Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 611-8, Tay 620-15, Tay 650-15, and Tay 651-54 Series Turbofan Engines, 3936-3939 [E7-1218]

Download as PDF 3936 Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations by adding the following new airworthiness directive (AD): 2007–02–24 Boeing: Amendment 39–14911. Docket No. FAA–2006–24410; Directorate Identifier 2005–NM–261–AD. Effective Date (a) This AD becomes effective March 5, 2007. Modification Affected ADs (b) None. Applicability (c) This AD applies to all Boeing Model 747–100, 747–100B, 747–100B SUD, 747– 200B, 747–200C, 747–200F, 747–300, 747– 400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category. Unsafe Condition (d) This AD results from analysis by the manufacturer that the radial lap splices of the station (STA) 2360 aft pressure bulkhead are subject to widespread fatigue damage. We are issuing this AD to detect and correct cracking of the bulkhead web at multiple sites along the radial lap splice, which could join together to form cracks of critical length, and result in rapid decompression and loss of control of 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. rmajette on PROD1PC67 with RULES Repetitive Inspections (f) Before the airplane accumulates 28,000 total flight cycles, or within 18 months after the effective date of this AD, whichever occurs later: Do a high-frequency eddy current inspection for cracking of the web of the STA 2360 aft pressure bulkhead around the fastener heads in the critical fastener rows in the web lap joints, from the Y-chord to the inner ring; in accordance with Part 2, ‘‘Access and Inspection,’’ of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2561, dated September 22, 2005. It is not necessary to inspect the web lap joints in the areas common to the Y-ring outer chord. Repeat the inspection thereafter at intervals not to exceed 2,000 flight cycles until the modification in paragraph (h) of this AD is done. Repair (g) If any cracking is found during any inspection required by paragraph (f) of this AD: Before further flight, do the applicable action in paragraph (g)(1) or (g)(2) of this AD. (1) If the cracking is within certain limits specified in Boeing Alert Service Bulletin 747–53A2561, dated September 22, 2005 (referencing the structural repair manual), do the repair in accordance with the Accomplishment Instructions of the alert service bulletin. (2) If the cracking is more than certain limits specified in Boeing Alert Service Bulletin 747–53A2561, dated September 22, 2005, or if the alert service bulletin specifies to ask Boeing for repair data: Repair the VerDate Aug<31>2005 14:38 Jan 26, 2007 Jkt 211001 cracking using a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. (h) Before the airplane accumulates 35,000 total flight cycles or within 18 months after the effective date of this AD, whichever occurs later: Modify the aft pressure bulkhead using a method approved by the Manager, Seattle ACO. For a repair method to be approved by the Manager, Seattle ACO, as required by this paragraph, the Manager’s approval letter must specifically refer to this AD. Doing this modification terminates the repetitive inspection requirements of paragraph (f) of this AD. Note 1: As of the effective date of this AD, the manufacturer has not informed us of any intent to produce the required terminating modification; however, the regulations do not prevent others from doing so. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 747–53A2561, dated September 22, 2005, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., Room PL–401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741–6030, or go to http:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on January 19, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–1212 Filed 1–26–07; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24777; Directorate Identifier 2006–NE–19–AD; Amendment 39–14913; AD 2007–03–02] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 611–8, Tay 620–15, Tay 650–15, and Tay 651–54 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for RollsRoyce Deutschland Ltd & Co KG (RRD) Tay 611–8, Tay 620–15, Tay 650–15, and Tay 651–54 series turbofan engines, with certain low pressure (LP) compressor modules installed. This AD requires an ultrasonic inspection (UI) of LP compressor fan blades for cracks, within 30 days after the effective date of the AD on certain serial number (SN) Tay 650–15 engines. This AD also requires initial and repetitive UIs of LP compressor fan blades on all engines. This AD also requires, for Tay 650–15 and Tay 651–54 engines, UIs of LP compressor fan blades whenever the blade set is removed from one engine and installed on a different engine. This AD results from a report that a set of LP compressor fan blades failed before reaching the LP compressor fan blade full published life limit. We are issuing this AD to prevent LP compressor fan blades from failing due to blade root cracks, leading to uncontained engine failure and damage to the airplane. DATES: This AD becomes effective March 5, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of March 5, 2007. ADDRESSES: You can get the service information identified in this AD from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D–15827 Dahlewitz, Germany; telephone 49 (0) 33–7086– 1768; fax 49 (0) 33–7086–3356. You may examine the AD docket on the Internet at http://dms.dot.gov or in Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC. FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England