ATA 06 Cessna 650.pdf

MANUAL DE ENTRENAMIENTO EN CESSNA 650 PARA MANTENIMIENTO

TORNADO ASESORA EN TRANSPORTACIN AREA S.A. DE C.V. SOLO CON FINES DE ADIESTRAMIENTO

ATA 06 Dimensiones y reas - Pgina 1

ATA 06 DIMENSIONS AND AREAS Definition A. Airplane Dimensions and Areas. (1) The section on airplane dimensions and areas provides airplane dimensions and identifies areas of the airplane. B. Airplane Locations.

(1) The section on airplane locations describes the airplane reference points which facilitate the location of specific areas of the airplane. Included are: identification and definition of airplane stations, water lines and/or buttock lines, access plates/panels identification and location, definition of airplane zoning and identification and location of the airplane systems drains.




Dimensions NOTE: 1. All dimensions are in feet. NOTE: 2. Airplanes -0001 thru -0093 not incorporating SB650-32-13: with the nose gear fully compressed and the main gear oleos at maximum extension, the maximum overall height at the tail increases to 18.70 feet. NOTE: 3. Airplanes -0001 thru -0093 incorporating SB650-32-13 and Airplanes -0094 and On: with the nose gear fully compressed and the main gear oleos at maximum extension, the maximum overall height at the tail increases to 18.33 feet. NOTE: 4. Wing span includes navigation lights on wing tips. Overall wing span including static wicks is 54.06 feet A. Airplane Overall: (1) Length = 55.20 Feet (2) Height (Static Condition) = 17.10 Feet (Refer to Note 2). (3) Height (Static Condition) = 16.73 Feet (Refer to Note 3) (4) Wing Span = 53.49 Feet (Refer to Note 4) B. Wing: (1) Type: Low Supercritical (2) Airfoil Section and Thickness (percent of chord): (a) At Root (WS 32.00) = 15.89 Percent (b) At Planform Break (WS 88.00) = 13.75 Percent (c) At Tip (WS 300.60) = 11.90 Percent (3) Incidence: (a) At Root (WS 32.00) = +2.88 Degrees (b) At Planform Break (WS 88.00) = +1.10 Degrees Flight (c) At Tip (WS 300.60) = -1.00 Degree Flight (4) Chords: (a) At Root (WS 32.00) = 9.80 Inches (b) At Construction Tip (WS 320.17) = 33.53 Inches (5) Dihedral 2.25 Degrees (6) Sweep-back: (a) Leading edge inboard (WS 88.00) = 37.00 Degrees (b) 25 percent chord outboard (WS 88.00) = 25.00 Degrees




(7) Aspect Ratio 8.94 C. Horizontal Stabilizer: (1) Span = 18.35 Feet (2) Chords: (a) At Root (HSS 0.00) = 5.44 Feet (b) At Tip (HSS 110.07) = 1.91 Feet (3) Incidence: (a) Mechanical = +1.90 to -13.40 Degrees (b) Electrical = +1.60 to -12.50 Degrees (4) Anhedral = 3.00 Degrees (5) Sweep-back: (a) At 25 Percent Chord = 31.66 Degrees (b) At Leading Edge = 35.43 Degrees (6) Aspect Ratio = 4.99 (7) Airfoil Section Thickness: (a) Root (HSS 0.00) = 9.5 Percent (b) Tip (HSS 110.07) = 8 Percent D. Vertical Stabilizer: (1) Span = 8.60 Feet (2) Chord: (a) At Root (WL 140.60) = 9.48 Feet (b) At Tip (WL 243.44) = 5.69 Feet (3) Airfoil Section Thickness: (a) At Root = 12 Percent (b) At Tip = 12 Percent (4) Sweep-back: (a) At 25 Percent Chord = 40.00 Degrees (b) At Leading Edge = 43.52 Degrees E. Cabin Length: (1) Forward Pressure Bulkhead to Aft Pressure Bulkhead = 23.9 Feet (2) Forward Divider to Aft Pressure Bulkhead = 18.49 Feet F. Cabin Internal Height and Width: (1) Height Maximum (interior stand up) = 5.83 Feet

(2) Width Maximum = 5.67 Feet 3. Areas A. Wing (total, less tips) (1) 311.73 Square Feet B. Horizontal Stabilizer (1) 67.41 Square Feet C. Vertical Stabilizer (exposed) (1) 55.89 Square Feet Description A. Abbreviations and Terminology. (1) The Model 650 airplane utilizes a reference point of 30.70 inches in front of the nose (radome) for its Fuselage Station (FS) datum line. A Datum Line is an imaginary plane or line from which distances are measured. The distance to a given fuselage station is measured in inches from the datum line in front of the airplane aft perpendicular to the center line. (2) The Center Line of the airplane is the imaginary vertical plane extending lengthwise through the middle of the fuselage. (3) Buttock Line (BL) is a width measurement to the left or right of, and parallel to, the vertical center line. Measurements in inches to the left of the airplane center line are identified as Left Buttock Lines (LBL) and measurements to the right are identified as Right Buttock Lines (RBL). (4) Water Line (WL) is the measurement of height in inches from a horizontal plane located at a fixed number of inches below the bottom of the fuselage. For the Model 650, the zero water line is 91.00 inches below the bottom of the fuselage. (5) Horizontal Stabilizer Station (HSS) is a length measurement in inches of the horizontal stabilizer from the airplane center line outboard to the left or right stabilizer tip parallel to the fuselage. (6) Vertical Stabilizer structure locations are identified by the fuselage stations and water lines extending through the vertical stabilizer, sometimes called the Vertical Fin. (7) Wing Station (WS) is a length measurement in inches of the wing from the airplane center line outboard to the left or right wing tip parallel to the fuselage.




(8) Canted Wing Station (CWS) is a length measurement in inches going outboard along the wing, perpendicular to the wing front spar. (9) Engine Station (ES) is a length measurement in inches with the front of the air inlet nacelle being ES 161.54 and the center of the engine at ES 200.00. The engine cowling or nacelle stations are identified by engine stations. (10) Engine Buttock Lines (EBL) is a width measurement in inches to the left or right of, and parallel to, the engine vertical center line. Buttock Lines to the left and right of the engine vertical center line are identified as LEBL and REBL respectively. The engine vertical center line is established at EBL 100.00. (11) "Chord" is defined as a straight line intersecting or touching an airfoil profile at two points. A "Chord Line" is usually a datum line joining the leading and trailing edges of an airfoil. Points or stations along a chord are designated in percentages or fractions of the chord, or the chord length from the leading edge. (a) Root Chord is the length of the chord where the wing and fuselage join. (b) Chord is the length of the chord at or near the wing tip. (c) Mean Chord is the gross airfoil surface area divided by the span.




ACCESS PLATES AND PANELS IDENTIFICATION - DESCRIPTION AND OPERATION 1. General A. All access plates, panels, and doors are identified by using the airplane zoning number plus one or two suffix letters as shown in the example below. (1) The first suffix letter is the primary identifier. The primary identifier identifies the plate, panel, or door in a logical sequence, such as: inboard, outboard, forward, or aft; starting with the letter in each zone. (Refer to Figure 1.) (2) The second suffix letter identifies the plate, panel, or door in its relation to the airplane, such as top, bottom, left, right, or internal.




AIRPLANE DRAIN LOCATION - DESCRIPTION AND OPERATION

Description A. Drains are located by fuselage station, water line or buttock line where drain protrudes through the fuselage. For removal and installation of drain lines, refer to applicable chapter.

ATA 06 Cessna 650.pdf

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