CITATION LATITUDE
SPECIFICATION AND DESCRIPTION
REVISION H FEBRUARY 2021 SERIAL NUMBER 680A0260 TO TBD SPECIFICATION AND DESCRIPTION
CITATION LATITUDE SERIAL NUMBER 680A0260 TO TBD FEBRUARY 2021 REVISION H 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 8.2 Auxiliary Power Unit (APU) ...... 9 9. SYSTEMS ...... 9 9.1 Flight Controls ...... 9 9.2 Fuel System ...... 9 9.3 Electrical System ...... 10 9.4 Exterior Lighting System ...... 10 9.4.1 Primary ...... 10 9.4.2 Secondary ...... 10 9.5 Pressurization and Environmental System ...... 11
i CITATION LATITUDE • FEBRUARY 2021 TABLE OF CONTENTS CONT
9.6 Oxygen System ...... 11 9.7 Anti-Icing System and Rain Removal ...... 11 9.7.1 Ice ...... 11 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 Multi-Function Display (MFD) ...... 14 10.3.2 Garmin Touchscreen Control Panels (GTC) ...... 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 Data Satellite Transceiver (Iridium) ...... 15 10.3.5 Cockpit Voice Recorder (CVR) ...... 16 10.3.6 Flight Management System (FMS) ...... 16 10.3.7 Electronic Charts and Maps ...... 16 10.3.8 Distance Measuring Equipment (DME) ...... 17 10.3.9 Engine Indicating System (EIS) ...... 17 10.3.10 Crew Alerting System (CAS) ...... 17 10.3.11 Flight Guidance System (FGS)...... 17 10.3.12 Attitude/Heading Reference System (AHRS) ...... 18 10.3.13 Transponders with ADS-B Out and ADS-B In Capability ...... 18 10.3.14 Weather Radar ...... 18 10.3.15 Radio Altimeter ...... 18 10.3.16 Traffi c Collision Avoidance System (TCAS II) ...... 18 10.3.17 Terrain Awareness and Warning System (TAWS) ...... 18
CITATION LATITUDE • FEBRUARY 2021 ii TABLE OF CONTENTS CONT
10.3.18 Synthetic Vision Technology (SVT) ...... 18 10.3.19 Emergency Locator Transmitter (ELT) ...... 19 10.3.20 Standby Instrumentation ...... 19 10.3.21 Maintenance Diagnostics ...... 19 11. INTERIOR ...... 20 11.1 Cabin ...... 20 11.2 Entertainment System ...... 21 11.3 Windows ...... 21 11.4 Cabin Lighting System ...... 22 11.4.1 Direct Lighting ...... 22 11.4.2 Indirect Lighting ...... 22 11.4.3 Emergency Lighting ...... 22 12. EXTERIOR ...... 22 12.1 Exterior Storage ...... 22 13. LOOSE EQUIPMENT ...... 23 14. EMERGENCY EQUIPMENT ...... 24 15. DOCUMENTATION AND TECHNICAL PUBLICATIONS ...... 24 16. MAINTENANCE TRACKING PROGRAM ...... 26 17. LIMITED WARRANTIES ...... 26 17.1 Limited Aircraft Warranty ...... 26 17.2 Summary of P&WC’s New Engine Warranty ...... 30 17.3 Summary of Honeywell APU Warranty ...... 35 18. TRAINING AGREEMENT ...... 39
iii CITATION LATITUDE • FEBRUARY 2021 LIST OF FIGURES
Figure 1: Exterior Dimensions ...... 3 Figure 2: Interior Dimensions ...... 4 Figure 3: Instrumentation ...... 13 Figure 4: Cabin Typical Confi guration ...... 20
CITATION LATITUDE • FEBRUARY 2021 iv INTRODUCTION
This Specifi cation and Description provides general information about the design, performance, and standard equipment of the Citation Latitude (Model 680A), Serial Number 680A0260 to TBD (hereinafter “Citation Latitude” 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 E-Mail: [email protected]
1 CITATION LATITUDE • FEBRUARY 2021 THE AIRCRAFT 1. GENERAL DESCRIPTION
The Citation Latitude is a transcontinental low-wing business jet. The Aircraft has provisions for 7-9 passengers (nine is standard) and is certifi ed for a crew of two. The Citation Latitude has internal and external storage compartments for personal items, baggage, and cargo.
Pratt & Whitney Canada (P&WC) PW306D1 engines power the Citation Latitude, and a fully integrated Garmin G5000 digital avionics suite provides pilots with state-of- the-art touchscreen controls.
