[Federal Register Volume 67, Number 124 (Thursday, June 27, 2002)]
[Rules and Regulations]
[Pages 43232-43234]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-16173]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-38-AD; Amendment 39-12790; AD 2002-13-03]
RIN 2120-AA64
Airworthiness Directives; CFM International (CFMI) CFM56-2, -2A,
-2B, -3, -3B, -3C, -5, -5B, -5C, and -7B Series Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), that is applicable to certain CFM International (CFMI) CFM56
series turbofan engines. That AD currently requires revisions to the
Airworthiness Limitations Section of applicable Engine Shop Manuals
(ESM's) to include required enhanced inspection of selected critical
life-limited parts at each piece-part exposure. This amendment requires
revisions to the Airworthiness Limitations Section of the applicable
manufacturer's manuals and air carrier's approved continuous
airworthiness maintenance program to incorporate additional inspections
of selected critical life-limited parts at each piece-part exposure.
This amendment is prompted by an FAA study of in-service events
involving uncontained failures of critical rotating parts. The actions
specified by this AD are intended to prevent critical life-limited
rotating engine part failure, which could result in an uncontained
engine failure and damage to the airplane.
DATES: Effective date August 1, 2002.
ADDRESSES: Information regarding this action may be examined, by
appointment, at the Federal Aviation Administration (FAA), New England
Region, Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Diane Cook, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7133, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2000-12-01,
Amendment 39-11779 (65 FR 37031, June 13, 2000), which is applicable to
certain CFMI CFM56 series turbofan engines, was published in the
Federal Register on October 5, 2001, (66 FR 50910). That action
proposed to modify the airworthiness limitations section of the
manufacturer's manual and an air carrier's approved continuous
airworthiness maintenance program to incorporate additional inspection
requirements.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comments received.
Typographical Errors
Four commenters requested typographical errors be corrected in the
Mandatory Inspections Table as follows:
For HPT Disk, change Engine Manual Section from 75-72-02
to 75-52-02.
For HPC Rear (CDP) Air Seal, change Engine Manual Section
from 72-52-03 to 72-31-08.
For LPT Stub Shaft, change Engine Models from All to -2, -
2A, -2B, -3, -3B, and -3C.
For LPT Stub Shaft, change Engine Manual Section from 72-
52-03 to 72-55-02.
For LPT Shaft, change Inspection from FPI to MPI.
The FAA agrees and has corrected these typographical errors in the
final rule.
Concern for Lead Time
One commenter is concerned that for operators to put procedures and
tooling in place in time to comply with the AD, the manufacturer should
release the Engine Manual time limit and procedural changes by
Temporary Revision before the issuance of the AD, or, revise the AD
compliance time to state compliance to be within 30 days after the
issuance of the Engine Manual revision (or Temporary Revision).
The FAA understands the commenter's concern. The FAA is aware that
the manufacturer has not yet issued Temporary Revisions to the Engine
Manual time limits section. However, the existing AD and this final
rule allow the manufacturer up to 30 days after the effective date of
the AD to issue the necessary revisions to the time limits section.
Therefore, no action is necessary to address the commenter's
observation.
Question on Model Effectivity
One commenter asks why the proposed rule does not affect the
various models of the CFM56-5A engine. The FAA understands that the
commenter is referring to the CFM56-5-A engine in the proposed rule and
in the final rule that is an engine subset covered under the -5 series.
The -5 series is listed in the Applicability section, and therefore,
the CFM56-5-A engine is included in the applicability of this AD.
After careful review of the available data, including the comments
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the changes described
previously. The FAA has determined that these changes will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Economic Analysis
The FAA estimates that 5,100 CFM56 engines installed on airplanes
of US registry would be affected by this AD and that there are
approximately 2,300 piece part annual inspections that would be
required. It would take approximately 2,775 work hours to do these
inspections. The average labor rate is $60 per work hour. The total
estimated annual cost of the new inspections on US operators is
expected to be approximately $166,500.
[[Page 43233]]
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) if promulgated,
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 39-11779 (65 FR
3731, June 13, 2000), and by adding a new airworthiness directive,
Amendment 39-12790, to read as follows:
2002-13-03 CFM International: Amendment 39-12790. Docket No. 98-
ANE-38-AD. Supersedes AD 2000-12-01, Amendment 39-11779.
Applicability
This airworthiness directive (AD) is applicable to CFM
International (CFMI) CFM56-2, -2A, -2B, -3, -3B, -3C, -5, -5B, -5C,
and -7B series turbofan engines, installed on but not limited to
McDonnell Douglas DC-8 series, Boeing 737 series, Airbus Industrie
A319, A320, A321, and A340 series, as well as Boeing C-135, E-3, E-
6, KC-135, KE-3, and RC-135 (military) 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 (c) 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
accomplished.
To prevent critical life-limited rotating engine part failure,
which could result in an uncontained engine failure and damage to
the airplane, accomplish the following:
Inspections
(a) Within the next 30 days after the effective date of this AD,
revise the Airworthiness Limitations Section (chapter 05-00-00) of
Engine Shop Manual (ESM) CFMI-TP.SM.4, for CFM56-2 series engines,
ESM CFMI-TP.SM.6, for CFM56-2A/-2B series engines, ESM CFMI-TP.SM.5,
for CFM56-3/-3B/-3C series engines, ESM CFMI-TP.SM.7 for CFM56-5
series engines, ESM CFMI-TP.SM.9 for CFM56-5B series engines, ESM
CFMI-TP.SM.8 for CFM56-5C series engines, and ESM CFMI-TP.SM.10 for
CFM56-7B series engines, and for air carrier operations, revise the
approved continuous airworthiness maintenance program, by adding the
following:
``MANDATORY INSPECTIONS
(1) Perform inspections of the following parts at each piece-
part opportunity in accordance with the Inspection/Check section
instructions provided in the applicable manual sections listed
below:
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Engine
Engine models Part name manual Inspection
section
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All Models.......................... Fan Disk (All Part Numbers 72-21-03 Disk Fluorescent Penetrant
(P/N)). Inspection (FPI) and Disk Bore
and Dovetail Eddy Current
Inspection (ECI).
