AD 63-27-02

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AD Number:
63-27-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Grumman Model G-21 Series Aircraft
Subject:
Rudder Control Push Rod End Fittings
Status:
Current
Citation:
Federal Register: December 19, 1963
Citation Publish Date:
12/19/1963
Effective Date:
01/20/1964
Make:
Grumman American Aviation Corporation
Model:
G-21 | G-21A (Army OA-9, Navy JRF-1, -2, -3, -4, -5, and -6B)
Product Type:
Aircraft
Product Subtype:
Small Airplane
Affected AD:
Superseded AD:
Affected By:
Superseded By:
Service/Office:
Office of Primary Responsibility:
CFR Part Reference:
Part 39
Comments:
AIRWORTHINESS DIRECTIVES FINAL RULES: 63-27-02
CITATION:   [Federal Register: December 19, 1963]

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:  

AD NUMBER:   63-27-02

SUBJECT HEADING:   Airworthiness Directives; Grumman Model G-21 Series Aircraft

ACTION:  

SUMMARY:  

DATES:   Effective January 20, 1964.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
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 approximately 9 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 an FAA 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.

FOOTER: