Cessna 525, 525a & 525b Atlas Winglet Maintenance Manual Supplement
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101TAMARACK AEROSPACE GROUPSANDPOINT, IDAHO USA 83864CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL 452/1475/1480EFFECTIVITY:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ONREPORT NUMBER: TAG-1100-0101Report Date:03 September 2019Prepared By:N. CropperChecked By:M. RoweApproved By:N. CropperEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 1G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101RECORD OF REVISIONSIssueDateByReason for ChangeIR3 February 2017NRInitial ReleaseA17 April 2017NRThroughout, various corrections in formatting & references,clarification of part numbers and materials.Sec. 6 – inserted NOTE specifying torque requirementsClarified process for disabling ATLAS prior to any maintenancethroughout.6.C.(1)(a)6 corrected 525B annunciator LRU removal instruction6.C.(3)(a) Expanded inspection process for annunciator6.D.(1)(a) inserted Step 26.F.(1)(a)2 added removal of winglet glare shield6.F.(b) updated NOTE6.F.(b) Expanded Step 1, updated Step 86.G.(3)(a) updated Step 36.K.(2)(b) expanded Step 1, added “clamp-up bushing” to Step 3,corrected part number in Step 4, corrected resistance specified inStep 5.6.L.(1)(b) corrected resistance specified in Step 5.6.L.(3)(b) updated Step 66L(4) added Step (e)6.N.(1)(g) added “ATLAS INOP button light should extinguish”6.N. inserted (2)Updated ACU PN in Table 7-3.B26 April 2017MRCorrected Table 7-2 to include life limitation for TACS ReturnSpring.C25 July 2017NRThroughout, various corrections in formatting & references.Add 525A information to document.6. Several adjustments to better harmonize with Cessnamaintenance program:6.D.(2)(f) Adjusted content to improve winglet inspection processand criteria.6.F.(2)(a) Adjusted content to include additional inspection todetermine internal damage without removing winglet at first.6.F.(2)(b) (Winglet Spar inspection) Deleted inspection, nowcovered with winglet inspection.6.K.(3)(a) Adjust Heading Name, added new 5 to inspect forgrease leakage and adjusted 6 (was 5)7. Revise Airworthiness Limitations; Added: “The Airworthinesslimitations section is EASA approved and provides instructions forcontinued airworthiness information.”Added “Inspection Interval Codes” and NOTE.Table 7-1 Change interval time to match Cessna inspectioninterval code, delete winglet spars, adjust TCU inspection intervaland order of items in table. Add caveat for inspection interval forBearings, Bushings, and Fasteners for those with improved (ball)bearing installed.22-50Page 2GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101IssueDateByC(cont.)D28 August 2017NRE01 February 2019JKEffectivity:Reason for ChangeTable 7-2 deleted TCU replacement. Added 6.K.(3).(a) to definereplacement.Table 7-3 Change ACU recalibration interval to harmonize withCessna inspection rhythm.Table 7-1 Correct Alignment of “internal hardware”Add new section M for TACS return spring removal / install.Update section labels and references as needed, updatereference shown in table 7-2.Table 7-3 added ref to 6.B.(1) for removal / install of ACU.Throughout, update numbering, and update opening and closingcircuit breakers for 525B.Cover and Section 1 add project 1475.Section 6.B.Update Section 6.B.(1) to specify for ACU w/o D38999 ConnectorsUpdate Section 6.B.(1)(b)1WAS: “Slide the ACU onto the wing root mounting rack until itnests against the aft clamp and per FIGURE 6-2.”IS: “Slide the ACU onto the wing root mounting rack until itnests against the aft clamp and tighten the four bolts thatsecure the ACU per FIGURE 6 2.”Add Section 6.B.(2) Removal/Installation of ACU w/ D38999ConnectorsInsert Figure 6-4Section 6.C.Update section 6.C.(1).(b) heading and steps 3 & 4Deleted section 6.C.