AD 84-01-04
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Honeywell International Inc. | TPE331-1 | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-1U | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-1UA | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-2 | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-2U | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-2UA | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-3 | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-3U | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-3UW | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-3W | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-5 | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-5U | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-6 | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
| engine | Honeywell International Inc. | TPE331-6U | GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. |
Unsafe Condition
Third Stage Turbine Wheels
Federal Register Abstract
Third Stage Turbine Wheels
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_84-01-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-01-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. Subject: Third Stage Turbine Wheels Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/25/1984 Make: Honeywell International Inc. Model: TPE331-1 | TPE331-1U | TPE331-1UA | TPE331-2 | TPE331-2U | TPE331-2UA | TPE331-3 | TPE331-3U | TPE33...Show more Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 84-01-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4792 AD NUMBER: 84-01-04 SUBJECT HEADING: GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. ACTION: SUMMARY: DATES: Effective January 25, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-01-04 GARRETT TURBINE ENGINE COMPANY (GTEC, formerly AiResearch Manufacturing Company of Arizona): Amendment 39-4792. Applies to GTEC Engine Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 series engines. Compliance required as indicated, unless already accomplished. To reduce the possibility of rapid destruction of the engine turbine, accomplish the following: (a) Inspect in accordance with the following schedule, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels, identified by serial number (S/N) below, in accordance with paragraph 2 of GTEC Service Bulletin (SB) No. TPE/TSE331-72-0351, dated April 14, 1982, or equivalent approved by the Manager, Western Aircraft Certification Field Office. Remove from service, prior to further flight, third stage turbine wheels not meeting the inspection criteria. Third stage turbine wheels meeting the inspection criteria may be continued in service to the life limits of paragraph (d) herein. WHEEL TOTAL CYCLES INSPECT Less than 900 Before accumulation of 1000 cycles. 900 or more, and less than 1000 Within the next 100 cycles. 1000 or more, and less than 1200 Within the next 50 cycles. More than 1200 Within the next 10 cycles. NOTES: For purposes of this AD, a cycle is defined as any operating sequence involving an engine start, aircraft takeoff and landing, followed by engine shutdown, and one cycle shall be counted for each such operational sequence. For purposes of this AD, turbine wheels which comply with paragraph 2 of GTEC SB No. TPE/TSE/331-72-0351 or an equivalent approved by the Manager, Western Aircraft Certification Field Office, must have the SB annotated on the life limited parts log card which is located either with the third stage wheel assembly or with the engine log book. Serial Numbers: 0-01345-419 0-01345-1313 0-01345-2372 9-01345-15426 420 1314 2374 15427 421 1315 2375 15428 422 1316 2376 15429 423 1317 2377 15432 424 1318 2378 15433 425 1319 2379 18246 426 1320 2380 18247 428 1321 2381 18248 430 1322 2382 18250 431 1323 2383 18251 432 1324 2384 18252 433 1325 2385 18253 435 1326 2386 18256 436 1328 2387 18258 437 1329 2388 18259 438 1330 2529 18260 439 1331 3106 18262 440 1332 3107 18263 441 1335 3109 18264 442 1336 3110 18265 443 1338 3111 18266 444 2336 3112 18286 446 2337 3113 18287 447 2338 3114 18288 448 2339 3118 18289 449 2340 3119 18302 450 2341 3121 18304 451 2342 3122 18305 452 2343 3123 18310 453 2344 3124 18311 454 2345 3125 18316 455 2346 3126 18317 456 2347 3127 18318 458 2348 3128 18320 459 2349 3129 18321 461 2350 3130 18323 463 2351 3131 18324 1296 2352 3121 18325 1298 2353 3133 18326 1299 2354 3124 18328 1301 2355 3135 18329 1302 2356 3136 18330 1304 2357 3140 18414 1305 2358 3141 18415 1306 2359 3145 1307 2364 3146 1308 2365 3147 1309 2366 3149 1311 2367 3150 1312 2369 3152 2371 3153 3737 (b) Remove from service according to the following schedule, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels identified by S/N below: WHEEL TOTAL CYCLES REMOVE* Less than 1300. Before accumulation of 1500 cycles. 