Airworthiness Directives; General Electric Company CF34 Series Turbofan Engines, 49215-49217 [05-16709]
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA 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.
§ 39.13
[Amended]
2. The Federal Aviation
Administration (FAA) amends § 39.13
by adding the following new
airworthiness directive (AD):
Airbus: Docket No. FAA–2005–22170;
Directorate Identifier 2005–NM–073–AD.
Comments Due Date
(a) The FAA must receive comments on
this AD action by September 22, 2005.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A320–
111, –211, –212, and –231 airplanes,
certificated in any category, that have not
received Airbus Modification 21088 or 21999
in production; and airplanes that have
received Airbus Modification 21088 in
production and have manufacturer’s serial
number 91 to 113 inclusive and 140 to 189
inclusive.
Unsafe Condition
(d) This AD results from fuel systems
reviews conducted by the manufacturer. We
are issuing this AD to prevent chafing of the
fuel pump cables, which could result in
electrical arcing and possible ignition of fuel
vapors and consequent explosion of the fuel
tank.
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.
Inspection and Modification of Fuel Pump
Access Holes
(f) Within 58 months after the effective
date of this AD, perform the actions required
by paragraph (f)(1) or (f)(2) of this AD, as
applicable.
(1) For airplanes that have not received
Airbus Modification 21088 or 21999 in
production: Modify the cables and access
holes to the inner tank fuel pumps, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
28–1008, Revision 1, dated April 10, 1989.
(2) For airplanes that have received Airbus
Modification 21088 in production and have
manufacturer’s serial number 91 to 113
VerDate jul<14>2003
16:15 Aug 22, 2005
Jkt 205001
inclusive and 140 to 189 inclusive: Perform
a general visual inspection for the correct
radius of the fuel pump access holes and
modify the access holes, if necessary, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
28–1054, dated August 23, 1993. Do any
applicable repairs before further flight.
Note 1: For the purposes of this AD, a
general visual inspection is: ‘‘A visual
examination of an interior or exterior area,
installation, or assembly to detect obvious
damage, failure, or irregularity. This level of
inspection is made from within touching
distance unless otherwise specified. A mirror
may be necessary to ensure visual access to
all surfaces in the inspection area. This level
of inspection is made under normally
available lighting conditions such as
daylight, hangar lighting, flashlight, or
droplight and may require removal or
opening of access panels or doors. Stands,
ladders, or platforms may be required to gain
proximity to the area being checked.’’
No Reporting Requirement
(g) Although Airbus Service Bulletin
A320–28–1054, dated August 23, 1993,
describes procedures for reporting inspection
findings to Airbus, this AD does not require
such a report.
Alternative Methods of Compliance
(AMOCs)
(h) The Manager, International Branch,
ANM–116, Transport Airplane Directorate,
FAA, has the authority to approve AMOCs
for this AD, if requested in accordance with
the procedures found in 14 CFR 39.19.
Related Information
(i) French airworthiness directive F–2005–
031, dated February 16, 2005, also addresses
the subject of this AD.
Issued in Renton, Washington, on August
11, 2005.
Kalene C. Yanamura,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 05–16753 Filed 8–22–05; 8:45 am]
BILLING CODE 4910–13–U
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000–NE–42–AD]
RIN 2120–AA64
Airworthiness Directives; General
Electric Company CF34 Series
Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
SUMMARY: The FAA proposes to
supersede an existing airworthiness
PO 00000
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Sfmt 4702
49215
directive (AD) for General Electric
Company (GE) CF34–1A, –3A, –3A1,
–3A2, –3B, and –3B1 turbofan engines.
That AD currently requires a onetime
inspection, and if necessary replacing
certain fan disks for electrical arc-out
indications. That AD also reduces the
life limit of certain fan disks. This
proposed AD would require the same
actions and adds one disk part number
(P/N) and serial number (SN) to the
affected fan disks. This proposed AD
results from an error in the first part
number and serial number listed in
Table 1 of the original AD. We are
proposing this AD to prevent rupture of
the fan disk due to cracks that initiate
at an electrical arc-out, which could
result in an uncontained failure of the
engine.
