[Federal Register Volume 65, Number 8 (Wednesday, January 12, 2000)]
[Rules and Regulations]
[Pages 1771-1774]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-597]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99-NE-58-AD; Amendment 39-11506; AD 2000-01-09]
RIN 2120-AA64


Airworthiness Directives; GE Aircraft Engines CJ610 Series 
Turbojet Engines and CF700 Turbofan Engines

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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SUMMARY: 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.

DATES: Effective February 11, 2000.
    Comments for inclusion in the Rules Docket must be received on or 
before March 13, 2000.

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-
[email protected].'' 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 (781) 238-7199.

SUPPLEMENTARY INFORMATION: 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 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

[[Page 1772]]

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 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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

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

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              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

[[Page 1773]]

 
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, stage 4..................  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 1.........  GATE2150
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

[[Page 1774]]

 
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 1...  GATWYR12358
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
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* 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 this AD 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 
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 February 11, 2000.

    Issued in Burlington, Massachusetts, on January 5, 2000.
Jay J. Pardee,
Manager, Engine and Propeller Directorate,
Aircraft Certification Service.
[FR Doc. 00-597 Filed 1-11-00; 8:45 am]
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