Airworthiness Directives; Eurocopter France Helicopters, 23107-23109 [2013-08763]
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Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations
be counted from the date of installation of the
MLG wheel axle on an airplane, which
occurs after the date of repair specified in the
Part 1 of Appendix 1 of Airbus AOT A330–
32A–3256, Revision 01, dated October 18,
2012 (for Model A330–200 and –300 series
airplanes); or Airbus AOT A340–32A–4292,
Revision 01, dated October 18, 2012 (for
Model A340–200 and –300 series airplanes).
TABLE 2 TO PARAGRAPH (h)(2) OF THIS AD—POST-REPAIR MLG WHEEL AXLE FLIGHT HOURS OR LANDINGS
Post-repair MLG wheel axle flight hours or
landings, whichever occurs first, not to be
exceeded (see paragraph (h)(2) of this
AD)
Affected airplanes
Model
Model
Model
Model
Model
Model
A340–311, –312, and –313 airplanes, WV00 .............................................................................
A340–211, –212, and –213 airplanes, WV00 .............................................................................
A340–313 airplanes, WV02 and WV05 .......................................................................................
A330–301, –321, –322, –341, and –342 airplanes, WV00 and WV01 .......................................
A330–201, –202, –203, –223, and –243 airplanes, WV02, WV05, and WV06 ..........................
A330–301, –302, –303, –323, –342, and –343 airplanes, WV02 and WV05 .............................
(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.
(j) Credit for Previous Actions
This paragraph provides credit for the
actions required by paragraph (h) of this AD
with respect to the affected MLG wheel axle
defined in paragraph (g)(1) of this AD, if
those actions were performed before the
effective date of this AD using the applicable
service information specified in paragraph
(j)(1) or (j)(2) of this AD, which is not
incorporated by reference in this AD.
(1) Airbus All Operator Telex A330–
32A3256, including Appendix 1, dated
August 24, 2011 (for Model A330–200 and
–300 series airplanes).
(2) Airbus All Operator Telex A340–
32A4292, including Appendix 1, dated
August 24, 2011 (for Model A340–200 and
–300 series airplanes).
TKELLEY on DSK3SPTVN1PROD with RULES
(i) Parts Installation Limitation
As of the effective date of this AD: An
affected MLG wheel axle may be installed on
an airplane, provided the MLG wheel axle
has not exceeded the limits specified in table
1 to paragraph (h)(1) of this AD and it is
replaced with a serviceable part before
reaching the life limit defined in table 1 to
paragraph (h)(1) of this AD.
(l) Related Information
(1) Refer to MCAI European Aviation
Safety Agency Airworthiness Directive 2011–
0170, dated September 7, 2011, and the
service information specified in paragraphs
(l)(1)(i) and (l)(1)(ii) of this AD, for related
information.
(i) Airbus AOT A330–32A–3256, Revision
01, including Appendix 1, dated October 18,
2012.
(ii) Airbus AOT A340–32A–4292, Revision
01, including Appendix 1, dated October 18,
2012.
(2) For service information identified in
this AD, contact Airbus SAS—Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(k) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–1138; fax (425)
227–1149. Information may be emailed to: 9ANM-116-AMOC-REQUESTS@faa.gov.
Before using any approved AMOC, notify
your appropriate principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office/
certificate holding district office. The AMOC
approval letter must specifically reference
this AD.
VerDate Mar<15>2010
16:07 Apr 17, 2013
Jkt 229001
(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Airbus Alert Operators Transmission
(AOT) A330–32A–3256, Revision 01,
including Appendix 1, dated October 18,
2012. The Document number and revision
level are not identified on pages 2–5 of this
AOT; the revision date is identified on only
page 1 of this AOT and the first page of
Appendix 1 of this AOT.
(ii) AOT A340–32A–4292, Revision 01,
including Appendix 1, dated October 18,
2012. The Document number and revision
level are not identified on pages 2–5 of this
AOT; the revision date is identified on only
page 1 of this AOT and the first page of
Appendix 1 of this AOT.
