Airworthiness Directives; Eurocopter France Model EC120 Helicopters, 24304-24305 [05-8951]
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Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Rules and Regulations
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By order of the Board of Governors of the
Federal Reserve System, May 4, 2005.
Jennifer J. Johnson,
Secretary of the Board.
[FR Doc. 05–9231 Filed 5–6–05; 8:45 am]
BILLING CODE 6210–02–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20289; Directorate
Identifier 2003–SW–55–AD; Amendment 39–
14073; AD 2005–09–05]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model EC120 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
This amendment adopts a
new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
EC120 helicopters that requires
inspecting the tail rotor drive shaft
(drive shaft) damper half-clamps (halfclamps) to determine if they are
centered on the friction ring, and if not
correctly positioned, centering the halfSUMMARY:
VerDate jul<14>2003
17:12 May 06, 2005
Jkt 205001
May
May
May
May
May
May
May
May
May
May
May
May
3,
3,
3,
3,
3,
3,
3,
4,
3,
3,
3,
3,
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
depository institutions under 201.4(b)
are:
Federal Reserve Bank
*
4.00
4.00
4.00
4.00
4.00
4.00
4.00
4.00
4.00
4.00
4.00
4.00
Effective
clamps on the friction ring. This
amendment is prompted by the
discovery of half-clamps that were
incorrectly positioned. The actions
specified by this AD are intended to
detect incorrect positioning of the drive
shaft half-clamps, and to prevent
interference of the half-clamps with the
drive shaft, which could result in
scoring on the drive shaft, failure of the
drive shaft, and subsequent loss of
control of the helicopter.
DATES: Effective June 13, 2005.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of June 13,
2005.
ADDRESSES: You may get the service
information identified in this AD from
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas
75053–4005, telephone (972) 641–3460,
fax (972) 641–3527.
Examining the Docket
You may examine the docket that
contains this AD, any comments, and
other information on the Internet at
https://dms.dot.gov, or at the Docket
Management System (DMS), U.S.
Department of Transportation, 400
Seventh Street SW., Room PL–401, on
the plaza level of the Nassif Building,
Washington, DC.
PO 00000
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4.50
4.50
Effective
May
May
May
May
May
May
May
May
May
May
May
May
3,
3,
3,
3,
3,
3,
3,
4,
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3,
3,
3,
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
2005.
Eric
Haight, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Regulations and
Policy Group, Fort Worth, Texas 76193–
0111, telephone (817) 222–5204, fax
(817) 222–5961.
FOR FURTHER INFORMATION CONTACT:
A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on February 10, 2005
(70 FR 7056). For helicopters with a
serial number of 1362 or below, that
action proposed to require, within 50
hours time-in-service (TIS) for
helicopters with 500 or more hours TIS;
or no later than 550 hours TIS for
helicopters with less than 500 hours
TIS, a one-time inspection of the drive
shaft half-clamps to determine if they
are centered on the friction ring, and if
they are not, centering the half-clamps
on the friction ring.
The Direction Generale De L’Aviation
Civile (DGAC), the airworthiness
authority for France, notified the FAA
that an unsafe condition may exist on
Eurocopter Model EC120B helicopters.
The DGAC advises of the discovery of
a case of incorrect drive shaft damper
positioning, which led to interference of
the two half-clamps with the drive shaft
tube and caused a score on the drive
shaft.
SUPPLEMENTARY INFORMATION:
E:\FR\FM\09MYR1.SGM
09MYR1
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Rules and Regulations
Eurocopter has issued Alert Telex No.
65A004 R1, dated January 27, 2004,
which specifies re-positioning of the
drive shaft damper, if necessary. The
DGAC classified this alert telex as
mandatory and issued AD No. UF–
2003–465, dated December 22, 2003,
and AD No. F–2003–465(A), dated
January 21, 2004, to ensure the
continued airworthiness of these
helicopters in France.
This helicopter model is
manufactured in France and is type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, the DGAC has kept
the FAA informed of the situation
described above. The FAA has
examined the findings necessary for
products of this type design that are
certificated for operation in the United
States.
