Airworthiness Directives; Eurocopter France Helicopters, 70202-70205 [2013-27637]
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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations
(d) Subject
Air Transport Association of America
(ATA) Code 28: Fuel.
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(e) Reason
This AD was prompted by mandatory
continuing airworthiness information (MCAI)
originated by an aviation authority of another
country to identify and correct an unsafe
condition on an aviation product. The MCAI
describes the unsafe condition as a defective
sealing of a tapped through bore hole at the
inside of the fuel tank openings in
combination with prolonged periods at
maximum fuel level. We are issuing this AD
to detect and correct a defective sealing of a
tapped through bore hole at the inside of the
fuel tank openings, which if not detected and
corrected, could cause long-term structural
degradation of the wing structure.
(f) Actions and Compliance
Unless already done, do the following
actions, as specified in paragraphs (f)(1)
through (f)(6), including subparagraphs, of
this AD:
Note 1 to paragraph (f) of this AD: The
service information referenced in this AD
contains German to English translation. The
MCAI cites the English translation. The
following is the English to German
translation of the service information
entitled: AQUILA Aviation GmbH
Vorgeschrieben Technische Mitteilung SB–
AT01–027, dated August 15, 2013 (English
translation: AQUILA Aviation GmbH
Mandatory Service Bulletin SB–AT01–027,
Issue A.02, dated August 15, 2013). For
paragraphs (f)(1) through (f)(6), the service
information will be cited using the English
translation.
(1) Within 100 hours time-in-service (TIS)
after December 30, 2013 (the effective date of
this AD) or 3 months after December 30, 2013
(the effective date of this AD), whichever
occurs first, and repetitively thereafter at
intervals not to exceed 12 months, visually
inspect the left hand (LH) and right hand
(RH) wing tank areas following paragraph (1)
of the Actions section of AQUILA Aviation
GmbH Mandatory Service Bulletin SB–
AT01–027, Issue A.02, dated August 15,
2013.
(2) Concurrent with the initial inspection
required in paragraph (f)(1) of this AD, seal
the tapped through bore holes inside the LH
and RH fuel tank openings following
paragraph (2) of the Actions section of
AQUILA Aviation GmbH Mandatory Service
Bulletin SB–AT01–027, Issue A.02, dated
August 15, 2013.
(3) If, during any subsequent inspection
required in paragraph (f)(1) of this AD, a
tapped through bore hole inside the LH or
RH fuel tank opening is found to be
improperly sealed, within the next 100 hours
TIS after detecting the improper seal or 3
months after detecting the improper seal,
whichever occurs first, renew the sealing of
the affected bore hole following paragraph (2)
of the Actions section of AQUILA Aviation
GmbH Mandatory Service Bulletin SB–
AT01–027, Issue A.02, dated August 15,
2013.
(4) If, during any inspection required in
paragraph (f)(1) of this AD, the upper wing
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shells show damaged finishing in the tank
areas, before further flight, contact AQUILA
Aviation GmbH following paragraph (3) of
the Actions section of AQUILA Aviation
GmbH Mandatory Service Bulletin SB–
AT01–027, Issue A.02, dated August 15,
2013, at the address identified in paragraph
(i)(3) of this AD for an approved repair
scheme and, accomplish the repair scheme
before further flight.
(5) Accomplishment of corrective actions
required in paragraph (f)(3) or (f)(4) of this
AD does not constitute terminating action for
the repetitive inspections required by
paragraph (f)(1) of this AD.
(6) After accomplishment of the required
initial inspection and sealing in paragraphs
(f)(1) and (f)(2) of this AD, compliance with
the requirements of this AD can be
demonstrated by:
(i) Revising the approved Aircraft
Maintenance Program (AMP) and standard
practices (Instructions for Continued
Airworthiness) on the basis of which the
operator or the owner ensures the continuing
airworthiness of each airplane: Incorporate
the repetitive 12 calendar month visual
inspection of the LH and RH wing tank areas
required in paragraph (f)(1) of this AD,
Actions section of AQUILA Aviation GmbH
Mandatory Service Bulletin SB–AT01–027,
Issue A.02, dated August 15, 2013; and
(ii) Complying with the approved AMP
described in paragraph (f)(6)(i) of this AD.
