Rule2022-26219
Airworthiness Directives; Airbus Helicopters
Primary source
Metadata and text below are from the Federal Register, a public-domain U.S. government work. Always verify the official published version before relying on it for any legal matter.
Published
December 2, 2022
Effective
January 6, 2023
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-23-05 for certain Airbus Helicopters Model EC225LP helicopters. AD 2020-23-05 required inspecting the control rod attachment yokes (yokes) of certain main rotor (M/R) rotating swashplates (swashplates), establishing a life limit, performing a one-time inspection of stripped yokes, and applicable corrective actions. Since the FAA issued AD 2020-23-05, the FAA has determined that certain swashplates are not susceptible to the unsafe condition, repetitive inspections for certain swashplates are necessary, and the criteria for when to perform a dye penetrant inspection needed to be revised. This AD retains some of the requirements of AD 2020-23-05 and also requires compliance with a revised life limit; performing a repetitive visual inspection of the yokes on certain swashplates; and depending on the inspection results, removing the affected swashplates from service, performing a dye penetrant inspection of the yoke, and additional corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
Full Text
<html>
<head>
<title>Federal Register, Volume 87 Issue 231 (Friday, December 2, 2022)</title>
</head>
<body><pre>
[Federal Register Volume 87, Number 231 (Friday, December 2, 2022)]
[Rules and Regulations]
[Pages 73921-73924]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-26219]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0015; Project Identifier AD-2021-00832-R;
Amendment 39-22252; AD 2022-24-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-23-05
for certain Airbus Helicopters Model EC225LP helicopters. AD 2020-23-05
required inspecting the control rod attachment yokes (yokes) of certain
main rotor (M/R) rotating swashplates (swashplates), establishing a
life limit, performing a one-time inspection of stripped yokes, and
applicable corrective actions. Since the FAA issued AD 2020-23-05, the
FAA has determined that certain swashplates are not susceptible to the
unsafe condition, repetitive inspections for certain swashplates are
necessary, and the criteria for when to perform a dye penetrant
inspection needed to be revised. This AD retains some of the
requirements of AD 2020-23-05 and also requires compliance with a
revised life limit; performing a repetitive visual inspection of the
yokes on certain swashplates; and depending on the inspection results,
removing the affected swashplates from service, performing a dye
penetrant inspection of the yoke, and additional corrective actions.
The FAA is issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective January 6, 2023.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of January 6,
2023.
ADDRESSES:
AD Docket: You may examine the AD docket at <a href="http://regulations.gov">regulations.gov</a> under
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 final rule, the European Union Aviation Safety
Agency (EASA) AD, any comments received, and other information. The
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.
[[Page 73922]]
Material Incorporated by Reference:
<bullet> For service information identified in this final rule,
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="http://airbus.com/helicopters/technical-services/support.html">airbus.com/helicopters/technical-services/support.html</a>.
<bullet> 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. It is also available at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-2022-0015.
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#b2dad3de9cd8d7dcc1d7dcf2d4d3d39cd5ddc4"><span class="__cf_email__" data-cfemail="6e060f0240040b001d0b002e080f0f40090118">[email protected]</span></a>.
SUPPLEMENTARY INFORMATION:
Background
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 to supersede AD 2020-23-05, Amendment 39-21321 (85 FR
73604, November 19, 2020) (AD 2020-23-05). AD 2020-23-05 applied to
Airbus Helicopters Model EC225LP helicopters with a swashplate part
number (P/N) 332A31-3074-00 or P/N 332A31-3074-01 installed. AD 2020-
23-05 required inspecting the yokes of certain swashplates,
establishing a life limit, performing a one-time inspection of stripped
yokes, and applicable corrective actions. The FAA issued AD 2020-23-05
to detect 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. The NPRM published in the Federal Register on January 26,
2022 (87 FR 3943). The NPRM was prompted by determinations following
the issuance of AD 2020-23-05 and EASA AD 2019-0074, dated March 28,
2019 (EASA AD 2019-0074), and issued by EASA, which is the Technical
Agent for the Member States of the European Union. EASA AD 2019-0074
stated that Airbus Helicopters established a life limit (also called a
service life limit) of 12 years for the swashplate and added a
reporting requirement if there is a crack or corrosion in a yoke. EASA
further advised that additional analysis determined that it is
necessary to introduce a new life limit for affected swashplates.
You may examine EASA AD 2019-0074 in the AD docket at
<a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA 2022-0015.
In the NPRM, the FAA proposed to continue to require all of the
requirements of AD 2020-23-05 and also proposed to require a revised
compliance time for the initial visual inspection of the yokes on
certain swashplates and clarify that dye penetrant inspection of the
yoke is required before further flight if no cracks are detected during
the visual inspection.
The FAA issued a supplemental notice of proposed rulemaking (SNPRM)
to amend 14 CFR part 39 to supersede AD 2020-23-05. The SNPRM published
in the Federal Register on July 29, 2022 (87 FR 45715). The SNPRM was
prompted by EASA AD 2019-0074R1, dated March 8, 2022 (EASA AD 2019-
0074R1), which revised EASA AD 2019-0074.
In the SNPRM, the FAA proposed to continue to require some of the
requirements of AD 2020-23-05 and also proposed to require compliance
with a revised life limit; performing a repetitive visual inspection of
the yokes on swashplates that have accumulated 7 or more years, but
less than 13 years, since the date of manufacture; and if a crack is
detected, removing the swashplate from service. If no cracks are
detected as a result of a visual inspection but a scratch or surface
degradation is detected, the SNPRM proposed to require performing a dye
penetrant inspection of the yoke. If a crack is detected during the dye
penetrant inspection, the SNPRM proposed to require removing the
swashplate from service.
Since the NPRM was issued, the FAA determined that swashplates that
have accumulated less than 7 years since the date of manufacture are
not susceptible to the unsafe condition. The FAA also determined that
repetitive inspections for swashplates that have accumulated 7 or more
years, but less than 13 years, since the date of manufacture are
necessary and the criteria for when to perform a dye penetrant
inspection needed to be revised. In light of this, the FAA revised the
SNPRM accordingly.
In the SNPRM, the FAA also corrected the description of what
prompted AD 2020-23-05, updated the related service information that
was proposed for incorporation by reference to the current revision,
and updated the estimated number of work-hours for inspecting the yokes
in the Costs of Compliance section.
Discussion of Final Airworthiness Directive
Comments
The FAA received no comments on the SNPRM 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. Except for minor editorial changes,
this AD is adopted as proposed in the SNPRM.
Related Service Information Under 1 CFR Part 51
The FAA reviewed one document that co-publishes two Airbus
Helicopters Emergency Alert Service Bulletin (EASB) identification
numbers: EASB No. 05A051 for Model EC225LP helicopters (EASB 05A051 Rev
4), and EASB No. 05A046 for non-FAA type-certificated Model EC725AP
helicopters (EASB 05A046 Rev 4), both Revision 4, and both dated
February 28, 2022. EASB 05A051 Rev 4 is incorporated by reference in
this AD; EASB 05A046 Rev 4 is not.
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 nondestructive inspection.
Additionally, this service information 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 13 years since
the date of manufacture for the swashplates and reporting requirements
if a crack or corrosion is discovered. EASB 05A051 Rev 4 also updates
the list of serial numbers and manufacture dates of the swashplates.
This service information is reasonably available because the
interested parties have access to it through their normal
[[Page 73923]]
course of business or by the means identified in the ADDRESSES section.
Differences Between This AD and EASA AD 2019-0074R1 or the Service
Information
EASB 05A051 Rev 4 specifies performing a non-destructive inspection
if in doubt about whether there is a crack in a yoke. This AD requires
a visual inspection and if no cracks are detected, visually inspecting
for a scratch and surface degradation. If a scratch or surface
degradation is detected, this AD requires a non-destructive inspection
(dye penetrant inspection). EASB 05A051 Rev 4 also specifies sending
the swashplate back to Airbus Helicopters if cracks are found, whereas
this AD does not require sending any affected parts back to Airbus
Helicopters.
EASA AD 2019-0074R1 requires reporting inspection results, whereas
this AD does not require reporting inspection results.
Costs of Compliance
The FAA estimates that this AD affects 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 AD.
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Determination of the manufacture 0.5 work-hour x $85 $0 $43................ $1,204.
date of the swashplate. per hour = $43.
Inspecting the yokes............. 0.5 work-hour x $85 0 $43 per inspection $1,204 per
per hour = $43 per cycle. inspection cycle.
inspection cycle.
Removing grease, stripping the 8 work-hours x $85 0 $680............... $19,040.
yokes, and inspecting the per hour = $680.
stripped yokes.
Creating a life limit record..... 1 work-hour x $85 0 $85................ $2,380.
per hour = $85.
----------------------------------------------------------------------------------------------------------------
The FAA estimates the following costs to do any necessary on-
condition actions that are 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
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
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
----------------------------------------------------------------------------------------------------------------
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 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:
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:
2022-24-12 Airbus Helicopters: Amendment 39-22252; Docket No. FAA-
2022-0015; Project Identifier AD-2021-00832-R.
(a) Effective Date
This airworthiness directive (AD) is effective January 6, 2023.
(b) Affected ADs
This AD replaces AD 2020-23-05, Amendment 39-21321 (85 FR 73604,
November 19, 2020).
