Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules 78937 

Number represented 

by label or test 

Maximum number 

within tolerances 

Number represented 

by label or test 

Maximum number 

within tolerances 

Number represented 

by label or test 

Maximum number 

within tolerances 

(X) (Y) (X) (Y) (X) (Y) 

32 41 66 79 100 116 

33 42 67 80 ................................... ...................................

10. In § 201.74, paragraph (a) is 

amended by removing the last sentence, 

and paragraph (c) is amended by adding 

a sentence at the end of the paragraph 

to read as follows: 

§ 201.74 Labeling of all classes of certified 

seed. 

* * * * * 

(c) * * * The seed lot number or 

other identification number, the kind, 

and variety name (if certified to variety) 

shall appear on the official label and/or 

directly on the container in a position 

to be viewed in conjunction with the 

official certification label. 

* * * * * 

11. In § 201.75, paragraph (c), the last 

sentence is revised to read as follows: 

§ 201.75 Interagency certification. 

* * * * * 

(c) * * * The seed lot number or 

other identification number, the kind, 

and variety name (if certified to variety) 

shall appear on the official label and/or 

directly on the container in a position 

to be viewed in conjunction with the 

official certification label. 

Dated: December 10, 2010. 

Robert C. Keeney, 

Acting Administrator, Agricultural Marketing 

Service. 

[FR Doc. 2010–31573 Filed 12–16–10; 8:45 am] 

BILLING CODE 3410–02–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1185; Directorate 

Identifier 2009–NE–24–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International LTS101 Series Turboshaft 

Engines and LTP101 Series Turboprop 

Engines 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: This supplemental NPRM 

revises an earlier proposed 

airworthiness directive (AD), for 

Honeywell International LTS101–600A 

series and LTS101–700D–2 turboshaft 

engines, and LTP101–600A–1A and 

LTP101–700A–1A turboprop engines 

with power turbine blades, part number 

(P/N) 4–141–084–06, installed. That 

proposed AD would have required 

removing power turbine blades, P/N 

4–141–084–06 from service, using a 

drawdown schedule specified in that 

proposed AD. That proposal was 

prompted by reports of fatigue cracks in 

the airfoil of the power turbine blade. 

This action revises the proposed rule by 

expanding and clarifying the 

applicability to include more engine 

models and power turbine blade P/Ns 

that could have the unsafe condition, 

and by clarifying the applicability by 

specifying power turbine rotor P/Ns 

instead of the blade P/Ns. The actions 

specified by this proposed AD are 

intended to prevent fracture of the 

power turbine blade airfoil, which could 

result in sudden loss of engine power 

and prevent continued safe flight or safe 

landing. 

DATES: We must receive any comments 

on this proposed AD by February 15, 

2011. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD. 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

Contact Honeywell International Inc., 

P.O. Box 52181, Phoenix, AZ 85072– 

2181; telephone (800) 601–3099 (U.S.A.) 

or (602) 365–3099 (International); or go 

to: https://portal.honeywell.com/wps/ 

portal/aero, for a copy of the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Robert Baitoo, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: 

robert.baitoo@faa.gov; telephone (562) 

627–5245; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2009–1185; Directorate Identifier 2009– 

NE–24–AD’’ in the subject line of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
78938 Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules 

Discussion 

The FAA proposed to amend part 39 

of the Federal Aviation Regulations (14 

CFR part 39) to add an AD, applicable 

to Honeywell International LTS101– 

600A series and LTS101–700D–2 

turboshaft engines, and LTP101–600A– 

1A and LTP101–700A–1A turboprop 

engines. We published the proposed AD 

in the Federal Register on December 21, 

2009 (74 FR 67829). That action 

proposed to require removing power 

turbine blades, P/N 4–141–084–06, from 

service using a specific drawdown 

schedule. That NPRM was prompted by 

reports of fatigue cracks in the airfoil of 

the power turbine blade. That condition, 

if not corrected, could result in fracture 

of the power turbine blade airfoil, which 

could result in sudden loss of engine 

power. 

Since we issued that NPRM, 

Honeywell International Inc. informed 

us that power turbine blades, P/N 4– 

141–084–03, could also have the unsafe 

condition. Those blades are used in 

power turbine rotors P/Ns 4–141–290– 

02 and 4–141–290–16. Based on the 

information we received from 

Honeywell International Inc., we also 

determined that specifying the 

applicability by power turbine rotors 

P/N is clearer than by specifying the 

blade P/N. 

Comments 

We provided the public the 

opportunity to participate in the 

development of that proposed AD. We 

have considered the comments received 

on the original NPRM. 

