Federal Register / Vol. 80, No. 117 / Thursday, June 18, 2015 / Rules and Regulations 34831 

effective date of this AD using Boeing Service 

Bulletin 777–52–0053, Revision 1, dated 

September 26, 2013; and Eaton Service 

Bulletin 692D100–52–4, Revision 2, dated 

August 1, 2013. This service information is 

not incorporated by reference in this AD. 

(k) Parts Installation Prohibition 

As of the effective date of this AD, no 

rotary actuator having Boeing part number 

S135W132–3 (supplier part number 

692D100–13) may be installed on any 

airplane. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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 manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Susan Monroe, Aerospace Engineer, 

Cabin Safety and Environmental Systems 

Branch, ANM–150S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6457; fax: 425–917–6590; email: 

susan.l.monroe@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the applicable addresses 

specified in paragraphs (n)(3), (n)(4), and 

(n)(5) of this AD. 

(n) 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) Boeing Service Bulletin 767–52A0100, 

Revision 3, dated January 19, 2015. 

(ii) Boeing Service Bulletin 777–52–0053, 

Revision 2, dated January 19, 2015. 

(iii) Eaton Service Bulletin 692D100–52–4, 

Revision 3, dated August 14, 2014. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) For Eaton service information identified 

in this AD, contact Eaton Corporation, 

Aerospace Operations, 3 Park Plaza, Suite 

1200, Irvine, CA 92614; telephone 949–253– 

2100; fax 949–253–2111; Internet http://

www.eaton.com. 

(5) You may view this service information 

at FAA, the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(6) 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 June 9, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14703 Filed 6–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0577; Directorate 

Identifier 2013–SW–042–AD; Amendment 

39–18184; AD 2015–12–09] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

July 6, 2015 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model EC135P1, EC135T1, 

EC135P2, EC135T2, EC135P2+, 

EC135T2+, and MBB–BK 117 C–2 

helicopters. This AD requires inspecting 

certain washers for movement and 

making appropriate repairs if the 

washers move. This AD was prompted 

by play found between the Smart 

Electro Mechanical Actuator (SEMA) 

and the control rod during installation 

work on a helicopter. The actions of this 

AD are intended to prevent loss of 

concerned control axis and subsequent 

loss of control of the helicopter. 

DATES: This AD is effective July 23, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of July 23, 2015. 

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.airbus

helicopters.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: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 18, 2014, at 79 FR 48707, 

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 Airbus Helicopters Model EC135P1, 

EC135T1, EC135P2, EC135T2, 

EC135P2+, EC135T2+, and MBB–BK 

117 C–2 helicopters. The NPRM 

proposed to require inspecting certain 

washers for movement in the 

attachment hardware that connects the 

SEMA and the control rod of the 

longitudinal, lateral, and yaw actuators. 

If a washer can be moved, the NPRM 

proposed replacing the four screws, 

installing two additional washers, and 

torque-tightening the screws. The 

proposed requirements were intended to 

prevent loss of concerned control axis 


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34832 Federal Register / Vol. 80, No. 117 / Thursday, June 18, 2015 / Rules and Regulations 

and subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2013–0176, dated August 7, 2013, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Eurocopter Deutschland 

GmbH Model EC 135 P1 (CDS), EC 135 

P1 (CPDS), EC 135 P2+, EC 135 P2 

(CPDS), EC 135 T1 (CDS), EC 135 T1 

(CPDS), EC 135 T2+, EC 135 T2 (CPDS), 

EC 635 P2+, EC 635 T1 (CPDS), EC 635 

T2+, and MBB–BK 117 C–2 helicopters. 

EASA advises that during installation 

work on a helicopter, it was discovered 

that it was not possible to install 

attachment hardware on a threaded 

blind borehole between the SEMA and 

the control rod without play. EASA 

advises that this condition, if not 

detected and corrected, could lead to 

loss of the concerned control axis, 

possibly resulting in loss of helicopter 

control. For these reasons, EASA AD 

No. 2013–0176 requires a one-time 

inspection of the affected SEMA 

attachment hardware to detect improper 

connection and play and, depending on 

the findings, replacement of the affected 

hardware. After the issuance of EASA 

AD No. 2013–0176, Eurocopter 

Deutschland GmbH changed its name to 

Airbus Helicopters Deutschland GmbH. 

Comments 

After our NPRM (79 FR 48707, August 

18, 2014) was published, we received 

comments from one commenter. 

Request 

Air Methods stated that the proposed 

AD requires compliance with Revision 1 

of the service information and requested 

that previous compliance with the 

original service information, Revision 0, 

be included as an acceptable method of 

compliance in the AD. 

We agree. We have added a paragraph 

to the AD giving credit for previous 

compliance with Revision 0 of the 

service information. 

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, reviewed the 

relevant information, considered the 

comment received, and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Differences Between This AD and the 

EASA AD 

The EASA AD applies to Eurocopter 

Model EC635P2+, EC635T1 and 

EC635T2+ helicopters. This AD does 

not apply to these model helicopters 

because they have no FAA type 

certificate. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter reported in Alert Service 

Bulletins (ASBs) EC135–22A–015, 

Revision 1, dated January 28, 2013, and 

MBB BK117 C–2–22A–009, Revision 1, 

dated August 3, 2009, that it was 

discovered during the installation work 

on a helicopter that it was not possible 

to establish attachment hardware on a 

threaded blind borehole between the 

SEMA and the control rod without play. 

The ASBs state that ‘‘unfavourable 

adding of the tolerances’’ of the 

individual attachment hardware 

elements caused the screw to push 

against the bottom of the threaded blind 

borehole on the SEMA, preventing any 

clamping force on the screw head. The 

ASBs call for inspecting the SEMA 

attachment hardware connected to their 

respective control rods for play and 

making the proper adjustments to 

eliminate any play. 

