Airworthiness Directives; Turbomeca Artouste III B and III B1 Turboshaft Engines, 1141-1143 [E6-22533]
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mstockstill on PROD1PC61 with RULES
Federal Register / Vol. 72, No. 6 / Wednesday, January 10, 2007 / Rules and Regulations
Note 1: Sikorsky Aircraft Corporation
issued an All Operators Letter (AOL) CCS–
61–AOL–04–0005, dated May 18, 2004, with
an example and additional information about
tracking cycles and the moving average
procedure. You can obtain this AOL from the
manufacturer at the address stated in the
ADDRESSES portion of this AD.
(c) For each REL IFWU assembly, at
intervals not to exceed 500 hours TIS or 7500
lift cycles, whichever occurs first, since the
last IFWU assembly inspection:
(1) Inspect for wear, surface distress, and
endplay by following paragraphs B.(1)
through B.(6) of the Accomplishment
Instructions of Sikorsky Aircraft Corporation
Alert Service Bulletin No. 61B35–67B,
Revision B, dated August 11, 2003 (ASB).
Record all the information specified in
Figures 1 through 3 attached to the ASB. You
may record this information on any suitable
maintenance record, or you may use the
Sikorsky evaluation forms provided in the
ASB. This AD does not require you to contact
Sikorsky.
(2) Replace any IFWU assembly part whose
average wear, wear marks, surface distress, or
endplay exceeds the limits stated in
paragraph B.(1) through B.(6) of the
Accomplishment Instructions of the ASB
with an airworthy IFWU assembly part.
Note 2: Sikorsky S–61 Overhaul Manual,
Number SA 4045–83, Revision 20, dated
August 15, 2003, as revised by Temporary
Revisions 65–193, –194, –195, and –196,
contains the overhaul procedures for the
IFWU assembly.
(d) For each REL IFWU assembly,
permanently mark IFWU camshafts, P/N
S6135–20611, S6135–20614 and S6137–
23075, and IFWU gear housings, P/N S6135–
20695 and S6137–23057, with the letters
‘‘REL’’. Mark the camshafts by applying
etching ink on the surface of the part that is
0.5 inch square with the depth of the letters
not to exceed 0.001 inch. After etching,
neutralize the etched surface and oil to
prevent corrosion.
(e) For the next 24 months and within 10
days after completing the requirements of
paragraph (c)(1) of this AD, provide a copy
of the recorded information to the Manager
of the Boston Aircraft Certification Office,
Engine and Propeller Directorate, FAA, 12
New England Executive Park, Burlington,
MA 01803.
Note 3: In the ASB, Sikorsky requests
copies of the completed inspection forms,
Figures 1 through 3 to their ASB. This AD
does not require you to provide these forms
to Sikorsky.
(f) Information collection requirements
contained in this AD have been approved by
the Office of Management and Budget (OMB)
under the provisions of the Paperwork
Reduction Act of 1980 (44 U.S.C. 3501 et
seq.) and have been assigned OMB Control
Number 2120–0056.
(g) 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 Manger, Boston Aircraft
Certification Office, Engine and Propeller
Directorate, FAA, ATTN: Kirk Gustafson,
Aviation Safety Engineer, 12 New England
VerDate Aug<31>2005
14:45 Jan 09, 2007
Jkt 211001
Executive Park, Burlington, MA 01803,
telephone (781) 238–7190, fax (781) 238–
7170, for information about previously
approved alternative methods of compliance.
(h) The inspections shall be done by
following the specified portions of Sikorsky
Aircraft Corporation Alert Service Bulletin
No. 61B35–67B, Revision B, dated August 11,
2003. The Director of the Federal Register
approved this incorporation by reference in
accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from
Sikorsky Aircraft Corporation, Attn: Manager,
Commercial Tech Support, 6900 Main Street,
Stratford, Connecticut 06614, phone (203)
386–3001, fax (203) 386–5983. Copies may be
inspected at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
(i) This amendment becomes effective on
February 14, 2007.
