Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650-15 Turbofan Engines, 29405-29407 [E8-10633]

Download as PDF Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations transferred or delivered pursuant to the Order will be subject to the same obligations imposed upon Board and the trustees. (d) Any residual funds not required to defray the necessary expenses of liquidation shall be turned over to the Department to be disposed of, to the extent practical, to one or more honey industry organizations in the interest of continuing honey promotion, research, and information programs. Dated: May 15, 2008. Lloyd C. Day, Administrator, Agricultural Marketing Service. [FR Doc. 08–1282 Filed 5–16–08; 3:33 pm] BILLING CODE 3410–02–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 § 1212.84 Effect of termination or amendment. Unless otherwise expressly provided by the Secretary, terminating or amending this subpart or any regulation issued under it will not: (a) Affect or waive any right, duty, obligation, or liability that arose or may arise in connection with any provision of this part; (b) Release or extinguish any violation of this part; or (c) Affect or impair any rights or remedies of the United States or any person with respect to any violation. § 1212.85 Personal liability. No member, alternate member, or employee of the Board may be held personally responsible, either individually or jointly with others, in any way whatsoever to any person for errors in judgment, mistakes, or other acts, either of commission or omission, as a member, alternate member, or employee, except for acts of dishonesty or willful misconduct. § 1212.86 Separability. If any provision of this subpart is declared invalid or the applicability of it to any person or circumstance is held invalid, the validity of the remainder of this subpart, or the applicability of it to other persons or circumstances will not be affected. § 1212.87 Amendments. Amendments to this Order may be proposed from time to time by the Board or any interested person affected by the provisions of the Act, including the Department. cprice-sewell on PROD1PC69 with RULES § 1212.88 OMB control number. The control number assigned to the information collection requirements in this part by the Office of Management and Budget pursuant to the Paperwork Reduction Act of 1995, 44 U.S.C. Chapter 35, is OMB control number 0505–0001, and OMB control number 0581–[NEW, to be assigned by OMB]. VerDate Aug<31>2005 14:17 May 20, 2008 Jkt 214001 [Docket No. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD; Amendment 39– 15521; AD 2008–10–14] RIN 2120–AA64 Airworthiness Directives; Rolls-Royce Deutschland Ltd. & Co. KG. (RRD) TAY 650–15 Turbofan Engines 29405 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. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on January 2, 2008 (73 FR 75). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states that: AGENCY: SUMMARY: We are adopting a new airworthiness directive (AD) for the products listed above. 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. Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Federal Aviation Administration (FAA), DOT. ACTION: Final rule. 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 stage 2 or stage 3 disk of the low pressure turbine to fail and result in an uncontained failure of the engine. DATES: This AD becomes effective June 25, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 25, 2008. ADDRESSES: The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. PO 00000 Frm 00019 Fmt 4700 Sfmt 4700 Editorial Change To Clarify the Actions and Compliance Section We added the revision date of September 1, 2006, to paragraph (e)(1) to clarify the requirements to that paragraph. Also, we added Tasks 72– 52–23–200–000 and 72–52–24–200–000 to paragraph (e)(3) to clarify the requirements of that paragraph. Conclusion We reviewed the available data and determined that air safety and the public interest require adopting the AD with the changes described previously. We determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. 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 work-hours to replace the disk. Required parts would cost about $40,000 per product. Based on these E:\FR\FM\21MYR1.SGM 21MYR1 29406 Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations 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. cprice-sewell on PROD1PC69 with RULES 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. available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. 14:17 May 20, 2008 Jkt 214001 Engine Serial No. 17561 17562 17563 17580 17581 17612 17618 17635 17637 17645 17661 17686 17699 17701 17702 17736 17737 17738 17739 17741 17742 17808 Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA 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 Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: I 2008–10–14 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly Rolls-Royce plc, Derby, England): Amendment 39–15521. FAA–2007–0037; Directorate Identifier 2007–NE–41–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 25, 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 No. PO 00000 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 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 17251 17255 17256 17273 17275 17280 17281 17282 17300 17301 17327 17332 17365 17393 17437 17443 17470 17520 17521 17523 17539 17542 17556 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 provided in the ADDRESSES section. Comments will be VerDate Aug<31>2005 TABLE 1.—AFFECTED TAY 650–15 ENGINES BY SERIAL NUMBER—Continued Frm 00020 Fmt 4700 Sfmt 4700 (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 disks stage 2 and stage 3 for corrosion in accordance with RRD Alert Service Bulletin TAY–72–A1524, Revision 1, dated September 1, 2006. (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 information on performing the inspection for corrosion and rejection criteria. E:\FR\FM\21MYR1.SGM 21MYR1 Federal Register / Vol. 73, No. 99 / Wednesday, May 21, 2008 / Rules and Regulations 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. Material Incorporated by Reference (i) You must use Rolls-Royce Deutschland Alert Service Bulletin TAY–72–A1524, Revision 1, dated September 1, 2006, to do the actions required by this AD, unless the AD specifies otherwise. (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 May 5, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–10633 Filed 5–20–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2007–29069; Directorate Identifier 2007–NM–176–AD; Amendment 39–15525; AD 2008–11–03] cprice-sewell on PROD1PC69 with RULES RIN 2120–AA64 Airworthiness Directives; Boeing Model 737–100, –200, and –200C Series Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Final rule. AGENCY: VerDate Aug<31>2005 14:17 May 20, 2008 SUMMARY: We are adopting a new airworthiness directive (AD) for all Boeing Model 737–100, –200, and –200C series airplanes. This AD requires revising the FAA-approved maintenance inspection program to include inspections that will give no less than the required damage tolerance rating for each structural significant item (SSI), doing repetitive inspections to detect cracks of all SSIs, and repairing cracked structure. This AD results from a report of incidents involving fatigue cracking in transport category airplanes that are approaching or have exceeded their design service objective. We are issuing this AD to maintain the continued structural integrity of the entire fleet of Model 737–100, –200, and –200C series airplanes. DATES: This AD is effective June 25, 2008. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 25, 2008. The Director of the Federal Register approved the incorporation by reference of Boeing Document D6–37089, ‘‘Supplemental Structural Inspection Document for Model 737–100/200/200C Airplanes,’’ Revision E, dated May 2007, as listed in this AD, on May 27, 2008 (73 FR 21237, April 21, 2008). ADDRESSES: For service information identified in this AD, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124–2207. Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov; or in person at the Docket Management Facility 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 address for the Docket Office (telephone 800–647–5527) is the Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. FOR FURTHER INFORMATION CONTACT: Nancy Marsh, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 917–6440; fax (425) 917–6590. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR Jkt 214001 PO 00000 Frm 00021 Fmt 4700 Sfmt 4700 29407 part 39 to include an airworthiness directive (AD) that would apply to all Boeing Model 737–100, –200, and –200C series airplanes. That NPRM was published in the Federal Register on August 31, 2007 (72 FR 50294). That NPRM proposed to require revising the FAA-approved maintenance inspection program to include inspections that will give no less than the required damage tolerance rating for each structural significant item (SSI), doing repetitive inspections to detect cracks of all SSIs, and repairing cracked structure. Comments We gave the public the opportunity to participate in developing this AD. We considered the comments received from the one commenter. Request To Allow Alternative Inspections for Previously Repaired/ Altered Structure Boeing requests that the NPRM be revised to include a provision for alternative inspections when a repair area prohibits operators from doing the inspections required by paragraph (i) of the NPRM. Boeing requests that the initial alternative inspection be done within 12 months after the repair is discovered during the initial inspection required by paragraph (i) of the NPRM. Boeing points out that a similar provision was provided in paragraph (e) of AD 98–11–04 R1, amendment 39– 10984 (64 FR 987, January 7, 1999). Boeing states that including such a provision will assist operators. We agree. We have added a new paragraph (j) to this AD (and reidentified subsequent paragraphs) that provides for alternative inspections to those in paragraph (i) of this AD. Request To Clarify Certain Sections of the Preamble of the NPRM Boeing requests that certain sections in the preamble of the NPRM be clarified for the following reasons: 1. Boeing states that Advisory Circular (AC) No. 91–56, ‘‘Supplemental Structural Inspection Program for Large Transport Category Airplanes,’’ dated May 6, 1981, applies to airplanes certified under the fail-safe and fatigue requirements of Civil Air Regulations (CAR) 4b or part 25 of the Federal Aviation Regulations (14 CFR part 25), not damage tolerance structural requirements as stated in the Issuance of Advisory Circular (AC) section. 2. Boeing notes that the Other Relevant Rulemaking section identifies the strut as one of the affected SSIs for Model 737–100, –200, and –200C series airplanes. Boeing states that those airplanes do not have an engine strut. E:\FR\FM\21MYR1.SGM 21MYR1

Agencies

[Federal Register Volume 73, Number 99 (Wednesday, May 21, 2008)]
[Rules and Regulations]
[Pages 29405-29407]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-10633]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0037; Directorate Identifier 2007-NE-41-AD; 
Amendment 39-15521; AD 2008-10-14]
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.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. 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 stage 2 or 
stage 3 disk of the low pressure turbine to fail and result in an 
uncontained failure of the engine.

DATES: This AD becomes effective June 25, 2008. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in this AD as of June 25, 2008.

ADDRESSES: The Docket Operations office is located at Docket Management 
Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, 
SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-
0001.

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.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on January 2, 2008 (73 
FR 75). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states that:

    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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM or on the determination of 
the cost to the public.

Editorial Change To Clarify the Actions and Compliance Section

    We added the revision date of September 1, 2006, to paragraph 
(e)(1) to clarify the requirements to that paragraph. Also, we added 
Tasks 72-52-23-200-000 and 72-52-24-200-000 to paragraph (e)(3) to 
clarify the requirements of that paragraph.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

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 work-
hours to replace the disk. Required parts would cost about $40,000 per 
product. Based on these

[[Page 29406]]

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 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.

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 provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

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 adding the following new AD:

2008-10-14 Rolls-Royce Deutschland Ltd & Co KG (RRD) (formerly 
Rolls-Royce plc, Derby, England): Amendment 39-15521. FAA-2007-0037; 
Directorate Identifier 2007-NE-41-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 25, 
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 No.
-------------------------------------------------------------------------
17251
17255
17256
17273
17275
17280
17281
17282
17300
17301
17327
17332
17365
17393
17437
17443
17470
17520
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 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 
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 disks stage 2 and stage 3 for 
corrosion in accordance with RRD Alert Service Bulletin TAY-72-
A1524, Revision 1, dated September 1, 2006.

    (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 information on performing the 
inspection for corrosion and rejection criteria.

[[Page 29407]]

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.

Material Incorporated by Reference

    (i) You must use Rolls-Royce Deutschland Alert Service Bulletin 
TAY-72-A1524, Revision 1, dated September 1, 2006, to do the actions 
required by this AD, unless the AD specifies otherwise.
    (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 May 5, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
 [FR Doc. E8-10633 Filed 5-20-08; 8:45 am]
BILLING CODE 4910-13-P
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