Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model S-92A Helicopters, 27409-27411 [2010-11069]
Download as PDF
<![CDATA[
27409
Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
having P/N 2844–19 and re-identifying the
safety valves, in accordance with Paragraph
2.C., ‘‘Part B—Modification—Replacement,’’
of the Accomplishment Instructions of
Bombardier Service Bulletin A100–21–08,
dated June 18, 2009, terminates the repetitive
cleanings required by paragraph (j) of this
AD.
FAA AD Differences
Note 2: This AD differs from the MCAI
and/or service information as follows: This
AD does not require the replacement of the
safety valve cabin pressure-sensing port
plugs and the re-identification of the safety
valves required in Part V of MCAI Canadian
Airworthiness Directive CF–2010–06, dated
February 24, 2010. The planned compliance
times for these actions would not allow
enough time to provide notice and
opportunity for prior public comment on the
merits of those actions. Therefore, we are
considering further rulemaking to address
these issues.
Other FAA AD Provisions
(l) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York Aircraft
Certification Office, ANE–170, FAA, has the
authority to approve AMOCs for this AD, if
requested using the procedures found in 14
CFR 39.19. Send information to ATTN:
Program Manager, Continuing Operational
Safety, FAA, New York ACO, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone 516–228–7300; fax 516–
794–5531. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to ensure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(m) Refer to MCAI Canadian Airworthiness
Directive CF–2010–06, dated February 24,
2010; and the service information specified
in Table 1 of this AD; as applicable; for
related information.
TABLE 1—SERVICE INFORMATION
Document
Date
Bombardier Service Bulletin A100–21–08 ...............................................................................................................................
Bombardier Service Bulletin 100–25–14 .................................................................................................................................
Bombardier Service Bulletin 100–25–21 .................................................................................................................................
Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘Certification Maintenance Requirements,’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks.
Material Incorporated by Reference
(n) You must use the service information
contained in Table 2 of this AD to do the
June 18, 2009.
June 30, 2008.
June 30, 2008.
October 1, 2009.
actions required by this AD, unless the AD
specifies otherwise.
TABLE 2—MATERIAL INCORPORATED BY REFERENCE
Document
Date
srobinson on DSKHWCL6B1PROD with RULES
Bombardier Service Bulletin A100–21–08 ...............................................................................................................................
Bombardier Service Bulletin 100–25–14 .................................................................................................................................
Bombardier Service Bulletin 100–25–21 .................................................................................................................................
Bombardier Temporary Revision 5–2–53, dated October 1, 2009, to Section 5–10–40, ‘‘Certification Maintenance Requirements,’’ in Part 2 of Chapter 5 of Bombardier Challenger 300 BD–100 Time Limits/Maintenance Checks.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
ˆ
this AD, contact Bombardier, Inc., 400 Cote´
Vertu Road West, Dorval, Quebec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; e-mail
thd.crj@aero.bombardier.com; Internet https://
www.bombardier.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221.
(4) You may also review copies of the
service information that is incorporated by
reference 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: https://www.archives.gov/federal_register/
VerDate Mar<15>2010
16:29 May 14, 2010
Jkt 220001
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on May 3,
2010.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
June 18, 2009.
June 30, 2008.
June 30, 2008.
October 1, 2009.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[FR Doc. 2010–11074 Filed 5–14–10; 8:45 am]
[Docket No. FAA–2010–0060; Directorate
Identifier 2010–SW–06–AD; Amendment 39–
16282; AD 2010–10–03]
BILLING CODE 4910–13–P
RIN 2120–AA64
PO 00000
Airworthiness Directives; Sikorsky
Aircraft Corporation (Sikorsky) Model
S–92A Helicopters
AGENCY: Federal Aviation
Administration, DOT.
ACTION: Final rule.
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
Sikorsky Model S–92A helicopters. The
Frm 00009
Fmt 4700
Sfmt 4700
E:\FR\FM\17MYR1.SGM
17MYR1
27410
Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
AD requires replacing the main gearbox
(MGB) filter bowl assembly with a twopiece MGB filter bowl assembly and
replacing the existing mounting studs.
