SPECIFICATION AND DESCRIPTION
Transcript of SPECIFICATION AND DESCRIPTION
REVISION C
SERIAL NUMBER 700-0068 TO TBDSEPTEMBER 2021
C I T A T I O N L O N G I T U D E
S P E C I F I C AT I O N A N D D E S C R I P T I O N
SPECIFICATIONAND DESCRIPTION
CITATION LONGITUDE
SERIAL NUMBER 700-0068 TO TBD
SEPTEMBER 2021
REVISION C
i CITATION LONGITUDE • SEPTEMBER 2021
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 ........................................................10
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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 (GTCs) ..........................................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 High Frequency Radio Voice Communication ......................................15
10.3.5 Data Link Services .........................................................................................15
10.3.6 Cockpit Voice Data Satellite Transceiver (Iridium) ...............................16
10.3.7 Cockpit Voice Recorder (CVR) ...................................................................16
10.3.8 Flight Management System (FMS) ............................................................16
10.3.9 Electronic Charts and Maps ........................................................................ 17
10.3.10 Distance Measuring Equipment (DME) .................................................. 17
10.3.11 Engine Indicating System (EIS) ................................................................ 17
10.3.12 Crew Alerting System (CAS) ...................................................................... 17
10.3.13 Flight Guidance System (FGS) .................................................................. 17
10.3.14 Electronically Controlled Rudder System ............................................... 18
10.3.15 Attitude/Heading Reference System (AHRS) ........................................ 18
10.3.16 Transponders with ADS-B Out Capability ............................................. 18
10.3.17 Weather Radar .............................................................................................. 18
TABLE OF CONTENTS CONT
iii CITATION LONGITUDE • SEPTEMBER 2021
10.3.18 Radio Altimeter .............................................................................................. 18
10.3.19 Traffi c Collision Avoidance System (TCAS II) ........................................ 18
10.3.20 Terrain Awareness Warning System......................................................19
10.3.21 Synthetic Vision Technology (SVT) .........................................................19
10.3.22 Emergency Locator Transmitter (ELT) ..................................................19
10.3.23 Standby Instrumentation ...........................................................................19
10.3.24 Maintenance Diagnostics..........................................................................19
11. INTERIOR ............................................................................................................................. 20
11.1 Cabin ............................................................................................................................. 20
11.2 Entertainment System ..............................................................................................21
11.3 Windows ......................................................................................................................22
11.4 Cabin Lighting System ...........................................................................................22
11.4.1 Direct Lighting ..................................................................................................22
11.4.2 Indirect Lighting ..............................................................................................22
11.4.3 Emergency Lighting .......................................................................................22
11.5 Water and Waste System .......................................................................................22
11.6 Internet .........................................................................................................................23
12. EXTERIOR ............................................................................................................................23
12.1 Exterior Storage .......................................................................................................23
13. LOOSE EQUIPMENT ........................................................................................................24
14. EMERGENCY EQUIPMENT ............................................................................................25
15. DOCUMENTATION AND TECHNICAL PUBLICATIONS ...........................................25
16. MAINTENANCE TRACKING PROGRAM ...................................................................27
17. LIMITED WARRANTIES .....................................................................................................27
17.1 Limited Aircraft Warranty ........................................................................................27
17.2 Honeywell’s Commercial Warranty for the HTF7700 Engine .....................31
17.3 Honeywell’s Commercial Warranty for the Cessna Longitude - ...................
36-150EMB APU .................................................................................................................36
18. TRAINING AGREEMENT ................................................................................................43
TABLE OF CONTENTS CONT
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Figure 1: Exterior Dimensions ................................................................................................. 3
Figure 2: Interior Dimensions ................................................................................................. 4
Figure 3: Instrumentation ........................................................................................................ 13
Figure 4: Cabin Typical Confi guration .............................................................................. 20
LIST OF FIGURES
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INTRODUCTION
This Specifi cation and Description provides general information about the
design, performance, and standard equipment of the Cessna Citation Longitude
(Model 700), Serial Number 700-0068 to TBD (hereinafter “Citation Longitude” 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]
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THE AIRCRAFT
1. GENERAL DESCRIPTION
The Citation Longitude is a transcontinental swept-wing business jet. The Aircraft
has provisions for 8 - 12 passengers (eight is standard) and is certifi ed for a crew
of two. The Citation Longitude has internally and externally accessible storage
compartments for personal items, baggage, and cargo.
Two Honeywell HTF7700L turbofan engines power the Citation Longitude and a
fully integrated Garmin G5000 digital avionics suite provides pilots with state-of-
the-art touch screen controls.
1.1 Certifi cation
The Citation Longitude 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 Longitude is compliant with RVSM certifi cation requirements.
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.
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EXTERIOR DIMENSIONS
Figure 1: Exterior Dimensions
25 ft 11 in (7.90 m)
68 ft 11 in (21.00 m)
73 ft 2 in (22.30 m)
19 ft 5 in(5.91 m)
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Figure 2: Interior Dimensions
INTERIOR DIMENSIONS
77 in(1.95 m)
31 in(0.79 m)
77 77 77 77 77 7777777777 77777 inininnininininininnn(1.(1.(1.(1.(1.(1.(1.(1.(1.(1(1.(1 95 95 95 95 95 95 9595 959595959 m)m)m)m)m)m)m)m)m)m)m)m)
72 in (1.83 m)
77 in (1.96 m)
65 in(1.65 m)
17 in(0.43 m)
26 in(0.66 m)
302 in(7.67 m)
13 in(0.33 m)
44 in (1.12 m)
20 in(0.51 m)
76 in(1.93 m)
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1.3 Approximate Dimensions
OVERALL HEIGHT 19 ft 5 in (5.91 m)
OVERALL WIDTH 68 ft 11 in (21.00 m)
OVERALL LENGTH 73 ft 2 in (22.30 m)
WHEELBASE 31 ft 7 in (9.62 m)
WING
SPAN
(overall)
68 ft 11 in (21.00 m)
AREA
556 ft2 (51.65 m2)
SWEEP
(at 25% chord
outboard panel)
28.6 o
HORIZONTAL TAIL
SPAN
(overall)
25 ft 11 in (7.90 m)
AREA
140 ft2 (13.00 m2)
SWEEP
(at 25% chord)
33.5 o
VERTICAL TAIL
HEIGHT
10 ft 4 in (3.15 m)
AREA
112 ft2 (10.40 m2)
SWEEP
(at 25% chord)
45 o
CABIN INTERIOR
(with typical interior)
HEIGHT
(max)
72 in (1.83 m)
LENGTH*
35 ft 5 in (10.79 m)
WIDTH
(max)
77 in (1.96 m)
LENGTH**
25 ft 2 in (7.67 m)
*Cabin Length: Forward pressure bulkhead to aft pressure bulkhead
**Cabin Length: Excluding fl ight compartment
1.4 Design Weights and Capacities
MAXIMUM TAKEOFF WEIGHT 39,500 lb (17,917 kg)
MAXIMUM LANDING WEIGHT 33,500 lb (15,195 kg)
FULL FUEL PAYLOAD 1,600 lb (726 kg)
MAXIMUM RAMP WEIGHT 39,700 lb (18,008 kg)
MAXIMUM ZERO FUEL WEIGHT 26,800 lb (12,156 kg)
BASIC OPERATING WEIGHT
(2 crew, 200 lb each, typically equipped)
23,600 lb (10,705 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.
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TAKEOFF FIELD LENGTH
(Maximum Takeoff Weight, Flaps Position 2, Sea Level, ISA)
4,810 ft (1,466 m)
MAXIMUM CERTIFIED ALTITUDE 45,000 ft (13,716 m)
MAXIMUM CRUISE SPEED (+/- 3%)
(35,000 feet {10,668 m} altitude; mid cruise weight; maximum cruise
thrust)
483 KTAS (895 km/hr)
NBAA IFR RANGE (+/- 4%)
(4 passengers, 0.80 Mach, 200 NM alternate)
3,500 NM (6,482 km)
LANDING DISTANCE
(Maximum Landing Weight, Full Flaps)
3,170 ft (966 m)
CERTIFIED NOISE LEVELS (Complies with 14 CFR 36, Appendix B, Stage 5 maximum noise level
requirements / ICAO Chapter 14 noise levels in Annex 16, Volume I, Seventh Addition, Amendment
11-B)
Flyover 72.9 EPNdB
Lateral 88.4 EPNdB
Approach 89.9 EPNdB
3. DESIGN LIMITS
DESIGN LOAD LIMITS
Flaps UP -1.00 to +2.70G
Flaps UP, 1, 2, or FULL 0.0 to +2.0G
OPERATING LIMIT SPEEDS
VMO
(8,000 ft {2,438 m} to 29,375 feet {8,953 m}) 325 KIAS (602 km/hr)
MMO
(above 29,375 feet {8,953m}) Mach 0.84 (Indicated)
FLAP LIMIT SPEEDS
Maximum Flap Extended Speed
VFE
(Flaps 1) 250 KIAS (463 km/hr)
VFE
(Flaps 2) 230 KIAS (426 km/hr)
VFE
(Flaps FULL) 180 KIAS (333 km/hr)
LANDING GEAR LIMIT SPEEDS
VLO
230 KIAS (426 km/hr)
VLE
230 KIAS (426 km/hr)
SPEED BRAKES
VSB
No Limit
2. PERFORMANCE CONT
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4. FUSELAGE
4.1 Design and Construction
The Citation Longitude incorporates a circular fuselage of metallic construction with
a pressurized cabin. A fl at fl oor from just behind the cockpit to the lavatory and
baggage compartment 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 an in-fl ight accessible heated and pressurized baggage
compartment detailed in Section 12.1. The aft fuselage also features servicing ports
for the hydraulic system, water system and toilet system.
5. WING
This Aircraft features a swept wing with winglets, employing supercritical airfoil
technology. One aileron, two hinge-type fl aps and three spoiler panels are
incorporated into each wing. The spoiler panels provide both roll control and speed
brake functions on the Aircraft.
6. EMPENNAGE
The empennage is a T-tail confi guration with a swept horizontal and vertical
stabilizer. The horizontal stabilizer provides pitch trim and can be positioned in-
fl ight using an electric actuator. Pitch control is provided by two elevators controlled
through a dual independent cable system. The single rudder is electronically
commanded and hydraulically operated.
