Airworthiness Directives; Eurocopter France Model EC130 B4 Helicopters, 15395-15397 [E8-5494]
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Federal Register / Vol. 73, No. 57 / Monday, March 24, 2008 / Rules and Regulations
order in which the petitions are filed.
USCIS will make projections of the
number of petitions necessary to
achieve the numerical limit of
approvals, taking into account historical
data related to approvals, denials,
revocations, and other relevant factors.
USCIS will monitor the number of
petitions (including the number of
beneficiaries requested when necessary)
received and will notify the public of
the date that USCIS has received the
necessary number of petitions (the
‘‘final receipt date’’). The day the news
is published will not control the final
receipt date. When necessary to ensure
the fair and orderly allocation of
numbers in a particular classification
subject to a numerical limitation or the
exemption under section 214(g)(5)(C) of
the Act, USCIS may randomly select
from among the petitions received on
the final receipt date the remaining
number of petitions deemed necessary
to generate the numerical limit of
approvals. This random selection will
be made via computer-generated
selection as validated by the Office of
Immigration Statistics. Petitions subject
to a numerical limitation not randomly
selected or that were received after the
final receipt date will be rejected.
Petitions filed on behalf of aliens
otherwise eligible for the exemption
under section 214(g)(5)(C) of the Act not
randomly selected or that were received
after the final receipt date will be
rejected if the numerical limitation
under 214(g)(1) of the Act has been
reached for that fiscal year. Petitions
indicating that they are exempt from the
numerical limitation but that are
determined by USCIS after the final
receipt date to be subject to the
numerical limit will be denied and
filing fees will not be returned or
refunded. If the final receipt date is any
of the first five business days on which
petitions subject to the applicable
numerical limit may be received (i.e., if
the numerical limit is reached on any
one of the first five business days that
filings can be made), USCIS will
randomly apply all of the numbers
among the petitions received on any of
those five business days, conducting the
random selection among the petitions
subject to the exemption under section
214(g)(5)(C) of the Act first.
*
*
*
*
*
(D) If the total numbers available in a
fiscal year are used, new petitions and
the accompanying fee shall be rejected
and returned with a notice that numbers
are unavailable for the particular
nonimmigrant classification until the
beginning of the next fiscal year.
Petitions received after the total
VerDate Aug<31>2005
16:13 Mar 21, 2008
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numbers available in a fiscal year are
used stating that the alien beneficiaries
are exempt from the numerical
limitation will be denied and filing fees
will not be returned or refunded if
USCIS later determines that such
beneficiaries are subject to the
numerical limitation.
*
*
*
*
*
Dated: March 18, 2008.
Michael Chertoff,
Secretary.
[FR Doc. E8–5906 Filed 3–21–08; 8:45 am]
BILLING CODE 4410–10–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2007–28229; Directorate
Identifier 2006–SW–23–AD; Amendment 39–
15434; AD 2008–06–22]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Model EC130 B4 Helicopters
Federal Aviation
Administration, DOT.
ACTION: Final rule.
AGENCY:
SUMMARY: This amendment adopts a
new airworthiness directive (AD) for the
specified Eurocopter France
(Eurocopter) Model EC 130 B4
helicopters, with certain twist grip
assemblies installed, that requires
inspecting the pilot and co-pilot
collective levers for proper bonding
between the twist grip drive tubes and
the control pinions and if debonding is
present, replacing the collective levers
before further flight. This amendment is
prompted by one incident in which the
engine remained at idle speed although
the twist grip had been turned to the
flight position. The actions specified by
this AD are intended to detect
debonding between the twist grip drive
tubes and the control pinions on the
pilot and co-pilot collective levers to
prevent loss of cockpit throttle control
of the engine, and subsequent loss of
control of the helicopter.
DATES: Effective April 28, 2008.
The incorporation by reference of
certain publications listed in the
regulations is approved by the Director
of the Federal Register as of April 28,
2008.
You may get the service
information identified in this AD from
American Eurocopter Corporation, 2701
Forum Drive, Grand Prairie, Texas
ADDRESSES:
PO 00000
Frm 00009
Fmt 4700
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15395
75053–4005, telephone (972) 641–3460,
fax (972) 641–3527.
Examining the Docket: You may
examine the docket that contains this
AD, any comments, and other
information on the Internet at https://
www.regulations.gov or at the Docket
Operations office, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue, SE., Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Ed
Cuevas, Aviation Safety Engineer, FAA,
Rotorcraft Directorate, Safety
Management Group, Fort Worth, Texas
76193–0111, telephone (817) 222–5355,
fax (817) 222–5961.
SUPPLEMENTARY INFORMATION: A
proposal to amend 14 CFR part 39 to
include an AD for the specified model
helicopters was published in the
Federal Register on May 21, 2007 (72
FR 28456). That action proposed to
require, within 110 hours time-inservice (TIS) or 4 months, whichever
occurs first, or before installing a
collective lever with an affected grip
assembly on a helicopter, inspecting the
bonding between the twist grip drive
tube and the control pinion on both the
pilot and co-pilot collective lever. If
debonding is present, replacing the
collective lever before further flight was
proposed.
The European Aviation Safety Agency
(EASA) notified us that an unsafe
condition may exist on Eurocopter
Model EC 130 B4 helicopters, with a
twist grip assembly, part number (P/N)
350A27520900, 350A27520901,
350A27520902, or 350A27520903, with
a serial number below 64, installed on
the pilot’s side, and a twist grip
assembly, P/N 350A27521201, with a
serial number below 67, installed on the
co-pilot’s side. EASA advises that
analysis of an incident that occurred
during autorotation training revealed a
failure of the twist grip drive tube and
control pinion bonded attachment. The
engine remained at idle speed although
the twist grip had been turned back to
the flight position. The autorotation
procedure continued to the ground
without damage to the helicopter. The
failure has been attributed to noncompliant surface preparation during
manufacture.
Eurocopter, an EADS Company, has
issued Alert Service Bulletin EC130 No.
76A001, dated February 10, 2006, which
specifies a check by use of a twist grip
adjusting gauge of the bonding between
the twist grip drive tube and the control
pinion on both the pilot and co-pilot
collective lever. EASA classified this
service bulletin as mandatory and
issued AD No. 2006–0079, dated April
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15396
Federal Register / Vol. 73, No. 57 / Monday, March 24, 2008 / Rules and Regulations
pwalker on PROD1PC71 with RULES
3, 2006, to ensure the continued
airworthiness of these helicopters in
France.
This helicopter model is
manufactured in France and is type
certificated for operation in the United
States under the provisions of 14 CFR
21.29 and the applicable bilateral
agreement. Pursuant to the applicable
bilateral agreement, France, through the
EASA, has kept the FAA informed of
the situation described above. The FAA
has 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.
Interested persons have been afforded
an opportunity to participate in the
making of this amendment. No
comments were received on the
proposal or the FAA’s determination of
the cost to the public. The FAA has
determined that air safety and the
public interest require the adoption of
the rule as proposed.
The FAA estimates that this AD will
affect 73 helicopters of U.S. registry.
The debonding inspection will take
approximately 0.25 work hours per
helicopter and replacing a collective
lever will take approximately 2 work
hours at an average labor rate of $80 per
work hour. If replacement is necessary,
required parts will cost approximately:
• $8,651 for a co-pilot twist grip
assembly, part number (P/N)
350A27521201;
• $12,542 for a pilot twist grip
assembly, P/N 350A27520903;
• $5 for a clamp, P/N ASNA0021;
• $2 for a bolt, P/N 22125BC050014L;
and
• $1 for a nut, P/N 22431BC050L.
Based on these figures, we estimate
the total cost impact of this AD on U.S.
operators to be $10,271, assuming one
co-pilot twist grip assembly is replaced
in one helicopter, that the twist grip
adjusting gage (tool) and spring scale
needed are on-site and available, and
that the co-pilot twist grip assembly is
not covered by warranty, and no pilot
twist grip assembly will need to be
replaced. The manufacturer has
indicated that parts are covered by
warranty up to 1,000 hours or 2 years
after the purchase of a new helicopter,
however, it indicated that labor is not
covered by a warranty.