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.
We estimate that this AD will affect
78 helicopters of U.S. registry. The onetime inspection will take approximately
2 work hours to accomplish, and the
modification will take 6 work hours, at
an average labor rate of $65 per work
hour. Required modification parts will
cost approximately $180 per helicopter.
Based on these figures, we estimate the
total cost impact of the proposed AD on
U.S. operators to be $14,700, assuming
8 helicopters need modification.
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.
VerDate jul<14>2003
17:12 May 06, 2005
Jkt 205001
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
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
2005–09–05 Eurocopter France:
Amendment 39–14073. Docket No.
FAA–2005–20289; Directorate Identifier
2003–SW–55–AD.
Applicability: Model EC120B helicopters,
serial number 1362 and below, certificated in
any category.
Compliance: Required within 50 hours
time-in-service (TIS) for helicopters with 500
or more hours TIS; or no later than 550 hours
TIS for helicopters with less than 500 hours
TIS, unless accomplished previously.
To detect incorrect positioning of the tail
rotor drive shaft (drive shaft) damper halfclamps (half-clamps), and to prevent
interference of the half-clamps with the drive
shaft, which could result in scoring on the
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
24305
drive shaft, failure of the drive shaft, and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Inspect the half-clamps, part number
C651A4103201 or C651A4103202, to
determine if they are centered on the friction
ring, using the Operational Procedure,
paragraph 2.B., of Eurocopter Alert Telex No.
65A004 R1, dated January 27, 2004 (Alert
Telex). If the half-clamps are not centered on
the friction ring, center the half-clamps on
the friction ring in accordance with the
Operational Procedure, paragraph 2.B, and
Rework Sheet No. EC 120–53–02–04 in
Appendix 1 of the Alert Telex.
(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 Safety Management Group,
Rotorcraft Directorate, FAA, for information
about previously approved alternative
methods of compliance.
(c) Special flight permits will not be
issued.
(d) The inspection and modification shall
be done in accordance with Eurocopter Alert
Telex No. 65A004 R1, dated January 27,
2004. 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
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas 75053–
4005, telephone (972) 641–3460, fax (972)
641–3527. 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 13, 2005.
Note: The subject of this AD is addressed
in Direction Generale De L’Aviation Civile
(France) AD No. UF–2003–465, dated
December 22, 2003, and AD No. F–2003–465,
Revision A, dated January 21, 2004.
Issued in Fort Worth, Texas, on April 27,
2005.
Carl F. Mittag,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 05–8951 Filed 5–6–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20292; Directorate
Identifier 2004–SW–26–AD; Amendment 39–
14075; AD 2005–09–07]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A109E Helicopters
Federal Aviation
Administration, DOT.
AGENCY:
E:\FR\FM\09MYR1.SGM
09MYR1
]]>Agencies
[Federal Register Volume 70, Number 88 (Monday, May 9, 2005)]
[Rules and Regulations]
[Pages 24304-24305]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-8951]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20289; Directorate Identifier 2003-SW-55-AD;
Amendment 39-14073; AD 2005-09-05]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC120
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model EC120 helicopters that requires
inspecting the tail rotor drive shaft (drive shaft) damper half-clamps
(half-clamps) to determine if they are centered on the friction ring,
and if not correctly positioned, centering the half-clamps on the
friction ring. This amendment is prompted by the discovery of half-
clamps that were incorrectly positioned. The actions specified by this
AD are intended to detect incorrect positioning of the drive shaft
half-clamps, and to prevent interference of the half-clamps with the
drive shaft, which could result in scoring on the drive shaft, failure
of the drive shaft, and subsequent loss of control of the helicopter.
DATES: Effective June 13, 2005.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 13, 2005.
