Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) Tay 650-15 Turbofan Engines, 55121-55123 [E9-25031]

Download as PDF Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations Alternative Methods of Compliance (AMOCs) DEPARTMENT OF TRANSPORTATION (j)(1) The Manager, International Branch, ANM–116, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. (2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. Federal Aviation Administration Related Information (k) European Aviation Safety Agency Airworthiness Directive 2007–0094 R1, dated May 2, 2007, also addresses the subject of this AD. Material Incorporated by Reference pwalker on DSK8KYBLC1PROD with RULES (l) You must use Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register previously approved the incorporation by reference of Airbus A300 Fuel Airworthiness Limitations, Document 95A.1928/05, Issue 2, dated May 11, 2007, on November 28, 2007 (72 FR 60240, October 24, 2007). (2) For service information identified in this AD, contact Airbus SAS—EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; e-mail: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221 or 425–227–1152. (4) You may also review copies of the service information that is incorporated by reference 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. Issued in Renton, Washington, on October 19, 2009. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E9–25772 Filed 10–26–09; 8:45 am] BILLING CODE 4910–13–P VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 14 CFR Part 39 [Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD; Amendment 39– 16052; AD 2009–22–01] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) Tay 650–15 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. SUMMARY: We are superseding an existing airworthiness directive (AD) for the products listed above. That AD currently requires initial and repetitive inspections of the low-pressure (LP) turbine discs stage 2 and stage 3 for corrosion, on certain serial number engines. This AD requires the same actions, but extends the applicability to additional engine serial numbers. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low-pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. DATES: This AD becomes effective November 12, 2009. We must receive comments on this AD by November 27, 2009. The Director of the Federal Register approved the incorporation by reference of Rolls-Royce Deutschland Alert Service Bulletin No. TAY–72–A1524, Revision 2, dated June 13, 2008, listed in the AD as of November 12, 2009. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow PO 00000 Frm 00033 Fmt 4700 Sfmt 4700 55121 the instructions for sending your comments electronically. • Mail: U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199. Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33–7086–1768; fax 49 (0) 33–7086–3356, for the service information referenced in this AD. SUPPLEMENTARY INFORMATION: Discussion On May 5, 2008, the FAA issued AD 2008–10–14 (Amendment 39–15521 (73 FR 29405, May 21, 2008). That AD requires initial and repetitive inspections of the LP turbine discs stage 2 and stage 3 for corrosion on 45 engines by serial number. That AD was the result of MCAI issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. That condition, if not corrected, could result in the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. Since AD 2008–10–14 was issued, RRD identified 34 additional engines by serial number that require the same inspections. The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2008– 0122, dated July 1, 2008. That MCAI E:\FR\FM\27OCR1.SGM 27OCR1 55122 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations extends the applicability to include the 34 additional engine serial numbers for inspections. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Rolls-Royce Deutschland has issued Alert Service Bulletin No. TAY–72– A1524, Revision 2, dated June 13, 2008. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. FAA’s Determination and Requirements of This AD Although no airplanes that are registered in the United States use these RRD Tay 650–15 engines, the possibility exists that the engines could be used on airplanes that are registered in the United States in the future. The unsafe condition described previously is likely to exist or develop on other RRD Tay 650–15 engines of the same type design. We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. This AD requires initial and repetitive inspections of the LP turbine discs stage 2 and stage 3 for corrosion on certain serial number engines. You must use the service information described previously to perform the actions required by this AD. pwalker on DSK8KYBLC1PROD with RULES FAA’s Determination of the Effective Date Since no domestic operators use this product, notice and opportunity for public comment before issuing this AD are unnecessary. Therefore, we are adopting this regulation immediately. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any VerDate Nov<24>2008 16:23 Oct 26, 2009 Jkt 220001 personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). 