49146 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 

Bulletin 32–JA981042 Rev 9, dated July 11, 

2017. 

(3) For all affected airplane models: Before 

further flight after the effective date of this 

AD, revise the FAA-approved maintenance 

program (instructions for continued 

airworthiness) on the basis of which the 

operator or the owner ensures the continuing 

airworthiness of each operated airplane, as 

applicable to the airplane model, by 

incorporating the limitations described in 

BAE Systems British Aerospace Jetstream 

Series 3100 and 3200 Service Bulletin 32– 

JA981042 Rev 9, dated July 11, 2017, as 

applicable to the airplane model and 

depending on the airplane configuration. 

(4) For all airplanes: The compliance times 

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

presented in flight cycles (landings). If the 

total flight cycles have not been kept, 

multiply the total number of airplane hours 

time-in-service (TIS) by 0.75 to calculate the 

cycles. For the purposes of this AD: 

(i) 100 hours TIS × .75 = 75 cycles; and 

(ii) 1,000 hours TIS × .75 = 750 cycles. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Small Airplane 

Standards Branch, 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: Doug Rudolph, 

Aerospace Engineer, FAA, Small Airplane 

Standards Branch, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. Before using any 

approved AMOC on any airplane to which 

the AMOC applies, notify your appropriate 

principal inspector (PI) in the FAA Flight 

Standards District Office (FSDO), or lacking 

a PI, your local FSDO. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, Small Airplane Standards 

Branch, FAA; or the European Aviation 

Safety Agency (EASA). 

(h) Related Information 

(1) Refer to MCAI EASA AD 2017–0157, 

dated August 25, 2017, and BAE Systems 

British Aerospace Jetstream Series 3100 and 

3200 Service Bulletin 32–JA981042 Rev 9, 

dated July 11, 2017, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating Docket No. FAA–2017–0993. 

For service information related to this AD, 

contact BAE Systems (Operations) Limited, 

Customer Information Department, Prestwick 

International Airport, Ayrshire, KA9 2RW, 

Scotland, United Kingdom; telephone: +44 

1292 675207; fax: +44 1292 675704; email: 

RApublications@baesystems.com; Internet: 

http://www.baesystems.com/Businesses/ 

RegionalAircraft/. You may review copies of 

the referenced service information at the 

FAA, Policy and Innovation Division, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

Issued in Kansas City, Missouri, on 

October 12, 2017. 

Melvin J. Johnson, 

Acting Deputy Director, Policy & Innovation 

Division, Aircraft Certification Service. 

[FR Doc. 2017–22708 Filed 10–23–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–1020; Product 

Identifier 2017–NM–114–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A318–111 and –112 

airplanes; Model A319–111, –112, –113, 

–114, and –115 airplanes; Model A320– 

211, –212, –214, and –216 airplanes; 

and Model A321–111, –112, –211, –212, 

and –213 airplanes. This proposed AD 

was prompted by a review of 

maintenance instructions for a blend 

repair of the snout diameter of the main 

beam assembly of the forward engine 

mount that would create an excessive 

gap between the bearing mono-ball and 

the snout. This proposed AD would 

require modifying the main beam 

assembly of the forward engine mount. 

We are proposing this AD to address the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by December 8, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Airbus, 

Airworthiness Office–EIAS, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone: +33 5 61 93 

36 96; fax: +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; 

Internet: http://www.airbus.com. You 

may view this service information at the 

FAA, Transport Standards Branch, 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 by searching for 

and locating Docket No. FAA–2017– 

1020; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this 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. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227– 

1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–1020; Product Identifier 2017– 

NM–114–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this NPRM. We will consider 

all comments received by the closing 

date and may amend this NPRM 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 NPRM. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD 2017–0132, 

dated July 27, 2017 (referred to after this 

as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for all Airbus Model A318–111 and 

–112 airplanes; Model A319–111, –112, 


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Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 49147 

