Νόμοι — ΦΕΚ A' 3/2025

Provide Fwd Partition Panels (Includes RH & LH Jepp Storage Cabinets)

Provide Fwd Facing Electric Flushing Recirculating Chemical Toilet

Provide Four (4) VIP Cabin Chairs (Loose Equipment)

Custom Paint Scheme as per above Modifications:

Dual Air Ambulance Configuration as detailed in Part 3A.

Provide Two (2) Medical Attendant Seats (Loose Equipment)

Custom Baggage Web Delivery & Services:

Six (6) Month Extended Airframe & Vendor Warranty covering the period from Aircraft Technical Acceptance in Wichita, Kansas to transfer of title (Does not include Avionics, Engines, Paint, or Interior), and governed by the provisions of Part 2, section 11 b.

One (1) Yr Jepp Electronic Charts Region Subscription (Europe & Mediterranean).

One (1) Yr Fit Mgmt System Database Region Subscription Pkg (Europe & Mediterranean).

Provide Ten (10) Yr's 434-590169-0003-WEB Online Access POH / AFM Revision Services.

Provide Ten (10) Yr's 434-590169-0005-WEB Online Access Fusion Pilot Checklist Revision Services.

Provide Ten (10) Yr's ML-B-300-DVD Online Access Maintenance Library (w/DVD) Revision Services.

Pilot services for Ferry of aircraft from USA to Greece, pursuant to a separate Ferry Flight Services Agreement (Exhibit 10).

Test and acceptance procedures (including test flights).

Transfer of aircraft title and export from USA.

Training as per Part 3 A, 3 B (Section 17) and Exhibit 11.

Program Management and Technical support. Deposit Stage and Balance of Payments Aircraft: An Initial Deposit amounting to USD $5,000,000 is due by Purchaser upon execution of the Purchase Agreement. The Deposit payment shall be made against Sellers on demand guarantee, issued by a U.S. bank. A stage payment (the “First Stage Payment”), amounting to USD $5,311,500 shall be paid by the Purchaser out of Escrow upon the signing of the Aircraft Technical Acceptance Certificate in Wichita, Kansas, as per Exhibit 4. Exhibit 7. 6

AIRCRAFT SPECIFICATION AND DESCRIPTION. a. Aircraft Definition and Price. Seller is selling and Purchaser is purchasing the aircraft identified in Part 1 as (i) described in the Aircraft Specification and Description set out in Part 3 B (“Specification”) of this Agreement with the modifications detailed in Part 3 A (“Air Ambulance Configuration Details”) of this Agreement, if any, (hereinafter the “Aircraft”) for the price set out in Part 1 in (ii) "as is, where is" condition, that is, in its actual state and condition, with no warranties whatsoever except for the conveyance to Purchaser of good title to the Aircraft, free and clear of any and all mortgages, liens, security interests, leases, claims, international interests, encumbrances and rights of others. This Agreement contains the sole description of the Aircraft binding on Seller. Seller is not bound by descriptions, advertisements, statements, or representations about the Aircraft that are not contained in this Agreement. b. Seller Provided Services. Unless otherwise expressly agreed, the price of the Aircraft does not include any additional services, other than those defined in this Agreement. c. Non-FAA Certification Requirements. Purchaser is responsible for the cost of any modification or change to the Aircraft or Aircraft documentation caused by any aviation authority other than the United States Federal Aviation Administration having jurisdiction over Purchaser’s intended country of registration or operation of the Aircraft which are not known by Seller as of the date this Agreement is finally signed, which arise after the date this Agreement is finally signed, or which are not otherwise included in the Total Purchase Price. d. Airworthiness. The Aircraft will be delivered with a standard FAA certificate of airworthiness (FAA Form 8100-2).

CONFIGURATION. Unless otherwise agreed, the Aircraft will be delivered with the manufacturer’s standard default exterior and standard default interior configurations modified for Medical Ambulance as per the details of Part 3 A. Any modifications requested after contract signature to such configurations, if expressly accepted by Seller, may result in an adjustment of the Purchase Price payment schedule and delivery date.

PRICING AND PAYMENT TERMS. Purchaser will pay through the Donor the Seller the Total Purchase Price as specified in Part 1 and any other mutually agreed upon charges pursuant to the terms of this Agreement. 7 below, subject to receiving the letter of Guarantee. This Agreement is binding as of the moment executed copies are exchanged via e-mail between the Parties but will only become effective upon receipt of the Initial Deposit for Aircraft. b. Stage Payment to be paid to escrow, as set out in Part 1. c. Balance of Payment. Pursuant to the Acceptance and Delivery process set out in Article 4 and as further set out therein, the Balance Payment must be made by Purchaser through the Donor to escrow at the time ofmodified technical acceptance and be released to the Seller from Escrow upon signing of the Delivery Receipt in Fargo. d. Acceptable Methods of Payment. The initial deposit must be made in United States dollars by a single wire transfer in accordance with the Wire Instructions set out in 3.d. (i) below. Payment documentation must show that funds came directly from Purchaser through its Donor. (i) Wire Instructions: A. Wire transfers must reflect Donor’s name as originator and be sent to the following Seller’s account as follows: Wiring Instructions to Account of: Bank: Routing #: Bank Swift Code: Address: Final Credit To: Account number: Address: U.S. Bank NA Fargo Jet Center, LLC U.S Bank NA 091300023 USBKUS44 505 2nd Ave. North Fargo, ND 58102 Fargo Jet Center, LLC 1-630-9599-5052 3802 20th St N Fargo, ND 58102 B. Purchaser name and payment reference must be typed on the transfer. C. Instruct the issuing bank to transfer the total value to the beneficiary. D. All bank charges relating to payer's bank are for the account of the payer. Any direction or information seeking to change these Wire Instructions must be confirmed by written amendment to this Agreement. 8 e. Taxes/Custom Charges. The Total Purchase Price does not include any sales, use, personal property, value-added, excise, or similar tax or assessments which may be imposed by any state and/or governmental authority upon this sales transaction, upon the Aircraft and equipment at delivery or thereafter, and use of the Aircraft by Purchaser (collectively “Taxes’), and any such Taxes, if imposed, will be Purchaser’s responsibility. Purchaser is also responsible for (i) any and all import duties or other custom charges (collectively “Custom Charges”), and in particular for any duties applying to the importation of the Aircraft into Greece, and (ii) any withholding taxes, or other charges (collectively “Other Charges”) imposed by any governmental authority at delivery or thereafter (except Seller’s income or gross receipt taxes). Purchaser agrees to pay and indemnify Seller against such Taxes, Custom Charges and Other Charges so that in all instances Seller receives payment, after Taxes, equal to the Total Purchase Price. Purchaser agrees to execute any documentation necessary to avoid the imposition of or to receive an exemption from applicable sales or other taxes. These provisions will inure to any successor or permitted assignee of Purchaser and will survive until twelve (12) months after the expiration of any applicable statute of limitations. Seller is responsible for the payment of its income, gross receipts taxes, and other charges and assessments levied on the Aircraft, its equipment, ownership and use prior to delivery to Purchaser.

