Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34211 

■ For the reasons stated in the preamble, 

NRCS amends part 636 of Title 7 of the 

CFR as set forth below: 

PART 636—WILDLIFE HABITAT 

INCENTIVE PROGRAM 

■ 1. The authority citation for part 1466 

continues to read as follows: 

Authority: 16 U.S.C. 3839bb–1. 

■ 2. Amend § 636.3 by revising the 

definition of ‘‘agricultural lands’’ to read 

as follows: 

§ 636.3 Definitions. 

* * * * * 

Agricultural lands means cropland, 

grassland, rangeland, pasture, and other 

land determined by NRCS to be suitable 

for fish and wildlife habitat 

development on which agricultural and 

forest-related products or livestock are 

produced or have the potential to be 

produced. Agricultural lands may 

include cropped woodland, marshes, 

incidental areas included in the 

agricultural operation, and other types 

of land used for or have the potential to 

be used for production. 

Signed this 8th day of July 2009, in 

Washington, DC. 

Dave White, 

Vice President, Commodity Credit 

Corporation and Chief, Natural Resources 

Conservation Service. 

[FR Doc. E9–16705 Filed 7–14–09; 8:45 am] 

BILLING CODE 3410–16–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0633; Directorate 

Identifier 2009–CE–037–AD; Amendment 

39–15964; AD 2009–15–01] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation (Type 

Certificate Previously Held by 

Raytheon Aircraft Company) Model 

G36 Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Hawker Beechcraft Corporation (Type 

Certificate previously held by Raytheon 

Aircraft Company) Model G36 airplanes. 

This AD requires you to inspect for any 

improper installation and/or chafing of 

the P60/J60 electrical connector, 

associated wiring, and fuel line and, if 

found, correct the installation and 

replace damaged parts. This AD results 

from reports of chafing between the wire 

harness/connector(s) and fuel line. We 

are issuing this AD to detect and correct 

chafing between the wire harness/ 

connector(s) and fuel line. This chafing 

could lead to fuel leaking into the 

cockpit and fire in the cockpit if wiring 

arcs through the fuel line. 

DATES: This AD becomes effective on 

July 27, 2009. 

On July 27, 2009, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

We must receive any comments on 

this AD by September 14, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this AD. 

• 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, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

To get the service information 

identified in this AD, contact Hawker 

Beechcraft Corporation, Attn: Piston 

Technical Support, P.O. Box 85, 

Wichita, Kansas 67201; telephone: (800) 

429–5372; fax: (316) 676–8745; E-mail: 

tmdc@hawkerbeechcraft.com; Internet: 

http://www.hawkerbeechcraft.com. 

To view the comments to this AD, go 

to http://www.regulations.gov. The 

docket number is FAA–2009–0633; 

Directorate Identifier 2009–CE–037–AD. 

FOR FURTHER INFORMATION CONTACT: Jeff 

Pretz, Aerospace Engineer, 1801 Airport 

Road, Room 100, Wichita, Kansas 

67209; telephone: (316) 946–4153; fax: 

(316) 946–4107. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received reports of chafing 

between the fuel line and the P60/J60 

connector and wiring. One report 

indicated arcing from a chafing wire 

harness burned a hole through the fuel 

tube. Another report resulted from an 

inspection finding where the P60/J60 

connector directly contacted the fuel 

line. 

During the manufacturing of fuel line 

part number (P/N) 36–920001–13, 

protective insulation tube P/N 106242– 

6–01300, or other post-manufacturing 

spiral wrap was not installed or was 

located improperly, thereby allowing 

chafing electrical wire/connectors to 

directly contact the fuel line. 

This condition, if not corrected, could 

result in chafing between the wire 

harness/connector(s) and fuel line. This 

chafing could lead to fuel leaking into 

the cockpit and fire in the cockpit if 

wiring arcs through the fuel line. 

Relevant Service Information 

We reviewed Hawker Beechcraft 

Mandatory Service Bulletin SB 28–3967, 

dated June 2009. The service 

information describes procedures for 

inspecting for any improper installation 

and/or chafing of the P60/J60 electrical 

connector, associated wiring, and fuel 

line and, if found, correcting the 

installation and replacing damaged 

parts. 

