Airworthiness Directives; Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines, 76291-76293 [E8-29712]

Download as PDF 76291 Federal Register / Vol. 73, No. 242 / Tuesday, December 16, 2008 / Proposed Rules Last digit of Registration No. 0 1 2 3 4 or or or or or 1 2 5 6 7 8 9 Year of renewal .................................................................................... .................................................................................... .................................................................................... .................................................................................... .................................................................................... by by by by by April April April April April 15 1 ............................................................... 15 ................................................................. 15 ................................................................. 15 ................................................................. 15 ................................................................. 2014, 2015, 2016, 2017, 2018, by by by by by April April April April April 15.1 2 15. 15. 15. 15. However, if records are kept on a fiscal year basis, renewal is due by 90 days after the close of the fiscal year. For all dates in this column, due date for renewal application is without regard to last digit of registration number. (2) Beginning January 14, 2014, all registrations must be renewed every 5 years by April 15 of the calendar year in which registration expires. (See notes 1 and 2 above.) (f) Registrations that expire during a period of suspension imposed as a result of an order or injunction may be renewed, but the renewal will not be effective until the specified suspension period terminates. * * * * * Terry D. Van Doren, Administrator, Grain Inspection, Packers and Stockyards Administration. [FR Doc. E8–29652 Filed 12–15–08; 8:45 am] BILLING CODE 3410–KD–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2008–1311; Directorate Identifier 2007–NE–48–AD] RIN 2120–AA64 Airworthiness Directives; Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). mstockstill on PROD1PC66 with PROPOSALS 2009, 2010, 2011, 2012, 2013, Next renewal due date SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) for Honeywell International Inc., T5313 and T5317 series turboshaft engines. This proposed AD would require initial and repetitive visual inspections and initial and repetitive ultrasonic inspections. This proposed AD results from eight instances of cracks in combustion chamber housings (CCHs). Two of the instances resulted in an engine shutdown during flight. We are proposing this AD to detect cracks in the CCH, which could result in rupture of the CCH, leading to loss of engine power and damage to the helicopter. DATES: We must receive any comments on this proposed AD by February 17, 2009. VerDate Aug<31>2005 17:08 Dec 15, 2008 Jkt 217001 Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to http://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 Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072–2181, U.S.A.; telephone (800) 601–3099 (U.S.A.) or (602) 365–3099 (International), Web site: http:// portal.honeywell.com/wps/portal/aero. FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los Angeles 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: ADDRESSES: 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– 2008–1311; Directorate Identifier 2007– NE–48–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 http:// 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. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Examining the AD Docket You may examine the AD docket on the Internet at http: // 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. Discussion We have received reports of eight instances of cracks developing in CCHs, part numbers (P/Ns) 1–130–610–05 and 1–130–610–12. Two of the instances resulted in an engine shutdown during flight. The cracks developed between the seam welds on the rear outer flange, in the angled bend area, forward of the fuel manifold mounting flange. Fatigue cracking in the ‘‘doubler detail’’ develops from the inside of the CCH, typically starting from corrosion pitting. There have been several instances in which a crack was found during maintenance activities or preflight inspection of the engine. In one instance, with a previously weldrepaired CCH (assumed to be a repair of a crack), additional fatigue cracks grew sufficiently to result in a loss of CCH integrity, subsequent in-flight engine shutdown, and significant airframe damage. A previously weld-repaired CCH has a high potential for additional cracks that might or might not be visible. This condition, if not corrected, could result in rupture of the CCH E:\FR\FM\16DEP1.SGM 16DEP1 76292 Federal Register / Vol. 73, No. 242 / Tuesday, December 16, 2008 / Proposed Rules leading to loss of engine power and damage to the helicopter. Relevant Service Information We have reviewed and approved the technical contents of Honeywell International Inc. Alert Service Bulletin (ASB) T53–A0142, Revision 1, dated September 14, 2006. That ASB describes procedures for performing an initial and subsequent daily visual inspections of the CCH for cracks. We also approved Service Bulletin (SB) T53–0144, Revision 4, dated March 31, 2008, that describes procedures for performing an initial and repetitive ultrasonic inspection of the CCH for cracks. Differences Between This AD and the Service Information Honeywell International Inc. ASB T53–A0142, Revision 1, dated September 14, 2006, requires daily repetitive inspections, and allows the flight crew to perform them. This AD would allow intervals of 50 hours timein-service between repetitive visual inspections, and allows appropriately certificated technicians only to perform the visual inspections. The ASB also requires removing a welded CCH before further flight. This proposed AD would require removing a welded CCH within 100 hours time-in-service after the visual inspection. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. We are proposing this AD to detect cracks in the CCH, which could result in rupture of the CCH leading to loss of engine power and damage to the helicopter. You must use the service information described previously to perform the actions required by this AD. mstockstill on PROD1PC66 with PROPOSALS Costs of Compliance We estimate that this proposed AD would affect 100 engines installed on helicopters of U.S. registry. We also estimate that it would take about 3 work-hours per engine to perform the proposed actions, and that the average labor rate is $80 per work-hour. No parts are required. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $24,000. 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, VerDate Aug<31>2005 17:08 Dec 15, 2008 Jkt 217001 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 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 that the proposed 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. Would 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. 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, Incorporation by reference, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration 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 FAA amends § 39.13 by adding the following new airworthiness directive: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 Honeywell International Inc. (Formerly AlliedSignal and Textron-Lycoming): Docket No. FAA–2008–1311; Directorate Identifier 2007–NE–48–AD. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this airworthiness directive (AD) action by February 17, 2009. Affected ADs (b) None. Applicability (c) This AD applies to Honeywell International Inc. T5313B, T5317A, T5317A– 1, T5317B, and T5317BCV turboshaft engines with combustion chamber housing (CCH), part numbers (P/Ns) 1–130–610–05, 1–130– 610–12, and 1–130–610–17, installed. These engines are installed on, but not limited to, Bell 205 and 210 Series and Kaman K–1200 helicopters. Unsafe Condition (d) This AD results from eight instances of cracks in CCHs. Two of the instances resulted in an engine shutdown during flight. We are issuing this AD to detect cracks in the CCH, which could result in rupture of the CCH, leading to loss of engine power and damage to the helicopter. 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. Initial Visual Inspection (f) For CCH, P/N 1–130–610–05 and 1– 130–610–12, within 50 hours time-in-service (TIS) after the effective date of this AD, inspect the area between points A and B around the entire housing circumference in Figure 1 of this AD for weld repairs and cracks. (1) If you find any cracks, replace the CCH before further flight. Honeywell International Inc. Alert Service Bulletin (ASB) T53–A0142, Revision 1, dated September 14, 2006, contains additional information on replacing the CCH. (2) If you find any weld repairs, replace the CCH within 100 hours TIS after the visual inspection. Honeywell International Inc. ASB T53–A0142, Revision 1, dated September 14, 2006, contains additional information on replacing the CCH. Repetitive Visual Inspection (g) For CCH, P/N 1–130–610–05 and 1– 130–610–12, inspect the area between points A and B around the entire housing circumference in Figure 1 of this AD for cracks within 50 hours time-since-last inspection. Honeywell International Inc. Standard Practices Manual 70–20–02, SP 1302, contains additional information on visual inspection. (h) If you find any cracks, replace the CCH before further flight. Honeywell International Inc. ASB T53–A0142, Revision 1, dated September 14, 2006, contains additional information on replacing the CCH. E:\FR\FM\16DEP1.SGM 16DEP1 Federal Register / Vol. 73, No. 242 / Tuesday, December 16, 2008 / Proposed Rules (i) Perform an ultrasonic inspection on the CCH. Use Honeywell International Inc. Service Bulletin (SB) No. T53–0144, Revision 4, dated March 31, 2008, section 3. Accomplishment Instructions, to perform the ultrasonic inspection at the following compliance times. (1) For CCH, P/N 1–130–610–05 and 1– 130–610–12, within 500 hours TIS or next hot section inspection, whichever occurs first after the effective date of this AD, but not to exceed 6 months after the effective date of this AD. (2) For CCH, P/N 1–130–610–17, perform at the first overhaul, but do not exceed 5,000 hours or 11,000 cycles, after the effective date of this AD, whichever occurs first. the last inspection to determine if the indication length increased. Optional Terminating Action (k) Replacing a CCH, P/N 1–130–610–05, 1–130–610–12, or 1–130–610–17, with a CCH, P/N 1–130–610–19 or 1–130–610R16, or an FAA-approved equivalent part, terminates the repetitive inspection requirements specified in paragraphs (g) and (i) of this AD. Alternative Methods of Compliance (l) 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. mstockstill on PROD1PC66 with PROPOSALS Repetitive Ultrasonic Inspection Related Information (j) Repeat the ultrasonic inspection on the CCH using Honeywell International Inc. SB No. T53–0144, Revision 4, dated March 31, 2008, section 3. Accomplishment Instructions, at the following compliance times: (1) Within 1,200 flights, as defined as the cumulative number of landings, since the last inspection; or (2) If the last inspection had unacceptable ultrasonic findings, within 200 flights after (m) Honeywell International Inc. ASB T53– A0142, Revision 1, dated September 14, 2006, SB No. T53–0144, Revision 4, dated March 31, 2008, and Standard Practices Manual 70–20–02, SP 1302, pertain to the subject of this AD. Contact Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072–2181; telephone (800) 601–3099, Web site: http://portal.honeywell.com/wps/ portal/aero, for a copy of this service information. VerDate Aug<31>2005 17:08 Dec 15, 2008 Jkt 217001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 (n) Contact Robert Baitoo, Aerospace Engineer, Los Angeles 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. Issued in Burlington, Massachusetts, on December 8, 2008. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E8–29712 Filed 12–15–08; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2008–1231; Airspace Docket No. 08–ASW–25] Proposed Amendment of Class E Airspace; Tulsa, OK AGENCY: Federal Aviation Administration (FAA), DOT. E:\FR\FM\16DEP1.SGM 16DEP1 EP16DE08.003</GPH> Initial Ultrasonic Inspection 76293

