AC 20-64 Appendix 2 8/1/69 Page 1 FIGURE B-1. WING STATION DIAGRAM
ACTUATOR TRACK TRACK ACHERIOR
FLAP STATIONS
SEE NOTE A
FLAP STATIONS
27.8 / 45.8 34-6 TRACK SCREW (TRAILING EDGE STRUCTURE) SEE NOTE A sd.I 94.I E / B21/ TRACK / 143.6 106.9 161.9/186.4 223.1 / 258.2 / TRACK 204.7 TRACK DRIVE SCREW TRACK AILERON STATIONS
(174.2) / 251.4 / 263.21 / 331.1 278.1 / 313.7/ | 00|309|65|2|133|675|2017 SEE NOTE B
FUS STA
694.
FUS STA.
571.2 15% CHORD (AFT FACE FRONT BEAMY 1291) 1282420 322 397/106/128 413) 159: 73|188/515|526:1541 |556:576 239 197 221 257 293 398 431
WING STATIONS
WING REFERENCE PLANE 6° 0°
NACELLE
NACELLE
CENTER OUTER SECTION AND TIP
SECTION NOTE A. FLAP STATION AND TRAILING EDGE STATION PLANES ARE PERPENDICULAR TO THE WING REAR BEAM.
B. AILERON STATION PLANES ARE PERPENDICULAR
TO HINGE CENTERLINE AND WING REFERENCE PLANE
Pagendix 2 AC 20-64 Page 8/1/69 FIGURE B-2. WING SKIN SKIN PLANKS AND MATERIAL INDEX FUS STA 694,9 FUS PANEL NO. 4 PANEL NO. 5 PANEL NO. 6 PANEL NO. 7 PANEL NO. 8 PANEL NO. 9 STA PANEL NO. 3
571.2 PANEL NO, 2 STIFF. NO. 61 PANEL NO. 1 STIFF. NO. 57 STIFF. NO. 50 STIFF. NO. 43 STIFF. NO. 36 STIFF. NO. 29 UPPER SURFACE STIFF. NO. 22 STIFF. NO. 15 B. L. 65.0 STIFF. NO. 8 STIFF. NO. 1 NOTE SYMMETRICAL ABOUT B.L. O.O.
PANEL NO. 4 PANEL NO. 5 PANEL NO. 6 PANEL NO. 7 PANEL NO. 8 PANEL NO. 9 STIFF. NO. 61 | STIFF. NO. 57 PANEL NO. 3 STIFF. NO. 50 PANEL NO. 2 STIFF. NO. 36 pariara STIFF. NO. 43 PANEL NO. 1 STUFF. NO. 29 LOWER SURFACE B.L. O.0 STIFF. NO. 22 (ROTATED 1800) STIFF. NO. 25 5 TEE - LS4113 (TYP 2 PLACES), SEE 51-3-6, FIGURE 1 (SHEET 2) STIFF. NO. 8 6 ATTACH ANGLE - LS6681, SEE 51-3-6, FIGURE 1 (SHEET 2) B: L. 65.0 STIFF. NO. 1 INTERCOSTAL ASSEMBLY:
INTERCOSTAL - LS6258, SEE 51-3-6, PANEL (TYP) - LS7255, SEE 57-2-1, FIGURE 3 FIGURE 1 (SHEET 2) PANEL (TYP) - LS7256, SEE 57-2-1, FIGURE 3 FITTING - LS6300-2-36-557 TUBE - 2024-T3 AL ALLOY SPLICE PLATES - .150 7075-T6 AL ALLOY 4 TEE - LS4929 (TYP 4 PLACES ), SEE • SPLICE PLATE - .190 7075-T6 CLAD 51-3-6, FIGURE 1 I SHEET 2)
AC 20-64 Appendix 2 8/1/69 Page 3 FIGURE B-3. WING ACCESS AND INSPECTION PROVISION
FUS STA
- 694. 9
FUS STA
- 571.2
BOTTOM VIEW DECAL
NO INSPECTION OR ACCESS ITEM DENTIFICATION FUEL TANK W106
LOWER TRAILING EDGE 3 FUEL TANK W107 TOP VIEW 4 AILERON TRAILING EDGE 5 FUEL TANK W108 6 AILERON
FLAP TRAILING EDGE
FILLETS
ENGINE START LINE (RIGHT SIDE ONLY) 10 LEADING EDGE * 11 LEADING EDGE LIGHTS AILERON TIP VIEW B 22 15 14 FUEL PUMP OVERWING FUEL FILLERS NOTE (ROTATED FOR CLARITY ) 16 FUEL TANK W105 A. LEFT SIDE SHOWN. ALL ACCESS OPENINGS 17 FUEL SYSTEM W103 ARE FOR RIGHT AND LEFT SIDES EXCEPT 18 FLAP LEADING EDGE WHERE NOTED.