ACCEPTANCE AND DELIVERY. On the Ready for Aircraft Technical Acceptance date and on the Ready for Modified Aircraft Technical Acceptance date, Purchaser will review the Aircraft (and following the procedure set out herein accept delivery) at the locations set out in Part 1. a. Review. On the Ready for Aircraft Technical Acceptance date, Seller will present the Aircraft in ready for review condition and Purchaser shall pay (through the donor) the Stage Payment for the Aircraft to Escrow. Purchaser may review the Aircraft in Wichita, Kansas pursuant to Part 3 B (excluding the modification to be performed in Fargo) and pursuant to Customer Acceptance Checklist attached hereto as Exhibit 3, such checklist including a flight test of not more than two (2) hours in duration. The flight test will be controlled by Seller and/or manufacturer and at total of two (2) of Purchaser’s representatives may participate in the flight test. If Purchaser's review reveals any material discrepancy in the Aircraft, Purchaser will immediately notify Seller in writing of any such discrepancy, Seller will correct the discrepancy within 30 days, and if necessary, the Aircraft Technical Acceptance, the Modified Aircraft Technical Acceptance, and the Delivery Date, will be adjusted accordingly. Following cure of any such discrepancy, the parties will continue with the Aircraft acceptance and Purchaser will sign a Technical Acceptance Certificate for Aircraft, set out and attached hereto as Exhibit 4, which constitutes Purchaser’s agreement that the Aircraft conforms to the Specification and other requirements of this Agreement. Upon receipt of a copy of the Technical Acceptance Certificate executed by Purchaser, the Escrow Agent shall release the Stage Payment for the Aircraft to Seller. In the event of postponement of the Technical Acceptance due to the need to correct discrepancies, the reasonable travel and accommodation costs of the Purchaser’s representatives will be borne by the Seller. 9 such minor deficiencies the extent of these and remedial action for their removal by the Seller shall be jointly agreed between the Purchaser and the Seller during the inspection and acceptance process. In the event that any of the Aircraft is affected by a major discrepancy (affecting form, fit, function and performance) the Parties shall agree, acting reasonably, a remedy plan (technical and/or commercial) in order to adjust the identified major discrepancies. b. Review - North Dakota. Following Purchaser’s execution of the Aircraft’s Technical Acceptance Certificate and receipt of any payment due, Seller will ferry the Aircraft to Fargo, North Dakota for the installation of the Modifications listed as per part 3 A and Exhibit 2. At the same time, the Purchaser will deliver to Spectrum Aeromed at its facilities in Fargo the medical equipment to be installed on the Aircraft after completion of the Modifications, as per Exhibit 8. Approximately twelve (12) days prior to the completion of the Modifications, Seller will notify Purchaser of the Ready for Modified Aircraft Technical Acceptance date by letter sent to Purchaser’s Address so Purchaser can make plans to arrive in Fargo, North Dakota for the inspection and acceptance of the Modifications. On the date provided by Seller, Purchaser will inspect the final Aircraft configuration as per Part 3 A and Exhibit 2 and the Modifications for the Aircraft in accordance with the Modifier Acceptance Checklist, set out and attached hereto as Exhibit 5, and accept that the Modifications have been completed. Prior to this inspection process, the medical equipment as indicated in Part 3 A, Exhibit 2 and Exhibit 8, may be trial fitted to the Aircraft using the appropriate equipment mounting brackets (such fitting only to be regarded as a material condition or a condition precedent to Delivery if it arises out of the Aircraft configuration and it jeopardizes the functioning of the equipment as per Exhibit 8). Purchaser will then sign a Modified Aircraft Technical Acceptance Certificate, set out and attached hereto as Exhibit 6, which constitutes Purchaser’s agreement that the Modifications conforms to the Agreement. The Purchaser shall not be entitled to reject the Aircraft purely on account of non-material discrepancies and in the event of there being any such non-material discrepancies the extent of these and remedial action for their removal by the Seller shall be jointly agreed between the Purchaser and the Seller during the inspection and acceptance process. In the event that any of the Aircraft is affected by a material discrepancies (affecting form, fit, function and performance) the Parties shall agree, acting reasonably, a remedy plan (technical and/or commercial) in order to adjust the identified material discrepancies. If the Parties are unable to reach an agreement on a remedy plan and the Aircraft cannot be delivered with all material discrepancies duly rectified within the Delivery Date, the provisions of Article 7 shall apply. c. Delivery Date Events. (i) Owner’s Trust. Prior to the Delivery Date of Aircraft, the Purchaser, if it chooses to keep the aircraft registered in the U.S, will establish an Owner’s Trust to enable registration in the U.S. on the FAA registry. Seller will assist with establishing such trust and will cover fees charged by the Owner Trustee. (ii) Delivery. Following the procedure set out in Article 4.a. and 4.b., these two events must occur on the Ready for Modified Aircraft Technical Acceptance Date: (i) if not previously paid, Purchaser will pay the full balance of the Purchase Price and any amount due to Seller under this Agreement for other known charges, pursuant to the provisions of Part 2, section 4.c. (iv) below; 1 0 (iii) Escrow Services and Closing Procedures: The parties agree Insured Aircraft Title Service, LLC will, as escrow agent (“Escrow Agent”), hold the Stage Payment at Aircraft Technical Acceptance and the Balance Due at Delivery and documents necessary to consummate the sale/purchase of Aircraft. Purchaser through the donor will make the relevant Payments for the Aircraft in United States dollars by wire transfer to the Escrow Agent as follows: INSTRUCTIONS FOR USD PAYMENTS TO BANK OF AMERICA U.S. & INTERNATIONAL WIRE TRANSFERS BENEFICIARY BANK: BANK OF AMERICA ABA #026009593 211 N Robinson Ave, Oklahoma City, OK 73102 SWIFT BOFAUS3N CREDIT: INSURED AIRCRAFT TITLE SERVICE ACCOUNT # 0028 6358 5210 21 E. Main Street, Suite 100, Oklahoma City, OK 73104 PHONE: 405-681-6663 FAX: 405-681-9299 ADVISE: JOAN ROBERTS EMAIL: jroberts@insuredaircraft.com REFERENCE: AIRCRAFT REGISTRATION AND SERIAL NUMBER (iii) When Seller has provided the Escrow Agent with a copy of the Aircraft Technical Acceptance signed by the Purchaser, the Escrow Agent will release the Stage Payment to Seller. (iv) When the Seller has provided the Escrow Agent with a copy of the Delivery Receipt and Ferry Completion Certificate signed by Purchaser for Aircraft, the Escrow Agent will release the Payment to Seller. (v) After confirming that all payment due have been received by Seller, Seller will then instruct the Escrow Agent to release the Owner Trust Documents for the delivered Aircraft to Purchaser, thereby transferring beneficial ownership to Purchaser. 1 1 accordance with those terms. If the Parties do not agree on this matter, the Escrow Agent shall withhold payment until an agreement is reached between the Parties or a final judgement is passed. d. Failure to Review/Compliance with Delivery Date Events. If Purchaser fails to (i) review the Aircraft or waive review, or (ii) comply with all Review, Acceptance and/or Delivery Date Events set out in Article 4, Purchaser will be in breach of this Agreement and the provisions of Article 6 will apply. e. Delivery. Seller will deliver the Aircraft EXW (INCOTERMS 2010) at the Delivery Location specified in Part 1. If this Agreement is cancelled or terminated for any reason and Purchaser is entitled to reimbursement, the reimbursement is conditioned upon (i) Purchaser discharging any registration created by or through it or by persons claiming by or through it, and (ii) Purchaser presenting Seller with evidence of the discharge. Seller will be entitled to offset any costs, fees, or expenses incurred as a result of Purchaser’s failure to discharge the registration.

RISK OF LOSS; TRANSFER OF TITLE; REGISTRATION. After the Aircraft has been accepted by Purchaser, Seller has received and accepted all monies owed as set out in Article 4, the Aircraft has been tendered for Delivery at the Delivery Location, and Purchaser has executed the delivery documents as further outlined in Part 2, section 4.c., then Seller will furnish to Purchaser a Bill of Sale transferring ownership of Aircraft to Purchaser free and clear of all liens, privileges, encumbrances, charges, and rights of others either directly to Purchaser or, at Purchaser's option to the trust owner. Risk of loss for the Aircraft will transfer from Seller to Purchaser upon Seller’s delivery of the Bill of Sale to Purchaser. Purchaser has sole responsibility for (i) obtaining all permits, licenses, and approvals for importation of the Aircraft into Greece and operation of the Aircraft, (ii) taking title to the Aircraft pursuant to Part 2, section 4 c (i) or registering the Aircraft with any other applicable aviation registry and timely providing any information to Seller necessary for such registration, and (iii) operating the Aircraft upon delivery.

DEFAULT BY PURCHASER. This Agreement may not be cancelled or terminated by Purchaser except as set out in this Agreement. The following events will be considered a default by Purchaser under this Agreement: (i) Purchaser informs Seller by any means that it will not take delivery of the Aircraft on the Delivery Date and Seller does not agree in writing to a later Delivery Date in which case Seller will inform of the reason (ii) Purchaser fails to make, when due, any payment for which it is responsible under this Agreement, (iii) Purchaser fails to comply with the provisions of Article 4.b. and/or 4.c., or (iv) Purchaser breaches any of its other obligations under this Agreement and such breach is not cured within five (5) calendar days of the date of Seller’s notice of default to Purchaser. The parties agree that Seller’s damages in the event of such breach are difficult to quantify, but that the liquidated damages identified herein are the parties reasonable estimate of those damages. In the event of any default by Purchaser prior to Aircraft delivery, including any breach of Article 4, 1 2 damages and thereafter the Agreement will be terminated and the parties’ rights and obligations under this Agreement will end. The parties agree that if Purchaser fails to obtain any permits and pay any fees as may be necessary for the Aircraft to be exported from the United States on the Delivery Date as set out in Article 4.b. (iii), Seller is entitled to receive from Purchaser reasonable liquidated damages for this default in the amount of $1,000 per day from the day after the Delivery Date until the Aircraft leaves the Delivery Location. The Aircraft will not be released until Purchaser has paid in full these post-delivery liquidated damages. Purchaser will indemnify and hold Seller harmless from and against all losses, damages, claims, liabilities, and causes of action of every kind, character, or nature arising out of or related to Purchaser’s failure to cause the Aircraft to be exported from the United States on the Delivery Date. Such liability is limited to the total contract value.

