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 Federal Register Information
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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
Airworthiness Directives; GE Aircraft Engines CJ610 Series Turbojet and CF700 Turbofan Engines
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Preamble Information
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 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.
Sec. 39.13 [Amended]
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:
Regulatory Information
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 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
| 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, 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 |
| 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 |
| 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 |
* 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 Number |
| 37E501428P102 | 1st Stg Disc/Shaft/Spacer | GAT14210WYR |
| 37E501428P106 | Disc & Shaft Stg 1 Comp | GAT115140WZA |
| 37D401312P101 | Disc Stg 2 Comp | GAT2107WYR |
| 37D401312P101 | Disc Stg 2 Comp | GAT07432WZA |
| 37D401313P101 | Disc Stg 3 Comp | GAT2432WYR |
| 37D401313P101 | Disc Stg 3 Comp | GAT10717WZA |
| 5018T16P01 | Disc Stg 4 Comp | GAT10058WYR |
| 5018T16P01 | Disc Stg 4 Comp | GAT05724WZA |
| 37D401315P101 | Disc Stg 5 Comp | GAT16068WYR |
| 37D401316P101 | Disc Stg 6 Comp | GAT15035WYR |
| 37D401317P101 | Disc Stg 7 Comp | GAT6493WYR |
| 5013T82P01 | Disc Stg 7 Comp | GAT15819WYR |
| 37D401709P101 | Disc Stg 8 Comp | GAT08842WYR |
| 5013T83P01 | Disc Stg 8 Comp | GAT07464WYR |
| 4010T010P02 | Seal Rot Stg 8 Comp | JADMSA09181 |
| 4010T010P01 | Seal Rot Stg 8 Comp | APVM0F00180 |
| 4010T01P01 | Seal Rot Stg 8 Comp | APVM0F00192 |
| 5004T73P02 | Shaft Rear Comp | HPCTQA12100 |
| 3007T98G01 | Shaft Rear Comp | HPCTQ1474 |
| 37D401303P102 | Spacer Stg 3 Comp | GGMWZA1112 |
| 5013T88P01 | Spacer Stg 4 Comp | GAT1A402 |
| 37D401302P101 | Spacer Stg 2 Comp | GATWRY12483 |
| 37D401302P103 | Spacer Stg 2 Comp | GATE0A00429 |
| 37D401303P102 | Spacer Stg 3 Comp | GATWZA5858 |
| 37D401304P103 | Spacer Stg 4 Comp | GATANW10309 |
| 37D401304P103 | Spacer Stg 4 Comp | GATANWA5510 |
| 5013T88P01 | Spacer Stg 4 Comp | GATCDY61557 |
| 37D401305P103 | Spacer Stg 5 Comp | GATANW11066 |
| 37D401306P103 | Spacer Stg 6 Comp | GATANW09191 |
| 37D401306P105 | Spacer Stg 6 Comp | GAT8654CDY |
| 37D401307P103 | Spacer Stg 7 Comp | GATANW9286 |
| 37D401307P103 | 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.
Footer Information
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
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