Airworthiness Directive · Amendment 39-17339 · Main rotor head
Bell Helicopter Textron Helicopters
This AD applies to Model 204B, 205A, 205A-1, 205B, 210 and 212 helicopters, certificated in any category, with a main rotor hub inboard strap fitting (fitting) with a part number (P/N) and serial number (S/N) listed in Table 1 to paragraph (a) of this AD.
| Helicopter models | Fitting P/Ns | Fitting S/Ns |
|---|---|---|
| 204B | 204-012-102-001 | All. |
| 204B, 205A and 205A-1 | 204-012-102-005 | All. |
| 204B, 205A and 205A-1 | 204-012-102-009 | All, except S/Ns 7500 or larger with a prefix of “A”. |
| 212 | 212-010-103-005 | All. |
| 212 | 212-010-103-007 | All, except S/Ns 140 or larger with a prefix of “SH” and except S/Ns 11021 or larger with a prefix of “A”. |
| 205A-1, 205B and 210 | 212-010-103-101 | All, except S/Ns 486 or larger with a prefix of “SH,” and except S/Ns 10997 or larger with a prefix of “A”. |
We are superseding an existing airworthiness directive (AD) for the Bell Helicopter Textron (Bell) Model 212 helicopters and adopting requirements for Bell Model 204B, 205A, 205A-1, 205B and 210 helicopters with certain part-numbered main rotor hub inboard strap fittings (fittings). This AD requires magnetic particle inspecting (MPI) the fittings for a crack, and if a crack exists, replacing the fittings with airworthy fittings. This AD is prompted by reports of additional cracked fittings and the determination that additional part-numbered fittings may not have been manufactured in accordance with approved manufacturing processes and controls. These actions are intended to identify a crack in the fitting, which may lead to the fitting's failure, loss of a main rotor blade, and subsequent loss of helicopter control.
You are responsible for performing each action required by this AD within the specified compliance time unless it has already been accomplished prior to that time.
(1) Within 25 hours time-in-service or 15 days, whichever occurs first, perform a magnetic particle inspection (MPI) of each fitting for a crack. If an MPI was already performed on a fitting resulting in re-identifying the fitting with “FM” at the end of the P/N or at the end of the P/N on the fitting's component history card or equivalent record, then the requirements of this AD have been met.
(2) If a fitting is cracked, before further flight, replace it with an airworthy fitting.
(3) If a fitting is not cracked, before further flight, re-identify the fitting by adding “FM” at the end of the P/N using a vibrating stylus. The depth of the “FM” must not exceed 0.005 inches or extend within 0.10 inch of the part's edge. Also, add “FM” at the end of the P/N on the fitting's component history card or equivalent record.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
