Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56599 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@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. 2011–0172, dated September 7, 2011. 

You may view the EASA AD in the AD 

Docket on the internet at http://

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2620: Extinguishing System. 

(i) 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 the AD specifies otherwise. 

(i) Eurocopter EC135 Alert Service Bulletin 

No. EC135–26A–003, Revision 2, dated 

December 19, 2011. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://www.eurocopter.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 also 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 August 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–22181 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0399; Directorate 

Identifier 2011–SW–064–AD; Amendment 

39–17574; AD 2013–18–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter France (Eurocopter) Model 

EC 155B, EC155B1, SA–365N, SA– 

365N1, AS–365N2, AS 365 N3, and SA– 

366G1 helicopters. This AD requires 

inspecting the collective pitch lever for 

correct locking and unlocking 

conditions. This AD was prompted by 

two separate reports of inadvertent 

collective pitch lever locking and 

unlocking. The actions of this AD are 

intended to detect an incorrectly 

adjusted collective pitch lever, which 

could result in loss of control of the 

helicopter. 

DATES: This AD is effective October 18, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of October 18, 2013. 

ADDRESSES: For service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; 

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

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

www.eurocopter.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 foreign 

authorities’ ADs, any incorporated-byreference 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: Matt 

Wilbanks, Aviation Safety Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 8, 2013, at 78 FR 26712, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 to 

include an AD that would apply to 

Eurocopter Model EC 155B, EC155B1, 

SA–365N, SA–365N1, AS–365N2, AS 

365 N3, and SA–366G1 helicopters, 

except helicopters with modification 

(MOD) 0767B5 installed. The NPRM 

proposed to require inspecting the 

collective pitch lever for correct 

unlocking with a spring scale, and if 

required, adjusting the collective pitch 

lever restraining tab and, for certain 

models, adjusting the collective link 

rods. The NPRM also proposed to 

require inspecting the collective pitch 

lever for the risk of inadvertent locking 

by measuring the clearance between the 

locking pin of the collective pitch lever 

and the L-section of the restraining tab, 

and if required, modifying the tab with 

a slight bend to the tab. The proposed 

requirements were intended to detect an 

incorrectly adjusted collective pitch 

lever, which could result in loss of 

control of the helicopter. 

The NPRM was prompted by AD No. 

2011–0154, dated August 22, 2011, 

issued by the European Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union. EASA issued AD 

2011–0154 to correct an unsafe 

condition for Eurocopter Model EC 

155B, EC155B1, SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters. EASA advises that two 

occurrences have been reported of 

inadvertent locking and unlocking of 

the collective pitch lever. One 

inadvertent collective pitch lever 

locking occurred when moving the 

collective pitch lever to the low-pitch 

position, and one inadvertent collective 

pitch lever unlocking occurred during 

engine start. To address this unsafe 

condition, Eurocopter issued AS 365 

Alert Telex No. 67.00.10, SA 366 Alert 

Telex No. 67.05, and EC 155 Alert Telex 

No. 67A007, which describe procedures 

to inspect the collective pitch lever for 

correct locking and unlocking 

conditions. This inspection was 


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56600 Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 

mandated by Direction Ge ́ne ́rale de 

l’Aviation Civile (DGAC) France AD No. 

F–2005–127, dated July 20, 2005. DGAC 

subsequently revised its AD, No. F– 

2005–127 R1, dated February 1, 2006 

(DGAC AD F–2005–127 R1), after 

Eurocopter issued Alert Service 

Bulletins containing the same 

inspection procedures and bearing the 

same numbers as the Alert Telexes. 

Since the issuance of DGAC AD F– 

2005–127 R1 Eurocopter developed an 

assembly comprised of a blade, a hinge, 

and a return spring to replace the 

flexible collective lever locking blade as 

terminating action for the inspection 

required by the AD. EASA then issued 

AD No. 2011–0154, which superseded 

DGAC AD F–2005–127 R1, retaining the 

inspection procedures for the collective 

pitch lever and removing from the 

applicability helicopters with the 

hinged, spring-loaded collective lever 

locking blade installed, designated as 

MOD 0767B65. 

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 26712, May 8, 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. 

Related Service Information 

We reviewed Eurocopter Alert Service 

Bulletin (ASB) No. 67.00.10 for Model 

AS365 helicopters, ASB No. 67.05 for 

Model SA366 helicopters, and ASB No. 

67A007 for Model EC155 helicopters. 

All three ASBs are Revision 1 and are 

dated February 25, 2009. These ASBs 

describe procedures for inspecting and 

adjusting the collective pitch lever for 

correct locking and unlocking 

conditions. 

Eurocopter has also issued ASB No. 

67.00.12, Revision 0, dated February 25, 

2009, for Model AS365 helicopters; ASB 

No. 67.07, Revision 0, dated February 

25, 2009, for Model AS366 helicopters; 

and ASB No. 67–009, Revision 1, dated 

July 19, 2010, for Model EC 155 

helicopters. These ASBs contain the 

procedures for MOD 0767B65. 

Costs of Compliance 

We estimate that this AD will affect 

32 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. Inspecting and adjusting the 

collective pitch lever will require about 

1 work hour at an average labor rate of 

$85 per hour, for a total cost per 

helicopter of $85 and a cost to U.S. 

operators of $2,720. 

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): 

2013–18–11 EUROCOPTER FRANCE: 

Amendment 39–17574; Docket No. 

FAA–2013–0399; Directorate Identifier 

2011–SW–064–AD. 

