SERVICE BULLETIN No. SB-300-2-97
Contents
1. spring Doubler mounting sleeve Tail spring mounting plate retrofit Inside view of bottom structure from top Bottom view Figure 5 Position and welds of retrofit kit Apply anti corrosion wax to steel tubes around tail spring mounting plate Make sure not to disturb the designated water drain path on the L H and R H sides of the retrofit plates Reassemble the aircraft Make appropriate logbook entry of compliance with PART II of this Service Bulletin Issue C SB 300 2 97 Date 24 09 09 Page 6 EASA 21J 073 Fuselage structure tail spring support EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X MATERIAL The material required for PART II needs to be ordered from EXTRA Flugzeugproduktions und Vertriebs GmbH Flugplatz Dinslaken Schwarze Heide 21 46569 H nxe Germany Order retrofit kit including following items Kit No SB297B2 1 Eligible for EA 300 L S N 01 44 80 170 172 173 and 1171 1174 1299 Parts tail spring mounting plate EA 26102 45 01 doubler EA 26102 45 02 shear plate EA 26102 45 03 fwd stiffener 2x EA 23102 44 tail spring mounting sleeve EA 23102 38 splice tube 16x2mm EA 86921 12 replacement tube 18x1mm EA 86921 13 Kit No SB297B2 2 Eligible for EA 300 L S N 45 79 EA 300 200 S N 01 31 and 1032 1043 Parts tail spring mounting plate EA 27102 345 01 doubler EA 27102 345 02 shear plate EA 27102 345 03 fwd stiffe2. EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X R EASA 21J 073 Fuselage structure tail spring support SERVICE BULLETIN No SB 300 2 97 Extra considers compliance mandatory Subject Fuselage structure tail spring support Aircraft affected Following models and SN EA 300 L S N 01 170 172 173 and 1171 1174 1299 EA 300 200 S N 01 31 and 1032 1043 Aircraft that comply with Part II of issue B of this service bulletin are not affected Purpose The combination of a redesigned tail spring support a stiffer tail spring and rough field operations has led to cracks in the tail spring support mounting base Cracks have been reported even for airplanes that comply with PART II of the previous issue A of this service bulletin This issue C of the service bulletin provides instructions for recurring inspection and modification in the area of the tail spring support Approval The technical content of this document is approved under the authority of DOA Nr EASA 21J 073 COMPLIANCE TIME First inspection as described in PART I prior to next flight Recurring inspection as part of the 50h inspection program only until PART II of this Service Bulletin has been complied with In case the inspection described in PART I reveals cracks PART I needs to be complied with prior to next flight Issue C SB 300 2 97 Date 24 09 09 Page 1 of 8 EXTRA Flugzeugproduktions Service Bulletin und
3. Vertriebs GmbH EA 300 X EASA 21J 073 Fuselage structure tail spring support PARTI VISUAL INSPECTION Note Alterations or repair of the aircraft must be accomplished by licensed personnel only A repetitive inspection is required at given compliance time Remove elevator control inspection window Visual inspection of tail spring mounting along welds to fuselage tubing Cracks have been reported at the spots marked in figure 1 Investigate these areas carefully To assist the visual inspection it is helpful to use a torchlight and a magnifying glass Incase cracks are found proceed with the instructions of PART IL Incase no cracks are found reinstall elevator control inspection window and make appropriate entry of compliance in aircraft logbook Figure 1 Possible crack locations in the area of tail gear spring attachment retrofit plates of SB 300 2 97 issue A installed Issue C SB 300 2 97 Date 24 09 09 Page 2 EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X R EASA 21J 073 Fuselage structure tail spring support PARTII RETROFIT Note Alterations or repair of the aircraft must be accomplished by licensed Issue C Date 24 09 09 personnel only Refer to AC 43 13 1B and Chapter 51 70 05 Structural Repair of Steel Components of the Service Manual TIG welding is required use appropriate welding rod Remove elevator control inspection windo
4. e or airmail to EXTRA Flugzeugproduktions und Vertriebs GmbH Engineering Department Office of Airworthiness Quality Assurance Schwarze Heide 21 46569 Hiinxe Germany Fax N 49 2858 9137 42 Issue C SB 300 2 97 Date 24 09 09 Page 8
