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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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Dassault Aviation F2000 AMM chapter 5–40 

at revision 12. 

Since that [EASA] AD was issued, Dassault 

Aviation have issued F2000 AMM chapter 5– 

40 at revision 17, which introduces new or 

more restrictive maintenance requirements 

and/or airworthiness limitations. 

Dassault Aviation AMM chapter 5–40 

revision 17 contains among other changes the 

following requirements: 

—Inspection and test of horizontal stabilizer 

jackscrew; 

—Operational test of voltage monitoring 

circuits; 

—Upgrade of screwjack of flap actuators from 

the older to the latest -3 version; 

—Revised Time Between Overhaul for 

screwjack of flap actuators -3 version; 

—Revised interval for checking the screw/nut 

play on screwjack of flap actuators -3 

version; 

—Removal of service life limit for screwjack 

of flap actuators; 

—Test of flap asymmetry protection system. 

Compliance with the flap asymmetry test is 

required by DGAC [Direction Ge ́ne ́rale de 

l’Aviation Civile] France AD F–1999–038– 

008(B)R1. F2000 AMM chapter 5–40 at 

revision 17 introduces extended inspection 

interval; 

—Inspection procedures of fuselage and 

wings; 

—Check of overpressure tightness on 

pressurization control regulating valves. 

Compliance with this check is required by 

EASA AD 2008–0072. F2000 AMM chapter 

5–40 at revision 17 introduces extended 

inspection interval. 

The maintenance tasks and airworthiness 

limitations, as specified in the F2000 AMM 

chapter 5–40, have been identified as 

mandatory actions for continued 

airworthiness of the F2000 type design. 

Failure to comply with AMM chapter 5–40 

at revision 17 might constitute an unsafe 

condition. 

* * * * * 

The required action is revising the 

maintenance program to incorporate all 

airworthiness limitations and 

maintenance tasks specified in Chapter 

5–40, Airworthiness Limitations, 

Revision 18, dated July 2012, of Chapter 

5, Maintenance Planning Document, of 

the Dassualt Falcon 2000 Maintenance 

Manual. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Explanation of Change to Applicability 

We have revised the applicability of 

AD 2002–23–19 in this proposed AD to 

clarify that only Dassault Model Falcon 

2000 airplanes are affected by this 

proposed AD and not Model Falcon 

2000EX airplanes. The applicability of 

AD 2002–23–19 states that the AD is 

applicable to Dassault Model Falcon 

2000 series airplanes, which includes 

Model Falcon 2000EX airplanes, but it 

was not the FAA’s intent to include 

Model Falcon 2000EX airplanes in the 

applicability of that AD. 

Change to Existing AD (67 FR 71452, 

December 2, 2002) 

This proposed AD would retain all 

requirements of AD 2002–23–19. Since 

AD 2002–23–19 was issued, the AD 

format has been revised, and certain 

paragraphs have been rearranged. As a 

result, the corresponding paragraph 

identifiers have changed in this 

proposed AD, as listed in the following 

table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in 

AD 2002–23–19, 

Amendment 39–12963 

(67 FR 71452, 

December 2, 2002) 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h)(1) 

paragraph (c) paragraph (h)(2) 

paragraph (d) paragraph (h)(3) 

paragraph (e) paragraph (h)(4) 

paragraph (f) paragraph (i)(1) 

paragraph (g) paragraph (i)(2) 

paragraph (h) paragraph (i)(3) 

Relevant Service Information 

Dassault has issued Chapter 5–40, 

Airworthiness Limitations, Revision 18, 

dated July 2012, of Chapter 5, 

Maintenance Planning Document, of the 

Dassualt Falcon 2000 Maintenance 

Manual. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections). Compliance 

with these actions is required by 14 CFR 

91.403(c). For airplanes that have been 

previously modified, altered, or repaired 

in the areas addressed by this proposed 

AD, the operator may not be able to 

accomplish the actions described in the 

revisions. In this situation, to comply 

with 14 CFR 91.403(c), the operator 

must request approval for an alternative 

method of compliance according to 

paragraph (m) of this proposed AD. The 

request should include a description of 

changes to the required inspections that 

will ensure the continued operational 

safety of the airplane. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 229 products of U.S. 

registry. 

The actions that are required by AD 

2002–23–19, and retained in this 

proposed AD, take about 17 work-hours 

per product, per test/replacement cycle, 

at an average labor rate of $85 per work 

hour. Required parts cost about $21,680 

per product, per replacement cycle. 

