Source: https://fr.scribd.com/document/2840954/Rule-Airworthiness-directives-General-Electric-Co
Timestamp: 2019-07-21 06:32:25
Document Index: 591221504

Matched Legal Cases: ['art 51', 'art 39', 'art 39', 'art 39', 'art 39', 'ART 39', 'art 39', '§ 39', '§ 39', 'art 51', 'art 39', 'art 39']

Rule: Airworthiness directives: General Electric Co. | Federal Aviation Administration | Élaboration d'un décret
Rule: Airworthiness directives: General Electric Co., 49178-49182 [05-16454] Federal Aviation Administration
enregistrerEnregistrer Rule: Airworthiness directives: General Electric C... pour plus tard
Rule: Airworthiness directives: Empresa Brasileira de Aeronautica, S. A. (EMBRAER)
Proposed Rule: Airworthiness directives: SOCATA-Groupe AEROSPATIALE
Proposed Rule: Airworthiness Directives: Bombardier Model DHC-8-102, DHC-8-103, DHC-8-106, DHC-8-201, DHC-8-202, DHC-8-301, DHC-8-311, and DHC-8-315 Airplanes
Proposed Rule: Airworthiness directives: CTRM Aviation Sdn. Bhd.
Notice: Advisory circulars; availability, etc.: Airworthiness and safety; continued improvements; subpart I
49178 Federal Register / Vol. 70, No.
162 / Tuesday, August 23, 2005 / Rules and Regulations
Boeing service bulletin Revision level Date
747–25–3253, including Appendices A, B, and C ....................................................................................... Original ............. June 29, 2000.
747–25–3253 ................................................................................................................................................ 3 ....................... September 4, 2003.
757–25–0226, including Appendices A, B, and C ....................................................................................... Original ............. July 3, 2000.
757–25–0226 ................................................................................................................................................ 3 ....................... September 2, 2004.
757–25–0228, including Appendices A, B, and C ....................................................................................... Original ............. July 3, 2000.
757–25–0228 ................................................................................................................................................ 1 ....................... March 28, 2002.
767–25–0290, including Appendices A, B, and C ....................................................................................... Original ............. June 29, 2000.
767–25–0290 ................................................................................................................................................ 4 ....................... October 28, 2004.
777–25–0164, including Appendices A, B, and C ....................................................................................... Original ............. June 29, 2000.
777–25–0164, including Appendices A, B, C, and D .................................................................................. 1 ....................... March 22, 2001.
(1) The Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
approves the incorporation by reference of part 51.
the documents listed in Table 3 of this AD
(2) On February 2, 2001 (65 FR 82901, by reference of the documents listed in Table
December 29, 2000), the Director of the 4 of this AD.
Federal Register approved the incorporation
TABLE 4.—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
(3) To get copies of the service information, DEPARTMENT OF TRANSPORTATION circumferential repair cuts, and to repair
contact Boeing Commercial Airplanes, P.O. or replace the spool shaft if you find
Box 3707, Seattle, Washington 98124–2207. Federal Aviation Administration certain circumferential cuts. This AD
To view the AD docket, go to the Docket results from an updated stress analysis.
Management Facility, U.S. Department of 14 CFR Part 39 We are issuing this AD to prevent
Transportation, 400 Seventh Street SW., failure of the HPCR stage 11–14 spool
room PL–401, Nassif Building, Washington, [Docket No. FAA–2004–19144; Directorate
Identifier 2003–NE–18–AD; Amendment 39– shaft due to low-cycle fatigue that could
DC. To review copies of the service result in an uncontained engine failure.
14226; AD 2005–17–05]
Records Administration (NARA). For RIN 2120–AA64 DATES: This AD becomes effective
information on the availability of this September 27, 2005. The Director of the
material at the NARA, call (202) 741–6030, Airworthiness Directives; General Federal Register approved the
or go to http://www.archives.gov/federal- Electric Company (GE) CF6–80C2 and incorporation by reference of certain
register/cfr/ibr-locations.html. CF6–80E1 Turbofan Engines publications listed in the regulations as
of September 27, 2005.