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7. LANDING GEAR
7.1 Design and Construction
The main landing gears are electrically controlled, hydraulically actuated, with a
trailing link design. Each landing gear is actuated by an individual hydraulic down-
locking actuator. When retracted, the main gears are covered by a pair of doors.
The landing gear emergency extension system allows the gear to free fall into the
down-lock 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-disk, anti-skid carbon brake system is electronically controlled and
hydraulically actuated. Emergency braking is through the modulated parking brake
system. A brake temperature monitoring system provides brake temperatures to
the fl ight crew.
PLY MAX SPEED RATING SIZE
NOSE GEAR TIRES 10 225 mph (362 kph) 16 x 4.4R8
MAIN TIRES 14 225 mph (362 kph) 26 x 66.R14
8. PROPULSION
8.1 Powerplant
The Aircraft is powered by two Honeywell HTF7700L turbofan engines installed
on the aft fuselage. The HTF7700L engines incorporate dual channel Full Authority
Digital Electronic Controls (FADEC) that are integrated with the Autothrottle (A/T).
The A/T is 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 engaged throughout the fl ight, approach and
fl are and landing touchdown (Aircraft does not incorporate autoland capability). The
A/T may be disengaged for manual throttle control. The engines are pneumatically
started using APU bleed air.
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Hydraulically actuated, target-type thrust reversers compatible with the engine
nacelles and powerplants are included.
TAKEOFF THRUST (at sea level) 7,665 lbs (34.1 kN)
TIME BETWEEN OVERHAUL ON CONDITION
8.2 Auxiliary Power Unit (APU)
The Honeywell 36-150 APU is certifi ed to start up to 31,000 ft and operate to
35,000 ft. Approved for unattended operations, it provides electrical power for the
Aircraft. The APU also provides bleed air for environmental controls and engine
starting while on the ground and at lower altitudes. The APU is located in the
stinger and access panels provide access for removal and servicing.
9. SYSTEMS
9.1 Flight Controls
The Primary Flight Controls consist of one aileron on each wing, horizontal
stabilizer, and one rudder on the vertical tail. Push rod and cable systems are used
to actuate the elevators and ailerons. Dual independent cable systems are routed
from each pilot’s controls to the respective elevator.
Secondary fl ight controls include electric pitch trim, roll spoilers, speed brakes,
and two hinged fl ap panels per side. All control surfaces, spoilers, speed brakes,
and fl aps are of composite construction. A full time yaw damper system improves
performance and comfort.
9.2 Fuel System
There are two integral fuel tanks, one per wing. System operation is fully automatic
throughout the normal fl ight profi le with each engine receiving fuel from its
respective wing tank.
The single point refueling system incorporates a standard fueling receptacle forward
of the right wing in the fairing, as well as a fuel service panel which permits operator
selection of desired total quantity. The system can also be used to defuel one or
both fuel tanks. The Citation Longitude is certifi ed for a wide range of jet fuels.
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9.3 Electrical System
The split-bus electrical system is powered by two engine-driven, 500 amp, brushless
DC generators. An additional generator is driven by the APU when the APU is
operating. The Aircraft’s main batteries are two 44-amp hour lithium ion batteries,
which are located in access panels on both sides of the fuselage behind the wing.
A DC backup (secondary) generating power source is provided by a hydraulic
driven generator, which is part of the bi-direction Power Transfer Control Unit (PTCU).
The PTCU backup generator is capable of providing 200 amperes at 28.5 VDC
from either A or B hydraulic system in the event of loss of power from both engine
mounted DC generators. If all generating 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 lights are all LED. The lighting consists of two red fl ashing
beacons, three anti-collision lights, three position lights, two taxi lights (located on
the nose gear) and two landing/taxi/recognition lights mounted on the forward belly
fairing.
9.4.2 Secondary
The Citation Longitude has two wing inspection lights, two down wash lights
mounted on the lower leading edge of the wingtips, two maintenance/work lights
mounted on the lower engine pylons, one over wing emergency light mounted on
the RH fairing, and two tail logo/fl ood lights mounted on the upper engine pylons.
Courtesy lights at the base of cabin door steps, in the door tread, illuminate when
the door is open.
9.5 Pressurization and Environmental System
Bleed air from each engine or the APU 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.
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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
The wing leading edge and engine inlets are heated by bleed air. The horizontal
stabilizer is electromechanically de-iced. Electric heat is used to remove ice from
the windshield and external sensors. Two electronic ice detectors provide primary
indication to the crew for activation of wing, engine and horizontal stabilizer ice
protection systems. Two wing inspection lights are mounted on the fuselage for
use during night fl ights.
9.7.2 Rain
The windshield has a hydrophobic coating that repels water.
9.8 Hydraulic System
The dual isolated hydraulic system employs pressure compensated pumps to
operate the rudder, multifunction and ground spoilers, landing gear, power brakes,
nose wheel steering, and thrust reversers. A bi-directional Power Transfer Control
Unit (PTCU) provides hydraulic pressure to both systems following loss of normal
hydraulic power, as well as electrical power in the case of generator failures. The
Hydraulic system maintains a continuous pressure of approximately 3,000 psi
(206.8 bar) while the electrical system provides a continuous 28V DC to the Aircraft.
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10. FLIGHT COMPARTMENT
10.1 General
The Garmin G5000 system is the featured avionics suite on the Citation Longitude.
Four full-color, touch screen 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 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. 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
copilot’s sidewalls.
