[Federal Register Volume 63, Number 13 (Wednesday, January 21, 1998)]
[Rules and Regulations]
[Pages 3031-3032]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-1326]
[[Page 3031]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-ANE-29-AD; Amendment 39-10286; AD 98-02-04]
RIN 2120-AA64
Airworthiness Directives; CFM International CFM56-5B/2P Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to CFM International (CFMI) CFM56-5B/2P series turbofan
engines, that requires a reduction of the low cycle fatigue (LCF)
retirement life for certain low pressure turbine (LPT) cases. This
amendment is prompted by the results of a refined life analysis
performed by the manufacturer which revealed minimum calculated LCF
lives significantly lower than the published LCF retirement life. The
actions specified by this AD are intended to prevent a LCF failure of
the LPT case, which could result in damage to the aircraft.
DATES: Effective March 23, 1998.
ADDRESSES: This information may be examined at the Federal Aviation
Administration (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: Robert J. Ganley, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7138; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an airworthiness
directive (AD) that is applicable to CFM International (CFMI) CFM56-5B/
2P series turbofan engines was published in the Federal Register on
September 19, 1997 (62 FR 49179). That action proposed to require a
reduction of the low cycle fatigue (LCF) retirement life for certain
low pressure turbine (LPT) cases.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
One commenter supports the rule as proposed.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
There are approximately 18 engines of the affected design in the
worldwide fleet. The manufacturer has advised the FAA that there are no
engines installed on U.S. registered aircraft that are affected by this
AD. Therefore, there is no associated cost impact on U.S. operators as
a result of this AD. However, should an affected engine be imported on
an aircraft and placed on the U.S. registry in the future, and assuming
that the parts cost is proportional to the reduction of the LCF
retirement life, the required parts would cost approximately $40,423
per engine. Based on these figures, the total cost impact of the AD is
estimated to be $40,423 per engine.
The regulations adopted herein will not have substantial direct
effects 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. Therefore, in
accordance with Executive Order 12612, it is determined that this final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
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 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
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 the following new
airworthiness directive:
98-02-04 CFM International: Amendment 39-10286. Docket 97-ANE-29-
AD.
Applicability: CFM International (CFMI) CFM56-5B1/2P, -5B2/2P, -
5B3/2P, and -5B4/2P turbofan engines, installed with low pressure
turbine (LPT) case, Part Number (P/N) 338-117-004-0, installed on
but not limited to Airbus A320 and A321 series aircraft.
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 (e) 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: Required as indicated, unless accomplished
previously.
To prevent a low cycle fatigue (LCF) failure of the LPT case,
which could result in damage to the aircraft, accomplish the
following:
(a) Remove from service LPT case, P/N 338-117-004-0, and replace
with a serviceable part, as follows:
(1) For CFM56-5B2/2P and -5B3/2P engines, prior to accumulating
10,500 cycles.
(2) For CFM56-5B1/2P and -5B4/2P engines, prior to accumulating
15,500 cycles.
(b) This action establishes the new LCF retirement lives of
10,500 and 15,500 cycles for the engines stated in paragraphs (a)(1)
and (a)(2) of this AD, which are published in Chapter 05 of CFM56-5B
Engine Shop Manual, CFMI-TP.SM.9.
(c) For the purpose of this AD, a ``serviceable part'' is one
that has not exceeded its respective new life limit as set out in
this AD.
(d) Except as provided in paragraph (e) of this AD, no
alternative replacement times may be approved for LPT case, P/N 338-
117-004-0.
(e) 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. The
request should be forwarded through an appropriate FAA Principal
Maintenance Inspector, who may add comments and then send it to the
Manager, Engine Certification Office.
[[Page 3032]]
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.
(f) Special flight permits may be issued in accordance with
sections 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.
(g) This amendment becomes effective on March 23, 1998.
Issued in Burlington, Massachusetts, on January 7, 1998.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 98-1326 Filed 1-20-98; 8:45 am]
BILLING CODE 4910-13-U
