Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28465 

Note 2: Guidance on revising Chapter 5 of 

the BAE SYSTEMS (Operations) Limited 

BAe146 Series/Avro146–RJ Series AMM, 

Revision 97, dated July 15, 2009, can be 

found in the applicable sub-chapters listed in 

Table 1 of this AD. 

TABLE 1—APPLICABLE AMM SUBCHAPTERS

AMM Subchapter Subject 

05–10–01 ....... Airframe Airworthiness Limitations before Life Extension Programme. 

05–10–05 1 ..... Airframe Airworthiness Limitations, Life Extension 

Programme Landings Life 

Extended. 

05–10–10 2 ..... Airframe Airworthiness Limitations, Life Extension 

Programme Calendar Life 

Extended. 

05–10–15 ....... Aircraft Equipment Airworthiness Limitations. 

05–10–17 ....... Power Plant Airworthiness 

Limitations. 

05–15–00 ....... Critical Design Configuration 

Control Limitations 

(CDCCL)—Fuel System 

Description and Operation. 

05–20–00 3 ..... Scheduled Maintenance. 

05–20–01 ....... Airframe Scheduled Maintenance—Before Life Extension Programme. 

05–20–05 1 ..... Airframe Scheduled Maintenance—Life Extension 

Programme Landings Life 

Extended. 

05–20–10 2 ..... Airframe Scheduled Maintenance—Life Extension 

Programme Calendar Life 

Extended. 

05–20–15 ....... Aircraft Equipment Scheduled Maintenance. 

1Applicable only to airplanes post-modification HCM20011A or HCM20012A or 

HCM20013A. 2Applicable only to airplanes post-modification HCM20010A. 3Paragraphs 5 and 6 only, on the Corrosion 

Prevention and Control Program (CPCP) and 

the Supplemental Structural Inspection Document (SSID). 

Note 3: Sub-chapter 05–15–00 of the BAE 

SYSTEMS (Operations) Limited BAe146 

Series/Avro146–RJ Series AMM, is the 

CDCCL. 

Note 4: Within Sub-chapter 05–20–00 of 

the BAE SYSTEMS (Operations) Limited 

BAe146 Series/Avro146–RJ Series AMM, the 

relevant issues of the support documents are 

as follows: BAE SYSTEMS (Operations) 

Limited BAe 146 Series/Avro 146–RJ 

Corrosion Prevention and Control Program 

Document CPCP–146–01, Revision 3, dated 

July 15, 2008, including BAE SYSTEMS 

(Operations) Limited Temporary Revision 

(TR) 2.1, dated December 2008; and BAE 

SYSTEMS (Operations) Limited BAe146 

Series Supplemental Structural Inspection 

Document SSID–146–01, Revision 1, dated 

June 15, 2009. 

Note 5: Within Sub-chapter 05–20–01 of 

the BAE SYSTEMS (Operations) Limited 

BAe146 Series/Avro146–RJ Series AMM, the 

relevant issue of BAE SYSTEMS (Operations) 

Limited BAe 146/Avro 146–RJ Maintenance 

Review Board Report Document MRB 146– 

01, Issue 2, is Revision 15, dated March 2009 

(mis-identified in EASA AD 2009–0215, 

dated October 7, 2009, as being dated May 

2009). 

Note 6: Notwithstanding any other 

maintenance or operational requirements, 

components that have been identified as 

airworthy or installed on the affected 

airplanes before the revision of the ALS, as 

required by paragraph (g) of this AD; or 

before revision of Chapter 5 of the AMM, as 

required by paragraph (h) of this AD; do not 

need to be reworked in accordance with the 

CDCCLs. However, once the ALS or AMM 

has been revised, future maintenance actions 

on these components must be done in 

accordance with the CDCCLs. 

(i) Except as specified in paragraph (k) of 

this AD: After the actions specified in 

paragraph (g) or (h) of this AD have been 

accomplished, no alternative inspections or 

inspection intervals may be approved for the 

structural elements specified in the 

documents listed in paragraph (g) or (h) of 

this AD. 

(j) Modifying the main fittings of the main 

landing gear in accordance with MessierDowty Service Bulletin 146–32–171, dated 

August 11, 2009, extends the safe limit of the 

main landing gear main fitting from 32,000 

landings to 50,000 landings on the main 

fitting. 

Alternative Methods of Compliance 

(AMOCs) 

(k) 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. Send information to 

ATTN: Todd Thompson, Aerospace 

Engineer, International Branch, ANM–116, 

FAA, Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington 

98057–4056; telephone (425) 227–1175; fax 

(425) 227–1149. Before using any approved 

AMOC on any airplane to which the AMOC 

applies, notify your principal maintenance 

inspector (PMI) or principal avionics 

inspector (PAI), as appropriate, or lacking a 

principal inspector, your local Flight 

Standards District Office. The AMOC 

approval letter must specifically reference 

this AD. 