1300 or more and less than 2550. Before accumulation of 2600 cycles or within the next 200 cycles whichever occurs first. 2550 or more. Within the next 50 cycles. *No wheel listed below may exceed 1500 total cycles in service after June 1, 1983. Serial Numbers: 0-01345-18350 0-01345-20025 0-01345-21873 18623 20026 21874 18659 20130 21875 18660 20588 21876 18663 20589 21877 18669 20590 21878 18672 20591 21879 18673 20592 21880 18674 20593 21881 18676 20594 21882 18677 20595 21883 18678 20596 21884 19294 20597 21885 19295 20598 21886 19321 20599 21887 19980 20600 21888 19983 20601 21889 19984 20602 21890 19985 20603 21891 19986 20604 21892 19987 20605 21893 19988 20606 21894 19989 20607 21895 19990 20608 21896 19991 20609 21897 19992 20611 21898 19993 20612 21899 19994 20613 21900 19995 20614 21903 20615 19996 20616 21904 19997 20617 21905 19998 20618 21906 19999 20619 21907 20000 20620 21908 20001 20621 21909 20002 20622 21910 20003 20623 21911 20004 20624 21914 20008 20625 22332 20009 20626 22333 20010 20627 20011 20628 20012 20629 20013 20630 20014 20631 20015 20632 20016 20633 20017 20634 20018 20635 20019 20637 20020 20779 20021 21869 20022 21870 20023 21871 20024 21872 (c) Inspect, prior to accumulating 2600 total wheel cycles, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels introduced into service on or after March 24, 1978, and not listed by S/N in paragraph (a) or (b) herein, in accordance with paragraph 2 of GTEC SB No. TPE/TSE/331-72-0351, dated April 14, 1982, or equivalent approved by the Manager, Western Aircraft Certification Field Office. Remove from service prior to further flight third stage turbine wheels not meeting the inspection criteria. Third stage turbine wheels meeting the inspection criteria may be continued in service to the life limits of paragraph (d) herein. (d) Remove from service the following turbine wheels within the cyclic life limits specified below: WHEEL STAGE PART NUMBER CYCLE LIFE First 867569-1, -3, -7 5700 cycles Second 868272-1, -2, -3, -4 5400 cycles Third 868630-1, -2, -3, -4, -7 3600 cycles Third 868630-8 4300 cycles Third 895539-1, -2, -3, -4 2000 cycles Turbine wheels listed in this paragraph introduced into service prior to March 24, 1978, were not required to have their cyclic lives recorded. As of the effective date of this AD, lives of these wheels shall be converted to cycles by crediting each hour of operation 9 with 1.5 cycles (i.e.: 3500 hrs x 1.5 = 5250 cycles). Actual cycles, if known, may be used in lieu of this conversion. Thereafter, wheel operating life shall be accrued in cycles. Remove from service in accordance with the following schedule P/N 895539-1, -2, -3, and -4 third stage turbine wheels which exceed the above-listed cyclic limits after converting from hours to cycles: WHEEL TOTAL CYCLES REMOVE 2,000 to 3,750 Within the next 300 cycles. 3,751 to 4,500 Within the next 175 cycles. 4,501 to 5,250 Within the next 75 cycles. Remove from service within the next 300 cycles or 10 months in service, whichever comes first after the effective date of this amendment, P/N 867569-1, -3, -7, P/N 868272-1, -2, -3, -4, and P/N 868630-1, -2, -3, -4, -7 turbine wheels which exceed the above-listed cyclic limits after converting from hours to cycles. (e) Prior to accumulating an additional 2700 cycles after February 11, 1982, on all affected engines containing P/N 868630-1, -2, -3, or -4 or P/N 895539-1, -2, -3, or -4 third stage turbine wheels, or upon next removal of the third stage turbine wheel, after September 9, 1982, whichever occurs earlier, either: (1) Remove curvic coupling gasket, P/N 