Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125-01, TAE 125-02-99, and TAE 125-02-114 Reciprocating Engines, 71371-71373 [2010-29449]

Download as PDF Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules Comments Due Date (a) We must receive comments by January 7, 2011. Affected ADs (b) None. Applicability (c) This AD applies to the Bombardier, Inc. airplanes, certificated in any category, identified in paragraphs (c)(1) and (c)(2) of this AD. (1) Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315, serial numbers 003 through 566 inclusive. (2) Model DHC–8–401, and –402 airplanes, serial numbers 4001, 4003, 4004, 4006, and 4008 through 4274 inclusive. Subject (d) Air Transport Association (ATA) of America Code 56: Windows. Reason (e) The mandatory continuing airworthiness information (MCAI) states: There have been several in-service reports of finding trapped water on the bottom of the cockpit windshield frames (or lower windshield frames) that resulted in either corrosion or water ingress into the cockpit. In one occurrence, the trapped water caused severe corrosion of numerous anchor nuts that secure the windshield to the lower windshield frame, such that the intended fastening function was seriously compromised. Corrosion of the lower windshield frames, including the anchor nuts that secure the windshield to the aircraft structure, can result in a serious structural degradation possibly leading to the loss of the windshield during flight. Also, water could leak into the cockpit and cause either a malfunction or failure of the electrical and electronics systems in the area of the cockpit instrument panels. * * * * * Compliance (f) You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. erowe on DSK5CLS3C1PROD with PROPOSALS-1 Actions (g) Within 6,000 flight hours or 36 months after the effective date of this AD, whichever occurs first, install a drain system in the cockpit windshield lower frames, and do all applicable related investigative and corrective actions, in accordance With the Accomplishment Instructions of Bombardier Service Bulletin 8–53–78, Revision C, dated April 29, 2010 (for Model DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes); or 84–53–43, dated April 27, 2010 (for Model DHC–8–401 and –402 airplanes); except where the service bulletins state to contact the manufacturer, contact the New York Aircraft Certification Office or Transport Canada Civil Aviation (TCCA) or its delegated agent. Do all applicable related investigative and corrective actions before further flight. VerDate Mar<15>2010 14:36 Nov 22, 2010 Jkt 223001 Credit for Actions Accomplished in Accordance With Previous Service Information (h) For Models DHC–8–102, –103, –106, –201, –202, –301, –311, and –315 airplanes: Modification of the drain system is also acceptable for compliance with the requirements of paragraph (g) of this AD, if done before the effective date of this AD, in accordance with Bombardier Service Bulletin 8–53–78, dated December 23, 1999; Revision A, dated June 7, 2001; or Revision B, dated May 2, 2002. FAA AD Differences Other FAA AD Provisions (i) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, New York Aircraft Certification Office, ANE–170, 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: Program Manager, Continuing Operational Safety, FAA, New York ACO, 1600 Stewart Avenue, Suite 410, Westbury, New York 11590; telephone 516–228–7300; fax 516– 794–5531. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD. (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: 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. Related Information (j) Refer to MCAI Canadian Airworthiness Directive CF–2010–16, dated May 18, 2010; Frm 00004 Fmt 4702 Bombardier Service Bulletin 8–53–78, Revision C, dated April 29, 2010; and Bombardier Service Bulletin 84–53–43, dated April 27, 2010; for related information. Issued in Renton, Washington, on November 15, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–29448 Filed 11–22–10; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Note: This AD differs from the MCAI and/ or service information as follows: No differences. PO 00000 71371 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0820; Directorate Identifier 2010–NE–31–AD] RIN 2120–AA64 Airworthiness Directives; Thielert Aircraft Engines GmbH Models TAE 125–01, TAE 125–02–99, and TAE 125– 02–114 Reciprocating Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for the products listed above. This proposed 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: SUMMARY: 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 proposing this AD to prevent engine in-flight shutdown or power loss, possibly resulting in reduced control of the airplane. DATES: We must receive comments on this proposed AD by January 7, 2011. ADDRESSES: You may send comments by any of the following methods: E:\FR\FM\23NOP1.SGM 23NOP1 71372 Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +49– 37204–696–0; fax: +49–37204–696– 2912; e-mail: info@centurionengines.com for the service information identified in this proposed AD. Examining the AD Docket You may examine the AD docket on the Internet at https:// 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone (800) 647–5527) is the same as the Mail address provided in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. 