Airworthiness Directives; Honeywell International Inc. ALF502L Series and ALF502R Series Turbofan Engines, 26823-26826 [06-4193]

Download as PDF mstockstill on PROD1PC68 with RULES Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Rules and Regulations proportion is determined using the average volume of domestic production and the average volume of imports into the U.S. market over the previous three years. Section 1219.30(c) of the Order provides that at the end of three years after assessment funds began, the Board shall review the production of domestic Hass avocados in the U.S. and the volume of imported Hass avocados on the basis of the amount of assessments collected from producers and importers over the immediately preceding threeyear period. The Board may recommend to the Secretary modification to the Board based on proportion of domestic production and imports supplying the U.S. market. At its January 2006 meeting, the Board reviewed the production for the domestic Hass avocados in the U.S. and the volume of imported Hass avocados over the 2003, 2004, and 2005 calendar years and decided to recommended one additional member and alternate member for importers and one less member and alternate for domestic producers of Hass avocados that are subject to the assessment. The total average combined volume of Hass avocados produced in the U.S. and imported into the U.S. for the 2003, 2004, and 2005 calendar years was 712 million pounds. Of this amount, 53.2 percent was Hass avocados imported into the U.S. and 46.8 percent was domestically produced Hass avocados. Representation on the Board (12) is comprised of: (1) Seven producer members and their alternates; (2) two importer members and their alternates; and, (3) three producer or importer members and their alternates, also known as the ‘‘swing seats.’’ Under the Act and Order the three ‘‘swing seats’’ are allocated so as to reflect as nearly as possible the proportion of domestic production and imports supplying the U.S. market. The proportion is based on the average volume of domestic production and the average volume of imports into the U.S. market over the previous three years. The current 12 member Board is composed of eight producer members and alternates, and four importer members and alternates; meaning (1) Seven producer members and alternates; (2) two importer members and alternates; and, (3) of the three ‘‘swing seats’’ two are currently importer member and alternate seats and one is a producer member and alternate seat. Representation on the Board based on the changes in the production of domestic Hass avocados and the volume of imported Hass avocadoes into the U.S. over the 2003, 2004, and 2005 VerDate Aug<31>2005 15:32 May 08, 2006 Jkt 208001 calendar year results in one additional importer member and alternate and one less producer member and alternate. Accordingly, all of the ‘‘swing seats’’ are importers’ therefore, the 12-member Board will be comprised of seven producer members and alternates and five importer members and alternates. Pursuant to 5 U.S.C. 553, it is found and determined upon good cause that it is impracticable, unnecessary, and contrary to the public interest to give preliminary notice prior to putting this rule into effect and that good cause exists for not postponing the effective date of this rule until 30 days after publication in the Federal Register because the Board adjustment provided for in this interim final rule needs to be effective as soon as possible in order to complete the 2006 Board appointments. List of Subjects in 7 CFR Part 1219 Administrative practice and procedure, Advertising, Consumer information, Hass avocados, Hass avocado promotion, Marketing agreements, Reporting and recordkeeping requirements. For the reasons set forth in the preamble, 7 CFR part 1219 is amended as follows: I PART 1219—HASS AVOCADO PROMOTION, RESEARCH, AND INFORMATION 1. The authority citation for part 1219 continues to read as follows: I Authority: 7 U.S.C. 7801–7813. Subpart C—Rules and Regulations 2. A new § 1219.203 is added to read as follows: I § 1219.203 Reapportionment of membership. Pursuant to § 1219.30(c), the positions authorized in § 1219.30(b)(3) are reapportioned as follows: 3 importer members and their alternates. Dated: May 3, 2006. Kenneth C. Clayton, Acting Administrator, Agricultural Marketing Service. [FR Doc. 06–4316 Filed 5–8–06; 8:45 am] BILLING CODE 3410–02–P PO 00000 Frm 00007 Fmt 4700 Sfmt 4700 26823 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 92–ANE–34–AD; Amendment 39–14584; AD 2006–09–13] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. ALF502L Series and ALF502R Series Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Honeywell International Inc. ALF502L series and ALF502R series turbofan engines. That AD currently establishes stress rupture retirement life limits for certain third stage turbine discs used in conjunction with certain third stage turbine nozzles. This AD brings requirements forward and unchanged, from the previous AD for ALF502R series turbofan engines. Also, this AD establishes new reduced stress rupture retirement life limits for certain part numbers (P/Ns) of third stage turbine disc and shaft assemblies installed in ALF502L