1) REFERENCES 1 MIL-HDBK-5F Metallic Materials and Elements for Aerospace Vehicle Structures. 2 FAR 25. Page 2 DA- G1085 Rev NC 05-08-2000 SDNY GM 02754002 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240924 EFTA01326517

SDNY_GM_02754003 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240925 EFTA01326518

r • 2) INTRODUCTION This report provides structural substantiation on the modification of the LH Fwd divan on Gulfstream G-IV model aircraft, S/N 1085. The existing three place divan assembly is modified by moving the existing center truss structure aft by 4.75 inches and the fwd truss structure fwd by 4 inches. The center truss structure is connected to the outboard truss structure, however the basic outboard truss design has not changed significantly. The divan framing is made of 6061-T6 SQ tubing (for vertical and horizontal members) and Rectangular tubing for diagonal members. The divan was a TSO item and with this modification, the TSO Tag is removed and the divan is substantiated under a new part no. for the following load conditions. The gust condition of 7.2 G Down and 9.0 G Fwd load. 3.0 g side and 4.5 g up load. Divan new part number is: 50100-1085 I 40.00- 65.88 1 o 0 0 fa n VIEW B-B OLD FOOT PATTERN Exism4 a) Page 3 DA- G1085 Rev NC 05-08-2000 SDNYGlvl02754004 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240926 EFTA01326519

• • SDNY_GM_02754005 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240927 EFTA01326520

3) STRUCTURAL SUBSTANTIATION: 3-PLACE DIVAN ASSEMBLY 9.0 O Fwd load Modified 3- Place Divan Weight including cushion, : 78 lbs Occupants : 3 x 170 = 510 lbs Total weight : 510 + 78 = 588 lbs .Total load : 9.0 x •588 = 5;292 lbs Attachment fitting loads The divan is tied down with six seat track fittings(Anchora) to the aircraft seat track. Load per fitting: 5,292 /6=882 lbs (shear) Tension load per fitting: (5,292 lbs x 22 in ) / 2 x 69.87 in = 833 lbs Minimum allowable for Tension for the seat track fitting is : 4000 lbs Minimum allowable for Shear for the seat track fitting is : 2000 lbs 1 MS = 1 —+ 1.05 [(882 / 2000)2 + (833 / 4600 )2] 1/2 X et t'x I ( ) Co 40.0 69.87 ° (%) ° (s) 4(5) ° (J (t-itotqcmD C onIF Page 4 DA- G1085 Rev NC 05-08-2000 SDNYGlvl02754006 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240928 EFTA01326521

• • SDNYGM02754007 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240929 EFTA01326522

3) STRUCTURAL SUBSTANTIATION: 3-PLACE DIVAN ASSEMBLY 9.0 G Fwd load Cont.d Fwd load on the divan, Outboard frame The Shoulder Harnesses are installed to the outboard divan frame for take off and landing. (The existing configuration). The center truss structurels connected to the outboard truss structure and by moving it to the aft by 4.7 inches resulted in minor redesigning of the outboard truss frame. The changes to the outboard truss structure are that the compression member (a) is longer by 3 inches and the tension member (b) is shortened by 4 inches. Since the basic truss design has not been changed, therefore it is still structurally adequate under fwd load and the change is considered minor. REMOVE LEGS (EX ISM-114G.) A I n ' tan via to -3 Cita ona,4 =WAD tat %IX ar PUY< FV11)..—.) (MODIFIED) Page 5 DA-G1085 Rev NC 05.08-2000 SDNYGlvl_02754008 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240930 EFTA01326523

SDNY_GM_02754009 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024093I EFTA01326524

3) STRUCTURAL SUBSTANTIATION: 3-PLACE DIVAN ASSEMBLY Center inboard/outboard truss structure The center piece moved to the aft and installed back as the original. Fwd . inboard/outboard truss structure The fwd truss structure moved to the most fwd frame. A SQ. Tube bridge is installed between the two top frames (fwd frames) and the existing vertical tube is welded to it and to the base frame. 0 groat.. 8 GUSSETS 10 BUSHING Page 6 DA- G1085 Rev NC 05-08-2000 SDNYGIv1_0275401 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240932 EFTA01326525

SDNY_GM_02754011 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240933 EFTA01326526

31 STRUCTURAL SUBSTANTIATION: 3-PLACE DIVAN ASSEMBLY 7.2 O Down load Pz = 7.2 g x 78 lbs = 562 lbs Load per three truss structures (inboard / out board): 562 lbs / 3 = 187 lbs See the end view (fwd end), load on the vertical post (-1). The post is at 18° Angle. Assume total 187 lbs acting on the -1 tube. Pz = 187 / COS 18° = 197 lbs for SG. Tubing: I= .0324 in4 A = .2300 in2 L = 12.62 13 inch PCR= n2 EI 2 /L 2 L=13 inch, E= 9.9X 106 PCR= C(712 E x .0324 ) / 132 -4 PCR = 606 lbs MS. = 606 / 197 -1 = + 2.0 -2 a ai tn) 1413 /D VIEW A-A M:177 165 10 BUSHING 0 Page 7 DA- G1085 Rev NC 05-08-2000 SDNYGIv10275401 2 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240934 EFTA01326527

• • SDNY_GM_02754013 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240935 EFTA01326528

3) STRUCTURAL SUBSTANTIATION: 3 PLACE DIVAN ASSEMBLY 7.2 G Down load Cont.(' Strength of the welded joint. The weld area is .176" x .176" x .25" Shear Stress of weld for a 6061-T6 material : 9,000 psi (ref. Lockheed weld design manual). P. = Area x Shear Stress T .707 S en' \2G . Area =tx L • 11 6" P = [(.707 x .176 x .25)1 x 9,000 = 280 lbs weld strength Pz= 197 lbs applied load MS = 280 / 197 -I = + .42 Page 8 DA- G1085 Rev NC 05-08-2000 SDNYGlvl02754014 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240936 EFTA01326529

• • SDNYGM02754015 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240937 EFTA01326530

C CCD L. rn H n 77 70 0 H rn n rn 0 77 rn 70 -o 70 Gl 70 cr) Co c) 2 y l to cu 0_ °,,, on C B A 4 M =XI MM Row =Man c was APOO .0 V= MORI MOW mlb0 COMM 00100115/11 07011•01 NM =ACME a UMW, MICR IteaCCI ORMAN Ram Dal WOO CC V Ti. 1. RELOCATE LEGS ON EXISTING DIVAN TO MAKE ROOM FOR 2 12 MAN LIFE RAFTS(61LBS EA), TO REPLACE ON 12 MAN AND ONE 6 MAN LIFE RAFT. 2. CUT LEGGS TO BE RELOCATED CAREFULLY, DO NOT DAMAGE REMAINING TUBING. 3. WELD LEGS PER MIL-W-2219 CLASS B, DYE-PEN INSPECT. ALL WELDED AREAS. NOTES: UNLESS OTP.ERMSE SPECIFIED 4 3 3 4 2 1 tatorrou twt 1 —41 -" 4 -$0 1 -0 -8 -7 -S OMMIIIR MS 0511-1 9(T1 waitasmasabinta _ 7V X I . 4541-19 %RIM VA1-11 DIM MR711:. 1-5 ;OM I'% A' X OM 5XCI 'As") 1. X A. X Of) KV Mt* • 8 1,45. ROL SO l'AC csr K41-11 SO ME I' ye', ou SO MI K01-10 PER 114-1-7:0/4 KR n -!-)Z/4 re in-i-70010 KR Vw-l-705/1 KA v•-4M1/1 7 • x 1041-10 'RI NOW S. , PM WOO OISCROPVI PAP, LEVI WROACATOR A/ 5//11005 41/N (480-40 P<Y, ASV tee) CM Ns= •••=.0 C. TAYLOR 5/1/0) MOM gmG.:eta won, dna 424,2-4011 DIVAN MODIFICATION GIV SIDE FACING freartivi 2 • C $.4.1 1/I 1 SAVED AS: Ise I Or 1 1w— I-- 50100-1085 EFTA01326531

• SDNYGM0275401 7 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240939 EFTA01326532

In co Cl -O 0 Cl 0 0 -O -O U) 9° N N O 2 ‘,1 4 II 3 4 2 REMOVE LEGS VIEW LOOKING OUTBOARD LEFT SIDE OF PLANE BEFORE MODIFICATIONS, REMOVED LEGS NOTED IN BLUE <---AFT FWD 3 t 2.' MOOS XVI MOIR MIAOW, MINE DIVAN MODIFICATION ON SIDE FACING J -' 501o0—lo&S 1/1 I sno /s: I —.dor 11'w EFTA01326533

SDNY_GM_02754019 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024[1941 EFTA01326534

4 -- tr) 0 c0 co oo In 0 O rnr z ce I- <▪ iL 0_ 0 U O L. (.4 G1 ; 3 ▪ Z < --- ‘=' O I n I 0 SDNYGNL02754020 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240942 EFTA01326535

SDNY_GM_02754021 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240943 EFTA01326536

Ln C CO rn H n 0 H rn n H rn 0 70 rn 77) -O 70 Gl 70 -O CO Co (-O O 2 'O I0 tl o_ 4 3 1 2 1 1SSET ADDED 3 PLACES O 58 O 7 O B NEW LEG AND ATTACHMENT 4S 3/4 SCALE 4 3 ..2 VYal%Y.0 win Lost q DIVAN MODIFICATION GIV SIDE FACING 7 — lb L'40 50100-1085 1 I -S K6 ruc EFTA01326537

SDNYGM02754023 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240945 EFTA01326538

00 VIP S. MEI JI C. CO O Os C) If) Cll Ifi CI • O I Cu r A In r, SONY GI,L 02754024 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00240046 EFTA01326539

SDNY_GM_02754025 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240947 EFTA01326540

cr) co H Cl -O 0 0 0 -O -O Go C) f-r g CD_ -9 GUSSET 3 REQUIRED 910.88e -12 DOUBLER DIVAN MODIFICATION GIV SIDE FACING 7 50100-1085 r: isvio I... or EFTA01326541

SDNY_GM_02754027 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240949 EFTA01326542

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r SDNY_Gtv1_02754029 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240951 EFTA01326544

In co H Cl 0 Cl 0 —O 6-) -O V) .O N N O 00 Iv g CL (6, - IJ In 4 3 2 1 4,88 4.06 -8 GUSSET 1.50 25.78' -2 DETAIL 115. 8° 11.61 -4 DETAIL 1.25 00.94 00.62r" -10 BUSHING 4 3 -7.19 12.62 \-) 71 2 PLS -1 DETAIL 15.00. 00.94 23.52 -3 DETAIL 25.08 2 -11 DETAIL Nte12800 ...mow., WI OWL II, III 01, Om 1.11411 DIVAN MODIFICATION GM SIDE FACING 7 i SINEO I". 3 Of 6 riC 50100-1085 1 EFTA01326545

SDNY_GM_02754031 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240953 EFTA01326546

• • 4- co 8 GUSSETS A 10 BUSHING (O (O 4- SDNYONL02754032 N 03 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00240954 EFTA01326547

• • SDNY_GM_02754033 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240955 EFTA01326548

9c6ortoo-vid9 (.1 co H n -O 70 0 n H H 70 70 73 Gl 7J Cr) Co lO O 2 I— Jo F t= OJ Cl. 4 4 3 4 2 I 1 A A B - 12 DOUBLER WELD TO - 3 LEG 2 PLCS VIEW LOOKING OUTBOARD LEFT SIDE OF PLANE (---AFT FWD 4 3 2 MAYO " DIVAN MODIFICATION GIV SIDE FACING - 50100 - 1085 .. SOW AS, f se 2 Of 6 PNC 1 EFTA01326549

SDNYGM02754035 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240957 EFTA01326550

, lar .3 iI lei Oil illi . SDNY GM 02754036 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240958 EFTA01326551

• • SDNY_GM_02754037 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240959 EFTA01326552

. U.S. DEPARTIMI ..TT OF TRANSPORTATION W FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATIONS DATE May 15, 2000 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE GULFSTREAM AEROSPACE MODEL NO. G-IV TYPE (Airplane, Radio. Helicopter. etc.) Airplane NM E OF APPLICANT PETERSEN AVIATION LIST OF DATA IDENTIFICATION TITLE DOCUMENT: - SY-GL1085 Rev. "NC" Dated: 5-15-2000 • STRUCTURAL SUBSTANTIATION - TWO 17 INCH LCD MONITOR INSTALLATIONS RH/LH, FWD I AFT AND ENTERTAINMENT SYSTEM MODIFICATION: This approval indicates the data listed above demonstrates compliance only with the regulations specified by paragraph and subparagraph listed below as 'Applicable Requirements: (Compliance to additional regulations not listed here may be required.) This form (does not) constitute FAA approval of all the data necessary foi substantiation of compliance to necessary requirements for the entire alteration/repair. ,(DETAIL DESIGN AND STRUCTURAL APPROVAL ONLY) PURPOSE OF DATA TO SUBSTANTIATE THE INSTALLATION OF TWO 17 INCH LCD MONITORS AND ENTERTAINMENT SYSTEM MODIFICATION ON GULFSTREAM G-IV AIRCRAFT, S/N 1085 ONLY APPLICABLE REQUIREMENTS (list specific sections) FAR 25.301, 25.303, 25.305, 25.307, 25.561, 25.603, 25.605, 25.607, 25.609, 25.613 and 25.789. CERTIFICATION - Under authority vested by direction of the Administrator and in accordance with conditions and limitations of appointment under Part 183 of the Federal Aviation Regulations, data listed above and on attached sheets numbered • have been examined in accordance with established procedures and found to comply with applicable requirements of the Federal Aviation Regulations. I (3.11e) Therefore C Recommend Approval of these data l= Approve these data . SIGNATURE(S) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION. mania /paraders- DERT-605434-NM Structures Howard L. Patterson FAA Form 8110.3 (11-70) SUPERSEDES PREVIOUS EDITION GPO 901.613 SDNYGlvl02754038 It SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40960 EFTA01326553

• • SDNYGM02754039 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024[1961 EFTA01326554

• AIRCRAFT MODEL: GULFSTRFAM G-IV • REPORT NO. SY-GL1085 8/N NO. : 1085 DATE: 5-15-2000 SYNCRO AIRCRAFT INTERIORS STRUCTURAL SUBSTANTIATION- 17 INCH LCD MONITOR INSTALLATION RH/LH, FWD/AFT BULKHEAD- MOUNT. AND ENTERTAINMENT SYSTEM MODIFICATION PREPARED BY: SHAHNAZ GALANTE 5-15-2000 APPROVED BY: HOWARD PATTERSON 5-15-2000 REV DATE SDNY GM 02754040 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240962 EFTA01326555

• • SDNY GM 02754041 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240963 EFTA01326556

TABLE OF CONTENTS 1) References 2) Introduction 3) Geometry 4) Structural Substantiation: Fwd and Aft RH/ LH 17" LCD Monitors Installation Page 1 SY-GL1085 Rev NC 5-15-2000 SDNY GM 02754042 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240964 EFTA01326557

• • SDNYGM02754043 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240965 EFTA01326558

1) REFERENCES 1 MIL-HDBK-5F Metallic Materials and Elements for Aerospace Vehicle Structures. 2 FAR Part 25 Page 2 SY-GL1085 Rev NC 5-15-2000 SONY GM 02754044 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240966 EFTA01326559

• • SDNYGM02754045 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240967 EFTA01326560

2) INTRODUCTION This report provides structural substantiation for the installation of twol7 inch LCD Monitors. One is mounted onto the Aft Bulkhead of the Fwd RH existing storage Cabinet (STA193) and the second one is mounted onto the fwd side of the Aft LH Bulkhead(STA442). The Aft LH Bulkhead is more like a divider than a load carrying Bulkhead for the existing Galley. The new 17 inch LCD monitors are installed in place of existing 14 inch monitors in exact locations. Also in the Fwd LH Comp (STA193). One Panasonic VCR Model PV4662, Weight 7.0 lbs is exchanged with DVD player model PS86802 , Weight 7.0. The subject installation and modification is on Gulfstream G-IV model aircraft SIN 1085. The subject installation is analyzed for the most critical load conditions. The following load factors are used herein: 9.0 G Fwd 7.2 G Down 4.5 G Up 3.0 G SIDE All the critical parts have been investigated, those not shown are considered not critical. Page 3 SY-GL1085 Rev NC 5-15-2000 SDNYGIvl_02754046 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240968 EFTA01326561

• • SDNY_GM_02754047 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240969 EFTA01326562

31 GEOMETRY- FWD/AFT RB/LR Bulkhead Mount, 17" LCD Monitor Installation art,Pith 0140 JO- tig„.a..12 Ebor ..3(ob ;opt ALIJA. iteu4Fbecibby cOrar Tritirt4ti Seal gevii LCD monin-00- rto Sand i7-‘43s. A041.e £ts4Y t.P /404434. •e./r Nett law. ovr-eor °La Mon/ wog- *" saitsch.I 7 Page 4 SY-GL1085 Rev NC 5-15-2000 SDNYGIvl_02754048 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40970 EFTA01326563

• • SDNYGM02754049 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024097I EFTA01326564

• • 4) STRUCTURAL SUBSTANTIATION- FWD/AFT R.H/LH Bulkhead Moon 17" LCD MonitorInstallation The subject LCD Monitor is installed on the Aft Bulkhead of the RH Fwd Cabinet with four Z- Brackets, top and bottom, Inb'd/Outed. The Z- Brackets are installed to the bulkhead with two #10-32 screws and NAS1836-13 inserts. Fwd LCD Installation WEIGHTS: New 17 inch LCD Monitor, Model # 170MP Total : 12.0 lbs Old 14 inch LCD Monitor. Weight 7.9 lbs 9.0 G Fwd load Px = 9.0 x 12 = 108 lbs total fwd load Load per 2-Bracket Px = 108 / 4 = 27 lbs Z- Bracket Supports. 2024-T3. t = .063" L = 5.0 in Rt = Px (2.0 in) / .50 in Rt = 108 lbs (tension in insert) Load per fastener. P = 108 /2 = 54 lbs (Tension) Bending stress of 2-Bracket, jb= 6M /b 12 width, b = 5.0" Max bending moment : 27 lbs x 1.0 in = 27 in-lbs .fro= 6 x27/5.0 in x.0632 =8,163 psi Ftu = 62000 psi for 2024-T3 (ref 1) MS = 62,000 / 8,163 -1 = HIGH Page 5 SY-CL1085 Rev NC 5-15-2000 SDNY Clvl 02754050 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240972 EFTA01326565

• • SDNYGM02754051 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240973 EFTA01326566

• • 4) STRUCTURAL SUBSTANTIATION- FWDIAFT RA/LB Bulkhead Mount, 17"_LCD Monitor Installation Cont'd Fwd LCD Installation. Contd 7.2 G Down load Pz = 7.2 gx (12.0 lbs ) = 86.4 lbs Take the overturn by the upper and lower bracket Rrop= - Racer= (86.4 lbs x 2.0" ) / 12.88" Rrop = - Raman = 13.42 lbs Load per upper and lower bracket Down load Pz bears on the bottom Z-Bracket Rzsocke = 86.4 lbs Load per inserts (NAS 1836-3) Shear load: 86.4 lbs / 2 = 43 lbs Check bendino of the Z- Bracket Bending stress, fb= 6M /b tz width, b = 5.0" Max bending moment 86.4 lbs x 1.0 in = 86.4 in-lbs fb=6 x86.4 / 5 in x.0632 = 26,122 psi Ftu = 62000 psi for 2024-T3 (ref 1) MS=62,000/26,122 -1 = +13 1.5 a Aft load condition! Px = 1.5 x 12 =18 lbs (this load bears on the aft bulkhead) gst...(astree,,) • Esti Page 6 SY-GL1085 Rev NC 5-15-2000 SDNYGlvl_02754052 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40974 EFTA01326567

• • SDNY_GM_02754053 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240975 EFTA01326568

• 4) STRUCTURAL SUBSTANTIATION- FWD/APT RHJLII Bulkhead Monnt. 17" LCD Monitor installation Coned Fwd LCD Installation. Contd Check flange bending of the Z- Bracket Bending stress, fb= 6M /b t2 width, b = 5.0" Max bending moment: 13.42 lbs x. .50 in = 7.0 in-lbs fb= 6)(7.0 15 in x .0632= 2,116 psi Ftu = 62000 psi for 2024-T3 (ref 1) MS = HIGH Check inserts. The largest Shear load and Tension Load on NAS1836-13: Pt = 54 lbs Ps = 43 lbs (Ref. P5,6) Insert Analysis Core shear allowable from: HEXCEL: 150 psi PALLowASLE = (150)(7t)(11 x .40) = 136 lbs Tension Bearing Allowable = Fen, = 121,000 psi (2024-T3) PALLOwASLE Br = (121,000 psi)(.02)(.451) = 1091 lbs Calculation of Margin of Safety Rs = 43/1091= .040 , R-r = 54/136 = .40 MS = 1/Rs + -1= 1/.040 + .40 = +1.27 Page 7 SY-CL1085 Rev NC 5-15-2000 SDNYGIvl_02754054 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240976 EFTA01326569

• • SDNYGM02754055 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240977 EFTA01326570

) STRUCTURAL SUBSTANTIATION- FWD/AFT RH/LH Bulkhead Mount, 17" LCD Monitor Installation Cont'd Aft LH LCD Installation WEIGHTS: New 17 inch LCD Monitor, Model # 170MP Total : 12.0 lbs Old 14 inch LCD Monitor. Weight 7.9 lbs.. 9.0 G Fwd load Px = 9.0 x 12 = 108 lbs total fwd load This load bears on the bulkhead (this bulkhead is more like a divider than a load carrying bulkhead for the existing Galley, STA 442.). This Monitor installation is identical to the Fwd RH one shown on pages 4,5,6,7 . Page 8 SY-GL1085 Rev NC 5-15-2000 SDNYGIv1_02754056 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240978 EFTA01326571

0 0 SDNYGM02754057 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240979 EFTA01326572

AIRCRAFT INTERIORS, INC. EMPTY WEIGHT RECORD Aircraft type. Gulfstream GIV Serial # 1085 Registration- N677RP Weight Arm Moment Current Empty Weight from Jan. 28, 00 41887.7 460.95 19308255 Removed R/H 1 singe seat -67.5 172 -11610.0 Removed L/H 2 singe seat • . :96.0 225 -21600.0 Removed R/H 2 single seat -97.5 225 -21937.5 Removed R/H 3 singe seat -68.0 370 -25160.0 Removed R/H 4 single seat -68.5 424 -29044.0 Removed L/H 1 singe seat -68.0 172 -11696.0 Removed L/H 4 double seat - -1175 326 -38305.0 Removed L/H 3 double seat .. -119.0 272 -32368.0 Removed divan cushions -56.0 395 -22120.0 Removed galley linoleum -9.0 458 -4122.0 Removed VCR PV-4662 -8.0 145 -1160.0 Removed LCD Monitor SB1410AAB -7.9 ,151 -1192.9 Removed LCD Monitor SB1410AAB -7.9 443 -3499.7 Installed DVD PS8680Z +9.0 145 +1305.0 Installed LCD Monitor 170MP +12.0 151 +1812.0 Installed LCD Monitor 170MP +12.0 443 +5316.0 Installed R/H 1 singe seat +76.0 172 +13072.0 Installed R/H 2 singe salt +105.0 225 +23625.0 Installed R /1-i 3 singe seat +77.0 370 +28490.0 Installed R/H 4 singe seat +77.0 424 +32648.0 Installed L/H 1 singe seat +77.0 172 +13244.0 Installed L/H 2 singe seat +105.0 225 +23625.0 Installed L/H 3 double seat +143.0 272 +38896.0 Installed L/H 4 double seat +142.0 326 +46292.0 Installed divan cushions • +67.0 395 +26465.0 Installed galley carpet +18.0 458 +8244.0 New Empty Weight ( May 23, 2000) 42129.9 460.16 19386557.775 43.591/4 MAC Hours: ital Landings: 2111 PREPARED BY: Richard P. Jose 245198915 7701 WOODLEY AVENUE.VAN NUYS,CAUFORNIA 91406 • RioNE 818.901.9828 • Fax 818.988.5251 SDNYGlvl02754058 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40980 EFTA01326573

SDNYGM02754059 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00240981 EFTA01326574

MATION.INIPR STANDARD AJAW011111INESS COMRCATEOCIN Nmu , I . 'VrTYLT6-se "rsOLlsoni Fs. Form BICP2 SONY_CA1_02754060 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA_00240982 EFTA01326575

SONYGM_027 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA_00240983 EFTA01326576

cr) C co UNITED STATES CF AMERICA • DEPARTMENT OF TRANSPORTATION-FEDERAL AVLAION ADAENISTRATICN STANDARD AIRWORTHINESS CERTIFICATE 1 NATIONALITY AND 2 MANUFACIVRERANDMCCEL 3 AIRCRAFT SERIAL 4 CATEGORY REGISTRATIONMARKS NUMBER N677RP GULFSTRP,AM/GIV 1085 TRANSPORT IS AUTHORITY AND BASIS FOR ISSUANCE Ms sirwaltilnesi IMIRCAle Is Issued pursonl 10 to Federal MINIm AD of 1958 and cerlites that as «Ns ebbs of Issumee. 0 ne Goan lo whr.A &wed Pas been Foxe*, aid Mond lo omform lo the type Oillfleolo therefor. b be b comKon fee eale oPersOn and nos teen ire« to real In. req‘f romans of IRO Oppieable areonshensM DM &Mtn! Mr.ontWesa Cae as -o 73 mote by Area Elo Me CenvenlIcn of Wanorcnef CM Aw/S:n. MØ fes rried Pne Exce~ NONE 0 TERMS AND CCCITIONS Wins son sweerOarenl. mspended ietefied. IX a werineikm dW Y etIrelse eSISEININ4 by IM AdmnblRlp. INS tinvorflass torOlc.IM Is elSecOm as Mop es Oro noi-anence. nnweolot49 ermlnlsnetCR Md Illtealkm> are perfenred In iNcaclanos wln Pals 31. 43. end 91 <I Na Fedensl ASIOn Pernik,g as ndomdelat end ha elnyeAl Is fe~:1 M Ine Wiled DATE OF t331/ANCE REPAESENTA As, p er DESIGNATION NUMBER May 23 2000 L. 1,4O1TER WP-FSDO-01 An ~irk" ~nil^ la ~so al mala ~kola Mr be weal~le by a Y. *a wade, §1M9 am &where« rei 0~ 3 A non VIATION REGULA ai bat THIS CER NS TIPICATE MUST DE DISPLAYED N THE AIRCRAFT N ACCORDANCE WITH APPLICABLE FEDERAL TIO FAA Eon 8100.2 (Rod) APSE:can:Me Fain Sy!~ • JolFarn Foials• 12/19913 e as. EFTA01326577

SDNYGM02754063 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240985 EFTA01326578

.e • 'I T: r •I7 • 0 • - • ' MAJOR REPAIR tp USOerotineni oftroaserrako Fedora Aviation (Airframe, Rowerplant Aro id \ L\ ALTERATION enE0 &Arian 10 ...) Form AOPirked OMII No 2120.0020 O For FAA Use Ny • Office Identification GI_ 13 Administnalen INSTRUCTIONS: Print or type all entries. See FAR 43.9. F 43 Appendix B.,:and AC 43.9- (or -70 subsequent revision thereof) for instructions and disposition o this form. This report is required by law (49 U.S.C. 1411). Failure report can result in a civil penalty not to exceed $1,000 for each vielationiSection 901 of Federal Aviation Act of 1958). Make &airstream Aerospace Cow: Model GM 1. Aircraft SaiaiNo. 1085 Nationality and Regetration Mark N864CE 2. Owner Name lessikoseroirmistatira rarcs tecia ... 1a) Coca Cola Enterprises Inc. Address iershounariniptatearerkkes) 2500 Windy Ridge Rosy SE Atlanta ,GA 30339-5677 3. For FAA Use On y 4. Unit Identification S Type Unit Make Model Serial No. Repair AJteration AIRFRAME described in item X As 1 above) powERriaa PROPELLER APPLIANCE TYPO Manufacturer G. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Gulfstream Aerospace Corporation W6365 Discovery Drive Appleton, WI 54915 U.S. Certikated Mechanic GIFE100Y Foreign Certificated Mechanic X Certified Repo': Station Manufacturer D. I certify that the repair and/or alteration made to the tin' (s) identified in item 4 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 this and correct to the best of my knowledge. Date DEC 1 0 1998 Signature e rd iii . 7. Approval for Return To Service Pursuant to the authority given persons specified below, the unit Identified In item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and IsPlAPPROVED CI REJECTED FAA FIL Standards Inspector Manufacturer Inspection Authorization Other (Spee) BY FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 1 0 i898 Certificate Of Designation No. GIFR1OOY Signatur odzed Indi du r FAA Form 337 ozak (CamputerGonended) SDNY_GIvl_02754064 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00240986 EFTA01326579

NOTICE • • • • • Weight and balance 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 mom space is required, attach additiOrtal sheets. Identify with aircraft nationally and registration mark and date work completed). Repaired L/H Flap "A" track recess I.A.W. Gulfstream Aerospace Corp. (FAA Approved) Structural Repair Manual Drawing 1169RDCS280 Rev. C dated 41-88, -901 Installation. Repaired R/H Flap "A" track recess per -904 installation same dwg. Note on -904 install, Sea. NAS1921M05-3 fasteners were substituted with tea. NAS1919M06-3 and lea. OSMLS100M04-03 per Gulfstream Service Engineering E-mail transmittal dated 12-6-98. Reworked L/H and Ft/H °A" flap tracks per -905 and -906 installation same dwg. END O Additional Sheets are attached. SDNY_GM_02754065 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240987 EFTA01326580

0 MAJOR REPAIF uswparrnw (Airframe, Powerpla curranomwm n - Federal Aviation Administration . id t iptValan • " I I Fare Approved OMB No.2120-0020 For FAA Use Only Office IdentificaterGL i 3 - . INSTRUCTIONS. Print or type all entries. See FAR 43.9, FAR-48-Appondi. O. oratA0 43r9al(a 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 $1.000 for each violationfSecgon 901 of Federal Aviation Act of 1958). Make. . Gulfstream Aerospace Corp. Model GIV 1. Aircraft Serial No. 1085 Natonaity and Regatation Mark N864CE 2. Owner Name (Ass/rowan fristfailonarrAfca.49) Coca Cola Enterprises Icc. Address (As goose or I fayStratiof makes) 2500 Windy Ridge Pkwy SE Atlanta ,GA 30339-5677 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME described in X (As Item 1 above) POwERMAiir PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement AL Agency's Name and Address B. Kind of Agency C. Certificate No. Gulfstuam Aerospace Corporation W6365 Discovery Drive Appleton. WI 54915 U.S. Certificated Mechanic GIFRIOOY Foreign Certificated Mechanic • X Certified Repair Station Manufacturer D. I certify that the repair and/or alteration made to the uni (s) Identified in item 4 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. Date DEC 1 0 I000 Signature of AutinrizJ, I raidual ca. ".4 .4-- 7. Approval for Return To eevlco Pursuant to the authority given persons specified beew, the unit identified In item 4 was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is EL APPROVED 0 REJECTED FAA FIL Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection • DEC 1 0 1998 Certificate or Designation No. GIFRIOOY 22of Authr I al AA Form 33 (12-aM (Compute. Generated) SDNY_GIvi_02754066 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240988 EFTA01326581

NOTICE Weight and balance 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. Doscription of Work Accomplished. • (If more space is required. attach additional sheets. Identify with aircraft nationality and registration mark and data work completed). Complied with Gulfstream Aerospace Corp. (FAA approved) Aircraft Service Change 400 dated 9-22-98 Structures - Aluminum Collar - Pressure Bulkhead FS 596 - Terminating Action. Aircraft weight and balance, Equipment list, and Electrical load is negligible or unchanged. END CI Additional Sheets are attached. SDNY_GM_02754067 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40989 EFTA01326582

- • • II" • ti - •" 0 MAJOR REPAIR AND ALTERATION I •-•• • US Depotrod (Airframe, Powerplant, Propfellebror A ppline) aratisartaron Administration 1 it , ; ULU 1 O Federal Aviation I. \‘: !it"; -:'. -tn- f 1 Form Approved OMB No. 2120-0020 For FAA Use Only ) Office IdentificatioG4._ i INSTRUCTIONS: Print or typo all entries. See FAR 43.9, FAR Appendix:ff. altI7(C-439-110mtuiSquent revision thereof) for instructions and disposition o this form. This report is required by law (49 U. 14..F_ailtrileJarnErtEnaesR in a civil penalty not to exceed $1,000 for each violation (Section 901 of Federal Aviation Act of 1958). 1. Aircraft Make Gulfstrearn Model G-IV Serial No. 1085 Nallerialit), and RegStraticn Mark N864CE 2. Owner Name (rtsslotrwaregisfrationtarriffsafe) Coca Cola Enterprises, Inc Address (Assbonnoaregisbaliontertikale) 2500 Windy Ridge Pkwy SE Atlanta, GA 30339.5677 3. For FAA Use On y 'The data/alteration identified herein cowries with the applicable airworthiness requirements and Is approved for the above described aircraft subject to calamity inspection by a person authorized In FAR 43, Section 43.7'. Date iz/9/9( FAA Inspector GL13 4. Unit anti cation 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME As described in Item X 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. Culla:tam Aerospace Corporation W6365 Discovery Drive Appleton, WI 54915 U.S. Certificated Mechanic GIFR100Y Foreign Certificated Mechanic X Certified Repair Station Manufacturer D. I certify that the repair and/or alteration made to the uni Cs) identified in item 4 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. Date /2/9/98 Signature of Authorized In • ual • t 7. Appro r Return To Service Pursuant to the authority given persons specified below, unit identified in Item 4 was inspected In the manner prescribed by the Administrator of the Federal Aviation Administration and is (APPROVED CI REJECTED FAA FR Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee x Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection /2 -4)-9se -• • - --- - - --- -- Certificate or Designation Designation No. Signature of AVUodiedl ual r Genera SDNY_Gtvl_02754068 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240990 EFTA01326583

NOTICE Weight and balance 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. DescdptIon of Work Accomplished Qf more space is required. attach additional sheets. Identity with aircraft nationally and registration mark and date work Completed). Replaced one AD rivet in clip angle bracket on the under side of right cockpit floor.structure, F.S. STA 56.812, forward of floor access panel FLR-4 installing a Hi-Lok P/N: HL18 fastener. Also installed an additional Hi-Lok P/N: HL18 fastener in adjacent hole of same clip, found missing since production. END O Additional Sheets are attached. SDNY_GM_02754069 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 0024099I EFTA01326584

- e 7.••• c r1 Ora .0 MAJOR REPAIR AND AL USecoretmere ontensooncoon (Airframe, Powerplant, Propelle Asepearericasen Admmemmon --• 7 . -7. . 2..0 1 441998 I; l _ JO. :Form Approved OMB No. 2120-0020 For FAA Use Only Office Identificatioph., 13 INSTRUCTIONS:Printer type all entries. See FAR 43.9, FAR43 A subsequent revision thereof) for Instructions and disposition of this form. This report is required by law (49 U.S.C. 1421). Failure to repo can result in a civil penalty not to exceed stood tor each such violation (Section 901 Federal Aviation Act of 1958). 1. Aircraft Make GULFSTREAM AEROSPACE Model G-IV • Serial No. 1085 Nationality and Registration Mark N864CE • • 2. Owner Name (As shown on registration certificate) COCA COLA ENTERPRISES, INC. Address (As sltown on registration certilkate) 2500 WINDY RIDGE PKWY SE ATLANTA, GA 30339-5671 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME • • (As described in Item I above) X . • ^. . . . POWERPLANT • PROPELLER APPLIANCE Type . Manufacturer . S. Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certi kale No. GULFSTREAM AEROSPACE CORP. W6365 DISCOVERY DR. APPI.PTCK WT T•421% U.S. Certificated Mechanic G1FR100Y Foreign certificated Mechanic It Certificated Rees& Station _ issausuturar D. I certify that the repair and/or alteration made to the un t(s) identified In Item 4 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 nowledge. Data • DEC 1 0 1998 . Signatur f Authottect' • 7. Approval for Return To Seneca Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is MAPPROVED 0 REJECTED BY FAA Fit. Standards Inspector Mariblacturer Inspection Authorization Other (Specify) FM Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of AppitNal or Refection DEC I 0 1998 ' Certificate or Designation No. G1FR100Y Signal Authoriz Inds • ual A Form 337 ilVeal SDNY_Givl_02754070 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240992 EFTA01326585

NOTICE Weight and balance oroperating 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. Descdption of Work Accomplished (II more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed.) Modified the existing Third Comm & Nat Systems by removing the Gables G6860-09 Conun/Nav Control Head, and installing a Collins CTL-23 Digital Control Head, P/N 622-9851-001. The third Comm / NAV system's interface was retained as previously installed with the exception of the controller. GAC modifications to the aircraft wiring for the new control head interface is depicted on the GAC revision to Western Commander Inc. wiring diagrams: No. 3 VHF COMM, 08069110; and No. 3 VHF NAV, 08069128, of which the electrical/electronic aspects of the GAC listed revision is DER approved by N. Kopesky, CHI-262. Existing wiring diagrams affected by the above referenced systems are revised to reflect changes iri system design or interface to the newly installed or modified systems as appropriate. All new single conductor wire meets MIL 22759/16 and all new multi-conductor shielded wire meets MIL 27500. All work done IAW AC43.13-2A, Chapters 1, 2 & 3 and manufacturers installation data. Aircraft equipment list and weight & balance manual revised. END K Additional Sheets Are Attached OILS. GOVERNMEET PRINTING OFFICE: t902-760-012/E0I57 SDNY_GM_02754071 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240993 EFTA01326586

0 MAJOR REPAIR ANII! us oecerirreni co tensonoton Acurmumnian (Airframe, Powerplant, PripterWergdgg) Federal manse 6 .• — — Ail I I Form Approved OMB NO. 2120-0020 I f For FAA Use Only li i. j Office Identificatior 1 3 (.71, k , i INSTRUCTIONS:Print or type all entries. See FAR 43.9. FAILSAppandiatranclACAS.W.US.16bsequent revision thereof) for instructions and disposition of this form. This report is required by law ( 9 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 of 1958). 1. Akcraft Make GULFSTREAM AEROSPACE Model G-IV Serial No. 1085 Nationality and Registration Mark N864CE - . . 2. Owner Name (As shown on registration certificate) COCA COLA ENTERPRISES, INC. Address (As shown on registration certificate) 2500 WINDY RIDGE PKWY SE ATLANTA, GA 30339-5677 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME . ' (As described In Item 7 above) X . .. . POWERPLANT PROPELLER APPLIANCE Type Manufacturer 8 Conformity Statement A. AgencYs Name and Address B. Kind of Agency C. Ceni kate No. US. Certificated mechanic G1FR100Y GULFSTREAM AEROSPACE CORP. Foreign certificated mechanic W6365 DISCOVERY DR It Certificated ROPOtStalion APPT MICK MGR 5491c Manufacturer D. Icertifythat the repair and/oralteration made to the un have been made in accordance with tht requirements furnished herein is true and correct to the best of my Rat Identified in item 4 above and described on the reverse or attachments hereto of Part 43 of the U.S. Federal Aviation Regulations and that the information nowledge. Date DEC 1 0 1998 Signatu Authord I . WI • 7. Approval for Return To nice Pu suant to the authority given persons specified below, the unit identified In Item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is CkAPPROVED O REJECTED FAA Fit. Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 1 0 1908 • CertlficaM or Designation No. GIMUDOY Signatu Author Nast . - , orm 337 mast SDNYGM_02754072 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240994 EFTA01326587

• r . NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate effete( t record. An alteration must be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. B. Description of Work Accomplished - • . (It more space is required, attach additional sheets. Identify withaircralt nationality and registration mark and date work completed.) Installed an Allied Signal Avionics Enhanced Ground Proximity Warning System (EGPWS), computer P/N 965-0976-003-104-104, as per Guffaws= Aerospace Corporation (GAC) STC ST01445AT. In order to facilitate this installation, the existing MK-V Ground Proximity Warning System (GPWS), computer P/N 965-0676-0010 (installed per Sits SA218850, FAA Form 337 dated 9/7/89 & ST00714AT, FAA Form 337 dated 1/26/96) was roved from the aircraft Additionally, the three (3) each Honeywell SG-884 Symbol Generators, P/N 7008570-904 have been modified to -905 and the two (2) each Honeywell DC-884 Display Controllers, P/N 7007540-942 have been modified to -946 to allow for EGPWS selection and display of the enhancement features. Deviations to STC ST01445AT include: • Utilized existing wiring where practicaL • Retained the previously installed GPWS circuit breakers and some of the annunciation by incorporating them into the new EGPWS system. System interface and wiring as depicted on GAC wiring diagram GIV-31085-34-10 is electrically equivalent to the aforementioned STC. • Mounting the computer in the R/H radio rack extension at the same location as the removed GPWS computer. Expanded the STCd EGPWS Relay Unit design to house system components. Installed this newly fabricated Avionics Interface Unit in the R/H radio rack extension, adjacent to the EGPWS computer, picking up existing structure. FAA Approved Airplane Flight Manual Supplement, SC41 349M37 dated 8/8/97, with Rev. 02 dated 4/8/98 is required for this approval and supersedes all previously issued AFMS' pertaining to GPWS. Maintenance Requirements - Instruction for Continued Airworthiness, GAC Document No. 5C41 349A01, Rev. 1, dated 6/22/97 with attached AlliedSignal.Line Maintenance Manual, Doc. No. 060- 4199-014 is required for this approval. Eating wiring diagrams affected by the above referenced systems are revised to reflect changes in system design or interface to the newly installed or modified systems as appropriate. All new single conductor wire meets MIL 22759/16 and all new multi-conductor shielded wire meets MIL 27500. All work done IAW AC43.13-2A, Chapters 1, 2 & 3 and manufacturers installation data. Aircraft equipment list and weight & balance manual revised. END O Additional Sheets Are Attached *U.S. GOVERNMENT PRINTING °EPICS: 1912-769-012/60IS7 SONY _GM_02754073 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240995 EFTA01326588

" 0 MAJOR REPAIR AN I I ) ' fRILT I I 1 TIO 1 1998 i I Form Approved OMB No. 2120-0020 uscepamert (Airframe, Powerplant, Pr dTrarasatatian wiener, or ApAliance) j For FAA Use Only Uldi Office klentficationGL Federal Aviation Administration /3 INSTRUCTIONS: Print or type all entries. See FAR 43.9, FAR 4247ZEftendirtralttlertraffitrzybesquent revision thereof) for instructions and disposition of this form. This report M required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed $1,000 for each violation (Section 901 of Federal Aviation Act of 1958). Make. Gulfstrezun Aerospace Corp. Model GIV 1. Aircraft Serial Na Iffil5 Nationality and Registraticn Mark P1864CE 2. Owner Name aflame oitapistrattisaceritecak) Coca Cola Enterprises Inc. . Address (As shaman faySiMaancefffitak) 2500 Windy Ridge Pkwy SE Atlanta GA 30339-5677 3. For FAA Use On y 4. Unit Identification 6. Type Unit Make Model Serial No. Repair Alteration AIRFRAME X (As descabcd in Item 1 above) POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6. Conformity Statement A. Agency's Name and Address B. IGnd Of Agency C. Certificate No. Oulfstream Aerospace CorpenitiOn ' W6365 Discovery Drive Appleton. WI 54915 U.S. Certificated Mechanic GI FRI 00Y Foreign Certificated Mechanic X Certified Repair Station Manufacturer D. I certify that the repair and/or alteration made to the unit(s) identified In item 4 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 hue and correct to the best of my knowledge. Date DEC 1 0 1998 . SIgnatu refuel 7. Approval for Return To Service Pursuant to the authority given persons specified below, the unit Identified In item 4 was inspected in the manner prescribed by the AdmInisUator of the Federal Aviation Administration and isySAPPROVED CI REJECTED FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FM Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC. 1 0 1998 Certificate or Designation No. GIFRIODY Signal Autho o rni f t nn 337 (1248) (Compote: Generated) SDNY_Gtvl_02754074 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240996 EFTA01326589

NOTICE Weight and balance limitation changes shall be entered tri 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). Removed Bendix Instrument Landing system (ILS), consisting of 2ea. ILS Receivers, 2ea. racks, and lea. ILS controller. The ILS system was originally installed at the factory. The ILS system was previously disabled I.A.W. AD 89.02-12 R1 dated March 21, 1994. #1 and #2 ILS circuit breakers were previously removed. Connectors are capped, bagged, and stowed. Removed the following equipment: 2ea. Bendix ILS Receivers P/N 2104-1230-3504 lea. Bendix ILS Controller P/N 1159SCAV404-3 lea. ILS Rack P/N 1159AV40369-1 lea. ILS Rack P/N 1159AV40369-2 The weight and balance manual and equipment list were revised. END K Additional Sheets are attached. SDNY_GIvl_02754075 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240997 EFTA01326590

.0 MAJOR REPAIR US Cocain/al orlandomaron Administration (Airframe, Powerplant, P Federal Aneden re:-Q7: r : •._,,, ts _., • ITERATION regal; Ay/ El I &zee Form Approved OMB NO. 21204020 For FAA Use Only Office IdentificationGt 13 INSTRUCTIONS:Print or type all entries. See FAR 43.9, F and disposition of this form. This report Is required by lave44946S.G..1421)...Eatakirggenad for each such violation (Section 901 Federal Aviation Act kR43Appendix 8. an = 01 1958). or ulnas:went revision thereof) for instructions result in a civil penalty not to exceed $1,000 1. Aircraft Make GULFSTREAIA AEROSPACE ' Model G-IV Serial No. 1085 Nationality and Registration Mark N864CE • z Owner Name (As shown on registration certificate) COCA COLA ENTERPRISES, INC. Address (As shown on registration certificate) 2500 WINDY RIDGE PKWY SE ATLANTA, GA 30339-5677 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in item 1 above) X • ' ',.. - . P0WERPLANT PROPELLER APPLIANCE Tyne • Manufacturer . 8. Conformity Statement A. Agency's Name and Address B. Kind of Agency C: Certificate No. GULFSTREAM AEROSPACE. CORP. W6365 DISCOVEItY DR. ADM PION, WI Sal 5, (U.S. Certificated mechanic • GIFRIOOY ' Foreign Certificated Mechanic Certificated Repak Station Manufacturer D. I certifythat the repairand/or alteration made to the un t(s)identified in item 4 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 nowledge. Date DEC 1 0 1998 Signature of Authorized Indiv u • 7. Approval for Return To Send Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and Is [(APPROVED . CI REJECTED BY FAA Fit. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station A oved by esTransport Person ppr Canada Ainvonhin s GrouP Dale of Approval or Rejection DEC 10 1998' Certificate or Designation No. GIFRIDOY Signatu uthorized dd - lt • FAA Form 337 ordist. SDNY_GI.1_02754076 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_00240998 EFTA01326591

NOTICE Weight and balance or operating limitation changes shall be enterid 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.) Installed dual digital Collins RTU-4210 Radio Control Units in the center pedestal in accordance with Atlantic Aviation/Delta Engineering STC ST00717NY-D, dated May 19, 1998, replacing the GAC installed Gables Comm/Nav/ATC/ADF / TCAS Control Heads. Newly installed equipment includes: 2 Ea. Collins RTU-4210 Radio Tune Units, P/N 822-0836-005 Removed equipment includes: 2 Ea. Gables 700-D36407A-002 Comm Controls 2 Ea. Gables 700-D36409A-002 Nav Controls 2 Ea. Gables 700-D36411A-002 AIDE Controls 1 Ea. Gables 700-D36413-008 ATC 1 Control 1 Ea. Gables 700-D36413-003 ATC 2 Control 1 Ea. Gables 700-D36415A-003 Marker Control 1 Ea. Gables G6969-04 TCAS Control Refer to GAC drawings: VHF Comm Mods, GIV-31085-23-20; VHF NAV/DME Moth, GIV-31085-34- 26; ADE System Mods, GIV-31085-34-32; ATC System Moth, GIV-31085-34-35; Control Heads, GIV- 31085-34-37; and FMS Mods, GIV-31085-34-58, which is electrically equivalent to the aforementioned STC. FAA Approved Airplane Flight Manual Supplement, 62743606-340 dated 5/19/98, with Rev. — is required for this approval and supersedes the existing AEM and attached supplements only in the areas contained therein. Maintenance Manual Supplement, Delta Engineering Document No. 727-03609-340 dated 5/19/98, with Rev. — is required for this approval. Existing wiring diagrams affected by the above referenced systems are revised to reflect changes in system design or interface to the newly installed or modified systems as appropriate. All new single conductor wire meets MIL 22759/16 and all new multi-conductor shielded wire meets MIL 27500. All work done IAW AC43.13-2A, Chapters 1, 2 & 3 and manufacturers installation data. Aircraft equipment list and weight & balance manual revised. END 0 Additional Sheets Are Attached dV.S. GOVERNMENT PRINTING OFFICE: 1,12-755-017/60I57 SONY GM 02754077 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002 40999 EFTA01326592

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION STATEMENT OF COMPLIANCE WITH THE FEDERAL AVIATION REGULATION DATE February 9.1996 AIRCRAFT OR AIRCRAFT COMPONENT IDENTIFICATION MAKE Gulfstream MODEL NO. G-IV TYPE (Airpkne,Radiodielicopter etc) Airplane NAME OF APPLICANT The Jet Center LIST OF DATA IDENTIFICATION TITLE Drawing Number Rev. Date 0 Shts Drawing Tide 3 FMS 1 & No. 2 Global Position and approved as it pertains to only. 08069100 08069324 A 01/20/96 5 No. A 01/20/96 1 No. 'END' Note: The above data is reviewed electrical systems and equipment PURPOSE OF DATA To show compliance with applicable Federal Airworthiness Regulations for minor deviations to S.T.C. SA3774NM for Gultstrearn G-TV, S/N 1085, N88GA ONLY via FAA. Form 337. APPLICABLE REQUIREMENTS Vitt specific sections) FAR's: 25.1301(nkod); 25.1309(a,b,c); 25.1322(be,d); 25.1355(c); 25.1357(a,c,d). CERTIFICATION - Under authority vested by direction of appointment under Part 183 of the Federal Aviation none have been examined in accordance of the Administrator and in accordance with conditions Regulations, data listed above and on attached sheets with established procedures and found to data and limitations numbered comply with applicable requirements of the Federal Aviation Regulations. I ewe) Therefore A Recommend approval of these Approve these data SIGNATURES) OF DESIGNATED ENGINEERING REPRESENTATIVE(S) DESIGNATION NUMBER(S) CLASSIFICATION(S) .gLits,ci re rt nA--- NM-2128 Systems & Equipment Sarlds A ICara,guzian . orm EI 10-3(11.70) SUPERSEDES PREVIOUS EDITION GPO 901-613 SDNYGlvl_02754078 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241000 EFTA01326593

SDNYGM02754079 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA _00241001 EFTA01326594

. A. A ch-cf4:-c-s C 1 U.S. Department MAJOR REPAIR AND ALTERATION of Transportation (Airframe Powerplant, Propeller, or Appliance) 'Federal Aviation Administradon Form Approval OMB No. 2120-0020 For FAA Use Only Office Identification STITS11O.11 .,114STRUCTI0NS. Print or type all antics. See F AR 43.9 FAR 43 Appendix B. and AC43.9-1 (cesubscquent revue= thereof) for =ass and cIsposilkm dais tbrin. Ibis report is required by law (49 U.S.U. 1421). Faun to report can remit illation penalty not to exceed $1,000 for cub nub violation (Section 901 Federal Aviation Actor 1938). 1. Aircraft Make Gulfstream Model (MV Serial No. 1085 Nationality and Registration Marks U.S.A. N864CE 2. Owner Name at shown on registration Certificate) Coca-C-ola Enterprises Inc. Address (As shown on registration certificate) 3931 Ann Dr NW Atlanta, GA 30336-1512 3. For FAA Use Only • 4. 17alt Identification 5. type Unit Make I Model I Serial no. Repairs Alterations Airframe - — X (As described in irem I above) P ea— Powerplant Propeller Appliance Type ManUfaCtUrtr 6. Conformity A. Agency's Name and Address B. Kind of Agency C. Certificate No. Gulfstream Aerospace Corporation P.O. Box 2206 - Travis Field Savannah. GA 31402-2206 U.S. Certificated Mechanic FAA CRS GR4R216M Foreign Certificated Mechanic X Certificated Repair Station Manufacturer D. I cab& that tbe repair andlor alteration made to the =Ns) idadified m item 4 above and !wailed ca the muse or anathacrits bare have been made in accordance with the requirements of Part 43 efthe US. Federal Regulations and that the information garnished benzin is true and ant the bet army knowledge- Date 09/05/97 Signature of Authorized Indivi ual Steven Sweeney 7. Approval for Return To Service Punuant to the authority giveo persons specified below, the unit identified in ban 4 was inspected in the manner prescribed by the Atli:enteral& Federal Aviation Administration and is El APPROVED O REJECTED BY FAA FIt. Standards Inspector- Manufacturer Inspection Authorization Other (Specify) FAA Designee X Repair Station Person Approved by Transport Canada Ai worthiness Group Date o Approval dr Rejection - - 09/05197 Certificate or - - Dedgoation No. FAA CRS GR4R216M Signature of Assiberized individual Jimmie K. Smith . ' A,.. g ntei, . SDNYGlvl_02754080 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241002 EFTA01326595

• NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate tuft retort An alteration must be compatible with al t previous alteration to assure continued conformity with the applicable airworthiness requirements 8. Description of Work Accomplished: (temote space is requited snub soiTstional sheets kleo* vale ainraft Whoa* end registration mark iodate bark completab. Aircraft Model: G-IV Aircraft Time Since New: 2853.9 Aircraft Serial No.: 1085 Aircraft Landings Since New: 1227 Aircraft Registration No.: N864CE Reference: Gulfstream Aerospace Corporation Workorder No.: C04-1085-097-0042 1. Incorporated the following FAA approved major Gulfstream Aircraft Service Changes: ASC No.: Subiect: 135 A2 ECS Pack Sequencing During Engine Start End O Additional Sheets Are Attached SDNY_GM_02754081 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241003 EFTA01326596

-- 8TAWDARISAIRWOMINES8 CITTFICATI II866CZ 0:11.18118Sall/GIV 10115 MUM= • J•I•antr".•••• WWI. ::•••.:::========" " "" Ion • 71:3. 12-16-88 Vitt FM Fo, Me" man SDNY_GM_02754682 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA 00241004 EFTA01326597

SONY_GM02/59083 T TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, EFTA 00241005 EFTA01326598

. _ • !r,7-• •-• • \\ (Cly t ; • II f - 6 L.,:,7 MA. mmn (Airframei if • • R REPAIR AND ALTERATION Powerplant, Propeller, or Appliance) Form Approved OMB No. 2120-0020 For FAA Use Only Office Identification AI /3 - ClitragtFriRroitype an en and disposition of this form. This report for each such violation (Section 901 des. See FAR 43.9, FAR 43Appendix B. and AC 43S-1 (or subsequent revision thereof) for instructions is required by law (49 U.S.C. 1421). Failure to report can result in a civil penalty not to exceed 91,000 Federal Aviation Act of 1958). 1. Aircraft Make Gulfstream Aerospace Model— -1.,-IV Serial No. 7085 Nationality and Registration Mark N 2. Owner Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 3. For FAA Use Only 4. Unit Identification S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item I above) X POWERPLANT PROPELLER APPUANCE Type Manufacturer 8 Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. U.S. Certificated mechanic QK2R112L K-C Aviation, Inc. Foreign Certificated Mechanic 301 Discovery Drive X c•niscanics sops swan Appleton, WI 54915 Manufacturer D. I certify that the repair and/or alteration made to the un have been made In accordance with the requirements furnished herein is true and correct to the best of my know t(s) identified in Item 4 above and describedon the reverse or attachments hereto of P n 43 of the U.S. Federal Aviation Regulations and that the Information edge. Date DEC 20 1996 Signature of Authorized Ina( ual 7. Appro I or Return To Service Pursuant to the authority given persons specified below, the unit identified in item 4 was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Ft.APPROVSO - 0 REJECTED FAA Rt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee x Repair Station Person Approved by Transport Canada Airworthiness Group Date& Approval or Rejection DEC 20 1996 Certificate or Designation No. ClK2R112L Signature of Authorized Ind' 'dual (cdseine. • FAA Form 337 /2.s SDNYGIvl_02754084 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241006 EFTA01326599

NOTICE Weight and balance or operating limitation changesshall be entered in the appiopriate aircraft record. An alteration niust be compatible with all previous alterations to assure continued conformity with the applicable airworthiness requirements. 8. Description of Work Accomplished (II more space is required, attach additional sheets. Identify with aircraft nationality and registration mark and date work completed:) . Fabricated and installed life raft storage provisions for two rafts under divan, F.S. 379 and F.S. 415 in accordance with K-C Aviation, Inc., Structural Drawing GIV-25-01-222, sheet 1. DER approval is in accordance with 8110-3 form dated 12/20/96 by A. Duncan, CHI-424. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC-43.13-1A chapter 6 as a guide. Materials used meet the requirements of FAR 25.853. END O Additional Sheets Are Attached OILS. 00VICRNMENT PRINTING OPPIGC: I192-749-0I2/101117 SDNY_GM_02754085 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241007 EFTA01326600

Form Approved OMB No. 2120-0020 MAJOR - 6 tlAn1d rams) Aviation tmrlinn IL" ' REPAIR AND ALTERATION Powerplant, Propeller, or Appliance) For FAA Use Only Office Identification Ch/3 atiglIaLICTIOAMPrig4014490411-sa and disposition of this form. This report for each such violation (Section 901 ries. See FAR 43.9, FAR 43Appendix EL and AC 43.9-1 (or subsequent revision thereof) for instructions is required by law (49 U.S.C. 1421). Failure to report can result In a civilpenalty not to exceed S1.000 Federal Aviation Act of 1958). 1. Aircraft make Gulfstream Aerospace ModelG-IV Serial No. 1085 Nationality and Registration Mark N88GA t Owner Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 3. For FAA UVVEINIXIA/ALI trUAI ILMIrrilzIJAIti ILltN I II-ICU ItHtinil GUM Itb WI I H I It mar 4GAbLt REQUIREMENTS AND IS APPROVED DESCRIBEDAIRCRAFT, SUBJECT TO INSPECTION BYA PERSON AUTHORIZED SECTIO 43. HIFIVVUti I FOR THE CONFORMITY I I-IINtbb ASOVE AR 3IGNA—U 4. Unit 'dentin; . Unit Make Model IAA MICE FSDO Serial No. Repair Alteration AIRFRAME (As described in Item 7 above) X POWERPtAfff PROPELLER APPLIANCE Type Manufacturer 6 Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. U.S. Cenificated Mechanic QK2R112L K-C Aviation, Inc. Foreign Certificated mechanic 301 Discovery Drive x Certificated Repair Station Appleton, WI 54915 manufacturer D. I certify that the repair and/or alteration made to the un have been made in accordance with the requirements furnished herein Is true and correct to the best of my knowledge. t(s) identified in item 4 above and described on the reverse orattachments hereto of Part 43 of the U.S. Federal Aviation Regulations and that the information Date DEC 0 9 1996 Signature of Authorized Individual -kO . 7. App a tor Return To Service Pursuant to the authority given persons specified below, the unit Identified In item 4 was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is Q, APPROVED O REJECTED FAA FIL Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee ., A Repair Station Person Approved by Transport Canada AIMOilhintSS Group Date of Approval or Rejection DEC 181996 DEC i 8 1996 Certificate or ignation No. Designation No. 0K2R112L Signature of Authorized Individual Coma ‘....a FAA Form 337 02401 SDNYGIvl_02754086 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241008 EFTA01326601

NOTICE Weight and balance or operating limitation changes shall be entered in the appropriate aircraft record. An alteration must be corn/sat/We with all previous alterations to assure continued conformity with the applicable airworthinesi requirements. 8. Description of Work Accomplished (If more space is requited. attach additional sheets. Identify with aircraft nationality and registration mark and dale work completed.)- ... Removed all 10 existing Aircraft Modular Products cabin chairs P/N: 1250-1399-001; P/N: 1250- 1399-002, forward (2 ea.), center group (4 ea.), aft group (4 ea.), retractable tables (6 ea.) and (2 ea.) left and right forward cabin cabinets at F.S. 176. Installed six new single ISO C39a Aircraft Modular Products chairs, two double TSO C39a Aircraft Modular Products chairs and a Tosington side facing three place TSO C39a, Type I divan reconfigured to 13 place passenger cabin in accordance with K-C Aviation, Inc., floor plan drawing GIV-25-05-200, sheet 1 dated 10/29/96. Seats and divan are installed in the conventional manner using new seat track over existing aircraft seat track in accordance with K-C Aviation STC SA1266GL approved drawing GIV-25- 50-205, sheet 1, revision B in the positions listed below: #1 IJH P/N: 2524.014(-866C) Aft Facing F.S. 173 #1 R/H P/N: 2524.014(-866D) Aft Facing F.S. 173 #2 L/H P/N: 2524.014.01(-874B) Forward Facing F.S. 225 #2 R/H P/N: 2524.014.01 (-874A) Forward Facing F.S. 225 #3/4 L/H P/N: 2524.015(-167C) Aft Facing F.S. 272 #5/6 L/H P/N: 2524.015(-1678) Forward Facing F.S. 326 #7 R/H P/N: 2524.014(-866A) Aft Facing F.S. 370 #8 R/H P/N: 2524.0141-866A) Forward Facing F.S. 424 Divan P/N: T480-40 Side Facing F.S. 397 All seats installed with new ISO C-22F color coordinated seat belts by C & M Marine. Details of additional interior components depicted and installed in accordance with floor plan drawing are approved on separate FAA form 337's. The floor plan drawing will be referenced for location purposes. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. Fasteners torqued using AC.43.13-1A chapter 5 as a guide. END K Additional Sheets Are Attached 0 U.S. GOVERNMENT SMINTINO OF NCI: 1M-769-012/60157 SDNY_GM_02754087 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241009 EFTA01326602

in Vat IS g Lt.,. I,.. MA 4 - 6 Iiigrframe Ansa await f • i • OR REPAIR AND ALTERATION Powerplant, Propeller, or Appliance) Form Approved OMB No. 21200020 For FAA Use Only Office Identificatiory is, alif...1 NSTRUCTIO NS: Print or type all e ermicitspositiorrof this . for each such violation (Section 901 ries. See FAR 43.9. FAR 43 Appendix B. and AC 43.9-1 (or subsequent revision thereof) for instructions is required by law (49 U.S.C. 1421). Failuret0 Alpert can result Ina civii penaity not to excee351800 Federal Aviation Act of 1958). I. Aircraft Make Gulfstream Aerospace u ModeL• -IV Serial No. 1085 Nationality and Registration Mark N88GA z Owner Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 3. For FAA Use Only 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described In Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6 Conformity Statement A. Agency's Name and Address 8. Kind of Agency C. Certificate No. U.S. Certificated Mechanic OK2R112L K-C Aviation, Inc. Foreign Cann-mated Mechanic 301 Discovery Drive y Certificate:1 Racal/ Station Appleton, WI 54915 ' Manufacturer O. I certify that the repair and/or alteration made to the un have been made in accordance with the requirements furnished herein Is true and correct to the best of my t(s) identified in item 4 above and described on the reverse or attaChmentS hereto of Part 43 of the U.S. Federal Aviation Regulations and that the information knowledge. Date DEC 18 1996 Signature of Authorized lndiv ual 7. Approv or Return To Service Pursuant to the authority given persons specified below. t unit identified in item 4 was Inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and is (APPROVED O REJECTED FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee x Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 1 8 1996 Certificate Or Oesignation No. OK2R112L Signature of Authoriz Indi dual CI A,-4-, c • FAA Form 337 02441 SDNYGIvl_02754088 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241010 EFTA01326603

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. S. Description of Wotk Accomplished of more Space is required, attach additional sheets. Identity with aircraft nationality and registration mark and date work completed.) Fabricated and installed the following new interior components in accordance with K-C Avlation, Inc., Floor Plan Drawing GIV-25.05-200, sheet 1 and the below listed Structural Drawings: GIV-25-02-203 Sheet 1 Rev. - Subwoofer Installation GIV-25-01-209 Sheet Rev. - Game Table Leaf Assembly GIV-25-02-209 Sheet 1 Rev. - Enflight Table Installation GIV-25-09-210 Sheet 1-3 Rev. - Galley Aft Right Modification GIV-25-10-210 Sheet 1-2 Rev. - Galley Aft Left Modification GIV-25-07-223 Sheet 1 Rev. - Aft Divan Cabinet Installation GIV-25-08-223 Sheet 1 Rev. - Forward Divan Cabinet Installation GIV-25-06-226 Sheet 1-5 Rev. - Credenza Details and Installation GIV-25-53-286 Sheet 1-2 Rev. - Conference Table Dual Pedestal Installation Subwoofers installation consists of four units installed below cabin window ledges at the following locations: two each forward left and right cabin F.S. 163; one each right aft cabin F.S. 350 and one each right aft cabin 436. Fabricated and installed three stowable game tables in the following locations: two each left and right forward cabin F.S. 198; one each right aft cabin F.S. 397. Fabricated and installed new manual height adjustable conference table in center left cabin F.S. 299. Fabricated and installed new credenza cabinet in right center cabin extending from F.S. 255 to F.S. 345. Credenza contains six drawers in center for miscellaneous storage and hinged compartments on each end for pillow and blanket storage. Fabricated and installed new divan forward and aft divan armrest cabinets located at F.S. 355 and F.S. 434. Cabinets contain drawers for miscellaneous storage. Modified left galley to include removal of decanter cabinet, replacing Sharp microwave oven P/N: R-1 M53 with new larger Tappen unit P/N: TMS083U1W and replaced 13" Hitachi TV monitor P/N: CT1386B with new 14" Baker LCD monitor P/N: TW1400. Modified right galley removing hot cup dispenser, replacing circuit breaker panel, adding the following equipment: new Krups coffee maker, hot and cold water spigot and sink, Nordskog Hi- Temp oven P/N: 50231 and new trash receptacle. New trash receptacle is in compliance with the flammability requirements of 14CFR25 (part 25), paragraph 25.853(h), amendment 25-83. DER approval is in accordance with 8110-3 form dated 12/18/96 by A Duncan, CHI-424. Electrical aspects covered separately. Cabin interior compartment placards description detailed in K-C Aviation drawing GIV-25-01-218 and layout per drawing GIV-25-04-218. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC 43.13-1A chapter 6 as a guide. Weight and balance accomplished using AC43.13-1A chapter 13 and the aircraft manufacturer's weight and balance manual as a guide. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. END 0 Additional Sheets Are Attached *U.S. GOVERNMENT PRINTING OFFICE: 1192-769-012/60157 SDNY_GM_02754089 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002410I I EFTA01326604

0 . I ; Vi L3 MAJOR US Doormen Mitenspermson - 6 Lymnr . Fare' krtallen An REPAIR AND ALTERATION Powerplant, Propeller, or Appliance) Form Approved ome No. 2120-0020 For FAA Use Onty Office Identificatiwi NJ3 itlUCTIONS: -for Catl tU Print or type alt entries. ispositicusoLthWoraatiisseairt each such violation (Section 901 See FAR 43.9. FAR 43 Appendix B. and AC 43.9.1 (or subsequent revision thereof) for instructions Is required by law (49 U.S.C. 1421). Failure to report can result In a civil penalty not to exceed $1.000 federal Aviation Act of 1958). Make Gulfstream Aerospace Model G-IV 1. Aircraft Serial No. 1085 Nationality and Registration Mark N88GA Z Owner Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 ,I.t_j,:,,,,rminajtmiu l 3 4;enotreers, .. For FAmp .. . tf. ,v4H44.h.7ipptitheipteleaFivvom rt REQUIREMENTS DESCRIBED INSPECTION SECTION ne-re zl AND IS APPROVED AIRCRAFT, SUBJECTTO BYA PERSON AUTHORIZED 7 1 In FOR THE CONFORMITY IN miciEsr -.,:r ABOVE 43 4. Unit Identification FAA NIKE I-SDO Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6 Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. . US. Certificated Mechanic CIK2R112L K-C Aviation, Inc. Foreign Certificated mechanic 301 Discovery Drive x Certificated Repair Station Appleton, WI 54915 Manufacturer D. I certify that the repair andtor alteration made to the un have been made in accordance with the requirements furnished herein is true and correct to the best of my knowledge. t(s) identified in item 4 above and described on the reverse or altachrnemts hereto of Part 43 of the U.S. Federal Aviation Regulations and that the information Oate DEC 0 9 1996 Signature of Authorized Individual c 7. App for Return To Service Pursuant to the authority given persons specified below, the unit identified in item 4 was inspected In the manner prescribed by the Administrator of the Federal Aviation Administration and is Ck.PPROVED CI REJECTED FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other Meal BY FAA Designee KRepair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 1 8 1996 Certificate or No. Des CIK ignation2R112L Signature of Authorized Individual Qs...-. cd-jd- FAA Form 337 11206) SDNYGIvl02754090 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241012 EFTA01326605

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 park and date work completed.) Modified existing forward right vestibule crew cabinet, F.S. 163 in accordance with K-C Aviation, Inc., Structural Drawing GIV-25.05-216, sheet 1 and PS100-26.04-600. Cabinet rework consists primarily of the following changes: Compartment #1 (Upper): 1) Removed existing upper cabinet compartment tambour door installing new hinged door 2) Relocated existing bleed air temp indicator in upper portion of compartment adjacent existing data loader and removed existing water tank from lower portion of compartment. Area now used for miscellaneous storage. 3) Compartment placarded 4.0# maximum Compartment #2: 1) Removed existing Proctor Silex coffee maker P/N: A607 installing new Krups auto fill maker P/N: 321 to existing slide out tray. 2) Installed new Baker 14' LCD TV monitor aft facing and adjacent to coffee maker. Monitor is retained in the cabinet by a removable shroud assembly, fabricated from Norlam aluminum sandwich panel P/N: NL610-10111-375, .75" X .75" X 0.050" 2024-73511 extruded aluminum angles and TYE 2004 thru inserts and TYE 2001 potted into cabinet. Compartment #3 (Drawer): 1) No changes 2) Compartment placarded 5.0# maximum Compartment #4 (Drawer): 1) No changes 2) Compartment placarded 10.0# maximum Compartment #5 (Bottom): 1) Removed two existing drawers installing new single drawer to fit compartment. 2) Compartment placarded 20.0# maximum Replaced all compartment drawer and door latches with new Actron positive type latches P/N: A23060-9 and A23551-35. Electrical aspects covered separately. All metal fabrication practices per K-C Aviation Process Specification 106. All threaded fastener installations per K-C Aviation Process Specification 105. Fabrication of bulkheads, cabinets, drawers and doors per K-C Aviation Process Specification 116. Cabin interior compartment placards description detailed in K-C Aviation drawing GIV-25.01-218 and layout per drawing GIV-25-04-218. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC 43.13-1A chapter 6 as a guide. Weight and balance accomplished using AC43.13-1A chapter 13 and the aircraft manufacturer's weight and balance manual as a guide. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. END K Additional Sheets Are Attached nu.s. aote vitamin T PRINTING OFFICE 1991-769-01 5/40157 SDNY_GM_02754091 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241013 EFTA01326606

. "; \11121 • JAN — 6 I997 OR REPAIR AND ALTERATION (AM , Powerplant, Propeller, or Appliance) ackremmenew, Form Approved OMB No. 2120-0020 For FAA Use Only Office Identifies,' ic)gn lig INSTRUCTIONS:Print or type all entries. See FAR 43.9. FAR 43 Appendix Et and AC43.9-1 (or subsequ nt revision thereof) for instructions anddisposition of this form. This report is required by law (49U.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 01 1958). 1. Aircraft Make Gulf stream Aerospace Mode IG-IV Serial No. 1085 Nationality and Registration Mark N88GA .2 owner Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. ,._ , Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 .,,..,,;.., „,...,, „„,„...,.,,,,,,..„.0‘.,....wicil miziks:IN 3. For FAA Urie(Gartel IFS WITH THE APPI CAR) F AIRIANIRTHIMFRR REQUIREIviENTS AND IS APPROVED DESCRIBED AIRCRAFT, SUBJECT TO INSPECTION BY A PERSON AUTHORIZED SECTION 7- DATE. ea- SIGNKRIRF. FOR THE ABOVE CONFORMITY IN F 43, 4. Unit Identification FAA MKE FSDO S. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As clisSeribed in hem 1 OM") X . POWERPLANT PROPELLER APPLIANCE Type Manufacturer 6 Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Cerli icate No. K-C Aviation, Inc. 301 Discovery Drive Appleton, WI 54915 U.S. Certificated mechanic C1K2R112L Foreign Certificated MeChailiC x Certificated Repair station Manufacturer D. I certify that the repair and/or alteration made to the can t(s) identified in item 4 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. Date DEC 0 9 1996 Signature of Authorized Individual (" ......A. . 7. Ap al for Return To Service Pursuant Administrator BY to the authority given persons specified below, the unit identified In Item 4 was inspected in the manner prescribed by the of the Federal Aviation Administration and is GAPPROVE0 0 REJECTED FAA Flt. Standards Inspect or Manufacturer Inspection Authorization Other (Specify) FAA Designee x Repair Station Person Approved by Transport Canada AInvorthiness Group °aloof Approval or Rejection 18 1996 Certificate or Designation No. 12K2R112L Signature of Authorized Individual DEC C)S`" d e"-" .• FAA Form 337 02.8e) SDNY_CM_02754092 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EF1'A_0024I0I4 EFTA01326607

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 LOnlOrmily with the applicable airworthiness requirements. 8. Description of Work Accomplished (If more space is required attach additional sheets. Identity with aircraft nationality and registration mark and dale work completed) Removed existing cabin window ledges and lower sidewalls, modified existing vestibule, cabin, aft galley headliner and existing floor conditioned air ducts, installed new window desiccant system, upper sidewall speakers, new ledges and lower sidewalls and two additional oxygen presentation units as detailed below. Interior components located in accordance with K-C Aviation, Inc. floor plan drawing GIV-25-05-200, sheet 1. Cabin peripheral interior rework extends from forward cabin bulkheads F.S. 155 to aft cabin bulkheads F.S. 445. Modified by sectioning existing cabin headliner into five 48.00" long sections using the following K-C Aviation drawings: GIV-25-50-213, sheet 1, rev. A - Headliner Vestibule Assy and Installation; GIV-25-50-213, sheet 2, rev. A - Headliner Main Cabin Bracket Details; GIV-25-01- 213, sheet 1 -Headliner Support Bracket Installation. The five panels interlock together on the forward and aft ends when installed in the aircraft with a flange and slot assembly fabricated from .040" 2024-T3 aluminum flat stock and 5 slots fabricated from 0.75 X .025" X .075" 2024-T3511 extruded aluminum Z angle. The headliner is retained in the aircraft on the outboard edges using existing isolator mounting provisions and ten 34.00" long support angles (5 ea. side) fabricated from 0.063" 2024-T3 aluminum installed between each existing headliner bracket. Added two new Scott dual oxygen presentation units P/N: 833-610 in left headliner F.S. 286.5 and 307.5 and two duel presentation units, one left valance F.S. 213.81 and one in right valance F.S. 213.81. All new units are plumbed to existing system. Additional presentation unit installation and seating configuration does not exceed limitation requirements of Aero Interiors continuous flow supplemental oxygen system STC SA4416NM. Fabricated and installed 11.0" X 5.0" light bracket assemblies in vestibule between F.S. 85.0 and F.S. 97 (1 ea.) and galley (2 ea.) using K-C Aviation, Inc. drawing GIV-25-50-213, sheet 4, rev. A - Headliner Aft Galley Assy and Installation. Each bracket assembly is fabricated from .040" 2024-T3 aluminum. Each assembly is retained by four brackets fabricated from 1" X 1" X .050" 2024-73511 extruded aluminum L angle riveted or hylocked to adjacent frames. Bracket assembly provides mounting surface for dome style lights. Fabricated and.installed mounting provisions for five upper sidewall entertainment system speakers on each side of the cabin between each cabin window, F.S. 200, 250, 301, 350 and 395 in accordance with K-C Aviation Inc., drawings GIV-25.02-211, sheet 1 & 2 - Upper Sidewall Speaker Installation. Each assembly consists two formed angles and four brackets constructed from 0.063" 2024-T3 aluminum to accommodate the 8.50" X 5.00" Baker HF93 speaker assemblies. Each speaker is retained to the aircraft by the four angle brackets riveted to the adjacent frames, four each isolator mounts P/N: 100147-40-062; four each MS21059L3 nutplates and MS227039-1 screws, two each formed angles and hardware provided by the speaker manufacturer. Fabricated and installed replacement left and right ledges using K-C Aviation, Inc., drawings GIV- 25-51-203, sheet 2, rev. A - Lower Sidewall Ledge Assembly and Install; GIV-25.04-203, sheet 1 - Ledge VIP Panel Installation; CL600-25-17-203, sheet 1 - Ledge Lid And Storage Compartment Install Installation consisting primarily of four sections fabricated from NL610-10122-500 and - 250 Norlam sandwich panel; two left and right forward and one right aft section with retractable table provisions; left aft section behind divan. Each section is secured to each side of the cabin below the window line using TYE 2004A3-500 and TYE 2001-08-10 thru and threaded inserts potted into ledge, isolators P/N: B-532-1 and MS hardware into a formed aluminum assembly consisting of a full length intercostal, aluminum gussets, angles, webs and gusset plates riveted together and to the aircraft structure. Ledges contain cup holders and electrical membrane switches at seating locations, VIP panel and Magnastar handset and cell phone storage at #2 left and right forward cabin seats. The lower sidewall panels are fabricated from NL 610-10111-250 Norlam sandwich panel and close-out area below ledges to existing floor conditioned air duct. Panels are sectioned for easy access and retained by the ledge end cap and an aluminum angle running full length of ledge. The lower end of sidewall panel is retained using an aluminum angle blind riveted to existing conditioned air duct and Velcro loop and hook fastener material. rif Additional Sheets Am Attached *U.S. GOVERNMENT PRINTING OFFICIO IS112-761-0ISNSOIS7 SDNY_GM_02754093 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241015 EFTA01326608

Gulfstream GIV, S/N: 1085 N88GA Page 2 Reworked existing floor length left and right cabin conditioned air ducts due to removal of previously installed cabin stowable tables at F.S. 206, 297 and 395 in accordance with K-C Aviation, Inc., drawing GIV-25-01-207, sheet 1 - Conditioned Air Heat Duct Repair. Rework consists of closing out upper duct recesses using a 0.040" 2024-T3 aluminum panel blind riveted with NAS9301B-4 rivets and PR1422 sealant. Relocated existing cabin temperature sensors P/N: 926485-1-1 in accordance with floor plan drawing. Right forward temperature sensor moved from F.S. 219 to F.S. 250 and left aft moved from F.S. 436.5 to 345. Fabricated and installed new left and right cabin window desiccant systems using K-C Aviation, Inc., drawing GIV-25-51-203, sheet 6, rev. A • Lower Sidewall Window Desiccant System Installation. Each desiccant system is constructed of 2.0" X 21.0" long Excelon tube bonded with 2.0" PVC end caps bonded on each end with PCV adhesive. One end cap contains a hose barb fitting P/N: 125HBL4-4 the other with an MS 20913-4D fill plug. Desiccant tubes are mounted below window ledges in lower sidewalls at F.S. 200 with two MS21919WH32 clamps and a bracket fabricated from 0.050" 2024-T3 aluminum riveted to the aircraft structure. Each desiccant tube is plumbed to each window with 5052-0 0.25" tubing, Tygon polyethylene tube, Nalgene nylon TEE P/N: 582707C/15221CA and Y P/N: 582747C/13366CA fittings as required. Performed an oxygen drop-out test in accordance with Gulfstream Aerospace Maintenance Manual chapter 35. Electrical requirements for above installations covered on separate form 337. All metal fabrication practices carried out per K-C Aviation Process Specification 106. All threaded fastener installations carried out per K-C Aviation Process Specification 105. Riveting accomplished using AC43.13-1A chapter 2 as a guide. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC43.13-1A chapter 6 as a guide. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. END SDNY_GIvl_02754094 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241016 EFTA01326609

SDNY_GM_02754095 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_002410 I 7 EFTA01326610

migrgoweE• C. • - "'"— -- lii US ontra— 6 ici l itJOR lit g. iliviniten 'I REPAIR AND e, Powerplant, Props !' fRato3N6 mg It • or Appliance) II' i' La I IL' : Form Approved OMB NO.2120-0020 For FAA Um Only Office identification 6 4 ia INSTRUCDO.NS:RsinSeotypea entries. See FAR 43.8 FAR 4 Appendix B. and AC 4.371-"Mu s7Vertu —ird nt revision thereof) for instructions disposition of this form. This report is required by law (49U.S.C. 1421). Failure to report can result i a civil penalty not to exceed $1.000 for each such violation (Section gat Federal Aviation Act of 1958). I. Aircraft Make Gulfstream Aerospace M°deb-IV Serial No. 1085 Nationality and Registration Mark 2. Owner Name (As shown on registration cenifkate) Coca-Cola Enterprises, Inc. Address (As shown on registration cetlificatel 2500 Windy Ridge Parkway Atlanta, Georgia 30338 3. For FAA Use Only 'The data/alteration identified herein complies with the applicable airworthiness requirements and is approved for the above discribed aircraft to conformity inspection by a person authorized in FAR 43, Section 43.r. \ Date \ 7 \s::\‘,0 FAA Inspector . k—L GL13 4. Unit Identification 5. Type Unit Make Model Serial No. Repair Alteration AIRFRAME (As described in Item 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 8. Conformity Statement A. Agency's Name and Address 8. Kind of Agency C. Certificate No. K-C Aviation, Inc. 301 Discovery Drive Appleton, WI 54915 V.S. Certificated Mechanic QK2R112L Foreign Certificated Mechanic x Cenificated Repair Station Manufacturer D. I certify that the repaira/xi/or alteration made to the un t(s) identified in item 4 above and described on the reverse or attachments hereto have been made In accordance with the requirements of P n 43 of the U.S. Federal Aviation Regulations and that the information furnished herein is true and correct to the best of my knowledge. Date • DEC 09 1996 Signature of Authorized individual 7. Approv r Return To Service Pu suant to the authority given persons specified below, the unit Identified in item 4 was inspected in the manner prescribed by the Administrator of the Federal Aviation Administration and s ja,APPROVED 0 REJECTED FAA FIL Standards Inspector Manufacturer Inspection Authorization Other (Specify) BY FAA Designee X Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 18 1996 Certificat ati e or Desn on No. ig QK2R112L Signature of Authorized Individual gsn,o FAA Form 337 one) SDNY_ GE/1_02754 096 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA_0024I0I8 EFTA01326611

NOTICE • • Weight and balance or operating limitatiorrafangesshalf qe 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 of more space Is required. attach additional sheets. Identity with akeraff nationality and registration mark and date work completed.) Remounted interior cabin door at F.S. 155 to hinge from right side. Door installed with new hinge assembly fabricated in accordance with K-C Aviation, Inc., drawing GIV-25-50-229, revision A, sheet 10. Door is retained in the open position by a door stop installed on lower vestibule storage cabinet. Fabricated and installed mounting tray for HPA/LNA on right lower cabin sidewall F.S. 250.5 in accordance with K-C Aviation, Inc., structural drawing GIV-25-51-203, sheet 7. Mounting tray is constructed from 0.040" 2024-T3 aluminum sheet. Tray is mounted using MS24693-10 screws and MS21059L3 nutplates to the aircraft structure between adjacent frames using brackets fabricated from 0.050" 2024-T3 aluminum sheet riveted to the aircraft structure. Fabricated and installed mounting trays for CDBR-2 on center right lower cabin sidewall F.S. 238 and CDBR-2 on left aft cabin below ledge, F.S. 430 in accordance with K-C Aviation, Inc., structural drawing GIV-23.02-301, sheets 1 & 2. Trays are constructed from 0.040" 2024-T3 aluminum mounted to the aircraft structure with four brackets fabricated from 0.050" 2024-T3 aluminum with rivets and MS hardware. Fabricated and installed miscellaneous electrical component mounting trays located on left lower forward cabin below ledge F.S. 170 and right forward cabin behind coat closet F.S. 127. Trays are primarily constructed from 0.050" 2024-T3 aluminum sheet mounted to the aircraft structure with MS hardware to 2.75" X 4.5" brackets fabricated from 0.050" 2024-T3 aluminum sheet riveted to frames or stringers as required. Overall dimensions of left trays (2 ea.) at F.S. 170 are 6.5" wide and 16" wide; 3.5" wide and 12.0" long. Overall dimensions of right forward tray F.S. 127 is 9.0" wide and 19.5" long. Trays provide mounting surface for cabin lighting power supplies, terminal strips and entertainment system controllers. Fabricated and installed new replacement lavatory vanity fluorescent accent light bar, F.S. 502. Unit is constructed from NL610-10111-250 Norlam aluminum honeycomb panel contoured to headliner extending from lavatory door to vanity top. Overall dimensions are 2.125" wide and 58" long. Light bar is mounted to the existing bulkhead using three 1.25" X 1.0" X 0.063" 2024-T3511 extruded aluminum L brackets, TYE threaded inserts potted into bulkhead, MS screws and nutplates. The light bar contains mounting provisions for two fluorescent tubes. Unit constructed using K-C Aviation Process Specification 106 and fasteners installed per Process Specification 105. Fabricated and installed feed thru behind entertainment cabinet for micellaneous electrical cable routing in accordance with K-C Aviation drawing GIV-25-15-293, sheet 1. Fabricated and installed replacement left and right life lines only. Lines fabricated in accordance with K-C Aviation emergency equipment and location drawing GIV-25-00-222, revision C, sheet 1. Life lines attach to existing seat tracks below emergency exits and when in use, to existing eye mounts on each wing. K Additional Sheets Are Attached GOVOINMENT PRINTING OFFICE: IM -769-012/60167 SDNY_GM_02754097 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241019 EFTA01326612

Gulfstream GIV, S/N: 1085 N88GA Page 2 Fabricated and installed a new cockpit curtain and track assembly, F.S. 73. Curtain is constructed from 100% wool pleated and sewn to the dimensions of 67.0" high and 24.0" wide. Curtain slides with nylon curtain guides on a curtain track P/N: 9046 fastened to the headliner MS hardware. Curtain is retained in the open position with two straps fabricated from same material as curtain and snaps. Electrical aspects covered separately. Cabin interior compartment placards description detailed in K-C Aviation drawing GIV-25.01-218 and layout per drawing GIV-25.04-218. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC 43.13-1A chapter 6 as a guide. Weight and balance accomplished using AC43.13-1A chapter 13 and the aircraft manufacturer's weight and balance manual as a guide. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. END SDNYGIvl_02754098 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241020 EFTA01326613

SDNY_GM_02754099 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA _00241021 EFTA01326614

T. • i • q I I il . • : JAN — 6p.?7, il,IAJOR REPAIR AND ALTERATION t0000101 (Airframe, Powerplant, Propeller, or Appliance) ;v 91 0, imb iF rM Approved OMB NO. 2120-0020 Use °ifil I Office IdeF:trifiFcAA a ri..13 tsrent or type of this form. such violation (Section 43.9, FAR 43 Appendix B.andAC 43.9-1 (or subsequent revision thereof) tor instructions by law (49U.S.C. 1421). Fa lure to report can result Ina civil penalty not to exceed S1,000 Act of 1958). , OCTieff4S-: and disposition for each all entries. See FAR This report is required 901 Federal Aviation 1. Aircraft Make Gulfstream Aerospace ModelG-IV Serial No. 1085 Nationality and Registration Mark N88GA 2 Owner . Name (As shown on registration certificate) Coca-Cola Enterprises, Inc. Address (As shown on registration certificate) 2500 Windy Ridge Parkway Atlanta, Georgia 30338 3. For FAA UslrOMt I fUrtl-i ti -U4i 5...filintiJFtliri lOhlq I I hitU FIEHIN t•UlYie Itb Wit H I It AYFLIUMULt AIM/KA-CI HIrsik&S REQUIREMENTS AND IS APPROVED FOR THE ABOVE DESCRIBED AIRCRAFT, SUBJECT TO CONFORMITY INSPECTION BY A PERSON AUTHORIZED IN F 43, SECTION 43.7. 4. Unit IdenTfiggiart-11VI Vie StuNAt UR . Unit Make Model FAA MKE FS • • Serial No. Repair Alteration AIRFRAME (As described in !tern 1 above) X POWERPLANT PROPELLER APPLIANCE Type Manufacturer 8 Conformity Statement A. Agency's Name and Address B. Kind of Agency C. Certificate No. K-C Aviation, Inc. 301 Discovery Drive Appleton, WI 54915 V.S. Certificated mechanic QK2R112L Foreign Certificated Mechanic y certificated Repair Station manwactunw O. I certify that the repair and/or alteration made to the un t(s) identified in item 4above 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. Date DEC 0 9 1996 Signature of Authorized Individual 7. App for Return To a Service Pursuant Administrator BY to the authority given persons specified below, the unit Identified in item 4 was inspected In the manner prescribed by the of the Federal Aviation Administration and is ikAPPROVED O REJECTED FAA Flt. Standards Inspector Manufacturer Inspection Authorization Other (Specify) FAA Designee x Repair Station Person Approved by Transport Canada Airworthiness Group Date of Approval or Rejection DEC 18 1996 Certificate or Designation No. QK2R112L Signature of Authorized Ind idual C stsre. d . FAA Form 337 112•0 SDNY_GM_02754100 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241022 EFTA01326615

NOTICE Weight and balance or operating limitation changes shall be entered in the approprlate 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 (lf more space is required, attach additional sheets. identity with aircraft nationality and registration mark and date work completed.) Reworked existing left vestibule entertainment cabinet at F.S. 144 as follows: Removed the following equipment: 1) Stereo cassette deck, Sony P/N: TC-WR808M 2) Stereo amp, Sony P/N: TA-808M 3) AM/FM tuner, Sony P/N: ST-707RM 4) CD player, Sony P/N: CDP-5107 5) Video switch, ASINC P/N: 912001 6) VCR, Panasonic P/N: F85A30987 7) Video monitor, Sony P/N: PVM-2030 8) Video distribution amp, United P/N: PD-6 9) Removed upper shelf and compartment doors retaining forward and aft bulkheads. 10) Relocated existing data loader P/N: DL-800 from upper cabinet to right vestibule upper crew cabinet. Fabricated and installed new replacement compartment cabinet to accommodate new ententainment equipment and provide miscellaneous storage. Compartment cabinet peripheral is conitructed.,from,ML610-10111-V5 Aluminum honeycomb panel assembled together in accOrdance-withi0C Aviation PrdbUOPecification 116. Overall dimensions of cabinet are 34.5" high, la".5" wide and 24.125" deep. Cabinet contains two compartments, an upper removable entertainment cabinet fabricated similarly to compartment cabinet using NL610-10111-250 aluminum honeycomb panel. Cabinet dimension are 17.25" high, 18.5" wide and 14.5" deep and contains mounting provisions for the following new equipment: 1) CD magazine or tape storage 3) AM/FM cassette player, Alpine P/N: TDA7552 3) CD changer, Sony P/N: CDX-91 4) CD controller, Sony P/N: RM-X59RF 5) VCR, Panasonic P/N: PV4662 Lower compartment dimensions are 16.0" high. 18.0" wide and 24.125" deep and is used for miscellaneous storage. The overall compartment cabinet is retained to the existing lower compartment structure and bulkheads using MS hardware and threaded inserts installed per K-C Aviation Process Specification 105. Entertainment and miscellaneous storage compartment are closed out with a hinged doors ancActron positive type latches. Fabricated and installed a new tapes and CD storage drawer in lower compartment. Overall dimensions are 5.0" high, 18.5" wide and 23.0" deep. Door is hinged with Brusso L23 knife hinges and retained in the closed position using an Actron positive type latch P/N: A23060-9. Entertainment cabinet compartments maximum placarded weights are as follows: 1) Upper CD magazine and tape storage compartment - 5.0 Lbs. 2) Miscellaneous storage compartment - 25.0 Lbs. 3) Fitted tapes/disc storage drawer - 25.0 Lbs. Electrical aspects covered separately. All metal fabrication practices per K-C Aviation Process Specification 106. All threaded fastener installations per K-C Aviation Process Specification 105. Fabrication of bulkheads, cabinets, drawers and doors per K-C Aviation Process Specification 116. Cabin interior compartment placards description detailed in K-C Aviation drawing GIV-25-01-218 and layout per drawing GIV-25.04-218. Fasteners torqued using AC43.13-1A chapter 5 as a guide. Corrosion protection accomplished using AC 43.13-1A chapter 6 as a guide. Weight and balance accomplished using AC43.13-1A chapter 13 and the aircraft manufacturer's weight and balance manual as a guide. Materials used meet the requirements of FAR 25.853. The aircraft weight and balance manual and equipment list revised. END 0 Additional sheets Are Attached *U.S. GOVERNMENT PRINTING OFFICE: 1912-769-0I2/601S7 SDNY_GM_02754101 SUBJECT TO PROTECTIVE ORDER PARAGRAPHS 7, 8, 9, 10, 15, and 17 EFTA 00241023 EFTA01326616