Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 36631 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2014–13–04 Columbia Helicopters, Inc. 

(Type Certificate Previously Held By 

Boeing Defense & Space Group) 

Helicopters: Amendment 39–17879; 

Docket No. FAA–2014–0385; Directorate 

Identifier 2013–SW–079–AD. 

(a) Applicability 

This AD applies to Model 234 helicopters, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue failure of aft pylon fitting attach 

structure combined with aft rotor blade 

damage. This condition could result in 

failure of a fore or aft rotor blade, vibration, 

overload of the aft pylon structure at the 

pylon attach fittings, departure of the aft 

pylon, and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective July 15, 2014. 

(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) Within 50 hours time-in-service (TIS): 

(i) Clean and inspect each fore and aft rotor 

blade for a defect, damage, or a disbond in 

accordance with the Accomplishment 

Instructions, paragraph 3.A.(1)(b) through 

3.A.(2)(b), of Columbia Helicopters, Inc., 

Service Bulletin No. 234–62–0008, Revision 

1, dated December 6, 2013 (SB 234–62–0008). 

(ii) Using a metallic coin or tap hammer, 

tap inspect each rotor blade trailing edge for 

defect, damage, or a disbond in accordance 

with the Accomplishment Instructions, 

paragraph 3.B.(1) through 3.B.(2)(e) and 

Figures 1 and 2 of SB 234–62–0008. 

(iii) If there is any defect, damage, or a 

disbond, repair the blade before further 

flight. If the defect, damage, or disbond is 

beyond acceptable limits, replace the blade 

before further flight. 

(2) Within 50 hours TIS and thereafter at 

intervals not to exceed 100 hours TIS, inspect 

the aft pylon at the station 534 and 594 

tension attachment fittings as follows: 

(i) Dye-penetrant inspect the aft pylon at 

the attachment fitting for a crack as shown 

in Figures 1, 2, and 3 and by following the 

Detailed Special Inspection-Dye Penetrant 

Method, paragraph 2.A.(2) through 2.G.(1), of 

Columbia Helicopters, Inc. Service Bulletin 

No. 234–54–0004, Revision 0, dated 

November 22, 2013 (SB 234–54–0004). 

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

repair or replace the aft pylon. Figures 2, 3, 

4, and 5 of SB 234–54–0004 contain 

examples of a crack. 

(3) Do not install an aft pylon or a rotor 

blade until the requirements of paragraphs 

(e)(1) and (e)(2) of this AD are accomplished. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

9-ANM-Seattle-ACO-AMOC-Requests@

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) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5400 and 6210 Nacelle/Pylon Structure 

and Main Rotor Blades. 

(h) 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) Columbia Helicopters, Inc., Service 

Bulletin No. 234–54–0004, Revision 0, dated 

November 22, 2013. 

(ii) Columbia Helicopters, Inc., Service 

Bulletin No. 234–62–0008, Revision 1, dated 

December 6, 2013. 

(3) For service information identified in 

this AD, contact Columbia Helicopters, Inc., 

14452 Arndt Road NE., Aurora, OR 97002, 

telephone (503) 678–1222, fax (503) 678– 

5841, or at http://www.colheli.com/. 

(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 June 16, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–14800 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0862; Directorate 

Identifier 2012–NM–098–AD; Amendment 

39–17863; AD 2014–12–02] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model FALCON 2000 

and FALCON 2000EX airplanes. This 

AD was prompted by a determination 

that new center of gravity (CG) limits are 

applicable during takeoff with certain 

conditions. This AD requires revising 

the airplane flight manual (AFM) to 

include procedures to advise the 

flightcrew of the new CG limits. We are 

issuing this AD to prevent an erratic 

takeoff path and consequent reduced 

controllability of the airplane. 

DATES: This AD becomes effective 

August 4, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 4, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/#!docketDetail;D=

FAA-2013-0862; or in person at the 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC. 