(g) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, Standards Office,
FAA, has the authority to approve AMOCs
for this AD, if requested using the procedures
found in 14 CFR 39.19. Send information to
ATTN: Doug Rudolph, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust,
Room 301, Kansas City, Missouri 64106;
telephone: (816) 329–4059; fax: (816) 329–
4090; email: doug.rudolph@faa.gov. Before
using any approved AMOC on any airplane
to which the AMOC applies, notify your
appropriate principal inspector (PI) in the
FAA Flight Standards District Office (FSDO),
or lacking a PI, your local FSDO.
(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 FAAapproved 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.
(h) Related Information
Refer to MCAI European Aviation Safety
Agency (EASA) AD No. 2013–0236, dated
September 25, 2013, for related information.
You may examine the MCAI on the Internet
at https://www.regulations.gov by searching
for and locating it in Docket No. FAA–2013–
0963.
(i) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
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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) AQUILA Aviation GmbH
Vorgeschrieben Technische Mitteilung SB–
AT01–027, dated August 15, 2013 (English
translation: AQUILA Aviation GmbH
Mandatory Service Bulletin SB–AT01–027,
Issue A.02, dated August 15, 2013).
Note 2 to paragraph (i)(2)(i) of this AD:
This service information contains German to
English translation. EASA used the English
translation in referencing the documents
from AQUILA Aviation GmbH. For
enforceability purposes, we will refer to the
AQUILA Aviation GmbH service information
as the titles appear on the documents.
(ii) Reserved.
(3) For AQUILA—Aviation by Excellence
AG service information identified in this AD,
contact AQUILA Aviation GmbH, OT
Schoenhagen, Flugplatz, D–14959 Trebbin,
Germany; phone: +49-(0) 33731–707–0; fax:
+49 (0) 33731–707–11; Internet: https://
www.aquila-aviation.de/; email:
maintenance@aquila-aviation.de.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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 Kansas City, Missouri, on
November 5, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–27914 Filed 11–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0354; Directorate
Identifier 2011–SW–072–AD; Amendment
39–17665; AD 2013–23–10]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
France Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2010–
21–01 for Eurocopter France
(Eurocopter) Model AS350B, BA, B1,
B2, B3, D, AS355E, F, F1, F2, and N
SUMMARY:
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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations
helicopters. AD 2010–21–01 required an
inspection to determine whether a
cross-member is installed at station X
2165 and doublers at X 2325 and Y 269,
and installing them if they are missing.
This new AD retains the requirements of
AD 2010–21–01 but clarifies the
inspection procedures and limits the
applicability to only those helicopters
with collective-to-yaw control coupling.
This AD is prompted by a crack
discovered in the area of the center
cross-member at station X 2325, at the
attachment point of the yaw channel
ball-type control sheath stop, of a Model
AS355N helicopter fitted with the
collective-to-yaw control coupling. The
actions of this AD are intended to
prevent reduced yaw control and
subsequent loss of helicopter control.
This AD is effective December
30, 2013.
The Director of the Federal Register
approved the incorporation by reference
of certain documents listed in this AD
as of December 30, 2013.
DATES:
For service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 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.
ADDRESSES:
Examining the AD Docket
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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, the European
Aviation Safety Agency (EASA) 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.
Gary
Roach, Aviation Safety Engineer,
Regulations and Policy Group,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, TX 76137;
telephone (817) 222–5110; email
gary.b.roach@faa.gov.
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010–21–01,
Amendment 39–16461 (75 FR 63050,
October 14, 2010), which applied to
Eurocopter Model AS350B, BA, B1, B2,
B3, D, AS355E, F, F1, F2, and N
helicopters. The NPRM was published
in the Federal Register on July 3, 2013
(78 FR 40045). AD No. 2010–21–01
required within 10 hours time-in-service
(TIS) or 1 month, inspecting the
helicopters to determine whether a
cross-member is installed at station X
2165 and doublers at X 2325 and Y 269.