AIRCRAFT DELIVERY DELAY; FORCE MAJEURE; RETURN OF DEPOSIT AS SOLE REMEDY. a. Delay for Any Cause. If Seller fails to deliver the Aircraft on the Delivery Date, except as the result of a Force Majeure Event which is regulated in Article 7.b., Seller will not be liable to Purchaser for any damages if the Aircraft is delivered within 60 calendar days after the Delivery Date or the parties agree to a later Delivery Date as set out in Article 7.c. (i). b. Force Majeure Event. If Seller fails to the deliver the Aircraft on the Delivery Date and the failure to timely deliver is the result of a Force Majeure Event which includes, but is not limited to, strikes, lockouts, or other labor or industrial disturbances; riots; epidemics; pandemics (e.g. And not limited to coronavirus); social distancing, quarantine, restrictions on travel, civil unrest; rebellion; war; natural disaster, terrorism; war; governmental actions; inactions, or regulations (including, but not limited to, preemptive priority allocation rights of the any government and Seller’s inability to obtain any governmental certification, export, or airworthiness approval for the Aircraft); fire; weather; delay in supplier deliveries; or other eventualities whether or not specifically enumerated in this contract and beyond Seller’s control, Seller will not be liable to Purchaser for any damages if the Aircraft is delivered within 200 calendar days after the Delivery Date or the parties agree to a later Delivery Date as set out in Article 7.c.(ii). If Purchaser fails to timely fulfill any of its obligations as a result of a Force Majeure Event, Purchaser must send a formal notification to the Seller without delay, stating the nature of the situation or of the event, its likely duration and foreseeable effects. In case the Purchaser invokes a Force Majeure Event to request or claim any postponement of the Aircraft delivery and acceptance, the parties will mutually set a new delivery date upon which the delivery and acceptance will take place. c. Purchaser’s Damages. (i) If Seller fails to deliver the Aircraft after the Delivery Date as contemplated in Article 7.a. other than in connection with a Force Majeure Event, the parties can, on or before the 61st day after the Delivery Date, agree to a later delivery date. If the parties agree to a later delivery date within the time specified, Seller will not be liable for damages if the Aircraft is delivered on the 1 3 after the Delivery Date, Seller will return to the Donor who made the payment all paid deposits and any payment received by Seller under the Agreement with interest (1 months LIBOR). Seller will pay Purchaser’s documented travel costs to Fargo and/or Wichita limited to a maximum amount of USD 5,000.00, or any other costs paid directly by Purchaser to Seller, with interest (one month LIBOR) and the parties will have no further liability to each other. The parties agree this is a fair and reasonable amount of liquidated damages to fully compensate Purchaser for Seller’s default. (ii) Subject to Purchaser’s acceptance of a late Delivery Date pursuant to section 7.c. (i), Purchaser shall be entitled to claim from Seller, as liquidated damages, an amount equal to USD 3,500 per day (the “Delay Fee”) commencing with the sixty first (61st) day after the original Delivery Date, and ending on the final delivery date of the Aircraft to the Purchaser under this Agreement. The Delay Fee shall be credited toward the balance of the Purchase Price which is due from Purchaser on delivery of the Aircraft. Notwithstanding the foregoing, in no event shall the Delay Fee exceed one percent (1%) of the total Purchase Price due by Purchaser under the Agreement. (iii) If Seller fails to deliver the Aircraft within 200 calendar days after the Delivery Date as contemplated in Article 7.b., due to a Force Majeure Event, the parties can, on or before the 200th day after the Delivery Date, agree to a later delivery date. If the parties agree to a later delivery date within the time specified, Seller will not be liable for damages if the Aircraft is delivered on the delivery date agreed to by the parties. If the parties do not agree to a later delivery date within the time specified, the parties’ rights and obligations under this Agreement will end and the parties will have no further liability to each other except, however, Seller will return to the Donor who made the payment all paid deposits and any payment received by Seller under the Agreement with interest (1 months LIBOR). In addition, Seller will pay Purchaser’s documented travel costs to Fargo and/or Wichita limited to a maximum amount of USD 5,000.00, or any other costs paid directly by Purchaser to Seller with interest (one month LIBOR) and the parties will have no further liability to each other. The parties agree this is a fair and reasonable amount of liquidated damages to fully compensate Purchaser for Seller’s default. (iv) The parties agree that the remedies outlined in this clause 7 are Purchaser’s sole remedy for Seller’s failure to deliver or to perform any of its obligations under this Agreement.

ASSIGNMENT. Purchaser may not assign this Agreement or any right, title, interest, duty, or obligation under this Agreement (collectively “Assignment”) without Seller’s prior written consent. Seller will not consent to an Assignment to any business entity whose name includes one or more of Seller’s trademarks or trade names. A direct or indirect change of more than fifty-one percent (51%) of Purchaser’s ownership interest will be deemed an Assignment and breach of this Agreement unless Seller has specifically consented to the change in writing. Any attempted Assignment by Purchaser that does not conform with this Agreement will be null and void, constitute a breach of this Agreement, and Seller will have the remedies set out herein. At no time prior to delivery will Purchaser engage in speculation or any attempted selling or marketing of the Aircraft or its delivery position either directly or through a third party. 1 4 performed wholly, save for the Modified Aircraft Technical Acceptance, within the State of Kansas, and any dispute arising under, out of, or related in any way to this Agreement, the legal relationship between Seller and Purchaser or the transaction that is the subject matter of this Agreement (collectively “Dispute”) will be governed and construed under the laws of the State of Kansas, USA, exclusive of conflicts of laws. Any Dispute will be adjudicated solely and exclusively in the United States District Court for the State of Kansas, in Wichita, Kansas, or, if that court lacks jurisdiction, Kansas state courts of the 18th Judicial District. Each of the parties (i) consents to the exclusive, personal jurisdiction of these courts and, by signing this Agreement, waives any objection to venue of these Kansas courts, and (ii) agrees that final judgment brought in these courts will be conclusive and binding upon the parties and may be enforced in any other courts with jurisdiction over the parties. The parties waive any right they may have to trial by jury in any legal proceeding directly or indirectly arising out of or relating to this Agreement. The present Agreement is entered into by the Purchaser in its private capacity and the Purchaser hereby waives any form for protection and immunity of whatsoever description to which it may be entitled by virtue of it being and/or purporting to act as a sovereign state.

COMPLIANCE WITH LAWS. a. Mutual Compliance. Both parties will comply with all applicable laws, rules, and regulations, including, but not limited to, all United States export, re-export, import and customs laws and regulations, the USA Patriot Act, the U.S. Foreign Corrupt Practices Act, and the U.K. Bribery Act. Purchaser will obtain authorizations, permits, or licenses as required. Purchaser will provide Seller, as requested by Seller, with documentation such as import and re-transfer statements or certificates and information reasonably related to Seller’s compliance with applicable laws and regulations. If Purchaser fails to provide Seller with requested documentation or information, Purchaser will be in breach of this Agreement and Seller will have the remedies set out herein. If Seller is unable to secure any required authorizations, permits, or licenses or if the transaction contemplated by this Agreement becomes prohibited by applicable law, executive order or regulation issued by the U.S. Government or other foreign government or political body to which Seller is subject, then the provisions of Article 7.b. will apply. b. End-Use/User Confirmation. Purchaser will submit a completed End User Certification (reference Exhibitl included with this Agreement) at least thirty (30) calendar days prior to when the Aircraft is Ready for Delivery. If this Agreement is executed within thirty (30) calendar days of the Ready for Delivery date, Purchaser will submit the completed End User Certification prior to Aircraft delivery. This certification must identify the (i) end-user of the Aircraft, (ii) end-use of the Aircraft, and (iii) country(s) where the Aircraft will be registered and operated. If this information changes prior to Aircraft delivery Purchaser will submit an updated End User Certification.

