Commander, Naval Air Systems Command (Code 2.2), 47123 Buse Road, Bldg 2272, Patuxent River, MD 20670-1547

16 -- DEVELOPMENT OF TIME COMPLIANCES FOR SLEP CRITICAL AREAS BASED ON USAGE DATA POC Contact, Jeff Schoerner, Phone, (301) 757-7033; Contracting Officer, Terrence O'Connell E-MAIL: shoernerja@navair/navy.mil, shoernerja@navair/navy.mil. The Naval Air Systems Command intends to place an order with Northrop Grumman Corporation. The Contractor shall calculate SLEP kit installation compliance limits for specific wing and fuselage locations, based on destructive teardown inspection results. These compliance limits are determined on an airplane-by-airplane basis, using individual aircraft landing usage. Navy supplied usage data will be applied against demonstrated fatigue life to determine the fatigue life expended for individual aircraft. Secondly, the Contractor shall perform the necessary structural fatigue analyses to determine if the original disposition for the selected Material Discrepancies (MRR and T-Tag) can be accepted as satisfying the SLEP spectrum criterion or require enhancement design. A combination of preexisting finite element models and newly created detailed splice models will be utilized to evaluate configurations exhibiting unique geometry. The Contractor shall document the analyses for the favorable discrepancies and provide recommendations for corrective actions to those discrepancies deemed inadequate. Finally, the Contractor, will define the critical control points on E-2C and C-2A airframes and review the recorded parameters available for use in establishing fatigue tracking parameters. It is anticipated that up to 6 control points will be candidates for tracking on each aircraft. Wing control points will be common for both aircraft. Some control points may be defined by more than one structural configuration. The basis for selection of control points will be the results of the C-2A(R) and E2C Full Scale Fatigue Tests (FSFT) and Tear down Inspections as well as existing fatigue analyses. A study will be made once the selection of control points has been finalized to determine whether any control points should be recommended for tracking using crack initiation and subsequent crack growth rather than fatigue life only. Output of recommendations, available flight parameters affecting each control point and rationale/criteria for selection. Northrop Grumman, as the designer, developer, sole manufacturer, and systems integrator of the E-2C/C-2A aircraft is uniquely qualified to perform these efforts due to their technical knowledge of the aircraft's design, production engineering and its highly complex systems integration. Only Northrop Grumman possesses the data and can provide the in depth technical/engineering services required to support the integration of this technology within the desired schedule dictated by program requirements. See Note 22. NAVAIR Synopsis No. 20067-00. !! Posted 07/13/00 (W-SN474406). (0195)

Loren Data Corp. http://www.ld.com (SYN# 0215 20000717\16-0011.SOL)

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