AD 2002-07-12

[Federal Register Volume 67, Number 69 (Wednesday, April 10, 2002)]
[Rules and Regulations]
[Pages 17279-17282]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-8641]



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Federal Register / Vol. 67, No. 69 / Wednesday, April 10, 2002 / 
Rules and Regulations

[[Page 17279]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-ANE-49-AD; Amendment 39-12707; AD 2002-07-12]
RIN 2120-AA64


Airworthiness Directives; General Electric Company CF6-80A, CF6-
80C2, and CF6-80E1 Series Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: This amendment supersedes an existing airworthiness directive 
(AD), that is applicable to General Electric Company (GE) CF6-80A, CF6-
80C2, and CF6-80E1 series turbofan engines. That AD currently requires 
revisions to the Life Limits Section of the manufacturer's Instructions 
for Continued Airworthiness (ICA) to include required inspection of 
selected critical life-limited parts at each piece-part exposure. This 
amendment adds additional mandatory inspections for certain high 
pressure compressor (HPC), low pressure turbine (LPT), and high 
pressure turbine (HPT) parts. 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 May 15, 2002.

ADDRESSES: This information 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; or 
at the Office of the Federal Register, 800 North Capitol Street, NW., 
suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803-5299; telephone (781) 
238-7192, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) by superseding AD 2000-08-12, 
Amendment 39-11698 (65 FR 21638, April 24, 2000), which is applicable 
to (GE) CF6-80A, CF6-80C2, and CF6-80E1 series turbofan engines was 
published in the Federal Register on October 5, 2001 (66 FR 50906). 
That action proposed to add to the revisions to the Life Limits section 
of the Engine Manuals, and for air carriers add to their approved 
continuous maintenance program, additional mandatory inspections for 
certain HPC, LPT, and HPT parts. 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.

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.

Intent of AD Perceived to Supersede AD 95-18-14

    Two commenters state that an existing AD (95-18-14) already 
requires fluorescent penetrant inspection (FPI) of certain CF6 HPC 
rotor stage 3-9 spools. These commenters suggest that this AD is 
intended to supersede AD 95-18-14 and, therefore, request that the 
final rule provide this clarification.
    The FAA disagrees that the intent is to supersede AD 95-18-14, but 
agrees that clarification is needed to prevent potential confusion. AD 
95-18-14 requires that a more detailed FPI of the HPC rotor stage 3-9 
spool (as described by GE All Operators' Wire dated 8/10/95) be used 
whenever FPI of these spools is done. AD 95-18-14, however, does not 
specify when the FPI is to be conducted. This final rule requires FPI 
of all HPC rotor stage 3-9 spools at piece-part exposure. This FPI 
technique is now contained in the GE Standard Practice Manual as the 
recommended inspection for deep disk spools.

Typographical Error

    Two commenters state that the proposal contains a typographical 
error in the task number for the CF6-80C2 No. 4R bearing FPI, and 
suggest that task number 72-31-10-200-000-A01 be changed to read task 
number 72-31-10-200-000-A001.
    The FAA disagrees, and believes the commenters were referencing an 
electronic version of the engine manual for this task number. The task 
number in the paper copy of the engine manual is consistent with the 
proposal. GE has advised the FAA that an electronic formatting routine 
incorrectly converted the text for this task number thereby causing the 
noted discrepancy between the paper and electronic (e.g. CD-ROM) 
versions. This electronic formatting routine is being corrected and the 
next publication of the CD will reflect this correction. The paper 
version of the manual is correct. Therefore, no change will be made in 
the final rule.

Intent of AD Perceived to Supersede AD 2001-10-07

    One commenter states that an existing AD (2001-10-07) already 
requires eddy current inspection (ECI) of the CF6-80C2 HPT stage 1 disk 
dovetail slot bottom. The commenter suggests that this proposal is 
intended to supersede AD 2001-10-07 and therefore requests that the 
final rule provide this clarification.
    The FAA disagrees that the intent is to supersede AD 2001-10-07, 
but agrees that clarification on this issue is appropriate to prevent 
any potential for confusion. AD 2001-10-07 requires both an initial and 
repetitive ECI of dovetail slot bottoms, but only for certain CF6-80C2 
HPT Stage 1 disk part numbers. The initial inspection is required 
within the time limits specified in that AD. This final rule requires 
only the repetitive ECI at each piece-part exposure for all current and 
future CF6-80C2 HPT Stage 1 disk dovetail slot bottoms. Repetitive 
ECI's performed on the HPT Stage 1 disks specified in AD 2001-10-07 
will satisfy both the requirements of that AD and the requirements of 
this final rule.