LIMITED AIRCRAFT WARRANTY. a. Seller’s Written Limited Aircraft Warranty. THE AIRCRAFT IS BEING SOLD TO PURCHASER AND ACCEPTED BY PURCHASER AT DELIVERY HEREUNDER IN 1 5 ACKNOWLEDGES THAT AS OF THE DELIVERY DATE, WITH THE EXCEPTION OF THE WARRANTY OF TITLE, THERE ARE NO 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 THEREOF. SELLER SPECIFICALLY DISCLAIMS AND EXCLUDES ALL OTHER WARRANTIES, INCLUDING, BUT NOT LIMITED TO, ANY IMPLIED WARRANTY OF MERCHANTABILITY OR FITNESS FOR A PARTICULAR PURPOSE, AIRWORTHINESS, SERVICEABILITY, VALUE, CONDITION, DESIGN, COMPLIANCE WITH SPECIFICATIONS, AGE, OPERATION, PERFORMANCE, QUALITY OF THE MATERIAL OR WORKMANSHIP OF THE AIRCRAFT OR ANY PART THEREOF, CONFORMITY OF THE AIRCRAFT TO THE DESCRIPTION OR CONDITIONS SET FORTH HEREIN OR OTHERWISE PROVIDED TO PURCHASER OR AS TO THE ADEQUACY OF ANY AIRCRAFT DOCUMENTS, OR AS TO THE ABSENCE OF LATENT OR OTHER DEFECTS, WHETHER OR NOT DISCOVERABLE AND WHETHER KNOWN OR UNKNOWN, OR AS TO THE ABSENCE OF ANY INFRINGEMENT OF ANY PATENT, TRADEMARK OR COPYRIGHT, OR ANY OTHER REPRESENTATION OR WARRANTY WHATSOEVER. 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, DIMINUTION 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 THE LIMITED AIRCRAFT WARRANTY. PURCHASER WAIVES, AS AGAINST SELLER, ITS OFFICERS, DIRECTORS, EMPLOYEES, AGENTS AND AFFILIATES, ALL RIGHTS, REMEDIES AND DAMAGES, INCLUDING INCIDENTAL AND CONSEQUENTIAL DAMAGES, EXPRESS OR IMPLIED, ARISING BY LAW OR OTHERWISE, IN CONTRACT OR IN TORT, WITH REGARD TO THE AIRCRAFT. b. Manufacturer Warranties and services. To the extent that any warranties are in effect with respect to the Aircraft (other than warranties which by their terms are non-assignable or which would be extinguished by their assignment), Seller hereby agrees to assign and transfer such to Purchaser including any balances to the extent they are transferable, at the time of delivery. In particular Seller assigns and transfers to Purchaser all warranties under Part 3 B and Exhibit 9 of the Agreement. If there are any subsisting warranties which could not be assigned despite Seller's commercially reasonable efforts, or if any necessary consents of such assignment were refused, then Seller shall, at Purchaser’s costs and expense, take such action as Purchaser may reasonably request to enforce such manufacturer's or supplier's warranties or any other of Seller's rights, interests and benefits mentioned above. For the avoidance of doubt, the Aircraft is sold without engine and airframe maintenance programs. Seller will also assign and transfer to Purchaser the benefit of any training program and other services provided by the Aircraft manufacturer. 1 6 or modifications. Seller disclaims all liability in contract or in tort, including, without limitation, negligence and strict tort liability, with respect to such exclusions. c. Other Warranties. The equipment and installation listed in Part 1, under Modifications, are not warranted directly by Fargo Jet Center. The Modifications, equipment and installation are warranted directly by Spectrum Aeromed. Copies of the applicable warranties are attached hereto as Exhibit 9 Reference to “Seller” in the Spectrum Aeromed warranty is intended as a reference to Spectrum Aeromed. Equipment and component warranties are governed by the original equipment manufacturer (OEM). Seller does not warrant equipment or components of the equipment or component. Seller does not warrant Modifications performed by a third party. If Modifications are performed or provided by other third parties (i.e. any party other than Seller, Textron Aviation, Spectrum Aeromed or subcontractors employed by them), Purchaser will receive any warranties provided by those parties. Seller disclaims all liability in contract or in tort, including, without limitation, negligence and strict tort liability, with respect to modifications, equipment and components supplied by third parties. d. Laws and Limitations. The laws of some states and jurisdictions do not permit certain limitations on warranties or remedies. If such laws apply, the foregoing exclusions and limitations are amended insofar and only insofar as required by law. e. Modified Aircraft. If, after Aircraft delivery by Seller, Purchaser installs equipment controlled by the United States International Traffic in Arms Regulations (“ITAR”) or the United States Export Administration Regulations (“US EAR - 600 Series equipment”) on the Aircraft, Purchaser will immediately notify Seller, Seller’s written Limited Aircraft Warranty will be null and void, and other manufacturers’ warranties may also be null and void. Seller and associated service providers (collectively “Service Providers’) will comply with all ITAR and US EAR regulations in providing service and support for modified Aircraft, including prohibitions against dealing with embargoed countries. Without prior U.S. government authorization, which may be granted or denied in the U.S. government’s sole discretion and may take several months to obtain, Service Providers may not be able to support modified Aircraft. Purchaser will provide information requested by Service Providers to support U.S. government applications to export parts and services. If Purchaser fails to provide such information or Service Providers fail to obtain required U.S. government authorizations for reasons beyond their control (even though Service Providers have no obligation to seek such authorization), then Service Providers will not have any further obligation to support Purchaser’s modified Aircraft.

LIMITATION OF LIABILITY. IN NO EVENT WILL EITHER PARTY BE LIABLE UNDER THIS AGREEMENT PURSUANT TO ANY CONTRACT, NEGLIGENCE, STRICT LIABILITY, TORT, WARRANTY, OR OTHER LEGAL OR EQUITABLE THEORY FOR ANY INCIDENTAL, SPECIAL, CONSEQUENTIAL, PUNITIVE, EXEMPLARY, MULTIPLE OR INDIRECT DAMAGES OF ANY NATURE WHATSOEVER, INCLUDING, BUT NOT LIMITED TO, LOSS OF PROFITS OR GOODWILL, LOSS OF USE, 1 7 HAS BEEN ADVISED OF THE POSSIBILITY OF SUCH DAMAGES. THE PARTIES ACKNOWLEDGE AND AGREE THAT THESE LIMITATIONS OF LIABILITY REFLECT THE ALLOCATION OF RISK SET FORTH IN THIS AGREEMENT AND THAT, IN THE ABSENCE OF SUCH LIMITATIONS, THE TERMS OF THIS AGREEMENT WOULD BE SUBSTANTIALLY DIFFERENT

SEVERABILITY AND WAIVER. If any provision of this Agreement is or becomes null or unenforceable by operation of law, the other provisions will remain valid and enforceable. The waiver by either party of a breach of any provision of this Agreement will not constitute a waiver of any subsequent breach of the same or any other provision nor will it be considered a waiver of the provision itself.

OUTSIDE COMPLETION SUPPORT. Purchaser acknowledges and agrees that Seller has no responsibility to provide any documentation or data to Purchaser or Purchaser's designated customizing supplier to support any outside completion effort (i.e. any completion effort provided by any party other than the Aircraft manufacturer) not included as part of this Agreement. If, in Seller’s sole discretion and upon its terms, such documentation or data is supplied to Purchaser’s designated customizing supplier, any delays or costs that result from such support will be the sole responsibility of Purchaser and its designated customizing supplier.

NOTICES. Except as otherwise provided herein, notices required under this Agreement will be in writing, in English, and sent by electronic mail (“E-Mail”) with confirmation; by courier; or by registered mail return receipt requested. Notice to Seller will be sent to Seller’s E-Mail address or address set forth in this Agreement. Notice to Purchaser will be sent to Purchaser’s address set forth in this Agreement or to Purchaser’s E-Mail address provided by Purchaser. E-Mail addresses and addresses may be changed by either party upon notice, per the terms of this Article, to the other. All notices will be deemed given on the date they are transmitted or placed in the hands of courier or post for delivery.

ORDER OF PRECEDENCE. In the event of an inconsistency or conflict between or among the provisions of this Agreement, the inconsistency or conflict will be resolved by giving precedence in the following order: Part 1, Part 2, exhibits. 1 8 Captions used in this Agreement are for convenience of reference only and will not be deemed a part of this Agreement or used in construing its meaning. This Agreement constitutes the entire agreement between the parties with respect to its subject matter and supersedes all prior written or oral agreements, representations, negotiations, proposals, or discussions between the parties with respect to its subject matter. No modification to this Agreement will be effective unless in writing as an Amendment to this Agreement, which specifically references this Agreement, and is signed by both parties (“Amendment(s)”) except, however, if the Aircraft has been identified with a serial number, Purchaser can change to a different serial number Aircraft if the new serial number Aircraft has the identical specifications, configuration, and pricing without an Amendment to this Agreement, in which case the Seller will provide explanation to the Purchaser. This Agreement is binding on Seller and Purchaser, their successors, heirs, executors, administrators, and permitted assignees. This Agreement is to be construed as if drafted jointly by the parties and no presumption will arise favoring or disfavoring either party by virtue of the authorship of any provision of this Agreement. The provisions of this Agreement survive closing and delivery of any documents of title with respect to the Aircraft. Purchaser hereby consents to receiving general business and product information, promotions, offers, invitations and various marketing material from Seller and its affiliates by mail, E-Mail, phone or other method.

LIABILITY INSURANCE The Seller shall maintain a general liability insurance covering its maximum aggregate liability under the Agreement. The maximum payable amount under such insurance shall not exceed the initial deposit and stage payments. The Seller shall maintain this insurance in full force, throughout the term of the Agreement and until the aircrafts is delivered in Greece. A copy of the insurance contract and coverage will be shared with the Purchaser, one (1) month prior the delivery of the Aircraft.

NETTING OF CLAIMS AND LIABILITIES The netting-out of claims and liabilities arising from this Agreement, shall be permitted between the Purchaser and the Seller.

WAIVER OF RIGHTS The present Agreement is entered into by the Purchaser in its private capacity and the Purchaser hereby waives any form for protection and immunity of whatsoever description to which it may be entitled by virtue of it being and/or purporting to act as a sovereign state. The omission of a Party to enforce the strict fulfilment of any provision of the Agreement or the failure or any delay by a Party in the exercise of any right or redress claims shall not be construed as a waiver of the right to claim remedy and may not result in a reduction in the obligations resulting from the Agreement. 1 9 claim, cause of action, remedy, or right of any kind.

CONFIDENTIALITY. The terms, conditions, and pricing of this Agreement are confidential, and Purchaser may not disclose such to any third party, in whole or in part, except as may be necessary to carry out its obligations under this Agreement.

DATA PRIVACY. Seller may receive or retain Personal Data (defined below) from Purchaser in connection with the purchase, registration or ongoing service or support of the Aircraft. This may include Personal Data of Purchaser, its employees, agents and/or other authorized representatives involved with the operation, maintenance, support and training for the Aircraft (collectively “Users”). Personal Data may include any User’s first and last name, email address, telephone number, record of purchases, training programs, and other information as requested to facilitate or complete delivery of products, services or support concerning the Aircraft including the provision of ongoing support, maintenance, repair and training. Seller will process Users' Personal Data only as necessary for this transaction as set out herein and to enable the continuous improvement, marketing and support of Seller's products and services.

BINDING CONTRACT. This Agreement is binding as of the moment executed copies are exchanged via e-mail between the Parties but will only become effective upon receipt of the Initial Deposit for Aircraft By signing below, the signatories to this Agreement verify they have read the complete Agreement, understand its contents and have full authority to bind and do hereby bind their respective parties.

