Airworthiness Directive · Amendment 39-16853 · Bell Helicopter Textron, Inc. (Bell), Model 205A-1, 205B, 210, and 212 Helicopters
Bell Helicopter Textron, Inc. (Bell), Model 205A-1, 205B, 210, and 212 Helicopters
Model 205A-1, 205B, 210 and 212 helicopters with a main rotor blade (blade), part number (P/N) 204-012-001-023 or -033; 210-015-001-101; 212-015-501-005, -111, -113, -115, -117, -119, or -121, installed, certificated in any category.
Note 1: Bell Helicopter Model 205A-1 helicopters, modified by Supplemental Type Certificate (STC) No. SH5132NM or SH5976NM, may have affected part-numbered blades installed.
This amendment supersedes an existing airworthiness directive (AD) for Bell Model 205B and 212 helicopters with certain main rotor blade (blade) assemblies installed. That AD currently requires washing the upper and lower surfaces of each blade and visually inspecting the grip plates, doublers, and the remaining upper and lower surfaces of the blades in the area between blade stations 24.5 to 40 for an edge void, corrosion, or a crack. This amendment retains the requirements of that AD for the affected part-numbered blades but increases the scope and frequency of the inspections and expands the applicability to include the Model 205A-1 and 210 helicopters, additional blade part numbers, and all helicopter serial numbers for the affected helicopter models. This amendment also requires applying a light coat of preservative oil (C-125) to all surfaces of the blade in addition to the inspection areas as required in the existing AD. This amendment is prompted by an additional report of a fatigue crack on a blade installed on a Model 212 helicopter. The actions specified by this AD are intended to detect an edge void, corrosion, or a crack on a blade, and to prevent loss of a blade and subsequent loss of control of the helicopter.
To detect an edge void, corrosion, or a crack on a blade, to prevent the loss of a blade and subsequent loss of control of the helicopter, do the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 25 hours TIS:
(1) Wash the upper and lower surfaces of each affected blade with a solution of cleaning compound (C-318) and water. Rinse thoroughly and wipe dry.
(2) Visually inspect each of the upper and lower grip plates and doublers of the blade for their entire length and chord width for an edge void, any corrosion, or a crack. Pay particular attention to any crack in the paint finish near or at a bond line that follows the outline of a grip plate or doubler.
Note 2: The inspections required by paragraphs (a)(2) and (a)(4) of this AD do not require removal of the blades from the main rotor hub and can be accomplished while the blades are installed on the helicopter.
(3) Wipe each of the bond lines at the edges of both grip plates and each of the layered doublers (bond lines) on the upper and lower surfaces of each affected blade with an alcohol-soaked cloth (C-385) in the area from blade stations 24.5 to 85 (inspection area) as depicted in Figure 1 of Bell Helicopter Alert Service Bulletin (ASB) No. 205B-08-51 for the Model 205B helicopters or ASB No. 212-08-130 for the Model 212 helicopters (and the Model 205A-1 helicopters), both Revision B, and both dated January 11, 2011; or ASB No. 210-08-03, Revision B, dated January 10, 2011, for the Model 210 helicopters, as appropriate for your model helicopter. Wipe dry with a clean cloth.
(4) Immediately after accomplishing paragraph (a)(3) of this AD, using a 3x power or higher magnifying glass and a bright light, visually inspect each of the bond lines on the upper and lower surfaces of the blade in the inspection area for any edge delamination, as indicated by a dark line located along any bond line, or a crack in the paint finish. An edge delamination is defined as a separation of the detail parts along an edge.
Note 3: An edge delamination along the edge of a grip plate or doubler, or “any potential cracks in the bond lines between doublers or grip plates” as described in the ASBs, is indicated by the presence of excess alcohol bleeding out of an edge void. The excess alcohol in the void will appear as a dark line along the bond line. A crack in the paint finish which follows the outline of a grip plate or doubler may indicate a possible edge void.
(5) If there is no edge void, corrosion, crack, an edge delamination, or a crack in the paint finish, apply a light coat of preservative oil (C-125) to all surfaces of the blade.
(b) Before further flight:
(1) If there is any edge delamination along any bond line of a grip plate or doubler, or a crack in the paint finish:
(i) Remove the paint in the affected area by lightly sanding with 180-220 grit paper in a span-wise direction to determine if there is an edge void, or if the grip plate, doubler, or skin is cracked. If any parent material is removed during the sanding operation, replace the blade with an airworthy blade or repair the blade if the amount of parent material removed is within the maximum repair damage limits.
Note 4: The maximum repair damage limits are contained in the applicable Component and Repair Overhaul Manual.
(ii) If there is an edge void, determine the depth and length using a.0015 inch feeler gauge.
(iii) If there is an edge void in a grip plate or doubler near the outboard tip, tap inspect the affected area to determine the size and shape of the void.
(iv) Repair the blade if the edge void is within the maximum repair damage limits or replace the blade with an airworthy blade.
(v) If there is not an edge void or a crack, refinish the sanded area.
(2) If there is a crack in any grip plate or doubler, replace the blade with an airworthy blade.
(3) If there is a crack in the blade skin, replace the blade with an airworthy blade, or repair the blade if the damage is within the maximum repair damage limits.
(4) If there is any corrosion, replace the blade with an airworthy blade or repair the blade if the damage is within the maximum repair damage limits.
(c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the Manager, Rotorcraft Certification Office, Attn: Michael Kohner, Aviation Safety Engineer, FAA, Rotorcraft Directorate, 2601 Meacham Blvd., Fort Worth, Texas 76137, telephone (817) 222-5170, fax (817) 222-5783, for information about previously approved alternative methods of compliance.
(d) The inspection area is depicted in Figure 1 of Bell Helicopter Alert Service Bulletin No. 205B-08-51 or No. 212-08-130, both Revision B, and both dated January 11, 2011; or No. 210-08-03, Revision B, dated January 10, 2011. The incorporation by reference of these documents was approved by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101, telephone (817) 280-3391, fax (817) 280-6466, or at http://www.bellcustomer.com/files/. Copies may be inspected at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas, or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
(e) The JASC Code is 6210: Main Rotor Blades.
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.