DATES: We must receive any comments
on this proposed AD by October 24,
2005.
ADDRESSES: Use one of the following
addresses to comment on this proposed
AD:
• By mail: Federal Aviation
Administration (FAA), New England
Region, Office of the Regional Counsel,
Attention: Rules Docket No. 2000–NE–
42–AD, 12 New England Executive Park,
Burlington, MA 01803–5299.
• By fax: (781) 238–7055.
• By e-mail: 9-aneadcomment@faa.gov.
You can get the service information
identified in this proposed AD from GE
Aircraft Engines, 1000 Western Avenue,
Lynn, MA 01910; Attention: CF34
Product Support Engineering, Mail
Zone: 34017; telephone (781) 594–6323;
fax (781) 594–0600.
You may examine the AD docket at
the FAA, New England Region, Office of
the Regional Counsel, 12 New England
Executive Park, Burlington, MA.
FOR FURTHER INFORMATION CONTACT:
Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine
and Propeller Directorate, 12 New
England Executive Park, Burlington, MA
01803–5299; telephone 781–238–7148;
fax 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 ‘‘AD Docket No.
2000–NE–42–AD’’ in the subject line of
your comments. If you want us to
acknowledge receipt of your mailed
comments, send us a self-addressed,
stamped postcard with the docket
number written on it; we will datestamp your postcard and mail it back to
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules
you. We specifically invite comments
on the overall regulatory, economic,
environmental, and energy aspects of
the proposed AD. If a person contacts us
verbally, and that contact relates to a
substantive part of this proposed AD,
we will summarize the contact and
place the summary in the docket. We
will consider all comments received by
the closing date and may amend the
proposed AD in light of those
comments.
Examining the AD Docket
You may examine the AD Docket
(including any comments and service
information), by appointment, between
8 a.m. and 4:30 p.m., Monday through
Friday, except Federal holidays. See
ADDRESSES for the location.
Discussion
On May 7, 2001, the FAA issued AD
2001–10–13, Amendment 39–12229 (66
FR 27017, May 16, 2001). That AD
requires a onetime inspection, and if
necessary replacing certain fan disks for
electrical arc-out indications. That AD
also reduces the life limit of certain fan
disks. That AD resulted from a report of
a crack that was found during a visual
inspection as part of routine engine
maintenance. That condition, if not
corrected, could result in rupture of the
fan disk due to cracks that initiate at an
electrical arc-out, which could result in
an uncontained failure of the engine.
Actions Since AD 2001–10–13 Was
Issued
Since we issued that AD, we
discovered that the first fan disk part
number and the first fan disk serial
number listed in Table 1, Fan Disks that
Require Removal Based on Blended
Callouts are incorrect. This proposed
AD would correct those numbers. In all
other respects, the proposed AD remains
the same as AD 2001–10–03.
Relevant Service Information
We have reviewed and approved the
technical contents of GE Aircraft
Engines (GEAE) Alert Service Bulletin
(ASB) CF34–BJ 72–A0088, Revision 1,
dated October 30, 2000; and ASB CF34–
AL 72–A0103, dated August 4, 2000.
These ASB’s provide procedures for
inspections of certain disks for electrical
arc-out indications, and if necessary,
replacement of the disk with a
serviceable disk.
Differences Between the Proposed AD
and the Service Information
Although fan disk part number (P/N)
5922T01G02 is not specified by ASB
CF34–BJ 72–A0088, Revision 1, dated
October 30, 2000, fan disk P/N
VerDate jul<14>2003
16:15 Aug 22, 2005
Jkt 205001
5922T01G02 is subject to the
requirements specified in this AD.
