Airworthiness Directives; General Electric Company CF6-80A, CF6-80C2, and CF6-80E1 Series Turbofan Engines, 63090-63094 [E8-25278]
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63090
Federal Register / Vol. 73, No. 206 / Thursday, October 23, 2008 / Proposed Rules
Done in Washington, DC, this 17th day of
October 2008.
Bruce Knight,
Under Secretary for Marketing and Regulatory
Programs.
[FR Doc. E8–25289 Filed 10–22–08; 8:45 am]
BILLING CODE 3410–34–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
dwashington3 on PRODPC61 with PROPOSALS
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 piecepart 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.
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
https://www.regulations.gov and follow
DATES:
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14:57 Oct 22, 2008
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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 https://
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 https://
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
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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 highpressure 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.
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Federal Register / Vol. 73, No. 206 / Thursday, October 23, 2008 / Proposed Rules
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
Part nomenclature
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.
63091
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.
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:
Compliance
PART 39—AIRWORTHINESS
DIRECTIVES
Inspections
1. The authority citation for part 39
continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–12707 (67 FR
17279, April 10, 2002) and by adding a
new airworthiness directive to read as
follows:
Part No. (P/N)
(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.
(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 manual inspection chapter
For CF6–80A Engines
dwashington3 on PRODPC61 with PROPOSALS
Disk, Fan Rotor, Stage 1 ................
All ...................................................
Fan Forward Shaft ..........................
Fan Mid Shaft ..................................
Disk, HPC Rotor, Stage One ..........
** Disk, HPC Rotor, Stage Two .......
Spool, HPC Rotor, Stage 3–9 .........
Disk, HPC Rotor, Stage 10 .............
Spool, HPC Rotor, Stage 11–14 .....
Rotating CDP Seal ..........................
Disk Shaft, HPT Rotor Stage One ..
All
All
All
All
All
All
All
All
All
* Disk Shaft, HPT Rotor Stage One
All ...................................................
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...................................................
...................................................
...................................................
...................................................
...................................................
...................................................
...................................................
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72–21–03 Paragraph 3. Fluorescent-Penetrant Inspect, and 72–21–
03 Paragraph 4. Eddy Current Inspect.
72–21–05 Paragraph 2. Magnetic Particle Inspect.
72–24–01 Paragraph 2. Magnetic Particle Inspect.
72–31–04 Paragraph 3. Fluorescent-Penetrant Inspect.
72–31–05 Paragraph 4. Fluorescent-Penetrant Inspect.
72–31–06 Paragraph 3. Fluorescent-Penetrant Inspect.
72–31–07 Paragraph 3. Fluorescent-Penetrant Inspect.
72–31–08 Paragraph 3.A. Fluorescent-Penetrant Inspect.
72–31–10 Paragraph 3. Fluorescent-Penetrant Inspect.
72–53–02 Paragraph 3. 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.
72–53–02 Paragraph 6.E. Disk Dovetail Slot Bottom Eddy Current Inspection.
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Federal Register / Vol. 73, No. 206 / Thursday, October 23, 2008 / Proposed Rules
Part nomenclature
Part No. (P/N)
Inspect per engine manual inspection chapter
* Disk Shaft, HPT Rotor, Stage One
Disk, HPT Rotor, Stage Two ..........
P/Ns 2047M33G01 thru G10, and
P/N 9362M58G11.
All ...................................................
Disk, LPT Rotor Stage 1–4 .............
Shaft, LPT Rotor .............................
All ...................................................
All ...................................................
72–53–02 Paragraph 7. Disk Dovetail Slot Bottom Aft Corner Chamfers Eddy Current Inspection.
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.
72–57–02 Paragraph 3. Fluorescent-Penetrant Inspection.
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 ...................................................
Shaft, Fan Forward .........................
All ...................................................
Fan Mid Shaft ..................................
HPCR Stage 1 Disk ........................
HPCR Stage 2 Disk ........................
HPCR Stage 3–9 Spool ..................
HPCR Stage 10 Disk ......................
HPCR Stage 11–14 Spool/Shaft .....
No. 4 Bearing Rotating (CDP) Air
Seal.
All
All
All
All
All
All
All
HPCR Stage 10–14 Spool/Shaft .....
** Disk/Shaft, HPT Rotor, Stage
One.
All ...................................................
All ...................................................
* Disk/Shaft, HPT Rotor, Stage One
Disk, HPT Rotor, Stage Two ..........
P/N 1531M84G12 and P/Ns
2047M32G01 thru G07.
All ...................................................
LPTR Stage 1–5 Disks ...................
LPTR Shaft ......................................
All ...................................................
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.
Task 72–21–05–200–000–001 Fluorescent Penetrant Inspection, and
Task 72–21–05–200–000–005 Vent Hole Eddy Current Inspection.
Task 72–24–01–200–000–003 Magnetic Particle Inspection.
Task 72–31–04–200–000–002 Fluorescent Penetrant Inspection.
