Service Letter Cql-99-02

Conquest SERVICE LETTER CQL-99-02

TITLE MISCELLANEOUS - ANNOUNCE TWO TEMPORARY REVISIONS TO MODEL 441 CONQUEST/CONQUEST II MAINTENANCE MANUAL

EFFECTIVITY MODEL SERIAL NUMBERS 441 441-0001 thru 441-0362 REASON To announce two temporary revisions to the Model 441 Conquest/Conquest II Maintenance Manual. DESCRIPTION The two temporary revisions to the Model 441 Conquest/Conquest II Maintenance Manual are available. Refer to the Reason For Temporary Revision sections for additional details, particularly the addition of the initial interval inspection of 2,000 hour or 4 years for the Emergency Exit Door Bond Inspection. Airplanes that have more than 2,000 hours have 50 flight hours to comply with the initial inspection. 1. Temporary Revision Number D2518-16TR5-8 2. Temporary Revision Number D2518-16TR20-1 NOTE: As a convenience, service documents are now available online to all our customers through a simple, free-of-charge registration process. If you would like to sign up, please visit the Customer Access link at www.txtavsupport.com to register.

COMPLIANCE INFORMATIONAL. This service document is for informational purposes only. A service document published by Textron Aviation may be recorded as completed in an aircraft log only when the following requirements are satisfied: 1) The mechanic must complete all of the instructions in the service document, including the intent therein. 2) The mechanic must correctly use and install all applicable parts supplied with the service document kit. Only with written authorization from Textron Aviation can substitute parts or rebuilt parts be used to replace new parts. 3) The mechanic or airplane owner must use the technical data in the service document only as approved and published. 4) The mechanic or airplane owner must apply the information in the service document only to aircraft serial numbers identified in the Effectivity section of the document. 5) The mechanic or airplane owner must use maintenance practices that are identified as acceptable standard practices in the aviation industry and governmental regulations. No individual or corporate organization other than Textron Aviation is authorized to make or apply any changes to a Textron Aviation-issued service document or flight manual supplement without prior written consent from Textron Aviation. Textron Aviation is not responsible for the quality of maintenance performed to comply with this document, unless the maintenance is accomplished at a Textron Aviation-owned Service Center.

CQL-99-02 January 21, 2021 Page 1 of 2

Textron Aviation Customer Service, P.O. Box 7706, Wichita, KS 67277, U.S.A. 1-316-517-5800 This document 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 COPYRIGHT © 2021 Conquest SERVICE LETTER CQL-99-02

CONSUMABLE MATERIAL No specialized consumable materials are required to complete this service document.

TOOLING No specialized tooling is required to complete this service document.

REFERENCES Model 441 Conquest/Conquest II Maintenance Manual

Temporary Revision Number D2518-16TR5-8

Temporary Revision Number D2518-16TR20-1

NOTE: To make sure all publications used are complete and current. Refer to www.txtavsupport.com.

PUBLICATIONS AFFECTED None

CQL-99-02 Page 2 January 21, 2021 TEMPORARY REVISION NUMBER 5-8

DATED 1 FEBRUARY 2021

MANUAL TITLE Model 441 Conquest/Conquest II Maintenance Manual MANUAL NUMBER - PAPER COPY D2518-16-13 TEMPORARY REVISION NUMBER D2518-16TR5-8

MANUAL DATE 1 August 1977 REVISION NUMBER 16 DATE 1 June 2007

This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper copy manual.

SECTION REMOVE PAGES INSERT PAGES 5-10-00 - Inspection 1 thru 4 1 thru 4 5-10-01 - Inspection Time Limits 1 thru 45 1 thru 45 5-12-58 - Inspection Phase 58 n/a 1 5-14-00 - Listing of Supplemental Inspections 1 thru 7 1 thru 7 5-14-52 - Supplemental Inspection Number 52-20-05 n/a 1 5-15-52 - Supplemental Inspection Number 52-20-03 n/a 1 thru 5

REASON FOR TEMPORARY REVISION 1. 5-10-00 - added Interval BD, Inspection Phase 58. 2. 5-10-01 - added Item Code Number A522005, inspection of the Emergency Exit Door Bond. 3. 5-12-58 - added Inspection Phase 58, a 2000 hour or 4 year interval, A522005 Emergency Exit Door Bond inspection requirement. 4. 5-14-00 - added Section 5-14-52, SID 52-20-05, inspection of the Emergency Exit Door Bond inspection. 5. 5-14-52 - added the Emergency Exit Door Bond Inspection with an initial inspection at 2000 hours or 4 years and a recurring interval of 2000 hours or 4 years. 6. 5-15-52 - added detailed Ultrasonic Bond Inspection procedures for the Emergency Exit Door Bond Inspection. 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 and remove 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. The export of these commodities, technology or software are subject to the US Export Administration Regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to US law is prohibited. For guidance on export control requirements, contact the Commerce Department's Bureau of Export Administration at 202-482-4811 or visit the US department of Commerce website.ECCN: 9E991

© TEXTRON AVIATION INC. PROPRIETARY RIGHTS NOTICE 1. These data are proprietary to Textron Aviation Inc. Use of this publication or any of the data contained herein for any purpose other than direct aircraft operation or maintenance is prohibited without prior written authorization from Textron Aviation Inc. Reproduction or redistribution of this publication in whole or in part is prohibited.

INSPECTIONS

1. General A. General inspection criteria. (1) During accomplishment of each of the specific inspections listed in this chapter, additional general inspections of surrounding areas should be performed while access is available. These general inspections are intended to detect obvious conditions which may warrant further action. (2) When an area is exposed, wire bundles should be inspected for chafing, proper security, and support. Verify that wire bundles are not secured to hydraulic tubes or lines. (3) Inspection items listed are for specific components and systems. However, the entire inspection program requires and expects a high degree of professionalism and judgment on the part of inspection personnel to ensure that all components and systems are maintained and inspected to verify highest safety standards. (4) If a component or system is disturbed (due to maintenance being performed) after completion of an initially required operational or functional test, then that specific test must be reconfirmed after completion of any maintenance, prior to returning system or component to service. Refer to appropriate chapter in this Maintenance Manual for removal, installation, operational tests, and functional tests of components and/or systems. (5) For items or components requiring lubrication as applicable, refer to Chapter 12, Scheduled Servicing - Description and Operation, for lubricant, lubricating points, and method. (6) Refer to Chapter 6, Airplane Zoning - Description and Operation, for airplane zone definition. (7) Conduct a preflight inspection upon completion of the applicable inspection to ensure all required items are properly serviced. Refer to Approved Airplane Flight Manual.

2. Interval and Phase Cross-Reference for Inspection Time Limits

INTERVAL PHASE DESCRIPTION OF INTERVAL A Not used B 2 Every 100 hours or 12 calendar months, whichever occurs first. C 3 Every 200 hours or 12 calendar months, whichever occurs first. D 4, 5, 6, D Every 600 hours or 24 calendar months, whichever occurs first. E 7 Every 600 hours or 18 calendar months, whichever occurs first. F 8 First 1900 hours and every 600 hours thereafter. G 9 Every 1000 hours. H Not used J 11 First 1300 hours and every 1200 hours thereafter. K 12 Every 2 years. L 13 Every 3 years. M 14 Every 5 years. N Not used O 16 Every 400 hours. P 17 Every 900 hours. Q 18 First 4000 hours and every 2000 hours thereafter.

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INTERVAL PHASE DESCRIPTION OF INTERVAL R 19 First 5000 hours and every 2000 hours thereafter. S 20 First 6000 hours and every 2000 hours thereafter. T Not used U 23 First 4000 hours and every 200 hours thereafter. V 24 First 4000 hours and every 400 hours thereafter. W 25 Every 3000 hours. X 26 Every 12 years. Y 27 Every 6 years. Z 28 First 3000 hours and every 2,000 hours thereafter. Refer to CQB91-1. AA 29 At the first 10,000 hours or 20 years, whichever occurs first, and every 2500 hours or 5 years thereafter, whichever occurs first. AB 30 At the first 7500 hours or 15 years, whichever occurs first, and every 2500 hours or 5 years thereafter, whichever occurs first. AC 31 At the first 5000 hours or 10 years, whichever occurs first, and every 1000 hours or 3 years thereafter, whichever occurs first. AD 32 At the first 10,000 landings or 15 years, whichever occurs first, and every 2000 landings or 4 years thereafter, whichever occurs first. AE 33 At the first 10,000 landings or 15 years, whichever occurs first, and every 1000 landings or 3 years thereafter, whichever occurs first. AF 34 Refer to CQB91-09 for the inspection initial and repeat intervals. AG 35 At the first 7500 landings or 15 years, whichever occurs first, and every 1000 landings or 3 years thereafter, whichever occurs first. AH 36 At the first 15,000 landings or 15 years, whichever occurs first, and every 5000 landings or 10 years thereafter, whichever occurs first. AI 37 At the first 7500 landings or 15 years, whichever occurs first, and every 2000 landings or 4 years thereafter, whichever occurs first. AJ 38 Refer to CQB00-03 for the inspection initial and repeat intervals. AK 39 At the first 7500 landings or 15 years, whichever occurs first, and every 2500 landings or 5 years thereafter, whichever occurs first. AL 40 Refer to CQB03-01 for the inspection initial and repeat intervals.

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INTERVAL PHASE DESCRIPTION OF INTERVAL AM 41 At the first 4000 hours or 8 years, whichever occurs first, and every 2000 hours or 4 years thereafter, whichever occurs first.

NOTE: Some inspections require a more frequent inspection interval after the accumulation of 12,000 flight hours. Refer to each Supplemental Inspection Document for repeat inspection information for airplanes with more than 12,000 flight hours. AQ 45 At the first 3000 hours or 6 years, whichever occurs first, and every 3000 hours or 6 years thereafter, whichever occurs first. AR 46 At the first 15,000 hours or 20 years, whichever occurs first, and every 3000 hours or 6 years thereafter, whichever occurs first. AS 47 At the first 15,000 hours or 20 years, whichever occurs first, and every 2500 hours or 5 years thereafter, whichever occurs first. AT 48 At the first 5000 hours or 10 years, whichever occurs first, and every 1000 hours or 2 years thereafter, whichever occurs first. AU 49 At the first 15,000 hours or 20 years, whichever occurs first, and every 1500 hours or 3 years thereafter, whichever occurs first. AV 50 At the first 1000 hours or 3 years, whichever occurs first, and every 1000 hours or 3 years thereafter, whichever occurs first. AW 51 Every 600 hours of operation AX 52 Corrosion Program Inspections (Baseline Program) items that are to be examined every 24 months. Refer to 5-30-00, Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals. AY 53 Corrosion Program Inspections (Baseline Program) items that are to be examined every 36 months. Refer to 5-30-00, Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals.

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INTERVAL PHASE DESCRIPTION OF INTERVAL AZ 54 Corrosion Program Inspections (Baseline Program) items that are to be examined every 48 months. Refer to 5-30-00, Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals. BA 55 Corrosion Program Inspections (Baseline Program) items that are to be examined every 60 months. Refer to 5-30-00, Corrosion Prevention and Control Program for additional information concerning repeat Corrosion Program Inspection intervals. BB 56 At the first 20 years (mild environment) or 10 years (moderate/severe environment) and every 5 years (mild environment) or 3 years (moderate/severe environment) thereafter. Refer to 51-12-00, Corrosion Severity Maps - Description and Operation for additional information concerning corrosion environments. BC 57 At the first 7000 hours or 15 years, whichever occurs first, and every 1000 hours or 3 years thereafter, whichever occurs first.. BD 58 Every 2000 hours or 4 years, whichever occurs first, and every 2000 hours or 4 years thereafter, whichever occurs first..

