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FALCON 200 No 133 DECEMBER 09, 2014
MANDATORY ATA 52-00 DOORS
PASSENGER/CREW DOOR
PASSENGER DOOR 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
PASSENGER/CREW DOOR
PASSENGER DOOR CLOSING INSPECTION Initial issuance December 09, 2014 List of effective pages :
1 to 11 FALCON 200 F200 -133 F200 -52-00
DOORS
PASSENGER/CREW DOOR
PASSENGER DOOR CLOSING INSPECTION
1. PLANNING INFORMATION A. EFFECTIVITY This Service Bulletin is applicable to the FALCON 200 aircraft.
B. REASON At the end of a FALCON 20 flight, in approach at 7000 ft, the passenger door 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 passenger/crew door closes and locks correctly as part of normal procedures.
C. DESCRIPTION The operation consists in:
• checking the operation of all hook latches (A1 to A10) with passenger/crew door in open position,
• checking the operation of the hook latch (A10) with passenger/crew door in closed position,
• checking the operation of the warning system that monitors the position of the latches when locking the passenger/crew door,
• checking the condition of the passenger/crew door locking system.
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 that may be performed on this occasion.
G. TOOLING - PRICE AND AVAILABILITY Normal maintenance tooling.
FALCON 200 F200 -133 December 09, 2014 F200 -52-00 Initial issuance Page 1 / 11 DASSAULT AVIATION Proprietary Data
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:
• PASSENGER / CREW-DOOR - INSPECTION/CHECK AMM ATA 52 703.0
• PASSENGER / CREW-DOOR - REMOVAL/INSTALLATION AMM ATA 52 704.0
• PASSENGER / CREW-DOOR - INSPECTION/CHECK (F200 Gardian) AMM ATA 52 705.0
• DOOR INDICATING MICROSWITCHES : REPLACEMENT/ADJUSTMENT AMM ATA 52 714.0 J. OTHER PUBLICATIONS AFFECTED The following publication is revised to account for the changes introduced by this Service Bulletin:
• 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 200 F200 -133 December 09, 2014 F200 -52-00 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 and baggage compartment sliding (option) doors are closed.
(3) Open the passenger/crew door.
CAUTION: IN ORDER TO LIMIT HEATING OF THE MASTER WARNING PANEL DURING TESTING, SET "BRIGHT-DIM" SWITCH TO "DIM" POSITION.
(4) Energize the aircraft system, switch on the aircraft electrical system.
(5) Make sure that the "CABIN" indicator light is illuminated on the master warning panel "32W" ( fig.
2).
B. INSPECTION OF CLOSING SYSTEM
(1) Inspection with passenger/crew door open:
(a) Remove the first step (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph A.4.).
NOTE: First step, (Refer to the AMM, work card AMM ATA 52 703.0 (705.0 / Gardian), item 6, figure 6).
(b) Remove the side fairings (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph A.4.d. and e.) and inspect:
• the cables (refer to the SRM, work card 20-35-01-910-801),
• the rollers general condition (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph B.6.),
• the pulleys general condition (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph B.6.).
NOTE 1: For correct inspection of cables near pulleys, actuate the inside control (D- fig. 1).
NOTE 2: If condition is not satisfactory (Refer to the AMM, work card ATA 52 703.0
(705.0 / Gardian)).
(c) Using the inside control ( fig. 1) move all the hook latches as follows:
1 Move the inside control from the open position (C-fig. 1) to the closed position (D-fig. 1).
NOTE 1: Before threshold 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 hook latches movement.
2 When inside control is in the closed position (D-fig. 1), push it firmly while checking the back and forth motion of the red safety lever (E-fig. 1).
NOTE: The back and forth motion is associated with a click (mechanical lock).
FALCON 200 F200 -133 December 09, 2014 F200 -52-00 Initial issuance Page 3 / 11 DASSAULT AVIATION Proprietary Data
(d) Make sure that inside control lock correctly by gently pulling on it.
(e) Make sure that the ten hook latches (A-fig. 1) have rotated all together.
NOTE: Hook latches (A1-fig. 1) to (A10-fig. 1).
(f) Make sure that the lateral hook latch (A10-fig. 1) has rotated by 90° ± 10°, if not (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph I).
(g) Push the red safety lever (E-fig. 1) to unlock the ten hook latches (A-fig. 1).
(h) Using the inside control, rotate the ten hook latches (F-fig. 1) to initial position 0°.
(2) Inspection with passenger/crew door in closed position:
(a) With door open, 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 hook latch (A10-fig. 1).
NOTE: Local painting, means, thickness 1 mm (0.04 in.).
2 Paint a quadrant (Y-fig. 3) on the lateral hook latch (A10-fig. 1).
NOTE: Local painting, means, thickness 11 mm (0.43 in.).
(b) From inside, make sure that all hook latches are correctlly linked together as follows:
NOTE: Hook 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 inside control from the open position (E-fig. 2) to the closed position (C-fig. 2).
NOTE 1: Before threshold 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 hook latches movement.
3 Make sure that the hook latches move jointly without any contact against their fittings (airframe side) (if contact, refer to the AMM, work card ATA 52 704.0, figure 2). More particularly check that picking latch (A10-fig. 1) moves jointly with (A1-fig. 1).
