ATA 53 Fuselage - Issue 6 January 2023_Compress.pdf

BOMBARDIER DHC 8-400 (PWC PW150) ATA 53 - FUSELAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE The windshield panels are of laminated glass construction stressed to take pressu...

BOMBARDIER DHC 8-400 (PWC PW150) ATA 53 - FUSELAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY B1/B2 MAINTENANCE TRAINING MANUAL Issue 6 - January 2023 Page 1 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE The windshield panels are of laminated glass construction stressed to take pressure from the inside. NOSE FUSELAGE The windshields are designed to withstand bird strikes. GENERAL DESCRIPTION The side window panels are constructed of stretched acrylic laminates. The Nose fuselage section is attached to the forward section of the main fuselage structure. The nose section has: The nose section extends from station X178.00 to X18.250 where it joins the forward centre fuselage. • • • • The forward pressure bulkhead is located just forward of the windshields at station (X-111.00). The flight compartment Nose wheel well Forward pressure bulkhead Forward equipment compartment The area forward of the bulkhead encloses the un-pressurized equipment compartment and supports the weather radar unit and the nose cone. The fuselage is a semi-monocoque structure with skin reinforced by circumferential frames and longitudinal stringers. The nose landing gear and nose-wheel well are located below the equipment compartment. The primary structures in the fuselage are the stringers, frames and aircraft skin. The fuselage structure is made of high strength aluminium alloys. A protective coating along the bottom of the fuselage is applied for protection from unpaved runways. One layer of F22 epoxy-polyamide enamel and two layers of corrosion preventive compound (F13) are applied to get an erosion resistant protective coating. The nose section of the fuselage has these components: • • • Nose Fuselage Access Panels Nose Fuselage Fairings Nose Fuselage Floor The nose section includes the flight compartment. It is separated from the passenger cabin by a bulkhead which contains a lockable door. A removable hatch type of emergency exit is provided in the flight compartment roof. It can be opened for ventilation purposes when the aircraft is on the ground. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 2 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - NOSE FUSELAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 3 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE NOSE FUSELAGE NOSE FUSELAGE ACCESS PANELS There is a vent panel - 112BR - on the bottom of the nose fuselage. There are four service panels - 121AL, 121BL, 122BR, 122AR - on the left and right side of the nose fuselage. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 4 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - NOSE ACCESS PANELS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 5 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE The use of riveting of stringers and window reinforcements to the skin uses minimum weight to permit a smooth riveted external surface. This also stops crack propagation. FORWARD CENTRE FUSELAGE GENERAL DESCRIPTION The forward centre fuselage is a part of the main fuselage which forms the primary structure of the aircraft. The fuselage is a semi-monocoque structure with skin reinforced by circumferential frames and longitudinal stringers. The primary structures in the fuselage are the stringers, frames and aircraft skin. The fuselage structure is made of high strength aluminium alloys. A protective coating along the bottom of the fuselage is applied for protection from unpaved runways and corrosion. One layer of F22 epoxy-polyamide enamel and two layers of corrosion preventive compound (F13) are applied. The forward centre fuselage has these components: • • Forward Centre Fuselage Access Panels Forward Centre Fuselage Floor The forward centre fuselage extends from the nose fuselage section joint to the middle centre fuselage section, Sta.X19.775 to Sta.X234.475. This part of the centre fuselage forms the forward baggage compartment and the forward passenger area of the aircraft. It contains the airstair door and a flight attendant seat. The flight attendant seat is attached to the aft wall of the forward wardrobe compartment. The forward centre fuselage is largely of a constant circular cross section of 106 in (2692 mm) outer diameter with a flat bottom of a larger radius. There is extensive use of flush riveting on stringers and window reinforcements. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 6 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - FORWARD CENTER FUSELAGE LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 7 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE FORWARD CENTRE FUSELAGE CUT THROUGH PANELS The sixth window aft of the forward passenger door or the fourth window aft of the emergency exit on the right side, are the recommended first choice cut-through areas. NOTE: Any window is suitable in extreme circumstances. Cut-through areas require portable metal cutting equipment. It is recommended that major effort is used to gain access to doors and hatches due to the type of structure and possible injury to personnel within. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 8 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - FORWARD CENTRE FUSELAGE CUT THROUGH PANELS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 9 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE FORWARD CENTRE FUSELAGE FLOOR The forward centre fuselage forms the horizontal base of the passenger and attendant area. It is largely of a constant with a flat bottom cross section of 80 in (2032 mm). Floor loads are held by the seat rails and frames. The floor structure makes the airframe stable if there is a wheels-up landing. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 10 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - FORWARD CENTRE FUSELAGE FLOOR LAYOUT TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 11 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE These panels withstand stress of 75 lbs/ft² (3.6 kNs/m²). FORWARD CENTRE FUSELAGE Floor panels used in entrance areas are sandwich construction with unidirectional fibreglass faces and aramid honeycomb core. FLOOR CONTINUED These panels are stronger and prevent moisture absorption and withstand stress of 75 lbs/ft² (3.6 kNs/m²). Floor covering in the passenger compartment uses an anti-static filament in the carpet weave. Floor covering in and ahead of the airstair door entrance way is a foam backed vinyl. Floor panels in the entrance way are sealed with vinyl tape and caulking to prevent moisture from going below floor level. Two types of floor coverings that be installed in the passenger compartment, Type 1 or Type 2 panels are selected based on: • • • Cabin interior noise and vibration levels The required stress resistance The area in which they are fitted COMP 28 TYPE 2 Floor panels used in galley and lavatory areas are sandwich construction with unidirectional S-glass/epoxy faces and aramid honeycomb core. These panels absorb moisture with negligible mechanical property degradation and withstand stress of 75 lbs/ft² (3.6 kNs/m²). Floor panels used in baggage compartments areas are sandwich construction with unidirectional fibreglass faces with a polyester overlay and aramid honeycomb core. COMP 27 TYPE 1 Panels used under the seats, made of unidirectional carbon/phenolic faces and aramid honeycomb core. These panels are stronger and prevent wear with negligible mechanical property degradation and withstand stress of 125 lbs/ft² (5.6 kNs/m²). These panels withstand stress of 37.5 lbs/ft² (1.8 kNs/m²). COMP 27 TYPE 2 Panels used in the centre aisle are sandwich construction with unidirectional carbon/ phenolic faces and aramid honeycomb core. These panels withstand stress of 75 lbs/ft² (3.6 kNs/m²). COMP 28 TYPE 1 Panels used in the cabin entry way area are sandwich construction with unidirectional S-glass/epoxy faces and aramid honeycomb core. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 12 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - FORWARD CENTRE FUSELAGE FLOOR PANEL STRESS LOADING TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 13 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE Floor loads are held by the seat rails and frames. The floor structure make the airframe stable if there is a wheels-up landing. MIDDLE CENTRE FUSELAGE GENERAL DESCRIPTION The middle centre fuselage is a part of the main fuselage which forms the primary structure of the aircraft. The fuselage is a semi-monocoque structure with skin reinforced by circumferential frames and longitudinal stringers. The primary structures in the fuselage are the stringers, frames and aircraft skin. The fuselage structure is made of high strength aluminium alloys. A protective, corrosion preventive is applied coating along the bottom of the fuselage for protection from unpaved runways. One layer of F22 epoxy-polyamide enamel and two layers of corrosion preventive compound F13 are applied. The middle centre fuselage has these components: • • • • Middle Centre Fuselage Access Panels Fuselage to Wing Fairing Middle Centre Fuselage Floor Middle Centre Fuselage Surfaces The middle centre fuselage extends from the forward centre fuselage section to the aft centre fuselage section Sta.X234.475 to Sta.X566.025. The part of the centre fuselage forms the majority of the passenger area of the aircraft. It is largely of a constant circular cross section of 106 in (2.7 m) outer diameter with a flat bottom of larger radius. Extensive use is made of flush riveting of stringers and window reinforcements to the skin. The wing structure is attached to fittings on the centre section with tension bolts. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 14 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - MIDDLE CENTER FUSELAGE LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 15 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE MIDDLE CENTRE FUSELAGE FLOOR There are two types of floor coverings that may be installed in the passenger compartment. Type 1 or Type 2 panels may be installed, dependent the cabin interior noise and vibration levels, the required stress resistance and the area in which they are fitted. Panels used under the seats, made of unidirectional carbon/phenolic faces and aramid honeycomb core. These panels withstand stress of 37.5 lbs/ft² (1.8 kNs/m²). Panels used in the centre aisle are sandwich construction with unidirectional carbon/ phenolic faces and aramid honeycomb core. These panels withstand stress of 75 lbs/ft² (3.6 kNs/m²). SURFACES The ice shields are installed on the left and right sides of the middle centre fuselage surfaces. These shields are installed on the plane of the propellers to protect the fuselage pressure shell from damage due to ice being thrown from the propellers. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 16 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - MIDDLE CENTER FUSELAGE / ICE SHIELDS TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 17 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE Floor loads are held by the seat rails and frames. The floor structure makes the airframe stable if there is a wheels-up landing. AFT CENTRE FUSELAGE Extensive use is made of riveting of stringers and window reinforcements to the skin. This gives minimum weight to permit a smooth riveted external surface. GENERAL DESCRIPTION The aft centre fuselage is a part of the main fuselage which forms the primary structure of the aircraft. The fuselage is a semi-monocoque structure with skin reinforced by circumferential frames and longitudinal stringers. DORSAL FAIRING The fuselage fairing is attached to the top surface of the fuselage. This fairing gives an aerodynamically smooth surface from the wing area to the aft dorsal fairing. The dorsal fairing is made from composite materials. The primary structures in the fuselage are the: • • • Stringers Frames Aircraft skin The fuselage structure is made of high strength aluminium alloys. A protective coating along the bottom of the fuselage is applied for protection from unpaved runways. One layer of F22 epoxy-polyamide enamel and two layers of corrosion preventive compound F13 are applied to get an erosion resistant protective coating. The aft centre fuselage has these components: • • Aft Centre Fuselage Floor Aft Centre Fuselage Dorsal Fairing The aft centre fuselage extends from the middle centre fuselage section Sta.X564.500 to the aft fuselage section Sta.X836.452. The part of the centre fuselage forms the majority of the passenger area of the aircraft. It is largely of a constant circular cross section of 106 in (2.7 m) outer diameter with a flat bottom of larger radius. Extensive use is made of flush riveting of stringers and window reinforcements to the skin. This gives minimum weight to permit a smooth riveted external surface. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 18 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - AFT CENTER FUSELAGE LOCATOR TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 19 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE AFT FUSELAGE GENERAL DESCRIPTION The aft fuselage is a part of the main fuselage which forms the primary structure of the aircraft. The aft fuselage is a semi-monocoque structure with skin reinforced by circumferential frames and longitudinal stringers. The primary structures in the fuselage are the stringers, frames and aircraft skin. The fuselage structure is made of high strength aluminium alloys. A protective coating along the bottom of the fuselage is applied for protection from unpaved runways. One layer of F22 epoxy-polyamide enamel and two layers of corrosion preventive compound F13 are applied to get an erosion resistant protective coating. The aft/tail fuselage has these components: • • Aft Fuselage Access Panels Aft Fuselage Dorsal Fairing The aft/tail fuselage section is the part of the aircraft behind the Sta.X836.452 without the tail cone. The vertical stabilizer and dorsal fin are a part of the aft/tail fuselage section. The lower part of the three stabilizer spars extend down to make the mainframe of the aft fuselage. The area between the front and centre frame is an equipment bay for the air cycle machine and other equipment. Access to the equipment bay is given by an access door from the outside. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 20 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - AFT FUSELAGE TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 21 of 24 BOMBARDIER DHC 8-400 (PWC PW150) FUSELAGE AFT FUSELAGE DORSAL FAIRING The aft fuselage dorsal fairing consists of a forward and aft assembly that connects the forward dorsal fin at Sta.846 to the vertical stabilizer. The aft fuselage dorsal fairing fairs the forward dorsal fin to the vertical stabilizer. The aft fuselage dorsal fairing is a combination of fairings and panels constructed from composite materials. TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 22 of 24 BOMBARDIER DHC 8-400 (PWC PW150) STRUCTURES - FUSELAGE - AFT FUSELAGE DORSAL FAIRING TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 23 of 24 BOMBARDIER DHC 8-400 (PWC PW150) INTENTIONALLY LEFT BLANK TO BE USED FOR MAINTENANCE TRAINING PURPOSES ONLY ATA 53 - FUSELAGE Issue 6 - January 2023 Page 24 of 24