Lockheed P-3C Orion (Update II).
On November 16, 2004 the US Administration notified Congress that Pakistan was to receive a $1.2 billion arms package from the United States, including the supply of eight Lockheed P-3 Orions which are currently in the AMARC inventory.
Once delivered these aircraft will be used to bolster Pakistan's search surveillance and control capability in support of maritime interdiction operations. They will also provide additional capability in the support of US Enduring Freedom operations by improving the ability to restrict littoral movement of terrorists along its southern border.
If all the P-3 Orion options are taken up they will form the bulk of the package with an estimated value of $970 million.
After flight preparation work has been completed by the AMARC technicians the aircraft will be flown to the Lockheed Martin Company at Greenville, SC. Lockheed will then carry out the final upgrades before they are officially handed over to the Pakistan Navy.
The eight P-3 Orions selected for Pakistan are detailed below :-
AN2P0165 159511 5629 13-JUL-95 VP-92, NAS Brunswick, ME.
AN2P0166 159890 5641 10-AUG-95 VP-69, NAS Whidbey Island, WA.
AN2P0171 159883 5634 21-SEP-95 VP-69, NAS Whidbey Island, WA.
AN2P0174 159505 5623 30-MAY-96 VP-69, NAS Whidbey Island, WA.
AN2P0175 159510 5628 30-MAY-96 VP-69, NAS Whidbey Island, WA.
AN2P0176 159509 5627 06-AUG-96 VP-65, NAS Point Mugu, CA.
AN2P0178 159508 5626 17-SEP-96 VP-94, NAS New Orleans, LA.
AN2P0184 160289 5652 16-DEC-97 VP-30, NAS Jacksonville, FL.
AMARC have previously been involved in the supply of P-3 Orions to Pakistan when they reactivated three embargoed P-3C Orions in 1996 and 1997 after the aircraft were withheld due to the Pressler Ammendment imposed in 1990. This amendment prohibited any United States Assistance to Pakistan if the President failed to certify Pakistan was not in possession of a nuclear explosive device.
Before their delivery to AMARC for storage the aircraft had been used to train Pakistan Navy aircrews with VP-30 at NAS Jacksonville, FL.
As part of the deal, the P-3Cs would be upgraded to the Update III Anti-Surface Warfare Improvement Program (AIP) and Block Modification Upgrade Program (BMUP) standards. The P-3C Update III AIP provides the following: the capability of carrying the Maverick infrared-guided missile; the AN/AAS-36A infrared detection set; the AN/AVX-1 electro-optical sensor system; the AN/APS-137B(V)5 synthetic-aperture radar (SAR), which also has an inverse-SAR mode; the EP-2060 pulse analyzer; color high-resolution displays; the Over-the-Horizon Airborne Sensor Information System (OASIS) III, and the OZ-72(V) Multimission Advanced Tactical Terminal (MATT) system. For self-protection, the AIP standard includes the AN/AAR-47 missile-warning system; the AN/ALE-47 countermeasures dispenser; and the AN/ALR-66C(V)3 electronic-support-measures system. The BMUP modification, meanwhile, consists of a new data-processing subsystem based on the CP-2451/ASQ-227 digital computer and a new acoustic subsystem based on the USQ-78B display and control unit, plus the capability to carry the Standoff Land Attack Missile - Expanded Response (SLAM-ER). In addition, Pakistan has also expressed the intention of adding modifications to the aircraft to allow carrying the French Exocet and Chinese C-802 anti-ship missiles and the French-Italian A244 torpedo.
ACTIVE : 10
OPERATIONAL SPEED : 410 kt (760 km/h).
SERVICE CEILING : 28,300 ft (8,625 m).
RANGE A/C : 4,000 n miles (7,410 km).
ROLE/WEAPON SYSTEMS : Order completed in 1991 but held up by the Pressler amendment, until delivery in December 1996. Sensors: APS-115 search radar; up to 100 sonobuoys; ASQ 81 MAD; ESM. Weapons: four Type 244S torpedoes or Mk 11 depth charges for ASW; four Harpoon for ASV.Update II: (Model 285A) Applied to 45 aircraft built from August 1977; added InfraRed Detection System (IRDS) and Sonobuoy Reference System (SRS); Harpoon missile system incorporated from August 1977. Total of 36 USN P-3Cs received interim Update II.5 of 1981 including more reliable navigation and communication systems; IACS submarine communications link; MAD compensation group adaptor; standardised wing pylons; and improved fuel tank vents. Also added AN/ASH-33 digital magnetic tape system ILO of RD-319 tape system.