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 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 this AD: 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 regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. PO 00000 Frm 00034 Fmt 4700 Sfmt 4700 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 FAA amends 14 CFR part 39 as follows: ■ PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by removing Amendment 39–15521 (73 FR 29405, May 21, 2008), and by adding a new airworthiness directive, Amendment 39–16052, to read as follows: ■ 2009–22–01 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc, Derby, England): Amendment 39–16052. Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 12, 2009. Affected ADs (b) This AD supersedes AD 2008–10–14, Amendment 39–15521. Applicability (c) This AD applies to RRD Tay 650–15 turbofan engines that have a serial number listed in Table 1 or Table 2 of this AD, and low-pressure (LP) turbine module M05300AA installed. These engines are installed on, but not limited to, Fokker F28 Mark 0100 airplanes. TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED FORWARD FROM AD 2008–10–14) Engine Serial Number 17251 17255 17256 17273 17275 17280 17281 17282 17300 17301 17327 17332 17365 17393 17437 17443 17470 17520 E:\FR\FM\27OCR1.SGM 27OCR1 Federal Register / Vol. 74, No. 206 / Tuesday, October 27, 2009 / Rules and Regulations TABLE 1—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (CARRIED FORWARD FROM AD 2008–10– 14)—Continued Engine Serial Number Engine Serial Number 17760 17807 17521 17523 17539 17542 17556 17561 17562 17563 17580 17581 17612 17618 17635 17637 17645 17661 17686 17699 17701 17702 17736 17737 17738 17739 17741 17742 17808 Reason (d) Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded lowpressure turbine disks stage 2 and stage 3. The corrosion is considered to be caused by the environment in which these engines are operated. Following a life assessment based on the strip findings it is concluded that inspections for corrosion attack are required. The action specified by this AD is intended to avoid a failure of a low-pressure turbine disk stage 2 or stage 3 due to potential corrosion problems which could result in uncontained engine failure and damage to the airplane. We are issuing this AD to detect corrosion that could cause the stage 2 or stage 3 disk of the LP turbine to fail and result in an uncontained failure of the engine. TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED NEW IN THIS AD) Engine Serial Number pwalker on DSK8KYBLC1PROD with RULES TABLE 2—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER (ADDED NEW IN THIS AD)—Continued 17249 17303 17358 17370 17425 17426 17433 17438 17445 17446 17460 17474 17478 17490 17491 17517 17518 17522 17534 17535 17536 17538 17540 17541 17552 17553 17585 17613 17723 17724 17740 17759 VerDate Nov<24>2008 Actions and Compliance (e) Unless already done, do the following actions. (1) Prior to accumulating 11,700 flight cycles (FC) since new, and thereafter at intervals not exceeding 11,700 FC of the engine, inspect the LP turbine disks stage 2 and stage 3 for corrosion in accordance with RRD Alert Service Bulletin No. TAY–72– A1524, Revision 2, dated June 13, 2008. (2) For engines that already exceed 11,700 FC on the effective date of this AD, perform the inspection within 90 days after the effective date of this AD. (3) When, during any of the inspections as required by paragraph (e)(1) of this directive, corrosion is found, replace the affected parts. The RRD TAY 650 Engine Manual—E–TAY– 3RR, Tasks 72–52–23–200–000 and 72–52– 24–200–000 contains guidance on performing the inspection for corrosion and rejection criteria. Previous Credit (f) Initial inspections done before the effective date of this AD on LP turbine disks stage 2 and stage 3 listed in Table 1 of this AD using RRD Alert Service Bulletin No. TAY–72–A1524, Revision 1, dated September 1, 2006, comply with the initial inspection requirements specified in this AD. Alternative Methods of Compliance (AMOCs) (g) The Manager, Engine Certification Office, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Related Information (h) Refer to European Aviation Safety Agency AD 2008–0122, dated July 1, 2008, for related information. (i) Contact Jason Yang, Aerospace Engineer, Engine Certification Office, FAA, 16:23 Oct 26, 2009 Jkt 220001 PO 00000 Frm 00035 Fmt 4700 Sfmt 4700 55123 Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199, for more information about this AD. Material Incorporated by Reference (j) You must use Rolls-Royce Deutschland Alert Service Bulletin No. TAY–72–A1524, Revision 2, dated June 13, 2008, to do the actions required by this AD. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33–7086–1768; fax 49 (0) 33–7086– 3356. (3) 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 (202) 741–6030, or go to: https://www. archives.gov/federal-register/cfr/ibrlocations.html. Issued in Burlington, Massachusetts, on October 8, 2009. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–25031 Filed 10–26–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0996; Directorate Identifier 2009–NM–156–AD; Amendment 39–16061; AD 2007–21–14 R1] RIN 2120–AA64 Airworthiness Directives; Airbus Model A310 Airplanes AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is revising an existing airworthiness directive (AD), which applies to all Airbus Model A310 airplanes. That AD currently requires revising the Airworthiness Limitations Section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from fuel system reviews conducted by the manufacturer. We are E:\FR\FM\27OCR1.SGM 27OCR1

