Airworthiness Directives; Sikorsky Aircraft Corporation (Sikorsky) Model Helicopters, 71087-71089 [2012-28427]
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Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations
(d) Reason
DEPARTMENT OF TRANSPORTATION
This AD was prompted by a report of a
low-pressure compressor (LPC) fan blade
separation. We are issuing this AD to detect
cracks in the LPC fan blades, which could
lead to uncontained failure of the LPC fan
blades and LPC fan disc, and damage to the
airplane.
(e) Actions and Compliance
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1206; Directorate
Identifier 2012–SW–021–AD; Amendment
39–17269; AD 2012–23–13]
RIN 2120–AA64
Unless already done, do the following
actions:
(1) Before further flight after the effective
date of this AD, perform a visual inspection
and ultrasonic inspection of the LPC fan
blades to determine general condition and/or
the presence of cracks.
(2) Thereafter, perform the inspections
specified in paragraph (e)(1) of this AD
within every additional 1,500 flight hours
(FHs), but not fewer than 1,000 FHs.
(3) If any fan blade is found cracked,
replace the LPC fan blade set and the LPC fan
disc before further flight.
(f) Terminating Action
Replacing the LPC fan blade set and the
LPC fan disc is terminating action to the
repetitive inspections required by this AD.
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
(h) Related Information
Airworthiness Directives; Sikorsky
Aircraft Corporation (Sikorsky) Model
Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Sikorsky Model S–70, S–70A, and S–
70C helicopters, which are restricted
category helicopters derived from the
military Model UH–60 helicopter. This
AD would require reducing or
establishing life limits for certain listed
helicopter parts. This AD is prompted
by a review of the United States Army’s
analysis of their Model UH–60 fleet,
which determined it necessary to
establish or reduce the life limits of
certain parts. The actions are intended
to prevent fatigue failure of a part and
subsequent loss of control of the
helicopter.
SUMMARY:
This AD becomes effective
December 14, 2012.
We must receive comments on this
AD by January 28, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Docket: Go to
https://www.regulations.gov. Follow the
online instructions for sending your
comments electronically.
• Fax: 202–493–2251.
• Mail: Send comments to the U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590–0001.
• Hand Delivery: Deliver to the
‘‘Mail’’ address between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
(1) For more information about this AD,
contact Frederick Zink, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
email: Frederick.zink@faa.gov; phone: 781–
238–7779; fax: 781–238–7199.
(2) Refer to European Aviation Safety
Agency AD 2012–0185–E, dated September
12, 2012, and RRD Alert Service Bulletin
TAY–72–A1775, Revision 1, dated
September 12, 2012, for related information.
(3) For service information identified in
this AD, contact Rolls-Royce Deutschland Ltd
& Co KG, Eschenweg 11, Dahlewitz, 15827
Blankenfelde-Mahlow, Germany; telephone:
49 0 33–7086–1944; fax: 49 0 33–7086–3276.
(4) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
DATES:
(i) Material Incorporated by Reference
Examining the AD Docket
pmangrum on DSK3VPTVN1PROD with RULES
None.
Issued in Burlington, Massachusetts, on
November 19, 2012.
Robert J. Ganley,
Acting Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 2012–28638 Filed 11–28–12; 8:45 am]
BILLING CODE 4910–13–P
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You may examine the AD docket on
the Internet at https://
www.regulations.gov or in person at the
Docket Operations Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this AD, the economic
evaluation, any comments received, and
other information. The street address for
PO 00000
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71087
the Docket Operations Office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Michael Davison, Flight Test Engineer,
New England Regional Office, FAA, 12
New England Executive Park,
Burlington, MA 01803; phone: (781)
238–7156, email:
michael.davison@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not provide you with notice and
an opportunity to provide your
comments prior to it becoming effective.
However, we invite you to participate in
this rulemaking by submitting written
comments, data, or views. We also
invite comments relating to the
economic, environmental, energy, or
federalism impacts that resulted from
adopting this AD. The most helpful
comments reference a specific portion of
the AD, 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 them only one time. We will file
in the docket all comments that we
receive, as well as a report summarizing
each substantive public contact with
FAA personnel concerning this
rulemaking during the comment period.
