•  The total time in service and the current status of  life-limited parts of the airframe, each engine, each  propeller, and each rotor. •  The time since last overhaul of all items installed on  the aircraft which are required to be overhauled on a  specified time basis. •  The current inspection status of the aircraft, including  the time since last inspection required by the program  under which the aircraft and its appliances are  maintained. •  The current status of applicable ADs including for  each, the method of compliance, the AD number, and  revision date. If the AD involves recurring action, the  time and date when the next action is required.  •  Copies of the forms prescribed by 14 CFR part 43,  section 43.9, for each major alteration to the airframe  and currently installed components. The owner/operator is required to retain the records of  inspection until the work is repeated, or for 1 year after the  work is performed. Most of the other records that include  total times and current status of life-limited parts, overhaul  times, and AD status must be retained and transferred with  the aircraft when it is sold. 14 CFR part 43, part 43.15, requires that each person  performing a 100-hour or annual inspection shall use a  checklist while performing the inspection. The checklist  may be one developed by the person, one provided by the  manufacturer of the equipment being inspected, or one  obtained from another source. The checklist must include the  scope and detail of the items contained in part 43, Appendix D. The inspection checklist provided by the manufacturer is  the preferred one to use. The manufacturer separates the  areas to inspect such as engine, cabin, wing, empennage  and landing gear. They typically list Service Bulletins and  Service Letters for specific areas of the aircraft and the  appliances that are installed. Initial run-up provides an assessment to the condition of the  engine prior to performing the inspection. The run-up should  include full power and idle rpm, magneto operation, including  positive switch grounding, fuel mixture check, oil and fuel  pressure, and cylinder head and oil temperatures. After the  engine run, check it for fuel, oil, and hydraulic leaks.  Following the checklist, the entire aircraft shall be opened  by removing all necessary inspection plates, access doors,  fairings, and cowling. The entire aircraft must then be cleaned  to uncover hidden cracks or defects that may have been  missed because of the dirt.  Following in order and using the checklist visually inspect each  item, or perform the checks or tests necessary to verify the  condition of the component or system. Record discrepancies  when they are found. The entire aircraft should be inspected  and a list of discrepancies be presented to the owner.  A typical inspection following a checklist, on a small single- engine airplane may include in part, as applicable: •  The fuselage for damage, corrosion, and attachment  of fittings, antennas, and lights; for “smoking rivets”  especially in the landing gear area indicating the  possibility of structural movement or hidden failure. •  The flight deck and cabin area for loose equipment  that could foul the controls; seats and seat belts for  defects; windows and windshields for deterioration;  instruments for condition, markings, and operation;  flight and engine controls for proper operation. •  The engine and attached components for visual  evidence of leaks; studs and nuts for improper torque  and obvious defects; engine mount and vibration  dampeners for cracks, deterioration, and looseness;  engine controls for defects, operation, and safetying;  the internal engine for cylinder compression; spark  plugs for operation; oil screens and filters for metal  particles or foreign matter; exhaust stacks and mufflers  for leaks, cracks, and missing hardware; cooling  baffles for deterioration, damage, and missing seals;  and engine cowling for cracks and defects. •  The landing gear group for condition and attachment;  shock absorbing devices for leaks and fluid levels;  retracting and locking mechanism for defects, damage,  and operation; hydraulic lines for leakage; electrical  system for chafing and switches for operation; wheels  and bearings for condition; tires for wear and cuts; and  brakes for condition and adjustment. •  The wing and center section assembly for condition,  skin deterioration, distortion, structural failure, and  attachment. •  The empennage assembly for condition, distortion,  skin deterioration, evidence of failure (smoking  rivets), secure attachment, and component operation  and installation. •  The propeller group and system components for torque  and proper safetying; the propeller for nicks, cracks,  and oil leaks; the anti-icing devices for defects and  operation; and the control mechanism for operation,  mounting, and restricted movement. •  The radios and electronic equipment for improper  installation and mounting; wiring and conduits for  improper routing, insecure mounting, and obvious  2-64