1.1 Certifi cation
The Citation Latitude is certifi ed in accordance with U.S. 14 CFR Part 25, Transport Category, including day, night, VFR, IFR, and fl ight into known icing conditions. The Citation Latitude 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 LATITUDE • FEBRUARY 2021 2 EXTERIOR DIMENSIONS
72 ft 4 in (22.05 m)
27 ft 7 in (8.41 m)
10 ft 0 in (3.05 m)
20 ft 11 in (6.38 m)
27 ft 0 in (8.23 m)
62 ft 3 in (18.97 m)
Figure 1: Exterior Dimensions
3 CITATION LATITUDE • FEBRUARY 2021 INTERIOR DIMENSIONS
76 in 207 in 54 in (1.93 m) (5.26 m) (1.37 m)
77 in (1.96 m)
20 in (0.51 m) 17 in (0.43 m)
65 in 36 in (1.65 m) (.91 m) 13 in (0.33 m)
31 in (0.79 m)
72 in (1.83 m)
Figure 2: Interior Dimensions
CITATION LATITUDE • FEBRUARY 2021 4 1.3 Approximate Dimensions OVERALL HEIGHT 20 ft 11 in (6.38 m) OVERALL WIDTH 72 ft 4 in (22.05 m) OVERALL LENGTH 62 ft 3 in (18.97 m) WHEELBASE 27 ft 0 in (8.23 m)
SPAN AREA SWEEP WING (overall) (at 25% chord) 72 ft 4 in (22.05 m) 542.5 ft2 (50.40 m2 ) 12.7o SPAN AREA SWEEP HORIZONTAL TAIL (overall) (at 25% chord) 27 ft 7 in (8.41 m) 138.5 ft2 (12.87 m2 ) 22.6o HEIGHT AREA SWEEP VERTICAL TAIL (at 25% chord) 10 ft 11 in (3.33 m) 95.3 ft2 (8.85 m2 ) 37.7o HEIGHT LENGTH* WIDTH (max) (max) CABIN INTERIOR 6 ft 0 in (1.83 m) 28 ft 1 in (8.56 m) 6 ft 5 in (1.96 m) (with typical interior) LENGTH** 21 ft 9 in (6.63 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 31,050 lb (14,084 kg) MAXIMUM TAKEOFF WEIGHT 30,800 lb (13,971 kg) MAXIMUM LANDING WEIGHT 27,575 lb (12,508 kg) MAXIMUM ZERO FUEL WEIGHT 21,430 lb (9,720 kg) BASIC OPERATING WEIGHT (2 crew, 200 lb each, typically equipped) 18,656 lb (8,462 kg) FUEL CAPACITY (usable at 6.7 lb/gal) 11,394 lb (5,168 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 LATITUDE • FEBRUARY 2021 2. PERFORMANCE CONT TAKEOFF FIELD LENGTH 3,580 ft (1,091 m) (Maximum Takeoff Weight, Flaps Position 2, Sea Level, ISA) MAXIMUM CERTIFIED ALTITUDE 45,000 ft (13,716 m)
MAXIMUM CRUISE SPEED (+/- 3%) 446 KTAS (826 km/hr) (35,000 feet {10,668 m} altitude; mid cruise weight; high speed cruise) MAXIMUM FERRY RANGE (+/- 4%) 2,850 nm ( 5,278 km) (Two crew, no payload, long range cruise, NBAA IFR reserves with 200 nm alternate) NBAA IFR RANGE (+/- 4%) 2,700 nm (5,000 km) (Four passengers, HSC, 200 nm alternate) LANDING DISTANCE 2,480 ft (756 m) (Maximum Landing Weight, Full Flaps) 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 73.5 EPNdB Lateral 87.7 EPNdB Approach 87.7 EPNdB 3. DESIGN LIMITS
DESIGN LOAD LIMITS Flaps UP -1.00 to +2.75G Flaps 1, 2, or FULL -0.00 to +2.00G OPERATING LIMIT SPEEDS
VMO (8,000 ft {2,438 m} to 29,833 feet {9,093 m}) 305 KIAS (565 km/hr)
MMO (above 29,833 feet {9,093m}) Mach 0.80 (indicated) FLAP LIMIT SPEEDS Maximum Flap Extended Speed
VFE (Flaps 1) 250 KIAS (463 km/hr)
VFE (Flaps 2) 200 KIAS (370 km/hr)
VFE (Flaps FULL) 175 KIAS (324 km/hr) LANDING GEAR LIMIT SPEEDS
VLO 210 KIAS (389 km/hr)
VLE 210 KIAS (389 km/hr) SPEED BRAKES
VSB No Limit
CITATION LATITUDE • FEBRUARY 2021 6 4. FUSELAGE
4.1 Design and Construction
The Citation Latitude incorporates a circular fuselage of metallic construction with a pressurized cabin. A fl at fl oor from just behind the cockpit through the lavatory provides stand-up access throughout the cabin.
4.2 Nose Section
The nose section has a contoured radome. The all-glass windshields meet bird resistance requirements of U.S. 14 CFR Part 25; they are electrically heated and defogged.
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 servicing ports for the hydraulic system and externally serviceable toilet.
5. WING
This Aircraft features a moderately swept wing.
Three Fowler-type fl aps and fi ve hydraulically actuated spoilers are incorporated into each wing. The design of the spoilers allow for drag and roll control with minimum pitching moment. Also included are mechanically actuated ailerons.
The Citation Latitude winglets improve performance. 6. EMPENNAGE
The empennage features a cruciform tail with movable horizontal stabilizer for trim. Elevators and rudder are mechanically actuated.
7 CITATION LATITUDE • FEBRUARY 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 dual wheels and tires. A hydraulic power steering system provides nosewheel steering.
7.3 Brakes and Tires
The multi-disc, anti-skid carbon brake system is powered by the main hydraulic system. Emergency braking is through a pneumatic back-up system.
The Citation Latitude is equipped with dual wheels and tires (six tires; two nose gear and two each left and right main).
PLY MAX SPEED RATING SIZE NOSE GEAR TIRES 10 210 mph (338 km/hr) 16” x 4.4R8” MAIN TIRES 14 210 mph (338 km/hr) 26” x 6.6R14” 8. PROPULSION
8.1 Powerplant
The Aircraft is powered by two P&WC PW306D1 engines installed on the aft fuselage. The PW306D1 engines incorporate dual channel Full Authority Digital Electronic Controls (FADEC) and are fully compatible with the Autothrottle (A/T) system.
The A/T is fully integrated with the Automatic Flight Control System (AFCS) and Flight Management Systems (FMS). The A/T controls engine thrust and includes speed and thrust modes. The A/T may be selected prior to initiating takeoff roll and remain engaged throughout the fl ight, approach, fl are, and landing touchdown (Aircraft does not incorporate autoland capability). The A/T may be disengaged for manual throttle control.
CITATION LATITUDE • FEBRUARY 2021 8 Each engine features electric start as well as access panels for Line Replacement Unit (LRU) maintenance and multiple borescope inspection ports.