[[Page 17280]]

Reference the Manual Revisions

    One commenter states that engine manual task numbers and/or 
paragraph numbers are subject to change, and therefore, suggested this 
final rule should reference the specific date and revision of the 
manual to ensure compliance. The commenter noted that AD references to 
other manufacturer publications such as service bulletins, always 
reference revisions numbers and issue dates.
    The FAA disagrees. Compliance with this AD is achieved by 
incorporating the schedule of inspections into the Life Limits Section 
of the Instructions for Continued Airworthiness (ICA). Each specific 
piece-part inspection is therefore done by following the operator's 
approved maintenance program, not by the AD itself, and, therefore, the 
AD need not make specific reference to a particular version of the 
manual. In addition, all revisions to the Life Limits Section of the 
manufacturer's ICA's are approved by the FAA. Any engine shop manual 
change that results in a change to the task number of a task in that 
section of the ICA's would require a change that would require FAA 
approval.

Final Rule Effectivity Date

    Two commenters state that the manufacturer has not yet released all 
of the engine manual changes necessary to comply with the final rule. 
One of these commenters suggests that the effective date of the final 
rule should be set for 30 days after release of the manual revisions.
    The FAA partially agrees. The FAA has worked closely with the 
manufacturer to ensure that any new procedures required for the 
additional inspections are incorporated in the engine shop manuals 
(ESM) in a timely fashion. These shop manual changes must be published 
(either by formal or temporary revision to the manual) prior to or 
simultaneous with the publication of revisions to the manufacturer's 
Life Limits Section of the Instructions for Continued Airworthiness 
(ICA). The AD allows up to 30 days after the effective date of the AD 
for the manufacturer to issue the necessary revisions to their ICA. The 
majority of the inspections added by this rule already exist in the 
ESM. Operators were made aware of any new inspections via the notice of 
proposed rulemaking (NPRM) process and separate communications from the 
manufacturer. Since publication of the NPRM, the manufacturer has 
issued temporary revisions to their manuals to add the new inspections 
(CF6-80C2; TR's 72-0842, -0843, -0844, and ``0845 dated 12/14/01, and 
CF6-80E1; TR's 72-0057, -0058, -0059, and -0060 dated 12/18/01). 
Therefore no changes are deemed necessary to the effective date for 
this AD.

Task Number Inconsistencies

    One commenter states that there are inconsistencies between the 
task numbers in the proposal and the manufacturer's engine manual for 
certain components, and requests that the final rule correct these 
inconsistencies.
    The FAA agrees. At the time of publication of the NPRM, the engine 
manual changes for the new inspections, specifically for certain HPT 
rotor R88DT turbine components, were not yet available and therefore 
the task numbers were not yet defined. Since then, the manufacturer has 
issued temporary revisions to the engine manuals to add these 
inspections including the correct task numbers (CF6-80C2, TR's 72-0842, 
-0843, -0844, and ``0845 dated 12/14/01 and CF6-80E1 TR's 72-0057, -
0058, -0059, -0060 dated 12/18/01). The corresponding changes to the 
ICA's have also been prepared to reflect these final task numbers. The 
final rule will reflect the correct task numbers for the new 
inspections.

Approved As-Written

    Three commenters state their approval of the rule as-written, and 
request no changes.
    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 790 engines installed on airplanes of US 
registry would be affected by this AD, that it would take approximately 
10 work hours per engine to accomplish the additional inspections and 
that the average labor rate is $60 per work hour. The total cost of the 
new inspections per engine would be approximately $600. The FAA 
estimates that there will be approximately 327 shop visits per year 
that result in piece-part exposure of the added affected components, 
therfore, the total annual cost for the additional inspections is 
estimated to be $196,200.

