Airworthiness Directives; Agusta S.p.A. Model A109E Helicopters, 24305-24307 [05-8952]
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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
24306
ACTION:
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Rules and Regulations
Final rule.
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
Agusta S.p.A. (Agusta) Model A109E
helicopters that requires visually
inspecting each main transmission
support fitting (fitting) attachment bolt
(bolt) for a fracture, a crack, or
looseness, and verifying the torque on
each fitting bolt. This amendment is
prompted by two incidents of fatigue
failure of the bolts that secure the
transmission rear support fittings to the
helicopter. The actions specified by this
AD are intended to detect a fracture, a
crack, or looseness of a fitting bolt, and
prevent fatigue failure of a fitting bolt
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
Agusta, 21017 Cascina Costa di
Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111,
fax 39 (0331) 229605–222595.
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:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for Agusta Model A109E
helicopters was published in the
Federal Register on February 10, 2005
(70 FR 7061). That action proposed to
require inspecting the fitting bolts, part
number (P/N) NAS625–14, for a
fracture, a crack, or looseness within 5
hours time-in-service (TIS), and then at
intervals not to exceed 10 hours TIS
until performing a torque inspection of
each fitting bolt. The torque inspection
would have to be accomplished before
further flight if looseness is found, or
within 25 hours TIS if looseness is not
found. If a fracture or a crack is found
on any bolt in any fitting, replacing all
4 of the bolts in a fitting with airworthy
VerDate jul<14>2003
17:12 May 06, 2005
Jkt 205001
fitting bolts would be required before
further flight. If any torque inspection
reveals that the torque of any bolt in a
fitting is not between 11.3–15.8 Nm
(100–140 inch-pounds), all 4 of the bolts
in the fitting would have to be replaced
with airworthy fitting bolts before
further flight.
The Ente Nazionale per l’Aviazione
Civile (ENAC), the airworthiness
authority for Italy, notified the FAA that
an unsafe condition may exist on Agusta
Model A109E helicopters. ENAC
advises of the need to check the bolts
that secure the fittings to the structure
by following the manufacturer’s
Bollettino Tecnico No. 109EP–43, dated
March 25, 2004.
Agusta has issued Bollettino Tecnico
No. 109EP–43, dated March 25, 2004,
which specifies a periodic visual
inspection to verify the integrity of the
slippage marks, and successively
checking the torque of the bolts to
exclude the possible presence of
looseness and/or a fracture or a crack.
ENAC classified this bollettino tecnico
as mandatory and issued AD No. 2004–
099, dated March 29, 2004, to ensure the
continued airworthiness of these
helicopters in Italy.
This helicopter model is
manufactured in Italy 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, ENAC has kept the
FAA informed of the situation described
above. The FAA has examined the
findings of ENAC, reviewed all available
information, and determined that AD
action is 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. However, we have
made a correction in the service
information date that was incorrectly
referenced in the preamble of the
proposal; the date was incorrectly listed
as March 3, 2004 but is correctly
referenced as March 25, 2004 in this
AD. We have determined that this
change will neither increase the
economic burden on any operator nor
increase the scope of the AD.
We estimate that this AD will affect
58 helicopters of U.S. registry. Three
inspections (one initial, one repetitive,
and the torque inspection) will take
approximately 4 work hours to
PO 00000
Frm 00014
Fmt 4700
Sfmt 4700
accomplish at an average labor rate of
$65 per work hour. (The manufacturer
states that it shall recognize a warranty
credit of up to $200 per helicopter for
the labor). Required parts will cost
approximately $1,600 per helicopter
($100 per fitting bolt for 16 fitting bolts).
Based on these figures, the total
estimated cost impact of the AD on U.S.
operators is $115,420, assuming that no
warranty credit is available and that all
affected fitting bolts are replaced.
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.