We will consider all the comments we
receive and may conduct additional
rulemaking based on those comments.
Discussion
We are adopting a new AD for
Sikorsky Model S–70, S–70A and S–70C
helicopters. This AD requires reducing
or establishing life limits for the main
rotor blade, tail rotor blade, planetary
carrier assembly, tail rotor servo,
elastomeric sleeve bearing, main
landing gear shock strut piston cylinder,
crossfeed valve, oil cooler axial fan ball
bearing assembly, dowel pins, main
rotor hub, and right tie rod attach bolt.
This AD is prompted by the need to
reduce life limits on the specified parts.
This determination is based on a review
of analysis by the U.S. Army of certain
parts installed on the military Model
UH–60 helicopters, which shows that
the life limits of those parts need to be
reduced. The Sikorsky Model S–70, S–
70A and S–70C helicopters are
restricted category helicopters derived
from the military Model UH–60
helicopter. The actions are intended to
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Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations
establish life limits for certain parts to
prevent fatigue failure of a part and
subsequent loss of control of the
helicopter.
FAA’s Determination
We are issuing this AD because we
evaluated all the relevant information
and determined the unsafe condition
described previously is likely to exist or
develop in other helicopters of these
same type designs.
AD Requirements
This AD requires, before further flight,
establishing or reducing life limits for
certain parts and removing from service
each part that has reached its life limit.
Costs of Compliance
We estimate that this AD will affect
nine helicopters of U.S. Registry. We
estimate that operators may incur the
following costs in order to comply with
this AD.
It will take about 4.7 work hours at
$85 per work hour to replace each part
plus the required costs per helicopter as
follows:
• $70,000 for the main rotor blade,
• $30,000 for the tail rotor blade,
• $490 for the elastomeric sleeve
bearing,
• $233 for the right tie rod attach bolt,
• $40,000 for the main rotor hub,
• $12,000 for the main landing gear
shock strut piston system,
• $44,000 for the tail rotor servo,
• $200 for the crossfeed breakaway
valve,
• $59,000 for the main module
planetary carrier assembly, and
• $3,700 for the dowel pins (11 total).
Based on these figures, the total
estimated cost is $2,372,607 to replace
all the parts for the entire U.S. fleet.
pmangrum on DSK3VPTVN1PROD with RULES
FAA’s Justification and Determination
of the Effective Date
Since a part must be replaced before
further flight if it has reached its life
limit and some of the parts may have
exceeded or be close to reaching the life
limit, this AD must be issued
immediately.
Since an unsafe condition exists that
requires the immediate adoption of this
AD, we determined that notice and
opportunity for public comment before
issuing this AD are impracticable and
that good cause exists for making this
amendment effective in less than 30
days.
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
VerDate Mar<15>2010
13:45 Nov 28, 2012
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the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are 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
We 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, I certify
that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska to the extent that it justifies
making a regulatory distinction; and
4. 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.
We prepared an economic evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
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.
PO 00000
Frm 00006
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2012–23–13 Sikorsky Aircraft Corporation:
Amendment 39–17269; Docket No.
FAA–2012–1206; Directorate Identifier
2012–SW–021–AD.
(a) Applicability
This AD applies to Model S–70, S–70A,
and S–70C helicopters, certificated in any
category.
(b) Unsafe Condition
This AD defines the unsafe condition as
fatigue failure of a main rotor blade, tail rotor
blade, planetary carrier assembly, tail rotor
servo, elastomeric sleeve bearing, main
landing gear shock strut piston cylinder,
crossfeed valve, oil cooler axial fan ball
bearing assembly, dowel pin, main rotor hub,
or right tie attach bolt remaining in service
beyond its life limit. This condition could
result in loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 14,
2012.
