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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52411 

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 we are updating some 

of the contact information to obtain 

service information from American 

Eurocopter Corporation and we are 

incorporating the two figures by 

reference instead of including them in 

our AD to meet current publication 

requirements. These minor changes are 

consistent with the intent of the 

proposals in the NPRM (77 FR 52265, 

August 29, 2012) and will not increase 

the economic burden on any operator 

nor increase the scope of this AD. 

Differences Between This AD and the 

EASA and TCCA ADs 

This AD does not provide an extra 60 

flight hours or 6 months beyond the 

repetitive compliance time of 600 flight 

hours or 48 months for the repetitive 

inspections. This AD only applies to 

those model helicopters typecertificated in the United States. 

Related Service Information 

Eurocopter issued Alert Service 

Bulletin (ASB) No. ASB–MBB–BK117– 

30–113, dated September 23, 2008, for 

all MBB BK117 model ‘‘A–1 to C–1’’ 

helicopters; ASB No. ASB BO105–30– 

116, dated September 23, 2008, for all 

Model BO105 helicopters ‘‘including 

BO105 CB–3 and BO105 CBS–5 KLH;’’ 

and Eurocopter Canada Limited issued 

ASB No. ASB BO 105 LS 30–12, dated 

December 12, 2008, for Model BO 105 

LS A–3 helicopters. These ASBs specify 

visually inspecting the weights and 

levers to detect corrosion or mechanical 

damage; corrosion at an advanced stage 

could destroy the threads. These ASBs 

also specify replacing damaged weights 

and levers that exceed certain limits. 

The actions described in the mandatory 

EASA and TCCA ADs are intended to 

correct the unsafe condition, identified 

in these ASBs, to ensure the continued 

airworthiness of these helicopters. 

Costs of Compliance 

We estimate that this AD will affect 

33 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs in order to comply with 

this AD. It will take approximately 4 

work-hours per helicopter to remove, 

inspect, and install 2 lever assemblies 

and 4 weights per helicopter at an 

average labor rate of $85 per work-hour. 

Based on these figures, we estimate the 

inspection cost of this AD will cost $340 

per helicopter or $11,220 on U.S. 

operators per inspection cycle. The 

required parts will cost about $5,332 per 

helicopter. We estimate the cost for 

replacement will be $5,672 per 

helicopter, assuming both lever 

assemblies and all 4 weights are 

replaced. 

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): 

2013–16–13 Eurocopter Deutschland GmbH 

(ECD): Amendment 39–17551; Docket 

No. FAA–2012–0887; Directorate 

Identifier 2009–SW–02–AD. 

(a) Applicability 

This AD applies to Model BO–105A, BO– 

105C, BO–105S, and BO–105LS A–1 

helicopters, with a tail rotor control lever 

(lever), part number (P/N) 105–317231, 105– 

317365, 105–31736, 105–31767, 105–31728, 

or 1121–31730, with tail rotor balance weight 

(weight) P/N 117–31715.01, 117–31715.02, 

105–31728.03, 105–31732.07, or 105– 

31732.08; Model BO–105LS A–3 helicopters, 

with lever P/N 105–31736 or 105–31767, 

with weight P/N 117–31715.01, 117– 

31715.02, B642M1011 201, or 105– 

317171.10; and Model 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 lever P/N 117– 

31730, 117–317361, or 105–31736, with 

weight P/N 117–31714.07, 117–31715.01, 

117–31720.01, or 117–31730.02, certificated 

in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

corrosion or thread damage in the threaded 

area of a lever or weight. This condition 

could result in failure of a weight or lever, 

separation of a tail rotor part, severe tail rotor 

vibration, and subsequent loss of control of 

the helicopter. 

(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 

Within 100 hours time-in-service (TIS) or 

2 months, whichever occurs first, and 

thereafter at intervals not to exceed 600 hours 

TIS or 48 months, whichever occurs first: 

(1) Remove the weights from the lever as 

depicted in Figure 1 of Eurocopter Alert 

Service Bulletin (ASB) No. ASB–MBB– 

BK117–30–113, dated September 23, 2008; 

ASB No. ASB BO105–30–116, dated 

September 23, 2008; or ASB No. ASB BO 105 

LS 30–12, dated December 12, 2008; as 

applicable to your model helicopter. Apply 

marks to the weights before they are removed 

in order to be able to re-establish the correct 

assignment and the old installation position 

towards the lever when the weights are 

installed. 


emcdonald on DSK67QTVN1PROD with RULES
52412 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(2) Visually inspect each weight and lever 

for corrosion and damage in the threaded 

areas as depicted in Figure 2 of ASB No. 

