| AD Number | 63-03-02 | Status | Active |
| Effective Date | February 06, 1963 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Large Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | Bombardier Inc. |
| Model(s) | CL-44D4 |
63-03-02 CANADAIR: Amdt. 533 Part 507 Federal Register February 6, 1963. Applies to all Model CL-44D4 aircraft.
Compliance required as indicated.
As a result of failure of a riveted rudder lower balance weight, the following must be accomplished:
(a) Prior to each departure from the principal maintenance base, inspect the rudder bottom closing rib for any indication of a balance weight becoming detached and dropping on to the rib. If so found, repair per (c) prior to further flight.
(b) Within the next 35 hours' time in service after the effective date of this AD, unless already accomplished, inspect the rivet attachment of the two weights (P/N 28-21250-16) to the bottom rudder balance weight assembly (P/N 28-21250-14). There are five 1/8-inch rivets per weight, a total of ten for the entire assembly. If any looseness or failure of the rivets is found, replace all rivets with bolts in accordance with (c).
(c) Within the next 250 hours' time in service after theeffective date of this AD, replace the ten 1/8-inch rivets referred to in (b) with AN 509-10R-30 bolts, AN 960-10 washers and NAS 679A3W lock nuts. This requires countersinking the aft face of the P/N 28-21250-14 assembly to accommodate the bolt heads. When this modification has been accomplished, the inspection in (a) may be discontinued.
(Canadair Service Information Circular 262-CL44D4 covers this subject.)
This directive effective February 6, 1963.