Airworthiness Directive · Amendment 39-11970 · Raytheon Model Hawker 800XP and Hawker 800 (U-125A) Series Airplanes
Raytheon Model Hawker 800XP and Hawker 800 (U-125A) Series Airplanes
Model Hawker 800XP series airplanes, as listed in Raytheon Service Bulletin SB 24-3212, dated August 1999; and Hawker 800 (U-125A) series airplanes, as listed in Raytheon Service Bulletin SB 24-3213, dated February 2000; certificated in any category.
Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model Hawker 800XP and Hawker 800 (U- 125A) series airplanes, that requires inspection of the wire bundle to relay "KT" on panel "JA" for correct routing, adequate clearance from the fuel cross-feed valve operating lever, and the presence of chafing; this amendment also requires corrective action, if necessary. The actions specified by this AD are intended to detect and correct chafing of the wire bundle exiting panel "JA" due to insufficient clearance from the fuel cross-feed valve operating lever. Such chafing of the wire bundle could result in a fire in the area of the fuel system in a confined space. This action is intended to address the identified unsafe condition.
To detect and correct chafing of the wire bundle exiting panel “JA” due to insufficient clearance from the fuel cross-feed valve operating lever, which could result in a fire in the area of the fuel system in a confined space, accomplish the following:
(a) Within 50 flight hours or 6 months after the effective date of this AD, whichever comes first, conduct a one-time detailed visual inspection of the panel “JA” wire bundle in accordance with the Accomplishment Instructions of Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999 (for Model 800XP series airplanes); or SB 24-3213, Revision 1, dated February 2000 (for Model 800 (U-125A) series airplanes; as applicable.
(1) Ensure that the wire bundle is routed correctly, in accordance with Figure 1 of the applicable service bulletin.
(2) Ensure that a minimum clearance of 0.25-inch exists between the wire bundle from relay “KT” and the fuel cross-feed valve operating lever throughout its range of travel.
Note 2: For the purposes of this AD, a detailed visual inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”
(b) If the wire bundle is routed correctly and sufficient clearance exists, no further action is required by this AD.
(c) If the wire bundle is not routed correctly or if sufficient clearance does not exist, prior to further flight, perform a detailed visual inspection of the wire bundle to relay “KT” for chafing, in accordance with the Accomplishment Instructions of Raytheon Aircraft Service Bulletin SB 24-3212, dated August 1999 (for Model 800XP series airplanes); or SB 24-3213, Revision 1, dated February 2000 (for Model 800 (U-125A) series airplanes); as applicable.
(1) If no chafing is detected, prior to further flight, ensure that the wire bundle is routed correctly and ensure that a minimum clearance of 0.25-inch exists between the wire bundle and the fuel cross-feed valve operating valve throughout its range of travel, in accordance with the applicable service bulletin.
(2) If any chafing is detected, prior to further flight, repair the chafed wire, ensure that the wire bundle is routed correctly and ensure that a minimum clearance of 0.25-inch exists between the wire bundle and the fuel cross-feed valve operating valve throughout its range of travel, in accordance with the applicable service bulletin.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
