Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft Engines, 64566-64568 [E8-25887]
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64566
Proposed Rules
Federal Register
Vol. 73, No. 211
Thursday, October 30, 2008
This section of the FEDERAL REGISTER
contains notices to the public of the proposed
issuance of rules and regulations. The
purpose of these notices is to give interested
persons an opportunity to participate in the
rule making prior to the adoption of the final
rules.
New Jersey Avenue, SE., West Building
Ground Floor, Room W12–140,
Washington, DC 20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
DEPARTMENT OF TRANSPORTATION
Examining the AD Docket
Federal Aviation Administration
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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is the
same as the Mail address provided in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine
& Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781)
238–7199.
SUPPLEMENTARY INFORMATION:
14 CFR Part 39
[Docket No. FAA–2008–0935; Directorate
Identifier 2008–NE–28–AD]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Arriel 2B and 2B1 Turboshaft Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
issued by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
pwalker on PROD1PC71 with PROPOSALS
Several cases of loss of internal
components from the Hydro Mechanical Unit
(HMU) low fuel pressure switch HydraElectric part number (P/N) 9 550 17 956 0
into the fuel system, have been reported on
Arriel 2 engines.
The loss of internal components from the
low fuel pressure switch into the fuel system
may lead to a rupture of the HP–LP pumps
drive shaft shear pin, and thus to a possible
uncommanded in-flight shutdown (IFSD). On
a single-engine helicopter, an uncommanded
IFSD results in an emergency autorotation
landing and in certain conditions may lead
to an accident.
We are proposing this AD to prevent
forced autorotation landing, or an
accident.
DATES: We must receive comments on
this proposed AD by December 1, 2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov and follow
the instructions for sending your
comments electronically.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 1200
VerDate Aug<31>2005
16:41 Oct 29, 2008
Jkt 217001
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–0935; Directorate Identifier
2008–NE–28–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on 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 with FAA
personnel concerning this proposed AD.
Using the search function of the Web
site, anyone can find and read the
comments in any of our dockets,
including, if provided, the name of the
individual who sent the comment (or
PO 00000
Frm 00001
Fmt 4702
Sfmt 4702
signed the comment on behalf of an
association, business, labor union, etc.).
You may review the DOT’s complete
Privacy Act Statement in the Federal
Register published on April 11, 2000
(65 FR 19477–78).
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2008–
0077, dated April 28, 2008 (and
corrected May 6, 2008) (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Several cases of loss of internal
components from the HMU low fuel pressure
switch Hydra-Electric P/N 9 550 17 956 0
into the fuel system, have been reported on
Arriel 2 engines.
The loss of internal components from the
low fuel pressure switch into the fuel system
may lead to a rupture of the HP–LP pumps
drive shaft shear pin, and thus to a possible
uncommanded IFSD. On a single-engine
helicopter, an uncommanded IFSD results in
an emergency autorotation landing and in
certain conditions may lead to an accident.
The evaluation of this condition prompts
the issuance of this AD, which requires the
following actions for the HMUs installed on
Arriel 2 single-engine applications in order
to:
• Verify the part number of the low fuel
pressure switch;
• If installed, replace the Hydra-Electric
low fuel pressure switch P/N 9 550 17 956
0 (with either of two different P/N low fuel
pressure switches, referenced in the MCAI).
• In case a Hydra-Electric switch P/N 9
550 17 956 0 is installed or may have been
installed on the HMU, verify that no parts are
found in the chamber of the HMU body
where the base of the low fuel pressure
switch has been installed.
You may obtain further information
by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca has issued Mandatory
Service Bulletin No. 292 73 2826, dated
March 13, 2008. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of France, and is
approved for operation in the United
States. Pursuant to our bilateral
E:\FR\FM\30OCP1.SGM
30OCP1
Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 / Proposed Rules
agreement with France, they have
notified us of the unsafe condition
described in the EASA AD and service
information referenced above. We are
proposing this AD because we evaluated
all information provided by EASA and
determined the unsafe condition exists
and is likely to exist or develop on other
products of the same type design. This
proposed AD would require a one-time
inspection for affected low fuel pressure
switches, for evidence of an affected
switch previously installed and
inspection for switch parts missing or
fallen into the HMU well.
Difference Between This Proposed AD
and the MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. We
have proposed to not reference the P/Ns
of the serviceable low pressure switch
as the MCAI does, in order to follow
FAA policies. This difference is
described in a separate paragraph of the
proposed AD. This requirement, if
ultimately adopted, will take
precedence over the actions in the
MCAI.
pwalker on PROD1PC71 with PROPOSALS
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 414 products installed on
helicopters of U.S. registry. We also
estimate that it would take about 1
work-hour per product to comply with
this proposed AD. The average labor
rate is $80 per work-hour. Required
parts would cost about $256 per
product. Based on these figures, we
estimate the cost of the proposed AD on
U.S. operators to be $139,104. Our cost
estimate is exclusive of possible
warranty coverage.
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 Aug<31>2005
16:41 Oct 29, 2008
Jkt 217001
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. 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 this 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 regulatory evaluation
of the estimated costs to comply with
this proposed 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.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 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:
Turbomeca: Docket No. FAA–2008–0935;
Directorate Identifier 2008–NE–28–AD.
Comments Due Date
(a) We must receive comments by
December 1, 2008.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Turbomeca Arriel 2B
and 2B1 turboshaft engines. These engines
are installed on, but not limited to,
Eurocopter France AS350B3 and EC130 B4
helicopters.
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Fmt 4702
Sfmt 4702
64567
Reason
(d) European Aviation Safety Agency
(EASA) AD No. 2008–0077, dated March 13,
2006 (and corrected May 6, 2008), states:
Several cases of loss of internal
components from the Hydro Mechanical Unit
(HMU) low fuel pressure switch HydraElectric part number (P/N) 9 550 17 956 0
into the fuel system, have been reported on
Arriel 2 engines.
The loss of internal components from the
low fuel pressure switch into the fuel system
may lead to a rupture of the HP–LP pumps
drive shaft shear pin, and thus to a possible
uncommanded in-flight shutdown (IFSD). On
a single-engine helicopter, an uncommanded
IFSD results in an emergency autorotation
landing and in certain conditions may lead
to an accident.
We are issuing this AD to prevent forced
autorotation landing, or an accident.
Actions and Compliance
(e) Unless already done, do the following
actions.
(1) No later than September 30, 2009,
perform a one-time inspection of the HMU,
using paragraph 2 of Turbomeca Mandatory
Service Bulletin (MSB) No. 292 73 2826,
dated March 13, 2008, to identify the low
fuel pressure switch installed on the adjusted
HMU.
(2) If a Hydra-Electric low fuel pressure
switch, part number (P/N) 9 550 17 956 0 is
installed:
(i) Inspect the low fuel pressure switch and
chamber of the HMU body.
(ii) If any parts from the low fuel pressure
switch are missing or found in the HMU
chamber, replace the HMU with a new or
overhauled HMU equipped with a
serviceable low fuel pressure switch.
(iii) If not, replace only the low fuel
pressure switch with a serviceable low fuel
pressure switch.
(3) If a low fuel pressure switch other than
a Hydra-Electric low fuel pressure switch, P/
N 9 550 17 956 0 is installed, and that is the
only type of low fuel pressure switch that has
been installed since new, repair, or overhaul,
no further action is required.
(4) If a Hydra-Electric switch, P/N 9 550 17
956 0, has been or may have been installed
previously, and the conditions of paragraph
(e)(3) of this AD are not met:
(i) Inspect the chamber of the HMU body.
(ii) If any parts are found in the HMU
chamber, replace the HMU with a new or
overhauled HMU equipped with a
serviceable low fuel pressure switch.
FAA AD Difference
(f) This AD differs from the Mandatory
Continuing Airworthiness Information
(MCAI) and/or service information, by not
referencing the P/Ns of the serviceable low
fuel pressure switch, and, defining a
serviceable low fuel pressure switch, for the
purpose of this AD.
