[Federal Register Volume 66, Number 90 (Wednesday, May 9, 2001)]
[Rules and Regulations]
[Pages 23541-23543]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-11615]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-08-AD; Amendment 39-12224; AD 2001-09-17]
RIN 2120-AA64


Airworthiness Directives; CFM International (CFMI) CFM56-5C 
Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: This amendment supersedes an emergency airworthiness directive 
(AD) that was sent previously to all known U.S. owners and operators of 
CFMI CFM56-5C turbofan engines by individual letters. That action 
required within 10 days after receipt of that emergency AD, an initial 
inspection of the fuel manifold for wear or chafing; and an initial 
inspection of the CJ9L harness for correct installation, for clamp wear 
and to verify a minimum clearance between the CJ9L harness and the fuel 
manifold. That action also required repetitive inspections of the fuel 
manifold, clamps, and the CJ9L harness within every 500 hours time in 
service until new configuration clamps are installed on the harness. 
This amendment requires the same inspections, and adds inspection 
requirements for the manifold, clamps, and the CJ10L harness, and 
clamps on the other side of the engine. The actions specified in this 
AD are intended to prevent fuel leakage on the hot section or in the 
primary fire zone of the engine which may result in an engine fire and 
subsequent damage to the airplane.

DATES: Effective May 14, 2001. The incorporation by reference of 
certain publications listed in the rule is approved by the Director of 
the Federal Register as of May 14, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before July 9, 2001.

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-08-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#dae3f7bbb4bff7bbbeb9b5b7b7bfb4ae9abcbbbbf4bdb5ac"><span class="__cf_email__" data-cfemail="f3cade929d96de9297909c9e9e969d87b3959292dd949c85">[email 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 CFM International, Technical 
Publications Department, 1 Neumann Way, Cincinnati, OH 45215; telephone 
(513) 552-2981, fax (513) 552-2816. This information may be examined 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: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; telephone (781) 238-7152; 
fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On April 10, 2001, the Federal Aviation 
Administration (FAA) issued emergency airworthiness directive (AD) 
2001-08-51, applicable to CFMI CFM56-5C turbofan engines, which 
requires within 10 days after the receipt of that AD, an initial 
inspection of the fuel manifold for wear or chafing; and an initial 
inspection of the CJ9L harness for wear and correct installation, for 
clamp wear and to verify a minimum clearance between the CJ9L harness 
and the fuel manifold. Repetitive inspections of the fuel manifold, 
clamps, and CJ9L harness are also required within every 500 hours time-
in-service until the new configuration clamps are installed on the 
harness. That AD was prompted by a report of a significant engine fuel 
leak under the thrust reverser cowls at the fuel manifold level on a 
CFMI CFM56-5C turbofan engine that was installed on an Airbus Industrie 
A340 airplane. The leak was confirmed to be coming from a hole in the 
fuel manifold pigtail. The hole was a result of interference and 
chafing between the CJ9L harness high pressure turbine clearance 
control (HPTCC) sensor lead and fuel manifold. This was the second fuel 
leak event at this location. Additional engine inspections by the 
operator who experienced the engine fuel leak discovered two other 
engines exhibiting interference of the CJ9L harness with fuel manifold 
and chafing of the fuel manifold. In addition, since the FAA issued the 
emergency AD, chafing was found on the CJ10L harness, located on the 
other side of an engine from the CJ9L harness. The investigation has 
identified three causes for lack of clearance between the HPTCC 
harnesses and the fuel manifold:
    (1) Incorrect routing of the CJ9L and CJ10L harnesses,
    (2) Incorrect orientation of the CJ9L and CJ10L harness cushion 
clamps, and
    (3) Wear of the silicone material in the clamp which allows the 
harnesses to move within the clamp. This clamp material is used on 
older configuration clamps. The later configuration uses a metallic 
material.
    The actions specified by this AD are intended to prevent fuel 
leakage on the hot section or in the primary fire zone of the engine, 
which may result in an engine fire and subsequent damage to the 
airplane.
    Since emergency AD 2001-08-51 was issued, it has been determined 
that the same unsafe condition exists at the CJ10L HPTCC harness, 
located on the opposite side of the engine from the CJ9L harness.

Manufacturer's Service Information

    The FAA has reviewed and approved CFMI Alert Service Bulletin (ASB) 
No. CFM56-5C S/B 73-A0106, Revision 1, dated April 19, 2001, that 
specifies procedures for inspection of the fuel

[[Page 23542]]

manifold for wear or chafing, and inspection of the CJ9L harness for 
wear and correct installation, for clamp wear and to verify a minimum 
clearance between the CJ9L harness and the fuel manifold.

