0 MAJOR REPAIR AND ALTERATION Deparment of (Airframe, Powerplant, Propeller, or Appliance) TrarreonatIon Ayarwal Aviation Aahaduration Form Approved OMB No. 2120-0020 lino/mg Electronic Tracking Number For FAA Use Only INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this loon. This report is required by law (49 U. S.C. 1421). Failure to report can result in a civil penalty not to exceed 51,000 for each such violation (Section 901 Federal Aviation Act 1959) 1. Aircraft Nationality and Registration Mark N493LX Serial No. RK 244 Make Raytheon Aircraft Company Model 400A Series 2. Owner Name (As shown on rogiSfrafion certificate) Flight Options .LLC Address (As shown on registration certificate) Adere6s cry Richmond Heights site OH tip 44143.1453 coowy USA 3. For FAA Use Only 4. Typo 5. Unit Identification Repair Alteration Unit Make Model Serial Number 0 0 AIRFRAME (As described in Nem 1 above) Ill IE POWERPLANT 0 • PROPELLER K O APPLIANCE Type manufacturer' 6. Conformity Statement A. Agencys Name and Address B. Kind of Agency Nana Nextant Aerospace Patron cry Cleveland State. OH tip 44143-1453 Country USA CI u.s. Certificated Mechanic O I Manufacturer O Foreign Certificated Mechanic C. Certificate No. B Certificated Repair Station CRS # 25NR667B O Certificated Maintenance Organization D. I certify that the repair and/Or alteration made to the unit(s) identified in item 5 above and described on tne reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 APP. B El 12/29/2013 7. Approval for Return to Service Pursuant to the authority given persons specified below, the unit identified Administrator of the Federal Aviation Administration and is Ell in item 5 was Inspected In the manner presalbecl by the APPROVED K REJECTED FAA Flt Inspector Standards Manufacturer Maintenance Organization I Person Approved by Canadian Department of Transport BY Certificate Designation CRS or # 25NR667B FM Designee No. X Repair Station InsPeCtiOn Authorization Other (Specify) 12/29/2013 FAA Form 337 (10.06) EFTA00011869

EFTA00011870

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N49311 Nationality and Registration Mark DEACTIVATE CLOCKS 12/29/2013 Date For Pilots Clock Deactivation: I.) Removed PLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 2.) At Radio Junction Box: a.) disconnected wire W78-I9 from 393IJ25 PIN R & S. b.) Spliced wire W78-19 from pin R with 3931322 wire W71-3 (20) pin D•. For Co-Pilots Clock Deactivation: 4.) Removed COPLT CLOCK circuit breakers from LH FWD CB Panel. Spliced feed wires together. Cap and Stowed Load side wires. 5.) At Radio Junction Box: a.) disconnected wire W78.45 from 39311B1 3931R3 pin 3. b.) cap and stowed wire. c.) Installed jumper from pin 3 to 3931.122 pin F* (splice with wire W71-4 (20)) 6.) Tested all WOW interface circuits at #1 & #2 DCU, #1 & #2 DCP,01 & #2 PFD,ti I & #2 MFD, DAU, #1 &#2 ADC, #1 & #2 GPS, #1 & #2 FSU, #1 & #2 TDR. 7.) Changed power wiring for ELT from #2 Clock to #2 Audio panel. Disconnected wire from inline fuse ELTFI feed side and connected to Audio power input 2350P4 pin 8 (spliced with wire W965.019 (20)). Tested ELT. This removal was electrically approved by FAA DERT-230019-CE using a FAA 8110-3 Dated November 15, 2013 Using Nextant Engineering order 1165 Rev B Dated 11/13/2013 End K Additional Sheets Are Attached FAA Form 337 (1005) EFTA00011871

EFTA00011872

V.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE 11.15-2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE - Hawker Beechcraft . \ 3. MODEL NO. 400A SIN RK-244 Only 4. TYPE (Airplane, Radio. Helicopter, etc.) Airplane 5. NAME OF APPLICANT Nextant Aerospace LLC LIST OF DATA G. IDENTIFICATION 7. TITLE Nextant Aerospace Document EO 1165 dated 11.13.13 Rev. B - Engineering Order Deactivate Clocks END This approval is for the electrical systems aspects onty. 8. PURPOSE OF DATA Support major alteration to aircraft Hawker Beechcraft 400A RK-244 Only. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR 25.1301(a) pig' Note: Compliance has been found to the amendment levels indicated on Hawker Beechcraft 400A TCDS Revision 26 Part 25 Amendment 25- 1 through 25-40 to the above applicable requirements. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Pan 183 of the Federal Aviation Regulations. data listed above and on attached sheets numbered WA have been examined In accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards listed. I (We) Therefore approve these data. 11. SIGNATURES I N ING REPRESENTATNE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-230019-CE Systems and Equipment 1-AA Form 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION GPO 90t413 EFTA00011873

EFTA00011874

C MAJOR REPAIR AND ALTERATION Trans •piinment el (Airframe, Powerplant, Propeller, or Appliance) T portaarn Federal Aviation Administration Form Appnarod om8 No.21204020 I 1r30,2C07 Electronic Tracking Number For FAA Use Only INSTRUCTIONS: Print or type 31 entries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S C. 1421). Failure to report can result In a civil penalty not to exceed $1,030 for each such violation (Section 901 Federal Aviation Act 1958) 1. Aircraft Nationality and Registration Mark N493LX Serial No. RK 244 Make Raytheon Aircraft Company Model 400A Bones 2. Owner Name (As shown on registration certificate) Flight Options .LLC Address (As shown on regtsfration certificate) AnSress Gila Richmond Heights sin OH zip 44143-14U Camay USA 3. Far FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number 0 ... AIRFRAME (As described in Item 1 above) 0 O POWERPLANT o K PROPELLER • U APPLIANCE TWO Mania:Leer 6. Conformity Slat mont A. Agency's Name and Address B. K nd of Agency Wits Nextant Aerospace Melon City Cleveland Stati OH co 44143-1453 cowry USA 0 u.S. CerbliCaMd Mechanic 0 I Manufacturer 0 Foreign Ceetbealed Mechanic C. Certificate NO. 0 Certificated Repair Station CRS # 25NR667B 0 Certificated Maintenance Organization D. !certify that the repair and/Or alteration made to the rings) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furniihed herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 K APP. B 12/29/2013 Pursuant to the authonly given persons specified below, the unit identified Administrator of the Federal Aviation Administration and is El in item 5 was inspected in the manner prescribed by the APPROVED 0 REJECTED av FM Fit Standards Inspector Manufacturer Maintenance Organization Person Approved by Canadian Department of Transport FAA Designee X Repair Station inspection Authorization Other (Specify) Cenificace Or Designation No 2/29/2013 CRS # 25NR667B FAA Form 337 (10-06) EFTA00011875

EFTA00011876

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (It more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nationality and Registration Mark TITLE: Aircraft Windshield Sealing Process Deviation: 12/29/2013 Allow Deviation from AMM 56-10-00-201 for the sealing of the aircraft windshield process. Date Temporary fasteners are not necessary during the sealing of the windshield. Original & typical bolts for installation may be used during the process, to keep retainers and shims in place during the entire sealing & installation of the windshield. After proper sealing time had elapsed, torqued bolts for installation of windshield per AMM. See attached FM Form 8110-3 Signed By DERT-410115-CE Dated June 12, 2013 using Nextant Aerospace Engineering Order 1257, Rev. A, Dated May 21, 2013 for details. ICA Weight change is Negligible. Continue with Beechjet 400/400A Maintenance Manual Inspection Procedures. End K Additional Sheets Are Attached FAA Form 337 (10-08) EFTA00011877

EFTA00011878

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE June 12, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft Engine. Propene( eta) Aircraft 5. NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA 6 IDFNTIRCATION 7 TITLE EC 1257 Rev. A May 21, 2013 ------- Aircraft Windshield Sealing Process Deviation. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire repair. 8. PURPOSE OF DATA: Engineering data in support of major repair to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23), 25.303[25-23), 25.305(a)(b)(c)(25-23], 25.307(a)[25-23], 25.601[25-00), 25.603(a)(b)(c)(25-38], 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)[25-00), 25.611[25-23), 25.613(a)(b)(c)(25- 00], 25.619[25-231, and 25.625(a)(b)(c)125-231. 10. CERTIFICATION - Under authority Part 183: data listed above and on applicable requirements of the Ainvorthiness K Recommend vested by direction of the Administrator and in accordance with condelices and limitations of appointment under 14 CFR attached sheets numbered _Ha_ have been examined in accordance with established procedures and found to comply with standards Listed. approval of these data these data I (We) Therefore i015 Approve II. SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION NUMBERS(S) 13. CIASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. H13367-01 Page 1 oft EFTA00011879

EFTA00011880

e MAJOR REPAIR AND ALTERATION u.s oepavvent or (Airframe, Powerplant,Propeller, or Appliance) Truirexitatien Folond AvlatIon Adonlnistration FormApprond OMB No. 2i2043020 iti3OIXOT Electronic Tracking Number For FAA Use Only INSTRUCTIONS: Print or type all entries. See FAR 43.9. FAR 43 Appendix 9. and AC 43.94 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 V $ C. 1421). Failure to report can result in a Civil penalty not to exceed $1,000 for each such violation (Section 901 Federal Aviation Act 1958) t. Aircraft Nationally and Registration Mark N493LX Serial No. RI< 244 Make Raytheon Aircraft Company Model 400A Series . t Owner Name (As shown on registration certificate) Flight Options .LLC Address (As shown on registration certificate) *guess Ci:y Richmond Heights Mete OH zp 44143-1453 CoJtry USA 3. For FAA Use Only 4. Typo 5. U It Identification Repair Alteration Unit Make Model Serial Number El AIRFRAME (As descnbed in Item I above) MI El POWERPLANT • l: PROPELLER 0 El APPLIANCE Typo manure:firer 6. Conformity Statement A. Agency's Name and AddreSS It Kmd of Agency mete Nextant Aerospace mons City Cleveland state. OH zo 44143.1453 cmintry USA O U.S. Certificated Mechanic O I Manufacturer O Foreign Certificated Mechanic C. Certificate No. 0 Certificated Repair Station CRS # 25NR667B O Certificated Maintenance Organization 0. I certify that the repair andror ateraten made to the twigs) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pad 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. B 0 2/29/2013 7. Approval for Return (Service Pursuant to the authority given pe sons specified below. the unit identified in item 5 was inspected in the manner prescribed by the AdMiNStrator of the Federal Aviation Administration and is 121 APPROVED K REJECTED FAA FR Standards Inspector Manufacturer Maintenance Organization I Person Approved by Canadian Department of Transport BY Certificate Designation CRS or # 25NR667B FAA Designee No. X Repair Station Inspection Authorization Other (Specify) • • /2013 FAA Form 337 no-06) EFTA00011881

EFTA00011882

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registratkin mark and date work completed.) N493LX Nationality and Registration Mark 12/29/2013 Date Requested for use of new processes & materials for the removal and installation of Main & Side Windscreen, deviation from HBC AMM When performing the removal and installation of the windscreen and/or cockpit side windows, the following deviations from the HBC AMM are allowed & recommended: 1. During the removal & installation of the main windscreen, reference FO-AMMS document, chapter 56-10-01 for the main windscreen installation using AVDEC materials. This document correctly defines the processes and materials to be used for the removal and installation of the main windscreen. 2. During the removal and installation of the cockpit side windows, reference Flight Options FO-AMMS Document, chapter 56-10-10 & 56-10-11 for the replacement of the side window inner rubber gasket. This document correctly defines the processes and materials to be used for the replacement of the cockpit side windows inner rubber gasket. NOTE: TG8498 & HT3935-7 may not be used on exterior surfaces unless sealant is to be painted after curing for protection against UV light. PERMISSIBLE TO PAINT OUTER WINDSHIELD RETAINER WITH Chevron White JET GLO, CM0570513 (Sherwin-Williams) This Alteration was FAA Approved by FM DERT-410115-CE using an FM Form 8110-3 dated December 28, 2013. Using Nextant Aerospace Engineering Order 1303 Rev B Dated November 13, 2013 ICA Continue with Normal Hawker Beech Maintenance manual Inspection Requirements for this Area End K Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011883

EFTA00011884

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 28, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine. Propeller, etc.) Aircraft 5. NAME OF APPLICANT Nextant Aerospace LLC Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 1303 Rev. B November 13, 2013 Process & Material Deviation for the Removal and Installation of the Main & Side Windscreens. -- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements? 2) This form constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. B. PURPOSE OF DATA. Engineering data in support of major alteration to Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (Ust specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)125-231, 25.562(c)[25-231, 25.601[25-00], 25.603(a)(b)(c)[25-38], 25.605(a)[25-00], 25.607[25-23], 25.609(a)(b)[25-00], 25.611[25-23), 25.613(a)(b)(c)[25-00], 25.619[25-23], 25.625(a)(b)(c)(25-23], and 25.789[25-32]. 10. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR Part 183. data listed above and on attached sheets numbered N/A , have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. 0 Recommend approval of these data I (We) Therefore 0 Approve these data 11. SIGNATURE $ OF DESIGNATED ENGINEERING REPRESENTATn/E(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fie Number H13949.01 Page tof EFTA00011885

EFTA00011886

0 MAJOR REPAIR AND ALTERATION u.s cworwienice (Airframe, Powerplant,Propeller, or Appliance) TranNonsoan Fetal Aviation Aomiresuation Fool Approved 04/43 No. 21200020 1 traOrau37 Electronic Tracking Number For FAA Use Only INSTRUCTIONS: Print or types. entries. Sec FAR 43.9. FAR 43 Appendix B. and AC 43.91 (or subsequent revision thereof) for instructions and disposition or this form. This report is required by law (49 U.S.C. 1421). Fa • i'e to report can result in a OM penally not to exceed S1.000 ror each such violation (Section 901 Federal Aviation Act 1956) 1. Aircraft Nationality and Registration Mark N493LX Serial No. RK 244 Make Raytheon Aircraft Company Mcdel 400A Series 2. Owner Name (As shown on registration certificate) Flight Options .LLC Address (As shown on regisfra bon certificate) Address Crly Richmond Heights Slate OH zip 44143-1453 cowry USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number AIRFRAME (As descnbed in Item I above) Ill 0 POWERPLANT El K PROPELLER K 0 APPLIANCE Tyco M-sgVactwer 6. Conformity Statement A. Agency's Name and Address e. Kind of Agency Name Nextant Aerospace Address City Cleveland Stale. OH Zip 44143-1453 count USA O U.S. Certificated Mechanit O Manufacturer O Foreign Cenneated Mechanic C. Certificate No. CB Certificated Repair Station CRS it 25NR667B O Certificated Maintenance Organization D. I certify that the repair and/or aileratlon made to the unit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of P rt 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my know: dge. Extended range fuel per 14 CFR Part 43 K 12/29/2013 App. S Pursuant to the authonty given persons specified below, the unit Identified in item 5 was inspected in the manner prescnbed by the Administrator of the Federal Aviation Administration and is 9 APPROVED 0 REJECTED FAA FR Standards inspector Manufacturer Maintenance Organization Person Approved by Canadian Departing/Mot Transport BY FM Designee X Repair Station Inspection Authorization Other tSpeci6r) Certificate or Designation No. 12/29/2013 CRS # 25NR667B FAA Form 337 (10-06) EFTA00011887

EFTA00011888

NOTICE Weight and balance or operating limitation changes shell be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nationality and Registration Mark Title : Replace MD-302 with Round Style Standby Gauges 12/29/2013 Date Aircraft with MD302 digit SAM instruments must be reverted back to using round standby gauges until issues are resolved. Modified Instrument Panel (373-92-4110-14) to allow the installation of the original round standby gauges per drawing NX311-10007-03 Rev A Fabricated round indictor subpanel per drawing NX311-10007-01 Rev B Installed instruments into subpanel and install subpanel into main instrument panel per drawing NX311-10007. See Attached 8110-3 DERT 410115-CE dated November 8, 2013 per Nextant Aerospace EO 1543 Rev D dated October 23, 2013 End K Additional Sheets Are Attached FAA Form 337 110.06) EFTA00011889

EFTA00011890

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS t. DATE November 8, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft. Engine. Propeller. efc) Aircraft 5. NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA 6 IDENTIFICATION 7 MI E EO 1543 Rev. D October 23, 2013 ---- Replace MD-302 With Round Style Gauges. ------------------ END-- Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as "Applicable Requirements." 2) This form does not constitute FM approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. The electrical requirements are not included in this approval and require separate approval. a. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23), 25.303[25-23], 25.305(a)(b)(c)[25-23], 25.307(a)[25-23], 25.562(c)[25-23], 25.601[25-00), 25.603(a)(b)(c)[25-38], 25.605(a)[25-00), 25.607(25-23], 25.609(a)(b)[25-00], 25.611[25-23], 25.613(a)(b)(c)[25.00], 25.619[25-23], 25.625(a)(b)(c)[25-23], and 25.789[25-32). IC. CERTIFICATION - Under authority Part 183, data listed above and on applicable requirements of the Airworthiness 0 Recommend vested by direction of the Administrator and in accordance with conditions and limitations of appointment under 14 CFR attached sheets numbered N!A have been examined in accordance wth estatished procedures and found to comply with Standards Listed. approval of these data these data I (We) Therefore )4 Approve i 1. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number. I413818-01 Paget off EFTA00011891

EFTA00011892

0 MAJOR REPAIR AND ALTERATION U.SOnertrrient of (Airframe, Powerplant, Propeller, or Appliance) rimironifion Foam Aviation ArtninIstration Fan Marano ENO 2120-ccdo waocco7 I Electronic Tricking Number For FAA Use Only INSTRUCTIONS: Print or typo ail entries. See FAR 419, FAR 43 Appenox B. and AC 43 9.I (or subseccent ression thereof)or instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 51.000 for each such violation (Section 901 Federal Aviation Act 1954) 1. Aircraft Nationality and Registration Mark N493LX Serial No. RK 244 Make Raytheon Aircraft Company Model 400A Series 2. Owner Name (As shown on registration certificate) Flight Options .LLC Address (As shown on registration certificate) Aram" city Richmond Heights Stale. OH 7.0 44143-1453 cvisdry USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number • 111 AIRFRAME (As described in Item 1 above) • • POWERPLANT PROPELLER II . APPLIANCE Typo Vardatheor 6. Conformity Statement A. Asiencys Name and Address 8. Kind of Agency Name Nextant Aerospace Address Cry Cleveland Sara. OH iv 44143-1453 Ccuray USA CI U.S. Certificated Mechanic O (Manufacturer O Foreign Certificated Mechanic C. Certificate No. 0 Certificated Repair Station CRS # 25N R667B O Certificated MaiMenance Organization D. I certify that the repair arilror alteration made to the unri(S) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 App. 8 INI 12/29/2013 Pursuant to the authOrity given persons pecilled below. the unit identified in item 5 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is 0 APPROVED K REJECTED FAA Flt Standards 1 Inspector Manufacturer Maintenance Organization i Person Approved by Canadian DeparUnent of Transport BY FAA Designee X Repair Station Inspection Authorization Other (Specify) Certificate or Designation No 12/29/2013 CRS # 25NR667B FAA Form 337 it 0-06) EFTA00011893

EFTA00011894

NOTICE Weight and balance or operating limitation changes shall be entered in the appropfiate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nationality and Registration Mark Spoiler Linkage Closeout Modification 12/29/2013 Date Modified the Cockpit Floor Close out Panels Part Number: LH 45A30839-7 (Pilots) and Part Number: RH 45A30839-7 ( Co-Pilots) . Installed Nextant Aerospace Closeout Panel Part Number NX532- 1004-1 between these Panels to allow room for the New Throttle Quadrant to fit under the Center Pedestal This Alteration was FAA Approved by FAA DERT-410114-CE using a FAA 8110-3 Dated December 28, 2013 using Nextant Aerospace Engineering Order 1563 Rev. B Dated December 24, 2013 ICA Continue with Normal Hawker Beech Maintenance Manual Inspection Requirements for this Area End K Additional Sheets Are Attached FAA Form 337 (lam EFTA00011895

I EFTA00011896

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE December 28, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 1. MODEL NO. 400A 4. TYPE (Aircraft Engine, Pnopetter. etc.) Aircraft 5. NAME OF APPLICANT Nextant Aerospace LLC Cleveland, Ohio LIST OF DATA 8 IDENTIFICATION 7 TITLE EO 1563 Rev. B December 24, 2013 Spoileron Linkage Closeout Modification. Notes: 1) The structural aspects only of the above listed data are approved herein. This approval is only for the engineering data. It indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements." 2) This constitutes FAA approval of all the engineering data necessary for substantiation of compliance to necessary requirements for the entire alteration. 8. PURPOSE OF DATA: Engineering data in support of major alteration to Hawker Beechcraft 400A, SIN RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25.23), 25.305(a)(b)(c)(25-23J, 25.307(a)(25-23], 25.601[25-00], 25.603(a)(b)(c)[25-381, 25.605(a)(25.00), 25.607[25-231, 25.609(a)(b)[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-231, and 25.625(a)(b)(c)(25-231. 10. CERTIFICATION • Under authority vested by drection of the Administrator and in accordance with conitions and irmitations of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered N/A have been examined in accordance with established procedures and found to comply with applicable requirements of the Airworthiness Standards Listed. K Recommend approval of these data I (We) Therefore 0 Approve these data 11. SIGNATURE OF DESIGNATED ENGINEERING REPRESENTATIVES) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICAT/ON(S) DERT-410115-CE Structures FAA Form 8110-3 (03.10) SUPERSEDES PREVIOUS EDITION Fite Number. H13950-0I Pageioll EFTA00011897

I EFTA00011898

le MAJOR REPAIR AND ALTERATION u S Deeinmem re (Airframe, Powerplant,Propeller, or Appliance) soopooion Federal Aviation Administration IC"' Itte.Orl AO OW No 2120-0020 11/3C/2007 Electronic Tracking' Number For FAA Use Only INSTRUCTIONS: Print or type a'l entnes See FAR 43.9. FAR 43 Appendix 8. and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed 51.000 for each such vitiation (Section 901 Federal Aviation Act 1958) 1. Aircraft Nationality and Registration Mark N493LX Sena' No. RK 244 Make Raytheon Aircraft Company Model 400A Series 2. Owner Name (As shown on registration certificate) Flight Options .LLC Address (As ShOwn on registration certificate) Addre ss City Richmond Heights sow. OH tip 441431453 couroy USA 3. For FAA Use Only 4. Type 5. Unit Identification Repair Alteration Unit Make Model Serial Number CI AIRFRAME (As described in Item 1 above) K O POWERPLANT O K PROPELLER O O APPLIANCE TIP° Manufactory • 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency Nome Nextant Aerospace Address City Cleveland sole OH 21p 44143-1453 cony USA O U.S. Cenificaled Mechanic O Manufacturer O Foreign Certificated Mechanic C. Certificate No. II9 Certificated Repair Station CRS # 25NR6676 O Cedaficated Maintenance Organization D. I certify that the repair and/or alteration made to the und(s) identified in dem 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Pail 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Extended range fuel per 14 CFR Part 43 K 12/29/2013 App. 8 Pursuant to the authority given persons specified below, the unit identified Administrator of the Federal Aviation Administration and is 0 in item 5 was iispected in the manner prescribed by the APPROVED O REJECTED FAA FR Standards Inspector Manufacturer Maintenance Organization I Person Approved by Canadian Department of Transport BY Certificate Designation CRS or # 25NR6676 FAA Designee No. X Repair Station Inspection Authorization Other (Specify) 12/29/2013 FAA Form 337 (0046) EFTA00011899

EFTA00011900

NOTICE Weight end balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations fo assure continued confomety with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX Nationality and Registration Mark Nextant Aerospace Carried out a Repair to the Horizontal Stabilizer Ribs 12/29/2013 Using Nextant Aerospace Kit Part Number NXK-128-6200 Rev B. Dated July16. 2012. The following Ribs were replaced. NXR-45A21112-007 NXR-45A21113-007 NXR-45A21101-021 NXR-45A21116-007 NXR-45A21117-007 Rib — H Stab Cant STA 13.779. Rib — H Stab Cant STA 29.921. Rib — H Stab Cant STA 46.063. Rib — H Stab Cant STA 62.205 Rib — H Stab Cant STA 78.346 The following Ribs were not Replaced as there was not Damaged. NXR128-620020-001 NXR128-620020-002 Date This Kit was FAA Approved by DER-T 410115-CE Structures on an FAA 8110-3. Dated June 12, 2013. Using Nextant Aerospace Engineering Drawing NXR-128-6200 Rev B Dated July 16.2012 END K Additional Sheets Are Attached FAA Form 337 (10.06) EFTA00011901

EFTA00011902

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE June 12, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO. 400A 4. TYPE (Aircraft, Engine, Propeller, etc) Aircraft 5. NAME OF APPLICANT Nextant Aeiospace LLC Richmond Heights. Ohio LIST OF DATA 6 IDENTIFICATION 7 TfTLE NXR-128-6200 Rev. B July 16, 2012 NXR-45A21112-007 Rev. C July 13, 2012 NXR-45A21113-007 Rev. B July 13, 2012 NXR-45A21114.007 Rev. B July 13. 2012 NXR-45A21115-007 Rev. C July 13, 2012 NXR-45A21101.021 Rev. A July 19. 2012 NXR-45A21116-007 Rev. B July 13, 2012 NXR-45A21117-007 Rev. B July 13, 2012 Kit — Horizontal Stabilizer Rib Replacement Installation Instructions. Rib - H Stab Cant STA 13.779. Rib — H Stab Cant STA 29.921. Rib — H Stab Cant STA 46.063. Rib — H Stab Cant STA 46.063. Rib Assy — H Stab Cant STA 46.063. Rib — H Stab Cant STA 62.205. Rib — H Stab Cant STA 78.346. e. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. 9. APPLICABLE REQUIREMENTS (List specific sections) CFR Title 14 Part 25.301[25-23], 25.303[25-23), 25.305(a)(b)(c)(25-23), 25.307(a)(25-23), 25.601[25-00], 25.603(a)(b)(c)125-381, 25.605(a)(25-00), 25.607(25-23], 25.609(a)(b)(25-00), 25.611(25-23), 25.613(a)(b)(c)(25- 00), 25.619[25-23], and 25.625(a)(b)(c)(25-23]. 10. CERTIFICATION • Under authority vested by direction of the Administrator and in accordance with conditions and tirnitatians of appointment under 14 CFR Part 183, data listed above and on attached sheets numbered .,..2_ have been examined in accordance with established procedures and found to comply mm applicable requirements of the seaworthiness Standards Listed. O Recommend approval of these data I (We) Therefore 0 Approve these data 1 I. SIGNATURE S OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERS(S) 13. CLASSIFICATION(S) DERT-410115-CE Structures FAA Form 8110-3 (03-10) SUPERSEDES PREVIOUS EDITION File Number H13370-01 Page 1 of 2 EFTA00011903

EFTA00011904

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE June 12, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Hawker Beechcraft Corporation 3. MODEL NO 400A 4. TYPE (Aircraft Engine, Propetter. etc.) Aircraft 5. NAME OF APPLICANT Nextant Aerospace LW Richmond Heights, Ohio LIST OF DATA 8 IDENTIFICATION 7 TIT' E ---------- ------ ------ --- Notes: 1) The structural aspects only of the above listed data is only for the engineering data. It indicates the data compliance only with the regulations specified by below as 'Applicable Requirements' 2) This form constitutes FM approval of all the engineering substantiation of compliance to necessary requirements ------------- herein. This approval demonstrates and subparagraph listed necessary for entire repair. -------------------- are approved listed above paragraph data for the 8. PURPOSE OF DATA: Engineering data to support repair procedure for Horizontal Stabilizer P/N 45A21002-0121 on Hawker Beechcraft 400A, S/N RK-244. 0. APPLICABLE REQUIREMENTS (List spectic sections) CFR Title 14 Part 25.301(25-23], 25.303[25-23), 25.305(a)(b)(c)[25-23), 25.307(a)[25.23], 25.601[25-00], 25.603(a)(b)(c)[25-38), 25.605(a)(25.00], 25.607[25-23], 25.609(O1:0[25-00], 25.611(25-23), 25.613(a)(b)(c)[25- 00], 25.619[25-23], and 25.625(a)(b)(c)[25-23). 10. CERTIFICATION • Under authority Part 163. data listed above and on applicable requirements of the Airworthiness vested by direction of the Administrator and in accordance with conditions and 5mitations of appointment under 14 CFR attached sheets numbered ...7,_ have been examined in accordance wdh established procedures and found to comply mlh Standards Usted. approval of these data these data • Recommend I (We) Therefore i, Approve It. SIGNATURES OF DESIGNATED ENGINEERING REPRESENTATIVE(S) 12. DESIGNATION NUMBERSIS) 13 CLASSIFICATION(S) DERT-410115-CE Structures • FAA Form 8110.3 (03-10) SUPERSEDES PREVIOUS EDITION File Number 1113370.01 Page 2 of 2 EFTA00011905

I EFTA00011906

0 MAJOR REPAIR AND ALTERATION he ovolownot Form APProved OMB No. 2120-0020 11M0f2007 Electronic Tracking Number Timmy/woo (Airframe, Powerplant, Propeller, or Appliance) For FAA Use Only Federal Ai/1HW Adrairdallntkia INSTRUCTIONS: Print or type all entries. See FAR 43.9 FAR 43 Appendix B, and AC 43.9.1 (or subsequent revision thereof) for instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed 31,000 for each such 10latiOn (Salon 901 Federal Aviation Act 1958) Nationality and Registration Mark N493LX Serial No. RK244 1. Aircraft Make Raytheon Aircraft Company Model 400A Series 2. Owner Name (As shown on registration cerfrfiCate) Flight Options, LLC Address As shown on registration certificate cayRichmond Heights swoOhio zo44143-1453 ecitritryUSA 3. For FAA Use Only 4. Type 5. Unit Identification Repar Alteration Unit Make Model Serial Number • 1 AIRFRAME (As described in Item 1 above) POWERPLANT • O PROPELLER K 0 APPLIANCE Trim Menulectirer IL Conformity Statement A. Agency's Name and Address B. K rid of Agency rwooConstant Aviation Add. cisCleveland swoOhio O U.S. Certificated Mechanic O I Manufacturer O Foreign Certificated Mechanic C. Certificate No. El Certificated Repair Station CRS#WC7R346J 444135 canyUnited States O Certificated Maintenance Organization D. I certify that the repair and/or alteration made to the wit(s) identified in item 5 above and described on the reverse or attachments hereto have been made in accordance with the requirements of Part 43 of the U.S. Federal Anabon Regulations and that the information furnished herein is true and correct to the best of m Extended range fuel per 14 CFR Part 43 K Date: December 30, 2013 App. 8 to Service Pursuant to the authority given pe sons specified below, the unit identi Administrator of the Federal Aviation Administration and is irl ed in item S was Inspected in the manner prescribed by the APPROVED K REJECTED FM Fit Standards Inspector Manufacturer Maintenance Orgarizatica Person Approved by Canadian Department of Transport BY FM Designee X Repair Staten Inspection Authorization Other (Specify) Certificate or Designation No. CRS#WC7R346J Signature/Date • Date: December 30 , 2013 FAA Form 337 (lo-os) EFTA00011907

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) N493LX 12130/2013 Nationality and Registration Mark Date ACCOMPLISHED INTERIOR REFURBISHMENT/MODIFICATION AND 3 PLACE DIVAN INSTALLATION THE FOLLOWING AIRCRAFT INTERIOR ITEMS HAVE BEEN REFURBISHED: Repainted, recovered control Ocrumns with Matte Black Leather Accordance with Beechjet 400A AMM 20-70-00.701, 25-00430-001 Removed and Replaced Glare sHeld and Eyebrow panel material with Matte Black Leathern Accordance with Beechjet 400A AMM 20.60.00.201 Removed and Replaced Cor-kpl Sidewise material with Matte Black Leather in Accordance with Beechjet 400A AMM 20-60-00-201. Removed and replaced Pilot Seat Pan Number TABHIOOPM0001 Serial Number 62, Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and replaced Co-Pilot Seat Part Number TABH100CM00-01 Serial Number 248. Foam and recovered with Garrett Sheepskin Oak and Excel' Cappuccino Leather. Removed and Replaced Lett Hard /Xs Passenger Seat Part Number 2524-014(-530A) Serial Number 990719.4 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand #5 Passenger Seat Pan Number 2524.014(4308) Serial Number 990426-7 Foam and recovered with Townsend LeaMer(Hertlage Brown) Removed and Replaced Left Hand 88 Passenger Seat Part Number 2524-014(530B)Serial Number 030818-6 Foam and recovered with Townsend Leather (Heritage Brown) Removed and replaced Right Hand *7 Passenger Seat Pal Number 2524-014(530A) Serial Number 030708-2 Foam and recovered with Townsend Loather (lenlage Brown) THE FOLLOWING MANUALS AND APPROVED DATA HAVE BEEN UTILIZED FOR BASIS OF REFURBISHMENT: Skandia Flammability Test S254978 as approved by FAA DER Jane Biberstein (DERV 832780-CE) on FM form 8110-3 dated 412312013. Flame Out Flammability Test 4311 as approved by FM DER Herb Reed II (GERT-230293-CE) on FM Form 8110-3 dated 12/23/2013. Skandia Flammabitly Test Report TP 22681 Rev A as approved by FM DER Jane Biberstein( DERV-832780-CE) on FM Form 8110-3 dated 05/02/2013. Three Place Divan installation: Installed (3) place divan part Number 32-0396(A6OPT)7123.K02 S/N 003702 In Accordance with Aviation Fabricators STCIST01572VVI and Skandia FlammiNity test report 5254976 per Jane Biberstein FM DER (DERY-832780-CE) dated 4/23-2013 THE FOLLOWING INTERIOR ITEMS HAVE BEEN MODIFIED: LM Gaily Assy. FUH Galley Assy, Divan Assy. LIM Galley Assy and Install per Delta G drawing OGO-CA01-101 Rev 0, DGD-CA01-101 E0 E-1, UH Galley Install DGD.CA01-501 Rev EO A-1, DGD-CA01-501 Rev IR as approved on FM form 8110-3 per FM DER Donald Mimeo (DERT-750t35-SW) dated March 25 2013. RM Galley Assy and Install per Delta G drawings DGD-CA02.101 Rev 8, DGD-CA02-501 Rev IR as approved on FM form 8110-3 by FM DER Donald Gillespie (DERT-750135SW) dated March 25. 2013, Divan Any per Delta G draynngs DGD-CA09.101 Rev C and OGOGA09-101 E0 D-1 as approved on FM form 6110-3 per FM DER Donald Gillespie (DERT 750135-SW) dated March 25, 2013, Bonner Kit Sideway assy drawing 2553-0036 Rev C, Bonner Sideledge assy drawing 2532-0002 Rev C, Bonner Kit Foldout Table assy «manes 2553.0041 Rev C and 2553-0040 Rev B. Bonner XTI liner Kit knit drawing 2553.0037 Rev C as approved on FM form 8110-3 per Stephen Forness DERT-230238-CE dated Dec 26. 2013. INSTRUCTIONS FOR CONTINUED AIRWORTHINESS: THE REMOVAL OF THE INTERIOR IS ON THE CONDITION OF FAILURE. THERE ME NO ADDITIONAL INSPECTIONS REQUIRED. CONTINUE TO INSPECT lAW MANUFACTURERS ANN, SRM, OR CMM AS APPLICABLE AIRCRAFT EQUIPMENT LIST AND WEIGHT AND BALANCE WERE UPDATED BY THE CUSTOMER END— El Additional Sheets Are Attached FAA Form 337 (10-06) EFTA00011908

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE Willi THE FEDERAL AVIATION REGULATIONS DATE Dec 26, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Beechcrall Corporation MODEL 400A TYPE (Airplane. Radio. Helicopter. etc.) AIRPLANE NAME OF APPLICANT NEXTANT Aerospace Cleveland OH. LIST OF DATA IDENTIFICAITON TITLE REPORT: BEECHJET 400A INTERIOR STRUCTURAL SUBSTANTIATION BEECHJET 400A XTI LINER KIT INSTL. Beechjet 400A, Aircraft Serial No. R K-244 Certification Bases for this aircraft modification is per Type Certificate Number Al 6SW Revision 28 dated April 12,2013 RKG3282 Rev. IR, 8-28-2013 2553-0037 Rev C, dated 8.30.2013 PURPOSE OF DATA DESCRIBE AND SHOW VERIFICATIONS FOR NEXTANT INTERIOR INSTALLATION ON BEECRIET 400A, AIRCRAFT SERIAL NO. RK-244 APPLICABLE REQUIREMENTS ( Ust specific sections) 14 CFR Part 25 §.301, 303, 305, 307a), 365, 561, 571, 601, 603, 605, 609.613 CERTIFICATION - Under authority of appointment under Part 183 of have been vested by direction of the Administrator and in accordance with conditions the Federal Aviation Regulations, data listed above and on attached sheets examined in accordance with established procedures and found to comply Regulations. approval of these data Approve these data and limitations numbered with applicable requirements of the Federal Aviation l(11AB Therefore ■ Recommend H SIGNATURE(S) Or DI s IGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) DERT-230238-CE STRUCR/RES AND DAMAGE TOLERANCE FAA Form 8110-3 (I I.70j surrasmrs PREVIOUS EDITION GPO 901 • 61) EFTA00011909

EFTA00011910

products engineering services, inc. STRUCTURAL ANALYSIS REPORT Forward Calley Cabinet Modifications - Beechcraft Model 400A, RK-244 & RK-305 Document No: 313-ST-001 Revision IR PREPARED BY: Date: December 24, 2013 APPROVED BY: APPROVED BY: Manager - Design Engineering President THIS DOCUMENT CONTAINS INFORMATION OF A PROPRIETARY NATURE AND SHALL NOT BE TRANSMITTED, REVEALED, OR DISCLOSED TO ANYONE WITHOUT THE EXPRESS WRITTEN PERMISSION OF LEE PRODUCTS ENGINEERING SERVICES, INC. ADDITIONALLY, USE OF THE INFORMATION IS PROHIBITED EXCEPT WHEN EXPRESSLY AUTHORIZED BY LEE PRODUCTS ENGINEERING SERVICES, INC. EFTA00011911

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE ii REVISION RECORD Revision Date Description Approval IR 12/24/13 Initial Release See Cover Sheet EFTA00011912

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE iii TABLE OF CONTENTS 1. INTRODUCTION 1 2. REFERENCES 2 2.1 CONSTANT AVIATION DRAWINGS 2 2.2 APPLICABLE SUPPLIER DRAWINGS (AVIATION FABRICATORS) 2 2.3 APPLICABLE LPESI REPORTS 2 2.4 APPLICABLE GOVERNMENT DOCUMENTS 2 3. CERTIFICATION BASIS 2 4. DESCRIPTION 3 4.1 GENERAL 3 4.2 RH FORWARD GALLEY ASSY & INSTL 3 4.3 RH FORWARD DIVAN MODIFICATION 4 4.4 LH FORWARD GALLEY ASSY & INSTL 5 4.5 LH AFT LAVATORY EXTENSION 7 5. STRUCTURAL SUBSTANTIATION 7 5.1 LH FORWARD GALLEY ASSY & INSTL 7 6. CONCLUSION 8 APPENDIX A A.1 EFTA00011913

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 1 1. INTRODUCTION The purpose of this report is to demonstrate the structural substantiation to applicable 14 CFR Part 25 regulations as they relate to the installation and modification of various interior cabinets on Beechcraft Model 400A, S/N's RK- 244 and RK-305, for a FAA Form 337 major alteration, performed by Constant Aviation at their Cleveland, OH facility. The installations consist of the replacement of new RH and LH forward galleys, and modification to the existing closet frame, an extension of the aft lavatory, and a modification to the side-facing divan with the manufacturer's approval. Everything except the new LH forward galley has been accomplished on a previous modification as documented in LPESI Report 222-ST-001. Therefore, only the new galley will be discussed and analyzed in this report. The floorplan for the two (2) Beechcraft Model 400A aircraft is as shown below. s• VA • P• way nom to. I IIVX ISM II CO Figure 1-1 — Floorplan RIO EFTA00011914

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 2 2. REFERENCES 2.1 Constant Aviation Drawings ,v Drawing Np. Rev. Title ... NXT0213-01 IR LH Galley Assembly NXT0213-02 IR LH Galley Installation NXT0213-05 IR Weight Placard Installation NXT0313-01 IR RH Galley Assembly NXT0313-02 IR RH Galley Installation NXT0313-03 IR Divan Assembly NXT0313-07 IR 4" Lay Ext 2.2 Applicable Supplier Drawings (Aviation Fabricators) Drawipg ri9. Rev. . Titla. D-10666 A 3 Place Divan Installation (STC ST01572WI) 2.3 Applicable LPESI Reports Drawing itch . iNvi Titlp ., 222-ST-001 B Miscellaneous Cabinet Modifications - Beechcraft Model 400A 2.4 Applicable Government Documents Document. ,,:,.R64,:. i, Titi#, . .i: ‹ , 14 CFR Part 25 See Sect. 3 Airworthiness Standards: Transport Category Airplanes ANM-115-09-017 1/28/10 Interaction of Interior Structures, Including Seats 3. CERTIFICATION BASIS The Beechcraft Model 400A certification basis is defined Type Certificate Data Sheet (TCDS) A16SW, Rev. 28, the Certification Basis is 14 CFR Part 25 dated February 1, 1965, including Amendments 25-1 through 25-40. The individual 14 CFR Part 25 subparagraphs that will be discussed herein are: 25.301(a)(b)(c) Loads (Amdt. 25-23) 25.303 Factors of Safety (Amdt. 25-23) 25.305(a)(b) Strength and Deformation (25-23) 25.307(a) Proof of Structure (Amdt. 25-23) EFTA00011915

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 3 25.341(c) 25.561(a)(b)(c) 25.601 25.603(a)(b) 25.605 25.607(a)(b) 25.609(a)(b) 25.613(a-e) 25.625(a)(b)(c) 25.787(a)(b) 25.789 4. DESCRIPTION Gust Loads (No Amdt.) Emergency Landing Loads - General (Amdt 25-23) Design and Construction - General (No Amdt.) Materials and Workmanship (Amdt. 25-38) Fabrication Methods (No Amdt.) Fasteners (Amdt. 25-23) Protection of Structure (No Amdt.) Materials Strength Properties ... (No Amdt.) Fitting Factors (Amdt. 25-23) Stowage Compartments (Amdt. 25-38) Retention of Items of Mass ... (Amdt. 25-32) 4.1 General The modification of the Model 400A aircraft consists of replacing the existing RH and LH forward cabinets with new assemblies, modifying the RH forward 3- place side-facing divan by refurbing the divan, and modifying the existing LH aft lavatory cabinet by extending its cabinet structure to close out the area around it. All but the new LH galley are previously installed and certified on previous 400A aircraft, and analyzed in LPESI Report 222-ST-001. 4.2 RH Forward Galley Assy & Instl The NXT0313-01 RH forward galley assembly (installed per NXT0313-02) is the same as that previously installed on other Model 400A aircraft. An illustration of the galley in Figure 4-1. EFTA00011916

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 4 Figure 4-1 - RH Forward GalleyAssy (Contact Pad on Upper Area Not Shown) The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The RH forward galley is installed between the existing RH forward structural partition (which separates the flight deck with the cabin) forward of it and the 3-place side-facing divan immediately aft of it. The lower wider section of the cabinet also encloses the aircraft's air conditioning evaporator mounted separately to the floor structure underneath. 4.3 RH Forward Divan Modification The NXT0313-03 3-place side-facing divan assembly consists of new drawer and fascia door panels onto the existing structural divan frame (Aviation Fabricators D-10666 STC'd Installation Kit - STC ST01572WI). It has also been installed in previous Model 400A aircraft, and analyzed in LPESI Report 222-ST-001. An illustration of the divan assembly is provided in Figure 4-2. EFTA00011917

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-5T-001 REV. IR PAGE 5 Figure 4-2 — RH Forward Divan Mod The divan closeout panels are manufactured from strong lightweight 0.50- inch thick ATR-FP-501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. The STC'd divan frame installation consists of a structural frame (bottom only - no seat backs, cushions form the divan backs), restraint systems consisting of lap belts and shoulder harnesses for all three (3) seated positions, and a D-106699 floorboard modification installation underneath the divan. The frame installed in eight (8) places into the existing cabinet "Brownline" seat track extrusions (inboard and outboard). 4.4 LH Forward Galley Assy & instl The NXT0213-01 LH forward galley assembly is a traditional aircraft galley and is located between the flight deck and the entry door, directly aft of the existing LH forward structural partition (bulkhead). The new galley replaces an existing galley of similar design and the same size. In fact, this new galley assembly is the same as previously installed in other Model 400A aircraft, and analyzed in LPESI Report 222-ST-001, except for a minor change to the upper forward portion of the cabinet. As can be seen in a comparison of the galley illustrations below and Fig. 4-3 of 222-ST- 001, the change consists of eliminating the small recessed condiment tray drawer and extending (down) the existing compartment to compensate. The galley is manufactured from strong lightweight 0.50-inch thick ATR-FP- 501F2 Nomex/fiberglass composite panels from AAR Composites, and fabricated using ATR panel pin construction. An illustration of the LH forward galley is provided in Figure 4-3. EFTA00011918

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT I 313-ST-001 REV. IR PAGE 6 Figure 4-3 - LH Forward Galley Assy The LH forward galley is installed per NXT0213-02 and is installed utilizing the same existing installation attachments - five (5) screw/insert attachments into the existing partition and four (4) floor attachments (2 into the existing seat track and 2 into existing floorboard mounts, and is the same as the previous NXT0313-05 installation analyzed in LPESI Report 222-ST-001. The empty cabinet weights 86.15 pounds (less than the 90.61 pound galley analyzed in LPESI Report 222-ST-001) and the total placarded content weight (Ref. NXT0213-05) of 141.0 pounds (only 1.0 pound more than the 222-ST-001 analyzed galley). Therefore, the total installation weight of the NXT0213-02 galley is 3.46 pounds lighter than that analyzed in LPESI Report 222-ST-001, and is therefore structurally substantiated by comparison. EFTA00011919

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 7 4.5 LH Aft Lavatory Extension The NXT0313-07 LH aft lavatory modification consists of augmenting the toilet cabinet with new panels and compartments between the existing cabinet and the RH aft partition. An illustration of the modification to the aft lavatory is shown in Figure 4-4 (new components in gray). , --7.-z it:Z-7XL It tl FWD Mgr Figure 4-4 — LH Aft Lavatory Extension This is the same as previously analyzed in LPESI Report 222-ST-001. 5. STRUCTURAL SUBSTANTIATION The structural analysis will be generated using traditional means based on conservative assumptions. In determining the Margin of Safety (MS), the resulting analytical result will be subtracted from 1.0 so that any MS greater than 0.0 is considered a positive margin. Also, MS's greater than 3.0 will be listed as "+Ample". 5.1 LH Forward Galley Assy & Instl The critical loadings for the LH forward galley are the 9.0g forward and 3.5g side load conditions. However, since the new galley weighs 3.5 pounds less than the previously analyzed galley, is of similar shape and design, includes that same installed equipment, and utilizing the same aircraft attachment points, the new galley assembly and installation is therefore structural substantiated by comparison. EFTA00011920

Lee Products Engineering Services, Inc. STRUCTURAL ANALYSIS REPORT 313-ST-001 REV. IR PAGE 8 The largest placarded drawer is the top, center drawer in the lower section of the galley, which is placarded for 45.0 pounds. The drawer is restrained by a standard Actron paddle latch, P/N A23511-1S. The applied load to the latch is (the drawer itself + hardware is 5.0 pounds): Applied Load = (5.0 lbs + 45.0 Ibs) x 3.5g x 1.15ff = 201.3 pounds The minimum load rating for the A23511 paddle latch by its manufacturer is 225.0 pounds. The resulting margin of safety is: M.S. = 225.0 lbs / 201.3 Ibs) - 1.0 = +0.12 6. CONCLUSION Based on the above structural analysis, the new cabinets and modification and their installations, listed in Sect. 2.1, into the aircraft have been shown to be compliant with the applicable 14 CFR Part 25 regulations, as defined in Sect. 3 with positive margins of safety. EFTA00011921

D C B A 4 3 2 ba Weed, Oaten(' • OWSOITSOCOOn osoOpyry /it Oaten Pa met) Oftmermo wan covelannla Imailtatoe, gat •Oneirtil 4211041.4vOltarano wan, Su, Si MO Sal fl tt O. OMIT .00.1.C. A f at RR lWeiaw ,O4T m2041,149 4' IV RN Ople u A vitt hit° n. sorrow of uomm O male. Px,vows now as to WRAC! OP Oa I* 0 ,11.0401000 • ft wnall Mitt /0 Lai O• sceerAMINITSINSOOVAN.,4114CaiK 61 ▪ taibic ramighwa Mat Oat la NIL •••0.CCIRO dthi %Welt% s Si PMTS. trilats3 Marl' 00.? • OD rSO .OtanSeli .0.0•04 on elin.ot flange. ...Gia✓ Nat 04.1.1 COMO worts nt man Ontala STOMP 1.73 B.. ito s1 I— .9381101 —]A 1.50 A 2'3511 004 Oda ITN O 0001:04•009 Ott @deaf* 0-12 100. ten a OLCS.ORTIP .301 SAM POT laXONOL5 A23511 .3 $ BASIC PART 511.0905R A 2951$ 39040. .00 X 94 th• .20 ROT nal A nsie lams aose ad A ISM son Nuo 0.40 not WOWS .4••• DASH Na A oat noos Beata 1 .44 45' 41* .5 45- .7 .13 NONE • 9 .75 45' Oa BOLT IIATCRIAL LETTER 9 41904.599. NO e ewe enemewei =1- =0, I %S Henn:- ate C I *23510 seed() It 4.4=95.TolIGHANAVICA Rom) ••••••• MOTO3 UST 091/4TEALIt 1.1100. WA, AST •••• —.CATION 10.11. •" .t.=•••• . - • W . S a n • e l s PS. of Oat if 00 SOY OCAS •Orr rem an-- cosh. Inman a-weans to SNOOP .00, eleC• MIS are 4••••• t Iwo. HIM palm. 2 tam LATCH :78;;: ft 7 : 1::are k ASS'Y. A23 511 SMOGS 4 3 1 A V XIIN3ddV STRUCTURAL ANALYSIS REPORT Lee Products Engineering Services, Inc. EFTA00011922

U. S. DEPARTMENT OF TRANSPORTATION - t.DA it 4/23/2013 FEDERAL AVIATION ADMINISTRATION STATEMENT Of COMPLIANCE WITH AIRWORTHINESS STANDARDS AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE Raytheon S.MODEL NO. 400A 4.TyPE(4SPIAFt. Engintt Propeler. eta) Airplane 5.NAME OF APPLICANT Constant Aviation-CLM . . LIST OF DATA 6.IDENTIFICATION 7,TITLE Design Data 5254976 Rev NC • Skandia, Inc. Flammability. Bunsen Burner Testing Test Specimen P/N's Cont. 25 (represents main entry 27 (represents upper med 28 (represents lower med, 29 (represents pax seat back 30 (represents'seat shrouds) 31 (represents entry Steps, 33 (represents cntrt coltimn 34 (repreientsckpt defog 35 (represents table shrouds) 36 (represents dado and aircelltloSeout) 39 (represents crew seats) Notes: 1) Work accomplished under 2) Flammability tettimitnessing 3) IAW Skandia. Flammability.Streamfine Test Results door trim) surround) lower.Med surround, lh aft blkhd) shrouds, arms, crash pad) cockpit ped step) boots, rudder boots) vent closeout) Skandia Inc. WO # /54976-13, Ref Document ID 9365(). only, does not constitute installation approval of materials. Testing Test Plan 21306, Rev IR, Dated 11/03/11 Page 2 8,PURPOSE OF DATA Demonstration of Compliance with material flammability regtilrenients for S/NRK;244 Q.APPLICAEILE REQUIREMENTS (Llsl specific sections) 14 CFR .Pert 25:853(a) Arndt 25-116 Appendix F Patti (a)(1)(6 14 CFR Pert 25.853 (a)Amdt 25,116 ApPenflixF Part I (p)(1) (ii) 14 CFR Part 25.855 (d).8met 25-118 Appendix F Part I (6) Amdt 25-111 . , 10.CERTIFICATION. under authority vested by direction of the of appointment under 14 CFR Part 183, data listed above and examined In accordance with established protedures and found Standards listed.. 0 Recommend approval of these data I (We) Therefore •, . E.w.: Approve these data • Administrator snd in accordance withrOnditione and 5i-ribbons on attached sheets numbered I — -1— have been to comply with appliCable requirement's of the AinmorthlRess • 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE %DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) DERV-832780-CE' Structural Special FAA—Form 8110-3 COMO-SUPERSEDES PREVIOUS. EDITION EFTA00011923

I i EFTA00011924

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMNISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE March 25, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Beechjet 3. MOOD- NO. 400A 4. TYPE ~ant Rathq tiolicopfix etc) AIRPLANE 5. NAME OF APPLICANT Constant Aviation Cleveland, Ohio UST OF DATA B. IDENTIFICATION 7 ITTI F Document No. DGD-CA08-501 REV: IR Dated: 6/13/12 DGD-CA09.101 REV; C Dated: 1/25113 OGD-CA09-101 EO: D-1 Dated: 2/28/13 DGD-CA13-101 REV: IR Dated: 2/28/13 DGD-CA14-101 REV: IR Dated: 1/31/13 ARMREST RH INSTL DIVAN ASSY DIVAN ASSY CARD TABLE ASSY LAV CLOSET FRAME ------ End of Data NOTES: MOD --- is for Beechjet model 400A (Nextant 400XT variant) SIN RK-244 only. is for the structural design aspects only on the above listed date and an Installation approval. only for regulations specified in the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 8110-3 approvals may be necessary for Damage Tolerance, Mechanical Systeme, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. Al 6SW Approvals are provided separately. 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification 5. Structural 8. PURPOSE OF DATA To provide type data fo FAA approval of structure in support of a return to service on S/N RK•244. This approval is for design data only on a major alteration and is not an Installation approval. 9. APPLICABLE REQUIREMENTS (List specific sections) 14 CFR Part 25.601 Amdt 25-0, 25.603(a)(b), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0, 25.611, Amdt 25-23, 25.613 (1)(b)(c) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (s)(6)(rXdXeX1) Amdt 25-32, 25.789 Amdt 25.32 10. CERTIFICATION - Under authority Pad 183, data Mod above and with applicable requirements of the K Recommend vested by Erection of on attached sheets numbered Aknorthiness Standards approval of teem Mese data the Administrator N/A have and In acc0rdenCe with conditions and limitations of appointment urger 14 CFR been examined In accordance with established procedures and found to comply Listed. data I (We) Therefore 0 Approve !IlaPRESENTATIVE(S) 12. DESIGNATION NUIABERDIS) 13. Ct scSIFICATION(S) DERT-750135-SW STRUCTURAL FM Form 8110-3 (03n o)SuPERSEDES PREVIOUS EDITION EFTA00011925

EFTA00011926

13DLG-CON-0325E U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE March 25, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Beechjet 3. MODEL NO. 4OOA 4. TYPE (AI/plane, Rs:No, HeScepter, at' AIRPLANE 5. NAME OF APPLICANT Constant Aviation Cleveland, Ohio LIST OF DATA 0 IDENTIFICATION 7 TITI F Document No. DGD-CA01-SS-07 REV: IR Dated: 3/6/13 SUBSTANTIATION ANALYSIS ---------- End of Data NOTES: of the Intenor on an Hawker Boochcratt 400A Aircraft Is for Beechiet model 40DA (Nextant 400XT variant) SIN RK-244 only. Is for the structural design aspects only on the above listed data and an installation approval. only for regulations specified In the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 8110.3 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A18SW 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification B. PURPOSE OF DATA Structural substantiation In support of FAA Form 337 for aircraft SIN RK-244. This approval is for design data only on a major alteration and is not an Installation approval. 9. APPLICABLE REQUIREMENTS Wit speck sections) 14 CFR Pert 25.30I(Amdt. 25-23), .303IAmdt. 25-23),...30S(s)(b)LAmdt. ES-23)..307lAmdt 25-231,.34t (Arndt. 25-0), .361 'Arndt. 25-231, .6011Amdt.25-01, .603(eXb)lArndt.25-381,.605lAmdt.23-01,.609[Arndt.23-0],.611fAmdt.25-231,.613(eXbXc)lAmdl.2S-Ob.625 'Arndt. 25- 23], .785(O(bXc)(d)(e)(BlAmdt. 25-32), .78700iAmdt 25-32),.789lAmdt. 25,32] 10. CERTIFICATION - Under authority Part 183, data listed above and with aPPlicable requkemertS Ot the vested by direction on attached sheets numbered Any:tininess Standards approval of these these dee of the Administrator NA have and In accordance with conditions end Inflations of appointment under 14 CFR been examined in accordance with established procedures and found to comply _ Listed. date . Recommend I (We) Therefore g.i Approve !I'M, • • ENTATIvE(S) 12. DESIGNATIoN NUmBERS(S) 13. CLASSIFICATIONS1 DERT-75O135-SW STRUCTURAL FAA Form 8110-3 (mate SUPERSEDES PREVIOUS EDITION EFTA00011927

EFTA00011928

13DLG-CON-0325B V.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADIANISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE March 25, 2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Beechjet 3. MODEL NO. 400A 4. TYPE (Aaptano. Radio, Itkopter. ac) AIRPLANE 5. NAME OF APPLICANT Constant Aviation Cleveland, Ohio UST OF DATA 6 IDFNTIFICATION 7 TITLE Document No. DGD-CA02.1O1 REV: B Dated: 1(25/13 DGD-CA02-501 REV: IR Dated: 6/13/12 DGD-CA13-501 REV: IR Dated: 12/21/12 DGD-CA13-501 £0: A-1 Dated: 2/28/12 DGD-CA04.1O1 REV: IR Dated: 6/13/12 RH GALLEY ASSY RH GALLEY INSTL CARD TABLE INSTL CARD TABLE INSTL SIDE LEDGE ASSY ------ End of Data NOTES: --- is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. is for the structural design aspects only on the above fisted data and an Installation approval. only for regulations specified In the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of all engineering design data for the entire Additional 81104 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A165W Approvals are provided separately. 1. This approval 2. This approval does not constitute 3. Approval le Compliance does not constitute alteration. Flammability, disciplines. 4. For certification S. Structural 8. PURPOSE OF DATA To provide type data fo FM approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an Installation approval. 9. AP PLICAI3LE REQUIREMENTS (List spec& sections) 14 CFR Part 25.601 Arndt 25-0, 25.603(004, Amdt 25-38, 25.605 Amdt 25-0, 25.609 Arndt 254, 25.6111 Amdt 25.23, 25.613 (a)(b)(c) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Amdt 25-23, 25.785 (a)(bXcXdXeXf) Amdt 25-32,25.789 Amdt 2542 10. CERTIFICATION - Under authority Part 183. date listed Stove and on with applicable requirements of the vested by direction of attached sheets numbered Nninwthiness Standards approval of those these data the Administraior N/A htwo and in ecoontanee vilth condbons and limitations of appointment under 14 CFR been examined in accordance with established procedures and found to comply Listed, data U Recommend I (we) Therefore tlif Approve 12. DESIGNATION NUMBERS(S} 13. CLASSIF1CATION(S) !IMISPRESENTATNE(S) DERT-750135-SW STRUCTURAL FM Form 8110-3 (03!10) SUPERSEDES PREVIOUS EDITION EFTA00011929

EFTA00011930

13DLG-CON-0325A U.S. DEPAarruENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1. DATE March 25.2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2. MAKE Beechjet 3. MODEL NO. 400A 4. TYPE (Afro/amt. R.d Hata( et. oft) AIRPLANE & NAME OF APPLICANT Constant Aviation Cleveland, Ohio LIST OF DATA 6 TIFNTIFiCATKIN 7 TiTLE Document No. OGD-CA01-101 REV: D Dated: 3/5/13 000-CA01.101 EO: E-1 Dated: 3/6/13 DGD-CA01-501 REV: IR Dated: 6/13/12 CGD-CA01-501 EO: A-1 Dated: 1/29/13 DOD-CA01-501 EO: A-2 Dated: 3/5/13 LH GALLEY ASSY LH GALLEY ASSY LH GALLEY INSTL LH GALLEY INSTL LH GALLEY INSTL ----- End of Data NOTES: ----- Is for Beechjet model 400A (Nextant 400XT variant) S/N RK-244 only. is for the structural design aspects only on the above listed data and an Installation approval. onlyfor regulations specified in the "Applicable Requirements" block. with additional regulations not listed herein may be required. This form FAA approval of ail engineering design data for the entire Additional 8110-3 approvals may be necessary for Damage Tolerance, Mechanical Systems, Electrical, Weight & Balance, as well as other basis, refer to TC data sheet No. A16SW Approvals are provided separately. 1. This approval 2. This approval does not constitute 3. Approval is Compliance does not constitute alteration. Flammability, disciplines. 4. For certification S. Structural 8. PURPOSE OF DATA To provide type data for FAA approval of structure in support of a return to service on S/N RK-244. This approval Is for design data only on a major alteration and is not an installation approval. 9. APPLICABLE REQUIREMENTS (LIN NAOS marina) 14 CFR Part 25.601 Arndt 25-0, 25.603(06), Amdt 25-38, 25.605 Amdt 25-0, 25.609 Amdt 25-0,25.611, Arndt 25-23, 25.613 (a)(bXe) Amdt 25-0, 25.619 Amdt 25-23, 25.625 Arndt 25-23, 25.785 (a)(b)(e)(dXeXf) Amdt 25-32, 25.789 Amdt 25-32 10. CERTIFICATION - Under authenly vested by direction of Pan 183. data 'sled above and on attached sheets numbensd with applicable requiroments of the Airworthiness Standards K Recommend approval al these I (We) Therefore CE3Approv. these data the Administrator WA have end h accordance with comfit:Ins and Imitations of appointment under 14 CFR been examined In accordance with astatoshed procedures and found to tarn* Listed. data 1 U RE OF DESIGNAT D ENGiNEERING REPRESENTATNE(S) 12. DESIGNATION NuMBERS(S) 13. CLASSIFICATION(SI CERT-750135-SW STRUCTURAL FAA Form 81104 (03/10) SUPERSEDES PREVIOUS EDITION EFTA00011931

EFTA00011932

Aviation Fabricators n e Clinton, Missouri 64735 Report # AF-475FTP August 09, 2010 Rev (A) Functional Test Procedure for STC # ST01572W1 Hawker Beechcraft Cabin Configuration Applicable Aircraft Model: Hawker Beechcraft 400, 400A EFTA00011933

Aviation Fabricators. Inc. Clinton, Missou►i 64735 Revision Log . . AF-475FTP ' 08-0940 Rev (A) Page 2 of 4 Date Rev Pages Description Approved by 08-09-10 A 1 -Added model 400A G.R. Lowe III -Changed data list # to AF-475MDL EFTA00011934

Aviation Fabricators Inc. Clinton, MO. 64735 INSTRUCTIONS FOR CONTINUED AIRWORTHINESS For Interior Cabin Configurations Document No.: AF-528 Revision "IR" Revision Date: 11121111 Applicable to: Hawker Beechcraft model 400A Modified by FAA STC ST01572WI The information in the Instructions (or Continued Airworthiness is FM accepted material and complies with 14 CFR 25.1529, Instructions for Continued Airworthiness. It supersedes or adds to that provided in the Maintenance Manual for the Hawker Beechcraft 400A Aircraft, only where covered in the items contained herein. For limitations and procedures not contained in the Supplement, consult the Component Maintenance Manual, or other approved airplane data. Page 1 of 16 EFTA00011935

aRIFABAt AVIATION FABRICATORS Fax Nov 7, 2012 571 * 00-3 70a CERTIFICATE OF CONFORMANCE This certifies that Aviation Fabricators, Divan, 3 Place with stowage provisions, Beechjet, part number, 32-0396(A60P)T1≥3.K-02, serial number, 003702, was manufactured in, or determined to be in conformity to anc with approved design data and is in a condition for safe operation for installation on aircraft. Vice-President Aviation Fabricators • Central Airmotive . _ EFTA00011936

) REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Todd Ponue Reviewed By: Jeffrey R. Lowe Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. NO. EFFECTED PAGE(S) DESCRIPTION DATE APPROVED BY IR All Initial Release 11/21/11 JRL Per the requirement of Appendix H of 14 CFR Part 25 paragraph 1-125.1 (c), the changes made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 EFTA00011937

1101011 Clinton, MO. 64735 TABLE OF CONTENTS ICA Document No.: AF-528 Revision (IR) Dale: November 21, 2011 DESCRIPTION PAGE REVISION PAGE 2 TABLE OF CONTENTS 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS. 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 EFTA00011938

1 REVISION PAGE Document Title: Instructions for Continued Airworthiness Prepared By: Reviewed By: Updates to the ICA will be made by Aviation Fabricators Inc. Updates will be listed in the log of revisions and the effective pages will be listed below. Log of Revisions REV. NO. EFFECTED PAGE(S) DESCRIPTION DATE APPROVED BY IR All Initial Release 11/21/11 JRL Per the requirement of Appendix H of 14 CFR Part 25 paragraph H25.1 (c), the changes ) made to the ICA by the applicant will be distributed via mail by means of paper copy Page 2 of 15 EFTA00011939

I c. ICA Document No.: AF-528 Revision (IR) n on, . Date: November 21, 2011 TABLE OF CONTENTS DESCRIPTION PAGE REVISION PAGE 2 TABLE OF CONTENTS 3 ABBREVIATIONS AND DEFINITIONS 4 1.0 INTRODUCTION 5 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 9 3.0 DIMENSION AND ACCESS' 11 4.0 LIFTING AND SHORING 11 5.0 LEVELING AND WEIGHING 11 6.0 TOWING AND TAXIING 11 7.0 PARKING AND MOORING 11 8.0 PLACARDS AND MARKINGS 12 9.0 SERVICE INFORMATION 13 10.0 AIRWORTHINESS LIMITATIONS 15 11.0 TROUBLESHOOTING INFORMATION 15 Page 3 of 16 EFTA00011940

n on, MO. 64735 ABBREVIATIONS AND DEFINITIONS ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Abbreviations Definitions AML FAA Approved Model List (AML) Detailed Inspection (DET) An intensive examination of a specific Item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an Intensity deemed appropriate. Inspection aids such as mirrors, magnifying tenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FAA Federal Aviation Administration FAA MIDO FAA Manufacturing Inspection District Office General Visual Inspection (GVI) A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of Inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the Inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed Inspection (SDI) An Intensive examination of a specific Item, Installation , or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 EFTA00011941

1.0 INTRODUCTION ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 CFR 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. Installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MDL Rev C or later FM approved revision. Applicable Aircraft Beechjet 400A Page 6 of 16 EFTA00011942

Tinton, MO. 64735 ABBREVIATIONS AND DEFINITIONS ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Abbreviations Definitions AML FM Approved Model List (AML) Detailed Inspection (DET) An intensive examination of a specific Item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required. FM Federal Aviation Administration FAA MIDO FM Manufacturing inspection District Office General Visual Inspection (GVI) A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection Is made from within touching distance unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of Inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or droplight and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked. ICA Instructions for Continued Airworthiness Special Detailed Inspection (SDI) An Intensive examination of a specific item, Installation , or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required. STC Supplemental Type Certificate Page 4 of 15 EFTA00011943

ICA Document No.: AF-528 Revision (IR) Clinton, MO. Date: November 21, 2011 1.0 INTRODUCTION The purpose of this Maintenance Manual Supplement and Instructions for Continued Airworthiness (ICA) is to provide the maintenance technician with the information necessary to ensure the continued airworthiness of the Aviation Fabricators cabin configuration, per installation number 400-3, when installed in the aircraft passenger cabin in accordance with Aviation Fabricators design data included on Master Data List AF-475MDL and per Supplement Type Certificate (STC) No. ST01572WI. Modifications to an aircraft obligates the operator to include the maintenance Information provided by this document into the operators aircraft Maintenance Manual and operator's aircraft scheduled maintenance program. This document defines supplementary maintenance operations and frequencies recommended by Aviation Fabricators Inc., to ensure the aircraft's airworthiness. The information contained herein addresses the requirements specified in 14 CFR 25.1529, Instructions for Continues Airworthiness and supplements the basic Airplane Maintenance Manual only in those areas listed as pertains to the installation of divan assemblies, as installed per the Aviation Fabricator Master Data List AF-475MDL. For limitations and procedures not contained in this supplement, consult the basic Airplane Maintenance Manual. DATA All information to support the continued airworthiness of this modification is contained in: STC ST01572WI. Master Data List: AF-475MDL. Installation: 3 Place Divan (Ref. installation number 400-3), Installation Instructions D-10666 for P/N 32-0396K-X Parts: P/N 32-0396K-X, 3 Place Divan Installation The new divan assembly (with restraint system) is a self contained complete assembly that mounts to the existing seat track, using standard fittings, in accordance with FAA approved floor plans. The (restraint system) seat belts are attached to the seat track with typical tie down fittings and the inertia reel shoulder harness Is bolted to the divan frame on the outboard side using standard aircraft hardware. Design Change Control All data and changes to the parts and assemblies will be tracked per Master Data List AF- 475MOL Rev C or later FAA approved revision. Applicable Aircraft Beechjet 400A Page 5 of 15 EFTA00011944

Clinton, MO. 64735 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) KOT p I falliew nO MOUM If I / II N ...IVA YAW &W intOTIA40 W>C0.101 RR infa INN rani letWOCOITIAMT LOCMOIOISKWIWitatil I nil FOOT ATTACHMENT TO DIVPN rat no A...nova PIX4 NS1nail MINI 'In WC.101/21t Wit* 01 FOOTA1TACWASIT TO TRACK ISO WAIN,11, Figure 1.0A ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 "War" FOOT AlTPCaCENT ...0 CKWIll WWII" WI Page 6 of 15 EFTA00011945

Inertia Reel Attachment Seat Belt Attachment Figure 1.0C 11.111.11 Clinton, MO. 64735 DIVAN FRAME NUT WASHER INERTIA REEL Figure 1.0B SEAT BELT TIE DOWN FITTING SEAT TRACK REF ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 BOLT Page 7 of 15 EFTA00011946

Clinton, MO. 64735 3 Place Divan P/N 32-0396K-X (Top not shown for clarity) FOOTATTACHMENT TO DIVAN °err 1.0=Erall FOOT ATTPCHMENr TOTRICK main AUCOrilt TOMMIADAMOICCI >RCS Figure 1.0A ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 FOOT ATTPV0MTMCKWn4 GAP Page 6 of 15 EFTA00011947

1 1 1 101 11 Inton, . 473 Inertia Reel Attachment Figure 1.0B Seat Belt Attachment Figure 1.0C ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Page 7 of 15 EFTA00011948

SEAT BOTTOM ASSEMBLY NALL n on, MO. 84735 auguiousssguiLieugeme Figure 1.0D ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Page 8 of 15 EFTA00011949

A ti r r ICA Document No.: AF-528 Revision (IR) nton, MO. 64735 Date: November 21, 2011 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 CFR 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than 1/2 " in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 15 EFTA00011950

SEAT BOTTOM ASSEMBLY Clinton, MO. 64736 CUSHION ASSEMBLY REFFRFN0F Figure 1.0D ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Page 8 of 16 EFTA00011951

A a r ICA Document No.: AF-528 Revision (IR) nton, MO. 4736 Date: November 21, 2011 2.0 INSPECTION REQUIREMENTS AND OVERHAUL SCHEDULE 1. To comply with14 CFR 25.1529, continue the new divan assembly (with restraint system) on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for cabin section inspections. a. The new cabin configuration components require no service other than inspection at normal inspection interval of 200 hours. b. The safety belts require no service other than inspection at normal inspection interval of every 200 hours. c. Perform a detailed visual inspection of each passenger seat bottom and back cushions and covering of all cabin interior components to detect apparent or obvious defects or irregularities. On the cushion assembly, check for cracks and punctures within a 4" diameter circle. The cushion assembly can have no more than three defects found within the 4" diameter circle. If a cushion develops a "lump", check to see if there are no more than two lumps within a 4" diameter circle. Any damage to the cushions outside of the described limits will require them to be replaced. Visually inspect the covering assemblies for holes, punctures, and tears. If the damage to the covering is holes smaller than '/Z' in diameter or a cut at a maximum of 2" in length then the covering is satisfactory. The sewing of the cover assemblies is not to exceed 1" tearing. Any damage to the covering assemblies outside of the described limits will require them to be replaced. d. Visually inspect the divan and seat assembly tubes and diaphragm for cracks and deformation. Damaged conditions could be detected as a crack at the edge of the tube or along the length of the tubes or as a crack, tear or cut found on the seat bottom or back diaphragm. Visually inspect all hardware for excessive wear before and after installation. Replace the seat back and bottom diaphragm if two cracks or deformations are found with a 4" diameter circle. If a tear or cut is found with a maximum of 6", replace the diaphragm. There shall be no broken tubes. There shall be no sharp corners, edges, or protrusions that may Injure passengers. Replace the tubes if they are bent in such a way that they are more than 2" off center. Replace the seat tubes if crack length is found to be .125" or greater. Replace the tube if a dent Is found running longer than 3". Replace the seat tubes if deformation is greater than .25" the overall thickness of the tube diameter. Cracked or broken fasteners or fittings are to be replaced with new immediately. Page 9 of 16 EFTA00011952

Clinton, MO. 64735 ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Code Schedule Date Mech Insp AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AFI-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 15 EFTA00011953

Clinton, MO. 64735 3.0 DIMENSION AND ACCESS: ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight = 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 EFTA00011954

non, MO. 64735 ICA Document No.: AF-528 Revision (IR} Date: November 21, 2011 For repair or replacement of damaged or broken parts or assemblies contact Aviation Fabricators Inc. 2. Inspection Time Limit for the cabin configuration installations: 200 +1- hour inspection for the new cabin configuration components Task Code Schedule Date Mech Insp AFI-100 a. Inspect for damage to upholstery. AFI-101 b. Inspect safety belts for wear, cuts, fraying, damage, and deterioration. AFI-102 c. Inspect safety belt attachment fittings for wear and damage AFI-103 d. Inspect foot fittings for damage, security, and function. AFI-104 e. Inspect seat frame for damage, and corrosion. AR-105 f. Inspect overall seat for fit and function. A. The new divan assembly and restraint system are on the same inspection and maintenance schedule used per the Hawker Beechcraft Maintenance Manual for passenger seats. Page 10 of 16 EFTA00011955

Clinton, MO. 64735 3.0 DIMENSION AND ACCESS: ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 The installation of this cabin configuration does not change the dimensions of the aircraft or alter the access to any existing aircraft system. 4.0 LIFTING AND SHORING No change. 5.0 LEVELING AND WEIGHING Divan Maximum Allowable Seat Weight = 80 lbs w/ Seat Bottom Upholstery Base Weight of Divan Assembly w/ Restraint System = 50 lbs (includes empty drawer weight) 6.0 TOWING AND TAXIING No change. 7.0 PARKING AND MOORING No change. Page 11 of 16 EFTA00011956

ICA Document No.: AF-528 Revision (IR) Clinton, O. 84735 Date: November 21, 2011 8.0 PLACARDS AND MARKINGS Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. LIFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 1S•0288 FASTEN SEATBELTANO SMOULDER HARNESS FOR TAXI. TAKEOFF AND LANDING P/N 32-0377-20 Figure 8.0A 2. A placard stating "to install harness over seat occupant's fwd shoulder" is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. Figure 8.0B Page 12 of 16 EFTA00011957

Clinton, MO. 64735 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 EFTA00011958

Clinton, MO. 64735 8.0 PLACARDS AND MARKINGS ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Three (3) placards are required in conjunction with this modification: 1. The divan installation requires placard part numbers 15-0288 and 32-0377-20 to be installed in plain view of the seat occupants on the forward divider. 35.6 UFE VEST LOCATED IN UNDER SEAT COMPARTMENT PIN 15.0288 FASTEN SEATBELT AND SHOULDER HARNESS FOR TAXI TAKEOFF AND LANDING Figure 8.0A PIN 32-0377-20 2. A placard stating "to install harness over seat occupant's fwd shoulder is sewn on to restraint system part numbers 3088-7-061-2396 and should be legible and easily viewed by the seat occupant. Figure 8.0B illitaill KIrILIZI nnmrunuu • fOISLROWINIllf Page 12 of 16 EFTA00011959

Clinton, MO. 84735 9.0 SERVICE INFORMATION Typical Passenger Seating Service Instructions: A. Upholstery Cleaning: Service Instructions ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 1. Remove seat back and seat bottom cushion assemblies from the interior seating components. 2. Clean the cushions in accordance with instructions issued by the company responsible for the upholstery covering so that knowledge of the upholstery material's fire retardant properties are known and will not be compromised. 3. Clean and inspect restraint system for damage, fraying, cuts or seam deterioration. 4. Inspect all attachment fittings and replace if necessary. 5. Inspect overall interior component for fit and function. Typical Maintenance Instructions: Divan Assembly The divans are self contained complete assemblies that mount to the existing aircraft cabin seat track using standard fittings in accordance with approved floor plans. Refer to Figure 1.0A. Divan Installation Installation of the divan requires aligned the feet on the existing seat track and -attaching the divan legs using standard hardware. Refer to Installation Instruction drawing O-10666 for complete installation details and hardware part numbers. Divan Removal Removal of the divan requires loosening the attaching hardware and lifting the divan from its location on the seat track. The feet will be slid forward or aft to the end of the seat track or a gap in the track for their removal. Cushions Seat back and seat bottom cushion assemblies are removed by simply pulling the cushion inboard away from the Velcro on the sidewall or up away from the Velcro on the pan of the divan assembly, respectively. All covering and upholstery materials must comply with 14 CFR 25.853 as stated on the Finish Materials Listing AF-476. The cushion design and layout were determined & manufactured by the seat installer to match the design of the cabin interior in the aircraft. Refer to Figure 1.0D for Cushion Assembly Reference for basic assemblies. Page 13 of 16 EFTA00011960

Clinton, M0. 647 ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.08. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 EFTA00011961

Clinton, MO. 64735 10.0 AIRWORTHINESS LIMITATIONS ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 The Airworthiness Limitations section is FAA approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FM approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement pads or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FM approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 16 of 15 EFTA00011962

Clinton, MO. 64736 ICA Document No.: AF-528 Revision (IR) Date: November 21, 2011 Inertia Reel Inertia reel removal is accomplished by loosening attaching hardware and removing from the divan frame bracket. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0B. Seat Belt Seat belt and removal is accomplished by loosening attaching hardware and removing from the existing aircraft seat track. Refer to Installation Instruction drawing D-10666 for complete installation details and hardware part numbers. Refer to Figure 1.0C. B. RECOMMENDED OVERHAUL PERIODS No additional overhaul time limitations and requirements apply to the Aviation Fabricators' interior cabin configuration. Page 14 of 15 EFTA00011963

Clinton, MO. 64735 10.0 AIRWORTHINESS LIMITATIONS ICA Document No.: AF-528 Revision (IR) Dale: November 21, 2011 The Airworthiness Limitations section is FM approved and specifies maintenance required under Sec. 43.16 and 91.403 of the Federal Aviation Regulations unless an alternative program has been FAA approved. There are no new (or additional) Airworthiness Limitations associated with this equipment and /or installation. 11.0 TROUBLESHOOTING INFORMATION Refer to the existing Aircraft Maintenance Manual for troubleshooting the 3 place divan installation that is required beyond the information found on the installation drawing D-10666. For replacement parts or repair of damage parts: Contact Aviation Fabricators at Troubleshooting this installation should only be accomplished by FAA approved repair stations with the appropriate ratings or appropriately rated operator/individuals, with required test equipment and service data. Page 15 of 15 EFTA00011964

U. S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH AIRWORTHINESS STANDARDS 1.DATE $/02/2013 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION 2.MAKE Raytheon 3.MODEL NO. 400A 4.TYPE(AiVane• Engine. PrOplber. etc) Airplane 5.NAME OF APPLICANT Constant Aviation-CLM LIST OF DATA 6,IDENTIFICATION 2.TITLE TP 22681 Rev A Dated 05/02/2013 Skandia, Inc. Flammability Oil Burner Testing and Vertical Notes: 1) Work accomplished under 2) Flammability test witnessing materials. Test Report Burner Testing Skandia Inc. WO # 254987-13, Ref Document ID 93685. only, does not constitute installation approval of the 8.PURPOSE OF DATA Demonstration of compliance with material flammability requirements for S/N RK-244 9.APPLICABLE REQUIREMENTS (Ust specific sections) 14 CFR Part 25.853 (a) Amdt 25.116 Appendix F Part I (a)(1)(ii) 14 CFR Part 25.853 (c) Amendment 25-116 Appendix F Part II 10.CERTIFICATION - Under authority vested by direction of the of appointment under 14 CFR Part 183, data listed above and on examined in accordance with established procedures and found Standards listed. O I ( ) Therefore Recommend approval of these data `?.{ECApprove these data Administrator attached to comply and in accordance with conditions and limitations sheets numbered have been with applicable requirements of the Ainvorthiness 11.SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE 12.DESIGNATION NUMBER(S) 13.CLASSIFICATION(S) I ERY-83278O-CE Structural Special FAA Forni 8110-3 (03/10) SUPERSEDES PREVIOUS EDITION EFTA00011965

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FAA FORM 8130-6, APPLICATION FOR U.S. AIRWORTHINESS CERTIFICATE Form Approved O.M.B. No.2120-0018 Expiration Dam 02/28/2013 a APPLICATION FOR U.S Deparonen U.S. AIRWORTHINESS bTrenStaaratten Federal !Mallon CERTIFICATE ANnuNarstion INSTRUCTIONS • Print or type. Do net wraci n shaded cent then are for FM use only &lam* colonel only Man aL4hOrited FM Remesentalive If additional space a reparad, For Pahl Sections use indented Wool permits ccmplete IL W. and VII as coolIcable. I. AIRCRAFT DESCRIPTION I. REGISTRATION NARK N493LX 1 ARCRAF I OuiLOER'S NAME Pam/ Raytheon Aircraft Co 3. AIRCRAFT MODEL DESIGNATION 400A 4. YR MFR. 1999 FM CODING 5. A.RCRAFT SERIAL NO. RK-244 6. ENGINE SULZER'S NAME (5 Williams International 7. ENGINE MODEL DESIGNATION FJ44-3AP B. HOMER OF ENGINES 2 9 PROPELLER BURGERS NAME Plate N/A 10. PROPELLER WO a DESIGNATION It AIRCRAFT IS nentia emmicaan N/A I IMPORT ; es 0 D cc ta G a ra AN es 0 APPUCAT ION IS HEREBY MADE FOR **a eforese.4...) I A I STA/COMO AIRWORTHINESS CERTiFICATE (woo sematm/ I I 'Knit I I mol l I maeoll I I ^AA"' I I ce's's" . I I Nato' I I ob'm B I SPEOAL AI IMORTFINESS CERTIFICATE cora swoon io•NI 7 PRIMARY 9 LIGHT-SPORT «—t,-, I Inman, I fr oar-Paractsa I_ I Weigi-Stetanved I I Oder !keret Wan Air 2 UNITED MORMON/M. 1 CLASS I 5 Mama dessa 2 CLASS rl 1 AGRICULTURE MO PEST CONTROL 2 AERIAL SURVEY 3 AERIAL ADVERTISING 3 RESTRICTED rens etesam(Al Iii 44 COI4WWII 4 FOREST fat tlie• tO4S/649 5 PATRIXUNS 0 HEATHER CONTROL 0 OTHER (Socorrt 1 if RESEARCH AANCCEVELOPME DEVELOPMENT 2 AMATEUR BUILT 3 EXHIBITION 4 AIR RACING 5 CREW TRAINING 6 MARKET SURVEY 0 TO SNOW CCMPUANCE W(I14 THE CfR 7 OPERATING "Mg Coney KIT MALT AIRCRAFT I M Eating Mart Hamm an eineortetess certficals 0 do real ma 1103.1 EXPERIMENTAL pate of eget) rowa:Lac a OPERATING 68 OWING UOI-Sport KR-bult LIGHT-SPORT SC OPerlen9 lighl-spcm pravfousle 'sued spa* Ilalt-Mierl Caletexy eirtvorthatass 21.190 colficalti tea m121.190 9 UNMANNED 9A RESEARCH NC DEVELOPMENT I K I I CREW TRAINING AIRCRAFT 98 MARKET SURVEY I FERRY FUG HT FOR REPAIRS. ALTERATIONS. MAINTENANCE. OR STORAGE FLIGHT PERMIT FROM AREA OF IMPENDING SPECIAL !MOW. 2 EVACUATE DAN3ER 8 0440.001 b be P:04444084 namaereis S•ex. VI a• vw es 4wecrat el town. lag 3 OPERATIONIN EXCESS OF MAXIMUM CERTIFICATED TAKECCF HEIGHT 4 CEUVEMNG OR EXPORTING 16 I I PRODUCTION FIGHT TESTING 6 CUSTOMER DEMONSTRATOR RAMS CI 6 MULTIPLE mRACRTHMESS CERTIFICATE gem MOstainmaid Oessorrarramesser astma, a melema/ i ft E at ii 1 li A REGETERED OWNER IF DEALER. CHECK HERE--ss I ma sin COIRCIAtt/Intia feifelnii NAME F igh Options LLC Richmond Heights .OH 44143 8 AIRCRAFT CERTIFICATION OASIS tOmm aeons. macs ramemec. ems. a$ evanesce AIRCRAFT SPECIFICATION OR TYPE CERTIFICATE DATA sasEET crass se and /imam no/ N/A / AIRWORTHINESS ORECTIVES ensecti444amaessam es am mei mee melee es 4004, a no wAD SOOWEAMMT ~YAP nes ilsesety same n fl eas al 4•044444 Bi Weekly 2013-22 10/21/2013 - 11/03/2013 AIRCRAFT LISTWG (Caaeme e.1003 N/A SUPPLEMENTAL TYPE CERTIFICATE AM ranks &lath SIC Acarnembel N/A C. AIRCRAFT OPERATION AND WuNTENANCE RECORDS I CHECK IF RECORDS IN COMPU c ANCE MATH 417 art, lat91. TOTAL AIRFRAME HOURS TTAF 8578.62 3 EXPERIMENTAL ONLY myna., /*was" pi ati. saw <e nrage) 14.82 0. CERTIFICATION slant, e•My Malian aceardwo6 `IS TIO• 49 al MA Urges Man alretalhaess canifiona racemrsIed. we mastered caws (or Ns gen° of Ma Mutt dsunbad Raw DIM We Wash CRCs 41101 1St RN WRNS Feel* Aviation Recatatons. SCout the is rageletinld Yana* Federal Ablation AcireNstralcet In ' DATE OF APPUCATON 1 /18/2013 illibila Agent H ill i A THE NRCRAFT CESCRO3E0 ABOVE HAS BEEN INSPECTED ANI)FOUNO SCOW/ BY: Crew we NeartstaY 2 14 CFR pwl 121 CERTIFICATE MADERO" cantariel 3 I CERTIFICATED MECHANIC gos Cameos on 6 CERTIFICATED REPAIR STATION (C.• Cfnea• Ab ) 5 AIRCRAFT MANLIFACTURER patesere rem/ DATE TITLE SIGNATURE V. FAA REPRESENTATIVE CERTIFICATION tow ALL aeons • Mom M.,4 ova) ,s THE CERTIFICATE REQUESTED A. I And Mat re Sand demoted in San I cc VII mow raparemerts rim 4 /JAEsfwENT CR IAOCCICATICN OF CURRENT MRIACRTHINESS CERTif iCATE avower., for a special not pooh weer Section VII .as conned Dr FM INSPECTOR FM DESIGNEE CERTIFICATE HOLDER UNCER 14 CFR 65 14 CF 121 OR 135 14 II DATE 11/16/2013 meCOFSDO OFFICE CLE-25 FAA Form 81304 (4J 11) AI P 'anus Editions Stpetseded Electronic Format -PO F RECtIvED QD co a 0 L. a PJ 0 DEC 1 a 2013 CLE — 01.22 EFTA00011967

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