80 FR 50554 - Airworthiness Directives; Airbus Helicopters (Previously Eurocopter France) (Airbus Helicopters) Helicopters

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 80, Issue 161 (August 20, 2015)

We are superseding Airworthiness Directive (AD) 2013-21-01 for Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. AD 2013-21-01 required certain inspections of each tail rotor pitch horn assembly (pitch horn) for a crack, replacing a cracked pitch horn before further flight, and a one-time visual inspection of pitch horns above certain hours time-in-service (TIS). This new AD retains the requirements of AD 2013-21-01 but requires a repetitive visual inspection for all pitch horns regardless of hours TIS. This AD was prompted by a report of a crack in the yoke of a pitch horn and is intended to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter.

[Federal Register Volume 80, Number 161 (Thursday, August 20, 2015)]
[Rules and Regulations]
[Pages 50554-50556]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2015-20510]



[[Page 50554]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0364; Directorate Identifier 2013-SW-041-AD; 
Amendment 39-18234; AD 2015-17-01]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters (Previously 
Eurocopter France) (Airbus Helicopters) Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2013-21-01 for 
Eurocopter France Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, 
AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and 
AS355NP helicopters. AD 2013-21-01 required certain inspections of each 
tail rotor pitch horn assembly (pitch horn) for a crack, replacing a 
cracked pitch horn before further flight, and a one-time visual 
inspection of pitch horns above certain hours time-in-service (TIS). 
This new AD retains the requirements of AD 2013-21-01 but requires a 
repetitive visual inspection for all pitch horns regardless of hours 
TIS. This AD was prompted by a report of a crack in the yoke of a pitch 
horn and is intended to detect a crack in the pitch horn to prevent 
failure of the pitch horn, loss of the anti-torque function, and 
subsequent loss of control of the helicopter.

DATES: This AD is effective September 24, 2015.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of October 25, 2013 
(78 FR 63853, October 25, 2013).

ADDRESSES: For service information identified in this AD, contact 
Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand Prairie, TX 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, 10101 Hillwood Pkwy, Room 6N-321, Fort Worth, Texas 
76177.

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-
0364; 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: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy, Fort 
Worth, Texas 76177; telephone (817) 222-5110; email 
[email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    On May 30, 2014, we issued a notice of proposed rulemaking (NPRM) 
(79 FR 32881, June 9, 2014) to amend 14 CFR part 39 to remove AD 2013-
21-01, Amendment 39-17625 (78 FR 63853, October 25, 2013) and add a new 
AD. AD 2013-21-01 applied to Eurocopter France Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters and required a one-
time visual inspection of each pitch horn with 135 or more hours TIS 
for a crack and replacing the pitch horn if there is a crack. AD 2013-
21-01 also required a dye-penetrant inspection of any pitch horn before 
it is installed. AD 2013-21-01 was prompted by AD No. 2013-0133, dated 
June 28, 2013, issued by EASA, which is the Technical Agent for the 
Member States of the European Union, to correct an unsafe condition for 
Model AS350B, AS350BA, AS350BB, AS350B1, AS350B2, AS350B3, AS350D, 
AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. EASA 
advises of an ongoing investigation of a crack in the yoke of a pitch 
horn for which a cause has not been determined. The EASA AD requires 
repetitive visual inspections of each pitch horn for a crack and 
replacing the pitch horn with a serviceable assembly if a crack is 
found.
    The NPRM proposed to continue to require the visual inspection for 
the pitch horn but to require it for all pitch horns regardless of 
hours TIS. The NPRM also proposed to require repeating the visual 
inspection every 165 hours TIS and changing the requirement for the dye 
penetration inspection so that it only applies to pitch horns that are 
not new. Also, since we issued AD 2013-12-01, Eurocopter France changed 
its name to Airbus Helicopters. The NPRM proposed to reflect that 
change.

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 32881, 
June 9, 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.

Interim Action

    We consider this AD to be an interim action. If final action is 
later identified, we might consider further rulemaking then.

Differences Between This AD and the EASA AD

    The EASA AD applies to Eurocopter Model AS350BB that does not have 
an FAA type certificate and therefore is not a part of this AD. The 
EASA AD does not apply to Eurocopter Model AS350C or AS350D1, but this 
AD does because those models have an FAA type certificate and may have 
the applicable pitch horn installed. This AD requires a dye-penetrant 
inspection before installing a pitch horn; the EASA AD does not.

Related Service Information Under 1 CFR Part 51

    We reviewed a Eurocopter (now Airbus Helicopters) Emergency Alert 
Service Bulletin (EASB), Revision 1, dated June 25, 2013, with four 
different numbers. EASB No. 05.00.74 is for Model AS350B, B1, B2, B3, 
BA, and D helicopters; and EASB No. 05.00.65 is for Model AS355E, F, 
F1, F2, N, and NP helicopters. EASB No. 05.00.74 and EASB No. 05.00.65 
are co-published as one document along with EASB No. 05.00.49 and EASB 
No. 05.00.44, which are not incorporated by reference in this AD. These 
EASBs specify Airbus

[[Page 50555]]

Helicopters has been informed of a case of a crack on the yoke of a 
pitch horn, which may lead to failure of the pitch horn, resulting in 
loss of the anti-torque function. These EASBs specify a check for 
cracks on the yokes of the two pitch horns and specifies replacing any 
cracked pitch horn. These EASBs state that it may be necessary to 
modify the log card of the tail rotor blade assembly due to some of the 
pitch horn part numbers being recorded incorrectly. 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.
    EASA classified these EASBs as mandatory and issued EASA AD No. 
2013-0133, dated June 28, 2013, to ensure the continued airworthiness 
of these helicopters.

