81-14-02 MAULE AIRCRAFT CORPORATION: Amendment 39-4146. Applies to M-4 and to M-5 series airplanes certificated in all categories.
M-4 Series. M-4, S/N 4 through 94, 1001 through 1045, 1S through 3S, 1T through 3T, 1C through 11C; M-4-210C, S/N 1001C through 1117C; M-4-220S, S/N 2001S; M-4-220C, S/N 2001C through 2190C; M-4-180C, S/N 3001C through 3006C.
M-5 Series. M-5-220C, S/N 5001C through 5057C; M-5-210C, S/N 6001C through 6204C; M-5-235C, S/N 7001C through 7254C; M-5-180C, S/N 8001C and M-5-210TC, S/N 9001C.
Compliance is required as indicated, unless already accomplished.
To prevent failure of the rudder pedal V-bar and associated structure of the rudder bar, within 25 hours time in service after the effective date of this AD accomplish the following:
(a) Visually inspect the rudder pedal V-bar tube for cracks with at least a 10-power magnifying glass.
NOTE: Instructions for access to the rudder bar are outlined in Maule Aircraft Corporation Service Bulletin No. 2, dated 2/17/81.
(b) If no cracks are found, modify the rudder bar assembly in accordance with the Maule Service Bulletin #2, dated 2/17/81.
(c) If a crack is found, prior to further flight accomplish either 1 or 2 below, as appropriate:
1. If the crack is one inch or less in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81, or stop drill at the end of the crack, weld and reinforce in accordance with the instructions provided in the Maule Service Bulletin #2, dated 2/17/81, and Advisory Circular 43.13-1A, Chapter 2, Aircraft Metal Structure, Section 2, Welding.
2. If the crack exceeds one inch in length, install modified rudder bar, P/N 4130F-12, in accordance with the instructions contained in Maule Service Bulletin #2, dated 2/17/81.
(d) Make appropriate maintenance record entry.
An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region.
This amendment becomes effective July 1, 1981.