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INSPECTION TIME LIMITS

1. Inspection Items

REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A112001 Exterior Placards, Decals, and D 4, D All Zones Jun 1/07 Markings - Inspect for security of installation and legibility. A112002 Airplane ID Plate - Inspect for security D 4, D 321 of installation and legibility. Revised A113001 Interior Placards and Decals - Inspect D 5, D All Zones Jun 1/07 for security of installation and legibility. B211001 Bleed Air Firewall Shutoff Valves - C 3 ENG Perform operational check of left and right valves. Revised A212001 Windshield Defog Blowers - Check D 5, D 231, 232 May 2/94 for security of installation. Revised A212002 Cabin Ventilation Fan - Inspect fan D 5, D 151 May 2/94 assembly for security of installation, evidence of damage, air leaks at air duct connections. A212003 Nose Ram Air Valve - Check for D 4, D 132 security and proper operation. B213001 Emergency Pressurization System - C 3 ENG Perform an operational test. Refer to Chapter 21, Compression System - Maintenance Practices. B213002 Cabin Pressurization System - D 5, D ENG Perform an operational test. Refer to Chapter 21, Pressurization Control System - Adjustment/Test, Pressurization System Operational Test. A213003 Outflow Valve and Safety Valve - D 5, D 172 Inspect for security of installation; check line assemblies for proper installation on fittings; check for broken diaphragm retention ring and evidence of damage. B213004 Cabin Altitude Barometric Pressure D 5 222 Switch - Complete a functional test of the switch. Refer to Chapter 21, Pressurization Control System - Maintenance Practices for functional test instructions.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A213004 Outflow Valve and Safety Valve - D 5, D 172 Clean units and filters. Refer to Chapter 21, Pressurization Control System - Maintenance Practices, Cleaning/Painting. D213005 Outflow and Safety Valve Static Ports D 4, D 312 - Inspect pressurization static ports for obstruction and evidence of damage. A213006 Emergency Pressurization Valve D 6, D 612 - Inspect valve for security of installation and evidence of damage. Inspect electrical wires at valve for evidence of damage. A213007 Ejector Pump - Inspect for security of D 6, D 612 installation, evidence of damage and plugged vent line. A213008 Pressurization Air Controller - Inspect D 5, D 243 controller for security and evidence of damage. Clean filter. Revised A213009 Pressurization Volume Tank - Inspect D 5, D 248 May 2/94 for security of installation and evidence of damage. A213010 Vacuum Regulator - Inspect for D 5, D 162 security of installation and evidence of damage. A213011 Pressurization Solenoid Valves - D 5, D 162, 172 Inspect for security of installation and evidence of damage. B215001 Environmental System - Perform D 4, D ENG an operational test of the air cycle machine. Refer to Chapter 21, Cooling System - Maintenance Practices, Air Conditioning System Operational Test. D215002 Air Cycle Machine Oil - Change. D 4, D 132 A215002 Air Cycle Machine Oil Level- Inspect B 2 132 oil level. A215003 ACM Bypass Valve and Actuator - D 4, D 132 Inspect for security of installation and evidence of electrical component damage. A215004 Air Cycle Machine - Inspect for D 4, D 132 security of installation and evidence of damage. Inspect line from aspirator to water separator for damage. Inspect all plumbing in and out of air cycle machine for security.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A215101 Evaporator Assembly (Freon System) D 5, D 252, 262 - Check for cleanliness and security. A215102 Air Conditioner Compressor Belt D 4, D 311 (Freon System) - Inspect for wear and tension. A215103 Condenser Fan Blade (Freon System) D 4, D 311 - Check blades for nicks and security of installation. A215104 Air Conditioner Condenser (Freon D 4, D 311 System) - Check coils for debris or damage. Revised A215105 Air Conditioning Lines (Freon System) D 5, D 152, 162, May 2/94 - Inspect for evidence of chafing and 172, 311, damage. Inspect for security of 312 installation. A215106 Air Conditioner (Freon System) - D 4, D 350 Inspect dorsal air inlet for obstructions. A215107 Dorsal Fin Air Inlet Water Drain D 4, D 311, 312 (Freon System) - Inspect drain hose for deterioration, chafing and security of installation. Inspect drain hole for obstruction. Revised A216001 Cabin Temperature Sensor and D 5, D 171 May 2/94 Blower - Inspect for cleanliness. A217001 Water Separator - Inspect water D 4, D 132 separator for security of installation. Inspect water separator coalescer bag, clean bag or replace damaged bag. A221001 Aileron Servo Actuator - Inspect for D 5, D 161, 162 security of installation, evidence of damage and evidence of overheating. Inspect electrical components for damage. A222001 Rudder/Yaw Damper Actuator - D 4, D 311 Inspect actuator for security of installation, mount for cracks and structure for evidence of damage. A223001 Elevator Servo Actuator - Inspect for D 4, D 311, 312 security of installation, evidence of damage and overheating. Inspect electrical components for damage. A231001 Antenna (COM 1) - Inspect for D 5, D 141 security of installation and evidence of damage.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A231002 Antenna (COM 2) - Inspect for D 4, D 252 or security of installation and evidence 350 of damage. A231003 Antenna (High Frequency) - Inspect D 4, D 312 for security of installation, corrosion and electrical bond. A232001 Flitefone Antenna - Inspect for D 5, D 171 security of installation, evidence of damage and corrosion. A236001 Control Surface Bond Jumpers - D 6, D 331, 332, Verify integrity of bond connection. 350, 542, 550, 642, 650 Revised A236002 Static Wicks - Inspect for security of D 4, D 331, 332, May 2/94 installation, corrosion and erosion of 350, 542, the tip. 550, 642, 650 D243001 Battery - Recondition. B 2 131 A243002 Battery Cables - Inspect cables C 3 131 for corrosion and deterioration; inspect cable ground for corrosion, cleanliness and cracks to the structure in the vicinity of the ground. Revised A243003 Batteries - Inspect overboard vents B 2 131 May 2/94 and vent lines for damage and obstructions. Revised B243004 Battery Overheat Warning System - C 3 LAB May 2/94 Perform functional test. Revised A243005 Battery Relays - Visually inspect for C 3 131 May 2/94 security of installation and damaged components. A243006 Generator Control Units - Inspect for D 5, D 141 security of installation and evidence of damage. Revised A244001 External Power Receptacle - Inspect D 5, D 171 May 2/94 for security of installation and damage. Revised A245001 All Wire Bundle/Electrical D 4, 5, 6, D All Zones Jul 1/02 Components - Visually inspect electrical components for damage. Visually inspect wiring for damage such as chafing, cuts and cracked insulation. Pay particular attention to the fuel tank boost pump wiring. Revised A245002 Emergency Bus Fuses - Check B 2 131 May 2/94 Condition.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A245003 Side Console (Left) - Inspect all D 5, D 245 internal components for security of installation and damaged electrical components. A245004 Starter Relay Box - Inspect all internal D 5, D 161 components for security of installation and damaged electrical components. A245005 Side Console (Right) - Inspect D 5, D 244 circuit breaker panel for security of installation and damaged electrical components. A251001 Pilot's and Copilot's Seat Track Stops C 3 241, 242 - Inspect for damage and security of installation. Revised A251002 Pilot's and Copilot's Seats - Inspect C 3 241, 242 May 2/94 seat rollers and seat tracks for wear and/or damage; controls for security of installation and operation and seat structure for evidence of damage. A251003 Pilot's and Copilot's Seat Belts - C 3 241, 242 Inspect for security of installation, frayed edges and evidence of damage. Revised A251004 Pilot's and Copilot's Inertia Reel - C 3 241, 242 May 2/94 Inspect for security of installation, evidence of damage. Revised A252001 Passenger Seat Stops - Inspect seat C 3 251, 252, May 2/94 stops for proper location, security of 261, 262 installation and condition. Revised A252002 Passenger Seats - Inspect seat C 3 251, 252, May 2/94 rollers and seat tracks for wear 261, 262 and/or damage; controls for security of installation and operation; seat structure for evidence of damage; seat cushions for damage. Revised A252003 Passenger Seat Belts - Inspect for C 3 251, 252, May 2/94 security of installation, frayed edges 261, 262 and evidence of damage. A255004 Baggage Tiedowns, Receptacles C 3 261, 262 and Straps - Inspect for security of installation and evidence of damage.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A256001 Emergency Locator Beacon (ELT) C 3 312 Transmitter and Antenna - Inspect transmitter and surrounding area for corrosion from battery pack. Inspect transmitter and antenna for security and evidence of damage. Verify battery pack replacement date and position of the function switch. B256001 Locator Beacon System - Perform C 3 BAT operational check. A261001 Fire Detection Sensor Cables - C 3 410, 420 Inspect for security of installation, cleanliness, nicks and abrasions. A261002 Fire Detection Control Units - Inspect D 5, D 245 for security of installation and evidence of damage. D262001 Cockpit and Cabin mounted Halon X 26 LAB type Fire Extinguishers - Perform hydrostatic test. The hydrostatic test shall be at twelve-year intervals based on initial servicing or date of last hydrostatic test. D262002 Cockpit or Cabin mounted Halon type Y 27 LAB Fire Extinguishers - Empty, inspect for damage and recharge. A262003 Fire Extinguisher Agent Deployment C 3 410, 420, Tubes - Inspect for security of 512, 612, installation and outlet for obstruction. 621, 521 Revised D262004 Fire Extinguisher Containers - Inspect C 3 512, 612 May 2/94 for proper pressure, security of installation and damaged electrical connectors and cartridge replacement schedule. Revised D262005 Engine Fire Extinguisher Containers - M 14 512, 612 May 2/94 Perform Hydrostatic Test. A271001 Control Wheels - Inspect control C 3 246, 247 wheels for evidence of damage and security of installation. Revised A271002 Aileron - Visually inspect the aileron C 3 542, 642 May 2/94 skins for cracks and loose rivets; aileron hinges for condition, cracks and security of installation; hinge bolts, hinge attach fittings and bonding jumpers for evidence of damage or wear, failed fasteners and security of installation. Visually inspect the aileron hinge bolts for proper safety of nuts with cotter pins.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A271003 Aileron Quadrant - Visually inspect C 3 542, 642 aileron quadrant for condition, security of installation, corrosion, evidence of damage to quadrant arm stops, bolts and support bracket. Inspect aileron quadrant bolt and stop bolts for proper safety wire installation. A271004 Aileron Actuator Yoke - Visually C 3 542, 642 inspect the aileron actuator yoke, yoke attach bracket, yoke attach bolts for evidence of damage or wear, condition and security. Visually inspect yoke attach bolts for proper safety of nuts with cotter pins. A271005 Aileron Bell Crank - Visually inspect D 5, D 161, 162 bell crank for security of installation, cleanliness, corrosion, evidence of damage to cable attach points. Revised A271006 Aileron Wing Cables - Inspect cables D 6, D 512, 612, May 2/94 for broken wires. Inspect cable 521, 621, fittings for cable slippage, cracks and 532, 632, distortion. Inspect aileron wing cable 542, 642 pulleys for freedom of rotation. Revised A271007 Aileron Fuselage Cables - Inspect D 5, D 231, 232, May 2/94 cables for broken wires. Inspect 141, 142, cable fittings for cable slippage, 151, 152, cracks and distortion. Inspect control 161, 162 wheel chains for condition and proper alignment on the sprockets. Inspect fuselage cable pulleys for freedom of rotation. Check cable tension. Inspect cable turnbuckle safetying. A271008 Aileron Hinges and Fittings - Inspect. AA 29 542, 642 Refer to Chapter 5, Section 5-14-01, Supplemental Inspection Document Number 27-10-05. Revised C271008 Aileron Wing Cable Seals - Inspect D 6, D 151, 152 May 2/94 cable seals for deterioration and lubrication. Revised A271009 Aileron - Check aileron travel. D 5, D 542, 642 May 2/94

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A271010 Elevator attachments. Make sure AX 52 331, 332 you examine these areas: (A.) Hinge brackets. (B.) Hinge bolts. (C.) Hinge bearings. NOTE: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A271011 Elevator torque tube assembly. Make AX 52 331, 332 sure you examine these areas: (A.) Torque tube external and internal surfaces. (B.) Torque tube fitting attachment. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A271012 Rudder attachments. Make sure you AX 52 350 examine these areas: (A.) Hinge brackets. (B.) Hinge bolts. (C.) Hinge bearings. NOTE: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A271013 Rudder torque tube assembly. Make AX 52 350 sure you examine these areas: (A.) Torque tube external and internal surfaces. (B.) Torque tube weld. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A271014 Aileron attachments. Make sure you AX 52 542, 642 examine these areas: (A.) Hinge brackets. (B.) Hinge bolts. (C.) Hinge and pushrod bearings. (D.) Attach fittings. NOTE: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A271015 Ailerons - Check the aileron control AW 51 231, 232, system, wing and fuselage control 141, 142, cables and pulleys in accordance with 151, 152, the Flight Control Cable Inspection 161, 162, procedures in 5-20-01 Expanded 512, 612, Inspection. 521, 621, 532, 632, 542, 642 Revised B271101 Aileron Trim Tab - Check free play. C 3 542 May 2/94 Revised B271102 Aileron Trim Tab Travel - Check D 5, D 542 May 2/94 aileron trim tab travel. A271103 Aileron Trim Tab Actuator - Visually C 3 542 inspect actuator, mounting clamp for cracks and structure for evidence of damage and security of installation. Check actuator mounting bolts for security of installation. Check actuator rod for evidence of bending. Visually inspect push rod bolt at actuator for proper safety of nut with cotter pin. Visually inspect push rod ends for bearing looseness and excessive wear. Revised C271103 Aileron Trim Tab Actuator - Lubricate D 5, D 542 May 2/94 actuator screws. A271104 Aileron Trim Tab Control and Indicator C 3 243 - Inspect control and indicator for security of installation and evidence of damage. Operate control and check aileron trim tab for freedom of movement. Inspect guide block for evidence of damage and security. Inspect chain for condition and proper alignment on sprocket. Revised A271105 Aileron Trim Tab - Visually inspect the C 3 542 May 2/94 trim tab skins for cracks and loose rivets and trim tab hinge for security and evidence of damage. Check hinge pin for proper installation at hinge pin retainer. Inspect horn and push rod for evidence of damage and security of installation and free play. Visually inspect push rod bolts for proper safety of nuts with cotter pins.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A271106 Aileron Trim Wing Cables - Inspect D 5, D 512, 521, May 2/94 cables for broken wires. Inspect cable 532, 542 fittings for cable slippage, cracks and distortion. Inspect aileron trim wing cable pulleys for freedom of rotation. Inspect tab stop blocks for security of installation. Inspect chain for condition and proper alignment on actuator sprocket. A271107 Aileron Trim Fuselage Cables - D 5, D 243, 141, Inspect cables for broken wires. 151, 161 Inspect cable fittings for cable slippage, cracks and distortion. Inspect aileron trim fuselage cable pulleys for freedom of rotation. Inspect cable tension and turnbuckle safetying. Revised C271108 Aileron Trim Cable Seals - Check D 5, D 151, 152 May 2/94 cable seals for deterioration and lubrication. A271109 Aileron Trim - Check the aileron AW 51 243, 141, trim control system, wing and 151, 161, fuselage control cables and pulleys 512, 521, in accordance with the Flight Control 532, 542 Cable Inspection procedures in 5-20-01 Expanded Inspection. A272001 Rudder Pedals - Check rudder pedals, D 5, D 231, 232 brake pedal return springs and rudder for freedom of movement. C272002 Rudder Pedal Linkage - Service. D 5, D 231, 232 C272003 Rudder Pedal Bearing Halves and D 5, D 231, 232 Cockpit Rudder Gust Lock - Service. Revised A272004 Rudder Bell Crank - Inspect bell crank C 3 321, 322 May 2/94 stop bolts for corrosion, evidence of damage and security of installation and that stop bolt cannot be turned by hand. Inspect clevis bolts attached to bell crank for proper cotter pin safetying. Revised A272005 Rudder Cables - Inspect cables for D 5, D 141, 142, May 2/94 broken wires. Inspect cable fittings for 151, 152, cable slippage, cracks and distortion. 161, 162, Inspect rudder fuselage cable pulleys 171, 172, for freedom of rotation. Inspect 311, 312, interconnect spring and guide tube for 321, 322 security of installation. Revised A272006 Rudder Cables - Inspect cable tension D 5, D 311, 312, May 2/94 and turnbuckle safetying. 321, 322

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised C272007 Rudder Cable Seals - Inspect cable D 5, D 311, 312 May 2/94 seals for deterioration and lubrication. Revised A272008 Rudder - Visually inspect the rudder C 3 350 May 2/94 skins for cracks and loose rivets. Inspect rudder hinges for condition, cracks and security of installation. Inspect bolts, hinge bearings, hinge attach fittings and bonding jumper for evidence of damage or wear, failed fasteners and security of installation. Visually inspect the rudder hinge bolts for proper safety of nuts with cotter pins. Check rudder balance weight for looseness. A272009 Rudder Gust Lock (Tailcone) - Inspect D 4, D 321, 322 for security of installation. Revised B272010 Rudder Gust Lock (Tailcone) - Perform D 4, D 321, 322 May 2/94 side load check and check for smooth operation and disengagement at correct elevator travel. Check that locking pin is completely retracted when it is in the UNLOCKED position. Revised A272011 Rudder - Check rudder balance D 5, D 350 May 2/94 weight for looseness. Revised B272012 Rudder - Check rudder travel. D 5, D 350 May 2/94 A272013 Rudder Structure - Inspect. Refer AB 30 350 to Chapter 5, Section 5-14-02, Supplemental Inspection Document Number 27-20-03. A272014 Rudder Torque Tube - Inspect. AB 30 350 Refer to Chapter 5, Section 5-14-03, Supplemental Inspection Document Number 27-20-04. A272015 Rudder - Check the rudder control AW 51 141, 142, system, control cables, and pulleys 151, 152, in accordance with the Flight Control 161, 162, Cable Inspection procedures in 171, 172, 5-20-01 Expanded Inspection. 311, 312, 321, 322