series turbofan engines. This AD also requires removing those same parts from service using a drawdown schedule. This AD results from a report of failure of a third stage turbine disc and shaft assembly, leading to turbine blade release and separation of the exhaust nozzle. We are issuing this AD to prevent total loss of engine power, inflight engine shutdown, release of turbine blades, separation of the exhaust nozzle, and possible damage to the airplane. DATES: This AD becomes effective June 13, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of June 13, 2006. ADDRESSES: Contact Honeywell Engines, Systems & Services, Customer Support Center, M/S 26–06/2102–323, P.O. Box 29003, Phoenix, AZ 85038–9003; telephone (800) 601–3099, for the service bulletins identified in this AD. You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service bulletins, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, E:\FR\FM\09MYR1.SGM 09MYR1 26824 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Rules and Regulations FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; telephone: (562) 627–5245, fax: (562) 627–5210. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39 with a proposed airworthiness directive (AD). The proposed AD applies to Honeywell International Inc. ALF502L series and ALF502R series turbofan engines. We published the proposed AD in the Federal Register on November 2, 2005 (70 FR 66302). That action proposed to bring requirements forward and unchanged, from the previous AD for ALF502R series turbofan engines. Also, that action proposed to establish new reduced stress rupture retirement life limits for certain P/Ns of third stage turbine disc and shaft assemblies installed in ALF502L series turbofan engines. That action also proposed to require removing those same parts from service using a drawdown schedule. Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. mstockstill on PROD1PC68 with RULES Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 180 Honeywell International, Inc. ALF502L, ALF502L– 2, ALF502L–2A, ALF502L–2C, ALF502L–3, and ALF502R series turbofan engines of the affected design in the worldwide fleet. We estimate the AD will affect 170 engines installed on airplanes of U.S. registry. We also estimate that it will take about 14 workhours per engine to perform the actions, and that the average labor rate is $65 per workhour. The prorated cost of a replacement third stage turbine disc and shaft assembly is estimated to be $40,000. Based on these figures, we estimate the total parts and labor cost of the AD on U.S. operators to be $6,954,700. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue VerDate Aug<31>2005 15:32 May 08, 2006 Jkt 208001 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 have 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 that this AD: (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) 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 summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 92–ANE–34– AD’’ in your request. 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 Federal Aviation Administration 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. PO 00000 Frm 00008 Fmt 4700 Sfmt 4700 § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–9163 (60 FR 11621, April 3, 1995) and by adding a new airworthiness directive, Amendment 39–14584, to read as follows: I 2006–09–13 Honeywell International Inc. (formerly AlliedSignal, Inc. and Textron Lycoming): Amendment 39–14584. Docket No. 92–ANE–34–AD. Effective Date (a) This AD becomes effective June 13, 2006. Affected ADs (b) This AD supersedes AD 95–04–11. Applicability (c) This AD applies to Honeywell International Inc. (formerly AlliedSignal, Inc. and Textron Lycoming) ALF502L, ALF502L– 2, ALF502L–2A, ALF502L–2C, and ALF502L–3 series turbofan engines with third stage turbine disc and shaft assemblies that have operated in the Honeywell Pre SB No. ALF502L 72–232 configuration. This AD also applies to ALF502R series engines. These engines are installed on, but not limited to, BAe Systems AVRO 146 and Bombardier (Canadair) CL600–1A11 series airplanes. Unsafe Condition (d) This AD results from a report of failure of a third stage turbine disc and shaft assembly, leading to turbine blade release and separation of the exhaust nozzle. We are issuing this AD to prevent total loss of engine power, in-flight engine shutdown, release of turbine blades, separation of the exhaust nozzle, and possible damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. ALF502L Series Turbofan Engines Determination of Third Stage Turbine Disc and Shaft Assembly Drawdown Schedule (f) For ALF502L series turbofan engines, determine if the third stage turbine disc and shaft assembly is currently operating in the Pre SB No. ALF502L 72–232 configuration as follows: (1) If a third stage turbine nozzle assembly, part number (P/N) 2–141–120R56/–57 is installed, then Honeywell SB No. ALF502L 72–232 has been complied with. Proceed to the drawdown schedule in paragraph (h) of this AD. (2) If any other third stage turbine nozzle assembly is installed, then the engine is in the Pre SB No. ALF502L 72–232 configuration. Proceed to the drawdown schedule in paragraph (g) of this AD. E:\FR\FM\09MYR1.SGM 09MYR1 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Rules and Regulations Drawdown Schedule for Third Stage Turbine Disc and Shaft Assemblies That Are Operating in the Pre SB No. ALF502L 72–232 Configuration (g) For ALF502L series turbofan engines, use the drawdown schedule described in the 26825 following Table 1, and replace with serviceable parts: TABLE 1.