FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 12 Appendix
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 500 Emergency exit doors Cracks None Visual (1) Cracks are located in to 600 the intercostal located immediately under the window. Cracks normally start in the angles.
F.S. 661 Passenger entrance Cracks/ (Ref: DSBs Visual (1) Moderate to heavy to 1194 door frames, skin, Corrosion 407 & 858) Dye Penetrant corrosion in the door floor, and buffet Removal of X-ray sill panel.
area buffet required for (2) Corrosion in the buffet thorough floor area can be severe.
inspection
(3) Frequent and close inspection of these areas recommended.
F.S. 661 Passenger entrance Cracks/ (Ref: DSBs Visual (1) Cracks are located at to 1194 door hinge case Corrosion 407 & 858) Dye Penetrant the front of the door frame.
(2) Fuselage skin cracks at the upper forward corner of the door hinge cutouts and both upper and lower hinges.
NOTE: Refer to the manufacturer's manual for repairs and modifications.
8/24/67 AC 20-52
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 661 Rear pressure bulk- Cracks Chonic Visual (1) Cracks are located in to 1194 head Dye Penetrant the stringers and attach X-ray fittings at the pressure bulkhead.
(2) Frequent and close attention should be given to this area.
F.S. 661 Tail cone area Corrosion Light/Medium Visual (1) This can be controlled to 1194 by cleaning treatment and painting.
(2) Blisters and flaking of paint are indicators.
F.S. 1030 Horizontal stabilizer Cracks None Visual (1) Cracks are located in to 1194 stub. (center section) X-ray the skin attach points to the front and rear spar.
F.S. 1030 Tail cone area Corrosion Light/Medium Visual (1) This can be controlled to 1194 by cleaning treatment and painting.
(2) Blisters and flaking of Page 13 Appendix paint are indicators.
F.S. 1030 Horizontal stabilizer Cracks None Visual (1) Cracks are located in to 1194 stub. (center section) X-ray the skin attach points to the front and rear spar.
EMPENNAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 14 Appendix
EMPENNAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS Sta. 70 Horizontal stabilizer Loose None Visual (1) Loose rivets located to 130 fasteners Dye Penetrant in the lower skin where (numerous) Magnifying it is attached to the Cracks glass front spar.
Sta. 30 Horizontal stabilizer Cracked Cracks are X-ray (1) Cracks are located in attach difficult the stabilizer attach fitting to locate. castings.
Critical
(2) Cracks usually start at the upper side of fitting which is covered by skin and progresses spanwise through the boltholes.
(3) Particular attention should be given to these fittings since the cracks do not progress from the outside where they could be detected visually or with dye penetrant.
NOTE: X-ray with steel bolts installed will result in blanking out defects in aluminum.
Corrosion is difficult to detect by X-ray if the particles remain intact in the metal.
8/24/67 AC 20-52
EMPENNAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
EMPENNAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS Sta. 126, Elevators Cracks None Visual (1) Cracks located at the 202, and hinge cutouts on the 252 elevator skin.
Rudder - torque tube Wear / None Visual (1) Excessive wear and Corrosion corrosion between the tube and the bearing seats.
(2) This can result in in-flight vibration due to looseness in the fits between the tube and bearing seats.
Sta. 937 Vertical stabilizers Cracks (Ref: DSBs 723| Visual (1) Cracks are located in to 1115 A796, and 796 X-ray the front fitting of the Dye Penetrant vertical stabilizer at the fuselage to vertical stabilizer attach point.
Sta. 959 Vertical stabilizer Cracks and (Ref: DSBs Visual (1) Cracks have been found to 986 loose bolts 723 A 796 and X-ray on the lower left side of in the 796) Dye Penetrant the vertical stabilizer.
nose section stabilizer (2) Particular attention Page 15 Appendix should be given to the metal cap after lightning strike report for burned areas.
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S.- Front upper spar cap Cracks (Ref. DSBs x-ray, (1) Particular attention should
0.-60 406 & 857) Visual, be given this area.
