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Support Aircrafts (Fixed Wing)

C-130 | BN-2A | T-41D | F27-200 | F-28-3000 | N.22B | Ce 210 | RQ-1 Next

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Lockheed model 382 USAF designation C-130B/H and model 382E commercial designation L-100-20 'Hercules'
Type: Medium/long range combat transport
Origin:
USA
Similar aircraft:
Belfast, An-12 Cub
Wings:
Cantilever high-wing monoplane. Wing section NACA 64A318 at root, NACA 64A412 at tip. Dihedral 2 30'. Incidence 3 at root 0 at tip. Sweepback at quarter-chord 0. All-metal two spar stressed skin structure, with integrally stiffened tapered machined skin panels up to 14.63 m (48' 0") long. Conventional aluminum alloy ailerons have tandem-piston hydraulic boost, operated by either of two independent hydraulic systems. Lockheed-Fowler aluminum alloy trailing-edge flaps. Trim tab in each aileron. Leading-edges anti-iced by engine bleed air.
Fuselage:
Semi-monocoque structure of aluminum and magnesium alloys.
Tail unit:
Cantilever all-metal stressed skin structure. Fixed incidence tailplane, with Kevlar afterbody strake on understructure at each side close to fuselage. Trim tab in each elevator and rudder. Elevator tabs use AC electrical power as primary source and DC as emergency source. Control surfaces have tandem-piston hydraulic boost. Hot air anti-icing of tailplane leading-edge, by engine bleed air.
Landing gear:
Hydraulically retractable tricycle type. Each main unit has two wheels in tandem, retracting into fairings built on to the sides of the fuselage. Nose unit has twin wheels and is steerable through 60 each side of center. Oleo shock absorbers. [H] Main wheel tire size 56 x 20-20, pressure 6.62 bars (96 psi). Nosewheel tire size 39 x 13-16, pressure 4.14 bars (60 psi); [L-100-20] Main wheel tire size 56 x 20-20, pressure 3.24-7.38 bars (47-107 psi). Nosewheel tire size 39 x 13-16, pressure 4.14 bars (60 psi). Goodyear air-cooled multiple disc hydraulic brakes with anti-skid units. Retractable combination wheel-skis available optionally.
Accommodation:
Crew of four on flight deck, comprising of pilot, co-pilot, navigator and systems manager (fully performance qualified flight engineer on USAF aircraft). Provisions for fifth man to supervise loading. Sleeping quarters for relief crew, and galley. Flight deck and main cabin pressurized and air-conditioned. Standard complements for C-130 are as follows: troops (maximum) 92, paratroops (maximum) 64, litters 74 and 2 attendants. As cargo carrier, loads can include heavy equipment such as 12,080 kg (26,640 lb) type F.6 refueling trailer, or a 155 mm howitzer and its high-speed tractor, or two to three HUMVEESs, or an M113 APC, or up to five 463L pallets of freight. Hydraulically operated main loading door and ramp at rear of cabin. Paratroop door on each side aft of landing gear fairing. Two emergency exit doors standard.
Powerplant:
[B] 4,050 shp (2,978kW) Four Allison T56-A-7A turboprops; [H] Four 4,508 ehp (3,363 kW) Allison T-56-A-15 turboprops; [L-100-20] Four 4,508 ehp (3,362 kW) Allison 501-D22A turboprops, each driving a Hamilton Standard type 54H60 four-blade constant-speed fully-feathering reversible pitch propeller. Fuel in six integral tanks in wings, with total capacity of 26,344 liters (6,960 US gallons; 5,795 Imp gallons) and two optional underwing pylon tanks, each with capacity of 5,146 liters (1,360 US gallons; 1,132 Imp gallons). Total fuel capacity 36,636 liters (9,680 US gallons; 8,060 Imp gallons). Single pressure refueling point in starboard wheel well. Overwing gravity fueling. Oil capacity 182 liters (48 US gallons; 40 Imp gallons).
Systems:
Air-conditioning and pressurization system maximum pressure differential 0.52 bars (7.5 psi). Three independent hydraulic systems, utility and booster systems operating at a pressure of 201 bars (3,000 psi), rated at 65.1 liters/min (17.2 US gallons/min) for utility and booster systems, 30.3 liters/min (8.0 US gallons/min) for auxiliary system. Reservoirs are unpressurized. Auxiliary system has handpump for emergencies. Electrical system supplied by four 40kVA AC alternators, plus one 40kVA auxiliary alternator driven by APU in port main landing gear fairing. Four transformer-rectifiers for DC power.
Avionics and equipment:
Dual 628T-2A HF com, dual 618M-3A VHF com, AN/ARC-164 UHF com, AN/AIC PA system, AN/AIC-18 intercom, dual 621A-6A ATC transponders, DF-301E UHF Nav, dual 51RV-4B VHF nav, CMA 771 Omega nav, LTN-72 INS, dual DF-206 ADF, 51Z-4 marker beacon receiver, dual 860E-5 DME, AL-101 radio altimeter, RDR-IF weather radar, dual C-12 compass systems, Mk2 GPWS, AP-105V autopilot, and dual FD-109 flight directors.