Definition
(g) For the purpose of this AD, a
serviceable low fuel pressure switch is a
switch that has a P/N other than P/N 9 550
17 956 0.
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64568
Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 / Proposed Rules
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, Engine Certification
Office, FAA, has the authority to approve
AMOCs for this AD, if requested, using the
procedures found in 14 CFR 39.19.
Related Information
(i) Refer to MCAI EASA AD 2008–0077,
dated April 28, 2008 (and corrected May 6,
2008), for related information.
(j) Contact James Lawrence, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: james.lawrence@faa.gov;
telephone (781) 238–7176; fax (781) 238–
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on
October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E8–25887 Filed 10–29–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1118; Directorate
Identifier 2007–NM–318–AD]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–600, –700, –700C, –800, and
–900 Series Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
pwalker on PROD1PC71 with PROPOSALS
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
directive (AD) that applies to all Boeing
Model 737–600, –700, –700C, –800, and
–900 series airplanes. The existing AD
currently requires reviewing the
airplane maintenance records to
determine whether an engine has been
removed from the airplane since the
airplane was manufactured. For
airplanes on which an engine has been
removed, the existing AD also requires
an inspection of the aft engine mount to
determine if the center link assembly is
correctly installed, and follow-on
actions if necessary. This proposed AD
would require the same actions for
airplanes on which the engine has not
been previously removed. This
proposed AD results from reports
indicating that operators found that the
center link assembly for the aft engine
mount was reversed on several airplanes
that had not had an engine removed
VerDate Aug<31>2005
16:41 Oct 29, 2008
Jkt 217001
since delivery. We are proposing this
AD to prevent increased structural loads
on the aft engine mount, which could
result in failure of the aft engine mount
and consequent separation of the engine
from the airplane.
DATES: We must receive comments on
this proposed AD by December 15,
2008.
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.
• 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.
For service information identified in
this AD, contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Allen Rauschendorfer, Aerospace
Engineer, Airframe Branch, ANM–120S,
FAA, Seattle Aircraft Certification
Office, 1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6432; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–1118; Directorate Identifier
2007–NM–318–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
PO 00000
Frm 00003
Fmt 4702
Sfmt 4702
consider all comments received by the
closing date and may amend this
proposed 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 proposed AD.
Discussion
On January 21, 2003, we issued AD
2003–03–01, amendment 39–13025 (68
FR 4367, January 29, 2003), for all
Boeing Model 737–600, –700, –700C,
–800, and –900 series airplanes. That
AD requires reviewing the airplane
maintenance records to determine
whether an engine has been removed
from the airplane since the airplane was
manufactured. For airplanes on which
an engine has been removed, that AD
requires an inspection of the aft engine
mount to determine if the center link
assembly is correctly installed, and
follow-on actions if necessary. That AD
resulted from reports indicating that
operators found that the center link
assembly for the aft engine mount was
reversed on several airplanes. We issued
that AD to prevent increased structural
loads on the aft engine mount, which
could result in failure of the aft engine
mount and consequent separation of the
engine from the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 2003–03–01, the
manufacturer informed us that it is
possible that some center links were
incorrectly installed in an aft engine
mount before the airplane was
delivered. In AD 2003–03–01 inspection
of the aft engine mounts was required
only for airplanes that had an engine
change after the airplane was delivered
to the operator. The inspection is now
necessary for all airplanes, line numbers
1 through 1277 inclusive.
Relevant Service Information
We have reviewed Boeing Alert
Service Bulletin 737–71A1462, Revision
3, dated May 20, 2004. The procedures
in Revision 3 of the service bulletin are
essentially the same as those in Boeing
Alert Service Bulletin 737–71A1462,
Revision 1, dated November 7, 2002. We
referred to Revision 1 of the service
bulletin as the appropriate source of
service information for accomplishing
the actions required by AD 2003–03–01.