(3) For service information identified in
this AD, contact Airbus SAS—Airworthiness
PO 00000
Frm 00003
Fmt 4700
Sfmt 4700
7,830
7,660
6,580
8,410
7,410
8,580
landings
landings
landings
landings
landings
landings
or
or
or
or
or
or
37,080
48,330
28,160
25,330
29,830
22,580
flight
flight
flight
flight
flight
flight
hours.
hours.
hours.
hours.
hours.
hours.
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@airbus.com;
Internet https://www.airbus.com.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of
this material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference 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/ibrlocations.html.
Issued in Renton, Washington, on April 5,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–08741 Filed 4–17–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1087; Directorate
Identifier 2009–SW–32–AD; Amendment 39–
17424; AD 2013–08–07]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter France (ECF) Model
AS332C, L, and L1 helicopters to
require an initial and repetitive
inspections of the outer skin, butt strap,
and fuselage frame for a crack and
modification of the helicopter. This AD
was prompted by an AD issued by the
SUMMARY:
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Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations
in the sliding cowling right-hand and
left-hand rail attachment areas on Frame
5295, and if there is a crack, inspecting
for a crack in Frame 5295 and repairing
any cracked part. The NPRM also
proposed to require modifying each
helicopter with MOD 0726478R2 on the
sliding cowling rails and shims in the
attachment areas on Frame 5295. The
proposed requirements were intended to
detect a crack, to prevent loss of
airframe structural integrity and
subsequent loss of control of the
helicopter.
EASA issued EASA AD No. 2008–
0035–E, dated February 21, 2008, to
correct an unsafe condition for the ECF
Model AS 332 C, C1, L, and L1
helicopters. EASA advises that a crack
was discovered on an ECF Model
AS332L helicopter in fuselage frame
5295, which has plates and angles
assembled by riveting that corresponds
to the first generation frame (before
MOD 0722907). The crack in the frame
was found because of a crack in the
outer skin and in the butt strap where
the rail of the main gear box (MGB)
sliding cowling is attached to the frame.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, any
incorporated-by-reference service
information, the economic evaluation,
any comments received, and other
information. The street address for the
Docket Operations Office (phone: 800–
647–5527) is U.S. Department of
Transportation, Docket Operations
Office, M–30, West Building Ground
Floor, Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary
Roach, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
gary.b.roach@faa.gov.
SUPPLEMENTARY INFORMATION:
TKELLEY on DSK3SPTVN1PROD with RULES
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, which states that a crack was
discovered in a fuselage frame during a
daily check. The actions of this AD are
intended to detect a crack, to prevent
loss of airframe structural integrity and
subsequent loss of control of the
helicopter.
DATES: This AD is effective May 23,
2013.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of May 23, 2013.
ADDRESSES: For service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, Texas 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.eurocopter.com/techpub. You may
review the referenced service
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we did not receive any comments on the
NPRM (77 FR 63262, October 16, 2012).
Discussion
On October 16, 2012, at 77 FR 63262,
the Federal Register published our
Notice of Proposed Rulemaking
(NPRM), which proposed to amend 14
CFR part 39 to include an AD that
would apply to certain ECF Model
AS332C, L, and L1 helicopters without
modification (MOD) 0722907. That
NPRM proposed to require an initial
and repetitive visual inspections for a
crack in the outer skin and the butt strap
VerDate Mar<15>2010
16:07 Apr 17, 2013
Jkt 229001
FAA’s Determination
These helicopters have been approved
by the aviation authority of France and
are approved for operation in the United
States. Pursuant to our bilateral
agreement with France, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
safety and the public interest require
adopting the AD requirements as
proposed, except we have updated the
contact information for American
Eurocopter Corporation. This minor
editorial change is consistent with the
intent of the proposals in the NPRM (77
FR 63262, October 16, 2012) and will
not increase the economic burden on
any operator nor increase the scope of
the AD.
Differences Between This AD and the
EASA AD
This AD requires you to repair Frame
5295 before further flight rather than
contacting the manufacturer. This AD
refers to a check as an inspection to be
performed by a mechanic versus a check
PO 00000
Frm 00004
Fmt 4700
Sfmt 4700
that a pilot can do if specifically
allowed by the AD. This AD also does
not list the Model AS332C1 in the
applicability because this model is not
type certificated in the U.S. This AD
also does not allow further flight with
the outer skin or butt strap cracked
unless it is a ferry flight to a repair
facility.
Related Service Information
Eurocopter has issued Alert Service
Bulletin No. 05.00.76, Revision 0, dated
February 20, 2008 (ASB), which
specifies checking for a crack on the
outside of the helicopter, on the skin,
and the butt strap near the sliding
cowling rail attachment. If a crack is
found in the outer skin or butt strap, the
ASB specifies visually checking for a
crack in Frame 5295. The ASB specifies
doing MOD 0726478R2, which consists
of cutting out a section of the sliding
cowling rails. This cut-out exposes the
splice near the rail attachment holes,
making it easier to detect a crack in the
frame during the 10-hour repetitive
inspection and thus reducing the risks
of a crack going undetected in Frame
5295. Also, the ASB specifies contacting
the manufacturer for the ‘‘appropriate
repair sheet according to how the crack
is situated’’ if there is a crack in Area
1 of Frame 5295. EASA classified this
ASB as mandatory and issued AD No.
2008–0035–E, dated February 21, 2008,
to ensure the continued airworthiness of
these helicopters.
Costs of Compliance
We estimate that this AD will affect 5
helicopters of U.S. Registry. We estimate
that operators may incur the following
costs in order to comply with this AD.
We estimate that it will take about 4.25
work-hours per helicopter to initially
inspect for a crack and to modify the
MGB sliding cowling rails. Each 10-hour
repetitive inspection will take about
0.25 work-hour. The average labor rate
is $85 per work-hour and required parts
will cost about $1,793 per helicopter.
Based on these figures, we estimate the
cost of this AD on U.S. operators will be
$17,145 or $3,429 per helicopter,
assuming 60 repetitive inspections will
be performed each year and assuming
the entire fleet is modified and no
cracks are found.
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.
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Federal Register / Vol. 78, No. 75 / Thursday, April 18, 2013 / Rules and Regulations
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
helicopters identified in this rulemaking
action.
Regulatory Findings
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
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation
in Alaska to the extent that it justifies
making a regulatory distinction; and
(4) 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 and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
TKELLEY on DSK3SPTVN1PROD with RULES
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2013–08–07 Eurocopter France:
Amendment 39–17424; Docket No.
VerDate Mar<15>2010
16:07 Apr 17, 2013
Jkt 229001
FAA–2012–1087; Directorate Identifier
2009–SW–32–AD.
(a) Applicability
This AD applies to all Model AS332C, L,
and L1 helicopters without modification
(MOD) 0722907, except helicopters with
serial numbers 2078 and 2102, certificated in
any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in the outer skin, butt strap, or fuselage
frame, which could result in loss of airframe
structural integrity, and subsequent loss of
control of the helicopter.
23109
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, we suggest that
you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office, before
operating any aircraft complying with this
AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in
European Aviation Safety Agency (France)
AD No. 2008–0035–E, dated February 21,
2008.
(c) Effective Date
This AD becomes effective May 23, 2013.
