Pilot's Operating Handbook

3- 42 AP Master Switch In ON Position . .. ......... .. ...... ... ... ... . . . . ... .... .. 3-34 3- 43 AP Display, FD Powered-Up. . ...... ....... ...... ................... ........... .. .. 3--35 3-44 FD Display. FD/AP Mode Engaged .. .......... .. ................ . . 3-35 3- 45 FD Master Switch In ON Position •••• ·••400 ♦ ••••••••••••• •• 3--36 3- 46 AP Master Switch In OFF Positmn. ............ 3-36 3- 47 FD Display, FD Mode Engaged 3--36 3- 48 Yaw Damper Master Switch 3--3/ 3- 49 Yaw DamperTnm Knob 3- 37 --- 3rd Ed Jun 30 07 VII s- rr c Tab le 2- 1 Pre-FhghtTest. ( ( VIII Li st of Tables Pg. 2-3 3 rd Cd Jun 30 . 07 3rd Eel Jun 30 0 7 SECTION 1 OVERVIEW STEC 1- 1 1 .1 Document Organization Section 1 Overview Section 2 Pre Flight Procedures Section 3 In-Flight Procedures Section 4 Operat.rng Parameters Section 5 Glossary 1.2 Purpose STEC This Pilot's Operating Handbo ok (POH) provides Pre - Flight and In- Flight operating procedures for the S- TEC System Sixty Two Autopil ot (AP) Note: T hi s PO H must b e carrie d in the A I C a nd mad e av a ilabl e to th e pilot at all time s. It can only b e u se d in co njun ct ion with th e Federa l Aviation Administration (FAA) approved Aircraft Flight Ma nual (AFM) or Aircraft F light M anua l S uppl e ment (AFMS) . R efer to the app li cab l e AFM or AFMS for A IC s pecific inform a tio n, s u c h as unique gro und t es t s, li mitation s, and em e rg en cy procedure s. Note: Th e S ystem S ixty Two a utopilot is a tool provided to a irc raft owne rs, that se rv es to ass i st them w ith cockpit workload managem e nt. Th e ability of th e autopilot to provid e optimum assistance an d performanc e is direc tly proportional to the pilot's knowl edge of its operating proce dures. Therefore , it is highly r eco mm en ded that the pilot deve lop a thorough under standing of the au topilo t, its modes , a nd operating pro cedures in Vis ual M eteo rologi ca l Conditions (VMC), prior to us ing it under In s trum e nt F light Rules (/FR). 1 .3 Gene ral Co ntrol Th eory The Sys ten1 Sixty Two 1s a rate based autopilot When 111 control of the ro ll axis. the autopilot senses turn rate, as well as closure rate to the selected course, along with the non-rate quantities of heading error, course error, and course deviation indication When 111 control of the pitch axis, the autopilot senses vertical speed acce le ration, and closure rate to the selected ghdeslope. along with the non-rate quantities of altitude and ghdeslope deviation 111dicati on These sensed data provide reedback to the autopilot, which processes th em 111 order to control the aircraft through the use of mechanisms coup l ed to the con trol system In mos t aircraft. the roll servo is coupled to the ail erons The pitch servo 1s coupled to lhe elevator Activation of roll axis control must always precede activation of pitch axis control The optional autotrim function senses when the aircraft needs to be trimm ed abou t the p itch axis and responds by dnvmg the trim servo 111 the proper dtrecllon to provide trun The trun servo is coupled to the elevator tnm tabs 3rd Ed Jun 30 0 7 1-3 s- rrc The optional yaw damper senses excessive adverse yaw about the yaw a,C1s and responds by driving the yaw servo in the proper direction to provide damping The yaw servo Is coupled to the rudder The optional night director Is a display of the flight profile 1.4 Mod es of Ope ration 1.4 .1 Roll Axis Contro l Heading (I IDGl Mode Used to Turn onto a Selected I leading and I lold 11 N av1ga t1on INAVl Mode Used to Intercept and Track a VOR Course Nav1gallon Approach (NAV APRl Mode Used to Intercept and Track a LOG Front Course Inbound Reverse (REVl Mode Used to Intercept and Track a VOR Back Course Inbound Reverse /\pproach !REV APR) Mode Used to Intercept and Track a LOG Back Course Inbound 1.4.2 Pitc h Axi s Contro l Altitude I lold (ALT HOLD) Mode Used to Hold Altitude Vertica l Speed cVSl Mode Used to Hold Vertical Speed Ghdeslope (GSl Mode Used to Intercept and Track Ghdeslope 1 .5 Block Diagram The System Sixty Two Block Diagram Is shown in r,g t • t n,e Yaw Damper Block Diagram Is shown ,n F,g I 2 f'he Flight Director Block Diagram Is shown In r,q 1 3 14 3rd Ed Jl111 10 0 7 DG HSI BATTERY MASTER SWITCH ROLL FLIGHT GUIDANCE COMPUTER S- TEC ROI I.SERVO MANUAL ELE CTRIC TRIM SWITCH AUTOILO'r IIASTER SWITCH PROGRAMMEl(IANNUNCIATOR Fig . 1-1. System Sixty Two Block Diagram - TRIM MASTER SWITCH PITCH SERVO TRIMS£RVO iOPTIOH.At.) AI.TITUO£ TRA NSDUC ER S£1.£CTORfALERTER (Ol'TIOHAI.) 3rd Ed Jun 30 07 1-5 S- TEC ( ' YAW DAMPER MASTER SWITCH <D YAW TRIM YAW DAMP ER (OPTIONAL) Fig. 1-2. Yaw Damp er Bl ock Diagra m YAW SERVO (OPTIONAL) FLIGHT DIRECTOR MASTER SWITCH FLIGHT DIRECTOR (OPTIONAL) Fig. 1-3. F light Director B lo ck Diagram 3rd Ed Jun 30 07 SECTION 2 PRE-FLIGHT PROCEDURES 3rd [d Jun JO 07 S - TC:C 2-1 'JI<D Cl) w 0...,, w S- TEC 2.1 Pre-F ligh t Test Pnor to takeoff and with engine running pc, form the actions shown in Table 2 1 For eac h action, verify the corresponding response wh ere applicable Table 2- 1. Pre- Flight Test ( co ntin u ed o n pa ge 2-5) ACTION RESPONSE Note: If a Flight Direct or is installed, then the FD annunciation appears on the AP display whenever one (or both) of the following conditions exist: Autopilot Master Switch in ON position Flight Director Master Switch in ON position For the purpose of brevity, this Pre-Flight Test precludes the installation of a Flight Director. The pilot should make allowance for this exception accordingly, ff a Flight Director is installed. 1. Set Yaw Damper M aster Switch -- to OFF position ( if installed). 2. Set Trim Master Switch to OFF -- position (if installed). 3. Set Battery Master Switch to ON -- position. 4. Set Avio nics Master Switch to O N -- position. 5. Set Autopilot Master Switch to O N ROY a nn unciation only appears on position. AP display within 3 mi nutes, as shown in Fig. 2-1. Note : Sho u ld a Turn Coordinator failure be detected, the ROY annuncia t ion will not appear as shown in Fig. 2-2, and the autopilot will not operate. 3rd Ed Jun 30 07 23 S-TEC ( Fig. 2-1. AP Display, ROY f or Operation I Fig. 2-2. AP Display, Turn Coordinator Failure, ROY Do es Not Appear 24 3rd Ed Jun 30 0/ STEC S-TEC Table 2-1. Pre- Flight Test (continu ed from page 2-3) Table 2-1. Pre - Flight Test (continued from page 2-5) ACTION RESPONSE ACTION RESPONS E 6. Set Autopilot Master Switch to The following annunciations all TEST position. appear on AP display, as shown in 13 . A ttempt movement of A/C A/C Control Wheel's reduced Control Wheel forward and aft. freedom of movement indicates that Fig. 2-3: Pitch Servo is engaged. ROY FD REV HOG NAV A PR Pitch Servo can be overridden. If not, set Autopil ot Master Switch to OFF vs A LT GS position and do not use. SEL CAP DSABL FAIL SOFT TR IM UP switch an d ON switch lamps are both illuminated on AP display. ( 14 . Press/Hold UP switch, while Pitch Servo disengages after ½ maintaining a grasp on A/C Control second, as sensed by the increased Wheel. freedom of A/C Control Wheel movement about pitch axis. 7. Set Heading Bug under Lubber -- Line. 15. Release UP switch, while Pitch Servo immediately re-engages, maintaining a grasp on A/C Control as sensed by the reduced freedom of Wheel. A/C Control Wheel movement about 8 . Move A/C Control Wheel left and -- pitch axis. right, to sense its freedom of movement about roll axis. 9. Press HOG mode selector switch - - 16 . Press/Hold ON switch, while Pitch Servo disengages after ½ maintaining a grasp on A/C Control second, as sensed by the increased Whee l. freedom of A/C Control Wheel to engage heading mode. movement about pitch axis. 10. Attempt movement of A/C A/C Control W heel's reduced Control Wh eel left and right. freedom of movement indicates that Roll Servo is engaged. 