Document ID: chunk:federal_register_of_legislation:F2006B10440:body:0:p2
Version: federal_register_of_legislation:F2006B10440
Segment Type: other
Provision Reference: 
Character Range: 2961–4749

shielded wire. Ensure a minimum 0.25-inch clearance exists between the wire bundle and valve actuator; and install spiral wrap, as necessary, in accordance with the service bulletin.

5.    Perform a borescope inspection of the entire forward wing spar/forward ventral tank area for chafing of any other wire or wire bundle; and install spiral wrap, as necessary; in accordance with Raytheon Aircraft Service Bulletin SB 24-3201 dated October 1998.

6.    Perform the applicable action when the following conditions are found during the Requirement 5 inspection:

                1. No chafing - No further action is required by this Airworthiness Directive.

               b.    Chafed wire or wire bundle - Repair in accordance with a method approved by the Head, Certification Standards Branch, Standards Division, CASA. For a repair method to be approved by the Head, Certification Standards Branch, as required by this paragraph, the approval letter must specifically reference this Airworthiness Directive.

           Note 2: FAA AD 99-23-10 Amdt 39-11406 refers.

 Compliance: 1. Within 50 hours time in service after 17 December 1999.

2.    Prior to further flight.

3.    Within 50 hours time in service after 17 December 1999.

4.    Prior to further flight.

5.    Within 50 hours time in service after 17 December 1999.

6.    Prior to further flight.

           This Airworthiness Directive becomes effective on 17 December 1999.

           Background:  Raytheon has received a report of wire bundle chafing against the forward tank transfer/crossfeed valve which caused an electrical short and resulted in the failure of a landing light. This directive is intended to prevent a short circuit caused by wire chafing, which can cause a fire in the ventral fuel tank area.