Airworthiness Directive · Amendment 39-17989 · Main rotor blade
Brantly International, Inc. Helicopters
This AD applies to the Brantly International, Inc., (Brantly) Model B-2, Model B-2A, and Model B-2B helicopters, with a main rotor (M/R) blade, part number (P/N) 248-101, 248-202, or 248-404, installed, certificated in any category.
We are adopting a new airworthiness directive (AD) for Brantly International, Inc. (Brantly) Model B-2, Model B-2A, and Model B-2B helicopters with certain main rotor blades. This AD requires inspecting each main rotor (M/R) blade for a crack or delamination and removing the blade if a crack exists or if the delamination exceeds certain thresholds. This AD was prompted by multiple reports of M/R blade cracks and an incident in which a crack that originated near the M/R blade trailing edge resulted in the loss of a large section of the M/R blade. The actions of this AD are intended to prevent loss of the M/R blade and subsequent loss of control of the helicopter.
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) Before the first flight of each day, visually check the top and bottom of each M/R blade for a crack. Pay particular attention to the M/R blade root area, the area around the lead/lag damper mounting fork, and the trailing edge. These actions may be performed by the owner/operator (pilot) holding at least a private pilot certificate, and must be entered into the aircraft records showing compliance with this AD in accordance with 14 CFR 43.9 (a)(1) through (4) and 14 CFR 91.417(a)(2)(v). The record must be maintained as required by 14 CFR 91.417, 121.380, or 135.439.
(2) Within 8 hours time-in-service (TIS), for a helicopter with an M/R blade, P/N 248-101 or P/N 248-202, and for a helicopter with an M/R blade P/N 248-404 with 10 or more years or 1,000 or more hours TIS, whichever occurs first, remove each M/R blade and:
(i) Using an inspector qualified to the American Society for Nondestructive Testing (ASNT) Level II or equivalent, eddy current inspect each M/R blade for a crack in accordance with paragraph 4 and paragraphs 7 through 17 of Brantly International B-2 Main Rotor Blade Root Skin Inspection Technique Number ET002, dated November 2007 (technique), except this AD only requires you to inspect the inboard first 12 inches of the top and bottom of each blade.
Note 1 to paragraph (e)(2)(i) of this AD: A copy of the Technique is attached to Brantly International, Inc., Service Bulletin No. 111, dated February 10, 2011 (SB 111).
(ii) Thereafter, at intervals not to exceed 300 hours TIS or five calendar years, whichever occurs first, repeat the eddy current inspection in accordance with the requirements of paragraph (e)(2)(i) of this AD.
(iii) Using a metallic coin or tap hammer, tap inspect each M/R blade for delamination in the bonded areas as shown on SB-111, Section 4. Pay particular attention to the root area in the first 12 inches of the top and bottom of each M/R blade.
(iv) Using a 10X or higher power magnifying glass, visually inspect the top and bottom of each M/R blade for a crack.
(v) Thereafter, at intervals not to exceed 25 hours TIS, repeat the tap inspection in accordance with the requirements of paragraph (e)(2)(iii) of this AD and the visual inspection using a 10X or higher power magnifying glass in accordance with the requirements of paragraph (e)(2)(iv) of this AD.
(3) Before further flight, remove from service any M/R blade with a crack, delamination within the inboard 12 inches, or total delamination greater than 2 square inches outside the inboard 12 inches.
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.
Aircraft