FAA’s Determination and Requirements
of the Proposed AD
We have evaluated all pertinent
information and identified an unsafe
condition that is likely to exist or
develop on other products of this same
type design. We are proposing this AD,
which would require requires an
inspection of fan disks, P/N’s
5921T18G01, 5921T18G09,
5921T18G10, 5921T54G01,
5922T01G02, 5922T01G04,
5922T01G05, 6020T62G04,
6020T62G05, 6078T00G01,
6078T57G01, 6078T57G02,
6078T57G03, 6078T57G04,
6078T57G05, and 6078T57G06, for
electrical arc-out indications and, if
necessary, replacement of the fan disk
with a serviceable disk. This AD would
also require replacing certain fan disks
with blended callouts and listed by
P/N and serial number (SN) in this AD
before achieving a new reduced life
limit. The proposed AD would require
that you do these actions using the
service information described
previously.
Costs of Compliance
We estimate that one General Electric
Company (GE) CF34–1A, –3A, –3A1,
–3A2, –3B, and –3B1 turbofan engine of
U.S. registry would be affected by this
proposed AD. We also estimate that it
would take approximately six work
hours per engine to perform the
proposed actions, and that the average
labor rate is $65 per work hour.
Required parts would cost
approximately $140,000 per engine.
Based on these figures, we estimate the
total cost of the proposed AD to U.S.
operators to be $140,390.
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 regulation:
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
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Fmt 4702
Sfmt 4702
under the criteria of the Regulatory
Flexibility Act.
We prepared a summary of the costs
to comply with this proposal and placed
it in the AD Docket. You may get a copy
of this summary by sending a request to
us at the address listed under
ADDRESSES. Include ‘‘AD Docket No.
2000–NE–42–AD’’ in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Safety.
The Proposed Amendment
Accordingly, 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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–12229 FR
27017, May 16, 2001, and by adding a
new airworthiness directive to read as
follows:
General Electric Company: Docket No. 2000–
NE–42–AD.
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
October 24, 2005.
Affected ADs
(b) This AD supersedes AD 2001–10–03,
Amendment 39–12229.
Applicability
(c) This AD applies to General Electric
Company (GE) CF34–1A, –3A, –3A1, –3A2,
–3B, and –3B1 turbofan engines. These
engines are installed on, but not limited to,
Bombardier, Inc. Canadair airplane models
CL–600–2A12, –2B16, and –2B19.
Unsafe Condition
(d) This AD results from a report of a crack
that was found during a visual inspection as
part of routine engine maintenance. We are
issuing this AD to prevent rupture of the fan
disk due to cracks that initiate at an electrical
arc-out, which could result in an
uncontained failure of the engine,
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.
Removal of Certain Fan Disks From Service
(f) On disk P/N’s 5921T18G01,
5921T18G09, 5921T18G10, 5921T54G01,
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Federal Register / Vol. 70, No. 162 / Tuesday, August 23, 2005 / Proposed Rules
5922T01G02, 5922T01G04, 5922T01G05,
6020T62G04, 6020T62G05, 6078T00G01,
6078T57G01, 6078T57G02, 6078T57G03,
6078T57G04, 6078T57G05, and 6078T57G06,
that are listed by P/N and serial number (SN)
in the following Table 1 of this AD and that
have less than 8,000 cycles-since-new (CSN)
on the effective date of this AD, replace fan
disk P/N’s before accumulating 8,000 CSN:
TABLE 1.—FAN DISKS THAT REQUIRE
REMOVAL BASED ON BLENDED
CALLOUTS
Disk serial
No.
Disk part No.
6078T57G02
6078T00G01
6078T57G02
5922T01G04
6078T57G04
..........................
..........................
..........................
..........................
..........................
GAT6306N
GAT3860G
GAT1924L
GAT9599G
GEE05831
TABLE 1.—FAN DISKS THAT REQUIRE
REMOVAL BASED ON BLENDED
CALLOUTS—Continued
Disk serial
No.
Disk part No.
6078T57G04
6078T57G04
6078T57G04
6078T57G04
6078T57G05
6078T57G05
6078T57G05
6078T57G05
6078T57G04
6078T57G04
6078T57G04
6078T57G05
6078T57G05
6078T57G05
6078T57G05
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
..........................
GEE06612
GEE06618
GEE06974
GEE06980
GEE143FY
GEE1453G
GEE14452
GEE145NA
GEE08086
GEE09287
GEE09337
GEE12720
GEE14214
GEE142YT
GEE146GT
49217
(g) For disks with SN’s listed in Table 1 of
this AD that have 8,000 CSN or greater on the
effective date of this AD, replace the disk
within 30 days after the effective date of this
AD.
Inspection of All Other Fan Disks
(h) Inspect all other fan disks, P/N’s
5921T18G01, 5921T18G09, 5921T18G10,
5921T54G01, 5922T01G02, 5922T01G04,
5922T01G05, 6020T62G04, 6020T62G05,
6078T00G01, 6078T57G01, 6078T57G02,
6078T57G03, 6078T57G04, 6078T57G05, and
6078T57G06 in accordance with paragraphs
3.A.(1) through 3.E.(2) of the
Accomplishment Instructions of Alert
Service Bulletin (ASB) CF34–BJ 72–A0088,
Revision 1, dated October 30, 2000 or
paragraphs 3.A.(1) through 3.A.(2)(f) of the
Accomplishment Instructions of ASB CF34–
AL 72–A0103, dated August 4, 2000. Use the
compliance times specified in the following
Table 2:
TABLE 2.—FAN DISK INSPECTION COMPLIANCE TIMES
Fan disk operating CSN
Inspect by
(1) Fewer than 8,000 CSN or the effective date of this AD ....................
Before accumulating 8,000 CSN or by the next hot section inspection
after the effective date of this AD, whichever occurs earlier.
Within 120 days after the effective date of this AD.
(2) 8,000 CSN or greater on the effective date of this AD ......................
Definitions
DEPARTMENT OF TRANSPORTATION
(i) For the purposes of this AD, the
following definitions apply:
(1) A serviceable fan disk is defined as a
fan disk that has been inspected as specified
in paragraph (h) of this AD and is not listed
in Table 1 of this AD.
(2) Cycles-since-new for fan disk P/N’s
5922T01G04 or 5922T01G05 is defined as
total cycles accrued since new as P/N
6078T57G02 or 6078T57G03, added to total
cycles accrued after modification from P/N
6078T57G02 or 6078T57G03.
(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.Special Flight Permits
Related Information
(k) None.
Issued in Burlington, Massachusetts, on
August 17, 2005.
Richard Noll,
Acting Manager, Engine and Propeller
Directorate, Aircraft Certification Service.
[FR Doc. 05–16709 Filed 8–22–05; 8:45 am]
VerDate jul<14>2003
16:15 Aug 22, 2005
Jkt 205001
14 CFR Part 39
[Docket No. FAA–2005–20712; Directorate
Identifier 2005–CE–15–AD]
RIN 2120–AA64
Airworthiness Directives; Raytheon
Aircraft Company, Model 390, Premier
1 Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
Alternative Methods of Compliance
BILLING CODE 4910–13–P
Federal Aviation Administration
SUMMARY: The FAA proposes to adopt a
new airworthiness directive (AD) for
certain Raytheon Aircraft Company
(Raytheon), Model 390, Premier 1
airplanes. For certain airplanes, this
proposed AD would require you (unless
already done) to replace the plastic
cover over the air conditioning motor
module with a metallic cover and
modify the air conditioning compressor
motor module electromagnetic
interference-radio frequency
interference (EMI–RFI) filter located
under the cover and reidentify the
module part number. For all airplanes,
the proposed AD would limit future
installations of the cover for the air
conditioner and the air conditioning
compressor motor module. This
proposed AD results from reports that
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Fmt 4702
Sfmt 4702
the plastic cover over the air
conditioning motor module was found
melted or burned and that the
overheating of the EMI–RFI filter
assembly located under the cover
caused this damage. We are issuing this
proposed AD to prevent the melting or
burning of the plastic cover. The
burning of the plastic cover could result
in a fire.