Appendix I
Section I: The first moving average of lift
cycles per hour TIS.
The first moving average calculation is
performed on the IFWU assembly when the
external lift component history card record
reflects that the IFWU assembly has reached
its first 250 hours TIS. To perform the
calculation, divide the total number of lift
cycles performed during the first 250 hours
TIS by 250. The result will be the first
moving average calculation of lift cycles per
hour TIS.
Section II: Subsequent moving average of
lift cycles per hour TIS.
Subsequent moving average calculations
are performed on the IFWU assembly at
intervals of 50 hour TIS after the first moving
average calculation. Subtract the total
number of lift cycles performed during the
first 50-hour TIS interval used in the
previous moving average calculation from the
total number of lift cycles performed on the
IFWU assembly during the previous 300
hours TIS. Divide this result by 250. The
result will be the next or subsequent moving
average calculation of lift cycles per hour
TIS.
Section III: Sample calculation for
subsequent 50 hour TIS intervals.
Assume the total number of lift cycles for
the first 50 hour TIS interval used in the
previous moving average calculation = 450
lift cycles and the total number of lift cycles
for the previous 300 hours TIS = 2700 lift
cycles. The subsequent moving average of lift
cycles per hour TIS = (2700–450) divided by
250 = 9 lift cycles per hour TIS.
Issued in Fort Worth, Texas, on December
26, 2006.
David A. Downey,
Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. E7–40 Filed 1–9–07; 8:45 am]
BILLING CODE 4910–13–P
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1141
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–26128; Directorate
Identifier 2006–NE–34–AD; Amendment 39–
14875; AD 2007–01–04]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Artouste III B and III B1 Turboshaft
Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This 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:
3 cases of cracking due to exfoliation
corrosion on the unions of fuel pipes P/N 0
202 12 800 0, connecting the Fuel Control
Unit to the start electrovalve, were reported.
These cases of cracking, if they had not
previously been detected, could have caused
a loss of integrity of the union conveying fuel
under pressure. A fuel leakage could then
have happened and would have led to an
uncommanded loss of power and to a fire
hazard. This AD requires the fuel pipe to be
inspected for cracking.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
January 25, 2007.
The Director of the Federal Register
approved the incorporation by reference
of Turbomeca Mandatory Service
Bulletin No. A218 73 0803, dated May
2, 2006, listed in the AD as of January
25, 2007.
We must receive comments on this
AD by February 9, 2007.
ADDRESSES: You may send comments by
any of the following methods:
• DOT Docket Web Site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Fax: (202) 493–2251.
• Mail: Docket Management Facility,
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
0001.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
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1142
Federal Register / Vol. 72, No. 6 / Wednesday, January 10, 2007 / Rules and Regulations
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
• Federal eRulemaking Portal: https://
www.regulations.gov. Follow the
instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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
AD, the regulatory evaluation, any
comments received, and other
information. The street address for the
Docket Office (telephone (800) 647–
5227) is in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine & Propeller Directorate, 12
New England Executive Park,
Burlington, MA 01803; telephone (781)
238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new
process for streamlining the issuance of
ADs related to MCAI. This streamlined
process will allow us to adopt MCAI
safety requirements in a more efficient
manner and will reduce safety risks to
the public. This process continues to
follow all FAA AD issuance processes to
meet legal, economic, Administrative
Procedure Act, and Federal Register
requirements. We also continue to meet
our technical decision-making
responsibilities to identify and correct
unsafe conditions on U.S.-certificated
products.
This AD references the MCAI and
related service information that we
considered in forming the engineering
basis to correct the unsafe condition.
The AD contains text copied from the
MCAI and for this reason might not
follow our plain language principles.
mstockstill on PROD1PC61 with RULES
Discussion
The European Aviation Safety Agency
(EASA), which is the aviation authority
for the European Union, has issued
Airworthiness Directive No. 2006–0154,
dated June 1, 2006, (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
3 cases of cracking due to exfoliation
corrosion on the unions of fuel pipes P/N 0
202 12 800 0, connecting the Fuel Control
Unit to the start electrovalve, were reported.
These cases of cracking, if they had not
previously been detected, could have caused
VerDate Aug<31>2005
14:45 Jan 09, 2007
Jkt 211001
a loss of integrity of the union conveying fuel
under pressure. A fuel leakage could then
have happened and would have led to an
uncommanded loss of power and to a fire
hazard. This AD requires the fuel pipe to be
inspected for cracking.
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.
You may obtain further information by
examining the MCAI in the AD docket.
Comments Invited
Relevant Service Information
Turbomeca has issued Mandatory
Service Bulletin No. A218 73 0803,
dated May 2, 2006. 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 AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with this State of
Design Authority, they have notified us
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all the
information provided by the State of
Design Authority and determined the
unsafe condition exists and is likely to
exist or develop on other products of the
same type design.
Differences Between the AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are described in a
separate paragraph of the AD. These
requirements take precedence over the
actions copied from the MCAI.
FAA’s Determination of the Effective
Date
An unsafe condition exists that
requires the immediate adoption of this
AD. The FAA has found that the risk to
the flying public justifies waiving notice
and comment prior to adoption of this
rule because undetected cracking could
cause loss of integrity of the union
conveying fuel under pressure. This
could result in a fuel leak and an
uncommmanded loss of power and a
fire hazard. Therefore, we determined
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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. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2006–26128;
Directorate Identifier 2006–NE–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://
dms.dot.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
products 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.
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Federal Register / Vol. 72, No. 6 / Wednesday, January 10, 2007 / Rules and Regulations
For the reasons discussed above, 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
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory 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:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
I
2007–01–04 Turbomeca: Amendment 39–
14875. Docket No. FAA–2006–26128;
Directorate Identifier 2006–NE–34–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective January 25, 2007.
Affected ADs
(b) None.
mstockstill on PROD1PC61 with RULES
Applicability
(c) This AD applies to Artouste III B and
III B1 turboshaft engines fitted with a fuel
pipe, part number 0 202 12 800 0. These
engines are installed on SA 315 B LAMA and
SA 316 B Alouette III helicopters.
Reason
(d) European Aviation Safety Agency,
(EASA), Airworthiness Directive No. 2006–
0154, dated June 1, 2006, states:
3 cases of cracking due to exfoliation
corrosion on the unions of fuel pipes P/N 0
202 12 800 0, connecting the Fuel Control
Unit to the start electrovalve, were reported.
These cases of cracking, if they had not
previously been detected, could have caused
a loss of integrity of the union conveying fuel
under pressure. A fuel leakage could then
have happened and would have led to an
uncommanded loss of power and to a fire
hazard. This AD requires the fuel pipe to be
inspected for cracking.
FAA AD Differences
(e) None.
VerDate Aug<31>2005
14:45 Jan 09, 2007
Jkt 211001
Actions and Compliance
1143
Issued in Burlington, Massachusetts, on
December 27, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. E6–22533 Filed 1–9–07; 8:45 am]
(f) At the next maintenance action on the
engine or airframe, but no later than 30 days
after the effective date of this AD, unless
already done, do the following action.
(1) Inspect for cracks in the lower union of
the flexible fuel pipe between the electric
fuel cock and the start valve.
(2) Use the instructions contained in
paragraph 2 of Turbomeca Mandatory Service
Bulletin No. A218 73 0803, dated May 2,
2006, to do the inspection.
BILLING CODE 4910–13–P
Other FAA AD Provisions
14 CFR Part 39
(g) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Engine Certification
Office, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act,
the Office of Management and Budget (OMB)
has approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
Related Information
(h) Refer to the EASA Airworthiness
Directive 2006–0154, dated June 1, 2006, and
Turbomeca Mandatory Service Bulletin A218
73 0803, dated May 2, 2006, for related
information.
(i) Contact Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7175; fax (781)
238–7199, for more information about this
AD.
Material Incorporated by Reference
(j) You must use Turbomeca Mandatory
Service Bulletin No. A218 73 0803, dated
May 2, 2006, to do the actions required by
this AD, unless the AD specifies otherwise.
(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 Turbomeca, 40220 Tarnos,
France; telephone (33) 05 59 74 40 00; fax
(33) 05 59 74 45 15.
(3) You may review copies 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.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. FAA–2006–25089; Directorate
Identifier 2006–NM–091–AD; Amendment
39–14873; AD 2007–01–02]
RIN 2120–AA64
Airworthiness Directives; McDonnell
Douglas Model MD–11 and –11F
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD),
which applies to certain McDonnell
Douglas Model MD–11 and –11F
airplanes. That AD currently requires an
initial general visual inspection of the
power feeder cables of the integrated
drive generator (IDG) and the fuel feed
lines of engine pylons No. 1 and No. 3
on the wings for proper clearance and
damage; corrective actions if necessary;
and repetitive general visual inspections
and a terminating action for the
repetitive inspections. This new AD
requires the existing actions, and for
certain airplanes, this AD requires
installation of new clamps on the power
feeder cables of the IDG of engine
pylons No. 1 and No. 3. This AD results
from reports of IDG power feeder cables
riding against structure and fuel lines in
the No. 1 and No. 3 pylons. We are
issuing this AD to prevent potential
chafing of the power feeder cables of the
IDG in engine pylons No. 1 and No. 3
on the wings, and consequent arcing on
the fuel lines in the engine pylons and
possible fuel fire.
DATES: This AD becomes effective
February 14, 2007.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of February 14, 2007.
On February 24, 2004 (69 FR 2657,
January 20, 2004), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin MD11–54A011,
Revision 02, dated May 31, 2002.
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]]>Agencies
[Federal Register Volume 72, Number 6 (Wednesday, January 10, 2007)]
[Rules and Regulations]
[Pages 1141-1143]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E6-22533]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26128; Directorate Identifier 2006-NE-34-AD;
Amendment 39-14875; AD 2007-01-04]
RIN 2120-AA64
Airworthiness Directives; Turbomeca Artouste III B and III B1
Turboshaft Engines
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 the
products listed above. This 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:
3 cases of cracking due to exfoliation corrosion on the unions
of fuel pipes P/N 0 202 12 800 0, connecting the Fuel Control Unit
to the start electrovalve, were reported. These cases of cracking,
if they had not previously been detected, could have caused a loss
of integrity of the union conveying fuel under pressure. A fuel
leakage could then have happened and would have led to an
uncommanded loss of power and to a fire hazard. This AD requires the
fuel pipe to be inspected for cracking.
This AD requires actions that are intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective January 25, 2007.
The Director of the Federal Register approved the incorporation by
reference of Turbomeca Mandatory Service Bulletin No. A218 73 0803,
dated May 2, 2006, listed in the AD as of January 25, 2007.
We must receive comments on this AD by February 9, 2007.
ADDRESSES: You may send comments by any of the following methods:
DOT Docket Web Site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Fax: (202) 493-2251.
Mail: Docket Management Facility, U.S. Department of
Transportation, 400 Seventh Street, SW., Nassif Building, Room PL-401,
Washington, DC 20590-0001.
Hand Delivery: Room PL-401 on the plaza level of the
Nassif Building,
[[Page 1142]]
400 Seventh Street, SW., Washington, DC, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
Federal eRulemaking Portal: https://www.regulations.gov.
Follow the instructions for submitting comments.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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 AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Office (telephone (800) 647-5227) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine & Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION:
Streamlined Issuance of AD
The FAA is implementing a new process for streamlining the issuance
of ADs related to MCAI. This streamlined process will allow us to adopt
MCAI safety requirements in a more efficient manner and will reduce
safety risks to the public. This process continues to follow all FAA AD
issuance processes to meet legal, economic, Administrative Procedure
Act, and Federal Register requirements. We also continue to meet our
technical decision-making responsibilities to identify and correct
unsafe conditions on U.S.-certificated products.
