Federal Register / Vol. 80, No. 71 / Tuesday, April 14, 2015 / Rules and Regulations 19873 

RJ100A airplanes; certificated in any 

category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by a report of a 

pressurization problem on an airplane during 

climb-out; a subsequent investigation showed 

a crack in the fuselage skin. We are issuing 

this AD to detect and correct cracking, 

corrosion, and other defects, which could 

affect the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

(1) Within the compliance times specified 

in paragraphs (g)(1)(i) and (g)(1)(ii) of this 

AD, as applicable: Do an external eddy 

current inspection on the aft skin lap joints 

of the rear fuselage for cracking, corrosion, 

and other defects (i.e., surface damage and 

spot displacement), in accordance with 

paragraph 2.C. of the Accomplishment 

Instructions of BAE Systems (Operations) 

Limited Inspection Service Bulletin 53–239, 

including Appendix 2, Revision 3, dated May 

7, 2014. 

(i) For any airplane which has accumulated 

9,000 flight cycles or more since the 

airplane’s first flight as of the effective date 

of this AD: Do the inspection within 1,000 

flight cycles or 6 months after of the effective 

date of this AD, whichever occurs first. 

(ii) For any airplane which has 

accumulated less than 9,000 flight cycles 

since the airplane’s first flight as the effective 

date of this AD: Do the inspection before 

accumulating 10,000 flight cycles since the 

airplane’s first flight. 

(2) Repeat the inspection required by 

paragraph (g)(1) of this AD thereafter at 

intervals not to exceed the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD, 

as applicable to the airplane’s modification 

status. 

(i) For Model BAe 146 series airplanes and 

Model Avro 146–RJ series airplanes post 

modification HCM50070E, or post 

modification HCM50070F, or post 

modification HCM50259A, repeat the 

inspection at intervals not to exceed 4,000 

flight cycles. 

(ii) For Model BAe 146 series airplanes and 

Model Avro 146–RJ series airplanes premodification HCM50070E, and premodification HCM50070F, and premodification HCM50259A, repeat the 

inspection at intervals not to exceed 7,500 

flight cycles. 

(h) Corrective Action 

If any cracking, corrosion, or other defect 

is found during any inspection required by 

this AD: Before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA); or BAE 

Systems (Operations) Limited’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. Accomplishment 

of the repair does not constitute a terminating 

action for the inspections required by 

paragraph (g) of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for the 

initial inspection and corrective action on 

stringer 30, left hand (LH) and right hand 

(RH), as required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin 53–239, dated June 13, 2012, which 

is not incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

initial inspection and corrective action, as 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin 53–239, Revision 1, dated June 18, 

2013, which is not incorporated by reference 

in this AD. 

(3) This paragraph provides credit for the 

initial inspection and corrective action, as 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using BAE Systems 

(Operations) Limited Inspection Service 

Bulletin 53–239, Revision 2, dated July 15, 

2013, which is not incorporated by reference 

in this AD. 

(j) 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: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1175; fax 425–227–1149. 

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) 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 Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or BAE Systems (Operations) 

Limited’s EASA DOA. If approved by the 

DOA, the approval must include the DOAauthorized signature. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0207, dated 

September 9, 2013, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0621-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(3) and (l)(4) of this AD. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) BAE Systems (Operations) Limited 

Inspection Service Bulletin 53–239, 

including Appendix 2, Revision 3, dated May 

7, 2014. 

(ii) Reserved. 

(3) For service information identified in 

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/index.htm. 

(4) You may view this 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. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on March 

19, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–07800 Filed 4–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0908; Directorate 

Identifier 2015–SW–007–AD; Amendment 

39–18136; AD 2015–05–52] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


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ACTION: Final rule; request for 

comments. 

SUMMARY: We are publishing a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model A109, A109A, 

A109A II, A109C, A109K2, A109E, 

A119, A109S, AW119 MKII, and 

AW109SP helicopters, which was sent 

previously to all known U.S. owners 

and operators of these helicopters. This 

AD requires inspecting certain tail rotor 

(T/R) pitch control links (pitch links) for 

freedom of movement, corrosion, 

excessive friction of the spherical 

bearings, and cracks. This AD is 

prompted by a report of an in-flight 

failure of a pitch link on an Agusta 

Model AW119 MKII helicopter. These 

actions are intended to prevent loss of 

T/R pitch control and subsequent loss of 

control of the helicopter. 

DATES: This AD becomes effective April 

29, 2015 to all persons except those 

persons to whom it was made 

immediately effective by Emergency AD 

(EAD) 2015–05–52, issued on March 4, 

2015, which contains the requirements 

of this AD. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of April 29, 2015. 

We must receive comments on this 

AD by June 15, 2015. 

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 AD, any 

incorporated by reference service 

information, the European Aviation 

Safety Agency (EASA) 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 AD, contact AgustaWestland, 

Product Support Engineering, Via del 

Gregge, 100, 21015 Lonate Pozzolo (VA) 

Italy, ATTN: Maurizio D’Angelo; 

telephone 39–0331–664757; fax 39 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins. 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. It is also available on the Internet 

at http://www.regulations.gov in Docket 

No. FAA–2015–0908. 

