[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.

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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:

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                                                                                    Inspect per engine manual
               Part nomenclature                         Part no. (P/N)                      chapter
----------------------------------------------------------------------------------------------------------------
For GE90 Engines:
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[[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