General Dynamics F-111 Aardvark

The F-111 was developed according to a US Air Force requirement for a new fighter-bomber and the US Navy’s need for a new air Defence fighter with a single platform. The US navy cancelled the F-111B in 1968 due to overweight. 

The F-111 was the first operational aircraft with features like swing wings, and afterburning turbofans, and it could cruise supersonically without using the afterburner in clean setup. It also had terrain following radar and a cockpit escape capsule.

At first some problems were experienced with the swing wing mechanism and the air inlets, but they were resolved eventually. 

F-111A    first model.

F-111E    with revised air inlets.

F-111D    included digital avionics.

F-111F    fitted with more powerful engines and improved analog avionics

FB-111    strategic nuclear bomber with longer wingspan and heavier undercarriage, in the early 1990’s the FB-111’s had their nuclear role removed, and were redesignated the F-111G (they went through a digital avionics upgrade)

F-111F    Gulf War veteran (with upgraded digital avionics and pave tack laser designator) was retired in July 1996 While the EW EF-111 Raven jammer bowed was fazed out in 1998. 

Australia operates 22 F-111C’s the C combined the engines and avionics of the F-111A with the FB-111B’s heavier undercarriage and longer span wings. Four were modified as RF-111C reconnaissance aircraft, with a similar equipment fit in the bomb-bay as in the F-14’s TARP pod. The F-111C’s carry the Pave Tack pod and the R/F-111C fleet underwent a comprehensive digital avionics upgrade program, completed in 1999. They were re-engined with 93.4 kN TF30-P109’s (from retired USAF F-111’s) in the late 1990’s Australia bought 15 ex USAF F-111G’s which were delivered from 1993. They will help to extend the RAAF F-111 fleet life to 2020.

 

Developing Nation:	United States
First Flight:	December 21st 1964
Crew:	2
Wing Span:	- Unswept: 19,20 m - Swept: 9,74 m
Wing Area:	-Unswept 48,77 m²
Length:	22,40 m
Engine (s):	Pratt & Whitney TF-30-P100 (2x) with 11385 kg thrust each
Weight:	21398 kg
Max.Take off weight:	45359 kg
Max. Speed:	2655 km/h (at optimum altitude)
Max. Range:	4707 km (on internal fuel only)
Max. Altitude:	17985 m (service ceiling)
Weapons:	- one 20 mm. multi-barreled M61A-1 cannon and one 340Kg. B43 bomb, or two B43 bombs in internal bay, eight underwing hard points with provision for 14,290 Kg of stores, inner four pivot to keep stores in alignment as wings sweep.

Boeing 747-8

On November 14, 2005 Boeing Company officially launched the new Boeing 747-8 program, which includes the 747-8 Intercontinental passenger airplane and the 747-8 Freighter airplane.

Cargolux, based in Luxembourg, has ordered 10 747-8 Freighters and will take delivery of the first 747-8F in third-quarter 2009. It also holds purchase rights for 10 additional airplanes. Cargolux currently operates an all-Boeing fleet of 13 747-400 freighters.

Nippon Cargo Airlines, based in Japan, has ordered eight 747-8 Freighters and will receive its first airplane in fourth-quarter 2009. The airline also acquired options for six additional airplanes. Nippon Cargo currently operates 13 747 freighters and has six more 747-400Fs on order.

Firm orders from the two launch customers are valued at approximately $5 billion at list prices.

“We are thrilled to have Cargolux and Nippon Cargo choose the new 747-8 and become the launch customers for this next generation of the proud and valuable 747 airplane family,” said Alan Mulally, president and chief executive officer, Boeing Commercial Airplanes. “The 747-8 will use the technologies of the 787 Dreamliner to significantly increase the passenger and freighter capabilities of the 747 and offer greater fuel efficiency, improved operating economics, and be more friendly to the environment with reduced noise and emissions.”

Both versions of the new 747 will feature GE’s 787-technology GEnx engines, meet Stage 4 and QC2 noise requirements, have reduced emissions, offer lower trip costs and have an upgraded flight deck and an improved wing.

“The 747-8 Freighter will be very important in allowing Nippon Cargo to take advantage of the high expected cargo market growth in Asia,” said Takuro Uchiyama, president and CEO, Nippon Cargo Airlines. “In addition, the 747-8 Freighter will be the world’s most efficient cargo airplane, which is a key attribute with today’s high cost of fuel.”

Ulrich Ogiermann, president and CEO, Cargolux Airlines, said, “The Boeing 747-400 Freighter has been a cornerstone of our success, and I have high expectations that the 747-8 Freighter will build on that success and expand our capabilities worldwide. The increased payload capacity and much improved efficiency will allow us to continue our expansion and maximize our profitability. Equally important to us and the communities where we operate is the new standard the 747-8 Freighter will set in noise reduction.”

The 747-8 Intercontinental passenger airplane will be stretched 3.6 m (11.7 ft) compared to the 747-400 to accommodate 34 additional seats in a typical three-class configuration. The only jetliner in the 400- to 500-seat category, it will have a range of 14,815 km (8,000 nmi) and will feature the new Boeing Signature Interior.

The Intercontinental will be quieter, produce fewer emissions, and achieve better fuel economy than any competing jetliner. It will offer 21 percent more lower-hold revenue cargo volume than the 747-400 and cost about 8 percent less per seat mile to operate. Compared to the A380, it will offer 22 percent lower trip costs.

The 747-8 Freighter will be 5.6 m (18.3 ft) longer than the 747-400 freighter. With a total payload capacity of 140 metric tonnes (154 tons), including tare weight, the 747-8F provides 16 percent more cargo revenue volume than the -400. The additional 117m³ (4,124 ft³) from the longer fuselage offers space for four additional main-deck pallets, two additional lower-hold pallets and two additional lower-hold containers. Cargo can be loaded and unloaded on the 747-8F using both the nose and side doors for maximum speed and efficiency.

Compared to the A380, the 747-8F will offer 20 percent lower trip costs. In addition, the 747-8F will maintain the operational flexibility of today’s 747 freighters, with good profit potential at less-than-full loads.

The 747-8 Freighter complements the existing 747-400 freighter family, which is the air-cargo industry’s standard. Both models accommodate 3.1-meter (10-foot) high pallets, providing operators with maximum flexibility.

The 747-8 also fits easily in today’s aviation infrastructure, flying into more than 210 airports worldwide without additional, expensive infrastructure changes required.

The 747 freighter family currently constitutes more than half of the world’s total freighter capacity. Boeing freighters of all models comprise more than 90 percent of the total worldwide freighter lift.

Boeing forecasts the need for about 900 airplanes — passengers and freighters — in the 400-plus-seat segment over the next 20 years. Boeing also forecasts that large widebody freighters (65 metric tons and above in capacity) will comprise 34 percent of the freighter market by 2024.

Bombardier Challenger

The Bombardier (Canadair) CL-600 Challenger, a medium to long range widebody corporate jet, was developed by Learjet designer Bill Lear. Known as the LearStar 600, this design was first conceived in 1974. In 1976 Canadair purchased the exclusive production, development and marketing rights.

Three development Challengers were built, the first of which flew for the first time on November 8 1978, the others flying in March and July the following year. However the first aircraft crashed in a deep stall accident and while certification was granted in August 1980.

Bombardier Challenger types:

• CL-600 original production version, powered by Avco Lycoming ALF-502L turbofans of 33.6 kN thrust each.
• 
• CL-601-1A refined version including winglets to reduce drag and more powerful General Electric CF34-1A engines.
• 
• CL-601-3A further up-rated engine and a glass cockpit. This was the first version marketed by Bombardier.
• 
• CL-604 major upgrade of the 601 design, incorporating more powerful General Electric CF34-3B engines, larger fuel supply, completely new undercarriage, structural improvements to wings and tail, and a new electronic flight instrumentation system.
• 
• Challenger 300 a new-generation CL-604 with two Honeywell AS907 turbofan engines each providing 35.81 kN thrust.
• 
• Challenger 800 a variant of the Bombardier Regional Jet airliner,has a5,778km transcontinental range. 

Developing nation:	Canada.
Manufacturer/designer:	Bombardier Aerospace.
Production line:	Montreal – Dorval IAP, Quebec Canada.
Type aircraft:	Medium to long range widebody corporate jet.
First flights:	- CL-600 November 8, 1978 C-GCGR-X. - CL-601-1A September 17, 1982. - CL-601-3A September 28, 1986. - CL-604 March 17,1995 C-FVUC. - Challenger 300 August 14, 2001 C-GJCJ. - Challenger 800 October 13,1996 C-FBGX.
First delivery:
	Canadair CL-601 Challenger
Cockpit crew:	two pilots.
Passengers:	up to 19.
Cabin Length:	8,72 m
Cabin diameter:	2,19 m.
Cabin height:	1,85 m.
Cabin floor:	13,56 m².
Cabin Volume:	24,35 m³.
Wing span:	19,61 m.
Wing area:	48,31 m².
Wing sweep:	degrees.
Fuselage length:	20,85 m.
Fuselage diameter:	2,49 m.
Height:	6,30 m.
Engines:	- two General Electric CF34-1A each rated 40,66 kN.
Weight:	- empty: 9.049 Kg. - max. zero-fuel weight: 11.151 Kg. - fuel: 7.559 Kg. - max. payload: 2.229 Kg.
Max. take off weight:	19.950 Kg.
Max. landing weight:	15.309 Kg.
Cruise speed:	786 km/h.
Max. speed:	851 km/h.
Max. ceiling:	12.495 m.
Range:	- max. range 6.375 km.
Performance:	- max. rate of climb at sea level 1.355 m per minute. - take-off run 1.646 m at max. take-off weight. - landing run 1.082 m at max. landing weight.

