THE SUPPLIER SHALL COMPLY WITH ALL REQUIREMENTS IN THE SOFIA CAVITY DOOR DRIVE SYSTEM, TECHNICAL SPECIFICATION AND REQUIREMENTS, DOCUMENT NUMBER USRA-DAL-1163-00 (LATEST REVISION) THE SUPPLIER SHALL FURNISH ALL LABOR, MATERIALS, TOOLS AND PERFORM ALL OPERATIONS NECESSARY FOR THE ENGINEERING, DETAILING, FABRICATION, INSPECTION, TESTING, VALIDATION, DOCUMENTATION AND DELIVERY OF THE UPPER RIGID DOOR (URD) AND APERTURE ASSEMBLY (AA)/LOWER FLEXIBLE DOOR (LFD) ACTUATOR UNITS AND CONTROL UNIT. THE CONTRACTOR SHALL HAVE COMPLETE RESPONSIBILITY FOR ALL EQUIPMENT AND ACCESSORIES INCLUDED IN THIS SPECIFICATION. THIS RESPONSIBILITY SHALL INCLUDE THE VERIFICATION OF DATA FURNISHED BY THE MANUFACTURER OF CONTRACTOR PROCURED COMPONENTS. THE CAVITY DOOR DRIVE SYSTEM SHALL MEET THE OVERALL DESIGN REQUIREMENTS AS SPECIFIED IN THE SOFIA CAVITY DOOR DRIVE SYSTEM TECHNICAL SPECIFICATION AND REQUIREMENTS, DOCUMENT NUMBER USRA-DAL-1163-00. THE SYSTEM SHALL BE DESIGNED, FABRICATED, ASSEMBLED AND TESTED. AS A MINIMUM THE URD AND AA/LFT ACTUATION SYSTEM SHALL INCLUDE: MOTORS, PLANETARY GEAR REDUCTION AND IDLER GEAR, COMMUTATION AND CONTROL FEEDBACK DEVICES AS REQUIRED. PACKAGING INTO LINE REPLACEABLE UNIT(S) (LRU) SHALL BE DETERMINED IN THE DESIGN CYCLE AND FINALIZED BY THE PDR. THE DESIGN SHALL CONSIDER EASE OF MAINTENANCE, INSPECTION AND REPLACEMENT OF EQUIPMENT AND SOFTWARE AS FOLLOWS: (1) ADEQUATE ACCESS FOR THE INSPECTION, SERVICE, MAINTENANCE, AND REPLACEMENT OF LRUS. (2) FULLY INTERCHANGEABLE COMPONENTS. (3) THE DESIGN SHALL REQUIRE NO SCHEDULED OVERHAUL OF COMPONENTS AND MINIMAL SCHEDULED MAINTENANCE OR SERVICE TO MAINTAIN OPERATION WITHIN THE SPECIFIED PERFORMANCE REQUIREMENTS. (4) THE DESIGN SHALL PROVIDE FOR ON-AIRCRAFT ISOLATION OF COMPONENT FAILURES AND VERIFICATION OF SYSTEM AND COMPONENT FAULTS USING EITHER AIRCRAFT OR EXTERNAL POWER. (5) THE DESIGN SHALL ALLOW ON-AIRCRAFT MAINTENANCE TO BE PERFORMED USING COMMON TOOLS AND/OR SUPPORT EQUIPMENT CONSISTENT WITH THE SUPPORT RESOURCES AVAILABLE AT THOSE AIRPORTS COMPATIBLE WITH THE OPERATION OF THE AIRCRAFT. (6) ANY SPECIAL TOOLS REQUIRED FOR INSTALLATION OR REMOVAL SHALL BE FULLY DETAILED IN THE DESIGN. (7) THE DESIGN SHALL CONTAIN FEATURES THAT ELIMINATE THE POSSIBILITY OF INCORRECT INSTALLATION, OR THE INADVERTENT CROSSING OF CONNECTIONS. (8) THE SOFTWARE SHALL BE OF A MODULAR DESIGN AND ALL COMPONENTS OF THE DEVELOPMENT AND VERIFICATION ENVIRONMENT IDENTIFIED. THE SUPPLIER SHALL ASSIST NASA IN PLANNING AND CONDUCTING A MAINTAINABILITY DEMONSTRATION TO VERIFY THAT THE SPECIFIED MAINTAINABILITY REQUIREMENTS HAVE BEEN MET. THE MAINTAINABILITY DEMONSTRATION SHALL BE PLANNED AND SCOPED TO: (1) DISCLOSE POTENTIAL PROBLEM AREAS IN THE DESIGN THAT COULD AFFECT THE MAINTAINABILITY AND SUPPORT OF THE FIELDED SYSTEM (2) VALIDATE ON-AIRCRAFT AND OFF-AIRCRAFT MAINTENANCE CONCEPTS AND REPAIR PROCEDURES REQUIRED TO SUCCESSFULLY OPERATE THE SYSTEM (3) VALIDATE GROUND SUPPORT EQUIPMENT REQUIREMENTS AND THE NUMBER OF PERSONNEL AND SPECIAL SKILLS REQUIRED FOR MAINTENANCE PUBLICATIONS AND TRAINING DATA THE SUPPLIER SHALL INSTALL ON, AND THEN REMOVE FROM, AN AIRCRAFT MOCK-UP, DEVELOPMENT FIXTURE OR PRODUCTION AIRCRAFT ONE OF EACH TYPE OF PRODUCTION UNITS TO VALIDATE INSTALLATION PROCEDURES AND ON-AIRCRAFT MAINTAINABILITY REQUIREMENTS.