Document ID: FAA-2021-0872-0003
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Helicopters
Posted Date: 2021-12-23T05:00Z

[Federal Register Volume 86, Number 244 (Thursday, December 23, 2021)]
[Rules and Regulations]
[Pages 72829-72833]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-27625]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-0872; Project Identifier MCAI-2021-00312-R; 
Amendment 39-21866; AD 2021-26-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-11-
05, which applied to all Airbus Helicopters Model EC120B helicopters. 
AD 2020-11-05 required repetitive inspections of the tail rotor (TR) 
hub body for cracks and applicable corrective actions if necessary, and 
repetitive replacement of the attachment bolts, washers, and nuts of 
the TR hub body. This AD was prompted by a report of recurrent loss of 
tightening torque on several attachment bolts on the TR hub body. This 
AD retains certain requirements of AD 2020-11-05, adds repetitive 
inspections, requires additional corrective actions, and updates 
applicable service information. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective January 27, 2022.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 27, 
2022.

ADDRESSES: For service information identified in this final rule, 
contact Airbus Helicopters, 2701 North 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 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. It is also available at 
https://www.regulations.gov by searching for and locating Docket No. 
FAA-2021-00872.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-0872; 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 final rule, the 
European Union Aviation Safety Agency (EASA) AD, any comments received, 
and other information. The 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: Andrea Jimenez, Aerospace Engineer, 
COS Program Management Section, Operational Safety Branch, Compliance & 
Airworthiness Division, FAA, 1600 Stewart Ave., Suite 410, Westbury, NY 
11590; telephone (516) 228-7330; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2020-11-05, Amendment 39-21130 (85 FR 
31042, May 22, 2020), (AD 2020-11-05). AD 2020-11-05 applied to Airbus 
Helicopters Model EC120B helicopters, all serial numbers. The NPRM 
published in the Federal Register on October 8, 2021 (86 FR 56220). In 
the NPRM, the FAA proposed to retain some of the requirements of AD 
2020-11-05, and proposed to require, within 15 hours time-in-service 
(TIS) or 7 days, whichever occurs first, performing repetitive 
inspections of the TR hub body for a crack and depending on the 
inspection results, removing the affected parts from service. The NPRM 
also proposed to require inspecting the TR spline flange for corrosion, 
impacts, fretting, wear, and a crack and depending on the inspection 
results, removing the TR splined flange from service. For helicopters 
with 9,000 or more total hours TIS or with unknown total hours TIS, the 
NPRM proposed to require, within 15 hours TIS or 7 days, whichever 
occurs first, and thereafter at intervals not to exceed 1,000 hours 
TIS, removing from service any bolt, washer, and nut installed on the 
TR hub body, replacing them with airworthy parts, inspecting the TR 
splined flange, and depending on the inspection results, removing the 
TR splined flange from service.
    Additionally, the NPRM proposed to require, for helicopters with 
less than 9,000 total hours TIS, within 1,000 hours TIS or before 
accumulating 9,000 total hours TIS, whichever occurs first, and 
thereafter at intervals not to exceed 1,000 hours TIS, removing from 
service any bolt, washer, and nut installed on the TR hub body 
replacing them with

[[Page 72830]]

airworthy parts, inspecting the TR splined flange, and depending on the 
inspection results, removing the TR splined flange from service. 
Finally, the NPRM proposed to prohibit the installation of a certain 
part-numbered TR hub body unless certain actions have been 
accomplished.
    The NPRM was prompted by EASA AD 2021-0069, dated March 11, 2021 
(EASA AD 2021-0069), 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, Model 
EC120 B helicopters, all serial numbers. EASA advises that an 
inspection of the TR hub body revealed a recurring loss of tightening 
torque on several attachment bolts. This condition, if not addressed, 
could result in cracking and potential loss of the TR drive and 
consequent loss of yaw control of the helicopter.
    Accordingly, EASA AD 2021-0069 retains the requirements of EASA AD 
2019-0272R1, dated November 18, 2019 (EASA AD 2019-0272R1), which 
prompted AD 2020-11-05, and requires additional repetitive detailed 
inspections of the interface between the TR hub body part number 
C642A0100103 and the splined flange. Depending on the inspection 
results, EASA AD 2021-0069 requires accomplishment of applicable 
corrective actions.

