- Effective
- October 19, 1971
- Models
- 99, 99A, 99A (FACH), A99, A99A, B99, C99
- Data sheet
- TCDSA14CE
- Registered aircraft
- 95 matched by model
- Product
- Aircraft · Small airplane
- Amendment
- 39-1321
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 January 21, 2026.
Copies of the files this page was built from, with their SHA-256. Retrieved October 18, 2026.
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On this page
The airworthiness directive
71-06-01 BEECH: Amdt. 39-1170 as amended by Amendment 39-1222 is further amended by Amendment 39-1321. Applies to all 99 series airplanes (Serial Numbers as applicable).
Compliance: Required as indicated, unless already accomplished.
To preclude the occurrence of faults, failures and improper operation, accomplish the following:
A) On all 99 series airplanes (Serial Numbers U-1 through U-95, U-97 through U- 127, U-130 through U-133, U-135 and U-136) within the next 100 hours' time-in-service after the effective date of this AD, modify the flap position selector in accordance with Beechcraft Service Instruction 0328-158 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri.
B) On all 99 series airplanes (Serial Numbers U-1 through U-133, U-135 and U- 136) within the next 100 hours' time-in-service after the effective date of this AD, modify the landing gear indicator and warning device in accordance with Beechcraft Service Instruction 0313-158 and 0318-350, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri.
C) On all 99 series airplanes (Serial Numbers U-2 through U-103, U-105 through U- 133, U-135 and U-136) within the next 75 hours' time-in-service after the effective date of this AD, modify the gear selector panel in accordance with Beechcraft Service Instructions 0299-395 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri.
D) On all 99 series airplanes (Serial Numbers U-1 through U-103 and U-106 through U-135) within the next 75 hours' time-in-service after the effective date of this AD, modify the instrument static air system in accordance with Beechcraft Service Instruction 0291- 394, Rev. 1, or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri.
E) On Models 99 and 99A (Serial Numbers U-1 through U-136) airplanes within the next 100 hours' time-in-service after the effective date of this AD (March 16, 1971), inspect and test the electrical power distribution system in accordance with Beechcraft Service Instructions 0348-351 or later FAA approved revision, or by any other method approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, Kansas City, Missouri.
Amendment 39-1170 became effective March 16, 1971.
Amendment 39-1222 became effective June 3, 1971.
This Amendment 39-1321 becomes effective October 19, 1971.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.
Registered aircraft · 95
Registered aircraft whose airframe or engine model this AD names. Matched by model only, so check each against the AD’s applicability.
| 1968 | 9 |
|---|---|
| 1969 | 19 |
| 1970 | 5 |
| 1971 | 1 |
| 1973 | 1 |
| 1974 | 1 |
| 1981 | 10 |
| 1982 | 14 |
| 1983 | 11 |
| 1984 | 8 |
| 1986 | 3 |
| 1987 | 5 |
8 with no year recorded