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,
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16:13 Mar 21, 2008
Jkt 214001
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that the regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared an economic evaluation
of the estimated costs to comply with
this AD. See the AD docket to examine
the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
Section 106, describes the authority of
the FAA Administrator. Subtitle VII,
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701,
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends part 39 of the Federal Aviation
Regulations (14 CFR part 39) as follows:
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. Section 39.13 is amended by adding
a new airworthiness directive to read as
follows:
I
PO 00000
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Fmt 4700
Sfmt 4700
2008–06–22 Eurocopter France:
Amendment 39–15434. Docket No.
FAA–2007–28229; Directorate Identifier
2006–SW–23–AD.
Applicability: Model EC130 B4 helicopters,
with a twist grip assembly, part number
(P/N) 350A27520900, 350A27520901,
350A27520902, or 350A27520903, with a
serial number below 64, installed on the
pilot’s side, and a twist grip assembly, P/N
350A27521201, with a serial number below
67, installed on the co-pilot’s side,
certificated in any category.
Compliance: Required within 110 hours
time-in-service (TIS) or 4 months, whichever
occurs first, and before installing a
replacement collective lever with an affected
twist grip assembly on a helicopter, unless
accomplished previously.
To detect a reduced bonding strength of the
control pinion on the pilot and co-pilot
collective lever drive tubes, which could lead
to failure of a twist grip drive tube and
control pinion bonded attachment, resulting
in loss of engine throttle control and
subsequent loss of control of the helicopter,
accomplish the following:
(a) Inspect the pilot and co-pilot collective
levers for proper bonding between the twist
grip drive tubes and the control pinions in
accordance with paragraphs 2.B.1. and 2.B.2.
of the Accomplishment Instructions, in
Eurocopter, an EADS Company, Alert Service
Bulletin EC130 No. 76A001, dated February
10, 2006, except you are neither required to
contact the manufacturer nor return a noncompliant collective lever.
(b) If a twist grip turns when applying the
35N load to the twist grip, before further
flight, replace the collective lever with an
airworthy collective lever that has been
inspected in accordance with paragraph (a) of
this AD, or a collective lever with a twist grip
assembly that is not listed in the
Applicability of this AD.
(c) To request a different method of
compliance or a different compliance time
for this AD, follow the procedures in 14 CFR
39.19. Contact the Manager, Safety
Management Group, ATTN: Ed Cuevas,
Aviation Safety Engineer, Rotorcraft
Directorate, FAA, Fort Worth, Texas 76193–
0111, telephone (817) 222–5355, fax (817)
222–5961, for information about previously
approved alternative methods of compliance.
(d) The inspection and replacement, if
necessary, shall be done in accordance with
the specified portions of Eurocopter, an
EADS Company, Alert Service Bulletin
EC130 No. 76A001, dated February 10, 2006.
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 American
Eurocopter Corporation, 2701 Forum Drive,
Grand Prairie, Texas 75053–4005, telephone
(972) 641–3460, fax (972) 641–3527. Copies
may be inspected at the FAA, Office of the
Regional Counsel, Southwest Region, 2601
Meacham Blvd., Room 663, Fort Worth,
Texas or at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
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Federal Register / Vol. 73, No. 57 / Monday, March 24, 2008 / Rules and Regulations
(e) This amendment becomes effective on
April 28, 2008.
Note: The subject of this AD is addressed
in EASA (France) AD 2006–0079, dated April
3, 2006.
Issued in Fort Worth, Texas, on March 10,
2008.
Mark R. Schilling,
Acting Manager, Rotocraft Directorate,
Aircraft Certification Service.
[FR Doc. E8–5494 Filed 3–21–08; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–0303; Directorate
Identifier 2008–NM–047–AD; Amendment
39–15441; AD 2008–06–29]
RIN 2120–AA64
Airworthiness Directives; Boeing
Model 737–300, –400, and –500 Series
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
pwalker on PROD1PC71 with RULES
AGENCY:
SUMMARY: We are adopting a new
airworthiness directive (AD) for all
Boeing Model 737–300, –400, and –500
series airplanes. This AD requires
repetitive inspections of the downstop
assemblies on the main tracks of the No.