DATES: We must receive any comments
on this proposed AD by October 21,
2005.
Use one of the following to
submit comments on this proposed AD:
• DOT Docket Web site: Go to
http://dms.dot.gov and follow the
instructions for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to http://www.regulations.gov
and follow the instructions for sending
your comments electronically.
• Mail: Docket Management Facility;
U.S. Department of Transportation, 400
Seventh Street, SW., Nassif Building,
Room PL–401, Washington, DC 20590–
001.
• Fax: 1–202–493–2251.
• Hand Delivery: Room PL–401 on
the plaza level of the Nassif Building,
400 Seventh Street, SW., Washington,
DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
To get the service information
identified in this proposed AD, contact
Raytheon Aircraft Company, PO Box 85,
ADDRESSES:
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]]>Agencies
[Federal Register Volume 70, Number 162 (Tuesday, August 23, 2005)]
[Proposed Rules]
[Pages 49215-49217]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-16709]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2000-NE-42-AD]
RIN 2120-AA64
Airworthiness Directives; General Electric Company CF34 Series
Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: The FAA proposes to supersede an existing airworthiness
directive (AD) for General Electric Company (GE) CF34-1A, -3A, -3A1, -
3A2, -3B, and -3B1 turbofan engines. That AD currently requires a
onetime inspection, and if necessary replacing certain fan disks for
electrical arc-out indications. That AD also reduces the life limit of
certain fan disks. This proposed AD would require the same actions and
adds one disk part number (P/N) and serial number (SN) to the affected
fan disks. This proposed AD results from an error in the first part
number and serial number listed in Table 1 of the original AD. We are
proposing this AD to prevent rupture of the fan disk due to cracks that
initiate at an electrical arc-out, which could result in an uncontained
failure of the engine.
DATES: We must receive any comments on this proposed AD by October 24,
2005.
ADDRESSES: Use one of the following addresses to comment on this
proposed AD:
By mail: Federal Aviation Administration (FAA), New
England Region, Office of the Regional Counsel, Attention: Rules Docket
No. 2000-NE-42-AD, 12 New England Executive Park, Burlington, MA 01803-
5299.
By fax: (781) 238-7055.
By e-mail: 9-ane-adcomment@faa.gov.
You can get the service information identified in this proposed AD
from GE Aircraft Engines, 1000 Western Avenue, Lynn, MA 01910;
Attention: CF34 Product Support Engineering, Mail Zone: 34017;
telephone (781) 594-6323; fax (781) 594-0600.
You may examine the AD docket at the FAA, New England Region,
Office of the Regional Counsel, 12 New England Executive Park,
Burlington, MA.
FOR FURTHER INFORMATION CONTACT: Eugene Triozzi, Aerospace Engineer,
Engine Certification Office, FAA, Engine and Propeller Directorate, 12
New England Executive Park, Burlington, MA 01803-5299; telephone 781-
238-7148; fax 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 ``AD Docket No. 2000-NE-42-AD'' in the
subject line of your comments. If you want us to acknowledge receipt of
your mailed comments, send us a self-addressed, stamped postcard with
the docket number written on it; we will date-stamp your postcard and
mail it back to
[[Page 49216]]
you. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of the proposed AD. If a
person contacts us verbally, and that contact relates to a substantive
part of this proposed AD, we will summarize the contact and place the
summary in the docket. We will consider all comments received by the
closing date and may amend the proposed AD in light of those comments.
Examining the AD Docket
You may examine the AD Docket (including any comments and service
information), by appointment, between 8 a.m. and 4:30 p.m., Monday
through Friday, except Federal holidays. See ADDRESSES for the
location.
Discussion
On May 7, 2001, the FAA issued AD 2001-10-13, Amendment 39-12229
(66 FR 27017, May 16, 2001). That AD requires a onetime inspection, and
if necessary replacing certain fan disks for electrical arc-out
indications. That AD also reduces the life limit of certain fan disks.
