Airworthiness Directives; Turbomeca S.A. Artouste III B, Artouste III B1, and Artouste III D Turboshaft Engines, 53937-53939 [E7-18434]
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Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
exhaust collector assembly with fewer than
50 operating hours and no cracks.
FAA AD Differences
(f) This AD differs from the Mandatory
Continuing Airworthiness Information
(MCAI) and/or service information as
follows:
(1) We require the initial inspection within
30 hours TSN instead of at 30 hours TSN.
(2) We require the repetitive inspections
within 10 hours TSLI instead of at 40 hours
TSN.
(3) We define a serviceable part.
Other FAA AD Provisions
(g) Alternative Methods of Compliance
(AMOCs): 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.
(h) Special Flight Permits: We will allow a
special flight permit to comply with
paragraph (e)(4) of this AD.
Related Information
(i) Refer to MCAI EASA Airworthiness
Directive 2007–0127, dated May 7, 2007, and
SMA Service Bulletin SB–01–78–78–001,
dated March 27, 2007, for related
information.
(j) Contact Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA,
Engine & Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; e-mail: christopher.spinney@faa.gov;
telephone (781) 238–7175; fax (781) 238–
7199 for more information about this AD.
Material Incorporated by Reference
(k) None.
Issued in Burlington, Massachusetts, on
September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–18412 Filed 9–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2006–23594; Directorate
Identifier 2005–NE–54–AD; Amendment 39–
15202; AD 2007–19–11]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
S.A. Artouste III B, Artouste III B1, and
Artouste III D Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
ebenthall on PROD1PC69 with RULES
AGENCY:
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD) for
Turbomeca Artouste III B, Artouste III
VerDate Aug<31>2005
15:32 Sep 20, 2007
Jkt 211001
B1, and Artouste III D turboshaft
engines. That AD currently requires
removing certain fuel pumps from
service and installing serviceable fuel
pumps. This AD requires the same
actions and adds to the applicability,
additional fuel pumps by serial number
(SN). This AD results from Turbomeca
identifying a number of fuel pump SNs
that they omitted from the original
population. We are issuing this AD to
prevent reduced engine fuel flow and
subsequent loss of control of the
helicopter, or an accident.
DATES: Effective October 9, 2007.
We must receive any comments on
this AD by November 20, 2007.
ADDRESSES: Use one of the following
addresses to comment on this AD.
• DOT Docket Web site: Go to
https://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: (202) 493–2251.
Contact Turbomeca, 40220 Tarnos,
France; telephone 33 05 59 74 40 00, fax
33 05 59 74 45 15, for the service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803; telephone (781)
238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: On
February 17, 2006, the FAA issued AD
2005–04–15, Amendment 39–14497 (71
FR 9692, February 27, 2006). That AD
requires removing affected fuel pumps
from service and installing serviceable
fuel pumps, within 30 days or 80
operating hours after receipt of a
serviceable fuel pump, whichever
occurs first, but no later than March 15,
2006. That AD was the result of fuel
pumps entering service after passing a
faulty acceptance test. Accordingly,
those fuel pumps may limit the
maximum fuel flow available to the
engine. That condition, if not corrected,
could result in reduced engine fuel flow
and subsequent loss of control of the
helicopter, or an accident.
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
53937
Actions Since AD 2006–04–15 Was
Issued
The European Aviation Safety Agency
(EASA), which is the airworthiness
authority for the European Union,
notified the FAA that Turbomeca has
identified an additional 58 fuel pumps,
by SN, that were omitted from the
original SN listing. These pumps may be
installed on U.S.-registered Eurocopter
France Alouette III SE.3160, SA.316B,
SA.315B, and SA.316C helicopters.
Turbomeca issued Mandatory Service
Bulletin No. 218 73 0802, Update 1,
dated January 8, 2007, to address the
160 suspect fuel pumps. We cannot
confirm that these fuel pumps have
been removed from service and retested
or replaced. The EASA issued AD 2007–
0030, dated February 6, 2007, in order
to ensure the airworthiness of these
engines in the European Union. We are
issuing this AD to prevent reduced
helicopter performance, subsequent loss
of control of the helicopter, or accident.
