User's Manual

SYSTEM DESCRIPTION, INSTALLATION, AND MAINTENANCE MANUAL
ARINC 781-200 SDU and SCM
23-15-30 5-2
DATE TBD
A. Airworthiness Limitations
When applicable, the Airworthiness Limitations section is FAA-approved, and specifies
maintenance required under Title 14 Code of Federal Regulations (CFR) Part 43.16 and
14 CFR 91.403 of the Federal Aviation Regulations unless an alternative program has
been FAA approved.
This section must be added to the Airplane Maintenance Manuals. The information
contained herein supplements the Airplane Maintenance Manuals only in those areas
covered by the A781-200 system installation. For limitations and procedures not
contained in this supplement, consult the basic Airplane Maintenance Manuals.
The inspections and airworthiness limitations specified in this section are FAA approved.
This section specifies the inspections and other maintenance required under sections
433.16 and 91.403 of the Federal Aviation Regulations unless an alternative program
has been FAA approved.
B. Electrical and Mechanical Inspection and Check
Periodic inspections of the mechanical and electrical interfaces of the A781 system
components to the aircraft should be completed as defined by the governing
airworthiness body (for example, Transport Canada, the FAA, the EASA).
C. Instructions for Continued Airworthiness
The following paragraphs describe all maintenance requirements and instructions for
continued airworthiness of the A781-200 system:
1. This manual contains maintenance information for the SDU and SCM, including
system description, system operation, installation, test, and fault isolation.
2. Add the following information to the illustrated parts catalog for the aircraft:
• all part numbers referred to in this manual
• all LRUs referred to in this manual
3. Add all wiring diagram information contained in this manual to the aircraft operator’s
appropriate aircraft Wiring Diagram Manuals.
4. No additional or routine maintenance is required for the on-condition SDU or SCM.
5. If an SDU or SCM is inoperative, follow the instructions listed in "Repair" on page 5-1.
6. Return all units to the RCI equipment supplier factory for repair. See Appendix A:
Return Material Authorization for detailed removal information and procedures.
7. Install repaired units on the aircraft in accordance with the installation instructions
provided in this manual.
8. Make sure that all repaired units are operating before approving them for return to
service, using the operational verification tests and procedures provided in this
manual.
9. Enter the approval for return to service in the logbook, as required by section 43.9
of the FAR.