Issued in Renton, Washington, on August AGENCY: Federal Aviation
11, 2005. Administration (FAA), Department of ADDRESSES: You can get the service
Kalene C. Yanamura, Transportation (DOT). information identified in this AD from
General Electric Company via Lockheed
Acting Manager, Transport Airplane ACTION: Final rule.
Martin Technology Services, 10525
Directorate, Aircraft Certification Service.
SUMMARY: The FAA is adopting a new Chester Road, Suite C, Cincinnati, Ohio
[FR Doc. 05–16455 Filed 8–22–05; 8:45 am]
airworthiness directive (AD) for certain 45215, telephone (513) 672–8400, fax
BILLING CODE 4910–13–P (513) 672–8422.
GE CF6–80C2 and CF6–80E1 turbofan
engines. This AD requires you to inspect You may examine the AD docket on
the high pressure compressor rotor the Internet at http://dms.dot.gov or in
(HPCR) stage 11–14 spool shaft for Room PL–401 on the plaza level of the
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 49179
Nassif Building, 400 Seventh Street, Request for Document or Procedure Applicability paragraph (c) would be
SW., Washington, DC. References clearer if it states that the list of affected
FOR FURTHER INFORMATION CONTACT: One commenter requests that we add SNs can be found in the referenced
Karen Curtis, Aerospace Engineer, document or procedure references such service bulletins. We have added a
Engine Certification Office, FAA, Engine as Repair Documents, Service Bulletin sentence to Applicability paragraph (c)
and Propeller Directorate, 12 New numbers, and Shop Manual tasks for the that states the affected stage 11–14 spool
England Executive Park, Burlington, MA circumferential repairs, to help the shafts are identified by SN in the GE
01803; telephone (781) 238–7192; fax commenter determine affected spools. service information described in
(781) 238–7199. We do not agree. The AD references the paragraphs (f) and (j) of this AD.
SUPPLEMENTARY INFORMATION: The FAA applicable GE Service Bulletins, which Request To Clarify Number of Affected
proposed to amend 14 CFR part 39 with include the lists of affected parts by Stage 11–14 Spool Shafts
a proposed airworthiness directive (AD). serial number (SN). The AD is only
The proposed AD applies to certain GE applicable to those parts. Additional One commenter requests that the
CF6–80C2 and CF6–80E1 turbofan references are not needed to determine number of affected stage 11–14 spool
engines. We published the proposed AD if the operator has an affected part. shafts be clarified, as the number in
in the Federal Register on September GEAE SB No. CF6–80C2 S/B 72–1052,
Request To Exclude Spools That Revision 01, dated February 5, 2004,
22, 2004 (69 FR 56730). That action Previously Complied
proposed to require inspection of the and in the Supplementary Information
spool shaft for circumferential repair One commenter requests that the AD of the NPRM are not the same.
cuts at the next piece-part level be modified to exclude spools that have We do not agree. The statement the
exposure, but not to exceed a specific previously complied with GEAE Service commenter is referring to in the
service cap specified in this proposed Bulletin (SB) No. CF6–80C2 S/B 72– Supplementary Information of the
AD, and repair or replacement of certain 1052, Revision 01, dated February 5, NPRM states that GE reports that as
spool shafts. 2004, or certain revisions of engine shop many as 135 CF6–80C2 and CF6–80E1
manual (ESM) section 72–31–08 or ESM HPCR 11–14 spool shafts have had this
Examining the AD Docket section 72–00–31. We partially agree. (circumferential cut) repair. This
You may examine the docket that We agree that no further action is quantity is the combined number of
contains the AD, any comments required for spools that have already affected spool shafts listed in not one,
received, and any final disposition in complied with GEAE SB No. CF6–80C2 but two SBs, which are the SB for CF6–
person at the Docket Management S/B 72–1052, Revision 01, dated 80C2 engines and the SB for CF6–80E1
System (DMS) Docket Office between 9 February 5, 2004. The AD clearly states engines. Since the issuance of the
a.m. and 5 p.m., Monday through in paragraph (e) that the AD actions are NPRM, however, these SBs have been
Friday, except Federal holidays. The only required if the actions are not revised to correct a few errors in the SN
Docket Office (telephone (800) 647– already done. lists of affected spool shafts. The revised
5227) is located on the plaza level of the We do not agree that accomplishment SBs referenced in this AD are GEAE SB
Department of Transportation Nassif of ESM section 72–31–08 or 72–00–31 is No. CF6–80C2 S/B 72–1052, Revision
Building at the street address stated in equivalent to compliance with GEAE SB 02, dated May 25, 2005, and GEAE SB
ADDRESSES. Comments will be available No. CF6–80C2 S/B 72–1052, Revision No. CF6–80E1 S/B 72–0232, Revision
in the AD docket shortly after the DMS 01, dated February 5, 2004. ESM section 01, dated February 5, 2004. Therefore,
receives them. 72–31–08, Revision 60 or later does we have not changed the AD to address
contain the same repair procedure this comment.
