35354 Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules 

principles and precedent for the award 

is required to be provided to the parties; 

(b) The language described in 

paragraph (a)(1) of this section shall 

immediately precede the following 

language, which must appear as follows 

on the signature page of the contract in 

bold conspicuous print: 

Right to Decline Arbitration. A 

poultry grower, livestock producer or 

swine production contract grower has 

the right to decline to be bound by the 

arbitration provision set forth in this 

agreement. A poultry grower, livestock 

producer or swine production contract 

grower shall indicate whether or not it 

desires to be bound by the arbitration 

provision by signing one of the 

following statements: 

I decline to be bound by the 

arbitration provisions set forth in this 

Agreement ________________________

________________ 

I accept the arbitration provisions as 

set forth in this Agreement ___________

_____________________________ 

Failure to choose an option by signing 

one of the above renders the contract 

void. 

J. Dudley Butler, 

Administrator, Grain Inspection, Packers and 

Stockyards Administration. 

[FR Doc. 2010–14875 Filed 6–18–10; 11:15 am] 

BILLING CODE 3410–KD–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0555; Directorate 

Identifier 2009–NE–18–AD] 

RIN 2120–AA64 

Airworthiness Directives; Honeywell 

International Inc. TPE331–10 and 

TPE331–11 Series Turboprop Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for Honeywell 

International Inc. TPE331–10 and 

TPE331–11 series turboprop engines. 

That AD currently requires removing 

certain first stage turbine disks from 

service. This proposed AD would 

require the same actions, and would 

also require performing fluorescent 

penetrant inspections (FPI) and eddy 

current inspections (ECI) on certain first 

stage turbine disks that have a serial 

number (S/N) listed in this proposed 

AD. This proposed AD results from our 

determination that we need to expand 

the affected population to include other 

disks from the same heat lot as the 

failed first stage turbine disk, and that 

certain inspections are also required. 

We are proposing this AD to prevent 

uncontained failure of the first stage 

turbine disk and damage to the airplane. 

DATES: We must receive any comments 

on this proposed AD by August 23, 

2010. 

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. 

FOR FURTHER INFORMATION CONTACT: 

Joseph Costa, Aerospace Engineer, Los 

Angeles Aircraft Certification Office, 

FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: 

joseph.costa@faa.gov; telephone (562) 

627–5246; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2009–0555; Directorate Identifier 2009– 

NE–18–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. 

Discussion 

The FAA proposes to amend 14 CFR 

part 39 by superseding AD 2009–17–05, 

Amendment 39–15996 (74 FR 41327, 

August 17, 2009). That AD requires 

removal from service of first stage 

turbine disks, P/Ns 3101520–1 and 

3107079–1, serial numbers 2–03501– 

2299, 2–03501–2300, 2–03501–2301, 2– 

03501–2302, and 2–03501–2304, within 

25 flight hours or 25 cycles-in-service 

(CIS) after the effective date of this AD, 

whichever occurs first. That AD was the 

result of a report of an uncontained 

failure of a first stage turbine disk that 

had a metallurgical defect. That 

condition, if not corrected, could result 

in uncontained failure of the first stage 

turbine disk and damage to the airplane. 

Actions Since AD 2009–17–05 was 

Issued 

Since that AD was issued, we 

determined that up to 360 other turbine 

disks have been produced from the 

same heat lot as the failed turbine disk 

and might have similar inclusions. 

These inclusions can result in cracks 

that could result in an uncontained 

separation of a turbine disks. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Honeywell 

International Inc. Alert Service Bulletin 

TPE331–72–A2156, dated December 2, 

2008, that describes S/Ns of the affected 

turbine disks and procedures for initial 

and repetitive FPI and ECI of the first 

stage turbine disk. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 


srobinson on DSKHWCL6B1PROD with PROPOSALS
Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules 35355 

condition that is likely to exist or 

develop on other products of this same 

type design. For that reason, we are 

proposing this AD, which would 

require: 

• For turbine disks that have a S/N 

listed in Table 1 of this proposed AD 

with 4,100 or fewer cycles-since-new 

(CSN) on the effective date of this 

proposed AD, performing an initial FPI 

and ECI within 4,500 CSN or at the next 

access, whichever occurs first. 

• For turbine disks that have a S/N 

listed in Table 1 of this proposed AD 

with more than 4,100 CSN on the 

effective date of this proposed AD, 

performing an initial FPI and ECI within 

400 CIS after the effective date of this 

proposed AD or at the next access, 

whichever occurs first. 

• Thereafter, for turbine disks that 

have a S/N listed in Table 1 of this 

proposed AD, perform a repetitive FPI 

and ECI at each scheduled hot section 

inspection, but not to exceed 3,600 

hours-since-last inspection. 

The proposed AD would require that 

you do these actions using the service 

information described previously. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 90 engines installed on 

airplanes of U.S. registry. We also 

estimate that it would take about 20 

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 

$19,000 per engine. We estimate that 

one disk would fail the initial 

inspection and that repetitive 

inspections would be performed on 89 

engines. We estimate that one engine 

would fail the repetitive inspections and 

that further repetitive inspections would 

be performed on 88 engines. We 

estimate that an additional one disk 

would fail those repetitive inspections 

before retirement. Based on these 

figures, we estimate the total cost of the 

proposed AD to U.S. operators to be 

$511,155. 

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 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. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 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 

removing Amendment 39–15996 (74 FR 

41327, August 17, 2009) and by adding 

a new airworthiness directive to read as 

follows: 

Honeywell International Inc. (formerly 

AlliedSignal Inc., Garrett Engine 

Division; Garrett Turbine Engine 

Company; and AiResearch 

Manufacturing Company of Arizona): 

Docket No. FAA–2009–0555; Directorate 

Identifier 2009–NE–18–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

August 23, 2010. 

Affected ADs 

(b) This AD supersedes AD 2009–17–05, 

Amendment 39–15996. 

Applicability 

(c) This AD applies to Honeywell 

International Inc. TPE331–10 and TPE331–11 

series turboprop engines with a first stage 

turbine disk, part number (P/N) 3101520–1 or 

3107079–1, with a serial number (S/N) listed 

in Table 1 of this AD, installed. These 

engines are installed on, but not limited to, 

British Aerospace Jetstream 3201 series, 

Cessna Aircraft Company Model 441 

Conquest, Construcciones Aeronauticas, S.A. 

(CASA) C–212 series, Dornier Luftfahrt 

Dornier 228 series, Hawker Beechcraft 

(formerly Raytheon, formerly Beech) B100, 

C90 and E90, M7 Aerospace (formerly 

Fairchild) SA226 and SA227 series 

(Swearingen Merlin and Metro series), 

Mitsubishi MU–2B series (MU–2 series), PZL 

M18 series, and Twin Commander 680 and 

690 series (Jetprop Commander) airplanes. 

TABLE 1—FIRST STAGE TURBINE DISK S/NS

Disk P/N Disk S/N 

3101520–1 or 3107079–1 ............................................................................................................... 1–03501–4275 thru 1–03501–4306 inclusive. 

1–03501–4308 thru 1–03501–4339 inclusive. 

1–03501–4341 thru 1–03501–4438 inclusive. 

1–03501–4440 thru 1–03501–4471 inclusive. 

1–03501–4473 thru 1–03501–4504 inclusive. 

1–03501–4506 thru 1–03501–4537 inclusive. 

1–03501–4539 thru 1–03501–4570 inclusive. 

1–03501–4572 thru 1–03501–4599 inclusive. 


srobinson on DSKHWCL6B1PROD with PROPOSALS
35356 Federal Register / Vol. 75, No. 119 / Tuesday, June 22, 2010 / Proposed Rules 

TABLE 1—FIRST STAGE TURBINE DISK S/NS—Continued 

Disk P/N Disk S/N 

2–03501–2260 thru 2–03501–2272 inclusive. 

2–03501–2274 thru 2–03501–2298 inclusive. 

Unsafe Condition 

(d) This AD results from our determination 

that we need to expand the affected 

population to include other disks from the 

same heat lot as the failed first stage turbine 

disk. We are issuing this AD to prevent 

uncontained failure of the first stage turbine 

disk and damage to the airplane. 

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. 

Removal of First Stage Turbine Disks From 

Service 

(f) Within 25 flight hours or 25 cycles-inservice (CIS) after September 1, 2009, remove 

from service first stage turbine disks, P/N 

3101520–1 and P/N 3107079–1, serial 

numbers 2–03501–2299, 2–03501–2300, 2– 

03501–2301, 2–03501–2302, and 2–03501– 

2304. 

Initial Inspection 

(g) For first stage turbine disks, P/N 

3101520–1 or 3107079–1, that have a S/N 

listed in Table 1 of this AD, perform a 

fluorescent penetrant inspection (FPI) on the 

disk as follows: 

(1) For turbine disks with 4,100 or fewer 

cycles-since-new (CSN) on the effective date 

of this proposed AD, perform an initial FPI 

by using paragraph 3.B.(2) through 3.B.(5) of 

Honeywell International Inc. Alert Service 

Bulletin (ASB) TPE331–72–A2156, dated 

December 2, 2008, within 4,500 CSN or at the 

next access, whichever occurs first. 

