Corrections Not Carried Forward

RollsRoyce Deutschland Ltd & Co KG also requests that we review the proposed AD for missing corrections that were made to AD 200426 10, but not carried forward.

We agree. The corrections were inadvertently left out of the proposed AD. We have made those corrections to this AD, which throughout the compliance section changed ``paragraph 3.E.'' to ``paragraphs 3.C. through 3.E.''

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 1,085 engines installed on airplanes of U.S. registry. We also estimate that it will take about 2.5 workhours per engine to perform an inspection, and about 12 work hours to perform a repair. The average labor rate is $80 per workhour. Required terminating action parts will cost about $7,500 per engine. Based on these figures, for the AD, we estimate:

Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency's authority.

We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ``General requirements.'' Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action.

Regulatory Findings

We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify that this AD: (1) Is not a ``significant regulatory action'' under Executive Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a summary of the costs to comply with this AD and placed it in the AD docket. You may get a copy of this summary 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: PART 39AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by removing Amendment 3913922 (70 FR 1172, January 6, 2005), and by adding a new airworthiness directive, Amendment 3915321, to read as follows:
20072619 RollsRoyce Deutschland Ltd & Co KG (Formerly RollsRoyce plc): Amendment 3915321. Docket No. FAA200727811; Directorate Identifier 2004NE11AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective February 11, 2008.
Affected ADs
(b) This AD supersedes AD 20042610, Amendment 3913922.
Applicability
(c) This AD applies to:
(1) RollsRoyce Deutschland Ltd & Co KG (RRD) Tay 6118, Tay 62015, Tay 65015, and Tay 65154 turbofan engines that have one or more iceimpact panels installed in the low pressure (LP) compressor case that conform to the (RRD) Service Bulletin (SB) No. TAY721326 standard.
(2) RRD Tay 6118C turbofan engines with serial numbers (SN) below SN 85078.
(3) The turbofan engines listed in paragraph (c) of this AD are installed on, but not limited to, Fokker F.28 Mk.0070 and Mk.0100 series airplanes, Gulfstream Aerospace GIV and GIVX series airplanes, and Boeing Company 727100 series airplanes modified in accordance with Supplemental Type Certificate SA8472SW (727QF). Unsafe Condition
(d) This AD results from RRD introducing new LP compressor case iceimpact panels with additional retention features, to these Tay turbofan engines. 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.
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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 IceImpact Panels in Tay 62015, Tay 65015, and Tay 65154 Engines
(f) For airplanes that have any Tay 62015, Tay 65015, or Tay 65154 engines with iceimpact panels incorporated by the RR SB No. TAY721326 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, rework all six iceimpact panels using repair scheme HRS3648 or HRS3649 on at least one of the affected engines.
(2) Before further flight, inspect the iceimpact panels and the surrounding fillers on the engine not reworked. Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY 721638, Revision 2, dated September 21, 2004, or SB No. TAY72 1638, Revision 3, dated February 25, 2005, and the inspection disposition criteria in Table 1 of this AD.
Table 1.Inspection Disposition Criteria
If: Then: (i) Any movement or rocking motion of Before further flight, replace LP compressor iceimpact panel, or any all panels using repair scheme movement of the front edge of ice HRS3648 or HRS3649. impact panel.
(ii) Reappearing signs of moisture on Before further flight, replace the iceimpact panel or the all panels using repair scheme surrounding filler. HRS3648 or HRS3649. (iii) Any dents or impact damage on the Before further flight, replace iceimpact panel that is greater than the damaged panel using repair 3.1 square inch in total. scheme HRS3648 or HRS3649. (iv) Any dents or impact damage on the Within 5 flight cycles or 5 iceimpact 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. (v) Any dents or impact damage on the Within 50 flight cycles or 50 iceimpact 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. (vi) Any crack appears on the ice Within 50 flight cycles or 50 impact panel and there is visible flight hours, whichever occurs distortion of the airwashed surface. first, replace the damaged panel using repair scheme HRS3648 or HRS3649. (vii) Any crack appears on the ice Within 150 flight cycles or 150 impact 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. (viii) 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.
