Airworthiness Directives; Airbus Helicopters

[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 [www.gpo.gov]
[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 regulations.gov 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 airbus.com/helicopters/technical-services/support.html.
    <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 
regulations.gov 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: [email protected].

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 
regulations.gov 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: [email protected].
    (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: [email protected].
    (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 regulations.gov 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 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 National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, email: [email protected], or go to: www.archives.gov/federal-register/cfr/ibr-locations.html.

    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

The complete text was extracted from the official GovInfo HTML edition for this publication. Acquired 2026-10-09T01:38:49.324071+00:00. Text extraction preserves the recorded source wording; it does not determine current requirements.

Open the captured official edition

Source SHA-256

3b1c1b60f9af407cc6b3f8a8c5e91e53d225d1e3d345856f972ed88bf6b98d91

Text SHA-256

03adcd7802a2cc56dadffe5c25e0f72426df6c694c74ca33280621e189d2a2c3