Airworthiness Directives; General Electric Company CF34 Series Turbofan Engines, 49215-49217 [05-16709]

Download as PDF 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 Frm 00016 Fmt 4702 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 E:\FR\FM\23AUP1.SGM 23AUP1 49216 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 PO 00000 Frm 00017 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, E:\FR\FM\23AUP1.SGM 23AUP1 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 PO 00000 Frm 00018 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: E:\FR\FM\23AUP1.SGM 23AUP1

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