2, 3, 4, and 5 slats and the inboard track
of the No. 1 and 6 slats to verify if any
parts are missing, damaged, or in the
wrong order. This AD also requires
other specified actions, and related
investigative and corrective actions if
necessary. This AD results from reports
of fuel leaking from a puncture in the
slat track housing (referred to as the
‘‘slat can’’). We are issuing this AD to
detect and correct loose or missing parts
from the main slat track downstop
assemblies, which could puncture the
slat can and result in a fuel leak and
consequent fire.
DATES: This AD is effective April 8,
2008.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 8, 2008.
We must receive comments on this
AD by May 23, 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.
VerDate Aug<31>2005
16:13 Mar 21, 2008
Jkt 214001
• 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 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:
Nancy Marsh, Aerospace Engineer,
Airframe Branch, ANM–120S, FAA,
Seattle Aircraft Certification Office,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 917–6440; fax (425) 917–6590.
SUPPLEMENTARY INFORMATION;
Discussion
Boeing has notified us that it has
received numerous reports of fuel
leaking from the slat track housing
(referred to as the ‘‘slat can’’) on Boeing
Model 737–300, –400, and –500 series
airplanes. In all cases, there were no
reports of a fire as a result of the fuel
leaks on these airplane models. In some
of the reports, the fuel leak was caused
by loose or broken parts falling off the
downstop assembly into the slat can,
which were then subsequently driven
into the slat can by the retracting slat
track. This condition, if not corrected,
could puncture the slat can and result
in a fuel leak and consequent fire.
Other Related Rulemaking
On August 28, 2007, we issued
emergency AD 2007–18–52, amendment
39–15197, to address the same unsafe
condition on all Model 737–600, –700,
–700C, –800, –900, and –900ER series
airplanes. That AD was published in the
Federal Register on September 21, 2007
(72 FR 53928). That AD requires
repetitive detailed inspections of the
slat track downstop assemblies to verify
PO 00000
Frm 00011
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15397
that proper hardware is installed, onetime torquing of the nut and bolt, and
corrective actions if necessary. That AD
resulted from reports of parts coming off
the main slat track downstop assemblies
and a resultant fire. That AD was issued
to detect and correct loose or missing
parts from the main slat track downstop
assemblies, which could result in a fuel
leak and consequent fire.
Because the main slat track downstop
assemblies of Model 737 airplanes are
similar in design to those of other
Boeing airplane models, we have been
working with the manufacturer to
evaluate its remaining airplane models
to determine if a similar unsafe
condition exists on them. As a result,
we may consider additional rulemaking
as those evaluations are completed.
Relevant Service Information
We reviewed Boeing Alert Service
Bulletin 737–57A1301, dated February
5, 2008. The service bulletin describes
procedures for doing repetitive detailed
inspections of the downstop assemblies
on the main tracks of the No. 2, 3, 4, and
5 slats and the inboard track of the No.
1 and 6 slats to verify if any parts are
missing, damaged, or in the wrong
order. The service bulletin specifies that
the downstop assembly may be
inspected using a borescope. The
service bulletin also describes
procedures for doing other specified
actions, and doing related investigative
and corrective actions if necessary. The
other specified actions include a onetime torquing of the nut of the downstop
assembly and a detailed inspection of
the bolt to verify that the entire
chamfered portion of the bolt protrudes
beyond the outer surface of the nut. The
related investigative action is a detailed
inspection of the inside of the slat can
for loose parts and damage to the wall
of the slat can, which is done if any
downstop assembly part is missing or
damaged. The corrective actions include
the following:
• Removing any loose downstop
assembly part found in the slat can.
• Replacing any damaged slat can, or
contacting Boeing for repair
information.
• Replacing any missing or damaged
downstop assembly part with a new or
serviceable part.
• Removing and reinstalling the
downstop assembly if any downstop
assembly parts are in the wrong order,
or if the entire chamfered portion of the
bolt does not protrude beyond the outer
surface of the nut after it is torqued.