Dimensions, External
Wing span:
40.41 m (132' 7")
Wing chord, at root:
4.88 m (16' 0")
Wing chord, at mean:
4.16 m (13' 8 ")
Wing aspect ratio:
10.09
Length, overall:
[B] 29.78 m (97' 9"); [H] 29.79 m (97' 9"); [L-100-20] 32.33 m (106' 1")
Fuselage max width:
Fuselage max depth:
Height, overall:
[B] 11.68 m (38' 4"); 11.66 m (38' 3")
Tailplane span:
16.05 m (52' 8")
Wheel track:
4.35 m (14' 3")
Wheel base:
[H] 9.77 m (32' 0 "); [L-100-20] 11.30 m (37' 1")
Propeller diameter:
4.11 m (13' 6")
Main cargo door, rear of cabin, height:
2.77 m (9' 1")
Main cargo door, rear of cabin, width:
3.05 m (10' 0")
Main cargo door, rear of cabin, height to sill:
1.03 m (3' 5")
Paratroop door, height:
1.83 m (6' 0")
Paratroop door, width:
0.91 m (3' 0")
Paratroop door, height to sill:
1.03 m (3' 5")
Emergency exit, height:
1.22 m (4' 0")
Emergency exit, width:
0.71 m (2' 4")
Crew door, height:
[L-100-20] 1.14 m (3' 9")
Crew door, width:
[L-100-20] 0.76 m (2' 6")
Crew door, height to sill:
1.04 m (3' 5")
Dimensions, Internal
Cabin, excl flight deck, length:
[L-100-20] 15.04 m (49' 4")
Cabin, excl flight deck, length, without ramp:
12.22 m (40' 1 ")
Cabin, excl flight deck, length, with ramp:
15.73 m (51' 8 ")
Cabin, excl flight deck, max width:
3.12 m (10' 3")
Cabin, excl flight deck, height:
[H] 2.81 m (9' 2 "); [L-100-20] 2.74 m (9' 0")
Cabin, excl flight deck, floor area, excl ramp:
[H] 39.5 m (425 ft); [L-100-20] 46.36 m (499 ft)
Cabin, excl flight deck, floor area, ramp:
[L-100-20] 9.57 m (103 ft)
Cabin, excl flight deck, volume incl ramp:
[H] 127.4 m (4,500 ft); [L-100-20] 150.28 m (5.307 ft)
Cabin volume:
[B] 121.7 m (4,300 ft)
Areas
Wings, gross:
162.12 m (1,745 ft)
Ailerons, total:
10.22 m (110 ft)
Trailing edge flaps, total:
31.77 m (342 ft)
Fin:
20.90 m (225 ft)
Rudder, incl tab:
6.97 m (75 ft)
Tailplane:
35.40 m (381 ft)
Elevator, incl tabs:
14.40 m (155 ft)
Weights and loadings
Operating weight, empty:
[H] 34,686 kg (76,469 lb); [L-100-20] 34,781 kg (76,680 lb)
Fuel, internal: 20,520 kg (45,240 lb)
Fuel, external:
8,020 kg (17,680 lb)
Max payload:
[H] 19,356 kg (42,673 lb); [L-100-20] 23,637 kg (52,110 lb)
Max ramp weight:
[L-100-20] 70,670 kg (155,800 lb)
Typical mission weights
Max T-O weight:
[B] 61,235 kg (135,000 lb); [H] 70,310 kg (155,000 lb); [L-100-20] 70,308 kg (155,000 lb)
Max landing weight:
[H] 70,310 kg (155,000 lb); [L-100-20] 61,235 kg (135,000 lb)
Max overload T-O/landing weight:
79,380 kg (175,000 lb)
Max zero fuel weight, 2.5 g:
[H] 54,040 kg (119,142 lb); [L-100-20] 54,420 kg (128,790 lb)
Max fuel weight:
[L-100-20] 29,380 kg (64,772 lb)
Max wing loading:
[H] 434.5 kg/m (89 lb/ft); [L-100-20] 433.5 kg/m (88.8 lb/ft)
Max power loading:
5.23 kg/kW (8.6 lb/ehp)
Performance (at max T-O weight, except where indicated)
Never exceed speed:
Max cruising speed:
602 kph (325 knts; 374 mph)
Max cruising speed at 6,100 m (20,000') at 54,430 kg (120,000 lb) AUW:
[L-100-20] 571 kph (308 knts; 355 mph)
Econ cruising speed:
556 kph (300 knts; 345 mph)
Stalling speed:
185 kph (100 knts; 115 mph)
Landing speed:
[L-100-20] 230 kph (124 knts; 143 mph)
Max rate of climb at S/L:
[H] 579 m/min (1,900 ft/min); [L-100-20] 518 m/min (1,700 ft/min)
Time to climb:
Service ceiling at 58,970 kg (130,000 lb) AUW:
10,060 m (33,000')
Service ceiling at 58,970 kg (130,000 lb) AUW, one engine out:
8,075 m (26,500')
Min ground turning radius:
[H] 19.2 m (63'); [L-100-20] 26.8 m (88')
Runway LCN at 70,310 kg (155,000 lb) AUW, asphalt:
37
Runway LCN at 70,310 kg (155,000 lb) AUW, concrete:
42
Runway LCN, asphalt:
[L-100-20] 37
Runway LCN, concrete:
[L-100-20] 42
T-O run:
1,091 m (3,580')
T-O run to 15 m (50'):
1,573 m (5,160')
FAR T-O field length:
[L-100-20] 1,905 m (6,250')
FAR landing field length, at max landing weight:
[L-100-20] 1,478 m (4,850')
Landing run from 15 m (50') at 45,360 kg (100,000 lb) AUW:
731 m (2,400')
Landing run from 15 m (50') at 58,967 kg (130,000 lb) AUW:
838 m (2,750')
Landing run at 58,967 kg (130,000 lb) AUW:
518 m (1,700')
Operational radius:
Range with max payload, with 5% reserves and allowance for 30 min at S/L:
3,791 km (2,046 nm; 2,356 mi)
Range with max fuel, incl external tanks, 7,081 kg (15,611 lb) payload, reserves of 5% initial fuel plus 30 min at S/L:
7,876 km (4,250 nm; 4,894 mi)
Range with max payload, 45 min reserves:
[B] 3,539 km (1,911 nm; 2,000 mi); [L-100-20] 2,472 km (1,334 nm; 1,536 mi)
Range with zero payload:
[L-100-20] 8,951 km (4,830 nm; 5,562 mi)
g Limits:
Endurance:
Weapon systems:
None
AFP weapon systems:
None
Program:
Three second-hand L-100-20 and one L-100-10 versions acquired in 1973. Three C-130H were acquired on March 1977 and were assigned to the 220th Heavy Airlift Wing (now the 220th Airlift Wing). The PAF has been using the C-130 to provide administrative airlift and military assistance, either international or domestic. Two C-130B were acquired on June 1995 and one C-130B acquired on September 2001 all under US EDA grant. One C-130B operational, one under repair as of May 2011

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Pilatus Britten-Norman Ltd. BN-2A 'Islander'
Type:
Twin-engined feederline transport
Origin:
United Kingdom
Similar aircraft:
Trislander, P.68 Victor, N.22 Nomad
Wings:
Cantilever high-wing monoplane. NACA 23012 constant wing section. No dihedral. Incidence 2. No sweepback. Conventional riveted two-spar torsion box structure in one piece, using L72 aluminum-clad aluminum alloys. Flared-up wingtips of Britten-Norman design. Wingtip fuel tanks optional. Slotted aileron and single-slotted flaps of metal construction. Flaps operated electrically, ailerons by pushrods and cables. Ground adjustable tab on starboard aileron. BTR-Goodrich pneumatic de-icing boots optional.
Fuselage:
Conventional riveted four-longeron semi-monocoque structure of pressed frames and stringers and metal skin, using L72 aluminum-clad aluminum alloys.
Tail unit: Cantilever two-spar structure, with pressed ribs and metal skin, using L72 aluminum-clad aluminum alloys. Fixed incidence tailplane and mass balanced elevator. Rudder and elevator are actuated by pushrods and cables. Trim tabs in rudder and elevator. Pneumatic de-icing of tailplane and fin optional.
Landing gear: Non-retractable tricycle-type, with twin wheels on each main unit and single steerable nosewheel. Cantilever main legs mounted aft of rear spar. All three legs fitted with oleo-pneumatic shock absorbers. All five wheels and tires size 16 x 7.7 supplied by Goodyear. Tire pressure: main 2.41 bars (35 psi); nose 2.00 bars (29 psi). Foot operated air-cooled Cleveland hydraulic brakes on main units. Parking brake. Wheel/ski gear available optionally.
Accommodation:
Up to ten persons, including pilot, on side by side seats and four bench seats. No aisle. Seat backs fold forward. Access to all seats via three forward opening doors, forward of wing and at rear of cabin on port side and forward of wing on starboard side. Baggage compartment at rear of cabin, with port side loading door in standard versions. Exit in emergency by removing door windows. Special executive layouts available. Can be operated as freighter, carrying more than a ton of cargo; this configuration the passenger seats can be stored in rear baggage bay. In ambulance role, up to three stretchers and two attendants can be accommodated. Other layouts possible, include photographic and geographical survey, parachutist transport or trainer (with accommodation for up to eight parachutist and a dispatcher), firefighting, public health spraying and crop spraying.
