[Federal Register Volume 67, Number 157 (Wednesday, August 14, 2002)]
[Rules and Regulations]
[Pages 52860-52861]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-20515]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NE-37-AD; Amendment 39-12857; AD 2002-16-18]
RIN 2120-AA64


Airworthiness Directives; CFM International CFM56-5B and -7B 
Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), that 
is applicable to CFM International (CFMI) CFM56-5B and -7B series 
turbofan engines. This amendment requires retirement of stage 2 low 
pressure turbine (LPT) nozzle segments and stage 3 LPT nozzle segments, 
listed in Table 1 of this AD, from service before accumulating 25,000 
cycles-since-new (CSN) or at the next LPT module shop visit when either 
stage 2 LPT nozzle segments or stage 3 LPT nozzle segments are exposed, 
whichever occurs first. This amendment also requires installation of 
new design (either new or reworked) nozzle segments, that will aid in 
containment of the LPT rotor in the event of LPT shaft failure. This 
amendment is prompted by a report of an LPT shaft failure caused by a 
hydromechanical unit (HMU) malfunction that induced a higher than 
anticipated LPT rotor overspeed. The actions specified by this AD are 
intended to aid in containment of the LPT rotor in the event of LPT 
shaft failure, which could result in uncontained engine failure and 
damage to the airplane.

DATES: Effective September 18, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from CFM International, Technical Publications Department, 1 
Neumann Way, Cincinnati, OH 45215; telephone (513) 552-2800; fax (513) 
552-2816.

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: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an AD that is 
applicable to CFMI CFM56-5B and -7B series turbofan engines was 
published in the Federal Register on April 4, 2002 (67 FR 16069). That 
action proposed to require retirement of stage 2 LPT nozzle segments 
and stage 3 LPT nozzle segments, listed in Table 1 of that proposed AD, 
from service before accumulating 25,000 cycles-since-new (CSN), or by 
October 31, 2008, whichever occurs earlier.

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the comments received.

Remove Compliance Date

    Three commenters request that the compliance date of October 31, 
2008, be removed. This date would not provide enough engine operating 
time to reach scheduled major maintenance when the affected parts would 
be exposed.
    The FAA agrees. The alternate AD compliance requirement of retiring 
stage 2 LPT nozzle segments and stage 3 LPT nozzle segments from 
service before accumulating 25,000 CSN meets the manufacturer's removal 
criteria. In addition, the FAA wishes to clarify that compliance with 
this AD is required before accumulating 25,000 CSN or at the next LPT 
module shop visit when either stage 2 LPT nozzle segments or stage 3 
LPT nozzle segments are exposed, whichever occurs first.
    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes described 
previously. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

[[Page 52861]]

Economic Analysis

    There are approximately 3,187 CFMI CFM56-5B and -7B series engines 
of the affected design in the worldwide fleet. The FAA estimates that 
910 engines installed on airplanes of U.S. registry would be affected 
by this AD. The FAA also estimates that it would take approximately 10 
work hours per engine to perform the actions, and that the average 
labor rate is $60 per work hour. Required parts would cost 
approximately $34,984 per engine. Based on these figures, the total 
cost of the AD on U.S. operators is estimated to be $32,381,440.

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.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under the DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
by contacting 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 a new airworthiness directive 
to read as follows:

2002-16-18  CFM International: Amendment 39-12857. Docket No. 2001-
NE-37-AD.

Applicability

    This airworthiness directive (AD) is applicable to CFM 
International (CFMI) CFM56-5B and -7B series turbofan engines. These 
engines are installed on, but not limited to Boeing 737-600, -700, -
800, and -900; and Airbus A319, A320, and A321 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 (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 before accumulating 25,000 
cycles-since-new (CSN) on the parts listed in Table 1 of this AD, or 
at the next low pressure turbine (LPT) module shop visit when either 
stage 2 LPT nozzle segments or stage 3 LPT nozzle segments are 
exposed, whichever occurs first, unless already done.
    To aid in containment of the LPT rotor in the event of LPT shaft 
failure, which could result in uncontained engine failure and damage 
to the airplane, do the following:
    (a) Retire from service stage 2 LPT nozzle segments and stage 3 
LPT nozzle segments listed in the following Table 1, and install new 
design (either new or reworked) nozzle segments:

   Table 1.--Stage 2 and Stage 3 LPT Nozzle Segment Part Numbers To Be
                                 Retired
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        Nozzle segments                        Part numbers
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(1) Stage 2....................  338-109-104-0, 338-109-105-0, 338-109-
                                  106-0, 338-109-204-0, 338-109-205-0,
                                  338-109-206-0, 338-109-304-0, 338-109-
                                  305-0, 338-109-306-0.
(2) Stage 3....................  338-109-702-0, 338-109-802-0.
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    (b) Information on reworking stage 2 LPT nozzle segments and 
stage 3 LPT nozzle segments, listed in Table 1 of this AD, can be 
found in CFM International Service Bulletins (SB's) 72-0328, dated 
May 25, 2000, for CFM56-5 series engines, and SB 72-0241, dated May 
25, 2000, for CFM56-7 series engines.

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 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 airplane to a location where the 
requirements of this AD can be done.

Effective Date

    (e) This amendment becomes effective on September 18, 2002.

    Issued in Burlington, Massachusetts, on August 5, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-20515 Filed 8-13-02; 8:45 am]
BILLING CODE 4910-13-P