Document ID: chunk:federal_register_of_legislation:F2006B08365:body:0:p2
Version: federal_register_of_legislation:F2006B08365
Segment Type: other
Provision Reference: 
Character Range: 3024–5916

in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 2.75 inches, replace the engine beam with a part number specified in the instructions to Service Kit SK414-19B, Revised 4 March 1986.

             4.    If parts for any of the engine beam modifications required by Requirements 1 and 2 of this Directive have been ordered from the manufacturer but are not available, accomplish the following in accordance with the Accomplishment Instructions section of Attachment to Service Bulletin MEB85-3, Revised 23 August 1985; as referenced in Cessna Service Bulletin MEB85-3, Revision 2, dated 23 October 1987:

(a)     For aircraft with Cessna Kit SK414-17 incorporated, inspect the engine mount beams using radiographic methods.

(b)     For aircraft without Cessna Kit SK414-17 incorporated, fluorescent penetrant inspect the engine mount beams.

             5.    If any of the following occurs during any of the inspections required by Requirement 4 of this Directive, accomplish the following specified actions:

(a)     If parts become available, terminate the repetitive inspections specified in Requirement 4 of this Directive, incorporate the modification kits required by Requirement 1 or 2 of this Directive, and inspect the engine mount beams as specified in Requirement 3 of this Directive;

(b)     If any crack is found in the left side (vertical portion) of the left engine beam of either nacelle, obtain a repair scheme from the manufacturer, incorporate this repair scheme, and continue the repetitive inspections required by Requirement 4 of this Directive.

(c)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is less than 1.75 inches, stop drill each end of each crack using a 0.098 inch drill bit, and continue the repetitive inspections required by Requirement 4 of this Directive;

(d)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 1.75 inches, but less than
                2.75 inches, obtain a repair scheme from the manufacturer, incorporate this repair scheme, and continue the repetitive inspections required by Requirement 4 of this Directive; or,

(e)     If cracks are found in the top (horizontal portion) of the engine beam and the total length of the cracks is equal to or greater than 2.75 inches, replace the engine beam with a part number specified in the instructions to Service Kit SK414-19B, Revised 4 March 1986, and inspect the engine mount beams as specified in Requirement 3 of this Directive.

               Note: FAA AD 97-26-16 Amdt 39-10259 refers.

                 Compliance: 1. Within 1,600 hours time in service after 23 April 1998 or at the next engine overhaul, whichever occurs first.

                 2.    Within 200