Powerplant:
Two Avco Lycoming flat-six engines each driving a Hartzell HC-C2YK-2B or 2C two-blade constant speed feathering metal propeller. Propeller synchronizers optional. Standard powerplant is the 260 hp (194 kW) O-540-E4C5 (designated BN-2B-26) horizontally-opposed piston engines, but the 300 hp (224 kW) IO-540-K1B5 (designated BN-2B-20) can be fitted at customer's option. Optional Rajay turbocharging installation on 260 hp (194 kW) engines, to improve high altitude performance. Integral fuel tank between spars in each wing, outboard of engine. Total fuel capacity (standard) 518 liters (137 US gallons; 114 Imp gallons). With optional wingtip fuel tanks, total capacity is increased to 855 liters (226 US gallons; 188 Imp gallons). Additional pylon mounted underwing auxiliary tanks, each 227 liters (60 US gallons; 50 Imp gallons) capacity, available optionally. Refueling point in upper surface of wing above each internal tank. Total oil capacity 22.75 liters (6 US gallons; 5 Imp gallons).
Systems:
Southwind cabin heater standard. 45,000 BTU Stewart Warner combustion unit, with circulating fan, provides hot air for distribution at floor level outlets and at windscreen demisting slots. Fresh air, boosted by propeller slipstream, is ducted to each seating position for on-ground ventilation. Electrical DC power, for instruments, lighting and radio, from two engine driven 24V 50A self-rectifying alternators and a controller to main busbar and circuit breaker assembly. Emergency busbar is supplied by a 24V 17Ah heavy duty lead-acid battery in the event of a twin alternator failure. Ground power receptacle provided. Optional electric de-icing of propellers and windscreen, and pneumatic de-icing of wing and tail unit leading-edges. Intercom system, including second headset, and passenger address system are standard. Oxygen system available optionally.
Avionics and equipment:
Standard items include blind-flying instrumentation, autopilot, dual flying controls and brake system. and a wide range of VHF and HF communications and navigation equipment. Some PNAG units are equipped with search radars and cameras for short-range Maritime surveillance.
Dimensions, External
Wing span:
14.94 m (49' 0")
Wing chord, constant:
2.03 m (6' 8")
Wing aspect ratio:
7.4
Length, overall:
10.86 m (35' 7 ")
Fuselage max width:
1.21 m (3' 11 ")
Fuselage max depth:
1.46 m (4' 9 ")
Height, overall:
4.18 m (13' 8 ")
Tailplane span:
4.67 m (15' 4")
Wheel track, c/l of shock absorbers:
3.61 m (11' 10")
Wheel base:
3.99 m (13' 1 ")
Propeller diameter:
1.98 m (6' 6")
Cabin door, height, front port:
1.10 m (3' 7 ")
Cabin door, width, top, front port:
0.64 m (2' 1 ")
Cabin door, height to sill, front port:
0.56 m (1' 11 ")
Cabin door, height, front starboard:
1.10 m (3' 7 ")
Cabin door, max width, front starboard:
0.86 m (2' 10")
Cabin door, height to sill, front starboard:
0.57 m (1' 10 ")
Cabin door, height, rear port:
1.09 m (3' 7")
Cabin door, width, top, rear port:
0.635 m (2' 1")
Cabin door, width, bottom, rear port:
1.19 m (3' 11")
Cabin door, height to sill, rear port:
0.52 m (1' 8 ")
Baggage door, height, rear port:
0.69 m (2' 3")
Dimensions, Internal
Passenger cabin, aft of pilot's seat, length:
3.05 m (10' 0")
Passenger cabin, aft of pilot's seat, max width:
1.09 m (3' 7")
Passenger cabin, aft of pilot's seat, height:
1.27 m (4' 2")
Passenger cabin, aft of pilot's seat, volume:
3.68 m (130 ft)
Baggage space aft of passenger cabin:
1.39 m (49 ft)
Freight capacity, aft of pilot's seat incl rear cabin baggage space:
4.70 m (166 ft)
Freight capacity, with four bench seats folded into rear cabin baggage space:
3.68 m (130 ft)
Areas
Wings, gross:
30.19 m (325 ft)
Ailerons, total:
2.38 m (25.6 ft)
Flaps, total:
3.62 m (39.0 ft)
Fin:
3.41 m (36.64 ft)
Rudder, incl tab:
1.60 m (17.2 ft)
Tailplane:
6.78 m (73.0 ft)
Elevator, incl tabs:
3.08 m (33.16 ft)
Weights and loadings
Weight, empty, equipped, without avionics:
1,925 kg (4,244 lb)
Max payload:
870 kg (1,918 lb)
Max fuel weight:
[standard] 354 kg (780 lb); [with optional tip tanks] 585 kg 1,290 lb)
Typical mission weights
Max T-O and landing weight:
2,993 kg (6,600 lb)
