67020 Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations 

Note 1 to paragraph (f)(6) of this AD: 

Appendix 2 of Embraer Phenom Alert 

Service Bulletin No. 505–32–A011, dated 

September 13, 2013, includes Meggitt 

Aircraft Braking System Service Bulletin No. 

SB–32–1625, dated September 13, 2013. 

(7) For the purposes of this AD, a GVI is 

a visual examination of an interior or exterior 

area, installation or assembly, to detect 

obvious damage, failure, or irregularity. This 

level of inspection is made from within 

touching distance, unless otherwise 

specified. A mirror may be necessary to 

enhance visual access to all exposed surfaces 

in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or drop-light. It may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(8) For the purposes of this AD, a DET is 

an intensive examination of a specific item, 

installation or assembly, to detect damage, 

failure, or irregularity. Available lighting is 

normally supplemented with a direct source 

of good lighting at an intensity deemed 

appropriate. Inspection aids such as mirrors, 

magnifying lenses, etc., may be necessary. 

Surface cleaning and elaborate access 

procedures may be required. 

(9) After the effective the date of this AD, 

do not install on any airplane a brake 

assembly P/N DAP00097–01 or P/N 

DAP00097–02 unless it is inspected per the 

requirements of this AD and continues to be 

crack free or the cracks do not exceed the 

allowable limits. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Jim Rutherford, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4165; fax: (816) 329– 

4090; email: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(h) Related Information 

Refer to MCAI Agencia Nacional De 

Aviacoa Civil (ANAC) AD No.: 2013–09–01, 

dated September 26, 2013, for related 

information. You may examine the MCAI on 

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

searching for and locating it in Docket No. 

FAA–2013–0936. 

(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) Embraer Phenom Alert Service Bulletin 

No. 505–32–A011, dated September 13, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact EMBRAER S.A., Phenom 

Maintenance Support, Avenida Brigadeiro 

Faria Lima, 2170, Putim, CEP: 12227–901, 

Sao Jose dos Campos, Sao Paulo, Brasil; 

phone: (+55 12) 3927–1000; Fax: (+55 12) 

3927–6600, Ext. 1448; email: 

phenom.reliability@embraer.com.br; Internet: 

http://www.embraerexecutivejets.com/enUS/customer-support/Pages/Service-CenterNetwork.aspx. 

(4) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(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 Kansas City, Missouri, on 

October 30, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–26474 Filed 11–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0519; Directorate 

Identifier 2010–SW–068–AD; Amendment 

39–17623; AD 2013–20–17] 

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 BO105C (C–2 and CB–2 Variants) 

and BO105S (CS–2 and CBS–2 Variants) 

helicopters with a certain third stage 

turbine wheel installed. This AD 

requires installing a placard on the 

instrument panel and revising the 

limitations section of the rotorcraft 

flight manual (RFM). This AD is 

prompted by several incidents of third 

stage engine turbine wheel failures, 

which were caused by excessive 

vibrations at certain engine speeds 

during steady-state operations. These 

actions are intended to alert pilots to 

avoid certain engine speeds during 

steady-state operations, prevent failure 

of the third stage engine turbine, engine 

power loss, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective December 

13, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of December 13, 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 


wreier-aviles on DSK5TPTVN1PROD with RULES
Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations 67021 

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: 

Chinh Vuong, Aviation Safety Engineer, 

Safety Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5110; email chinh.vuong@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On June 20, 2013, at 78 FR 37150, 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 ECD 

Model BO105C (C–2 and CB–2 Variants) 

and BO105S (CS–2 and CBS–2 Variants) 

helicopters with a third stage turbine 

wheel, part number (P/N) 23065833, 

installed. The NPRM proposed to 

require installing a placard on the 

instrument panel next to the triple RPM 

indicator and revising the Limitations 

sections of the Model BO 105C/CS and 

BO105 CB/CBS RFMs to limit steadystate operations between speeds of 

86.5% and 95.5%. The proposed 

requirements were intended to alert 

pilots to avoid certain engine speeds 

during steady-state operations, prevent 

failure of the third stage engine turbine, 

engine power loss, and subsequent loss 

of control of the helicopter. 

The NPRM was prompted by AD No. 

2010–0128, dated June 25, 2010, issued 

by the European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union. EASA issued AD No. 2010–0128 

to correct an unsafe condition for Model 

BO 105 C, BO 105 D, and BO 105 S 

helicopters, and certain variants of those 

models. EASA advises that several 

failures of third stage turbine wheels 

used in Rolls Royce Corporation (RRC) 

250 series engines have occurred. 

According to EASA, RRC has 

determined that detrimental vibrations 

can occur within a particular range of 

turbine speeds, and may be a 

contributing factor to these failures. 

This condition, if not corrected, could 

result in loss of engine power, possibly 

resulting in an emergency landing and 

injuries to the helicopter occupants. To 

address this, RRC issued Commercial 

Engine Bulletin (CEB) A–1400, now at 

revision 3, for engines with a third stage 

turbine wheel, P/N 23065833, installed. 

CEB A–1400 introduces an operational 

limitation to avoid engine power turbine 

(N2) steady-state operation in a speed 

range between 86.5% and 95.5% for 

more than 60 seconds in single or 

cumulative events. In response, ECD has 

revised the RFM and has provided a 

placard to inform pilots to avoid steadystate operations between 86.5% and 

95.5% turbine speeds. 