If the cross-member and doublers are
not installed, AD No. 2010–21–01
required inspecting for a crack in the
center cross-member, and replacing the
center cross-member if there is a crack
before further flight. If a crack does not
exist, AD No. 2010–21–01 required
inspecting the tail rotor control rigging
before further flight. Lastly, if needed,
AD 2010–21–01 required installing a
cross-member and two doublers within
55 hours TIS. AD 2010–21–01 was
prompted by AD No. 2007–0139–E,
dated May 15, 2007 (corrected May 23,
2007), issued by EASA, which is the
Technical Agent for the Member States
of the European Union. EASA advised
that a crack was discovered in the area
of the center cross-member at station X
2325, at the attachment point of the yaw
channel ball-type control sheath stop, of
a Model AS355N helicopter fitted with
the collective-to-yaw control coupling.
Since we issued AD No. 2010–21–01,
we discovered that we included all
helicopters in the AD applicability
rather than limiting it to only those
helicopters with collective-to-yaw
control coupling. Therefore, this new
AD retains the requirements in AD No.
2010–21–01 with some revisions for the
inspection of the tail rotor control
rigging to clarify those procedures. This
AD also reduces the applicability to
only those Model AS350 and AS355
helicopters with collective-to-yaw
control coupling installed.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(78 FR 40045, July 3, 2013).
FOR FURTHER INFORMATION CONTACT:
FAA’s Determination
SUPPLEMENTARY INFORMATION:
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
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15:59 Nov 22, 2013
Jkt 232001
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70203
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.
Differences Between This AD and the
EASA AD
This AD differs from the EASA AD as
follows:
• We require the installation of the
cross-member at station X 2165 and the
two doublers at stations X 2325 and Y
269 within 55 hours time-in-service.
The EASA AD requires that this action
be accomplished within 12 months.
• We do not require repetitive
inspections if no crack exists in the
center cross-member, whereas the EASA
AD does.
• We do not include military model
helicopters in the applicability.
Related Service Information
We reviewed Eurocopter Emergency
Alert Service Bulletin (EASB), Revision
0, dated April 11, 2007, that contains
three different numbers (Nos. 53.00.37,
53.00.11, and 53.00.23) for Eurocopter
Model 350, 355, 550, and 555
helicopters. EASB No. 53.00.37 relates
to two Model 350 (350 BB and 350 L1)
helicopters that are not type certificated
in the United States. EASB No. 53.00.11
relates to four Model 550 and six Model
555 military helicopters that are not
type-certificated in the United States.
The EASB describes procedures for
checking the conformity for the cross
member at X 2325 under the cabin floor.
The actions in the EASA AD are
intended to correct the same unsafe
condition as that identified in the
service bulletin.
Costs of Compliance
We estimate that this AD affects 72
helicopters of U.S. Registry and that
labor costs average $85 a work-hour. It
takes about one work-hour to perform
the inspections, and if needed, to install
the cross-member, two doublers and an
airworthy center-cross member.
Required parts cost about $161 per
helicopter. Based on these figures, we
estimate the cost of the AD to be $246
per helicopter and $17,712 for the fleet
if all repairs are needed.
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:
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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations
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
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:
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PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
■
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Jkt 232001
2010–21–01, Amendment 39–16461 (75
FR 63050, October 14, 2010), and
adding the following new AD:
2013–23–10 Eurocopter France:
Amendment 39–17665; Docket No.
FAA–2013–0354; Directorate Identifier
2011–SW–072–AD.
(a) Applicability
This AD applies to Eurocopter France
Model AS350B, BA, B1, B2, B3, D, AS355E,
F, F1, F2, and N helicopters with collectiveto-yaw control coupling, part number
350A27–2178–04, 350A27–2178–06, or
350A27–2178–0601, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
reduced yaw control travel, which could
result in loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010–21–01,
Amendment 39–16461 (75 FR 63050, October
14, 2010).
(d) Effective Date
This AD becomes effective December 30,
2013.
(e) 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.
