AD 75-18-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Taylorcraft 2000, LLC | F19 | Airworthiness Directives; Taylorcraft Model F19 |
Unsafe Condition
Engine mount bolts (P/N AN6-44) have suspect strength, and burrs or sharp edges on engine mount and engine bosses could cause damage or failure.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Remove and inspect engine mount components including bolts, spacers, hoses, bushings, washers, nuts, pins, and seats. Replace suspect AN6-44 bolts, spacers, and cup washers with Taylorcraft Kit #SK75-001 or FAA approved parts. Torque bolts to 180-190 inch-lb without overtorque. Check bushing alignment after torquing. Reinspect components between 25-50 hours and every 100 hours thereafter for wear/deterioration, replacing as needed.
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Compliance Time
Before further flight
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Affected Aircraft
Taylorcraft Model F19, all serial numbers
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Federal Register Abstract
Engine Mount Bolts
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_75-18-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-18-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Taylorcraft Model F19 Subject: Engine Mount Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Taylorcraft 2000, LLC Model: F19 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 75-18-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2344 AD NUMBER: 75-18-05 SUBJECT HEADING: Airworthiness Directives; Taylorcraft Model F19 ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-18-05 TAYLORCRAFT AVIATION CORPORATION: Amendment 39-2344. Applies to Model F19, all serial numbers. Before further flight, unless already accomplished: 1. Remove engine mount bolts (P/N AN6-44), spacer (P/N 530627), hose (P/N AN8848-6), bushings (P/N 53074), cup washers (P/N 530741), nut (P/N AN310-6), pin (P/N AN380-3-3), and engine mount seats (P/N 530626) on each of four (4) bolt assemblies, and inspect for damages. (Note: The AN6-44 bolt strength is suspect.) Remove any burr and sharp edges on engine mount and engine bosses. Replace bolt, spacer, and cup washers with those supplied by Taylorcraft Kit #SK75-001 dated May 15, 1975, or subsequent FAA approved parts. Replace other parts found defective with parts supplied by Taylorcraft or subsequent FAA approved parts. Taylorcraft Service Bulletin #75-002 dated March 20, 1975, or subsequent FAA approved revisions, concerns this same subject. Torque bolts to 180-190 inch-lb by tightening nut. Do not overtorque. Caution: Do not apply torque wrench on bolt head. Tightening bolt head will give incorrect value of torque due to presence of shank friction. Also turning of bolt may scratch the bolt shank, causing stress riser and premature failure. 2. Check after torquing for proper alignment of rubber (shock) bushing. 3. Between twenty-five (25) and fifty (50) hours time in service after initial accomplishment of Items 1 and 2, remove engine mount bolts, spacer, hose, bushings, cup washers, nut, pin, and engine mount seats on each of four (4) bolt assemblies and inspect for any signs of wear and deterioration. If evidence of such is found, replace with parts furnished by Taylorcraft. Reassemble using the procedures of Items 1 and 2. 4. Every one hundred (100) hours time in service after accomplishment of Item 3, repeat the actions required in Item 3. 5. A special flight permit per FAR 21.197 may be issued to allow ferrying of the aircraft to a qualified inspection and repair facility. This amendment is effective August 25, 1975, and was effective upon receipt for all recipients of the air mail letter dated May 19, 1975, which contained this amendment. FOOTER:
Document Text
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AD Final Rules - DRS_75-18-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 75-18-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; Taylorcraft Model F19 Subject: Engine Mount Bolts Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: Make: Taylorcraft 2000, LLC Model: F19 Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 75-18-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2344 AD NUMBER: 75-18-05 SUBJECT HEADING: Airworthiness Directives; Taylorcraft Model F19 ACTION: SUMMARY: DATES: ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 75-18-05 TAYLORCRAFT AVIATION CORPORATION: Amendment 39-2344. Applies to Model F19, all serial numbers. Before further flight, unless already accomplished: 1. Remove engine mount bolts (P/N AN6-44), spacer (P/N 530627), hose (P/N AN8848-6), bushings (P/N 53074), cup washers (P/N 530741), nut (P/N AN310-6), pin (P/N AN380-3-3), and engine mount seats (P/N 530626) on each of four (4) bolt assemblies, and inspect for damages. (Note: The AN6-44 bolt strength is suspect.) Remove any burr and sharp edges on engine mount and engine bosses. Replace bolt, spacer, and cup washers with those supplied by Taylorcraft Kit #SK75-001 dated May 15, 1975, or subsequent FAA approved parts. Replace other parts found defective with parts supplied by Taylorcraft or subsequent FAA approved parts. Taylorcraft Service Bulletin #75-002 dated March 20, 1975, or subsequent FAA approved revisions, concerns this same subject. Torque bolts to 180-190 inch-lb by tightening nut. Do not overtorque. Caution: Do not apply torque wrench on bolt head. Tightening bolt head will give incorrect value of torque due to presence of shank friction. Also turning of bolt may scratch the bolt shank, causing stress riser and premature failure. 2. Check after torquing for proper alignment of rubber (shock) bushing. 3. Between twenty-five (25) and fifty (50) hours time in service after initial accomplishment of Items 1 and 2, remove engine mount bolts, spacer, hose, bushings, cup washers, nut, pin, and engine mount seats on each of four (4) bolt assemblies and inspect for any signs of wear and deterioration. If evidence of such is found, replace with parts furnished by Taylorcraft. Reassemble using the procedures of Items 1 and 2. 4. Every one hundred (100) hours time in service after accomplishment of Item 3, repeat the actions required in Item 3. 5. A special flight permit per FAR 21.197 may be issued to allow ferrying of the aircraft to a qualified inspection and repair facility. This amendment is effective August 25, 1975, and was effective upon receipt for all recipients of the air mail letter dated May 19, 1975, which contained this amendment. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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