
[Federal Register: October 23, 2008 (Volume 73, Number 206)]
[Proposed Rules]               
[Page 63090-63094]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr23oc08-18]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0952; Directorate Identifier 98-ANE-49-AD]
RIN 2120-AA64

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

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for General Electric Company (GE) CF6-80A, CF6-80C2, and 
CF6-80E1 series turbofan engines. That AD currently requires revisions 
to the Airworthiness Limitations Section (ALS) 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 proposed AD would require revisions to the CF6-80A, CF6-
80C2, and CF6-80E1 series engines ALS sections of the manufacturer's 
manuals and an air carrier's approved continuous airworthiness 
maintenance program to incorporate additional inspection requirements, 
and to update certain Engine Manual Inspection Task and Sub Task Number 
references. This proposed AD results from the need to require enhanced 
inspection of selected critical life-limited parts of CF6-80A, CF6-
80C2, and CF6-80E1 series engines. We are proposing this AD to prevent 
critical life-limited rotating engine part failure, which could result 
in an uncontained engine failure and damage to the airplane.

DATES: We must receive any comments on this proposed AD by December 22, 
2008.

ADDRESSES: Use one of the following addresses to comment on this 
proposed AD.
     Federal eRulemaking Portal: Go to http://
www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 1200 New Jersey Avenue, SE., West Building Ground 
Floor, Room W12-140, Washington, DC 20590-0001.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
     Fax: (202) 493-2251.

FOR FURTHER INFORMATION CONTACT: Robert Green, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
robert.green@faa.gov; telephone (781) 238-7754; (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2008-0952; Directorate 
Identifier 98-ANE-49-AD'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    We will post all comments we receive, without change, to http://
www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact 
with FAA personnel concerning this proposed AD. Using the search 
function of the Web site, anyone can find and read the comments in any 
of our dockets, including, if provided, the name of the individual who 
sent the comment (or signed the comment on behalf of an association, 
business, labor union, etc.). You may review the DOT's complete Privacy 
Act Statement in the Federal Register published on April 11, 2000 (65 
FR 19477-78).

Examining the AD Docket

    You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
the same as the Mail address provided in the ADDRESSES section. 
Comments will be available in the AD docket shortly after receipt.

Discussion

    On April 3, 2002, we issued AD 2002-07-12, Amendment 39-12707 (67 
FR 17279, April 10, 2002), to require revisions to the ALS of the 
manufacturer's ICA for GE CF6-80A, CF6-80C2, and CF6-80E1 series 
turbofan engines to include required enhanced inspection of selected 
critical life-limited parts at each piece-part exposure.

Additional Inspection Procedures

    Since the issuance of that AD, an FAA study of in-service events 
involving uncontained failures of critical rotating engine parts has 
indicated the need for additional 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 engine failures. This proposal would require revisions to 
the CF6-80A, CF6-80C2, and CF6-80E1 series engines ALS sections of the 
manufacturer's manuals and an air carrier's approved continuous 
airworthiness maintenance program to incorporate additional inspection 
requirements.

FAA's Determination and Requirements of the Proposed AD

    Since an unsafe condition has been identified that is likely to 
exist or develop on other products of this same type design, the 
proposed AD would supersede AD 2002-07-12 to add additional inspections 
for certain high-pressure turbine (HPT) components, and to update 
certain Engine Manual Inspection Task and or Sub Task Number 
references. These inspections would be required at each piece-part 
opportunity. For reference, this proposed AD carries forward the 
requirements from AD 2002-07-12. Also for reference, the parts added to 
the table in the compliance section of this AD are identified by an 
asterisk (*) that precedes the part nomenclature. Also for reference, 
parts that have an Engine Manual Inspection Task and or Sub Task Number 
reference updated in the table in the compliance section of this AD, 
are identified by two asterisks (**) that precede the part 
nomenclature.

Costs of Compliance

    We estimate that this proposed AD would affect 315 CF6-80A series 
engines and 926 CF6-80C2 series engines installed on airplanes of U.S.

[[Page 63091]]

registry. We also estimate that it would take about 5 work-hours per 
CF6-80A series engine and about 2 work-hours per CF6-80C2 series engine 
to do the proposed additional inspections and that the average labor 
rate is $80 per work-hour. The total cost of the new inspections per 
CF6-80A series engine would be about $400. The total cost of the new 
inspections per CF6-80C2 series engine would be about $160. We estimate 
that there will be about 42 shop visits per year for CF6-80A series 
engines, and about 128 shop visits per year for CF6-80C2 series engines 
that result in piece-part-exposure of the added affected components. 
Therefore, we estimate the total annual cost for the additional 
inspections to be $37,280.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, Section 106, describes the 
authority of the FAA Administrator. Subtitle VII, Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701, ``General 
Requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We have determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD 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.
    For the reasons discussed above, I certify that the proposed AD:
    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. Would not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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. The FAA amends Sec.  39.13 by removing Amendment 39-12707 (67 FR 
17279, April 10, 2002) and by adding a new airworthiness directive to 
read as follows:

General Electric Company: Docket No. FAA-2008-0952; Directorate 
Identifier 98-ANE-49-AD.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this airworthiness directive (AD) action by December 22, 
2008.