E:\FR\FM\09MYR1.SGM
09MYR1
Federal Register / Vol. 70, No. 88 / Monday, May 9, 2005 / Rules and Regulations
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
2005–09–07 Agusta S.p.A.: Amendment 39–
14075. Docket No. FAA–2005–20292;
Directorate Identifier 2004–SW–26–AD.
Applicability: Model A109E helicopters,
certificated in any category.
Compliance: Required as indicated, unless
accomplished previously.
To detect a fracture, a crack, or looseness
of a main transmission support fitting
(fitting) attachment bolt (bolt), and prevent
fatigue failure of a fitting bolt and subsequent
loss of control of the helicopter, accomplish
the following:
(a) Within 5 hours time-in-service (TIS),
and then at intervals not to exceed 10 hours
TIS until a torque inspection of each fitting
bolt is accomplished in accordance with
paragraph (b) of this AD, inspect each fitting
bolt, part number NAS625–14, for a fracture,
a crack, or looseness using a light and a
mirror in accordance with Part I, steps 1.
through 4., of Agusta Bollettino Tecnico No.
109EP–43, dated March 25, 2004 (BT).
(1) On each of the 4 fittings, if a fracture
or a crack is found in any bolt, replace all
4 bolts in the fitting with airworthy fitting
bolts before further flight.
(2) If looseness is found in any bolt in any
fitting, inspect each of the 4 bolts on each of
the 4 fittings (16 bolts total) to determine if
the torque is between 11.3–15.8 Nm (100–140
inch-pounds). If the indicated torque is not
within the acceptable range on any bolt in a
fitting, before further flight, remove all 4
bolts in the fitting and replace them with
airworthy fitting bolts in accordance with
Part II, steps 5.1 through 9. of the BT.
(b) Within 25 hours TIS, inspect each bolt
in each fitting to determine if the torque is
between 11.3–15.8 Nm (100–140 inchpounds). If the indicated torque is not within
the acceptable range on any bolt, before
further flight, remove all 4 bolts in the fitting
and replace them with airworthy fitting bolts
in accordance with Part II, steps 5.1 through
9., of the BT.
(c) Accomplishing the inspections
specified in paragraphs (a) and (b) constitute
terminating actions for the requirements of
this AD.
(d) 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
VerDate jul<14>2003
17:12 May 06, 2005
Jkt 205001
about previously approved alternative
methods of compliance.
(e) Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the helicopter to a location where
the requirements of this AD can be
accomplished, provided that no fracture or
crack or looseness was found during the
inspections required by this AD.
(f) The inspections and replacements shall
be done in accordance with Agusta Bollettino
Tecnico No. 109EP–43, dated March 25,
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 Agusta,
21017 Cascina Costa di Samarate (VA) Italy,
Via Giovanni Agusta 520, telephone 39
(0331) 229111, fax 39 (0331) 229605–222595.
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.
(g) This amendment becomes effective on
June 13, 2005.
Note: The subject of this AD is addressed
in Ente Nazionale per l’Aviazione Civile
(Italy) AD No. 2004–099, dated March 29,
2004.
Issued in Fort Worth, Texas, on April 27,
2005.
Carl F. Mittag,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 05–8952 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–2005–20291; Directorate
Identifier 2004–SW–25–AD; Amendment 39–
14074; AD 2005–09–06]
RIN 2120–AA64
Airworthiness Directives; Agusta
S.p.A. Model A119 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for
Agusta S.p.A. (Agusta) Model A119
helicopters that requires visually
inspecting each main transmission
support fitting (fitting) attachment bolt
(bolt) for a fracture, a crack, or
looseness, and verifying the torque on
each fitting bolt. This amendment is
prompted by two incidents of fatigue
failure of the bolts that secure the
transmission rear support fittings to the
helicopter. The actions specified by this
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
24307
AD are intended to detect a fracture, a
crack, or looseness of a fitting bolt, and
prevent fatigue failure of a fitting bolt
and subsequent loss of control of the
helicopter.
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.
DATES:
You may get the service
information identified in this AD from
Agusta, 21017 Cascina Costa di
Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111,
fax 39 (0331) 229605–222595.
