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FALCON 20 No 789 DECEMBER 09, 2014
MANDATORY ATA 52-26 DOORS
MAIN ENTRY DOOR (MED)
MED CLOSING INSPECTION
FALCON SERVICE BULLETIN Copyright © 2014 by Dassault Aviation All rights reserved. No part of this work may be reproduced or copied in any form or by any means without written permission of Dassault Aviation.
DOORS
MAIN ENTRY DOOR (MED)
MED CLOSING INSPECTION Initial issuance December 09, 2014 List of effective pages :
1 to 11 FALCON 20 F20 -789 F20 -52-26
DOORS
MAIN ENTRY DOOR (MED)
MED CLOSING INSPECTION
1. PLANNING INFORMATION A. EFFECTIVITY This Service Bulletin is applicable to all FAN JET FALCON series, all MYSTERE-FALCON 20 series, and MYSTERE-FALCON 20 GF aircraft.
B. REASON At the end of a flight, in approach at 7000 ft, the MED opened and separated from the aircraft. The crew managed to maintain control of the aircraft and landed without incident.
The purpose of this Service Bulletin is to make sure that the MED closes and locks correctly as part of normal procedures.
C. DESCRIPTION The operation consists in:
• checking the operation of all picking latches (A1 to A10) with MED in open position,
• checking the operation of the picking latch (A10) with MED in closed position.
• checking the operation of the warning system that monitors the position of the latches when locking the MED,
• checking the condition of the MED locking system (aircraft with M2089 or SB 615 applied).
D. COMPLIANCE Mandatory:
• It is anticipated that this Service Bulletin will be rendered mandatory by an EASA Airworthiness Directive.
• As prescribed by the Airworthiness Authorities of the country of registration of the aircraft.
It is anticipated that this Service Bulletin will be rendered mandatory by an EASA Airworthiness Directive.
E. APPROVAL The technical content of this document is approved under the authority of DOA nr. EASA.21J.051.
F. LABOR Estimated labor-hours: Refer to Service Bulletin Commercial Summary.
NOTE: These labor-hours only concern the work described in this Service Bulletin and do not include other maintenance work which may be performed on this occasion.
G. TOOLING - PRICE AND AVAILABILITY Normal maintenance tooling.
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H. WEIGHT AND BALANCE Change in weight: None.
Change in balance with respect to 25% MAC: None.
I. REFERENCES Structure Repair Manual:
• BASIC SEALING METHODS (Refer to TASK 20-32-00-390-801)
• CABLES: INSPECTION - REJECT CRITERIA - MAINTENANCE SRM 20-35-01-910-801
• PROTECTION SCHEME SRM 20-60-00 Aircraft Maintenance Manual:
• DC GENERATION AMM 24-30-0-0
• REAR COMPARTMENT - ADJUSTMENT / TEST AMM 33-30-00-5
• PASSENGER / CREW DOOR - ADJUSTMENT / TEST AMM 52-10-1-5
• PASSENGER / CREW DOOR - INSPECTION / CHECK AMM 52-10-3-3 Illustrated Parts Catalog
• MECHANISM,LOCKING CENTER PART IPC 52-10-50-30 J. OTHER PUBLICATIONS AFFECTED The following publication will be revised as a supplemental improvement in the scope of this issue:
• Airplane Flight Manual.
The following publication will be revised at a later date to account for the changes introduced by this Service Bulletin:
• Aircraft Maintenance Manual.
FALCON 20 F20 -789 December 09, 2014 F20 -52-26 Initial issuance Page 2 / 11 DASSAULT AVIATION Proprietary Data
2. ACCOMPLISHMENT INSTRUCTIONS A. PRELIMINARY STEPS
(1) The aircraft must be in the maintenance configuration.
(2) Make sure that the rear compartment door is closed.
(3) Open the MED.
(4) Energize the aircraft system (refer to AMM 24-30-0-0).
(5) Make sure that the "DOOR" warning light (42H-fig. 2) is illuminated on the warning panel (51W).
B. INSPECTION OF CLOSING SYSTEM
(1) Inspection with MED in open position:
(a) Remove the first step (refer to the AMM, procedure 52-10-3-3, paragraph 2.D).
NOTE: First step, (refer to the AMM, procedure 52-10-3-3, (item 6, figure 306)).
(b) Remove the side fairings (refer to the AMM, procedure 52-10-3-3, paragraphs 2.D.(4) and
(5)) and inspect:
• the cables (refer to SRM, procedure 20-35-01-910-801),
• the rollers general condition (refer to the AMM, procedure 52-10-3-3 paragraphs 3.F),
• the pulleys general condition (refer to the AMM, procedure 52-10-3-3 paragraph 3.F), NOTE 1: For correct inspection of cables near pulleys, actuate the internal locking control (C-fig. 3).
NOTE 2: If condition is not satisfactory (refer to the AMM, procedure 52-10-3-3).
