Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations 40483 

12 3927–5852 or +55 12 3309–0732; fax +55 

12 3927–7546; email distrib@embraer.com.br; 

Internet http://www.flyembraer.com. 

(4) You may view this 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. 

(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 Renton, Washington, on June 8, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–14305 Filed 6–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–2042; Directorate 

Identifier 2016–NE–02–AD; Amendment 39– 

18568; AD 2016–13–04] 

RIN 2120–AA64 

Airworthiness Directives; BRPPowertrain GmbH & Co KG 

Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

BRP-Powertrain GmbH & Co KG Rotax 

912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 

912 S4, 914 F2, 914 F3, and 914 F4 

reciprocating engines. This AD requires 

re-identification of the engine model 

and concurrent modification of the 

aircraft to indicate the maximum 

coolant temperature limit. This AD was 

prompted by a design change 

introduced by the manufacturer that 

relocated the engine cylinder head 

temperature sensor to a different 

location and converted it to a coolant 

temperature sensor. We are issuing this 

AD to prevent exceeding engine coolant 

temperature limits, which could result 

in loss of engine coolant, damage to the 

engine, and loss of control of the 

airplane. 

DATES: This AD becomes effective July 

27, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact BRPPowertrain GmbH & Co KG, Rotaxstrasse 

1, A–4623 Gunskirchen, Austria; phone: 

+43 7246 6010; fax: +43 7246 601 9130; 

email: airworthiness@brp.com; Internet: 

http://www.FLYROTAX.com. You may 

view this service information at the 

FAA, Engine & Propeller Directorate, 

1200 District Avenue, Burlington, MA. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2016–2042. 

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–2016– 

2042; 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 mandatory 

continuing airworthiness information 

(MCAI), 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, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 1200 District 

Avenue, Burlington, MA 01803; phone: 

781–238–7754; fax: 781–238–7199; 

email: robert.green@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM was published in the Federal 

Register on March 18, 2016 (81 FR 

14804). The NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

A design change of the engine cylinder 

heads was introduced by BRP-Powertrain in 

March 2013 which modifies the engine/ 

aircraft interfaces by substituting the 

previous cylinder head temperature (CHT) 

measurement (limit temperature 135 °C/150 

°C) with a coolant temperature (CT) 

measurement (limit temperature 120 °C). 

The design change was communicated on 

15 May 2013 by BRP-Powertrain Service 

Instruction (SI) 912–020R7/914–022R7 

(single document) but was not identified by 

a change of the engine model designation or 

of the engine P/N but only through the 

cylinder head P/N and the position of the 

temperature sensor. 

Consequently, engines with the new 

cylinder heads (installed during production 

or replaced in-service during maintenance) 

may be installed on an aircraft without 

concurrent modification of that aircraft, 

instructions for which should be provided by 

the type certificate (TC) holder or the 

supplemental type certificate (STC) holder, 

as applicable. In this case, the coolant 

temperature with a maximum engine 

operating limit of 120 °C (valid for engines 

operated with water diluted glycol coolant) is 

displayed on a CHT indicator with a typical 

limit marking (red radial/range) of more than 

120 °C. 

You may obtain further information 

by examining the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

2042. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (81 

FR 14804, March 18, 2016). 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed expect for minor editorial 

changes. We determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

BRP-Powertrain GmbH & Co KG has 

issued Service Bulletin (SB) SB–912– 

068/SB–914–049 (one document), dated 

April 16, 2015. The service information 

describes procedures for reidentification of the type plate for 

certain BRP-Powertrain GmbH & Co KG 

Rotax 912 and 914 engines. 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. 

Costs of Compliance 

We estimate that this AD affects about 

40 engines installed on aircraft of U.S. 

registry. We also estimate that it will 

take about 5 hours per engine to inspect 

and re-identify the type plate. The 

average labor rate is $85 per hour. Based 

on these figures, we estimate the cost of 

this AD on U.S. operators to be $17,000. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 


sradovich on DSK3TPTVN1PROD with RULES
40484 Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations 

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 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 this AD: 

(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. 

