[Federal Register Volume 78, Number 178 (Friday, September 13, 2013)]
[Rules and Regulations]
[Pages 56599-56601]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-22170]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0399; Directorate Identifier 2011-SW-064-AD;
Amendment 39-17574; AD 2013-18-01]
RIN 2120-AA64
Airworthiness Directives; Eurocopter France Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for
Eurocopter France (Eurocopter) Model EC 155B, EC155B1, SA-365N, SA-
365N1, AS-365N2, AS 365 N3, and SA-366G1 helicopters. This AD requires
inspecting the collective pitch lever for correct locking and unlocking
conditions. This AD was prompted by two separate reports of inadvertent
collective pitch lever locking and unlocking. The actions of this AD
are intended to detect an incorrectly adjusted collective pitch lever,
which could result in loss of control of the helicopter.
DATES: This AD is effective October 18, 2013.
The Director of the Federal Register approved the incorporation by
reference of certain documents listed in this AD as of October 18,
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 http://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 http://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 authorities' ADs,
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: Matt Wilbanks, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA,
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110;
email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
On May 8, 2013, at 78 FR 26712, 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 EC 155B,
EC155B1, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters, except helicopters with modification (MOD) 0767B5
installed. The NPRM proposed to require inspecting the collective pitch
lever for correct unlocking with a spring scale, and if required,
adjusting the collective pitch lever restraining tab and, for certain
models, adjusting the collective link rods. The NPRM also proposed to
require inspecting the collective pitch lever for the risk of
inadvertent locking by measuring the clearance between the locking pin
of the collective pitch lever and the L-section of the restraining tab,
and if required, modifying the tab with a slight bend to the tab. The
proposed requirements were intended to detect an incorrectly adjusted
collective pitch lever, which could result in loss of control of the
helicopter.
The NPRM was prompted by AD No. 2011-0154, dated August 22, 2011,
issued by the European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Union. EASA
issued AD 2011-0154 to correct an unsafe condition for Eurocopter Model
EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, AS 365 N3, and SA-366G1
helicopters. EASA advises that two occurrences have been reported of
inadvertent locking and unlocking of the collective pitch lever. One
inadvertent collective pitch lever locking occurred when moving the
collective pitch lever to the low-pitch position, and one inadvertent
collective pitch lever unlocking occurred during engine start. To
address this unsafe condition, Eurocopter issued AS 365 Alert Telex No.
67.00.10, SA 366 Alert Telex No. 67.05, and EC 155 Alert Telex No.
67A007, which describe procedures to inspect the collective pitch lever
for correct locking and unlocking conditions. This inspection was
[[Page 56600]]
mandated by Direction G[eacute]n[eacute]rale de l'Aviation Civile
(DGAC) France AD No. F-2005-127, dated July 20, 2005. DGAC subsequently
revised its AD, No. F-2005-127 R1, dated February 1, 2006 (DGAC AD F-
2005-127 R1), after Eurocopter issued Alert Service Bulletins
containing the same inspection procedures and bearing the same numbers
as the Alert Telexes. Since the issuance of DGAC AD F-2005-127 R1
Eurocopter developed an assembly comprised of a blade, a hinge, and a
return spring to replace the flexible collective lever locking blade as
terminating action for the inspection required by the AD. EASA then
issued AD No. 2011-0154, which superseded DGAC AD F-2005-127 R1,
retaining the inspection procedures for the collective pitch lever and
removing from the applicability helicopters with the hinged, spring-
loaded collective lever locking blade installed, designated as MOD
0767B65.
Comments
We gave the public the opportunity to participate in developing
this AD, but we did not receive any comments on the NPRM (78 FR 26712,
May 8, 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.
Related Service Information
We reviewed Eurocopter Alert Service Bulletin (ASB) No. 67.00.10
for Model AS365 helicopters, ASB No. 67.05 for Model SA366 helicopters,
and ASB No. 67A007 for Model EC155 helicopters. All three ASBs are
Revision 1 and are dated February 25, 2009. These ASBs describe
procedures for inspecting and adjusting the collective pitch lever for
correct locking and unlocking conditions.
Eurocopter has also issued ASB No. 67.00.12, Revision 0, dated
February 25, 2009, for Model AS365 helicopters; ASB No. 67.07, Revision
0, dated February 25, 2009, for Model AS366 helicopters; and ASB No.
67-009, Revision 1, dated July 19, 2010, for Model EC 155 helicopters.
These ASBs contain the procedures for MOD 0767B65.
Costs of Compliance
We estimate that this AD will affect 32 helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD. Inspecting and adjusting the collective
pitch lever will require about 1 work hour at an average labor rate of
$85 per hour, for a total cost per helicopter of $85 and a cost to U.S.
operators of $2,720.
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 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):
2013-18-11 EUROCOPTER FRANCE: Amendment 39-17574; Docket No. FAA-
2013-0399; Directorate Identifier 2011-SW-064-AD.
(a) Applicability
This AD applies to Model EC 155B, EC155B1, SA-365N, SA-365N1,
AS-365N2, AS 365 N3, and SA-366G1 helicopters, except helicopters
with modification (MOD) 0767B5 installed, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as inadvertent locking and
unlocking of the collective pitch lever, which could result in
subsequent loss of control of the helicopter.
(c) Effective Date
This AD becomes effective October 18, 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
Within 50 hours time-in-service:
(1) For Model EC155B and EC155B1 helicopters:
(i) Lock the collective pitch lever, and using a spring scale,
measure the load (G) required to unlock the pilot's collective pitch
lever as depicted in Figure 1, Detail B of Eurocopter Alert Service
Bulletin (ASB) No. 67A007, Revision 1, dated February 25, 2009 (ASB
67A007).
