Airworthiness Directives; International Aero Engines AG (IAE) V2500-A1, V2527E-A5, V2530-A5, and V2528-D5 Turbofan Engines, 54895-54896 [E9-25644]

Download as PDF 54895 Rules and Regulations Federal Register Vol. 74, No. 205 Monday, October 26, 2009 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. Prices of new books are listed in the first FEDERAL REGISTER issue of each week. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0294; Directorate Identifier 2009–NE–08–AD; Amendment 39–16057; AD 2009–22–06] RIN 2120–AA64 Airworthiness Directives; International Aero Engines AG (IAE) V2500–A1, V2527E–A5, V2530–A5, and V2528–D5 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule. erowe on DSK5CLS3C1PROD with RULES AGENCY: SUMMARY: The FAA is adopting a new airworthiness directive (AD) for International Aero Engines AG (IAE) V2500–A1, V2527E–A5, V2530–A5, and V2528–D5 turbofan engines. This AD requires reducing the published life limit of certain high-pressure compressor (HPC) stage 9–12 disc assemblies. This AD also removes from service those HPC stage 9–12 disc assemblies using a drawdown schedule. This AD results from IAE updating the low-cycle-fatigue (LCF) life analysis for certain HPC stage 9–12 disc assemblies. We are issuing this AD to prevent an uncontained failure of the HPC stage 9–12 disc assembly, resulting in an inflight engine shutdown and possible damage to the airplane. DATES: This AD becomes effective November 30, 2009. ADDRESSES: You can get the service information identified in this AD from International Aero Engines AG, 400 Main Street, East Hartford, CT 06108; telephone: (860) 565–5515; fax: (860) 565–5510. The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building VerDate Nov<24>2008 14:49 Oct 23, 2009 Jkt 220001 Ground Floor, Room W12–140, Washington, DC 20590–0001. FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to IAE V2500–A1, V2527E–A5, V2530–A5, and V2528–D5 turbofan engines. We published the proposed AD in the Federal Register on June 29, 2009 (74 FR 30981). That action proposed to require reducing the published life limit of certain HPC stage 9–12 disc assemblies. That action also proposed to remove from service those HPC stage 9–12 disc assemblies using a drawdown schedule. 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. Comments We provided the public the opportunity to participate in the development of this AD. We received no comments on the proposal or on the determination of the cost to the public. Conclusion We have carefully reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed. Costs of Compliance We estimate that this AD will affect 18 engines installed on airplanes of U.S. registry. We also estimate that it will take about 200 work-hours per engine to perform the actions, and that the average labor rate is $80 per work-hour. The prorated cost due to a life reduction for a HPC stage 9–12 disc assembly PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 installed in a V2500–A1 engine, is about $5,600 per engine, and for one installed in a V2527E–A5, V2530–A5, or V2528– D5 engine, is about $29,700 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $485,200. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, ‘‘General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We have determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. For the reasons discussed above, I certify that this AD: (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a summary of the costs to comply with this AD and placed it in the AD Docket. You may get a copy of this summary at the address listed under ADDRESSES. E:\FR\FM\26OCR1.SGM 26OCR1 54896 Federal Register / Vol. 74, No. 205 / Monday, October 26, 2009 / Rules and Regulations List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the Federal Aviation Administration amends 14 CFR part 39 as follows: ■ PART 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 adding the following new airworthiness directive: ■ 2009–22–06 International Aero Engines AG: Amendment 39–16057. Docket No. FAA–2009–0294; Directorate Identifier 2009–NE–08–AD. Effective Date (a) This airworthiness directive (AD) becomes effective November 30, 2009. Affected ADs (b) None. Applicability (c) This AD applies to International Aero Engines AG (IAE) V2500–A1, V2527E–A5, V2530–A5, and V2528–D5 turbofan engines. These engines are installed on, but not limited to, Airbus A320 and A321 series, and McDonnell Douglas Corporation MD–90 airplanes. Unsafe Condition (d) This AD results from IAE updating the low-cycle-fatigue (LCF) life analysis for certain high-pressure compressor (HPC) stage 9–12 disc assemblies. We are issuing this AD to prevent an uncontained failure of the HPC stage 9–12 disc assembly, resulting in an inflight engine shutdown and possible damage to the airplane. erowe on DSK5CLS3C1PROD with RULES 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. V2500–A1 Turbofan Engines (f) For V2500–A1 turbofan engines with HPC stage 9–12 disc assemblies, P/N 2A3200, 2A3300, 2A3400, 2A3500, 6A4131, and 6A7545, installed, remove from