(1).(c) and Figure 6-5 ANNUNCIATOR LRUINSTALLATION - 525B Only; this configuration was neverinstalled and has been removed as an alternate installation inthe drawing package.Update Figure 6-22 TACS Balancing Fixture (Top View) to avoidclash with TACS centering stripsSection 6.O.(1):(e) added: First to test the upper LEDs, second to test the lowerLEDs and third to test all the LEDs.(g) added “NOTE: If this circuit breaker is left open for more than 3seconds, then a button push or a power cycle will be needed toextinguish the light.”Section 7. update Table 7-1 to clarify applicability of intervalvariation for Bearings, Bushings, and FastenersWAS: 100 Flight Hours / 3C* IS: 3C / *100 Flight HoursNote below table updatedWAS: *Applicable for ATLAS Kit 022 and higher; or if SBATLAS57-02 has been completed.IS: *Applicable if ATLAS Kit 101-0001 thru 101-0021 is installedand SBATLAS-57-02 has not been completed.525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 3G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101IssueDateByReason for ChangeF30 April 2019JKFormatting changesUpdate Table 3-1 WAS: 5180002-1, IS: 5180002-1 (or equivalent)Section 6.L.(2)1. WAS: TACS balancing limits are 1.5 in-lbover balance to -1.5 in-lb underbalance;IS: TACS balancing limits are 1.5 in-lb over balance to -4.9in-lb underbalanceG22-50Page 4G03 September 2019NCSection 6.B.(4)(c) updated, ACU sealant only applicable to ACU w/oD38999 receptacles.Section 6.L.(5)(a)Update step 1 added disbondAdded step 2, inspection of centering strips,Added Figure 6-30Table 7-1 updated,WAS: TACS Skins IS: TACS Skins & Centering StripsEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101TABLE OF CONTENTSRECORD OF REVISIONS . 2TABLE OF CONTENTS . 5LIST OF FIGURES. 6LIST OF TABLES . 71. Introduction . 82. Applicability . 93. Special Tools, Materials and Reference Documents . 94. Abbreviations and Acronyms . 105. Description and Operation . 11A. Description . 11B. Operation . 11C. System Components . 13D. Torque Data . 15E. Dimensions and Areas . 156. Maintenance Instructions . 16A. ATLAS INOP Button . 16B. ACU . 19C. Annunciator LRU . 25D. Extension . 28E. Wing Tip Navigation/Anti-Collision Light . 33F. Winglet. 35G. Static Wicks . 44H. Vertical Tail Navigation/Anti-Collision Light . 45I. Main ATLAS Relay . 47J. Bellcrank . 50K. TCU. 53L. TACS . 56M. TACS Return Spring . 72N. Hinge Bearings . 73O. ATLAS . 757. Airworthiness Limitations . 768. ATLAS Troubleshooting. 79Effectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 5G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101LIST OF FIGURESFIGURE 1-1 ATLAS WING TIP .8FIGURE 5-1 ATLAS FUNCTIONAL DIAGRAM. 12FIGURE 6-1 ATLAS INOP BUTTON INSTALLATION . 18FIGURE 6-2 ACU INSTALLATION w/o D38999 CONNECTORS . 22FIGURE 6-3 ACU SEALANT APPLICATION; ACU w/o D38999 CONNECTORS . 23FIGURE 6-4 ACU INSTALLATION w/ D38999 CONNECTORS . 24FIGURE 6-5 ANNUNCIATOR LRU INSTALLATION . 27FIGURE 6-6 EXTENSION LEADING EDGE INSTALLATION . 29FIGURE 6-7 NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION. 34FIGURE 6-8 WINGLET INSTALLATION. 37FIGURE 6-9 AILERON & TACS ALIGNMENT . 38FIGURE 6-10 WINGLET/END RIB INTERFACE . 39FIGURE 6-11 WINGLET Z CLIP FASTENER LOCATIONS. 40FIGURE 6-12 WINGLET Z CLIP LOCATION . 41FIGURE 6-13 WINGLET ATTACHMENT FASTENER LOCATIONS – 525 & 525A . 42FIGURE 6-14 WINGLET ATTACHMENT FASTENER LOCATIONS – 525B . 43FIGURE 6-15 VERTICAL TAIL NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION . 46FIGURE 6-16 MAIN ATLAS RELAY INSTALLATION – 525 . 48FIGURE 6-17 MAIN ATLAS RELAY INSTALLATION – 525A & 525B . 49FIGURE 6-18 BELLCRANK INSTALLATION . 52FIGURE 6-19 TCU INSTALLATION . 55FIGURE 6-20 TACS INSTALLATION . 57FIGURE 6-21 BALANCE WEIGHT ACCESS . 59FIGURE 6-22 TACS BALANCING FIXTURE (Top View) . 60FIGURE 6-23 TACS BALANCING FIXTURE (Side View) . 