44308 Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules 

As part of its priority-setting activities 

for fiscal year 2006, DOE conducted 

analyses for residential clothes washers 

to estimate the energy savings potential 

of amended standards. DOE determined 

that amended standards could result in 

energy savings for residential clothes 

washers of 5.5 quads cumulative over 

the period of 2004–2030. A summary of 

these analyses is available on DOE’s 

Web site at http:// 

www1.eere.energy.gov/buildings/ 

appliance_standards/pdfs/ 

2006_activities_data_sheets.pdf. 

Subsequently, Congress enacted the 

Energy Independence and Security Act 

of 2007 (EISA 2007), Public Law 110– 

140, which revised the energy 

conservation standards for residential 

clothes washers. The revised standards 

established a maximum water factor of 

9.5 and become effective on January 1, 

2011. See EISA 2007, Section 311(a)(2), 

codified at 42 U.S.C. 6295(g)(9). EISA 

2007 further required that DOE publish 

a final rule no later than December 31, 

2011, to determine whether to amend 

the standards in effect for clothes 

washers manufactured on or after 

January 1, 2015. (42 U.S.C. 

6295(g)(9)(B)(i)) DOE is embarking on a 

standards rulemaking for these products 

to comply with these EISA 2007 

requirements. 

To begin the required rulemaking 

process, the Department has prepared a 

framework document to explain the 

issues, analyses, and process that it is 

considering for the development of 

amended energy conservation standards 

for residential clothes washers. This 

document will be publicly available for 

review. Additionally, DOE will hold a 

public meeting to focus on the analyses 

and issues contained in various sections 

of the framework document. For each 

item listed, the Department will make a 

presentation with discussion to follow. 

The Department will also make a brief 

presentation on the rulemaking process 

for these products. 

The Department encourages anyone 

who wishes to participate in the public 

meeting to obtain the framework 

document and to be prepared to discuss 

its contents. A copy of the draft 

framework document is available at 

http://www1.eere.energy.gov/buildings/ 

appliance_standards/residential/ 

clothes_washers.html. However, public 

meeting participants need not limit their 

comments to the topics identified in the 

framework document. The Department 

is also interested in receiving views on 

other relevant issues that participants 

believe would affect energy 

conservation standards for these 

products. The Department welcomes all 

interested parties, whether or not they 

participate in the public meeting, to 

submit in writing by September 28, 

2009, comments and information on 

matters addressed in the framework 

document and on other matters relevant 

to consideration of standards for 

residential clothes washers. 

DOE will conduct the public meeting 

in an informal, conference style. A court 

reporter will record the minutes of the 

meeting. The discussion will not 

include proprietary information, costs 

or prices, market shares, or other 

commercial matters regulated by U.S. 

antitrust laws. 

After the public meeting and the 

expiration of the period for submitting 

written statements, the Department will 

begin collecting data, conducting the 

analyses as discussed at the public 

meeting, and reviewing public 

comments. 

Anyone who wishes to participate in 

the public meeting, receive meeting 

materials, or be added to the DOE 

mailing list to receive future notices and 

information about residential clothes 

washers should contact Ms. Brenda 

Edwards at (202) 586–2945. 

Issued in Washington, DC, on August 21, 

2009. 

Cathy Zoi, 

Assistant Secretary, Energy Efficiency and 

Renewable Energy. 

[FR Doc. E9–20803 Filed 8–27–09; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0778; Directorate 

Identifier 2009–CE–040–AD] 

RIN 2120–AA64 

Airworthiness Directives; Twin 

Commander Aircraft Corporation 

Models 690, 690A, and 690B Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Twin Commander Aircraft Corporation 

Models 690, 690A, and 690B airplanes. 

This proposed AD would require you to 

inspect between the surface of the lefthand (LH) and right-hand (RH) upper 

wing skins and the engine mount beam 

support straps for any signs of 

corrosion, replace the upper steel straps 

with parts of improved design, and 

modify both wings. This proposed AD 

results from reports that corrosion was 

found between the mating surfaces of 

the wing upper skin surface and the 

engine mount beam support straps. We 

are proposing this AD to detect and 

correct corrosion on the engine mount 

beam support straps and the upper wing 

skins, which could result in failure of 

the engine mount beam support straps. 

This failure could lead to loss of the 

engine and possible loss of control of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by October 13, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

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. 

For service information identified in 

this proposed AD, contact Twin 

Commander Aircraft, LLC, 19010 59th 

Drive, NE., Arlington, WA 98223, 

telephone: (360) 435–9797; fax: (360) 

435–1112; Internet: 

www.twincommander.com. 

FOR FURTHER INFORMATION CONTACT: 

Vince Massey, Aerospace Engineer, 

FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone: 

(425) 917–6475; fax: (425) 917–6590; 

e-mail: vince.massey@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposed AD. Send your 

comments to an address listed under the 

ADDRESSES section. Include the docket 

number, ‘‘FAA–2009–0778; Directorate 

Identifier 2009–CE–040–AD’’ at the 

beginning 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:// 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules 44309 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

concerning this proposed AD. 

Discussion 

We have received a report that 

corrosion was found between the mating 

surfaces of the wing upper skin surface 

and the engine mount beam support 

straps. These straps carry engine loads 

from the support beams into the upper 

wing skins and wing internal support 

structure. Severe corrosion of the straps 

can lead to inability to carry engine 

loads. 

This condition, if not corrected, could 

result in failure of the engine mount 

beam support straps. This failure could 

lead to loss of the engine and possible 

loss of control of the airplane. 

Relevant Service Information 

We have reviewed Twin Commander 

Aircraft LLC Alert Service Bulletin No. 

237, dated May 13, 2005. The service 

information describes procedures for 

inspecting the surface of the LH and RH 

upper wing skins and the engine mount 

beam support straps for any signs of 

corrosion, replacing the upper steel 

straps with parts of improved design, 

and modifying both wings. 

We have reviewed Twin Commander 

Aircraft Corporation Custom Kit No. 

150, dated July 8, 1994. The service 

information describes procedures for 

installing inspection access holes in the 

LH and RH upper wing skins. 

We have reviewed Gulfstream 

American Corporation Service Bulletin 

No. 182, dated March 2, 1981. The 

service information describes 

procedures for installing additional 

wing fasteners on the LH and RH wing. 

FAA’s Determination and Requirements 

of the Proposed AD 

We are proposing this AD because we 

evaluated all information and 

determined the unsafe condition 

described previously is likely to exist or 

develop on other products of the same 

type design. This proposed AD would 

require you to inspect between the 

surface of the LH and RH upper wing 

skins and the engine mount beam 

support straps for any signs of 

corrosion, replace the upper steel straps 

with parts of improved design, and 

modify both wings. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 275 airplanes in the U.S. 

registry. 

We estimate the following costs to do 

the proposed inspection: 

Labor cost Parts cost Total cost 

per airplane 

Total cost on 

U.S. operators 

80 work-hours × $80 per hour = $6,400 ...................................................... Not applicable ................................... $6,400 $1,760,000 

We estimate the following costs to do 

any necessary repairs/replacements that 

would be required based on the results 

of the proposed inspection. We have no 

way of determining the number of 

airplanes that may need this repair/ 

replacement: 

SHORT MODIFICATION—OPTION A* 

Labor cost Parts cost 

Total cost 

per airplane 

per side 

250 work-hours × $80 per hour = $20,000 per side ...................................................... $9,170 per kit per side ............................... $29,170 

MIDDLE MODIFICATION—OPTION B* 

Labor cost Parts cost 

Total cost 

per airplane 

per side 

280 work-hours × $80 per hour = $22,400 per side ...................................................... $9,170 per kit per side ............................... $31,570 

LONG MODIFICATION—OPTION C* 

Labor cost Parts cost 

Total cost 

per airplane 

per side 

320 work-hours × $80 per hour = $25,600 per side ...................................................... $9,170 per kit per side ............................... $34,770 

Note: *Depending on airplane 

configuration, airplanes with rectangular 

plates would need the Plate and Hardware 

Kit (SB237–4) at $2,090 per side. Labor to 

install this kit is included in Options A, B, 

and C. 