(i) Subject
(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(j) Material Incorporated by Reference
(e) Required Actions
(1) Within 10 hours time-in-service (TIS)
for helicopters that have 8,800 or more hours
TIS or before or upon reaching 8,810 hours
TIS for helicopters that have less than 8,800
hours TIS, and thereafter at intervals not to
exceed 10 hours TIS, visually inspect for a
crack on the outer skin and the butt strap in
the sliding cowling right-hand and left-hand
rail attachment areas on Frame 5295 as
shown in Figure 2 of Eurocopter Alert
Service Bulletin No. 05.00.76, Revision 0,
dated February 20, 2008 (ASB).
(i) If there is a crack in the outer skin or
in the butt strap per paragraph (e)(1) of this
AD, before further flight, inspect for a crack
in Frame 5295 in the areas shown in Figure
3, Area 1, and Figure 4, of the ASB.
(ii) If there is a crack in the outer skin, the
butt strap, or in Frame 5295 in the areas
inspected as required by this AD, before
further flight, repair the part in accordance
with a method approved by the FAA.
(2) Within 300 hours TIS, for each
helicopter that has 8,800 or more hours TIS,
modify the sliding cowling rails and shims in
the attachment areas on Frame 5295
(corresponds to MOD 0726478R2), as
depicted in Figure 5 and by following the
Accomplishment Instructions, paragraph
2.B.3., of the ASB.
(f) Special Flight Permits
A special flight permit is permitted for a
helicopter with a crack in the outer skin or
butt strap to operate the helicopter to a
location where the requirements of this AD
can be accomplished. A special flight permit
is not permitted for a helicopter with a crack
in Frame 5295.
(g) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Safety Management
Group, FAA, may approve AMOCs for this
AD. Send your proposal to: Gary Roach,
Aviation Safety Engineer, Regulations and
Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
gary.b.roach@faa.gov.
PO 00000
Frm 00005
Fmt 4700
Sfmt 9990
Joint Aircraft Service Component (JASC)
Code: 5311, Fuselage, Main Frame.
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No.
05.00.76, Revision 0, dated February 20,
2008.
(ii) Reserved.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, Texas 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
641–3775; or at https://www.eurocopter.com/
techpub.
(4) You may view this service information
at FAA, Office of the Regional Counsel,
Southwest Region, 2601 Meacham Blvd.,
Room 663, Fort Worth, Texas 76137. For
information on the availability of this
material at the FAA, call (817) 222–5110.
(5) You may view this service information
that is incorporated by reference 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/ibrlocations.html.
Issued in Fort Worth, Texas, on April 8,
2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2013–08763 Filed 4–17–13; 8:45 am]
BILLING CODE 4910–13–P
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18APR1
]]>Agencies
[Federal Register Volume 78, Number 75 (Thursday, April 18, 2013)]
[Rules and Regulations]
[Pages 23107-23109]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-08763]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1087; Directorate Identifier 2009-SW-32-AD;
Amendment 39-17424; AD 2013-08-07]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (ECF) Model AS332C, L, and L1 helicopters to require
an initial and repetitive inspections of the outer skin, butt strap,
and fuselage frame for a crack and modification of the helicopter. This
AD was prompted by an AD issued by the
[[Page 23108]]
European Aviation Safety Agency (EASA), which is the Technical Agent
for the Member States of the European Union, which states that a crack
was discovered in a fuselage frame during a daily check. The actions of
this AD are intended to detect a crack, to prevent loss of airframe
structural integrity and subsequent loss of control of the helicopter.
DATES: This AD is effective May 23, 2013.
The Director of the Federal Register approved the incorporation by
reference of a certain document listed in this AD as of May 23, 2013.
