REMOVAL OF ABSOLUTE PRESSURE RELIEF VALVE.
1. Remove the four screws and washers which secure the relief valve to the duct.
2. Lift the relief valve assembly from the duct.
3. Remove the O-ring from the seating surface of the relief valve mounting flange on the duct.
INSTALLATION OF ABSOLUTE PRESSURE RELIEF VALVE.
1. Install a new O-ring and position the relief valve on the mounting flange of the duct.
2. Install the washers, screws and safety wire.
EXHAUST BYPASS VALVE.
The exhaust bypass valve is mounted on the crossover tube between the exhaust turbine inlet duct and the
tailpipe. This ground adjustable unit is set to a predetermined value, thus bypassing a fixed amount of exhaust
gas away from the turbocharger turbine limiting the turbocharger speed and the degree of compression of the air
leaving the compressor.
ADJUSTMENT OF EXHAUST BYPASS VALVE.
— Note —
Before making any adjustments to the exhaust bypass valve, perform a complete
inspection of the power plant system.
The exhaust bypass valve is preset at the factory so as to reach critical altitude at 12,000 feet density altitude.
full throttle and 36.5 inches hg. manifold pressure. Adjustment should be accomplished only if the critical
altitude cannot be reached and the powerplant system has been thoroughly checked.
1. After removing the upper cowling to gain access to the exhaust bypass valve, remove the safety wire from
the valve.
2. Adjust the exhaust bypass valve initially so that there is 1/4 inch between the bolt head and the top of the
jam nut.
3. If critical altitude is not obtainable at the initial setting, further adjustments should be made as follows:
a. To increase critical altitude turn bolt clockwise. To decrease turn bolt counterclockwise.
b. For each flat turned of the adjusting bolt head the critical altitude will change 200 feet.
4. Upon completion of adjustments, safety wire the adjusting bolt and reinstall the cowling.
— END —
PA - 4 4 - 1 8 0 / 1 8 0 T
AIRPLANE MAINTENANCE MANUAL
8 1 - 2 7 - 0 0
Page 81-12
Revised: May 15, 1989
3J14
PIPER AIRCRAFT
Summary of Contents for SEMINOLE PA-44-180
Page 38: ...CHAPTER DIMENSIONS AND AREAS 1B14...
Page 49: ...CHAPTER LIFTING AND SHORING 1C1...
Page 53: ...CHAPTER LEVELING AND WEIGHING 1C5...
Page 58: ...CHAPTER TOWING AND TAXIING 1C10...
Page 62: ...CHAPTER PARKING AND MOORING 1C14...
Page 65: ...CHAPTER REQUIRED PLACARDS 1C17...
Page 70: ...CHAPTER SERVICING 1C22...
Page 98: ...CHAPTER STANDARD PRACTICES AIRFRAME 1E2...
Page 108: ...CHAPTER ENVIRONMENTAL SYSTEM 1E12...
Page 189: ...CHAPTER AUTOFLIGHT 1H21...
Page 192: ...CHAPTER COMMUNICATIONS 1H24...
Page 202: ...CHAPTER ELECTRICAL POWER 1I10...
Page 228: ...CHAPTER EQUIPMENT FURNISHINGS 1J12...
Page 233: ...CHAPTER FIRE PROTECTION 1J17...
Page 238: ...CHAPTER FLIGHT CONTROLS 1J24...
Page 304: ...2A18 CHAPTER FUEL...
Page 325: ...2B17 CHAPTER HYDRAULIC POWER...
Page 357: ...2D1 CHAPTER ICE AND RAIN PROTECTION...
Page 414: ...CHAPTER LANDING GEAR 2F13...
Page 479: ...2I6 CHAPTER LIGHTS...
Page 488: ...2I16 CHAPTER NAVIGATION AND PITOT STATIC...
Page 503: ...2J7 CHAPTER OXYGEN...
Page 524: ...2K6 CHAPTER VACUUM...
Page 535: ...2K19 CHAPTER ELECTRICAL ELECTRONIC PANELS AND MULTIPURPOSE PARTS...
Page 546: ...INTENTIONALLY LEFT BLANK PA 44 180 180T AIRPLANE MAINTENANCE MANUAL 2L6 PIPER AIRCRAFT...
Page 547: ...2L7 CHAPTER STRUCTURES...
Page 582: ...CHAPTER DOORS 3A18...
Page 593: ...CHAPTER STABILIZERS 3B8...
Page 604: ...CHAPTER WINDOWS 3B22...
Page 611: ...CHAPTER WINGS 3C10...
Page 624: ...CHAPTER PROPELLER 3D1...
Page 643: ...CHAPTER POWER PLANT 3D21...
Page 667: ...CHAPTER ENGINE FUEL SYSTEM 3F1...
Page 681: ...CHAPTER IGNITION 3F16...
Page 712: ...CHAPTER ENGINE INDICATING 3H1...
Page 730: ...CHAPTER EXHAUST 3H19...
Page 734: ...CHAPTER OIL 3I1...
Page 743: ...CHAPTER STARTING 3I11...
Page 755: ...CHAPTER TURBINES 3J1...