That AD resulted from a report of a crack that was found during a
visual inspection as part of routine engine maintenance. That
condition, if not corrected, could result in rupture of the fan disk
due to cracks that initiate at an electrical arc-out, which could
result in an uncontained failure of the engine.
Actions Since AD 2001-10-13 Was Issued
Since we issued that AD, we discovered that the first fan disk part
number and the first fan disk serial number listed in Table 1, Fan
Disks that Require Removal Based on Blended Callouts are incorrect.
This proposed AD would correct those numbers. In all other respects,
the proposed AD remains the same as AD 2001-10-03.
Relevant Service Information
We have reviewed and approved the technical contents of GE Aircraft
Engines (GEAE) Alert Service Bulletin (ASB) CF34-BJ 72-A0088, Revision
1, dated October 30, 2000; and ASB CF34-AL 72-A0103, dated August 4,
2000. These ASB's provide procedures for inspections of certain disks
for electrical arc-out indications, and if necessary, replacement of
the disk with a serviceable disk.
Differences Between the Proposed AD and the Service Information
Although fan disk part number (P/N) 5922T01G02 is not specified by
ASB CF34-BJ 72-A0088, Revision 1, dated October 30, 2000, fan disk P/N
5922T01G02 is subject to the requirements specified in this AD.
FAA's Determination and Requirements of the Proposed AD
We have evaluated all pertinent information and identified an
unsafe condition that is likely to exist or develop on other products
of this same type design. We are proposing this AD, which would require
requires an inspection of fan disks, P/N's 5921T18G01, 5921T18G09,
5921T18G10, 5921T54G01, 5922T01G02, 5922T01G04, 5922T01G05, 6020T62G04,
6020T62G05, 6078T00G01, 6078T57G01, 6078T57G02, 6078T57G03, 6078T57G04,
6078T57G05, and 6078T57G06, for electrical arc-out indications and, if
necessary, replacement of the fan disk with a serviceable disk. This AD
would also require replacing certain fan disks with blended callouts
and listed by P/N and serial number (SN) in this AD before achieving a
new reduced life limit. The proposed AD would require that you do these
actions using the service information described previously.
Costs of Compliance
We estimate that one General Electric Company (GE) CF34-1A, -3A, -
3A1, -3A2, -3B, and -3B1 turbofan engine of U.S. registry would be
affected by this proposed AD. We also estimate that it would take
approximately six work hours per engine to perform the proposed
actions, and that the average labor rate is $65 per work hour. Required
parts would cost approximately $140,000 per engine. Based on these
figures, we estimate the total cost of the proposed AD to U.S.
operators to be $140,390.
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
regulation:
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 summary of the costs to comply with this proposal and
placed it in the AD Docket. You may get a copy of this summary by
sending a request to us at the address listed under ADDRESSES. Include
``AD Docket No. 2000-NE-42-AD'' in your request.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, 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 39-12229 FR
27017, May 16, 2001, and by adding a new airworthiness directive to
read as follows:
General Electric Company: Docket No. 2000-NE-42-AD.
Comments Due Date
(a) The Federal Aviation Administration (FAA) must receive
comments on this airworthiness directive (AD) action by October 24,
2005.
Affected ADs
(b) This AD supersedes AD 2001-10-03, Amendment 39-12229.
Applicability
(c) This AD applies to General Electric Company (GE) CF34-1A, -
3A, -3A1, -3A2, -3B, and -3B1 turbofan engines. These engines are
installed on, but not limited to, Bombardier, Inc. Canadair airplane
models CL-600-2A12, -2B16, and -2B19.
Unsafe Condition
(d) This AD results from a report of a crack that was found
during a visual inspection as part of routine engine maintenance. We
are issuing this AD to prevent rupture of the fan disk due to cracks
that initiate at an electrical arc-out, which could result in an
uncontained failure of the engine,
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.