STRAP ONLY REPLACEMENT—OPTION D 

Labor cost Parts cost 

Total cost 

per airplane 

per side 

75 work-hours × $80 per hour = $6,000 per side .......................................................... $6,190 per strap per side ........................... $12,190 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
44310 Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules 

We estimate the following costs to do 

the proposed installation of access 

holes: 

Labor cost Parts cost Total cost 

per airplane 

Total cost on 

U.S. operators 

30 work-hours × $80 per hour = $2,400 ............................................................................................. $1,293 $3,693 $1,015,575 

We estimate the following costs to do 

the proposed wing fastener 

modification: 

Labor cost Parts cost Total cost 

per airplane 

Total cost on 

U.S. operators 

8.5 work-hours × $80 per hour = $680 ............................................................................................... $250 $930 $255,750 

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 regulation: 

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. 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 proposed AD and placed it in the 

AD docket. 

Examining the AD Docket 

You may examine the AD docket that 

contains the proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA 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 adding 

the following new AD: 

Twin Commander Aircraft Corporation: 

Docket No. FAA–2009–0778; Directorate 

Identifier 2009–CE–040–AD. 

Comments Due Date 

(a) We must receive comments on this 

airworthiness directive (AD) action by 

October 13, 2009. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

airplane models and serial numbers that are 

certificated in any category: 

Models Serial Nos. (S/Ns) 

690 ..................... All S/Ns. 

690A ................... All S/N except 11195 and 

11279. 

690B ................... All S/Ns except 11361, 

11383, 11527, and 

11536. 

Unsafe Condition 

(d) This AD results from reports that 

corrosion was found between the mating 

surfaces of the wing upper skin surface and 

the engine mount beam support straps. We 

are issuing this AD to detect and correct 

corrosion on the engine mount beam support 

straps and upper wing skins, which could 

result in failure of the engine mount beam 

support straps. This failure could lead to loss 

of the engine and possible loss of control of 

the airplane. 

Compliance 

(e) To address this problem, you must do 

the following, unless already done: 


jlentini on DSKJ8SOYB1PROD with PROPOSALS
Federal Register / Vol. 74, No. 166 / Friday, August 28, 2009 / Proposed Rules 44311 

Actions Compliance Procedures 

(1) Inspect between the surface of the left-hand 

(LH) and right-hand (RH) upper wing skins 

and the engine mount beam support straps 

for any signs of corrosion and determine the 

extent of any corrosion found.

Within the next 150 hours time-in-service after 

the effective date of this AD or within the 

next 12 months after the effective date of 

this AD, whichever occurs first.

Follow Twin Commander Aircraft LLC Alert 

Service Bulletin No. 237, dated May 13, 

2005, pages 1 through 14. 

(2) Install modification access holes in the LH 

and RH lower wing skins.

Before further flight after the inspection required in paragraph (e)(1) of this AD.Follow the Accomplishment Instructions, steps 

1 through 4 and 6 through 9, of Twin Commander Aircraft Corporation Custom Kit No. 

150, dated July 8, 1994, as specified in 

Twin Commander Aircraft LLC Alert Service 

Bulletin No. 237, dated May 13, 2005. 

(3) If corrosion damage is found during the inspection required in paragraph (e)(1) of this 

AD, perform necessary modification.

Before further flight after the inspection required in paragraph (e)(1) of this AD.Follow Twin Commander Aircraft LLC Alert 

Service Bulletin No. 237, dated May 13, 

2005, Part II, Options A, B, or C, on pages 

15 through 29, and 31. 

(4) If corrosion damage is not found during the 

inspection required in paragraph (e)(1) of this 

AD, do the upper steel strap replacements.

Before further flight after the inspection required in paragraph (e)(1) of this AD.Follow Twin Commander Aircraft LLC Alert 

Service Bulletin No. 237, dated May 13, 

2005, Part II, Option D, on pages 30 and 

31. 

(5) Install additional wing fasteners on the LH 

and RH wing.

Before further flight after the inspection required in paragraph (e)(1) of the AD.Follow Gulfstream American Corporation 

Service Bulletin No. 182, dated March 2, 

1981. 

Note: Although not required by this AD, 

we highly recommend compliance with Twin 

Commander Aircraft Corporation Service 

Bulletin No. 217, Revision No. 1, dated May 

26, 1993, Engine Nacelle Firewall 

Reinforcement; and Twin Commander 

Aircraft LLC Alert Service Bulletin No. 239, 

dated February 13, 2006, Outboard Flap— 

Inboard Hinge Inspection & Reinforcement. 

Alternative Methods of Compliance 

(AMOCs) 

(f) The Manager, Seattle 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: Vince 

Massey, Aerospace Engineer, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone: (425) 

917–6475; fax: (425) 917–6590; e-mail: 

vince.massey@faa.gov. 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 Office (FSDO), or lacking 

a PI, your local FSDO. 

Related Information 

(g) To get copies of the service information 

referenced in this AD, contact Twin 

Commander Aircraft, LLC, 19010 59th Drive, 

NE., Arlington, WA 98223, telephone: (360) 

435–9797; fax: (360) 435–1112; Internet: 

www.twincommander.com. To view the AD 

docket, go to U.S. Department of 

Transportation, Docket Operations, M–30, 

West Building Ground Floor, Room W12– 

140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, or on the Internet at 

http://www.regulations.gov. 

Issued in Kansas City, Missouri, on August 

21, 2009. 

Kim Smith, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. E9–20789 Filed 8–27–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0797; Directorate 

Identifier 2009–CE–032–AD] 

RIN 2120–AA64 

Airworthiness Directives; Hawker 

Beechcraft Corporation Models 58, 

58A, 58P, 58PA, 58TC, 58TCA, 95–B55, 

95–B55A, A36, A36TC, B36TC, E55, 

E55A, F33A, and V35B Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 91–18–19, 

which applies to certain Hawker 

Beechcraft Corporation (Hawker) (Type 

Certificate Numbers 3A15, 3A16, and 

A23CE formerly held by Raytheon 

Aircraft Company; formerly held by 

Beech Aircraft Corporation) Models 58, 

58A, 58P, 58PA, 58TC, 58TCA, 95–B55, 

95–B55A, A36, A36TC, B36TC, E55, 

E55A, F33A, and V35B airplanes. AD 

91–18–19 currently requires you to do a 

one-time inspection of the pilot and 

copilot shoulder harnesses for an 

incorrect washer and replace any 

incorrect washer with the correct 

washer. Since we issued AD 91–18–19, 

we have found that the applicability of 

AD 91–18–19 was incorrectly stated 

when the Model A36TC airplane was 

omitted from the Applicability section. 

Consequently, this proposed AD would 

retain the actions and the serial number 

(SN) applicability of AD 91–18–19 and 

realign the SN applicability for Models 

A36TC and B36TC airplanes. We are 

proposing this AD to detect and correct 

an incorrect washer installed in the 

pilot and copilot shoulder harnesses. 

This failure could result in a 

malfunctioning shoulder harness. Such 

a failure could lead to occupant injury. 

DATES: We must receive comments on 

this proposed AD by October 27, 2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

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. 

For service information identified in 

this proposed AD, contact Hawker 

Beechcraft Corporation, P.O. Box 85, 

Wichita, Kansas 67201–0085; telephone: 

(800) 429–5372 or (316) 676–3140; 

Internet: http:// 

pubs.hawkerbeechcraft.com. 

FOR FURTHER INFORMATION CONTACT: 

Steve Potter, Aerospace Engineer, ACE– 

118W, Wichita Aircraft Certification 

Office (ACO), 1801 Airport Road, Room 

100, Wichita, Kansas 67209; telephone: 

(316) 946–4124; fax: (316) 946–4107. 

SUPPLEMENTARY INFORMATION: 


jlentini on DSKJ8SOYB1PROD with PROPOSALS