Airworthiness Directives; Sikorsky Aircraft Corporation Helicopters, 35814-35818 [2019-15757]
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35814
Federal Register / Vol. 84, No. 143 / Thursday, July 25, 2019 / Rules and Regulations
Revision 05, dated June 13, 2018. The initial
compliance time for doing the tasks is at the
time specified in Airbus A318/A319/A320/
A321 Airworthiness Limitations Section
(ALS), Part 5, Fuel Airworthiness Limitations
(FAL), Revision 05, dated June 13, 2018, or
within 90 days after the effective date of this
AD, whichever occurs later.
(h) No Alternative Actions, Intervals, or
Critical Design Configuration Control
Limitations (CDCCLs)
After the maintenance or inspection
program has been revised as required by
paragraph (g) of this AD, no alternative
actions (e.g., inspections), intervals, or
CDCCLs may be used unless the actions,
intervals, and CDCCLs are approved as an
alternative method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (j)(1) of this AD.
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(i) Terminating Action for AD 2018–17–21
Accomplishing the actions required by this
AD terminates all requirements of AD 2018–
17–21.
(j) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (k)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2018–17–21 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): If any
service information contains procedures or
tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
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changes to procedures or tests identified as
RC require approval of an AMOC.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
(k) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0231, dated October 25, 2018, for
related information. This MCAI may be
found in the AD docket on the internet at
https://www.regulations.gov by searching for
and locating Docket No. FAA–2019–0116.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
14 CFR Part 39
(l) Material Incorporated by Reference
The FAA is adopting a new
airworthiness directive (AD) for certain
Sikorsky Aircraft Corporation (Sikorsky)
Model S–92A helicopters. This AD was
prompted by fatigue analysis indicating
stress concentrations, as well as the
discovery of a helicopter with a crack in
the station (STA) 362 frame and skin.
This AD requires inspecting the main
transmission forward and aft frame
assemblies and adjacent skins for a
crack and loose fasteners, and
establishing life limits for certain frame
assemblies. The FAA is issuing this AD
to address the unsafe condition on these
products.
DATES: This AD is effective August 29,
2019.
ADDRESSES: For service information
identified in this final rule, contact
Sikorsky Aircraft Corporation, Customer
Service Engineering, 124 Quarry Road,
Trumbull, CT 06611; telephone 1–800–
Winged–S or 203–416–4299; email:
wcs_cust_service_eng.gr-sik@lmco.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.
(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 this AD specifies otherwise.
(i) Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS),
Part 5, Fuel Airworthiness Limitations (FAL),
Revision 05, dated June 13, 2018.
(ii) Reserved
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on July
16, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–15821 Filed 7–24–19; 8:45 am]
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[Docket No. FAA–2016–8501; Product
Identifier 2014–SW–042–AD; Amendment
39–19678; AD 2019–13–05]
RIN 2120–AA64
Airworthiness Directives; Sikorsky
Aircraft Corporation Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
SUMMARY:
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–2016–8501; 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 regulatory
evaluation, 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:
Kristopher Greer, Aviation Safety
Engineer, Boston ACO Branch,
Compliance and Airworthiness
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Federal Register / Vol. 84, No. 143 / Thursday, July 25, 2019 / Rules and Regulations
Request To Revise Certain Terminology
in the SNPRM
Division, 1200 District Avenue,
Burlington, Massachusetts 01803;
telephone (781) 238–7799; email
Kristopher.Greer@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Sikorsky Model S–92A
helicopters. The NPRM published in the
Federal Register on July 15, 2016 (81 FR
46002). The NPRM was prompted by a
fatigue analysis that indicates stress
concentrations may develop at the steel
doublers on the main transmission
airframe support structure top deck,
adjacent to the transmission feet.
Additionally, a helicopter was
discovered with a crack in the STA 362
frame and skin. The NPRM proposed to
require inspecting the main
transmission forward and aft frame
assemblies and adjacent skins for a
crack and loose fasteners, and replacing
or repairing any cracked part or loose
fastener. The NPRM also proposed to
require establishing life limits for
certain frame assemblies.
The FAA issued a supplemental
NPRM (SNPRM) (83 FR 66167,
December 26, 2018) that proposed to
revise the NPRM by increasing the
estimated costs of compliance and
removing the daily inspection
requirements.
The FAA is issuing this AD to detect
a crack in a main transmission airframe
support structure, which could result in
failure of a main transmission frame and
subsequent loss of control of the
helicopter.
