# AD 68-04-04 R2: Tail Rotor Blade - Type: Airworthiness directive - Status: Current - Products: Brantly International B-2, B-2A and B-2B - Effective: February 14, 1983 - Superseded by: Nothing supersedes this AD - Product type: Aircraft, Rotorcraft - Amendment: 39-4552 - Registered aircraft: 53 may be affected, by airframe or engine model (OpenAirDocs) - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/F34E6BA5E0FDDF2C86256A380060BB0A.0001 - DRS record last changed: May 30, 2024 - Page: https://openairdocs.org/ad/68-04-04-R2 ## The airworthiness directive 68-04-04 R2 BRANTLY: Amendment 39-557 as amended by Amendment 39-3568 is further amended by Amendment 39-4552. Applies to Model B-2, B-2A, and B-2B helicopters, certificated in all categories. For tail rotor blades, P/N 111-11, with 100 or more hours' time in service after February 27, 1968, compliance required prior to further flight, unless already accomplished, and, thereafter, at intervals not to exceed 100 hours' time in service from the last inspection. For tail rotor blades, P/N 111-11A, with 300 or more hours' time in service after August 15, 1979, compliance required prior to further flight, unless already accomplished, and, thereafter, at intervals not to exceed 300 hours' time in service from the last inspection. To prevent failures of the tail rotor blade at the spar retention areas, accomplish the following: (a) Remove, clean, and mark the tail rotor blades in accordance with Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968, and accomplish the following inspections: (1) Visually inspect the inside and outside of the spars of the tail rotor blades particularly at the inside bearing boss radius for evidence of pitting corrosion. If corrosion is detected, replace the blade assembly before further flight with an airworthy part. (2) Inspect the inside and outside of the spars of the tail rotor blades particularly at the inside bearing boss radius for evidence of cracks using dye penetrant procedures as indicated in Figure 1 of Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968, or use an equivalent method approved by the Manager, Aircraft Certification Division, FAA, Southwest Region, Fort Worth, Texas 76101. If a crack is detected, replace the blade assembly before further flight with an airworthy part. (b) After the tail rotor blades have been inspected or replaced with an airworthy part as provided in paragraphs (a)(1) and (a)(2) of this Airworthiness Directive, assemble them in accordance with Brantly Service Bulletin, SB No. B2B-68-1, dated February 14, 1968. (c) To prevent confusion during subsequent inspections of tail rotor blades due to similarity between tail rotor blade assembly, PN 111-11, and assembly, PN 111-11A, use a permanent marking ink or equivalent acceptable for aluminum aircraft components to mark the tail rotor blade assembly with the proper part number identification (see Fig. 1 for dimensions that determine the part configuration). (d) In order to facilitate inspection of the tail rotor blade spar retention area, do not repaint the spar retention area. (e) The requirements of paragraphs (c) and (d) above must be implemented no later than the next compliance with paragraph (a) of this AD after February 14, 1983. Amendment 39-557 became effective February 27, 1968, to all persons except those to whom it was made effective on receipt of airmail letter dated February 14, 1968. Amendment 39-3568 became effective October 28, 1979. This Amendment 39-4552 becomes effective February 14, 1983. ## Affected data sheets (1) (OpenAirDocs) The type certificate data sheets whose models the AD names. - [TCDS 2H2](https://openairdocs.org/tcds/2H2): Brantly International Inc.; names 3 of 3 models: B-2B, B-2A, B-2 ## 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: 53 (53 by airframe model, 0 by engine model) - Makers: Brantly 53 Models with the most aircraft: - [Brantly B-2B](https://openairdocs.org/model/brantly-b-2b): 34 aircraft (airframe model) - [Brantly B-2](https://openairdocs.org/model/brantly-b-2): 17 aircraft (airframe model) - [Brantly B-2A](https://openairdocs.org/model/brantly-b-2a): 2 aircraft (airframe model) All 3 models: https://openairdocs.org/ad/68-04-04-R2/models.md Every aircraft: https://openairdocs.org/ad/68-04-04-R2/aircraft.md Its text cites no advisory circulars or STCs. ## NTSB investigations that cite this AD (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB CEN18LA313](https://openairdocs.org/ntsb/CEN18LA313), Aug 3, 2018: Brantly B-2 (N5901X), Midland, MI, substantial damage. Probable cause: The in-flight separation of the tail rotor blade due to fatigue, which resulted in the subsequent emergency landing and dynamic rollover. --- 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.