- Effective
- January 25, 1967
- Models
- Navy PV-1, 500
- Data sheets
- TCDSA1SWTCDSLTC AL-13
- Registered aircraft
- 2 matched by model
- Product
- Aircraft · Large airplane
- Amendment
- 39-342
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
|---|---|---|---|
| FAA DRS HTML | 20 KB | d798854e…67726f1 | FAA DRS (API key needed) |
On this page
The airworthiness directive
67-03-04 HOWARD AND LOCKHEED: Amdt. 39-342 Part 39 Federal Register January 20, 1967. Applies to All Howard Model 500 Series Airplanes, and to Lockheed Model PV-1 Series Airplanes, Serial Numbers 5272, 5373, 5500, 5554, 5560, and 6642.
Compliance required as indicated.
To detect cracks in the flap cable support clamps, P/N 5-104268-1, unless already accomplished, within the next 10 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the date of the last inspection, remove the flap actuator clamp, P/N 5-104268-1, attached to the flap actuating cylinder, and inspect for cracks in the bend radius using dye penetrant or FAA-approved equivalent. Before further flight replace any clamp found cracked in accordance with Dee Howard Company, San Antonio, Texas, Drawing Number 13-0766-013-3, or later FAA Engineering and Manufacturing Branch approved equivalent. The inspection provisions of this AD may bediscontinued when P/N 5-104268-1 is replaced in accordance with this AD.
This directive effective January 25, 1967.
Affected TCDS · 2
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 2
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.