
[Federal Register Volume 78, Number 178 (Friday, September 13, 2013)]
[Rules and Regulations]
[Pages 56599-56601]
From the Federal Register Online via the Government Printing 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 matt.wilbanks@faa.gov.

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 matt.wilbanks@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.

(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