868892-2, located forward of third stage turbine wheel, and replace it with a serviceable P/N 868892-9 curvic coupling gasket or subsequently approved part number gasket as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0300, dated September 9, 1981, or an equivalent approved by the Manager, Western Aircraft Certification Field Office; or, (2) Replace the third stage turbine wheel with a P/N 868630-7, P/N 868630-8, or an equivalent approved by the Manager, Western Aircraft Certification Field Office. NOTE: The P/N 868630-1, -2, -3, or -4 turbine wheel may be modified to the P/N 868630-7 third stage turbine wheel design by compliance with instructions provided in GTEC SB No. TPE331-72-0327, dated December 14, 1981, or an equivalent approved by the Manager, Western Aircraft Certification Field Office. (f) Remove the third stage turbine seal P/N 868259-1 and replace with a serviceable P/N 868259-2 or subsequently approved part number seal as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0380, dated November 17, 1982, or an equivalent approved by the Manager, Western Aircraft Certification Field Office, upon next removal of the third stage turbine wheel from all affected engines after February 1, 1983. (g) Remove third stage turbine stators P/N 868379-1 from all affected engines and replace with a serviceable P/N 868379-3 or subsequently approved part number stator, as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0384, dated November 17, 1982, or an equivalent approved by the Manager, Western Aircraft Certification Field Office, no later than next removal of the third stage turbine wheel after 2000 hours stator third stage total time, or time since new, or time since overhaul. NOTE: Operating time and cycles are to be recorded in the Engine Log Book for P/N 868379-3 and subsequent P/N turbine stators. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (i) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, Attn: Customer Service Engineering, Department 77-4, P.O. Box 5217, Phoenix, Arizona 85010. These documents also may be examined at FAA Rules Docket, Federal Aviation Administration, New England Region, Office of the Regional Counsel, Burlington, Massachusetts 01803. This AD supersedes AD 82-27-07, Amendment 39-4528, which became effective January 7, 1983. This amendment becomes effective January 25, 1984. FOOTER:
Document Text
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AD Final Rules - DRS_84-01-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 84-01-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. Subject: Third Stage Turbine Wheels Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 01/25/1984 Make: Honeywell International Inc. Model: TPE331-1 | TPE331-1U | TPE331-1UA | TPE331-2 | TPE331-2U | TPE331-2UA | TPE331-3 | TPE331-3U | TPE33...Show more Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185 AIRWORTHINESS DIRECTIVES FINAL RULES: 84-01-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-4792 AD NUMBER: 84-01-04 SUBJECT HEADING: GARRETT TURBINE ENGINE COMPANY Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 Series Engines. ACTION: SUMMARY: DATES: Effective January 25, 1984. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 84-01-04 GARRETT TURBINE ENGINE COMPANY (GTEC, formerly AiResearch Manufacturing Company of Arizona): Amendment 39-4792. Applies to GTEC Engine Models TSE331-3 and TPE331-1, -2, -3, -5, and -6 series engines. Compliance required as indicated, unless already accomplished. To reduce the possibility of rapid destruction of the engine turbine, accomplish the following: (a) Inspect in accordance with the following schedule, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels, identified by serial number (S/N) below, in accordance with paragraph 2 of GTEC Service Bulletin (SB) No. TPE/TSE331-72-0351, dated April 14, 1982, or equivalent approved by the Manager, Western Aircraft Certification Field Office. Remove from service, prior to further flight, third stage turbine wheels not meeting the inspection criteria. Third stage turbine wheels meeting the inspection criteria may be continued in service to the life limits of paragraph (d) herein. WHEEL TOTAL CYCLES INSPECT Less than 900 Before accumulation of 1000 cycles. 900 or more, and less than 1000 Within the next 100 cycles. 1000 or more, and less than 1200 Within the next 50 cycles. More than 1200 Within the next 10 cycles. NOTES: For purposes of this AD, a cycle is defined as any operating sequence involving an engine start, aircraft takeoff and landing, followed by engine shutdown, and one cycle shall be counted for each such operational sequence. For purposes of this AD, turbine wheels which comply with paragraph 2 of GTEC SB No. TPE/TSE/331-72-0351 or an equivalent approved by the Manager, Western Aircraft Certification Field Office, must have the SB annotated on the life limited parts log card which is located either with the third stage wheel assembly or with the engine log book. Serial Numbers: 0-01345-419 0-01345-1313 0-01345-2372 9-01345-15426 420 1314 2374 15427 421 1315 2375 15428 422 1316 2376 15429 423 1317 2377 15432 424 1318 2378 15433 425 1319 2379 18246 426 1320 2380 18247 428 1321 2381 18248 430 1322 2382 18250 431 1323 2383 18251 432 1324 2384 18252 433 1325 2385 18253 435 1326 2386 18256 436 1328 2387 18258 437 1329 2388 18259 438 1330 2529 18260 439 1331 3106 18262 440 1332 3107 18263 441 1335 3109 18264 442 1336 3110 18265 443 1338 3111 18266 444 2336 3112 18286 446 2337 3113 18287 447 2338 3114 18288 448 2339 3118 18289 449 2340 3119 18302 450 2341 3121 18304 451 2342 3122 18305 452 2343 3123 18310 453 2344 3124 18311 454 2345 3125 18316 455 2346 3126 18317 456 2347 3127 18318 458 2348 3128 18320 459 2349 3129 18321 461 2350 3130 18323 463 2351 3131 18324 1296 2352 3121 18325 1298 2353 3133 18326 1299 2354 3124 18328 1301 2355 3135 18329 1302 2356 3136 18330 1304 2357 3140 18414 1305 2358 3141 18415 1306 2359 3145 1307 2364 3146 1308 2365 3147 1309 2366 3149 1311 2367 3150 1312 2369 3152 2371 3153 3737 (b) Remove from service according to the following schedule, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels identified by S/N below: WHEEL TOTAL CYCLES REMOVE* Less than 1300. Before accumulation of 1500 cycles. 1300 or more and less than 2550. Before accumulation of 2600 cycles or within the next 200 cycles whichever occurs first. 2550 or more. Within the next 50 cycles. *No wheel listed below may exceed 1500 total cycles in service after June 1, 1983. Serial Numbers: 0-01345-18350 0-01345-20025 0-01345-21873 18623 20026 21874 18659 20130 21875 18660 20588 21876 18663 20589 21877 18669 20590 21878 18672 20591 21879 18673 20592 21880 18674 20593 21881 18676 20594 21882 18677 20595 21883 18678 20596 21884 19294 20597 21885 19295 20598 21886 19321 20599 21887 19980 20600 21888 19983 20601 21889 19984 20602 21890 19985 20603 21891 19986 20604 21892 19987 20605 21893 19988 20606 21894 19989 20607 21895 19990 20608 21896 19991 20609 21897 19992 20611 21898 19993 20612 21899 19994 20613 21900 19995 20614 21903 20615 19996 20616 21904 19997 20617 21905 19998 20618 21906 19999 20619 21907 20000 20620 21908 20001 20621 21909 20002 20622 21910 20003 20623 21911 20004 20624 21914 20008 20625 22332 20009 20626 22333 20010 20627 20011 20628 20012 20629 20013 20630 20014 20631 20015 20632 20016 20633 20017 20634 20018 20635 20019 20637 20020 20779 20021 21869 20022 21870 20023 21871 20024 21872 (c) Inspect, prior to accumulating 2600 total wheel cycles, P/N 868630-1, -2, -3, -4, and -7 third stage turbine wheels introduced into service on or after March 24, 1978, and not listed by S/N in paragraph (a) or (b) herein, in accordance with paragraph 2 of GTEC SB No. TPE/TSE/331-72-0351, dated April 14, 1982, or equivalent approved by the Manager, Western Aircraft Certification Field Office. Remove from service prior to further flight third stage turbine wheels not meeting the inspection criteria. Third stage turbine wheels meeting the inspection criteria may be continued in service to the life limits of paragraph (d) herein. (d) Remove from service the following turbine wheels within the cyclic life limits specified below: WHEEL STAGE PART NUMBER CYCLE LIFE First 867569-1, -3, -7 5700 cycles Second 868272-1, -2, -3, -4 5400 cycles Third 868630-1, -2, -3, -4, -7 3600 cycles Third 868630-8 4300 cycles Third 895539-1, -2, -3, -4 2000 cycles Turbine wheels listed in this paragraph introduced into service prior to March 24, 1978, were not required to have their cyclic lives recorded. As of the effective date of this AD, lives of these wheels shall be converted to cycles by crediting each hour of operation 9 with 1.5 cycles (i.e.: 3500 hrs x 1.5 = 5250 cycles). Actual cycles, if known, may be used in lieu of this conversion. Thereafter, wheel operating life shall be accrued in cycles. Remove from service in accordance with the following schedule P/N 895539-1, -2, -3, and -4 third stage turbine wheels which exceed the above-listed cyclic limits after converting from hours to cycles: WHEEL TOTAL CYCLES REMOVE 2,000 to 3,750 Within the next 300 cycles. 3,751 to 4,500 Within the next 175 cycles. 4,501 to 5,250 Within the next 75 cycles. Remove from service within the next 300 cycles or 10 months in service, whichever comes first after the effective date of this amendment, P/N 867569-1, -3, -7, P/N 868272-1, -2, -3, -4, and P/N 868630-1, -2, -3, -4, -7 turbine wheels which exceed the above-listed cyclic limits after converting from hours to cycles. (e) Prior to accumulating an additional 2700 cycles after February 11, 1982, on all affected engines containing P/N 868630-1, -2, -3, or -4 or P/N 895539-1, -2, -3, or -4 third stage turbine wheels, or upon next removal of the third stage turbine wheel, after September 9, 1982, whichever occurs earlier, either: (1) Remove curvic coupling gasket, P/N 868892-2, located forward of third stage turbine wheel, and replace it with a serviceable P/N 868892-9 curvic coupling gasket or subsequently approved part number gasket as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0300, dated September 9, 1981, or an equivalent approved by the Manager, Western Aircraft Certification Field Office; or, (2) Replace the third stage turbine wheel with a P/N 868630-7, P/N 868630-8, or an equivalent approved by the Manager, Western Aircraft Certification Field Office. NOTE: The P/N 868630-1, -2, -3, or -4 turbine wheel may be modified to the P/N 868630-7 third stage turbine wheel design by compliance with instructions provided in GTEC SB No. TPE331-72-0327, dated December 14, 1981, or an equivalent approved by the Manager, Western Aircraft Certification Field Office. (f) Remove the third stage turbine seal P/N 868259-1 and replace with a serviceable P/N 868259-2 or subsequently approved part number seal as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0380, dated November 17, 1982, or an equivalent approved by the Manager, Western Aircraft Certification Field Office, upon next removal of the third stage turbine wheel from all affected engines after February 1, 1983. (g) Remove third stage turbine stators P/N 868379-1 from all affected engines and replace with a serviceable P/N 868379-3 or subsequently approved part number stator, as prescribed in paragraph 2 of GTEC SB No. TPE331-72-0384, dated November 17, 1982, or an equivalent approved by the Manager, Western Aircraft Certification Field Office, no later than next removal of the third stage turbine wheel after 2000 hours stator third stage total time, or time since new, or time since overhaul. NOTE: Operating time and cycles are to be recorded in the Engine Log Book for P/N 868379-3 and subsequent P/N turbine stators. (h) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate aircraft to a base for the accomplishment of inspections or modifications required by this AD. (i) Alternative inspections, modifications, or other actions which provide an equivalent level of safety may be used when approved by the Manager, Western Aircraft Certification Field Office, FAA Northwest Mountain Region. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Garrett Turbine Engine Company, Attn: Customer Service Engineering, Department 77-4, P.O. Box 5217, Phoenix, Arizona 85010. These documents also may be examined at FAA Rules Docket, Federal Aviation Administration, New England Region, Office of the Regional Counsel, Burlington, Massachusetts 01803. This AD supersedes AD 82-27-07, Amendment 39-4528, which became effective January 7, 1983. This amendment becomes effective January 25, 1984. FOOTER:
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