17 . Release ON switch, while Pitch Servo immediately re-engages, maintaining a grasp on A/C Control as sensed by the reduced freedom of Wheel. A/C Control Wheel movement about pitch axis. Roll Servo can be overridden. If not, set Autopilot Master Switch to OFF position and do not use. f 18. Set Autopilot Master Switch to All annunciations except ROY are O N position. extinguished. 11 . Move A/C Control W heel forward -- and aft., to sense its freedom of UP switch and ON switch lamps are extinguished. movement about pitch axis. 12. Press ALT mode sel ector switch -- 19. Press HOG mode selector switch HOG annunciation only appears on to engage heading mode. AP display, as shown in Fig. 2-4. to engage altitude hold mode. 20. Turn Heading Bug to the left A/C Co ntrol Wheel turns to the left. side of Lubber Line. 3rd f-d Jun 30. 07 25 2-6 3rd Ed Jun 30 07 S- TEC S- TEC Table 2-1. Pre- Flight Test (continued from page 2-6) ACTION RESPONSE 21 . Turn Heading Bug side of Lubber Line. to the right NC Control Wheel turns to the right. 22 . Set Heading Bug under Lubber A/C Control Wheel stops. Line. Note: If it is not possible to select a local VOR frequency on Navigation Receiver, then proceed to step 36. Otherwise, proceed to step 23. 23 . Select local VOR frequency on ___.. Navigation Receiver. Fig . 2-3. AP Di sp l ay , A ll Ann u nciati ons Appear Note: Proceed to either step 24 (HSI) or step 30 (DG). 24. Turn Course Pointer until CDI ---- needle is centered. 25 . Turn NC until Course Pointer is ----- under Lubber Line, to null course error input to autopilot. 26 . Press NAV mode selector switch NAV and SOFT annunciations only to engage navigation mode. appear on AP display, as shown in Fig. 2-5 . ( 27 . Turn Course Pointer left until A/C Control Wheel turns to the right. CDI needle deflection is 2 dots right of cent er. 28 . Turn Course Pointer right until A/C Control Wheel turns to the left. CDI needle deflection is 2 dots left of center. Fig. 2-4. AP Disp lay, HOG Mode Engaged 29 . Turn Course Pointer left until COi NC Control Wheel stops. needle deflection is centered. 3rd Ed Jun 30 07 27 2-8 3rd Ed Jun 30 , 07 s r Ec S-TEC Table 2-1. Pre-F lig ht Test (con t in ued from page 2-8) Table 2-1. Pre- Flight Test (continu ed from page 2-9) ACTION RESPONSE ACTION RESPONSE N ote: Proceed to step 35. 35. Press HOG mode selector switch HO G ann unciation only appears on to engage headi ng mode. AP display. 30. Turn OBS until COi needle is --centered. 36 . Press ALT mode selector switch HOG an d ALT annunciations only to engage altitude hold mode. appear on AP display, as shown in Fig. 2-6. 31 . Press NAV mode selector switch NAV and SOFT annunciations only to engage navigation mode. appear on AP display, as shown in Fig. 2-5. 37. Move A/C Control Wheel until --- elevator is in neutral position. 32. Tum OBS until COi need le A/C Control Wheel turns to the right. deflection is 2 dots right of center. 38. Press/Hold UP switch. A/C Control Wheel moves in aft direction. 33. Tum OBS until CO i needle A/C Control Wheel turns to the left. deflection is 2 dots left of center. 39. Release UP switch. A/C Control Wheel continues moving in aft direction. 34. Tum OBS until C Oi needle is A/C Control Wheel stops. centered. 40. Press/Hold ON switch. A/C Control Wheel slows to a stop in aft direction, and then moves in forward direction. 41 . Release ON switch. A/C Control Wheel continues moving in forward direction. 42. Press VS mode selector switch A/C Control Wheel stops. to engage vertical speed mode. H OG and vs annunciations only appear on AP display, as shown in Fig. 2-7 43. Press/Hold UP switch. A/C Control Wheel moves in aft direction. Fig. 2-5. AP Display, NAV Mode Engaged, SOFT Condition 44 . Release UP switch. A/C Control Wheel continues moving in aft direction. 3rd Fcl Jun 30 0 1 2-9 2-10 3rd Ed Jun 30. 07 S ILC S- TEC Table 2-1 . Pre-Flight Test {continued from page 2-10) ACTION RESPONSE 45 . Press/Hold ON switch. A/C Control Wheel slows to a stop in aft direction, and then moves in forward direction. 46 . Release DN switch. A/C Control Wheel continues moving in forward direction. 47. Press ALT mode selector switch A/C Control Wheel stops to engage altitude hold mode. ( ' HOG and ALT annunciations only appear on AP display. Note: Fig. 2-6. AP Display, HOG and ALT HOLD Modes Engaged If autopilot is equipped with autotrim, then proceed to step 52. Otherwise, proceed to step 48. 48. Move A/C Control Wheel as far After 3 seconds, TRIM annunciation forward as possible. appears on AP display as shown in Fig. 2-8, UP switch lamp becomes illuminated, and audible alert sounds a steady tone. After 7 seconds, TRIM annunciation flashes, UP switch lamp flashes, and audible alert becomes periodic. 49 . Move A/C Control Wheel aft until UP switch lamp is extinguished, and TRIM annunciation is extinguished. audible alert is squelched. 50. Move A/C Control Wheel as far After 3 seconds, TR IM annunciation aft as possible. appears on AP display as shown in Fig. 2-8, DN switch lamp becomes illuminated, and audible alert sounds a steady tone. Fig. 2-7. AP Di sp lay, HOG and VS Mod es Engaged After 7 seconds, TRIM annunciation flashes, DN switch lamp flashes, and audible alert becomes periodic. 3rd E:d Jun 30 07 2-1 1 2-12 3rd Ed Jun 30 07 STEC S- TEC Table 2-1. Pre- Flight Test (continued from pag e 2-12) ACTION RESPONSE Table 2-1. Pre- Flight Te st (continued from pag e 2-13) ACTION RESPONSE 51 . Move A/C Control Wheel forward DN switch lamp is extinguished, and until TRIM annunciation is audible alert is squelched. extinguished. 55. Move A/C Control Wheel as far After 3 seconds, Elevator Trim Wheel aft as possible. begins to run nose down with increasing speed. Note: Proceed to step 67. 56. Move A/C Control Wheel forward - -until Elevator Trim Wheel stops. 52. Set Trim Master Switch to ON --position. 57. Press either forward or aft on Autopilot disconnects as follows: both segments of Manual Electric 53. Move A/C Control Wheel as far After 3 seconds, Elevator Trim Wheel forward as possible. begins to run nose up with increasing speed. Trim Switch. ROY annunciation appears flashi ng, while all other annunciations are extinguished. After 5 seconds, ROY annunciation 54. Move A/C Control Wheel aft until - - stops flashing but remains. Elevator Trim Wheel stops. 58. Press/ Hold either forward or aft Elevator Trim Wheel does not begin on only one segment of Manual to run. Electric Trim Switch, but not both. 59. Press/Hold forward on both Elevator Trim Wheel runs nose down segments of Manual Electric Trim at full speed, and TRIM annunciation Switch. appears flashing on AP display. 60 . Press/Hold AP DISC I TR IM Elevator Trim Wheel stops. INTR Switch. 61 . Release AP DISC / TRIM INTR Elevator Trim Wheel resumes running Switch. nose down at full speed. 62. Release Manual Electric Trim Elevator Trim Wheel stops. Switch. TRIM annunciation is extinguished. Fig . 2-8. AP Di splay, HDG and ALT HOLD Mode s Engaged , Trim Required 3rd Ed Jun 30 07 2-13 2-14 3rd Ed Jun 30 07 STEC Table 2-1. Pre- Flight Test (continued from page 2-14) Table 2-1. Pre- Flight Test (continu ed from page 2-15) ACTION RESPONSE ACTION RESPONSE 63 . Press/Hold aft on both segments Elevator Trim Wheel runs nose up at 68. Actuate NC Rudder Pedals -- of Manual Electric Trim Switch. full speed, and TRIM annunciation alternately in succession, to sense appears flashing on AP display. their freedom of movement about yaw axis. 64. Press/Hold AP DISC I TRIM Elevator Trim Wheel stops. INTR Switch. 69 . Set Yaw Damper Master Switch -- to ON position. 65 . Release AP DISC/ TRIM INTR Elevator Trim Wheel resumes running Switch. nose up at full speed. ( 70 . Turn Yaw Trim Knob until NC -- Rudder Pedals stop. 66 . Release Manual Electric Trim Elevator Trim Wheel stops. Switch. TRIM annunciation is extinguished. 71 . Attempt actuation of NC Rudder NC Rudder Pedals' reduced freedom Pedals alternately in succession. of movement indicates that Yaw Servo is engaged. Note: Yaw Servo can be overridden. If not, If autopilot is equipped with a Yaw Damper, then proceed lo step 68. Otherwise, proceed to step 77. set Yaw Damper Master Switch to OFF position, and do not use. 67 . Press AP DISC I TRIM INTR Autopilot disconnects as follows: Switch. 72. Tum Yaw Trim Knob fully CCW. Left NC Rudder Pedal slowly moves forward. ROY annunciation appears flashing, while all other annunciations are extinguished. 73 . Tum Yaw Trim Knob fully CW . Right NC Rudder Pedal slowly moves forward. After 5 seconds, ROY annunciation stops flashing but remains. 74. Turn Yaw Trim Knob CCW until --NC Rudder Pedals stop. Nole: ( \ If autopilot is equipped with a Yaw Damper, then proceed lo step 68. Otherwise, proceed lo step 77. 75. Set Yaw Damper Master Switch -- to OFF position. 76 . Actuate NC Rudder Pedals NC Rudder Pedals' increased alternately in succession. freedom of movement indicates that Yaw Servo is disengaged. 77. Trim A/C for takeoff. -- 3rd [d Jun 30 07 2-15 2 16 3rd Ed Jun 30 07 SECTION 3 IN-FLIGHT PROCEDURES 3rd Ed Jun 30 07 S- TEC 3- 1 STEC Page lntent1onally Blank 32 3rd Ed Jun 30 07 S- TEC 3.1 No rm al Ope rating Pro c edu res 3.1.1 Hea ding (HOG) Mode Set the Heading Bug to the desired heading on the compass card (HSI or DG) And then press the HOG mode selector switch to engage the heading mode The I IDG annunc1at1on w, 11 appear as shown In Fig 3 1 to acknowledge that this mode Is engaged fhe autopilot will turn the aircraft onto the selected heading and hold ,t A new heading can be subsequently selected by setting the Heading Bug to II Fig. 3-1. AP Di s play, HOG Mod e E ng a ged 3.1 .2 Navig a tion (NAV) Mode Select the VOR frequency on the Naviga ti on Receiver Heading System HSI Set Course Pointer to desired course on compass card Heading System DG Set I leading Bug and OBS to desired course on each respective compass card Press the NAV mode se l ect or sw it ch to engage the navigation mode The NAV annuncIatIon will appear as shown In Fig 3 2 to acknowledge that this mode Is engaged 3rd E:d Jun 30 07 33 ( S- TEC Fig. 3-2. AP Display, NAV Mode E ngag ed If the Course Dev1allon lnd1cat1on (COi) Is at full scale {100%) needle deflection from center then the autopilot w ill establish the air craft on a 45 in tercept angle relative to the selected course l::ven 1f COi needle deflection Is less than I00% the autopilot may still establish an intercept angle of 45°, provided that the aircraft's closure rate to the selected course Is sufficiently slow Otherwise the intercept angle will be less than 45° As the aircraft approaches the se l ected course , the autopilot senses the corresponding rate at which COi needle deflection approaches center (closure rate). in order to 1nit1ate the aircraft's turn onto the course at the proper point, and thereby prevent overshoot The point at which this turn begins Is variable. being further from the course at faster closure rates. and closer to the course at slower closure rates Although closure rate is pr incipally a function of groundspeed, the distance of the aircraft from the VOR station also has an effect Nevertheless. the turn will always begin between 100% and 20% COi needle deflection During this stage of the in tercept sequence, the autopilot operates at maximum gain and sens1t1vIty to closure rate In addition, 11 limits the aircraft's turn rate to 90% of a standard rate turn although for some higher performance (turboprop) aircraft this Is 75% When the aircraft arrives at 15% COi needle deflection. the course Is captured At that instant. a step reduction in autopilot gain occurs , so tha t the Course Pointer (HSI) or I leading Bug (DGJ has sufficient authority lo complete the intercept In addition the sens11iv1ty to closure rate Is reduced The overall au thority or the autopilot dunng this stage of the intercept sequence Is called the CAP condition wh i ch Is acknowledged by the appearance of the CAP annunciation as shown in Fig 3 3 Fifteen seconds after course capture. a second step reduction in autopilot gain occurs, to limit the aircraft's turn rate to 45% of a standard rate turn. although for some higher performance (turboprop) aircraft this Is 37 5% In addition the sensItIvIty to closure rate Is reduced again The overall authority of the autopilot during this stage of the intercept sequence Is called the CAP sorr cond1t1on which Is acknowledged by the appearance of the SOFT annuncIatIon as shown in Fig 3 4 3-4 3rd Ed Jun 30 07 S- TEC Fig. 3-3. AP Display, NAV Mode Engaged, CAP Condition Fig. 3-4 . AP Disp lay, NAV Mode Engaged, CAP SOFT Condition Thirty seconds after course ca pture the autop il ot es tablishes the required crosswind correction angle Seventy five seconds after co urse capture, a third step reduction in autopilot gain occurs to limit the aircraft's turn rate to 15% of a standard rate turn although for some higher performance (turboprop) aircraft this Is 12 5% In add1t1on the se nsItIvIty to cl osure rate is reduced once more This Is acknow ledged by th e extingu1shment of the CAP annunciation. as shown 111 Fig 3 5 It marks the end of the intercept sequence. and the beginning of tracking The overall authonty