cessna 525, 525a & 525b atlas winglet maintenance …

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

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TAMARACK AEROSPACE GROUP

SANDPOINT, IDAHO USA 83864

CESSNA 525, 525A & 525B ATLAS WINGLET

MAINTENANCE MANUAL SUPPLEMENT Modification

CAeM/Cessna/1375/1430/1440/1452/1475/1480

EFFECTIVITY:

525-0001 TO 525-0701, 525-0800 & ON

525A-0001 TO 525A-0300 & ON

525B-0001 TO 525B-0451 & ON

REPORT NUMBER: TAG-1100-0101

Report Date: 03 September 2019

Prepared By: N. Cropper

Checked By: M. Rowe

Approved By: N. Cropper

CESSNA 525, 525A & 525B ATLAS WINGLET MAINTENANCE MANUAL SUPPLEMENT

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RECORD OF REVISIONS

Issue Date By Reason for Change

IR 3 February 2017 NR Initial Release

A 17 April 2017 NR Throughout, various corrections in formatting & references, clarification of part numbers and materials. Sec. 6 – inserted NOTE specifying torque requirements Clarified process for disabling ATLAS prior to any maintenance throughout. 6.C.(1)(a)6 corrected 525B annunciator LRU removal instruction 6.C.(3)(a) Expanded inspection process for annunciator 6.D.(1)(a) inserted Step 2 6.F.(1)(a)2 added removal of winglet glare shield 6.F.(b) updated NOTE 6.F.(b) Expanded Step 1, updated Step 8 6.G.(3)(a) updated Step 3 6.K.(2)(b) expanded Step 1, added “clamp-up bushing” to Step 3, corrected part number in Step 4, corrected resistance specified in Step 5. 6.L.(1)(b) corrected resistance specified in Step 5. 6.L.(3)(b) updated Step 6 6L(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.

B 26 April 2017 MR Corrected Table 7-2 to include life limitation for TACS Return Spring.

C 25 July 2017 NR Throughout, various corrections in formatting & references. Add 525A information to document. 6. Several adjustments to better harmonize with Cessna

maintenance program: 6.D.(2)(f) Adjusted content to improve winglet inspection process and criteria. 6.F.(2)(a) Adjusted content to include additional inspection to determine internal damage without removing winglet at first. 6.F.(2)(b) (Winglet Spar inspection) Deleted inspection, now covered with winglet inspection. 6.K.(3)(a) Adjust Heading Name, added new 5 to inspect for grease leakage and adjusted 6 (was 5)

7. Revise Airworthiness Limitations; Added: “The Airworthiness

limitations section is EASA approved and provides instructions for continued airworthiness information.” Added “Inspection Interval Codes” and NOTE. Table 7-1 Change interval time to match Cessna inspection interval code, delete winglet spars, adjust TCU inspection interval and order of items in table. Add caveat for inspection interval for Bearings, Bushings, and Fasteners for those with improved (ball) bearing installed.



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C (cont.)

Table 7-2 deleted TCU replacement. Added 6.K.(3).(a) to define replacement. Table 7-3 Change ACU recalibration interval to harmonize with Cessna inspection rhythm.

D 28 August 2017 NR 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, update reference shown in table 7-2. Table 7-3 added ref to 6.B.(1) for removal / install of ACU.

E 01 February 2019 JK Throughout, update numbering, and update opening and closing circuit 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 Connectors Update Section 6.B.(1)(b)1

WAS: “Slide the ACU onto the wing root mounting rack until it nests against the aft clamp and per FIGURE 6-2.”

IS: “Slide the ACU onto the wing root mounting rack until it nests against the aft clamp and tighten the four bolts that secure the ACU per FIGURE 6 2.”

Add Section 6.B.(2) Removal/Installation of ACU w/ D38999 Connectors

Insert Figure 6-4 Section 6.C.

Update section 6.C.(1).(b) heading and steps 3 & 4 Deleted section 6.C.(1).(c) and Figure 6-5 ANNUNCIATOR LRU

INSTALLATION - 525B Only; this configuration was never installed and has been removed as an alternate installation in the drawing package.

Update Figure 6-22 TACS Balancing Fixture (Top View) to avoid clash with TACS centering strips

Section 6.O.(1): (e) added: First to test the upper LEDs, second to test the lower LEDs and third to test all the LEDs. (g) added “NOTE: If this circuit breaker is left open for more than 3 seconds, then a button push or a power cycle will be needed to extinguish the light.”

Section 7. update Table 7-1 to clarify applicability of interval variation for Bearings, Bushings, and Fasteners WAS: 100 Flight Hours / 3C* IS: 3C / *100 Flight Hours Note below table updated WAS: *Applicable for ATLAS Kit 022 and higher; or if SBATLAS-

57-02 has been completed. IS: *Applicable if ATLAS Kit 101-0001 thru 101-0021 is installed

and SBATLAS-57-02 has not been completed.


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F 30 April 2019 JK Formatting changes Update Table 3-1 WAS: 5180002-1, IS: 5180002-1 (or equivalent) Section 6.L.(2)1. WAS: TACS balancing limits are +1.5 in-lb

over balance to -1.5 in-lb underbalance; IS: TACS balancing limits are +1.5 in-lb over balance to -4.9 in-lb underbalance

G 03 September 2019 NC Section 6.B.(4)(c) updated, ACU sealant only applicable to ACU w/o D38999 receptacles.

Section 6.L.(5)(a) Update step 1 added disbond Added step 2, inspection of centering strips, Added Figure 6-30

Table 7-1 updated, WAS: TACS Skins IS: TACS Skins & Centering Strips



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TABLE OF CONTENTS

RECORD OF REVISIONS ............................................................................................................... 2 TABLE OF CONTENTS ................................................................................................................... 5 LIST OF FIGURES ........................................................................................................................... 6 LIST OF TABLES ............................................................................................................................. 7

1. Introduction ............................................................................................................................................. 8

2. Applicability ............................................................................................................................................. 9

3. Special Tools, Materials and Reference Documents ............................................................................... 9

4. Abbreviations and Acronyms ................................................................................................................. 10

5. Description and Operation .................................................................................................................... 11

A. Description ......................................................................................................................................... 11

B. Operation ........................................................................................................................................... 11

C. System Components .......................................................................................................................... 13

D. Torque Data ....................................................................................................................................... 15

E. Dimensions and Areas ....................................................................................................................... 15

6. Maintenance Instructions ...................................................................................................................... 16

A. ATLAS INOP Button ............................................................................................................................ 16

B. ACU .................................................................................................................................................... 19

C. Annunciator LRU ................................................................................................................................ 25

D. Extension ........................................................................................................................................... 28

E. Wing Tip Navigation/Anti-Collision Light ........................................................................................... 33

F. Winglet ............................................................................................................................................... 35

G. Static Wicks ........................................................................................................................................ 44

H. Vertical Tail Navigation/Anti-Collision Light ...................................................................................... 45

I. Main ATLAS Relay .............................................................................................................................. 47

J. Bellcrank ............................................................................................................................................ 50

K. TCU ..................................................................................................................................................... 53

L. TACS ................................................................................................................................................... 56

M. TACS Return Spring ............................................................................................................................ 72

N. Hinge Bearings ................................................................................................................................... 73

O. ATLAS ................................................................................................................................................. 75

7. Airworthiness Limitations ...................................................................................................................... 76

8. ATLAS Troubleshooting .......................................................................................................................... 79


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LIST OF FIGURES

FIGURE 1-1 ATLAS WING TIP ........................................................................................................ 8 FIGURE 5-1 ATLAS FUNCTIONAL DIAGRAM ............................................................................... 12 FIGURE 6-1 ATLAS INOP BUTTON INSTALLATION .................................................................... 18 FIGURE 6-2 ACU INSTALLATION w/o D38999 CONNECTORS ................................................... 22 FIGURE 6-3 ACU SEALANT APPLICATION; ACU w/o D38999 CONNECTORS ........................... 23 FIGURE 6-4 ACU INSTALLATION w/ D38999 CONNECTORS ..................................................... 24 FIGURE 6-5 ANNUNCIATOR LRU INSTALLATION ....................................................................... 27 FIGURE 6-6 EXTENSION LEADING EDGE INSTALLATION ......................................................... 29 FIGURE 6-7 NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION ........................................... 34 FIGURE 6-8 WINGLET INSTALLATION ......................................................................................... 37 FIGURE 6-9 AILERON & TACS ALIGNMENT ................................................................................ 38 FIGURE 6-10 WINGLET/END RIB INTERFACE ............................................................................ 39 FIGURE 6-11 WINGLET Z CLIP FASTENER LOCATIONS ............................................................ 40 FIGURE 6-12 WINGLET Z CLIP LOCATION .................................................................................. 41 FIGURE 6-13 WINGLET ATTACHMENT FASTENER LOCATIONS – 525 & 525A ........................ 42 FIGURE 6-14 WINGLET ATTACHMENT FASTENER LOCATIONS – 525B .................................. 43 FIGURE 6-15 VERTICAL TAIL NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION .............. 46 FIGURE 6-16 MAIN ATLAS RELAY INSTALLATION – 525 ........................................................... 48 FIGURE 6-17 MAIN ATLAS RELAY INSTALLATION – 525A & 525B ............................................ 49 FIGURE 6-18 BELLCRANK INSTALLATION .................................................................................. 52 FIGURE 6-19 TCU INSTALLATION ............................................................................................... 55 FIGURE 6-20 TACS INSTALLATION ............................................................................................. 57 FIGURE 6-21 BALANCE WEIGHT ACCESS .................................................................................. 59 FIGURE 6-22 TACS BALANCING FIXTURE (Top View) ................................................................ 60 FIGURE 6-23 TACS BALANCING FIXTURE (Side View) ............................................................... 61 FIGURE 6-24 TACS BALANCE WEIGHT ....................................................................................... 62 FIGURE 6-25 TCU ROD END ........................................................................................................ 65 FIGURE 6-26 TACS KINEMATICS ................................................................................................. 66 FIGURE 6-27 ATLAS HARD STOP CLEARANCE CHECK ............................................................ 67 FIGURE 6-28 TACS SPRING BOLT RIGGING .............................................................................. 68 FIGURE 6-29 TACS HINGE FUNCTIONAL TEST .......................................................................... 69 FIGURE 6-30 TACS CENTERING STRIPS .................................................................................... 70 FIGURE 6-31 TACS RETURN SPRING ......................................................................................... 72 FIGURE 6-32 TACS HINGES ......................................................................................................... 73 FIGURE 6-33 BEARING INSTALLATION ....................................................................................... 74 FIGURE 8-1 ATLAS FAULT VERIFICATION; FLOW DIAGRAM .................................................... 80 FIGURE 8-2 ATLAS UNPOWERED, NO FAULT ANNUNCIATION; FLOW DIAGRAM .................. 81 FIGURE 8-3 TACS INOPERATIVE; FLOW DIAGRAM ................................................................... 82 FIGURE 8-4 ATLAS WON'T RUN BIT; FLOW DIAGRAM .............................................................. 83



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LIST OF TABLES

TABLE 3-1 SPECIAL TOOLS........................................................................................................... 9 TABLE 3-2 MATERIALS .................................................................................................................. 9 TABLE 3-3 REFERENCE DOCUMENTS ......................................................................................... 9 TABLE 5-1 MODIFIED DIMENSIONS – 525 .................................................................................. 15 TABLE 5-2 MODIFIED DIMENSIONS – 525A ................................................................................ 15 TABLE 5-3 MODIFIED DIMENSIONS – 525B ................................................................................ 15 TABLE 7-1 INSPECTION INTERVALS – ATLAS COMPONENTS ................................................. 77 TABLE 7-2 REQUIRED REPLACEMENT TIMES ........................................................................... 78 TABLE 7-3 REQUIRED MAINTENANCE INTERVAL ..................................................................... 78 TABLE 8-1 ATLAS TROUBLESHOOTING ..................................................................................... 79


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1. Introduction

The procedures in this manual describe the personnel, tools, skills, techniques and steps required to maintain the Tamarack Active Technology Load Alleviation System (ATLAS) winglets on the Cessna 525, 525A and 525B Citation in accordance with Cranfield Aerospace Solutions modifications CAeM/Cessna/1375/1430/1440/1452/1475/1480. This manual is intended to satisfy the requirements of EASA CS-23.1529 and CFR Part 23, Sec. 23.1529 by presenting information essential to the continued airworthiness of the aircraft.

Maintenance of the ATLAS and its associated components must be performed by appropriately rated personnel or facilities. Prior to performing maintenance on the ATLAS, carefully read these instructions and ensure that you understand them fully.

FIGURE 1-1 ATLAS WING TIP

(525B Winglet Shown)



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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.

Cessna 525B 525B-0001 to 525B-0056 525B-0058 to 525B-0450 525B-0057 525B-0451 and on.

3. Special Tools, Materials and Reference Documents

TABLE 3-1 SPECIAL TOOLS

PN Name Use Vendor 5180002-1 (or equivalent)

Control Surface Balance Fixture Kit

TACS Balancing Cessna

- Digital Inclinometer TACS Rigging Local Procurement

TABLE 3-2 MATERIALS

PN Name Use Vendor P/S 870 CLASS B Corrosion Inhibitive

Sealant Edge and Gap Sealing Local Procurement

Loctite 242 or Loctite 243

Threadlocker ACU fastener security Local Procurement

3M 23 or AA59163 FR4 Tape

Self-Fusing Tape ACU Sealing Local Procurement

3145 RTV Adhesive Sealant ACU Sealing Local Procurement

TABLE 3-3 REFERENCE DOCUMENTS

Document Name Description CA/DD/SB1375 Installation of Tamarack ATLAS

Service Bulletin - 525 Overview of ATLAS 525 Installation.

CAS/SB1440 Installation of Tamarack ATLAS Service Bulletin – 525B

Overview of ATLAS 525B Installation.

CAS/SB1452 Installation of Tamarack ATLAS Service Bulletin – 525A

Overview of ATLAS 525A Installation.

CA/DD/M022 Cessna 525, 525A and 525B ATLAS Winglet Illustrated Parts Catalog

Illustrated Parts Catalogue for ATLAS Installation.

CA/DD/M024 Wiring Diagram Manual Supplement Wiring diagrams applicable to installation of the Tamarack ATLAS system.


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OEM Reference Documentation

Name Revision

Model 525 Maintenance Manual ............................................................................................. Current

Model 525A Maintenance Manual ........................................................................................... Current

Model 525B Maintenance Manual ........................................................................................... Current

4. Abbreviations and Acronyms

See below for a list of abbreviations and acronyms used throughout this document.

ACU ATLAS Control Unit

ATLAS Active Technology Load Alleviation System

AFMS Airplane Flight Manual Supplement

BIT Built-In-Test

FWD Forward

INBD Inboard

LED Light Emitting Diode

OTBD Outboard

TACS Tamarack Active Camber Surface

TCU TACS Control Unit



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5. Description and Operation

A. Description

The Active Technology Load Alleviation System (ATLAS) is a system which provides for the installation of aluminum wing extensions and carbon fiber composite winglets on the Cessna Citation 525, 525A and 525B without requiring the traditional major structural modifications of the wing.

Aerodynamic surfaces called Tamarack Active Camber Surfaces (TACS) mounted in the wing extensions either hold their position in trail with the wing, or symmetrically deploy trailing edge up or down to modify wing lift and relieve structural loads as required by different flight conditions. An electronic controller called the ATLAS Control Unit (ACU) is mounted near the center of gravity of the airplane and detects fuselage vertical accelerations. Based on fuselage acceleration, the ACU commands movements of TACS Control Units (TCUs) in the wingtips. This causes the TACS to deploy as required during flight. The actuation of the TACS is independent of any other flight control and responds proportionally 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 new integrated anti-collision/navigation tail light is also installed in place of the existing unit.

B. Operation

The ATLAS takes the vertical acceleration of the fuselage and converts it to an automatic aerodynamic load alleviation targeted at the wing tip. Normal operation of the ATLAS is automatic, requiring no input from the pilot. A basic functional diagram of the ATLAS is shown in FIGURE 5-1.

A new LED-illuminated momentary button, the ATLAS INOP Button, is installed in the cockpit as a part of the installation. In the event of a system fault, the LEDs in the button will illuminate to alert the pilot of the fault condition. In response, the pilot need only reduce airspeed to 140 KIAS (525), 161 KIAS (525A & 525B) or below. The ATLAS Airplane Flight Manual 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’s perspective.

WARNING: THE TACS WILL MOVE RAPIDLY AND FORCEFULLY TO NEUTRAL POSITION WHEN THE AVIONICS POWER SWITCH IS MOVED TO THE ON POSITION. BE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR BEFORE MOVING SWITCH TO THE ON POSITION.


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FIGURE 5-1 ATLAS FUNCTIONAL DIAGRAM

ATLAS INOP BUTTON – DISPLAYS FAULTED CONDITIONS AND PROVIDES BIT COMMANDS TO ANNUNCIATOR LRU (525A & 525B shown)

AIRCRAFT VERTICAL ACCELERATION

ACU –

INTERPRETS AIRCRAFT ACCELERATION INPUTS AND CONVERTS TO COMMAND SIGNAL TO SEND TO TCU, MONITORS ATLAS HEALTH AND OUTPUTS FAULTS TO ANNUNCIATOR LRU.

ANNUNCIATOR LRU – CONVERTS FAULTED INPUTS FROM ACU TO A FAULT OUTPUT WHICH CAN BE DISPLAYED BY THE ATLAS INOP BUTTON. INPUTS BIT COMMAND TO ACU.

TCU – CONVERTS ACU COMMAND SIGNAL TO LINEAR MECHANICAL ACTUATION PROPORTIONAL TO VERTICAL ACCELERATION

TACS – CONVERTS LINEAR ACTUATION FROM TCU AND MECHANICAL LINKAGES TO A LOAD ALLEVIATING AERODYNAMIC FORCE



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C. System Components

ATLAS INOP Button

The ATLAS INOP Button is positioned in the pilot’s primary field of view on the left hand side of the instrument panel.

The ATLAS INOP Button serves three purposes. Its primary purpose is to receive ATLAS fault condition signals from the Annunciator LRU and display the faulted condition to the pilot.

Its second purpose is to clear faulted conditions. If the ATLAS faults the button will illuminate. A single button push will reset the fault annunciation circuitry in the ACU in an attempt to clear a latched faulted condition. If after a single button push the button remains illuminated, the pilot may attempt to reset the system via the Built-In-Test (BIT), as described below.