Differences Between This AD and the
Service Information
Turbomeca SB 218 73 0802, Update 1,
dated January 8, 2007, requires
compliance by March 1, 2007, at the
latest. This AD requires compliance no
later than 30 days after the effective date
of this AD.
Bilateral Airworthiness Agreement
This engine model is manufactured in
France and is type certificated for
operation in the United States under the
provisions of section 21.29 of the
Federal Aviation Regulations (14 CFR
21.29) and the applicable bilateral
airworthiness agreement. Under this
bilateral airworthiness agreement, the
EASA has kept the FAA informed of the
situation described above. We have
examined the findings of the EASA,
reviewed all available information, and
determined that AD action is necessary
for products of this type design that are
certificated for operation in the United
States.
FAA’s Determination and Requirements
of This AD
The unsafe condition described
previously is likely to exist or develop
on other Turbomeca Artouste III B,
Artouste III B1, and Artouste III D
turboshaft engines of the same type
design. We are issuing this AD to
prevent reduced engine fuel flow and
subsequent loss of control of the
helicopter, or an accident. This AD
requires:
• For pumps with a SN listed in
Table 1 of this AD, removing affected
fuel pumps from service and installing
serviceable fuel pumps no later than
E:\FR\FM\21SER1.SGM
21SER1
53938
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
March 15, 2006, the compliance end
date of AD 2005–04–15.
• For pumps with a SN listed in
Table 2 of this AD, removing affected
fuel pumps from service and installing
serviceable fuel pumps before
accumulating 50 cycles-in-service after
the effective date of this AD, but no later
than 30 days after the effective date of
this AD.
FAA’s Determination of the Effective
Date
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we have found that notice and
opportunity for public comment before
issuing this AD are impracticable, and
that good cause exists for making this
amendment effective in less than 30
days.
ebenthall on PROD1PC69 with RULES
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety and
was not preceded by notice and an
opportunity for public comment;
however, we invite you to send us any
written relevant data, views, or
arguments regarding this AD. Send your
comments to an address listed under
ADDRESSES. Include ‘‘AD Docket No.
FAA–2006–23594; Directorate Identifier
2005–NE–54–AD’’ in the subject line of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of the rule that might suggest a
need to modify it.
We will post all comments we
receive, without change, to https://
dms.dot.gov, including any personal
information you provide. We will also
post a report summarizing each
substantive verbal contact with FAA
personnel concerning this AD. Using the
search function of the DMS Web site,
anyone can find and read the comments
in any of our dockets, including 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) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://dms.dot.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
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is
VerDate Aug<31>2005
15:32 Sep 20, 2007
Jkt 211001
provided in the ADDRESSES section.
Comments will be available in the AD
docket shortly after receipt.
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 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 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 summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
Adoption of the Amendment
Under the authority delegated to me
by the Administrator, the Federal
Aviation Administration amends part 39
of the Federal Aviation Regulations (14
CFR part 39) as follows:
I
PO 00000
Frm 00026
Fmt 4700
Sfmt 4700
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
removing Amendment 39–14497 (71 FR
9692, February 27, 2006), and by adding
a new airworthiness directive,
Amendment 39–15202, to read as
follows:
I
2007–19–11 Turbomeca S.A.: Amendment
39–15202. Docket No. FAA–2005–23594;
Directorate Identifier 2005–NE–54–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective October 9, 2007.
Affected ADs
(b) This AD supersedes AD 2005–04–15,
Amendment 39–14497.
Applicability
(c) This AD applies to Turbomeca Artouste
III B, Artouste III B1, and Artouste III D
turboshaft engines. These engines are
installed on, but not limited to, Eurocopter
France Alouette III SE.3160, SA.316B,
SA.315B, and SA.316C helicopters.
Unsafe Condition
(d) This AD results from Turbomeca S.A.
identifying a number of fuel pump serial
numbers (SNs) that they omitted from the
original population. We are issuing this AD
to prevent reduced engine fuel flow and
subsequent loss of control of the helicopter,
or an accident.