of the au topilot during tracking Is called the SOFr cond1 tIon 3rd Ed Jun 30 07 35 ( ( S - TEC Fig. 3-5. AP Disp lay, NAV Mode Engaged, SOFT Condition The pilot should make speed, distance, and time considerations dunng the 75 second penod from course capture to the beginning of tracking , to account for the aircraft's position For example at 115 kts, a distance of 24 naultcal miles will be traveled in 75 seconds. If it should happen that the Course Pointer (HSI) or Heading Bug (OG) is already within 5° of the selected course, and COi needle deflection Is less than 10%, then the autopilot will Immed1ately establis h th e SOFT con d1t1on upon engagement of the navigalton mode Whil e tracking 111 the SOFT condition, the autopilot ignores short term COi needle deflections (excursions). to thereby 1nh1b1t aircraft scalloping dunng VOR station passage Should COi needle deflection exceed 50% for a penod of 60 seco nd s. the au topilot will r eve rt to th e CAP SOFT con d1t1 on as a means to re establish the aircraft on co urse The NAV annuncIatIon will flash whenever CD I needle deflection exceeds 50%. or the NAV Flag is 111 view In the latter event, th e FAIL annuncIatIon will also appear 3.1.2.1 Pilot Selectable Interc ept Angle To select an intercept angle other than 45°. se t th e I leading Bug to the desired intercept heading on the compass card. such th at th e difference between this heading and the desired co urse Is the intercept angle Th en set t he Course Pointer (HSI) or OBS (OG) to the desired course Press and hold the HOG mode se lector switch. and then press the NAV mode se lector switch to engage the heading mode and arm the navigation mode The HOG and NAV annuncIatIons will appear as shown 111 Fig 3-6. to acknowledge this The autopilot will establish the aircraft on the selected intercept angle (heading). until 11 must turn the aircraft onto the selected course to prevent overshoot At that point in the intercept sequence. the HO G annuncIatIon will ex tinguish to indicate engagement of the nav1gatron mode 36 3rd Ed Jun 30 07 S- TEC If the selected intercept angle 1s greater than 35°. then the HDG annunciation will extinguish at 90% COi needle deflection However. 1f the selected intercept angle is less than 35°. then the HOG annunciation will ex t inguish at 20% CDI needle deflection In addition. the course is captured at one of the following points: 15% CD I needle deflection (Roll Computers with Mod Code Kand below) 20% COi needle deflection (Roll Computers with Mod Code L and above) If the heading system 1s a DG, al the moment the HOG annunaation ex1inguiaj,es, 1mmed1ately set the Heading Bug to the course in order to input a course error lo the autopilot Otherwise. the a utopilot will lack sufficient authority to turn the a ircraft onto the course Fig . 3-6. AP Disp lay, HOG Mode Engaged, NAV Mod e Arm ed 3.1. 3 Altitud e Hold (ALT HOLD) Mod e The al titude hold mode can only be engaged if a ro ll mode ( HOG NAV NAV APR, REV, REV APR) 1s already engaged With a roll mode engaged and the aircraft al the desired altitude, press the ALT mode selector switch to engage the altitude hold mode The ALT annunc1at1on will appear as shown in Fig 3-7 to acknowledge that this mode 1s engaged The autopilot will hold the aircraft at ,ts current (cap tured) absolute pressure altitude This altitude may be modified for barometnc pressure changes . by pressing and holding either the UP sw itch for an increase in altit ude or the DN switch for a decrease rn a l titude The altitude changes 20 feet for each second the respective switch 1s pressed and held The range 1s .t200 feet from the on9 1nal c:aptured altitude 3rd Ed Jun 30 07 3-7 ( S-TEC Fi g. 3-7. AP Display, HOG a nd ALT HOLD Mod es Engaged 3. 1.4 Ve rtic a l Spee d (VS) Mod e Ca ution : n, e vertical sp eed mode is u sed to esta blis h and hold a PILOT sel ec t ed vertica l s peed . Since th e autopilot re ceives no airspeed information, it is th e responsibility of th e pilot to e nsure that th e vertical speed sel ec tion is w ithin the operatin g limits of the aircraft's capabilities. Se lection of a vertical s p ee d be yond th e capa bility of the aircraft ca n create a condition of reduced airspeed, a nd possib ly l ead to a sta ll conditio n. The vertical speed mode can only be engaged 1f a roll mode (H OG, NAV, NAV APR, REV. REV APR) 1s already engaged . With a roll mode engaged and the aircraft at the desired vertical speed, press the VS mode selector switch to engage the vertical speed mode. The VS annunciation will appear as shown in Fig. 3-8 , to ack n owledge that this mode 1s engaged . The autopilot will hold the ai rcraft at ,ts current (captured) vertical speed . This vert i cal speed may be modified by pressing and ho l ding either the UP switch or the DN switch In a climb, pressing and holding the UP switch increases the climb rate whereas pressing and holding the ON switch decreases the c limb rate In a descent. pressing and holding the ON switch increases the descent rate whereas pressing and holding the UP switch decreases the descent rate The vertical speed changes 160 FPM for each second the respective switch is pressed and held The range is ±1600 FPM from the original captured vertical speed During a climb, should the aircraft become unable to hold the captured vertical speed for a period of fifteen seconds. the VS annunc1at1on will flash as an alert to the potential for an impending stall condit ion In that event. immediate ly increase the aircraft's thrust 1f possible. reduce the commanded vertical speed using the DN switch or both until the VS annuncratron stops flashing 3-8 3rd Ed Jun 30 . 07 Fig. 3-8. AP Display, HOG a nd VS Mod es Engaged 3.1.5 Elevator Trim 3. 1. 5.1 M an ual Ele vator Trim S- TEC If the autopilot Is not eq uipped with autotrim, or Is so equipped but the Trim Master Sw itch 1s in the OFF position, and a pitch mode (A LT HOLD , VS, GS) Is en gaged , then the a ut opilo t will provide an an nun ciation whenever ii is necessary to manually 1nm the aircraft abo ut the p itch axis using the Elevator Tnm Wheel Sho uld lhe pitch servo loading exceed a preset threshold for a period of three seco nds, the TRIM annunciatio n wi ll appear as shown in Fig 3-9. and either the UP or ON _swit ch l amp will Illum111ate , as a prompt to trim the aircraft in the 1nd1ca ted direction In addition an audible alert will sound a steady tone If no ac ti on Is taken after four more seconds, then both the TRIM annuncia ti on and illuminated _switch l amp w ill flash, and the audible alert will become periodic. Once the ai rcraft has been sufficiently tnmmed. such that the pitch servo loading 1s below the pre set thre s hold , the TR IM annunciation and swilch lamp will extinguish, and th e audible alert will be squelched 3.1. 