63-27-02: Rudder Control Push Rod End Fittings
FAA order 63-27-02 is an airworthiness directive in force since January 20, 1964. The FAA's subject line: Rudder Control Push Rod End Fittings. It names Grumman G-21: about 35 aircraft on the U.S. register today, though an order usually covers particular versions or serial numbers rather than every one. System: flight controls.
What it applies to as the FAA lists it
- Kind of product
- Aircraft
- Makes
- Grumman American Aviation Corporation
- Models
- G-21, G-21A (Army OA-9, Navy JRF-1, -2, -3, -4, -5, and -6B)
- On this site
- Grumman G-21 35 registered
Dates and paperwork
- In force since
- January 20, 1964
- Published
- December 19, 1963
- Docket
- Unknown
- Status
- Current
- The FAA's document
- Read the order on the FAA's site
The order itself the regulatory text, as published
Show the full text (2,240 characters)
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.
Source: FAA Dynamic Regulatory System, airworthiness directives. The FAA's document is the authority; the register counts are this site's, from the FAA register of November 12, 2026. Connections as data: /graph/directive/63-27-02.json · aircraft systems.