—DRAWDOWN SCHEDULE FOR THIRD STAGE TURBINE DISC AND SHAFT ASSEMBLIES IN PRE SB ALF502L 72– 232 CONFIGURATION For third stage turbine disc and shaft assembly P/Ns: If hours-in-service (HIS) on the effective date of this AD are: Then remove: 2–143–030–05, 2–143–030–08, 2–143–030– 14, 2–143–030R21, 2–143–030–22, 2–143– 030–23. (1) (2) (3) (4) Within 50 additional HIS. Before reaching 5,250 HIS. Within 250 additional HIS. Before reaching 2,800 HIS. Determination of Drawdown Schedule for Third Stage Turbine Disc and Shaft Assemblies That Have Operated in Pre and Post SB No. ALF502L 72–232 Configurations No. ALF502L 72–232 configuration, do the following: (1) Determine the total HIS accumulated on the third stage turbine disc and shaft assembly at time of installation of third stage turbine nozzle assembly, P/N 2–141–120– R56/–57. (2) If the total is 2,800 HIS or more, use the drawdown schedule in Table 1 of this AD to remove the assembly from service. (h) For ALF502L series turbofan engines, with third stage turbine disc and shaft assemblies converted from Pre SB No. ALF502L 72–232 configuration to Post SB 5,200 5,001 2,551 2,550 or more HIS. to 5,199 HIS. to 5,000 HIS. or fewer HIS. ..................................... .................................... .................................... .................................... (3) If the total is fewer than 2,800 HIS, calculate the remaining service life using paragraphs 2.A. through 2.B.(4)(i) of the Accomplishment Instructions of Honeywell SB No. ALF502 72–0004, Revision 17, dated January 16, 2005. (i) For ALF502L series turbofan engines, use the drawdown schedule described in the following Table 2 to remove the assembly from service: TABLE 2.—DRAWDOWN SCHEDULE FOR THIRD STAGE TURBINE DISC AND SHAFT ASSEMBLIES OPERATED IN PRE AND POST SB NO. ALF502L 72–232 CONFIGURATION For third stage turbine disc and shaft assembly part numbers: If HIS on the effective date of this AD are: Then: (1) 2–143–030–05, 2–143–030–08, 2–143– 030–14. (i) 30,000 or more HIS. .................................... (ii) 27,250 to 29,999 HIS. ................................. (iii) Fewer than 27,250 HIS. ............................. (2) 2–143–030R21, 2–143–030–23 .................. (i) 24,650 or more HIS. .................................... (ii) 22,150 to 24,649 HIS. ................................. (iii) Fewer than 22,150 HIS. ............................. (3) 2–143–030–22 ............................................. (i) 50,000 or more HIS. .................................... (ii) 49,750 to 49,999 HIS. ................................. (iii) Fewer than 49,750 HIS. ............................. Remove within 50 additional HIS. Remove within 250 additional HIS. Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, dated January 16, 2005. Remove within 50 additional HIS. Remove within 250 additional HIS. Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, dated January 16, 2005. Remove within 50 additional HIS. Remove within 250 additional HIS. Remove using Tables 1 through 5 of Honeywell SB No. ALF502 72–0004, Revision 17, dated January 16, 2005. ALF502R Series Turbofan Engines 1995, before accumulating more than 13,300 hours TIS since new, but not to exceed the existing cyclic life limit. (iii) Thereafter, remove disks before accumulating more than 13,300 hours TIS since new, but not to exceed the existing cyclic life limit. (2) For disks that have been installed only with third stage turbine nozzles, P/Ns 2–141– 120–57 or 2–141–120–R56, remove from service as follows: (i) For disks that have accumulated 27,420 or more hours TIS since new on April 13, 1995, within 80 hours TIS after April 13, 1995, but not to exceed the existing cyclic life limit. (ii) For disks that have accumulated less than 27,420 hours TIS since new on April 13, 1995, before accumulating more than 27,500 hours TIS since new, but not to exceed the existing cyclic life limit. mstockstill on PROD1PC68 with RULES Requirements Brought Forward, and Unchanged From AD 95–04–11 (j) For ALF502R series turbofan engines, remove from service and replace with a serviceable part third stage turbine disks, P/Ns 2–143–030–05, 2–143–030–08, and 2– 143–030–14, as follows: (1) For disks that have been installed only with third stage turbine nozzles P/Ns 2–141– 130–52 or 2–141–120–53, remove from service as follows: (i) For disks that have accumulated 13,220 or more hours time in service (TIS) since new on April 13, 1995 (the effective date of AD 95–04–11), within the next 80 hours TIS after December 11, 1990, but not to exceed the existing cyclic life limit. (ii) For disks that have accumulated less than 13,220 hours TIS since new on April 13, VerDate Aug<31>2005 15:32 May 08, 2006 Jkt 208001 PO 00000 Frm 00009 Fmt 4700 Sfmt 4700 (iii) Thereafter, remove disks before accumulating more than 27,500 hours TIS since new, but not to exceed the existing cyclic life limit. (3) For disks that have been installed with both third stage turbine nozzles, P/Ns 2–141– 120–52 or 2–141–120–120–53, and third stage turbine nozzles P/Ns 2–141–120–57 or 2–141–120–R56, remove from service as follows: (i) Determine the prorated hourly life limit using the procedure defined in the Accomplishment Instructions, Section 2.B.