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:
Sharon Miles, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for Agusta Model A119
helicopters was published in the
Federal Register on February 10, 2005
(70 FR 7057). That action proposed to
require inspecting each fitting bolt, part
number (P/N) NAS625–14 and P/N
NAS625–18, for a fracture, a crack, or
looseness, within 5 hours time-inservice (TIS) and then at intervals not to
exceed 10 hours TIS until
accomplishing a torque inspection of
each fitting bolt. The torque inspection
would have to be accomplished before
further flight if looseness is found, or
within 25 hours TIS if looseness is not
found. If a fracture or a crack is found
on any bolt in a fitting, replacing all 4
of the bolts in the fitting would be
required. If looseness is detected on any
fitting bolt, a torque inspection would
be required. If any torque inspection
reveals that the torque of any bolt in a
fitting is not between 11.3–15.8 Nm
(100–140 inch-pounds), all 4 of the bolts
in the fitting would have to be replaced
with airworthy fitting bolts before
further flight.
The Ente Nazionale per l’Aviazione
Civile (ENAC), the airworthiness
authority for Italy, notified the FAA that
an unsafe condition may exist on Agusta
Model A119 helicopters. ENAC advises
ADDRESSES:
E:\FR\FM\09MYR1.SGM
09MYR1
]]>Agencies
[Federal Register Volume 70, Number 88 (Monday, May 9, 2005)]
[Rules and Regulations]
[Pages 24305-24307]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-8952]
-----------------------------------------------------------------------
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
AGENCY: Federal Aviation Administration, DOT.
[[Page 24306]]
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
Agusta S.p.A. (Agusta) Model A109E helicopters that requires visually
inspecting each main transmission support fitting (fitting) attachment
bolt (bolt) for a fracture, a crack, or looseness, and verifying the
torque on each fitting bolt. This amendment is prompted by two
incidents of fatigue failure of the bolts that secure the transmission
rear support fittings to the helicopter. The actions specified by this
AD are intended to detect a fracture, a crack, or looseness of a
fitting bolt, and prevent fatigue failure of a fitting bolt 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 Agusta, 21017 Cascina Costa di Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111, fax 39 (0331) 229605-222595.
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: Sharon Miles, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Guidance Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5122, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for Agusta Model A109E helicopters was published in the
Federal Register on February 10, 2005 (70 FR 7061). That action
proposed to require inspecting the fitting bolts, part number (P/N)
NAS625-14, for a fracture, a crack, or looseness within 5 hours time-
in-service (TIS), and then at intervals not to exceed 10 hours TIS
until performing a torque inspection of each fitting bolt. The torque
inspection would have to be accomplished before further flight if
looseness is found, or within 25 hours TIS if looseness is not found.
If a fracture or a crack is found on any bolt in any fitting, replacing
all 4 of the bolts in a fitting with airworthy fitting bolts would be
required before further flight. If any torque inspection reveals that
the torque of any bolt in a fitting is not between 11.3-15.8 Nm (100-
140 inch-pounds), all 4 of the bolts in the fitting would have to be
replaced with airworthy fitting bolts before further flight.
The Ente Nazionale per l'Aviazione Civile (ENAC), the airworthiness
authority for Italy, notified the FAA that an unsafe condition may
exist on Agusta Model A109E helicopters. ENAC advises of the need to
check the bolts that secure the fittings to the structure by following
the manufacturer's Bollettino Tecnico No. 109EP-43, dated March 25,
2004.
Agusta has issued Bollettino Tecnico No. 109EP-43, dated March 25,
2004, which specifies a periodic visual inspection to verify the
integrity of the slippage marks, and successively checking the torque
of the bolts to exclude the possible presence of looseness and/or a
fracture or a crack. ENAC classified this bollettino tecnico as
mandatory and issued AD No. 2004-099, dated March 29, 2004, to ensure
the continued airworthiness of these helicopters in Italy.
