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D2000-9TR9 - Cessna Support

1. Initial 3 000 hours or 15 210 5 years whichever occurs first Repeat 1 000 hours or 5 years whichever occurs first Initial 10 years 16 210 Repeat 10 years Initial 5 years 17 210 Repeat 5 years Initial 12 000 18 510 hours or 20 years 610 whichever occurs first Repeat 2 000 hours or 10 years whichever occurs first Initial 20 years 11 510 Repeat 10 years 610 Initial 12 000 18 510 hours or 20 years 610 whichever occurs first Repeat 2 000 hours or 10 years whichever occurs first Initial 6 000 hours or 19 510 10 years whichever 610 occurs first Repeat 1 000 hours or 5 years whichever occurs first Initial 10 years 13 510 Repeat 5 years 610 Initial 6 000 hours or 19 510 10 years whichever 610 occurs first Repeat 1 000 hours or 5 years whichever occurs first 2A 10 01 Page 6 Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL TASK Inspect horizontal stabilizer and elevator including torque tube spars ribs hinge bolts hinge bearings brackets and attach fittings Refer to Section 2A 14 11 Supplemental Inspection Document 55 10 01 for inspection procedures This interval is for severe corrosion environment Inspect wing root rib Refer to Section 2A 14 18 Supplemental Inspection Document 57 12 01 for inspection procedure Inspect vertical stabilizer rear spar Refer to Section 2A 14 13 Supplemental Inspection
2. c There must be a continuous liquid path between the two metals which acts as the electrolyte This liquid path may be condensation or in some cases only the humidity in the air 2 Elimination of any one of the three conditions will stop the corrosion reaction process 3 Asimple method of minimizing corrosion is adding a layer of pure Aluminum to the surface The pure Aluminum is less susceptible to corrosion and also has a very low electro potential voltage relative to the remainder of the alloyed sheet This process is conducted at the fabricating mill and the product is called Alclad Model 180 185 airplanes had sheet metal parts constructed of Al clad sheet 4 One of the best ways to eliminate one of the conditions is to apply an organic film such as paint grease or plastic to the surface of the metal affected This will prevent electrolyte from connecting the cathode to the anode so current cannot flow and therefore prevent corrosive reaction and was not available for production Model 180 185 airplanes 5 Other means employed to prevent electrochemical corrosion include anodizing and electroplating Anodizing and other passivating treatments produce a tightly adhering chemical film which is much less electrochemically reactive than the base metal Because the electrolyte cannot reach the base metal corrosion is prevented Electroplating deposits a metal layer on the surface of the base material which is either less electrochemic
3. OPERATION All of the inspections included in one operation are grouped together in the 2A 12 XX documents XX equals the operation number ZONE This column locates the components within a specific zone For a breakdown of how the airplane is zoned refer to 2A 30 00 Figure 1 Airplane Zones Inspection Interval Requirements 1 2 3 4 5 Operation iva 2 3 4 5 6 7 Details Every 100 hours of operation or 12 months whichever occurs first Corrosion Prevention and Control Program Inspections Baseline Program items that are to be examined every 12 months Refer to Section 2A 30 00 Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals Corrosion Prevention and Control Program Inspections Baseline Program items that are to be examined every 24 months Refer to Section 2A 30 00 Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals Corrosion Prevention and Control Program Inspections Baseline Program items that are to be examined every 36 months Refer to Section 2A 30 00 Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals Corrosion Prevention and Control Program Inspections Baseline Program items that are to be examined every 48 months Refer to Section 2A 30 00 Corrosion
4. calendar inspection times are per REPEAT flight hour or calendar time specified whichever occurs first Corrosion Prevention and Control Program CPCP remain calendar time based If the INITIAL inspection has been completed and a CPCP is in effect then REPEAT inspections are based entirely on flight hours D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company 2A 14 00 Page 4 Oct 2 1995 1 2 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL SUPPLEMENTAL INSPECTION NUMBER 53 10 01 TITLE Tailcone Reinforcement Inspection EFFECTIVITY Model 180 Serial Numbers 18051994 thru 18053167 Model 185 Serial Numbers 185 1448 thru 18504138 Model A185 Serial Numbers 185 1448 thru 18504138 INSPECTION COMPLIANCE TYPICAL INITIAL 5 000 Hours or 20 Years NOTE REPEAT 2 000 Hours Or 5 Years NOTE SEVERE INITIAL 3 000 Hours Or 10 Years NOTE REPEAT 500 Hours OF 5 Years NOTE NOTE Refer to Note 1 Section 2A 14 00 3 PURPOSE To ensure the structural integrity of the horizontal bulkhead reinforcement 4 INSPECTION INSTRUCTIONS A Remove the vertical and horizontal stabilizers to get access to the aft horizontal attachment area near F S 230 refer to the applicable sections of the service manual for stabilizer removal instructions B Do a visual inspection of the stabilizer hinge bracket Part Numbers 0712042 1 2 or 0712302 1 2 for crack s 1 If grime or debris is
5. 5 Years Years SEVERE 3 SEVERE 3 Years Years 2A 14 19 57 40 01 Strut and Strut Wing TYPICAL TYPICAL 2 000 Attachment Inspec 12 000 Hours Hours or 10 tion or 20 Years Years SEVERE 6 000 SEVERE 1 000 Hours or 10 Hours or 5 Years Years 2A 14 20 57 51 01 Aileron Support 3 000 Hours or 500 Hours or 5 Structure Inspection D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company 10 Years Years INSPEC TION OP ERATION 20 20 22 18 19 11 13 11 13 12 21 18 19 2A 14 00 Page 3 Oct 2 1995 DETAILS FOUND IN SECTION 2A 14 XX 2A 14 21 2A 14 22 2A 14 23 SUPPLEMENTAL INSPECTION NUMBER 57 53 01 71 20 01 53 10 01 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL TITLE Flap Tracks Corro sion Inspection Engine Mount Inspec tion Tailcone Reinforce ment Inspection INSPECTION COMPLIANCE Refer to Note 1 ON aa INITIAL REPEAT ERATION MILD MILD 11 MODERATE MODERATE 10 20 Years Years SEVERE 10 SEVERE 5 Years 13 Years 5 000 Hours or At Engine 10 20 Years Overhaul TYPICAL 5 000 TYPICAL 2 000 26 hours or 20 hours or 5 years years SEVERE 3 000 SEVERE 500 27 hours or 10 hours or 5 years years NOTE 1 Time limits for the INITIAL inspections are set by either flight hours or calendar time whichever occurs first Except for Section 2A 14 22 Supplemental Inspection Document 71 20 01 corresponding
6. inspections are not required Analytical Assessment Flowchart Figure 1 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page7 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A25373 DISCREPANCY REPORT SID NO AIRPLANE LOCATION nn SIN OF AIRPLANE INSPECTION CONDUCTED Date Airplane Total Hours Cycles Component Total Hours Cycles OWNER NAME OWNER PHONE NUMBER OWNER ADDRESS SERVICE HISTORY INSPECTION METHOD LIMITS ACCESS REQUIRED REPAIR DESCRIPTION COMMENTS Enclose all available data including photos sketches etc to Cessna Aircraft Company Attn SID Program Customer Service P O Box 7706 Wichita Kansas USA 67277 FAX 316 517 7271 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page 8 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL LISTING OF SUPPLEMENTAL INSPECTIONS 1 Supplemental Inspection Procedures A Each of the supplemental inspections listed in this section has the instructions to do each Nondestructive Testing procedure needed B Procedure 1 Each 2A 14 XX section has the details of the inspection and if needed a reference to the Nondestructive Testing procedure for that inspection 2 The supplemental inspections that reference a Nondestructive Testing procedure will refer to 2A 13
7. whichever 320 occurs first Repeat 2 000 hours or 5 years whichever occurs first Initial 3 years 21 510 Repeat 3 years 610 Initial 100 hours or 22 340 1 year whichever occurs first Repeat 100 hours or 1 year whichever occurs first Initial 4 000 hoursor 23 721 10 years whichever 722 occurs first Repeat 1 000 hours or 3 years whichever occurs first Initial Every time 24 721 skis are installed or 722 removed Repeat Every time skis are installed or removed Initial 100 hours 25 210 Repeat every 600 510 hours or 12 months 610 whichever occurs first Initial 100 hours 25 210 Repeat every 600 510 hours or 12 months 520 whichever occurs 610 first 620 Initial 100 hours 25 210 Repeat every 600 310 hours or 12 months 320 whichever occurs 330 first Initial 100 hours 25 210 Repeat every 600 310 hours or 12 months 320 whichever occurs 330 first 2A 10 01 Page 7 Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL TASK Rudder 1 Check rudder travel and cable tension 2 Check rudder cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables This interval is for typical usage environment Inspect stabilizer hinge bracket and tailcone reinforcement angle Refer to Section 2A 14 23 Supplemental Inspection Documents 53 10
8. 01 document for the details of the procedure 3 The supplemental inspection numbers in the list below agree with the number for the Nondestructive Testing procedure if applicable Refer to Inspection Requirements Hours to Years Equivalence C Ifan airplane has exceeded the inspection limits given the inspection must be done before June 30 2014 Inspections in subsequent revisions to the SID shall be accomplished in accordance with the requirements of the revised inspection D Service Information Letters Service Bulletins 1 In addition to this service manual the following service information will be required to complete the SID inspections 2A 14 XX document sections Bulletin Title Associated Service Kit SE79 62 185 Engine Mount SK185 22A SE80 85 Vertical Fin Rear Spar Inspection for units 18052385 thru SK180 36 18053147 18502311thru 18504070 SK185 25 SEBO7 5 Pilot and Copilot Secondary Seat Stop Installation SK210 174A SK210 175A SEB87 04 Aileron Hinge Inspection SEB95 02 Vertical Stabilizer Rear Spar Inspection And Reinforcement SK180 43 for units 18052385 thru 18053167 18502311 thru SK185 25 18504138 SEB95 03 Flap Support Inspection and Roller Washer Installation SK180 44 SEB96 07 AN3 5A Bolt Inspection Replacement D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 14 00 Page 1 O Cessna Aircraft Company Oct 2 1995 2 Supplemental Inspections DETAILS FOUND IN SECTION 2A 14 XX 2A 14 01 2A 14 02 2A
9. 01 for inspection procedure This interval is for severe usage environment Inspect stabilizer hinge bracket and tailcone reinforcement angle Refer to Section 2A 14 23 Supplemental Inspection Documents 53 10 01 for inspection procedure D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company INTERVAL Initial 100 hours Repeat every 600 hours or 12 months whichever occurs first Initial 5 000 hours or 20 years whichever occurs first Repeat Every 2 000 hours or 5 years whichever occurs first Initial 3 000 hours or 10 years whichever occurs first Repeat Every 500 hours or 5 years whichever occurs first 2A 10 01 OPERATION ZONE 25 210 310 340 26 310 27 310 Page 8 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL INSPECTION OPERATION 26 Date Registration Number Serial Number Total Time 1 Description A Operation 26 gives Supplemental Inspection Document items that are to be examined after the first 5 000 hours of operation or 20 years whichever occurs first The inspection is to be repeated every 2 000 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished for airplanes operating in a typical usage environment Inspection items are given in the order of the zone in which the inspection is to be completed Frequently tasks give more i
10. 14 03 2A 14 04 2A 14 05 2A 14 06 2A 14 07 2A 14 08 2A 14 09 2A 14 10 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL SUPPLEMENTAL INSPECTION NUMBER 27 20 01 27 30 01 27 42 01 32 13 01 32 13 02 32 13 03 32 13 04 53 11 01 53 30 01 53 47 01 TITLE Rudder Pedal Torque Tube Inspection Stabilizer Trim Pul ley Bracket and Screw Jack Structure Inspection Horizontal Stabilizer Screw Jack Actuator Inspection Main Landing Gear Spring and Attach Fit tings Corrosion In spection Main Landing Gear Spring Axle Attach In spection Main Landing Gear Spring Axle Attach In spection Main Landing Gear Fittings Inspection Carry Thru Structure Corrosion Inspection Fuselage Interior Skin Panels Corrosion In spection Seat Rails amp Seat Rail Structure Corrosion Inspection D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company INSPECTION COMPLIANCE Refer to Note 1 INITIAL REPEAT 10 000 Hours or 3 000 Hours or 5 20 Years Years 1 000 Hours 1 000 Hours 1 000 Hours 1 000 Hours MILD MILD MODERATE MODERATE 10 20 Years Years SEVERE 10 SEVERE 5 Years Years Every time Skis Every time Skis are installed or are installed or removed removed 4 000 Hours or 1 000 Hours or 3 10 Years Years 3 000 Hours or 1 000 Hours or 5 5 Years Years MILD MILD MODERATE MODERATE 10 20 Years Years SEVERE 10 SEVERE
11. 5 Years Years MILD MILD MODERATE MODERATE 10 20 Years Years SEVERE 10 SEVERE 5 Years Years MILD MILD MODERATE MODERATE 10 10 Years Years SEVERE 5 SEVERE 5 Years Years INSPEC TION OP ERATION 7 14 14 11 13 24 23 11 13 11 13 16 17 2A 14 00 Page 2 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL DETAILS FOUND IN SUPPLEMENTAL ed an en SECTION INSPECTION Refer to Note 1 2A 14 XX NUMBER TITLE INITIAL REPEAT 2A 14 11 55 10 01 Horizontal Stabilizer 5 000 Hours or 2 000 Hours or 5 Elevators and Attach 20 Years Years ments Inspection 2A 14 12 55 30 01 Vertical Stabilizer 5 000 Hours or 2 000 Hours or 5 Rudder and Attach 20 Years Years ments Inspection 2A 14 13 55 30 02 Vertical Stabilizer 100 Hours or 1 100 Hours or 1 Rear Spar Inspection Year Year 2A 14 14 57 11 01 Wing Structure In TYPICAL TYPICAL 2 000 spection 12 000 Hours Hours or 10 or 20 Years Years SEVERE 6 000 SEVERE 1 000 Hours or 10 Hours or 5 Years Years 2A 14 15 57 11 02 Wing Structure Corro MILD MILD sion Inspection MODERATE MODERATE 10 20 Years Years SEVERE 10 SEVERE 5 Years Years 2A 14 16 57 11 03 Wing Spar Inspection 4 000 Hours 100 Hours 2A 14 17 57 11 04 Wing Splice Joint at MILD MILD Strut Attach Inspec MODERATE MODERATE 10 tion 20 Years Years SEVERE 10 SEVERE 5 Years Years 2A 14 18 57 12 01 Wing Root Rib Corro MILD MILD sion Inspection MODERATE MODERATE 5
12. Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals Corrosion Prevention and Control Program Inspections Baseline Program items that are to be examined every 60 months Refer to Section 2A 30 00 Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals Supplemental Inspection Document items that are to be examined after the first 10 000 hours of operation or 20 years whichever occurs first The inspection is to be repeated every 3 000 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished Cessna Aircraft Company 2A 10 00 Page 3 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL Operation Details 8 Supplemental Inspection Document items that are to be examined after the first 4 000 hours of operation The inspection is to be repeated every 100 hours of operation after the initial inspection has been accomplished 9 Supplemental Inspection Document items that are to be examined after the first 3 000 hours of operation or 10 years whichever occurs first The inspection is to be repeated every 500 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished 10 Supplemental Inspection Document items that are to be examined after the first 5 000 hours of o
13. Refer to Figure 1 H Filiform Corrosion 1 Filiform corrosion is a concentration cell corrosion process When a break in the protective coating over aluminum occurs the oxygen concentration at the back or bottom of the corrosion cell is lower than that at its open surface The oxygen concentration gradient thus established causes an electric current flow and corrosion results Filiform corrosion results when this happens along the interface between the metal and the protective coating and appears as small worm like tracks Filiform corrosion generally starts around fasteners holes and countersinks and at the edge of sheet metal on the outer surface of the airplane Filiform corrosion is more prevalent in areas with a warm damp and salty environment 2 To help prevent filiform corrosion development the airplane should be a Spray washed at least every two to three weeks especially ina warm damp environment b Waxed with a good grade of water repellent wax to help keep water from accumulating in skin joints and around countersinks NOTE Wax only clean surfaces Wax applied over salt deposits will almost guarantee a trapped salt deposit which is capable of accumulating moisture and developing into filiform corrosion D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 2 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL pee HIGH OXYGEN HIGH
14. first 10 years The inspection is to be repeated every 10 years after the initial inspection has been accomplished for airplanes operating in a mild or moderate corrosion environment 17 Supplemental Inspection Document items that are to be examined after the first 5 years The inspection is to be repeated every 5 years after the initial inspection has been accomplished for airplanes operating in a severe corrosion environment 18 Supplemental Inspection Document items that are to be examined after 12 000 hours or 20 years whichever occurs first The inspection is to be repeated every 2 000 hours or 10 years whichever occurs first after the initial inspection has been accomplished for airplanes operating in a typical usage environment D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 00 Page 4 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL Operation Details 19 Supplemental Inspection Document items that are to be examined after the first 6 000 hours of operation or 10 years whichever occurs first The inspection is to be repeated every 1 000 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished for airplanes operating in a severe usage environment 20 Supplemental Inspection Document items that are to be examined after the first 5 000 hours of operation or 20 years whichever occurs first The ins
15. for severe corrosion environment Initial 10 years 13 510 Inspect flap tracks for corrosion Refer to Section Repeat 5 years 610 2A 14 21 Supplemental Inspection Document 57 53 01 for inspection procedure Stabilizer trim system 1 Inspect stabilizer trim Initial 1 000 hours 14 330 brackets and actuator support brackets 2 Inspect Repeat 1 000 hours 320 pulleys attaching structure and fasteners Refer to Section 2A 14 02 Supplemental Inspection Document 27 30 01 for inspection procedures Inspect trim screw barrels and stabilizer screw jack Initial 1 000 hours 14 330 actuator threads Refer to Section 2A 14 03 Repeat 1 000 hours 340 Supplemental Inspection Document 27 42 01 for inspection procedures D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 01 Page5 Cessna Aircraft Company Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL TASK Inspect main landing gear fittings and attachment of the fittings to the bulkheads Refer to Section 2A 14 07 Supplemental Inspection Document 32 13 04 for inspection procedure This interval is for mild moderate corrosion environment Inspect seat rails for corrosion Refer to Section 2A 14 10 Supplemental Inspection Document 53 47 01 for inspection procedure This interval is for severe corrosion environment Inspect seat rails for corrosion Refer to Section 2A 14 10 Supplemental Inspection Do
16. impractical to replace an assembly or component contact an authorized repair shop D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL B Direct Chemical Attack 1 Direct chemical attack may take place when corrosive chemicals such as battery electrolyte caustic cleaning solutions or residual flux deposits are allowed to remain on the surface or become entrapped in cracks or joints Welding or soldering flux residues are hydroscopic and will tend to cause severe pitting Any potentially corrosive substance should be carefully and completely removed whenever such spillage occurs C Pitting Corrosion 1 The most common effect of corrosion on polished aluminum parts is called pitting It is first noticeable as a white or gray powdery deposit similar to dust which blotches the surface Refer to Figure 1 2 When the deposit is cleaned away tiny pits can be seen in the surface Pitting may also occur in other types of metal alloys D Intergranular Corrosion 1 Intergranular corrosion Refer to Figure 1 takes place because of the nature of the structure of metal alloys As metals cool from the molten state a granular structure is formed The size and composition of the grains and the material in the grain boundaries depend on several factors including the type of alloy and rate of cooling from the
17. molten state or cooling after heat treating The grains differ chemically and may differ electrochemically from the boundary material If an electrolyte comes in contact with this type of structure the grains and boundary material will act as anode and cathode and undergo galvanic corrosion The corrosion proceeds rapidly along the grain boundaries and destroys the solidity of the metal E Exfoliation gives the appearance of sheets of very thin metal separated by corrosion products It is a form of intergranular corrosion Since the corroded products are thicker than the uncorroded aluminum exfoliation shows itself by lifting up the surface grains of a metal by the force of expanding corrosion This type of corrosion is most often seen on extruded sections where the grain thicknesses are usually less than in rolled alloy form F Dissimilar Metal Corrosion Refer to Figure 1 1 Dissimilar metal corrosion occurs when dissimilar metals are in contact in the presence of an electrolyte A common example of dissimilar metal contact involves the attachment of aluminum parts by steel fasteners G Concentration Cell Corrosion Refer to Figure 1 1 Concentration cell corrosion occurs when two or more areas of the same metal surface are in contact with different concentrations of the same solution such as moist air water and chemicals 2 The general types of concentration cell corrosion are identified as metal ion cells and oxygen cells
18. skins NOTE Corrosion Prevention and 620 Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Wing structure external Make sure you inspect these Every 60 months 6 510 areas 1 Skin with emphasis at skin overlaps and 520 under access panels 2 Rear spar upper and lower 610 caps 3 Rear spar web NOTE Corrosion Prevention 620 and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Vertical stabilizer structure Make sure you inspect Every 60 months 6 310 these areas 1 Forward spar attachment to tailcone 340 bulkhead 2 Aft spar attachment to lower vertical stabilizer spar 3 Front and rear spars 4 Rear spar rudder hinges NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 01 Page 3 O Cessna Aircraft Company Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL TASK Horizontal stabilizer structure Make sure you inspect these areas 1 Stabilizer attachment to the tailcone bulkhead 2 Front and rear spars NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Inspect rudder pedal
19. torque tube shafts support brackets and cable attachment arms Refer to Section 2A 14 01 Supplemental Inspection Document 27 20 01 for inspection procedure Inspect vertical stabilizer and rudder including spars ribs hinge bolts hinge bearings and attach fittings Refer to Section 2A 14 12 Supplemental Inspection Document 55 30 01 for inspection procedure Inspect wing main spar and rear spar Refer to Section 2A 14 16 Supplemental Inspection Document 57 11 03 for inspection procedure Inspect aileron hinges hinge bolts hinge bearings hinge and pushrod attach fittings Refer to Section 2A 14 20 Supplemental Inspection Document 57 51 01 for inspection procedure Inspect tubular engine mount Refer to Section 2A 14 22 Supplemental Inspection Document 71 20 01 for inspection procedure This inspection is for mild moderate corrosion environment Inspect main landing gear spring and attach fittings for rust or damage to finish Inspect entry step attachment Refer to Section 2A 14 04 Supplemental Inspection Document 32 13 01 for inspection procedure This inspection is for mild moderate corrosion environment Inspect carry thru spar area wing attach fittings spar channel and lugs Refer to Section 2A 14 08 Supplemental Inspection Document 53 11 01 for inspection procedure This interval is for mild moderate corrosion environment Inspect the cabin interior skin panels frames and stringers Refer to Section 2
20. 015 Cessna Aircraft Company CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS Stabilizer trim system Make sure you inspect these Every 24 months 3 330 areas 1 Stabilizer trim brackets 2 Actuator support 320 brackets and bearings 3 Pulleys and attaching structure NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor on hinge bearing Rudder attachments Make sure you inspect these Every 24 months 3 340 areas 1 Hinge brackets 2 Hinge bolts 3 Hinge bearings NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor on hinge bearing Rudder structure Make sure you inspect these areas Every 24 months 3 340 1 Skin 2 Forward and aft spars at hinge locations NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information Main landing gear axle assembly Make sure you Every 36 months 4 721 inspect these areas 1 Main gear axle and attach 722 bolts 2 Wheel halves NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional insp
21. 46 Bulkhead Assembly STA 230 187 Stabilizer Hinge Brackets Inspect the brackets for cracks Bulkhead Assembly STA 209 00 Angle Tailcone Reinforcement DETAIL A Inspect reinforcement angle for cracks in this area Angle Tailcone Reinforcement STA 228 62 Inspect rivet for condition and security DETAIL B 0710T1030 Tailcone Reinforcement Inspection Figure 1 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 14 23 Page 3 O Cessna Aircraft Company May 18 2015 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL CORROSION 1 General A B This section describes corrosion to assist maintenance personnel in identification of various types of corrosion and application of preventative measures to minimize corrosion activity Corrosion is the deterioration of a metal by reaction to its environment Corrosion occurs because most metals have a tendency to return to their natural state 2 Corrosion Characteristics A Metals corrode by direct chemical or electrochemical galvanic reaction to their environment The following describes electrochemical reaction 1 Electrochemical corrosion can best be compared to a battery cell Three conditions must exist before electrochemical corrosion can occur a There must be a metal that corrodes and acts as the anode positive b There must be a less corrodible metal that acts as the cathode negative
22. A 14 09 Supplemental Inspection Document 53 30 01 for inspection procedure D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company INTERVAL OPERATION ZONE Every 60 months 6 330 320 Initial 10 000 7 211 hours or 20 years whichever occurs first Repeat 3 000 hours or 5 years whichever occurs first Initial 5 000 hours or 20 340 20 years whichever occurs first Repeat 2 000 hours or 5 years whichever occurs first Initial 4 000 hours 8 510 Repeat 100 hours 520 610 620 Initial 3 000 hours or 9 520 10 years whichever 620 occurs first Repeat 500 hours or 5 years whichever occurs first Initial 5 000 hours or 10 120 20 years whichever occurs first Repeat At Engine Overhaul Initial 20 years 11 721 Repeat 10 years 722 Initial 20 years 11 210 Repeat 10 years Initial 20 years 11 210 Repeat 10 years 2A 10 01 Page 4 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS This interval is for mild moderate corrosion Initial 20 years 11 510 environment Inspect wing for corrosion and missing Repeat 10 years 520 or loose fasteners Refer to Section 2A 14 15 610 Supplemental Inspection Document 57 11 02 for 620 inspection procedure This interval is for mild moderate corrosion Initial 20 years 11 510 environment Inspect flap tracks for corros
23. Document 55 30 02 for inspection procedure Inspect main landing gear spring axle attach bolt holes Refer to Section 2A 14 06 Supplemental Inspection Document 32 13 03 for inspection procedure Inspect main landing gear spring axle attach bolt holes Refer to Section 2A 14 05 Supplemental Inspection Document 32 13 02 for inspection procedure Flaps 1 Check flap travel cable tension and travel time 2 Check flap cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables Aileron 1 Check aileron travel and cable tension 2 Check aileron cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables Elevator 1 Check elevator travel and cable tension 2 Check elevator cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables Stabilizer Trim 1 Check stabilizer trim travel and cable tension 2 Check stabilizer trim cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables D2000 9 13 Temporary Revision Number 9 May 18 2015 O Cessna Aircraft Company INTERVAL OPERATION ZONE Initial 5 000 hours or 20 330 20 years
24. METAL ION CONCENTRATION CONCENTRATION en ES KE D METAL ION OXYGEN CONCENTRATION CONCENTRATION CELL CELL LOW METAL ION LOW OXYGEN CONCENTRATION CONCENTRATION CONCENTRATION CELL CORROSION CORROSION ELECTROLYTE PRODUCTS ELECTROLYTE TEEL AR PASSIVE FILM FASTENER ALUMINUM ALLOY PINHOLE CORROSION DISSIMILAR METAL CORROSION FILIFORM CORROSION WORM LIKE TRACKS INTERGRANULAR METALLIC GRAIN CORROSION STRUCTURE INTERGRANULAR CORROSION HIGHLY MAGNIFIED FILIFORM CORROSION nn PAINTED HIGHLY MAGNIFIED 65911001 SURFACE Es ie 62911013 62916004 Corrosion Figure 1 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 3 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL c Keep the airplane hangared to protect it from the atmosphere d Fly the airplane to promote aeration of enclosed parts e Ensure all vent drain holes are open to ventilate the interior of airplane 3 To remove filiform corrosion once it has been discovered a Remove paint from corroded area b Remove corrosion by sanding area to metal surface using either a ScotchBrite pad or 320 grit sandpaper aluminum oxide or silicone carbide grit c Clean and refinish surface Stress Corrosion Cracking 1 This corrosion is caused by the simultaneous effects of tensile stress and corrosion The stress may be internal or applied Int
25. May 18 2015 2A 13 00 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL Table 1 Typical Examples of Principal Structural Elements Wing and Empennage Control surfaces flaps and their mechanical systems and attachments hinges tracks and fittings Primary fittings Principal splices Skin or reinforcement around cutouts or discontinuities Skin stringer combinations Spar caps Spar webs Fuselage Circumferential frames and adjacent skin Door frames Pilot window posts Bulkheads Skin and single frame or stiffener element around a cutout Skin and or skin splices under circumferential loads Skin or skin splices under fore and aft loads Skin around a cutout Skin and stiffener combinations under fore and aft loads Door skins frames and latches Window frames Landing Gear and Attachments Engine Support Structure and Mounts B Selection Criteria 1 The factors used to find the PSE s in this document include a Service Experience 1 Multiple sources of information were used to find the service discrepancies a Cessna Service Bulletins and Service Information Letters issued to repair common service discrepancies were examined b FAA Service Difficulty Records and Foreign certification agency Service Difficulty Records were examined 2 Existing analyses were reviewed to identify components in areas that may have exhibited the potential for additional inspection r
26. RATE severe North America Corrosion Severity Map Figure 2 Sheet 1 2A 30 01 Page 8 D2000 9 13 Temporary Revision Number 9 May 18 2015 Oct 2 1995 Cessna Aircraft Company CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL ae Aruba Netherlands Antilles amp Grenada Trinidad amp Tobago Severe o Yee Rio de Janeiro UN CORROSION SEVERITY LEGEND MILD MODERATE SEVERE South America Corrosion Severity Map Figure 3 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page9 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A91673 Canary Islands CORROSION SEVERITY LEGEND Johannesburg gi Moderate MODERATE Cape Town Durban _ SEVERE Africa Corrosion Severity Map Figure 4 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 10 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A91674 Beijing Vladivostok Severe Severe g Taiwan Ryukyu Islands amp Spratly Islands Maldives amp 4 Singapore Severe Indian Islands Severe CORROSION SEVERITY LEGEND MILD pa MODERATE Y SEVERE m Asia Corros