(c) Using the internal locking control ( fig. 1) move all the picking latches as follows:
1 Move the internal locking control from the open position (C-fig. 1) to the closed position (D-fig. 1).
NOTE 1: Before pull latches (B-fig. 1) start to move, the operator should feel a hard spot that disappears continuing movement.
NOTE 2: There is a second hard spot before the beginning of picking latches movement.
2 When internal locking control is in the closed position (D-fig. 1), push it firmly while checking the back and forth motion of the red safety lever.
NOTE: The back and forth motion is associated with a click (mechanical lock).
(d) Make sure that internal locking control lock correctly by gently pulling on it.
(e) Make sure that the ten picking latches (A-fig. 1) have rotated all together.
NOTE: Picking latches (A1-fig. 1) to (A10-fig. 1).
(f) Make sure that the lateral picking latch (A10-fig. 1) has rotated by 90° ± 10°, if not (refer to the AMM, procedure 52-10-3-3 paragraph 10) .
(g) Push the red safety lever (E-fig. 1) to unlock the ten picking latches (A-fig. 1).
FALCON 20 F20 -789 December 09, 2014 F20 -52-26 Initial issuance Page 3 / 11 DASSAULT AVIATION Proprietary Data
(h) Using the internal locking control, rotate the ten picking latches (F-fig. 1) to initial position 0°.
(2) Inspection of MED in closed position:
(a) With door opened, as indicated on fig. 3, do identification marks as follows:
1 Paint a marker (X-fig. 3) on the lateral door fitting corresponding to lateral picking latch (A10-fig. 1).
NOTE: Local painting means, thickness 1 mm (0.04 in.).
2 Paint a quadrant (Y-fig. 3) on the lateral picking latch (A10-fig. 1).
NOTE: Local painting means, thickness 11 mm (0.43 in.).
(b) From inside, make sure that all picking latches are correctlly linked together as follows:
NOTE: Picking latches (A1-fig. 1) to (A10-fig. 1).
1 Using the control lever (F-fig. 2), slowly close the door and hold it in position.
2 Move the internal locking control from the open position (E-fig. 2) to the closed position (C-fig. 2).
NOTE 1: Before pull latches (B-fig. 2) start to move, the operator should feel a hard spot that disappears continuing movement.
NOTE 2: There is a second hard spot before the beginning of picking latches movement.
3 Make sure that the picking latches move jointly without any contact against their fittings (airframe side) (if contact, refer to the AMM, procedure 52-10-1-5 figure 501). More particularly check that picking latch (A10-fig. 1) moves jointly with (A1-fig. 1).
4 Before pull latches (B-fig. 2) movement, there is a hard point that disappears during inside control transition.
5 With the internal locking control at the closed position (C-fig. 2), firmly push the internal locking control while checking the back and forth motion of the red safety lever (D-fig.
2).
NOTE: The back and forth motion is associated with a click (mechanical lock).
6 Make sure that the internal locking control locks correctly by gently pulling on it.
7 Make sure that the lateral picking latch (A10-fig. 1) has rotated and that the marker (X- fig. 3) points within the quadrant (Y-fig. 3).
8 If it does not, (refer to the AMM, procedure 52-10-3-3 paragraph 10).
9 Open the MED.
(3) Make sure that the following microswitches operate properly:
• passenger/crew door microswitch "40H",
• external control lever microswitch "49H",
• rear compartment door microswitch "44L".
(a) In accordance with the aircraft configuration, adjust microswitch (40H) (Refer to the AMM, procedure 52-10-1-5, paragraph "Adjusting microswitch (40H)").
(b) Test of microswitch (49H) as follows:
FALCON 20 F20 -789 December 09, 2014 F20 -52-26 Initial issuance Page 4 / 11 DASSAULT AVIATION Proprietary Data
1 Open the MED.
2 Push and hold microswitch (40H).
3 Make sure that the "DOOR" warning light (42H-fig. 2) stays illuminated on the failure warning panel (51W).
4 If not, adjust microswitch (49H) (refer to the AMM, procedure 52-10-1-5, paragraph "Adjusting microswitch (49H)").
5 Release microswitch (40H).
(c) Test of microswitch "44L" as follows:
1 With MED in open position, lock the internal locking control (paragraph 2.B.(c)).
2 Open the rear compartment door.
3 Push and hold microswitch (40H).
4 Make sure that the "DOOR" warning light (42H-fig. 2) stays illuminated on the failure warning panel (51W).
5 If not, adjust microswitch (44L) (Refer to the AMM, procedure 33-30-00-5).
6 Release microswitch (40H).
7 Unlock the internal locking control (paragraph 2.B.(g) and (h)).
8 Close the rear compartment door.
WARNING: INSPECTION WITH MED UNLOCKED. TAKE ALL SAFETY PRECAUTIONS REQUIRED FOR THIS OPERATION.
(4) Overlapping inspection between outer handle and rocker assy (aircraft with M2089 or SB 615 applied):
(a) With outer handle (C-fig. 4) open, position modeling clay (D-fig. 4) on the claw (A-fig. 4).