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): 

2016–13–04 BRP-Powertrain GmbH & Co 

KG (formerly BRP-Rotax GmbH & Co 

KG, Bombardier-Rotax GmbH & Co. KG, 

and Bombardier-Rotax GmbH): 

Amendment 39–18568; Docket No. 

FAA–2016–2042; Directorate Identifier 

2016–NE–02–AD. 

(a) Effective Date 

This AD becomes effective July 27, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to BRP-Powertrain GmbH 

& Co KG Rotax model 912 F2, 912 F3, 912 

F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, 

and 914 F4 reciprocating engines with a 

cylinder head that has a part number (P/N) 

listed in Figure 1 to paragraph (c) of this AD 

and that is installed in position 2 or 3. 

FIGURE 1 TO PARAGRAPH (c) OF THIS

AD—POST-MODIFICATION CYLINDER

HEAD P/N 

Engine model Cylinder head P/N 

912 F2, 912 F3, 912 

F4, 914 F2, 914 

F3, and 914 F4.

P/N 413235 or P/N 

413236. 

912 S2, 912 S3, and 

912 S4.

P/N 413185. 

(d) Reason 

This AD was prompted by a design change 

introduced by the manufacturer that 

relocated the engine cylinder head 

temperature sensor to a new location and 

converted it to a coolant temperature sensor. 

We are issuing this AD to prevent exceeding 

coolant temperature limits, which could 

result in loss of engine coolant, damage to the 

engine, and loss of control of the airplane. 

(e) Actions and Compliance 

Comply with this AD within 6 months after 

the effective date of this AD, unless already 

done. 

(1) For engines with cylinder heads that 

have a P/N listed in Figure 1 to paragraph (c) 

of this AD installed on both position 2 and 

position 3, change the engine model 

designation on the engine type data plate to 

include a ‘‘–01’’ suffix. Use paragraph 3.1.1 

of BRP-Powertrain Service Bulletin (SB) SB– 

912–068/SB–914–049, dated April 16, 2015, 

to make this change. 

(2) For engines with only one cylinder 

head having a P/N listed in Figure 1 to 

paragraph (c) of this AD installed in position 

2 or 3, do one of the following: 

(i) Replace the cylinder head having a P/ 

N listed in Figure 1 to paragraph (c) of this 

AD with a P/N 623682 cylinder head on 

Rotax 912 F2, 912 F3, 912 F4, 914 F2, 914 

F3, and 914 F4 engines and with a P/N 

623687 cylinder head on Rotax 912 S2, 912 

S3, and 912 S4 engines. If you complete the 

actions in paragraph (e)(2)(i), no further 

action is required. Or, 

(ii) Install cylinder heads identified in 

Figure 1 to paragraph (c) of this AD on both 

cylinder head positions 2 and 3 and change 

the engine model designation of the engine 

type data plate in accordance with paragraph 

(e)(1) of this AD. 

(3) For engines re-identified in accordance 

with paragraph (e)(1) or (e)(2)(ii) of this AD, 

before further flight, modify the aircraft 

cockpit instrumentation and related 

documentation to indicate a maximum 

coolant temperature limit of 120 degrees 

Celsius using FAA-approved procedures. 

These re-identified engines remain eligible 

for installation on approved aircraft-engine 

combinations. 

(f) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(g) Related Information 

(1) For more information about this AD, 

contact Robert Green, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7754; fax: 781–238–7199; email: 

robert.green@faa.gov. 

(2) For more information about the 

installation modifications described in 

paragraph (e)(3) of this AD, contact Jim 

Rutherford, Aerospace Engineer, FAA, Small 

Airplane Directorate, 901 Locust Ave. Room 

301, Kansas City, MO; phone: 816–329–4165; 

fax: 816–329–4090; email: 

Jim.Rutherford@faa.gov. 

(3) Refer to MCAI European Aviation 

Safety Agency, AD 2015–0240, dated 

December 18, 2015, for more information. 

You may examine the MCAI in the AD 

docket on the Internet at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2016–2042. 