Agencies

[Federal Register Volume 74, Number 206 (Tuesday, October 27, 2009)]
[Rules and Regulations]
[Pages 55121-55123]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-25031]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD; 
Amendment 39-16052; AD 2009-22-01]
RIN 2120-AA64


Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. 
(RRD) Tay 650-15 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
for the products listed above. That AD currently requires initial and 
repetitive inspections of the low-pressure (LP) turbine discs stage 2 
and stage 3 for corrosion, on certain serial number engines. This AD 
requires the same actions, but extends the applicability to additional 
engine serial numbers. This AD results from mandatory continuing 
airworthiness information (MCAI) issued by an aviation authority of 
another country to identify and correct an unsafe condition on an 
aviation product. The MCAI describes the unsafe condition as:

    Strip results from some of the engines listed in the 
applicability section of this directive revealed excessively 
corroded low-pressure turbine disks stage 2 and stage 3. The 
corrosion is considered to be caused by the environment in which 
these engines are operated. Following a life assessment based on the 
strip findings it is concluded that inspections for corrosion attack 
are required. The action specified by this AD is intended to avoid a 
failure of a low-pressure turbine disk stage 2 or stage 3 due to 
potential corrosion problems which could result in uncontained 
engine failure and damage to the airplane.

We are issuing this AD to detect corrosion that could cause the stage 2 
or stage 3 disk of the LP turbine to fail and result in an uncontained 
failure of the engine.

DATES: This AD becomes effective November 12, 2009.
    We must receive comments on this AD by November 27, 2009.
    The Director of the Federal Register approved the incorporation by 
reference of Rolls-Royce Deutschland Alert Service Bulletin No. TAY-72-
A1524, Revision 2, dated June 13, 2008, listed in the AD as of November 
12, 2009.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: U.S. Department of Transportation, 1200 New Jersey 
Avenue, SE., West Building Ground Floor, Room W12-140, Washington, DC 
20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this AD, the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (telephone (800) 647-5527) is the same as 
the Mail address provided in the ADDRESSES section. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Jason Yang, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-7199.
    Contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, 
Dahlwitz, 15827 Blankenfelde-Mahlow, Germany; telephone 49 (0) 33-7086-
1768; fax 49 (0) 33-7086-3356, for the service information referenced 
in this AD.

SUPPLEMENTARY INFORMATION:

Discussion

    On May 5, 2008, the FAA issued AD 2008-10-14 (Amendment 39-15521 
(73 FR 29405, May 21, 2008). That AD requires initial and repetitive 
inspections of the LP turbine discs stage 2 and stage 3 for corrosion 
on 45 engines by serial number. That AD was the result of MCAI issued 
by an aviation authority of another country to identify and correct an 
unsafe condition on an aviation product. That condition, if not 
corrected, could result in the stage 2 or stage 3 disk of the LP 
turbine to fail and result in an uncontained failure of the engine.
    Since AD 2008-10-14 was issued, RRD identified 34 additional 
engines by serial number that require the same inspections. The 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2008-0122, dated July 1, 2008. That MCAI

[[Page 55122]]

extends the applicability to include the 34 additional engine serial 
numbers for inspections.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Rolls-Royce Deutschland has issued Alert Service Bulletin No. TAY-
72-A1524, Revision 2, dated June 13, 2008. The actions described in 
this service information are intended to correct the unsafe condition 
identified in the MCAI.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these RRD Tay 650-15 engines, the possibility exists that the engines 
could be used on airplanes that are registered in the United States in 
the future. The unsafe condition described previously is likely to 
exist or develop on other RRD Tay 650-15 engines of the same type 
design. We are issuing this AD to detect corrosion that could cause the 
stage 2 or stage 3 disk of the LP turbine to fail and result in an 
uncontained failure of the engine. This AD requires initial and 
repetitive inspections of the LP turbine discs stage 2 and stage 3 for 
corrosion on certain serial number engines. You must use the service 
information described previously to perform the actions required by 
this AD.

FAA's Determination of the Effective Date

    Since no domestic operators use this product, notice and 
opportunity for public comment before issuing this AD are unnecessary. 
Therefore, we are adopting this regulation immediately.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2007-0037; Directorate 
Identifier 2007-NE-41-AD'' at the beginning of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this AD. We will consider all 
comments received by the closing date and may amend this AD because of 
those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this AD. Using the search function of the 
Web site, anyone can find and read the comments in any of our dockets, 
including, if provided, the name of the individual who sent the comment 
(or signed the comment on behalf of an association, business, labor 
union, etc.). You may review the DOT's complete Privacy Act Statement 
in the Federal Register published on April 11, 2000 (65 FR 19477-78).

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 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 this AD:
    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 regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 FAA 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 39-15521 (73 FR 
29405, May 21, 2008), and by adding a new airworthiness directive, 
Amendment 39-16052, to read as follows:

2009-22-01 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly 
Rolls-Royce plc, Derby, England): Amendment 39-16052. Docket No. 
FAA-2007-0037; Directorate Identifier 2007-NE-41-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
12, 2009.