(2) of Textron Lycoming SB No. ALF 502 72– 0002, Revision 22, dated December 23, 1992. From this prorated hourly life limit, subtract 80 hours TIS to determine the compliance threshold. (ii) For disks that have equaled or exceeded the compliance threshold on April 13, 1995, E:\FR\FM\09MYR1.SGM 09MYR1 26826 Federal Register / Vol. 71, No. 89 / Tuesday, May 9, 2006 / Rules and Regulations within the next 80 hours TIS, but not to exceed the existing cyclic life limit. (iii) For disks that have accumulated fewer than the compliance threshold on April 13, 1995, before accumulating more than the calculated prorated hourly life limit. (iv) Thereafter, remove disks at or before accumulating the prorated hourly life limit, but not to exceed the existing cyclic life limit. Alternative Methods of Compliance (k) The Manager, Los Angeles Aircraft Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Special Flight Permits incorporation by reference of this service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Rolls-Royce plc, P.O. Box 31, Derby, DE248BJ; UK, telephone: 011–44–1332–242424; fax: 011–44–1332– 249936, for a copy of this service information. You can review copies at the FAA, New England Region, Office of the Regional Counsel, 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/federalregister/cfr/ibr-locations.html. (l) Under 14 CFR part 39.23, we are limiting the special flight permits for this AD by allowing a onetime special flight if the disc life limit has been reached. Related Information (m) Honeywell SB No. ALF/LF A72–1085, Revision 1, dated January 16, 2005, pertains to the subject of this AD. Material Incorporated by Reference (n) You must use the service bulletins listed in Table 3 of this AD to perform the inspections required by this AD. The Director of the Federal Register approved the TABLE 3.—INCORPORATION BY REFERENCE Service bulletin (SB) No. Pages Textron Lycoming SB No. ALF 502 72–0002 ..................................................................... Total Pages: 27 Revision Date Issued in Burlington, Massachusetts, on April 26, 2006. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 06–4193 Filed 5–8–06; 8:45 am] insurance trade or business subject to section 1060, and to the acquisition of insurance contracts through assumption reinsurance. This correction is effective April 10, 2006. DATES: BILLING CODE 4910–13–P FOR FURTHER INFORMATION CONTACT: Mark Weiss, (202) 622–7790 (not a tollfree number). DEPARTMENT OF THE TREASURY SUPPLEMENTARY INFORMATION: Internal Revenue Service The final and temporary regulations (TD 9257) that are the subjects of this correction are under sections 197, 338, 381, and 1060 of the Internal Revenue Code. [TD 9257] RIN 1545–AY49 Application of Section 338 to Insurance Companies; Correction Need for Correction Internal Revenue Service (IRS), Treasury. ACTION: Correcting amendment. mstockstill on PROD1PC68 with RULES AGENCY: As published, TD 9257 contains an error that may prove to be misleading and is in need of clarification. SUMMARY: This document corrects final and temporary regulations (TD 9257) that were published in the Federal Register on Monday, April 10, 2006 (71 FR 17990) applying to a deemed sale or acquisition of an insurance company’s assets pursuant to an election under section 338 of the Internal Revenue Code, to a sale or acquisition of an List of Subjects in 26 CFR Part 1 VerDate Aug<31>2005 15:32 May 08, 2006 Jkt 208001 Income taxes, Reporting and recordkeeping requirements. Correction of Publication Accordingly, 26 CFR part 1 is corrected by making the following correcting amendment: I PO 00000 Frm 00010 December 23, 1992. 3 4–7 8 9–10 11 12–26 27 1 18 22 21 22 21 22 21 17 December 21, 1989. December 23, 1992. September 25, 1992. December 23, 1992. September 25, 1992. December 23, 1992. September 25, 1992. January 16, 2005. 16 17 16 17 November 7, 2003. January 16, 2005. November 7, 2003. January 16, 2003. PART 1—INCOME TAXES Paragraph 1. The authority citation for part 1 continues to read, in part, as follows: I Authority: 26 U.S.C. 7805 * * * I Par. 2. Section 1.338.11T is corrected by revising paragraph (d)(3)(ii)(2) to read as follows: § 1.338–11T Effect of section 338 election on insurance company targets (temporary). Background 26 CFR Part 1 22 2 3 4 5–30 Honeywell SB No. ALF502 72–0004 .................................................................................. Total Pages: 30 1–2 Fmt 4700 Sfmt 4700 * * * * * (d) * * * (3) * * * (ii) * * * (2) B equals old target’s undiscounted unpaid losses (determined under section 846(b)(1) as of the close of the acquisition date; * * * * * Guy R. Traynor, Chief, Publications and Regulations Branch, Legal Processing Division, Associate Chief Counsel, (Procedure and Administration). [FR Doc. 06–4272 Filed 5–8–06; 8:45 am] BILLING CODE 4830–01–P E:\FR\FM\09MYR1.SGM 09MYR1