This helicopter model is manufactured in Italy 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, ENAC has kept the FAA informed of the
situation described above. The FAA has examined the findings of ENAC,
reviewed all available information, and determined that AD action is
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. However, we have made a correction in
the service information date that was incorrectly referenced in the
preamble of the proposal; the date was incorrectly listed as March 3,
2004 but is correctly referenced as March 25, 2004 in this AD. We have
determined that this change will neither increase the economic burden
on any operator nor increase the scope of the AD.
We estimate that this AD will affect 58 helicopters of U.S.
registry. Three inspections (one initial, one repetitive, and the
torque inspection) will take approximately 4 work hours to accomplish
at an average labor rate of $65 per work hour. (The manufacturer states
that it shall recognize a warranty credit of up to $200 per helicopter
for the labor). Required parts will cost approximately $1,600 per
helicopter ($100 per fitting bolt for 16 fitting bolts). Based on these
figures, the total estimated cost impact of the AD on U.S. operators is
$115,420, assuming that no warranty credit is available and that all
affected fitting bolts are replaced.
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.
[[Page 24307]]
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:
2005-09-07 Agusta S.p.A.: Amendment 39-14075. Docket No. FAA-2005-
20292; Directorate Identifier 2004-SW-26-AD.
Applicability: Model A109E helicopters, certificated in any
category.
Compliance: Required as indicated, unless accomplished
previously.
To detect a fracture, a crack, or looseness of a main
transmission support fitting (fitting) attachment bolt (bolt), and
prevent fatigue failure of a fitting bolt and subsequent loss of
control of the helicopter, accomplish the following:
(a) Within 5 hours time-in-service (TIS), and then at intervals
not to exceed 10 hours TIS until a torque inspection of each fitting
bolt is accomplished in accordance with paragraph (b) of this AD,
inspect each fitting bolt, part number NAS625-14, for a fracture, a
crack, or looseness using a light and a mirror in accordance with
Part I, steps 1. through 4., of Agusta Bollettino Tecnico No. 109EP-
43, dated March 25, 2004 (BT).
(1) On each of the 4 fittings, if a fracture or a crack is found
in any bolt, replace all 4 bolts in the fitting with airworthy
fitting bolts before further flight.
(2) If looseness is found in any bolt in any fitting, inspect
each of the 4 bolts on each of the 4 fittings (16 bolts total) to
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range
on any bolt in a fitting, before further flight, remove all 4 bolts
in the fitting and replace them with airworthy fitting bolts in
accordance with Part II, steps 5.1 through 9. of the BT.
(b) Within 25 hours TIS, inspect each bolt in each fitting to
determine if the torque is between 11.3-15.8 Nm (100-140 inch-
pounds). If the indicated torque is not within the acceptable range
on any bolt, before further flight, remove all 4 bolts in the
fitting and replace them with airworthy fitting bolts in accordance
with Part II, steps 5.1 through 9., of the BT.
(c) Accomplishing the inspections specified in paragraphs (a)
and (b) constitute terminating actions for the requirements of this
AD.
(d) 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.
(e) Special flight permits may be issued in accordance with 14
CFR 21.197 and 21.199 to operate the helicopter to a location where
the requirements of this AD can be accomplished, provided that no
fracture or crack or looseness was found during the inspections
required by this AD.
(f) The inspections and replacements shall be done in accordance
with Agusta Bollettino Tecnico No. 109EP-43, dated March 25, 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 Agusta, 21017 Cascina Costa di Samarate
(VA) Italy, Via Giovanni Agusta 520, telephone 39 (0331) 229111, fax
39 (0331) 229605-222595. 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.
(g) This amendment becomes effective on June 13, 2005.
Note: The subject of this AD is addressed in Ente Nazionale per
l'Aviazione Civile (Italy) AD No. 2004-099, dated March 29, 2004.
Issued in Fort Worth, Texas, on April 27, 2005.
Carl F. Mittag,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-8952 Filed 5-6-05; 8:45 am]
BILLING CODE 4910-13-P
