Airworthiness Directives; Rolls-Royce Deutschland (RRD) (Formerly Rolls-Royce, plc) Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10, and Tay 651-54 Turbofan Engines, 1172-1176 [05-40]

Download as PDF 1172 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations Actions Compliance Procedures (2) If the airplane records show that a MIL–H– 6000B fuel hose has been replaced, inspect the airplane fuel hoses for a 3⁄8-inch-wide red or orange-red, length-wise stripe, with manufacturer’s code, 94519, printed periodically along the line in red letters on one side. The hoses have a spiral or diagonal outer wrap with a fabric-type texture on the rubber surface. (3) Replace any fuel hose that matches the description in paragraph (e)(2) of this AD with an FAA-approved MIL–H–6000B fuel hose that has a criss-cross or braided external wrap. For all affected airplanes other than the Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours TIS after August 28, 1998 (the effective date of AD 98–15–13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD). Documented compliance with AD 98–15–13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. For all affected airplanes other than the Models 99, 99A, A99, A99A, B99, and C99: Within 200 hours TIS after August 28, 1998 (the effective date of AD 98–15–13). For all affected Models 99, 99A, A99, A99A, B99, and C99 airplanes: Within the next 200 hours TIS after February 22, 2005 (the effective date of this AD). Within 200 hours TIS after August 28, 1998 (the effective date of AD 98–15–13). Documented compliance with AD 98–15–13 or follow PART II of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. (4) For Raytheon Models C90A, B200, and B300 airplanes that were manufactured on January 1, 1994, and after, replace the MIL– H–6000B fuel hoses. (5) Do not install a rubber fuel hose having spiral or diagonal external wrap with a 3⁄8-inchwide red or orange-red, length-wise stripe running down the side of the hose, with the manufacturer’s code, 94519, printed periodically along the line in red letters on any of the affected airplanes. As of February 22, 2005 (the effective date of this AD). May I Request an Alternative Method of Compliance? (f) You may request a different method of compliance or a different compliance time for this AD by following the procedures in 14 CFR 39.19. Unless FAA authorizes otherwise, send your request to your principal inspector. The principal inspector may add comments and will send your request to the Manager, Standards Office, Small Airplane Directorate, FAA. For information on any already approved alternative methods of compliance, contact Jeffrey A. Pretz, Aerospace Engineer, ACE–116W, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946–4153; facsimile: (316) 946–4407. Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590–001 or on the Internet at https:// dms.dot.gov. The docket number is FAA– 2004–19089. Does This AD Incorporate Any Material by Reference? (g) You must do the actions required by this AD following the instructions in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. 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. To get a copy of this service information, contact Raytheon Aircraft Company, P.O. Box 85, Wichita, Kansas 67201–0085; telephone: (800) 625– 7043. To review copies of this service information, go to the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, go to: https:// www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html or call (202) 741–6030. To view the AD docket, go to the Docket VerDate jul<14>2003 18:52 Jan 05, 2005 Jkt 205001 Issued in Kansas City, Missouri, on December 27, 2004. William J. Timberlake, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–35 Filed 1–5–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2004–NE–11–AD; Amendment 39–13922; AD 2004–26–10] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland (RRD) (Formerly RollsRoyce, plc) Tay 611–8, Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650–15/10, and Tay 651–54 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for PO 00000 Frm 00012 Fmt 4700 Sfmt 4700 Documented compliance with AD 98–15–13 or follow PART I of the ACCOMPLISHMENT INSTRUCTIONS section in Raytheon Aircraft Mandatory Service Bulletin SB 2718, Revision 1, dated June 1997; or Revision 2, dated April 2000. Not applicable. certain RRD Tay 611–8, Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650– 15/10, and Tay 651–54 turbofan engines with ice-impact panels installed in the low pressure (LP) compressor case. That AD currently requires visually inspecting all ice-impact panels and fillers in the LP compressor case for certain conditions, and if necessary, replacing any ice-impact panels and fillers that have those conditions. This AD requires initial and repetitive visual inspections of all ice-impact panels and fillers in the LP compressor case for certain conditions and replacing as necessary, any or all panels. This AD also introduces a new compliance date of no later than March 1, 2005, to have all but one engine on each airplane in compliance with the polysulfide bonding of panels. This AD results from RRD issuing two service bulletins since AD 2004–05–22 was published, that required repetitive visual inspections of panels, and defines a minimum configuration and repair standard. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines. DATES: Effective January 21, 2005. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the regulations as of January 21, 2005. We must receive any comments on this AD by March 7, 2005. E:\FR\FM\06JAR1.SGM 06JAR1 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations Use one of the following addresses to comment on this AD. • DOT Docket Web site: Go to https://dms.dot.gov and follow the instructions for sending your comments electronically. • Government-wide rulemaking Web site: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility; U.S. Department of Transportation, 400 Seventh Street, SW., Nassif Building, Room PL–401, Washington, DC 20590– 001. • Fax: (202) 493–2251. • Hand Delivery: Room PL–401 on the plaza level of the Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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 the service information referenced in this AD. You may examine the comments on this AD in the AD docket on the Internet at https:// dms.dot.gov. ADDRESSES: FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803– 5299; telephone (781) 238–7747; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: On March 3, 2004, the FAA issued AD 2004–05– 22, Amendment 39–13517 (69 FR 11305, March 10, 2004). That AD requires visually inspecting all LP compressor case ice-impact panels and fillers that conform to the RR Service Bulletin (SB) No. TAY–72–1326 standard or were repaired using RR repair scheme TV5451R or HRS3491, for certain conditions. That AD also requires replacing any ice-impact panels and fillers that have those conditions, if necessary. That AD was the result of two reported events of ice-impact panels that released during flight, one of which resulted in reduction of power in both engines. That condition, if not corrected, could result in release of iceimpact panels due to improper bonding that can result in loss of thrust in both engines. Actions Since AD 2004–05–22 Was Issued Since AD 2004–5–22 was issued, RRD issued two SBs that supersede the existing SBs used in that AD. The new SBs require initial and repetitive visual inspections of all LP compressor case ice-impact panels and fillers that VerDate jul<14>2003 18:52 Jan 05, 2005 Jkt 205001 conform to RR SB No. TAY–72–1326, or were repaired using RR repair scheme TV5451R or HRS3491, for certain conditions. The new SBs also require bonding of replacement ice-impact panels using polysulfide bonding. Also, the new SBs introduce a new compliance date of no later than March 1, 2005, to have all but one engine on each airplane in compliance with the polysulfide bonding of panels. Relevant Service Information We have reviewed and approved the technical contents of RRD SB No. TAY– 72–1638, Revision 2, dated September 21, 2004, and RRD SB No. TAY–72– 1639, Revision 2, dated September 21, 2004, that are described in the previous paragraph. The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, classified these SBs as mandatory and issued AD D2004–313R2, dated September 21, 2004, in order to ensure the airworthiness of these RRD engines in Germany. Bilateral Airworthiness Agreement This engine model is manufactured in the United Kingdom (U.K). and is type certificated for operation in the United States under the provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Under this bilateral airworthiness agreement, the Civil Aviation Authority (CAA), which is the airworthiness authority for the U.K., has kept the FAA informed of the situation described above. We have examined the findings of the CAA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States. FAA’s Determination and Requirements of This AD The unsafe condition described previously is likely to exist or develop on other RRD Tay 611–8, Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650– 15/10, and Tay 651–54 turbofan engines of the same type design. We are issuing this AD to prevent release of ice-impact panels due to improper bonding that can result in loss of thrust in both engines. This AD requires the following: • Initial and repetitive visual inspections of all ice-impact panels and fillers in the LP compressor case for certain conditions and replacing any or all panels, based on condition. • Bonding of replacement ice-impact panels using polysulfide bonding. • Introduction of a new compliance date of no later than March 1, 2005, to PO 00000 Frm 00013 Fmt 4700 Sfmt 4700 1173 have all but one engine on each airplane in compliance with the polysulfide bonding of panels. You must use the service information described previously to perform the actions required by this AD. FAA’s Determination of the Effective Date Since an unsafe condition exists that requires the immediate adoption of this AD, we have found that notice and opportunity for public comment before issuing this AD are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Interim Action These actions are interim actions and we may take further rulemaking actions in the future. Comments Invited This AD is a final rule that involves requirements affecting flight safety and was not preceded by notice and an opportunity for public comment; however, we invite you to submit any written relevant data, views, or arguments regarding this AD. Send your comments to an address listed under ADDRESSES. Include ‘‘AD Docket No. 2004–NE–11–AD’’ in the subject line of your comments. If you want us to acknowledge receipt of your mailed comments, send us a self-addressed, stamped postcard with the docket number written on it; we will datestamp your postcard and mail it back to you. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify it. If a person contacts us verbally, and that contact relates to a substantive part of this AD, we will summarize the contact and place the summary in the docket. We will consider all comments received by the closing date and may amend the AD in light of those comments. 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. 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 E:\FR\FM\06JAR1.SGM 06JAR1 1174 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations responsibilities among the various levels of government. For the reasons discussed above, I certify that the regulation: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and 3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a 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. 2004–NE–11– 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 part 39 of the Federal Aviation Regulations (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 removing Amendment 39–13517 (69 FR 11305, March 10, 2004), and by adding a new airworthiness directive, Amendment 39–13922, to read as follows: I 2004–26–10 Rolls-Royce Deutschland (RRD) (Formerly Rolls-Royce, plc): Amendment 39–13922. Docket No. 2004–NE–11–AD. Supersedes AD 2004– 05–22, Amendment 39–13517. Effective Date (a) This airworthiness directive (AD) becomes effective January 21, 2005. Affected ADs (b) This AD supersedes AD 2004–05–22, Amendment 39–13517. Applicability (c) This AD applies to RRD Tay 611–8, Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650–15/10, and Tay 651–54 turbofan engines that have one or more ice-impact panels installed in the low pressure (LP) compressor case that conform to the Rolls-Royce, plc (RR) Service Bulletin (SB) No. TAY–72–1326 standard. These engines are installed on, but not limited to, Fokker F.28 Mk.0070 and Mk.0100 series airplanes, Gulfstream Aerospace G–IV series airplanes, and Boeing Company 727–100 series airplanes modified in accordance with Supplemental Type Certificate SA8472SW (727–QF). Unsafe Condition (d) This AD results from RRD issuing two SBs since AD 2004–05–22 was published, that require repetitive visual inspections of ice-impact panels and defines a minimum configuration and repair standard. We are issuing this AD to prevent release of iceimpact panels due to improper bonding that can result in loss of thrust in both engines. 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. Inspecting Ice-Impact Panels in Tay 620–15, Tay 620–15/20, Tay 650–15, and Tay 650–15/ 10 Engines (f) For airplanes that have one Tay 620–15, Tay 620–15/20, Tay 650–15, or Tay 650–15/ 10 engine with ice-impact panels incorporated by the RR SB No. TAY–72–1326 standard, and not all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following: (1) Within 500 cycles-in-service (CIS) after the effective date of this AD, but no later than February 15, 2005, inspect the ice-impact panels and the surrounding fillers. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. TABLE 1.