Removal of Certain Fan Disks From Service
(f) On disk P/N's 5921T18G01, 5921T18G09, 5921T18G10,
5921T54G01,
[[Page 49217]]
5922T01G02, 5922T01G04, 5922T01G05, 6020T62G04, 6020T62G05,
6078T00G01, 6078T57G01, 6078T57G02, 6078T57G03, 6078T57G04,
6078T57G05, and 6078T57G06, that are listed by P/N and serial number
(SN) in the following Table 1 of this AD and that have less than
8,000 cycles-since-new (CSN) on the effective date of this AD,
replace fan disk P/N's before accumulating 8,000 CSN:
Table 1.--Fan Disks That Require Removal Based on Blended Callouts
------------------------------------------------------------------------
Disk part No. Disk serial No.
------------------------------------------------------------------------
6078T57G02............................... GAT6306N
6078T00G01............................... GAT3860G
6078T57G02............................... GAT1924L
5922T01G04............................... GAT9599G
6078T57G04............................... GEE05831
6078T57G04............................... GEE06612
6078T57G04............................... GEE06618
6078T57G04............................... GEE06974
6078T57G04............................... GEE06980
6078T57G05............................... GEE143FY
6078T57G05............................... GEE1453G
6078T57G05............................... GEE14452
6078T57G05............................... GEE145NA
6078T57G04............................... GEE08086
6078T57G04............................... GEE09287
6078T57G04............................... GEE09337
6078T57G05............................... GEE12720
6078T57G05............................... GEE14214
6078T57G05............................... GEE142YT
6078T57G05............................... GEE146GT
------------------------------------------------------------------------
(g) For disks with SN's listed in Table 1 of this AD that have
8,000 CSN or greater on the effective date of this AD, replace the
disk within 30 days after the effective date of this AD.
Inspection of All Other Fan Disks
(h) Inspect all other fan disks, P/N's 5921T18G01, 5921T18G09,
5921T18G10, 5921T54G01, 5922T01G02, 5922T01G04, 5922T01G05,
6020T62G04, 6020T62G05, 6078T00G01, 6078T57G01, 6078T57G02,
6078T57G03, 6078T57G04, 6078T57G05, and 6078T57G06 in accordance
with paragraphs 3.A.(1) through 3.E.(2) of the Accomplishment
Instructions of Alert Service Bulletin (ASB) CF34-BJ 72-A0088,
Revision 1, dated October 30, 2000 or paragraphs 3.A.(1) through
3.A.(2)(f) of the Accomplishment Instructions of ASB CF34-AL 72-
A0103, dated August 4, 2000. Use the compliance times specified in
the following Table 2:
Table 2.--Fan Disk Inspection Compliance Times
------------------------------------------------------------------------
Fan disk operating CSN Inspect by
------------------------------------------------------------------------
(1) Fewer than 8,000 CSN or the Before accumulating 8,000 CSN
effective date of this AD. or by the next hot section
inspection after the effective
date of this AD, whichever
occurs earlier.
(2) 8,000 CSN or greater on the Within 120 days after the
effective date of this AD. effective date of this AD.
------------------------------------------------------------------------
Definitions
(i) For the purposes of this AD, the following definitions
apply:
(1) A serviceable fan disk is defined as a fan disk that has
been inspected as specified in paragraph (h) of this AD and is not
listed in Table 1 of this AD.
(2) Cycles-since-new for fan disk P/N's 5922T01G04 or 5922T01G05
is defined as total cycles accrued since new as P/N 6078T57G02 or
6078T57G03, added to total cycles accrued after modification from P/
N 6078T57G02 or 6078T57G03.
Alternative Methods of Compliance
(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.Special Flight
Permits
Related Information
(k) None.
Issued in Burlington, Massachusetts, on August 17, 2005.
Richard Noll,
Acting Manager, Engine and Propeller Directorate, Aircraft
Certification Service.
[FR Doc. 05-16709 Filed 8-22-05; 8:45 am]
BILLING CODE 4910-13-P