19 FUEL TANK W102 B. REFER TO 54-0, FIGURE 3 FOR ACCESS TO 20 FUEL TANK W101 WING IN VICINITY OF NACELLES.
21 DRY BAY C. REFER TO 53-0, FIGURES 3 AND 4 FOR 22 CENTER SECTION ACCESS TO WING IN THE CENTER SECTION.
* INDICATES A HINGED ACCESS DOOR. ALL OTHERS ARE REMOVABLE
AC 20-64 Appendix 3 8/1/69 Page 1 FIGURE C-1. NACELLE STATION DIAGRAM NACELLE STATIONS
• 30.4 33.6 54.4 90.6 120.0
53. 1 1-19.1 0.0 24.4 48. 8 77.6 110.0 & THRUST 41.75 1 - 9.5 12.0 | 140.01. | 64.0 104.0/ 130.0 145.0 NAC W.L
0.0 NAC W.L.
-86 NAC STA INBOARD NACELLE
- 76. 1
NACELLE STATIONS
- 9.5 & THRUST -44.2 -31.5 -19.0 0.0 110.0 / 18.0 25.0 70.0 43.96 81.5 91.3 103.2 | 109.0 NAC
• W.L.
0.0
NAC OUTBOARD NACELLE W. L. NAC -&4 STA
- 67.2 P.P. P.P.
STA 81. 1 STA P.P. 49.5 STA STA P.P.
63.2 29.7 & SIDE COWL HINGES A. POWERPLANT STATIONING IS SAME FOR INBOARD AND OUTBOARD NACELLES.
B. POWERPLANT STATIONS ARE PERPENDICULAR TO THRUST CENTERLINE.
- E THRUST C. NACELLE STATIONS ARE PERPENDICULAR TO NACELLE WATER LINE.
COWLING PROP BLADES P.P. P.P. P.P. P.P. P.P.
STA STA STA STA STA
120.6 95 52.0 21.2 0.0
716.4 8/1/69 AC 20-64 742
754.0 765.7 758.5 < 770.35 768 FIGURE D-1.
789.3- 796.5 129.8 130.4 - 140.1 107.4- 118. 8 - -825
853.5 844 863 837 176. 7- 176.8-5 8 m
872.5 882 875 200 208. 5- - 202.6 FUSELAGE STATIONS DIAGRAM (SERIAL NOS. 1001 AND UP)
907.8 901 920 ( SEE SHEET 2 FOR LAC SERIALS 2001 AND UP) 2645274 245.5- 255 - 253.4 -236 -272.9
- 958 LAC SERIALS 1001 AND UP 283.5 275.6
- 977 302.5 - - 293
309.3 1005.5 996 VIN 326.3 1024.5 - 1031.4-1031.6 1015 350- 337.5- 354· -333 - 329.3 1037.5 1034 366.5- - 352 -1053 -371 1063.7 - 1072 404. 4397.5 400 -1091 416.5- -407 1122. CANTED CANTED) 1117- 1110 439.7- 426 1133.7 ( CANTED) 454,5- Z447.3 -445 1150. 7( CANTED). $73.5- — 464 1159.2( CANTED ) 1167.71 CANTD- 486.9- 1185.7 ( CANTED) 511.5- 1203. CANTED CANTED) 530.5- -521 1221. CANTED CANTED).