ADDRESSES: For service information identified in this AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie,
Texas 75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-
3775; or at https://www.eurocopter.com/techpub. You may review the
referenced service information at the FAA, Office of the Regional
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth,
Texas 76137.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, any incorporated-by-reference
service information, the economic evaluation, any comments received,
and other information. The street address for the Docket Operations
Office (phone: 800-647-5527) is U.S. Department of Transportation,
Docket Operations Office, M-30, West Building Ground Floor, Room W12-
140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Gary Roach, Aviation Safety Engineer,
Regulations and Policy Group, Rotorcraft Directorate, FAA, 2601 Meacham
Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; email
gary.b.roach@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On October 16, 2012, at 77 FR 63262, the Federal Register published
our Notice of Proposed Rulemaking (NPRM), which proposed to amend 14
CFR part 39 to include an AD that would apply to certain ECF Model
AS332C, L, and L1 helicopters without modification (MOD) 0722907. That
NPRM proposed to require an initial and repetitive visual inspections
for a crack in the outer skin and the butt strap in the sliding cowling
right-hand and left-hand rail attachment areas on Frame 5295, and if
there is a crack, inspecting for a crack in Frame 5295 and repairing
any cracked part. The NPRM also proposed to require modifying each
helicopter with MOD 0726478R2 on the sliding cowling rails and shims in
the attachment areas on Frame 5295. The proposed requirements were
intended to detect a crack, to prevent loss of airframe structural
integrity and subsequent loss of control of the helicopter.
EASA issued EASA AD No. 2008-0035-E, dated February 21, 2008, to
correct an unsafe condition for the ECF Model AS 332 C, C1, L, and L1
helicopters. EASA advises that a crack was discovered on an ECF Model
AS332L helicopter in fuselage frame 5295, which has plates and angles
assembled by riveting that corresponds to the first generation frame
(before MOD 0722907). The crack in the frame was found because of a
crack in the outer skin and in the butt strap where the rail of the
main gear box (MGB) sliding cowling is attached to the frame.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (77 FR 63262,
October 16, 2012).
FAA's Determination
These helicopters have been approved by the aviation authority of
France and are approved for operation in the United States. Pursuant to
our bilateral agreement with France, EASA, its technical
representative, has notified us of the unsafe condition described in
the EASA AD. We are issuing this AD because we evaluated all
information provided by EASA and determined the unsafe condition exists
and is likely to exist or develop on other helicopters of these same
type designs and that air safety and the public interest require
adopting the AD requirements as proposed, except we have updated the
contact information for American Eurocopter Corporation. This minor
editorial change is consistent with the intent of the proposals in the
NPRM (77 FR 63262, October 16, 2012) and will not increase the economic
burden on any operator nor increase the scope of the AD.
Differences Between This AD and the EASA AD
This AD requires you to repair Frame 5295 before further flight
rather than contacting the manufacturer. This AD refers to a check as
an inspection to be performed by a mechanic versus a check that a pilot
can do if specifically allowed by the AD. This AD also does not list
the Model AS332C1 in the applicability because this model is not type
certificated in the U.S. This AD also does not allow further flight
with the outer skin or butt strap cracked unless it is a ferry flight
to a repair facility.
Related Service Information
Eurocopter has issued Alert Service Bulletin No. 05.00.76, Revision
0, dated February 20, 2008 (ASB), which specifies checking for a crack
on the outside of the helicopter, on the skin, and the butt strap near
the sliding cowling rail attachment. If a crack is found in the outer
skin or butt strap, the ASB specifies visually checking for a crack in
Frame 5295. The ASB specifies doing MOD 0726478R2, which consists of
cutting out a section of the sliding cowling rails. This cut-out
exposes the splice near the rail attachment holes, making it easier to
detect a crack in the frame during the 10-hour repetitive inspection
and thus reducing the risks of a crack going undetected in Frame 5295.
Also, the ASB specifies contacting the manufacturer for the
``appropriate repair sheet according to how the crack is situated'' if
there is a crack in Area 1 of Frame 5295. EASA classified this ASB as
mandatory and issued AD No. 2008-0035-E, dated February 21, 2008, to
ensure the continued airworthiness of these helicopters.
