[Federal Register Volume 87, Number 145 (Friday, July 29, 2022)]
[Proposed Rules]
[Pages 45715-45719]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2022-16163]



[[Page 45715]]

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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: Supplemental notice of proposed rulemaking (SNPRM).

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SUMMARY: The FAA is revising a notice of proposed rulemaking (NPRM) 
that would have applied to certain Airbus Helicopters Model EC225LP 
helicopters. This action revises the NPRM by removing the requirement 
to remove main rotor (M/R) rotating swashplates (swashplates) from 
service that have accumulated less than 7 years since the date of 
manufacture; increasing the life limit for certain swashplates; 
requiring additional visual inspections, and adding repetitive 
inspections for certain swashplates that have accumulated 7 or more 
years, but less than 13 years, since the date of manufacture; and 
updating the service information. The FAA is proposing this 
airworthiness directive (AD) to address the unsafe condition on these 
products. Since these actions would impose an additional burden over 
those in the NPRM, the agency is requesting comments on this SNPRM.

DATES: The FAA must receive comments on this SNPRM by September 12, 
2022.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to www.regulations.gov. 
Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     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.
     Hand Delivery: Deliver to Mail address between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this SNPRM, 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 
www.airbus.com/helicopters/technical-services/support.html. 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 www.regulations.gov 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 the NPRM, this SNPRM, 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: [email protected].

SUPPLEMENTARY INFORMATION:

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 again 
revise 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 
www.regulations.gov, including any personal information you provide. 
The agency will also post a report summarizing each substantive verbal 
contact received about this proposed AD.

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 SNPRM 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 SNPRM, 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 SNPRM. 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; telephone: (202) 267-9167; email: 
[email protected]. 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 an NPRM to amend 14 CFR part 39 by adding an AD that 
would apply to Airbus Helicopters Model EC225LP helicopters, with an M/
R swashplate part number (P/N) 332A31-3074-00 or P/N 332A31-3074-01 
installed. The NPRM published in the Federal Register on January 26, 
2022 (87 FR 3943). The NPRM proposed to supersede AD 2020-23-05, 
Amendment 39-21321 (85 FR 73604, November 19, 2020) (AD 2020-23-05), 
which applies to certain Airbus Helicopters Model EC225LP helicopters. 
AD 2020-23-05 requires inspecting the swashplate control rod attachment 
yokes (yokes) of certain swashplates, establishing a life limit, 
performing a one-time inspection of stripped yokes, and applicable 
corrective actions. AD 2020-23-05 was prompted by a crack in a yoke, 
which could result in failure of the yoke, loss of M/R control, and 
subsequent loss of control of the helicopter. AD 2020-23-05 was also 
prompted by EASA AD 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 correct an unsafe condition for Airbus 
Helicopters (AH), formerly Eurocopter, Eurocopter France, Model EC 225 
LP helicopters. EASA advised 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 the affected 
swashplates.
    In the NPRM, the FAA proposed to retain all the requirements of AD 
2020-23-05. The NPRM also proposed to include a revised compliance time 
for the initial visual inspection of the yokes

[[Page 45716]]

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 
during the visual inspection.
    The NPRM was prompted by the determination that a revised 
compliance time is necessary for swashplates that have accumulated less 
than seven years since the date of manufacture. The FAA has also 
determined that clarification is necessary regarding when it is 
necessary to do a dye penetrant inspection of the yoke.

Actions Since the NPRM Was Issued

    Since the NPRM was issued, EASA issued EASA AD 2019-0074R1, dated 
March 8, 2022 (EASA AD 2019-0074R1), which supersedes EASA AD 2019-
0074. EASA advises that additional investigation confirmed that the 
life limit of certain swashplates can be extended and Airbus 
Helicopters has issued updated service information to reflect the new 
life limit.
    Also, 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 and should be 
removed from paragraph (g) of the proposed AD. The FAA also determined 
that paragraph (g) of the proposed AD needs to be revised to include 
repetitive inspections for swashplates that have accumulated 7 or more 
years, but less than 13 years, since the date of manufacture, and the 
criteria for when to perform a dye penetrant inspection needs to be 
revised.
    The FAA determined there was an error in the Background section of 
the NPRM, which stated, ``AD 2020-23-05 was prompted by a crack in a 
swashplate yoke.'' The FAA determined AD 2020-23-05 was not prompted by 
a crack in a yoke, but was prompted by testing conducted by Airbus 
Helicopters, which determined cracks may develop overtime. The FAA also 
determined that the applicable service information required by the 
proposed AD needs to be revised in order to include the updated 
revision.
    Finally, the FAA determined that the time estimated for inspecting 
the yokes needed to be increased from 0.25 work-hour to 0.50 work-hour, 
which increased the estimated cost for that inspection from $21 to $43 
per helicopter per inspection cycle.

Comments

    The following discussion presents the comments received on the NPRM 
and the FAA's response.