 

	Bombardier Challenger 300*
Engines:	- two Honeywell HTF7000 turbofan each rated 30.4 kN.
Weight:	- empty: 8.369 Kg. - max. zero-fuel weight: 11.839 Kg. - fuel: 6.418 Kg. - max. payload: 1.247 Kg.
Max. take off weight:	17.463 Kg.
Max. landing weight:	15.309 Kg.
Range:	5.741 Km.

* Generally similar to the Canadair CL-601 except in the following particulars.

 

	Bombardier Challenger 800*
Passengers:	- executive up to 19 pax. - corporate shuttle up to 50 pax.
Cabin Length:	14,76 m
Cabin diameter:	2,19 m.
Cabin height:	1,85 m.
Cabin floor:	30,29 m².
Cabin Volume:	53,80 m³.
Wing span:	21,21 m.
Wing area:	48,35 m².
Fuselage length:	26,77 m.
Fuselage diameter:	2,49 m.
Height:	6,22 m.
Engines:	- two General Electric CF34-3B1 turbofan each rated 38.84 kN.
Weight:	- max. zero-fuel weight: 17.917 Kg. - fuel: 8.303 Kg. - max. payload: 2.540 Kg.
Max. take off weight:	24.040 Kg.
Max. landing weight:	21.319 Kg.
Cruise speed:	719 km/h.
Max. speed:	851 km/h.
Max. ceiling:	12.495 m.
Range:	5.778 Km.
Performance:	- take-off run 1.919 m at max. take-off weight. - landing run 887 m at max. landing weight.

* Generally similar to the Canadair CL-601 except in the following particulars.

 

Canadair Challenger production:

Approximately built 709, active 697, stored 2, scrapped 0 and written-off 10 at May 2005.

Canadair Challenger built of each type:

85 CL-600.

66 CL-601.

134 CL-601-3A.

59 CL-601-3R.

314 CL-604.

51 Challenger 300.

?  Challenger 800.

 

10 Canadair Challengers written-off by accidents:

– 03apr1980 C-GCGR-X CL-600 Canadair crashed after a non-scheduled stall at Mojave, CA USA 1 fatalities / 3 on board. – 03jan1983 N805C CL-600 A.E. Stanley Manufacturing Co crashed against mountain during approach to Sun Valley-Friedman Memorial Airport, ID USA crash site 4 km N of Hailey, ID. 2 fatalities / 2 on board. – 07feb1985 N779XX CL-601 TAG Aviation undercarriage collapsed after too early landing (44 m) during approach at Milano-Linate Airport Italy. 0 fatalities / 12 on board. – 20mar1994 N88HA CL-601-3A Crystal Aviation written-off after emergency landing in a field in attempt to reach Bassett AP, NE USA after loss of power in both engines. 0 fatalities / 2 on board. – 24apr1995 144613 CC-144B Canadian Armed Forces written-off at CFB Shearwater, Canada 0 fatalities / ? on board. 10oct2000 C-FTBZ CL-604 Bombardier Aerospace during take-off from Wichita-Mid-Continent Airport, KS USA the airplane stall at an altitude too low for recovery. 2 fatalities / 3 on board. – 04jan2002 N90AG CL-604 Agco Corporation crashed during take-off from Birmingham IAP, United Kingdom. 5 fatalities / 5 on board. – 28nov2004 N873G CL-600 Air Castle crashed out of control in take-off from Montrose County Airport, CO USA. 3 fatalities / 6 on board. – 02feb2005 N370V CL-600 DDH Aviation the pilot aborted the takeoff at Teterboro Airport, NJ USA, but the plane skidded off the runway. It went through the perimeter fence, crossed a highway and crashed into a building. About 15 people were injured, one critically, but nobody was killed. 0 fatalities / 11 on board. 09mar2005 N660RM CL-600 Romeo Mike Aviation during take-off at Tupelo Regional Airport, MS USA. 0 fatalities / 7 on board.