Agencies

[Federal Register Volume 71, Number 89 (Tuesday, May 9, 2006)]
[Rules and Regulations]
[Pages 26823-26826]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4193]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 92-ANE-34-AD; Amendment 39-14584; AD 2006-09-13]
RIN 2120-AA64

Airworthiness Directives; Honeywell International Inc. ALF502L
Series and ALF502R Series Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Honeywell International Inc. ALF502L series and ALF502R series
turbofan engines. That AD currently establishes stress rupture
retirement life limits for certain third stage turbine discs used in
conjunction with certain third stage turbine nozzles. This AD brings
requirements forward and unchanged, from the previous AD for ALF502R
series turbofan engines. Also, this AD establishes new reduced stress
rupture retirement life limits for certain part numbers (P/Ns) of third
stage turbine disc and shaft assemblies installed in ALF502L series
turbofan engines. This AD also requires removing those same parts from
service using a drawdown schedule. This AD results from a report of
failure of a third stage turbine disc and shaft assembly, leading to
turbine blade release and separation of the exhaust nozzle. We are
issuing this AD to prevent total loss of engine power, in-flight engine
shutdown, release of turbine blades, separation of the exhaust nozzle,
and possible damage to the airplane.

DATES: This AD becomes effective June 13, 2006. The Director of the
Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of June 13, 2006.

