Airworthiness Directives; General Electric Company (GE) CF6-80C2 and CF6-80E1 Turbofan Engines, 49178-49182 [05-16454]
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49178
Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
TABLE 2.—MATERIAL INCORPORATED BY REFERENCE
Boeing service bulletin
Revision level
Date
747–25–3253, including Appendices A, B, and C .......................................................................................
747–25–3253 ................................................................................................................................................
757–25–0226, including Appendices A, B, and C .......................................................................................
757–25–0226 ................................................................................................................................................
757–25–0228, including Appendices A, B, and C .......................................................................................
757–25–0228 ................................................................................................................................................
767–25–0290, including Appendices A, B, and C .......................................................................................
767–25–0290 ................................................................................................................................................
777–25–0164, including Appendices A, B, and C .......................................................................................
777–25–0164, including Appendices A, B, C, and D ..................................................................................
Original .............
3 .......................
Original .............
3 .......................
Original .............
1 .......................
Original .............
4 .......................
Original .............
1 .......................
June 29, 2000.
September 4, 2003.
July 3, 2000.
September 2, 2004.
July 3, 2000.
March 28, 2002.
June 29, 2000.
October 28, 2004.
June 29, 2000.
March 22, 2001.
(1) The Director of the Federal Register
approves the incorporation by reference of
the documents listed in Table 3 of this AD
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 3.—NEW MATERIAL INCORPORATED BY REFERENCE
Boeing service bulletin
Revision level
747–25–3253 ................................................................................................................................................
757–25–0226 ................................................................................................................................................
757–25–0228 ................................................................................................................................................
767–25–0290 ................................................................................................................................................
777–25–0164, including Appendices A, B, C, and D ..................................................................................
(2) On February 2, 2001 (65 FR 82901,
December 29, 2000), the Director of the
Federal Register approved the incorporation
3
3
1
4
1
.......................
.......................
.......................
.......................
.......................
Date
September 4, 2003.
September 2, 2004.
March 28, 2002.
October 28, 2004.
March 22, 2001.
by reference of the documents listed in Table
4 of this AD.
TABLE 4.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Boeing service bulletin
747–25–3253,
757–25–0226,
757–25–0228,
767–25–0290,
777–25–0164,
including
including
including
including
including
Appendices
Appendices
Appendices
Appendices
Appendices
A,
A,
A,
A,
A,
B,
B,
B,
B,
B,
and
and
and
and
and
C
C
C
C
C
Revision level
.......................................................................................
.......................................................................................
.......................................................................................
.......................................................................................
.......................................................................................
(3) To get copies of the service information,
contact Boeing Commercial Airplanes, P.O.
Box 3707, Seattle, Washington 98124–2207.
To view the AD docket, go to the Docket
Management Facility, U.S. Department of
Transportation, 400 Seventh Street SW.,
room PL–401, Nassif Building, Washington,
DC. To review copies of the service
information, go to the National Archives and
Records Administration (NARA). For
information on the availability of this
material at the NARA, call (202) 741–6030,
or go to https://www.archives.gov/federalregister/cfr/ibr-locations.html.
DEPARTMENT OF TRANSPORTATION
Issued in Renton, Washington, on August
11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–16455 Filed 8–22–05; 8:45 am]
AGENCY:
BILLING CODE 4910–13–P
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Original
Original
Original
Original
Original
.............
.............
.............
.............
.............
Date
June 29, 2000.
July 3, 2000.
July 3, 2000.
June 29, 2000.
June 29, 2000.
[Docket No. FAA–2004–19144; Directorate
Identifier 2003–NE–18–AD; Amendment 39–
14226; AD 2005–17–05]
circumferential repair cuts, and to repair
or replace the spool shaft if you find
certain circumferential cuts. This AD
results from an updated stress analysis.
We are issuing this AD to prevent
failure of the HPCR stage 11–14 spool
shaft due to low-cycle fatigue that could
result in an uncontained engine failure.
RIN 2120–AA64
DATES:
Federal Aviation Administration
14 CFR Part 39
Airworthiness Directives; General
Electric Company (GE) CF6–80C2 and
CF6–80E1 Turbofan Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for certain
GE CF6–80C2 and CF6–80E1 turbofan
engines. This AD requires you to inspect
the high pressure compressor rotor
(HPCR) stage 11–14 spool shaft for
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This AD becomes effective
September 27, 2005. The Director of the
Federal Register approved the
incorporation by reference of certain
publications listed in the regulations as
of September 27, 2005.
You can get the service
information identified in this AD from
General Electric Company via Lockheed
Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio
45215, telephone (513) 672–8400, fax
(513) 672–8422.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
ADDRESSES:
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803; telephone (781) 238–7192; fax
(781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed airworthiness directive (AD).
The proposed AD applies to certain GE
CF6–80C2 and CF6–80E1 turbofan
engines. We published the proposed AD
in the Federal Register on September
22, 2004 (69 FR 56730). That action
proposed to require inspection of the
spool shaft for circumferential repair
cuts at the next piece-part level
exposure, but not to exceed a specific
service cap specified in this proposed
AD, and repair or replacement of certain
spool shafts.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
person at the Docket Management
System (DMS) Docket Office between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The
Docket Office (telephone (800) 647–
5227) is located on the plaza level of the
Department of Transportation Nassif
Building at the street address stated in
ADDRESSES. Comments will be available
in the AD docket shortly after the DMS
receives them.
Comments
We provided the public the
opportunity to participate in the
development of this AD. We have
considered the comments received.
Request To Add a Definition
One commenter requests that for
clarity, we add a definition for cyclessince-repair (CSR) to the AD. We agree
and have added a definition to the
compliance section. That definition
states that for the purposes of this AD,
CSR limit is the current cycles-sincenew (CSN) minus the CSN at the time
of the repair.
Request To Add Instructions
One commenter requests that for
clarity, we add instructions to the
compliance section if the CSR limit
cannot be determined from the engine
records. We agree and have added a
sentence to the compliance section.
That sentence states that if the CSR limit
cannot be determined from the engine
records, then CSN must be used.
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Request for Document or Procedure
References
One commenter requests that we add
document or procedure references such
as Repair Documents, Service Bulletin
numbers, and Shop Manual tasks for the
circumferential repairs, to help the
commenter determine affected spools.
We do not agree. The AD references the
applicable GE Service Bulletins, which
include the lists of affected parts by
serial number (SN). The AD is only
applicable to those parts. Additional
references are not needed to determine
if the operator has an affected part.
Request To Exclude Spools That
Previously Complied
One commenter requests that the AD
be modified to exclude spools that have
previously complied with GEAE Service
Bulletin (SB) No. CF6–80C2 S/B 72–
1052, Revision 01, dated February 5,
2004, or certain revisions of engine shop
manual (ESM) section 72–31–08 or ESM
section 72–00–31. We partially agree.
We agree that no further action is
required for spools that have already
complied with GEAE SB No. CF6–80C2
S/B 72–1052, Revision 01, dated
February 5, 2004. The AD clearly states
in paragraph (e) that the AD actions are
only required if the actions are not
already done.
We do not agree that accomplishment
of ESM section 72–31–08 or 72–00–31 is
equivalent to compliance with GEAE SB
No. CF6–80C2 S/B 72–1052, Revision
01, dated February 5, 2004. ESM section
72–31–08, Revision 60 or later does
contain the same repair procedure
(Repair 12) referenced in the
accomplishment instructions of the SB
and incorporated by reference in this
AD. Credit for repairs done before the
effective date of the AD using ESM
section 72–31–08, Revision 60 or later,
should be requested using the
alternative methods of compliance
procedure described in this AD.
However, ESM 72–00–31 does not
include the necessary repair
instructions. Therefore, we have not
changed the AD to incorporate this
comment.
Request To Add a Reference to List of
Affected SNs
One commenter requests that
Applicability paragraph (c) of the AD be
modified to include a reference to the
list of affected SNs of stage 11–14 spool
shafts in the manufacturer’s SBs. The
commenter states that this additional
information would clarify that the AD is
only intended to apply to those specific
spools and not the entire fleet. We
partially agree. We agree that
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49179
Applicability paragraph (c) would be
clearer if it states that the list of affected
SNs can be found in the referenced
service bulletins. We have added a
sentence to Applicability paragraph (c)
that states the affected stage 11–14 spool
shafts are identified by SN in the GE
service information described in
paragraphs (f) and (j) of this AD.
Request To Clarify Number of Affected
Stage 11–14 Spool Shafts
One commenter requests that the
number of affected stage 11–14 spool
shafts be clarified, as the number in
GEAE SB No. CF6–80C2 S/B 72–1052,
Revision 01, dated February 5, 2004,
and in the Supplementary Information
of the NPRM are not the same.
We do not agree. The statement the
commenter is referring to in the
Supplementary Information of the
NPRM states that GE reports that as
many as 135 CF6–80C2 and CF6–80E1
HPCR 11–14 spool shafts have had this
(circumferential cut) repair. This
quantity is the combined number of
affected spool shafts listed in not one,
but two SBs, which are the SB for CF6–
80C2 engines and the SB for CF6–80E1
engines. Since the issuance of the
NPRM, however, these SBs have been
revised to correct a few errors in the SN
lists of affected spool shafts. The revised
SBs referenced in this AD are GEAE SB
No. CF6–80C2 S/B 72–1052, Revision
02, dated May 25, 2005, and GEAE SB
No. CF6–80E1 S/B 72–0232, Revision
01, dated February 5, 2004. Therefore,
we have not changed the AD to address
this comment.
Request To Include List of Affected
Stage 11–14 Spool Shafts in AD
One commenter requests that we
include in the AD the list of affected
stage 11–14 spool shafts, instead of
referring readers to the SBs for the lists,
to avoid the potential for confusion. The
commenter also requests that we delete
the stage 11–14 spool shaft SN
MPOAP580 from the list of affected
spools in the AD, suggesting that only
stage 11 of spool shaft SN MPOAP580
was reworked, and so the proposed AD
is inapplicable to that spool.
We do not agree that referring readers
to the SBs for the lists is confusing. We
believe it would be confusing to
maintain lists of affected SNs in both
the AD and the SBs. We agree that the
AD doesn’t affect spools repaired on
stage 11. We also verified through the
manufacturer that spool SN MPOAP580
was repaired in only stage 11. This SN
spool shaft has been deleted from the
revised SBs.
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
Request To Clarify Paragraph (f)
One commenter requests that
compliance section paragraph (f) be
clarified by adding the words ‘‘not to
exceed the life limits specified in Table
2 in the column entitled Replace by
(CSR) Limit’’, to the end of the sentence.
We do not agree. Compliance section
paragraphs (f)(1) and (f)(2) already
include this necessary ‘‘not to exceed’’
information.
Request for Additional Cycles-inService
One commenter requests that up to
420 additional cycles-in-service (CIS) be
granted for those affected spools that
will have accumulated more cycles than
the ‘‘Repair By Limit’’ but are within
420 cycles of the ‘‘Replace By Limit’’ on
the effective date of the AD. The
commenter states that this would
provide margin for those operators
suffering heavy impact from this AD.
The commenter notes that paragraph (h)
of the proposed AD provides an
allowance of 420 CIS if an affected spool
has already accumulated more cycles
than the ‘‘Replace by Limit’’ on the
effective date of the AD. We agree, and
revised the compliance section based on
this request.