Based on these figures, the estimated 

cost of the currently required actions is 

$23,125 per product, per test/ 

replacement cycle. 

We estimate that it would take about 

1 work-hour per product to comply with 

the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$19,465, or $85 per product. 

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 proposed 

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 above, I 

certify this proposed regulation: 


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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; 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 a regulatory 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) 

2002–23–19, Amendment 39–12963 (67 

FR 71452, December 2, 2002), and 

adding the following new AD: 

Dassault Aviation: Docket No. FAA–2013– 

0466; Directorate Identifier 2012–NM– 

156–AD. 

(a) Comments Due Date 

We must receive comments by August 26, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2002–23–19, 

Amendment 39–12963 (67 FR 71452, 

December 2, 2002). Certain requirements of 

this AD terminate certain requirements of AD 

2010–26–05, Amendment 39–16544 (75 FR 

79952). 

(c) Applicability 

This AD applies to Dassault Aviation 

Model FALCON 2000 airplanes, certificated 

in any category, all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Time limits and 

maintenance checks. 

(e) Reason 

This AD was prompted by manufacturer 

revisions to the airplane maintenance manual 

(AMM) that introduces new or more 

restrictive maintenance requirements and 

airworthiness limitations. We are issuing this 

AD to prevent reduced controllability of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Requirement: Repetitive 

Operational Test 

This paragraph restates the requirements of 

paragraph (a) of AD 2002–23–19, 

Amendment 39–12963 (67 FR 71452, 

December 2, 2002), with revised repair 

approval. Within 5 flight cycles after August 

11, 1999 (the effective date of AD 99–14–07, 

Amendment 39–11218 (64 FR 36561, July 7, 

1999)): Perform an operational test of the flap 

asymmetry detection system to ensure that 

the system is functioning correctly, in 

accordance with the procedures specified in 

Dassault Falcon 2000 Airplane Maintenance 

Manual (AMM) 27–502, dated November 

1995. Prior to further flight, repair any 

discrepancy detected, in accordance with a 

method approved by the Manager, 

International Branch, ANM–116, FAA, 

Transport Airplane Directorate; the Direction 

Ge ́ne ́rale de l’Aviation Civile (or its delegated 

agent); or the European Aviation Safety 

Agency (EASA) (or its delegated agent). 

Repeat the operational test thereafter at 

intervals not to exceed 330 flight hours or 7 

months, whichever occurs first, until the 

maintenance program revision required by 

paragraph (j) of this AD is accomplished. 

(h) Retained Requirement: Repetitive 

Replacement 

This paragraph restates the requirements of 

paragraphs (b), (c), (d), and (e) of AD 2002– 

23–19, Amendment 39–12963 (67 FR 71452, 

December 2, 2002), with terminating action. 

(1) Prior to the accumulation of 1,000 total 

flight cycles on the inboard jackscrew located 

on the inboard flap in the inboard position, 

or within 25 flight cycles after August 11, 

1999 (the effective date of AD 99–14–07, 

Amendment 39–11218 (64 FR 36561, July 7, 

1999)), whichever occurs later: Replace each 

jackscrew having part number (P/N) 5318–1 

or 5318–1 Amdt A, which is located on the 

inboard flap in the inboard position, in 

accordance with Dassault Falcon 2000 AMM 

27–510, dated November 1995. The 

replacement jackscrew may be new or may 

have been reconditioned in accordance with 

paragraph (h)(2) of this AD. Repeat the 

replacement of a jackscrew having P/N 5318– 

1 or 5318–1 Amdt A thereafter at intervals 

not to exceed 1,000 flight cycles on the 

jackscrew located on the inboard flap in the 

inboard position, until the maintenance 

program revision required by paragraph (j) of 

this AD is accomplished. 

(2) A jackscrew having P/N 5318–1 and 

located on the inboard flap in the inboard 

position may be replaced by a reconditioned 

jackscrew having P/N 5318–1 Amdt A, 

provided that all of the conditions specified 

in paragraphs (h)(1) and (h)(2) of this AD are 

met. 

(i) The jackscrew has been reconditioned 

and reidentified as P/N 5318–1 Amdt A, in 

accordance with Dassault Service Bulletin 

AVIAC 5318–27–01, dated September 16, 

1999. 

(ii) The jackscrew has been reconditioned 

only one time. 

