D2064-1TR8 - Cessna Support
Contents
1. Europe and Asia Minor Corrosion Severity Map Figure 6 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 12 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL A91676 All South Pacific Islands Severe g Es gt CORROSION SEVERITY LEGEND gt d 2 MILD MODERATE 7 SEVERE Ha South Pacific Corrosion Severity Map Figure 7 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 13 Cessna Aircraft Company Oct 2 19952. 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 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 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 10 01 Page 4 O Cessna Aircraft Company Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TASK Areas of the cabin structure Make sure you inspect 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
3. The 10 fittings are heat treated after welding and so cannot be rewelded and used without subsequent heat treatment Repairs may be made in accordance with Section 17 Structural Repair of the applicable Model 152 Service Manual Any repair not available in Section 17 should be coordinated with Cessna Customer Service prior to beginning the repair 8 COMMENTS D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 14 11 Page 2 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL B18022 VERTICAL STABILIZER 0432001 56 STABILIZER SPAR DETAIL A 0432005 2 FITTING 0431009 0432004 BRACKET 0432001 15 REINFORCEMENT 0432005 1 FITTING DETAIL C DETAIL B 0410T1003 VERTICAL STABILIZER ATTACH BRACKET AND HORIZONTAL STABILIZER REAR SPAR ATTACHMENT INSPECTION Figure 1 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company 2A 14 11 Page 3 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL SUPPLEMENTAL INSPECTION NUMBER 55 11 03 TITLE Vertical Fin Attach Bracket Inspection EFFECTIVITY 15279406 thru 15286033 F15201449 thru F15201980 A15200735 thru A15201049 FA1520337 thru FA1520425 INSPECTION COMPLIANCE ALL USAGE INITIAL 100 Hours OF 1 Year NOTE REPEAT 100 Hours or 1 Year NOTE NOTE Refer to Note 1 Section 2A 14 00 PURPOSE To inspect the vertical stabilizer rear spar attachments for sig
4. May 18 2015 Title Nut Plate Inspection Vertical Fin Attach Bracket for units 15279406 thru 15284541 F15201429 thru F15201808 681 A1500433 A1520735 thru 1520943 FA1520337 thru FA1520372 Rudder Stop Modification Vertical Tail Attach Bracket and Aft Horizontal Stabilizer Spar Inspection for units 15279406 thru 15284541 F15201429 thru F15201808 A1500433 A1520735 thru 1520943 681 FA1520337 thru FA1520372 Floorboard Seat Pan Crack Inspection Aileron Hinge Inspection Rudder Spar Inspection Replacement Flap Support Inspection and Roller Washer Installation AN3 5A Bolt Inspection Replacement O Cessna Aircraft Company Associated Service Kit SK152 24A SK152 25A SK180 44 2A 14 00 Page 1 Oct 2 1995 2 Supplemental Inspections DETAILS FOUND SUPPLEMEN IN SECTION TAL INSPEC 2 14 XX TION NUMBER 2A 14 01 27 20 01 2A 14 02 27 30 01 2A 14 03 32 13 01 2A 14 04 32 13 02 2A 14 05 32 20 01 2A 14 06 53 11 01 2A 14 07 53 30 01 2A 14 08 53 47 01 2A 14 09 55 10 01 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TITLE Rudder Pedal Torque Tube Inspection Elevator Trim Pulley Bracket and Actuator Bracket Structure Inspection Landing Gear Spring Corrosion Inspection Main Landing Gear Fittings Inspection Nose Gear Torque Link and Fork Inspection Carry Thru Structure Corrosion Inspection Fuselage Interior Skin Panels Corrosion Inspection Seat Rails and Seat Rail Struct
5. May 18 2015 2A 14 22 Page2 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 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 A simple 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
6. bearing D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 10 01 Page7 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS Rudder structure Make sure you inspect these areas Every 24 months 3 320 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 Engine support structure Make sure you inspectthese Every 12 months 2 120 areas 1 Engine truss Pay particular attention to vicinity of welds NOTE Corrosion Prevention and Control Program Inspection item refer to Section 2A 30 00 for additional inspection information Vertical Fin Inspect the vertical fin attachment Every 100 hours or 1 22 320 Refer to Section 2A 14 22 Supplemental Inspection year Document 55 11 03 for inspection procedure D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 10 01 Page 8 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL INSPECTION OPERATION 22 Date Registration Number Serial Number Total Time 1 Description A Operation 22 gives 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 y
7. 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 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page5 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 fungus 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 wil
8. 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 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 for corrosion and missing or loose fasteners Refer to Section 2A 14 15 Supplemental Inspection Document 57 11 02 for inspection procedure This interval is for severe corrosion environment Inspect wing for corrosion and missing or loose fasteners Refer to Section 2A 14 15 Supplemental Inspection Document 57 11 02 for inspection procedure This interval is for mild moderate usage environment Inspect wing splice joint at strut attach Refer to Section 2A 14 16 Supplemental Inspection Document 57 11 03 for inspection procedure This interval is for severe usage environment Inspect wing splice joint at strut attach Refer to Section 2A 14 16 Supplemental Inspection Document 57 11 03 for inspection procedure This interval is for mild moderate corrosion environment Inspect wing root rib Refer to Section 2A 14 17 Supplemental Inspection Document 57 12 01 for inspection procedure This interval is for severe corrosion environme
9. 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 impractical to replace an assembly or component contact an authorized repair shop D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 becom
10. 0 hours 9 520 hinge and pushrod attach fittings Refer to Section 2A or 10 years repeat 620 14 19 Supplemental Inspection Document 57 51 01 500 hours or 5 years for inspection procedure This interval is for mild moderate corrosion Initial 20 years 11 510 environment Inspect flap tracks for corrosion repeat 10 years 610 Refer to Section 2A 14 20 Supplemental Inspection Document 57 53 01 for inspection procedure This interval is for severe corrosion environment Initial 10 years 13 510 Inspect flap tracks for corrosion Refer to Section repeat 5 years 610 2A 14 20 Supplemental Inspection Document 57 53 01 for inspection procedure Inspect tubular engine mount Refer to Section 2A 14 Initial 5 000 hours or 10 120 21 Supplemental Inspection Document 71 20 01 for 20 years repeat At inspection procedure Engine Overhaul Fuselage lower internal structure beneath the floor Every 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 24 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
11. Corrosion Inspection Engine Mount Inspection Vertical Fin Attach Bracket INSPECTION COMPLIANCE INSPECTION Refer to Note 1 OPERATION INITIAL REPEAT MILD MILD 11 MODERATE MODERATE 20 Years 10 Years SEVERE 10 SEVERE 5 13 Years Years 5 000 Hours At Engine 10 or 20 Years Overhaul 100 Hours or 100 Hours or 22 1 Year 1 Year Time limits for the INITIAL inspections are set by either flight hours or calendar time whichever Except for Section 2A 14 21 Supplemental Inspection 71 20 01 corresponding 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 D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company 2A 14 00 Page 4 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL SUPPLEMENTAL INSPECTION NUMBER 55 11 02 1 TITLE Vertical Stabilizer Attach Bracket and Horizontal Stabilizer Rear Spar Attachment Inspection 2 EFFECTIVITY 15279406 thru 15286033 F15201449 thru F15201980 A15200735 thru A15201049 FA15200337 thru FA1520425 INSPECTION COMPLIANCE ALL USAGE INITIAL 2 000 Hours Or 4 Years NOTE REPEAT 2 000 Hours or 4 Years NOTE NOTE Refer to Note 1 Section 2A 14 00 3 PURPOSE To inspect the ve
12. MANUAL TITLE i Cessna A Textron Company TEMPORARY REVISION NUMBER 8 DATED 18 MAY 2015 Model 152 Series 1978 Thru 1985 Service Manual MANUAL NUMBER PAPER COPY D2064 1 13 TEMPORARY REVISION NUMBER D2064 1TR8 MANUAL DATE 7 February 1985 REVISION NUMBER 1 DATE 2 October 1995 This Temporary Revision consists of the following pages which add to existing pages in the paper copy manual SECTION 2A 10 01 2A 12 22 2A 14 00 2A 14 11 2A 14 22 2A 30 01 PAGE 1 thru 8 1 1 thru 4 1 thru 3 1 thru 2 1 thru 13 REASON FOR TEMPORARY REVISION 1 To add additional SID inspection requirements for the vertical stabilizer on 152 model series airplanes 2 To provide revised Corrosion Severity Maps in Section 2A 30 01 FILING INSTRUCTIONS FOR THIS TEMPORARY REVISION 1 For Paper Publications file this cover sheet behind the publication s title page to identify the inclusion of the temporary revision into the manual Insert the new pages into the publication at the appropriate locations and discard the superseded pages 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 library for quick reference EXPORT COMPLIANCE 1 This publication contains technical data
13. NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information 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 Elevator Trim 1 Check elevator trim travel and cable tension 2 Check elevator trim cable system control cables and pulleys in accordance with the flight cable inspection procedures in Section 2A 20 01 Expanded Maintenance Control Cables 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 Wing structure internal Make sure you inspect these areas 1 Main spar upper and lower carry thru fittings 2 Main spar upper and lower ca
14. ON PAINTED HIGHLY MAGNIFIED 65911001 SURFACE ooo 62911013 62916004 Corrosion Figure 1 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 3 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 Internal 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 Corros
15. amps 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 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
16. 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 152 SERIES 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 Inspect rudder pedal torque tube shafts support brackets and cable attachment arms Refer to 2A 14 01 Supplemental Inspection Document 27 20 01 for inspection procedure Elevator trim system 1 Inspect elevator trim brackets and actuator support brackets 2 Inspect pulleys attaching structure and fasteners Refer to Section 2A 14 02 Supplemental Inspection Document 27 30 01 for inspection procedures This inspection is for mild moderate corrosion environment Inspect main landing gear tubular spring for rust or damage to finish Inspect entr
17. 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 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 2 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL pee HIGH OXYGEN HIGH 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 oi 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 CORROSI
18. e aft side of the bracket 4 Visually inspect 0432001 56 spar for cracks near bracket and reinforcement attach area Remove the inspection plate on the top surface of the horizontal stabilizer and use a borescope to inspect the forward side of 0432001 56 spar D Detailed Inspection 1 If no cracks are found on 0432004 bracket during visual inspection conduct a surface eddy current inspection If no cracks are found during the surface eddy current inspection proceed to 4 E below 2 Conduct a surface eddy current inspection of 0432001 15 horizontal rear spar reinforcement where the 0432004 bracket attaches If no cracks are found during the surface eddy current inspection proceed to 4 E below 3 Remove 0432001 15 rear spar reinforcement and conduct a surface eddy current inspection of 0432001 56 spar where the 0432004 and 0432001 15 are installed E Install all removed parts Refer to the applicable Model 152 Service Manual D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 14 11 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL 5 ACCESS AND DETECTABLE CRACK SIZE ACCESS LOCATION DETECTABLE CRACK SIZE Rudder Not Allowed 6 INSPECTION METHOD Visual and Eddy Current 7 REPAIR MODIFICATION Replace damaged or cracked parts 0431009 1 and 2 brackets may be replaced with 0431009 3 brackets 0432004 1 or 9 fittings have been replaced by 0432004 10 fittings
19. e 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 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 f
20. ear whichever occurs first after the initial inspection has been accomplished 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 rudder spar Refer to Section 2A 14 13 320 Supplemental Inspection Document 55 41 01 for inspection procedure Inspect the vertical fin attachment Refer to Section 320 2A 14 22 Supplemental Inspection Document 55 11 03 for inspection procedure End of Operation 22 Inspection Items kkk D2064 1 13 Tempora
21. ese areas 1 Nose gear axle and attach bolt 2 Wheel halves NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information NOTE Disassemble the nose gear strut to get access NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor to the sliding surfaces of the oleo strut NOTE Coordinate with tire change Horizontal stabilizer structure Make sure you inspect Every 60 months 6 330 these areas 1 Stabilizer attachment to the tailcone 340 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 Elevator trim system Make sure you inspect these Every 24 months 3 330 areas 1 Elevator trim brackets 2 Actuator support 340 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 3 320 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
22. ion 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 3596 sulfuric acid and 6596 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 Ifcorrosion appears use an approved repair method to repair the structure 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 Ifthe 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 wi
23. l 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 components 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 acco
24. mon Agricultural operations On floats INI gt IOIA D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page7 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL A91671 Montreal Severe Toronto Moderate NS Y S pf 4 GE Walter Severe 5 yy Y SS S N Ss N NS R RN NS 7 New York City ES MN AS 8 1 Y X RARAN Ts CIS gt Los Angeles IS 7 A Hawaiian Island C A j y Severe IN pese Caribbean a Houston 7 Islands amp do a Bermuda Q NGS Y QN Severe Monterey EC N Guadalajara L j Cuba 77 Haiti Mexico City a T 7 Jamaica Dominican Cm a Central America gt Republic CORROSION SEVERITY LEGEND ar ED a MILD MODERATE severe North America Corrosion Severity Map Figure 2 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 8 Oct 2 1995 Cessna Aircraft Company CESSNA AIRCRAFT COMPANY o Yee CORROSION SEVERITY LEGEND MILD MODERATE E SEVERE MODEL 152 SERIES SERVICE MANUAL ae Aruba Netherlands Antilles amp Grenada Trinidad amp Tobago Severe SS z 7 South America Corrosion Severity Map Figure 3 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page9 C Cessna Ai
25. ns of corrosion or cracks INSPECTION INSTRUCTIONS A Visually inspect the vertical stabilizer to horizontal aft spar fitting for cracks or corrosion Refer to Figure 1 1 Clean the area before inspecting if grime or debris is present 2 Pay particular attention to the 0431009 brackets at the radius of the vertical to horizontal flanges of each bracket 3 If a crack is suspected do the following a Do a surface eddy current inspection Refer to Section 2A 13 01 Nondestructive Inspection Methods and Requirements Eddy Current Inspection for additional inspection instructions B Doan inspection ofthe vertical fin attachment nutplates in accordance with the latest revision of SE79 49 C Install all removed parts Refer to the applicable sections of the Model 152 Service Manual ACCESS AND DETECTABLE CRACK SIZE ACCESS LOCATION DETECTABLE CRACK SIZE Vertical Stabilizer Not Allowed INSPECTION METHOD Visual and Eddy Current REPAIR MODIFICATION Replace damaged or cracked parts 0431009 1 and 2 brackets may be replaced with 0431009 3 brackets COMMENTS D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 14 22 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL B20642 VERTICAL STABILIZER DETAIL A 0431009 BRACKET DETAIL B 0410T1003 VERTICAL STABILIZER ATTACH BRACKET INSPECTION Figure 1 Sheet 1 D2064 1 13 Temporary Revision Number 8
26. nt Inspect wing root rib Refer to Section 2A 14 17 Supplemental Inspection Document 57 12 01 for inspection procedure This interval is for typical usage environment Inspect wing strut and strut tube Refer to Section 2A 14 18 Supplemental Inspection Document 57 40 01 for inspection procedure This interval is for severe usage environment Inspect wing strut and strut tube Refer to Section 2A 14 18 Supplemental Inspection Document 57 40 01 for inspection procedure D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company INTERVAL OPERATION ZONE Initial 12 000 hours 18 510 or 20 years repeat 610 2 000 hours or 10 years Initial 6 000 hours 19 510 or 10 years repeat 610 1 000 hours or 5 years Initial 20 years 11 510 repeat 10 years 520 610 620 Initial 10 years 13 510 repeat 5 years 520 610 620 Initial 20 years 11 510 repeat 10 years 610 Initial 10 years 13 510 repeat 5 years 610 Initial 5 years 12 510 repeat 5 years 610 Initial 3 years 21 510 repeat 3 years 610 Initial 12 000 hours 18 510 or 20 years repeat 610 2 000 hours or 10 years Initial 6 000 hours 19 510 or 10 years repeat 610 1 000 hours or 5 years 2A 10 01 Page 3 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS Inspect aileron hinges hinge bolts hinge bearings Initial 3 00
27. orm 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 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
28. osion Prevention 620 and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information Aileron attachments Make sure you inspect these Every 24 months 3 520 areas 1 Aileron hinges 2 Hinge bolts 3 Hinge 620 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 Vertical stabilizer structure Make sure you inspect Every 60 months 6 310 these areas 1 Forward spar attachment to tailcone 320 bulkhead 2 Aft spar attachment to lower 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 Main landing gear axle assembly Make sure you Every 36 months 4 730 inspect these areas 1 Main gear axle and attach 740 bolts 2 Wheel halves NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information NOTE Do not apply LPS 3 Heavy Duty Rust Inhibitor to the bearing NOTE Coordinate with tire change Nose gear trunnion steering assembly torque link Every 36 months 4 720 assembly nose gear fork and axle Make sure you inspect the
29. plice Joint at Strut Attach Inspection Wing Root Rib Corrosion Inspection Strut and Strut Wing Attachment Inspection Aileron Support Structure Inspection D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company INSPECTION COMPLIANCE Refer to Note 1 INITIAL 2 000 Hours or 4 Years 10 000 Hours or 20 Years 100 Hours or 1 Year TYPICAL 12 000 Hours or 20 Years SEVERE 6 000 Hours or 10 Years MILD MODERATE 20 Years SEVERE 10 Years MILD MODERATE 20 Years SEVERE 10 Years MILD MODERATE 5 Years SEVERE 3 Years TYPICAL 12 000 Hours or 20 Years SEVERE 6 000 Hours or 10 Years 3 000 Hours or 10 Years REPEAT 2 000 Hours or 4 Years 3 000 Hours or 5 Years 100 Hours or 1 Year TYPICAL 2 000 Hours or 10 Years SEVERE 1 000 Hours or 5 Years MILD MODERATE 10 Years SEVERE 5 Years MILD MODERATE 10 Years SEVERE 5 Years MILD MODERATE 5 Years SEVERE 3 Years TYPICAL 2 000 Hours or 10 Years SEVERE 1 000 Hours or 5 Years 500 Hours or 5 Years 2A 14 00 Page 3 Oct 2 1995 INSPECTION OPERATION 23 22 18 11 13 11 13 12 21 18 19 DETAILS FOUND SUPPLEMEN IN SECTION 2 14 XX 2A 14 20 2A 14 21 2A 14 22 NOTE 1 occurs first TAL INSPEC TION NUMBER 57 53 01 71 20 01 55 11 03 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TITLE Flap Tracks
30. ps 3 Main spar web 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 areas 1 Wing front spar and lower spar caps 2 Upper and lower wing attach spar fittings 3 Wing lower skins NOTE Corrosion Prevention and Control Program Inspection item baseline interval refer to Section 2A 30 00 for additional inspection information D2064 1 13 Temporary Revision Number 8 May 18 2015 O Cessna Aircraft Company INTERVAL OPERATION ZONE Every 60 months 6 210 Initial 100 hours 24 210 repeat every 600 510 hours or 12 months 610 Initial 100 hours 24 210 repeat every 600 510 hours or 12 months 520 610 620 Initial 100 hours 24 210 repeat every 600 310 hours or 12 months 340 330 Initial 100 hours 24 210 repeat every 600 310 hours or 12 months 340 330 Initial 100 hours 24 210 repeat every 600 310 hours or 12 months 320 Every 12 months 2 510 520 610 620 Every 60 months 6 510 520 610 620 2A 10 01 Page 5 Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS 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 Corr
31. rcraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL A91673 Canary Islands CORROSION SEVERITY LEGEND Johannesburg io Moderate MODERATE Cape Town Durban E SEVERE Africa Corrosion Severity Map Figure 4 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 10 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 T Y MODERATE Y SEVERE Li Asia Corrosion Severity Map Figure 5 Sheet 1 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 11 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL A91675 i3 Reykjavik Helsinki Severe Y SSt Petersburg Moderate London Moderate y t H 27 Paris 7 Marseille 7 m nen G Ly E Y Severe gt AD E Barcelona gt iu yy SI Lisbon d 8 e VAthens e A Ss AU gt A NT Seville Corsica amp A ZKE ZI SS Sardinia Sicily pps Severe Severe CORROSION SEVERITY LEGEND Crete amp Cyprus MILD Severe PIANI MODERATE E SEVERE
32. rding to Section 18 of the Model 152 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 D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page 6 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 location 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 com
33. relative to the remainder of the alloyed sheet This process is conducted at the fabricating mill and the product is called Alclad Model 152 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 152 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 electrochemically 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
34. rtical and horizontal stabilizer rear spar attachments for signs of damage cracks or deterioration 4 INSPECTION INSTRUCTIONS A Do an inspection of the vertical stabilizer to horizontal stabilizer aft spar fitting Refer to Figure 1 Detail B 1 Visually inspect the vertical stabilizer to horizontal stabilizer aft spar fitting for cracks or corrosion a Clean area before inspecting if grime or debris is present b Pay particular attention to the 0431009 brackets at the radius of the vertical to horizontal flanges 2 Do a surface eddy current inspection of the 0431009 brackets at the radius of the vertical to horizontal flanges Refer to Section 2A 13 01 Nondestructive Inspection Methods and Requirements Eddy Current Inspection for additional inspection instructions B Visually inspect the 0432005 1 and 2 fittings that attach the horizontal stabilizer rear spar to the fuselage 1 Inspect for loose screws in the attachment of the fittings to the horizontal stabilizer C Remove 0432004 bracket from 0432001 15 reinforcement and visually inspect the horizontal stabilizer rear spar and vertical stabilizer attach bracket for cracks Refer to Figure 1 1 Clean area before inspecting if grime or debris is present 2 Visually inspect bracket and reinforcement for cracks Use inspection holes to inspect around nut plates on upper and lower flanges 3 Pay particular attention to the edge of the plate welded to th
35. ry Revision Number 8 May 18 2015 2A 12 22 Page 1 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 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 maintenance manual the following service information will be required to complete the SID inspections 2A 14 XX document sections Bulletin SE79 49 SEBO1 01 SEBO03 6 SEBO7 4 SEB87 04 SEB94 03 SEB95 03 SEB96 07 D2064 1 13 Temporary Revision Number 8
36. se areas 1 Nose gear trunnion surface 2 Steering collar and steering collar attach bolt 3 Torque link torque link attach pin and attach bolt 4 Nose gear fork 5 Nose gear axle NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information Nose gear trunnion torque link assembly and nose Every 36 months 4 720 gear fork Make sure you inspect these areas 1 Nose gear trunnion upper and lower inner bore surface and bearing 2 Torque link bolt and attach pin inner bore surface 3 Nose gear fork lug inner bore surface NOTE Corrosion Prevention and Control Inspection Item baseline interval refer to Section 2A 30 00 for additional inspection information D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 10 01 Page 6 O Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL REVI TASK INTERVAL OPERATION ZONE SION STATUS Nose landing gear outer barrel assembly Make sure Every 36 months 4 720 you inspect these areas 1 Outer barrel assembly 2 Upper strut end and lower collar assembly 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 to the sliding surfaces of the oleo strut Nose gear axle assembly Make sure you inspect Every 60 months 6 720 th
37. spection procedures Inspect vertical stabilizer attach bracket and horizontal stabilizer rear spar attachments Refer to Section 2A 14 11 Supplemental Inspection Document 55 11 02 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 rudder spar Refer to Section 2A 14 13 Supplemental Inspection Document 55 41 01 for inspection procedure D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company INTERVAL OPERATION ZONE Initial 20 years 11 210 repeat 10 years Initial 10 years 13 210 repeat 5 years Initial 20 years 11 210 repeat 10 years Initial 10 years 13 210 repeat 5 years Initial 10 years 16 210 repeat 10 years Initial 5 years 17 210 repeat 5 years Initial 10 000 hours 20 330 or 20 years repeat 340 2 000 hours or 4 years Initial 2 000 hours 23 310 or 4 years repeat 320 2 000 hours or 4 years Initial 10 000 hours 7 320 or 20 years repeat 3 000 hours or 5 years Initial 100 hours or 22 320 1 year repeat 100 hours or 1 year 2A 10 01 Page 2 Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TASK This interval is for typical usage environment 1 Inspect inboard wing structure and wing attachment to fuselage including working
38. th 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 aluminum hinge Solid film lubricants are often applied to reduce corrosion problems D2064 1 13 Temporary Revision Number 8 May 18 2015 2A 30 01 Page4 Cessna Aircraft Company Oct 2 1995 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES 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 fit
39. tings 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 surfaces 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 cl
40. tion is for mild moderate corrosion environment Inspect carry thru spar area wing attach fittings spar channel and lugs Refer to Section 2A 14 06 Supplemental Inspection Document 53 11 01 for inspection procedure This interval is for severe corrosion environment Inspect carry thru spar area wing attach fittings spar channel and lugs Refer to Section 2A 14 06 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 2A 14 07 Supplemental Inspection Document 53 30 01 for inspection procedure This interval is for severe corrosion environment Inspect the cabin interior skin panels frames and stringers Refer to Section 2A 14 07 Supplemental Inspection Document 53 30 01 for inspection procedure This interval is for mild moderate corrosion environment Inspect seat rails for corrosion Refer to Section 2A 14 08 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 08 Supplemental Inspection Document 53 47 01 for inspection procedure Inspect horizontal stabilizer and elevator including torque tube spars ribs hinge bolts hinge bearings brackets and attach fittings Refer to Section 2A 14 09 Supplemental Inspection Document 55 10 01 for in
41. ure Corrosion Inspection Horizontal Stabilizer Elevators and Attachments Inspection D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company INSPECTION COMPLIANCE Refer to Note 1 INITIAL REPEAT 10 000 Hours 3 000 Hours or 20 Years or 5 Years 1 000 Hours 1 000 Hours MILD MILD MODERATE MODERATE 20 Years 10 Years SEVERE 10 SEVERE 5 Years Years 3 000 Hours 1 000 Hours or 5 Years or 5 Years 3 000 Hours 3 000 Hours or 5 Years or 5 Years MILD MILD MODERATE MODERATE 20 Years 10 Years SEVERE 10 SEVERE 5 Years Years MILD MILD MODERATE MODERATE 20 Years 10 Years SEVERE 10 SEVERE 5 Years Years MILD MILD MODERATE MODERATE 10 Years 10 Years SEVERE 5 SEVERE 5 Years Years 10 000 Hours 2 000 Hours or 20 Years or 4 Years INSPECTION OPERATION 14 11 13 15 11 13 11 13 16 17 20 2A 14 00 Page 2 Oct 2 1995 DETAILS FOUND SUPPLEMEN IN SECTION TAL INSPEC 2 14 XX TION NUMBER 2A 14 11 55 11 02 2A 14 12 55 30 01 2A 14 13 55 41 01 2A 14 14 57 11 01 2A 14 15 57 11 02 2A 14 16 57 11 03 2A 14 17 57 12 01 2A 14 18 57 40 01 2A 14 19 57 51 01 CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TITLE Vertical Stabilizer Attach Bracket and Horizontal Stabilizer Rear Spar Attachment Inspection Vertical Stabilizer Rudder and Attachments Inspection Rudder Spar Inspection Wing Structure Inspection Wing Structure Corrosion Inspection Wing S
42. y step attachment Refer to Section 2A 14 03 Supplemental Inspection Document 32 13 01 for inspection procedure This interval is for severe corrosion environment Inspect main landing gear tubular spring for rust or damage to finish Inspect entry step attachment Refer to Section 2A 14 03 Supplemental Inspection Document 32 13 01 for inspection procedure Inspect main landing gear fittings and attachment of the fittings to the bulkheads Refer to Section 2A 14 04 Supplemental Inspection Document 32 13 02 for inspection procedure Inspect nose landing gear torque links bolts bushings and fork Refer to Section 2A 14 05 Supplemental Inspection Document 32 20 01 for inspection procedure D2064 1 13 Temporary Revision Number 8 May 18 2015 Cessna Aircraft Company INTERVAL OPERATION ZONE Every 100 hours or 1 z 12 months Every 100 hours or 1 12 months Every 100 hours or 1 5 12 months Every 100 hours or 1 2 12 months Initial 10 000 hours 7 211 or 20 years repeat 3 000 hours or 5 years Initial 1 000 hours 14 330 repeat 1 000 hours 340 Initial 20 years 11 730 repeat 10 years 740 Initial 10 years 13 730 repeat 5 years 740 Initial 3 000 hours 15 210 or 5 years repeat 1 000 hours or 5 years Initial 3 000 hours 8 720 or 5 years repeat 3 000 hours or 5 years 2A 10 01 Page 1 Oct 2 1995 REVI SION STATUS CESSNA AIRCRAFT COMPANY MODEL 152 SERIES SERVICE MANUAL TASK This inspec
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