DESIGN FEATURES: Pressurised cabin. Wing section NACA 0014 (modified) at root, NACA 0012 (modified) at tip; dihedral 6°; incidence 3° at root, 0° 30' at tip.
FLYING CONTROLS: Hydraulically boosted ailerons, elevators and rudders; fixed tailplane; Lockheed-Fowler trailing-edge flaps.
STRUCTURE: Conventional aluminium alloy with fail-safe box beam wing.
LANDING GEAR: Hydraulically retractable tricycle type, with twin wheels on each unit. All units retract forward, mainwheels into inner engine nacelles. Oleo-pneumatic shock-absorbers. Mainwheels have size 40-14 Type VII 26 ply tubeless tyres, pressure 7.58 to 12.41 bars (110 to 180 lb/sq in) at 36,287 kg (80,000 lb) T-O weight, 12.41 bars (180 lb/sq in) at 57,606 kg (127,000 lb) T-O weight, 13.10 bars (190 lb/sq in) at 61,235 kg (135,000 lb) maximum normal T-O weight. Nosewheels have size 28-7.7 Type VII tubeless tyres, pressure 10.34 bars (150 lb/sq in). Hydraulic brakes. No anti-skid units.
POWER PLANT: Four 3,661 kW (4,910 ehp) Allison T56-A-14 turboprops, each driving a Hamilton Standard 54H60-77 four-blade constant-speed propeller. Fuel in one tank in fuselage and four wing integral tanks, with total usable capacity of 34,826 litres (9,200 US gallons; 7,660 Imp gallons). Four overwing gravity fuelling points and central pressure refuelling point. Oil capacity (minimum usable) 111 litres (29.4 US gallons; 24.5 Imp gallons) in four tanks.
ACCOMMODATION: (P-3C) Normal 10-man crew: pilot, co-pilot, and flight engineer on flight deck; tactical co-ordinator, nav/com operator, two acoustic sensor operators, MAD operator, ordnance man and flight technician; up to 13 additional relief crew or passengers. Flight deck has wide-vision windows and circular windows for observers are provided fore and aft in the main cabin, each bulged to give 180° view. Main cabin is fitted out as a five-man tactical compartment (containing advanced electronic, magnetic and sonic detection equipment), an all-electric galley and large crew and rest area.
SYSTEMS: Air conditioning and pressurisation system supplied by two engine-driven compressors. Pressure differential 0.37 bar (5.4 lb/sq in). Hydraulic system, pressure 207 bars (3,000 lb/sq in), for flaps, control surface boosters, landing gear actuation, brakes and bomb bay doors. Three hydraulic pumps, each rated at 30.3 litres (8.0 US gallons; 6.7 Imp gallons)/min at 0 to 152 bars (0 to 2,200 lb/sq in), 22.7 litres (6.0 US gallons; 5.0 Imp gallons)/min at 205 bars (2,975 lb/sq in). Class one non-separated air/oil reservoir. Type B pressurised. Electrical system utilises three 60 kVA generators for 120/208 V 400 Hz AC supply. 24 V DC supply. Integral APU with 60 kVA generator for ground air conditioning, electrical supply and engine starting. Anti-icing by bleed air on wing and electrical heating on tailplane and fin. Electrically de-iced propeller spinners.
AVIONICS: The AN/ASQ-114 general purpose digital computer is the heart of the P-3C system. Together with the AN/AYA-8 data processing equipment and computer-controlled display systems, it permits rapid analysis and utilisation of electronic, magnetic and sonic data. Nav/com system comprises two LTN-72 inertial navigation systems; AN/APN-227 Doppler; AN/ARN-81 Loran A and C; AN/ARN-118 Tacan; two VIR-31A VOR/LOC/GS/MB receivers; AN/ARN-83 LF-ADF; AN/ARA-50 UHF direction-finder, AN/AJN-15 flight director indicator for tactical directions; HSI for long-range flight directions; glide slope indicator; on-top position indicator; two AN/ARC-161 HF transceivers; two AN/ARC-143 UHF transceivers; AN/ARC-101 VHF receiver/transmitter; AN/AGC-6 teletype and high-speed printer; HF and UHF secure communication units; AN/ACQ-5 datalink communication set and AN/AIC-22 interphone set; AN/APX-72 IFF transponder and AN/APX-76 SIF interrogator. Electronic computer-controlled display equipment includes AN/ASA-70 tactical display, AN/ASA-66 pilot's display, AN/ASA-70 radar display and two auxiliary readout (computer stored data) displays.
