AIRPLANE MAINTENANCE MANUAL For the CIRRUS DESIGN SR22 SR CIRRUS DESIGN INCORPORATED 4515 Taylor Circle Duluth, MN 55811 FAA APPROVAL HAS BEEN OBTAINED ON THE TECHNICAL DATA IN THIS PUBLICATION THAT AFFECTS AIRPLANE TYPE DESIGN.
Log of Revisions Revision Number 13773-001 30 Nov 2000 Issue Date Date Inserted Inserted By Revision Number Issue Date Date Inserted Inserted By AMM-RevLog Page 1
Log of Temporary Revisions TR Number 13773-001 30 Nov 2000 Issue Date Date Inserted Inserted By Date Removed Removed By AMM-TmpRevLog Page 1
INTRODUCTION 1. COVERAGE This Cirrus Design SR22 Airplane Maintenance Manual was prepared by Cirrus Design Technical Publications. This manual contains information necessary to enable a trained mechanic to inspect, service, clean, trouble shoot, functionally test, and repair systems and equipment in the Cirrus Design SR22.
4. LIST OF PUBLICATIONS The following publications should be used in conjunction with this manual: Manual No.
Manual No. Manual Title - Miscellaneous Manufacture 13775-001 SR22 Wiring Manual Cirrus Design Corporation GSM-590 Gill Battery Service Manual Teledyne 9/94 Model E-01 ELT Installation and Operation Manual ACK Technologies Document No. I-194 Inspection Intervals for Filters Brackett Aircraft Technologies 5. REVISIONS This manual has been prepared in loose-leaf form for ease in inserting revisions.
CHAPTER AIRWORTHINESS LIMITATIONS
CHAPTER 4 - AIRWORTHINESS LIMITATIONS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 4-LOEP 1 31 JULY 2001 4-TOC 1 31 JULY 2001 4-00 1 31 JULY 2001 4-00 2 31 JULY 2001 4-00 3 31 JULY 2001 13773-001 31 July 2001 4-LOEP Page 1
CHAPTER 4 - AIRWORTHINESS LIMITATIONS TABLE OF CONTENTS Subject AIRWORTHINESS LIMITATIONS Chapter/Section Page 4-00 General 1 Maintenance Limitations Replacement Limitations Structural Limitations Description 1 1 1 2 Maintenance Limitations Replacement Limitations Structural Limitations 2 2 3 13773-001 31 July 2001 4-TOC Page 1
AIRWORTHINESS LIMITATIONS 1. GENERAL The Airworthiness Limitations Section is FAA approved and specifies inspection and maintenance required under paragraphs 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. This chapter outlines the maximum replacement intervals and/or maintenance requirements for aircraft components, systems, and structures determined to be life limited and/or require monitoring through scheduled maintenance.
2. DESCRIPTION A. Maintenance Limitations (1) The scheduled maintenance requirements listed below are also included in AMM 5-20 (Scheduled Maintenance Checks). The following criteria must be adhered to: (a) Paint Finish To ensure that the temperature of the composite structure is kept below 150 degrees Fahrenheit, the maximum allowable paint on the wing will have an absorptivity not greater than 0.4, with an emissivity of at least 0.9.
C. Structural Limitations The certification requirements of FAR 23.573 require that the composite airframe structure, cabin, wing, empennage their carry thru, and attaching structure whose failure would be catastrophic must be designed to damage tolerant criteria. Damage tolerant certification for the selected airframe life of 4350 flight hours has been established for all of the affected parts with no special structural limitations or inspections.
CHAPTER TIME LIMITS AND MAINTENANCE CHECKS
CHAPTER 5 - TIME LIMITS/MAINTENANCE PRACTICES LIST OF EFFECTIVE PAGES Chapter/Section Page Date 5-LOEP 1 31 JULY 2001 5-TOC 1 31 JULY 2001 5-TOC 2 31 JULY 2001 5-00 1 30 NOV 2000 5-10 1 31 JULY 2001 5-10 2 31 JULY 2001 5-20 1 30 NOV 2000 5-20 2 30 NOV 2000 5-20 3 31 JULY 2001 5-20 4 31 JULY 2001 5-20 5 31 JULY 2001 5-20 6 31 JULY 2001 5-20 7 31 JULY 2001 5-20 8 31 JULY 2001 5-20 9 31 JULY 2001 5-20 10 31 JULY 2001 5-20 11 31 JULY 2001 5-20 12 31 JULY 2
CHAPTER 5 - TIME LIMITS/MAINTENANCE PRACTICES TABLE OF CONTENTS Subject TIME LIMITS AND MAINTENANCE CHECKS Chapter/Section Page 5-00 General 1 Annual Inspections 1 100-Hour Inspections 1 Unscheduled Maintenance Checks 1 Special Conditions - Cautionary Notice 1 OVERHAUL AND REPLACEMENT SCHEDULE 5-10 Description SCHEDULED MAINTENANCE CHECKS 1 5-20 Description 1 Inspection Groups and Criteria 1 Visual Inspection Moving Parts Composite Parts Metal Parts Fuel, Air, and Hydraulic Oil Lines a
CHAPTER 5 - TIME LIMITS/MAINTENANCE PRACTICES TABLE OF CONTENTS Subject Chapter/Section UNSCHEDULED MAINTENANCE CHECKS Page 5-50 Description 1 Hard/Overweight Landings Overspeed Severe Air Turbulence or Severe Maneuvers Lightning Strike High Drag/Side Loads Due to Ground Handling Maintenance Practices 1 1 1 1 1 2 Hard/Overweight Landing Landing Gear Wings Overspeed Landing gear Fuselage Cowling Stabilizers Wings Severe Turbulence and/or Maneuvers Stabilizers Wing Lightning Strike Communications Nav
TIME LIMITS AND MAINTENANCE CHECKS 1. GENERAL This chapter outlines the recommended intervals for overhaul and replacement of components, scheduled and unscheduled maintenance, and annual inspections. The following Scheduled Maintenance Check table shows the recommended intervals at which items are to be inspected based on normal usage under average environmental conditions. 2. ANNUAL INSPECTIONS As required by Federal Aviation Regulation Part 91.
OVERHAUL AND REPLACEMENT SCHEDULE 1. DESCRIPTION The following components must be overhauled or replaced at the specified intervals. To ensure correct observation of these times, the date of removal, installation, or overhaul of such components as well as the airplanes flight hours must be entered into the Service Time Record filed in the Airplane Maintenance Log. Item Interval Replc. O’haul Notes 1. Engine Per Manufacturer.
Item (Continued) Interval Replc. O’haul Notes 16. Emergency Locator Transmitter Batteries Batteries at 50 percent of useful life or after 1 hour use - whichever comes first ❍ Refer to ACK Technologies Model E-01 Installation and Operation Manual. 17. Fire Extinguisher 20 Years ❍ Refer to Chapter 26-20. 18. Cirrus Airframe Parachute System 10 Years (CAPS) Rocket Motor ❍ Replace with new unit. Refer to Chapter 95 Special Purpose Equipment for CAPS maintenance practices. 19.
SCHEDULED MAINTENANCE CHECKS 1. DESCRIPTION The owner and/or operator is primarily responsible for maintaining the airplane in an airworthy condition. This includes compliance with all applicable Airworthiness Directives. It is further the responsibility of the owner or operator to ensure the that the airplane is inspected as specified in Parts 43 and 91 of the Federal Aviation Regulations.
(3) Metal Parts Security, condition of finish, cleanliness, distortion, fatigue cracks, welding cracks, corrosion, and any other apparent damage. (4) Fuel, Air, and Hydraulic Oil Lines and Hoses Cracks, dents, kinks, loss of flexibility, deterioration, obstruction, chaffing, improper bend radius, cleanliness, security, and any other apparent damage.
Scheduled Inspection Report Make Cirrus Design Model SR22 Serial Number Owner Date Type of Inspection Hobbs Time Note: Registration Number All references to “5-20” under the Chap-Sect column are to be understood as reference to Visual Inspection criteria defined above under Inspection Groups and Criteria. Pre-Inspection Chap-Sect Interval Initials Reference 100 Special - ❍ 2. Airplane Interior Clean and vacuum. 12-20 ❍ 3. Fuselage and Empennage Clean. 12-20 ❍ 4.
Chap-Sect Reference Engine Group 1. 25 Hour Inspection After first 25 hours of operation on new, rebuilt, or overhauled engine, perform complete 100-Hour Engine Inspection in accordance with Teledyne Continentals Motors Maintenance Manual, Section 5. Interval Initials 100 Special Manual No. X30634A 1st 25 Hrs 2. Engine Cowling Visual Inspection for cracks, distortion, and loose or missing fasteners. 5-20 ❍ 3.
Engine Group (Continued) Chap-Sect Reference Interval Initials 100 Special 13. Spark Plugs Manual No. Inspect, clean, re-gap and rotate in accordance with Teledyne Conti- X30634A nentals Motors Maintenance Manual, Section 12. ❍ 14. Spark Plug Cable Leads Visual Inspection for corrosion and deposits. 5-20 ❍ 15. Cylinder Cooling Fins Visual Inspection for cracking, bending, and general condition. 5-20 ❍ 16. Engine Baffling and Seals Visual Inspection for cracks, tears, and rips.
Engine Group (Continued) Chap-Sect Reference Interval Initials 100 Special 27. Fuel Injection System Functional Inspection of Fuel Injection System in accordance with Teledyne Continentals Motors Service Information Directive 97-3 every 100 hours and after engine installation or fuel system component replacement. SID97-3 ❍ Engine Install or Fuel Sys Cmpnt Rplcmnt 28. Exhaust System Perform Inspection/Check for cracks, dents, missing parts, security, and corrosion. 78-20 ❍ 50 Hrs 29.
Propeller Group Chap-Sect Interval Initials Reference 100 Special 1. Spinner Remove, clean and perform Visual Inspection for cracks and corrosion. 5-20 ❍ 2. Spinner Backing Plate Visual Inspection for condition. 5-20 ❍ 3. Blades Visual Inspection for nicks, bends, cracks, and condition of tips. 5-20 ❍ 4. Blades Inspect blades for radial play or movement of blade tip. 61-10 ❍ 5. Propeller Assembly Manual No. Lubricate in accordance with Hartzell Propeller Owner’s Manual and 115N Log Book.
Cabin Group (Continued) Chap-Sect Reference Interval Initials 100 Special 10. Parking Brake Valve and Control Knob Visual Inspection for leaks, security, chafing, and condition. 5-20 ❍ 11. Flexible Brake Lines Visual Inspection for leaks, security, and condition. 5-20 ❍ 12. Fuel Selector Visual Inspection for operation. 5-20 ❍ 13. Avionics Visual Inspection of components, wiring, and for security. 5-20 ❍ 14. Turn and Bank Indicator Batteries Replace. 24-30 Annual 15.
Cabin Group (Continued) Chap-Sect Reference Interval Initials 100 Special 26. Cable Attachments, Cables, and Pulleys Visual Inspection for security, chafing, wear, and general condition. 5-20 ❍ 27. Wing Attachment Bolts Visual Inspection for condition, fit, and evidence of distress. 5-20 ❍ 28. Flap Actuation Motor and Attach Bracket Visual inspection for condition and security. 5-20 ❍ 29. Fuselage Drainage Holes Visual Inspection for obstructions or blockage. 5-20 ❍ 30.
Fuselage and Empennage Group Chap-Sect Reference Interval Initials 100 Special 1. Skin Visual Inspection for general condition, deterioration, delamination, distortion, cracks, paint condition, and other evidence of failure. 5-20 ❍ 2. CAPS Exit Cover Visual Inspection of perimeter for cracking or crazing. 5-20 ❍ 3. Vertical Stabilizer and Rudder Surfaces Visual Inspection for distortion, and condition. 5-20 ❍ 4.
Wing Group (Continued) Chap-Sect Reference Interval Initials 100 Special 5. Walkway Visual Inspection for condition. 5-20 ❍ 6. Aileron Surfaces Visual Inspection for distortion, and condition. 5-20 ❍ 7. Aileron System Rigging Perform Inspection/Check for gap tolerances, cable tension, system alignment, and security. 27-10 ❍ 8. Aileron Actuation Arm Visual Inspection for safetying, and condition. 5-20 ❍ 9.
Landing Gear Group (Continued) Chap-Sect Reference Interval Initials 100 Special 2. Tires Visual Inspection for cuts, uneven or excessive wear, and slippage. 5-20 ❍ 3. Tires Inspect for proper tire pressure. 12-10 ❍ 4. Brake System Check system for proper operation. 5-20 ❍ 5. Brake System Perform Inspection/Check for disk and lining wear, condition, and evidence of distress. 32-42 ❍ 6. Flexible Brake Lines Visual Inspection for leaks, security, and condition. 5-20 ❍ 7.
Return to Service 1. - Install Engine Cowling. - Install Landing Gear Fairings. - Install Fuselage Access Panels. - Install Cabin Seats. - Install Cabin Carpet. - Install Cabin Access Panels. - Install Wing Access Panels LW1, LW2, LW4, LW5, LW6, LW7, LW8, LW9, LW12, LW13, LW14, LW15, and RW1, RW2, RW4, RW5, RW6, RW7, RW8, RW9, RW12, RW13, RW14. Chap-Sect Reference 71-10 32-00 6-00 25-10 25-10 6-00 6-00 Interval Initials 100 Special ❍ 2.
AIRPLANE OPERATIONAL AND FUNCTIONAL CHECK 1. DESCRIPTION The following check must be performed before and after the Scheduled Maintenance Inspection to detect any airplane abnormalities or malfunctions. A portion of the check is accomplished with the engine running and warmed up. WARNING: In order to perform the following check the engine must be operating. Do not stand or let anyone else stand close to the arc of the airplane’s propeller while conducted this check.
Operational Inspection Report 1. Flight Controls Check for full range of travel and excessive friction. Visual Inspection for obstructions. 2. Flaps Operate through full extension and retraction for steady and complete deployment. Flap position light illuminates at the retracted, 50%, and 100% positions. 3. Trim Controls Aileron trim functions fully left and right without rudder movement caused by the rudder-aileron interconnect. Check for full range of travel and excessive friction. 4.
Operational Inspection Report (Continued) 8. Communications Transceivers Verify the communications capability on both the high and low ends of the VHF COM band. 9. Start Engine (Refer to POH Section 4) Starter spins propeller rapidly without slipping or dragging. Set engine speed at 1000 RPM. Chk’d Notes 10. Oil Pressure Indicates pressure in the green arc within 30 seconds. If extremely cold, oil pressure may be in yellow arc for one to two minutes. 11.
Operational Inspection Report (Continued) Chk’d Notes 18. Brakes Rudder pedal brakes should hold airplane stationary with no slipping at full power. Parking brake should hold airplane stationary with no slipping at full power. 19. Oil and Cylinder Head Temperatures Verify temperatures indicate in the green arc. 20. Fuel Flow Advance throttle to full forward. Verify fuel flow indicates approximately 28 gal/hr. 21. Engine Idle Move throttle control lever to full aft.
UNSCHEDULED MAINTENANCE CHECKS 1. DESCRIPTION During operation, the airplane may be subject to: A. Hard/Overweight Landings A hard landing is any landing made at what is believed to be an excessive sink rate. An overweight landing is defined as landing the airplane at any gross weight which exceeds the maximum take-off weight as specified in the Pilot’s Operating Handbook and the Airplane Flight Manual. B.
2. MAINTENANCE PRACTICES A. Hard/Overweight Landing Note: (1) (2) If the hard/overweight landing is combined with high drag/side loads, additional checks are required. Landing Gear (a) Main gear struts - Inspect for security of attachment, permanent deformation, delamination, and cracking or splintering of strut.
(c) (2) Elevator and rudder balance weight supporting structure - Inspect for security, loose or failed fasteners, and evidence of structural damage. Wing (a) Wing to body fittings and supporting structure - Inspect for security, loose or failed fasteners, and evidence of structural damage. (b) Trailing Edge - Inspect for and deformation affecting normal operation of flap and aileron. D.
F. High Drag/Side Loads Due to Ground Handling (1) (2) Page 4 Landing Gear (a) Main gear and fairings - Inspect for loose or failed fasteners, buckling, security, cracks, and evidence of structural damage. (b) Nose gear and fairing - Inspect for loose or failed fasteners, cracks, security, buckling, and evidence of structural damage. Wings (a) Wing to fuselage fittings and attaching structure - Inspect for security, loose or failed fasteners, and evidence of structural failure.
CHAPTER DIMENSIONS AND AREAS
CHAPTER 6 - DIMENSIONS AND AREAS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 6-LOEP 1 30 NOV 2000 6-TOC 1 30 NOV 2000 6-00 1 30 NOV 2000 6-00 2 30 NOV 2000 6-00 3 30 NOV 2000 6-00 4 30 NOV 2000 6-00 5 30 NOV 2000 6-00 6 30 NOV 2000 6-00 7 30 NOV 2000 6-00 8 30 NOV 2000 6-00 9 30 NOV 2000 6-00 10 30 NOV 2000 13773-001 30 Nov 2000 6-LOEP Page 1
CHAPTER 6 - DIMENSIONS AND AREAS TABLE OF CONTENTS Subject DIMENSIONS AND AREAS Chapter/Section Page 6-00 General 1 Airplane Dimensions and Areas 1 General Cabin Wings Flaps Ailerons Horizontal Stabilizer Elevator Vertical Stabilizer Rudder Landing Gear Access Panels 1 1 1 1 1 2 2 2 2 2 2 Cabin Floor Wing Empennage Control Surface Travels And Cable Tension Settings 2 2 2 2 Aileron Elevator Rudder Flaps 13773-001 30 Nov 2000 2 2 3 3 6-TOC Page 1
DIMENSIONS AND AREAS 1. GENERAL This section describes those diagrams and text which shows the area, dimensions, stations, access doors, and physical locations of the structural members of the airplane. Also included is the cardinal rigging dimensions. 2. AIRPLANE DIMENSIONS AND AREAS The airplane is divided into reference points in inches. These reference points provide a means of quickly identifying the locations of components. Three axes are used as reference points.
F. Horizontal Stabilizer Span .................................................................................................... 13.17 ft ..................... 4.01 m Area..................................................................................................... 25.75 ft².................... 2.39 m² Aspect Ratio .......................................................................................... 5.59 ........................ 5.59 G. Elevator Span .........................................
C. Rudder Maximum Right Rudder Deflection:20.0° +/- 1.0° Maximum Left Rudder Deflection:20.0° +/- 1.0° D. Flaps Flap UP:0.0° +/- 0.5° Flap 50%:16.0° +/- 0.5° Flap 100%32.0° +/- 0.
Figure 6-001 Airplane Principal Dimension Page 4 6-00 13773-001 30 Nov 2000
Figure 6-002 Fuselage Stations 13773-001 30 Nov 2000 6-00 Page 5
Figure 6-003 Wing Stations Page 6 6-00 13773-001 30 Nov 2000
Figure 6-004 Elevator Stations 13773-001 30 Nov 2000 6-00 Page 7
Figure 6-005 Floor Access Panels Page 8 6-00 13773-001 30 Nov 2000
Figure 6-006 Wing Access Panels 13773-001 30 Nov 2000 6-00 Page 9
Figure 6-007 Empennage Access Panels Page 10 6-00 13773-001 30 Nov 2000
CHAPTER LIFTING AND SHORING
CHAPTER 7 - LIFTING AND SHORING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 7-LOEP 1 30 NOV 2000 7-TOC 1 30 NOV 2000 7-00 1 30 NOV 2000 7-10 1 30 NOV 2000 7-10 2 30 NOV 2000 7-20 1 30 NOV 2000 13773-001 30 Nov 2000 7-LOEP Page 1
CHAPTER 7 - LIFTING AND SHORING TABLE OF CONTENTS Subject LIFTING AND SHORING Chapter/Section Page 7-00 General JACKING 1 7-10 Description 1 Maintenance Practices 1 Jacking the Airplane Raise Airplane Lower Airplane 1 1 1 HOISTING 7-20 Description 1 Maintenance Practices 1 Hoisting The Airplane Raise Airplane Lower Airplane 13773-001 30 Nov 2000 1 1 1 7-TOC Page 1
LIFTING AND SHORING 1. GENERAL This chapter describes the materials necessary to lift and shore the airplane for maintenance, overhaul, repair, and abnormal conditions such as collapsed gear. The entire airplane may be lifted by using standard aircraft hydraulic jacks in conjunction with jack pads at the jack points provided on the fuselage and wings. The jacking site, when possible, should be on level ground and should be protected from wind, preferably inside a hanger.
JACKING 1. DESCRIPTION Three jack points, located at each wing tiedown and empennage tiedown, are provided to perform maintenance operations. Tie-down rings must be removed and replaced with jack points prior to lifting. Jack points are stowed in the baggage compartment. The airplane may be jacked using two standard aircraft hydraulic jacks at the wing jacking points and a weighted tailstand attached to the tail tiedown. 2. MAINTENANCE PRACTICES A.
Figure 7-101 Lifting and Jacking Points Page 2 7-10 13773-001 30 Nov 2000
HOISTING 1. DESCRIPTION This chapter describes those instructions necessary to support the airplane during maintenance and repair. In some instances (i.e. off-runway landing, collapsed gear, etc.) it may be necessary to lift the airplane using hoisting straps. 2. MAINTENANCE PRACTICES A. Hoisting The Airplane (See Figure 7-101) (1) Raise Airplane (a) Acquire necessary tools, equipment, and supplies.
CHAPTER LEVELING AND WEIGHING
CHAPTER 8 - LEVELING AND WEIGHING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 8-LOEP 1 30 NOV 2000 8-TOC 1 30 NOV 2000 8-00 1 30 NOV 2000 8-10 1 30 NOV 2000 8-20 1 30 NOV 2000 8-20 2 30 NOV 2000 8-20 3 30 NOV 2000 13773-001 30 Nov 2000 8-LOEP Page 1
CHAPTER 8 - LEVELING AND WEIGHING TABLE OF CONTENTS Subject LEVELING AND WEIGHING Chapter/Section Page 8-00 General LEVELING 1 8-10 Description 1 Maintenance Practices 1 Leveling the Airplane Longitudinal Leveling - Spirit Level Using Pilot’s Door Sill Longitudinal Leveling - Optical Level Using Fuselage Leveling Points Lateral Leveling WEIGHING 1 1 1 1 8-20 Description 1 Maintenance Practices 1 Weighing the Airplane Preparation Weighing Measuring 13773-001 30 Nov 2000 1 1 1 1 8-TOC Pag
LEVELING AND WEIGHING 1. GENERAL This chapter provides information necessary to properly level and weigh the airplane for any of the various maintenance, overhaul, or major repairs which might become necessary. To obtain the expected flight performance, flight characteristics, and flight safety, the airplane must be operated within the permissible load and center of gravity envelope.
LEVELING 1. DESCRIPTION This chapter provides information necessary to properly level the airplane for any of the various maintenance, overhaul, or major repairs which might become necessary. The cabin door sill edge is parallel within 0.10° relative waterline 100. The door sill is used in conjunction with a spirit level to determine airplane ground attitude. Two forward leveling points are located on either side of the cowl at fuselage station 99.00.
Figure 8-101 Airplane Leveling Page 2 8-10 13773-001 30 Nov 2000
WEIGHING 1. DESCRIPTION This chapter provides information necessary to properly weigh the airplane for any of the various maintenance, overhaul, or major repairs which might become necessary. To obtain the expected flight performance, flight characteristics, and flight safety, the airplane must be operated within the permissible load and center of gravity envelope.
(c) (d) (e) (f) (g) (h) Page 2 surements. Subtract this measurement from dimension ‘A’ to obtain the nose wheel weighting point arm (dimension ‘B’). Determine and record the moment for each of the main nose gear weighting points using the following formula: Moment = Net Weight x Arm Calculate and record the as-weighed C.G. weight and moment by totaling the appropriate columns. Determine and record the as-weighed C.G. in inches aft of datum using the following formula: C.G.
Weighing Point Scale Reading = Net Weight - Tare X Arm Left Main A= Right Main A= Nose Gear B= Total As Weighed CG = = Moment CG = Total Moment + Total Weight Space below provided for additions or subtractions to as weighed condition. Empty Weight CG = Engine Oil (if oil drained) 15 lb at FS 79.3, Moment = 1176 Unusable Fuel 18.0 Basic Empty Weight 154.9 2788 CG = C.G. % MAC = 100 x(C.G. Inches - LEMAC)/MAC = 100 x(C.G. Inches - 133.1)/47.
CHAPTER TOWING AND TAXIING
CHAPTER 9 - TOWING AND TAXIING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 9-LOEP 1 30 NOV 2000 9-TOC 1 30 NOV 2000 9-00 1 30 NOV 2000 9-10 1 30 NOV 2000 9-10 2 30 NOV 2000 9-10 3 30 NOV 2000 9-20 1 30 NOV 2000 13773-001 30 Nov 2000 9-LOEP Page 1
CHAPTER 9 - TOWING AND TAXIING TABLE OF CONTENTS Subject TOWING AND TAXIING Chapter/Section Page 9-00 General TOWING 1 9-10 Description 1 Maintenance Practices 1 Airplane Towing Towing Manually Towing With Tow Vehicle TAXIING 1 1 1 9-20 Description 1 Maintenance Practices 1 Airplane Taxiing 13773-001 30 Nov 2000 1 9-TOC Page 1
TOWING AND TAXIING 1. GENERAL This chapter provides instructions necessary to tow and taxi the airplane. Movement of the airplane on the ground is accomplished using the manufacturer supplied, yoke-type tow bar, power equipment that will not damage or excessively strain the nose gear steering assembly, or by taxiing. One person is capable of moving the airplane on a smooth, level surface using the tow bar.
TOWING 1. DESCRIPTION This chapter provides instructions necessary to tow the airplane by hand or with tow vehicle. 2. MAINTENANCE PRACTICES A. Airplane Towing (1) Towing Manually CAUTION: (a) During the towing operation, do not turn the nose gear beyond its steering radius on either side of center. Exceeding the steering radius will result in damage to the nose gear and steering mechanism. (See Figure 9-101) Acquire necessary tools, equipment, and supplies.
(g) (h) (i) Page 2 Position chocks in front of tires. Remove tow bar from tow vehicle and airplane. Set parking brake.
Figure 9-101 Minimum Turning Radius 13773-001 30 Nov 2000 9-10 Page 3
TAXIING 1. DESCRIPTION This chapter provides instructions necessary to taxi the aircraft. The airplane is controlled with toe operated brakes during taxiing. 2. MAINTENANCE PRACTICES A. Airplane Taxiing Note: Engine starting, taxiing, and shut-down may only be performed by authorized personnel. CAUTION: During the towing operation, do not turn the nose gear beyond its steering radius on either side of center. Exceeding the steering radius will result in damage to the nose gear and steering mechanism.
CHAPTER PARKING AND MOORING
CHAPTER 10 - PARKING AND MOORING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 10-TOC 1 30 NOV 2000 10-LOEP 1 30 NOV 2000 10-00 1 30 NOV 2000 10-10 1 30 NOV 2000 10-10 2 30 NOV 2000 10-20 1 30 NOV 2000 10-20 2 30 NOV 2000 10-30 1 30 NOV 2000 10-30 2 30 NOV 2000 10-30 3 30 NOV 2000 13773-001 30 Nov 2000 10-LOEP Page 1
CHAPTER 10 - PARKING AND MOORING TABLE OF CONTENTS Subject PARKING AND MOORING Chapter/Section Page 10-00 General PARKING 1 10-10 Description 1 Maintenance Practices 1 Parking Temporary Parking or Mild Weather Long Term Parking or Severe Weather MOORING 1 1 1 10-20 General 1 Maintenance Practices 1 Mooring Temporary and Mild Weather Conditions Mooring, Long Term and Severe Weather Conditions STORAGE 1 1 1 10-30 General 1 Maintenance Practices 1 Storage Temporary Storage - 30 to 90 Days
PARKING AND MOORING 1. GENERAL This chapter provides instructions necessary to park and moor the aircraft in any of the probable conditions to which it may be subjected. Mooring procedures should be followed if anticipating high winds, or when the airplane is to remain outside for extended periods of time. In addition, this chapter also includes instructions for short and long term storage.
PARKING 1. DESCRIPTION This chapter provides instructions necessary to park or store the airplane in any of the probable conditions to which it may be subjected. Maintenance practices necessary to prepare the aircraft for parking and mooring are included. 2. MAINTENANCE PRACTICES A. Parking (1) Temporary Parking or Mild Weather (See Figure 10-101) (a) Acquire necessary tools, equipment, and supplies. Description (b) (2) Purpose - Any Source Tow the airplane.
Figure 10-101 Parking and Mooring - Fair Weather Page 2 10-10 13773-001 30 Nov 2000
MOORING 1. GENERAL This chapter provides instructions necessary to moor the airplane. Three fixed mooring points are provided on the airplane. Two are located on the underside of the wings and a third is located on the underside of the empennage directly below the horizontal stabilizer 2. MAINTENANCE PRACTICES A. Mooring (1) Temporary and Mild Weather Conditions (See Figure 10-101) (a) Acquire necessary tools, equipment, and supplies.
Figure 10-201 Parking and Mooring - Long Term Page 2 10-20 13773-001 30 Nov 2000
STORAGE 1. GENERAL This chapter provides instruction necessary to store the airplane for temporary or long-term durations. 2. MAINTENANCE PRACTICES A. Storage (1) (2) Temporary Storage - 30 to 90 Days (a) Parking and Mooring 1 Park and moor airplane. (Refer to 10-20) (b) Engine Preservation 1 Refer to the Teledyne Continental Motors Maintenance and Operator’s Manual listed in the List of Publications in the front of this publication. (c) Fuel Supply 1 The fuel tank must be completely filled.
(b) (c) (d) 1 Park and moor airplane. (Refer to 10-20) Engine Preservation 1 Refer to the Teledyne Continental Motors Maintenance and Operator’s Manual listed in the List of Publications in the front of this publication. Fuel Supply 1 Drain fuel tanks. (Refer to 12-10) Landing Gear, Wheels, and Tires 1 Clean brake assemblies. 2 The wheels should be turned three to four revolutions per 30 days to prevent corrosion. 3 Touch up all spots where paint has been chipped from the wheels.
WARNING: (f) (g) (h) 13773-001 30 Nov 2000 Before rotating the propeller blades, make certain the magneto/start switch is OFF, throttle is in CLOSED position, and the mixture control is in the IDLE CUT-OFF position. Always stand clear while turning the propeller. Rotate propeller by hand through all compressions of the engine to check for liquid lock and to clear excess preservative oil from cylinders. Start engine in normal manner. (Refer to POH, Chapter 4) Perform normal warm-up and Operational Check.
CHAPTER PLACARDS AND MARKINGS
CHAPTER 11 - REQUIRED PLACARDS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 11-LOEP 1 30 NOV 2000 11-TOC 1 30 NOV 2000 11-00 1 30 NOV 2000 11-20 1 30 NOV 2000 11-20 2 30 NOV 2000 11-20 3 30 NOV 2000 11-20 4 30 NOV 2000 11-30 1 30 NOV 2000 11-30 2 30 NOV 2000 11-30 3 30 NOV 2000 11-30 4 30 NOV 2000 11-30 5 30 NOV 2000 11-30 6 30 NOV 2000 11-30 7 30 NOV 2000 13773-001 30 Nov 2000 11-LOEP Page 1
CHAPTER 11 - REQUIRED PLACARDS TABLE OF CONTENTS Subject REQUIRED PLACARDS Chapter/Section Page 11-00 General EXTERIOR PLACARDS 1 11-20 Description 1 Maintenance Practices 1 Exterior Placard Installation Exterior Placard Removal INTERIOR PLACARDS 1 1 11-30 Description 1 Maintenance Practices 1 Polycarbonate Graphic Overlay Removal - Polycarbonate Graphic Overlay Installation - Polycarbonate Graphic Overlay Cast Vinyl Interior Placard Removal - Cast Vinyl Interior Placard Installation - Cast
REQUIRED PLACARDS 1. GENERAL Placards are used for identification and indication purposes. Placards give operating instructions, directional movements, servicing instructions, part or position identification, escape instructions, and safety precautions. Self adhesive cast vinyl decals or polycarbonate overlays are used for all placards located on the interior and exterior surfaces of the airplane. Missing, or placards with poor readability must be replaced.
EXTERIOR PLACARDS 1. DESCRIPTION This section describes the maintenance practices pertinent to those placards and markings which give operating instructions, directional movements, servicing instructions, part or position identification, escape instructions, and safety precautions. Exterior placards are printed on cast vinyl. Exterior placards include: Door; Open & Close, Baggage Door Location, ELT Location, C.A.P.S.
Figure 11-201 Exterior Placards (Sheet 1 of 3) Page 2 11-20 13773-001 30 Nov 2000
Figure 11-201 Exterior Placards (Sheet 2 of 3) 13773-001 30 Nov 2000 11-20 Page 3
Figure 11-201 Exterior Placards (Sheet 3 of 3) Page 4 11-20 13773-001 30 Nov 2000
INTERIOR PLACARDS 1. DESCRIPTION This section describes the maintenance practices pertinent to those placards and markings which give operating instructions, directional movements, servicing instructions, part or position identification, escape instructions, and safety precautions. Most airplane interior placards are integral to the individual panel’s polycarbonate graphic overlay. The remaining placards are printed on cast vinyl.
(e) (f) (g) (h) Align overlay half with protective backing still in place on panel and press exposed overlay half onto panel. Bend overlay back and peel remaining protective backing from overlay. Carefully work overlay toward opposite panel edge, pressing bubbles and wrinkles out with rubber roller. Ensure all edges are firmly adhered. Install panel and surrounding trim (if applicable). (Refer to 25-10) B.
Figure 11-301 Interior Placards (Sheet 1 of 5) 13773-001 30 Nov 2000 11-30 Page 3
Figure 11-301 Interior Placards (Sheet 2 of 5) Page 4 11-30 13773-001 30 Nov 2000
Figure 11-301 Interior Placards (Sheet 3 of 5) 13773-001 30 Nov 2000 11-30 Page 5
Figure 11-301 Interior Placards (Sheet 4 of 5) Page 6 11-30 13773-001 30 Nov 2000
Figure 11-301 Interior Placards (Sheet 5 of 5) 13773-001 30 Nov 2000 11-30 Page 7
CHAPTER SERVICING
CHAPTER 12 - SERVICING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 12-LOEP 1 30 NOV 2000 12-TOC 1 30 NOV 2000 12-TOC 2 30 NOV 2000 12-00 1 30 NOV 2000 12-00 2 30 NOV 2000 12-00 3 30 NOV 2000 12-10 1 30 NOV 2000 12-10 2 30 NOV 2000 12-10 3 30 NOV 2000 12-10 4 30 NOV 2000 12-10 5 30 NOV 2000 12-10 6 30 NOV 2000 12-10 7 30 NOV 2000 12-20 1 30 NOV 2000 12-20 2 30 NOV 2000 12-20 3 30 NOV 2000 12-20 4 30 NOV 2000 12-20 5 30 NOV 2000 12-20 6 30 NOV 2
CHAPTER 12 - SERVICING TABLE OF CONTENTS Subject SERVICING Chapter/Section Page 12-00 General REPLENISHING 1 12-10 Description 1 Maintenance Practices 1 Fuel System Safety Precautions Approved Fuels and Capacities Refueling Procedure Oil System Oil System Replenishing Hydraulic Brake System Brake Fluid Replenishing Tires Tire Air Pressure Replenishing Battery System Battery Electrolyte Level Check (Battery 1) SCHEDULED SERVICING 1 1 1 2 3 3 5 5 5 5 6 6 12-20 Description 1 Maintenance Practices
CHAPTER 12 - SERVICING TABLE OF CONTENTS Subject Chapter/Section Engine Cleaning: Leather Interior Leather Cleaning UNSCHEDULED SERVICING Page 11 13 13 12-30 Description 1 Maintenance Practices 1 Snow and Ice Removal: Page 2 12-TOC 1 13773-001 30 Nov 2000
SERVICING 1. GENERAL The information in this chapter pertains to general servicing procedures and maintenance practices used when servicing the airplane. This chapter contains illustrations, descriptions and servicing procedures necessary to locate system or component service points and to replenish operating fluids or service the airplane as required. (See Figure 12-001) The replenishment charts provide tank and reservoir capacities. Where applicable, capacities are listed in U.S.
Figure 12-001 Service Points Page 2 12-00 13773-001 30 Nov 2000
Service Capacities Item Fluid Capacity Fuel 100 LL (Blue) or 100 (Green) 42 Gallons (159 L) each wing Oil Mil-L-6082 Mineral Oil (1st 25 Hours) See Approved Oil Listing 8.0 US Quarts (7.6 L) Battery 1 Distilled Water As Required Brakes Mil-H-5606 Hydraulic 0.25 US Quart (0.
REPLENISHING 1. DESCRIPTION This section covers the replenishing of all fluids used on the airplane. 2. MAINTENANCE PRACTICES A. Fuel System (1) Safety Precautions WARNING: A fire extinguisher must be available. Ground exhaust pipe outlet and fuel service equipment prior to every fueling and defueling procedure. Check wing fuel tank vents for obstruction before refueling. Do not fill tanks within 100 feet (30.48 meters) of any energized electrical equipment capable of producing sparks.
(3) Refueling Procedure (a) Acquire necessary tools, equipment, and supplies. P/N or Spec. Description (b) (c) (d) - Any Source Extinguish fire in an emergency Rubber protective cover - Any Source Protect finish of airplane Fuel sampler cup 50627-001* Cirrus Design (h) (i) (j) (k) (l) (m) Page 2 Inspect fuel for contaminates * or equivalent substitute Place a fire extinguisher near the fuel tank to be serviced.
B. Oil System (See Figure 12-101) The Teledyne Continental IO-550-N engine uses a wet sump pressurized lubrication system with an 8 quart (7.57 L) capacity. A filler cap with an integral dipstick is provided for determining the amount of oil in the crankcase. (1) Oil System Replenishing CAUTION: For the first 25 hours of operation (on a new or rebuilt engine) or until oil consumption stabilizes, use straight mineral oil conforming to MIL-L-6082.
Average Ambient Air Temperature for Starting (Sea Level) Viscosity Grade Below 40°F SAE 30 or Multi Viscosity Above 40°F SAE 50 or Multi Viscosity Brand Page 4 Supplier Aeroshell (R) W Shell Australia Aeroshell Oil W Aeroshell Oil W 15W-50 Anti-Wear Formulation Aeroshell 15W-50 Shell Canada Ltd.
C. Hydraulic Brake System The main wheels have hydraulically operated, single-cylinder dual piston type disc brakes, individually activated by floor mounted toe pedals at both pilot stations. A parking brake mechanism holds induced hydraulic pressure on the disc brake for parking. The system is replenished by filling the hydraulic reservoir, located in the engine compartment on the upper right corner of the firewall. Replenish the system with MIL-H-5606 hydraulic fluid only.
Whenever an air pressure specification is called out, but not defined as loaded or unloaded, it should be considered as unloaded. Always service tires in a warm environment, this will keep the valve stem from freezing and eliminate the possibility of leaks through the valve core. After inspecting or adjusting tire pressure, always inspect the valve core for leaks before reinstalling the valve cap. Always install a valve cap to prevent contaminates from entering the valve core.
(c) (d) (e) (f) (g) Remove each cell cap and inspect each cell for the proper electrolyte level. The electrolyte should barely touch or be slightly short of the eyelet (level indicator) when the battery is warm and in a good state of charge. As an example, this condition would exist just after a bench charge or when the aircraft has just returned from a flight of ninety minutes or more. At all other times, no water should be added as long as the electrolyte is about 1/4” above the plates.
SCHEDULED SERVICING 1. DESCRIPTION This section contains information necessary to perform the scheduled servicing requirements of the airplane. Servicing the fuel system, lubrication system, tires, brakes, and battery are covered. Cleaning of interior and exterior surfaces are also covered. 2. MAINTENANCE PRACTICES A. Fuel System (1) Drain Valves Five fuel drains are provided throughout the fuel system to drain fuel, water or sediment from the fuel system.
(2) Defueling Airplane Siphoning Method (a) Acquire necessary tools and equipment.
(3) Defueling Airplane Electric Fuel Pump Method (a) Acquire necessary tools and equipment.
(4) Defueling Airplane Drain Valve Method (a) Acquire necessary tools and equipment.
fluid loss, must be determined before continued operation of the airplane. Any spilled brake fluid must be removed immediately as it will damage any painted surface upon contact. Remove any dirt on the brake fluid reservoir filler cap before opening. C. Engine Oil System Straight mineral oil (MIL-L-6082) should be used for the first initial oil change period (25 hours). After oil consumption stabilizes the mineral oil should be drained and an approved engine oil used.
(1) Changing Engine Oil and Filter Note: (a) The engine should be warm, prior to changing oil. Acquire necessary tools and equipment. Description (b) (c) (g) Snap-on Tools Kenosha, WI Removal of oil filter Oil drain pan - Any Source Retrieve used oil Safety wire,.032” MS20995 Any Source Secure fasteners Safety wire plier M-84 * Genair Ltd. Tension safety wire Flexible oil funnel - Any Source Replace engine oil * or equivalent substitute Remove the upper and lower engine cowlings.
(3) Oil Filter Particle Inspection/Check (a) Acquire necessary tools and equipment. Description Oil filter can cutter (b) (c) (d) (e) (f) P/N or Spec. CT-470 * Supplier Purpose Champion Spark Plug Inspecting oil filter element Toledo, OH * or equivalent substitute Secure the filter in a vise. Using a can cutter, secure the cutter on the filter mounting plate. Tighten the knurled head screw until the cutter blade meets the filter metal can surface.
Item Lubricant P/N or Spec. Supplier Engine cowling access 300 hours panel door Powdered Graphite SS-G-659A Any source Cabin door hinge Lubricating Oil Aeroshell ASF3 SAE 10W30 or MIL-L-7870 Shell Oil Co.
G. Cleaning To maintain the flying characteristics of the airplane, the external surfaces of the airplane and propeller must remain clean, especially the leading edges of the wings. To aid in protecting the finish, insect residue should be immediately washed off after every flight. For best cleaning results on cured paint, (paint that has been in a warm climate for at least 90 days after being applied and prior to being washed with hot soapy water) use a generous amount of fresh warm water.
(d) (e) (f) (g) Wash the airplane using plenty of clean, fresh water. Rinse the airplane with fresh, clean water. Dry the airplane using a soft chamois. Remove all pitot head, brake disc and static port covers. WARNING: (2) Inspect the pitot head and static port orifices for any obstructions or restrictions. Never allow any of the aforementioned orifices to remain obstructed or restricted.
(3) Interior Cleaning: Seats, carpet, upholstery panels, and headliners should be vacuumed at regular intervals to remove surface dirt and dust. While vacuuming, use a fine bristle nylon brush to help loosen particles. Carpet may be cleaned like household carpet made with the same composition and similar weave. The headliner is made from polyester. The headliner can be cleaned using the same methods for cleaning any object made out of polyester.
CAUTION: (a) The engine must be cool to the touch, prior to cleaning. Always inspect engine for leaks, loose hardware, and worn hardware prior to cleaning. Always cover all windows, magneto vents, engine electrical components and connections when washing any portion of the engine compartment. Remove the air filter and cover the air induction inlet prior to washing the engine compartment. Never use any flammable or corrosive cleaning solvents.
mulation allows leather to breath and imparts a soft and supple tone. It also provides emollients, color restoration, water retardation, and ultraviolet ray protection, which decreases color fading. If applied regularly, the conditioner will enhance the natural luster of fine leather, while increasing the longevity of the product. The approved leather conditioner is safe for use on all colors.
Approved Cleaning Products for Simulated Leather Description P/N or Spec.
UNSCHEDULED SERVICING 1. DESCRIPTION This section contains information on unscheduled servicing which includes the removal of snow and ice. 2. MAINTENANCE PRACTICES A. Snow and Ice Removal: Snow and ice must never be allowed to remain on the airplane. If snow or ice have accumulated, it is recommended to remove it by placing the airplane in a heated hanger. This will prevent melted snow and ice from refreezing on the surface, or in any gaps.
CHAPTER STANDARD PRACTICES: AIRFRAME
CHAPTER 20 - STANDARD PRACTICES: AIRFRAME LIST OF EFFECTIVE PAGES Chapter/Section Page Date 20-TOC 1 30 NOV 2000 20-TOC 2 30 NOV 2000 20-TOC 3 30 NOV 2000 20-TOC 6 20-LOEP 1 30 NOV 2000 20-LOEP 2 30 NOV 2000 20-00 1 30 NOV 2000 20-10 1 30 NOV 2000 20-10 2 30 NOV 2000 20-10 3 30 NOV 2000 20-10 4 30 NOV 2000 20-10 5 30 NOV 2000 20-10 6 30 NOV 2000 20-10 7 30 NOV 2000 20-10 8 30 NOV 2000 20-10 9 30 NOV 2000 20-10 10 30 NOV 2000 20-10 11 30 NOV 2000 20-10
CHAPTER 20 - STANDARD PRACTICES: AIRFRAME LIST OF EFFECTIVE PAGES Chapter/Section Page Date 20-40 1 30 NOV 2000 20-40 2 30 NOV 2000 20-50 1 30 NOV 2000 20-50 2 30 NOV 2000 20-50 3 30 NOV 2000 20-50 4 30 NOV 2000 20-50 5 30 NOV 2000 20-60 1 30 NOV 2000 20-60 2 30 NOV 2000 20-60 3 30 NOV 2000 20-60 4 30 NOV 2000 20-60 5 30 NOV 2000 20-60 6 30 NOV 2000 20-60 7 30 NOV 2000 20-60 8 30 NOV 2000 20-60 9 30 NOV 2000 20-60 10 30 NOV 2000 20-60 11 30 NOV 2000 2
CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS Subject STANDARD PRACTICES - AIRFRAME Chapter/Section Page 20-00 General SEALANTS 1 20-10 Description 1 Approved Sealants Shelf Life Storage Criteria Refrigerated Storage - Mixed Sealants Thawing of Frozen Sealant Application Time / Work Life Tack-Free Time Cure Time Types of Seals Fillet Seals Faying Surface Seals Injection Seals Brush Seals Method of Application Brush Application Roller Application Extrusion Application Spatula Applicati
CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS Subject Chapter/Section ADHESIVES Page 20-20 Description 1 Maintenance Practices 1 Adhesives SOLVENT CLEANING 1 20-30 Description 1 Maintenance Practices 2 Solvent Cleaning Metal Parts Solvent Cleaning Composite Materials Cleaning Acrylic Surfaces Cleaning Painted or Primed Surfaces for Decal Application LOCTITE/TORQUE SEAL 2 4 6 8 20-40 Description 1 Maintenance Practices 1 Threadlock Shelf Life Application of Thread Lock Tor
CHAPTER 20 - STANDARD PRACTICES - AIRFRAME TABLE OF CONTENTS Subject Chapter/Section FASTENER AND HARDWARE GENERAL REQUIREMENTS Page 20-70 Description 1 Maintenance Practices 1 Cotter Pins Proper Usage of Cotter Pins.
STANDARD PRACTICES - AIRFRAME 1. GENERAL This chapter contains torque factors, torque tables and measuring techniques for various components. Instructions necessary for proper usage and identification of special tools, thread lock and fastening hardware are also provided.
SEALANTS 1. DESCRIPTION This section contains information which defines the proper usage, storage, shelf life, and application of sealants used on the airplane. Sealant is used to prevent the spread of fire or flames from the engine compartment to the airplane, prevent air leakage, prevent fastener corrosion, prevent water or dust intrusion, and to prevent fluid leakage. The following sealants are recommended by Cirrus Design Corporation. A.
Approved Sealants Item P/N or Spec. Supplier Application RTV Silicone Sealant (high temperature) RTV 736 Dow Corning General fillet & faying surface sealing. Brushable Sealant MIL-S-8802 Type 2 Class A* GC408A P/S 890A EC1675A CS3204 C1.A PR1440A Fuel tank repair surface Goal seal. PRC Aerospace Sealants 3M Chem Seal - Flame Master PRC Aerospace Sealants Extrusion Gun Sealant MIL-S-8802 Type 2 Class B* CS3204 C1.
Note: Thawed sealant must not be re-frozen. All sealants must extrude freely before application to any surface. Adhesion may be lowered by condensation of moisture if the sealant is not thawed to an extruded temperature of at least 60° F. D. Application Time / Work Life Application time refers to the time a mixed compound remains at a consistency suitable for application.
(3) Injection Seals Injection seals are used to fill holes, joggles, channels and other voids. Injection seals may be applied to provide continuity where fillet seals are interrupted by structure. Injection sealing forces air out of a cavity and fills the vacated space with sealant. Injection seals are accomplished by injecting the area with an extrudable sealant through an extrusion cartridge or a tube.
Figure 20-101 Fillet Sealing 13773-001 30 Nov 2000 20-10 Page 5
Figure 20-102 Injection & Faying Surface Sealing Page 6 20-10 13773-001 30 Nov 2000
2. MAINTENANCE PRACTICES A. Preparation for Sealing (1) Acquire necessary tools, equipment, and supplies.
CAUTION: (8) Examine rework area for clean cuts, adequate notching, and for access. All loose pieces of sealant in the repair area must be removed. If required, the area can be lightly sanded or brushed briskly with a stiff-bristle brush to remove sealant. CAUTION: (9) Cutting tools must be made only from non-ferrous materials that are softer than the surrounding structure. Use hardwood or acrylic tools for composite structure and polyethylene, polypropylene, or Teflon around acrylic windows.
(1) Acquire necessary tools, equipment, and supplies. Description (2) P/N or Spec. Supplier Purpose Clean, Wax Free Container - Any Source Hand mix sealant Spatula - Any Source Hand mix sealant Scales, Accuracy ± 2% - Any Source Proportion sealant Rotary Mixer 1384 Semco Application Systems PRC-DeSoto Intl Inc.
(c) Slowly stir accelerator into the base compound and thoroughly mix for approximately 7 to 10 minutes. Note: (4) Be sure to scrape the sides and bottom of the container in order to include all the compound in the mixture and to ensure uniform blending. Scrape mixing paddle on container sides periodically to ensure all material, including that on paddle, is mixed.
C. Application of Sealants (General Procedure) (1) Acquire necessary tools, equipment, and supplies.
(b) (c) WARNING: Remove metal and composite chips, shavings, and lint using stiff bristle brushes or vacuum. Solvent clean all surfaces using acetone or isopropyl alcohol. (Refer to 20-30) Keep all sealants away from open flames or other sources of ignition. Mix and use sealants only in areas with adequate ventilation. Wear protective gloves when handling sealants and cleaned parts. Do not use protective hand creams as they can contaminate the sealant. Avoid skin contact.
CAUTION: (f) (g) Sealant which does not wet properly or which is difficult to extrude from the sealing gun must be discarded. Sealant should never be applied at temperatures below 60° F (15.5° C) or to a structure that is below 60° F (15.5° C). Sealed structures must be handled with care and should never be moved until sealant has achieved a tack-free surface. Pressure testing, if required, must never be performed, until all sealant has cured.
Sealant which does not wet properly or which is difficult to extrude from the sealing gun must be discarded. Sealant should never be applied at temperatures below 60° F (15.5° C) or to a structure that is below 60° F (15.5° C). Sealed structures must be handled with care and should never be moved until sealant has achieved a tack-free surface. Pressure testing, if required, must never be performed, until all sealant has cured.
Note: (e) A fillet may be applied in two or more applications. A small fillet should be applied first and allowed to partially cure, followed by a second application of sealant sufficient to form the final fillet. The final fillet must be smooth and should have the dimensions as specified. CAUTION: 13773-001 30 Nov 2000 Sealant must be applied so that it provides an airtight seal. Ensure that folds, laps, and entrapped air are not created during sealing.
Figure 20-103 Fastener Sealing Page 16 20-10 13773-001 30 Nov 2000
(f) (4) Work out all entrapped air and remove excess sealant with a fairing tool. Fair out extruded sealant to leave a smooth fillet along joint and at ends.The tool should be pressed against the sealant and moved parallel to the bead. (g) Inspect seal for poor adhesion and evidence of air bubbles. Evidence of air bubbles is cause to rework the seal.
Figure 20-104 Bulkhead Fitting Seal Page 18 20-10 13773-001 30 Nov 2000
(a) If not already accomplished remove all sealant from damaged seal with cutting tools and suitable hardwood or plastic scrapers as described in paragraph A. - “Preparation for Sealing.” CAUTION: After thoroughly cleaning surfaces to be sealed, wear clean, white, cotton gloves to prevent contaminating the surfaces to be sealed. Use care in selecting solvent. Do not use acetone to clean acrylic. Use only isopropyl alcohol for solvent cleaning acrylic surfaces.
Figure 20-105 Cable Pass-Through Sealing Page 20 20-10 13773-001 30 Nov 2000
(a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec.
CAUTION: (c) (d) WARNING: Use caution not to sand through resin coat exposing fibers. Sanding through the resin coat and exposing fibers will be cause for composite repair. Remove metal and composite chips, shavings, and lint using stiff bristle brushes and vacuum. Solvent clean all surfaces using acetone or isopropyl alcohol. Thoroughly dry surfaces and remove all residue. (Refer to 20-30) Keep all sealants away from open flames or other sources of ignition.
ADHESIVES 1. DESCRIPTION This section contains information on the adhesives that are used on the airplane. 2. MAINTENANCE PRACTICES A. Adhesives The following adhesives, when applied properly in the appropriate area, have been approved by Cirrus Design. Contact Neoprene Adhesive is used for securing the seat foam and seat to the seat assembly. Epoxy is used for retaining the light strips to the glareshield. WARNING: Always follow the directions from the manufacture of the product being used.
SOLVENT CLEANING 1. DESCRIPTION This section covers solvent cleaning procedures for metallic and non-metallic materials. These procedures may be used for general cleaning when solvents are required and must be used to clean surfaces prior to the application of adhesive, resin, or sealants. WARNING: Cleaning solvents are toxic and flammable. Therefore, special precautions must be used whenever solvents are used for any purpose. Always follow the solvent manufacture’s directions.
2. MAINTENANCE PRACTICES A. Solvent Cleaning Metal Parts (1) Acquire necessary tools, equipment, and supplies. Description (2) Supplier Purpose Isopropyl Alcohol TT-I-735 Grade A or B Any Source Preliminary and Final Cleaning Acetone ASTM D-329 Any Source Preliminary and Final Cleaning.
(3) Final Cleaning Note: (a) Final cleaning must be accomplished prior to applying any adhesive, or sealant. All surfaces shall be thoroughly cleaned and dried before application of any adhesive or sealant. When handling cleaned surfaces, wear clean white cotton gloves to prevent surface contamination. Surfaces shall be recleaned in the event of contamination. Fold clean lint-free cloths in such a manner as to eliminate raw edges to reduce the possibility of lint contaminating the surface to be cleaned.
B. Solvent Cleaning Composite Materials CAUTION: (1) Isoproply alcohol is the only cleaning agent recommended when preparing composite surfaces (excluding fuel compartments) for repair. When cleaning a composite surface in any of the fuel compartments, acetone is the recommended cleaning agent. Acquire necessary tools, equipment, and supplies. Description Page 4 P/N or Spec. Supplier Purpose Cleaner DX 330 PPG Industries, Inc.
(2) Preliminary Cleaning WARNING: (a) If fuel tank interior is to be cleaned, ground aircraft to suitable earthground. Evacuate oxygen from fuel tank by filling tank with an inert gas such as nitrogen or argon. Gas should be applied continuously until tank is clean and dry. Laminates that come in contact with moisture must be dried before performing composite repairs. Remove excess material (chips, shavings, lint, etc.) using a vacuum sweeper, clean bristle brush, etc.
Note: (e) Never pour or spray cleaning solvent on aircraft structure because it will run back between structural layers, then run back out again after the cleaning operations are completed, bringing contamination to surfaces previously cleaned. Thoroughly clean small areas at a time and immediately wipe area dry with a clean, dry, lint-free cloth. Note: (f) If adhesive, resin, or sealant is to be applied, always clean an area wider than the width of final product being applied.
(2) Clean acrylic parts (interior surface of windshield which is to be sealed) with aliphatic naphtha or Isoproply alcohol. Note: (a) If sealant is to be applied, acrylic surfaces must be completely dry, without contaminants, prior to sealing. Fold clean lint-free cloths in such a manner as to eliminate raw edges to reduce the possibility of lint contaminating the surface to be cleaned. WARNING: (b) Dampen one cloth with cleaning solvent from polyethylene squirt bottle.
D. Cleaning Painted or Primed Surfaces for Decal Application (1) Acquire necessary tools and equipment.
LOCTITE/TORQUE SEAL 1. DESCRIPTION This section contains surface preparations and cleaning procedures for the usage of thread lock and thread sealing agents. 2. MAINTENANCE PRACTICES A. Threadlock (1) Shelf Life Threadlock itself has no designated maximum shelf life when stored at room temperature in a unopened container. Once the container is opened, temperature and environmental factors, such as humidity and exposure to sunlight, have a major affect on shelf life.
LOCTITE USAGE SPECIFICATIONS Product Number 222 222MS 242 262 271 277 Small remov- Removable able screws grade to 3/4” P/N or Spec.
SAFETYING 1. DESCRIPTION This section contains information on the proper safetying techniques and procedures used when fastening hardware. 2. MAINTENANCE PRACTICES A. Safety Wiring There are two basic forms of safety wiring. The single-wire method and the double-twist method. Safety wire comes in three types which are identified by size and color. The three types are classified by use. Inconel and Monel wire is used for general safety wiring and is identified by a natural wire color.
Note: (3) Widely spaced multiple groups shall mean those in which fasteners are from four to six inches apart. General Installation Procedures CAUTION: Screws in closely spaced geometric pattern which secure hydraulic or air seals, hold hydraulic pressure, or are used in critical areas should use the double-twist method of lockwiring.
Note: (e) It is preferable to safety wire all electrical connectors individually. Do not safety wire one connector to another unless it is necessary to do so. Drilled head bolts and screws need not be safety wired if installed into self-locking nuts or installed with lockwashers. Castellated nuts with cotter pins or safety wire are preferred on bolts or studs with drilled shanks.
Figure 20-501 Single Twist Safety Wiring Page 4 20-50 13773-001 30 Nov 2000
Figure 20-502 Double Twist Safety Wiring 13773-001 30 Nov 2000 20-50 Page 5
FASTENER IDENTIFICATION AND TORQUE DATA 1. DESCRIPTION This section contains information on the correct usage and identification of bolts, flat washers, lock washers, nuts, lock nuts, fittings and torque data. The nuts, bolts, and washers used on the airplane are in accordance with Air Force Navy Specifications, Military Specifications, and National Aircraft Standards. CAUTION: Overtorquing of fasteners can result in failed fasteners and/or components.
Figure 20-601 Bolt Identification Page 2 20-60 13773-001 30 Nov 2000
Figure 20-602 General Torque Pattern 13773-001 30 Nov 2000 20-60 Page 3
Specific Torque Requirements Chapter/ Section Reference Item Inch Pounds Minimum Dry Torque Maximum Dry Torque Nm Minimum Dry Torque Maximum Dry Torque Propeller mounting nuts 61-10 840.0 960.0 92.4 105.6 Propeller mounting bolts 61-10 264.0 264.0 29.0 29.0 Propeller governor nuts 61-20 155 175 17.0 19.2 Spark plugs 72-00 300.0 360.0 33.9 40.7 Engine mount to firewall bolts (1/4”) 71-20 75.0 100.0 8.5 11.3 Engine mount to firewall bolts (1/2”) 71-20 456.0 480.0 50.
The required torque values are shown for fasteners used on this airplane. Make sure that the needed torque value is selected from the correct table. NON-COMPOSITE STRUCTURE Torque Specifications for High Strength Steel Tension Nuts and Bolts with FINE Threads Inch Pounds Item STEEL TENSION NUTS AN310 AN315 AN363 AN365 MS17825 MS20365 MS21045 NAS1021 NAS679 NAS1291 Thread Size Nm Minimum Dry Torque Maximum Dry Torque Minimum Dry Torque Maximum Dry Torque 10-32 25 30 2.8 3.
NON-COMPOSITE STRUCTURE Torque Specifications for High Strength Steel Shear Nuts and Bolts with FINE Threads Inch Pounds Item STEEL SHEAR NUTS AN320 AN364 NAS1022 MS17826 MS20364 Thread Size Minimum Dry Torque Maximum Dry Torque Nm Minimum Dry Torque Maximum Dry Torque 10-32 15 20 1.7 2.2 1/4”-28 50 60 5.5 6.6 5/16”-24 70 90 7.7 9.9 3/8”-24 120 150 13.2 16.5 7/16”-20 300 400 33.0 44.0 1/2”-20 450 550 49.5 60.5 9/16”-18 650 800 71.5 88.0 5/8”-18 750 950 82.
NON-COMPOSITE STRUCTURE Torque Specifications for Standard Steel Shear Nuts with FINE Threads Inch Pounds Item STEEL SHEER NUTS AN320 AN364 NAS1022 MS17826 MS20364 MS21042 MS21083 MS21245 13773-001 30 Nov 2000 Thread Size Nm Minimum Dry Torque Maximum Dry Torque Minimum Dry Torque Maximum Dry Torque 8-36 7 9 .8 1.0 10-32 12 15 1.3 1.7 1/4”-28 30 40 3.3 4.4 5/16”-24 60 85 6.6 9.4 3/8”-24 95 110 10.5 12.1 7/16”-20 270 300 29.7 33.0 1/2”-20 290 410 31.9 45.
NON-COMPOSITE STRUCTURE Torque Specifications for Standard Steel Tension Nuts and Bolts with FINE Threads Inch Pounds Item STEEL TENSION NUTS AN310 AN315 AN363 AN365 NAS1021 MS17825 MS21044 MS21045 MS21046 MS20365 MS20500 NAS679 STEEL TENSION BOLTS AN3 thru AN20 AN42 thru AN49 AN73 thru AN81 AN173 thru AN186 MS20033 thru MS20046 MS20073 MS20074 AN509NK9 MS24694 AN525NK525 MS27039 Page 8 20-60 Thread Size Minimum Dry Torque Maximum Dry Torque Nm Minimum Dry Torque Maximum Dry Torque 8-36 12 15
NON-COMPOSITE STRUCTURE Torque Specifications for Standard Steel Tension Nuts and Bolts with COARSE Threads Inch Pounds Item STEEL TENSION NUTS AN310 AN315 AN363 AN365 NAS1021 MS17825 MS21044 MS21045 MS21046 MS20365 MS20500 NAS679 STEEL TENSION BOLTS AN3 thru AN20 AN42 thru AN49 AN73 thru AN81 AN173 thru AN186 MS20033 thru MS20046 MS20073 MS20074 AN509NK9 MS24694 AN525NK525 MS27039 13773-001 30 Nov 2000 Thread Size Minimum Dry Torque Nm Maximum Dry Torque Minimum Dry Torque Maximum Dry Torque 8-3
NON-COMPOSITE STRUCTURE Torque Specifications for Standard Steel Shear Nuts with COARSE Threads Inch Pounds Item STEEL SHEER NUTS AN320 AN364 NAS1022 MS17826 MS20364 MS21042 MS21083 MS21245 Page 10 20-60 Thread Size Minimum Dry Torque Nm Maximum Dry Torque Minimum Dry Torque Maximum Dry Torque 8-32 7 9 .8 1.0 10-24 12 15 1.3 1.7 1/4”-20 25 30 2.8 3.3 5/16”-18 48 55 5.3 6.1 3/8”-16 95 110 10.5 12.1 7/16”-14 140 155 15.4 17.1 1/2”-13 240 290 26.4 31.
COMPOSITE STRUCTURE Torque Specifications For FINE Thread Hex-head Tension And Shear Bolts, Or Any Bolted Structure With Combinations Of Composite And Metallic Parts Inch Pounds Thread Size Minimum Dry Torque Maximum Dry Torque Nm Minimum Dry Torque Maximum Dry Torque 10-32 15 20 1.7 2.2 1/4-28 25 30 2.8 3.3 5/16-24 50 60 5.5 6.6 3/8-24 80 95 8.8 10.5 7/16-20 150 170 16.5 18.7 1/2-20 220 245 24.2 27.0 B.
(h) (i) (j) (k) Page 12 Screws using dimpled washers should be drawn tight enough to eliminate the crown of the washer. Specified torques must be considered dry torques. Castellated nuts requiring cotter pins should be tightened to low torque value. Torque can be increased to install cotter pin, but should never exceed maximum torque value. When nut cannot be tightened within given torque values to install cotter pins, remove nut, install a washer, then reinstall nut.
Figure 20-603 Torque Wrench Adapter 13773-001 30 Nov 2000 20-60 Page 13
FASTENER AND HARDWARE GENERAL REQUIREMENTS 1. DESCRIPTION This section contains general requirements for common hardware installation. Covered are selection and installation of cotter pins, installation of turnbuckle locking clips, rod end inspection requirements, fastener flushness requirements, self-locking nut installation requirements, and installation and usage requirements for washers and lockwashers. 2. MAINTENANCE PRACTICES A.
Figure 20-701 Cotter Pin Safetying Page 2 20-70 13773-001 30 Nov 2000
Cotter Pin Specifications Material Temperature Carbon Steel (MS24665) Usage Up to 450°F Pins that contact cadmium-plated surfaces. General Applications Normal Atmospheres Corrosion-Resistant (MS24665C) Up to 800°F Pins that contact corrosion-resistant steel. Corrosive atmospheres Minimum Allowable Cotter Pin Size 13773-001 30 Nov 2000 Thread Size Diameter of Cotter Pin 6 0.028 8 0.044 10 0.044 1/4 0.044 5/16 0.044 3/8 0.072 7/16 0.072 1/2 0.072 9/16 0.086 5/8 0.086 3/4 0.
B. Locking Clip (1) Proper use of Locking Clips (a) Prior to safetying, both threaded terminals shall be screwed an equal distance into the turnbuckle body and shall be screwed in at least so that not more than three threads of any terminal are exposed outside of body.
Figure 20-702 Locking Clip Safetying 13773-001 30 Nov 2000 20-70 Page 5
Figure 20-703 Rod End Page 6 20-70 13773-001 30 Nov 2000
D. Fastener Flushness (1) (2) (3) (4) Flush Head Screws (a) The gap under the head of screws and bolts, and under nuts, shall be.002” maximum for no more than 40% of the circumference. The heads of flush rivets, screws and Hi-Loks on the exterior of the airplane shall be flush with the local skin contour to within the tolerances specified. For fasteners installed in the exterior skin, head protrusion for flush head screws shall meet the following requirements. Heads shall not be shaved.
Note: (1) Observe torque values and the installation of the recommended safetying device for every fastener. The end of a flat end bolt or screw shall extend through the nut or nutplate at least 1/32”, or the end of a round or chamfered end bolt or screw shall extend through the nut or nutplate the full round or chamfer. Do not use MS17826 nuts for tension applications. The aforementioned nuts can be used on standard and high strength bolts.
Figure 20-704 Fastener Head Flushness 13773-001 30 Nov 2000 20-70 Page 9
F. Washers Do not use washers under the head of flush screws unless specifically called out. When installing a countersunk MS20002 washer under the head of bolts, the washer shall be installed so that the countersunk side faces the bolt head. A maximum of two AN960 (thick or thin) washers may be used under a nut on all bolts, except when a AN 970 washer is specified; then a maximum of only one additional AN960 washer may be used between the nut and AN970 washer.
Figure 20-705 Washer Placement 13773-001 30 Nov 2000 20-70 Page 11
FLARED TUBING 1. DESCRIPTION This section contains the proper torque specifications for hydraulic fittings. 2. MAINTENANCE PRACTICES A. Hydraulic Fittings Hydraulic fittings must be torqued to the following specifications to prevent loosening while in flight, or damage due to over tightening. CAUTION: 13773-001 30 Nov 2000 The tube nut must never be used to pull the tube assembly to seat against the fitting.
Hydraulic Fitting Torque Torque for AN-818 Nuts with Steel Tubing Inch Pounds Dash # Nm Tube OD Minimum Maximum Minimum Maximum -3 3/16 95 105 10.5 11.6 -4 1/4 135 150 14.9 16.5 -6 3/8 270 300 29.7 33.0 -8 1/2 450 500 49.5 55.0 Torque for AN-818 Nuts with Aluminum Alloy Tubing Inch Pounds Dash # Nm Tube OD Minimum Maximum Minimum Maximum -3 3/16 25 35 2.8 3.9 -4 1/4 50 65 5.5 7.2 -6 3/8 110 130 12.1 14.3 -8 1/2 230 260 25.3 28.
CABLE INSPECTION 1. DESCRIPTION This section covers procedures necessary for the proper inspection of control cables. 2. MAINTENANCE PRACTICES A. Control Cables (See Figure 20-901) Control cable assemblies are subject to a variety of environmental conditions and forms of deterioration that ultimately may be easy to recognize such as wire/strand breakage. The not so readily visible types of deterioration include corrosion and/or distortion.
Figure 20-901 Control Cable Inspection Page 2 20-90 13773-001 30 Nov 2000
CHAPTER ENVIRONMENTAL SYSTEMS
CHAPTER 21 - ENVIRONMENTAL SYSTEMS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 21-LOEP 1 30 NOV 2000 21-TOC 1 30 NOV 2000 21-TOC 2 30 NOV 2000 21-00 1 30 NOV 2000 21-00 2 30 NOV 2000 21-00 3 30 NOV 2000 21-20 1 30 NOV 2000 21-20 2 30 NOV 2000 21-20 3 30 NOV 2000 21-20 4 30 NOV 2000 21-20 5 30 NOV 2000 21-40 1 30 NOV 2000 21-40 2 30 NOV 2000 21-40 3 30 NOV 2000 21-60 1 30 NOV 2000 21-60 2 30 NOV 2000 21-60 3 30 NOV 2000 21-60 4 30 NOV 2000 21-60
CHAPTER 21 - ENVIRONMENTAL SYSTEMS TABLE OF CONTENTS Subject ENVIRONMENTAL SYSTEMS Chapter/Section Page 21-00 General 1 Troubleshooting 1 AIR DISTRIBUTION SYSTEM 21-20 Description 1 Maintenance Practices 1 Eyeball Outlets Removal - Bolster Panel Eyeball Air Vent Installation - Bolster Panel Eyeball Air Vent Removal - Armrest Eyeball Air Vent Installation - Armrest Eyeball Air Vent Air Ducts Removal - Plenum Box Air Ducts Installation - Plenum Box Air Ducts Removal - Side Panel Air Ducts Instal
CHAPTER 21 - ENVIRONMENTAL SYSTEMS TABLE OF CONTENTS Subject Chapter/Section Adjustment - Heat Position Control Adjustment/Test - Defrost and Cold Air Position Linkage Heat Box Control Cable Removal - Heat Box Control Cable Installation - Heat Box Control Cable Adjustment - Heat Box Control Cable Page 2 21-TOC Page 1 1 4 4 4 5 13773-001 30 Nov 2000
ENVIRONMENTAL SYSTEMS 1. GENERAL The airplane fresh air and conditioned air systems are covered in this chapter. Temperature, volume, and flow selection are regulated by manipulation of the cabin temperature and cabin air selector knobs on the lower right side of the instrument panel. Cabin heating and ventilation is accomplished by supplying conditioned air for heating and windshield defrost and fresh air for ventilation.
Figure 21-001 Heating and Ventilation System (Sheet 1 of 2) Page 2 21-00 13773-001 30 Nov 2000
Figure 21-001 Heating and Ventilation System (Sheet 2 of 2) 13773-001 30 Nov 2000 21-00 Page 3
AIR DISTRIBUTION SYSTEM 1. DESCRIPTION This section covers the servicing procedures for the integral fresh air inlets, fresh air ducts, and eyeball vents. Fresh air vents are located along the sidewall near each rear passenger seat and directly forward of the pilot and co-pilot seats. One integral fresh air inlet is located on the forward side of each wing. Fresh ram air flows through the fresh air inlets and into the cabin.
Figure 21-201 Air Distribution Vents Page 2 21-20 13773-001 30 Nov 2000
B. Air Ducts (1) (2) Removal - Plenum Box Air Ducts (a) Remove MFD. (Refer to 34-40) (b) Remove the appropriate kick panel. (Refer to 25-10) (c) Remove the cable ties securing the appropriate air duct. (d) Remove the air duct. Installation - Plenum Box Air Ducts CAUTION: (a) Ensure air duct routing doesn’t interfere with other components. Acquire necessary tools, equipment, and supplies. Description Cable Ties P/N or Spec.
(8) Installation - Passenger Heat Duct CAUTION: (a) Ensure air duct routing doesn’t interfere with other components. Acquire necessary tools, equipment, and supplies. Description Cable Ties (b) (c) (d) (e) (f) Page 4 P/N or Spec. 8 inch Supplier Any Source Purpose Retain air duct Install air duct into position. Secure duct with cable ties at both ends. Install MFD. (Refer to 34-40) Secure armrest interior trim panel. (Refer to 25-10) Secure side duct cover.
Figure 21-202 HVAC System 13773-001 30 Nov 2000 21-20 Page 5
HEAT AND DEFROST SYSTEM 1. DESCRIPTION Heated air is available at floor level for all occupants. Positive pressure inside the engine cowling causes airflow from the inlet at the rear engine baffle to the engine exhaust muffler. The airflow is then ducted to the heat box on the firewall. When the heat box damper is closed, the heated air remains in the engine compartment. When the heat box damper is open, heated air flows from the heat box into the cabin air plenum mixing chamber.
(i) Install engine cowling. (Refer to 71-10) B. Cabin Air Plenum The cabin air plenum is located inside the fuselage. The plenum is mounted to the firewall on the righthand side. (1) (2) Removal - Cabin Air Plenum (a) Remove the co-pilot kick plate. (Refer to 25-10) (b) Remove the MFD for improved access to the plenum. (Refer to 34-40) (c) Cut and remove the cable ties securing the ducts to the plenum. (d) Disconnect the ducts from the plenum. (e) Disconnect the temperature control linkage.
Figure 21-401 Conditioned Air Flow 13773-001 30 Nov 2000 21-40 Page 3
TEMPERATURE CONTROL 1. DESCRIPTION The amount of cooling air allowed into the air mixing plenum is controlled by rotating the Cabin Cold Control Knob, located outboard of the Cabin Air Selector (Defrost-Floor). The control is mechanically linked to a butterfly valve at the fresh air entrance to the mixing plenum. Rotating the control full counterclockwise shuts down cooling airflow to the mixing plenum from the fresh air inlet in the right wing root.
Figure 21-601 Temperature Controls (Sheet 1 of 2) Page 2 21-60 13773-001 30 Nov 2000
Figure 21-601 Temperature Controls (Sheet 2 of 2) 13773-001 30 Nov 2000 21-60 Page 3
B. Heat Box Control Cable (1) (2) Removal - Heat Box Control Cable (a) Remove engine cowling to gain access to heat box cable. (Refer to 71-10) (b) Solvent clean adhesive (with alcohol) from cable pass-through on the forward side of the firewall. (Refer to 20-30) (c) Loosen lower cable stop bolt from heat box actuation arm. (d) Loosen cable stop bolt from the inner core wire. Slide cable stop off heater cable core wire. (e) Loosen clamp fastened to angle bracket and engine mount. Slide cable out of clamp.
(3) 13773-001 30 Nov 2000 (l) Install MFD. (Refer to 34-40) (m) Install co-pilot kick plate. (Refer to 25-10) (n) Install engine cowling. (Refer to 71-10) (o) Verify proper operation of temperature controls and MFD. Adjustment - Heat Box Control Cable (a) Remove MFD. (Refer to 34-40) (b) Remove engine cowling. (c) Loosen the cable stop bolt from the inner core wire (located above the heat box actuation arm). (d) Loosen the heat box actuation arm cable stop bolt.
CHAPTER AUTO FLIGHT
CHAPTER 22 - AUTOFLIGHT LIST OF EFFECTIVE PAGES Chapter/Section Page Date 22-LOEP 1 31 JULY 2001 22-TOC 1 31 JULY 2001 22-00 1 30 NOV 2000 22-00 2 31 JULY 2001 22-10 1 31 JULY 2001 22-10 2 31 JULY 2001 22-10 3 31 JULY 2001 22-10 4 31 JULY 2001 22-10 5 31 JULY 2001 22-10 6 31 JULY 2001 22-10 7 31 JULY 2001 13773-001 31 July 2001 22-LOEP Page 1
CHAPTER 22 - AUTOFLIGHT TABLE OF CONTENTS Subject AUTOFLIGHT Chapter/Section Page 22-00 General SYSTEM 55 AUTOPILOT 1 22-10 Description 1 Maintenance Practices 1 Flight Guidance Programmer/Computer Removal - Flight Guidance Programmer/Computer Installation - Flight Guidance Programmer/Computer Altitude Selector/Alerter Removal - Altitude Selector/Alerter Installation - Altitude Selector/Alerter Altitude Transducer Removal - Altitude Transducer Installation - Altitude Transducer Autopilot Disconnec
AUTOFLIGHT 1. GENERAL This chapter describes the airplane’s automated guidance system. The System 55 Autopilot offers a means of automatically or manually controlling the flight of the airplane by providing directional, heading, altitude, and attitude control. (See Figure 22-001) For additional information regarding S-TEC autopilot systems refer to the List of Publications listed in the front of this manual.
Figure 22-001 System 55 Schematic Page 2 22-00 13773-001 31 July 2001
SYSTEM 55 AUTOPILOT 1. DESCRIPTION The S-TEC System 55 is a dual axis autopilot system that provides roll stability, heading hold, NAV/GPS tracking, altitude hold, vertical speed selection, automatic glideslope capture, and automatic 45 ° intercept to desired flight path capabilities controlled via the roll-trim cartridge and pitch servo. The system components consist of a Flight Guidance Programmer/Computer, Altitude Selector/Alerter, Altitude Transducer, and Pitch Servo.
C. Altitude Transducer (See Figure 22-101) (1) (2) Removal - Altitude Transducer (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull AUTOPILOT circuit breaker. (c) Remove MFD. (Refer to 34-40) (d) Disconnect cable from altitude transducer. (e) Disconnect static line from altitude transducer. (f) Remove screws and washers securing altitude transducer to console rib. (g) Remove altitude transducer from airplane.
Figure 22-101 System 55 Installation 13773-001 31 July 2001 22-10 Page 3
E. Pitch Servo (See Figure 22-102) (1) Removal - Pitch Servo (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull AUTOPILOT circuit breaker. (c) Remove baggage floor carpet and access panel CF5. (Refer to 6-00) (d) Disconnect pitch servo plug from socket. Note: Note location of bridle clamps on outboard elevator cable to facilitate reinstallation. (e) (2) (3) (4) Page 4 Loosen nuts securing bridle clamps to elevator outboard cable and remove bridle from cable.
(5) Adjustment/Test - Pitch-Servo Torque (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) P/N or Spec. Spanner Adapter (1 of 2) 6622-1 Spanner Adapter (2 of 2) 6624-1 Supplier One S-TEC Way Municipal Airport Mineral Wells, TX 76067-9236 ““ Purpose Torque Adjustment ““ Insert pins of spanner adapter into capstan tooling holes. Position dial torque wrench to spanner adapter. Push servo flapper down and adjust clutch torque to 35.0 ± 3.0 in-lbs (3.9 ± 0.3 Nm).
Note: (i) (j) (k) (l) Page 6 While tightening bridal clamp to elevator cable, capstan will rotate. Offset this rotation while adjusting opposite bridal cable tension so that when specified tension is reached, the middle spanner adapter tooling hole is at the 12 o’clock position (stop-ball at top of capstan). At aft bridal clamp assembly, push clamp assembly aft while tightening clamp to elevator cable. Using the techniques described above, adjust bridal cable tension to 17.0 +/- 4.0 lb (7.7 +/ - 1.
Figure 22-102 Pitch Trim Servo Installation 13773-001 31 July 2001 22-10 Page 7
CHAPTER COMMUNICATIONS
CHAPTER 23 - COMMUNICATIONS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 23-LOEP 1 30 NOV 2000 23-TOC 1 30 NOV 2000 23-00 1 30 NOV 2000 23-00 2 30 NOV 2000 23-10 1 30 NOV 2000 23-50 1 30 NOV 2000 23-50 2 30 NOV 2000 23-50 3 30 NOV 2000 13773-001 30 Nov 2000 23-LOEP Page 1
CHAPTER 23 - COMMUNICATIONS TABLE OF CONTENTS Subject COMMUNICATIONS Chapter/Section Page 23-00 General SPEECH COMMUNICATIONS 1 23-10 Description 1 Maintenance Practices 1 Garmin GNS 430 GPS/COM/NAV AUDIO INTEGRATING 1 23-50 Description 1 Maintenance Practices 1 Garmin GMA 340 Audio Control Unit Removal - Garmin GMA 340 Audio Control Unit Installation - Garmin GMA 340 Audio Control Unit Inspection/Check - Garmin GMA 340 Audio Control Unit Audio Jacks Removal - Cockpit Audio Jacks Installatio
COMMUNICATIONS 1. GENERAL This chapter describes the systems, units, components which provide a means of communicating from one part of the airplane to another and between the airplane and other airplanes or ground stations. Included are voice and continuous wave communicating components and intercom.
Figure 23-001 Communications System Page 2 23-00 13773-001 30 Nov 2000
SPEECH COMMUNICATIONS 1. DESCRIPTION This section covers the systems which utilize the voice to transmit and/or receive messages from air-to-air or air-to-ground. For additional maintenance practice information refer to the appropriate Garmin Installation Manual indexed in the front of this manual. The speech communications system consists of two digitally-tuned integrated VHF communications (COM) transceiver.
AUDIO INTEGRATING 1. DESCRIPTION This section covers the portion of the system which controls the output of the communications and navigation receivers into the flight crew headphones and speakers, and the output of the flight crew microphones into the communications transmitters. Included are the audio control panel, audio jacks, cockpit loud speaker, and push-to-talk (PTT) switch.
4 5 Copilot PA microphone speaker output level MUSIC1 mute trip level B. Audio Jacks (See Figure 23-501) (1) (2) (3) (4) Removal - Cockpit Audio Jacks (a) Open center console armrest and remove glove box. (Refer to 25-10) (b) Remove nut, shoulder washer, and nylon washer securing jack to console. (c) Disconnect audio harness leads from jack and remove from airplane. Installation - Cockpit Audio Jacks (a) Connect audio harness lead to jack and position in console.
Figure 23-501 Audio Integration 13773-001 30 Nov 2000 23-50 Page 3
CHAPTER ELECTRICAL POWER
CHAPTER 24 - ELECTRICAL POWER LIST OF EFFECTIVE PAGES Chapter/Section Page Date 24-LOEP 1 31 JULY 2001 24-TOC 1 30 NOV 2000 24-TOC 2 30 NOV 2000 24-00 1 30 NOV 2000 24-00 2 30 NOV 2000 24-00 3 30 NOV 2000 24-30 1 30 NOV 2000 24-30 2 30 NOV 2000 24-30 3 30 NOV 2000 24-30 4 30 NOV 2000 24-30 5 30 NOV 2000 24-30 6 30 NOV 2000 24-30 7 30 NOV 2000 24-30 8 30 NOV 2000 24-30 9 30 NOV 2000 24-30 10 30 NOV 2000 24-30 11 30 NOV 2000 24-30 12 30 NOV 2000 24-30
CHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS Subject ELECTRICAL POWER Chapter/Section Page 24-00 General 1 Troubleshooting 1 DC GENERATION 24-30 Description 1 Alternator 1 Alternator 2 Master Control Unit (MCU) Low Volts Warning Light ALT 1 and ALT 2 Fail Lights Volt and Ampere Meter Ammeter Select Switch Battery 1 Battery 2 Maintenance Practices 2 2 2 3 3 4 4 4 4 5 Alternator 1 (Forward Alternator) Removal Installation Alternator 2 (Aft Alternator) Removal Installation Master Control Unit
CHAPTER 24 - ELECTRICAL POWER TABLE OF CONTENTS Subject Chapter/Section Removal - Battery 1 Installation - Battery 1 Adjustment/Test - Battery 1 Specific Gravity Inspection/Check - Battery 1 Capacity Battery Charging (Battery 1) Battery 2 Removal - Battery 2 Installation - Battery 2 Top-charging (Battery 2) EXTERNAL POWER Page 14 15 15 16 16 18 18 18 18 24-40 Description 1 Maintenance Practices 1 External Power Receptacle Removal - Refer to MCU removal. Installation - Refer to MCU removal.
ELECTRICAL POWER 1. GENERAL The information in this chapter covers DC Generation, External Power, and Electrical Load Distribution. This airplane is equipped with a 28-volt direct-current (VDC) electrical system. Two alternators and two batteries are used to ensure sufficient electrical power. Electrical power is supplied to the essential bus from both batteries and both alternators.
Troubleshooting Power Generation System Trouble Battery will not hold charge Short battery life (Battery 1) External Power Receptacle Inoperable Low Volts Light Illuminates Probable Cause Remedy Flights too short to recharge suffi- Remove corresponding battery ciently and recharge when necessary Loose connections, corrosion Tighten, clean, and neutralize connections Faulty battery Replace corresponding battery Standing too long (hot climate) Remove corresponding battery and recharge when necessar
Figure 24-001 Electrical Power and Distribution 13773-001 30 Nov 2000 24-00 Page 3
DC GENERATION 1. DESCRIPTION This section covers the systems to generate, regulate, control, and indicate DC electrical power. The DC generation portion of the system includes the batteries, alternators (with internal rectifiers), and regulator. Two batteries (battery 1 and battery 2) and two alternators (alternator 1 and alternator 2) are used in the power generation system on this airplane. Both batteries are used for power storage. The two alternators are very similar in design to each other.
A. Alternator 1 The front alternator (alternator 1) is mounted directly to the front of the engine on the co-pilots’ side. Alternator 1 is a 60-amp (rated at 58-amps) engine-driven alternator. Alternator 1 is controlled by the ALT 1 master switch located in the bolster panel. Battery 1 and alternator 1 are independently controlled and can be alternately connected to main bus 2. Failure or malfunction of alternator 1 will not impair the capability of the main battery to provide power to main bus 2.
The master switch arrangement, located in the pilot's bolster contains battery 1, battery 2, alternator 1, and alternator 2 control switches. Each switch disconnects the associated device from the corresponding bus. The switches are located in a side-by-side arrangement and are labeled as to their function. The BAT 2 switch, when closed, connects battery 2 to the essential bus. This switch activates a relay located next to BAT 2, providing the ability to connect and disconnect battery 2 from the aircraft.
F. Volt and Ampere Meter A combination Volt and Ampere meter is mounted on the right instrument panel immediately outboard of the oil temperature and pressure gage. The AMP pointer sweeps a scale from -60 to +60 amps with zero at the 9 o'clock position. The ammeter will indicate the current generation provided by Alternator 1, Alternator 2, and the charge or discharge status of battery 1. The VOLT pointer sweeps a scale from 16 to 32 volts.
2. MAINTENANCE PRACTICES A. Alternator 1 (Forward Alternator) (1) (2) 13773-001 30 Nov 2000 Removal (a) Verify ignition switch is in the off position and remove the key. (Refer to POH) (b) Ensure BAT 1, BAT 2 and AVIONICS master switches are in the off position. (c) Remove engine cowling. (Refer to 71-10) (d) Disconnect battery and insulate battery terminals to prevent accidental connection. (Refer to 24-30) (e) Identify each wire from the alternator terminals and disconnect.
Figure 24-301 Alternator One (Forward Alternator) Page 6 24-30 13773-001 30 Nov 2000
B. Alternator 2 (Aft Alternator) (1) (2) 13773-001 30 Nov 2000 Removal (a) Verify ignition switch is in the off position and remove the key. (Refer to POH) (b) Ensure BAT 1, BAT 2 and AVIONICS master switches are in the off position. (c) Remove engine cowling. (Refer to 71-10) (d) Disconnect battery and insulate battery terminals to prevent accidental connection. (Refer to 24-30) (e) Identify each wire from the alternator terminals and disconnect. (f) Remove the alternator mounting nuts and washers.
Figure 24-302 Alternator 2 (Aft alternator) Page 8 24-30 13773-001 30 Nov 2000
C. Master Control Unit (MCU) (1) (2) 13773-001 30 Nov 2000 Removal - MCU (a) Verify the ignition switch is in the off position and remove the key. (Refer to POH) (b) Ensure BAT 1, BAT 2, and AVIONICS master switches are in the off position. (c) Remove the engine cowling. (Refer to 71-10) (d) Disconnect battery and insulate battery terminals to prevent accidental connection. (Refer to 24-30) (e) Identify and disconnect all wires from the MCU.
Figure 24-303 Master Control Unit (MCU) Page 10 24-30 13773-001 30 Nov 2000
D. Low-Volts Warning Light (Annunciator Panel) (1) (2) Removal - (Refer to 31-50) Installation - (Refer to 31-50) E. ALT 1 and ALT 2 Fail Lights (Annunciator Panel) (1) (2) F. Removal - ALT 1 and ALT 2 Fail Lights (a) Verify the ignition switch is in the off position and remove the key. (Refer to POH) (b) Ensure BAT 1, BAT 2, and AVIONICS master switches are in the off position. (c) Pull BAT 2 circuit breaker to the off position. (d) Remove the engine cowling.
G. Ammeter Select Switch (1) (2) Removal - Ammeter Select Switch (a) Verify the ignition switch is in the off position and remove the key. (Refer to POH) (b) Ensure BAT 1, BAT 2, and AVIONICS master switches are in the off position. (c) Pull BAT 2 circuit breaker to the off position. (d) Remove the engine cowling. (Refer to 71-10) (e) Disconnect primary battery and insulate battery terminals to prevent accidental connection. (Refer to 24-30) (f) Remove the MFD.
Note: (a) The battery should be removed from the airplane prior to inspection. The battery box should be washed out thoroughly and dried each time the battery is removed. The battery vent hose should be inspected periodically for any damage, kinks or obstructions. If adding distilled water in freezing weather, charge battery long enough to mix electrolyte and water. Never use a wire brush to clean the battery; instead use a brush with non-conductive bristles. Acquire necessary tools and equipment.
(d) Inspect the battery box for corrosion and spilled electrolyte. If the battery box, battery cables, or battery terminals need to be cleaned, use a solution of bicarbonate of soda and clean fresh water. Do not allow bicarbonate of soda to enter the battery cells. CAUTION: (2) When cleaning a battery, never allow bicarbonate of soda to enter the battery cells or permanent battery damage will result. (e) Rinse the battery with clean fresh water and wipe clean with a dry cloth.
(3) Installation - Battery 1 (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) P/N or Spec. Supplier Purpose Contact Cleaner - Any Source Clean terminals Non-conductive Bristle Brush - Any Source Clean terminals Petroleum Jelly W-P-236 Any Source Prevent corrosion Examine battery contacts. Any dirt or corrosion should be gently removed using electrical contact cleaner and a stiff brush. Install battery into battery hold-down bracket and secure the bracket.
returned to the same cell from which it was taken. The electrolyte should have a specific gravity of 1.225 or above to avoid freezing. (e) CAUTION: To prevent contamination from one cell to the other, immediately reinstall cell caps into their original location after testing the specific gravity. Note: If the level is too low for accurate hydrometer readings, add just enough distilled water to cover the plates and charge the battery to mix the electrolyte.
If it is necessary to prepare electrolyte to 1.285 specific gravity from concentrated sulfuric acid, always pour the acid into the water, not the water into the acid. Use non-metallic receptacles and/or funnels except for lead or lead-lined containers. While charging Battery 1, the battery cell caps must be installed. Electrolyte splashed into the eyes is extremely dangerous. If this should happen, force the eye open and flood it with cool, clean water for approximately five minutes.
(h) Continue charging until the voltage and specific gravity readings are constant over three readings taken at 1/2-hour intervals. CAUTION: (i) (j) (k) (l) I. To prevent contamination from one cell to the other, immediately reinstall cell caps into their original location after testing the specific gravity. Turn off and unplug the battery charger. Disconnect negative battery charger lead first and then disconnect positive battery charger lead. Rinse the battery off with clean fresh water.
WARNING: Charging batteries in an airplane or within 10 feet of a fuel servicing area is prohibited by the National Electric Code. If battery 2 becomes damaged and electrolyte is spilled or splashed on clothing or the body, it should be neutralized immediately with a solution of baking soda and water and then rinsed with clean water. Electrolyte splashed into the eyes is extremely dangerous. If this should happen, force the eye open and flood it with cool, clean water for approximately five minutes.
Figure 24-304 Battery 2 Page 20 24-30 13773-001 30 Nov 2000
EXTERNAL POWER 1. DESCRIPTION The external power connector is mounted on the Master Control Unit (MCU). The MCU is mounted on the left side of the fuselage, just forward of the firewall. The receptacle is comprised of a three-contact connector. The long contacts are used for transferring power. The shorter, third connector, engages the external power relay located in the MCU, which connects the external power to the Main Distribution Bus.
Figure 24-401 External Power Receptacle Page 2 24-40 13773-001 30 Nov 2000
ELECTRICAL LOAD DISTRIBUTION 1. DESCRIPTION The power distribution system for this airplane consists of the main distribution bus and the essential distribution bus in the MCU along with the associated buses in the circuit breaker panel and their associated circuit breakers and switches. Each bus and circuit are labeled on the circuit breaker panel. The clock bus is fused within the MCU and is the only bus not connected to the master switch arrangement.
(1) BAT & ALT Master Switches Note: Prior to engine start-up, the pilot must activate only the BAT 2 switch to verify that BAT 2 properly energizes the electrical loads powered by the ESSENTIAL Bus and that BAT 2 has proper voltage. The voltage reading must be taken from the combination Volt and Ampere meter mounted on the right instrument panel. Use BAT 1 for suppling electrical power to the avionics system when performing general servicing tests.
2. MAINTENANCE PRACTICES A. Circuit Breakers (1) Removal - Circuit Breakers (a) Verify the ignition switch is in the OFF position and remove the key. (b) Disconnect both batteries (BAT 1 and BAT 2). (Refer to 24-30) (c) Remove the two aft screws securing circuit breaker panel to the center console. Swing the panel open. (d) Identify and disconnect all wires to the selected breaker and/or bus. (e) Remove the retaining ring from the circuit breaker and remove the breaker.
Figure 24-501 Circuit Breaker Panel (Sheet 1 of 2) Page 4 24-50 13773-001 30 Nov 2000
Figure 24-502 Circuit Breaker Panel (Sheet 2 of 2) 13773-001 30 Nov 2000 24-50 Page 5
CHAPTER EQUIPMENT AND FURNISHINGS
CHAPTER 25 - EQUIPMENT AND FURNISHINGS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 25-LOEP 1 31 JUL 2001 25-TOC 1 31 JUL 2001 25-TOC 3 31 JUL 2001 25-00 1 30 NOV 2000 25-10 1 31 JUL 2001 25-10 2 30 NOV 2000 25-10 3 31 JUL 2001 25-10 4 30 NOV 2000 25-10 5 31 JUL 2001 25-10 6 31 JUL 2001 25-10 7 31 JUL 2001 25-10 8 31 JUL 2001 25-10 9 31 JUL 2001 25-50 1 31 JUL 2001 25-50 2 31 JUL 2001 25-60 1 30 NOV 2000 25-60 2 30 NOV 2000 25-60 3 30 NOV 2000 25
CHAPTER 25 - EQUIPMENT AND FURNISHINGS TABLE OF CONTENTS Subject EQUIPMENT AND FURNISHINGS Chapter/Section Page 25-00 General CABIN 1 25-10 Description 1 Maintenance Practices 1 Crew Seats Removal - Crew Seats Installation - Crew Seats Inspection/Check - Crew Seats Cleaning - Crew Seats Passenger Seats Removal - Passenger Seats Installation - Passenger Seats Cleaning - Passenger Seats Rear Seat Harness Removal - Rear Seat Harness Installation - Rear Seat Harness Trim Removal - Glareshield Assembly
CHAPTER 25 - EQUIPMENT AND FURNISHINGS TABLE OF CONTENTS Subject Chapter/Section Installation - Right Aft Console Lower Panel Removal - Left Aft Console Lower Panel Installation - Left Aft Console Lower Panel Removal - Center Armrest Console Installation - Center Armrest Console Removal - Aft Console Rear Cover Installation - Aft Console Rear Cover Removal - Side Duct Cover Panel Installation - Side Duct Cover Panel Removal - Right Aft Console Trim Installation - Right Aft Console Trim Removal - Left Aft
CHAPTER 25 - EQUIPMENT AND FURNISHINGS TABLE OF CONTENTS Subject EMERGENCY Chapter/Section Page 25-60 DEScription 1 Emergency Locator Transmitter (ELT) Maintenance Practices 1 2 Emergency Locator Transmitter (ELT) Removal - ELT Installation - ELT Inspection Check - ELT ELT Function Test ELT and Remote Control Panel Indicator (RCPI) Batteries Removal - ELT Battery ELT Remote Control Panel Indicator (RCPI) Removal - Remote Control Panel Indicator Installation - Remote Control Panel Indicator Removal -
EQUIPMENT AND FURNISHINGS 1. GENERAL Interior equipment and furnishings on the airplane include forward and rear seats, four-point seat belts with inertia-reel retractors, carpeting, headliner panels, interior panels and trim, console panels and trim, center console, sunvisors, and baggage restraints. The front seats adjust on inclined tracks and can be individually reclined to three different positions. The front and rear seats feature independent fold-down features for each side.
CABIN 1. DESCRIPTION This section covers cabin compartment seats, seat harness, trim, cabin headliner, and floor covering. This airplane has two individual front seats and a split rear bench seat for two passengers. Each front (crew) seat has a four-point restraint, with inertia-reel retractors on the shoulder belts. The fore and aft travel path is adjusted through the seat position control located below the center of the seat cushion.
Figure 25-101 Passenger Seat Page 2 25-10 13773-001 30 Nov 2000
C. Rear Seat Harness (1) (2) Removal - Rear Seat Harness (See Figure 25-102) (a) Remove the bolt, washer, bushing, washer, and nylon self-locking nut from lower outboard harness mount. (b) Remove the bolt, washer, bushing, washer, and self-locking nut from lower (central) harness mount. (c) Remove the aft bulkhead trim panel and the rear headliner. (Refer to 25-50) (d) Remove the bolts, washers, and self-locking nuts from upper seat harness mount.
Figure 25-102 Rear Seat Belt Harness Page 4 25-10 13773-001 30 Nov 2000
D. Trim (1) (2) (3) (4) (5) (6) (7) 13773-001 31 Jul 2001 Removal - Glareshield Assembly (a) Remove glareshield mounting screws located just inside the aft edge on the left-hand side of the glareshield. (b) Remove glareshield mounting screws located just outside the aft edge on the right-hand side of the glareshield. (c) Disconnect GPS antenna lead located underneath the glareshield. (d) Disconnect glareshield light wire harness and remove glareshield.
(8) (9) (10) (11) (12) (13) (14) Page 6 Installation - Lower Windshield Trim (a) Install glareshield. (Refer to 34-20) (b) Secure the upper and lower A-pillar trim on both sides. (Refer to 25-10) (c) Install both forward door-seals. (Refer to 52-10) (d) Remove the protective cover from the windshield. Removal - Center Bolster Trim (a) Loosen the four screws on the bolster switch panel. (b) Lift edge of bolster trim and slowly remove the panel.
(15) Removal - Interior Door Trim (a) Remove the bolt and washer securing the door handle to the door. Remove door handle. (b) Remove the screws securing the trim to the door. (c) Gently lift the corner of the door trim and slowly release the hook and loop fasteners, and remove door trim. (16) Installation - Interior Door Trim (a) Place trim into position and firmly push down on trim in areas of hook and loop fasteners. (b) Secure trim with screws.
(29) Removal - Side Duct Cover Panel (Refer to 25-10) (a) Remove door seal. (Refer to 52-10) (b) Lift forward edge of side duct cover and slowly release the hook and loop fasteners. Remove side duct cover. (30) Installation - Side Duct Cover Panel (a) Place side duct cover into position and secure. Firmly push on trim in areas of hook and loop fasteners. (b) Install door seal. (Refer to 52-10) (31) Removal - Right Aft Console Trim (a) Unscrew friction control knob and remove. (b) Remove co-pilot seat.
G. Floor Covering (1) (2) 13773-001 31 Jul 2001 Removal - Floor Covering (a) Lift corner of carpet and pull carpet from floor to release the hook and loop fasteners. Installation - Floor Covering (a) Clean floor surface and the hook and loop fasteners using a whisk broom and a vacuum cleaner. (b) Place carpet into position and firmly push down on the hook and loop fasteners.
BAGGAGE AREA 1. DESCRIPTION This section covers the cargo floor carpet, anchor plates, and trim panels that are located directly behind the passenger seats. 2. MAINTENANCE PRACTICES A. Anchor Plates (1) (2) Removal - Anchor Plates (a) Remove carpet from cargo compartment. (Refer to 25-10) (b) Remove access panel CF5. (Refer to 6-00) (c) Remove the bolts, nuts, and washers securing the anchor plate to the floor.
(2) Page 2 (a) If required, remove screws securing floor trim. (b) Lift corner of carpet and pull up carpet from floor to release the hook and loop fasteners. Installation - Floor Covering (a) Clean floor surface and the hook and loop fasteners using a whisk broom and a vacuum cleaner. (b) Place carpet into position and firmly push down on the hook and loop fasteners. (c) If required, secure floor trim with screws.
EMERGENCY 1. DESCRIPTION A. Emergency Locator Transmitter (ELT) For specific information on the ACK model E-01 ELT, refer to the ACK Technologies Installation and Operation Manual (Manual Number 9/94). (See Figure 25-601) WARNING: The ACK model E-01 ELT is designed to use only Duracell MN1300 alkaline batteries which are dated by the manufacturer. This ELT does not meet the requirements of TSO-91a or FAR 91.207 if used with any other type of battery.
2. MAINTENANCE PRACTICES A. Emergency Locator Transmitter (ELT) (1) Removal - ELT CAUTION: (2) (a) Remove carpet from baggage compartment floor. (Refer to 25-50) (b) Remove access panel CB06. (Refer to 6-00) (c) Move the main transmitter control switch (labeled ON-OFF-ARMED) to the “OFF” position. (d) Disconnect transmitter RJ-11 plug from RJ-11 jack. (e) Disconnect fixed antenna lead from front panel on ELT. Remove portable antenna. (f) Unstrap transmitter and remove.
(3) (k) Install baggage compartment carpet. (Refer to 25-50) Inspection Check - ELT For inspection of the ACK model E-01 ELT, refer to the ACK Technologies Installation and Operation Manual (manual number 9/94). (a) (b) (c) (d) (e) (f) (g) (h) (i) (j) Remove ELT from the mount and inspect the mounting tray to ensure all fasteners and mechanical assemblies are secure. Inspect the coaxial cable connecting the ELT to the antenna for cuts or abrasions on its outer jacket.
Note: (4) Because the ELT radiates on the emergency frequency, the federal communications commission allows these tests to be conducted only within the first five minutes after any hour and limits the tests to three sweeps of the transmitter audio modulation. (k) Verify that all switches are properly labeled and positioned. (l) Perform ELT function test.
(a) (b) (c) Remove the three retaining screws which secure the upper and lower half of the RCPI unit. Loosen the two switch retaining nuts located on the front of the unit. Carefully remove the top half of the RCPI unit exposing the battery compartment. Note: (d) (e) (f) (g) If replacing an old battery carefully inspect the battery contacts for dirt or corrosion. If the contacts need cleaning use only nonabrasive electrical contact cleaner and a stiff brush.
Figure 25-601 Emergency Locator Transmitter Page 6 25-60 13773-001 30 Nov 2000
CHAPTER FIRE PROTECTION
CHAPTER 26 - FIRE PROTECTION LIST OF EFFECTIVE PAGES Chapter/Section Page Date 26-LOEP 1 30 NOV 2000 26-TOC 1 30 NOV 2000 26-00 1 30 NOV 2000 26-20 1 30 NOV 2000 26-20 2 30 NOV 2000 13773-001 30 Nov 2000 26-LOEP Page 1
CHAPTER 26 - FIRE PROTECTION TABLE OF CONTENTS Subject FIRE PROTECTION Chapter/Section Page 26-00 General EXTINGUISHING 1 26-20 Description 1 Maintenance Practices 1 Fire Extinguisher Removal - Fire Extinguisher Installation - Fire Extinguisher Operation - Fire Extinguisher Inspection/Check - Fire Extinguisher 13773-001 30 Nov 2000 1 1 1 1 1 26-TOC Page 1
FIRE PROTECTION 1. GENERAL This chapter describes that portion of the airplane system which is used to extinguish fire. Fire protection is provided by a portable Halon 1211/1301 fire extinguisher, mounted on the forward inboard side of the pilot’s seat base.
EXTINGUISHING 1. DESCRIPTION The airplane is equipped with a liquefied-gas type fire extinguisher mounted within a quick-release bracket assembly attached at the forward inboard side of the pilot’s seat base. The extinguishing agent is Halon 1211/1301 blend and is approved for use on class B (liquid, grease) and class C (electrical equipment) fires. The fire extinguisher must be replaced after each use. 2. MAINTENANCE PRACTICES A.
Figure 26-201 Fire Extinguisher Installation Page 2 26-20 13773-001 30 Nov 2000
CHAPTER FLIGHT CONTROLS
CHAPTER 27 - FLIGHT CONTROLS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 27-LOEP 1 31 JULY 2001 27-LOEP 2 31 JULY 2001 27-TOC 1 31 JULY 2001 27-TOC 2 31 JULY 2001 27-TOC 3 31 JULY 2001 27-TOC 4 31 JULY 2001 27-00 1 30 NOV 2000 27-00 2 30 NOV 2000 27-10 1 30 NOV 2000 27-10 2 30 NOV 2000 27-10 3 30 NOV 2000 27-10 4 30 NOV 2000 27-10 5 30 NOV 2000 27-10 6 30 NOV 2000 27-10 7 30 NOV 2000 27-10 8 30 NOV 2000 27-10 9 30 NOV 2000 27-10 10 30 NOV 2000 2
CHAPTER 27 - FLIGHT CONTROLS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 27-20 10 30 NOV 2000 27-20 11 30 NOV 2000 27-20 12 30 NOV 2000 27-20 13 30 NOV 2000 27-20 14 31 JULY 2001 27-20 15 31 JULY 2001 27-20 16 31 JULY 2001 27-20 17 31 JULY 2001 27-30 1 30 NOV 2000 27-30 2 30 NOV 2000 27-30 3 30 NOV 2000 27-30 4 30 NOV 2000 27-30 5 30 NOV 2000 27-30 6 30 NOV 2000 27-30 7 30 NOV 2000 27-30 8 30 NOV 2000 27-30 9 30 NOV 2000 27-30 10 30 NOV 2000 27-
CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS Subject FLIGHT CONTROLS Chapter/Section Page 27-00 General 1 Troubleshooting 2 AILERON AND ROLL TRIM SYSTEM 27-10 Description 1 Maintenance Practices 1 Aileron System Cables Removal - Aileron System Cables Installation - Aileron System Cables Adjustment/Test - Aileron System Rigging Inspection/Check - Aileron System Rigging Control Grip Assembly Removal - Control Grip Assembly Installation - Control Grip Assembly 4-Way Trim/Autopilot Disconnect Sw
CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS Subject Chapter/Section Removal - Cross-Over Pulley Installation - Cross-Over Pulley Roll Trim System Removal - Aileron Actuation Pulley-Wing Installation - Aileron Actuation Pulley-Wing Removal - Roll Trim Cartridge Installation - Roll Trim Cartridge Adjustment/Test - Roll Trim Cartridge Inspection/Check - Roll Trim Cartridge Removal - Roll Trim Motor Assembly Installation - Roll Trim Motor Assembly RUDDER AND YAW TRIM SYSTEM Page 15 15 18 18 18 18 18 20 20
CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS Subject Chapter/Section Page Removal - Yaw Trim Gage Installation - Yaw Trim Gage Rudder-Aileron Interconnect Removal - Rudder-Aileron Interconnect Installation - Rudder-Aileron Interconnect Adjustment/Test - Rudder-Aileron Interconnect Inspection/Check - Rudder-Aileron Interconnect ELEVATOR AND PITCH TRIM SYSTEM 15 15 15 15 15 15 16 27-30 Description 1 Maintenance Practices 1 Elevator System Rigging Removal - Elevator System Cable Installation - Eleva
CHAPTER 27 - FLIGHT CONTROLS TABLE OF CONTENTS Subject Chapter/Section Stall Warning Pressure Switch Removal - Stall Warning Pressure Switch Installation - Stall Warning Pressure Switch Inspection/Check - Stall Warning Operational Check - Ground Inspection/Check - Stall Warning Operational Check - Flight Stall Warning Horn Removal - Stall Warning Horn Installation - Stall Warning Horn FLAPS Page 1 1 1 1 2 2 2 2 27-50 General 1 Maintenance Practices 1 Flap Actuator Assembly Removal - Flap Actuator A
FLIGHT CONTROLS 1. GENERAL This chapter describes those units and components which furnish a means of manually controlling the flight attitude characteristics of the airplane. The flight controls for the airplane consist of ailerons, roll trim cartridges, rudder, elevator, pitch trim cartridges, and flap system.
2.
AILERON AND ROLL TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the ailerons. Included are; aileron system rigging, control grip assembly, control yoke assembly, V-groovedguide wheel, pulleys and cables, roll trim cartridge, and 4-way trim/autopilot disconnect switch. Aileron control motion is transferred by conventional yoke motion through a linkage to a pulley mounted on the console structure.
(k) (l) (m) Remove cotter pins and washers securing pulley guard pins to forward pulley gang bracket and remove pins. Remove safety wire securing aileron cable to console actuation pulley. Loosen nuts securing pulley keepers to console. Note: Attach string to end of cable prior to removing from airplane to facilitate cable routing during installation. (n) (2) Attach string to end of forward aileron cable below access hole CF3C and pull cable through. Remove cable from airplane.
Figure 27-101 Aileron System Cables 13773-001 30 Nov 2000 27-10 Page 3
(3) Adjustment/Test - Aileron System Rigging Note: (a) All control surface cable tensions should be rigged at an ambient temperature of 70°. Allow temperature to stabilize for a period of four hours before setting cable tensions. Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) P/N or Spec. Supplier Purpose WS 144 Rigging Template - Cirrus Design Corp.
WARNING: (p) Turning control yoke counterclockwise should put left aileron trailing edge in raised position. If this is not true, system is improperly rigged. The system MUST BE RIGGED CORRECTLY. Check for crossed or wrapped cables. Rotate control yoke counterclockwise placing LH aileron in raised position. Note: Aileron removal may be necessary to facilitate aileron travel limits/stop adjustments. (q) (4) Adjust stop screws at LH aileron actuation pulley to allow 12.
(b) (c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) (n) (o) (p) (q) (r) (s) Page 6 Defuel airplane. (Refer to 12-20) Verify gap between aileron leading edge and trailing edge of wing has a minimum of 0.110 inch (2.8 mm) and a maximum of 0.200 inch (5.0 mm) clearance when aileron is fully deflected, trailing edge down. In the area near the aileron actuation arm where there is no leading edge cover, the minimum shall be 0.125 inch (3.2 mm). Verify overlap between aileron and wing has a minimum of 0.
Minimum Maximum Min. at Actuation Arm Max. Adjacent to Aileron Cove Leading Edge Gap 0.110" 2.8 mm 0.200" 5.1 mm 0.125" 3.2 mm - Overlap 0.010" 0.25 mm 0.125" 3.2 mm - - Neutral Position Gap 0.060" 1.5" 0.210" 5.3 mm - 0.150" 3.
B. Control Grip Assembly (See Figure 27-103) (1) Removal - Control Grip Assembly (a) Acquire necessary tools, equipment, and supplies. Description Pin Extractor (2) P/N or Spec. 305183 Supplier AMP Purpose Removal of connector pins. (b) Remove kick plate. (Refer to 25-10) (c) Remove seat. (Refer to 25-10) (d) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (e) Pull AUTOPILOT, PITCH TRIM, and ROLL TRIM circuit breakers.
Figure 27-103 Control Grip Assembly Installation 13773-001 30 Nov 2000 27-10 Page 9
D. Push-to-Talk (PPT) Switch (See Figure 27-103) (1) Removal - Push-to-Talk (PPT) Switch (a) Remove screws securing switch plate assembly to top of control grip to gain access to switch terminals. CAUTION: (2) Identify and mark electrical leads prior to cutting to facilitate reinstallation. (b) Cut electrical leads from push-to-talk switch as close to switch base as possible. (c) Remove bezel and unscrew push-to-talk switch from grip.
Figure 27-104 Control Yoke Assembly (Sheet 1 of 2) 13773-001 30 Nov 2000 27-10 Page 11
Figure 27-104 Control Yoke Assembly (Sheet 2 of 2) Page 12 27-10 13773-001 30 Nov 2000
(3) F. Inspection/Check - Control Yoke Assembly (a) Remove seat. (Refer to 25-10) (b) Remove kick plate. (Refer to 25-10) (c) Verify zero vertical play exists between yoke tube and V-grooved-guide wheels. (d) Verify V-grooved-guide wheel bolts torqued to 50-55 inch lb (5.5-6.1 Nm). (e) Verify positive clearance and proper operation of control yoke assembly through full range of motion. (f) Verify yoke movement free of resistance. (g) Verify yoke tubes/bearing free of grit build-up.
H. Aileron System Pulleys (See Figure 27-105) (1) (2) (3) Removal - Aileron Actuation Pulley-Console (a) Remove carpeting and access panel CF3C from passenger compartment floor. (Refer to 6-00) (b) Identify and loosen aileron cable tension via turnbuckle. (c) Remove MFD. (Refer to 34-40) (d) Remove cotter pin, castellated nut, washers, and bolt securing aileron push/pull rods to aileron actuation pulley. (e) Cut safety wire securing cable to aileron actuation pulley.
(d) (e) (6) (7) (8) 13773-001 30 Nov 2000 Remove cotter pins and washers securing cable retainer clevis pins to pulley brackets Remove cotter pin, nut, washers, and bolt securing kick-out pulley to pulley brackets and remove from airplane. Installation - Kick-Out Pulley (a) Install pulley, bolt, washers, nut, and cotter pin securing kick-out pulley to brackets. (b) Position cable on pulley and install cable retainer clevis pins, washers, and cotter pins.
Figure 27-105 Aileron System Pulleys (Sheet 1 of 2) Page 16 27-10 13773-001 30 Nov 2000
Figure 27-105 Aileron System Pulleys (Sheet 2 of 2) 13773-001 30 Nov 2000 27-10 Page 17
I. Roll Trim System(See Figure 27-106) (1) (2) Removal - Aileron Actuation Pulley-Wing (a) Remove passenger compartment seats. (Refer to 25-10) (b) Remove carpeting and access panels CF3C and CF4C (Refer to 6-00) from passenger compartment. (c) Identify and loosen aileron cable tension via turnbuckles. (d) Remove ailerons. (Refer to 57-50) (e) Remove aileron cove access panel. (Refer to 6-00) (f) Cut safety wire securing cable to aileron actuation pulley.
Figure 27-106 Roll Trim System Installation 13773-001 30 Nov 2000 27-10 Page 19
(5) Adjustment/Test - Roll Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description Inclinometer (b) (c) (d) P/N or Spec. PRO360 Supplier Maclanburg Duncan Purpose Deflection Angle Determination Remove MFD. (Refer to 34-40) Insert lock-out pin at aileron actuation pulley in center console. Remove LH aileron.
(7) (8) 13773-001 30 Nov 2000 (i) Verify minimum rod end thread engagement of 0.312 inch (0.79 cm). (j) Verify proper installation of safety wires and cotter pins on all fasteners. Removal - Roll Trim Motor Assembly (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull ROLL TRIM circuit breaker. (c) Remove LH aileron. (Refer to 57-50) (d) Remove aileron cove access panel. (Refer to 6-00) (e) Slightly loosen trim motor assembly to facilitate trim cartridge removal.
RUDDER AND YAW TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the rudder. Included are; rudder system rigging, rudder pedal assembly, pulleys, cables and bellcranks, rudder-aileron interconnect, and yaw trim system. Rudder control is transferred by conventional rudder pedals through to the forward pulley gang at the bottom of the center console.
(2) Page 2 (j) At access hole CF5 pull forward rudder cables through and remove cables from airplane. Installation - Rudder System Cables (a) Install empennage pulley gang. (Refer to 27-20) (b) At access hole CF5, install turnbuckles on forward and aft rudder cables. (c) At rudder pedal torque tubes, route forward rudder cable through mid and forward pulleys gangs. (d) Install bolts, washers, nuts and cotter pins securing rudder cables to rudder pedal torque tubes.
Figure 27-201 Rudder System Cables 13773-001 30 Nov 2000 27-20 Page 3
(3) Adjustment/Test - Rudder System Rigging Note: (a) All control surface cable tensions should be rigged at an ambient temperature of 70°. Allow temperature to stabilize for a period of four hours before setting cable tensions. Acquire necessary tools, equipment, and supplies. Description Wood Block (b) (c) (d) (e) (f) (g) (h) (k) (l) (m) Page 4 - Supplier Any Source Purpose Spacer Remove baggage compartment carpet and access panel CF5.
(4) Inspection/Check - Rudder System Rigging (See Figure 27-202) Note: If the following rudder leading edge gap and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service Department for disposition. The following rudder gap and overlap inspections apply only to the area between the waterline of the horizontal stabilizer to the tip of the vertical stabilizer (a) Acquire necessary tools, equipment, and supplies.
Minimum Maximum Leading Edge Gap 0.060" 1.5" 0.150" 3.8 mm Overlap 0.000" 0.0 mm 0.125" 3.
B. Rudder Pedal Assembly (See Figure 27-203) (1) (2) (3) 13773-001 30 Nov 2000 Removal - Rudder Pedal Assembly (a) Remove pilot and co-pilot seats. (Refer to 25-10) (b) Remove left mid console circuit breaker trim panel. (Refer to 25-10) (c) Remove carpeting and access panel CF5 from baggage compartment floor. (Refer to 600) (d) Identify and loosen rudder cable tension via turnbuckle. (e) Remove yaw trim cartridge.
Figure 27-203 Rudder Pedal Installation Page 8 27-20 13773-001 30 Nov 2000
C. Rudder System Pulleys and Bellcranks (See Figure 27-204), (See Figure 27-205) (1) Pulley Gang-Forward The forward pulley gang is used to route the aileron, rudder, and elevator system control cables. Maintenance practices pertinent to the forward pulley gang are covered under the Aileron and Roll Trim System. (Refer to 27-10) (2) Removal - Rudder-Elevator Pulley Gang (a) Remove carpeting and access panel CF5 from baggage compartment floor.
(c) (6) Page 10 Insert pulley gang into empennage and position gang assembly over vertical stabilizer bulkhead holes. Install bolts securing pulley gang to bulkhead. (d) Screw rudder push/pull rod onto rod end attached to rudder actuation pulley and tighten jam nut. (e) Screw elevator push/pull rod onto rod end attached to elevator actuation pulley and tighten jam nut. (f) Install bolt, spacer, washer, castellated nut, and cotter pin securing rudder push/pull rod to rudder bell crank.
Figure 27-204 Rudder-Elevator Pulley Gang 13773-001 30 Nov 2000 27-20 Page 11
Figure 27-205 Empennage Pulley Gang (Sheet 1 of 2) Page 12 27-20 13773-001 30 Nov 2000
Figure 27-205 Empennage Pulley Gang (Sheet 1 of 2) 13773-001 30 Nov 2000 27-20 Page 13
D. Yaw Trim Cartridge (See Figure 27-203) (1) (2) (3) Removal - Yaw Trim Cartridge (a) Remove left mid console circuit breaker trim. (Refer to 25-10) (b) Remove cotter pin, castellated nut, washers, bushing, spacers, and bolt securing trim cartridge to console bracket. (c) Remove cotter pin, castellated nut, washers, and bolt securing trim cartridge push/pull rod to left torque tube actuation arm and remove from airplane.
F. Yaw Trim Gage (1) (2) Removal - Yaw Trim Gage (a) Disconnect Pitch/Yaw Trim circuit breaker. (b) Remove screws securing gage to center console. (c) Disconnect yaw trim gage connector and remove from airplane. Installation - Yaw Trim Gage (a) Connect yaw trim gage connector. (b) Position yaw trim gage connector to center console and secure with screws. (c) Reset Pitch/Yaw Trim circuit breaker G.
(f) (4) Page 16 Remove excess slack from interconnect arm to forward clamp by pulling excess bungee through clamp. (g) Set roll trim to full left. (h) Remove excess slack from interconnect arm to aft clamp by pulling excess bungee through clamp. (i) Position aileron rigging template on wing. (j) Verify that steady rudder application will move the ailerons the required travel while also ensuring that at full aileron trim travel, the bungee does not get tensioned.
Figure 27-206 Rudder-Aileron Interconnect Installation 13773-001 31 July 2001 27-20 Page 17
ELEVATOR AND PITCH TRIM SYSTEM 1. DESCRIPTION This section describes that portion of the flight control system which controls the position and movement of the elevator. Included are; elevator system torque tube, rigging, push/pull rods, pulleys, and pitch trim cartridge. Elevator control motion is transferred by conventional yoke motion through a linkage to a pulley sector mounted on the elevator torque tube.
(2) Page 2 Installation - Elevator System Cable (a) Install empennage pulley gang. (Refer to 27-20) (b) At access hole CF5, install turnbuckles on forward and aft elevator cables. (c) At access hole CF5, route forward elevator cable through forward and mid pulleys gangs. (d) Install screws, washers, and nuts securing elevator cables to elevator pulley sector. (e) At forward pulley gang, verify cable routing, insert pulley guard pins, and install washers and cotter pins.
Figure 27-301 Elevator System Cables 13773-001 30 Nov 2000 27-30 Page 3
(3) Adjustment/Test - Elevator System Rigging Note: (a) All control surface cable tensions should be rigged at an ambient temperature of 70°. Allow temperature to stabilize for a period of four hours before setting cable tensions. Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) Page 4 Supplier Purpose BL 60 Template Reserved Cirrus Design Corp. Elevator Rigging BL 12 Template Reserved Cirrus Design Corp.
1 2 (o) (p) (q) (r) (s) (t) (u) 13773-001 30 Nov 2000 the empennage elevator actuation pulley stops contact before secondary stops, secondary stops mounted on either control yoke assemblies show a 0.035 inch +/0.020 (0.89 mm +/- 0.51 mm) gap between stop and yoke bearing mount. Verify trim cartridge minimum rod end thread engagement of 0.312 inch (0.79 cm). Tighten jam nuts. Perform Pitch Trim Inspection/Check. (Refer to 27-30) Remove inclinometer.
(4) Inspection/Check - Elevator System Rigging (See Figure 27-302) Note: (a) If the following elevator leading edge gap and overlap inspections do not fall within the specified clearances, contact Cirrus Design Customer Service Department for disposition. Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) Page 6 P/N or Spec.
Minimum Maximum Leading Edge Gap 0.060" 1.5" 0.150" 3.8 mm Overlap 0.010" 0.25 mm 0.125" 3.
B. Forward Elevator Push/Pull Rod (See Figure 27-303) (1) (2) Removal - Forward Elevator Push/Pull Rod (a) Remove seat. (Refer to 25-10) (b) Remove kick plate. (Refer to 25-10) (c) Remove mid-console trim panel. (Refer to 25-10) (d) Remove cotter pin, castellated nut, washers, and bolt securing elevator push/pull rod end to control-yoke elevator stop.
Figure 27-303 Elevator System 13773-001 30 Nov 2000 27-30 Page 9
D. Elevator System Pulleys (See Figure 27-105), (See Figure 27-204),(See Figure 27-205), (See Figure 27-303) WARNING: (1) (2) (3) A system rigging Inspection/Check must be performed after loosening any flight control cable to assure proper control surface operation. Refer to the appropriate control system’s rigging procedures for the Inspection/Check maintenance practices. Removal - Elevator Pulley Sector (a) Remove co-pilot seat. (Refer to 25-10) (b) Remove right mid console trim.
Figure 27-304 Pitch Trim System 13773-001 30 Nov 2000 27-30 Page 11
(3) Adjustment/Test - Pitch Trim Cartridge (a) Acquire necessary tools, equipment, and supplies. Description Inclinometer P/N or Spec. PRO360 Supplier Maclanburg Duncan Purpose Deflection Angle Determination (b) (c) (4) Remove access panels RE1 and RE2. (Refer to 6-00) Set elevators to neutral position using BL 12 and BL 60 templates. 1 Align elevator trailing edges to horizontal stabilizer chord line.
(5) (6) F. (j) Verify minimum rod end thread engagement of 0.312 inch (0.79 cm). (k) Verify proper installation of safety wires and cotter pins on all fasteners. Removal - Pitch Trim Motor (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in OFF position. (b) Pull PITCH TRIM circuit breaker. (c) Remove access panel RE2. (Refer to 6-00) (d) Remove composite rudder bottom. (Refer to 55-40) (e) Remove nut, washer, and screw securing pulley gang support brace to empennage.
STALL WARNING SYSTEM 1. DESCRIPTION The airplane utilizes an electro-pneumatic stall warning system to indicate an approach to aerodynamic stall. As the angle of attack increases and the airplane approaches an aerodynamic stall, the stagnation point moves lower on the leading edge causing low pressure on the upper leading edge to increase.
(c) (d) (4) Lightly moisten suction cup and firmly press cup over stall warning port. Activate stall warning pressure switch by sharply pulling the suction cup directly away from the warning port. Note momentary audible warning signal. Inspection/Check - Stall Warning Operational Check - Flight WARNING: (a) (b) (c) (d) (e) (f) (g) The following Adjustment/Test must be performed by a Cirrus Design authorized pilot.
Figure 27-311 Stall Warning System Installation 13773-001 30 Nov 2000 27-31 Page 3
FLAPS 1. GENERAL This section describes that portion of the flight control system which controls the position and movement of the flaps. Included are the torque tube assembly, flap actuator assembly, flap indicator and switch. Flap control is achieved via a flap activation switch mounted on the center console. Indicator lights identify flap position. A linear actuator, located under the baggage floor, drives a torque tube interconnect between the left and right flaps.
(e) (2) Remove nuts, washers, spacers, and bolts, securing torque tube coupler and torque tubes. (f) Withdraw torque tube from outboard tube bushing. (g) Withdraw torque tube coupler from inboard tube bushing. Installation -Torque Tube Assembly (a) Insert torque tube coupler into inboard tube bushing. (b) Insert LH torque tube through outboard bushing into torque tube coupler. (c) Insert RH torque tube through outboard bushing into torque tube coupler.
D. Flap Circuit Card Assembly (CCA) (See Figure 27-501) (1) (2) Removal - Flap Circuit Card Assembly (a) Pull FLAPS circuit breaker. (b) Remove passenger compartment seats. (Refer to 25-10) (c) Remove carpet and access panels CF4C. (Refer to 6-00) (d) Disconnect flap CCA connector. (e) Remove nuts, washers, spacers, and screws securing flap CCA to longeron. Installation - Flap Circuit Card Assembly (a) Position flap CCA to longeron and install screws, washers, spacers, and nuts.
Figure 27-501 Flap System Installation (Sheet 1 of 3) Page 4 27-50 13773-001 30 Nov 2000
Figure 27-501 Flap System Installation (Sheet 2 of 3) 13773-001 30 Nov 2000 27-50 Page 5
Figure 27-501 Flap System Installation (Sheet 3 of 3) Page 6 27-50 13773-001 30 Nov 2000
F. Flap Adjustments and Inspections (1) Adjustment/Test - Flap Travel (a) Acquire necessary tools, equipment, and supplies. Description (e) (f) (g) (h) (i) Supplier Purpose WS 40 Wing Template 13057-101/-102 Cirrus Design Corp. Flap Rigging WS 132 Wing Template 13057-107/-180 Cirrus Design Corp. Flap Rigging Inclinometer PRO360 Deflection Angle Determination Note: (b) (c) (d) P/N or Spec. Maclanburg Duncan Flap may exhibit a slight twist from root to tip.
(l) Ensure flap exhibits a 32° angle change. If flaps are not set at 100% deployed position adjust the flap actuator proximity sensor as follows: 1 Turn switch to 50%. Note: For best results in determining proximity sensor location, do not move sensor more than 0.10 inch (2.5 mm) per positioning attempt. 2 (m) (n) Reposition full down proximity sensor by loosening screw and repositioning on flap actuation extension tube. 3 Turn flap switch to 100%.
2 (g) 13773-001 30 Nov 2000 Airplane S/N 1035 and subsequent; verify the flap actuator and the rod end at the flap actuator end fitting are installed to a depth between the end fitting inspection holes. Verify proper installation of safety wires and cotter pins on all fasteners and engagement of all jam nuts through complete flap control system.
Max. at Root of Flap Min. at Root of Flap Max. at Tip of Flap Min. at Tip of Flap Leading Edge Gap 1.265" 3.21 cm 0.665" 1.7 cm 1.143" 2.90 cm 0.543" 1.4 cm Overlap Gap 1.775" 4.5 cm 1.175" 3.0 cm 1.113" 2.82 cm 0.513" 1.
CHAPTER FUEL
CHAPTER 28 - FUEL LIST OF EFFECTIVE PAGES Chapter/Section Page Date 28-LOEP 1 31 JULY 2001 28-TOC 1 31 JULY 2001 28-TOC 2 31 JULY 2001 28-00 1 30 NOV 2000 28-00 2 30 NOV 2000 28-00 3 30 NOV 2000 28-00 4 30 NOV 2000 28-10 1 30 NOV 2000 28-10 2 30 NOV 2000 28-10 3 30 NOV 2000 28-10 4 30 NOV 2000 28-10 5 30 NOV 2000 28-10 6 30 NOV 2000 28-10 7 30 NOV 2000 28-10 8 30 NOV 2000 28-10 9 30 NOV 2000 28-10 10 30 NOV 2000 28-10 11 30 NOV 2000 28-20 1 30 NOV 2
CHAPTER 28 - FUEL TABLE OF CONTENTS Subject FUEL Chapter/Section Page 28-00 General 1 Troubleshooting 1 STORAGE 28-10 Description 1 Maintenance Practices 2 Wing Fuel Tank Adjustment/Test - Wing Fuel Tank Pressure Test Inspection/Check - Wing Fuel Tank Cleaning - Wing Fuel Tank Repairing - Wing Fuel Tank Collector Tanks Adjustment/Test - Collector Tank Inspection/Check - Collector Tank Fuel Strainers Removal - Fuel Strainers Installation - Fuel Strainers Inspection/Check - Fuel Strainers Fuel S
CHAPTER 28 - FUEL TABLE OF CONTENTS Subject Chapter/Section Removal - Gascolator Fuel Filter Screen Installation - Gascolator Fuel Filter Screen Cleaning - Gascolator Fuel Filter Screen Electric Fuel (Boost) Pump Removal - Electric Fuel (Boost) Pump Installation - Electric Fuel (Boost) Pump Selector Valve Removal - Selector Valve Installation - Selector Valve Cabin Fuel System Fuel Enclosure (Firewall) Removal - Cabin Fuel System Fuel Enclosure Installation - Cabin Fuel System Fuel Enclosure INDICATING P
FUEL 1. GENERAL This chapter contains information on storage, distribution, and indicating components of the fuel system. The engine is supplied with fuel drawn out of the left or right integral fuel tank (depending on the fuel selector valve position).
Trouble Fuel starvation after start up Probable Cause Partial fuel flow from preceding causes Malfunction of engine-driven fuel pump or fuel system Fuel vents plugged Water in fuel Remedy See remedies from above Replace pump Remove obstruction Remove water No fuel output indicated from fuel Mixture control set in lean position flow gage when auxiliary pump is and throttle lever is pulled back Fuel line disconnected before fuel operated flow sensor Defective fuel pump switch NOTE: If the auxiliary pump is
Figure 28-001 Fuel System Schematic 13773-001 30 Nov 2000 28-00 Page 3
Figure 28-002 Fuel System Page 4 28-00 13773-001 30 Nov 2000
STORAGE 1. DESCRIPTION The fuel storage system consists primarily of a vented integral 42-gallon (159-liters) capacity fuel tank in each wing, a integral fuel collector tank/sump in each wing, a three-position selector valve, an electric boost pump, gascolator, an engine-driven fuel pump, and five fuel drains. Each wing contains an integral fuel tank bounded by the upper and lower wing skins, main spar web, aft wing shear web, and the inboard and outboard fuel tank ribs.
2. MAINTENANCE PRACTICES A. Wing Fuel Tank (1) Adjustment/Test - Wing Fuel Tank Pressure Test (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) Page 2 P/N or Spec.
(n) (o) If leakage is suspected (manometer level or pressure readings drop), apply soapy water to the area in question and inspect for bubbles. WARNING: If the fuel system leaks, release all pressure from the system before removing the fuel filler caps. Never attempt to remove the fuel filler cap with pressure in the fuel system. Never remove the fuel filler cap when a soapy water solution is present or contamination of the fuel system could occur.
Figure 28-101 Fuel Cap Assembly Page 4 28-10 13773-001 30 Nov 2000
(2) Inspection/Check - Wing Fuel Tank Note: No detectable fuel leaks are allowed after the repair procedure has been performed. (Refer to 28-10) (a) (3) Drain a pint of fuel from the fuel tank through the drain valve into a clean, clear container. Check this fuel sample for any evidence of contaminates. Repeat this same procedure, draining at least a quart of fuel from the collector tank through drain valve. (b) If no contaminates are found then no further action is required.
(a) Acquire necessary tools, equipment, and supplies.
Note: If the fuel leak is located at a bondline, joint or seam, mix sealant (MIL-8802 Type 2 Class A and/or Class B) per manufacture’s instructions. (Refer to 2010) If the leak is coming from a small pinhole located away from any bondlines, joints or seams, mix non-structural resin (Type 2, Class 1) per the manufacture’s instructions. (l) (m) (n) (o) (p) (q) (r) Fillet, fay or injection seal as required. Brush sealant or resin over repair area making sure brushed area is larger than the repaired area.
Figure 28-102 Wing Fuel System Components Page 8 28-10 13773-001 30 Nov 2000
C. Fuel Strainers (1) (2) (3) Removal - Fuel Strainers (a) Drain the corresponding fuel tank for the side being serviced. (Refer to 12-10) (b) Remove the appropriate fuel tank access panel (LW10 or RW10) from the wing to gain access to the fuel pickup strainers. (Refer to 6-00) (c) Remove the strainers. (d) Remove all sealant from the access panel cover and wing. Installation - Fuel Strainers (a) Install and secure the strainers. (b) Fay surface seal and install the fuel tank access panel to the wing.
(a) F. A running leak will vary in size depending on location and intensity of the leak. Fuel usually will flow and immediately drip after being wiped dry. Fuel Drain Valves (See Figure 28-103) (1) (2) Removal - Fuel Drain Valves (a) Drain the corresponding fuel tank. (Refer to 12-10) (b) Cut safety wire and remove drain valve (fuel tank drain valves only). Installation - Fuel Drain Valves WARNING: The collector tank drain valves are certified to tolerate swept stroke lightning.
Figure 28-103 Fuel Tank Drain Valve 13773-001 30 Nov 2000 28-10 Page 11
DISTRIBUTION 1. DESCRIPTION This section contains information on the distribution system. The fuel distribution system consists of electric and mechanical (engine-driven) fuel pumps, fuel gascolator, fuel hose, fuel lines, fuel selector valve, and the fuel pump switch. A gascolator is installed on the forward side of the firewall after the electric fuel pump and before the engine driven fuel pump.
2. MAINTENANCE PRACTICES A. Gascolator (See Figure 28-201) (1) (2) (3) Removal - Gascolator (a) Disconnect battery and insulate both cable ends to prevent accidental reconnection. (Refer to 24-30) (b) Place the fuel selector valve in the off position. (c) Using fuel sampler, drain fuel from gascolator and valve line. (d) Disconnect fuel inlet and outlet lines. (e) Disconnect gascolator drain line. (f) Remove bolts securing gascolator to mounting bracket. Remove gascolator.
Figure 28-201 Gascolator Assembly 13773-001 30 Nov 2000 28-20 Page 3
B. Electric Fuel (Boost) Pump (See Figure 28-202) (1) (2) Removal - Electric Fuel (Boost) Pump (a) Disconnect battery and insulate both cable ends to prevent accidental reconnection. (Refer to 24-30) (b) Place the fuel selector valve in the off position. (c) Disconnect inlet tube from gascolator. (d) Disconnect tube from gascolator to electric auxiliary fuel pump. Drain fuel from tube. (e) Disconnect fuel drain hose. (f) Disconnect the pump wires.
Figure 28-202 Electric Fuel Pump Installation 13773-001 30 Nov 2000 28-20 Page 5
C. Selector Valve (See Figure 28-203) (1) Removal - Selector Valve WARNING: Disconnect the battery prior to servicing the selector valve. (a) (2) Disconnect battery and insulate both cable ends to prevent accidental reconnection. (Refer to 24-30) (b) Remove crew seats and inboard seat track mounting hardware. (Refer to 25-10), (Refer to 53-40) (c) Remove mid console trim from each side. (Refer to 25-10) (d) Remove console support side brackets.
(f) (g) (h) (i) (j) (k) (l) Place one new seal on each side of banjo fitting and slide banjo fitting bolt through banjo fitting. Finger-tighten banjo fitting bolt. Support banjo fittings and secure all fuel supply and return lines (with grommets) to the corresponding fitting. CAUTION: Always support banjo fittings during the torquing procedure to prevent damaging the fuel supply lines, return lines, and selector valve assembly. Always use new seals to help prevent fuel leaks.
Figure 28-203 Fuel Selector Valve Installation Page 8 28-20 13773-001 30 Nov 2000
D. Cabin Fuel System Fuel Enclosure (Firewall) (1) Removal - Cabin Fuel System Fuel Enclosure WARNING: Disconnect the battery prior to servicing the selector valve. Note: Steps B through G do not need to be performed if you are just going to inspect the fuel lines under the firewall fuel enclosure. (a) (2) Disconnect battery and insulate both cable ends to prevent accidental reconnection. (Refer to 24-30) (b) Remove carpet, crew seats, and mounting hardware.
(h) CAUTION: Always support fittings during the torquing procedure to prevent damaging the fuel supply line, return line, or selector valve assembly. Note: The fuel line grommets must lay flat against the interior and exterior surfaces of the panel. Fuel line grommets must seal all fuel and vapors inside fuel selector valve housing. Support fittings and secure the forward fuel supply and return line (with grommets) to the corresponding fitting.
INDICATING 1. DESCRIPTION Fuel flow is monitored with a turbine flow transducer located between the throttle body and injection manifold. A fuel flow gage is installed in the instrument panel adjacent to the other engine instruments. The fuel quantity in each integral fuel tank and each integral collector tank is displayed by a single fuel quantity indicator (fuel gage). One float type fuel quantity sensor is installed in each integral fuel tank and each integral collector tank.
(4) (i) Turn BAT switch to the ON position. (j) Adjust both the left and right full adjustment screws until the needles indicate full. (k) Turn BAT switch to the OFF position. (l) Install the fuel indicator adjustment screw covers. (m) Install right mid-console trim. (Refer to 25-10) Test - Fuel Quantity Indicator and Fuel Sender Test (a) Verify the ignition switch is in the OFF position and remove the key. (b) Place the BAT Master Switch in the OFF position.
Figure 28-401 Fuel Quantity Indicator 13773-001 30 Nov 2000 28-40 Page 3
B. Fuel Quantity Sensors (1) (2) (3) (4) (5) Page 4 Removal - Wing Tank Fuel Quantity Sensors (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in the off position. (b) Pull ENGINE INSTRUMENTS circuit breaker. (c) Disconnect battery and insulate both cable ends to prevent accidental connection. (Refer to 24-30) (d) De-fuel airplane. (Refer to 12-10) (e) Remove appropriate access panels (LW10 or RW10). (Refer to 6-00) (f) Identify and disconnect wires to sensor.
(b) (c) (d) (e) (f) (g) Pull ENGINE INSTRUMENTS circuit breaker. Disconnect battery and insulate both cable ends to prevent accidental connection. (Refer to 24-30) De-fuel airplane. (Refer to 12-10) Remove appropriate access panel(s) (LW3 and LW4, RW3 and RW4, or LW10 and RW10. (Refer to 6-00) Identify and disconnect the center wire to the corresponding sensor. Place multimeter in the 50-ohm scale and zero out the ohmmeter.
Figure 28-402 Fuel Quantity Sensor Page 6 28-40 13773-001 30 Nov 2000
CHAPTER INDICATING AND RECORDING
CHAPTER 31 - INDICATING AND RECORDING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 31-LOEP 1 30 NOV 2000 31-TOC 1 30 NOV 2000 31-00 1 30 NOV 2000 31-30 1 30 NOV 2000 31-30 2 30 NOV 2000 31-50 1 30 NOV 2000 31-50 2 30 NOV 2000 31-50 3 30 NOV 2000 13773-001 30 Nov 2000 31-LOEP Page 1
CHAPTER 31 - INDICATING AND RECORDING TABLE OF CONTENTS Subject INDICATING/RECORDING SYSTEMS Chapter/Section Page 31-00 General RECORDERS 1 31-30 Description 1 Hour Meter Removal - Hour Meter Installation - Hour Meter INDICATING/RECORDING SYSTEMS 1 1 1 31-50 Description 1 Annunciator Panel Removal - Annunciator Panel Installation - Annunciator Panel 13773-001 30 Nov 2000 1 1 1 31-TOC Page 1
INDICATING/RECORDING SYSTEMS 1. GENERAL This chapter describes those units which give visual or aural warning of conditions in unrelated systems. This includes the Hour Meter and Central Caution/Warning Annuciator Panel.
RECORDERS 1. DESCRIPTION This section describes those components used for recording data not related to specific systems. This includes the hour meter. Located inside the glove box, the hour meter is powered by 28 VDC supplied through the 5-amp ENGINE INSTRUMENTS circuit breaker on the Main Bus. Recording begins when the BAT 1 switch is ON and either ALT 1 or ALT 2 switch is ON. A. Hour Meter (See Figure 31-301) (1) (2) Removal - Hour Meter (a) Pull ENGINE INSTRUMENTS circuit breaker.
Figure 31-301 Hour Meter Installation Page 2 31-30 13773-001 30 Nov 2000
INDICATING/RECORDING SYSTEMS 1. DESCRIPTION This section describes the Central Caution/Warning System which consists of an annunciator assembly and related sensors and switches. The annunciator assembly is mounted center, high on the flight instrument panel and contains six annunciators. Each annunciator has two individual LEDs as light sources. The annunciator panel has bright, dim, and test modes, which are activated by a toggle switch mounted to the left of the annunciator panel.
(b) (c) (d) (e) Page 2 Install washer on toggle switch and position on instrument panel so keyway on switch faces down. Install washer and dress nut. Connect electrical connector to annunciator. Install glareshield. (Refer to 25-10) Reset ANNUNCIATOR PANEL circuit breaker.
Figure 31-501 Annunciator Panel Installation 13773-001 30 Nov 2000 31-50 Page 3
CHAPTER LANDING GEAR
CHAPTER 32 - LANDING GEAR LIST OF EFFECTIVE PAGES Chapter/Section Page Date 32-LOEP 1 31 JULY 2001 32-LOEP 2 31 JULY 2001 32-TOC 1 31 JULY 2001 32-TOC 2 31 JULY 2001 32-00 1 30 NOV 2000 32-00 2 30 NOV 2000 32-10 1 31 JULY 2001 32-10 2 31 JULY 2001 32-10 3 30 NOV 2000 32-10 4 30 NOV 2000 32-10 5 30 NOV 2000 32-10 6 30 NOV 2000 32-10 7 30 NOV 2000 32-10 8 31 JULY 2001 32-20 1 31 JULY 2001 32-20 2 31 JULY 2001 32-20 3 31 JULY 2001 32-20 4 30 NOV 2000 32-
CHAPTER 32 - LANDING GEAR LIST OF EFFECTIVE PAGES Chapter/Section Page Date 32-42 8 30 NOV 2000 32-42 9 30 NOV 2000 32-42 10 30 NOV 2000 Page 2 32-LOEP 13773-001 31 July 2001
CHAPTER 32 - LANDING GEAR TABLE OF CONTENTS Subject LANDING GEAR Chapter/Section Page 32-00 General MAIN LANDING GEAR 1 32-10 Description 1 Troubleshooting 1 Maintenance Practices 1 Main Gear Fairing Removal - Main Gear Fairing Installation - Main Gear Fairing Main Gear Assembly Removal - Main Gear Assembly Installation - Main Gear Assembly Inspection/Check - Main Landing Gear and Fairings Adjustment/Test - Wheel Toe-In Check NOSE GEAR 1 1 2 4 4 4 4 6 32-20 Description 1 Troubleshooting 1
CHAPTER 32 - LANDING GEAR TABLE OF CONTENTS Subject Chapter/Section Servicing Tires and Tubes Main Wheel, Tire, and Tube Removal - Main Wheel, Tire, and Tube Disassembly - Main Wheel, Tire, and Tube Reassembly - Main Wheel, Tire, and Tube Installation - Main Wheel, Tire, and Tube Inspection/Check - Main Wheel Inspection Nose Wheel, Tire, and Tube Removal - Nose Wheel, Tire, and Tube Disassembly - Nose Wheel, Tire, and Tube Reassembly - Nose Wheel, Tire, and Tube Installation - Nose Wheel, Tire, and Tube I
LANDING GEAR 1. GENERAL This chapter describes those units and components which furnish a means of supporting and steering the airplane. The landing gear design is of the fixed tricycle type, employing composite leaf-spring main gear strut assemblies and a tubular nose-gear leg with a castering nose wheel. Aluminum nose and main landing gear wheels are installed and are designed to be used with tubes and tires.
Figure 32-001 Landing Gear Page 2 32-00 13773-001 30 Nov 2000
MAIN LANDING GEAR 1. DESCRIPTION A rugged, maintenance free fiberglass strut assembly is utilized for the main landing gear. The strut attaches to the airplane via a canted wing rib and an upper attach fitting that bolts to the WS 37 rib. The wheel, brake, axle, tire and tube, wheel bearing, and attaching hardware is mounted on each main gear. (See Figure 32-101) 2. TROUBLESHOOTING TROUBLE Airplane leans to one side. Tires wear excessively. Obvious vibration on smooth surface.
(2) Installation - Main Gear Fairing Note: (a) (b) To ensure clearance between wheel assembly and fairing assembly, finger tighten all attaching parts and adjust fairing assembly before final tightening. Pry trailing edge seam of upper strut fairing open, position around strut, and install screws attaching upper strut fairing to wing. Pry trailing edge seam of strut fairing open, slide fairing into position under upper strut fairing, and install screws securing fairing to strut.
SR2_MM32_1382 Reserved Figure 32-101 Main Gear Fairing Installation 13773-001 30 Nov 2000 32-10 Page 3
B. Main Gear Assembly (See Figure 32-102) (1) Removal - Main Gear Assembly (a) Acquire necessary tools, equipment, and supplies. Description Plastic Wedge P/N or Spec. - Supplier Any Source Purpose Removal of strut. (b) (c) (d) (e) (f) (g) (2) (3) Page 4 Remove main gear fairings. (Refer to 32-10) Raise airplane on jacks. (Refer to 7-00) Drain hydraulic fluid from brake system. Disconnect and cap flexible brake line at upper end of strut at rib fitting.
Figure 32-102 Main Landing Gear Installation 13773-001 30 Nov 2000 32-10 Page 5
(4) Adjustment/Test - Wheel Toe-In Check (See Figure 32-103) Correct wheel alignment plays a critical role in maintaining tire wear and should be checked whenever abnormal or excessive wear is noted. To correct wheel alignment the airplane is placed on greased-slide plates which allow the main wheels to easily assume their true alignment position. Shims are inserted or removed to adjust camber and toe-in. Measurements are taken on wheel flange. (a) Acquire necessary tools, equipment, and supplies.
Figure 32-103 Wheel Alignment (Sheet 1 of 2) 13773-001 30 Nov 2000 32-10 Page 7
Figure 32-103 Wheel Alignment (Sheet 2 of 2) Page 8 32-10 13773-001 31 July 2001
NOSE GEAR 1. DESCRIPTION The nose gear consists of a tubular steel strut attached to the engine mount. The free castering nosewheel’s maximum turning arc is 216 degrees (108 degrees either side of center). Shock absorption is provided by a series of stacked, polymer pucks which react against the engine mount. Steering is accomplished by differential application of the main gear brakes. The wheel, axle, tire and tube, wheel bearing, and seal are mounted on the nose gear. (See Figure 32-202) 2.
(2) (h) Reinstall towing lug. Installation - Nose Gear Fairing (a) Acquire necessary tools, equipment, and supplies. Description Safety Wire (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) Page 2 P/N or Spec. - Supplier Any Source Purpose Secure hinge pin Remove towing lug from nose wheel assembly. Turn nose wheel to full 108 degree deflection. Pry trailing edge seam of strut fairing open and position strut fairing around strut.
Figure 32-201 Nose Gear Fairing Installation 13773-001 31 July 2001 32-20 Page 3
B. Nose Gear Assembly (See Figure 32-202) (1) (2) Removal - Nose Gear Assembly (a) Remove nose gear fairing. (Refer to 32-20) (b) Remove engine cowling. (Refer to 71-10) (c) Raise airplane on jacks (Refer to 7-10) (d) With nose gear assembly supported, remove cotter pin, nut, washers, spacers, and bolt at top of puck stack securing strut assembly to engine mount. (e) Remove cotter pins, washers, spacers, nuts, and bolts securing aft strut assembly to engine mount.
(b) Apply thin coat of grease to spindle threads. CAUTION: Improper orientation of Belleville washers may result in undesirable handling characteristics of the airplane and/or damage to the airplane. (c) (d) (e) (3) Insert washers and Belleville washers in proper orientation. (See Figure 32-202) Install spindle nut. Attach spring scale to axle fork and torque spindle nut so that side load required to rotate wheel assembly, after initial break-free pull, is 10 to 20 lbs (4.5 kg to 9.1 kg).
Figure 32-202 Nose Gear Assembly and Installation Page 6 32-20 13773-001 30 Nov 2000
WHEELS AND BRAKES 1. GENERAL This chapter describes that portion of the landing gear system which provides for rolling and stopping of the airplane while on the ground. Chapter 32-41 contains maintenance practices pertinent to the wheels, tires, and tubes. (Refer to 32-41) Chapter 32-42 contains maintenance practices pertinent to the brake system.
2. TROUBLESHOOTING Trouble Airplane Leans To One Side. Probable Cause Remedy Bent axle. Replace with new parts. Incorrect tire pressure. Inflate to proper pressure. (Refer to 12-10) Attaching parts loose or defective. Replace with new parts. Brake Drag. Piston cocked in cylinder, resulting Remove and repair cylinder or pisin overheating brake and/or ton, or replace brake (Refer to 32excessive lining wear. 42) Foreign matter wedged in brakes. Locate and remove.
Trouble Brakes Inoperative. Parking brake inoperative. Probable Cause Remedy Brake fluid level low. Replenish brake fluid. (Refer to 12-10) Air in brake system. Bleed brake system. (Refer to 3242) Defective master cylinder. Replace master cylinder (Refer to 32-42) Defective caliper. Replace caliper (Refer to 32-42) Worn brake linings. Replace linings (Refer to 32-42) Leaky brake line connections Tighten or replace connectors. Parking brake valve defective.
Trouble Brakes Won't Hold. Probable Cause Contaminated lining. Remedy Replace lining. Improper conditioning of brake lin- Replace linings. ings. Lining worn below minimum wear Replace linings. limits. Discs worn below minimum wear limits. Replace discs. Organic brake lining carbonized (overheated). Replace lining. Pressure plate contacting torque plate assembly. Check for correct torque plate/ wheel installation. New Lining installed with old disc, Replace excessively worn disc.
WHEELS 1. DESCRIPTION The main wheels are of aluminum construction and designed to be used with tires and tubes. Each main wheel consists of two wheel halves, two bearing cups, two bearing cones, grease seals, a brake disc assembly, and a snap ring. The wheel halves are joined with bolts, washers, and nuts. A hole in one wheel half provides for valve stem installation. The 15 x 6.00 x 6 wheels use 6-ply-rated tube tires and rotate on two bearings protected against contamination by grease seals.
Note: (3) The bearing cup is press fit into the wheel half and should not be removed unless replacement is necessary. To remove bearing cup, insert wheel into boiling water or place in an oven not exceeding 212° Fahrenheit for 15 minutes. Remove wheel half from heat source and immediately remove bearing cup with a fiber drift pin or suitable arbor press. Press in new bearing cup while wheel half is still hot. Reassembly - Main Wheel, Tire, and Tube (a) Acquire necessary tools, equipment, and supplies.
(c) (d) (e) (f) (g) 13773-001 30 Nov 2000 Inspect bearing cups for looseness, scratches, pitting, corrosion, or evidence of overheating. Replace cup if any defect exists. Inspect snap rings and grease seals for distortion or wear. Replace grease seal felts if contaminated or hard. Carefully inspect through bolts. Check for cracks by magnetic particle inspection, especially in radius under head and in threads adjacent to bolt shank. Replace any doubtful bolt. Inspect self locking nuts for damage.
Figure 32-411 Main Wheel Installation Page 4 32-41 13773-001 30 Nov 2000
Figure 32-412 Main Wheel Assembly 13773-001 30 Nov 2000 32-41 Page 5
C. Nose Wheel, Tire, and Tube (See Figure 32-413), (See Figure 32-414) (1) Removal - Nose Wheel, Tire, and Tube (a) Remove nose gear fairings. (Refer to 32-20) (b) Raise airplane on jacks. (Refer to 7-00) (c) Deflate tire completely. WARNING: (d) (e) (f) Remove valve core. While supporting wheel/tire assembly, remove axle plugs, cotter pin, axle nut, washers, and withdraw bolt from axle. Pull tire, axle, and wheel from fork.
(c) (d) (e) (f) Position tire and tube on wheel half ensuring valve stem protrudes from hole in wheel half. Place wheel half in proper alignment position with opposite wheel half and apply light force to mate the wheel halves together. Do not pinch tube between wheel halves. Install nuts, washers, and bolts. Torque nuts to 90 inch-pounds (10.2 N.m.). CAUTION: (4) (5) 13773-001 30 Nov 2000 Uneven torque of nuts can cause bolt failure with resultant wheel failure. (g) Inflate tire and adjust pressure.
Figure 32-413 Nose Wheel Installation Page 8 32-41 13773-001 30 Nov 2000
Figure 32-414 Nose Wheel Assembly 13773-001 30 Nov 2000 32-41 Page 9
BRAKES 1. DESCRIPTION The hydraulically operated brakes are individually activated by floor mounted toe pedals located at both pilot stations. The brake system is designed to use MIL-H-5606 hydraulic fluid. The brake system consists of a dual disc brake assembly on each main landing gear wheel, master cylinder for each rudder pedal, hydraulic fluid reservoir, parking brake valve, and associated hydraulic plumbing.
Description (b) (c) (d) (e) (f) (j) (k) Parker Aerospace Sealing device. O-Ring Lubricant Dow Corning 55 O-Ring Lubricant Dow Corning Lubrication. Silicon Spray - Any Source Lubrication. If anchor bolts were removed, install anchor bolts using arbor press and a holding fixture. Install washers and nuts. Torque nuts to 90 inch-pounds (7.9 N.m.). Install O-rings on pistons and lubricate.
Note: (f) (g) (h) (i) (j) Dry film lubricants such as silicone spray should be applied to anchor bolts and torque plate bushing to assist sliding motion. Exercise care to insure that linings do not become contaminated with fluid or lubricant. For best service life, cylinders must slide freely in torque plate. Install back plate and back plate attachment bolts and washer. Torque to 75-80 inchpounds (8.5-9.1 N.m.). Uncap and attach hydraulic line to cylinder inlet fitting. Bleed the system.
Note: Pressure plates should not be used if warped in excess of 0.010 inch (0.254 mm) flatness. Excessive warping can result in brake drag especially when new disc and linings are installed. (k) (2) Align new lining segments on pressure plate/back plate and install rivets. Insure lining is tight and movement free with no distortion of parts. Installation - Brake Linings (a) Acquire necessary tools, equipment, and supplies. Description Silicon Spray (b) (c) F.
Figure 32-421 Brake Assembly 13773-001 30 Nov 2000 32-42 Page 5
G. Brake Master Cylinder (See Figure 32-422), (See Figure 32-423) (1) (2) (3) Removal - Brake Master Cylinder (a) Drain hydraulic fluid from brake system. (b) Remove cotter pins and washers from rudder pedal pivot tubes. (c) Slide rudder pedal pivot tube from bearing. (d) Detach rudder pedals from torque tube weldment. (e) Disconnect hoses from master cylinders. Cap or plug ports and hoses. (f) Remove cotter pins, washers, and clevis pins from upper connection at rudder pedals of each master cylinder.
Figure 32-422 Master Cylinder Assembly 13773-001 30 Nov 2000 32-42 Page 7
H. Inspection/Check - Master Cylinder Components (See Figure 32-422) (a) (b) (c) I. Inspect retaining rings for cracks or burns. Inspect bushing, piston, end gland, and piston rod for nicks, scratches, or damaged threads. Inspect cylinder body for damage to threaded ports and cracks in the floor attach point. Parking Brake Valve (See Figure 32-423) (1) (2) Removal - Parking Brake Valve (a) With parking brake knob in “off” position, drain hydraulic fluid from brake system (b) Remove left crew seat.
Figure 32-423 Brake System 13773-001 30 Nov 2000 32-42 Page 9
J. Adjustment/Test - Bleeding the Brake System If a brake line has been disconnected or the brake pedal has a “spongy” feel, there is a strong likelihood that air has entered the brake system. To ensure proper braking, all trapped air must be removed from the brake system. (a) Acquire necessary tools and equipment Description (b) (c) (d) (e) (f) (g) (h) Page 10 P/N or Spec. Supplier Purpose Pressure Pot - Any Source Bleed brake system.
CHAPTER LIGHTS
CHAPTER 33 - LIGHTS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 33-LOEP 1 30 NOV 2000 33-TOC 1 30 NOV 2000 33-TOC 2 30 NOV 2000 33-00 1 30 NOV 2000 33-10 1 30 NOV 2000 33-10 2 30 NOV 2000 33-10 3 30 NOV 2000 33-10 4 30 NOV 2000 33-10 5 30 NOV 2000 33-10 6 30 NOV 2000 33-10 7 30 NOV 2000 33-20 1 30 NOV 2000 33-20 2 30 NOV 2000 33-40 1 30 NOV 2000 33-40 2 30 NOV 2000 33-40 3 30 NOV 2000 33-40 4 30 NOV 2000 33-40 5 30 NOV 2000 33-40 6 30 NOV 2000
CHAPTER 33 - LIGHTS TABLE OF CONTENTS Subject LIGHTS Chapter/Section Page 33-00 General FLIGHT COMPARTMENT 1 33-10 Description 1 Troubleshooting 3 Maintenance Practices 4 Cabin Lights Removal - Glareshield Light Strip Installation - Glareshield Light Strip Removal - Cabin Eyeball Light and Switch Installation - Cabin Eyeball Light and Switch Removal - Cabin Dome Light Installation - Cabin Dome Light Removal - CAPS Handle Lighting Installation - CAPS Handle Lighting Removal - Circuit Breaker Pane
CHAPTER 33 - LIGHTS TABLE OF CONTENTS Subject Chapter/Section EXTERIOR LIGHTING Description Landing Light Removal - Landing Light Installation - Landing Light Adjustment - Landing Light Anti-collision Strobe Light Assembly Removal - Anti-collision Strobe Light assembly Installation - Anti-collision Strobe Light assembly Light Bulb Replacement Removal - Navigation Light bulb Installation - Navigation Light bulb Removal - Position Light bulb Installation - Position Light bulb Removal - Strobe Light Installa
33-00LIGHTS LIGHTS 1. GENERAL This chapter contains information for troubleshooting, removal, installation and adjustments of the interior and exterior lighting systems used on the airplane. Exterior lighting consists of standard wing tip navigation lights with integral anti-collision strobe lights and position lights. A single landing light is mounted in the lower engine cowling.
33-10FLIGHT COMPARTMENT FLIGHT COMPARTMENT 1. DESCRIPTION The interior lights include the following: instrument, pilot control, environmental control, glareshield, circuit breaker, alternate air induction handle, CAPS handle, and individual reading lights above each seat. The instrument panel flood lighting is controlled by the dimmer control on the bolster panel. The flight instruments and avionics equipment are integrally lighted and are controlled by a single dimming circuit.
Figure 33-101 Cabin Light Location Page 2 33-10 13773-001 30 Nov 2000
2. TROUBLESHOOTING Trouble Reading Lights inoperative Probable Cause Remedy Defective bulb Replace bulb. Loose connection Tighten electrical connection. Circuit breaker or switch tripped Inspect for short circuit. Reset circuit breaker. Circuit breaker switch defective Check for continuity through switch. Replace if defective. Defective power supply Replace power supply. BAT Master Switch in “off” position Place switch in “on” position.
3. MAINTENANCE PRACTICES A. Cabin Lights (1) (2) (3) (4) (5) (6) Page 4 Removal - Glareshield Light Strip (a) Open (pull) the CABIN LIGHTS circuit breaker. (b) Remove glareshield. (Refer to 25-10) (c) Locate and mark the outer edges of the light strip. (d) Remove the retaining clips. (e) Gently pull the light strip from the glareshield. Installation - Glareshield Light Strip (a) Place the lighting strip into position and secure with clips. (b) Install glareshield.
(7) Removal - CAPS Handle Lighting WARNING: CAPS must be serviced and maintained by Cirrus Design trained and authorized parachute system technicians only. Airframe and powerplant license is not sufficient credentials for performing maintenance on CAPS. Ground activation of the CAPS will render the system and the airplane unusable until the CAPS and fuselage have been rebuilt by a certified technician. (a) Open (pull) the CABIN LIGHTS circuit breaker. (b) Remove CAPS Activation T-Handle Cover.
(13) Removal - Dimmer Switch (a) Remove the pilot’s kick panel. (Refer to 25-10) (b) Remove left bolster panel to gain access to dimmer switch. (Refer to 25-10) (c) Identify each wire to the switch and desolder wires. (d) Remove nut and star washer securing switch to bolster panel. (e) Remove switch from bolster panel. (14) Installation - Dimmer Switch (a) Place switch into bolster panel and secure with a star washer and nut. (b) Connect and solder each wire to the corresponding terminal of the switch.
Figure 33-102 Interior Lamp Replacement 13773-001 30 Nov 2000 33-10 Page 7
33-20PASSENGER COMPARTMENT PASSENGER COMPARTMENT 1. DESCRIPTION AND OPERATION This section covers the passenger compartment lighting. Each passenger light is controlled by an overhead switch. The eyeball lights consist of two lights and switches mounted in the headliner above the seats. Each light is round, and flush mounted with a swivel lens. Each light is individually switched with a push on/off toggle switch.
B. Lamp Replacement (1) (2) Page 2 Removal - Passenger Eyeball Light (a) Pull CABIN LIGHTS circuit breaker. (b) Remove cabin headliner.(Refer to 25-10)) (c) To remove the eyeball light bulb, rotate the socket and pull the bulb out. Installation - Passenger Eyeball Light (a) Push and rotate eyeball light bulb assembly into position. (b) Install cabin headliner. (Refer to 33-10) (c) Reset the CABIN LIGHTS circuit breaker. (d) Verify proper operation of light.
33-40EXTERIOR LIGHTING EXTERIOR LIGHTING 1. DESCRIPTION This section contains information on servicing the landing, position, and integral anti-collision strobe lights. The anti-collision light assembly and strobe light power supply are mounted to the outboard surface of each wing tip. The light assembly includes a strobe light with forward (red-left, green-right) and white position lights. A single 34-watt High Intensity Discharge (HID) landing light is installed in the lower left engine cowling.
(3) Adjustment - Landing Light Note: (a) The airplane must be on a level and flat surface prior to adjusting the beam of light from the landing light. There must be a vertical wall or door in front of the landing light lens. Check and adjust tire pressure and fuel level if necessary. (Refer to 12-10) Note: (b) (c) (d) (e) (f) Page 2 To aid in obtaining an accurate adjustment, each fuel tank must have the same amount of fuel in it.
Figure 33-401 Landing Light Assembly 13773-001 30 Nov 2000 33-40 Page 3
B. Anti-collision Strobe Light Assembly (1) (2) Removal - Anti-collision Strobe Light assembly (a) Place the Strobe light and NAV light switches in the “off” position. (b) Pull the Strobe Lights and NAV Lights circuit breaker to open the circuit. (c) Remove the screws securing the lens retainer to the base plate. (d) Disconnect the Anti-collision Strobe Light assembly wire harnesses. (e) Remove the Anti-collision Strobe Light assembly.
Figure 33-402 Anti-Collision Strobe Light Assembly 13773-001 30 Nov 2000 33-40 Page 5
C. Light Bulb Replacement (1) (2) Removal - Navigation Light bulb (a) Place the Strobe light and NAV light switches in the “off” position. (b) Pull the Strobe Lights and NAV Lights circuit breakers to open the circuit. (c) Remove the screws securing the lens retainer to the base plate. (d) To remove the Navigation Light bulb, push in and rotate the bulb counterclockwise.
(7) (8) 13773-001 30 Nov 2000 (b) Connect the strobe light wire harness. (c) Secure the lens retainer to the base plate with screws. (d) Reset the Strobe Lights and NAV Lights circuit breakers. (e) Ensure proper Anti-collision Strobe Light operation. Removal - Strobe Light Module (a) Place the Strobe light and NAV light switches in the “off” position. (b) Pull the Strobe Lights and NAV Lights circuit breakers to open the circuit. (c) Remove wing tip.
CHAPTER NAVIGATION AND PITOT STATIC
CHAPTER 34 - NAVIGATION LIST OF EFFECTIVE PAGES Chapter/Section Page Date 34-LOEP 1 31 JULY 2001 34-LOEP 2 31 JULY 2001 34-TOC 1 31 JULY 2001 34-TOC 2 31 JULY 2001 34-TOC 3 31 JULY 2001 34-00 1 30 NOV 2000 34-00 2 31 JULY 2001 34-10 1 31 JULY 2001 34-10 2 30 NOV 2000 34-10 3 30 NOV 2000 34-10 4 30 NOV 2000 34-10 5 30 NOV 2000 34-10 6 30 NOV 2000 34-10 7 30 NOV 2000 34-10 8 30 NOV 2000 34-10 9 30 NOV 2000 34-10 10 30 NOV 2000 34-10 11 30 NOV 2000 34-10
CHAPTER 34 - NAVIGATION LIST OF EFFECTIVE PAGES Chapter/Section Page Date 34-40 8 31 JULY 2001 34-40 9 31 JULY 2001 34-40 10 31 JULY 2001 34-50 1 31 JULY 2001 34-50 2 30 NOV 2000 34-50 3 30 NOV 2000 34-50 4 30 NOV 2000 Page 2 34-LOEP 13773-001 31 July 2001
CHAPTER 34 - NAVIGATION TABLE OF CONTENTS Subject Chapter/Section NAVIGATION AND PITOT-STATIC SYSTEMS Page 34-00 General 1 FLIGHT ENVIRONMENTAL DATA/PITOT-STATIC SYSTEMS 34-10 Description 1 Troubleshooting 2 Maintenance Practices 3 Pitot Tube Assembly Removal - Pitot Tube Assembly Installation - Pitot Assembly Inspection/Check - Purging the Pitot System Inspection/Check - Pitot System Leak Test Alternate Static Source Valve Removal - Alternate Static Source Valve Installation - Alternate Static
CHAPTER 34 - NAVIGATION TABLE OF CONTENTS Subject Chapter/Section Maintenance Practices 3 Magnetic Compass Removal - Magnetic Compass Assembly Installation - Magnetic Compass Adjustment/Test - Magnetic Compass Calibration Turn Coordinator Removal - Turn Coordinator Installation - Turn Coordinator Attitude Indicator Removal - Attitude Indicator Installation - Attitude Indicator HSI - NSD 1000 System Removal - NSD 1000 Display Installation - NSD 1000 Display Removal - Slave Amplifier Installation - Slave
CHAPTER 34 - NAVIGATION TABLE OF CONTENTS Subject Chapter/Section Page GPS 1 Antenna Removal - GPS 1 Antenna Installation - GPS 1 Antenna COM 1 Antenna Removal - COM 1 Antenna Installation - COM 1 Antenna GPS 2 Antenna Removal - GPS 2 Antenna Installation - GPS 2 Antenna COM 2 Antenna Removal - COM 2 Antenna Installation - COM 2 Antenna Stormscope Removal - Stormscope Processor and Tray Installation - Stormscope Processor and Tray Removal - Stormscope Antenna Installation - Stormscope Antenna Stormscope
NAVIGATION AND PITOT-STATIC SYSTEMS 1. GENERAL This chapter describes the navigation systems, units, and components which provide airplane navigational information. Included are pitot-static, gyros, compass, landing aids, global positioning system (GPS), and indicators. The subjects to be covered in this chapter are as follows: The Flight Environmental Data/Pitot Static Section describes systems which sense environmental conditions and use the data to influence navigation of the airplane.
Figure 34-001 Navigation System Layout Page 2 34-00 13773-001 31 July 2001
FLIGHT ENVIRONMENTAL DATA/PITOT-STATIC SYSTEMS 1. DESCRIPTION This section covers that portion of the system which senses environmental conditions and uses the data to influence navigation of the airplane. This includes pitot-static, outside air temperature gage/clock, vertical speed indicator, airspeed indicator, and altimeter. The pitot system utilizes an “L” shaped mast with integral pitot tube and heater located on the left wing just inboard of the wing tip to sense impact or ram air pressure.
2. TROUBLESHOOTING Trouble - Pitot Static Probable Cause Low or sluggish airspeed indica- Pitot tube deformed. tion. Normal altimeter and vertical Leak or obstruction in pitot line. speed indication. Remedy Repair or replace damaged component. Incorrect or sluggish response on Leaks or obstruction in static line. Repair or replace line. Remove all three pitot-static instruments. obstruction. Pitot tube does not heat or melt ice. Pitot Heat switch turned OFF. Turn switch ON.
Trouble - Pitot Static Pointer vibrates. Trouble - Altimeter Probable Cause Remedy Excessive vibration caused by loose mounting screws. Tighten mounting screws. Excessive tube vibration. Tighten clamps and connections. Probable Cause Remedy Excess scale error. Improper calibration adjustment. Replace instrument. Excessive pointer oscillation. Defective instrument. Replace or repair instrument. High reading. Static system leak. Inspect static system.
(c) (4) Blow clean, low-pressure air from the disconnected line at the airspeed indicator to the pitot tube. (d) Connect line at airspeed indicator. (e) Perform pitot system leakage test. (Refer to 34-10) (f) Install glareshield. (Refer to 25-10) Inspection/Check - Pitot System Leak Test The following procedure outlines inspection and testing of the pitot system. Perform this test any time an instrument, fitting, line, or pitot head is disconnected. (a) Acquire necessary tools, equipment, and supplies.
(a) (b) Open circuit breaker panel to gain access to altitude digitizer. Identify and disconnect lower static line at altitude digitizer branch tree and cap off branch tee. CAUTION: (c) (d) (e) (f) Never blow air through the line toward the instruments. To do so will seriously damage the instruments. Blow clean, low-pressure air from the disconnected line at the altitude digitizer branch tree to the static ports. Connect static line at altitude digitizer branch tree. Perform static system leakage test.
Description Hose Fitting (b) (c) (d) (e) (g) (h) (i) (l) (o) (p) (q) (r) Page 6 Hose attachment to valve. Do not apply positive pressure with airspeed indicator or vertical speed indicator connected into static system. If leakage rate exceeds the maximum allowable, check all fittings and hoses for condition and tightness and repeat leakage test. If leakage rate still exceeds the maximum allowable, perform the following procedure: Remove glareshield.
Figure 34-101 Pitot-Static System (Sheet 1 of 3) 13773-001 30 Nov 2000 34-10 Page 7
Figure 34-101 Pitot-Static System (Sheet 2 of 3) Page 8 34-10 13773-001 30 Nov 2000
Figure 34-101 Pitot-Static System (Sheet 3 of 3) 13773-001 30 Nov 2000 34-10 Page 9
D. Vertical Speed Indicator (See Figure 34-102) (1) (2) (3) Removal - Vertical Speed Indicator (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove MFD. (Refer to 34-40) (d) Remove and cap off static line. (e) Disconnect electrical connector. (f) While supporting vertical speed indicator, remove screws securing unit to instrument panel. (g) Cap off fitting on back of vertical speed indicator and remove from airplane.
Figure 34-102 VSI and Altimeter Installation 13773-001 30 Nov 2000 34-10 Page 11
F. Airspeed Indicator (See Figure 34-103) (1) (2) Removal - Airspeed Indicator (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull INSTRUMENT LIGHTS circuit breaker. (c) Remove glareshield. (Refer to 25-10) (d) Remove and cap off static and pitot line. (e) Disconnect electrical connector. (f) While supporting airspeed indicator, remove screws securing unit to instrument panel.
Figure 34-103 Airspeed Speed and OAT/Clock Gage Installation 13773-001 30 Nov 2000 34-10 Page 13
ATTITUDE AND DIRECTION 1. DESCRIPTION This section contains information pertaining to those portions of the system which use magnetic, gyroscopic, and inertia forces. Included is the magnetic compass, turn coordinator, attitude indicator, and horizontal situation indicator. (See Figure 34-001) The magnetic compass, mounted to the fuselage above the windshield, contains a circular compass card, visible through the compass case window, suspended in alcohol solution.
2. TROUBLESHOOTING Trouble - Magnetic Compass Excessive card error. Probable Cause Remedy Compass not properly compensated. Compensate instrument. External magnetic interference. Locate magnetic interference and eliminate if possible. Excessive card oscillation. Insufficient fluid. Replace instrument. Card sluggish. Weak card magnet. Replace instrument. Excessive pivot friction or broken jewel. Replace instrument. Loose bezel screws. Replace instrument.
Trouble - Attitude Indicator Horizon bar does not settle. Horizon bar oscillates or vibrates excessively. Probable Cause Remedy Defective instrument. Replace instrument. Excessive vibration. Tighten mounting screws. Excessive vibration. Tighten mounting screws. 3. MAINTENANCE PRACTICES A. Magnetic Compass (See Figure 34-201) (1) Removal - Magnetic Compass Assembly WARNING: When performing maintenance practices on the magnetic compass, use a non-magnetic or plastic screwdriver.
(f) (g) (h) Align centerline of airplane on magnetic South heading and note resulting South error. Adjust N-S set screw until one-half of error is removed. Align centerline of airplane on magnetic West heading and note resulting West error. Adjust E-W set screw until one-half of error is removed. Align centerline of airplane in successive magnetic 30-degree headings and record compass readings on appropriate deviation card. Deviations must not exceed 10 degrees on any heading. B.
Figure 34-201 Magnetic Compass Installation 13773-001 30 Nov 2000 34-20 Page 5
Figure 34-202 Turn Coordinator and Attitude Indicator Installation Page 6 34-20 13773-001 30 Nov 2000
D. HSI - NSD 1000 System (See Figure 34-203) (1) (2) (3) (4) (5) (6) Removal - NSD 1000 Display (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull HSI circuit breaker. (c) Remove pilot-side kick plate. (Refer to 25-10) (d) Disconnect cable. (e) While supporting HSI, remove screws securing unit to instrument panel. Installation - NSD 1000 Display (a) Position HSI in instrument panel and attach with screws. (b) Connect data cable. (c) Install pilot-side kick plate.
(c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) (n) (o) Page 8 Align airplane with North. Rotate HSI compass card to center slaving meter at 45°. Record heading deviation. Align airplane with East. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. Align airplane with South. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation. Align airplane with West. Rotate HSI compass card to center slaving meter at 45°. Read heading deviation.
Figure 34-203 HSI System Installation 13773-001 30 Nov 2000 34-20 Page 9
LANDING AIDS 1. DESCRIPTION This section covers that portion of the system which provides guidance during approach, landing, and taxiing. This includes glideslope and marker beacon systems. (See Figure 34-001) 2. MAINTENANCE PRACTICES A. Garmin GNS 430 GPS/COM/NAV The GNS 430 is an IFR certified VHF communications transceiver and Navigation Management System (NMS). The NMS includes GPS sensor, VOR/Localizer and Glideslope receivers.
Figure 34-301 Marker Beacon Antenna Installation Page 2 34-30 13773-001 30 Nov 2000
INDEPENDENT POSITION DETERMINING 1. DESCRIPTION This section covers that portion of the system which provides information to determine position from sources which are mainly independent of ground installations. This includes the GPS, multifunction display (MFD), and Stormscope systems. Two VHF communications (COM) transceivers are installed to provide VHF communication. The transceivers and integrated controls are mounted in the Garmin GNS 430 units.
(2) Installation - Garmin GNS 430 GPS/COM CAUTION: When mounting the transceiver, do not press on display window as damage may result. (a) (3) With light to medium pressure, push transceiver into mounting tray to engage electrical connectors. (b) Insert hex wrench into front panel bolt hole and engage hex bolt. (c) Turn bolt clockwise to tighten locking cam. (d) Reset ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers.
Figure 34-401 GNS 430 and Multifunction Display 13773-001 30 Nov 2000 34-40 Page 3
C. GPS 1 Antenna (See Figure 34-402) (1) (2) Removal - GPS 1 Antenna (a) Remove forward headliner. (Refer to 25-10) (b) Disconnect antenna cable from antenna. (c) Pry antenna from hook and loop fastener securing antenna to fuselage. (d) Remove antenna from airplane. Installation - GPS 1 Antenna (a) To secure antenna to fuselage, firmly press fastener strip on antenna against fastener strip fastened to the fuselage. (b) Connect antenna cable. (c) Install forward headliner. (Refer to 25-10) D.
F. COM 2 Antenna (See Figure 34-402) (1) (2) Removal - COM 2 Antenna (a) Remove baggage compartment floor access panel. (Refer to 6-00) (b) Disconnect antenna cable from antenna. (c) Remove nuts and washers securing antenna to fuselage. (d) Remove antenna and gasket from belly of fuselage (e) Peel off remaining sealant from fuselage. Installation - COM 2 Antenna (a) Acquire necessary tools, equipment, and supplies. Description Adhesive/Sealant (b) (c) (d) (e) (f) 13773-001 30 Nov 2000 P/N or Spec.
Figure 34-402 GPS and COM Antenna Installation Page 6 34-40 13773-001 30 Nov 2000
G. Stormscope (See Figure 34-403) (1) (2) (3) (4) Removal - Stormscope Processor and Tray (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull ESSENTIAL and NON-ESSENTIAL AVIONICS circuit breakers. (c) Remove processor: 1 Remove baggage compartment access panel CF5. (Refer to 6-00) 2 Remove safety wire securing knurled nut to mounting tray, loosen and swing knurled nut away from clasp.
(f) (g) Install center headliner. (Refer to 25-10) Fillet seal antenna perimeter. (Refer to 20-10) H. Stormscope System Tests (1) Test - Stormscope System (a) Set BATTERY and AVIONICS master switches to ON position. (b) On MFD, press top button to enter Software Main menu. (c) Press the CHECKLIST button. (d) Press the END PROGRAM button. (e) At left/right button pair, press left button to highlight END. (f) Press the SEL button to End Program. (g) Press the SETUP/USER GRAPHICS button.
(2) Antenna Mount Top J3 - 3 Jumper (aa) Press the top button. (ab) The SELF-TEST procedure will fail if the Stormscope Setup procedure (steps a through aa) isn’t performed prior to performing the SELF-TEST procedure. (ac) Press the SELF-TEST button and wait approximately 10 seconds. (ad) Verify Test Complete and PASSED. (ae) Press the top button. (af) Press the NOISE MONITOR button. (ag) A small number of triggers and/or random noise points inside display ring is acceptable.
Figure 34-403 Stormscope Installation Page 10 34-40 13773-001 31 July 2001
DEPENDENT POSITION DETERMINING 1. DESCRIPTION This section covers that portion of the system which provides information to determine position from sources which are mainly dependent on ground installations. This includes the Garmin GNS 430 GPS/ COM/NAV, Garmin GTX 327 Transponder system, and VOR/LOC Antenna.
Figure 34-501 Transponder and Antenna Installations Page 2 34-50 13773-001 30 Nov 2000
D. VOR/LOC Antenna (See Figure 34-502) (1) (2) Removal - VOR/LOC Antenna (a) Remove screws securing antenna mounting-plate to vertical stabilizer. (b) Lift antenna mounting-plate assembly from vertical stabilizer recess. (c) Disconnect antenna cable from antenna. (d) Remove screws securing antenna to mounting plate and remove antenna from airplane. Installation - VOR/LOC Antenna (a) Acquire necessary tools, equipment, and supplies.
Figure 34-502 VOR/LOC Antenna Installation Page 4 34-50 13773-001 30 Nov 2000
CHAPTER OXYGEN
CHAPTER 35 - OXYGEN LIST OF EFFECTIVE PAGES Chapter/Section Page Date 35-LOEP 1 30 NOV 2000 35-TOC 1 30 NOV 2000 35-00 1 30 NOV 2000 13773-001 30 Nov 2000 35-LOEP Page 1
CHAPTER 35 - OXYGEN TABLE OF CONTENTS Subject OXYGEN Chapter/Section Page 35-00 General 13773-001 30 Nov 2000 1 35-TOC Page 1
OXYGEN 1. GENERAL This chapter describes those units and components which store, regulate and deliver oxygen to the passengers and crew. Certain portable oxygen systems are approved for use in the airplane. Refer to the Pilot’s Operating Handbook and the applicable operating manuals listed in the front of this book for additional operating and maintenance information.
CHAPTER ELECTNC PNLS & MULTIPURPOSE PARTS
CHAPTER 39 - ELECTRONIC PANELS AND MULTIPURPOSE PARTS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 39-LOEP 1 30 NOV 2000 39-TOC 1 30 NOV 2000 39-00 1 30 NOV 2000 39-10 1 30 NOV 2000 39-10 2 30 NOV 2000 39-10 3 30 NOV 2000 39-10 4 30 NOV 2000 39-10 5 30 NOV 2000 13773-001 30 Nov 2000 39-LOEP Page 1
CHAPTER 39 - ELECTRONIC PANELS AND MULTIPURPOSE PARTS TABLE OF CONTENTS Subject ELECTRONIC PANELS AND MULTIPURPOSE PARTS Chapter/Section Page 39-00 General INSTRUMENT AND CONTROL PANEL 1 39-10 Description 1 Maintenance Practices 1 Instrument Panel Removal - Instrument Panel Installation - Instrument Panel Circuit Breaker Panel Removal - Circuit Breaker Panel Installation - Circuit Breaker Panel 13773-001 30 Nov 2000 1 1 1 3 3 3 39-TOC Page 1
ELECTRONIC PANELS AND MULTIPURPOSE PARTS 1. GENERAL The instrument panel is designed for glare-free use in all flight conditions. The instrument panel is arranged primarily for use by the pilot in the left seat; however, it can be viewed from either seat. Flight instruments and annunciators are located on the left side of the panel and engine instruments are located on the right side of the instrument panel.
INSTRUMENT AND CONTROL PANEL 1. DESCRIPTION The airplane uses standard flight instruments arranged in the “basic-six” pattern. The airspeed indicator, attitude gyro, altimeter, turn coordinator, horizontal situation indicator (HSI), and vertical speed indicator are mounted in the instrument panel. A switch panel located in the bolster panel below the flight instruments contains the avionics power switch, pitot heat switch, lighting dimmer switches, BAT 1, BAT 2, and alternator switches.
Figure 39-101 Instrument Panel Assembly Page 2 39-10 13773-001 30 Nov 2000
B. Circuit Breaker Panel (1) Removal - Circuit Breaker Panel CAUTION: The External Power Receptacle must be disconnected during the following procedure. (a) (b) (2) 13773-001 30 Nov 2000 Disconnect battery. (Refer to 24-30) Remove the screws securing the circuit breaker panel to the hinge and console. (Refer to 24-50) (c) Identify and disconnect all wire terminal connectors. Remove the circuit breaker panel.
Figure 39-102 Electronic Panel Locator Page 4 39-10 13773-001 30 Nov 2000
Figure 39-103 Bolster Panel Assembly 13773-001 30 Nov 2000 39-10 Page 5
CHAPTER STANDARD PRACTICES:
CHAPTER 51 - STANDARD PRACTICES: STRUCTURES LIST OF EFFECTIVE PAGES Chapter/Section Page Date 51-LOEP 1 31 JULY 2001 51-LOEP 2 31 JULY 2001 51-TOC 1 30 NOV 2000 51-TOC 2 30 NOV 2000 51-00 1 30 NOV 2000 51-00 2 30 NOV 2000 51-00 3 30 NOV 2000 51-00 4 30 NOV 2000 51-00 5 30 NOV 2000 51-00 6 30 NOV 2000 51-00 7 30 NOV 2000 51-00 8 30 NOV 2000 51-00 9 30 NOV 2000 51-00 10 31 JULY 2001 51-00 11 31 JULY 2001 51-10 1 30 NOV 2000 51-10 2 30 NOV 2000 51-10 3 30
CHAPTER 51 - STANDARD PRACTICES: STRUCTURES LIST OF EFFECTIVE PAGES Chapter/Section Page Date 51-20 21 30 NOV 2000 51-20 22 30 NOV 2000 51-20 23 30 NOV 2000 51-20 24 30 NOV 2000 51-20 25 30 NOV 2000 51-20 26 30 NOV 2000 51-20 27 30 NOV 2000 51-20 28 30 NOV 2000 51-20 29 30 NOV 2000 51-20 30 30 NOV 2000 51-20 31 30 NOV 2000 51-20 32 30 NOV 2000 51-20 33 30 NOV 2000 51-20 34 30 NOV 2000 51-20 35 30 NOV 2000 51-20 36 30 NOV 2000 51-20 37 30 NOV 2000 51-20
CHAPTER 51 - STANDARD PRACTICES: STRUCTURES TABLE OF CONTENTS Subject STANDARD PRACTICES: STRUCTURES Chapter/Section Page 51-00 General 1 Repairs Areas Lightning Protection (EMM) Composite Repair Requirements and Materials Exterior Finish Requirements and Materials Terminology ASSESSING COMPOSITE DAMAGE 1 1 1 1 2 51-10 Description 1 Maintenance Practices 1 Determining Extent of Damage Visual Coin Tap Exploration Types Of Damage COMPOSITE REPAIR 1 1 1 1 2 51-20 Description 1 Maintenance pract
CHAPTER 51 - STANDARD PRACTICES: STRUCTURES TABLE OF CONTENTS Subject Chapter/Section Maintenance Practices - Composite Repair Procedures 26 Preparation for Repair Repair Techniques Outer Laminate Repair Minor Core Damage Core Replacement Inner Laminate Repair Pure Laminate Repair EXTERIOR FINISH Page 27 31 31 34 36 38 38 51-30 Description 1 Maintenance Practices 1 Identification/Markings Surfacer (High Build Primer) Application of Surfacer Fillers Application of Body Filler Application of Spot P
STANDARD PRACTICES: STRUCTURES 1. GENERAL This chapter contains information and procedures applicable to all composite repairs as well as information and procedures for aircraft painting and priming. The basic elements of successful repair are; preparation of the laminate and repair material, proper mixing of resin, technique, and a complete cure cycle. If any element is not properly executed the repair will be substandard.
E. Terminology The following terms are used throughout this Chapter. Technicians involved in composite repair should be familiar with the following definitions, the materials used, and the procedures required. Page 2 Backing Plate A plate used behind a hole in the structure when making a composite repair. The backing plate is considered a tool and is not considered to add any strength to the repair.
Figure 51-001 Repair Areas (Sheet 1 of 3) 13773-001 30 Nov 2000 51-00 Page 3
Figure 51-001 Repair Areas (Sheet 2 of 3) Page 4 51-00 13773-001 30 Nov 2000
Figure 51-001 Repair Areas (Sheet 3 of 3) 13773-001 30 Nov 2000 51-00 Page 5
Figure 51-002 Lightning Protection (Sheet 1 of 4) Page 6 51-00 13773-001 30 Nov 2000
Figure 51-002 Lightning Protection (Sheet 2 of 4) 13773-001 30 Nov 2000 51-00 Page 7
Figure 51-002 Lightning Protection (Sheet 3 of 4) Page 8 51-00 13773-001 30 Nov 2000
Figure 51-002 Lightning Protection (Sheet 4 of 4) 13773-001 30 Nov 2000 51-00 Page 9
APPROVED COMPOSITE REPAIR MATERIALS Description P/N or Spec. Supplier Shelf Life Release Film WL5200 (Red or Blue) AIRTECH Int’l Inc. 18 months from date of manufacture Peel Ply Stitch Ply G AIRTECH Int’l Inc.
APPROVED PAINT MATERIALS Description P/N or Spec. Supplier Purpose Primer Surfacer Sys- K 36 Base tem * K 210 Hardener DT 860, 870, 885 Reducer DX 84 Enhancer PPG Industries, Inc. Aid paint adhesion and to fill minor surface imperfections Epoxy Primer Sealer DP 40 Base System * DP 410/402 Catalyst DT 860, 870, 885 Reducer PPG Industries, Inc.
ASSESSING COMPOSITE DAMAGE 1. DESCRIPTION Most damage to a composite structure will be visually detectable. An impact is the most common cause of damage and will usually leave visual evidence. Other types of damage are more difficult to detect but can be detected by simple methods. If the exterior surface is damaged, always assume that the underlying structure may also be damaged. 2. MAINTENANCE PRACTICES A.
Exploration is an extension of visual inspection, but requires removal of the surface coat. Removing the surface coat is a difficult task, and care must be taken to ensure that more damage is not created in the process. The exploration method must be used when the suspect area is hard or impossible to access or to evaluate the damage. A borescope or ultrasound can also be used for inspecting damage. B. Types Of Damage Structural damage to composite laminates can be divided into four categories or types.
Figure 51-101 Types of Laminate Damage 13773-001 30 Nov 2000 51-10 Page 3
COMPOSITE REPAIR 1. DESCRIPTION The quality of all repairs is directly related to application of proper repair procedures. This includes: cleaning and preparing the damaged area, cutting reinforcements, mixing and applying resin and curing the repair. The following are general practices used during most composite repairs. A repair technician must be familiar with these practices prior to attempting composite repairs on this airplane. 2. MAINTENANCE PRACTICES - GENERAL A.
(8) To determine the amount curing agent (CA) required for a given base resin weight (BRW) use the following formula: CA = BRW x 0.4 For example: If a repair required 250 gm of base resin, the amount of curing agent is calculated as follows: CA = BRW x 0.4 CA = 250 gm x 0.4 CA = 100 gm. Note: Mix ratio for MGS L418 resin is 100 parts resin, to 40 parts curing agent (100:40). (9) Place a second mixing cup on the scale. Record second mixing cup weight.
(1) (2) (3) (4) 13773-001 30 Nov 2000 Initial-Cure An initial-cure must be performed before handling the repaired area. Cure time at temperature for the initial cure is: (a) 5 hours at 125°-150°F (52°-66°C) (b) 3 hours at 150°-195°F (66°-91°C) Post-Cure Post-Cure must be completed before the assembly is ready for service. Multi-step post-cure may be used providing the total time at temperature meets the minimum requirement.
D. Laminating Laminating is accomplished after repair plies have been cut and the repair area is prepared (backing plates attached, core section replaced, repair surface abraded, repair surface solvent cleaned, etc.). Two methods are used for lamination of repair plies; Laminating in Place and the Transfer Method. WARNING: When using peel ply, position the peel ply on the outer ply (largest) only. Never bond repair plies to peel ply.
Note: Do not allow cleaning cloth to contact unprepared areas adjacent to the bond area. Contaminates could adhere to the cleaning cloth and become transferred onto the previously prepared area. Never apply solvent directly onto the part. Wipe surface until no sign of dust, particles or other contamination is visible on the cloth. After wiping, if cloth shows any signs of contamination, replace cloth. After solvent cleaning, the repair area must be allowed to air dry for a minimum of 15 minutes.
(2) Transfer Method This method is used when the repair is in a difficult position. The Transfer Method is similar to Laminating in Place, except the repair plies are wet with resin and then stacked-up on a clean sheet of plastic or release film. Repair plies are then centered over the damaged area. WARNING: Place each repair ply in the same direction as the original plies were positioned. Every other repair ply must have the directional fiber orientation staggered to prevent the repair from warping.
(i) (j) (k) Lay-up all remaining repair plies (largest to smallest) using the previous steps as guidelines. The remaining repair plies must be staggered from largest to smallest. Each repair ply must have an even amount of overlap around all edges of the previously installed repair ply. Place the second sheet of plastic directly over the stacked and evenly centered repair plies. Work out trapped air bubbles and excess resin out from between the plastic sheets with a squeegee.
Note: (a) Always manufacture backing plate on a surface with shape similar to the damaged area. Backing plate shall be approximately one inch larger (0.5" overlap on each side) than diameter of puncture if the backing plate is being bonded to backside of puncture. Acquire necessary tools, equipment, and supplies.
CAUTION: Ensure that size and shape of backing plate will not interfere with internal structure or other systems. Backing plate shall be approximately one-inch larger (0.5" overlap on each side) than diameter of puncture if the backing plate is being bonded to backside of puncture. If impossible to bond backing plate to backside of puncture, the backing plate must be sanded to form a scarf joint with a maximum overlap of 0.25-inch before installing the backing plate on the topside of the puncture.
Figure 51-201 Inner Laminate Damage Using Backing Plate Page 10 51-20 13773-001 30 Nov 2000
F. Cutting Reinforcements (1) Templates After the extent of damage is determined and the area is prepared, repair ply templates should be made. A template is used to assist in cutting the correct shape and size of glass-fabric. A template should be made for each layer (ply) of composite repair. Clear plastic sheet is commonly used for this purpose, however release film may be used instead of clear plastic. (a) (b) Remove surface coats from the surrounding area of laminate damage.
G. Ply Orientation Each ply has a fiber orientation. Fiber orientation, is the direction that the 0° axis fibers point. The glass-fabric used for repair in this airplane is Hexcel 7781-F16 fabric (the number 7781-F16 denotes the weave style and the fiber type). For repair purposes, 7781 is considered a balanced cloth, meaning that approximately 50% of the fibers run parallel to warp, and approximately 50% run perpendicular to warp. Fibers that run parallel to the edge are the 0° axis fibers.
Figure 51-202 Fiber Orientation 13773-001 30 Nov 2000 51-20 Page 13
H. Determining Ply Count Ply count refers to the thickness of unfinished laminate (no surfacer, sealer or paint). To determine ply count, measure the thickness of the damaged laminate (unpainted) in a relatively undamaged area. Always verify and compare the measurement taken from the damaged laminate to the following ply lay-up figures. A three-ply laminate without paint should measure approximately.030 inch.
Figure 51-203 Ply Lay-up (Sheet 1 of 11) 13773-001 30 Nov 2000 51-20 Page 15
Figure 51-203 Ply Lay-up (Sheet 2 of 11) Page 16 51-20 13773-001 30 Nov 2000
Figure 51-203 Ply Lay-up (Sheet 3 of 11) 13773-001 30 Nov 2000 51-20 Page 17
Figure 51-203 Ply Lay-up (Sheet 4 of 11) Page 18 51-20 13773-001 30 Nov 2000
Figure 51-203 Ply Lay-up (Sheet 5 of 11) 13773-001 30 Nov 2000 51-20 Page 19
Figure 51-203 Ply Lay-up (Sheet 6 of 11) Page 20 51-20 13773-001 30 Nov 2000
Figure 51-203 Ply Lay-up (Sheet 7 of 11) 13773-001 30 Nov 2000 51-20 Page 21
Figure 51-203 Ply Lay-up (Sheet 8 of 11) Page 22 51-20 13773-001 30 Nov 2000
Figure 51-203 Ply Lay-up (Sheet 9 of 11) 13773-001 30 Nov 2000 51-20 Page 23
Figure 51-203 Ply Lay-up (Sheet 10 of 11) Page 24 51-20 13773-001 30 Nov 2000
Figure 51-203 Ply Lay-up (Sheet 11 of 11) 13773-001 30 Nov 2000 51-20 Page 25
3. MAINTENANCE PRACTICES - COMPOSITE REPAIR PROCEDURES Always perform repairs in a clean, heated, and well ventilated area with good lighting. Before attempting a repair make sure all required tools, equipment, and material are ready. WARNING: Always use twice as many repair plies as the original lay-up in order to assure that the original strength is achieved. CAUTION: Many tools are needed to perform composite repairs properly.
A. Preparation for Repair (1) Acquire necessary tools, equipment, and supplies. Description 13773-001 30 Nov 2000 P/N or Spec.
(2) (3) Determine type of damage: (a) Laminate Only, Minor Core, Major Core, or Sandwich Penetration. (Refer to 51-10) Expose Damage and Prepare Repair Area (a) Cover the damaged area with plastic sheet and seal the edges with tape to prevent moisture from penetrating the composite laminate and core. (b) Clean the area surrounding the damage with hot soapy water. Rinse repair area with clean water and dry. When dry, remove plastic sheet from damaged area.
(j) CAUTION: Chemical strippers should not be used as they may damage the laminate, leave a residue or become trapped. Mechanical abrasion can also damage a laminate, and may be particularly damaging to certain joint designs (wing leading edge and fuselage joints). Grinders, air files and other single-action tools tend to intensify pressure at the edges and will rapidly remove paint and damage the underlying laminate. Note: Highly contoured or fine detail areas should always be done by hand.
Figure 51-204 Repair Patch Orientation Page 30 51-20 13773-001 30 Nov 2000
B. Repair Techniques One or more of the following techniques will be used to repair the damage. Expose and prepare the area as previously described under the section titled “Preparation for Repair”. WARNING: (1) Always use twice as many repair plies as the original lay-up in order to assure that the original strength is achieved. Outer Laminate Repair (a) If required, repair the inner laminate and core. (See Figure 51-205) (b) Determine ply count and orientation.
Note: (l) (m) (n) Page 32 When sanding EMM under antennas, the EMM should be exposed in at least 70% of the defined area. The defined area is typically the antenna footprint. The footprint area can be exceeded, but should not be more than 0.5-inch outside the footprint. When sanding EMM under bolts or washers, the EMM should be exposed in at least 90% of the defined area. Areas under bolts and washers can be exposed outside the bolt/washer area but should not exceed twice the diameter area.
Figure 51-205 Outer Laminate Damage Only 13773-001 30 Nov 2000 51-20 Page 33
(2) Minor Core Damage If the core has sustained only minor damage, it does not require replacement and may be filled with filler paste. If the core is gouged or dented, fill the indentation with filler paste. Mix filler paste. (See Figure 51-206), (Refer to 51-20) Note: (a) (b) Use more filler for vertical or overhead repairs, use less for filling small gaps. Using a clean spatula or wooden applicator, fill indentation with paste. Paste should be approximately flush with surrounding core.
Figure 51-206 Minor Core Damage and Outer Laminate Damage 13773-001 30 Nov 2000 51-20 Page 35
(3) Core Replacement If the damage penetrated the inner laminate or there is major damage to the core, a core section will have to be replaced and the integrity of the inner laminate restored. (See Figure 51-207) (a) (b) (c) (d) Using a utility knife, carefully cut through the core to the inner laminate. Cut perpendicular to the outer surface at the inside edge of the damage, do not score the inner laminate. Remove enough core to expose a border of undamaged inner laminate approximately 0.
Figure 51-207 Core Replacement and Outer Laminate Repair 13773-001 30 Nov 2000 51-20 Page 37
(4) Inner Laminate Repair WARNING: (a) If there is a hole in the inner laminate, trim the damaged laminate back until all damaged laminate is removed.(See Figure 51-201) Note: (b) (c) (d) (e) (f) (g) Always use twice as many repair plies as the original lay-up in order to assure that the original strength is achieved. If there is a hole in the inner laminate, make and attach a backing plate.
EXTERIOR FINISH 1. DESCRIPTION This section covers the proper procedures for painting the airplane, as well as procedures for preparing the exterior surface of the airplane for paint. The following procedures are used for application of surfacer, filler, sealer, and top coat. The following information must be used when painting the airplane. 2. MAINTENANCE PRACTICES A. Identification/Markings WARNING: Application of Identification/Markings must not cover pitot/static ports, drain holes or vent holes.
Note: It is unnecessary to use a straight primer when surfacer (high build primer) is being used. Always apply the surfacer per manufacturer’s instructions. Usually surfacer will be applied in three individual coats. It is preferable to use a finishing system (primer, surfacer, sealer, and paint) from one manufacturer for the entire refinishing procedure. If body filler is applied prior to surfacer, allow filler to fully cure and then apply surfacer. Surfacer should not exceed 4 mil. over large areas.
Note: (f) (g) (h) Wipe surface in one direction only to prevent smearing contaminates. For maximum results, wipe dry with clean white cloths in one direction only, while the surface is still wet. Mix surfacer per manufacturer's instructions, mix thoroughly. Apply surfacer as recommended by the manufacturer. Allow surfacer to fully cure. To determine low areas after application of the first surfacer coat, block sand with 120-grit sandpaper. Once the low areas are located, apply body filler to those areas.
C. Fillers Body filler and spot putty are two types of fillers used for repairing cosmetic blemishes and minor surface defects. Body filler is primarily used for repairing small dents and to fill large surface imperfections and gaps at seams or bond joints. Spot putty is used to fill minute cosmetic defects such as pits and minor scratches. WARNING: Aircraft control surface balance is critical to safe flight.
(c) (d) (e) Sand area with 80-grit to 120-grit sandpaper. Blow surface clean with compressed air. Solvent clean the application area with DX 330. (Refer to 20-30) Note: (f) (g) (h) (i) Mix body filler thoroughly per manufacturer's instructions. Apply body filler with a clean applicator according to the manufacturer's instructions. When the body filler is cured, rough out shape with 36-grit sandpaper. When the shape is approximately correct, switch to 80-grit sandpaper for final shaping.
(2) Application of Spot Putty After the repair area has been filled with body filler (if required) and/or coated with surfacer, apply a thin layer of spot putty to fill all minute cosmetic defects and/or minor scratches. (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. DX 330 PPG Industries, Inc.
(3) Filler Thickness Inspection Filler thickness is verified by inserting the pointed end of the toothpick into uncured filler. The wet portion of the toothpick is then measured with a vernier caliper. The wet portion of the toothpick is referred to as the filler thickness. Note: (a) If multiple layers of filler are used, each layer must be measured. Add the thickness of each layer together for total filler thickness. Over large areas, body filler thickness shall not exceed 0.13 inch (3.
(a) Acquire necessary tools, equipment, and supplies. Description (b) (d) (e) (h) Purpose DX 330 PPG Industries, Inc. Surface preparation Sandpaper 400-grit Any Source Abrade bonding surfaces Compressed air (contaminate free) - Any Source General repair Cotton cloth (clean and lint free) Any Source General cleaning Epoxy Primer/Sealer DP 40 Epoxy Primer Catalyst DP 401 Fast Epoxy Primer Catalyst DP 402 PPG Industries, Inc.
CAUTION: Cover any system that may be contaminated by paint or where extraneous paint may cause the system not to operate properly (for example, the flight control system and the pitot/static system). Mask bearings on lower vertical stabilizer hinge (rudder), aileron hinges, rod end bearings on flap actuation link, and rod end on aileron actuation arm. Mask off push-pull tube for rudder actuation. Do not paint plastic cap access panels on empennage.
(e) (f) (g) (h) (i) (j) Remove all exterior access panels except for the fuel system access panels. Remove wing tip fairings and landing gear fairings. (Refer to 57-20), (Refer to 32-10) Remove anti-collision strobe light assemblies from wing tip fairings. (Refer to 33-40) Remove upper and lower engine cowlings. (Refer to 71-10) Remove lower engine cowling access panel. Remove oil access door. Note: (k) (l) (m) (n) Remove VOR antenna wicks and rubber grommets. Remove baggage door.
(2) Application of Paint Note: Paint can be applied over the sealer if applied within the time frame set by the manufacturer. If set time of the sealer is unknown, beyond the manufacturer allowed limit, or if the surface required rework, the surface must be sanded with 400-grit wet/dry sandpaper and solvent cleaned with DX 330 prior to top coating. As an alternative to wet-sanding, the entire surface may be abraded with a fine grade of Scotchbrite.
(3) (g) Mix and apply top coat per manufacturer's instructions. Allow to fully cure. Post Painting Instructions The following components should be installed back onto the airplane: oil access door, lower engine cowling access panel, upper engine cowling, lower engine cowling, wing tip fairings, antenna components, and landing gear fairings. (a) Remove masking tape within the paint manufacture’s specified removal time. CAUTION: (b) (c) (d) (e) (f) (g) (h) (i) (j) Install all exterior access panels.
CHAPTER DOORS
CHAPTER 52 - DOORS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 52-LOEP 1 30 NOV 2000 52-TOC 1 30 NOV 2000 52-00 1 30 NOV 2000 52-10 1 30 NOV 2000 52-10 2 30 NOV 2000 52-10 3 30 NOV 2000 52-10 4 30 NOV 2000 52-10 5 30 NOV 2000 52-10 6 30 NOV 2000 52-10 7 30 NOV 2000 52-10 8 30 NOV 2000 52-10 9 30 NOV 2000 52-30 1 30 NOV 2000 52-30 2 30 NOV 2000 13773-001 30 Nov 2000 52-LOEP Page 1
CHAPTER 52 - DOORS TABLE OF CONTENTS Subject DOORS Chapter/Section Page 52-00 General PASSENGER AND CREW DOORS 1 52-10 Description and Operation 1 Maintenance Practices 2 Cabin Doors Removal - Cabin Door Installation - Cabin Doors Removal - Cabin Door Latching Mechanism Installation - Cabin Door Latching Mechanism Adjustment - Cabin Door Latching Mechanism Removal - Pin Receiver Installation - Pin Receiver Removal - Door Seals Installation - Door Seals Cleaning - Cabin Door Seals BAGGAGE DOOR 2 2
DOORS 1. GENERAL Two forward hinged doors on both sides of the fuselage allow cabin ingress and egress. Latching pins at the rear of each door are engaged by a door handle. A gas strut provides assistance opening, and holding, the door open. Front seat armrests are integral with the doors' interior. A baggage door is located on the left side of the airplane behind the rear seat. Occupants exit rearward off of the wing via a step.
52-10PASSENGER AND CREW DOORS PASSENGER AND CREW DOORS 1. DESCRIPTION AND OPERATION The two crew/passenger doors incorporate a flush-mount outside door handle, key-operated door lock, and a conventional inside door handle. The door latch handle is centered under the window. Latching pins at the rear of each door are engaged by that door’s handle.
2. MAINTENANCE PRACTICES A. Cabin Doors (1) Removal - Cabin Door (a) Remove locking cap from inboard end of gas strut. Remove gas strut from fuselage mounting bracket. (b) Remove glareshield trim and lower windshield trim to allow access to the lower door hinge retaining screw. (Refer to 25-10) CAUTION: The lower door hinge retaining screw only needs to be loosened to accomplish door removal. Removal of the lower door hinge screw is not recommended for door removal.
Figure 52-101 Crew Door Mounts 13773-001 30 Nov 2000 52-10 Page 3
(3) Removal - Cabin Door Latching Mechanism Note: The external handle can be removed by just removing the roll pin from the interior handle shaft. Always use the correct size pin punch when removing roll pins. (a) (b) (c) (4) Remove the screw and washer securing the interior handle to the interior handle shaft. Remove door panel screws. Remove inner door panel by gently pulling it away from the door, allowing hook and loop fasteners to separate.
Figure 52-102 Cabin Door Latch Hardware (Sheet 1 of 2) 13773-001 30 Nov 2000 52-10 Page 5
Figure 52-102 Cabin Door Latch Hardware (Sheet 2 of 2) Page 6 52-10 13773-001 30 Nov 2000
(5) Adjustment - Cabin Door Latching Mechanism (a) Open the cabin door and hold the cabin door handle in the full open position (keeping pressure on the compression springs). (b) Inspect and measure the clearance between both door pins and receivers using a feeler gage. Note: (c) (d) (e) (f) 13773-001 30 Nov 2000 The door pin and receiver clearance should be between 0.0 to 0.05-inch. If the pins need adjusting, proceed with the following steps. Remove door trim panel.
Figure 52-103 Cabin Door Adjustment Points Page 8 52-10 13773-001 30 Nov 2000
(6) Removal - Pin Receiver The pin receiver has four wear surfaces available. The pin receiver can be rotated to the new wear surface and then resealed with a white latex caulk. Note: (7) An alternate pin receiver is available. The alternate pin receiver has the receiver hole offset to one side. This offset pin receiver can be used if it’s impossible to latch the door with the standard pin receiver. (a) Remove the cabin headliner.
BAGGAGE DOOR 1. DESCRIPTION AND OPERATION The baggage door is located on the left side of the fuselage, just aft of the wing. This door allows easy access to the baggage compartment. The baggage door contains a molded storage pocket for storing small lightweight items. The baggage door is hinged on the forward edge and latched on the rear edge. The door is locked from the outside with a key lock. The baggage compartment key will also open the cabin doors. 2. MAINTENANCE PRACTICES A.
Figure 52-301 Baggage Door Hardware Page 2 52-30 13773-001 30 Nov 2000
CHAPTER FUSELAGE
CHAPTER 53 - FUSELAGE LIST OF EFFECTIVE PAGES Chapter/Section Page Date 53-LOEP 1 31 JULY 2001 53-TOC 1 31 JULY 2001 53-TOC 2 31 JULY 2001 53-00 1 30 NOV 2000 53-00 2 30 NOV 2000 53-10 1 30 NOV 2000 53-20 1 30 NOV 2000 53-20 2 30 NOV 2000 53-20 3 30 NOV 2000 53-20 4 30 NOV 2000 53-30 1 30 NOV 2000 53-30 2 30 NOV 2000 53-40 1 31 JULY 2001 53-40 2 30 NOV 2000 13773-001 31 July 2001 53-LOEP Page 1
CHAPTER 53 - FUSELAGE TABLE OF CONTENTS Subject FUSELAGE Chapter/Section Page 53-00 General MAIN FRAME 1 53-10 Description 1 Firewall FS 222 Bulkhead FS 289 Bulkhead FS 306 Bulkhead Spar Tunnel Roll Cage AUXILIARY STRUCTURE 1 1 1 1 1 1 53-20 Description 1 Entry Step and Support Handle Fuselage Floor Structure Maintenance Practices 1 1 1 Fuselage Floor Access Panels Removal - Fuselage Floor Access Panels Installation - Fuselage Floor Access Panels Entry Step Removal - Entry Step Installation -
CHAPTER 53 - FUSELAGE TABLE OF CONTENTS Subject Chapter/Section ATTACH FITTINGS Page 53-40 Description 1 Maintenance Practices 1 Seat Track Removal - Seat Track Installation - Seat Track Footman Loops Removal - Footman Loops Installation - Footman Loops Page 2 53-TOC 1 1 1 1 1 1 13773-001 31 July 2001
FUSELAGE 1. GENERAL The SR22 fuselage is a semi monocoque structure made primarily of composite materials. The fuselage structure is comprised of two halves fabricated from fiberglass laminate bonded along a centerline lapjoint. The vertical stabilizer, door frames, window frames, and recess channel for the forward parachute risers, are all integral to the fuselage structure. The cabin area is limited by the forward firewall at FS 100, and the cargo compartment bulkhead at FS 222.
Figure 53-001 Fuselage Components Page 2 53-00 13773-001 30 Nov 2000
MAIN FRAME 1. DESCRIPTION This section describes those structural components which make up the main frame including vertical stabilizer, firewall, bulkheads, spar tunnel, and roll cage. A. Firewall The firewall is designed to separate the engine compartment from the rest of the fuselage and support various airplane components on both the forward and aft sides.
AUXILIARY STRUCTURE 1. DESCRIPTION This section describes those structural components which make up the auxiliary structure including fuselage floor structure, floor access panels, entry step, and support handle. A. Entry Step and Support Handle The entry step is constructed 0.049" gage streamline steel tubing. The entry step has 0.09" gage flanges that are welded to the tubing and secured to the fuselage belly and the aft floor. The support handle is constructed of 0.
C. Support Handle (See Figure 53-202) (1) (2) Removal - Support Handle (a) Remove cabin headliner. (Refer to 25-10) (b) Remove screws and washers securing support handle to fuselage and remove from airplane. Installation - Support Handle (a) Acquire necessary tools, equipment, and supplies. Description Loctite (b) (c) Page 2 P/N or Spec. 242 Blue Supplier Loctite Corp Newington, CT Purpose Sealant Position support handle to fuselage, apply loctite to handle stud, and install washers and screws.
Figure 53-201 Floor Access Panel Installation 13773-001 30 Nov 2000 53-20 Page 3
Figure 53-202 Entry Step and Handle Installation Page 4 53-20 13773-001 30 Nov 2000
PLATES AND SKIN 1. DESCRIPTION This section describes the exterior covering of the fuselage which makes up the skin. Also included are the fuselage access panels. A. Fuselage Skin The fuselage skin is composed primarily of bi-directional E-glass fiberglass with a PVC foam core. Some areas are of solid laminate construction. Areas around the passenger door are reinforced with unidirectional fiberglass.
Figure 53-301 Empennage Access Panels Page 2 53-30 13773-001 30 Nov 2000
ATTACH FITTINGS 1. DESCRIPTION Attach fittings are provided for attachment of the wing assembly (Refer to 57-00), landing gear (Refer to 3200), doors (Refer to 52-00), engine (Refer to 72-00), and seats. Footman loops are installed on baggage compartment floor and F.S. 222 cabin bulkhead. Cockpit seats are secured to the airplane through the use of aluminum tracks mounted to the wing spar tunnel. The track assemblies are installed at a 10° angle which allows the seat to rise as it is moved forward.
Figure 53-401 Seat Track Installation Page 2 53-40 13773-001 30 Nov 2000
CHAPTER STABILIZERS
CHAPTER 55 - STABILIZERS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 55-LOEP 1 30 NOV 2000 55-TOC 1 30 NOV 2000 55-00 1 30 NOV 2000 55-10 1 30 NOV 2000 55-20 1 30 NOV 2000 55-20 2 30 NOV 2000 55-20 3 30 NOV 2000 55-20 4 30 NOV 2000 55-30 1 30 NOV 2000 55-40 1 30 NOV 2000 55-40 2 30 NOV 2000 55-40 3 30 NOV 2000 55-40 4 30 NOV 2000 55-40 5 30 NOV 2000 55-40 6 30 NOV 2000 55-40 7 30 NOV 2000 55-40 8 30 NOV 2000 13773-001 30 Nov 2000 55-LOEP Page 1
CHAPTER 55 - STABILIZERS TABLE OF CONTENTS Subject STABILIZERS Chapter/Section Page 55-00 General HORIZONTAL STABILIZER 1 55-10 Description 1 Maintenance Practices 1 Horizontal Stabilizer 1 ELEVATOR 55-20 General 1 Maintenance Practices 1 Elevator Removal - Elevator Installation - Elevator Inspection/Check - Elevator Elevator Balancing VERTICAL STABILIZER 1 1 1 1 2 55-30 Description 1 Maintenance Practices 1 RUDDER 55-40 General 1 Maintenance Practices 1 Rudder Removal - Rudder
STABILIZERS 1. GENERAL The horizontal stabilizer and vertical stabilizers are fully cantilever, semimonocoque design consisting of spars, ribs, and skin. The skin is bonded to the supporting structure. The horizontal stabilizer is a single composite structure from tip to tip. The two-piece elevator, attached to the horizontal stabilizer, is aluminum. The vertical stabilizer is composite structure integral to the main fuselage shell for smooth transfer of flight loads.
HORIZONTAL STABILIZER 1. DESCRIPTION The horizontal stabilizer is a lifting surface (fixed airfoil) attached to the rear of the fuselage and provides stability in pitch. 2. MAINTENANCE PRACTICES A. Horizontal Stabilizer Because the horizontal stabilizer is made from composite materials and is bonded to the fuselage, no servicing is required. An aerodynamically balanced elevator is hinged to the trailing edge of the horizontal stabilizer.
ELEVATOR 1. GENERAL This section covers procedures for servicing the elevator assembly. The elevator is a movable control surface which is mounted in a horizontal position on the tail of the airplane. It is mounted to the horizontal stabilizer and is used to rotate the airplane about its lateral axis. The elevator itself is made from aluminum and the elevator tips are made from composite materials.
(4) (f) Verify proper installation of safety wire and for use of new cotter pins on all fasteners. (g) Install access panels LE1 and RE1. (Refer to 6-00) (h) Operate elevator controls and inspect for any abnormal resistance. Elevator Balancing CAUTION: Before balancing, ensure no breeze or drafts are in balancing room. Note: To balance the elevator, the assembly must be complete including composite elevator tip and all attaching hardware. (a) Remove elevator.
Figure 55-201 Elevator Assembly (Sheet 1 of 2) 13773-001 30 Nov 2000 55-20 Page 3
Figure 55-201 Elevator Assembly (Sheet 2 of 2) Page 4 55-20 13773-001 30 Nov 2000
VERTICAL STABILIZER 1. DESCRIPTION The vertical stabilizer is the fixed vertical surface on the airplane empennage in which the rudder is hinged to. The vertical stabilizer consists of two C-channel spars fabricated from S2 uni-directional and 7781 bidirectional fiberglass. Two ribs are bonded to the spars at WL 131.25 and WL 159.
RUDDER 1. GENERAL The rudder provides airplane directional (yaw) control. It is of conventional design with skin, spar and ribs manufactured of aluminum. It is attached to the aft vertical stabilizer shear web at three hinge points and to the fuselage tailcone at the rudder control bell crank. Rudder motion is transferred from conventional rudder pedals to the rudder by a single cable system under the cabin floor to the elevator sector pulley in the aft fuselage.
Figure 55-401 Rudder Assembly (Sheet 1 of 2) Page 2 55-40 13773-001 30 Nov 2000
Figure 55-401 Rudder Assembly (Sheet 2 of 2) 13773-001 30 Nov 2000 55-40 Page 3
(5) Balancing - Rudder (See Figure 55-402) CAUTION: (a) When balancing the rudder, the rudder assembly must be complete including mounting brackets, paint, stripes, rudder bottom, and rudder tip. The bench used to support the knife edge supports must be level. Before balancing, ensure there are no drafts in the balancing room, which can deflect the surface from its balanced condition. Maximum mass balance weight is 2.5 pounds. Acquire necessary tools and equipment.
(o) Carefully place rudder assembly onto knife edge supports and determine if a static overbalance (leading edge heavy) or static underbalance (trailing edge heavy) condition exists. Note: If chord line mark is parallel to balance arm without any additional weight the rudder assembly is balanced.