Request To Include a Note
The same commenter requests that a
note be included in the AD to specify
that execution of the Accomplishment
Instructions of GEAE SB No. CF6–80C2
S/B 72–1052, Revision 01, dated
February 5, 2004, is considered
terminating action for the AD. The
commenter is unclear whether or not
the SB is terminating action for the AD.
We do not agree. The AD requires that
spools either be repaired or replaced.
Once a spool has been repaired or
replaced, no further action is required.
Conclusion
We have carefully reviewed the
available data, including the comments
received, and determined that air safety
and the public interest require adopting
the AD with the changes described
previously. We have determined that
these changes will neither increase the
economic burden on any operator nor
increase the scope of the AD.
Costs of Compliance
There are approximately 173 GE CF6–
80C2 and CF6–80E1 turbofan engines of
the affected design in the worldwide
fleet. We estimate that 24 engines
installed on airplanes of U.S. registry
will be affected by this AD. We also
estimate that it will take about one work
hour per engine to inspect for the
location of previous circumferential cut
repairs and 5 work hours per engine to
repair the spool shaft. We estimate that
24 engines will be repaired and that
three spool shafts will be replaced. The
average labor rate is $65 per work hour.
Each replacement spool shaft will cost
approximately $447,400. Based on these
figures, we estimate the total cost of the
AD to U.S. operators to be $1,351,755.
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 AD will
not have federalism implications under
Executive Order 13132. This AD will
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 this AD:
(1) Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
(2) Is not a ‘‘significant rule’’ under
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
(3) Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this AD and placed it in
the AD Docket. You may get a copy of
this summary at the address listed
under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the Federal Aviation Administration
amends 14 CFR part 39 as follows:
I
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
I
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive:
I
2005–17–05 General Electric Company:
Amendment 39–14226. Docket No.
FAA–2004–19144; Directorate Identifier.
2003–NE–18–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective September 27, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain GE CF6–
80C2 and CF6–80E1 turbofan engines that
have a high pressure compressor rotor
(HPCR) stage 11–14 spool shaft with a part
number (P/N) listed in Table 1 of this AD and
that had a seal wire groove repaired using a
circumferential cut at a location specified in
Table 2 of this AD. The affected stage 11–14
spool shafts are identified by serial number
(SN) in the GE service information described
in paragraphs (f) and (j) of this AD. These
engines are installed on, but not limited to,
Airbus Industrie A300, A310, and A330
series airplanes and Boeing 747, 767, and
MD–11 series airplanes.
TABLE 1.—STAGE 11–14 SPOOL SHAFT P/NS BY ENGINE MODEL AND FORGING GROUP DESIGNATIONS
Engine model
CF6–80C2 ......................................
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Forging group
designations
Stage 11–14 Spool Shaft P/Ns
9380M30G07,
9380M30G08,
9380M30G09,
9380M30G10,
1509M71G02, 1509M71G03, 1509M71G04, and 1509M71G05.
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Group 1.
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
TABLE 1.—STAGE 11–14 SPOOL SHAFT P/NS BY ENGINE MODEL AND FORGING GROUP DESIGNATIONS—Continued
Forging group
designations
Engine model
Stage 11–14 Spool Shaft P/Ns
CF6–80C2 ......................................
1531M21G01,
1531M21G02,
1531M21G04,
1509M71G06,
1509M71G07,
1509M71G08, 1509M71G11, 1509M71G12, 1703M74G01, and 1703M74G03.
1509M71G11, 1509M71G12, 1509M71G13, 1644M99G03, 1703M74G01, and
1703M74G03.
CF6–80E1 ......................................
Unsafe Condition
(d) This AD results from an updated stress
analysis. We are issuing this AD to prevent
failure of the HPCR stage 11–14 spool shaft
due to low-cycle fatigue that could result in
an uncontained engine failure.
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.
CF6–80C2 Engines
(f) For CF6–80C2 series engines with HPCR
stage 11–14 spool shaft SNs listed in 1.A.(2)
of GE Aircraft Engines (GEAE) Service
Bulletin (SB) No. CF6–80C2 S/B 72–1052,
Revision 02, dated May 25, 2005, inspect the
spool shaft for the location of the
circumferential cut repair at the next piecepart exposure.
(1) If the stage and location of the repair
is specified in the engine records, inspect
prior to exceeding the cycles-since-repair
(CSR) limit specified in the column titled,
Replace By (CSR), in Table 2.
(2) For the purposes of this AD, CSR limit
is defined as the current cycles-since-new
(CSN) minus the CSN at the time of the
repair.
Group 2.
Not Applicable.
(3) If the CSR limit cannot be determined
from the engine records, then CSN must be
used.
(4) If the stage or location of the repair is
not known from the engine records, remove
the spool shaft for inspection before
exceeding 4,200 CSR for the Group 1 or
before exceeding 10,000 CSR for Group 2.
Use 3.A.(1) of the Accomplishment
Instructions of GEAE SB No. CF6–80C2 S/B
72–1052, Revision 02, dated May 25, 2005,
for the inspection. Table 2 follows:
TABLE 2.—REPAIR AND REPLACEMENT LIMITS FOR SPOOL SHAFTS BY FORGING GROUP AND LOCATION OF THE
CIRCUMFERENTIAL CUT REPAIR
Engine model
Forging group
(from Table 1)
(1) CF6–80C2 ....................
Group 1 ...........
(2) CF6–80C2 ....................
Stage
14
Group 1 ...........
13
(3) CF6–80C2 ....................
(4) CF6–80C2 ....................
Group 1 ...........
Group 2 ...........
12
14
(5) CF6–80C2 ....................
Group 2 ...........
13
(6) CF6–80C2 ....................
(7) CF6–80E1 .....................
Group 2 ...........
Not Applicable
12
14
(8) CF6–80E1 .....................