—INSPECTION DISPOSITION CRITERIA If: Then: (a) Any movement or rocking motion of LP compressor ice-impact panel, or any movement of the front edge of ice-impact panel. (b) Reappearing signs of moisture on the ice-impact panel or the surrounding filler. (c) Any dents or impact damage on the ice-impact panel that is greater than 3.1 square inch in total. (d) Any dents or impact damage on the ice-impact panel that is between 1.55 square inch and 3.1 square inch in total. (e) Any dents or impact damage on the ice-impact panel that is less than 1.55 square inch in total. (f) Any crack appears on the ice-impact panel and there is visible distortion of the airwashed surface. (g) Any crack appears on the ice-impact panel and there is no visible distortion of the airwashed surface. Before further flight, replace all panels using repair scheme HRS3648 or HRS3649. Before further flight, replace all panels using repair scheme HRS3648 or HRS3649. Before further flight, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 5 flight cycles or 5 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 50 flight cycles or 50 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 50 flight cycles or 50 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 150 flight cycles or 150 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Before further flight, replace the damaged panel using repair scheme HRS3648 or HRS3649. (h) Delamination or peeling of the compound layers of the airwashed surface and the penetrated area is greater than 3.1 square inch in total. (i) Delamination or peeling of the compound layers of the airwashed surface and the penetrated area is between 1.55 square inch and 3.1 square inch in total. (j) Delamination or peeling of the compound layers of the airwashed surface and the penetrated area is less than 1.55 square inch in total. (k) Delamination or peeling of the compound layers but the airwashed surface is not penetrated. (l) Missing filler surrounding the LP compressor case ............................. (m) Damage to the filler surrounding the LP compressor case such as chipped, cracked, or missing material. VerDate jul<14>2003 18:52 Jan 05, 2005 Jkt 205001 PO 00000 Frm 00014 Fmt 4700 Within 5 cycles or 5 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 50 cycles or 50 flight hours, whichever occurs first, replace the damaged panel using repair scheme HRS3648 or HRS3649. Within 150 flight cycles or 150 flight hours, whichever occurs first, repair the damaged panel using repair scheme HRS3630. Before further flight, repair the damaged filler using repair scheme HRS3630. Within 25 flight cycles or 25 flight hours, whichever occurs first, repair damaged filler using repair scheme HRS 3630. Sfmt 4700 E:\FR\FM\06JAR1.SGM 06JAR1 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations (2) Re-inspect within every 500 cyclessince-last-inspection (CSLI) or two months since-last-inspection, whichever occurs first. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (g) For airplanes that have two Tay 620– 15, Tay 620–15/20, Tay 650–15, or Tay 650– 15/10 engines with ice-impact panels incorporated by the RR SB No. TAY–72–1326 standard, and not all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following: (1) Before further flight, inspect the iceimpact panels and the surrounding fillers on at least one of the affected engines. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (2) Within 60 CIS after the effective date of this AD, but no later than January 15, 2005, inspect the remaining engine ice-impact panels and the surrounding fillers. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (3) Re-inspect one of the affected engines on the airplane, within every 250 CSLI or one month since-last-inspection, whichever occurs first. Thereafter, alternate the repetitive inspections between the two engines. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (h) Before March 1, 2005, rework all six ice-impact panels using repair scheme HRS3648 or HRS3649 on at least one of the affected engines. (i) After complying with paragraph (h) of this AD, re-inspect the engine not reworked, using the intervals in paragraph (f)(2) of this AD. Inspecting Ice-Impact Panels in Tay 651–54 Engines (j) For airplanes that have one Tay 651–54 engine with ice-impact panels incorporated by the RR SB No. TAY–72–1326 standard, and not all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following: (1) Within 30 CIS after the effective date of this AD, inspect the ice-impact panels and the surrounding fillers on the affected engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (2) Re-inspect the affected engine within every 500 CSLI or six months since-lastinspection, whichever occurs first. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. VerDate jul<14>2003 18:52 Jan 05, 2005 Jkt 205001 (k) For airplanes that have more than one Tay 651–54 engine with ice-impact panels incorporated by the RR SB No. TAY–72–1326 standard, and not all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following: (1) Before further flight, inspect the iceimpact panels and the surrounding fillers on at least one of the engines affected. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (2) Within 30 CIS after the effective date of this AD, inspect the ice-impact panels and the surrounding fillers on the remaining engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (3) Re-inspect at least one of the affected engines within every 250 CSLI or three months since-last inspection, whichever occurs first. Use paragraph 3.E of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (l) Before March 1, 2005, rework all six iceimpact panels using RR repair scheme HRS3648 or HRS3649 on at least one of the affected engines. (m) After complying with paragraph (l) of this AD, re-inspect the engine not reworked, using the intervals in paragraph (j)(2) of this AD. Repetitive Inspections for Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650–15/10, and Tay 651–54 Engines With All Ice-impact Panels Repaired by Polysulfide Bonding Material (n) For Tay 620–15, Tay 620–15/20, Tay 650–15, Tay 650–15/10, and Tay 651–54 engines with ice-impact panels incorporated by the RRD SB No. SB 72–1326 standard, and all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648 or HRS3649, do the following: (1) Re-inspect within every 1,500 CSLI, for the condition of the ice-impact panels and the surrounding fillers. (2) Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. Inspecting Ice-Impact Panels in Tay 611–8 Engines (o) For airplanes that have one Tay 611– 8 engine with ice-impact panels incorporated by the RR SB No. TAY–72–1326 standard, and RR repair scheme HRS3491 or HRS3615 was done with two pack epoxy (Omat 8/52) on one or more of the six ice-impact panels, do the following: (1) Within 450 flight hours after the effective date of this AD, inspect the iceimpact panels on the affected engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1639, PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 1175 Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (2) Re-inspect the ice impact panels within every 1,000 CSLI or six months since-lastinspection, whichever occurs first, Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (p) For airplanes with both Tay 611–8 engines with ice-impact panels incorporated with the RR SB No. TAY–72–1326 standard, and RR repair scheme HRS3491 or HRS3615 was done with two pack epoxy (Omat 8/52) on one or more of the six ice-impact panels on the affected engines, do the following: (1) Within 150 flight hours after the effective date of this AD, inspect the iceimpact panels on one of the affected engines. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (2) Within 450 flight hours after the effective date of this AD, inspect the iceimpact panels on the remaining engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. (3) Re-inspect the ice impact panels within every 500 CSLI or three months since-lastinspection, whichever occurs first, Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD, on at least one of the affected engines. (q) Before March 1, 2005, rework all six ice-impact panels using RR repair scheme HRS3648, or HRS3649 on at least one of the affected engines. (r) After complying with paragraph (q) of this AD, re-inspect the engine not reworked, using the intervals in paragraph (o)(2) of this AD. Repetitive Inspections for Tay 611–8 Engines With All Ice-impact Panels Repaired by Polysulfide Bonding Material or Introduced Since New Production (s) For Tay 611–8 engines with ice-impact panels incorporated by the RRD SB No. SB 72–1326 standard and all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648 or HRS3649, or panels were introduced since new production, do the following: (1) Re-inspect within every 3,000 CSLI, for the condition of the ice-impact panels and the surrounding fillers. (2) Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD. Installing Engines That Are Not Inspected (t) After the effective date of this AD, do not install any Tay 620–15, Tay 620–15/20, E:\FR\FM\06JAR1.SGM 06JAR1 1176 Federal Register / Vol. 70, No. 4 / Thursday, January 6, 2005 / Rules and Regulations Tay 650–15, Tay 650–15/10, and Tay 651–54 engines with ice-impact panels if: (1) Those ice-impact panels incorporate the RR SB No. TAY–72–1326 standard; and (2) Ice-impact panels were repaired using RR repair scheme TV5451R, HRS3491, or HRS3615 and bonding material other than polysulfide; unless (3) The panels and the surrounding fillers are inspected for condition using 3.B. through 3.D.(3) (in-service) or 3.K.(1) through 3.(M)(3) (at overhaul or shop visit) of the Accomplishment Instructions of RRD SB No. TAY–72–1638, Revision 2, dated September 21, 2004. (u) Perform repetitive inspections as specified in paragraph (n) of this AD. (v) After the effective date of this AD, do not install any Tay 611–8 engine with iceimpact panels if: (1) Those ice-impact panels incorporate the RR SB No. TAY–72–1326 standard; and (2) Ice-impact panels were repaired using RR repair scheme TV5451R, HRS3491, or HRS3615 and bonding material other than polysulfide, unless (3) The panels and the surrounding fillers are inspected for condition using 3.B. through 3.D.(2) (in-service) or 3.K.(1) through 3.M.(3) (at overhaul or shop visit) of the Accomplishment Instructions of RRD SB No. TAY–72–1639, Revision 2, dated September 21, 2004. (w) Perform repetitive inspections as specified in paragraph (s) of this AD. Alternative Methods of Compliance (x) 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. Material Incorporated by Reference (y) You must use the Rolls-Royce service information specified in Table 2 to perform the inspections required by this AD. The Director of the Federal Register approved the incorporation by reference of the documents listed in Table 2 of this AD in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a copy 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 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/ code_of_federal_regulations/ ibr_locations.html. Table 2 follows: TABLE 2.—INCORPORATION BY REFERENCE Service information No. Page Revision Date SB No. TAY–72–1638 ................................................................................. Total Pages: 35 SB No. TAY–72–1639 ................................................................................. Total Pages: 28 Repair Scheme No. HRS3648 Front Sheet ................................................ Total Pages: 1 Repair Scheme No. HRS3648 History Sheet .............................................. Total Pages: 3 Repair Scheme No. HRS3648 ..................................................................... Total Pages: 30 Repair Scheme No. HRS3649 Front Sheet ................................................ Total Pages: 1 Repair Scheme No. HRS3649 History Sheet .............................................. Total Pages: 3 Repair Scheme No. HRS3649 ..................................................................... Total Pages: 24 ALL ................................................... 2 Sept. 21, 2004. ALL ................................................... 2 Sept. 21, 2004. ALL ................................................... 2 Jan. 28, 2004. ALL ................................................... 2 Jan. 28, 2004. ALL ................................................... 2 Jan. 27, 2004. ALL ................................................... 2 Sept. 1, 2004. ALL ................................................... 2 Sept. 7, 2004. ALL ................................................... 2 June 17, 2004. Related Information DEPARTMENT OF TRANSPORTATION (z) LBA AD D2004–313R2, dated September 21, 2004, also addresses the subject of this AD. Federal Aviation Administration Issued in Burlington, Massachusetts, on December 22, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–40 Filed 1–5–05; 8:45 am] BILLING CODE 4910–13–P 14 CFR Part 39 [Docket No. FAA–2004–19494; Directorate Identifier 2004–NM–135–AD; Amendment 39–13919; AD 2004–26–07] RIN 2120–AA64 Airworthiness Directives; Airbus Model A318, A319, A320, and A321 Series Airplanes Equipped With Air Cruisers/ Aerazur Forward and Aft Passenger Door Emergency Escape Slides Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes equipped with certain forward and aft passenger door emergency escape slides. This AD requires modifying the forward and aft VerDate jul<14>2003 18:52 Jan 05, 2005 Jkt 205001 PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 door slides. This AD is prompted by manufacturer testing that has shown contact between the inflation hose and fabric roll, within a short period of time after inflation of the emergency escape slides, can rupture the inflation hose at its end fittings. We are issuing this AD to prevent interference between the inflation hose and slide fabric and rupture of the inflation hose, which could result in incomplete inflation of the emergency escape slides and consequent unavailability of those slides during an emergency evacuation. This AD becomes effective February 10, 2005. The incorporation by reference of a certain publication listed in the AD is approved by the Director of the Federal Register as of February 10, 2005. DATES: For service information identified in this AD, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. You can examine this information at the National Archives and Records Administration ADDRESSES: E:\FR\FM\06JAR1.SGM 06JAR1

