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 Department of Transportation Federal Aviation Administration 14 CFR Part 39
[Docket No. 99-NE-58-AD; Amendment 39-12238; AD 2001-10-12]
RIN 2120-AA64
 AGENCY: Federal Aviation Administration, DOT.
 ACTION: Final rule; request for comments.
 SUMMARY: This amendment supersedes an existing airworthiness directive (AD) that is applicable to GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines that currently requires removal of certain unapproved parts before further flight. This amendment requires removal of additional unapproved parts. This amendment is prompted by the discovery by the FAA of additional unapproved parts not listed in the original AD that have been introduced into the field and might be installed on the affected engines. The actions specified in this AD are intended to prevent the use of unapproved parts which could lead to an uncontained 
                        ( print page 28365)
                        engine failure and damage to the airplane.
 DATES: Effective June 7, 2001. Comments for inclusion in the Rules Docket must be received on or before July 23, 2001.
 ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), New England Region, Office of the Regional Counsel, Attention: Rules Docket No. 99-NE-58-AD, 12 New England Executive Park, Burlington, MA 01803-5299. Comments may also be sent via the Internet using the following address: “9-ane-adcomment@faa.gov”. Comments sent via the Internet must contain the docket number in the subject line.
 FOR FURTHER INFORMATION CONTACT: Kevin Donovan, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803-5299; telephone (781) 238-7743, fax (238) 238-7199.


SUPPLEMENTARY INFORMATION: On January 5, 2000, the FAA issued AD 2000-01-09, Amendment 39-11506 (65 FR 1771) to require removal of certain unapproved parts before further flight. That amendment was prompted by findings that life-limited parts, with inaccurate records, have been introduced into the field and might be installed on the affected engines. That condition, if not corrected, could lead to an uncontained engine failure and damage to the airplane. Since the issuance of that AD, the FAA discovered a compressor rotor during an audit with suspected military markings. The manufacturer confirmed that the marking was an electro-etched Low Cycle Fatigue Cycles (LCFC) marking used strictly on military parts. The original AD, AD 2000-01-09, did not identify this particular compressor rotor or the three additional rotors containing unapproved parts discovered at other locations during subsequent audits. FAA's Determination of an Unsafe Condition and Proposed Actions Since an unsafe condition has been identified that is likely to exist or develop on other GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines of the same type design, this AD supersedes AD 2000-01-09 to require removal before further flight of the additional unapproved parts not listed in the original AD that have been introduced into the field and might be installed on the affected engines. Immediate Adoption of This AD Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days. Comments Invited Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications should identify the Rules Docket number and be submitted in triplicate to the address specified under the caption 
                    **ADDRESSES.**
                     All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed. Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket. Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this action must submit a self-addressed, stamped postcard on which the following statement is made: “Comments to Docket Number 99-NE-58-AD.” The postcard will be date stamped and returned to the commenter. Regulatory Impact This final rule does not have federalism implications, as defined in Executive Order 13132, because it 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. Accordingly, the FAA has not consulted with state authorities prior to publication of this final rule. The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and is not a “significant regulatory action” under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption 