ADDRESSES: Contact Honeywell Engines, Systems & Services, Customer
Support Center, M/S 26-06/2102-323, P.O. Box 29003, Phoenix, AZ 85038-
9003; telephone (800) 601-3099, for the service bulletins identified in
this AD.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA. You may examine the service bulletins, at the FAA, New
England Region, Office of the Regional Counsel, 12 New England
Executive Park, Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los
Angeles Aircraft Certification Office,

[[Page 26824]]

FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA
90712-4137; telephone: (562) 627-5245, fax: (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR Part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to Honeywell International Inc. ALF502L series and ALF502R series
turbofan engines. We published the proposed AD in the Federal Register
on November 2, 2005 (70 FR 66302). That action proposed to bring
requirements forward and unchanged, from the previous AD for ALF502R
series turbofan engines. Also, that action proposed to establish new
reduced stress rupture retirement life limits for certain P/Ns of third
stage turbine disc and shaft assemblies installed in ALF502L series
turbofan engines. That action also proposed to require removing those
same parts from service using a drawdown schedule.

Examining the AD Docket

You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.

Comments

We provided the public the opportunity to participate in the
development of this AD. We received no comments on the proposal or on
the determination of the cost to the public.

Conclusion

We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

There are about 180 Honeywell International, Inc. ALF502L, ALF502L-
2, ALF502L-2A, ALF502L-2C, ALF502L-3, and ALF502R series turbofan
engines of the affected design in the worldwide fleet. We estimate the
AD will affect 170 engines installed on airplanes of U.S. registry. We
also estimate that it will take about 14 workhours per engine to
perform the actions, and that the average labor rate is $65 per
workhour. The prorated cost of a replacement third stage turbine disc
and shaft assembly is estimated to be $40,000. Based on these figures,
we estimate the total parts and labor cost of the AD on U.S. operators
to be $6,954,700.

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 have 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 that this AD:
(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) 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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 92-ANE-34-AD'' in your request.

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 Federal Aviation Administration 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 removing Amendment 39-9163 (60 FR
11621, April 3, 1995) and by adding a new airworthiness directive,
Amendment 39-14584, to read as follows:

2006-09-13 Honeywell International Inc. (formerly AlliedSignal, Inc.
and Textron Lycoming): Amendment 39-14584. Docket No. 92-ANE-34-AD.

Effective Date

(a) This AD becomes effective June 13, 2006.

Affected ADs

(b) This AD supersedes AD 95-04-11.

Applicability

(c) This AD applies to Honeywell International Inc. (formerly
AlliedSignal, Inc. and Textron Lycoming) ALF502L, ALF502L-2,
ALF502L-2A, ALF502L-2C, and ALF502L-3 series turbofan engines with
third stage turbine disc and shaft assemblies that have operated in
the Honeywell Pre SB No. ALF502L 72-232 configuration. This AD also
applies to ALF502R series engines. These engines are installed on,
but not limited to, BAe Systems AVRO 146 and Bombardier (Canadair)
CL600-1A11 series airplanes.

Unsafe Condition

(d) This AD results from a report of failure of a third stage
turbine disc and shaft assembly, leading to turbine blade release
and separation of the exhaust nozzle. We are issuing this AD to
prevent total loss of engine power, in-flight engine shutdown,
release of turbine blades, separation of the exhaust nozzle, and
possible damage to the airplane.

Compliance

(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.

ALF502L Series Turbofan Engines

Determination of Third Stage Turbine Disc and Shaft Assembly Drawdown
Schedule

(f) For ALF502L series turbofan engines, determine if the third
stage turbine disc and shaft assembly is currently operating in the
Pre SB No. ALF502L 72-232 configuration as follows:
(1) If a third stage turbine nozzle assembly, part number (P/N)
2-141-120R56/-57 is installed, then Honeywell SB No. ALF502L 72-232
has been complied with. Proceed to the drawdown schedule in
paragraph (h) of this AD.
(2) If any other third stage turbine nozzle assembly is
installed, then the engine is in the Pre SB No. ALF502L 72-232
configuration. Proceed to the drawdown schedule in paragraph (g) of
this AD.