(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 Action
Before further flight:
(1) Establish or reduce the retirement life
of the following parts listed in Table 1–1 of
the Sikorsky Technical Manual TM 1–70–
23AW–2, change 3, section 1.1,
Airworthiness Limitations, by inserting a
copy of Table 1–1 into the Airworthiness
Limitations section of TM 1–70–23AW–2 or
by making the following pen and ink changes
to the Airworthiness Limitations of the
maintenance manual:
(i) For each dowel pin on the main
transmission housing, part number (P/N)
NAS607–10–12P, NAS607–12–14P, and
NAS607–12–18P, establish a life limit of
3,000 hours time-in-service (TIS).
(ii) For elastomeric sleeve bearing, P/N
SB5203–202, establish a life limit of 720
hours TIS.
(iii) For right tie rod attach bolt, P/N
SS5025–04H010, establish a life limit of
3,500 hours TIS.
(iv) For right tie rod attach bolt, P/N
SS5025–04H10, establish a life limit of 5,000
hours TIS.
(v) For oil cooler axial fan ball bearing,
P/N 210SFFC, installed in oil cooler axial
fans, P/N 70361–03005–103 through –106,
establish a life limit of 2,000 hours TIS; and
for bearings installed in oil cooler axial fan,
P/N 70361–03005–107, establish a life limit
of 2,500 hours TIS.
(vi) For oil cooler axial fan ball bearing,
P/N 210SFFC–0129, installed in oil cooler
axial fan, 70361–03005–103 through –106,
establish a life limit of 2,000 hours TIS; and
for bearings installed in oil cooler axial fan,
P/N 70361–03005–107, establish a life limit
of 2,500 hours TIS.
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Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations
pmangrum on DSK3VPTVN1PROD with RULES
(vii) For main rotor hub, P/N 70070–
10046–055, establish a life limit of 5,100
hours TIS.
(viii) For main rotor blade, P/N 70080–
15001–041, establish a life limit of 5,000
hours TIS.
(ix) For tail rotor blade, P/N 70080–15002–
041, establish a life limit of 5,000 hours TIS.
(x) For main rotor blade, P/N 70080–
15003–041, establish a life limit of 5,000
hours TIS.
(xi) For tail rotor blades, P/N 70080–
15004–041 and P/N 70080–15005–041,
establish a life limit of 5,000 hours TIS.
(xii) For main landing gear shock strut
piston assembly, P/N 70250–12067–102,
establish a life limit of 9,000 hours TIS.
(xiii) For Number 2 crossfeed breakaway
valve, P/N 70307–03600–103, establish a life
limit of 1,500 hours TIS;
(xiv) For main module planetary carrier
assembly, P/N 70351–08175–043, –044, and
–045, establish a life limit of 1,400 hours TIS;
and for P/N 70351–08175–046 establish a life
limit of 12,000 hours TIS.
(xv) For dowel pins, P/N 70351–08404–
101, –102, and –103 on main transmission
housings, P/N 70351–08110–044 and –045,
establish a life limit of 3,000 hours TIS; for
dowel pins, P/N 70351–08404–101, –102,
–103, and –104 on main transmission
housings, P/N 70351–28110–043 and –044,
establish a life limit of 7,300 hours TIS; for
dowel pins, P/N 70351–08404–101, –103,
and –104, on main transmission housings,
P/N 70351–38110–043, –044, and –045,
establish a life limit of 11,000 hours TIS.
(xvi) For dowel pin, flight control support
mounting to main transmission housing, P/N
70531–04805–101, 70531–04805–102, and
70531–08405–103, establish a life limit of
3,000 hours TIS.
(xvii) For dowel pin, flight control support
mounting to transmission case, P/N 70351–
28404–101, on main transmission housings,
P/N 70351–08110–044 and –045, reduce the
life limit from 4,300 hours TIS to 3,000 hours
TIS.
(xviii) For main module planetary carrier
assembly, P/N 70351–38175–041, establish a
life limit of 6,500 hours TIS.
