Airworthiness Directive · Amendment 39-16651 · Bell Helicopter Textron, Inc. Model 212 Helicopters
Bell Helicopter Textron, Inc. Model 212 Helicopters
Superseded. A later AD replaced this one: AD 2013-03-16. Comply with the one in force.
This AD applies to Model 212 helicopters certificated in any category, with a main rotor hub inboard strap fitting (fitting), part number (P/N) 212-010-103-007, installed, with the serial numbers (S/Ns) listed in the following Table 1:
| Serial numbers with a prefix of: |
|---|
| “A” or “A-FS”: 7 through 10946. |
| “A1”: 430 through 7606. |
| “DI”: 22296 through 22681. |
| “EA”: 333 through 381. |
| “LK”: 4619 through 4631. |
| “MB”: 11908 through 11916. |
| “SH”: 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113, 137, and 139. |
| “WR”: 275 through 319. |
We are superseding an existing emergency airworthiness directive (EAD) for the Bell Helicopter Textron, Inc. (Bell) Model 212 helicopters with a certain main rotor hub inboard strap fitting (fitting) installed. That EAD requires, before further flight, removing certain serial-numbered fittings and replacing them with airworthy fittings. It also requires performing a magnetic particle inspection (MPI) on fittings with certain serial numbers (S/Ns) to inspect for a crack. If a crack is found, the cracked fitting must be replaced with an airworthy fitting, and certain data must be reported to the FAA. This airworthiness directive (AD) retains the requirements of that EAD and expands the applicability to require performing an MPI for a crack on additional serial-numbered fittings. This AD is prompted by the determination that certain fittings were not manufactured in accordance with the approved manufacturing processes and controls. In total, eight fittings have been found that have cracks. We are issuing this AD to prevent failure of a fitting, loss of a main rotor blade, and subsequent loss of control of the helicopter.
Required as indicated, unless accomplished previously.
(f) Before further flight, for any helicopter with a fitting, serial number (S/N) 9956 through 10005 with a prefix of “A”, and S/N 52, 54, 55, 57 through 65, 67, 69, 70, 71, 73, 103, 112, 113, 137, and 139 with a prefix of “SH” installed, replace the fitting with an airworthy fitting. Any fitting with a S/N identified in this paragraph is no longer eligible for installation on any helicopter.
(g) Before further flight, for any helicopter with a fitting, S/N 9911 through 9955, 10006 through 10049, 10075 through 10174, 10455 through 10460, 10581 through 10655, 10742 through 10791, and 10862 through 10946 with a prefix of “A”, perform an MPI of each fitting for a crack. If a fitting is cracked, replace it with an airworthy fitting. If a fitting is not cracked, reidentify and refinish the fitting using a vibrating stylus (not to exceed 0.005 inch depth nor to extend within 0.10 inch of part edge) by adding “FM” at the end of the P/N. Touch up the reworked area with brush cadmium plating or zinc chromate primer. Reidentify the historical service records with “FM” at the end of the P/N.
Note 1: The Bell Model 212 Component, Repair, and Overhaul Manual, which is not incorporated by reference, contains additional information about MPI procedures.
(h) For any fitting with a S/N identified in Table 1 of the Applicability section of this AD, and not identified in paragraph (f) or (g) of this AD, perform an MPI of each fitting for a crack as follows:
(1) For a fitting with 400 or less hours time-in-service (TIS), perform an MPI within 25 hours TIS or 15 days, whichever comes first.
(2) For a fitting with more than 400 but less than 800 hours TIS, perform an MPI within 100 hours TIS or 30 days, whichever comes first.
(3) For a fitting with 800 or more hours TIS, perform an MPI at the next main rotor hub teardown inspection or tension-torsion strap replacement, whichever comes first.
(4) If a fitting is cracked, replace it with an airworthy fitting.
(5) If a fitting is not cracked, reidentify and refinish the fitting in accordance with the instructions in paragraph (g) of this AD.
(i) Within 24 hours after finding any cracked fitting, report the information requested in Appendix 1 of this AD to the Manager, Rotorcraft Certification Office, to the address, fax number, or email specified in the Appendix.
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor shall a person be subject to a penalty for failure to comply with a collection of information subject to the requirements of the Paperwork Reduction Act unless that collection of information displays a current valid Office of Management and Budget (OMB) Control Number. Under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq.), the OMB has approved the information collection requirements contained in this AD and has assigned OMB Control Number 2120-0056. Public reporting for this collection of information is estimated to be approximately 5 minutes per response, including the time for reviewing instructions, completing and reviewing the collection of information. All responses to this collection of information are mandatory. Comments concerning the accuracy of this burden and suggestions for reducing the burden should be directed to the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn: Information Collection Clearance Officer, AES-200.
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.