E:\FR\FM\29JAR1.SGM 29JAR1 Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations Executive Park, Burlington, MA 01803; telephone (781) 238–7747; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to RRD Tay 611–8, Tay 620–15, Tay 650–15, and Tay 651–54 series turbofan engines, with certain low pressure (LP) compressor modules installed. We published the proposed AD in the Federal Register on June 27, 2006 (71 FR 36493). That action proposed to require a UI of LP compressor fan blades for cracks, within 30 days after the effective date of the AD on certain serial number (SN) Tay 650– 15 engines. That action also proposed to require repetitive UIs of LP compressor fan blades on all engines. That action also proposed to require, for Tay 650– 15 and Tay 651–54 engines, UIs of LP compressor fan blades whenever the blade set is removed from one engine and installed on a different engine. Examining the AD Docket You may examine the docket that contains the AD, any comments received, and any final disposition in person at the Docket Management Facility Docket Offices between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Office (telephone (800) 647–5227) is located on the plaza level of the Department of Transportation Nassif Building at the street address stated in ADDRESSES. Comments will be available in the AD docket shortly after the DMS receives them. rmajette on PROD1PC67 with RULES Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. RRD Request To Change Compliance Paragraphs (h)(1) and (h)(2) RRD requests that we change the compliance schedule for Tay 650–15 and Tay 651–54 engines in proposed AD paragraph (h)(1), from ‘‘at every shop visit for any reason or before reaching every 4,000 flight hours-since-last fan blade UI, whichever occurs first’’ to ‘‘at every engine shop visit for any reason or before reaching every 10,000 flight hours-since-last fan blade UI, whichever occurs first.’’ RRD also requests that we change the compliance schedule for Tay 620–15 engines in proposed AD paragraph (h)(2) from ‘‘before reaching every 8,000 flight hours but no later than every 10 years since-last-fan-blade UI, whichever occurs first’’ to ‘‘before reaching every 10,000 flight hours for airline operation, VerDate Aug<31>2005 14:38 Jan 26, 2007 Jkt 211001 and before reaching 8,000 flight hours but no later than every 10 years sincelast-fan-blade UI, whichever occurs first, for non-airline operation.’’ RRD bases these changes on their Engine Management Program. We agree with the intent of the requested changes to proposed AD paragraph (h)(1). We changed that paragraph, and added subparagraphs to clarify the initial inspection requirements in the AD. Regarding paragraph (h)(2), we do not agree with having different inspection schedules for airline and non-airline operations. However, we changed paragraph (h)(2) to paragraph (h)(2)(iii), to read ‘‘before reaching every 10,000 flight hours but no later than every 10 years since-lastfan-blade UI, whichever occurs first’’. We feel that this drawdown schedule will take care of both low- and highutilization of Tay 620–15 engines. Air Transport Association Request To Change Compliance Paragraph (h)(1) Air Transport Association (ATA) requests that we change the compliance schedule in paragraph (h)(1) from ‘‘at every engine shop visit for any reason or before reaching every 4,000 flight hours-since-last fan blade UI, whichever occurs first’’ to ‘‘at every engine shop visit for any reason or before reaching every 12 years or 15,000 flight hourssince-last fan blade UI, whichever occurs first’’. ATA states that this schedule is described in the Engine Management Program for Tay 651–54 engines installed in the Boeing 727 airplanes. We do not agree. The intent of proposed AD paragraph (h)(1) is to UI Tay 650–15 and Tay 651–54 engines at all scheduled and unscheduled shop visits, using RRD SB No. TAY–72–1442, Revision 3, dated November 26, 2003. Also, the intent of the paragraph is to parallel the SB requirement of an initial UI within 3 months after the SB issue date. We did change paragraph (h) and added subparagraphs as described under the first comment above. Request To Change Compliance Paragraph (h)(3) One commenter requests that we change the Tay 611–8 compliance schedule in proposed AD paragraph (h)(3). The commenter requests that we call out an initial UI inspection to be done at the next engine mid-life or overhaul inspection after the effective date of this AD. The commenter also requests that we call out repetitive UI inspections to be done before reaching every 8,000 flight hours but no later than every 10 years since-last-fan blade UI, whichever occurs first. These changes would prevent many airplanes PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 3937 from being immediately grounded, upon issuance of the AD. We agree with the commenter’s intent. We changed and added paragraphs (h) through (h)(2)(iii) to clarify the initial inspection requirements in the AD, and to incorporate the compliance schedule changes. Request To Add LP Compressor Fan Blade Part Numbers ATA requests that we include LP compressor fan blade part numbers in the AD. We agree and added the part numbers to the AD. Incorrect Supplemental Type Certificate (STC) Number In paragraph (c) of the proposed AD, STC number SA842SW is incorrect. That STC applies to a Cessna Model 414 airplane. We corrected the STC No. in paragraph (c) of this AD to SA8472SW, which applies to a Boeing 727 airplane. Conclusion We have carefully reviewed the available data, including the comments received, and determined that air safety and the public interest require adopting the AD with the changes described previously. We have determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. Costs of Compliance We estimate that this AD will affect about 1,000 RRD Tay 611–8, Tay 620– 15, Tay 650–15, and Tay 651–54 series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 4 work-hours per engine to perform an inspection, and that the average labor rate is $80 per work-hour. Required parts will cost about $95,000 per LP compressor fan disk and $140,000 per set of LP compressor fan blades. We estimate that 5 percent or 50 engines will require replacing the LP compressor fan disc and LP compressor fan blade set. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $11,750,000. 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 E:\FR\FM\29JAR1.SGM 29JAR1 3938 Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations 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 at the address listed under ADDRESSES. 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: I JR30649 .............................................................................................................................................. JR31702 .............................................................................................................................................. JR31983 .............................................................................................................................................. (d) This AD results from a report that a set of LP compressor fan blades failed before reaching the LP compressor fan blade full published life limit. We are issuing this AD to prevent LP compressor fan blades from failing due to blade root cracks, leading to uncontained engine failure and 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. rmajette on PROD1PC67 with RULES Ultrasonic Inspection (UI) of LP Compressor Fan Blades for Certain Tay 650–15 Engines That Have Not Yet Had UI of the LP Compressor Fan Blades (f) For Tay 650–15 engines, serial numbers 17201, 17202, 17226, 17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530, 17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805, and 17806 that have not yet had UI of the LP compressor fan blades: VerDate Aug<31>2005 14:38 Jan 26, 2007 Jkt 211001 Effective Date (a) This airworthiness directive (AD) becomes effective March 5, 2007. Affected ADs (b) None. Applicability (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611–8 and Tay 620–15 turbofan engines with low pressure (LP) compressor module part number (P/N) MO1100AA or P/N MO1100AB installed, and Tay 650–15 and Tay 651–54 turbofan engines with LP compressor module P/N MO1300AA or P/N MO1300AB installed. These engines are installed on, but not limited to, Fokker F.28 Mark 0070 and 0100 airplanes, Boeing 727 airplanes modified in accordance with Supplemental Type Certificate No. SA8472SW, and Gulfstream G–IV airplanes. The following P/N LP compressor fan blades are installed in these modules: Tay 620–15 LP compressor fan blade P/Ns Tay 611–8 LP compressor fan blade P/Ns Unsafe Condition 2007–03–02 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce plc): Amendment 39–14913. Docket No. FAA–2006–24777; Directorate Identifier 2006–NE–19–AD. Tay 650–15 LP compressor fan blade P/Ns Tay 651–54 LP compressor fan blade P/Ns JR30649 ...... JR31702 ...... JR31983 ...... JR33863 ...... JR33864 ...... ..................... JR31911 ...... JR31912 ...... JR35120 ...... JR35121 ...... JR33865. JR33866. JR31911. JR31912. JR35120. JR35121. UI of LP Compressor Fan Blades for All Tay Engines (i) Initial UI at next shop visit for any reason but no later than 6 months after the effective date of this AD, whichever occurs first. (ii) Repetitive UIs at every engine shop visit for any reason but before reaching every 10,000 flight hours-since-last fan blade UI, whichever occurs first. (2) For Tay 611–8 and Tay 620–15 engines: (i) Initial UI at next shop visit for engine mid-life inspection or overhaul, but no later than 12 months after the effective date of this AD, whichever occurs first. (ii) For Tay 611–8 engines, repetitive UIs before reaching every 8,000 flight hours but no later than every 10 years since-last-fanblade UI, whichever occurs first. (iii) For Tay 620–15 engines, repetitive UIs before reaching every 10,000 flight hours but no later than every 10 years since-last-fanblade UI, whichever occurs first. (h) Perform UI of the LP compressor fan blades for cracks, using Part 2 of RRD SB No. TAY–72–1442, Revision 3, dated November 26, 2003, at the following: (1) For Tay 650–15 and Tay 651–54 engines: LP Compressor Fan Blades That Are Cracked (i) If any LP compressor fan blade is cracked, then remove the complete LP compressor fan blade set and the LP compressor fan disc from service. (1) Within 30 days after the effective date of this AD, perform UI of the LP compressor fan blades for cracks. (2) Use Part 1 of RRD Service Bulletin (SB) No. TAY–72–1591, dated May 8, 2003, to do the inspection. UI of LP Compressor Fan Blades Being Installed in a Different Engine; Tay 650–15 and Tay 651–54 Engines (g) For Tay 650–15 and Tay 651–54 engines, whenever LP compressor fan blades are removed and are being installed in a different engine: (1) Perform UI of the LP compressor fan blades for cracks. (2) Use Part 1 of RRD SB No. TAY–72– 1442, Revision 3, dated November 26, 2003, to do the inspection. PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 E:\FR\FM\29JAR1.SGM 