Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52407 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 27, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A330– 

301, –302, –303, –321, –322, –323, –341, 

–342, and –343 airplanes; and Model A340– 

211, –212, –213, –311, –312, and –313 

airplanes; certificated in any category; all 

manufacturer serial numbers; if fitted with a 

trimmable horizontal stabilizer actuator 

(THSA) having part number (P/N) 47147–500 

or P/N 47147–700. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Reason 

This AD was prompted by a determination 

that ballscrew rupture could occur on certain 

THSAs. We are issuing this AD to detect and 

correct ballscrew rupture, which, along with 

corrosion on the ballscrew lower splines, 

may lead to loss of transmission of THSA 

torque loads from the ballscrew to the tie-bar 

and consequent THSA blowback, which 

could result in loss of control 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) Repetitive Integrity Tests 

At the later of the times specified in 

paragraph (g)(1) or (g)(2) of this AD, as 

applicable, do a THSA ballscrew shaft 

integrity test, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3191, 

dated June 7, 2012; or Airbus Mandatory 

Service Bulletin A340–27–4186, dated June 

7, 2012; as applicable. Repeat the integrity 

test thereafter at intervals not to exceed 

12,000 flight hours or 4,400 flight cycles, 

whichever occurs first. 

(1) At the latest of the times specified in 

paragraph (g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of 

this AD. 

(i) Within 12,000 flight hours since the 

airplane’s first flight; or 

(ii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done as specified in maintenance 

review board report (MRBR) Task 274000–12; 

or 

(iii) Within 12,000 flight hours since the 

most recent THSA ballscrew shaft integrity 

test was done, as specified in Airbus 

Mandatory Service Bulletin A330–27–3179 

or Airbus Mandatory Service Bulletin A340– 

27–4175, as applicable. (These service 

bulletins specify testing in case of type II or 

type III findings). 

(2) Within 1,000 flight hours after the 

effective date of this AD, but without 

exceeding the latest of the times specified in 

paragraph (g)(2)(i), (g)(2)(ii), or (g)(2)(iii) of 

this AD. 

(i) 16,000 flight hours since the airplane’s 

first flight. 

(ii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in MRBR task 274000– 

12. 

(iii) 16,000 flight hours since the most 

recent THSA ballscrew shaft integrity test 

was done, as specified in Airbus Mandatory 

Service Bulletin A330–27–3179, or Airbus 

Mandatory Service Bulletin A340–27–4175, 

as applicable. (These service bulletins specify 

testing in case of type II or type III findings). 

(h) Replacement 

If the result from any test required by 

paragraph (g) of this AD is not correct, as 

specified in the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A330–27–3191, dated June 7, 2012; 

or Airbus Mandatory Service Bulletin A340– 

27–4186, dated June 7, 2012; as applicable: 

Before further flight, replace the THSA with 

a serviceable THSA, in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–27–3191, 

dated June 7, 2012; or Airbus Mandatory 

Service Bulletin A340–27–4186, dated June 

7, 2012; as applicable. Replacement of a 

THSA, as required by this paragraph, with a 

THSA having P/N 47147–500 or P/N 47147– 

700, is not terminating action for the 

repetitive tests required by paragraph (g) of 

this AD. 

(i) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; 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. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0210, dated October 11, 2012, 

for related information, which can be found 

in the AD docket on the internet at http://

www.regulations.gov. 

(k) 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) Airbus Mandatory Service Bulletin 

A330–27–3191, dated June 7, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A340–27–4186, dated June 7, 2012. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

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

Issued in Renton, Washington, on August 

1, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19161 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0341; Directorate 

Identifier 2012–SW–025–AD; Amendment 

39–17557; AD 2013–16–19] 

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 

EC120B and EC130B4 helicopters with 

a certain emergency flotation gear (float) 

installed. This AD requires inspecting 

the float for chafing of the fabric 

covering and adding protectors to the 

float installation to prevent contact 

between the float and the protruding 


emcdonald on DSK67QTVN1PROD with RULES
52408 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

sections of the installation. This AD was 

prompted by a report of a float that 

would not inflate during overhaul 

because one of the float compartments 

was punctured due to chafing. The 

actions of this AD are intended to 

prevent failure of float and subsequent 

loss of control of the helicopter during 

an emergency water landing. 