[[Page 26825]]

Drawdown Schedule for Third Stage Turbine Disc and Shaft Assemblies
That Are Operating in the Pre SB No. ALF502L 72-232 Configuration

(g) For ALF502L series turbofan engines, use the drawdown
schedule described in the following Table 1, and replace with
serviceable parts:

Table 1.--Drawdown Schedule for Third Stage Turbine Disc and Shaft
Assemblies in Pre SB ALF502L 72-232 Configuration
------------------------------------------------------------------------
If hours-in-
For third stage turbine disc and service (HIS) on
shaft assembly P/Ns: the effective date Then remove:
of this AD are:
------------------------------------------------------------------------
2-143-030-05, 2-143-030-08, 2- (1) 5,200 or more Within 50
143-030-14, 2-143-030R21, 2-143- HIS.. additional HIS.
030-22, 2-143-030-23. (2) 5,001 to 5,199 Before reaching
HIS.. 5,250 HIS.
(3) 2,551 to 5,000 Within 250
HIS.. additional HIS.
(4) 2,550 or fewer Before reaching
HIS.. 2,800 HIS.
------------------------------------------------------------------------

Determination of Drawdown Schedule for Third Stage Turbine Disc and
Shaft Assemblies That Have Operated in Pre and Post SB No. ALF502L 72-
232 Configurations

(h) For ALF502L series turbofan engines, with third stage
turbine disc and shaft assemblies converted from Pre SB No. ALF502L
72-232 configuration to Post SB No. ALF502L 72-232 configuration, do
the following:
(1) Determine the total HIS accumulated on the third stage
turbine disc and shaft assembly at time of installation of third
stage turbine nozzle assembly, P/N 2-141-120-R56/-57.
(2) If the total is 2,800 HIS or more, use the drawdown schedule
in Table 1 of this AD to remove the assembly from service.
(3) If the total is fewer than 2,800 HIS, calculate the
remaining service life using paragraphs 2.A. through 2.B.(4)(i) of
the Accomplishment Instructions of Honeywell SB No. ALF502 72-0004,
Revision 17, dated January 16, 2005.
(i) For ALF502L series turbofan engines, use the drawdown
schedule described in the following Table 2 to remove the assembly
from service:

Table 2.--Drawdown Schedule for Third Stage Turbine Disc and Shaft
Assemblies Operated In Pre and Post SB No. ALF502L 72-232 Configuration
------------------------------------------------------------------------
If HIS on the
For third stage turbine disc and effective date of Then:
shaft assembly part numbers: this AD are:
------------------------------------------------------------------------
(1) 2-143-030-05, 2-143-030-08, (i) 30,000 or more Remove within 50
2-143-030-14. HIS.. additional HIS.
(ii) 27,250 to Remove within 250
29,999 HIS.. additional HIS.
(iii) Fewer than Remove using
27,250 HIS.. Tables 1 through
5 of Honeywell SB
No. ALF502 72-
0004, Revision
17, dated January
16, 2005.
(2) 2-143-030R21, 2-143-030-23.. (i) 24,650 or more Remove within 50
HIS.. additional HIS.
(ii) 22,150 to Remove within 250
24,649 HIS.. additional HIS.
(iii) Fewer than Remove using
22,150 HIS.. Tables 1 through
5 of Honeywell SB
No. ALF502 72-
0004, Revision
17, dated January
16, 2005.
(3) 2-143-030-22................ (i) 50,000 or more Remove within 50
HIS.. additional HIS.
(ii) 49,750 to Remove within 250
49,999 HIS.. additional HIS.
(iii) Fewer than Remove using
49,750 HIS.. Tables 1 through
5 of Honeywell SB
No. ALF502 72-
0004, Revision
17, dated January
16, 2005.
------------------------------------------------------------------------

