[Federal Register Volume 85, Number 107 (Wednesday, June 3, 2020)]
[Proposed Rules]
[Pages 34118-34121]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-11821]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0513; Product Identifier 2019-SW-037-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to supersede Airworthiness Directive (AD) 
2018-08-01 for Airbus Helicopters Model EC225LP helicopters. AD 2018-
08-01 requires inspecting the control rod attachment yokes (yoke) of 
certain main rotor rotating swashplates (swashplate). Since the FAA 
issued AD 2018-08-01, Airbus Helicopters has identified additional 
swashplate serial numbers affected by the unsafe condition and has 
established a life limit for the swashplates. This proposed AD would 
retain the inspection requirements of AD 2018-08-01, expand the 
applicability, establish a life limit, and add a one-time inspection of 
stripped yokes. The actions of this proposed AD are intended to address 
an unsafe condition on these products.

DATES: The FAA must receive comments on this proposed AD by August 3, 
2020.

[[Page 34119]]


ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your 
comments electronically.
     Fax: 202-493-2251.
     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.
     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 https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0513; 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 proposed AD, the European Union Aviation Safety Agency (EASA) AD, 
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 proposed 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 this referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, 
Fort Worth, TX 76177.

FOR FURTHER INFORMATION CONTACT: Matt Fuller, Senior Aviation Safety 
Engineer, Safety Management Section, Rotorcraft Standards Branch, FAA, 
10101 Hillwood Pkwy., Fort Worth, TX 76177; telephone 817-222-5110; 
email Matthew.Fuller@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    The FAA invites you to participate in this rulemaking by submitting 
written comments, data, or views. The FAA also invites comments 
relating to the economic, environmental, energy, or federalism impacts 
that might result from adopting the proposals in this document. The 
most helpful comments reference a specific portion of the proposal, 
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 only one 
time.
    The FAA will file in the docket all comments received, as well as a 
report summarizing each substantive public contact with FAA personnel 
concerning this proposed rulemaking. Before acting on this proposal, 
the FAA will consider all comments received on or before the closing 
date for comments. The FAA will consider comments filed after the 
comment period has closed if it is possible to do so without incurring 
expense or delay. The FAA may change this proposal in light of the 
comments received.

Discussion

    The FAA issued AD 2018-08-01, Amendment 39-19254 (83 FR 17617, 
April 23, 2018) (``AD 2018-08-01'') for Airbus Helicopters Model 
EC225LP helicopters. AD 2018-08-01 requires, for certain serial-
numbered swashplates part number (P/N) 332A31-3074-00 and P/N 332A31-
3074-01, a repetitive visual inspection of the five yokes for a crack 
and replacing the swashplate if there is a crack in any of the yokes.
    AD 2018-08-01 was prompted by EASA AD No. 2017-0191R2, dated 
December 15, 2017 (EASA AD 2017-0191R2), issued by EASA, which is the 
Technical Agent for the Member States of the European Union. EASA 
advised of a finding by Airbus Helicopters that the yoke is susceptible 
to cracking due to strain aging of the metal. EASA advised that this 
condition, if not detected and corrected, could lead to structural 
failure of a yoke, possibly resulting in loss of control of the 
helicopter.

Actions Since AD 2018-08-01 Was Issued

    Since the FAA issued AD 2018-08-01, Airbus Helicopters revised the 
related service information, Emergency Alert Service Bulletin (EASB) 
No. 05A051, Revision 1, dated November 16, 2017, to Revision 2, dated 
February 26, 2019 (EASB 05A051). EASB 05A051 establishes a life limit 
(also called a service life limit) of 12 years for the swashplate and 
adds a reporting requirement if there is a crack or corrosion in a 
yoke.
    Thereafter, EASA superseded EASA AD 2017-0191R2 with EASA AD No. 
2019-0074, dated March 28, 2019 (EASA AD 2019-0074). EASA advises that 
additional analysis determined that it is necessary to introduce a new 
life limit for the affected swashplates. Accordingly, EASA AD 2019-0074 
retains the requirements of EASA AD 2017-0191R2 and adds the life limit 
and the reporting requirement.
    Additionally, the FAA issued AD 2018-08-01 to address the unsafe 
condition of a crack in a swashplate yoke. However, AD 2018-08-01 did 
not require stripping certain yokes and performing a one-time 
inspection within 100 hours time-in-service (TIS) for corrosion and a 
crack as specified in EASA AD 2017-0191R2, as there is sufficient time 
to allow for notice and comment prior to this long-term AD requirement 
going into effect. The FAA has determined this inspection is needed to 
address this unsafe condition and has proposed to require, within 100 
hours TIS and for certain yokes, removing the grease and stripping 
certain areas of the yokes and inspecting these areas for corrosion, 
pitting, loss of material, and a crack in this proposed AD.

