[Federal Register Volume 69, Number 174 (Thursday, September 9, 2004)]
[Rules and Regulations]
[Pages 54557-54558]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 04-20411]



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  Federal Register / Vol. 69, No. 174 / Thursday, September 9, 2004 / 
Rules and Regulations  

[[Page 54557]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-ANE-64-AD; Amendment 39-13791; AD 97-09-02R3]
RIN 2120-AA64


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

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment revises an existing airworthiness directive 
(AD) for CFMI CFM56-5C series turbofan engines. That AD currently 
establishes new life limits for certain high pressure turbine rotor 
(HPTR) front shafts, HPTR front air seals, and booster spools. This 
action removes the booster spool, part number (P/N) 337-005-210-0, and 
the HPTR front shaft, P/Ns 1498M40P03, 1498M40P05, and 1498M40P06, from 
the parts listed with lowered life limits in the existing AD. This 
amendment results from a life management review completed by the 
manufacturer. We are issuing this AD to prevent low-cycle fatigue (LCF) 
failure of certain HPTR front air seals, which could result in an 
uncontained engine failure and damage to the airplane.

DATES: Effective October 14, 2004.
    We must receive any comments on this AD by November 8, 2004.

ADDRESSES: Use one of the following addresses to submit comments on 
this AD:
     By mail: 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.
     By fax: (781) 238-7055.
     By e-mail: [email protected].
    You may examine the AD docket at the FAA, New England Region, 
Office of the Regional Counsel, 12 New England Executive Park, 
Burlington, MA.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7754; fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: On March 19, 2003, the FAA issued AD 97-09-
02R2, Amendment 39-13094 (68 FR 14312, March 25, 2003). That AD reduces 
the LCF retirement lives of certain HPTR front shafts, HPTR front air 
seals, HPTR disks, booster spools, and LPTR stage 3 disks.

Actions Since AD 97-09-02R2 Was Issued

    After we issued AD 97-09-02R2, the manufacturer conducted an 
extensive life management program for the HPTR front shaft and booster 
spool listed in the AD. The results indicated higher LCF retirement 
lives for those HPTR front shafts and booster spools than the lives 
published in AD 97-09-02R2. Those LCF retirement lives are now the same 
as originally calculated and are in agreement with the current 
airworthiness limitations section of Chapter 05 of the CFM56-5C Engine 
Shop Manual, CFMI-TP.SM.8. This AD revision removes HPTR front shafts, 
part numbers (P/Ns) 1498M40P03, 1498M40P05, and 1498M40P06; and booster 
spools, P/N 337-005-210-0, from the parts listed with lower LCF 
retirement lives. The LCF retirement lives of the HPTR front air seals 
P/N 1523M34P02 and 1523M34P03 remain unchanged.

FAA's Determination and Requirements of This AD

    Although no airplanes that are registered in the United States use 
these affected engine models, 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 to remain as 
published in AD 97-09-02R2.

FAA's Determination of the Effective Date

    Since there are currently no domestic operators of this engine 
model, notice and opportunity for public comment before issuing this AD 
are unnecessary, and a situation exists that allows the immediate 
adoption of this regulation.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment; however, we invite you to submit any written relevant data, 
views, or arguments regarding this AD. Send your comments to an address 
listed under ADDRESSES. Include ``AD Docket No. 95-ANE-64-AD'' in the 
subject line of your comments. If you want us to acknowledge receipt of 
your mailed comments, send us a self-addressed, stamped postcard with 
the docket number written on it; we will date-stamp your postcard and 
mail it back to you. We specifically invite comments on the overall 
regulatory, economic, environmental, and energy aspects of the rule 
that might suggest a need to modify it. If a person contacts us 
verbally, and that contact relates to a substantive part of this AD, we 
will summarize the contact and place the summary in the docket. We will 
consider all comments received by the closing date and may amend the AD 
in light of those comments.
    We are reviewing the writing style we currently use in regulatory 
documents. We are interested in your comments on whether the style of 
this document is clear, and your suggestions to improve the clarity of 
our communications with you. You may get more information about plain 
language at http://www.faa.gov/language and http://www.plainlanguage.gov.

Examining the AD Docket

    You may examine the AD Docket (including any comments and service 
information), by appointment, between 8 a.m. and 4:30 p.m., Monday 
through Friday, except Federal holidays. See ADDRESSES for the 
location.

Regulatory Findings

    We have determined that this AD will not have federalism 
implications under Executive Order 13132. This AD will not have a 
substantial direct effect on

[[Page 54558]]

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.
    For the reasons discussed above, I certify that the regulation:
    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.
    We prepared a summary of the costs to comply with this AD and 
placed it in the AD Docket. You may get a copy of this summary by 
sending a request to us at the address listed under ADDRESSES. Include 
``AD Docket No. 95-ANE-64-AD'' in your request.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

Adoption of the Amendment

0
Accordingly, under 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

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-13094 68 FR 
14312, March 25, 2003, and by adding a new airworthiness directive, 
Amendment 39-13791, to read as follows:

97-09-02R3 CFM International: Amendment 39-13791. 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 air seal, which could result in an 
uncontained failure and damage to the airplane, do the following:
    (a) LCF retirement lives for HPTR front shafts, part numbers (P/
Ns) 1498M40P03, 1498M40P05, and 1498M40P06, are now the same as 
originally calculated and are in agreement with the current 
airworthiness limitations section of Chapter 05 of the CFM56-5C 
Engine Shop Manual, CFMI-TP.SM.8.
    (b) Remove from service HPTR front air seals, P/Ns 1523M34P02 
and 1523M34P03, before accumulating 4,000 cycles-since-new, and 
replace with a serviceable part.
    (c) LCF retirement lives for HPTR disks P/N 1498M43P04 are now 
the same as originally calculated and are in agreement with the 
current airworthiness limitations section of Chapter 05 of the 
CFM56-5C Engine Shop Manual, CFMI-TP.SM.8.
    (d) LCF retirement lives for booster spools, P/N 337-005-210-0, 
are now the same as originally calculated and are in agreement with 
the current airworthiness limitations section of Chapter 05 of the 
CFM56-5C Engine Shop Manual, CMFI-TP.SM.8.
    (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 agreement 
with the current airworthiness limitations section of Chapter 05 of 
the CFM56-5C Engine Shop Manual, CMFI-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 agreement with the current 
airworthiness limitations section of Chapter 05 of the CFM56-5C 
Engine Shop Manual, CMFI-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, CMFI-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 October 14, 2004.

    Issued in Burlington, Massachusetts, on September 1, 2004.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 04-20411 Filed 9-8-04; 8:45 am]
BILLING CODE 4910-13-P