Airworthiness Directives; Rolls-Royce Deutschland (Formerly Rolls-Royce plc) Models Tay 650-15 and 651-54 Turbofan Engines, 77299-77301 [05-24642]

Download as PDF Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Rules and Regulations International, Inc., apply at a later date for a supplemental type certificate to modify any other model on the same type certificate to incorporate the same novel or unusual design feature, the special conditions would apply to that model as well under the provisions of § 21.101. Conclusion This action affects only certain novel or unusual design features on one model of airplane. It is not a rule of general applicability and affects only the applicant who applied to the FAA for approval of these features on the airplane. The substance of these special conditions has been subjected to the notice and comment period in several prior instances and has been derived without substantive change from those previously issued. It is unlikely that prior public comment would result in a significant change from the substance contained herein. For this reason, and because a delay would significantly affect the certification of the airplane, which is imminent, the FAA has determined that prior public notice and comment are unnecessary and impracticable, and good cause exists for adopting these special conditions upon issuance. The FAA is requesting comments to allow interested persons to submit views that may not have been submitted in response to the prior opportunities for comment described above. List of Subjects in 14 CFR Part 23 Aircraft, Aviation safety, Signs and symbols. Citation The authority citation for these special conditions is as follows: I wwhite on PROD1PC61 with RULES Authority: 49 U.S.C. 106(g), 40113 and 44701; 14 CFR 21.16 and 21.101; and 14 CFR 11.38 and 11.19. The Special Conditions I Accordingly, pursuant to the authority delegated to me by the Administrator, the following special conditions are issued as part of the type certification basis for the Mooney M20M and M20R airplanes modified by Garmin International, Inc., to add the GFC–700 autopilot system. 1. Protection of Electrical and Electronic Systems from High Intensity Radiated Fields (HIRF). Each system that performs critical functions must be designed and installed to ensure that the operations, and operational capabilities of these systems to perform critical functions, are not adversely affected when the airplane is exposed to high VerDate Aug<31>2005 17:36 Dec 29, 2005 Jkt 208001 intensity radiated electromagnetic fields external to the airplane. 2. For the purpose of these special conditions, the following definition applies: Critical Functions: Functions whose failure would contribute to, or cause, a failure condition that would prevent the continued safe flight and landing of the airplane. Issued in Kansas City, Missouri on December 21, 2005. Kim Smith, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 05–24668 Filed 12–29–05; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. 2001–NE–02–AD; Amendment 39–14439; AD 2005–26–18] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland (Formerly Rolls-Royce plc) Models Tay 650–15 and 651–54 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: SUMMARY: The FAA is superseding an existing airworthiness directive (AD) for Rolls-Royce Deutschland (formerly Rolls-Royce plc) (RRD) models Tay 650– 15 and 651–54 turbofan engines. That AD currently requires borescope inspection of the high pressure compressor (HPC) stage 12 disc assembly to detect damage caused by HPC outlet guide vane (OGV) retaining bolt failure, and replacement of unserviceable parts with serviceable parts. That AD also requires as terminating action, the incorporation of a new design retention arrangement for the HPC OGV to prevent HPC OGV retaining bolt failure. This ad requires the same actions but extends the terminating action compliance time for Tay 650–15 engines. This AD also includes references to later revisions of two of the applicable RRD service bulletins (SBs). This AD results from RRD relaxing the terminating action compliance time for Tay 650–15 engines due to reassessment by RRD. We are issuing this AD to prevent an uncontained failure of the HPC stage 11/ 12 disc spacer, which could result in damage to the airplane. DATES: This AD becomes effective February 3, 2006. The Director of the PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 77299 Federal Register previously approved the incorporation by reference of certain publications listed in the regulations as of February 15, 2002 (67 FR 4652, January 31, 2002). ADDRESSES: You can get the service information identified in this AD from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 15827 BlankenfeldeMahlow, Germany, telephone: 011 49 (0) 33–7086–1768, fax: 011 49 (0) 33– 7086–3356. You may examine the AD docket at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. You may examine the service information, at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA. 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: The FAA proposed to amend 14 CFR part 39 with a proposed airworthiness directive (AD). The proposed AD applies to RRD models Tay 650–15 and 651–54 turbofan engines. We published the proposed AD in the Federal Register on July 25, 2005 (70 FR 42515). That action proposed to require the same actions as AD 2002–01–29 but extends the terminating action compliance time for Tay 650–15 engines. Examining the AD Docket You may examine the AD Docket (including any comments and service information), by appointment, between 8 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. See ADDRESSES for the location. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance There are about 400 Tay 650–15 and 651–54 turbofan engines of the affected design in the worldwide fleet. We estimate that 105 engines installed on airplanes of U.S. registry will be affected by this AD. We also estimate that it will E:\FR\FM\30DER1.SGM 30DER1 77300 Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Rules and Regulations take about 3 work hours per engine to perform the proposed borescope inspection, and that the average labor rate is $65 per work hour. Required parts will cost about $3,200 per engine. We estimate that one third of the engines will have the parts replaced at time of engine overhaul. We also estimate that one third of the engines will have the parts replaced during an engine mid-life shop visit. We also estimate that one third of the engines will have the parts replaced at an engine shop visit dedicated for these parts replacements, at a cost of about $90,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $3,600,000. Special Flight Permits Paragraph Removed Paragraph (f) of the current AD, AD 2002–01–29, contains a paragraph pertaining to special flight permits. Even though this AD does not contain a similar paragraph, we have made no changes with regard to the use of special flight permits to operate the airplane to a repair facility to do the work required by this AD. In July 2002, we published a new Part 39 that contains a general authority regarding special flight permits and airworthiness directives; see Docket No. FAA–2004–8460, Amendment 39–9474 (69 FR 47998, July 22, 2002). Thus, when we now supersede ADs we will not include a specific paragraph on special flight permits unless we want to limit the use of that general authority granted in section 39.23. wwhite on PROD1PC61 with RULES Authority for This Rulemaking 17:36 Dec 29, 2005 Jkt 208001 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 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. VerDate Aug<31>2005 Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary by sending a request to us at the address listed under ADDRESSES. Include ‘‘AD Docket No. 2001–NE–02– AD’’ in your request. Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–12624 (67 FR 4652, January 31, 2002) and by adding a new airworthiness directive, Amendment 39–14439, to read as follows: I 2005–26–18 Rolls-Royce Deutschland (formerly Rolls-Royce plc): Amendment 39–14439. Docket No. 2001–NE–02–AD. Effective Date (a) This AD becomes effective February 3, 2006. Affected ADs (b) This AD supersedes AD 2002–01–29. (c) This AD applies to Rolls-Royce Deutschland (formerly Rolls-Royce plc) (RRD) models Tay 650–15 and 651–54 turbofan engines with high pressure compressor (HPC) outlet guide vane (OGV) PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 retaining bolts part numbers (P/Ns) BLT3602, DU909, and DU818 installed. These engines are installed on, but not limited to Boeing 727 and Fokker F.28 Mark 0100 airplanes. Unsafe Condition (d) This AD results from RRD relaxing the terminating action compliance time for Tay 650–15 engines due to reassessment by RRD. We are issuing this AD to prevent an uncontained failure of the HPC stage 11/12 disc spacer, which could result in 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. Initial Inspection (f) Perform a borescope inspection of the rear side of the stage 12 rotor disc at or before accumulating 8,000 cycles-since-new on the OGV retaining bolts, or within 30 days from the effective date of this AD, whichever occurs later. Use paragraph 3.A.(1) of the Accomplishment Instructions of RRD Mandatory Service Bulletin (MSB) Tay–72– 1483, Revision 2, dated October 20, 2000, to do the inspection. If damage is observed on the stage 12 rotor disc, remove the engine from service. Repetitive Inspections (g) Thereafter, perform repetitive borescope inspections of the rear side of the stage 12 rotor disc no earlier than 1,800 and no later than 2,200 cycles-since-last-inspection, or no later than 18 months since-last-inspection, whichever occurs first. Use paragraph 3.A.(1) of the Accomplishment Instructions of RRD MSB Tay–72–1483, Revision 2, dated October 20, 2000, to do the inspections. If damage is observed on the stage 12 rotor disc, remove the engine from service. OGV Retaining Bolt Replacement (h) For engines that had OGV bolts replaced with new bolts P/Ns BLT3602, DU909, and DU818 as specified in RRD SB Tay–72–1484, dated November 15, 1999, or Revision 1, dated December 17, 1999, the initial and repetitive inspection requirements, based on engine cycles-sincebolt installation, are the same as specified in paragraphs (f) and (g) of this AD. Terminating Action (i) As terminating action for the inspections required by this AD, do the following: (1) Before November 1, 2007, for Tay 650– 15 engines, and before October 1, 2012, for Tay 651–54 engines, remove from service the parts listed in the following Table 1: TABLE 1.