Comments (Repair 12) referenced in the
We provided the public the accomplishment instructions of the SB Request To Include List of Affected
opportunity to participate in the and incorporated by reference in this Stage 11–14 Spool Shafts in AD
development of this AD. We have AD. Credit for repairs done before the
effective date of the AD using ESM One commenter requests that we
considered the comments received.
section 72–31–08, Revision 60 or later, include in the AD the list of affected
Request To Add a Definition stage 11–14 spool shafts, instead of
should be requested using the
One commenter requests that for alternative methods of compliance referring readers to the SBs for the lists,
clarity, we add a definition for cycles- procedure described in this AD. to avoid the potential for confusion. The
since-repair (CSR) to the AD. We agree However, ESM 72–00–31 does not commenter also requests that we delete
and have added a definition to the include the necessary repair the stage 11–14 spool shaft SN
compliance section. That definition instructions. Therefore, we have not MPOAP580 from the list of affected
states that for the purposes of this AD, changed the AD to incorporate this spools in the AD, suggesting that only
CSR limit is the current cycles-since- comment. stage 11 of spool shaft SN MPOAP580
new (CSN) minus the CSN at the time was reworked, and so the proposed AD
Request To Add a Reference to List of is inapplicable to that spool.
Affected SNs We do not agree that referring readers
Request To Add Instructions One commenter requests that to the SBs for the lists is confusing. We
One commenter requests that for Applicability paragraph (c) of the AD be believe it would be confusing to
clarity, we add instructions to the modified to include a reference to the maintain lists of affected SNs in both
compliance section if the CSR limit list of affected SNs of stage 11–14 spool the AD and the SBs. We agree that the
cannot be determined from the engine shafts in the manufacturer’s SBs. The AD doesn’t affect spools repaired on
records. We agree and have added a commenter states that this additional stage 11. We also verified through the
sentence to the compliance section. information would clarify that the AD is manufacturer that spool SN MPOAP580
That sentence states that if the CSR limit only intended to apply to those specific was repaired in only stage 11. This SN
cannot be determined from the engine spools and not the entire fleet. We spool shaft has been deleted from the
records, then CSN must be used. partially agree. We agree that revised SBs.
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49180 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
Request To Clarify Paragraph (f) the affected design in the worldwide under the criteria of the Regulatory
One commenter requests that fleet. We estimate that 24 engines Flexibility Act.
compliance section paragraph (f) be installed on airplanes of U.S. registry We prepared a summary of the costs
clarified by adding the words ‘‘not to will be affected by this AD. We also to comply with this AD and placed it in
exceed the life limits specified in Table estimate that it will take about one work
the AD Docket. You may get a copy of
2 in the column entitled Replace by hour per engine to inspect for the
this summary at the address listed
(CSR) Limit’’, to the end of the sentence. location of previous circumferential cut
repairs and 5 work hours per engine to under ADDRESSES.