This service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section of 

this AD. 

Costs of Compliance 

We estimate that this AD affects 385 

helicopters of U.S. Registry and that 

labor costs average $85 per work hour. 

Based on these estimates, we expect the 

following costs: 

• Inspecting for movement of the 

washers requires 1.5 work hours for a 

labor cost of $128 per helicopter and 

$49,280 for the U.S. fleet. 

• Replacing the screws and related 

work requires an additional 0.5 workhours for a labor cost of $43. Screws 

cost $4 each while washers cost $10 

each. We estimate the cost at $79 per 

repair. 

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): 


tkelley on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 80, No. 117 / Thursday, June 18, 2015 / Rules and Regulations 34833 

2015–12–09 Airbus Helicopters 

Deutschland GmbH (Previously 

Eurocopter Deutschland GmbH) (Airbus 

Helicopters): Amendment 39–18184; 

Docket No. FAA–2014–0577; Directorate 

Identifier 2013–SW–042–AD. 

(a) Applicability 

This AD applies to Airbus Helicopters 

Model EC135P1, EC135T1, EC135P2, 

EC135T2, EC135P2+, EC135T2+, and MBB– 

BK 117 C–2 helicopters, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

loose attachment hardware between the 

Smart Electro Mechanical Actuator (SEMA) 

and a control rod. This condition could result 

in loss of the control axis and subsequent 

loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective July 23, 2015. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 50 hours time in service (TIS), 

for Model EC135P1, EC135T1, EC135P2, 

EC135T2, EC135P2+, and EC135T2+ 

helicopters, do the following: 

(i) Using Figure 1 and Figure 2 of 

Eurocopter Alert Service Bulletin EC135– 

22A–015, Revision 1, dated January 28, 2013 

(ASB EC135–22A–015) as reference, inspect 

the attachment hardware between the SEMA 

and the longitudinal actuator control rod to 

determine whether any of the washers can be 

moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, part number (P/N) EN2139–05016, 

to connect the SEMA with the control rod. 

Torque-tighten each screw to 5–6 Nm. 

(ii) Using Figure 1 and Figure 2 of ASB 

EC135–22A–015 as reference, inspect the 

attachment hardware between the SEMA and 

the lateral actuator control rod to determine 

whether any of the washers can be moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm. 

(iii) Using Figure 1, Figure 3, and Figure 

4 of ASB EC135–22A–015 as reference, 

inspect the attachment hardware between the 

SEMA and the yaw actuator control rod to 

determine whether any of the washers can be 

moved. 

(A) If no washer can be moved, no further 

action is needed. 

(B) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm. 

(2) Within 50 hours TIS, for Model MBB 

BK117 C–2 helicopters, using Figure 1 of 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 1, dated 

August 3, 2009, as reference, inspect the 

attachment hardware between the YawSEMA and the Yaw-SEMA control rod to 

determine whether any of the washers can be 

moved. 

(i) If no washer can be moved, no further 

action is needed. 

(ii) If a washer can be moved, replace the 

four screws and install two additional 

washers, P/N EN2139–05016, to connect the 

SEMA with the control rod. Torque-tighten 

each screw to 5–6 Nm and apply 

polyurethane lacquer onto the attachment 

hardware. 

(f) Credit for Previous Actions 

If you performed the actions in Eurocopter 

Alert Service Bulletin EC135–22A–015, 

Revision 0, dated May 13, 2018, or 

Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 0, May 13, 

2008, before the effective date of this AD, you 

met the requirements of this AD. 

(g) 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, Regulations and 

Policy Group, 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. 

(h) Additional Information 

The subject of this AD is addressed in the 

European Aviation Safety Agency (EASA) AD 

No. 2013–0176, dated August 7, 2013. You 

may view the EASA AD on the Internet at 

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

FAA–2014–0577. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2213, Flight Controller. 

(j) 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 

EC135–22A–015, Revision 1, dated January 

28, 2013. 

(ii) Eurocopter Alert Service Bulletin MBB 

BK117 C–2–22A–009, Revision 1, dated 

August 3, 2009. 

(3) For Airbus Helicopters 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://www.

archives.gov/federal-register/cfr/ibr-locations

.html. 

Issued in Fort Worth, Texas, on June 9, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14852 Filed 6–17–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2015–0552] 

Drawbridge Operation Regulation; 

Chambers Creek, Steilacoom, WA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of deviation from 

drawbridge regulation. 

SUMMARY: The Coast Guard has issued a 

temporary deviation from the operating 

schedule that governs the Burlington 

Northern Santa Fe (BNSF) Chambers 

Creek Railway Bridge across Chambers 

Creek, mile 0.0, at Steilacoom, 

Washington. The deviation is necessary 

to minimize the effects of train noise on 

the 2015 U.S. Golf Association 

Championship held at Chambers Bay 

Golf Course. This deviation allows the 

bridge to open only upon 1 hour notice 

from 7 a.m. to 4 p.m. on June 14, 2015 

and 7 a.m. to 5 p.m. each day from June 

15, 2015 to June 22, 2015. At all other 

times the bridge will open on signal in 

accordance with its normal operating 

regulation. 

DATES: This deviation is effective 

without actual notice from June 18, 

2015 to 5 p.m. on June 22, 2015. For the 

purposes of enforcement, actual notice 

will be used from 7 a.m. on June 14, 

2015, until June 18, 2015. 

ADDRESSES: The docket for this 

deviation, [USCG–2015–0552] is 

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


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