W&B

• factors in the safe and efficient operation of aircraft:

  • proper weight and balance control
• The weight and balance system commonly employed among aircraft consists of three equally important elements:

  • weighing the aircraft
  • maintaining weight and balance records
  • proper loading of the aircraft
• Improper loading - it decreases the efficiency and performance of an aircraft from the standpoint of altitude, maneuverability, rate of climb, and speed
• State Of-The-Art Technology and Materials - modern aircraft are engineered utilizing this to achieve maximum reliability and performance for the intended category
• Responsibility for weight and balance control:

  1. Designers
  2. Manufacturer
  3. Certificated Mechanic/ Repairman
  4. Pilot in Command (PIC)
• Weight - a major factor in airplane construction and operation, and it demands respect from all pilots and particular diligence by all maintenance personnel
• Wings or Rotors - designed to support the maximum allowable weight
• CFR - Code of Federal Regulations
• In accordance with title 14 of the code of federal regulations (14 cfr) part 23, the structure of a normal category airplane must be strong enough to sustain a load factor of 3.8 times its weight. an aircraft operated in the utility category must sustain a load factor of 4.4 times its weight, and acrobatic category aircraft must be strong enough to withstand 6.0 times their weight
• Structure Category of Aircraft:

  • Normal Category
  • Utility Category
  • Acrobatic Category
• Overloading an aircraft can create a variety of problems:

  -          (B.t.R.a.A.o.C.a.R) both the rate and angle of climb are reduced

  -          (T.S.C.i.L) the service ceiling is lowered

  -          (T.C.S.i.R) the cruising speed is reduced

  -          (T.C.R.i.S) the cruising range is shortened

  -          (M.i.D) maneuverability is decreased
• Effects on an overloaded aircraft:

  1. (N.L.R.f.T.O.o.L) Needs longer runway for take off or Landing
  2. (A.C.A.w.b.L.a.H.S.i.N) Aircraft climb angle will be lower and higher speed is necessary
  3. (S.S.F.m.J) Structural safety factors may jeopardize
  4. (A.S.m.O) Aircraft stall may occur
  5. (A.H.R.o.E.P) A higher requirements of engine power
• Effects on an aircraft with too much weight forward:

  1. (A.M.D.F.S) Aircraft might dive forward suddenly
  2. (T.S.o.A.i.D) The stableness of aircraft is decreasing
  3. (A.S.m.O) Adverse spin may occur
  4. (N.a.H.R.o.E.P) Needs a higher requirements of engine power
• Effects on an aircraft with too much weight aft:

  1. (F.S.i.D) Flying speed is decreasing
  2. (S.C.m.O) Stall characteristic may occur
  3. (T.S.i.D) The Stableness is decreasing
  4. (M.E.P.i.R) More engine power is required
  5. (A.S.C.o) Adverse spin character occurs
• Two elements are vital in the weight and balance considerations of an aircraft:

  • The total weight of the aircraft
  • The center of gravity
• total weight of the aircraft - must be no greater than the maximum weight allowed by the FAA for the make and model of the aircraft
• Center of Gravity (CG) - the point at which all of the weight of the aircraft is considered to be concentrated, must be maintained within the allowable range for the operational weight of the aircraft
• Arm - usually measured and expressed in inches and refers to the horizontal distance between the CG of an item or object
• Datum - a point from where all measurements are taken. Arms to the left of the datum are negative (–) and those to the right of the datum are positive (+)
• Datum - an imaginary vertical plane from which all horizontal distances are measured for balance purposes
• Typical Datum Location

  1. Firewall Datum
  2. Leading Edge
  3. Nose
  4. Forward of the nose
  5. Other location
• Moment - a force that tries to cause rotation and is the product of the arm, in inches, and the weight, in pounds
• Primary source of data investigation.

  1. FAA
  2. Aircraft Manufacturer
• Aircraft data sheets will include important information such as:

  1. CG Range/Limits
  2. Empty Weight CG Range (EWCG)
  3. Maximum Weights
  4. Number of Seats
  5. Maximum Baggage
  6. Fuel Capacity
  7. Oil Capacity (Wet Sump)
• Maximum landing weight - it is the greatest amount of lift approved during landing
• Maximum permissible hoist load - the maximum external load that is permitted for a helicopter to carry
• Maximum ramp weight -the maximum weight approved during ground maneuver
• Maximum takeoff weight - the greatest amount of weight approved during takeoff run
• Maximum taxi weight - the allowable amount of weight used for ground maneuvers
• Maximum weight - the maximum authorized weight of the aircraft and all of its equipment as specified in the Type Certificate Data Sheets (TCDS) for the aircraft
• TCDS - Type Certificate Data Sheets
• Maximum zero fuel weight - the maximum weight of an aircraft minus fuel
• TYPE OF MAXIMUM WEIGHTS:

  1. Maximum landing weight
  2. Maximum permissible hoist load
  3. Maximum ramp weight
  4. Maximum takeoff weight
  5. Maximum taxi weight
  6. Maximum weight
  7. Maximum zero fuel weight