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

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)


## 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 alsoestimate 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


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

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: