CITATION CJ3+
SPECIFICATION AND DESCRIPTION
REVISION C JANUARY 2021 SERIAL NUMBER 525B0610 TO TBD SPECIFICATION AND DESCRIPTION
CITATION CJ3+ SERIAL NUMBER 525B0610 TO TBD JANUARY 2021 REVISION C TABLE OF CONTENTS
LIST OF FIGURES ...... iv INTRODUCTION ...... 1 THE AIRCRAFT...... 2 1. GENERAL DESCRIPTION ...... 2 1.1 Certifi cation...... 2 1.2 Purchaser’s Responsibility...... 2 1.3 Approximate Dimensions ...... 5 1.4 Design Weights and Capacities ...... 5 2. PERFORMANCE ...... 5 3. DESIGN LIMITS ...... 6 4. FUSELAGE ...... 7 4.1 Design and Construction ...... 7 4.2 Nose Section ...... 7 4.3 Interior Spaces ...... 7 4.4 Aft Fuselage ...... 7 5. WING ...... 7 6. EMPENNAGE ...... 7 7. LANDING GEAR ...... 8 7.1 Design and Construction ...... 8 7.2 Nosewheel Steering ...... 8 7.3 Brakes and Tires ...... 8 8. PROPULSION ...... 8 8.1 Powerplant ...... 8 9. SYSTEMS ...... 9 9.1 Flight Controls ...... 9 9.2 Fuel System ...... 9 9.3 Electrical System ...... 9 9.4 Exterior Lighting System ...... 10 9.4.1 Primary ...... 10 9.4.2 Secondary ...... 10 9.5 Pressurization and Environmental System ...... 10
i CITATION CJ3+ • JANUARY 2021 TABLE OF CONTENTS CONT
9.6 Oxygen System ...... 10 9.7 Anti-Icing System and Rain Removal ...... 10 9.7.1 Ice ...... 10 9.7.2 Rain ...... 11 9.8 Hydraulic System ...... 11 10. FLIGHT COMPARTMENT ...... 12 10.1 General ...... 12 10.2 Instrumentation ...... 13 10.3 Avionics...... 14 10.3.1 Flight Displays ...... 14 10.3.1.1 Primary Flight Displays (PFDs) ...... 14 10.3.1.2 Multifunction Display (MFD) ...... 14 10.3.2 Garmin Touchscreen Control (GTC) Panels ...... 15 10.3.3 Garmin Integrated Avionics Unit (GIA) ...... 15 10.3.3.1 Global Positioning System (GPS) ...... 15 10.3.3.2 Very High Frequency Radio (VHF) ...... 15 10.3.3.3 Navigation Receivers ...... 15 10.3.4 Cockpit Voice Recorder (CVR) ...... 15 10.3.5 Flight Management System (FMS) ...... 15 10.3.6 Electronic Charts and Maps ...... 16 10.3.7 Distance Measuring Equipment (DME) ...... 16 10.3.8 Engine Indicating System (EIS) ...... 16 10.3.9 Crew Alerting System (CAS) ...... 16 10.3.10 Flight Guidance System (FGS) ...... 17 10.3.11 Attitude/Heading Reference System (AHRS) ...... 17 10.3.12 Transponders with ADS-B Out Capability ...... 17 10.3.13 Weather Radar ...... 17 10.3.14 Radio Altimeter...... 17 10.3.15 Traffi c Collision Avoidance System (TCAS) ...... 18 10.3.16 ADS-B In Capability ...... 18 10.3.17 Terrain Awareness And Warning System (TAWS) ...... 18
CITATION CJ3+ • JANUARY 2021 ii TABLE OF CONTENTS CONT
10.3.18 Emergency Locator Transmitter (ELT) ...... 18 10.3.19 Standby Instrumentation ...... 18 10.3.20 Maintenance Diagnostics ...... 18 11. INTERIOR ...... 19 11.1 Cabin ...... 19 11.2 Windows ...... 20 11.3 Cabin Lighting System ...... 20 11.3.1 Direct Lighting ...... 20 11.3.2 Indirect Lighting ...... 20 11.3.3 Emergency Lighting ...... 20 12. EXTERIOR ...... 20 12.1 Exterior Storage ...... 21 13. LOOSE EQUIPMENT ...... 21 14. EMERGENCY EQUIPMENT ...... 22 15. DOCUMENTATION AND TECHNICAL PUBLICATIONS ...... 22 16. MAINTENANCE TRACKING PROGRAM ...... 24 17. LIMITED WARRANTIES ...... 24 17.1 Limited Aircraft Warranty ...... 24 17.2 Williams’ FJ44-3A Limited Engine Warranty ...... 28 18. TRAINING AGREEMENT ...... 33
iii CITATION CJ3+ • JANUARY 2021 LIST OF FIGURES
Figure 1: Exterior Dimensions ...... 3 Figure 2: Interior Dimensions ...... 4 Figure 3: Instrumentation ...... 13 Figure 4: Cabin Typical Confi guration ...... 19
CITATION CJ3+ • JANUARY 2021 iv INTRODUCTION
This Specifi cation and Description provides general information about the design, performance, and standard equipment of the Citation CJ3+ (Model 525B), Serial Number 525B0610 to TBD (hereinafter Citation CJ3+ or Aircraft). Due to the lapse of time between the date of this publication and Aircraft delivery, Textron Aviation Inc. (hereinafter Seller) reserves the right to revise this Specifi cation and Description when occasioned by product improvements, government regulations, or other good cause, as long as the revisions do not result in a material reduction in Aircraft performance. If there is a confl ict between this Specifi cation and Description and the Aircraft Purchase Agreement into which it is incorporated, the terms and conditions of the Aircraft Purchase Agreement control.
For further information contact:
Textron Aviation Contracts Textron Aviation Inc. P.O. Box 7706 Wichita, Kansas 67277-7706
Telephone: 316-517-6000 Fax: 316-517-6640 E-Mail: [email protected]
1 CITATION CJ3+ • JANUARY 2021 THE AIRCRAFT 1. GENERAL DESCRIPTION
The Citation CJ3+ is a twin engine turbofan jet aircraft. The Aircraft has provisions for 10 occupants including pilot(s) and is certifi ed for single pilot operations. The Citation CJ3+ has internal and external storage compartments for personal items, baggage and cargo.
Two Williams International Co., LLC (Williams) FJ44-3A turbofan engines power the Citation CJ3+ and the fully integrated Garmin G3000 digital avionics suite provides pilots with state-of-the-art touchscreen controls.
1.1 Certifi cation
The Citation CJ3+ is certifi ed in accordance with U.S. 14 CFR Part 23 Commuter Category, including day, night, VFR, IFR and fl ight into known icing conditions. The Citation CJ3+ is compliant with RVSM certifi cation requirements and is FAA and EASA certifi ed for steep approach operations.
Note: Specifi c operator approval is required for operation within RVSM airspace; Seller off ers a no-charge service to assist with this process.
1.2 Purchaser’s Responsibility
International aircraft certifi cation may require modifi cations to and the incorporation of additional equipment into the Aircraft. The Aircraft purchaser (Purchaser) is responsible for the costs of any such modifi cations and incorporation of additional equipment. In addition, the Purchaser is responsible for obtaining approval to operate the Aircraft from the relevant civil aviation authority and for understanding and complying with applicable crew requirements.
