AD 2001-17-14

[Federal Register Volume 66, Number 164 (Thursday, August 23, 2001)]
[Rules and Regulations]
[Pages 44297-44299]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 01-21221]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-15-AD; Amendment 39-12405; AD 2001-17-14]
RIN 2120-AA64


Airworthiness Directives; CFM International CFM56 Series Turbofan 
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 CFM International (CFMI) CFM56-5C4/1 series turbofan 
engines. This action requires that the LPT conical support, P/N 337-
002-407-0, installed in CFM56-5C4/1 engines, be removed from service at 
or before reaching the cyclic life limit of 9,350 cycles-since-new 
(CSN). This amendment is prompted by the discovery of an error in the 
Time Limits Section of Chapter 5 of the CFM56-5C Engine Shop Manual. 
The manual incorrectly lists the published cyclic life limit of the 
CFMI CFM56-5C4/1 LPT conical support, (P/N) 337-002-407-0, as 15,000 
CSN, rather than the certified value of 9,350 CSN. The actions 
specified in this AD are intended to prevent LPT conical supports from 
remaining in service beyond their certified cyclic life limit, which 
could result in an uncontained engine failure and damage to the 
airplane.

DATES: Effective September 7, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before October 22, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation

[[Page 44298]]

Administration (FAA), New England Region, Office of the Regional 
Counsel, Attention: Rules Docket No. 2001-NE-15-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. Comments may also be sent 
via the Internet using the following address: ``<a href="/cdn-cgi/l/email-protection#5c65713d3239713d383f3331313932281c3a3d3d723b332a"><span class="__cf_email__" data-cfemail="58617539363d75393c3b3735353d362c183e3939763f372e">[email&#160;protected]</span></a>''. Comments sent via the Internet must contain the 
docket number in the subject line.

FOR FURTHER INFORMATION CONTACT: Diane Cook, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: The FAA has been informed by CFMI that the 
cyclic life limit of the CFM56-5C4/1 Low Pressure Turbine (LPT) conical 
support, P/N 337-002-407-0, published in the Time Limits Section of 
Chapter 5 of the CFM56-5C Engine Shop Manual is incorrect, and will be 
corrected at the next revision to the manual. The incorrect published 
cyclic life reads 15,000 cycles since new (CSN) instead of the 
certified value of 9,350 CSN. This condition, if not corrected, could 
result in the LPT conical support remaining in service beyond its 
certified cyclic life limit, which could result in an uncontained 
engine failure and damage to the airplane. Currently, the CFMI fleet 
has not incorporated LPT Conical Support, P/N 337-002-407-0, into any 
of the CFM56-5C4/1 engines. Therefore, this AD will not result in any 
economic impact on the U.S. operators. However, as the operators 
convert CMF56-5C engines into different model configurations, there is 
a potential that LPT Conical Support, P/N 337-002-407-0, will be 
installed in the CFM56-5C4/1 engine model.

FAA's Determination of An Unsafe Condition and Proposed Actions

    Although this affected engine model is not used on any airplanes 
that are registered in the United States, the possibility exists this 
engine model could be used on airplanes that are registered in the 
United States in the future. This AD reestablishes the certified cyclic 
life limit for LPT conical support P/N 337-002-407-0, by requiring the 
replacement of LPT conical support P/N 337-002-407-0, at or before 
accumulating 9,350 CSN. This AD is being issued to prevent LPT conical 
supports from remaining in service beyond their certified cyclic life 
limit, which could result in an uncontained engine failure and damage 
to the airplane.

Immediate Adoption of This AD

    Since there are no domestic operators of this engine model, notice 
and opportunity for prior public comment are unnecessary. Therefore, a 
situation exists that allows the immediate adoption of this regulation.

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-15-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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:

2001-17-14  CFM International: Amendment 39-12405. Docket 2001-NE-
15-AD.

Applicability

    This airworthiness directive (AD) is applicable to CFM 
International (CFMI) CFM56-5C4/1 series turbofan engines with low 
pressure turbine (LPT) conical support, part number (P/N) 337-002-
407-0, installed. These engines are installed on, but not limited to 
Airbus Industrie A320 series airplanes.

    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 (d) 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

[[Page 44299]]

been eliminated, the request should include specific proposed 
actions to address it.

Compliance

    Compliance with this AD is required as indicated.
    To prevent an LPT conical support from remaining in service 
beyond its certified cyclic life limit, which could result in an 
uncontained engine failure and damage to the airplane, accomplish 
the following:
    (a) Remove LPT conical support, P/N 337-002-407-0, at or before 
accumulating 9,350 cycles-since-new (CSN) and replace with a 
serviceable part.
    (b) After the effective date of this AD, do not install any LPT 
conical support, P/N 337-002-407-0 with 9,350 CSN or greater, into 
CFM56-5C4/1 model engines.
    (c) This AD reestablishes the certified cyclic life limit for 
LPT conical support,
P/N 337-002-407-0, which was published incorrectly in the Time 
Limits Section of Chapter 5 of the CFM56-5C Engine Shop Manual. This 
Manual will be revised to correct this error. Thereafter, except as 
provided in paragraph (d) of this AD, no alternative cyclic 
retirement life limits may be approved for LPT conical support, P/N 
337-002-407-0.

Alternative Methods of Compliance

    (d) 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.

Effective Date of This AD

    (e) This amendment becomes effective on September 7, 2001.


    Issued in Burlington, Massachusetts, on August 15, 2001.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 01-21221 Filed 8-22-01; 8:45 am]
BILLING CODE 4910-13-P