Airworthiness Directives; Eurocopter France Model EC 155B and EC155B1 Helicopters, 11004-11006 [E9-4953]
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11004
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
on any operator nor increase the scope
of the AD.
The FAA estimates that this AD will
affect 259 2101 I/O Approach Plus
systems installed on aircraft of U.S.
registry, and the required actions will
take approximately 2 work hours per
aircraft to accomplish at an average
labor rate of $80 per work hour.
Required parts will cost approximately
$300 per aircraft. Based on these figures,
we estimate the total cost impact of the
AD on U.S. operators to be $72,520,
assuming one 2101 I/O Approach Plus
system is installed on each aircraft, the
manufacturer will provide all $300 in
parts at no cost, and the only costs for
these parts will be $120 for shipping
costs for each unit.
Regulatory Findings
We have determined that this AD will
not have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national Government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in subtitle VII,
part A, subpart III, section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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:
■
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Special
Certification Office, FAA, ATTN: Sung-Hui
Cavazos, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Special Certification
Office, Fort Worth, Texas 76193–0190,
telephone (817) 222–5142, fax (817) 222–
5785, for information about previously
approved alternative methods of compliance.
(d) Special flight permits may be issued in
accordance with 14 CFR 21.197 and 21.199
to operate the aircraft to a location where the
requirements of this AD can be accomplished
provided that the aircraft is operated under
VFR only.
(e) This amendment becomes effective on
April 20, 2009.
Issued in Fort Worth, Texas, on February
19, 2009.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E9–4942 Filed 3–13–09; 8:45 am]
BILLING CODE 4910–13–P
2009–05–08 Trimble or Freeflight Systems:
Amendment 39–15832. Docket No.
FAA–2007–28689; Directorate Identifier
2006–SW–17–AD.
DEPARTMENT OF TRANSPORTATION
Applicability
All aircraft with a Trimble or FreeFlight
Systems 2101 I/O Approach Plus global
positioning system (GPS) navigation system
(2101 I/O Approach Plus system), part
number 81440–xx–241E, 81440–xx–241F, or
81440–xx–241G (xx indicates either the
numbers 02, 03, or 12), with software
revision –241E, –241F, or 241G, installed,
certificated in any category.
14 CFR Part 39
Compliance
Required within 180 days after the
effective date of this AD for aircraft approved
for instrument flight rule (IFR) flight, or 270
days after the effective date of this AD for
aircraft approved for visual flight rule (VFR)
flight, unless accomplished previously.
To prevent a pilot from making an unsafe
decision based on erroneous information
provided by the 2101 I/O Approach Plus
system, which could result in loss of control
of the aircraft, accomplish the following:
(a) Upgrade the system software of any
Trimble or FreeFlight Systems 2101 I/O
Approach Plus GPS navigation system, part
number (P/N) 81440–xx–241E, 81440–XX–
241F, or 81440–xx–241G (xx indicates the
numbers 02, 03, or 12), that currently has
software revision –241E, –241F, or –241G, to
system software revision, P/N 81440–XX–
241J.
Note: Sections II and III of FreeFlight
Systems Service Bulletin No. SB 81440–XX–
00–19, dated December 12, 2006, pertains to
the requirements of this AD.
(b) Upgrading the Trimble or FreeFlight
Systems 2101 I/O Approach Plus GPS
Navigation System’s software, to system
software revision, P/N 81440–xx–241J, is
considered a terminating action for the
requirements of this AD.
(c) To request a different method of
compliance or a different compliance time
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
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Federal Aviation Administration
[Docket No. FAA–2009–0195; Directorate
Identifier 2007–SW–34–AD; Amendment 39–
15837; AD 2009–06–01]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model EC 155B and EC155B1
Helicopters
SUMMARY: We are adopting a new
airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model
EC 155B and EC155B1 helicopters. This
AD results from mandatory continuing
airworthiness information (MCAI)
issued by the European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Community. The MCAI states
that ‘‘the Airworthiness Directive (AD)
is prompted by the discovery of a short
circuit evidence in hoist connector ‘‘24
Delta’’ even though the hoist was
removed from the rotorcraft. The short
circuit generated sufficient heat to ignite
the paint on the cooler support cowling
near the hoist cut-off connector ‘‘24
Delta.’’ This condition, if not corrected,
could result in a fire in this area which
could propagate to surrounding zones.’’
