| AD Number | 75-21-02 | Status | Active |
| Effective Date | October 16, 1975 | Issue Date | Not specified |
| Docket Number | Unknown | Amendment | 39-2380 |
| Product Type | ["Aircraft"] | Product Subtype | ["Small Airplane"] |
| CFR Part | --- - Part 39 | CFR Section | N/A |
| Citation | This information is not available. | ||
| Manufacturer(s) | DaimlerChrysler Aerospace AG |
| Model(s) | BO-209-150 FF BO-209-150 FV BO-209-150 RV BO-209-160 FV BO-209-160 RV |
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.