# AD 65-14-05: Engine Detector Electrical Systems

- Type: Airworthiness directive
- Status: Current
- Products: Lockheed Martin 1329-23A and 1329-23D
- Effective: June 26, 1965
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Large airplane
- Amendment: 39-95
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/C8BC2C17D53851248625697500488BD1.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/65-14-05

## The airworthiness directive

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) Applyheat 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.

## Affected data sheets (1) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS 2A15](https://openairdocs.org/tcds/2A15): Lockheed Martin Corporation; names 2 of 4 models: 1329-23D, 1329-23A

## Registered aircraft it may apply to (OpenAirDocs)

No registered aircraft matched the models it names.

Its text cites no advisory circulars or STCs.

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