Not Applicable
13
(9) CF6–80E1 .....................
Not Applicable
12
(g) If you have a Group 2 spool shaft, and
the circumferential cut repair is in the Stage
14 forward location, and not in Area X, no
further action is required by this AD.
However, GEAE recommends that you repair
these spools at the next exposure of the spool
shaft.
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Repair by (CSR) limit
(i) Aft Seal Wire Groove Not in Area X ...
(ii) Aft Seal Wire Groove—In Area X .......
(iii) Forward Seal Wire Groove—Not in
Area X.
(iv) Forward Seal Wire Groove—In Area
X.
(i) Aft Seal Wire Groove—Not in Area X
(ii) Aft Seal Wire Groove—In Area X .......
(iii) Forward Seal Wire Groove—Not in
Area X.
(iv) Forward Seal Wire Groove—In Area
X.
Aft Seal Wire Groove—In Area X ............
(i) Aft Seal Wire Groove—Not in Area X
(ii) Aft Seal Wire Groove—In Area X .......
(iii) Forward Seal Wire Groove—In Area
X.
(i) Aft Seal Wire Groove—In Area X ........
(ii) Forward Seal Wire Groove—In Area
X.
Aft Seal Wire Groove—In Area X ............
(i) Aft Seal Wire Groove—Not in Area X
(ii) Aft Seal Wire Groove—In spool Area
X.
(iii) Forward Seal Wire Groove—In Area
X.
(i) Aft Seal Wire Groove—In Area X ........
(ii) Forward Seal Wire Groove—In Area
X.
Aft Seal Wire Groove—In Area X ............
3,600 ...........................
None—Replace spool
7,100 ...........................
4,200
4,200
7,100
None—Replace spool
7,100
7,100 ...........................
2,740 ...........................
7,100 ...........................
7,100
7,100
7,100
7,100 ...........................
7,100
7,100 ...........................
13,700 .........................
None—Replace spool
9,830 ...........................
7,100
13,700
13,700
10,000
9,830 ...........................
9,830 ...........................
10,000
10,000
9,830 ...........................
11,600 .........................
None—Replace spool
10,000
11,600
11,600
8,080 ...........................
11,600
8,080 ...........................
8,080 ...........................
11,600
11,600
8,080 ...........................
11,600
Replacement of the Spool Shaft
(h) After the effective date of this AD,
replace spool shafts as follows:
(1) If the spool shaft exceeds the CSR limit
in the column titled, Repair by (CSR), in
Table 2 of this AD, replace the spool shaft
within 420 cycles-in-service (CIS) or prior to
exceeding the CSR limit in the column titled,
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Replace by
(CSR) limit
Location of circumferential cut repair
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Replace by (CSR), in Table 2 of this AD,
whichever occurs later.
(2) If the spool shaft exceeds the CSR limit
in the column titled, Replace by (CSR), in
Table 2 of this AD, replace the spool shaft
within 420 CIS or within the published part
life limit, whichever occurs first.
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Repair of the Spool Shaft
(i) You may repair the spool if the CSR on
the spool shaft are fewer than or equal to the
limit in the column titled, Repair by (CSR),
in Table 2 of this AD. Use 3.B. of the
Accomplishment Instructions of GEAE SB
No. CF6–80C2 S/B 72–1052, Revision 02,
dated May 25, 2005, for the repair.
CF6–80E1 Engines
(j) For CF6–80E1 series engines with HPCR
stage 11–14 spool shafts with SNs listed in
1.A.(2) of GEAE SB No. CF6–80E1 S/B 72–
0232, Revision 01, dated February 5, 2004, do
the following:
(1) Inspect the spool shaft for the location
of the cut circumferential repair at the next
piece-part exposure, but before exceeding
11,600 CSR. Use 3.A.(1) of the
Accomplishment Instructions of GEAE SB
No. CF6–80E1 S/B 72–0232, Revision 01,
dated February 5, 2004 for the inspection.
(2) For the purposes of this AD, CSR limit
is defined as the current CSN minus the CSN
at the time of the repair.
(3) If the CSR limit cannot be determined
from the engine records, then CSN must be
used.
(4) If the circumferential cut repair is in the
Stage 14 forward location, and not in Area X,
no further action is required by this AD.
However, GEAE recommends that you repair
these spools at the next exposure of the spool
shaft.
Table 2 of this AD, replace the spool shaft
within 420 CIS or within the published part
life limit, whichever occurs first.
Repair of the Spool Shaft
(l) You may repair the spool shaft if the
CSR on the spool shaft are fewer than or
equal to the limit in the column titled, Repair
by (CSR), in Table 2 of this AD. Use 3.B. of
the Accomplishment Instructions of GEAE
SB CF6–80E1 S/B 72–0232, Revision 01,
dated February 5, 2004, for the repair.
Replacement of the Spool Shaft
(k) After the effective date of this AD,
replace spool shafts as follows:
(1) If the spool shaft exceeds the CSR limit
in the column titled, Repair by (CSR), in
Table 2 of this AD, replace the spool shaft
within 420 CIS or prior to exceeding the CSR
limit in the column titled, Replace by (CSR),
in Table 2 of this AD, whichever occurs later.
(2) If the spool shaft exceeds the CSR limit
in the column titled, Replace by (CSR), in
Alternative Methods of Compliance
(m) 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.
Material Incorporated by Reference
(n) You must use the service information
specified in Table 3 of this AD to perform the
actions required by this AD.
TABLE 3.—INCORPORATION BY REFERENCE
Service bulletin No.
Page
Revision
Date
CF6–80C2 S/B 72–1052 ........................................................................................................
ALL ...................
02
May 25, 2005.
ALL ...................
01
February 5, 2004.
Total Pages: 11
CF6–80E1 S/B 72–0232 ........................................................................................................
Total Pages: 9
The Director of the Federal Register
approved the incorporation by reference of
the documents listed in Table 3 of this AD
in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Contact General Electric Company
via Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati,
Ohio 45215, telephone (513) 672–8400, fax
(513) 672–8422, for a copy of this service
information. You may review copies at the
Docket Management Facility; U.S.
Department of Transportation, 400 Seventh
Street, SW., Nassif Building, Room PL–401,
Washington, DC 20590–0001, on the internet
at https://dms.dot.gov, or at the National
Archives and Records Administration
(NARA). For information on the availability
of this material at NARA, call 202–741–6030,
or go to: https://www.archives.gov/federalregister/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on
August 12, 2005.
Peter A. White,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–16454 Filed 8–22–05; 8:45 am]
BILLING CODE 4910–13–P
VerDate jul<14>2003
16:13 Aug 22, 2005
Jkt 205001
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2005–20849; Directorate
Identifier 2005–NE–04–AD; Amendment 39–
14227; AD 2005–17–06]
RIN 2120–AA64
Airworthiness Directives; Turbomeca
Artouste III Series Turboshaft Engines
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
SUMMARY: The FAA is adopting a new
airworthiness directive (AD) for
Turbomeca Artouste III series turboshaft
engines. This AD requires modification
of the engine air intake assembly. This
AD results from a report of an in-flight
shutdown and subsequent loss of
control of the helicopter due to ice
ingestion into the engine. We are issuing
this AD to prevent ice ingestion into the
engine, which could lead to an in-flight
shutdown and subsequent loss of
control of the helicopter.
DATES: This AD becomes effective
September 27, 2005. The Director of the
Federal Register approved the
incorporation by reference of certain
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
publications listed in the regulations as
of September 27, 2005.
ADDRESSES: Contact Turbomeca, 40220
Tarnos, France; telephone +33 05 59 74
40 00, fax +33 05 59 74 45 15, for the
service information identified in this
AD.
You may examine the AD docket on
the Internet at https://dms.dot.gov or in
Room PL–401 on the plaza level of the
Nassif Building, 400 Seventh Street,
SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Christopher Spinney, Aerospace
Engineer, Engine Certification Office,
FAA, Engine and Propeller Directorate,
12 New England Executive Park,
Burlington, MA 01803–5299; telephone
(781) 238–7175; fax (781) 238–7199.
SUPPLEMENTARY INFORMATION: The FAA
proposed to amend 14 CFR part 39 with
a proposed airworthiness directive (AD).
The proposed AD applies to Turbomeca
Artouste III series turboshaft engines.
We published the proposed AD in the
Federal Register on April 6, 2005 (70 FR
17368). That action proposed to require
adding two additional water drain holes
in the engine air intake assembly.
Examining the AD Docket
You may examine the docket that
contains the AD, any comments
received, and any final disposition in
E:\FR\FM\23AUR1.SGM
23AUR1
]]>Agencies
[Federal Register Volume 70, Number 162 (Tuesday, August 23, 2005)]
[Rules and Regulations]
[Pages 49178-49182]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16454]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-19144; Directorate Identifier 2003-NE-18-AD;
Amendment 39-14226; AD 2005-17-05]
RIN 2120-AA64
Airworthiness Directives; General Electric Company (GE) CF6-80C2
and CF6-80E1 Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for
certain GE CF6-80C2 and CF6-80E1 turbofan engines. This AD requires you
to inspect the high pressure compressor rotor (HPCR) stage 11-14 spool
shaft for circumferential repair cuts, and to repair or replace the
spool shaft if you find certain circumferential cuts. This AD results
from an updated stress analysis. We are issuing this AD to prevent
failure of the HPCR stage 11-14 spool shaft due to low-cycle fatigue
that could result in an uncontained engine failure.
DATES: This AD becomes effective September 27, 2005. The Director of
the Federal Register approved the incorporation by reference of certain
publications listed in the regulations as of September 27, 2005.
ADDRESSES: You can get the service information identified in this AD
from General Electric Company via Lockheed Martin Technology Services,
10525 Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513)
672-8400, fax (513) 672-8422.
You may examine the AD docket on the Internet at https://dms.dot.gov
or in Room PL-401 on the plaza level of the
[[Page 49179]]
Nassif Building, 400 Seventh Street, SW., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Karen Curtis, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803; telephone (781) 238-
7192; fax (781) 238-7199.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with a proposed airworthiness directive (AD). The proposed AD applies
to certain GE CF6-80C2 and CF6-80E1 turbofan engines. We published the
proposed AD in the Federal Register on September 22, 2004 (69 FR
56730). That action proposed to require inspection of the spool shaft
for circumferential repair cuts at the next piece-part level exposure,
but not to exceed a specific service cap specified in this proposed AD,
and repair or replacement of certain spool shafts.
Examining the AD Docket
You may examine the docket that contains the AD, any comments
received, and any final disposition in person at the Docket Management
System (DMS) Docket Office between 9 a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The Docket Office (telephone (800)
647-5227) is located on the plaza level of the Department of
Transportation Nassif Building at the street address stated in
ADDRESSES. Comments will be available in the AD docket shortly after
the DMS receives them.
Comments
We provided the public the opportunity to participate in the
development of this AD. We have considered the comments received.
Request To Add a Definition
One commenter requests that for clarity, we add a definition for
cycles-since-repair (CSR) to the AD. We agree and have added a
definition to the compliance section. That definition states that for
the purposes of this AD, CSR limit is the current cycles-since-new
(CSN) minus the CSN at the time of the repair.
Request To Add Instructions
One commenter requests that for clarity, we add instructions to the
compliance section if the CSR limit cannot be determined from the
engine records. We agree and have added a sentence to the compliance
section. That sentence states that if the CSR limit cannot be
determined from the engine records, then CSN must be used.
