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**** Hidden Message ***** <P>CONDITIONAL INSPECTIONS - GENERAL<BR>1. General<BR>A. This section contains the recommended checks and inspections which are dictated by special<BR>or unusual conditions. The following subjects identify the conditions and list the recommended<BR>checks and inspections. Procedures required for accomplishing specific checks or inspections<BR>are covered in the individual system or component subjects in the appropriate chapters of the<BR>manual.</P><P>OVERWEIGHT TAXI CONDITION - MAINTENANCE PRACTICES (CONDITIONAL INSPECTION)<BR>1. General<BR>Overweight Taxi:<BR>Taxiing at a weight that is more than the maximum-design-taxi-weight (MTW).<BR>Before flight, you must decrease airplane weight to that specified by the<BR>Airplane Flight Manual for takeoff.<BR>A. Inspection Criteria; An immediate structural inspection is necessary if you:<BR>(1) taxi the airplane overweight by more than 1/2% of the maximum-taxi-weight (MTW).<BR>(2) taxi the airplane overweight any weight over the Maximum Design Taxi Weight (MTW) and<BR>have any of these conditions:<BR>(a) High speed ground turn<BR>(b) Sharp radius turn<BR>(c) Heavy braking<BR>(d) Taxi over rough pavement<BR>(e) Pivoting (sharp radius turning with brakes on)<BR>B. The Inspections<BR>(1) The inspection is divided into Phase 1 and 2.<BR>(2) If the inspection for Phase 1 shows no signs of damage, the inspection is complete. If the<BR>Phase 1 inspection shows any sign of damage, the Phase 2 inspection must be done.<BR>(3) If the criteria for the above paragraphs 1.B.(1) or 1.B.(2) have not been met, no inspection<BR>is required, but you must decrease airplane weight to that specified by the Airplane Flight<BR>Manual before takeoff.<BR>C. Inspections, Repairs, and Replacements<BR>(1) When this procedure tells you to "examine" a part, look for these conditions:<BR>– cracks<BR>– structure that pulled apart<BR>– loose paint (paint flakes)<BR>– twisted parts (distortion)<BR>– bent parts<BR>– wrinkles or buckles in structure<BR>– fastener holes that became larger or longer<BR>– loose fasteners<BR>– missing fasteners (fasteners that have pulled out or are gone)<BR>– delaminations (a component with one or more layers pulled apart)<BR>– parts that are not aligned correctly<BR>– interference (clearance that is not sufficient between two parts)<BR>– discoloration (heat damage)<BR>– nicks or gouges<BR>– other signs of damage<BR>(2) Replace or repair the components that have one or more of the conditions given above.</P>
<P>2. Phase 1 Inspection<BR>A. Airplane Inspection<BR>(1) Main and Nose Landing Gear Inspection<BR>(a) Examine all tires and wheels.<BR>(b) Examine the support structure.<BR>(c) Look for signs of fluid leakage at the top and bottom of the outer cylinder of the shock<BR>strut.<BR>NOTE: A small quantity of hydraulic fluid on the surface of the inner cylinder of the<BR>shock strut is satisfactory.<BR>(2) Landing Gear, Fuselage, and Wing Inspection<BR>(a) Look for fuel leaks, and other fluid leaks, in the areas that follow:<BR>1) All wheel well areas of the main and nose landing gear.<BR>2) The lower external surface of the fuselage in the area of the wing-to-body<BR>fairing.<BR>3) The wing.<BR>3. Phase 2 Inspection<BR>A. References<BR>(1) 7-11-11, Jacking Airplane<BR>(2) 12-15-31, Main Gear Shock Strut - Servicing<BR>(3) 12-15-41, Nose Gear Shock Strut - Servicing<BR>(4) 32-11-0, Main Landing Gear<BR>(5) 32-11-21, Main Gear Shock Strut<BR>(6) 32-21-0, Nose Landing Gear<BR>(7) 32-21-11, Nose Gear Shock Strut<BR>(8) 32-32-0, Main Landing Gear Extension and Retraction<BR>(9) 32-33-0, Nose Landing Gear Extension and Retraction<BR>(10) 32-51-0, Nose Wheel Steering System<BR>B. Airplane Inspection<BR>(1) Main Landing Gear and Support Structure Inspection<BR>(a) Make sure the shock strut pressures are normal and the hydraulic fluids are at the<BR>correct levels (Ref 12-15-31).<BR>(b) Lift the airplane with jacks (Ref 7-11-11).<BR>(c) Examine the inner and outer cylinder lugs.<BR>(d) Examine all structural components of the main landing gear and carefully examine<BR>the components that follow:<BR>1) Shock strut<BR>2) Trunnion link<BR>3) Drag strut<BR>4) Torsion links<BR>5) Side strut<BR>6) Walking beam fitting of the shock strut<BR>7) Walking beam for the main gear actuator<BR>8) Linkage fittings of the walking beam and actuator<BR>9) The attach nut of the orifice support tube (signs of fluid leakage).<BR>10) Strut doors and the mechanism that retracts and extends the doors</P>
