Document ID: FAA-2020-0792-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Sikorsky Aircraft Corporation Helicopters
Posted Date: 2020-09-17T04:00Z

[Federal Register Volume 85, Number 181 (Thursday, September 17, 2020)]
[Proposed Rules]
[Pages 58007-58010]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-20482]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2020-0792; Product Identifier 2018-SW-049-AD]
RIN 2120-AA64

Airworthiness Directives; Sikorsky Aircraft Corporation 
Helicopters

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters. 
This proposed AD was prompted by seven incidents of fatigue cracks in 
the horizontal stabilizer root fitting FWD (forward root fitting). This 
proposed AD would require establishing the life limit of certain part-
numbered forward root fittings, establishing the life limit of certain 
part-numbered stabilizer strut fittings, repetitively inspecting 
certain parts, and depending on the inspection results, removing parts 
from service. This proposed AD would also prohibit the installation of 
certain parts. The FAA is proposing this AD to address the unsafe 
condition on these products.

DATES: The FAA must receive comments on this proposed AD by November 2, 
2020.

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 https://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 above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact your local 
Sikorsky Field Representative or Sikorsky's Service Engineering Group 
at Sikorsky Aircraft Corporation, 124 Quarry Road, Trumbull, CT 06611; 
telephone 1-800-946-4337 (1-800-Winged-S); email 
wcs_cust_service_eng.gr-sik@lmco.com. Operators may also log on to the 
Sikorsky 360 website at https://www.sikorsky360.com. 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 on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2020-
0792; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, any comments received, and other information. The street 
address for Docket Operations is listed above. Comments will be 
available in the AD docket shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dorie Resnik, Aerospace Engineer, 
Boston ACO Branch, 1200 District Avenue, Burlington, Massachusetts 
01803; telephone 781-238-7693; email dorie.resnik@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    The FAA invites you to send any written relevant data, views, or 
arguments about this proposal. The most helpful comments reference a 
specific portion of the proposal, explain the reason for any 
recommended change, and include supporting data. To ensure the docket 
does not contain duplicate comments, commenters should send only one 
copy of written comments, or if comments are filed electronically, 
commenters should submit only one time.
    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 file in the docket all comments received, as well 
as a report summarizing each substantive public contact with FAA 
personnel concerning this proposed rulemaking. Before acting on this 
proposal, the FAA will consider all comments received on or before the 
closing date for comments. The FAA will consider comments filed after 
the comment period has closed if it is possible to do so without 
incurring expense or delay. The FAA may change this proposal in light 
of the comments received.

Confidential Business Information

    Confidential Business Information (CBI) is commercial or financial 
information that is both customarily and actually treated as private by 
its owner. Under the Freedom of Information Act (FOIA) (5 U.S.C. 552), 
CBI is exempt from public disclosure. If your comments responsive to 
this NPRM contain commercial or financial information that is 
customarily treated as private, that you actually treat as private, and 
that is relevant or responsive to this NPRM, it is important that you 
clearly designate the submitted comments as CBI. Please mark each page 
of your submission containing CBI as ``PROPIN.'' The FAA will treat 
such marked submissions as confidential under the FOIA, and they will 
not be placed in the public docket of this NPRM. Submissions containing 
CBI should be sent to Dorie Resnik, Aviation Safety Engineer, Boston 
ACO Branch, 1200 District Avenue, Burlington, Massachusetts 01803; 
telephone 781-238-7693; email dorie.resnik@faa.gov. Any commentary that 
the FAA receives which is not specifically designated as CBI will be 
placed in the public docket for this rulemaking.

