33050 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0938; Directorate 

Identifier 2012–SW–057–AD; Amendment 

39–17852; AD 2014–11–02] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (Previously Eurocopter 

France) (Airbus Helicopters) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters to require repetitively 

inspecting frame number (No.) 9 for a 

crack. This AD was prompted by a 

report of a crack in frame No. 9 on an 

AS365 helicopter. The actions of this 

AD are intended to detect a crack and 

prevent loss of structural integrity and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective July 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of July 15, 2014. 

ADDRESSES: For service information 

identified in this AD, 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, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

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, 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: Gary 

Roach, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 6, 2013, at 78 FR 66668, 

the Federal Register published our 

notice of proposed rulemaking (NPRM), 

which proposed to amend 14 CFR part 

39 by adding an AD that would apply 

to Eurocopter (now Airbus Helicopters) 

Model SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters. The 

NPRM proposed to require, for 

helicopters that have a No. 9 frame that 

has had any repair or alteration made, 

within 10 hours time-in-service (TIS) 

and every 110 hours TIS thereafter, 

inspecting the left-hand (LH) and righthand (RH) frame No. 9 for a crack in the 

areas of the latch support and stretcher 

support with a 10X or higher power 

magnifying glass. For all other 

helicopters, the NPRM proposed to 

require the inspection within 110 hours 

TIS and every 110 hours TIS thereafter. 

If there is a crack, the NPRM proposed 

to require, before further flight, 

repairing the crack. The proposed 

requirements were intended to detect a 

crack and prevent loss of structural 

integrity and subsequent loss of control 

of the helicopter. 

The NPRM was prompted by AD No. 

2012–0108–E, dated June 15, 2012 (AD 

2012–0108–E), issued by EASA, which 

is the Technical Agent for the Member 

States of the European Union, to correct 

an unsafe condition for Eurocopter 

Model SA 365 N, SA 365 N1, AS 365 

N2, and AS 365 N3 helicopters with a 

frame No. 9 installed, if certain 

‘‘doublers or repairs have been 

installed.’’ EASA advises that a crack 

discovered during the ‘‘T’’ inspection of 

a Model AS365 helicopter started at a 

rivet hole of a doubler installed on the 

frame No. 9 in accordance with 

Eurocopter Alert Service Bulletin (ASB) 

No. 53.00.42, dated January 31, 2001. 

EASA further states that structural 

alteration of frame No. 9 by 

modifications or repairs can result in 

fatigue crack initiation under normal 

operational loads. According to EASA, 

this condition, if not corrected, could 

lead to crack propagation and failure of 

frame No. 9, which would adversely 

affect the structural integrity of the 

helicopter. For these reasons, AD 2012– 

0108–E requires repetitive inspections 

of frame No. 9 for a crack in the area of 

the doubler or any repair performed in 

the area of the latch support and 

stretcher support. 

Since we issued the NPRM, 

Eurocopter France has changed its name 

to Airbus Helicopters. This AD reflects 

that change and updates the contact 

information to obtain service 

documentation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 66668, November 6, 

2013). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, 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 except for the minor change 

previously described. This change is 

consistent with the intent of the 

proposals in the NPRM (78 FR 66668, 

November 6, 2013) and will not increase 

the economic burden on any operator 

nor increase the scope of the AD. 

Differences Between This AD and the 

EASA AD 

The EASA AD requires contacting 

Eurocopter (now Airbus Helicopters) for 

repair instructions if there is a crack, 

and this AD does not. This AD applies 

to all Model 365 helicopters, not just 

those that were altered or repaired in 

accordance with specific Eurocopter 

modifications (MODs). 

Related Service Information 

Eurocopter issued one Emergency 

ASB (EASB) with two numbers: EASB 

No. 05.00.63, Revision 1, dated June 18, 

2012, for Model AS365 helicopters and 

EASB No. 05.00.30, Revision 1, dated 

June 18, 2012, for Model AS565 

helicopters. The EASB applies to 

helicopters with a frame No. 9 that has 

not been modified by MOD 07 53C17 or 

MOD 07 53D02, and that has had 

doublers installed or repairs performed 

in accordance with certain service 

instructions. The EASB describes 

procedures to inspect the frame No. 9 

for a crack, and for contacting 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 33051 

Eurocopter for further procedures if 

there is a crack. 

Costs of Compliance 

We estimate that this AD affects 37 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

At an average labor rate of $85 per workhour, inspecting LH and RH frame No. 

9 will require about 3 work-hours, for a 

cost per helicopter of $255 and a total 

cost to U.S. operators of $9,435 per 

inspection cycle. Repairing a cracked 

frame No. 9 will require about 20 workhours, and required parts will cost about 

$10,000, for a cost per helicopter of 

$11,700. 

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: 

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): 

2014–11–02 Airbus Helicopters (Previously 

Eurocopter France): Amendment 39– 

17852; Docket No. FAA–2013–0938; 

Directorate Identifier 2012–SW–057–AD. 