Internal Magnifying inspection glass (2) Crack length range up to 2" access door Dye Penetrant long.
W.S. Stringers, wing cen- Cracks Internal x-ray, (1) Cracks found along forward 0-60 ter section inspection Visual, or side of stringer.
access door Dye Penetrant W.S. Center spar cap Cracks Internal X-ray, (1)*Frequent and close attention 0 - 60 splices inspection Visual, or should be given this area.
access door Dye Penetrant (NOTE 1)
w.S. Front lower spar cap Cracks Internal Visual, (1) Routine inspection 32 forward tang (extend- inspection Dye Penetrant necessary.
ing thru fuselage) access door or X-ray W.S. Front lower spar cap Cracks Internal Visual, (1) Located at the bulkhead lap 32 aft tang (extending inspection Dye Penetrant to tang thru fuselage) access door or X-ray
(2) Particular attention should be given this area.
NOTE 1. * Cracks have developed exceeding limitations requiring spar replacement. This is a complex Page 1 Appendix 5 operation due to exacting fits, wing angle, and disassembly required.
• WING STATIONS - DC-6/7 AIRCRAFT INSPECTION Page 2 Appendix 5
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S. 32 Center lower spar cap Cracks None Visual, (1) Routine inspection forward tang (extend- Dye Penetrant, necessary.
ing thru fuselage) or x-ray W.S. Center lower spar cap Cracks Internal Visual, (1) Located at bulkhead lap 32 aft (extending thru inspection Dye Penetrant, to tang.
fuselage) access door or X-ray
(2) This area should receive frequent attention.
W.S. Wing stringers 17 & Cracks Internal Visual or (1) Cracks found along for- 32 26 at intersections inspection X-ray ward side of stringer.
with fuselage attach access door angles (2) Cracks located in forward line of rivets in spar cap.
W.S. Center upper spar cap Cracks None Visual or (1) Cracks located inboard 55 - 60 forward tang X-ray of attach angles.
(2) Place particular emphasis on this area.
W.S.
55 - 60 Center lower cap for- Cracks Internal Visual or (1) Cracks located in tang at ward tang inspection x-ray skin lap.
access doors
(2) This area should be NOTE: Refer to manufacturer repair manual and service bulletins for repair instructions. frequently inspected. 8/24/67 AC 20-52
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20 - 52
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S. Center upper spar Cracks None Visual or (1) Cracks located inboard of 55-60 cap aft tang X-ray attach angle.
(2) Place special emphasis on inspection of cap at longeron 22.
W.S. Center lower spar Cracks None Visual or (1) Cracks located in tang at 55-60 cap aft tang X-ray skin lap.
(2) Particular attention should be given this area.
W.S. Inboard end of flap Cracks Outside sur- Visual, (1) Cracks located along rivet 60 top nose section face inspec- Magnifying lines and difficult to skin tion glass locate.
W.S. Nos. 2 & 3 fuel tank Cracks Outside sur- Visual, (1) Crack location - radius 60 access doors and popped face inspec- Magnifying of cutouts and skin.
tion glass
(2) Routine inspection necessary.
W.S. Upper wing to fuse- Cracks Internal Visual, (1) Crack location - cracks in 60 lage attach angles inspection Dye Pene- boltholes.
access door trant, X-ray
(2) Frequen (2) Frequent inspections should Page 3 Appendix 5 be accomplished in this area.
NOTE: Refer to manufacturer repair manual and service bulletins for repair instructions.
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 4 Appendix 5
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S. Front lower spar cap Cracks Internal Visual or (1) Crack location - 60 aft tang boltholes inspection X-ray horizontally between tang access door and spar cap.
(2) DSBs A678, 678, and 694 apply.
W.S. Front lower spar cap Cracks Internal Visual or (1) Cracks located at skin lap 60 - 65 aft tang inspection X-ray in tang.
access doors
(2) Routine inspection necessary.
W.S. Front lower spar cap Cracks Internal Visual or (1) Cracks located horizontally 60 - 65 forward tang inspection X-ray between tang and spar cap.
access doors
(2) Frequent inspection should be made of this area.