ASW equipment includes AN/ARR-72 sonar receivers, replaced in Update III by AN/ARR-78; two AN/AQA-7(V)8 DIFAR (directional acoustic frequency analysis and recording) sonobuoy indicator sets, replaced in Update III by AN/UYS-1 Proteus; hyperbolic fix unit; acoustic source signal generator; time code generator and AN/AQH-4(V) sonar tape recorder; AN/ASQ-81 magnetic anomaly detector; AN/ASA-64 submarine anomaly detector; AN/ASA-65 magnetic compensator; AN/ALQ-78 electronic countermeasures set; AN/APS-115 radar set (360° coverage); AN/ASA-69 radar scan converter; undernose AN/AAS-36 IRDS; KA-74 forward computer assisted camera (deleted with IRDS installation); KB-18A automatic strike assessment camera with horizon-to-horizon coverage; RO-308 bathythermograph recorder.
Additional items include AN/APN-194 radar altimeter; two AN/APQ-107 radar altimeter warning systems; A/A24G-9 true airspeed computer; AN/ASW-31 automatic flight control system. P-3Cs delivered from 1975 have the avionics/electronics package updated by addition of an extra 393 kbit memory drum and fourth logic unit. Omega navigation, new magnetic tape transport, and an AN/ASA-66 tactical display for the sonar operators. To accommodate the new systems a new operational software computer programme was written in CMS-2 language. GEC-Marconi AQS-901 acoustic signal processing and display system in RAAF P-3Ws. AN/ALR-66(V)5 passive radar detection system (ESM), to be housed in wingtip pods, is under development by Litton, and will also provide targeting data for the aircraft's Harpoon missiles. AN/ALR-66(V)3 installed in Japanese and Norwegian P-3Cs and as retrofit in P-3P and CP-140. Wing span increased by some 0.81 m (2 ft 8 in) to accommodate ESM antennae and receivers. Loral AN/ALQ-157 IR jammers retrofitted each side of rear fuselage on USN P-3Cs. AN/ALR-66(V)5 replaces Loral AN/ALQ-78A on Korean P-3C.
EQUIPMENT: Searchlight replaces one wing pylon, starboard. Search stores, such as sonobuoys and sound signals, are launched from inside cabin area in the P-3A/B. In the P-3C sonobuoys are loaded and launched externally and internally. Sonobuoys are ejected from P-3C aircraft with explosive Cartridge Actuating Devices (CAD), eliminating the need for a pneumatic system. Australian P-3Ws use SSQ-801 Barra sonobuoys.
ARMAMENT: Bomb bay 2.03 m wide, 0.88 m deep and 3.91 m long (80 x 34.5 x 154 in), forward of wing, and 10 underwing pylons. Stores can include (weapons bay/underwing, maximum) Mk 46 torpedo 8/0; Mk 50 torpedo 6/0; Mk 54 depth bomb 8/10; B57 nuclear depth charge 3/0; Mk 82 560 lb bomb 8/10; Mk 83 980 lb bomb 3/8; Mk 36 destructor 8/10; Mk 40 destructor 3/8; LAU-68A pod (seven 2.75 in rockets), or LAU-69AS (19 2.75 in rockets), or LAU-10A/C (four 5 in rockets), or SUU-44A (eight flares) 0/4; Mk 52 mine 3/8; Mk 55 or Mk 56 mine 1/6; Mk 60 torpedo 0/6; AGM-85 Harpoon anti-ship missile 0/8. Two AIM-9L Sidewinder AAMs underwing for self-defence. Maximum total weapon load includes six 2,000 lb mines under wings and a 3,290 kg (7,252 lb) internal load made up of two Mk 101 depth bombs, four Mk 44 torpedoes, pyrotechnic pistol and 12 signals, 87 sonobuoys, 100 Mk 50 underwater sound signals (P-3A/B), 18 Mk 3A marine markers (P-3A/B), 42 Mk 7 marine markers, two B. T. buoys, and two Mk 5 parachute flares. Harpoon missiles are standard fit on a proportion of US Navy P-3Cs. US Navy is conducting analysis of arming its P-3C Orions with the Joint Air-to-Surface Standoff Missile (JASSM). The US Navy has fitted the AGM-65 Maverick air-to-surface missile and carried out successful launch of AGM-84 Standoff Land Attack Missile (SLAM).