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 39-11698 (65 FR 
21638, April 24, 2000) and by adding a new airworthiness directive, 
Amendment 39-12707, to read as follows:

2002-07-12  General Electric Company: Amendment 39-12707. Docket No. 
98-ANE-49-AD. Supersedes AD 2000-08-12, Amendment 39-11698

Applicability

    This airworthiness directive (AD) is applicable to General 
Electric Company (GE) CF6-80A, CF6-80C2, and CF6-80E1 series 
turbofan engines, installed on but not limited to Airbus Industrie 
A300, A310, and A330 series, Boeing 747 and 767 series, and 
McDonnell Douglas MD-11 series airplanes.


[[Page 17281]]


    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, accomplish the following:

Inspections

    (a) Within the next 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:

----------------------------------------------------------------------------------------------------------------
        Part nomenclature                  Part No. (P/N)                Inspect per engine manual chapter
----------------------------------------------------------------------------------------------------------------
For CF6-80A Engines:
Disk, Fan Rotor, Stage 1.........  All...........................  72-21-03 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect, and 72-21-03 Paragraph 4. Eddy
                                                                    Current Inspect.
Fan Forward Shaft................  All...........................  72-21-05 Paragraph 2. Magnetic Shaft Particle
                                                                    Inspect.
Fan Mid Shaft....................  All...........................  72-24-01 Paragraph 2. Magnetic Particle
                                                                    Inspect.
Disk, HPC Rotor, Stage One.......  All...........................  72-31-04 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect.
Disk, HPC Rotor, Stage Two.......  All...........................  72-31-05 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect.
Spool, HPC Rotor, Stage 3-9......  All...........................  72-31-06 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect.
Disk, HPC Rotor, Stage 10........  All...........................  72-31-07 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect.
Spool, HPC Rotor, Stage 11-14....  All...........................  72-31-08 Paragraph 3.A. Fluorescent-Penetrant
                                                                    Inspect.
Rotating CDP Seal................  All...........................  72-31-10 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspect.
Disk Shaft, HPT Rotor, Stage One.  All...........................  72-53-02 Paragraph 3. Fluorescent-Penetrant-
                                                                    Inspect per 70-32-02, and 72-53-02 Paragraph
                                                                    6.C. Eddy Current Inspection, and 72-53-02
                                                                    Paragraph 6.D. Disk Bore Area Eddy Current
                                                                    Inspection.
Disk, HPT Rotor, Stage Two.......  All...........................  72-53-06 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspection, and 72-53-06 Paragraph 6. Eddy
                                                                    Current Inspection of Rim Boltholes for
                                                                    Cracks, and 72-53-06 Paragraph 7. Disk Bore
                                                                    Area Eddy Current Inspection.
Disk, LPT Rotor Stage, 1-4.......  All...........................  72-57-02 Paragraph 3. Fluorescent-Penetrant
                                                                    Inspection.
Shaft, LPT Rotor.................  All...........................  72-57-03 Paragraph 3. Fluorescent- Penetrant
                                                                    Inspection, and 72-57-03 Paragraph 6. Eddy
                                                                    Current Inspection.
For All CF6-80C2 Engines:
Disk, Fan Rotor, Stage 1.........  All...........................  Task 72-21-03-200-000-004 Fluorescent-
                                                                    Penetrant Inspection, and Task 72-21-03-200-
                                                                    000-008 Eddy Current Inspect Fan Rotor Disk
                                                                    Stage 1 Bore, Forward and Aft Hub Faces, and
                                                                    Bore Radii.
Shaft, Fan Forward...............  All...........................  Task 72-21-05-200-000-001 Fluorescent-
                                                                    Penetrant Inspection, and Task 72-21-05-200-
                                                                    000-005 Vent Hole Eddy Current Inspection.
