AD 2000-01-09

This amendment adopts a new airworthiness directive (AD) that is applicable to GE Aircraft Engines (GEAE) CJ610 series turbojet and CF700 series turbofan engines. This action requires removal of certain unapproved parts before further flight. This amendment is prompted by findings that life-limited parts, with forged and inaccurate records, 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. This condition, if not corrected, could lead to an uncontained engine failure and damage to the airplane.

Final rule; request for comments.

2000-01-09 General Electric Aircraft Engines (GEAE): Amendment 39-11506. Docket 99-NE-58-AD.
Applicability: CJ610 series turbojet and CF700 series turbofan engines, with parts listed by part number (P/N) and serial number (SN) in Appendix 1, 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.
Appendix 1

PART NUMBER
PART NAME
SERIAL NUMBER
3007T98G01
Shaft, compressor drive
HPCTQA11693
3007T98G01
Shaft, compressor drive
HPCTQA11929
3007T98G01
Shaft, compressor drive
HPCTQA1929
3007T98G01
Shaft, compressor drive
HPGTQA9947
3007T98G01
Shaft, compressor drive
TQA14300
37D401014P101
Torque ring, turbine
GGM681
37D401014P101
Torque ring, turbine
GGMCBK1977
37D401014P101
Torque ring, turbine
GGMWZA1230
37D401014P101
Torque ring, turbine
GGMWZA2322
37D401014P101
Torque ring, turbine
GGMWZA4665
37D401014P101
Torque ring, turbine
PMB08403P
37D401014P102
Torque ring, turbine
PMB19204
37D401302P101
Spacer, stage 2
GATI2099WYR
37D401302P101
Spacer, stage 2
GATWZA09656
37D401302P101
Spacer, stage 2
GATWZA10002
37D401302P101
Spacer, stage 2
GATWZA10148
37D401302P101
Spacer, stage 2
GATWZA5419
37D401303P102
Spacer, stage 3
GATCBK02192
37D401303P102
Spacer, stage 3
GATWZA12030
37D401303P102
Spacer, stage 3
GGMWZA1022
37D401303P104
Spacer, stage 3
GATWYR5364
37D401304P104
Spacer, stage 4
GATANWA2378
37D401305P103
Spacer, stage 5
GATANW9528
37D401305P103
Spacer, stage 5
GATANWA7441
37D401305P103
Spacer, stage 5
GATANWA8542
37D401305P103
Spacer, stage 5
GGMANW3172
37D401306P103
Spacer, stage 6
GATANW6380
37D401306P103
Spacer, stage 6
GGMANW2331
37D401306P105
Spacer, stage 6
GATCDY71386
37D401306P105
Spacer, stage 6
GATO7040CDY
37D401307P103
Spacer, stage 7
GAT59653
37D401307P103
Spacer,stage 7
GATANW7170
37D401307P103
Spacer, stage 7
GATANWA7134
37D401307P103
Spacer, stage 7
GGMANW3104
37D401312P101
Disc, stage 2
GATI0156WZA
37D401312P101
Disc, stage 2
GATO8253WZA
37D401312P101
Disc, stage 2
GATWZA3983
37D401312P101
Disc, stage 2
GATWZA6604
37D401312P101
Disc, stage 2
GGMCBK620
37D401312P101
Disc, stage 2
GGMLBA4491
37D401313P101
Disc, stage 3
GATI3249WYI
37D401313P101
Disc, stage 3
GATO7644WZA
37D401313P101
Disc, stage 3
GATWZA6522
37D401313P101
Disc, stage 3
GATWZA6723
37D401313P101
Disc, stage 3
GGMLBA2102
37D401314P102
Disc, stage4
GAT05572WZA
37D401314P102
Disc, stage 4
GATO4383WZA
37D401314P102
Disc, stage 4
GGMWZA6818
37D401315P101
Disc, stage 5
GAT12406WZA
37D401315P101
Disc, stage 5
GATWZA4753
37D401315P101
Disc, stage 5
GATWZA7093
37D401316P101
Disc, stage 6
GAT10162WZA
37D401316P101
Disc, stage 6
GATWZA4435
37D401316P101
Disc, stage 6
GATWZA7208
37D401316P101
Disc, stage 6
GGMWZA3376
37D401317P101
Disc, stage 7
GAT10013WZA
37D401317P101
Disc, stage 7
GAT13322WZA
37D401317P101
Disc, stage 7
GATI5009WYR
37D401709P101
Disc, stage 8
GATO3900WZA
37D401709P101
Disc, stage 8
GATO5381WZA
37D401709P101
Disc, stage 8
GGMWZA6906
37D401709P101
Disc, stage 8
GGMWZA6942
37E501428P102
Disc and shaft, stage 1
GATI2001WZA
37E501428P102
Disc and shaft, stage 1
GATWZA8639
37E501428P106
Disc and shaft, stage 1
GATO8474WZA
37E501428P106
Disc and shaft, stage 1
GGMWZA3231
4010T01P01
Seal labyrinth, stage 8
JADCSF334P59
4010T01P01
Seal labyrinth, stage 8
JADCSF5222
4010T01P01
Seal labyrinth, stage 8
JADCSF5444P21
4010T01P01
Seal labyrinth, stage 8
JADMCI3214
4036T24P01
Turbine wheel, stage 2
GATWYR14035
4036T24P01
Turbine wheel, stage 2
GATWYR14655
5013T79P01
Disc, stage 5
GATI1679WZA
5013T82P01
Disc, stage 7
GATI7662WYR
5013T88P01
Spacer, stage 4
GAT69935
5013T88P01
Spacer, stage 4
GATCDY66715
5013T89P01
Spacer, stage 5
GAT60180CDY
5013T90P01
Spacer, stage 7
GAT81678CDY
5013T90P01
Spacer, stage 7
GATCDY82036
5018T16P01
Disc, stage 4
GAT12222WYR
6028T44P01
Turbine wheel, stage 1
GAT11900
6028T44P01
Turbine wheel, stage 1
GAT13094
6028T44P01
Turbine wheel, stage 1
GAT14749
6028T44P01
Turbine wheel, stage 1
GAT15160
6028T44P01
Turbine wheel, stage 1
GAT15396WYR
6028T44P01
Turbine wheel, stage 1
GAT15703
6028T44P01
Turbine wheel, stage 1
GAT15821
6028T44P01
Turbine wheel, stage 1
GAT15899
6028T44P01
Turbine wheel, stage 1
GAT59743
6028T44P01
Turbine wheel, stage 1
GAT60190
6028T44P01
Turbine wheel, stage 1
GAT60197
6028T44P01
Turbine wheel, stage 1
GAT60483
6028T44P01
Turbine wheel, stage 1
GAT7321
6028T44P01
Turbine wheel, stage 1
GATA8475
6028T44P01
Turbine wheel, stage 1
GATA8492
6028T44P01
Turbine wheel, stage 1
GATAJ204
6028T44P01
Turbine wheel, stage 1
GATB6925
6028T44P01
Turbine wheel, stage 1
GATBE998
6028T44P01
Turbine wheel, stage 1GATE2150
6028T44P01
Turbine wheel, stage 1
GATE2259
6028T44P01
Turbine wheel, stage 1
GATE2291
6028T44P01
Turbine wheel, stage 1
GATE2336
6028T44P01
Turbine wheel, stage 1
GATF4496
6028T44P01
Turbine wheel, stage 1
GATF4507
6028T44P01
Turbine wheel, stage 1
GATFE953
6028T44P01
Turbine wheel, stage 1
GATG6470
6028T44P01
Turbine wheel, stage 1
GATV6541
6028T44P01
Turbine wheel, stage 1
GATV6588
6028T44P01
Turbine wheel, stage 1
GATW1573
634E583P04
Turbine wheel, stage 1
GATWZA4994
634E583P5
Turbine wheel, stage 1
GAT10650
634E583P5
Turbine wheel, stage 1
GAT13048
646C596P2
Turbine wheel, stage 2
GATCBK01912
646C596P2
Turbine wheel, stage 2
GATWYR12725
* 646C596P2
Turbine wheel, stage 2
GATWZA9723
* 646C594P2
Turbine wheel, stage 2
GATWZA9723
* 646C594P1
Turbine wheel, stage 2
GATWZA9723
841B690P7
Assy, Turbine wheel, stage 1
GAT9383WZA
841B690P7
Assy, Turbine wheel, stage 1
GATMKF07225
841B690P7
Assy, Turbine wheel, stage 1GATWYR12358
841B690P7
Assy, Turbine wheel, stage 1
GATWYR13457
841B690P7
Assy, Turbine wheel, stage 1
GATWYR13677
841B690P7
Assy, Turbine wheel, stage 1
GATWZA8110
841B690P7
Assy, Turbine wheel, stage 1
GATWZA8263
841B690P7
Assy, Turbine wheel, stage 1
GATWZA9182
841B690P7
Assy, Turbine wheel, stage 1
OJL0145
841B690P7
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.
Note 1: This airworthiness directive (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 thisAD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) 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: Required as indicated, unless accomplished previously.
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 after the effective date of this AD, remove any part listed by P/N and SN in Appendix 1 of this AD, and replace it with a serviceable part.