service as follows: (1) For HPC stage 9–12 disc assemblies that have accumulated fewer than 12,000 cyclessince-new (CSN) on the effective date of this AD, remove from service before the disc assembly accumulates 14,600 CSN. (2) For HPC stage 9–12 disc assemblies that have accumulated 12,000 or more CSN but fewer than 14,600 CSN on the effective date of this AD: (i) If the next engine shop visit will occur before accumulating 14,600 CSN, then VerDate Nov<24>2008 14:49 Oct 23, 2009 Jkt 220001 remove from service before accumulating 14,600 CSN. (ii) If the next engine shop visit will occur upon accumulating 14,600 or more CSN, then remove from service at the next engine shop visit but not to exceed 15,000 CSN. (3) For HPC stage 9–12 disc assemblies that have accumulated 14,600 or more CSN on the effective date of this AD, remove from service at the next engine shop visit but not to exceed 15,000 CSN. V2527E–A5 and V2530–A5 Turbofan Engines (g) For V2527E–A5 and V2530–A5 turbofan engines with HPC stage 9–12 disc assemblies, P/N 6A4156 and 6A7547 installed, remove from service as follows: (1) For HPC stage 9–12 disc assemblies that have accumulated fewer than 9,000 CSN on the effective date of this AD, remove from service before the disc assembly accumulates 11,800 CSN. (2) For HPC stage 9–12 disc assemblies that have accumulated 9,000 or more CSN but fewer than 11,800 CSN on the effective date of this AD: (i) If the next engine shop visit will occur before accumulating 11,800 CSN, then remove from service before accumulating 11,800 CSN. (ii) If the next engine shop visit will occur upon accumulating 11,800 or more CSN, then remove from service at the next engine shop visit but not to exceed 12,000 CSN. (3) For HPC stage 9–12 disc assemblies that have accumulated 11,800 or more CSN on the effective date of this AD, remove from service at the next engine shop visit but not to exceed 12,000 CSN. V2528–D5 Turbofan Engines (h) For V2528–D5 turbofan engines with HPC stage 9–12 disc assemblies, P/N 6A4156 and 6A7547 installed, remove from service as follows: (1) For HPC stage 9–12 disc assemblies that have accumulated fewer than 9,000 CSN on the effective date of this AD, remove from service before the disc assembly accumulates 11,800 CSN. (2) For HPC stage 9–12 disc assemblies that have accumulated 9,000 or more CSN but fewer than 11,800 CSN on the effective date of this AD: (i) If the next engine shop visit will occur before accumulating 11,800 CSN, then remove from service before accumulating 11,800 CSN. (ii) If the next engine shop visit will occur upon accumulating 11,800 or more CSN, then remove from service at the next engine shop visit but not to exceed 13,200 CSN. (3) For HPC stage 9–12 disc assemblies that have accumulated 11,800 or more CSN on the effective date of this AD, remove from service at the next engine shop visit but not to exceed 13,200 CSN. Definition (i) For the purpose of this AD, an ‘‘engine shop visit’’ is the induction of an engine into the shop for maintenance involving the separation of pairs of major mating engine flanges except that the separation of engine flanges solely for the purposes of transportation without subsequent engine PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 maintenance does not constitute an engine shop visit. Alternative Methods of Compliance (j) The Manager, Engine Certification Office, has the authority to approve alternative methods of compliance for this AD if requested using the procedures found in 14 CFR 39.19. Related Information (k) IAE Alert Service Bulletin No. V2500– ENG–72–A0554, Revision 1, dated June 27, 2008, also pertains to the subject of this AD. Contact International Aero Engines AG, 400 Main Street, East Hartford, CT 06108; telephone: (860) 565–5515; fax: (860) 565– 5510, for a copy of this service information. (l) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: Kevin.dickert@faa.gov; telephone (781) 238–7117; fax (781) 238– 7199, for more information about this AD. Material Incorporated by Reference (m) None. Issued in Burlington, Massachusetts, on October 16, 2009. Robert J. Ganley, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–25644 Filed 10–23–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2009–0128; Airspace Docket No. 08–ASW–15] RIN 2120–AA66 Amendment of Federal Airways V–163 and V–358 in the Lampasas, TX, Area AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: This action amends the legal descriptions of two Federal airways that have ‘‘Lampasas, TX, very high frequency omnidirectional range/ tactical air navigation (VORTAC)’’ included as part of their route structure. Currently, the Lampasas VORTAC and the Lampasas Airport share the same location name and identifier (LZZ). To eliminate confusion and potential flight safety issues, the ‘‘Lampasas VORTAC’’ (LZZ) will be renamed the ‘‘Gooch Springs VORTAC’’ (AGJ). All airways with Lampasas [VORTAC] included in their legal descriptions will be amended, concurrent with the effective date of this final rule, to reflect the name change. E:\FR\FM\26OCR1.SGM 26OCR1

