[Federal Register Volume 85, Number 224 (Thursday, November 19, 2020)]
[Rules and Regulations]
[Pages 73604-73607]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-25472]


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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; Amendment 
39-21321; AD 2020-23-05]
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) 2018-08-01 
for Airbus Helicopters Model EC225LP helicopters. AD 2018-08-01 
required inspecting the control rod attachment yokes (yoke) of certain 
main rotor rotating swashplates (swashplate). This new AD retains the 
inspection requirements of AD 2018-08-01, expands the applicability, 
establishes a life limit, and adds a one-time inspection of stripped 
yokes. This AD was prompted by the identification of additional 
swashplate serial numbers affected by the unsafe condition and the 
establishment of a life limit for the swashplates. The FAA is issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective December 24, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 24, 
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-
0513.

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 AD, the European Union Aviation Safety Agency (EASA) AD, any 
service information that is incorporated by reference, any comments 
received, and other information. The address for Docket Operations is 
Document Operations, 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: Matthew Fuller, AD Program Manager, 
Operational Safety Branch, Airworthiness Products Section, General 
Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort Worth, TX 
76177; telephone 817-222-5110; email [email protected].

SUPPLEMENTARY INFORMATION:

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-08-01, Amendment 39-19254 (83 FR 
17617, April 23, 2018) (AD 2018-08-01) and add a new AD. AD 2018-08-01 
applied to Airbus Helicopters Model EC225LP helicopters with certain 
serial-numbered swashplates part number (P/N) 332A31-3074-00 or P/N 
332A31-3074-01 installed. The NPRM published in the Federal Register on 
June 3, 2020 (85 FR 34118). The NPRM proposed to require determining 
the date of manufacture of the swashplate and establishing a life limit 
of 12 years since the date of manufacture. The NPRM proposed to 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 (TIS) 
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, the NPRM proposed 
to 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, the NPRM proposed to require 
performing a dye penetrant inspection of the yoke for a crack. 
Depending on the results of this inspection, the NPRM proposed to 
require either repairing the surface of the swashplate or removing it 
from service.
    The NPRM was prompted by EASA AD No. 2019-0074, dated March 28, 
2019 (EASA AD 2019-0074) issued by EASA, which is the Technical Agent 
for the Member States of the European Union, to supersede EASA AD No. 
2017-0191R2, dated December 15, 2017

[[Page 73605]]

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

Comments

    The FAA gave the public the opportunity to participate in 
developing this AD. The FAA received no comments on the NPRM or on the 
determination of the cost to the public.

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 known relevant information and determining that 
an unsafe condition is likely to exist or develop on other helicopters 
of the same type design and that air safety and the public interest 
require adopting the AD requirements as proposed.

Differences Between This 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 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 AD does not.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes two Airbus 
Helicopters EASB identification numbers: EASB No. 05A051 for Model 
EC225LP helicopters and EASB No. 05A046 for non-FAA type-certificated 
Model EC725AP helicopters, each Revision 2 and dated February 26, 2019 
(EASB 05A051 and EASB 05A046). EASB 05A051 is incorporated by reference 
in this AD. EASB 05A046 is not incorporated by reference in this 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 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: EASB No. 05A051 for Model 
EC225LP helicopters and EASB 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.

Costs of Compliance

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

    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

[[Page 73606]]

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 part 39 of the Federal Aviation 
Regulations (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:2020-23-05

Airbus Helicopters: Amendment 39-21321; Docket No. FAA-2020-0513; 
Product Identifier 2019-SW-037-AD.

(a) Applicability

    This airworthiness directive (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) Effective Date

    This AD is effective December 24, 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

    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 05A05.
    (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) of this AD 
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, Rotorcraft Standards Branch, FAA, may approve 
AMOCs for this AD. Send your proposal to: Matthew Fuller, AD Program 
Manager, Operational Safety Branch, Airworthiness Products Section, 
General Aviation & Rotorcraft Unit, FAA, 10101 Hillwood Pkwy., Fort 
Worth, TX 76177; telephone 817-222-5110; email [email protected].
    (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

    (1) Airbus Helicopters Emergency Alert Service Bulletin No. 
05A051, Revision 1, dated November 16, 2017, which is not 
incorporated by reference, contains additional information about the 
subject of this AD. 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. You may view a copy of the service information at the 
FAA, Office of the Regional Counsel, Southwest Region, 10101 
Hillwood Pkwy., Room 6N-321, Fort Worth, TX 76177.
    (2) 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 Docket No. FAA-2020-0513.

(j) Subject

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

(k) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) 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 (EASB) 
No. 05A051, Revision 2, dated February 26, 2019.
    (ii) [Reserved]

    Note 1 to paragraph (k)(2): Airbus Helicopters EASB No. 05A051, 
Revision 2, dated February 26, 2019, is co-published as one document 
along with Airbus Helicopters EASB No. 05A046, Revision 2, dated 
February 26, 2019, which is not incorporated by reference in this 
AD.

    (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

[[Page 73607]]

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 October 29, 2020.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification 
Service.
[FR Doc. 2020-25472 Filed 11-18-20; 8:45 am]
BILLING CODE 4910-13-P