Airworthiness Directives; Sikorsky Aircraft Corporation Model S-92A Helicopters, 30798-30800 [06-4911]
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30798
Federal Register / Vol. 71, No. 104 / Wednesday, May 31, 2006 / Rules and Regulations
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
I
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Gulfstream
Model Galaxy and Model Gulfstream 200
airplanes, certificated in any category.
Unsafe Condition
(d) This AD results from a correction of the
power setting logic and table limits in the
performance model by the engine
manufacturer. We are issuing this AD to
ensure that the flightcrew is provided with
correct information to ensure a safe takeoff at
certain altitudes; inadequate takeoff
performance tables used in such conditions
could result in reduced control of the
airplane during takeoff.
mstockstill on PROD1PC61 with RULES
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.
Airplane Flight Manual (AFM) Revision
(f) Within 50 flight hours after the effective
date of this AD: Revise the Limitations
section of the Gulfstream 200 AFM, by
incorporating the information specified in
Section V, ‘‘Performance,’’ of Israel Aircraft
Industries Gulfstream 200 Temporary
Revision (TR) 7, dated August 18, 2003, as
specified in the TR. Section V of TR 7
includes procedures for incorporating revised
takeoff performance tables. Thereafter,
operate the airplane according to the
limitations and procedures in Section V of
TR 7. This may be done by inserting a copy
of Section V of Gulfstream TR 7 into the
AFM. When Section V of TR 7 has been
Jkt 208001
[Docket No. FAA–2006–24875; Directorate
Identifier 2006–SW–03–AD; Amendment 39–
14618; AD 2006–11–14]
(g)(1) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
(2) Before using any AMOC approved in
accordance with § 39.19 on any airplane to
which the AMOC applies, notify the
appropriate principal inspector in the FAA
Flight Standards Certificate Holding District
Office.
(h) Israeli airworthiness directive 72–03–
05–09, dated September 22, 2003, also
addresses the subject of this AD.
Effective Date
(a) This AD becomes effective July 5, 2006.
14:53 May 30, 2006
DEPARTMENT OF TRANSPORTATION
Related Information
2006–10–18 Gulfstream Aerospace LP
(formerly Israel Aircraft Industries,
Ltd.): Amendment 39–14602. Docket No.
FAA–2005–23478; Directorate Identifier
2005–NM–175–AD.
VerDate Aug<31>2005
included in the general revisions of the AFM,
the general revisions may be inserted in the
AFM, provided the relevant information in
the general revision is identical to that in
Section V of TR 7.
Alternative Methods of Compliance
(AMOCs)
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Material Incorporated by Reference
(i) You must use Israel Aircraft Industries
Gulfstream 200 Temporary
Revision 7, dated August 18, 2003, to the
Gulfstream 200 Airplane Flight
Manual, to perform the actions that are
required by this AD, unless the AD specifies
otherwise. The Director of the Federal
Register approved the incorporation by
reference of this document in accordance
with 5 U.S.C. 552(a) and 1 CFR part 51.
Contact Gulfstream Aerospace Corporation,
P.O. Box 2206, Mail Station D–25, Savannah,
Georgia 31402–2206, for a copy of this
service information. You may review copies
at the Docket Management Facility, U.S.
Department of Transportation, 400 Seventh
Street, SW., Room PL–401, Nassif Building,
Washington, DC; on the Internet at https://
dms.dot.gov; or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/
federal_register/code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on May 9,
2006.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 06–4910 Filed 5–30–06; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 39
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Model S–92A
Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
specified Sikorsky Aircraft Corporation
(Sikorsky) Model S–92A helicopters.
This action requires inspecting each
main transmission assembly mounting
bolt (bolt) for wear or corrosion, and if
wear or corrosion is found, replacing the
bolt, bolt barrel nut, and cage. This
amendment is prompted by a report of
a failure of a bolt that was discovered
during a routine maintenance
inspection. The actions specified in this
AD are intended to prevent failure of a
bolt, which could result in loss of
support of the main transmission and
subsequent loss of control of the
helicopter.
DATES: Effective June 15, 2006.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of June 15,
2006.
Comments for inclusion in the Rules
Docket must be received on or before
July 31, 2006.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD:
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically;
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically;
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590;
• Fax: (202) 493–2251; or
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
You may get the service information
identified in this AD from Sikorsky
E:\FR\FM\31MYR1.SGM
31MYR1
Federal Register / Vol. 71, No. 104 / Wednesday, May 31, 2006 / Rules and Regulations
Aircraft Corporation, Attn: Manager,
Commercial Tech Support, 6900 Main
Street, Stratford, Connecticut 06614,
phone (203) 386–3001, fax (203) 386–
5983.
mstockstill on PROD1PC61 with RULES
Examining the Docket
You may examine the docket that
contains the AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or in person at the
Docket Management System (DMS)
Docket Offices between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The Docket Office
(telephone (800) 647–5227) is located on
the plaza level of the Department of
Transportation Nassif Building at the
street address stated in the ADDRESSES
section. Comments will be available in
the AD docket shortly after the DMS
receives them.