Costs of Compliance

    We estimate that this AD will affect 938 helicopters of U.S. 
Registry. We estimate that operators may incur the following costs in 
order to comply with this AD. Labor costs are estimated at $85 per work 
hour. We estimate 0.1 work hours to visually inspect a pitch horn for a 
total cost of $8.50 per helicopter or $7,973 for the fleet, per 
inspection cycle. We estimate 1 work hour to do a dye-penetrant 
inspection for a total cost of $85 per helicopter. We estimate 1 work 
hour to replace a part, if necessary, and a cost for required parts of 
$1,946, for a total cost of $2,031 per helicopter.

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 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) 
2013-21-01, Amendment 39-17625 (78 FR 63853, October 25, 2013), Docket 
No. FAA-2013-0878, Directorate Identifier 2013-SW-033-AD, and adding 
the following new AD:

2015-17-01 Airbus Helicopters (Previously Eurocopter France) (Airbus 
Helicopters): Amendment 39-18234; Docket No. FAA-2014-0364; 
Directorate Identifier 2013-SW-041-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS350B, AS350BA, 
AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, 
AS355F1, AS355F2, AS355N, and AS355NP helicopters with tail rotor 
hub pitch horn (pitch horn) assembly, part number (P/N) 
350A121368.01, 350A121368.02, 350A121368.03, or 350A121368.04, with 
a pitch horn, P/N 350A121368.XX, where XX stands for a two-digit 
dash number, installed, certificated in any category. The pitch horn 
may be marked with either the pitch horn assembly P/N or pitch horn 
P/N.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in the yoke of a 
pitch horn. This condition could result in failure of a pitch horn, 
loss of the anti-torque function, and subsequent loss of control of 
the helicopter.

(c) Affected ADs

    This AD supersedes 2013-21-01, Amendment 39-17625 (78 FR 63853, 
October 25, 2013).

(d) Effective Date

    This AD becomes effective September 24, 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

    (1) For parts with 155 or less hours time-in-service (TIS), 
before exceeding 165 hours TIS, or for parts with more than 155 
hours TIS, within 10 hours TIS, and thereafter at intervals not to 
exceed 165 hours TIS, visually inspect each pitch horn for a crack 
in the areas shown in Figure 1 of Eurocopter Emergency Alert Service 
Bulletin (EASB) No. 05.00.74 or No. 05.00.65, both Revision 1 and 
both dated June 25, 2013, as appropriate for your model helicopter.
    (2) If there is a crack, before further flight, replace the 
pitch horn with an airworthy pitch horn.
    (3) Do not install a pitch horn, P/N 350A121368 (any dash 
number), with more than 0 hours TIS on any helicopter unless it has 
passed a dye penetrant inspection for a crack in the areas shown in 
Figure 1 of Eurocopter EASB No. 05.00.74 or No. 05.00.65, both 
Revision 1 and both dated June 25, 2013, as appropriate for your 
model helicopter.

(g) Special Flight Permits

    Special flight permits are prohibited.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Group, FAA, may approve AMOCs 
for this AD. Send your proposal to: Robert Grant, Aviation Safety 
Engineer, Safety Management Group, FAA, 10101 Hillwood Pkwy, Fort 
Worth, Texas 76177; 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.

(i) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) AD No. 2013-0133, dated June 28, 2013. You may view 
the EASA AD on the Internet at http://www.regulations.gov in Docket 
No. FAA-2014-0364.

[[Page 50556]]

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6400 Tail Rotor.

(k) 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 25, 2013 (78 FR 63853, October 25, 2013).
    (i) Eurocopter Emergency Alert Service Bulletin No. 05.00.74, 
Revision 1, dated June 25, 2013.
    (ii) Eurocopter Emergency Alert Service Bulletin No. 05.00.65, 
Revision 1, dated June 25, 2013.

    Note 1 to paragraph (k)(3) of this AD:  Eurocopter Emergency 
Alert Service Bulletin No. 05.00.74 and No. 05.00.65, both Revision 
1, and both dated June 25, 2013, are co-published as one document 
along with Eurocopter Emergency Alert Service Bulletin No. 05.00.49 
and No. 05.00.44, both Revision 1, and both dated June 25, 2013, 
which are not incorporated by reference in this AD.

    (4) For Eurocopter service information identified in this AD, 
contact Airbus Helicopters, Inc., 2701 N. Forum Drive, Grand 
Prairie, TX 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, 10101 Hillwood Pkwy, Room 6N-
321, Fort Worth, Texas 76177. 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 August 6, 2015.
Larry M. Kelly,
Acting Directorate Manager, Rotorcraft Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-20510 Filed 8-19-15; 8:45 am]
BILLING CODE 4910-13-P