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; telephone (781) 238–7143; fax (781) 238–7199. SUPPLEMENTARY INFORMATION: erowe on DSK5CLS3C1PROD with PROPOSALS-1 Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–0820; Directorate Identifier 2010–NE–31–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments. We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA VerDate Mar<15>2010 14:36 Nov 22, 2010 Jkt 223001 personnel concerning this proposed AD. Using the search function of the Web site, anyone can find and read the comments in any of our dockets, including, if provided, the name of the individual who sent the comment (or signed the comment on behalf of an association, business, labor union, etc.). You may review the DOT’s complete Privacy Act Statement in the Federal Register published on April 11, 2000 (65 FR 19477–78). Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD 2010–0137, dated June 30, 2010 (referred to after this as ‘‘the MCAI’’), 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. We are proposing to require installation of full-authority digital electronic control (FADEC) software version 2.91 to prevent automatic switching to channel B if the channel B MAP sensor hose is leaking. The current software cannot detect the difference between a manifold leak and a real manifold pressure change. This software installation will prevent the undesired limiting of fuel to the engine. Installing FADEC software version 2.91 will also prevent the FADEC from self-testing during flight, which would cause an engine in-flight shutdown. You may obtain further information by examining the MCAI in the AD docket. FAA’s Determination and Requirements of This Proposed AD These products 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 has notified us of the unsafe condition described in the MCAI. We are PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 proposing 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 products of the same type design. This proposed AD would require installing full authority digital electronic control software version 2.91. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 112 engines installed on airplanes of U.S. registry. We also estimate that it would take about 0.5 work-hour per engine to comply with this proposed 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 proposed 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 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation: 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 E:\FR\FM\23NOP1.SGM 23NOP1 Federal Register / Vol. 75, No. 225 / Tuesday, November 23, 2010 / Proposed Rules under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. (i) For TAE 125–01 engines, Operation & Maintenance Manual OM–01–02, Issue 3, Revision 13. (ii) For TAE 125–02–99 and TAE 125–02– 114 engines, Operation & Maintenance Manual OM–02–02, Issue 1, Revision 10. List of Subjects in 14 CFR Part 39 Prohibition of FADEC Software Earlier Versions Air transportation, Aircraft, Aviation safety, Safety. (f) Once FADEC software version 2.91 is installed, do not install any earlier version of FADEC software. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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): Thielert Aircraft Engines GmbH: Docket No. FAA–2010–0820; Directorate Identifier 2010–NE–31–AD. Comments Due Date (a) We must receive comments by January 7, 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. erowe on DSK5CLS3C1PROD with PROPOSALS-1 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. 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 AD 2010–0137, dated June 30, 2010, for related information. Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D–09350, Lichtenstein, Germany, telephone: +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; telephone (781) 238–7143; fax (781) 238–7199, for more information about this AD. Issued in Burlington, Massachusetts, on November 16, 2010. Peter A. White, Assistant Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 2010–29449 Filed 11–22–10; 8:45 am] BILLING CODE 4910–13–P 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: VerDate Mar<15>2010 14:36 Nov 22, 2010 Jkt 223001 PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 71373 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–0494; Directorate Identifier 2010–NE–20–AD] RIN 2120–AA64 Airworthiness Directives; International Aero Engines V2500–A1, V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to adopt a new airworthiness directive (AD) for International Aero Engines (IAE) V2500–A1, V2522–A5, V2524–A5, V2525–D5, V2527–A5, V2527E–A5, V2527M–A5, V2528–D5, V2530–A5, and V2533–A5 turbofan engines. This proposed AD would require initial and repetitive 360° borescope inspections of high-pressure turbine (HPT) stage 1 blade outer air seal segments for evidence of certain distress conditions. This proposed AD would also require incorporation of improved durability stage 1 blade outer air seal segments at the next exposure to the HPT module subassembly, as terminating action to the repetitive inspections. This proposed AD results from three reports received of HPT case burn-through events, numerous shop reports of loss of stage 1 blade outer air seal segments, and HPT case bulging. We are proposing this AD to prevent HPT case burnthrough, uncontrolled under-cowl engine fire, and damage to the airplane. DATES: We must receive any comments on this proposed AD by January 24, 2011. SUMMARY: Use one of the following addresses to comment on this proposed AD. • Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your comments electronically. • Mail: Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue, SE., West Building Ground Floor, Room W12–140, Washington, DC 20590–0001. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. • Fax: (202) 493–2251. ADDRESSES: E:\FR\FM\23NOP1.SGM 23NOP1