29JAR1 3939 Federal Register / Vol. 72, No. 18 / Monday, January 29, 2007 / Rules and Regulations Alternative Methods of Compliance (j) The Manager, Engine 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. Related Information (k) Luftfahrt-Bundesamt airworthiness directive D–1998–055R3, dated December 15, 2003, which was approved by EASA under approval No. 1869 on December 15, 2003, also addresses the subject of this AD. (l) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; telephone (781) 238–7747, fax (781) 238–7199; e-mail: jason.yang@faa.gov for more information about this AD. by reference of the documents listed in Table 1 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact RollsRoyce Deutschland Ltd & Co KG, Eschenweg 11, D–15827 Dahlewitz, Germany; telephone 49 (0) 33–7086–1768; fax 49 (0) 33–7086– 3356 for a copy of this service information. You may review copies 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: http://www.archives.gov/federalregister/cfr/ibr-locations.html. Material Incorporated by Reference (m) You must use the Rolls-Royce Deutschland Ltd & Co KG service information specified in Table 1 to perform the actions required by this AD. The Director of the Federal Register approved the incorporation TABLE 1.—INCORPORATION BY REFERENCE Service Bulletin No. Page Revision TAY–72–1591, Total Pages: 8 .................................................................................................. TAY–72–1442, Total Pages: 11 ................................................................................................ Appendix 1 of TAY–72–1442, Total Pages: 4 ........................................................................... All ............ All ............. All ............. Original .... 3 .............. 3 ............... Issued in Burlington, Massachusetts, on January 22, 2007. Peter A. White, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–1218 Filed 1–26–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–25642; Directorate Identifier 2006–NM–121–AD; Amendment 39–14912; AD 2007–03–01] RIN 2120–AA64 Airworthiness Directives; Boeing Model 757 Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. rmajette on PROD1PC67 with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. This AD results from a report that a power feeder wire bundle chafed against the number six auxiliary slat track, causing electrical wires in the bundle to arc, which damaged both the auxiliary slat track and power feeder wires. We are issuing this AD to prevent arcing that could be a possible ignition source for leaked flammable fluids, which could result in a fire. Arcing could also result in a loss of power from the generator VerDate Aug<31>2005 14:38 Jan 26, 2007 Jkt 211001 connected to the power feeder wire bundle, and consequent loss of systems, which could reduce controllability of the airplane. DATES: This AD becomes effective March 5, 2007. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of March 5, 2007. ADDRESSES: You may examine the AD docket on the Internet at http:// dms.dot.gov or in person at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Nassif Building, Room PL–401, Washington, DC. Contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207, for the service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Philip Sheridan, Aerospace Engineer, Systems and Equipment Branch, ANM– 130S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6441; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the airworthiness directive (AD) docket on the Internet at http://dms.dot.gov or in person at the Docket Management Facility office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The Docket Management Facility office (telephone (800) 647–5227) is located on the plaza level of the Nassif Building at the street address stated in the ADDRESSES section. Discussion The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 CFR PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 Date May 8, 2003. November 26, 2003. November 26, 2003. part 39 to include an AD that would apply to certain Boeing Model 757 airplanes. That NPRM was published in the Federal Register on August 21, 2006 (71 FR 48493). That NPRM proposed to require inspecting certain power feeder wire bundles for damage, inspecting the support clamps for these wire bundles to determine whether the clamps are properly installed, and performing corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comments received. Request To Clarify Scope of Service Information Northwest Airlines (NWA) states that the service bulletins referred to in the NPRM indicate that Boeing technical publication revisions are not required to support the referenced modification. NWA adds that, typically, wire bundle installations are not detailed in Boeing technical publications; wire bundles are installed and maintained in accordance with the Boeing standard wiring practices manual (SWPM). NWA notes that the addition of spacers and rivets to wire bundle support brackets is not supported by Boeing technical publications. NWA adds that this burdens operators with the cost of developing their own system of maintaining the required configuration for continued compliance with the AD. We infer that the commenter is asking for clarification of the scope of the referenced service information regarding related technical publications. Regarding the comment on adding spacers and rivets, the spacers should already have been installed, and the purpose of the rivets is to ensure that E:\FR\FM\29JAR1.SGM 29JAR1

