MAINTENANCE RECORD (THIS FORM IS TO BE RETAINED IN THE AIRCRAFT LOG)

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1 (THIS FORM IS TO BE RETAINED IN THE AIRCRAFT LOG) AIRCRAFT MAKE / MODEL: Hawker 800A AIRCRAFT TIME IN SERVICE: AIRCRAFT REGISTRATION NUMBER: N803CE AIRCRAFT LANDINGS: 5457 AIRCRAFT SERIAL NUMBER: Complied with (A1 A6, B1-B12, C1-C12 and D1- D12) 300/600/1200/2400 Hour Inspection and (E1-E12, F1-F12, and G) 12/24/48 Month Routine Airframe Inspection in accordance with the Raytheon Aircraft Flexible Maintenance Schedule 2. Complied with No. 1 and No.2 Engine 150 to 200 and 300 to 400 hour inspection (057120, ). 3. Complied with the following APU Inspections in accordance with Hamilton Sundstrand SB-T-62T Revision 10 dated August 29, 2005 and Customer supplied CAMP cards: a) 6 month / 125 hour / 250 cycle Inspection (490010) b) 6 month / 250 hour/ 500 cycle Inspection (490020) c) 12 month / 500 hour / 1000 cycle Inspection (490030) d) 12 month / 1000 hour / 2000 cycle Inspection (490040) 4. Complied with No.1 and No.2 Thrust Reverser 150 and 300 hour inspection in accordance with the Raytheon Aircraft Flexible Maintenance Schedule and using customer supplied CAMP cards Inspect No.1 Engine thrust reverser ( ) Inspect No.1 Engine thrust reverser ( ) Inspect No.2 Engine thrust reverser ( ) Inspect No.2 Engine thrust reverser ( ) 5. Complied with the following Service Bulletins and Airworthiness Directives. a) to prevent loss of all primary electrical power, which could result in the airplane operating only under emergency power. b) SB dated May 1, 2006 Electrical Power Inspection and Replacement of UMA 100 Limiter 5.1 The following Mandatory Service Bulletins have been found to be (NOT APPLICABLE) a) Revision 1 Dated AIR CONDITIONING - Installation Of Improved Air Conditioning Duct Sleeves And Clamps Mod. 25F963A Mod. 25F963B (A.D ) (Not Applicable) b) Revision 1 Dated AIR CONDITIONING - Removal Of Air Conditioning Duct Sleeve Bedding Strips Mod. 25G032A Mod. 25G032B Mod. 25F032C (A.D ) (Not Applicable) c) Dated ELECTRICAL POWER Emergency Power Supply Unit To Revise Jet Pack Battery Output Voltage Monitoring. Mod 25A624A Effectivity: (Not Applicable By Serial Number) d) Revision 1 Dated INSTRUMENTS - Removal Of The Fuel Flow Electrical Signal To The Fairchild F1000 Flight Data Recorder (FDR). (Not Applicable) e) Dated LANDING GEAR - Brake Control Valve - Failure Of Knife Edges (A.D ) (Not Applicable) f) Dated DUNLOP EMERGENCY BRAKE REDUCING VALVE - Failure Of Knife Edges (A.D ) (Not Applicable) g) Dated LANDING GEAR - Main Landing Gear Door Uplock Thread Inspection (A.D ) (Not Applicable By Serial Number) h) Revision 1 Dated LIGHTS Pulselite System Bus Wiring Modification (Not Applicable) i) Dated LIGHTS Reactivation Of Precise Flight Pulelite System (Not Applicable By Serial Number) j) Dated NAVIGATION - Introduction Of Revised Setting Module For Altitude Alerting Unit Mod. No (Not Applicable) k) 35-A25 Dated SUPPLY VALVE - Insecurity Of Threaded Insert In Gland Bush (A.D ) (Not Applicable) l) Dated OXYGEN To Introduce Replacement Oxygen Fitting In Lieu Of Fitting Incompatible With The Oxygen System Effectivity: All (Not Applicable) m) Revision 1 Dated FUSELAGE - To Introduce Improved Fluid Drainage In The Fuselage. Mod D (A/C S/N Only) (Not Applicable By Serial Number) 6. Complied with the following AFMS, NTM / NDT techniques Inspect main landing gear fairing strut NTM Inspect flight compartment skin and window structure above windshields NTM A Main entrance door X-Ray NTM Elevators X-Ray the internal structure NTM & Rudder X-Ray the internal structure NTM