1240. 5( CANTED) 549.5- 559 _565.3 1259( CANTED) 1295.5( CANTED) 1283( CANTED) REFERENCE LINE- TAIL SECTION -571 597 -578 - 613.7 Appendix 4
625.5- 633. 9 637.4 654 Page 1 _673
683. 9
Appendix 4 AC 20-64 Page 2 8/1/69 FIGURE D-2. FUSELAGE STATIONS DIAGRAM (SERIAL NOS. 2001 AND UP) U LEVEL FLOOR W.L. 123.5 NI un 731223 LAC SERIALS 2001 AND UP 1117
TAIL SECTION
REFERENCE LINE 1005.5- 1024, 5- 1037.5 1063.7- 1122. 3( CANTED) - 1133.7 ( CANTED )- 1150. 7 (CANTED) 1187 4 CANTED 1185. 7( CANTED )- 1203.7( CANTED). 1221. CANTED CANTED) 1240. 5( CANTED)- 1259( CANTED). 1283( CANTED) 1295,5( CANTED)
AC 20-64 Appendix 4 8/1/69 Page 3 FIGURE D-3. FUSELAGE CONTOUR COORDINATES FUS STA 42 TO FUS STA 217 - BETWEEN THESE STATIONS THE FUSELAGE IS A FAIRED SECTION. THE CONTOUR SHOULD CONFORM TO THE SURROUNDING STRUCTURE.
ONTOUR IS GIVEN: SUBTRACT SKIN THICKNESS (SEE 53-2-1, OBTAIN FRAME, FORMER OR BULKHEAD CONTOUR. 68.00 RAD
- W.L. 150
I SYMMETRICAL FUS STA 901 TO FUS STA 1117 - SEE TABLE ABOUT
FOR VALUES OF DIMENSIONS AT APPROPRIATE FUSELAGE STATION.
POINT "A"
• W. L. 150 POINT "B" POINT "C" POINT "A" POINT IB" POINT 'C" FUS STA Ru B.L. W.L. B.L. W.L. B.L. W.L.
907.8 25 . 13 149.96 64,94 129.83 28.23 88.19 68.00 67.86 68.18 920 1.34 - 96 149.78 66.32 134.96 36.11 92.73 68. 00 67.01 58.85 939 3,75 3.15 149.73 67.76 144.24 45,14 98,09 68,00 64,04 09-94 958 _04 6.57 5,.61 150.20 67.93 152.01 46. 86 103.45 67.96 62.35 70.83 977 .82 9.62 -7.04 150.75 67.18 150.17 44.42 103.63 67.19 60.14 71.47 996 2.26 12.84 7.21 151.58 65.45 140.08 38.75 102.30 65.74 58.50 71. 88 1005.5 3.15 14.50 6.92 152.17 64.21 144. 06 35.23 101.71 64. 85 57.86 72.00 1015 4.06 15.99 6.43 152.94 62.91 143.09 31.76 101.51 63.86 57.33 71.89 1024.5 4.97 17.16 5.87 153.82 61.62 142.96 28.75 101.83 62.78 56.80 71.31 1034 5.88 17.99 5.25 154.81 60.40 143.60 26.07 102.53 61.63 56.28 70.46 1037.5 6.22 18.20 5.00 155.19 59.92 143.80 25.10 102.84 61.18 56.08 70.02 1053 7.70 18.55 3.92 156.97 58.11 146.83 21.58 104.74 59.12 55.14 67.36 1063.7 8.73 18.18 3.19 158.19 56.79 149.15 19.71 106.41 57.59 54.36 64.84 1072 9.52 17.53 2.73 159.08 55.64 150.47 19.21 108.07 56. 37 53.60 62.48 m17 13.83 13.83 163.83 48.96 48.96 48.96 NOTE DATA GIVEN FOR OUTER-SURFACE CONTOUR. SUBTRACT SKIN THICKNESS (SEE 53-2-1, FIGURE 1) TO OBTAIN FRAME, FORMER OR BULKHEAD CONTOUR.
