AD 81-14-02

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AD Number:
81-14-02
Document Type:
AD Final Rules
Docket Number:
Unknown
Subject Heading:
Airworthiness Directives; Maule Model M-4, M-4-210C, M-4-220S, M-4-220C, M-4-180C, M-5-220C, M-5-21...Show more
Subject:
Rudder Pedal V-Bar
Status:
Current
Citation:
This information is not available.
Citation Publish Date:
Effective Date:
07/01/1981
Make:
Maule Aerospace Technology, Inc.
Model:
M-4 | M-4-180C | M-4-210C | M-4-220C | M-4-220S | M-4C | M-4S | M-4T | M-5-180C | M-5-210C | M-5-210...Show more
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Superseded AD: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Superseded By: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: 81-14-02
CITATION:   This information is not available.

PAGE NUMBER:  

DOCKET NUMBER:   Unknown

AMENDMENT:   39-4146

AD NUMBER:   81-14-02

SUBJECT HEADING:   Airworthiness Directives; Maule Model M-4, M-4-210C, M-4-220S, M-4-220C, M-4-180C, M-5-220C, M-5-210C, M-5-235C, M-5-180C and M-5-210TC Series Airplanes

ACTION:  

SUMMARY:  

DATES:   Effective July 1, 1981.

ADDRESSES:  

FOR FURTHER INFORMATION CONTACT:  

SUPPLEMENTARY INFORMATION:  

REGULATORY TEXT:  
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.

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