W.S. Wing stringer 22 Cracks Internal Visual or (1) Cracks located forward 67 inboard and outboard inspection X-ray row of rivets.
of this station access doors
(2) Close and frequent inspection necessary.
W.S. Wing stringer 23 Cracks Internal Visual or (1) Cracks start in forward 67 inboard and outboard of this station inspection access doors X-ray row of rivets. 8/24/67 AC 20-52
(2) DSB issued on this area.
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS
w.S. Stringers at splices Cracks Internal Visual or (1) Refer to DSB 561.
60 on lower wing plate inspection X-ray access doors (2) Cracks start in forward row of rivets.
W.S. Stringers 17, 18, 19, Cracks (Ref: DSBs Visual or (1) Cracks have been found in 60 - 20, and 21 406 & 857) X-ray both forward and rear rivet 130 holes.
(2) Particular attention should be given this area.
W.S. Stringers 18, 19, Fatigue Internal Visual (1) Crack location - forward 96 and 20 Cracks inspection X-ray row of rivets.
access door
(2) Reference DSB 561.
w.S. Center spar web Cracks (Ref: DSBs (1) Cracks located vertically 77 - 96 inside wing fuel cell ( Some 406 & 857) Magnifying along web stiffener.
cavity cases 5" glass to 6" Dye Penetrant (2) Full ce11 liners must be long) removed for access to this W.S. Upper and lower spar Cracks Access Visual (1) Cracks radiate horizontally Page 5 Appendix 5 133 - caps in corner of (fuel between land- Dye Penetrant from rivet holes.
163 nacelle spar area stains are ing gear, X-ray telltale drag strut, (2) Particular attention should signs) and main gear be given this area.
strut
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 6 Appendix 5
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S. Top wing skin under Corrosion/ Area suscep- Visual (1) Reference DSB 762.
130 - nacelle fairing wing Cracks tible to 167 engine (2) This can be controlled by exhaust, cleaning treatment and gases, and painting.
vibration (Ref: DSBs (3) Blisters and flakes of 406 & 857) paint are indicators.
W.S. Center lower spar cap Cracks Internal Visual or (1) Cracks radiate from bolt- 122 aft tang at three inspection X-ray holes.
boltholes access door
(2) Routine inspection necessary.
W.S. Center lower spar cap Cracks Internal Visual or (1) Cracks radiate 171 aft tang at three inspection X-ray horizontally, length of boltholes access door crack up to 3".
W.S. Center lower spar cap Cracks Internal Visual or (1) Crack location - forward
114.5 and wing skin from inspection X-ray line of rivets.
inboard side of No. 2 access door nacelle inboard to this W.S.
w.S. Center lower spar caps Cracks Internal Visual or (1) Crack location - forward 148 and wing skin from inspection X-ray and aft row of rivets.
outboard side of No. access door nacelle outboard to (2) Cracks found in skin 8/24/67 AC. 20-52 this W.S. under spar.
NOTE: Refer to manufacturer's manual and service bulletins for crack repair and corrosion treatment.
WING STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
WING DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS W.S. Center lower spar caps Cracks Internal Visual or (1) Crack length varies up to
114.5 and wing skin from inspection X-ray 2" - 3".
inboard side of No. 3 access door nacelle inboard to (2) Usually located on front this W.S. line of rivets.
W.S. Center lower spar Cracks Internal Visual or (1) Crack location - forward 148 caps and wing skin inspection X-ray and aft line of rivets.
from outboard side of access door No. 3 nacelle out - (2) Routine inspection board of this W.S. necessary.
W.S. Nos. 2 and 3 nacelle Cracks/ Internal Visual or (1) Moderate to severe 131 lower wing skin Corrosion inspection X-ray corrosion.
inboard of W.S. 167 access door outboard W.S. 131 (2) Cracks radiating from rivet holes.:
NOTE: Refer to manufacturer's manual and service bulletins for crack repair and corrosion treatment.
Page 7 Appendix 5