FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 4 Skin, framing, pres- Cracks Access for Visual (1) This area should receive sure bulkhead flanges inspection Dye Penetrant frequent inspection.
at the windshield "V" through nose wheel well F.S. 18 Slant panel attach Loose Internal Visual (1) Particular attention points at the tra- fastener inspection Magnifying should be given to this verse beam - cockpit cracks/ from cockpit glass area.
area corrosion area
(2) The stiffener angles crack in the attach holes F.S. 18.
F.S. 41 Fuselage skin under Numerous Outside sur- Visual (1) Cracks are located along to 58 the pilot/copilot cracks face (Ref: the rivet lines and are window DSBS 407 & difficult to detect.
858) Produc- Bulkhead, including Cracks, Remove cock- Visual (1) Cracks are located in the tion the surrounding skin 1oose pit sound- 10-power upper skin/frame areas and Break fasteners proofing glass develop- the lower frame fittings.
F.S. 69 paneling ment
(2) Special repairs have been developed for this area.
Page 1 Appendix
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 2 Appendix 4
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 4 Cockpit area - floor Cracks/. Floor removed Visual (1) Check for corrugation to 69 boards Corrosion cracks.
(2)*Check floor beams, frames stringers. (NOTE 1) F.S. 41. Nosewheel well. Nose Loose and None Visual (1) Check for black residue to 69 gear trunnion working around inner face of fitfastener ting and the rivets.
cracks
(2) Looseness of the trunnion fitting may result in nose gear shimmy.
F.S. 69 Battery box cutouts, Cracks/ Internal Visual (1) Indications of corrosion skin and lap joints Corrosion inspection of can be found along (internal/external) the frames edges of the skin lap, and stringers rivets along with pitted surfaces, blisters.
(2) Frequent cleaning treatment and protection necessary.
F.S. 69 Production joint Cracks Visual (1) Crack location in metal attach angle adjacent and inline with crew door.
NOTE: Refer to Douglas Service Bulletins 407 and 858 for additional information.
NOTE 1. * Close and frequent attention should be given to the under floor cleanliness of the cockpit area.
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOL F.S. 69 Crew door Rigging Critical Visual (1) Particular attention to 134 should be given to rigging of bayonets and rollers.
(2) Improper rigging results in excessive wear, cracks, and pressurization leaks.
F.S. 69 Front crew door Cracks/ Remove fuse- Dye Penetrant (1) Critical Area - Cracks to 134 frame, and door Corrosion lage around Visual are located in the aft hinges door frame section, upper section down midway of door.
Most critical point is located between stringer Nos. 10 and 11 approximately to 17" from floor line. Also, cracks occur in a lower corner of door sil1. Area prone to severe corrosion.
F.S. 69 Front crew door hinge Cracks None Visual (1) Crack location - hinge to 134 case 10-power line. Area should receive glass, Dye Penetrant tion. close and frequent atten- Page 3 Appendix 4
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 4 Appendix
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 69 Intercostals below Cracks/ (Ref: DSBs Visual and/or (1) Close and frequent to 134 crew door Corrosion 407 & 858) as required attention should be given to this area.
F.S. 69 Crew door Cracks/ None Visual (1) *Cracks start in the to 134 wear bayonet cutouts in the door intercostals.
(NOTE 1) F.S. 69 Crew entrance door Cracks Remove lining Visual (1) Crack location No. 1 to 134 jamb above door Dye Penetrant upper forward and No. 2 and X-ray upper aft latch cutouts.
(2) Close and frequent inspections.
F.S. 89. Stringer No. 31 left Cracks/ (Ref: DSBs 407 X-ray and/or (1) Frequent and close to 100 and right side- Corrosion & 858) as required attention should be fuselage given to this area.
F.S. 101 Nosewheel well Cracks/ Thorough Visual (1) Crack location - aft to 118 tunnel Corrosion cleaning lower corners.
prior to inspection NOTE: NOTE 1.* Typical repair instructions may be found in the Rigging of the crew door bayonets and rollers is manufacturer's manual. critical. Improper rigging results in 8/24/67 AC 20-52 excessive wear, cracks and pressurization leaks.
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS 8/24/67 AC 20-52
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 69 Fuselage skin, Corrosion Access to Visual (1) Corrosion located inner to 400 longerons, frames internal/ area through X-ray and outer sides of fuselage (belly) external front lower skin longerons, frames, and baggage bin skin laps.
(2) White deposits on edges of skin laps, around rivets, blisters in paint, pits are indications.
(3) Frequent cleaning and treatment necessary.
F.S. 134 Cargo door hinge Cracks None Visual (1) Crack location - radius to 179 cutouts of the cutouts and skin panel.
(2) Routine inspection necessary.
F.S. 149 Stringers Nos. 28 Cracks Internal/ Visual and 31 and frames external (Ref; X-ray DSBS 407 & Dye Penetrant (1) Cracks 2 to 7 inches
858) found along right side
(2) Cracks are located in stringer. Page 5 Appendix bottom row of rivet in the skin cap.
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 6 Appendix 4
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 178 Fuselage skin lap - Corrosion (Ref: DSBs Visual and/or (1) Located at the skin lap to 260 longeron No. 26 Loose fas- 407 & 858) as required just below the forward teners water tank service panel.
(2) Particular attention should be given to this area.
F.S. 186 Fuselage skin lap - Corrosion None Visual and/or (1) Severe corrosion in this longeron No. 31 X-ray area.
(2) Particular attention should be given to this area.
F.S. 178 Lavatory floor and Corrosion (Ref: DSBs Visual (1) Corrosion located in the to 260 floor beams 407 & 858) floor and floor beams.
Critical Heavy especially around the sink area. (NOTE 1)
(2) Inspection can be made from the forward lower baggage bins.
(3) Popped rivets and paint blisters are. external indicators.
NOTE: NOTE 1: * Typical repairs and modifications may be found in the manufacturer's manual. Particular attention should be given to inspection of magnesium floor beams. 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. 178 Butt joint - hydraulic Corrosion (Ref: DSBs Visual (1)*This condition is due to to 260 compartment 407 & 858) spillage from the Critical lavatories. (NOTE 1)
(2)*Close and frequent inspection should be made in this area.
F.S. 241 Fuselage skin lap Cracks/ Area covered X-ray (1) Frequent inspections to 280 stringers Nos. 19 Corrosion by ice plates Visual should be accomplished through 23 crushed (Ref: DSBs in this area.
frames 407 & 858) F.S. 261 Fuselage frames Crushed Remove bag- Visual (1) None to 280 cargo bin fuse lage gage bin frames / floor and cracks lining F.S. 301 Fuselage - skin lap Corrosion None Visual (1) Corrosion located in the (Ref: DSBs faying surfaces of the 407 & 858) skin lap approximately 17" above the top of the first cabin window.
(2) Popped rivets, paint blisters, pitted areas Page 7 Appendix 4 indicators.
NOTE: Particular attention should be given to inspection of magnesium floor beams.
NOTE 1: * Typical repairs and modifications may be found in the manufacturer's manual.
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 8 Appendix 4
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 341 Fuselage skin lap Corrosion None Visual (1) Severe corrosion along stringer No. 26 X-ray located in the skin laps.
F.S. 358 Fuselage skin, longe- Corrosion/ None Visual (1) Corrosion located just to 391 ron frames Cracks X-ray below the cabin window.
(2) Area should receive frequent attention.
F.S. 400 Fuselage skin Cracks/ Access throughVisual (1) Cracks located in skin to 417 Corrosion wing fillet X-ray above the front spar cap inspection and along the floor line.
plates.
Remove fillet (2) Loose and popped rivets, for thorough paint and metal blisters inspection. are indicators of this (Ref: DSBs condition.
407 & 858) F.S. 400 Fuselage skin lap - Corrosion (Ref: DSBs Visual (1) Corrosion extended over to 512 stringer No. 19 407 & 858) X-ray a 2-inch wide strip along stringer No. 19.
(2) Corrosion around and under the lower hinge fitting of the forward
448. emergency exit at F.S. 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. 500 Fuselage skin Cracks (Ref: DSB Visual (1) Cracks are located in the
652) X-ray fastener holes in the Dye Penetrant fuselage skin at the wing to fuselage attach angle.
(2) Cracks also found in fuselage skin above rear spar.
F.S. 448 Fuselage longitudinal Cracks Visual (1) Cracks located in the to 500 skin lap skin lap above the first and second cabin windows right side.
(2) Crack length range up to 2" long.
F.S. 280 Cabin floor structure Cracks Inspect all Visual (1) Place particular emphasis to 600 and supports exposed on inspection of fuselage, structure. frames 413, 421, 460, and Remove sound- 500.
proofing as necessary for (2) Ref. to DSB 567 for access to information concerning front and floor to frame bracket.
rear spars. Page 9 Appendix (Ref: DSB (3) Ref. DSB 611 and 651 for 4& 567) inspection of attach "tee" fittings.
FUSELAGE STATIONS - DC-6/7 AIRCRAFT INSPECTIONS Page 10 Appendix 4
FUSELAGE DESCRIPTION INSPECT COMMENTS INSPECTION REMARKS
STATION FOR TOOLS F.S. 280 Emergency exit Cracks (Ref: DSBs Visual (1) Cracks are located in to 600 cutouts 407 & 858) the radius of the cutouts.
(2) A service bulletin was issued covering this area.
(3) Frequent attention should be given to this area.
F.S. 280 Window frames Corrosion Visual (1) Intergrannular corrosion to 600 located in the lower corner of No. 8 window.
(2) Popped rivets, blisters in the skin, and paint are indicators.
(3) Check for presence of moisture in the insulation material. Ref.
DSB 840.
NOTE: Refer to the manufacturer's manual and service bulletins for necessary repairs.
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. 280 Lavatory window Corrosion (Ref: DSBs Visual (1) Corrosion can found to 600 407 & 858) between the fuselage skin and doubler at the lower edge of the cutout.
(2) Corrosion can become severe. Particular attention should be given to this area.
(3) Evidence of moisture in the insulating material should be checked.
F.S. 500 Heater compartment, Corrosion/ If blankets Visual (1) Cracks are located in to 600 frames, longerons, Cracks are instal- the frames and longerons.
floor beams 1ed, check for moisture (2) Moderate to severe (Ref: DSB corrosion in the floor
520) beams.
F.S. 500 Heater exhaust area - Cracks/ Visual (1) Cracks and damage results to 600 longeron 24 Exhaust from high heat exhaust damage temperatures.
(2) Modifications have been Page 11 Appendix developed.