(3) Prior to the accumulation of 2,200 total 

flight cycles on the middle jackscrew located 

on the inboard flap and in the outboard 

position, or within 25 flight cycles after 

August 11, 1999 (the effective date of AD 99– 

14–07, Amendment 39–11218 (64 FR 36561, 

July 7, 1999)), whichever occurs later: 

Replace each jackscrew having P/N 5318–1 

or 5318–1 Amdt A on the inboard flap and 

in the outboard position, in accordance with 

Dassault Falcon 2000 AMM 27–510, dated 

November 1995. The replacement jackscrew 

may be new or may have been reconditioned 

in accordance with paragraph (h)(4) of this 

AD. Repeat the replacement of a jackscrew 

having P/N 5318–1 or 5318–1 Amdt A 

thereafter at intervals not to exceed 2,200 

flight cycles on the jackscrew located on the 

inboard flap and in the outboard position, 

until the maintenance program revision 

required by paragraph (j) of this AD is 

accomplished. 

(4) A jackscrew having P/N 5318–1 and 

located on the inboard flap and in the 

outboard position may be replaced by a 

reconditioned jackscrew having P/N 5318–1 

Amdt A, provided that all of the conditions 

specified in paragraphs (h)(4)(i) and (h)(4)(ii) 

of this AD are met. 

(i) The jackscrew has been reconditioned 

and reidentified as P/N 5318–1 Amdt A, in 

accordance with Dassault Service Bulletin 

AVIAC 5318–27–01, dated September 16, 

1999. 

(ii) The jackscrew has been reconditioned 

only one time. 

(i) Retained Requirement: Repetitive 

Measurements 

This paragraph restates the requirements of 

paragraphs (f), (g), and (h) of AD 2002–23– 

19, Amendment 39–12963 (67 FR 71452, 

December 2, 2002), with terminating action 

added. 

(1) Prior to the accumulation of 1,000 total 

flight cycles on the outboard jackscrews 

located on the outboard flaps, or within 25 

flight cycles after August 11, 199 (the 

effective date of AD 99–14–07, Amendment 

39–11218 (64 FR 36561, July 7, 1999)), 

whichever occurs later: Measure the screw/ 

nut play of the jackscrews having P/N 1– 

5319–1 or 1–5319–1 Amdt A (on the left 

wing) and P/N 2–5319–1 or 2–5319–1 Amdt 

A (on the right wing) on the outboard flaps, 

in accordance with the procedures specified 

in Dassault Falcon 2000 AMM Temporary 

Revision (TR) 27–504, dated October 1998. 

Repeat the measurement as specified in 

paragraph (i)(1) of this AD until the 

maintenance program revision required by 

paragraph (j) of this AD is accomplished. 

Note 1 to paragraph (i)(1) of this AD: 

Jackscrews having P/N 1–5319–1 or 2–5319– 

1 may be reconditioned in accordance with 

Dassault Service Bulletin AVIAC 5319–27– 

01, dated September 16, 1999. These 

jackscrews may be reconditioned and reused 

more than one time. 

(i) If the initial measurement is equal to or 

less than 0.014 inch: Repeat the measurement 

thereafter at intervals not to exceed 330 flight 


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hours or 7 months, whichever occurs first. If 

any repetitive measurement detects a nut/ 

screw play greater than 0.014 inch, perform 

the actions required by paragraph (i)(1)(ii) of 

this AD. 

(ii) If the initial measurement is greater 

than 0.014 inch: Perform the actions required 

by paragraphs (i)(1)(ii)(A) and (i)(1)(ii)(B) of 

this AD. 

(A) Prior to further flight, replace the 

jackscrew with a new or reconditioned 

jackscrew, in accordance with Dassault 

Falcon 2000 AMM 27–510, dated November 

1995. 

(B) Prior to the accumulation of 1,000 total 

flight cycles on the new or reconditioned 

jackscrew, perform a follow-on measurement 

of the screw/nut play, in accordance with the 

procedures specified in Dassault Falcon 2000 

AMM TR 27–504, dated October 1998. 

(C) If any follow-on measurement required 

by paragraph (i)(1)(ii)(B) of this AD detects a 

nut/screw play equal to or less than 0.014 

inch, perform the actions required by 

paragraph (i)(1) of this AD. If any follow-on 

measurement required by paragraph 

(i)(1)(ii)(B) of this AD detects a nut/screw 

play greater than 0.014 inch, perform the 

actions required by paragraphs (i)(1)(ii)(A) 

and (i)(1)(ii)(B) of this AD. 