5.2 Automatic Elevator Trim If the autopilot Is equipped w1lh autotrim. the Tnm Master Switch 1s 111 the ON pos1 t 1on and a pitch mode (A LT HOLD VS , GS) Is engaged, then the autopilot will automatically 1nm the aircraft about the pitch axis Should the pitch servo loading exceed a preset threshold f or a period of three seco nd s, lh e trim servo will become ac tive, and so the Elevator Tn m Wheel will run e ither nose up or nose d own with increas ing speed O nce the aircraft has been sufficiently trunrned, such that the pitch servo loading Is below the preset threshold . the trim servo will b ecome inacti ve and so the Elevat or Trim Wheel will stop 3rd Ed Jun 30 07 3-9 ( ( ( S- TEC Fig . 3-9. AP Display, Manual Trim Prompt 3.1 .5 .3 Manual El ectric El evator Trim If t he au t op il ot Is equipped w ith au totr im , then th ere wi ll also be the Manu al Electric Trim Switch located on the Control Wheel This switch can be used to trim the aircraft about the pitch axis from the ROY. or when only a roll mode (HOG. NAV, NAV APR , R EV, REV APR) Is engaged, prov id ed that the Tnm Master Sw itch Is m lhe ON position. To tnm the aircraft nose up, pr ess aft and hold both segments of t he Manual Electric Trim Switch The TRIM annunciation will appear flashing as shown m Fig 3-10 and lh e El evator Trim Wh ee l will run nose up at full speed Upon release of this switch, the TR IM annunciation will extinguish and the Elevator Trim Wh ee l will stop ro trim the a ircraft nose down, press forward and hold both segments of the Manual El ec tric Tnm Swi tch. The TRIM annunciation will app ear flashing r1s shown In Fig 3-10 and the Elevator Trim Wh ee l will run n ose down at full speed Upon release of this swi tch, the TRIM an nun cia t ion will ext111gu1sh and the Elevator Trim Wheel will stop Should the Manual El ectric Trim Switch eve r be actuated wh en a pitch mode (ALT HOLD , VS, GS) Is engaged, the autopilot will disconnect 3-10 3rd Ed Jun 30 07 F ig. 3-10. AP Display, Manual El ectric Trim in Progress 3.2 Precision Approach Procedures 3.2.1 Straight- In ILS Approach S- fEC Execute a straight- in intercept and track of the FRONT INBOUND LOC course (reference section 3.3.3), while holding th e approach altitude. The NAV. APR. ALT, CAP and SOFT annunciations w, 11 appear as shown in Fig 3- 11 F ig . 3- 11 . AP Disp lay, NAV APR and ALT HOLD Modes Engaged 3rd Ed Ju n 30 07 3- 11 ( S-TEC Once the following conditions have existed simultaneously for a penod of ten seconds. the GS annunciation will appear to acknowledge that th e ghdeslope mode has automatically armed, as shown in Fig. 3-12: NAV APR mode en gaged 2 ALT mode engaged 3 NAV Flag out of view 4 GS Flag out of view 5 LOC frequency selected 6 NC within 50% COi needle deflection of Loe · centerline 7 NC more than 60% Ghdeslope Deviation Indication (GDI) needle deflection below GS centerline If the last condition cannot be met because the aircraft 1s too near the GS centerline. then manual arming of the ghdeslope mode can be instantly achieved by pressing the ALT mode selector sw itch. The armed ghdeslope mode can be subsequently disabled by pressing the NAV mode sel ector switch The GS annuncia tion will flash , and the DSABL annunc1at1on will appear to acknowledge this. as shown in Fig. 3-13 To then re -arm the ghdeslope mode, press the NAV mode selector switch again. The GS and OSABL annunc1at1ons will immediately extinguish , but the GS annunciation will re-appear after ten seconds With the glideslope mode armed, once the aircraft arrives at 5% GDI needle deflection below the GS centerline the ALT annunciation will ex tinguish to indicate engagement of the glideslope mode. as shown in Fig 3-14 Note: If the approach positions the a ircraft slightly above UIe GS ce nterline, then manual engagement of the glides/ope mode can be instantly achieved by press ing the ALT mode se l ector s witch . Caution: Manual e ngagement of th e glides /ope mode above the GS ce nterlin e wlll resu lt in the aircraft moving aggressive ly toward the GS centerline. Do not manually engage the glides/op e mode if GD/ needle deflection is greater than 10% above the GS centerlin e. The GS annunc,ation will flash whenever GD I needle deflection exceeds 50% or the GS Flag ,s in view In the latter event. the FAIL annunc,auon will also appear At the Decision Height (D H). disconnect the autopilot to execute either a landing or go-around (GA) A p1ctonal of lh1 s procedure 1s shown 1n Fig 3-15 3- 12 3rd Ed Jun 30 07 S- TEC ( Fig. 3-12. AP Dis pl ay, NAVAPR a nd ALT HOLD Modes Engaged, GS Mode Armed Fig. 3- 13. AP Display, NAV APR a nd A LT HOLD Modes Engaged, GS Mode Disabled ( ( 3rd Ed Jun 30 07 3-13 S- TEC Fi g. 3-14. A P Dis pl ay, NAV APR a nd GS Mod es En ga ged \( GS Intercept ecision Height (OH) - -~ - - - - ~ - ':== -;;;;;::_......_..]t._._ Fi g. 3-15. S trai gh t-In ILS Appro ach 3.2.2 ILS A pp roac h with P roce dure T urn Execute a procedure turn intercept and track of the FRONT INBOUND LOG co urse (refere nce section 3 3.5) above the approach altitude , Just until the aircraft Is established on the FRONT INBOUND PROCEDURE TURN heading, with the heading mode still engaged Establish the desired vertical descent s peed . and then press the VS mode selector switch to engage the vertical speed mode Upon reaching the approach al titude , pres s the ALT mode se lector sw itch to enga ge the altitude hold mode. Press the NAV mode selector sw itch to engage the navigation approach mode , such that the autopilot will exec ute a s tra1ght- 1n intercept and track of the FRONT INBOUND LOC course (refere nce section 3 3 3). Execute a straight- in i ntercept and tra ck of the ghdeslope (reference section 3 2 1) 3- 14 3rd [d Jun 30 07 3.3 Non-Precision Approach Procedures 3.3.1 Straight-In Back Course Approach Select the LOC frequency on the Navigation Receiver Heading System I ISi Set Course Pointer to FRONT INBOUND LOC course on compass card Heading System DG Set Heading Bug to BACK INBOUND LOC course on compass card S- TEC Press the REV mode selector swi tch lo engage the reverse approach mode. fhe REV and APR annunciations will appear as shown in Fig 3- 16. to acknowledge I that this mode is engaged The autopi l ot will in tercept and track the BACK INBOU ND LOC course To ensure that 1t has sufficient overall authority, the autopilot will track this course in the CAP SOFT condition which Is acknowledged by the appearance of those respecllve annun c1at 1ons as s ho wn m Fig 3- 17 If the heading system is a DG, then the autopil ot will fly the aircraft 1n the direction opposite to th at of CD I needle deflection The REV annunciation will flash whenever CD I needle deflection exceeds 50%, o r the NAV Flag 1s m view. In the latter event. the FAIL annunc iallon will also appear A summary pictorial of this procedure 1s shown in Fig. 3- 18 Fig. 3-16. AP Displa y, REV APR Mode Engaged, Before LOC Back Course Intercept 3rd Ed Jun 30 . 07 3- 15 / I S- TEC Fig. 3-17. AP Display, REV APR Mod e Engaged, Track LOC Back Course I nbound L ~ Back Course _+ - y - ~ ----.___ f X'a Select LOC frequency. b Head1 □ g System HSI Se t Co urse Pointer to FRO NT INBOUND LOC course Heading System DG Set Heading Bug to BACK INBOUND LOC co urse c. Press REV mode selector switch to engage reverse approach mode d Intercept and track BACK IN BOUND LOC course Fig . 3-18 . Straight- In Bac k Course Approac h 3 16 3rd Ed Jun 30 07 S-TEC 3.3.1.1 Pil ot Selecta ble Intercept Angle To s~lect an intercept angle, se t the Heading Bug to the desired intercept heading on the compass card, such that the difference between this heading and the BACK IN BOUND LOC course is the intercept angle If the heading system 1s an HSI, se t the Course Pointer to th e FRONT INBOUND LOC course on the compass card. Press and hold the HDG mode selector switch. and then press the REV mode selector switch to engage the heading mode a nd arm the reverse appr.oach mode The HOG. REV, and APR annunciations will appear as shown 1n Fig 3-19 to acknowledge this The autopilot will establish th e ai rcr aft on 11,e selected intercept angle (headin g) until it must turn th e aircraft onto the BACK INBOUND LOC course to prevent overshoot At that poi nt in the intercept sequence, the HDG annunciation w,11 extinguish to 1nd1cate engagement of the reverse approach mode At the 1 moment this occu rs, if the heading system 1s a DG. immediately set the Heading Bug to the BACK INBOUND LOC co urse. in order to input a course error to the autopilot Otherwise, the autopilot will lack sufficient au th ority to turn the aircraft onto the course. Fig . 3-19. AP Display, HOG M ode Engaged, REV APR Mode Arm ed 3rd Ed Jun 30 07 3-17 ( S TCC 3.3.2 Back Course Approa ch w ith Proced ure Turn Select the LOC frequency on th e Nav,gahon Receiver. Heading System HSI Set Course Pointer to FRONT INBOUND LOC course on compass card Headrng System DG Set Heading Bug to FRO NT INBOUND LOC course on compass card Press th e NAV mode selector switch to engage the navigation ap proach mode The N~V and AP_R annunciations will appear as shown in Fig 3--20, to acknowledge that this mode 1s engaged The au topilot will intercept and track the BACK OUTBOU ":'D LOC course To ens ure that 1I has sufficient overall auth ority, the autopilot will track this course 1n the CAP SOFT condillon , which 1s acknowledged by the appearance of those respecltve annunc,altons as shown 1n Fig 3-21 At th e appropriate lime , se t the Heading Bug to the BACK O UT BO UND PROCEDURE TURN heading, and th en press th e HDG mode selector switch to engage t~ e heading mode. Hold this heading until the point at which it is time to turn the a ircraft again. At that point turn the Heading Bug in two successive 90° increments, to est ab lish the aircraft on the BACK INBOU ND PROCEDURE TURN heading Heading System HSI Course Pointer remains unchanged on compass card Headrng System DG Set Headrng Bug to BACK INB O UND LOC c our se on compass card Press th e REV mode se lec tor sw itch to engage the reverse approach mode. The R ~V and AP_R annunciations will appe~r as shown in F ig. 3- 22 , to acknowledge t hat th,s mode 1s engaged The autopilot will mterce pl and track the BACK INBO_UND LOC co_urse To ensure th at it has suff ic ient overall authority, the autopilot will track th is course 111 the CAP SOFT condition, which ,s acknowledged by th e appearance of those respective annunc,allons as shown in Fig 3-23 If the hea din g system ts a DG. th en the autopilot will fly the aircraft in the direction opposite to that of CD I needle deflection A summary pictoria l of this procedure 1s shown 1n Fig 3- 24 3 18 3rd Ed Jun 30 , 07 S- TEC S rEC ( Fig . 3-20. AP Disp lay, NAV APR Mode Engaged, Before LOC Back Course Inter cept Fig. 3- 22. AP Display, REV APR Mode Engaged, Before LOC Back Course Intercept Fig . 3-21. AP Disp lay, NAV APR Mode Engaged, Track LOC Back Course Outbound Fig . 3-23 . AP Display , REV APR Mod e Engaged , Track LOC Back Course Inb ound 3rd Ed Jun 30 07 3-19 3-20 3rd Ed Jun 30 . 07 S- TEC BaekCoutM ' ........ a Se le ct LOC frequency. b Heading System HS I Set Course Pointer to FRONT INBOUND LOC course. Heading System PG Set Heading Bug to FRONT INBOUND LOC course c Press NAV mode se lector switch to engage navigat io n approach mode d In te rcep t and track BACK OUTBOUND LOC course. 2 a At appropriate time, set Heading Bug to BACK OUTBOUND PROCEDURE TURN heading. b. Press HOG mode se lector switch to engage heading mode. 3 a. Turn Hea ding Bug in two successive 90~ increments, to establish aircraft on BACK INBOUND PROCEDURE TURN headi ng b Heading System HSI Co urse Pointer remains unchan ged. Heading System DG Set Heading Bug to BACK INBOUND LOC course c. Press REV mode selector switch to engage reverse approach mode. d Intercept and track BACK INBO UND LOC course Fig. 3-24 . Back Cou r se Approach with Proced ur e Turn 3rd Ed Jun 30 07 3-21 STEC 3.3.3 S trai g ht-In LOC Approach Sel ec t the LOC frequency on the Nav1gat1on Receiver Head ing System HSI Set Course Pointer to FRONT INBOUND LOC co urse on compass card Heading System PG Set I l eading Bug to FRO NT IN BOU N D LOC course on compass card P1ess the NAV mode sel ec tor switch to engage the navigation approach mode The N AV a nd APR annuncia tions wi ll appear as s hown in Fig 3 25 to acknowledge that this mod e is e ngaged Th e au t opi l ot wi ll intercept and track the FRONT INBOUND LOC course . To ensure that it ha s sufficient overall authority, th e autopilot will track th is course 1n the CAP SOFT condition. which 1s acknowledged by th e a ppearance of tho se respective annunciations as shown in Fig 3-26 A sum mary pictorial of this proce dure is shown 1n Fig 3-27. Fig . 3-25. AP Di splay, NAV APR Mode Engaged, Before LOC Front Course Inte rcept 3-22 3rd Ed Jun 30 0 7 S- TEC F ig. 3-26. AP Dis pl ay, NAV APR Mod e E ng aged, Track LOC Fro nt Course Inbound ..... - - - - a Select LOC frequency b Heading System HSI Se t Course Point er to FRONT INBOUND LOC co urse Heading System PG Se t Heading Bug to FRO NT INBOUND LOC co urse ... c Press NAV mode selector switch to engage nav1gat1on approach mode • d Intercept a nd track FRONT INBOU ND LOC course 2 a At middle marker 1f mi ssed ap proach 1s declared di sconn ec t autopilot b Stabilize aircraft c Se t Heading Bug to missed approach heading d Press I IDG mode selector switch to engage heading mode Fig. 3- 27 . Str aig ht-In LOC Approach 3rd Ed Jun 30 07 3-23 S TCC 3. 3.4 Straight -In VOR Approach Se l ect Lh e VOR frequency on the Nav1gallon Receiver. Heading System HSI Se t Course Pointer to FRONT INBOUND VOR course on compass card Heading System DG Set I leading Bug and OBS to FRO NT INBOUND VOR co urse on eac h 1especllve co mpass card Press the N AV mode selector switch to engage the navigation mode The NAV annunc1at1on will appear as shown in Fig 3-28, to acknowledge that this mode ;s engaged The a utopilot will intercept and track the FRONT INBOUND VOR course It will track this course in the SOFT condi ti on, which is acknowledged by th e a pp earance o f that an nun c1at1o n and the ex tingui shme nt of the CAP annunc1at1on. as shown in Fig. 3-29 A summary pictorial of this procedure 1s shown in Fig 3--30 F ig . 