Related Information 

(l) EASA Airworthiness Directive 2009– 

0215, dated October 7, 2009; and MessierDowty Service Bulletin 146–32–171, dated 

August 11, 2009; also address the subject of 

this AD. 

Material Incorporated by Reference 

(m) If you do the optional modification 

specified in this AD, you must use MessierDowty Service Bulletin 146–32–171, dated 

August 11, 2009, to do those actions, 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 Messier-Dowty service information 

identified in this AD, contact Messier-Dowty 

Limited, Cheltenham Road, Gloucester GL2 

9QH, England; telephone +44(0)1452 712424; 

fax +44(0)1452 713821; Internet https:// 

techpubs.services.messier-dowty.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on May 3, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11356 Filed 5–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0791; Directorate 

Identifier 2008–NM–213–AD; Amendment 

39–16303; AD 2010–10–24] 

RIN 2120–AA64 

Airworthiness Directives; DassaultAviation Model FALCON 2000 and 

FALCON 2000EX Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

originated by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

During the overhaul of a Main Landing 

Gear (MLG) of a Falcon 2000, the sleeve on 

the hydraulic flow restrictor in the shock 

absorber was found displaced, because of the 

rupture of its three retaining screws. * * * 

Failure of the retaining screws has been 

determined to be the final phase of a slow 

unscrewing process under normal 

operational conditions. The unsafe condition 

only exists once the three screws have failed. 

* * * * * 


cprice-sewell on DSK8KYBLC1PROD with RULES
28466 Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 

The unsafe condition is failure of three 

retaining screws of the MLG shock 

absorber, which could adversely affect 

the structural integrity of these 

airplanes. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective June 

25, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 25, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 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) 227–1149. 

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 September 24, 2009 (74 FR 

48668). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

During the overhaul of a Main Landing 

Gear (MLG) of a Falcon 2000, the sleeve on 

the hydraulic flow restrictor in the shock 

absorber was found displaced, because of the 

rupture of its three retaining screws. In this 

situation, the energy dissipation function of 

the shock absorber is lost and high loads may 

be transmitted to the aircraft structure during 

landing. Structural integrity may thus not be 

guaranteed over the entire certified landing 

conditions domain particularly in 

combination of high landing weight and high 

vertical speed. 

Failure of the retaining screws has been 

determined to be the final phase of a slow 

unscrewing process under normal 

operational conditions. The unsafe condition 

only exists once the three screws have failed. 

For the reasons described above, 

Airworthiness Directive (AD) 2008–0178 had 

been released to require a repetitive 

borescope inspection of the flow restriction 

system [for damage; such as condition of the 

sleeve of the dumping device, and broken or 

loose screws] and, if necessary, repair of the 

shock absorber per Dassault Aviation Service 

Bulletins (SB) F2000–367 and F2000EX–185 

(corresponding to modification M3120) 

developed with the landing gear 

manufacturer’s instructions. * * * 

After qualification testing, modification 

M3120 has been approved by EASA as a 

definitive solution. 

As a consequence, the present AD retains 

the requirements of AD 2008–0178 which is 

superseded and introduces M3120 as a 

terminating action to the repetitive 

inspections requirement, and further 

mandates its embodiment no later than the 

next MLG shock absorber overhaul. 

The unsafe condition is failure of three 

retaining screws of the MLG shock 

absorber, which could adversely affect 

the structural integrity of these 

airplanes. The repair can include 

additional inspections, modifying the 

shock absorbers, and contacting the 

manufacturer for repair instructions and 

doing the repair. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Extend Compliance Time 

Dassault-Aviation (Dassault) asks that 

we extend the compliance time for 

repairing the shock absorber if any 

damage is found from before further 

flight to the compliance times specified 

in European Aviation Safety Agency 

(EASA) AD 2009–0050, dated March 5, 

2009. Dassault states that requiring 

immediate repair of the shock absorber 

before further flight is unnecessary 

because it has been established that a 

two-tier approach of prompt inspection 

followed by repair, if necessary, is a 

more efficient means of addressing the 

unsafe condition. Dassault adds that this 

requirement would cause scheduling 

issues at maintenance facilities with 

trained personnel available to perform 

the repair, and would result in 

unnecessary grounding of its airplanes. 

