AD 2020-19-02

[Federal Register Volume 85, Number 184 (Tuesday, September 22, 2020)]
[Rules and Regulations]
[Pages 59416-59419]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2020-20751]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0793; Project Identifier MCAI-2020-00976-R; 
Amendment 39-21243; AD 2020-19-02]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2000-22-19 
for Eurocopter France (now Airbus Helicopters) Model SA330F, G, and J 
helicopters. AD 2000-22-19 required repetitively inspecting certain 
tail rotor (T/R) blades for skin debonding and a crack. Since the FAA 
issued AD 2000-22-19, the inspection procedures have been revised. 
Additionally, the FAA is adding an affected part-numbered T/R blade and 
the FAA-validation for Model SA330F and G helicopters has been 
cancelled. This new AD revises the applicability, requires repetitively 
inspecting affected T/R blades with the new inspection procedures, and 
depending on the inspection results, repairing or replacing the T/R 
blade. This new AD also prohibits installing an affected T/R blade 
unless it has passed the inspections. The actions of this AD are 
intended to address an unsafe condition on these products.

DATES: This AD becomes effective October 7, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain document listed in this AD as of October 7, 
2020.
    The FAA must receive comments on this AD by November 6, 2020.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Docket: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the online instructions for sending your 
comments electronically.
    <bullet> Fax: 202-493-2251.
    <bullet> Mail: Send comments to the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590-0001.
    <bullet> Hand Delivery: Deliver to the ``Mail'' address between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2020-
0793; 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 Aviation Safety Agency (EASA) (now European Union 
Aviation Safety Agency) AD, any service information that is 
incorporated by reference, any comments received, and other 
information. The street address for Docket Operations is listed above. 
Comments will be available in the AD docket shortly after receipt.
    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 <a href="https://www.airbus.com/helicopters/services/technical-support.html">https://www.airbus.com/helicopters/services/technical-support.html</a>. 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 <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No. FAA-2020-
0793.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, AD Program Manager, 
Continued Operational Safety Branch, Airworthiness Products Section, 
General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#4a272b3e3e222f3d642c3f26262f380a2c2b2b642d253c"><span class="__cf_email__" data-cfemail="137e7267677b76643d75667f7f7661537572723d747c65">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION:

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and the FAA did not provide you with notice and an opportunity 
to provide your comments prior to it becoming effective. However, the 
FAA invites you to participate in this rulemaking by submitting written 
comments, data, or views. The most helpful comments reference a 
specific portion of the AD, explain the reason for any recommended 
change, and include supporting data. To ensure the docket does not 
contain duplicate comments, commenters should send only one copy of 
written comments, or if comments are filed electronically, commenters 
should submit them only one time.
    Except for Confidential Business Information (CBI) as described in 
the following paragraph, and other information as described in 14 CFR 
11.35, the FAA will file in the docket all

[[Page 59417]]

comments received, as well as a report summarizing each substantive 
public contact with FAA personnel concerning this rulemaking during the 
comment period. The FAA will consider all the comments received and may 
conduct additional rulemaking based on those comments.

Confidential Business Information

    Confidential Business Information (CBI) is commercial or financial 
information that is both customarily and actually treated as private by 
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), 
CBI is exempt from public disclosure. If your comments responsive to 
this final rule contain commercial or financial information that is 
customarily treated as private, that you actually treat as private, and 
that is relevant or responsive to this final rule, it is important that 
you clearly designate the submitted comments as CBI. Please mark each 
page of your submission containing CBI as ``PROPIN.'' The FAA will 
treat such marked submissions as confidential under the FOIA, and they 
will not be placed in the public docket of this final rule. Submissions 
containing CBI should be sent to Matt Fuller, AD Program Manager, 
Continued Operational Safety Branch, Airworthiness Products Section, 
General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#c8a5a9bcbca0adbfe6aebda4a4adba88aea9a9e6afa7be"><span class="__cf_email__" data-cfemail="dfb2beababb7baa8f1b9aab3b3baad9fb9bebef1b8b0a9">[email&#160;protected]</span></a>. 
Any commentary that the FAA receives which is not specifically 
designated as CBI will be placed in the public docket for this 
rulemaking.

Discussion

    The FAA issued AD 2000-22-19, Amendment 39-11967 (65 FR 68071, 
November 14, 2000) (``AD 2000-22-19''), for Eurocopter France (now 
Airbus Helicopters) Model SA330F, G, and J helicopters with a T/R blade 
part number (P/N) 330A12-0000-(all dash numbers), 330A12-0000-(all dash 
numbers), or 330A12-0006-(all dash numbers), installed.
    AD 2000-22-19 required, within a compliance time interval based on 
whether a de-icing system was installed, repetitively inspecting each 
T/R blade for skin debonding and eddy current inspecting for a crack. 
The FAA issued AD 2000-22-19 to prevent fatigue cracking of a T/R 
blade, failure of a T/R blade, and subsequent loss of control of the 
helicopter.

