[Federal Register Volume 76, Number 62 (Thursday, March 31, 2011)]
[Rules and Regulations]
[Pages 17757-17758]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-7293]


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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.

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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: 
<a href="/cdn-cgi/l/email-protection#86e7eae7e8a8f5f2f4e9ebc6e0e7e7a8e1e9f0"><span class="__cf_email__" data-cfemail="8beae7eae5a5f8fff9e4e6cbedeaeaa5ece4fd">[email protected]</span></a>; 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

[[Page 17758]]

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

0
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]

0
2. The FAA amends Sec.  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: <a href="/cdn-cgi/l/email-protection#3c55525a537c5f595248494e55535211005d1c544e595a01" http: engines.com">engines.com</a>">info@centurion-engines.com</a>, 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: <a href="/cdn-cgi/l/email-protection#07666b666929747375686a4761666629606871"><span class="__cf_email__" data-cfemail="adccc1ccc383ded9dfc2c0edcbcccc83cac2db">[email protected]</span></a>; 
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


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