| AD Number | 63-27-02 | Status | Active |
| Effective Date | January 20, 1964 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | N/A |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | Federal Register: December 19, 1963 | ||
| Manufacturer(s) | Grumman American Aviation Corporation |
| Model(s) | G-21 G-21A (Army OA-9, Navy JRF-1, -2, -3, -4, -5, and -6B) |
63-27-02 GRUMMAN: Amdt. 655 Part 507 Federal Register December 19, 1963. Applies to All Model G-21 Series Aircraft.
Compliance required as indicated.
As a result of cracks found on the rod end fitting, P/N 12727-7 located at the aft end of the rudder control push rod assembly, P/N 12727-1, accomplish the following within 100 hours' time in service after the effective date of this AD, and thereafter at intervals not to exceed 100 hours' time in service from the last inspection.
(a) Remove the rudder control push rod assembly, P/N 12727-1. This assembly consists of a tube with a fitting, P/N 12727-7, attached at each end. The length of the assembly is 20 1/2 inches from fitting center to fitting center. The rod assembly, used in conjunction with the left rudder pedals, is located below the pilot's compartment floor, the forward end approximately 2 1/2 inches below, and the aft end approximately 12 inches below . Laterally, the rod assembly is located approximately9 1/2 inches to the right of the aircraft's centerline.
(b) Clean both rod end fittings, removing all grease and dirt.
(c) Inspect both rod end fittings for cracks using a dye penetrant in conjunction with at least a 10-power magnifying glass, or an FAA approved equivalent inspection.
(d) If a crack is found, that part shall be replaced in accordance with Grumman Drawing No. 12727 with a new part having the same part number, or an FAA approved equivalent before further flight.
(e) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator.
NOTE: It should be ascertained that the proper rudder control stop bolt, Grumman P/N G19-4-11, or anFAA approved equivalent bolt (having a smooth head) is presently installed in the pedal stop block (P/N 12779) which is part of the rudder and elevator torque shaft support assembly (P/N 12722) at Hull Station 11.
This directive effective January 20, 1964.