Agencies

[Federal Register Volume 73, Number 242 (Tuesday, December 16, 2008)]
[Proposed Rules]
[Pages 76291-76293]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-29712]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1311; Directorate Identifier 2007-NE-48-AD]
RIN 2120-AA64


Airworthiness Directives; Honeywell International Inc., T5313 and 
T5317 Series Turboshaft Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Honeywell International Inc., T5313 and T5317 series turboshaft 
engines. This proposed AD would require initial and repetitive visual 
inspections and initial and repetitive ultrasonic inspections. This 
proposed AD results from eight instances of cracks in combustion 
chamber housings (CCHs). Two of the instances resulted in an engine 
shutdown during flight. We are proposing this AD to detect cracks in 
the CCH, which could result in rupture of the CCH, leading to loss of 
engine power and damage to the helicopter.

DATES: We must receive any comments on this proposed AD by February 17, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
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 Honeywell International Inc., P.O. Box 52181, Phoenix, AZ 85072-
2181, U.S.A.; telephone (800) 601-3099 (U.S.A.) or (602) 365-3099 
(International), Web site: http://portal.honeywell.com/wps/portal/aero.

FOR FURTHER INFORMATION CONTACT: Robert Baitoo, Aerospace Engineer, Los 
Angeles 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:

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-2008-1311; Directorate 
Identifier 2007-NE-48-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 http://
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, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http: //
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.

Discussion

    We have received reports of eight instances of cracks developing in 
CCHs, part numbers (P/Ns) 1-130-610-05 and 1-130-610-12. Two of the 
instances resulted in an engine shutdown during flight. The cracks 
developed between the seam welds on the rear outer flange, in the 
angled bend area, forward of the fuel manifold mounting flange. Fatigue 
cracking in the ``doubler detail'' develops from the inside of the CCH, 
typically starting from corrosion pitting. There have been several 
instances in which a crack was found during maintenance activities or 
preflight inspection of the engine. In one instance, with a previously 
weld-repaired CCH (assumed to be a repair of a crack), additional 
fatigue cracks grew sufficiently to result in a loss of CCH integrity, 
subsequent in-flight engine shutdown, and significant airframe damage. 
A previously weld-repaired CCH has a high potential for additional 
cracks that might or might not be visible. This condition, if not 
corrected, could result in rupture of the CCH

[[Page 76292]]

leading to loss of engine power and damage to the helicopter.

Relevant Service Information

    We have reviewed and approved the technical contents of Honeywell 
International Inc. Alert Service Bulletin (ASB) T53-A0142, Revision 1, 
dated September 14, 2006. That ASB describes procedures for performing 
an initial and subsequent daily visual inspections of the CCH for 
cracks. We also approved Service Bulletin (SB) T53-0144, Revision 4, 
dated March 31, 2008, that describes procedures for performing an 
initial and repetitive ultrasonic inspection of the CCH for cracks.

Differences Between This AD and the Service Information

    Honeywell International Inc. ASB T53-A0142, Revision 1, dated 
September 14, 2006, requires daily repetitive inspections, and allows 
the flight crew to perform them. This AD would allow intervals of 50 
hours time-in-service between repetitive visual inspections, and allows 
appropriately certificated technicians only to perform the visual 
inspections. The ASB also requires removing a welded CCH before further 
flight. This proposed AD would require removing a welded CCH within 100 
hours time-in-service after the visual inspection.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. We are proposing this AD to detect cracks in 
the CCH, which could result in rupture of the CCH leading to loss of 
engine power and damage to the helicopter. You must use the service 
information described previously to perform the actions required by 
this AD.

Costs of Compliance

    We estimate that this proposed AD would affect 100 engines 
installed on helicopters of U.S. registry. We also estimate that it 
would take about 3 work-hours per engine to perform the proposed 
actions, and that the average labor rate is $80 per work-hour. No parts 
are required. Based on these figures, we estimate the total cost of the 
proposed AD to U.S. operators to be $24,000.

