Airworthiness Directives; Eurocopter France Model AS355E, F, F1, F2, and N Helicopters, 7059-7061 [05-2590]
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Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
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, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend 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:
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:
Agusta S.p.A.: Docket No. FAA–2005–20291;
Directorate Identifier 2004–SW–25–AD.
Applicability: Model A119 helicopters,
serial numbers 14001 through 14037, except
serial number 14036, 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 hour
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 and NAS625–
18, for a fracture, a crack, or looseness, using
a light and a mirror.
(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
VerDate jul<14>2003
16:17 Feb 09, 2005
Jkt 205001
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 4.1 through 5., of Agusta
Bollettino Tecnico No. 119–8, dated April 7,
2004 (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 4.1 through
5., 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,
crack, or looseness was found during the
inspections required by this AD.
Note: The subject of this AD is addressed
in Ente Nazionale per l’Aviazione Civile
(Italy) AD No. 2004–108, dated April 8, 2004.
Issued in Fort Worth, Texas, on February
1, 2005.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 05–2588 Filed 2–9–05; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20293; Directorate
Identifier 2004–SW–34–AD]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model AS355E, F, F1, F2, and
N Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
superseding an existing airworthiness
directive (AD) for the specified
Eurocopter France (ECF) model
helicopters. That AD currently requires
replacing certain main or combiner
gearboxes with airworthy gearboxes.
PO 00000
Frm 00008
Fmt 4702
Sfmt 4702
7059
Further investigation has shown that the
main gearbox is not affected, and this
action would require replacing a certain
combiner gearbox with a modified
airworthy gearbox. This proposal is
prompted by a report of a freewheel unit
slipping resulting in an engine
overspeed and shutdown. Also, this
proposal is prompted by the conclusion
of the investigation, which finds the
freewheel slippage is due to the surface
treatment applied to certain freewheel
rollers in the combiner gearbox. The
actions specified by the proposed AD
are intended to prevent an engine
overspeed, an engine shutdown, and
subsequent loss of control of the
helicopter.
DATES: Comments must be received by
April 11, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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 examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Uday Garadi, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0110, telephone (817) 222–5123,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send your comments to
the address listed under the caption
ADDRESSES. Include the docket number
‘‘FAA–2005–20293, Directorate
Identifier 2004–SW–34–AD’’ at the
beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
E:\FR\FM\10FEP1.SGM
10FEP1
7060
Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
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 proposed
rulemaking. 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 or signed 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.
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5227) is located at the plaza level of the
Department of Transportation NASSIF
Building in Room PL–401 at 400
Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
On January 8, 2004, we issued
Emergency AD 2004–01–51 followed by
the publication in the Federal Register
of the final rule AD, issued February 20,
2004, Amendment 39–13495, Docket
No. 2004–SW–34–AD (69 FR 9201,
February 27, 2004) for the specified
model helicopters. The AD requires
replacing a main or combiner gearbox
received from Eurocopter Marignane,
France, works with airworthy gearboxes
received from another source. This was
an interim action pending the results of
an investigation. That action was
prompted by a report of a main gearbox
free-wheel unit slipping, resulting in an
engine overspeed and shut down, which
occurred during the single-engine phase
of an acceptance flight. This condition,
if not corrected, could result in an
engine overspeed, an engine shut down,
and subsequent loss of control of the
helicopter.
Since issuing those ADs, the FAA has
reviewed ECF Alert Telex No. 63.00.21
R2, dated February 4, 2004 (AT 63.00.21
R2). The Alert Telex describes the
conclusion of the investigation that the
freewheel slippage is due to the surface
treatment applied to freewheel rollers,
pre-MOD 077212. The freewheel rollers
are located in the combiner gearbox;
therefore, the main gearbox has been
VerDate jul<14>2003
16:17 Feb 09, 2005
Jkt 205001
eliminated as the cause of this unsafe
condition. The results of the
investigation led ECF to cancel the
cleaning procedure described in Alert
Telex No. 63.00.21 R1, dated December
19, 2003, but to extend the effectivity of
their instructions to all combiner
gearboxes. Also, Alert Telex 63.00.21 R2
specifies modifying the combiner
gearboxes at an approved repair station
by replacing the freewheel rollers and
after that recording the modification on
the Equipment Log Card.