Hydraulically actuated, target-type thrust reversers compatible with the engine nacelles and powerplants are included.
TAKEOFF THRUST (at sea level) 5,907 lbs (26.28 kN) FLAT RATED TO 89.6o F (32oC) Time Between Overhaul 6,000 hours
8.2 Auxiliary Power Unit (APU)
Certifi ed for in-fl ight use up to 30,000 feet, the Honeywell APU provides electrical power and bleed air. The APU, which is located in the tailcone stinger for easy maintenance, can also be operated on the ground. 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 electric trim, hydraulically actuated roll spoilers and three electrically operated Fowler-type fl ap panels per side. The spoilers are of composite construction, all other control surfaces are of aluminum construction. A single yaw damper system improves ride quality 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 tank. 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, APU start, crossfeed, and as needed to supply the required fuel pressure.
9 CITATION LATITUDE • FEBRUARY 2021 Both single point refueling and defueling, located in the fairing near the leading edge of the right wing, can be operated without powering the Aircraft. The Citation Latitude is certifi ed for a wide range of jet fuels.
9.3 Electrical System
The split-bus electrical system is powered by two engine-driven, 300 amp, starter/ generators. A third starter/generator, limited to 275 amps is driven by the APU when the APU is operating. The Aircraft’s main batteries are two 44-amp hour Nickel-Cadmium batteries, which are located in access panels on each side of the fuselage behind the wing.
An engine-driven Alternating Current (AC) system aids in de-icing and defogging the windshield. In the unlikely event of dual generator loss, the alternators can also provide backup electrical power through transformer-rectifi er units to the emergency bus. The emergency bus can power components of the G5000 system that are essential for fl ight, including two display units and the Flight Director functionality. The emergency bus design and its multiple power sources provide greater reliability and situational awareness in the event of an electrical emergency. If all engine-driven power sources are lost, the Aircraft main batteries provide power to the emergency bus for a limited period of time.
9.4 Exterior Lighting System
9.4.1 Primary Standard exterior lighting consists of pulsing red LED lights for ground recognition, LED anti-collision lights, LED position lights, landing/recognition lights (including the Pulse Light system which, when activated, pulses the landing/recognition lights), windshield ice detection lights, and taxi lights (located on the nose landing gear).
9.4.2 Secondary The Citation Latitude has two wing inspection lights, two down wash lights mounted on the lower leading edge of the wingtips, one over wing emergency light mounted on the RH fairing, and two LED tail logo/fl ood lights mounted on the upper engine pylons.
CITATION LATITUDE • FEBRUARY 2021 10 9.5 Pressurization and Environmental System
Bleed air from each engine supplies cabin pressurization through a digital controller. Cabin pressure and cabin rate of climb are displayed on the Multi- Function Display. Separate cockpit and cabin temperature controls are provided. Also, the cabin temperature can be controlled through the wireless cabin management system application or from the master control panel location at the refreshment center.
CABIN PRESSURIZATION* Nominal Pressurization Diff erential 9.66 PSID Cabin Altitude at Aircraft’s Certifi ed Ceiling 5,950 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 Multi-Function 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, horizontal stabilizer leading edge, and engine inlets are heated by bleed air. Electric heat is used to remove ice from the windshield, pitot/static system, and Angle of Attack (AOA) systems.
9.7.2 Rain The windshield has a hydrophobic coating that repels rain water.
9.8 Hydraulic System
The hydraulic system employs pressure to operate the landing gear, brakes, nose wheel steering, spoilers, and thrust reversers. The main hydraulic system is engine driven while an electrical auxiliary pump provides a backup source of pressure. The hydraulic system maintains a continuous pressure of approximately 3,000 psi (206.8 bar).
11 CITATION LATITUDE • FEBRUARY 2021 10. FLIGHT COMPARTMENT
10.1 General
The Garmin G5000 system is the featured avionics suite on the Citation Latitude. Four full-color, touchscreen control panels are used by the crew to manipulate G5000 system features.
Two complete crew stations are furnished with dual controls, including control columns (with stick shaker), 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. A storage case is fi tted behind the seat on the RH side of cockpit area. Two USB charging ports are provided in the cockpit.
The oxygen system provides two pressure demand masks with microphones for the crew members. The oxygen masks are stored in the lower sidewall and circuit breaker panels are located on both the pilot’s and co-pilot’s sidewalls.
LED illuminated panels, instrument fl oodlights, push button switches, overhead map lights, and blue-white background lighting are standard in the fl ight compartment.
CITATION LATITUDE • FEBRUARY 2021 12 10.2 Instrumentation
7 9 5 3 4 2
1
6
12 10 14 11 13 8
Figure 3: Instrumentation 1. Touchscreen LCD Control Panel 8. Pressurization and Environmental Control Panel 2. Primary Flight Display (PFD) 9. Flight Guidance Panel - FGP 3. Secondary PFD Controller 10. LH Tilt Panel 4. Master Caution and Master Warning 11. RH Tilt Panel Annunciations 5. Multi-Function Display (MFD) 12. Engine Throttle Levers with Thrust Reverser and Autothrottle Controls 6. Dual Touchscreen LCD Control Panels 13. Flaps Control 7. Electronic Standby Flight Display - ESFD 14. Speed Brake and Spoiler Control
13 CITATION LATITUDE • FEBRUARY 2021 10.3 Avionics
The Garmin G5000 integrated 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, Air Data 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 Multi-Function 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 Multi-Function Display (MFD)
The MFD, which is located in the center panel, displays a detailed moving map, aircraft system synoptic diagrams, 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 Flight 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 LATITUDE • FEBRUARY 2021 14 10.3.2 Garmin Touchscreen Control Panels (GTC) Four full-color touchscreen LCD control panels are used to manipulate G5000 system features such as radio tuning, transponders, intercom, fl ight planning, and 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 panels can take on additional control responsibility.