DATES: This AD is effective September 

27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 27, 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 

authority’s AD, 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: 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 April 15, 2013, at 78 FR 22213, 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 EC120B helicopters 

with a left-hand (LH) emergency 

flotation gear, part number (P/N) 

215674–0, 215674–1, or 215674–2 

installed, fitted with a float, P/N 

215481–0; or with a right-hand (RH) 

emergency flotation gear, P/N 215675–0, 

215675–1, or 215675–2 installed, fitted 

with a float, P/N 215482–0; and Model 

EC130B4 helicopters with a LH 

emergency flotation gear P/N 217227–0 

installed, fitted with a float P/N 

217174–0; or with a RH emergency 

flotation gear P/N 217228–0 installed, 

fitted with a float, P/N 217195–0. The 

NPRM proposed to require inspecting 

the float for chafing of the fabric 

covering and adding protectors to the 

float installation to prevent contact 

between the float and the protruding 

sections of the installation. The 

proposed requirements were intended to 

prevent failure of float and subsequent 

loss of control of the helicopter during 

an emergency water landing. 

The NPRM was prompted by AD No. 

2011–0185, dated September 23, 2011 

(AD 2011–0185), issued by the 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD 2011–0185 to 

correct an unsafe condition for 

Eurocopter Model EC120 and EC130 

helicopters. EASA advises that during 

overhaul of an emergency flotation gear 

installation, it was impossible to inflate 

the RH float according to the 

instructions in the equipment 

manufacturer’s manual. An 

investigation revealed that one of the 

compartments in the float was 

punctured and several areas of the LH 

and RH floats were damaged, caused by 

chafing between the float and the 

protruding sections of the supply bars 

and banjo unions. To address this 

potentially unsafe condition, EASA 

issued AD No. 2009–0190, dated August 

26, 2009 (AD 2009–0190), which 

required repetitive inspections of the 

floats to detect chafing. Aerazur, the 

float manufacturer, later developed 

protectors to be installed on the floats to 

eliminate interference between the float 

and the blunt parts of the installation. 

EASA then issued AD 2011–0185, 

which superseded AD 2009–0190 and 

required installation of the protectors on 

the floats as terminating action for the 

repetitive inspections. 

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 22213, April 15, 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 

Eurocopter has issued Alert Service 

Bulletin (ASB) No. 05A011, Revision 0, 

dated June 8, 2009 (ASB 05A011), for 

Model EC120B helicopters and ASB No. 

05A008, Revision 0, dated June 8, 2009 

(ASB 05A008), for Model EC130B4 

helicopters. Both ASBs specify 

inspecting the floats for deterioration 

and chafing at specified intervals and, if 

necessary, repairing the floats. 

Eurocopter has also issued ASB No. 

EC120–25A026, Revision 0, dated July 

11, 2011 (ASB EC120–25A026), for 

Model EC120B helicopters and ASB No. 

EC130–25A042, Revision 0, dated July 

11, 2011 (ASB EC130–25A042), for 

Model EC130B4 helicopters. Both ASBs 

specify modifying certain partnumbered LH and RH emergency 

flotation gear by adding protectors onto 

the rear bracket and supply couplings of 

the float installation. The ASBs specify 

following procedures in Aerazur Service 

Bulletin (SB) No. 25–69–87, dated 

March 14, 2011, for floats installed on 

Model EC120B helicopters and Aerazur 

SB No. 25–69–58, dated March 14, 2011, 

for floats installed on Model EC130B4 

helicopters. Each Aerazur SB is 

incorporated as an appendix to the 

corresponding Eurocopter ASB. 

Costs of Compliance 

We estimate that this AD will affect 

60 helicopters of U.S. Registry. Based on 

an average labor rate of $85 per workhour, we estimate that operators may 

incur the following costs to comply with 

this AD. Inspecting the floats for chafing 

will require about .5 hour, for a cost per 

helicopter of $43, and a cost to U.S. 

operators of $2,580. Modifying the floats 

with protective covers will require 

about 1 hour and required parts cost 

about $500, for a cost per helicopter of 

$585, and a cost to U.S. operators of 

$35,100. The total estimated cost of this 

AD is $628 per helicopter and $37,680 

for the U.S. operator fleet. 

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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52409 

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): 

2013–16–19 Eurocopter France: 

Amendment 39–17557; Docket No. 

