Aircraft Systems

Operational Limits A-4N/TA-4

Aircraft Systems

Operational Limits

A-4N/TA-4 STARTER LIMITS

ONE OF TWO AVAILABLE ENGINE STARTERS IS INSTALLED IN THE TA-4. THE LIMITS OF EACH ARE EXPRESSED IN THE NOTES PORTION OF THIS SLIDE IN YOUR LECTURE GUIDE.

Aircraft Systems

Operational Limits

STARTING/IDLE EGT LIMITATIONS

CONDUCT OVERTEMP INSPECTION IF TEMP DURING START EXCEEDS:455 deg C FIVE TIMES, OR 531 deg C FOR ONE PERIOD OF 5 SECONDS OR MORECONDUCT TEARDOWN INSPECTION OF ALL HOT SECTION PARTS IF STARTING EGT EXCEEDS: 565 deg C FOR ANY PERIOD OF TIME.

IDLE EG 340 deg - GUIDE, NOT LIMIT

Aircraft SystemsOperational Limits

ENGINE: EGT     

Operating Condition MAX EGT°C

MAX %RPMLimit Time

StartJ52-P6/8/408

 455

 Start to Idle

 2 Minutes

Idle *P-6/8/408

 340

 Idle

 —-

AccelerationP-6P-8P-408

 660680815

 MilitaryMilitaryMilitary

 8 Minutes8 Minutes8 Minutes

NormalP-6P-8P 408

 602595705

 Mil Minus 3%Mil Minus 3%Mil Minus 3%

 ———

MilitaryP-6P-8P 408

 621650785

 MilitaryMilitaryMilitary

 30 Minutes30 Minutes30 Minutes

* Temperature of 340 C is not a limit, but is given as a guide to indicate temperature that, if exceeded, may signify engine malfunction.

Aircraft SystemsOperational Limits

ENGINE LIMITS

ENGINE SPEED P-408 P-8NORMAL MILITARY RPM RANGE 97-100% 97-100%MAXIMUM ALLOWABLE RPM 102.4% 102.9EXTREME AMBIENT TEMPERATURE EFFECTS ON MAX RPM (HOT/COLD) +1,-5% +1, -5%SPEED ABOVE WHICH FUEL CONTROL MALFUNCTION OR

TRIM ERROR IS INDICATED 101% 101%P-8 – MIN INFLIGHT 70% W/ SMOKELESS ENG MOD

Aircraft Systems

Operational Limits

IF OIL PRESSURE IS LESS THAN 30 PSI AT IDLE, OR 40 PSI ABOVE 60 PERCENT RPM, SHUTDOWN THE ENGINE TO DETERMINE THE REASON FOR THE LACK OF, OR LOW OIL PRESSURE.

ENGINE: OIL

PRESSURE

     

Operating Condition

Oil PressureNormal

Oil Pressure Minimum LimitTime

StartJ52-P6/8/408

 risingIndication

   

IdleP-6/8/P 408 P6/8/408

 40-50 psi40-50 psi

On Deck30 psi35 psiAirborne<40 psi

    1 Min

Aircraft Systems

Operational Limits

WEIGHT

The gross weights are:1. Field takeoff..........................................................24,500 pounds2. Field landing (minimum rate of descent)..............16,000 pounds3. Field landing (non flared and field arrestments)...14,500 pounds

Note: Field landings at gross weights in excess of maximum recommended weights should be attempted only in an emergency; refer to the Flight Manual for more on Landing at High Gross Weights.

Aircraft Systems

Operational LimitsAIRSPEED LIMITATIONS

Aircraft Systems

Operational Limits

MANEUVERING FLIGHT/PROHIBITED MANEUVERS

1. Negative-g flight in excess of 10 seconds2. Intentional spins3. Aileron rolls:a. That exceed 360 degrees of rollb. That exceed one-half stick deflection with fuel in the external fuel tanks 4. The maximum permissible change in angle of bank during rolling pullouts or rolling pushovers is 180 degrees 5. (TA-4) 90º to 100º nose up zero airspeed.

Aircraft SystemsOperational Limits

ACCEL (G)VS GWT

Aircraft Systems

Operational Limits

ACCELERATION (G) ACELERATION LIMITATIONS

Accelerations at which moderate buffeting occurs shall not be exceeded. Otherwise, the maximum permissible accelerations for flight are shown in the Flight manual. As gross weight increases above 12,500 pounds, maximum permissible accelerations decrease as shown in the Flight manual. During conditions of moderate turbulence, avoid deliberate accelerations in excess of those permitted as shown in the Flight manual to minimize the probability of overstressing the aircraft as a result of the combined effects of gust and maneuvering loads. Transonic pitchup can occur during speed reductions in the transonic region. Buffet onset and flight strength limits at low altitude combat conditions are shown in the Flight manual.

****CAUTION****

*To minimize the probability of exceeding the maximum permissible load factor due to the combined effects of maneuvering load factor and transonic pitchup, the following procedure is recommended:

1. Below 15,000 feet, at speeds in excess of 0.94 IMN, avoid deliberate accelerations in excess of +4g.

2. Above 15,000 feet, avoid deliberate accelerations that exceed buffet onset.

Aircraft Systems

Operational Limits

OPERATING STRENGTH (Vn)

Aircraft Systems

Operational Limits

ASYMETRICAL LOAD

TAKEOFF ASYMETRY LIMIT IS 7,500 FOOT-POUNDSLANDING CROSSWIND UNDER LIGHT WING, NOT RECOMMENDED.FLARED FIELD LANDINGS PERMITTED UP TO 12,500 FOOT-POUNDS ASYMMETRIC MOMENT.MINIMUM APPROACH SPEED WITH UP TO 7500 FOOT-POUNDS OF ASYMMETRIC MOMENT 115MINIMUM SPEED VARIES LINEARLY TO 130 KIAS AT 12,500 FOOT-POUNDS

Aircraft Systems

Operational Limits

ASYMETRY CALCULATION NOMOGRAM

Aircraft SystemsOperational Limits

WING PRESSURIZED

The below limitations apply at all times that the wing fuel cell is pressurized (Emergency Transfer):

1. No landings2. Coordinated turns only3. Aircraft load factor limits of +0.1 to +2.04. No air refueling as receiver aircraft5. No nosedown attitudes6. 45-degree bank, maximum7. 400 KIAS maximum

Aircraft SystemsOperational Limits

CROSS WIND LANDINGS

THE BELOW ARE MAXIMUM RECOMMENDED 90 DEGREE CROSSWIND COMPONENTS FOR THE INDICATED CONDITION:

NORMAL AIRCRAFT: 25 knotsNO SPOILERS: 15 knotsDISCONNECTED CONTROLS: 8 knots (take arresting gear above)

DRAG CHUTE: 10 knots

Aircraft SystemsOperational Limits

TIRE AND DRAG CHUTE

TIRE LIMIT SPEED

A maximum of 175 knots groundspeed is imposed upon the aircraft during ground operations because of structural limits of the tires.

DRAG CHUTE LIMITATION

A maximum speed of 160 KIAS is imposed upon the aircraft with the F-4 5-ring slot type drag chute deployed. Flight without the drag chute canister is not permitted due to inadequate engine cooling.

Aircraft Systems

Operational Limits

MISCELLANEOUS MISCELLANEOUS LIMITATIONS

The external baggage container (EBC) may be carried, loaded or empty, within the limits of flight for full 300-gallon tanks except as modified by the following restrictions.

1. Airspeed limitation is 525 KIAS or Mach 0.80, whichever is lower.

2. Normal acceleration limitations are -1.0 to positive 3.0g’s.

3. Flight controls, propulsion controls, or other systems shall not be moved or operated so as to result in rapid or abrupt aircraft responses.

4. Side slipping or skidding shall be avoided.

5. Angle of bank shall not exceed 60 degrees.

6. Jettison in emergency only, in 1.0g level flight at a maximum of 475 KIAS/0.80 IMN.

Aircraft Systems

Operational Limits

SUMMARY

YOU CAN’T FLY YOUR AIRCRAFT TO THE LIMIT

IF YOU DON’T KNOW THE LIMIT!