10.3.3 Garmin Integrated Avionics Unit (GIA) Dual Integrated Avionics Units include the Global Positioning System, Wide Area Augmentation System (WAAS) receivers, Very High Frequency (VHF) communication radios, VHF navigation radios, and glide slope receivers. In addition the GIA supports input-output processing, aural alert generation, and Dual Flight Director functions.
10.3.3.1 Global Positioning System (GPS)
The G5000 system includes dual GPS with WAAS/LPV receivers as part of the GIA. 10.3.3.2 Very High Frequency Radio (VHF)
The G5000 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 G5000 system includes two standard VHF navigation radios as part of the GIA. 10.3.4 Cockpit Voice Data Satellite Transceiver (Iridium) The Citation Latitude is equipped with a single-channel Garmin Iridium SatCom system that enables voice calling capability via crew headsets as well as specifi c cockpit data communications.
Available services include request/response-based Garmin Connext Worldwide Weather with graphical and text weather services (where available); in-fl ight text messaging, and transmission of specifi c diagnostics data to ground-based maintenance/support operations, enabling remote support prior to landing.
Seller will cover costs associated with aircraft diagnostics data transmission through the Iridium SatCom system (GSR56) for an introductory period of two years from the date of delivery of a new Citation Latitude.
Subscription/data charges for other services associated with the Iridium SatCom system still apply and are the Purchaser’s responsibility.
15 CITATION LATITUDE • FEBRUARY 2021 10.3.5 Cockpit Voice Recorder (CVR) A Cockpit Voice Recorder (CVR) is included with the Aircraft. The CVR also records Controller-Pilot Data Link Communications when equipped with an applicable data link system and meets FAA and EASA requirements for datalink recording.
10.3.6 Flight Management System (FMS) A dual Flight Management System (FMS) is fully integrated into the Garmin G5000 system. Each FMS provides navigation and fl ight planning capabilities as well as enroute, take off , 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 • Takeoff and Landing Data (TOLD)—Computes Vspeeds based on Aircraft confi guration, loading, and runway conditions • Enroute and terminal operations • Precision and non-precision approach operations including LNAV/VNAV and Localizer Performance with Vertical Guidance (LPV) approaches • Navigational Operations including NAT, 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.
10.3.7 Electronic Charts and Maps The Electronic Charts function allows the crew to view ChartView electronic charts on the Garmin Display Units (GDU), customizable to either the PFDs or MFD. The ChartView database is available by subscription from Jeppesen, Inc. and is updated on a 14-day cycle.
Applicable subscription services are the Purchaser’s responsibility.
CITATION LATITUDE • FEBRUARY 2021 16 10.3.8 Distance Measuring Equipment (DME) There are two standard Collins Aerospace DME-4000 units integrated into the Garmin G5000 system. These dual scanning units provide DME information to the pilots and provide scanning DME/DME input capability for the Flight Management System.
10.3.9 Engine Indicating System (EIS) The Engine Indicating System (EIS) displays electrical, fuel, engine, pressurization, and fl ight control information on the left side of the MFD.
10.3.10 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.
10.3.11 Flight Guidance System (FGS) The Automatic Flight Control System (AFCS) is part of the Garmin G5000 avionics suite. 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, 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.
• Autothrottle—The Autothrottle commands thrust levers to achieve selected airspeed and sets the thrust levers based on phase of fl ight and Flight Director modes, and prevents the aircraft from entering an underspeed or overspeed condition.
17 CITATION LATITUDE • FEBRUARY 2021 10.3.12 Attitude/Heading Reference System (AHRS) Two Litef LCR-100 gyrocompassing 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.
10.3.13 Transponders with ADS-B Out and ADS-B In Capability The G5000 system includes two standard Garmin GTX 3000 transponders. The transponders are controlled by the fl ight crew via the GTCs. ADS-B Out and ADS-B In capability is standard.
10.3.14 Weather Radar Weather radar information is provided via the Garmin GWX processor which includes a 14-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.
10.3.15 Radio Altimeter The G5000 system includes one standard Garmin GRA 5500 radar altimeter unit that supplies information to the Traffi c Collision Avoidance System (TCAS) and the Terrain Awareness Warning System (TAWS).
10.3.16 Traffi c Collision Avoidance System (TCAS II) 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.
10.3.17 Terrain Awareness and Warning System (TAWS) The G5000 system includes a Class A 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.
Reactive windshear alerting capability is included.
10.3.18 Synthetic Vision Technology (SVT) Garmin Synthetic Vision Technology (SVT) is included. The system presents terrain and obstacle information on the PFDs in a dynamic, three-dimensional format, providing for increased situational awareness. Airports, runways, heading, traffi c, color-coded terrain alerts, and a fl ight path indicator display through the SVT.
CITATION LATITUDE • FEBRUARY 2021 18 10.3.19 Emergency Locator Transmitter (ELT) An Artex 406 MHz Emergency Locator Transmitter (ELT) with navigation interface is standard.
Note: Some authorities may not permit the use of navigation interface capability.
10.3.20 Standby Instrumentation An Electronic Standby Flight Display (ESFD), powered by the emergency bus and having its own backup battery, provides standby airspeed, heading, attitude, altitude, and VOR/ILS navigation information.
10.3.21 Maintenance Diagnostics The G5000 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 25+ 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.
19 CITATION LATITUDE • FEBRUARY 2021 11. INTERIOR
11.1 Cabin
There is one main cabin door with integral air stairs thatat is electrically operated. The cabin is separated from the fl ight compartment by curtains. The cabin extends from the fl ight compartment divider to the aft pressure bulkhead. The fl at fl oor extends aft from the cockpit divider to the aft wall of the lavatory and provides a cabin height of 72 inches (1.83 m). An emergency exit hatch is located in the lavatory on the right hand side.