Agencies

[Federal Register Volume 74, Number 205 (Monday, October 26, 2009)]
[Rules and Regulations]
[Pages 54895-54896]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-25644]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 
Prices of new books are listed in the first FEDERAL REGISTER issue of each 
week.

========================================================================


Federal Register / Vol. 74, No. 205 / Monday, October 26, 2009 / 
Rules and Regulations

[[Page 54895]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0294; Directorate Identifier 2009-NE-08-AD; 
Amendment 39-16057; AD 2009-22-06]
RIN 2120-AA64


Airworthiness Directives; International Aero Engines AG (IAE) 
V2500-A1, V2527E-A5, V2530-A5, and V2528-D5 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
International Aero Engines AG (IAE) V2500-A1, V2527E-A5, V2530-A5, and 
V2528-D5 turbofan engines. This AD requires reducing the published life 
limit of certain high-pressure compressor (HPC) stage 9-12 disc 
assemblies. This AD also removes from service those HPC stage 9-12 disc 
assemblies using a drawdown schedule. This AD results from IAE updating 
the low-cycle-fatigue (LCF) life analysis for certain HPC stage 9-12 
disc assemblies. We are issuing this AD to prevent an uncontained 
failure of the HPC stage 9-12 disc assembly, resulting in an in-flight 
engine shutdown and possible damage to the airplane.

DATES: This AD becomes effective November 30, 2009.

ADDRESSES: You can get the service information identified in this AD 
from International Aero Engines AG, 400 Main Street, East Hartford, CT 
06108; telephone: (860) 565-5515; fax: (860) 565-5510.
    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: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to IAE V2500-A1, V2527E-A5, 
V2530-A5, and V2528-D5 turbofan engines. We published the proposed AD 
in the Federal Register on June 29, 2009 (74 FR 30981). That action 
proposed to require reducing the published life limit of certain HPC 
stage 9-12 disc assemblies. That action also proposed to remove from 
service those HPC stage 9-12 disc assemblies using a drawdown schedule.

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.

Comments

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

Conclusion

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

Costs of Compliance

    We estimate that this AD will affect 18 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
200 work-hours per engine to perform the actions, and that the average 
labor rate is $80 per work-hour. The prorated cost due to a life 
reduction for a HPC stage 9-12 disc assembly installed in a V2500-A1 
engine, is about $5,600 per engine, and for one installed in a V2527E-
A5, V2530-A5, or V2528-D5 engine, is about $29,700 per engine. Based on 
these figures, we estimate the cost of the AD on U.S. operators to be 
$485,200.

Authority for This Rulemaking

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

Regulatory Findings

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

    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and
    (3) Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

[[Page 54896]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive:

2009-22-06 International Aero Engines AG: Amendment 39-16057. Docket 
No. FAA-2009-0294; Directorate Identifier 2009-NE-08-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective November 
30, 2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to International Aero Engines AG (IAE) 
V2500-A1, V2527E-A5, V2530-A5, and V2528-D5 turbofan engines. These 
engines are installed on, but not limited to, Airbus A320 and A321 
series, and McDonnell Douglas Corporation MD-90 airplanes.