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the SNPRM
and the FAA’s response to each
comment.
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Request To Reference the Latest Service
Information
Sikorsky requested that the FAA
reference the latest revision of Sikorsky
S–92A–AMM–000 Maintenance
Manual, Chapter 53–20–00, Task 53–
20–00–210–003, ‘‘Inspection of Main
Transmission Airframe Support
Structure.’’
The FAA agrees. The FAA has revised
this final rule to reference Sikorsky
S–92A–AMM–000 Maintenance
Manual, Chapter 53–20–00, Task 53–
20–00–210–003, ‘‘Inspection of Main
Transmission Airframe Support
Structure,’’ dated November 30, 2018.
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Sikorsky requested that all instances
of ‘‘life limits’’ be changed to
‘‘replacement intervals.’’ Sikorsky stated
that this terminology is consistent with
14 CFR Appendix A to part 29 and the
approved airworthiness limitations
section of the maintenance manual.
The FAA disagrees. The term ‘‘life
limit’’ has been used in previous ADs
applicable to Sikorsky aircraft and is
well understood by the aviation
industry. In addition, the use of life
limit conveys the mandatory nature of
the replacement intervals. The FAA has
not changed this final rule in this
regard.
Request To Revise the Life Limit Hours
Time-In-Service (TIS) in the SNPRM
Sikorsky requested that the FAA
revise the values for the life limit hours
TIS. Sikorsky stated that the
replacement intervals for the frame
assembly part numbers shown in table
1 to paragraph (e)(1) of the SNPRM
(which is referred to as figure 1 to
paragraphs (a) and (e) in this final rule)
increased since issuance of the NPRM.
Sikorsky also stated that a recent
certification effort for these parts
increased the replacement intervals by a
minimum of 7,900 hours, to as much as
17,400 hours, above the limits proposed
in the SNPRM. Sikorsky commented
that incorporation of these new
replacement intervals (ranging from
18,300 life limit hours TIS to 29,400 life
limit hours TIS, as applicable) will
avoid unnecessary removal from service
of frame assemblies and avoid the need
for issuance of alternate methods of
compliance to address differences
between the life limits proposed by the
SNPRM and those subsequently
approved by the FAA.
The FAA agrees. The FAA has revised
the life limits in this final rule for the
reasons provided by the commenter
because these longer life limits have
been approved by the FAA.
Sikorsky further commented that with
approval of recent certification work,
Forward STA 328 frame assemblies that
are altered and changed to P/N 92070–
20124–064, 92070–20124–067, 92070–
20127–045, 92070–20124–065, 92070–
20124–047, or 92070–20127–046 are no
longer counted from TIS of alternation.
They are only counted from the original
frame part number initial service date
instead. These part-numbered
assemblies were proposed in the
SNPRM for removal from service upon
accumulating 12,000 hours TIS from the
alteration or 28,500 hours TIS total
(regardless of part number) from the
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35815
total original frame part number initial
service date, whichever occurs first.
The FAA agrees and has omitted
‘‘remove from service of upon
accumulating 12,000 hours TIS from the
alteration’’ in this final rule.
Additional Changes Made in This Final
Rule
The four tables in the SNPRM have
been re-identified as figures in this AD.
The FAA has also relocated these
figures to all follow paragraph (a) of this
AD.
FAA’s Determination
The FAA has reviewed the relevant
information, considered the comments
received, and determined that an unsafe
condition exists and is likely to exist or
develop on other helicopters of the same
type design and that air safety and the
public interest require adopting the AD
requirements as proposed with the
changes described previously. These
changes are consistent with the intent of
the proposals in the SNPRM and do not
add any additional burden upon the
public than was already proposed in the
SNPRM. Additionally, these changes
will not increase the economic burden
on any operator or increase the scope of
the AD.
Related Service Information
Sikorsky issued Alert Service Bulletin
(ASB) 92–53–008, Basic Issue, dated
June 13, 2012 (ASB 92–53–008); ASB
92–53–009, Basic Issue, dated December
6, 2012 (ASB 92–53–009); ASB 92–53–
012, Basic Issue, dated February 10,
2014 (ASB 92–53–012); and S–92A–
AMM–000 Maintenance Manual,
Chapter 53–20–00, Task 53–20–00–210–
003, ‘‘Inspection of Main Transmission
Airframe Support Structure,’’ dated
November 30, 2018 (Task 53–20–00–
210–003).
