[Federal Register Volume 66, Number 106 (Friday, June 1, 2001)]
[Rules and Regulations]
[Pages 29689-29691]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-13720]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-18-AD; Amendment 39-12246; AD 2001-11-05]
RIN 2120-AA64


Airworthiness Directives; CFM International (CFMI) CFM56-2, -2B, 
-3, -5B, -5C and -7B 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 CFMI CFM56-2, -2B, -3, -5B, -5C and -7B series 
turbofan engines. This action requires limiting engines with certain 
No. 4 bearings to one on each airplane, replacement of certain No. 4 
bearings, and increased frequency of inspections for magnetic particles 
until the suspect bearing is replaced. This action is prompted by 
reports of two bearing failures in the fleet since December 2000. The 
actions specified in this AD are intended to prevent bearing failures, 
which could cause an engine failure.

DATES: Effective June 11, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before July 31, 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-18-AD, 12 New England 
Executive Park, Burlington, MA 01803-5299. 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: James Rosa, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7152, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: This proposal is prompted by reports of two 
No. 4 bearing failures on CFMI CFM56-7B series turbofan engines since 
December 2000. Inspections of the failed bearings indicate marginal 
metallurgical structure, most likely due to an uneven heat treatment 
process. Both failed bearings are from a manufacturing lot of 47 parts 
simultaneously heat-treated. This condition, if not corrected, could 
result in bearing failures, which could cause an engine failure.

FAA's Determination of an Unsafe Condition and Proposed Actions

    Since an unsafe condition has been identified that is likely to 
exist or develop on other CFMI CFM56-2, -2B, -3, -5B, -5C and -7B 
series turbofan engines of the same type design, this AD is being 
issued to prevent bearing failures which could cause an engine failure.
    This AD requires:
     Limiting the number of engines with a suspect No. 4 
bearing installed to one on each airplane within 300 hours time-in-
service (TIS) after the effective date of this AD, but no later than 
July 1, 2001, whichever occurs earlier. AND
     Increasing the frequency of inspections for magnetic 
particles until the suspect bearing is replaced. AND
     Replacing all suspect No. 4 bearings within 2,000 hours 
TIS after the effective date of this AD, but no later than December 31, 
2001, whichever occurs earlier.

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 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-18-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

[[Page 29690]]

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:

2001-11-05  CFM International: Amendment 39-12246. Docket 2001-NE-
18-AD.

    Applicability: This airworthiness directive (AD) is applicable 
to CFM International CFM56-2, -2B, -3, -5B, -5C and -7B series 
turbofan engines with a No. 4 bearing, part number (P/N) 305-355-
717-0, that has a serial number (SN) listed in Table 1 of this AD 
installed. These engines are installed on, but not limited to Airbus 
Industrie A319, A320, A321 and A340 series airplanes, Boeing 737 and 
KC135 series airplanes, and McDonnell Douglas DC8 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 (h) 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 bearing failures, which could cause an engine 
failure, do the following:

Number of Hours Until Number of Engines Must Be Limited

    (a) Limit the number of engines with a suspect No. 4 bearing 
that has a SN listed in the following Table 1 of this AD to one on 
each airplane within 300 hours time-in-service (TIS) after the 
effective date of this AD, but no later than July 1, 2001, whichever 
occurs earlier:

                               Table 1.--CFM56 Engines With Suspect No. 4 Bearings
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                                                                                                   Engine serial
                Part No.                         Part serial No.              Engine model              No.
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305-355-717-0...........................  DB387598-C                    2B                                714172
305-355-717-0...........................  DB387670-5                    2                                 692251
305-355-717-0...........................  DB387608-F                    3                                 725109
305-355-717-0...........................  DB387612-8                    3                                 720493
305-355-717-0...........................  DB387614-4                    3                                 721253
305-355-717-0...........................  DB387625-H                    3                                 720383
305-355-717-0...........................  DB387647-Y                    3                                 857594
305-355-717-0...........................  DB387650-6                    3                                 721237
305-355-717-0...........................  DB387651-5                    3                                 726245
305-355-717-0...........................  DB387661-K                    3                                 856671
305-355-717-0...........................  DB387604-K                    5B                                779783
305-355-717-0...........................  DB387605-J                    5B                                779784
305-355-717-0...........................  DB387603-L                    5B                                779785
305-355-717-0...........................  DB387590-5                    5B                                779786
305-355-717-0...........................  DB387591-4                    5B                                779787
305-355-717-0...........................  DB387634-3                    5B                                779796
305-355-717-0...........................  DB387658-D                    5B                                779798
305-355-717-0...........................  DB387654-2                    5B                                779799
305-355-717-0...........................  DB387683-G                    5B                                779802
305-355-717-0...........................  DB387648-W                    5B                                779803
305-355-717-0...........................  DB387660-L                    5B                                779804
305-355-717-0...........................  DB387606-H                    5B                                779960
305-355-717-0...........................  DB387618-O                    5B                                779961
305-355-717-0...........................  DB387599-B                    5C                                741948
305-355-717-0...........................  DB387609-Y                    7B                                876395
305-355-717-0...........................  DB387611-7                    7B                                876399
305-355-717-0...........................  DB387615-3                    7B                                876400
305-355-717-0...........................  DB387601-N                    7B                                876401
305-355-717-0...........................  DB387594-1                    7B                                876403
305-355-717-0...........................  DB387592-3                    7B                                876405
305-355-717-0...........................  DB387610-8                    7B                                876406
305-355-717-0...........................  DB387600-P                    7B                                876410
305-355-717-0...........................  DB387649-V                    7B                                876421
305-355-717-0...........................  DB387678-C                    7B                                876423
305-355-717-0...........................  DB387652-4                    7B                                876424
305-355-717-0...........................  DB387659-C                    7B                                876429
305-355-717-0...........................  DB387693-1                    7B                                876431
305-355-717-0...........................  DB387655-1                    7B                                876432
305-355-717-0...........................  DB387684-F                    7B                                876434
305-355-717-0...........................  DB387588-V                    7B                                876727
305-355-717-0...........................  DB387657-E                    7B                                876729
305-355-717-0...........................  DB387653-3                    7B                                876730
305-355-717-0...........................  DB387597-D                    7B                                877404
305-355-717-0...........................  DB387602-M                    7B                                877408

[[Page 29691]]

 
305-355-717-0...........................  DB387589-U                    7B                                877427
305-355-717-0...........................  DB387656-O                    7B                                875232
305-355-717-0...........................  DB387671-4                    7B                                874219
----------------------------------------------------------------------------------------------------------------

Replacement of Suspect No. 4 Bearings

    (b) For engines that have a suspect No. 4 bearing that has a SN 
listed in Table 1 of this AD, replace the No. 4 bearing with a 
serviceable part within 2,000 hours TIS, after the effective date of 
this AD, but no later than December 31, 2001, whichever occurs 
earlier.

Installation of Suspect No. 4 Bearings

    (c) After the effective date of this AD, do not install any No. 
4 bearing that has a SN listed in Table 1 of this AD.
    (d) After the effective date of this AD, do not install any 
engine that has a No. 4 bearing with a serial number listed in Table 
1 of this AD.

Initial Inspections for Chip Detector Indications

    (e) For engines that have a suspect No. 4 bearing that has a SN 
listed in Table 1 of this AD, inspect for magnetic chip indications 
within in the specified times, and if necessary, disposition as 
follows:
    (1) For CFM56-5B engines, check electronic magnetic chip 
detector (EMCD) visual indicator within 50 to 75 hours TIS after the 
effective date of this AD.
    (2) For CFM56-5C engine (741948), check for class 2 Electronic 
Centralized Aircraft Monitor (ECAM) message ``MAGNETIC CHIP 
DETECTED'' before further flight.
    (3) For CFM56-7B engines equipped with Debris Monitoring System 
(DMS) option, check Flight Management Computer--Master Control 
Display Unit (FMC-MCDU) for message 79-2114 before further flight.
    (4) For CFM56-7B engines equipped with classic magnetic chip 
detectors (MCD), inspect aft sump MCD within 50 to 75 hours TIS 
after the effective date of this AD.
    (5) For CFM56-2, -2B, and -3 engines, inspect aft sump MCD 
within 50 to 75 hours TIS after the effective date of this AD.
    (6) If bearing particles are found, remove engine from service 
before further flight.

Repetitive Inspections for Chip Detector Indications

    (f) Thereafter, inspect for chip indications in accordance with 
the specified time-since-last-inspection (TSLI), and if necessary, 
disposition as follows:
    (1) For CFM56-5B engines, check EMCD visual indicator every 50-
75 hours TSLI.
    (2) For CFM56-5C engine (741948), check for class 2 ECAM message 
``MAGNETIC CHIP DETECTED'' after every flight.
    (3) For CFM56-7B engines equipped with DMS option, check FMC-
MCDU for message 79-2114 once per day.
    (4) For CFM56-7B engines equipped with classic MCD, inspect aft 
sump MCD every 50-75 hours TSLI.
    (5) For CFM56-2, -2B, and -3 engines, inspect aft sump MCD every 
50-75 hours TSLI.
    (6) If bearing particles are found, remove engine from service 
before further flight.

Terminating Action

    (g) Replacement of a No. 4 bearing that has a SN listed in Table 
1 of this AD with a No. 4 bearing that does not have a SN listed in 
Table 1 of this AD is terminating action for the repetitive 
inspection requirements specified in paragraph (f) of this AD.

Alternative Methods of Compliance

    (h) 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. 
Operators shall submit their request through an appropriate FAA 
Principal Maintenance Inspector, who may add comments and then send 
it to the Manager, Engine Certification Office.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this airworthiness directive, 
if any, may be obtained from the Engine Certification Office.

Special Flight Permits

    (i) Special flight permits may be issued in accordance 
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.

Effective Date of This AD

    (j) This amendment becomes effective on June 11, 2001.

    Issued in Burlington, Massachusetts, on May 24, 2001.
Thomas A. Boudreau,
Acting Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 01-13720 Filed 5-31-01; 8:45 am]
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