CITATION CJ3+ • JANUARY 2021 2 EXTERIOR DIMENSIONS
53 ft 4 in (16.26 m)
20 ft 10 in (6.35 m)
16 ft 0 in (4.88 m)
15 ft 2 in (4.62 m)
20 ft 0 in (6.10 m) 51 ft 2 in (15.59 m)
Figure 1: Exterior Dimensions
3 CITATION CJ3+ • JANUARY 2021 INTERIOR DIMENSIONS
59 in 161 in 27 in (1.50 m) (4.09 m) (.69 m)
58 in (1.47 m)
20 in 19 in (.51 m) (.48 m)
29 in 51 in 11 in (.74 m) (1.30 m) 15 in (.28 m) (.38 m)
57 in (1.45 m)
Figure 2: Interior Dimensions
CITATION CJ3+ • JANUARY 2021 4 1.3 Approximate Dimensions OVERALL HEIGHT 15 ft 2 in (4.62 m) OVERALL WIDTH 53 ft 4 in (16.26 m) OVERALL LENGTH 51 ft 2 in (15.59 m) WHEELBASE 20 ft 0 in (6.10 m)
SPAN AREA SWEEP WING (overall) (at 31% chord) 53 ft 4 in (16.26 m) 294.1 ft2 (27.32 m2 ) 0o SPAN AREA SWEEP HORIZONTAL TAIL (overall) (at 25% chord) 20 ft 10 in (6.35 m) 70.7 ft2 (6.57 m2 ) 20o HEIGHT AREA SWEEP VERTICAL TAIL (at 25% chord) 7 ft 5 in (2.26 m) 56.3 ft2 (5.23 m2 ) 49o HEIGHT LENGTH* WIDTH (max) (max) CABIN INTERIOR 4 ft 9 in (1.45 m) 20 ft 7 in (6.27 m) 4 ft 10 in (1.47 m) (with typical interior) LENGTH**
15 ft 8 in (4.78 m)
*Cabin Length: Forward pressure bulkhead to aft pressure bulkhead **Cabin Length: Excluding fl ight compartment
1.4 Design Weights and Capacities MAXIMUM RAMP WEIGHT 14,070 lb (6,382 kg) MAXIMUM TAKEOFF WEIGHT 13,870 lb (6,291 kg) MAXIMUM LANDING WEIGHT 12,750 lb (5,783 kg) MAXIMUM ZERO FUEL WEIGHT 10,675 lb (4,842 kg)
BASIC OPERATING WEIGHT (Single pilot, 200 lb, typically equipped) 8,540 lb (3,874 kg) FUEL CAPACITY (usable at 6.7 lb/gal) 4,710 lb (2,136 kg) 2. PERFORMANCE
All performance data is based on a standard aircraft confi guration, operating in International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing lengths are based on a fl at even, hard surface at sea level with dry runway. Actual performance will vary with the individual aircraft and other factors such as environmental conditions, aircraft confi guration, and operational/ATC procedures.
5 CITATION CJ3+ • JANUARY 2021 2. PERFORMANCE CONT TAKEOFF FIELD LENGTH 3,180 ft (969 m) (Maximum takeoff weight, 15 degree fl aps, and bleed air on) MAXIMUM CERTIFIED ALTITUDE 45,000 ft (13,716 m)
MAXIMUM CRUISE SPEED (+/- 3%) 416 ktas (770 km/hr) (33,000 feet {10,058 m} altitude; mid-cruise weight, high speed cruise) MAXIMUM FERRY RANGE (+/- 4%) 2,040 nm (3,778 km) (Single pilot, no payload, long range cruise, NBAA IFR reserves with 100 nm alternate) NBAA IFR RANGE (+/- 4%) 1,865 nm (3,454 km) (Max weight, full fuel payload, single pilot, high speed cruise, 100 nm alternate) LANDING DISTANCE 2,770 ft (844 m) (Maximum landing weight, full fl aps) CERTIFIED NOISE LEVELS (Complies with 14 CFR 36, Appendix B, Stage 4 maximum noise level requirements / ICAO Chapter 4 noise levels in Annex 16, Volume 1, Appendix 2, Amendment 7) Flyover 74.0 EPNdB Lateral 88.7 EPNdB Approach 88.6 EPNdB 3. DESIGN LIMITS
DESIGN LOAD LIMITS Flaps UP -1.00 to +2.70G Flaps 15o or 35o 0.00 to +2.00G OPERATING LIMIT SPEEDS
VMO (8,000 ft {2,438 m} to 29,300 feet {8,931 m}) 278 KIAS (515 km/hr)
MMO (above 29,300 feet {8,931 m}) Mach 0.737 (indicated) FLAP LIMIT SPEEDS Maximum Flap Extended Speed
o VFE (Flaps 15 ) 200 KIAS (370 km/hr) o VFE (Flaps 35 ) 161 KIAS (298 km/hr) LANDING GEAR LIMIT SPEEDS
VLO 200 KIAS (370 km/hr)
VLE 200 KIAS (370 km/hr) SPEED BRAKES
VSB No Limit
CITATION CJ3+ • JANUARY 2021 6 4. FUSELAGE
4.1 Design and Construction
The Citation CJ3+ incorporates a circular fuselage of metallic construction with a pressurized cabin. A continuous dropped aisle in the passenger cabin provides optimized cabin room and passenger comfort.
4.2 Nose Section
The nose section has a contoured radome and baggage compartment externally accessible from either side of the Aircraft. The acrylic windshields are designed to meet bird resistance requirements of U.S. 14 CFR Part 25; they are heated and defogged via engine bleed air.
4.3 Interior Spaces
The fl ight compartment and cabin are described in Section 10 and 11, respectively.
4.4 Aft Fuselage
The aft fuselage features a baggage compartment as detailed in Section 12.1. The aft fuselage also features a servicing port for the hydraulic system. 5. WING
This Aircraft features a straight wing design with a natural laminar fl ow airfoil.
Flaps, ailerons and speed brake panels are incorporated into each wing. Additionally, the design of the speed brakes allow for drag control with minimum pitching moments. 6. EMPENNAGE
The empennage features a T-Tail confi guration. Elevators and rudder are mechanically actuated.
7 CITATION CJ3+ • JANUARY 2021 7. LANDING GEAR
7.1 Design and Construction
The main landing gear is of a trailing link design. The gear is hydraulically actuated and for back-up operation, the landing gear off ers two means of emergency gear extension: a pneumatic blow-down system and a manual uplock release that allows the gear to free-fall into the down and locked position.
7.2 Nosewheel Steering
The nose gear assembly is of conventional strut design with a single wheel and tire. Rudder pedals provide mechanical nosewheel steering.
7.3 Brakes and Tires
The multi-disc, anti-skid brake system is powered by an independent electrically driven hydraulic system. Emergency braking is through a pneumatic back-up system.
The Citation CJ3+ is equipped with single wheels and tires (three tires; one nose gear and one each left and right main).
PLY MAX SPEED RATING SIZE NOSE GEAR TIRES 10 190 mph (306 km/hr) 18” x 4.4R8” MAIN TIRES 14 190 mph (306 km/hr) H22” X 8.25-10” 8. PROPULSION
8.1 Powerplant
The Aircraft is powered by two Williams FJ44-3A turbofan engines installed on the aft fuselage. The FJ44-3A engines incorporate dual channel Full Authority Digital Electronic Controls (FADEC) that provide automation and effi ciency in engine management.