–113, –114, and –115 airplanes; Model 

A320–211, –212, –214, and –216 

airplanes; and Model A321–111, –112, 

–211, –212, and –213 airplanes. The 

MCAI states: 

A review of maintenance instructions 

revealed that the Goodrich Aerospace 

CFM56–5B, Forward Engine Mount 

Component Maintenance Manual (CMM) 71– 

21–08, revision (rev.) 1 up to 46 (inclusive), 

repair 10 (Blend Repair-Beam Assembly 

Snout Diameter), provides instructions to 

blend the wear on the forward engine mount 

assembly, Part Number (P/N) 642–2000–9, 

642–2000–13, or 642–2000–25, creating an 

excessive gap between the bearing mono-ball 

and the snout of the forward engine mount 

main beam assembly, P/N 642–2006–501, or 

P/N 642–2006–503. 

This condition, if not detected and 

corrected, could lead to in-flight failure of a 

forward engine mount and consequent 

detachment of an engine, possibly resulting 

in reduced control of the aeroplane and 

injury to persons on the ground. 

To address this potential unsafe condition, 

Airbus issued Service Bulletin (SB) A320– 

71–1065 and SB A320–71–1066, and 

Goodrich Aerospace issued SB RA32071– 

159, providing instructions for an in-shop 

inspection(s) for the main beam snout and, 

depending on findings, applicable corrective 

action(s) and re-identification. 

For the reason described above, this 

[EASA] AD requires replacement of the 

affected forward engine mount main beam 

assemblies. As the same main beam 

assemblies are certified for CFM56–5A 

engine installation, this [EASA] AD also 

applies to aeroplanes with that engine. 

Required actions include modifying 

the main beam assembly of the forward 

engine mount. The modification 

includes repairing, replacing, or 

reworking the main beam assembly. You 

may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

1020. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–71–1065, Revision 01, dated July 

28, 2017. This service information 

describes procedures for modifying the 

main beam assembly of the forward 

engine mount. The modification 

includes, among other things, repair or 

replacement of the main beam assembly. 

Airbus has also issued Service 

Bulletin A320–71–1066, dated 

December 1, 2016. This service 

information describes procedures for 

modifying the main beam assembly of 

the forward engine mount. The 

modification includes, among other 

things, rework of the main beam 

assembly. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

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 these same 

type designs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 500 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Modification .................. Up to 76 work-hours × $85 per hour = $6,460 ... $778 Up to $7,238 ................ Up to $3,619,000. 

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. 

This proposed AD is issued in 

accordance with authority delegated by 

the Executive Director, Aircraft 

Certification Service, as authorized by 

FAA Order 8000.51C. In accordance 

with that order, issuance of ADs is 

normally a function of the Compliance 

and Airworthiness Division, but during 

this transition period, the Executive 

Director has delegated the authority to 

issue ADs applicable to transport 

category airplanes to the Director of the 

System Oversight Division. 

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: 

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. 

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. 


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49148 Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

Airbus: Docket No. FAA–2017–1020; Product 

Identifier 2017–NM–114–AD. 

(a) Comments Due Date 

We must receive comments by December 8, 

2017. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Airbus Model A318– 

111 and –112 airplanes; Model A319–111, 

–112, –113, –114, and –115 airplanes; Model 

A320–211, –212, –214, and –216 airplanes; 

and Model A321–111, –112, –211, –212, and 

–213 airplanes; certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 71, Powerplant. 

(e) Reason 

This AD was prompted by a review of 

maintenance instructions for a blend repair 

of the diameter of the snout of the main beam 

assembly of the forward engine mount that 

would create an excessive gap between the 

bearing mono-ball and the snout. We are 

issuing this AD to prevent in-flight failure of 

a forward engine mount, and consequent 

detachment of an engine, which could result 

in reduced controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Definition of Affected Parts 

For the purposes of this AD: An ‘‘affected 

main beam’’ is any main beam assembly of 

the forward engine mount, part number (P/ 

N) 642–2006–501 or P/N 642–2006–503, 

identified in paragraph (g)(1) or (g)(2) of this 

AD. 

(1) Any part for which no maintenance 

records are available to confirm the part has 

never been repaired. 

(2) Any part that was repaired as specified 

in the instructions of Goodrich Aerospace 

component maintenance manual (CMM) 71– 

21–08, Revision 1 through 46, repair 10, 

except for parts identified in paragraphs 

(g)(2)(i), (g)(2)(ii), and (g)(2)(iii) of this AD. 

(i) Any part on which a qualifying 

inspection identified in paragraph (h) of this 

AD has been done and there were no findings 

(the inspection was passed). 

(ii) Any part on which a qualifying 

inspection identified in paragraph (h) of this 

AD has been done and that part has been 

repaired as specified in the instructions of 

Goodrich Aerospace Service Bulletin 

RA32071–159. 

(iii) Any part that has been repaired in 

accordance with other instructions approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). 

(h) Definition of Qualifying Inspection 

For the purposes of this AD: ‘‘A qualifying 

inspection’’ is an inspection done as 

specified in the instructions of Goodrich 

Aerospace Service Bulletin RA32071–159; or 

for CFM56–5B engines, an inspection done as 

specified in the instructions of Goodrich 

Aerospace CMM 71–21–08, Revision 47, 

repair 10; or for CFM56–5A engines, an 

inspection done as specified in the 

instructions of Goodrich Aerospace CMM 

71–21–06, Revision 59, repair 21. 

(i) Definition of Airplane Groups 

For the purposes of this AD: ‘‘Group 1 

airplanes’’ are airplanes on which an affected 

main beam has been installed as of the 

effective date of this AD. ‘‘Group 2 airplanes’’ 

are airplanes on which an affected main 

beam has not been installed as of the 

effective date of this AD; this includes 

airplanes with an original certificate of 

airworthiness or original export certificate of 

airworthiness that was issued after the 

effective date of this AD. 

(j) Modification of Affected Main Beam 

Assemblies 

For Group 1 airplanes as identified in 

paragraph (i) of this AD: At the earliest of the 

compliance times specified in paragraphs 

(j)(1), (j)(2), and (j)(3) of this AD, modify each 

affected main beam identified in paragraph 

(g) of this AD, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–71–1065, Revision 01, 

dated July 28, 2017; and Airbus Service 

Bulletin A320–71–1066, dated December 1, 

2016; as applicable, except as required by 

paragraph (k) of this AD. 

(1) Within 48 months after the effective 

date of this AD. 

(2) Within 10,000 flight cycles after the 

effective date of this AD. 

(3) Within 15,000 flight hours after the 

effective date of this AD. 

(k) Exception to Service Information 

Where Airbus Service Bulletin A320–71– 

1065, Revision 01, dated July 28, 2017, 

specifies to contact a manufacturer for 

appropriate action, and specifies that action 

as ‘‘RC’’ (Required for Compliance): Before 

further flight, accomplish corrective actions 

in accordance with the procedures specified 

in paragraph (n)(2) of this AD. 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (j) of this AD 

involving Airbus Service Bulletin A320–71– 

1065, Revision 01, dated July 28, 2017, if 

those actions were performed before the 

effective date of this AD using Airbus Service 

Bulletin A320–71–1065, dated December 1, 

2016. 

(m) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install an affected main beam 

identified in paragraph (g) of this AD or a 

forward engine mount assembly equipped 

with an affected main beam identified in 

paragraph (g) of this AD, on any airplane. 

(n) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Section, Transport Standards Branch, 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 manager of the International 

Section, send it to the attention of the person 

identified in paragraph (o)(2) of this AD. 

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. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Section, 

Transport Standards Branch, FAA; or EASA; 

or Airbus’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (k) of this AD: If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(o) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2017–0132, dated July 27, 2017, for related 

information. This MCAI may be found in the 

AD docket on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2017–1020. 

