Pago 234 AC 43.13-14 1972
- DATUM
- NO BAGGAGE
NO PASSENGERS
FULL OIL- - MINIMUM FUEL
- PILOT ONLY FORWARD C.G. LIMIT.
TO CHECK: MOST FORWARD WEIGHT AND BALANCE EXTREME.
GIVEN: Actual empty weight of the airplane - 1169# Empty weight center of gravity - +10.6'' *Maximum weight 2100# *Forward C,G. limit + 8,5" "Oil, capacity 8 qts. 17# at - 49 *Pilot in farthest forward seat equipped with controls (unless otherwise placarded) -- 170# at + 16" *Since the fuel tank is located to the rear of the forward C.G. limit, minimum fuel should be Included. 12 12 13,75 gal. × 64 83# at + 22" *Information should be obtained from the aircraft specification.
Note: Any items or passengers must be used if they are located ahead of the forward C.G. limit.
Full fuel must be used If the tank is located ahead of the forward C.G. limit.
CHECK OF FORWARD WEIGHT AND BALANCE EXTREME Weight (*) x Arm ("") Moment (P+) Aircraft Empty + 1169 + 10.6 + 12391 OIL + 17 - 49 B33 Pilot + 170 + 16 + 2720 Fuel 83 + 22 + 1828 Total + 1439 (TW) + 16104 (TM) Divide the TM (Total Moment) by the TW (Total Weight) to obtain the forward weight and balance extreme.
TM - 16190 = + 11.21 Since the forward C.G. limit and the maximum weight are not exceeded, the forward weight and balance extreme condition is satisfactory.
FIGURE 18.10.-Example of check of most forward weight and balance extreme.
Par 660 Chap 13
AC 49.13-1А Page 251 1972
WEIGHING POINT (C MAIN WHEEL) SCALE
WEIGHING POINT SCALE -→ (@ TAIL WHEEL)
WEIGHING POINT (& NOSE WHEEL) SCALE
- SCALE
WEIGHING POINT (JACKPAD) SCALE FOURE 19.8.-Weighing point centerline.
under the wheels of a iandplane, the keel of a seaplane float, or the skis of a skiplane. Other structural locations capable of supporting the aircraft, such as jack pads, may be used.
Clearly indicate these points in the weight and balance report.
f. Unless otherwise noted in the aircraft specification, drain the fuel system until the quantity indicator reads "zero" or empty with the Chap 13 aircraft in level flight attitude. The amount of fuel remaining in the tank, lines, and engine is termed "residual fuel" and it is to be included in the empty weight. In special cases, the aircraft may be weighed with full fuel in tanks provided a definite means of determining the exact weight of the fuel is available.
g. Unless otherwise noted in the aircraft specification, the oil system should be completely Par 658
AC 43.13-1A 1972
- DATUM
• EMPTY WEIGHT C.G.
OIL TANK 9QTS AT - 49" C.G. AS WEIGHED WITH OIL IS +9.7" WEIGHT OF AIRCRAFT WITH OIL IS 1186 LES.
EMPTY WEIGHT AND EMPTY WEIGHT CENTER OF GRAVITY (when aircraft is weighed with oil) GIVEN:
Aircraft as weighed with full oll-. 1186 lbs.
Center of gravity---- 9.718 Full oil capacity 9 qts. 17 ibs.
SOLVING:
Weight # × Arm" = Moment "# Aircrait as weighed + 1186 + 9.7 + 11504 Less oil 17 - 49.0 833 Total + 1169(A)| + 12337(B) Empty Weight (A) = 1169 pounds.
Empty Weight Center of Gravity B = 12337 = +10.6"1 1169 FIGURE 18.9 -Empty weight and empty weight center-of-gravity when aircraft is weighed with oil.
drained with all drain cocks open. Under these conditions, the amount of oil remaining in the oll tank, lines and engine is termed "residual oil," and it will be included in the empty weight. When weighed with full oil, actual empty weight equals the actual recorded weight less the weight of the oil in the oil tank (oil weight = oil capacity in gallons × 7.5 pounds). Indicate in all weight and balance reports whether weights include full oil or oil drained (see figure 18.9).
h. Do not set brakes while taking scale reading.