FAA–2013–0341; Directorate Identifier 

2012–SW–025–AD. 

(a) Applicability 

(1) This AD applies to the following 

helicopters, certificated in any category: 

(i) Model EC120B helicopters with a lefthand (LH) emergency flotation gear, part 

number (P/N) 215674–0, 215674–1, or 

215674–2 installed, fitted with a float, P/N 

215481–0; or with a right-hand (RH) 

emergency flotation gear, P/N 215675–0, 

215675–1, or 215675–2 installed, fitted with 

a float, P/N 215482–0; and 

(ii) Model EC130B4 helicopters with a LH 

emergency flotation gear P/N 217227–0 

installed, fitted with a float P/N 217174–0; or 

with a RH emergency flotation gear P/N 

217228–0 installed, fitted with a float, P/N 

217195–0. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

chafing of the float due to contact with the 

protruding sections of the supply bars and 

banjo sections of the emergency flotation gear 

installation. This condition could result in 

the float becoming punctured, failure of the 

float to inflate, and subsequent loss of control 

of the helicopter during an emergency water 

landing. 

(c) Effective Date 

This AD becomes effective September 27, 

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 

(1) For emergency flotation gear that have 

accumulated 250 or more hours time-in 

service (TIS), within 50 hours TIS, 

accomplish the following: 

(i) Undo the Velcro tapes and remove the 

break laces. Remove the caps from the cover 

end. Unfold the cover. 

(ii) Inspect each float area in contact with 

the emergency flotation gear protruding parts 

(supply bar, banjo union, and fittings) for 

chafing as shown in Figure 1 of Eurocopter 

Alert Service Bulletin (ASB) No. 05A011, 

Revision 0, dated June 8, 2009, or Eurocopter 

ASB No. 05A008, Revision 0, dated June 8, 

2009, as appropriate for your model 

helicopter. 

(iii) If there is any chafing between the 

protruding parts and the float fabric, before 

further flight, inspect the flotation gear. 

(A) Unfold and visually inspect the float 

assemblies for any cuts, tears, punctures, or 

abrasion. Replace the cover if the internal 

polycarbonate sheet is cut or if the cover is 

cut or punctured. 

(B) Lightly inflate the floats to 

approximately 50 hectopascals through the 

manual inflating valve and inspect the fabric 

panels and girts for any cuts, tears, 

punctures, or abrasion. If there is a cut, tear, 

puncture, or any abrasion, repair the float. 

(2) For emergency floatation gear that have 

accumulated less than 250 hours TIS, on or 

before accumulating 300 hours TIS, inspect 

the float gear as described in paragraph 

(e)(1)(i) through (iii) of this AD. 

(3) Within 300 hours TIS: 

(i) For Model EC120B helicopters, install 

protectors on and re-identify the P/N of each 

LH and RH emergency floatation gear as 

described in the Operating Instructions, 

paragraph 2.C., of Aerazur Service Bulletin 

(SB) No. 25–69–87, dated March 14, 2011. 

The Aerazur SB is attached as an appendix 

to Eurocopter Alert Service Bulletin (ASB) 

No. EC120–25A026, Revision 0, dated July 

11, 2011. 

(ii) For Model EC130B4 helicopters, install 

protectors on and re-identify the P/N of each 

LH and RH emergency floatation gear as 

described in the Operating Instructions, 

paragraph 2., of Aerazur SB No. 25–69–58, 

dated March 14, 2011. The Aerazur SB is 

attached as an appendix to Eurocopter ASB 

No. EC130–25A042, Revision 0, dated July 

11, 2011. 

(f) 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. 

(g) Additional Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2011–0185, dated September 23, 2011, which 

can be found in the AD Docket on the 

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

(2) Eurocopter ASB No. EC120–25A026, 

Revision 0, dated July 11, 2011, and 

Eurocopter ASB No. EC130–25A042, 

Revision 0, dated July 11, 2011, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. You may view this service 

information at the 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. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 3212: Emergency Flotation Section. 

(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. 


emcdonald on DSK67QTVN1PROD with RULES
52410 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(i) Aerazur SB No. 25–69–58, dated March 

14, 2011, which is attached as an appendix 

to Eurocopter ASB No. EC130–25A042, 

Revision 0, dated July 11, 2011. 

(ii) Aerazur SB No. 25–69–87, dated March 

14, 2011, which is attached as an appendix 

to Eurocopter ASB No. EC120–25A026, 

Revision 0, dated July 11, 2011. 

(iii) Eurocopter ASB No. 05A008, Revision 

0, dated June 8, 2009. 

(iv) Eurocopter ASB No. 05A011, Revision 

0, dated June 8, 2009. 

(3) For Eurocopter and Aerazur 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 

that is incorporated by reference in the AD 

Docket on the Internet at http://

www.regulations.gov. 

(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 2, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19438 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0887; Directorate 

Identifier 2009–SW–02–AD; Amendment 39– 

17551; AD 2013–16–13] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH (ECD) 

Model BO–105A, BO–105C, BO–105S, 

BO–105LS A–1, BO–105LS A–3, MBB– 

BK 117 A–1, MBB–BK 117 A–3, MBB– 

BK 117 A–4, MBB–BK 117 B–1, MBB– 

BK–117 B–2, and MBB–BK 117 C–1 

helicopters to require inspections for 

corrosion or thread damage to each tail 

rotor balance weight (weight) and each 

tail rotor control lever (lever). This AD 

was prompted by a European Aviation 

Safety Agency (EASA) AD and a 

Transport Canada Civil Aviation (TCCA) 

AD, both issued based on a report that 

corrosion was detected on a weight in 

the area of the attachment thread on a 

model BO–105 helicopter. The actions 

of this AD are intended to detect 

corrosion and thread damage in the 

threaded area of the weight and lever, 

and to prevent failure of a weight or 

lever, separation of tail rotor parts, 

severe vibration, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective September 

27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 27, 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, TX 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 EASA and 

TCCA 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: 

Sharon Miles, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

sharon.y.miles@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 29, 2012, at 77 FR 52265, 

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 ECD Model BO–105A, BO–105C, BO– 

105S, BO–105LS A–1, BO–105LS A–3, 

MBB–BK 117 A–1, MBB–BK 117 A–3, 

MBB–BK 117 A–4, MBB–BK117 B–1, 

MBB–BK 117 B–2, and MBB–BK 117 C– 

1 helicopters with certain levers and 

weights installed. The NPRM proposed 

to require conducting repetitive visual 

inspections of each weight and lever 

and proposed procedures for installing 

a weight or lever. Additionally, the 

NPRM proposed allowable tolerances 

for corrosion or thread damage on the 

threaded portion of a weight or lever 

and proposed to require that a part with 

corrosion or mechanical damage in 

excess of allowable tolerances be 

replaced with an airworthy part. The 

proposed requirements were intended to 

detect corrosion and thread damage in 

the threaded area of a weight or lever, 

to prevent failure of a weight or lever, 

separation of tail rotor parts, severe 

vibration, and subsequent loss of control 

of the helicopter. 

The NPRM was prompted by AD No. 

2008–0206, dated November 25, 2008, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, and AD No. CF–2009– 

12, dated March 24, 2009, issued by the 

TCCA, which is the aviation authority 

for Canada. EASA issued AD No. 2008– 

0206 to correct the unsafe condition for 

ECD Model BO 105 A, BO 105 C, BO 

105 LS A–1, BO 105 D, BO 105 DS, BO 

105 DB, BO 105 DBS, BO 105 DB–4, BO 

105 DBS–4, BO 105 DBS–5, BO 105 S, 

MBB–BK 117 A–1, MBB–BK 117 A–3, 

MBB–BK 117 A–4, MBB–BK 117 B–1, 

MBB–BK 117 B–2, and MBB–BK 117 C– 

1 helicopters. The TCCA issued AD No. 

CF–2009–12 to correct the unsafe 

condition for Eurocopter Model BO 105 

LS A–3 helicopters. These ADs state 

that during a periodical inspection, 

corrosion was detected on the weights 

in the area of the attachment thread. 

Since the issuance of the Canadian AD, 

the type certificate for the Model BO 

105 LS A–3 has been transferred from 

Eurocopter Canada Limited to 

Eurocopter Deutschland (Germany). 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (77 FR 52265, August 29, 2012). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of Germany 

and are approved for operation in the 

United States. Pursuant to our bilateral 

agreement with Germany, 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 


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