(xvix) For dowel pin, flight control support
mounting to transmission case, P/N 70351–
38404–101, on main transmission housings,
P/N 70351–38110–043, –044, and –045,
reduce the life limit from 20,000 hours TIS
to 11,000 hours TIS.
(xx) For the tail rotor servo, P/N 70410–
06520–044, –045, and –046, establish a life
limit of 15,000 hours TIS.
(2) Remove from service any part with a
number of hours time-in-service equal to or
greater than the part’s retirement life as
stated in paragraph (e)(1) of this AD.
(f) Special Flight Permit
Special flight permits to allow flight in
excess of life limits will not be issued.
(g) Alternative Methods of Compliance
(AMOC)
(1) The Manager, Boston Aircraft
Certification Office, FAA, may approve
AMOCs for this AD. Send your proposal to:
Michael Davison, Flight Test Engineer, New
England Regional Office, 12 New England
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13:45 Nov 28, 2012
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Executive Park, Burlington, MA 01803;
phone: (781) 238–7156; email:
michael.davison@faa.gov.
(2) For operations conducted under 14 CFR
part 119 operating certificate or under 14
CFR part 91, subpart K, we suggest 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.
(h) Subject
Joint Aircraft Service Component (JASC)
Codes: 7921 Engine Oil Cooler, 6210 Main
Rotor Blades, 6320 Tail Rotor Head, 6410
Tail Rotor Blades, 6720 Tail Rotor Control
System, 3213 Main Landing Gear Strut/Axle/
Truck, 2824 Fuel Transfer Valve, and 1430
Fasteners.
Issued in Fort Worth, Texas, on November
2, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate,
Aircraft Certification Service.
[FR Doc. 2012–28427 Filed 11–28–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 43
[Docket No. FAA–2011–0763; Amendment
No. 43–45]
RIN 2120–AJ91
Pilot Loading of Aeronautical Database
Updates
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This action amends the
maintenance regulations by removing
from the preventive maintenance
category the task of updating databases
used in self-contained, front-panel or
pedestal-mounted navigation
equipment. Further, we are adding text
to the maintenance regulations that
describes which equipment and, under
which conditions, may have
aeronautical databases updated by pilots
as a non-maintenance function.
Equipment which does not meet the
criteria outlined in the new regulation
will continue to be updated as a
maintenance function. This revision
will ensure that pilots using specified
avionics equipment have the most
current and accurate data and thereby
increase aviation safety.
DATES: This rule becomes effective
January 28, 2013.
FOR FURTHER INFORMATION CONTACT: For
technical questions about this
SUMMARY:
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71089
rulemaking action, contact Chris Parfitt,
Flight Standards Service, Aircraft
Maintenance Division—Avionics
Maintenance Branch, AFS–360, Federal
Aviation Administration, 950 L’Enfant
Plaza SW., Washington, DC 20024;
telephone (202) 385–6398; facsimile
(202) 385–6474; email
chris.parfitt@faa.gov.
For legal questions about this action,
contact Viola M. Pando, Office of the
Chief Counsel, International Law,
Legislation, and Regulations Division—
Policy and Adjudication Branch, AGC–
210, Federal Aviation Administration,
800 Independence Ave. SW.,
Washington DC 20591; telephone (202)
493–5293; email viola.pando@faa.gov.
SUPPLEMENTARY INFORMATION:
Authority for This Rulemaking
The FAA’s authority to issue rules on
aviation safety is found in Title 49 of the
United States Code. 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.
This rulemaking is promulgated
under the authority described in
Subtitle VII, Part A, Subpart III, section
44701(a)(1), section 44703(b)(1)(D), and
section 44711(a)(2). In section
44701(a)(1), the FAA is charged with
prescribing regulations and minimum
standards in the interest of safety for the
manner of servicing of aircraft
appliances. In section 44703(b)(1)(D),
the FAA is charged with specifying the
capacity in which the holder of a
certificate may serve as an airman with
respect to an aircraft. Section
44711(a)(2) prohibits any person from
serving in any capacity as an airman
with respect to a civil aircraft or aircraft
appliance used, or intended for use, in
air commerce without an airman
certificate authorizing the airman to
serve in the capacity for which the
certificate was issued. This regulation is
within the scope of the cited authority.
