Applicability of this Directive but not listed in Table 1 of this AD. (A) Inspect the HP turbine disc at next shop visit where the HP turbine rotor is removed from the Combustor Outer Case and the HP turbine disc life is greater than 700 cycles since new. If a HP turbine disc that meets these cyclic life criteria is currently at shop visit, and if, at the effective date of this Airworthiness Directive, it has not yet been reinstalled into the Combustion Outer Case, then the HP turbine disc must be inspected in accordance with the requirements of this Airworthiness Directive at the current shop visit. (B) If a HP turbine disc has previously passed the inspection to Rolls-Royce NMSB 72–C816 or the focused inspection carried out in accordance with Rolls-Royce TS594– J Overhaul Process Manual Task 70–00–00– 200–223 at greater than 700 cycles since new, then either of these inspections meets the requirements of this Airworthiness Directive. FAA AD Differences (f) Wherever the MCAI AD specifies 24 November 2005, this AD specifies the effective date of this AD. Other FAA AD Provisions (g) 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 (h) Refer to the Civil Aviation Authority Airworthiness Directive G–2006–0002, dated February 13, 2006, for related information. (i) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199, for more information about this AD. E:\FR\FM\11AUR1.SGM 11AUR1 46552 Federal Register / Vol. 73, No. 155 / Monday, August 11, 2008 / Rules and Regulations Material Incorporated by Reference (j) You must use Rolls-Royce Service Bulletin RB.211–72–AE718, dated January 24, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Rolls-Royce plc, PO Box 31, Derby, England; telephone: 011 44 1332– 242424; fax: 011 44 1332–249936. (3) You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or 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: https:// www.archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on July 31, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–18102 Filed 8–8–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2008–0308; Airspace Docket No. 08–AEA–19] Modification of Class E Airspace; Rome, NY Federal Aviation Administration (FAA), DOT. ACTION: Final rule. jlentini on PROD1PC65 with RULES AGENCY: 15:34 Aug 08, 2008 On January 1, 2007, the Oneida County Airport, Utica, NY was permanently closed and operations moved to the Griffiss Airfield. The local area Terminal VFR Radar Service Area (TRSA) is being revised and there is a requirement for the base of the TRSA to not be below the associated Class E airspace. A careful analysis of operations determined a need for additional Class E airspace extending upward from 700 feet above the surface of the Earth to enhance the management, safety and efficiency of air traffic services in the area. This modification would satisfy that requirement. On May 8, 2008, the FAA published in the Federal Register a notice of proposed rulemaking (NPRM) to establish additional Class E airspace at Griffiss Airfield (73 FR 26047). Interested parties were invited to participate in this rulemaking effort by submitting written comments on this proposal to the FAA. No comments objecting to the proposal were received, and the rule is being promulgated as proposed. Designations for Class E Airspace designations for airspace areas extending upward from 700 feet or more above the surface of the Earth are published in Paragraph 6005 of FAA Order 7400.9R, signed August 15, 2007, and effective September 15, 2007, which is incorporated by reference in 14 CFR 71.1. The Class E airspace designation listed in this document will be published subsequently in the Order. The Rule SUMMARY: This action modifies Class E Airspace at Rome, New York to support the amendment of the current Terminal Visual Flight Rule (VFR) Radar Service Area (TRSA) and to allow for a lower vectoring altitude known as the Minimum Vectoring Altitude (MVA) for vectoring of both VFR and Instrument Flight Rule (IFR) aircraft around the Rome, NY area. This action will enhance the safety and airspace management around the Griffiss Airport area. DATES: Effective Date: 0901 UTC, November 20, 2008. FOR FURTHER INFORMATION CONTACT: Daryl Daniels, Airspace Specialist, System Support Group, Eastern Service Center, Air Traffic Organization, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320; telephone (404) 305–5581. SUPPLEMENTARY INFORMATION: VerDate Aug<31>2005 History Jkt 214001 This amendment to part 71 of the Federal Aviation Regulations (14 CFR part 71) modifies Class E airspace at Rome, NY. To provide for a lower MVA in the Rome, NY, area for VFR and IFR operations, it establishes Class E airspace upward from 700 feet above the surface of the Earth within a 15-mile radius of Griffiss Airfield and within a 26-mile radius of the airport to the southeast and south of the airport. The FAA has determined that this final rule only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. It, therefore, (1) is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a Regulatory Evaluation as the anticipated impact is so minimal. Since this is a PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 routine matter that will only affect air traffic procedures and air navigation, it is certified that this rule, when promulgated, will not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the United States Code. 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. This rulemaking is promulgated under the authority described in subtitle VII, part A, subpart I, section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it modifies Class E airspace at Rome, NY. Lists of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (Air). Adoption of the Amendment: In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: I PART 71—DESIGNATION OF CLASS A, CLASS B, CLASS C, CLASS D, AND CLASS E AIRSPACE AREAS; AIRWAYS; ROUTES; AND REPORTING POINTS 1. The authority citation for part 71 will continue to read as follows: I Authority: 49 U.S.C. 106(g); 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9R, Airspace Designations and Reporting Points, signed August 15, 2007, effective September 15, 2007, is amended as follows: I Paragraph 6005 Class E Airspace Areas Extending Upward from 700 feet or More Above the Surface of the Earth. * * * * * AEA NY E5 Rome, NY [REVISED] Griffiss Airfield, NY (Lat. 43°14′02″ N., long. 75°24′25″ W.) That airspace extending upward from 700 feet above the surface of the Earth within a 15-mile radius of Griffiss Airfield and within a 26-mile radius of the airport extending clockwise from a 125° bearing to a 200° bearing from the airport. * E:\FR\FM\11AUR1.SGM * * 11AUR1 * *