ADDRESSES: You may get the service information identified in this AD
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie,
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
Examining the Docket
You may examine the docket that contains this AD, any comments, and
other information on the Internet at https://dms.dot.gov, or at the
Docket Management System (DMS), U.S. Department of Transportation, 400
Seventh Street SW., Room PL-401, on the plaza level of the Nassif
Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Eric Haight, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Policy Group, Fort Worth,
Texas 76193-0111, telephone (817) 222-5204, fax (817) 222-5961.
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 February 10, 2005 (70 FR 7056). For helicopters
with a serial number of 1362 or below, that action proposed to require,
within 50 hours time-in-service (TIS) for helicopters with 500 or more
hours TIS; or no later than 550 hours TIS for helicopters with less
than 500 hours TIS, a one-time inspection of the drive shaft half-
clamps to determine if they are centered on the friction ring, and if
they are not, centering the half-clamps on the friction ring.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on Eurocopter Model EC120B helicopters. The DGAC
advises of the discovery of a case of incorrect drive shaft damper
positioning, which led to interference of the two half-clamps with the
drive shaft tube and caused a score on the drive shaft.
[[Page 24305]]
Eurocopter has issued Alert Telex No. 65A004 R1, dated January 27,
2004, which specifies re-positioning of the drive shaft damper, if
necessary. The DGAC classified this alert telex as mandatory and issued
AD No. UF-2003-465, dated December 22, 2003, and AD No. F-2003-465(A),
dated January 21, 2004, to ensure the continued airworthiness of these
helicopters in France.
This helicopter model is manufactured in France and is type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, the DGAC has kept the FAA informed of
the situation described above. The FAA has examined the findings
necessary for products of this type design that are certificated for
operation in the United States.
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.
We estimate that this AD will affect 78 helicopters of U.S.
registry. The one-time inspection will take approximately 2 work hours
to accomplish, and the modification will take 6 work hours, at an
average labor rate of $65 per work hour. Required modification parts
will cost approximately $180 per helicopter. Based on these figures, we
estimate the total cost impact of the proposed AD on U.S. operators to
be $14,700, assuming 8 helicopters need modification.
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 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:
2005-09-05 Eurocopter France: Amendment 39-14073. Docket No. FAA-
2005-20289; Directorate Identifier 2003-SW-55-AD.
Applicability: Model EC120B helicopters, serial number 1362 and
below, certificated in any category.
Compliance: Required within 50 hours time-in-service (TIS) for
helicopters with 500 or more hours TIS; or no later than 550 hours
TIS for helicopters with less than 500 hours TIS, unless
accomplished previously.
To detect incorrect positioning of the tail rotor drive shaft
(drive shaft) damper half-clamps (half-clamps), and to prevent
interference of the half-clamps with the drive shaft, which could
result in scoring on the drive shaft, failure of the drive shaft,
and subsequent loss of control of the helicopter, accomplish the
following:
(a) Inspect the half-clamps, part number C651A4103201 or
C651A4103202, to determine if they are centered on the friction
ring, using the Operational Procedure, paragraph 2.B., of Eurocopter
Alert Telex No. 65A004 R1, dated January 27, 2004 (Alert Telex). If
the half-clamps are not centered on the friction ring, center the
half-clamps on the friction ring in accordance with the Operational
Procedure, paragraph 2.B, and Rework Sheet No. EC 120-53-02-04 in
Appendix 1 of the Alert Telex.
(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 Safety Management Group, Rotorcraft Directorate, FAA,
for information about previously approved alternative methods of
compliance.
(c) Special flight permits will not be issued.
(d) The inspection and modification shall be done in accordance
with Eurocopter Alert Telex No. 65A004 R1, dated January 27, 2004.
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 American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas 75053-4005, telephone (972) 641-
3460, fax (972) 641-3527. 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 13, 2005.
Note: The subject of this AD is addressed in Direction Generale
De L'Aviation Civile (France) AD No. UF-2003-465, dated December 22,
2003, and AD No. F-2003-465, Revision A, dated January 21, 2004.
Issued in Fort Worth, Texas, on April 27, 2005.
Carl F. Mittag,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-8951 Filed 5-6-05; 8:45 am]
BILLING CODE 4910-13-P
