Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 17757 

Products LLC; (24) Trane; (25) Triangle 

Tube; (26) US Boiler Company; and (27) 

Weil-McLain. 

The intent of the amended test 

procedure was to require manufacturers 

to test for standby mode and off mode 

power at this time only if they intended 

to publicize such information, and for 

the above-stated reasons regarding the 

volume of and limited time available for 

testing, DOE agrees that requiring all 

basic models to be retested before April 

18, 2011, would place an undue burden 

upon the petitioners. Likewise, DOE 

does not believe that it would be 

appropriate to prevent the 

dissemination of representations 

regarding auxiliary electrical energy 

consumption of residential furnaces and 

boilers, because consumers may find 

such information beneficial. 

Furthermore, DOE agrees that a 180-day 

extension would not be expected to 

harm consumers or undermine the 

purpose of the final rule. For these 

reasons, and given that the petitioners 

fulfilled their obligations under 42 

U.S.C. 6293(c)(3), DOE hereby issues 

this Decision and Order which grants 

the 27 petitioners above an extension of 

180 days for compliance with the 

amended provisions of the furnaces and 

boilers test procedure final rule that was 

published in the Federal Register on 

October 20, 2010. Accordingly, the 

petitioners must meet a new compliance 

date of October 15, 2011. With respect 

to Rheem’s request that DOE extend the 

compliance date to the end of the 

calendar year 2011, DOE reiterates that 

the maximum extension allowed by the 

statute is 180 days. As such, DOE denies 

Rheem’s request. 

DOE notes that this extension does 

not release petitioners from the 

certification requirements set forth in 10 

CFR 430.62. 

Issued in Washington, DC, on March 24, 

2011. 

Kathleen Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Office of Technology 

Development, Energy Efficiency and 

Renewable Energy. 

[FR Doc. 2011–7579 Filed 3–30–11; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0820; Directorate 

Identifier 2010–NE–31–AD; Amendment 

39–16646; AD 2011–07–09] 

RIN 2120–AA64 

Airworthiness Directives; Thielert 

Aircraft Engines GmbH Models TAE 

125–01, TAE 125–02–99, and 

TAE 125–02–114 Reciprocating 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

Service experience has shown that a case 

of FADEC channel B manifold air pressure 

(MAP) sensor hose permeability is not always 

recognized as fault by the FADEC. The MAP 

value measured by the sensor may be lower 

than the actual pressure value in the engine 

manifold, and limits the amount of fuel 

injected into the combustion chamber and 

thus the available power of the engine. A 

change in FADEC software version 2.91 will 

change the logic in failure detection and in 

switching to channel B (no automatic switch 

to channel B if MAP difference between 

channel A and B is detected and lower MAP 

is at channel B). 

In addition, previous software versions 

allow—under certain conditions and on 

DA 42 aircraft only—the initiation of a 

FADEC self test during flight that causes an 

engine in-flight shutdown. 

We are issuing this AD to prevent 

engine in-flight shutdown or power loss, 

possibly resulting in reduced control of 

the airplane. 

DATES: This AD becomes effective May 

5, 2011. 

ADDRESSES: The Docket Operations 

office is located at Docket Management 

Facility, U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine and 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: alan.strom@faa.gov; phone: 

(781) 238–7143; fax: (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

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 was published in the Federal 

Register on November 23, 2010 (75 FR 

71371). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

Service experience has shown that a case 

of FADEC channel B manifold air pressure 

(MAP) sensor hose permeability is not always 

recognized as fault by the FADEC. The MAP 

value measured by the sensor may be lower 

than the actual pressure value in the engine 

manifold, and limits the amount of fuel 

injected into the combustion chamber and 

thus the available power of the engine. A 

change in FADEC software version 2.91 will 

change the logic in failure detection and in 

switching to channel B (no automatic switch 

to channel B if MAP difference between 

channel A and B is detected and lower MAP 

is at channel B). 