FOR FURTHER INFORMATION CONTACT: 

Martin Crane, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email martin.r.crane@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

On March 4, 2015, we issued EAD 

2015–05–52, which requires inspecting 

each pitch link part number (P/N) 109– 

0130–05–117 with 100 hours or less 

time-in-service since overhaul for 

freedom of movement, corrosion, and to 

determine the force required to rotate 

the spherical bearings. If there is any 

corrosion or if the force exceeds a 

certain amount, then the pitch link is 

unairworthy. If there is no corrosion and 

the force does not exceed the amount, 

then EAD 2015–05–52 requires cleaning 

and visually inspecting the pitch link 

rod for a crack. If there is a crack, then 

the pitch link is unairworthy. EAD 

2015–05–52 was sent previously to all 

known U.S. owners and operators of 

these helicopters and resulted from a 

report of an in-flight failure of a pitch 

link P/N 109–0130–05–117 on an 

Agusta Model AW119 MKII helicopter. 

EAD 2015–05–52 was prompted by 

EAD No. 2015–0035–E, dated February 

27, 2015, issued by EASA, which is the 

Technical Agent for the Member States 

of the European Union, to correct an 

unsafe condition for AgustaWestland 

S.p.A. Model A109A, A109AII, A109C, 

A109E, A109K2, A109LUH, A109S, 

AW109SP, A119, and AW119MKII 

helicopters. EASA advises of the 

reported ‘‘in-flight breaking’’ of the T/R 

pitch control link P/N 109–0130–05– 

117. EASA EAD 2015–0035–E requires 

inspecting the T/R pitch control link for 

corrosion, rotation resistance or binding, 

and cracks. 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Italy and are 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Italy, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information Under 1 

CFR Part 51 

AgustaWestland issued Alert 

Bollettino Tecnico (BT) Nos. 109–145, 

109EP–141, 109K–65, 109S–065, 

109SP–087, and 119–072, all revision A, 

and all dated February 27, 2015. These 

alert BTs specify inspections of pitch 

link P/N 109–0130–05–117 for 

corrosion, freedom of movement, 

excessive friction of the spherical 

bearings, and cracks. This information is 

reasonably available at http://

www.regulations.gov in Docket No. 

FAA–2015–0908. Or see ADDRESSES for 

other ways to access this service 

information. 

AD Requirements 

This AD retains the requirements of 

EAD 2015–05–52 and requires 

inspecting the pitch link for freedom of 

movement for rotation resistance or 

binding. This AD also requires removing 


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the pitch link and inspecting each pitch 

link spherical bearing for corrosion and 

the force required to rotate each pitch 

link spherical bearing. If there is any 

corrosion, the pitch link is unairworthy. 

If the force required to rotate a spherical 

bearing in either end of the pitch link 

is greater than 7.30 N (1.64 pounds 

force), the pitch link is unairworthy. If 

the force required to rotate the spherical 

bearings in both ends of the pitch link 

is equal to or less than 7.30 N (1.64 

pounds force), this AD requires cleaning 

and visually inspecting the pitch link 

rod for a crack using a 10× or higher 

power magnifying glass or by 

performing a dye penetrant inspection. 

If there is a crack, the pitch link is 

unairworthy. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking. 

Costs of Compliance 

We estimate that this AD affects 253 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

It takes about 2.5 work-hours at $85 per 

work-hour to perform the inspections, 

for a total cost of $213 per helicopter 

and $53,889 for the U.S. operator fleet. 

If required, replacing a pitch link will 

cost about $1,957 for parts. We do not 

anticipate any additional labor costs to 

install a new pitch link as opposed to 

re-installing the existing pitch link. 

According to AgustaWestland’s 

service information some of the costs of 

this AD may be covered under warranty, 

thereby reducing the cost impact on 

affected individuals. We do not control 

warranty coverage by Agusta. 

Accordingly, we have included all costs 

in our cost estimate. 

FAA’s Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments prior to adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore, we found and continue to 

find that the risk to the flying public 

justifies waiving notice and comment 

prior to the adoption of this rule 

because the previously described unsafe 

condition can adversely affect the 

controllability of the helicopter and the 

initial required action must be 

accomplished before further flight. 

Since it was found that immediate 

corrective action was required, notice 

and opportunity for prior public 

comment before issuing this AD were 

impracticable and contrary to the public 

interest and good cause existed to make 

the AD effective immediately by EAD 

2015–05–52, issued on March 4, 2015, 

to all known U.S. owners and operators 

of these helicopters. These conditions 

still exist and the AD is hereby 

published in the Federal Register as an 

amendment to section 39.13 of the 

Federal Aviation Regulations (14 CFR 

39.13) to make it effective to all persons. 

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, I certify 

that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska to the extent that it justifies 

making a regulatory distinction; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this 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. 

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 airworthiness 

directive (AD): 

2015–05–52 Agusta S.p.A.: Amendment 39– 

18136; Docket No. FAA–2015–0908; 

Directorate Identifier 2015–SW–007–AD. 

(a) Applicability 

This AD applies to Agusta S.p.A. Model 

A109, A109A, A109A II, A109C, A109K2, 

A109E, A119, A109S, AW119 MKII, and 

AW109SP helicopters, certificated in any 

category, with a tail rotor pitch control link 

(pitch link) part number 109–0130–05–117 

with 100 hours or less time-in-service since 

overhaul. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

failure of a pitch link. This condition could 

result in loss of tail rotor pitch control and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective April 29, 2015 

to all persons except those persons to whom 

it was made immediately effective by 

Emergency AD 2015–05–52, issued on March 

4, 2015, which contains the requirements of 

this AD. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Before further flight, inspect the pitch 

link for freedom of movement while it is 

installed on the helicopter. 

(i) If there is rotation resistance or binding, 

before further flight, perform the actions in 

paragraphs (e)(2) through (e)(3) of this AD. 

(ii) If there is no rotation resistance and no 

binding, within 5 hours time-in-service, 

perform the actions in paragraphs (e)(2) 

through (e)(3) of this AD. 

(2) Remove the pitch link and inspect each 

pitch link spherical bearing for corrosion. If 

there is any corrosion, the pitch link is 

unairworthy. 

(3) Determine the force required to rotate 

each pitch link spherical bearing as depicted 

in Figure 1 of AgustaWestland Alert 

Bollettino Tecnico (BT) No. 109–145, 109EP– 

141, 109K–65, 109S–065, 109SP–087, or 119– 

072, all Revision A, and all dated February 

27, 2015, as applicable to your model 

helicopter. 


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(i) If the force required to rotate a spherical 

bearing in either end of the pitch link is 

greater than 7.30 N (1.64 pounds force), the 

pitch link is unairworthy. 

(ii) If the force required to rotate the 

spherical bearings in both ends of the pitch 

link is equal to or less than 7.30 N (1.64 

pounds force), after cleaning the pitch link 

rod using aliphatic naphtha or equivalent 

and a soft non-metallic bristle brush, visually 

inspect the pitch link rod for a crack in the 

area depicted in Figure 1 of AgustaWestland 

Alert BT No. 109–145, 109EP–141, 109K–65, 

109S–065, 109SP–087, or 119–072, all 

Revision A, and all dated February 27, 2015, 

as applicable to your model helicopter, using 

a 10x or higher power magnifying glass or by 

dye penetrant inspection. If there is a crack, 

the pitch link is unairworthy. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Martin Crane, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

martin.r.crane@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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency AD No. 2015–0035–E, dated 

February 27, 2015. You may view the EASA 

AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2015–0908. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6720, Tail Rotor Controls. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) AgustaWestland Alert Bollettino 

Tecnico (BT) No. 109–145, Revision A, dated 

February 27, 2015. 

(ii) AgustaWestland Alert BT No. 109EP– 

141, Revision A, dated February 27, 2015. 

(iii) AgustaWestland Alert BT No. 109K– 

65, Revision A, dated February 27, 2015. 

(iv) AgustaWestland Alert BT No. 109S– 

065, Revision A, dated February 27, 2015. 

(v) AgustaWestland Alert BT No. 109SP– 

087, Revision A, dated February 27, 2015. 

(vi) AgustaWestland Alert BT No. 119–072, 

Revision A, dated February 27, 2015. 

(3) For AgustaWestland service 

information identified in this AD, contact 

AgustaWestland, Product Support 

Engineering, Via del Gregge, 100, 21015 

Lonate Pozzolo (VA) Italy, ATTN: Maurizio 

D’Angelo; telephone 39–0331–664757; fax 39 

0331–664680; or at http://

www.agustawestland.com/technicalbulletins. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on April 6, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–08384 Filed 4–13–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0825; Directorate 

Identifier 2015–NM–035–AD; Amendment 

39–18138; AD 2015–08–02] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2015–02– 

04 for certain Dassault Aviation Model 

MYSTERE–FALCON 50 airplanes. AD 

2015–02–04 required installing two 

protective plates between the electrical 

wiring under the glare shield and the 

engine fire pull handles. This new AD 

continues to require installing two 

protective plates between the electrical 

wiring under the glare shield and the 

engine fire pull handles. This AD was 

prompted by our determination that the 

published version of AD 2015–02–04 

incorrectly identified the AD number as 

‘‘AD 2014–02–04’’ in a certain 

paragraph. We are issuing this AD to 

prevent chafing of the electrical wiring, 

which could result in a short circuit and 

generation of smoke in the cockpit, 

potential loss of several functions 

essential for safe flight, and consequent 

reduced controllability of the airplane. 

DATES: This AD becomes effective April 

29, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 6, 2015 (80 FR 5034, 

January 30, 2015). 

We must receive comments on this 

AD by May 29, 2015. 

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 AD, contact Dassault Falcon Jet, 

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 

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 by searching for 

and locating Docket No. FAA–2015– 

0825; 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 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, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 12, 2015, we issued AD 

2015–02–04, Amendment 39–18071 (80 


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