Proposed AD Should Apply to Engines 

on Multi-Engine Helicopters 

One commenter, the National 

Transportation Safety Board (NTSB) 

asks us to consider adding to the 

applicability of the proposed AD, 

engines that also use the affected P/N 

turbine rotor blade, and are installed on 

multi-engine helicopters. The NTSB 

states that loss of power in one of the 

two engines is a safety issue. 

We agree with the NTSB that the 

fracture of a power turbine airfoil of an 

LTS101 series turboshaft engine 

installed on a twin-engine helicopter is 

a safety issue. We added Honeywell 

International Inc. LTS101–650B–1, 

LTS101–650C–3, LTS101–650C–3A, 

LTS101–750B–1, LTS101–750B–2, 

LTS101–750C–1, and LTS101–850B–2 

turboshaft engines that are installed on 

twin-engine helicopters to the 

applicability of the proposed AD. We 

also added to the applicability, 

paragraph (g), and Table 1 of the 

proposed AD, Honeywell International 

Inc. LTP101–600A–1A and LTP101– 

700A–1A turboprop engines that use the 

same blades. 

The NTSB also requested that we 

reduce the drawdown schedule for the 

affected blades to remove the at risk 

power turbine rotor blades sooner. 

We don’t agree. Our risk assessment 

for the unsafe condition doesn’t justify 

accelerating the drawdown schedules. 

Editorial Changes to Table 1 and Table 

1 of the Proposed AD 

We changed Table 1 and Table 2 in 

the proposed AD to eliminate arbitrary 

step changes. 

Since these changes expand the scope 

of the originally proposed rule, we 

determined that reopening the comment 

period is appropriate. 

FAA’s Determination of an Unsafe 

Condition and Proposed Actions 

Since an unsafe condition has been 

identified that is likely to exist or 

develop on other Honeywell 

International Inc. LTS101–600A–2, –3, 

–3A, LTS101–700D–2, LTS101–650B–1, 

LTS101–650C–3, LTS101–650C–3A, 

LTS101–750B–1, LTS101–750B–2, 

LTS101–750C–1, and LTS101–850B–2 

turboshaft engines; and LTP101–600A– 

1A and LTP101–700A–1A turboprop 

engines of the same type design, the 

proposed AD would require removing 

from service, power turbine rotors, P/Ns 

4–141–290–01, –02, –03, –05, –06, –11, 

–12, –13, –14, or –16, using the 

compliance drawdown schedule 

specified in Table 1, and Table 2 of this 

AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 240 engines installed on 

aircraft of U.S. registry. We also estimate 

that it would take about 30 work-hours 

per engine to perform the proposed 

actions, and that the average labor rate 

is $85 per work-hour. Required parts 

would cost about $70,000 per engine. 

Based on these figures, we estimate the 

total cost of the proposed AD to U.S. 

operators to be $17,412,000. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Would 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 a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. You may get a copy 

of this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Accordingly, pursuant to the 

authority delegated to me by the 

Administrator, the Federal Aviation 

Administration proposes to amend part 

39 of the Federal Aviation Regulations 

(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: 

Honeywell International Inc. (Formerly 

AlliedSignal, Textron Lycoming): Docket 

No. FAA–2009–1185; Directorate 

Identifier 2009–NE–24–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

February 15, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Honeywell 

International LTS101–600A–2, –3, –3A, 

LTS101–700D–2, LTS101–650B–1, LTS101– 

650C–3, LTS101–650C–3A, LTS101–750B–1, 

LTS101–750B–2, LTS101–750C–1, and 

LTS101–850B–2 turboshaft engines; and 

LTP101–600A–1A and LTP101–700A–1A 

turboprop engines with power turbine rotor, 

part number (P/N) 4–141–290–01, –02, –03, 

–05, –06, –11, –12, –13, –14, or –16, 

installed. These engines are installed on, but 

not limited to, Eurocopter AS350 and BK117 

series and Bell 222 series helicopters; and 

Page Thrush, Air Tractor AT–302, and Pacific 

Aero 08–600, Piaggio P166 DL3, and Riley 

International R421 airplanes. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 242 / Friday, December 17, 2010 / Proposed Rules 78939 

Unsafe Condition 

(d) This AD results from reports of fatigue 

cracks in the airfoil of the power turbine 

blade. We are issuing this AD to prevent 

fracture of the power turbine blade airfoil, 

which could result in sudden loss of engine 

power and prevent continued safe flight or 

safe landing. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

(f) For engines with power turbine rotors, 

P/Ns 4–141–290–11, –12, –13, and –14, 

marked with ‘‘ORI T41881,’’ on the aft hub in 

the vicinity of the P/N, no further action is 

required. 

