5.3 5.4 5.41 5.42 5. 421 5. 422 5.423 capable of withstanding a torque which is 80 percent of the above without yielding to the point of impairing service operation. SEAPLANE FLOATS Main seaplane floats shall be approved for the design landing weight of the airplane. Approval of a float does not include approval of the structure attaching it to the aircraft, because such structure is approved as an integral part of the aircraft in which it is installed. Nor does it authorize its use on any approved airplane until performance and operation requirements are complied with on the particular aircraft involved. SKIS Skis, including ski pedestals, shall be approved for a maximum static load determined from the strength of the skis. Approval of a ski and its pedestal does not include approval of any special structure attaching it to the airplane. Nor does it include approval for installation on any improved [approved] airplane until performance and operation requirements are complied with on the particular aircraft involved. Strength. The strength of a ski, including its pedestal, its cables and lugs or mechanical trimming device shall be substantiated by a stress analysis or by static tests. Design Loads. A ski, including its pedestal, shall be capable of carrying the following loads without failure when supported at the pedestal bearing sleeve. Distributed Up Load. This load shall be applied to the ski bottom symmetrically with respect to the pedestal bearing sleeve in the fore and aft direction. The required design load "L" shall be equal to: (P)X(n)X(1.5) where P= the maximum static load in pounds (kg.) for which approval is requested Concentrated Up Load. This load shall be applied to the ski bottom directly under the pedestal bearing sleeve. The required test load is the same as the load used in Section 5.421. Distributed Side Load. A uniformly distributed side load shall be applied to the side of the ski runner, symmetrically disposed with respect to the pedestal bearing sleeve in the fore and aft direction. The required load shall be 35 percent of the load used in Section 5.421. When the pedestal height (the axle height from the ground with the ski installed) is 5.424 5.425 INCHES greater than the moment arm given in Fig. 5-1 for the static load for which approval is requested, such side load may be reduced by multiplying by the ratio of the moment arm given in Fig. 5-1 to the pedestal height. Concentrated Side Load. A concentrated side load shall be applied to the edge of the ski runner at a distance forward of the axle equal to three times the pedestal height, except that if the pedestal height is less than the moment arm given in Fig. 5-1 for the static load for which approval is requested, then the distance shall be three times the moment arm given in Fig. 5–1. Restraining Gear Loads. The restraining cable assemblies or other equivalent means used to maintain the ski attitude for all approved flight operations of the airplane on which the skis are installed, shall be designed to withstand ultimate CM 63.5 5.5 5.51 2000 4000 6000 8000 10000 12000 14000 FIG. 5-1 SKI DESIGN MOMENT ARM 16000-POUNDS 7250-KILOGRAMS loads equal to 1.25 times the maximum static ski reaction applied individually at the end of the flat portion of the nose and tail of the ski. The elastic means used shall be such as to keep the ski properly trimmed during the above specified flight operations. POSITION LIGHTS Position lights required for night operation shall meet the following requirements. Angular Definition. Three dihedral angles hereinafter referred to as dihedral angle L, dihedral angle R and dihedral angle A, shall be defined as follows: Dihedral angle L is formed by the intersection of two vertical planes, one passing through the fore and aft axis of the light unit and the other at an angle of 110° to the first, measured to the left when looking along the fore and aft axis of the unit; dihedral angle R is formed by the intersection of two vertical planes, one passing through the fore and aft axis of the light unit, and the other at an angle of 110° to the first, measured to the right when 5.52 5.521 looking along the fore and aft axis of the unit; and dihedral angle A (aft) is formed by the intersection of two vertical planes making dihedral angles of 90° to the left and 90° to the right, respectively, when facing aft of a vertical plane passing through the fore and aft axis of the light unit. Each dihedral angle shall be understood to include the bounding planes as well as the space between the planes. Classification. Position lights shall be separated into three categories according to their use and candlepower distribution. Forward Position Lights. Each forward position light shall have an intensity of not less than 3 candles in all directions in dihedral angle L for the left light and in dihedral angle R for the right light. Within these dihedral angles, respectively, the intensity in all directions shall equal or exceed the minimum values given in Table I according to the angle between the direction of measurement and forward axis of the unit. TABLE I Minimum Permissible Intensities in Any Plane Through the Within the same dihedral angles the intensities in the horizontal plane shall equal or exceed the minimum values given in Table II according to the angle between the direction of measurement and the forward axis of the unit. TABLE II Minimum