Agencies

[Federal Register Volume 72, Number 18 (Monday, January 29, 2007)]
[Rules and Regulations]
[Pages 3936-3939]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-1218]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-24777; Directorate Identifier 2006-NE-19-AD; 
Amendment 39-14913; AD 2007-03-02]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd & Co KG Tay 
611-8, Tay 620-15, Tay 650-15, and Tay 651-54 Series Turbofan Engines

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

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611-8, Tay 620-15, Tay 
650-15, and Tay 651-54 series turbofan engines, with certain low 
pressure (LP) compressor modules installed. This AD requires an 
ultrasonic inspection (UI) of LP compressor fan blades for cracks, 
within 30 days after the effective date of the AD on certain serial 
number (SN) Tay 650-15 engines. This AD also requires initial and 
repetitive UIs of LP compressor fan blades on all engines. This AD also 
requires, for Tay 650-15 and Tay 651-54 engines, UIs of LP compressor 
fan blades whenever the blade set is removed from one engine and 
installed on a different engine. This AD results from a report that a 
set of LP compressor fan blades failed before reaching the LP 
compressor fan blade full published life limit. We are issuing this AD 
to prevent LP compressor fan blades from failing due to blade root 
cracks, leading to uncontained engine failure and damage to the 
airplane.

DATES: This AD becomes effective March 5, 2007. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of March 5, 2007.