This AD requires actions that are
intended to address this unsafe
condition.
E:\FR\FM\16MRR1.SGM
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Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
DATES: This AD becomes effective on
March 31, 2009.
The incorporation by reference of
certain publications is approved by the
Director of the Federal Register as of
March 31, 2009.
We must receive comments on this
AD by May 15, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting your
comments electronically.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590, 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 American
Eurocopter Corporation, 2701 Forum
Drive, Grand Prairie, TX 75053–4005,
telephone (972) 641–3460, fax (972)
641–3527, or at https://
www.eurocopter.com.
Examining the Docket: You may
examine the AD docket on the Internet
at https://www.regulations.gov or in
person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this AD, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
stated in the ADDRESSES section of this
AD. Comments will be available in the
AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
George Schwab, Aviation Safety
Engineer, FAA, Rotorcraft Directorate,
Regulations and Policy Group, Fort
Worth, Texas 76193–0111, telephone
(817) 222–5114, fax (817) 222–5961.
SUPPLEMENTARY INFORMATION:
Discussion
EASA, which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Emergency AD No. 2007–0159–E, dated
June 6, 2007, to correct an unsafe
condition for Eurocopter Model EC
155B and EC155B1 helicopters.
This AD requires actions that are
intended to detect a short circuit in a
hoist connector and prevent a fire in the
aircraft. You may obtain further
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
information by examining the MCAI and
any related service information in the
AD docket.
Related Service Information
Eurocopter has issued Emergency
Alert Service Bulletin No. 25A085,
dated June 1, 2007. The actions
described in the MCAI are intended to
correct the same unsafe condition as
that identified in the service
information.
FAA’s Evaluation and Unsafe Condition
Determination
This product has been approved by
the aviation authority of France, and is
approved for operation in the United
States. Pursuant to our bilateral
agreement with France, their Technical
Agent has notified us of the unsafe
condition described in the MCAI. We
are issuing this AD because we
evaluated all information provided by
EASA on behalf of France and
determined the unsafe condition exists
and is likely to exist or develop on other
helicopters of this same type design.
Differences Between This AD and the
MCAI
We have used a compliance time of 1
month rather than 3 months because of
the serious consequences of an
undetected short circuit and potential
aircraft fire.
Costs of Compliance
We estimate that this AD will affect 1
helicopter of U.S. registry. We also
estimate that it will take about 3 workhours to comply with the basic
requirements of this AD. The average
labor rate is $80 per work-hour.
Required parts will cost about $500 per
helicopter. Based on these figures, we
estimate the cost of this AD on U.S.
operators will be $740.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. We find that the risk to the flying
public justifies waiving notice and
comment prior to adoption of this rule
because a wiring short circuit near the
hoist cut-off connector caused the paint
on the cooler support cowling to catch
on fire. Therefore, we have determined
that notice and opportunity for public
comment before issuing this AD are
impracticable and that good cause exists
for making this amendment effective in
fewer than 30 days.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
PO 00000
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11005
we did not precede it by notice and
opportunity for public comment.
However, we invite you to send us any
written data, views, or arguments
concerning this AD. Send your
comments to an address listed under the
ADDRESSES section of this AD. Include
‘‘Docket No. FAA–2009–0195;
Directorate Identifier 2007–SW–34–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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
product(s) identified in this rulemaking
action.
Regulatory Findings
We 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.
Therefore, I certify this AD:
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
E:\FR\FM\16MRR1.SGM
16MRR1
11006
Federal Register / Vol. 74, No. 49 / Monday, March 16, 2009 / Rules and Regulations
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 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. The FAA amends § 39.13 by adding
the following new AD:
■
2009–06–01 Eurocopter France:
Amendment 39–15837. Docket No.
FAA–2009–0195; Directorate Identifier
2007–SW–34–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective on March 31, 2009.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model EC 155B and
EC155B1 helicopters with a serial number (S/
N) less than 6763, and with optional
equipment OP 45C07 (OP 45C07), installed,
certificated in any category. OP 45C07 is the
helicopter provision kit (electrical and
structural mount modifications) used to
support installation and operation of a hoist.