Max zero fuel weight (BCAR):
2,855 kg (6,300 lb)
Max wing loading:
99.1 kg/m (20.3 lb/ft)
Max floor loading, without cargo panels:
586 kg/m m (120 lb/ft)
Max power loading:
6.68 kg/kW (11.0 lb/hp)
Performance (at max T-O weight)
Never exceed speed:
339 kph (183 knts; 211 mph)
Max level speed at S/L:
280 kph (151 knts; 173 mph)
Max cruising speed, at 75% power, 2,135 m (7,000'):
264 kph (142 knts; 164 mph)
Cruising speed, at 67% power, 2,750 m (9,000'):
254 kph (137 knts; 158 mph)
Cruising speed, at 59% power, 3,660 m (12,000'):
245 kph (132 knts; 152 mph)
Stalling speed:
[flaps up] 92 kph (50 knts; 57 mph IAS); [flaps down] 74 kph (40 knts; 46 mph IAS)
Max rate of climb at S/L:
334 m/min (1,130 ft/min)
Rate of climb one engine out:
61 m/min (200 ft/min)
Absolute ceiling:
6,005 m (19,700')
Service ceiling:
5,240 m (17,200')
Service ceiling, one engine out:
1,980 m (6,500')
Min ground turning radius:
9.45 m (31' 0")
T-O run at S/L, zero wind, hard runway:
234 m (866')
T-O run at 1,525 m (5,000'):
372 m (1,221')
T-O run to 15 m (50') at S/L, zero wind, hard runway:
352 m (1,155')
T-O run to 15 m (50') at 1,525 m (5,000'):
496 m (1,628')
Landing run from 15 m (50'), at S/L, zero wind, hard runway:
299 m (980')
Landing run from 15 m (50'), at 1,525 m (5,000'):
357 m 1,170')
Landing run at S/L, zero wind, hard runway:
140 m (460')
Landing run at 1,525 m (5,000'):
171 m (560')
Operational radius:
Range at 75% power at 2,315 m (7,000'):
1,028 km (555 nm; 639 mi)
Range at 67% power at 2,750 m (9,000'):
1,070 km (577 nm; 665 mi)
Range at 59% power at 3,660 m (12,000'):
1,136 km (613 nm; 706 mi)
g Limits:
Endurance, one way:
6 hrs
Weapon systems:
(BN-2 'Defender') Four NATO standard underwing pylons for a variety of external stores, the inboard pair each carrying up to 317.5 kg (700 lb) and the outboard pair up to 204 kg (450 lb). Typical underwing loads include twin 7.62 mm machine-gun in pod racks, 114 or 227 kg (250 or 500 lb) GP bombs, Matra rocket packs, SURA rocket clusters, wire guided missiles, 5" reconnaissance flares, anti-personnel grenades, smoke bombs, marker bombs and 227 liters (60 US gallons; 50 Imp gallons) drop tanks.
AFP weapon systems:
Normally none, but the aircraft can perform offensive missions with installation of 4 underwing pylons with a capacity of 1,045 kg (2,300 lb) of munitions.
Program:
First acquired in 1975 by the then Naval Air Unit (now Naval Air Group). Thirty-one BN-2s were transferred between 1975-1982 including 2 units for police. Twenty-six units were assembled by PADC and some from the Belgian production line. One BN Islander was upgraded in 2004 by Hawker Pacific Ltd. of Australia under the BNI Aircraft Upgrade I. Two BN Islanders were refurbished in 2007 by Hawker Pacific Ltd. of Australia. under the BNI Aircraft Upgrade II. The projects involved the improvement of the aircraft's structure (airframe refurbishment), powerplant, communications and avionics, including the installation of surveillance equipment (Honeywell weather and sea search radar), making them IFR capable.

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Fokker F-27-200, F-27-500 'Friendship' and F-27MPA 'Maritime'
Type:
Twin-turboprop short-haul transport, Maritime reconnaissance aircraft
Origin:
Netherlands
Similar aircraft:
Grumman S-2 Tracker, Herald, Coke/Curl, F-50
Wings:
Cantilever high-wing monoplane.
Fuselage:
Tail unit:
Landing gear:
Retractable tricycle type.
Accommodation:
[Mk. 200] Crew of two on flight deck plus forty-four passengers; [Mk. 500] Crew of two on flight deck plus fifty-two passengers; [F-27MPA] Crew of up to six persons. All versions have pressurized cabins.
Powerplant:
[Mk. 200] Two Rolls Royce Dart Mk. 532 turboprops; [Mk. 500] Two 2,250 eshp (1,678 kW) Rolls Royce Dart Mk. 528-7R turboprops; [F-27MPA] Two 2,330 eshp (1,738 ekW) Rolls-Royce Dart Mk. 552 turboprops, all driving a four-blade propeller with spinner.
Systems:
Pneumatic system
Avionics and equipment:
[F-27MPA] Litton APS-504 S.R. under-fuselage search radar, nose-mounted Bendix weather radar, magnetic anomaly detector, sonar, sonobuoys and navigational systems; [Mk. 500] FAA and ICAO compliant avionics package.