(ii) If the collective pitch lever unlocks at a load less than
11 deca Newtons (daN) (24.7 lbs) or greater than 14 daN (31.5 lbs),
before further flight, adjust the collective pitch lever restraining
tab (F) using the oblong holes.
(iii) Set the collective pitch lever to the ``low pitch''
position and hold it in this position, without forcing it downwards.
(iv) Measure the clearance (J1) between the locking pin of the
collective pitch lever (C) and the L-section of the restraining tab
(F) as depicted in Figure 1, Detail A of ASB 67A007.
[[Page 56601]]
(v) If the clearance between the locking pin of the collective
pitch lever and the L-section of the restraining tab is less than 3
millimeters (mm), before further flight, remove the restraining tab,
clamp the restraining tab (F) in a vice with soft jaws, and
gradually apply a load (H) to ensure a clearance of 3 mm or more, as
depicted in Figure 1, Detail K of ASB 67A007.
(2) For Model SA-365N, SA-365N1, AS-365N2, and AS 365 N3
helicopters:
(i) Completely loosen the friction, lock the collective pitch
lever, and using a spring scale, measure the load (G) required to
unlock the pilot's collective pitch lever as depicted in Figure 1,
Detail B of Eurocopter ASB No. 67.00.10, Revision 1, dated February
25, 2009 (ASB 67.00.10).
(ii) If the collective pitch lever unlocks at a load less than 5
daN (11.3 lbs) or greater than 14 daN (31.5 lbs), before further
flight, adjust the collective pitch lever restraining tab (F) using
the oblong holes and adjust the collective link rods as described in
the Accomplishment Instructions, paragraph 2.B.4., of ASB 67.00.10.
(iii) Set the collective pitch lever to the ``low pitch''
position and hold it in this position, without forcing it downwards.
(iv) Tighten the friction lock and measure the clearance (J1)
between the locking pin of the collective pitch lever (C) and the L-
section of the restraining tab (F) as depicted in Figure 1, Detail A
of ASB 67.00.10.
(v) If the clearance between the locking pin of the collective
pitch lever and the L-section of the restraining tab is less than 3
mm, before further flight, remove the restraining tab, clamp the
restraining tab (F) in a vice with soft jaws, and gradually apply a
load (H) to ensure a clearance of 3 mm or more, as depicted in
Figure 1, Detail K, of ASB 67.00.10.
(3) For Model SA-366G1 helicopters:
(i) Completely loosen the friction, lock the collective pitch
lever, and using a spring scale, measure the load (G) required to
unlock the pilot's collective pitch lever as depicted in Figure 1,
Detail B of Eurocopter ASB No. 67.05, Revision 1, dated February 25,
2009 (ASB 67.05).
(ii) If the collective pitch lever unlocks at a load less than 5
daN (11.3 lbs) or greater than 14 daN (31.5 lbs), before further
flight, adjust the collective pitch lever restraining tab (F) using
the oblong holes and adjust the collective link rods as described in
the Accomplishment Instructions, paragraph 2.B.4., of ASB 67.05.
(iii) Set the collective pitch lever to the ``low pitch''
position and hold it in this position, without forcing it downwards.
(iv) Tighten the friction lock and measure the clearance (J1)
between the locking pin of the collective pitch lever (C) and the L-
section of the restraining tab (F) as depicted in Figure 1, Detail
A, of ASB 67.05.
(v) If the clearance between the locking pin of the collective
pitch lever and the L-section of the restraining tab is less than 3
mm, before further flight, remove the restraining tab, clamp the
restraining tab (F) in a vice with soft jaws, and gradually apply a
load (H) to ensure a clearance of 3 mm or more, as depicted in
Figure 1, Detail K, of ASB 67.05.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Safety Management Group, FAA, may approve AMOCs
for this AD. Send your proposal to: Matt Wilbanks, Aviation Safety
Engineer, Rotorcraft Certification Office, Rotorcraft Directorate,
FAA, 2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817)
222-5110; email [email protected].
(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.
(g) Additional Information
(1) Eurocopter Alert Service Bulletin (ASB) No. 67.00.12,
Revision 0, dated February 25, 2009; ASB No. 67.07, Revision 0,
dated February 25, 2009; and ASB No. 67-009, Revision 1, dated July
19, 2010, which are not incorporated by reference, contain
additional information about this AD. 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 http://www.eurocopter.com/techpub. You may review a copy of the service information at the
FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham
Blvd., Room 663, Fort Worth, Texas 76137.
(2) The subject of this AD is addressed in European Aviation
Safety Agency (EASA) AD No. 2011-0154, dated August 22, 2011. You
may view the EASA AD in the AD Docket on the internet at http://www.regulations.gov.
(h) Subject
Joint Aircraft Service Component (JASC) Code: 6710: Main Rotor
Control
(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 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. 67.00.10, Revision 1,
dated February 25, 2009.
(ii) Eurocopter Alert Service Bulletin No. 67.05, Revision 1,
dated February 25, 2009.
(iii) Eurocopter Alert Service Bulletin No. 67A007, Revision 1,
dated February 25, 2009.
(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) 641-3775; or at http://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 also 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Fort Worth, Texas, on August 21, 2013.
Kim Smith,
Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2013-22170 Filed 9-12-13; 8:45 am]
BILLING CODE 4910-13-P