Published 2002-03-04 · Federal Register document 02-5003
Airworthiness Directives; General Electric Company GE90 Series Turbofan Engines
Publication summary
This amendment supersedes an existing airworthiness directive (AD), applicable to certain General Electric Company (GE) GE90 series turbofan engines, that currently requires revisions to the Life Limits Section 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 action 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. This amendment is prompted by additional focused inspection procedures that have been developed by the manufacturer. 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.
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Final-rule publication
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- 2002-04-11
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Official source · 2002-03-04
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[Federal Register Volume 67, Number 42 (Monday, March 4, 2002)]
[Rules and Regulations]
[Pages 9582-9584]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 02-5003]
[[Page 9582]]
=======================================================================
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 98-ANE-39-AD; Amendment 39-12668; AD 2002-04-11]
RIN 2120-AA64
Airworthiness Directives; General Electric Company GE90 Series
Turbofan Engines
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: This amendment supersedes an existing airworthiness directive
(AD), applicable to certain General Electric Company (GE) GE90 series
turbofan engines, that currently requires revisions to the Life Limits
Section 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 action 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. This amendment is
prompted by additional focused inspection procedures that have been
developed by the manufacturer. 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 8, 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: Ian Dargin, Aerospace Engineer, Engine
Certification Office, FAA, Engine and Propeller Directorate, 12 New
England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-
7178, fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal
Aviation Regulations (14 CFR part 39) by superseding (AD) 2000-08-10,
Amendment 39-11696 (65 FR 21642, April 24, 2000), that is applicable to
General Electric GE90 series turbofan engines was published in the
Federal Register on October 10, 2001 (66 FR 51607). 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 39-11696 (65 FR
21642, April 24, 2000), and by adding a new airworthiness directive,
Amendment 39-12668 to read as follows:
AD 2002-04-11 General Electric Company: Docket No. 98-ANE-39-AD.
Supersedes AD 2000-08-10, Amendment 39-11696.
Applicability
This airworthiness directive (AD) is applicable to General
Electric Company (GE) GE90-76B/ -77B/ -85B/ -90B/ -94B series
turbofan engines. These engines are installed on but not limited to
Boeing 777 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
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 manufacturer's Life Limits Section of the Instructions for
Continued Airworthiness (ICA), 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 instructions provided in the
applicable manual provisions:
----------------------------------------------------------------------------------------------------------------
Inspect per engine manual
Part nomenclature Part no. (P/N) chapter
----------------------------------------------------------------------------------------------------------------
For GE90 Engines:
----------------------------------------------------------------------------------------------------------------
[[Page 9583]]
HPCR Disk, Stage 1........................ All............................ 72-31-05-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-31-05-
230-051), and 72-31-05-200-001-
001 Eddy Current Inspection of
the Bore, and 72-31-05-200-001-
001 Eddy Current Inspection of
the Dovetail Slots.
----------------------------------------------------------------------------------------------------------------
HPCR Spool, Stage 2-6..................... All............................ 72-31-06-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-31-06-
230-051), and 72-31-06-200-001-
001 Eddy Current Inspection of
the S2 Dovetail Slots.
----------------------------------------------------------------------------------------------------------------
HPCR, Disk, Stage 7....................... All............................ 72-31-07-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-31-07-
230-051), and 72-31-07-200-001-
001 Eddy Current Inspection
(subtask 72-31-07-250-051 or
72-31-07-230-052 or 72-31-07-
230-053.
----------------------------------------------------------------------------------------------------------------
HPCR Spool, Stage 8-10.................... All............................ 72-31-08-200-001-001
Fluorescent Penetrant
Inspection and 72-31-08-800-
001 Eddy Current Inspection of
the stage 8-9 inertia weld.
----------------------------------------------------------------------------------------------------------------
HPCR Seal, Compressor Discharge Pressure.. All............................ 72-31-09-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-31-09-
230-051), and 72-31-09-200-001-
001 Eddy Current Inspection of
the Boltholes.
----------------------------------------------------------------------------------------------------------------
HPCR Ring, Tube Supporter................. All............................ 72-31-10-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
HPTR, Interstage Seal..................... All............................ 72-53-03-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-53-03-
230-053), and 72-53-03-200-001-
001 Eddy Current Inspection of
the Bore.
----------------------------------------------------------------------------------------------------------------
Fan Disk, Stage 1......................... All............................ 72-21-03-200-001-001
Fluorescent Penetrant
Inspection (subtask 72-21-03-
230-051), and 72-21-03-200-001-
001 Eddy Current of the bore,
and 72-21-03-200-001-001
Ultrasonic Inspection of
Dovetail Slots.
----------------------------------------------------------------------------------------------------------------
HPTR Disk, Stage 1........................ All............................ 72-53-02-200-001-002
Fluorescent Penetrant
Inspection (subtask 72-53-02-
160-051), and 72-53-02-200-001-
002 Eddy Current Inspection of
the Bore.
----------------------------------------------------------------------------------------------------------------
HPTR Disk, Stage 2........................ All............................ 72-53-04-200-001-004
Fluorescent Penetrant
Inspection (subtask 72-53-04-
230-052), and 72-53-04-200-001-
004 Eddy Current Inspection of
the Bore.
----------------------------------------------------------------------------------------------------------------
LPTR Cone Shaft........................... All............................ 72-56-07-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Fan Mid Shaft........................ All............................ 72-58-01-200-001-001 Magnetic
Particle Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 1........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 2........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 3........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 4........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 5........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
LPTR Disk, Stage 6........................ All............................ 72-56-02-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
Fan Shaft, Forward........................ All............................ 72-22-01-200-001-001
Fluorescent Penetrant
Inspection.
----------------------------------------------------------------------------------------------------------------
(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 section 43.16 of the Federal
Aviation Regulations (14 CFR 43.16), these mandatory inspections
must be performed only in accordance with the Life Limits Section of
the manufacturer's ICA.
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 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 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
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
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 Life Limits Section of the ICA 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,
[[Page 9584]]
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
requirements in the engine manuals.
Effective Date
(f) This amendment becomes effective on April 8, 2002.
Issued in Burlington, Massachusetts, on February 21, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 02-5003 Filed 3-1-02; 8:45 am]
BILLING CODE 4910-13-U
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