We do not agree. Compliance section
paragraphs (f)(1) and (f)(2) already repair the spool shaft. We estimate that List of Subjects in 14 CFR Part 39
include this necessary ‘‘not to exceed’’ 24 engines will be repaired and that
information. three spool shafts will be replaced. The Air transportation, Aircraft, Aviation
average labor rate is $65 per work hour. safety, Incorporation by reference,
Request for Additional Cycles-in- Each replacement spool shaft will cost Safety.
Service approximately $447,400. Based on these
figures, we estimate the total cost of the Adoption of the Amendment
One commenter requests that up to
420 additional cycles-in-service (CIS) be AD to U.S. operators to be $1,351,755.
■ Accordingly, under the authority
granted for those affected spools that Authority for This Rulemaking delegated to me by the Administrator,
will have accumulated more cycles than
Title 49 of the United States Code the Federal Aviation Administration
the ‘‘Repair By Limit’’ but are within
420 cycles of the ‘‘Replace By Limit’’ on specifies the FAA’s authority to issue amends 14 CFR part 39 as follows:
the effective date of the AD. The rules on aviation safety. Subtitle I,
Section 106, describes the authority of PART 39—AIRWORTHINESS
commenter states that this would
the FAA Administrator. Subtitle VII, DIRECTIVES
provide margin for those operators
suffering heavy impact from this AD. Aviation Programs, describes in more
detail the scope of the Agency’s ■ 1. The authority citation for part 39
The commenter notes that paragraph (h)
authority. continues to read as follows:
of the proposed AD provides an
allowance of 420 CIS if an affected spool We are issuing this rulemaking under Authority: 49 U.S.C. 106(g), 40113, 44701.
has already accumulated more cycles the authority described in subtitle VII,
than the ‘‘Replace by Limit’’ on the part A, subpart III, section 44701, § 39.13 [Amended]
effective date of the AD. We agree, and ‘‘General requirements.’’ Under that
section, Congress charges the FAA with ■ 2. The FAA amends § 39.13 by adding
revised the compliance section based on the following new airworthiness
this request. promoting safe flight of civil aircraft in
air commerce by prescribing regulations directive:
Request To Include a Note for practices, methods, and procedures 2005–17–05 General Electric Company:
The same commenter requests that a the Administrator finds necessary for Amendment 39–14226. Docket No.
note be included in the AD to specify safety in air commerce. This regulation FAA–2004–19144; Directorate Identifier.
that execution of the Accomplishment is within the scope of that authority 2003–NE–18–AD.
Instructions of GEAE SB No. CF6–80C2 because it addresses an unsafe condition
S/B 72–1052, Revision 01, dated that is likely to exist or develop on
February 5, 2004, is considered products identified in this rulemaking (a) This airworthiness directive (AD)
terminating action for the AD. The action. becomes effective September 27, 2005.
commenter is unclear whether or not Regulatory Findings Affected ADs
the SB is terminating action for the AD.
We have determined that this AD will (b) None.
We do not agree. The AD requires that
spools either be repaired or replaced. not have federalism implications under Applicability
Once a spool has been repaired or Executive Order 13132. This AD will
(c) This AD applies to certain GE CF6–
replaced, no further action is required. not have a substantial direct effect on
80C2 and CF6–80E1 turbofan engines that
Conclusion have a high pressure compressor rotor
the national government and the States, (HPCR) stage 11–14 spool shaft with a part
We have carefully reviewed the or on the distribution of power and number (P/N) listed in Table 1 of this AD and
available data, including the comments responsibilities among the various that had a seal wire groove repaired using a
received, and determined that air safety levels of government. circumferential cut at a location specified in
and the public interest require adopting For the reasons discussed above, I Table 2 of this AD. The affected stage 11–14
the AD with the changes described certify that this AD: spool shafts are identified by serial number
previously. We have determined that (1) Is not a ‘‘significant regulatory
(SN) in the GE service information described
these changes will neither increase the action’’ under Executive Order 12866;
in paragraphs (f) and (j) of this AD. These
economic burden on any operator nor (2) Is not a ‘‘significant rule’’ under
engines are installed on, but not limited to,
increase the scope of the AD. DOT Regulatory Policies and Procedures
Airbus Industrie A300, A310, and A330
Costs of Compliance series airplanes and Boeing 747, 767, and
(3) Will not have a significant
MD–11 series airplanes.
