Airworthiness Directives; Honeywell International Inc. ALF502L-2 and ALF502L-2C Turbofan Engines, 16755-16758 [E9-8264]

Download as PDF Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations Costs of Compliance We estimate that this AD will affect 3 out of 316 CF6–80A series turbofan engines installed on airplanes of U.S. registry. We also estimate that it will take about 1 work-hour per engine to perform the actions if the engine is already removed and disassembled to piece-part exposure of the disk, and will take about 115 work-hours per engine for an unplanned engine shop visit. The average labor rate is $80 per work-hour. Required parts would cost about $300,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $927,600. List of Subjects in 14 CFR Part 39 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. § 39.13 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. VerDate Nov<24>2008 18:17 Apr 10, 2009 Jkt 217001 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. [Amended] 2. The FAA amends § 39.13 by adding the following new airworthiness directive: ■ 2009–08–06 General Electric Company: Amendment 39–15879. Docket No. FAA–2008–0827; Directorate Identifier 2008–NE–26–AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 18, 2009. (b) None. Applicability (c) This AD applies to General Electric Company (GE) CF6–80A series turbofan engines with any of the following stage 1 high-pressure turbine (HPT) rotor disk part numbers (P/Ns), installed: (1) 1380M69G01; 1380M69G02; 1380M69G04; 1380M69G05; or 1380M69G06; or (2) 9234M67G12; 9234M67G13; 9234M67G14; 9234M67G15; or 9234M67G16; or (3) 9362M58G04; or (4) 9367M45G01; 9367M45G03; 9367M45G05; 9367M45G06; 9367M45G07; or 9367M45G08. (d) These CF6–80A series turbofan engines are installed on, but not limited to, Airbus A310–200 series and Boeing 767–200 and –300 series airplanes. Unsafe Condition (e) This AD results from the FAA learning that those disks are susceptible to cracks developing at the aft chamfer of the blade dovetail slots. We are issuing this AD to prevent cracks developing at the aft chamfer of the blade dovetail slots that could propagate to a failure of the disk and cause an uncontained engine failure and damage to the airplane. Compliance (f) You are responsible for having the actions required by this AD performed Frm 00003 Fmt 4700 within 30 days after the effective date of this AD, unless the actions have already been done. (g) Remove from service HPT stage 1 rotor disks identified by P/N in paragraph (c) of this AD. Prohibition of HPT Stage 1 Rotor Disks (h) After the effective date of this AD, do not install any of the HPT stage 1 rotor disks, listed by P/N in paragraph (c) of this AD into any engine. Alternative Methods of Compliance (i) 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 (j) Contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: robert.green@faa.gov; telephone: (781) 238–7754, fax: (781) 238–7199, for more information about this AD. Material Incorporated by Reference (k) None. Affected ADs PO 00000 16755 Sfmt 4700 Issued in Burlington, Massachusetts, on April 6, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–8263 Filed 4–10–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1207; Directorate Identifier 2007–NE–47–AD; Amendment 39– 15880; AD 2009–08–07] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc. ALF502L–2 and ALF502L–2C Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: The FAA is adopting a new airworthiness directive (AD) for Honeywell International Inc. ALF502L– 2 and ALF502L–2C turbofan engines with certain high-pressure compressor (HPC) first stage discs installed. This AD requires performing a dimensional inspection to determine if excessive disc balance material was removed and a magnetic particle inspection if the disc E:\FR\FM\13APR1.SGM 13APR1 16756 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations passes the dimensional inspection. This AD results from reports of discs found with excessive material removed from the balancing locations of the disc. We are issuing this AD to prevent the discs from fracturing before reaching the currently published life limit. A disc fracture could result in an uncontained failure of the disc and damage to the airplane. DATES: This AD becomes effective May 18, 2009. ADDRESSES: You can get the service information identified in this AD from Honeywell International Inc. 111 S. 34th Street, Phoenix, AZ 85034–2802, U.S.A.; telephone (800) 601–3099, Web site https://portal.honeywell.com/wps/portal/ aero. 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: Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: robert.baitoo@faa.gov; telephone (562) 627–5245; fax (562) 627–5210. SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 with a proposed AD. The proposed AD applies to Honeywell International Inc. ALF502L–2 and ALF502L–2C turbofan engines with certain HPC first stage discs installed. We published the proposed AD in the Federal Register on November 28, 2008 (73 FR 72370). That action proposed to require performing a dimensional inspection to determine if excessive disc balance material was removed and a magnetic particle inspection if the disc passes the dimensional inspection. 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 VerDate Nov<24>2008 18:17 Apr 10, 2009 Jkt 217001 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 148 engines installed on airplanes of U.S. registry. We also estimate that it will take about 3 work-hours per engine to perform the actions, and that the average labor rate is $80 per work-hour. Required parts will cost about $21,000 per engine. Based on these figures, we estimate the total cost of the AD to U.S. operators to be $3,143,520. 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. PO 00000 Frm 00004 Fmt 4700 Sfmt 4700 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. 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: ■ 2009–08–07 Honeywell International Inc. (Formerly AlliedSignal and Lycoming): Amendment 39–15880. Docket No. FAA–2008–1207; Directorate Identifier 2007–NE–47–AD. Effective Date (a) This airworthiness directive (AD) becomes effective May 18, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. ALF502L–2 and ALF502L– 2C turbofan engines with high pressure compressor (HPC) first stage discs, part numbers (P/Ns) 2–101–331–03, 2–101–331– 04, and 2–101–331–10, installed. These engines are installed on, but not limited to, Bombardier CL–600–1A11 airplanes. Unsafe Condition (d) This AD results from reports of discs found with excessive material removed from the balancing locations of the disc. We are issuing this AD to prevent the discs from fracturing before reaching the currently published life limit. A disc fracture could result in an uncontained failure of the disc and damage to the airplane. Compliance (e) You are responsible for having the actions required by this AD performed at the next shop visit, but not later than 2,500 cycles-in-service after the effective date of this AD, unless the actions have already been done. Visual Inspection (f) For discs with 5,000 or more cyclessince-new on the effective date of this AD, perform a dimensional inspection of the HPC first stage disc to determine if excessive disc E:\FR\FM\13APR1.SGM 13APR1 Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations 16757 balance material was removed. See the following Figure 1 for limits. VerDate Nov<24>2008 18:17 Apr 10, 2009 Jkt 217001 PO 00000 Frm 00005 Fmt 4700 Sfmt 4725 E:\FR\FM\13APR1.SGM 13APR1 ER13AP09.012</GPH> BILLING CODE 4910–13–P Federal Register / Vol. 74, No. 69 / Monday, April 13, 2009 / Rules and Regulations (g) Replace the disc if excessive disc balance material was removed. See limits in Figure 1 of this AD. (h) If the removed balance material condition is acceptable, perform a magnetic particle inspection of the disc rim and slots for cracks using a 3 to 7 power magnification glass. The Engine Overhaul Manual, 72–34– 11, Inspection/Check, contains information on the magnetic particle inspection procedure. Contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802, U.S.A.; telephone (800) 601–3099, Web site https://portal.honeywell.com/wps/portal/ aero, for a copy of this service information. (i) Replace the disc if you find any cracks. Related Information Alternative Methods of Compliance Material Incorporated by Reference (j) The Manager, Los Angeles Aircraft 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. VerDate Nov<24>2008 18:17 Apr 10, 2009 Jkt 217001 (k) Honeywell Alert Service Bulletin ALF/ LF A72–1102, dated April 24, 2007, contains information that pertains to the subject of this AD. Contact Honeywell International Inc., 111 S. 34th Street, Phoenix, AZ 85034– 2802, U.S.A.; telephone (800) 601–3099, Web site https://portal.honeywell.com/wps/portal/ aero, for a copy of this service information. (l) Contact Robert Baitoo, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712–4137; e-mail: robert.baitoo@faa.gov; telephone (562) 627–5245; fax (562) 627– 5210, for more information about this AD. (m) None. PO 00000 Issued in Burlington, Massachusetts, on April 6, 2009. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–8264 Filed 4–10–09; 8:45 am] BILLING CODE 4910–13–C DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 95 [Docket No. 30653; Amdt. No. 479] IFR Altitudes; Miscellaneous Amendments AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. Frm 00006 Fmt 4700 Sfmt 4700 E:\FR\FM\13APR1.SGM 13APR1 ER13AP09.013</GPH> 16758