The Direction Generale De L’Aviation
Civile (DGAC), the airworthiness
authority for France, notified the FAA
that an unsafe condition may exist on
the specified model helicopters. The
DGAC advises of a combiner gearbox
freewheel slippage with resulting engine
shutdown due to overspeed, which
occurred during the single-engine phase
of an acceptance flight at the Eurocopter
works. The DGAC classified AT
63.00.21 R2 as mandatory and issued
AD F–2004–021, dated March 3, 2004,
to ensure the continued airworthiness of
these helicopters in France.
These helicopter models are
manufactured in France and are 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. We have examined the
findings of the DGAC, reviewed all
available information, and determined
that AD action is necessary for products
of these type designs that are
certificated for operation in the United
States.
This previously described unsafe
condition is likely to exist or develop on
other helicopters of the same type
design. Therefore, the proposed AD
would supersede AD 2004–01–51 to
require, before further flight, replacing
each combiner gearbox pre-MOD
077212 that has logged 10 hours or less
TIS with a combiner gearbox modified
by replacing the free-wheel rollers.
We estimate that this proposed AD
would affect 104 helicopters of U.S.
registry, and the proposed actions
would take about 1⁄2 work hour to
determine applicability and 12 work
hours to replace a gearbox at an average
labor rate of $65 per work hour.
Required parts would cost about
$97,000 per helicopter. Based on these
figures, we estimate the total cost
impact of the proposed AD on U.S.
operators to be $981,180 assuming 10
gearboxes are replaced.
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
Regulatory Findings
We have determined that this
proposed AD would not have federalism
implications under Executive Order
13132. Additionally, this proposed AD
would not have a substantial direct
effect on the States, on the relationship
between the national Government and
the States, or on the distribution of
power and responsibilities among the
various levels of government.
For the reasons discussed above, I
certify that the proposed 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 a draft economic
evaluation of the estimated costs to
comply with this proposed AD. See the
DMS to examine the draft 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the
authority delegated to me by the
Administrator, the Federal Aviation
Administration proposes to amend part
39 of the Federal Aviation Regulations
(14 CFR part 39) as follows:
E:\FR\FM\10FEP1.SGM
10FEP1
Federal Register / Vol. 70, No. 27 / Thursday, February 10, 2005 / Proposed Rules
[Amended]
2. Section 39.13 is amended by
removing Amendment 39–13495 (69 FR
9201, February 27, 2004), and by adding
a new airworthiness directive (AD), to
read as follows:
Eurocopter France: Docket No. FAA–2005–
20293; Directorate Identifier 2004–SW–
34–AD. Supersedes AD 2004–01–51,
Amendment 39–13495, Docket No.
2003–SW–56–AD.
Applicability: Model AS355E, F, F1, F2,
and N helicopters with a pre-MOD 077212
combiner gearbox that has 10 or less hours
time-in-service installed, certificated in any
category.
Compliance: Before further flight, unless
accomplished previously.
To prevent an engine overspeed, an engine
shutdown, and subsequent loss of control of
the helicopter, accomplish the following:
(a) Before further flight, replace each preMOD 077212 combiner gearbox with a
combiner gearbox modified by replacing the
freewheel rollers in accordance with MOD
077212.
Note 1: Eurocopter France Alert Telex No.
63.00.21 R2, dated February 4, 2004, pertains
to the subject AD.
(b) Performing paragraph (a) of this AD is
terminating action for the requirements of
this AD.
(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 Safety Management Group,
FAA, for information about previously
approved alternative methods of compliance.
(d) Special flight permits will not be
issued.
Note 2: The subject of this AD is addressed
in Direction Generale de L’Aviation Civile,
France, AD No. F–2004–021, dated March 3,
2004.
Issued in Fort Worth, Texas, on January 24,
2005.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 05–2590 Filed 2–9–05; 8:45 am]
16:17 Feb 09, 2005
Jkt 205001
Comments Invited
We invite you to submit any written
data, views, or arguments regarding this
proposed AD. Send or deliver your
comments to the address listed under
the caption ADDRESSES. Include the
docket number ‘‘FAA–2005–20292,
Directorate Identifier 2004–SW–26–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. We will consider all
comments received by the closing date
and may amend the proposed AD in
light of those comments.
We will post all comments we
receive, without change, to https://
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 proposed
rulemaking. 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 or signed 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.
Federal Aviation Administration
Authority: 49 U.S.C. 106(g), 40113, 44701.