Request for Document or Procedure References
One commenter requests that we add document or procedure references
such as Repair Documents, Service Bulletin numbers, and Shop Manual
tasks for the circumferential repairs, to help the commenter determine
affected spools. We do not agree. The AD references the applicable GE
Service Bulletins, which include the lists of affected parts by serial
number (SN). The AD is only applicable to those parts. Additional
references are not needed to determine if the operator has an affected
part.
Request To Exclude Spools That Previously Complied
One commenter requests that the AD be modified to exclude spools
that have previously complied with GEAE Service Bulletin (SB) No. CF6-
80C2 S/B 72-1052, Revision 01, dated February 5, 2004, or certain
revisions of engine shop manual (ESM) section 72-31-08 or ESM section
72-00-31. We partially agree. We agree that no further action is
required for spools that have already complied with GEAE SB No. CF6-
80C2 S/B 72-1052, Revision 01, dated February 5, 2004. The AD clearly
states in paragraph (e) that the AD actions are only required if the
actions are not already done.
We do not agree that accomplishment of ESM section 72-31-08 or 72-
00-31 is equivalent to compliance with GEAE SB No. CF6-80C2 S/B 72-
1052, Revision 01, dated February 5, 2004. ESM section 72-31-08,
Revision 60 or later does contain the same repair procedure (Repair 12)
referenced in the accomplishment instructions of the SB and
incorporated by reference in this AD. Credit for repairs done before
the effective date of the AD using ESM section 72-31-08, Revision 60 or
later, should be requested using the alternative methods of compliance
procedure described in this AD. However, ESM 72-00-31 does not include
the necessary repair instructions. Therefore, we have not changed the
AD to incorporate this comment.
Request To Add a Reference to List of Affected SNs
One commenter requests that Applicability paragraph (c) of the AD
be modified to include a reference to the list of affected SNs of stage
11-14 spool shafts in the manufacturer's SBs. The commenter states that
this additional information would clarify that the AD is only intended
to apply to those specific spools and not the entire fleet. We
partially agree. We agree that Applicability paragraph (c) would be
clearer if it states that the list of affected SNs can be found in the
referenced service bulletins. We have added a sentence to Applicability
paragraph (c) that states the affected stage 11-14 spool shafts are
identified by SN in the GE service information described in paragraphs
(f) and (j) of this AD.
Request To Clarify Number of Affected Stage 11-14 Spool Shafts
One commenter requests that the number of affected stage 11-14
spool shafts be clarified, as the number in GEAE SB No. CF6-80C2 S/B
72-1052, Revision 01, dated February 5, 2004, and in the Supplementary
Information of the NPRM are not the same.
We do not agree. The statement the commenter is referring to in the
Supplementary Information of the NPRM states that GE reports that as
many as 135 CF6-80C2 and CF6-80E1 HPCR 11-14 spool shafts have had this
(circumferential cut) repair. This quantity is the combined number of
affected spool shafts listed in not one, but two SBs, which are the SB
for CF6-80C2 engines and the SB for CF6-80E1 engines. Since the
issuance of the NPRM, however, these SBs have been revised to correct a
few errors in the SN lists of affected spool shafts. The revised SBs
referenced in this AD are GEAE SB No. CF6-80C2 S/B 72-1052, Revision
02, dated May 25, 2005, and GEAE SB No. CF6-80E1 S/B 72-0232, Revision
01, dated February 5, 2004. Therefore, we have not changed the AD to
address this comment.
Request To Include List of Affected Stage 11-14 Spool Shafts in AD
One commenter requests that we include in the AD the list of
affected stage 11-14 spool shafts, instead of referring readers to the
SBs for the lists, to avoid the potential for confusion. The commenter
also requests that we delete the stage 11-14 spool shaft SN MPOAP580
from the list of affected spools in the AD, suggesting that only stage
11 of spool shaft SN MPOAP580 was reworked, and so the proposed AD is
inapplicable to that spool.
We do not agree that referring readers to the SBs for the lists is
confusing. We believe it would be confusing to maintain lists of
affected SNs in both the AD and the SBs. We agree that the AD doesn't
affect spools repaired on stage 11. We also verified through the
manufacturer that spool SN MPOAP580 was repaired in only stage 11. This
SN spool shaft has been deleted from the revised SBs.
[[Page 49180]]
Request To Clarify Paragraph (f)
One commenter requests that compliance section paragraph (f) be
clarified by adding the words ``not to exceed the life limits specified
in Table 2 in the column entitled Replace by (CSR) Limit'', to the end
of the sentence. We do not agree. Compliance section paragraphs (f)(1)
and (f)(2) already include this necessary ``not to exceed''
information.
Request for Additional Cycles-in-Service
One commenter requests that up to 420 additional cycles-in-service
(CIS) be granted for those affected spools that will have accumulated
more cycles than the ``Repair By Limit'' but are within 420 cycles of
the ``Replace By Limit'' on the effective date of the AD. The commenter
states that this would provide margin for those operators suffering
heavy impact from this AD. The commenter notes that paragraph (h) of
the proposed AD provides an allowance of 420 CIS if an affected spool
has already accumulated more cycles than the ``Replace by Limit'' on
the effective date of the AD. We agree, and revised the compliance
section based on this request.
Request To Include a Note
The same commenter requests that a note be included in the AD to
specify that execution of the Accomplishment Instructions of GEAE SB
No. CF6-80C2 S/B 72-1052, Revision 01, dated February 5, 2004, is
considered terminating action for the AD. The commenter is unclear
whether or not the SB is terminating action for the AD.
We do not agree. The AD requires that spools either be repaired or
replaced. Once a spool has been repaired or replaced, no further action
is required.