This AD references the MCAI and related service information that we
considered in forming the engineering basis to correct the unsafe
condition. The AD contains text copied from the MCAI and for this
reason might not follow our plain language principles.
Discussion
The European Aviation Safety Agency (EASA), which is the aviation
authority for the European Union, has issued Airworthiness Directive
No. 2006-0154, dated June 1, 2006, (referred to after this as ``the
MCAI''), to correct an unsafe condition for the specified products. The
MCAI states:
3 cases of cracking due to exfoliation corrosion on the unions
of fuel pipes P/N 0 202 12 800 0, connecting the Fuel Control Unit
to the start electrovalve, were reported. These cases of cracking,
if they had not previously been detected, could have caused a loss
of integrity of the union conveying fuel under pressure. A fuel
leakage could then have happened and would have led to an
uncommanded loss of power and to a fire hazard. This AD requires the
fuel pipe to be inspected for cracking.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Turbomeca has issued Mandatory Service Bulletin No. A218 73 0803,
dated May 2, 2006. 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 AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are issuing this AD because we
evaluated all the information provided by the State of Design Authority
and determined the unsafe condition exists and is likely to exist or
develop on other products of the same type design.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the AD. These requirements take
precedence over the actions copied from the MCAI.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
undetected cracking could cause loss of integrity of the union
conveying fuel under pressure. This could result in a fuel leak and an
uncommmanded loss of power and a fire hazard. Therefore, we 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. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2006-26128; Directorate
Identifier 2006-NE-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://
dms.dot.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 products 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.
[[Page 1143]]
For the reasons discussed above, 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 under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory 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:
2007-01-04 Turbomeca: Amendment 39-14875. Docket No. FAA-2006-26128;
Directorate Identifier 2006-NE-34-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective January
25, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Artouste III B and III B1 turboshaft
engines fitted with a fuel pipe, part number 0 202 12 800 0. These
engines are installed on SA 315 B LAMA and SA 316 B Alouette III
helicopters.
Reason
(d) European Aviation Safety Agency, (EASA), Airworthiness
Directive No. 2006-0154, dated June 1, 2006, states:
3 cases of cracking due to exfoliation corrosion on the unions
of fuel pipes P/N 0 202 12 800 0, connecting the Fuel Control Unit
to the start electrovalve, were reported. These cases of cracking,
if they had not previously been detected, could have caused a loss
of integrity of the union conveying fuel under pressure. A fuel
leakage could then have happened and would have led to an
uncommanded loss of power and to a fire hazard. This AD requires the
fuel pipe to be inspected for cracking.
FAA AD Differences
(e) None.
Actions and Compliance
(f) At the next maintenance action on the engine or airframe,
but no later than 30 days after the effective date of this AD,
unless already done, do the following action.
(1) Inspect for cracks in the lower union of the flexible fuel
pipe between the electric fuel cock and the start valve.
(2) Use the instructions contained in paragraph 2 of Turbomeca
Mandatory Service Bulletin No. A218 73 0803, dated May 2, 2006, to
do the inspection.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Engine Certification Office, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to the EASA Airworthiness Directive 2006-0154, dated
June 1, 2006, and Turbomeca Mandatory Service Bulletin A218 73 0803,
dated May 2, 2006, for related information.
(i) Contact Christopher Spinney, Aerospace Engineer, Engine
Certification Office, FAA, Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803; telephone (781) 238-
7175; fax (781) 238-7199, for more information about this AD.
Material Incorporated by Reference
(j) You must use Turbomeca Mandatory Service Bulletin No. A218
73 0803, dated May 2, 2006, to do the actions required by this AD,
unless the AD specifies otherwise.
(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
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax
(33) 05 59 74 45 15.
(3) You may review copies 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 Burlington, Massachusetts, on December 27, 2006.
Ann C. Mollica,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. E6-22533 Filed 1-9-07; 8:45 am]
BILLING CODE 4910-13-P