For Dassault 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.dassault

falcon.com. For Aviation Partners, Inc. 

service information identified in this 

AD, contact Aviation Partners, Inc., 

7299 Perimeter Road South, Seattle, WA 

98108; telephone 800–946–4638; 

Internet http://www.aviation

partners.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. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 


wreier-aviles on DSK5TPTVN1PROD with RULES
36632 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 

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 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain Dassault Aviation 

Model FALCON 2000 and FALCON 

2000EX airplanes. The NPRM published 

in the Federal Register on October 3, 

2013 (78 FR 61220). The NPRM was 

prompted by a determination that new 

center of gravity (CG) limits applicable 

during takeoff with a Slat/Flap SF2 

setting are necessary. The NPRM 

proposed to require revising the 

airplane flight manual (AFM) to include 

procedures to advise the flightcrew of 

the new CG limits. We are issuing this 

AD to prevent an erratic takeoff path 

and consequent reduced controllability 

of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0081, 

dated May 14, 2012 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

During a test flight on a Falcon 2000EX 

equipped with winglets (commercial 

designation Falcon 2000LX), performed for 

the certification of a maximum takeoff weight 

increase, the aeroplane took off and 

experienced unsatisfactory control 

characteristics under specific combined 

conditions of loading, slat-flap setting and 

horizontal tailplane trim setting. The weight 

and the Center of Gravity (CG) of the 

aeroplane during that test flight were within 

the already certified limits. 

This condition, if not corrected, could 

result in an erratic take-off path and reduced 

control of the aeroplane, which could 

ultimately jeopardize the aeroplane safe 

flight. 

To address this condition, Dassault 

Aviation developed Change Proposal (CP) 

036 to the Airplane Flight Manual (AFM), 

which introduced new CG limits which are 

applicable during take-off with Slat/Flap SF2 

setting. 

Since issuance of EASA PAD [proposed 

airworthiness directive] 11–077, Dassault 

Aviation issued a normal AFM revision 

currently at revision 15, which incorporates 

Dassault Aviation CP 036. 

For the reasons described above, this 

[EASA] AD requires amendment of the 

applicable AFM to ensure that the flight crew 

applies the appropriate operational 

procedure. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2013-0862-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 61220, 

October 3, 2013) and the FAA’s 

response to each comment. 

Request To Exclude Certain Airplanes 

Dassault stated that the NPRM (78 FR 

61220, October 3, 2013) excludes Model 

FALCON F2000EX airplanes on which 

Dassault Service Bulletin F2000EX–300, 

Revision 1, dated May 17, 2013, has 

been embodied. Dassault added that this 

service information requires installation 

of a new Arthur unit that is compatible 

with EASy II avionics, for airplanes on 

which winglets have been installed 

using Dassault Modification M2846 or 

Dassault Aviation Technical 

Instructions TI–F2000EX–M2846–ME. 

Dassault does not know whether 

airplanes which have been fitted with 

winglets per Aviation Partners 

Incorporated Supplemental Type 

Certificates (STCs) can be excluded from 

the applicability. 

We agree to clarify. We have 

determined that, for Model FALCON 

F2000EX airplanes modified by 

Aviation Partners Incorporated STC 

ST01987SE http://rgl.faa.gov/Regulatory

_and_Guidance_Library/rgstc.nsf/0/

1804CCC8BA5562958625770C0077

57C6?OpenDocument&Highlight=

st01987se, the actions specified in 

Dassault Service Bulletin F2000EX–300, 

Revision 1, dated May 17, 2013, can be 

accomplished. Therefore, if the actions 

specified in Dassault Service Bulletin 

F2000EX–300, Revision 1, dated May 

17, 2013, have been accomplished on 

any Model FALCON F2000EX airplane, 

that airplane is excluded from the 

applicability of this AD. We have not 

changed this AD in this regard. 