Conclusion
We have carefully reviewed the available data, including the
comments received, and determined that air safety and the public
interest require adopting the AD with the changes described previously.
We have determined that these changes will neither increase the
economic burden on any operator nor increase the scope of the AD.
Costs of Compliance
There are approximately 173 GE CF6-80C2 and CF6-80E1 turbofan
engines of the affected design in the worldwide fleet. We estimate that
24 engines installed on airplanes of U.S. registry will be affected by
this AD. We also estimate that it will take about one work hour per
engine to inspect for the location of previous circumferential cut
repairs and 5 work hours per engine to repair the spool shaft. We
estimate that 24 engines will be repaired and that three spool shafts
will be replaced. The average labor rate is $65 per work hour. Each
replacement spool shaft will cost approximately $447,400. Based on
these figures, we estimate the total cost of the AD to U.S. operators
to be $1,351,755.
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 AD will not have federalism
implications under Executive Order 13132. This AD will 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 this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a summary of the costs to comply with this AD and
placed it in the AD Docket. You may get a copy of this summary at the
address listed under ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the Federal Aviation Administration amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
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]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2005-17-05 General Electric Company: Amendment 39-14226. Docket No.
FAA-2004-19144; Directorate Identifier. 2003-NE-18-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective
September 27, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to certain GE CF6-80C2 and CF6-80E1 turbofan
engines that have a high pressure compressor rotor (HPCR) stage 11-
14 spool shaft with a part number (P/N) listed in Table 1 of this AD
and that had a seal wire groove repaired using a circumferential cut
at a location specified in Table 2 of this AD. The affected stage
11-14 spool shafts are identified by serial number (SN) in the GE
service information described in paragraphs (f) and (j) of this AD.
These engines are installed on, but not limited to, Airbus Industrie
A300, A310, and A330 series airplanes and Boeing 747, 767, and MD-11
series airplanes.
Table 1.--Stage 11-14 Spool Shaft P/Ns by Engine Model and Forging Group Designations
----------------------------------------------------------------------------------------------------------------
Engine model Stage 11-14 Spool Shaft P/Ns Forging group designations
----------------------------------------------------------------------------------------------------------------
CF6-80C2................................ 9380M30G07, 9380M30G08, 9380M30G09, Group 1.
9380M30G10, 9380M30G12, 1509M71G02,
1509M71G03, 1509M71G04, and
1509M71G05.
[[Page 49181]]
CF6-80C2................................ 1531M21G01, 1531M21G02, 1531M21G04, Group 2.
1509M71G06, 1509M71G07, 1509M71G08,
1509M71G11, 1509M71G12, 1703M74G01,
and 1703M74G03.
CF6-80E1................................ 1509M71G11, 1509M71G12, 1509M71G13, Not Applicable.
1644M99G03, 1703M74G01, and
1703M74G03.
----------------------------------------------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from an updated stress analysis. We are
issuing this AD to prevent failure of the HPCR stage 11-14 spool
shaft due to low-cycle fatigue that could result in an uncontained
engine failure.
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.
CF6-80C2 Engines
(f) For CF6-80C2 series engines with HPCR stage 11-14 spool
shaft SNs listed in 1.A.(2) of GE Aircraft Engines (GEAE) Service
Bulletin (SB) No. CF6-80C2 S/B 72-1052, Revision 02, dated May 25,
2005, inspect the spool shaft for the location of the
circumferential cut repair at the next piece-part exposure.
(1) If the stage and location of the repair is specified in the
engine records, inspect prior to exceeding the cycles-since-repair
(CSR) limit specified in the column titled, Replace By (CSR), in
Table 2.
(2) For the purposes of this AD, CSR limit is defined as the
current cycles-since-new (CSN) minus the CSN at the time of the
repair.
(3) If the CSR limit cannot be determined from the engine
records, then CSN must be used.
(4) If the stage or location of the repair is not known from the
engine records, remove the spool shaft for inspection before
exceeding 4,200 CSR for the Group 1 or before exceeding 10,000 CSR
for Group 2. Use 3.A.(1) of the Accomplishment Instructions of GEAE
SB No. CF6-80C2 S/B 72-1052, Revision 02, dated May 25, 2005, for
the inspection. Table 2 follows:
Table 2.--Repair and Replacement Limits for Spool Shafts by Forging Group and Location of the Circumferential Cut Repair
--------------------------------------------------------------------------------------------------------------------------------------------------------
Location of
Engine model Forging group (from Table Stage circumferential cut Repair by (CSR) limit Replace by
1) repair (CSR) limit
--------------------------------------------------------------------------------------------------------------------------------------------------------
(1) CF6-80C2........................ Group 1................... 14 (i) Aft Seal Wire 3,600.............................. 4,200
Groove Not in Area X.
(ii) Aft Seal Wire None--Replace spool................ 4,200
Groove--In Area X.
(iii) Forward Seal Wire 7,100.............................. 7,100
Groove--Not in Area X.
(iv) Forward Seal Wire None--Replace spool................ 7,100
Groove--In Area X.
(2) CF6-80C2........................ Group 1................... 13 (i) Aft Seal Wire 7,100.............................. 7,100
Groove--Not in Area X.
(ii) Aft Seal Wire 2,740.............................. 7,100
Groove--In Area X.
(iii) Forward Seal Wire 7,100.............................. 7,100
Groove--Not in Area X.
(iv) Forward Seal Wire 7,100.............................. 7,100
Groove--In Area X.
(3) CF6-80C2........................ Group 1................... 12 Aft Seal Wire Groove-- 7,100.............................. 7,100
In Area X.
(4) CF6-80C2........................ Group 2................... 14 (i) Aft Seal Wire 13,700............................. 13,700
Groove--Not in Area X.
(ii) Aft Seal Wire None--Replace spool................ 13,700
Groove--In Area X.
