CTHIn ForceLegislation
AD/PREMIER/3 - Hydraulic Pump Outlet Tubes
Hawker Beechcraft (Raytheon) 390 Series Hawker Beechcraft (Raytheon) 390 Series Aeroplanes
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Hawker Beechcraft (Raytheon) 390 Series Aeroplanes
| AD/PREMIER/3 | Hydraulic Pump Outlet Tubes | 13/2007 TX |
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| Applicability: | Hawker Beechcraft Corporation Model 390 aeroplanes:- Serial numbers RB-1 through RB-49 that have Field Service Kit 390-9100 installed; and- Serial numbers RB-50 through RB-209. |
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| Requirement: | 1. Visually inspect the hydraulic pump outlet tube for evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage, as follows:a. For the left-hand (LH) engine: Remove the clamp, perform the inspection, and replace the clamp with a new one as specified in Raytheon Mandatory Service Bulletin No. SB 29-3771 dated January 2006, after each inspection.b. For the right-hand (RH) engine: Perform the inspection. Removal and replacement of the clamps are not necessary.Inspect following Raytheon Safety Communiqué No. 267, dated January 2006. Raytheon Safety Communiqué No. 267 addresses the LH engine. Use the same inspection procedures for the RH engine hydraulic pump outlet tube (P/N390-580037). Remove and replace the clamp (LH only) following Raytheon Mandatory Service Bulletin No. SB 29-3771.2. Replace the hydraulic pump outlet tube, part number (P/N) 390-580035 (orFAA-approved equivalent) for the LH engine or P/N 390-580037 (orFAA-approved equivalent) for the RH engine in accordance with Raytheon Aircraft Premier 1 Model 390 Maintenance Manual, P/N 390-590001-0015.3. Incorporate Raytheon Aircraft Company Part Number 390-590001-0003C3TC6, dated September 16, 2006 into the aircraft flight manual (AFM).4. Unless previously accomplished, incorporate Kits No. 390-5804-0001 and390-5805-0001Note: FAA AD 2007-12-21 Amdt 39-15099 dated 4 June 2007 refers. |
| Compliance: | 1. Within the next 25 hours TIS after the effective date of this AD and thereafter at intervals not to exceed 25 hours time-in-service (TIS) until the kits detailed in Requirement 4 of this AD are incorporated.2. Each and every time any of the following occurs until the kits detailed in Requirement 4 of this AD are incorporated:a. Prior to further flight after any inspection detailed in Requirement 1 of this AD where evidence of chafing, excessive vibration, wear, deterioration, or hydraulic fluid leakage is found; andb. Within 1 hour TIS following identification of an intended or unintended engine operation with the hydraulic shutoff valve closed.3. Within 5 days after the effective date of this AD, unless previously accomplished.4. Within the next 25 hours TIS after the effective date of this AD, or within the next 45 days after the effective date of this AD, whichever occurs first. |
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