Discussion of Final Airworthiness Directive

Comments

    The FAA received no comments on the NPRM or on the determination of 
the costs.

Conclusion

    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 about the 
unsafe condition described in its AD. The FAA reviewed the relevant 
data, and determined that air safety requires adopting this AD as 
proposed. Accordingly, the FAA is issuing this AD to address the unsafe 
condition on these helicopters. Except for minor editorial changes, 
this AD is adopted as proposed in the NPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Emergency Alert Service 
Bulletin 05A020, Revision 2, dated February 8, 2021. This service 
information specifies procedures for repetitive inspections of the TR 
hub body for cracks and the TR spline flange for cracks and fretting 
and the appropriate corrective actions.
    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.[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]

Differences Between This AD and EASA AD 2021-0069

    EASA AD 2021-0069 uses flight hours (FH) for certain compliance 
times, whereas this AD uses hours TIS. EASA AD 2021-0069 retains the 
compliance time of November 1, 2019 for certain actions, which is the 
effective date of EASA AD 2019-0272R1, whereas this AD requires 
compliance in terms of the effective date of this AD.
    Where Note 1 of EASA AD 2021-0069 allows a non-cumulative tolerance 
of 100 FH to be applied to the compliance times for the initial 
replacement of bolts, washers, and nuts (Table 1 of EASA AD 2021-0069) 
to allow for synchronization of the required inspections with other 
maintenance tasks, this AD does not allow a non-cumulative tolerance to 
be applied to the compliance times.

Costs of Compliance

    The FAA estimates that this AD affects 89 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates the following costs to comply with 
this AD.
    Visually inspecting each TR hub body for a crack takes about 0.25 
work-hour for an estimated cost of $22 per inspection and $1,958 for 
the U.S. fleet per inspection.
    Visually inspecting each TR spline flange for corrosion, impacts, 
fretting, wear, and a crack takes about 0.25 work-hour for an estimated 
cost of $22 per inspection and $1,958 for the U.S. fleet per 
inspection.
    Replacing a TR hub body takes about 2 work-hours and parts would 
cost about $16,417 for an estimated cost of $16,587 per TR hub body 
replacement.
    Replacing a TR spline flange takes about 0.5 work-hour and parts 
would cost about $2,950 for an estimated cost of $2,993 per TR spline 
flange replacement.
    Replacing a bolt, washer, and nut takes about 0.5 work-hour and 
parts would cost about $68 for an estimated cost of $111 per 
replacement.

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 products 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.

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:
0
a. Removing Airworthiness Directive 2020-11-05, Amendment 39-21130 (85 
FR 31042, May 22, 2020); and
0
b. Adding the following new airworthiness directive:

2021-26-07 Airbus Helicopters: Amendment 39-21866; Docket No.

[[Page 72831]]

FAA-2021-0872; Project Identifier MCAI-2021-00312-R.

(a) Effective Date

    This airworthiness directive (AD) is effective January 27, 2022.

(b) Affected ADs

    This AD replaces AD 2020-11-05, Amendment 39-21130 (85 FR 31042, 
May 22, 2020) (AD 2020-11-05).

(c) Applicability

    This AD applies to Airbus Helicopters Model EC120B helicopters, 
certificated in any category, all serial numbers.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6400, Tail rotor 
system.

(e) Unsafe Condition

    This AD was prompted by a report of recurrent loss of tightening 
torque on several attachment bolts on the tail rotor (TR) hub body. 
The FAA is issuing this AD to detect cracking and fretting, which if 
not addressed, could result in potential loss of the TR drive and 
consequent loss of yaw control of the helicopter.