There are approximately 173 GE CF6– economic impact, positive or negative,
80C2 and CF6–80E1 turbofan engines of on a substantial number of small entities
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 designations
CF6–80C2 ...................................... 9380M30G07, 9380M30G08, 9380M30G09, 9380M30G10, 9380M30G12, Group 1.
1509M71G02, 1509M71G03, 1509M71G04, and 1509M71G05.
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations 49181
TABLE 1.—STAGE 11–14 SPOOL SHAFT P/NS BY ENGINE MODEL AND FORGING GROUP DESIGNATIONS—Continued
CF6–80C2 ...................................... 1531M21G01, 1531M21G02, 1531M21G04, 1509M71G06, 1509M71G07, Group 2.
1509M71G08, 1509M71G11, 1509M71G12, 1703M74G01, and 1703M74G03.
CF6–80E1 ...................................... 1509M71G11, 1509M71G12, 1509M71G13, 1644M99G03, 1703M74G01, and Not Applicable.
1703M74G03.
Unsafe Condition of GE Aircraft Engines (GEAE) Service (3) If the CSR limit cannot be determined
(d) This AD results from an updated stress Bulletin (SB) No. CF6–80C2 S/B 72–1052, from the engine records, then CSN must be
analysis. We are issuing this AD to prevent Revision 02, dated May 25, 2005, inspect the used.
failure of the HPCR stage 11–14 spool shaft spool shaft for the location of the (4) If the stage or location of the repair is
due to low-cycle fatigue that could result in circumferential cut repair at the next piece- not known from the engine records, remove
an uncontained engine failure. part exposure. the spool shaft for inspection before
Compliance (1) If the stage and location of the repair exceeding 4,200 CSR for the Group 1 or
is specified in the engine records, inspect before exceeding 10,000 CSR for Group 2.
prior to exceeding the cycles-since-repair Use 3.A.(1) of the Accomplishment
(CSR) limit specified in the column titled, Instructions of GEAE SB No. CF6–80C2 S/B
the compliance times specified unless the
actions have already been done. Replace By (CSR), in Table 2. 72–1052, Revision 02, dated May 25, 2005,
(2) For the purposes of this AD, CSR limit for the inspection. Table 2 follows:
CF6–80C2 Engines is defined as the current cycles-since-new
(f) For CF6–80C2 series engines with HPCR (CSN) minus the CSN at the time of the
stage 11–14 spool shaft SNs listed in 1.A.(2) repair.
TABLE 2.—REPAIR AND REPLACEMENT LIMITS FOR SPOOL SHAFTS BY FORGING GROUP AND LOCATION OF THE
CIRCUMFERENTIAL CUT REPAIR
Forging group Replace by
Engine model Stage Location of circumferential cut repair Repair by (CSR) limit
(from Table 1) (CSR) limit
(1) CF6–80C2 .................... Group 1 ........... 14 (i) Aft Seal Wire Groove Not in Area X ... 3,600 ........................... 4,200
(ii) Aft Seal Wire Groove—In Area X ....... None—Replace spool 4,200
(iii) Forward Seal Wire Groove—Not in 7,100 ........................... 7,100
(iv) Forward Seal Wire Groove—In Area None—Replace spool 7,100
(2) CF6–80C2 .................... Group 1 ........... 13 (i) Aft Seal Wire Groove—Not in Area X 7,100 ........................... 7,100
(ii) Aft Seal Wire Groove—In Area X ....... 2,740 ........................... 7,100
(iv) Forward Seal Wire Groove—In Area 7,100 ........................... 7,100
(3) CF6–80C2 .................... Group 1 ........... 12 Aft Seal Wire Groove—In Area X ............ 7,100 ........................... 7,100
(4) CF6–80C2 .................... Group 2 ........... 14 (i) Aft Seal Wire Groove—Not in Area X 13,700 ......................... 13,700
(ii) Aft Seal Wire Groove—In Area X ....... None—Replace spool 13,700
(iii) Forward Seal Wire Groove—In Area 9,830 ........................... 10,000
(5) CF6–80C2 .................... Group 2 ........... 13 (i) Aft Seal Wire Groove—In Area X ........ 9,830 ........................... 10,000
