Federal Register / Vol. 77, No. 18 / Friday, January 27, 2012 / Rules and Regulations 4217 

C82.2 instead of the versions listed as 

normative references in ANSI C82.2. 

* * * * * 

■ 9. Appendix Q1 to subpart B of part 

430 is amended by revising sections 2.1, 

2.3.1, and 2.4.1 to read as follows: 

Appendix Q1 to Subpart B of Part 430— 

Uniform Test Method for Measuring the 

Energy Consumption of Fluorescent 

Lamp Ballasts 

* * * * * 

2. Active Mode Procedure 

2.1. Where ANSI C82.2 (incorporated by 

reference; see § 430.3) references ANSI 

C82.1–1997, the operator shall use ANSI 

C82.1 (incorporated by reference; see § 430.3) 

for testing low-frequency ballasts and shall 

use ANSI C82.11 (incorporated by reference; 

see § 430.3) for testing high-frequency 

ballasts. In addition when applying ANSI 

C82.2, ANSI C78.81 (incorporated by 

reference; see § 430.3), ANSI C82.1, ANSI 

C82.11, and ANSI C82.13 (incorporated by 

reference; see § 430.3) shall be used instead 

of the versions listed as normative references 

in ANSI C82.2. 

* * * * * 

2.3. Test Setup 

2.3.1. The ballast shall be connected to a 

main power source and to the fluorescent 

lamp load according to the manufacturer’s 

wiring instructions and ANSI C82.1 

(incorporated by reference; see § 430.3) and 

ANSI C78.81 (incorporated by reference; see 

§ 430.3). 

* * * * * 

2.4. Test Conditions 

2.4.1. The test conditions for testing 

fluorescent lamp ballasts shall be done in 

accordance with ANSI C82.2 (incorporated 

by reference; see § 430.3). DOE further 

specifies that the following revisions of the 

normative references indicated in ANSI 

C82.2 should be used in place of the 

references directly specified in ANSI C82.2: 

ANSI C78.81 (incorporated by reference; see 

§ 430.3), ANSI C82.1 (incorporated by 

reference; see § 430.3), ANSI C82.3 

(incorporated by reference; see § 430.3), ANSI 

C82.11 (incorporated by reference; see 

§ 430.3), and ANSI C82.13 (incorporated by 

reference; see § 430.3). All other normative 

references shall be as specified in ANSI 

C82.2. 

* * * * * 

■ 10. Appendix R to subpart B of part 

430 is amended by: 

■ a. Revising sections 2.1, 2.9, 3.1, 3.2, 

4.1.1, 4.2.1, 4.2.2, and, 4.4.1; 

■ b. Adding new sections 4.2.3 and 

4.2.3.1; and 

■ c. Removing section 4.5. 

The revisions and additions read as 

follows: 

Appendix R to Subpart B of Part 430— 

Uniform Test Method for Measuring 

Average Lamp Efficacy (LE), Color 

Rendering Index (CRI), Correlated 

Color Temperature (CCT), and Lamp 

Lifetime of Electric Lamps 

* * * * * 

2. Definitions 

2.1 To the extent that definitions in the 

referenced IESNA and CIE standards do not 

conflict with the DOE definitions, the 

definitions specified in section 3.0 of IES 

LM–9 (incorporated by reference; see 

§ 430.3), section 3.0 of IESNA LM–20 

(incorporated by reference; see § 430.3), 

section 3.0 and the Glossary of IES LM–45 

(incorporated by reference; see § 430.3), 

section 2 of IESNA LM–58 (incorporated by 

reference; see § 430.3), and Appendix 1 of 

CIE 13.3 (incorporated by reference; see 

§ 430.3) shall be included. 

* * * * * 

2.9 Reference condition means the test 

condition specified in IES LM–9 for general 

service fluorescent lamps, in IESNA LM–20 

for incandescent reflector lamps, and in IES 

LM–45 for general service incandescent 

lamps. 

3. Test Conditions 

3.1 General Service Fluorescent Lamps: 

For general service fluorescent lamps, the 

ambient conditions of the test and the 

electrical circuits, reference ballasts, 

stabilization requirements, instruments, 

detectors, and photometric test procedure 

and test report shall be as described in the 

relevant sections of IES LM–9 (incorporated 

by reference; see § 430.3). 

3.2 General Service Incandescent Lamps: 

For general service incandescent lamps, the 

selection and seasoning (initial burn-in) of 

the test lamps, the equipment and 

instrumentation, and the test conditions shall 

be as described in IES LM–45 (incorporated 

by reference; see § 430.3). 

