AD 2008-23-13 Airworthiness Directives; Hawker Beechcraft Corporation Model 390 Airplanes

Makes named: hawker beechcraft. Models named: 390. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Model 390 airplanes, serial numbers RB-4 through RB-224, that are certificated in any category.

To address this problem, you must do the following, unless already done:   Actions Compliance Procedures (1) Remove current preformed packing (part number (P/N) MS28778-6), elbow fitting (P/N MS21908J6), and jam nut (P/N AN924-6J) from the left and right hydraulic pump pressure output port and install new preformed packing (P/N MS28778-6), union (P/N MS21902J6), and swivel fitting (P/N NAS1762J0606) in the left and right hydraulic pressure pump output port Within the next 200 hours time-in-service (TIS) after December 22, 2008 (the effective date of this AD) or within the next 6 months after December 22, 2008 (the effective date of this AD), whichever occurs first Follow Hawker Beechcraft Mandatory Service Bulletin SB 29-3869, dated January 2008. (2) Install hydraulic pump case drain check valve Kit No. 390-5803-0001 Within the next 200 hours TIS after December 22, 2008 (the effective date of this AD) or within the next 6 months after December 22, 2008 (the effective date of this AD), whichever occurs first Hawker Beechcraft Mandatory Service Bulletin SB 29-3851, dated January 2008. Alternative Methods of Compliance (AMOCs) (f) The Manager, Wichita Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Aaron Waters, Aerospace Engineer, Wichita ACO, 1801 Airport Road, Room 100, Wichita, Kansas 67209; telephone: (316) 946-4174; fax: (316) 946-4107. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. Material Incorporated by Reference (g) You must use Hawker Beechcraft Mandatory Service Bulletin SB 29-3869, dated January 2008; and Hawker Beechcraft Mandatory Service Bulletin SB 29-3851, dated January 2008, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Hawker Beechcraft Corporation, 9709 East Central, Wichita, Kansas 67201; telephone: (316) 676-5034; fax: (316) 676-6614; Internet: https://www.hawkerbeechcraft.com/service_support/pubs/ . (3) You may review copies at the FAA, Central Region, Office of the Regional Counsel, 901 Locust, Kansas City, Missouri 64106; or at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . Issued in Kansas City, Missouri, on November 5, 2008. Patrick R. Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. E8-26879 Filed 11-14-08; 8:45 am] BILLING CODE 4910-13-P

This AD results from nine occurrences of hydraulic fluid leaking from the engine hydraulic pump output fitting as a result of an improperly installed elbow connecting the output port to the pulse dampener hose. We are issuing this AD to prevent hydraulic fluid leaking from the left and right hydraulic fluid pump and to prevent the flow of hydraulic fluid into the engine compartment. The loss of hydraulic fluid can result in loss of airplane hydraulic system pressure and the consequent loss of hydraulic system functions including gear extension/retraction, spoiler functions, and anti-skid braking system actuation. The inability of the hydraulic installation to isolate flow of hydraulic fluid could result in a hazardous amount of flammable fluid in the corresponding engine compartment. These conditions, if not corrected, could result in loss of system functions and/or fire in the engine compartment.