(2) For more information about this AD, 

contact Sanjay Ralhan, Aerospace Engineer, 

International Section, Transport Standards 

Branch, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; telephone 425– 

227–1405; fax 425–227–1149. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office–EIAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone: +33 

5 61 93 36 96; fax: +33 5 61 93 44 51; email: 

account.airworth-eas@airbus.com; Internet: 

http://www.airbus.com. You may view this 

service information at the FAA, Transport 

Standards Branch, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, call 

425–227–1221. 


ethrower on DSK3G9T082PROD with PROPOSALS
Federal Register / Vol. 82, No. 204 / Tuesday, October 24, 2017 / Proposed Rules 49149 

Issued in Renton, Washington, on October 

17, 2017. 

Jeffrey E. Duven, 

Director, System Oversight Division, Aircraft 

Certification Service. 

[FR Doc. 2017–23014 Filed 10–23–17; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2017–0909; Product 

Identifier 2017–NM–081–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 adopt a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model MYSTERE– 

FALCON 900, FALCON 900EX, 

FALCON 2000, and FALCON 2000EX 

airplanes. This proposed AD was 

prompted by reports of a loose screw on 

certain slat mechanical stop assemblies, 

and punctures in certain fuel caps. This 

proposed AD would require a one-time 

inspection, and corrective action if 

necessary. We are proposing this AD to 

address the unsafe condition on these 

products. 

DATES: We must receive comments on 

this proposed AD by December 8, 2017. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. 

Box 2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet 

http://www.dassaultfalcon.com. You 

may view this referenced service 

information at the FAA, Transport 

Standards Branch, 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 by searching for 

and locating Docket No. FAA–2017– 

0909; or in person at the Docket 

Management Facility 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 Section, Transport 

Standards Branch, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 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 proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2017–0909; Product Identifier 2017– 

NM–081–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 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2017–0106, dated June 19, 

2017 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model MYSTERE–FALCON 

900, FALCON 900EX, FALCON 2000, 

and FALCON 2000EX airplanes. The 

MCAI states: 

On some aeroplanes in-service, the screw 

of the slat mechanical stop assembly on slat 

tracks #6, #7 and #8 was found loose. In 

some cases, a puncture was found in the fuel 

cap. The results of the technical 

investigations concluded that the most 

probable reason for these events was 

improper installation of the lock washers on 

the screws during production or 

maintenance. 

This condition, if not detected and 

corrected, could lead to structural damage to 

the wing front spar, and consequent fuel 

leakage, possibly resulting in an uncontrolled 

fire. 

To address this potential unsafe condition, 

Dassault issued [Service Bulletin] SB F900– 

460 Revision 1, SB F900EX–508 Revision 3, 

SB F2000–433 Revision 1, and SB F2000EX– 

386 Revision 3 (hereafter collectively referred 

as ‘the applicable SB’ in this [EASA] AD), as 

applicable to aeroplane type/model, to 

provide inspection instructions. 

For the reasons described above, this 

[EASA] AD requires a one-time [general 

visual] inspection of the slat tracks #6, #7 

and #8 to verify the tightening torque of the 

screw and proper lock washer installation 

and, depending on findings, accomplishment 

of applicable corrective action(s). 

Applicable corrective actions include 

replacement, if necessary. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2017– 

0909. 

Related Service Information Under 1 

CFR Part 51 

Dassault Aviation has issued the 

following service information. 

• Dassault Service Bulletin F900–460, 

Revision 1, dated February 10, 2017 

• Dassault Service Bulletin F900EX– 

508, Revision 3, dated February 10, 

2017 

• Dassault Service Bulletin F2000–433, 

Revision 1, dated February 10, 2017 

• Dassault Service Bulletin F2000EX– 

386, Revision 3, dated February 10, 

2017 

This service information describes 

procedures for doing a one-time general 

visual inspection of the screw on the 

affected slat tracks, and replacement if 

necessary. These documents are distinct 

since they apply to different airplane 

models. The service information is 

reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

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 


ethrower on DSK3G9T082PROD with PROPOSALS