Agencies

[Federal Register Volume 70, Number 4 (Thursday, January 6, 2005)]
[Rules and Regulations]
[Pages 1172-1176]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-40]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2004-NE-11-AD; Amendment 39-13922; AD 2004-26-10]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland (RRD) (Formerly 
Rolls-Royce, plc) Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 
650-15/10, and Tay 651-54 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for certain RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, 
Tay 650-15/10, and Tay 651-54 turbofan engines with ice-impact panels 
installed in the low pressure (LP) compressor case. That AD currently 
requires visually inspecting all ice-impact panels and fillers in the 
LP compressor case for certain conditions, and if necessary, replacing 
any ice-impact panels and fillers that have those conditions. This AD 
requires initial and repetitive visual inspections of all ice-impact 
panels and fillers in the LP compressor case for certain conditions and 
replacing as necessary, any or all panels. This AD also introduces a 
new compliance date of no later than March 1, 2005, to have all but one 
engine on each airplane in compliance with the polysulfide bonding of 
panels. This AD results from RRD issuing two service bulletins since AD 
2004-05-22 was published, that required repetitive visual inspections 
of panels, and defines a minimum configuration and repair standard. We 
are issuing this AD to prevent release of ice-impact panels due to 
improper bonding that can result in loss of thrust in both engines.

DATES: Effective January 21, 2005. The Director of the Federal Register 
approved the incorporation by reference of certain publications listed 
in the regulations as of January 21, 2005.
    We must receive any comments on this AD by March 7, 2005.

[[Page 1173]]


ADDRESSES: Use one of the following addresses to comment on this AD.
     DOT Docket Web site: Go to https://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility; U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401, 
Washington, DC 20590-001.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

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 the service information referenced in this AD. You may 
examine the comments on this AD in the AD docket on the Internet at 
https://dms.dot.gov.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7747; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On March 3, 2004, the FAA issued AD 2004-05-
22, Amendment 39-13517 (69 FR 11305, March 10, 2004). That AD requires 
visually inspecting all LP compressor case ice-impact panels and 
fillers that conform to the RR Service Bulletin (SB) No. TAY-72-1326 
standard or were repaired using RR repair scheme TV5451R or HRS3491, 
for certain conditions. That AD also requires replacing any ice-impact 
panels and fillers that have those conditions, if necessary. That AD 
was the result of two reported events of ice-impact panels that 
released during flight, one of which resulted in reduction of power in 
both engines. That condition, if not corrected, could result in release 
of ice-impact panels due to improper bonding that can result in loss of 
thrust in both engines.

Actions Since AD 2004-05-22 Was Issued

    Since AD 2004-5-22 was issued, RRD issued two SBs that supersede 
the existing SBs used in that AD. The new SBs require initial and 
repetitive visual inspections of all LP compressor case ice-impact 
panels and fillers that conform to RR SB No. TAY-72-1326, or were 
repaired using RR repair scheme TV5451R or HRS3491, for certain 
conditions. The new SBs also require bonding of replacement ice-impact 
panels using polysulfide bonding. Also, the new SBs introduce a new 
compliance date of no later than March 1, 2005, to have all but one 
engine on each airplane in compliance with the polysulfide bonding of 
panels.

Relevant Service Information

    We have reviewed and approved the technical contents of RRD SB No. 
TAY-72-1638, Revision 2, dated September 21, 2004, and RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004, that are described in 
the previous paragraph. The Luftfahrt-Bundesamt (LBA), which is the 
airworthiness authority for Germany, classified these SBs as mandatory 
and issued AD D2004-313R2, dated September 21, 2004, in order to ensure 
the airworthiness of these RRD engines in Germany.

Bilateral Airworthiness Agreement

    This engine model is manufactured in the United Kingdom (U.K). and 
is type certificated for operation in the United States under the 
provisions of section 21.29 of the Federal Aviation Regulations (14 CFR 
21.29) and the applicable bilateral airworthiness agreement. Under this 
bilateral airworthiness agreement, the Civil Aviation Authority (CAA), 
which is the airworthiness authority for the U.K., has kept the FAA 
informed of the situation described above. We have examined the 
findings of the CAA, reviewed all available information, and determined 
that AD action is necessary for products of this type design that are 
certificated for operation in the United States.

FAA's Determination and Requirements of This AD

    The unsafe condition described previously is likely to exist or 
develop on other RRD Tay 611-8, Tay 620-15, Tay 620-15/20, Tay 650-15, 
Tay 650-15/10, and Tay 651-54 turbofan engines of the same type design. 
We are issuing this AD to prevent release of ice-impact panels due to 
improper bonding that can result in loss of thrust in both engines. 
This AD requires the following:
     Initial and repetitive visual inspections of all ice-
impact panels and fillers in the LP compressor case for certain 
conditions and replacing any or all panels, based on condition.
     Bonding of replacement ice-impact panels using polysulfide 
bonding.
     Introduction of a new compliance date of no later than 
March 1, 2005, to have all but one engine on each airplane in 
compliance with the polysulfide bonding of panels.

You must use the service information described previously to perform 
the actions required by this AD.

FAA's Determination of the Effective Date

    Since an unsafe condition exists that requires the immediate 
adoption of this AD, we have found that notice and opportunity for 
public comment before issuing this AD are impracticable, and that good 
cause exists for making this amendment effective in less than 30 days.

Interim Action

    These actions are interim actions and we may take further 
rulemaking actions in the future.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 2004-NE-11-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.

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.

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

[[Page 1174]]

responsibilities among the various levels of government.
    For the reasons discussed above, I certify that the regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a 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. 2004-NE-11-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 part 39 of the Federal 
Aviation Regulations (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 39-13517 (69 FR 
11305, March 10, 2004), and by adding a new airworthiness directive, 
Amendment 39-13922, to read as follows:

2004-26-10 Rolls-Royce Deutschland (RRD) (Formerly Rolls-Royce, 
plc): Amendment 39-13922. Docket No. 2004-NE-11-AD. Supersedes AD 
2004-05-22, Amendment 39-13517.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
21, 2005.

Affected ADs

    (b) This AD supersedes AD 2004-05-22, Amendment 39-13517.

Applicability

    (c) This AD applies to RRD Tay 611-8, Tay 620-15, Tay 620-15/20, 
Tay 650-15, Tay 650-15/10, and Tay 651-54 turbofan engines that have 
one or more ice-impact panels installed in the low pressure (LP) 
compressor case that conform to the Rolls-Royce, plc (RR) Service 
Bulletin (SB) No. TAY-72-1326 standard. These engines are installed 
on, but not limited to, Fokker F.28 Mk.0070 and Mk.0100 series 
airplanes, Gulfstream Aerospace G-IV series airplanes, and Boeing 
Company 727-100 series airplanes modified in accordance with 
Supplemental Type Certificate SA8472SW (727-QF).

Unsafe Condition

    (d) This AD results from RRD issuing two SBs since AD 2004-05-22 
was published, that require repetitive visual inspections of ice-
impact panels and defines a minimum configuration and repair 
standard. We are issuing this AD to prevent release of ice-impact 
panels due to improper bonding that can result in loss of thrust in 
both engines.

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.

Inspecting Ice-Impact Panels in Tay 620-15, Tay 620-15/20, Tay 650-15, 
and Tay 650-15/10 Engines

    (f) For airplanes that have one Tay 620-15, Tay 620-15/20, Tay 
650-15, or Tay 650-15/10 engine with ice-impact panels incorporated 
by the RR SB No. TAY-72-1326 standard, and not all panels were 
repaired using polysulfide bonding material by RR repair scheme 
TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following:
    (1) Within 500 cycles-in-service (CIS) after the effective date 
of this AD, but no later than February 15, 2005, inspect the ice-
impact panels and the surrounding fillers. Use paragraph 3.E. of the 
Accomplishment Instructions of RRD SB No. TAY-72-1638, Revision 2, 
dated September 21, 2004, and the inspection disposition criteria in 
Table 1 of this AD.

                Table 1.--Inspection Disposition Criteria
------------------------------------------------------------------------
                  If:                                 Then:
------------------------------------------------------------------------
(a) Any movement or rocking motion of    Before further flight, replace
 LP compressor ice-impact panel, or any   all panels using repair scheme
 movement of the front edge of ice-       HRS3648 or HRS3649.
 impact panel.
(b) Reappearing signs of moisture on     Before further flight, replace
 the ice-impact panel or the              all panels using repair scheme
 surrounding filler.                      HRS3648 or HRS3649.
(c) Any dents or impact damage on the    Before further flight, replace
 ice-impact panel that is greater than    the damaged panel using repair
 3.1 square inch in total.                scheme HRS3648 or HRS3649.
(d) Any dents or impact damage on the    Within 5 flight cycles or 5
 ice-impact panel that is between 1.55    flight hours, whichever occurs
 square inch and 3.1 square inch in       first, replace the damaged
 total.                                   panel using repair scheme
                                          HRS3648 or HRS3649.
(e) Any dents or impact damage on the    Within 50 flight cycles or 50
 ice-impact panel that is less than       flight hours, whichever occurs
 1.55 square inch in total.               first, replace the damaged
                                          panel using repair scheme
                                          HRS3648 or HRS3649.
(f) Any crack appears on the ice-impact  Within 50 flight cycles or 50
 panel and there is visible distortion    flight hours, whichever occurs
 of the airwashed surface.                first, replace the damaged
                                          panel using repair scheme
                                          HRS3648 or HRS3649.
(g) Any crack appears on the ice-impact  Within 150 flight cycles or 150
 panel and there is no visible            flight hours, whichever occurs
 distortion of the airwashed surface.     first, replace the damaged
                                          panel using repair scheme
                                          HRS3648 or HRS3649.
(h) Delamination or peeling of the       Before further flight, replace
 compound layers of the airwashed         the damaged panel using repair
 surface and the penetrated area is       scheme HRS3648 or HRS3649.
 greater than 3.1 square inch in total.
(i) Delamination or peeling of the       Within 5 cycles or 5 flight
 compound layers of the airwashed         hours, whichever occurs first,
 surface and the penetrated area is       replace the damaged panel
 between 1.55 square inch and 3.1         using repair scheme HRS3648 or
 square inch in total.                    HRS3649.
(j) Delamination or peeling of the       Within 50 cycles or 50 flight
 compound layers of the airwashed         hours, whichever occurs first,
 surface and the penetrated area is       replace the damaged panel
 less than 1.55 square inch in total.     using repair scheme HRS3648 or
                                          HRS3649.
(k) Delamination or peeling of the       Within 150 flight cycles or 150
 compound layers but the airwashed        flight hours, whichever occurs
 surface is not penetrated.               first, repair the damaged
                                          panel using repair scheme
                                          HRS3630.
(l) Missing filler surrounding the LP    Before further flight, repair
 compressor case.                         the damaged filler using
                                          repair scheme HRS3630.
(m) Damage to the filler surrounding     Within 25 flight cycles or 25
 the LP compressor case such as           flight hours, whichever occurs
 chipped, cracked, or missing material.   first, repair damaged filler
                                          using repair scheme HRS 3630.
------------------------------------------------------------------------