Request To Revise the Required Actions Paragraph of the Proposed AD

    Five commenters requested the FAA revise the Required Actions 
paragraph of the proposed AD by removing the visual inspection for 
swashplates that have accumulated less than 7 years since the date of 
manufacture. Airbus Helicopters stated that testing was performed for 
certain aluminum alloys and as a result Airbus Helicopters defined a 
calendar threshold of 7 years, after which the swashplate may present 
crack initiation. Airbus Helicopters further explained due to this 
testing, there is no rationale to require the visual inspection prior 
to the 7 year threshold. An additional commenter stated the inspection 
for swashplates that have accumulated less than 7 years since the date 
of manufacture is not in line with the required service information. 
Additionally, Air Center Helicopters Inc., explained that the EASA AD 
and the service information do not require repetitive visual 
inspections for any swashplates that have accumulated less than 7 years 
since the date of manufacture and that these repetitive inspections are 
not required until after the swashplate has accumulated 7 or more years 
since the date of manufacture.
    The FAA agrees and has revised the Required Actions paragraph of 
this proposed AD by removing the inspection requirements for 
swashplates that have accumulated less than 7 years since the date of 
manufacture.
    Four commenters requested the FAA revise the Required Actions 
paragraph to include a repetitive visual inspection, at intervals not 
to exceed 15 hours time-in-service (TIS) or 7 days, after certain 
swashplates have accumulated 7 or more years since the date of 
manufacture. Three commenters also requested that the FAA revise the 
Required Actions paragraph of this proposed AD to require that this 
repetitive visual inspection be performed utilizing a bright light and 
10X magnifying glass.
    The FAA partially agrees. The FAA agrees to revise the Required 
Actions paragraph of this proposed AD to include a repetitive visual 
inspection, at intervals not to exceed 15 hours TIS or 7 days, 
whichever occurs first, for swashplates that have accumulated 7 or more 
years, but less than 13 years, since the date of manufacture, until the 
swashplate accumulates 13 years since the date of manufacture. The FAA 
disagrees with mandating the use of a bright light and 10X magnifying 
glass for this repetitive visual inspection because the FAA has not 
determined that a bright light or 10X magnifying glass are necessary 
for this repetitive visual inspection; however an operator may choose 
to use this inspection method.
    Five commenters requested the FAA revise the Required Actions 
paragraph to remove the dye penetrant inspection in situations where no 
crack is detected. Airbus Helicopters stated with regards to crack 
detectability, the dye penetrant inspection creates an unnecessary 
burden if no crack is detected visually, and should only be performed 
if a scratch or surface degradation is detected. Two commenters also 
stated performing the dye penetrant inspection, if a crack is not 
detected, would increase the estimated costs and downtime for 
operators.
    The FAA agrees to revise the Required Actions paragraph of this 
proposed AD to include an additional visual inspection for a scratch 
and surface degradation, if no crack is detected. The FAA determined if 
any indications of scratches or surface degradation are detected during 
the visual inspection, a dye penetrant inspection must be performed to 
address the unsafe condition. Accordingly, the FAA has revised the 
Required Actions paragraph to require a visual inspection for a scratch 
and surface degradation if no cracks are visually detected, and a dye 
penetrant inspection if there is any scratch or surface degradation.
    Five commenters requested the FAA revise the Required Actions 
paragraph to extend the life limit of the swashplate from 12 years to 
13 years, in accordance with the revised service information.
    The FAA agrees and has revised the Required Actions paragraph of 
this proposed AD by increasing the life limit of the swashplate to 13 
years.

Request To Use Latest Revision of the Applicable Service Information

    Three commenters requested that the FAA revise the proposed AD to 
reference EASA AD 2019-0074R1 instead of EASA AD 2019-0074. The 
commenters also requested that the FAA revise the proposed AD to 
reference Airbus Helicopters Emergency Alert Service Bulletin (EASB) 
No. 05A051, Revision 4, dated February 28, 2022 (EASB 05A051 Rev 4), 
instead of Airbus Helicopters EASB No. 05A051 and EASB No. 05A046, each 
Revision 2, and dated February 26, 2019.
    The FAA agrees EASA AD 2019-0074R1 and EASB 05A051 Rev 4 are the 
appropriate sources of related information for the actions specified, 
and has revised this proposed AD to reference this updated information.

