AD 2002-15-05

[Federal Register Volume 67, Number 148 (Thursday, August 1, 2002)]
[Rules and Regulations]
[Pages 49859-49861]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-19164]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-23-AD; Amendment 39-12833; AD 2002-15-05]
RIN 2120-AA64


Airworthiness Directives; Turbomeca Makila 1 A, 1 A1, and 1 A2 
Turboshaft Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD) that 
is applicable to Turbomeca Makila 1 A, 1 A1, and 1 A2 turboshaft 
engines. This action requires replacing certain digital electronic 
control units (DECU's) and electronic control units (ECU's) with 
modified DECU's and ECU's. This amendment is prompted by a report of an 
uncontained engine turbine wheel failure and the subsequent loss of 
control of the helicopter. The actions specified in this AD are 
intended to prevent an engine overspeed condition resulting from the 
failure of two or more NTL channels.

DATES: Effective August 16, 2002. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of August 16, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before September 30, 2002.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-23-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8:00 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. Comments may also be sent via 
the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#c8f1e5a9a6ade5a9acaba7a5a5ada6bc88aea9a9e6afa7be"><span class="__cf_email__" data-cfemail="dae3f7bbb4bff7bbbeb9b5b7b7bfb4ae9abcbbbbf4bdb5ac">[email&#160;protected]</span></a>''. 
Comments sent via the Internet must contain the docket number in the 
subject line.
    The service information referenced in this AD may be obtained from 
Turbomeca, 40220 Tarnos, France; telephone (33) 05 59 74 40 00; fax 
(33) 05 59 74 45 15. This information may be examined, by appointment, 
at the FAA, New England Region, Office of the Regional Counsel, 12 New 
England Executive Park, Burlington, MA; or at the Office of the Federal 
Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Glorianne Niebuhr, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7132; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The Direction Generale De L'Aviation Civile 
(DGAC), which is the airworthiness authority for France, recently 
notified the FAA that an unsafe condition may exist on Turbomeca Makila 
1 A, 1 A1, and 1 A2 turboshaft engines. The DGAC advises that there has 
been an accident in which the helicopter experienced an engine 
overspeed, which resulted in an uncontained power turbine burst and the 
failure of both engines. Investigation has determined that the power 
turbine overspeed was caused by a failure of an engine-to-main gearbox 
(MGB) connection. One of the two failed NTL channels could be selected 
by the ECU and used to set the gas generator (Ng) demand, which in turn 
could cause an overspeed condition. Modification TU 203 to the ECU's 
that are used on the Makila 1 A and 1 A1 turboshaft engines improves 
failure detection of the ECU and simulates a fixed power turbine speed 
(Npt) if two of the three channels fail. Modification TU 215 to the 
ECU's used on the Makila 1A and 1A1 turboshaft engines changes the 
ceramic case timer to a metal case timer, which improves the unit's 
mechanical resistance. The simulated fixed Npt causes the gas generator 
to decelerate to a safe level. Modification TU 205C to the DECU's used 
on the Makila 1 A2 turboshaft engines upgrades the DECU software from 
version 6.01 to version 7.01. That upgrade improves the failure 
detection of the DECU and simulates a revised fixed Npt when both 
channels fail. The revised simulated fixed Npt value drives the gas 
generator to decelerate to 65% instead of the 85% value before 
modification. The 85% value before modification may not have been 
enough to avoid Npt overspeed.
    The compliance times required by this AD were determined as a 
function of the manufacturing rate of the required parts and the 
maximum availability of the repairing centers.

Manufacturer's Service Information

    Turbomeca has issued the following service bulletins (SB's):
    <bullet> SB No. 298 73 0149, dated January 13, 2000, that specifies 
procedures for incorporating modification TU 205C on DECU's used on 
Makila 1 A2 turboshaft engines.
    <bullet> SB No. 298 73 0166, dated October 5, 2001, that specifies 
procedures for incorporating modification TU 215 on ECU's used on 
Makila 1 A and 1 A1 turboshaft engines.
    The DGAC classified these service bulletins as mandatory and issued 
AD's 2000-068(A), dated February 9, 2000, and 2001-546(A), dated 
November 14, 2001, in order to assure the airworthiness of these 
Turbomeca engines in France.

Bilateral Agreement Information

    This engine model is manufactured in France and is type 
certificated for operation in the United States under the provisions of 
Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the 
applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. The FAA has examined the findings of 
the DGAC, reviewed all available information, and determined that AD 
action is necessary for products of this type design that are 
certificated for operation in the United States.

FAA's Determination of an Unsafe Condition and Required Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other Turbomeca Makila 1 A, 1 A1, and 1 A2 
turboshaft engines of the same type design, this AD is being issued to 
prevent an engine overspeed condition resulting from the failure of two 
or more NTL channels. This AD requires replacing the Makila 1 A and 1 
A1 ECU's, P/N's 0 177 69 810 0, 0 177 69 811 0, 0 177 69 812 0, 0 177 
69 813 0, 0 177 69 814 0, 0 177 69 815 0, 0 177 69 816 0, 0 177 69 817 
0, 0 177 69 818 0, 0 177 69 819 0, 0 177 69 820 0, and 0 177 69 824 0, 
0 177 69 825 0, 0 177 69 826 0, 0 177 69 827 0, 0 177 69 828 0, and 0 
177 69 829 0; with ECU's that have been modified to modification 
standard TU 215. This AD also requires replacing Makila 1 A2 DECU's, P/
N 70CMB01040, with modified DECU's, P/N 70CMB01050.

