Airworthiness Directive · Amendment 39-21724 · Landing gear system
RUAG Aerospace Services GmbH (Type Certificate Previously Held by Dornier Luftfahrt GmbH) Airplanes
This AD applies to RUAG Aerospace Services GmbH (Type Certificate Previously Held by Dornier Luftfahrt GmbH) Model Dornier 228-212 airplanes, all serial numbers, certificated in any category.
The FAA is superseding Airworthiness Directive (AD) 2007-02- 13, which applied to certain Dornier Luftfahrt GmbH (type certificate currently held by RUAG Aerospace Services GmbH) Model Dornier 228-212 airplanes. AD 2007-02-13 required inspecting the landing gear carbon brake assembly. This AD requires inspecting certain carbon brake assemblies and corrective actions if necessary. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by the European Union Aviation Safety Agency (EASA) to correct an unsafe condition on an aviation product. The MCAI identifies the unsafe condition as loose bolts and nuts on the landing gear carbon brake assembly. The FAA is issuing this AD to address the unsafe condition on these products.
(1) For purposes of this AD, an affected part is a carbon brake assembly having part number (P/N) 5009850-1, P/N 5009850-2, P/N 5009850-3, or P/N 5009850-4.
(2) For purposes of this AD, a Group 1 airplane is an airplane with an affected part that has never been overhauled installed.
(3) For purposes of this AD, a Group 2 airplane is an airplane with an affected part that has been overhauled installed.
(1) For Group 1 airplanes: Before further flight and thereafter at intervals not to exceed 50 hours time-in-service (TIS) or 150 flight cycles, whichever occurs first, inspect each affected part for tight fit and damage of the bolts and self-locking nuts and for a gap between the brake housing subassembly and the torque tube subassembly, and take any necessary corrective actions before further flight in accordance with steps (1)a) through (1)c) of the Accomplishment Instructions in RUAG Dornier 228 Alert Service Bulletin No. ASB-228-265, Revision 2, dated December 10, 2019, except you are not required to contact the manufacturer. Instead, repair using a method approved by the Manager, International Validation Branch, FAA, or the European Union Aviation Safety Agency (EASA), or replace the brake assembly.
(2) For Group 2 airplanes: Before further flight and thereafter at intervals not to exceed 150 hours TIS, inspect each affected part for tight fit and damage of the bolts and self-locking nuts and for a gap between the brake housing subassembly and the torque tube subassembly, and take any necessary corrective actions before further flight in accordance with steps (2)a) through (2)c) of the Accomplishment Instructions in RUAG Dornier 228 Alert Service Bulletin No. ASB-228-265, Revision 2, dated December 10, 2019, except you are not required to contact the manufacturer. Instead, repair using a method approved by the Manager, International Validation Branch, FAA, or EASA, or replace the brake assembly.
As of the effective date of this AD, do not install an affected part on any airplane unless, prior to installation, you have complied with this AD.