2. BETWEEN FUS STA 1072 AND 1117 THE FUSELAGE IS A FAIRED SECTION.
THE CONTOUR SHOULD CONFORM TO THE SURROUNDING STRUCTURE.
FUS STA 1117 TO FUS STA 1295 - BETWEEN THESE STATIONS THE FUSELAGE IS A FAIRED SECTION. THE CONTOUR SHOULD CONFORM TO THE SURROUNDING
Appendix 4 AC 20-64 Page 4 8/1/69 FIGURE D-4. FUSELAGE CANTED SECTION
- W. L.207 -W. L.184
TAIL SECTION
REFERENCE LINE W. L. 150 1117 1122.3 (CANTED) 1133,7 (CANTED) 1150.7 (CANTED) 1159.2 (CANTED) 1167.7 (CANTED) 1185.7 (CANTED) 1203.7 (CANTED) 1221.7 (CANTED) 1240.5 (CANTED) 1259 (CANTED) - 1283 (CANTED) 1295.5 (CANTED) NOTE
FRAME OR FORMER SEGMENTS
ARE LOCATED APPROXIMATELY FUS STA FRAME OR FORMER REINFORCEMENT AS SHOWN: - (CANTED) 1117 SEE 53-2-3,FIGURE FIGURE I (SHEET 5) 68 - STRINGER NOS 1122.3 (6) THRU (11) - .040 7075-16 CLAD| (8) (9) - LS3255 * 63 (15) (16) (1) (2) 1133.7 (1) THRU (16) -1•032 7075-T6 CLAD FWD FACE - (3) THRU (5), (12) THRU (14) - LS3572-40 (7) THRU (10) - .040 7075-T6 CLAD • 59 (14) 14 1LS3572-4* AFT FACE - (1) THRU (16) - LS6844• 1150.7 SEE SHEET 2
(13) (4) 1159.2 (7) THRU (10) - .040 2024-T4 CLAD.
54 012) 1167.7 SEE SHEET 2 1185.7 SEE SHEET 2 50 1203.7 SEE SHEET 1221.7 SEE SHEET 3 45 (10)
(9) 1259 1240.5 .032 2024-T4 CLAD 1283 032 6061-T4 AL ALLOY VIEW LOOKING FORWARD AT A TYPICAL FRAME 1295.5 SEE 53-3-1, FIGURE 1 (SHEET 2) B. PORTION OF FRAME OR FORMER SEGMENT IS INDICATED WHERE NECESSARY AS FOLLOWS:
* INNER FLANGE
• OUTER FLANGE
• WEB C. REFER TO 53-2-3, FIGURE 2 FOR REPAIRS AND NEGLIGIBLE DAMAGE.
IF NOT APPLICABLE, REFER TO 51-3-6, FIGURE 1 (SHEETS 1 AND 2).
AC 20-64 Appendix 5 8/1/69 Page 1 FIGURE E-1. STABILIZERS STATIONS DIAGRAM HORIZONTAL STABILIZER STATIONS 235.5 200.5 218.0 241.3 *ALLIONS NE CANTED
183.0
107.5 134.5 155.5 80 (H.S.S) * 148.0
94.0
80.5
67.0 VERTICAL STABILIZER STATIONS (V.S.S) * - W. L 184 - 00 30° 18.28 1204.0 11 50 FUSELAGE STATIONS (F.S.)
183.5 176.7 106.5 99.0 1072.0 1110.0 1024.0 1091.0 1117.0 1015.0 1053.0
996.0
958.0
920.0
Appendix 5 AC 20-64 Page 2 8/1/69 FIGURE E-2. HORIZONTAL STABILIZER STRINGER IDENTIFICATION STA
28.0 STA STA STA STA STA STA STA (CANTED) STA 53.5 80. 5 107.5 134.5 165.5 200. 5 235.5 AIRPLANE EDGE 40. 0 STA STA STA STA STA STA STA OF ( CANTED) 67.0 94.0 121.0 148. 0 18.0 218. 0 253.0
REAR FILLET BEAM -
STRINGER NC. XI
UPPER SURFACE
FRONT BLAM
REAR BEAM 5650 9000000000
LOWER SURFACE FRONT BEAM!