(2) Prior to the accumulation of 750 total 

flight cycles on the jackscrew located on the 

inboard flap in the inboard position, or 

within 25 flight cycles after the effective date 

of this AD, whichever occurs later: Measure 

the screw/nut play of the jackscrew having P/ 

N 5318–1 or 1–5318–1 Amdt A, which is 

located on the inboard flap in the inboard 

position, to detect discrepancies, in 

accordance with the procedures specified in 

Dassault Falcon 2000 AMM TR 27–504, 

dated October 1998. If the measurement is 

greater than 0.014 inch, prior to further flight, 

replace the discrepant jackscrew with a new 

or reconditioned jackscrew, in accordance 

with Dassault Falcon 2000 AMM 27–510, 

dated November 1995. 

(3) Prior to the accumulation of 1,000 total 

flight cycles on the jackscrew located on the 

inboard flap in the outboard position, or 

within 25 flight cycles after the effective date 

of this AD, whichever occurs later: Measure 

the screw/nut play of the jackscrew having P/ 

N 5318–1 or 5318–1 Amdt A, which is 

located on the inboard flap in the outboard 

position, in accordance with the procedures 

specified in Dassault Falcon 2000 AMM TR 

27–504, dated October 1998. 

(i) If the initial measurement is equal to or 

less than 0.014 inch: Repeat the 

measurements thereafter at intervals not to 

exceed 330 flight hours or 7 months, 

whichever occurs first. If repetitive 

measurement detects a nut/screw play greater 

than 0.014 inch, perform the actions required 

by paragraph (i)(3)(ii)(B) of this AD. 

(ii) If the initial measurement is greater 

than 0.014 inch: Perform the actions required 

by paragraphs (i)(3)(ii)(A) and (i)(3)(ii)(B) of 

this AD. 

(A) Prior to further flight, replace the 

jackscrew with a new or reconditioned 

jackscrew, in accordance with Dassault 

Falcon 2000 AMM 27–510, dated November 

1995. 

(B) Prior to the accumulation of 1,000 total 

flight cycles on the new or reconditioned 

jackscrew, perform a follow-on measurement 

of the screw/nut play, in accordance with the 

procedures specified in Dassault Falcon 2000 

AMM TR 27–504, dated October 1998. 

(C) If any follow-on measurement required 

by paragraph (i)(3)(ii)(B) of this AD detects a 

nut/screw play equal to or less than 0.014 

inch, perform the actions required by 

paragraph (i)(3)(i) of this AD. If any followon measurement required by paragraph 

(i)(3)(ii)(B) of this AD detects a nut/screw 

play greater than 0.014 inch, perform the 

actions required by paragraphs (i)(3)(ii)(A) 

and (i)(3)(ii)(B) of this AD. 

(j) New Requirement of This AD: Revision of 

the Maintenance Program 

Within 30 days after the effective date of 

this AD, revise the maintenance program to 

incorporate the information specified in 

Chapter 5–40, Airworthiness Limitations, 

Revision 18, dated July 2012, of Chapter 5, 

Maintenance Planning Document, of the 

Dassault Falcon 2000 Maintenance Manual. 

The initial compliance time for the tasks are 

at the applicable times specified in Chapter 

5–40, Airworthiness Limitations, Revision 

18, dated July 2012, of Chapter 5, 

Maintenance Planning Document, of the 

Dassault Falcon 2000 Maintenance Manual, 

or within 30 days after the effective date of 

this AD, whichever occurs later. 

Accomplishing the requirements of this 

paragraph terminates the applicable 

requirements of paragraphs (g), (h), and (i) of 

this AD. Clarification of compliance time 

terminology used in the tables in the service 

information is provided in paragraphs (j)(1) 

through (j)(5) of this AD. 

(1) The term ‘‘landings’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information specified in paragraph (j) 

of this AD means total airplane landings. 

(2) The term ‘‘flight hours’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information specified in paragraph (j) 

of this AD means total flight hours. 

(3) The term ‘‘flight cycles’’ in the ‘‘First 

Inspection’’ column of any table in the 

service information specified in paragraph (j) 

of this AD means total flight cycles. 

(4) For Task 30–11–09–350–801 30–103 

identified in the service information 

specified in paragraph (j) of this AD, the 

initial compliance time is prior to the 

accumulation of 2,400 total flight hours or 

2,000 total flight cycles, or within 2,400 flight 

hours or 2,000 flight cycles after the effective 

date of this AD, whichever occurs first; or 

within 30 days after the effective date of this 

AD; whichever occurs later. 