Immediate Adoption of This AD

    Since a situation exists that requires the immediate adoption of 
this regulation, it is found that notice and opportunity for prior 
public comment

[[Page 49860]]

hereon are impracticable, and that good cause exists for making this 
amendment effective in less than 30 days.

Comments Invited

    Although this action is in the form of a final rule that involves 
requirements affecting flight safety and, thus, was not preceded by 
notice and an opportunity for public comment, comments are invited on 
this rule. Interested persons are invited to comment on this rule by 
submitting such written data, views, or arguments as they may desire. 
Communications should identify the Rules Docket number and be submitted 
in triplicate to the address specified under the caption ADDRESSES. All 
communications received on or before the closing date for comments will 
be considered, and this rule may be amended in light of the comments 
received. Factual information that supports the commenter's ideas and 
suggestions is extremely helpful in evaluating the effectiveness of the 
AD action and determining whether additional rulemaking action would be 
needed.
    Comments are specifically invited on the overall regulatory, 
economic, environmental, and energy aspects of the rule that might 
suggest a need to modify the rule. All comments submitted will be 
available, both before and after the closing date for comments, in the 
Rules Docket for examination by interested persons. A report that 
summarizes each FAA-public contact concerned with the substance of this 
AD will be filed in the Rules Docket.
    Commenters wishing the FAA to acknowledge receipt of their comments 
submitted in response to this action must submit a self-addressed, 
stamped postcard on which the following statement is made: ``Comments 
to Docket Number 2001-NE-23-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Analysis

    This final rule does not have federalism implications, as defined 
in Executive Order 13132, because it 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. Accordingly, 
the FAA has not consulted with state authorities prior to publication 
of this final rule.
    The FAA has determined that this regulation is an emergency 
regulation that must be issued immediately to correct an unsafe 
condition in aircraft, and is not a ``significant regulatory action'' 
under Executive Order 12866. It has been determined further that this 
action involves an emergency regulation under DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979). If it is determined 
that this emergency regulation otherwise would be significant under DOT 
Regulatory Policies and Procedures, a final regulatory evaluation will 
be prepared and placed in the Rules Docket. A copy of it, if filed, may 
be obtained from the Rules Docket at the location provided under the 
caption ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (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. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-15-05  Turbomeca: Amendment 39-12833. Docket No. 2001-NE-23-AD.

Applicability

    This airworthiness directive (AD) is applicable to Turbomeca 
Makila 1 A, 1 A1, and 1 A2 turboshaft engines with digital 
electronic control units (DECU's) and electronic control units 
(ECU's) that have a part number (P/N) listed in the following Table 
1:

                      Table 1.--ECU and DECU P/N's
------------------------------------------------------------------------
              ECU or DECU P/N                          Used on
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0 177 69 810 0, 0 177 69 811 0, 0 177 69     Makila 1 A and 1 A1
 812 0, 0 177 69 813 0, 0 177 69 814 0, 0     engines.
 177 69 815 0, 0 177 69 816 0, 0 177 69 817
 0, 0 177 69 818 0, 0 177 69 819 0, 0 177
 69 820 0, 0 177 69 824 0, 0 177 69 825 0,
 0 177 69 826 0, 0 177 69 827 0, 0 177 69
 828 0, and 0 177 69 829 0.
70CMB01040.................................  Makila 1 A2 engines.
------------------------------------------------------------------------

These engines are installed on, but not limited to Eurocopter France 
model AS 332C, AS 332L, AS 332L1 and AS 332L2, helicopters.

    Note 1: This AD applies to each engine identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For engines that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (c) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

Compliance

    Compliance with this AD is required within 45 days after the 
effective date of this AD, unless already done.
    To prevent an engine overspeed condition resulting from the 
failure of two or more NTL channels, do the following:
    (a) For Makila 1 A and 1 A1 engines do either of the following:
    (1) Replace ECU's that have a P/N listed in Table 1 of this AD, 
with ECU's that have been modified to modification standard TU 215, 
or
    (2) Replace the comparator / selector circuit board in 
accordance with Turbomeca service bulletin (SB) 298 73 0166, dated 
October 5, 2001.
    (b) For Makila 1 A2 engines, replace DECU, P/N 70CMB01040, with 
modified DECU, P/N 70CMB01050. Information on the modified DECU may 
be found in Turbomeca service bulletin (SB) 298 73 0149, dated 
January 13, 2000.

Alternative Methods of Compliance

    (c) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be 
used if approved by the Manager, Engine Certification Office (ECO). 
Operators must submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, ECO.

    Note 2: Information concerning the existence of approved 
alternative methods of

[[Page 49861]]

compliance with this airworthiness directive, if any, may be 
obtained from the ECO.

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 
21.197 and 21.199) to operate the helicopter to a location where the 
requirements of this AD can be done.

Documents That Have Been Incorporated By Reference

    (e) The inspection must be done in accordance with Turbomeca 
Service Bulletin No. 298 73 0166, dated October 5, 2001. This 
incorporation by reference was approved by the Director of the 
Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 
51. Copies may be obtained from Turbomeca, 40220 Tarnos, France. 
Copies may be inspected at the FAA, New England Region, Office of 
the Regional Counsel, 12 New England Executive Park, Burlington, MA; 
or at the Office of the Federal Register, 800 North Capitol Street, 
NW, suite 700, Washington, DC.

    Note 3: The subject of this AD is addressed in DGAC 
airworthiness directives 2000-068(A), dated February 9, 2000, and 
2001-546(A), dated November 14, 2001.

Effective Date

    (f) This amendment becomes effective on August 16, 2002.

    Issued in Burlington, Massachusetts, on July 23, 2002.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 02-19164 Filed 7-31-02; 8:45 am]
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