Rule2022-10952
Airworthiness Directives; Sikorsky Aircraft Corporation 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
May 23, 2022
Effective
June 27, 2022
Issuing agencies
Transportation DepartmentFederal Aviation Administration
Abstract
The FAA is superseding Airworthiness Directive (AD) 2020-26- 13, which applied to certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. AD 2020-26-13 required establishing the life limit for certain part-numbered horizontal stabilizer root fittings FWD (forward root fittings) and certain part-numbered stabilizer strut fittings. AD 2020-26-13 also required repetitively inspecting certain parts, and depending on the inspection results, removing parts from service. Finally AD 2020-26-13 prohibited installing certain stabilizer assemblies on any helicopter. Since the FAA issued AD 2020-26-13, the manufacturer notified the FAA that due to an error in the service information, certain part numbers in AD 2020-26-13 are incorrect. Also, the FAA determined that additional inspections are required to address the unsafe condition. This AD retains certain requirements and the prohibition for installing certain stabilizer assemblies on any helicopter from AD 2020-26-13, corrects certain part numbers, and requires additional repetitive inspections. The actions of this AD are intended to address an unsafe condition on these products.
Full Text
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<title>Federal Register, Volume 87 Issue 99 (Monday, May 23, 2022)</title>
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[Federal Register Volume 87, Number 99 (Monday, May 23, 2022)]
[Rules and Regulations]
[Pages 31125-31129]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2022-10952]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2022-0146; Project Identifier AD-2021-00449-R;
Amendment 39-22054; AD 2022-11-04]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding Airworthiness Directive (AD) 2020-26-
13, which applied to certain Sikorsky Aircraft Corporation (Sikorsky)
Model S-92A helicopters. AD 2020-26-13 required establishing the life
limit for certain part-numbered horizontal stabilizer root fittings FWD
(forward root fittings) and certain part-numbered stabilizer strut
fittings. AD 2020-26-13 also required repetitively inspecting certain
parts, and depending on the inspection results, removing parts from
service. Finally AD 2020-26-13 prohibited installing certain stabilizer
assemblies on any helicopter. Since the FAA issued AD 2020-26-13, the
manufacturer notified the FAA that due to an error in the service
information, certain part numbers in AD 2020-26-13 are incorrect. Also,
the FAA determined that additional inspections are required to address
the unsafe condition. This AD retains certain requirements and the
prohibition for installing certain stabilizer assemblies on any
helicopter from AD 2020-26-13, corrects certain part numbers, and
requires additional repetitive inspections. The actions of this AD are
intended to address an unsafe condition on these products.
DATES: This AD is effective June 27, 2022.
[[Page 31126]]
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of February 1,
2021 (85 FR 84201, December 28, 2020).
ADDRESSES: For service information identified in this final rule,
contact Sikorsky's Engineering Group at Sikorsky Aircraft Corporation,
124 Quarry Road, Trumbell, CT 06611, United States; phone: (800) 946-
4337; email: <a href="/cdn-cgi/l/email-protection#7f081c0c201c0a0c0b200c1a0d09161c1a201a111851180d520c16143f13121c10511c1012"><span class="__cf_email__" data-cfemail="a4d3c7d7fbc7d1d7d0fbd7c1d6d2cdc7c1fbc1cac38ac3d689d7cdcfe4c8c9c7cb8ac7cbc9">[email protected]</span></a>; website:
<a href="http://www.sikorsky360.com">www.sikorsky360.com</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. It is also available
at <a href="https://www.regulations.gov">https://www.regulations.gov</a> by searching for and locating Docket No.
FAA-2022-0146.
Examining the AD Docket
You may examine the AD docket on the internet at <a href="https://www.regulations.gov">https://www.regulations.gov</a> in Docket No. FAA-2022-0146; or in person at Docket
Operations between 9 a.m. and 5 p.m., Monday through Friday, except
Federal holidays. The AD docket contains this AD, any service
information that is incorporated by reference, 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.
FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aerospace Engineer,
Aviation Safety Section, Boston ACO Branch, Compliance & Airworthiness
Division, 1200 District Avenue, Burlington, MA 01803; telephone (781)
238-7693; email <a href="/cdn-cgi/l/email-protection#ecd5c1adbabfc1ada5bec1aeadafa3c1afa3bfac8a8d8dc28b839a"><span class="__cf_email__" data-cfemail="01382c4057522c4048532c4340424e2c424e52416760602f666e77">[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 2020-26-13, Amendment 39-21368 (85 FR
84201, December 28, 2020) (AD 2020-26-13). AD 2020-26-13 applied to
Sikorsky Model S-92A helicopters with forward root fitting part number
(P/N) 92209-07111-101 or 92070-20125-101; or stabilizer strut fitting
P/N 92209-07404-041, 92209-07403-041, or 92070-20117-041 installed on
horizontal stabilizer assembly (stabilizer assembly) P/N 92070-20117-
045, 92070-20117-046, 92070-20125-041, 92070-20125-042, 92070-20125-
043, 92070-20125-044, 92205-07400-043, or 92205-07400-045. The NPRM
published in the Federal Register on February 23, 2022 (87 FR 10115).
The NPRM was prompted by the discovery that incorrect P/Ns were
identified in the Applicability and the Required Actions paragraphs of
AD 2020-26-13. Additionally, after the FAA issued AD 2020-26-13,
Sikorsky notified the FAA that an additional repetitive inspection of
certain parts of the stabilizer strut assembly is required to prevent
the unsafe condition. Finally, after the FAA issued AD 2020-26-13,
Sikorsky requested and the FAA approved a global Alternative Method of
Compliance (AMOC) to allow only removing parts from service that are
cracked, corroded, or have fretting, deformation, or wear rather than
require removing the upper and lower support strut rod ends, including
lug and conical fitting and both upper and lower attachment fittings on
the stabilizer from service.
In the NPRM, the FAA proposed to expand the applicability of AD
2020-26-13 by adding an additional part-numbered stabilizer assembly.
The NPRM also proposed to correct paragraph (g)(4) of the Required
Actions so that the installation of the titanium stabilizer strut
fitting is terminating action for the 50-hour time-in-service (TIS)
inspections of the aluminum stabilizer strut fitting. The NPRM also
proposed to require an additional repetitive inspection of certain
parts of the stabilizer strut assembly. Finally, the NPRM proposed to
incorporate the FAA approved global AMOC.
Discussion of Final Airworthiness Directive
Comments
The FAA received a comments from Sikorsky stating that in the
section titled ``Actions Since AD 2020-26-13 Was Issued'' of the NPRM,
the part number specified (92070-20117-04) is incorrect and should be
92070-20117-041. The FAA acknowledges this comment; however, the part
number is not used in the ``Background'' section of this final rule. In
light of this, the commenter's request no longer applies.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety requires adopting the AD as
proposed. Accordingly, the FAA is issuing this AD to address the unsafe
condition on these products. Except for minor editorial changes, and
any other changes described previously, this AD is adopted as proposed
in the NPRM. None of the changes will increase the economic burden on
any operator.
Related Service Information Under 1 CFR Part 51
This AD continues to require S-92 Maintenance Manual, SA S92A-AMM-
000, Temporary Revision (TR) 55-33, dated March 24, 2020 (TR 55-33),
which the Director of the Federal Register approved for incorporation
by reference as of February 1, 2021 (85 FR 84201, December 28, 2020).
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section.
Other Related Service Information
The FAA reviewed S-92 Maintenance Manual SA S92A-AWL-000, TR No. 4-
58, dated October 2, 2017 (TR 4-58), and S-92 Maintenance Manual SA
S92A-AWL-000, TR No. 4-66 dated November 20, 2019 (TR 4-66). This
service information revises Task 4-00-00-200-000, Table 1 Replacement
Schedule, dated November 30, 2015. Both TR 4-58 and 4-66 revise the
Airworthiness Limitations Schedule by removing certain part-numbered
components, introducing new part-numbered components, and establishing
replacement intervals and recurring inspections for the forward root
fitting and the horizontal stabilizer strut fitting. TR 4-58 also
specifies inspecting the horizontal stabilizer and attaching hardware
at a recurring interval of 250 hours TIS.
Differences Between This AD and the Service Information
The service information requires returning affected parts to a
Sikorsky specialist; this AD does not.
Costs of Compliance
The FAA estimates that this AD affects 82 helicopters of U.S.
registry. Labor costs are estimated at $85 per work-hour. Based on
these numbers, the FAA estimates the following costs to comply with
this AD.
Visually inspecting the stabilizer assembly and attached hardware
takes about 3 work-hours for an estimated cost of $255 per helicopter
and $20,910 for the U.S. fleet per inspection cycle.
If required, replacing a hat bushing and both upper fittings and
lower fittings takes about 1 work-hour and parts cost about $10,000 for
an estimated cost of $10,085 per replacement.