FOR FURTHER INFORMATION CONTACT:
Wayne Gaulzetti, Aviation Safety
Engineer, Boston Aircraft Certification
Office, 12 New England Executive Park,
Burlington, MA 01803, telephone (781)
238–7156, fax (781) 238–7170.
SUPPLEMENTARY INFORMATION: This
amendment adopts an AD for Sikorsky
Model S–92A helicopters with bolts,
part number SS5211–10–47, installed.
This action requires opening the No. 1
and No. 2 engine work platforms to gain
access to the bolts and inspecting each
of the 8 bolts for wear or corrosion. The
inspections for wear or corrosion are
required within 100 hours time-inservice (TIS), unless accomplished
within the last 500 hours TIS. This
action also requires, before further
flight, replacing any bolt on which wear
or corrosion is found, together with the
bolt barrel nut and cage. This
amendment is prompted by a report of
a bolt failure, which was discovered
during a routine 1,250-hours TIS
maintenance inspection. Subsequent
investigation and analysis of the failed
bolt revealed damage from wear and
corrosion. The actions specified in this
AD are intended to prevent failure of a
bolt, which could result in loss of
support of the main transmission and
subsequent loss of control of the
helicopter.
We have reviewed Sikorsky Alert
Service Bulletin (ASB) No. 92–63–003,
dated February 1, 2006, which describes
inspecting the 8 bolts to verify that each
bolt has the correct torque, as well as
inspecting for wear or corrosion on the
bolt, and replacing any bolt on which
wear or corrosion is discovered, together
with the bolt barrel nut and cage. The
ASB also describes reporting the
condition of any damaged bolt and
returning any removed hardware to
VerDate Aug<31>2005
14:53 May 30, 2006
Jkt 208001
Sikorsky. This AD does not require
verifying that each bolt has the correct
torque, reporting the bolt torque or bolt
damage information, nor returning the
hardware to Sikorsky. Sikorsky plans to
make available a redesigned bolt that
should eliminate the fretting that leads
to corrosion and subsequent failure of
the bolt. In light of that information, we
anticipate that we will later issue
further AD action to require repetitive
inspections at intervals of 500 hours TIS
until that bolt is made available by
Sikorsky and is installed on helicopters.
This unsafe condition is likely to exist
or develop on other helicopters of the
same type design. Therefore, this AD is
being issued to prevent failure of a bolt,
which could result in loss of support of
the main transmission and subsequent
loss of control of the helicopter.
Accomplish the actions by following the
specified portions of the ASB described
previously. The short compliance time
is required because the previously
described critical unsafe condition can
adversely affect the structural integrity
and controllability of the helicopter.
Since the fleet has helicopters accruing
8 to 10 hours TIS per day, those
helicopters could accrue 100 hours TIS
in approximately 2 weeks of operation.
Therefore, inspecting each bolt for wear
or corrosion is required within 100
hours TIS and replacing any bolt on
which wear or corrosion is found, as
well as replacing the bolt barrel nut and
cage, are required before further flight,
and this AD must be issued
immediately.
Since a situation exists that requires
the immediate adoption of this
regulation, it is found that notice and
opportunity for prior public comment
hereon are impracticable, and that good
cause exists for making this amendment
effective in less than 30 days.
We estimate that this AD will affect 8
helicopters, and the inspections for
wear or corrosion will take
approximately 3.5 work hours to
accomplish at an average labor rate of
$80 per work hour. Required parts will
cost approximately $197 for each bolt,
$28 for each bolt barrel nut, and $4 for
each cage. Based on these figures, we
estimate the total cost impact of the AD
on U.S. operators to be $4,072 per
helicopter, assuming that replacing 8
bolts, 8 bolt barrel nuts, and 8 cages is
necessary.
Comments Invited
This AD is a final rule that involves
requirements that affect flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to submit any
written data, views, or arguments
PO 00000
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Fmt 4700
Sfmt 4700
30799
regarding this AD. Send your comments
to an address listed under ADDRESSES.
