```

[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 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: 
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
```