                    **ADDRESSES.** List of Subjects in 14 CFR Part 39 Air transportation
Aircraft
Aviation safety
Safety
 Adoption of the Amendment Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (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
  2. Section 39.13 is amended by removing Amendment 39-11506 (65 FR 1771, January 12, 2000), and by adding a new airworthiness directive (AD), Amendment 39-12238, to read as follows: **2001-10-12 GE Aircraft Engines (GEAE)**
                                 Amendment 39-12238. Docket 99-NE-58-AD. Supersedes AD 2000-01-09, Amendment 39-11506. Applicability This airworthiness directive (AD) is applicable to GEAE CJ610 series turbojet and CF700 series turbofan engines, with parts listed by part number (P/N) and serial number (SN) in Tables I and II, installed. These engines are installed on, but not limited to, the Dassault-Aviation Fan Jet Falcon 20 series, Sabreliner NA265 series, Learjet 20 series, Israel Aircraft Industries Westwind series, Hansa Jet, Aero Commander, and Jet Commander. Note 1: This AD applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the 
                                    ( print page 28366)
                                    owner/operator must request approval for an alternative method of compliance in accordance with paragraph (c) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance Compliance with this AD is required as indicated, unless already done. To prevent the use of unapproved parts, which could lead to an uncontained engine failure and damage to the airplane, accomplish the following: Replacement of Unapproved Parts (a) Before further flight, remove any part listed by P/N and SN in Tables I and II of this AD, and replace it with a serviceable part: Table I.—Unapproved Parts Listed in AD 2000-01-09
Part number
Part name
Serial number3007T98G01
Shaft, compressor drive
HPCTQA116933007T98G01
Shaft, compressor drive
HPCTQA119293007T98G01
Shaft, compressor drive
HPCTQA19293007T98G01
Shaft, compressor drive
HPGTQA99473007T98G01
Shaft, compressor drive
TQA1430037D401014P101
Torque ring, turbine
GGM68137D401014P101
Torque ring, turbine
GGMCBK197737D401014P101
Torque ring, turbine
GGMWZA123037D401014P101
Torque ring, turbine
GGMWZA232237D401014P101
Torque ring, turbine
GGMWZA466537D401014P101
Torque ring, turbine
PMB08403P37D401014P102
Torque ring, turbine
PMB1920437D401302P101
Spacer, stage 2
GATI2099WYR37D401302P101
Spacer, stage 2
GATWZA0965637D401302P101
Spacer, stage 2
GATWZA1000237D401302P101
Spacer, stage 2
GATWZA1014837D401302P101
Spacer, stage 2
GATWZA541937D401303P102
Spacer, stage 3
GATCBK0219237D401303P102
Spacer, stage 3
GATWZA1203037D401303P102
Spacer, stage 3
GGMWZA102237D401303P104
Spacer, stage 3
GATWYR536437D401304P104
Spacer, stage 4
GATANWA237837D401305P103
Spacer, stage 5
GATANW952837D401305P103
Spacer, stage 5
GATANWA744137D401305P103
Spacer, stage 5
GATANWA854237D401305P103
Spacer, stage 5
GGMANW317237D401306P103
Spacer, stage 6
GATANW638037D401306P103
Spacer, stage 6
GGMANW233137D401306P105
Spacer, stage 6
GATCDY7138637D401306P105
Spacer, stage 6
GATO7040CDY37D401307P103
Spacer, stage 7
GAT5965337D401307P103
Spacer, stage 7
GATANW717037D401307P103
Spacer, stage 7
GATANWA713437D401307P103
Spacer, stage 7
GGMANW310437D401312P101
Disc, stage 2
GATI0156WZA37D401312P101
Disc, stage 2
GATO8253WZA37D401312P101
Disc, stage 2
GATWZA398337D401312P101
Disc, stage 2
GATWZA660437D401312P101
Disc, stage 2
GGMCBK62037D401312P101
Disc, stage 2
GGMLBA449137D401313P101
Disc, stage 3
GATI3249WYI37D401313P101
Disc, stage 3