However, Revision 3 of the service
bulletin also specifies inspecting to
determine if the center link assembly is
installed correctly on any installed
engine that has not been removed from
E:\FR\FM\30OCP1.SGM
30OCP1
Agencies
[Federal Register Volume 73, Number 211 (Thursday, October 30, 2008)]
[Proposed Rules]
[Pages 64566-64568]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25887]
========================================================================
Proposed Rules
Federal Register
________________________________________________________________________
This section of the FEDERAL REGISTER contains notices to the public of
the proposed issuance of rules and regulations. The purpose of these
notices is to give interested persons an opportunity to participate in
the rule making prior to the adoption of the final rules.
========================================================================
Federal Register / Vol. 73, No. 211 / Thursday, October 30, 2008 /
Proposed Rules
[[Page 64566]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-28-AD]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Arriel 2B and 2B1 Turboshaft
Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Several cases of loss of internal components from the Hydro
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part
number (P/N) 9 550 17 956 0 into the fuel system, have been reported
on Arriel 2 engines.
The loss of internal components from the low fuel pressure
switch into the fuel system may lead to a rupture of the HP-LP pumps
drive shaft shear pin, and thus to a possible uncommanded in-flight
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD
results in an emergency autorotation landing and in certain
conditions may lead to an accident.
We are proposing this AD to prevent forced autorotation landing, or
an accident.
DATES: We must receive comments on this proposed AD by December 1,
2008.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: Docket Management Facility, U.S. Department of
Transportation, 1200 New Jersey Avenue, SE., West Building Ground
Floor, Room W12-140, Washington, DC 20590-0001.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Examining the AD 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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
the same as the Mail address provided in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer,
Engine Certification Office, FAA, Engine & Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2008-0935;
Directorate Identifier 2008-NE-28-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on 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
with FAA personnel concerning this proposed AD. Using the search
function of the Web site, anyone can find and read the comments in any
of our dockets, including, if provided, the name of the individual who
sent the comment (or signed the comment on behalf of an association,
business, labor union, etc.). You may review the DOT's complete Privacy
Act Statement in the Federal Register published on April 11, 2000 (65
FR 19477-78).
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
AD 2008-0077, dated April 28, 2008 (and corrected May 6, 2008)
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
Several cases of loss of internal components from the HMU low
fuel pressure switch Hydra-Electric P/N 9 550 17 956 0 into the fuel
system, have been reported on Arriel 2 engines.
The loss of internal components from the low fuel pressure
switch into the fuel system may lead to a rupture of the HP-LP pumps
drive shaft shear pin, and thus to a possible uncommanded IFSD. On a
single-engine helicopter, an uncommanded IFSD results in an
emergency autorotation landing and in certain conditions may lead to
an accident.
The evaluation of this condition prompts the issuance of this
AD, which requires the following actions for the HMUs installed on
Arriel 2 single-engine applications in order to:
Verify the part number of the low fuel pressure switch;
If installed, replace the Hydra-Electric low fuel
pressure switch P/N 9 550 17 956 0 (with either of two different P/N
low fuel pressure switches, referenced in the MCAI).
In case a Hydra-Electric switch P/N 9 550 17 956 0 is
installed or may have been installed on the HMU, verify that no
parts are found in the chamber of the HMU body where the base of the
low fuel pressure switch has been installed.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca has issued Mandatory Service Bulletin No. 292 73 2826,
dated March 13, 2008. The actions described in this service information
are intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of France,
and is approved for operation in the United States. Pursuant to our
bilateral
[[Page 64567]]
agreement with France, they have notified us of the unsafe condition
described in the EASA AD and service information referenced above. We
are proposing this AD because we evaluated all information provided by
EASA and determined the unsafe condition exists and is likely to exist
or develop on other products of the same type design. This proposed AD
would require a one-time inspection for affected low fuel pressure
switches, for evidence of an affected switch previously installed and
inspection for switch parts missing or fallen into the HMU well.
Difference Between This Proposed AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. We have proposed to not reference
the P/Ns of the serviceable low pressure switch as the MCAI does, in
order to follow FAA policies. This difference is described in a
separate paragraph of the proposed AD. This requirement, if ultimately
adopted, will take precedence over the actions in the MCAI.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 414 products installed on helicopters of U.S.
registry. We also estimate that it would take about 1 work-hour per
product to comply with this proposed AD. The average labor rate is $80
per work-hour. Required parts would cost about $256 per product. Based
on these figures, we estimate the cost of the proposed AD on U.S.
operators to be $139,104. Our cost estimate is exclusive of possible
warranty coverage.