ASB 92–53–008 provides procedures
for a one-time inspection of the main
transmission frames and beams for a
crack, missing or loose fastener or
collar, damage, deformation, and
corrosion. ASB 92–53–009 specifies,
among other actions, a recurring 150hour inspection of the interior and
exterior surfaces of the upper flanges
and beams. ASB 92–53–012 specifies
altering the forward and aft
transmission support frames by
removing steel doublers, cold-working
the holes, oversizing the holes,
trimming skin panels, and reassembling
the parts with interference fit fasteners
in accordance with Special Service
Instructions 92–074–E. After this
alteration, the parts are re-identified
with a new part number. Sikorsky refers
to this alteration as a service life
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Federal Register / Vol. 84, No. 143 / Thursday, July 25, 2019 / Rules and Regulations
extension program modification. Task
53–20–00–210–003 describes
procedures for an inspection of the main
transmission airframe support structure.
Differences Between This AD and the
Service Information
The service information recommends
providing certain information to
Sikorsky, and this AD does not. The
service information specifies performing
a fluorescent penetrant inspection if
there is a suspected crack and
contacting Sikorsky if there is a crack,
while this AD only requires repairing or
replacing any cracked part. Contacting
Sikorsky is not required by this AD.
Costs of Compliance
The FAA estimates that this AD
affects 50 helicopters of U.S. Registry.
The FAA estimates that operators may
incur the following costs to comply with
this AD. Labor costs are estimated at $85
per work-hour.
The FAA estimates a minimal cost to
establish and revise the life limit of the
frame assembly. The FAA estimates it
takes 1 work-hour to inspect STA 328
and 362 frames. No parts are needed for
a total cost of $4,250 for the U.S. fleet
for each inspection per inspection cycle.
If a fastener is replaced, the FAA
estimates the cost to be minimal. If a
frame is replaced, it takes 5,000 workhours and required parts cost $296,000
for a total cost of $721,000 per
helicopter.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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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
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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.
Adoption of 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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2019–13–05 Sikorsky Aircraft Corporation:
Amendment 39–19678; Docket No.
FAA–2016–8501; Product Identifier
2014–SW–042–AD.
(a) Applicability
This AD applies to Sikorsky Aircraft
Corporation Model S–92A helicopters,
certificated in any category, with a forward
station (STA) 328 or aft STA 362 frame
assembly with a part number (P/N) as shown
in Figure 1 to paragraphs (a) and (e) of this
AD, Figure 2 to paragraphs (a) and (e) of this
AD, Figure 3 to paragraphs (a) and (e)(2) of
this AD, or Figure 4 to paragraphs (a) and
(e)(2) of this AD.
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35817
Figure 1 to Paragraphs (a) and (e)
Forward STA 328 Frame
Assembly PIN
92070-20124-064
92070-20124-067
92070-20127-045
92070-20124-065
92070-20124-047
92070-20127-046
92070-20124-063
92070-20124-066
92070-20127-041
Life Limit Hours TIS
Aft STA 362 Frame
Assembly PIN
92070-20124-041
92070-20124-044
92070-20127-042
92070-20124-042
92070-20124-045
92070-20127-049
92070-20124-043
92070-20124-046
92070-20127-050
92070-20141-050
92070-20141-051
92070-20141-052
Life Limit Hours TIS
28,500
28,500
28,500
28,500
28,500
28,500
29,400
29,400
29,400
18,300
18,300
18,300
18,300
18,300
18,300
18,300
18,300
18,300
27,600
27,600
27,600
Figure 2 to Paragraphs (a) and (e)
Life Limit Hours TIS
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28,500
28,500
28,500
28,500
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Forward STA 328 Frame
Assembly PIN
92070-20097-058
92080-2004 7-04 7
92070-20097-060
92080-2004 7-048
Federal Register / Vol. 84, No. 143 / Thursday, July 25, 2019 / Rules and Regulations
(b) Unsafe Condition
This AD defines the unsafe condition as a
crack in a main transmission airframe
support structure. This condition could
result in failure of a main transmission frame
and subsequent loss of control of the
helicopter.
(c) Effective Date
This AD is effective August 29, 2019.
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(d) Compliance
You are responsible for performing each
action required by this AD within the
specified compliance time unless it has
already been accomplished prior to that time.
