AD 87-26-02 R1
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus Helicopters Deutschland GmbH | BO-105A | Airworthiness Directives; MESSERSCHMITT-BOLKOW-BLOHM (MBB) Model BO-105 Series Helicopters |
| aircraft | Airbus Helicopters Deutschland GmbH | BO-105C | Airworthiness Directives; MESSERSCHMITT-BOLKOW-BLOHM (MBB) Model BO-105 Series Helicopters |
| aircraft | Airbus Helicopters Deutschland GmbH | BO-105LS A-1 | Airworthiness Directives; MESSERSCHMITT-BOLKOW-BLOHM (MBB) Model BO-105 Series Helicopters |
| aircraft | Airbus Helicopters Deutschland GmbH | BO-105LS A-3 | Airworthiness Directives; MESSERSCHMITT-BOLKOW-BLOHM (MBB) Model BO-105 Series Helicopters |
| aircraft | Airbus Helicopters Deutschland GmbH | BO-105S | Airworthiness Directives; MESSERSCHMITT-BOLKOW-BLOHM (MBB) Model BO-105 Series Helicopters |
Unsafe Condition
Fatigue cracks in the threads of the main rotor pitch links rod ends, P/N's 105-13141.01 and 105-13142.01, could result in failure of the main rotor control system.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Check main rotor control rods for binding of spherical bearings before first flight daily. Within 50 hours' time in service after the effective date, inspect rod ends for cracks and corrosion via fluorescent magnetic particle or dye penetrant methods. Replace cracked or corroded rod ends before further flight. Repeat inspections after each bearing replacement.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight for cracked or corroded rod ends. Initial inspection required within 50 hours' time in service after the effective date of this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Messerschmitt-Bolkow-Blohm (MBB) Model BO-105A, BO-105C, BO-105LS A-1, BO-105LS A-3, BO-105S helicopters equipped with main rotor blade rotating control rod ends, P/N's 105-13141.01 and 105-13142.01.
AI-generated summary from the source AD text. Verify against the official source before acting.
Source: Official FAA Source ↗
Retrieved: Apr 8, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.