The AD also requires inspecting the
MGB lube system filters, the housing,
the housing threads, and the lockring
counterbore and repairing or replacing
them as necessary. This amendment is
prompted by tests indicating that an
existing MGB filter bowl assembly can
fail under certain loading conditions
including those associated with a
damaged MGB filter or mounting stud
resulting from high frequency
maintenance tasks. Testing of the
improved MGB filter bowl assembly
demonstrates a significant increase in
strength and durability over the existing
filter bowl. The actions specified by this
AD are intended to prevent failure of the
MGB filter bowl assembly due to failure
of the mounting studs or the filter bowl,
loss of oil from the MGB, failure of the
MGB, and subsequent loss of control of
the helicopter.
DATES: Effective June 21, 2010.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of June 21,
2010.
You may get the service
information identified in this AD from
Sikorsky Aircraft Corporation, Attn:
Manager, Commercial Technical
Support, mailstop s581a, 6900 Main
Street, Stratford, CT, telephone (203)
383–4866, e-mail address
tsslibrary@sikorsky.com, or at https://
www.sikorsky.com.
Examining the Docket: You may
examine the docket that contains this
AD, any comments, and other
information on the Internet at https://
www.regulations.gov or at the Docket
Operations office, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
srobinson on DSKHWCL6B1PROD with RULES
ADDRESSES:
FOR FURTHER INFORMATION CONTACT: Kirk
Gustafson, Aviation Safety Engineer,
Boston Aircraft Certification Office,
Engine and Propeller Directorate, FAA,
12 New England Executive Park,
Burlington, MA 01803, telephone (781)
238–7190, fax (781) 238–7170.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on January 27, 2010
(75 FR 4308). That action proposed to
require replacing the MGB filter bowl
assembly with a two-piece MGB filter
bowl assembly and replacing the
existing mounting studs. That action
VerDate Mar<15>2010
16:29 May 14, 2010
Jkt 220001
also proposed inspecting the MGB lube
system filters, the housing, the housing
threads, and the lockring counterbore
and repairing and replacing them as
necessary.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the
proposal or the FAA’s determination of
the cost to the public. The FAA has
determined that air safety and the
public interest require the adoption of
the rule as proposed.
The FAA estimates that this AD will
affect 22 helicopters of U.S. registry.
The required actions will take about 6
hours to inspect the existing filter bowl
assembly and replace the MGB lube
system filters, the mounting studs, and
to install an improved filter bowl
assembly at an average labor rate of $85
per work hour. Required parts will cost
about $3,257 per helicopter. Based on
these figures, the total cost impact of the
AD on U.S. operators is $82,214.
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 the regulation:
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. 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 an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
Authority: 49 U.S.C. 106(g), 40113, 44701.
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
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
■
2010–10–03 Sikorsky Aircraft Corporation:
Amendment 39–16282. Docket No.
FAA–2010–0060; Directorate Identifier
2010–SW–06–AD.
Applicability: Model S–92A helicopters,
with main gearbox (MGB) filter bowl
assembly, part number (P/N) 92351–15802–
101, installed, certificated in any category.
Compliance: Required as indicated, unless
done previously.
To prevent failure of the MGB filter bowl
assembly due to failure of the mounting studs
or the filter bowl, loss of oil from the MGB,
failure of the MGB, and subsequent loss of
control of the helicopter, do the following:
(a) Within 60 days:
(1) Remove the MGB filter bowl assembly
by following the Accomplishment
Instructions, paragraphs 3.A. (1) through
3.A.(5), of Sikorsky Alert Service Bulletin No.
92–63–022A, dated December 18, 2009
(ASB).
(2) Remove the primary filter element, P/
N 70351–38801–102, from the MGB lube
system filter and visually inspect it for
damage as depicted in Figures 1, 2, and 3 of
the ASB. If the primary filter element has
‘‘wavy’’ pleats, internal buckling, or indented
dimples, before further flight, replace it with
an airworthy filter element.
(3) Visually inspect the secondary filter
element, P/N 70351–38801–103, for damage
as depicted in Figures 4 and 5 of the ASB.
If the secondary filter element has ‘‘wavy’’
pleats or an elongated cup, before further
flight, replace it with an airworthy filter
element.