Discussion

    The FAA proposes to adopt a new AD for Sikorsky Model S-92A 
helicopters with certain part-numbered horizontal stabilizer assemblies 
(stabilizer assembly), certain part-numbered forward root fittings, or 
certain part-numbered stabilizer strut fittings installed. This 
proposed AD was prompted by seven incidents of fatigue cracks in 
forward root fittings. Fatigue cracking in a forward root fitting 
degrades the load path and increases the load on other assembly parts,

[[Page 58008]]

particularly at the aft horizontal stabilizer attachment points.
    This proposed AD would require establishing the life limit of 
certain part-numbered forward root fittings and certain part-numbered 
stabilizer strut fittings. This proposed AD would also require 
repetitively inspecting each stabilizer assembly attachment bolt and 
barrel nut set, each forward root fitting, each attachment fitting 
including the bolt holes and fastener holes, condition of the 
fasteners, and each attachment fitting mating surface. Depending on the 
inspection results, this proposed AD would require removing parts from 
service. Finally, this proposed AD would prohibit installing certain 
stabilizer assemblies on any helicopter.
    The proposed actions are intended to prevent a forward root fitting 
remaining in service beyond its fatigue life, detect fatigue cracking 
in a forward root fitting, and prevent increased load and stress 
cracking in the stabilizer root fitting aft. This condition, if not 
addressed, could result in failure of a forward root fitting, 
separation of the stabilizer assembly from the helicopter, and 
subsequent loss of control of the helicopter.

Related Service Information Under 1 CFR Part 51

    The FAA reviewed S-92 Maintenance Manual, SA S92A-AMM-000, 
Temporary Revision (TR) 55-33, dated March 24, 2020 (TR 55-33), which 
adds additional part numbers (P/N) to the Horizontal Stabilizer--
Maintenance Practices and specifies procedures for inspecting each 
forward root fitting and aft root fitting bolt holes and fasteners, 
each forward and aft root fitting mating surface for wear of the 
abrasion-resistant Teflon coating, procedures for chemically striping 
the abrasion-resistant Teflon coating from the entire mounting pad, 
applying alodine, and applying an abrasion-resistant Teflon coating. 
This service information also describes procedures for removing and 
installing a stabilizer (Tasks 55-11-01-900-001 and 55-11-01-900-002), 
checking the torque stabilization (Task 55-11-01-280-001), and 
inspecting the stabilizer and attaching hardware (Task 55-11-01-210-
004). This service information also provides assembly diagrams and 
lists interchangeable stabilizer P/Ns and compatible strut P/Ns.
    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 also 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 time in service (TIS).

FAA's Determination

    The FAA is proposing this AD after evaluating all the relevant 
information and determining the unsafe condition described previously 
is likely to exist or develop in other helicopters of the same type 
design.

Proposed AD Requirements

    This proposed AD would require determining the total hours TIS of 
the forward root fitting and the stabilizer strut fitting. This 
proposed AD would require establishing a life limit of 7,900 hours TIS 
for certain part-numbered forward root fittings and establishing a life 
limit of 19,100 hours TIS for stabilizer strut fitting P/N 92070-20117-
041. This proposed AD would also require for certain part-numbered 
stabilizer strut fittings installed, repetitively inspecting the 
following at intervals not to exceed 50 hours TIS:
     The hat bushing and both upper and lower fittings for a 
crack, corrosion, fretting, deformation, and wear.
     Both upper and lower support strut rod ends, including 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.
    This proposed AD would also require repetitively inspecting the 
following at intervals not to exceed 250 hours TIS or one year, 
whichever occurs first:
     Each stabilizer attachment bolt and barrel nut set for 
corrosion, a crack, and damage to the threads indicated by uneven 
threads, missing threads, or cross-threading.
     Each forward root fitting and aft attachment fitting, 
including inspecting the bolt holes and fastener holes for a crack, 
wear, and corrosion, or as an alternative to detect cracks, fluorescent 
penetrant inspecting (FPI) the area.
     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. 
If there is any wear of the coating or fretting, this proposed AD would 
require stripping the coating and performing a FPI or eddy current 
inspection to inspect for a crack. If there are no cracks, this 
proposed AD would require recoating the surfaces.
    Depending on the inspection results, this proposed AD would require 
removing parts from service before further flight.
    Finally, this proposed AD would prohibit installing stabilizer 
assembly P/N 92205-07400-043, 92205-07400-045, and 92205-07400-047 on 
any helicopter.