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All Models.......................... Fan Shaft (All P/N)......... 72-22-01 Magnetic Particle Inspection
(MPI).
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CFM56-2, -2A, -2B, -3, -3B, and -3C. HPT Disk (All P/N).......... 72-52-02 FPI, Disk Bore ECI and Disk Rim
Bolt Hole(s) ECI.
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CFM56-5,-5B, -5C, and -7B........... HPT Disk (All P/N).......... 72-52-02 FPI, Disk Bore ECI.
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CFM56-2............................. HPT Front Rotating Air Seal 72-52-03 FPI, Seal Bore ECI and Bolt
(All P/N). Hole(s) or Focused FPI as
applicable.
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CFM56-2A, -2B, -3, -3B, and -3C..... HPT Front Rotating Air Seal 72-52-03 FPI, Seal Bore ECI and Bolt
(All P/N). Hole(s) ECI.
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CFM56-5, -5B, -5C, and -7B.......... HPT Front Rotating Air Seal 72-52-03 FPI, Seal Bore ECI and Bolt
(All P/N). Hole(s) Focused FPI.
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All Models.......................... HPC Stage 1-2 Spool (All P/ 72-31-04 FPI.
N).
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All Models.......................... HPC Stage 3 Disk (All P/N).. 72-31-05 FPI.
----------------------------------------------------------------------------------------------------------------
All Models.......................... HPC Stage 4-9 Spool (All P/ 72-31-06 FPI.
N).
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All Models.......................... HPC Front Shaft (All P/N)... 72-31-07 FPI
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[[Page 43234]]
All Models.......................... HPC Rear (CDP) Air Seal (All 72-31-08 FPI.
P/N).
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All Models.......................... LPT Stage 1 Disk (All P/N).. 72-54-03 FPI.
----------------------------------------------------------------------------------------------------------------
All Models.......................... LPT Stage 2 Disk (All P/N).. 72-54-03 FPI.
----------------------------------------------------------------------------------------------------------------
All Models.......................... LPT Stage 3 Disk (All P/N).. 72-54-03 FPI
----------------------------------------------------------------------------------------------------------------
All Models.......................... LPT Stage 4 Disk (All P/N).. 72-54-03 FPI.
----------------------------------------------------------------------------------------------------------------
CFM56-5C............................ LPT Stage 5 Disk (All P/N).. 72-54-03 FPI.
----------------------------------------------------------------------------------------------------------------
All Models.......................... LPT Rotor Support (All P/N). 72-54-05 FPI.
----------------------------------------------------------------------------------------------------------------
All Models.......................... LPT Shaft (All P/N)......... 72-55-01 MPI.
----------------------------------------------------------------------------------------------------------------
CFM56-2, -2A, -2B, -3, -3B and -3C.. LPT Stub Shaft (All P/N).... 72-55-02 FPI.
----------------------------------------------------------------------------------------------------------------
(2) For the purposes of these mandatory inspections, piece-part
opportunity means:
(i) The part is considered completely disassembled when
accomplished in accordance with the disassembly instructions in the
manufacturer's engine manual; and
(ii) The part has accumulated more than 100 cycles in service
since the last piece-part opportunity inspection, provided that the
part was not damaged or related to the cause for its removal from
the engine.''
(b) Except as provided in paragraph (c) of this AD, and
notwithstanding contrary provisions in Sec. 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections
must be performed only in accordance with the Time Limits section of
the manufacturer's ESM.
Alternative Methods of Compliance
(c) 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.
Operators must submit their request through an appropriate FAA
Principal Maintenance Inspector, who may add comments and then send
it to the Manager, Engine Certification Office.
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.
Special Flight Permits
(d) Special flight permits may be issued in accordance with
Secs. 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 accomplished.
Continuous Airworthiness Maintenance Program
(e) FAA-certificated air carriers that have an approved
continuous airworthiness maintenance program in accordance with the
record keeping requirement of Sec. 121.369(c) of the Federal
Aviation Regulations (14 CFR 121.369(c)) of this chapter must
maintain records of the mandatory inspections that result from
revising the Airworthiness Limitations Section of the applicable ESM
and the air carrier's continuous airworthiness program.
Alternatively, certificated air carriers may establish an approved
system of record retention that provides a method for preservation
and retrieval of the maintenance records that include the
inspections resulting from this AD, and include the policy and
procedures for implementing this alternate method in the air
carrier's maintenance manual required by Sec. 121.369(c) of the
Federal Aviation Regulations (14 CFR 121.369 (c)); however, the
alternate system must be accepted by the appropriate PMI and require
the maintenance records be maintained either indefinitely or until
the work is repeated. Records of the piece-part inspections are not
required under Sec. 121.380(a)(2)(vi) of the Federal Aviation
Regulations (14 CFR 121.380(a)(2)(vi)). All other operators must
maintain the records of mandatory inspections required by the
applicable regulations governing their operations.
Note 3: The requirements of this AD have been met when the ESM
changes are made and air carriers have modified their continuous
airworthiness maintenance plans to reflect the requirements in the
applicable ESM.
Effective Date
(f) This amendment becomes effective on August 1, 2002.
Issued in Burlington, Massachusetts, on June 17, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 02-16173 Filed 6-26-02; 8:45 am]
BILLING CODE 4910-13-P