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

[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]


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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.

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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

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