(e) Required Actions
(1) For helicopters with a frame assembly
with a part number shown in Figure 1 to
paragraphs (a) and (e) of this AD or Figure
2 to paragraphs (a) and (e) of this AD, before
further flight, remove from service any part
that has reached or exceeded its new life
limit. Forward STA 328 frame assemblies
that are altered and changed to P/N 92070–
20124–064, 92070–20124–067, 92070–
20127–045, 92070–20124–065, 92070–
20124–047, or 92070–20127–046 must be
removed from service upon accumulating
28,500 hours time-in-service (TIS) total
(regardless of P/N) from the original frame
part number initial service date.
(2) For each frame assembly listed in
Figure 1 to paragraphs (a) and (e) of this AD
or Figure 4 to paragraphs (a) and (e)(2) of this
AD with 1,801 or more hours TIS, and for
each frame assembly listed in Figure 2 to
paragraphs (a) and (e) of this AD or Figure
3 to paragraphs (a) and (e)(2) of this AD with
1,301 or more hours TIS, within 150 hours
TIS and thereafter at intervals not to exceed
150 hours TIS, do the following inspections.
For guidance on performing these
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inspections, refer to Sikorsky S–92A–AMM–
000 Maintenance Manual Chapter 53–20–00,
Task 53–20–00–210–003, ‘‘Inspection of
Main Transmission Airframe Support
Structure,’’ dated November 30, 2018.
(i) Inspect the STA 328 frame and STA 362
frame between the left and right butt line
(BL) 16.5 beams and inspect the area on the
left and right BL 16.5 beams six inches on
either side of the mounting pads for a crack
and loose fasteners. If there is a loose fastener
or a crack, repair or replace any cracked part
and any loose fastener before further flight.
(ii) Inspect the STA 328 and STA 362
outboard frames, left and right sides, from the
BL 16.5 beam to water line 252.25 for a crack
and loose fasteners. If there is a loose fastener
or a crack, repair or replace any cracked part
and any loose fastener before further flight.
(f) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Boston ACO Branch,
FAA, may approve AMOCs for this AD. Send
your proposal to: Kristopher Greer, Aviation
Safety Engineer, Boston ACO Branch,
Compliance and Airworthiness Division,
1200 District Avenue, Burlington,
Massachusetts 01803; telephone (781) 238–
7799; email Kristopher.Greer@faa.gov.
(2) For operations conducted under a 14
CFR part 119 operating certificate or under
14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or
lacking a principal inspector, the manager of
the local flight standards district office or
certificate holding district office before
operating any aircraft complying with this
AD through an AMOC.
February 10, 2014, Sikorsky Special Service
Instructions No. 92–074–E, Revision E, dated
April 9, 2014, and Sikorsky S–92A–AMM–
000 Maintenance Manual, Chapter 53–20–00,
Task 53–20–00–210–003, ‘‘Inspection of
Main Transmission Airframe Support
Structure,’’ dated November 30, 2018, which
are not incorporated by reference, contain
additional information about the subject of
this AD. For service information identified in
this AD, contact Sikorsky Aircraft
Corporation, Customer Service Engineering,
124 Quarry Road, Trumbull, CT 06611;
telephone 1–800–Winged–S or 203–416–
4299; email wcs_cust_service_eng.gr-sik@
lmco.com. You may view this information at
the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy.,
Room 6N–321, Fort Worth, TX 76177.
(h) Subject
Joint Aircraft System Component (JASC)
Code: 5311, Fuselage Main, Frame.
Issued in Fort Worth, Texas, on July 10,
2019.
James A. Grigg,
Acting Deputy Director for Regulatory
Operations, Compliance & Airworthiness
Division, Aircraft Certification Service.
[FR Doc. 2019–15757 Filed 7–24–19; 8:45 am]
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(g) Additional Information
Sikorsky Alert Service Bulletin (ASB) 92–
53–008, Basic Issue, dated June 13, 2012;
ASB 92–53–009, Basic Issue, dated December
6, 2012; ASB 92–53–012, Basic Issue, dated
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]]>Agencies
[Federal Register Volume 84, Number 143 (Thursday, July 25, 2019)]
[Rules and Regulations]
[Pages 35814-35818]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-15757]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-8501; Product Identifier 2014-SW-042-AD; Amendment
39-19678; AD 2019-13-05]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain Sikorsky Aircraft Corporation (Sikorsky) Model S-92A
helicopters. This AD was prompted by fatigue analysis indicating stress
concentrations, as well as the discovery of a helicopter with a crack
in the station (STA) 362 frame and skin. This AD requires inspecting
the main transmission forward and aft frame assemblies and adjacent
skins for a crack and loose fasteners, and establishing life limits for
certain frame assemblies. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective August 29, 2019.