(4) Replace the MGB lube system filter
assembly mounting studs:
E:\FR\FM\17MYR1.SGM
17MYR1
srobinson on DSKHWCL6B1PROD with RULES
Federal Register / Vol. 75, No. 94 / Monday, May 17, 2010 / Rules and Regulations
(i) Remove the studs by following the
Accomplishment Instructions, paragraphs
3.B.(1) through 3.B.(4) of the ASB. Visually
inspect the tapped holes for any damage to
the threads. Serrations on the entire counter
bore (360 degrees) are acceptable. Serrations
in the housing must be intact, and mating
serrations on the lock ring must line up with
serrations on the housing. Visually inspect
the housing to determine that the housing
threads are free from damage and corrosion.
Visually inspect housing lockring
counterbore to determine if the housing is
airworthy.
(ii) If you find damage or corrosion to the
housing threads, the housing, or the lockring
counterbore, stop work and contact Kirk
Gustafson, Aviation Safety Engineer, Boston
Aircraft Certification Office, Engine and
Propeller Directorate, FAA, 12 New England
Executive Park, Burlington, MA 01803,
telephone (781) 238–7190, fax (781) 238–
7170.
(iii) If you do not find damage to the
housing threads, the housing, or the lockring
counterbore that requires repair, replace the
mounting studs by following the
Accomplishment Instructions, paragraphs
3.B.(7) through 3.B.(15) of the ASB.
(5) Install an airworthy, two-piece MGB
filter bowl assembly modification kit, P/N
92070–35005–011, as depicted in Figures 8
and 9 of the ASB and by following the
Accomplishment Instructions, paragraphs
3.C.(1) through 3.C.(20), of the ASB.
(b) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Boston Aircraft
Certification Office, Attn: Kirk Gustafson,
Aviation Safety Engineer, Boston Aircraft
Certification Office, Engine and Propeller
Directorate, FAA, 12 New England Executive
Park, Burlington, MA 01803, telephone (781)
238–7190, fax (781) 238–7170, for
information about previously approved
alternative methods of compliance.
(c) The Joint Aircraft System/Component
(JASC) Code is 6320: Main Rotor Gearbox.
(d) Inspecting and replacing the MGB filter
bowl assembly shall be done by following the
specified portions of Sikorsky Alert Service
Bulletin No. 92–63–022A, dated December
18, 2009. The Director of the Federal Register
approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager,
Commercial Technical Support, mailstop
s581a, 6900 Main Street, Stratford, CT,
telephone (203) 383–4866, e-mail address
tsslibrary@sikorsky.com, or at https://
www.sikorsky.com. Copies may be inspected
at the FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas, 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: https://
www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(e) This amendment becomes effective on
June 21, 2010.
VerDate Mar<15>2010
16:29 May 14, 2010
Jkt 220001
Issued in Fort Worth, Texas, on April 27,
2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2010–11069 Filed 5–14–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–21242; Directorate
Identifier 2005–NE–09–AD; Amendment 39–
16288; AD 2010–10–09]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 1B, 1D, 1D1, and 1S1 Turboshaft
Engines
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
certain Turbomeca Arriel 1B, 1D, 1D1,
and 1S1 turboshaft engines. That AD
requires initial and repetitive relative
position checks of the gas generator 2nd
stage turbine blades on Turbomeca
Arriel 1B (that incorporate Turbomeca
Modification (mod) TU 148), Arriel 1D,
1D1, and 1S1 turboshaft engines that do
not incorporate mod TU 347. That AD
also requires initial and repetitive
replacements of 2nd stage turbines on
Arriel 1B, 1D, and 1D1 engines. This AD
requires lowering the initial and
repetitive thresholds for replacement of
2nd stage turbines on Arriel 1B, 1D, and
1D1 engines. This AD results from
reports of new cases of failures of 2nd
stage turbine blades since we issued AD
2008–07–01. We are issuing this AD to
prevent the failure of 2nd stage turbine
blades, which could result in an
uncommanded in-flight engine
shutdown, and a subsequent forced
autorotation landing or accident.
DATES: This AD becomes effective June
21, 2010. The Director of the Federal
Register approved the incorporation by
reference of certain publications listed
in the regulations as of June 21, 2010.
ADDRESSES: You can get the service
information identified in this AD from
Turbomeca, 40220 Tarnos, France;
telephone (33) 05 59 74 40 00, fax (33)
05 59 74 45 15.
