PARAVION TECHNOLOGY, INC AIRWAY AVENUE FT. COLLINS, COLORADO 80524

Transcription

1 PARAVION TECHNOLOGY, INC AIRWAY AVENUE FT. COLLINS, COLORADO REPORT NO. PR-369DA-900M PNEUMATIC DOOR OPENER INSTALLATION INSTRUCTIONS FOR 369PDO , 500N & 600N HELICOPTERS

2 Page i REVISIONS REV. DATE DESCRIPTION BY N/C Original NS A Revised pg i, and 1. Name change to Paravion NS Technology, Inc. was Helicraft Corporation B 12/27/91 Added Model Effectivity, Page 1 REB C 10/29/97 Added MDHC 600N, Page 1 REB D 09/05/00 Added Weight and Balance for Front Door on the 600N. Updated report format

3 Page ii REFERENCES 1. Paravion Drawing 07DA-100; Installation - Door Actuator. 2. Paravion Drawing 07DA-200; Installation - Door Mtg Bracket. 3. Paravion Drawing 07DA-201; Installation - Fuselage Mtg Bracket. 4. AC43.13; Acceptable Practices, Aircraft Alteration and Repair.

4 Page iii TABLE OF CONTENTS ITEM Revisions References Table of Contents PAGE i ii iii 1.0 Introduction Installation Instructions Weight and Balance Data 3 Table LIST OF TABLES Page I Weight and Balance, 369 and 500N 3 II Weight and Balance, 600N 3 Appendix LIST OF APPENDICES Page A STC Certificate A-0

5 Page INTRODUCTION This document presents a convenient compilation of the necessary data to install the Paravion 07DA- 100 Pneumatic Door Actuator System on the Hughes Model 369, 500N, and 600N Helicopters. MODEL EFFECTIVITY 369H (S/N 0101 and subs.) 369D 369E 369F 369FF 500N 600N 2.0 INSTALLATION INSTRUCTIONS 2.1 Fuselage Mount Bracket Installation 07DA-201-1/ Referring to the installation drawing, locate the proper position for the Rod End on the cabin floor. Then drill the indicated hole through the existing doubler, the cabin floor and the existing lateral clip. Deburr hole Install the Rod End using the indicated hardware. It is recommended by the manufacture to seal the faying surfaces between the doubler and the Rod End using MIL-S-8802F Class B2 sealant or equivalent. 2.2 Fuselage Mount Bracket Installation 07DA-201-3/ Referring to the installation drawing, locate the proper position for the Bracket Assembly Remove the 4 existing rivets at this location, then match drill the Bracket Assembly flange that does not have any holes in it from the previously removed rivets to the indicated hole size. Deburr holes Match drill the 4 indicated holes in the aircraft from the 4 holes located in the other flange of the Bracket Assembly. Deburr holes Fasten the Bracket Assembly to the aircraft using the indicated rivets. It is recommended by the manufacture to seal the faying surfaces between the Bracket Assembly and the aircraft using MIL-S-8802F Class B2 sealant or equivalent.

6 Page Installation Instructions 07DA Referring to the installation drawing, locate the proper position for the Bracket Assembly Match drill the indicated holes in the door from the Bracket Assembly. Deburr holes Fasten the Bracket Assembly to the door using the indicated rivets. It is recommended by the manufacture to seal the faying surfaces between the Bracket Assembly and the aircraft using MIL-S-8802F Class B2 sealant or equivalent. 2.4 Door Actuator Installation 07DA Snap the actuator onto the lower ball assembly with the ACTUATOR ROD END DOWN. While holding the door open; snap the cylinder end onto the ball assembly on the door. Safety the attachment points by using the provided clips or alternate cotter pins No flight manual supplement is required since there are no additional restrictions or alterations to the aircraft s flight characteristics. 2.5 Service Instructions NOTE: WHEN REMOVING THE DOOR, IT IS NECESSARY TO FIRST REMOVE THE ACTUATOR. WHEN REMOVING THE ACTUATOR, FIRST REMOVE SAFETY CLIPS Prior to removing the door, remove the actuator When removing the actuator, first remove the safety clip Periodically check the tightness of the ball assemblies Periodically lubricate the ball sockets of the actuator with a light grease To prevent actuator seal damage, insure the cylinder rod is kept clean Inspect door hinges for wear per manufacturer s recommendations.

7 Page WEIGHT AND BALANCE DATA After completion of the installation, the aircraft empty weight and center of gravity data should be revised to reflect the increase in empty weight shown below. In addition, the enclosed STC should be removed and filed with the aircraft logbook. TABLE I 369 and 500N WEIGHT AND BALANCE Weight (lbs) Fuselage STA (in) Moment (in-lbs) Forward Door Installation (2) Aft Door Installation (2) TOTAL TABLE II 600N WEIGHT AND BALANCE Weight (lbs) Fuselage STA (in) Forward Door Installation (2) Moment (in-lbs)

8 Page A-0 APPENDIX A SUPPLEMENTAL TYPE CERTIFICATE