Federal Register / Vol. 77, No. 230 / Thursday, November 29, 2012 / Rules and Regulations 71087 

(d) Reason 

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 

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 

(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. 

(i) Material Incorporated by Reference 

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 

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 


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71088 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. 

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 

■ 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): 

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 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 

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 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: 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 

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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