Dimensions, External
Wing span:
29.0 m (95' 1")
Wing chord:
Wing aspect ratio:
Length, overall:
[Mk. 200] 23.5 m (77' 2"); [Mk. 500] 25.06 m (82' 2 "); [F-27MPA] 23.56 m (77' 3 ")
Fuselage max width:
Fuselage max depth:
Height, overall:
[F-27MPA] 8.70 m (28' 6 ")
Elevator span:
Wheel track:
Wheel base:
Dimensions, Internal
Cabin, length:
Cabin, max width:
Cabin, height:
Cabin volume:
Areas
Wings, gross:
70.0 m (753 ft)
Ailerons, total incl tabs:
Trailing edge flaps, total:
Fin:
Dorsal Fin:
Rudder, incl tab:
Tailplane:
Elevator, incl tab:
Weights and loadings
Weight, empty, equipped:
[F-27MPA] 13,725 kg (30,258 lb)
Fuel:
Typical mission weights
Max T-O weight:
19,950 kg (42,000 lb); [F-27MPA] 22,680 kg (50,000 lb)
Max wing loading:
Max power loading:
Performance
Max speed:
[F-27MPA] 463 kph (287 mph)
Max cruising speed:
483 kph (300 mph); [Mk. 500] 522 kph (325 mph)
Stalling speed:
Max rate of climb at S/L:
Time to climb:
Service ceiling:
9,900 m (32,600')
T-O run at S/L:
Landing run at S/L:
Operational radius:
Range:
1,468 km (912 mi); [Mk. 500] 1,741 km (1,082 mi); [F-27MPA] 5,000 km (3,107 mi)
g Limits:
Endurance:
[F-27MPA] 12 hrs
Weapon systems:
[Mk. 200 & 500] None; [F-27MPA] Provision for up to 3,930 kg (8,664 lb) of disposable stores carried on two fuselage pylons and six underwing hardpoints; typical weapons include up to four AS torpedoes; or AM.39 Exocet, Sea Eagle, Harpoon, Maverick or Sea Skua anti-ship missiles.
AFP weapon systems:
None
Program:
One F-27-500 with uprated engine, FAA/ICAO compliant avionics, greater payload and passenger capacity was acquired in October 2006 from Aeroglobe Ltd. Inc.under negotiated procurement for Php 91.2 million.

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Fokker F-28-3000 'Fellowship'
Type:
Twin-turbofan, short/medium-haul transport
Origin:
Netherlands
Similar aircraft:
F-100
Wings:
Cantilever low-wing monoplane.
Fuselage:
Tail unit:
Cantilever light alloy T structure.
Landing gear:
Retractable tricycle type.
Accommodation:
Crew of two on flight deck plus up to twenty-five passengers.
Powerplant:
Two Rolls Royce RB183 Spey Mk. 555-15H turbofan engines mounted on the rear fuselage.
Systems:
Avionics and equipment:
Cabin pressurized.
Dimensions, External
Wing span:
25.07 m (82' 3")
Wing chord:
Wing aspect ratio:
Length, overall:
27.40 m (89' 11")
Fuselage max width:
Fuselage max depth:
Height, overall:
Elevator span:
Wheel track:
Wheel base:
Dimensions, Internal
Cabin, length:
Cabin, max width:
Cabin, height:
Cabin volume:
Areas
Wings, gross:
78.97 m (850 ft)
Ailerons, total incl tabs:
Trailing edge flaps, total:
Fin:
Dorsal Fin:
Rudder, incl tab:
Tailplane:
Elevator, incl tab:
Weights and loadings
Manufacturer's basic empty weight:
Weight, empty, equipped:
Fuel:
Typical mission weights
Max T-O weight:
29,000 kg (65,000 lb)
Max wing loading:
Max power loading:
Performance
Never exceed speed:
Max cruising speed:
843 kph (523 mph)
Stalling speed:
Max rate of climb at S/L:
Time to climb:
Service ceiling:
10,700 m (35,000')
T-O run at S/L:
Landing run at S/L:
Operational radius:
Range:
1,900 km (1,180 mi)
g Limits:
Endurance:
4 hrs, 30 minutes
Weapon systems:
None
AFP weapon systems:
None
Program:
First acquired on 1980 as a presidential aircraft by the Central Bank under the 700th SMW. Underwent D-check and IRAN in 2009 by Indopelita Aircraft Services in Jakarta, Indonesia. The PAF's lone F-28, callsigh 'Kalayaan 1' is operated by the 250th Presidential Airlift Wing and is the primary aircraft of the President of the Philippines.


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Government Aircraft Factories N.22B 'Nomad/ Missionmaster'
Type:
Multi-role STOL aircraft
Origin:
Australia
Similar aircraft:
BN-2 Islander
Wings:
Cantilever high-wing monoplane, braced with struts with double slotted flaps and drooping ailerons. Wing section NACA 23018 (modified).
Fuselage:
All metal, semi-monocoque structure.
Tail unit:
Landing gear:
Retractable tricycle type with twin-wheel main units and a single-wheel nose unit.
Accommodation:
Crew of two and up to 17 passengers.
Powerplant:
Two 420 shp (313 kW) Allison 250-B17C turboprops
Systems:
Avionics and equipment:
Optional dual controls.
