Airworthiness Directive · Amendment 39-19131 · Elevator structure
Agusta S.p.A. Helicopters
This AD applies to Model A109S and AW109SP helicopters with elevator assemblies, part number (P/N) 109-0200-02-601, 109-0200-02-801, 109-0200-02-602, 109-0200-02-802, 109-0200-02-803, or 109-0200-02-804 installed, certificated in any category.
We are superseding airworthiness directive (AD) 2011-27-08 for Agusta S.p.A. (Agusta) Model A109S and AW109SP helicopters. AD 2011-27- 08 required repetitively inspecting each elevator assembly for a crack. This new AD retains the initial inspection interval and adds a repetitive borescope inspection. This AD is prompted by the discovery of another crack on an elevator assembly since AD 2011-27-08 was issued. The actions of this AD are intended to prevent an unsafe condition on these helicopters.
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 further flight or before the elevator assembly accumulates 400 hours time-in-service (TIS), whichever occurs later, inspect the left and right elevator upper skin along the 4th rib station rivet line from the leading edge to 200 mm aft with a 10X or higher power magnifying glass for a crack in the area depicted in Figure 1 of Leonardo Helicopters Emergency Alert Service Bulletin (EASB) No. 109S-076, Revision A, dated May 12, 2017 (EASB 109S-076), or EASB No. 109SP-113, Revision A, dated May 12, 2017 (EASB 109SP-113), as appropriate for your model helicopter. If there is a crack, before further flight, replace the elevator assembly.
(2) Within 10 hours TIS or before the elevator assembly accumulates 400 hours TIS, whichever occurs later:
(i) Drill a 19.05 mm access hole on the lower face of each elevator assembly as depicted in Figure 2 of EASB 109S-076 or EASB 109SP-113, as appropriate for your model helicopter. Apply Alodine or equivalent coating and epoxy polyamide primer to the hole surface.
(ii) Using a borescope, inspect the internal area of each elevator assembly for a crack along the leading edge and trailing edge longerons and upper web as depicted in Figure 3 of EASB 109S-076 or EASB 109SP-113, as appropriate for your model helicopter. If there is a crack, before further flight, replace the elevator assembly. Repeat this inspection at intervals not to exceed 25 hours TIS.
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
