AD 77-08-04
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Textron Aviation Inc. | 58P | Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes |
| aircraft | Textron Aviation Inc. | 58PA | Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes |
| aircraft | Textron Aviation Inc. | 58TC | Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes |
| aircraft | Textron Aviation Inc. | 58TCA | Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes |
Unsafe Condition
Failure of engine mount fitting bolts that are not NAS bolts (National Aerospace Standard) could result in engine separation from the airframe.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect engine mount fitting bolts to verify NAS bolts are installed. Replace non-NAS bolts with NAS1104-7 or NAS1104-7M bolts using new AN960-416L washers and MS21042-4 self-locking nuts, torque to 50-70 inch-pounds. Document compliance in aircraft maintenance records.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
within the next 100 hours' time in service after the effective date of this AD, with a possible extension up to 110 hours total
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
BEECH Models 58P, 58PA, 58TC, 58TCA with specified serial numbers: Models 58P/58PA (TJ-46 thru TJ-74, TJ-76, TJ-78-80, TJ-82-85, TJ-88, TJ-89); Models 58TC/58TCA (TK-7-18, TK-20, TK-21, TK-25, TK-27, TK-30, TK-32, TK-34, TK-37, TK-38)
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Federal Register Abstract
Engine Mount Fittings
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_77-08-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-08-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes Subject: Engine Mount Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/26/1977 Make: Textron Aviation Inc. Model: 58P | 58PA | 58TC | 58TCA Product Type: Aircraft Product Subtype: Small Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: AIRWORTHINESS DIRECTIVES FINAL RULES: 77-08-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2875 AD NUMBER: 77-08-04 SUBJECT HEADING: Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes ACTION: SUMMARY: DATES: Effective May 26, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-08-04 BEECH: Amendment 39-2875. Applies to Models 58P and 58PA (Serial Numbers TJ-46 thru TJ-74, TJ-76, TJ-78 thru TJ-80, TJ-82 thru TJ-85, TJ-88 and TJ-89) and Models 58TC and 58TCA (Serial Numbers TK-7 thru TK-18, TK-20, TK-21, TK-25, TK-27, TK-30, TK-32, TK-34, TK-37 and TK-38) airplanes certified in all categories. Compliance: Required as indicated, unless already accomplished. To assure that the correct bolts are installed in the engine mount fittings, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A. Inspect, and if necessary, replace the engine mount fitting bolts in accordance with the following procedures: 1. Remove the access covers just aft of the engine firewall on the upper and lower inboard and outboard sides of both right and left engine nacelles to gain access to the engine mount fittings (four per engine). 2. Visually inspect the two attach bolts in each fitting (eight bolts for each engine) to determine that NAS bolts are installed. NAS bolts may be identified by a concave indentation on the bolt head and NAS stamped on the bolt head. 3. If NAS bolts are installed, reinstall the access covers and proceed to Paragraph A.6. below. If NAS bolts are not installed, proceed with Paragraphs A.4. thru A.6. below. 4. Using engine hoist and sling as noted in the engine removal section of the applicable Beech Maintenance Manual, lift the engine weight off of the engine mount fittings. 5. Remove any of the engine mount fitting bolts that are not NAS bolts (remove and replace one bolt at a time). Discard the bolts and self-locking nuts removed and install new NAS1104-7 or NAS1104-7M bolts using new AN960-416L washers and new MS21042-4 self-locking nuts. Torque bolts to 50 to 70 inch pounds. Reinstall access covers and proceed to Paragraph A.6. 6. Make proper entry in the aircraft maintenance records that are to be transferred with the aircraft showing compliance with this AD. B. Compliance time for this AD may be extended up to 10 hours to a maximum of 110 hours to allow compliance with this AD at previously scheduled maintenance periods. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D. Beechcraft Service Instructions No. 0875-038 covers the subject matter of this AD. This amendment becomes effective May 26, 1977. FOOTER:
Document Text
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AD Final Rules - DRS_77-08-04.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 77-08-04 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes Subject: Engine Mount Fittings Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 05/26/1977 Make: Textron Aviation Inc. Model: 58P | 58PA | 58TC | 58TCA 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: 77-08-04 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-2875 AD NUMBER: 77-08-04 SUBJECT HEADING: Airworthiness Directives; BEECH Models 58P, 58PA, 58TC and 58TCA Airplanes ACTION: SUMMARY: DATES: Effective May 26, 1977. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 77-08-04 BEECH: Amendment 39-2875. Applies to Models 58P and 58PA (Serial Numbers TJ-46 thru TJ-74, TJ-76, TJ-78 thru TJ-80, TJ-82 thru TJ-85, TJ-88 and TJ-89) and Models 58TC and 58TCA (Serial Numbers TK-7 thru TK-18, TK-20, TK-21, TK-25, TK-27, TK-30, TK-32, TK-34, TK-37 and TK-38) airplanes certified in all categories. Compliance: Required as indicated, unless already accomplished. To assure that the correct bolts are installed in the engine mount fittings, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A. Inspect, and if necessary, replace the engine mount fitting bolts in accordance with the following procedures: 1. Remove the access covers just aft of the engine firewall on the upper and lower inboard and outboard sides of both right and left engine nacelles to gain access to the engine mount fittings (four per engine). 2. Visually inspect the two attach bolts in each fitting (eight bolts for each engine) to determine that NAS bolts are installed. NAS bolts may be identified by a concave indentation on the bolt head and NAS stamped on the bolt head. 3. If NAS bolts are installed, reinstall the access covers and proceed to Paragraph A.6. below. If NAS bolts are not installed, proceed with Paragraphs A.4. thru A.6. below. 4. Using engine hoist and sling as noted in the engine removal section of the applicable Beech Maintenance Manual, lift the engine weight off of the engine mount fittings. 5. Remove any of the engine mount fitting bolts that are not NAS bolts (remove and replace one bolt at a time). Discard the bolts and self-locking nuts removed and install new NAS1104-7 or NAS1104-7M bolts using new AN960-416L washers and new MS21042-4 self-locking nuts. Torque bolts to 50 to 70 inch pounds. Reinstall access covers and proceed to Paragraph A.6. 6. Make proper entry in the aircraft maintenance records that are to be transferred with the aircraft showing compliance with this AD. B. Compliance time for this AD may be extended up to 10 hours to a maximum of 110 hours to allow compliance with this AD at previously scheduled maintenance periods. C. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. D. Beechcraft Service Instructions No. 0875-038 covers the subject matter of this AD. This amendment becomes effective May 26, 1977. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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