Airworthiness directives › 2022-22-08
AD 2022-22-08 Airworthiness Directives; Bell Textron Canada Limited (Type Certificate Previously Held by Bell Helicopter Textron Canada Limited) Helicopters
Models named: 206L, 206L-1, 206L-3, 206L-4. Read the applicability below — it usually turns on serial or part numbers too.
Applicability*9
This AD applies to Bell Textron Canada Limited (type certificate previously held by Bell Helicopter Textron Canada Limited) Model 206L, 206L-1, 206L-3, and 206L-4 helicopters, certificated in any category, with main rotor (M/R) blade part number (P/N) 20633000-101 with serial number A007, A008, A009, or A012 through A104 inclusive, installed under Supplemental Type Certificate SR02684LA.
Compliance
Comply with this AD within the compliance times specified, unless already done.
Required actions
(1) Accomplish the actions required by paragraph (g)(2) of this AD at the following compliance time, whichever occurs later: (i) Before the M/R blade accumulates 400 total hours time-in-service (TIS) or 2,400 engine starts since initial installation on any helicopter, whichever occurs first; or (ii) Within 100 hours TIS after the effective date of this AD. (2) Remove each M/R blade from the helicopter, place it on a flat, stable surface, and accomplish the following: (i) Use a permanent marker to draw rectangular inspection “Zone 1” on the upper surface of the M/R blade at M/R blade stations 185.75 and 192.75, or measured from the tip end of the M/R blade between 36.25 inches and 29.25 inches, beginning 1.2 inches from the leading edge of the M/R blade to 5.0 inches from the leading edge of the M/R blade. Draw lines from the inboard end to the outboard end to connect each end at 1.2 inches and 5.0 inches. Draw parallel lines from the inboard end of the inspection zone to the outboard end of the inspection zone, with the lines spaced 0.50 inch apart. Note 1 to paragraph (g)(2)(i): This note applies to paragraphs (g)(2)(i) and (ii) of this AD. Figure 4 of Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-4R3, dated November 8, 2021 (SB 33000-4R3), and Van Horn Aviation, LLC, Service Bulletin Notice No. 33000-4R4, dated March 31, 2022 (SB 33000-4R4) depict “Zone 1” and “Zone 2.” (ii) Use a permanent marker to draw rectangular inspection “Zone 2” on the lower surface of the M/R blade at M/R blade stations 185.9 and 192.9, or measured from the tip end of the M/R blade between 36.1inches and 29.1 inches, beginning from the forward edge of the weight receptacle pocket and extending 1 inch in the direction towards the leading edge of the M/R blade. Draw lines from the inboard end to the outboard end to connect each end at the weight receptacle pocket and 1 inch forward of the weight receptacle pocket. Draw parallel lines from the inboard end of the inspection zone to the outboard end of the inspection zone, with the lines spaced 0.50 inch apart. (iii) Using composite tap hammer Abaris Training Tap Hammer P/N ABATH, HeatCon Tap Hammer P/N HCS1104-01, Brown Tool Composite Tap Hammer P/N BAT-CTH8, MATCO Tools Composite Tap Hammer P/N T4BAT-CTH8, or Van Horn Aviation Tap Hammer P/N VHACS0003, tap inspect the areas within “Zone 1” and “Zone 2” for any delamination by following Tap Inspect Balance Receptacle, paragraph A.(4) of SB 33000-4R3 or SB 33000-4R4. Where SB 33000-4R3 and SB 33000-4R4 specify to mark the location where the delamination starts, use a permanent marker. (iv) If there are any marks where the delamination starts, connect the marks indicating the delamination location and measure the length at the farthest point from the inboard end of the inspection area. (v) If there is any delamination in the lower surface inspection zone (“Zone 2”) that is 6.0 or more inches in length or if there is any delamination in the upper surface inspection zone (“Zone 1”), before further flight, remove the M/R blade from service. (3) Thereafter repeat the actions required by paragraph (g)(2) of this AD at intervals not to exceed 400 hours TIS or 2,400 engine starts, whichever occurs first. (4) If there is any delamination, within 30 days after accomplishing the actions required by paragraphs (g)(1) or (3) of this AD, report each delamination size and location, and the total hours TIS and total engine starts since initial installation of the M/R blade, to Mr. Dean Rosenlof, Van Horn Aviation, LLC, 1510 West Drake Drive, Tempe, AZ 85283, or by email to info@vanhornaviation.com.
Unsafe condition
This AD was prompted by reports of delamination of M/R blades. The FAA is issuing this AD to address delamination of an M/R blade initiating in the 90° plies at the lower inboard end of the weight pocket receptacle. The unsafe condition, if not addressed, could result in reduced structural integrity of the M/R blade, excessive vibration, and subsequent loss of control of the helicopter.
Affected ADs
None.
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