# AD 61-22-06: Elevator Control Mast Castings

- Type: Airworthiness directive
- Status: Current
- Products: Air Trading Army B-34, Navy PV-1 and 18
- Effective: November 21, 1961
- Superseded by: Nothing supersedes this AD
- Product type: Aircraft, Large airplane
- Registered aircraft: 2 may be affected, by airframe or engine model (OpenAirDocs)
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/EE816066859034CD862569B30071D644.0001
- DRS record last changed: May 30, 2024
- Page: https://openairdocs.org/ad/61-22-06

## The airworthiness directive

61-22-06 LOCKHEED: Amdt. 351 Part 507 Federal Register October 21, 1961. Applies to All PV-1, B-34, and 18 Series Aircraft Having Elevator Control Mast Assembly Castings P/N 11467 or 56045.

Compliance required within the next 100 hours' time in service after effective date.

As a result of reported cracks in the elevator control mast assembly castings, the following inspections and installation procedures are required unless already accomplished:

  (a) Inspect the elevator control mast assembly casting prior to removal, for mating marks to insure correct assembly. If none exist, determine the proper position of the cap on the mast and mark the assembly with a paint stripe or equivalent to insure future correct assembly of parts.

  (b) Remove the elevator control mast assembly casting and inspect both the control mast and the cap castings for cracks in the attach bolt lugs using dye penetrant methods or equivalent. If any cracks are found, the casting must be replaced prior to further flight.

  (c) Install the four AN 5-16A bolts in the casting in place on the aircraft, with the lockplate between the cast cap and the casting on the aft side, and with the mating marks matched. Torque the two bolts which go through the lockplate to 50-70 inch-pounds, then the other two bolts to the same range of torque values. Measure the gap between the forward side of the castings. Fabricate an aluminum alloy shim, +0.002 to +0.005-inch greater than the measured gap. Remove the forward bolts, install the shim, replace the bolts, and torque all bolts to 100-140 inch-pounds. Ensure that the shim does not contact the surrounding structure.

This directive effective November 21, 1961.

## Affected data sheets (2) (OpenAirDocs)

The type certificate data sheets whose models the AD names.

- [TCDS LTC AL-13](https://openairdocs.org/tcds/LTC%20AL-13): Air Trading Corporation; names 2 of 3 models: Navy PV-1, Army B-34
- [TCDS A-723](https://openairdocs.org/tcds/A-723): Lockheed Martin Aeronautics Company; names 1 of 1 models: 18

## Registered aircraft it may apply to (OpenAirDocs)

Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment.

- Aircraft: 2 (2 by airframe model, 0 by engine model)
- Makers: Lockheed 2

Models with the most aircraft:

- [Lockheed 18](https://openairdocs.org/model/lockheed-18): 2 aircraft (airframe model)

All 1 models: https://openairdocs.org/ad/61-22-06/models.md
Every aircraft: https://openairdocs.org/ad/61-22-06/aircraft.md

Its text cites no advisory circulars or STCs.

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