Permissible Intensities in the Horizontal Plane In all directions in dihedral angle R for the left light and in dihedral angle L for the right light, a tolerance of 10° will be allowed in which the intensity of these lights shall be reduced to not over 10 candles. In these same directions a further tolerance of an additional 10° will be allowed in which the intensity of these lights shall be reduced to not over 10 candles. In all directions in dihedral angle A a tolerance of 10° will be allowed in which the intensity shall be reduced 5.522 5.523 to not more than 1 candle. In all directions outside the specified dihedral angle and the allowed tolerance angles for each unit, the stray light intensity shall not exceed 1 candle. Rear Position Lights. Rear position lights shall emit an alternate aviation red and aviation white flash repeated at a frequency of 40 cycles a minute. Each cycle shall have the following characteristics: 150° white-10° dark-150° red50° dark. The flasher shall be tested for the voltage range for which it is designed. The variation in frequency and the variation of the component parts of each cycle shall not exceed 10 percent throughout the voltage range for which the flasher was designed. Both white and red lights shall be fitted with 32 candlepower lamps. The red and white units of the light may be separate units spaced as closely as possible. Each color of light shall be completely visible in dihedral angle A. Each rear position light shall have an intensity of not less than 4 candles in dihedral angle A. Within this dihedral angle the intensity in all directions not exceeding 70° from the rear axis of the unit, shall be not less than 8 candles. Beyond the limits of dihedral angle A, a tolerance of 10° in all directions in dihedral angle L and in dihedral angle R will be allowed in which the intensity of this light must be reduced to a maximum stray light intensity of 1 candle. In all directions outside the specified dihedral angle and the allowed tolerance angles, the stray light intensity shall not exceed 1 candle. Alternate Non-Transport Category Rear Position Lights. -NUA These lights shall emit a continuous white light in all directions in dihedral angle A as specified in Section 5.522. 5.53 Color. All left forward position lights shall be aviation red, all right forward position lights shall be aviation green, and all rear position lights for non-air carrier aircraft shall be aviation white. These colors are defined as follows: (a) Aviation red is a color having the following International Commission on Illumination (ICI) chromaticity coordinates: y is not greater than 0.355, and z is not greater than 0.002 (b) Aviation green is a color having the following ICI chromaticity coordinates: x is not greater than 0.440-0.320 y x is not greater than y-0.170 and (c) Aviation white is a color having the following ICI chromaticity coordinates: x is not less than 0.350 x is not greater than 0.540 y-y, is not numerically greater than 0.01 yo being the y coordinate of the Planckian radiator for which X.-X. 5.6 5.61 5.611 5.612 5.613 5.62 5.7 5.71 5.711 5.712 5.713 5.8 5.81 5.811 LANDING LIGHTS Landing lights if required for night operation shall meet the following requirements. Classification. Landing lights shall be separated into three classes with regard to their candlepower. Class I (Spot). The candlepower shall not be less than 350,000 candles in all directions within 1.5° of the axis of the beam, except that, in the horizontal plane through the axis the candlepower shall not be less than 350,000 candles throughout a sector within 2° measured to the left and right of the axis of the beam. Class 2 (Flood). The candlepower shall not be less than 200,000 candles within 4° of the axis of the beam on a horizontal plane through that axis. Class 3 (Spot). The candlepower shall not be less than 150,000 candles in all directions within 1° of the axis of the beam, except that, in the horizontal plane through the axis the candlepower shall not be less than 150,000 throughout a sector within 1.5° measured to the left and right of the axis of the beam. Color. All landing lights shall be aviation white. PARACHUTE FLARES Parachute flares required for night operation shall meet the following requirements. Classification. Parachute flares shall be separated into three classes with regard to intensity, burning time and rate of descent. Class 1. Class 1 flares shall have a light duration of at least 3 minutes, a light intensity of at least 200,000 candles and a rate of descent not greater than 550 feet per minute (167.6 m/min.). Class 2. Class 2 flares shall have a light duration of at least 11⁄2 minutes, a light intensity of at least 110,000 candles and a rate of descent not greater than 550 feet per minute (167.6 m/min.). Class 3. Class 3 flares shall have a light duration of at least 1 minute, a light intensity of at least 70,000 candles and a rate of descent not greater than 550 feet per minute (167.6 m/min.). SAFETY BELTS Safety belts shall be capable of passing the following tests. Static Test. A safety belt for one person shall be capable of withstanding a static load of 1,000 pounds (454 kg.) and for two persons a static load of 2,000 pounds (907 kg.) applied to the fastened belt midway between the points of attachment, simulating the manner in which a person's weight would be applied in a crash. The quick release |