The service bulletin specifies doing
the initial inspection within 90 days
and repeating the inspection thereafter
at intervals not to exceed 4,500 flight
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]]>Agencies
[Federal Register Volume 73, Number 57 (Monday, March 24, 2008)]
[Rules and Regulations]
[Pages 15395-15397]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-5494]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2007-28229; Directorate Identifier 2006-SW-23-AD;
Amendment 39-15434; AD 2008-06-22]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Model EC130 B4
Helicopters
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD) for
the specified Eurocopter France (Eurocopter) Model EC 130 B4
helicopters, with certain twist grip assemblies installed, that
requires inspecting the pilot and co-pilot collective levers for proper
bonding between the twist grip drive tubes and the control pinions and
if debonding is present, replacing the collective levers before further
flight. This amendment is prompted by one incident in which the engine
remained at idle speed although the twist grip had been turned to the
flight position. The actions specified by this AD are intended to
detect debonding between the twist grip drive tubes and the control
pinions on the pilot and co-pilot collective levers to prevent loss of
cockpit throttle control of the engine, and subsequent loss of control
of the helicopter.
DATES: Effective April 28, 2008.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 28, 2008.
ADDRESSES: You may get the service information identified in this AD
from American Eurocopter Corporation, 2701 Forum Drive, Grand Prairie,
Texas 75053-4005, telephone (972) 641-3460, fax (972) 641-3527.
Examining the Docket: You may examine the docket that contains this
AD, any comments, and other information on the Internet at https://
www.regulations.gov or at the Docket Operations office, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Ed Cuevas, Aviation Safety Engineer,
FAA, Rotorcraft Directorate, Safety Management Group, Fort Worth, Texas
76193-0111, telephone (817) 222-5355, fax (817) 222-5961.
SUPPLEMENTARY INFORMATION: A proposal to amend 14 CFR part 39 to
include an AD for the specified model helicopters was published in the
Federal Register on May 21, 2007 (72 FR 28456). That action proposed to
require, within 110 hours time-in-service (TIS) or 4 months, whichever
occurs first, or before installing a collective lever with an affected
grip assembly on a helicopter, inspecting the bonding between the twist
grip drive tube and the control pinion on both the pilot and co-pilot
collective lever. If debonding is present, replacing the collective
lever before further flight was proposed.
The European Aviation Safety Agency (EASA) notified us that an
unsafe condition may exist on Eurocopter Model EC 130 B4 helicopters,
with a twist grip assembly, part number (P/N) 350A27520900,
350A27520901, 350A27520902, or 350A27520903, with a serial number below
64, installed on the pilot's side, and a twist grip assembly, P/N
350A27521201, with a serial number below 67, installed on the co-
pilot's side. EASA advises that analysis of an incident that occurred
during autorotation training revealed a failure of the twist grip drive
tube and control pinion bonded attachment. The engine remained at idle
speed although the twist grip had been turned back to the flight
position. The autorotation procedure continued to the ground without
damage to the helicopter. The failure has been attributed to non-
compliant surface preparation during manufacture.
Eurocopter, an EADS Company, has issued Alert Service Bulletin
EC130 No. 76A001, dated February 10, 2006, which specifies a check by
use of a twist grip adjusting gauge of the bonding between the twist
grip drive tube and the control pinion on both the pilot and co-pilot
collective lever. EASA classified this service bulletin as mandatory
and issued AD No. 2006-0079, dated April
[[Page 15396]]
3, 2006, to ensure the continued airworthiness of these helicopters in
France.
This helicopter model is manufactured in France and is type
certificated for operation in the United States under the provisions of
14 CFR 21.29 and the applicable bilateral agreement. Pursuant to the
applicable bilateral agreement, France, through the EASA, has kept the
FAA informed of the situation described above. The FAA has 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.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
The FAA estimates that this AD will affect 73 helicopters of U.S.
registry. The debonding inspection will take approximately 0.25 work
hours per helicopter and replacing a collective lever will take
approximately 2 work hours at an average labor rate of $80 per work
hour. If replacement is necessary, required parts will cost
approximately:
$8,651 for a co-pilot twist grip assembly, part number (P/
N) 350A27521201;
$12,542 for a pilot twist grip assembly, P/N 350A27520903;
$5 for a clamp, P/N ASNA0021;
$2 for a bolt, P/N 22125BC050014L; and
$1 for a nut, P/N 22431BC050L.
Based on these figures, we estimate the total cost impact of this
AD on U.S. operators to be $10,271, assuming one co-pilot twist grip
assembly is replaced in one helicopter, that the twist grip adjusting
gage (tool) and spring scale needed are on-site and available, and that
the co-pilot twist grip assembly is not covered by warranty, and no
pilot twist grip assembly will need to be replaced. The manufacturer
has indicated that parts are covered by warranty up to 1,000 hours or 2
years after the purchase of a new helicopter, however, it indicated
that labor is not covered by a warranty.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD will not have a
substantial direct effect on the States, on the relationship between
the national Government and the States, or on the distribution of power
and responsibilities among the various levels of government.
For the reasons discussed above, I certify that the regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared an economic evaluation of the estimated costs to comply
with this AD. See the AD docket to examine the economic evaluation.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, Section 106, describes the
authority of the FAA Administrator. Subtitle VII, Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701, ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends part 39 of
the Federal Aviation Regulations (14 CFR part 39) as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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. Section 39.13 is amended by adding a new airworthiness directive to
read as follows:
2008-06-22 Eurocopter France: Amendment 39-15434. Docket No.
FAA-2007-28229; Directorate Identifier 2006-SW-23-AD.
Applicability: Model EC130 B4 helicopters, with a twist grip
assembly, part number (P/N) 350A27520900, 350A27520901,
350A27520902, or 350A27520903, with a serial number below 64,
installed on the pilot's side, and a twist grip assembly, P/N
350A27521201, with a serial number below 67, installed on the co-
pilot's side, certificated in any category.
Compliance: Required within 110 hours time-in-service (TIS) or 4
months, whichever occurs first, and before installing a replacement
collective lever with an affected twist grip assembly on a
helicopter, unless accomplished previously.
To detect a reduced bonding strength of the control pinion on
the pilot and co-pilot collective lever drive tubes, which could
lead to failure of a twist grip drive tube and control pinion bonded
attachment, resulting in loss of engine throttle control and
subsequent loss of control of the helicopter, accomplish the
following:
(a) Inspect the pilot and co-pilot collective levers for proper
bonding between the twist grip drive tubes and the control pinions
in accordance with paragraphs 2.B.1. and 2.B.2. of the
Accomplishment Instructions, in Eurocopter, an EADS Company, Alert
Service Bulletin EC130 No. 76A001, dated February 10, 2006, except
you are neither required to contact the manufacturer nor return a
non-compliant collective lever.
(b) If a twist grip turns when applying the 35N load to the
twist grip, before further flight, replace the collective lever with
an airworthy collective lever that has been inspected in accordance
with paragraph (a) of this AD, or a collective lever with a twist
grip assembly that is not listed in the Applicability of this AD.
(c) To request a different method of compliance or a different
compliance time for this AD, follow the procedures in 14 CFR 39.19.
Contact the Manager, Safety Management Group, ATTN: Ed Cuevas,
Aviation Safety Engineer, Rotorcraft Directorate, FAA, Fort Worth,
Texas 76193-0111, telephone (817) 222-5355, fax (817) 222-5961, for
information about previously approved alternative methods of
compliance.
(d) The inspection and replacement, if necessary, shall be done
in accordance with the specified portions of Eurocopter, an EADS
Company, Alert Service Bulletin EC130 No. 76A001, dated February 10,
2006. 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 American Eurocopter
Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005,
telephone (972) 641-3460, fax (972) 641-3527. Copies may be
inspected at the FAA, Office of the Regional Counsel, Southwest
Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas or at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: https://www.archives.gov/federal_register/code_of_federal_
regulations/ibr_locations.html.
[[Page 15397]]
(e) This amendment becomes effective on April 28, 2008.
Note: The subject of this AD is addressed in EASA (France) AD
2006-0079, dated April 3, 2006.
Issued in Fort Worth, Texas, on March 10, 2008.
Mark R. Schilling,
Acting Manager, Rotocraft Directorate, Aircraft Certification Service.
[FR Doc. E8-5494 Filed 3-21-08; 8:45 am]
BILLING CODE 4910-13-P