I. Overview of the Final Rule
This final rule allows all pilots
operating aircraft equipped with
certificated avionics equipment as
described herein to perform updates of
aeronautical databases. In 1996, the
FAA updated the regulations defining
preventive maintenance to include
updating the navigation database of selfcontained, front-panel or pedestalmounted navigation equipment. This
allowed the holder of a pilot certificate
issued under part 61 to perform the
database upload on any aircraft owned
or operated by that pilot not used under
parts 121, 129, or 135 (hereafter refered
to as ‘‘restricted operations’’). The safety
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]]>Agencies
[Federal Register Volume 77, Number 230 (Thursday, November 29, 2012)]
[Rules and Regulations]
[Pages 71087-71089]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-28427]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1206; Directorate Identifier 2012-SW-021-AD;
Amendment 39-17269; AD 2012-23-13]
RIN 2120-AA64
Airworthiness Directives; Sikorsky Aircraft Corporation
(Sikorsky) Model Helicopters
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for
Sikorsky Model S-70, S-70A, and S-70C helicopters, which are restricted
category helicopters derived from the military Model UH-60 helicopter.
This AD would require reducing or establishing life limits for certain
listed helicopter parts. This AD is prompted by a review of the United
States Army's analysis of their Model UH-60 fleet, which determined it
necessary to establish or reduce the life limits of certain parts. The
actions are intended to prevent fatigue failure of a part and
subsequent loss of control of the helicopter.
DATES: This AD becomes effective December 14, 2012.
We must receive comments on this AD by January 28, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Docket: Go to https://www.regulations.gov. Follow the online instructions for sending your
comments electronically.
Fax: 202-493-2251.
Mail: Send comments to the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590-0001.
Hand Delivery: Deliver to the ``Mail'' address between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov or in person at the Docket Operations Office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the economic evaluation, any
comments received, and other information. The street address for the
Docket Operations Office (telephone 800-647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT: Michael Davison, Flight Test Engineer,
New England Regional Office, FAA, 12 New England Executive Park,
Burlington, MA 01803; phone: (781) 238-7156, email:
michael.davison@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not provide you with notice and an opportunity to
provide your comments prior to it becoming effective. However, we
invite you to participate in this rulemaking by submitting written
comments, data, or views. We also invite comments relating to the
economic, environmental, energy, or federalism impacts that resulted
from adopting this AD. The most helpful comments reference a specific
portion of the AD, 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 them only one time. We will file in the docket all comments that
we receive, as well as a report summarizing each substantive public
contact with FAA personnel concerning this rulemaking during the
comment period. We will consider all the comments we receive and may
conduct additional rulemaking based on those comments.
Discussion
We are adopting a new AD for Sikorsky Model S-70, S-70A and S-70C
helicopters. This AD requires reducing or establishing life limits for
the main rotor blade, tail rotor blade, planetary carrier assembly,
tail rotor servo, elastomeric sleeve bearing, main landing gear shock
strut piston cylinder, crossfeed valve, oil cooler axial fan ball
bearing assembly, dowel pins, main rotor hub, and right tie rod attach
bolt. This AD is prompted by the need to reduce life limits on the
specified parts. This determination is based on a review of analysis by
the U.S. Army of certain parts installed on the military Model UH-60
helicopters, which shows that the life limits of those parts need to be
reduced. The Sikorsky Model S-70, S-70A and S-70C helicopters are
restricted category helicopters derived from the military Model UH-60
helicopter. The actions are intended to
[[Page 71088]]
establish life limits for certain parts to prevent fatigue failure of a
part and subsequent loss of control of the helicopter.
FAA's Determination
We are issuing this AD because we evaluated all the relevant
information and determined the unsafe condition described previously is
likely to exist or develop in other helicopters of these same type
designs.
AD Requirements
This AD requires, before further flight, establishing or reducing
life limits for certain parts and removing from service each part that
has reached its life limit.
Costs of Compliance
We estimate that this AD will affect nine helicopters of U.S.
Registry. We estimate that operators may incur the following costs in
order to comply with this AD.
It will take about 4.7 work hours at $85 per work hour to replace
each part plus the required costs per helicopter as follows:
$70,000 for the main rotor blade,
$30,000 for the tail rotor blade,
$490 for the elastomeric sleeve bearing,
$233 for the right tie rod attach bolt,
$40,000 for the main rotor hub,
$12,000 for the main landing gear shock strut piston
system,
$44,000 for the tail rotor servo,
$200 for the crossfeed breakaway valve,
$59,000 for the main module planetary carrier assembly,
and
$3,700 for the dowel pins (11 total).
Based on these figures, the total estimated cost is $2,372,607 to
replace all the parts for the entire U.S. fleet.
FAA's Justification and Determination of the Effective Date
Since a part must be replaced before further flight if it has
reached its life limit and some of the parts may have exceeded or be
close to reaching the life limit, this AD must be issued immediately.
Since an unsafe condition exists that requires the immediate
adoption of this AD, we determined that notice and opportunity for
public comment before issuing this AD are impracticable and that good
cause exists for making this amendment effective in less than 30 days.
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.
We are 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
We 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, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska to the extent that
it justifies making a regulatory distinction; and
4. 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.
We prepared an economic evaluation of the estimated costs to comply
with this AD and placed it in the AD docket.
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):
2012-23-13 Sikorsky Aircraft Corporation: Amendment 39-17269; Docket
No. FAA-2012-1206; Directorate Identifier 2012-SW-021-AD.
(a) Applicability
This AD applies to Model S-70, S-70A, and S-70C helicopters,
certificated in any category.
(b) Unsafe Condition
This AD defines the unsafe condition as fatigue failure of a
main rotor blade, tail rotor blade, planetary carrier assembly, tail
rotor servo, elastomeric sleeve bearing, main landing gear shock
strut piston cylinder, crossfeed valve, oil cooler axial fan ball
bearing assembly, dowel pin, main rotor hub, or right tie attach
bolt remaining in service beyond its life limit. This condition
could result in loss of control of the helicopter.
(c) Effective Date
This AD becomes effective December 14, 2012.
(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 Action
Before further flight:
(1) Establish or reduce the retirement life of the following
parts listed in Table 1-1 of the Sikorsky Technical Manual TM 1-70-
23AW-2, change 3, section 1.1, Airworthiness Limitations, by
inserting a copy of Table 1-1 into the Airworthiness Limitations
section of TM 1-70-23AW-2 or by making the following pen and ink
changes to the Airworthiness Limitations of the maintenance manual:
(i) For each dowel pin on the main transmission housing, part
number (P/N) NAS607-10-12P, NAS607-12-14P, and NAS607-12-18P,
establish a life limit of 3,000 hours time-in-service (TIS).
(ii) For elastomeric sleeve bearing, P/N SB5203-202, establish a
life limit of 720 hours TIS.
(iii) For right tie rod attach bolt, P/N SS5025-04H010,
establish a life limit of 3,500 hours TIS.
(iv) For right tie rod attach bolt, P/N SS5025-04H10, establish
a life limit of 5,000 hours TIS.
(v) For oil cooler axial fan ball bearing, P/N 210SFFC,
installed in oil cooler axial fans, P/N 70361-03005-103 through -
106, establish a life limit of 2,000 hours TIS; and for bearings
installed in oil cooler axial fan, P/N 70361-03005-107, establish a
life limit of 2,500 hours TIS.
(vi) For oil cooler axial fan ball bearing, P/N 210SFFC-0129,
installed in oil cooler axial fan, 70361-03005-103 through -106,
establish a life limit of 2,000 hours TIS; and for bearings
installed in oil cooler axial fan, P/N 70361-03005-107, establish a
life limit of 2,500 hours TIS.