* * * * * 

4. Test Methods and Measurements * * * 

4.1.1 The measurement procedure shall 

be as described in IES LM–9 (incorporated by 

reference; see § 430.3), except that lamps 

shall be operated at the appropriate voltage 

and current conditions as described in ANSI 

C78.375 (incorporated by reference; see 

§ 430.3) and in ANSI C78.81 (incorporated by 

reference; see § 430.3) or ANSI C78.901 

(incorporated by reference; see § 430.3), and 

lamps shall be operated using the appropriate 

reference ballast at input voltage specified by 

the reference circuit as described in ANSI 

C82.3 (incorporated by reference; see 

§ 430.3). If, for a lamp, both low-frequency 

and high-frequency reference ballast settings 

are included in ANSI C78.81 or ANSI 

C78.901, the lamp shall be operated using the 

low-frequency reference ballast. 

* * * * * 

4.2 General Service Incandescent Lamps 

4.2.1 The measurement procedure shall 

be as described in IES LM–45 (incorporated 

by reference; see § 430.3). Lamps shall be 

operated at the rated voltage as defined in 

§ 430.2. 

4.2.2 The test procedure shall conform to 

sections 6 and 7 of IES LM–45, and the 

lumen output of the lamp shall be 

determined in accordance with section 7 of 

IES LM–45. Lamp electrical power input in 

watts shall be measured and recorded. Lamp 

efficacy shall be determined by computing 

the ratio of the measured lamp lumen output 

and lamp electrical power input at 

equilibrium for the reference condition. The 

test report shall conform to section 8 of IES 

LM–45. 

4.2.3 The measurement procedure for 

testing the lifetime of general service 

incandescent lamps shall be as described in 

IESNA LM–49 (incorporated by reference; see 

§ 430.3). The lifetime measurement shall be 

taken by measuring the operating time of a 

lamp, expressed in hours, not including any 

off time. The percentage of the sample size 

that meets the minimum rated lifetime shall 

be recorded. The lamp shall be deemed to 

meet minimum rated lifetime standards if 

greater than 50 percent of the sample size 

specified in § 429.27 meets the minimum 

rated lifetime. 

4.2.3.1 Accelerated lifetime testing is not 

allowed. The second paragraph of section 6.1 

of IESNA LM–49 is to be disregarded. 

* * * * * 

4.4 Determination of Color Rendering 

Index and Correlated Color Temperature 

4.4.1 The CRI shall be determined in 

accordance with the method specified in CIE 

13.3 (incorporated by reference; see § 430.3) 

for general service fluorescent lamps. The 

CCT shall be determined in accordance with 

the method specified in IES LM–9 

(incorporated by reference; see § 430.3) and 

rounded to the nearest 10 kelvin for general 

service fluorescent lamps. The CCT shall be 

determined in accordance with the CIE 15 

(incorporated by reference; see § 430.3) for 

incandescent lamps. The required 

spectroradiometric measurement and 

characterization shall be conducted in 

accordance with the methods set forth in 

IESNA LM–58 (incorporated by reference; see 

§ 430.3). 

* * * * * 

[FR Doc. 2012–1681 Filed 1–26–12; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0956; Directorate 

Identifier 2011–NE–23–AD; Amendment 39– 

16928; AD 2012–02–05] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all 

Thielert Aircraft Engines GmbH (TAE) 


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4218 Federal Register / Vol. 77, No. 18 / Friday, January 27, 2012 / Rules and Regulations 

TAE 125–02–99 and TAE 125–02–114 

reciprocating engines. This AD was 

prompted by in-flight engine shutdown 

incidents reported on airplanes 

equipped with TAE 125 engines. We are 

issuing this AD to prevent in-flight 

engine shutdown, which could result in 

loss of control of the airplane. 

DATES: This AD is effective March 2, 

2012. 

ADDRESSES: For service information 

identified in this AD, contact Thielert 

Aircraft Engines GmbH, Platanenstrasse 

14 D–09350, Lichtenstein, Germany, 

telephone: +49–37204–696–0; fax: +49– 

37204–696–55; email: info@centurionengines.com. You may review copies of 

the referenced service information at the 

FAA, Engine & Propeller Directorate, 12 

New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, 

call (781) 238–7125. 

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 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: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, 12 New 

England Executive Park, Burlington, 

MA; phone: (781) 238–7143; fax: (781) 

238–7199; email: alan.strom@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, issued EASA AD 2011– 

0087–E, dated May 12, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

In-flight engine shutdown incidents have 

been reported on aeroplanes equipped with 

TAE 125 engines. 