Actions Since AD 2000-22-19 Was Issued

    Since the FAA issued AD 2000-22-19, EASA, which is the Technical 
Agent for the Member States of the European Union, issued EASA AD No. 
2016-0059-E, dated March 22, 2016 (EASA AD 2016-0059-E), to correct an 
unsafe condition for Airbus Helicopters (formerly Eurocopter, 
Eurocopter France, Aerospatiale) Model SA 330 J helicopters. EASA AD 
2016-0059-E retains the requirements of Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) France AD 87-032-
052(B)R3, dated January 23, 1991, which it supersedes, and also 
mandates improved service instructions.
    Airbus Helicopters issued the improved service instructions in 
Emergency Alert Service Bulletin No. 05.101, Revision 0, dated March 
21, 2016, to extend the eddy current inspection area and specify new 
tooling to inspect the extended area.
    Also, since the FAA issued AD 2000-22-19, it was identified that AD 
2000-22-19 inadvertently listed T/R blade P/N 330A12-0000-(all dash 
numbers) twice in its applicability and omitted T/R blade P/N 330A12-
0005-(all dash numbers). This final rule removes T/R blade P/N 330A12-
0000-(all dash numbers) altogether from the applicability because these 
part-numbered T/R blades have been retired from the fleet and expands 
the applicability by adding helicopters with T/R blade P/N 330A12-0005-
(all dash numbers) installed.
    Additionally, at the request of Airbus Helicopters, Model SA330F 
and G helicopters have been removed from the FAA Type Certificate Data 
Sheet (TCDS). According to Airbus Helicopters, none of these aircraft 
models are in existence. EASA, the state of design, has also removed 
these models from its TCDS. As a result, the FAA is removing these 
models from the applicability.

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 about the 
unsafe condition described in its AD. The FAA is issuing this AD after 
evaluating all of the information provided by EASA and determining the 
unsafe condition exists and is likely to exist or develop on other 
helicopters of the same type design.

Related Service Information Under 1 CFR Part 51

    Airbus Helicopters has issued Emergency Alert Service Bulletin No. 
05.101, Revision 0, dated March 21, 2016, for Model SA330J helicopters 
with certain T/R blades with and without a de-icing system installed. 
This service information specifies procedures for a visual and in-depth 
inspection of the T/R blades for skin debonding and an eddy current 
inspection of the T/R blades for a crack using various crack detectors.
    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.

AD Requirements

    This AD requires within 30 hours time-in-service (TIS) after the 
effective date of this AD or within 30 hours TIS after last inspecting 
the T/R blades as required by paragraph (a) of AD 2000-22-19, whichever 
occurs first, and thereafter at intervals not to exceed 15 hours TIS 
for blades with de-icing systems installed or 30 hours TIS for blades 
without de-icing systems installed:
    <bullet> Accomplishing a visual and in-depth inspection of each T/R 
blade for debonding. If there is debonding within allowable limits, 
this AD requires repairing or replacing the T/R blade before further 
flight. If there is debonding that exceeds allowable limits, this AD 
requires replacing the T/R blade before further flight.
    <bullet> Eddy current inspecting each blade for a crack. If there 
is a crack, this AD requires replacing the T/R blade before further 
flight.
    This AD also prohibits installing an affected T/R blade on any 
helicopter unless it passes the inspections required by this AD.

Differences Between This AD and the EASA AD

    The EASA AD requires returning a T/R blade with debonding that 
exceeds allowable limits or a crack to Airbus Helicopters, whereas this 
AD requires replacing the T/R blade instead.

Regulatory Flexibility Act

    The requirements of the Regulatory Flexibility Act (RFA) do not 
apply when an agency finds good cause pursuant to 5 U.S.C. 553 to adopt 
a rule without prior notice and comment. Because the FAA has determined 
that it has good cause to adopt this rule without notice and comment, 
RFA analysis is not required.

[[Page 59418]]

Costs of Compliance

    The FAA estimates that this AD affects 15 helicopters of U.S. 
Registry. Labor rates are estimated at $85 per work-hour. Based on 
these numbers, the FAA estimates that operators may incur the following 
costs in order to comply with this AD.
    Inspecting the T/R blades for debonding takes about 0.75 work-hour 
for an estimated cost of $64 per helicopter and $960 for the U.S. 
fleet, per inspection cycle. Eddy current inspecting the T/R blades for 
a crack takes about 1.75 work-hours for an estimated cost of $149 per 
helicopter and $2,235 for the U.S. fleet, per inspection cycle.
    If required, replacing a T/R blade takes about 4 work-hours and 
parts cost about $19,000, for an estimated cost of $19,340.