The EASA AD requires amending the 

RFMs and installing a placard as 

described in ECD Alert Service Bulletin 

No. BO105–60–110, Revision 1, dated 

March 3, 2010 (ASB BO105). 

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 37150, June 20, 2013). 

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 

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 

ECD has issued ASB BO105, which 

contains procedures for installing a 

placard on the instrument panel stating 

the prohibited steady-state turbine 

operating range. Revision 1 of ASB 

BO105 removed the temporary RFM 

pages as these changes were included in 

the most recent revisions of the 

BO105C/CS and BO105CB/CBS RFMs. 

Costs of Compliance 

We estimate that this AD affects 80 

helicopters of U.S. Registry. 

Based on an average labor rate of $85 

per hour, we estimate that operators will 

incur the following costs in order to 

comply with this AD. Amending the 

RFM will require about 0.5 work-hour, 

for a cost per helicopter of about $43 

and a cost to U.S. operators of $3,440. 

Installing the decal will require about 

0.2 work-hour, and required parts will 

cost about $5, for a cost per helicopter 

of $22 and a cost to U.S. operators of 

$1,760. Based on these estimates, the 

total cost of this AD is $65 per 

helicopter and $5,200 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 

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: 


wreier-aviles on DSK5TPTVN1PROD with RULES
67022 Federal Register / Vol. 78, No. 217 / Friday, November 8, 2013 / Rules and Regulations 

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): 

2013–20–17 Eurocopter Deutschland 

GMBH (ECD): Amendment 39–17623; 

Docket No. FAA–2013–0519; Directorate 

Identifier 2010–SW–068–AD. 

(a) Applicability 

This AD applies to ECD Model BO105C (C– 

2 and CB–2 Variants) and BO105S (CS–2 and 

CBS–2 Variants) helicopters with a third 

stage turbine wheel, part number 23065833, 

installed, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

third stage turbine vibration, which could 

result in turbine failure, engine power loss 

and subsequent loss of control of the 

helicopter. 

(c) Effective Date 

This AD becomes effective December 13, 

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 30 days: 

(1) For BO105C–2 and BO105CS–2 Variant 

helicopters, revise the Rotorcraft Flight 

Manual (RFM), Section 2, Limitations 

Section, by inserting page 2–25 of ECD Flight 

Manual BO 105 C/CS, revision 5, dated 

March 12, 2010. 

(2) For BO105CB–2 and BO105CBS–2 

Variant helicopters, revise the RFM, Section 

2, Limitations Section, by inserting pages 2– 

8 and 2–27 of ECD Flight Manual BO 105 CB/ 

CBS, revision 8, dated March 12, 2010. 

(3) Install a placard on the instrument 

panel next to the triple RPM indicator that 

states: MIN. CONTINUOUS 98% N2—MIN. 

TRANSIENT 95% N2. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Chinh Vuong, 

Aviation Safety Engineer, Safety Management 

Group, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 76137; 

telephone (817) 222–5110; email 

chinh.vuong@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) ECD Alert Service Bulletin No. BO105– 

60–110, Revision 1, dated March 3, 2010, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. 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 a copy of the 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2010–0128, dated June 25, 2010. You 

may view the EASA AD on the internet in 

the AD Docket at http://www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine 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. 

(i) Page 2–25 of Section 2, Limitations, of 

Eurocopter Deutschland GmbH Flight 

Manual BO 105 C/CS, Revision 5, dated 

March 12, 2010. 

(ii) Pages 2–8 and 2–27 of Section 2, 

Limitations, of Eurocopter Deutschland 

GmbH Flight Manual BO 105 CB/CBS, 

Revision 8, dated March 12, 2010. 

(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 review a copy of this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(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 September 

20, 2013. 

Scott A. Horn, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–26562 Filed 11–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0481; Directorate 

Identifier 2011–SW–003–AD; Amendment 

39–17653; AD 2013–22–21] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc., Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Bell 

Helicopter Textron, Inc. (Bell), Model 

206A, 206B, 206L, 206L–1, 206L–3, 

206L–4, and 407 helicopters with an 

Apical Industries, Inc. (Apical) 

emergency float kit installed under 

Supplemental Type Certificate (STC) 

Number SR01535LA. This AD was 

prompted by an incident in which the 

floats installed on a helicopter failed to 

deploy. This AD requires inspecting, 

labeling, and replacing the float 

inflation hoses. We are issuing this AD 

to prevent failure of the emergency 

floatation gear to deploy during an 

emergency event. 

DATES: This AD is effective December 

13, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of December 13, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Apical 

Industries, Inc., 2608 Temple Heights 

Drive, Oceanside, CA 92056–3512; 

telephone (760) 724–5300; fax: (760) 

758–9612; or at 

www.apicalindustries.com. You may 

review copies of 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 Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, the STC, the 

regulatory evaluation, any comments 

received, and other information. The 

address for the Docket Office (phone: 

800–647–5527) is Document 

Management Facility, U.S. Department 

of Transportation, Docket Operations, 

M–30, West Building Ground Floor, 


wreier-aviles on DSK5TPTVN1PROD with RULES