—PARTS TO BE REMOVED FROM SERVICE Part No. Part name JR12314A .... HPT Rotor Inner Seal Support Assembly. HP Compressor Outlet Guide Vane 5-Span. EU57842A .... E:\FR\FM\30DER1.SGM 30DER1 Federal Register / Vol. 70, No. 250 / Friday, December 30, 2005 / Rules and Regulations TABLE 1.—PARTS TO BE REMOVED FROM SERVICE—Continued Part No. Part name EU57843A .... HP Compressor Outlet Guide Vane 6-Span. HP Rotor Thrust Bearing Housing Assembly. Diffuser Case Assembly. Tab Washer. Retaining Lock Plate. Hex Head Bolt. JR30962A .... JR30568A .... KB7106 ........ EU12042 ...... DU818 .......... Alternative Methods of Compliance (k) 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 (l) Luftfhart Bundesamt airworthiness directive D–2004–365, dated January 31, 2005, also addresses the subject of this AD. Material Incorporated by Reference wwhite on PROD1PC61 with RULES (m) You must use Rolls-Royce Mandatory Service Bulletin Tay–72–1483, Revision 2, dated October 20, 2000, to perform the inspections required by this AD. The Director of the Federal Register previously approved the incorporation by reference of this service bulletin as of February 15, 2002 (67 FR 4652, January 31, 2002), 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, 15827 BlankenfeldeMahlow, Germany, telephone: 011 49 (0) 33– 7086–1768, fax: 011 49 (0) 33–7086–3356. You can review copies at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: https://www.archives.gov/federal-register/ cfr/ibr-locations.html. Issued in Burlington, Massachusetts, on December 23, 2005. Carlos Pestana, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 05–24642 Filed 12–29–05; 8:45 am] VerDate Aug<31>2005 17:36 Dec 29, 2005 Jkt 208001 Federal Aviation Administration 14 CFR Part 39 (2) Information on removing these parts from service can be found in RRD MSB Tay– 72–1498, dated October 20, 2000, or RRD MSB Tay–72–1498, Revision 1, dated December 1, 2000, or RRD SB Tay–72–1498, Revision 2, dated December 31, 2004. (j) After performing the actions specified in paragraph (i) of this AD, the inspections specified in paragraphs (f) through (h) of this AD are no longer required. BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION [Docket No. FAA–2005–21611; Directorate Identifier 2004–NM–234–AD; Amendment 39–14438; AD 2005–26–17] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model A300 C4– 605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes); and Model A310–200 and –300 Series Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A300–600, A310–200, and A310–300 series airplanes. This AD requires inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and doing corrective actions if necessary. This AD results from reports of debonded skins on the elevators. We are issuing this AD to detect and correct debonding of the skins on the elevators, which could cause reduced structural integrity of an elevator and reduced controllability of the airplane. DATES: This AD becomes effective February 3, 2006. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of February 3, 2006. ADDRESSES: You may examine the AD docket on the Internet at https:// 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 Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, for service information identified in this AD. FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, International Branch, ANM–116, FAA, PO 00000 Frm 00005 Fmt 4700 Sfmt 4700 77301 Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055–4056; telephone (425) 227–2797; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: Examining the Docket You may examine the AD docket on the Internet at https://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 part 39 to include an AD that would apply to certain Airbus Model A300 B4– 600, B4–600R, and F4–600R series airplanes; Model A300 C4–605R Variant F airplanes (collectively called A300– 600 series airplanes); and Model A310 series airplanes. That NPRM was published in the Federal Register on June 22, 2005 (70 FR 36073). That NPRM proposed to require inspecting for certain serial numbers on elevators, and doing a detailed inspection, visual inspection with a low-angle light, and tap-test inspection of the upper and lower surfaces of the external skins on certain identified elevators for any damage (i.e., debonding of the graphite fiber reinforced plastic/Tedlar film protection, bulges, debonding of the honeycomb core to the carbon fiber reinforced plastic, abnormal surface reflections, and torn-out plies), and corrective actions if necessary. Comments We provided the public the opportunity to participate in the development of this AD. We have considered the comment received. Request To Clarify Applicability The commenter, the airplane manufacturer, requests that we clarify the applicability statement of the proposed AD. The proposed AD states that the AD would apply to affected models ‘‘equipped with carbon fiber elevators having part number (P/N) A55276055000 (left-hand side) or P/N A55276056000 (right-hand side).’’ The commenter notes that the related French airworthiness directive states that it is effective for affected models ‘‘equipped with carbon fiber elevators P/N A55276055000 (left-hand side) and P/N A55276056000 (right-hand side), installed as per modification 4805, * * *.’’ The commenter asks that we E:\FR\FM\30DER1.SGM 30DER1