NOTE: Modeling clay to be positioned on the width of the claw.
(b) Lock the MED.
NOTE: Outer handle (C-fig. 4) and rocker assy (B-fig. 4) in locked position.
(c) Unlock the MED.
(d) Measure the distance (X-fig. 4) on the modeling clay (D-fig. 4).
(e) Make sure that the distance (X-fig. 4) is X ≥ 1.8 mm (0.07 in.).
(f) If not:
1 Remove and discard the claw (A-fig. 4) then replace it, as follows:
• Remove the outer handle from the MED.
• Remove the claw and its fasteners then discard the assembly.
NOTE: Fasteners : Two screws (item 350), two washers (item 360) and two nuts (item 370) (refer to the IPC 52-10-50-30).
• Retrieve the shim (refer to the IPC, 52-10-50-30, item 380).
• Clean outer handle and the shim using cleaner.
• Position the shim and the new claw on the outer handle as indicated on fig. 5.
FALCON 20 F20 -789 December 09, 2014 F20 -52-26 Initial issuance Page 5 / 11 DASSAULT AVIATION Proprietary Data
NOTE: Claw, (refer to the IPC, 52-10-50-30, item 340), p/n : MY20295-40921.
• Make sure that the claw is positioned at 213.6+0.2+0 mm ( 8.4+0.0078+0 in.) from handle rotation axis as indicated on fig. 5 then hold it in position.
• Counterdrill the claw for screws (item 350) to a diameter of 3.2 mm (0.126 in.)
then remove the assembly.
• Apply interlaying sealant PR1440 (Refer to TASK 20-32-00-390-801 ) on both sides of the shim (A-fig. 5).
• Secure the claw in position using new fasteners.
NOTE 1: Fasteners : Two screws (item 350), two washers (item 360) and two nuts (item 370) (refer to the IPC 52-10-50-30).
NOTE 2: Interlaying sealant PR1440 under screw heads (B-fig. 5) (Refer to TASK 20-32-00-390-801).
• Shave the screws flush with the nut then safety the screw/nut assembly with a punch.
• Restore sealant PR1440 between the ribs of the outer handle (C-fig. 5) (Refer to TASK 20-32-00-390-801).
• Touch up as necessary (Refer to the SRM, procedure 20-60-00).
• Install the outer handle on the MED.
2 Close then open the MED to make sure that the locking system operates correctly.
C. FINAL STEPS
(1) De-energize the aircraft systems (refer to AMM 24-30-0-0).
(2) Install the side fairings (refer to the AMM, procedure 52-10-3-3 paragraphs 12.B.(5) and (6)).
(3) Install the first step (refer to the AMM, procedure 52-10-3-3, paragraph 12.B).
D. LOCAL PROCUREMENT As indicated in Consumable Products Manual (CPM):
• sealant PR1440
• modeling clay
• cleaner E. RECORDING Record compliance with this Service Bulletin in the appropriate aircraft documents.
Fill out the card located at the end of the Service Bulletin and mail or fax it to Dassault Aviation or Dassault Falcon Jet, or fill out the electronic Service Bulletin reply form located in the ”Service Bulletin" page on the Falcon portal.
FALCON 20 F20 -789 December 09, 2014 F20 -52-26 Initial issuance Page 6 / 11 DASSAULT AVIATION Proprietary Data
DASSAULT SERVICE BULLETIN
AVIATION FALCON 20 F20 -789 FWD Picking latch Pull latch ) Before M1203 or without BS 290 (40H) 2 After M1203 or with BS 290 (moving micro switch) Views from outside etical Unlock position Lock position Open position Safety lever E Internal locking control D (Closed position) Figure 1: INSPECTION FROM OUTSIDE December 09, 2014 F20-52-26 Initial issuance Page 7 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 20 F20 -789 "51W" "DOOR" warning light FWD "42H" Unlock position "MED" view from outside Control lever (F Safety lever "49H" Internal locking control (Open position) "40H" X' 2 After M1203 or with BS 290 (moving micro switch) Views from inside Picking latch ® Pul latch Lock position Closed position Figure 2: INSPECTION FROM INSIDE December 09, 2014 F20-52-26 Initial issuance Page 8 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 20 F20 -789 Lateral picking latch (A10) in locked position Door fitting Picking latch Center line Door fitting Picking latch Center line Marker thichness 1 mm (0.04 in.) 11 mm (0.43 in.)
(local manufacture) Quadrant (local manufacture) Figure 3: ANGULAR POSITION - INSPECTION December 09, 2014 F20-52-26 Initial issuance Page 9 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 20 F20 -789 FWD Outer handle in opened position MED Rocker assy C Outer handle Outer handle and rocker assy in closed position D Modeling clay X Figure 4: OVERLAPPING - INSPECTION December 09, 2014 F20 -52-26 Initial issuance Page 10 / 11