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9450

RULES AND REGULATIONS

bulkheads. These inspections shall be con tion 6 to Station 13 which is hidden by the Fatigue cracks. Inspection periods and ducted at intervals specified and in the fo l wing skin attached to the chord i, e., chord locations.
Inspection required every 35
lowing manner :
face areas hidden by gusset plates used to hours of operation. Inspect the visible por A. SA-307B. In the inspection of 24SRT attach web members are excluded.
tions of all the wing spar 24SRT diagonal members in this model airplane, it is recom c
Inspection required annually. Inspecttube members, between Stations 1 and 30 on mended that the visual inspection proce by X -ray all inaccessible portions of 24SRT the front spar and between Stations 5 and dure outlined for Boeing Model 314 and spar chord members for their entire length. 23 on the rear spar, for fatigue cracks at A314 under A. D. 45-4-1 be followed. I f This inspection period may coincide with intervals not to exceed 35 hours flight time.
defects are located, they shall be reported to the inspection periods in paragraph b
Inspection procedures. Same as parts a the CAA for evaluation. Past experience has above.
and b of the inspection procedures for shown that once cracking starts, it may Inspection procedures. The required visual stress corrosion cracks.
progress at a rapid rate, thus requiring closer inspection for new or elongated cracks shall Identification and lim its. Fatigue types of inspections and corrective action. It shall be done in a manner satisfactory to th e Civil also be the operators responsibility to keep Aeronautics Administration. The following failures are denoted by fine hairline trans a record of all cracks on this model airplane. procedure is an acceptable method for mak verse cracking in the members. These cracks generally emanate from rivet holes under This record shall be revised periodically to ing these visual inspections:
gussets and progress transversely or diago show the status of existing cracks and to a Clean the surfaces of the members nally around the periphery of the tube.
record newly developed cracks. Copies of with a rag as necessary and closely examine the original report and all revised pages the members especially around gussets They may also originate from a longitudinal should be submitted to the CAA for exam with the naked eye. Direct a light on each crack, scratch or other stress-raising discon tinuity. In case fatigue cracks of any length ination.
member at varying angles so that no defects 1. Inspections of readily accessible areas. will be overlooked. Make certain to inspect are found, the defective member should be These inspections shall be conducted at in all sides of each member using a mirror where reinforced before flight is continued and upon arrival at the home base, the member should tervals not to exceed 150 horns of operation necessary.
be replaced. A proposed repair to take care or 90 days, whichever occurs first. This b Examine any suspicious indication o f this contingency should be submitted to inspection is intended to cover only those with a magnifying glass 10 power or over portions of 24SRT tubing that are accessible preferred. A crack will appear to have the Civil Aeronautics Administration for ap to visual inspection through available in jagged edges and considerable depth. A proval. I t shall also be the operators re spection panels, removal of gap strips and scratch will appear to have smooth edges and sponsibility to keep a record of ah the cracks on each airplane. This record shall be re the openings in the nacelles.
the bottom of the groove should be visible.
vised periodically to show the status of exist 2. Detailed inspections. These inspections c I f a new crack is found, the finish if will be conducted annually or at engine other than Roxalin Clear Primer should be ing cracks and to record newly developed overhaul periods, whichever occurs first. removed around the crack to facilitate in cracks. Copies of the original reports and all This inspection is required of all 24SRT spection. Extreme care should be exercised revised pages should be submitted to the tubing visible through all available inspec while stripping areas immediately adjacent Civil Aeronautics Administration for exami tion panels, removal o f gap strips, leading to gusset plates in order to prevent the strip nation.
edges, wing tips, stress plates and fuel tanks. ping solvent from entering the inaccessible 46-1-1 C essna Was Service Note 1 of The use of at least a 10 power glass will be regions between the gussets and members.
AD-722-5
required. To more thoroughly cover the The crack should be further inspected for Improper flap chain operation, character wing area, it w ill be necessary for a man corrosion and its length measured to the ized by jumpy chain action, may lead to the to crawl outboard in the wings as far as nearest Vie inch. The two ends of a stress chain jumping the idler and jamming. Im possible.
corrosion crack should be marked with a proper operation is probably due to incorrect B. SA307B1. A t intervals not to ex sharp indelible pencil, and Roxalin Clear chain tension or excessively worn sprockets ceed 850 hours of operation or 120 days, Primer No. 3200 brushed over the stripped or both. The chain tension can be checked whichever occurs first. I f defects are lo area.
