- Effective
- October 16, 1975
- Models
- BO-209-150 FF, BO-209-150 FV, BO-209-150 RV, BO-209-160 FV, BO-209-160 RV
- Data sheet
- TCDSA27EU
- Product
- Aircraft · Small airplane
- Amendment
- 39-2380
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.
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|---|---|---|---|
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On this page
The airworthiness directive
75-21-02 MESSERSCHMITT-BOLKOW-BLOHM: Amendment 39-2380. Applies to Models BO-209 airplanes, S/N's 101 thru 201, and 301, certificated in all categories.
Compliance is required as indicated.
To prevent possible failure of the fuselage carry-through member of the wing, accomplish the following:
(a) Within the next 10 hours' time in service after the effective date of this AD, unless already accomplished, visually inspect the rear side of the beam web of fuselage frame No. 2 for cracks, in accordance with paragraph C.1. of Messerschmitt-Bolkow-Blohm (MBB) Service Bulletin No. 209-20-1 7/74 dated 7/74, or an FAA-approved equivalent.
(b) If the inspection required by paragraph (a) of this AD reveals cracks, before further flight, repair and reinforce fuselage frame No. 2 in accordance with MBB Instruction No. MBB 209-1/74, undated, or an FAA-approved equivalent.
(c) If the inspection required by paragraph (a) of this AD reveals no cracks, within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, reinforce fuselage frame No. 2 in accordance with MBB Instruction No. MBB 209-1/74, undated, or an FAA-approved equivalent.
This amendment becomes effective October 16, 1975.
Affected TCDS · 1
The type certificate data sheets for the models this AD names, matched by model and maker.