This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

45900 

Vol. 80, No. 148 

Monday, August 3, 2015 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0577; Directorate 

Identifier 2013–SW–042–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to revise 

airworthiness directive (AD) 2015–12– 

09 for Airbus Helicopters Model 

EC135P1, EC135T1, EC135P2, EC135T2, 

EC135P2+, EC135T2+, and MBB–BK 

117 C–2 helicopters. AD 2015–12–09 

currently requires inspecting certain 

washers for movement and making the 

appropriate repairs if the washers move. 

As published, AD 2015–12–09 

references an incorrect date for the 

service information in the Credit for 

Previous Actions section. This proposed 

AD would correct the error while 

retaining the requirements of AD 2015– 

12–09. These proposed actions are 

intended to prevent loss of concerned 

control axis and subsequent loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by August 18, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 proposed AD, the 

European Aviation Safety Agency 

(EASA) AD, the economic evaluation, 

any comments received and other 

information. The street address for the 

Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this proposed AD, contact Airbus 

Helicopters, Inc., 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

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

(972) 641–3775; or at http://

www.airbushelicopters.com/techpub. 

You may review service information at 

the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood 

Pkwy, Room 6N–321, Fort Worth, TX 

76177. 

FOR FURTHER INFORMATION CONTACT: Matt 

Wilbanks, Aviation Safety Engineer, 

Regulations and Policy Group, 

Rotorcraft Directorate, Rotorcraft 

Directorate, FAA, 10101 Hillwood 

Pkwy, Fort Worth, TX 76177; telephone 

(817) 222–5110; email matt.wilbanks@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On June 18, 2015, at 80 FR 34831, the 

Federal Register published AD 2015– 

12–09, Amendment 39–18184, for 

Airbus Helicopters Model EC135P1, 

EC135T1, EC135P2, EC135T2, 

EC135P2+, EC135T2+, and MBB–BK 

117 C–2 helicopters. AD 2015–12–09 

requires inspecting certain washers for 

movement in the attachment hardware 

that connects the Smart Electro 

Mechanical Actuator (SEMA) and the 

control rod of the longitudinal, lateral, 

and yaw actuators. If a washer can be 

moved, AD 2015–12–09 requires 

replacing the four screws, installing two 

additional washers, and torquetightening the screws. AD 2015–12–09 

was prompted by play found between 

the SEMA and the control rod during 

installation work on a helicopter. The 

requirements of AD 2015–12–09 are 

intended to prevent loss of concerned 

control axis and subsequent loss of 

control of the helicopter. 

AD 2015–12–09 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 

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Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Proposed Rules 45901 

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. 

When AD 2015–12–09 was published, 

an incorrect reference to the date of 

Eurocopter Alert Service Bulletin (ASB) 

EC135–22A–015, Revision 0, dated May 

13, 2008, appeared in the text of the 

rule. Specifically, AD 2015–12–09 

includes the following under paragraph 

(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.’’ As published, the reference to May 

13, 2018, is incorrect. The correct date 

for Eurocopter ASB EC135–22A–015, 

Revision 0, is May 13, 2008. 

The FAA has determined that it is 

appropriate to revise AD 2015–12–09 to 

correct the date for Eurocopter ASB 

EC135–22A–015, Revision 0. Further, 

we are changing the physical address of 

the FAA Southwest Regional Office 

throughout the NPRM and the email 

address in paragraph (g), Alternative 

Methods of Compliance (AMOCs). Since 

AD 2015–12–09 was issued, the FAA 

Southwest Regional Office has relocated 

and a group email address has been 

established for requesting an FAA 

AMOC for a helicopter of foreign design. 

We are not proposing to change any 

other part of the preamble or regulatory 

information. The final rule would be 

reprinted in its entirety for the 

convenience of affected operators. 

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 its 

AD. We are proposing this AD because 

we evaluated all known relevant 

information and determined that an 

unsafe condition is likely to exist or 

develop on other products of the same 

type design. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter reported in 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 proposed AD. 

Proposed AD Requirements 

This proposed AD would continue to 

require, within 50 hours time-in-service, 

inspecting whether the washers can be 

moved in the attachment hardware that 

connects the SEMA and the control rod 

of the longitudinal, lateral, and yaw 

actuators. For Model MBB BK117 C–2 

helicopters, this inspection is only for 

the hardware connecting the YawSEMA and the Yaw-SEMA control rod. 

If none of the washers can be moved, 

then no further action is needed. If a 

washer can be moved, then this 

proposed AD would require replacing 

the four screws, installing two 

additional washers, and torquetightening the screws to 5–6 Nm. 

Differences Between This Proposed AD 

and the EASA AD 

The EASA AD applies to Eurocopter 

Model EC635P2+, EC635T1 and 

EC635T2+ helicopters. This proposed 

AD does not apply to these model 

helicopters because they have no FAA 

type certificate. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 385 helicopters of U.S. 

Registry and that labor costs would 

average $85 per work-hour. Based on 

these estimates, we expect the following 

costs: 

• Inspecting for movement of the 

washers would require 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 would require an additional 0.5 

work-hours for a labor cost of $43. 

Screws would cost $4 each while 

washers would cost $10 each. We 

estimate the cost would be $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 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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, I certify 

this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

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 proposed 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

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45902 Federal Register / Vol. 80, No. 148 / Monday, August 3, 2015 / Proposed Rules 

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 

removing Airworthiness Directive (AD) 

2015–12–09, Amendment 39–18184 (80 

FR 34831, June 18, 2015), and adding 

the following new AD: 

Airbus Helicopters Deutschland GmbH 

(Previously Eurocopter Deutschland 

GmbH) (Airbus Helicopters): 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) Comments Due Date 

We must receive comments by August 18, 

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) Affected ADs 

This AD revises AD 2015–12–09, 

Amendment 39–18184 (80 FR 34831, June 

18, 2015). 

(g) Credit for Previous Actions 

If you performed the actions in Eurocopter 

Alert Service Bulletin EC135–22A–015, 

Revision 0, dated May 13, 2008, 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. 

(h) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Regulations and Policy 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

10101 Hillwood Pkwy, Fort Worth, TX 

76177; telephone (817) 222–5110; email 9- 

ASW-FTW-AMOC-Requests@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. 

(i) 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. 

(j) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2213, Flight Controller 

Issued in Fort Worth, Texas, on July 24, 

2015. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18865 Filed 7–31–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2967; Directorate 

Identifier 2014–NM–072–AD] 

RIN 2120–AA64 

Airworthiness Directives; DASSAULT 

AVIATION Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2002–23– 

20, for certain Dassault Aviation Model 

FALCON 900EX and MYSTERE– 

FALCON 900 airplanes. AD 2002–23–20 

currently requires repetitive operational 

tests of the flap asymmetry detection 

system to verify proper functioning, and 

repair if necessary; repetitive 

replacement of the inboard flap 

jackscrews with new or reconditioned 

jackscrews; and repetitive measurement 

of the screw/nut play of the jackscrews 

on the inboard and outboard flaps to 

detect discrepancies, and corrective 

action if necessary. AD 2002–23–20 

currently requires a revision of the 

airplane flight manual. Since we issued 

AD 2002–23–20, the maintenance 

manual has been revised. This proposed 

AD would require revising the 

maintenance or inspection program, as 

applicable, to include the maintenance 

tasks and airworthiness limitations 

specified in the Airworthiness 

Limitations section of the airplane 

maintenance manual. This proposed AD 

also removes the Model FALCON 900EX 

airplanes from the applicability of the 

existing AD. We are proposing this AD 

to prevent reduced structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 17, 

2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

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