| AD Number | 75-10-01 | Status | Active |
| Effective Date | May 08, 1975 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2193 |
| Product Type | ["Aircraft"] | Product Subtype | ["Rotorcraft"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Hiller Aviation Siam Hiller Holdings, Inc. |
| Model(s) | UH-12D UH-12L UH-12L4 UH-12E UH-12E-L |
75-10-01 HILLER: Amendment 39-2193. Applies to all UH-12D (Mil. H-23D, OH- 23D), UH-12E (Mil. H-23F, OH-23F, OH-23G), UH-12E-L, UH-12L and UH-12L4 helicopters certificated in all categories except those helicopters modified to incorporate Allison 250 series engines in accordance with Supplemental Type Certificate No. SH177WE or SH178WE.
Compliance required within 50 hours' time in service after the effective date of this AD unless already accomplished.
In order to prevent power loss due to slippage of the mercury clutch in the rotor drive system:
(a) Remove the existing placard reading "No further flight if clutch engagement time exceeds 25 seconds."
(b) Install decal placard, part number 81426-7, on the instrument panel in accordance with Hiller Service Letter 21-4 dated April 3, 1975. The placard is to read, "No further flight if clutch engagement time exceeds 20 seconds."
(c) Incorporate the Hiller Rotorcraft Flight Manual Revision dated April 15, 1975in the applicable rotorcraft flight manual.
Equivalent modifications may be approved by the Chief, Aircraft Engineering Division, FAA Western Region.
This supersedes Amendment 39-1462 (37 F.R. 11857), AD 72-13-4.
This amendment becomes effective May 8, 1975.