SD3-60 STRUCTURAL REPAIR MANUAL

Transcription

1 SRM DOORS - GENERAL 1. Introduction This chapter contains information on the identification and location of the access, cargo, and emergency exit doors, and provides information on the materials of construction and sealing. Limits of allowable damage, replacement of seals, and repair procedures are also included. If the repair is of a major nature Bombardier Aerospace (Belfast) will advise on the method and procedures necessary to carry out the repair, or to fit a new unit, and information may be obtained on request from the operator by the company's technical department. An Application for Repair Scheme/Damage Report document must be completed, as described in the INTRODUCTION to this manual. 2. General The aircraft contains the following doors:- - Passenger door (rear left) - Cargo door (forward left) - Emergency door (rear right) - Emergency exit (forward left) contained within cargo door (b) - Emergency exit (forward right) - Nose baggage compartment door - Aft baggage compartment door - Flight crew emergency exit - Internal flight compartment doors (forward passenger compartment bulkhead) In addition, the aircraft is provided with service doors in the nose fuselage, for access to the hydraulic and avionics bays. NOTE: Access doors are also provided at the rear of the left and right main landing gear fairings, for access to hydraulic connections, and pressure refuelling. These doors are of composite material construction, and repair to these materials is fully described. Refer to , pb1. the aircraft doors noted at (a) through (h) above are of conventional light alloy skin and stringer construction. If repair of doors is necessary, the procedures shown in this section are typical. Similarly, the seal replacement is also standard for (a), and (c) to (g) inclusive. Page 1

2 3. Internal Flight Compartment Doors The internal flight compartment sliding doors, are constructed from glass fibre faced 'Nomex' honeycomb panels. Repair to these materials is described. Refer to , pb1. This covers repair to "Fibrelam" floor panels, but are of a similar construction, and the same materials and procedures are applicable. It is to be noted however, that the covering of these doors with furnishing fabric, makes the repair to them difficult to achieve, and still retain the aesthetic appearance necessary for internal furnishings. This is particularly relevant to the fire retardent coverings fitted to later aircraft which are almost impossible to remove. Repairs to these sliding doors will therefore be at the discretion of the operator and replacement is the only effective repair procedure for serious damage. Page 2

3 SRM DOORS - ALLOWABLE DAMAGE 1. General The allowable damage for the aircraft doors are given in the following pages. These limits are typical for all doors and emergency exits on the SD3-60 aircraft. The limitations are given in tabular form as follows:- - Door Skin. Refer to Table Door Frame (see note). Refer to Table 102. Refer to , pb1. Definitions of types of damage (para 5). NOTE: As noted previously in Paragraph 1, damage beyond the allowable limits quoted in this section shall be referred to Bombardier Aerospace (Belfast). Minor (or cosmetic) repairs however, may be rectified, unless the operational capability of the aircraft is affected (e.g. when the door operating mechanism is prevented from functioning correctly, thus rendering the aircraft unsafe). Refer to , pb1. In such cases door replacement could prove more economical than grounding the aircraft for repair. Page 101

4 TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH MIN EDGE DIST INCHES MIN DIM FROM LINES OF FASTENER S OTHER LIMITATIONS REMEDIAL ACTION REQUIRED Isolated dents 1.50 x tb 10D min Dents smooth and free of cracks and delamination. No dents allowed in skin at frame station. Gouges, nicks, scratches and surface corrosion 0.10 x tb 0.50 max Must not extend over more than two adjacent fasteners, except where damage does not exceed depth of cladding. If beyond limits repair is required. Clean up damage Refer to , pb1. If beyond limits repair is required. Punctures Repair is required. Cracks Repair is required. owable damage - Door skin Table 101 NOTE: tb = thickness of skin Page 102

5 TYPE OF DAMAGE 'D' MAX DEPTH 'L' LENGTH MIN EDGE DIST INCHES MIN DIM FROM LINES OF FASTENERS OTHER LIMITATIONS REMEDIAL ACTION REQUIRED Isolated dents 1.50xtf 10D tf Dents smooth and free from cracks Gouges, nicks scratches and surface corrosion. If beyond limits repair is required. 1.10xtf 0.50 max Clean up damage Refer to , pb1. If beyond limits repair is required. Punctures Repair is required. Cracks (a) Radiating from lightening hole - Repair. Refer to , pb1. (b) Other crack - Repair is required. owable damage - Door frame Table 102 NOTE: tf = thickness of frame Page 103

6 SRM REPAIRS - DOORS 1. General The following pages contain details of approved typical permanent repairs suitable to the construction of all the doors on the SD3-60 aircraft. Reference must also be made to CHAPTER 51 for structural damage and repair practices of a general nature, and alternative materials, etc. CAUTION: THESE REPAIRS MAY AFFECT THE FATIGUE CRITICAL BASELINE STRUCTURE. REFER TO FOR FURTHER INFORMATION ON FCBS AND PROCEDURES TO BE FOLLOWED, PRIOR TO INCORPORATING ANY OF THESE REPAIRS. 2. List of Approved Repairs for External Doors: - Typical Door Member, Insertion Repair. Refer to Figure Typical External Patch & Stringer Insert. Refer to Figure Typical Repair to Door Structure. Refer to Figure 203. Page 201 Feb 01/10

7 Typical door member insertion repair Figure 201 Page 202

8 Typical external patch & stringer insert - Doors Figure 202 Page 203

9 Typical repair to door structure Figure 203 Page 204