[[Page 31127]]
If required, replacing the upper and lower support strut rod ends,
including lug and conical fitting, takes about 1 work-hour and parts
cost about $10,000 for an estimated cost of $10,085 per replacement.
If required, replacing Mylar washers takes about 0.5 work-hour and
parts cost about $76 for an estimated cost of $119 per replacement.
If required, performing a fluorescent penetrant inspection takes
about 3 work-hours for an estimated cost of $255 per inspection.
If required, replacing a stabilizer assembly takes about 6 work-
hours and parts cost about $312,000 for an estimated cost of $312,510
per replacement.
If required, replacing a forward root fitting takes about 10 work-
hours and parts cost about $25,000 for an estimated cost of $25,850 per
replacement.
If required, replacing a stabilizer strut fitting takes about 10
work-hours and parts cost about $10,000 for an estimated cost of
$10,850 per replacement.
If required, replacing a forward root fitting and an aft attachment
fitting takes about 20 work-hours and parts cost about $50,000 for an
estimated cost of $51,700 per replacement.
If required, removing wear or corrosion and applying corrosion
preventative compound takes about 0.5 work-hour and parts cost a
nominal amount for an estimated cost of $43 per action.
If required, replacing a stabilizer attachment bolt and barrel nut
set takes about 1 work-hour and parts cost about $500 for an estimated
cost of $585 per replacement.
If required, replacing a fastener takes about 0.1 work-hour and
parts cost a nominal amount for an estimated cost of $9 per fastener.
If required, removing the abrasion-resistant Teflon coating to
inspect each forward and aft attachment fitting mating surface takes
about 5 work-hours for an estimated cost of $425 per inspection.
If required, applying alodine or equivalent and applying abrasion-
resistant Teflon coating takes about 5 work hours with minimal parts
cost for an estimated cost of $425 per application.
According to Sikorsky, some of the costs of this AD may be covered
under warranty, thereby reducing the cost impact on affected
individuals. The FAA does not control warranty coverage for affected
individuals. As a result, the FAA has included all costs in this cost
estimate.
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 has determined that 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 AD 2020-26-13, Amendment 39-21368
(85 FR 84201, December 28, 2020); and
0
b. Adding the following new airworthiness directive:
2022-11-04 Sikorsky Aircraft Corporation: Amendment 39-22054; Docket
No. FAA-2022-0146; Project Identifier AD-2021-00449-R.
(a) Effective Date
This airworthiness directive (AD) is effective June 27, 2022.
(b) Affected ADs
This AD replaces AD 2020-26-13, Amendment 39-21368 (85 FR 84201,
December 28, 2020) (AD 2020-26-13).
(c) Applicability
This AD applies to Sikorsky Aircraft Corporation Model S-92A
helicopters, certificated in any category, with the following
installed: Horizontal stabilizer root fitting FWD (forward root
fitting) part number (P/N) 92209-07111-101 or 92070-20125-101; or
stabilizer strut fitting P/N 92209-07403-041 or 92070-20117-041
installed on horizontal stabilizer assembly (stabilizer assembly) P/
N 92070-20117-045, 92070-20117-046, 92070-20125-041, 92070-20125-
042, 92070-20125-043, 92070-20125-044, 92205-07400-043, 92205-07400-
045, or 92205-07400-047.
(d) Subject
Joint Aircraft System Component (JASC) Code: 5510, Horizontal
Stabilizer Structure.
(e) Unsafe Condition
This AD was prompted by incidents of fatigue cracks in a forward
root fitting and life limit recalculations for forward root fitting
P/N 92209-07111-101 and 92070-20125-101. The FAA is issuing this AD
to prevent a forward root fitting from remaining in service beyond
its life limit, detect fatigue cracking in a forward root fitting,
and prevent increased load and stress cracking in the stabilizer
root fitting aft. The unsafe condition, if not addressed, could
result in failure of a stabilizer root fitting, separation of the
stabilizer assembly from the helicopter, 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
(1) Within 50 hours time-in-service (TIS) after the effective
date of this AD:
(i) Determine the total hours TIS of the forward root fitting P/
N 92209-07111-101 or 92070-20125-101. If the total hours TIS of the
forward root fitting is unknown, use the total hours TIS of the
stabilizer assembly instead.
(A) If the forward root fitting has accumulated 7,900 or more
total hours TIS, before further flight, remove the forward root
fitting from service.
(B) If the forward root fitting has accumulated less than 7,900
total hours TIS,
[[Page 31128]]
before exceeding 7,900 total hours TIS, remove the forward root
fitting from service.