Agencies

[Federal Register Volume 74, Number 69 (Monday, April 13, 2009)]
[Rules and Regulations]
[Pages 16755-16758]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-8264]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1207; Directorate Identifier 2007-NE-47-AD; 
Amendment 39-15880; AD 2009-08-07]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc. ALF502L-2 
and ALF502L-2C Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Honeywell International Inc. ALF502L-2 and ALF502L-2C turbofan engines 
with certain high-pressure compressor (HPC) first stage discs 
installed. This AD requires performing a dimensional inspection to 
determine if excessive disc balance material was removed and a magnetic 
particle inspection if the disc

[[Page 16756]]

passes the dimensional inspection. This AD results from reports of 
discs found with excessive material removed from the balancing 
locations of the disc. We are issuing this AD to prevent the discs from 
fracturing before reaching the currently published life limit. A disc 
fracture could result in an uncontained failure of the disc and damage 
to the airplane.

DATES: This AD becomes effective May 18, 2009.

ADDRESSES: You can get the service information identified in this AD 
from Honeywell International Inc. 111 S. 34th Street, Phoenix, AZ 
85034-2802, U.S.A.; telephone (800) 601-3099, Web site https://portal.honeywell.com/wps/portal/aero.
    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: Robert Baitoo, Aerospace Engineer, Los 
Angeles Aircraft Certification Office, FAA, Transport Airplane 
Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: 
robert.baitoo@faa.gov; telephone (562) 627-5245; fax (562) 627-5210.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 
with a proposed AD. The proposed AD applies to Honeywell International 
Inc. ALF502L-2 and ALF502L-2C turbofan engines with certain HPC first 
stage discs installed. We published the proposed AD in the Federal 
Register on November 28, 2008 (73 FR 72370). That action proposed to 
require performing a dimensional inspection to determine if excessive 
disc balance material was removed and a magnetic particle inspection if 
the disc passes the dimensional inspection.

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 148 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 3 
work-hours per engine to perform the actions, and that the average 
labor rate is $80 per work-hour. Required parts will cost about $21,000 
per engine. Based on these figures, we estimate the total cost of the 
AD to U.S. operators to be $3,143,520.

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.

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:

2009-08-07 Honeywell International Inc. (Formerly AlliedSignal and 
Lycoming): Amendment 39-15880. Docket No. FAA-2008-1207; Directorate 
Identifier 2007-NE-47-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 18, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc. ALF502L-2 
and ALF502L-2C turbofan engines with high pressure compressor (HPC) 
first stage discs, part numbers (P/Ns) 2-101-331-03, 2-101-331-04, 
and 2-101-331-10, installed. These engines are installed on, but not 
limited to, Bombardier CL-600-1A11 airplanes.

Unsafe Condition

    (d) This AD results from reports of discs found with excessive 
material removed from the balancing locations of the disc. We are 
issuing this AD to prevent the discs from fracturing before reaching 
the currently published life limit. A disc fracture could result in 
an uncontained failure of the disc and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed at the next shop visit, but not later than 2,500 
cycles-in-service after the effective date of this AD, unless the 
actions have already been done.

Visual Inspection

    (f) For discs with 5,000 or more cycles-since-new on the 
effective date of this AD, perform a dimensional inspection of the 
HPC first stage disc to determine if excessive disc

[[Page 16757]]

balance material was removed. See the following Figure 1 for limits.
BILLING CODE 4910-13-P
[GRAPHIC] [TIFF OMITTED] TR13AP09.012


[[Page 16758]]


[GRAPHIC] [TIFF OMITTED] TR13AP09.013

    (g) Replace the disc if excessive disc balance material was 
removed. See limits in Figure 1 of this AD.
    (h) If the removed balance material condition is acceptable, 
perform a magnetic particle inspection of the disc rim and slots for 
cracks using a 3 to 7 power magnification glass. The Engine Overhaul 
Manual, 72-34-11, Inspection/Check, contains information on the 
magnetic particle inspection procedure. Contact Honeywell 
International Inc., 111 S. 34th Street, Phoenix, AZ 85034-2802, 
U.S.A.; telephone (800) 601-3099, Web site https://portal.honeywell.com/wps/portal/aero, for a copy of this service 
information.
    (i) Replace the disc if you find any cracks.

Alternative Methods of Compliance

    (j) The Manager, Los Angeles Aircraft 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) Honeywell Alert Service Bulletin ALF/LF A72-1102, dated 
April 24, 2007, contains information that pertains to the subject of 
this AD. Contact Honeywell International Inc., 111 S. 34th Street, 
Phoenix, AZ 85034-2802, U.S.A.; telephone (800) 601-3099, Web site 
https://portal.honeywell.com/wps/portal/aero, for a copy of this 
service information.
    (l) Contact Robert Baitoo, Aerospace Engineer, Los Angeles 
Aircraft Certification Office, FAA, Transport Airplane Directorate, 
3960 Paramount Blvd., Lakewood, CA 90712-4137; e-mail: 
robert.baitoo@faa.gov; telephone (562) 627-5245; fax (562) 627-5210, 
for more information about this AD.

Material Incorporated by Reference

    (m) None.

    Issued in Burlington, Massachusetts, on April 6, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-8264 Filed 4-10-09; 8:45 am]
BILLING CODE 4910-13-C
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