Page 24 AC 20-64 8/1/69 Pilot reported No. 3 engine vibration indication at and above 220 knots. The vibration was also noticeable by slight buzzing of the power lever on the ground. During cruise, a definite vibration was experienced in the ailerons, elevators, and rudder. The engine vibration was pronounced above 800 degrees engine tailpipe temperature. Inspection of the control surfaces revealed rudder rib damage requiring reinforcement.
The rudder was replaced. Total time on the airframe was 15,949 flight hours.
d. Main Landing Gears,
(1) During overhaul inspection two 3/4-inch cracks were found at the top of the left main landing gear inboard truss rib tabs at wing station 167. The cracks originated from the tab cutouts extending downward and aft toward the truss cap between risers Nos. 16, 17, 18, and 19 of the No. 3 upper wing plank. Total time on the aircraft was 21,734 flight hours.
During inspection, the left main landing gear door actuator fitting, P/N 802058-1, was found broken. The mounting bolt was holding the fitting in place. There were 857 landings since the last removal of the door actuator. Total time on the aircraft was 20,268 flight hours.
During a dye penetrant inspection, a 1/2-inch crack was detected on the left main landing gear actuator support fitting, P/N 841275-101. The crack was located aft of the outboard hole.
Total time on the aircraft was 14,356 flight hours.
e • Corrosion.
During inspection, exfoliation corrosion was found on the left fuselage longeron, P/N 897596-1, between fuselage stations
474.5 and 484.5. Total time on the aircraft was 20,740 flight hours.
During a main base check inspection, corrosion was found in several spots on the aft cargo door fuselage doubler. The bottom edge of the aft cargo door sill is covered by a stainless steel striker plate. Total time on the aircraft was 17,721 flight hours.
(3) Heavy corrosion was found on the floor beams at fuselage stations 333 and 371. Total time on the aircraft was 21,520 flight hours.
Par 29 Chap T
AC 20-64 Page 25 (and 26) 8/1/69
(4) Three separately corroded areas were found on the left upper wing at station 65. The corroded areas were .030 inch deep and 1/2 inch in diameter around the fuselage-fillet-to-wing attach fasteners at wing planks Nos. 1, 6, and 7. Total time on the aircraft was 23,315 flight hours.
During scheduled inspection, corrosion was found on the lower wing surface. The corrosion occurred under the fuselage-towing fillet chafe strip at numbers 4, 5, and 6 wing planks.
Four spots of corrosion were found measuring .011 inch, .024 inch, .024 inch, and .013 inch. The areas were treated and and filled with epoxy filler before installing repaired doublers. Total time on the aircraft was 21,715 flight hours.
(6) Corrosion was found on the lower section of the captain's sliding window frame. Total time on the aircraft was 21,620 flight hours.
(7) During inspection, an area of approximately 12 inches by 6 inches on the outside skin at stringer No. 30 and fuselage stations 500 to 549 was found to be corroded beyond limits.
Also, two small areas approximately 1 inch square were found corroded at stringer 22, fuselage stations 685 and 690. Total time on the aircraft was 24,649 flight hours.
Miscellaneous.
(1) An unscheduled landing was made as a precautionary measure due to in-flight cracking of the first officer's windshield. The windshield heat was in the low position. The aircraft was ferried to Buffalo, where the windshield was replaced. Flight time since the last inspection was 17 hours. Total time on the aircraft was 19,644 flight hours.
(2) The No. 4 oil cooler flap door was found cracked at the door actuator attach bracket. The crack was approximately one-half inch in length and progressed out of a screw hole toward the door hinge. The oil cooler flap door, P/N 836505-9, was replaced. Total time on the aircraft was 14,286 flight hours.
(3) During ground inspection, the No. 4 propeller oil access door, /N 811567-11, was found excessively worn. The wear allowed the upper hinge end of the door to protrude sufficiently to be caught by the propeller blade cuff and be torn free. The aircraft was ferried to its main base, where the propeller cowl panel, P/N 813395-27, was replaced and the propeller cuff repaired.
Chap T Par 29
AC 20-64 Appendix 1 8/1/69 Page 1 FIGURE A-1. BASIC DIMENSIONS
ELEVATOR HINGE O% CHORI BUTT LINE
357.03 29 FT 1 IN.
SUIT FWD FACE FRONT LINE BEAM: 19.11% CHORD •
186.97 42 FT 10 IN.
29 FT 7 IN.
• 4 FT 7 5 IN AFT FACE FRONT BEAM: 15% CHORD 7 FT 7 IN.
FWD FACE REAR BEAM: 58,56% CHORD & RUDDER HINGE:
& AILERON HINGE: 72.5% CHORD 70% CHORD
WATER LINE FUS - 415.0 STA
571.19 17 FT 4 IN 32 FT .10.5 IN.
WATER LINE 150.00 .000 g000 000. 000 10° 5F5 IN 8FT 5 IN - FLOOR 8 FT 1 IN WATER LINE
- 5 FT 1 IN. 1 FT 9 IN. 123.94 37 FT O IN 104 FT 8 IN
42.00 STA FUS 177.00 FUS STA 621.00 FUS STA STATIC GROUND 195,000 LBS WITH C.G. @ 25% M. A.C.)
11 FT 4 IN. MAX DIA
- 3 FT 3.7 IN. CLEARANCE 13 FT 6 IN
• WING REFERENCE PLANE
- &7 IN.
31 FT 2 IN CLEARANCE 99 FT 0 IN. -
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