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 usedif 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 February 11, 2000.

On or about October 20, 1999, an investigation jointly conducted by the Department of Transportation Inspector General and the Federal Bureau of Investigation concluded that the airworthiness documentation accompanying certain parts distributed contained false and inaccurate data. Some airworthiness approvals appear to contain signature blocks that were electronically scanned from a signature block obtained from a previous airworthiness approval form. The scanned signature block was then electronically applied to other airworthiness approval forms, which contained fictitious cycle counts. In addition, documents appear to have been created by splicing together several items then photocopying the created document to make the copy appear as an original document. Thus, the airworthiness of those parts is suspect. The FAA has identified 127 rotating parts, identified in Appendix 1 by part number and serial number, that are determined to be unapproved parts. Continued operation of these unapproved parts may result in life limited parts exceeding the FAA approved low-cycle fatigue life limits. This condition, if not corrected, could lead to an uncontained engine failure and damage to the airplane.

Required Actions
Since an unsafe condition has been identified that is likely to exist or develop on other GE CJ610 series turbojet and CF700 series turbofan engines of the same type design, this AD is being issued to prevent use of unapproved parts, which could lead to an uncontained engine failure. This AD requires removal of parts listed in Appendix 1 of this AD before further flight and replacement with serviceable parts.

Immediate Adoption
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 actionis 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 notice 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 does 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 publicationof 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 [Amended] 2. Section 39.13 is amended by adding the following new airworthiness directive: