Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650-15 Turbofan Engines, 75-77 [E7-25457]

Download as PDF Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that the proposed 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 regulatory evaluation of the estimated costs to comply with this supplemental NPRM and placed it in the AD docket. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 Federal Aviation Administration (FAA) amends § 39.13 by adding the following new airworthiness directive (AD): Boeing: Docket No. FAA–2007–28348; Directorate Identifier 2007–NM–060–AD. Comments Due Date (a) The FAA must receive comments on this AD action by January 28, 2008. Inspection (g) Within 60 months after the effective date of this AD: Perform a general visual inspection of the wire bundle support installation in the equipment cooling system bays to identify the type of clamp installed, and determine whether the Teflon sleeve is installed. Do these actions in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1279, dated January 24, 2007. Do all applicable corrective actions before further flight in accordance with the service bulletin. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (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 appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Issued in Renton, Washington, on December 20, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7–25477 Filed 12–31–07; 8:45 am] DEPARTMENT OF TRANSPORTATION Federal Aviation Administration Applicability (c) This AD applies to Model 737–600, –700, –700C, –800 and –900 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 737–57A1279, dated January 24, 2007. mstockstill on PROD1PC66 with PROPOSALS Fastener Sealant (f) Within 60 months after the effective date of this AD: Seal the fasteners on the front and rear spars inside the main fuel tank and on the lower panel of the center fuel tank, as applicable, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–57A1279, dated January 24, 2007. BILLING CODE 4910–13–P Affected ADs (b) None. Unsafe Condition (d) This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent arcing at certain fuel tank fasteners in the event of a lightning strike or fault current event, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane. VerDate Aug<31>2005 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. 16:49 Dec 31, 2007 Jkt 214001 14 CFR Part 39 [Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650–15 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 75 SUMMARY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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 states the following: Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs 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 proposing this AD to detect corrosion that could cause stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine. DATES: We must receive comments on this proposed AD by February 1, 2008. 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: Docket Management Facility, 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 proposed 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:\FR\FM\02JAP1.SGM 02JAP1 76 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules e-mail: jason.yang@faa.gov; telephone (781) 238–7747; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed 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 proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on 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 we receive about this proposed AD. Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Airworthiness Directive 2006–0288, dated September 15, 2006, to correct an unsafe condition for the specified products. The EASA AD states: Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs 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. You may obtain further information by examining the MCAI in the AD docket. mstockstill on PROD1PC66 with PROPOSALS Relevant Service Information RRD has issued Alert Service Bulletin No. TAY–72–A1524, Revision 1, dated September 1, 2006. 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 Proposed AD This product has been approved by the aviation authority of Germany, and is approved for operation in the United States. Under this bilateral airworthiness agreement, the EASA has VerDate Aug<31>2005 16:49 Dec 31, 2007 Jkt 214001 kept the FAA informed of the situation described above. We have examined the findings of the EASA, 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. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about two engines installed on airplanes of U.S. registry. We also estimate that it would take about 1.0 work-hours per product to inspect the disk, and that the average labor rate is $80 per work-hour. If corrosion is found, we estimate that it would take about 2.0 work-hours to replace the disk. Required parts would cost about $40,000 per product. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $80,480. Our cost estimate is exclusive of possible warranty coverage. 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. 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 proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc, Derby, England): Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD. Comments Due Date (a) We must receive comments by February 1, 2008. Affected ADs (b) None. Applicability (c) This AD applies to RRD TAY 650–15 turbofan engines that have a serial number listed in Table 1 of this AD, and low pressure 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 Regulatory Findings We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed 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 PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: E:\FR\FM\02JAP1.SGM Engine serial number 17251 17255 17256 17273 17275 17280 17281 17282 17300 17301 17327 17332 17365 17393 17437 17443 17470 17520 02JAP1 Federal Register / Vol. 73, No. 1 / Wednesday, January 2, 2008 / Proposed Rules TABLE 1.—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER—Continued Engine serial number 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 Issued in Burlington, Massachusetts, on December 26, 2007. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E7–25457 Filed 12–31–07; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION mstockstill on PROD1PC66 with PROPOSALS 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 low pressure turbine discs stage 2 and stage 3 for corrosion in accordance with Rolls-Royce Deutschland Non-Modification Alert Service Bulletin TAY–72–A1524, Revision 1. (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 using the rejection criteria described in the 16:49 Dec 31, 2007 Other FAA AD Provisions (f) Alternative Methods of Compliance (AMOCs): 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 (g) Refer to EASA Airworthiness Directive 2006–0288, dated September 15, 2006, and RRD Alert Service Bulletin TAY–72–A1524, Revision 1, dated September 1, 2006, for related information. (h) 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. Reason (d) Strip results from some of the engines listed in the applicability section of this directive revealed excessively corroded low pressure turbine discs 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 proposing this AD to detect corrosion that could cause stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine. VerDate Aug<31>2005 Rolls-Royce TAY 650 Engine Manual—ETAY–3RR. Jkt 214001 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2006–24145; Directorate Identifier 2006–NE–06–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company CF6–45 and CF6–50 Series Turbofan Engines Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of comment period. AGENCY: SUMMARY: This supplemental NPRM revises an earlier proposed airworthiness directive (AD), applicable to certain General Electric Company (GE) CF6–45 and CF6–50 series turbofan engines. That proposed AD would have required inspecting and reworking certain forward and aft centerbodies of the long fixed core exhaust nozzle (LFCEN) assembly. That proposed AD resulted from reports of separation of the forward and aft centerbodies of the LFCEN assembly due to high-imbalance engine conditions. This supplemental NPRM revises the proposed AD to add one engine model, and by replacing the LFCEN instead of repairing the centerbodies. This proposed AD results from the engine manufacturer issuing PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 77 new service information. We are proposing this AD to prevent the forward and aft centerbody of the LFCEN assembly from separating, leading to additional damage to the airplane. DATES: We must receive any comments on this proposed AD by February 19, 2008. ADDRESSES: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, 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. You can get the service information identified in this proposed AD from General Electric Company via GEAviation, Attn: Distributions, 111 Merchant St., Room 230, Cincinnati, Ohio 45246, telephone (513) 552–3272; fax (513) 552–3329. FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone (781) 238–7754; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send us any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2006–24145; Directorate Identifier 2006–NE–06–AD’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light 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 proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, E:\FR\FM\02JAP1.SGM 02JAP1

Agencies

[Federal Register Volume 73, Number 1 (Wednesday, January 2, 2008)]
[Proposed Rules]
[Pages 75-77]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-25457]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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 states the following:

    Strip results from some of the engines listed in the 
applicability section of this directive revealed excessively 
corroded low pressure turbine discs 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 proposing this AD to detect corrosion that could cause stage 2 
or stage 3 disk of the low pressure turbine to fail and result in an 
uncontained failure of the engine.

DATES: We must receive comments on this proposed AD by February 1, 
2008.

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: Docket Management Facility, 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 proposed 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;

[[Page 76]]

e-mail: jason.yang@faa.gov; telephone (781) 238-7747; fax (781) 238-
7199.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed 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 proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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 we 
receive about this proposed AD.

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2006-0288, dated September 15, 2006, to correct 
an unsafe condition for the specified products. The EASA AD states:

    Strip results from some of the engines listed in the 
applicability section of this directive revealed excessively 
corroded low pressure turbine discs 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.

    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    RRD has issued Alert Service Bulletin No. TAY-72-A1524, Revision 1, 
dated September 1, 2006. 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 Proposed AD

    This product has been approved by the aviation authority of 
Germany, and is approved for operation in the United States. Under this 
bilateral airworthiness agreement, the EASA has kept the FAA informed 
of the situation described above. We have examined the findings of the 
EASA, 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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about two engines installed on airplanes of U.S. registry. 
We also estimate that it would take about 1.0 work-hours per product to 
inspect the disk, and that the average labor rate is $80 per work-hour. 
If corrosion is found, we estimate that it would take about 2.0 work-
hours to replace the disk. Required parts would cost about $40,000 per 
product. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $80,480. Our cost estimate is 
exclusive of possible warranty coverage.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new AD:

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

Comments Due Date

    (a) We must receive comments by February 1, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to RRD TAY 650-15 turbofan engines that have 
a serial number listed in Table 1 of this AD, and low pressure 
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
------------------------------------------------------------------------
                       Engine serial number
------------------------------------------------------------------
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520

[[Page 77]]

 
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 low pressure turbine discs 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 proposing this AD to detect corrosion that could cause 
stage 2 or stage 3 disk of the low pressure 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 low pressure turbine discs stage 2 and stage 3 for 
corrosion in accordance with Rolls-Royce Deutschland Non-
Modification Alert Service Bulletin TAY-72-A1524, Revision 1.
    (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 using the rejection criteria described in the Rolls-Royce TAY 
650 Engine Manual--E-TAY-3RR.

Other FAA AD Provisions

    (f) Alternative Methods of Compliance (AMOCs): 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

    (g) Refer to EASA Airworthiness Directive 2006-0288, dated 
September 15, 2006, and RRD Alert Service Bulletin TAY-72-A1524, 
Revision 1, dated September 1, 2006, for related information.
    (h) 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.

    Issued in Burlington, Massachusetts, on December 26, 2007.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E7-25457 Filed 12-31-07; 8:45 am]
BILLING CODE 4910-13-P
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