The cabin is sized to off er passenger comfort and fl exibility for a variety of interior arrangements. The typical arrangement is a nine passenger, single club seating arrangement with a forward dual side facing couch just aft of the right hand forward cabinet and a belted side facing seat located in the lavatory. Optionalal seating arrangements are available.
The following are included in the typical arrangement:
• A left-hand refreshment center with hot and cold beverage capability, large ice drawer, numerous storage areas, large trash receptacle, glassware storage capability, and provisions for catering;
• A right-hand cabinet, forward of the cabin entry door, provides storage for the navigation chart, fl ightt manual, briefcase, and general storage;
• Six fully-adjustable, pedestal-mounted passenger seats with extendable headrests. All passenger seatsts adjust fore and aft, track laterally into the aisle for additional space, recline fully (berthable), and swivell 180-degrees. Each seat is equipped with a seat beltt and an over-water life vest stored in the seat; Figure 4: Cabin Typical Confi guration • Four fold out tables with ample work area are included. Side ledges have multipurpose areas for cups and personal electronic devices;
• The cabin management system includes one iPad
CITATION LATITUDE • FEBRUARY 2021 20 with the cabin management system application installed, which can also be installed on personal devices. This application provides passengers with VIP controls for audio, video, moving map entertainment, cabin temperature, and lighting. The VIP functions are also available in a master switch panel at the refreshment center;
• Four individual 115V AC outlets, twelve USB charging ports (two at each pedestal seat);
• The aft lavatory, with fl ushing toilet (non-belted), has sliding privacy doors and is externally serviceable. There is a belted seat on the left hand side of the lavatory that off ers an additional passenger seat. The large vanity provides temperature- controlled water and numerous storage compartments;
• A large aft lavatory storage closet accommodates hanging clothes, coats, briefcases, or additional storage for passenger amenities.
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 Entertainment System
The cabin entertainment system comes standard with a digital media server and a video monitor located in the forward cabin. The media server can store audio and video. A moving map can be viewed on the cabin monitor or on any Personal Electronic Device (PED) connected to the wireless access point. A wireless cabin management app is available for Apple and Android devices. Two high-power USB data/charging ports are available at each of the six forward and aft facing passenger seats.
11.3 Windows
Ten cabin windows are equipped with dual-mode, pleated window shades.
21 CITATION LATITUDE • FEBRUARY 2021 11.4 Cabin Lighting System
11.4.1 Direct Lighting General LED lighting and aisle LED lighting with variable adjustment settings, entrance, and emergency exit lights are located in the passenger cabin. There are several controls available for the lighting: (1) a touch switch control, mounted in the side ledge by each passenger seat, (2) an on/off control in the wireless cabin management system, and (3) the master switch panel mounted on the refreshment center.
11.4.2 Indirect Lighting Cabin-length indirect LED lighting is provided overhead in the Passenger Service Units (PSU) with variable adjustment settings and can be controlled via the wireless cabin management system or the master switch panel mounted on the refreshment center.
11.4.3 Emergency Lighting Emergency Exit Lighting (in the cabin and over the wing) runs via the Emergency Lighting Battery Pack in the 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.
12.1 Exterior Storage
An exterior baggage compartment located in the aft fuselage off ers external storage. The large baggage area is accessible through a lockable door with an integral step located on the left hand side of the fuselage and features a 1,000 lb capacity with a coat rod.
WEIGHT VOLUME EXTERNAL BAGGAGE AREA* 1,000 lb (454 kg) 100 ft3 (2.83 m3 ) 104 in (2.6 m) L x 37 in (.94 m) W x 47 in (1.19 m) H
*The external baggage area is tapered and dimensions listed are maximums.
CITATION LATITUDE • FEBRUARY 2021 22 13. LOOSE EQUIPMENT
Aircraft Keys (10)
Baggage Tie-Down Straps (12)
Cabin Door Pull Strap (1)
Cargo Net (1)
Coat Hangers (11)
Coat Rod (1)
Crew Noise-Canceling Headsets (2)
Engine Cover Set (1)
Fuel Cap Keys (4)
Garmin G5000 Software Set
Jack Pads (3)
Leather Cleaning Kit (1)
Leather Hand Rail Cover (1)
Maintenance Locks (2)
Passenger Briefi ng Cards (10)
Pitot Cover Set (1)
Service Locks (2)
Static Wick Protectors (10)
Thrust Reverser Placards (1)
23 CITATION LATITUDE • FEBRUARY 2021 14. EMERGENCY EQUIPMENT
Emergency Blankets (1 Per Seat)
Fire Extinguishers (2)
First Aid Kit (1)
Flashlights (2)
Individual Life Vest (1 per seat) 15. DOCUMENTATION AND TECHNICAL PUBLICATIONS
The following will be provided to Purchaser.
Print material:
Airplane Flight Manual which includes the Weight and Balance Manual and 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
Available via online subscription at https://ww2.txtav.com.
Component Maintenance Manual
Illustrated Parts Catalog — Airframe
CITATION LATITUDE • FEBRUARY 2021 24 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 at ww2.txtav.com. Registration at www.txtavsupport.com is required.
Available post-delivery:
APU Manual
Illustrated Parts Catalog - Engine
Maintenance Manual - Engine
Service Bulletins and Service Letters — Engine
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.
25 CITATION LATITUDE • FEBRUARY 2021 16. MAINTENANCE TRACKING PROGRAM
The Aircraft will deliver with an online computerized maintenance record service for one year from the date the Citation Latitude 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 eet- wide 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 Latitude 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 Pratt and Whitney Canada (P&WC). The auxiliary power unit (APU) is warranted by Honeywell. The Limited Aircraft Warranty and summaries of P&WC’s engine and Honeywell’s APU warranties are set out below.