The G5000 system also allows each crew member to mute audio alerts (TAWS,
TCAS, etc.) from the respective on-side overhead speaker. The crew is required to
wear headsets when the cockpit speakers are disabled.
LED illuminated panels, instrument fl oodlights, push button switches, overhead map
lights, and blue-white background lighting are standard in the fl ight compartment.
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10.2 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
Annunciations
11. RH Tilt Panel
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. Parking Brake Handle
Figure 3: Instrumentation
1
23 4
5
6
7
8
9
10 1112
1314
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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 Systems.
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 wide screen, 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.
15 CITATION LONGITUDE • SEPTEMBER 2021
10.3.2 Garmin Touchscreen Control Panels (GTCs)
Four full-color touch screen LCD control panels are used to manipulate G5000
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 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 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 High Frequency Radio Voice Communication
A single High Frequency (HF) radio, the Honeywell KHF-1050, is interfaced to the
Garmin G5000 system. The HF is controlled via the Garmin GTCs, and used by the
fl ight crew for voice communications with ATC, etc. when voice communications
are required over distances exceeding the capability of the VHF radio. The SELCAL
function is included in the G5000 system and can be used by the HF system with
the VHF radio. Provisions for a second HF system are included.
10.3.5 Data Link Services
Weather graphics and Aircraft Communications Addressing and Reporting System
(ACARS) operate over a dedicated third VHF radio via a data link service provider.
Applicable subscription services are the Purchaser’s responsibility.
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10.3.6 Cockpit Voice Data Satellite Transceiver (Iridium)
The Citation Longitude 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 Longitude.
Subscription/data charges for other services associated with the Iridium SatCom system still apply and are the
Purchaser’s responsibility.
10.3.7 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.
The CVR is also equipped with a Recorder Independent Power Supply (RIPS)
enabling the CVR to continue recording for an additional ten minutes following a
loss of electrical power.
10.3.8 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
17 CITATION LONGITUDE • SEPTEMBER 2021
• 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.
10.3.9 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
electronic chart database resides on the SD-card that is internal to each PFD and
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.
10.3.10 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.
10.3.11 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.
10.3.12 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.
10.3.13 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, attitude and rate information, and airspeed.
18CITATION LONGITUDE • SEPTEMBER 2021
• 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 under speed or over speed condition.
10.3.14 Electronically Controlled Rudder System
The Thales Rudder Control System provides automatic full time yaw damping and
turn coordination (independent of the Garmin AFCS) while monitoring yaw rate, roll
angle, lateral acceleration and airspeed from the onboard sensors.
10.3.15 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.
10.3.16 Transponders with ADS-B Out 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 capability is
standard.
10.3.17 Weather Radar
Weather radar information is provided via the GWX-8000 weather radar system
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.
10.3.18 Radio Altimeter
The G5000 system includes one standard Garmin GRA 5500 radar altimeter unit
that supplies information to the PFDs and to the Traffi c Collision Avoidance System
(TCAS) and the Terrain Awareness Warning System (TAWS).
10.3.19 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.
The Garmin GTS 8000 is also ADS-B in capable providing the crew the ability to
display ADS-B airborne and surface traffi c from targets that are transmitting ADS-B
information.
19 CITATION LONGITUDE • SEPTEMBER 2021
10.3.20 Terrain Awareness Warning System
The G5000 system includes a Class A Terrain Awareness 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.
10.3.21 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.
10.3.22 Emergency Locator Transmitter (ELT)
An Artex ELT 4000 Emergency Locator Transmitter (ELT) with navigation interface is
standard.
Note: Some authorities may not permit the use of navigation interface capability.
10.3.23 Standby Instrumentation
An Electronic Standby Flight Display (ESFD), powered by the emergency bus and
having its own backup battery, displays standby airspeed, attitude, altitude, heading
and VOR/ILS navigation information.
10.3.24 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. Textron Aviation’s Aircraft Recording
System (AReS) for Cessna Citation jets 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.
20CITATION LONGITUDE • SEPTEMBER 2021
11. INTERIOR
11.1 Cabin
There is one main cabin door that is electrically
operated and features integral air stairs. The cabin is
separated from the fl ight compartment by a curtain
or optional divider. A one-piece, half-length curtain is
mounted on the LH forward side and may be pulled
across the aisle and fastened on the RH side.
The cabin extends from the fl ight compartment
curtain to the in-fl ight accessible walk in baggage
compartment. The cabin fl at fl oor extends aft from the
cockpit to the in-fl ight accessible walk in baggage
compartment and provides a cabin height of 72 inches
(1.83 m). The fl at fl oor continues into the baggage
compartment to the aft pressure bulkhead. An
emergency exit hatch is located on the right-hand side
next to the aftmost seat area.
The cabin is sized to off er passenger comfort and
fl exibility for a variety of interior arrangements. The
typical arrangement is an eight-passenger, double
club seating arrangement with a right-hand forward
refreshment center and left-hand forward closet.
Optional seating arrangements can provide for up to
10 passengers, and the Aircraft is certifi ed for up to 12
passengers for future growth and customer requested
special confi gurations.
The following are included in the typical arrangement:
• A right-hand refreshment center with hot and cold
beverage capability, large divided ice drawer,
numerous storage areas, large trash receptacle,
glassware storage capabilities, and provisions for
catering;
• A left-hand coat closet, forward of the cabin entry
door, provides storage for navigation charts, fl ight
manual, briefcase, entertainment equipment and
blankets and also has entry door curtain stowed on
the aft side when not in use;
Figure 4: Cabin Typical
Confi guration
#10
#8
#6
#4#3
#5
#7
#9
21 CITATION LONGITUDE • SEPTEMBER 2021
• Eight pedestal-mounted passenger seats with extendable headrests and dual
fi xed armrests (except seat #10). All passenger seats (except seat #10) adjust fore
and aft, track laterally into the aisle for additional space, recline fully (berthable),
and swivel 180-degrees. Each seat is equipped with a seat belt, a shoulder
harness strap with inertia reel, and an over-water life vest stored nearby;
• Four executive tables with ample work area are included. The table between
seats #8 and #10 is smaller due to the escape hatch. Side ledges have
multipurpose areas for cups and personal electronic devices;
• The cabin management system includes one iPad with the cabin management
system application installed, which can also be installed on personal devices.
This app provides passengers with VIP controls for audio, video, and moving
map entertainment, cabin temperature and lighting. The VIP functions are also
available in a master control switch panel in the refreshment center;
• Four individual Universal 115V AC outlets;
• Twenty individual USB charging ports (2 at each seat including crew seats);
• The aft lavatory, with vacuum assisted, non-belted fl ushing toilet, has sliding
privacy doors and is externally serviceable. The vanity provides hot and cold
fi ltered potable water, storage for baggage compartment required safety
equipment, and numerous small storage compartments;
• The in-fl ight accessible baggage area accommodates storage for luggage and
is accessible both internally and externally. A fl ip down coat rod is located in the
center of the compartment. A designated storage area for life rafts is located in
the baggage compartment forward of the external access door;
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 best in class, given its operating speeds and environment.
11.2 Entertainment System
The cabin entertainment system comes standard with a Digital Media Server and a
22 inch video monitor located in the forward cabin. The media server can store music
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. The wireless cabin
management system application is available for Apple devices.
22CITATION LONGITUDE • SEPTEMBER 2021
11.3 Windows
Fifteen elliptical cabin windows are equipped with electric window shades.
11.4 Cabin Lighting System
11.4.1 Direct Lighting
General LED lighting with variable adjustment settings, aisle LED lighting,
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 Packs in the case of a power interruption.
11.5 Water and Waste System
The water and waste systems include an externally serviceable vacuum assisted
toilet, and an aircraft level water system. The waste system includes a six gallon
waste holding tank located in the aft fairing of the Aircraft. The water system
includes a 12 gallon holding tank located outboard of the vanity. The water system
holding tank can be fi lled externally through the external service panel, or fi lled
internally through an internal port located outboard of the vanity work surface.
23 CITATION LONGITUDE • SEPTEMBER 2021
11.6 Internet
A U.S.ground-based wireless connectivity system is included and provides
broadband data connection to and from the Aircraft via a US-based terrestrial
network. The system off ers wireless internet access for multiple users in the Aircraft
cabin and cockpit and is compatible with IEEE 802.11 ac wireless equipped personal
devices such as laptops, tablets, and handheld devices. The system is operational
above 3,000 feet above ground level (AGL) in the continental U.S. and portions of
Canada and Alaska.
Service charges apply.
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 in-fl ight and externally accessible baggage compartment is located in the
aft fuselage. The baggage area is also accessible through a 26 in (.66 m) wide
lockable door that slides up and into the baggage area. This area is heated and
pressurized.
WEIGHT VOLUME
MAIN BAGGAGE AREA 1,000 lb (453.6 kg) 98 ft3 (2.78 m3)
24CITATION LONGITUDE • SEPTEMBER 2021
13. LOOSE EQUIPMENT
Aircraft Keys (10)
Baggage Restraint Kit (1)
Cabin Door Pull Strap Assembly (1)
Coat Hangers (13)
Coff ee Mugs (12)
Crew Noise-Canceling Headsets (2)
Crystal Old Fashioned Glasses (12)
Crystal Wine Glasses (12)
Emergency Exit Lock Pin (1)
Engine Cover Set (1)
Fuel Cap Keys (4)
Garmin G5000 Software Set (1 set of 4 SD cards)
iPad (1)
Jack Pads (3)
Leather Cleaning Kit (1)
Leather Hand Rail Cover (2)
Passenger Briefi ng Cards (10)
Pitot Cover Set (1)
Static Wick Protectors (10)
Thrust Reverser Lockouts (2)
25 CITATION LONGITUDE • SEPTEMBER 2021
14. EMERGENCY EQUIPMENT
Crew and Passenger Oxygen (1 per seat)
Emergency Exit Lights
Emergency Lighting Battery Packs
First Aid Kit (1)
Flashlight (two D-cells) (1)
Hand Held Fire Extinguisher in Cockpit, Cabin and Vanity (3)
Individual Overwater Life Vests (1 per seat)
Vanity PBE (Personal Breathing Equipment)
Water Barrier (1)
15. DOCUMENTATION AND TECHNICAL PUBLICATIONS
The following will be provided to Purchaser.
