PIPER CHEROKEE SERVICE MANUAL PA-28-140/150/160/180/235/200 PART 753-586
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1999-2010 KTM 125 144 150 200 SX, SXS, MXC, EGS, EXC, EXC SIX DAYS, XC, XC-W Workshop Service Repair Manual Download 1999 2000 2001 2002 2003 2004 2005 2006 2007 2008 2009 2010
200 SX, SXS, MXC, EGS, EXC, EXC SIX DAYS, XC, XC-W Workshop Service Repair Manual Download 1999 2000 2001 2002 2003 2004 2005 2006 2007
* PAGES: 916
When servicing or inspecting vendor equipment installed in Piper
aircraft, it is the user's responsibility to refer to the applicable vendor
1-1. GENERAL. This manual contains service and maintenance instructions for PA-28-140.-150. -160. -180. -235 and PA-28R-180 200 Cherokees. designed and manufactured asversatile airplanes in the personal and business aviation field. by the Piper Aircraft Corporation . Vero Beach. Florida.
1-2. SCOPE OF MANUAL. Sections II and III comprise the service part of this manual, whereas Sections IV through XIII comprise the maintenance instructions. The service instructions include ground handling, servicing and inspections. The maintenance instructions for each system include troubleshooting, removal and installation of components, and corrective maintenance and testing; each major system of the airplane is covered in a separate section. Only qualified personnel should perform the operations
described in this manual.
The description of the airplane included in this section is limited to general
information. Section II gives leading particulars and principal dimensions, while each major system is described in its appropriate section of the manual. For a more detailed description of the airplane, refer to the Owner's Handbook, or Pilot's Information Manual for the particular airplane.
1-3. DESCRIPTION. The Cherokee PA-28 is a single-engine. low-wing monoplane of all metal construction. The standard PA-28-140 is a two place. with third and fourth family seats available as optional equipment. The PA-28-150. -160. -180. -235 and PA-28R-180 200 are four place airplanes. Paragraphs 1-4 through 1-17 provide descriptions of the major components and systems.
1-4. WING. The laminar flow wing is of all-metal stressed-skin, full cantilever, low-wing design, consisting of two wing panels bolted to a spar box assembly in the fuselage. The wing tips are removable. The ailerons are cable and push rod controlled and are dynamically balanced. The trailing edge wing flaps are manually operated.
1-5. EMPENNAGE. The empennage consists of the fin, rudder, stabilator and stabilator trim tabs. The stabilator is dynamically balanced.