(f) Compliance[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES][RULE][PREAMB][AGENCY]*[/AGENCY][SUBJECT]*[/SUBJECT][/
PREAMB][SUPLINF][HED]*[/HED]

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Required Actions

    (1) Within 15 hours time-in-service (TIS) or 7 days, whichever 
occurs first after the effective date of this AD, and thereafter at 
intervals not to exceed 15 hours TIS, using a light source and 
mirror, visually inspect TR hub body part number (P/N) C642A0100103 
for a crack in the entire inspection area depicted in Figure 1 of 
Airbus Helicopters Emergency Alert Service Bulletin 05A020 Revision 
2, dated February 8, 2021. If there is a crack, before further 
flight, perform the actions in paragraphs (g)(1)(i) and (ii) of this 
AD.
    (i) Remove the TR hub body and each bolt, washer, and nut 
installed on the TR hub body from service and replace with airworthy 
parts.
    (ii) Inspect the TR splined flange for corrosion, impacts, 
fretting, wear, and a crack in the areas identified in Figure 2 to 
paragraph (g)(1)(ii) of this AD. If the condition of the part 
(including corrosion, impacts, fretting, wear, or cracks) exceeds 
the criteria as specified in Figure 1 to paragraph (g)(1)(ii) of 
this AD, before further flight, remove the splined flange from 
service and replace with an airworthy part.
    Note 1 to paragraph (g)(1)(ii): You may refer to ``Detailed 
Check--Splined Flange,'' Task 64-21-00, 6-5, Airbus Aircraft 
Maintenance Manual (AMM), dated October 15, 2020, which pertains to 
the TR splined flange inspection.
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[[Page 72832]]

[GRAPHIC] [TIFF OMITTED] TR23DE21.001

BILLING CODE 4910-13-C
    (2) For helicopters with 9,000 or more total hours TIS, or with 
unknown total hours TIS, within 15 hours TIS or 7 days, whichever 
occurs first after the effective date of this AD, and thereafter at 
intervals not to exceed 1,000 hours TIS, remove each bolt, washer, 
and nut installed on the TR hub body from service and replace with 
airworthy parts and perform the actions in paragraph (g)(1)(ii) of 
this AD.
    (3) For helicopters with less than 9,000 total hours TIS, within 
1,000 hours TIS or before accumulating 9,000 total hours TIS, 
whichever occurs first after the effective date of this AD, and 
thereafter at intervals not to exceed 1,000 hours TIS, remove each 
bolt, washer, and nut installed on the TR hub body from service and 
replace with airworthy parts and perform the actions in paragraph 
(g)(1)(ii) of this AD.
    (4) As of the effective date of this AD, do not install TR hub 
body P/N C642A0100103 on any helicopter, unless the actions of 
paragraph (g)(1) of this AD have been accomplished.

(h) Special Flight Permits

    A special flight permit may be permitted provided that there are 
no passengers onboard.

(i) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, International Validation Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Validation Branch, send 
it to the attention of the person identified in paragraph (j)(1) of 
this AD.

[[Page 72833]]

Information may be emailed to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(j) Related Information

    (1) For more information about this AD, contact Andrea Jimenez, 
Aerospace Engineer, COS Program Management Section, Operational 
Safety Branch, Compliance & Airworthiness Division, FAA, 1600 
Stewart Ave., Suite 410, Westbury, NY 11590; telephone (516) 228-
7330; email [email protected].
    (2) Service information identified in this AD, is available at 
the contact information specified in paragraphs (k)(3) and (4) of 
this AD.
    (3) The subject of this AD is addressed in European Union 
Aviation Safety Agency (EASA) AD 2021-0069, dated March 11, 2021. 
You may view the EASA AD on the internet at https://www.regulations.gov in Docket No. FAA-2021-0872.

(k) 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 Emergency Alert Service Bulletin 05A020, 
Revision 2, dated February 8, 2021.
    (ii) [Reserved]
    (3) For service information identified in this AD, contact 
Airbus Helicopters, 2701 North 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, email: [email protected], or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on December 9, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-27625 Filed 12-22-21; 8:45 am]
BILLING CODE 4910-13-P[FEDREG][VOL]*[/VOL][NO]*[/NO][DATE]*[/
DATE][RULES]