 

Canadair Challenger military operators:
Canadian Armed Forces.*	- 1 CX-144A. - 2 CC-144. - 2 CE-144C. - 2 CU-144A - 3 CC-144B - 3 CE-144C - 4 CC-144A
Luftwaffe (Germany).	- 6 CL-601-1A
Royal Australian Air Force.	- 3 CL-604
Royal Danish Air Force.	- 3 CL-604
Croatia Government.	- 1 CL-604
Czech Government.	- 1 CL-601-3A
Gouvernement du Quebec.	- 1 CL-601
Jordanian Government.	- 1 CL-604
Korea Maritime.	- 1 CL-604

Summary May 2005. 

* delivered original as: 

1 CX-144A test aircraft by AETE, Cold Lake

4 CC-144B VIP and utility transports

7 CE-144A electronic warfare trainers

3 CP-144A maritime patrol aircraft

2 CC-144 VIP utility transport

Lockheed Martin F-16 Fighting Falcon

In March 1993 the Fort Worth division of General Dynamics was sold to Lockheed, and the aircraft is now known as the Lockheed Martin F-16 Fighting Falcon.

The F-16 is world’s most successful warplane of recent times, over 4.000 Falcons have been build.

The prototype YF-16 (72-1567) rolled out at Fort Worth on 13 December 1973, and was delivered by C-5A Galaxy to Edwards AFB California. During high speed taxi testing on 20 January 1974 test-pilot Phil Oestricher had to take-off with his YF-16, followed by the first official flight on 2 February 1974.

Delivery of the first operational USAF F-16A and F-16B began in January 1979, with the 388th TFW at Hill AFB, Utah. The first European F-16 (FB-01) was delivered to the Belgian Air Force also in January 1979. The Netherlands accepted their first F-16B (J-259) in February 1979.

The F-16C/D models introduce more high-tech for night operations, a new Hughes APG-68 multi-mode radar with increased range, sharper resolution and more operating modes. The first F-16C Flew 19 June 1984. To recognize the C/D models, note the antenna on the tail-fin.

Since 1992 the European Partners ( Netherlands, Belgium, Norway and Denmark) working together at the Mid-Life-Update program. The MLU program was designed to bring the Block 15 aircraft up to the standards of the Block 50/52 F-16C/D, in particular to give them the capability of carrying and launching Beyond Visual Range weapons such as the AIM-120 AMRAAM, together with the ability to carry out precision weapons delivery missions at night and in adverse weather.  The first MLU aircraft flew in April of 1995. By early 1998, conversions were being carried out in all four countries. Present plans are for 48 Belgian, 61 Danish, 156 Dutch, and 56 Norwegian F-16A/Bs to go through the MLU program. The program is scheduled with software updates to continue into 2009.

F-16AM MM7246 AMI

Developing Nation:	USA
Manufacturer/designer:	General Dynamics
Task:	Multi-role Fighter
First Flight:	YF-16 72-1468 20 January 1974  F-16A 75-0745 8 December 1976  F-16B 75-0751 8 August 1977  F-16C 83-1118 19 June 1984  F-16D 83-1174 14 September 1984
First Delivery:	6 January 1979
First Operational:	12 November 1980 by USAF’s 4th TFS of the 388th TFW at Hill AFB, Utah.
Crew:	F-16A/C 1  F-16B/D 2
Ejection Seat:	ACES II zero-zero canted to recline 30°.
	F-16A block 15 OCU specification
Wing Span:	9,45 m, with tip-mounted AAM’s 10,00 m.
Wing Area:	28,87 m².
Length:	15,03 m.
Height:	5,01 m.
Engine (s):	One Pratt & Whitney F100-PW-220 rated at 64,9 kN dry and with afterburner 105.7 kN.
Weight:	Empty: 6.607 Kg.  Internal fuel: 3.162 Kg.  External fuel: 3.066 Kg.  Max. payload: 6.894 Kg.
Max. Take off weight:	Max. take off: 14.968 Kg.
Max. Speed:	2.124 km/h at 12.190 m.
Max. Range:	3.891 Km.
Performance:	Max. endurance hours.
g limits:	+ 9.
Radar:	Westinghouse APG-66 pulse- Doppler radar.
Centerline hard point(’s):	1
Underwing hard points:	6
Wingtip hard points:	2
Weapons:	20 mm M61A1 Vulcan Cannon with 511 rounds.  AIM-7 Sparrow.  AIM-9L/M/P  Sidewinder.  AGM-45 Shrike.  AGM-65 Maverick.  AGM-78 Standard.  AGM-88 Harm.  GBU-10.  GBU-15.  Mk 20 Rockeye.  CBU -87 Cluster bomb.  GP Bombs.  Paveway II Bombs.
Extra:	Orpheus reconnaissance pods, only Dutch F-16A(R).

