[Federal Register Volume 67, Number 181 (Wednesday, September 18, 2002)]
[Rules and Regulations]
[Pages 58686-58687]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-23652]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-42-AD; Amendment 39-12882; AD 2002-19-02]
RIN 2120-AA64


Airworthiness Directives; Turbomeca S.A. Makila Models 1A, 1A1, 
and 1A2 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 S.A. Makila Models 1A, 1A1, and 1A2 
turboshaft engines with exhaust pipes incorporating modification TU 
200A installed. This action requires visual inspections of exhaust 
pipes for cracks and tears, upon completion of the last flight of each 
day, and replacement of cracked and torn exhaust pipes before further 
flight. This action also requires removal from service of modification 
TU 200A exhaust pipes at the next shop visit or no later than a certain 
date. This amendment is prompted by several reports of modification TU 
200A exhaust pipes cracking at several of the ejector attachment tabs. 
The actions specified in this AD are intended to prevent the ejector 
from becoming loose from the exhaust pipe, resulting in damage to the 
main rotor and tail rotor and loss of helicopter control.

DATES: Effective October 3, 2002.
    Comments for inclusion in the Rules Docket must be received on or 
before November 18, 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-42-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at 
this location, by appointment, between 8 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: ``[email protected]''. 
Comments sent via the Internet must contain the docket number in the 
subject line.

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 S.A. 
Makila Models 1A, 1A1, and 1A2 turboshaft engines with modification TU 
200A exhaust pipes installed. The exhaust pipe is composed of a primary 
exhaust pipe mounted on the engine, and an ejector pipe fixed on the 
primary exhaust pipe by eight attachment tabs. The DGAC advises that 
several reports were received of modification TU 200A exhaust pipes 
cracking at several of the ejector attachment tabs. This type of 
deterioration, if allowed to continue, can result in damage to the main 
rotor and tail rotor and loss of helicopter control. The DGAC issued AD 
T2001-301(A), dated July 3, 2001, and AD 2002-124(A), dated March 6, 
2002, in order to assure the airworthiness of these Turbomeca S.A. 
Makila models 1A, 1A1, and 1A2 turboshaft engines in France.

Bilateral Airworthiness Agreement

    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 S.A. Makila Models 1A, 1A1, and 1A2 
turboshaft engines of the same type design, this AD is being issued to 
prevent the ejector from becoming loose from the exhaust pipe, 
resulting in damage to the main rotor and tail rotor and loss of 
helicopter control. This AD requires visual inspections of exhaust 
pipes for cracks and tears, upon completion of the last flight of each 
day and replacement of cracked and torn exhaust pipes before further 
flight. This action also requires as terminating action to the 
repetitive inspections, removal from service of modification TU 200A 
exhaust pipes at the next shop visit, or no later than June 30, 2003.

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 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

[[Page 58687]]

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-42-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, 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:

2002-19-02 Turbomeca S.A.: Amendment 39-12882. Docket No. 2001-NE-
42-AD.

Applicability

    This airworthiness directive (AD) is applicable to Turbomeca 
S.A. Makila models 1A, 1A1, and 1A2 turboshaft engines with exhaust 
pipes incorporating modification TU 200A installed. These engines 
are installed on, but not limited to, Aerospatiale AS 332 ``Super 
Puma Mark I'' C, C1, L, L1, and ``Super Puma Mark II'' L2 
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 (f) 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 as indicated, unless already 
done.
    To prevent the ejector from becoming loose from the exhaust 
pipe, resulting in damage to the main rotor and tail rotor and loss 
of helicopter control, do the following:
    (a) Upon completion of the last flight of each day, clean and 
visually inspect exhaust pipes for cracks and tears, focusing on the 
ejector attachment tabs that connect the ejector to the primary 
exhaust pipe. Information on exhaust pipe inspection for Turbomeca 
S.A. Makila models 1A and 1A1 may be found in Engine Maintenance 
Manual (EMM) Section 78-10-601, and EMM Section 78-11-00 for Makila 
model 1A2.
    (b) On exhaust pipes also incorporating modification TU 54, use 
a mirror placed between the engine firewall and the exhaust pipe, 
and visually inspect the furthest aft attachment tab, as specified 
in paragraph (a) of this AD.
    (c) Replace exhaust pipe at the first visual sign of any exhaust 
pipe crack or tear before further flight. Information on exhaust 
pipe replacement for Turbomeca S.A. Makila models 1A and 1A1 may be 
found in EMM Section 78-10-401, and EMM Section 78-11-00 for Makila 
model 1A2.
    (d) After the replacement exhaust pipe is installed, before 
further flight, perform engine vibration level checks to ensure all 
vibration levels are within manufacturer's limits. Information on 
vibration level checks for Turbomeca S.A. Makila models 1A and 1A1 
may be found in EMM Section 71-00-601, and EMM Section 71-00-00 for 
Makila model 1A2.

Terminating Action

    (e) Remove from service exhaust pipes incorporating modification 
TU 200A at the next shop visit, or no later than June 30, 2003. 
Removal from service constitutes terminating action to the 
repetitive visual inspections required by this AD. Information on 
removal from service may be found in Turbomeca S.A. Alert Service 
Bulletin No. A298 72 0148, Update No. 1, dated February 18, 2002.

Alternative Methods of Compliance

    (f) 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 requests 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 compliance with this airworthiness directive, 
if any, may be obtained from the ECO.


    Note 3: The subject of this AD is addressed in the Direction 
Generale de L'Aviation Civile airworthiness directive AD T2001-
301(A), dated July 3, 2001, and AD 2002-124(A), dated March 6, 2002.

Effective Date

    (g) This amendment becomes effective on October 3, 2002.

    Issued in Burlington, Massachusetts, on September 9, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-23652 Filed 9-17-02; 8:45 am]
BILLING CODE 4910-13-P