(ii) Thereafter following paragraph (g)(1)(i) of this AD, remove
the forward root fitting from service before accumulating 7,900
total hours TIS.
(iii) For stabilizer assemblies with stabilizer strut fitting P/
N 92070-20117-041 installed, perform the following actions:
(A) Determine the total hours TIS of stabilizer strut fitting P/
N 92070-20117-041.
(B) If the stabilizer strut fitting has accumulated 19,100 or
more total hours TIS, before further flight, remove the stabilizer
strut fitting from service.
(C) If the stabilizer strut fitting has accumulated less than
19,100 total hours TIS, before exceeding 19,100 total hours TIS,
remove the stabilizer strut fitting from service.
(iv) Thereafter following paragraph (g)(1)(iii) of this AD,
remove the stabilizer strut fitting from service before accumulating
19,100 total hours TIS.
(2) For helicopters with stabilizer strut fitting P/N 92070-
20117-041 or 92209-07403-041 installed, within 50 hours TIS after
the effective date of this AD and thereafter at intervals not to
exceed 50 hours TIS:
(i) Remove the support strut and using a cheese cloth (or
similar cloth) and isopropyl alcohol, clean the upper and lower
support strut rod ends, horizontal stabilizer attachment fitting,
and the tail rotor pylon attachment fitting.
(ii) If installed, visually inspect the surface of each Mylar
washer P/N 92070-20117-104 (Mylar washer). The surface should be
smooth and continuous. If there is any visible damage such as any
tear or scrape, remove the Mylar washer from the peelable-ply washer
P/N 92070-20117-105 (peelable-ply washer) and remove the Mylar
washer from service as follows:
(A) Dampen a low-lint cloth with 3M 6041 adhesive remover and
place on the top of the Mylar washer.
(B) Allow the adhesive remover to soften the Mylar washer and
peel the Mylar washer back.
(C) Repeat with more solvent until the Mylar washer and adhesive
are removed.
(D) Clean the peelable-ply washer with cheese cloth moistened
with isopropyl alcohol and adhere a new Mylar washer to the
peelable-ply washer.
Note 1 to paragraph (g)(2)(ii): Stabilizer assembly P/Ns 92070-
20125-041, 92070-20125-042, 92070-20125-043, and 92070-20125-044 do
not utilize the Mylar washer. The inspection of the Mylar washer is
not required on helicopters with stabilizer assembly P/N 92070-
20125-041, 92070-20125-042, 92070-20125-043, or 92070-20125-044
installed.
(iii) Using a 10X or higher power magnifying glass, a
flashlight, and a mirror, visually inspect the hat bushing and both
upper fittings and lower fittings for a crack, corrosion, fretting,
deformation, and wear. If there is a crack, corrosion, fretting,
deformation, or wear on any part, before further flight, remove the
part from service.
(iv) Using a 10X or higher power magnifying glass, a flashlight,
and a mirror, visually inspect both upper and lower support strut
rod ends, including each lug and conical fitting, and both upper and
lower attachment fittings on the stabilizer and pylon including the
bushings for a crack, corrosion, fretting, deformation, and wear. If
there is a crack, corrosion, fretting, deformation, or wear on any
part, before further flight, remove the part from service.
(3) Within 250 hours TIS or one year, whichever occurs first
after the effective date of this AD, and thereafter at intervals not
to exceed 250 hours TIS or one year, whichever occurs first:
(i) Remove the stabilizer assembly and visually inspect each
stabilizer attachment bolt and barrel nut set for corrosion, a
crack, and damage to the threads. For the purposes of this
inspection, damage may be indicated by uneven threads, missing
threads, or cross-threading.
(A) If there is corrosion within allowable limits, before
further flight, treat for corrosion in accordance with FAA-approved
procedures.
(B) If there is corrosion that exceeds allowable limits, or a
crack, or damage to the threads, before further flight, remove the
bolt and barrel nut set from service.
(ii) Inspect the forward root fitting and the aft attachment
fitting by:
(A) Gaining access to the inside of the horizontal stabilizer.
(B) Using Brulin Cleaner SD 1291 (or equivalent) and a low-lint
cloth, remove all traces of sealing compound, oil, and dirt from the
stabilizer mounting surfaces.
(C) Using a 10X or higher magnifying glass, inspect for any
crack, wear, and corrosion.
(1) If there is a crack, before further flight, remove the
affected forward root fitting and the affected aft attachment
fitting from service.
