Document ID: FAA-2020-0410-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2020-10-08T04:00Z

[Federal Register Volume 85, Number 196 (Thursday, October 8, 2020)]
[Rules and Regulations]
[Pages 63440-63443]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-22241]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0410; Product Identifier 2019-SW-030-AD; Amendment 
39-21274; AD 2020-21-01]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus Helicopters Model AS-365N2, AS 365N3, EC 155B, EC155B1, 
and SA-365N1 helicopters. This AD requires modifying the main gearbox 
(MGB) tail rotor (T/R) drive flange installation.

[[Page 63441]]

This AD was prompted by several reported occurrences of loss of 
tightening torque of the Shur-Lok nut, which serves as a retainer of 
the T/R drive flange. The actions of this AD are intended to address an 
unsafe condition on these products.

DATES: This AD is effective November 12, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain documents listed in this AD as of November 12, 
2020.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 
75052; telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at 
https://www.airbus.com/helicopters/services/technical-support.html. You 
may view the referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177. It is also available on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0410.

Examining the AD Docket

    You may examine the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0410; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this AD, the European Union Aviation Safety Agency (EASA) AD, any 
service information that is incorporated by reference, any comments 
received, and other information. The street address for Docket 
Operations is 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 Fuller, AD Program Manager, 
Airworthiness Products Section, General Aviation and Rotorcraft Unit, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
email Matthew.Fuller@faa.gov.

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to Airbus Helicopters 
Model AS-365N2, AS 365N3, EC 155B, EC155B1, and SA-365N1 helicopters 
with modification 0763B64 installed, except those with modification 
0763C81. The NPRM published in the Federal Register on April 23, 2020, 
(85 FR 22688). The NPRM proposed to require within 600 hours time-in-
service, modifying the MGB T/R drive flange installation by removing 
the sliding flange from the flexible coupling and installing the 
sliding flange with aft output stop part number 365A32-7836-20 added, 
as per helicopter model and configuration. The NPRM also proposed to 
require removing from service certain washers, degreasing the bolt 
threads, applying a sealant between the interlay mating surfaces, and 
applying torque to the nuts. The proposed requirements were intended to 
prevent loosening and disengagement of the Shur-Lok nut threads, 
possibly resulting in reduction of T/R drive control, rear transmission 
vibrations, and subsequent loss of control of the helicopter.
    The NPRM was prompted by EASA AD No. 2019-0046, dated March 11, 
2019 (EASA AD 2019-0046), issued by EASA, which is the Technical Agent 
for the Member States of the European Union, to correct an unsafe 
condition for Airbus Helicopters (formerly Eurocopter, Eurocopter 
France, Aerospatiale) Model SA 365 N1, AS 365 N2, AS 365 N3, EC 155 B, 
and EC 155 B1 helicopters, all serial numbers, with modification 
0763B64 installed, except those with 07 63C81 installed. EASA advises 
of reported occurrences of loss of tightening torque of the Shur-Lok 
nut, which serves as a retainer of the T/R drive flange of the MGB. 
EASA also advises of subsequent investigation that determined that 
these occurrences were the result of failure of the Shur-Lok nut 
locking function, which is normally ensured by two anti-rotation tabs 
engaged into two slots at the end of the MGB output shaft pinion. EASA 
states this condition could lead to the loosening and disengagement of 
the Shur-Lok nut threads, possibly resulting in reduction of T/R drive 
control, rear transmission vibrations, and subsequent loss of control 
of the helicopter.
    To address this unsafe condition, EASA issued a series of ADs, 
initially with EASA AD No. 2014-0165, dated July 14, 2014 (EASA AD 
2014-0165), which required a one-time inspection of the radial play 
inside the T/R drive flange and the condition of the Shur-Lok nut. 
Shortly after, EASA issued EASA AD No. 2014-0179, dated July 25, 2014 
(EASA AD 2014-0179) to supersede EASA AD 2014-0165. EASA AD 2014-0179 
retained the requirements of EASA AD 2014-0165 and expanded the 
applicability of helicopters affected by the unsafe condition. EASA 
later revised EASA AD 2014-0179 to Revision 1, dated July 29, 2014, to 
revise the applicability and specify updated related service 
information, and again to Revision 2, dated April 11, 2016 (EASA AD 
2014-0179R2), to reduce the applicability and specify additional 
updated related service information. Since EASA issued EASA AD 2014-
0179R2, another occurrence was reported that involved an on-ground loss 
of T/R synchronization, resulting from disengagement of the Shur-Lok 
nut. This additional occurrence prompted EASA to issue EASA AD 2019-
0046 to require installation of modification 07 63C81, which consists 
of installing a rear output stop with 5 spigots on the T/R shaft 
flexible coupling. According to Airbus Helicopters, the 5 spigots will 
come into contact with the row of 5 bolt heads of the front T/R shaft 
if the T/R drive flange moves backwards. This contact limits backward 
displacement of the T/R drive flange and subsequently prevents T/R 
drive flange disengagement.

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD, but the FAA did not receive any comments on the 
NPRM.