ADDRESSES: For service information identified in this final rule,
contact Sikorsky Aircraft Corporation, Customer Service Engineering,
124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or 203-
416-4299; email: [email protected]. 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.
Examining the AD Docket
You may examine the AD docket on the internet at https://www.regulations.gov gov by searching for and locating Docket No. FAA-2016-
8501; 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 regulatory evaluation, 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: Kristopher Greer, Aviation Safety
Engineer, Boston ACO Branch, Compliance and Airworthiness
[[Page 35815]]
Division, 1200 District Avenue, Burlington, Massachusetts 01803;
telephone (781) 238-7799; email [email protected].
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to certain Sikorsky Model
S-92A helicopters. The NPRM published in the Federal Register on July
15, 2016 (81 FR 46002). The NPRM was prompted by a fatigue analysis
that indicates stress concentrations may develop at the steel doublers
on the main transmission airframe support structure top deck, adjacent
to the transmission feet. Additionally, a helicopter was discovered
with a crack in the STA 362 frame and skin. The NPRM proposed to
require inspecting the main transmission forward and aft frame
assemblies and adjacent skins for a crack and loose fasteners, and
replacing or repairing any cracked part or loose fastener. The NPRM
also proposed to require establishing life limits for certain frame
assemblies.
The FAA issued a supplemental NPRM (SNPRM) (83 FR 66167, December
26, 2018) that proposed to revise the NPRM by increasing the estimated
costs of compliance and removing the daily inspection requirements.
The FAA is issuing this AD to detect a crack in a main transmission
airframe support structure, which could result in failure of a main
transmission frame and subsequent loss of control of the helicopter.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the SNPRM and the FAA's response to each comment.
Request To Reference the Latest Service Information
Sikorsky requested that the FAA reference the latest revision of
Sikorsky S-92A-AMM-000 Maintenance Manual, Chapter 53-20-00, Task 53-
20-00-210-003, ``Inspection of Main Transmission Airframe Support
Structure.''
The FAA agrees. The FAA has revised this final rule to reference
Sikorsky S-92A-AMM-000 Maintenance Manual, Chapter 53-20-00, Task 53-
20-00-210-003, ``Inspection of Main Transmission Airframe Support
Structure,'' dated November 30, 2018.
Request To Revise Certain Terminology in the SNPRM
Sikorsky requested that all instances of ``life limits'' be changed
to ``replacement intervals.'' Sikorsky stated that this terminology is
consistent with 14 CFR Appendix A to part 29 and the approved
airworthiness limitations section of the maintenance manual.
The FAA disagrees. The term ``life limit'' has been used in
previous ADs applicable to Sikorsky aircraft and is well understood by
the aviation industry. In addition, the use of life limit conveys the
mandatory nature of the replacement intervals. The FAA has not changed
this final rule in this regard.
Request To Revise the Life Limit Hours Time-In-Service (TIS) in the
SNPRM
Sikorsky requested that the FAA revise the values for the life
limit hours TIS. Sikorsky stated that the replacement intervals for the
frame assembly part numbers shown in table 1 to paragraph (e)(1) of the
SNPRM (which is referred to as figure 1 to paragraphs (a) and (e) in
this final rule) increased since issuance of the NPRM. Sikorsky also
stated that a recent certification effort for these parts increased the
replacement intervals by a minimum of 7,900 hours, to as much as 17,400
hours, above the limits proposed in the SNPRM. Sikorsky commented that
incorporation of these new replacement intervals (ranging from 18,300
life limit hours TIS to 29,400 life limit hours TIS, as applicable)
will avoid unnecessary removal from service of frame assemblies and
avoid the need for issuance of alternate methods of compliance to
address differences between the life limits proposed by the SNPRM and
those subsequently approved by the FAA.
The FAA agrees. The FAA has revised the life limits in this final
rule for the reasons provided by the commenter because these longer
life limits have been approved by the FAA.