Affected ADs

    (b) This AD supersedes AD 2008-10-14, Amendment 39-15521.

Applicability

    (c) This AD applies to RRD Tay 650-15 turbofan engines that have 
a serial number listed in Table 1 or Table 2 of this AD, and low-
pressure (LP) turbine module M05300AA installed. These engines are 
installed on, but not limited to, Fokker F28 Mark 0100 airplanes.

 Table 1--Affected Tay 650-15 Engines by Serial Number (Carried Forward
                           From AD 2008-10-14)
------------------------------------------------------------------------
                          Engine Serial Number
-------------------------------------------------------------------------
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520

[[Page 55123]]

 
17521
17523
17539
17542
17556
17561
17562
17563
17580
17581
17612
17618
17635
17637
17645
17661
17686
17699
17701
17702
17736
17737
17738
17739
17741
17742
17808
------------------------------------------------------------------------


Table 2--Affected Tay 650-15 Engines by Serial Number (Added New in This
                                   AD)
------------------------------------------------------------------------
                          Engine Serial Number
-------------------------------------------------------------------------
17249
17303
17358
17370
17425
17426
17433
17438
17445
17446
17460
17474
17478
17490
17491
17517
17518
17522
17534
17535
17536
17538
17540
17541
17552
17553
17585
17613
17723
17724
17740
17759
17760
17807
------------------------------------------------------------------------

Reason

    (d) Strip results from some of the engines listed in the 
applicability section of this directive revealed excessively 
corroded low-pressure turbine disks stage 2 and stage 3. The 
corrosion is considered to be caused by the environment in which 
these engines are operated. Following a life assessment based on the 
strip findings it is concluded that inspections for corrosion attack 
are required. The action specified by this AD is intended to avoid a 
failure of a low-pressure turbine disk stage 2 or stage 3 due to 
potential corrosion problems which could result in uncontained 
engine failure and damage to the airplane.
    We are issuing this AD to detect corrosion that could cause the 
stage 2 or stage 3 disk of the LP turbine to fail and result in an 
uncontained failure of the engine.

Actions and Compliance

    (e) Unless already done, do the following actions.
    (1) Prior to accumulating 11,700 flight cycles (FC) since new, 
and thereafter at intervals not exceeding 11,700 FC of the engine, 
inspect the LP turbine disks stage 2 and stage 3 for corrosion in 
accordance with RRD Alert Service Bulletin No. TAY-72-A1524, 
Revision 2, dated June 13, 2008.
    (2) For engines that already exceed 11,700 FC on the effective 
date of this AD, perform the inspection within 90 days after the 
effective date of this AD.
    (3) When, during any of the inspections as required by paragraph 
(e)(1) of this directive, corrosion is found, replace the affected 
parts. The RRD TAY 650 Engine Manual--E-TAY-3RR, Tasks 72-52-23-200-
000 and 72-52-24-200-000 contains guidance on performing the 
inspection for corrosion and rejection criteria.

Previous Credit

    (f) Initial inspections done before the effective date of this 
AD on LP turbine disks stage 2 and stage 3 listed in Table 1 of this 
AD using RRD Alert Service Bulletin No. TAY-72-A1524, Revision 1, 
dated September 1, 2006, comply with the initial inspection 
requirements specified in this AD.

Alternative Methods of Compliance (AMOCs)

    (g) The Manager, Engine Certification Office, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19.

Related Information

    (h) Refer to European Aviation Safety Agency AD 2008-0122, dated 
July 1, 2008, for related information.
    (i) Contact Jason Yang, Aerospace Engineer, Engine Certification 
Office, FAA, Engine & Propeller Directorate, 12 New England 
Executive Park, Burlington, MA 01803; e-mail: jason.yang@faa.gov; 
telephone (781) 238-7747; fax (781) 238-7199, for more information 
about this AD.

Material Incorporated by Reference

    (j) You must use Rolls-Royce Deutschland Alert Service Bulletin 
No. TAY-72-A1524, Revision 2, dated June 13, 2008, to do the actions 
required by this AD.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this AD, contact 
Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlwitz, 15827 
Blankenfelde-Mahlow, Germany; telephone 49 (0) 33-7086-1768; fax 49 
(0) 33-7086-3356.
    (3) 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 (202) 741-6030, or go 
to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on October 8, 2009.
Diane S. Romanosky,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-25031 Filed 10-26-09; 8:45 am]
BILLING CODE 4910-13-P
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