Par 65B Chap 13
Pago 237 AC 43.13-1A 1972 FIGURE 12.8.-Blade leading edge and trim tab.
Par 644 Chap 13
Page 238 AC 43.13-14 1972 FIGURE 12.9.-Blade bonding and crack location.
E A FIGURE 12.10.-Blade damage location.
Par 644 Chap 12
AC 43.13-1A Page 255 1972
• DATUM
• MAXIMUM BAGGAGE -MAXIMUM PASSENGERS FULL OIL → MAXIMUM FUEL PILOT ONLY - - REARWARD C.G. LIMIT TO CHECK: MOST REARWARD WEIGHT AND BALANCE EXTREME.
GIVEN: Actual empty weight of the airplane 1169# Empty weight center of gravity 10.6" *Maximum weight - 2100# *Rearward C.O. limit 21.9" *Oll capacity 9 ots. 17# at - 49" *Baggage, placarded do not exceed 100 ibs. 100# at + 75.5" *Two passengers in rear seats, 170 x 2 - 340# at + 48" *Pilot in most rearward seat equipped with controls (unless otherwise placarded) 170# at + 16" *Since the fuel tank is located aft of the rearward C.G. limit full fuel must be used --- 240# at + 22"
• Information should be obtained from the aircraft specification.
Note: If fuel tanks are located ahead of the rearward C.G. limit minimum fuel should be used.
CHECK OF REARWARD WEIGHT AND BALANCE EXTREME Weight (P) x Arm ("'). = Moment ("*) Aircraft empty + 1169 + 10,6 + 12391 17 49 833 Pilot (1) 170 + 18 2720 Passengers (2) + 340 + 48 + 16920 Fuel (40 gals.) + 240 + 22 + 5280 Baggage + 100 + 75.5 7650 Total + 2038 (TW) + 43428 (TM) Divide the TM (Total Moment) by the TW (Total Weight) to obtain the rearward weight and balance extreme. TH - 19428 2038 - + 31,9" Since the rearward C.G. limit and the maximum weight are not exceeded, the rearward woight and balance extreme condition is satisfactory.
FIGURE 18.11. -Example of check of most rearward weight and balance extreme.
Chap 13 Par 660
Lage 356 AC 43.13-14 1972
EXAMPLE OF THE DETERMINATION OF THE NUMBER OF
PASSENGERS AND BAGGAGE PERMISSIBLE WITH FULL FUEL GIVEN:
Actual empty weight of the aircraft 1168+ Empty weight center of gravity ---. 10.6" Maximum weight ------ 2100# Datum is leading edge of the wing Forward center of gravity limit -- Rearward center of gravity limit - 21.9" Oil capacity, 9 qts.; show full capacity 17# at -49" Baggage, maximum -- 100# at +75.5" Two passengers in rear seat, 170# x 2 - 340# at +48" Pilot in most rearward seat equipped with controls (unless otherwise placarded) 170# at + 16" Full fuel, 40 gals. × 6# -- 240# at + 22" Weight(*) × Arm (") = Moment("") Aircrait empty + 1168 + 10,6 + 12391 oil 17 - 49 833 Full fuel + 240 + 22 + 5280 Passengers, 2 rear + 340* + 48 + 16320 Pilot + 170 + 26 + 2720 Baggage + 100 + 75.5 + 7550 Total + 2036 (TW) + 43428(TM) Divide the TM (total moment) by the TW (total weight) to obtain the loaded center of gravity.
TM = 43428 = +21.3" TW 2036 The above computations show that with full fuel, 100 pounds of baggage and two passengers in the rear seat may be carried in this aircraft without exceeding either the maximum weight or the approved C.G. range.
This condition may be entered in the loading schedule as follows:
GALLONS NUMBER OF POUNDS OF
OF FUEL PASSENGERS BAGGAGE Full 2 Rear 100 * Only two passengers are listed to prevent the maximum weight of 2100 Ibs. from being exceeded.
Fiours 18.12. -Loading conditions: determinatlon of the number of passengers and baggage permissible with full fuel.
Par 660 Chap 13
AC 49.13-1A 1972 aircraft specification is exceeded. To make this check, the following information is needed:
(1) The weight, arms, and moments of empty aircraft;
(2) The maximum weights, arms, and moments of the items of useful load which are located aft of the rearward c.g. limit; and
(3) The minimum weights, arms, and moments of the items of useful load which are located ahead of the rearward c.g. limit.
A typical example of the computation necessary to make this check, using the above data, is shown in figure 18.11.
661, LOADING CONDITIONS AND/OR PLACARDS.
If the following items have not been covered in the weight and balance extreme condition checks, or are not covered by suitable placards in the aircraft, additional computations are necessary.
These computations should indicate the permissible distribution of fuel, passengers, and baggage which may be carried in the aircraft at any one time without exceeding either the maximum weight or c.g. range. The conditions to check are:
a. With full fuel, determine the number of passengers and baggage permissible.
b. With maximum passengers, determine the fuel and baggage permissible.
(1) Examples of the computations for the above items are given in figures 18.12, 13.13, and 13.14 respectively. The above cases are mainly applicable to the lighter type personal aircraft. In the case of the larger type transport aircraft, a variety of loading conditions is possible and it is necessary to have a loading schedule.
662. EQUIPMENT LIST. A list of the equipment included in the certificated empty weight may be found in either the approved Airplane Flight Manual or the weight and balance report. Enter in the weight and balance report all required, optional and special equipment installed in the aircraft at time of weighing and/or subsequent equipment changes.
Chap 13 Page 257
a. Required equipment items are items so listed in the pertinent aircraft specification.
b. Optional equipment items are so liated in the pertinent aircraft specification and may be installed in the aircraft at the option of the owner.
c. Special equipment is any item not corresponding exactly to the descriptive information in the aircraft specification. This includes such items as flares, instruments, ashtrays, radios, navigation lights, carpets, etc.
d. Required and optional equipment may be shown on the equipment list making reference to the pertinent item number listed in the applicable specification only when they are identical to that number item with reference to description, weight, and arm given in the specification.
Show all special equipment items by making reference to the item by name, make, model, weight, and arm. When the arm for such an item is not available, determine by actual measurement.
(1) Equipment Changes. The person making an equipment change is obligated to make an entry on the equipment list indicating items added, removed, or relocated with the date accomplished, and identify himself by name and certificate number in the aircraft records.
Examples of items so affected are the installation of extra fuel tanks, seats, or baggage compartments. Figure 18.15 illustrates the effect on balance when equipment items are added within the acceptable c.g. limits and fore and aft of the established c.g. limits. Moment computations for typical equipment changes are given in figure 18.16 and are also included in the sample weight and balance sheet in figure 18.18.
663. SAMPLE WEIGHT AND BALANCE REPORT.
Suggested methods of tabulating the various data and computations for determining the
c.g., both in the empty weight condition and fully loaded condition, are given in figures
18.17 and 19.18, respectively, and represent a suggested means of recording this information.
The data presented in figure 18.17 have previously been computed in figures 13.10 and Par 660
Page 258 AC 48.13-1A 1972
EXAMPLE OF THE DETERMINATION OF THE POUNDS OF FUEL
AND BAGGAGE PERMISSIBLE WITH MAXIMUM PASSENGERS Weight (#) x Arm () = Moment (*#) Aircraft empty + 1169 + 10.6 + 12391 Oil + 17 - 49 833 Pilot + 170 + 16 + 2720 Passenger, 1 front + 170 + 16 + 2720 Passengers, 2 rear 340 + 48 + 16320 Fuel (39 gals.) + 234 + 22 + 5148 Baggage - → Total + 2100 + 38466 Divide the TM (total moment) by the TW (total weight) to obtain the loaded center of gravity.