FAA's Justification and Determination of the Effective Date

    Section 553(b)(3)(B) of the Administrative Procedure Act (5 U.S.C.) 
authorizes agencies to dispense with notice and comment procedures for 
rules when the agency, for ``good cause'' finds that those procedures 
are ``impracticable, unnecessary, or contrary to the public interest.'' 
Under this section, an agency, upon finding good cause, may issue a 
final rule without seeking comment prior to the rulemaking.
    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because fatigue cracking in a T/R blade could lead to failure of a T/R 
blade and subsequent loss of control of the helicopter. This type of 
fatigue cracking in a T/R blade could cause a pilot to perform an 
emergency landing. Because these helicopters primarily conduct 
operations over water or forested mountains, the FAA determined the 
corrective action must be completed within 30 hours TIS, a time period 
of up to approximately two months based on the average flight-hour 
utilization rates of these helicopters. Therefore, notice and 
opportunity for prior public comment are impracticable and contrary to 
public interest pursuant to 5 U.S.C. 553(b)(3)(B). In addition, for the 
reasons stated above, the FAA finds that good cause exists pursuant to 
5 U.S.C. 553(d) for making this amendment effective in less than 30 
days.

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

    The FAA 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, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866, and
    2. Will not affect intrastate aviation in Alaska.

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:
0
a. Removing Airworthiness Directive (AD) 2000-22-19, Amendment 39-11967 
(65 FR 68071, November 14, 2000); and
0
b. Adding the following new AD:

2020-19-02 Airbus Helicopters: Amendment 39-21243; Docket No. FAA-
2020-0793; Project Identifier MCAI-2020-00976-R.

(a) Applicability

    This AD applies to Airbus Helicopters (previously Eurocopter 
France) Model SA330J helicopters, certificated in any category, with 
a tail rotor (T/R) blade part number 330A12-0005-(all dash numbers) 
or 330A12-0006-(all dash numbers) installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as fatigue cracking of a T/
R blade. This condition could result in failure of a T/R blade and 
subsequent loss of control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2000-22-19, Amendment 39-11967 (65 FR 68071, 
November 14, 2000) (``AD 2000-22-19'').

(d) Effective Date

    This AD becomes effective October 7, 2020.

(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) Within 30 hours time-in-service (TIS) after the effective 
date of this AD or within 30 hours TIS after last inspecting the T/R 
blades as required by paragraph (a) of AD 2000-22-19, whichever 
occurs first, and thereafter at intervals not to exceed 15 hours TIS 
for T/R blades with deicing systems installed or 30 hours TIS for T/
R blades without deicing systems installed:
    (i) Inspect each T/R blade for debonding by following the visual 
and in-depth inspection procedures in the Accomplishment 
Instructions, paragraph 3.B.2., of Airbus Helicopters Emergency 
Alert Service Bulletin No. 05.101, Revision 0, dated March 21, 2016 
(EASB 05.101). If there is debonding within allowable limits, before 
further flight, repair or replace the T/R blade. If there is 
debonding that exceeds allowable limits, before further flight, 
replace the T/R blade.
    (ii) Eddy current inspect each T/R blade for a crack by 
following the Accomplishment Instructions, paragraph 3.B.3.a. of 
EASB 05.101, then either paragraph 3.B.3.b.1. or 3.B.3.b.2. of EASB 
05.101 depending on your crack detector, and paragraph 3.B.3.c. of 
EASB 05.101 except the ``if there are no cracks'' and ``if there are 
one or several cracks'' steps. Instead of the ``if there are no 
cracks'' and ``if there are one or several cracks'' steps, if there 
is a crack, before further flight, replace the T/R blade.
    (2) As of the effective date of this AD, do not install a T/R 
blade identified in paragraph (a) of this AD on any helicopter 
unless the actions of paragraph (f)(1) of this AD have been 
accomplished.

(g) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this

[[Page 59419]]

AD. Send your proposal to: Matt Fuller, AD Program Manager, 
Continued Operational Safety Branch, Airworthiness Products Section, 
General Aviation and Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., 
Fort Worth, TX 76177; telephone 817-222-5110; email <a href="/cdn-cgi/l/email-protection#566f7b1705017b1002017b171b19157b04332723332522251630373778313920"><span class="__cf_email__" data-cfemail="ecd5c1adbfbbc1aab8bbc1ada1a3afc1be899d99899f989fac8a8d8dc28b839a">[email&#160;protected]</span></a>.
    (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.

(h) Additional Information

    The subject of this AD is addressed in European Aviation Safety 
Agency (EASA) (now European Union Aviation Safety Agency) No. 2016-
0059-E, dated March 22, 2016. You may view the EASA AD on the 
internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and 
locating it in Docket No. FAA-2020-0793.

(i) Subject

    Joint Aircraft Service Component (JASC) Code: 6410, Tail Rotor 
Blades.

(j) 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 No. 
05.101, Revision 0, dated March 21, 2016.
    (ii) [Reserved]
    (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 
<a href="https://www.airbus.com/helicopters/services/technical-support.html">https://www.airbus.com/helicopters/services/technical-support.html</a>.
    (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 <a href="/cdn-cgi/l/email-protection#8fe9eaebfdeae8a1e3eae8eee3cfe1eefdeea1e8e0f9"><span class="__cf_email__" data-cfemail="197f7c7d6b7c7e37757c7e78755977786b78377e766f">[email&#160;protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued on August 31, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-20751 Filed 9-21-20; 8:45 am]
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