Print material:
Airplane Flight Manual/Pilot’s Checklists which includes the Weight and
Balance Manual
Log Books (Aircraft and Engines)
Passenger Briefi ng Cards
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 Electronic Media only:
Cabin Equipment Operation Manual
Illustrated Parts Catalog — Interior
Interior Maintenance Manual
26CITATION LONGITUDE • SEPTEMBER 2021
Available via online subscription at ww2.txtav.com:
Component Maintenance Manual
Electrical Wiring Interconnect System Manual
Illustrated Parts Catalog — Airframe
Maintenance Manual — Airframe
Nondestructive Testing Manual
Service Bulletins and Service Letters — Airframe
Structural Repair Manual
Wiring Diagram Manual
Documents containing 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.
27 CITATION LONGITUDE • SEPTEMBER 2021
16. MAINTENANCE TRACKING PROGRAM
The Aircraft will deliver with an online computerized maintenance record service for
one year from the date the Citation Longitude 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 Longitude Limited Aircraft Warranty (Limited Aircraft Warranty)
covers Textron Aviation manufactured Aircraft components, avionics, Vendor Items,
Interior Furnishings, Paint and Customer Requests. The Aircraft engines and auxiliary
power unit (APU) are warranted by Honeywell. Honeywell’s Commercial Warranty
for the HTF7700 Engine, which means a new HTF7700L Engine delivered for
commercial use, and Honeywell’s Commercial Warranty for the Cessna Longitude -
36-150EMB APU are set out below.
17.1 Limited Aircraft Warranty
Periods
The Seller warrants each new Citation Longitude 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;
28CITATION LONGITUDE • SEPTEMBER 2021
(c) Five years or 3,000 hours, whichever occurs fi rst, for Vendor Items including
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 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 expense to the Support
Facility from where the replacement part is procured; and
(iii) the return part is accompanied by the Textron Aviation issued
Return Authorization; and
29 CITATION LONGITUDE • SEPTEMBER 2021
(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.
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);
30CITATION LONGITUDE • SEPTEMBER 2021
(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 expire 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
MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE. THE REMEDIES
OF REPAIR OR REPLACEMENT OF THE DEFECTIVE PART(S) AS SET OUT
31 CITATION LONGITUDE • SEPTEMBER 2021
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 Honeywell’s Commercial Warranty for the HTF7700 Engine
The Aircraft engines are warranted by Honeywell.
The following was provided by Honeywell Aerospace. However, if there is any
inconsistency between what follows and current Honeywell documentation, the
latter controls.
Original Equipment Engines
Honeywell warrants to the purchaser that each HTF7700 Engine (model number
AS907-2-1S) sold for installation as original equipment on new aircraft will at time of
delivery be free from defects in material and workmanship and will be of the kind
and type specifi ed. Warranty shall run to the original purchaser, its successors and
assigns. This warranty shall expire sixty (60) months from date of aircraft delivery or
three thousand (3,000) Engine operating hours whichever occurs fi rst.
32CITATION LONGITUDE • SEPTEMBER 2021
Defi nitions
As used herein, the following words and phrases have the following meanings:
1. “Honeywell” means Honeywell through its Propulsion Engines business.
2. “Owner” means the owner of the aircraft registered with the Federal Aviation
Administration (FAA) or its equivalent in which the Engine is installed at time of
warranty claim, or the legal owner of the Honeywell Engine.
3. “Engine” means a new HTF7700L Engine delivered for commercial use.
4. “Commercial Use” means the operation of the Engines in aircraft licensed by
FAA or its equivalent for general civilian and routine commercial use excluding
aerial dusting and spraying and any other type of fl ying requiring special
authorization or dispensation by FAA or its equivalent.
5. “Initial Operation” means the fi rst running of the Engine after obtaining a
certifi cate of airworthiness on the aircraft. “Initial Operation” of a new spare
Engine means the fi rst running of the spare Engine after installation on the
aircraft.
6. “Engine Operating Hours” means the total number of engine hours.
7. “Failure” or “Malfunction” in an Engine or part means breakage or inability to
function properly in a manner for which it was designed and as a serviceable
engine in accordance with the Engine Maintenance Manual.
8. “Parts” means only those parts of the Engine which are delivered, repaired or
replaced by Honeywell or their Authorized Representative as identifi ed in the
appropriate Illustrated Parts Catalog (IPC).
Responsibility of Honeywell – Original Equipment and Spare Engines
1. If an engine or part is returned to Honeywell or an Authorized Service Center
in accordance with the provisions of this warranty and is found in the sole
discretion of Honeywell to contain a defect in material or workmanship covered
by this warranty, Honeywell shall provide the following at no charge to the
Owner:*
a. Repair or replacement, at Honeywell’s discretion, of the Part(s) with a new,
repaired, refurbished, or overhauled part.
b. Engine Access Labor
33 CITATION LONGITUDE • SEPTEMBER 2021
c. Engine Removal and Reinstallation Labor
d. Troubleshooting Labor
e. Rental Engine associated with Unscheduled Heavy Maintenance
f. Engine accessory removal and replacement labor
g. Freight – Reasonable Freight charges to the nearest Honeywell authorized
representative.
*Based on Honeywell guidelines.
2. A part covered by the terms of this warranty shall be considered for coverage
if damaged as a result of the failure of another part covered by the terms of this
warranty.
3. The correction of any failure or malfunction shall in no way extend the period of
this warranty.
