3308 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

Eurocopter Deutschland GmbH):

Amendment 39–18373; Docket No. 

FAA–2015–0669; Directorate Identifier 

2013–SW–038–AD. 

(a) Applicability 

This AD applies to AHD Model MBB–BK 

117 A–1, A–3, A–4, B–1, B–2, C–1, and C– 

2 helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion, a crack, or a scratch on an N2 

control arm. This condition could lead to 

failure of the N2 control arm, resulting in a 

reduction in rotor speed and subsequent loss 

of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2016. 

(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 

For helicopters that have not reached 2 

years from the date of first flight, within 1 

year or before reaching 2 years from the date 

of first flight, whichever occurs first; and for 

helicopters that have reached or exceeded 2 

years from the date of first flight, within 50 

hours TIS: 

(1) Visually inspect each N2 control arm 

for corrosion, a crack, and a scratch as 

depicted in Figure 1 of Eurocopter Alert 

Service Bulletin (ASB) MBB–BK117–60A– 

126 or ASB MBB–BK117 C–2–76A–005, both 

Revision 0, and both dated June 24, 2013, as 

applicable to your model helicopter. 

(i) If an N2 control arm has corrosion or a 

scratch less than 0.5 millimeter (mm) (0.020 

inch) in depth, before further flight, remove 

the corrosion and repair the scratch. 

(ii) If an N2 control arm has any exfoliation 

corrosion, a crack, or has corrosion or a 

scratch 0.5 mm (0.020 inch) or greater in 

depth, before further flight, replace the N2 

control arm. 

(2) Thereafter, perform the requirements in 

paragraph (e)(1) of this AD at intervals not to 

exceed 12 months. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: James Blyn, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy., Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-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) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2013–0154, dated July 22, 2013. You may 

view the EASA AD on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2015–0669. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: Engine Controls, 7600. 

(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) Eurocopter Alert Service Bulletin (ASB) 

MBB–BK117–60A–126, Revision 0, dated 

June 24, 2013. 

(ii) Eurocopter ASB MBB–BK117 C–2– 

76A–005, Revision 0, dated June 24, 2013. 

(3) For Eurocopter service information 

identified in this final rule, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, Texas 75052; telephone (972) 

641–0000 or (800) 232–0323; fax (972) 641– 

3775; or at http://

www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 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 January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00658 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1935; Directorate 

Identifier 2014–SW–008–AD; Amendment 

39–18374; AD 2016–01–15] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model AB139 and 

AW139 helicopters. This AD requires 

visually inspecting certain subfloor 

frames for a crack. This AD was 

prompted by reports of cracks on inservice helicopters. The actions of this 

AD are intended to detect or prevent a 

crack in the subfloor frame, which could 

result in failure of the pilot and co-pilot 

pedal support frame and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 25, 2016. 

ADDRESSES: For service information 

identified in this rule, 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/

technical-bulletins. You may review the 

referenced service information at the 

FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy., Room 6N–321, Fort Worth, TX 

76177. 

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– 

1935 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 European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5110; email robert.grant@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 5, 2015, at 80 FR 32072, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 


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Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 3309 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Agusta Model AB139 and AW139 

helicopters, serial number (S/N) 31005 

through 31517 (except S/N 31007, 

31415, 31431, 31491, 31500, 31508, and 

31516) and S/N 41001 through 41356 

(except S/N 41355). The NPRM 

proposed to require visually inspecting 

certain subfloor frames for a crack. The 

proposed requirements were intended to 

detect or prevent a crack in the subfloor 

frame, which could result in failure of 

the pilot and co-pilot pedal support 

frame and subsequent loss of control of 

the helicopter. 

The NPRM was prompted by AD No. 

2014–0048, dated March 4, 2014, issued 

by EASA, which is the Technical Agent 

for the Member States of the European 

Union, to correct an unsafe condition 

for Agusta Model AB139 and AW139 

helicopters with a S/N 31005 through 

31517 (except S/N 31007, 31415, 31431, 

31491, 31500, 31508, and 31516) and S/ 

N 41001 through 41356 (except S/N 

41355). EASA advises that cracks have 

been reported in the subfloor frame at 

station (STA) 2105 on in-service 

helicopters. This condition, if not 

detected and corrected, could lead to 

failure of the pedals supporting the 

frame, which in turn could lead to the 

pedals being inoperative and 

subsequent loss of control of the 

helicopter, EASA advises. 

The EASA AD requires repetitive 

inspections of the subfloor frame at STA 

2105 for a crack. The EASA AD also 

requires installation of frame 

reinforcements before further flight if 

there is a crack or within 1,200 flight 

hours if there is no crack. The EASA AD 

provides that installation of the frame 

reinforcements constitutes terminating 

action for the repetitive inspections 

required by the AD. 

Since the NPRM was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

Alternative Method of Compliance 

(AMOC) for a helicopter of foreign 

design. This AD contains the current 

physical address of the FAA Southwest 

Regional Office and the new email 

address for requesting an AMOC. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we received no comments on the NPRM 

(80 FR 32072, June 5, 2015). 

