AD 89-24-03
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| engine | Continental Motors | TSIO-520-UB | TELEDYNE CONTINENTAL MOTORS (TCM) Model TSIO-520-UB Engines |
Unsafe Condition
Cracking of the turbocharger inlet assembly part number 642668, especially in the weld joints just above the turbine inlet temperature boss, which could result in engine compartment fire.
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Required Actions
Visually inspect turbocharger inlet assembly P/N 642668 for cracks in the weld joints. If a crack is found, replace P/N 642668 with P/N 646795. Make log book entry showing compliance.
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Compliance Time
At the next 100 hour inspection or annual inspection, or within 100 flight hours, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 100 flight hours.
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Affected Aircraft
TCM Model TSIO-520-UB engines, serial numbers 515000 thru 515999 and 527000 thru 527070, and all remanufactured/overhauled engines of this model with P/N 642668 turbocharger inlet assembly.
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Federal Register Abstract
Turbocharger Inlet Assembly
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_89-24-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-24-03 Document Type: AD Final Rules Docket Number: 89-ANE-19 Subject Heading: TELEDYNE CONTINENTAL MOTORS (TCM) Model TSIO-520-UB Engines Subject: Turbocharger Inlet Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/18/1990 Make: Continental Motors Model: TSIO-520-UB Product Type: Engine Product Subtype: Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 89-24-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ANE-19 AMENDMENT: 39-6386 AD NUMBER: 89-24-03 SUBJECT HEADING: TELEDYNE CONTINENTAL MOTORS (TCM) Model TSIO-520-UB Engines ACTION: SUMMARY: DATES: Effective June 18, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-24-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-6386. Correction issued on May 8, 1990. Docket No. 89-ANE-19. Applicability: TCM Model TSIO-520-UB engines, serial numbers 515000 thru 515999 and 527000 thru 527070, and to all remanufactured and overhauled engines of this model, regardless of serial number, which are equipped with part number (P/N) 642668 turbocharger inlet assembly. Compliance: Required at the next 100 hour inspection or annual inspection, or within 100 flight hours, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 100 flight hours. To prevent possible cracking of the turbocharger inlet assembly which could result in engine compartment fire, accomplish the following: (a) Visually inspect turbocharger inlet assembly P/N 642668 for cracks especially in the weld joints just above the turbine inlet temperature boss. If a crack is found, replace P/N 642668 with P/N 646795 turbocharger inlet assembly, prior to further flight. (b) Make appropriate log book entry showing compliance with this AD. NOTES: (1) Beechcraft Aircraft Corporation Service Communique No. 70, dated October 28, 1983, refers to this subject. NOTES: (2) When determining the P/N assembly installed in order to comply with this AD, a distinguishing feature of the P/N 646795 turbocharger inlet assembly is 2 ribs (approximately 0.25 inches in height, 0.1 inches in width, and 2.1 inches in length) on the top of the turbocharger mating flange. NOTES: (3) If P/N 642668 is not installed, no action is required. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This amendment 39-6386 (AD 89-24-03) became effective on December 4, 1989. This correction becomes effective on June 18, 1990. FOOTER:
Document Text
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AD Final Rules - DRS_89-24-03.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 89-24-03 Document Type: AD Final Rules Docket Number: 89-ANE-19 Subject Heading: TELEDYNE CONTINENTAL MOTORS (TCM) Model TSIO-520-UB Engines Subject: Turbocharger Inlet Assembly Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/18/1990 Make: Continental Motors Model: TSIO-520-UB 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: AIRWORTHINESS DIRECTIVES FINAL RULES: 89-24-03 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: 89-ANE-19 AMENDMENT: 39-6386 AD NUMBER: 89-24-03 SUBJECT HEADING: TELEDYNE CONTINENTAL MOTORS (TCM) Model TSIO-520-UB Engines ACTION: SUMMARY: DATES: Effective June 18, 1990. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 89-24-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-6386. Correction issued on May 8, 1990. Docket No. 89-ANE-19. Applicability: TCM Model TSIO-520-UB engines, serial numbers 515000 thru 515999 and 527000 thru 527070, and to all remanufactured and overhauled engines of this model, regardless of serial number, which are equipped with part number (P/N) 642668 turbocharger inlet assembly. Compliance: Required at the next 100 hour inspection or annual inspection, or within 100 flight hours, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 100 flight hours. To prevent possible cracking of the turbocharger inlet assembly which could result in engine compartment fire, accomplish the following: (a) Visually inspect turbocharger inlet assembly P/N 642668 for cracks especially in the weld joints just above the turbine inlet temperature boss. If a crack is found, replace P/N 642668 with P/N 646795 turbocharger inlet assembly, prior to further flight. (b) Make appropriate log book entry showing compliance with this AD. NOTES: (1) Beechcraft Aircraft Corporation Service Communique No. 70, dated October 28, 1983, refers to this subject. NOTES: (2) When determining the P/N assembly installed in order to comply with this AD, a distinguishing feature of the P/N 646795 turbocharger inlet assembly is 2 ribs (approximately 0.25 inches in height, 0.1 inches in width, and 2.1 inches in length) on the top of the turbocharger mating flange. NOTES: (3) If P/N 642668 is not installed, no action is required. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This amendment 39-6386 (AD 89-24-03) became effective on December 4, 1989. This correction becomes effective on June 18, 1990. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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