Compliance
(e) You are responsible for having the
actions required by this AD performed within
the compliance times specified unless the
actions have already been done.
Original Requirement
(f) Remove from service the fuel pumps
listed by SN in Table 1 of this AD, and install
a serviceable fuel pump no later than March
15, 2006.
TABLE 1.—AFFECTED FUEL PUMP SNS
A59B
A82B
A91B
B14B
B29B
B42B
C27B
C6B
C92B
D16B
D18B
D20B
D80B
D99B
E49B
E77B
E90B
E:\FR\FM\21SER1.SGM
F504B
F506B
F537B
F561B
F589B
F596B
F607B
F630B
F643B
F706B
F724B
F743B
F745B
F748B
F759B
F760B
F762B
21SER1
2827
2828
2830
2838
2854
2867
2868
2884
2944
3078
3175
3230
3259
3282
3343
3376
3383
Federal Register / Vol. 72, No. 183 / Friday, September 21, 2007 / Rules and Regulations
(k) Turbomeca Mandatory Service Bulletin
No. 218 73 0802, Update No. 1, dated January
8, 2007, pertains to the subject of this AD.
TABLE 1.—AFFECTED FUEL PUMP
SNS—Continued
F112B
F131B
F176B
F220B
F243B
F253B
F262B
F293B
F317B
F320B
F357B
F368B
F420B
F464B
F466B
F477B
F47B
F957B
808
1725
1766
1770
1897
1941
2154
2155
2233
2512
2620
2729
2759
2763
2786
2787
3385
3397
3458
3515
3548
3660
3746
3756
3757
3783
3792
3826
3858
3888
3894
3979
4066
Issued in Burlington, Massachusetts, on
September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. E7–18434 Filed 9–20–07; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
New Requirement
(g) Remove from service the fuel pumps
listed by SN in Table 2 of this AD, and install
a serviceable fuel pump, before accumulating
50 hours in service after the effective date of
this AD, but no later than 30 days from the
effective date of this AD.
TABLE 2.—ADDITIONAL AFFECTED
FUEL PUMP SNS
158B
1749
1750
2103
2577
2665
2728
2837
2882
2887
2894
2933
3045
3120
3200
3220
3277
3293
3323
3326
3395
3438
3581
3725
3729
3884
3923
4123
4129
4213
4241B
B52B
B82B
C01B
D14B
D2B
D71B
D93B
E67B
F129B
F151B
F164B
F335B
F350B
F472B
F48B
F551B
F620B
F652B
F66B
F776B
F801B
F817B
F833B
F944B
F971B
G58B
G61B
ebenthall on PROD1PC69 with RULES
Related Information
(j) European Aviation Safety Agency AD
No. 2007–0030, dated February 6, 2007, also
addresses the subject of this AD.
Jkt 211001
Airworthiness Directives; Boeing
Model 747–100, 747–100B, 747–100B
SUD, 747–200B, 747–200C, 747–200F,
747–300, 747SR, and 747SP Series
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
Alternative Methods of Compliance
(i) The Manager, Engine Certification
Office, has the authority to approve
alternative methods of compliance for this
AD if requested using the procedures found
in 14 CFR 39.19.
15:32 Sep 20, 2007
RIN 2120–AA64
AGENCY:
Definition
(h) For the purpose of this AD, a
serviceable fuel pump is:
(1) A fuel pump that is not listed in Table
1 or Table 2 of this AD; or
(2) A fuel pump that is listed in Table 1
or Table 2 of this AD that has been retested
to verify that it meets maximum fuel flow
requirements.
VerDate Aug<31>2005
[Docket No. FAA–2007–29263; Directorate
Identifier 2007–NM–198–AD; Amendment
39–15210; AD 2007–19–19]
SUMMARY: The FAA is superseding an
existing airworthiness directive (AD)
that applies to certain Boeing Model 747
series airplanes. The existing AD
currently requires repetitive inspections
and torque checks of the hanger fittings
and strut forward bulkhead of the
forward engine mount and adjacent
support structure, and corrective actions
if necessary. The existing AD also
currently requires a terminating action
for the repetitive inspections and
checks. This new AD requires, among
other actions, new repetitive inspections
in the existing area and new areas. This
new AD also provides for an optional
inspection and no longer allows the
existing fastener replacement to
terminate repetitive inspections. This
AD results from new reports of undertorqued or loose fasteners, a cracked
bulkhead chord, and a fractured back-up
angle after operators accomplished the
terminating action required by the
existing AD. We are issuing this AD to
detect and correct loose fasteners and/
or damaged or cracked hanger fittings,
back-up angles, and bulkhead of the
forward engine mount, which could
lead to failure of the hanger fitting and
bulkhead and consequent separation of
the engine from the airplane.
DATES: This AD becomes effective
October 9, 2007.
PO 00000
Frm 00027
Fmt 4700
Sfmt 4700
53939
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of October 9, 2007.
On December 6, 2000 (65 FR 69862,
November 21, 2000), the Director of the
Federal Register approved the
incorporation by reference of Boeing
Alert Service Bulletin 747–54A2203,
dated August 31, 2000.
We must receive any comments on
this AD by November 20, 2007.
ADDRESSES: Use one of the following
addresses to submit comments on this
AD.
• DOT Docket Web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Fax: (202) 493–2251.
• Hand Delivery: Room W12–140 on
the ground floor of the West Building,
1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Contact Boeing Commercial
Airplanes, P.O. Box 3707, Seattle,
Washington 98124–2207, for service
information identified in this AD.
FOR FURTHER INFORMATION CONTACT:
Tamara Anderson, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6421; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION:
Discussion
On July 13, 2001, we issued AD 2001–
15–02, amendment 39–12336 (66 FR
37884, July 20, 2001). That AD applies
to certain Boeing Model 747 series
airplanes. That AD requires repetitive
inspections and torque checks of the
hanger fittings and strut forward
bulkhead of the forward engine mount
and adjacent support structure, and
corrective actions if necessary. That AD
also requires a terminating action for the
repetitive inspections and checks. That
AD resulted from reports indicating the
detection of loose fasteners of the
hanger fittings and strut forward
bulkhead of the forward engine mount.
The actions specified in that AD are
intended to prevent loose fasteners and
associated damage to the hanger fittings
E:\FR\FM\21SER1.SGM
21SER1
]]>Agencies
[Federal Register Volume 72, Number 183 (Friday, September 21, 2007)]
[Rules and Regulations]
[Pages 53937-53939]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E7-18434]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-23594; Directorate Identifier 2005-NE-54-AD;
Amendment 39-15202; AD 2007-19-11]
RIN 2120-AA64
Airworthiness Directives; Turbomeca S.A. Artouste III B, Artouste
III B1, and Artouste III D Turboshaft Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) for Turbomeca Artouste III B, Artouste III B1, and Artouste III D
turboshaft engines. That AD currently requires removing certain fuel
pumps from service and installing serviceable fuel pumps. This AD
requires the same actions and adds to the applicability, additional
fuel pumps by serial number (SN). This AD results from Turbomeca
identifying a number of fuel pump SNs that they omitted from the
original population. We are issuing this AD to prevent reduced engine
fuel flow and subsequent loss of control of the helicopter, or an
accident.
DATES: Effective October 9, 2007.
We must receive any comments on this AD by November 20, 2007.
ADDRESSES: Use one of the following addresses to comment on this AD.
DOT Docket Web site: Go to https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
www.regulations.gov and follow the instructions for sending your
comments electronically.
Mail: 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: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Fax: (202) 493-2251.
Contact Turbomeca, 40220 Tarnos, France; telephone 33 05 59 74 40
00, fax 33 05 59 74 45 15, for the service information identified in
this AD.