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-7086-
3356.
    You may examine the AD docket on the Internet at http://dms.dot.gov 
or in Room PL-401 on the plaza level of the Nassif Building, 400 
Seventh Street, SW., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England

[[Page 3937]]

Executive Park, Burlington, MA 01803; telephone (781) 238-7747; fax 
(781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to RRD Tay 611-8, Tay 620-
15, Tay 650-15, and Tay 651-54 series turbofan engines, with certain 
low pressure (LP) compressor modules installed. We published the 
proposed AD in the Federal Register on June 27, 2006 (71 FR 36493). 
That action proposed to require a UI of LP compressor fan blades for 
cracks, within 30 days after the effective date of the AD on certain 
serial number (SN) Tay 650-15 engines. That action also proposed to 
require repetitive UIs of LP compressor fan blades on all engines. That 
action also proposed to require, for Tay 650-15 and Tay 651-54 engines, 
UIs of LP compressor fan blades whenever the blade set is removed from 
one engine and installed on a different engine.

Examining the AD Docket

    You may examine the docket that contains the AD, any comments 
received, and any final disposition in person at the Docket Management 
Facility Docket Offices between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The Docket Office (telephone (800) 
647-5227) is located on the plaza level of the Department of 
Transportation Nassif Building at the street address stated in 
ADDRESSES. Comments will be available in the AD docket shortly after 
the DMS receives them.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We have considered the comments received.

RRD Request To Change Compliance Paragraphs (h)(1) and (h)(2)

    RRD requests that we change the compliance schedule for Tay 650-15 
and Tay 651-54 engines in proposed AD paragraph (h)(1), from ``at every 
shop visit for any reason or before reaching every 4,000 flight hours-
since-last fan blade UI, whichever occurs first'' to ``at every engine 
shop visit for any reason or before reaching every 10,000 flight hours-
since-last fan blade UI, whichever occurs first.''
    RRD also requests that we change the compliance schedule for Tay 
620-15 engines in proposed AD paragraph (h)(2) from ``before reaching 
every 8,000 flight hours but no later than every 10 years since-last-
fan-blade UI, whichever occurs first'' to ``before reaching every 
10,000 flight hours for airline operation, and before reaching 8,000 
flight hours but no later than every 10 years since-last-fan-blade UI, 
whichever occurs first, for non-airline operation.'' RRD bases these 
changes on their Engine Management Program.
    We agree with the intent of the requested changes to proposed AD 
paragraph (h)(1). We changed that paragraph, and added subparagraphs to 
clarify the initial inspection requirements in the AD. Regarding 
paragraph (h)(2), we do not agree with having different inspection 
schedules for airline and non-airline operations. However, we changed 
paragraph (h)(2) to paragraph (h)(2)(iii), to read ``before reaching 
every 10,000 flight hours but no later than every 10 years since-last-
fan-blade UI, whichever occurs first''. We feel that this drawdown 
schedule will take care of both low- and high-utilization of Tay 620-15 
engines.

Air Transport Association Request To Change Compliance Paragraph (h)(1)

    Air Transport Association (ATA) requests that we change the 
compliance schedule in paragraph (h)(1) from ``at every engine shop 
visit for any reason or before reaching every 4,000 flight hours-since-
last fan blade UI, whichever occurs first'' to ``at every engine shop 
visit for any reason or before reaching every 12 years or 15,000 flight 
hours-since-last fan blade UI, whichever occurs first''. ATA states 
that this schedule is described in the Engine Management Program for 
Tay 651-54 engines installed in the Boeing 727 airplanes. We do not 
agree. The intent of proposed AD paragraph (h)(1) is to UI Tay 650-15 
and Tay 651-54 engines at all scheduled and unscheduled shop visits, 
using RRD SB No. TAY-72-1442, Revision 3, dated November 26, 2003. 
Also, the intent of the paragraph is to parallel the SB requirement of 
an initial UI within 3 months after the SB issue date. We did change 
paragraph (h) and added subparagraphs as described under the first 
comment above.