Removing Power Turbine Rotors From 

LTS101–600A–2, –3, –3A, and LTS101– 

700D–2 Turboshaft Engines and LTP101– 

600A–1A and LTP101–700A–1A Turboprop 

Engines 

(g) For LTS101–600A–2, –3, –3A, and 

LTS101–700D–2 turboshaft engines and 

LTP101–600A–1A and LTP101–700A–1A 

turboprop engines, remove power turbine 

rotors, P/Ns 4–141–290–01, –02, –03, –05, 

–06, –11, –12, –13, –14, or –16, using the 

cycles specified in Table 1 of this AD: 

TABLE 1—DRAWDOWN CYCLES FOR LTS101–600A–2, –3, –3A, AND LTS101–700D–2 TURBOSHAFT ENGINES AND

LTP101–600A–1A AND LTP101–700A–1A TURBOPROP ENGINES

If power turbine rotor time on the effective date of this AD is * * * Then remove the power turbine rotor from the engine * * * 

(1) Fewer than 5,000 cycles-since-new (CSN) ........................................ Between 5,000 and 5,500 CSN. 

(2) 5,000 to 7,899 CSN ............................................................................ Within 500 cycles-in-service (CIS) after the effective date of this AD or 

before exceeding 8,000 CSN, whichever occurs first. 

(3) 7,900 to 9,999 CSN ............................................................................ Within 100 CIS after the effective date of this AD or before exceeding 

10,050 CSN, whichever occurs first. 

(4) 10,000 or more CSN ........................................................................... Within 50 CIS after the effective date of this AD. 

Removing Power Turbine Rotors From 

LTS101–650B–1, –650C–3,—650C–3A, 

–750B–1, –2, –750C–1, and –850B–2 Engines 

(h) Remove power turbine rotors, P/Ns 

4–141–290–01, –02 –03, –05, –06, –11, –12, 

–13, –14, or –16, using the cycles specified 

in Table 2 of this AD: 

TABLE 2—DRAWDOWN CYCLES FOR LTS101–650B–1, –650C–3,–650C–3A, –750B–1, –2, –750C–1, AND –850B–2 

ENGINES

If power turbine rotor time on the effective date of this AD is * * * Then remove the power turbine rotor from the engine * * * 

(1) Fewer than 5,500 CSN ....................................................................... Between 5,000 and 7,200 CSN. 

(2) 5,500 to 7,999 CSN ............................................................................ Within 1,700 CIS after the effective date of this AD or before exceeding 

8,950 CSN, whichever occurs first. 

(3) 8,000 to 9,999 CSN ............................................................................ Within 950 CIS after the effective date of this AD or before exceeding 

10,400 CSN, whichever occurs first. 

(4) 10,000 or more CSN ........................................................................... Within 400 CIS after the effective date of this AD. 

Alternative Methods of Compliance 

(i) The Manager, Los Angles Aircraft 

Certification Office, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(j) Contact Robert Baitoo, Aerospace 

Engineer, Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: robert.baitoo@faa.gov; 

telephone (562) 627–5245; fax (562) 627– 

5210, for more information about this AD. 

(k) Honeywell International Inc. Service 

Bulletins LT 101–71–00–0252 and LTS101– 

71–00–0253, pertain to the subject of this AD. 

Contact Honeywell International Inc., P.O. 

Box 52181, Phoenix, AZ 85072–2181; 

telephone (800) 601–3099 (U.S.A.) or (602) 

365–3099 (International); or go to: https:// 

portal.honeywell.com/wps/portal/aero, for a 

copy of this service information. 

Issued in Burlington, Massachusetts, on 

December 13, 2010. 

Thomas A. Boudreau, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–31782 Filed 12–16–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employment and Training 

Administration 

20 CFR Part 641 

RIN 1205–AB60 

Senior Community Service 

Employment Program; Notice of 

Proposed Rulemaking, Additional 

Indicator on Volunteer Work; 

Correction 

AGENCY: Employment and Training 

Administration, Labor. 

ACTION: Proposed rule; correction. 

SUMMARY: This document corrects an 

expiration date cited in the Notice of 

Proposed Rulemaking (NPRM) of the 

Senior Community Service Employment 

Program (SCSEP), Additional Indicator 

on Volunteer Work that was published 

on November 23, 2010. The NPRM 

updates the SCSEP regulations to add an 

indicator to measure the number of 

exiting participants who enter volunteer 

work. The relevant Office of 

Management and Budget (OMB) Control 

Number for SCSEP’s approved 

information collection is 1205–0040. 

The NPRM stated that the expiration 

date for 1205–0040 was October 31, 

2010. However, that date is incorrect. 

The information collection is now 

pending with OMB, as the Department 

has requested a 3-year extension on the 

expiration of the approval date for it. 

Therefore 1205–0040 remains current 

on a month-by-month basis until OMB 

acts on the current information 


srobinson on DSKHWCL6B1PROD with PROPOSALS