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 and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires conducting 

the initial inspection within 30 flight 

hours or 2 months, whichever occurs 

first, and thereafter, at intervals not to 

exceed 300 flight hours or 6 months, 

whichever occurs first. This AD requires 

conducting the initial inspection within 

30 hours time-in-service (TIS), and 

thereafter, at intervals not to exceed 300 

hours TIS. 

Related Service Information Under 1 

CFR Part 51 

We reviewed AgustaWestland 

Bolletino Tecnico No. 139–311, 

Revision B, dated June 4, 2014 (BT), for 

certain serial-numbered Agusta Model 

AB139 and AW139 helicopters. The BT 

calls for visual inspections of the 

subfloor frames within 30 flight hours or 

two months, whichever occurs first, and 

thereafter at intervals of 300 flight hours 

or 6 months, whichever comes first, 

until frame reinforcements are installed 

to prevent future failures. The BT also 

specifies installing the frame 

reinforcements immediately if a crack is 

found and within 1,200 flight hours if 

a crack is not found. 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. 

Costs of Compliance 

We estimate that this AD affects 102 

U.S.-registered helicopters and that 

labor costs average $85 a work hour. 

Based on these estimates, we expect the 

following costs: 

• The visual inspection requires 2 

work-hours for a labor cost of $170 per 

helicopter. No parts are needed, so the 

cost totals $170 per helicopter, $17,340 

for the U.S. fleet. 

• If there are no cracks, installing the 

frame reinforcements requires 240 workhours for a labor cost of $20,400 and 

$2,274 for parts. The total cost is 

$22,674 per helicopter. 

• If there is a crack, installing the 

frame reinforcements requires 240 workhours for a labor cost of $20,400 and 

$3,401 for parts. The total cost is 

$23,801 per helicopter. 

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 

helicopters 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. 

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: 


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3310 Federal Register / Vol. 81, No. 13 / Thursday, January 21, 2016 / Rules and Regulations 

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): 

2016–01–15 Agusta S.p.A.: Amendment 39– 

18374; Docket No. FAA–2015–1935; 

Directorate Identifier 2014–SW–008–AD. 

(a) Applicability 

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

AB139 and AW139 helicopters, serial 

number (S/N) 31005 through 31517 (except 

S/N 31007, 31415, 31431, 31491, 31500, 

31508, and 31516) and S/N 41001 through 

41356 (except S/N 41355), certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in a subfloor frame. This condition 

could result in failure of the pilot and copilot pedal support frame and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

2016. 

(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 30 hours time-in-service (TIS) 

and thereafter at intervals not to exceed 300 

hours TIS, using a light, inspect all visible 

surfaces of the left hand subfloor frame, right 

hand subfloor frame, and middle subfloor 

frame at station (STA) 2105 for a crack as 

shown in Figures 10 through 13 of 

AgustaWestland Bollettino Tecnico No. 139– 

311, Revision B, dated June 4, 2014 (BT 139– 

311). 

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

install frame STA 2105 retromod part 

number (P/N) 3G5306P47211 by following 

the Compliance Instructions, Part II, 

paragraphs 7 through 7.10. of BT 139–311. 

(3) If there are no cracks, within 1200 

hours TIS, install frame STA 2105 retromod 

P/N 3G5306P47211 by following the 

Compliance Instructions, Part II, paragraphs 

7 through 7.10. of BT 139–311. 

(4) Installing frame STA 2105 retromod P/ 

N 3G5306P47211 terminates the repetitive 

inspection requirements in paragraph (e)(1) 

of this AD. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 9-ASWFTW-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. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0048, dated March 4, 2014. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA–2015–1935. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5300, Fuselage Structure (General). 

(j) 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 Bollettino Tecnico No. 

139–311, Revision B, dated June 4, 2014. 

(ii) Reserved. 

(3) For Agusta S.p.A. 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, 10101 Hillwood Pkwy., 

Room 6N–321, Fort Worth, TX 76177. 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 January 6, 

2016. 

Bruce E. Cain, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–00659 Filed 1–20–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0577; Directorate 

Identifier 2013–SW–042–AD; Amendment 

39–18375; AD 2015–12–09 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are revising airworthiness 

directive (AD) 2015–12–09 for Airbus 

Helicopters Model EC135P1, EC135T1, 

EC135P2, EC135T2, EC135P2+, 

EC135T2+, and MBB–BK 117 C–2 

helicopters. AD 2015–12–09 required 

inspecting certain washers for 

movement and making the appropriate 

repairs if the washers move. As 

published, AD 2015–12–09 referenced 

an incorrect date for the service 

information in the Credit for Previous 

Actions section. This AD corrects the 

error while retaining the requirements 

of AD 2015–12–09. These actions are 

intended to prevent loss of concerned 

control axis and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective February 25, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 23, 2015 (80 FR 34831, June 

18, 2015). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

telephone (972) 641–0000 or (800) 232– 

0323; fax (972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

Room 6N–321, 10101 Hillwood Pkwy, 

Fort Worth, TX 76177. 

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–2014– 

0577; 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 European Aviation 

Safety Agency (EASA) AD, any 


jstallworth on DSK7TPTVN1PROD with RULES