| AD Number | 64-10-03 | Status | Active |
| Effective Date | Not specified | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-856 |
| Product Type | ["Appliance"] | Product Subtype | Not specified |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Davis Aircraft Products, Inc. |
| Model(s) | Safety Belts |
64-10-03 DAVIS AIRCRAFT PRODUCTS: Amdt. 39-856. Applies to All Aircraft Equipped With Davis Aircraft P/N FDC-2700 Series Safety Belts Manufactured Prior to September 1, 1963.
Compliance required within 125 hours' time in service after the effective date of this AD.
As the result of the investigation of reports of the failure of Davis Aircraft P/N FDC-2700 Series safety belts to latch properly, it has been determined that binding of the latching mechanism has resulted from the loss of lubricant during belt cleaning processes and also from certain manufacturing and assembly errors.
(a) Inspect each belt assembly as follows:
(1) Determine whether the buckle cover P/N FD-2674 is fully closed. If the buckle cover is fully opened and does not automatically snap back into the completely closed position when released, it may be assumed that the spring is damaged.
(2) Slowly raise the buckle cover taking careful note of any tendency of binding of the latching mechanism components. The buckle cover P/N FD-2674 and release latch P/N FD-2668 must be free to snap into the fully closed position when the buckle cover is opened and released.
(b) If any of the deficiencies specified in (a) are found, disassemble and further inspect the components to determine whether they meet the following requirements:
(1) The tangs or straight ends of the coil spring P/N FD-3007 shall be 9/32 plus 0- 1/16 inch and be straight throughout this length. (A bent tang will result in binding of the latching mechanism.)
(2) The release latch P/N FD-2668, shall be counterbored in one end to receive spring P/N FD-3007. The counterbored depth shall be 15/32 plus or minus 1/32 inch.
(c) Replace any components found to be defective under the inspection required in paragraph (b).
(d) Clean latch components and relubricate hexagonal headed hinge bolt and spring of the latching mechanism as required using Alemite No. 33 lubricant or equivalent.(e) After reassembly inspect the spring to determine that it is seated in the release latch retaining groove and apply spring tension by rotating the hexagonal headed hinge bolt from the unloaded position through two to three flats of the hexagonal head. Secure the hinge bolt in the hexagonal cutout in the buckle frame.
Effective June 5, 1964.
Revised October 8, 1969.