DIMENSIONS, EXTERNAL:
Wing span.......................................30.37 m (99 ft 8 in) Wing chord: at root.............................5.77 m (18 ft 11 in) at tip..........................................2.31 m (7 ft 7 in) Wing aspect ratio................................................7.5 Length overall................................35.61 m (116 ft 10 in) Height overall.............................10.27 m (33 ft 8{1/2} in) Fuselage diameter................................3.45 m (11 ft 4 in) Tailplane span.................................13.06 m (42 ft 10 in) Wheel track (c/l shock-absorbers)................9.50 m (31 ft 2 in) Wheelbase........................................9.07 m (29 ft 9 in) Propeller diameter...............................4.11 m (13 ft 6 in) Cabin door: Height................................1.83 m (6 ft 0 in) Width...........................................0.69 m (2 ft 3 in)
DIMENSIONS, INTERNAL:
Cabin, excl flight deck and electrical load centre:
Length........................................21.06 m (69 ft 1 in) Max width.....................................3.30 m (10 ft 10 in) Max height......................................2.29 m (7 ft 6 in) Floor area................................61.13 m{2} (658.0 sq ft) Volume....................................120.6 m{3} (4,260 cu ft)
AREAS:
Wings, gross.............................120.77 m{2} (1,300.0 sq ft) Ailerons (total)..............................8.36 m{2} (90.0 sq ft) Trailing-edge flaps (total).................19.32 m{2} (208.0 sq ft) Fin, incl dorsal fin........................10.78 m{2} (116.0 sq ft) Rudder, incl tab..............................5.57 m{2} (60.0 sq ft) Tailplane...................................22.39 m{2} (241.0 sq ft) Elevators, incl tabs..........................7.52 m{2} (81.0 sq ft)
WEIGHTS AND LOADINGS (P-3B/C): {st} Weight empty...................................27,890 kg (61,491 lb) Max fuel weight................................28,350 kg (62,500 lb) Max expendable load.............................9,071 kg (20,000 lb) Max normal T-O weight.........................61,235 kg (135,000 lb) Max permissible weight........................64,410 kg (142,000 lb) Design zero-fuel weight........................35,017 kg (77,200 lb) Max landing weight............................47,119 kg (103,880 lb) Max wing loading......................507.0 kg/m{2} (103.8 lb/sq ft) Max power loading...........................4.18 kg/kW (6.87 lb/ehp)
PERFORMANCE (P-3B/C, at max T-O weight, except where indicated otherwise):
Max level speed at 4,575 m (15,000 ft) at AUW of 47,625 kg (105,000 lb) .............................................411 kt (761 km/h; 473 mph) Econ crusing speed at 7,620 m (25,000 ft) at AUW of 49,895 kg (110,000 lb) .............................................328 kt (608 km/h; 378 mph) Patrol speed at 457 m (1,500 ft) at AUW of 49,895 kg (110,000 lb) .............................................206 kt (381 km/h; 237 mph) Stalling speed: flaps up.....................133 kt (248 km/h; 154 mph) flaps down.................................112 kt (208 km/h; 129 mph) Rate of climb at 457 m (1,500 ft)...............594 m (1,950 ft)/min Time to 7,620 m (25,000 ft)...................................30 min Service ceiling..................................8,625 m (28,300 ft) Service ceiling, OEI.............................5,790 m (19,000 ft) T-O run...........................................1,290 m (4,240 ft) T-O to 15 m (50 ft)...............................1,673 m (5,490 ft) Landing from 15 m (50 ft) at design landing weight..845 m (2,770 ft) Mission radius (3 h on station at 457 m; 1,500 ft).....1,346 n miles ....(2,494 km; 1,550 miles) Max mission radius (no time on station) at 61,235 kg (135,000 lb) ...............................2,070 n miles (3,835 km; 2,383 miles) Ferry range....................4,830 n miles (8,950 km; 5,562 miles) Max endurance at 4,575 m (15,000 ft): two engines............................................17 h 12 min four engines...........................................12 h 20 min
Fokker F27-200.
ACTIVE : 5
OPERATIONAL SPEED : 250 kt (463 km/h).
SERVICE CEILING : 29,500 ft (8,990 m).
RANGE A/C : 2,700 n miles (5,000 km).
ROLE/WEAPON SYSTEMS : Acquired in 1994-96 for maritime surveillance. Sensors: APS 504(V)2 radar, Thomson-CSF DR 3000A ESM.
Breguet Atlantic 1
ACTIVE : 4 OPERATIONAL SPEED : 355 kt (658 km/h). SERVICE CEILING : 32,800 ft (10,000 m). RANGE A/C : 4,855 n miles (8,995 km). ROLE/WEAPON SYSTEMS : Long-range MR/ASW cover for Arabian Sea; ex-French and Dutch stock. Upgraded in 1992-93. Three more acquired in 1994 for spares. Sensors: Thomson-CSF Ocean Master radar, Thomson-CSF DR 3000A ESM, MAD, sonobuoys, Sadang 1C sonobuoy signal processor. Weapons: ASW; nine Mk 46 or244/S torpedoes, Mk 11 depth bombs, mines. ASV; two AS 12 or AM 39 Exocet missiles.
PROGRAMME: On 31 July 1974, Dassault-Breguet delivered the 18th Breguet 1150 Atlantic maritime patrol aircraft ordered by the Italian government. This completed the production programme for 87 operational Atlantics of the basic type, made up of 40 aircraft for the French Navy, three of which were passed on to Pakistan. Manufacture was shared by companies in France, Germany, Italy and Pakistan, with additional airframe components supplied by the Belgian ABAP group and some equipment from the USA and UK.
UPGRADES: Alenia: See separate entry in Italy section. Dornier: See separate entry in Germany section. Germany: In late 1996 the German government announced that it was developing a requirement for a life-extension programme for the German Navy's fleet of 18 Atlantic 1 maritime patrol aircraft. The programme will add 12,000 hours to the airframe life to keep the aircraft in service until 2010. The requirement also includes retrofitting the following equipment: a Forward-Looking InfraRed (FLIR) sensor as well as improved navigation, communications (GMDSS) and Electronic Support Measures (ESM) systems. All equipment is to be Commercial Off The Shelf (COTS).
Thomson-CSF: Awarded contract to upgrade Pakistan Navy Atlantic 1 aircraft with the AMASCOS mission system (see separate entry in France section).
OPERATORS: Versions of the Atlantic are in service with the armed forces of the following countries: Germany (19); Italy (18) and Pakistan (4). The following description applies to the basic version.
DESIGN FEATURES: Cantilever mid-wing monoplane. Wing section NACA 64 series. Dihedral on outer wings only. Fixed-incidence tailplane.
FLYING CONTROLS: Conventional all-metal ailerons actuated by SAMM twin-cylinder jacks. All-metal slotted flaps, with bonded light-alloy honeycomb filling, over 75 per cent of span. Three hinged spoilers on upper surface of each outer wing, forward of flaps. Metal airbrake above and below each wing. No trim tabs. Tail unit control surfaces operated through SAMM twin-cylinder jacks. No trim tabs.
STRUCTURE: All-metal three-spar fail-safe structure, with bonded light-alloy honeycomb skin panels on torsion box and on main landing gear doors. The fuselage is an all-metal `double-bubble' fail-safe structure, with bonded honeycomb sandwich skin on pressurised central section of upper fuselage, weapons bay doors and nosewheel door. The tail unit is a cantilever all-metal structure with bonded honeycomb sandwich skin panels on torsion boxes.
SYSTEMS: Kleber-Colombes pneumatic de-icing boots on wing leading-edges. Kleber-Colombes pneumatic de-icing boots on tail unit leading-edges.
LANDING GEAR: Retractable tricycle type, supplied by Messier-Hispano, with twin wheels on each unit. Hydraulic retraction, nosewheels rearward, main units forward into engines nacelles. Kleber-Colombes dimpled tyres, size 956 x 319-392 mm on mainwheels, 637 x 190-319 mm on nosewheels. Tyre pressures: main 9.52 bars (138 lb/sq in), nose 6.07 bars (88 lb/sq in). Messier-Hispano disc brakes with Maxaret anti-skid units.
POWER PLANT: Two 4,553 kW (6,106 ehp) SNECMA-built Rolls-Royce Tyne RTy.20 Mk 21 turboprop engines, each driving a Ratier-built HSD four-blade constant-speed propeller. Six integral fuel tanks with total capacity of 21,000 litres (5,547 US gallons; 4,619 Imp gallons). Provision for wingtip tanks to be fitted.
ACCOMMODATION: Normal flight crew of 12 comprising observer in nose; pilot and co-pilot on flight deck; a tactical co-ordinator, navigator, two sonobuoy operators, and radio, radar and ECM/MAD/Autoycus operators in tactical compartment; and two observers in beam positions. On long-range patrol missions a further 12 crew can be carried as relief crew. The upper, pressurised section of the fuselage, from front to rear, comprises the nose observer's compartment, flight deck, tactical operations compartment, rest compartment for crew, and beam observers' compartment.
SYSTEMS: SEMCA air conditioning and pressurisation system. Hydraulic system pressure 207 bars (3,000 lb/sq in). Electrical system provides 28.5 V DC, 115/200 V variable-frequency AC and 115/200 V stabilised-frequency AC. AirResearch GTCP 85-100 APU in starboard side of front fuselage, adjacent radar compartment, for engine starting and ground air conditioning, can also power one 20 kVA AC alternator and one 4 kW DC generator for emergency electrical power supply.
ARMAMENT AND OPERATIONAL EQUIPMENT: Main weapons carried in bay in unpressurised lower fuselage. Weapons include all NATO standard bombs, 175 kg (385 lb) US or French depth charges. HVAR rockets, homing torpedoes, including types such as the Mk 46 Brush or LX.4 with acoustic heads, or four underwing air-to-surface missiles with nuclear or high-explosive warheads. Electronic equipment includes a retractable Thomson-CSF radar installation, a MAD tailboom and an electrical countermeasures pod at the top of the tailfin. Sonobuoys are carried in a compartment aft of the main weapons bay, while the whole of the upper and lower rear fuselage acts as a storage compartment for sonobuoys and marker flares. Compartment for retractable Thomson-CSF radar `dustbin' forward of the main weapons bay. Forward of this, the lower nose section acts as additional storage for military equipment and the APU. Weapons system includes Plotac optical tactical display, 80 x 80 cm (31.5 x 31.5 in) in size, consisting of separate tables for search display and localisation and attack display. At 1:30,000 scale, this gives coverage of any area 21,950 x 21,950 m (72,000 x 72,000 ft) to an accuracy of 1 mm (that is less than 30.5 m; 100 ft at that scale). Heading references provided by duplicated gyrosopic platforms of the 3-gyro (1° of freedom) 4-gimbals type, with magnetic compasses as back-up system. Janus-type Doppler has stabilised antenna and works in the Ke band to provide direct indication of ground speed and drift. In case of failure an automatic switch is made to the air data system. The analogue type navigation computer is accurate to 0.25 per cent. The MAD is of the atomic resonance type and uses light simulation techniques. Plotac system has provision to accept additional detectors. Radar has `sea-return' circuits and stabilised antenna enabling it to detect a submarine snorkel at up to 40 n miles (75 km; 46 miles) even in rough seas.
Thomson-CSF AMASCOS multisensor system
Type: Maritime sensor (air).
Description
The AMASCOS (Airborne MAritime Situation COntrol System) is a family of integrated maritime patrol and surveillance mission systems, designed for building up and updating tactical situations in real time and as a decision aid for operators. The modular systems can be integrated on any type of fixed-wing aircraft or helicopter. The typical AMASCOS configuration integrates Thomson-CSF equipment with the Ocean Master radar developed by Thomson-CSF and Daimler Benz Aerospace. The three versions of AMASCOS - AMASCOS 100, AMASCOS 200 and AMASCOS 300 - correspond to three broad categories of mission requirement ranging from simple maritime surveillance to anti-surface and anti-submarine warfare.
AMASCOS 100 is a lightweight configuration which weighs less than 250 kg. It includes radar and FLIR plus an integrated tactical computer and is suited for a wide range of missions, such as EEZ surveillance, search and rescue and law enforcement. It can be fitted on carrier or ground-based helicopters and light turboprop aircraft with one or two operators working in close co-ordination with the cockpit crew.
AMASCOS 200 adds ESM equipment to the AMASCOS 100 for anti-surface missions and can be extended to provide an Anti-Submarine Warfare (ASW) capability. It can be fitted to fixed- and rotary-wing aircraft in the 8 ton class. Two or three operators are required.
In addition to basic maritime patrol and surveillance functions, AMASCOS 300 offers both anti-surface and ASW capabilities and is suitable for naval operations command and control assignments. It can be installed on any maritime patrol aircraft in the 10 ton class and above. Three or more operators are required. The heart of the system is a dedicated tactical computer which collates and processes data from different sensors and other onboard equipment. The system can be equipped with the following: the Ocean Master radar, Sextant Avionique Nadir Mk II inertial GPS, Thomson-CSF Optronique Chlio FLIR, Thomson-CSF DR 3000 ESM, Thomson-CSF Link W data link, Thomson Sintra ASM Sadang 1000 sonobuoys, Thomson Sintra ASM HS 312S dipping sonar and Sextant Avionique MAD Mk III.
Operational status
In 1994 the Indonesian Navy chose AMASCOS 100 for its CN-212 maritime patrol aircraft and NBO-105 helicopters. This will include the Ocean Master radar and Chlio FLIR. In January 1997 the Indonesian Navy ordered a further six systems for the CN-212. In 1993 the Pakistan Navy chose AMASCOS to refurbish its four Atlantic long-range maritime patrol aircraft and three MPA Fokker 27. By the first quarter of 1996 the first aircraft modification was complete, including the integration of the Ocean Master Radar, the DR-3000-A ESM with interferometry, the SADANG 1001-C Acoustic Processor and a new radio-navigation set.
COMPANY NAME : Thomson-CSF Radars & Contremesures (RCM)
DIMENSIONS, EXTERNAL:
Wing span......................................36.30 m (119 ft 1 in) Wing aspect ratio..............................................10.94 Length overall.................................31.75 m (104 ft 2 in) Height overall..................................11.33 m (37 ft 2 in) Fuselage: Max width...............................2.90 m (9 ft 6 in) Max depth.................................4.00 m (13 ft 1{1/2} in) Tailplane span...........................12.31 m (40 ft 4{1/2} in) Wheel track...............................9.00 m (29 ft 6{1/4} in) Wheelbase......................................9.44 m (31 ft 0 in) Propeller diameter...............................4.88 m (16 ft 0 in)
DIMENSIONS, INTERNAL:
Tactical compartment: Length................8.60 m (28 ft 2{1/2} in) Height..........................................1.93 m (6 ft 4 in) Max width.................................2.70 m (8 ft 10{1/2} in) Rest compartment: Length....................5.10 m (16 ft 8{3/4} in) Height..........................................1.93 m (6 ft 4 in) Max width.................................2.70 m (8 ft 10{1/2} in) Beam observer's compartment: Length.....................................1.00 m (3 ft 3{1/4} in) Main weapons bay: Length....................9.00 m (29 ft 6{1/4} in) Height..........................................1.55 m (5 ft 1 in) Height under wing..........................1.00 m (3 ft 3{1/4} in) Max width..................................2.20 m (7 ft 2{1/2} in)
AREAS:
Wings, gross...............................120.34 m{2} (1,295 sq ft) Ailerons......................................5.40 m{2} (58.0 sq ft) Trailing-edge flaps (total).................26.80 m{2} (288.4 sq ft) Spoilers (total)..............................1.66 m{2} (17.8 sq ft) Fin.........................................16.64 m{2} (179.1 sq ft) Rudder........................................5.96 m{2} (64.1 sq ft) Tailplane....................................32.5 m{2} (349.7 sq ft) Elevators.....................................8.28 m{2} (89.1 sq ft)
WEIGHTS AND LOADINGS:
Useful load....................................18,551 kg (40,900 lb) Max zero-fuel..................................30,500 kg (67,252 lb) Max T-O weight................................46,000 kg (101,430 lb)
PERFORMANCE (at max T-O weight):
Max level speed at high altitudes.........350 kt (648 km/h; 403 mph) Cruising speed............................300 kt (556 km/h; 345 mph) Service ceiling..................................9,144 m (30,000 ft) T-O to 10.7 m (35 ft), ISA........................1,500 m (4,925 ft) T-O to 10.7 m (35 ft), ISA + 17°C, 15° flap.......1,700 m (5,575 ft) Max range......................4,200 n miles (7,778 km; 4,838 miles) Max endurance at patrol speeds of 169 kt (320 km/h; 195 mph)....18 h
AMD-BA Mirage 5.