Preliminary investigations showed that it 

was mainly the result of the sensitivity of 

friction disk Part Number (P/N) 05–7211– 

K010201 against possible misalignment of 

gearbox and core engine during assembly. 

This condition, if not corrected, could 

result in further cases of engine in-flight 

shutdown and consequent loss of control of 

the aeroplane. 

To address this unsafe condition, Thielert 

Aircraft Engines GmbH has developed a new 

friction disk. 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on October 18, 2011 (76 FR 

64289). That NPRM was proposed to 

require on all TAE 125–02–99 and TAE 

125–02–114 reciprocating engines, 

replacing the friction disk, P/N 05– 

7211–K010201. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (76 

FR 64289, October 18, 2011). 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

206 TAE 125–02–99 and TAE 125–02– 

114 reciprocating engines installed on 

airplanes of U.S. registry. We also 

estimate that it will take about 3 workhours per engine to comply with this 

AD. The average labor rate is $85 per 

work-hour. Required parts will cost 

about $1,500 per engine. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators to be $361,530. Our 

cost estimate is exclusive of possible 

warranty coverage. 

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 

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, 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): 

2012–02–05 Thielert Aircraft Engines 

GmbH: Amendment 39–16928; Docket 

No. FAA–2011–0956; Directorate 

Identifier 2011–NE–23–AD. 

(a) Effective Date 

This AD is effective March 2, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all Thielert Aircraft 

Engines GmbH TAE 125–02–99 and TAE– 

125–02–114 reciprocating engines with 

friction disk, part number (P/N) 05–7211– 

K010201, installed. 

(d) Reason 

This AD was prompted by in-flight engine 

shutdown incidents reported on airplanes 

equipped with TAE 125 engines. Preliminary 

investigations showed that it was mainly the 

result of the sensitivity of friction disk P/N 


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Federal Register / Vol. 77, No. 18 / Friday, January 27, 2012 / Rules and Regulations 4219 

05–7211–K010201 against possible 

misalignment of gearbox and core engine 

during assembly. We are issuing this AD to 

prevent in-flight engine shutdown, which 

could result in loss of control of the airplane. 

(e) Actions and Compliance 

Unless already done, do the following 

actions. 

(1) TAE 125–02–99 Engines, P/Ns 05–7200– 

K000201; 05–7200–K000701; 05–7200– 

K000101; 05–7200–K000901; 05–7200– 

K001101; and 05–7200–K001301; and TAE 

125–02–114 Engines, P/Ns 05–7200–K000501; 

05–7200–K000801; and 05–7200–K001401 

For TAE 125–02–99 engines, P/Ns 05– 

7200–K000201; 05–7200–K000701; 05–7200– 

K000101; 05–7200–K000901; 05–7200– 

K001101; and 05–7200–K001301; and TAE 

125–02–114 engines, P/Ns 05–7200– 

K000501; 05–7200–K000801; and 05–7200– 

K001401, remove friction disk, P/N 05–7211– 

K010201, within 100 flight hours (FH) timesince-new (TSN) on the clutch or within 10 

FH time-in-service (TIS) after the effective 

date of this AD, whichever is later. 

(2) TAE 125–02–99 Engines, P/Ns 05–7200– 

K000301 

For TAE 125–02–99 engines, P/N 05–7200– 

K000301, installed on multiengine aircraft, 

remove friction disk, P/N 05–7211–K010201, 

on one engine within 100 FH TSN on the 

clutch or within 10 FH TIS after the effective 

date of this AD, whichever is later. Remove 

friction disk, P/N 05–7211–K010201, from 

the other engine within 300 FH TSN on the 

clutch or within 10 FH TIS after the effective 

date of this AD, whichever is later. 

(f) Installation Prohibition 

After the effective date of this AD: 

(1) Do not install any friction disk, P/N 05– 

7211–K010201, into any engine. 

(2) Do not install any TAE 125–02–99 

engine, P/N 05–7200–K000201, 05–7200– 

K000301, or 05–7200–K000701, or TAE 125– 

02–114 engine, P/N 05–7200–K00801 or 05– 

7200–K00501, that has a friction disk, P/N 

05–7211–K010201 installed, onto any 

airplane. 

(g) Operating Prohibition 

Do not operate any multi-engine aircraft 

after 300 FH TSN on the clutch or 10 FH TIS 

after the effective date of this AD, whichever 

is later, which has installed a friction disk, 

P/N 05–7211–K010201. 

(h) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

may approve AMOCs for this AD. Use the 

procedures found in 14 CFR 39.19 to make 

your request. 

