[Federal Register: September 9, 2004 (Volume 69, Number 174)]
[Rules and Regulations]
[Page 54557-54558]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr09se04-1]
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Rules and Regulations
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[[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.
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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: 9-ane-adcomment@faa.gov.
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]
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