27. RE inspection time limits D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page 3 O Cessna Aircraft Company Oct 2 1995 5 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL For all other operating environments inspections should be conducted using the TYPICAL Inspection Time Limits Corrosion Severity 1 2 Prior to conducting the initial corrosion inspection determine where the airplane has resided throughout its life If the airplane has resided in a severe corrosion environment for 30 or more of the years to the initial inspection refer to maps in Section 2A 30 01 use the severe inspection time otherwise use the mild moderate inspection time Prior to conducting a repetitive corrosion inspection determine where the airplane has resided since the last inspection If the airplane has resided in a severe environment for 30 or more of the years since the last inspection use the severe inspection time otherwise use the mild moderate inspection time 4 Reporting Communications A Discrepancies 1 For the SID to continue to stay applicable it is necessary to have a free flow of information between the operator the FAA and Cessna Aircraft Company The important information about the inspection results repairs and modifications done must be supplied to Cessna Aircraft Company in order to assess the effectiveness of the recommended inspection procedures and inspection interva
28. a Complete a check of the effect on the structural or operational condition b Complete a check of other high time airplanes to find if a service bulletin shall be issued c Find if a reinforcement is required d Change the SID if required D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page 4 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 5 Inspection Methods A very important part of the SID program is selecting and evaluating state of the art nondestructive inspection NDI methods applicable to each PSE Potential NDI methods were selected and evaluated on the basis of crack orientation part thickness and accessibility Inspection reliability depends on size of the inspection task human factors such as qualifications of the inspector equipment reliability and physical access Visual fluorescent liquid penetrant eddy current and magnetic particle methods are used A complete description of those methods are presented in Section 2A 13 01 Nondestructive Inspection Methods and Requirements 6 Related Documents A Existing Inspections Modifications and Repair Documents 1 Cessna has a number of documents that are useful to maintaining continued airworthiness of airplanes a Cessna Model 180 185 Service Manual P N D2000 9 13 b Cessna Model 180 185 Illustrated Parts Catalog P N P527 12 and P699 12 c Cessna Single Engine Service I
29. ally reactive Example chrome on steel or is more compatible with the metal to which it is coupled Example cadmium plated steel fasteners used in aluminum 6 At normal atmospheric temperatures metals do not corrode appreciably without moisture However the moisture in the air is usually enough to start corrosive action 7 The initial rate of corrosion is usually much greater than the rate after a short period of time This slowing down occurs because of the oxide film that forms on the metal surfaces This film tends to protect the metal underneath 8 When components and systems constructed of many different types of metals must perform under various climatic conditions corrosion becomes a complex problem The presence of salts on metal surfaces sea or coastal operations greatly increases the electrical conductivity of any moisture present and accelerates corrosion 9 Other environmental conditions that contribute to corrosion are a Moisture collecting on dirt particles b Moisture collecting in crevices between lap joints around rivets bolts and screws 3 Types of Corrosion A The common types of corrosion that are encountered in airplane maintenance are described in this section In many instances more than one form of corrosion may exist at the same time While this makes it difficult to determine the exact type of corrosion it should still be possible to determine that a corrosive process is taking place If it is
30. aluminum alloy of suitable design should be used under machine screws countersunk fasteners bolt heads and nuts 6 Adjustable parts threads such as tie rod ends turnbuckles etc should be protected with solid film lubrication conforming to Specification MIL PRF 46010 and or MIL L 46147 7 Slip fits should be assembled using wet primer conforming to Specification MIL PRF 23377G or later non drying zinc chromate paste or solid film lubricant conforming to Specification MIL PRF 46010 and or MIL L 46147 8 Press fits should be accomplished with oil containing material conforming to Specification MIL C 11796 Class 3 and or MIL C 16173 Class 1 or with other suitable material that will not induce corrosion F Electrical 1 Bonding and ground connections should be as described by the installation procedure 2 Potting compounds are used to safeguard against moisture Corrosion in electrical systems and resultant failure can often be attributed to moisture and climatic condition D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Pages O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 3 Corrosion of metal can be accelerated because of the moisture absorbed by fungi Fungi can create serious problems since it can act as an electrolyte destroying the resistance of electrical insulating surfaces Specification ASTM D3955 or ASTM D295 58 outlines moisture and fu
31. aluminum hinge Solid film lubricants are often applied to reduce corrosion problems D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 4 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 2 Care and replacement of solid film lubricants require special techniques peculiar to the particular solid film being used Good solid film lubricants are lubricants conforming to Specification MIL PRF 81322 a Solid film lubricants prevent galvanic coupling on close tolerance fittings and reduce fretting corrosion Surface preparation is extremely important to the service or wear life of solid film lubricants b Solid film lubricants are usually applied over surfaces coated with other films such as anodize and phosphate They have been successfully applied over organic coatings such as epoxy primers CAUTION Solid film lubricants containing graphite either alone or in mixture with any other lubricants should not be used since graphite is cathodic to most metals and will cause galvanic corrosion in the presence of electrolytes E Requirements peculiar to faying surfaces of airframes airframe parts and attaching surfaces of equipment accessories and components 1 When repairs are made on equipment or when accessories and components are installed the attaching surfaces of these items should be protected The following requirements are peculiar to faying surfac
32. cument 53 47 01 for inspection procedure This interval is for typical usage environment 1 Inspect inboard wing structure and wing attachment to fuselage including working rivets 2 Inspect flap actuator support structure Refer to Section 2A 14 14 Supplemental Inspection Document 57 11 01 for inspection procedure This interval is for mild moderate corrosion environment Inspect wing splice joint at strut attach Refer to Section 2A 14 17 Supplemental Inspection Document 57 11 04 for inspection procedure This interval is for typical usage environment Inspect wing strut and strut tube Refer to Section 2A 14 19 Supplemental Inspection Document 57 40 01 for inspection procedure This interval is for severe usage environment 1 Inspect inboard wing structure and wing attachment to fuselage including working rivets 2 Inspect flap actuator support structure Refer to Section 2A 14 14 Supplemental Inspection Document 57 11 01 for inspection procedure This interval is for severe usage environment Inspect wing splice joint at strut attach Refer to Section 2A 14 17 Supplemental Inspection Document 57 11 04 for inspection procedure This interval is for severe usage environment Inspect wing strut and strut tube Refer to Section 2A 14 19 Supplemental Inspection Document 57 40 01 for inspection procedure D2000 9 13 Temporary Revision Number 9 May 18 2015 Cessna Aircraft Company INTERVAL OPERATION ZONE
33. e C Steel Control Cable 1 Checking for corrosion on a control cable is normally accomplished during the preventative maintenance check During preventative maintenance broken wire and wear of the control cable are also checked 2 If the surface of the cable is corroded carefully force the cable open by reverse twisting and visually inspect the interior Corrosion on the interior strands of the cable constitutes failure and the cable must be replaced If no internal corrosion is detected remove loose external rust and corrosion with a clean dry coarse weave rag or fiber brush CAUTION Do not use metallic wools or solvents to clean installed cables Metallic wools will embed dissimilar metal particles in the cables and create further corrosion Solvents will remove internal cable lubricant allowing cable strands to abrade and further corrode 3 After thorough cleaning of exterior cable surfaces if the cable appears dry the lubrication originally supplied on the cable has probably oxidized and needs to be replaced with a light oil 5w motor oil 3 in 1 oil LPS 2 WD 40 or Diesel Fuel Apply the oil with a cloth and then rub the cable with the cloth to coat the cable with a thin layer of oil Excessive oil will collect dust and be as damaging to the cable as no lubrication D Piano Type Hinges 1 The construction of piano type hinges forms moisture traps as well as the dissimilar metal couple between the steel hinge pin and the
34. e completed based on hour time if the Corrosion Prevention and Control Program CPCP in Section 2A 30 00 is included in the airplane maintenance program C Repairs Alterations and Modifications RAM 1 Repairs alterations and modifications RAM made to PSE s may affect the inspection times and methods presented in the SID The flowchart in Figure 1 can be used to determine if a new assessment and FAA approved supplemental inspections are required 2 Repairs may be made in accordance with Section 17 of the Model 180 185 Service Manual or the REPAIR MODIFICATION Section of the SID 3 Repairs not covered by the recommendations in these documents may be coordinated with Cessna Customer Service at telephone 316 517 5800 FAX 316 517 7271 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page 6 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A81680 Start Evaluation STC Non STC Alteration or Modification Repair Does installation affect an existing Does repair affect an existing inspection inspection area listed in the SID If area listed in the SID If Has installation altered Analytical the affected structure y or increased redistributed Assessment the loads acting on it If and supplemental inspections are required Analytical Assessment and supplemental inspections are required Analytical Assessment and supplemental
35. ection information NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor to the bearing NOTE Coordinate with tire change Horizontal stabilizer screw jack actuator Make sure Every 36 months 4 320 you inspect these areas 1 Horizontal screw jack 330 actuator threads 2 Actuator hinge assemblies NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Passenger Crew door retention system Make sure Every 48 months 5 210 you inspect these areas 1 Bell cranks 2 Pushrods 3 Handle 4 Pin retention 5 Pins 6 Lockplates and guides 7 Hinges 8 Internal door framing NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Note Remove interior panels for access Areas of the cabin structure for the passenger crew Every 48 months 5 210 door Make sure you inspect these areas 1 Door frames 2 Door hinges NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 01 Page 2 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS Fuselage lower internal structure beneath the floor E
36. efers to the physical location s in the airplane affected by the item 2 Primary purpose of the Inspection Time Limits section is to provide a complete listing of all inspection items in an order that allows easy access for the information listed previously This section is not intended to be utilized as a guideline for inspection of the airplane 3 The Inspection Time Limits Chart shows the recommended intervals at which items are to be inspected based on usage and environmental conditions The operator s inspection intervals shall not deviate from the inspection time limits shown in this table except as provided below a Each inspection interval can be exceeded by 10 hours if time controlled or by 30 days if date controlled or can be performed early at any time prior to the regular interval as provided below 1 In the event of late compliance of any operation scheduled the next operation in sequence retains a due point from the time the late operation was originally scheduled 2 In the event of early compliance of any operation scheduled that occurs 10 hours or less ahead of schedule the next operation due point may remain where originally set In the event of early compliance of any operation scheduled that occurs more than 10 hours ahead of schedule the next operation due point must be rescheduled to establish a new due point from the time of early accomplishment IC Section 2A 20 01 Expanded Maintenance This section pr
37. equirements 3 Areview of test results applicable to the design was made to identify the critical areas of the PSE s 4 The data collected was also used to find a component s susceptibility to corrosion or accidental damage as well as its inspectability D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Page 2 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 3 Usage A Aircraft Usage 1 Aircraft usage data for the SID program is based on the evaluation of the in service utilization of the aircraft This data was used to develop the representative fatigue loads spectra Operational data for development of the Supplemental Structural Inspection Program was obtained from surveys of aircraft operators 2 Usage for spectra determination is defined in terms of a single flight representing typical average in service utilization of the aircraft This usage reflects the typical in service flight variation of flight length takeoff gross weight payload and fuel 3 The flight is defined in detail in terms of a flight profile The profile identifies the gross weight payload fuel altitude speed distance etc required to define the pertinent flight and ground parameters needed to develop the fatigue loads The flight is then divided into operational segments where each segment represents the average values of the parameters speed payload fuel etc that are used t
38. ernal stresses are produced by nonuniform shaping during cold working of the metal press and shrink fitting general hardware and those induced when pieces such as rivets and bolts are formed The amount of stress varies from point to point within the component Stress corrosion is most likely to occur at points of highest stress which are also subject to corrosion influence Fatigue Corrosion 1 Fatigue corrosion is a special case of stress corrosion caused by the combined effects of cyclic stress and corrosion 4 Typical Corrosion Areas A Aluminum appears high in the electrochemical series of elements and its position indicates that it should corrode very easily However the formation of a tightly adhering oxide film offers increased resistance under mild corrosive conditions Most metals in contact with aluminum form couples which undergo galvanic corrosion attack The alloys of aluminum are subject to pitting intergranular corrosion and intergranular stress corrosion cracking B Battery Electrolyte 1 Battery electrolyte used in lead acid batteries is composed of 35 sulfuric acid and 65 water When electrolyte is spilled it should be cleaned up immediately A weak boric acid solution may be applied to the spillage area followed by a thorough flushing with clean cold running water If boric acid is not available flush the area with clean cold water 2 If corrosion appears use an approved repair method to repair the structur
39. es on airframes airframe parts and attaching surfaces of equipment accessories and components 2 Surfaces of similar or dissimilar metals a All faying surfaces seams and lap joints protected by sealant must have the entire faying surface coated with sealant Excess material squeezed out should be removed so that a fillet seal remains Joint areas which could hold water should be filled or coated with sealant 3 Attaching Parts a Attaching parts such as nuts bushings spacers washers screws self tapping screws self locking nuts and clamps do not need to be painted in detail except when dissimilar metals or wood contact are involved in the materials being joined Such parts should receive a wet or dry coat of primer NOTE Corrosion inhibiting solid film lubricants Specification MIL PRF 46010 and or MIL L 46147 may be used to protect attaching parts from corrosion b All holes drilled or reworked in aluminum alloys to receive bolts bushings screws rivets and studs should be treated before installation of fasteners or bushings c All rivets used to assemble dissimilar metals should be installed wet with sealant conforming to Specification MIL PRF 81733 Corrosion inhibiting sealer Type X 4 Close tolerance bolts passing through dissimilar metals should be coated before installation with a corrosion inhibiting solid film lubricant conforming to Specification MIL PRF 46010 and or MIL L 46147 5 Washers made of
40. ext operation in sequence retains a due point from the time the late operation was originally scheduled D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 00 Page 2 O Cessna Aircraft Company Oct 2 1995 5 6 D2000 9 13 Temporary Revision Number 9 May 18 2015 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL c Inthe event of early compliance of any operation scheduled that occurs 10 hours or less ahead of schedule the next phase due point may remain where originally set d In the event of early compliance of any operation scheduled that occurs more than 10 hours ahead of schedule the next operation due point must be rescheduled to establish a new due point from the time of early accomplishment Inspection Time Limits Legend A Each page of the inspection listed in Inspection Time Limits Section 24 10 01 contains the following five columns REVISION STATUS This column provides the date that a given item was added deleted or revised A blank entry in this column indicates no change since the reissue of this manual TASK This column provides a short description of the inspection and or servicing procedures Where a more detailed description of the procedure is required a reference will be made to either another section located within the Model 180 185 Service Manual or a specific reference to a supplier publication INTERVAL This column lists the frequency of the inspection
41. ion Repeat 10 years 610 Refer to Section 2A 14 21 Supplemental Inspection Document 57 53 01 for inspection procedure This interval is for mild moderate corrosion Initial 5 years 12 510 environment Inspect wing root rib Refer to Section Repeat 5 years 610 2A 14 18 Supplemental Inspection Document 57 12 01 for inspection procedure This interval is for severe corrosion environment Initial 10 years 13 721 Inspect main landing gear spring and attach fittings for Repeat 5 years 722 rust or damage to finish Inspect entry step attachment Refer to Section 2A 14 04 Supplemental Inspection Document 32 13 01 for inspection procedure This interval is for severe corrosion environment Initial 10 years 13 210 Inspect carry thru spar area wing attach fittings Repeat 5 years spar channel and lugs Refer to Section 2A 14 08 Supplemental Inspection Document 53 11 01 for inspection procedure This interval is for severe corrosion environment Initial 10 years 13 210 Inspect the cabin interior skin panels frames and Repeat 5 years stringers Refer to Section 2A 14 09 Supplemental Inspection Document 53 30 01 for inspection procedure This interval is for severe corrosion environment Initial 10 years 13 510 Inspect wing for corrosion and missing or loose Repeat 5 years 520 fasteners Refer to Section 2A 14 15 Supplemental 610 Inspection Document 57 11 02 for inspection 620 procedure This interval is
42. ion Severity Map Figure 5 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 11 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A91675 As Reykjavik E Helsinki Severe Borgen St Petersburg Moderate Liverpool Severe Paris gt Marseille y E Y f Ne ES 7 A N HEHE iY j Za IE J Barcelona GE UY Z woh J oe Yasnend ad amp o Seville Corsica amp S a La 7 y Sardinia Sicily Cros A Severe Severe CORROSION SEVERITY LEGEND I Crete amp Cyprus MILD Severe MODERATE SEVERE Europe and Asia Minor Corrosion Severity Map Figure 6 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Cessna Aircraft Company Page 12 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A91676 All South Pacific Islands Severe g gt 0 Y o 8 A 2 o o Re CORROSION SEVERITY LEGEND gt 2 MILD MODERATE Y SEVERE ZA South Pacific Corrosion Severity Map Figure 7 Sheet 1 D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 13 O Cessna Aircraft Company Oct 2 1995
43. ion item refer to Section 2A 30 00 for additional inspection information Control Yoke Make sure you inspect these areas 1 Center section of control yoke NOTE Corrosion Prevention and Control Program Inspection item refer to Section 2A 30 00 for additional inspection information Wing structure internal Make sure you inspect these areas 1 Main spar upper and lower carry thru fittings 2 Main spar upper and lower caps 3 Main spar web NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Aileron attachments Make sure you inspect these areas 1 Aileron hinges 2 Hinge bolts 3 Hinge bearings 4 Hinge and pushrod support structure NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor on hinge bearing INTERVAL 100 hours months occurs Every or 12 whichever first 100 hours months occurs Every or 12 whichever first 100 hours months occurs Every or 12 whichever first 100 hours months occurs Every or 12 whichever first Every 12 months Every 12 months Every 12 months Every 24 months OPERATION ZONE 120 210 510 520 610 620 520 620 2A 10 01 Page 1 Oct 2 1995 D2000 9 13 Temporary Revision Number 9 May 18 2
44. ls 2 Also the operator s inspections and reports can find items not included in the SID before These items will be examined by Cessna Aircraft Company and will be added to the SID for all of the operators if applicable 3 Cessna Customer Service has a system to collect the reports The applicable forms are included in this document Copies of these forms are also available from a Cessna Service Station or Cessna Field Service Engineer B Discrepancy Reporting 1 Discrepancy reporting is essential to provide for adjusting the inspection thresholds and the repeat times as well as adding or deleting PSE s It may be possible to improve the inspection methods repairs and modifications involving the PSE s based on the data reported 2 All cracks multiple cut off fasteners and corrosion found during the inspection must be reported to Cessna Aircraft Company within ten days The PSE inspection results are to be reported on a form as shown on the pages that follow C Send the Discrepancy Form 1 Send all available data which includes forms repairs photographs sketches etc to Cessna Aircraft Company Attn Customer Service P O Box 7706 Wichita KS 67277 USA Phone 316 517 5800 Fax 316 517 7271 NOTE This system does not replace the normal channels to send information for items not included in the SID D Cessna Aircraft Company Follow Up Action 1 All SID reports will be examined to find if any of the steps are necessary
45. mponents 1 Replace damaged or corroded steel or aluminum fasteners 2 Ifthe material is sheet or plate the thickness is allowed to be as little as 90 of the nominal thickness 3 This general allowance is not allowed if a The area of the part contains fasteners b The reduced thickness compromises the fit or function of a part Finish the new or repaired parts 1 Apply Alodine or similar anticorrosion compounds to new or repaired parts or 2 Apply zinc chromate or 3 Apply epoxy fuel tank primer 4 Paint the exterior or visible interior parts according to Section 18 of the applicable Model 180 185 Service Manual Replace Removed Components 6 General A This section contains maps which define the severity of potential corrosion on the airplane structure B The Corrosion Severity Zones identified in Figure 2 Figure 3 Figure 4 Figure 5 Figure 6 and Figure 7 are provided for guidance to determine types and frequency of required inspections and other maintenance D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page 6 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL C Corrosion Severity Zones are affected by atmospheric and other climatic factors It is the responsibility of the owner and operator to determine the specific corrosion severity level with respect to the operating environment of the aircraft based on geographic locatio
46. n and known environmental conditions Corrosion Severity Zones are defined as follows 1 Mild Corrosion Severity Zone a Airplanes operated in arid temperate or cold regions 2 Moderate Corrosion Severity Zone a Airplanes operated in tropical or subtropical high humidity regions 3 Severe Corrosion Severity Zone a Airplanes operated in the following conditions should follow the procedures for severe corrosion zones Salt water or coastal regions Based in or near industrial and or metropolitan areas with heavy atmospheric pollution From airports where the use of chemical de icers is common Agricultural operations On floats INI gt IOIA D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 30 01 Page7 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A91671 Montreal Severe Toronto Moderate N a 7 PP Halifax J Severe fs New York City yy Y ENS 4 N VAN x SES PS SEN Y X SI Ro S 4 Los Angeles SD A 9 z que Hawaiian Islands Lip gt or Severe S Caribbean yy SY Houston O Islands amp Lo Bermuda N Y Severe an N x Monterrey Y ma N q Guadalajara nn yo Cuba ZZ Haiti Mexico City ZA 2 ae a Jamaica Dominican Y LV Republic Central sica CORROSION SEVERITY LEGEND we MILD SS MODE
47. nformation Letters and Service Bulletin Summaries d Cessna Service Newsletters and Newsletter Summaries B For information regarding these documents contact Cessna Aircraft Company Customer Service P O Box 7706 Wichita KS 67277 USA Phone 316 517 5800 Fax 316 517 7271 7 Applicability Limitations A This SID is applicable to the Cessna Model 180 185 B STC Modifications 1 The Cessna Model 180 185 airplanes can have modifications that were done by STCs by other organizations without Cessna Engineering approval The inspection intervals given in this SID are for unchanged airplanes 2 Airplanes that have been modified to alter the airplane design gross weight or airplane performance may need to be inspected more frequently Examples of common STC s not covered by this SID document include non Cessna wing extensions winglets speed brakes STOL conversions vortex generators tip tanks under wing tanks and nonstandard engines The owner and or maintenance organization should contact the STC holder s or modification originator for obtaining new FAA approved inspection criteria C The SID inspection times are based on total airframe hours OR calendar times in service If a specific airframe component has been replaced the component is to be inspected based on total component hours or calendar time requirements However any attachment structure that was not replaced when the component was replaced must be inspected based on
48. nformation about each required inspection The right portion of each page gives space for the mechanic s and inspector s initials and remarks A copy of these pages can be used as a checklist when these inspections are completed 2 General Inspection Criteria A TASK While each of the specified inspection tasks in this section are done more general inspections of the adjacent areas must be done while access is available These general inspections are used to find apparent conditions which can need more maintenance If a component or system is changed after a required task has been completed then that specified task must be done again to make sure it is correct before the system or component is returned to service Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced Refer to the Approved Airplane Flight Manual ZONE MECH INSP REMARKS Inspect horizontal stabilizer hinge bracket and 310 tailcone reinforcement angle Refer to Section 2A 14 23 Supplemental Inspection Document 53 10 01 for inspection procedures End of Operation 26 Inspection Items kkk D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 12 26 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL INSPECTION OPERATION 27 Date Registration Number Serial Number Total Time 1 De
49. nge bracket and 310 tailcone reinforcement angle Refer to Section 2A 14 23 Supplemental Inspection Document 53 10 01 for inspection procedures End of Operation 27 Inspection Items D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 12 27 Page 1 Cessna Aircraft Company Oct 2 1995 1 2 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL SUPPLEMENTAL INSPECTION DOCUMENT Supplemental Inspection Document A Introduction 1 The Supplemental Structural Inspection Program for the Cessna Model 180 185 airplane is based on the affected Model 180 185 airplane current usage testing and inspection methods A practical state of the art inspection program is established for each Principle Structural Element PSE A PSE is that structure whose failure if it remained undetected could lead to the loss of the airplane Selection of a PSE is influenced by the susceptibility of a structural area part or element to fatigue corrosion stress corrosion or accidental damage The Supplemental Structural Inspection Program was developed through the combined efforts of Cessna Aircraft Company operators of affected Model 180 185 airplanes and the FAA The inspection program consists of the current structural maintenance inspection plus supplemental inspections as required for continued airworthiness of the airplane as years of service are accumulated The current inspection program is conside
50. ngus resistant varnish to be used 5 General Corrosion Repair A G This section provides general guidance on the repair of corroded area The procedure presented is 1 Gain access to the entire corroded area 2 Mechanically remove the corrosion products 3 Determine the extent of the corrosion damage 4 Repair or replace the damaged components 5 Finish the new or repaired parts 6 Replace removed components Gain access to the entire corroded area 1 Corrosion products typically retain moisture If those products are not removed corrosion will continue Corrosion can take place within layered construction or under behind equipment fastened in place Mechanically remove the corrosion 1 Chemicals will not remove corrosion The best chemicals can do is interrupt the corrosion cell by either displacing water or shielding corrosion products from oxygen In either case the effect is temporary and will need to be renewed 2 Sand mild corrosion 3 Use rotary files or sanding disks for heavier corrosion Finish up with fine sand paper NOTE Do not use metallic wool Metal particles will be embedded in the surface which will initiate additional corrosion Determine the extent of corrosion damage 1 Direct measurement is simplest 2 Indirect measurement may be necessary a Eddy Current or ultrasound tools can be used for thickness measurement away from part edges Repair or replace corrosion damaged co
51. o calculate the loads spectrum B Stress Spectrum 1 A fatigue loads spectrum in terms of gross area stress was developed for each PSE to be analyzed based on the usage flight profiles The spectrum represents the following loading environments flight loads gust and maneuver landing impact taxi loads and ground air ground cycles The resulting spectrum is a representative flight by flight cycle by cycle loading sequence that reflects the appropriate and significant airplane response characteristics 2 After reviewing the aircraft usage data and the way in which the surveyed aircraft were flown two sets of stress spectra were developed The first flight profile represents typical usage while the second profile represents severe usage as described in Paragraph 3 D below C Fatigue Assessment 1 The fatigue assessment provides the basis for establishing inspection frequency requirements for each PSE The evaluation includes a determination of the probable location and modes of damage and is based on analytical results available test data and service experience In the analysis particular attention is given to potential structural condition areas associated with aging aircraft Examples include a large areas of structure working at the same stress level which could develop widespread fatigue damage b anumber of small less than detectable size adjacent cracks suddenly joining into a long crack e g as in a line of rivet hole
52. ovides additional information on some maintenance inspection procedures It describes where the component item is located what to inspect for how to inspect it etc Detailed requirements such as functional checks operational checks etc are listed in the appropriate section of the Model 180 185 Service Manual Refer to the appropriate section for complete detailed information Section 2A 30 00 Corrosion Prevention and Control Program CPCP This section gives the guidelines and applications of the CPCP This is a program used to control the corrosion in the airplane s primary structure The objective of the CPCP is to help to prevent or to control the corrosion so that it does not cause a risk to the continued airworthiness of the airplane 4 Inspection Time Limits A A complete airplane inspection includes all inspection items as required by 14 CFR Part 43 Appendix D Scope and Detail of annual 100 hour inspections Refer to Section 2 of the Model 180 185 Service Manual The intervals shown are recommended intervals at which items are to be inspected 1 The 14 CFR Part 91 operator s inspection intervals shall not deviate from the inspection time limits shown in this manual except as provided below Refer to 14 CFR 91 409 a The airplane can only exceed its inspection point up to 10 hours if the airplane is en route to a facility to have the inspection completed b Inthe event of late compliance of any operation scheduled the n
53. pection is to be repeated every 2 000 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished 21 Supplemental Inspection Document items that are to be examined after the first 3 years The inspection is to be repeated every 3 years after the initial inspection has been accomplished for airplanes operating in a severe corrosion environment 22 Supplemental Inspection Document items that are to be examined after the first 100 hours of operation or 1 year whichever occurs first The inspection is to be repeated every 100 hours or 1 year whichever occurs first after the initial inspection has been accomplished 23 Supplemental Inspection Document items that are to be examined after the first 4 000 hours of operation or 10 years whichever occurs first The inspection is to be repeated every 1 000 hours or 3 years whichever occurs first after the initial inspection has been accomplished 24 Supplemental Inspection Document items that are to be examined every time when skis are installed or removed 25 Expanded Maintenance Inspection items that are to be examined after the first 100 hours of operation The inspection is to be repeated every 600 hours of operation or 12 months whichever occurs first after the initial inspection has been accomplished 26 Supplemental Inspection items that are to be examined after 5 000 hours of operation or 20 years whichever occurs first The in
54. peration or 20 years whichever occurs first The inspection is to be repeated at engine overhaul after the initial inspection has been accomplished 11 Supplemental Inspection Document items that are to be examined after the first 20 years The inspection is to be repeated every 10 years after the initial inspection has been accomplished for airplanes operating in a mild or moderate corrosion environment 12 Supplemental Inspection Document items that are to be examined after the first 5 years The inspection is to be repeated every 5 years after the initial inspection has been accomplished for airplanes operating in a mild or moderate corrosion environment 13 Supplemental Inspection Document items that are to be examined after the first 10 years The inspection is to be repeated every 5 years after the initial inspection has been accomplished for airplanes operating in a severe corrosion environment 14 Supplemental Inspection Document items that are to be examined after the first 1 000 hours The inspection is to be repeated every 1 000 hours after the initial inspection has been accomplished 15 Supplemental Inspection Document items that are to be examined after 3 000 hours or 5 years whichever occurs first The inspection is to be repeated every 1 000 hours or 5 years whichever occurs first after the initial inspection has been accomplished 16 Supplemental Inspection Document items that are to be examined after the
55. present in the inspection area clean the area before doing the inspection C Doa visual inspection of the tailcone reinforcement angle Part Numbers 0712207 1 2 or 0712048 7 8 for crack s near F S 228 62 Inspect the rivet aft of F S 228 62 to make sure it is not loose or sheared Replace any loose or sheared rivets 1 If grime or debris is present in the inspection area clean the area before doing the inspection D If no cracks are found install item removed to accomplish this inspection 1 Refer to the applicable sections of the service manual for horizontal and vertical stabilizer installation instructions E If one or more cracks are found in the inspection area no further flight is permitted 1 You must replace the cracked part s before further flight 5 ACCESS AND DETECTABLE CRACK SIZE ACCESS LOCATION DETECTABLE CRACK SIZE Tailcone Horizontal and Vertical Stabilizers Not Allowed 6 INSPECTION METHOD Visual 7 REPAIR MODIFICATION If one or more cracks are found no further flight is permitted until the cracked parts are replaced D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 14 23 Page 1 Cessna Aircraft Company May 18 2015 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 8 COMMENTS D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 14 23 Page 2 O Cessna Aircraft Company May 18 2015 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL B206
56. rcraft Company on a reporting form Changes can then be made to SID program if necessary c The inspections presented in the SID apply to all Model 180 185 airplanes The inspection intervals presented are for unmodified airplanes Airplanes that have been modified to alter the airplane s design gross weight or performance may need to be inspected more frequently Examples of common STCs which will require modified inspection intervals include non Cessna wing extensions winglets speed brakes STOL conversions vortex generators tip tanks under wing tanks and nonstandard engines The owner and or maintenance organization should contact the STC holder s or modification originator for obtaining new FAA approved inspection criteria A Corrosion Prevention and Control Program CPCP should be established for each airplane Details of the CPCP are contained in Section 2A 30 00 of this manual Principal Structural Elements A Principal Structural Elements Description An airplane component is classified as a Principal Structural Element PSE if a The component contributes significantly to carrying flight and ground loads b Ifthe component fails it can result in a catastrophic failure of the airframe The monitoring of these PSE s is the main focus of this Supplemental Structural Inspection Program Typical examples of PSE s taken from FAA Advisory Circular 25 571 are shown in Table 1 D2000 9 13 Temporary Revision Number 9
57. red to be adequate in detecting corrosion and accidental damage The emphasis of the Supplemental Structural Inspection Program is to detect fatigue damage whose probability increases with time Since fatigue damage increases at an increasing rate with increasing crack length earlier detection and repair minimizes the damage and the magnitude of the repair The Supplemental Structural Inspection Program is valid for Model 180 185 airplanes with less than 30 000 flight hours Beyond this continued airworthiness of the airplane can no longer be assured Retirement of this airframe is recommended when 30 000 flight hours has been accumulated Function 1 2 The function of the Supplemental Structural Inspection Program is to find damage from fatigue overload or corrosion through the use of the Nondestructive Inspections NDI and visual inspections This Supplemental Inspection Document SID is only for primary and secondary airframe components Engine electrical items and primary and secondary systems are not included in this document A list is included to show the requirements for the SID program for primary and secondary airframe components a The airplane has been maintained in accordance with Cessna s recommendations or the equivalent b If the SID is for a specific part or component you must examine and evaluate the surrounding area of the parts and equipment If problems are found outside these areas report them to Cessna Ai
58. ry for quick reference EXPORT COMPLIANCE 1 This publication contains technical data and is subject to U S export regulations This information has been exported from the United States in accordance with export administration regulations Diversion contrary to U S law is prohibited ECCN 9E991 Cessna Aircraft Company CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL INSPECTION TIME LIMITS STRUCTURE 1 Scope A This provides the mandatory times and inspection time intervals for components and airplane structures This section also gives the required details to monitor them using scheduled inspections This section applies to items such as fatigue components and structures which are part of the certification procedures Refer to the description paragraph below for detailed information concerning each of these sections NOTE The time limits and maintenance checks listed in this section are the minimum requirements for airplanes operated under normal conditions For airplanes operated in areas where adverse operating conditions may be encountered such as high salt coastal environments areas of high heat and humidity areas where industrial or other airborne pollutants are present extreme cold unimproved surfaces etc the time limits should be modified accordingly NOTE The inspection guidelines contained in this section are not intended to be all inclusive for no such charts can replace the good j
59. s c redistribution of load from adjacent failing or failed parts causing accelerated damage of nearby parts i e the domino effect and d concurrent failure of multiple load path structure e g crack arrest structure 2 Initial inspections of a particular area of structure are based on fatigue analytical results For locations with long fatigue the maximum initial inspection was limited to 12 000 flight hours D Classifications for Types of Operation 1 The severity of the operation environment needs to be identified to determine the correct inspection program a You mustfirst find the category of your airplane s operation based on average flight length b You must also find the number of hours and number of landings on the airplane then find the average flight length based on the formula found below Average Flight Length Number of Flight Hours Number of Flights 2 Ifthe average flight length is less than 30 minutes then you must use the SEVERE inspection time limits For airplanes with an average flight length greater than thirty minutes you must find the severity of the operating environment 3 Airplanes which have engaged in operations at low altitudes such as pipeline patrol fish or game spotting aerial applications police patrol sightseeing livestock management etc more than 30 of its life must use the SEVERE inspection time limits 4 Airplanes which are equipped with floats or skis must use the SEVE
60. scription A Operation 27 gives Supplemental Inspection Document items that are to be examined after the first 3 000 hours of operation or 10 years whichever occurs first The inspection is to be repeated every 500 hours of operation or 5 years whichever occurs first after the initial inspection has been accomplished for airplanes operating in a severe usage environment Inspection items are given in the order of the zone in which the inspection is to be completed Frequently tasks give more information about each required inspection The right portion of each page gives space for the mechanic s and inspector s initials and remarks A copy of these pages can be used as a checklist when these inspections are completed 2 General Inspection Criteria A TASK While each of the specified inspection tasks in this section are done more general inspections of the adjacent areas must be done while access is available These general inspections are used to find apparent conditions which can need more maintenance If a component or system is changed after a required task has been completed then that specified task must be done again to make sure it is correct before the system or component is returned to service Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced Refer to the Approved Airplane Flight Manual ZONE MECH INSP REMARKS Inspect horizontal stabilizer hi
61. spection is to be repeated every 2 000 hours or 5 years whichever occurs first after the initial inspection has been completed for airplanes operating in a typical usage environment 27 Supplemental Inspection items that are to be examined after 3 000 hours of operation or 10 years whichever occurs first The inspection is to be repeated every 500 hours or 5 years whichever occurs first after the initial inspection has been completed for airplanes operating in a severe usage environment D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 00 Pages O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL INSPECTION TIME LIMITS Inspection Items REVI SION STATUS TASK Inspect aircraft records to verify that all applicable Cessna Service Information Letters Cessna Service Bulletins and Supplier Service Bulletins are complied with Inspect aircraft records to verify that all applicable Airworthiness Directives and Federal Aviation regulations are complied with Inspect aircraft records to verify that all logbook entries required by the Federal Aviation Regulations are complied with Inspect aircraft records to verify that all SID Inspections have been complied with as scheduled Engine support structure Make sure you inspect these areas 1 Engine truss Pay particular attention to vicinity of welds NOTE Corrosion Prevention and Control Program Inspect
62. the total airframe hours or calendar time requirements Inspections are due at the lessor of specified flight hours or calendar time The inspections must be completed by June 30 2014 8 PSE DETAILS A Details 1 This section contains the important instructions selected by the rationale process described in Section 2 Principal Structural Elements Those items are considered important for continued airworthiness of the Model 180 185 B PSE Data Sheets D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 13 00 Pages O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL A data sheet for each PSE is provided in Section 2A 14 XX Supplemental Inspection Documents Each data sheet contains the following 1 2 3 4 5 6 7 8 9 10 11 12 13 Supplemental Inspection Number Title Effectivity Inspection Compliance Initial Inspection Interval s Repeat Inspection Interval s Purpose Inspection Instructions Access Location Zone Detectable Crack Size Inspection Procedure Repair Modification Comments NOTE Accomplishment of SID inspections does not in any way replace preflight inspections good maintenance practices or maintenance and inspections specified in the Model 180 185 Service Manual NOTE Inspection intervals are given in both hour and calendar time After the completion of each initial SID inspection repeat inspections may b
63. udgment of certified airframe and power plant mechanics in performance of their duties As the one primarily responsible for the airworthiness of the airplane the owner or operator should select only qualified personnel to maintain the airplane 2 Inspection Requirements A Two types of inspection requirements are available based on operating usage and two additional types of inspections are available based on operating environment 1 Operating Usage a Severe Usage Environment 1 If the average flight length is less than 30 minutes then you must use the SEVERE inspection time limits 2 If the airplane has been engaged in operations at low altitudes such as pipeline patrol fish or game spotting aerial applications police patrol sightseeing livestock management etc more than 30 of its life you must use the SEVERE inspection time limits 3 Airplanes which are equipped with floats or skis must use the SEVERE inspection time limits b Typical Usage Environment 1 If neither 2 A 1 a 1 or 2 A 1 a 2 2 A 1 a 3 or above applies the TYPICAL usage environment applies 2 Operating Environment a Severe corrosion environment 1 If the airplane is operating more than 30 of the time in a zone shown as severe on the corrosion severity maps in Section 2A 30 01 then the SEVERE CORROSION environment time limits apply b Mild or Moderate Corrosion Environment 1 If 2 A 2 a 1 does not apply then the MILD MODERATE CORROSION en
64. very 60 months 6 210 panels Make sure you inspect these areas 1 Cabin structure under floorboards NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Fuselage internal structure in upper fuselage Make Every 60 months 6 210 sure you inspect these areas 1 Cabin bulkhead corners 2 Fuselage skin NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Areas of the cabin structure Make sure you inspect Every 60 months 6 210 these areas 1 Firewall 2 Firewall attachments NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Areas of the cabin structure Make sure you inspect Every 60 months 6 210 these areas 1 Cabin door forward and aft frames 2 Window frames with emphasis at stringers and channel assemblies from aft of door frame to aft bulkhead 3 Seat attachment structure 4 Aft Cabin Bulkhead NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Wing structure internal Make sure you inspect these Every 60 months 6 510 areas 1 Wing front spar and lower spar caps 520 2 Upper and lower wing attach spar fittings 3 610 Wing lower
65. vironment time limits apply 8 B After the operating usage and the operating environment are determined make a logbook entry that states which inspection schedules TYPICAL or SEVERE operating usage and MILD MODERATE or SEVERE operating environment are being used D2000 9 13 Temporary Revision Number 9 May 18 2015 2A 10 00 Page 1 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 180 185 SERIES 1969 1980 SERVICE MANUAL 3 Description NOTE Listed below is a detailed description and intended purpose of the following sections A B Section 2A 10 00 Time Limits Maintenance Checks General This section provides a description and purpose of the inspection time intervals Section 2A 10 01 Inspection Time Limits 1 This section lists in chart format all inspection requirements which must be performed Each page contains the following five columns a Revision Status provides the date that a given item was added deleted or revised A blank entry in this column indicates no change since the reissue of this manual b Inspection Requirements provide a short description of the maintenance item c Inspection Interval indicates the frequency of the item d Applicable Operation s indicates the applicable inspection operation currently containing the inspection item The frequencies corresponding to each operation are listed in Inspection Interval Requirements in this section e Applicable Zone r
66. wal Cessna A Textron Company TEMPORARY REVISION NUMBER 9 DATED 18 MAY 2015 MANUAL TITLE 1969 Thru 1980 Model 180 185 Series Service Manual MANUAL NUMBER PAPER COPY D2000 9 13 TEMPORARY REVISION NUMBER D2000 9TR9 MANUAL DATE 15 September 1972 REVISION NUMBER 9 DATE 2 October 1995 This Temporary Revision consists of the following pages which add to existing pages in the paper copy manual SECTION PAGE SECTION PAGE 2A 10 00 1 Thru 5 2A 10 01 1 Thru 8 2A 12 26 1 2A 12 27 1 2A 13 00 1 Thru 8 2A 14 00 1 Thru 4 2A 14 23 1 Thru 3 2A 30 01 1 Thru 13 REASON FOR TEMPORARY REVISION 1 To add the requirement to use the Severe Inspection Limits for airplanes equipped with floats or skies 2 To add additional SID inspection requirements for the horizontal stabilizer aft attach points 3 To provide revised Corrosion Severity Maps in Section 24 30 01 FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION 1 For Paper Publications file this cover sheet behind the publication s title page to identify inclusion of the temporary revision in the manual Insert the new pages in the publication at the appropriate locations 2 For CD Publications mark the temporary revision part number on the CD label with permanent red marker This will be a visual identifier that the temporary revision must be referenced when the content of the CD is being used Temporary revisions should be collected and maintained in a notebook or binder near the CD libra

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