[[Page 73924]]
(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 (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 results of testing, which determined
that a crack could develop in a swashplate control rod attachment
yoke (yoke), and the notification of a new life limit for certain
swashplates. 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 (EASB) No. 05A051,
Revision 4, dated February 28, 2022 (EASB 05A051 Rev 4) to determine
the date of manufacture of the swashplate.
(1) If the swashplate has accumulated 13 or more years since the
date of manufacture, remove the swashplate from service.
(2) If the swashplate has accumulated less than 13 years since
the date of manufacture, create a component history card or
equivalent record indicating a life limit of 13 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 any swashplate from service before accumulating 13 years
since the date of manufacture.
(3) For each swashplate that has accumulated 7 or more years,
but less than 13 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 13 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
Rev 4. If there is any crack on the yoke, before further flight,
remove the swashplate from service.
(i) If no cracks are visually detected, before further flight,
visually inspect for a scratch and surface degradation on the yoke.
(ii) If there is any scratch or surface degradation on the yoke,
before further flight, perform a dye penetrant inspection of the
yoke for a crack.
(iii) If there is any crack on the yoke, before further flight,
remove the swashplate from service.
(4) For each swashplate that has accumulated 7 or more years,
but less than 13 years, since the date of manufacture, within 100
hours TIS after the effective date of this AD:
(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 Rev 4. 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 Rev 4. 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 Rev 4 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 the
swashplate from service.
(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 Rev 4.
(A) If there is any crack on the yoke, before further flight,
remove the swashplate from service.
(B) If no cracks are visually detected, before further flight,
perform the actions as required in paragraphs (g)(3)(i) through
(iii) of this AD.
(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 EASB
No. 05A051, Revision 1, dated November 16, 2017; Airbus Helicopters
EASB No. 05A051, Revision 2, dated February 26, 2019; or Airbus
Helicopters EASB No. 05A051 Revision 3, dated December 7, 2021, you
have met the requirements of paragraph (g)(4) of this AD.
(i) Special Flight Permits
Special flight permits are prohibited.
(j) 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 (k)(1) of
this AD. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#576e7a1601047a161e057a6064677a161a18141731363679303821"><span class="__cf_email__" data-cfemail="596074180f0a7418100b746e6a69741814161a193f3838773e362f">[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.
(k) 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#4820292466222d263b2d26082e2929662f273e"><span class="__cf_email__" data-cfemail="89e1e8e5a7e3ece7faece7c9efe8e8a7eee6ff">[email protected]</span></a>.
(2) Airbus Helicopters Emergency Alert Service Bulletin (EASB)
No. 05A051, Revision 1, dated November 16, 2017; Airbus Helicopters
EASB No. 05A051, Revision 2, dated February 26, 2019; and Airbus
Helicopters EASB No. 05A051 Revision 3, dated December 7, 2021,
which are not incorporated by reference, contain additional
information about the subject of this AD. This service information
is available at the contact information specified in paragraphs
(l)(3) and (4) of this AD.
(3) The subject of this AD is addressed in European Union
Aviation Safety Agency (EASA) AD 2019-0074R1, dated March 8, 2022.
You may view the EASA AD at <a href="http://regulations.gov">regulations.gov</a> under Docket No. FAA-
2022-0015.
(l) 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.
05A051, Revision 4, dated February 28, 2022.
Note 1 to paragraph (l)(2)(i): Airbus Helicopters Emergency
Alert Service Bulletin No. 05A051, Revision 4, dated February 28,
2022, is co-published as one document along with Airbus Helicopters
Emergency Alert Service Bulletin No. 05A046, Revision 4, dated
February 28, 2022, which is not incorporated by reference in this
AD.
(ii) [Reserved]
(3) For Airbus Helicopters 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="http://airbus.com/helicopters/services/technical-support.html">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#690f1b4700071a190c0a1d0006072907081b08470e061f"><span class="__cf_email__" data-cfemail="dbbda9f5b2b5a8abbeb8afb2b4b59bb5baa9baf5bcb4ad">[email protected]</span></a>, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on November 16, 2022.
Christina Underwood,
Acting Director, Compliance & Airworthiness Division, Aircraft
Certification Service.
[FR Doc. 2022-26219 Filed 12-1-22; 8:45 am]
BILLING CODE 4910-13-P
</pre><script data-cfasync="false" src="/cdn-cgi/scripts/5c5dd728/cloudflare-static/email-decode.min.js"></script></body>
</html>Indexed from Federal Register on December 2, 2022.
This is legal information, not legal advice. Laws vary by jurisdiction and change frequently. Always verify current law with official sources and consult a licensed attorney in your jurisdiction for advice on your specific situation.