| AD Number | 70-03-03 | Status | Active |
| Effective Date | February 22, 1970 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-930 |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Vickers-Armstrongs (Aircraft Limited) |
| Model(s) | Viscount 744 Viscount 745D Viscount 810 |
70-03-03 BRITISH AIRCRAFT CORPORATION: Amdt. 39-930. Applies to Viscount Models 744, 745D, and 810 series airplanes.
Compliance is required as indicated.
To prevent possible failure of the fuselage pressure shell in the areas under the cockpit hood, accomplish the following:
(a) For airplanes manufactured before February 28, 1959 -
(1) Within the next 90 days after the effective date of this airworthiness directive, comply with the inspection requirements of paragraph (c).
(2) Within the next 12 months after the effective date of this airworthiness directive, unless already accomplished, accomplish the rework required in paragraph (f).
(b) For airplanes manufactured on or after February 28, 1959 -
(1) Within the next 90 days after the effective date of this airworthiness directive, or within eight years after the date of manufacture, whichever occurs later, and thereafter at intervals not to exceed 12 months since the last inspection, comply withthe inspection requirements of paragraph (c).
(2) Within 11 years after the date of manufacture, accomplish the rework required in paragraph (f).
(c) Remove the cockpit hood fairing side panels. Visually inspect the exposed skin panels for corrosion, and visually inspect the wood packing strips around the window frames for water saturation. Guidance on identification of the degree of corrosion is given in the Airplane Corrosion Section of the Viscount Overhaul Manual for Model 744 airplanes; in the Instruction Manual for Model 745D airplanes; and in the Aircraft Manual for Model 810 airplanes.
(d) If, during the inspections required by paragraph (c), skin corrosion is found which does not extend beyond the skin area exposed by removal of the cockpit hood fairing side panels, before further flight repair the corroded skin in accordance with the Viscount Repair Manual or comply with the requirements of paragraph (f).
(e) If, during the inspections required by paragraph (c), skin corrosion is found which extends beyond the skin area exposed by removal of the cockpit hood fairing side panels, or the wood packing strips around the windows are found to be saturated with water, before further flight comply with the requirements of paragraph (f).
(f) Remove the complete cockpit hood assembly, including the eyebrow fairing panels located above the windshield panels. Rework and reprotect the fuselage skin under these panels, and replace the wood window packing strips in accordance with paragraph 5.2.3 of British Aircraft Corporation Preliminary Technical Leaflet No. 278, Issue 1, for Models 744 and 745D airplanes; Preliminary Technical Leaflet No. 143, Issue 1, for Model 810 airplanes; or a later ARB- approved issue or FAA-approved equivalent.
(g) The repetitive inspections required by paragraph (b)(1) may be discontinued after compliance with the requirements of paragraph (f) has been accomplished.
This amendment becomes effective February 22, 1970.