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 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 that the proposed 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. Would 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. 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, Incorporation by 
reference, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration 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 
airworthiness directive:

Honeywell International Inc. (Formerly AlliedSignal and Textron-
Lycoming): Docket No. FAA-2008-1311; Directorate Identifier 2007-NE-
48-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by February 17, 
2009.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Honeywell International Inc. T5313B, 
T5317A, T5317A-1, T5317B, and T5317BCV turboshaft engines with 
combustion chamber housing (CCH), part numbers (P/Ns) 1-130-610-05, 
1-130-610-12, and 1-130-610-17, installed. These engines are 
installed on, but not limited to, Bell 205 and 210 Series and Kaman 
K-1200 helicopters.

Unsafe Condition

    (d) This AD results from eight instances of cracks in CCHs. Two 
of the instances resulted in an engine shutdown during flight. We 
are issuing this AD to detect cracks in the CCH, which could result 
in rupture of the CCH, leading to loss of engine power and damage to 
the helicopter.

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.

Initial Visual Inspection

    (f) For CCH, P/N 1-130-610-05 and 1-130-610-12, within 50 hours 
time-in-service (TIS) after the effective date of this AD, inspect 
the area between points A and B around the entire housing 
circumference in Figure 1 of this AD for weld repairs and cracks.
    (1) If you find any cracks, replace the CCH before further 
flight. Honeywell International Inc. Alert Service Bulletin (ASB) 
T53-A0142, Revision 1, dated September 14, 2006, contains additional 
information on replacing the CCH.
    (2) If you find any weld repairs, replace the CCH within 100 
hours TIS after the visual inspection. Honeywell International Inc. 
ASB T53-A0142, Revision 1, dated September 14, 2006, contains 
additional information on replacing the CCH.

Repetitive Visual Inspection

    (g) For CCH, P/N 1-130-610-05 and 1-130-610-12, inspect the area 
between points A and B around the entire housing circumference in 
Figure 1 of this AD for cracks within 50 hours time-since-last 
inspection. Honeywell International Inc. Standard Practices Manual 
70-20-02, SP 1302, contains additional information on visual 
inspection.
    (h) If you find any cracks, replace the CCH before further 
flight. Honeywell International Inc. ASB T53-A0142, Revision 1, 
dated September 14, 2006, contains additional information on 
replacing the CCH.

[[Page 76293]]

[GRAPHIC] [TIFF OMITTED] TP16DE08.003

Initial Ultrasonic Inspection

    (i) Perform an ultrasonic inspection on the CCH. Use Honeywell 
International Inc. Service Bulletin (SB) No. T53-0144, Revision 4, 
dated March 31, 2008, section 3. Accomplishment Instructions, to 
perform the ultrasonic inspection at the following compliance times.
    (1) For CCH, P/N 1-130-610-05 and 1-130-610-12, within 500 hours 
TIS or next hot section inspection, whichever occurs first after the 
effective date of this AD, but not to exceed 6 months after the 
effective date of this AD.
    (2) For CCH, P/N 1-130-610-17, perform at the first overhaul, 
but do not exceed 5,000 hours or 11,000 cycles, after the effective 
date of this AD, whichever occurs first.

Repetitive Ultrasonic Inspection

    (j) Repeat the ultrasonic inspection on the CCH using Honeywell 
International Inc. SB No. T53-0144, Revision 4, dated March 31, 
2008, section 3. Accomplishment Instructions, at the following 
compliance times:
    (1) Within 1,200 flights, as defined as the cumulative number of 
landings, since the last inspection; or
    (2) If the last inspection had unacceptable ultrasonic findings, 
within 200 flights after the last inspection to determine if the 
indication length increased.

Optional Terminating Action

    (k) Replacing a CCH, P/N 1-130-610-05, 1-130-610-12, or 1-130-
610-17, with a CCH, P/N 1-130-610-19 or 1-130-610R16, or an FAA-
approved equivalent part, terminates the repetitive inspection 
requirements specified in paragraphs (g) and (i) of this AD.

Alternative Methods of Compliance

    (l) 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

    (m) Honeywell International Inc. ASB T53-A0142, Revision 1, 
dated September 14, 2006, SB No. T53-0144, Revision 4, dated March 
31, 2008, and Standard Practices Manual 70-20-02, SP 1302, pertain 
to the subject of this AD. Contact Honeywell International Inc., 
P.O. Box 52181, Phoenix, AZ 85072-2181; telephone (800) 601-3099, 
Web site: http://portal.honeywell.com/wps/portal/aero, for a copy of 
this service information.
    (n) Contact Robert Baitoo, Aerospace Engineer, Los Angeles 
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.

    Issued in Burlington, Massachusetts, on December 8, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-29712 Filed 12-15-08; 8:45 am]
BILLING CODE 4910-13-P