43970 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 

Background 

The ‘‘primary’’ category for aircraft 

was created specifically for the simple, 

low performance personal aircraft. 

Section 21.17(f) provides a means for 

applicants to propose airworthiness 

standards for their particular primary 

category aircraft. The FAA procedure 

establishing appropriate airworthiness 

standards includes reviewing and 

possibly revising the applicant’s 

proposal, publication of the submittal in 

the Federal Register for public review 

and comment, and addressing the 

comments. After all necessary revisions, 

the standards are published as approved 

FAA airworthiness standards. 

Accordingly, the applicant, AutoGyro, 

has submitted a request to the FAA to 

include the following: 

Proposed Airworthiness Standards for 

Acceptance Under the Primary 

Category Rule 

For Aircraft Certification and the 

Powerplant Installation: 

Section T Light Gyroplanes, of the 

British Civil Airworthiness 

Requirements, Issue 3, dated August 12, 

2005. 

14 CFR 27.853(a) and (c)(1) Amdt 27– 

37 Compartment Interior; §§ 23.735(a) 

through (c) Amdt 23–62 Brakes except 

that the reference to 23.75 is replaced 

with Section T75 of BCAR Section T, 

Issue 3; §§ 27.735(a) and (c)(1) Amdt 

27–21 Brakes; §§ 27.1365(b) and (c) 

Amdt 27–35 Electrical Cables; and 

§ 27.1561(a) Safety Equipment, as 

applicable to these aircraft. 

For Engine Assembly Certification: 

ASTM F2339–06 (2009), ‘‘Standard 

Practice for Design and Manufacture of 

Reciprocating Spark Ignition Engines for 

Light Sport Aircraft,’’ except paragraph 

A1.1.3. 

For Propeller Certification: 

Section T Light Gyroplanes, of the 

British Civil Airworthiness 

Requirements, Issue 3, dated August 12, 

2005; ASTM F2506–10 (2009), 

‘‘Standard Specification for Design and 

Testing of Fixed-Pitch or Ground 

Adjustable Light Sport Aircraft 

Propellers,’’ paragraph 5.5 Propeller 

Strength and Endurance and Section 6 

Tests and Inspections. 

Issued in Fort Worth, Texas on July 16, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18221 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2994; Directorate 

Identifier 2014–SW–057–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters Deutschland GmbH 

(Formerly Eurocopter Deutschland 

GmbH) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for Airbus 

Helicopters Deutschland GmbH (Airbus) 

(formerly Eurocopter Deutschland 

GmbH) Model MBB–BK 117C–2 

helicopters with an external mounted 

hoist system wiring harness installed. 

This proposed AD would require 

inspecting the hoist control pendant 

wiring harness for chafing, and if there 

is chafing, before the next hoist 

operation, replacing the wiring harness. 

This proposed AD would also require a 

installing a protection sleeve on the 

hoist control pendant wiring harness. 

This proposed AD is prompted by an 

uncommanded hoist release involving 

chafing on the wiring harness of the 

hoist control pendant and on the wiring. 

The proposed actions are intended to 

prevent loss of an external load or 

person from the hoist resulting in injury 

to persons being lifted and loss of 

control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 22, 

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 the referenced 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: 

George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 

Hillwood Pkwy., Fort Worth, TX 76177; 

telephone (817) 222–5110; email 

george.schwab@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 

EASA, which is the Technical Agent 

for the Member States of the European 


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Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 43971 

Union, issued EASA AD No. 2014–0211, 

dated September 19, 2014, to correct an 

unsafe condition for the Airbus Model 

MBB–BK117 C–2 helicopters ‘‘equipped 

with optional equipment external 

mounted hoist system.’’ EASA advises 

that an uncommanded hoist cable cut 

occurred and that an investigation 

revealed chafing on the wiring harness 

of the hoist control pendant and on the 

wiring of the +28V wire of the stand-by 

horizon inside the middle ceiling panel. 

The wire of the stand-by horizon 

contacted the hoist control pendant 

wiring harness and caused the 

uncommanded cable cut. EASA also 

states that this condition, if not detected 

and corrected, could lead to load 

release, possibly resulting in injury to a 

human load or to the persons on the 

ground. EASA issued AD No. 2014– 

0211 requiring an inspection and 

modification of the wiring harness to 

correct this unsafe condition. 

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 

Airbus Helicopters issued Alert 

Service Bulletin (ASB) MBB–BK117 C– 

2–88A–009, Revision 0, on June 18, 

2014, specifying a visual inspection of 

the hoist control pendant wiring harness 

for chafing. If there is heavy chafing, 

before the next hoist operation, the ASB 

specifies replacing the wiring harness. 

The ASB also specifies a ‘‘retrofit’’ of an 

additional protective sleeve for the hoist 

control pendant wiring harness. 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 NPRM. 

