2.
Hydraulic pressures:

Engine driven pumps (High).3000 psi (+100-200), (+200 allowable) Engine driven pumps (Low)..1500 psi (+100-200), (+200 allowable) Auxiliary pump.....................3000 psi (+100-200), (+200 allowable) Transfer pump ................................ 2000 - 3000 psi to either system

3.
Minimum hydraulic quantity for dispatch (per system) ................................................ 4.25 quarts

4.  
Landing gear retraction speed ........................................... 250 KIAS

5.  
Landing gear extension / extended speed........300 KIAS or .70 mach

6.  
The antiskid must be operative for takeoff.

7.  
Do not use autobrakes if either hydraulic system fails.

Operating Parameters
1.  
Gear retraction time........................................................8.5 seconds

2.  
Gear extension time .........................................................15 seconds

3.  
Gear free-fall time (flaps retracted, speed 165 KIAS) .......25 seconds

4.  
Useable brake pressure ................................................. 700-3000 psi

5.  
Minimum parking brake pressure (assures 8 hours).....1400-1700 psi

6.  
Tire pressures:

Cold ........................................................................ 178-185 psi
Hot..........................................................................250 psi max

(Continued)
7.
Gear load limit (sink rate):

At max takeoff weight ...................................................360 fpm
At max landing weight..................................................600 fpm

8.
Do not takeoff or land if brake temperature exceeds ...............205. C

9.
Do not set parking brake if brake temperature exceeds ...........300. C

10.
The use of the MAX setting for the autobrakes is prohibited for normal landings on a dry runway.

Temporary RevisionMD-80 Sec. 1 Page 18 Flight Manual Continental Rev. 01-01  04/16/01
Ice and Rain Protection
Limitations:
1.  The windshield heat must be on and checked for all flight operations except as follows:
Inoperative windshield heat limits (below 10,000 feet)
Center or side windshield .................................................315 KIAS

Cracked windshield limits (below 10,000 feet)
Outer panel (center or side)..............................................315 KIAS
Inner panel (center or side)...............................................235 KIAS

Do not operate windshield heat if the windshield is cracked.

There are no speed restrictions above 10,000 feet and there are no restrictions on the clearview or eyebrow windows.
2.  
During takeoff, engine anti-ice must be turned on if icing conditions exist or are anticipated.

3.  
Ice on upper wing surface:

Caution:  Ice shedding from the wing upper surface during takeoff can cause severe damage to one or both engines leading to surge, vibration, and complete thrust loss. The formation of ice can occur on wing surfaces during exposure of the airplane to normal icing conditions. Clear ice can also occur on the wing upper surfaces when cold-soaked fuel is in the main wing fuel tanks, and the airplane is exposed to conditions of high humidity, rain, drizzle, or fog at ambient temperatures well above freezing. Often the ice accumulation is clear and difficult to detect visually. The ice forms most frequently on the inboard, aft corner of the main wing tanks.
Aircraft Without Operational Upper Wing Anti-Ice System
Caution:  The wing upper surfaces must be physically checked for ice prior to all departures. Takeoff may not be initiated unless the flight crew verifies that a visual check and a physical (hands-on) check of the wing upper surfaces have been accomplished, and that the wing is clear of ice accumulation.
On aircraft equipped with the tuft and triangular decal assemblies, installed in accordance with DAC SB 30-59, the physical check may be made by assuring that all installed tufts move freely.
(Continued)
Temporary Revision Sec. 1 Page 19 MD-80 Rev. 01-01  04/16/01 Continental Flight Manual
On aircraft equipped with the painted ice protection triangle the physical check may be made by assuring that the rough-smooth-rough contrast is felt with the ice wand as it is rubbed across the painted ice protection triangle.
Note: This limitation does not relieve the requirement that aircraft surfaces are free of frost, snow, and ice accumulation, as required by FAR’s 91.527 and 121.629.
Aircraft With Operational Upper Wing Anti-Ice System
　
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