Airworthiness Directive · Amendment 39-22066 · Rudder control system
British Aerospace (Operations) Limited and British Aerospace Regional Aircraft Airplanes
This AD applies to British Aerospace (Operations) Limited Model Jetstream Model 3101 airplanes and British Aerospace Regional Aircraft Model Jetstream Model 3201 airplanes, all serial numbers, certificated in any category.
The FAA is adopting a new airworthiness directive (AD) for all British Aerospace (Operations) Limited Model Jetstream Model 3101 airplanes and British Aerospace Regional Aircraft Model Jetstream Model 3201 airplanes. This AD was prompted by mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as stress corrosion cracking of the primary flight control cable terminals. This AD requires repetitively inspecting the turnbuckle type control cable terminals in the rudder and elevator primary flight control circuits for corrosion, pitting, and cracking and, depending on the inspection results, replacing an affected cable assembly. The FAA is issuing this AD to address the unsafe condition on these products.
(1) Before any primary rudder or primary elevator flight control circuit cable accumulates 16 years since first installation on an airplane or within 12 months after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 24 months, inspect all threaded turnbuckle type control cable terminals for signs of corrosion, pitting, and cracking by following paragraph (2) in Section 2.B. Part 1 and Section 2.B. Part 2 of the Accomplishment Instructions in British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 27-JA181040, Original Issue, dated January 17, 2019 (SB 27-JA181040). If the age of any primary rudder or primary elevator flight control circuit cable is unknown, do the inspection within 12 months after the effective date of this AD and thereafter at intervals not to exceed 24 months.
(2) If, during any inspection required by paragraph (g)(1) of this AD, there is pitting or cracking or corrosion that exceeds minimum damage limits, before further flight, replace the affected cable assembly with a new (zero hours time-in-service) cable assembly.
(3) Replacing a cable assembly does not terminate the inspections required by this AD. After replacing a cable assembly, do the inspection in paragraph (g)(1) of this AD before the cable assembly accumulates 15 years since first installation on an airplane and thereafter at intervals not to exceed 24 months.
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