Detents in the throttle quadrant for idle, takeoff (TO), climb (CLB), and maximum cruise (CRU) give pilots the optimal power settings for each phase of fl ight based on ambient conditions. A takeoff /go-around button is located on the throttle lever.
TAKEOFF THRUST (at sea level) 2,820 lb (12.54 kN) FLAT RATED TO 78.8oF (26oC) TBO 4,000 Hours 5,000 Hours on TAP Blue
CITATION CJ3+ • JANUARY 2021 8 9. SYSTEMS
9.1 Flight Controls
The Primary Flight Controls (PFC) are mechanically operated via a push rod and cable system. PFCs consist of one aileron on each wing, one elevator on each side of the horizontal tail, and one rudder on the vertical tail.
Secondary fl ight controls include trim, speed brakes and fl aps. The elevator trim is electrically controlled while the aileron and rudder trim is mechanically controlled. The speed brakes and fl aps are electrically controlled and hydraulically actuated. All control surfaces, speed brakes and fl aps are of aluminum construction. Trim tabs are of composite construction. A single yaw damper system improves performance and comfort.
9.2 Fuel System
There are two integral fuel tanks, one in each wing.
There are two independent fuel supply systems, one located in each wing. System operation is fully automatic with each engine receiving fuel from its respective wing tank.
Electric boost pumps located in the wing roots supply fuel during engine start, crossfeed, and as needed to supply the required fuel pressure.
Refueling is accomplished through over wing fi ller ports with fl ush mounted locking caps. The Citation CJ3+ is certifi ed for a wide range of jet fuels. Total useable fuel is 4,710 lb (2,136 kg).
9.3 Electrical System
The parallel bus electrical system is powered by two engine-driven, 300 amp starter/generators. The Aircraft’s main battery is a 44 amp-hour Nickel-Cadmium battery which is located in an access panel in the aft baggage compartment. A sealed lead acid 24V, 14 amp-hour auxiliary battery, installed underneath the tailcone baggage compartment, works in conjunction with the primary ships battery to allow for avionics to be powered on during engine starts.
If all engine-driven power sources are lost, the Aircraft’s main and auxiliary batteries provide power to the emergency bus for a limited period of time.
9 CITATION CJ3+ • JANUARY 2021 9.4 Exterior Lighting System
9.4.1 Primary Standard exterior lighting consists of a fl ashing red beacon for ground recognition, anti-collision lights, position lights, landing/recognition lights (including the Pulse Light system which, when activated, pulses the landing/recognition lights) and taxi lights.
9.4.2 Secondary Tail logo lights, located on the left and right horizontal stabilizer, illuminate the vertical stabilizer surfaces. Other secondary lighting includes a wing inspection light and ice detection lights mounted on the glareshield and left side of the fuselage.
9.5 Pressurization and Environmental System
Bleed air from each engine supplies cabin pressurization. The pressurization control system automatically schedules cabin altitude. Cabin pressure and cabin rate of climb are displayed on the Multifunction Display. Cabin temperature can be controlled through the cockpit controls.
CABIN PRESSURIZATION* Nominal Pressurization Diff erential 8.9 PSID Cabin Altitude at Aircraft’s Certifi ed Ceiling 8,000 ft @ 45,000 ft *NOTE: Nominal cabin pressurization diff erential refers to the control setpoint programmed into the pressurization controller. There can be variances from this value due to system design tolerances.
9.6 Oxygen System
An automatic dropout oxygen mask is provided for each passenger. Pressure demand masks are provided for the crew. Oxygen pressure readout is available on the Multifunction Display.
9.7 Anti-Icing System and Rain Removal
9.7.1 Ice Engine bleed air sustains the anti-icing system. The wing leading edge, engine inlets and windshield are heated by bleed air. The horizontal stabilizer utilizes a pneumatic boot ice protection system. Electric heat is used to remove ice from the pitot/static system and Angle of Attack (AOA) systems.
CITATION CJ3+ • JANUARY 2021 10 9.7.2 Rain The windshield rain removal is accomplished with engine bleed air during normal operations and by mechanically actuated rain doors in heavy rain.
9.8 Hydraulic System
The hydraulic system employs pressure to operate the landing gear, speedbrakes, and fl aps. The main hydraulic system is engine driven. A separate electrically driven hydraulic system provides pressure for the brakes.
The hydraulic system maintains a continuous pressure of approximately 1,500 psi (103.4 bar).
11 CITATION CJ3+ • JANUARY 2021 10. FLIGHT COMPARTMENT
10.1 General
The Garmin G3000 system is the featured avionics suite on the Citation CJ3+. Two full-color, touchscreen control panels are used by the crew to manipulate G3000 system features.
Two complete crew stations are furnished with dual controls, including control columns, adjustable rudder pedals and brakes. The fully adjustable crew seats include fi ve-point restraint harnesses, and some storage is provided behind each of the two seats. The oxygen system provides two pressure demand masks with microphones for the crew members. The oxygen masks are stored in a container above the shoulder of each crewmember and circuit breaker panels are located on both the pilot’s and co-pilot’s sidewalls.
LED illuminated panels, instrument fl oodlights, toggle switches and overhead map lights are standard in the fl ight compartment.
CITATION CJ3+ • JANUARY 2021 12 10.2 Instrumentation
4 5 2 3
1
7
10 8
6 9 11
Figure 3: Instrumentation 1. Primary Flight Display (PFD) 7. LH Tilt Panel 2. Multifunction Display (MFD) 8. RH Tilt Panel 3. Master Caution and Master Warning 9. Engine Throttle Levers Annunciations 4. Electronic Standby Instrument (ESI) 10. Flaps Control
5. Automatic Flight Control System (AFCS) 11. Speed Brake Control
6. Dual Touchscreen LCD Control Panels
13 CITATION CJ3+ • JANUARY 2021 10.3 Avionics
The Garmin G3000 avionics system includes the Garmin Integrated Flight Deck (GIFD), fl ight crew radio communications, Flight Management System, Engine Indicating System, Crew Alerting System, Automatic Flight Control System and Attitude/Heading Reference System.
During the normal course of aircraft manufacturing, maintenance and operation, technicians install or update certain software and data onto standard and optional avionics and other equipment. During the course of such installation, it may be necessary to digitally “accept” or otherwise consent to certain supplier required end-user license agreements (EULA) and other terms and conditions in order to proceed with the software or data installation process. These are commonly referred to as “click-wrap” or “click-through” digital agreements. Purchaser hereby authorizes and consents to technicians clicking “accept” on such agreements and agrees to be bound by the terms of such agreements. Purchaser acknowledges and agrees that it will independently review such “click-wrap” agreements.
10.3.1 Flight Displays The GIFD includes three 14-diagonal-inch, high-resolution Liquid Crystal Displays (LCD) in widescreen, landscape orientation. The two outer displays are the Primary Flight Displays. The Multifunction Display is centrally located.
10.3.1.1 Primary Flight Displays (PFDs)
The two PFDs are located on the pilot’s and copilot’s instrument panels. The PFDs display fl ight information, moving map imagery and color- coded Crew Alerting System messages. 10.3.1.2 Multifunction Display (MFD)
The MFD, which is located in the center panel, displays a detailed moving map, terrain, traffi c and weather information as well as a dedicated engine and systems information window. Display of electronic charts and taxi diagrams with Aircraft position shown is included. All fl ight displays can operate in full-screen or split-screen mode. Multiple reversionary modes provide for control redundancy.
