01-12942. Airworthiness Directives; GE Aircraft Engines CJ610 Series Turbojet and CF700 Turbofan Engines
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Start Preamble
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 Start Printed Page 28365engine 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.
Start Further InfoFOR 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.
End Further Info End Preamble Start Supplemental InformationSUPPLEMENTARY 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.
Start List of SubjectsList of Subjects in 14 CFR Part 39
- Air transportation
- Aircraft
- Aviation safety
- Safety
Adoption of the Amendment
Start Amendment PartAccordingly, 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:
End Amendment Part Start PartPART 39—AIRWORTHINESS DIRECTIVES
End Part Start Amendment Part1. The authority citation for part 39 continues to read as follows:
End Amendment PartStart Signature[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:
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 Start Printed Page 28366owner/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:
Start Printed Page 28368Table I.—Unapproved Parts Listed in AD 2000-01-09
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, 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 Start Printed Page 28367 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.
End Signature End Supplemental InformationIssued 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
Document Information
- Effective Date:
- 6/7/2001
- Published:
- 05/23/2001
- Department:
- Federal Aviation Administration
- Entry Type:
- Rule
- Action:
- Final rule; request for comments.
- Document Number:
- 01-12942
- Dates:
- Effective June 7, 2001.
- Pages:
- 28364-28368 (5 pages)
- Docket Numbers:
- Docket No. 99-NE-58-AD, Amendment 39-12238, AD 2001-10-12
- RINs:
- 2120-AA64: Airworthiness Directives
- RIN Links:
- https://www.federalregister.gov/regulations/2120-AA64/airworthiness-directives
- Topics:
- Air transportation, Aircraft, Aviation safety, Safety
- PDF File:
- 01-12942.pdf
- CFR: (1)
- 14 CFR 39.13