Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules 41877 

the date provided at the beginning of 

this notice. After the close of the 

comment period, DOE will review the 

comments received and determine 

whether computers are a covered 

product under EPCA. 

Comments, data, and information 

submitted to DOE’s email address for 

this proposed determination should be 

provided in WordPerfect, Microsoft 

Word, PDF, or text (ASCII) file format. 

Submissions should avoid the use of 

special characters or any form of 

encryption, and wherever possible 

comments should include the electronic 

signature of the author. No 

telefacsimiles (faxes) will be accepted. 

According to 10 CFR 1004.11, any 

person submitting information that he 

or she believes to be confidential and 

exempt by law from public disclosure 

should submit two copies: one copy of 

the document should have all the 

information believed to be confidential 

deleted. DOE will make its own 

determination as to the confidential 

status of the information and treat it 

according to its determination. 

Factors of interest to DOE when 

evaluating requests to treat submitted 

information as confidential include (1) 

A description of the items; (2) whether 

and why such items are customarily 

treated as confidential within the 

industry; (3) whether the information is 

generally known or available from 

public sources; (4) whether the 

information has previously been made 

available to others without obligations 

concerning its confidentiality; (5) an 

explanation of the competitive injury to 

the submitting persons which would 

result from public disclosure; (6) a date 

after which such information might no 

longer be considered confidential; and 

(7) why disclosure of the information 

would be contrary to the public interest. 

B. Issues on Which DOE Seeks 

Comments 

DOE welcomes comments on all 

aspects of this proposed determination. 

DOE is particularly interested in 

receiving comments from interested 

parties on the following issues related to 

the proposed determination for 

computers: 

• Definition(s) of computers; 

• Whether classifying computers as a 

covered product is necessary or 

appropriate to carry out the purposes of 

EPCA; 

• Calculations and values for average 

household energy consumption; and 

• Availability or lack of availability of 

technologies for improving energy 

efficiency of computers. 

The Department is interested in 

receiving views concerning other 

relevant issues that participants believe 

would affect DOE’s ability to establish 

test procedures and energy conservation 

standards for computers. The 

Department invites all interested parties 

to submit in writing by August 12, 2013, 

comments and information on matters 

addressed in this notice and on other 

matters relevant to consideration of a 

determination for computers. 

After the expiration of the period for 

submitting written statements, the 

Department will consider all comments 

and additional information that is 

obtained from interested parties or 

through further analyses, and it will 

prepare a final determination. If DOE 

determines that computers qualify as a 

covered product, DOE will consider a 

test procedure and energy conservation 

standards for computers. Members of 

the public will be given an opportunity 

to submit written and oral comments on 

any proposed test procedure and 

standards. 

List of Subjects in 10 CFR part 430 

Administrative practice and 

procedure, Confidential business 

information, Energy conservation, 

Reporting and recordkeeping 

requirements. 

Issued in Washington, DC, on July 5, 2013. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2013–16728 Filed 7–11–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0574; Directorate 

Identifier 2008–SW–22–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) for 

the Bell Model 407 helicopters. The 

existing AD currently requires preflight 

checking and repetitively inspecting for 

a crack in certain tailbooms that have 

been redesigned, replacing the tailboom 

if there is a crack, modifying and reidentifying certain tailbooms, installing 

an improved horizontal stabilizer 

assembly, and assigning a 5,000 hour 

time-in-service (TIS) limit. Since we 

issued that AD, we have received 

several additional reports of cracked 

tailboom skins. This proposed AD 

would retain the existing requirements 

and apply additional inspection 

requirements. The proposed actions are 

intended to prevent separation of the 

tailboom and subsequent loss of control 

of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 10, 

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 proposed 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 service information identified in 

this proposed AD, contact Bell 

Helicopter Textron Canada, 12,800 Rue 

de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363– 

8023, fax (450) 433–0272 or at http:// 

www.bellcustomer.com/files/. You may 

review service information at the FAA, 

Office of the Regional Counsel, 

Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 

76137. 

FOR FURTHER INFORMATION CONTACT: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5110, fax 

(817) 222–5961, email 

sharon.y.miles@faa.gov. 


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SUPPLEMENTARY INFORMATION: 

Comments Invited 

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 might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, 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 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 proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On March 21, 2000, we issued AD 

2000–06–10, Amendment 39–11651 (65 

FR 16804, March 30, 2000), to require 

preflight checking and repetitively 

inspecting the tailboom for a crack and 

replacing the tailboom if a crack was 

found. On March 3, 2003, we issued AD 

2003–05–03, Amendment 39–13079 (68 

FR 11967, March 13, 2003), which 

superseded AD 2000–06–10. AD 2003– 

05–03 requires prelight checks and 

repetitive inspections, modifying and 

reidentifying certain tailbooms, 

installing an improved horizontal 

stabilizer assembly, and assigning a 

5,000-hour TIS life limit to certain 

tailbooms. AD 2003–05–03 was 

intended to prevent separation of the 

tailboom and subsequent loss of control 

of the helicopter. 

Actions Since Existing AD Was Issued 

Since we issued AD 2003–05–03, 

Transport Canada, which is the aviation 

authority for Canada, has issued 

Canadian AD No. CF–2008–04, dated 

January 11, 2008 (AD CF–2008–04), 

based on several reports of cracks to the 

tailboom skin on the left side in the area 

of horizontal stabilizer found by visual 

inspection. AD CF–2008–04 mandates 

new inspection requirements based on 

the manufacturer’s service information 

discussed in the ‘‘Related Service 

Information’’ section of this NPRM. 

FAA’s Determination 

This helicopter model has been 

approved by the aviation authority of 

Canada and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement, Transport Canada 

has kept the FAA informed of the 

situation described above. We are 

proposing this AD because we evaluated 

all known relevant information and 

determined that an unsafe condition is 

likely to exist or develop on other 

helicopters of these same type designs. 

Related Service Information 

We reviewed Bell Alert Service 

Bulletin (ASB) No. 407–07–80 and ASB 

No. 407–01–48, Revision C, both dated 

August 27, 2007. In ASB No. 407–07– 

80, Bell states they have received 

additional reports of cracked tailboom 

skins, part number (P/N) 407–030–801– 

157, affecting tailboom assemblies, P/N 

407–530–014–101 and –103 (modified 

per AD 2003–05–03, reference ASB 

407–01–48, Revision B, dated April 25, 

2002), and original production tailboom 

assembly, P/N 407–030–801–107. Each 

report indicated a crack above the left 

side upper stabilizer attachment support 

at Station 98.89. Further investigation 

conducted by Bell revealed other areas 

of the tailbooms require additional 

attention. Thus, ASB 407–07–080 

contains procedures for preparing the 

tailboom for repetitive inspection, 

preflight checking the tailboom, and 

repetitively inspecting the tailboom. 

Bell specifies that replacing the affected 

tailboom assembly, P/N 407–530–014– 

101, –103 or 407–030–801–107, with 

tailboom assembly, P/N 407–030–801– 

201, –203, –205, or later dash numbers 

is terminating action for Bell ASB No. 

407–07–80. 

In ASB 407–01–48, Bell states that 

since issuing ASB 407–99–26, Revision 

C, dated February 28, 2002, they have 

received additional reports of cracks in 

the upper skins, which originated from 

holes where the fasteners are installed at 

the forward and aft section of the left 

upper stabilizer support, P/N 407–023– 

800–117. ASB 407–01–48 contains 

procedures for inspecting the tailboom 

on the left side where the fasteners are 

installed, installing an improved 

horizontal stabilizer assembly and reidentifying the tailboom, and assigning 

a 5,000-hour TIS life limit to the 

tailboom. 

Proposed AD Requirements 

This proposed AD addresses certain 

part-numbered tailbooms that were 

modified and reidentified as one new P/ 

N. These same P/Ns are addressed by 

new inspection requirements. This 

proposed AD retains the requirements of 

the superseded AD for certain partnumbered tailbooms and establishes 

new requirements for certain other P/ 

Ns, by requiring compliance with 

portions of the Bell ASBs as follows: 

• For tailboom, P/Ns 407–030–801– 

101 and –105, which have not been 

modified, conduct daily preflight checks 

of the tailboom for a crack and 

repetitively inspect the tailboom for a 

crack. Within 600 hours TIS or 30 days, 

modify and re-identify these partnumbered tailbooms as P/N 407–530– 

014–101 or 407–530–014–103, and 

install an improved horizontal stabilizer 

assembly. 

• For P/Ns 407–530–014–101 and 

–103 and P/N 407–030–801–107, revise 

the Airworthiness Limitations section of 

the maintenance manual by establishing 

a retirement life of 5,000 hours TIS, 

prepare the tailboom for daily visual 

checks and inspections, and inspect the 

tailboom for a crack. Thereafter, visually 

check the tailboom for a crack before the 

first flight of each day and repetitively 

inspect the tailboom for a crack every 

100 hours TIS. 

• For all P/Ns, if there is a crack, 

before further flight, replace the 

tailboom. If there is no crack, ensure 

both surfaces are dry and protect each 

reworked area with a thin coat of clear 

coating. 

• An owner/operator (pilot) may 

perform the daily visual checks required 

by this proposed AD because these 

checks require no special tools and can 

be performed equally well by a pilot or 

a mechanic. This authorization is an 

exception to our standard maintenance 

regulations. 