FAA’s Determination and Requirements 

of This AD 

We are issuing this AD because we 

evaluated all the information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This AD requires you to 

inspect for any improper installation 

and/or chafing of the P60/J60 electrical 

connector, associated wiring, and fuel 

line and, if found, correct the 

installation and replace damaged parts. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because chafing between the wire 

harness/connector(s) and fuel line could 

lead to fuel leaking into the cockpit and 

fire in the cockpit if wiring arcs through 

the fuel line. Therefore, 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 

fewer than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and an 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments regarding this 

AD. Send your comments to an address 

listed under the ADDRESSES section. 

Include the docket number ‘‘FAA– 

2009–0633; Directorate Identifier 2009– 

CE–037–AD’’ at the beginning of your 


srobinson on DSKHWCL6B1PROD with RULES
34212 Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the AD. We will consider all 

comments received by the closing date 

and may amend the 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 we receive 

concerning this AD. 

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 above, 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); and 

(3) 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket that 

contains the AD, the regulatory 

evaluation, any comments received, and 

other information on the Internet at 

http://www.regulations.gov; or in person 

at the Docket Management Facility 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647– 

5527) is located at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

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): 

2009–15–01 Hawker Beechcraft 

Corporation (Type Certificate previously 

held by Raytheon Aircraft Company): 

Amendment 39–15964; Docket No. 

FAA–2009–0633; Directorate Identifier 

2009–CE–037–AD. 

Effective Date 

(a) This AD becomes effective on July 27, 

2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model G36 

airplanes, serial numbers E–3630, E–3636 

through E–3817, E–3819 through E–3834, E– 

3836 through E–3887, E–3889 through E– 

3896, E–3898, and E–3899, that are 

certificated in any category. 

Unsafe Condition 

(d) This AD results from reports of chafing 

between the wire harness/connector(s) and 

fuel line. We are issuing this AD to detect 

and correct improper installation and/or 

chafing between the wire harness/ 

connector(s) and fuel line. This chafing could 

lead to fuel leaking into the cockpit and fire 

in the cockpit if wiring arcs through the fuel 

line. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 

Actions Compliance Procedures 

(1) Inspect for improper installation of the P60/ 

J60 electrical connector, associated wiring, 

and fuel line. Also inspect for any chafing 

damage of the electrical wiring and fuel line.

Within 10 hours time-in-service (TIS) after 

July 27, 2009 (the effective date of this AD) 

or 6 calendar months after July 27, 2009 

(the effective date of this AD), whichever 

occurs first.

Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 28–3967, dated June 2009. 

(2) If, as a result of the inspection required by 

paragraph (e)(1) of this AD, you find any improper installation of the P60/J60 electrical 

connector, associated wiring, or fuel line, correct the installation of the P60/J60 electrical 

connector, associated wiring, and fuel line. If, 

as a result of the inspection required by paragraph (e)(1) of this AD, you find any chafing 

damage of the electrical wiring or fuel line, 

replace or repair the damaged parts.

Before further flight after the inspection required by paragraph (e)(1) of this AD.Follow Hawker Beechcraft Mandatory Service 

Bulletin SB 28–3967, dated June 2009. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Wichita Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to Attn: Jeff 

Pretz, Aerospace Engineer, 1801 Airport 

Road, Room 100, Wichita, Kansas 67209; 

telephone: (316) 946–4153; fax: (316) 946– 

4107. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your appropriate principal inspector 

(PI) in the FAA Flight Standards District 


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Federal Register / Vol. 74, No. 134 / Wednesday, July 15, 2009 / Rules and Regulations 34213 

Office (FSDO), or lacking a PI, your local 

FSDO. 

Material Incorporated by Reference 

(g) You must use Hawker Beechcraft 

Mandatory Service Bulletin SB 28–3967, 

dated June 2009, to do the actions required 

by this AD, unless the AD specifies 

otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Hawker Beechcraft 

Corporation, Attn: Piston Technical Support, 

P.O. Box 85, Wichita, Kansas 67201; 

telephone: (800) 429–5372; fax: (316) 676– 

8745; E-mail: tmdc@hawkerbeechcraft.com; 

Internet: http://www.hawkerbeechcraft.com. 