Task 72–31–05–200–000–002 Fluorescent Penetrant Inspection.
Task 72–31–06–200–000–001 Fluorescent Penetrant Inspection.
Task 72–31–07–200–000–001 Fluorescent Penetrant Inspection.
Task 72–31–08–200–000–002 Fluorescent Penetrant Inspection.
Task 72–31–10–200–000–001 Fluorescent Penetrant Inspection or
Task 72–31–10–200–000–A01 Fluorescent Penetrant Inspection.
Task 72–31–22–200–000–002 Fluorescent Penetrant Inspection.
Task 72–53–02–200–000–001 (Inspection—Configuration 1), or Task
72–53–02–230–801 (Inspection—Configuration 2), FluorescentPenetrant 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.
Task 72–53–02–250–801 (Inspection—Configuration 1), Disk Dovetail
Slot Bottom Aft Corner Chamfers Eddy Current Inspection.
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.
Task 72–57–02–200–000–001 Fluorescent-Penetrant Inspection.
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
(R88DT, No Rim Bolt Holes).
Disk, HPT Rotor, Stage Two
(R88DT, No Rim Bolt Holes).
All ...................................................
Task 72–53–16–200–000–001 Fluorescent-Penetrant Inspect, and
All ...................................................
Task 72–53–16–200–000–005 Disk Bore Area Eddy Current Inspection.
Task 72–53–18–200–000–002 Fluorescent-Penetrant Inspect, and
All ...................................................
Forward Outer Seal (R88DT) ..........
dwashington3 on PRODPC61 with PROPOSALS
Rotating Interstage Seal (R88DT) ..
All ...................................................
Task 72–53–18–200–000–005 Disk Bore Area Eddy Current Inspection.
Task 72–53–17–200–000–001 Fluorescent-Penetrant Inspect, and
Task 72–53–17–200–000–005 Seal Bore Area Eddy Current.
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 ...................................................
Shaft, Fan ........................................
All ...................................................
Compressor Rotor, Stage 1 Disk ....
Compressor Rotor, Stage 2 Disk ....
All ...................................................
All ...................................................
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Sub Task 72–21–03–230–051
Sub Task 72–21–03–250–051
Current Inspection.
Sub Task 72–21–05–230–051
Sub Task 72–21–05–250–051
Sub Task 72–31–04–230–051
Sub Task 72–31–05–230–051
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Fluorescent-Penetrant Inspection, and
or 72–21–03–250–052 Disk Bore Eddy
Fluorescent Penetrant Inspection, and
Vent Hole Eddy Current Inspection.
Fluorescent Penetrant Inspection.
Fluorescent Penetrant Inspection.
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Federal Register / Vol. 73, No. 206 / Thursday, October 23, 2008 / Proposed Rules
Part nomenclature
Compressor
Spool.
Rotor,
Stage
Part No. (P/N)
63093
Inspect per engine manual inspection chapter
3–9
All ...................................................
Sub Task 72–31–06–230–051 Fluorescent Penetrant Inspection.
Compressor Rotor, Stage 10 Disk
(Pre SB 72–0150).
Compressor Rotor Spool/Shaft,
Stage 11–14 (Pre SB 72–0150).
Compressor Rotor Spool/Shaft,
Stage 10–14 (SB 72–0150).
Compressor Rotor No. 4 Bearing
Rotating Air Seal (CDP Rotating
Seal).
HPT Disk/Shaft, Stage 1 .................
All ...................................................
Sub Task 72–31–07–230–051 Fluorescent Penetrant Inspection.
All ...................................................
Sub Task 72–31–08–230–051 Fluorescent Penetrant Inspection.
All ...................................................
Sub Task 72–31–23–230–052 Fluorescent Penetrant Inspection.
All ...................................................
Sub Task 72–31–10–230–051 Fluorescent Penetrant Inspection.
All ...................................................
HPT Disk, Stage 2 ..........................
All ...................................................
LPT Rotor Shaft ..............................
LPT Disks, Stages 1–5 ...................
LPT Rotor Torque Cone .................
All ...................................................
All ...................................................
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.
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.
Sub Task 72–55–01–240–051 Magnetic Particle Inspect.
Sub Task 72–57–02–230–051 Fluorescent-Penetrant Inspect.
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
(R88DT, No Rim Bolt Holes).
All ...................................................
Sub Task 72–53–16–230–052 Fluorescent-Penetrant Inspect, and
All ...................................................
Sub Task 72–53–16–250–051 Disk Bore Area Eddy Current Inspection.
Sub Task 72–53–18–230–051 Fluorescent-Penetrant Inspect, and
** HPT Rotor Rotating Interstage
Seal (R88DT).
All ...................................................
Sub Task 72–53–18–250–051 Disk Bore Area Eddy Current Inspection.
Sub Task 72–53–17–230–056 Fluorescent-Penetrant Inspect, and
HPT Rotor Forward Outer Seal
(R88DT).