GATO7644WZA37D401313P101
Disc, stage 3
GATWZA652237D401313P101
Disc, stage 3
GATWZA672337D401313P101
Disc, stage 3
GGMLBA210237D401314P102
Disc, stage 4
GAT05572WZA37D401314P102
Disc, stage 4
GATO4383WZA37D401314P102
Disc, stage 4
GGMWZA681837D401315P101
Disc, stage 5
GAT12406WZA37D401315P101
Disc, stage 5
GATWZA475337D401315P101
Disc, stage 5
GATWZA709337D401316P101
Disc, stage 6
GAT10162WZA37D401316P101
Disc, stage 6
GATWZA443537D401316P101
Disc, stage 6
GATWZA720837D401316P101
Disc, stage 6
GGMWZA337637D401317P101
Disc, stage 7
GAT10013WZA37D401317P101
Disc, stage 7
GAT13322WZA37D401317P101
Disc, stage 7
GATI5009WYR37D401709P101
Disc, stage 8
GATO3900WZA37D401709P101
Disc, stage 8
GATO5381WZA37D401709P101
Disc, stage 8
GGMWZA690637D401709P101
Disc, stage 8
GGMWZA694237E501428P102
Disc and shaft, stage 1
GATI2001WZA( print page 28367)37E501428P102
Disc and shaft, stage 1
GATWZA863937E501428P106
Disc and shaft, stage 1
GATO8474WZA37E501428P106
Disc and shaft, stage 1
GGMWZA32314010T01P01
Seal labyrinth, stage 8
JADCSF334P594010T01P01
Seal labyrinth, stage 8
JADCSF52224010T01P01
Seal labyrinth, stage 8
JADCSF5444P214010T01P01
Seal labyrinth, stage 8
JADMCI32144036T24P01
Turbine wheel, stage 2
GATWYR140354036T24P01
Turbine wheel, stage 2
GATWYR146555013T79P01
Disc, stage 5
GATI1679WZA5013T82P01
Disc, stage 7
GATI7662WYR5013T88P01
Spacer, stage 4
GAT699355013T88P01
Spacer, stage 4
GATCDY667155013T89P01
Spacer, stage 5
GAT60180CDY5013T89P01
Spacer, stage 5
GAT60180CDY5013T90P01
Spacer, stage 7
GAT81678CDY5013T90P01
Spacer, stage 7
GATCDY820365018T16P01
Disc, stage 4
GAT12222WYR6028T44P01
Turbine wheel, stage 1
GAT119006028T44P01
Turbine wheel, stage 1
GAT130946028T44P01
Turbine wheel, stage 1
GAT147496028T44P01
Turbine wheel, stage 1
GAT151606028T44P01
Turbine wheel, stage 1
GAT15396WYR6028T44P01
Turbine wheel, stage 1
GAT157036028T44P01
Turbine wheel, stage 1
GAT158216028T44P01
Turbine wheel, stage 1
GAT158996028T44P01
Turbine wheel, stage 1
GAT597436028T44P01
Turbine wheel, stage 1
GAT601906028T44P01
Turbine wheel, stage 1
GAT601976028T44P01
Turbine wheel, stage 1
GAT604836028T44P01
Turbine wheel, stage 1
GAT73216028T44P01
Turbine wheel, stage 1
GATA84756028T44P01
Turbine wheel, stage 1
GATA84926028T44P01
Turbine wheel, stage 1
GATAJ2046028T44P01
Turbine wheel, stage 1
GATB69256028T44P01
Turbine wheel, stage 1
GATBE9986028T44P01
Turbine wheel, stage 1
GATE21506028T44P01
Turbine wheel, stage 1
GATE22596028T44P01
Turbine wheel, stage 1
GATE22916028T44P01
Turbine wheel, stage 1
GATE23366028T44P01
Turbine wheel, stage 1
GATF44966028T44P01
Turbine wheel, stage 1
GATF45076028T44P01
Turbine wheel, stage 1
GATFE9536028T44P01
Turbine wheel, stage 1
GATG64706028T44P01
Turbine wheel, stage 1
GATV65416028T44P01
Turbine wheel, stage 1
GATV65886028T44P01
Turbine wheel, stage 1
GATW1573634E583P04
Turbine wheel, stage 1
GATWZA4994634E583P5
Turbine wheel, stage 1
GAT10650634E583P5
Turbine wheel, stage 1
GAT13048646C596P2
Turbine wheel, stage 2
GATCBK01912646C596P2
Turbine wheel, stage 2
GATWYR12725646C596P2 *
Turbine wheel, stage 2
GATWZA9723646C594P2 *
Turbine wheel, stage 2
GATWZA9723646C594P1 *
Turbine wheel, stage 2
GATWZA9723841B690P7
Assy, Turbine wheel, stage 1
GAT9383WZA841B690P7
Assy, Turbine wheel, stage 1
GATMKF07225841B690P7
Assy, Turbine wheel, stage 1
GATWYR12358841B690P7
Assy, Turbine wheel, stage 1
GATWYR13457841B690P7
Assy, Turbine wheel, stage 1
GATWYR13677841B690P7
Assy, Turbine wheel, stage 1
GATWZA8110841B690P7
Assy, Turbine wheel, stage 1
GATWZA8263841B690P7
Assy, Turbine wheel, stage 1
GATWZA9182841B690P7
Assy, Turbine wheel, stage 1
OJL0145841B690P7
Assy, Turbine wheel, stage 1
WDBMKF07219* The FAA has determined that up to three Stage 2 Turbine wheels, SN GATWZA9723, may have been distributed with three different P/N's. Therefore, while only P/N 646C596P1 is an approved P/N for the CJ610 and CF700 model engine, all three part numbers are listed.