Request To Correct Typographical 

Error 

Dassault noted that there is a 

typographical error in paragraph (c)(1) 

of the NPRM (78 FR 61220, October 3, 

2013). Dassault stated that Dassault 

Aviation Modification M2848 should be 

changed to M2846 because number 

M2848 is incorrect. 

We agree with the commenter’s 

request. The correct modification 

number is identified in the applicability 

section of the MCAI; therefore, the 

modification number in paragraph (c)(1) 

of this final rule has been changed from 

M2848 to M2846. 

Additional Change Made to This Final 

Rule 

We have revised the formatting of 

paragraph (g) of this final rule for easier 

readability. This change does not affect 

the content of that paragraph. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

61220, October 3, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 61220, 

October 3, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 69 

airplanes of U.S. registry. 

We also estimate that it will take 

about 1 work-hour 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. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $5,865, or $85 

per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This 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 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 36633 

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 that 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); 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0862; 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 

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. 

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: 

2014–12–02 Dassault Aviation: 

Amendment 39–17863. Docket No. 

FAA–2013–0862; Directorate Identifier 

2012–NM–098–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective August 4, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

airplanes, certificated in any category, 

identified in paragraphs (c)(1) and (c)(2) of 

this AD; except Model FALCON F2000EX 

airplanes on which Dassault Aviation 

Modification M3254 or Dassault Service 

Bulletin F2000EX–300, Revision 1, dated 

May 17, 2013, has been embodied. 

(1) Model FALCON 2000EX airplanes on 

which Dassault Aviation modification M2846 

or Dassault Aviation Technical Instruction 

TI–F2000EX–M2846–ME or TI–F2000EX– 

M3118/M2846–ME has been embodied for 

the installation of winglets, including the 

airplane having serial number 602. 

(2) Model FALCON 2000 and FALCON 

2000EX airplanes modified by Aviation 

Partners Incorporated Supplemental Type 

Certificate (STC) ST01987SE http://rgl.faa.

gov/Regulatory_and_Guidance_Library/

rgstc.nsf/0/1804CCC8BA5562958625770C0

07757C6?OpenDocument&Highlight=

st01987se (installation of winglets). 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that new center of gravity (CG) limits 

applicable during takeoff with a Slat/Flap 

SF2 setting are necessary. We are issuing this 

AD to prevent an erratic takeoff path and 

consequent reduced controllability of the 

airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Airplane Flight Manual (AFM) Revision 

Within 14 days after the effective date of 

this AD: Revise the AFM by incorporating the 

CG limits identified in the service 

information specified in paragraph (g)(1), 

(g)(2), or (g)(3) of this AD, as applicable. 

(1) For airplanes identified in paragraph 

(c)(1) of this AD: Sub-sub-section 1–050–05C, 

‘‘Weights; Center of gravity limits (A/C with 

M2846 and M3390),’’ Issue 2; and Sub-subsection 1–050–05D, ‘‘Weights; Center of 

gravity limits (A/C with M2846 and M3000),’’ 

Issue 1; of Sub-section 1–050, ‘‘Weights and 

Loading,’’ of Section 1, ‘‘Limitations,’’ Issue 

5, of the Dassault Aviation FALCON 2000EX 

EASy, FALCON 2000DX, and FALCON 

2000LX AFM DGT88898, Revision 15, dated 

October 30, 2011. 

(2) For Model FALCON 2000 airplanes 

identified in paragraph (c)(2) of this AD: 

Aviation Partners, Inc. Dassault Aviation 

Falcon 2000 with CFE 738 Engines—Blended 

Winglets Installation, AFM Supplement 

APF2–0601, Code 002, Revision 3, dated June 

1, 2012. 

(3) For Model FALCON 2000EX airplanes 

identified in paragraph (c)(2) of this AD: 

Aviation Partners, Inc. Dassault Aviation 

Falcon 2000EX Series—Blended Winglets 

Installation, AFM Supplement APF2–0601, 

Code 001, Revision 4, dated June 1, 2012. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; 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) 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. 