(1) To determine if your helicopter has OP
45C07 installed, review aircraft
documentation, which should state if OP
45C07 equipment is installed, or
(2) Perform a physical inspection for the
existence of the 24 Delta hoist electrical
female connector (MIL–C–5015 type
connector), which is installed, just forward of
the right-hand engine cowling and just below
the right engine inlet. Figures 1 and 6 of
Eurocopter Emergency Alert Service Bulletin
No. 25A085, dated June 1, 2007 (ASB), depict
where the connector is located.
Reason
(d) The mandatory continuing
airworthiness information (MCAI) states that
‘‘the Airworthiness Directive (AD) is
prompted by the discovery of a short circuit
evidence in hoist connector ‘‘24 Delta’’ even
though the hoist was removed from the
rotorcraft. The short circuit generated
sufficient heat to ignite the paint on the
cooler support cowling near the hoist cut-off
connector ‘‘24 Delta.’’ This condition, if not
corrected, could result in a fire in this area
VerDate Nov<24>2008
13:57 Mar 13, 2009
Jkt 217001
which could propagate to surrounding
zones.’’ This AD requires actions that are
intended to address this unsafe condition.
material at NARA, call (202) 741–6030, or go
to: https://www.archives.gov/federal-register/
cfr/ibr-locations.html.
Actions and Compliance
(e) Within 7 days, unless already
accomplished, do the following:
(1) Determine the orientation of the fixed
connector ‘‘24 Delta’’ and if the large contacts
are not oriented ‘‘aft,’’ re-orient the fixed
connector so that they are facing ‘‘aft’’ by
following the Accomplishment Instructions,
paragraphs 2.B.1. and 2.B.2.a., of the ASB.
(2) Immediately after each hoist removal
until the electrical bonding braid for the
fixed hoist connector ‘‘24 Delta’’ is installed,
disconnect the hoist power cable by
following the Accomplishment Instructions,
paragraph 2.B.2.b., of the ASB.
(f) Within 1 month, install an electrical
bonding braid for connector ‘‘24 Delta’’ by
following the Accomplishment Instructions,
paragraph 2.B.2.c., of the ASB.
(g) Factory-implemented modification
MOD 0745C82 is acceptable terminating
action for the requirements of this AD.
Issued in Fort Worth, Texas on February
19, 2009.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. E9–4953 Filed 3–13–09; 8:45 am]
Differences Between This AD and the MCAI
(h) We have used a compliance time of 1
month rather than 3 months because of the
serious consequences of an undetected short
circuit and potential aircraft fire.
Other Information
(i) Alternative Methods of Compliance
(AMOCs): The Manager, Safety Management
Group, FAA, ATTN: George Schwab,
Aerospace Engineer, Rotorcraft Directorate,
Regulations and Policy Group, Fort Worth,
Texas 76193–0111, telephone (817) 222–
5114, fax (817) 222–5961, has the authority
to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Related Information
(j) Mandatory Continuing Airworthiness
Information (MCAI) Emergency
Airworthiness Directive No. 2007–0159–E,
dated June 6, 2007, contains related
information.
Air Transport Association of America (ATA)
Tracking Code
(k) ATA Code 25: 2500–Hoist box; 1420–
Hoist cut-off connector.
Material Incorporated by Reference
(l) You must use the specified portions of
Eurocopter Emergency Alert Service Bulletin
No. 25A085, dated June 1, 2007, to do the
actions required.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact American Eurocopter
Corporation, 2701 Forum Drive, Grand
Prairie, TX 75053–4005, telephone (972)
641–3460, fax (972) 641–3527, or at https://
www.eurocopter.com.
(3) You may review copies at the FAA,
Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort
Worth, Texas, or at the National Archives
and Records Administration (NARA). For
information on the availability of this
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BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2009–0215; Directorate
Identifier 2007–NM–278–AD; Amendment
39–15850; AD 2009–06–13]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A321–131 Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
Airbus Model A321–131 airplanes. This
AD requires repetitive ultrasonic
inspections to detect cracks in the wing
inner rear spars at the attachment holes
of the Main Landing Gear (MLG)
forward pintle fitting, the actuator
cylinder anchorage fitting, and rib 5
fitting; and repair of the sealant or repair
of any crack. This AD results from a
finding that certain A321–131 airplanes
may not reach the design life goal due
to differences in thickness of the inner
rear spars and that fatigue cracks may
develop on inner rear spars starting
from the fastener holes for the
attachment of gear rib 5, the forward
pintle fitting, and the actuating cylinder
anchorage on these airplanes. We are
issuing this AD to detect and correct
such fatigue cracks, which could result
in reduced structural integrity of the
airplane.