Figure 55-402 Rudder Balancing (Sheet 1 of 3) Page 6 55-40 13773-001 30 Nov 2000
Figure 55-402 Rudder Balancing (Sheet 2 of 3) 13773-001 30 Nov 2000 55-40 Page 7
Figure 55-402 Rudder Balancing (Sheet 3 of 3) Page 8 55-40 13773-001 30 Nov 2000
CHAPTER WINDOWS
CHAPTER 56 - WINDOWS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 56-LOEP 1 30 NOV 2000 56-TOC 1 30 NOV 2000 56-00 1 30 NOV 2000 56-10 1 30 NOV 2000 56-10 2 30 NOV 2000 56-10 3 30 NOV 2000 56-10 4 30 NOV 2000 56-10 5 30 NOV 2000 56-10 6 30 NOV 2000 56-10 7 30 NOV 2000 56-10 8 30 NOV 2000 56-10 9 30 NOV 2000 56-10 10 30 NOV 2000 56-10 11 30 NOV 2000 56-10 12 30 NOV 2000 56-20 1 30 NOV 2000 56-20 2 30 NOV 2000 56-20 3 30 NOV 2000 56-20 4 30 NOV 2
CHAPTER 56 - WINDOWS TABLE OF CONTENTS Subject WINDOWS Chapter/Section Page 56-00 General FLIGHT COMPARTMENT 1 56-10 Description and Operation 1 Maintenance Practices 1 Windshield Removal - Windshield Installation - Windshield Windshield - Cleaning CABIN 1 1 5 12 56-20 Description and Operation 1 Maintenance Practices 1 Passenger and Aft Windows Removal - Passenger and aft Windows Installation - Passenger and aft Windows Window - Cleaning DOOR 1 1 4 11 56-30 Description and Operation 1 M
WINDOWS 1. GENERAL The airplane is equipped with an acrylic windshield and side windows. The windows are made of stretched acrylic. The windows are adhesive bonded to the fuselage or door structure. The windows are all fixed and cannot be opened.
FLIGHT COMPARTMENT 1. DESCRIPTION AND OPERATION The flight compartment windows on the Cirrus Design SR22 covers the windshield only. All windshield replacements are accomplished by removing the interior panels around the windshield, removing the four retaining clips, removing sealant around the windshield, and then removing the windshield itself. In general the reverse process is used to install a replacement windshield.
Note: (i) (j) Cut sealant loose from between fuselage and windshield using a small pocket knife. While pushing in on the windshield, follow the edge of the fuselage with the tip of the blade, then back cut in towards the fuselage to clean out the sealant. (See Figure 56-102) Using a phenolic or hardwood utility knife, isopropyl alcohol and aluminum oxide sandpaper (80-grit), remove all remaining sealant from the fuselage bonding flange.
Figure 56-101 Windshield Clips 13773-001 30 Nov 2000 56-10 Page 3
Figure 56-102 Windshield Removal Page 4 56-10 13773-001 30 Nov 2000
(2) Installation - Windshield (See Figure 56-103) and (See Figure 56-104) Windshield sealant is intended to provide a seal between the windshield and fuselage and to prevent the leakage of air through the airframe structure. Window sealant is used in the installation of all windows in the aircraft. Isopropyl alcohol, kerosene, white alptha naptha, mineral spirits, and cotton are acceptable for cleaning acrylic windows.
Description (d) (e) (f) (h) LP Aero Plastics Rd#1 Box 201-B Jeannette, PA 15644 Aid in adhesion Protective Coating AC-940 Blue AC Products, Inc. 172 Ela Jolla St.
Note: (k) (l) Five or more padded cargo rods may be necessary to hold the windshield into the proper position. Padded cargo rods may be placed on each corner of the windshield and in the center of the windshield. Additional padded cargo rods may be required to prevent the windshield from sliding down. Inspect the windshield for proper fit. The windshield must have equal amounts of space around the perimeter of the windshield.
Figure 56-103 Windshield Alignment Page 8 56-10 13773-001 30 Nov 2000
(n) (o) (p) (q) Remove a small amount (approximately 2-inches wide) of protective coating from around edge of windshield. Install a continuous piece of fine line tape (pinstripe tape) around the edge of the windshield (next to the bonding flange). The fine line tape should be adhered to the windshield with equal amounts of space between the fine line tape on the fuselage and the fine line tape on the windshield.
(aa) Mix sealant per manufacturer's instructions. Mix the required quantity in the ratio specified in the adhesive manufacturer's instructions. (Refer to 25-10) CAUTION: Do not apply sealant to windshield bonding flange. The sealant must be applied to the fuselage bonding flange. (ab) Apply a thin layer of sealant to the outer edge of the fuselage bonding flange. Spread the sealant out using an application spatula.
Figure 56-104 Windshield Installation 13773-001 30 Nov 2000 56-10 Page 11
(3) Windshield - Cleaning (Refer to 12-20) Acrylic windows should be cleaned using the following chemicals, and by following the manufactures instructions for each individual product. (a) Acquire necessary tools, equipment, and supplies. Description Page 12 P/N or Spec. Supplier Purpose Acrylic Polish and Sealant SP-PL16 LP Aero Plastics, Inc. Polish acrylic Plastic Cleaner and Polish SP-210A LP Aero Plastics, Inc. Clean acrylic Plastic Scratch Remover SP-210P LP Aero Plastics, Inc.
CABIN 1. DESCRIPTION AND OPERATION All replacements are accomplished by removing the interior panels around the window, removing the sealant around the window, and then removing the window itself. In general the reverse process is used to install a replacement window. This method is literally seamless, and the fuselage will show no marks or evidence of maintenance. The passenger and aft windows are made from acrylic plastic. 2. MAINTENANCE PRACTICES A.
CAUTION: Page 2 56-20 Exercise care to prevent removal of laminate from fuselage when cutting and removing sealant from between fuselage and window. If laminate is damaged, it must be repaired prior to installing the window.
Figure 56-201 Window Removal 13773-001 30 Nov 2000 56-20 Page 3
(2) Installation - Passenger and aft Windows (See Figure 56-202) and (See Figure 56-203) Window sealant is intended to provide an acceptable seal between the window and fuselage and to prevent the leakage of air through the airframe structure. Window sealant is used in the installation of all windows in the aircraft. Isopropyl alcohol, kerosene, white alptha naptha, mineral spirits, and cotton are acceptable for cleaning acrylic windows.
Description (d) (e) (f) (h) LP Aero Plastics Rd#1 Box 201-B Jeannette, PA 15644 Aid in adhesion Protective Coating AC-940 Blue AC Products, Inc. 172 Ela Jolla St.
Note: (k) (l) Five or more padded cargo rods may be necessary to hold the window into the proper position. Padded cargo rods may be placed on each corner of the window and in the center of the window. Additional padded cargo rods may be required to prevent the window from sliding down. Inspect the window for proper fit. The window must have equal amounts of space around the perimeter of the window. The exterior surface of the window should be flush with exterior surface of fuselage.
Figure 56-202 Window Alignment 13773-001 30 Nov 2000 56-20 Page 7
(n) (o) (p) (q) Remove a small amount (approximately 2-inches wide) of protective coating from around edge of window. Install a continuous piece of fine line tape (pinstripe tape) around the edge of the window (next to the bonding flange). The fine line tape should be adhered to the window with equal amounts of space between the fine line tape on the fuselage and the fine line tape on the window.
(aa) Mix sealant per manufacturer's instructions. Mix the required quantity in the ratio specified in the adhesive manufacturer's instructions. (Refer to 20-10) CAUTION: Do not apply sealant to window bonding flange. The sealant must be applied to the fuselage bonding flange. (ab) Apply a thin layer of sealant to the outer edge of the fuselage bonding flange. Spread the sealant out using an application spatula.
Figure 56-203 Window Installation Page 10 56-20 13773-001 30 Nov 2000
(3) 13773-001 30 Nov 2000 (ah) Remove cargo rods. (ai) Remove the drop cloth. (aj) Using a vacuum cleaner, remove all debris. (ak) Install and secure interior trim panels.
DOOR 1. DESCRIPTION AND OPERATION The cabin door windows are stretched acrylic bonded to the door structure. All cabin door window replacements are accomplished by removing the interior panels around the window and removing sealant around the window, and then removing the window itself. In general the reverse process is used to install a replacement window. This method is literally seamless, and the door will show no marks or evidence of maintenance. 2. MAINTENANCE PRACTICES A.
CAUTION: Page 2 56-30 Exercise care to prevent removal of laminate from door when cutting and removing sealant from between door and window. If laminate is damaged, it must be repaired prior to installing the window.
Figure 56-301 Window Removal 13773-001 30 Nov 2000 56-30 Page 3
(2) Installation - Door Window (See Figure 56-302) and (See Figure 56-303) Window sealant is intended to provide an acceptable seal between the window and door and to prevent the leakage of air through the airframe structure. Window sealant is used in the installation of all windows in the aircraft. Isopropyl alcohol, kerosene, white alptha naptha, mineral spirits, and cotton are acceptable for cleaning acrylic windows.
Description (d) (e) (f) (h) LP Aero Plastics Rd#1 Box 201-B Jeannette, PA 15644 Aid in adhesion Protective Coating AC-940 Blue AC Products, Inc. 172 Ela Jolla St.
Note: (k) (l) Five or more cargo rods may be necessary to hold the window into the proper position. Cargo rods may be placed on each corner of the window and in the center of the window. Additional cargo rods may be required to prevent the window from sliding down. Inspect the window for proper fit. The window must have equal amounts of space around the perimeter of the window. The exterior surface of the window should be flush with exterior surface of door skin.
Figure 56-302 Window Alignment 13773-001 30 Nov 2000 56-30 Page 7
(n) (o) (p) (q) Remove a small amount (approximately 2-inches wide) of protective coating from around edge of window. Install a continuous piece of fine line tape (pinstripe tape) around the edge of the window (next to the bonding flange). The fine line tape should be adhered to the window with equal amounts of space between the fine line tape on the door and the fine line tape on the window.
(aa) Mix sealant per manufacturer's instructions. Mix the required quantity in the ratio specified in the adhesive manufacturer's instructions. (Refer to 20-10) CAUTION: Do not apply sealant to window bonding flange. The sealant must be applied to the door bonding flange. (ab) Apply a thin layer of sealant to the outer edge of the door bonding flange. Spread the sealant out using an application spatula.
Figure 56-303 Window Installation Page 10 56-30 13773-001 30 Nov 2000
(3) 13773-001 30 Nov 2000 (ah) Remove cargo rods. (ai) Remove the drop cloth. (aj) Using a vacuum cleaner, remove all debris. (ak) Install and secure interior trim panels.
CHAPTER WINGS
CHAPTER 57 - WINGS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 57-LOEP 1 30 NOV 2000 57-TOC 1 30 NOV 2000 57-TOC 2 30 NOV 2000 57-00 1 30 NOV 2000 57-10 1 30 NOV 2000 57-20 1 30 NOV 2000 57-30 1 30 NOV 2000 57-30 2 30 NOV 2000 57-40 1 30 NOV 2000 57-40 2 30 NOV 2000 57-40 3 30 NOV 2000 57-50 1 30 NOV 2000 57-50 2 30 NOV 2000 57-50 3 30 NOV 2000 57-50 4 30 NOV 2000 57-50 5 30 NOV 2000 57-50 6 30 NOV 2000 13773-001 30 Nov 2000 57-LOEP Page 1
CHAPTER 57 - WINGS TABLE OF CONTENTS Subject WINGS Chapter/Section Page 57-00 General WING STRUCTURE 1 57-10 Description AUXILIARY STRUCTURE 1 57-20 Description 1 Maintenance Practices 1 Wing Tip Removal - Wing Tip Installation - Wing Tip PLATES/SKIN 1 1 1 57-30 Description 1 Maintenance Practices 1 Wing Access Panels Removal - Collector Tank and Fuel Tank Panels (Type 3 and 4) Installation - Collector Tank and Fuel Tank Panels (Type 3 and 4) Removal - Wing Panels Installation - Wing Panel
CHAPTER 57 - WINGS TABLE OF CONTENTS Subject Chapter/Section FLIGHT SURFACES Page 57-50 Description 1 Maintenance Practices 1 Aileron Assembly Removal - Aileron Assembly Installation - Aileron Assembly Inspection/Check - Aileron Assembly Adjustment - Aileron Balancing Flap Assembly Removal - Flap Assembly Installation - Flap Assembly Page 2 57-TOC 1 1 1 1 1 6 6 6 13773-001 30 Nov 2000
WINGS 1. GENERAL The wing is manufactured from composite materials, which produce smooth and seamless flight surfaces. The wings provide attachment structure for the main landing gear and contain one integral fuel tank and one integral collector tank in each wing.
WING STRUCTURE 1. DESCRIPTION The wing is constructed in a conventional spar, rib, and shear section arrangement. The upper and lower skins are bonded to the spar, ribs, and aft shear web forming a torsion box that carries all of the wing bending and torsion loads. The rear shear webs are similar in construction but do not carry through the fuselage. The wing spar is manufactured in one piece and is continuous from wing tip to wing tip.
AUXILIARY STRUCTURE 1. DESCRIPTION The leading edge of the wing is manufactured from composite materials. This airplane has a one-piece wing with individual wing tips. The wing tips are manufactured from composite materials. Each strobe light module is secured inside the corresponding wing tip. 2. MAINTENANCE PRACTICES A. Wing Tip (1) (2) Removal - Wing Tip (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in the “OFF” position. (b) Pull NAV LIGHTS and STROBE LIGHTS circuit breakers.
PLATES/SKIN 1. DESCRIPTION Access openings with covers are provided between ribs to allow access to the integral fuel tanks, fuel lines, and the wing electrical components. The fuel tank access panels (oval shaped panels) allow access for servicing the integral fuel tank components. The access panels located next to the fuselage on the aft portion of the wing allows access to the integral collector tanks. 2. MAINTENANCE PRACTICES A.
Approved Sealants Item P/N or Spec. Extrusion Gun Seal- MIL-S-8802 Type 2 ant Class B* CS3204 C1.B GC408B P/S 890B PR1440B EC1675B AC-240B Supplier Chem Seal - Flame Master Goal PRC Aerospace Sealants PRC Aerospace Sealants 3M Dynamold Aerospace Application Fillet, faying surface, and injection seal in fuel tanks. Install and seal windows. Seal fuel system enclosure in cabin. * When ordering MIL-S-8802 sealants make sure that an appropriate work life is specified.
ATTACH FITTINGS 1. DESCRIPTION Wing loads are transferred to the fuselage through four wing-attach points, two which are located under each front seat and the remaining two on either sidewall just aft of the rear seats. The forward attach points transfer load into the spar tunnel. The aft attach points transfer load into the fuselage skin and aft floor. 2. MAINTENANCE PRACTICES A. Wing Attachments The wing is not field removable, therefore, removal of the wing attachments is not permissible.
(b) (c) (d) (e) (f) Remove existing liquid shim material. Solvent clean the attach bracket with isopropyl alcohol. (Refer to 20-30) Apply release agent (Frekote NC700 or release tape) to inner surfaces of the attach bracket. Mix liquid shim in accordance with manufacture’s instructions. Inject a 3/8-inch (9.5 mm) wide bead of liquid shim across the entire width (inner surface) of the attach bracket.
Figure 57-401 Wing Attach Hardware 13773-001 30 Nov 2000 57-40 Page 3
FLIGHT SURFACES 1. DESCRIPTION The flaps are mounted to the trailing edge of each wing between the inboard end of the ailerons and the fuselage. The ailerons are located near the wing tips and hinge to the aileron spar to become part of the trailing edge of the wing. The ailerons and flaps are made from aluminum. 2. MAINTENANCE PRACTICES A. Aileron Assembly (1) Removal - Aileron Assembly (a) Remove wing tip.
To balance the aileron, the assembly must be painted and complete, including all attaching hardware. WARNING: (a) Before balancing, ensure no breeze or drafts are in balancing room. Maximum allowable mass balance is 1.05 pound at each mass balance location. Acquire necessary tools, equipment, and supplies.
Note: Underbalanced (trailing edge heavy) conditions are corrected by adding additional weight to the control surface. Typically, by placing additional washers, lead or steel, under each nut or bolt head retaining the balance mass, as required. A maximum of four washers per bolt and nut retaining the balance masses and a maximum of three washers under any bolt head or nut. Always place steel washer next to nut.
Figure 57-501 Aileron Assembly (Sheet 1 of 2) Page 4 57-50 13773-001 30 Nov 2000
Figure 57-501 Aileron Assembly (Sheet 2 of 2) 13773-001 30 Nov 2000 57-50 Page 5
B. Flap Assembly (1) Removal - Flap Assembly (a) Cut safety wire securing rod end mounting bolt to the actuation fitting on the flap. CAUTION: When removing the rod end mounting bolt, exercise caution to prevent the flap from swinging downward and making contact with the landing gear. (b) (2) Remove the rod end mounting bolt and washer to allow the flap to swing down to the underside of the wing. (c) Remove the cotter pins from each of the flap mounting bolts.
CHAPTER PROPELLER
CHAPTER 61 - PROPELLER LIST OF EFFECTIVE PAGES Chapter/Section Page Date 61-LOEP 1 30 NOV 2000 61-TOC 1 30 NOV 2000 61-00 1 30 NOV 2000 61-00 2 30 NOV 2000 61-00 3 30 NOV 2000 61-00 4 30 NOV 2000 61-10 1 30 NOV 2000 61-10 2 30 NOV 2000 61-10 3 30 NOV 2000 61-10 4 30 NOV 2000 61-10 5 30 NOV 2000 61-10 6 30 NOV 2000 61-10 7 30 NOV 2000 61-10 8 30 NOV 2000 61-10 9 30 NOV 2000 61-20 1 30 NOV 2000 61-20 2 30 NOV 2000 61-20 3 30 NOV 2000 13773-001 30 Nov 20
CHAPTER 61 - PROPELLER TABLE OF CONTENTS Subject PROPELLER Chapter/Section Page 61-00 General 1 Troubleshooting 2 PROPELLER ASSEMBLY 61-10 Description 1 Maintenance Practices 1 Propeller Removal - Propeller Installation - Propeller Adjustment/Test - Propeller Balance Inspection/Check - Propeller Assembly Inspection/Check - Blade Track Inspection/Check - Loose Blades Approved Repairs - Blades Cleaning/Painting - Propeller Blades PROPELLER CONTROL 1 1 2 4 4 4 4 6 8 61-20 General 1 Maintenanc
PROPELLER 1. GENERAL The airplane employs a 3 blade, Hartzell Compact PHC-J3YF-1RF/F7694, constant speed, non-feathering propeller. The aluminum blades are mounted in an aluminum hub which contains the pitch changing mechanism consisting of a piston/cylinder, piston rod, and blade actuating components. For propeller speed adjustment, a propeller control cable is terminated on a cam plate which is mounted to the throttle control lever.
2. TROUBLESHOOTING Trouble Surging propeller. Probable Cause Remedy Governor out of adjustment. Inspect and adjust governor. Air in propeller governor oil body. Cycle propeller through pitch range several times. Engine speed varies with attitude Governor not properly controlling or airspeed. propeller blade angle. Inspect and adjust governor. Friction in propeller. Inspect propeller and make necessary adjustments. Decrease in engine speed while increasing airspeed.
Figure 61-001 Propeller Schematic 13773-001 30 Nov 2000 61-00 Page 3
SR2_MM34_1480 RESERVED Figure 61-002 Propeller Control Page 4 61-00 13773-001 30 Nov 2000
PROPELLER ASSEMBLY 1. DESCRIPTION The propeller assembly consists of a hollow aluminum hub which supports the propeller blades and also houses the pitch changing mechanism. Movement of propeller blades is controlled by a hydraulic piston/ cylinder combination mounted on the front of the hub. The linear motion of the hydraulic piston is transmitted to each blade through a pitch change rod and fork. A pitch change knob at the base of each blade intersects with the fork.
(k) (2) Remove bolts, spacers, washers, and nuts securing spinner backing plate to propeller hub. (l) Remove O-ring from groove inside hub at flange mounting and discard. Installation - Propeller (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (i) Any Source Hoist propeller. Sling - Any Source Secure propeller to hoist. Degreaser - Any Source Degrease components. O-Ring C-3317-228 Hartzell Propellers Inc. Sealing compoPiqua, Ohio nent.
Figure 61-101 Propeller Installation 13773-001 30 Nov 2000 61-10 Page 3
(3) Adjustment/Test - Propeller Balance (a) Acquire necessary tools, equipment, and supplies. Description P/N or Spec. Vibrex 2000 Balancer/Ana- 13590 lyzer Kit Supplier Chadwick-Helmuth Purpose Propeller Balance (b) (4) (5) Perform dynamic balancing in accordance with Chadwick Helmuth Vibrex 2000 Users Guide and propeller balancing booklet; The Smooth Propeller, indexed in the List or Publications in the front of this manual.
Figure 61-102 Propeller Inspection 13773-001 30 Nov 2000 61-10 Page 5
(7) Approved Repairs - Blades (See Figure 61-103) Nicks, gouges, and scratches on blade surfaces or on leading or trailing edges must be removed prior to flight. Field repair of small nicks and scratches may be performed by qualified personnel in accordance with FAA Advisory Circular 43.13-1(latest approved revision), as well as the maintenance practices specified below. WARNING: (a) Re-work which involves cold working the metal, resulting in concealment of damaged area, is NOT acceptable.
Figure 61-103 Repair Limitations 13773-001 30 Nov 2000 61-10 Page 7
(8) Cleaning/Painting - Propeller Blades Propeller blades are painted with a durable specialized coating that is resistant to abrasion. If this coating becomes eroded, it is necessary to re-paint the blades to provide proper corrosion and erosion protection. Painting should be performed by an authorized propeller repair station in accordance with Hartzell Propeller Owner’s Manual and Handbook. It is permissible to perform a blade touch-up with aerosol paint in accordance with the procedure below.
(g) (h) 13773-001 30 Nov 2000 WARNING: Finish coatings are flammable and toxic to the skin, eyes, and respiratory tract. Skin and eye protection is required. Avoid prolonged contact. Use in well ventilated area. CAUTION: Apply finish coating only to the degree required to uniformly cover the repair/erosion. Avoid excessive paint build-up along trailing edge to avoid changing blade profile. Apply the appropriate finish coat to achieve 2 to 4 mils (0.51 - 0.10 mm) thickness when dry.
PROPELLER CONTROL 1. GENERAL The Woodward Governor Assembly P/N D210760 is an engine RPM sensing device and high pressure oil pump. Pressurized engine oil is directed to the propeller hydraulic cylinder or released from the hydraulic cylinder in response to engine RPM change. Change in oil volume in the hydraulic cylinder changes the blade angle and returns the propeller system RPM to the value set by the cockpit throttle/propeller control.
Note: (g) (h) With power lever full forward, observe engine RPM which should read 2650 RPM. If engine tachometer does not read 2650 RPM, shut down engine, and adjust the low pitch/high RPM screw on the governor: cut safety-wire from adjustment screw, loosen adjustment screw locknut and turn screw in clockwise direction to decrease engine speed or in counterclockwise direction to increase engine speed.
Figure 61-201 Governor Installation 13773-001 30 Nov 2000 61-20 Page 3
CHAPTER POWER PLANT
CHAPTER 71 - POWERPLANT LIST OF EFFECTIVE PAGES Chapter/Section Page Date 71-LOEP 1 31 JULY 2001 71-TOC 1 30 NOV 2000 71-TOC 2 30 NOV 2000 71-00 1 30 NOV 2000 71-00 2 30 NOV 2000 71-00 3 30 NOV 2000 71-00 4 30 NOV 2000 71-00 5 30 NOV 2000 71-00 6 30 NOV 2000 71-00 7 30 NOV 2000 71-00 8 30 NOV 2000 71-00 9 30 NOV 2000 71-00 10 30 NOV 2000 71-00 11 30 NOV 2000 71-00 12 30 NOV 2000 71-00 13 30 NOV 2000 71-10 1 30 NOV 2000 71-10 2 30 NOV 2000 71-10 3 30
CHAPTER 71 - POWERPLANT TABLE OF CONTENTS Subject POWER PLANT Chapter/Section Page 71-00 General 1 Description 1 Troubleshooting 2 Maintenance Practices 12 Engine Removal - Engine Installation - Engine Engine Baffling Removal - Engine Baffling Installation - Engine Baffling COWLING 12 12 13 14 14 14 71-10 Description 1 Maintenance Practices 1 Engine Cowling Removal - Engine Cowling Installation - Engine Cowling MOUNTS 1 1 1 71-20 Description 1 Maintenance Practices 1 Engine Mount Wel
CHAPTER 71 - POWERPLANT TABLE OF CONTENTS Subject Chapter/Section Mixture Control Cable Bracket Removal - Mixture Control Cable Bracket Installation - Mixture Control Cable Bracket Fuel and Hose Line Stand-Off Clamps Removal - Fuel and Hose Line Stand-Off Clamps Installation - Fuel Line and Hose Stand-offs ELECTRICAL HARNESS Page 1 1 2 2 2 2 71-50 Description 1 Maintenance Practices 1 Electrical Harness Removal - Electrical Harnesses Installation - Electrical Harnesses AIR INTAKES 1 1 1 71-60 Des
POWER PLANT 1. GENERAL This chapter describes maintenance practices for the airplane systems which provide the means to induce and convert fuel-air mixture into power such as the engine, air intake, mount, cowling, and attach fittings. 2. DESCRIPTION (See Figure 71-001) The SR22 is powered by a Teledyne Continental IO-550-N, six-cylinder, normally aspirated, fuel-injected engine rated to 310 hp at 2700 RPM. Dual, conventional magnetos provide ignition.
3. TROUBLESHOOTING TROUBLE Engine Will Not Start. PROBABLE CAUSE REMEDY Improper use of starting procedure. Refer to Pilot’s Operating Handbook. (List of Publications) Fuel tank empty. Inspect and fill tank. (Refer to 1210) Mixture control in SHUTOFF posi- Advance mixture control to RICH tion. position. Page 2 71-00 Fuel selector valve in OFF position. Place selector valve in ON position to tank known to contain fuel. Fuel vaporization. Turn boost pump ON. Engine flooded.
TROUBLE Engine Will Not Run At Idling Speed Rough Idling PROBABLE CAUSE REMEDY Fuel injection system improperly adjusted. See “Engine Fuel System Troubleshooting.” (Refer to 73-00) Air leak in intake manifold. Torque loose connection or replace malfunctioning part Fuel injection system improperly adjusted. Adjust fuel system in accordance with IO-550 Maintenance Manual Chapter 22 “Fuel System Adjustment.” (Refer to TCM Model IO550 Overhaul Manual) Mixture levers set for improper mixture.
TROUBLE PROBABLE CAUSE REMEDY Continuous Fouling Of Spark Plugs Piston rings excessively worn or broken Piston rings are not seated. Engine Runs Rough At High Speed Loose mounting bolts or damaged Torque mounting bolts. Replace mount pads. mount pads. (Refer to 71-20) Continuous Missing At High Speed Sluggish Operation And Low Power Replace rings. Replace cylinder if damaged Hone cylinder walls, replace rings. Plugged fuel nozzle jet. Clean.
TROUBLE High Cylinder Head Temperature Oil Leaks PROBABLE CAUSE REMEDY Lean fuel/air mixture. See the Pilot’s Operating Handbook (POH) for correct leaning procedure. (List of Publications) Debris between cylinder fins. Clean thoroughly. Incorrect engine timing. Adjust engine timing in accordance with IO-550 Maintenance Manual Chapter 12.” (Refer to TCM Model IO-550 Overhaul Manual) Exhaust system gas leakage. Locate and correct in accordance with the Pilot’s Operating Handbook (POH) instructions.
TROUBLE Low Fuel Pressure High Fuel Pressure PROBABLE CAUSE REMEDY Incorrect fuel pump adjustment. Check and adjust in accordance with IO-550 Maintenance Manual Chapter 22, “Fuel System Adjustment.” (Refer to Model IO-550 Maintenance Manual) Malfunctioning fuel pump relief valve. Replace fuel pump. Malfunctioning relief valve operation in fuel pump. Replace fuel pump. Restricted recirculation passage in Replace fuel pump. fuel pump. Incorrect fuel pump adjustment.
TROUBLE Engine Runs Rough At Speeds Above Idle PROBABLE CAUSE REMEDY Improper Fuel/Air mixture. Check fuel manifold connections for leaks. Torque loose connections. Check fuel control/metering unit and linkage for setting and adjustment in accordance with IO550 Maintenance Manual Chapter 22, “Fuel System Adjustment.” (Refer to Model IO-550 Maintenance Manual) Check fuel filters and screens for debris. Check for proper fuel pump pressure. Restricted fuel nozzle jet. Clean.
Figure 71-001 Engine Components (Sheet 1 of 4) Page 8 71-00 13773-001 30 Nov 2000
Figure 71-001 Engine Components (Sheet 2 of 4) 13773-001 30 Nov 2000 71-00 Page 9
Figure 71-001 Engine Components (Sheet 3 of 4) Page 10 71-00 13773-001 30 Nov 2000
Figure 71-001 Engine Components (Sheet 4 of 4) 13773-001 30 Nov 2000 71-00 Page 11
4. MAINTENANCE PRACTICES A. Engine (1) Removal - Engine CAUTION: Place a tail stand of suitable capacity under tail of airplane before removing engine. Note: Tag each component when disconnected to facilitate reinstallation. Protect openings exposed as a result of removing or disconnecting components against entry of foreign material by installing covers or sealing with tape. (a) (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) Place all electrical switches in the cockpit in the OFF position.
CAUTION: (y) (z) Loosen bolts securing engine to engine mounts. Attach hoist at forward and aft lifting points. Lift engine just enough to relieve weight from engine mounts. CAUTION: (2) Prior to removing engine attach bolts, ensure all hoses, wires, lines, cables, cable ties, and clamps are disconnected or removed from positions which would interfere with engine removal. Note location and position of engine mount isolators prior to engine removal for reference on reinstallation.
(w) (x) Fill engine with proper grade and amount of engine oil. (Refer to 12-20) Place fuel selector valve in the ON position, open throttle and mixture to full, turn on electric full pump, and check fuel lines for leaks. (y) Perform Functional Inspection of Fuel Injection System in accordance with Teledyne Continentals Motors Service Information Directive 97-3. (Refer to 5-20) (z) Perform operational check. (Refer to 5-30) (aa) Install engine cowling. (Refer to 71-10) B.
Figure 71-002 Engine Baffling Installation 13773-001 71-00 Page 15
COWLING 1. DESCRIPTION The engine cowling, fabricated from fiberglass and epoxy, consists of one upper and two lower halves. A urethane close-out seal is secured to the lower cowl halves to fully surround the nose gear strut. The cowling is secured to the fuselage with quarter-turn fasteners and screws. The oil inspection door is located on the upper cowling and external power receptacle door is located on the lower cowling. The landing light assembly is integral to the RH lower cowl.
(g) (h) (i) (j) Page 2 Ensure clearance between propeller spinner and cowling measures at least 0.25" (0.64 cm). Open engine oil access door and inspect engine baffle seal. Seal must be bent inward ensuring a seal along the radius of the upper cowling. Close engine oil access door. Remove protective tape from spinner.
SR2_MM71_1442 RESERVED Figure 71-101 Engine Cowling Installation 13773-001 30 Nov 2000 71-10 Page 3
MOUNTS 1. DESCRIPTION This section describes the framework which supports and attaches the engine to the airplane. Included are the engine mount weldment and elastomeric vibration isolators. The engine is attached to a welded tubular steel engine mount. The engine mount weldment is fastened to the fuselage firewall at four points by steel bolts. Conventional elastomeric isolators are employed for vibration dampening.
(e) (2) Raise or lower hoist just enough to force separation between engine mounting point and engine mount isolators. Remove isolators from airplane. Installation - Engine Mount Isolators Note: (a) (b) (c) (d) Page 2 If isolator is being reused, ensure isolators are reinstalled in same location as originally installed. Raise or lower hoist just enough to insert stepped isolator into engine side of mounting point.
Figure 71-201 Engine Mount and Isolator Installation 13773-001 31 July 2001 71-20 Page 3
ATTACH FITTINGS 1. DESCRIPTION This section describes those fittings and brackets which are used for support of components in and about the powerplant. These items include the throttle control cable, governor control cable, mixture control cable, and fuel and hose line stand-off clamps. 2. MAINTENANCE PRACTICES A. Throttle Control Cable Bracket (See Figure 71-401) (1) (2) Removal - Throttle Control Cable Bracket (a) Remove engine cowling.
(d) (2) Remove nuts and washers, and spacers securing cable bracket to engine mounting pad and remove bracket from airplane. Installation - Mixture Control Cable Bracket (a) Align control cable bracket with mounting pad studs and install spacers, washers, and nuts. (b) Insert control cable into bracket, align retaining plate over cable bracket, and install bolt, washers, and nut. (c) Connect control cable to mixture control arm and install bolt, washers, nut, and cotter pin.
SR2_MM71_1449 RESERVED Figure 71-401 Attach Fittings (Sheet 1 of 2) 13773-001 30 Nov 2000 71-40 Page 3
SR2_MM71_1449 RESERVED Figure 71-401 Attach Fittings (Sheet 2 of 2) Page 4 71-40 13773-001 30 Nov 2000
ELECTRICAL HARNESS 1. DESCRIPTION This chapter describes the electrical cables, plugs, connectors, etc. which serve power plant and airplane systems, but are banded together to facilitate removal and installation of the engine. The airplane employs two engine wiring harnesses.
AIR INTAKES 1. DESCRIPTION This section describes that portion of the power plant which directs mass air flow to the engine. Induction air enters the engine through a filter mounted on the left, forward side of the engine then flows into the induction duct assembly mounted center, forward on the engine.
(c) (d) (e) (f) (g) (h) (i) (j) (k) (l) Page 2 Route alternate air control cable through mounting bracket, firewall, and engine baffling, to flapper valve control arm. Install washer and nut securing alternate air control knob to cockpit mounting bracket. Install bolt, washers, nut, and cotter pin securing control cable to flapper valve control arm. Wrap FiberFrax paper around portion of control cable which will pass through firewall fitting so a tight fit is achieved at the cable/firewall interface.
Figure 71-601 Induction System Installation 13773-001 30 Nov 2000 71-60 Page 3
ENGINE DRAINS 1. DESCRIPTION This section describes those components and manifold assemblies which are used to drain off excess fluids for the power plant and its accessories. This includes the fuel, oil, and battery system engine drains. 2. MAINTENANCE PRACTICES A. System Drain Hoses (See Figure 71-701) (1) (2) 13773-001 30 Nov 2000 Removal - System Drain Hose (a) Remove engine cowling. (Refer to 71-10) (b) Determine length of new hose by measuring existing hose on airplane.
SR2_MM71_1482 RESERVED Figure 71-701 Engine Drains Page 2 71-70 13773-001 30 Nov 2000
CHAPTER ENGINE
CHAPTER 72 - ENGINE LIST OF EFFECTIVE PAGES Chapter/Section Page Date 72-LOEP 1 30 NOV 2000 72-TOC 1 30 NOV 2000 72-00 1 30 NOV 2000 13773-001 30 Nov 2000 72-LOEP Page 1
CHAPTER 72 - ENGINE TABLE OF CONTENTS Subject ENGINE Chapter/Section Page 72-00 General 13773-001 30 Nov 2000 1 72-TOC Page 1
ENGINE 1. GENERAL For information pertaining to this chapter such as maintenance practices, limits, and procedures for teardown, cleaning, inspection, assembly, testing, etc., refer to Teledyne Continental Motors Maintenance Manual listed in the introduction of this manual in the List of Publications.
CHAPTER ENGINE FUEL SYSTEMS
CHAPTER 73 - ENGINE FUEL SYSTEM LIST OF EFFECTIVE PAGES Chapter/Section Page Date 73-LOEP 1 30 NOV 2000 73-TOC 1 30 NOV 2000 73-00 1 30 NOV 2000 73-00 2 30 NOV 2000 73-00 3 30 NOV 2000 73-00 4 30 NOV 2000 73-30 1 30 NOV 2000 73-30 2 30 NOV 2000 13773-001 30 Nov 2000 73-LOEP Page 1
CHAPTER 73 - ENGINE FUEL SYSTEM TABLE OF CONTENTS Subject ENGINE FUEL SYSTEM Chapter/Section Page 73-00 General 1 Troubleshooting 2 INDICATING 73-30 Description 1 Maintenance Practices 1 Map/Fuel Flow Gage Fuel Flow Sensor Removal - Fuel Flow Sensor Installation - Fuel Flow Sensor 13773-001 30 Nov 2000 1 1 1 1 73-TOC Page 1
ENGINE FUEL SYSTEM 1. GENERAL This chapter describes those units and components which deliver metered fuel and air to the engine. Components covered include the manifold pressure gage/fuel flow gage. For additional information on fuel injection system components, refer to the Teledyne Continental Motors Model IO-550 Fuel Injection Systems Overhaul and Parts Catalog indexed in the List of Publications in the front of this manual.
2. TROUBLESHOOTING Trouble Probable Cause Remedy Engine Will Not Start And No Fuel No fuel to engine. Check fuel tank level. Flow Indication Mixture control improperly rigged. Check mixture control for proper rigging. (Refer to TCM Model IO550 Overhaul Manual) Engine Will Not Start With Fuel Flow Indication Rough Idle Poor Acceleration Engine not primed. Auxiliary pump switch to BOOST position. Selector valve in OFF position. Position selector valve to ON position. Engine flooded.