Dimensions, External
Wing span:
16.52 m (54' 2 ")
Wing chord:
Wing aspect ratio:
Length, overall:
12.56 m (41' 2 ")
Fuselage max width:
Fuselage max depth:
Height, overall:
5.52 m (18' 1 ")
Elevator span:
Wheel track:
Wheel base:
Dimensions, Internal
Cabin, length:
Cabin, max width:
Cabin, height:
Cabin volume:
Areas
Wings, gross:
30.10 m (324 ft)
Ailerons, total incl tabs:
Trailing edge flaps, total:
Fin:
Dorsal Fin:
Rudder, incl tab:
Tailplane:
Elevator, incl tab:
Weights and loadings
Weight, empty:
2,150 kg (4,740 lb)
Fuel:
Typical mission weights
Max T-O weight:
3,855 kg (8,500 lb)
Max wing loading:
Max power loading:
Performance
Max speed:
311 kph (168 knts; 193 mph)
Max cruising speed:
269 kph (167 mph)
Stalling speed, power off, flaps down:
88 kph (47 knts; 55 mph)
Rate of climb:
7.4 m/sec (1,460 fps)
Time to climb:
Service ceiling:
6,400 m (21,000')
T-O run at S/L:
Landing run at S/L:
Operational radius:
Max range:
1,352 km (730 nm; 840 mi)
g Limits:
Endurance:
Weapon systems:
Four underwing hardpoints each rated at 227 kg (500 lb) can carry gun pods, rocket launchers, and various air munitions.
AFP weapon systems:
None
Program:
Twelve N-22B Nomad initially transferred between 1975-1976. Four additional N-22Bs acquired in 1990 under a $5.3 m deal.

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Cessna model R172E 'Skyhawk' USAF designation T-41D 'Mescalero'
Type:
Primary Pilot Trainer
Origin:
USA
Similar aircraft:
Wings:
Cantilever high-wing monoplane.
Fuselage:
Tail unit:
Landing gear:
Non-retractable tricycle type.
Accommodation:
One pilot and one student pilot. Baggage capacity 90.5 kg (200 lb).
Powerplant:
One 210 hp (156.5 kW) Continental IO-360-D, flat six-cylinder piston engine driving a McCauley 2A34-C209/78CCA-2 two-blade constant-speed propeller. Two fuel tanks in wings with total capacity of 197 liters (52 US gallons), of which 174 liters (46 US gallons) are useable. Provision for long-range tanks, giving total useable capacity of 238 liters (63 US gallons). Refueling points above wing. Oil capacity 9.5 liters (2.5 US gallons).
Systems:
Avionics and equipment:
28V electrical system.
Dimensions, External
Wing span:
10.92 m (35' 10")
Wing chord at root:
1.63 m (5' 4")
Wing aspect ratio:
7.52
Length, overall:
8.21 m (26' 11")
Fuselage max width:
Fuselage max depth:
Height, overall:
2.68 m (8' 9 ")
Elevator span:
Tailplane span:
3.45 m (11' 4")
Wheel track:
2.53 m (8' 3 ")
Wheel base:
1.63 m (5' 4")
Propeller diameter:
1.93 m (6' 4")
Passenger door height (each):
1.01 m (3' 3 ")
Passenger door width (each):
0.89 m (2' 11")
Dimensions, Internal
Cabin, length:
Cabin, max width:
Cabin, height:
Cabin volume:
Areas
Wings, gross:
16.17 m (174 ft)
Ailerons, total:
1.70 m (18.3 ft)
Trailing edge flaps, total:
Fin:
1.04 m (11.24 ft)
Rudder:
0.69 m (7.43 ft)
Tailplane:
2.0 m (21.56 ft)
Elevator, incl tab:
1.35 m (14.53 ft)
Weights and loadings
Weight, empty, equipped:
637 kg (1,405 lb)
Fuel:
Typical mission weights
Max T-O weight and landing:
1,156 kg (2,550 lb)
Max wing loading:
71.3 kg/m (14.6 lb/ft)
Max power loading:
7.39 kg/kW (12.1 lb/hp)
Performance (at max T-O weight)
Never exceed speed:
293 kph (158 knts; 182 mph)
Max speed at S/L:
246 kph (133 knts; 153 mph)
Max cruising speed at 1,675 m (5,500'):
233 kph (126 knts; 145 mph)
Econ cruising speed at 3,050 m (10,000'):
169 kph (91 knts; 105 mph)
Stalling speed, flaps up:
103 kph (55.6 knts; 64 mph)
Stalling speed, flaps down:
85 kph (46 knts; 53 mph)
Max rate of climb at S/L:
268 m/min (880 ft/min)
Time to climb:
Service ceiling:
5,180 m (17,000')
T-O run:
226 m (740')
T-O run to 15 m (50'):
375 m (1,230')
Landing run from 15 m (50'):
387 m (1,270')
Landing run:
189 m (620')
Operational radius:
Range with max fuel at econ cruising speed at 3,050 m (10,000'):
1,625 km (877 nm; 1,010 mi)
g Limits:
Endurance:
Weapon systems:
None
AFP weapon systems:
None
Program:
First twenty units acquired in 1968 from US. Five units acquired in 1998 from US. Sixteen units acquired in 2009 from South Korea as military aid, 4 ex-SK T-41Ds grounded after metal filings on the oil were detected. Used as basic trainers by the PAF Flying School

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Cessna 210 'Centurion'
Type:
Six-seat high performance, general aviation aircraft
Origin:
USA
Similar aircraft:
Cessna 206, Piper Saratoga, Piper Malibu, Beechcraft Bonanza
Wings:
Cantilever high-wing strutless monoplane.