In addition, previous software versions 

allow—under certain conditions and on 

DA 42 aircraft only—the initiation of a 

FADEC self test during flight that causes an 

engine in-flight shutdown. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM. 

We updated the revision levels to the 

two referenced Thielert Operation & 

Maintenance Manuals, and corrected a 

manual number reference error in 

paragraph (e)(2) of this AD. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this AD will affect about 

112 engines installed on airplanes of 

U.S. registry. We also estimate that it 

will take about 0.5 work-hour per 

engine to comply with this AD. The 

average labor rate is $85 per work-hour. 

There are no required parts cost. Based 

on these figures, we estimate the cost of 

the AD on U.S. operators to be $4,760. 

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 


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17758 Federal Register / Vol. 76, No. 62 / Thursday, March 31, 2011 / Rules and Regulations 

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); and 

3. 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

(800) 647–5527) is provided in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, 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 AD: 

2011–07–09 Thielert Aircraft Engines 

GmbH: Amendment 39–16646. Docket 

No. FAA–2010–0820; Directorate 

Identifier 2010–NE–31–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective May 5, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Thielert Aircraft 

Engines GmbH models TAE 125–01, TAE 

125–02–99, and TAE 125–02–114 

reciprocating engines installed in, but not 

limited to, Cessna 172 and (Reims-built) F172 

series (European Aviation Safety Agency 

(EASA) STC No. EASA.A.S.01527); Piper 

PA–28 series (EASA STC No. EASA.A.S. 

01632); APEX (Robin) DR 400 series (EASA 

STC No. A.S.01380); and Diamond Aircraft 

Industries Models DA 40, DA 42, and DA 

42M NG airplanes. 

Reason 

(d) This AD results from mandatory 

continuing airworthiness information (MCAI) 

issued by an aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. We are 

issuing this AD to prevent engine in-flight 

shutdown or power loss, possibly resulting in 

reduced control of the airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions. 

(1) Within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, install 

full-authority digital electronic control 

(FADEC) software version 2.91. 

(2) Guidance on FADEC software 

installation can be found in the following: 

(i) For TAE 125–01 engines, Operation & 

Maintenance Manual OM–02–01, Version 3, 

Revision 15. 

(ii) For TAE 125–02–99 and TAE 125–02– 

114 engines, Operation & Maintenance 

Manual OM–02–02, Version 2, Revision 1. 

Prohibition of FADEC Software Earlier 

Versions 

(f) Once FADEC software version 2.91 is 

installed, do not install any earlier version of 

FADEC software. 

FAA AD Differences 

(g) EASA AD 2010–0137 permits 

installation of earlier FADEC software 

versions, once version 2.91 is installed. This 

AD does not. 

(h) EASA AD 2010–0137 requires 

compliance within 110 flight hours after the 

effective date of the AD or during next 

maintenance, whichever occurs first, but no 

later than 6 months after the effective date of 

the AD. This AD requires compliance within 

110 flight hours after the effective date of the 

AD or during next maintenance, whichever 

occurs first. 

Alternative Methods of Compliance 

(AMOCS) 

(i) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(j) Refer to EASA AD 2010–0137, dated 

June 30, 2010, for related information. 

Contact Thielert Aircraft Engines GmbH, 

Platanenstrasse 14 D–09350, Lichtenstein, 

Germany, phone: +49–37204–696–0; fax: 

+49–37204–696–2912; e-mail: 

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

the service information referenced in this 

AD. 

(k) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; phone: 

(781) 238–7143; fax: (781) 238–7199, for 

more information about this AD. 

Material Incorporated by Reference 

(l) None. 

Issued in Burlington, Massachusetts, on 

March 22, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–7293 Filed 3–30–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1200; Directorate 

Identifier 2010–NM–136–AD; Amendment 

39–16647; AD 2011–07–10] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–100–1A10 (Challenger 

300) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 


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