(ix) Delamination or peeling of the Within 5 flight cycles or 5 compound layers of the airwashed flight hours, whichever occurs surface and the penetrated area is first, replace the damaged between 1.55 square inch and 3.1 panel using repair scheme square inch in total. HRS3648 or HRS3649. (x) Delamination or peeling of the Within 50 flight cycles or 50 compound layers of the airwashed flight hours, whichever occurs surface and the penetrated area is first, replace the damaged less than 1.55 square inch in total. panel using repair scheme HRS3648 or HRS3649. (xi) 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.
(xii) Missing filler surrounding the LP Before further flight, repair compressor case. the damaged filler using repair scheme HRS3630. (xiii) 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. (3) Reinspect all iceimpact panels within every 500 cycles sincelastinspection (CSLI) or two months sincelastinspection, whichever occurs first. Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY721638, Revision 2, dated September 21, 2004, or SB No. TAY721638, Revision 3, dated February 25, 2005, and the inspection disposition criteria in Table 1 of this AD.
Repetitive Inspections for Tay 62015, Tay 65015, and Tay 65154 Engines With All IceImpact Panels Repaired by Polysulfide Bonding Material
(g) For Tay 62015, Tay 65015, and Tay 65154 engines with ice impact panels incorporated by the RRD SB No. TAY721326 standard, and all panels were repaired using polysulfide bonding material by RR repair scheme TV5451R, HRS3491, HRS3615, HRS3648 or HRS3649, do the following:
(1) Reinspect within every 1,500 CSLI, for the condition of the iceimpact panels and the surrounding fillers.
(2) Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY721638, Revision 2, dated September 21, 2004 or SB No. TAY721638, Revision 3, dated February 25, 2005, and the inspection disposition criteria in Table 1 of this AD. Inspecting IceImpact Panels in Tay 6118 Engines
(h) For airplanes that have any Tay 6118 engines with ice impact panels incorporated by the RR SB No. TAY721326 standard, and RR repair scheme HRS3491 or HRS3615 was done with two pack epoxy (Omat 8/52) on one or more of the six iceimpact panels, do the following:
(1) Before further flight, rework all six iceimpact panels using repair scheme HRS3648 or HRS3649 on at least one of the affected engines.
(2) Before further flight, inspect the iceimpact panels and the surrounding fillers on the engine not reworked. Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY 721639, Revision 2, dated September 21, 2004 and the inspection disposition criteria in Table 1 of this AD.
(3) Reinspect the iceimpact panels within every 1,000
operating hours or six months sincelastinspection, whichever occurs first. Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY721639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD.
Repetitive Inspections for Tay 6118 Engines With All IceImpact Panels Repaired by Polysulfide Bonding Material or Introduced Since New Production
(i) For Tay 6118 engines with iceimpact panels incorporated by the RRD SB No. TAY721326 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) Reinspect within every 3,000 hourssincelastinspection, for the condition of the iceimpact panels and the surrounding fillers.
(2) Use paragraphs 3.C. through 3.E. of the Accomplishment Instructions of RRD SB No. TAY721639, Revision 2, dated September 21, 2004, and the inspection disposition criteria in Table 1 of this AD.
[[Page 1051]]
Installing Tay 62015, Tay 65015, or Tay 65154 Engines That Are Not Inspected
(j) After the effective date of this AD, do not install any Tay 62015, Tay 65015, or Tay 65154 engines with iceimpact panels if: (1) Those iceimpact panels incorporate the RR SB No. TAY72 1326 standard; and
(2) Iceimpact 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) (inservice) or 3.K.(1) through 3.(M)(3) (at overhaul or shop visit) of the Accomplishment Instructions of RRD SB No. TAY721638, Revision 2, dated September 21, 2004, or SB No. TAY721638, Revision 3, dated February 25, 2005.
(k) Perform repetitive inspections as specified in paragraph (g) of this AD.
Installing Tay 6118 Engines That Are Not Inspected
(l) After the effective date of this AD, do not install any Tay 6118 engine with iceimpact panels if:
(1) Those iceimpact panels incorporate the RR SB No. TAY72 1326 standard; and
(2) Iceimpact 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) (inservice) or 3.K.(1) through 3.M.(3) (at overhaul or shop visit) of the Accomplishment
Instructions of RRD SB No. TAY721639, Revision 2, dated September 21, 2004.
(m) Perform repetitive inspections as specified in paragraph (i) of this AD.
Mandatory Terminating Action
