Institute of Engineering and Technology
Philippine State College of Aeronautics
Piccio Garden, Villamor, Pasay City

DRAW 122
Mechanical Drawing
&
Blueprint Reading

Name: Mike Melvin L. Tiano
2nd Semester S.Y. 2014-2015

Professor: Mr. Richard E. Olipas

Institute of Engineering and Technology
Philippine State College of Aeronautics
Piccio Garden, Villamor, Pasay City

ACKNOWLEDGEMENT

Name: Chester Allan Mill D. Fetalino
2nd Semester S.Y. 2014-2015
Institute of Engineering and Technology
Philippine State College of Aeronautics
Piccio Garden, Villamor, Pasay City

Table of Content Plate NO. | Title | Grade | 1 | 3 views | 1.25 | 2 | A/C Specification | 1.00 | 3 | Engine Description | 1.00 | 4 | Weight Estimation | 1.00 | 5 | Wing tips | 1.00 | 6 | Aft tail variations | 1.00 | 7 | Other tail configuration | 1.00 | 8 | Propulsion system options | 1.00 | 9 | Inlet locations-buried engines | 1.00 | 10 | Inlet locations-podded engines | 1.00 | 11 | Propeller location matrix | 1.00 | 12 | Landing gear arrangement | 1.00 | 13 | Gear/shock arrangement | 1.00 | 14 | A home for the gear | 1.00 | 15 | Flap types | 1.00 | 16 | Leading edge devices | 1.00 | 17 | Average cockpit dimensions needed to provide adequate room for the pilot | 1.00 | 18 | Suggested dimension for windows, doors, and spacing for passengers | 1.00 | 19 | Normal tandem seating arrangement | 1.00 | 20 | Average dimensions for seating when the leg is vertical | 1.00 | 21 | Average dimensions for seating when the lower leg is 45 degree to the vertical | 1.00 | 22 | Interior arrangement of a cabin | 1.00 | 23 | Toilet seating | 1.00 | 24 | A few governing dimensions are given in this illustration | 1.00 | 25 | “pick-a-back” seating arrangement | 1.00 | 26 | Staggered seat arrangement | 1.00 | 27 | Back-to-back seat arrangement | 1.00 | 28 | Average dimension (in inches) for the standard-type seat provided in airplane | 1.00 | 29 | Pilot seated normally (toboggan fashion) | 1.00 | 30 | Normal side-by-side seating | 1.00 | 31 | Average dimensions of a 6feet tall | 1.00 | 32 | Allowances to be made in seating with various type parachutes | 1.00 | 33 | Side and plan views of control and instrument board for prone position of pilot | 1.00 | 34 | Aisle | 1.00 | 35 | A shock absorber developed by firestone | 1.00 | 36 | A shimmy-damper installation | 1.00 | 37 | NOSE INLET IN FUSELAGE OR NACELLE | | 38 | THE ANNULAR INLET | | 39 | THE EXTERNAL SCOOP | | 40 | LOW-WING MONOPLANE WITH A TWIN VERTICAL TAIL SURFACE ARRANGEMENT | | 41 | MID-WING DESIGN WITH A JET-ENGINE INSTALLATION | | 42 | SO-CALLED BUTTERFLY TAIL COMBINES THE FUNCTIONS OF THE VERTICAL AND HORIZONTAL TAIL SURFACES IN THIS MID-WING MONOPLANE | | 43 | INVERTED GULL WING DESIGNED TO RAISE THE PROPELLER