AD 65-14-05
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Lockheed Martin Corporation | 1329-23A | LOCKHEED Model 1329 Aircraft |
| aircraft | Lockheed Martin Corporation | 1329-23D | LOCKHEED Model 1329 Aircraft |
Unsafe Condition
Improper engine fire and overheat warning indications due to incorrect connections in the engine fire (forward) and overheat (aft) detector electrical systems.
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Required Actions
Inspect engine fire and overheat detector electrical systems to ensure proper connections to the correct fire warning control unit. Use a Simpson 260 meter or equivalent to check resistance and apply heat with a heater blower to verify decreasing resistance readings. Correct discrepancies using Lockheed Drawing No. JR156 if results are unsatisfactory.
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Compliance Time
within the next 25 hours' time in service after the effective date of this AD unless already accomplished
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Affected Aircraft
Lockheed Model 1329 Aircraft, serial numbers 5001 through 5057
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Federal Register Abstract
Engine Detector Electrical Systems
Applicability Source Text
Show captured applicability text from the source AD
AD Final Rules - DRS_65-14-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 65-14-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 1329 Aircraft Subject: Engine Detector Electrical Systems Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/26/1965 Make: Lockheed Martin Corporation Model: 1329-23A | 1329-23D Product Type: Aircraft Product Subtype: Large Airplane Affected AD: Superseded AD: Affected By: Superseded By: Service/Office: Office of Primary Responsibility: CFR Part Reference: Part 39 Comments: Updated RGL applicability to match AD applicability; CAR C-11-185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: 65-14-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-95 AD NUMBER: 65-14-05 SUBJECT HEADING: LOCKHEED Model 1329 Aircraft ACTION: SUMMARY: DATES: Effective June 26, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 65-14-05 LOCKHEED: Amdt. 39-95 Part 39 Federal Register June 26, 1965. Applies to Model 1329 Aircraft Serial Numbers 5001 through 5057. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent improper engine fire and overheat warning indications, accomplish the following: Inspect in the following manner all engine fire (forward) and overheat (aft) detector electrical systems to ascertain that each detector is properly connected to the correct fire warning control unit: (a) Disconnect electrical connector from the control unit corresponding to the detector element to be checked. (b) Connect one lead of a Simpson 260 meter, or equivalent, to pin C or D of the fire warning control unit connector, ships, wiring, and one lead to ground. (c) Set the meter to read a resistance of 10,000 Ohms or greater, depending on the unit being checked and the temperature of the unit. (d) Apply heat to a segment of the detector element being checked, using a heater blower with a temperature range of 500 degrees to 750 degrees F., or equivalent, and observe the meter reading. The blower should be held approximately 1/2 inch from the element. Make sure no wind interferes to cut down the heat conduction to the element and to assure a good meter reading. (e) In approximately 5 to 10 seconds of elapsed time after application of heat, the meter reading should decrease at a moderate rate. A decreasing resistance reading indicates correct wire connections. (f) After the above procedure is followed and the results are not as required, a complete check of the fire warning circuitry for the engine in error must be made using Lockheed Drawing No. JR156 (wiring diagram). Correct all discrepancies. (g) When all circuits are in proper operating condition, the aircraft may be returned to service. Other means of compliance with the requirements of this directive may be utilized if approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (Lockheed Alert Service Bulletins Nos. 329-202 and 329-202A cover this same subject.) This directive effective June 26, 1965. FOOTER:
Document Text
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AD Final Rules - DRS_65-14-05.html Copy URL Print/Save as PDF Document Versions Feedback Details AD Number: 65-14-05 Document Type: AD Final Rules Docket Number: Unknown Subject Heading: LOCKHEED Model 1329 Aircraft Subject: Engine Detector Electrical Systems Status: Current Citation: This information is not available. Citation Publish Date: Effective Date: 06/26/1965 Make: Lockheed Martin Corporation Model: 1329-23A | 1329-23D Product Type: Aircraft Product Subtype: Large Airplane 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: 65-14-05 CITATION: This information is not available. PAGE NUMBER: DOCKET NUMBER: Unknown AMENDMENT: 39-95 AD NUMBER: 65-14-05 SUBJECT HEADING: LOCKHEED Model 1329 Aircraft ACTION: SUMMARY: DATES: Effective June 26, 1965. ADDRESSES: FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: REGULATORY TEXT: 65-14-05 LOCKHEED: Amdt. 39-95 Part 39 Federal Register June 26, 1965. Applies to Model 1329 Aircraft Serial Numbers 5001 through 5057. Compliance required within the next 25 hours' time in service after the effective date of this AD unless already accomplished. To prevent improper engine fire and overheat warning indications, accomplish the following: Inspect in the following manner all engine fire (forward) and overheat (aft) detector electrical systems to ascertain that each detector is properly connected to the correct fire warning control unit: (a) Disconnect electrical connector from the control unit corresponding to the detector element to be checked. (b) Connect one lead of a Simpson 260 meter, or equivalent, to pin C or D of the fire warning control unit connector, ships, wiring, and one lead to ground. (c) Set the meter to read a resistance of 10,000 Ohms or greater, depending on the unit being checked and the temperature of the unit. (d) Apply heat to a segment of the detector element being checked, using a heater blower with a temperature range of 500 degrees to 750 degrees F., or equivalent, and observe the meter reading. The blower should be held approximately 1/2 inch from the element. Make sure no wind interferes to cut down the heat conduction to the element and to assure a good meter reading. (e) In approximately 5 to 10 seconds of elapsed time after application of heat, the meter reading should decrease at a moderate rate. A decreasing resistance reading indicates correct wire connections. (f) After the above procedure is followed and the results are not as required, a complete check of the fire warning circuitry for the engine in error must be made using Lockheed Drawing No. JR156 (wiring diagram). Correct all discrepancies. (g) When all circuits are in proper operating condition, the aircraft may be returned to service. Other means of compliance with the requirements of this directive may be utilized if approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region. (Lockheed Alert Service Bulletins Nos. 329-202 and 329-202A cover this same subject.) This directive effective June 26, 1965. FOOTER:
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
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