Unsafe Condition

    (d) This AD results from IAE updating the low-cycle-fatigue 
(LCF) life analysis for certain high-pressure compressor (HPC) stage 
9-12 disc assemblies. We are issuing this AD to prevent an 
uncontained failure of the HPC stage 9-12 disc assembly, resulting 
in an in-flight engine shutdown and possible damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

V2500-A1 Turbofan Engines

    (f) For V2500-A1 turbofan engines with HPC stage 9-12 disc 
assemblies, P/N 2A3200, 2A3300, 2A3400, 2A3500, 6A4131, and 6A7545, 
installed, remove from service as follows:
    (1) For HPC stage 9-12 disc assemblies that have accumulated 
fewer than 12,000 cycles-since-new (CSN) on the effective date of 
this AD, remove from service before the disc assembly accumulates 
14,600 CSN.
    (2) For HPC stage 9-12 disc assemblies that have accumulated 
12,000 or more CSN but fewer than 14,600 CSN on the effective date 
of this AD:
    (i) If the next engine shop visit will occur before accumulating 
14,600 CSN, then remove from service before accumulating 14,600 CSN.
    (ii) If the next engine shop visit will occur upon accumulating 
14,600 or more CSN, then remove from service at the next engine shop 
visit but not to exceed 15,000 CSN.
    (3) For HPC stage 9-12 disc assemblies that have accumulated 
14,600 or more CSN on the effective date of this AD, remove from 
service at the next engine shop visit but not to exceed 15,000 CSN.

V2527E-A5 and V2530-A5 Turbofan Engines

    (g) For V2527E-A5 and V2530-A5 turbofan engines with HPC stage 
9-12 disc assemblies, P/N 6A4156 and 6A7547 installed, remove from 
service as follows:
    (1) For HPC stage 9-12 disc assemblies that have accumulated 
fewer than 9,000 CSN on the effective date of this AD, remove from 
service before the disc assembly accumulates 11,800 CSN.
    (2) For HPC stage 9-12 disc assemblies that have accumulated 
9,000 or more CSN but fewer than 11,800 CSN on the effective date of 
this AD:
    (i) If the next engine shop visit will occur before accumulating 
11,800 CSN, then remove from service before accumulating 11,800 CSN.
    (ii) If the next engine shop visit will occur upon accumulating 
11,800 or more CSN, then remove from service at the next engine shop 
visit but not to exceed 12,000 CSN.
    (3) For HPC stage 9-12 disc assemblies that have accumulated 
11,800 or more CSN on the effective date of this AD, remove from 
service at the next engine shop visit but not to exceed 12,000 CSN.

V2528-D5 Turbofan Engines

    (h) For V2528-D5 turbofan engines with HPC stage 9-12 disc 
assemblies, P/N 6A4156 and 6A7547 installed, remove from service as 
follows:
    (1) For HPC stage 9-12 disc assemblies that have accumulated 
fewer than 9,000 CSN on the effective date of this AD, remove from 
service before the disc assembly accumulates 11,800 CSN.
    (2) For HPC stage 9-12 disc assemblies that have accumulated 
9,000 or more CSN but fewer than 11,800 CSN on the effective date of 
this AD:
    (i) If the next engine shop visit will occur before accumulating 
11,800 CSN, then remove from service before accumulating 11,800 CSN.
    (ii) If the next engine shop visit will occur upon accumulating 
11,800 or more CSN, then remove from service at the next engine shop 
visit but not to exceed 13,200 CSN.
    (3) For HPC stage 9-12 disc assemblies that have accumulated 
11,800 or more CSN on the effective date of this AD, remove from 
service at the next engine shop visit but not to exceed 13,200 CSN.

Definition

    (i) For the purpose of this AD, an ``engine shop visit'' is the 
induction of an engine into the shop for maintenance involving the 
separation of pairs of major mating engine flanges except that the 
separation of engine flanges solely for the purposes of 
transportation without subsequent engine maintenance does not 
constitute an engine shop visit.

Alternative Methods of Compliance

    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Related Information

    (k) IAE Alert Service Bulletin No. V2500-ENG-72-A0554, Revision 
1, dated June 27, 2008, also pertains to the subject of this AD. 
Contact International Aero Engines AG, 400 Main Street, East 
Hartford, CT 06108; telephone: (860) 565-5515; fax: (860) 565-5510, 
for a copy of this service information.
    (l) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
Kevin.dickert@faa.gov; telephone (781) 238-7117; fax (781) 238-7199, 
for more information about this AD.

Material Incorporated by Reference

    (m) None.

    Issued in Burlington, Massachusetts, on October 16, 2009.
Robert J. Ganley,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-25644 Filed 10-23-09; 8:45 am]
BILLING CODE 4910-13-P