Covers Multiple Models With Retractable Landing Gear

The FAA has issued a Special Airworthiness Information Bulletin (SAIB) concerning landing gear actuators on Textron Aviation Inc. (Cessna Aircraft Company) Models 172RG, R182, TR182, FR182, and all variants of 210/T210/P210-series airplanes with the exception of the Models 210 and 210A airplanes. The intent is to emphasize the importance of the inspection of main landing gear actuator assemblies following Textron Aviation Inc. supplemental inspection documents (SIDs) applicable to each model to prevent malfunctions related to gear extension and retraction.

The FAA recently investigated an accident involving a Model 172RG airplane that had performed a gear up landing when the pilot was unsuccessful in getting the left main gear down and locked. During review of the landing gear system, investigators found the left main gear actuator (part number 9882015-2) housing cracked across the forward attach bolt hole. The crack allowed the actuator bore to open enough such that the piston would not engage the landing gear pivot sector sufficiently to move the gear. This failure will result in the affected side not being able to fully retract or extend through normal method or prevent use of the emergency hand pump.

The main landing gear was subject to FAA AD 2001-06-06 and required inspection for cracks in the gear pivot assemblies. However, the area of concern identified through this SAIB addresses the actuator assembly that mates with the main gear pivot. The FAA has published maintenance alerts (Advisory Circular 43-16) in prior years highlighting this issue and Textron Aviation published SEB01-2 in 2001 and later revised in 2007 to address the need for initial and repetitive inspections of the actuators. Textron later published inspection techniques and times within their SIDs.

The FAA has found through our review that most service difficulty reports (SDRs), incidents, or accidents occur on the Model 172RG airplane. We believe this is primarily due to its heavy use in a training environment. Our review of over 100 SDRs identifying cracks in the actuator reflect mechanics and inspectors finding the majority of these during scheduled inspections (100 hour/annual) and often referencing Cessna bulletin SEB01-2.

Textron (Cessna) produced several actuator assembly and actuator body part numbers with different version or dash numbers for use on the affected airplane models. Actuator assemblies utilize base part number 1298100, 1281000, 1281006, 9882000, and 9882015. Actuator bodies utilize base part number 1281001 and 1241619.

The FAA recommends performing the inspections detailed in Textron SID 32-10-01 appropriate for the applicable airplane model. These inspections incorporate a combination of visual, fluorescent penetrant, and eddy current depending on the airplane model.

Initial inspection of the actuator is recommended at 3,000 hours time-in-service (TIS) or 10 years of age, whichever occurs first, for all models except the 210/T210 series airplanes produced from 1962 to 1968. Repetitive inspections are recommended every 500 hours (TIS) or 5 years, whichever occurs first.

Initial Inspection Of The Actuator Is Recommended At 6,000 Hours (Tis) Or 10 Years Of Age, Whichever
Occurs First, For 210/T210 Series Airplanes Produced From 1962 To 1968 With Repetitive Inspections At
1,000 Hours Tis Or 3 Years, Whichever Occurs First.

Additionally, an inspection is recommended following any unplanned event such as a hard landing to ensure cracks have not developed.

(Images provided with FAA SAIB)

FMI: SAIB