(i) Related Information 

(1) For more information about this AD, 

contact Alan Strom, Aerospace Engineer, 

Engine Certification Office, FAA, 12 New 

England Executive Park, Burlington, MA; 

phone: (781) 238–7143; fax: (781) 238–7199; 

email: alan.strom@faa.gov. 

(2) Refer to EASA Airworthiness Directive 

2011–0087–E, dated May 12, 2011, and 

Thielert Service Bulletin No. TM TAE 125– 

1013 P1, for related information. 

(3) Contact Thielert Aircraft Engines 

GmbH, Platanenstrasse 14 D–09350, 

Lichtenstein, Germany, telephone: +49– 

37204–696–0; fax: +49–37204–696–55; email: 

info@centurion-engines.com, for a copy of 

this service information. 

(4) You may review copies of the service 

information at the FAA, Engine & Propeller 

Directorate, 12 New England Executive Park, 

Burlington, MA. For information on the 

availability of this material at the FAA, call 

(781) 238–7125. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

January 19, 2012. 

Peter A. White, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–1607 Filed 1–26–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 121 

[Docket No. FAA–2011–1343; Amdt. No. 

121–358] 

FAA-Approved Portable Oxygen 

Concentrators; Technical Amendment 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; technical 

amendment. 

SUMMARY: The FAA is amending 

regulations relating to operating rules 

for FAA approved portable oxygen 

concentrators (POC) onboard aircraft. 

This document updates the names of 

two manufacturers of approved POCs 

listed in the Special Federal Aviation 

Regulation (SFAR). 

DATES: Effective January 27, 2012. 

FOR FURTHER INFORMATION CONTACT: For 

technical questions concerning this 

action, contact DK Deaderick, Air 

Transportation Division, AFS–200, 

Federal Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone: (202) 

267–7480; email: 

DK.Deaderick@faa.gov. For legal 

questions concerning this action, 

contact Alex Zektser, AGC–220, Office 

of Chief Counsel, Regulations Division, 

Federal Aviation Administration, 800 

Independence Avenue SW., 

Washington, DC 20591; telephone (202) 

267–3073; email: Alex.Zektser@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

On July 12, 2005, the FAA published 

SFAR 106, ‘‘Use of Certain Portable 

Oxygen Concentrator Devices Onboard 

Aircraft’’ (70 FR 40156). SFAR 106 

permits passengers to carry on and use 

certain small portable oxygen 

concentrators (POCs) on board aircraft if 

the operator ensures compliance with 

conditions specified in the SFAR. Some 

of the devices determined acceptable for 

use in SFAR 106 are Delphi Medical 

Systems’ RS–00400 (added to the SFAR 

in 74 FR 2351) and International 

Biophysics Corporation’s LifeChoice 

(added to the SFAR in 75 FR 739). 

As a result of business changes that 

took place after SFAR 106 was 

published, the LifeChoice POC is now 

manufactured by Inova Labs, Inc. and 

not by the International Biophysics 

Corporation. Similarly, the RS–00400 

POC is now manufactured by Oxus, Inc. 

and not by Delphi Medical Systems. 

The two companies currently 

manufacturing these POCs have 

petitioned the FAA to amend SFAR 106, 

Section 2 and section 3(a), of Title 14, 

Code of Federal Regulations (14 CFR). 

This amendment would update section 

2 and section 3(a) of SFAR 106 with the 

names of the current manufacturers of 

the LifeChoice and RS–00400 POCs. 

Technical Amendment 

LifeChoice and RS–00400 are still the 

same products that were originally 

approved in SFAR 106—only the names 

of their manufacturers have changed. As 

such, this technical amendment makes 

two revisions to the final rule. First, the 

language in SFAR 106 section 2 and 

section 3(a) is revised to refer to 

LifeChoice as being manufactured by 

Inova Labs. Second, the reference to the 

RS–00400 POC is revised to refer to this 

device as being manufactured by Oxus, 

Inc. 

Because the changes in this technical 

amendment result in no substantive 

change, we find good cause exists under 

5 U.S.C. 553(d)(3) to make the 

amendment effective in less than 30 

days. 

List of Subjects in 14 CFR Part 121 

Air carriers, Aircraft, Airmen, 

Aviation safety, Charter flights, Safety, 

Transportation, Air taxis. 

The Amendment 

In consideration of the foregoing, the 

Federal Aviation Administration 

amends chapter 1 of title 14, Code of 

Federal Regulations as follows: 

PART 121—OPERATING 

REQUIREMENTS: DOMESTIC, FLAG, 

AND SUPPLEMENTAL OPERATIONS 

■ 1. The authority citation for part 121 

continues to read as follows: 


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