[[Page 45717]]

Request To Approve Future Revisions of the Service Information

    Three commenters requested that the FAA revise the proposed AD to 
consider the accomplishment of future revisions of EASB 05A051 Rev 4 as 
acceptable for compliance with the proposed AD. Two commenters stated 
EASA AD 2019-0074R1 allows the use of future revisions of the 
applicable service information and requested that the FAA also allow 
compliance with later revisions. One commenter stated later revisions 
of the applicable service information should be allowed in order to 
capture future applicable appendixes, swashplate serial numbers, and 
swashplate manufacture dates.
    The FAA disagrees with the request to allow future revisions of the 
applicable service information as acceptable for compliance with the 
proposed AD. Referring to documents that do not exist at the time the 
final rule is published violates Office of the Federal Register (OFR) 
regulations regarding approval of materials ``incorporated by 
reference'' in rules. These OFR regulations require that either the 
service document be submitted for approval by the OFR as ``referenced'' 
material, in which case it may be simply called out in the text of an 
AD, or the service document contents be published as part of the actual 
AD language. An AD may reference only the specific service document 
that was submitted and approved by the OFR for ``incorporation by 
reference.'' In order for operators to use later revisions of the 
referenced document (issued after the publication of the AD), either 
the FAA must revise the AD to reference the specific later revisions, 
or operators must request the approval of their use as an alternative 
method of compliance under the provisions of paragraph (j) of this 
proposed AD.

Request To Revise the Background Section of the Proposed AD

    One commenter requested that the FAA revise the background section 
of the NPRM to indicate that no cracks to the swashplate have been 
detected in service, but testing by Airbus Helicopters determined that 
cracks could develop over time.
    The FAA agrees with the commenter and has revised the Actions Since 
the NPRM was Issued section in this proposed AD accordingly.

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 determining the unsafe condition described previously is likely 
to exist or develop in other helicopters of the same type design. 
Certain changes described above expand the scope of the NPRM. As a 
result, it is necessary to reopen the comment period to provide 
additional opportunity for the public to comment on this SNPRM.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed one document that co-publishes two Airbus 
Helicopters EASB identification numbers: EASB 05A051 Rev 4 for Model 
EC225LP helicopters and EASB No. 05A046 for non-FAA type-certificated 
Model EC725AP helicopters, Revision 4, dated February 28, 2022 (EASB 
05A046 Rev 4). 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. 
EASB 05A046 Rev 4, dated February 28, 2022, is not proposed for 
incorporation by reference in this SNPRM.
    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 SNPRM

    This proposed AD would retain some of the requirements of AD 2020-
23-05. This proposed AD would also require compliance with a revised 
life limit, 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 but a scratch or 
surface degradation is detected, this proposed AD would require 
performing a dye penetrant inspection of the yoke. If a crack is 
detected during the dye penetrant inspection, this proposed AD would 
require removing the swashplate from service.

Differences Between This SNPRM and EASA AD 2019-0074R1 or the Service 
Information

    EASB 05A051 Rev 4 requires performing a non-destructive inspection 
if in doubt about whether there is a crack in a yoke. This proposed AD 
would require 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 proposed AD would require 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 proposed AD would not require sending 
any affected parts back to Airbus Helicopters.
    EASA AD 2019-0074R1 specifies instructions for reporting inspection 
results, whereas this proposed AD would not require reporting 
inspection results.

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.

                                                          Estimated Costs for Required Actions
--------------------------------------------------------------------------------------------------------------------------------------------------------
                Action                          Labor cost           Parts cost             Cost per product                 Cost on U.S. operators
--------------------------------------------------------------------------------------------------------------------------------------------------------
Determination of the manufacture date   0.5 work-hour x $85 per                $0  $43...............................  $1,204.
 of the swashplate.                      hour = $43.

[[Page 45718]]

 
Inspecting the yokes..................  0.5 work-hour x $85 per                 0  43 per inspection cycle...........  1,204 per inspection cycle.
                                         hour = $43 per
                                         inspection cycle.
Removing grease, stripping the yokes,   8 work-hours x $85 per                  0  680...............................  19,040.
 and inspecting the stripped yokes.      hour = $680.
Creating a life limit record..........  1 work-hour x $85 per                   0  85................................  2,380.
                                         hour = $85.
--------------------------------------------------------------------------------------------------------------------------------------------------------

    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
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Removing any corrosion or repairing damage      3 work-hours x $85 per hour =                 $0            $255
 within the allowable limit.                     $255.
Replacing the swashplate......................  6 work-hours x $85 per hour =             85,661          86,171
                                                 $510.
Dye-penetrant inspection......................  6 work-hours x $85 per hour =                 50             560
                                                 $510.
----------------------------------------------------------------------------------------------------------------

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 September 12, 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 (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

[[Page 45719]]

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 Permit

    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; telephone: (202) 267-9167; email: [email protected].
    (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 
www.airbus.com/helicopters/services/technical-support.html. You may 
view this referenced service information at the FAA, Office of the 
Regional Counsel, Southwest Region, 10101 Hillwood Pkwy., Room 6N-
321, Fort Worth, TX 76177. For 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 2019-0074R1, dated March 8, 2022. 
You may view the EASA AD at www.regulations.gov in Docket No. FAA-
2022-0015.

    Issued on July 22, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2022-16163 Filed 7-28-22; 8:45 am]
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