216-01329-1 - Triumph Aerostructures Aircraft Component Hoisting Unit

216-01329-1 – Triumph Aerostructures Aircraft Component Hoisting Unit

Available now on the Airparts.aero Marketplace.

Overview

The Triumph Aerostructures 216-01329-1 is a flight-critical piece of Ground Support Equipment (GSE), specifically an OEM-engineered hoisting unit or lifting sling. This specialized tool is designed for the safe removal and installation of the inboard trailing edge flap on the Boeing 747-400 aircraft. Given the immense size, weight, and aerodynamic importance of a 747 flap, this is not a simple sling; it is a precision-engineered structural tool designed to securely attach to the flap at specific, load-bearing hardpoints. Its primary purpose is to ensure the component can be lifted and maneuvered without inducing any structural stress, bending, or damage to the flap's skin, internal structure, or sensitive trailing edge.

Constructed from high-strength steel and manufactured to exacting tolerances, the 216-01329-1 is designed to maintain the component's center of gravity and stability during the entire removal, transport, and installation process. It features multiple attachment points that interface directly with the flap's structure, ensuring the lifting loads are distributed exactly as intended by the airframe manufacturer. For any MRO or operator conducting heavy maintenance on a Boeing 747-400, this OEM tool is indispensable for safety, efficiency, and preventing damage to multi-million-dollar flight control surfaces.

Key Features

• OEM Certification: Genuine Triumph Aerostructures (formerly Vought Aircraft Industries) tool, built to the precise specifications required by Boeing.

• Component-Specific Design: Engineered exclusively for the Boeing 747-400 inboard trailing edge flap, ensuring a perfect and safe interface.

• Load-Distributing Structure: Spreads the lifting forces across multiple, reinforced hardpoints on the flap to prevent structural damage.

• Proof-Load Tested: Designed, manufactured, and tested to a safety factor well above the component's actual weight, in accordance with aerospace GSE standards.

• High-Strength Steel Construction: Fabricated from welded, high-grade structural steel for maximum strength, rigidity, and durability.

• Corrosion-Resistant Finish: Coated with a durable industrial finish to protect against corrosion and wear in the demanding hangar environment.

Technical Specifications

• Part Number: 216-01329-1

• Component Type: Hoisting Unit / Lifting Sling

• OEM Manufacturer: Triumph Aerostructures (Vought)

• Application: Removal & Installation of Boeing 747-400 Inboard Trailing Edge Flap

• Material: High-Strength Structural Steel.

• Finish: Industrial Enamel or Powder Coat.

• Rated Capacity: Specific to the weight of the B747-400 inboard flap. Must be verified on the tool's data plate.

• Governing Specifications: Manufactured to proprietary Triumph/Boeing engineering drawings and meets or exceeds ASME standards for lifting devices.

Aircraft Compatibility

This is a piece of Ground Support Equipment (GSE) and is not installed for flight. It is used during heavy maintenance on the following aircraft:

• Boeing: 747-400

Note: This tool is specific to the 747-400 inboard flap. Its use on other components or aircraft models is strictly prohibited. Always verify the correct GSE part number in the Aircraft Maintenance Manual (AMM).

Applications

• Flight Control Surface Removal: Used with an overhead crane or hoist to safely detach and lower the inboard flap from the wing.

• Flight Control Surface Installation: Provides a stable, controlled means of lifting and aligning the flap for attachment to the wing structure and actuator linkages.

• Component Transportation: Facilitates the safe transport of the flap between the aircraft and the maintenance shop.

Why Choose 216-01329-1?

Improperly lifting a large, heavy, and delicate aircraft component like a trailing edge flap is a direct path to catastrophic damage. A standard sling can crush the thin aluminum skin, bend the trailing edge, or apply stress to areas not designed to carry the load, leading to a multi-million-dollar scrap event. The Triumph 216-01329-1 is the OEM-mandated tool, co-engineered with the aircraft's structure. It guarantees that lifting forces are applied only to the designated hardpoints. Using this certified, proof-load tested hoisting unit eliminates guesswork, ensures the safety of maintenance personnel, and protects the integrity of the flight-critical component.

The engineering design of the 216-01329-1 hoisting unit is critically dependent on the principles of structural mechanics and load path management. The fixture is not merely a hook, but a rigid space frame designed to act as an intermediate structure between the crane's single lift point and the flap's multiple attachment points. Finite Element Analysis (FEA) is used during the design phase to model the stresses not only within the tool itself but also the stresses it induces in the aircraft component. The geometry of the hoist is precisely calculated to orient the lifting cables and attachment lugs at specific angles. This ensures that the applied forces resolve into pure tensile loads at the flap's hardpoints, minimizing any parasitic shear or bending moments that could damage the component's internal ribs, spars, or delicate honeycomb structures. The unit must also be designed to hold the component at a specific pitch and roll attitude that facilitates alignment with the wing's track and carriage system during the delicate installation process.

Note: The 216-01329-1 is a piece of critical lifting equipment. It must be visually inspected for damage, cracks, or distortion before each use. It is also subject to periodic inspection and re-certification (proof-load testing) in accordance with manufacturer recommendations and local safety regulations (e.g., OSHA, ASME). Operation must only be performed by trained and qualified personnel in strict accordance with the Boeing 747-400 Aircraft Maintenance Manual (AMM) procedures.

Documentation

No public-facing OEM or regulatory documentation was located for this specific part number. All authoritative data, including rated capacity, inspection criteria, and detailed procedures, are contained within the proprietary Boeing 747-400 Aircraft Maintenance Manual (AMM) and the tool manufacturer's certification documents.