Document ID: FAA-2008-1311-0002
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines
Posted Date: 2009-07-21T04:00Z

[Federal Register: July 21, 2009 (Volume 74, Number 138)]
[Rules and Regulations]               
[Page 35782-35785]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr21jy09-7]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-1311; Directorate Identifier 2007-NE-48-AD; 
Amendment 39-15976; AD 2009-15-13]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
Honeywell International Inc., T5313 and T5317 series turboshaft 
engines. This AD requires initial and repetitive visual inspections and 
initial and repetitive ultrasonic inspections of combustion chamber 
housings (CCHs) for cracks. 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.

DATES: This AD becomes effective August 25, 2009. The Director of the 
Federal Register approved the incorporation by reference of certain 
publications listed in the regulations as of August 25, 2009.

ADDRESSES: You can get the service information identified in this 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.
    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., T5313 and T5317 series turboshaft engines. We published the 
proposed AD in the Federal Register on December 16, 2008 (73 FR 76291). 
That action proposed to require initial and repetitive visual 
inspections and initial and repetitive ultrasonic inspections of CCHs 
for cracks.

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 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.

Change to Optional Terminating Action Paragraph

    We changed optional terminating action paragraph (k) to state that 
installation of a CCH P/N 1-130-610-19 or 1-130-610R16 terminates the 
inspection requirements of this AD. These CCHs eliminate the failure 
mode that cause cracking.

[[Page 35783]]

Incorporation by Reference of Service Bulletin Appendix

    Since we issued the proposed AD, we realized that we need to add 
the incorporation by reference of the Appendix of Honeywell 
International Inc. Service Bulletin No. T53-0144, Revision 4, dated 
March 31, 2008 for operators to perform the ultrasonic inspections. We 
added that reference to inspection paragraphs (i) and (j) of this AD.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
changes described previously.

Costs of Compliance

    We estimate that this AD will affect 100 engines installed on 
helicopters 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. No parts are required. Based on these 
figures, we estimate the total cost of the 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 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, Incorporation by 
reference, 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:

2009-15-13 Honeywell International Inc. (Formerly AlliedSignal and 
Textron-Lycoming): Amendment 39-15976. Docket No. FAA-2008-1311; 
Directorate Identifier 2007-NE-48-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective August 
25, 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 
guidance 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 guidance on replacing the CCH.

Repetitive Visual Inspections

    (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 every 50 hours time-since-last 
inspection. Honeywell International Inc. Standard Practices Manual 
70-20-02, SP 1302, contains additional guidance 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 guidance on replacing 
the CCH.

[[Page 35784]]

[GRAPHIC] [TIFF OMITTED] TR21JY09.000

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 and the 
SB Appendix 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 Inspections

    (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 and the SB Appendix at 
the following compliance times:
    (1) Within every 1,200 flights, defined as the cumulative number 
of landings, since the last inspection; or
    (2) Within every 200 flights, if the last inspection had 
ultrasonic findings as defined in paragraph 3.A.(2) or paragraph 
3.A.(3) of Honeywell International Inc. SB No. T53-0144, Revision 4, 
dated March 31, 2008.

Optional Terminating Action

    (k) Installation of a CCH P/N 1-130-610-19 or 1-130-610R16, or 
an FAA approved equivalent part, terminates the inspection 
requirements 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, 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 
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

    (o) You must use the service information specified in the 
following Table 1 to perform the ultrasonic inspections required by 
this AD. The Director of the Federal Register approved the 
incorporation by reference of the documents listed in the following 
Table 1 in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. 
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. 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: 
http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 35785]]

                                       Table 1--Incorporation by Reference
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  Honeywell International Inc. Service
              Bulletin No.                           Page             Revision                Date
----------------------------------------------------------------------------------------------------------------
T53-0144, Total Pages: 10...............  ALL......................          4  March 31, 2008.
T53-0144, Appendix, Total Pages: 13.....  ALL......................          C  January 25, 2008.
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    Issued in Burlington, Massachusetts, on July 14, 2009.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E9-17146 Filed 7-20-09; 8:45 am]

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