Include ‘‘Docket No. FAA–2006–24875;
Directorate Identifier 2006–SW–03–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the AD. We will consider all comments
received by the closing date and may
amend the AD in light of those
comments.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of our docket Web site,
you can find and read the comments to
any of our dockets, including the name
of the individual who sent the
comment. You may review the DOT’s
complete Privacy Act Statement in the
Federal Register published on April 11,
2000 (65 FR 19477–78), or you may visit
https://dms.dot.gov.
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 DMS 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
E:\FR\FM\31MYR1.SGM
31MYR1
30800
Federal Register / Vol. 71, No. 104 / Wednesday, May 31, 2006 / Rules and Regulations
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
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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
2006–11–14 Sikorsky Aircraft Corporation:
Amendment 39–14618. Docket No.
FAA–2006–24875; Directorate Identifier
2006–SW–03–AD.
mstockstill on PROD1PC61 with RULES
Applicability
Model S–92A helicopters, with main
transmission mounting bolt (bolt), part
number (P/N) SS5211–10–47, installed,
certificated in any category.
14:53 May 30, 2006
Jkt 208001
(e) This amendment becomes effective
on June 15, 2006.
Issued in Fort Worth, Texas, on May 18,
2006.
Judy I. Carl,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 06–4911 Filed 5–30–06; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
Compliance
Required as indicated.
To prevent failure of a bolt, which could
result in loss of support of the main
transmission and subsequent loss of control
of the helicopter, accomplish the following:
(a) Within 100 hours time-in-service (TIS),
unless accomplished within the last 500
hours TIS, open the No. 1 and No. 2 engine
work platforms to gain access to the 8 bolts.
Remove each bolt, one at a time, and visually
inspect the bolt shank and threads for wear
or corrosion in accordance with paragraphs
3.A.(6)(a) of the Accomplishment
Instructions in Sikorsky Aircraft Corporation
Alert Service Bulletin No. 92–63–003, dated
February 1, 2006 (ASB). Reporting the
condition of the mounting bolt, tagging the
mounting bolt with location, and sending the
removed mounting bolt and barrel nut to
Sikorsky Aircraft Corporation are not
required to satisfy the requirements of this
AD.
(b) Before further flight, replace any bolt on
which wear or corrosion is found, as well as
the bolt barrel nut and cage, with an
VerDate Aug<31>2005
airworthy bolt, P/N SS5211–10–47, barrel
nut, P/N RMLH2577–108, and cage, P/N
NAS578–10B.
(c) 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, Engine and Propeller
Directorate, FAA, ATTN: Wayne Gaulzetti,
Aviation Safety Engineer, 12 New England
Executive Park, Burlington, MA 01803,
telephone (781) 238–7156, fax (781) 238–
7170, for information about previously
approved alternative methods of compliance.
(d) The inspections shall be done in
accordance with the specified paragraphs of
Sikorsky Aircraft Corporation Alert Service
Bulletin No. 92–63–003, dated February 1,
2006. 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 Tech Support, 6900 Main Street,
Stratford, Connecticut 06614, phone (203)
386–3001, fax (203) 386–5983. Copies may be
inspected 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.
14 CFR Part 97
[Docket No. 30494; Amdt. No. 3167]
Standard Instrument Approach
Procedures; Miscellaneous
Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment amends
Standard Instrument Approach
Procedures (SIAPs) for operations at
certain airports. These regulatory
actions are needed because of changes
occurring in the National Airspace
System, such as the commissioning of
new navigational facilities, addition of
new obstacles, or changes in air traffic
requirements. These changes are
designed to provide safe and efficient
use of the navigable airspace and to
promote safe flight operations under
PO 00000
Frm 00006
Fmt 4700
Sfmt 4700
instrument flight rules at the affected
airports.
This rule is effective May 31,
2006. The compliance date for each
SIAP is specified in the amendatory
provisions.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of May 31,
2006.
DATES:
Availability of matter
incorporated by reference in the
amendment is as follows:
For Examination—
1. FAA Rules Docket, FAA
Headquarters Building, 800
Independence Ave., SW., Washington,
DC 20591;
2. The FAA Regional Office of the
region in which affected airport is
located; or
3. The National Flight Procedures
Office, 6500 South MacArthur Blvd.,
Oklahoma City, OK 73169; or
4. 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.
For Purchase—Individual SIAP
copies may be obtained from:
1. FAA Public Inquiry Center (APA–
200), FAA Headquarters Building, 800
Independence Avenue, SW.,
Washington, DC 20591; or
2. The FAA Regional Office of the
region in which the affected airport is
located.
By Subscription—Copies of all SIAPs,
mailed once every 2 weeks, are for sale
by the Superintendent of Documents,
U.S. Government Printing Office,
Washington, DC 20402.