(f) Required Actions
(1) Within 10 hours time-in-service (TIS) or
within one month, whichever occurs first,
determine whether the cross-member
(numbered ‘‘1’’) at station X 2165 and the two
doublers (numbered ‘‘2’’ and ‘‘3’’) at stations
X 2325 and Y 269 are installed as shown in
Figure 1 of Eurocopter Emergency Alert
Service Bulletin (EASB) No. 53.00.37,
Revision 0, dated April 11, 2007 (EASB
53.00.37), for Model AS350 helicopters and
EASB No. 53.00.23, Revision 0, dated April
11, 2007 (EASB 53.00.23), for Model AS355
helicopters.
(2) If the cross-member (numbered ‘‘1’’)
and doublers (numbered ‘‘2’’ and ‘‘3’’) are not
installed, before further flight, inspect for a
crack in the center cross-member (numbered
‘‘4’’) in the area around the attachment point
of the tail rotor directional ball-type control
as shown in Figure 1 of EASB 53.00.37 for
Model AS350 helicopters or EASB 53.00.23
for Model AS355 helicopters.
(i) If a crack exists, before further flight,
replace the unairworthy center cross-member
(Numbered ‘‘4’’) with an airworthy center
cross-member as described in paragraph (f)(3)
of this AD.
(ii) If a crack does not exist, before further
flight, inspect the tail rotor control rigging to
determine whether it meets conformity
limits.
(A) If all items of the tail rotor control
rigging are found within conformity limits,
install the cross-member and doublers as
described in paragraph (f)(3) of this AD.
(B) For any items of the tail rotor control
rigging found outside of conformity limits,
perform appropriate corrective action in
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accordance with FAA-accepted procedures,
and install the cross-member and doublers as
described in paragraph (f)(3) of this AD.
(3) Within 55 hours TIS, if the cross
member (Numbered ‘‘1’’) is not installed,
install the cross-member at station X 2165
and the 2 doublers (Numbered ‘‘2’’ and ‘‘3’’)
at stations X 2325 and Y 269 by following the
Appendix, the referenced figures 2 and 3 of
EASB 53.00.37 for Model AS350 helicopters
or EASB 53.00.23 for Model AS355
helicopters.
(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, TX 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 the
European Aviation Safety Agency (EASA) AD
No. 2007–0139–E, dated May 15, 2007
(corrected May 23, 2007). You may view the
EASA AD at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2013–0354.
(i) Subject
Joint Aircraft Service Component (JASC)
Code: 5320, Fuselage Miscellaneous
Structure.
(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 Emergency Alert Service
Bulletin No. 53.00.37, Revision 0, dated April
11, 2007.
(ii) Eurocopter Emergency Alert Service
Bulletin No. 53.00.23, Revision 0, dated April
11, 2007.
Note 1 to paragraph (j)(2): Eurocopter
Emergency Alert Service Bulletin (EASB) No.
53.00.37, Revision 0, dated April 11, 2007,
and Eurocopter EASB No. 53.00.23, Revision
0, dated April 11, 2007, are co-published as
one document along with Eurocopter EASB
No. 53.00.11, Revision 0, dated April 11,
2007, which is not incorporated by reference
in this AD.
(3) For Eurocopter service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052; telephone
(972) 641–0000 or (800) 232–0323; fax (972)
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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 November
5, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft
Directorate, Aircraft Certification Service.
[FR Doc. 2013–27637 Filed 11–22–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0487; Directorate
Identifier 2010–SW–056–AD; Amendment
39–17666; AD 2013–23–11]
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 (Eurocopter) Model
AS332L2 and EC225LP helicopters. This
AD requires inspecting the torque value
of the bolts that secure the front and rear
main gearbox (MGB) suspension bar
attaching fittings, and re-torqueing the
bolts to the proper value if the torque
value is out of tolerance. This AD also
requires, if the torque value is out of
tolerance by more than 20 percent,
inspecting the bolts, frames, and related
equipment for a crack and repairing or
replacing them if cracked. This AD was
prompted by reports of cracks on Frame
5295 of Model AS332L2 helicopters.
