# AD 2010-24-51: Cracked fitting - Type: Emergency airworthiness directive - Status: Historical - Products: Bell Helicopter Textron 212 - Issued: November 12, 2010 - Issued as: Emergency AD - Superseded by: [AD 2010-24-52](https://openairdocs.org/ad/2010-24-52) - Product type: Aircraft, Rotorcraft - Registered aircraft: 59 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/01D849D77E388A90862577D90073D724.0001 - DRS record last changed: August 7, 2025 - Page: https://openairdocs.org/ad/2010-24-51 ## The airworthiness directive FAA Aviation Safety EMERGENCY AIRWORTHINESS DIRECTIVE www.faa.gov/aircraft/safety/alerts/ DATE: November 12, 2010 AD #: 2010-24-51 Background This EAD is prompted by a recent accident that resulted in several fatalities. During the investigation of the accident, a crack was found on the main rotor hub inboard strap fitting (fitting). Subsequently, 4 additional fittings from the same manufacturing lot were inspected and two were found to exhibit the same type of cracking as found on the fitting installed on the helicopter involved in the accident. A cracked fitting could result in failure of the fitting, loss of a main rotor blade, and subsequent loss of control of the helicopter. Relevant Service Information We reviewed Bell Alert Service Bulletin No. 212-10-141, dated November 11, 2010 (ASB), which specifies the immediate removal of certain serial-numbered fittings from service. Bell states that they have determined that the fitting may not have been manufactured in accordance with the engineering design requirements and may fracture as a result of the non-conformance. Bell further states that their investigation is ongoing and indicates that fittings serial numbers A-9956 through A-10005 inclusive are affected by the ASB. FAA’s Determination We are issuing this EAD because we evaluated all the relevant information and determined the unsafe condition described is likely to exist or develop in other products of this same type design. AD Requirements This EAD requires, before further flight, removing each affected fitting and replacing it with an airworthy fitting. Any fitting with a part and serial number identified in the Applicability section of this EAD is no longer eligible for installation on any helicopter. Differences Between This EAD and the Service Information This EAD differs from the ASB in that we do not require returning parts to Bell. Authority for this Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III, Section 44701, “General requirements.” Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This 1 regula tion is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Pursuant to this Authority delegated to me by the Administrator, we are hereby issuing this Emergency Airworthiness Directive (EAD). 2010-24-51 BELL HELICOPTER TEXTRON, INC.: Directorate Identifier 2010-SW-094-AD. Effective Date (a) This Emergency Airworthiness Directive (EAD) is effective upon receipt. Other Affected ADs (b) None. Applicability (c) This AD applies to Bell Helicopter Textron, Inc. Model 212 helicopters, with a main rotor hub inboard strap fitting (fitting), part number (P/N) 212-010-103-007, S/N 9956 through 10005, with a prefix of “A” installed, certificated in any category. Unsafe Condition (d) This EAD is prompted by a crack found on a fitting after a recent accident. Subsequently, 2 additional fittings from the same manufacturing lot were found to have the same type crack. A cracked fitting could result in failure of the fitting, loss of a main rotor blade, and subsequent loss of control of the helicopter. Compliance (e) Before further flight, unless accomplished previously, replace each affected fitting with an airworthy fitting. Any fitting with a part and serial number identified in the Applicability section of this EAD is no longer eligible for installation on any helicopter. Special Flight Permit (f) A special flight permit will not be issued. Alternative Methods of Compliance (AMOCs) (g) The Manager, Rotorcraft Certification Office, FAA, has the authority to approve AMOCs for this EAD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the Rotorcraft Certification Office, send it to the attention of the person identified in the Other Information section of this EAD. Note: Before using any approved AMOC, we request that you notify your appropriate principal inspector, or lacking a principal inspector, your local Flight Standards District Office. 2 3 Other Information (h)(1) For further information about this EAD, contact: Michael Kohner, Aerospace Engineer, FAA, Rotorcraft Directorate, Rotorcraft Certification Office, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170, fax (817) 222-5783; e-mail: mike.kohner@faa.gov. (2) Bell Helicopter Alert Service Bulletin No. 212-10-141, dated November 11, 2010, which is not incorporated by reference, contains additional information about the subject of this EAD. Subject (i) The Joint Aircraft System Component Code is: 6220 Main Rotor Hub. Issued in Fort Worth, Texas, on November 12, 2010. Lance T. Gant, Acting Manager, Rotorcraft Directorate, Aircraft Certification Service. ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS H4SW](https://openairdocs.org/tcds/H4SW): Bell Textron Inc.; names 1 of 4 models: 212 ## Registered aircraft it may apply to (OpenAirDocs) Matched by airframe and engine model; the AD's applicability may narrow it by serial number, part number or equipment. - Aircraft: 59 (59 by airframe model, 0 by engine model) - Makers: Bell 54, Bell Helicopter Textron 5 Models with the most aircraft: - [Bell 212](https://openairdocs.org/model/bell-212): 54 aircraft (airframe model) - [Bell Helicopter Textron 212](https://openairdocs.org/model/bell-helicopter-textron-212): 5 aircraft (airframe model) All 2 models: https://openairdocs.org/ad/2010-24-51/models.md Every aircraft: https://openairdocs.org/ad/2010-24-51/aircraft.md ## Related documents - [AD 2010-24-52](https://openairdocs.org/ad/2010-24-52) (historical): Cracked fitting · Bell Helicopter Textron 212. Supersedes this AD Its text cites no advisory circulars or STCs. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.