Differences Between This Proposed AD 

and the Transport Canada AD 

This AD would not require you to 

contact the manufacturer. This AD does 

not state that replacing the affected 

tailboom with tailboom, P/N 407–030– 

801–201, –203, –205, or later numbers 

constitutes terminating action because 

installing other part-numbered 

tailbooms than those listed in the 

applicability of this AD may also result 

in terminating action for the 

requirements of this AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 464 helicopters of 

U.S. registry. We estimate that operators 

would incur the following costs in order 

to comply with this AD. We estimate the 

time for conducting pilot checks is 

minimal and thus we are assuming there 

is no cost. It would take about .5 workVerDate Mar<15>2010 14:58 Jul 11, 2013 Jkt 229001 PO 00000 Frm 00022 Fmt 4702 Sfmt 4702 E:\FR\FM\12JYP1.SGM 12JYP1

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hour to perform the annotations in the 

helicopter records, 1.5 work hours to 

prepare the inspection area and do the 

magnification inspection, and 2.5 work 

hours to do the repetitive 100-hour TIS 

inspections at an average labor rate of 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators would 

be $1,445 per helicopter and $670,480 

for the U.S. operator fleet to do the 

checks and inspections, based on 6 

repetitive inspections the first year. The 

previous AD affected 284 helicopters, 

and we estimated 3.5 work hours to do 

the initial inspection, 1.5 work hours to 

do the recurring inspections, and 18 

work hours to do the modification at an 

average labor rate of $60 per work hour. 

Required parts were estimated at $1,244 

per helicopter. Based on these figures, 

the total cost of the AD on U.S. 

operators was estimated to be $3,254 per 

helicopter or $924,136, based on 8 

repetitive inspections per year. 

According to Bell, the cost of a new 

tailboom is $82,850. Per Bell ASB 407– 

07–80, the costs to replace the tailboom 

may be covered under warranty, thereby 

reducing the cost impact on affected 

individuals. We do not control warranty 

coverage by Bell. We have included all 

costs in our cost estimate. 

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 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, I certify 

this 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); 

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 proposed 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. 

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 

removing Airworthiness Directive (AD) 

2003–05–03 (68 FR 11967, March 13, 

2003) and by adding the following new 

AD: 

Bell Helicopter Textron Canada: Docket No. 

FAA–2013–0574; Directorate Identifier 

2008–SW–22–AD. 

(a) Applicability 

This AD applies to Model 407 helicopters, 

serial numbers 53000 through 53475, with 

tailboom, part number (P/N) 407–030–801– 

101, –105, or –107, or 407–530–014–101 or 

–103, installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

cracks in the tailboom skin on the left side 

in the area of horizontal stabilizer, which 

could result in separation of the tailboom and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 2003–05–03, 

Amendment 39–13079 (68 FR 11967, March 

13, 2003), which superseded AD 2000–06– 

10, Amendment 39–11651 (65 FR 16804, 

March 30, 2000). 

(d) Comments Due Date 

We must receive comments by September 

10, 2013. 

(e) 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. 

(f) Required Actions 

(1) For tailboom, P/Ns 407–030–801–101 

and –105: 

(i) Unmodified per Bell Alert Service 

Bulletin (ASB) 407–01–48, Revision C, dated 

August 27, 2007 (ASB 407–01–48): 

(A) Before the first flight of each day, 

visually check the tailboom for a crack, as 

depicted in Figure 1 to paragraph (f)(1)(i)(A) 

of this AD. 

BILLING CODE 4910–13–P 


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BILLING CODE 4910–13–C 

(B) For a tailboom with 600 or more hours 

time-in-service (TIS), within 25 hours TIS 

and thereafter at intervals not to exceed 50 

hours TIS, visually inspect the tailboom for 

a crack using a 10X or higher magnifying 

glass by following the Accomplishment 

Instructions, Part II, of Bell ASB 407–99–26, 

Revision C, dated February 28, 2002, except 

this AD does not require you to contact Bell. 

(ii) Within 600 hours TIS, but not later 

than 30 days: 

(A) Modify and re-identify each tailboom, 

P/N 407–030–801–101 as 407–530–014–101, 

and P/N 407–030–801–105 as 407–530–014– 

103, by following the Accomplishment 

Instructions, Parts I and III, of ASB 407–01– 

48. 

(B) Install improved horizontal stabilizer 

assembly, P/N 407–023–800–ALL, by 

following Bell Technical Bulletin No. 407– 

01–33, dated August 29, 2001, except this AD 

does not require you to contact Bell. 

(2) For tailboom, P/Ns 407–530–014–101 

and –103, and P/N 407–030–801–107: 

(i) Before further flight after the tailboom 

is modified and re-identified, revise the 

Airworthiness Limitations section of the 

maintenance manual by establishing a 

retirement life of 5,000 hours TIS. Create a 

component history card or equivalent record 

and assign a life limit of 5,000 hours TIS by 


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following the Accomplishment Instructions, 

Part IV, of ASB 407–01–48. 

(ii) Within 25 hours TIS or 30 days, 

whichever occurs first, prepare the tailboom 

for daily visual checks and recurring 

inspections and inspect the tailboom for a 

crack by following the Accomplishment 

Instructions, Part II, Steps 1.a) through 1.f), 

of Bell ASB 407–07–80, dated August 27, 

2007 (ASB 407–07–80). 

(iii) Thereafter, before the first flight of 

each day, clean the area on the tailboom 

where paint has been removed and visually 

check the tailboom for a crack as depicted in 

Figure 2 to Paragraph (f)(2)(iii) of this AD. 

BILLING CODE 4910–13–P 

BILLING CODE 4910–13–C 

(iv) Within 100 hours TIS and thereafter at 

intervals not to exceed 100 hours TIS, using 

a 10× or higher power magnifying glass, 

inspect each tailboom for a loose rivet, a 

crack, skin corrosion, or any other damage, 

by following the Accomplishment 

Instructions, Part IV, Steps 1 through 6, of 

ASB 407–07–80, except this AD does not 

require you to contact Bell. If there is 

corrosion within an allowable tolerance, 

repair each area of corrosion. 

(3) If there is a crack, before further flight, 

replace the tailboom. 

(4) If there is no crack, make sure both of 

the inspection area surfaces are dry and 

protect each reworked area with a thin coat 

of clear coating. 


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(5) The actions required by paragraphs 

(f)(1)(i)(A) and (f)(2)(iii) of this AD may be 

performed by the owner/operator (pilot) 

holding at least a private pilot certificate and 

must be entered into the aircraft records 

showing compliance with this AD in 

accordance with 14 CFR 43.9 (a)(1)–(4) and 

91.417(a)(2)(v). This record must be 

maintained as required by 14 CFR 91.417, 

121.380, or 135.439. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

(2) For operations conducted under a 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) Additional Information 

The subject of this AD is addressed in 

Transport Canada Civil Aviation (TCCA) AD 

No. CF–2008–04, dated January 11, 2008. 

You may view the TCCA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2013–0574. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code is 5300: Rotorcraft Tail Boom, and 

5302: Middle Section. 

Issued in Fort Worth, Texas, on June 12, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–16727 Filed 7–11–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0466; Directorate 

Identifier 2012–NM–156–AD] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2002–23– 

19, which applies to all Dassault 

Aviation Model Falcon 2000 series 

airplanes. That AD currently requires 

repetitive operational tests, repetitive 

measurements, and repetitive 

replacement of certain jackscrews. Since 

we issued that AD, the manufacturer 

revised the airplane maintenance 

manual (AMM) maintenance 

requirements and airworthiness 

limitations. This proposed AD would 

require revising the maintenance 

program to incorporate new or revised 

maintenance requirements and 

airworthiness limitations. We are 

proposing this AD to prevent reduced 

controllability of the airplane. 

DATES: We must receive comments on 

this proposed AD by August 26, 2013. 

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, 

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, between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. 

For service information identified in 

this proposed AD, contact Dassault 

Falcon Jet, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http:// 

www.dassaultfalcon.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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 in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

227–1137; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0466; Directorate Identifier 

2012–NM–156–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on 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 

about this proposed AD. 

Discussion 

On November 19, 2002, we issued AD 

2002–23–19, Amendment 39–12963 (67 

FR 71452, December 2, 2002), for all 

Dassault Aviation Model Falcon 2000 

airplanes. (That AD superseded AD 99– 

14–07, Amendment 39–11218 (64 FR 

36561, July 7, 1999)). AD 2002–23–19 

requires repetitive operational tests of 

the flap asymmetry detection system, 

repetitive replacement of the inboard 

flap jackscrews, and repetitive 

measurement of the screw/nut play of 

the jackscrews on the inboard and 

outboard flaps. 

Since we issued AD 2002–23–19, we 

have determined that existing 

maintenance requirements and 

airworthiness limitations are inadequate 

and additional inspections are necessary 

to address the identified unsafe 

condition. The European Aviation 

Safety Agency (EASA), which is the 

Technical Agent for the Member States 

of the European Community, has issued 

EASA Airworthiness Directive 2012– 

0156, dated August 23, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

The airworthiness limitations and 

maintenance requirements for the Falcon 

2000 type design are included in Dassault 

Aviation Falcon 2000 (F2000) Aircraft 

Maintenance Manual (AMM) chapter 5–40 

and are approved by the European Aviation 

Safety Agency (EASA). EASA issued AD 

2008–0221 to require accomplishment of the 

maintenance tasks, and implementation of 

the airworthiness limitations, as specified in 


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