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.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. 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 this 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 regulatory evaluation of the estimated costs to
comply with this proposed 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.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Turbomeca: Docket No. FAA-2008-0935; Directorate Identifier 2008-NE-
28-AD.
Comments Due Date
(a) We must receive comments by December 1, 2008.
Affected Airworthiness Directives (ADs)
(b) None.
Applicability
(c) This AD applies to Turbomeca Arriel 2B and 2B1 turboshaft
engines. These engines are installed on, but not limited to,
Eurocopter France AS350B3 and EC130 B4 helicopters.
Reason
(d) European Aviation Safety Agency (EASA) AD No. 2008-0077,
dated March 13, 2006 (and corrected May 6, 2008), states:
Several cases of loss of internal components from the Hydro
Mechanical Unit (HMU) low fuel pressure switch Hydra-Electric part
number (P/N) 9 550 17 956 0 into the fuel system, have been reported
on Arriel 2 engines.
The loss of internal components from the low fuel pressure
switch into the fuel system may lead to a rupture of the HP-LP pumps
drive shaft shear pin, and thus to a possible uncommanded in-flight
shutdown (IFSD). On a single-engine helicopter, an uncommanded IFSD
results in an emergency autorotation landing and in certain
conditions may lead to an accident.
We are issuing this AD to prevent forced autorotation landing,
or an accident.
Actions and Compliance
(e) Unless already done, do the following actions.
(1) No later than September 30, 2009, perform a one-time
inspection of the HMU, using paragraph 2 of Turbomeca Mandatory
Service Bulletin (MSB) No. 292 73 2826, dated March 13, 2008, to
identify the low fuel pressure switch installed on the adjusted HMU.
(2) If a Hydra-Electric low fuel pressure switch, part number
(P/N) 9 550 17 956 0 is installed:
(i) Inspect the low fuel pressure switch and chamber of the HMU
body.
(ii) If any parts from the low fuel pressure switch are missing
or found in the HMU chamber, replace the HMU with a new or
overhauled HMU equipped with a serviceable low fuel pressure switch.
(iii) If not, replace only the low fuel pressure switch with a
serviceable low fuel pressure switch.
(3) If a low fuel pressure switch other than a Hydra-Electric
low fuel pressure switch, P/N 9 550 17 956 0 is installed, and that
is the only type of low fuel pressure switch that has been installed
since new, repair, or overhaul, no further action is required.
(4) If a Hydra-Electric switch, P/N 9 550 17 956 0, has been or
may have been installed previously, and the conditions of paragraph
(e)(3) of this AD are not met:
(i) Inspect the chamber of the HMU body.
(ii) If any parts are found in the HMU chamber, replace the HMU
with a new or overhauled HMU equipped with a serviceable low fuel
pressure switch.
FAA AD Difference
(f) This AD differs from the Mandatory Continuing Airworthiness
Information (MCAI) and/or service information, by not referencing
the P/Ns of the serviceable low fuel pressure switch, and, defining
a serviceable low fuel pressure switch, for the purpose of this AD.
Definition
(g) For the purpose of this AD, a serviceable low fuel pressure
switch is a switch that has a P/N other than P/N 9 550 17 956 0.
[[Page 64568]]
Alternative Methods of Compliance (AMOCs)
(h) The Manager, Engine Certification Office, FAA, has the
authority to approve AMOCs for this AD, if requested, using the
procedures found in 14 CFR 39.19.
Related Information
(i) Refer to MCAI EASA AD 2008-0077, dated April 28, 2008 (and
corrected May 6, 2008), for related information.
(j) Contact James Lawrence, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; e-mail:
james.lawrence@faa.gov; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.
Issued in Burlington, Massachusetts, on October 23, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E8-25887 Filed 10-29-08; 8:45 am]
BILLING CODE 4910-13-P