(3) You may review copies of the service 

information incorporated by reference for 

this AD at the FAA, Central Region, Office of 

the Regional Counsel, 901 Locust, Kansas 

City, Missouri 64106. For information on the 

availability of this material at the Central 

Region, call (816) 329–3768. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/

code_of_federal_regulations/

ibr_locations.html. 

Issued in Kansas City, Missouri, on July 2, 

2009. 

Scott A. Horn, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–16383 Filed 7–14–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0437; Directorate 

Identifier 2009–CE–018–AD; Amendment 

39–15963; AD 2009–14–13] 

RIN 2120–AA64 

Airworthiness Directives; Pilatus 

Aircraft Ltd. Models PC–12, PC–12/45, 

PC–12/47, and PC–12/47E Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI (two different 

MCAI) describes the unsafe condition 

as: 

FOCA AD HB 2002–271 was issued 

because the Nose Landing Gear (NLG) Right 

Hand (RH) upper drag link, Part Number (P/ 

N) 532.20.12.140 was found broken on some 

aircraft due to fatigue cracking, and therefore 

a life limit of 4,000 landings was introduced. 

Recent investigation of a new occurrence 

revealed that the replacement part NLG RH 

upper drag link P/N 532.20.12.289 also 

suffered fatigue cracking, however on a 

different location. 

Complete failure of the NLG RH upper drag 

link could result in NLG collapse during 

landing. 

and 

This Airworthiness Directive (AD) is 

prompted by reports of several in-service 

cracked torque tubes. A reduced wall 

thickness produced during the 

manufacturing process has been determined 

to be the initial cause. 

Additionally, all the involved torque tubes 

have been found to show fatigue cracking 

problems. 

Such a condition, if left uncorrected, could 

lead to failure of the torque tube and result 

in loss of the steering control on ground and 

consequent unsafe condition. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective 

August 19, 2009. 

On August 19, 2009, the Director of 

the Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on May 8, 2009 (74 FR 21561), 

and proposed to supersede AD 2003– 

14–07, Amendment 39–13226 (68 FR 

41903, July 16, 2003). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

(two different MCAI) states: 

FOCA AD HB 2002–271 was issued 

because the Nose Landing Gear (NLG) Right 

Hand (RH) upper drag link, Part Number (P/ 

N) 532.20.12.140 was found broken on some 

aircraft due to fatigue cracking, and therefore 

a life limit of 4,000 landings was introduced. 

Recent investigation of a new occurrence 

revealed that the replacement part NLG RH 

upper drag link P/N 532.20.12.289 also 

suffered fatigue cracking, however on a 

different location. 

Complete failure of the NLG RH upper drag 

link could result in NLG collapse during 

landing. To address that condition, this AD 

is issued to mandate the implementation of 

the latest revision of the PC–12 Aircraft 

Maintenance Manual (AMM) chapter 4— 

airworthiness limitations section—by 

establishing repetitive inspections for the 

NLG RH upper drag links P/N 532.20.12.140 

and P/N 532.20.12.289. 

and 

This Airworthiness Directive (AD) is 

prompted by reports of several in-service 

cracked torque tubes. A reduced wall 

thickness produced during the 

manufacturing process has been determined 

to be the initial cause. 

Additionally, all the involved torque tubes 

have been found to show fatigue cracking 

problems. 

Such a condition, if left uncorrected, could 

lead to failure of the torque tube and result 

in loss of the steering control on ground and 

consequent unsafe condition. 

For the reason described above, this new 

AD mandates the replacement of certain 

torque tubes by new ones of an improved 

design and the latest revision of chapter 4 

‘limitations’ of the PC–12 Aircraft 

Maintenance Manual (AMM) which 

introduces the new life limit for torque tubes 

with Part Number (P/N) 532.50.12.047. 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Comment Issue: Require Using 

Limitations Document in Latest 

Maintenance 

Manual Revision 

Tim Kitzman states that document 

12–A–04–00–00–00A–000T–A, dated 

January 28, 2009, has been incorporated 

into the latest revision of the aircraft 

maintenance manual. He requests that 

we update the AD to require 

incorporating the data module found in 

PC–12 AMM, Document No. 02049, Rev 

19, dated March 1, 2009. 

We disagree with the commenter. 

Structural and Component 

Limitations—Airworthiness Limitations, 

document 12–A–04–00–00–00A–000T– 


srobinson on DSKHWCL6B1PROD with RULES