FOR FURTHER INFORMATION CONTACT: Christopher Spinney, Aerospace
Engineer, Engine Certification Office, FAA, Engine and Propeller
Directorate, 12 New England Executive Park, Burlington, MA 01803;
telephone (781) 238-7175; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On February 17, 2006, the FAA issued AD
2005-04-15, Amendment 39-14497 (71 FR 9692, February 27, 2006). That AD
requires removing affected fuel pumps from service and installing
serviceable fuel pumps, within 30 days or 80 operating hours after
receipt of a serviceable fuel pump, whichever occurs first, but no
later than March 15, 2006. That AD was the result of fuel pumps
entering service after passing a faulty acceptance test. Accordingly,
those fuel pumps may limit the maximum fuel flow available to the
engine. That condition, if not corrected, could result in reduced
engine fuel flow and subsequent loss of control of the helicopter, or
an accident.
Actions Since AD 2006-04-15 Was Issued
The European Aviation Safety Agency (EASA), which is the
airworthiness authority for the European Union, notified the FAA that
Turbomeca has identified an additional 58 fuel pumps, by SN, that were
omitted from the original SN listing. These pumps may be installed on
U.S.-registered Eurocopter France Alouette III SE.3160, SA.316B,
SA.315B, and SA.316C helicopters.
Turbomeca issued Mandatory Service Bulletin No. 218 73 0802, Update
1, dated January 8, 2007, to address the 160 suspect fuel pumps. We
cannot confirm that these fuel pumps have been removed from service and
retested or replaced. The EASA issued AD 2007-0030, dated February 6,
2007, in order to ensure the airworthiness of these engines in the
European Union. We are issuing this AD to prevent reduced helicopter
performance, subsequent loss of control of the helicopter, or accident.
Differences Between This AD and the Service Information
Turbomeca SB 218 73 0802, Update 1, dated January 8, 2007, requires
compliance by March 1, 2007, at the latest. This AD requires compliance
no later than 30 days after the effective date of this AD.
Bilateral Airworthiness Agreement
This engine model is manufactured in France and is type
certificated for operation in the United States under the provisions of
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and
the applicable bilateral airworthiness agreement. Under this bilateral
airworthiness agreement, the EASA has kept the FAA informed of the
situation described above. We have examined the findings of the EASA,
reviewed all available information, and determined that AD action is
necessary for products of this type design that are certificated for
operation in the United States.
FAA's Determination and Requirements of This AD
The unsafe condition described previously is likely to exist or
develop on other Turbomeca Artouste III B, Artouste III B1, and
Artouste III D turboshaft engines of the same type design. We are
issuing this AD to prevent reduced engine fuel flow and subsequent loss
of control of the helicopter, or an accident. This AD requires:
For pumps with a SN listed in Table 1 of this AD, removing
affected fuel pumps from service and installing serviceable fuel pumps
no later than
[[Page 53938]]
March 15, 2006, the compliance end date of AD 2005-04-15.
For pumps with a SN listed in Table 2 of this AD, removing
affected fuel pumps from service and installing serviceable fuel pumps
before accumulating 50 cycles-in-service after the effective date of
this AD, but no later than 30 days after the effective date of this AD.
FAA's Determination of the Effective Date
Since an unsafe condition exists that requires the immediate
adoption of this AD, we have found that notice and opportunity for
public comment before issuing this AD are impracticable, and that good
cause exists for making this amendment effective in less than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety and was not preceded by notice and an opportunity for public
comment; however, we invite you to send us any written relevant data,
views, or arguments regarding this AD. Send your comments to an address
listed under ADDRESSES. Include ``AD Docket No. FAA-2006-23594;
Directorate Identifier 2005-NE-54-AD'' in the subject line of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify it.
We will post all comments we receive, without change, to https://
dms.dot.gov, including any personal information you provide. We will
also post a report summarizing each substantive verbal contact with FAA
personnel concerning this AD. Using the search function of the DMS Web
site, anyone can find and read the comments in any of our dockets,
including 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) or you may visit
https://dms.dot.gov.