(n) No later than December 31, 2011, as mandatory terminating action to the repetitive visual inspections or rework required by paragraphs (f), (g), (h), (i), (j), (k), (l), and (m) of this AD, do the following:
(1) Rework the LP compressor case and install new LP compressor case iceimpact panels with additional retention features, at the next shop visit requiring the removal of any module, except when the work scope requires only the removal of the high speed gearbox module.
(2) For Tay 62015, Tay 65015, and Tay 65154 turbofan engines, do the rework and installation using the Accomplishment Instructions of RRD Alert SB No. TAY72A1643, Revision 1, dated November 2, 2005.
(3) For Tay 6118 turbofan engines, do the rework and
installation using the Accomplishment Instructions of RRD Alert SB No. TAY72A1650, dated November 2, 2005.
Tay 6118C Turbofan Engines
(o) For Tay 6118C turbofan engines, no later than December 31, 2011, do the following:
(1) Rework the LP compressor case and install new LP compressor case iceimpact panels with additional retention features, at the next shop visit after the effective date of this AD, requiring the removal of any module, except when the work scope requires only the removal of the high speed gearbox module.
(2) Do the rework and installation using the Accomplishment Instructions of RRD Alert SB No. TAY72A1650, dated November 2, 2005.
Alternative Methods of Compliance
(p) 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
(q) German AD D2004313R5, dated November 15, 2005, also addresses the subject of this AD.
(r) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: Jason.yang@faa.gov; telephone (781) 2387747; fax (781) 2387199, for more information about this AD.
Material Incorporated by Reference
(s) You must use the service information specified in Table 2 of this AD to perform the inspections and rework required by this AD. Except for Service Bulletin No. TAY721638, Revision 3, Alert Service Bulletin No. TAY72A1643, Revision 1, and Alert Service Bulletin No. TAY72A1650, the Director of the Federal Register previously approved the incorporation by reference of the Rolls Royce Deutschland Ltd & Co KG service information listed in Table 2 of this AD as of January 21, 2005 (70 FR 1172, January 6, 2005). The Director of the Federal Register approved the incorporation by reference of Service Bulletin No. TAY721638, Revision 3, dated February 25, 2005, Alert Service Bulletin No. TAY72A1643, Revision 1, dated November 2, 2005, and Alert Service Bulletin No. TAY72 A1650, dated November 2, 2005, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact RollsRoyce Deutschland Ltd & Co KG, Eschenweg 11, D15827 Dahlewitz, Germany; telephone 49 (0) 337086 1768; fax 49 (0) 3370863356 for a copy of this service
information. You may review copies at the FAA, New England Region, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 2027416030, or go to: http://www.archives.gov/federalregister/cfr/ibrlocations.html. Table 2.Incorporation by Reference Service information No. Page Revision Date SB No. TAY721638................ ALL.................. 2................... September 21, 2004. Total Pages: 35
SB No. TAY721638................ ALL.................. 3................... February 25, 2005. Total Pages: 35
SB No. TAY721639................ ALL.................. 2................... September 21, 2004. Total Pages: 28
Alert SB No. TAY72A1643......... ALL.................. 1................... November 2, 2005. Total Pages: 13
Alert SB No. TAY72A1643 Appendix ALL.................. 1................... November 2, 2005. 1.
Total Pages: 43
Alert SB No. TAY72A1650......... ALL.................. Original............ November 2, 2005. Total Pages: 11
Alert SB No. TAY72A1650 Appendix ALL.................. Original............ November 2, 2005. 1.
Total Pages: 45
Repair Scheme No. HRS3648 Front ALL.................. 2................... January 28, 2004. Sheet.
Total Pages: 1
Repair Scheme No. HRS3648 History ALL.................. 2................... January 28, 2004. Sheet.
Total Pages: 3
Repair Scheme No. HRS3648......... ALL.................. 2................... January 27, 2004. Total Pages: 30
Repair Scheme No. HRS3649 Front ALL.................. 2................... September 1, 2004. Sheet.
Total Pages: 1
Repair Scheme No. HRS3649 History ALL.................. 2................... September 7, 2004. Sheet.
[[Page 1052]]
Total Pages: 3
Repair Scheme No. HRS3649......... ALL.................. 2................... June 17, 2004. Total Pages: 24

Issued in Burlington, Massachusetts, on December 21, 2007. Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service.
[FR Doc. E725497 Filed 1408; 8:45 am]
BILLING CODE 491013P

FOR FURTHER INFORMATION CONTACT Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email:
Jason.yang@faa.gov; telephone (781) 2387747; fax (781) 2387199.