ELECTRONIC TRANSACTIONS. Should the parties mutually agree to execute this Agreement and Amendments electronically through Seller’s e-signature vendor Purchaser agrees to accept communications from Seller’s esignature vendor. Electronic signatures will have the same legal significance as written signatures pursuant to the Electronic Signatures in Global and National Commerce Act and the Kansas Uniform Electronic Transactions Act.

COUNTERPARTS. This Agreement may be signed in counterparts. Signature scanned and sent to the other party via E-Mail or similar methods will be binding. Each counterpart will be deemed an original for all purposes and together they will constitute one and the same instrument. 2 0 PURCHASER: HELLENIC MINISTRY OF HEALTH (“MOH”) By: Name :5mDotJ Nitons 66oR b>^i5 ^ Title: SELLER: FARGO JET CENTER, LLC 2 2 (UTILITY INTERIOR) Specification and Description, October 2023 Revision B (Serial Number FM-110 to TBD), as enclosed with the agreed modifications as defined in the following.

Military Registration The aircraft will be registered and operated by Hellenic Air Force, under Military registration.

Performance Data All performance data is based on a standard aircraft configuration as described in Part 3B and after Medivac FAASTC Number: SA1213CH is applied. There will be adoptions developed for the specific requirements which will lead to change in this STC. Air Ambulance Configuration Details 2200 SERIES POWERED MODULE Two (2) Spectrum 2200 Series will be installed, including the below equipment: • Base contains a 1,000-watt inverter, 3,500 Liter oxygen bottle, dual air pumps (11 Lpm @ 50 psi each), and a vacuum pump (14 Lpm @ 14 in. hg) • Remote fill port for oxygen • Four (4) AC outlets (230-volt) and One (1) DC Outlet (28-volt) • Circuit breakers • Four (4) IV mounts to attach Spectrum modified IV poles and/or Patient Loader • Seat Rail Adapter STRETCHER Used to transport patient to and from the aircraft; attaches to Module Base. • 2” foam pad (operating room grade) • Pad covered with Staph-Check bacteriostatic, flame retardant and anti-static material • Pneumatically assisted fully adjustable backrest • Dual left and right armrests • Quick release safety belt harness STRETCHER 1 (FWD) • Length: 76” (195 cm) 2 3 STRETCHER 2 (AFT) • Length: 72” (183 cm) • Weight: 40 lbs. (18.14 kg) SPECTRUM MEDICAL EQUIPMENT DETAIL QTY ITEM 2 2200-016 Ambulance Module - 28-volt input, 230-volt output w/ European style outlets, 1000-watt inverter, Drager DIN pneumatics connectors (oxygen, air, vacuum). No overhead 1 6302 Seat Rail Adapter for connecting system to aircraft floor. 1 6311 Adapter Mechanism Assembly 1 1213-002 Stretcher (195 cm), 5-point shoulder/chest belt, dual leg belts. 1 1213-001 Stretcher (183cm), 5-point shoulder/chest belt, dual leg belts. 2 SLA001-1 Stretcher Lock for systems with brownline mounting rail. 2 S LA-001-3 Stretcher Lock for systems with brownline mounting rail. 2 1403-015 Stretcher Bridge - Mounts directly to stretcher 2 650272 I.V. Pole w/ adjustable height and four IV Hooks 4 W0588 2 4 1 1 1 1 1 Overhead IV Hook. Secures to the center ceiling tracks. Each hook can hold at least two IV bags. 400187 Oxygen D-Cylinder Mount for Stretcher Bridge W0973, Medical Device Mount Mount for Stryker Lifepak 15 defibrillator/monitor W0971, Medical Device Mount Mount for Draeger Oxylog VE300 ventilator W0969, Medical Device Mount Mount for Dual Braun Space Infusomat 400159 Stretcher Bridge Adapter 400189 Cabin sidewall brownline mount HPO-01-1 Electrical Installation Kit - interface to provide aircraft power to Spectrum Aeromed systems. SP-KT-84-1 Installation Kit- Sidewall Brownline (Extended) SP-KT-85-1 Installation Kit- Pneumatic All gas outlets in Draeger style; one (1) 02 outlet above each patient station; one (1) air outlet above each patient station, no LOX, no overboard vent. SP-KT-86-1 Installation Kit- Sidewall Electrical Five (5) 230VAC european style electrical sockets above each patient station (10 in total) 650005 Manual patient loader - assists with loading the patient into the aircraft. Folds for easy storage. Includes storage bag. 400005 Electric Loader- no lift patient loader, folding, w/ storage bag. 2 5 3 650299 Loader Bar (to be used for loading with single stretcher setup) 1 1430-014 Cabinet - 2 Drawer w/ rails for mounting on top. 1 W0576 KA 350 FWD RH Cabinet Rev-A 1 W0589 Table Assembly 1 1305-015 Incubator Transport System w/ housing for 2 E cylinder bottles and mounts for a Voyageurlncubator. Does not include cylinders. Fits 20 / 2200 System 1 Oxygen Filling Adapter Kit Oxygen Filling Adapter Kit - CGA540 to various different connections TRAINING Equipment Familiarization Training for Medical Crews: This training provides comprehensive hands-on familiarization with the Spectrum Aeromed equipment and integrated systems for the medical crews. It covers general equipment functions, including operation of integrated systems (oxygen, electrical, pneumatic), stretcher loading/unloading, handling and mounting of medical equipment, pre- and post-operational activities and cleaning procedures. Training Details: • Duration: 4 hours • Location: on the aircraft (no classroom) • Max. Attendees: up to 5 students • Training Material: Based on Instructions for Continued Airworthiness (no training handbook) 2 6 receives a trainings certificate. 2 7 2 8 K I N G AI R 3 6 0 C ( U T I L I T Y I N T E R I O R ) SPECIFICATION AND DESCRIPTION OCTOBER 2023 REVISION B SERIAL NUMBER FM-110 TO TBD KING AIR 360C ‘UTILITY INTERIOR’ SERIAL NUMBER FM-110 TO TBD OCTOBER 2023 REVISION B THE AIRCRAFT........................................................................................................... 2

GENERAL DESCRIPTION...................................................................................... 2 1.1 Certification...................................................................................................... 2 1.2 Purchaser’s Responsibility.............................................................................2 1.3 Approximate Dimensions.............................................................................. 5 1.4 Design Weights and Capacities................................................................... 5

PERFORMANCE.................................................................................................... 6

DESIGN LIMITS......................................................................................................6

FUSELAGE............................................................................................................. 7 4.1 Design and Construction...............................................................................7 4.2 Nose Section................................................................................................. 7 4.3 Interior Spaces...............................................................................................7 4.4 Aft Fuselage ................................................................................................ 7 4.5 Cargo Door....................................................................................................7

WING......................................................................................................................7

EMPENNAGE.........................................................................................................7

LANDING GEAR..................................................................................................... 8 7.1 Design and Construction................................................................................8 7.2 Nosewheel Steering......................................................................................8 7.3 Brakes and Tires............................................................................................8

PROPULSION.........................................................................................................8 8.1 Powerplant...................................................................................................... 8 8.2 Propellers...................................................................................................... 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 TABLE OF CONTENTS 1 KIN G AIR 3 6 0 C UTILITY IN TERIOR · OCTOBER 2 0 2 3 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

FLIGHT COMPARTMENT....................................................................................11 10.1 General.......................................................................................................... 11 10.2 Instrumentation.......................................................................................... 12 10.3 Avionics........................................................................................................13 10.3.1 Flight Displays..................................................................................... 13 10.3.1.1 Primary Flight Displays (PFDs)....................................................13 10.3.1.2 Multi-Function Display (MFD)..................................................... 13 10.3.2 Radio System..................................................................................... 14 10.3.2.1 Global Positioning System (GPS)...............................................14 10.3.2.2 Very High Frequency Radio (VHF).......................................... 14 10.3.2.3 Navigation Receivers................................................................14 10.3.3 Audio System..................................................................................... 14 10.3.4 Cockpit Voice Recorder (CVR)..........................................................14 10.3.5 Flight Management System (FMS)....................................................14 10.3.6 Electronic Charts............................................................................... 15 10.3.7 Surface Management System.......................................................... 15 10.3.8 Distance Measuring Equipment (DME).............................................15 10.3.9 Engine Indicating and Crew Alerting System (EICAS)....................15 10.3.10 Flight Guidance System (FGS).........................................................15 10.3.11 Autothrottle..........................................................................................16 10.3.12 Air Data System................................................................................ 16 10.3.13 Attitude/Heading Reference System (AHRS)................................. 16 10.3.14 Transponders with ADS-B Out Capability.......................................16 10.3.15 Weather Radar.................................................................................16 10.3.16 Radio Altimeter................................................................................. 17 10.3.17 Traffic Collision Avoidance System (TCAS II)...................................17 KING AIR 3 6 0 C UTILITY INTERIOR · OCTOBER 2 0 2 3 i i 10.3.19 Synthetic Vision Technology (SVT).................................................. 17 10.3.20 Emergency Locator Transmitter (ELT).............................................17 10.3.21 Standby Instrumentation..................................................................17 10.3.22 Onboard Maintenance System...................................................... 17