DATES: This AD becomes effective
March 31, 2009.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 31, 2009.
We must receive comments on this
AD by April 15, 2009.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
E:\FR\FM\16MRR1.SGM
16MRR1
]]>Agencies
[Federal Register Volume 74, Number 49 (Monday, March 16, 2009)]
[Rules and Regulations]
[Pages 11004-11006]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-4953]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2009-0195; Directorate Identifier 2007-SW-34-AD;
Amendment 39-15837; AD 2009-06-01]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC 155B and
EC155B1 Helicopters
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model EC 155B and EC155B1 helicopters.
This AD results from mandatory continuing airworthiness information
(MCAI) issued by the European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Community.
The MCAI states that ``the Airworthiness Directive (AD) is prompted by
the discovery of a short circuit evidence in hoist connector ``24
Delta'' even though the hoist was removed from the rotorcraft. The
short circuit generated sufficient heat to ignite the paint on the
cooler support cowling near the hoist cut-off connector ``24 Delta.''
This condition, if not corrected, could result in a fire in this area
which could propagate to surrounding zones.'' This AD requires actions
that are intended to address this unsafe condition.
[[Page 11005]]
DATES: This AD becomes effective on March 31, 2009.
The incorporation by reference of certain publications is approved
by the Director of the Federal Register as of March 31, 2009.
We must receive comments on this AD by May 15, 2009.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov. Follow the instructions for submitting your
comments electronically.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, 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
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX
75053-4005, telephone (972) 641-3460, fax (972) 641-3527, or at https://
www.eurocopter.com.
Examining the Docket: You may examine the AD docket on the Internet
at https://www.regulations.gov or in person at the Docket Operations
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations office (telephone (800) 647-5527) is stated in the
ADDRESSES section of this AD. Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: George Schwab, Aviation Safety
Engineer, FAA, Rotorcraft Directorate, Regulations and Policy Group,
Fort Worth, Texas 76193-0111, telephone (817) 222-5114, fax (817) 222-
5961.
SUPPLEMENTARY INFORMATION:
Discussion
EASA, which is the Technical Agent for the Member States of the
European Community, has issued EASA Emergency AD No. 2007-0159-E, dated
June 6, 2007, to correct an unsafe condition for Eurocopter Model EC
155B and EC155B1 helicopters.
This AD requires actions that are intended to detect a short
circuit in a hoist connector and prevent a fire in the aircraft. You
may obtain further information by examining the MCAI and any related
service information in the AD docket.
Related Service Information
Eurocopter has issued Emergency Alert Service Bulletin No. 25A085,
dated June 1, 2007. The actions described in the MCAI are intended to
correct the same unsafe condition as that identified in the service
information.
FAA's Evaluation and Unsafe Condition Determination
This product has been approved by the aviation authority of France,
and is approved for operation in the United States. Pursuant to our
bilateral agreement with France, their Technical Agent has notified us
of the unsafe condition described in the MCAI. We are issuing this AD
because we evaluated all information provided by EASA on behalf of
France and determined the unsafe condition exists and is likely to
exist or develop on other helicopters of this same type design.
Differences Between This AD and the MCAI
We have used a compliance time of 1 month rather than 3 months
because of the serious consequences of an undetected short circuit and
potential aircraft fire.
Costs of Compliance
We estimate that this AD will affect 1 helicopter of U.S. registry.
We also estimate that it will take about 3 work-hours to comply with
the basic requirements of this AD. The average labor rate is $80 per
work-hour. Required parts will cost about $500 per helicopter. Based on
these figures, we estimate the cost of this AD on U.S. operators will
be $740.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. We find that the risk to the flying public justifies waiving
notice and comment prior to adoption of this rule because a wiring
short circuit near the hoist cut-off connector caused the paint on the
cooler support cowling to catch on fire. Therefore, we have determined
that notice and opportunity for public comment before issuing this AD
are impracticable and that good cause exists for making this amendment
effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. However, we invite you to send us any written data, views, or
arguments concerning this AD. Send your comments to an address listed
under the ADDRESSES section of this AD. Include ``Docket No. FAA-2009-
0195; Directorate Identifier 2007-SW-34-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this AD. We will
consider all comments received by the closing date and may amend this
AD because of those comments.
