[Federal Register Volume 67, Number 46 (Friday, March 8, 2002)]
[Rules and Regulations]
[Pages 10606-10608]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-5527]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NE-49-AD; Amendment 39-12670; AD 2002-05-02]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34-3A1 and -
3B1 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 General Electric Company (GE) CF34-3A1 and
-3B1 series turbofan engines, that currently requires revisions to the
Engine Maintenance Program specified in the manufacturer's Instructions
for Continued Airworthiness (ICA) for GE CF34-3A1 and -3B1 series
turbofan engines. Those revisions require enhanced inspection of
selected critical life-limited parts at each piece-part exposure. The
existing AD also requires that an air carrier's approved continuous
airworthiness maintenance program incorporate these inspection
procedures. This amendment modifies the airworthiness limitations
section of the manufacturer's manual and an air carrier's approved
continuous airworthiness maintenance program to incorporate additional
inspection requirements. An FAA study of in-service events involving
uncontained failures of critical rotating engine parts has indicated
the need for mandatory inspections. The mandatory inspections are
needed to identify those critical rotating parts with conditions, which
if allowed to continue in service, could result in uncontained
failures. 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 April 12, 2002.
ADDRESSES: The information referenced 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.
FOR FURTHER INFORMATION CONTACT: Barbara Caufield, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone (781)
238-7146; fax (781) 238-7199.
[[Page 10607]]
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding AD 2000-03-03 R1,
Amendment 39-12228 (66 FR 26787, May 15, 2001), which is applicable to
General Electric Company CF34-3A1 and -3B1 series turbofan engines was
published in the Federal Register on October 5, 2001 (66 FR 50891).
That action proposed to modifiy 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. No comments were received on the
proposal or the FAA's determination of the cost to the public. The FAA
has determined that air safety and the public interest require the
adoption of the rule as proposed.
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 39-12228 (66 FR
26787, May 15, 2001) and by adding a new airworthiness directive,
Amendment 39-12670, to read as follows:
2002-05-02 General Electric Company: Amendment 39-12670. Docket No.
99-NE-49-AD. Supersedes AD 2000-03-03 R1, Amendment 39-12228.
Applicability
This airworthiness directive (AD) is applicable to General
Electric Company (GE) CF34-3A1 and -3B1 series turbofan engines,
installed on but not limited to Bombardier Canadair CL 600-2B19(RJ)
aircraft.
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:
Inspections
(a) Within 30 days after the effective date of this AD, revise
the CF34 Engine Maintenance Program, Chapter 5-21-00, of the GE
CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756. For air
carrier operations, revise the approved continuous airworthiness
maintenance program, by adding the following:
``9. CF34-3A1 and CF34-3B1 Engine Maintenance Program--Mandatory
Inspection Requirements.
(A) This procedure is used to identify specific piece-parts that
require mandatory inspections that must be accomplished at each
piece-part exposure using the applicable Chapters referenced in
Table 804 for the inspection requirements. The inspection
requirements listed in Table 804 are not required for any piece-part
exposure resulting when the engine remains on-wing while performing
maintenance practice, special procedure Number 41 listed in SEI-756,
chapter 72-00-00.
(B) Piece-part exposure is defined as follows: Note: Fan disk
piece-part includes the fan disk with the 56 fan pin bushings
installed.
(1) For engines that utilize the ``On Condition'' maintenance
requirements:
The part is considered completely disassembled to the piece-part
level when done in accordance with the disassembly instructions in
the GEAE authorized overhaul Engine Manual, and 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.
(2) For engines that utilize the ``Hard Time'' maintenance
requirements:
The part is considered completely disassembled when done in
accordance with the disassembly instructions used in the ``Minor
Maintenance'' or ``Overhaul'' instructions in the GEAE engine
authorized Engine Manual, and 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.
C. Refer to Table 804 below for the mandatory inspection
requirements.
Table 804.--Mandatory Inspection Requirements
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Manual/chapter Mandatory
Part nomenclature section/subject inspection
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Fan Disk (all)................... 72-21-00, All areas (FPI)
INSPECTION. Bores (ECI)
Stage 1 high pressure turbine 72-46-00, All areas (FPI)
(HPT) Rotor Disk (all). INSPECTION. Bores (ECI)
Boltholes (ECI)
Air Holes (ECI)
[[Page 10608]]
Stage 2 HPT Rotor Disk (all)..... 72-46-00, All areas (FPI)
INSPECTION. Bores (ECI)
(a) Boltless Rim Configuration... .................. Boltholes (FPI)
Air Holes (FPI)
(b) Bolted Rim Configuration..... .................. Boltholes (ECI)
Air Holes (ECI)
HPT Rotor Outer Torque Coupling 72-46-00, All areas (FPI)
(all). INSPECTION. Bore (ECI)
Forward Fan Shaft (all).......... 72-21-00, All areas (FPI)
INSPECTION.
Fan Drive Shaft (all)............ 72-22-00, All areas (FPI)
INSPECTION.
Stage 1 Compressor; Rotor Disk 72-33-00, All areas (FPI)
(CF34-3A1) or; Stage 1 INSPECTION.
Compressor Rotor; Blisk (CF34-
3B1) (all).
Compressor Forward Shaft (all)... 72-33-00, All areas (FPI)
INSPECTION.
Stage 2 Compressor Rotor Disk 72-33-00, All areas (FPI)
(all). INSPECTION.
Stage 3-8 Compressor Rotor Spool 72-33-00, All areas (FPI)
(all). INSPECTION.
Stage 9 Compressor Rotor Disk 72-33-00, All areas (FPI)
(all). INSPECTION.
Compressor Rotor Rear Shaft (all) 72-33-00, All areas (FPI)
INSPECTION.
Compressor Discharge Rotating 72-33-00, All non-coated
Seal (all). INSPECTION. Areas (FPI)
Stage 10-14 Compressor Areas 72-33-00, All non-coated
Rotor Spool (all). INSPECTION. (FPI)
Turbine Rear Shaft (LPT Rotor) 72-53-00, All areas (FPI)
(all). INSPECTION.
Stage 3 Turbine Disk (all)....... 72-53-00, All areas (FPI)
INSPECTION.
Stage 4 Turbine Disk (all)....... 72-53-00, All areas (FPI)
INSPECTION.
Stage 5 Turbine Disk (all)....... 72-53-00, All areas (FPI)
INSPECTION.
Stage 6 Turbine Disk (all)....... 72-53-00, All areas (FPI)
INSPECTION.
Turbine Driver Cone (all)........ 72-53-00, All areas (FPI)
INSPECTION.
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FPI = Fluorescent Penetrant Inspection Method
ECI = Eddy Current Inspection''
(b) Except as provided in paragraph (c) of this AD, and
notwithstanding the provisions of section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections
shall be performed only in accordance with the CF34 Engine
Maintenance Program, Chapter 5-21-00, of the General Electric
Company, CF34-3A1 and -3B1 Series Turbofan Engine Manual, SEI-756.
Alternative Method 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 requests through an appropriate FAA
Principal Maintenance Inspector (PMI), 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 AD, if any, may be
obtained from the ECO.
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 done.
Continuous Airworthiness Maintenance Program
(e) FAA-certificated air carriers that have an approved
continuous airworthiness maintenance program in accordance with the
recordkeeping 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 CF34-3A1 and -
3B1 Series Turbofan Engine Manual.
Effective Date
(f) This amendment becomes effective on April 12, 2002.
Issued in Burlington, Massachusetts, on February 27, 2002.
Mark C. Fulmer,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 02-5527 Filed 3-7-02; 8:45 am]
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