ASB–MBB–BK117–30–113, dated September 

23, 2008; ASB No. ASB BO105–30–116, 

dated September 23, 2008; or ASB No. ASB 

BO 105 LS 30–12, dated December 12, 2008; 

as applicable to your model helicopter. 

(i) If there is no corrosion or thread damage 

on either the weight or lever, before further 

flight, reinstall the weight by following 

paragraph (e)(3) of this AD. 

(ii) If there is corrosion or thread damage 

on the threaded portion of a weight: 

(A) If the total area of corrosion or thread 

damage, or both, covers less than 25 percent 

of the length of the threaded area, the weight 

can be threaded (screwed) onto the lever, and 

the cylindrical mating surface has no 

damage, before further flight, remove the 

corrosion and reinstall the weight by 

following paragraph (e)(3) of this AD. 

(B) If the total area of corrosion or thread 

damage, or both, covers 25 percent or more 

of the length of the threaded area, the weight 

cannot be threaded (screwed) onto the lever, 

or the cylindrical mating surface has damage, 

before further flight, replace the weight with 

an airworthy weight by following paragraph 

(e)(3) of this AD. 

(iii) If there is corrosion or thread damage 

on the threaded portion of the lever, polish 

out the corrosion and thread damage using a 

polishing cloth 600 and: 

(A) If the thread depth does not exceed 0.3 

millimeter (mm) and the diameter of the 

lever in the area before the threaded area is 

not less than 9.95 mm after polish out, before 

further flight, install airworthy weights to the 

lever by following paragraph (e)(3) of this 

AD. 

(B) If the thread depth is 0.3 mm or greater 

or the diameter of the lever in the area before 

the threaded area is less than 9.95 mm after 

polish out, before further flight, replace the 

lever with an airworthy lever. 

(3) Apply corrosion preventive paste onto 

the thread of the lever and install weights to 

the lever as depicted in Figure 1 of ASB No. 

ASB–MBB–BK117–30–113, dated September 

23, 2008; ASB No. ASB BO105–30–116, 

dated September 23, 2008; or ASB No. ASB 

BO 105 LS 30–12, dated December 12, 2008; 

as applicable to your model helicopter. 

Ensure during installation of the weights that 

the weights are correctly assigned and 

installed to the control lever in accordance 

with the applied marks. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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. 2008–0206, dated November 25, 2008, 

and in Transport Canada Civil Aviation 

(TCCA) AD No. CF–2009–12, dated March 

24, 2009. You may view the EASA and the 

TCCA AD on the Internet at http://

www.regulations.gov in Docket No. FAA– 

2012–0887. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6420, Tail Rotor Head. 

(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 (ASB) 

No. ASB–MBB–BK117–30–113, dated 

September 23, 2008. 

(ii) Eurocopter ASB No. ASB BO105–30– 

116, dated September 23, 2008. 

(iii) Eurocopter ASB No. ASB BO 105 LS 

30–12, dated December 12, 2008. 

(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, TX 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

(202) 741–6030, or go to: http://

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

Issued in Fort Worth, Texas, on August 2, 

2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19442 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–2013–0020; Directorate 

Identifier 2010–SW–107–AD; Amendment 

39–17558; AD 2013–16–20] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH (ECD) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for ECD 

Model MBB–BK 117 C–2 helicopters. 

This AD requires inspecting the rigging 

of the power-boosted control system 

and, if there is a nonparallel gap 

between the rigging wedges and the 

inner sleeves, performing a rigging 

procedure. This AD was prompted by 

the discovery, during rigging of the 

main rotor controls, of movement of the 

longitudinal main rotor actuator piston 

after shut-down of the external pump 

drive. Such movement could cause 

incorrect rigging results. The actions of 

this AD are intended to prevent 

incorrect rigging results, which could 

impair freedom of movement of the 

upper controls and subsequent reduced 

control of the helicopter. 

DATES: This AD is effective September 

27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document 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, any 

incorporated-by-reference service 

information, the foreign authority’s AD, 

the economic evaluation, any comments 

received, and other information. The 


emcdonald on DSK67QTVN1PROD with RULES