(ii) Forward Seal Wire Groove—In Area 9,830 ........................... 10,000
(6) CF6–80C2 .................... Group 2 ........... 12 Aft Seal Wire Groove—In Area X ............ 9,830 ........................... 10,000
(7) CF6–80E1 ..................... Not Applicable 14 (i) Aft Seal Wire Groove—Not in Area X 11,600 ......................... 11,600
(ii) Aft Seal Wire Groove—In spool Area None—Replace spool 11,600
(iii) Forward Seal Wire Groove—In Area 8,080 ........................... 11,600
(8) CF6–80E1 ..................... Not Applicable 13 (i) Aft Seal Wire Groove—In Area X ........ 8,080 ........................... 11,600
(ii) Forward Seal Wire Groove—In Area 8,080 ........................... 11,600
(9) CF6–80E1 ..................... Not Applicable 12 Aft Seal Wire Groove—In Area X ............ 8,080 ........................... 11,600
(g) If you have a Group 2 spool shaft, and Replacement of the Spool Shaft Replace by (CSR), in Table 2 of this AD,
the circumferential cut repair is in the Stage (h) After the effective date of this AD, whichever occurs later.
14 forward location, and not in Area X, no replace spool shafts as follows: (2) If the spool shaft exceeds the CSR limit
further action is required by this AD. (1) If the spool shaft exceeds the CSR limit in the column titled, Replace by (CSR), in
However, GEAE recommends that you repair in the column titled, Repair by (CSR), in Table 2 of this AD, replace the spool shaft
these spools at the next exposure of the spool Table 2 of this AD, replace the spool shaft within 420 CIS or within the published part
shaft. within 420 cycles-in-service (CIS) or prior to life limit, whichever occurs first.
exceeding the CSR limit in the column titled,
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49182 Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Rules and Regulations
Repair of the Spool Shaft (2) For the purposes of this AD, CSR limit Table 2 of this AD, replace the spool shaft
(i) You may repair the spool if the CSR on is defined as the current CSN minus the CSN within 420 CIS or within the published part
at the time of the repair. life limit, whichever occurs first.
the spool shaft are fewer than or equal to the
(3) If the CSR limit cannot be determined
limit in the column titled, Repair by (CSR), from the engine records, then CSN must be Repair of the Spool Shaft
in Table 2 of this AD. Use 3.B. of the used. (l) You may repair the spool shaft if the
Accomplishment Instructions of GEAE SB (4) If the circumferential cut repair is in the CSR on the spool shaft are fewer than or
No. CF6–80C2 S/B 72–1052, Revision 02, Stage 14 forward location, and not in Area X, equal to the limit in the column titled, Repair
dated May 25, 2005, for the repair. no further action is required by this AD. by (CSR), in Table 2 of this AD. Use 3.B. of
However, GEAE recommends that you repair the Accomplishment Instructions of GEAE
CF6–80E1 Engines these spools at the next exposure of the spool SB CF6–80E1 S/B 72–0232, Revision 01,
(j) For CF6–80E1 series engines with HPCR shaft. dated February 5, 2004, for the repair.
stage 11–14 spool shafts with SNs listed in Replacement of the Spool Shaft Alternative Methods of Compliance
1.A.(2) of GEAE SB No. CF6–80E1 S/B 72–
0232, Revision 01, dated February 5, 2004, do (k) After the effective date of this AD, (m) The Manager, Engine Certification
replace spool shafts as follows: Office, has the authority to approve
(1) If the spool shaft exceeds the CSR limit alternative methods of compliance for this
(1) Inspect the spool shaft for the location
in the column titled, Repair by (CSR), in AD if requested using the procedures found
of the cut circumferential repair at the next Table 2 of this AD, replace the spool shaft in 14 CFR 39.19.
