| 11-9-18 |
Dassault |
Install dedicated fuses on WOW proximity sensors as specified if applicable | Falcon 7X |
| 11-8-6 |
Honeywell |
AD is due to reports of fatigue cracks in the airfoil of the power turbine blade, see AD for details | LTS-101-600A-2, -650B-1, -650C-2, -650C-3, -750C-1 |
| 11-8-1 |
Bell Helicopter |
Superseded by 13-3-16 |
| 11-7-13 |
CPAC |
Superseded by 12-2-10 |
| 11-7-11 |
Dassault |
Visually inspect the extinguishing system line and the low pressure bleed line of the number 2 engine at frame 42 in the rear compartment as specified | Falcon 50 |
| 11-7-10 |
Bombardier |
Supersedes 10-10-18 | Revise Airworthiness Limitations section of the Instructions for Continued Airworthiness as specified | Challenger 300 |
| 11-6-7 |
Eurocopter |
Helicopters with an applicable flotation gear unit, see AD for details | EC130B4 |
| 11-6-6 |
Eclipse |
Supersedes 08-24-7 | Applicable to EA500s with P&W610F-A engines; add text in AD to the Limitation's section of the AFM as specified | EA500 |
| 11-6-10 |
Piper |
Supersedes 99-15-4 | Perform turbine inlet temperature guage and probe cleaning, inspection and calibration and copy AD to POH | PA-46-350P |
| 11-5-8 |
Turbomeca |
Supersedes 11-5-51 | AD propmted due to incorrectly assembled low-pressure fuel system ejectors, see for details | Arriel 1E2, 1S, 1S1 |
| 11-5-7 |
Allied Ag Cat |
Supersedes 08-22-21 | Inspect rudder tubular spar for corrosion | G164, A, G164B |
| 11-5-51 |
Turbomeca |
Superseded by 11-5-8 |
| 11-5-1 |
Piaggio |
AD due to compass mismatch due to ferro-magnetic masses stowed in the baggage compartment, see for details | P-180 |
| 11-4-8 |
Bombardier |
Visually inspect for damage of wiring and correct routing in left & right circuit breaker panels as specified | Learjet 45 |
| 11-3-6 |
Eurocopter |
Remove and replace the aluminum T/R blade pitch control shaft with a steel shaft as specified | AS-365N2, N3 and SA-365N1 |
| 11-3-4 |
Cessna |
Supersedes 09-9-9 | Inspect/repair rudder hinges and hinge brackets as specified | LC-40, -41, -42 |
| 11-3-3 |
Bell Helicopter |
Inspect the tail rotor driveshaft hanger bearing bracket p/n 427-044-223-101 for cracks as specified | 427 |
| 11-3-2 |
Eurocopter |
Within the next 10 hours TIS do a functional test of the pedal unit adjustment system as specified | SA330J |
| 11-3-16 |
Cessna |
AD to detect and correct overvoltage condition on the DC electrical busses caused by exciter stator winding failures | Citation X |
| 11-3-12 |
Hawker Beechcraft |
Perform a detailed inspection for appropriate coverage of firewall sealant, left and right pylon firewall structure as specified | 400A and T |