17.1 Limited Aircraft Warranty
Periods The Seller warrants each new Citation Latitude 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 hardware;
(c) Five years or 3,000 hours, whichever occurs fi rst, for Vendor Items including
CITATION LATITUDE • FEBRUARY 2021 26 other standard and optional avionics, actuators, ACMs, brakes, GCUs, oleos, starter generators, valves, windshields and engine accessories supplied by the Seller, unless otherwise stated in the Optional Equipment Selection Guide;
(d) Two years for Interior Furnishings and Paint; and
(e) 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.
27 CITATION LATITUDE • FEBRUARY 2021 The Seller may refuse a warranty claim not submitted within the above time frame.
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);
CITATION LATITUDE • FEBRUARY 2021 28 (d) damage due to wear, exposure, environmental elements, and neglect;
(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 Aircraft Warranty), software 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
29 CITATION LATITUDE • FEBRUARY 2021 HEREOF. SELLER SPECIFICALLY DISCLAIMS AND EXCLUDES ALL OTHER WARRANTIES, INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTY OF 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 Summary of P&WC’s New Engine Warranty
The Aircraft engines are warranted by P&WC.
The following is a summary of the P&WC warranty for new PW306C, PW306D and PW306D1 Series Turbofan Engines. Please refer to P&WC warranty documentation for complete terms and conditions. If there is an inconsistency between the summary provided herein and complete P&WC warranty documentation, the latter controls.
P&WC warrants that the new Engine will be free from defects in material or manufacturing workmanship and is covered for 3000 engine operating hours or 5 years from shipment of the Engine from P&WC’s facilities whichever occurs fi rst during which time P&WC will:
CITATION LATITUDE • FEBRUARY 2021 30 at its option, repair or replace any Engine parts found to be defective including resultant damage to the Engine. Replacement parts may be new or serviceable. When P&WC supplies a replacement part, or issues credit towards the acquisition of a new part, the removed part becomes the property of P&WC.
pay reasonable removal and reinstallation labour for the Engine and reasonable transportation charges (excluding insurance, duties, brokerage fees, and taxes) to and from the facility designated by P&WC Warranty Administration.
Following the expiration of the Basic Coverage Period, P&WC off ers the Primary Parts Service Policy (“PPSP”) and the Extended Engine Service Policy (“EESP”), which it may cancel or change at any time. P&WC may also provide other commercial support, all in accordance with P&WC terms and further set out in P&WC documentation.
What is not covered
Costs of normal scheduled maintenance services
routine line maintenance and adjustment costs;
Hot Section Inspection (HSI) and refurbishment costs;
Engine overhaul or major refurbishment costs; and
any other costs related to Engine maintenance not specifi cally covered under the Policy.
Normal deterioration
normal wear and tear and deterioration (note: a worn part capable of continued operation which, because it has been accessed, must be restored using repair schemes fully described in the applicable P&WC Engine Maintenance and Overhaul Manuals, is considered normal); and
no warranty coverage is provided for the overhaul life of assemblies, service life limits of parts, and/or operating limits.
Unsupported parts
P&WC reserves the right to exclude Policy coverage (i) for the following parts, and (ii) for subsequent Engine repairs or damages directly attributable to the use of the following parts which:
31 CITATION LATITUDE • FEBRUARY 2021 are not originally supplied by P&WC or its authorized distributors and accompanied by the P&WC Manufacturer’s Release Certifi cate or Canadian Department of Transport Certifi cate of Airworthiness, as applicable; or
are not identifi ed in the applicable P&WC Illustrated Parts Catalogue (“IPC”) and accompanied by the Supplier’s Release Certifi cate; or
are not repaired in accordance with P&WC approved repair processes; or
are not traceable, e.g. insuffi cient supporting documentation; or
have been involved in an accident and for other parts or Engine failure attributable to that part.
Factors beyond P&WC’s control
improper storage, usage, maintenance or operation of an Engine, part or accessory (e.g. non-compliance with P&WC’s written instructions, including without limitation, the applicable P&WC Engine Maintenance and Overhaul Manuals, P&WC Service Bulletins, or with the Aircraft Flight Manuals, and airworthiness regulations);
any work performed on Engines without due cause, such as pre-purchase inspections, or scheduled maintenance performed at other than P&WC recommended intervals;
accidents, collisions, propeller strikes, fi re, fl ood, lightning strike, theft, explosion, riot, war, rebellion, seizure or any other belligerent acts, foreign object damage (FOD), erosion, corrosion, sulphidation or any other damage due to the operating environment;
alteration to, modifi cation of, or tampering with any Engine, part or accessory after delivery by P&WC, other than strictly in accordance with the applicable P&WC manuals and this Policy;
use of stolen parts, or use of a part or Engine from which P&WC’s name, part number, identifi cation mark or serial number has been removed or defaced;
workmanship performed by a facility other than P&WC-owned manufacturing facilities;
Engines operated by a military, para-military or government service unless it is determined, at the sole discretion of P&WC, that the Engine has not been
CITATION LATITUDE • FEBRUARY 2021 32 used in operations or on fl ight missions which compromise Engine or parts life or reliability when compared to typical commercial, corporate, or private transportation operations;
repair or overhaul of a defective part or Engine at a facility other than a facility designated by P&WC Warranty Administration;
unused cycles (stub life) of an LC F part removed at the operator’s request prior to reaching the service limit;
insurance, duties, brokerage fees, and taxes; and
any other factor beyond P&WC’s control which is not specifi cally listed herein.
In addition, as all of the above are considered to be factors beyond P&WC’s reasonable control, no pro-rata credit per the PPSP will be awarded on Primary Parts, repaired, or exchanged following access to the Engine due to any of the above.