FAA's Determination

    These helicopters have been approved by EASA and are approved for 
operation in the United States. Pursuant to the FAA's bilateral 
agreement with the European Union, EASA has notified the FAA of the 
unsafe condition described in its AD. The FAA is issuing this AD after 
evaluating all information provided by EASA and determining the unsafe 
condition exists and is likely to exist or develop on other products of 
the 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

    The FAA reviewed Airbus Helicopters Alert Service Bulletin (ASB) 
No. AS365-63.00.19, for Model AS365N, N1, N2, and N3 helicopters and 
non FAA-type certificated military Model AS365F, Fi, Fs, K, and K2 
helicopters; and Airbus Helicopters ASB No. EC155-63A013 for Model 
EC155B and B1 helicopters, both Revision 1 and dated January 31, 2019. 
This service information specifies procedures for modification 0763C81 
to install a rear (aft) output stop between the T/R drive flange and T/
R drive shaft.
    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.

[[Page 63442]]

Costs of Compliance

    The FAA estimates that this AD affects 46 helicopters of U.S. 
Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this AD. Labor costs are estimated at $85 
per work-hour. Modifying the MGB T/R drive flange installation takes 
about 14 work-hours and parts cost about $2,704 for an estimated cost 
of $3,894 per helicopter and $179,124 for the U.S. fleet.

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.
    The FAA is 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. Will not affect intrastate aviation in Alaska, and
    3. 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 adding the following new airworthiness 
directive (AD):

2020-21-01 Airbus Helicopters: Amendment 39-21274; Docket No. FAA-
2020-0410; Product Identifier 2019-SW-030-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model AS-365N2, AS 365N3, 
EC 155B, EC155B1, and SA-365N1 helicopters, certificated in any 
category, with modification 0763B64 installed, except those with 
modification 0763C81.

(b) Unsafe Condition

    This AD defines the unsafe condition as loss of tightening 
torque of the Shur-Lok nut, which serves as a retainer of the tail 
rotor (T/R) drive flange of the main gearbox. This condition could 
result in loss of the Shur-Lok nut, possibly resulting in 
disengagement of the T/R drive flange, reduction of T/R drive 
control, rear transmission vibrations, and subsequent loss of 
control of the helicopter.

(c) Effective Date

    This AD becomes effective November 12, 2020.

(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 600 hours time-in-service:
    (1) For Model AS-365N2, AS 365N3, and SA-365N1 helicopters:
    (i) Without removing the tail drive shaft flange (a), remove the 
sliding flange (b) from the flexible coupling (c) as shown in Detail 
``B'' of Figure 1, PRE MOD, of Airbus Helicopters Alert Service 
Bulletin (ASB) No. AS365-63.00.19, Revision 1, dated January 31, 
2019 (ASB AS365-63.00.19); replace the 3 bolts (d) and remove from 
service the 3 washers (e).
    (ii) Install the sliding flange (b) with aft output stop (1) 
part number (P/N) 365A32-7836-20 as shown in Detail ``B'' of Figure 
1, POST MOD, of ASB AS365-63.00.19 and by following the 
Accomplishment Instructions, paragraph 3.B.2.b, of ASB AS365-
63.00.19.
    (2) For Model EC 155B and EC155B1 helicopters:
    (i) Without removing the Shur-Lok nut (a), remove the sliding 
flange (b) from the flexible coupling (c) as shown in Detail ``B'' 
of Figure 1, PRE MOD, of Airbus Helicopters ASB No. EC155-63A013, 
Revision 1, dated January 31, 2019 (ASB EC155-63A013); replace the 3 
bolts (d) and remove from service the 3 washers (e).
    (ii) Install the sliding flange (b) with aft output stop (1) P/N 
365A32-7836-20 as shown in Detail ``B'' of Figure 1, POST MOD, of 
ASB EC155-63A013 and by following the Accomplishment Instructions, 
paragraph 3.B.2.b, of ASB EC155-63A013.

    Note 1 to paragraph (e)(2)(ii):  ASB EC155-63A013 refers to the 
``aft output stop'' as ``rear output stop.''

 (f) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matt Fuller, AD Program 
Manager, Airworthiness Products Section, General Aviation and 
Rotorcraft Unit, 10101 Hillwood Pkwy., Fort Worth, TX 76177; 
telephone 817-222-5110; email 9-ASW-FTW-AMOC-Requests@faa.gov.
    (2) For operations conducted under a 14 CFR part 119 operating 
certificate or under 14 CFR part 91, subpart K, the FAA suggests 
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

    The subject of this AD is addressed in European Union Aviation 
Safety Agency (EASA) AD No. 2019-0046, dated March 11, 2019. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
Docket No. FAA 2020-0410.

(h) Subject

    Joint Aircraft Service Component (JASC) Code: 6500, Tail Rotor 
Drive System.

(i) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference 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) Airbus Helicopters Alert Service Bulletin (ASB) No. AS365-
63.00.19, Revision 1, dated January 31, 2019.
    (ii) Airbus Helicopters ASB No. EC155-63A013, Revision 1, dated 
January 31, 2019.
    (3) For service information identified in this AD, contact 
Airbus Helicopters, 2701 N Forum Drive, Grand Prairie, TX 75052; 
telephone 972-641-0000 or 800-232-0323; fax 972-641-3775; or at 
https://www.airbus.com/helicopters/services/technical-support.html.
    (4) You may view this service information at the FAA, Office of 
the Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 
6N-321, Fort Worth, TX 76177. 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,

[[Page 63443]]

email fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on September 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-22241 Filed 10-7-20; 8:45 am]
BILLING CODE 4910-13-P