[[Page 71089]]
(vii) For main rotor hub, P/N 70070-10046-055, establish a life
limit of 5,100 hours TIS.
(viii) For main rotor blade, P/N 70080-15001-041, establish a
life limit of 5,000 hours TIS.
(ix) For tail rotor blade, P/N 70080-15002-041, establish a life
limit of 5,000 hours TIS.
(x) For main rotor blade, P/N 70080-15003-041, establish a life
limit of 5,000 hours TIS.
(xi) For tail rotor blades, P/N 70080-15004-041 and P/N 70080-
15005-041, establish a life limit of 5,000 hours TIS.
(xii) For main landing gear shock strut piston assembly, P/N
70250-12067-102, establish a life limit of 9,000 hours TIS.
(xiii) For Number 2 crossfeed breakaway valve, P/N 70307-03600-
103, establish a life limit of 1,500 hours TIS;
(xiv) For main module planetary carrier assembly, P/N 70351-
08175-043, -044, and -045, establish a life limit of 1,400 hours
TIS; and for P/N 70351-08175-046 establish a life limit of 12,000
hours TIS.
(xv) For dowel pins, P/N 70351-08404-101, -102, and -103 on main
transmission housings, P/N 70351-08110-044 and -045, establish a
life limit of 3,000 hours TIS; for dowel pins, P/N 70351-08404-101,
-102, -103, and -104 on main transmission housings, P/N 70351-28110-
043 and -044, establish a life limit of 7,300 hours TIS; for dowel
pins, P/N 70351-08404-101, -103, and -104, on main transmission
housings, P/N 70351-38110-043, -044, and -045, establish a life
limit of 11,000 hours TIS.
(xvi) For dowel pin, flight control support mounting to main
transmission housing, P/N 70531-04805-101, 70531-04805-102, and
70531-08405-103, establish a life limit of 3,000 hours TIS.
(xvii) For dowel pin, flight control support mounting to
transmission case, P/N 70351-28404-101, on main transmission
housings, P/N 70351-08110-044 and -045, reduce the life limit from
4,300 hours TIS to 3,000 hours TIS.
(xviii) For main module planetary carrier assembly, P/N 70351-
38175-041, establish a life limit of 6,500 hours TIS.
(xvix) For dowel pin, flight control support mounting to
transmission case, P/N 70351-38404-101, on main transmission
housings, P/N 70351-38110-043, -044, and -045, reduce the life limit
from 20,000 hours TIS to 11,000 hours TIS.
(xx) For the tail rotor servo, P/N 70410-06520-044, -045, and -
046, establish a life limit of 15,000 hours TIS.
(2) Remove from service any part with a number of hours time-in-
service equal to or greater than the part's retirement life as
stated in paragraph (e)(1) of this AD.
(f) Special Flight Permit
Special flight permits to allow flight in excess of life limits
will not be issued.
(g) Alternative Methods of Compliance (AMOC)
(1) The Manager, Boston Aircraft Certification Office, FAA, may
approve AMOCs for this AD. Send your proposal to: Michael Davison,
Flight Test Engineer, New England Regional Office, 12 New England
Executive Park, Burlington, MA 01803; phone: (781) 238-7156; email:
michael.davison@faa.gov.
(2) For operations conducted under 14 CFR part 119 operating
certificate or under 14 CFR part 91, subpart K, we suggest 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.
(h) Subject
Joint Aircraft Service Component (JASC) Codes: 7921 Engine Oil
Cooler, 6210 Main Rotor Blades, 6320 Tail Rotor Head, 6410 Tail
Rotor Blades, 6720 Tail Rotor Control System, 3213 Main Landing Gear
Strut/Axle/Truck, 2824 Fuel Transfer Valve, and 1430 Fasteners.
Issued in Fort Worth, Texas, on November 2, 2012.
Kim Smith,
Directorate Manager, Rotorcraft Directorate, Aircraft Certification
Service.
[FR Doc. 2012-28427 Filed 11-28-12; 8:45 am]
BILLING CODE 4910-13-P