Owner/operator responsibilities
The coverage provided herein is subject to the following conditions:
Maintenance
The Engine must be operated and maintained in accordance with P&WC’s written instructions including, without limitation, the applicable P&WC Engine Maintenance and Overhaul Manuals, P&WC Service Bulletins, as well as the Aircraft Flight Manual and airworthiness regulations.
Maintenance records
Adequate records of Engine operation and maintenance must be kept. Upon request, P&WC is entitled to have access to the records.
For Warranty service
P&WC must be notifi ed of any Defect within thirty (30) days of discovery, and any claim must be submitted within one hundred and eighty (180) days after such discovery.
Any claim, which may include the return of defective parts, must be made through the P&WC source of supply (identifi ed in the applicable P&WC IPC), or the P&WC designated facility or distributor which will furnish or has furnished the replacement parts.
33 CITATION LATITUDE • FEBRUARY 2021 For any warranty work (including, without limitation, disassembly), the Engine must be sent to a facility designated by P&WC Warranty Administration, in accordance with P&WC’s written instructions. Any work performed at a facility other than a facility designated by P&WC Warranty Administration, without prior written authorization from P&WC Warranty Administration, will be at the claimant’s expense.
LIMITATION OF P&WC LIABILITY
THIS IS THE ONLY WARRANTY APPLICABLE TO PW306C, PW306D AND PW306D1 SERIES TURBOFAN ENGINES OPERATED IN NON- MILITARY AIRCRAFT USED FOR COMMERCIAL, CORPORATE OR PRIVATE TRANSPORTATION SERVICE, ENGINES AND IS GIVEN AND ACCEPTED IN PLACE OF ALL OTHER EXPRESS, IMPLIED OR STATUTORY TERMS, REPRESENTATIONS, WARRANTIES OR CONDITIONS, IN CONTRACT OR IN TORT, INCLUDING WITHOUT LIMITATION, ANY WARRANTY OR CONDITION OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE AND ALL SUCH OTHER TERMS, REPRESENTATIONS, WARRANTIES OR CONDITIONS ARE HEREBY EXPRESSLY DISCLAIMED. THE ONLY REMEDY FOR BREACH OF THIS WARRANTY IS AS SET OUT HEREIN. FOR GREATER CERTAINTY, IN NO EVENT SHALL P&WC BE RESPONSIBLE FOR ANY SPECIAL, INCIDENTAL OR CONSEQUENTIAL DAMAGES ARISING OUT OF OR IN CONNECTION WITH EITHER A BREACH OF THIS WARRANTY OR ANY TORTIOUS OR NEGLIGENT ACT OR OMISSION BY P&WC. SPECIAL, INCIDENTAL, OR CONSEQUENTIAL DAMAGES INCLUDE, WITHOUT LIMITATION, ECONOMIC LOSS, LOSS OR DAMAGE TO ANY PROPERTY OR PERSON OR ANY OTHER EXEMPLARY, PUNITIVE OR SIMILAR DAMAGES, AS WELL AS EXPENSES INCURRED EXTERNAL TO THE ENGINE AS A RESULT OF AN ENGINE OR PART DEFECT. NO VARIATION OR EXTENSION OF THIS WARRANTY OR REMEDIES SHALL BE BINDING UNLESS IN WRITING AND SIGNED BY A DULY AUTHORIZED REPRESENTATIVE OF P&WC.
YOUR ACCEPTANCE OF THIS WARRANTY FOR NEW ENGINES AND SERVICE POLICIES OR THE MAKING OF ANY CLAIM OR RECEIPT OF ANY BENEFIT HEREUNDER, CONSTITUTES YOUR ACCEPTANCE OF ALL THE FOREGOING TERMS, CONDITIONS AND LIMITATIONS.
THIS WARRANTY IS GOVERNED BY THE LAWS OF THE PROVINCE OF ONTARIO, CANADA
With advance written notifi cation to P&WC, this Policy is transferable to subsequent owners.
If you have any questions or require assistance regarding this Policy, please call or write to:
CITATION LATITUDE • FEBRUARY 2021 34 Manager, Warranty Administration Pratt & Whitney Canada Corp. 1000 Marie-Victorin Longueuil, Quebec Canada, J4G 1A1 Telephone: 1 450 647-8180 Fax: 1 450 647-2831 Email: [email protected] 17.3 Summary of Honeywell APU Warranty
The APU is warranted by Honeywell.
The following is a summary of the Honeywell’s warranty for installed RE100-CS APUs. Please refer to Honeywell warranty documentation for defi nitions and complete terms and conditions. If there is an inconsistency between the summary provided herein and complete Honeywell warranty documentation, the latter controls.
Commercial Warranty for the RE100-CS APU
Administrative Overview
Warranty claims for the Honeywell RE100[CS] APU may be submitted on an Honeywell Engines, Systems & Services Electronic Warranty Claim system or customer invoice/purchase order providing all required information. Contact Honeywell for the required information.
Warranty claims will be honored for work accomplished at Honeywell Authorized Service Facilities or within the guidelines of the Honeywell warranty policy. All warranty claims are authorized by Honeywell, at Honeywell’s discretion. All hardware valued at greater than $500 must be returned with a warranty claim form for warranty consideration.
Honeywell will replace or repair at its option any manufactured non-conforming hardware during the eff ective warranty period set forth below. Warranty replacement with new hardware is at the discretion of Honeywell.
Warranty coverage includes:
• Parts and labor to repair the APU or APU component
• Shipping of the APU or APU component within the continental United States, when warranty is accepted.
35 CITATION LATITUDE • FEBRUARY 2021 Warranty coverage does not include (but is not limited to):
• Handling fees
• APU or LRU removal and / or re-installation
• New replacement parts except at Honeywell discretion
• Rental of APUs
• Component exchange fees
• Scheduled and routine maintenance (HSI, inspections, etc.)