We will post all comments we receive, without change, to https://
www.regulations.gov including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
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 product(s) identified in this
rulemaking action.
Regulatory Findings
We 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.
Therefore, I certify this AD:
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
[[Page 11006]]
under the criteria of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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. The FAA amends Sec. 39.13 by adding the following new AD:
2009-06-01 Eurocopter France: Amendment 39-15837. Docket No. FAA-
2009-0195; Directorate Identifier 2007-SW-34-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective on March
31, 2009.
Other Affected ADs
(b) None.
Applicability
(c) This AD applies to Model EC 155B and EC155B1 helicopters
with a serial number (S/N) less than 6763, and with optional
equipment OP 45C07 (OP 45C07), installed, certificated in any
category. OP 45C07 is the helicopter provision kit (electrical and
structural mount modifications) used to support installation and
operation of a hoist.
(1) To determine if your helicopter has OP 45C07 installed,
review aircraft documentation, which should state if OP 45C07
equipment is installed, or
(2) Perform a physical inspection for the existence of the 24
Delta hoist electrical female connector (MIL-C-5015 type connector),
which is installed, just forward of the right-hand engine cowling
and just below the right engine inlet. Figures 1 and 6 of Eurocopter
Emergency Alert Service Bulletin No. 25A085, dated June 1, 2007
(ASB), depict where the connector is located.
Reason
(d) The mandatory continuing airworthiness information (MCAI)
states that ``the Airworthiness Directive (AD) is prompted by the
discovery of a short circuit evidence in hoist connector ``24
Delta'' even though the hoist was removed from the rotorcraft. The
short circuit generated sufficient heat to ignite the paint on the
cooler support cowling near the hoist cut-off connector ``24
Delta.'' This condition, if not corrected, could result in a fire in
this area which could propagate to surrounding zones.'' This AD
requires actions that are intended to address this unsafe condition.
Actions and Compliance
(e) Within 7 days, unless already accomplished, do the
following:
(1) Determine the orientation of the fixed connector ``24
Delta'' and if the large contacts are not oriented ``aft,'' re-
orient the fixed connector so that they are facing ``aft'' by
following the Accomplishment Instructions, paragraphs 2.B.1. and
2.B.2.a., of the ASB.
(2) Immediately after each hoist removal until the electrical
bonding braid for the fixed hoist connector ``24 Delta'' is
installed, disconnect the hoist power cable by following the
Accomplishment Instructions, paragraph 2.B.2.b., of the ASB.
(f) Within 1 month, install an electrical bonding braid for
connector ``24 Delta'' by following the Accomplishment Instructions,
paragraph 2.B.2.c., of the ASB.
(g) Factory-implemented modification MOD 0745C82 is acceptable
terminating action for the requirements of this AD.
Differences Between This AD and the MCAI
(h) We have used a compliance time of 1 month rather than 3
months because of the serious consequences of an undetected short
circuit and potential aircraft fire.
Other Information
(i) Alternative Methods of Compliance (AMOCs): The Manager,
Safety Management Group, FAA, ATTN: George Schwab, Aerospace
Engineer, Rotorcraft Directorate, Regulations and Policy Group, Fort
Worth, Texas 76193-0111, telephone (817) 222-5114, fax (817) 222-
5961, has the authority to approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
Related Information
(j) Mandatory Continuing Airworthiness Information (MCAI)
Emergency Airworthiness Directive No. 2007-0159-E, dated June 6,
2007, contains related information.
Air Transport Association of America (ATA) Tracking Code
(k) ATA Code 25: 2500-Hoist box; 1420-Hoist cut-off connector.
Material Incorporated by Reference
(l) You must use the specified portions of Eurocopter Emergency
Alert Service Bulletin No. 25A085, dated June 1, 2007, to do the
actions required.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact
American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie, TX
75053-4005, telephone (972) 641-3460, fax (972) 641-3527, or at
https://www.eurocopter.com.
(3) You may review copies at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas, or at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/
federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas on February 19, 2009.
Scott A. Horn,
Acting Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. E9-4953 Filed 3-13-09; 8:45 am]
BILLING CODE 4910-13-P