FOR REPAIRS:
IN AREA MARKED THUS AN. NOTE ITEMS INDICATED THUS * IN CALLOUTS BELOW.
IN AREA MARKED THUS . NOTE ITEMS INDICATED THUS * IN CALLOUTS BELOW IN AREAS MARKED THUS EZZA, NOTE ITEMS INDICATED THUS • IN CALLOUTS BELOW.
IN AREAS MARKED THUS B229 SEE SHEET 2
THIS TYPE REPAIR MAY BE MADE ONLY IN THE LOCATIONS INDICATED ABOVE, ON LEF
AND RIGHT STABILIZERS NOTE: NO REPAIR SHOULD BE ADJACENT TO, NOR DIRECTLY OPPOSITE (IN THE OTHER SURFACE ANOTHER REPAIR OF THIS TYPE.
1 ACCESS DOOR - MAKE FROM .050 7075-T6 CLAD. SHAPE TO SUIT CUT-OUT IN SKIN WITH MINIMUM GAP. ATTACH WITH NASS17-3 SCREWS.
2 DOUBLER - WAKE FROM .050 7075-T6 CLAD. DIMENSIONS NOT SHOWN ARE TO BE TAKEN FROM AIRPLANE. MAKE ACCESS HOLE ENDS SEMI-CIRCULAR. TRIM FLANGE AS SHOWN FOR ANGLE. JOGGLE SIDES ON TO STRINGER FLANGES.
3 ANGLE - MAKE FROM ,040 7075-T6 CLAD, SAME LENGTH AS DOUBLER. TRIM ENDS AS SHOWN IN MAIN VIEW, OR WHERE APPLICABLE, AS IN VIEW "A" 4 FILLER - MAKE FROM .032 7075-T6 CLAD. TRIM ENDS AS SHOWN.
5 SKIN ATTACHMENTS:
ROW O-FOR LENGTH OF DOUBLER, ADD MS20426ADS RIVETS MIDWAY BETWEEN EXISTING RIVETS.
*FOR LENGTH OF DOUBLER, REPLACE EXISTING MS20426ADS RIVETS WTH MS20426DD6 RIVETS.
ROWS) AND - IN AREA OF CUT-OUT IN SKIN ADD ANCHOR NUTS (SAME TYPE AS ITEM 7) MIDWAY BETWEEN MS20426AD5 RIVETS RE-
PLACED IN EXISTING HOLES ( COUNTERSUNK IN STRINGER OUTSIDE AREA OF CUT-OUT IN SKIN, REPLACE 3 EXISTING RIVETS WITH MS20426DD6 RIVETS.
ROWS AND 1 - MS20426DD6. USE 3 IN EACH ROW, SPACED 1.00 APART EACH
SIDE OF DAMAGE ROWS AND - MS20426DD6. USE 3 IN EACH ROW, SPACED 1.10 APART EACH SIDE OF DAMAGE.
**RETAIN ORIGINAL RIVETS.
•FOR LENGTH OF DOUBLER ADD MS20426ADS RIVETS MIDWAY BETWEEN EXISTING RIVETS.
STEM ATTACHMENTS - AN470AD5. SPACE 1.00 APART.
ANCHOR NUTS (NIMBER AS REQ) - NAS680A3. POSITION AROUND PERIPHERY OF CUT- CUT-OUT IN S' MAKE ENDS SEMI-CIRCULAR.
9 ADJACENT RIB 10 ORIGINAL SKIN 11 ADJACENT STRINGERS 12 EXISTING STRAP ON ADJACENT STRINGER (WHERE APPLICABLE).
0 8/1/69 AC 20-64 ЛИАНАНАНИ FIGURE E-3.