ACTIVE : 12
OPERATIONAL SPEED : 750 kt (1,390 km/h).
SERVICE CEILING : 59,055 ft (18,000 m).
RANGE A/C : 740 n miles (1,370 km).
ROLE/WEAPON SYSTEMS : Operated by the Air Force, and all can be used for maritime strike. Sensors: Thomson-CSF radar. Weapons: ASV; two AM 39 Exocet or Harpoon; two 30 mm DEFA.
DASSAULT MIRAGE 5
Single- and two-seat ground attack aircraft.PROGRAMME:
The Mirage 5 is a ground attack aircraft using the same airframe and engine as the Mirage III-E. The basic VFR version has simplified avionics, 470 litres (123 US gallons; 103 Imp gallons) greater fuel capacity than the III-E, in a tank between the engine air intakes, and considerably extended stores carrying capability. It combines the full M2+ capability of the Mirage III, and its capability to operate from semi-prepared airfields, with simpler maintenance. In ground attack configuration, up to 4,000 kg (8,818 lb) of weapons and 1,000 litres (264 US gallons; 220 Imp gallons) of fuel can be carried externally on seven wing and fuselage attachment points. The Mirage 5 can also be flown as an interceptor, with two Magic or Sidewinder air-to-air missiles and 4,700 litres (1,241 US gallons; 1,034 Imp gallons) of external fuel. At customer's option any degree of IFR/all-weather operation was provided for, with reduced fuel or weapons load. The Mirage 5 was flown for the first time on 19 May 1967. A total of 517 Mirage 5 aircraft were built.
VERSIONS:
Mirage 5: Initial version developed for Israel with Atar 9C-3 turbojet engines as a clear weather fighter bomber. Mirage 5D: Export version based on Mirage 5 airframe. Radar omitted.
Mirage 5R: Reconnaissance version with cameras fitted in modified nosecone.
Nesher/Dagger: Israeli-built Mirage 5 named Nesher. Subsequently transferred to Argentina and renamed Dagger.UPGRADES: Dassault: For details see Advanced Technology Upgrade Programmes in this section.
SABCA: Mirsip/Elkan programme see separate entry in Belgium section.
SAGEM: Responsible for general overhaul of 40 Mirage 5 aircraft acquired from French Air Force. SAGEM will undertake an avionics upgrade on 20 of these aircraft. Also participation in the Mirsip/Elkan programme. See separate entry in this section.
SNECMA: Contract to re-engine Colombian Air Force Mirage 5s with Atar 9K-50 turbojets.
OPERATORS: Versions of the Mirage 5 are in service with the armed forces of the following countries: Abu Dhabi (22); Argentina (8); Colombia (13); Egypt (74); Gabon (7); Libya (70); Pakistan (52); Peru (15) and Zaire (6).
The structural description of the Mirage III-E is generally applicable to the Mirage 5, with the following exceptions:ARMAMENT: Seven attachment points for external loads with multiple launchers permitting a maximum load of more than 4 tonnes. Ground attack weapons are similar to those carried by the III-E. For interception, two Magic or Sidewinder missiles can be carried under the wings.
EQUIPMENT: Optional equipment on the latest versions includes an inertial nav system and nav/attack system, with head-up display and either Agave multipurpose radar or an air-to-surface laser rangefinder and Aida II radar.
DIMENSIONS, EXTERNAL: As Mirage III-E except:
Length overall.............................15.55 m (51 ft 0{1/4} in)
WEIGHTS AND LOADINGS: As Mirage III-E except:
Weight empty....................................6,600 kg (14,550 lb)
PERFORMANCE (in `clean' condition, with guns installed, except where indicated): As III-E, plus:
Combat radius with 907 kg (2,000 lb) bomb load: hi-lo-hi..................................700 n miles (1,300 km; 808 miles) lo-lo-lo..................................350 n miles (650 km; 404 miles) Ferry range with three external tanks.....2,158 n miles (4,000 km; 2,485 miles)