The Docket Operations office is
located at Docket Management Facility,
U.S. Department of Transportation, 1200
New Jersey Avenue, SE., West Building
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
27411
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
FOR FURTHER INFORMATION CONTACT:
Kevin Dickert, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: kevin.dickert@faa.gov;
phone: (781) 238–7117, fax: (781) 238–
7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 by
superseding AD 2008–07–01,
Amendment 39–15442 (73 FR 15866,
March 26, 2008), with a proposed AD.
The proposed AD applies to Turbomeca
Arriel 1B (that incorporate mod TU
148), 1D, 1D1, and 1S1 turboshaft
engines that do not incorporate mod TU
347. We published the proposed AD in
the Federal Register on March 10, 2010
(75 FR 11072). That action proposed to
require lowering the repetitive threshold
for relative position checks on Arriel 1B
engines. That action also proposed to
require lowering the initial and
repetitive thresholds for replacement of
2nd stage turbines on Arriel 1B, 1D, and
1D1 engines.
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 (phone
(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
Based on the service information, we
estimate that this AD will affect about
587 Turbomeca Arriel 1B, 1D, 1D1, and
1S1 turboshaft engines installed on
products of U.S. registry. We also
estimate that it will take about 2 workhours per engine to perform one
inspection, and about 40 work-hours per
engine to replace the gas turbine discs
E:\FR\FM\17MYR1.SGM
17MYR1
]]>Agencies
[Federal Register Volume 75, Number 94 (Monday, May 17, 2010)]
[Rules and Regulations]
[Pages 27409-27411]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-11069]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0060; Directorate Identifier 2010-SW-06-AD;
Amendment 39-16282; AD 2010-10-03]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
(Sikorsky) Model S-92A Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the Sikorsky Model S-92A helicopters. The
[[Page 27410]]
AD requires replacing the main gearbox (MGB) filter bowl assembly with
a two-piece MGB filter bowl assembly and replacing the existing
mounting studs. The AD also requires inspecting the MGB lube system
filters, the housing, the housing threads, and the lockring counterbore
and repairing or replacing them as necessary. This amendment is
prompted by tests indicating that an existing MGB filter bowl assembly
can fail under certain loading conditions including those associated
with a damaged MGB filter or mounting stud resulting from high
frequency maintenance tasks. Testing of the improved MGB filter bowl
assembly demonstrates a significant increase in strength and durability
over the existing filter bowl. The actions specified by this AD are
intended to prevent failure of the MGB filter bowl assembly due to
failure of the mounting studs or the filter bowl, loss of oil from the
MGB, failure of the MGB, and subsequent loss of control of the
helicopter.
DATES: Effective June 21, 2010.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 21, 2010.
ADDRESSES: You may get the service information identified in this AD
from Sikorsky Aircraft Corporation, Attn: Manager, Commercial Technical
Support, mailstop s581a, 6900 Main Street, Stratford, CT, telephone
(203) 383-4866, e-mail address tsslibrary@sikorsky.com, or at https://www.sikorsky.com.
Examining the Docket: You may examine the docket that contains this
AD, any comments, and other information on the Internet at https://www.regulations.gov or at the Docket Operations office, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Kirk Gustafson, Aviation Safety
Engineer, Boston Aircraft Certification Office, Engine and Propeller
Directorate, FAA, 12 New England Executive Park, Burlington, MA 01803,
telephone (781) 238-7190, fax (781) 238-7170.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for the specified model helicopters was published in the
Federal Register on January 27, 2010 (75 FR 4308). That action proposed
to require replacing the MGB filter bowl assembly with a two-piece MGB
filter bowl assembly and replacing the existing mounting studs. That
action also proposed inspecting the MGB lube system filters, the
housing, the housing threads, and the lockring counterbore and
repairing and replacing them as necessary.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 22 helicopters of U.S.
registry. The required actions will take about 6 hours to inspect the
existing filter bowl assembly and replace the MGB lube system filters,
the mounting studs, and to install an improved filter bowl assembly at
an average labor rate of $85 per work hour. Required parts will cost
about $3,257 per helicopter. Based on these figures, the total cost
impact of the AD on U.S. operators is $82,214.