4 Before threshold latches (B-fig. 2) movement, there is a hard point that disappears during inside control transition.
5 With the inside control at the closed position (C-fig. 2), firmly push the inside 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 inside control locks correctly by gently pulling on it.
7 Make sure that the lateral hook 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, work card ATA 52 703.0 (705.0 / Gardian), paragraph I).
9 Open the passenger/crew door.
(3) Make sure that the following microswitches operate properly:
• microswitch (41M) (X-fig. 1),
• microswitch (42M) (Y-fig. 1), FALCON 200 F200 -133 December 09, 2014 F200 -52-00 Initial issuance Page 4 / 11 DASSAULT AVIATION Proprietary Data
• microswitch (44M) (outer handle of the passenger/crew door),
• microswitch (43M) (rear compartment door),
• microswitch (45M) (baggage compartment door) (option).
(a) Adjust microswitch (41M) (X-fig. 1) (Refer to the AMM, work card ATA 52 714.0).
(b) Install the side fairings (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph K.2.e. to g.).
(c) Test microswitches (42M) and (44M) (Refer to the AMM, work card ATA 52 714.0, paragraph A.11.).
NOTE 1: Before performing testing, check that the rear compartment door is closed and locked.
NOTE 2: If option is installed, check that the baggage compartment door is closed and locked.
(d) Troubleshoot the microswitches (42M) or (44M) if tests are not correct.
(e) Test each microswitch compartment door individually as follows:
• microswitch (43M) (rear compartment door),
• microswitch (45M) (baggage compartment door) (option).
1 With the passenger/crew door in closed position, alternately open each of the rear compartment or baggage compartment door and make sure that the "CABIN" indicator light illuminates on the master warning panel "32W".
2 Troubleshoot the microswitches (43M) or (45M) if tests are not correct.
(4) Overlapping inspection between outer handle and rocker assy:
(a) With outer handle (C-fig. 4) opened, 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 passenger/crew door.
NOTE: Outer handle (C-fig. 4) and rocker assy (B-fig. 4) in locked position.
(c) Unlock the passenger/crew door.
(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 340), two washers (item 350) and two nuts (item 360) (refer to the IPC 52-10-50-30).
• Retrieve the shim (refer to the IPC, 52-10-50-30, item 370).
• Clean outer handle and the shim using cleaner.
• Position the shim and the new claw on the outer handle as indicated on fig. 5.
NOTE: Claw, (refer to the IPC, 52-10-50-30, item 330), p/n : MY20295-40921.
FALCON 200 F200 -133 December 09, 2014 F200 -52-00 Initial issuance Page 5 / 11 DASSAULT AVIATION Proprietary Data
• 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 340) 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 340), two washers (item 350) and two nuts (item 360) (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 passenger/crew door.
2 Close then open the passenger/crew door to make sure that the locking system operates correctly.
C. FINAL STEPS
(1) De-energize the aircraft systems.
(2) Install the side fairings (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph K.2.e. to g.).
(3) Install the first step (Refer to the AMM, work card ATA 52 703.0 (705.0 / Gardian), paragraph K.
2.a.).
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 200 F200 -133 December 09, 2014 F200 -52-00 Initial issuance Page 6 / 11 DASSAULT AVIATION Proprietary Data
DASSAULT SERVICE BULLETIN
AVIATION FALCON 200 F200 -133 EWD Hinges Rotary latch Approach Hook latch B) I (X) "31М1" (У "31М2" eoretical Views from outside Unlock position Lock position C Open position Inner latching control D (Closed position) Safety catch E Figure 1: INSPECTION FROM OUTSIDE December 09, 2014 F200 -52-00 Initial issuance Page 7 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 200 F200 -133 FWD A/C without PROLINE4 avionics "CABIN" warning light Unlock position Control lever COPUTER COMPUTER COPUTER CONFIG L.PITOT R.PITOT O. UNIT UNLOCI
PRESS ACCU GEN 2 TEN 3 APU GEN Safety catch FUEL ING LO FUEL APU BLEED BLEED CABIN DOORS "32W" "DOORS" warning light "32W47" FWD 31M E Inner latching control (Open position) Lock position Lock position Left door view Views from inside Rotary latch Closed position C B Approach Hook latch Figure 2: INSPECTION FROM INSIDE December 09, 2014 F200-52-00 Initial issuance Page 8 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 200 F200 -133 Lateral rotary latch (A10) in locked position Door fitting Rotary latch Door fitting Center line Rotary Latch Center Tine Marker thickness 1 mm (0.04 in.) 11 mm (0.43 in.)
(local manufacture) Quadrant (local manufacture) Figure 3: ANGULAR POSITION - INSPECTION December 09, 2014 F200 -52-00 Initial issuance Page 9 / 11
DASSAULT SERVICE BULLETIN
AVIATION FALCON 200 F200 -133 FWD Outer handle in opened position Passenger/crew door Rocker assy C Outer handle Outer handle and rocker assy in closed position D Modeling clay X Figure 4: OVERLAPPING - INSPECTION December 09, 2014 F200-52-00 Initial issuance Page 10 / 11