61FIGURE 6-24 TACS BALANCE WEIGHT . 62FIGURE 6-25 TCU ROD END . 65FIGURE 6-26 TACS KINEMATICS . 66FIGURE 6-27 ATLAS HARD STOP CLEARANCE CHECK . 67FIGURE 6-28 TACS SPRING BOLT RIGGING . 68FIGURE 6-29 TACS HINGE FUNCTIONAL TEST . 69FIGURE 6-30 TACS CENTERING STRIPS . 70FIGURE 6-31 TACS RETURN SPRING . 72FIGURE 6-32 TACS HINGES . 73FIGURE 6-33 BEARING INSTALLATION . 74FIGURE 8-1 ATLAS FAULT VERIFICATION; FLOW DIAGRAM . 80FIGURE 8-2 ATLAS UNPOWERED, NO FAULT ANNUNCIATION; FLOW DIAGRAM . 81FIGURE 8-3 TACS INOPERATIVE; FLOW DIAGRAM . 82FIGURE 8-4 ATLAS WON'T RUN BIT; FLOW DIAGRAM . 8322-50Page 6GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101LIST OF TABLESTABLE 3-1 SPECIAL TOOLS. 9TABLE 3-2 MATERIALS . 9TABLE 3-3 REFERENCE DOCUMENTS . 9TABLE 5-1 MODIFIED DIMENSIONS – 525 . 15TABLE 5-2 MODIFIED DIMENSIONS – 525A. 15TABLE 5-3 MODIFIED DIMENSIONS – 525B. 15TABLE 7-1 INSPECTION INTERVALS – ATLAS COMPONENTS . 77TABLE 7-2 REQUIRED REPLACEMENT TIMES. 78TABLE 7-3 REQUIRED MAINTENANCE INTERVAL . 78TABLE 8-1 ATLAS TROUBLESHOOTING . 79Effectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 7G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-01011. IntroductionThe procedures in this manual describe the personnel, tools, skills, techniques and stepsrequired to maintain the Tamarack Active Technology Load Alleviation System (ATLAS)winglets on the Cessna 525, 525A and 525B Citation in accordance with Cranfield AerospaceSolutions modifications CAeM/Cessna/1375/1430/1440/1452/1475/1480. This manual isintended to satisfy the requirements of EASA CS-23.1529 and CFR Part 23, Sec. 23.1529 bypresenting information essential to the continued airworthiness of the aircraft.Maintenance of the ATLAS and its associated components must be performed by appropriatelyrated personnel or facilities. Prior to performing maintenance on the ATLAS, carefully readthese instructions and ensure that you understand them fully.FIGURE 1-1 ATLAS WING TIP(525B Winglet Shown)22-50Page 8GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-01012. ApplicabilityMakeModelSerial NumberCessna525525-0001 to 525-0701525-0800 and on.Cessna525A525A-0001 to 525A-0299525A-0300 and on.Cessna525B525B-0001 to 525B-0056525B-0058 to 525B-0450525B-0057525B-0451 and on.3. Special Tools, Materials and Reference DocumentsTABLE 3-1 SPECIAL TOOLSPN5180002-1(or equivalent)-NameControl Surface BalanceFixture KitDigital InclinometerUseVendorTACS BalancingCessnaTACS RiggingLocal ProcurementTABLE 3-2 MATERIALSPNP/S 870 CLASS BLoctite 242 orLoctite 2433M 23 orAA59163 FR4 Tape3145 RTVNameCorrosion InhibitiveSealantThreadlockerUseEdge and Gap SealingVendorLocal ProcurementACU fastener securityLocal ProcurementSelf-Fusing TapeACU SealingLocal ProcurementAdhesive SealantACU SealingLocal ProcurementTABLE 3-3 REFERENCE DOCUMENTSDocumentNameCA/DD/SB1375 Installation of Tamarack ATLASService Bulletin - 525DescriptionOverview of ATLAS 525 Installation.CAS/SB1440Installation of Tamarack ATLASService Bulletin – 525BOverview of ATLAS 525B Installation.CAS/SB1452Installation of Tamarack ATLASService Bulletin – 525AOverview of ATLAS 525A Installation.CA/DD/M022Cessna 525, 525A and 525B ATLASWinglet Illustrated Parts CatalogIllustrated Parts Catalogue for ATLASInstallation.CA/DD/M024Wiring Diagram Manual SupplementWiring diagrams applicable to installationof the Tamarack ATLAS system.Effectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 9G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101OEM Reference DocumentationNameRevisionModel 525 Maintenance Manual . CurrentModel 525A Maintenance Manual. CurrentModel 525B Maintenance Manual. Current4. Abbreviations and AcronymsSee below for a list of abbreviations and acronyms used throughout this document.ACUATLAS Control UnitATLASActive Technology Load Alleviation SystemAFMSAirplane Flight Manual Light Emitting DiodeOTBDOutboardTACSTamarack Active Camber SurfaceTCUTACS Control Unit22-50Page 10GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-01015. Description and OperationA. DescriptionThe Active Technology Load Alleviation System (ATLAS) is a system which provides for theinstallation of aluminum wing extensions and carbon fiber composite winglets on the CessnaCitation 525, 525A and 525B without requiring the traditional major structural modificationsof the wing.Aerodynamic surfaces called Tamarack Active Camber Surfaces (TACS) mounted in thewing extensions either hold their position in trail with the wing, or symmetrically deploytrailing edge up or down to modify wing lift and relieve structural loads as required bydifferent flight conditions. An electronic controller called the ATLAS Control Unit (ACU) ismounted near the center of gravity of the airplane and detects fuselage verticalaccelerations. Based on fuselage acceleration, the ACU commands movements of TACSControl Units (TCUs) in the wingtips. This causes the TACS to deploy as required duringflight. The actuation of the TACS is independent of any other flight control and respondsproportionally to fuselage acceleration.The ATLAS installation also includes modifications to the anti-collision and navigation lights.A new integrated LED anti-collision/navigation unit is included with each winglet. A newintegrated anti-collision/navigation tail light is also installed in place of the existing unit.B. OperationThe ATLAS takes the vertical acceleration of the fuselage and converts it to an automaticaerodynamic load alleviation targeted at the wing tip. Normal operation of the ATLAS isautomatic, requiring no input from the pilot. A basic functional diagram of the ATLAS isshown in FIGURE 5-1.A new LED-illuminated momentary button, the ATLAS INOP Button, is installed in thecockpit as a part of the installation. In the event of a system fault, the LEDs in the button willilluminate to alert the pilot of the fault condition. In response, the pilot need only reduceairspeed to 140 KIAS (525), 161 KIAS (525A & 525B) or below. The ATLAS Airplane FlightManual Supplement (AFMS) presents procedures for resetting ATLAS in the event of a fault.The ATLAS INOP Button is tied into the cockpit light dimming switch.Operation of the navigation and anti-collision lights is unchanged from the pilot’sperspective.WARNING:Effectivity:THE TACS WILL MOVE RAPIDLY AND FORCEFULLY TO NEUTRALPOSITION WHEN THE AVIONICS POWER SWITCH IS MOVED TO THEON POSITION. BE SURE THAT ALL PERSONNEL AND EQUIPMENT ARECLEAR BEFORE MOVING SWITCH TO THE ON POSITION.525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 11G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101ATLAS INOP BUTTON –DISPLAYS FAULTEDCONDITIONS ANDPROVIDES BIT COMMANDSTO ANNUNCIATOR LRU(525A & 525B shown)AIRCRAFT VERTICALACCELERATIONACU –INTERPRETS AIRCRAFTACCELERATION INPUTSAND CONVERTS TOCOMMAND SIGNAL TOSEND TO TCU,MONITORS ATLASHEALTH AND OUTPUTSFAULTS TOANNUNCIATOR LRU.ANNUNCIATOR LRU – CONVERTSFAULTED INPUTS FROM ACU TO AFAULT OUTPUT WHICH CAN BEDISPLAYED BY THE ATLAS INOPBUTTON. INPUTS BIT COMMANDTO ACU.TCU – CONVERTS ACUCOMMAND SIGNAL TO LINEARMECHANICAL ACTUATIONPROPORTIONAL TO VERTICALACCELERATIONTACS – CONVERTS LINEARACTUATION FROM TCU ANDMECHANICAL LINKAGES TOA LOAD ALLEVIATINGAERODYNAMIC FORCEFIGURE 5-1 ATLAS FUNCTIONAL DIAGRAM22-50Page 12GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101C. System ComponentsATLAS INOP ButtonThe ATLAS INOP Button is positioned in the pilot’s primary field of view on the lefthand side of the instrument panel.The ATLAS INOP Button serves three purposes. Its primary purpose is to receiveATLAS fault condition signals from the Annunciator LRU and display the faultedcondition to the pilot.Its second purpose is to clear faulted conditions. If the ATLAS faults the button willilluminate. A single button push will reset the fault annunciation circuitry in the ACUin an attempt to clear a latched faulted condition. If after a single button push thebutton remains illuminated, the pilot may attempt to reset the system via theBuilt-In-Test (BIT), as described below.When the button is pushed 3 times within 3 seconds the ATLAS will run a BIT andtest its internal fault annunciation circuitry and the functionality of the Light EmittingDiodes (LEDs) internal to the button.The sequence for a BIT is as follows:1. Push Button 3 times within a 3 second window.2. The button will flash 3 times. One to test the upper LEDs, one to test the lowerLEDs and one to test all the LEDs.3. When all the LEDs are illuminated the ATLAS is running its BIT and if no faultexists in its internal circuitry the lights will extinguish. If an internal fault wasdetected the lights will remain illuminated and maintenance action is required.The ATLAS INOP Button may blink off momentarilybefore re-illuminating and showing a faultedcondition. The TACS may move as well but will returnto their neutral positions.Annunciator Line Replaceable Unit (LRU)The purpose of the Annunciator LRU is to take the faulted condition signal from theACU and convert it into a powered signal that drives the illumination of the ATLASINOP Button. No fault annunciation logic circuitry exists in the Annunciator LRU.ATLAS Control UnitThe ATLAS Control Unit (ACU) contains the logic circuitry which is used to convertaircraft vertical acceleration into a command output signal.Also contained within the ACU is circuitry for health monitoring of the ATLAS. TheACU monitors several internal parameters of the ATLAS and if any one of them fallsoutside of their normal operational limits the ACU will sense the condition andconvert it to a fault signal. The fault signal is sent out to the Annunciator LRU whichis then displayed to the pilot.The ACU is mounted under the fuselage forward of the forward wing spar, accessedthrough panels: 525 – 191AL; 525A – 192A; 525B – 163A, 163B.Effectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 13G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101TACS Control UnitThe TACS Control Unit (TCU) contains an electromechanical actuator and itsassociated control circuitry. It converts the command output signal from the ACU to amechanical actuation proportional to fuselage vertical acceleration.There are 2 TCUs, one located in each wing tip and can be accessed throughpanels: 525 – 542HB & 642HB; 525A – 542GB & 642GB; 525B – 542GB & 642GB.Main ATLAS RelayThe main ATLAS relay controls the 28VDC supply to the TCUs. 28VDC is drawnfrom the RH feeder bus through the main ATLAS relay and then out to the right sideand left side TCUs.The main ATLAS relay is located on the relay rack in the right side of the AFT J-Boxwhich is accessed through the aft baggage compartment.Tamarack Active Camber SurfaceThe Tamarack Active Camber Surface (TACS) and its associated mechanicallinkages convert the mechanical actuation of the TCU into aerodynamic force usedfor load alleviation. The TACS will symmetrically deflect trailing edge up or down toalleviate wing loads resulting from a positive or negative fuselage verticalacceleration, respectively.The TACS are located outboard of the ailerons. There are 2 for any ATLASinstallation, one per wing tip. The TACS is physically connected to the aft spar of thewing extension by two hinges.Wing ExtensionTwo wing extensions, one per wing tip are added to the end of the original wing andextend outboard 28 inches from the last wing rib.WingletTwo carbon fiber winglets (one per wing tip) provide an aerodynamic efficiencyincrease. They are mounted to the most outboard rib of the wing extension.Wingtip Navigation/Anti-collision LightInstallation of the winglets on the Cessna 525, 525A and 525B eliminates the originalwing tip navigation light assemblies. They are replaced with new TSO-approvednavigation/anti-collision light assemblies mounted on the leading edge of the wingletjust outboard of the wing extension.Vertical Tail Navigation/Anti Collision LightA new TSO-approved vertical tail dual navigation/anti-collision light replaces theoriginal vertical tail light assembly which was only a single navigation light. Twoadditional wires run to the tail to provide power and synchronization for theanti-collision light. A new connector mounting bracket is also installed along with theupdated tail light.22-50Page 14GEffectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG-1100-0101D. Torque DataUnless otherwise noted, torque fasteners in accordance with the Cessna 525/525A/525BMaintenance Manual (AMM) Chapter 20-10.E. Dimensions and AreasThe winglet and wing extension installation increases several dimensions on the 525, 525A, and525B. See the tables below for the relevant updated dimensions and areas.TABLE 5-1 MODIFIED DIMENSIONS – 525DimensionMeasurementWingspan52.5 ft(16.0 m)Wing Area248.8 ft2(23.1 m2)TABLE 5-2 MODIFIED DIMENSIONS – 525ADimensionMeasurementWingspan56.16 ft(17.12 m)Wing Area273.15 ft2(25.38 m2)TABLE 5-3 MODIFIED DIMENSIONS – 525BDimensionMeasurementWingspan59.95 ft(18.27 m)Wing Area302.876 ft2(28.19 m2)Effectivity:525-0001 TO 525-0701, 525-0800 & ON525A-0001 TO 525A-0300 & ON525B-0001 TO 525B-0451 & ON22-50Page 15G
CESSNA 525, 525A & 525B ATLAS WINGLETMAINTENANCE MANUAL SUPPLEMENTTAG
CESSNA 525, 525A & 525B ATLAS WINGLET MAINTENANCE MANUAL SUPPLEMENT TAG-1100-0101 Effectivity: 525-0001 TO 525-0701, 525-0800 & ON 525A-0001 TO 525A-0300 & ON 525B-0001 TO 525B-0451 & ON 22-50 Page 9 G 2. Applicability Make Model Serial Number Cessna 525 525-0001 to 525-0701 525-0800 and on. Cessna 525A 525A-0001 to 525A-0299 525A-0300 and on.
-66 Type rating endorsement 441 Cessna 441 (Honeywell TPE331) 500 Citation/ Citation I Cessna 500/ 501/551 (PWC JT15D) 501 Citation I 510 Cessna 510 (PWC PW615) 525 Citation Jet CJ1 Cessna 525/525A (Williams FJ 44) 525A Citation Jet CJ2 525B Citation Jet CJ3 Cessna 525B/C (Williams FJ 44) Annex to ED Decision 2013/024/R 10/09/2013 .
EASA Type Rating and licence endorsement list - all aircraft, excluding helicopters 17 May 2021 -CMA Page 2 of 15 Single-engine piston (sea) with . Cessna 525 - CJ C525 X X SP HPA X OSD FC C525 -CJ1 525 525A - CJ2 525 - CJ1 525A - CJ2 525B - CJ3 525B - CJ3 525C - CJ4 525 - M2 .
Operational Evaluation Report - Cessna CE-525, 525A, 525B, 525C Original - March 12, 2015 ANAC, Rio de Janeiro OPERATIONAL EVALUATION REPORT - PAGE 9 3 Pilot Type Rating There are two pilot type ratings assigned to the CE-525, 525A, 525B and 525C aircraft, depending on the kind of operation: C525, for single pilot operations; and
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Operational Evaluation Board Report Cessna Citation 525C (CJ4) 22 Oct 2010 OSD FC Original Replaces and incorporates the OEB reports for the Cessna 525 (CJ, CJ1, CJ2, CJ1 , CJ2 , CJ3) and for the Cessna 525 (CJ4). Addition of the Cessna 525 M2 operational suitability data. 20 Jun 2014 OSD FC Rev 1 OSD Data for Cessna 525 CJ3 incorporated.
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Type Certificate Holder: CESSNA AIRCRAFT COMPANY P.O. Box 7704 Wichita, Kansas 67277 USA EA-9304-08 Sheet 01 CESSNA 525 525A 525B 525C 17 August 2012 This data sheet, which is part of Type Certificate No. 9304, prescribes conditions and limitations under which the product, for which the Type Certificate was issued, meets the airworthiness .
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