Sikorsky further commented that with approval of recent
certification work, Forward STA 328 frame assemblies that are altered
and changed to P/N 92070-20124-064, 92070-20124-067, 92070-20127-045,
92070-20124-065, 92070-20124-047, or 92070-20127-046 are no longer
counted from TIS of alternation. They are only counted from the
original frame part number initial service date instead. These part-
numbered assemblies were proposed in the SNPRM for removal from service
upon accumulating 12,000 hours TIS from the alteration or 28,500 hours
TIS total (regardless of part number) from the total original frame
part number initial service date, whichever occurs first.
The FAA agrees and has omitted ``remove from service of upon
accumulating 12,000 hours TIS from the alteration'' in this final rule.
Additional Changes Made in This Final Rule
The four tables in the SNPRM have been re-identified as figures in
this AD. The FAA has also relocated these figures to all follow
paragraph (a) of this AD.
FAA's Determination
The FAA has reviewed the relevant information, considered the
comments received, and determined that an unsafe condition exists and
is likely to exist or develop on other helicopters of the same type
design and that air safety and the public interest require adopting the
AD requirements as proposed with the changes described previously.
These changes are consistent with the intent of the proposals in the
SNPRM and do not add any additional burden upon the public than was
already proposed in the SNPRM. Additionally, these changes will not
increase the economic burden on any operator or increase the scope of
the AD.
Related Service Information
Sikorsky issued Alert Service Bulletin (ASB) 92-53-008, Basic
Issue, dated June 13, 2012 (ASB 92-53-008); ASB 92-53-009, Basic Issue,
dated December 6, 2012 (ASB 92-53-009); ASB 92-53-012, Basic Issue,
dated February 10, 2014 (ASB 92-53-012); and S-92A-AMM-000 Maintenance
Manual, Chapter 53-20-00, Task 53-20-00-210-003, ``Inspection of Main
Transmission Airframe Support Structure,'' dated November 30, 2018
(Task 53-20-00-210-003).
ASB 92-53-008 provides procedures for a one-time inspection of the
main transmission frames and beams for a crack, missing or loose
fastener or collar, damage, deformation, and corrosion. ASB 92-53-009
specifies, among other actions, a recurring 150-hour inspection of the
interior and exterior surfaces of the upper flanges and beams. ASB 92-
53-012 specifies altering the forward and aft transmission support
frames by removing steel doublers, cold-working the holes, oversizing
the holes, trimming skin panels, and reassembling the parts with
interference fit fasteners in accordance with Special Service
Instructions 92-074-E. After this alteration, the parts are re-
identified with a new part number. Sikorsky refers to this alteration
as a service life
[[Page 35816]]
extension program modification. Task 53-20-00-210-003 describes
procedures for an inspection of the main transmission airframe support
structure.
Differences Between This AD and the Service Information
The service information recommends providing certain information to
Sikorsky, and this AD does not. The service information specifies
performing a fluorescent penetrant inspection if there is a suspected
crack and contacting Sikorsky if there is a crack, while this AD only
requires repairing or replacing any cracked part. Contacting Sikorsky
is not required by this AD.
Costs of Compliance
The FAA estimates that this AD affects 50 helicopters of U.S.
Registry. The FAA estimates that operators may incur the following
costs to comply with this AD. Labor costs are estimated at $85 per
work-hour.
The FAA estimates a minimal cost to establish and revise the life
limit of the frame assembly. The FAA estimates it takes 1 work-hour to
inspect STA 328 and 362 frames. No parts are needed for a total cost of
$4,250 for the U.S. fleet for each inspection per inspection cycle. If
a fastener is replaced, the FAA estimates the cost to be minimal. If a
frame is replaced, it takes 5,000 work-hours and required parts cost
$296,000 for a total cost of $721,000 per helicopter.
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.
Adoption of 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 adding the following new airworthiness
directive (AD):
2019-13-05 Sikorsky Aircraft Corporation: Amendment 39-19678; Docket
No. FAA-2016-8501; Product Identifier 2014-SW-042-AD.
(a) Applicability
This AD applies to Sikorsky Aircraft Corporation Model S-92A
helicopters, certificated in any category, with a forward station
(STA) 328 or aft STA 362 frame assembly with a part number (P/N) as
shown in Figure 1 to paragraphs (a) and (e) of this AD, Figure 2 to
paragraphs (a) and (e) of this AD, Figure 3 to paragraphs (a) and
(e)(2) of this AD, or Figure 4 to paragraphs (a) and (e)(2) of this
AD.