All ...................................................
Sub Task 72–53–17–250–051 Seal Bore Area Eddy Current.
Sub Task 72–53–21–230–051 Fluorescent-Penetrant Inspect, and
Disk, HPT Rotor, Stage 2 (R88DT,
No Rim Bolt Holes).
dwashington3 on PRODPC61 with PROPOSALS
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
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(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:
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(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.
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63094
Federal Register / Vol. 73, No. 206 / Thursday, October 23, 2008 / Proposed Rules
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
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2008–1115; Directorate
Identifier 2008–NM–134–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier
Model CL–600–2C10 (Regional Jet
Series 700, 701 & 702) Airplanes and
Model CL–600–2D24 (Regional Jet
Series 900) Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: We propose to adopt a new
airworthiness directive (AD) for the
products listed above. This proposed
AD results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
dwashington3 on PRODPC61 with PROPOSALS
Bombardier Aerospace has completed a
system safety review of the CL–600–2C10/
CL–600–SD24 aircraft fuel system against the
new fuel tank safety standards. * * *
The assessment showed that a single
failure due to chafing of fuel system wiring
with high power wiring at the centre fuel
tank front spar could result in overheating of
the fuel boost pump. The assessment also
showed that chafing of the high power wiring
with the centre fuel tank front spar structures
could result in overheating of the fuel tank
wall. Overheating of the fuel tank wall could
lead to hot surface ignition resulting in a fuel
tank explosion.
The proposed AD would require actions
that are intended to address the unsafe
condition described in the MCAI.
DATES: We must receive comments on
this proposed AD by November 24,
2008.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
VerDate Aug<31>2005
14:57 Oct 22, 2008
Jkt 217001
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
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 in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Rocco Viselli, Aerospace Engineer,
Airframe and Propulsion Branch,
ANE–171, FAA, New York Aircraft
Certification Office, 1600 Stewart
Avenue, Suite 410, Westbury, New York
11590; telephone (516) 228–7331; fax
(516) 794–5531.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2008–1115; Directorate Identifier
2008–NM–134–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
Discussion
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2008–24,
dated July 3, 2008 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Bombardier Aerospace has completed a
system safety review of the CL–600–2C10/
PO 00000
Frm 00011
Fmt 4702
Sfmt 4702
CL–600–2D24 aircraft fuel system against the
new fuel tank safety standards, introduced in
Chapter 525 of the Airworthiness Manual
through Notice of Proposed Amendment
(NPA) 2002–043. The identified noncompliances were assessed using Transport
Canada Policy Letter No. 525–001 to
determine if mandatory corrective action was
required.
The assessment showed that a single
failure due to chafing of fuel system wiring
with high power wiring at the centre fuel
tank front spar could result in overheating of
the fuel boost pump. The assessment also
showed that chafing of the high power wiring
with the centre fuel tank front spar structures
could result in overheating of the fuel tank
wall. Overheating of the fuel tank wall could
lead to hot surface ignition resulting in a fuel
tank explosion.
To correct the unsafe condition, this
directive mandates separation of the high
power wiring from the fuel system wiring at
the centre fuel tank front spar area and the
installation of additional clamping and
support for the high power wiring [i.e.,
modifying the routing and support of
electrical wires in the centre fuel tank front
spar area].
Required actions also include an
inspection to determine if pins have a
minimum of one thread above the nuts,
and a visual inspection for damage of
the sealant. Corrective actions include
replacing pins and nuts and applying
sealant. You may obtain further
information by examining the MCAI in
the AD docket.
The FAA has examined the
underlying safety issues involved in fuel
tank explosions on several large
transport airplanes, including the
adequacy of existing regulations, the
service history of airplanes subject to
those regulations, and existing
maintenance practices for fuel tank
systems. As a result of those findings,
we issued a regulation titled ‘‘Transport
Airplane Fuel Tank System Design
Review, Flammability Reduction and
Maintenance and Inspection
Requirements’’ (66 FR 23086, May 7,
2001). In addition to new airworthiness
standards for transport airplanes and
new maintenance requirements, this
rule included Special Federal Aviation
Regulation No. 88 (‘‘SFAR 88,’’
Amendment 21–78, and subsequent
Amendments 21–82 and 21–83).
Among other actions, SFAR 88
requires certain type design (i.e., type
certificate (TC) and supplemental type
certificate (STC)) holders to substantiate
that their fuel tank systems can prevent
ignition sources in the fuel tanks. This
requirement applies to type design
holders for large turbine-powered
transport airplanes and for subsequent
modifications to those airplanes. It
requires them to perform design reviews
and to develop design changes and
E:\FR\FM\23OCP1.SGM
23OCP1
]]>Agencies
[Federal Register Volume 73, Number 206 (Thursday, October 23, 2008)]
[Proposed Rules]
[Pages 63090-63094]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E8-25278]
=======================================================================
-----------------------------------------------------------------------
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 https://
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 https://
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 https://
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