We agree with the commenter. The 

compliance times referred to in EASA 

AD 2009–0050, and specified in 

Dassault Mandatory Service Bulletins 

F2000–366, Revision 2; and F2000EX– 

167, Revision 1; both dated December 1, 

2008; are based on technical 

information and calculations 

coordinated between EASA and 

Dassault. The compliance times for the 

repairs are based on inspection results 

showing the number of loose or broken 

screws that attach the sleeve of the 

damping device to the shock absorber. 

If one, two, or three screws are loose 

with a visible gap, the screws must be 

repaired within 12 months after the 

damage is found. If one screw is broken 

the screw must be repaired within 6 

months after the damage is found. If two 

screws are broken, the screws must be 

repaired within 10 flight cycles after the 

damage is found. And, if three screws 

are broken and the damping device is no 

longer attached, the repair must be done 

before further flight. Extending the 

compliance times for the repairs based 

on the number of loose or broken screws 

would not adversely affect airplane 

safety. Therefore, we have changed the 

requirements specified in paragraphs 

(f)(1), (f)(2), and (f)(3) of this AD and 

added a new Table 1 to allow the repair 

to be done at the applicable compliance 

times specified in the Accomplishment 

Instructions of the applicable service 

bulletin. We have reidentified 

subsequent tables accordingly. In 

addition, we have removed the 

compliance time difference specified in 

paragraph (1) under Note 1 of the 

NPRM. 

Request To Change the Description of 

the Unsafe Condition 

Dassault also asks that we revise the 

NPRM to remove the language 

describing the unsafe condition as 

failure of three retaining screws of the 

MLG shock absorber, which could result 

in collapse of the landing gear during 

ground maneuvers or landing. Dassault 

states that, based on engineering 

studies, it believes that the failure or 

absence of these screws will not result 

in collapse of the landing gear during 

ground maneuvers or landing. Dassault 

adds that, as specified in the EASA AD, 

the failure of these screws would only 

potentially affect the life of the airplane 

structure under all landing conditions, 

particularly with respect to the 

combination of high landing weights 

and high vertical speeds at touchdown. 

Dassault notes that the current language 

in the NPRM has caused needless alarm 

and concern among Model Falcon 2000 

and Falcon 2000EX owners and 

operators. 

We agree with the commenter for the 

reasons provided. Based on those 

reasons, we have changed the 

description of the unsafe condition 

throughout this AD as follows: ‘‘The 

unsafe condition is failure of three 

retaining screws of the MLG shock 

absorber, which could adversely affect 

the structural integrity of these 

airplanes.’’ 

Explanation of Change Made to This 

AD 

We have changed this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 


cprice-sewell on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28467 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a NOTE within the AD. 

Explanation of Change to Costs of 

Compliance 

After the NPRM was issued, we 

reviewed the figures we have used over 

the past several years to calculate AD 

costs to operators. To account for 

various inflationary costs in the airline 

industry, we find it necessary to 

increase the labor rate used in these 

calculations from $80 per work hour to 

$85 per work hour. The cost impact 

information, below, reflects this 

increase in the specified hourly labor 

rate. 

Costs of Compliance 

We estimate that this AD will affect 

236 products of U.S. registry. We also 

estimate that it will take about 25 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $501,500, or 

$2,125 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 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 this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. 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 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 the NPRM, 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. 

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 AD: 

2010–10–24 Dassault-Aviation: 

Amendment 39–16303. Docket No. 

FAA–2009–0791; Directorate Identifier 

2008–NM–213–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 25, 2010. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all Dassault-Aviation 

Model FALCON 2000 and FALCON 2000EX 

airplanes, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing gear. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During the overhaul of a Main Landing 

Gear (MLG) of a Falcon 2000, the sleeve on 

the hydraulic flow restrictor in the shock 

absorber was found displaced, because of the 

rupture of its three retaining screws. In this 

situation, the energy dissipation function of 

the shock absorber is lost and high loads may 

be transmitted to the aircraft structure during 

landing. Structural integrity may thus not be 

guaranteed over the entire certified landing 

conditions domain particularly in 

combination of high landing weight and high 

vertical speed. 

Failure of the retaining screws has been 

determined to be the final phase of a slow 

unscrewing process under normal 

operational conditions. The unsafe condition 

only exists once the three screws have failed. 

For the reasons described above, 

Airworthiness Directive (AD) 2008–0178 had 

been released to require a repetitive 

borescope inspection of the flow restriction 

system [for damage; such as condition of the 

sleeve of the dumping device, and broken or 

loose screws] and, if necessary, repair of the 

shock absorber per Dassault Aviation Service 

Bulletins (SB) F2000–367 and F2000EX–185 

(corresponding to modification M3120) 

developed with the landing gear 

manufacturer’s instructions. * * * 

After qualification testing, modification 

M3120 has been approved by the European 

Aviation Safety Agency (EASA), as a 

definitive solution. 


cprice-sewell on DSK8KYBLC1PROD with RULES
28468 Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 

As a consequence, the present AD retains 

the requirements of AD 2008–0178 which is 

superseded and introduces M3120 as a 

terminating action to the repetitive 

inspections requirement, and further 

mandates its embodiment no later than the 

next MLG shock absorber overhaul. 

The unsafe condition is failure of three 

retaining screws of the MLG shock absorber, 

which could adversely affect the structural 

integrity of these airplanes. The repair can 

include additional inspections, modifying 

the shock absorbers, and contacting the 

manufacturer for repair instructions and 

doing the repair. 

Actions and Compliance 

(f) Unless already done, do the following 

actions. 

(1) For airplanes on which each new or 

previously overhauled MLG shock absorber 

has accumulated 4,200 or more total landings 

since new or overhauled as of the effective 

date of this AD: Within 8 months after the 

effective date of this AD, inspect the shock 

absorber for damage, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin F2000–366, 

Revision 2; or F2000EX–167, Revision 1; both 

dated December 1, 2008; as applicable. If any 

damage is found, repair the shock absorber at 

the time specified in Table 1 of this AD, in 

accordance with the Accomplishment 

Instructions of Dassault Mandatory Service 

Bulletin F2000–366, Revision 2; or F2000EX– 

167, Revision 1; both dated December 1, 

2008; as applicable. 

(2) For airplanes on which each new or 

previously overhauled MLG shock absorber 

has accumulated 1,900 or more total landings 

and less than 4,200 total landings since new 

or overhauled as of the effective date of this 

AD: At the applicable compliance time 

specified in paragraph (f)(2)(i) or (f)(2)(ii) of 

this AD, inspect the shock absorber for 

damage, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin F2000–366, 

Revision 2; or F2000EX–167, Revision 1; both 

dated December 1, 2008; as applicable. If any 

damage is found, repair the shock absorber at 

the applicable time specified in Table 1 of 

this AD, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin F2000–366, 

Revision 2; or F2000EX–167, Revision 1; both 

dated December 1, 2008; as applicable. 

(i) For airplanes on which 6 or more steepapproach landings have been performed 

before the effective date of this AD: Within 

8 months after the effective date of this AD, 

do the actions required by paragraph (f)(2) of 

this AD. 

(ii) For airplanes on which less than or 

equal to 5 steep-approach landings have been 

performed before the effective date of this 

AD: Within 18 months after the effective date 

of this AD or 5,000 total landings since new 

or overhauled, whichever occurs first, do the 

actions required by paragraph (f)(2) of this 

AD. 

(3) For airplanes on which each new or 

previously overhauled MLG shock absorber 

has accumulated less than 1,900 total 

landings since new or overhauled as of the 

effective date of this AD: Before the 

accumulation of 3,000 total landings since 

new or overhauled, inspect the shock 

absorber for damage, in accordance with the 

Accomplishment Instructions of Dassault 

Mandatory Service Bulletin F2000–366, 

Revision 2; or F2000EX–167, Revision 1; both 

dated December 1, 2008; as applicable. If any 

damage is found, repair the shock absorber at 

the time specified in Table 1 of this AD, in 

accordance with the Accomplishment 

Instructions of Dassault Mandatory Service 

Bulletin F2000–366, Revision 2; or F2000EX– 

167, Revision 1; both dated December 1, 

2008; as applicable. 

TABLE 1—COMPLIANCE TIMES FOR REPAIR

Damage found Compliance time 

1, 2, or 3 loose screws ............................................................................................................... Within 12 months after the finding. 

1 broken screw ........................................................................................................................... Within 6 months after the finding. 

2 or 3 broken screws .................................................................................................................. Within 10 flight cycles after the finding. 

3 broken screws with detached damping device ....................................................................... Before further flight. 

(4) Repeat the inspections required by 

paragraphs (f)(1), (f)(2), and (f)(3) of this AD, 

as applicable, thereafter at intervals not to 

exceed 1,900 landings until accomplishment 

of the actions specified in paragraph (f)(6) of 

this AD. 

(5) Accomplishment of any inspection or 

repair before the effective date of this AD in 

accordance the applicable service 

information specified in Table 2 of this AD 

is acceptable for compliance with the 

corresponding requirements of this AD. 

TABLE 2—CREDIT SERVICE INFORMATION

Document Revision Date 

Dassault Mandatory Service Bulletin F2000–366 .................................................................................... 1 ............................ August 18, 2008. 

Dassault Mandatory Service Bulletin F2000EX–167 ............................................................................... Original .................. August 18, 2008. 

Dassault Service Bulletin F2000–366 ...................................................................................................... Original .................. April 18, 2008. 

(6) For airplanes on which Dassault 

Modification M3120 has not been embodied 

as of the effective date of this AD: Before the 

accumulation of 6,000 total landings or 144 

months on each new or previously 

overhauled MLG shock absorber, whichever 

occurs first: Modify the existing left- and 

right-hand MLG shock absorbers by installing 

MLG shock absorbers with part number (P/ 

N) D23365000–4 or P/N D23366000–4 (for 

Model Falcon 2000 airplanes), or P/N 

D23745000–2 or P/N D23746000–2 (for 

Model Falcon 2000EX airplanes), in 

accordance with the Accomplishment 

Instructions of Dassault Service Bulletin 

F2000EX–185, Revision 2; or F2000–367, 

Revision 4; both dated February 4, 2009; as 

applicable. Where these service bulletins 

specify contacting the manufacturer for 

repair instructions, contact the manufacturer 

and do the repair at the applicable 

compliance times specified in the 

Accomplishment Instructions of the 

applicable service bulletin. 

(7) Accomplishment of the modification 

required by paragraph (f)(6) of this AD before 

the effective date of this AD in accordance 

with the applicable service information 

specified in Table 3 of this AD is acceptable 

for compliance with the corresponding 

requirements of this AD. 

TABLE 3—CREDIT SERVICE INFORMATION FOR MODIFICATION

Document Revision Date 

Dassault Service Bulletin F2000EX–185 .................................................................................................. Original .................. August 18, 2008. 

Dassault Service Bulletin F2000EX–185 .................................................................................................. 1 ............................ December 1, 2008. 

Dassault Service Bulletin F2000–367 ...................................................................................................... 1 ............................ July 10, 2008. 


cprice-sewell on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 75, No. 98 / Friday, May 21, 2010 / Rules and Regulations 28469 

TABLE 3—CREDIT SERVICE INFORMATION FOR MODIFICATION—Continued 

Document Revision Date 

Dassault Service Bulletin F2000–367 ...................................................................................................... 2 ............................ August 18, 2008. 

Dassault Service Bulletin F2000–367 ...................................................................................................... 3 ............................ December 1, 2008. 

(8) Accomplishment of the modification 

required by paragraph (f)(6) of this AD ends 

the repetitive inspections required by 

paragraph (f)(4) of this AD. 

(9) As of the effective date of this AD, no 

person may install on any airplane as a 

replacement part, a MLG shock absorber, 

unless it has been modified according to the 

requirements specified in paragraph (f)(6) of 

this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

Paragraph (1) of the MCAI requires updating 

the operator’s maintenance program; 

however, that action is not required by this 

AD. The maintenance program does not 

require FAA approval. 

Other FAA AD Provisions 

(g) 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. 

Send information 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) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI EASA Airworthiness 

Directive 2009–0050, dated March 5, 2009, 

and the service information identified in 

Table 4 of this AD, for related information. 

TABLE 4—SERVICE INFORMATION

Document Revision Date 

Dassault Mandatory Service Bulletin F2000–366 ............................................................................................ 2 December 1, 2008. 

Dassault Mandatory Service Bulletin F2000EX–167 ....................................................................................... 1 December 1, 2008. 

Dassault Service Bulletin F2000–367 .............................................................................................................. 4 February 4, 2009. 

Dassault Service Bulletin F2000EX–185 ......................................................................................................... 2 February 4, 2009. 

Material Incorporated by Reference 

(i) You must use the applicable service 

information contained in Table 5 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

TABLE 5—MATERIAL INCORPORATED BY REFERENCE

Document Revision Date 

Dassault Mandatory Service Bulletin F2000–366 ............................................................................................ 2 December 1, 2008. 

Dassault Mandatory Service Bulletin F2000EX–167 ....................................................................................... 1 December 1, 2008. 

Dassault Service Bulletin F2000–367 .............................................................................................................. 4 February 4, 2009. 

Dassault Service Bulletin F2000EX–185 ......................................................................................................... 2 February 4, 2009. 

(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 Dassault Falcon Jet, P.O. Box 

2000, South Hackensack, New Jersey 07606; 

telephone 201–440–6700; Internet http:// 

www.dassaultfalcon.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on May 4, 

2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–11358 Filed 5–20–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0491; Directorate 

Identifier 2009–SW–64–AD; Amendment 39– 

16293; AD 2010–10–14] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS332L2 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


cprice-sewell on DSK8KYBLC1PROD with RULES