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(b) Unsafe Condition
This AD defines the unsafe condition as a crack in a main
transmission airframe support structure. This condition could result
in failure of a main transmission frame and subsequent loss of
control of the helicopter.
(c) Effective Date
This AD is effective August 29, 2019.
(d) Compliance
You are responsible for performing each action required by this
AD within the specified compliance time unless it has already been
accomplished prior to that time.
(e) Required Actions
(1) For helicopters with a frame assembly with a part number
shown in Figure 1 to paragraphs (a) and (e) of this AD or Figure 2
to paragraphs (a) and (e) of this AD, before further flight, remove
from service any part that has reached or exceeded its new life
limit. Forward STA 328 frame assemblies that are altered and changed
to P/N 92070-20124-064, 92070-20124-067, 92070-20127-045, 92070-
20124-065, 92070-20124-047, or 92070-20127-046 must be removed from
service upon accumulating 28,500 hours time-in-service (TIS) total
(regardless of P/N) from the original frame part number initial
service date.
(2) For each frame assembly listed in Figure 1 to paragraphs (a)
and (e) of this AD or Figure 4 to paragraphs (a) and (e)(2) of this
AD with 1,801 or more hours TIS, and for each frame assembly listed
in Figure 2 to paragraphs (a) and (e) of this AD or Figure 3 to
paragraphs (a) and (e)(2) of this AD with 1,301 or more hours TIS,
within 150 hours TIS and thereafter at intervals not to exceed 150
hours TIS, do the following inspections. For guidance on performing
these inspections, refer to Sikorsky S-92A-AMM-000 Maintenance
Manual Chapter 53-20-00, Task 53-20-00-210-003, ``Inspection of Main
Transmission Airframe Support Structure,'' dated November 30, 2018.
(i) Inspect the STA 328 frame and STA 362 frame between the left
and right butt line (BL) 16.5 beams and inspect the area on the left
and right BL 16.5 beams six inches on either side of the mounting
pads for a crack and loose fasteners. If there is a loose fastener
or a crack, repair or replace any cracked part and any loose
fastener before further flight.
(ii) Inspect the STA 328 and STA 362 outboard frames, left and
right sides, from the BL 16.5 beam to water line 252.25 for a crack
and loose fasteners. If there is a loose fastener or a crack, repair
or replace any cracked part and any loose fastener before further
flight.
(f) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Boston ACO Branch, FAA, may approve AMOCs for
this AD. Send your proposal to: Kristopher Greer, Aviation Safety
Engineer, Boston ACO Branch, Compliance and Airworthiness Division,
1200 District Avenue, Burlington, Massachusetts 01803; telephone
(781) 238-7799; email [email protected].
(2) For operations conducted under a 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, the FAA suggests
that you notify your principal inspector, or lacking a principal
inspector, the manager of the local flight standards district office
or certificate holding district office before operating any aircraft
complying with this AD through an AMOC.
(g) Additional Information
Sikorsky Alert Service Bulletin (ASB) 92-53-008, Basic Issue,
dated June 13, 2012; ASB 92-53-009, Basic Issue, dated December 6,
2012; ASB 92-53-012, Basic Issue, dated February 10, 2014, Sikorsky
Special Service Instructions No. 92-074-E, Revision E, dated April
9, 2014, and Sikorsky S-92A-AMM-000 Maintenance Manual, Chapter 53-
20-00, Task 53-20-00-210-003, ``Inspection of Main Transmission
Airframe Support Structure,'' dated November 30, 2018, which are not
incorporated by reference, contain additional information about the
subject of this AD. For service information identified in this AD,
contact Sikorsky Aircraft Corporation, Customer Service Engineering,
124 Quarry Road, Trumbull, CT 06611; telephone 1-800-Winged-S or
203-416-4299; email [email protected]. You may
view this information at the FAA, Office of the Regional Counsel,
Southwest Region, 10101 Hillwood Pkwy., Room 6N-321, Fort Worth, TX
76177.
(h) Subject
Joint Aircraft System Component (JASC) Code: 5311, Fuselage
Main, Frame.
Issued in Fort Worth, Texas, on July 10, 2019.
James A. Grigg,
Acting Deputy Director for Regulatory Operations, Compliance &
Airworthiness Division, Aircraft Certification Service.
[FR Doc. 2019-15757 Filed 7-24-19; 8:45 am]
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