The actions of this AD are intended to
detect the torque loss of the bolts that
secure the MGB bar attaching fittings
and to prevent cracks that could lead to
failure of the MGB supporting structure,
detachment of the MGB, and loss of
helicopter control.
DATES: This AD is effective December
30, 2013.
The Director of the Federal Register
approved the incorporation by reference
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SUMMARY:
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15:59 Nov 22, 2013
Jkt 232001
of certain documents listed in this AD
as of December 30, 2013.
For service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 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.
ADDRESSES:
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, the foreign
authority’s AD, any incorporated-byreference 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.
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.
FOR FURTHER INFORMATION CONTACT:
SUPPLEMENTARY INFORMATION:
Discussion
On June 7, 2013, at 78 FR 34288, 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
Eurocopter Model AS332L2 and
EC225LP helicopters. The NPRM
proposed to require inspecting the
torque value of the bolts that secure the
front and rear MGB suspension bar
attaching fittings, and re-torqueing the
bolts to the proper value if the torque
value is out of tolerance. The NPRM
also proposed to require that if the
torque value is out of tolerance by more
than 20 percent, inspecting the bolts,
frames, and related equipment for a
crack and repairing or replacing them if
cracked. The proposed requirements
were intended to detect the torque loss
of the bolts that secure the MGB bar
attaching fittings and to prevent cracks
that could lead to failure of the MGB
PO 00000
Frm 00015
Fmt 4700
Sfmt 4700
70205
supporting structure, detachment of the
MGB, and loss of helicopter control.
The NPRM was prompted by AD No.
2006–0163 R1, dated December 13, 2007
(AD No. 2006–0163R1), issued by the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, to correct an unsafe
condition in Model AS 332 L2 and
Model EC 225 LP helicopters. According
to EASA, analysis of tightening torques
revealed some cases of tightening torque
loss, which can lead to the formation of
a crack at the MGB bar attaching fittings.
As a result, EASA AD No. 2006–0163R1
requires checking the bolts securing the
front and rear of the MGB bar attaching
fittings for tightening torque loss and, if
the loss is equal to or greater than 20
percent, readjusting the torque and
checking the four bolts securing the
MGB bar attaching fitting mounting
plate, as well as the frame 3855, for a
crack. If there is a crack in at least one
of the bolts, AD No. 2006–0163R1
requires replacing all four bolts. If there
is a crack in frame 3855, AD No. 2006–
0163R1 requires suspending all flights
and contacting the manufacturer for
corrective action.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(78 FR 34288, June 7, 2013).
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.
Differences Between This AD and the
EASA AD
This AD differs from the EASA AD in
that we use the word ‘‘inspect’’ to
describe actions required by a mechanic
versus the word ‘‘check,’’ which is how
we describe actions allowed by a pilot.
We also require that if you find a crack
in a frame or fitting, you repair or
replace the cracked part instead of
contacting the manufacturer. Also, we
have different compliance times for the
initial inspection for the tightening
E:\FR\FM\25NOR1.SGM
25NOR1
]]>Agencies
[Federal Register Volume 78, Number 227 (Monday, November 25, 2013)]
[Rules and Regulations]
[Pages 70202-70205]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-27637]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0354; Directorate Identifier 2011-SW-072-AD;
Amendment 39-17665; AD 2013-23-10]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2010- 21-01
for Eurocopter France (Eurocopter) Model AS350B, BA, B1, B2, B3, D,
AS355E, F, F1, F2, and N
[[Page 70203]]
helicopters. AD 2010-21-01 required an inspection to determine whether
a cross-member is installed at station X 2165 and doublers at X 2325
and Y 269, and installing them if they are missing. This new AD retains
the requirements of AD 2010-21-01 but clarifies the inspection
procedures and limits the applicability to only those helicopters with
collective-to-yaw control coupling. This AD is prompted by a crack
discovered in the area of the center cross-member at station X 2325, at
the attachment point of the yaw channel ball-type control sheath stop,
of a Model AS355N helicopter fitted with the collective-to-yaw control
coupling. The actions of this AD are intended to prevent reduced yaw
control and subsequent loss of helicopter control.