Affected ADs

    (b) This AD supersedes AD 2002-07-12, Amendment 39-12707.

Applicability

    (c) This AD applies to General Electric Company CF6-80A, CF6-
80C2, and CF6-80E1 series turbofan engines. These engines are 
installed on, but not limited to, Airbus A300, A310, and A330 
series, Boeing 747 and 767 series, and McDonnell Douglas MD-11 
series airplanes.

Unsafe Condition

    (d) This AD results from the need to require enhanced inspection 
of selected critical life-limited parts of CF6-80A, CF6-80C2, and 
CF6-80E1 series engines. We are issuing this AD to prevent critical 
life-limited rotating engine part failure, which could result in an 
uncontained engine failure and damage to the airplane.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified unless the 
actions have already been done.

Inspections

    (f) Within the next 180 days after the effective date of this 
AD, revise the Airworthiness Limitations Section (ALS) of the 
manufacturer's 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
       Part nomenclature          Part No. (P/N)     manual inspection
                                                          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 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 4.
                                                    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     All..............  72-53-02 Paragraph 3.
 One.                                               Fluorescent-
                                                    Penetrant Inspect
                                                    per 70-32-02, and
                                                   72-53-02 Paragraph
                                                    6.C. Disk Rim Bolt
                                                    Hole Eddy Current
                                                    Inspection, and
                                                   72-53-02 Paragraph
                                                    6.D. Disk Bore Eddy
                                                    Current Inspection.
* Disk Shaft, HPT Rotor Stage   All..............  72-53-02 Paragraph
 One.                                               6.E. Disk Dovetail
                                                    Slot Bottom Eddy
                                                    Current Inspection.

[[Page 63092]]


* Disk Shaft, HPT Rotor, Stage  P/Ns 2047M33G01    72-53-02 Paragraph 7.
 One.                            thru G10, and P/   Disk Dovetail Slot
                                 N 9362M58G11.      Bottom Aft Corner
                                                    Chamfers 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
                                                    Bolt Holes for
                                                    Cracks, and
                                                   72-53-06 Paragraph 7.
                                                    Disk Bore 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.
Fan Mid Shaft.................  All..............  Task 72-24-01-200-000-
                                                    003 Magnetic
                                                    Particle 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)    All..............  Task 72-31-10-200-000-
 Air Seal.                                          001 Fluorescent
                                                    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.
** Disk/Shaft, HPT Rotor,       All..............  Task 72-53-02-200-000-
 Stage One.                                         001 (Inspection--
                                                    Configuration 1), or
                                                    Task 72-53-02-230-
                                                    801 (Inspection--
                                                    Configuration 2),
                                                    Fluorescent-
                                                    Penetrant Inspect,
                                                    and
                                                   Task 72-53-02-200-000-
                                                    005 (Inspection--
                                                    Configuration 1), or
                                                    Task 72-53-02-250-
                                                    802 (Inspection--
                                                    Configuration 2),
                                                    Disk Rim Bolt Hole
                                                    Eddy Current
                                                    Inspection, and
                                                   Task 72-53-02-200-000-
                                                    006 (Inspection--
                                                    Configuration 1), or
                                                    Task 72-53-02-250-
                                                    803 (Inspection--
                                                    Configuration 2),
                                                    Disk Bore Area Eddy
                                                    Current Inspection,
                                                    and
                                                   Task 72-53-02-200-000-
                                                    007 (Inspection--
                                                    Configuration 1), or
                                                    Task 72-53-02-250-
                                                    804 (Inspection--
                                                    Configuration 2),
                                                    Disk Dovetail Slot
                                                    Bottom Eddy Current.
* Disk/Shaft, HPT Rotor, Stage  P/N 1531M84G12     Task 72-53-02-250-801
 One.                            and P/Ns           (Inspection--Configu
                                 2047M32G01 thru    ration 1), Disk
                                 G07.               Dovetail Slot Bottom
                                                    Aft Corner Chamfers
                                                    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, and
                                                   Task 72-53-06-200-000-
                                                    007 Disk Bore 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    All..............  Task 72-53-16-200-000-
 One (R88DT, No Rim Bolt                            001 Fluorescent-
 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-
 (R88DT, No Rim Bolt Holes).                        002 Fluorescent-
                                                    Penetrant Inspect,
                                                    and
                                                   Task 72-53-18-200-000-
                                                    005 Disk Bore Area
                                                    Eddy Current
                                                    Inspection.
Rotating Interstage Seal        All..............  Task 72-53-17-200-000-
 (R88DT).                                           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.
------------------------------------------------------------------------
                          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....................  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.