(a) Applicability 

This AD applies to Model SA–365N, SA– 

365N1, AS–365N2, and AS 365 N3 

helicopters, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in frame number (No.) 9, which could 

result in failure of frame No. 9, loss of 

structural integrity, 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) For helicopters that have any repair or 

alteration to the frame No. 9, within 10 hours 

time-in-service (TIS) and thereafter at 

intervals not to exceed 110 hours TIS, using 

a 10X or higher power magnifying glass, 

inspect the left-hand (LH) and right-hand 

(RH) frame No. 9 for a crack in the area of 

the latch support and stretcher support, as 

depicted in Figure 1 of Eurocopter 

Emergency Alert Service Bulletin No. 

05.00.63, Revision 1, dated June 18, 2012. 

(2) For all other helicopters, within 110 

hours TIS and thereafter at intervals not to 

exceed 110 hours TIS, perform the inspection 

in paragraph (e)(1) of this AD. 

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

repair the frame No. 9. Repairing a frame is 

not terminating action for the repetitive 

inspections required by paragraphs (e)(1) and 

(e)(2) of this AD. 

(f) Special Flight Permits 

Special flight permits may be issued for up 

to 10 hours TIS and a maximum crack length 

of 80 mm. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

gary.b.roach@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) 

Emergency AD No. 2012–0108–E, dated June 

15, 2012. You may view the EASA AD on the 

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

Docket number FAA–2013–0938. 

(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) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.63, Revision 1, dated June 

18, 2012. 

(ii) Reserved. 

Note 1 to paragraph (j)(2): Eurocopter 

Emergency Alert Service Bulletin (EASB) No. 

05.00.63, Revision 1, dated June 18, 2012, is 

co-published as one document along with 

Eurocopter EASB No. 05.00.30, Revision 1, 

dated June 18, 2012, which is not 

incorporated by reference. 

(3) For Eurocopter service information 

identified in this AD, 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. 

(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://


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33052 Federal Register / Vol. 79, No. 111 / Tuesday, June 10, 2014 / Rules and Regulations 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Fort Worth, Texas, on May 21, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–12721 Filed 6–9–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0156; Directorate 

Identifier 2014–CE–001–AD; Amendment 

39–17860; AD 2014–11–09] 

RIN 2120–AA64 

Airworthiness Directives; Costruzioni 

Aeronautiche Tecnam srl Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Costruzioni Aeronautiche Tecnam srl 

Model P2006T airplanes. This AD 

results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as a cracked engine mount. 

We are issuing this AD to require 

actions to address the unsafe condition 

on these products. 

DATES: This AD is effective July 15, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of July 15, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0156; or in person at 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 service information identified in 

this AD, contact Costruzioni 

Aeronautiche Tecnam Airworthiness 

Office, Via Maiorise–81043 Capua (CE) 

Italy; telephone: +39 0823 620134; fax: 

+39 0823 622899; email: m.oliva@

tecnam.com or g.paduano@tecnam.com; 

Internet: www.tecnam.com/it-IT/

documenti/service-bulletins.aspx. You 

may view this referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, 

call (816) 329–4148. 

FOR FURTHER INFORMATION CONTACT: 

Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4119; fax: (816) 329–4090; email: 

albert.mercado@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to adding an AD that would 

apply to Costruzioni Aeronautiche 

Tecnam srl Model P2006T airplanes. 

The NPRM was published in the 

Federal Register on March 14, 2014 (79 

FR 14447). The NPRM proposed to 

correct an unsafe condition for the 

specified products and was based on 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country. 

The MCAI states: 

During a ‘‘100 hours’’ inspection of a 

P2006T aeroplane, one engine mount Part 

Number (P/N) 26–7–1200–000 was found 

cracked on a node. 

This condition, if not detected and 

corrected, could lead to engine damage, 

possibly resulting in damage to the aeroplane 

and injury to the occupants. 

To address this potential unsafe condition, 

TECNAM issued Service Bulletin (SB) 138– 

CS-Rev0, providing inspection instructions. 

For the reasons described above, this AD 

requires a one-time inspection of each engine 

mount P/N 26–7–1200–000 and, depending 

on findings, replacement of the engine 

mount(s). 

This AD is considered an interim action 

and further AD action may follow. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2014-0156- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 14447, March 14, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

14447, March 14, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 14447, 

March 14, 2014). 

Interim Action 

We consider this AD interim action. 

We are requiring inspection of the left 

hand and right hand engine mounts 

with a report to the manufacturer of the 

results if cracks or deformation is found. 

We will work with the type certificate 

holder to evaluate the report results to 

determine repetitive inspection 

intervals and subsequent terminating 

action. Based on this evaluation, we 

may initiate further rulemaking action 

to address the unsafe condition 

identified in this AD. 

Costs of Compliance 

We estimate that this AD will affect 

10 products of U.S. registry. We also 

estimate that it would take about 6 

work-hours per product to comply with 

the basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

the cost of the AD on U.S. operators to 

be $5,100, or $510 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 18 work-hours and require parts 

costing $1,570 (per engine mount), for a 

cost of $3,100 per product. We have no 

way of determining the number of 

products that may need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591. ATTN: Information 

Collection Clearance Officer, AES–200. 


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