piece-part exposure, but before exceeding within 420 CIS or prior to exceeding the CSR
11,600 CSR. Use 3.A.(1) of the limit in the column titled, Replace by (CSR), Material Incorporated by Reference
Accomplishment Instructions of GEAE SB in Table 2 of this AD, whichever occurs later. (n) You must use the service information
No. CF6–80E1 S/B 72–0232, Revision 01, (2) If the spool shaft exceeds the CSR limit specified in Table 3 of this AD to perform the
dated February 5, 2004 for the inspection. in the column titled, Replace by (CSR), in actions required by this AD.
Service bulletin No. Page Revision Date
CF6–80C2 S/B 72–1052 ........................................................................................................ ALL ................... 02 May 25, 2005.
CF6–80E1 S/B 72–0232 ........................................................................................................ ALL ................... 01 February 5, 2004.
The Director of the Federal Register DEPARTMENT OF TRANSPORTATION publications listed in the regulations as
approved the incorporation by reference of of September 27, 2005.
the documents listed in Table 3 of this AD Federal Aviation Administration ADDRESSES: Contact Turbomeca, 40220
in accordance with 5 U.S.C. 552(a) and 1 CFR Tarnos, France; telephone +33 05 59 74
part 51. Contact General Electric Company 14 CFR Part 39 40 00, fax +33 05 59 74 45 15, for the
via Lockheed Martin Technology Services,
[Docket No. FAA–2005–20849; Directorate service information identified in this
10525 Chester Road, Suite C, Cincinnati, Identifier 2005–NE–04–AD; Amendment 39– AD.
Ohio 45215, telephone (513) 672–8400, fax 14227; AD 2005–17–06] You may examine the AD docket on
(513) 672–8422, for a copy of this service
information. You may review copies at the RIN 2120–AA64 the Internet at http://dms.dot.gov or in
Docket Management Facility; U.S.
Room PL–401 on the plaza level of the
Department of Transportation, 400 Seventh Airworthiness Directives; Turbomeca Nassif Building, 400 Seventh Street,
Street, SW., Nassif Building, Room PL–401, Artouste III Series Turboshaft Engines SW., Washington, DC.
Washington, DC 20590–0001, on the internet AGENCY: Federal Aviation FOR FURTHER INFORMATION CONTACT:
at http://dms.dot.gov, or at the National Administration (FAA), Department of Christopher Spinney, Aerospace
Archives and Records Administration Transportation (DOT). Engineer, Engine Certification Office,
(NARA). For information on the availability ACTION: Final rule.
FAA, Engine and Propeller Directorate,
of this material at NARA, call 202–741–6030, 12 New England Executive Park,
or go to: http://www.archives.gov/federal- SUMMARY: The FAA is adopting a new Burlington, MA 01803–5299; telephone
register/cfr/ibr-locations.html. airworthiness directive (AD) for (781) 238–7175; fax (781) 238–7199.
Issued in Burlington, Massachusetts, on Turbomeca Artouste III series turboshaft SUPPLEMENTARY INFORMATION: The FAA
August 12, 2005. engines. This AD requires modification proposed to amend 14 CFR part 39 with
of the engine air intake assembly. This a proposed airworthiness directive (AD).
AD results from a report of an in-flight The proposed AD applies to Turbomeca
Acting Manager, Engine and Propeller shutdown and subsequent loss of
Artouste III series turboshaft engines.
control of the helicopter due to ice We published the proposed AD in the
[FR Doc. 05–16454 Filed 8–22–05; 8:45 am] ingestion into the engine. We are issuing Federal Register on April 6, 2005 (70 FR
BILLING CODE 4910–13–P this AD to prevent ice ingestion into the 17368). That action proposed to require
engine, which could lead to an in-flight adding two additional water drain holes
shutdown and subsequent loss of in the engine air intake assembly.
DATES: This AD becomes effective
September 27, 2005. The Director of the You may examine the docket that
Federal Register approved the contains the AD, any comments
incorporation by reference of certain received, and any final disposition in
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