Differences Between This AD and the Manufacturer's Service 
Information

    CFMI ASB CFM56-5C S/B 73-A0106, Revision 1, dated April 19, 2001, 
requires only inspections of the CJ9L HPTCC sensor harness. The FAA has 
determined that the same inspections must be performed on the CJ10L 
HPTCC sensor harness, located on the opposite side of the engine from 
the CJ9L harness.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Although none of these affected engine models are used on any 
airplanes that are registered in the United States, the possibility 
exists that the engine models could be used on airplanes that are 
registered in the United States in the future. This AD is being issued 
to prevent fuel leakage on the hot section or in the primary fire zone 
of the engine, which may result in an engine fire and subsequent damage 
to the airplane. This AD requires within 10 days after the effective 
date of this AD, an initial inspection of the fuel manifold for wear or 
chafing; and an initial inspection of the CJ9L and CJ10L harnesses for 
wear and correct installation, for clamp wear and to verify a minimum 
clearance between the harnesses and the fuel manifold. Repetitive 
inspections of the fuel manifold, clamps, and the CJ9L and CJ10L 
harnesses will be required within every 500 hours time in service until 
the new configuration clamps are installed on the harness. The actions 
must be done in accordance with the service bulletin described 
previously.

Immediate Adoption of This AD

    Since there are currently 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-08-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, 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 a new airworthiness 
directive, Amendment 39-12224, to read as follows:

2001-09-17  CFM International: Amendment 39-12224. Docket 2001-NE-
08-AD. Supersedes AD 2001-08-51.

    Applicability: This airworthiness directive (AD) is applicable 
to CFM International (CFMI) CFM56-5C turbofan engines. These engines 
are installed on, but not limited to, Airbus Industrie A340 
airplanes.

    Note 1: This airworthiness directive (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 been eliminated, the request should include specific 
proposed actions to address it.

Compliance

    Compliance is required as indicated unless already done.
    To prevent fuel leakage on the hot section or in the primary 
fire zone of the engine, which may result in an engine fire and 
subsequent damage to the airplane, do the following:

Initial Inspection Requirements

    (a) Within 10 days after the effective date of this AD, do the 
following:
    (1) Inspect the fuel manifold on both sides of the engine for 
serviceability, and disposition in accordance with paragraphs 3.A. 
through 3.A.(3) of CFMI ASB CFM56-5C S/B 73-A0106, dated April 19, 
2001.
    (2) Visually inspect harnesses CJ9L and CJ10L for wear. If the 
wire braid is worn through (pierced), replace the harness within

[[Page 23543]]

3,000 hours time-in-service after the first inspection where the 
wire braid is found to be pierced.
    (3) Visually inspect and, if necessary, correct the bracket and 
clamp locations for the CJ10L harness in accordance with paragraphs 
3.C. through 3.C.(5) of the Accomplishment Instructions of CFMI ASB 
CFM56-5C S/B 73-A0106, dated April 19, 2001.

Repetitive Inspections

    (b) Thereafter, repeat the actions required by paragraph (a) of 
this AD at intervals not to exceed 500 hours time-since-last-
inspection.

Terminating Actions

    (c) Replacement of existing clamps (red and brown silicon) at 
details R, and S of CJ9L and detail S, R, and Q of CJ10L with new 
clamp (metallic) part number 649-412-351-0 and at detail Q of CJ9L 
with new clamp 649-412-354-0 constitutes terminating action for the 
repetitive inspection requirements of paragraph (b) of this AD.

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 shall submit their requests through an appropriate FAA 
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.

Special Flight Permits

    (e) 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 aircraft to a location where the 
requirements of this AD can be accomplished.

Documents That Have Been Incorporated By Reference

    (f) The inspections shall be done in accordance with CFM 
International Alert Service Bulletin CFM56-5C S/B 73-A0106, Revision 
1, dated April 19, 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 CFM 
International, Technical Publications Department, 1 Neumann Way, 
Cincinnati, OH 45215; telephone (513) 552-2981, fax (513) 552-2816. 
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 directive N T2001-145 (B) Revision 1.

    (g) This amendment becomes effective on May 14, 2001.

    Issued in Burlington, Massachusetts, on May 3, 2001.
Francis A. Favara,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-11615 Filed 5-4-01; 4:46 pm]
BILLING CODE 4910-13-P


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