[[Page 63093]]


Compressor Rotor, Stage 3-9     All..............  Sub Task 72-31-06-230-
 Spool.                                             051 Fluorescent
                                                    Penetrant
                                                    Inspection.

Compressor Rotor, Stage 10      All..............  Sub Task 72-31-07-230-
 Disk (Pre SB 72-0150).                             051 Fluorescent
                                                    Penetrant
                                                    Inspection.
Compressor Rotor Spool/Shaft,   All..............  Sub Task 72-31-08-230-
 Stage 11-14 (Pre SB 72-0150).                      051 Fluorescent
                                                    Penetrant
                                                    Inspection.
Compressor Rotor Spool/Shaft,   All..............  Sub Task 72-31-23-230-
 Stage 10-14 (SB 72-0150).                          052 Fluorescent
                                                    Penetrant
                                                    Inspection.
Compressor Rotor No. 4 Bearing  All..............  Sub Task 72-31-10-230-
 Rotating Air Seal (CDP                             051 Fluorescent
 Rotating Seal).                                    Penetrant
                                                    Inspection.
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.
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.
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, Stage 1  All..............  Sub Task 72-53-16-230-
 (R88DT, No Rim Bolt Holes).                        052 Fluorescent-
                                                    Penetrant Inspect,
                                                    and
                                                   Sub Task 72-53-16-250-
                                                    051 Disk Bore Area
                                                    Eddy Current
                                                    Inspection.
Disk, HPT Rotor, Stage 2        All..............  Sub Task 72-53-18-230-
 (R88DT, No Rim Bolt Holes).                        051 Fluorescent-
                                                    Penetrant Inspect,
                                                    and
                                                   Sub Task 72-53-18-250-
                                                    051 Disk Bore Area
                                                    Eddy Current
                                                    Inspection.
** HPT Rotor Rotating           All..............  Sub Task 72-53-17-230-
 Interstage Seal (R88DT).                           056 Fluorescent-
                                                    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-
 (R88DT).                                           051 Fluorescent-
                                                    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.
    (g) The parts added to the table of this AD are identified by an 
asterisk (*) that precedes the part nomenclature. Also, parts that 
have an Engine Manual Inspection Task and/or Sub Task Number 
reference updated in the table of this AD, are identified by two 
asterisks (**) that precede the part nomenclature.
    (h) Except as provided in paragraph (i) 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 ALS of the 
manufacturer's ICA.

Alternative Methods of Compliance (AMOC)

    (i) You must perform these mandatory inspections using the ALS 
of the ICA and the applicable Engine Manual unless you receive 
approval to use an AMOC under paragraph (j) of this AD. Section 
43.16 of the Federal Aviation Regulations (14 CFR 43.16) may not be 
used to approve alternative methods of compliance or adjustments to 
the times in which these inspections must be performed.
    (j) The Manager, Engine Certification Office, has the authority 
to approve alternative methods of compliance for this AD if 
requested using the procedures found in 14 CFR 39.19.

Maintaining Records of the Mandatory Inspections

    (k) You have met the requirements of this AD when you revise the 
ALS of the manufacturer's ICA as specified in paragraph (f) of this 
AD. For air carriers operating under part 121 of the Federal 
Aviation Regulations (14 CFR part 121), you have met the 
requirements of this AD when you modify your continuous 
airworthiness maintenance plan to reflect those changes. You do not 
need to record each piece-part inspection as compliance to this AD, 
but you must maintain records of those inspections according to the 
regulations governing your operation. For air carriers operating 
under part 121, you may use either the system established to comply 
with section 121.369 or an alternative accepted by your principal 
maintenance inspector if that alternative:
    (1) Includes a method for preserving and retrieving the records 
of the inspections resulting from this AD; and
    (2) Meets the requirements of section 121.369(c); and
    (3) Maintains the records either indefinitely or until the work 
is repeated.
    (l) These recordkeeping requirements apply only to the records 
used to document the mandatory inspections required as a result of 
revising the ALS of the manufacturer's ICA as specified in paragraph 
(f) of this AD. These recordkeeping requirements do not alter or 
amend the recordkeeping requirements for any other AD or regulatory 
requirement.

Related Information

    (m) Contact Robert Green, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
robert.green@faa.gov; telephone (781) 238-7754; fax (781) 238-7199, 
for more information about this AD.


[[Page 63094]]


    Issued in Burlington, Massachusetts, on October 16, 2008.
Peter A. White,
Assistant Manager, Engine and Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. E8-25278 Filed 10-22-08; 8:45 am]

BILLING CODE 4910-13-P
