| AD Number | 67-07-05 | Status | Active |
| Effective Date | February 25, 1967 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-353 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Kelowna Flightcraft R & D Ltd. |
| Model(s) | 240 Series 340 440 |
67-07-05 GENERAL DYNAMICS: Amdt. 39-353 Part 39 Federal Register February 25, 1967. Applies to General Dynamics Model 240 Airplanes Equipped with Rolls Royce Mk 542-4 Engines and Dowty Rotol (c)R245/4-40-4.5/13 Propellers in Accordance with General Dynamics Supplemental Type Certificate SA1054WE (hereinafter referred to as the CV-600), and General Dynamics Model 340 and 440 Airplanes Equipped with Rolls Royce MK542-4 Engines and Dowty Rotol (c)R245/4-40-4.5/13 or Dowty Rotol (c)R259/4-40-4.5/17 Propellers in Accordance with General Dynamics Supplemental Type Certificate SA1096WE (hereinafter referred to as the CV-640).
Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished.
To prevent unwanted withdrawal of the propeller flight fine pitch stops, de-activate the propeller-gust lock interlock system (P/N 2D3120907-1) on CV-600 and CV-640 airplanes in accordance with the following:
(a) CV-600
(1) Disconnect the gust lock switches from the propeller control circuit in accordance with the instruction outlined in General Dynamics Alert Service Bulletin 600 (240D) S.B. No. A61-5 or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(2) Concurrently, with the modification described in (a) (1), incorporate an FAA approved revision to the Normal Procedures Section of the FAA approved Model 600- (240D) Airplane Flight Manual (General Dynamics Report CS-65-021) which deletes all reference to the gust lock handle control of the propeller flight fine pitch stops.
(b) CV-640
(1) Disconnect the gust lock switches from the propeller control circuit in accordance with the instructions outlined in General Dynamics Alert Service Bulletin 640 (340D) S.B. No. A61-4 or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region.
(2) Concurrently with the modification described in (b) (1), incorporate an FAA approved revision to the Normal Procedures Section of the FAA approved Model 640- (340D) Airplane Flight Manual (General Dynamics Report CS-65-024) which deletes all reference to the gust lock handle control of the propeller flight fine pitch stops.
This directive effective February 25, 1967.