at the flap screw inspection opening by press cated, they shall be repaired in a manner d Inspect known cracks for elongation ing the chains together at a point approxi satisfactory to the CAA.
by noting the pencil lines placed at the pre mately 4 inches inboard of the flap screw C. S-307. At intervals not to exceed 700 vious ends of each crack the same as for new sprocket. The distance between the chains should not be less than 4 nor more than %
hours of operation or 120 days, whichever cracks see c above.
The required X-ray inspections should be inches. The chain tension may be adjusted occurs first. I f defects are located, they shall done with suitable equipment and by a com by means of the adjustable arm or the idler.
be repaired in a manner satisfactory to the pany or personnel that have demonstrated to The sprockets are considered excessively CAA.
the Civil Aeronautics Administration that worn and should be replaced when the teeth 44- 52-1 B o eing Was Service Note 1 of their procedure will adequately show the con are one-half the thickness of the sprocket AD-558-1 and Service Note 1 of AD - dition o f the hidden faces of the chord web. In addition, the chain guard on the 524-1
members.
idler should be checked to make certain that Inspect immediately and every 250 hours Identification and lim its. Stress corro it has not been bent or worn through. In thereafter the outer wing panel 17SRT alu sion types of failures are denoted by longitu spect all chain links for cracks and replace minum alloy spar chord members for cracks. dinal fissures in the members. These cracks any links that are found cracked. I t is rec Unless special openings are installed, the may have a small transverse component. ommended that the chain be replaced every outer panels may have to be removed to They vary in length and, as time elapses, 1,000 hours.
Cessna Service Bulletin No.
permit thorough inspection. I f cracks are may run together or continue from one 100 dated July 13, 1945, covers this same found, the members should be repaired or rivet hole to another. I f stress-corrosion subject.
replaced in a manner satisfactory to the cracks are within certain lim its the airplane Was Service Note 2 of CAA. I f replacement 24ST tubing is in may be operated without reinforcing the a f 46-1-2 C essna AD-722-5
stalled no further inspection w ill be neces fected member; however, I f the magnitude, When airplane has been subjected to a sary. Boeing Service Bulletin No. 1 of D-6134 direction, or location of the crack is such describes a satisfactory method of installa as to violate any of the following provisions, hail storm, a careful inspection should be made fo r damage to plywood reinforcements tion of inspection openings in the lower the affected member shall be reinforced or surface of the outer wing. Boeing S. B. No. 2 replaced in a manner satisfactory to the under fabric covering, even when hail has not caused apparent damage. Cessna Serv o f D-6134 covers replacement of 17SRT spar Civil Aeronautics Administration.
ice Bulletin No. 101 dated July 19, 1945, also chords with 24ST spar chords.
1 No crack should be allowed to exceed covers this subject.
45- 4-1 B oeing Was Service Note 1 of eight inches in length. Diagonal or trans Was Service Note 7 of verse cracks should in no case extend trans 46-4-1 Culver AD-704-1
AD-730-2
The 24SRT aluminum alloy tubular mem versely in the member for a distance greater Inspect immediately and after every 100
than the largest rivet or bolt diameter in bers must be inspected for stress-corrosion hours of operation, the landing gear throttle and fatigue cracks by visual and X-ray the nearest fitting.
2 Cracks should not be allowed in joints, stop operation and mechanism for proper methods in accordance with the instruc Install placard Culver Dwg.
fittings, rivet holes, reduced sections, etc., clearance.
tions listed below:
Stress corrosion cracks. Inspection periods unless it can be determined that the a f 7132 Never unlock landing gear with throt and locations, a Inspection required every fected area is not critical or that adequate tle retarded below cruising setting. Culver 250 hours of operation or 60 days, which margins of safety exist to compensate for Service Memorandum No. 22 dated October 26, 1945, covers this same subject.
ever occurs first. Inspect the visible portion such cracks.
3 I f two or more parallel cracks exist o f all readily accessible aluminum alloy 46-4-2 C ulver Was Service Note 6 of ADin the same face, none should exceed six 24SRT members for cracks.
730-2 Applies only to Model LCA
inches in length.
b Inspection required every 750 hours o f having Stromberg Model NA-S3A1 car 4

I
f numerous small longitudinal cracks operation or 120 days, whichever occurs first.
buretors installed Inspect the visible faces o f all aluminum exist in one face of a member but are not When inspecting or replacing carburetor joined by diagonal or transverse cracks, the alloy 24SRT tubing structure for cracks.
float needle or needle seat, a check should In addition, inspect by X-ray the inaccessible length of the member so affected should not be made to assure that when a rubber .tipPec face of the spar chord members from Sta exceed twelve inches.
needle is used, a seat having rounded edges