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

iiCITATION LONGITUDE • SEPTEMBER 2021

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

ivCITATION LONGITUDE • SEPTEMBER 2021

Figure 1: Exterior Dimensions ................................................................................................. 3

Figure 2: Interior Dimensions ................................................................................................. 4

Figure 3: Instrumentation ........................................................................................................ 13

Figure 4: Cabin Typical Confi guration .............................................................................. 20

LIST OF FIGURES

1 CITATION LONGITUDE • SEPTEMBER 2021

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]

2CITATION LONGITUDE • SEPTEMBER 2021

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.


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)


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)


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.


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


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.


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.


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.


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.


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.


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.


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


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.


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.



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


• 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


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.


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.


• 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.


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.


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


• 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.


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.


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)


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)


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


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.


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;


(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


(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);


(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


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.


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


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.


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.


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.


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.


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


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.


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.


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


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


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


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;


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