Agencies

[Federal Register Volume 70, Number 250 (Friday, December 30, 2005)]
[Rules and Regulations]
[Pages 77299-77301]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-24642]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-02-AD; Amendment 39-14439; AD 2005-26-18]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland (Formerly 
Rolls-Royce plc) Models Tay 650-15 and 651-54 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Rolls-Royce Deutschland (formerly Rolls-Royce plc) (RRD) 
models Tay 650-15 and 651-54 turbofan engines. That AD currently 
requires borescope inspection of the high pressure compressor (HPC) 
stage 12 disc assembly to detect damage caused by HPC outlet guide vane 
(OGV) retaining bolt failure, and replacement of unserviceable parts 
with serviceable parts. That AD also requires as terminating action, 
the incorporation of a new design retention arrangement for the HPC OGV 
to prevent HPC OGV retaining bolt failure. This ad requires the same 
actions but extends the terminating action compliance time for Tay 650-
15 engines. This AD also includes references to later revisions of two 
of the applicable RRD service bulletins (SBs). This AD results from RRD 
relaxing the terminating action compliance time for Tay 650-15 engines 
due to reassessment by RRD. We are issuing this AD to prevent an 
uncontained failure of the HPC stage 11/12 disc spacer, which could 
result in damage to the airplane.

DATES: This AD becomes effective February 3, 2006. The Director of the 
Federal Register previously approved the incorporation by reference of 
certain publications listed in the regulations as of February 15, 2002 
(67 FR 4652, January 31, 2002).

ADDRESSES: You can get the service information identified in this AD 
from Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 15827 
Blankenfelde-Mahlow, Germany, telephone: 011 49 (0) 33-7086-1768, fax: 
011 49 (0) 33-7086-3356.
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA. You may examine the service information, at the FAA, 
New England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA.

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: The FAA proposed to amend 14 CFR part 39 
with a proposed airworthiness directive (AD). The proposed AD applies 
to RRD models Tay 650-15 and 651-54 turbofan engines. We published the 
proposed AD in the Federal Register on July 25, 2005 (70 FR 42515). 
That action proposed to require the same actions as AD 2002-01-29 but 
extends the terminating action compliance time for Tay 650-15 engines.

Examining the AD Docket

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

Comments

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

Conclusion

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

Costs of Compliance

    There are about 400 Tay 650-15 and 651-54 turbofan engines of the 
affected design in the worldwide fleet. We estimate that 105 engines 
installed on airplanes of U.S. registry will be affected by this AD. We 
also estimate that it will

[[Page 77300]]

take about 3 work hours per engine to perform the proposed borescope 
inspection, and that the average labor rate is $65 per work hour. 
Required parts will cost about $3,200 per engine. We estimate that one 
third of the engines will have the parts replaced at time of engine 
overhaul. We also estimate that one third of the engines will have the 
parts replaced during an engine mid-life shop visit. We also estimate 
that one third of the engines will have the parts replaced at an engine 
shop visit dedicated for these parts replacements, at a cost of about 
$90,000 per engine. Based on these figures, we estimate the total cost 
of the AD to U.S. operators to be $3,600,000.

Special Flight Permits Paragraph Removed

    Paragraph (f) of the current AD, AD 2002-01-29, contains a 
paragraph pertaining to special flight permits. Even though this AD 
does not contain a similar paragraph, we have made no changes with 
regard to the use of special flight permits to operate the airplane to 
a repair facility to do the work required by this AD. In July 2002, we 
published a new Part 39 that contains a general authority regarding 
special flight permits and airworthiness directives; see Docket No. 
FAA-2004-8460, Amendment 39-9474 (69 FR 47998, July 22, 2002). Thus, 
when we now supersede ADs we will not include a specific paragraph on 
special flight permits unless we want to limit the use of that general 
authority granted in section 39.23.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
subtitle VII, part A, subpart III, section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 2001-NE-02-AD'' in your request.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-12624 (67 FR 
4652, January 31, 2002) and by adding a new airworthiness directive, 
Amendment 39-14439, to read as follows:

2005-26-18 Rolls-Royce Deutschland (formerly Rolls-Royce plc): 
Amendment 39-14439. Docket No. 2001-NE-02-AD.

Effective Date

    (a) This AD becomes effective February 3, 2006.