FOR FURTHER INFORMATION CONTACT:
Donald P. Pate, Flight Procedure
Standards Branch (AFS–420), Flight
Technologies and Programs Division,
Flight Standards Service, Federal
Aviation Administration, Mike
Monroney Aeronautical Center, 6500
South MacArthur Blvd., Oklahoma City,
OK 73169 (Mail Address: P.O. Box
25082, Oklahoma City, OK 73125)
telephone: (405) 954–4164.
SUPPLEMENTARY INFORMATION: This
amendment to Title 14, Code of Federal
Regulations, Part 97 (14 CFR part 97)
amends Standard Instrument Approach
Procedures (SIAPs). The complete
regulatory description of each SIAP is
contained in the appropriate FAA Form
8260, as modifiedby the the National
Flight Data Center (FDC)/Permanent
ADDRESSES:
E:\FR\FM\31MYR1.SGM
31MYR1
]]>Agencies
[Federal Register Volume 71, Number 104 (Wednesday, May 31, 2006)]
[Rules and Regulations]
[Pages 30798-30800]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 06-4911]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-24875; Directorate Identifier 2006-SW-03-AD;
Amendment 39-14618; AD 2006-11-14]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation Model S-
92A Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Sikorsky Aircraft Corporation (Sikorsky) Model S-92A
helicopters. This action requires inspecting each main transmission
assembly mounting bolt (bolt) for wear or corrosion, and if wear or
corrosion is found, replacing the bolt, bolt barrel nut, and cage. This
amendment is prompted by a report of a failure of a bolt that was
discovered during a routine maintenance inspection. The actions
specified in this AD are intended to prevent failure of a bolt, which
could result in loss of support of the main transmission and subsequent
loss of control of the helicopter.
DATES: Effective June 15, 2006.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 15, 2006.
Comments for inclusion in the Rules Docket must be received on or
before July 31, 2006.
ADDRESSES: Use one of the following addresses to submit comments on
this AD:
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically;
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically;
Mail: Docket Management Facility; U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590;
Fax: (202) 493-2251; or
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
You may get the service information identified in this AD from
Sikorsky
[[Page 30799]]
Aircraft Corporation, Attn: Manager, Commercial Tech Support, 6900 Main
Street, Stratford, Connecticut 06614, phone (203) 386-3001, fax (203)
386-5983.
Examining the Docket
You may examine the docket that contains the AD, any comments, and
other information on the Internet at https://dms.dot.gov, or in person
at the Docket Management System (DMS) Docket Offices between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The Docket
Office (telephone (800) 647-5227) is located on the plaza level of the
Department of Transportation Nassif Building at the street address
stated in the ADDRESSES section. Comments will be available in the AD
docket shortly after the DMS receives them.
FOR FURTHER INFORMATION CONTACT: Wayne Gaulzetti, Aviation Safety
Engineer, Boston Aircraft Certification Office, 12 New England
Executive Park, Burlington, MA 01803, telephone (781) 238-7156, fax
(781) 238-7170.
SUPPLEMENTARY INFORMATION: This amendment adopts an AD for Sikorsky
Model S-92A helicopters with bolts, part number SS5211-10-47,
installed. This action requires opening the No. 1 and No. 2 engine work
platforms to gain access to the bolts and inspecting each of the 8
bolts for wear or corrosion. The inspections for wear or corrosion are
required within 100 hours time-in-service (TIS), unless accomplished
within the last 500 hours TIS. This action also requires, before
further flight, replacing any bolt on which wear or corrosion is found,
together with the bolt barrel nut and cage. This amendment is prompted
by a report of a bolt failure, which was discovered during a routine
1,250-hours TIS maintenance inspection. Subsequent investigation and
analysis of the failed bolt revealed damage from wear and corrosion.
The actions specified in this AD are intended to prevent failure of a
bolt, which could result in loss of support of the main transmission
and subsequent loss of control of the helicopter.
We have reviewed Sikorsky Alert Service Bulletin (ASB) No. 92-63-
003, dated February 1, 2006, which describes inspecting the 8 bolts to
verify that each bolt has the correct torque, as well as inspecting for
wear or corrosion on the bolt, and replacing any bolt on which wear or
corrosion is discovered, together with the bolt barrel nut and cage.
The ASB also describes reporting the condition of any damaged bolt and
returning any removed hardware to Sikorsky. This AD does not require
verifying that each bolt has the correct torque, reporting the bolt
torque or bolt damage information, nor returning the hardware to
Sikorsky. Sikorsky plans to make available a redesigned bolt that
should eliminate the fretting that leads to corrosion and subsequent
failure of the bolt. In light of that information, we anticipate that
we will later issue further AD action to require repetitive inspections
at intervals of 500 hours TIS until that bolt is made available by
Sikorsky and is installed on helicopters.