2 Inspect X-Ray wing bottom skins and stringers between the front and rear spars, rib 0 to rib1 and between the center spar and rear spar from rib 1 to rib 4 NTM Ailerons inspect hinge brackets NTM Inspect flap and flap vanes NTN , Inspect aileron horn balance weight NTM Complied with the following Raytheon Aircraft Flexible Maintenance Schedule codes, customer supplied CAMP cards Lubricate area G-150 hour Inspect APU starter/generator No.2 Starter/Generator overhaul 32R123 Inspect and reshim main gear scissor links on all three gear Test passenger Oxygen masks Inspect font pressure bulkhead Inspect entry door surround Inspect skin exterior under the dorsal intake, forward of frame Inspect fuselage skin under wing-to-fuselage Inspect wing to fuselage attachment links, brackets and bolts Inspect left side front face of rear pressure bulkhead Inspect horizontal stabilizer to vertical stabilizer rear attachment fittings Inspect elevators Lubricate connecting rods, elevator trim tabs Inspect rudder Lubricate connecting rods, rudder trim tab and anti-servo tab Inspect elevator mass balance weights and spigots Inspect main landing gear and side stay attachment fittings Inspect wing top skin, left and right, in the area of the wing fence Inspect left lower, left upper, right lower and right upper airbrake Inspect wing rear spar, rear face Inspect ailerons Lubricate connecting rods, aileron trim and servo tabs Inspect wing leading edges (post mod B) Inspect aileron at outboard hinge casting Inspect wing fairing (Avionics) seal Replace No.1 and No.2 fuel filters Check No. 3 battery electrolyte Check No. 4 battery electrolyte Check No. 5 battery electrolyte Inspect life vests 8. Removed, replaced, repaired, inspected and/or reinstalled the following items. a) Brake Assembly, No.1 removed P/N: AHA1897 S/N: YO23 installed P/N: AHA1897 S/N: QN162 reference FAA Form dated July 31, 2006, Tracking No.WO32187 b) Brake Assembly, No.2 removed P/N: AHA1897 S/N: SM039 installed P/N: AHA1897 S/N: ZV104 reference FAA Form dated July 11, 2006, Tracking No.WO31964 c) Fuel filter, No.1 and No.2 engine removed P/N: installed new P/N: same reference FAA Form dated March 13, 2006, Tracking No d) Oxygen Bottle, No.3 removed P/N: S/N: installed inspected P/N: same S/N: same reference FAA Form dated July 31, 2006, Tracking No Note: Next Hydro Test Due July 2011 e) Rods, thrust reverser left 4ea removed P/N: installed inspected 4ea P/N: same f) Rods, thrust reverser right 4ea removed P/N: installed inspected 4ea P/N: same g) Starter/Generator, No.2 removed P/N: S/N: 6141 installed overhauled P/N: S/N: 6141 reference FAA Form dated August 7, 2006, Tracking No. SE2R h) Switch, Cabin lighting removed P/N: HSP-017 S/N: installed repaired P/N: same S/N: same reference FAA Form dated July 31, 2006, Tracking No. AI i) Switch, Cabin lighting removed P/N: HSP-018 S/N: installed repaired P/N: same S/N: same reference FAA Form dated August 4, 2006, Tracking No. AI j) Switch, hydraulic reservoir over heat detector removed P/N: 150T283 S/N: 1277 installed inspected P/N: same S/N: same reverence FAA Form dated July 25, 2006, Tracking No. M k) Windshield, Copilots A removed P/N: S/N: L installed new P/N: S/N: L reference EASA Form 1 dated July 1, 2006, Tracking No l) Windshield, Copilots B removed P/N: S/N: installed new P/N: S/N: L reference EASA Form 1 dated July 7, 2006, Tracking No m) Battery, No.1 removed P/N: S/N: Installed new P/N: S/N: reference FAA Form dated, Tracking No. n) Battery, No.2 removed P/N: S/N: Installed new P/N: S/N: reference FAA Form dated, Tracking No.

3 o) Battery, No3 removed P/N: CA-126 S/N: installed inspected P/N: same S/N: same reference FAA Form dated August 7, 2006, Tracking M4659 p) Battery, No4 removed P/N: CA-126 S/N: installed inspected P/N: same S/N: same reference FAA Form dated August 7, 2006, Tracking M4659 q) Battery, No3 removed P/N: CA-126 S/N: installed inspected P/N: same S/N: same reference FAA Form dated August 7, 2006, Tracking M4659 r) Controller, removed P/N: S/N: installed repaired P/N: same S/N: same reference FAA Form dated August 8, 2006, Tracking No s) Life Vest, P/N: P S/N: A37724 inspected reference FAA Form dated August 2, 2006, Tracking No. AN16697 t) Life Vests, 7ea P/N: P0723E105P S/N: 33816, 33832, 33868, 33881, 33919, and inspected reference FAA Form dated August 2, 2006, Tracking No. AN16696 u) Life Vest, 2ea P/N: P S/N: and inspected reference FAA Form dated August 2, 2006, Tracking No The following wing attaching links and bolts have been inspected reference FAA form dated July 24, 2006, July 25, 2006 and July 26, 2006 a) Left forward upper wing link bolt P/N: 25-8WS b) Left forward inboard wing link bolt P/N: 25-8WS c) Left forward lower wing link bolt P/N: 25-8WS d) Left forward horizontal wing link P/N: 25-8WS e) Left forward vertical wing link P/N: 25-8WS f) Right forward wing link P/N: 25-8WS g) Right forward upper wing link bolt P/N: 25-8WS h) Right forward lower wing link bolt P/N: 25-8WS i) Left aft upper wing link bolt P/N: 25-8WS j) Left aft lower wing link bolt P/N: 25-8WS k) Left aft wing link P/N: 25-8WS l) Right aft upper wing link bolt P/N: 25-8WS m) Right aft lower sing link bolt P/N: 25-8WS n) Right aft wing link P/N: 25-8WS This Aircraft is in compliance with all applicable Airworthiness Directives through Bi-Weekly NOTE: All components removed, replaced and/or reinstalled were rigged, operationally checked and leak checked in accordance with current revisions of the Hawker 800 Maintenance Manual, with respect to work performed, this aircraft is approved for return to service. For more information on work performed, reference Work Order No. M 4660, M4659, E, E and WO on file at this facility. (.Airframe Log- ) (MC-RSM-013A (Revision 2, 05/06)) (f) (3) INSPECTION PROGRAM THE AIRCRAFT IS DETERMINED TO BE

4 (THIS FORM IS TO BE RETAINED IN THE ENGINE LOG) AIRFRAME HOURS: AIRFRAME LANDINGS: 5457 ENGINE MODEL: TFE731-5/-5AR/-5 ENGINE TIME: ENGINE SERIAL NUMBER: P (No.1) ENGINE CYCLES: Complied with No. 1 Engine 150 to 200 and 300 to 400 hour inspection. 2. Removed, replaced, repaired, inspected and/or reinstalled the following items. a) Fuel filter, No.1 and No.2 engine removed P/N: installed new P/N: same reference FAA Form dated March 13, 2006, Tracking No b) Adapter, Starter/Generator removed P/N: NSN installed new P/N: same NSN reference FAA Form dated June 6, 2006, Tracking No. B All Maintenance, Operational, Functional and Leak Checks were complied with in accordance with HS Maintenance Manual and 731-5R Light Maintenance Manual Report No , Revision 3, dated January 16, For more information on work performed, reference Work Order No. M4660, M4669 on file at this facility. (.Engine- -Log- ) (MC-RSM-013B (Revision 2, 05/06)) (f)(3) INSPECTION PROGRAM THE ENGINE IS DETERMINED TO BE

5 (THIS FORM IS TO BE RETAINED IN THE ENGINE LOG) AIRFRAME HOURS: AIRFRAME LANDINGS: 5457 ENGINE MODEL: TFE731-5/-5AR/-5 ENGINE TIME: ENGINE SERIAL NUMBER: P (No.2) ENGINE CYCLES: Complied with No.2 Engine 150 to 200 and 300 to 400 hour inspection. 2. Removed, replaced, repaired, inspected and/or reinstalled the following items. a) Fuel filter, No.1 and No.2 engine removed P/N: installed new P/N: same reference FAA Form dated March 13, 2006, Tracking No All Maintenance, Operational, Functional and Leak Checks were complied with in accordance with HS Maintenance Manual and 731-5R Light Maintenance Manual Report No , Revision 3, dated January 16, For more information on work performed, reference Work Order No. M4660, M4669 on file at this facility. (.Engine- -Log- ) (MC-RSM-013B (Revision 2, 05/06)) (f)(3) INSPECTION PROGRAM THE ENGINE IS DETERMINED TO BE

6 (THIS FORM IS TO BE RETAINED IN THE APU LOG) AIRFRAME HOURS: AIRFRAME LANDINGS: 5457 APU MODEL: T-62T-40C8D1 APU HOURS: APU SERIAL NUMBER: SP-E APU STARTS Complied with the following APU Inspections in accordance with Hamilton Sundstrand SB-T-62T Revision 10 dated August 29, 2005 and Customer supplied CAMP cards: a) 6 month / 125 hour / 250 cycle Inspection (490010) b) 6 month / 250 hour/ 500 cycle Inspection (490020) For more information on work performed, reference Work Order No. M4659, M4660 on file at this facility. (.APU Log- ) (MC-RSM-013C (Revision 2, 05/06)) (f)(3) INSPECTION PROGRAM THE APU IS DETERMINED TO BE

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