AD 2008-08-16

[Federal Register Volume 73, Number 74 (Wednesday, April 16, 2008)]
[Rules and Regulations]
[Pages 20525-20526]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: E8-8083]



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Federal Register / Vol. 73, No. 74 / Wednesday, April 16, 2008 / 
Rules and Regulations

[[Page 20525]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0157; Directorate Identifier 2001-NE-23-AD; 
Amendment 39-15469; AD 2008-08-16]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Makila 1A and 1A1 Turboshaft 
Engines

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: The FAA is superseding an existing airworthiness directive 
(AD) for Turbomeca Makila 1A, 1A1, and 1A2 turboshaft engines. That AD 
currently requires replacing certain digital electronic control units 
(DECUs) and electronic control units (ECUs) with modified DECUs and 
ECUs. This AD applies only to Makila 1A and 1A1 turboshaft engines, and 
requires replacing the selector-comparator board in the ECU with a 
board incorporating Turbomeca modification TU 250. This AD results from 
recent unexplained reversions of the ECU to the 65% N1 back-up mode. We 
are issuing this AD to prevent dual-engine continued operation at 65% 
N1 after reversion of the ECU to the 65% N1 back-up mode due to 
temporary loss of N2 speed signal, which could lead to inability to 
continue safe flight, emergency autorotation landing, or an accident.

DATES: This AD becomes effective May 21, 2008.

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.
    You can get the service information identified in this AD from 
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax 
(33) 05 59 74 45 15.

FOR FURTHER INFORMATION CONTACT: James Lawrence, 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#365c575b5345185a574144535855537650575718515940"><span class="__cf_email__" data-cfemail="157f747870663b79746267707b7670557374743b727a63">[email&#160;protected]</span></a>; telephone (781) 238-7176; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39 by 
superseding AD 2002-15-05, Amendment 39-12833 (67 FR 49859, August 1, 
2002), with a proposed AD. The proposed AD applies to Turbomeca Makila 
1A and 1A1 turboshaft engines. We published the proposed AD in the 
Federal Register on November 15, 2007 (72 FR 64172). That action 
proposed to require replacing the selector-comparator board in the ECU 
with a board incorporating Turbomeca modification TU 250.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; 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 (telephone (800) 647-5527) is provided in 
the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the proposal or on 
the determination of the cost to the public. We also found we needed to 
clarify the unsafe condition statement from ``We are issuing this AD to 
prevent dual-engine reversion of the ECU to the 65% N1 back-up mode, 
which could lead to inability to continue safe flight, emergency 
autorotation landing, or an accident'' to ``We are issuing this AD to 
prevent dual-engine continued operation at 65% N1 after reversion of 
the ECU to the 65% N1 back-up mode due to temporary loss of N2 speed 
signal, which could lead to inability to continue safe flight, 
emergency autorotation landing, or an accident''.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD with the 
change described previously.

Makila 1A2 Turboshaft Engines Excluded From This AD

    Although Makila 1A2 turboshaft engines, which were also listed in 
the previous AD, might be affected by this unsafe condition, EASA is 
reviewing the need to mandate a corrective action. Depending on the 
review outcome, we might address those engines in another AD action.

Costs of Compliance

    We estimate that this AD will affect 10 Makila 1A and 1A1 
turboshaft engines installed on helicopters of U.S. registry. We also 
estimate that it will take about 1 work-hour per engine to perform the 
actions, and that the average labor rate is $80 per work-hour. Required 
parts will cost about $3,500 per engine. Based on these figures, we 
estimate the total cost of the AD to U.S. operators to be $35,800.

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 have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will

[[Page 20526]]

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); 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 summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary at the 
address listed under ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the Federal Aviation Administration 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 removing Amendment 39-12833 (67 FR 
49859, August 1, 2002), and by adding a new airworthiness directive, 
Amendment 39-15469, to read as follows:

2008-08-16 Turbomeca: Amendment 39-15469. Docket No. FAA-2007-0157; 
Directorate Identifier 2001-NE-23-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 21, 
2008.

Affected ADs

    (b) This AD supersedes AD 2002-15-05, Amendment 39-12833.

Applicability

    (c) This AD applies to Turbomeca Makila 1A and 1A1 turboshaft 
engines. These engines are installed on, but not limited to, 
Eurocopter France model AS 332C, AS 332L, and AS 332L1 helicopters.

Unsafe Condition

    (d) This AD results from recent unexplained reversions of the 
electronic control unit (ECU) to the 65% N1 back-up mode. The 
actions specified in this AD are intended to prevent dual-engine 
continued operation at 65% N1 after reversion of the ECU to the 65% 
N1 back-up mode due to temporary loss of N2 speed signal, which 
could lead to inability to continue safe flight, emergency 
autorotation landing, or an accident.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed before June 30, 2008, unless the actions have already 
been done.
    (f) Replace the selector-comparator board in the ECU with a 
board incorporating Turbomeca Modification TU 250. Information on 
Modification TU 250 can be found in Turbomeca Mandatory Service 
Bulletin No. 298 73 0250, dated March 23, 2007.

Alternative Methods of Compliance

    (g) The Manager, Engine Certification Office, FAA, has the 
authority to approve alternative methods of compliance for this AD 
if requested using the procedures found in 14 CFR 39.19.

Related Information

    (h) European Aviation Safety Agency AD 2007-0144, dated May 18, 
2007, also addresses the subject of this AD.
    (i) Contact James Lawrence, 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#214b404c44520f4d405653444f4244614740400f464e57"><span class="__cf_email__" data-cfemail="acc6cdc1c9df82c0cddbdec9c2cfc9eccacdcd82cbc3da">[email&#160;protected]</span></a>; telephone (781) 238-7176; fax (781) 238-
7199, for more information about this AD.

    Issued in Burlington, Massachusetts, on April 8, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-8083 Filed 4-15-08; 8:45 am]
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