TM TW 38466 2100 = + 18.3" The above computations show that with the maximum number of passengers, 39 gallons of fuel and zero pounds of baggage may be carried in this aircraft without exceeding either the maximum weight or the approved C.G.
range.
This condition may be entered in the loading schedule as follows:
GALLONS NUMBER OF POUNDS OF
OF FUEL PASSENGERS BAGGAGE * FULL * 2 rear * 100 39 1(F) 2(R) None * Conditions as entered from Figure 13.12 (F) Front seat (R) Rear seat FIGuRE 18.13.-Loading conditions: determination of the fuel and baggage permissible with maximum passengers.
18.11 for the extreme load conditions, and figure 13.16 for equipment change and represent suggested means of recording this information.
664. INSTALLATION OF BALLAST. Ballast is sometimes permanently installed for c.g. balance Par 663 purposes as & result of installation or removal of equipment items and is not used to correct a nose-up or nose-down tendency of an aircraft.
It is usually located as far aft or as far forward as possible in order to bring the c.g. position within acceptable limits with a minimum of weight increase. Permanent ballast is often Chap 13
AC 43.13-1A Page 259 1972
EXAMPLE OF THE DETERMINATION OF THE FUEL AND THE NUMBER AND
LOCATION OF PASSENGERS PERMISSIBLE WITH MAXIMUM BAGGAGE Weight (*) ×Arm (") = Moment ("#) Aircrait empty + 1169 + 10.6 + 12391 Ou 17 • 49 833 Pilot + 170 + 16 + 2720 Passenger 1) rear + 170 48 + 8160 Passenger (L) front + 170 + 16 2720 Fuel (40 gals.) + 240 22 + 5280 Baggage + 100 + 75.5 7550 Total + 2036 + 37988 Divide the TM (total moment) by the TW (total weight) to obtain the loaded center of gravity.
IM = 92036 2036 = + 18.7 The above computations show that with maximum baggage, full fuel and 2 passengers (1 in the front seat and 1 in the rear seat) may be carried in this aircraft without exceeding either the maximum weight or the approved C.G. range.
This condition may be entered in the loading schedule as follows:
GALLONS OF FUEL NUMBER OF PASSENGERS POUNDS OF
BAGGAGE * Full * 2 Rear *100 ** 39 *1(F) 2(R) **None Ful 1(F) 1(R) Full * Conditions as entered from Figure 13.12 ** Conditions as entered from Figure 13.13 (F) Front seat (R) Rear seat FIGURE 18.14.-Loading conditions: determination of the fuel and the number and location of passengers permissible with maximum baggage.
Chap 13 Par 664
Page 260 AC 43.13-1A 1972
- WEIGHTS FORWARD C.G. LIMIT I REARWARD C.G. LIMIT Weights added anywhere between the C.G. limits will not upset the balance of the aircraft.
WEIGHT FORWARD C.G. LIMIT REARWARD C.G. LIMIT Any weights added ahead of the forward C.G. limit would tend to upset the balance around the forward balance limit.
WEIGHT FORWARD C.G. LIMIT -REARWARD C.G. LIMIT Any weights added aft of the rearward C.G. limit would tend to upset the balance around the rearward balance limit.
FIGURE 18.15.-Effects of the addition of equipment items on balance.
Par 664 Chap 13
AC 43.13-1A Pago 361 1972 Forward Rearward
- Moments (counterclockwise) + Moments (clockwise) Wheel pants added (+B# at -1'') Battery added (+29# at +13") Battery removed (-24# at -29") Landing light removed (-1# at +4") DATUM Weight () x Arm () = Moment "")) ADDED Item 204 wheel pants Item 302b Battery + 6 + 29 +13 - 1 +877 - 8
REMOVED Item 302a Battery - 24 -29 +896 Item 303 Landing light - 1 + 4 - 4 This condition is shown properly entered on a sample weight and balance report on Figure 13.18 under Equipment Change.
FIGURE 18.16.-Example of moment and weight changes resulting from equipment changes.
Chap 13 Par 664