Proposed Rule2022-01440
Airworthiness Directives; Airbus Helicopters
Primary source
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Published
January 26, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA proposes to supersede Airworthiness Directive (AD) 2020-23-05, which applies to certain Airbus Helicopters Model EC225LP helicopters. AD 2020-23-05 requires inspecting the control rod attachment yokes (yokes) of certain main rotor (M/R) rotating swashplates (swashplates), establishing a life limit, a one-time inspection of stripped yokes, and applicable corrective actions. Since the FAA issued AD 2020-23-05, the FAA has determined that a revised compliance time is necessary for swashplates that have accumulated less than seven years since the date of manufacture and that clarification is necessary for the condition that concludes with a dye penetrant inspection of the yoke. This proposed AD would continue to require the actions in AD 2020-23-05, with a revised compliance time for a certain inspection. The FAA is proposing this AD to address the unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 17 (Wednesday, January 26, 2022)</title>
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[Federal Register Volume 87, Number 17 (Wednesday, January 26, 2022)]
[Proposed Rules]
[Pages 3943-3946]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-01440]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0015; Project Identifier AD-2021-00832-R]
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)
2020-23-05, which applies to certain Airbus Helicopters Model EC225LP
helicopters. AD 2020-23-05 requires inspecting the control rod
attachment yokes (yokes) of certain main rotor (M/R) rotating
swashplates (swashplates), establishing a life limit, a one-time
inspection of stripped yokes, and applicable corrective actions. Since
the FAA issued AD 2020-23-05, the FAA has determined that a revised
compliance time is necessary for swashplates that have accumulated less
than seven years since the date of manufacture and that clarification
is necessary for the condition that concludes with a dye penetrant
inspection of the yoke. This proposed AD would continue to require the
actions in AD 2020-23-05, with a revised compliance time for a certain
inspection. The FAA is proposing this AD to address the unsafe
condition on these products.
DATES: The FAA must receive comments on this proposed AD by March 14,
2022.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="https://www.regulations.gov">https://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: (202) 493-2251.
<bullet> Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
<bullet> Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For service information identified in this NPRM, contact Airbus
Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052; phone:
(972) 641-0000 or (800) 232-0323; fax (972) 641-3775; or at <a href="https://www.airbus.com/helicopters/technical-services/support.html">https://www.airbus.com/helicopters/technical-services/support.html</a>. 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.
Examining the AD Docket
You may examine the AD docket at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2022-0015; 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 NPRM, the European
Union Aviation Safety Agency (EASA) AD, any comments received, and
other information. The street address for Docket Operations is listed
above.
FOR FURTHER INFORMATION CONTACT: Hal Jensen, Aerospace Engineer,
Operational Safety Branch, Compliance & Airworthiness Division, FAA,
950 L'Enfant Plaza N SW, Washington, DC 20024; phone: (202) 267-9167;
email: <a href="/cdn-cgi/l/email-protection#cba3aaa7e5a1aea5b8aea58badaaaae5aca4bd"><span class="__cf_email__" data-cfemail="95fdf4f9bbfff0fbe6f0fbd5f3f4f4bbf2fae3">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
[[Page 3944]]
Comments Invited
The FAA invites you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under ADDRESSES. Include ``Docket No. FAA-2022-0015; Project Identifier
AD-2021-00832-R'' at the beginning of your comments. The most helpful
comments reference a specific portion of the proposal, explain the
reason for any recommended change, and include supporting data. The FAA
will consider all comments received by the closing date and may amend
this proposal because of those comments.
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 post all comments received, without change, to
<a href="https://www.regulations.gov">https://www.regulations.gov</a>, including any personal information you
provide. The agency will also post a report summarizing each
substantive verbal contact received about this NPRM.
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 NPRM 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 NPRM, 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 NPRM. Submissions containing CBI should be sent to Hal
Jensen, Aerospace Engineer, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC
20024; phone: (202) 267-9167; email: <a href="/cdn-cgi/l/email-protection#274f464b094d42495442496741464609404851"><span class="__cf_email__" data-cfemail="026a636e2c68676c71676c426463632c656d74">[email 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.
Background
The FAA issued AD 2020-23-05, Amendment 39-21321 (85 FR 73604,
November 19, 2020), (AD 2020-23-05), for certain Airbus Helicopters
Model EC225LP helicopters. AD 2020-23-05 requires inspecting the yokes
of certain swashplates, establishing a life limit, a one-time
inspection of stripped yokes, and applicable corrective actions. AD
2020-23-05 was prompted by a crack in a swashplate yoke, which could
result in failure of the yoke, loss of M/R control, and subsequent loss
of control of the helicopter.
EASA AD 2019-0074, dated March 28, 2019 (EASA AD 2019-0074), was
issued by EASA, which is the Technical Agent for the Member States of
the European Union, to supersede EASA AD 2017-0191R2, dated December
15, 2017 (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.
Actions Since AD 2020-23-05 Was Issued
Since the FAA issued AD 2020-23-05, the FAA has determined that a
revised compliance time is necessary for swashplates that have
accumulated less than seven years since the date of manufacture. This
revised compliance time matches the compliance time specified in EASA
AD 2019-0074. The FAA has also determined that paragraphs (g)(3)(i) and
(g)(4)(iii)(A) of this AD need clarification regarding when it is
necessary to do a dye penetrant inspection of the yoke.
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
the unsafe condition described previously 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 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.
This service information specifies inspections for swashplate part
number (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 nondestructive 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. The Director of the Federal Register
approved EASB No. 05A051, Revision 2, dated February 26, 2019, for
incorporation by reference as of December 24, 2020 (85 FR 73604,
November 19, 2020). EASB No. 05A046, Revision 2, dated February 26,
2019, is not incorporated by reference in this AD.
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.
Proposed AD Requirements in This NPRM
This proposed AD would retain all of the requirements of AD 2020-
23-05. This proposed AD would require inspecting the yokes of certain
swashplates, compliance with the established life limit, and a one-time
inspection of stripped yokes. This proposed AD would also include a
revised compliance time for the initial visual inspection of the yokes
on swashplates that have accumulated less than seven years since the
date of manufacture; and clarification that dye penetrant inspection of
the yoke is required before further flight if no cracks are detected
visually during the visual inspection. This proposed AD would require
accomplishing the actions specified in the service information
described previously, except as discussed under ``Differences Between
this Proposed AD and the EASA AD or Service Information.''
[[Page 3945]]
Differences Between This Proposed AD and the EASA AD or Service
Information
EASB No. 05A051, Revision 2, dated February 26, 2019 requires
performing a non-destructive inspection only if there is doubt whether
there is a crack. Instead, this proposed AD would require a visual
inspection and if no cracks are visually detected, would require a non-
destructive inspection.
The EASA AD specifies instructions for reporting inspection
results; this proposed AD would not.
Costs of Compliance
The FAA estimates that this AD, if adopted as proposed, would
affect 28 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 proposed AD. The new requirements
of this proposed AD add no additional economic burden.
Estimated Costs for Required Actions
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Action Labor cost Parts cost Cost per product Cost on U.S. operators
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Determination of the manufacture date 0.5 work-hour x $85 per hour $0 $43.............................. $1,204.
of the swashplate. = $43.
Inspecting the yokes.................. 0.25 work-hour x $85 per hour 0 $21 per inspection cycle......... $588 per inspection cycle.
= $21 per inspection cycle.
Removing grease, stripping the yokes, 8 work-hours x $85 per hour = 0 $680............................. $19,040.
and inspecting the stripped yokes. $680.
Creating a life limit record.......... 1 work-hour x $85 per hour = 0 $85.............................. $2,380.
$85.
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The FAA estimates the following costs to do any necessary on-
condition actions that would be required based on the results of any
required actions. The FAA has no way of determining the number of
aircraft that might need these on-condition actions:
Estimated Costs of On-Condition Actions
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Cost per
Action Labor cost Parts cost product
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Removing any corrosion or repairing damage 3 work-hours x $85 per hour = $255. $0 $255
within the allowable limit.
Replacing the swashplate................... 6 work-hours x $85 per hour = $510. 85,661 86,171
Dye-penetrant inspection................... 6 work-hours x $85 per hour = $510. 50 560
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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) Would not affect intrastate aviation in Alaska, and
(3) Would 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:
0
a. Removing Airworthiness Directive 2020-23-05, Amendment 39-21321 (85
FR 73604, November 19, 2020); and
0
b. Adding the following new airworthiness directive:
Airbus Helicopters: Docket No. FAA-2022-0015; Project Identifier
AD-2021-00832-R.
(a) Comments Due Date
The FAA must receive comments on this airworthiness directive
(AD) action by March 14, 2022.
(b) Affected ADs
This AD replaces AD 2020-23-05, Amendment 39-21321 (85 FR 73604,
November 19, 2020) (AD 2020-23-05).
(c) 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
[[Page 3946]]
(P/N) 332A31-3074-00 or P/N 332A31-3074-01 installed.
(d) Subject
Joint Aircraft Service Component (JASC) Code: 6230, Main Rotor
Mast/Swashplate.
(e) Unsafe Condition
This AD was prompted by a crack in a swashplate control rod
attachment yoke (yoke). The FAA is issuing this AD to detect and
correct a crack in a yoke. The unsafe condition, if not addressed,
could result in failure of the yoke, loss of M/R control, and
subsequent loss of control of the helicopter.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) 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)
or 7 days, whichever occurs first after the effective date of this
AD, and thereafter at intervals not to exceed 15 hours TIS or 7
days, whichever occurs first, 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 no cracks are visually detected, before further flight,
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, before further flight, 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.
(h) Credit for Previous Actions
If you performed the actions in paragraph (g)(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 have met the requirements of paragraph (g)(4)
of this AD.
(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: <a href="/cdn-cgi/l/email-protection#97aebad6c1c4bad6dec5baa0a4a7bad6dad8d4d7f1f6f6b9f0f8e1"><span class="__cf_email__" data-cfemail="8ab3a7cbdcd9a7cbc3d8a7bdb9baa7cbc7c5c9caecebeba4ede5fc">[email protected]</span></a>.
(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 Hal Jensen,
Aerospace Engineer, Operational Safety Branch, Compliance &
Airworthiness Division, FAA, 950 L'Enfant Plaza N SW, Washington, DC
20024; phone: (202) 267-9167; email: <a href="/cdn-cgi/l/email-protection#462e272a682c23283523280620272768212930"><span class="__cf_email__" data-cfemail="d6beb7baf8bcb3b8a5b3b896b0b7b7f8b1b9a0">[email protected]</span></a>.
(2) For service information identified in this AD, contact
Airbus Helicopters, 2701 North Forum Drive, Grand Prairie, TX 75052;
phone: (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 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 information on the
availability of this material at the FAA, call (817) 222-5110.
(3) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2019-0074, dated March 28, 2019
(EASA AD 2019-0074). You may view the EASA AD on the internet at
<a href="https://www.regulations.gov">https://www.regulations.gov</a> in Docket No. FAA-2022-0015.
Issued on January 20, 2022.
Lance T. Gant,
Director, Compliance & Airworthiness Division, Aircraft Certification
Service.
[FR Doc. 2022-01440 Filed 1-25-22; 8:45 am]
BILLING CODE 4910-13-P
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