Agencies

[Federal Register Volume 75, Number 225 (Tuesday, November 23, 2010)]
[Proposed Rules]
[Pages 71371-71373]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-29449]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0820; Directorate Identifier 2010-NE-31-AD]
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: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above. This proposed 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 proposing this AD to prevent engine in-flight shutdown or 
power loss, possibly resulting in reduced control of the airplane.

DATES: We must receive comments on this proposed AD by January 7, 2011.

ADDRESSES: You may send comments by any of the following methods:

[[Page 71372]]

     Federal eRulemaking Portal: Go to https://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.
    Contact Thielert Aircraft Engines GmbH, Platanenstrasse 14 D-09350, 
Lichtenstein, Germany, telephone: +49-37204-696-0; fax: +49-37204-696-
2912; e-mail: engines.com">info@centurion-engines.com for the service information 
identified in this proposed AD.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (phone (800) 647-5527) is the 
same as the Mail address provided in the ADDRESSES section. Comments 
will be available in the AD docket shortly after receipt.

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; telephone (781) 238-7143; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-0820; 
Directorate Identifier 2010-NE-31-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
2010-0137, dated June 30, 2010 (referred to after this as ``the 
MCAI''), 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.

    We are proposing to require installation of full-authority digital 
electronic control (FADEC) software version 2.91 to prevent automatic 
switching to channel B if the channel B MAP sensor hose is leaking. The 
current software cannot detect the difference between a manifold leak 
and a real manifold pressure change. This software installation will 
prevent the undesired limiting of fuel to the engine. Installing FADEC 
software version 2.91 will also prevent the FADEC from self-testing 
during flight, which would cause an engine in-flight shutdown.
    You may obtain further information by examining the MCAI in the AD 
docket.

FAA's Determination and Requirements of This Proposed AD

    These products 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 has notified us of the 
unsafe condition described in the MCAI. We are proposing 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 
products of the same type design. This proposed AD would require 
installing full authority digital electronic control software version 
2.91.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 112 engines installed on airplanes of U.S. registry. 
We also estimate that it would take about 0.5 work-hour per engine to 
comply with this proposed 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 proposed 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 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 proposed 
regulation:
    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

[[Page 71373]]

under the criteria of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by adding the following new 
airworthiness directive (AD):

Thielert Aircraft Engines GmbH: Docket No. FAA-2010-0820; 
Directorate Identifier 2010-NE-31-AD.

Comments Due Date

    (a) We must receive comments by January 7, 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-
01-02, Issue 3, Revision 13.
    (ii) For TAE 125-02-99 and TAE 125-02-114 engines, Operation & 
Maintenance Manual OM-02-02, Issue 1, Revision 10.

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 AD 2010-0137, dated June 30, 2010, for related 
information. Contact Thielert Aircraft Engines GmbH, Platanenstrasse 
14 D-09350, Lichtenstein, Germany, telephone: +49-37204-696-0; fax: 
+49-37204-696-2912; e-mail: engines.com">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; 
telephone (781) 238-7143; fax (781) 238-7199, for more information 
about this AD.

    Issued in Burlington, Massachusetts, on November 16, 2010.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2010-29449 Filed 11-22-10; 8:45 am]
BILLING CODE 4910-13-P