ATA 00-20 Aircraft General - Bombardier DHC 8-400 (PWC PW150) PDF

BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL DIMENSIONS The aircraft dimensions are: OVERALL DIMENSIONS • • • • Span - 93 ft 3 in (28.42 m) Length - 107 ft 9 in (32.83 m) Height - 27 ft 4 in (8.34 m) Propeller Ground Clearance - 38.67 in (98.22) WINGS • • • Root chord -121.26 in (3.08 m) Tip...

BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL DIMENSIONS The aircraft dimensions are: OVERALL DIMENSIONS • • • • Span - 93 ft 3 in (28.42 m) Length - 107 ft 9 in (32.83 m) Height - 27 ft 4 in (8.34 m) Propeller Ground Clearance - 38.67 in (98.22) WINGS • • • Root chord -121.26 in (3.08 m) Tip chord - 46.59 in (1.18 m) Aspect ratio - 12.8 HORIZONTAL STABILIZERS AND ELEVATORS • • • • • • Span - 30 ft 5 in (28.42 m) Root chord - 6 ft 8 in (2.03) Tip chord - 4 ft 11 in (1.50 m) Aspect ratio - 2.27 Incidence - 1° Dihedral - 2.5° TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 2 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL DIMENSIONS AIRCRAFT STATIONS The three primary axes are given X, Y and Z and the ordinates are identified along these axes from a point of origin. The longitude axis is X, the lateral axis is Y and the vertical axis is Z. The point of origin for the three axes is in front of the forward passenger door and below the ground reference line of the aircraft. Identification of the ordinates is by the dimension in inches from the point of origin. The X, Y, Z axis system has more points of origin that are set in the aircraft. These datum points show the location of primary assemblies. The wings, horizontal stabilizer, nacelles and vertical stabilizer are primary assemblies. These ordinates are identified by: • • • • • XW, YW and ZW (Wings) XH, YH, and ZH (Horizontal stabilizer) XV, YV, and ZV (Vertical stabilizer) XN, YN, and ZN (Nacelles) XP, YP and ZP (Bullet fairing). TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 4 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL AIRCRAFT ZONES The aircraft is divided into eight major zones. • • • • • • • • Zone 100 Zone 200 Zone 300 Zone 400 Zone 500 Zone 600 Zone 700 Zone 800 Lower fuselage Upper fuselage Empennage Powerplants and nacelles Left wing Right wing Landing gear and landing gear doors Doors Each major zone is further broken down into subzones for ease of location components and panels. Some examples of these are: • • Subzone 120 Flight compartment under floor area Subzone 130 Fuselage under floor area TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 6 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL EXTERNAL AND INTERNAL ACCESS PANELS AND DOORS The access panels and doors are identified by an alphanumeric code. The identification code makes it easier to find the different access panels, doors and fairings. Each panel, door and fairing has a two-group code to indicate its position on the aircraft. A three digit numeric group indicates the Major zone and sub zone where the panel, door or fairing is located. A two digit letter group gives the position of the panel, door or fairing in relation to the aircraft as follows: The first letter identifies the general position. This starts with the letter A and goes from the inboard to outboard and from the front to the rear the letters I and O are not used. The second letter identifies the location of the panel, door or fairing in relation to the aircraft as follows: • • • • • T (Top) B (Bottom) L (Left side) R (Right side) Z (Internal). TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 12 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL LIFTING AND SHORING JACKING Jacking of the aircraft fuselage is done by using the three fuselage jacking points. One is located on the forward fuselage aft of the nose landing gear and one on each rear spar in the centre part of the wing. The jacking weight of the nose is 4,700 lb/2,132 kg. The jacking weight of the aircraft is 48,792 lb/22,132 kg. • • Install a tail stand in the adapter on the bottom of the aft fuselage Lift the aircraft on jacks at the nose and main landing gear axles as follows: • • • • • • Centre the nosewheel Make sure the nose wheel steering is off Install the nose landing gear castor lockpin in its hole Release the parking brake Remove the chocks from the landing gear tyres Put the nose landing gear jack or the main landing gear jack at its related jack pad Increase the jack height until the jack correctly engages the related jack pad Lift the aircraft on the applicable axle jack until the related wheel is approximately 2 inches (51 mm) clear of the ground • • NOTE: Before jacking the aircraft, the forward right hand side emergency exit must be removed and a plum bob attached to a hanger at the top of the door frame. Lift the aircraft on jacks at the wing and the nose landing gear fuselage as follows: • • • • • • • • • • • • Release the parking brake Move the chocks sufficiently clear of the NLG tyres Put a nose fuselage jack at the jacking point of the nose fuselage Put the jack adapter in the nose fuselage receptacle and hold it there. Increase the jack height until the jack correctly engages the adapter Lift the aircraft at the jacking point of the nose fuselage. Continuously move the lock collar while you lift the aircraft Stop when the plumb bob aligns with the longitudinal level mark on the target plate Put a wing jack at each wing jacking point Move the chocks sufficiently clear of the main landing gear tyres Put the jack adapter in the right wing receptacle and hold it there. Increase the jack height until the jack touches the adapter Repeat for the other side Lift the aircraft on the jacks at the three positions at the same time A crewmember must monitor the plumb bob to make sure that the longitudinal axis of the aircraft stays level TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 14 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL LEVELLING AND WEIGHING WEIGHING OF THE AIRCRAFT Electronic load sensing devices must be used to weight the aircraft at the nose fuselage and the axles of the main landing gear. The weights are recorded to calculate the total weight and the centre of gravity of the aircraft. If an operator wants to use a different procedure to calculate the weight of the aircraft, bombardier engineering must be consulted. The basic weight of the aircraft is the weight that includes all fixed operating equipment, both standard and optional, trapped and unusable fuel and full engine oil. To calculate the weight and the centre of gravity of the aircraft, refer to PSM 1-84-8, Weight and Balance Manual. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 16 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL TOWING AND TAXIING TOWING Chapter 09 of the AMM incorporates the procedures for aircraft towing and taxiing. Tow the aircraft as follows: • • • • • • • • • • • • Disconnect the grounding wire from the aircraft Make sure that you remove external servicing connections from the aircraft Do a general visual inspection of the landing gear tyres Close all external doors of the aircraft Set the nosewheel steering to off Connect the towbar head to the towing spools. The spools are on the inner cylinder of the nose landing gear Remove the chocks from the landing gear wheels Set the parking brake to the off position Make sure that you do not tow the aircraft at a more than maximum speed of 5 mph Keep the aircraft turning radii in the limits. The towing turn limits are 120° each side of centre. Painted arrows on the two landing gear doors show these limits Engage the parking brake after you tow the aircraft Make sure the nosewheel is straight before you disconnect the towbar TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 18 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL - TAXI STEERING ANGLES TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 21 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL - AIRCRAFT TURNING RADIUS (LOW-SPEED TAXI) TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 22 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL PARKING, MOORING, AND RETURN TO SERVICE PARKING AND MOORING Chapter 10 of the AMM incorporates the procedures to park and moor the aircraft. The chapter has all the instructions to be followed for parking the aircraft. It contains a list of all the covers that have to be installed, instructions on installing the main gear locking pins and instructions and safety precautions on engaging the nose gear ground lock. NOTE: If you cannot engage the NLG lock then the nose landing gear is not safe. If this condition exists, then the forward fuselage must be supported by a jack, as the gear could collapse. Also in this chapter are all the procedures for mooring the aircraft. It provides the instructions on the mooring rings and tie down procedures as well as the conditions when the aircraft should be moored. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 24 of 30 BOMBARDIER DHC 8-400 (PWC PW150) AIRCRAFT GENERAL PLACARDS AND MARKINGS Chapter 11 of the AMM incorporates a component location index that shows the placards, labels and markings for the aircraft. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 00-20 - AIRCRAFT INTRODUCTION Issue 6 - January 2023 Page 28 of 30