AXIS OF THE CENTRALLY LOCATED ENGINE | | 44 | A JET ENGINE DESIGN WITH AIR INLETS ALONG THE FUSELAGE | | 45 | HIGH-WING MONOPLANE WITH A PUSHER-TYPE ENGINE INSTALLATION | | 46 | A SMALL PUSHER AIRPLANE WITH TWIN BOOMS SUPPORTING THE TAIL SURFACE | | 47 | A CANARD PUSHER-TYPE AIRPLANE OF UNUSUAL DESIGN WITH THE HORIZONTAL TAIL SURFACE AHEAD OF THE WING | | 48 | A PROPOSED SIGN WITH A JET ACTUATED PROPELLER | | 49 | A MULTI-ENGINE MONOPLANE INCORPORATING A TRIPLE VERTICAL TAIL SURFACE ARRANGEMENT | | 50 | MULTIPLE-ENGINE DESIGN USES A PUSHER INSTALLATIONIN ORDER TO OBTAIN A MORE FAVORABLE CG LOCATION | | 51 | CARGO AIRPLANE WITH TWIN BOOMS SUPPORTING THE TAIL SURFACES HIGH AND CLEAR OF THE REARLOADING AREA OF THE FUSELAGE | | 52 | TWIN FUSELAGE MONOPLANE WHICH MAKES USE OF TWIN-ENGINE NACELLES AND TWIN BOOMS | | 53 | TWIN FUSELAGE DESIGN WITH A SPECIAL COMPARTMENT FOR PERSONNEL | | 54 | A MONOPLANE WITH AN UNUSUALLY WIDE FUSELAGE OF AIRFOIL CROSS SECTION DESIGNED | | 55 | AN INCREASE IN BEDROOM IS OBTAINED BY INCLINING THE BACK OF THE SEAT | | 56 | PASSENGER COULD SIT THIS WAY OR THE SECOND AND THIRD MAN COULD MOVE FORWARD BY SPREADING THEIR LEGS | | 57 | AILERON PLANFORMS AND SECTIONS | | 58 | LIFT-INCREASE DEVICE: (A) PLAIN FLAP; (B) SLOTTED FLAP;(C) DOUBLE SLOTTED FLAP; (D) HANDLEY-PAGE SLOT AND FLAP;(E) EXTERNAL AIRFOIL FLAP; (F) SPLIT FLAP; (G) SPLIT FLAP WITH A REAR HINGE POINT | | 59 | PRELIMINARY CONSIDERATIONIN LOCATING THE LANDING GEAR | | 60 | THE FRONT WHEEL SHOULD NOT SWING MORE THAN 5 DEGREESAHEAD OF THE VERTICAL FOR THE TAIL-HIGH POSITION AIRPLANE | | 61 | NOTE THE CLEARANCE THAT HAVE TO BE KEPT IN MIND: A, PROPELLER AND GROUND CLEARANCE; B, WHEEL AND WING CLEARANCE; C, DEFLECTED FLAP CLEARANCE WITH THE GROUND; D, DEFLECTED E;AVATOR CLEARANCE WITH THE GROUND | | 62 | ANGULAR REQUIREMENTS FOR THE COMPONENTS OF THE TRICYCLE LANDING GEAR | | 63 | NOTE THE CLEARANCE THAT HAVE TO BE KEPT IN MIND: A, PROPELLER AND GROUND CLEARANCE; B, WHEEL AND WING CLEARANCE; C, DEFLECTED FLAP CLEARANCE WITH THE GROUND; D, DEFLECTED E;AVATOR CLEARANCE WITH THE GROUND. E AND F ARE ROLLING RADII OF WHEELS | | 64 | A LANDING GEAR RETRACTED SIDEWAYS INTO THE FUSELAGE | | 65 | THE LANDING GEAR IS RETRACTED DIRECTLY REARWARD INTO THE WING BETWEEN THE FRONT AND REAR SPARS | | 66 | ANOTHER RETRACTABLE LANDING GEAR DESIGN WHERE SPACE BETWEEN THE FRONT REAR WING SPARS IS LIMITED | | 67 | MINIMUM CLEARANCE BETWEEN WHEEL AND SUPPORTING STRUCTURE IS APPROXIMATELY 1/25 TO 1/30 OF THE WHEEL DIAMETER | | 68 | A SIMPLE BRAKE INSTALLATION | | 69 | A DETAIL DRAWING OF THE LANDING GEAR USED ON EUROPE | | 70 | A THREE-QUARTER VIEW OF A TWIN ENGINEMONOPLANE WITH THE MAIN COMPONENTS NAMED | | Final Rating: _________

Remarks: _______________