[Federal Register Volume 68, Number 57 (Tuesday, March 25, 2003)]
[Rules and Regulations]
[Pages 14312-14314]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-7003]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-ANE-64-AD; Amendment 39-13094; AD 97-09-02R2]
RIN 2120-AA64
Airworthiness Directives; CFM International (CFMI) CFM56-5C
Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment revises an existing airworthiness directive
(AD) that is applicable to CFMI CFM56-5C series turbofan engines. That
AD currently establishes new life limits for certain low pressure
turbine rotor (LPTR) stage 3 disks and certain high pressure turbine
rotor (HPTR) disks. This action removes the LPTR stage 3 disks and the
HPTR disks from the parts listed with lowered life limits in the
existing AD. This amendment is prompted by the results of an extensive
life management program completed by the manufacturer, which no longer
requires lower life limits for the LPTR stage 3 disks and HPTR disks
listed in the existing AD. The actions specified in this AD are
intended to prevent low-cycle-fatigue (LCF) failure of certain HPTR
front shafts, HPTR front air seals, and booster spools, which could
result in an uncontained engine failure and damage to the airplane.
DATES: Effective April 29, 2003.
Comments for inclusion in the Rules Docket must be received on or
before May 27, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), New England Region, Office of the Regional
Counsel, Attention: Rules Docket No. 95-ANE-64-AD, 12 New England
Executive Park, Burlington, MA 01803-5299. Comments may be inspected at
this location, by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. 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-
[[Page 14313]]
5299; telephone (781) 238-7152; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: On August 29, 2002, the FAA issued AD 97-09-
02R1, Amendment 39-12876 (67 FR 57146, September 9, 2002), applicable
to CFMI CFM56-5C series turbofan engines, to reduce the LCF retirement
lives of certain HPTR front shafts, HPTR front air seals, HPTR disks,
booster spools, and LPTR stage 3 disks. Since AD 97-09-02R1 was issued,
the manufacturer conducted an extensive life management program for the
LPTR stage 3 disks and HPTR disks listed in the AD. The results
indicated higher LCF retirement lives for those LPTR stage 3 disks and
HPTR disks than the lives published in AD 97-09-02R1. Those LCF
retirement lives are now the same as originally calculated and are in
accordance with the current airworthiness limitations section of
Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8. Therefore,
this AD revision removes LPT stage 3 disks, part numbers (P/Ns) 337-
001-602-0 and 337-001-605-0, and HPTR disks, P/N 1498M43P04, from the
parts listed with lower LCF retirement lives. The LCF retirement lives
of the HPTR front air seals P/N 1523M34P02 and P/N 1523M34P03, and HPT
front shafts P/N 1498M40P03, 1498M40P05, and 1498M40P06, and booster
spools P/N 337-005-210-0, remain unchanged.
FAA's Determination of an Unsafe Condition and Required Actions
Although these affected engine models are not used on any airplanes
that are registered in the United States, the possibility exists these
engine models could be used on airplanes that are registered in the
United States in the future. This AD requires the LCF retirement lives
of HPTR front air seals P/N 1523M34P02 and P/N 1523M34P03, and HPT
front shafts P/N 1498M40P03, 1498M40P05, and 1498M40P06, and booster
spools P/N 337-005-210-0 to remain as they were published in AD 97-09-
02R1.
Immediate Adoption of This AD
Since there are currently no domestic operators of CFM56-5C series
turbofan engines, 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 95-ANE-64-AD.'' The postcard will be date stamped and
returned to the commenter.
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 removing Amendment 39-12876 (67 FR
57146, September 9, 2002) and by adding the following new airworthiness
directive:
97-09-02R2 CFM International: Amendment 39-13094. Docket No. 95-ANE-
64-AD.
Applicability: This airworthiness directive (AD) is applicable
to CFM International (CFMI) CFM56-5C2/G, -5C3/G, and -5C4 series
turbofan engines. These engines are installed on, but not limited
to, Airbus Industrie A340 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 (i) 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 low cycle fatigue (LCF) failure of the high pressure
turbine rotor (HPTR) front shaft, HPTR front air seal, and booster
spool, which could result in an uncontained failure and damage to
the airplane, do the following:
(a) Remove from service HPTR front shafts, part numbers (P/Ns)
1498M40P03, 1498M40P05, and 1498M40P06, before accumulating 8,400
cycles-since-new (CSN), and replace with a serviceable part.
(b) Remove from service HPTR front air seals, P/Ns 1523M34P02
and 1523M34P03, before accumulating 4,000 CSN, and replace with a
serviceable part.
[[Page 14314]]
(c) LCF retirement lives for HPTR disks P/N 1498M43P04 are now
the same as originally calculated and are in accordance with the
current airworthiness limitations section of Chapter 05 of the
CFM56-5C Engine Shop Manual, CFMI-TP.SM.8.
(d) Remove from service booster spools, P/N 337-005-210-0,
before accumulating 13,000 CSN, and replace with a serviceable part.
(e) For CFM56-5C4 engines, LCF retirement lives for low pressure
turbine rotor (LPTR) stage 3 disks, P/Ns 337-001-602-0 and 337-001-
605-0 are now the same as originally calculated and are in
accordance with the current airworthiness limitations section of
Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8.
(f) For CFM56-5C2/G and -5C3/G engines, LCF retirement lives for
LPTR stage 3 disks, P/Ns 337-001-602-0 and 337-001-605-0 are now the
same as originally calculated and are in accordance with the current
airworthiness limitations section of Chapter 05 of the CFM56-5C
Engine Shop Manual, CFMI-TP.SM.8.
(g) This action establishes the new LCF retirement lives stated
in paragraphs (a) through (f) of this AD, which are published in
Chapter 05 of the CFM56-5C Engine Shop Manual, CFMI-TP.SM.8.
(h) 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.
Alternative Methods of Compliance
(i) 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
(j) Special flight permits may be issued in accordance with
Sec. Sec. 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
(k) This amendment becomes effective on April 29, 2003.
Issued in Burlington, Massachusetts, on March 19, 2003.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 03-7003 Filed 3-24-03; 8:45 am]
BILLING CODE 4910-13-P