Applicable subscription services are the Purchaser’s responsibility.
CITATION CJ3+ • JANUARY 2021 14 10.3.2 Garmin Touchscreen Control (GTC) Panels Two full-color touchscreen LCD control panels are used to manipulate G3000 system features such as radio tuning, transponders, intercom, fl ight planning, selected Aircraft systems such as environmental control and internal lighting and MFD windows to display desired information. If a control panel becomes inoperative, the remaining control panel can take on additional control responsibility.
10.3.3 Garmin Integrated Avionics Unit (GIA) Dual Integrated Avionics Units include the Global Positioning System (GPS), Wide Area Augmentation System (WAAS) receivers, Very High Frequency (VHF) communication radios, VHF navigation radios and glide slope receivers in addition to supporting input-output processing, aural alert generation and Flight Director functions.
10.3.3.1 Global Positioning System (GPS)
The G3000 system includes dual GPS with WAAS/LPV receivers as part of the GIA. 10.3.3.2 Very High Frequency Radio (VHF)
The G3000 system includes two standard VHF voice radios that are part of the GIA. The VHF voice radios are controlled by the fl ight crew via the GTCs for voice communications with ATC, etc. 10.3.3.3 Navigation Receivers
The G3000 system includes two standard VHF navigation radios as part of the GIA. 10.3.4 Cockpit Voice Recorder (CVR) The Aircraft is equipped with provisions for a CVR.
10.3.5 Flight Management System (FMS) Dual Flight Management Systems (FMS) are fully integrated into the Garmin G3000 system. Each FMS provides navigation and fl ight planning capabilities as well as takeoff , and landing performance calculations. Supported features include (among others):
• Map Displays—Moving maps on the PFDs and MFD
• Flight Planning—Direct-To navigation, lateral and vertical navigation, procedures, etc.; fl ight planning is controlled by the GTCs
15 CITATION CJ3+ • JANUARY 2021 • Takeoff and Landing Data (TOLD)—Computes Vspeeds based on Aircraft confi guration, loading and runway conditions
• Precision and non-precision approach operations including LNAV/VNAV and Localizer Performance with Vertical Guidance (LPV) approaches
• Navigational Operations including NAT, NAT HLA (formerly MNPS), RNP 10, BRNAV, RNP 4, PRNAV, and RNP-APCH to a minimum value of RNP 0.3
• Aircraft position based upon GPS/SBAS and scanning DME/DME inputs
Applicable subscription services are the Purchaser’s responsibility.
10.3.6 Electronic Charts and Maps The Electronic Charts function allows the crew to view ChartView electronic charts on the Garmin Display Units (GDU), which are customizable to either the PFDs or MFD. The ChartView database is available by subscription from Jeppesen, Inc.
Applicable subscription services are the Purchaser’s responsibility.
10.3.7 Distance Measuring Equipment (DME) A Collins Aerospace DME-4000 unit is integrated into the Garmin G3000 system. This unit provides DME information to the pilots and provides scanning DME/DME input capability for the FMS.
10.3.8 Engine Indicating System (EIS) The Engine Indicating System (EIS) displays electrical, fuel, engine, pressurization and temperature information on the left side of the MFD.
10.3.9 Crew Alerting System (CAS) The Crew Alerting System (CAS) displays Master Caution (yellow) and Master Warning (red) Messages on both PFDs. Messages fl ash inverse video until acknowledged by depressing either the Master Caution or Master Warning switches as appropriate. Master Warning Messages appear at the top of the display area followed by Master Caution Messages.
CITATION CJ3+ • JANUARY 2021 16 10.3.10 Flight Guidance System (FGS) The Automatic Flight Control System (AFCS) is part of the Garmin G3000 system. The AFCS can be divided into the following functions:
• Flight Director—The Flight Director provides vertical/lateral mode selection and processing, command bars showing pitch/roll guidance and pitch/roll commands to the autopilot.
• Autopilot—The autopilot provides automatic fl ight control in response to Flight Director steering commands, hybrid navigator attitude and rate information and airspeed.
• Yaw Damper—The yaw damp actuator provides Dutch roll damping and turn coordination in response to yaw rate, roll angle, lateral acceleration and airspeed.
• Automatic Pitch Trim—The pitch trim system provides automatic pitch trim when the autopilot is engaged.
10.3.11 Attitude/Heading Reference System (AHRS) Two Garmin GRS 77 Attitude Heading Reference System (AHRS) computers are installed to supply attitude, heading and fl ight dynamics information to the fl ight control and display system.
10.3.12 Transponders with ADS-B Out Capability The G3000 system includes two standard Garmin GTX 3000 transponders. The transponders are controlled by the fl ight crew via the GTCs. ADS-B Out capability is standard.
10.3.13 Weather Radar Weather radar information is provided via the Garmin GWX processor. The system includes a 12-inch antenna. Solid-state electronics (i.e., no magnetron) and transmitter power of 40 Watts provide for enhanced performance compared with traditional radar systems having higher output power. The weather radar system includes WATCH automatic range limiting and vertical scan capability.
10.3.14 Radio Altimeter The G3000 system includes one standard Collins ALT-4000 radio altimeter unit that supplies information to the Traffi c Collision Avoidance System (TCAS) and the Terrain Awareness and Warning System (TAWS).
17 CITATION CJ3+ • JANUARY 2021 10.3.15 Traffi c Collision Avoidance System (TCAS) A Garmin GTS 8000 TCAS II system is included, providing traffi c and resolution advisories. This system is compliant with Change 7.1 regulatory requirements.
10.3.16 ADS-B In Capability ADS-B In functionality increases crew situational awareness by providing position, direction and altitude information for aircraft within the vicinity of the Aircraft’s current position. The crew can display other aircraft (both on the ground and in air) relative to the Aircraft’s position.
10.3.17 Terrain Awareness And Warning System (TAWS) The G3000 system includes a Class B Terrain Awareness and Warning System (TAWS). The TAWS function is allocated to the fl ight display units, providing weight and hardware resource savings as well as increased redundancy and availability.
10.3.18 Emergency Locator Transmitter (ELT) An Artex C406-N Emergency Locator Transmitter (ELT) with navigation interface is standard.
Note: Some authorities may not permit the use of navigation interface capability.
10.3.19 Standby Instrumentation An Electronic Standby Instrument (ESI), powered by the main bus, with its own backup battery, provides standby airspeed, attitude, altitude and slip/skid information.
10.3.20 Maintenance Diagnostics The G3000 system includes the capability to record specifi c maintenance diagnostic information that can be reviewed on the MFD while on the ground and downloaded for review off the Aircraft. The Textron Aviation Aircraft Recording System (AReS) records useful data during the previous 800+ fl ight hours in non- volatile memory for advanced troubleshooting and analysis by systems specialists from Textron Aviation Inc.’s Service and Support network. AReS is on whenever the Aircraft is powered on.
Purchaser agrees that Seller has a perpetual license to use all information contained in the Aircraft recording and/or diagnostic system for any reason, including maintenance and accident investigation. Purchaser expressly provides Seller with licensed permission to download use, and/or read such information at any time. Purchaser further agrees this perpetual license runs with and is automatically transferred with the title to the Aircraft and is binding on any and all subsequent purchasers of the Aircraft.
CITATION CJ3+ • JANUARY 2021 18 11. INTERIOR
11.1 Cabin
There is one main cabin door with a folding air stair that is mechanically operated. The cabin is separated from the fl ight compartment by a curtain. The cabin extends from the fl ight compartment divider to the aft pressure bulkhead. A dropped aisle extends aft from the cockpit curtain into the lavatory and provides a cabin height of 57 inches (1.45 m). An emergency exit hatch is located on the right side over the wing.
The cabin is sized to off er passenger comfort and fl exibility for two separate interior arrangements. The typical arrangement is an eight-passenger, single club seating arrangement with dual forward facing seats aft of the club and a belted side facing seat located in the lavatory. Optional seating arrangements are available.
The following are included in the typical arrangement:
• A right-hand refreshment center with a heated liquid container, two dispensers for disposable cups, beverage storage, ice drawer, trash receptacle, multiple storage areas;
• A left-hand cabinet, forward of the cabin entry door, contains various general storage areas with adjustable shelves;
• Six pedestal-mounted passenger seats with adjustable headrests. Seats #5 and #6 have fl oor tracking. Each seat is equipped with a seat belt and an over-water life vest stored under the seat; Figure 4: Cabin Typical Confi guration
19 CITATION CJ3+ • JANUARY 2021 • Four fold out tables with ample work area are included. Side ledges have cup holders;
• Two individual 115V AC outlets are located at the center club forward facing seats. Each outlet plate contains two USB charging ports;
• The aft lavatory with a belted fl ushing toilet has sliding privacy doors.
A full range of fabrics, leathers, carpets, laminates, selected wood veneers and metal fi nishes are available to custom confi gure the interior furnishings to meet a wide variety of customer tastes. Certifi ed burn-resistant materials are used throughout the cabin and fl ight compartment. Bagged insulation and sound proofi ng are consistent with this category of aircraft, given its operating speeds and environment.
11.2 Windows
Fourteen cabin windows are equipped with manual window shades.
11.3 Cabin Lighting System
11.3.1 Direct Lighting Direct LED lighting includes a cabin entry light, reading/table lights and lavatory lights. The lighting can be controlled by the toggle switches at each passenger seat, the entry switch, or the master switch panel mounted in the LH forward cabinet.
11.3.2 Indirect Lighting Cabin-length indirect LED lighting is provided overhead and can be controlled via the master switch panel.
11.3.3 Emergency Lighting Emergency Exit Lighting is powered by the Emergency Lighting Battery Pack in case of a power interruption. 12. EXTERIOR
Distinctive exterior styling featuring polyurethane paint in a variety of colors is provided.
The available registration number of Purchaser’s choice will be painted on the Aircraft at no additional cost to Purchaser. It may be necessary to use a temporary registration number until the number selected by Purchaser is assigned to the Aircraft by the appropriate aviation authority.
CITATION CJ3+ • JANUARY 2021 20 12.1 Exterior Storage
Two exterior baggage areas off er external storage. The main baggage area is accessible through a 26” wide lockable door located on the left hand side of the fuselage beneath the engine pylon and features a 600 lb capacity. The nose baggage compartment is externally accessible from either side of the aircraft and features a 400 lb capacity.
Weight Volume Main Baggage Area* 600 lb (272 kg) 50.0 ft3 (1.42 m3) 84 in (2.13 m) L x 46 in (1.17 m) W x 23 in (0.58 m) H Nose Baggage Area 400 lb (181 kg) 15.0 ft3 (0.42 m3) 40 in (1.01 m) L x 57 in (1.45 m) W x 18 in (0.46 m) H Total Exterior Storage 1,000 lb (454 kg) 65 ft3 (1.84 m3)
*The main baggage area is tapered and dimensions listed are maximums. 13. LOOSE EQUIPMENT
Aircraft Keys (10)
Baggage Tie-Down Straps (6)
Blank Nav Data SD Card (1)
Center Aisle Carpet (1)
Coat Hangers (8)
Crew Noise-Canceling Headsets (2)
Engine Cover Set (1)
Fuel Cap Keys (4)
Interior Cleaning Kit (1)
Jack Pad (1)
Leather Cleaning Kit (1)
Passenger Briefi ng Cards (10)
Pitot Cover Set (1)
21 CITATION CJ3+ • JANUARY 2021 Screwdriver (1)
Static Wick Covers (7)
Sump Cup (1) 14. EMERGENCY EQUIPMENT
Emergency Exit Lock Pin (1)
Fire Extinguisher (2)
First Aid Kit (1)
Flashlights (2)
Life Vest Per Seat (1)
MLG Tow Straps (2) 15. DOCUMENTATION AND TECHNICAL PUBLICATIONS
The following will be provided to Purchaser.
Print material:
Airplane Flight Manual which includes the Weight and Balance Manual Log Books (Aircraft and Engines)
Passenger Briefi ng Cards
Pilot’s Checklist
Pilot’s Operating Manual
U.S. Standard Airworthiness Certifi cate, FAA8100-2; Export Certifi cation of Airworthiness, FAA8130-4 or Special Airworthiness Certifi cate FAA8130-7 as appropriate
Available on Flash Drive only:
Cabin Equipment Operation Manual
Illustrated Parts Catalog — Interior
Interior Maintenance Manual
CITATION CJ3+ • JANUARY 2021 22 Available via online subscription at https://ww2.txtav.com:
Component Maintenance Manual
Illustrated Parts Catalog — Airframe
Maintenance Manual — Airframe
Nondestructive Testing Manual
Service Bulletins and Service Letters — Airframe
Structural Repair Manual
Wiring Diagram Manual
Documents providing instructions for continued airworthiness are provided via www.txtavsupport.com.
Available post-delivery:
Illustrated Parts Catalog — Engine
Maintenance Manual — Engine
Service Bulletins and Service Letters - Engine
Airframe Nondestructive Testing Manual
Service Bulletins and Service Letters
Airframe Structural Repair Manual
Wiring Diagram Manual
Some post-delivery documents are fee-based and are the Purchaser’s responsibility.
Seller will provide technical manual revisions for documents published by Seller for fi ve years beginning on the start date of airframe warranty.
Seller’s Documentation and Technical Publications include proprietary data which is to be used solely for direct maintenance and operation of the Aircraft. Any other use of Seller’s proprietary data requires a data license agreement to be separately negotiated. Using Seller’s proprietary data to modify the Aircraft is one example of when a separate data license agreement is required.
23 CITATION CJ3+ • JANUARY 2021 16. MAINTENANCE TRACKING PROGRAM
The Aircraft will deliver with an online computerized maintenance record service for one year from the date the Citation CJ3+ is delivered to the Purchaser. This service provides management and operations personnel with the reports necessary for the effi cient control of maintenance activities. The service provides an accurate and simple method for staying abreast of aircraft components inspections, service bulletins, and airworthiness directives while providing aircraft records of maintenance performed. On-demand reports show the current status, upcoming scheduled maintenance activity, and the historical aircraft maintenance. Semi-annual reports concerning projected annual maintenance requirements, component removal history, and fl eetwide component reliability are provided as part of the service. Services are provided through a secure Internet site and require a computer with Internet connectivity. A local printer is required to print paper versions of the online reports and documentation. 17. LIMITED WARRANTIES
The Seller’s Citation CJ3+ Limited Aircraft Warranty (Limited Aircraft Warranty) covers Textron Aviation manufactured Aircraft components, avionics, Vendor Items, Interior Furnishings, Paint and Customer Requests. The Aircraft engines are warranted by Williams International Co., L.L.C. The Limited Aircraft Warranty and summary of the Williams International Co., L.L.C. engine warranty are set out below.
17.1 Limited Aircraft Warranty
Periods The Seller warrants each new Citation CJ3+ Aircraft to be free from defects in material and workmanship for the following periods after delivery of the Aircraft to Purchaser.
(a) Five years or 5,000 operating hours, whichever occurs fi rst, for Aircraft components manufactured by Textron Aviation;
(b) Five years or 5,000 operating hours, whichever occurs fi rst, for Garmin Standard and Garmin Optional Avionics;
(c) Two years on standard and optional avionics;
(d) Three years or 1,800 hours, whichever occurs fi rst, for vendor items including actuators, ACMs, brakes, GCUs, oleos, starter generators, valves, windshields, and engine accessories supplied by the Seller, unless otherwise stated in the
CITATION CJ3+ • JANUARY 2021 24 Optional Equipment Selection Guide;
(e) One year for Interior Furnishings and Paint; and;
(f) One year for Customer Requests (CRQs).
Any remaining term of this Limited Aircraft Warranty automatically transfers to subsequent purchasers of the Aircraft.
Defi nitions
Support Facility means Textron Aviation Parts Distribution, Textron Aviation-owned service facilities and service facilities authorized by Textron Aviation to perform warranty service on the Aircraft.
Service Facility means Textron Aviation-owned service facilities and service facilities authorized by Textron Aviation to perform warranty service on the Aircraft.
Warranty Holder means Aircraft owner.
Seller’s Obligation
Parts Seller’s obligation under this Limited Aircraft Warranty is limited to repairing the defective part or replacing the defective part with an exchange part, in Seller’s sole discretion, when:
(a) the failure occurs within the applicable warranty period;
(b) all of the following occur within 30 days of failure for a U.S. Warranty Holder and 45 days of failure for an international Warranty Holder:
(i) a claim is made and a Textron Aviation Return Authorization is issued;
(ii) the part is returned at the Warranty’s Holders e x p e n s e t o t h e S u p p o r t Facility from where the replacement part is procured; and
(iii) the return part is accompanied by the Textron Aviation issued Return Authorization; and
(c) the Support Facility identifi es the part and determines the part is defective.
The Seller may refuse a warranty claim not submitted within the above time frame.
25 CITATION CJ3+ • JANUARY 2021 Replacement parts are only warranted for the remainder of the applicable, original Limited Aircraft Warranty period. In other words, a new warranty period is not established for replacement parts.
No Aircraft part or equipment will be regarded as breaching this Limited Aircraft Warranty merely because, subsequent to its delivery, some modifi cation or alternation becomes necessary for product improvements or in order to meet a change in the requirements of applicable Federal Aviation Regulations.
Service Service under this Limited Aircraft Warranty must be performed at a Service Facility. The Warranty Holder will not be charged for parts or labor covered by this Limited Aircraft Warranty. The location of Service Facilities is available on the Seller’s website.
Warranty Holder’s Responsibility
All freight, transportation expenses, import duties, customs brokerage fees, sales taxes and use taxes, if any, on warranty repairs or replacement parts are the Warranty Holder’s sole responsibility. The Warranty Holder is responsible for the cost of getting the Aircraft to and from a Service Facility.
Application
This Limited Aircraft Warranty applies to Aircraft operated under normal, conventional, non-military use. It applies only to the repair or replacement of defective parts that have been used, maintained and operated in accordance with the Federal Aviation regulations and the applicable manuals, bulletins, communications, or other written instructions of the Aircraft or component manufacturers.
Limitations
This Limited Aircraft Warranty does not apply to:
(a) normal maintenance services (such as engine adjustments, cleaning, control rigging, brake and other mechanical adjustments, and maintenance inspections);
(b) the replacement of service items (such as brakes, lights/bulbs, fi lters, de-ice boots, hoses, belts, tires, batteries, rubber-like items, fuel or lubricants);
(c) normal deterioration of appurtenances (such as paint, cabinetry and upholstery);
(d) damage due to wear, exposure, environmental elements and neglect;
CITATION CJ3+ • JANUARY 2021 26 (e) parts, components or systems that have been modifi ed or altered after delivery other than by the Aircraft manufacturer or in accordance with an alternation scheme approved in writing by Textron Aviation;
(f) items that have been subjected to misuse, abuse, negligence, accident, foreign object damage (FOD);
(g) items that have been installed, repaired, or altered by repair facilities not authorized by Textron Aviation;
(h) items that, in Textron Aviation’s sole discretion, have been installed, repaired, or altered by other than Textron Aviation-owned service facilities contrary to applicable manuals, bulletins and other written instructions provided by Textron Aviation so that the performance, stability, or reliability of such items are adversely aff ected;
(i) any part or system that has been modifi ed or altered by a third party at the Warranty Holder or its predecessor’s request and any part or system of the Aircraft aff ected by such modifi ed or altered part or system;
(j) vendor subscription services (including for items covered by the Limited Warranty), software (unless specifi cally provided otherwise) and databases (collectively “Services”), and patches, replacements, revisions, updates or upgrades thereto (collectively “Updates”) and any impairment to the Aircraft or its components caused by Services or Updates; and
(k) Warranty Holder or predecessor’s furnished equipment.
The warranty provided for life-limited parts is pro-rated. For Aircraft components, parts, or systems with life limitations Seller’s liability under this Limited Aircraft Warranty is limited to the remaining pro-rated life of the defective part, calculated as of the date the defect is discovered and reported to Seller and per additional terms administered by Textron Aviation’s Warranty Department. Nothing about this provision will be construed to extend the total warranty period beyond the applicable Periods set out above. All warranty Periods expires as noted above, regardless of any remaining life limits on parts.
WITH THE EXCEPTION OF THE WARRANTY OF TITLE AND TO THE EXTENT ALLOWED BY APPLICABLE LAW, THIS LIMITED AIRCRAFT WARRANTY IS EXPRESSLY IN LIEU OF ANY OTHER WARRANTIES, EXPRESSED OR IMPLIED, IN FACT OR BY LAW, APPLICABLE TO THE AIRCRAFT. THERE ARE NO WARRANTIES WHICH EXTEND BEYOND THE DESCRIPTION ON THE FACE HEREOF. SELLER SPECIFICALLY DISCLAIMS AND EXCLUDES ALL OTHER WARRANTIES, INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTY OF
27 CITATION CJ3+ • JANUARY 2021 MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. THE REMEDIES OF REPAIR OR REPLACEMENT OF THE DEFECTIVE PART(S) AS SET OUT HEREIN ARE THE ONLY REMEDIES UNDER THIS LIMITED AIRCRAFT WARRANTY. SELLER EXPRESSLY AND SPECIFICALLY DISCLAIMS ALL OTHER REMEDIES, OBLIGATIONS, AND LIABILITIES, INCLUDING, BUT NOT LIMITED TO, LOSS OF AIRCRAFT USE, LOSS OF TIME, INCONVENIENCE, COMMERCIAL LOSS, LOSS OF PROFITS, LOSS OF GOODWILL, DIMUNITION OF MARKET VALUE, AND ANY AND ALL OTHER CONSEQUENTIAL, INDIRECT, INCIDENTAL, SPECIAL, MULTIPLE OR PUNITIVE DAMAGES, OR ANY DAMAGES TO THE AIRCRAFT CLAIMED BY PURCHASER OR ANY OTHER PERSON OR ENTITY UPON THE THEORIES OF NEGLIGENCE OR STRICT LIABILITY IN TORT. SELLER NEITHER ASSUMES NOR AUTHORIZES ANYONE ELSE TO ASSUME ON ITS BEHALF ANY FURTHER OBLIGATIONS OR LIABILITY PERTAINING TO THE AIRCRAFT NOT CONTAINED IN THIS LIMITED AIRCRAFT WARRANTY.
