3.
Secure second clamp to ignition assembly using remaining screws.
4.
Attach wire assemblies to rear of gauge.
5.
Raise nose cone into position and secure.
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Figure 21-23. Heater Hourmeter Installation
21-40-00
Page 21-54
Revised: February 28, 2002
1J4
CHAPTER
22
AUTOFLIGHT
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CHAPTER 22 - AUTOFLIGHT
TABLE OF CONTENTS / EFFECTIVITY
CHAPTER/ SECTION SUBJECT GRID NO. EFFECTIVITY
22-00-00 GENERAL 1J9 1R0202
A.F.C.S. EQUIPMENT CONTACTS 1J9 1R0202
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1J8
GENERAL.
— WARNING —
NEVER USE A SUBSTITUTE TRIM SYSTEM COMPONENT PART, FOR AN ORIGINAL DESIGN PART, BECAUSE THE FAIL-SAFE CHARACTERISTICS OF THE SYSTEM MIGHT BE COMPROMISED. REFER TO THE P.O.H. FOR GROUND CHECK OF ELECTRIC PITCH TRIM SYSTEM BEFORE THE FIRST FLIGHT AFTER SERVICING. A TRIM SYSTEM RUNNING IN THE WRONG DIRECTION IS THE SAME AS A RUN-AWAY. EXCESSIVE PILOT YOKE FORCE IS POSSIBLE IN ONLY 3-4 SECONDS UNDER SUCH CONDITIONS.
Due to the wide variety of A.F.C.S. (Automated Flight Control System) options, it is mandatory to follow the service literature published by the individual manufacturer of the A.F.C.S. equipment installed in any particular airplane. This includes mechanical service such as; adjusting bridle cable tension, servo removal and installation, servo clutch adjustments, etc.
A.F.C.S. EQUIPMENT CONTACTS.
Refer to the following Autopilot/Flight Director manufacturer(s) to obtain service directions, parts support and service literature.
Honeywell One Technology Center 23500 W. 105th St., M/D #45 Olathe, Kansas 66061-1950 http://www.bendixking.com/
S-TEC Corporation One S-TEC Way Mineral Wells, Texas 76067-9236 PH - (940) 325-9406 http://www.s-tec.com
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1J10
CHAPTER
24
ELECTRICAL POWER
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CHAPTER 24 - ELECTRICAL POWER
TABLE OF CONTENTS / EFFECTIVITY
CHAPTER/ SECTION SUBJECT GRID NO. EFFECTIVITY
24-00-00 GENERAL 1J15 1R0202
Description and Operation 1J15
Troubleshooting Alternator Battery 1J15 1J16 1J21
24-30-00 D.C. GENERATION 1J23
Alternator System Precautions Checking Alternator Belt Tension 1J23 1J24 1J24
Battery Service Procedures Servicing Removal Installation Testing Charging Battery Box Description Removal Installation Corrosion Prevention 1K1 1K1 1K3 1K3 1K3 1K4 1K4 1K4 1K4 1K4 1K4
Voltage Regulators and Overvoltage Relays Lamar Model No. B-00392-1 Voltage Regulator Operation Adjusting 1K5 1K5 1K5 1K6 1R0202
Ammeter 1K6
24-40-00 EXTERNAL POWER 1K7
External Power Receptacle 1K7
—Note —
Refer to Chapter 91, Charts and Wiring Diagrams for electrical schematics.
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1J14
GENERAL.
— WARNING —
FAILURE TO CONSULT APPLICABLE VENDOR PUBLICATION(S), WHEN SERVICING OR INSPECTING VENDOR EQUIPMENT INSTALLED IN PIPER AIRCRAFT, MAY RENDER THE AIRCRAFT UNAIRWORTHY. (SEE INTRODUCTION - SUPPLEMENTARY PUBLICATIONS.)
This chapter deals with the complete electrical system and provides service procedures and a trouble-shooting guide.
Electrical generation, distribution and storage are covered, as well as the optional external power facility.
DESCRIPTION AND OPERATION.
Electrical energy is generated by two engine-driven 70 ampere alternators and stored in a 12 volt, 35 amp-hour battery. The system is D.C. and has a negative ground.
Each alternator is protected by an alternator control unit which incorporates a voltage regulator and an overvoltage relay. This relay protects the electrical and avionic equipment from regulator malfunction. The overvoltage relay will take its respective alternator offline if the alternator's output exceeds 17 volts. The ALT light on the annunciator panel will illuminate simultaneously. The individual circuits are protected from overloads and shorts by resettable circuit breakers located on the right side of the instrument panel.
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