HPCR Stage 1 Disk................  All...........................  Task 72-31-04-200-000-002 Fluorescent-
                                                                    Penetrant Inspection.
HPCR Stage 2 Disk................  All...........................  Task 72-31-05-200-000-002 Fluorescent-
                                                                    Penetrant Inspection.
HPCR Stage 3-9 Spool.............  All...........................  Task 72-31-06-200-000-001 Fluorescent-
                                                                    Penetrant Inspection.
HPCR Stage 10 Disk...............  All...........................  Task 72-31-07-200-000-001 Fluorescent-
                                                                    Penetrant Inspection.
HPCR Stage 11-14 Spool/Shaft.....  All...........................  Task 72-31-08-200-000-002 Fluorescent-
                                                                    Penetrant Inspection.
No. 4 Bearing Rotating (CDP) Air   All...........................  Task 72-31-10-200-000-001 Fluorescent-
 Seal.                                                              Penetrant Inspection or Task 72-31-10-200-
                                                                    000-A01 Fluorescent-Penetrant Inspection.
HPCR Stage 10-14 Spool/Shaft.....  All...........................  Task 72-31-22-200-000-002 Fluorescent-
                                                                    Penetrant Inspection.
Fan Mid Shaft....................  All...........................  Task 72-24-01-200-000-003 Magnetic Particle
                                                                    Inspection.
Disk Shaft, HPT Rotor, Stage One.  All...........................  Task 72-53-02-200-000-001 Fluorescent-
                                                                    Penetrant Inspect, and Task 72-53-02-200-000-
                                                                    005 Disk Rim Bolt Hole Eddy Current
                                                                    Inspection, and Task 72-53-02-200-000-006
                                                                    Disk Bore Area Eddy Current Inspection, and
                                                                    Task 72-53-02-200-000-007 Disk Dovetail Slot
                                                                    Bottom Eddy Current Inspection.
Disk, HPT Rotor, Stage Two.......  All...........................  Task 72-53-06-200-000-002 Fluorescent-
                                                                    Penetrant Inspect, and Task 72-53-06-200-000-
                                                                    006 Disk Rim Bolt Hole Eddy Current
                                                                    Inspection Rim Boltholes, and Task 72-53-06-
                                                                    200-000-007 Disk Bore Area Eddy Current
                                                                    Inspection.
LPTR Stage 1-5 Disks.............  All...........................  Task 72-57-02-200-000-001 Fluorescent-
                                                                    Penetrant Inspection.
LPTR Shaft.......................  All...........................  Task 72-57-03-200-000-002 Fluorescent-
                                                                    Penetrant Inspect, and Task 72-57-03-200-000-
                                                                    006 Eddy Current Inspection.
For CF6-80C2 Engines configured
 with the R88DT Turbine (Models
 CF6-80C2B2F, 80C2B4F, 80C2B6F,
 80C2B7F, 80C2B8F):
Disk Shaft, HPT Rotor, Stage One   All...........................  Task 72-53-16-200-000-001 Fluorescent-
 (R88DT, No Rim Bolt Holes).                                        Penetrant Inspect, and Task 72-53-16-200-000-
                                                                    005 Disk Bore Area Eddy Current Inspection.
Disk, HPT Rotor, Stage Two         All...........................  Task 72-53-18-200-000-002 Fluorescent-
 (R88DT, No Rim Bolt Holes).                                        Penetrant Inspect, and Task 72-53-18-200-000-
                                                                    005 Disk Bore Area Eddy Current Inspection.
Rotating Interstage Seal (R88DT).  All...........................  Task 72-53-17-200-000-001 Fluorescent-
                                                                    Penetrant Inspect, and Task 72-53-17-200-000-
                                                                    005 Seal Bore Area Eddy Current.
Forward Outer Seal (R88DT).......  All...........................  Task 72-53-21-200-000-001 Fluorescent-
                                                                    Penetrant Inspect, and Task 72-53-21-200-000-
                                                                    004 Seal Bore Area Eddy Current.

