
[Federal Register Volume 80, Number 109 (Monday, June 8, 2015)]
[Rules and Regulations]
[Pages 32294-32297]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-13355]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0464; Directorate Identifier 2014-SW-002-AD; 
Amendment 39-18169; AD 2015-11-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-18-01 for 
Eurocopter France Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, 
AS 365 N3, and SA-366G1 helicopters. AD 2013-18-01 required inspecting 
the collective pitch lever for correct locking and unlocking 
conditions. As published, AD 2013-18-01 contained certain errors. This 
new AD retains the requirements of AD 2013-18-01, corrects the errors, 
and updates the type certificate holder's name. The actions in this AD 
are intended to detect an incorrectly adjusted collective pitch lever, 
which

[[Page 32295]]

could result in loss of control of the helicopter.

DATES: This AD is effective July 13, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 18, 
2013 (78 FR 56599, September 13, 2013).

ADDRESSES: For service information identified in this AD, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, Texas 
75052; telephone (972) 641-0000 or (800) 232-0323; fax (972) 641-3775; 
or at http://www.airbushelicopters.com/techpub. You may view this 
referenced service information at the FAA, Office of the Regional 
Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, 
Texas 76137. It is also available on the Internet at http://www.regulations.gov in Docket No. FAA-2014-0464.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2014-
0464; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this AD, the European Aviation Safety Agency (EASA) AD, any 
incorporated-by-reference information, the economic evaluation, any 
comments received, and other information. The address for the Docket 
Office (phone: 800-647-5527) is Document Management Facility, U.S. 
Department of Transportation, Docket Operations, 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, Regulations and Policy Group, Rotorcraft Directorate, FAA, 
2601 Meacham Blvd., Fort Worth, Texas 76137; telephone (817) 222-5110; 
email matt.wilbanks@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to remove AD 2013-18-01, Amendment 39-17574 (78 FR 56599, 
September, 13, 2013) and add a new AD. AD 2013-18-01 applied to 
Eurocopter France Model EC 155B, EC155B1, SA-365N, SA-365N1, AS-365N2, 
AS 365 N3, and SA-366G1 helicopters, except helicopters with 
modification (MOD) 0767B5 installed. AD 2013-18-01 required 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. AD 2013-
18-01 also required 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. 
As published, the AD number after the amendatory language section of AD 
2013-18-01 is incorrect. The AD number was published as ``2013-18-11.'' 
The MOD number in paragraph (a), Applicability, of the AD is also 
incorrect. The correct MOD number is 0767B65. Also, since we issued AD 
2013-18-01, the type certificate holder's name for the affected models 
changed from Eurocopter France to Airbus Helicopters.
    AD 2013-18-01 was prompted by AD No. 2011-0154, dated August 22, 
2011, issued by EASA, which is the Technical Agent for the Member 
States of the European Union, 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 of two occurrences 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, EASA AD No. 2011-0154 requires 
inspecting the collective pitch lever for correct locking and unlocking 
conditions, except for those helicopters with a hinged, spring-loaded 
collective lever locking blade installed, designated as MOD 0767B65.
    The NPRM published in the Federal Register on July 16, 2014 (79 FR 
41466). The NPRM proposed to continue to require all of the inspection 
and adjustment requirements of AD 2013-18-01. The NPRM also proposed to 
correct the MOD number in paragraph (a) and reflect the current type 
certificate holder's name and contact information. Removing AD 2013-18-
01 and issuing a new AD would also remove the incorrect AD number after 
the amendatory language. The NPRM proposed no other changes to other 
parts of the regulatory information.

Comments

    We gave the public the opportunity to participate in developing 
this AD, but we did not receive any comments on the NPRM (79 FR 41466, 
July 16, 2014).

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 Under 1 CFR Part 51

    We reviewed Eurocopter (now Airbus Helicopters) 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. 
This service information is reasonably available because the interested 
parties have access to it through their normal course of business or by 
the means identified in the ADDRESSES section of this AD.

Other Related Service Information

    Eurocopter 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 requires about 1 work-hour at an average labor rate of $85 
per work-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

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detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on the States, on the relationship between 
the national government and the States, or on the distribution of power 
and responsibilities among the various levels of government.
    For the reasons discussed above, I certify that 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.

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) 
2013-18-01, Amendment 39-17574 (78 FR 56599, September 13, 2013), and 
adding the following new AD:

2015-11-06 Airbus Helicopters (Previously Eurocopter France): 
Amendment 39-18169; Docket No. FAA-2014-0464; Directorate Identifier 
2014-SW-002-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) 0767B65 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) Affected ADs

    This AD supersedes AD 2013-18-01, Amendment 39-17574 (78 FR 
56599, September 13, 2013).

(d) Effective Date

    This AD becomes effective July 13, 2015.

(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

    Within 50 hours time-in-service:
    (1) For Model EC 155B 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.
    (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.

(g) 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, Regulations and Policy Group, 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.

[[Page 32297]]

(h) 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 Airbus Helicopters, Inc., 2701 N. 
Forum Drive, Grand Prairie, Texas 75052; telephone (972) 641-0000 or 
(800) 232-0323; fax (972) 641-3775; or at http://www.airbushelicopters.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 on the Internet at http://www.regulations.gov 
in Docket No. FAA-2014-0464.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6710, Main Rotor 
Control.

(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.
    (3) The following service information was approved for IBR on 
October 18, 2013, (78 FR 56599, September 13, 2013).
    (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.
    (4) For Eurocopter service information identified in this AD, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand 
Prairie, Texas 75052; telephone (972) 641-0000 or (800) 232-0323; 
fax (972) 641-3775; or at http://www.airbushelicopters.com/techpub.
    (5) 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.
    (6) 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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Fort Worth, Texas, on May 26, 2015.
Lance T. Gant,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-13355 Filed 6-5-15; 8:45 am]
 BILLING CODE 4910-13-P