(2) For turbine disks with more than 4,100 

CSN on the effective date of this proposed 

AD, perform an initial FPI by using 

paragraph 3.B.(2) through 3.B.(5) of 

Honeywell International Inc. ASB TPE331– 

72–A2156, dated December 2, 2008, within 

400 CIS after the effective date of this 

proposed AD or at the next access, whichever 

occurs first. 

(3) If you find a crack in the disk, remove 

the disk from service. 

(4) If the disk passes the FPI inspection, 

perform a special eddy current inspection 

(ECI) by using paragraph 3.B.(6) of 

Honeywell International Inc. ASB TPE331– 

72–A2156, dated December 2, 2008. 

Repetitive Inspection 

(h) Thereafter, perform repetitive FPI and 

ECI at each scheduled hot section inspection, 

but not to exceed 3,600 hours-since-last 

inspection. Use paragraph 3.B.(2) through 

3.B.(6) of Honeywell International Inc. ASB 

TPE331–72–A2156, dated December 2, 2008. 

(i) If you find a crack in the disk, remove 

the disk from service. 

Installation Prohibition 

(j) After September 1, 2009, do not approve 

for return to service, any engine that has a 

first stage turbine disk, P/N 3101520–1 and 

P/N 3107079–1, with S/N 2–03501–2299, 2– 

03501–2300, 2–03501–2301, 2–03501–2302, 

and 2–03501–2304. 

(k) After the effective date of this AD, do 

not approve for return to service, any engine 

that has a first stage turbine disk, P/N 

3101520–1 and P/N 3107079–1, and a S/N 

listed in Table 1 of this AD, unless that disk 

has passed an FPI as specified in paragraph 

3.B.(3) through 3.B.(6) of Honeywell 

International Inc. ASB TPE331–72–A2156, 

dated December 2, 2008. 

Alternative Methods of Compliance 

(l) The Manager, Los Angles Aircraft 

Certification Office, FAA, has the authority to 

approve alternative methods of compliance 

for this AD if requested using the procedures 

found in 14 CFR 39.19. 

Definition 

(m) For the purpose of this AD, ‘‘next 

access to the first stage turbine disk’’ is 

defined as the removal of the second stage 

turbine nozzle from the turbine stator 

housing. 

Related Information 

(n) Contact Joseph Costa, Aerospace 

Engineer, Los Angeles Aircraft Certification 

Office, FAA, Transport Airplane Directorate, 

3960 Paramount Blvd., Lakewood, CA 

90712–4137; e-mail: joseph.costa@faa.gov; 

telephone (562) 627–5246; fax (562) 627– 

5210, for more information about this AD. 

(o) Honeywell International Inc. ASB 

TPE331–72–A2156, dated December 2, 2008, 

pertains to the subject of this AD. Contact 

Honeywell International Inc., 111 S. 34th 

Street, Phoenix, AZ 85034–2802; Web site: 

http://portal.honeywell.com, for a copy of 

this service information. 

Issued in Burlington, Massachusetts, on 

June 16, 2010. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–15068 Filed 6–21–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0552; Directorate 

Identifier 2009–NM–095–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–200B, 

and 747–200F Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede two existing airworthiness 

directives (AD) that apply to certain 

Model 747–100, 747–200B, and 747– 

200F series airplanes. The existing ADs 

currently require inspections to detect 

fatigue-related skin cracks and corrosion 

of the skin panel lap joints in the 

fuselage upper lobe, and repair if 

necessary. One of the existing ADs, AD 

94–12–09, also requires modification of 

certain lap joints and inspection of 

modified lap joints. The other AD, AD 

90–15–06, requires repetitive detailed 

external visual inspections of the 

fuselage skin at the upper lobe skin lap 

joints for cracks and evidence of 

corrosion, and related investigative and 

corrective actions. This proposed AD 

would reduce the maximum interval of 

the post-modification inspections, and 

adds post-repair inspection 

requirements for certain airplanes. This 

proposed AD results from reports of 

cracking on modified airplanes. We are 

proposing this AD to detect and correct 

fatigue cracking and corrosion in the 

fuselage upper lobe skin lap joints, 

which could lead to rapid 

decompression of the airplane and 

inability of the structure to carry failsafe loads. 

DATES: We must receive comments on 

this proposed AD by August 6, 2010. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 


srobinson on DSKHWCL6B1PROD with PROPOSALS