[[Page 17282]]

 
For CF6-80E1 Engines:
Disk, Fan Rotor, Stage One.......  All...........................  Sub Task 72-21-03-230-051 Fluorescent-
                                                                    Penetrant Inspection, and Sub Task 72-21-03-
                                                                    250-051 or 72-21-03-250-052 Disk Bore Eddy
                                                                    Current Inspection.
Shaft, Fan Forward...............  All...........................  Sub Task 72-21-05-230-051 Fluorescent-
                                                                    Penetrant Inspection, and Sub Task 72-21-05-
                                                                    250-051 Vent Hole Eddy Current Inspection.
Compressor Rotor, Stage 1 Disk...  All...........................  Sub Task 72-31-04-230-051 Fluorescent-
                                                                    Penetrant Inspection.
Compressor Rotor, Stage 2 Disk...  All...........................  Sub Task 72-31-05-230-051 Fluorescent-
                                                                    Penetrant Inspection.
Compressor Rotor, Stage 3-9 Spool  All...........................  Sub Task 72-31-06-230-051 Fluorescent-
                                                                    Penetrant Inspection.
Compressor Rotor, Stage 10 Disk    All...........................  Sub Task 72-31-07-230-051 Fluorescent-
 (Pre SB 72-0150).                                                  Penetrant Inspection.
Compressor Rotor, Spool/Shaft,     All...........................  Sub Task 72-31-08-230-051 Fluorescent-
 Stage 11-14 (Pre SB 72-0150).                                      Penetrant Inspection
Compressor Rotor, Spool/Shaft,     All...........................  Sub Task 72-31-23-230-052 Fluorescent-
 Stage 10-14 (SB 72-0150).                                          Penetrant Inspection.
Compressor Rotor, No. 4 Bearing    All...........................  Sub Task 72-31-10-230-051 Fluorescent-
 Rotating Air Seal (CDP Rotating                                    Penetrant Inspection.
 Seal).
HPT Disk/Shaft, Stage 1..........  All...........................  Sub Task 72-53-02-230-051 Fluorescent-
                                                                    Penetrant Inspection, and Sub Task 72-53-02-
                                                                    250-051 Eddy Current Inspection, Rim Bolt
                                                                    Holes, and Sub Task 72-53-02-250-054 Eddy
                                                                    Current Inspection, Disk Bore Area.
HPT Disk, Stage 2................  All...........................  Sub Task 72-53-06-230-051 Fluorescent-
                                                                    Penetrant Inspection, and Sub Task 72-53-06-
                                                                    250-051 Eddy Current Inspection, Rim Bolt
                                                                    Holes, and Sub Task 72-53-06-250-054 Eddy
                                                                    Current Inspection, Disk Bore Area.
LPT Rotor Shaft..................  All...........................  Sub Task 72-55-01-240-051 Magnetic Particle
                                                                    Inspect.
LPT Disks, Stages 1-5............  All...........................  Sub Task 72-57-02-230-051 Fluorescent-
                                                                    Penetrant Inspect.
LPT Rotor Torque Cone............  All...........................  Sub Task 72-57-03-220-051 Fluorescent-
                                                                    Penetrant Inspect
For CF6-80E1 Engines configured
 with the R88DT Turbine:
Disk Shaft, HPT Rotor............  All...........................  Sub Task 72-53-16-230-052 Fluorescent-
                                                                    Penetrant Inspect, and Sub Task 72-53-16-250-
                                                                    051 Disk Bore Area Eddy Current Inspection.
Disk, HPT Rotor, Stage 2 (R88DT,   All...........................  Sub Task 72-53-18-230-051 Fluorescent-
 No Rim Bolt Holes).                                                Penetrant Inspect, and Sub Task 72-53-18-250-
                                                                    051 Disk Bore Area Eddy Current Inspection.
HPT Rotor Rotating Interstage      All...........................  Sub Task 72-53-17-230-051 Fluorescent-
 Seal (R88DT).                                                      Penetrant Inspect, and Sub Task 72-53-17-250-
                                                                    051 Seal Bore Area Eddy Current.
HPT Rotor Forward Outer Seal       All...........................  Sub Task 72-53-21-230-051 Fluorescent-
 (R88DT).                                                           Penetrant Inspect, and Sub Task 72-53-21-250-
                                                                    051 Seal Bore Area Eddy Current.
----------------------------------------------------------------------------------------------------------------

    (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 
shall 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.

Continuous Airworthiness Maintenance Program

    (d) 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 Instructions for Continuous 
Airworthiness (ICA) and the air carrier's continuous airworthiness 
program. Alternately, 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 
requirements in the engine manuals.

Effective Date

    (e) This amendment becomes effective on May 15, 2002.

    Issued in Burlington, Massachusetts, on April 3, 2002.
Jay J. Pardee,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 02-8641 Filed 4-9-02; 8:45 am]
BILLING CODE 4910-13-U