UPPER SURFACE HORIZONTAL STABILIZER STRINGER IDENTIFICATION
STRINGER NUMBER STA * U. S. GOVERNMENT PRINTING OFFICE: 1980 O - 360-655 STRINGER LOWER SURFACE
NUMBER E SYMMETRICAL 1 STRINGER - .071 7075-76 CLAD, SEE 51-3-6, FIGURE 1 (SHEET 1) AND 51-3-7 ABOUT € OF AIRPLANE FIGURE 1 (SHEET 2 2 STRINGER - .050 7075-T6 CLAD, SEE 51-3-6, FIGURE 1 (SHEET 1) AND 51-3-7, FIGURE 1 (SHEET 2) 3 STRINGER - LS6658, SEE FIGURE 2 STRINGER - LS6778, SEE FIGURE 2 NOTE STRINGER - LS6777, SEE FIGURE 2 A. FOR LOCATION OF ALL RIBS, STRINGER - LS6659. SEE FIGURE 2 Appendix 5 SEE 55-0, FIGURE L. STRINGER - LS6796, SEE FIGURE 2 B. LETTERS INDICATE APPLICABLE REPAIR TYPE AS SHOWN ON 8 STIFFENER - .040 2024-4 CLAD, SEE 51-3-6, FIGURE 1 (SHEET 1) STIFFENER - LS6881 (TYPICAL EXCEPT AS SHOWN), SEE 51-3-6, FIGURE 1 Page 3 FIGURE 2. (SHEET 2) 10 STIFFENER - LS3505, SEE 51-3-6. FIGURE 1 (SHEET 2)
AC 20-64 CHG 1 10/26/73 Appendix 6 APPENDIX 6. MAINTENANCE NOTES FOR WING STRUCTURAL AREAS
1. INTRODUCTION. These maintenance notes have been compiled to assist L-188 series aircraft owners/operators in maintaining the wing of their airplanes for a long and useful service life. Summarized herein are structural areas of the wing which have shown need for special inspections and/or maintenance during the service history of the L-188 fleet. Types of discrepancies which may be found, the locations, and corrective action measures are listed. The purpose of this information is to acquaint maintenance planning personnel with specific areas of the wing which should be included in an overall wing inspection/ maintenance program.
This documentation has been assembled for reference usage and is not intended to replace nor be used in lieu of any maintenance/ inspection material or manual. Detail methods for inspections, maintenanc.
and repairs/reinforcements are contained in these existing documents and in the service bulletins referenced herein.
Direct assistance for your maintenance/inspection activities can be obtained by contacting the aircraft manufacturer.
2. SERIAL NUMBER (S/N) CODING FOR AIRCRAFT.
1001, 1002, 1004, thru 1148, 2001 thru 2022.
b. 1002, 1004 thru 1043, 1045 thru 1120, 2001 thru 2012.
c. 1001, 1002, 1004 thru 1056, 1058, (Right Wing Only), and 1059 thru 1069.
3. LOCKHEED STRUCTURAL SERVICE BULLETIN INDEX• 88/SB-334 - Wing - Wing Leading Edge Attaching Screws - Replacement Of 88/SB-564 - Wing - Inspection of Wing Plank Depressions 88/SB-587 - Wing - No. 4 Wing Plank - Inspection Of 88/SB-591 - Wing - Flap Track Attaching Bolts - Inspection Of 88/SB-593 - Wing - Main Landing Gear Actuating Cylinder Attach Fitting Intercostal - Inspection Of 88/SB-599 - Wing - Main Landing Gear Actuator Support Fittings - Inspection Of 88/ SB - 600 - Wing - Upper Skin Planks - Inspection and Repair Of 88/SB-616 - Wing - Upper & Lower Access Door Lands - Inspection Of 88/SB-619 - Wing - Upper Surface at W.S. 167 and W.S. 209 - Reinforcement 88/SB-620 - Wing - Wing Plank Splices Corrosion and Stress Corrosion Cracks - Inspection and Repair Of 88/SB-625 - Wing - Wing Plank Splices Aft of Main Landing Gear Fulcrum Fittings - Inspection Of 88/SB-628 - Wing - Corrosion of Wing Panels at Centroid Risers - Prevention Of 88/SB-631 - Wing - MLG Ribs - Inspection and Rework Of Par 1