Costs of Compliance
We estimate that this AD will affect 5 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. We estimate that it will take about 4.25
work-hours per helicopter to initially inspect for a crack and to
modify the MGB sliding cowling rails. Each 10-hour repetitive
inspection will take about 0.25 work-hour. The average labor rate is
$85 per work-hour and required parts will cost about $1,793 per
helicopter. Based on these figures, we estimate the cost of this AD on
U.S. operators will be $17,145 or $3,429 per helicopter, assuming 60
repetitive inspections will be performed each year and assuming the
entire fleet is modified and no cracks are found.
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.
[[Page 23109]]
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 helicopters identified in this
rulemaking action.
Regulatory Findings
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 DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
(3) Will not affect intrastate aviation in Alaska to the extent
that it justifies making a regulatory distinction; and
(4) 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 and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
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 airworthiness
directive (AD):
2013-08-07 Eurocopter France: Amendment 39-17424; Docket No. FAA-
2012-1087; Directorate Identifier 2009-SW-32-AD.
(a) Applicability
This AD applies to all Model AS332C, L, and L1 helicopters
without modification (MOD) 0722907, except helicopters with serial
numbers 2078 and 2102, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as a crack in the outer
skin, butt strap, or fuselage frame, which could result in loss of
airframe structural integrity, and subsequent loss of control of the
helicopter.
(c) Effective Date
This AD becomes effective May 23, 2013.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) Within 10 hours time-in-service (TIS) for helicopters that
have 8,800 or more hours TIS or before or upon reaching 8,810 hours
TIS for helicopters that have less than 8,800 hours TIS, and
thereafter at intervals not to exceed 10 hours TIS, visually inspect
for a crack on the outer skin and the butt strap in the sliding
cowling right-hand and left-hand rail attachment areas on Frame 5295
as shown in Figure 2 of Eurocopter Alert Service Bulletin No.
05.00.76, Revision 0, dated February 20, 2008 (ASB).
(i) If there is a crack in the outer skin or in the butt strap
per paragraph (e)(1) of this AD, before further flight, inspect for
a crack in Frame 5295 in the areas shown in Figure 3, Area 1, and
Figure 4, of the ASB.
(ii) If there is a crack in the outer skin, the butt strap, or
in Frame 5295 in the areas inspected as required by this AD, before
further flight, repair the part in accordance with a method approved
by the FAA.
(2) Within 300 hours TIS, for each helicopter that has 8,800 or
more hours TIS, modify the sliding cowling rails and shims in the
attachment areas on Frame 5295 (corresponds to MOD 0726478R2), as
depicted in Figure 5 and by following the Accomplishment
Instructions, paragraph 2.B.3., of the ASB.
(f) Special Flight Permits
A special flight permit is permitted for a helicopter with a
crack in the outer skin or butt strap to operate the helicopter to a
location where the requirements of this AD can be accomplished. A
special flight permit is not permitted for a helicopter with a crack
in Frame 5295.
(g) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Gary Roach, Aviation Safety
Engineer, Regulations and Policy Group, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-
5110; email gary.b.roach@faa.gov.
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest that you
notify your principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office or
certificate holding district office, before operating any aircraft
complying with this AD through an AMOC.
(h) Additional Information
The subject of this AD is addressed in European Aviation Safety
Agency (France) AD No. 2008-0035-E, dated February 21, 2008.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5311, Fuselage,
Main Frame.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(i) Eurocopter Alert Service Bulletin No. 05.00.76, Revision 0,
dated February 20, 2008.
(ii) Reserved.
(3) For Eurocopter service information identified in this AD,
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand
Prairie, Texas 75052; telephone (972) 641-0000 or (800) 232-0323;
fax (972) 641-3775; or at https://www.eurocopter.com/techpub.
(4) You may view this service information at FAA, Office of the
Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663,
Fort Worth, Texas 76137. For information on the availability of this
material at the FAA, call (817) 222-5110.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call (202) 741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on April 8, 2013.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2013-08763 Filed 4-17-13; 8:45 am]
BILLING CODE 4910-13-P