(4) The following aircraft service 

information, which are not incorporated by 

reference in this AD, contain FAA-approved 

procedures for complying with paragraph 

(e)(3) of this AD and can be obtained from 

BRP-Powertrain GmbH & Co. KG, using the 

contact information in paragraph (h)(3) of 

this AD: 

FIGURE 2 TO PARAGRAPH (g) OF THIS

AD—AIRCRAFT TYPE/MODEL AND

SERVICE INFORMATION

Type/model(s) SB 

Aquila AT01 ......................... SB–AT01–029. 

TECNAM P92, P2002 and 

P2006T.

SB–183–CS. 

TECNAM P2008 JC ............ SB–185–CS. 

Diamond H 36 ‘‘Dimona’’ 

and HK 36 ‘‘Super 

Dimona’’.

OSB 36–111. 

Diamond DV 20 ‘‘Katana’’ ... OSB 20–066. 

Diamond (Canada) DA20– 

A1 ‘‘Katana’’.

SB Da20–72– 

04. 

M&D AVO 68 ‘‘Samburo’’ .... TM 808–31. 


sradovich on DSK3TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 120 / Wednesday, June 22, 2016 / Rules and Regulations 40485 

FIGURE 2 TO PARAGRAPH (g) OF THIS

AD—AIRCRAFT TYPE/MODEL AND

SERVICE INFORMATION—Continued 

Type/model(s) SB 

Scheibe SF 25 C and SF 36 

R.

SI_02–14. 

(h) 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) BRP-Powertrain Service Bulletin SB– 

912–068/SB–914–049 (one document), dated 

April 16, 2015. 

(ii) Reserved. 

(3) For BRP-Powertrain service information 

identified in this AD, contact BRP-Powertrain 

GmbH & Co. KG, Rotaxstrasse 1, A–4623 

Gunskirchen, Austria; phone: +43 7246 6010; 

fax: +43 7246 601 9130; email: 

airworthiness@brp.com; Internet: 

www.flyrotax.com. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

June 14, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–14789 Filed 6–21–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4812; Directorate 

Identifier 2015–NM–034–AD; Amendment 

39–18560; AD 2016–12–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 787–8 

airplanes. This AD was prompted by a 

report that certain center and outboard 

stowage bin modules were incorrectly 

installed. This AD requires an 

inspection of the center and outboard 

stowage bin modules for missing parts, 

quick release pins that are not fully 

engaged, and parts that are installed in 

incorrect locations; and corrective 

actions if necessary. We are issuing this 

AD to detect and correct incorrectly 

installed center and outboard stowage 

bin modules that might not remain 

intact during an emergency landing, 

resulting in injuries to occupants and 

interference with airplane evacuation. 

DATES: This AD is effective July 27, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 27, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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– 

4812. 

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– 

4812; 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 regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Stanley Chen, Aerospace Engineer, 

Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6585; 

fax: 425–917–6590; email: 

stanley.chen@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 787–8 airplanes. The NPRM 

published in the Federal Register on 

November 17, 2015 (80 FR 71745), (‘‘the 

NPRM’’). The NPRM was prompted by 

a report that certain center and outboard 

stowage bin modules were incorrectly 

installed. The NPRM proposed to 

require an inspection of the center and 

outboard stowage bin modules for 

missing parts, quick release pins that are 

not fully engaged, and parts that are 

installed in incorrect locations; and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

incorrectly installed center and 

outboard stowage bin modules that 

might not remain intact during an 

emergency landing, resulting in injuries 

to occupants and interference with 

airplane evacuation. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the NPRM and the FAA’s 

response to that comment. 

Request To Include Additional 

Illustrations in Service Information 

United Airlines stated that it would 

be helpful if the service information 

provided examples (illustrations or 

descriptions) of incorrectly installed 

parts that required removal. We infer 

that the commenter is requesting a 

revision to the service information to 

include examples of incorrectly 

installed parts. 

We disagree with the commenter’s 

request. We consider that it would be 

potentially confusing to show examples 

of possible incorrect part installations. 

We have determined that the service 

information should provide detailed 

illustrations of proper installation 

configurations. A general description of 

the incorrect installations is provided. 

We have not changed this final rule 

regarding this issue. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed, except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 


sradovich on DSK3TPTVN1PROD with RULES