[Federal Register: November 20, 2002 (Volume 67, Number 224)]
[Rules and Regulations]
[Page 70004-70006]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr20no02-8]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2002-NE-13-AD; Amendment 39-12946; AD 2002-23-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-8C1
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness (AD), that is
applicable to General Electric Company CF34-8C1 turbofan engines. This
amendment requires revisions to the Airworthiness Limitations Section
(ALS) of the manufacturer's Instructions for Continued Airworthiness
(ICA) to include required enhanced inspection of selected critical
life-limited parts at each piece-part exposure. This amendment also
requires an air carrier's approved continuous airworthiness maintenance
program to incorporate these inspection procedures. Air carriers with
an approved continuous airworthiness maintenance program will be
allowed to either maintain the records showing the current status of
the inspections using the record keeping system specified in the air
carrier's maintenance manual, or establish an acceptable alternate
method of record keeping. This amendment is prompted by the need to
require enhanced inspection of selected critical life-limited parts of
CF34-8C1 turbofan engines at each piece-part exposure. 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 December 26, 2002.
ADDRESSES: The information contained in this AD 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.
[[Page 70005]]
FOR FURTHER INFORMATION CONTACT: Keith Mead, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7744; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) to include an AD that is
applicable to General Electric Company CF34-8C1 turbofan engines was
published in the Federal Register on July 10, 2002 (67 FR 45675). That
action proposed to require an air carrier's approved continuous
airworthiness maintenance program to incorporate these inspection
procedures. That action also proposed that air carriers with an
approved continuous airworthiness maintenance program would be allowed
to either maintain the records showing the current status of the
inspections using the record keeping system specified in the air
carrier's maintenance manual, or establish an acceptable alternate
method of record keeping.
Comments
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the comment received.
One commenter expresses concern that compliance with this amendment
will require removal of coatings on four parts located in noncritical
areas. These include the HPT outer torque coupling, HPT shaft, HPC aft
shaft spool and the HPC discharge rotating seal listed in Table 805 of
the proposal. The FAA agrees that it is unnecesssary to remove the
coating on these four parts to meet the intent of the enhanced
inspection procedures specified in this AD. Table 805 has been changed
accordingly.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule with the change described
previously. The FAA has determined that this change will neither
increase the economic burden on any operator nor increase the scope of
the AD.
Economic Analysis
Since this proposal was published in July of 2002, additional
aircraft have been added to the domestic and worldwide fleet.
Therefore, the numbers cited in the Economic Analysis have also
increased.
There are approximately 104 General Electric Company CF34-8C1
turbofan engines of the affected design in the worldwide fleet. The FAA
estimates that 60 engines installed on airplanes of U.S. registry will
be affected by this AD, that it will take approximately 75 work hours
per engine to perform the required actions, and that the average labor
rate is $60 per work hour. Using average shop visitation rates, five
engines are expected to be affected per year. Based on these figures,
the total cost of the AD on U.S. operators is estimated to be $22,500
per year.
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 adding a new airworthiness directive
to read as follows:
2002-23-02 General Electric Company: Amendment 39-12946. Docket No.
2002-NE-13-AD.
Applicability: This airworthiness directive (AD) is applicable
to General Electric Company CF34-8C1 turbofan engines. These engines
are installed on, but not limited to, Bombardier Aerospace CRJ700
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 done.
To prevent critical life-limited rotating engine part failure,
which could result in an uncontained engine failure and damage to
the airplane, do the following:
(a) Within the next 30 days after the effective date of this AD,
revise the Time Limits Section (TLS) of the manufacturer's Engine
Manual (EM), GEK 105091 and for air carrier operations revise the
approved continuous airworthiness maintenance program, by adding the
following:
``MANDATORY INSPECTIONS
(1) Perform inspections of the parts listed in the following
Table 805 at each piece-part opportunity in accordance with the
instructions provided in the applicable manual provisions:
Table 801.--Mandatory Inspection Requirements
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Manual/Chapter Section /
Part nomenclature Subject Mandatory Inspection
----------------------------------------------------------------------------------------------------------------
Fan Disk............................ 72-21-15, INSPECTION........ All areas (FPI).\1\
Bores (ECI).\2\
Fan Drive Shaft..................... 72-22-00, INSPECTION........ All areas (FPI).\1\
[[Page 70006]]
Stage 1 High Pressure Turbine (HPT) 72-51-06, INSPECTION........ All areas (FPI).\1\
Rotor Disk. Bores (ECI).\2\
Boltholes (ECI).\2\
Air Holes (ECI).\2\
HPT Rotor Outer Torque Coupling..... 72-51-10, INSPECTION........ All non-coated areas (FPI).\1\
Bores (ECI).\2\
Stage 2 HPT Rotor Disk.............. 72-51-14, INSPECTION........ All areas (FPI).\1\
Bores (ECI).\2\
HPT Shaft........................... 72-51-03, INSPECTION........ All non-coated areas (FPI).\1\
Stage 1 and Stage 2 High Pressure 72-33-01, INSPECTION........ All areas (FPI).\1\
Compressor (HPC) Rotor Blisks.
HPC Forward Shaft................... 72-33-02, INSPECTION........ All areas (FPI).\1\
Stage 3 HPC Rotor Blisk............. 72-33-03, INSPECTION........ All areas (FPI).\1\
HPC Aft Shaft Spool................. 72-33-05, INSPECTION........ All non-coated areas (FPI).\1\
HPC Discharge Rotating Seal......... 72-33-08, INSPECTION........ All non-coated areas (FPI).\1\
Stage 3 Low Pressure Turbine (LPT) 72-57-10, INSPECTION........ All areas (FPI).\1\
Rotor Disk.
Stage 4 LPT Rotor Disk.............. 72-57-16, INSPECTION........ All areas (FPI).\1\
Rear LPT Shaft...................... 72-57-23, INSPECTION........ All areas (FPI).\1\
Stage 5 LPT Rotor Disk.............. 72-57-20, INSPECTION........ All areas (FPI).\1\
Stage 6 LPT Rotor Disk.............. 72-57-28, INSPECTION........ All areas (FPI).\1\
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\1\ FPI = Fluorescent Penetrant Inspection Method
\2\ ECI = Eddy Current Inspection Method
(2) For the purposes of these mandatory inspections, piece-part
opportunity means:
(i) The part is considered at ``piece-part opportunity'', when
it is completely disassembled 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 section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections
shall be performed only in accordance with the TLS of the GE CF34-
8C1 EM.
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 (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
(d) 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.
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)) must maintain records of
the mandatory inspections that result from revising the CF34 Engine
Maintenance Program 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
engine manual changes are made and air carriers have modified their
continuous airworthiness maintenance plans to reflect the Engine
Maintenance Program requirements specified in the GE CF34-8C1 Engine
Manual.
Effective Date
(f) This amendment becomes effective on December 26, 2002.
Issued in Burlington, Massachusetts, on November 7, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 02-29355 Filed 11-19-02; 8:45 am]
BILLING CODE 4910-13-P