D) 06 aircraft areas and dimensions

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D) 06 aircraft areas and dimensions

  1. 1. ATA 06 Aircraft areas and dimensions
  2. 2. Table of Content06-00 Aircraft areas and dimensionsIntroduction . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 1The aircraft measurement Embraer 170. . . . . . . . . . . . . . . . . . . . . 3The aircraft measurement Embraer 175. . . . . . . . . . . . . . . . . . . . . 5The aircraft measurement. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 7The aircraft stations . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 9Wing station diagram . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 11The vertical stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 12The horizontal stabilizer . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 14The power plant and the engine pylons . . . . . . . . . . . . . . . . . . . . 15The aircraft zoning system . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 16The major aircraft zones . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 17Sub zones. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 18Access panels. . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 20Issue: July04 FOR TRAINING ONLYRevision: 00 GE Capital Aviation Training. Reproduction Prohibited TOC 06 Page 1
  3. 3. Intentionally left blankIssue: July04 FOR TRAINING ONLYRevision: 00 GE Capital Aviation Training. Reproduction Prohibited TOC 06 Page 2
  4. 4. 06-00 Aircraft areas and dimensionsIntroductionThis chapter describes the aircraft’s general external dimensions, aircraftzoning and station identification. The fuselage stations show the lengthmeasurements along the longitudinal axis.All horizontal measurements are taken from the datum line FS 0 which is lo-cated at the nose tip. The forward pressure bulkhead is located at station610 and the fuselage is pressurized between the forward pressure bulkheadand the rear pressure bulkhead, which is located at station 23500.Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 1Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  5. 5. Figure 1: Horizontal measurements FS 0 FS 23500 FS 610 Longitudinal axis Forward pressure Rear pressure bulkhead bulkheadIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 2Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  6. 6. The aircraft measurement Embraer 170The aircraft has a total length from the nose to the tail of 29.90m (98 ft 1 in.),the height from the ground to the top of the vertical tail is 9.67m (31 ft 9 in.)and a vertical tail area of 16.20 m² (174 ft² 54 in²).The distance from the nose gear to the main gear is 10.60 meters (34ft 9 in).The aircraft has a total wing span of 26.00m (85 ft 4 in) with a total wing areaof 72.72 m² (782 ft² 180 in²), a horizontal tail span of 9.84 m (32 ft 4 in.), witha horizontal tail area of 23.25 m² (250 ft² 38 in²) and a fuselage external di-ameter of 3.01 m (9 ft 11 in.).The distance from the left to right main gear is 5.20 meters (17ft).Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 3Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  7. 7. Figure 2: Aircraft measurements Embraer 170 Total wingspan: 26.00 (85 ft 4 in) Total wing area: 72.72 m 2 Horizontal tail area: 23.25 m 2 2 (782 ft 180 in2) (250 ft 2 38 in 2) Horizontal tail span: 9.84 m (32 ft 4 in) 9.67 m (31 ft 9 in) Vertical tail area: 16.20 m 2 (174 ft 2 54 in2 ) Distance from nose gear to main gear: 10.6 m (34 ft 9 in) 29.90 m (98 ft 1 in)Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 4Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  8. 8. The aircraft measurement Embraer 175The aircraft has a total length from the nose to the tail of 31.68m (103 ft 11in.), the height from the ground to the top of the vertical tail is 9.73m (31ft 9in.) and a vertical tail area of 16.20m² (174 ft² 54 in²).The distance from the nose gear to the main gear is 11.40 meters (37ft 5 in).The aircraft has a total wing span of 26.00 meters (85 ft 4 in) with a total wingarea of 72.72 m² (782 ft² 180 in²), a horizontal tail span of 10.00 meters (32ft 9 in), with a horizontal tail area of 23.25m² (250 ft² 38 in²) and a fuselageexternal diameter of 3.01 m (9 ft 11 in).The distance from the left to the right main gear is 5.20 meters (17 ft).Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 5Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  9. 9. Figure 3: The aircraft measurement Embraer 175 11.40 m 37 ft 5 in 31.68 m 10 ft 11in 10.00 m 32 ft 9 in 5.20 m 17 ft 26.00 m 85 ft 4 inIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 6Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  10. 10. The aircraft measurementLocated on the left side of the fuselage are two main doors, which qualifiesas type 1 emergency exits. Located on the right side of the fuselage are twoservice doors, which qualify as type 1 exits, and two baggage compartmentdoors.Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 7Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  11. 11. Figure 4: The aircraft measurement Type 1 emergency exits Main door Main door Type 1 exits Service door 3.01 m (9 ft 11 in) Baggage Service door compartment doors 5.20 m (17 ft)Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 8Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  12. 