McDonnell Model 119 / 220 — Technical Archive Collection

Originally engineered by McDonnell Aircraft Corporation before its 1967 merger with Douglas, the Model 119 — later marketed as the Model 220 — represents one of the most technically ambitious utility transport and business jet prototypes of the late 1950s. Defined by its distinctive four-engine underwing podded layout, the aircraft was a bold departure from conventional twin-engine executive jet design and remains a rare subject in primary-source aviation documentation.

⚠️ Regulatory Notice

Under FAA 14 CFR § 43.13 and EASA Part-M, any mechanic performing maintenance on an active aircraft must use current, manufacturer-approved revision-controlled data. This archival document does not satisfy that requirement.

Document Manifest

• McDonnell UCX — Hydraulic System Schematic (Report No. 5708, 21 October 1957)
• McDonnell UCX — Controls Technical Description (Report No. 5708, 21 October 1957)
• McDonnell UCX — Electrical System & Schematic (Report No. 5708, 21 October 1957)
• McDonnell UCX — Hydraulic & Landing Gear System (Report No. 5708, 21 October 1957)
• McDonnell Model 119 — General Arrangement Drawing (Report No. 5708, 21 October 1957)
• McDonnell Model 119 / 220 — Memento Booklet (promotional/technical overview)
• McDonnell Model 119A — Pilot's Handbook
• McDonnell Model 220 — Pilot's Handbook
• McDonnell Model 119A — USAF Flight Evaluation Report
• McDonnell Model 119 — Aircraft Estimated Performance Manual (multiple performance data sheets)

This collection contains 10 unique primary-source documents.

Aerodynamic Configuration

• Wing: Low-mounted, swept 35° along the leading edge for optimal transonic Mach cruise efficiency.
• Control Surfaces: Conventional trailing-edge ailerons paired with wing-mounted spoilers for roll control and high-speed braking (spoiler-speedbrake travel: 60°).
• Tail Unit: Single vertical fin with low-mounted horizontal stabilizers, matching sweepback and clipped tips for pitch authority.
• Vortex Alleviation: Unique square engine intakes engineered to prevent ground vortex formation and mitigate runway suction.

Engine Technical Notes

• Prototype Propulsion: Four Westinghouse J34-WE-22 turbojet engines, 2,980 lbf thrust each as installed.
• Engine Substitution: Fairchild J83 program cancelled late 1958; Westinghouse J34 substituted during development.
• Production Variants: Certified and planned for Pratt & Whitney JT12 or General Electric CF700 turbofans.
• Pylon System: Structural pylons reinforced as impact skids, isolating catastrophic engine failures and protecting wing fuel tanks.

Handling & Stability

• Centre of Gravity: Underwing engine placement isolated heavy mass elements on the aircraft CG line.
• Wing Loading: 74.4 lb/ft² — stabilised high-altitude cruise; necessitated faster, precise landing approach profiles.
• FOD Susceptibility: Low-slung pods raised significant USAF concerns regarding Foreign Object Damage during unpaved operations.
• Safety Certification: Class I FAA provisional type certificate achieved 17 October 1960, meeting strict transport category stability standards.

Performance Data — Model 119 Estimated Performance Manual

General Arrangement — Model 119

• Powerplant: Four Fairchild J83-R-1 engines (prototype spec); alternate: four General Electric J-85
• Wingspan: 57 ft 1 in
• Length: 66 ft 6 in
• Height: 23 ft 8 in
• Main Gear Tires: 36 × 11 Type VII — 140 PSI (normal)
• Nose Gear Tires: 18 × 5.5 Type VII — 125 PSI (normal)

Engineering Bulletins & Programme History

• Cabin Layouts: 10-seat executive configuration or 26–29 passenger 3-abreast regional layout.
• Cockpit: Dual control column and rudder pedal system; wide "greenhouse" glass arrays for maximum pilot visibility.
• Programme Termination: Following a failed commercial lease agreement with Pan American World Airways, further airframe assemblies were halted.
• Airframe Status: Sole flyable prototype (N4AZ) transferred to research groups for crash survival testing before entering private storage.

This is an archival, static-copy edition fixed at its original publication date. Intended for historical reference, flight simulation, museum restoration, and educational use only. Not approved for active airworthiness maintenance under FAA 14 CFR § 43.13, EASA Part-M, or equivalent international regulations. Operators of active aircraft must use current, revision-controlled publications from the Type Certificate holder or an authorised distributor.

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