3-28. AP Display, NAV Mod e E ngag ed, Before VOR Front Course Intercept 3 2 4 3 rd Cd Jun 30 07 S TCC F ig . 3-29. AP Dis p l ay, NAV Mode E ngag ed, Trac k VOR F ront Cou rse Inbound a Select VOR frequency b Headmq System HSI Set Course Pointer to FRONT INBOUND VOR cou rse Heading System DG Set Heading Bug and OBS to FRO NT INBOUND VOR course c Press NAV mode selector switch to engage navigation mode d Intercept and track FRONT INBOUND VOR course ... . 2 a At middle marker, 1r missed approach 1s declared disconnect autopilot b Stab1hze aircraft c Set Heading Bug to missed approach heading d Press HOG mode selector switch to engage heading mode Fig . 3-3 0. Stra ight- In VO R Approac h 3rd Ed Jun 30 07 3-25 S-TEC F ig. 3-31. AP Display, REV APR Mode Engaged, Before LOC Front Course Interc ept F ig. 3-32. AP Dis play, REV APR Mode Engaged, Track LOC Front Course Outbound 3rd Fd Jun 30 07 3-27 S- TEC 3.3 .5 LOC Approach with Procedure Turn Select the LOC frequency on the Navigation Receiver Heading System HSI Set Course Pointer to FRO NT INB OU ND LOC course on compass card H eading System DG Se t Heading 0ug to BAC K IN BOU ND L OC co urse on compass card Press the REV mode selector sw itch to en gag e the rever se approach m ode rhe REV and APR annunciations will appear as shown in Fig 3-3 1. to acknowledge that this mode Is enga ged Th e au topilot will interce pt and track the FRONT O UTBOUND LOC course. To ensure that 11 ha s su fficient overall au thority, the autopilot will track this course in the CA P SOFT condi ti on, which Is acknowledged by t he appearance of those respective annun ciations as shown in Fig 3- 32 . If the heading system Is a OG, then the au topilot will fly the aircraft 111 the direction opposi te to th at of CO i needle deflection A l the appropriate time , se t t he H ea ding Bug to th e FRONT OU T BO UN D PROCEDURE TURN heading. and then pr ess the HOG mode se lector switch to engage the heading mode. Hold this heading until the point at which 1t is time to turn the aircra ft again At that point, turn the Heading Bug in two successi ve 90° increments . to establish the aircra ft on the FRO NT INB O UND PROCEDURE TURN heading H ea ding System HSI Co urse Pointer remains unchanged on compass card H ead ing System DG Set H eadr ng Bug to FRO NT INB O UND LO G co ur se o n compass card Press th e NAV mode se l ec tor sw itch to enga ge the navIgat1on approac h mod e The NAV and APR annu nc IatIon s wil l ap p ear as shown in Fig 3- 33 to ack no wl ed ge that this mode Is e ngaged The autop il o t will intercept and track the FRONT INBOUND LOC course To ensure that 11 has sufficient overa ll authority, the autopilot will track this course in the CAP SOFT conditmn , which Is acknowledged by the appearance of those respective annuncIa tI ons as shown In Fig 3- 34 A summary pictorial of this procedure Is shown In Fig J 35 3 26 3rd Ed Jun 30 0 7 S- f EC F ig . 3- 33. AP Display, NAV APR Mode Engaged, Before LOC Front Course Intercept Fig. 3-34. AP Display, NAV APR Mode Engaged, Track LOC Front Course Inbound 3- 28 3rd Ed Jun 30 . 0 7 a Select LOC frequency b Heading Sys tem HSI 1 N I 3to" --- -0- Set Course Pointer to FRONT IN BOUND LOC course Headi ng System DG Set Heading Bug to BACK INBOUND LOC course S- TEC c. Press R EV mode selector switch to engage reverse approach mode d Intercept and track FRONT OUTBOUND LOC course. 2 a At appropriate time, set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading. b Press HOG mode se lector switch to engage heading mode 3 a Turn Heading Bug in two successive 90 ' increments. to es tablish aircraft on FRONT INBOUND PROCEDURE TUR N heading 4 a Heading System HSI Course Pointer remains unchanged Heading System DG Set Heading Bug to FRONT IN BOU ND LOC co urse b Press NAV mode selector switch to engage navigation approach mode c Intercept and track FRONT IN BOUND LOC course d At middle marker 1f mis sed approach 1s d eclared disconnect autopilot e Stab1 h,e aircraft Set Heading Bug to missed approach heading g Press HOG mode se lec tor switch to engage hea ding mode Fig. 3-35. LOG Approac h with Proce dure Tu rn 3rd Ed Jun 30 0/ 3-29 ( \ ( S- TEC 3.3.6 V OR Appr oac h w i th Proc e dure T urn Se lect the VOR frequency on the Navigation Receiver H ead ing System HSI Se t Course Pointer to FRONT I NBOUND VOR course on compass card H eading System DG Se t Heading Bug and OBS lo BACK INBOUND VOR co urse on each respective co mp ass card Press the REV mode sel ector switch to engage the reverse mode The REV annunc1at1on will appear as shown in Fig. 3-36, to acknow le dge that this mode ,s engaged The autopilot will inter cept and track t he FRO NT OUTBOUND VOR co urse It will track this course in the SOFT cond1t1on , which 1s acknowledged by the appearan ce of that annun c1at1011 and the ex tingu1 s hment of the CAP annuncia ti on, as shown 111 Fig 3-37 At the appropriate time. set the Heading Bug to the FRONT O U TBOU ND PROCED URE TURN heading, and then press the HOG mode selector switch to engage the heading mode. Hold this heading until the point at which it is time to turn the aircraft again. At that point , turn t he Heading Bug ,n two successive 90 ° increments. to establish the aircraft on the FRONT IN BOUND PROCEDURE T URN head111g Heading System HSI Course Pointer re mains unchanged on compass card Head,og System PG Set Headi ng Bug and OBS to FRO NT IN BOUND VOR co u rse on each respective compass card Press the NAV mode sel ec tor switch to engage the navigation mod e The NAV annunciation will appear as shown in Fig. 3-38 to acknowledge that this mode 1s engaged The autopilot will intercept and track the FRONT INBOUND VOR course . It will track this course 1n the SOFT condition, which 1s acknowledged by the appearance of that annunciation and the ext111gu1shment of the CAP annunc1at1on. as shown 111 Fig 3-39. A summary pictorial of this proced ure 1s shown in Fig 3-40 3-30 Jrd Ed Jun 30 07 S- TCC STEC Fig . 3-36. AP Display, REV Mode Engaged, Before VOR Front Course Intercept Fig . 3-38. AP Display, NAV Mod e Engaged, Before VOR Front Course Intercept Fig. 3-37. AP Display, REV Mode Engaged, Track VOR Front Course Outbound Fig . 3-39. AP Disp lay, NAV Mode Engaged , Track VOR Front Course Inb ound 3rd Ed Jun 30, 07 3- 31 3-32 3rd rd Jun 30 07 a Select VOR frequency b Heading System HSI , "I 310" - - -0- Set Course Pointer to FRONT INBOUND VOR course I leading System DG Set Heading Bug and OBS to BACK INBOUND VOR course c Press REV mode selector switch to engage reverse mode d Intercept and track FRO NT OUTBOUND VOR course S- TEC 2 a At appropriate time. set Heading Bug to FRONT OUTBOUND PROCEDURE TURN heading b Press HOG mode selector switch to engage heading mode 3 a Turn Heading Bug in two successive 90 · increments, to establish aircraft on FRONT INBOUND PROCEDURE TURN heading 4 a Heading System HSI Course Pointer remains unchanged Heading System PG Set I leading Bug and OBS lo FRONT INBOUND VOR course b Press NAV mode selector switch to engage navI9atIon mode c Intercept and track FRONT INBOUND VOR course d At middle marker. 