VerDate jul<14>2003
[Docket No. FAA–2005–20292; Directorate
Identifier 2004–SW–26–AD]
DEPARTMENT OF TRANSPORTATION
1. The authority citation for part 39
continues to read as follows:
BILLING CODE 4910–13–P
14 CFR Part 39
FAA, Rotorcraft Directorate, Regulations
and Guidance Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5122,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
RIN 2120–AA64
PART 39—AIRWORTHINESS
DIRECTIVES
§ 39.13
7061
Airworthiness Directives; Agusta
S.p.A. Model A109E Helicopters
Federal Aviation
Administration, DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: This document proposes
adopting a new airworthiness directive
(AD) for Agusta S.p.A. (Agusta) Model
A109E helicopters. This proposal would
require 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
proposal 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 proposed 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: Comments must be received on
or before April 11, 2005.
ADDRESSES: Use one of the following
addresses to submit comments on this
proposed 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 proposed AD from
Agusta, 21017 Cascina Costa di
Samarate (VA) Italy, Via Giovanni
Agusta 520, telephone 39 (0331) 229111,
fax 39 (0331) 229605–222595.
You may examine the comments to
this proposed AD in the AD docket on
the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT:
Sharon Miles, Aviation Safety Engineer,
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
Examining the Docket
You may examine the docket that
contains the proposed AD, any
comments, and other information in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone 1–800–647–
5227) is located at the plaza level of the
Department of Transportation NASSIF
Building in Room PL–401 at 400
Seventh Street, SW., Washington, DC.
Comments will be available in the AD
docket shortly after the DMS receives
them.
Discussion
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 3, 2004.
E:\FR\FM\10FEP1.SGM
10FEP1
]]>Agencies
[Federal Register Volume 70, Number 27 (Thursday, February 10, 2005)]
[Proposed Rules]
[Pages 7059-7061]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-2590]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2005-20293; Directorate Identifier 2004-SW-34-AD]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model AS355E, F, F1,
F2, and N Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: This document proposes superseding an existing airworthiness
directive (AD) for the specified Eurocopter France (ECF) model
helicopters. That AD currently requires replacing certain main or
combiner gearboxes with airworthy gearboxes. Further investigation has
shown that the main gearbox is not affected, and this action would
require replacing a certain combiner gearbox with a modified airworthy
gearbox. This proposal is prompted by a report of a freewheel unit
slipping resulting in an engine overspeed and shutdown. Also, this
proposal is prompted by the conclusion of the investigation, which
finds the freewheel slippage is due to the surface treatment applied to
certain freewheel rollers in the combiner gearbox. The actions
specified by the proposed AD are intended to prevent an engine
overspeed, an engine shutdown, and subsequent loss of control of the
helicopter.
DATES: Comments must be received by April 11, 2005.
ADDRESSES: Use one of the following addresses to submit comments on
this proposed 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 examine the comments to this proposed AD in the AD docket
on the Internet at https://dms.dot.gov.
FOR FURTHER INFORMATION CONTACT: Uday Garadi, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Regulations and Guidance Group, Fort
Worth, Texas 76193-0110, telephone (817) 222-5123, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to submit any written data, views, or arguments
regarding this proposed AD. Send your comments to the address listed
under the caption ADDRESSES. Include the docket number ``FAA-2005-
20293, Directorate Identifier 2004-SW-34-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. We will
consider all comments received by the closing date and may amend the
proposed AD in light of those comments.
[[Page 7060]]
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 proposed rulemaking. 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 or
signed 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.
Examining the Docket
You may examine the docket that contains the proposed AD, any
comments, and other information in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone 1-800-
647-5227) is located at the plaza level of the Department of
Transportation NASSIF Building in Room PL-401 at 400 Seventh Street,
SW., Washington, DC. Comments will be available in the AD docket
shortly after the DMS receives them.
Discussion
On January 8, 2004, we issued Emergency AD 2004-01-51 followed by
the publication in the Federal Register of the final rule AD, issued
February 20, 2004, Amendment 39-13495, Docket No. 2004-SW-34-AD (69 FR
9201, February 27, 2004) for the specified model helicopters. The AD
requires replacing a main or combiner gearbox received from Eurocopter
Marignane, France, works with airworthy gearboxes received from another
source. This was an interim action pending the results of an
investigation. That action was prompted by a report of a main gearbox
free-wheel unit slipping, resulting in an engine overspeed and shut
down, which occurred during the single-engine phase of an acceptance
flight. This condition, if not corrected, could result in an engine
overspeed, an engine shut down, and subsequent loss of control of the
helicopter.