Warranty Coverage
Seller warrants to the Owner (i.e. the legal or registered owner of the APU) that each APU sold for installation as original equipment on new aircraft comply with applicable Seller drawings and specifi cations and be free from defects in material and workmanship. These warranties shall run to the original purchaser, its successors, assigns and customers when they are the Owner.
Duration of Warranty
ORIGINAL EQUIPMENT APUS
Duration will be sixty (60) months from date of shipment to the Owner, or two thousand fi ve hundred (2,500) APU operating hours, whichever fi rst occurs.
Warranty claim determination for new APUs will be based on the data supplied to Seller by the Owner, its successors and customers when they are the Owner, substantiated by inspection, testing, failure analysis, and information from Seller’s representatives. Seller will have the sole right to determine whether the failure qualifi es under the terms and conditions of this warranty.
RESPONSIBILITY OF SELLER
If an APU or Part is returned to Seller or an Honeywell Authorized Service Center and is found by Seller, in its sole discretion, to have failed as a result of a failure in material or workmanship covered by this warranty, Seller will at no cost to the Owner:
1. Repair or replace, at Seller’s sole option, the failed APU or Part. Any APU or Part which is replaced or exchanged will become the property of Seller.
CITATION LATITUDE • FEBRUARY 2021 36 2. Assume round trip shipping costs for failed or non-conforming APUs or Parts within the continental United States; however, if Seller’s inspection discloses the returned APU or Part does not require repair or replacement under warranty, Seller’s usual inspection charges will apply.
3. The correction of any failure or malfunction will in no way extend the period of this warranty.
4. Seller reserves the right to make changes in its products without incurring any obligation to incorporate the same on previously delivered APUs or Parts.
RESPONSIBILITY OF OWNER
The following conditions govern the application of this warranty:
1. All Owners must send in a Warranty Registration Card form within thirty (30) days of becoming an Owner. Warranty registration cards are in the Engine Log book or may be obtained from Seller by writing to:
HONEYWELL P.O. Box 29003, Mailstop 2102-229 Phoenix, Arizona 85038 ATTENTION: WARRANTY DEPARTMENT
2. Owner will assure that records are maintained which will accurately refl ect APU operating hours and when maintenance was performed. At Seller’s request, such records will be provided to substantiate warranty claims.
3. Owner will be responsible for costs of removal and reinstallation.
4. Scheduled routine maintenance and inspection, including, but not limited to: disassembly, assembly, cleaning, inspection, replacement of consumable hardware such as gaskets, fi lters, packings, igniter plugs, nuts, bolts, etc., minor repairs for cracks, nicks, dents, and all repair eff ort required as a result of Normal Wear and Tear are the responsibility of the Owner and are specifi cally excluded from this warranty.
5. Owner shall submit a warranty claim within the warranty period and the aff ected APU or Part must be returned to Seller, accompanied by an Honeywell Standard Claim form, within thirty (30) days after discovery of such defect or nonconformity.
6. APUs and LRUs returned without the required warranty data are subject to returned and/or repair charges.
37 CITATION LATITUDE • FEBRUARY 2021 EXCLUSIONS
1. The provisions of this warranty will not apply if the APU or Part has been subjected to:
a. Any maintenance, repair, installation, storage, operation, use, handling or environmental condition which is improper or not in accordance with Seller manuals, Bulletins, or other written instructions; or
b. Any alteration, modifi cation or repair by anyone other than Seller or its authorized representatives which adversely aff ects the normal operation and performance of the APU; or
c. Any accident, misuse, neglect, or negligence after delivery by Seller, or
d. Ingestion of foreign material or foreign object damage; or
e. Lack of incorporation of Service Bulletins related to the cause of failure.
2. This warranty will not apply to:
a. Any APU or Part to the extent that the defect or nonconformity is attributable to and Part not supplied by Seller; or
b. Malfunction or failure due to accident, nonconformance, or noncompliance with Seller’s operating, scheduled maintenance or other pertinent instructions.
LIMITATIONS
THIS WARRANTY IS EXCLUSIVE AND IN LIEU OF ALL OTHER WARRANTIES, WHETHER WRITTEN OR ORAL, EXPRESS, IMPLIED OR STATUTORY, INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTIES OF MERCHANTABILITY OR FITNESS FOR PARTICULAR PURPOSE OR USE AND WARRANTIES ARISING FROM COURSE OF PERFORMANCE, DEALING, USAGE OR TRADE, WHICH ARE HEREBY EXPRESSLY DISCLAIMED. IN NO EVENT SHALL SELLER BE LIABLE FOR INCIDENTAL OR CONSEQUENTIAL DAMAGES.
THE EXCLUSION OF INCIDENTAL AND CONSEQUENTIAL DAMAGES AS SET FORTH IN THIS WARRANTY STATEMENT SHALL BE DEEMED INDEPENDENT OF, AND SHALL SURVIVE, ANY FAILURE OF THE ESSENTIAL PURPOSE OF ANY LIMITED REMEDY UNDER THE TERMS OF THIS AGREEMENT.
NO EXTENSION OR EXPANSION OF THIS WARRANTY SHALL BE BINDING UPON SELLER UNLESS SET FORTH IN WRITING AND SIGNED BY SELLER’S AUTHORIZED REPRESENTATIVE.
CITATION LATITUDE • FEBRUARY 2021 38 For more information myaerospace.honeywell.com
Honeywell Aerospace Honeywell Engines, Systems, and Services P.O. Box 29003 1944 E. Sky Harbor Circle Phoenix, AZ 85034 U.S. Toll Free: 1.800.601.3099 www.honeywell.com 18. TRAINING AGREEMENT
The first retail Aircraft Purchaser will be provided training for one (1) Citation Latitude 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-680 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.
39 CITATION LATITUDE • FEBRUARY 2021 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;
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 LATITUDE • FEBRUARY 2021 40 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.
February 2021 SD-JET-680A-0221