(i) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0081, dated 

May 14, 2012, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov/#!

documentDetail;D=FAA-2013-0862-0002. 

(j) 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) Dassault Aviation FALCON 2000EX 

EASy, FALCON 2000DX, and FALCON 

2000LX Airplane Flight Manual (AFM) 

DGT88898, Revision 15, dated October 30, 

2011. This document does not contain dates 

for the ‘‘Issue’’ levels of the individual subsub-sections. The revision level and date of 

this document are identified on only the title 

page of the document. 

(ii) Aviation Partners, Inc. Dassault 

Aviation Falcon 2000 with CFE 738 

Engines—Blended Winglets Installation, 

AFM Supplement APF2–0601, Code 002, 

Revision 3, dated June 1, 2012. The revision 

level of this document is identified on only 

the title page, Revision Highlights, and Log 

of Pages of this document. 

(iii) Aviation Partners, Inc. Dassault 

Aviation Falcon 2000EX Series—Blended 

Winglets Installation, AFM Supplement 

APF2–0601, Code 001, Revision 4, dated June 


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36634 Federal Register / Vol. 79, No. 125 / Monday, June 30, 2014 / Rules and Regulations 

1, 2012. The revision level of this document 

is identified on only the title page, Revision 

Highlights, and Log of Pages of this 

document. 

(3) For Dassault 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. 

(4) For Aviation Partners, Inc. service 

information identified in this AD, contact 

Aviation Partners, Inc., 7299 Perimeter Road 

South, Seattle, WA 98108; telephone 800– 

946–4638; Internet http://www.aviation

partners.com. 

(5) 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. 

(6) 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 May 28, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–13319 Filed 6–27–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23809; Directorate 

Identifier 2005–NE–52–AD; Amendment 39– 

17866; AD 2014–12–05] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

S.A. Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2007–10– 

07 for all Turbomeca S.A. Arriel 2B, 

2B1, and 2B1A turboshaft engines. AD 

2007–10–07 required an inspection of 

the splines of the coupling assembly 

and the hydro-mechanical metering unit 

(HMU) drive gear shaft for wear. This 

AD requires the same inspection and 

expands the affected population. This 

AD also removes Arriel 2B1A engines 

from the applicability. We are issuing 

this AD to prevent failure of the HMU 

drive gear shaft, which could lead to 

damage to the engine and damage to the 

airplane. 

DATES: This AD is effective August 4, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 4, 2014. 

ADDRESSES: For service information 

identified in this AD, contact 

Turbomeca, S.A., 40220 Tarnos, France; 

phone: 33 (0)5 59 74 40 00; telex: 570 

042; fax: 33 (0)5 59 74 45 15. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call 781–238–7125. 

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–2006– 

23809; 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 AD, the mandatory 

continuing airworthiness information 

(MCAI), the regulatory evaluation, any 

comments received, and other 

information. The address for the Docket 

Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Davison, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park; phone: (781) 238–7156; 

fax: (781) 238–7199; email: 

Michael.Davison@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–10–07, 

Amendment 39–15048 (72 FR 26711, 

May 11, 2007), (‘‘AD 2007–10–07’’). AD 

2007–10–07 applied to the specified 

products. The NPRM published in the 

Federal Register on February 21, 2014 

(79 FR 9868). The NPRM proposed to 

require the same inspection as AD 

2007–10–07 and expand the affected 

population. The NPRM also proposed to 

remove Arriel 2B1A engines from the 

applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 9868, February 21, 2014). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 470 

engines installed on aircraft of U.S. 

registry. We also estimate that it will 

take about 2 hours per engine to comply 

with this AD. The average labor rate is 

$85 per hour. Based on these figures, we 

estimate the cost of this AD on U.S. 

operators to be $79,900. 

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 

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 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. 


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