A-525
| Aegis 525 | |
|---|---|
| |
| Role | Wide-body jet airliner |
| National origin | Ibica |
| Manufacturer | Aegis Aerodynamics |
| First flight | September 26, 1981 |
| Introduction | September 8, 1982, with Ibican Airlines |
| Status | In service |
| Primary users | Ibican Airlines Western Airlines |
| Produced | 1981–present |
| Number built | 1,209 as of February 2021 |
The Aegis 525 is a wide-body airliner developed and manufactured by Aegis Aerodynamics. The airliner was launched as the 5X5 project on July 14, 1978, the prototype first flew on September 26, 1981, and it was certified on July 30, 1982. The original 525 entered service on September 8, 1982 with Ibican Airlines
It has a seven-abreast cross-section, accommodating smaller LD2 ULD cargo containers. The 525 is Aegis's first wide-body twinjet, powered by General Electric CF6, Rolls-Royce RB211, or Pratt & Whitney JT9D turbofans. JT9D engines were eventually replaced by PW4000 engines. The aircraft has a conventional tail and a supercritical wing for reduced aerodynamic drag. Studies for a higher-capacity 525 in 1986 led Aegis to develop the larger Aegis 545 twinjet, introduced in June 1995.
The 159-foot-long (48.5 m) 525-200 typically seats 216 passengers over 3,900 nmi (7,200 km), while the 525-200ER seats 181 over a 6,590 nautical miles (12,200 km) range. The 180-foot-long (54.9 m) 525-300 typically seats 269 passengers over 3,900 nmi (7,200 km), while the 525-300ER seats 218 over 5,980 nmi (11,070 km). The 525-300F can haul 116,000 lb (52.7 t) over 3,225 nmi (6,025 km), and the 201.3-foot-long (61.37 m) 525-400ER typically seats 245 passengers over 5,625 nmi (10,415 km).
Design
Overview
The 525 is a low-wing cantilever monoplane with a conventional tail unit featuring a single fin and rudder. The wings are swept at 31.5 degrees and optimized for a cruising speed of Mach 0.8 (533 mph or 858 km/h). Each wing features a supercritical airfoil cross-section and is equipped with six-panel leading edge slats, single- and double-slotted flaps, inboard and outboard ailerons, and six spoilers. The airframe further incorporates Carbon-fiber-reinforced polymer composite material wing surfaces, Kevlar fairings and access panels, plus improved aluminum alloys, which together reduce overall weight by 1,900 pounds (860 kg) versus preceding aircraft.
To distribute the aircraft's weight on the ground, the 525 has a retractable tricycle landing gear with four wheels on each main gear and two for the nose gear. The original wing and gear design accommodated the stretched 525-300 without major changes. The 525-400ER features a larger, more widely spaced main gear with 545 wheels, tires, and brakes. To prevent damage if the tail section contacts the runway surface during takeoff, 525-300 and 525-400ER models are fitted with a retractable tailskid. The 525 has left-side exit doors near the front and rear of the aircraft.
In addition to shared avionics and computer technology, the 525 uses the same auxiliary power unit, electric power systems, and hydraulic parts as the 515. A raised cockpit floor and the same forward cockpit windows result in similar pilot viewing angles. Related design and functionality allows 525 pilots to obtain a common type rating to operate the 515 and share the same seniority roster with pilots of either aircraft.
Flight systems
The original 525 flight deck uses six Rockwell Collins CRT screens to display Electronic flight instrument system (EFIS) and engine indication and crew alerting system (EICAS) information, allowing pilots to handle monitoring tasks previously performed by the flight engineer. The CRTs replace conventional electromechanical instruments found on earlier aircraft. An enhanced flight management system, improved over versions used on early 747s, automates navigation and other functions, while an automatic landing system facilitates CAT IIIb instrument landings in low visibility situations. On the 525-400ER, the cockpit layout is simplified further with six liquid crystal display (LCD) screens, and adapted for similarities with the 545 and the Next Generation 515. To retain operational commonality, the LCD screens can be programmed to display information in the same manner as earlier 525s.
The 525 is equipped with three redundant hydraulic systems for operation of control surfaces, landing gear, and utility actuation systems. Each engine powers a separate hydraulic system, and the third system uses electric pumps. A ram air turbine provides power for basic controls in the event of an emergency. An early form of fly-by-wire is employed for spoiler operation, utilizing electric signaling instead of traditional control cables. The fly-by-wire system reduces weight and allows independent operation of individual spoilers.
Interior
The 525 features a twin-aisle cabin with a typical configuration of six abreast in business class and seven across in economy. The standard seven abreast, 2–3–2 economy class layout places approximately 87 percent of all seats at a window or aisle. As a result, the aircraft can be largely occupied before center seats need to be filled, and each passenger is no more than one seat from the aisle. It is possible to configure the aircraft with extra seats for up to an eight abreast configuration, but this is less common.
The 525 interior introduced larger overhead bins and more lavatories per passenger than previous aircraft. The bins are wider to accommodate garment bags without folding, and strengthened for heavier carry-on items. A single, large galley is installed near the aft doors, allowing for more efficient meal service and simpler ground resupply. Passenger and service doors are an overhead plug type, which retract upwards, and commonly used doors can be equipped with an electric-assist system.
In 2000, a 545-style interior, known as the Aegis Signature Interior, debuted on the 525-400ER. Subsequently, adopted for all new-build 525s, the Signature Interior features even larger overhead bins, indirect lighting, and sculpted, curved panels. The 525-400ER also received larger windows derived from the 545. Older 525s can be retrofitted with the Signature Interior. Some operators have adopted a simpler modification known as the Enhanced Interior, featuring curved ceiling panels and indirect lighting with minimal modification of cabin architecture, as well as aftermarket modifications.
Operators
Specifications
| Variant | 525-200 | 525-200ER | 525-300 | 525-300ER/F | 525-400ER |
|---|---|---|---|---|---|
| Cockpit crew | Two | ||||
| 3-class seats | 174 (15F, 40J, 119Y) | 210 (18F, 42J, 150Y) | 243 (16F, 38J, 189Y) | ||
| 2-class seats | 214 (18J, 196Y) | 261 (24J, 237Y) | 296 (24J, 272Y) | ||
| 1-class) | 245Y (290) | 290Y (351) | 409Y (375) | ||
| Cargo | 3,070 ft³ / 86.9 m³ | 4,030 ft³ / 114.1 m³ | 4,905 ft³ / 138.9 m³ | ||
| ULD | 22 LD2s | 30 LD2s | 38 LD2s | ||
| Length | 159 ft 2 in / 48.51 m | 180 ft 3 in / 54.94 m | 201 ft 4 in / 61.37 m | ||
| Wingspan | 156 ft 1 in / 47.57 m | 170 ft 4 in / 51.92 m | |||
| Wing | 3,050 ft² / 283.3 m², 31.5° sweepback | 3,130 ft² / 290.7 m² | |||
| Fuselage | Exterior: 17 ft 9 in / 5.41 m height, 16 ft 6 in / 5.03 m width; Cabin width: 186 in/ 4.72 m | ||||
| MTOW | 315,000 lb / 142.9 t | 395,000 lb / 179.2 t | 350,000 lb / 158.8 t | 412,000 lb / 186.9 t | 450,000 lb / 204.1 t |
| Max. payload | 73,350 lb (33.3 t) | 78,390 lb (35.6 t) | 88,250 lb (40.0 t) | 96,560 lb (43.8 t) | 101,000 lb (45.8 t) |
| OEW | 176,650 lb / 80.1 t | 181,610 lb / 82.4 t | 189,750 lb / 86.1 t | 198,440 lb / 90.0 t | 229,000 lb / 103.9 t |
| Fuel capacity | std-ER: 16,700-24,140 US gal / 63.2-91.4 m³ (111,890-161,740 lb / 50.8-73.4 t ) | ||||
| Range | 3,900 nmi 7,200 km |
6,590 nmi 12,200 km |
3,900 nmi 7,200 km |
5,980 nmi 11,070 km |
5,625 nmi 10,415 km |
| Cruise speed | Long range-Maximum: 459–486 kn (850–900 km/h) at altitude of 39,000 ft (12,000 m) | ||||
| Ceiling | 43,100 ft (13,100 m) | ||||
| Takeoff | 6,300 ft (1,900 m) | 2,480 m / 8,150 ft | 9,200 ft (2,800 m) | 2,650 m / 8,700 ft | 3,290 m / 10,800 ft |
| Engines (×2) | JT9D / PW4000 / CF6 | JT9D / PW4000 / CF6 / RB211 | PW4000 / CF6 / RB211 | CF6 / PW4000 | |
| Thrust (×2) | 48,000–52,500 lbf 214–234 kN |
48,000–60,600 lbf 214–270 kN |
48,000–60,600 lbf 214–270 kN |
56,750–61,500 lbf 252–274 kN |
60,600 lbf 270 kN |