5. eattach the fabric using the standard fabric glue Follow procedures as given in the Ceconite 102 manual Make sure the fabric is pulled tight during the reattachment Do not attempt to restore fabric tension by heating the already painted fabric If necessary refinish the fabric Reconnect battery ground wire and engine ground wire to the firewall SB 300 2 97 Page 3 EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X EASA 21J 073 Fuselage structure tail spring support Lx See SASA SS L SE NS lt g Figure 2 Removing the fabric Figure 3 Cutout for crack repair and retrofit Issue C SB 300 2 97 Date 24 09 09 Page 4 EASA 21J 073 Fuselage structure tail spring support EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X ALLOW I 38 GAP BETWEEN ORIGINAL AND ROSETTE WELD REPLACEMENT TUBES FOR WELDING INSIDE SLEEVE tuse REPLACEMENT TUBE ROSETTE WELD PORRE Ye Gap INSIDE SLEEVE TUBE gt ORIGINAL TUBE Figure 4 Method of inner sleeve splicing recommended for tubing crack repair ref AC 43 13 1B Aircraft Inspection and Repair Chapter 04 Issue C SB 300 2 97 Date 24 09 09 Page 5 EXTRA Flugzeugproduktions Service Bulletin ee und Vertriebs GmbH EA 300 X EASA 21J 073 Fuselage structure tail spring support Shear plate Fwd stiffener AIID IIIDIDID D DNB DIDI DIDI Tail
6. ner 2x EA 27102 344 tail spring mounting sleeve EA 27102 338 splice tube EA 86921 312 replacement tube EA 86921 313 Please note For aircraft in warranty only 20 manhours is the maximum time to be allowed for the inspection and modification work per aircraft Extra Flugzeugproduktions und Vertriebs GmbH will only pay for the hours it actually takes an Authorized Service Center in Europe Extra Flugzeugproduktions amp Vertriebs GmbH to perform the task up to but not exceeding the hours listed Please reimburse for hourly rates Issue C SB 300 2 97 Date 24 09 09 Page 7 EXTRA Flugzeugproduktions Service Bulletin und Vertriebs GmbH EA 300 X R A EASA 21J 073 Fuselage structure tail spring support Appendix A Aircraft Type and model MEA 300 L EA300 200_ Serial Number Owner Registration Total Time Total landings if known The aircraft mentioned above has been inspected according PART I of this Service Bulletin Damage has been found O Yes O No If yes description of damage found if possible attach supporting sketch Note If extend of damage is not covered by this Service Bulletin contact EXTRA Flugzeugproduktions und Vertriebs GmbH The appropriate instruction of O Part I and or Part II of this Service Bulletin has been carried out No deviation from given instructions Comments Company Aircraft inspector Date Please return a copy of this page by facsimil
7. w Remove tail fairing rudder vertical and horizontal stabilizer according Chapter 27 and 55 of the Service Manual Remove tail spring assembly according Chapter 32 of the Service Manual Disconnect battery ground wire and engine ground wire to firewall Peel off fabric from upper L H and R H longeron from rear facing fuselage surface and R H lower longeron in the area of the inspection window refer to figure 2 for detailed sketch Do not use sharp objects that could damage the fabric while peeling it off Fold the fabric far enough forward to have sufficient access to the area for welding Make sure to work gently in order not to introduce cracks in the fabric paint coat finish Inspect tail spring mounting base for previously unnoticed cracks especially at the spots marked in figure1 Remove paint from fuselage tubes and tail spring mounting plate for welding in cracked areas and installation of the retrofit plates Cut out tail spring mounting plate including front and rear stiffener figure 3 shows detail of rear truss after cutting Proceed with caution Avoid damaging any truss tubes except those tubes that are replaced Repair any cracks found Refer to Chapter 51 70 05 Structural Repair of Steel Components of the Service Manual and figure 4 Weld retrofit plates in place refer to figure 5 for correct position of plates and welds Refinish fuselage paint coat according Chapter 51 70 07 of the Service Manual R
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