When the button is pushed 3 times within 3 seconds the ATLAS will run a BIT and test its internal fault annunciation circuitry and the functionality of the Light Emitting Diodes (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 lower

LEDs and one to test all the LEDs. 3. When all the LEDs are illuminated the ATLAS is running its BIT and if no fault

exists in its internal circuitry the lights will extinguish. If an internal fault was detected the lights will remain illuminated and maintenance action is required.

The ATLAS INOP Button may blink off momentarily before re-illuminating and showing a faulted condition. The TACS may move as well but will return to their neutral positions.

Annunciator Line Replaceable Unit (LRU)

The purpose of the Annunciator LRU is to take the faulted condition signal from the ACU and convert it into a powered signal that drives the illumination of the ATLAS INOP Button. No fault annunciation logic circuitry exists in the Annunciator LRU.

ATLAS Control Unit

The ATLAS Control Unit (ACU) contains the logic circuitry which is used to convert aircraft vertical acceleration into a command output signal.

Also contained within the ACU is circuitry for health monitoring of the ATLAS. The ACU monitors several internal parameters of the ATLAS and if any one of them falls outside of their normal operational limits the ACU will sense the condition and convert it to a fault signal. The fault signal is sent out to the Annunciator LRU which is then displayed to the pilot.

The ACU is mounted under the fuselage forward of the forward wing spar, accessed through panels: 525 – 191AL; 525A – 192A; 525B – 163A, 163B.


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TACS Control Unit

The TACS Control Unit (TCU) contains an electromechanical actuator and its associated control circuitry. It converts the command output signal from the ACU to a mechanical actuation proportional to fuselage vertical acceleration.

There are 2 TCUs, one located in each wing tip and can be accessed through panels: 525 – 542HB & 642HB; 525A – 542GB & 642GB; 525B – 542GB & 642GB.

Main ATLAS Relay

The main ATLAS relay controls the 28VDC supply to the TCUs. 28VDC is drawn from the RH feeder bus through the main ATLAS relay and then out to the right side and left side TCUs.

The main ATLAS relay is located on the relay rack in the right side of the AFT J-Box which is accessed through the aft baggage compartment.

Tamarack Active Camber Surface

The Tamarack Active Camber Surface (TACS) and its associated mechanical linkages convert the mechanical actuation of the TCU into aerodynamic force used for load alleviation. The TACS will symmetrically deflect trailing edge up or down to alleviate wing loads resulting from a positive or negative fuselage vertical acceleration, respectively.

The TACS are located outboard of the ailerons. There are 2 for any ATLAS installation, one per wing tip. The TACS is physically connected to the aft spar of the wing extension by two hinges.

Wing Extension

Two wing extensions, one per wing tip are added to the end of the original wing and extend outboard 28 inches from the last wing rib.

Winglet

Two carbon fiber winglets (one per wing tip) provide an aerodynamic efficiency increase. They are mounted to the most outboard rib of the wing extension.

Wingtip Navigation/Anti-collision Light

Installation of the winglets on the Cessna 525, 525A and 525B eliminates the original wing tip navigation light assemblies. They are replaced with new TSO-approved navigation/anti-collision light assemblies mounted on the leading edge of the winglet just outboard of the wing extension.

Vertical Tail Navigation/Anti Collision Light

A new TSO-approved vertical tail dual navigation/anti-collision light replaces the original vertical tail light assembly which was only a single navigation light. Two additional wires run to the tail to provide power and synchronization for the anti-collision light. A new connector mounting bracket is also installed along with the updated tail light.



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D. Torque Data

Unless otherwise noted, torque fasteners in accordance with the Cessna 525/525A/525B Maintenance Manual (AMM) Chapter 20-10.

E. Dimensions and Areas

The winglet and wing extension installation increases several dimensions on the 525, 525A, and 525B. See the tables below for the relevant updated dimensions and areas.

TABLE 5-1 MODIFIED DIMENSIONS – 525

Dimension Measurement

Wingspan 52.5 ft (16.0 m)

Wing Area 248.8 ft2 (23.1 m2)

TABLE 5-2 MODIFIED DIMENSIONS – 525A



Wing Area 273.15 ft2 (25.38 m2)

TABLE 5-3 MODIFIED DIMENSIONS – 525B



Wing Area 302.876 ft2 (28.19 m2)


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6. Maintenance Instructions

Prior to any maintenance activities, the airplane is to be made safe. Refer to Cessna 525/525A/525B Maintenance Manual Section 20-00-00 for safe maintenance information and procedures. ATLAS may be disabled by opening the ATLAS MAIN circuit breaker.

Unless otherwise specified, torque fasteners per Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35.

A. ATLAS INOP Button

ATLAS INOP Button - Removal/Installation

(a) Removal – ATLAS INOP Button (refer to FIGURE 6-1)

1 Disable ATLAS TACS movement by opening the following circuit breakers: 525: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525A: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525B: ATLAS MAIN (If present: ATLAS EMER 1 and ATLAS EMER 2)

2 Pull out and rotate down the Pushbutton Cap to access the integral mounting hardware.

3 Loosen the two screws inside the housing until the tabs disengage the mounting sleeve and remove the housing.

4 Remove the ATLAS INOP Button from the panel.

5 De-solder the wires from the back of the ATLAS INOP button to remove it from the wiring harness.

(b) Installation – ATLAS INOP Button

1 Solder the wires onto the solder terminals of the ATLAS INOP Button. Refer to the ATLAS Wiring Manual Supplement for correct wiring.

Refer to the Cessna WDM 20-10-03 for soldering requirements.

2 Slide the INOP Button through the panel from the front.

3 Slide the mounting sleeve onto the back of the INOP button and slide up to the panel.

4 Torque the screws inside the switch body until the integral mounting hardware pulls the mounting sleeve tight against the mounting plate (18 in-oz. torque typical).

5 Press in the Pushbutton Cap.




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6 Close the following circuit breakers on the Co-Pilot Circuit Breaker Panel: 525: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525A: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525B: ATLAS MAIN (If present: ATLAS EMER 1 and ATLAS EMER 2)

ATLAS INOP Button – Test

(a) Perform an ATLAS Functional Test (refer to Section 6O).


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FIGURE 6-1 ATLAS INOP BUTTON INSTALLATION

A



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B. ACU

ACU - Removal/Installation of ACU w/o D38999 Connectors

(a) Removal - ACU w/o D38999 Receptacles (refer to FIGURE 6-2)

1 Disable ATLAS TACS movement by opening the following circuit breakers: 525: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525A: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525B: ATLAS MAIN

2 Remove access panel forward of the wing at BL0; 525 – 191AL; 525A – 192A, 525B – 163A, 163B.

3 Remove the sealant and spiral wrap around the wire bundles in order to allow the connector cover to slide over the wire harness.

4 Remove the four screws that secure the cover to the ACU and slide the ACU cover away from the ACU in order access the two electrical connectors.

5 Remove the two electrical connectors.

6 Remove the bonding strap from the ACU.

7 Loosen the four bolts that secure the ACU only enough to allow the ACU to slide out of the wing root mounting rack and remove the ACU.

(b) Installation - ACU w/o D38999 Connectors

1 Slide the ACU onto the wing root mounting rack until it nests against the aft clamp and tighten the four bolts that secure the ACU per FIGURE 6-2.

2 Install bonding strap.

3 Install the two electrical connectors.

4 Install the connector cover.

5 Apply Loctite 242 or 243 and torque the connector cover screws to 12-16 in-lb.

6 Install 3M 23 or AA59163 FR4 self-fusing tape and apply Dow-Corning 3145 sealant per FIGURE 6-3.

7 Install access panel.

8 Close the following circuit breakers on the Co-Pilot Circuit Breaker Panel: 525: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525A: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525B: ATLAS MAIN

ACU - Removal/Installation of ACU w/ D38999 Connectors

(a) Removal – ACU w/ D38999 Connectors (refer to FIGURE 6-4)



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2 Remove access panel forward of the wing at BL0; 525 – 191AL; 525A – 192A, 525B – 163A, 163B.

3 Remove the two electrical connectors.

4 Remove the bonding strap from the ACU.

5 Loosen the four bolts that secure the ACU only enough to allow the ACU to slide out of the wing root mounting rack and remove the ACU.

(b) Installation – ACU w/ D38999 Connectors

1 Slide the ACU onto the wing root mounting rack until it nests against the aft clamp and tighten the four bolts that secure the ACU per FIGURE 6-4.

2 Install bonding strap.

3 Install the two electrical connectors.

4 Install access panel.


ACU - Test

(a) Perform ATLAS Functional Test (refer to Section 6O)



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ACU - Inspection

(a) ACU Mount

1 Access via panel forward of wing root at BL0; 525 – 191AL; 525A – 192A; 525B – 163A, 163B.

2 Visually inspect for: Corrosion, cracks, scratches, dents, distortion, missing paint/primer, or other signs of damage.

3 If cracks or distortion are found, replace component(s).

4 If corrosion, or scratches are found repair is limited to minor damage. Reference Cessna Model 525/525A/525B Structural Repair Manual 51-10-01. Repair per 51-70-01 or 51-70-08.

5 Restore protective treatment per Cessna Model 525/525A/525B Structural Repair Manual 51-20-01.

6 If missing paint/primer is found, restore paint/primer per Cessna Model 525/525A Maintenance Manual 20-33-00, or 525B Maintenance Manual 20-31-00.

(b) ACU Mount Hardware and Bonding Jumper

1 Visually inspect for corrosion, damage or looseness.

2 If corrosion or any damage is found replace component(s).

3 If loose fasteners are found, re-torque per FIGURE 6-2, FIGURE 6-4 or Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35.

(c) ACU Sealant - ACU w/o D38999 Receptacles

1 Visually inspect sealant for gaps. Reseal any gaps found with 3M 23 or AA59163 FR4 tape, and/or RTV sealant. Reference FIGURE 6-3.


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FIGURE 6-2 ACU INSTALLATION w/o D38999 CONNECTORS

A



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FIGURE 6-3 ACU SEALANT APPLICATION; ACU w/o D38999 CONNECTORS

A

Apply sealant between wires prior

to wrapping

Wrap self-fusing tape around wire bundle. Ensure wrapped area overlaps sealant

applied between wires


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FIGURE 6-4 ACU INSTALLATION w/ D38999 CONNECTORS

A



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C. Annunciator LRU

Annunciator LRU - Removal/Installation

(a) Removal - Annunciator LRU (refer to FIGURE 6-5)


2 Remove seat and floor covering as required to floor panel: 525 – 251CT; 525A – 261DT; 525B – 261ET (refer to Cessna 525 MM 25-21-01, 525A MM 25-20-02, 525B MM 25-20-00).

3 Remove floor panel: 525 – 251CT; 525A – 261DT, 525B – 261ET.

ATLAS installation allows for Annunciator LRU to be installed under any left hand floorboard panel between the following panels: 525 – FS 187 to FS 275 525A – FS 151 to FS 310 525B – FS 187 to FS 344. If Annunciator LRU isn’t present under panel 251CT(525), 261DT(525A), 261ET(525B) check other panels until located.

4 Disconnect electrical connectors.

5 525 & 525A - Remove two each screws securing annunciator LRU to floor structure and remove annunciator LRU.

6 525B Only - Remove two each screws securing annunciator LRU to annunciator LRU mount and remove annunciator LRU.

(b) Installation - Annunciator LRU (refer to FIGURE 6-5)

1 Position and install the Annunciator LRU using the two screws to secure it to the floor structure.

2 Attach electrical connectors.

3 Install floor panel 251AT (525), 261BT (525A) or 261BT (525B), coverings and seat.


4 Close the following circuit breakers on the Co-Pilot Circuit Breaker Panel: 525: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525A: ATLAS MAIN, ATLAS EMER 1 and ATLAS EMER 2 525B: ATLAS MAIN, (If present: ATLAS EMER 1 and ATLAS EMER 2)


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Annunciator LRU – Test

(a) Perform an ATLAS Functional Test (refer to Section 6O)

Annunciation LRU – Inspection

(a) Annunciator Mount and Mounting Hardware.

1 For access see Section 6C.

2 Visually inspect for: corrosion, cracks, scratches, dents, distortion, missing paint/primer, loose, or other signs of damage.

3 If corrosion or damage is found replace component(s).

4 If fasteners are loose, re-torque per Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35.

5 If cracks or distortion are found replace component(s).


7 Dents are classified per Cessna Model 525/525A/525B Structural Repair Manual 51-10-01 and repaired per 51-70-01.





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DETAIL A

FIGURE 6-5 ANNUNCIATOR LRU INSTALLATION

A


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D. Extension

Extension Leading Edge - Removal/Installation

(a) Removal - Leading Edge (refer to FIGURE 6-6)

1 Remove and retain all the leading edge attachment screws.

2 Remove and retain leading edge shims, if applicable.

3 Remove and retain the leading edge.

(b) Installation - Leading Edge (refer to FIGURE 6-6

1 Remove old sealant from inside and along the outer edge of the wing extension.

2 Apply a bead of P/S 870 Class B corrosion inhibitive sealant to the inside of the leading edge where it is common to the air dam.

3 Install the leading edge.

4 Secure the leading edge to the wing extension with either new or retained fasteners; MS24694C4, refer to 101-57-0000, 102-57-0000 or 103-57-0000.

5 Fillet seal along the outer edge with P/S 870 Class B corrosion inhibitive sealant.



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DETAIL A

FIGURE 6-6 EXTENSION LEADING EDGE INSTALLATION

A


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Extension - Inspections

(a) Extension Leading Edge

1 Visually inspect for corrosion, cracks, scratches, dents, distortion, missing paint/primer, or other signs of damage

2 If cracks or distortion are found replace component(s).





(b) Extension Spar Straps, Shear Ties, and Skin Splices

1 Access via louver panel in Wing Extension and/or via panels 525: 542HB, 642HB 525A: 542GB, 642GB 525B: 542GB, 642GB

2 Visually inspect for corrosion, cracks, scratches, dents, distortion, missing paint/primer, or other signs of damage.

3 If any damage is found except missing paint/primer or minor scratches as classified in step 4, replace component.

4 Repair scratches that meet depth requirements per Cessna Model 525/525A/525B Structural Repair Manual 51-70-08, Class 2 and Class 4 or 51-70-02 Section 2.



(c) Extension Spar Caps

1 Access via louver panel in wing extension and by removing the leading edge as described in Section 6D.

2 Visually inspect for: corrosion, cracks, scratches, dents, distortion, missing paint/primer, or other signs of damage.

3 If dents, distortion, cracks or other damage is found replace component.



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(d) Extension Spar Webs and Internal Brackets

1 Access via louver panel in wing extension and by removing the leading edge as described in Section 6D.


3 If cracks or distortion are found replace component.





(e) Extension Skins

1 Access via louver panel in Wing Extension.


3 If cracks or distortion are found, replace components.






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(f) Extension Winglet Attachment Rib

1 Access the winglet attachment rib by removing glare shield and tip light assembly (refer to Section 6E). Inspections are to be performed with a good light source, mirror, and borescope as required.

2 Visually inspect the attachment rib for signs of cracks, dents, distortion. If dents, cracks, distortion, or other damage is found, replace component.

3 Visually inspect the Attachment Rib for signs of corrosion, missing or bubbled paint/primer, or scratches. Indications of corrosion around rivet holes or adjacent to the faying surfaces of Winglet and Attachment rib are cause for removal of the winglet to allow adequate inspection of the faying surfaces. Light corrosion (0.001” max depth) can be mechanically removed. More severe corrosion should be addressed by replacing the part. Minor scratches should be sanded smooth. Reference Cessna Model 525/525A/525B Structural Repair Manual 51-10-01. Repair per 51-70-01 or 51-70-08. All bare surfaces should be cleaned and primed per Cessna Model 525/525A Maintenance Manual 20-33-00, or 525B Maintenance Manual 20-31-00. Restore protective treatment per Cessna Model 525/525A/525B Structural Repair Manual 51-20-01.

4 Visually inspect the rivets that attach the winglet to the Attachment Rib and the rivets that attach the Attachment Rib to the Wing Extension for signs of looseness, smoking, tipping, or corrosion. Smoking or tipped rivets could be an indication of other structural damage and further investigation may be required. Smoking rivets could also be an indication of looseness. Reference Cessna Model 525/525A/525B Maintenance Manual 51-40-00 for further guidance. Replace all loose or corroded rivets with the same type and size per Cessna Model 525/525A/525B Structural Repair Manual 51-40-03.



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E. Wing Tip Navigation/Anti-Collision Light

Wing Tip Navigation/Anti-Collision Light - Removal/Installation

(a) Removal - Navigation/Anti-Collision Light (refer to FIGURE 6-7)

1 Open the NAV and ANTI COLL circuit breaker located on the Co-Pilot circuit breaker panel.

2 Remove and retain (if condition permits) the screws attaching the lamp assembly and glare shield to the wing extension.

3 Remove the glare shield.

4 Remove the old sealant from the perimeter of the lamp assembly.

5 Disconnect the cannon plug and remove the light assembly.

(b) Installation - Navigation/Anti-Collision Light (refer to FIGURE 6-7)

1 Connect the cannon plug to the lamp assembly.

2 Slide the lamp assembly into place and align fastener holes.

3 Fillet seal the perimeter of the lamp assembly with P/S 870 Class B corrosive inhibitive sealant.

4 Attach the glare shield to the wing extension and navigation/anti-collision light assembly using either the retained fasteners or new fasteners.

5 Close the NAV and ANTI COLL circuit breaker located on the Co-Pilot circuit breaker panel.

Wing Tip Navigation/Anti-Collision Light – Test

(a) Perform functional test of Navigation and Anti-Collision Light per Cessna 525/525A/525B Maintenance Manual 33-40-00.

(b) The light is to be considered inoperable if any of the LED’s in the light assembly fail to function.


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DETAIL A

FIGURE 6-7 NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION

A

NAV LIGHT ASSY (REF)

LEADING EDGE (REF)

GLARE SHIELD (REF)



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F. Winglet

Winglet - Removal/Installation

(a) Winglet - Removal

1 Open the ATLAS MAIN circuit breaker, located in the Co-Pilot’s circuit breaker panel.

2 Remove wing tip navigation/anti-collision light assembly and winglet glare shield (refer to Section 6E).

3 Remove bonding strap and ground wire from the extension rib.

4 Remove the TACS (refer to Section 6L).

5 Remove the six bolts securing the outboard hinge bracket to the wing extension and remove.

6 Remove the four rivets securing the Z Clip to the winglet close-out rib.

7 Remove paint/primer from winglet attachment fasteners.

WARNING: USE CAUTION WHEN REMOVING PAINT AND PRIMER FROM CARBON COMPOSITE LAMINATES. ONLY REMOVE SURFACE COATINGS. DO NOT REMOVE ANY CARBON MATERIAL.

8 Locate and remove winglet attachment fasteners common to outboard rib.

9 Remove winglet

(b) Winglet - Installation

Fastener sizes described below are nominal. Remove and install fasteners per Cessna Structural Repair Manual 51-40-03. Before reinstalling winglet inspect all fastener holes for damage or defects. If any of the fastener holes do not meet the fastener hole specifications, it is permissible to upsize one diameter larger.

1 Install the winglet to the wing extension per FIGURE 6-8 through FIGURE 6-14. This includes attachment at the winglet spar (FIGURE 6-10) and at the z clip (FIGURE 6-11).

2 Restore aerodynamic filler as necessary.

3 Prime and paint per the Cessna Model 525/525A Maintenance Manual 20-33-00, or 525B Maintenance Manual 20-31-00.

4 Reinstall the TACS outboard hinge bracket.

5 Reinstall the TACS (refer to Section 6L).

6 Reinstall the bonding strap between the winglet and wing extension and the light assembly ground wire.


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7 Cap seal all bonding strap and ground wire terminations with non-conductive sealant (refer to Model 525/525A Maintenance Manual 20-21-02, or 525B Maintenance Manual 20-20-03).

8 Reinstall wing tip navigation/anti-collision light assembly and winglet glare shield (refer to Section 6E).

9 Close the ATLAS MAIN circuit breaker, located in the Co-Pilot’s circuit breaker panel.

10 Perform ATLAS functional test (refer to Section 6O).

11 Perform functional test of Navigation and Anti-Collision Light per Cessna 525/525A/525B Maintenance Manual 33-40-00.

Winglet - Inspection

(a) Winglet Skins

1 Visually inspect for: delamination, cracks, scratches, dents, missing paint/primer, loose or smoking rivets or other signs of damage. Surface indications of internal damage due to impact may be very slight. Closely inspect the painted surface for indications of impact. Use tap test methods at any location of potential impact to determine if internal delamination occurred (refer to Cessna Model 525/525A/525B Structural Repair Manual 51-71-01). If tap testing results are inconclusive, further inspection may be required, including the use of a mirror, borescope or removal of the winglet (for removal refer to section 6F) to visually inspect the internal structure.

2 If damage is found reference Cessna Model 525/525A/525B Structural Repair Manual 51-70-02. Type A1 damage may be repaired. Contact Cessna Citation Service Center if damage exceeds A1.

3 Refer to Cessna Model 525/525A/525B Structural Repair Manual 51-40-00 for identification and replacement of loose and/or smoking rivets.



(b) Winglet Leading Edge Tape

1 Visually inspect for: loose or worn tape.

2 If Leading Edge tape is found to be loose or worn, remove tape and re-apply. Reference the Illustrated Parts Catalogue, CA/DD/M022.



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DETAIL A

FIGURE 6-8 WINGLET INSTALLATION

A

BOTTOM TOP

MAKE GAPS EQUAL


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FIGURE 6-9 AILERON & TACS ALIGNMENT



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DETAIL B

FIGURE 6-10 WINGLET/END RIB INTERFACE

B


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DETAIL C

FIGURE 6-11 WINGLET Z CLIP FASTENER LOCATIONS

C



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DETAIL D

FIGURE 6-12 WINGLET Z CLIP LOCATION

(525B Winglet Shown)

D


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525:

DETAIL E

FIGURE 6-13 WINGLET ATTACHMENT FASTENER LOCATIONS – 525 & 525A

TOP AND BOTTOM SAME

E



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525B:

DETAIL F

FIGURE 6-14 WINGLET ATTACHMENT FASTENER LOCATIONS – 525B

TOP AND BOTTOM SAME

F


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G. Static Wicks

Static Wick – Removal/Installation

(a) Removal – Static Wick

1 Remove the static wick by unscrewing it from the threaded stud of the discharger base.

(b) Installation – Static Wick

1 Screw the static wick onto the threaded stud of the discharger base.

2 Tighten and secure as needed (refer to Model 525 Maintenance Manual 23-61-00, or 525A/525B Maintenance Manual 23-60-00).

Static Wick – Test

(a) Perform an electrical bonding test of the static wick per Model 525 Maintenance Manual 23-61-00, 525A/525B Maintenance Manual 23-60-00.

Static Wick – Inspection

(a) Visually inspect for corrosion, cracks, scratches, dents, distortion, or other signs of damage.

1 If any damage or corrosion is found, replace damaged component(s).

2 Perform electrical bonding test per (2) Static Wick – Test.

3 If electrical bonding test is failed refer to Model 525 Maintenance Manual 23-61-00, or 525A/525B Maintenance Manual 23-60-00 for repair/replacement instructions.



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H. Vertical Tail Navigation/Anti-Collision Light

Vertical Tail Navigation/Anti-Collision Light - Removal/Installation

(a) Removal - Tail Navigation/Anti-Collision Light (refer to FIGURE 6-15)

1 Open the NAV and ANTI COLL circuit breaker located on the Co-Pilot circuit breaker panel.

2 Remove faring 340BTC.

3 Cut any cable-ties securing wire harness and disconnect electrical connector P12.

4 Unpin lamp assembly wires from electrical connector.

5 Remove the two screws securing the lamp assembly to the fairing and pull lamp assembly and wires free.

(b) Installation - Tail Navigation/Anti-Collision Light (refer to FIGURE 6-15)

1 Secure lamp to fairing and insert contacts into electrical connector.

2 Connect electrical connector and secure harness.

3 Install fairing 340BTC.

4 Close the NAV and ANTI COLL circuit breaker located on the Co-Pilot circuit breaker panel.

Vertical Tail Navigation/Anti-Collision Light – Test

(a) Perform functional test of Navigation and Anti-Collision Light per Cessna 525/525A/525B Maintenance Manual 33-40-00.

(b) The light is to be considered inoperable if any of the LED’s in the light assembly fail to function.


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DETAIL A

FIGURE 6-15 VERTICAL TAIL NAVIGATION/ANTI-COLLISION LIGHT INSTALLATION

A

Light assembly

Retaining clip

Lens

Retaining hardware



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I. Main ATLAS Relay

Main ATLAS Relay – Removal/Installation

(a) Removal - Main ATLAS Relay (refer to FIGURE 6-16 or FIGURE 6-17)

1 Disconnect Aircraft Battery and remove external power.

2 Open the ATLAS MAIN circuit breaker on the Co-Pilot Circuit Breaker Panel and the ATLAS circuit breaker on the Aft J-Box.

3 Remove panel 525: 322A; 525A & 525B: 321BL and 321CC.

4 Remove wire terminals from Main ATLAS Relay.

5 Remove screws securing Main ATLAS Relay.

(b) Installation - Main ATLAS Relay (refer to FIGURE 6-16 or FIGURE 6-17)

1 Secure Main ATLAS Relay to Aft J-Box equipment rack.

2 Secure wire terminals to Main ATLAS Relay.

3 Install panel 525: 322A; 525A & 525B: 321BL and 321CC.

4 Close the ATLAS MAIN circuit breaker on the Co-Pilot Circuit Breaker Panel and the ATLAS circuit breaker on the Aft J-Box.

Main ATLAS Relay – Test

(a) Perform an ATLAS Functional Test (refer to Section 6O).


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525:

(REPRESENTATIVE OF THE RH POWER JUNCTION BOX, CONFIGURATION MAY VARY DEPENDING ON OTHER INSTALLED EQUIPMENT)

DETAIL A

FIGURE 6-16 MAIN ATLAS RELAY INSTALLATION – 525

A



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525B:

(REPRESENTATIVE OF THE RH POWER JUNCTION BOX, CONFIGURATION MAY VARY DEPENDING ON OTHER INSTALLED EQUIPMENT)

DETAIL A

FIGURE 6-17 MAIN ATLAS RELAY INSTALLATION – 525A & 525B

A

MAIN ATLAS RELAY


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J. Bellcrank

Bellcrank - Removal/Installation

(a) Removal – Bellcrank (refer to FIGURE 6-18)


2 Remove the wing extension louver panel on the lower surface of the wing extension.

3 Remove the bell crank bolt access panel on the upper surface of wing extension.

4 Disconnect the TACS and walking beam pushrods.

5 Remove the bellcrank retaining nut.

6 Remove the bellcrank bolt.

7 Remove the bellcrank.

(b) Installation – Bellcrank (refer to FIGURE 6-18)

1 Install the bellcrank.

2 Insert the bellcrank bolt through the bellcrank bolt access panel on the upper skin.

3 Install bellcrank retaining nut.

4 Connect the TACS pushrod and the walking beam pushrod.

5 Verify the TACS Deflections (refer to Section 6L(3)(b))


7 Verify the ATLAS electrical neutral position (refer to Section 6L(3))


9 Install wing extension bell crank bolt access panel and louver panel.


11 Torque and safety all fasteners.



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Bellcrank – Inspection

(a) Bellcrank, Bellcrank Bracket, Control Rods, TACS spring and associated internal fittings and hardware.

1 Access view louver panel in wing extension.


3 If cracks, dents or distortion are found, replace components.






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DETAIL A

FIGURE 6-18 BELLCRANK INSTALLATION

A



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K. TCU

TCU – Removal/Installation

(a) Removal – TCU (refer to FIGURE 6-19)

1 Disable ATLAS TACS movement by opening ATLAS MAIN.

2 Remove access panels 525: 542FB (642FB), 542HB (642HB), 525A: 542EB (642EB), 542GB (642GB) or 525B: 542EB (642EB), 542GB (642GB) and the wing extension louver panel.

3 Disconnect the TCU cannon plug.

4 Remove bonding straps and retain for reinstallation.

5 Remove and discard cotter pins from the bolts at the TCU mount fitting and rod end.

6 Remove the TCU inboard and outboard mount bolts (refer to FIGURE 6-19).

7 Remove TCU.

(b) Installation – TCU (refer to FIGURE 6-19)

1 If the TCU is being replaced, remove rod end and bonding strap from “old” TCU. Install bonding strap and rod end to new TCU.

The rod end orientation and thread protrusion must match that of the TCU previously removed as well as the TCU located in the other wing to ensure symmetry. Ensure that there is a minimum of eight threads engaged in the TCU rod.

2 Torque jam-nut and safety.

Installing the TCU rod with more than the minimum thread engagement allows more available adjustment in the walking beam pushrod.

3 Position TCU and install the bolts, washers, clamp up bushing and nuts for the TCU mount and rod end.

4 Torque and safety TCU rod end and mount bolts. Use MS24665-132 cotter pins.

5 Install Bonding straps and perform electrical bonding test per Cessna 525/525A Maintenance Manual 20-21-02; or 525B Maintenance Manual 20-20-03. Verify the resistance value does not exceed 4.5 mΩ.

For the most accurate bond measurement, measure between two points on the LRU and Cessna structure as close to the attachment points as possible. Measurement on the bonding strap screw is acceptable. Do not measure on the bonding strap itself.

6 Connect TCU cannon plug.


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7 Verify TACS Deflections (refer to Section 6L(3)(b)).

8 Close all ATLAS circuit breakers.

9 Verify ATLAS electrical neutral positions (refer to Section 6L(3))

10 Re-install any access panels that were removed during maintenance.

TCU – Test

(a) Perform an ATLAS functional test (refer to Section 6O).

TCU – Inspection

(a) TCU

1 Remove the TCU (refer to Section 6K(1)(a)).

2 Position the TCU actuator shaft at any position not contacting either of the actuator hard stops.

3 Using calipers or an equivalent precision measuring device, measure the free play in the actuator shaft.

4 If the free play exceeds 0.020 in, replace the TCU.

5 Visually inspect TCU actuator for leaking and/or weeping grease. If leaking / weeping grease is found, replace the TCU.

6 If the free play is less than 0.020 in and no leaking grease is found, re-install the TCU (refer to Section 6K(1)(b)).

(b) Mounting Hardware

1 Visually inspect for: corrosion, cracks, scratches, dents, distortion, missing paint/primer, loose, or other signs of damage.

2 If corrosion, cracks, scratches, dents, or distortion is found replace component.




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DETAIL A

FIGURE 6-19 TCU INSTALLATION

BONDING STRAP (REFERENCE)

OUTBOARD MOUNT

BOLT (REFERENCE)

INBOARD

MOUNT BOLT

(REFERENCE)

TCU (REFERENCE)

TCU ROD END

(REFERENCE)

TCU MOUNT

(REFERENCE) WALKING BEAM

MOUNT

(REFERENCE)


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L. TACS

TACS – Removal/Installation

(a) Removal – TACS (refer to FIGURE 6-20)


2 Remove access panel 525: 542HB (642HB), 525A: 542GB (642GB), or 525B: 542GB (642GB) and the wing extension louver panel.

3 Remove and discard cotter pins from TACS hinge and pushrod bolts.

4 Remove TACS push rod bolt.

5 Remove TACS hinge bolts.

6 Detach TACS bonding straps.

7 Remove the TACS.

(b) Installation – TACS (refer to FIGURE 6-20)

1 Align the TACS to the hinges.

2 Secure TACS and bonding straps with the hinge bolts.

3 Attach TACS pushrod.

Ensure correct alignment of TACS pushrod end locking tabs to prevent interference with the surrounding structure.

4 Safety all bolts with new cotter pins, PN MS24665-132.

5 Perform electrical bonding test per Cessna 525/525A Maintenance Manual 20-21-02; or 525B Maintenance Manual 20-20-03. Verify the resistance value does not exceed 4.5 mΩ.


7 Perform TACS Adjustment/Test (refer to Section 6L(3)).

8 Re-install any access panels that were removed for maintenance.



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DETAIL A

FIGURE 6-20 TACS INSTALLATION

A


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TACS - Balancing

TACS balancing is required any time repairs have been performed on the TACS or paint has been added or removed.

(a) Verify TACS Balance (refer to FIGURE 6-22)

TACS must be balanced with all fasteners installed.

1 TACS balancing limits are +1.5 in-lb over balance to -4.9 in-lb underbalance.

2 Install the balancing tool included with the Control Surface Balancing Kit (refer to Section 3) on the TACS as shown in FIGURE 6-22, using washers as necessary on the bolts at the either end of the tool.

3 Insert bolts into hinge locations and place TACS on the Control Surface Balancing Kit balancing mandrels as shown in FIGURE 6-23. Assure mandrels are centered on the hinge bolts and TACS is free to rotate around the bolts without resistance.

Mandrels must be level to each other ±0.1°

4 If TACS assumes a level position with the 1 lb moveable balance weight within the stated limits, the TACS is correctly balanced.

5 If the TACS is level with the movable balance weight aft of the aft limit, then weight must be added. Add washers as necessary to balance weight fasteners to bring TACS balance to within tolerance (refer to FIGURE 6-24).

WARNING: DO NOT DRILL WITHIN .5 INCH FROM EDGE OR EXISTING MOUNTING HOLES IN BALANCE WEIGHT (REFER TO FIGURE 6-24).

6 If the TACS is level with the movable balance weight forward of the forward limit, then weight must be removed. Drill .25 inch holes and/or remove washers as necessary from lead balance weight to bring TACS balance within tolerance (refer to FIGURE 6-24).

7 Weigh the TACS. TACS total weight is not to exceed 8.4 lb in the balanced configuration. If this cannot be obtained, strip and repaint the TACS, then repeat the balancing procedure.

8 Once the TACS is balanced, install using Loctite on the threads of the balance weight screws and torque to 14 in-lb (refer to FIGURE 6-21).

9 Reinstall balance weight cover using Loctite on the threads of balance weight cover screws and torque to 8 in-lb (refer to FIGURE 6-21).

If the TACS can be balanced without modifying the weight the screws must be removed to properly install fasteners per steps 8 and 9.



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FIGURE 6-21 BALANCE WEIGHT ACCESS


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FIGURE 6-22 TACS BALANCING FIXTURE (Top View)

VIEW LOOKING DOWN



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FIGURE 6-23 TACS BALANCING FIXTURE (Side View)

TACS chord line


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FIGURE 6-24 TACS BALANCE WEIGHT

ADD WASHERS UNDER BOLT HEADS (3X) IF NECESSARY

(REFERENCE)

BALANCE WEIGHT

100-57-1440

(REFERENCE)

.5 inch TYPICAL

(REFERENCE)

LEAD REMOVAL AREA

(REFERENCE)



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TACS - Rigging

(a) TACS Rigging Preparation

Be sure the ATLAS INOP light is extinguished. If ATLAS INOP light is illuminated, troubleshoot the system prior to proceeding. ATLAS must be rigged in a “NO FAULT” condition.

25VDC minimum is required for correct ATLAS function.

1 Remove access panel 525: 542FB (642FB), 542HB (642HB), 525A: 542EB (642EB), 542GB (642GB), or 525B: 542EB (642EB), 542GB (642GB) and the wing extension louver panel.

2 Insert rig pin in Aileron Wing Sector, reference Cessna 525/525A/525B Maintenance Manual 27-10-00.

(b) TACS Rigging Procedure (refer to FIGURE 6-25 and FIGURE 6-26)

1 Remove the TCU and thread rod end into actuator approximately ½” to obtain recommended TCU rod end length 1.063” (reference FIGURE 6-25) and then install to the TCU anchor bracket and to the walking beam.

The short pushrod should not be installed at this point (reference FIGURE 6-26).

2 Power on the TCU to obtain the TCU 0° position. Power is applied by switching BATTERY switch to the BATT position, then the AVIONICS switch to ON. The TCUs will move to their 0° positions after up to three seconds of initialization. After ATLAS is initiated and the TCUs have moved to their 0° positions, move the BATTERY switch to the OFF position.

WARNING: THE TCU MAY MOVE RAPIDLY WITH GREAT FORCE WHEN POWER IS APPLIED. ENSURE THE AREA NEAR THE TCU IS FREE OF TOOLS AND HANDS WHEN POWER IS APPLIED.

If TCUs are moved from their neutral positions, it will be necessary to re-apply power to ATLAS and re-establish a 0° position on the TCUs.

3 Adjust long push rod to recommended length of 8.660” (reference FIGURE 6-26) and install it between the TACS hinge and bellcrank.

4 With the TCU powered (TCU 0° position) and the aileron rig pin installed manually align TACS to their neutral (0 degree) positions. Position an inclinometer and tare it with the TACS in the neutral position.

TACS are at their neutral positions when the upper surface of the TACS is even with the upper surface of the rigged ailerons.

5 Position TACS full trailing edge up and full trailing edge down.

525: -19° (trailing edge up) and 9° (trailing edge down)


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525A & 525B: -21° (trailing edge up) and 10° (trailing edge down).

Angles of TACS deflection are given in degrees. TACS trailing edge up is negative (-) and TACS trailing edge down is positive (+).

6 While holding TACS at the deflection angles defined in step 5, adjust long push rod length as required to obtain .015” clearance, at both the forward and aft bellcrank stops, and repeat Step 5.

Adjusting the long pushrod will bias the entire range of deflection. If .015” clearance is not attainable on both stops, adjust long rod length until there is approximately equal clearance at both hard stops. If correct TACS deflections cannot be obtained without contacting the forward and aft stops on the bellcrank contact a Cessna Citation Service Center.

7 With both TACS and TCU at their neutral positions, as described in Step 4, adjust small push rod to length required and secure to both bellcrank and walking beam.

The length will be approximately 3.519 inches, but is expected to need adjustment.

8 Conduct a final check of ATLAS Electrical Neutral Position by powering on the TCU to obtain the TCU 0° position. If the upper surface of the TACS are not faired with the upper surface of the rigged ailerons adjust the walking beam control rod to achieve a match.

WARNING: THE TACS WILL MOVE RAPIDLY AND FORCEFULLY TO NEUTRAL POSITION WHEN THE AVIONIC POWER SWITCH IS MOVED TO THE ON POSITION. BE SURE THAT ALL PERSONNEL AND EQUIPMENT ARE CLEAR BEFORE MOVING SWITCH TO THE ON POSITION.

9 Conduct a final check TACS total travel. Position TACS full trailing edge up and full trailing edge down and confirm the following.

525: -19°±1° (trailing edge up) and 9°±1° (trailing edge down)

525A & 525B: -21°±1° (trailing edge up) and 10°±1° (trailing edge down).

10 Torque all fasteners per Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35 and install safeties on TACS pushrods.

With TACS deflections correctly rigged, an operational ATLAS will not contact the forward and aft bellcrank stops.

11 Remove aileron rig pins.



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FIGURE 6-25 TCU ROD END


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FIGURE 6-26 TACS KINEMATICS

525: -19° (T.E. UP)

9° (T.E. DOWN)

525A & 525B: -21° (T.E. UP)

10° (T.E. DOWN)



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FIGURE 6-27 ATLAS HARD STOP CLEARANCE CHECK

AFT

OTBD

CHECK MINIMUM .015 INCH HERE

(REFERENCE)


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(c) Rigging for TACS Spring

1 Using an inclinometer, set TACS deflection trailing edge up 2 degrees.

2 Adjust SPRING BOLT so that it is engaged, tighten JAM NUTS and safety (refer to FIGURE 6-28).

FIGURE 6-28 TACS SPRING BOLT RIGGING

TACS Hinge Functional Test

(a) Disconnect the TACS pushrod at the TACS.

(b) Apply hand pressure at the trailing edge of the TACS and ensure that the inboard and outboard bearing center ball rotate with the TACS and the bolts through the full TACS travel (refer to FIGURE 6-29)

(c) If either of the bearing center balls do not rotate with the TACS, ensure the bolts are torqued per Section 5D and perform Step (b) again.

(d) If more than 1 lb of force is required at the inboard trailing edge of the TACS, or the bearing center balls do not rotate with the TACS, there is excess friction in the bearings, they must be replaced, per Section 6N.

(e) Reconnect the TACS pushrod at the TACS. Torque all fasteners per Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35 and install safeties on TACS pushrods.

SPRING BOLT

JAM NUTS



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FIGURE 6-29 TACS HINGE FUNCTIONAL TEST


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TACS - Inspection

(a) TACS Skins

1 Visually inspect for: corrosion, disbond, cracks, scratches, dents, distortion, missing paint/primer, or other signs of damage.

2 Inspect the security of the centering strips and the bond line between the strips and the TACS skin as shown in FIGURE 6-30.

FIGURE 6-30 TACS CENTERING STRIPS

3 If cracks or distortion are found, replace components.





(b) TACS Balance Weight

1 Access via Balance Weight Cover, refer to FIGURE 6-21.

2 If corrosion is found repair is limited to minor damage. Reference Cessna Model 525/525A/525B Structural Repair Manual 51-10-01. Repair per 51-70-01 or 51-70-08.

3 If loose hardware is found, re-apply Loctite to fasteners and re-torque. MS51957-45 torque to 14 in-lb. MS24693S26 torque to 8 in-lb.



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(c) TACS Hinge Internal Fittings and Hardware

1 Visually inspect for: corrosion, cracks, scratches, dents, distortion, missing paint/primer, loose hardware or other signs of damage.

2 If any damage is found except missing paint/primer or minor scratches as classified below, replace component.

3 Repair scratches that meet depth requirements per Cessna Model 525/525A/525B Structural Repair Manual 51-70-08, Class 2 and Class 4 or 51-70-02 Section 2.





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M. TACS Return Spring

TACS Return Spring – Removal / Installation

(a) Remove bellcrank per Section 6J1(a).

(b) Remove or install 2X bolts and associated hardware that secure spring to bellcrank. Refer to FIGURE 6-31.

FIGURE 6-31 TACS RETURN SPRING



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N. Hinge Bearings

Hinge Bearing - Inspection

(a) Perform bearing functional check per Section 6L(4).

(b) If either of the bearing center balls do not rotate with the TACS, ensure the bolts are torqued per Section 5D and perform Step (b) of Section 6L(4) again.

(c) If more than 1 lb of force is required at the inboard trailing edge of the TACS there is excess friction in the bearings, they must be replaced, per Section 6N(2).

Hinge Bearing - Replacement

(a) Remove TACS (see Section 6L(1))

(b) Remove the 6 bolts and pertaining hardware securing the hinge fittings to the Hinge Support Brackets, 100-57-1125 and 100-57-1126, FIGURE 6-32.

FIGURE 6-32 TACS HINGES

100-57-1125 BRACKET, INBOARD HINGE SUPPORT, OUTBOARD

100-57-1126 BRACKET, OUTBOARD HINGE SUPPORT, INBOARD

100-57-1122 BRACKET, TACS HINGE, INBD

100-57-1120 BRACKET, TACS HINGE, OUTBD


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(c) Remove 2X Hinge Brackets, 100-57-1120 and 100-57-1122.

(d) Split brackets and replace bearings P/N – MS27645-4 (refer to FIGURE 6-33).

FIGURE 6-33 BEARING INSTALLATION

(e) Reinstall 2X Hinge Brackets, 100-57-1120 and 100-57-1122.

(f) Reinstall and torque fasteners per Cessna 525/525A Maintenance Manual 20-10-01, or Cessna 525B Maintenance Manual 20-10-35.

(g) Apply surface protection to any bare surfaces.

(h) Reconnect the TACS per Section 6L(1) and check per Section 6L(4).

(i) Rig the TACS per Section 6L(3).



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O. ATLAS

ATLAS Functional Test

(a) Apply external power and verify that the aircraft has 25 VDC minimum.

(b) Move aircraft BATT SWITCH to EMER and verify that the ATLAS INOP Button illuminates, indicating a fault.

(c) Move aircraft BATT SWITCH to BATT, turn on avionics master switch, and verify that the ATLAS INOP Button extinguishes, indicating a no fault condition.

(d) Perform a BIT by pushing the ATLAS INOP Button three times in a three second window.

(e) Verify the ATLAS INOP Button flashes three times then extinguishes, indicating a no fault condition. First to test the upper LEDs, second to test the lower LEDs and third to test all the LEDs.

(f) Open the ATLAS MAIN circuit breaker on the Co-Pilot circuit breaker panel and verify that the ATLAS INOP Button illuminates, indicating a fault. Close ATLAS MAIN circuit breaker. ATLAS INOP button light should extinguish.

(g) Open the ATLAS circuit breaker on the aft J-Box circuit breaker panel and verify that the ATLAS INOP Button illuminates, indicating a fault. Close ATLAS circuit breaker in aft J-Box. ATLAS INOP button light should extinguish.

If this circuit breaker is left open for more than 3 seconds, then a button push or a power cycle will be needed to extinguish the light.

(h) Remove external power.

If ATLAS INOP Button does not extinguish refer to Section 8.


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7. Airworthiness Limitations

The Airworthiness limitations section is EASA approved and provides instructions for continued airworthiness information.

The Airworthiness Limitations section is FAA approved and specifies maintenance required under Secs. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved.

There are no new (or additional) airworthiness limitations associated with this equipment and/or installation.

When each of the specific inspections in this section is performed, general examination of the adjacent areas must be performed while access is available. These general visual examinations are done to find easily seen conditions for which additional maintenance procedures are necessary. When access has been made to an area, visually inspect for general condition of all adjacent components, including structural, mechanical systems, and electrical components. Visual inspect for corrosion, fretting, cracks, loose fasteners, loose electrical connections, loosened or damaged wires, loose safety wire connections, and other worn or damaged conditions. The inspection program calls for attention to detail and professional judgment from the inspection personnel to make sure that all of the components and systems are maintained and inspected to the high standard consistent with the industry.

The installation of ATLAS winglets on the Cessna 525, 525A or 525B Citation requires interval changes to the maintenance actions as listed in this section.

Cessna Wing Inspections

Inspection intervals are those shown in the Model 525, 525A or 525B Maintenance Manual under Inspection Time Limits (Section 4-10-00) and are not affected by the ATLAS installation.

Wing Tip & ATLAS Inspections

The items listed in TABLE 7-1 through TABLE 7-3 of this AMM supplement are required maintenance items and must be performed to satisfy all applicable regulatory maintenance requirements. The inspection intervals for ATLAS components (wing extension, TACS, winglet, etc.) given in TABLE 7-1 are measured from the aircraft time or calendar time at initial installation.

Required replacement times are shown in TABLE 7-2. Times shown are recurrent after initial installation.

Required maintenance actions are shown in TABLE 7-3. Times shown are recurrent after initial installation.

Inspection Interval Codes

Interval 3C – Item(s) which are completed every 36 calendar months.

ATLAS 3C inspections to be completed during Doc 4 or Doc 10 OEM inspections except if ATLAS has less than 100 hours or 12 calendar months since ATLAS installation.



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TABLE 7-1 INSPECTION INTERVALS – ATLAS COMPONENTS

ITEM INTERVAL INSPECTION PROCEDURES /

ALLOWABLES REFER TO

Spar Straps, Shear Ties, Skin Splices

3C 6D(2)

Spar Caps 3C 6D(2)

Spar Webs, Leading Edge & Internal Brackets

3C 6D(2)

Extension Skins 3C 6D(2)

Winglet Attachment Rib 3C 6D(2)

Internal Hardware 3C 6D(2)

Bearings, Bushings, and Fasteners

3C *100 Flight Hours

6N(1)

TACS Skins & Centering Strips

3C 6L(5)

Balance Weight 3C 6L(5)

TACS Hinges and associated internal fittings and hardware.

3C 6L(5)

Winglet Skins 3C 6F(2)

Winglet Leading Edge Tape

3C 6F(2)

Static Wicks 3C 6G(3)

ACU Mount Structure & Hardware

3C 6B(4)

Annunciator LRU mount & hardware

3C 6C0

TCU 3C 6K(3)

*Applicable if ATLAS Kit 101-0001 thru 101-0021 is installed and SBATLAS-57-02 has not been completed.


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TABLE 7-2 REQUIRED REPLACEMENT TIMES

ITEM REQUIRED REPLACEMENT TIME 100-57-1044 SPRING, TACS RETURN Reference Section 6M(1)

1000 Hours Replace part 100-57-1044 Replace chafe tape and inspect for chaffing on the bellcrank at this time also. (If chaffing is present on bellcrank, sand the surface smooth and restore surface finish.)

TABLE 7-3 REQUIRED MAINTENANCE INTERVAL

ITEM REQUIRED ACTION INTERVAL 100-39-0100 ACU Assembly Reference 6B(1) for removal / installation.

Recalibration 6 Years



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8. ATLAS Troubleshooting

Prior to any troubleshooting activities, the airplane is to be made safe. Refer to Cessna 525/525A/525B Maintenance Manual Section 20-00-00 for safe maintenance information and procedures.

TABLE 8-1 ATLAS TROUBLESHOOTING

Problem Probable Cause Remedy

ATLAS INOP Button won’t extinguish

Aircraft electrical system is below ATLAS minimum operational voltage (less than 25 VDC)

Turn at least one of the generators to the ON position (Engines Running) or engage external power unit (Ground Power)

AVIONICS switch not in the ON position

Turn AVIONICS power switch to the ON position

BATT switch in the EMER position

Switch battery switch to the BATT position

ATLAS MAIN; or (525 ONLY) ATLAS MAIN, EMER1, or EMER 2 circuit breakers disengaged

Engage ATLAS all ATLAS Circuit Breakers

ACU has detected an ATLAS fault

Refer to FIGURE 8-1 for ATLAS fault verification procedure

ATLAS INOP Button is dim or no fault annunciated with AVIONICS switch off or main ATLAS circuit breaker open

Malfunctioning ACU, Annunciator LRU, ATLAS INOP Button, or Wiring

Refer to FIGURE 8-2 for isolation procedure.

TACS does not move to faired position when AVIONICS switch is switched on

Malfunctioning wiring, TCU or Main ATLAS Relay

Refer to FIGURE 8-3 for fault isolation procedure

ATLAS will not run Built In Test (BIT)

Malfunctioning ATLAS INOP Button, Annunciator LRU or ACU

Refer to FIGURE 8-4 for fault isolation procedure

TACS has excessive free play (see Section (3) for tolerance)

Loose bolts, worn bearings or worn bushings in mechanical linkage between TCU and TACS

Investigate loose or worn hardware and replace as necessary

Note that all flow charts presented below are presented for ground troubleshooting by maintenance personnel only.

For connector names and pin assignments, refer to the ATLAS Wiring Diagram Manual Supplement.


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FIGURE 8-1 ATLAS FAULT VERIFICATION; FLOW DIAGRAM

Light extinguishes: Press the ATLAS INOP Button three times rapidly to run the Built In Test (BIT). If-

ATLAS INOP Button illuminated (Faulted Condition)

Press ATLAS INOP Button once. If-

Light remains illuminated: ATLAS Fault remains. Contact a Cessna Citation Service Center.

Light extinguishes: Fault has cleared. No further action is required unless the ATLAS continues to fault.

Light remains illuminated: ATLAS fault remains. Open ATLAS MAIN circuit breaker located in Co-Pilot’s circuit

breaker panel and reset. If-

Light remains illuminated: ATLAS Fault remains. Contact a Cessna Citation Service Center.

Light illuminates and extinguishes in a pattern, then illuminates and extinguishes: Fault has cleared. No further action is required unless the ATLAS continues to fault.



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FIGURE 8-2 ATLAS UNPOWERED, NO FAULT ANNUNCIATION; FLOW DIAGRAM

ATLAS INOP Button dim or will not illuminate (ATLAS unpowered).

Engage Ground Power.

Engage all ATLAS circuit breakers.

Move BATT Switch to EMER position.

No voltage is present, check for 25 VDC minimum on Pin 1 of P2 and Pin 9 of P1 on the Annunciator LRU while connected. If-

Voltage is present, Verify ground wiring of relay unit. If no fault is found, replace Annunciator LRU.

There is no voltage, troubleshoot open circuit between essential bus inputs and ACU / Annunciator LRU.

Voltage is present, supply a ground to pin 1 on P1 and Pin 8 on P2 on the Annunciator LRU without disconnecting P1 or P2. If-

Light does not illuminate, Verify conductivity of wiring between Annunciator LRU and ATLAS INOP Button. If no fault is found, Replace ATLAS INOP Button.

Light illuminates, Verify Conductivity of wiring between the Annunciator LRU and ACU. If no fault found, replace ACU.

Check for 25 VDC minimum on pins 6 and 7 of P2 and pins 7 and 8 of P1 on the Annunciator LRU while connected. If-


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FIGURE 8-3 TACS INOPERATIVE; FLOW DIAGRAM

TACS will not move to faired position when power is applied.

Check Main ATLAS circuit breaker in Aft J-Box. If-

Closed, verify P3 and P4 connectors are connected and fully engaged to the TCUs.

Open, then close the ATLAS circuit breaker. If ATLAS circuit breaker opens when power is applied, troubleshoot electrical short between circuit breaker and LH/RH TCU.

Check for adequate electrical grounding between ground points ATG04 and ATG05 located in most outboard wing bay and pin G on TCU connectors P3 and P4.

Disconnect P3 and P4 connectors at TCUs. Apply ATLAS power and verify 28VDC on pin C of TCU connectors P3 and P4. If-

If 28VDC is present, remove and replace TCU associated with TACS that won’t move when

power is applied.

Open, then close the ATLAS circuit breaker. If the ATLAS circuit breaker opens when power is applied, troubleshoot electrical short between circuit breaker and LH/RH TCU.



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FIGURE 8-4 ATLAS WON'T RUN BIT; FLOW DIAGRAM

This is TRUE, remove and replace ACU.

Press and hold the ATLAS INOP Button. With the ATLAS INOP Button pressed, there should be 28 VDC on the wire removed from pin 9 (P6). Release the ATLAS INOP Button and there should be no voltage.

Assure correct switch operation. Move BATT switch to the OFF position. Disconnect P1 connector from Annunciator LRU. Using an ohmmeter, there should be no conductivity between pins 9 and 5 and there should be conductivity between pins 4 and 5. Push the ATLAS INOP Button and the opposite should be true. Ensure test is being conducted on internal Annunciator connector and not unplugged wire harness. If-

This is TRUE, the switch is operating normally. Re-connect P1.

This is FALSE, the switch doesn’t

operate normally. Replace the ATLAS INOP Button.

If this is FALSE, remove and replace Annunciator LRU.

ATLAS will not run Built in Test (BIT)

Engage ground power; assure 25 VDC minimum system voltage.

Close all ATLAS circuit breakers.

Move BATT Switch to BATT position.

Assure that the ATLAS INOP Button is extinguished, indicating a no fault condition.

Remove pin 9 from P6 (ACU) and connect a voltmeter to the removed pin