DATES: This AD is effective December 30, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of December 30,
2013.
ADDRESSES: For service information identified in this AD, contact
American Eurocopter Corporation, 2701 N. Forum Drive, Grand Prairie, TX
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, the European Aviation Safety
Agency (EASA) 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, TX 76137; telephone (817) 222-5110; email
gary.b.roach@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2010-21-01, Amendment 39-16461 (75 FR 63050,
October 14, 2010), which applied to Eurocopter Model AS350B, BA, B1,
B2, B3, D, AS355E, F, F1, F2, and N helicopters. The NPRM was published
in the Federal Register on July 3, 2013 (78 FR 40045). AD No. 2010-21-
01 required within 10 hours time-in-service (TIS) or 1 month,
inspecting the helicopters to determine whether a cross-member is
installed at station X 2165 and doublers at X 2325 and Y 269. If the
cross-member and doublers are not installed, AD No. 2010-21-01 required
inspecting for a crack in the center cross-member, and replacing the
center cross-member if there is a crack before further flight. If a
crack does not exist, AD No. 2010-21-01 required inspecting the tail
rotor control rigging before further flight. Lastly, if needed, AD
2010-21-01 required installing a cross-member and two doublers within
55 hours TIS. AD 2010-21-01 was prompted by AD No. 2007-0139-E, dated
May 15, 2007 (corrected May 23, 2007), issued by EASA, which is the
Technical Agent for the Member States of the European Union. EASA
advised that a crack was discovered in the area of the center cross-
member at station X 2325, at the attachment point of the yaw channel
ball-type control sheath stop, of a Model AS355N helicopter fitted with
the collective-to-yaw control coupling.
Since we issued AD No. 2010-21-01, we discovered that we included
all helicopters in the AD applicability rather than limiting it to only
those helicopters with collective-to-yaw control coupling. Therefore,
this new AD retains the requirements in AD No. 2010-21-01 with some
revisions for the inspection of the tail rotor control rigging to
clarify those procedures. This AD also reduces the applicability to
only those Model AS350 and AS355 helicopters with collective-to-yaw
control coupling installed.
Comments
We gave the public the opportunity to participate in developing
this AD, but we received no comments on the NPRM (78 FR 40045, July 3,
2013).
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.
Differences Between This AD and the EASA AD
This AD differs from the EASA AD as follows:
We require the installation of the cross-member at station
X 2165 and the two doublers at stations X 2325 and Y 269 within 55
hours time-in-service. The EASA AD requires that this action be
accomplished within 12 months.
We do not require repetitive inspections if no crack
exists in the center cross-member, whereas the EASA AD does.
We do not include military model helicopters in the
applicability.
Related Service Information
We reviewed Eurocopter Emergency Alert Service Bulletin (EASB),
Revision 0, dated April 11, 2007, that contains three different numbers
(Nos. 53.00.37, 53.00.11, and 53.00.23) for Eurocopter Model 350, 355,
550, and 555 helicopters. EASB No. 53.00.37 relates to two Model 350
(350 BB and 350 L1) helicopters that are not type certificated in the
United States. EASB No. 53.00.11 relates to four Model 550 and six
Model 555 military helicopters that are not type-certificated in the
United States. The EASB describes procedures for checking the
conformity for the cross member at X 2325 under the cabin floor. The
actions in the EASA AD are intended to correct the same unsafe
condition as that identified in the service bulletin.
Costs of Compliance
We estimate that this AD affects 72 helicopters of U.S. Registry
and that labor costs average $85 a work-hour. It takes about one work-
hour to perform the inspections, and if needed, to install the cross-
member, two doublers and an airworthy center-cross member. Required
parts cost about $161 per helicopter. Based on these figures, we
estimate the cost of the AD to be $246 per helicopter and $17,712 for
the fleet if all repairs are needed.
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:
[[Page 70204]]
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 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 removing Airworthiness Directive (AD)
2010-21-01, Amendment 39-16461 (75 FR 63050, October 14, 2010), and
adding the following new AD:
2013-23-10 Eurocopter France: Amendment 39-17665; Docket No. FAA-
2013-0354; Directorate Identifier 2011-SW-072-AD.