Agencies

[Federal Register Volume 73, Number 155 (Monday, August 11, 2008)]
[Rules and Regulations]
[Pages 46550-46552]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-18102]



[[Page 46550]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0036; Directorate Identifier 2007-NE-22-AD; 
Amendment 39-15636; AD 2008-16-18]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce plc RB211-524 Series 
Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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:

    Recently an RB211 HP turbine disc has been found with a crack 
which had propagated further than expected from the risk model that 
was used to establish the original inspection.

We are issuing this AD to detect cracks that could cause the high 
pressure (HP) turbine disc to fail and result in uncontained failure of 
the engine.

DATES: This AD becomes effective September 15, 2008. The Director of 
the Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of September 15, 2008.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on October 24, 2007 (72 
FR 60293). That NPRM proposed to correct an unsafe condition for the 
specified products. The Civil Aviation Authority (CAA), which is the 
aviation authority for the United Kingdom, has issued United Kingdom 
Airworthiness Directive G-2006-0002, dated February 13, 2006, to 
correct an unsafe condition for the specified products. The CAA AD 
states:

    A population of HP turbine discs that were manufactured between 
1989-1999 and which were subject to possible machining anomalies, 
were believed to have an increased chance of suffering from cooling 
air hole cracking, compared to the general fleet population of HP 
turbine discs. As a result of this risk, Rolls-Royce issued Non-
Modification Service Bulletin (NMSB) 72-C816, recommending in-
service inspections of the subject discs.
    Recently an RB211 HP turbine disc has been found with a crack 
which had propagated further than expected from the risk model that 
was used to establish the original inspection defined in the above 
NMSB; This has led to the need for a revision of the original 
inspection requirements.
    An HP turbine disc fracture would be uncontained and create a 
potential unsafe condition. Accordingly, this AD introduces revised 
inspection requirements to reflect the increased risk of HP turbine 
disc cracking and potential disc fracture.

You may obtain further information by examining the CAA AD in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supports the 
NPRM.

Editorial Change for Clarity

    We changed the paragraph layering in paragraph (e) of the 
regulatory text to clarify the requirements for disks that have a 
serial number in Table 1 of this AD and disks that don't have a serial 
number in Table 1 of this AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the change described previously. We determined that this change 
will not increase the economic burden on any operator or increase the 
scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 72 engines of U.S. registry. 
We also estimate that it will take about 10 work-hours per product to 
comply with this AD. The average labor rate is $80 per work-hour. 
Required parts will cost about $15,000 per product. Based on these 
figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $1,137,600. Our cost estimate is exclusive of possible 
warranty coverage.

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 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 AD and placed it in the AD docket.

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 AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be

[[Page 46551]]

available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2008-16-18 Rolls-Royce plc: Amendment 39-15636. Docket No. FAA-2007-
0036; Directorate Identifier 2007-NE-22-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective 
September 15, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce (RR) RB211-524 series 
turbofan engines with certain high pressure (HP) turbine discs 
installed. These engines are installed on, but not limited to, 
Boeing 747 series and 767 series airplanes and Lockheed L1011 series 
airplanes.

Reason

    (d) Recently an RB211 HP turbine disc has been found with a 
crack which had propagated further than expected from the risk model 
that was used to establish the original inspection.

    We are issuing this AD to detect cracks that could cause the HP 
turbine disc to fail and result in uncontained failure of the 
engine.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Carry out the eddy current inspection as detailed in Section 
3--Accomplishment Instructions of Rolls-Royce NMSB RB.211-72-AE718, 
dated January 24, 2006.
    (2) Carry out the eddy current inspection in accordance with the 
following schedule:
    (i) The HP disc serial numbers listed in Table 1 are to be 
inspected as follows:

             Table 1--HP Disc Serial Numbers by Part Number
------------------------------------------------------------------------
               Part No.                            Serial No.
------------------------------------------------------------------------
UL29473...............................  LAQDY6043
UL29473...............................  LAQDY6048
UL29473...............................  LAQDY6079
UL29473...............................  LDRCZ10057
UL29473...............................  LDRCZ10264
UL29473...............................  LDRCZ10415
UL29473...............................  LDRCZ11402
UL29473...............................  LDRCZ11425
UL29473...............................  LDRCZ11497
UL29473...............................  LDRCZ11663
UL29473...............................  LDRCZ11679
UL29473...............................  LDRCZ12301
UL29473...............................  LDRCZ12308
UL29473...............................  LDRCZ12316
UL29473...............................  LDRCZ12319
UL29473...............................  LQDY6957
UL29473...............................  LQDY9075
UL29473...............................  LQDY9084
UL29473...............................  LQDY9557
UL29473...............................  LQDY9906
UL29473...............................  LQDY9956
UL29473...............................  LQDY9970
UL29473...............................  LQDY9985
UL29472...............................  LQDY9125
UL29472...............................  LQDY9554
UL29472...............................  LQDY9582
UL29472...............................  LQDY9895
UL29472...............................  LQDY9910
UL29472...............................  LQDY9947
UL29472...............................  LQDY9960
UL24994...............................  LQDY6777
UL24994...............................  LQDY6792
UL24994...............................  LQDY6859
UL24994...............................  LQDY6860
UL24994...............................  LQDY6866
UL24994...............................  LQDY6869
UL24994...............................  LQDY6934
UL24994...............................  LQDY6946
UL24994...............................  LQDY6963
UL23166...............................  LQDY6745
UL23166...............................  LQDY6846
UL23166...............................  LQDY6848
UL23166...............................  LQDY6954
FK24790...............................  LDRCZ12492
FK24790...............................  LDRCZ12694
------------------------------------------------------------------------

    (A) For all RB211-524 engine marks except RB211-524D4 variants:
    (1) If the HP turbine disc cycles are greater than 6150 cycles 
since new on the effective date of this AD, inspect the HP turbine 
disc within 500 cycles after the effective date of this AD.
    (2) If the HP turbine disc cycles are less than 6150 cycles 
since new on the effective date of this AD, inspect the disc by 
whichever is the soonest of the conditions below:
    (i) Prior to reaching 6650 cycles since new. The HP turbine disc 
life at inspection must be greater than 700 cycles since new.
    (ii) At next shop visit where the HP turbine rotor is removed 
from the Combustor Outer Case and the HP turbine disc life is 
greater than 700 cycles since new. If a HP turbine disc that meets 
these cyclic life criteria is currently at shop visit, and if, at 
the effective date of this Airworthiness Directive, it has not yet 
been reinstalled into the Combustion Outer Case, then the HP turbine 
disc must be inspected in accordance with the requirements of this 
Airworthiness Directive at the current shop visit.
    (B) For all RB211-524D4 engine mark variants:
    (1) If the HP turbine disc cycles are greater than 5000 cycles 
since new on the effective date of this AD, inspect the HP turbine 
disc within 500 cycles after the effective date of this AD.
    (2) If the HP turbine disc cycles were less than 5000 cycles 
since new on the effective date of this AD, inspect the HP turbine 
disc by whichever is the soonest of the conditions below:
    (i) Prior to reaching 5500 cycles since new. The HP turbine disc 
life at inspection must be greater than 700 cycles since new.
    (ii) At the next shop visit where the HP turbine rotor is 
removed from the Combustor Outer Case and the HP turbine disc life 
is greater than 700 cycles since new. If a HP turbine disc that 
meets these cyclic life criteria is currently at shop visit, and if, 
at the effective date of this Airworthiness Directive, it has not 
yet been reinstalled into the Combustion Outer Case, then the HP 
turbine disc must be inspected in accordance with the requirements 
of this Airworthiness Directive at the current shop visit.
    (ii) For all other HP turbine discs specified in the 
Applicability of this Directive but not listed in Table 1 of this 
AD.
    (A) Inspect the HP turbine disc at next shop visit where the HP 
turbine rotor is removed from the Combustor Outer Case and the HP 
turbine disc life is greater than 700 cycles since new. If a HP 
turbine disc that meets these cyclic life criteria is currently at 
shop visit, and if, at the effective date of this Airworthiness 
Directive, it has not yet been reinstalled into the Combustion Outer 
Case, then the HP turbine disc must be inspected in accordance with 
the requirements of this Airworthiness Directive at the current shop 
visit.
    (B) If a HP turbine disc has previously passed the inspection to 
Rolls-Royce NMSB 72-C816 or the focused inspection carried out in 
accordance with Rolls-Royce TS594-J Overhaul Process Manual Task 70-
00-00-200-223 at greater than 700 cycles since new, then either of 
these inspections meets the requirements of this Airworthiness 
Directive.

FAA AD Differences

    (f) Wherever the MCAI AD specifies 24 November 2005, this AD 
specifies the effective date of this AD.

Other FAA AD Provisions

    (g) 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

    (h) Refer to the Civil Aviation Authority Airworthiness 
Directive G-2006-0002, dated February 13, 2006, for related 
information.
    (i) Contact Jason Yang, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; 
telephone (781) 238-7747; fax (781) 238-7199, for more information 
about this AD.

[[Page 46552]]

Material Incorporated by Reference

    (j) You must use Rolls-Royce Service Bulletin RB.211-72-AE718, 
dated January 24, 2006, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce plc, PO Box 31, Derby, England; telephone: 011 44 1332-
242424; fax: 011 44 1332-249936.
    (3) You may review copies at the FAA, New England Region, 12 New 
England Executive Park, Burlington, MA; or 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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on July 31, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-18102 Filed 8-8-08; 8:45 am]
BILLING CODE 4910-13-P
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