Trouble Low Fuel Flow Indication High Fuel Flow Indication Probable Cause Remedy Restricted flow to metering valve. Check mixture control for full travel. Inadequate flow from fuel pump. Verify pump pressure, adjust engine-driven pump. (Refer to TCM Service Bulletin SID97-3) Restricted flow beyond metering valve. Check for restricted nozzles or fuel metering valve. Clean or replace as required.
Figure 73-001 Fuel System Page 4 73-00 13773-001 30 Nov 2000
INDICATING 1. DESCRIPTION This section describes that portion of the engine fuel system which is used to indicate the flow rate. This includes the MAP/fuel flow gage and fuel flow transducer. The Fuel Flow Transducer located between the throttle body metering valve and the injector manifold is mounted on the RH inter-cylinder baffling. The electrically operated Fuel Flow Transducer transmits fuel flow rate data to the cockpit Fuel Flow gage. 2. MAINTENANCE PRACTICES A. Map/Fuel Flow Gage (Refer to 77-10) B.
SR2_MM73_1483 RESERVED Figure 73-301 Fuel Sensor Installation Page 2 73-30 13773-001 30 Nov 2000
CHAPTER IGNITION
CHAPTER 74 - IGNITION LIST OF EFFECTIVE PAGES Chapter/Section Page Date 74-LOEP 1 30 NOV 2000 74-TOC 1 30 NOV 2000 74-00 1 30 NOV 2000 74-00 2 30 NOV 2000\ 74-00 3 30 NOV 2000 74-00 4 30 NOV 2000 74-00 5 30 NOV 2000 74-00 6 30 NOV 2000 74-00 7 30 NOV 2000 74-10 1 30 NOV 2000 74-10 2 30 NOV 2000 74-20 1 30 NOV 2000 74-20 2 30 NOV 2000 74-20 3 30 NOV 2000 74-20 4 30 NOV 2000 74-30 1 30 NOV 2000 74-30 2 30 NOV 2000 74-30 3 31 JULY 2001 13773-001 31 July
CHAPTER 74 - IGNITION TABLE OF CONTENTS Subject IGNITION Chapter/Section Page 74-00 General 1 Troubleshooting 2 ELECTRICAL POWER SUPPLY 74-10 Description 1 Maintenance Practices 1 Magnetos Removal - Magnetos Installation - Magnetos DISTRIBUTION 1 1 1 74-20 Description 1 Maintenance Practices 1 Ignition Harness Removal - Ignition Harness Installation - Ignition Harness Spark Plugs Removal - Spark Plugs Installation - Spark Plugs SWITCHING 1 1 1 2 2 2 74-30 Description 1 Maintenance Pr
IGNITION 1. GENERAL This chapter describes those units and components which furnish, distribute, and control an electrical current to ignite the fuel-air mixture in the engine cylinders. The ignition components include magnetos, ignition harness, spark plugs, and ignition switch. The magnetos are completely self-contained ignition generating devices. Mounted center aft on the accessory case, each magneto utilizes a rotating magnet to induce a voltage into a magnetic coil.
2. TROUBLESHOOTING Trouble Hard Starting Probable Cause Remedy Incorrect external timing to engine. (Refer to TCM Model IO-550 Overhaul Manual) Correct as required. Incorrect internal timing. Correct as required. Point gap setting incorrect. (Refer to TCM Ignition Systems Master Service Manual) Correct as required. Faulty impulse coupling. (Refer to TCM Ignition Systems Master Service Manual) Correct as required. Worn pawls or stop pin. Inspect pawls and stop pin for wear. Correct as necessary.
Trouble Hard Starting Rough Running 13773-001 30 Nov 2000 Probable Cause Remedy Condenser Inspect for faulty P-lead connection, P-lead stud for overtorqued condition, damaged pigtail connector, and integrity of windings. Coil Inspect for cracks, damage to high tension strap or pigtail connector, and integrity of windings. Distributor Gear Inspect electrode finger for looseness, gear teeth, and shaft. Inspect carbon brush for damage.
Trouble Rough Running or Vibration in Specific RPM Range Probable Cause Remedy Magneto internal component failure: (Refer to TCM Ignition Systems Master Service Manual) Specifications and inspection procedures. Points Inspect for excessive burning, pitting, corrosion, gap setting, and general condition. Cam Inspect cam for excessive wear or unevenness that could cause “point spread”.
Trouble Probable Cause Remedy Excessive RPM Drop During Mag- Corrosion on harness lead conneto Check tacts. (Refer to TCM Ignition Systems Master Service Manual) Cleaning and inspection procedures. Magneto Will Not Fire Faulty ignition switch. Inspect ignition switch for possibility of intermittent grounding and proper operation. Repair or replace as necessary. Faulty condenser.
Trouble Probable Cause Remedy High Tension Lead on Coil Worn or Burned Through Improper tension between high tension lead and carbon brush. (Refer to TCM Ignition Systems Master Service Manual) High tension lead loading specifications. Coil Cracked or Arcing in Case Faulty coil. (Refer to TCM Ignition Systems Master Service Manual) Inspect for cracks, damage to high tension strap or pigtail connector, and integrity of windings. Incorrect spark plug gap.
Figure 74-001 Ignition System 13773-001 30 Nov 2000 74-00 Page 7
ELECTRICAL POWER SUPPLY 1. DESCRIPTION This section describes the maintenance practices pertinent to the magnetos. For additional maintenance practices pertaining to the magnetos, refer to the List of Publications listed in the front of this manual. (Refer to TCM Ignition Systems Master Service Manual) 2. MAINTENANCE PRACTICES A. Magnetos (See Figure 74-101) (1) Removal - Magnetos (a) Remove cowling.
Figure 74-101 Magneto Installation Page 2 74-10 13773-001 30 Nov 2000
DISTRIBUTION 1. DESCRIPTION This section describes the maintenance practices of that portion of the ignition system which conducts high-voltage electricity from the magnetos to the spark plugs. For additional information pertaining to the ignition harness and spark plugs, refer to the List of Publications in the front of this manual. (Refer to TCM Ignition Systems Master Service Manual) 2. MAINTENANCE PRACTICES A.
B. Spark Plugs (See Figure 74-202) (1) Removal - Spark Plugs (a) Remove engine cowling. (Refer to 71-10) CAUTION: (2) To prevent damage to the spark plug insulator and connector, when withdrawing insulator from spark plug, pull the harness lead straight out and at same angle as the barrel. (b) Remove ferrule assembly nut on harness lead and remove insulator from spark plug. (c) Remove spark plug from engine and place in identification tray.
SR2_MM74_1465 RESERVED Figure 74-201 Ignition System Installation 13773-001 30 Nov 2000 74-20 Page 3
Figure 74-202 Spark Plug Installation Page 4 74-20 13773-001 30 Nov 2000
SWITCHING 1. DESCRIPTION This section describes that portion of the ignition system which provides a means of rendering the ignition electrical power supply inoperative. This includes the ignition switch. 2. MAINTENANCE PRACTICES A. Ignition Switch (See Figure 74-301) (1) (2) (3) Removal - Ignition Switch (a) Turn ignition switch to the OFF position. (b) Remove engine cowling. (Refer to 71-10) (c) Disconnect battery.
(f) (g) Page 2 1 Remove P-lead from left magneto. 2 Attach P-lead to ohmmeter and to airframe ground 3 With switch in OFF or R position, ohmmeter should indicate a closed circuit With ignition switch in L or BOTH position, ohmmeter should indicate an open circuit 4 5 Connect P-lead to left magneto Connect battery. (Refer to 24-30) Install engine cowling.
Figure 74-301 Ignition Switch Installation 13773-001 31 July 2001 74-30 Page 3
CHAPTER ENGINE CONTROLS
CHAPTER 76 - ENGINE CONTROLS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 76-LOEP 1 31 JULY 2001 76-TOC 1 31 JULY 2001 76-00 1 30 NOV 2000 76-00 2 30 NOV 2000 76-00 3 30 NOV 2000 76-10 1 31 JULY 2001 76-10 2 31 JULY 2001 76-10 3 31 JULY 2001 76-10 4 31 JULY 2001 76-10 5 31 JULY 2001 76-10 6 31 JULY 2001 76-10 7 31 JULY 2001 76-10 8 31 JULY 2001 13773-001 31 July 2001 76-LOEP Page 1
CHAPTER 76 - ENGINE CONTROLS TABLE OF CONTENTS Subject ENGINE CONTROLS Chapter/Section Page 76-00 General 1 Troubleshooting 3 POWER CONTROL 76-10 Description 1 Maintenance Practices 1 Control Quadrant Removal - Control Quadrant Installation - Control Quadrant Throttle Control Cable Removal - Throttle Control Cable Installation - Throttle Control Cable Adjustment/Test - Throttle Control Cable Mixture Control Cable Removal - Mixture Control Cable Installation - Mixture Control Cable Adjustment/T
ENGINE CONTROLS 1. GENERAL This chapter describes the controls which govern operation of the engine. The engine controls for the airplane consist of the following: throttle, mixture, and propeller. The primary controls employ conventional push-pull type levers and are connected to a control quadrant mounted forward on the center console. The quadrant control assembly incorporates a friction lock which can be adjusted to retain the throttle and mixture control lever positions.
SR2_MM76_1481 RESERVED Figure 76-001 Engine Controls Page 2 76-00 13773-001 30 Nov 2000
2. TROUBLESHOOTING Trouble Power Lever Binding Probable Cause Remedy Control-quadrant friction knob too Loosen friction knob. tight. Cable defective or worn. Replace cable. Quadrant assembly nuts too tight. Loosen nuts, reinstall cotter pins. Bearing worn on cam follower. Mixture Lever Binding Control-quadrant friction knob too Loosen friction knob. tight. Cable defective or worn. Engine Rpm Too High Or Low During Flight Replace bearing. Replace cable.
POWER CONTROL 1. DESCRIPTION This section describes those components which furnish a means of controlling engine power. Engine controls for the airplane include the following: control quadrant, throttle control cable, mixture control cable, and governor control cable. 2. MAINTENANCE PRACTICES A. Control Quadrant (See Figure 76-101) (1) (2) 13773-001 31 July 2001 Removal - Control Quadrant (a) Remove RH cockpit seat. (Refer to 25-10) (b) Remove control-quadrant friction knob and washer.
Figure 76-101 Control Quadrant Installation Page 2 76-10 13773-001 31 July 2001
B. Throttle Control Cable (See Figure 76-102) (1) Removal - Throttle Control Cable (a) Remove engine cowling. (Refer to 71-10) (b) At throttle body, remove cotter pin, nut, washers, and bolt securing throttle cable rod-end bearing to throttle control arm. (c) Remove rod-end bearing. (d) Remove bolts securing control-cable support bracket to engine. (e) Remove any clamps or ties securing control cable to engine mount. (f) Remove control-quadrant friction knob and washer. (g) Remove RH cockpit seat.
(i) (3) At throttle body, secure throttle cable rod-end bearing to throttle control arm with bolt, washers, nut, and cotter pin. (j) Wrap fiber paper around portion of throttle cable which passes through firewall fitting so a tight fit is achieved at the cable/firewall interface. (k) Adjust slack in cable, tighten throttle bracket retaining clip nut, align throttle bracket with engine mounting pad studs, and install nut. (l) Install clamps or ties securing control cable to engine mount.
(2) Installation - Mixture Control Cable (a) Acquire necessary tools, equipment, and supplies. Description (b) P/N or Spec. Supplier Purpose High Temperature Silicone Sealant RTV 736 Dow Corning Sealant Fiber Frax Paper 970J,TON0146 UniFrax Firewall Insulation Ensure cable fitting on firewall is clear and free of old sealant. CAUTION: When routing the control cable, ensure the cable does not interfere with airplane control rigging, wires, or hoses.
SR2_MM76_1468 RESERVED Figure 76-102 Control Cable Installation Page 6 76-10 13773-001 31 July 2001
D. Governor Control Cable (See Figure 76-102) (1) Removal - Governor Control Cable (a) Remove engine cowling. (Refer to 71-10) (b) Remove cotter pin, nut, washers, and bolt securing governor control cable rod-end bearing to governor control arm. (c) Remove rod-end bearing. (d) At forward cable support bracket mounted to engine, remove retaining plate nut, washers, and bolt and remove control cable from support bracket.
(i) (j) (k) (l) (m) (n) (o) (p) (q) (r) Page 8 At governor, secure rod-end bearing to governor control arm with bolt, washers, nut, and cotter pin Wrap fiber paper around portion of control cable which will pass through firewall fitting so a tight fit is achieved at the cable/firewall interface. Install clamps or ties securing control cable to engine mount. Perform Governor Rigging and Maximum RPM Adjustment (Refer to 61-20) Solvent clean firewall fitting and fitting/cable interface.
CHAPTER ENGINE INDICATING
CHAPTER 77 - ENGINE INDICATING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 77-LOEP 1 31 JULY 2001 77-TOC 1 30 NOV 2000 77-00 1 30 NOV 2000 77-00 2 30 NOV 2000 77-10 1 30 NOV 2000 77-10 2 30 NOV 2000 77-10 3 30 NOV 2000 77-20 1 30 NOV 2000 77-20 2 30 NOV 2000 77-20 3 31 JULY 2001 13773-001 31 July 2001 77-LOEP Page 1
CHAPTER 77 - ENGINE INDICATING TABLE OF CONTENTS Subject ENGINE INDICATING Chapter/Section Page 77-00 General 1 Troubleshooting 2 POWER 77-10 Description 1 Maintenance Practices 1 Tachometer Removal - Tachometer Installation - Tachometer Map/Fuel Flow Gage Removal - MAP/Fuel Flow Gage Installation - MAP/Fuel Flow Gage Manifold Pressure Sensor Removal - Manifold Pressure Sensor Installation - Manifold Pressure Sensor TEMPERATURE 1 1 1 1 1 1 2 2 2 77-20 Description 1 Maintenance Practices 1
ENGINE INDICATING 1. GENERAL This chapter describes those components which indicate engine operation. The engine indicating components include the tachometer, manifold pressure, and the EGT/CHT sensors and gages.
2. TROUBLESHOOTING Trouble No RPM indication. Page 2 77-00 Probable Cause Tachometer circuit breaker open. Remedy Check circuit breaker.
POWER 1. DESCRIPTION This section describes that portion of the engine indicating system which indicates power. Included are the Tachometer, Manifold Pressure Gage (MAP), and MAP Sensor. A 2¼” Tachometer is mounted on the right instrument panel adjacent to the other engine instruments. The tachometer pointer sweeps a scale marked from 0 to 3500 RPM in 100 RPM increments. The electrically operated tachometer receives a speed signal from a the RH magneto.
C. Manifold Pressure Sensor (See Figure 77-101) CAUTION: (1) (2) Page 2 Protect openings exposed as a result of removing sensor against entry of foreign material by installing covers or sealing with tape. Removal - Manifold Pressure Sensor (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull ENGINE INSTRUMENT circuit breaker. (c) Remove engine cowling. (Refer to 71-10) (d) Disconnect sensor electrical leads.
Figure 77-101 MAP Sensor, MAP/Fuel Flow Gage, and Tachometer Installation 13773-001 30 Nov 2000 77-10 Page 3
TEMPERATURE 1. DESCRIPTION This section describes that portion of the engine indicating system which indicates temperature. Included is the EGT/CHT gage and sensors. A 2¼” combination Exhaust Gas Temperature (EGT) and Cylinder Head Temperature (CHT) indicator is mounted in the right instrument panel. 28 VDC for instrument operation and lighting is supplied through the 5-amp ENGINE INSTRUMENTS circuit breaker on the Essential Bus.
(e) (f) Install engine cowling. (Refer to 71-10) Reset ENGINE INSTRUMENT circuit breaker. C. CHT Sensor (See Figure 77-201) CAUTION: (1) (2) Page 2 Protect openings exposed as a result of removing sensor against entry of foreign material by installing covers or sealing with tape. Removal - CHT Sensor (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull ENGINE INSTRUMENT circuit breaker. (c) Remove engine cowling. (Refer to 71-10) (d) Disconnect sensor electrical leads.
Figure 77-201 EGT/CHT Sensor and Gage Installation 13773-001 31 July 2001 77-20 Page 3
CHAPTER EXHAUST
CHAPTER 78 - EXHAUST LIST OF EFFECTIVE PAGES Chapter/Section Page Date 78-LOEP 1 30 NOV 2000 78-TOC 1 30 NOV 2000 78-00 1 30 NOV 2000 78-00 2 30 NOV 2000 78-10 1 30 NOV 2000 78-10 2 30 NOV 2000 78-20 1 30 NOV 2000 78-20 2 30 NOV 2000 78-20 3 30 NOV 2000 13773-001 30 Nov 2000 78-LOEP Page 1
CHAPTER 78 - EXHAUST TABLE OF CONTENTS Subject EXHAUST Chapter/Section Page 78-00 General 1 Troubleshooting 2 COLLECTOR 78-10 Description 1 Maintenance Practices 1 Tail Pipe Removal - Tail Pipe Installation - Tail Pipe Exhaust Headers Removal - Exhaust Headers Installation - Exhaust Header Assembly NOISE SUPPRESSOR 1 1 1 1 1 2 78-20 Description 1 Maintenance Practices 1 Exhaust Muffler/Heat Exchanger Removal - Exhaust Muffler/Heat Exchanger Disassembly - Exhaust Muffler/Heat Exchanger As
EXHAUST 1. GENERAL This chapter describes those units and components which direct the engine exhaust gases overboard. The engine exhaust system consists of exhaust headers, Y-pipe, midpipe, muffler, heat exchanger, tailpipe, and associated slip joints and fasteners. The exhaust system carries engine exhaust gasses directly from the engine exhaust ports to outside the cowling on the underside of the fuselage.
2. TROUBLESHOOTING Trouble Excessive Engine Noise. Exhaust Gas In Cabin. Probable Cause Defective muffler. Replace or repair muffler. (Refer to 78-10) Crack in exhaust system. Inspect for leaks or cracks. Repair of replace as required. (Refer to 78-10) Defective heat exchanger Weld or replace heat exchanger. (Refer to 78-20) Traces Of Exhaust Gas On Cylin- Defective gasket on cylinder. der. Bent flange. Crack on exhaust header. Page 2 78-00 Remedy Replace gasket.
COLLECTOR 1. DESCRIPTION This section describes the portion of the exhaust system which collects the exhaust gases from the cylinder and conducts them overboard. Included are the exhaust gas temperature probe, the exhaust header assembly, and the tailpipe. Each of the six headers are connected to the engine by brass nuts on the engines exhaust studs. Gaskets seal the header to each cylinder.
(f) (g) Remove EGT probe from #4 cylinder header. (Refer to 77-20) Remove brass nuts attaching exhaust headers to engine cylinders. Note: (2) Individual headers can be removed from the Y-pipe weldment at the slip joint. (h) Remove exhaust headers from airplane. (i) Remove old gaskets from cylinders. Installation - Exhaust Header Assembly (a) Acquire necessary tools, equipment, and supplies. Description Exhaust Header Gasket (b) (c) (d) (e) (f) (g) (h) (i) (j) Page 2 P/N or Spec.
NOISE SUPPRESSOR 1. DESCRIPTION Noise suppression is accomplished through use of an exhaust muffler connected to the exhaust header assembly. The muffler incorporates a heat exchanger to supply warm air to the cabin. Heat sinks are welded to the exterior of the muffler to improve efficiency. A shroud with accommodations for ducts surrounds the muffler.
(5) Inspection/Check - Exhaust Muffler/Heat Exchanger The exhaust muffler/heat exchanger must be inspected for secure mounting, leakage, and general condition at each 100 hour inspection. Inspect the heater muffler visually and the heat exchanger by pressure check to determine possible leakage which could allow carbon monoxide to enter the heating system. (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) (h) (i) (j) (k) (l) (m) Page 2 P/N or Spec.
Figure 78-201 Exhaust System Installation 13773-001 30 Nov 2000 78-20 Page 3
CHAPTER OIL
CHAPTER 79 - OIL LIST OF EFFECTIVE PAGES Chapter/Section Page Date 79-LOEP 1 30 NOV 2000 79-TOC 1 30 NOV 2000 79-00 1 30 NOV 2000 79-00 2 30 NOV 2000 79-20 1 30 NOV 2000 79-20 2 30 NOV 2000 79-30 1 30 NOV 2000 79-30 2 30 NOV 2000 79-30 3 30 NOV 2000 13773-001 30 Nov 2000 79-LOEP Page 1
CHAPTER 79 - OIL TABLE OF CONTENTS Subject OIL Chapter/Section Page 79-00 General 1 Troubleshooting 2 DISTRIBUTION 79-20 Description 1 Maintenance Practices 1 Oil Filter Removal - Oil Filter Installation - Oil Filter Oil Cooler Removal - Oil Cooler Installation - Oil Cooler INDICATING 1 1 1 1 1 2 79-30 Description 1 Maintenance Practices 1 Oil Filler Cap/Dipstick Oil Pressure/Temperature Gage Removal - Oil Pressure/Temperature Gage Installation - Oil Pressure/Temperature Indicator Oil Pr
OIL 1. GENERAL This chapter covers those units and components external to the engine concerned with storing and delivering lubricating oil to and from the engine. These items include the oil filter, oil cooler, oil filler cap/dipstick, oil pressure sensor/temperature indicator, oil pressure sensor, and oil temperature sensor.
2. TROUBLESHOOTING Trouble High Oil Temperature Indication Low Oil Pressure Indication Probable Cause Remedy Thermostat damaged or held open Remove, clean valve and seat. If by solid matter. still inoperative, replace. Oil viscosity too high. Drain and refill with correct seasonal oil grade. (Refer to 12-20) Prolonged ground operation. Limit ground operation to a minimum. Malfunctioning gage or bulb unit. Check wiring. Check bulb unit. Check gage. Replace malfunctioning parts.
DISTRIBUTION 1. DESCRIPTION This section describes that portion of the oil system which is used to conduct oil from and to the engine. These items include the oil filter and oil cooler. Refer to 12-20 for approved engine oil specifications and servicing procedures. (Refer to 12-20) 2. MAINTENANCE PRACTICES A. Oil Filter (1) Removal - Oil Filter (a) Acquire necessary tools, equipment, and supplies. Description Strap Wrench P/N or Spec.
(2) Installation - Oil Cooler (a) Acquire necessary tools, equipment, and supplies. Description (b) (c) (d) (e) (f) (g) Page 2 P/N or Spec. Supplier Purpose Oil Cooler Gasket 649989 TCM Seal Washer Gasket 649961 TCM Seal Slide washer gasket and oil cooler gaskets onto crankcase studs. Position oil cooler on engine mount and install plain washer, lock washers and bolts. Torque bolts to 23 - 27 foot-pounds (31 - 37 N.m.
INDICATING 1. DESCRIPTION This section describes that portion of the oil system which is used to indicate the quantity, temperature, and pressure of the oil. Components included are the oil filler cap/dipstick, oil pressure/temperature gage, oil pressure sensor, and oil temperature sensor. A 2¼” combination Oil Temperature and Oil Pressure indicator is mounted on the right instrument panel immediately below the EGT/CHT indicator. The instrument is internally lighted.
(2) Installation - Oil Pressure Sensor (a) Install sensor to engine fitting. (b) Connect electrical connector to sensor. (c) Install engine cowling. (Refer to 71-10) (d) Reset ENGINE INSTRUMENTS circuit breaker. (e) Perform Oil System Leak Inspection/Check. (Refer to 12-20) D. Oil Temperature Sensor (See Figure 79-301) CAUTION: (1) (2) Protect openings exposed as a result of removing sensor against entry of foreign material by installing covers or sealing with tape.
Figure 79-301 Oil Pressure Sensor and Oil Temperature Sensor Installation 13773-001 30 Nov 2000 79-30 Page 3
CHAPTER STARTING
CHAPTER 80 - STARTING LIST OF EFFECTIVE PAGES Chapter/Section Page Date 80-LOEP 1 30 NOV 2000 80-TOC 1 30 NOV 2000 80-00 1 30 NOV 2000 80-00 2 30 NOV 2000 80-10 1 30 NOV 2000 80-10 2 30 NOV 2000 13773-001 30 Nov 2000 80-LOEP Page 1
CHAPTER 80 - STARTING TABLE OF CONTENTS Subject STARTING Chapter/Section Page 80-00 General 1 Troubleshooting 2 CRANKING 80-10 Description 1 Maintenance Practices 1 Starter Removal - Starter Installation - Starter 13773-001 30 Nov 2000 1 1 1 80-TOC Page 1
STARTING 1. GENERAL This chapter describes the components used for starting the airplane engine. This includes the starter. For additional information on starter system components, refer to the Teledyne Continental Motors Model IO550 Overhaul Manual indexed in the List or Publications in the front of this manual. The starting system employs an electric starter motor mounted on a right angled starter-to-engine adapter. The right angle drive adapter serves to shorten the engine’s overall length.
2. TROUBLESHOOTING Trouble Starter will not operate. Probable Cause Remedy Defective master switch or circuit. Check continuity of master switch or circuit. Install new switch or wires. Defective starter switch, contactor, Check continuity of switch, contacor switch circuit. tor and circuit. Install new switch or wires. Defective starter motor power cable. Inspect cable. Install new cable. Starter motor runs, but does not turn crankshaft. Damaged worm gear. Remove starter and inspect worm gear.
CRANKING 1. DESCRIPTION This section describes that portion of the system used to perform the cranking portion of the starting operation. 2. MAINTENANCE PRACTICES A. Starter (See Figure 80-101) (1) (2) Removal - Starter (a) Ensure BAT 1, BAT 2, and AVIONICS master switches are in off position. (b) Pull STARTER RELAY circuit breaker. (c) Remove engine cowling. (Refer to 71-10) (d) Disconnect positive battery cable at battery. (e) Disconnect electrical cable at starter motor.
Figure 80-101 Starter Installation Page 2 80-10 13773-001 30 Nov 2000
CHAPTER CHARTS
CHAPTER 91 - CHARTS LIST OF EFFECTIVE PAGES Chapter/Section Page Date 91-LOEP 1 31 JULY 2001 91-TOC 1 31 JULY 2001 91-00 1 31 JULY 2001 91-10 1 31 JULY 2001 91-10 2 31 JULY 2001 91-10 3 31 JULY 2001 91-10 4 31 JULY 2001 91-10 5 31 JULY 2001 91-20 1 31 JULY 2001 91-20 2 31 JULY 2001 91-20 3 31 JULY 2001 91-20 4 31 JULY 2001 91-20 5 31 JULY 2001 91-30 1 31 JULY 2001 91-30 2 31 JULY 2001 91-30 3 31 JULY 2001 13773-001 31 July 2001 91-LOEP Page 1
CHAPTER 91 - CHARTS TABLE OF CONTENTS Subject CHARTS Chapter/Section Page 91-00 General SYSTEM LOAD CHARTS AND BUS SCHEMATICS 1 91-10 General REFERENCE TABLES 1 91-20 General 1 Measuring 1 Linear Liquid Capacity Dry Capacity Capacity approximate WeighT 1 2 2 2 3 Liquids Materials Miscellaneous Tables 3 3 3 Length Volume Displacement Pressure Speed Torque Temperature MANUFACTURES AND SUPPLIERS 3 4 4 4 5 5 5 91-30 General 1 Manufactures and Suppliers 1 13773-001 31 July 2001 91-TOC Pag
CHARTS 1. GENERAL This chapter includes system load charts, bus schematics, conversion charts, measurements, and supplier addresses.
SYSTEM LOAD CHARTS AND BUS SCHEMATICS 1. GENERAL The airplane is equipped with a two alternator system, with each alternator operating continuously. The forward (ALT 1) alternator is a rated at 58 amps. The aft (ALT 2) alternator 2, is rated at 20 amperes. The total system load of the airplane is supported by the two alternator configuration. The battery is charged in flight. The total continuous connected load is held to less than 80% of the total rated generator output capacity.
Circuit Identification Avionics Essential Avionics Non-Essential Main Bus 1 Non-Essential Bus Protector Value (Amps) Electrical Load Current Max Drain at Protector Duty Cycle 28 Vdc (Amps) (Amps) Avionics Essential Relay Coil 15 20 Cont. 0.08 COM 1 7.5 7.5 Cont. (Rx) Inter. (Tx) 0.01 1.74 GPS 1 5 7.5 Cont. 1.12 Avionics Non-Essential Relay Coil 15 20 Cont. 0.08 GPS 2 5 7.5 Cont. 1.12 Encoder Transponder 2 7.5 Cont. Cont. 0.48 0.35 COM 2 7.5 7.5 Cont. (Rx) Inter.
Circuit Identification Protector Value (Amps) Electrical Load Current Max Drain at Protector Duty Cycle 28 Vdc (Amps) (Amps) Starter Relay 2 5 Inter. 0.1 Flaps 10 15 Cont. Inter. 0.07 6.5 Right Strobe Light P.S. Left Strobe Light P.S. 5 10 Cont. 2.1 2.1 Right Nav Light Left Nav Light 5 10 Cont. 1.99 1.99 Convenience Outlet 3 5 Cont. 3.0 Stall Warning 2 5 Inter. 0.001 Turn Coordinator #1 2 5 Cont. 0.46 Attitude # 1 3 5 Cont. 0.65 HSI #1 5 5 Cont. 3.
0A Main Distribution Bus Essential Distribution Bus 50A 9.72 A Non-Essential Bus 25 A 25 A 3.25 A 11.2 A 9.72 A Main Bus 2 25 A 8.28 A 25 A 21.40 A 25 A Main Bus 1 Essential 1 Bus Essential 2 Bus 2.41 A 8.28 A 1.0 A 21.40 A 15 A 8.79 A 2.25 A 15 A Avionics NonEssential Bus Avionics Essential Bus 8.79 A 2.25 A Figure 91-102 depicts the system loading during normal system operation with alternator 1 and alternator 2 generating at nominal values.
11.53 A Main Distribution Bus Essential Distribution Bus 50A 9.72 A Non-Essential Bus 25 A 25 A 3.25 A 11.2 A 9.72 A Main Bus 2 25 A 8.28 A 25 A 21.40 A 25 A Main Bus 1 Essential 1 Bus Essential 2 Bus 2.41 A 8.28 A 1.0 A 21.40 A 15 A 8.79 A 2.25 A 15 A Avionics NonEssential Bus Avionics Essential Bus 8.79 A 2.25 A Figure 91-103 depicts the system loading during operation with only alternator 1 generating at nominal values, such as low RPM operation, or a failure of alternator 2.
REFERENCE TABLES 1. GENERAL This chapter includes information on conversion factors and measurements. 2. MEASURING Note: To determine the opposite conversion from that given, divide by the conversion number instead of multiplying. A. Linear Measurement Equivalent to: 1 Millimeter - 0.03937 Inch 10 Millimeters 1 Centimeter 0.3937 Inch 10 Centimeters 1 Decimeter 3.937 Inches 10 Decimeters 1 Meter 39.37 Inches 10 Meters 1 Decameter 32.8 Feet 10 Decameters 1 Hectometer 328.
B. Liquid Capacity Measurement Equivalent to: 1 Minim 0.004 Cubic inch 0.062 Milliliter 60 Minims 1 Fluid dram 3.697 Milliliters 8 Fluid drams 1 Fluid ounce 0.030 Liter 4 Fluid ounces 1 Gill 0.118 Liter 8 Fluid ounces 1 Cup 0.236 Liter 2 Cups 1 Pint 0.473 Liter 2 Pints 1 Quart 0.946 Liter 4 Quarts 1 Gallon 3.785 Liters 1 Teaspoon 1 1/3 Fluid drams - 1 Tablespoon 3 Teaspoons - C. Dry Capacity Measurement Equivalent to: 1 Pint 33.60 Cubic Inches 0.
3. APPROXIMATE WEIGHT A. Liquids Type Pound per Gallon: Alcohol 6.576 Gasoline 6.042 Kerosene 6.668 Lubricating Oil 7.584 Water 8.335 B. Materials Type Pound per Gallon: Aluminum (cast) 165 Bronze (phosphor) 554 Brass (cast-rolled) 534 Copper (cast-rolled) 556 Glass (plate) 184 4. MISCELLANEOUS TABLES A. Length Multiply by To Obtain: Inches 2.54 Centimeters Feet 0.305 Meters Miles 1.609 Kilometers Kilometers 0.621 Miles Square inches 6.
B. Volume Multiply by To Obtain: Fluid ounces 29.57 Cubic centimeters Quarts 0.946 Liters Diameter circle 3.1416 Circumference of circle Diameter circle 0.8862 Side of equal square Diameter circle squared 0.7854 Area of circle Diameter sphere squared 3.1416 Area of sphere Diameter sphere cubed 0.5236 Volume of sphere U.S. Gallons 0.8327 Imperial gallons (British) U.S. Gallons 0.1337 Cubic feet C. Displacement Multiply by To Obtain: Cubic inches 16.
E. Speed Multiply F. by To Obtain: Knots 1.1516 Miles per hour M.p.h. 1.61 Km/h Km/h 0.62137 M.p.h. Torque Multiply by To Obtain: N-m 0.102 Kg-m N-m 0.7376 Ft.-lb N-m 8.851 In-lb Kg-m 9.807 N-m Kg-m 7.233 Ft.-lb Kg-m 86.8 In-lb Ft.-lb 12.0 In-lb Ft.-lb 0.1383 M/Kgs. Ft.-lb 0.13826 Kg-m Ft.-lb 13.8 Cm. - Kgs. In-lb 0.113 N-m G.
MANUFACTURES AND SUPPLIERS 1. GENERAL This chapter includes information on manufactures and suppliers: 2. MANUFACTURES AND SUPPLIERS Manufacturer/Supplier Address ACK Technologies 440 W. Julian Street San Jose, CA 95110 AIRTECH International Inc. 2542 East Del Amo Blvd. P.O. Box 6207 Carson, CA 90749-6207 AMP Inc. P.O. Box 91869 Chicago,IL 60693-1869 ARNAV Systems P.O. Box 73730 Pullyallup, WA 98373 Automotive Refinish Technologies Circle Pines, MN Brackett Aircraft Company Inc.
Manufacturer/Supplier Page 2 Address General Electric Waterford, NY General Aircraft Corporation Hanscom Field Bedford, MA 01730 Garmin International 1200 E. 151 First St. Olathe, KS 66062 Goal P.O. Box 678TR Niantic, CT 06357 Hartzell Propellers Inc. P.O. Box 630313 Cincinnati, OH 45263-0313 Hemisphere 3415 Eastern Ave. Southeast Grand Rapids, MI 49508 Hexcel Knytex Con LLC Dept. 77-3053 Chicago, IL Integral Products Bonder Avenue Torrance, CA 90501 John Fluke Mfg. Company, Inc.
Manufacturer/Supplier Address Semco Application Systems (PRC-DeSoto Intl Inc.) Glendale, CA Quaker State Corporation 255-T Elm St. Oil City, PA 16301 S-TEC Corporation One S-TEC Way Municipal Airport Mineral Wells, TX 76067-92 Sanford Inc Company 2740-T Washington Blvd. Bellwood, IL 60104 Shell Oil Company One Shell Plaza Houston, TX 77002 Sinclair Oil Company 683-T Academ Dr. Northbrook, IL 60062 Snap-on Tools Intl. Ltd. 2801 80th St.
CHAPTER SPECIAL EQUIP.
CHAPTER 95 - SPECIAL PURPOSE EQUIPMENT (CAPS) LIST OF EFFECTIVE PAGES Chapter/Section Page Date 95-LOEP 1 30 NOV 2000 95-TOC 1 30 NOV 2000 95-00 1 30 NOV 2000 95-00 2 30 NOV 2000 95-00 3 30 NOV 2000 13773-001 30 Nov 2000 95-LOEP Page 1
CHAPTER 95 - SPECIAL PURPOSE EQUIPMENT (CAPS) TABLE OF CONTENTS Subject SPECIAL PURPOSE EQUIPMENT Chapter/Section Page 95-00 General 1 Description 1 Maintenance Practices 2 13773-001 30 Nov 2000 95-TOC Page 1
95-00SPECIAL PURPOSE EQUIPMENT SPECIAL PURPOSE EQUIPMENT 1. GENERAL The airplane is equipped with a Cirrus Airplane Parachute System (CAPS) designed to bring the aircraft and its occupants to the ground in the event of a life-threatening emergency. CAPS consists of a parachute, a solid-propellant rocket to deploy the parachute, a rocket activation handle, and a harness imbedded within the fuselage structure.
3. MAINTENANCE PRACTICES Refer to Cirrus Airframe Parachute System Maintenance Manual w/ Illustrated Parts List (P/N 12128-001) for CAPS Maintenance Practices. WARNING: CAPS must be serviced and maintained by Cirrus Design trained and authorized parachute system technicians only. Airframe and Powerplant license is not sufficient credentials for performing maintenance on CAPS.
Figure 95-001 CAPS Deployment 13773-001 30 Nov 2000 95-00 Page 3