Affected ADs

    (b) This AD supersedes AD 2002-01-29.
    (c) This AD applies to Rolls-Royce Deutschland (formerly Rolls-
Royce plc) (RRD) models Tay 650-15 and 651-54 turbofan engines with 
high pressure compressor (HPC) outlet guide vane (OGV) retaining 
bolts part numbers (P/Ns) BLT3602, DU909, and DU818 installed. These 
engines are installed on, but not limited to Boeing 727 and Fokker 
F.28 Mark 0100 airplanes.

Unsafe Condition

    (d) This AD results from RRD relaxing the terminating action 
compliance time for Tay 650-15 engines due to reassessment by RRD. 
We are issuing this AD to prevent an uncontained failure of the HPC 
stage 11/12 disc spacer, which could result in 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.

Initial Inspection

    (f) Perform a borescope inspection of the rear side of the stage 
12 rotor disc at or before accumulating 8,000 cycles-since-new on 
the OGV retaining bolts, or within 30 days from the effective date 
of this AD, whichever occurs later. Use paragraph 3.A.(1) of the 
Accomplishment Instructions of RRD Mandatory Service Bulletin (MSB) 
Tay-72-1483, Revision 2, dated October 20, 2000, to do the 
inspection. If damage is observed on the stage 12 rotor disc, remove 
the engine from service.

Repetitive Inspections

    (g) Thereafter, perform repetitive borescope inspections of the 
rear side of the stage 12 rotor disc no earlier than 1,800 and no 
later than 2,200 cycles-since-last-inspection, or no later than 18 
months since-last-inspection, whichever occurs first. Use paragraph 
3.A.(1) of the Accomplishment Instructions of RRD MSB Tay-72-1483, 
Revision 2, dated October 20, 2000, to do the inspections. If damage 
is observed on the stage 12 rotor disc, remove the engine from 
service.

OGV Retaining Bolt Replacement

    (h) For engines that had OGV bolts replaced with new bolts P/Ns 
BLT3602, DU909, and DU818 as specified in RRD SB Tay-72-1484, dated 
November 15, 1999, or Revision 1, dated December 17, 1999, the 
initial and repetitive inspection requirements, based on engine 
cycles-since-bolt installation, are the same as specified in 
paragraphs (f) and (g) of this AD.

Terminating Action

    (i) As terminating action for the inspections required by this 
AD, do the following:
    (1) Before November 1, 2007, for Tay 650-15 engines, and before 
October 1, 2012, for Tay 651-54 engines, remove from service the 
parts listed in the following Table 1:

               Table 1.--Parts To Be Removed From Service
------------------------------------------------------------------------
              Part No.                             Part name
------------------------------------------------------------------------
JR12314A............................  HPT Rotor Inner Seal Support
                                       Assembly.
EU57842A............................  HP Compressor Outlet Guide Vane 5-
                                       Span.

[[Page 77301]]

 
EU57843A............................  HP Compressor Outlet Guide Vane 6-
                                       Span.
JR30962A............................  HP Rotor Thrust Bearing Housing
                                       Assembly.
JR30568A............................  Diffuser Case Assembly.
KB7106..............................  Tab Washer.
EU12042.............................  Retaining Lock Plate.
DU818...............................  Hex Head Bolt.
------------------------------------------------------------------------

    (2) Information on removing these parts from service can be 
found in RRD MSB Tay-72-1498, dated October 20, 2000, or RRD MSB 
Tay-72-1498, Revision 1, dated December 1, 2000, or RRD SB Tay-72-
1498, Revision 2, dated December 31, 2004.
    (j) After performing the actions specified in paragraph (i) of 
this AD, the inspections specified in paragraphs (f) through (h) of 
this AD are no longer required.

Alternative Methods of Compliance

    (k) 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

    (l) Luftfhart Bundesamt airworthiness directive D-2004-365, 
dated January 31, 2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (m) You must use Rolls-Royce Mandatory Service Bulletin Tay-72-
1483, Revision 2, dated October 20, 2000, to perform the inspections 
required by this AD. The Director of the Federal Register previously 
approved the incorporation by reference of this service bulletin as 
of February 15, 2002 (67 FR 4652, January 31, 2002), 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, 15827 
Blankenfelde-Mahlow, Germany, telephone: 011 49 (0) 33-7086-1768, 
fax: 011 49 (0) 33-7086-3356. You can review copies at the FAA, New 
England Region, Office of the Regional Counsel, 12 New England 
Executive Park, Burlington, MA; or at the National Archives and 
Records Administration (NARA). For information on the availability 
of this material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on December 23, 2005.
Carlos Pestana,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 05-24642 Filed 12-29-05; 8:45 am]
BILLING CODE 4910-13-P

This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.