| AD Number | 61-23-03 | Status | Active |
| Effective Date | December 04, 1961 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Small/Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | Federal Register: November 2, 1961 | ||
| Manufacturer(s) | de Havilland Aircraft Co., Ltd., The |
| Model(s) | D.H.114 Heron Series 2A D.H.114 Heron Series 2DA D.H.114 Heron Series 2X |
Final Rule
61-23-03 DE HAVILLAND: Amdt. 358 Part 507 Federal Register November 2, 1961. Applies to All Heron Model 114 Aircraft Without Modification No. 1454.
Compliance required as indicated.
(a) Cases have occurred of cracking of the wing rear false spar web adjacent to the wing-to-fuselage attachment P/N 14W253/4. To preclude failure of the spar, an X-ray or visual inspection for cracks must be conducted in accordance with de Havilland Technical News Sheet CT(114) No. W.10 Issue 2, within the next 250 hours' time in service after the effective date of this directive and at each 600 hours' time in service thereafter. If cracks are found, repair in accordance with de Havilland Drawing RD14W 224, Issue 4, or subsequent, within the time in service given in paragraphs (1), (2), and (3).
(1) Cracks less than 1/2 inch in length must be repaired at the next wing removal and the inspection in (a) must be made every 600 hours' time in service in the interim between the inspection and the wing removal.
(2) Cracks of 1/2 inch to 1 1/2 inches in length must be repaired within 300 hours' time in service after the inspection.
(3) Cracks exceeding 1 1/2 inches in length must be repaired within the next 150 hours' time in service after the inspection.
(b) The special inspection in (a) is no longer required when the repair per Drawing RD 14W 224, Issue 4, or subsequent, has been incorporated.
(de Havilland Technical News Sheet CT(114) No. W.10 Issue 2 dated July 24, 1961, covers this subject.)
This directive effective December 4, 1961.