[[Page 1175]]

    (2) Re-inspect within every 500 cycles-since-last-inspection 
(CSLI) or two months since-last-inspection, whichever occurs first. 
Use paragraph 3.E. of the Accomplishment Instructions of RRD SB No. 
TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.
    (g) For airplanes that have two Tay 620-15, Tay 620-15/20, Tay 
650-15, or Tay 650-15/10 engines with ice-impact panels incorporated 
by the RR SB No. TAY-72-1326 standard, and not all panels were 
repaired using polysulfide bonding material by RR repair scheme 
TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, do the following:
    (1) Before further flight, inspect the ice-impact panels and the 
surrounding fillers on at least one of the affected engines. Use 
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004, and the inspection 
disposition criteria in Table 1 of this AD.
    (2) Within 60 CIS after the effective date of this AD, but no 
later than January 15, 2005, inspect the remaining engine ice-impact 
panels and the surrounding fillers. Use paragraph 3.E. of the 
Accomplishment Instructions of RRD SB No. TAY-72-1638, Revision 2, 
dated September 21, 2004, and the inspection disposition criteria in 
Table 1 of this AD.
    (3) Re-inspect one of the affected engines on the airplane, 
within every 250 CSLI or one month since-last-inspection, whichever 
occurs first. Thereafter, alternate the repetitive inspections 
between the two engines. Use paragraph 3.E. of the Accomplishment 
Instructions of RRD SB No. TAY-72-1638, Revision 2, dated September 
21, 2004, and the inspection disposition criteria in Table 1 of this 
AD.
    (h) Before March 1, 2005, rework all six ice-impact panels using 
repair scheme HRS3648 or HRS3649 on at least one of the affected 
engines.
    (i) After complying with paragraph (h) of this AD, re-inspect 
the engine not reworked, using the intervals in paragraph (f)(2) of 
this AD.

Inspecting Ice-Impact Panels in Tay 651-54 Engines

    (j) For airplanes that have one Tay 651-54 engine with ice-
impact panels incorporated by the RR SB No. TAY-72-1326 standard, 
and not all panels were repaired using polysulfide bonding material 
by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or HRS3649, 
do the following:
    (1) Within 30 CIS after the effective date of this AD, inspect 
the ice-impact panels and the surrounding fillers on the affected 
engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD 
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.
    (2) Re-inspect the affected engine within every 500 CSLI or six 
months since-last-inspection, whichever occurs first. Use paragraph 
3.E. of the Accomplishment Instructions of RRD SB No. TAY-72-1638, 
Revision 2, dated September 21, 2004, and the inspection disposition 
criteria in Table 1 of this AD.
    (k) For airplanes that have more than one Tay 651-54 engine with 
ice-impact panels incorporated by the RR SB No. TAY-72-1326 
standard, and not all panels were repaired using polysulfide bonding 
material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648, or 
HRS3649, do the following:
    (1) Before further flight, inspect the ice-impact panels and the 
surrounding fillers on at least one of the engines affected. Use 
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1638, Revision 2, dated September 21, 2004, and the inspection 
disposition criteria in Table 1 of this AD.
    (2) Within 30 CIS after the effective date of this AD, inspect 
the ice-impact panels and the surrounding fillers on the remaining 
engine. Use paragraph 3.E. of the Accomplishment Instructions of RRD 
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.
    (3) Re-inspect at least one of the affected engines within every 
250 CSLI or three months since-last inspection, whichever occurs 
first. Use paragraph 3.E of the Accomplishment Instructions of RRD 
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.
    (l) Before March 1, 2005, rework all six ice-impact panels using 
RR repair scheme HRS3648 or HRS3649 on at least one of the affected 
engines.
    (m) After complying with paragraph (l) of this AD, re-inspect 
the engine not reworked, using the intervals in paragraph (j)(2) of 
this AD.

Repetitive Inspections for Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 
650-15/10, and Tay 651-54 Engines With All Ice-impact Panels Repaired 
by Polysulfide Bonding Material

    (n) For Tay 620-15, Tay 620-15/20, Tay 650-15, Tay 650-15/10, 
and Tay 651-54 engines with ice-impact panels incorporated by the 
RRD SB No. SB 72-1326 standard, and all panels were repaired using 
polysulfide bonding material by RR repair scheme TV5451R, HRS3491, 
HRS3615, HRS3648 or HRS3649, do the following:
    (1) Re-inspect within every 1,500 CSLI, for the condition of the 
ice-impact panels and the surrounding fillers.
    (2) Use paragraph 3.E. of the Accomplishment Instructions of RRD 
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.

Inspecting Ice-Impact Panels in Tay 611-8 Engines

    (o) For airplanes that have one Tay 611-8 engine with ice-impact 
panels incorporated by the RR SB No. TAY-72-1326 standard, and RR 
repair scheme HRS3491 or HRS3615 was done with two pack epoxy (Omat 
8/52) on one or more of the six ice-impact panels, do the following:
    (1) Within 450 flight hours after the effective date of this AD, 
inspect the ice-impact panels on the affected engine. Use paragraph 
3.E. of the Accomplishment Instructions of RRD SB No. TAY-72-1639, 
Revision 2, dated September 21, 2004, and the inspection disposition 
criteria in Table 1 of this AD.
    (2) Re-inspect the ice impact panels within every 1,000 CSLI or 
six months since-last-inspection, whichever occurs first, Use 
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004, and the inspection 
disposition criteria in Table 1 of this AD.
    (p) For airplanes with both Tay 611-8 engines with ice-impact 
panels incorporated with the RR SB No. TAY-72-1326 standard, and RR 
repair scheme HRS3491 or HRS3615 was done with two pack epoxy (Omat 
8/52) on one or more of the six ice-impact panels on the affected 
engines, do the following:
    (1) Within 150 flight hours after the effective date of this AD, 
inspect the ice-impact panels on one of the affected engines. Use 
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004, and the inspection 
disposition criteria in Table 1 of this AD.
    (2) Within 450 flight hours after the effective date of this AD, 
inspect the ice-impact panels on the remaining engine. Use paragraph 
3.E. of the Accomplishment Instructions of RRD SB No. TAY-72-1639, 
Revision 2, dated September 21, 2004, and the inspection disposition 
criteria in Table 1 of this AD.
    (3) Re-inspect the ice impact panels within every 500 CSLI or 
three months since-last-inspection, whichever occurs first, Use 
paragraph 3.E. of the Accomplishment Instructions of RRD SB No. TAY-
72-1639, Revision 2, dated September 21, 2004, and the inspection 
disposition criteria in Table 1 of this AD, on at least one of the 
affected engines.
    (q) Before March 1, 2005, rework all six ice-impact panels using 
RR repair scheme HRS3648, or HRS3649 on at least one of the affected 
engines.
    (r) After complying with paragraph (q) of this AD, re-inspect 
the engine not reworked, using the intervals in paragraph (o)(2) of 
this AD.

Repetitive Inspections for Tay 611-8 Engines With All Ice-impact Panels 
Repaired by Polysulfide Bonding Material or Introduced Since New 
Production

    (s) For Tay 611-8 engines with ice-impact panels incorporated by 
the RRD SB No. SB 72-1326 standard and all panels were repaired 
using polysulfide bonding material by RR repair scheme TV5451R, 
HRS3491, HRS3615, HRS3648 or HRS3649, or panels were introduced 
since new production, do the following:
    (1) Re-inspect within every 3,000 CSLI, for the condition of the 
ice-impact panels and the surrounding fillers.
    (2) Use paragraph 3.E. of the Accomplishment Instructions of RRD 
SB No. TAY-72-1638, Revision 2, dated September 21, 2004, and the 
inspection disposition criteria in Table 1 of this AD.

Installing Engines That Are Not Inspected

    (t) After the effective date of this AD, do not install any Tay 
620-15, Tay 620-15/20,

[[Page 1176]]

Tay 650-15, Tay 650-15/10, and Tay 651-54 engines with ice-impact 
panels if:
    (1) Those ice-impact panels incorporate the RR SB No. TAY-72-
1326 standard; and
    (2) Ice-impact panels were repaired using RR repair scheme 
TV5451R, HRS3491, or HRS3615 and bonding material other than 
polysulfide; unless
    (3) The panels and the surrounding fillers are inspected for 
condition using 3.B. through 3.D.(3) (in-service) or 3.K.(1) through 
3.(M)(3) (at overhaul or shop visit) of the Accomplishment 
Instructions of RRD SB No. TAY-72-1638, Revision 2, dated September 
21, 2004.
    (u) Perform repetitive inspections as specified in paragraph (n) 
of this AD.
    (v) After the effective date of this AD, do not install any Tay 
611-8 engine with ice-impact panels if:
    (1) Those ice-impact panels incorporate the RR SB No. TAY-72-
1326 standard; and
    (2) Ice-impact panels were repaired using RR repair scheme 
TV5451R, HRS3491, or HRS3615 and bonding material other than 
polysulfide, unless
    (3) The panels and the surrounding fillers are inspected for 
condition using 3.B. through 3.D.(2) (in-service) or 3.K.(1) through 
3.M.(3) (at overhaul or shop visit) of the Accomplishment 
Instructions of RRD SB No. TAY-72-1639, Revision 2, dated September 
21, 2004.
    (w) Perform repetitive inspections as specified in paragraph (s) 
of this AD.

Alternative Methods of Compliance

    (x) 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.

Material Incorporated by Reference

    (y) You must use the Rolls-Royce service information specified 
in Table 2 to perform the inspections required by this AD. The 
Director of the Federal Register approved the incorporation by 
reference of the documents listed in Table 2 of this AD in 
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. You can get a 
copy 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 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/code_of_federal_regulations/
ibr_locations.html. Table 2 follows:

                                      Table 2.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
        Service information No.                     Page               Revision                Date
----------------------------------------------------------------------------------------------------------------
SB No. TAY-72-1638.....................  ALL.......................           2   Sept. 21, 2004.
    Total Pages: 35
SB No. TAY-72-1639.....................  ALL.......................           2   Sept. 21, 2004.
    Total Pages: 28
Repair Scheme No. HRS3648 Front Sheet..  ALL.......................           2   Jan. 28, 2004.
    Total Pages: 1
Repair Scheme No. HRS3648 History Sheet  ALL.......................           2   Jan. 28, 2004.
    Total Pages: 3
Repair Scheme No. HRS3648..............  ALL.......................           2   Jan. 27, 2004.
    Total Pages: 30
Repair Scheme No. HRS3649 Front Sheet..  ALL.......................           2   Sept. 1, 2004.
    Total Pages: 1
Repair Scheme No. HRS3649 History Sheet  ALL.......................           2   Sept. 7, 2004.
    Total Pages: 3
Repair Scheme No. HRS3649..............  ALL.......................           2   June 17, 2004.
    Total Pages: 24
----------------------------------------------------------------------------------------------------------------

Related Information

    (z) LBA AD D2004-313R2, dated September 21, 2004, also addresses 
the subject of this AD.

    Issued in Burlington, Massachusetts, on December 22, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 05-40 Filed 1-5-05; 8:45 am]
BILLING CODE 4910-13-P
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