<P>(e) Examine the support structure of the main landing gear and carefully examine the<BR>components that follow:<BR>1) Landing gear beam<BR>2) Support fittings for the landing gear beam<BR>– Inboard<BR>– Outboard<BR>3) Trunnion support fittings and attachments<BR>– Forward<BR>– Aft<BR>4) Stabilizer link and fittings between the rear spar and landing gear beam.<BR>5) Body fitting for side strut and uplock attachment.<BR>(f) Examine all of the pin joints and fuse pin connections.<BR>(g) If you found tire damage in Phase 1, do the steps that follow:<BR>1) Remove and examine the wheel structure.<BR>2) Remove and examine the brake assembly.<BR>3) Examine the axles.<BR>(h) If one or more of the conditions that follow occurred, remove, disassemble, and<BR>examine all parts of the shock strut (Ref 32-11-21).<BR>1) The shock strut pressures were sufficiently low to cause damage.<BR>2) The hydraulic fluid levels were sufficiently low to cause damage.<BR>3) You found damage to one or more of the parts during your inspection of the<BR>landing gear.<BR>NOTE: Do not remove the orifice support tube to examine it.<BR>(i) Make sure the main landing gear retracts and extends correctly (Ref 32-32-0).<BR>(j) Lower the airplane from the jacks (Ref 7-11-1).<BR>(2) Nose Landing Gear and Support Structure Inspection<BR>(a) Make sure the shock strut pressures are normal and the hydraulic fluids are at the<BR>correct levels (Ref 12-15-41).<BR>(b) Lift the nose of the airplane with jacks (Ref 7-11-1).<BR>(c) If you found tire damage in Phase 1, do the steps that follow.<BR>1) Remove and examine the wheel structure.<BR>2) Examine the axle.<BR>(d) Examine all structural components of the nose landing gear and carefully examine<BR>the components that follow:<BR>1) Shock strut<BR>2) Torsion links<BR>3) Drag strut<BR>4) Lock links<BR>5) Drag brace link<BR>6) The attach nut of the orifice support tube (signs of fluid leakage).</P>
<P>(e) Examine the wheel well area and carefully examine the parts that follow:<BR>1) Web (the left and right side walls)<BR>2) Aft bulkhead<BR>3) Trunnion attachments<BR>4) Drag strut attachments<BR>(f) Examine the wheel well bulkheads and fuselage outboard of nose wheel well at<BR>(Body Stations 294.5 and 360).<BR>NOTE: You can do this inspection on the forward side through the access holes in<BR>the sidewalls of the nose wheel well. Examine the aft side of the bulkhead at<BR>Body Station 294.5 from the electronics compartment.<BR>(g) If one or more of the conditions that follow occurred; remove, disassemble, and<BR>examine all parts of the shock strut (Ref 32-21-11).<BR>1) The shock strut pressures were sufficiently low to cause damage.<BR>2) The hydraulic fluid levels were sufficiently low to cause damage.<BR>3) You found damage to one or more of the parts during your inspection of the<BR>landing gear.<BR>NOTE: Do not remove the orifice support tube to examine it.<BR>(h) Make sure that steering system is adjusted and operates correctly (Ref 32-51-0).<BR>(i) Make sure the nose landing gear retracts and extends correctly (Ref 32-33-0).<BR>(j) Lower the nose of the airplane from the jacks (Ref 7-11-11).<BR>(3) Fuselage Inspection<BR>NOTE: If you find external damage to the fuselage, always examine the adjacent internal<BR>structure.<BR>(a) Examine the lower fuselage structure.<BR>NOTE: Examine carefully in the area below the body crease from Body Station 727<BR>to 100 inches aft.<BR>(b) Examine carefully these components (Body Stations 540 through 727A):<BR>1) Keel beam chords<BR>2) Stiffeners<BR>3) Webs and splices<BR>(c) Also examine carefully the top of the fuselage between S-6 left and S-6 right (Body<BR>Stations 540, 664, and 727).</P> TIME LIMITS
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