Examining the AD Docket
You may examine the AD docket on the Internet at https://
dms.dot.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 regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone (800) 647-5527) is provided in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
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 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 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 summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
Adoption of the Amendment
0
Under the authority delegated to me by the Administrator, the Federal
Aviation Administration amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-14497 (71 FR
9692, February 27, 2006), and by adding a new airworthiness directive,
Amendment 39-15202, to read as follows:
2007-19-11 Turbomeca S.A.: Amendment 39-15202. Docket No. FAA-2005-
23594; Directorate Identifier 2005-NE-54-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
9, 2007.
Affected ADs
(b) This AD supersedes AD 2005-04-15, Amendment 39-14497.
Applicability
(c) This AD applies to Turbomeca Artouste III B, Artouste III
B1, and Artouste III D turboshaft engines. These engines are
installed on, but not limited to, Eurocopter France Alouette III
SE.3160, SA.316B, SA.315B, and SA.316C helicopters.
Unsafe Condition
(d) This AD results from Turbomeca S.A. identifying a number of
fuel pump serial numbers (SNs) that they omitted from the original
population. We are issuing this AD to prevent reduced engine fuel
flow and subsequent loss of control of the helicopter, or an
accident.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified unless the
actions have already been done.
Original Requirement
(f) Remove from service the fuel pumps listed by SN in Table 1
of this AD, and install a serviceable fuel pump no later than March
15, 2006.
Table 1.--Affected Fuel Pump SNs
------------------------------------------------------------------------
------------------------------------------------------------------------
A59B F504B 2827
A82B F506B 2828
A91B F537B 2830
B14B F561B 2838
B29B F589B 2854
B42B F596B 2867
C27B F607B 2868
C6B F630B 2884
C92B F643B 2944
D16B F706B 3078
D18B F724B 3175
D20B F743B 3230
D80B F745B 3259
D99B F748B 3282
E49B F759B 3343
E77B F760B 3376
E90B F762B 3383
[[Page 53939]]
F112B F957B 3385
F131B 808 3397
F176B 1725 3458
F220B 1766 3515
F243B 1770 3548
F253B 1897 3660
F262B 1941 3746
F293B 2154 3756
F317B 2155 3757
F320B 2233 3783
F357B 2512 3792
F368B 2620 3826
F420B 2729 3858
F464B 2759 3888
F466B 2763 3894
F477B 2786 3979
F47B 2787 4066
------------------------------------------------------------------------
New Requirement
(g) Remove from service the fuel pumps listed by SN in Table 2
of this AD, and install a serviceable fuel pump, before accumulating
50 hours in service after the effective date of this AD, but no
later than 30 days from the effective date of this AD.
Table 2.--Additional Affected Fuel Pump SNs
------------------------------------------------------------------------
------------------------------------------------------------------------
158B 3395 F129B
1749 3438 F151B
1750 3581 F164B
2103 3725 F335B
2577 3729 F350B
2665 3884 F472B
2728 3923 F48B
2837 4123 F551B
2882 4129 F620B
2887 4213 F652B
2894 4241B F66B
2933 B52B F776B
3045 B82B F801B
3120 C01B F817B
3200 D14B F833B
3220 D2B F944B
3277 D71B F971B
3293 D93B G58B
3323 E67B G61B
3326
------------------------------------------------------------------------
Definition
(h) For the purpose of this AD, a serviceable fuel pump is:
(1) A fuel pump that is not listed in Table 1 or Table 2 of this
AD; or
(2) A fuel pump that is listed in Table 1 or Table 2 of this AD
that has been retested to verify that it meets maximum fuel flow
requirements.
Alternative Methods of Compliance
(i) The Manager, Engine Certification Office, has the authority
to approve alternative methods of compliance for this AD if
requested using the procedures found in 14 CFR 39.19.
Related Information
(j) European Aviation Safety Agency AD No. 2007-0030, dated
February 6, 2007, also addresses the subject of this AD.
(k) Turbomeca Mandatory Service Bulletin No. 218 73 0802, Update
No. 1, dated January 8, 2007, pertains to the subject of this AD.
Issued in Burlington, Massachusetts, on September 11, 2007.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. E7-18434 Filed 9-20-07; 8:45 am]
BILLING CODE 4910-13-P
