[Federal Register Volume 86, Number 184 (Monday, September 27, 2021)]
[Rules and Regulations]
[Pages 53185-53187]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2021-20824]



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 Rules and Regulations
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  Federal Register / Vol. 86, No. 184 / Monday, September 27, 2021 / 
Rules and Regulations  

[[Page 53185]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2021-500; Project Identifier 2017-SW-069-AD; Amendment 
39-21720; AD 2021-19-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Helicopters Model EC130B4 and EC130T2 helicopters. This AD was 
prompted by a report of a jammed pilot collective pitch lever 
(collective). This AD requires inspecting the collective for proper 
engagement of the locking pin. The FAA is issuing this AD to address 
the unsafe condition on these products.

DATES: This AD is effective November 1, 2021.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of November 1, 
2021.

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 the referenced 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-2021-500.

Examining the AD Docket

    You may examine the AD docket at https://www.regulations.gov by 
searching for and locating Docket No. FAA-2021-500; 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 Aviation Safety Agency (now European Union Aviation Safety 
Agency) (EASA) AD, 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: Anthony Kenward, Aviation Safety 
Engineer, Fort Worth ACO Branch, Compliance & Airworthiness Division, 
FAA, 10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone (817) 222-
5152; email [email protected].

SUPPLEMENTARY INFORMATION:

Background

    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 EC130B4 and Model EC130T2 helicopters. The NPRM published in the 
Federal Register on July 7, 2021 (86 FR 35695). In the NPRM, the FAA 
proposed to require, within 90 hours time-in-service (TIS) after the 
effective date of the AD, or before the next autorotation training 
flight, whichever occurs first, removing the protective boot along the 
collective and measuring the clearance between the collective tab hook 
(hook) and low pitch locking pin (pin). If the clearance is less than 5 
mm (0.196 in), adjusting the clearance between the hook and the pin to 
prevent interference was proposed. The NPRM then proposed to require 
re-installing the protective boot in accordance with the manufacturer's 
service information. The NPRM was prompted by EASA AD 2017-0062, dated 
April 11, 2017 (EASA AD 2017-0062), issued by EASA, which is the 
Technical Agent for the Member States of the European Union, to correct 
an unsafe condition for Airbus Helicopters Model EC130B4 and EC130T2 
helicopters. EASA states that during an autorotation test conducted 
during an acceptance flight, the pilot felt a jamming sensation when 
pushing the collective to the low pitch position, and he subsequently 
was able to free the collective by pulling on it. According to EASA, an 
analysis determined that the hook and the pin were extremely close, and 
that a fold in the control lever boot may have become caught between 
the two components. EASA states that this condition, if not detected 
and corrected, could result in an untimely locking of the collective 
and subsequent reduced control of the helicopter.
    Accordingly, EASA AD 2017-0062 requires inspecting and adjusting, 
if necessary, the clearance between the hook and the pin while in the 
low pitch position.

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.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed Airbus Helicopters Alert Service Bulletin ASB No. 
EC130-67A019, Revision 0, dated February 23, 2016, which specifies 
inspecting and adjusting the clearance between the hook and pin.
    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.

Differences Between This AD and the EASA AD

    The EASA AD requires compliance within 165 hours TIS or 3 months, 
whichever occurs first. Since the unsafe condition occurred at a 
collective position commanded during an autorotation, this AD requires 
compliance within 90 hours TIS after

[[Page 53186]]

the effective date of this AD or before the next autorotation training 
flight, whichever occurs first. Based on the average fleet usage, 90 
hours TIS corresponds with the 3-month compliance requirement of the 
EASA AD.

Costs of Compliance

    The FAA estimates that this AD affects 214 helicopters of U.S. 
Registry. At an average labor rate of $85 per work-hour, the FAA 
estimates that operators may incur the following costs in order to 
comply with this AD. Removing the protective boot will require about 2 
work-hours for a cost of $170 per helicopter and a cost of $36,380 for 
the U.S. fleet. Determining the clearance between the hook and pin will 
require about 0.5 work-hour, for a cost of $43 per helicopter and a 
cost of $9,202 for the U.S. fleet. If required, adjusting the clearance 
will take about 2 work-hours for a cost of $170 per helicopter. Re-
installing the protective boot will require about 2 work-hours, for a 
cost of $170 per helicopter and a cost of $36,380 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.

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:

2021-19-02 Airbus Helicopters: Amendment 39-21720 Docket No. FAA-
2021-500; Project Identifier 2017-SW-069-AD.

(a) Effective Date

    This airworthiness directive (AD) is effective November 1, 2021.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Helicopters Model EC130B4 and Model 
EC130T2 helicopters, certificated in any category.

(d) Subject

    Joint Aircraft Service Component (JASC) Code: 6700, Rotorcraft 
flight control.

(e) Unsafe Condition

    This AD was prompted by a report of a jammed pilot collective 
pitch lever (collective). The FAA is issuing this AD to prevent an 
untimely locking of the collective and subsequent reduced control of 
the helicopter.

(f) Compliance

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

(g) Required Actions

    Within 90 hours time-in-service after the effective date of this 
AD or before the next autorotation training flight, whichever occurs 
first:
    (1) For each collective, remove the protective boot along the 
collective and measure the clearance between the edge of the 
collective tab hook (a) and the edge of the low pitch locking pin 
(b) as shown in Figure 1 of Airbus Helicopters Alert Service 
Bulletin ASB No. EC130-67A019, Revision 0, dated February 23, 2016 
(ASB EC130-67A019). If the clearance is less than 5 mm (0.196 in), 
before further flight:
    (i) Adjust the clearance by following the Accomplishment 
Instructions, paragraph 3.B.3., of ASB EC130-67A019.
    (ii) Test the collective for proper engagement of the low pitch 
locking pin by following the Accomplishment Instructions, paragraph 
3.B.4., of ASB EC130-67A019.
    (2) Re-install the protective boot on the collective, ensuring 
that no boot folds have entered the space between the collective tab 
hook and the low pitch locking pin, by following the Accomplishment 
Instructions, paragraph 3.B.5., of ASB EC130-67A019.

(h) Special Flight Permits

    Special flight permits are prohibited.

(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. 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 Anthony Kenward, 
Aviation Safety Engineer, Fort Worth ACO Branch, Compliance & 
Airworthiness Division, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone (817) 222-5152; email [email protected].
    (2) The subject of this AD is addressed in European Aviation 
Safety Agency (now European Union Aviation Safety Agency) (EASA) AD 
2017-0062, dated April 11, 2017. You may view the EASA AD at https://www.regulations.gov in Docket No. FAA-2021-500.

(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 Alert Service Bulletin ASB No. EC130-
67A019, Revision 0, dated February 23, 2016.
    (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://

[[Page 53187]]

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 August 30, 2021.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2021-20824 Filed 9-24-21; 8:45 am]
BILLING CODE 4910-13-P