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 the regulation:
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. 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 an economic evaluation of the estimated costs to comply
with this AD. See the AD docket to examine the economic evaluation.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2010-10-03 Sikorsky Aircraft Corporation: Amendment 39-16282. Docket
No. FAA-2010-0060; Directorate Identifier 2010-SW-06-AD.
Applicability: Model S-92A helicopters, with main gearbox (MGB)
filter bowl assembly, part number (P/N) 92351-15802-101, installed,
certificated in any category.
Compliance: Required as indicated, unless done previously.
To prevent failure of the MGB filter bowl assembly due to
failure of the mounting studs or the filter bowl, loss of oil from
the MGB, failure of the MGB, and subsequent loss of control of the
helicopter, do the following:
(a) Within 60 days:
(1) Remove the MGB filter bowl assembly by following the
Accomplishment Instructions, paragraphs 3.A. (1) through 3.A.(5), of
Sikorsky Alert Service Bulletin No. 92-63-022A, dated December 18,
2009 (ASB).
(2) Remove the primary filter element, P/N 70351-38801-102, from
the MGB lube system filter and visually inspect it for damage as
depicted in Figures 1, 2, and 3 of the ASB. If the primary filter
element has ``wavy'' pleats, internal buckling, or indented dimples,
before further flight, replace it with an airworthy filter element.
(3) Visually inspect the secondary filter element, P/N 70351-
38801-103, for damage as depicted in Figures 4 and 5 of the ASB. If
the secondary filter element has ``wavy'' pleats or an elongated
cup, before further flight, replace it with an airworthy filter
element.
(4) Replace the MGB lube system filter assembly mounting studs:
[[Page 27411]]
(i) Remove the studs by following the Accomplishment
Instructions, paragraphs 3.B.(1) through 3.B.(4) of the ASB.
Visually inspect the tapped holes for any damage to the threads.
Serrations on the entire counter bore (360 degrees) are acceptable.
Serrations in the housing must be intact, and mating serrations on
the lock ring must line up with serrations on the housing. Visually
inspect the housing to determine that the housing threads are free
from damage and corrosion. Visually inspect housing lockring
counterbore to determine if the housing is airworthy.
(ii) If you find damage or corrosion to the housing threads, the
housing, or the lockring counterbore, stop work and contact Kirk
Gustafson, Aviation Safety Engineer, Boston Aircraft Certification
Office, Engine and Propeller Directorate, FAA, 12 New England
Executive Park, Burlington, MA 01803, telephone (781) 238-7190, fax
(781) 238-7170.
(iii) If you do not find damage to the housing threads, the
housing, or the lockring counterbore that requires repair, replace
the mounting studs by following the Accomplishment Instructions,
paragraphs 3.B.(7) through 3.B.(15) of the ASB.
(5) Install an airworthy, two-piece MGB filter bowl assembly
modification kit, P/N 92070-35005-011, as depicted in Figures 8 and
9 of the ASB and by following the Accomplishment Instructions,
paragraphs 3.C.(1) through 3.C.(20), of the ASB.
(b) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Boston Aircraft Certification Office, Attn:
Kirk Gustafson, Aviation Safety Engineer, Boston Aircraft
Certification Office, Engine and Propeller Directorate, FAA, 12 New
England Executive Park, Burlington, MA 01803, telephone (781) 238-
7190, fax (781) 238-7170, for information about previously approved
alternative methods of compliance.
(c) The Joint Aircraft System/Component (JASC) Code is 6320:
Main Rotor Gearbox.
(d) Inspecting and replacing the MGB filter bowl assembly shall
be done by following the specified portions of Sikorsky Alert
Service Bulletin No. 92-63-022A, dated December 18, 2009. The
Director of the Federal Register approved this incorporation by
reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51.
Copies may be obtained from Sikorsky Aircraft Corporation, Attn:
Manager, Commercial Technical Support, mailstop s581a, 6900 Main
Street, Stratford, CT, telephone (203) 383-4866, e-mail address
tsslibrary@sikorsky.com, or at https://www.sikorsky.com. Copies may
be inspected at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, 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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
(e) This amendment becomes effective on June 21, 2010.
Issued in Fort Worth, Texas, on April 27, 2010.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2010-11069 Filed 5-14-10; 8:45 am]
BILLING CODE 4910-13-P