 

 

	F-16C block 25 specification.
Wing Span:	9,45 m, with tip-mounted AAM’s 10,00 m.
Wing Area:	28,87 m².
Length:	15,03 m.
Height:	5,09 m.
Engine (s):	- General Electric F110-GE-100 turbofan rated at 122,77 kN with afterburner (1x) Or: - Pratt & Whitney F100-P-220 turbofan rated with afterburner 104,31 kN. (1x)
Weight:	- Empty: 8.663 Kg with F110 turbofan. - Empty: 8.316 kg with F100 turbofan. - Internal fuel: 3.162 Kg. - External fuel: 3.066 Kg. - Max. payload: 9.276 Kg.
Max. Take off weight:	Max. take off: 19.187 Kg.
Max. Speed:	2.124 km/h at 12.190 m.
Max. Range:	3.891 Km.
Performance:	Service ceiling 15.240 m.
g limits:	+ 9.
Radar:	Hughes AN/APG-68 (V5) multi mode radar.
Centerline hard point(’s):	1
Underwing hard points:	6
Wingtip hard points:	2
Weapons:	- 20 mm M61A1 Vulcan Cannon with 511 rounds. - AIM-9L/M/P  Sidewinder. - AIM-120 AMRAAM. - AGM-45 Shrike. - AGM-65 Maverick. - AGM-88 Harm. - GBU-10 laser guided bombs. - GBU-12 laser guided bombs. - Mk 20 Rockeye. - CBU -87 Cluster bombs. - GP Bombs. - Paveway II Bombs.
Extra:	LANTIRN navigation and targeting pod.

Special F-16’s:

 

·         YF-16/CCV        72-1567        single        ff 16-03-1976         Control Configured Vehicle.

·         F-16/79            75-0752        dual          ff 29-10-1980        General Electric J79-GE-17X single shaft turbojet engine.

·         F-16/101           75-0745        single        ff 19-12-1980        General Electric GE-YJ-101 two shaft turbojet engine.

·         AFTI/F-16         75-0750         single       ff 10-07-1982        Advanced Fighter Technology Integration.

·         F-16XL              75-0749         single       ff 03-07-1982        “Cranked Delta” Wing with F100 engine.

·         F-16XL              75-0747         dual          ff 29-10-1982        “Cranked Delta” Wing with F110 engine.

·         F-16D DFLCS     83-1176         dual          ff     -10-1992        Digital Flight Control System

 

F-16 Operators:

 

Bahrain	18 F-16C
	4 F-16D
Belgium	136 F-16A
	24 F-16B
Chile	11 F-16A
	7 F-16B
	6 F-16C
	4 F-16D
Denmark	60 F-16A
	17 F-16B
Egypt	34 F-16A
	8 F-16B
	136 F-16C
	42 F-16D
General Dynamics	1 NF-16D-30
Greece	100 F-16C
	30 F-16D
Indonesia	8 F-16A
	4 F-16B
Israel	103 F-16A
	22 F-16B
	81 F-16C
	54 F-16D
	100 F-16I
Italy *	30 F-16A ADF
	4 F-16B OCU
Jordan	24 F-16A
	6 F-16B
	17 F-16A/B ADF
Morocco	24 F-16C/D?
Netherlands	177 F-16A
	36 F-16B
Norway	60 F-16A
	14 F-16B
Oman	8 F-16C
	4 F-16D
Pakistan	28 F-16A
	12 F-16B
	12 F-16C
	6 F-16D
Poland	36 F-16C
	12 F-16D
Portugal	38 F-16A
	7 F-16B
Singapore	4 F-16A
	4 F-16B
	22 F-16C
	20 F-16D
South Korea	125 F-16C
	55 F-16D
Taiwan	120 F-16A
	30 F-16B
Thailand	43 F-16A
	11 F-16B
Turkey	196 F-16C
	44 F-16D
United Arab Emirates	55 F-16E
	25 F-16F
United States Air force	672 F-16A
	123 F-16B
	1240 F-16C
	205 F-16D
United States Navy	22 F-16N
	4 TF-16N
Venezuela	18 F-16A
	6 F-16B