INTERIOR............................................................................................................. 18 11.1 C abin......................................................................................................................... 18 11.2 Windows.......................................................................................................18 11.3 Cabin Lighting System ............................................................................... 18 11.3.1 Direct Lighting...................................................................................... 18 11.3.2 Indirect Lighting..................................................................................18 11.3.3 Emergency Lighting............................................................................18

EXTERIOR............................................................................................................19 12.1 Exterior Storage ......................................................................................... 19

LOOSE EQUIPMENT.......................................................................................... 19

EMERGENCY EQUIPMENT...............................................................................20

DOCUMENTATION AND TECHNICAL PUBLICATIONS.....................................20

MAINTENANCE TRACKING PROGRAM ...........................................................21

LIMITED WARRANTIES........................................................................................21 17.1 Limited Aircraft Warranty............................................................................22 17.2 Summary of P&WC’s New Engine Limited Warranty...............................25 17.3 Summary of Hartzell’s New Propeller Limited Warranty......................... 30

TRAINING AGREEMENT ...................................................................................33 iii K IN G AIR 3 6 0 C UTILITY IN TER IO R · O CTOBER 2 0 2 3 Figure 2: Interior Dimensions....................................................................................4 Figure 3: Instrumentation......................................................................................... 12 Figure 4: Cabin Configuration..................................................................................18 K IN G A IR 3 6 0 C U T IL IT Y IN T E R IO R · O C T O B E R 2 0 2 3 IV performance and standard equipment of the Beechcraft® King Air® 360C (Model B300) with a ‘Utility Interior’, Serial Number FM-110 to TBD (hereinafter “King Air® 360C” 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 Specification 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 conflict between this Specification 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: contracts@txtav.com K IN G AIR 3 6 0 C UTILITY IN TER IO R · OCTOBER 2 0 2 3 The King Air® 360C is a twin engine turboprop aircraft fitted with the optional cargo door. The Aircraft with a ‘Utility Interior’ as described herein forms the baseline for special mission configurations. The Aircraft is certified for a single pilot operation. Two Pratt & Whitney® Canada PT6A-60A turboprop engines with Hartzell four blade propellers power the King Air® 360C, and a fully integrated Collins Aerospace® Pro Line Fusion® digital avionics suite provides pilot(s) with state-of-the-art touchscreen controls. 1.1 Certification The King Air® 360C is certified in accordance with U.S. 14 CFR Part 23, Commuter Category, including day, night, VFR, IFR, and flight into known icing conditions. The King Air® 360C is compliant with RVSM certification requirements. Note: The aircraft operator is responsible for ensuring that RVSM operations are authorized and approved by the applicable aviation authority. 1.2 Purchaser’s Responsibility International aircraft certification may require modifications to and the incorporation of additional equipment into the Aircraft. The Aircraft purchaser (“Purchaser”) is responsible for the costs of any such modifications 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. KIN G AIR 3 6 0 C U TILITY INTERIO R · OCTO BER 2 0 2 3 2 (14.22 m) 18 ft 5 in (5.61 m) Figure 1: Exterior Dimensions 3 K IN G AIR 3 6 0 C UTILITY INTERIO R · OC TO BER 2 0 2 3 (0.51 m) (0.36 m) (1.32 m) T t 4 ft 4 in. 3 ft1 0 in · 2 ft 6 in 1ft 2 in (1.32 m) (1.17 m) (0.76 m) (0.36 m) - 1 ft 8 in (0.51 m) Figure 2: Interior Dimensions ‘Width between door support struts is 4 ft 1 in (1.24m) K IN G AIR 3 6 0 C U TILITY INTER IO R · O C TO BE R 2 0 2 3 4 OVERALL WIDTH OVERALL LENGTH WHEELBASE 14 ft 4 in (4.37 m) 57 ft 11 in (17.65 m) 46 ft 8 in (14.22 m) 16 ft 3 in (4.95 m) WING HORIZONTAL TAIL VERTICAL TAIL CABIN INTERIOR (with Utility interior) SPAN AREA SWEEP (overall) (at 25% chord) 57 ft 11 in (17.65 m) 310 ft2 (28.8 m2) 0‘ SPAN AREA SWEEP (overall) (at 25% chord) 18 ft 5 in (5.61 m) 68 ft2 (6.32 m2) 17 HEIGHT AREA SWEEP (overall) (at 25% chord) 14 ft 4 in (4.37 m) 52.3 ft2 (4.86 m2 ) 37.T HEIGHT LENGTH WIDTH (max) (max) 4 ft 9 in (1.45 m) 24 ft 10 in (7.75 m) 4 ft 6 in (1.37 m) LENGTH* 19 ft 6 in (5.94 m) * Cabin Length: Forward pressure bulkhead to aft bulkhead. ” Cabin Length: Cockpit divider to aft bulkhead. 1.4 Design Weights and Capacities MAXIMUM RAMP WEIGHT MAXIMUM TAKEOFF WEIGHT MAXIMUM LANDING WEIGHT MAXIMUM ZERO FUEL WEIGHT BASIC OPERATING WEIGHT (1 pilot, 200 lb) FUEL CAPACITY (usable at 6.7 Ib/gal) 15,100 lb (6,849 kg) 15.000 lb (6,804 kg) 15.000 lb (6,804 kg) 12,500 lb (5,670 kg) 9,360 lb (4,241 kg) 3,611 lb (1,638 kg) 5 K IN G AIR 3 6 0 C UTILITY INTERIO R · OCTOBER 2 0 2 3 International Standard Atmosphere (ISA) conditions with zero wind. Takeoff and landing lengths are based on a flat, 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 configuration, and operational/ATC procedures. TAKEOFF FIELD LENGTH 3,300 ft (1,006 m) (Maximum Takeoff Weight, Flaps Approach, A/C and Bleed Air On) MAXIMUM CERTIFIED ALTITUDE 35,000 ft (10,668 m) MAXIMUM CRUISE SPEED (+/- 3%) 312 KTAS ( 578 km/hr) (26,000 feet {7,925 m) altitude; 12,000 pounds (5,443 kg] cruise weight; maximum cruise power) MAXIMUM FERRY RANGE 1,895 NM (3,506 km) (One pilot, no payload, Max Range Cruise, NBAA IFR Reserves with 100 NM alternate) NBAA IFR RANGE 1,485 NM ( 2,750 km) (Max weight, full fuel payload, one pilot, Max Speed Cruise, 100 NM alternate) LANDING DISTANCE 2,692 ft (821 m) (Maximum Landing Weight, Flaps Down, no Prop Reverse) CERTIFIED NOISE LEVELS (Complies with 14 CFR 36, Appendix G) Takeoff 72.9 dB(A)

DESIGN LIMITS DESIGN LOAD LIMITS Flaps Up -1.24 to +3.10G OPERATING LIMIT SPEEDS VM0 (sea level to 21,000 ft {6,400 m)) VMO (21,000 ft {6,400 m} to 35,000 feet {10,668 m}) 263 KIAS (487 km/hr) 263 to 194 KIAS (487 to 359 km/hr) Mach 0.58 (indicated) FLAP LIMIT SPEEDS VFE (Flaps Approach) VFE (Flaps Full Down) 202 KIAS (374 km/hr) 158 KIAS (293 km/hr) LANDING GEAR LIMIT SPEEDS VL0 (extension) VL0 (retraction) VLE (emergency operating) 184 KIAS (341 km/hr) 166 KIAS (307 km/hr) 184 KIAS (341 km/hr) K IN G A IR 3 6 0 C U T ILIT Y IN T E R IO R ♦ O C T O B E R 2 0 2 3 6 The King Air® 360C incorporates a “square oval” fuselage of metallic construction with an internal cabin. A dropped aisle in the passenger cabin provides optimized cabin room and passenger comfort. 4.2 Nose Section The nose section has a contoured radome. The glass and acrylic windshields meet bird resistance requirements of Part 23, Commuter Category; they are electrically heated and defogged. 4.3 Interior Spaces The flight compartment and cabin are described in Section 10 and 11, respectively. 4.4 Aft Fuselage The aft fuselage contains space for the oxygen bottle and cockpit voice recorder. An optional flight data recorder may also be located in this area. 4.5 Cargo Door The King Air® 360C is fitted with a large upward and outward opening cargo door. Integral to the cargo door is a passenger airstair door which allows passengers to enter and exit the cabin without the need to open the main cargo door.

WING The Aircraft features a straight wing with semi-monocoque construction incorporating dual spar structures from wing tip to wing tip. Electrically driven flaps are attached to the trailing edges of each wing. Winglets of composite construction are fitted at the wingtips to improve performance.

EMPENNAGE The empennage features a vertical and horizontal stabilizer in a T-tail configuration. 7 K IN G AIR 3 6 0 C UTILITY INTERIO R · O CTOBER 2 0 2 3 The main landing gear hydraulically retracts forward into each engine nacelle. For back-up operation, the landing gear extension is accomplished by a manual system that requires the landing gear to be pumped down using the alternate extension handle. 7.2 Nosewheel Steering The nose gear assembly is of conventional strut design. Nosewheel steering is mechanically actuated by the rudder pedals. 7.3 Brakes and Tires The multi-disc, metallic-lined brake assemblies, one at each main gear wheel, are hydraulically operated. The King Air® 360C is equipped with dual wheels and tires on the main gear (four tires; two each left and right main) and a single wheel and tire on the nose gear. PLY MAX SPEED RATING SIZE NOSE GEAR TIRES 8 160 mph 22 x 6.75-10 MAIN TIRES 10 190 mph 22 x 6.75-10

PROPULSION 8.1 Powerplant The Aircraft is powered by two Pratt & Whitney® Canada PT6A-60A turboprop engines installed on the wings. The PT6A-60A engines are free turbines, therefore, the power requirement during engine start is relatively low. The propulsion system is operated by the power levers, propeller levers, and condition levers. TAKEOFF POWER RATING (at sea level) 1,050 SHP EACH FLAT RATED TO ISA+10°C HOT SECTION INSPECTION/TBO 1,800 HR/3,600 HR K IN G A IR 3 6 0 C U T ILITY IN TE R IO R · O C TO B E R 2 0 2 3 full feathering, constant speed propeller.

SYSTEMS 9.1 Flight Controls The manually operated primary flight controls are mechanically operated through a push rod, cable and bellcrank system. The primary flight controls consist of one aileron on each wing, one elevator on the horizontal tail and one rudder on the vertical tail. Secondary flight controls include mechanical trim for the roll and yaw systems, as well as mechanical and electrical trim for the pitch system. Four flaps, mounted on the wings are electrically operated by the Direct Current (DC) system. All control surfaces are of aluminum construction. A single yaw damper system improves performance and comfort. 9.2 Fuel System The King Air® 360C features a conventional, large capacity fuel system that provides an independent fuel supply for each engine. There are two separate systems connected by a crossfeed line. The fuel system for each engine is further divided into a main and auxiliary fuel system. The main system consists of a nacelle tank, two wing leading edge tanks, two box section bladder tanks, and an integral (wet cell) tank, all interconnected to flow into the nacelle tank by gravity. The auxiliary fuel system consists of a center section tank with its own filler opening and an automatic fuel transfer system to transfer the fuel into the main fuel system. When the auxiliary tanks are filled, they will be used first. Fuel is supplied to the engines through an engine driven fuel pump mounted on the accessory case in conjunction with the fuel control unit. Refueling is accomplished through over wing filler ports with flush mounted fuel caps. The King Air® 360C is certified for a variety of fuels. Total useable fuel is 3,611 lb (1,638 kg). 9 K IN G A IR 3 6 0 C U T ILIT Y IN T E R IO R · O C T O B E R 2 0 2 3 starter/generators. The Aircraft’s battery is a 24 volt, 42 ampere-hour lead acid battery, which is located in the right inboard wing leading edge. A 28V DC external power receptacle is provided for connection of an external power unit. Power from these sources is distributed through the DC electrical power distribution system, which provides power to the individual electrical loads through a multi-bus system. If all engine-driven power is lost, the Aircraft main battery provides power to the triple-fed bus for a limited period of time. A 1,000 volt-ampere inverter located in the center fuselage under the floor provides 115 volt 60 Hz AC power to four electrical outlets located in the cabin. 9.4 Exterior Lighting System 9.4.1 Primary Standard exterior lighting consists of recognition lights, landing lights, position lights, white flashing beacons on tail and fuselage, strobe lights on the wing tips and tail, and taxi lights (located on the nose landing gear). 9.4.2 Secondary Courtesy lights illuminate the entrance door area. ‘Logo’ lights located in the horizontal tail illuminate the vertical stabilizer. Other secondary lighting includes two wing leading edge ice lights. 9.5 Pressurization and Environmental System Bleed air from each engine supplies cabin pressurization through a pressurization controller. The pressurization control system automatically schedules cabin altitude. Cabin pressure, cabin altitude, and cabin rate of change are displayed on the Multifunction Display. Engine bleed air is also utilized to warm the cockpit and cabin. CABIN PRESSURIZATION* Nominal Maximum Pressurization Differential 6.8 PSID Cabin Altitude at Aircraft’s Certified Ceiling 9,620 ft @ 35,000 ft ‘ NOTE: Nominal cabin pressurization differential refers to the control setpoint programmed into the pressurization controller. There can be variances from this value due to system design tolerances. A supplemental heating system is provided for cabin heating on the ground through the Aircraft electrical system or by a 28V ground power cart. K IN G AIR 3 6 0 C UTILITY INTERIO R · O CTO BER 2 0 2 3 10 demand masks are provided for the crew. Oxygen pressure readout is provided by a gauge located on the co-pilot’s right sub-panel. 9.7 Anti-Icing System and Rain Removal 9.7.1 Ice An inertial separation system is built into each engine air inlet to prevent moisture particles from entering the engine inlet plenum under icing conditions. Engine exhaust heat is utilized for heating the engine air inlet lips. The wing leading edge and horizontal stabilizer leading edge anti-icing boots are driven by bleed air. Electric heat is used to remove ice from the windshield, pitot mast, fuel vent, propellers and stall warning vane. 9.7.2 Rain The windshield has dual, two speed electromechanical windshield wiper system for rain removal on the ground and during slow speed flight operations. 9.8 Hydraulic System The hydraulic system is powered by an electric motor-driven pump and provides hydraulic pressure for landing gear retraction and extension.

FLIGHT COMPARTMENT 10.1 General The Collins Aerospace® Pro Line Fusion® is the featured avionics suite on the King Air® 360C. Three full-color Electronic Flight Instrumentation System (EFIS) Adaptive Flight Displays featuring touch screen operation are included. Two complete crew stations are furnished with dual controls, including control columns, adjustable rudder pedals, and brakes. Each crew seat features an adjustable headrest and inboard armrest and includes a four-point restraint harnesses with some storage space provided behind each seat. The oxygen system provides two pressure demand masks with microphones for the crew members. The oxygen masks are stored in the overhead roof panel and circuit breaker panels are located on both the pilot’s and co-pilot’s sidewalls. Illuminated panels, instrument floodlights, push button switches, and background lighting are standard in the flight compartment. l l K IN G A IR 3 6 0 C U T ILITY IN T E R IO R · O C TO B E R 2 0 2 3

