[Federal Register Volume 77, Number 230 (Thursday, November 29, 2012)]
[Rules and Regulations]
[Pages 71087-71089]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2012-28427]
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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.
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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 http://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 http://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:
[email protected].
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:
[email protected].
(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]
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