 
 
 Table II.—Additional Unapproved Parts Discovered Since Publication of AD 2000-01-09
Part Number
Part name
Serial Number37E501428P102
1st Stg Disc/Shaft/Spacer
GAT14210WYR37E501428P106
Disc & Shaft Stg 1 Comp
GAT115140WZA37D401312P101
Disc Stg 2 Comp
GAT2107WYR37D401312P101
Disc Stg 2 Comp
GAT07432WZA37D401313P101
Disc Stg 3 Comp
GAT2432WYR37D401313P101
Disc Stg 3 Comp
GAT10717WZA5018T16P01
Disc Stg 4 Comp
GAT10058WYR5018T16P01
Disc Stg 4 Comp
GAT05724WZA37D401315P101
Disc Stg 5 Comp
GAT16068WYR37D401316P101
Disc Stg 6 Comp
GAT15035WYR37D401317P101
Disc Stg 7 Comp
GAT6493WYR5013T82P01
Disc Stg 7 Comp
GAT15819WYR37D401709P101
Disc Stg 8 Comp
GAT08842WYR5013T83P01
Disc Stg 8 Comp
GAT07464WYR4010T010P02
Seal Rot Stg 8 Comp
JADMSA091814010T010P01
Seal Rot Stg 8 Comp
APVM0F001804010T01P01
Seal Rot Stg 8 Comp
APVM0F001925004T73P02
Shaft Rear Comp
HPCTQA121003007T98G01
Shaft Rear Comp
HPCTQ147437D401303P102
Spacer Stg 3 Comp
GGMWZA11125013T88P01
Spacer Stg 4 Comp
GAT1A40237D401302P101
Spacer Stg 2 Comp
GATWRY1248337D401302P103
Spacer Stg 2 Comp
GATE0A0042937D401303P102
Spacer Stg 3 Comp
GATWZA585837D401304P103
Spacer Stg 4 Comp
GATANW1030937D401304P103
Spacer Stg 4 Comp
GATANWA55105013T88P01
Spacer Stg 4 Comp
GATCDY6155737D401305P103
Spacer Stg 5 Comp
GATANW1106637D401306P103
Spacer Stg 6 Comp
GATANW0919137D401306P105
Spacer Stg 6 Comp
GAT8654CDY37D401307P103
Spacer Stg 7 Comp
GATANW928637D401307P103
Spacer Stg 7 Comp
GATANWA6612
 Alternate Methods of Compliance (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Engine Certification Office (ECO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, ECO. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the ECO. Effective Date of This AD (c) This amendment becomes effective on June 7, 2001.
 Issued in Burlington, Massachusetts, on May 16, 2001. Diane S. Romanosky, Acting Manager, Engine and Propeller Directorate, Aircraft Certification Service.


[FR Doc. 01-12942 Filed 5-22-01; 8:45 am] BILLING CODE 4910-13-P