Differences Between This Proposed AD and the Service Information

    The service information requires returning affected parts to a 
Sikorsky specialist; this proposed AD would not.

Costs of Compliance

    The FAA estimates that this proposed AD would affect 85 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 proposed AD.
    Visually inspecting the stabilizer assembly and attached hardware 
would take about 3 work-hours for an estimated cost of $255 per 
helicopter and $21,675 for the U.S. fleet per inspection cycle.
    If required, replacing a hat bushing and both upper fittings and 
lower fittings would take about 1 work-hour and parts would cost about 
$10,000 for an estimated cost of $10,085 per replacement.
    If required, replacing the upper and lower support strut rod ends, 
including lug and conical fitting, would take about 1 work-hour and 
parts would cost about $10,000 for an estimated cost of $10,085 per 
replacement.
    If required, performing a fluorescent penetrant inspection would 
take about 3 work-hours for an estimated cost of $255 per inspection.
    If required, replacing a stabilizer assembly would take about 6 
work-hours and parts would cost about $312,000 for an estimated cost of 
$312,510 per replacement.
    If required, replacing a forward root fitting would take about 10 
work-hours and parts would cost about $25,000 for

[[Page 58009]]

an estimated cost of $25,850 per replacement.
    If required, replacing a stabilizer strut fitting would take about 
10 work-hours and parts would 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 would take about 20 work-hours and parts would cost about 
$50,000 for an estimated cost of $51,700 per replacement.
    If required, removing wear or corrosion and applying corrosion 
preventative compound would take about 0.5 work-hour and parts would 
cost a nominal amount for an estimated cost of $43 per action.
    If required, replacing a stabilizer attachment bolt and barrel nut 
set would take about 1 work-hour and parts would cost about $500 for an 
estimated cost of $585 per replacement.
    If required, replacing a fastener would take about 0.1 work-hour 
and parts would 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 would 
take about 5 work-hours for an estimated cost of $425 per inspection.
    If required, applying alodine or equivalent and applying abrasion-
resistant Teflon coating would take 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 proposed 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 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 above, I certify this proposed 
regulation:
    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 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 adding the following new airworthiness 
directive (AD):

Sikorsky Aircraft Corporation: Docket No. FAA-2020-0792; Product 
Identifier 2018-SW-049-AD.

(a) Comments Due Date

    The FAA must receive comments by November 2, 2020.

(b) Affected ADs

    None.

(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 92209-07404-041, 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.

(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):
    (i) Determine the total hours TIS of the forward root fitting P/
N 92209-07111-101 or 92070-20125-101. If the hours TIS of the 
forward root fitting is unknown, use the 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, before exceeding 7,900 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 92209-
07404-041 or 92209-07403-041 installed, within 50 hours TIS 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

[[Page 58010]]

strut rod ends, horizontal stabilizer attachment fitting, and the 
tail rotor pylon attachment fitting.
    (ii) 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, before further flight, remove the hat bushing 
and both upper fittings and lower fittings from service.
    (iii) Using a 10X or higher power magnifying glass, a 
flashlight, and a mirror, visually inspect both upper and lower 
support strut rod ends, including 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, before further flight, remove 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.
    (3) Within 250 hours TIS or one year, whichever occurs first, 
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 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 
penetrate 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 92070-20117-041 is a 
terminating action for the 50 hour TIS repetitive 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)(1) of this AD. Information may be 
emailed to: ANE-AD-AMOC@faa.gov.
    (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

    (1) 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 
dorie.resnik@faa.gov.
    (2) For service information identified in this AD, contact your 
local Sikorsky Field Representative or Sikorsky's Service 
Engineering Group at Sikorsky Aircraft Corporation, 124 Quarry Road, 
Trumbull, CT 06611; telephone 1-800-946-4337 (1-800-Winged-S); email 
wcs_cust_service_eng.gr-sik@lmco.com. 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.

    Issued on September 11, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-20482 Filed 9-16-20; 8:45 am]
BILLING CODE 4910-13-P