(iii) Forward Seal Wire 9,830.............................. 10,000
Groove--In Area X.
(5) CF6-80C2........................ Group 2................... 13 (i) Aft Seal Wire 9,830.............................. 10,000
Groove--In Area X.
(ii) Forward Seal Wire 9,830............................. 10,000
Groove--In Area X.
(6) CF6-80C2........................ Group 2................... 12 Aft Seal Wire Groove-- 9,830.............................. 10,000
In Area X.
(7) CF6-80E1........................ Not Applicable............ 14 (i) Aft Seal Wire 11,600............................. 11,600
Groove--Not in Area X.
(ii) Aft Seal Wire None--Replace spool................ 11,600
Groove--In spool Area
X.
(iii) Forward Seal Wire 8,080.............................. 11,600
Groove--In Area X.
(8) CF6-80E1........................ Not Applicable............ 13 (i) Aft Seal Wire 8,080.............................. 11,600
Groove--In Area X.
(ii) Forward Seal Wire 8,080.............................. 11,600
Groove--In Area X.
(9) CF6-80E1........................ Not Applicable............ 12 Aft Seal Wire Groove-- 8,080.............................. 11,600
In Area X.
--------------------------------------------------------------------------------------------------------------------------------------------------------
(g) If you have a Group 2 spool shaft, and the circumferential
cut repair is in the Stage 14 forward location, and not in Area X,
no further action is required by this AD. However, GEAE recommends
that you repair these spools at the next exposure of the spool
shaft.
Replacement of the Spool Shaft
(h) After the effective date of this AD, replace spool shafts as
follows:
(1) If the spool shaft exceeds the CSR limit in the column
titled, Repair by (CSR), in Table 2 of this AD, replace the spool
shaft within 420 cycles-in-service (CIS) or prior to exceeding the
CSR limit in the column titled, Replace by (CSR), in Table 2 of this
AD, whichever occurs later.
(2) If the spool shaft exceeds the CSR limit in the column
titled, Replace by (CSR), in Table 2 of this AD, replace the spool
shaft within 420 CIS or within the published part life limit,
whichever occurs first.
[[Page 49182]]
Repair of the Spool Shaft
(i) You may repair the spool if the CSR on the spool shaft are
fewer than or equal to the limit in the column titled, Repair by
(CSR), in Table 2 of this AD. Use 3.B. of the Accomplishment
Instructions of GEAE SB No. CF6-80C2 S/B 72-1052, Revision 02, dated
May 25, 2005, for the repair.
CF6-80E1 Engines
(j) For CF6-80E1 series engines with HPCR stage 11-14 spool
shafts with SNs listed in 1.A.(2) of GEAE SB No. CF6-80E1 S/B 72-
0232, Revision 01, dated February 5, 2004, do the following:
(1) Inspect the spool shaft for the location of the cut
circumferential repair at the next piece-part exposure, but before
exceeding 11,600 CSR. Use 3.A.(1) of the Accomplishment Instructions
of GEAE SB No. CF6-80E1 S/B 72-0232, Revision 01, dated February 5,
2004 for the inspection.
(2) For the purposes of this AD, CSR limit is defined as the
current CSN minus the CSN at the time of the repair.
(3) If the CSR limit cannot be determined from the engine
records, then CSN must be used.
(4) If the circumferential cut repair is in the Stage 14 forward
location, and not in Area X, no further action is required by this
AD. However, GEAE recommends that you repair these spools at the
next exposure of the spool shaft.
Replacement of the Spool Shaft
(k) After the effective date of this AD, replace spool shafts as
follows:
(1) If the spool shaft exceeds the CSR limit in the column
titled, Repair by (CSR), in Table 2 of this AD, replace the spool
shaft within 420 CIS or prior to exceeding the CSR limit in the
column titled, Replace by (CSR), in Table 2 of this AD, whichever
occurs later.
(2) If the spool shaft exceeds the CSR limit in the column
titled, Replace by (CSR), in Table 2 of this AD, replace the spool
shaft within 420 CIS or within the published part life limit,
whichever occurs first.
Repair of the Spool Shaft
(l) You may repair the spool shaft if the CSR on the spool shaft
are fewer than or equal to the limit in the column titled, Repair by
(CSR), in Table 2 of this AD. Use 3.B. of the Accomplishment
Instructions of GEAE SB CF6-80E1 S/B 72-0232, Revision 01, dated
February 5, 2004, for the repair.
Alternative Methods of Compliance
(m) 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.
Material Incorporated by Reference
(n) You must use the service information specified in Table 3 of
this AD to perform the actions required by this AD.
Table 3.--Incorporation by Reference
----------------------------------------------------------------------------------------------------------------
Service bulletin No. Page Revision Date
----------------------------------------------------------------------------------------------------------------
CF6-80C2 S/B 72-1052................. ALL......................... 02 May 25, 2005.
--------------------------------------
Total Pages: 11
----------------------------------------------------------------------------------------------------------------
CF6-80E1 S/B 72-0232................. ALL......................... 01 February 5, 2004.
Total Pages: 9
----------------------------------------------------------------------------------------------------------------
The Director of the Federal Register approved the incorporation
by reference of the documents listed in Table 3 of this AD in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact General
Electric Company via Lockheed Martin Technology Services, 10525
Chester Road, Suite C, Cincinnati, Ohio 45215, telephone (513) 672-
8400, fax (513) 672-8422, for a copy of this service information.
You may review copies at the Docket Management Facility; U.S.
Department of Transportation, 400 Seventh Street, SW., Nassif
Building, Room PL-401, Washington, DC 20590-0001, on the internet at
https://dms.dot.gov, or at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://
www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on August 12, 2005.
Peter A. White,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-16454 Filed 8-22-05; 8:45 am]
BILLING CODE 4910-13-P