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A272101 Rudder Trim Tab Actuator - Visually C 3 350 May 2/94 inspect actuator for security of installation and evidence of damage. Inspect guide block and clamp for evidence of damage and security of installation. Check actuator mounting bolts for security. Visually inspect pushrod bolt for proper safety of nut with cotter pin. Visually inspect pushrod ends for looseness and excessive wear. Revised C272101 Rudder Trim Tab Actuator - Lubricate D 4, D 350 May 2/94 Actuator Screws. A272102 Rudder Trim Tab Control and Indicator C 3 243 - Inspect control and indicator for security of installation and evidence of damage. Operate control and check rudder trim tab for freedom of movement. Inspect chain for condition and alignment on sprocket. Revised A272103 Rudder Trim Tab Cables - Inspect D 5, D 141, 151, May 2/94 cables for broken wires. Inspect cable 161, 171, fittings for cable slippage, cracks and 243, 311, distortion. Inspect cable pulleys for 321, 350 freedom of rotation. Inspect travel stop blocks for security. Inspect cable tension and turnbuckle for proper safetying. Inspect chain for condition and proper alignment on sprocket. Revised C272104 Rudder Trim Tab Cable Seals - Check D 5, D 311, 312 May 2/94 cable seals for deterioration and lubrication. Revised A272105 Rudder Trim Tab - Visually inspect C 3 350 May 2/94 trim tab skins for cracks and loose rivets and trim tab hinge for security of installation, evidence of damage and hinge pin for proper installation and proper cotter pin safetying at both ends. Inspect horn and pushrod for evidence of damage and security of installation and bearing for looseness. Visually inspect pushrod for proper safety of nut with cotter pin. Revised B272106 Rudder Trim Tab - Check tab free C 3 350 May 2/94 play. Revised B272107 Rudder Trim Tab - Check rudder trim D 5, D 350 May 2/94 tab travel.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A272108 Rudder Trim - Check the rudder trim AW 51 141, 151, control system, control cables, and 161, 171, pulleys in accordance with the Flight 243, 311, Control Cable Inspection procedures 321, 350 in 5-20-01 Expanded Inspection. A273001 Control Column - Inspect bob D 5, D 231, 232, weights, control column for evidence 246, 247 of damage, failed fasteners and security of installation. Revised A273002 Elevators - Visually inspect elevator C 3 321, 322, May 2/94 skins for cracks and loose rivets. 331, 332 Inspect elevator hinges for condition, cracks and security of installation. Inspect hinge bolts, hinge bearings, torque tube horns and horn bearings for evidence of damage, wear and security. Inspect attach fittings and bonding jumpers for evidence of damage or wear, failed fasteners and security of installation. Visually inspect elevator hinge bolts for looseness, proper safety of nuts with cotter pins. Inspect elevator torque tube end assemblies for looseness. Check outboard tips for cracks in the rib flange and web. A273003 Elevator Push-Pull Tubes - Inspect C 3 321, 322 push-pull tubes for looseness at riveted end fittings. If loose, replace push-pull tube. Inspect bearings for looseness and security of installation. A273004 Elevator Bell Crank - Inspect bell C 3 321, 322 crank, push-pull tubes, stop bolts and brackets for corrosion, evidence of damage, failed fasteners and security of installation. Proper safetying of bell crank stop bolts. Push pull tube bolts for proper safety of nuts with cotter pins. Revised B273005 Elevator Horn Bearing Side Play - D 5, D 321, 322 May 2/94 Inspect elevator horn bearing side play. Refer to Elevator - Maintenance Practices, Check Elevator Horn Bearing Side Play. Revised A273006 Elevators - Check elevator balance D 5, D 331, 332 May 2/94 weights for looseness.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A273007 Elevator Cables - Inspect cables for D 5, D 231, 141, May 2/94 broken wires. Inspect cable fittings for 142, 151, cable slippage, cracks and distortion. 152, 161, Inspect elevator fuselage cable 162, 171, pulleys for freedom of rotation. Revised C273008 Elevator Cable Seals - Check cable D 5, D 311, 312 May 2/94 seals for deterioration and lubrication. Revised A273009 Elevator Cables - Inspect cable D 5, D 311, 312 May 2/94 tension and turnbuckle safetying. Revised B273010 Elevator - Check elevator travel. D 5, D 331, 332 May 2/94 Revised C273011 Elevator Hinge Bearing - Lubricate. E 7 331, 332 Jun 1/07 Remove the elevator. Lubricate the hinge bearings. Refer to Chapter 12, 12-20-02 and SNL86-28. Install the elevator. A273012 Elevator Torque Tube Assembly - AC 31 340A Inspect. Refer to Chapter 5, Section 5-14-04, Supplemental Inspection Document Number 27-30-01. A273013 Elevator - Check the elevator control AW 51 231, 141, system, control cables, and pulleys 142, 151, in accordance with the Flight Control 152, 161, Cable Inspection procedures in 162, 171 5-20-01 Expanded Inspection. Revised A273101 Elevator Trim Tabs - Visually inspect C 3 331, 332 May 2/94 trim tab for cracks and loose rivets; trim tab hinge for security of installation and evidence of damage. Inspect hinge pin for proper security. Inspect horn, horn bearing and push rods for evidence of damage, free play and security. Visually inspect push-rod bolts for proper safety of nuts with cotter pins. Verify that pushrod bolt heads are positioned outboard at actuator screw and trim tab horn.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A273102 Elevator Trim Tab Actuators - Visually C 3 331, 332 May 2/94 inspect actuator attach bolts at the rear spar of the horizontal stabilizer. Check that bolts are secure and safety wired in pairs. Looking through the actuator access holes in the horizontal stabilizer, inspect actuator mounting bolt nut plates for cracks and inspect the chain guard for security of installation. Check that guard attach bolts are secure. Check actuator sprockets for condition and security. Compare index marks on sprockets to ensure that they are in the same relative position. Visually inspect actuator bearings (push rod attachment) for evidence of damage and security. Check that slide retainer bolt through actuator housing is safety wired. Inspect the actuator chains for condition. Check chain to cable attach turnbuckle for security and proper safety. Revised C273103 Elevator Trim Tab Cable Seals - D 5, D 171, 172 May 2/94 Check cable seals for deterioration and lubrication. Revised C273104 Elevator Trim Tab Actuators - Service D 5, D 331, 332 May 2/94 (disassembly required). C273105 Elevator Trim Tab Actuators - Service C 3 331, 332 (no disassembly required). Revised B273106 Elevator Trim Tabs - Check elevator D 5, D 331, 332 May 2/94 trim tab travels. A273107 Elevator Trim Tab Control and C 3 243 Indicator - Inspect control and indicator for security of installation and evidence of damage. Operate tab control and check for freedom of movement. Inspect chain for condition and alignment on sprocket. Revised A273108 Elevator Trim Tab Cables - Inspect D 5, D 161 May 2/94 cable tension and turnbuckle safetying. Revised B273109 Elevator Trim Tab - Check tab free C 3 331, 332 May 2/94 play.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A273110 Elevator Trim Tab Cables - Inspect D 5, D 243, 141, Jul 1/02 cables for broken wires. Inspect cable 151, 161, fittings for cable slippage, cracks and 171, 311, distortion. Inspect cable pulleys for 312, 321 freedom of rotation. Inspect travel stop blocks for security of installation. Inspect cable tension and turnbuckle safetying. A273111 Elevator Trim - Check the elevator trim AW 51 231, 141, control system, trim control cables, 142, 151, and pulleys in accordance with 152, 161, the Flight Control Cable Inspection 162, 171 procedures in 5-20-01 Expanded Inspection. A273201 Electric Elevator Trim Actuator D 4, D 311 - Inspect actuator for evidence of damage, damaged electrical components and security of installation. Inspect mount structure for cracks. B273202 Electric Elevator Trim - Operate D 5, D BAT electric trim; check trim travel time. Refer to Chapter 27, Elevator Electric Trim Actuator - Maintenance Practices. A273302 Stall Warning Transmitter - Inspect D 6, D 550 for security of installation, cleanliness, vane operates freely and evidence of damage. Revised A275001 Flap Preselect System - Inspect D 4, D 248, 243, May 2/94 control and indicator for security of 141, 151, installation and evidence of damage. 161 Check cable for deterioration and security of installation. A275002 Flaps - Inspect skin for cracks, loose C 3 513, 613, or failed fasteners and evidence of 532, 632 damage. A275003 Inboard and Outboard Flap Bell D 6, D 513, 532, Cranks and Pushrods - Inspect bell 613, 632 cranks and pushrods for evidence of damage and security of installation. A275004 Flap Idler Bell Crank - Inspect bell D 6, D 513, 613 crank arm for looseness. Revised A275005 Flap Actuator - Check for security D 4, D 161, 162 May 2/94 of installation and for indication of hydraulic fluid leaks.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A275006 Center Flap Bell Crank - Inspect bell D 4, D 161, 162 May 2/94 crank and pushrods for evidence of damage and security of installation. Check pushrod boots for evidence of deterioration and security of installation. Inspect electrical components for evidence of damage and security of installation. A275007 Flap Control Valve and Plumbing D 6, D 512 - Inspect control valve for security of installation and for hydraulic fluid leakage. Check plumbing for security of installation, chafing, routing and for leakage. A275008 Flaps - Inspect flap track rollers, D 6, D 513, 532, pushrods and fittings for evidence 613, 632 of damage or wear and security of installation. B275009 Flaps - Check flap travel. D 6, D 513, 532, 613, 632 A281001 Fuel Vent Scoops - Inspect for C 3 542, 642 evidence of damage, cleanliness and obstructions. A281002 Fuel Tank Area - Inspect the external C 3 512, 513, area for fuel leaks. 521, 531, 532, 541, 542, 612, 613, 621, 631, 632, 641, 642 A281003 Fuel Flapper Check Valves - Inspect J 11 512, 612 Flapper Check Valves for deterioration and proper seating. A282001 Fuel Tank Fillers - Inspect for damage C 3 542, 642 or damaged components. A282002 Fuel Cross feed Valves - Inspect for D 6, D 511, 611 leaks, security of installation and damaged electrical components. Inspect cross feed plumbing for condition, security and leaks. A282003 Cross feed Selector Switch - Inspect D 5, D 231 for security of installation and evidence of damaged electrical components. Revised A282004 Fuel Firewall Shutoff Valves - Inspect D 6, D 521, 621 Jul 1/02 for leaks and security of installation and damaged electrical components.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A284001 Fuel Indicator, Transfer Fail Warning J 11 512, 612 May 2/94 and Low Fuel Level Warning Lights - Functional Test. A284002 Signal Conditioners - Inspect for D 6, D 512, 612 security of installation and evidence of damage to electrical components. A284003 Fuel Quantity Indicating System J 11 512, 521, Probes - Inspect for security of 532, 542, installation and damaged electrical 612, 621, components. 632, 642 B284004 Low Fuel Warning - Perform J 11 512, 612 Functional Test and Dry Tank Calibration. Revised A284005 Low Fuel Warning - Inspect for J 11 512, 612 May 2/94 damaged electrical components. A291001 Hydraulic Pumps - Inspect for leaks, C 3 410, 420 security of installation and damaged hoses. A291002 Hydraulic Reservoir - Inspect for D 6, D 512 leaks, security of installation and cleanliness. Revised B291002 Hydraulic Lines - Perform a Hydraulic F 8 AUX May 2/94 Pressure Lines Leak Test. A291003 Hydraulic Components - Inspect D 6, D 512 plumbing and component mounting for condition, security and system for leaks. A291004 Hydraulic Filter Assemblies - Inspect C 3 410, 420 for leaks and security of installation. D291005 Hydraulic Filter Elements - Replace. D 6, D 410, 420 A301001 Surface Deice System - Check lines D 4, D 312, 331, for condition and clamps for security. 332, 350 A301002 Stall Warning/Angle-of-Attack C 3 550 Transducer - Inspect for evidence of overheating. A301003 Deice Boots - Check for abrasions, C 3 511, 611, cuts, nicks and security of mounting. 531, 631, 541, 641, 550, 650, 331 A301004 Surface Deice System - Check lines D 5, D 141, 142 for condition and clamps for security. 151, 152, 162, 172 A301005 Surface Deice System - Check lines D 6, D 511, 611, for condition and clamps for security. 521, 621

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A302001 Engine Inlet Anti-Ice - Inspect for C 3 410, 420 evidence of damage and tubing for chafing. Inspect pressure switch for security of installation and evidence of damaged electrical components. A303001 Static Ports - Inspect static ports for C 3 261, 262, evidence of overheating. 311, 312 A303002 Pitot Tubes - Inspect for evidence of C 3 121, 122 overheating. B304001 Windshield Bleed Air System - L 13 ENG Functional test. A304002 Windshield Overheat Switch and D 4, D 221 Temperature Sensors - Inspect for security of installation and evidence of electrical damage. A304003 Windshield Anti-Ice System (Alcohol) C 3 222 - Inspect spray tube for security of installation and obstruction. A304004 Windshield Anti-Ice System (Alcohol) D 4, D 222 - Inspect reservoir, pump and plumbing for condition and security of installation. A304005 Windshield Bleed Air Nozzle(s) - C 3 221, 222 Inspect for security, evidence of damage and obstruction to nozzle outlet. Revised A304006 Windshield Bleed Air Solenoid Valve D 4, D 222 May 2/94 (Airplanes -0001 thru -0023) - Inspect for security of installation. Revised A304007 Windshield Bleed Air Solenoid Valve D 4, D 132 May 2/94 (Airplanes -0024 and On) - Inspect for security of installation. A304008 Windshield Bleed Air Regulating Valve D 6, D 612 - Inspect for security of installation. A304009 Windshield Bleed Air Temperature D 5, D 141 Control Unit - Inspect for Security and evidence of damaged electrical components. A304010 Windshield Bleed Air Heat D 4, D 132 Exchangers - Inspect for security and condition. A306001 Propeller Deice Slip Rings, Brushes B 2 410, 420 and Boots - Check for condition and security of attachment.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A321001 Main Landing Gear Assemblies - C 3 720, 730 Inspect the main gear assemblies for security of installation, attach points for wear and condition. Revised A321002 Main Gear Shock Struts - Check C 3 720, 730 May 2/94 for evidence of leakage, check strut barrel for corrosion, pitting and cleanliness. Revised A321003 Main Landing Gear Trunnion - BC 57 720, 730 Dec 1/18 Inspect. Refer to Chapter 5, Section 5-14-05, Supplemental Inspection Document Number 32-10-05. A321004 Main Gear Shock Struts - Inspect. AE 33 720, 730 Refer to Chapter 5, Section 5-14-06, Supplemental Inspection Document Number 32-10-06. A321005 Main Landing Gear Trailing Link - AD 32 720, 730 Inspect. Refer to Chapter 5, Section 5-14-07, Supplemental Inspection Document Number 32-10-07. A321006 Nose wheel well structure. Make AY 53 131, 132 sure you examine these areas: (A.) Webs. (B.) Stiffeners. (C.) Braces. (D.) Brackets. (E.) Support channels. (F.) Structural attachments. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321007 Nose gear outer barrel assembly. AY 53 710 Make sure you examine these areas: (A.) Outer Barrel Surface. (B.) End Upper Strut and Lower Collar Assembly. Corrosion Inspection Descriptions NOTE 1: Disassemble the nose gear strut to get access. NOTE 2: Do not apply LPS-3 Heavy-Duty Rust Inhibitor to the sliding surfaces of the oleo strut. NOTE:3: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A321008 Nose gear inner barrel assembly. AY 53 710 Make sure you examine these areas: (A.) Inner Barrel Surface. (B.) Strut Tube Assembly. NOTE 1: Disassemble the nose gear strut to get access. NOTE 2: Do not apply LPS-3 Heavy-Duty Rust Inhibitor to the sliding surfaces of the oleo strut. NOTE 3: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321009 Nose gear trunnion steering assembly, AY 53 710 torque link assembly, and nose gear fork. Make sure you examine these areas: (A.) Nose Gear Trunnion Surface. (B.) Steering Collar and Steering Collar Attach Bolt. (C.) Torque Link, Torque Link Attach Pin and Attach Bolt. (D.) Nose Gear Fork and Shock Strut Bearing Block. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321010 Nose gear trunnion steering assembly, AY 53 710 torque link assembly, and nose gear fork. Make sure you examine these areas: (A.) Nose Gear Trunnion Upper, Lower Inner Bore Surface and Bearing. (B.) Torque Link Bolt and Attach Pin Inner Bore Surface. (C.) Nose Gear Fork Lug Inner Bore Surface. NOTE 1: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321011 Nose gear axle assembly. Make sure AY 53 710 you examine this area: (A.) Nose Gear Axle and Attach Bolt. NOTE 1: Disassemble the nose gear wheel assembly to get access. NOTE 2: Do not apply LPS-3 Heavy-Duty Rust Inhibitor to the bearing. NOTE 3: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information)

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A321012 Nose gear retraction systems. Make AY 53 710 sure you examine these areas: (A.) Mechanisms. (B.) Bushings. (C.) Bearings (D.) Structural attachments. NOTE 1: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321013 Main gear trunnion assembly. Make AY 53 720, 730 sure you examine these areas: (A.) Main Gear Trunnion External Surface. (B.) Main Gear Trunnion Internal Bore. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321014 Main gear Fork and Axle assembly. AY 53 720, 730 Make sure you examine these areas: (A.) Main Gear Fork and Axle External Surface. (B.) Main Gear Axle Attach Bolt. (C.) Main Gear Fork and Axle Internal Bores. NOTE 1: Remove the main gear wheel assembly and attach bolt to get access. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A321015 Main gear retraction systems. Make AY 53 720, 730 sure you examine these areas: (A.) Mechanisms. (B.) Bushings. (C.) Bearings. (D.) Structural attachments. NOTE 1: Do not apply LPS-3 Heavy-Duty Rust Inhibitor on bearing. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). C322001 Nose Gear Torque Links - Lubricate. C 3 710 A322001 Nose Gear Torque Links - Inspect for C 3 710 wear and condition. C322002 Nose Gear Trunnion Fitting - C 3 710 Lubricate. D322003 Nose Gear Trunnion Upper Pivot C 3 710 Bearings - Lubricate.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER D322004 Nose Gear Shimmy Damper - Service. C 3 710 Revised A322005 Nose Gear Assembly - Inspect for C 3 710 May 2/94 security of installation, cracks and evidence of damage. Check shock strut for evidence of leakage, check strut barrel for corrosion, pitting and cleanliness. A322006 Nose Gear Shimmy Damper - Check C 3 710 for leakage and attach points for wear and condition. C322007 Nose Gear Shimmy Damper Pivot C 3 710 Bearings - Lubricate. A322008 Nose Gear Wheel - Inspect for nicks, C 3 710 cracks, abrasions and corrosion. A322009 Nose Gear Door Retraction Linkage - C 3 710 Inspect for evidence of damage. A322010 Nose Gear Fork - Inspect for cracks, C 3 710 condition and security of installation. Revised A322011 Nose Gear Wheel Bearings - Clean C 3 710 May 2/94 and inspect for corrosion and evidence of damage. Repack. A322012 Nose Landing Gear Drag Brace AF 34 710 - Inspect per CQB91-9. Refer to Chapter 5, Section 5-14-08, Supplemental Inspection Document Number 32-20-00. A322013 Nose Gear Attachment and Wheel AG 35 710 Well Structure - Inspect. Refer to Chapter 5, Section 5-14-09, Supplemental Inspection Document Number 32-20-01. A322014 Nose Gear Fork - Inspect. Refer AH 36 710 to Chapter 5, Section 5-14-10, Supplemental Inspection Document Number 32-20-02. A322015 Nose Gear Trunnion Inspection (1.19 AJ 38 710 inch lugs) - Inspect. Refer to Chapter 5, Section 5-14-12, Supplemental Inspection Document Number 32-30-07. A322016 Nose Gear Trunnion Inspection (1.31 AJ 38 710 inch lugs) - Inspect. Refer to Chapter 5, Section 5-14-13, Supplemental Inspection Document Number 32-30-08.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A322017 Nose Gear Steering Bell Crank - AK 39 710 Inspect. Refer to Chapter 5, Section 5-14-14, Supplemental Inspection Document Number 32-50-00. A323001 Main Landing Gear Uplock Hook D 6, D 720, 730 Support Bracket - Inspect for cracks. Airplanes -0001 thru -0205 except airplanes incorporating Service Bulletin CQB87-4. Revised A323002 Main Gear Actuator - Inspect for leaks, C 3 720, 730 May 2/94 evidence of damage and security of installation. Inspect actuator piston rod end for cracks and security of installation. Revised A323003 Nose Gear Actuator - Inspect for C 3 710 May 2/94 evidence of leaks, damage and security of installation. Inspect actuator piston rod end for cracks and security of installation. Revised A323004 Nose Landing Gear Drag Brace U 23 710 Feb 2/98 Part Number 5142002-3 - Inspect for cracks. Airplanes with drag braces reworked to remove cracks in accordance with Service Bulletin CQB91-9. Revised A323005 Nose Landing Gear Drag Brace Part V 24 710 Jul 1/02 Number 5142002-3 (Not reworked by CQB91-9) - Inspect for cracks. A323006 Emergency Blowdown Bottle - Check D 6, D 221 bottle and cable for security of installation. D323007 Emergency Blowdown Bottle - M 14 221 Hydrostatic test. Revised B323008 Landing Gear Actuators and D 6, D 710, 720, May 2/94 Control/Indicating Systems Functional 730 Test - Perform test as scheduled or any time the landing gear emergency blow down bottle has been discharged or a landing gear actuator is replaced. A323009 Perform Landing Gear Rigging D 6, D 710, 720, Inspection - (Refer to Expanded 730 Inspection and Maintenance Checks). A323010 Main/Nose Gear Retraction Systems AI 37 710, Teardown and Inspection - Perform. 720,730 Refer to Chapter 5, Section 5-14-11, Supplemental Inspection Document Number 32-30-06.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A324001 Main Gear Wheels - Inspect for nicks, C 3 720, 730 cracks, abrasions and corrosion. Revised A324002 Tires - Inspect for pressure, wear and B 2 710, 720, May 2/94 cuts. 730 A324003 Brake System Plumbing (Wheel Well) C 3 720, 730 - Inspect for leaks, condition and security; check for proper routing and support. Revised A324004 Brake System Plumbing (Fuselage D 5, D 141, 151, May 2/94 and Wing) - Inspect for leaks, 152 condition and security of installation; check for proper routing and support. Revised A324005 Brake System Plumbing (Fuselage D 6, D 512, 612 May 2/94 and Wing) - Inspect for leaks, condition and security of installation; check for proper routing and support. Revised A324006 Main Gear Wheel Bearings - Clean C 3 720, 730 May 2/94 and inspect for corrosion and evidence of damage. Repack. A324007 Brake Assemblies - Check wear of C 3 720, 730 linings and discs. D324008 Brake Master Cylinders - Service. C 3 231 Revised A325001 Nose Gear Steering Stop Block - C 3 710 May 2/94 Check for damage and security. A325002 Nose Wheel Steering System - Check C 3 710 gimbal bolts for condition. Check cable attach fittings for security of installation and clevis for freedom of movement at swivel end. A325003 Nose Wheel Steering Cables - Check D 4, D 710 cable tension. Revised A325004 Nose Wheel Steering Cables - Inspect D 4, D 710, 131, May 2/94 cables for broken wires. Inspect cable 132, 141, fittings for cable slippage, cracks and 142 distortion. Inspect cable pulleys for freedom of rotation and the presence of cable guard pins. A332001 No Smoking, Oxygen and Seat C 3 251, 252 Belt Lights - Inspect for security of installation, evidence of damage and operation. A334001 Wing Inspection (Deice) Lights - C 3 241, 242, Inspect for security of installation, 410, 420 evidence of damage and operation. C334002 Landing Light Exposed Sector Gear - D 6, D 550, 650 Lubricate.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER C334003 Landing Light Hinge Point - Lubricate. D 6, D 550, 650 A334040 Landing Lights - Inspect for security C 3 550, 650 of installation, evidence of damage and operation. A340001 General Nose Compartment D 4, D 110, 121, Inspection - All components for 122, security of installation and evidence 131, 132, of damage. 211, 212, 212A A340002 Cockpit Instrument Panels - Inspect D 4, D 231, 232, instrument panels and area forward 248 to pressure bulkhead. Inspect all components and related structures for security of installation, cracks, corrosion and damaged electrical components. A340003 Tailcone Electronic and Avionics D 4, D 311, 312 Equipment Wire Bundles - Check for drip loop to keep moisture from entering connectors. Revised A341001 Static Sumps - Inspect sumps for D 4, D 172, 311, May 2/94 cracks, leaks and presence of 312 water; drain sumps. Inspect static system plumbing (in the tailcone) for security of installation and evidence of damage. Airplanes with air data computer in tailcone, inspect plumbing for adequate clearance with air data computer. Revised A341002 Altimeter System and Altitude K 12 231, 232 May 2/94 Reporting Equipment - Inspect as required by FAR Part 91, Paragraph 91.411 in accordance with FAR, Part 43, Appendix E, by authorized repair station. Revised B345003 Transponder Control - Operate K 12 231, 248 May 2/94 Individual Control and Operational Test Transponder System to comply with FAR 91.413. B350001 Altitude Barometric Pressure Switch - D 5 222 Complete a functional test. Revised A351001 Crew Masks and Stowage C 3 241, 242 May 2/94 (Compartment 33,000 foot Certified Airplanes) - Inspect mask and hoses for deterioration, cleanliness and proper stowage. Inspect stowage compartment for cleanliness and evidence of damage.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A351002 Crew Masks (35,000 foot Certified C 3 241, 242 Airplanes) - Inspect mask and hoses for deterioration, cleanliness and proper stowage. A351003 Oxygen Cylinder, Pressure Regulator D 4, D 312 and Shutoff Valve - Inspect for security of installation, corrosion, cleanliness and evidence of damage. A351004 Oxygen Altitude Compensating D 5, D 172 Regulator - Inspect for security of installation and evidence of damage. A351005 Oxygen Filler Valve - Inspect for D 4, D 312 security of installation, corrosion, cleanliness and evidence of damage. Revised D351006 Oxygen Cylinder - DOT-3HT L 13 312 May 2/94 (Lightweight) - Inspect condition and hydrostatic test. Revised D351007 Oxygen Cylinder - DOT-3AA M 14 312 May 2/94 (Standard Weight) - Inspect condition and hydrostatic test. B352001 Passenger Mask and Stowage D 5, D AUX Compartments - Operational test to verify oxygen mask drop. Revised A352002 Passenger Mask and Stowage D 5, D 251, 252, May 2/94 Compartments - Inspect mask and 261, 262 hoses for deterioration, cleanliness and proper stowage. Inspect pintle pin, lanyard cord and stowage compartment for cleanliness, evidence of damage, deterioration. A361001 Instrument Air Water Separator - D 4, D 132 Inspect for security of installation and evidence of damage. D361001 Instrument Air Water Separator - D 4, D 132 Replace filter. A361002 Air Pressure Hoses - Inspect for D 5, D 231, 232 hardness, deterioration, looseness and bulging. A361003 Instrument Air Pressure Regulator - D 4, D 222 Inspect for security of installation. Revised A361004 Air Pressure Lines - Inspect for D 5, D 132, 141, May 2/94 security of installation, corrosion and 142, 151, evidence of damage. 152, 222

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A383001 Flush Toilet - Inspect seat assembly D 5, D 262 May 2/94 for corrosion, security of installation, evidence of damage, damaged electrical components, and proper service. A383002 Non-flush Toilet - Inspect for security D 5, D 262 of installation. A383003 Relief Tube - Inspect for security D 5, D 262 of installation, deterioration and evidence of damage. A521001 Cabin Door Seal - Inspect for C 3 830 condition. A521002 Cabin Door Latch Pin Receptacles - C 3 830 Inspect for damage, cracks and wear. A521003 Cabin Door Latch Pin Guides - Inspect C 3 830 for damage, cracks and wear. Revised A521004 Cabin Door Latch Pins (Upper and C 3 830 May 2/94 Lower) - Inspect for damage, cracks, wear and proper pin extension. C521005 Cabin Door Hinges, Latch Pins, D 5, D 830 Step Hinges and Stop Assembly - Lubricate. Revised A521006 Cabin Door - Inspect for condition, C 3 830 Apr 5/99 operation and security of installation, and inspect door cables for proper rigging. A521007 Cabin Door Hinges - For airplanes Q 18 830 incorporating CQB98-9, perform a surface eddy current inspection of the hinge. A521008 Cabin Door Retention - Inspect. AP 44 830 Refer to Chapter 5, Section 5-14-15, Supplemental Inspection Document 52-10-01. A521009 Lower Cabin Door Hinges - Inspect. AM 41 830 Refer to Chapter 5, Section 5-14-16, Supplemental Inspection Document Number 52-10-02.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A521010 Emergency exit door retention AZ 54 820 system. Make sure you examine these areas: (A.) Bell cranks. (B.) Pushrods. (C.) Handle. (D.) Pin retention linkages. (E.) Pins. (F.) Lockplates and guides. (G.) Hinges. (H.) Internal door framing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A521011 Cabin upper and lower entry door AZ 54 830 (or wide door, if installed) retention system. Make sure you examine these areas: (A.) Bell cranks. (B.) Pushrods. (C.) Handle. (D.) Pin retention linkages. (E.) Pins. (F.) Lockplates and guides. (G.) Hinges. (H.) Internal door framing. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A522001 Emergency Exit Door - Check for D 5, D 820 condition, security of installation and operation. A522002 Emergency Exit Door - Visually Q 18 820 inspect for cracks. A522003 Emergency Exit Door - Inspect. AM 41 820 Refer to Chapter 5, Section 5-14-17, Supplemental Inspection Document Number 52-20-01. A522004 Cabin Door and Door Frame - Inspect. AN 42 830 Refer to Chapter 5, Section 5-14-18, Supplemental Inspection Document Number 52-20-02. Added A522005 Emergency Exit Door Bond Inspection BD 58 820 Feb - Inspect perimeter of the emergency 1/2021 exit door. Refer to Chapter 5, Section 5-14-52, Supplemental Inspection Document 52-20-05. A523001 Avionics and Nose Baggage Door C 3 211A, Seals - Inspect for cuts, tears, 211A abrasions and excessive wear.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A523002 Avionics and Nose Baggage Doors D 4, D 211A, - Check condition, security of 212A, installation and operation. Inspect 212B door latches for proper adjustment. Inspect latch handle for binding and chafing in latch housing. Inspect key lock for proper operation. B527001 Door Warning System - Check C 3 BAT operation. A528001 Nose Landing Gear Doors - Inspect C 3 710 hinges for security of installation and doors for evidence of damage. A528002 Main Landing Gear Doors - Inspect C 3 720, 730 hinge for corrosion and doors for evidence of damage. Revised A530001 Fuselage Exterior Surfaces - Inspect D 5, D All Zones May 2/94 for cracks, loose or failed fasteners and evidence of structural damage. Revised A531001 Horizontal and Vertical Stabilizer D 4, D 321, 322 May 2/94 Attach Bulkheads - Check for cracks, loose or failed fasteners and evidence of structural damage. (Removal of stabilizer not required). Revised A531002 Horizontal Stabilizer Forward Attach Z 28 321, 322 Jul 1/02 Bulkheads - Check for cracks (Airplanes not incorporating CQB91-1 [SK441-103]). A531003 Nose Wheelwell Structure - Check for D 4, D 710 security and cracks. A531004 Fuselage Structure - Inspect fuselage Q 18 151, 152, structure upper corners FS 193 and 251, 252 223; front spar stiffeners BL 0 and BL 6 for cracks, loose or failed fasteners and evidence of structural damage. A531005 Fuselage Structure - Inspect lower S 20 141, 142, corners from FS 118 through FS 273, 151, 152, upper corners FS 247 through FS 161, 162, 290, side frames FS 130, FS 235 and 171, 172, FS 247, forward pressure bulkhead 241, 242, top angle and horizontal stiffeners for 251, 252, cracks, loose or failed fasteners and 261, 262 evidence of structural damage. A531006 Horizontal and Vertical Stabilizer AO 43 311, 312, Attach Bulkheads - Inspect. Refer 331, 332, to Chapter 5, Section 5-14-19, 350 Supplemental Inspection Document Number 53-10-01.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A531007 Fuselage Left- and Right-Hand AO 43 251, 252 Channel Assemblies - Inspect. Refer to Chapter 5, Section 5-14-20, Supplemental Inspection Document Number 53-10-02. A531008 Forward Pressure Bulkhead at F.S. AP 44 221, 222 100.00 - Inspect. Refer to Chapter 5, Section 5-14-21, Supplemental Inspection Document Number 53-10-03. A531009 Aft Pressure Bulkhead at F.S. 324.94 AP 44 311, 312 - Inspect. Refer to Chapter 5, Section 5-14-22, Supplemental Inspection Document Number 53-10-04. A531010 Fuselage Bulkhead Structure - AP 44 141, 142, Inspect. Refer to Chapter 5, Section 151, 152, 5-14-23, Supplemental Inspection 161, 162, Document Number 53-10-05. NOTE: 171, 172, For airplanes with more than 12,000 222, 251, flight hours, repeat the inspection 252, 261, every 1,000 hours of operation or 2 262 years, whichever occurs first. A531011 Fuselage Structure Upper Bulkhead AM 41 251, 252 Corners - Inspect. Refer to Chapter 5, Section 5-14-24, Supplemental Inspection Document Number 53-10-06. NOTE: For airplanes with more than 12,000 flight hours, repeat the inspection every 1,000 hours of operation or 2 years, whichever occurs first. A531012 Fuselage nose baggage. Make sure AZ 54 131, 132 you examine these areas: (A.) Nose baggage shelves. (B.) Nose baggage lower internal structure. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531013 Fuselage lower internal structure AZ 54 141, 142 beneath the floor panels. Make sure you examine these areas: (A.) Cabin structure under floor boards. (B.) Lower bulkhead corners from FS 118.00 to crew window's aft frame. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A531014 Fuselage lower internal structure AZ 54 151, 152 beneath the floor panels. Make sure you examine these areas: (A.) Forward, main, and rear carry-thru spar webs from BL 0.00 to BL 21.36. (B.) Main and rear spar caps from BL 0.00 to BL 21.36. (C.) Fuselage bulkhead structure at FS 169.05 attachment. (D.) Fuselage bulkhead structure at FS 177.45 attachment. (E.) Fuselage bulkhead structure at FS 204.05 attachment. (F.) Bulkhead lower corners from crew window's rear frame to frame common to aft wing attach fitting. (G.) Cabin structure under refreshment center (if installed). NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531015 Fuselage lower internal structure AZ 54 161, 162 beneath the floor panels. Make sure you examine these areas: (A.) Bulkhead lower corners from frame common to rear wing attach fitting to cabin door's aft frame. (B.) Cabin structure under floorboards. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531016 Fuselage lower internal structure AZ 54 171, 172 beneath the floor panels. Make sure you examine these areas: (A.) Bulkhead lower corners from cabin door's aft frame to cabin bulkhead. (B.) Cabin structure under toilet (if installed). (C.) Cabin structure under refreshment center (if installed). NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531017 Areas of cabin structure. Make sure AZ 54 221, 222 you examine this area: (A.) Forward cabin bulkhead at FS 100.00. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A531018 Areas of cabin structure. Make sure AZ 54 241, 242 you examine this area: (A.) Seat tracks. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531019 Areas of the cabin structure. Make AZ 54 251, 252 sure you examine these areas: (A.) Seat tracks. (B.) Window frame channel assemblies between crew's aft window frame and cabin door's forward frame. (C.) Bulkhead upper corners from frame aft of first cabin window to cabin door's aft frame. (D.) Bulkhead side frames from FS 169.05 to cabin door's aft frame. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531020 Areas of the cabin structure. Make AZ 54 261, 262 sure you examine these areas: (A.) Window frame channel assemblies from cabin door's aft frame to last cabin window's aft frame. (B.) Seat tracks. (C.) Bulkhead upper corners from cabin door's aft frame to aft cabin bulkhead. (D.) Aft cabin bulkhead. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531021 Fuselage to horizontal stabilizer AZ 54 321, 322 attachment. Make sure to examine these areas: (A.) Tailcone bulkhead at forward spar assembly attachment. (B.) Tailcone bulkhead at aft spar assembly attachment. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A531022 Fuselage to vertical stabilizer AZ 54 321, 322 attachment. Make sure to examine these areas: (A.) Tailcone bulkhead at forward spar assembly attachment. (B.) Tailcone bulkhead at aft spar assembly attachment. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531023 Emergency exit door frame. Make AZ 54 820 sure you examine these areas: (A.) Door frame. (B.) Door hinges. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531024 Cabin entry door frame (or wide AZ 54 830 door frame, if installed). Make sure you examine these areas: (A.) Door frame. (B.) Door hinges. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A531025 Fuselage external skin. Make BA 55 121, 122, sure you examine these areas: 131, 132, (A.) Fuselage skin underneath 141, 142, antenna installations. NOTE: 151, 152, Corrosion Prevention and Control 161, 162, Program Inspection item (baseline 171, 172, interval, refer to Section 5-30-00 for 241, 242, additional inspection information and 251, 261, illustrations). 262, 311, 312 A531026 Fuselage Structure Stringers - AM 41 141, 142, Inspect. Refer to Chapter 5, Section 151, 152, 5-14-50, Supplemental Inspection 161, 162, Document Number 53-10-07. NOTE: 171, 172, For airplanes with more than 12,000 241, 242, flight hours, repeat the inspection 251, 252, every 1,000 hours of operation or 2 261, 262 years, whichever occurs first. C532001 Control Pedestal Bearings - Service. D 5, D 243 A532002 Bulkhead Structure at the Wing Attach AQ 45 151, 152, Fittings - Inspect. Refer to Chapter 161, 162 5, Section 5-14-25, Supplemental Inspection Document Number 53-20-02.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A533001 Tailcone Drain Tubes - Inspect for D 4, D 311, 312 May 2/94 any blockage and remove any trash in tailcone area which might cause blockage. Refer to Service Bulletin CQB88-4. Revised A541001 Nacelle Structure - Visually inspect D 6, D 521, 621 May 2/94 for cracks, dents and other damage. A541002 Nacelle Firewall Structure - Inspect D 6, D 410, 420 for condition and proper sealing. A541003 Engine support structure. Make sure AY 53 410, 420 you examine this area: (A.) Engine support structure with emphasis at engine mounts and fittings. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A544001 Engine Truss - Inspect. Refer AQ 45 410, 420, to Chapter 5, Section 5-14-26, 521, 621 Supplemental Inspection Document Number 54-40-01. A544002 Engine Mounts - Inspect. Refer AR 46 410, 420 to Chapter 5, Section 5-14-27, Supplemental Inspection Document Number 54-40-02. A551001 Horizontal Stabilizer - Inspect for D 4, D 331, 332 cracks, loose or failed fasteners and evidence of structural damage. Inspect hinge bracketry for cracks and loose and/or working fasteners; inspect hinge bearings for looseness. Revised A551003 Horizontal Stabilizer Spars and AS 47 311, 312, Jun 1/07 Attachments - Inspect. Refer 331, 332 to Chapter 5, Section 5-14-28, Supplemental Inspection Document Number 55-10-03. Revised A551004 Horizontal Stabilizer Forward Spar AS 47 311, 312, Jun 1/07 Upper Cap - Inspect. Refer to Chapter 331, 332 5, Section 5-14-29, Supplemental Inspection Document Number 55-10-04. Revised A551005 Horizontal Stabilizer Forward Spar AS 47 311, 312, Jun 1/07 Lower Cap - Inspect. Refer to Chapter 331, 332 5, Section 5-14-30, Supplemental Inspection Document Number 55-10-05.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A551006 Horizontal Stabilizer Front Spar Lower AS 47 311, 312, Jun 1/07 Cap Near Attach Fitting - Inspect. 331, 332 Refer to Chapter 5, Section 5-14-31, Supplemental Inspection Document Number 55-10-06. Revised A551007 Horizontal Stabilizer Aft Spar AS 47 311, 312, Jun 1/07 Lower Cap Attach - Inspect. Refer 331, 332 to Chapter 5, Section 5-14-32, Supplemental Inspection Document Number 55-10-07. A551008 Horizontal Stabilizer Aft Spar Lower AS 47 311, 312, Cap - Inspect. Refer to Chapter 331, 332 5, Section 5-14-33, Supplemental Inspection Document Number 55-10-08. A551009 Horizontal Stabilizer Aft Spar Upper AS 47 311, 312, Cap - Inspect. Refer to Chapter 331, 332 5, Section 5-14-34, Supplemental Inspection Document Number 55-10-09. A551010 Horizontal Stabilizer Bond Inspection. AS 47 311, 312, Refer to Chapter 5, Section 5-14-49, 321, 322, Supplemental Inspection Document 321AB, Number 55-10-10. 321B, 331, 332, 321AT A551011 Horizontal stabilizer. Make sure you AZ 54 331, 332 examine these areas: (A.) Forward upper and lower spar cap at access panel locations and from SS 0.00 to SS 10.00. (B.) Rear spar upper and lower spar caps. (C.) Forward spar splice between SS 0.00 and SS 10.00. (D.) Forward spar attachment to the tailcone bulkhead. (E.) Aft spar attachment to the tailcone bulkhead. (F.) Auxiliary spars at access panel locations. (G.) Horizontal stabilizer skins. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A551012 Antenna installation. Make sure you BA 55 350 examine this area: (A.) Skin under any existing antenna installations. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A551013 Vertical stabilizer. Make sure you AY 53 350 examine these areas: (A.) Forward spar caps. (B.) Rear spar web and spar caps. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). Revised A551014 Horizontal Stabilizer Skin-to- BB 56 331, 332 Jun 2/08 Honeycomb Bond - Inspect. Refer to Chapter 5, Section 5-14-51, Supplemental Inspection Document Number 55-10-11. A552001 Outboard Elevator Hinge Bracket AT 48 331, 332 and Attachment - Inspect. Refer to Chapter 5, Section 5-14-35, Supplemental Inspection Document Number 55-20-01. A552002 Elevator Hinges and Fittings - Inspect. AS 47 311, 312, Refer to Chapter 5, Section 5-14-36, 331, 332 Supplemental Inspection Document Number 55-20-02. A553001 Vertical Stabilizer - Inspect for cracks, D 4, D 350 loose or failed fasteners and evidence of structural damage. A553002 Vertical Stabilizer Spars and AS 47 311, 312 Attachments - Inspect. Refer to Chapter 5, Section 5-14-37, Supplemental Inspection Document Number 55-30-01. A553003 Rudder Hinges and Fittings - Inspect. AS 47 350 Refer to Chapter 5, Section 5-14-38, Supplemental Inspection Document Number 55-30-02. A553004 Vertical Stabilizer Spar Attachments - AU 49 311, 312, Inspect. Refer to Chapter 5, Section 350 5-14-39, Supplemental Inspection Document Number 55-30-03. A561001 Windshield - Inspect windshield for C 3 241, 242 scratches, cracks, delamination, discoloration and deformities. A561002 Side Windows - Inspect flight C 3 241, 242 compartment side windows for scratches, cracks, deformities and cleanliness.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A561003 Windshield Retention Holes (Center Q 18 241, 242 May 2/94 Bow Area) - Inspect (Optical Prism method) for cracks in acrylic windshield propagating between fastener holes. A561004 Pilot and Copilot Windshield Attach AV 50 241, 242 Hole Inspection - Acrylic Windshield - Inspect. Refer to Chapter 5, Section 5-14-40, Supplemental Inspection Document Number 56-10-01. A562001 Cabin Windows - Inspect windows for C 3 251, 252, scratches, cracks and deformities. 261, 262, 820, 830 A571001 Inspect Center Wing Carry-Thru R 19 511, 611, Structure for Cracks. 512, 612, 513, 613, 251, 252 A571002 Main Spar Lower Cap From B.L. AR 46 511, 512, 24.00 to B.L. 30.00 - Inspect. Refer 531, 532, to Chapter 5, Section 5-14-41, 541, 542, Supplemental Inspection Document 611, 612 Number 57-10-01. A571003 Main Spar Lower Cap From B.L. AR 46 151, 152, 22.00 to C.W.S. 111.00 - Inspect. 511, 512, Refer to Chapter 5, Section 5-14-42, 611, 612 Supplemental Inspection Document Number 57-10-02. A571004 Main Spar Lower Wing Attach Fittings AR 46 151, 152, and Cap at C.W.S. 111.00 - Inspect. 511, 512, Refer to Chapter 5, Section 5-14-43, 611, 612 Supplemental Inspection Document Number 57-10-03. A571005 Front Spar Lower Cap From B.L. AR 46 151, 152 23.00 to C.W..S. 30.00 - Inspect. Refer to Chapter 5, Section 5-14-44, Supplemental Inspection Document Number 57-10-04. A571006 Aft Spar Lower Cap From B.L. AR 46 151, 152, 23.00 to C.W.S. 112.10 - Inspect. 511, 512, Refer to Chapter 5, Section 5-14-45, 611, 612 Supplemental Inspection Document Number 57-10-05. A571007 Aft Spar Lower Wing Attach Fittings AR 46 161, 162, and Spar Cap at C.W.S. 112.10 - 512, 513, Inspect. Refer to Chapter 5, Section 612, 613 5-14-46, Supplemental Inspection Document Number 57-10-06.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A571008 Center Wing Spar Web Inspection. AS 47 151, 152, Refer to Chapter 5, Section 5-14-47, 161, 162, Supplemental Inspection Document 511, 512, Number 57-10-07. 513, 611, 612, 613 Revised A571009 Wing skin external. Make sure you BA 55 511, 611 Dec 1/18 examine these areas: (A.) Bonded wing skin. (B.) Leading edge skin under de-ice boot. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). NOTE 2: Remove wing de-ice boot for the initial corrosion inspection of the leading edge. After the initial inspection is complete, remove the de-ice boot for every second inspection (i.e. every 10 years) for airplanes operated in a severe corrosion environment and every third inspection (i.e. every 15 years) for airplanes operated in a mild or moderate corrosion environment. A571010 Wing structure internal. Make sure BA 55 511, 611 you examine these areas: (A.) Front spar lower cap from BL 23.00 to CWS 30.00. (B.) Bonded wing skin. NOTE 1: Make sure you examine the bonded waffle doublers for corrosion. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A571011 Wing skin external. Make sure you BA 55 511, 611 examine this area: (A.) Bonded wing skin. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A571012 Wing structure internal. Make sure BA 55 512, 612 you examine these areas: (A.) Front spar upper and lower caps. (B.) Main spar upper and lower caps in gear well. (C.) Rear spar upper and lower caps in gear well. (D.) Wing rear spar web. (E.) Main spar center wing attach fittings at CWS 111.00. (F.) Rear spar center wing attach fittings at CWS 112.10. (G.) Bonded wing skin. NOTE 1: Make sure you examine the bonded waffle doublers for corrosion. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A571013 Wing structure external. Make sure BA 55 513, 613 you examine these areas: (A.) Rear spar upper cap. (B.) Rear spar lower cap. (C.) Rear spar web. (D.) Bonded wing skin. NOTE: Make sure you examine the bonded waffle doublers for corrosion. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). Revised A571014 Wing skin external. Make sure you BA 55 531, 631 Dec 1/18 examine these areas: (A.) Bonded wing skin. (B.) Leading edge skin under de-ice boot. NOTE 1: Make sure you examine the bonded waffle doublers for corrosion. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). NOTE 3: Remove wing de-ice boot for the initial corrosion inspection of the leading edge. After the initial inspection is complete, remove the de-ice boot for every second inspection (i.e. every 10 years) for airplanes operated in a severe corrosion environment and every third inspection (i.e. every 15 years) for airplanes operated in a mild or moderate corrosion environment.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A571015 Wing structure internal. Make sure BA 55 531, 631 you examine these areas: (A.) Main spar cap and outer wing attach fittings. (B.) Bonded wing skin. NOTE: Make sure you examine the bonded waffle doublers for corrosion. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A571016 Wing structure external. Make sure BA 55 532, 632 you examine these areas: (A.) Bonded wing skin. (B.) Rear spar upper cap. (C.) Rear spar lower cap. (D.) Rear spar web. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A571017 Wing structure internal. Make sure BA 55 532, 632 you examine these areas: (A.) Main spar upper and lower caps and outer wing attach fittings. (B.) Rear spar upper and lower caps and outer wing attach fittings. NOTE: Make sure you examine the bonded waffle doublers for corrosion. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). Revised A571018 Wing skin external. Make sure you BA 55 541, 641 Dec 1/18 examine these areas: (A.) Bonded wing skin. (B.) Leading edge skin under de-ice boot. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). NOTE 2: Remove wing de-ice boot for the initial corrosion inspection of the leading edge. After the initial inspection is complete, remove the de-ice boot for every second inspection (i.e. every 10 years) for airplanes operated in a severe corrosion environment and every third inspection (i.e. every 15 years) for airplanes operated in a mild or moderate corrosion environment.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A571019 Wing structure internal. Make sure BA 55 541, 641 you examine these areas: (A.) Bonded wing skin. (B.) Main spar upper and lower caps. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A571020 Wing structure external. Make sure BA 55 542, 642 you examine these areas: (A.) Bonded wing skin. (B.) Rear spar upper cap. (C.) Rear spar lower cap. (D.) Rear spar web. NOTE 1: Make sure you examine the bonded waffle doublers for corrosion. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A571021 Wing structure internal. Make sure BA 55 542, 642 you examine these areas: (A.) Main spar upper and lower caps. (B.) Rear spar upper and lower caps. (C.) Wing rear spar webs. (D.) Bonded wing skin. NOTE 1: Make sure you examine the bonded waffle doublers for corrosion. NOTE 2: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Section 5-30-00 for additional inspection information). A572001 Canted Rib Cap Inspection/Repair AL 40 151, 152, - Perform per CQB03-1. Refer 161, 162, to Chapter 5, Section 5-14-48, 511, 512, Supplemental Inspection Document 513, 611, Number 57-10-08. 612, 613 A573001 Wing Structure (Type A). C 3 511, 512, 513, 521 531, 532 541, 542 550, 611, 612, 621, 631, 632, 641, 642, 650

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A573002 Wing Structure (Type B). W 25 511, 512, May 2/94 513, 521, 531, 532, 541, 542, 611, 612, 613, 621, 631, 632, 641, 641 A573003 Wing Access Plates - Inspect for C 3 511, 550, security of installation and evidence 611, 650, of damage. 512, 612, 532, 632, 542, 642, 521, 621, 541, 641 C611001 Propeller Blade Clamps - Lubricate B 2 410, 420 (Hartzell only). A611001 Propeller assembly. Make sure you BA 55 410, 420 examine these areas: (A.) Propeller blade and attachment. (B.) Propeller hub. (C.) Propeller assembly bearings and pins. NOTE: Corrosion Prevention and Control Program Inspection item (baseline interval, refer to Chapter 5, Section 5-30-00 for additional inspection information). A611002 Propeller Blades - Inspect for nicks C 3 410, 420 and cracks. A611003 Propeller Mounting - Check for C 3 410, 420 security of installation. A611004 Propeller - Inspect for oil leaks. C 3 410, 420 D611005 Propeller Oil - Check level (McCauley G 9 410, 420 only). A611006 Propeller Hub - Inspect for cracks, C 3 410, 420 condition and security of installation. A611007 Spinner Bulkhead - Check for cracks C 3 410, 420 and security of installation. A611008 Propeller Spinners - Inspect for cracks C 3 410, 420 and security of installation. A611009 Propeller Blades - Check red mark on C 3 410, 420 blade and hub to ensure alignment (Hartzell only). A612001 Propeller Unfeathering Oil Pump C 3 410, 420 - Inspect for leaks, condition and security of installation.

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER A612002 Propeller Governor - Inspect for C 3 410, 420 oil leaks, condition and security of installation. A711001 Cowling - Inspect the upper and lower C 3 410, 420 cowl and inlet assembly for loose or failed fasteners, security of installation and evidence of damage. A711002 Oil Filler Door and Access Panels - C 3 410, 420 Inspect for security of installation and evidence of damage. A711003 Engine Mounts - Inspect for security C 3 410, 420 of installation, deterioration of elastomers, cracks and evidence of damage. A712001 Engine Truss - Inspect using W 25 410, 420 Nondestructive Testing method described in Service Bulletin CQB85-24. A715001 Electrical Harness - Inspect C 3 410, 420 connectors, terminals and wires for damage. A717001 Engine Drains - Inspect for security of C 3 410, 420 installation, line routing, deterioration of hoses and evidence of damage. Revised A717002 Engine Compartment Hoses - Inspect D 6, D 410, 420 May 2/94 for condition; inspect fuel (inspect fuel lines under pressure), oil vacuum and hydraulic hoses for leaks, chafing, deterioration discoloration, bleaching. Inspect rubber hoses for stiffness. A720000 Engine - (refer to Garrett Engine -- 2 410, 420 Maintenance Manual for Periodic Inspection Requirements and Checks. A731001 Fuel Lines - Inspect fuel supply lines B 2 410, 420 for deterioration, chafing, fuel leaks and security of installation. A732001 Engine EPA System - Inspect D 6 410, 420 plumbing and components for security of installation and damage. D732002 Engine EPA System Filter - Clean. D 6, D 410, 420 A733001 Fuel Flow Transmitters - Inspect for C 3 410, 420 security of installation, fuel leaks and evidence of damage. A761001 Engine Controls - Check travel B 2 410, 420 and security of installation, routing and evidence of damage (engine compartment).

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REVISION ITEM CODE TASK INTERVAL Phase ZONE STATUS NUMBER Revised A761002 Engine Controls - Check travel and D 5, D 141, 142, May 2/94 security of installation, routing and 151, 152, evidence of damage (cabin area). 243 Revised A761003 Engine Controls - Check travel and D 6, D 511, 611 May 2/94 security of installation, routing and evidence of damage (wing area). A771001 Torque Pressure Transducers - C 3 410, 420 Inspect for security of installation and evidence of leaks. A781001 Engine Exhaust System - Inspect B 2 410, 420 for cracks, distortion, security of installation and evidence of damage. A781002 Exhaust Pipe Swirl Vanes - Inspect D 6, D 410, 420 for security and evidence of damage. D791001 Engine Oil Viscosity Type Rating O 16 410, 420 (Type I) - Change. D791002 Engine Oil Viscosity Type Rating P 17 410, 420 (Type II) - Change. D792001 Engine Oil Filter Element - Replace. C 3 410, 420 A793001 Engine Oil Temperature Sensors - C 3 410, 420 Inspect for security of installation, damage to electrical connector and evidence of damage. A793002 Engine Oil Pressure Sensors - Inspect C 3 410, 420 for security of installation, damage to electrical connector and evidence of damage. A793003 Engine Oil Pressure Switch - Inspect C 3 410, 420 for security of installation, damage to electrical connectors and evidence of damage. A801001 Starter-Generator Brush Holders - B 2 410, 420 Inspect for cracks, wear, cleanliness; brush springs for proper tension and looseness. A801002 Starter-Generator Brushes - Inspect B 2 410, 420 for cracks, wear and cleanliness. Revised A801003 Starter-Generator - Inspect splines C 3 410, 420 May 2/94 for wear. C801003 Starter-Generator - Lubricate splines. C 3 410, 420 A801004 Starter-Generators - Inspect for B 2 410, 420 security of installation, terminal block and electrical connections for cleanliness, evidence of heat or electrical arcing and evidence of damage.

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CESSNA® MODEL 441 MAINTENANCE MANUAL

INSPECTION PHASE 58

Date: ______Registration Number: ______Serial Number: ______Total Time: ______

1. Description A. Phase 58 consists of items to be inspected every 2000 hours or 4 years, whichever occurs first, then every 2000 hours or 4 years thereafter. B. Inspection items are given in the order of the zone in which the inspection is to be completed. A general description of the inspection required and the Item Code Number for cross-reference to section 5-10-01 are shown. Frequently, tasks give more information about each required inspection. These tasks are printed in the individual chapters of this manual. C. 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. While each of the specified inspection tasks in this section is 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 may need more maintenance. B. 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. C. Do a preflight inspection after these inspections are completed to make sure all the required items are correctly serviced. Refer to the Pilot's Operating Handbook.

ITEM CODE TASK ZONE MECH INSP REMARKS NUMBER A522005 Emergency Exit Door Bond Inspection - Inspect 820 perimeter of the emergency exit door. Refer to Chapter 5, Section 5-14-52, Supplemental Inspection Document 52-20-05. *** End of Phase 58 Inspection Items ***

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CESSNA® MODEL 441 MAINTENANCE 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. All inspections must be done by September 1, 2008, except for SID Inspection Number 55-10-11. C. SID Inspection Number 55-10-11 must be done by June 1, 2009. D. Procedure (1) Each supplemental inspection is assigned an independent item code in Chapter 5. (2) The item codes are in Chapter 5, Inspection Time Limits. They are found in section 5-10-01. (3) The item code contains the subject and a reference to the actual supplemental inspection. These inspections are found in sections that begin with 5-14-XX. (4) Each 5-14-XX section has the details of the inspection and, if needed, a reference to the Nondestructive Testing procedure for that inspection. (5) The supplemental inspections that reference a Nondestructive Testing procedure will refer to 5-15-XX document for the details of the procedure. (6) 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. (7) As an example, if a supplemental inspection is found in Section 5-14-16, then the Nondestructive Testing procedure, if applicable, would be found in 5-15-16. E. Service Information Letters/Service Bulletins (1) In addition to this maintenance manual, the following service information will be required to complete the SID inspections (5-14-XX and 5-15-XX document sections).

Reference SID Number Title Date Number CQB85-24 Engine Truss Inspection 11-22-85 54-40-01 CQB91-9 Landing Gear Drag Brace 2-24-03 32-20-02 Inspection/Replacement CQB00-3 Nose Gear Trunnion Inspection/ 10-02-00 32-20-07, 32-20-08 Replacement CQB03-1 Canted Rib Cap Inspection/Modification 3-24-03 57-10-08

(2) The following Service Bulletins and Service Kits are assumed to have been accomplished, as applicable, prior to performing the SID inspections (5-14-XX and 5-15-XX document sections).

Number Title Effectivity PJ79-5 R4 Inboard Elevator Hinge Bracket Replacement 441-0001 thru 441-0032, 441-0034 thru 441-0064, 441-0066 thru 441-0078 PJ79-23 R1 Nose Gear Trunnion Replacement 441-0001 thru 441-0079, 441-0081 thru 441-0088, 441-0090 thru 441-0096, 441-0098, 441-0099, 441-0101 thru 441-0106, 441-0109 PJ80-13 Cabin Overhead Bulkhead Inspection 441-0001 thru 441-0139 PJ80-21 Elevator Push Pull Rod Replacement 441-0001 thru 441-0155, 441-0158

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Number Title Effectivity PJ81-6 Tailcone Bulkhead Support Improvement 441-0064 thru 441-0171 PJ81-21 Lower Cabin Door Hinge Support Improvement 441-0173 thru 441-0192 PJ82-1 Elevator Bellcrank Bolt Replacement 441-0173 thru 441-0192 PJ82-24 Nose Landing Gear Drag Link Assembly Inspection/ 441-0001 thru 441-0231, Replacement 441-0233 thru 441-0240, 441-0242 thru 441-0244, 441-0246, 441-0251 PJ82-35 Elevator and Elevator Trim Tab Hardware Replacement 441-0001 thru 441-0311 PJ83-10 Horizontal Stabilizer Forward Attach Bolts Torque Inspection 441-0001 thru 441-0311 PJ84-10 Actuator Rod End Replacement – Nose Landing Gear 441-0001 thru 441-0333 Airplanes equipped with a part number 9910139-3, -5, or -6 Nose Landing Gear Actuator. CQB85-20 Horizontal Stabilizer Aft Attachment Inspection/Modification 441-0111 thru 441-0342

CQB85-25 R2 Horizontal Stabilizer Forward Attach Bolt – Retaining Nut 441-0001 thru 441-0354 Replacement CQB87-4 Main Landing Gear Uplock Hook Support Bracket 441-0001 thru 441-0205 Inspection/Replacement

CQB91-1 R1 Horizontal Stabilizer Forward Attach Bulkhead Inspection and 441-0001 thru 441-0362 Reinforcement CQB92-3 Main Landing Gear Shock Strut Retention Modification 441-0001 thru 441-0362, 698 CQB94-2 Elevator Bellcrank Bracket Inspection and Modification 441-0001 thru 441-0362, 698 CQB95-24 Engine Truss Inspection 441-0001 thru 441-0362 CQB91-1 Horizontal Stabilizer Forward Attach Bulkhead Inspection and 441-0001 thru 441-0362 Reinforcement CQB93-1 Elevator Forward Spar Inspection and Hinge Bearing Lubrication 441-0001 thru 441-0362, 698 CQB98-9 Lower Cabin Door Hinge Replacement 441-0001 thru 441-0362, 698 CQB00-2 Rudder Hinge Bearing Inspection/Replacement 441-0001 thru 441-0042, 441-0044 thru 441-0111, 441-0113, 441-0114, 441-0117 thru 441-0121, 441-0124, 441-0128, 441-0133, 441-0314 thru 441-0326, 698

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2. Supplemental Inspections

DETAILS SUPPLE- INSPECTION FOUND MENTAL COMPLIANCE IN INSPEC- (See Note 1 and Note 3) SECTION TION INSPECTION ITEM 5-14-XX NUMBER TITLE INITIAL REPEAT PHASE CODE 5-14-01 27-10-05 Aileron Hinges and 10,000 2,500 29 A271008 Fittings Hours or 20 Hours or Years 5 Years 5-14-02 27-20-03 Rudder Structure 7,500 Hours 2,500 30 A272013 or 15 Years Hours or 5 Years 5-14-03 27-20-04 Rudder Torque Tube 7,500 Hours 2,500 30 A272014 or 15 Years Hours or 5 Years 5-14-04 27-30-01 Elevator Torque Tube 5,000 Hours 1,000 31 A273012 Assembly or 10 Years Hours or 3 Years 5-14-05 32-10-05 Main Landing Gear 7000 1000 57 A321003 Trunnion Landings or Landings 15 Years or 3 Years 5-14-06 32-10-06 Main Gear Shock 10,000 1,000 33 A321004 Struts Landings or Landings 15 Years or 3 Years 5-14-07 32-10-07 Main Landing Gear 10,000 2,000 32 A321005 Trailing Link Landings or Landings 15 Years or 4 Years 5-14-08 32-20-00 Nose Landing Gear Per CQB Per CQB 34 A322012 Drag Brace 91-9 91-9 5-14-09 32-20-01 Nose Gear Attachment 7,500 1,000 35 A322013 and Wheel Well Landings or Landings Structure 15 Years or 3 Years 5-14-10 32-20-02 Nose Gear Fork 15,000 5,000 36 A322014 Landings or Landings 15 Years or 10 Years 5-14-11 32-30-06 Main/Nose Gear 7500 2000 37 A323010 Retraction Systems Landings or Landings Teardown and 15 Years or 4 Years Inspection 5-14-12 32-30-07 Nose Gear Trunnion Per CQB Per CQB 38 A322015 Inspection (1.19 inch 00-3 00-3 lugs) 5-14-13 32-30-08 Nose Gear Trunnion Per CQB Per CQB 38 A322016 Inspection (1.31 inch 00-3 00-3 lugs)

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DETAILS SUPPLE- INSPECTION FOUND MENTAL COMPLIANCE IN INSPEC- (See Note 1 and Note 3) SECTION TION INSPECTION ITEM 5-14-XX NUMBER TITLE INITIAL REPEAT PHASE CODE 5-14-14 32-50-00 Nose Gear Steering 7500 2500 39 A322017 Bell crank Landings or Landings 15 Years or 5 Years 5-14-15 52-10-01 Cabin Door Retention 6000 Hours 2000 Hours 44 A521008 or 12 Years or 4 Years 5-14-16 52-10-02 Lower Cabin Door 4000 Hours 2000 Hours 41 A521009 Hinges or 8 Years or 4 Years 5-14-17 52-20-01 Emergency Exit Door 4000 Hours 2000 Hours 41 A522003 or 8 Years or 4 Years 5-14-18 52-20-02 Cabin Door and Door 6000 Hours 3600 Hours 42 A522004 Frame or 12 Years or 7 Years 5-14-19 53-10-01 Horizontal and Vertical 15,000 2000 Hours 43 A531006 Stabilizer Attach Hours or 20 or 4 Years Bulkheads Years 5-14-20 53-10-02 Fuselage Left and 15,000 2000 Hours 43 A531007 Right Hand Window Hours or 20 or 4 Years Frame Stringers Years 5-14-21 53-10-03 Forward Pressure 6000 Hours 2000 Hours 44 A531008 Bulkhead at F.S. 100.00 or 12 Years or 4 Years 5-14-22 53-10-04 Aft Pressure Bulkhead 6000 Hours 2000 Hours 44 A531009 at F.S. 324.94 or 12 Years or 4 Years 5-14-23 53-10-05 Fuselage Bulkhead 6000 Hours 2000 Hours 44 A531010 Structure or 12 Years or 4 Years, refer to Note 2 5-14-24 53-10-06 Fuselage Structure 4000 Hours 2000 Hours 41 A531011 Upper Bulkhead or 8 Years or 4 Years, Corners refer to Note 2 5-14-25 53-20-02 Bulkhead Structure at 3000 Hours 3000 Hours 45 A532002 the Wing Attach Fittings or 6 Years or 6 Years 5-14-26 54-40-01 Engine Truss 3000 Hours 3000 Hours 45 A544001 or 6 Years or 6 Years 5-14-27 54-40-02 Engine Mounts 15,000 3000 Hours 46 A544002 Hours or 20 or 6 Years Years 5-14-28 55-10-03 Horizontal Stabilizer 15,000 2500 Hours 47 A551003 Spars and Attachments Hours or 20 or 5 Years Years 5-14-29 55-10-04 Horizontal Stabilizer 15,000 2500 Hours 47 A551004 Forward Spar Upper Hours or 20 or 5 Years Cap Years

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DETAILS SUPPLE- INSPECTION FOUND MENTAL COMPLIANCE IN INSPEC- (See Note 1 and Note 3) SECTION TION INSPECTION ITEM 5-14-XX NUMBER TITLE INITIAL REPEAT PHASE CODE 5-14-30 55-10-05 Horizontal Stabilizer 15,000 2500 Hours 47 A551005 Forward Spar Lower Hours or 20 or 5 Years Cap Years 5-14-31 55-10-06 Horizontal Stabilizer 15,000 2500 Hours 47 A551006 Front Spar Lower Cap Hours or 20 or 5 Years Near Attach Fitting Years 5-14-32 55-10-07 Horizontal Stabilizer Aft 15,000 2500 Hours 47 A551007 Spar Lower Cap Attach Hours or 20 or 5 Years Years 5-14-33 55-10-08 Horizontal Stabilizer Aft 15,000 2500 Hours 47 A551008 Spar Lower Cap Hours or 20 or 5 Years Years 5-14-34 55-10-09 Horizontal Stabilizer Aft 15,000 2500 Hours 47 A551009 Spar Upper Cap Hours or 20 or 5 Years Years 5-14-35 55-20-01 Outboard Elevator 5,000 Hours 1000 Hours 48 A552001 Hinge Bracket and or 10 Years or 2 Years Attachment 5-14-36 55-20-02 Elevator Hinges and 15,000 2500 Hours 47 A552002 Fittings Hours or 20 or 5 Years Years 5-14-37 55-30-01 Vertical Stabilizer 15,000 2500 Hours 47 A553002 Spars and Attachments Hours or 20 or 5 Years Years 5-14-38 55-30-02 Rudder Hinges and 15,000 2500 Hours 47 A553003 Fittings Hours or 20 or 5 Years Years 5-14-39 55-30-03 Vertical Stabilizer Spar 15,000 1500 Hours 49 A553004 Attachments Hours or 20 or 3 Years Years 5-14-40 56-10-01 Pilot's and Copilot's 1000 Hours 1000 Hours 50 A561004 Windshield Attach Hole or 3 Years or 3 Years Inspection - Acrylic Windshield 5-14-41 57-10-01 Main Spar Lower Cap 15,000 3000 Hours 46 A571002 From B.L. 24.00 to B.L. Hours or 20 or 6 Years 30.00 Years 5-14-42 57-10-02 Main Spar Lower Cap 15,000 3000 Hours 46 A571003 From B.L. 22.00 to Hours or 20 or 6 Years C.W.S. 111.0 Years 5-14-43 57-10-03 Main Spar Lower Wing 15,000 3000 Hours 46 A571004 Attach Fittings and Hours or 20 or 6 Years Spar Cap at C.W.S. Years 111.00

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DETAILS SUPPLE- INSPECTION FOUND MENTAL COMPLIANCE IN INSPEC- (See Note 1 and Note 3) SECTION TION INSPECTION ITEM 5-14-XX NUMBER TITLE INITIAL REPEAT PHASE CODE 5-14-44 57-10-04 Front Spar Lower Cap 15,000 3000 Hours 46 A571005 From B.L. 23.00 to Hours or 20 or 6 Years C.W.S. 30.00 Years 5-14-45 57-10-05 Aft Spar Lower Cap 15,000 3000 Hours 46 A571006 From B.L. 23.00 to Hours or 20 or 6 Years C.W.S. 112.10 Years 5-14-46 57-10-06 Aft Spar Lower Wing 15,000 3000 Hours 46 A571007 Attach Fittings and Hours or 20 or 6 Years Spar Cap at C.W.S. Years 112.10 5-14-47 57-10-07 Center Wing Spar Web 15,000 2500 Hours 47 A571008 Inspection Hours or 20 or 5 Years Years 5-14-48 57-10-08 Canted Rib Cap Per CQB Per CQB 40 A572001 Inspection/Repair 03-1 03-1 5-14-49 55-10-10 Horizontal Stabilizer 15,000 2500 Hours 47 A551010 Bond Inspection Hours or 20 or 5 Years Years 5-14-50 53-10-07 Fuselage Structure 4,000 Hours 2000 Hours 41 A531026 Stringers or 8 Years or 4 Years, refer to Note 2 5-14-51 55-10-11 Horizontal Stabilizer 20 Years 5 Years 56 A551014 Skin-to-Honeycomb (mild envi- (mild en- Bond Inspection ronment) or vironment) 10 Years or 3 Years (moder- (moderate/severe ate/severe environ- environ- ment) ment) 5-14-52 52-20-05 Emergency Exit Door 2000 Hours 2000 Hours 58 A522005 Bond Inspection or 4 Years or 4 Years

NOTE 1: If the number of landings is not known, use the following to calculate the required inspection intervals: 1 flight hour is equal to 1 landing.

NOTE 2: Repeat inspection is initially at 2,000 hours or 4 years. After accumulation of 12,000 flight hours, repeat inspection is 1,000 hours or 2 years.

NOTE 3: Inspection intervals are given in both hour and calendar time. After the completion of each initial SID inspection, repeat inspections may be completed based on hour time if the Corrosion Prevention and Control Program (CPCP) in document 5-30-00 is included in the airplane maintenance program.

NOTE 4: Refer to SID details for initial and repeat inspection times.

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Inspection Requirements - Hours to Years Equivalence Figure 1

CESSNA® MODEL 441 MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 52-20-05

1. Title Emergency Exit Door Bond Inspection

2. Effectivity A. Airplanes 441-0001 thru 441-0362, and 441-0698.

3. Inspection Compliance

INITIAL REPEAT 2000 Hours or 4 Years 2000 Hours or 4 Years

4. Purpose A. To verify the integrity of the bond between the emergency exit door outer skin and the pan doubler.

5. Inspection Instructions A. Remove the emergency exit door. Refer to Removal/Installation Emergency Exit Door procedure, 52-20-00. B. Clean the area with mild soap and water to remove dirt, grease, oil, loose paint, and any other materials that can effect the inspection. C. Do an Ultrasonic Bond Inspection. Refer to Supplemental Inspection Document 5-15-52, Supplemental Inspection Number 52-20-03, for specific instructions.

6. Access And Detectable Crack Size

Access/Location Detectable Crack Size Emergency Exit Door Bond N/A

7. Inspection Method A. Ultrasonic Bond Inspection.

8. Repair/Modification A. If a debond is detected and within limitations listed in Supplemental Inspection Document 5-15-52, Supplemental Inspection Number 52-20-03, perform the Adhesive Bond procedure, 20-31-01. If a debond is detected and exceeds the limitations, contact Textron Aviation Customer Service.

9. Comments A. Use the Discrepancy Report form in Supplemental Inspection Document 5-13-00 to report a debond found during this inspection.

CESSNA® MODEL 441 MAINTENANCE MANUAL

SUPPLEMENTAL INSPECTION NUMBER: 52-20-03

1. Title Emergency Exit Door Bond Inspection

2. Effectivity A. Airplanes 441-0001 thru 441-0352, and 441-0698.

3. Description A. Detailed inspection of the emergency exit door perimeter to find debonds.

4. Preparation A. Remove the emergency exit door. Refer to Removal/Installation Emergency Exit Door procedure, 52-20-00. B. Clean the area with mild soap and water to remove dirt, grease, oil, loose paint, and any other materials that can effect the inspection. C. Visually inspect all edges of the emergency exit door for disbonds between the outer skin and the pan doubler. D. Using a scale or other measuring device identify the inspection area. Measure and mark 0.70 inch around the entire perimeter of the emergency exit door. Refer to Figure 1. E. Using a scale or other measuring device, measure and mark a single point at 4.0 inches from both the lower edge and the forward edge of the emergency exit door. This point will be location used for the Single Layer/Void Condition during the Inspection System Calibration. Refer to Figure 2.

5. Inspection Method A. Untrasonic Bond Inspection. Refer to Nondestructive Inspection Methods and Requirements, 5-13-01 for NDT personal certification requirements.

6. Limitation Criteria • A single disbond must not exceed 6 inches in length. • Disbonds ending within 2 inches of each other are considered as 1 continuous disbond. • The disbond must not exceed 12 inches over a span of 28 inches. • If the above limitations are exceeded, contact Textron Aviation, Repair Design Office (RDO).

7. Equipment A. The equipment listed in Table 1 was used to develop this inspection technique. Equivalent substitutes may be used for listed items provided the required sensitivity

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EQUIPMENT MODEL MANUFACTURER Resonance Bond Testing Bondmaster 600 Olympus NDT Intstrument 48 Woerd Avenue Waltham, MA 02453 Phone: 781-419-3900 Fax: 781-419-3980 Email: [email protected] Web: http://www.olympusndt.com Resonance Probe L3280 NDT Systems Inc. 5542 Buckingham Dr. Huntington Beach, CA 92649 Phone: 714-893-2438 Email: [email protected] Web: https://www.ndtsystems.com NOTE 1: The maximum allowable diameter of the Resonance Probe is 0.500 inch. NOTE 2: Prove frequency range must be between 155 kHz and 340 kHz.

8. Inspection System Calibration A. Set up the instrument in accordance with the manufacturer's instructions. B. Apply couplant to the inspection area. Refer to Figure 1. C. Place the probe on the exterior surface of the escape hatch door in the inspection area and press the Null button on the instrument. D. Position the null point so that it is located along the 20 percent full screen height position. This is the Null/Balance Point shown in Figure 2.

NOTE: Positioning the null point at the 20 percent full screen height position will allow for more distinguishable signals between coupling issues and disbond conditions. E. Hold the probe in the air and note or store the location where the dot moves. This is the Air/Lift-off Point shown in Figure 2.

NOTE: In order to get enough separation between dots, it is acceptable for the Air/Lift-off dot location to be off screen. F. Put the probe on the part in the location that represents the Single Layer/Disbond Condition as instructed in step 4.E. Note or store this location on the instrument screen. This is the Single Layer/Disbond Condition shown in Figure 2.

NOTE: It is important that the Air/Lift-off Point on the display is not located in the immediate vicinity, or move in the same direction as the Single Layer/Disbond Condition point. With this type of setup, a coupling issue can be misinterpreted as a disbond condition. G. Use the phase/angle and amplitude/gain controls on the instrument to adjust the display so to maximize the separation between the Air/Lift-off Point and the Single Layer/Disbond Condition point. H. Verify all three points on the bond testing instrument are easily distinguishable as shown in Figure 2.

NOTE: If unable to get easily distinguishable points, it may be necessary to adjust the instrument's operating frequency plus or minus 10 kHz and repeat section 8, Inspection System Calibration.

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9. Inspection Instructions A. Perform the untrasonic bond inspection around the entire perimeter of the emergency exit door as identified in Figure 1.

NOTE: Perform a minimum of two overlapping passes so the entire width of the 0.7 inch inspection area is scanned and evaluated. B. If no disbonds are found, install the emergency exit door. Refer to Removal/Installation Emergency Exit Door procedure, 52-20-00. C. If any disbonds are detected, map out each location in all directions using a permanent writing utensil and contact Textron Aviation Customer Service.

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Emergency Exit Door Inspection Definition (View Looking Inboard) Figure 1 (Sheet 1)

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Bond Instrument Display Setup Figure 2 (Sheet 1)

TEMPORARY REVISION NUMBER 20-1

DATED 1 FEBRUARY 2021

MANUAL TITLE Model 441 Conquest/Conquest II Maintenance Manual MANUAL NUMBER - PAPER COPY D2518-16-13 TEMPORARY REVISION NUMBER D2518-16TR20-1

MANUAL DATE 1 August 1977 REVISION NUMBER 16 DATE 1 June 2007

This Temporary Revision consists of the following pages, which affect and replace existing pages in the paper copy manual.

SECTION REMOVE PAGES INSERT PAGES 20-31-00 - Adhesive Bonding n/a 201 thru 203

REASON FOR TEMPORARY REVISION 1. 20-31-01 - added Adhesive Bonding procedures to support the repair of the Emergency Exit Door Bond Inspection required in D2518-16TR5-8. 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 and remove 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. The export of these commodities, technology or software are subject to the US Export Administration Regulations. This information has been exported from the United States in accordance with export administration regulations. Diversion contrary to US law is prohibited. For guidance on export control requirements, contact the Commerce Department's Bureau of Export Administration at 202-482-4811 or visit the US department of Commerce website.ECCN: 9E991 PROPRIETARY RIGHTS NOTICE 1. These data are proprietary to Textron Aviation Inc. Use of this publication or any of the data contained herein for any purpose other than direct aircraft operation or maintenance is prohibited without prior written authorization from Textron Aviation Inc. Reproduction or redistribution of this publication in whole or in part is prohibited.

CESSNA® MODEL 441 MAINTENANCE MANUAL

ADHESIVE BONDING - MAINTENANCE PRACTICES

1. General A. This section describes the procedures for obtaining a field repair bond joint in which fasteners are used to apply pressure. This type of bond joint will improve the fatigue resistance and stiffness of mechanically fastened structure. B. The adhesives used for field repair adhesive bonds will be a room temperature curing paste adhesive. Approved adhesives are as follows:

EA9309.3na Henkel Loctitie Corp* 35 minutes pot life EA9339 Henkel Loctitie Corp* 160 minutes pot life EA9396 Henkel Loctitie Corp* 75 to 95 minutes pot life *Henkel Loctite Corp, Bay Point, CA 94565

2. Surface Preparation A. The best surface preparation for this type of field repair bonding is phosphoric acid anodize (PAA) and bond primer, on both mating surfaces. The recommended repair detail finish is PPA and bond primer which has a translucent greenish-gold appearance. If repair details are not or cannot be fabricated from pre-finished material (e.g. S3806 Type "C" or "F") , the details should be chemical film and epoxy primed. B. If the existing structure is part of a production bond assembly, it may have either finish listed below: • PAA (or FPL etch) and bond primer only; or • PAA (or FPL etch) and bond primer with epoxy primer or zinc chromate primer topcoat. C. There may be an additional topcoat of gray enamel or other polyurethane on top of the epoxy primer finishes. D. For an existing structure bond assembly which has had the production autoclave bond separated, any clean residual bond adhesive should be left on the surface. No surface preparation is required; the repair paste adhesive will be applied directly to the residual adhesive. The residual adhesive should be masked off using clean Kraft paper to protect it from dirt and other foreign particles until paste adhesive can be applied, and/or to protect it if adjacent material surfaces are to be prepared and utilized in the repair.

CAUTION: Do not remove any of the translucent bond primer.

(1) In order to obtain the best possible bond in an area adjacent to an original bond adhesive zone common to repair details, it is recommended that the existing adjacent structure be chemically stripped using only a plastic spatula and/or mild Scotchbrite pad to remove the softened finishes (e.g., paint, epoxy primer).

CAUTION: Solvents should be considered flammable and should not be exposed to flame or spark. Fresh air masks and adequate ventilation are required.

(2) Thoroughly flush the stripped area with Methyl Propyl Ketone (MPK) and remove any trapped stripper. (3) The stripper surface should then be double wiped with MPK and clean cheesecloth to remove any residual paint or stripper. (a) Wipe the surface with a wetted cheesecloth as needed to dissolve or loosen soil. Work on a small enough area so that the surface being cleaned remains wet. If solvent evaporates it will redeposit the contamination onto the surface.

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(b) Immediately wipe the wet surface with a dry clean cheesecloth. Repeat wet and dry wipes until there is no discoloration on the drying cloth. (c) Solvent-cleaned surfaces shall be processed as soon as possible after cleaning and drying.

NOTE: If solvent-cleaned details are not processed within 12 hours, they shall be cleaned again before processing. E. If the existing structure is not part if a production bond assembly, it may simply have chemical film and epoxy primer (or zinc chromate primer) as a finish. Bonds should never be done directly to zinc chromate primer. If the existing finish is zinc chromate primer over chemical film, chemically strip the primer and apply chemical film and epoxy primer. F. Although not the preferred method, bonds directly to epoxy primer should only be done after the epoxy primer is vigorously scuffed with mild Scotchbrite pad to roughen the surface, followed by double wiping with MPK , then with a clean cheesecloth to remove residue.

3. Repair Detail Layout A. Perform operations for mechanical fasteners such as detail location, hole drilling, and deburring. B. Disassemble and clean all bond faying surfaces with MPK. Double wipe with a clean cheesecloth and solvent, then final wipe with a clean dry cheesecloth as described above. Handle cleaned surfaces only if necessary and only with clean cotton gloves.

4. Adhesive Mixing - Room Temperature Type I Paste (EA9309.3na and EA9339) A. Both referenced adhesives are a two-part material which must be weighed to get the correct proportions. Pre-weighed tube applicators of EA9339 (Cessna Part No. U000710, 6 oz. Sem Kit) require no additional weighing. B. Limit the amount of adhesive to be mixed at one time. Larger amounts create heat, reducing pot life. Reducing mixed adhesive into small batches will prolong pot life. Pot life is approximately 1/2 hour for EA9309.3na or 2 to 2 1/2 hours for each EA9339 after mixing. Each component of two-part material shall be weighed and thoroughly mixed before use. Follow manufacturer's mixing instructions and shelf-life of materials.

5. Application of Paste Adhesive A. Room temperature curing paste adhesives may be applied using a spatula, knife-type spreader, roller, or brush. Apply adhesive between 0.010 and 0.020 inch thickness to both bond mating surfaces. Ensure complete coverage over entire mating surfaces. Paste adhesives shall have a bondline thickness of 0.005 to 0.015 inch when cured. Nylon monofilament or glass yarn scrim cloth may be used to obtain correct bondline thickness.

NOTE: With structural adhesives, the strength of the bondline will go down if the thickness exceeds recommended limits.

6. Assembly of Bond Details A. Assemble details, install clamps or other mechanical means of pressure, and cure adhesive a minimum of 18 hours at room temperature prior to installing fasteners or removing clamps.

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CAUTION: Extreme care must be used when silicone release agent is in the vicinity of a bonding operation. Insure that application of silicone is done away from any bond surface to eliminate airborne silicone contamination. Insure that wiping cloths or other materials exposed to silicone are discarded and not reused.

NOTE: Pressure must be applied within the pot life of the adhesive. Excess adhesive must be removed before the adhesive cures. On outside skin joints, use excess adhesive or apply sufficient adhesive to fill skin gap and give a smooth surface. Excess uncured adhesive beyond the skin gap can be removed with a plastic spatula followed by clean cheesecloth and MPK.

NOTE: If using Clecos, it is recommended that draw-type or wing nut type Clecos be used in every fastener hole. If the material being bonded is thin sheet (<0.040) it is recommended that large, flat, thick washers or thick plates be used next to the thin sheets to more evenly distribute the adhesive locally and to minimize the “pillowing effect” between fasteners. To ease removal later, dip the Clecos in liquid silicone lubricant and allow lubricant to dry completely prior to installation. Install the Clecos starting at the center of the area being bonded and in a circular pattern from the center to the outer edges of the bonded area to gently allow the paste adhesive to flow and extrude the excess adhesive outward.

NOTE: Accelerated cure can be done by the addition of heat no greater than 200° F for one hour.