5 ATTENT. FLIG. PER. EXAM. PREP.

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231 Calculate the Centre of Gravity and total weight "mass", given the following conditions.
MASS LEVER ARM MOM/1000
BEM 2122 lb 35.76 _
Pilot & Copilot 340 lb 37.0 12.6
Centre row seat _ lb 70.0 23.8
Aft row seat 340 lb _ 34.0
Bagg. Compartment 104 lb 126.9 _
Aft Bagg. Area _ _ _
Fuels (55USG) _ 48.0 17.0

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232 Four on board. Investigate using tables in Fig. 33, the total moments (/100) and if within limits?

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233 After new equipment installed on aeroplane, as in technical certificate shown in Fig. 34, what's the Basic Empty Mass and total moments(/100)?

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239 If air density is increased above ISA conditions, the take-off distance required at full throttle compared with that for standard conditions will be:

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241 What is the maximum zero fuel mass ?

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242 TORA is the:

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248 Which of the following items are included in the Dry Operating Mass?

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251 The maximum range in a glide path will be achieved by:

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253 If the aircraft C of G is on the forward centre of gravity limit:

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254 When gliding for maximum range, the greater the aircraft weight:

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255 In comparison to gliding in still air conditions, the rate of descent will be …..(i)….. and the distance llown will be …(ii)…… in a tailwind:

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257 The distance covered when gliding headwind compared with gliding in still air will result in ….. (i)…….. distance traveled over the ground together with ….. (ii)…… descent:

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262 Flight for the maximum range in a piston engined aircraft is achieved by flying:

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266 The primary reason for making a take-off into the wind is to: (i) reduce the take-off run available (TORA) (ii) reduce the take-off distance required and (iii) reduce the ground speed at which the aircraft will take off.
Select from he following:

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269 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?

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270 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?

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271 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in Kilograms and moment arm in millimeters .Conversion formula: (lb-in) x 11.5 = (Kgr-mm)

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272 If an aircraft at maximum Take-off Weight (MTOW) is loaded in a manner that positions its C of G at or beyond its aft limit it will:

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273 An aircraft with a C of G out of its forward limit may experience that:

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274 If the angle of attack is increased from 4° to 8°:

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278 The length of a runway available plus the addition of the clearway is named:

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280 One effect during the cruise of operating with partial flap extension would be:

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281 Lift being produced by the wing of an aircraft maintaining a constant true air speed(TAS) will:

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282 The speed at which the aircraft wheels leave the ground during take off is:

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285 The maximum demonstrated cross wind component for the aircraft is 11kt.Given a 16kt wind speed, by how many degrees can a runway heading differ from the wind direction before the surface cross wind component equals 11kt? See.Fig.9

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286 The maximum demonstrated cross wind component for your aircraft is 15kts. Given a 19kts wind speed, by how many degrees can a runway heading differ from the wind direction before the surface cross wind component equals 15kts. (Use CRP-1 or consult Fig. 9)

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287 Loading manifest sheet and C.G. envelope graph for Class "B" aircraft in passenger configuration, is given in Fig.6.
Front occupants……………………………..340 lb
Middle row occupants ………………….340 lb
Baggage comp. Zone "B"……………….200 lb
Fuel Loaded ...............................................58 USG
Trip Fuel ......................................................40 USG

Determine if take-off, landing mass and associated C.G.s are within limits and choose the correct answer.

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288 Loading manifest sheet and C.G. envelope graph for Class "B" aircraft in cargo configuration, is given in Fig.6.
Front occupants……………………………..200 lb
3rd & 4th seats pax…………………….missing
Baggage comp. Zone "A"……………… 520 lb
Baggage comp. Zone "B"……………… 300 lb
Baggage comp. Zone "C"……………… 100 lb
Fuel loaded.....................................................48 USG
Trip fuel ...........................................................44USG
Determine if take-off, landing mass and associated C.G.s are within limits and choose the correct answer.

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291 Determine from the "loading graph" in Fig.35, if aircraft's total moments are within envelope? (Max. MTOW 3600 Lb)
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 300 -
Cargo "B" 340 -
Cargo "C" 320 -
Fuels[40USG] 240 -

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292 Determine from the "loading graph" in Fig.35, if aircraft can be allowed to take-off for max. MTOW of3600 lb?
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 350 -
Cargo "B" 380 -
Cargo "C" 320 -
Fuels[40USG] 240

5 ATTENT. FLIG. PER. EXAM. PREP.

5 ATTENT. FLIG. PER. EXAM. PREP.

232 Four on board. Investigate using tables in Fig. 33, the total moments (/100) and if within limits?

233 After new equipment installed on aeroplane, as in technical certificate shown in Fig. 34, what's the Basic Empty Mass and total moments(/100)?

239 If air density is increased above ISA conditions, the take-off distance required at full throttle compared with that for standard conditions will be:

241 What is the maximum zero fuel mass ?

242 TORA is the:

248 Which of the following items are included in the Dry Operating Mass?

251 The maximum range in a glide path will be achieved by:

253 If the aircraft C of G is on the forward centre of gravity limit:

254 When gliding for maximum range, the greater the aircraft weight:

255 In comparison to gliding in still air conditions, the rate of descent will be …..(i)….. and the distance llown will be …(ii)…… in a tailwind:

257 The distance covered when gliding headwind compared with gliding in still air will result in ….. (i)…….. distance traveled over the ground together with ….. (ii)…… descent:

262 Flight for the maximum range in a piston engined aircraft is achieved by flying:

266 The primary reason for making a take-off into the wind is to: (i) reduce the take-off run available (TORA) (ii) reduce the take-off distance required and (iii) reduce the ground speed at which the aircraft will take off. Select from he following:

269 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?

270 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in pounds and moment arm in inches?

271 Refer to the diagram (Fig.2). For the Utility category, what is the acceptable combination of both aircraft weight in Kilograms and moment arm in millimeters .Conversion formula: (lb-in) x 11.5 = (Kgr-mm)

272 If an aircraft at maximum Take-off Weight (MTOW) is loaded in a manner that positions its C of G at or beyond its aft limit it will:

273 An aircraft with a C of G out of its forward limit may experience that:

274 If the angle of attack is increased from 4° to 8°:

266 The primary reason for making a take-off into the wind is to: (i) reduce the take-off run available (TORA) (ii) reduce the take-off distance required and (iii) reduce the ground speed at which the aircraft will take off.
Select from he following:

291 Determine from the "loading graph" in Fig.35, if aircraft's total moments are within envelope? (Max. MTOW 3600 Lb)
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 300 -
Cargo "B" 340 -
Cargo "C" 320 -
Fuels[40USG] 240 -

292 Determine from the "loading graph" in Fig.35, if aircraft can be allowed to take-off for max. MTOW of3600 lb?
ITEM MASS (lb) TOTAL MOMENTS/1000 (lb-in)
BEM 2122 75.9
Pilot 270 -
Cargo "A" 350 -
Cargo "B" 380 -
Cargo "C" 320 -
Fuels[40USG] 240