Proposed AD Requirements 

This proposed AD would require: 

• Before the next hoist operation: 

Æ Visually inspecting the hoist 

control pendant wiring harness for 

chafing, and replacing the wiring 

harness if there is chafing on the wiring 

harness protection sleeve and any 

internal wiring is visible, or if there is 

chafing on any internal wire. 

Æ Installing each wiring harness cable 

tie so that the cable tie heads do not 

contact any adjacent parts or wiring 

harnesses. 

• Within the next 100 hours time-inservice, installing a protection sleeve on 

the wiring harness and inspecting each 

cable tie for correct installation. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 109 helicopters of U.S. 

Registry. 

We estimate that operators may incur 

the following costs in order to comply 

with this AD. Labor costs are estimated 

at $85 per work hour. We estimate 1.5 

work hours to inspect the hoist control 

pendant wiring harness at a cost of 

about $128 per helicopter and $13,952 

for the fleet. We estimate 2 work hours 

to install a protection sleeve and inspect 

the cable ties and $125 for required 

parts at a cost of $295 per helicopter and 

$32,155 for the fleet. If required, we 

estimate a minimal amount of time for 

labor and $224 for required parts to 

replace a wiring harness. 

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: 

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): 

Airbus Helicopters Deutschland GmbH 

(formerly Eurocopter Deutschland 

GmbH): Docket No. FAA–2015–2994; 

Directorate Identifier 2014–SW–057–AD. 

(a) Applicability 

This AD applies to Model MBB–BK 117 C– 

2 helicopters with an external mounted hoist 

system wiring harness part number (P/N) 

B851M2063101 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

chafing on the wiring harness or wiring of a 

hoist control pendant. This condition could 

result in loss of an external load or person 

from the hoist resulting in injury to persons 

being lifted and loss of control of the 

helicopter. 

(c) Comments Due Date 

We must receive comments by September 

22, 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) Before the next hoist operation: 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
43972 Federal Register / Vol. 80, No. 142 / Friday, July 24, 2015 / Proposed Rules 

(i) Visually inspect the hoist control 

pendant wiring harness (wiring harness) for 

chafing. The wiring harness is shown in 

Figure 1 of Airbus Helicopters Alert Service 

Bulletin (ASB) MBB–BK117 C–2–88A–009, 

Revision 0, dated June 18, 2014 (MBB–BK117 

C–2–88A–009). If there is chafing on the 

wiring harness protection sleeve such that 

any internal wiring is visible, or if there is 

chafing on any internal wire, replace the 

wiring harness. 

(ii) Install each wiring harness cable tie so 

that the cable tie heads do not contact any 

adjacent parts or wiring harnesses, as shown 

in Figure 3 of ASB MBB–BK117 C–2–88A– 

009. 

(2) Within the next 100 hours time-inservice, install a protection sleeve on the 

wiring harness and inspect each cable tie by 

following the Accomplishment Instructions, 

paragraph 3.B.3, of ASB MBB–BK117 C–2– 

88A–009. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Regulations Group, FAA, 

may approve AMOCs for this AD. Send your 

proposal to: George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 10101 Hillwood 

Pkwy., Fort Worth, TX 76177; telephone 

(817) 222–5110; email george.schwab@

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) 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.airbushelicopters.com/techpub. You 

may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 10101 

Hillwood Pkwy., Room 6N–321, Fort Worth, 

TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0211, dated September 19, 2014. 

You may view the EASA AD on the Internet 

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

FAA–2015–2994. 

(h) Subject 

Joint Aircraft System Component (JASC) 

Code: 5397 Fuselage Wiring. 

Issued in Fort Worth, Texas, on July 15, 

2015. 

Bruce E. Cain, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–18049 Filed 7–23–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2959; Directorate 

Identifier 2015–NM–008–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This proposed AD was 

prompted by reports indicating that the 

ram air turbine (RAT) assembly may fail 

to operate if deployed at low airspeeds. 

This proposed AD would require 

replacing either the RAT pump and 

control module assembly or the entire 

RAT assembly. We are proposing this 

AD to prevent failure of the RAT 

assembly to operate at low air speeds. 

The volume fuse on the RAT assembly 

may be activated in-flight before the 

RAT is deployed. This may lead to 

improper pump hydraulic pressure 

offloading when the RAT is needed. 

Failure of the RAT to operate in an all 

engine out event would result in loss of 

control of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 8, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. You may view 

this referenced 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA 2015– 

2959. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

2959; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6479; fax: 425–917–6590; email: 

sean.schauer@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–2959; Directorate Identifier 2015– 

NM–008–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

An engineering review by Boeing’s 

RAT supplier discovered that the RAT 

assembly may fail to operate if deployed 

at low airspeeds. A hydraulic fuse in the 

RAT control module is intended to 

remain open to enable RAT spin-up at 

low air speeds by off-loading the RAT 

hydraulic pump. After the RAT is 

spinning, the fuse sets and the pump 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS