Airworthiness Directives; Honeywell International Inc., T5313 and T5317 Series Turboshaft Engines, 76291-76293 [E8-29712]
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76291
Federal Register / Vol. 73, No. 242 / Tuesday, December 16, 2008 / Proposed Rules
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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
https://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: https://
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 https://
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: https://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 https://
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: https://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 https://
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: https://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