Multi-Function Display (MFD) 7. Audio Panels

Copilot’s Primary Flight Display (PFD) 8. Flight Guidance Panel

Multifunction Keypad 9. Electronic Standby Instrument System

Cursor Control Panels Figure 3: Instrumentation KIN G AIR 3 6 0 C U TILITY INTERIOR · OCTOBER 2 0 2 3 12 touchscreen LCD panels, flight crew radio communications, Flight Management System, Engine Indicating and Crew Alerting System, Automatic Flight Control System, Air Data System and Attitude/Heading Reference System. During the normal course of aircraft manufacturing, maintenance, and operation, technicians install or update certain software and data onto standard and optional avionics and other equipment. During the course of such installation, it may be necessary to digitally "accept” or otherwise consent to certain supplier required end-user license agreements (“EULA”) and other terms and conditions in order to proceed with the software or data installation process. These are commonly referred to as "click-wrap” or “click-through” digital agreements. Purchaser hereby authorizes and consents to technicians clicking “accept” on such agreements and agrees to be bound by the terms of such agreements. Purchaser acknowledges and agrees to independently review such “click-wrap” agreements. 10.3.1 Flight Displays The Pro Line Fusion® system includes three 14-diagonal-inch, high-resolution Liquid Crystal Displays (LCD) in widescreen, landscape orientation. The two outer displays are the Primary Flight Displays. The Multi-Function Display is centrally located. The primary and multi-function displays incorporate touchscreen technology to allow for interactive control of display functions. 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 primary attitude, heading, altitude, airspeed, navigation, flight guidance and pilot selectable formats. 10.3.1.2 Multi-Function Display (MFD) The MFD provides display of engine indication, crew alerting messages and pilot selectable formats including maps, charts, weather, navigation data, avionics diagnostics and checklist. 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. 13 K IN G AIR 3 6 0 C UTILITY IN TER IO R · O CTOBER 2 0 2 3 System (WAAS) receivers, Very High Frequency (VHF) communication radios, VHF navigation radios and glideslope receivers in addition to supporting input-output processing and Flight Director functions. 10.3.2.1 Global Positioning System (GPS) The Pro Line Fusion® system includes a single GPS with WAAS/LPV receiver. 10.3.2.2 Very High Frequency Radio (VHF) The Pro Line Fusion® system includes two standard VHF voice radios. The VHF voice radios are controlled by the flight crew through the touch screen or multifunction keypad. 10.3.2.3 Navigation Receivers The Pro Line Fusion® system includes two standard VHF navigation radios controlled by the flight crew through the touch screen or multifunction keypad. 10.3.3 Audio System The dB Systems model 700 amplifiers with Model 804 (pilot) / Model 805 (copilot) Audio Panels feature dual auto COMM and audio switches, crew interphone, dual cockpit speakers, microphone key button on pilot and copilot control wheels, dual hand-held microphones, dual boom microphone handsets, voice and ident filters. 10.3.4 Cockpit Voice Recorder (CVR) A Solid State Cockpit Voice Recorder (CVR) with a 120 minute recording time is included with the Aircraft. 10.3.5 Flight Management System (FMS) A dual Flight Management System (FMS) is fully integrated into the Pro Line Fusion® system. Each FMS provides navigation and flight planning. Supported features include (among others): • Map Displays — Moving map on the MFD • Flight Planning — Direct- Το navigation, lateral and vertical navigation, procedures, etc.; flight planning is controlled by the touchscreen, cursor control panels or multifunction keypad. Flight plans can also be uploaded via USB. K IN G A IR 3 6 0 C UTILITY IN TER IO R · O C TO BE R 2 0 2 3 14 RNP 0.3 accuracy and WAAS/LPV approach capability and Radius-to-fix (RF) legs. Applicable subscription services are the Purchaser's responsibility. 10.3.6 Electronic Charts The Electronic Charts function allows the crew to view geo-referenced electronic navigation charts that display “own-ship” aircraft position for enhanced situational awareness during approaches. Airport diagrams can be displayed after landing to make surface navigation easier. Displaying charts on each PFD is an optional feature. Applicable subscription services are the Purchaser’s responsibility. 10.3.7 Surface Management System The Surface Management System provides automated checks and aural advisories to the flight crew, and adds a visual overlay that highlights the target runway on the airport chart display. Pro Line Fusion® supports runway awareness by displaying aircraft position during taxi. Should an unsafe takeoff or landing operation occur aural alerts and other annunciators provide additional situational awareness. 10.3.8 Distance Measuring Equipment (DME) A single DME-4000 unit is integrated into the Pro Line Fusion® system. This unit provides DME information to the pilots and provide scanning DME/DME input capability for the Flight Management System. 10.3.9 Engine Indicating and Crew Alerting System (EICAS) The Engine Indicating and Crew Altering System (EICAS) provides an electronic display of primary engine operating information and provides alerts and display changes when operating outside limits. Crew alerts include caution, warning, advisory and status annunciators on the MFD. 10.3.10 Flight Guidance System (FGS) The Automatic Flight Control System (AFCS) is part of the Pro Line Fusion® system. The AFCS can be divided into the following functions: • Flight Director—The Flight Director provides vertical/lateral mode selection and processing, command bars showing pitch/roll guidance, and pitch/roll commands to the autopilot. 1 5 K IN G AIR 3 6 0 C UTILITY IN TERIO R · O CTO BER 2 0 2 3 • Yaw Damper—The yaw damp actuator provides Dutch roll damping and turn coordination in response to yaw rate, roll angle, lateral acceleration and airspeed. • Automatic Pitch Trim—The pitch trim system provides automatic pitch trim when the autopilot is engaged. 10.3.11 Autothrottle The IS&S ThrustSense Autothrottle provides automatic control of each engine’s power through commanding the thrust levers to achieve the desired torque or airspeed based on the Aircraft’s phase of flight and the pilot defined mode of operation. When engaged by the pilot, the autothrottie is designed to prevent the Aircraft from entering underspeed, overspeed, overtemperature and overtorque conditions through constant monitoring technology and is controlled via the IS&S Electronic Standby Instrument System (ESIS). 10.3.12 Air Data System The Air Data System (ADS) supplies digital output signals (airspeed and altitude) to the AHRS, transponders and Flight Guidance System. The system is RVSM capable. 10.3.13 Attitude/Heading Reference System (AHRS) The Attitude/Heading Reference System (AHRS) provides attitude, heading and flight dynamics information to the flight control and display system. 10.3.14 Transponders with ADS-B Out Capability The Pro Line Fusion® system includes dual TDR-94D solid-state, airborne, Mode A/C/S air traffic control Transponders with Flight ID and is ADS-B Out compliant with the DO-260B standard. 10.3.15 Weather Radar Weather radar information is provided via the solid state color Multi-Scan RTA-4112 weather radar system. The system combines multiple radar scans at pre-selected tilt angles in order to detect short, mid, and long range weather. The display presentation represents an optimized weather picture regardless of the aircraft altitude or the range selected. The radar is fully automatic and offers ground clutter suppression as well as turbulence detection. K IN G A IR 3 6 0 C U TILITY IN TER IO R · O C TO BE R 2 0 2 3 16 that provides altitude information from 0 to 2,500 feet (762 m) AGL. 10.3.17 Traffic Collision Avoidance System (TCAS II) A Collins Aerospace® TTR-4100 system is included, providing traffic and resolution advisories. This system is compliant with Change 7.1 regulatory requirements. 10.3.18 Integrated Terrain Awareness Warning System (iTAWS) The Collins Aerospace® iTAWS system includes a Class A Terrain Awareness and Warning System (TAWS) displayed on the PFD and MFD. The system provides predictive warnings with enhanced TAWS visual cues including TAWS alerts shown on the synthetic vision. 10.3.19 Synthetic Vision Technology (SVT) Pro Line Fusion® Synthetic Vision Technology (SVT) is included. The system presents terrain and obstacle information on the PFDs in a dynamic, threedimensional format, providing for increased situational awareness. Airports, runways, heading, traffic, color-coded terrain alerts and a flight path indicator display through the SVT. Applicable subscription services are the Purchaser’s responsibility. 10.3.20 Emergency Locator Transmitter (ELT) An Artex C406N Emergency Locator Transmitter (ELT) is located in the tail of the aircraft. A control switch is located in the flight compartment. The ELT transmits on 121.5, 234 and 406 MHz. 10.3.21 Standby Instrumentation An IS&S Electronic Standby Instrument System (ESIS) provides autothrottle control as well as back-up display of attitude, heading, airspeed, and altitude with back-up battery. 10.3.22 Onboard Maintenance System The Onboard Maintenance System provides data to the flight line technician to be used for aircraft maintenance. The system collects data from the various components of the avionic system and provides fault detection and analysis as well as identification, recording and display of maintenance information on the MFD. 17 K IN G A IR 3 6 0 C UTILITY IN TER IO R · O C TO BER 2 0 2 3 There is one main cabin door, with integral air stairs, that is manually operated. The cabin is separated from the flight compartment by a 3/4 length curtain. The cabin extends from the flight compartment door to the aft pressure bulkhead. A dropped aisle extends aft of the wing spar through the cabin. An emergency exit hatch is located on both the left and right hand side. A ‘Utility Interior’ provides a smooth hard vinyl interior surface with no seats, cabinetry or toilet. A durable vinyl floor covering is provided in this baseline configuration. Certified burn-resistant materials are used throughout the cabin and flight compartment. Cabin noise and vibration from the propellers is reduced through the use of bagged insulation, sound dampening trim panels and a number of dynamic vibration absorbers mounted throughout the cabin and flight deck. 10.5 Windows Fifteen cabin windows are equipped with a rotating inner pane which is polarized to provide dimming capability. Two additional clear windows are located in the rear baggage compartment. 10.6 Cabin Lighting System 10.6.1 Direct Lighting General LED lighting, entrance door step and emergency exit lights are located in the passenger cabin. 10.6.2 Indirect Lighting Accent lighting is located in the dropped aisle. 10.6.3 Emergency Lighting Emergency Exit Lighting (in the cabin and over the wing) runs via the Emergency Lighting Battery Pack in case of a power interruption. KIN G AIR 3 6 0 C UTILITY INTER IO R · OCTOBER 2 0 2 3 Figure 4: Cabin Configuration 18 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. 11.1 Exterior Storage Two exterior compartments located in the wing nacelles offer external storage. These areas are unheated and unpressurized. WEIGHT VOLUME EXTERIOR STORAGE AREA (each nacelle) Max: 72 in (1.83 m) L 28 in (0.71 m) W 12 in (0.30 m) H 300 lb (136 kg) 8.0 ft3 (0.23 m3)

LOOSE EQUIPMENT Bleed Air Plugs (2) Bose® Aviation Headset (2) Cargo Door Stabilizer (1) Engine Inlet Plugs (2) Flight Bag Fuel Sump Drain Wrench (1) Gust Lock Assembly First Aid Kit Pitot Tube Covers (2) Propeller Slings (2) Shorting Plug (1) 19 K IN G AIR 3 6 0 C UTILITY IN TERIO R · O CTOBER 2 0 2 3 Fire Extinguisher in Cockpit and Cabin Flashlight

DOCUMENTATION AN D TECHNICAL PUBLICATIONS The following will be provided to Purchaser. Print material: Aircraft Technical Log, Section 3, Engine (2) Aircraft Technical Log, Section 3, Propeller (2) Avionics Pilots Guides Flight Log Pilot’s Checklist Pilot’s Operating Handbook/Airplane Flight Manual Maintenance Information Sheet Maintenance/lnspection Log Supplementary Log Accessible via online subscription at https://ww2.txtav.com. Component Maintenance Manual Maintenance Manual Illustrated Parts Catalog Printed Circuit Board Manual Structural Inspection Repair Manual Wiring Diagram Manual Documents providing instructions for continued airworthiness are provided atww2.txtav.com. K IN G AIR 3 6 0 C UTILITY IN TERIO R · O CTO BER 2 0 2 3 20 start date of the airframe warranty. Continued online access is available through a paid subscription which is Purchaser’s responsibility. Purchaser will receive Safety of Flight Information on paper at no cost to Purchaser for as long as Purchaser owns or operates the Aircraft. For more information on this free service contact TMDC@txtav.com. 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.