1AD/BELL 206/90 Amdt 6 - Tail Rotor Blade Tip Block

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY

SCHEDULE OF AIRWORTHINESS DIRECTIVES

Bell Helicopter Textron Canada (BHTC) 206 and Agusta Bell 206 Series Helicopters

AD/BELL 206/90

Amdt 6

Tail Rotor Blade Tip Block 9/85

Applicability: All models Bell 206A, 206B, 206BIII, 206L, 206L-1 and 206L-3, and Agusta Bell AB.206A, AB.206B and AB.206B-1 fitted with Tail Rotor Blades P/N 206-016-201- 001, 206-016-201-103 and 206-016-201-107. with S/N’s referred to in Requirement S.B’s.

Requirement: 1. Clean the tip block area thoroughly and visually inspect for working, corroded and/or missing rivet heads and evidence of voids or separations between the shell and the tip block. Refer to Bell Alert S.B.’s 206-85-28 Rev.B or 206L-85-34 Rev.B for allowable damage/repair requirements as applicable.

2. Any evidence of voids or separations other than those listed as acceptable by the manufacturer in the respective service documents shall be confirmed by attempting to insert 0.0015 inch feeler gauge between the shell and tip block. See Note 2.

Note 1. The coin tap test method is not considered a valid means of determining separation at this location.

Note 2. Peel tests on various rejected blades have shown that separation can exist without being visually obvious.

3. Replace the existing five (5) rivets in the tip block area with rivets P/N CSR903B4-14 as described in Bell Alert SB’s 206-85-28 Rev B and 206L-85-34 Rev B.

Compliance: 1. Inspect in accordance with requirement item 1 at each daily inspection after

20 February, 1984. Any suspected void or separation shall be confirmed before further flight in accordance with requirement item 2.

Note: For aircraft maintained in accordance with ANO 100.5.1 this inspection shall be entered on the maintenance release as maintenance required. Inspection in accordance with requirement item 1 may be performed by the pilot in command on a daily basis, in which case certification is not required. In all other cases certification shall be made on the maintenance release. This inspection may also be performed and certified for by any licensed aircraft maintenance engineer.

2. Install rivets in accordance with requirement item 3 on or before 1 January 1986.

3. Repeat inspections in accordance with requirement items 1 and 2 at intervals not exceeding 100 hours time in service after compliance in accordance with requirement item 3.

Background: This directive is amended to revise the Requirement Document issue status and the Compliance date.