4. When Honeywell replaces any Engine or Part, the Part removed shall become
the property of Honeywell.
5. Honeywell 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 Honeywell.
New Spare Parts for Engines
Honeywell warrants that new spare parts sold for installation in Engines will at time
of delivery be free from defects in material, workmanship and title and will be of the
kind and type specifi ed. Warranty shall run to the original purchaser, its successors,
assigns and consists of repair, refurbishment or replacement of the failed part. This
warranty shall expire twelve (12) months from the date of shipment by Honeywell or
six (6) months from date of installation of the new spare part in Engine, whichever
occurs fi rst. However, the warranty for parts replaced under the original equipment
warranty shall not extend beyond the date of expiration of the warranty for the
given Engine.
34CITATION LONGITUDE • SEPTEMBER 2021
Repaired Parts for Engines
Honeywell warrants that repaired, overhauled or refurbished Parts sold for
installation in Engines and provided through Honeywell, will at time of delivery,
be free of defects in material and workmanship and will be of the kind and type
specifi ed. Warranty shall run to the original purchaser, its successors and assigns,
and consists of repair, refurbishment, or replacement of the failed Part. This
warranty shall expire twelve (12) months from the date of shipment by Honeywell
or six (6) months from date of installation, whichever occurs fi rst. However, the
warranty for repaired parts replaced under the original equipment warranty shall
not extend beyond the date of expiration of the warranty for the given Engine.
Responsibility of Owner
The following conditions govern the application of each of the warranties described
above for Original Equipment Engine, New Spare Engine, New Spare Parts for
Engines and Repaired Parts for Engines:
1. Owner shall assure that records are maintained which will accurately refl ect
Engine operating hours and date and extent of maintenance performed. At
Honeywell’s request, such record shall be provided to substantiate any warranty
claim.
2. This Warranty will not apply if the Engine has been subjected to:
a. Any maintenance, overhaul, installation, storage, operation, or use, which is
not in accordance with Honeywell’s instructions; or
b. Any alteration or repair by anyone other than Honeywell or its authorized
representatives or
c. Any accident, misuse, neglect, or negligence after delivery by Honeywell; or
d. Any tests other than normal production fl ight tests, unless Honeywell grants
prior written approval; or
e. Ingestion of foreign material; or
f. Any other cause not within the control of Honeywell.
3. Owner must notify Honeywell or its representative of a failure within 30 days
following the failure and return of the engine or part for repair or replacement
within thirty (30) days following such notice.
35 CITATION LONGITUDE • SEPTEMBER 2021
4. Owner is responsible for scheduled and unscheduled 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 other repair eff ort required as a result of normal wear and tear is the
responsibility of the owner and are specifi cally excluded from this warranty.
5. The Operator shall ensure all removed, unserviceable engine units are shipped
to Honeywell or its representative within 5 days after receipt of a serviceable
rental or exchange engine unit. Failure by Operator to return a rental engine
to Honeywell or its representative within 15 days after Operator’s removed
engine has been repaired and returned in a serviceable condition shall subject
operator to the then current engine rental rate and late return charges.
Hassle Free Factory Warranty
Your warranty is designed to cover unscheduled maintenance engine costs.
During an engine failure, your warranty covers:*
• Repair or replacement, at Honeywell’s discretion, of the Part(s) with a new,
repaired, refurbished, or overhauled part.
• Engine Access Labor
• Engine Removal & Reinstallation Labor
• Troubleshooting Labor
• Rental Engine associated with heavy unscheduled maintenance
• Engine Accessory Removal & Replacement Labor
• Freight - reasonable charges to nearest authorized Honeywell representative
* Within Honeywell guidelines
Your HTF7700 engines are covered under this warranty for:
60 Months from date of new aircraft delivery or 3000 engine operating hours
whichever occurs fi rst.
After the initial new engine warranty period, new spare parts and repaired parts
will have a warranty of:
12 months from ship date from Honeywell or 6 months from installation date,
whichever occurs fi rst.
36CITATION LONGITUDE • SEPTEMBER 2021
EXCEPT AS EXPRESSLY PROVIDED ABOVE IN EACH OF THE WARRANTIES FOR
ORIGINAL EQUIPMENT ENGINE, NEW SPARE ENGINE, NEW SPARE PARTS FOR
ENGINES AND REPAIRED PARTS FOR ENGINES, HONEYWELL SHALL HAVE NO
FURTHER OBLIGATION UNDER THIS WARRANTY.
LIMITATIONS (APPLIES TO EACH OF THE WARRANTIES DESCRIBED ABOVE) FOR
ORIGINAL EQUIPMENT ENGINE, NEW SPARE ENGINE, NEW SPARE PARTS FOR
ENGINES AND REPAIRED PARTS FOR ENGINES.
1. ALL OTHER WARRANTIES, WHETHER EXPRESS, IMPLIED OR STATUTORY,
SUCH AS WARRANTIES OR MERCHANTABILITY OR FITNESS FOR A
PARTICULAR PURPOSE, ARE HEREBY EXCLUDED AND DISCLAIMED TO THE
EXTENT THEY EXCEED THE WARRANTIES GRANTED HEREIN. IN NO EVENT
SHALL HONEYWELL BE LIABLE FOR CONSEQUENTIAL OR INCIDENTAL
DAMAGES.
2. NO AGREEMENT EXTENDING THIS WARRANTY SHALL BE BINDING UPON
HONEYWELL UNLESS IN WRITING AND SIGNED BY A DULY AUTHORIZED
OFFICER OR REPRESENTATIVE.
For more information:
myaerospace.honeywell.com
Honeywell Aerospace
1944 East Sky Harbor Circle
Phoenix, Arizona 85034
800.421.21133 US & Canada
602.365.2180 All Other
www.honeywell.com
17.3 Honeywell’s Commercial Warranty for the Cessna Longitude -
36-150EMB APU
The APU is warranted by Honeywell.
The following was provided by Honeywell Aerospace. However, if there is any
inconsistency between what follows and current Honeywell documentation, the
latter controls.
37 CITATION LONGITUDE • SEPTEMBER 2021
Administrative Overview
Warranty claims for the Honeywell 36-150[EMB] APU may be submitted via
Honeywell Electronic Claim system, or customer invoice/purchase order providing
all required information listed below.
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.
The following information is required to process 36-150[EMB] APU warranty for
[Cessna Longitude (“Cessna”)] aircraft:
• Date of purchase / Date of delivery
• Date of installation and removal
• APU Part Number and component or LRU Part Number, if applicable, including
dash numbers
• Corresponding APU and component or LRU Serial Numbers
• Cessna Aircraft Serial Number and date of entry into service (or date of spare
part installation)
• Total APU hours (TSN) accrued on item or component
• Description of claimed non-conformance and reason for removal.
• Date of claimed non-conformance
• Itemized account of labor hours directly expended in performing repair, if
applicable
• Itemized account of material furnished by Owner directly incorporated in the
repair, if applicable
• Purchase Order
38CITATION LONGITUDE • SEPTEMBER 2021
Warranty coverage includes:
• Parts and labor to repair the APU or APU component
• Shipping of the APU or APU component within geographical region, when
warranty is accepted.
Warranty coverage does not include:
• 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.)
• Customs and Importation Fees
• Taxes
Warranty Program Details
Defi nitions
The following words or phrases have the noted meanings:
1. “Seller” means Honeywell Engines, Systems & Services and its affi liates, and
business units of Honeywell Inc.
2. “Owner” means the legal or registered owner of the APU.
3. “APU” means a new 36-150[EMB] Auxiliary Power Unit, Part Number 70720189-[X]
delivered for use on Cessna aircraft.
4. “Parts” means components or Line Replaceable Units (LRU’s) of the APU which
may be repaired or replaced by Seller or its Authorized Facility.
5. “APU Operating Hours” means the Time Since New (TSN) accumulated on the
APU or its Parts, as recorded by the APU hourmeter.
39 CITATION LONGITUDE • SEPTEMBER 2021
6. “Installation” means the date the APU or Part is originally installed on the aircraft.
7. “Failure”, “Malfunction”, or “Non-Conformance” in an APU or Part means
breakage or improper function.
8. “Normal Wear and Tear” means the gradual and expected deterioration of
an APU or Part, the need for regular overhaul and periodic maintenance and
consumable hardware, and does not constitute a failure or malfunction under
this warranty.
Warranty Coverage
Seller warrants to the Owner that each APU sold for installation as original
equipment on new Cessna aircraft and new spare APUs will, as set forth below,
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 new Cessna aircraft delivery to Owner,
or two thousand (2,000) APU Operating Hours, whichever fi rst occurs.
NEW SPARE APUS
Duration will be sixty (60) months from date of shipment to the Owner, or two
thousand (2,000) APU Operating Hours, whichever fi rst occurs.
Warranty claim determination 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.
NEW SPARE PART WARRANTY
Duration will be twelve (12) months from ship date from Honeywell or six (6) months
after date of installation in the aircraft, whichever occurs fi rst. Seller warrants to
the Owner that each new spare part sold for installation on an APU will, at the time
of shipment or installation as identifi ed above, conform to the applicable Seller
drawings and specifi cations, and be free from defects in material and workmanship.
40CITATION LONGITUDE • SEPTEMBER 2021
REPAIR AND OVERHAUL (after original equipment / spare warranty expiration)
Duration will be twelve (12) months from ship date from Honeywell or six (6) months
after date of installation of the repaired or overhauled Part on the APU, whichever
occurs fi rst. Repair and overhaul warranty is applied at the expiry of the original
equipment, new spare APU and new spare parts warranties, and does not in any
way extend the original warranty periods.
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.
2. Assume round trip shipping costs for failed or non-conforming APUs or Parts
within geographical region; 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 85034
ATTENTION: WARRANTY DEPARTMENT
41 CITATION LONGITUDE • SEPTEMBER 2021
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 a 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.
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 a Part not supplied by Seller; or
42CITATION LONGITUDE • SEPTEMBER 2021
b. Malfunction or failure due to accident, non conformance, 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 INCLUDING, INDIRECT DAMAGES,
LOST PROFITS, OR LOSS OF USE.
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.
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
43 CITATION LONGITUDE • SEPTEMBER 2021
18. TRAINING AGREEMENT
The first retail Aircraft Purchaser will be provided training for one (1) Citation
Longitude 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
700 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;
44CITATION LONGITUDE • SEPTEMBER 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.
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September 2021SD-JET-700-0921