Fuselage:
Tail unit:
Landing gear:
Non-retractable tricycle type.
Accommodation:
One pilot and up to five passengers.
Powerplant:
One 285 bhp Continental TSIO-520-R engine driving a three-blade propeller with spinner.
Systems:
Avionics and equipment:
Dimensions, External
Wing span:
12.12 m (39' 9")
Wing chord:
Wing aspect ratio:
Length, overall:
8.59 m (28' 2")
Fuselage max width:
Fuselage max depth:
Height, overall:
2.95 m (9' 8")
Elevator span:
Wheel track:
Wheel base:
Dimensions, Internal
Cabin, length:
Cabin, max width:
Cabin, height:
Cabin volume:
Areas
Wings, gross:
Ailerons, total incl tabs:
Trailing edge flaps, total:
Fin:
Dorsal Fin:
Rudder, incl tab:
Tailplane:
Elevator, incl tab:
Weights and loadings
Weight, empty:
1,090.91 kg (2,400 lb)
Fuel:
Typical mission weights
Max T-O weight:
1,818.18 kg (4,000 lb)
Max wing loading:
(22.9 lb/ft)
Max power loading:
Performance
Max speed:
(199 knts)
Max cruising speed:
Stalling speed:
Rate of climb:
284 m/min (930 ft/min)
Time to climb:
Service ceiling:
8,232 m (27,000')
T-O run at S/L:
Landing run at S/L:
Operational radius:
Range, 75% power at 7,317 m (24,000'):
(1,000 nm)
g Limits:
Endurance:
Weapon systems:
None
AFP weapon systems:
None
Program:
Three Cessna 210s transferred in 1982.

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General Atomics Aeronautical Systems Inc. MQ-1 'Predator-A'
Type: Unmanned Aerial Vehicle
Origin: USA
Similar aircraft:
Wings: Cantilever, low-wing monoplane
Fuselage:
Tail unit:
Landing gear: Retractable, tricycle type.
Crew: Pilot + Sensor Operator (Not onboard).
Powerplant: One 115 hp (86kW) Rotax 914F turbocharged four cylinder engine, 100 US gal capacity
Systems:
Avionics and equipment: The Predator air vehicle and sensors are controlled from the ground station via a C-band line-of-sight data link or a Ku-band satellite data link for beyond-line-of-sight operations. During flight operations the crew in the ground control station is a pilot and two sensor operators. The aircraft is equipped with the AN/AAS-52 Multi-spectral Targeting System, a color nose camera (generally used by the pilot for flight control), a variable aperture day-TV camera, and a variable aperture infrared camera (for low light/night). Previously, Predators were equipped with a AN/ZPQ-1 Synthetic Aperture Radar for looking through smoke, clouds or haze, but lack of use validated its removal to reduce weight and conserve fuel. The cameras produce full motion video and the synthetic aperture radar produced still frame radar images. There is sufficient bandwidth on the datalink for two video sources to be used at one time, but only one video source from the sensor ball can be used at any time due to design limitations. Either the daylight variable aperture or the infrared electro-optical sensor may be operated simultaneously with the synthetic aperture radar, if equipped.
Dimensions, External
Wing span: 14.8 m (48.7')
Wing chord at root:
Wing aspect ratio:
Length, overall: 8.22 m (27')
Height, overall: 2.1 m (6.9')
Elevator span:
Tailplane span:
Wheel track:
Wheel base:
Areas
Wings, gross: 11.5 m (123.3 ft)
Ailerons, total:
Trailing edge flaps, total:
Fin:
Rudder:
Tailplane:
Elevator, incl tab:
Weights and loadings
Weight, empty, equipped: 512 kg (1,130 lb)
Fuel: 301.64 kg (665 lb)
Typical mission weights
Max T-O weight and landing: 1,020 kg (2,250 lb)
Max wing loading:
Max power loading:
Performance (at max T-O weight)
Never exceed speed:
Max speed: 217.26 kph (117.31 knts; 135 mph)
Max cruising speed: 130 kph (70 knts; 80.55 mph)
Stalling speed: 100 kph (54 knts; 62 mph)
Max rate of climb at S/L:
Time to climb:
Service ceiling: 7,620 m (25,000')
T-O run:
Landing run:
Operational radius:
Range: 730.64 km (454 mi; 394.52 nm)
g Limits:
Endurance: 24 hours
Weapon systems: 2 x AGM-114 Hellfire missiles; or 4 x AIM-92 Stinger; or 6 x Griffin ASMs on two hardpoints, 204 kg (450 lb) payload.
AFP weapon systems: None
Program: Two civil-registered unarmed MQ-1s are operated by the Office of the National Security Advisor in the Philippines since 2006.
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