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 proposing this AD 
after evaluating all known relevant information and determining that an 
unsafe condition is likely to exist or develop on other helicopters of 
the same type design.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes two Airbus 
Helicopters EASB identification numbers: EASB 05A051 for Model EC225LP 
helicopters and EASB No. 05A046, Revision 2, dated February 26, 2019, 
for non-FAA type-certificated Model EC725AP helicopters. EASB 05A051 is 
proposed for incorporation by reference in this proposed AD. Airbus 
Helicopters EASB No. 05A046 is not proposed for incorporation by 
reference in this proposed AD.
    This service information specifies inspections for swashplate P/N 
332A31-3074-00 and P/N 332A31-3074-01. This service information 
specifies procedures for a repetitive inspection of the yokes for a 
crack and a one-time inspection of the stripped yokes for corrosion and 
a crack. If in doubt about whether there is a crack, this service 
information specifies performing a non-destructive inspection. This 
service information also specifies touching up the swashplate with 
varnish if there is corrosion, removing any damage within

[[Page 34120]]

allowable limits, and refinishing the yokes. If there is a crack in a 
yoke, this service information specifies replacing the swashplate. This 
service information also specifies a life limit of 12 years since the 
date of manufacture for the swashplates and reporting requirements if a 
crack or corrosion is discovered.
    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.

Other Related Service Information

    The FAA reviewed one document that co-publishes two Airbus 
Helicopters EASB identification numbers: No. 05A051 for Model EC225LP 
helicopters and No. 05A046 for non-FAA type-certificated Model EC725AP 
helicopters, each Revision 1 and dated November 16, 2017. Revision 1 of 
this service information specifies the same inspections as Revision 2 
of this service information. However, Revision 2 of this service 
information clarifies some of the inspection instructions and adds a 
life limit and a reporting requirement.

Proposed AD Requirements

    This proposed AD would require, before further flight, reviewing 
Appendix 4.A. of EASB 05A051 to determine the date of manufacture of 
the swashplate and establishing a life limit of 12 years since the date 
of manufacture. This proposed AD would retain the repetitive visual 
inspections of AD 2018-08-01 to inspect each yoke for a crack at 
intervals not to exceed 15 hours time-in-service for swashplates that 
have accumulated less than 7 years since the date of manufacture. For a 
swashplate that has accumulated 7 or more years, but less than 12 
years, since the date of manufacture, this proposed AD would require 
removing the grease and stripping certain areas of the yokes and 
inspecting these areas for corrosion, pitting, loss of material, and a 
crack. If there are no cracks, this AD would require performing a dye 
penetrant inspection of the yoke for a crack.
    Depending on the results of this inspection, the proposed AD would 
require either repairing the surface of the swashplate or removing it 
from service.

Differences Between This Proposed AD and the EASA AD

    The EASA AD requires performing a non-destructive inspection only 
if there is doubt whether there is a crack. Instead, this proposed AD 
requires a visual inspection and if there are no cracks, requires a 
non-destructive inspection. The EASA AD specifies instructions for 
reporting inspection reports; this proposed AD does not.

Costs of Compliance

    The FAA estimates that this proposed AD affects 26 helicopters of 
U.S. Registry. The FAA estimates that operators may incur the following 
costs in order to comply with this proposed AD. Labor costs are 
estimated at $85 per work-hour.
    Determining the date of manufacture of the swashplate would take 
about 0.5 work-hour for an estimated cost of $43 per helicopter and 
$1,118 for the U.S. fleet.
    Inspecting the yokes would take about 0.25 work-hour for an 
estimated cost of $21 per helicopter and $546 for the U.S. fleet per 
inspection cycle.
    Removing grease, stripping the yokes, and inspecting the stripped 
yokes would take about 8 work-hours, for a total estimated cost of $680 
per helicopter.
    Dye-penetrant inspecting a yoke for a crack would take about 6 
work-hours and parts would cost about $50, for an estimated cost of 
$560 per yoke.
    Removing any corrosion or repairing damage within the allowable 
limit would take about 3 work-hours, for an estimated cost of $255 per 
yoke.
    Replacing the swashplate would take about 6 work-hours, and parts 
would cost about $85,661 for an estimated cost of $86,171 per instance.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed regulation:
    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 Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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) 
2018-08-01, Amendment 39-19254 (83 FR 17617, April 23, 2018), and 
adding the following new AD:

Airbus Helicopters: Docket No. FAA-2020-0513; Product Identifier 
2019-SW-037-AD.

(a) Applicability

    This AD applies to Airbus Helicopters Model EC225LP helicopters, 
certificated in any category, with a main rotor (M/R) rotating 
swashplate (swashplate) part number (P/N) 332A31-3074-00 or P/N 
332A31-3074-01 installed.

(b) Unsafe Condition

    This AD defines the unsafe condition as a crack in a swashplate 
control rod attachment yoke (yoke). This condition could result in 
failure of the yoke, loss of M/R control, and subsequent loss of 
control of the helicopter.

(c) Affected ADs

    This AD replaces AD 2018-08-01, Amendment 39-19254 (83 FR 17617, 
April 23, 2018).

(d) Comments Due Date

    The FAA must receive comments by August 3, 2020.

(e) Compliance

    You are responsible for performing each action required by this 
AD within the

[[Page 34121]]

specified compliance time unless it has already been accomplished 
prior to that time.

(f) Required Actions

    Before further flight, review Appendix 4.A. of Airbus 
Helicopters Emergency Alert Service Bulletin No. 05A051, Revision 2, 
dated February 26, 2019 (EASB 05A051) to determine the date of 
manufacture of the swashplate.
    (1) If the swashplate has accumulated 12 or more years since the 
date of manufacture, remove from service the swashplate.
    (2) If the swashplate has accumulated less than 12 years since 
the date of manufacture, create a component history card or 
equivalent record indicating a life limit of 12 years since the date 
of manufacture. Thereafter, continue to record the life limit of the 
swashplate on its component history card or equivalent record and 
remove from service any swashplate before accumulating 12 years 
since the date of manufacture.
    (3) For each swashplate that has accumulated less than 7 years 
since the date of manufacture, within 15 hours time-in-service (TIS) 
and thereafter at intervals not to exceed 15 hours TIS, until the 
swashplate accumulates 7 years since the date of manufacture, 
visually inspect each yoke for a crack, paying particular attention 
to the areas shown in Details B, C, and D of Figure 1 of EASB 
05A051.
    (i) If there are no cracks, perform a dye penetrant inspection 
of the yoke for a crack.
    (ii) If there is a crack on a yoke, before further flight, 
remove from service the swashplate.
    (4) For each swashplate that has accumulated 7 or more years, 
but less than 12 years, since the date of manufacture, within 100 
hours TIS:
    (i) Remove the grease from areas (E), (F), (G), (H), (J), and 
(K) of each yoke as shown in Details B, C, and D of Figure 1 of EASB 
05A051. Using a plastic spatula, strip areas (E), (F), (G), (H), 
(J), and (K) of each yoke as shown in Details B, C, and D of Figure 
1 of EASB 05A051. Do not use a metal tool to strip any area of a 
yoke.
    (ii) Inspect areas (E), (F), (G), (H), (J) and (K) of each yoke 
as shown in Details B, C, and D of Figure 1 of EASB 05A051 for 
corrosion, pitting, and loss of material.
    (A) If there is any corrosion less than 0.0078 in. (0.2 mm), 
before further flight, remove the corrosion and apply varnish 
(Vernelec 43022 or equivalent) to the surface of areas (E), (F), 
(G), (H), (J) and (K).
    (B) If there is any pitting or loss of material of less than 
0.0078 in. (0.2 mm), before further flight, remove the damage by 
sanding with sandpaper 200/400 or 330.
    (C) If there is any corrosion, pitting, or loss of material of 
0.0078 in. (0.2 mm) or greater, before further flight, remove from 
service the swashplate.
    (iii) Visually inspect each yoke for a crack, paying particular 
attention to the areas shown in Details B, C, and D of Figure 1 of 
EASB 05A051.
    (A) If there are no cracks, perform a dye penetrant inspection 
of the yoke for a crack.
    (B) If there is a crack on a yoke, before further flight, remove 
from service the swashplate.

 (g) Credit for Previous Actions

    If you performed the actions in paragraph (f)(4) before the 
effective date of this AD using Airbus Helicopters Emergency Alert 
Service Bulletin No. 05A051, Revision 1, dated November 16, 2017, 
you met the requirements of paragraph (f)(4) of this AD.

 (h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, Safety Management Section, Rotorcraft Standards 
Branch, FAA, may approve AMOCs for this AD. Send your proposal to: 
Matt Fuller, Senior Aviation Safety Engineer, Safety Management 
Section, Rotorcraft Standards Branch, FAA, 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.

(i) Additional Information

    The subject of this AD is addressed in European Union Aviation 
Safety Agency (EASA) AD No. 2019-0074, dated March 28, 2019. You may 
view the EASA AD on the internet at https://www.regulations.gov in 
the AD Docket.

(j) Subject

    Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor 
Mast/Swashplate.

    Issued on May 27, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-11821 Filed 6-2-20; 8:45 am]
 BILLING CODE 4910-13-P


