AD/Premier/3 Hydraulic Pump Outlet Tubes (Cth)

AIRWORTHINESS DIRECTIVE

For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Hawker Beechcraft (Raytheon) 390 Series Aeroplanes

AD/PREMIER/3 Hydraulic Pump Outlet Tubes 13/2007 TX

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.

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/N
390-580037).  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 (or
FAA-approved equivalent) for the LH engine or P/N 390-580037 (or
FAA-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 and
390-5805-0001

Note:  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; and

b.    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.

This Airworthiness Directive becomes effective on 5 November 2007.

Background:

This AD is the result of continuing failures of the hydraulic pump outlet tubes and the need to incorporate improved design.  The issuing of this AD is to prevent failure of the hydraulic pump outlet tube and consequent leaking of hydraulic fluid.  Such leakage could result in a fire.  There is also a risk of loss of hydraulic system functions including normal gear extensions, speed brakes, roll spoilers, lift dump, and normal brakes.

David Punshon
Delegate of the Civil Aviation Safety Authority

29 October 2007