Multi-Engine Turboprop Communiqué ME-TP-0024

case by case basis. Damage to the axles are reviewed by engineering through the structures team. When you contact the structures team, they will ask you to do the following. Note: With the intent of saving you some time we have included the preliminary steps that the structures team will required before they can assist: 1. Locally strip cad plate in damage areas; 2. Locally blend and polish smooth, removing minimum amount of material necessary to clear all damage and achieve a smooth profile. Maintain 5:1 minimum blend slope and 63 RMS (or better) surface finish; 3. Magnetic particle inspect the axle per ASTM E1444, using acceptance criteria per MIL-STD-1907 Grade A; 4. Use Ultrasonic NDT method to determine remaining wall thickness within the blend area(s); and 5. Complete and submit a Structural Damage Report (SDR) form along with post blend data (wall thickness/blended area dimensions) and photographs of blend areas. The form is found at https://ww2.txtav.com/service/tasdaq and requires login with your customer account. Contact team structures at Structures@txtav.com or technical support at teamturboprop@txtav.com for assistance. Issue: January 2021 Page 6 of 8 Communiqué ME-TP-0024 ATA 32- Placarding tire pressure Effectivity: All It is of utmost importance to verify that the tire pressures are kept at the proper inflation pressures. This ensures longevity of the tread and proper safe operation of the wheel assembly. To make the task easier for maintenance personnel servicing the tires you can placard the tire pressure on a pressure sensitive tape made locally. Suggested placards should be placed on the inside of the affected gear doors (location as desired). Below is a suggested format. These can be made any size and font as desired. Consult the appropriate Maintenance Manual for the correct tire pressures for the model. ATA 34 – Loss of GPS signal Textron Aviation has received reports of operators losing GPS signal while the aircraft is on the ground taxiing, parked on the ramp, or kept in a hanger. A loss of GPS signal will affect operations of multiple systems including; transponder operation, ADS-B operation, FMS navigation, FMS operation, etc. Depending on the avionics suite installed in the aircraft, different annunciations will be displayed when GPS signal is lost. For example, a loss of GPS signal in a Collins Aerospace equipped aircraft will usually present itself as a transponder failure, while a Garmin equipped aircraft will present GPS loss as an ADS-B failure. It has been determined that these signal losses are usually caused by local interference. This interference may come from: (1) hangers and other structures located in the area, (2) local GPS repeaters, or (3) GPS jamming. Should you experience an issue with any of these systems, position the aircraft at least 100 feet away from any hanger, structure, repeaters, etc. Request any hanger doors in close proximity be closed, if possible, to prevent a repeater from interfering with the GPS signal. You may also notice that while taxiing past certain facilities or areas of an airport, you may receive a message or fault associated with a loss of GPS signals. Lots of electronic devices emit frequencies that are stronger than GPS signals and can overwhelm the relatively low power of a GPS signal. These devices can be anything from automatic door openers, security systems or many other electronic devices. The FCC regulates the output frequencies and power levels of these systems, but they can interfere with a GPS signal when in close proximity. While in flight these sources of interference are far too weak to cause an issue. Issue: January 2021 Page 7 of 8 Communiqué ME-TP-0024 ATA 57- Wing bolt washer-MTL-57-01 and AD 2020-25-01 clarification Effectivity: When applicable Textron Aviation issued MTL-57-01 to alert operators of the installation of Preload Indicating Washer (PLI) that would reach its torqueing value too early which is needed for the application in the lower forward wing fitting. The FAA has issued a corresponding Airworthiness Directive (AD), 2020-25-01. The purpose of this article is to provide additional clarity around the serial effectivity for the Multi-Engine Turboprop Letter (MTL) and AD. MTL-57-01 and AD 2020-25-01 are applicable to the aircraft listed in the model effectivity that have had kits 90-4077 or 101-4024 installed. Notice that C90A, C90B and C90GTs are not listed although they also carry the LJ prefix on the serial number. This MTL is NOT applicable to aircraft with the clevis type lower forward wing fitting, only aircraft with the bathtub style wing fitting. Kit 90-4077 replaces the center section lower main spar cap and the outboard wing spar assemblies. The wing fittings on this spar system are integral to the spar caps. Kit 101-4024 replaced the original steel wing bolts with Inconel wing bolts. This kit is associate with Service Instruction 1235 published in November,1982. Once it has determined if one or both of these kits has been incorporated then inspection of the washers using the colors mentioned in the MTL is needed to determine applicability. The color of the washer is irrelevant outside of these kits. ATA 71- Engine mounts Beechcraft part numbers vs. vendors’ Effectivity: All The Beechcraft King Air Illustrated Parts Catalog provides the part numbers of the engine mounts using the Beechcraft part number. When looking for replacement parts or damage limit information you must refer to the King Air Component Maintenance Manual (CMM) but you may need to know the vendor’s part number for either Barry Control Aerospace or Lord Corporation. Following find a cross reference between the Beechcraft part number and the vendor part number to help you find the correct CMM. As a reminder, each engine must have the same brand of engine isolators. Beechcraft part number Vendor part number 50-389133-3 LM-412-SA11 50-389133-9 5906-2SA1 50-389133-11 5906-2SA4 50-389133-13 LM-427-SA1 50-389133-15 5906-2SA5 50-389133-17 LM-427-SA7 114-389031-15 93880-9 117-389012-1 93880-18 114-389031-17 93880-19 129-389001-7 95596-1 Issue: January 2021 Page 8 of 8 Communiqué ME-TP-0024 ATA 76 – Autothrottle programming cable Effectivity: Beechcraft King Air FL-1201, FL-1234 & after; BY-393 & after IS&S Thrustsense Autothrottle Ops & install manual 1D-88129 is available on the Instructions for Continued Airworthiness page on http://txtavsupport.com. Appendix B has the procedure for system data loading that may be necessary if an autothrottle component is replaced. A cable is required to connect the RS-485 serial interface from a PC to the maintenance port of the autothrottle standby unit. Textron Aviation has a cable available for this interface, part number PR00145715, or a harness can be fabricated as follows: 1) USB to serial adapter, ICUSB422 or equivalent. Set DIP switch 1 to the RS-485 setting; 2) M24308/2-1F or equivalent 9-pin dsub plug with socket contacts; 3) M24308/4-4F or equivalent 37-pin dsub jack with pin contacts; and 4) Approx. 6 feet of 22 gage wire, twisted shielded if available. This cable connects to the pedestal maintenance port 3456J2 shown in WDM 34-25-01.