Since issuing those ADs, the FAA has reviewed ECF Alert Telex No.
63.00.21 R2, dated February 4, 2004 (AT 63.00.21 R2). The Alert Telex
describes the conclusion of the investigation that the freewheel
slippage is due to the surface treatment applied to freewheel rollers,
pre-MOD 077212. The freewheel rollers are located in the combiner
gearbox; therefore, the main gearbox has been eliminated as the cause
of this unsafe condition. The results of the investigation led ECF to
cancel the cleaning procedure described in Alert Telex No. 63.00.21 R1,
dated December 19, 2003, but to extend the effectivity of their
instructions to all combiner gearboxes. Also, Alert Telex 63.00.21 R2
specifies modifying the combiner gearboxes at an approved repair
station by replacing the freewheel rollers and after that recording the
modification on the Equipment Log Card.
The Direction Generale De L'Aviation Civile (DGAC), the
airworthiness authority for France, notified the FAA that an unsafe
condition may exist on the specified model helicopters. The DGAC
advises of a combiner gearbox freewheel slippage with resulting engine
shutdown due to overspeed, which occurred during the single-engine
phase of an acceptance flight at the Eurocopter works. The DGAC
classified AT 63.00.21 R2 as mandatory and issued AD F-2004-021, dated
March 3, 2004, to ensure the continued airworthiness of these
helicopters in France.
These helicopter models are manufactured in France and are 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. We have examined the findings of the
DGAC, reviewed all available information, and determined that AD action
is necessary for products of these type designs that are certificated
for operation in the United States.
This previously described unsafe condition is likely to exist or
develop on other helicopters of the same type design. Therefore, the
proposed AD would supersede AD 2004-01-51 to require, before further
flight, replacing each combiner gearbox pre-MOD 077212 that has logged
10 hours or less TIS with a combiner gearbox modified by replacing the
free-wheel rollers.
We estimate that this proposed AD would affect 104 helicopters of
U.S. registry, and the proposed actions would take about \1/2\ work
hour to determine applicability and 12 work hours to replace a gearbox
at an average labor rate of $65 per work hour. Required parts would
cost about $97,000 per helicopter. Based on these figures, we estimate
the total cost impact of the proposed AD on U.S. operators to be
$981,180 assuming 10 gearboxes are replaced.
Regulatory Findings
We have determined that this proposed AD would not have federalism
implications under Executive Order 13132. Additionally, this proposed
AD would not have a substantial direct effect on the States, on the
relationship between the national Government and the States, or on the
distribution of power and responsibilities among the various levels of
government.
For the reasons discussed above, I certify that the proposed
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 a draft economic evaluation of the estimated costs to
comply with this proposed AD. See the DMS to examine the draft 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, Safety.
The Proposed Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration proposes to amend
part 39 of the Federal Aviation Regulations (14 CFR part 39) as
follows:
[[Page 7061]]
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by removing Amendment 39-13495 (69 FR
9201, February 27, 2004), and by adding a new airworthiness directive
(AD), to read as follows:
Eurocopter France: Docket No. FAA-2005-20293; Directorate Identifier
2004-SW-34-AD. Supersedes AD 2004-01-51, Amendment 39-13495, Docket
No. 2003-SW-56-AD.
Applicability: Model AS355E, F, F1, F2, and N helicopters with a
pre-MOD 077212 combiner gearbox that has 10 or less hours time-in-
service installed, certificated in any category.
Compliance: Before further flight, unless accomplished
previously.
To prevent an engine overspeed, an engine shutdown, and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Before further flight, replace each pre-MOD 077212 combiner
gearbox with a combiner gearbox modified by replacing the freewheel
rollers in accordance with MOD 077212.
Note 1: Eurocopter France Alert Telex No. 63.00.21 R2, dated
February 4, 2004, pertains to the subject AD.
(b) Performing paragraph (a) of this AD is terminating action
for the requirements of this AD.
(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 Safety Management Group, FAA, for information about
previously approved alternative methods of compliance.
(d) Special flight permits will not be issued.
Note 2: The subject of this AD is addressed in Direction
Generale de L'Aviation Civile, France, AD No. F-2004-021, dated
March 3, 2004.
Issued in Fort Worth, Texas, on January 24, 2005.
Mark R. Schilling,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 05-2590 Filed 2-9-05; 8:45 am]
BILLING CODE 4910-13-P