ALF502R Series Turbofan Engines

Requirements Brought Forward, and Unchanged From AD 95-04-11

(j) For ALF502R series turbofan engines, remove from service and
replace with a serviceable part third stage turbine disks, P/Ns 2-
143-030-05, 2-143-030-08, and 2-143-030-14, as follows:
(1) For disks that have been installed only with third stage
turbine nozzles P/Ns 2-141-130-52 or 2-141-120-53, remove from
service as follows:
(i) For disks that have accumulated 13,220 or more hours time in
service (TIS) since new on April 13, 1995 (the effective date of AD
95-04-11), within the next 80 hours TIS after December 11, 1990, but
not to exceed the existing cyclic life limit.
(ii) For disks that have accumulated less than 13,220 hours TIS
since new on April 13, 1995, before accumulating more than 13,300
hours TIS since new, but not to exceed the existing cyclic life
limit.
(iii) Thereafter, remove disks before accumulating more than
13,300 hours TIS since new, but not to exceed the existing cyclic
life limit.
(2) For disks that have been installed only with third stage
turbine nozzles, P/Ns 2-141-120-57 or 2-141-120-R56, remove from
service as follows:
(i) For disks that have accumulated 27,420 or more hours TIS
since new on April 13, 1995, within 80 hours TIS after April 13,
1995, but not to exceed the existing cyclic life limit.
(ii) For disks that have accumulated less than 27,420 hours TIS
since new on April 13, 1995, before accumulating more than 27,500
hours TIS since new, but not to exceed the existing cyclic life
limit.
(iii) Thereafter, remove disks before accumulating more than
27,500 hours TIS since new, but not to exceed the existing cyclic
life limit.
(3) For disks that have been installed with both third stage
turbine nozzles, P/Ns 2-141-120-52 or 2-141-120-120-53, and third
stage turbine nozzles P/Ns 2-141-120-57 or 2-141-120-R56, remove
from service as follows:
(i) Determine the prorated hourly life limit using the procedure
defined in the Accomplishment Instructions, Section 2.B.(2) of
Textron Lycoming SB No. ALF 502 72-0002, Revision 22, dated December
23, 1992. From this prorated hourly life limit, subtract 80 hours
TIS to determine the compliance threshold.
(ii) For disks that have equaled or exceeded the compliance
threshold on April 13, 1995,

[[Page 26826]]

within the next 80 hours TIS, but not to exceed the existing cyclic
life limit.
(iii) For disks that have accumulated fewer than the compliance
threshold on April 13, 1995, before accumulating more than the
calculated prorated hourly life limit.
(iv) Thereafter, remove disks at or before accumulating the
prorated hourly life limit, but not to exceed the existing cyclic
life limit.

Alternative Methods of Compliance

(k) The Manager, Los Angeles Aircraft Certification Office, has
the authority to approve alternative methods of compliance for this
AD if requested using the procedures found in 14 CFR 39.19.

Special Flight Permits

(l) Under 14 CFR part 39.23, we are limiting the special flight
permits for this AD by allowing a onetime special flight if the disc
life limit has been reached.

Related Information

(m) Honeywell SB No. ALF/LF A72-1085, Revision 1, dated January
16, 2005, pertains to the subject of this AD.

Material Incorporated by Reference

(n) You must use the service bulletins listed in Table 3 of this
AD to perform the inspections required by this AD. The Director of
the Federal Register approved the incorporation by reference of this
service bulletin in accordance with 5 U.S.C. 552(a) and 1 CFR part
51. Contact Rolls-Royce plc, P.O. Box 31, Derby, DE248BJ; UK,
telephone: 011-44-1332-242424; fax: 011-44-1332-249936, for a copy
of this service information. You can review copies at the FAA, New
England Region, Office of the Regional Counsel, 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.

Table 3.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service bulletin (SB) No. Pages Revision Date
----------------------------------------------------------------------------------------------------------------
Textron Lycoming SB No. ALF 502 72-0002.. 1-2 22 December 23, 1992.
Total Pages: 27
3 18 December 21, 1989.
4-7 22 December 23, 1992.
8 21 September 25, 1992.
9-10 22 December 23, 1992.
11 21 September 25, 1992.
12-26 22 December 23, 1992.
27 21 September 25, 1992.
Honeywell SB No. ALF502 72-0004.......... 1 17 January 16, 2005.
Total Pages: 30
2 16 November 7, 2003.
3 17 January 16, 2005.
4 16 November 7, 2003.
5-30 17 January 16, 2003.
----------------------------------------------------------------------------------------------------------------

Issued in Burlington, Massachusetts, on April 26, 2006.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 06-4193 Filed 5-8-06; 8:45 am]
BILLING CODE 4910-13-P

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