limitations, systems, performance, weight and balance,  normal procedures, emergency procedures, and handling  requirements.  [Figure 16-9] Transitioning pilots find an LSA very familiar when  conducting a preflight inspection; however, some preflight  differences are worth pointing out. For example, many LSAs  do not have adjustable seats but rather adjustable rudder  pedals.  [Figure 16-10]  Often, LSA seats are in a fixed  position. There are varied methods that LSA manufacturers  have implemented for rudder pedal position adjustment.  Some manufacturers use a simple removable pin while others  use a knob near the rudder pedals for position adjustment.  Shorter pilots may find that the adjustment range may not  be sufficient for certain heights and an appropriate seat  cushion may be required to have the proper range of rudder  pedal movement. In addition, seats in some LSAs are in a  semi-reclined position. The first time a pilot sits in a semi- reclining seat, it may seem somewhat unusual. A pilot should  take time to get comfortable. LSA airplanes use conventional control stick while others  use a yoke. One manufacturer has combined the two types  of controls in what has been termed a “stoke.” While this  control may seem unique, it provides a completely natural  feel for flight control.  [Figure 16-11]  Regardless of the flight  controls, a full range of motion check of the flight controls is  required. This means full forward to full forward left to full  aft left to full aft right and then full forward right. Verify that  each control surface moves freely and smoothly. On some  LSAs, aileron control geometry, in an attempt to minimize  adverse yaw, moves ailerons in a highly differential manner;  Another area that transitioning pilots require familiarity  is with the flight and engine controls. These may vary  significantly from airplane model to airplane model. Some  Figure 16-9.  Pilot’s Operating Handbook for a LSA. 16-8 N O I T C U D O R T N I A N S S E C M O D E L 1 6 2 G A R M I N $_{ }$G 3 0 0 U . S . PILOT’ S  OPERATING  HANDBOOK AND FLIGHT TRAINING SUPPLEMENT CESSNA MODEL 162 S E R I A L S 16200001  AND  ON ORIGINAL ISSUE 22 JUL Y 2009 REVISION 4 - 21 OCTOBER 201 1 P A RT  NUMBER:  162PHUS-04 162PHUS-04 i / i A N S E C N O I T C U D O R T N I MODEL 162 GARMIN G300 U . S . PERFORMANCE - SPECIFICA TIONS * SPEED: Maximum at Sea Level  . . . . . . .  . . . . . . .  1 8 K N O T S ( 2 1 8 . 5 k m / h r ) Crui se, 69% Power at 6000 Feet .  . . . 0 9 K N OTS  (201.9  km/hr) CRUISE: Recommended  lean  mi xture  wi th  fuel al lowance  for  engine st art, t axi, t a k e o f , c l i m b a n d 3 0 m i n u t e s r e s e r v e . RANGE: 69% Power at 6000 Feet . . . . . . . . .  . . . . . . R a n g e - 3 6 N M 24 Gallons Usabl e Fuel . .  . . . . . . $^{. . . .}$T ime - 3.16 HOURS RA TE OF CLIMB A T SEA LEVEL  . . .  . . . . . . . .  880 FPM (268.2 mpm) SER V ICE CEILING  . . . . . . . . . . .  . . . . . . . . .  14,625 FEET (4457.7 m) T A KEOFF PERFORMANCE A T  SEA LEVEL: G r o u n d R o l . . . . . . . . . . . . . . . . . 640 FEET (195.1 m) T t a l D i s t a n c e O v e r 5 0 F o t O b s t a c le . . . . . . . 1 138 FEET (346.9 m) LANDING PERFO RMANCE A T  SEA LEVEL: G r o u n d R o l . . . . . . . . . . . . . . . . . 671 FEET (204.6 m) T t a l D i s t a n c e O v e r 5 0 F o t O b s t a c le . . . . . . . 1 369 FEET (417.3 m) ST ALL SPEED: Flap s UP Power Idle . . . . .  . . . . . . . . . . . . . 4 1 K I A S Flap FULL, Power Idle . . . . . . . . . .  . . . . . . . . . 3 7 K A S N O T E *  S p eed  performance i s  $_{show}$ n $_{for }$ ai rplanes  not  equi pped with  the  optional  wheel fair ings.  Airplanes  equi pped  with optional  wheel fairi ngs wil l  not i c e  an  increase  in  speeds  by approximately 2 knot s.There is  a corresponding dif ference in  range,  while  all other  performance  figures  are unchanged when speed fa irings are inst alled. The  above  performan ce  fi gures are  based  on  airplane  weight s  at  1320 pounds  (598.7  $^{kg), }$st andard atmospheric  cond itions,  level,  hard- surfaced  dry  runways  and n o w i n d . T h e y a r e c a lculated  values  derived from  fli ght  test s  conducted  by  Cess n a A i r c a f t C o m p a n y  under  carefull y documented  conditions  and  will v ary  with  indivi dual  airplanes  and numerous factors af fect ing flight performance. (Continued Next Page) 162PHUS-03 iv COPYRIGHT © 2009 CESSNA AIRCRAFT COMPANY WICHITA, KANSAS, USA SERIAL NUMBER REGISTRATION NUMBER Model 162 Serials 16200001 and On This publication includes the material required to be furnished to the pilot by ASTM F2245. ORIGINAL ISSUE - 22 JULY 2009 REVISION 4 - 21 OCTOBER 2011 U.S. Inside of the Airplane Figure 16-10.  Adjustment lever for the rudder pedal position. Rudder pedal position adjustment