12. The aircraft stationsThe aircraft stations are defined by a coordinate system using three mainreference axes. The point of origin for the longitudinal axis X, laterall axis Yand vertical axis Z is in front of the aircraft.The ordinates are identified by the letter for the major axes, followed by thedimension in inches from the point of origin.There are additional points of origin selected for locating major assemblies.These points are identified with a suffix letter indicating the assembly. Theseassemblies are the wings, the vertical stabilizer, the horizontal stabilizer, thepower plant and the engine pylons.Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 9Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  13. 13. Figure 5: Fuselage dimension FWD Fuselage Center Fuselage 1 Center Fuselage 2 Center Fuselage 3 Rear Fuselage Tail ConeX=0 X=610 X=6232.5 X=11035 X=16809 X=23295 X=27090 X=29900Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 10Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  14. 14. Figure 6: Wing station diagram RIB 1 Y= -1380.00 DRY BAY SLAT 1 ENGINE RIB 10 YA= -4617.57 WING REF. SLAT 2 POINT YA = 00.00 SLAT 3 WING SPAR 1 SLAT 4 RIB 26 YA= -12196.00 WING SPAR 3 INBOARD FLAP Y = 00.00 OUTBOARD FLAP WING SPAR 2 YA = 00.00 AILERON WING TRAILING EDGEIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 11Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  15. 15. Figure 7: Vertical stabilizer ZV 7020,10 ZV 4269,00 ZV 1069,00 ZV 622,98 Z= 00,00 ZV= 00,00 A XV= 00,00Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 12Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  16. 16. Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 13Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  17. 17. Figure 8: Horizontal stabilizer Y = 00.00 YH -2546.40 TRACE YH -5050.00 YH -3883.41 TRACEIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 14Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  18. 18. Figure 9: Power plant and engine pylons X ENG 3877.60 X ENG 5589.90 CANT XP 3256.97 XP XP XP XP 4722.0 6340.0 7201.0 8191.0Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 15Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  19. 19. The aircraft zoning systemThe aircraft zoning system provides identification of areas in the aircraft ac-cording to 8 major zones, major sub-zones and zones.The major aircraft zones are: • The lower fuselage, zone 100 • The upper fuselage, zone 200 • The tail cone and horizontal and vertical tail, zone 300 • The power plants and pylons, zone 400 • The left wing, zone 500 • The right wing, zone 600 • The landing gear and landing gear wheel well doors, zone 700 • The aircraft doors, zone 800Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 16Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  20. 20. Figure 10: The major aircraft zones Right wing Tail cone and horizontal zone 600 and vertical tail Power - plants zone 300 and pylons Upper fuselage zone 400 zone 200 Doors zone 800 Left wing zone 500 Lower fuselage Landing gears zone 100 and gear wheel - well doors 700Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 17Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  21. 21. Sub zonesThe major zones are divided into major sub-zones, which are shown by thesecond digit of the major zone number.The major sub-zones are further di-vided into zones using the third digit of the major zone number.Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 18Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  22. 22. Figure 11: Sub-zones ZONE 116 ZONE 115 ZONE 114 Zone number ZONE 113 ZONE 111 SUBZONE 170 SUBZONE 160 SUBZONE 150 SUBZONE 140 SUBZONE 130 SUBZONE 120 SUBZONE 110 Subzone numberIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 19Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  23. 23. Access panelsTo carry out maintenance on aircraft systems and their components, or toperform inspection of the aircraft structure, adequate access panels anddoors are provided in the aircraft surface.Each access panel has an identification number which consists of a threedigit zone number followed by two or three letters.The first letter shows thenumber of the panel within the zone in a logical in a logical sequence andthe second letter indicates the location of the panel in relation to the air-craft.An optional third letter is used to identify a floor, wall or ceiling panel.Each panel has a fastener identification code, which identifies the type andthe quantity of the fasteners for each panel.Issue: July04 FOR TRAINING ONLY Chapter 06-00 Page 20Revision: 01 GE Capital Aviation Training. Reproduction Prohibited
  24. 24. Figure 12: Access panels identification letters 191 DL 191 EL 192 CL 192 BL 192 AL 195 HL 195 FL 195 JL 191 AL 195 KL 195 GL 191 BL 191 CL 195 EL Shows the number of the Indicates the location of the panel within the zone panel in relation to the aircraft 195 AL 195 DL 195 BL 195 CL 19 S An optional third letter is used to identify a floor(F), wall(W) or ceiling(C) panel. 19 S Each panel has a fastener identification code: L = Latch S = Screw C = CamlocIssue: July04 FOR TRAINING ONLY Chapter 06-00 Page 21Revision: 01 GE Capital Aviation Training. Reproduction Prohibited

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