Request To Change Compliance Paragraph (h)(3)

    One commenter requests that we change the Tay 611-8 compliance 
schedule in proposed AD paragraph (h)(3). The commenter requests that 
we call out an initial UI inspection to be done at the next engine mid-
life or overhaul inspection after the effective date of this AD. The 
commenter also requests that we call out repetitive UI inspections to 
be done before reaching every 8,000 flight hours but no later than 
every 10 years since-last-fan blade UI, whichever occurs first. These 
changes would prevent many airplanes from being immediately grounded, 
upon issuance of the AD. We agree with the commenter's intent. We 
changed and added paragraphs (h) through (h)(2)(iii) to clarify the 
initial inspection requirements in the AD, and to incorporate the 
compliance schedule changes.

Request To Add LP Compressor Fan Blade Part Numbers

    ATA requests that we include LP compressor fan blade part numbers 
in the AD. We agree and added the part numbers to the AD.

Incorrect Supplemental Type Certificate (STC) Number

    In paragraph (c) of the proposed AD, STC number SA842SW is 
incorrect. That STC applies to a Cessna Model 414 airplane. We 
corrected the STC No. in paragraph (c) of this AD to SA8472SW, which 
applies to a Boeing 727 airplane.

Conclusion

    We have carefully reviewed the available data, including the 
comments received, and determined that air safety and the public 
interest require adopting the AD with the changes described previously. 
We have determined that these changes will neither increase the 
economic burden on any operator nor increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect about 1,000 RRD Tay 611-8, Tay 
620-15, Tay 650-15, and Tay 651-54 series turbofan engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 4 
work-hours per engine to perform an inspection, and that the average 
labor rate is $80 per work-hour. Required parts will cost about $95,000 
per LP compressor fan disk and $140,000 per set of LP compressor fan 
blades. We estimate that 5 percent or 50 engines will require replacing 
the LP compressor fan disc and LP compressor fan blade set. Based on 
these figures, we estimate the total cost of the AD to U.S. operators 
to be $11,750,000.

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

[[Page 3938]]

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 at the 
address listed under ADDRESSES.

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 adding the following new airworthiness 
directive:

2007-03-02 Rolls-Royce Deutschland Ltd & Co KG (formerly Rolls-Royce 
plc): Amendment 39-14913. Docket No. FAA-2006-24777; Directorate 
Identifier 2006-NE-19-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective March 5, 
2007.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) 
Tay 611-8 and Tay 620-15 turbofan engines with low pressure (LP) 
compressor module part number (P/N) MO1100AA or P/N MO1100AB 
installed, and Tay 650-15 and Tay 651-54 turbofan engines with LP 
compressor module P/N MO1300AA or P/N MO1300AB installed. These 
engines are installed on, but not limited to, Fokker F.28 Mark 0070 
and 0100 airplanes, Boeing 727 airplanes modified in accordance with 
Supplemental Type Certificate No. SA8472SW, and Gulfstream G-IV 
airplanes. The following P/N LP compressor fan blades are installed 
in these modules:

----------------------------------------------------------------------------------------------------------------
                                                                     Tay 650-15 LP            Tay 651-54 LP
Tay 611-8 LP compressor fan blade P/  Tay 620-15 LP compressor  compressor fan blade P/  compressor fan blade P/
                 Ns                        fan blade P/Ns                  Ns                       Ns
----------------------------------------------------------------------------------------------------------------
JR30649.............................  JR30649.................  JR31911................  JR31911.
JR31702.............................  JR31702.................  JR31912................  JR31912.
JR31983.............................  JR31983.................  JR35120................  JR35120.
                                      JR33863.................  JR35121................  JR35121.
                                      JR33864.................  JR33865................
                                      ........................  JR33866................
----------------------------------------------------------------------------------------------------------------

Unsafe Condition

    (d) This AD results from a report that a set of LP compressor 
fan blades failed before reaching the LP compressor fan blade full 
published life limit. We are issuing this AD to prevent LP 
compressor fan blades from failing due to blade root cracks, leading 
to uncontained engine failure and 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.

Ultrasonic Inspection (UI) of LP Compressor Fan Blades for Certain Tay 
650-15 Engines That Have Not Yet Had UI of the LP Compressor Fan Blades

    (f) For Tay 650-15 engines, serial numbers 17201, 17202, 17226, 
17253, 17341, 17356, 17428, 17450, 17457, 17458, 17497, 17530, 
17622, 17643, 17655, 17678, 17709, 17751, 17755, 17805, and 17806 
that have not yet had UI of the LP compressor fan blades:
    (1) Within 30 days after the effective date of this AD, perform 
UI of the LP compressor fan blades for cracks.
    (2) Use Part 1 of RRD Service Bulletin (SB) No. TAY-72-1591, 
dated May 8, 2003, to do the inspection.

UI of LP Compressor Fan Blades Being Installed in a Different Engine; 
Tay 650-15 and Tay 651-54 Engines

    (g) For Tay 650-15 and Tay 651-54 engines, whenever LP 
compressor fan blades are removed and are being installed in a 
different engine:
    (1) Perform UI of the LP compressor fan blades for cracks.
    (2) Use Part 1 of RRD SB No. TAY-72-1442, Revision 3, dated 
November 26, 2003, to do the inspection.

UI of LP Compressor Fan Blades for All Tay Engines

    (h) Perform UI of the LP compressor fan blades for cracks, using 
Part 2 of RRD SB No. TAY-72-1442, Revision 3, dated November 26, 
2003, at the following:
    (1) For Tay 650-15 and Tay 651-54 engines:
    (i) Initial UI at next shop visit for any reason but no later 
than 6 months after the effective date of this AD, whichever occurs 
first.
    (ii) Repetitive UIs at every engine shop visit for any reason 
but before reaching every 10,000 flight hours-since-last fan blade 
UI, whichever occurs first.
    (2) For Tay 611-8 and Tay 620-15 engines:
    (i) Initial UI at next shop visit for engine mid-life inspection 
or overhaul, but no later than 12 months after the effective date of 
this AD, whichever occurs first.
    (ii) For Tay 611-8 engines, repetitive UIs before reaching every 
8,000 flight hours but no later than every 10 years since-last-fan-
blade UI, whichever occurs first.
    (iii) For Tay 620-15 engines, repetitive UIs before reaching 
every 10,000 flight hours but no later than every 10 years since-
last-fan-blade UI, whichever occurs first.

LP Compressor Fan Blades That Are Cracked

    (i) If any LP compressor fan blade is cracked, then remove the 
complete LP compressor fan blade set and the LP compressor fan disc 
from service.

[[Page 3939]]

Alternative Methods of Compliance

    (j) The Manager, Engine 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.

Related Information

    (k) Luftfahrt-Bundesamt airworthiness directive D-1998-055R3, 
dated December 15, 2003, which was approved by EASA under approval 
No. 1869 on December 15, 2003, also addresses the subject of this 
AD.
    (l) Contact Jason Yang, Aerospace Engineer, Engine Certification 
Office, FAA, Engine and Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; telephone (781) 238-7747, fax 
(781) 238-7199; e-mail: jason.yang@faa.gov for more information 
about this AD.

Material Incorporated by Reference

    (m) You must use the Rolls-Royce Deutschland Ltd & Co KG service 
information specified in Table 1 to perform the actions required by 
this AD. The Director of the Federal Register approved the 
incorporation by reference of the documents listed in Table 1 of 
this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, D-15827 
Dahlewitz, Germany; telephone 49 (0) 33-7086-1768; fax 49 (0) 33-
7086-3356 for a copy of this service information. You may review 
copies 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: http://www.archives.gov/federal-register/
cfr/ibr-locations.html.

                                      Table 1.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
       Service Bulletin No.                 Page               Revision                      Date
----------------------------------------------------------------------------------------------------------------
TAY-72-1591, Total Pages: 8.......  All................  Original...........  May 8, 2003.
TAY-72-1442, Total Pages: 11......  All................  3..................  November 26, 2003.
Appendix 1 of TAY-72-1442, Total    All................  3..................  November 26, 2003.
 Pages: 4.
----------------------------------------------------------------------------------------------------------------


    Issued in Burlington, Massachusetts, on January 22, 2007.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-1218 Filed 1-26-07; 8:45 am]
BILLING CODE 4910-13-P