THIS LIMITED AIRCRAFT WARRANTY WILL BE CONSTRUED UNDER THE LAWS OF THE STATE OF KANSAS AND ANY DISPUTES AND/OR CLAIMS ARISING THEREFROM WILL BE EXCLUSIVELY RESOLVED IN THE STATE AND/OR FEDERAL COURTS LOCATED IN WICHITA, KANSAS. THE PARTIES CONSENT TO PERSONAL JURISDICTION IN THE FORUM CHOSEN AND WAIVE THEIR RIGHT TO JURY TRIAL. ANY ACTION BY PURCHASER FOR BREACH OF THIS WARRANTY MUST BE COMMENCED WITHIN ONE (1) YEAR AFTER THE CAUSE OF ACTION ACCRUES. THE CAUSE OF ACTION ACCRUES WHEN THE PURCHASER FIRST LEARNS THAT THE WARRANTY HAS BEEN BREACHED.
17.2 Williams’ FJ44-3A Limited Engine Warranty
The Aircraft engines are warranted by Williams International Co., LLC. The following is provided for reference only. Please refer to offi cial Williams International Co., LLC warranty documentation. If there is an inconsistency between the information provided below and offi cial Williams International Co., LLC warranty documentation, the latter controls.
This limited warranty covers Williams International Co., LLC’s (Williams) FJ44-3A Engines, Spare Parts and Exchange Parts installed in Cessna aircraft which are sold for Commercial Business Jet use. Capitalized terms used throughout this warranty are defi ned in Section II hereof.
CITATION CJ3+ • JANUARY 2021 28 SECTION I: ALLOWANCES
1. ENGINE WARRANTY Williams warrants to the Owner or Operator that each new Engine sold for installation on Aircraft (as either original equipment or a Spare Part) will at the time of delivery be free from defects in material, workmanship and title. Warranty shall run to the original purchaser, its successors, assigns, and customers when they are the Owner or Operator. This warranty shall expire 36 months from the date of delivery to the original retail purchaser or First User or 1,500 Engine Operating Hours (EOH) prorated on a straight line basis to 2,000 EOH, whichever occurs fi rst. Williams will, at its option, during the warranty period: 1.1 Undertake Repair or replacement of an Engine, which in the sole discretion of Williams is found to have suff ered a Failure pursuant to the defi nition of “Failure” in Section II, Paragraph 3.4 of this warranty; 1.2 For engines which have 1,500 EOH or less, grant an allowance of 100 percent of the Price of Parts suff ering Failure or Resultant Damage (or at its option Repair or exchange such Parts free of charge) plus reasonable cost of labor used during Repair at Williams’ authorized Repair Facility; 1.3 For engines which have 1,500 to 2,000 EOH, grant an allowance of, based on a straight line basis, the Price of Parts suff ering Failure or Resultant Damage, or at its option, the Price to Repair or exchange such failed or damaged Parts. 2. SPARE PARTS AND EXCHANGE PARTS WARRANTY Williams warrants to the Owner or Operator that each new Spare Part or Exchange Part sold for installation in Engines will at the time of delivery be free from defects in material, workmanship and title. Warranty shall run to the original purchaser, its successors, assigns, and customers when they are the Owner or Operator. This warranty shall expire 36 months from the date of shipment from Williams or 12 months from the day of installation of the new Spare Part or Exchange Part in an Engine, whichever occurs fi rst. Williams will during this warranty period grant an allowance of 100 percent on the Price of the Spare Part or Exchange Part which, in the sole discretion of Williams is found to have suff ered a Failure or the Resultant Damage of a warranted Part or at its option Repair or exchange such Spare Part or Exchange Part free of charge. SECTION II: DEFINITIONS 3. In this warranty, the following defi nitions shall apply to the exclusion of all other meanings, and words in the plural shall have similar meanings:
29 CITATION CJ3+ • JANUARY 2021 3.1 “Commercial Use” means the operation of the Engines in aircraft licensed by FAA or its equivalent for general civilian and Commercial Use excluding aerial dusting and spraying and any other type of fl ying requiring special authorization or dispensation by FAA or its equivalent; 3.2 “Engine” means a Williams’ FJ44-3A Engine; 3.3 “Engine Operating Hours” means the total number of hours run by an Engine since new; 3.4 “Failure” means the breakdown or deterioration of a Part or Spare Part or Exchange Part which is established to the reasonable satisfaction of Williams to be due to a defect in material or workmanship in the manufacture of that Part or Spare Part or Exchange Part and which either: 3.4.1 Necessitates the removal of the Engine or Part or Spare Part or Exchange Part from the aircraft before the next scheduled shop visit of the Engine, or is discovered during a Repair performed in connection with such removal; or 3.4.2 Is discovered during a scheduled shop visit and necessitates the scrapping of the Part or Spare Part or Exchange Part because in the opinion of Williams, the Part or Spare Part or Exchange Part is beyond Repair in accordance with Repair instructions approved in writing by Williams. 3.5 “First User” means that individual, fi rm or agency eff ecting initial operation of the Engine, exclusive of operation incidental to production and initial distribution of the aircraft in which the Engine is installed. 3.6 “Operator” means that individual, fi rm or agency actually operating the Engine as Part of an Aircraft. 3.7 “Owner” means the Owner of the aircraft in which the Engine is installed who is registered with the Federal Aviation Agency (FAA) or its equivalent at the time of the warranty claim, or the legal Owner of the Engine. 3.8 “Part” means any Part manufactured or supplied by Williams, originally assembled into or attached to an Engine. “Spare Part” means any Part manufactured or supplied by Williams, not originally assembled into or attached to an Engine. “Exchange Part” means any Part or Spare Part which has been newly overhauled in accordance with 14 CFR Part 43. Where two or more Parts are permanently attached together by a manufacturing process, Part or Spare Part or Exchange Part means the minimum assembly listed in the Williams’ Illustrated Parts Catalog. 3.9 “Price” as used in 1, Engine Warranty, and 2, Spare Parts and Exchange Parts Warranty, of Section I, Allowances, means the net selling Price to the Operator (excluding import duties and sales or other taxes imposed in the Operator’s country), last published by Williams, prior to the time when the Failure is discovered.
CITATION CJ3+ • JANUARY 2021 30 3.10 “Repair” means the work comprising the tear down of one or more major assemblies which is required to render serviceable an Engine or Part or Spare Part or Exchange Part which has suff ered Failure, necessitating the removal of that Engine from the aircraft. 3.11 “Resultant Damage” means the damage suff ered by a Part, necessitating the scrapping of that Part because that Part is beyond economic Repair in accordance with Repair instructions approved in writing by Williams, provided such damage is caused by the Failure of another warranted Part. SECTION III: GOVERNING CONDITIONS 4. The obligations of Williams hereunder shall be subject to the following conditions: 4.1 The Operator shall present any claim to Williams in writing within 30 days after the date upon which the claim is discovered, shall keep and disclose accurate records of Engine operation and maintenance adequate to support such claims. Owner shall ship the failed Engine or Part for Repair or replacement within 30 days after notice; 4.2 Williams shall have no obligation under this Warranty in respect of any Engine, Part, Spare Part or Exchange Part which in the reasonable opinion of Williams: 4.2.1 Has not been properly installed, operated, and maintained in accordance with the recommendations of Williams, as contained in its manuals or other written instructions, including operating procedures; 4.2.2 Has been repaired or altered outside the authorized facilities of Williams; 4.2.3 Has been subject to misuse, negligence, accident; 4.2.4 Has suff ered damage due to the ingestion of a foreign body; or 4.2.5 Was acquired by the Operator other than from Williams, or through channels not specifi cally approved in writing by Williams. 4.3 Except as expressly stated in Section I, Allowances, hereof, Williams shall not be liable for any other expenses, taxes, duties or liabilities. In particular costs of removal or replacement from/in an aircraft and transportation costs to/from a Repair facility are excluded from Section I, Allowances. 4.4 The Operator shall notify a Williams’ Customer Support representative of a potential warranty problem prior to removing or shipping Engines pursuant to a warranty claim. The Operator shall make available as requested all Engines, Parts, Spare Parts and Exchange Parts for inspection and preliminary analysis relative to said claim.
31 CITATION CJ3+ • JANUARY 2021 4.5 Upon request of Williams, any Part, Spare Part or Exchange Part for which an allowance has been granted by Williams, hereunder, shall be returned by the Operator at Williams’ expense, and upon such return any such Part, Spare Part or Exchange Part shall become the property of Williams. 4.6 Duration of the warranty for Products replaced under the terms of this Warranty shall be for the unused portion of the new Engine warranty, Spare Part or Exchange Part warranty as applicable. Replacement of an Engine, Spare Part or Exchange Part does not commence a new warranty period. 4.7 Williams reserves the right to make changes in the design and to add improvements without incurring any obligation to incorporate the same on other Engines or Parts sold by Williams. 4.8 ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY, SUCH AS WARRANTIES OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE ARE HEREBY EXCLUDED AND DISCLAIMED TO THE EXTENT THEY EXCEED THE WARRANTIES GRANTED HEREIN. THIS WARRANTY COMPRISES WILLIAMS’ ENTIRE LIABILITY IN RELATION TO ANY MALFUNCTION, FAILURE OR DEFECT TO THE EXCLUSION OF ALL OTHER LIABILITY, IN TORT (WHETHER FOR NEGLIGENCE, PRODUCT LIABILITY OR OTHERWISE) OR IN CONTRACT, INCLUDING LIABILITY FOR CONSEQUENTIAL OR INCIDENTAL LOSS, DAMAGE OR EXPENSE. 4.9 NO AGREEMENT EXTENDING THIS WARRANTY SHALL BE BINDING UPON WILLIAMS, UNLESS IN WRITING AND SIGNED BY A DULY AUTHORIZED OFFICER OR REPRESENTATIVE OF WILLIAMS.
CITATION CJ3+ • JANUARY 2021 32 18. TRAINING AGREEMENT
The first retail Aircraft Purchaser will be provided training for one (1) Citation CJ3+ crew, subject to the following:
1. A crew consists of up to two (2) current private or commercial licensed pilots with instrument and multi-engine ratings and up to two (2) mechanics with an A&P license or equivalent experience (each hereinafter referred to as a “Trainee” or collectively as “Trainees”).
2. Training will be conducted by FlightSafety Textron Aviation Training LLC, Seller’s preferred training provider (or by Seller or another designated training organization, in Seller’s discretion), at the location designated by Seller. The organization providing training will be referred to as the “Trainer.”
3. Training will consist of the following:
a. Ground school training for each pilot Trainee and theoretical classroom instruction for each mechanic Trainee in accordance with the Trainer’s standards.
b. Except as set out below, pilot Trainees will be provided fl ight simulation training to simulator proficiency in accordance with the Trainer’s standards but not to exceed one (1) additional simulator session per pilot crew.
i. A simulator that is certifi ed will be used to provide training for the model CE-525 type rating and in lieu of a model specific simulator, training may be provided in the most appropriate type simulator available that is capable of accomplishing FAA type rating with diff erences training provided. In Seller’s sole discretion and in accordance with Seller’s terms (including Purchaser’s cost), alternate pilot training may be provided if warranted by extraordinary circumstances.
4. Purchaser will be responsible for:
a. The cost of any additional training which would be provided under terms and conditions established by the Trainer or Seller;
b. Transportation of the Trainees to and from the training site and for all living expenses associated with the training;
c. Providing an interpreter during the course of training for any of the Trainees not conversant in the English language;
d. Extra charges, if any, for scheduling pilot Trainees in separate training classes;
33 CITATION CJ3+ • JANUARY 2021 e. Reimbursing Seller at the retail rate for training provided if the Aircraft to be purchased by Purchaser does not deliver to Purchaser; and
f. Ensuring compliance with TSA regulations including requirements that all current United States citizens present a current United States passport before training can start.
5. All training furnished under this Training Agreement will be scheduled to commence no earlier than three (3) months prior to Aircraft delivery and must be completed within twenty-four (24) months after the earlier of (a) Aircraft delivery or (b) commencement of the fi rst training event for the Aircraft.
6. Seller or Trainer will schedule all training, furnish Purchaser training schedules and endeavor to schedule training at a time convenient for Purchaser. A rescheduling fee of fi ve percent (5%) of the retail price of training a Trainee was scheduled to attend will be paid to Seller by Purchaser within thirty (30) days of the date of Seller’s invoice if a Trainee fails to appear for scheduled training, except for reasons beyond the Trainee’s control, unless Purchaser gives Seller written notice of cancellation received at least twenty-one (21) days prior to the scheduled training. For avoidance of doubt, this rescheduling fee applies to each Trainee who fails to attend training as scheduled and the exceptions to the rescheduling fee do not apply.
7. Neither Seller nor Trainer will be responsible for any delay in providing training.
8. Neither Seller nor Trainer will be responsible for the competency of any Trainee during and after training. Trainer will make the same eff orts to qualify each Trainee as it makes in training other trainees; however, neither Seller nor Trainer can guarantee that any Trainee will qualify for any license, certificate or rating.
9. This Training Agreement is part of the Specification and Description and thus part of the Aircraft Purchase Agreement. Purchaser’s execution of the Aircraft Purchase Agreement constitutes Purchaser’s acceptance of the foregoing terms and conditions of the Training Agreement and Purchaser’s agreement that Seller can provide Purchaser’s name, address, the name and address of each Trainee and other relevant information to the Trainer for purposes of scheduling training.
CITATION CJ3+ • JANUARY 2021 34 U.S. +1.844.44.TXTAV | INTERNATIONAL +1.316.517.8270 | TXTAV.COM
© 2021 Textron Aviation Inc. All rights reserved. Product names, company names, trademarks, service marks, trade names, trademark designs and logos of Textron Aviation Inc. or its subsidiaries (collectively “Marks”), whether or not appearing in large print, italics, or with trade marking symbols, are Marks of Textron Aviation Inc. or an affi liate and may be registered in the United States. Third party marks whether or not appearing in large print, italics, or with trade marking symbols are marks of others.
January 2021 SD-JET-525B-0121