This unsafe condition is likely to exist or develop on other
helicopters of the same type design. Therefore, this AD is being issued
to prevent failure of a bolt, which could result in loss of support of
the main transmission and subsequent loss of control of the helicopter.
Accomplish the actions by following the specified portions of the ASB
described previously. The short compliance time is required because the
previously described critical unsafe condition can adversely affect the
structural integrity and controllability of the helicopter. Since the
fleet has helicopters accruing 8 to 10 hours TIS per day, those
helicopters could accrue 100 hours TIS in approximately 2 weeks of
operation. Therefore, inspecting each bolt for wear or corrosion is
required within 100 hours TIS and replacing any bolt on which wear or
corrosion is found, as well as replacing the bolt barrel nut and cage,
are required before further flight, and this AD must be issued
immediately.
Since a situation exists that requires the immediate adoption of
this regulation, it is found that notice and opportunity for prior
public comment hereon are impracticable, and that good cause exists for
making this amendment effective in less than 30 days.
We estimate that this AD will affect 8 helicopters, and the
inspections for wear or corrosion will take approximately 3.5 work
hours to accomplish at an average labor rate of $80 per work hour.
Required parts will cost approximately $197 for each bolt, $28 for each
bolt barrel nut, and $4 for each cage. Based on these figures, we
estimate the total cost impact of the AD on U.S. operators to be $4,072
per helicopter, assuming that replacing 8 bolts, 8 bolt barrel nuts,
and 8 cages is necessary.
Comments Invited
This AD is a final rule that involves requirements that affect
flight safety and was not preceded by notice and an opportunity for
public comment; however, we invite you to submit any written data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``Docket No. FAA-2006-24875;
Directorate Identifier 2006-SW-03-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the AD. We will consider
all comments received by the closing date and may amend the AD in light
of those comments.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of our docket
Web site, you can find and read the comments to any of our dockets,
including the name of the individual who sent the comment. You may
review the DOT's complete Privacy Act Statement in the Federal Register
published on April 11, 2000 (65 FR 19477-78), or you may visit https://
dms.dot.gov.
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 DMS 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
[[Page 30800]]
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:
2006-11-14 Sikorsky Aircraft Corporation: Amendment 39-14618. Docket
No. FAA-2006-24875; Directorate Identifier 2006-SW-03-AD.
Applicability
Model S-92A helicopters, with main transmission mounting bolt
(bolt), part number (P/N) SS5211-10-47, installed, certificated in
any category.
Compliance
Required as indicated.
To prevent failure of a bolt, which could result in loss of
support of the main transmission and subsequent loss of control of
the helicopter, accomplish the following:
(a) Within 100 hours time-in-service (TIS), unless accomplished
within the last 500 hours TIS, open the No. 1 and No. 2 engine work
platforms to gain access to the 8 bolts. Remove each bolt, one at a
time, and visually inspect the bolt shank and threads for wear or
corrosion in accordance with paragraphs 3.A.(6)(a) of the
Accomplishment Instructions in Sikorsky Aircraft Corporation Alert
Service Bulletin No. 92-63-003, dated February 1, 2006 (ASB).
Reporting the condition of the mounting bolt, tagging the mounting
bolt with location, and sending the removed mounting bolt and barrel
nut to Sikorsky Aircraft Corporation are not required to satisfy the
requirements of this AD.
(b) Before further flight, replace any bolt on which wear or
corrosion is found, as well as the bolt barrel nut and cage, with an
airworthy bolt, P/N SS5211-10-47, barrel nut, P/N RMLH2577-108, and
cage, P/N NAS578-10B.
(c) 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, Engine
and Propeller Directorate, FAA, ATTN: Wayne Gaulzetti, Aviation
Safety Engineer, 12 New England Executive Park, Burlington, MA
01803, telephone (781) 238-7156, fax (781) 238-7170, for information
about previously approved alternative methods of compliance.
(d) The inspections shall be done in accordance with the
specified paragraphs of Sikorsky Aircraft Corporation Alert Service
Bulletin No. 92-63-003, dated February 1, 2006. 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 Tech Support, 6900 Main Street, Stratford, Connecticut
06614, phone (203) 386-3001, fax (203) 386-5983. Copies may be
inspected 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 15, 2006.
Issued in Fort Worth, Texas, on May 18, 2006.
Judy I. Carl,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 06-4911 Filed 5-30-06; 8:45 am]
BILLING CODE 4910-13-P