(5) For Task 52–20–00–610–801–01 52–205 

identified in the service information 

specified in paragraph (j) of this AD, the 

initial compliance time is 24 months after the 

effective date of this AD. 

(6) The limited service life of part number 

F2MA721512100 is 3,750 total flight cycles 

on the part or 6 years since the 

manufacturing date of the part, whichever 

occurs first. 

(k) Terminating Action for a Certain AD 

Accomplishment of the actions required by 

paragraph (j) of this AD terminates the 

requirements of paragraph (g) of AD 2010– 

26–05, Amendment 39–16544 (75 FR 79952, 

December 21, 2010), for all Dassault Aviation 

Model FALCON 2000 airplanes. 

(l) No Alternative Actions or Intervals 

After accomplishing the revision required 

by paragraph (j) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an alternative method of 

compliance in accordance with the 

procedures specified in paragraph (m)(1) of 

this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone 425–227–1137; fax 425–227– 

1137. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(n) Related Information 

(1) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2012– 

0156, dated August 23, 2012; and Chapter 5– 

40, Airworthiness Limitations, Revision 18, 

dated July 2012, of Chapter 5, Maintenance 

Planning Document, of the Dassualt Falcon 

2000 Maintenance Manual; for related 

information. 

(2) For service information identified in 

this 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. 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS
41886 Federal Register / Vol. 78, No. 134 / Friday, July 12, 2013 / Proposed Rules 

Issued in Renton, Washington, on June 14, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15952 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–2013–0603; Directorate 

Identifier 2009–SW–079–AD] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

serial-numbered Bell Helicopter Textron 

Canada Limited (BHTC) Model 206L, 

206L–1, 206L–3, and 206L–4 helicopters 

with a certain tailboom upper left 

attachment fitting (fitting). This 

proposed AD would require inspecting 

the fitting for a crack and other 

conditions. This proposed AD is 

prompted by the manufacturer revising 

and extending the 100 hour time-inservice (TIS) inspection requirements 

for the fitting. The proposed actions are 

intended to detect a crack, loose rivet, 

corrosion, or any other damage, which 

could lead to loss 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 Limited, 

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 the referenced 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, Aerospace Engineer, 

FAA, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5110; 

email: sharon.y.miles@faa.gov. 

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 

Transport Canada (TC), which is the 

aviation authority for Canada, has 

issued AD No. CF–2009–41, dated 

November 16, 2009 (AD CF–2009–41), 

to correct an unsafe condition for BHTC 

Model 206L series helicopters, 

specifically: Model 206L, serial number 

(S/N) 45004 through 45153, and 46601 

through 46617; Model 206L–1, S/N 

45154 through 45790; Model 206L–3, S/ 

N 51001 through 51612; and Model 

206L–4, all S/Ns. TC AD No. CF–2009– 

41 was prompted by a new 

airworthiness limitation for the fitting 

that requires an inspection of fitting part 

number 203–032–409–001 at each 100- 

hour or annual inspection. The TC AD 

requires inspecting the fitting, and 

replacing or repairing it if necessary, in 

accordance with the Accomplishment 

Instructions of BHTC Alert Service 

Bulletin (ASB) 206L–09–158, Revision 

A, dated August 31, 2009 (ASB 206L– 

09–158 Revision A). TC further states 

that incorporating this inspection into 

the applicable maintenance manual 

revision constitutes terminating action 

to TC AD No. CF–2009–41. The actions 

in TC AD No. CF–2009–41 are intended 

to detect a crack in a tailboom 

attachment fitting, which could result in 

loss of the tailboom and subsequent loss 

of control of the helicopter. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Canada and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Canada, TC, its 

technical representative, has notified us 

of the unsafe condition described in its 

AD. 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 products of the same 

type design. 

Related Service Information 

We reviewed ASB 206L–09–158 

Revision A for certain serial-numbered 

Model 206L, L–1, L–3, and L–4 

helicopters with certain tailboom 

assemblies installed. That ASB requires 

an inspection of the fitting for a crack, 

loose rivets, corrosion, and damage at 

each 100-hour or annual inspection. If 

there is a crack, the ASB specifies 

replacing the fitting with an airworthy 

fitting. If there is a loose rivet, the ASB 

specifies replacing the rivet with an 

airworthy rivet. If the fitting has 

corrosion or mechanical damage, the 

ASB specifies determining if the 

corrosion or mechanical damage is 

within acceptable limits. If the corrosion 


wreier-aviles on DSK5TPTVN1PROD with PROPOSALS