1f missed approach Is declared, discon nect autopilot e Stabilize aircraft Set Heading Bug to missed approach heading g Press HOG mode sele ctor switch to engage heading mode Fig. 3-40. VOR Approach with Procedure Turn 3rd Ed Jun 30 07 333 S - TEC 3.4 Flight Director Operation The optional Flight Director (FD) is a display of the flight profile It Is commanded by th e autopilot A pair of Steering Command Bars and an Aircraft Reference Symbol (ARS) are the principal FD components of interest The posIlion of the Steering Command Bars can be ad1usted by the pilot using the Parallax AdJustment shown in Fig 3-4 1 The FD operates In e1the1 the rO/AP mode or the FD mode FD PUC ADJ Fig. 3-41 . FD Para ll ax Adju stment 3.4.1 FD/AP Mode Set the Autopilot (AP) Master Switch to the ON posItIon, as shown in Fig 3 42 The position of the FD Master Switch does not matter The FD annunciation will appear as shown in Fig 3-43 , to acknowledge th at the FD Is powered up [ngage a roll mode (HOG NAV, N AVAPR, REV, REV APR) and a pitch mode (ALT HOLD. VS , GS) The autopil ot will steer the aircraft toward the Steering Command Bars. until the ARS is tucked into them The ro provides a visual ind1cat1on of how accurately the autopilot Is tracking its own roll and pitch commands A typical view of the FD with the FD/AP mode engaged Is shown In Fig 344 ON OFF TEST Fig. 3-42 . AP Ma s ter Switc h in ON Position 3 .34 3rd Ed Jun 30 0 7 S- TI C ( Fig. 3-43. AP Display, FD Powered - Up Fig . 3-44. FD Display, FD/AP Mode Engaged ( 3rd Ed Jun 30 07 3 35 S- l lC 3.4 .2 FD Mode W ith a ro ll mo de (H DG NAV, N /\V /\P R REV, RCV A P R) and a pitch mode (ALT HOLD VS GS) engaged, set tho FD M aster Switch to the ON position as shown 1n Fig 3-45 Set t he AP M aster Switch to the OFF pos1t1011 . as shown in Fig 3-46 This disengages both the roll servo and pitch servo although the prev iously engaged roll mode and pitch mode annunciations will still appear on the AP display along w it h the FD annunc1a t1 011 The pi lot must st eer the aircraft toward the Steenng Command Bars until the ARS 1s tucked into them The FD prov ides a visual 111 d 1cat 1on of how accurately the pilot 1s tracking the autopilot's roll and pitch commands A typical view of t he FD w ith the FD mode engaged 1s shown 1n rig 347 ON OFF Fig . 3-45 . FD Master Switch in ON Position Fig . 3-46. AP Master Switch in OFF Position F ig . 3-47. FD Dis pl ay, FD Mod e E ngaged 3 -36 3rd Ed Jun 30 07 S- TEC 3.5 Yaw Damper Operation The optional Yaw Damper serves to dampen excessive adverse yaw. It operates In eith er th e AUTO mode or ON mode. depending upon the position of the Yaw Damper Master Switch shown in Fig 3-48. AUTO H I~OFF ON Fig. 3-48. Yaw Damper Ma ste r Switch The Yaw Damper Trim Knob shown in Fig. 3-49 Is used to center the shp/sk1d ball when the yaw servo Is engaged Fig. 3-49. Yaw Damper Trim Knob 3.5.1 AUTO Mode With the Yaw Damper Ma ster Switch in the AUTO position, the yaw servo will become automatically engaged whenever a roll mode (HOG NAV, NAV APR , REV, REV APR) is engaged 3.5.2 ON Mod e With the Yaw Damper Master Switch in the ON position, the yaw servo will be ( engaged at all times. en tire ly independent of autopilot operation 3.5 .3 Yaw Damper Trim With the yaw servo engaged. rotate the Yaw Damper Tnm Knob to center the shp/sk 1d ball 3rd Ed Jun 30 07 3-37 S- TEC 3.6 Autopilot Disconnect The autopilot can be disconnected by any of the following means Press AP DISC/ rR IM IN TR Switch typically located on Con trol Wheel 2 Press either forward or aft on both segments of Manual Electric Tnm Switch l ocated on Control Wheel , whenever a pitch mode (ALT HOLD . VS , GS) Is engaged 3 Set AP Master Switch to OFF position 4 Pull AP Circuit Breaker 3.7 Automatic Trim Disable In the event of a tnm runaw ay. the automatic trim function can be di sabled by execu ting the following se q uence Press/Hold AP DISC / TRIM INTR Switch typically located on Control Wheel 2 Set Tnm Master Sw itch to OFF position 3 Pull Tnm C 1rcu1 t Breaker 3-38 3rd Ed Jun 30. 07 SECTION 4 OPERATING PARAMETERS 3rd Ed Jun 30 07 S- IEC 4- 1 ( ( S-TEC Page Intentionally Blank 4-2 3rd Ed Jun 30 07 4.1 Roll Axis Limi ts Turn Rate Piston A/C 90% Standard Rate Turn (HOG, N AV. NAV APR. REV. REV APR Modes) Turboprop A/C 75% Standard Rate Turn (HOG N/\V. NAVAPR . REV REV APR Modes) AIIA/C 4.2 Pitch Axis Limits 32,000 FT Vertical Force Due to Acceleration 060 g Vertical Speed 1600 FPM Climbing or Descending ~ S-TEC A pitch mode (ALT HOLD . VS , GS) can only be engaged after a roll mode (HOG. NAV, NAVAPR , REV. REV APR) has been engaged 3rd Ed Jun 30 , 07 4-3 3rd Ed Jun 30 07 SECTION 5 GLOSSARY S- TEC 5-1 S- TEC S- TEC ( ( Page Intent ionally Blank lil.ag&-I Atem10Aall~ G l O.SS/1 IJ.. 'I ( f 4 -4 3 rd Ed Jun 30 , 07 3rd Ed J un 30 , 07 Term A/C ADJ ALT AP APR ARS CAP ccw COi CRS cw DG DH DISC DSABL FAA FD FPM FT Q\ GDI GS HOG HSI IFR ILS INTR KTS LOC MAP NAV NM OBS PFGC PLX PN POH ROY REV RFGC SEL \IMC VOR vs YD 3rd Ed Jun 30 07 Mea ning Aircraft Adjustment Altitude Autopilot Approach Aircraft Reference Symbol Capture Counter- Clockwise Course Deviation Indication Course Clockwise Directional Gyro Decision Height Disconnect Disable Federal Aviation Adm1nistrat1on Flight Director Fee t- per- Minute Feet Go Around Glideslope Deviation Indication Glideslope Heading Horizontal Situation Indicator Instrument Flight Rules Instrument Landing System Interrupt Knots Localizer Missed Approach Point Navigation Nautical Miles Omnibeanng Selector Pitch Flight Guidance Computer Parallax Part Number Pilot's Operating Handbook Ready Reverse Roll Flight Guidance Computer Selector Visual Meteorological Conditions S- TEC Very High Frequency Omn1d1rectional Radio Range Vertical Speed Yaw Damper 5--3 ( ( Information contained in t his doc u ment is subj ect to change with out notice. © 2007 S-TEC. All rights reserved. Printed in the United States of America . S-TEC and the S-TEC logo are registered trademarks of S-TEC. Notice Contact S- TEC Customer S upport at 800 - 872-7832 for a Return Material Authorization (RMA) number prior to the return of any component for any reason One S- TEC Way Municipal Airpo rt Mineral We lls , TX 76067- 9236 Tel: 800-87 2-7 832 Fa x: 940-32 5-3904 www. s- te c.c om w ww.c obh am.c om S- TEC PN 8783 ( ' ' 5-TEC ~ ff r Pilot's Operating Handbook GPSS .... - ti!tO 11) w 0...,, w S-TEC List of Effective Pages • Asterisk indicates pages changed, added, or deleted by current revision. Record of Revisions Retain this record In front of handbook. Upon receipt of a revision, Insert chanaes and complete table below. Revision Number Revision Date Insertion Date/I nitials 1st Ed. Mar 14 , 00 2nd Ed. Dec 13, 00 3 rd Ed . Jan 14, 02 4 th Ed. Sep 05 , 03 5th Ed. Feb 15 , 08 5th Ed . Feb 15 , 08 ( \ ( I i / ( / ,( ✓ j ( \ S-TEC Page Intention ally Blank ii 5t h Ed . Feb 15, 08