Airworthiness Directive · Amendment 39-16186 · Bell Helicopter Textron, Inc. Model 205B and 212 Helicopters
Bell Helicopter Textron, Inc. Model 205B and 212 Helicopters
Superseded. A later AD replaced this one: AD 2011-23-02. Comply with the one in force.
Serial-numbered Model 205B and Model 212 helicopters, with the specified part-numbered main rotor (M/R) blade that is listed in Table 1 of this AD installed, certificated in any category.
| Helicopter model and serial No. (S/N) | M/R blade P/N |
|---|---|
| Model 205B: S/N 30066, 30166, 30188, or 30297 | P/N 212-015-501-005, -111, -113, -115, -117, -119, or -121. |
| Model 212: S/N 30502 through 30603, 30611 through 30999, 31101 through 31311, 32101 through 32262, or 35001 through 35103 | P/N 212-015-501-005, -111, -113, -115, -117, -119, or - 121. |
This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (Bell) Model 205B and 212 helicopters with certain main rotor (M/R) blade assemblies installed. This action requires inspecting the M/R blades paying particular attention to an area near the blade root for an edge void, corrosion, or a crack. This amendment is prompted by two reports of fatigue cracks on M/R blades installed on Model 212 helicopters. Both model helicopters use the same part-numbered M/R blades. The actions specified in this AD are intended to detect an edge void, corrosion, or a crack on a M/R blade, which could lead to loss of the M/R blade and subsequent loss of control of the helicopter.
To detect an edge void, corrosion, or a crack on a M/R blade, which could lead to loss of the M/R blade and subsequent loss of control of the helicopter, accomplish the following:
(a) Within 25 hours time-in-service (TIS), unless accomplished previously, and thereafter at intervals not to exceed 100 hours TIS:
(1) Wash the upper and lower surfaces of the M/R blade with a solution of cleaning compound (C-318) and water. Rinse thoroughly and wipe dry.
(2) Using a 3x power or higher magnifying glass, on each affected M/R blade, in an area from blade stations 24.5 to 40, including the entire width of the M/R blade chord, as depicted in Figure 1 in Bell Helicopter Alert Service Bulletin No. 205B-08-51 for the Model 205B helicopters, or No. 212-08-130 for the Model 212 helicopters, both Revision A, dated January 13, 2009 (ASBs), as applicable:
(i) Visually inspect the upper and lower grip plates and doublers of the M/R blade in the specified area for an edge void, corrosion, or a crack.
(ii) Visually inspect the remaining upper and lower surfaces of the M/R blade in the specified area for any corrosion or a crack.
Note 1: The inspections required by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD can be accomplished with the M/R blade installed on the helicopter.
Note 2: Crack indications on an actual M/R blade are shown in Figure 2 of both ASBs.
(3) Apply a light coat of preservative oil (C-125) to all surfaces of the M/R blade in the specified area.
(b) Before further flight:
(1) If any corrosion or an edge void is found, replace the M/R blade with an airworthy M/R blade, or repair the M/R blade if the damage is within the maximum repair damage limits.
(2) If a crack is found in the M/R blade paint finish, remove the paint in the affected area by lightly sanding with 180-220 grit paper in a span wise direction to determine if the grip plate, doubler, or skin is cracked. Do not remove any parent material of the M/R blade during the sanding operation. Refinish the sanded area.
(3) If a crack is found in any part of the M/R blade other than the paint finish, replace the M/R blade with an airworthy M/R blade.
(4) If any parent material is removed during the sanding operation required by paragraph (b)(2) of this AD, replace the M/R blade with an airworthy M/R blade, or repair the M/R blade if the amount of parent material removed is within the maximum repair damage limits.
Note 3: The maximum repair damage limitations specified in paragraphs (b)(1) through (b)(4) of this AD are contained in the applicable Component and Repair Overhaul Manual.
(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.
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.