(a) Applicability 

This AD applies to Model EC 155B, 

EC155B1, SA–365N, SA–365N1, AS–365N2, 

AS 365 N3, and SA–366G1 helicopters, 

except helicopters with modification (MOD) 

0767B5 installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

inadvertent locking and unlocking of the 

collective pitch lever, which could result in 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 18, 

2013. 

(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 

Within 50 hours time-in-service: 

(1) For Model EC155B and EC155B1 

helicopters: 

(i) Lock the collective pitch lever, and 

using a spring scale, measure the load (G) 

required to unlock the pilot’s collective pitch 

lever as depicted in Figure 1, Detail B of 

Eurocopter Alert Service Bulletin (ASB) No. 

67A007, Revision 1, dated February 25, 2009 

(ASB 67A007). 

(ii) If the collective pitch lever unlocks at 

a load less than 11 deca Newtons (daN) (24.7 

lbs) or greater than 14 daN (31.5 lbs), before 

further flight, adjust the collective pitch lever 

restraining tab (F) using the oblong holes. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Measure the clearance (J1) between the 

locking pin of the collective pitch lever (C) 

and the L-section of the restraining tab (F) as 

depicted in Figure 1, Detail A of ASB 

67A007. 


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Federal Register / Vol. 78, No. 178 / Friday, September 13, 2013 / Rules and Regulations 56601 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 

millimeters (mm), before further flight, 

remove the restraining tab, clamp the 

restraining tab (F) in a vice with soft jaws, 

and gradually apply a load (H) to ensure a 

clearance of 3 mm or more, as depicted in 

Figure 1, Detail K of ASB 67A007. 

(2) For Model SA–365N, SA–365N1, AS– 

365N2, and AS 365 N3 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.00.10, Revision 1, dated February 

25, 2009 (ASB 67.00.10). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.00.10. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the Lsection of the restraining tab (F) as depicted 

in Figure 1, Detail A of ASB 67.00.10. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 

67.00.10. 

(3) For Model SA–366G1 helicopters: 

(i) Completely loosen the friction, lock the 

collective pitch lever, and using a spring 

scale, measure the load (G) required to 

unlock the pilot’s collective pitch lever as 

depicted in Figure 1, Detail B of Eurocopter 

ASB No. 67.05, Revision 1, dated February 

25, 2009 (ASB 67.05). 

(ii) If the collective pitch lever unlocks at 

a load less than 5 daN (11.3 lbs) or greater 

than 14 daN (31.5 lbs), before further flight, 

adjust the collective pitch lever restraining 

tab (F) using the oblong holes and adjust the 

collective link rods as described in the 

Accomplishment Instructions, paragraph 

2.B.4., of ASB 67.05. 

(iii) Set the collective pitch lever to the 

‘‘low pitch’’ position and hold it in this 

position, without forcing it downwards. 

(iv) Tighten the friction lock and measure 

the clearance (J1) between the locking pin of 

the collective pitch lever (C) and the Lsection of the restraining tab (F) as depicted 

in Figure 1, Detail A, of ASB 67.05. 

(v) If the clearance between the locking pin 

of the collective pitch lever and the L-section 

of the restraining tab is less than 3 mm, 

before further flight, remove the restraining 

tab, clamp the restraining tab (F) in a vice 

with soft jaws, and gradually apply a load (H) 

to ensure a clearance of 3 mm or more, as 

depicted in Figure 1, Detail K, of ASB 67.05. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Rotorcraft 

Certification Office, Rotorcraft Directorate, 

FAA, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; telephone (817) 222–5110; 

email matt.wilbanks@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 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. 67.00.12, Revision 0, dated February 25, 

2009; ASB No. 67.07, Revision 0, dated 

February 25, 2009; and ASB No. 67–009, 

Revision 1, dated July 19, 2010, which are 

not incorporated by reference, contain 

additional information about this AD. For 

service information identified in this AD, 

contact American Eurocopter Corporation, 

2701 N. Forum Drive, Grand Prairie, TX 

75052; telephone (972) 641–0000 or (800) 

232–0323; fax (972) 641–3775; or at http://

www.eurocopter.com/techpub. You may 

review a copy of the service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0154, dated August 22, 2011. You 

may view the EASA AD in the AD Docket on 

the internet at http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6710: Main Rotor Control 

(i) 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 the AD specifies otherwise. 

(i) Eurocopter Alert Service Bulletin No. 

67.00.10, Revision 1, dated February 25, 

2009. 

(ii) Eurocopter Alert Service Bulletin No. 

67.05, Revision 1, dated February 25, 2009. 

(iii) Eurocopter Alert Service Bulletin No. 

67A007, Revision 1, dated February 25, 2009. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

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

641–3775; or at http://www.eurocopter.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 also 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 August 21, 

2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–22170 Filed 9–12–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0270; Directorate 

Identifier 2011–NM–113–AD; Amendment 

39–17570; AD 2013–17–06] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Fokker Services B.V. Model F.27 Mark 

050 airplanes, and Model F.28 Mark 

0070 and 0100 airplanes. This AD was 

prompted by reports of loose nuts on 

contactors in the electrical power center 

(EPC), and in some cases, burned 

contactors. This AD requires inspecting 

and, if necessary, adjusting, the torque 

values of nuts on circuit breakers, 

contactors, and terminal blocks of the 

EPC and battery relay panel. This AD 

also requires inspecting to determine if 

certain parts are installed, and installing 

the parts if necessary. We are issuing 

this AD to detect and correct loose nuts, 

which could result in arcing and 

potentially an onboard fire, possibly 

resulting in damage to the airplane and 

injury to occupants or maintenance 

personnel. 

DATES: This AD becomes effective 

October 18, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of October 18, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 


emcdonald on DSK67QTVN1PROD with RULES