(a) Applicability
This AD applies to Eurocopter France Model AS350B, BA, B1, B2,
B3, D, AS355E, F, F1, F2, and N helicopters with collective-to-yaw
control coupling, part number 350A27-2178-04, 350A27-2178-06, or
350A27-2178-0601, certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as reduced yaw control
travel, which could result in loss of control of the helicopter.
(c) Affected ADs
This AD supersedes AD 2010-21-01, Amendment 39-16461 (75 FR
63050, October 14, 2010).
(d) Effective Date
This AD becomes effective December 30, 2013.
(e) 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.
(f) Required Actions
(1) Within 10 hours time-in-service (TIS) or within one month,
whichever occurs first, determine whether the cross-member (numbered
``1'') at station X 2165 and the two doublers (numbered ``2'' and
``3'') at stations X 2325 and Y 269 are installed as shown in Figure
1 of Eurocopter Emergency Alert Service Bulletin (EASB) No.
53.00.37, Revision 0, dated April 11, 2007 (EASB 53.00.37), for
Model AS350 helicopters and EASB No. 53.00.23, Revision 0, dated
April 11, 2007 (EASB 53.00.23), for Model AS355 helicopters.
(2) If the cross-member (numbered ``1'') and doublers (numbered
``2'' and ``3'') are not installed, before further flight, inspect
for a crack in the center cross-member (numbered ``4'') in the area
around the attachment point of the tail rotor directional ball-type
control as shown in Figure 1 of EASB 53.00.37 for Model AS350
helicopters or EASB 53.00.23 for Model AS355 helicopters.
(i) If a crack exists, before further flight, replace the
unairworthy center cross-member (Numbered ``4'') with an airworthy
center cross-member as described in paragraph (f)(3) of this AD.
(ii) If a crack does not exist, before further flight, inspect
the tail rotor control rigging to determine whether it meets
conformity limits.
(A) If all items of the tail rotor control rigging are found
within conformity limits, install the cross-member and doublers as
described in paragraph (f)(3) of this AD.
(B) For any items of the tail rotor control rigging found
outside of conformity limits, perform appropriate corrective action
in accordance with FAA-accepted procedures, and install the cross-
member and doublers as described in paragraph (f)(3) of this AD.
(3) Within 55 hours TIS, if the cross member (Numbered ``1'') is
not installed, install the cross-member at station X 2165 and the 2
doublers (Numbered ``2'' and ``3'') at stations X 2325 and Y 269 by
following the Appendix, the referenced figures 2 and 3 of EASB
53.00.37 for Model AS350 helicopters or EASB 53.00.23 for Model
AS355 helicopters.
(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, TX 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 the European Aviation
Safety Agency (EASA) AD No. 2007-0139-E, dated May 15, 2007
(corrected May 23, 2007). You may view the EASA AD at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2013-0354.
(i) Subject
Joint Aircraft Service Component (JASC) Code: 5320, Fuselage
Miscellaneous Structure.
(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 Emergency Alert Service Bulletin No. 53.00.37,
Revision 0, dated April 11, 2007.
(ii) Eurocopter Emergency Alert Service Bulletin No. 53.00.23,
Revision 0, dated April 11, 2007.
Note 1 to paragraph (j)(2): Eurocopter Emergency Alert Service
Bulletin (EASB) No. 53.00.37, Revision 0, dated April 11, 2007, and
Eurocopter EASB No. 53.00.23, Revision 0, dated April 11, 2007, are
co-published as one document along with Eurocopter EASB No.
53.00.11, Revision 0, dated April 11, 2007, which is not
incorporated by reference in this AD.
(3) For Eurocopter service information identified in this AD,
contact American Eurocopter Corporation, 2701 N. Forum Drive, Grand
Prairie, TX 75052; telephone (972) 641-0000 or (800) 232-0323; fax
(972)
[[Page 70205]]
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 November 5, 2013.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft
Certification Service.
[FR Doc. 2013-27637 Filed 11-22-13; 8:45 am]
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