(2) If there is wear or corrosion that exceeds allowable limits,
before further flight, remove the affected forward root fitting and
the affected aft attachment fitting from service.
(3) If there is wear or corrosion within allowable limits,
before further flight, treat for corrosion in accordance with FAA-
approved procedures.
(D) Visually inspect each attachment fitting bolt hole and
fastener hole for a crack, wear, and corrosion.
(1) If there is a crack, before further flight, remove the
affected forward root fitting and the affected aft attachment
fitting from service.
(2) If there is wear or corrosion that exceeds allowable limits,
before further flight, remove the affected forward root fitting and
the affected aft attachment fitting from service.
(3) If there is wear or corrosion within allowable limits,
before further flight, treat for corrosion in accordance with FAA
approved procedures.
(E) Inspect for loose or working fasteners. If there is a loose
or working fastener, before further flight, remove the fastener from
service.
(iii) As an alternative means to inspect for cracks in
paragraphs (g)(3)(i) and (ii) of this AD, perform a florescent
penetrant inspection (FPI).
(iv) Visually inspect each forward and aft attachment fitting
mating surface for wear of the abrasion-resistant Teflon coating and
degradation. For the purposes of this inspection, degradation may be
indicated by fretting. Refer to Figure 204, of S-92 Maintenance
Manual, SA S92A-AMM-000, Temporary Revision 55-33, Task 55-11-01-
210-004, dated March 24, 2020 (TR 55-33), for a depiction of the
area to be inspected. For the purposes of this inspection, wear may
be indicated by less than 100% coverage of the abrasion-resistant
Teflon coating. If there is wear to the abrasion-resistant Teflon
coating or degradation, before further flight:
(A) Chemically strip the abrasion-resistant Teflon coating from
the entire mounting pad in accordance with paragraph 7.A.(7)(a) of
TR 55-33.
(B) FPI or eddy current inspect for a crack. If there is a
crack, before further flight, remove the stabilizer assembly from
service.
(C) If there is no crack, treat the affected area by applying
alodine or equivalent. Apply abrasion-resistant Teflon coating in
accordance with paragraphs 7.A.(7)(d) through (e) of TR 55-33.
(4) Installing stabilizer strut fitting P/N 92209-07404-041 is a
terminating action for the requirements in paragraph (g)(2) of this
AD.
(5) As of the effective date of this AD, do not install
stabilizer assembly P/N 92205-07400-043, 92205-07400-045, or 92205-
07400-047 on any helicopter.
(h) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston ACO 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 certification office, send it to the attention of the
person identified in paragraph (i) of this AD.
(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.
(i) Related Information
For more information about this AD, contact Dorie Resnik,
Aerospace Engineer, Boston ACO Branch, 1200 District Avenue,
Burlington, Massachusetts 01803; telephone 781-238-7693; email <a href="/cdn-cgi/l/email-protection#231a0e6275700e626a710e6162606c0e606c70634542420d444c55"><span class="__cf_email__" data-cfemail="10293d5146433d5159423d5251535f3d535f43507671713e777f66">[email protected]</span></a>.
(j) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless the AD specifies otherwise.
(3) The following service information was approved for IBR on
February 1, 2021 (85 FR 84201, December 28, 2020).
[[Page 31129]]
(i) S-92 Maintenance Manual, SA S92A-AMM-000, Temporary Revision
(TR) 55-33, dated March 24, 2020.
(ii) [Reserved]
(4) For Sikorsky Aircraft Corporation service information
identified in this AD, contact Sikorsky's Engineering Group at
Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbell, CT 06611,
United States; phone: (800) 946-4337; email:
<a href="/cdn-cgi/l/email-protection#611602123e021412153e120413170802043e040f064f06134c12080a210d0c020e4f020e0c"><span class="__cf_email__" data-cfemail="017662725e627472755e726473776862645e646f662f66732c72686a416d6c626e2f626e6c">[email protected]</span></a>; website: <a href="http://www.sikorsky360.com">www.sikorsky360.com</a>.
(5) You may view this service information at 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.
(6) 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#274155094e4954574244534e4849674946554609404851"><span class="__cf_email__" data-cfemail="2543570b4c4b56554046514c4a4b654b4457440b424a53">[email protected]</span></a>, or go to: <a href="https://www.archives.gov/federal-register/cfr/ibr-locations.html">https://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued on May 16, 2022.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2022-10952 Filed 5-20-22; 8:45 am]
BILLING CODE 4910-13-P
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