- Effective
- July 1, 1981
- Models
- M-4, M-4-180C, M-4-210C, M-4-220C, M-4-220S, M-4C and 7 more
- Data sheet
- TCDS3A23
- Registered aircraft
- 546 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-4146
Unofficial copy of the text in the FAA’s Dynamic Regulatory System. The FAA’s own copy is the authoritative one. DRS record last changed May 30, 2024.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
| File | Size | SHA-256 | Original |
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On this page
The airworthiness directive
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.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 546
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1962 | 1 |
|---|---|
| 1963 | 16 |
| 1964 | 13 |
| 1965 | 5 |
| 1966 | 13 |
| 1967 | 8 |
| 1968 | 7 |
| 1969 | 5 |
| 1970 | 11 |
| 1971 | 13 |
| 1972 | 23 |
| 1973 | 32 |
| 1974 | 40 |
| 1975 | 32 |
| 1976 | 47 |
| 1977 | 43 |
| 1978 | 31 |
| 1979 | 22 |
| 1980 | 18 |
| 1981 | 9 |
| 1982 | 1 |
| 1983 | 2 |
| 1984 | 17 |
| 1985 | 6 |
| 1986 | 3 |
| 1987 | 4 |
| 1988 | 3 |
| 1989 | 1 |
| 2024 | 1 |
119 with no year recorded