Proposed changes for malfunction procedures symptoms of Guidance and Control System (GC).  Full set.https://scholars.fhsu.edu/apollo/1031/thumbnail.jp

National Aeronatics and Space Administration (NASA)

English

Fort Hays State University

Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures changes - November 11, 1968

Proposed changes for malfunction procedures symptoms of Guidance and Control System (GC); dated February 4, 1969. Full set.https://scholars.fhsu.edu/apollo/1032/thumbnail.jp

Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures changes - March 1, 1968

Proposed changes for malfunction procedures symptoms of Guidance and Control System (GC); diagrams designed by Massachusetts Institute of Technology (MIT). Dated May 25 - 29, 1968.https://scholars.fhsu.edu/apollo/1033/thumbnail.jp

Fort Hays State University FHSU Scholars Repository Apollo One Investigation Materials Cosmosphere Collection 5-29-1968 Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures change - May 1968 National Aeronatics and Space Administration (NASA) Follow this and additional works at: https://scholars.fhsu.edu/apollo Recommended Citation National Aeronatics and Space Administration (NASA), "Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures change - May 1968" (1968). Apollo One Investigation Materials. 34. https://scholars.fhsu.edu/apollo/34 This Document is brought to you for free and open access by the Cosmosphere Collection at FHSU Scholars Repository. It has been accepted for inclusion in Apollo One Investigation Materials by an authorized administrator of FHSU Scholars Repository. .:;c ( _;_") r-l ~ f r-l ~-0 -..... ~ r-l E-l -....-~ H -· ~ .,c e::: C) 5 G&N CMC RED· Lighted in STBY and OPR modes by: Prime power failure or Scaler foi lure . Lighted for 5 sec in STBY or OPR modu ·by repeated (>0. 9 pps) issuance of counter foi lure or double / frequency scoler foi lure. Lighted for 5 sec only in OPR mode by repeated ( >0, 4 pps) restarh . Restart is caused by: RUPT LOCK TC TRAP OSCILLATOR FAIL PARITY FAIL NI GHT\oV A TCHMAN or VOLTAGE FAIL. Lighted for S sec only in STBY mode by repeated (>0. 9 pps)issuonce of VOLTAGE FAILURE of + 28v , + 14v , or + 4v power supplies. -2J • SC CONT - YES 2 I Power up NO scs ~ • Perform C MC CMC in stby? power .up NO Can CMC be powered up? YES ___ ......_ __ NO ~ CMClt on continuously? YES 7 j Input chan ck ev11 Nl0E 33E 8 I i----------1 YES ..:..J DSKY operational?--. 0, 1, 4 , Sin Rl? ,-YES NO cp ~ CMC FAILED NO 'q)q) l.!..!J C/W FAILED O R CMC LT RELAY ON DSKY FAILED CLOS Eu cp 2.J CMC FAILED w Any DSKY status It on? YES PROG It on? NO ~ • YES ~ Display ALM code •vs N9E YES •Perform action for I-------..,. displayed alarm RESTART it on? 121 CMCselfck • Perform CMC self cp ck (SSR-1) 131 . --------iNO .;,.:.i Self ck OK? ~ CMC FAILED YES ~ CMC lt(s) still ON? YES l cl Scaler foi I ck •vis NiOE • 3E E<» RI changes ·every S sec? ~YES YES cp 0 1151 NO ~ TRANSIENT __, MALFUNCTION cp NO -G&N 9 1 RESTART 0 0 0 0 0 0 0 All CMC . This Rl re CMC FAIL sig,ol to C~. Subsequent CMC malfunction indication from uncrffectad CMC light. If the LEB CMC It. is on, all gyro to<quing and PIPA capa-bili ty lost . CMC monitor and control of bot+. TVC and Entry lost. If DSKY will not accept inputs, force a restart by simultane-ously pressing RESET and MARK REJECT pb's. Tronsient condition could hove existed in eittier OK. or C/W system. Complete identification of subsequent foi lures impossi-ble. Poma.I identification from DS KY status I ights. @ "The ~MC. -1 b~ used "t_o ~"- ~)d:«-nt 1n,bc.c,+~ ;-., -th.~ C,DIAl'\ter c.,1-\e.c.k.1 ss R.- 4. MIT 101-FOR MAY 27 ,968 TRW A;_9() 25 May 1968 Comments on AOH Change# CSM 879 Reference: AOH Change CSM-879, Malfunction Procedure Upiate for SC 101, dated 9 May 1968. · The following coIIDnents are provided on the reference malfunction procedures: J - 1. On sheet with G&C #1, in box 3 it is unnecessary to select POO before starting P40. In boxes 9 and 11, only a value of 2 should be seen in C of channel 12 (i.e. bit 8 should equal 1, with bits 9 'arid 7 both 0). Bit 9 is assigned for S4B Takeover; bit 7 is not assigned at all • .J-- 2. On sheet with G&C #2, in box 12 V43E can be selected only in POO: a similar entrance to POO is indicated explicitly in several other places. J- 3. On sheet with SCS #2, in box #2 the +ROLL and -ROLL bit patterns are reversed with respect to the definitions conventionally used. Same connnent applies to next sheet (with SCS #3, in box #12). Shown correctly e.g. in box #6 on sheet with SCS #4. · . .--- 4. On sheet with G&N #1, it might be appropriate to specifically set RCS ·;:> 11 1. ✓<utput channels to Oby going through a V37 (or V99E). If, for example, ~ l ~s-1t? off IMU suddenly, then jets would re.main on due to design of software, not .due ' b to any hardware failure. See page 3.2-7 of Section 3 of Sundisk DAP GSOP. Same -po thing could happen if select 11no73KP11 via V46 from an automatic mode, under which RCS jets were being timed under control of jet selection logic (especially if translations also taking place). ,;I .:fl ~..-,,.5. On sheet with G&N #6, list of items in left column causing PIPA fail J V sh oul ention 312.5 microsec, not 312.2; should also mention 3.84 seconds, not 3 .8 seco List of items causing IMU fail should refeJ,;jiiiti4~~200 -pps power, not ,_ 600 .PPS power. or ICDU, angle generally referenced as ~ - i.e. phi, not psi) • p 6. On sheet with G&N , misleading, since alarm 002058) ~ rated o(y when Average-G is running, and 00211 only in a coarse align ia i outine as shown with this alarm code several p~ges later). vJ ?. On sheet with G&N #10, TR~CKER light also turned on if IMU CDU chan~e t oo ~ uch after taking an optics mark (i.e. nothing at all to do with optics CDU) • . -~,;J See PCR # NASA-47 (approved by MSC about 2/20/68), or the discussion of ala rm ·;l,;~ 218 in AOH ap~roved change # CSM-693 • .:.~ 8 . On sheet wi th G&N #10, box #8 might mention that optics coarse align drive .. can be accomplished by V41N91E before loading the indicated values, and that the ,.1 0 .~,:;:a 4.4 presumably should be 11 TRUN11 , not 11 TURN11 • , ~ ,J"9. On sheet with G&N #11, remark #3 at the top is too drastic, since alarms .:-:~ ,, Mi s ~ill be observed by V05N09 means, and the main alarms via normal DSKY :?# dis plays . ~ ✓ 10. On sheet with G&N #12, alann 002058 wo~ ~, occur wll:iJe Average --G is · on: i t appears that fro~ note it ~-- · ~ r also at othe r t imes: see CSM-693. ~ V / 11. On sheet with G&N SSR-1, box #6 Rl contents is the magnitude of the sum oA.fthe contents of the bank (which, by definition of the word displayed in RS, is 3Upposed to be equa 1 to b.1.nv r• 11mh ,r ~ MIT Instrumentation Laboratory PROPOSED SP .ACECRAFT OPERATIONAL PROCEDURES CHANGE INITIATED BY ID A TE Russ Larson · May 28, 1968 CHANGE NUMBER S/C EFFECTIVITY MIT-101-3 101 AOH VOLUME 11 SI C I PAGE NUMBER BASIC OR CHANGE DA TE I TIME OR STEP NUMBER DETAIL CHANGE IN EXACT HANDBOOK WORDING Program Alarm Light ✓ Change Remark 3 to read, "Program alarm light failed on. 0 tL-Program alarm indications available by keying V5N9E, if not displayed as main alarm. II Tracker Lig:ht J A. Add logic for Tracker light coming on with . a MARK and B. Add V41N91 to block~, (see attached) . REASON: Pro9:ram Alarm Light Clarifies remark. Tracker Light A. The Tracker light coming on with a MARK indicates an ICDU transient. B. V41N91 must be keyed in to drive optics. COORDINATION FROM TO DATE FROM TO DATE ~ ~Approved ¥,"''Z''"'' ~ ____ J DA TE - .. ~48'-~~ n Disapproved J ,. r-7 ~~ FINAL DISPOSITION □ FCOD S IGNATURE DATE SIGNED SUSPE NSE DATE Approved □ Di sa pprovecl MSC Form 482 (Jul 67) MT'T' Tn~+-r11mont-.:::1 +- i <,n T.-"lhr,r;:i t-r,rv PROPOSED SPACECRAFT OPERATIONAL PROCEDURES CHANGE INITI ATED BY l°A TE Russ Larson May 29, 1968 CHANGE NUMBER S/ C EFFECTIVITY MT,,,-101-2 101 AOH VOLUME 11 S/ C I p AGE NUMBER I BASIC OR CHANGE OA TE I TIME OR STEP NUMBER • DETAIL CHANGE IN EXACT HANDBOOK WORDING ~ l. ISS Lt - Blk 10 Change "G1('>00029?" To "or ,-> 29 eounts/-min?" (9 ~ J 2. Restart Lt - Blk 1 A:0) Change to read "DSKY blank except status lts?" (:)\L uh~~ J 3. Restart Lt - Blk 2 /4 . Change "Alm 01107 displayed?" To "verify Alm 01107 is di,layed" Alarm Codes - Remark v r1 · Change "Updata must be manually verified loaded" To , Jr- "r' a or ~~~ "Updata must be manually verified." J 5. ~ CMC Self Test - Blk 6 Change "No. of cells" To "Sum of cells" ~ ~ 6 • CMC Jet Re-config - Blks 9 & 12 Change "V21E" To "V241-EII ~ f-REASON: 1. Error 2. To indicate that the verb, noun and program windows are also blank. 3. If a fresh start occurs, 01107 code is stored. 4. It i s not required that this be manually loaded ... 5. Error 6 . V 2♦ must be used to load Rl and R2. COORDINATION FROM TO DATE FROM TO DATE ~ (3""A p p r o v e d ",'/~"""" -- DA TE -., ;J.... ~ -i:z8 n 0 i s a pp r ov ed ~ . .,,,,,,,._L ~~ ) j FINAL DISPOSITION -□ FC DD SIG NA TURE DATE S I GNED SUSP ENSE DA TE Approved □ D1 s ;ippr ov ed ,.-' MS C Fo rm 482 ( J u l 67 ) MIT Instrumentation Laboratory PROPOSED SPACECRAFT OPERATIONAL PROCEDURES CHANGE IN I TIA TED BY l°A TE . Russ Larson May 29, 1968 CHANGE NUMB ER S/ C EFFECTIVITY MIT-101-1 101 AOH VOLUME 11 S/ C IPAGE NUMBER . BASIC DR CHANGE DA TE I TIME DR STEP NUMHR DETAIL CHANGE IN EXACT HANDBOOK WORDING CMC Lt. --Add Scaler check and counter check to procedur e, (see attached) . Add SSR-4 Counter Fail System ~est to procedures, (see attached). REASON: ) If the scaler check i ndicates the scaler h as failed, complete loss of CMC is verif ied . If the counter check indicates which c ounter has failed, powering down that c omponent may extinguish CMC Lt and enable further use of the· CM,C . "-----CO OR DI NA TION FROM TO DATE FROM TO DATE -~ ~ ~ ·Approved '°•'/ D~ NA TUR£ I"") DA TE j' -;2'8-, ~ n Disapproved .-. -.- A ---1~. - ,-~-,--FlNAL DI SPOSITION □ FCOO SIGNATURE DATE SIGNED SUSPENSE DATE Approved □ Disapproved MSC Form 482 (Jul 67) l ~ (. ('Y) I ,---{ 0 ,---{ E-1 H ~ .. ·· . PR,-Lf'\\\fl 1 '\~ r, l1v C. , 1dl•n,\t FOR INFORMAf \ON ONLY 1\.'1,~V ')•,- '1 ::,'.r .. . 'I 4.-.! ...J '- ' ._ :: ✓ to ~ •MC,K.€,rt a.\'\.J •RSI.. T TRACl<ER PrtOC.. L-t. C4 ..... ~ !Yes ,.J • MARK °4"-l" . YHLOW Light on if: Optics CDU foiled c:,"""- d.i...t.r\1'1. · No "f ! Attempt reset •RSET TRACKER It OFF? YES J 1-1 I YES TRACKER It on both DSKYS? NO ?J TRACKER LT RELAY FAILED CLOSED lQ • OPT MODE -MAN TRACKER It on? NO I YES 3 6l • Vl l NlOE, 30E 0, 2, 4or6inCof . Rl? YES TRACKER It off during zero mode? tl •OPl MODE< •V4\N.'3\~-• Locd 8.4° SHAFT ond 4 . 4° TURN-4 • V16 N91E Optics drive to angles locded? NO NO NO U>\ol.h"',,IA -c ',\oym e>r<>-erp.1-lO"\,\ s CMC OUTPUT CHAN FAILED 0 lig~t signific.:int only during optics use. ® iRI\Gl<-eR _ l;~h. t ou .. u...-.s. 1~ o. MAtRk ts "'-"-de @ © ® dv.ri'>I.~ "'-"'- lC'DU tra.'I\St~n t: This Rl readout indicates an OCDU foi led. Tracker a'::normol indicotians ovailcble from unaffected DSKY only. Al I tracker c!:>normol indications lost. @ Trcruient abnormal condition. 0 Use cltemcte !MU alignment program (P53 and P54). ISS and CMC unaffected. .. - ;:_;:1 \ MALFUNCTION PROCEDURES INDEX J>./ ~ µ,' - r~ CUIDANr,J~ AND CO.NTTWJ, ri&c 1 . Abnormal Vehicle Dynamics during SPS Thrusting 2 . FDAI Attitude Error Abnormal 3 . FDAI Rat e Ind. Abnormal G, 4. FDAI Total Attitude Display Abnormal A. 5 . FDAI Fails to Slew with ORDEAL 6. FDAI Total Attitude does not respond to GDC Align 7. GPI/Fuel P-.'e ss Ind. ( s) Pegged or Zero Abnormal Vehi cle Dynamic s During Non- SPS _~~rusting : scs 1. RCS Failed On 2 . Accel CMID Troubleshooting Routine 3. Rate CMD Troubleshooting Routine 4. Min Imp Troubleshooting Routine 5. Direct RCS Troubleshooting Routine 6. Vehicle Dynamics Oscillating & Diverging 7. Translation Troubleshooting Routine G&N 1. RCS Failed on 2 . RHC Troubleshooting Routine 3. THC Troubleshooting Routine 4. Min Imp. Controller Troubleshooting Routine 5. CMC Lite On 6. ISS Lite On 7. Temp Lite On 8 . Gimbal Lock Lite On 9. Re start Lite On 10. Tracker Lite On 11. Frog Lit e On 12 . Alarm Codes SSR-1 SSr-2 SSR- 3 CMC Self Test CMC Quad Fail Fr esh Start SERVI CE PROPULSI ON SYSTEM 1. SPS Pres s Lite On. 2 . Premature Eng Cut-Off 2a . No SPS Eng Ignit ion 2b . Rough ECO Lite On 3. Engine Does Not Shut-Down 4. SPS Fl ange Temp Hi 5. SPS Pc Abnormal 6 . SPS He Vl v tb Abnormal I 7- He Tank Press Low or Decreasing 8. GN2 Press Low 9. SPS Eng Ins Vlv Ind Abnormal 10. No Propellant Temp Control 11. No Response of OXID Flow VLV tb During Flow Adjust 12. SPS Qt Qxid Unbalance Ind Erratic or Pegged 13. SPS Qty % OXID (% Fuel) Ind. Readout Abnormal REACT ION CONTROL SYSTEM SM-RCS 1. SM RCS A(B, C, D) Lite On la. CM RCS Pkg. Temp Ind - Low lb. SM RCS Pkg. Temp Ind - High le. SM RCS Manf Press Ind-Low ld. SM RCS Manf Press Ind - High 2. SM RCS He Press Ind - Low or Deer. CM RCS ~ , 3. 3a. 3b. 4. 5. CM RCS A(B) Lite On CM RCS Fuel/Oxid Manf Press Ind - High CMRCS Fuel/Oxid Manf Press Ind - Low CM RCS He Press - Low or Decreasing CM RCS Eng Temp Fails to Increase ELECTRICAL POWER SYSTEM CRYO 1. CRYO Press Lite - On la. Oz (H2) Press - High lb. OZ (H2) Press - Low FUEL CELLS: 1. FC 1 (2,3) Lite - on la. FC 1 (2,3) MOD Skin Temp lb. FC 1 (2,3) Mod Skin Temp le. FC 1 (2,3) Mod. Cond Exh - High - Low Temp - High ld. FC 1 (2,3) Mod Cond Exh Temp - Low le. FC 1 (2,3) pH Hl tb - bp lf. FC 1 (2,3) Rad Temp Low lg. FC 1 (2,3) 02 (H2) Flow - High 2. FC 1 (2,3) 02 (H2) 3. FC Reg 02 (H}) Out Press - High 4. cb FC 1 (2,3 PUMPS AC - open 5. FC 1 (2,3) VIT Performance Low l + 2. 2, POWER DI STRI BUTION: 1. MN BUS A (B) Undervolt LT - On la. AC BUS 1 (2) Lt - ON lb. Mn BUS A (B) Indicates 26V le. AC BUS 1 (2) Voltage Low s ld. AC BUS 1 (2) Voltage High 2 . Inv 1 (2,3) Temp HI Lt - ON 3. FC BUS Disconnect Lt - ON 4. Suspected High Current for SC Configuration SSR-1 FC Shutdown SSR-2 Bus Short Isolation TELECOMM 1. One Crewman has no Intercom Capability 2. Loss of Intercom (All Crewman) 3. One Crewman has Abnormal Hot Mike Condition 4. Loss of VHF Comm 5. Loss of S Band Voice Comm 6. Cannot Acquire Phaselock 7. MSFN Reports Loss of Ranging 8. MSFN Reports Loss of PCM ENVIRONMENTAL CONTROL SYSTEM: 1. 02 Flow Hilt - on la. 02 Flow ind - HIGH 2. 02 Flowind - LOW 3. SURGE TANK PRESS HIGH 4. SURGE TANK PRESS LOW 5. CO2 PP HI lt - on 5g. CO2 PART PRESS ind - HIGH 5d. CO2 PART PRESS ind - LOW 6. CO2 FILTER Seizure Within Canister 7. Ballooned PGA's 8 . CLINGING SUIT 9. SUIT COMPRESSOR lt - on 9a. SUIT COMPR PLOW 10. CREW UNCOMFORTABLE IN SUIT LOOP lOa.Suit CKT HUMIDITY HIGH 11. CABIN PRESS HIGH OR INCREASING 12. CABIN PRESS LOW OR DECREASITW 13. CREW UNCOMFORTABLE IN CABIN 13a.CABIN HUMIDITY HIGH 14. GLYCOL TEMP LOW - lt - on 14g .PRIM ECS RAD OUT TEMP LOW 1 5 . PRI M ECS RAD OUT TEMP HIGH 16 . PRIM GLY EVAP OUT TEMP HIGH 17. PRI M GLY EVAP OUT TEMP LOW 18 . PRIM GLY DISCH PRESS LOW 19 . PRIM GLY ACCUM QTY LOW OR DECREASING \5 3. 20. PRIM GLY ACCUM QTY HIGH 21. SEC ECS RAD OUT TEMP LOW 22. SEC ECS RAD OUT TEMP HIGH 23. SEC GLY ACCUM QTY DECREASING ENTRY MONITOR SYSTEM: 1 .. 05 G lt - on (TEST 1) 2. G/V Scroll assy does not slew (TEST 1) 3 .. 05 G lt - out (TEST 2) 4. RSI Lower lt will not come on ()EST 3) 4a. RANGE ind will not slew (TEST 3 5. V-AXIS only or multiple displays abnormal (TEST 4) 6. RANGE ind only abnormal (TEIT) 4) 7. G-AXIS only abnormal (TEST 8. RSI Upper lt not on (TEST 5 8a. G-AXIS does not drive TEST 5) 9. RANGE ind does not slew in RNG SET 9a. G-AXIS does not zero in RNG SET 10. V-AXIS does not slew in Vo SET 11. RANGE/ Vind abnormal in V TEST 12. SPS THRUST lt not on in V TEST 13. V ind does not slew in V SE1r 14. Abnormal thrust cutoff in SCS V 15. RANGE/ Vind fails to count after SPS firing 16. G-noted but .05 G lt not on in ENTRY 16a.RANGE ind does not decrease when .05 G noted (.05 G, CMC, or MSFN) 17. Scroll display(s) do not drive during ENTRY (G build up noted) 18. Neither RSI lts on 10 sec after .05 G lt 19. RSI Upper lt on after 2 G 4. CJ') I ~ ::0 -i - ,:-- . --- -~ .. - -- ..... , - •' .... ~ " ;, - . . ~.;., ... 1,· ·-~~· -:,/~ ... ~"' .j Jt.;i.,. ~: ... ~. ';~ . ~ ,...n :,;. : .. ·;, .,,. ' S S R .--........ -------~ I PROCEDURE ,---,-----------, ,----------<, REMA RIC S ~ ~ w ~ ~ 4 [ couNTER FAILL~ LIGHT CAME ON ..nL- ~ LICHT cOEs ouT ..ru.__. • oom ~ T6 COUNTER FAILED 0 DO oor usE CMC cowoc FOR Amru~ MA~vms SYSTEM TEST 1- DUR ING MA'lEUVER? AITTR MANEUVER? • CMD MANEUVER Rl DECREMENTS TO ZERO? ________ __, 0 DO t«)T USE CMC lO ORIVt: OPTICS 00 toot--------1-------' NO YES 0 VER IFY BY ZEROING OPTICS, TH£N REPEATING ST£P 11 ,--.,......--------1--:"'I BUT THIS TIME LOAD 5• IN Rl AND ZfRO IN R2. 2_3 ~ l2J ~ CMC LIGHT SHOULD COME ON DURING OPTICS DRIVE IS OSS ON? ,..fil__ IS V4tN9l OR AUTO ..1fil. - T6 COUNTER FAI LED OR OPTI CS POS ITIONING FAIL DffiCTOR FAILED © DO OOT USE OPTICS BEING DONE Kl YES 0 VERIFY BY COMMANDING TRUNNION ANGLE Of-l.Y, ANO ~ ,---,---------, ,--.,......--------, OBSERVING IF R2 CHANGES : · I R I ~ ! 10 I G) © DO OOT USE CMC UPLINK ',,. ~ • V41N91E µ 0 ~ .... l e OPTICS ZERO. ZERO ,.Yli ~ • LOAD ZERO 1111 RI ~ SHAFT COMMAND - •LOAD 5' IN R2 REGISTER FAILURE _ I t----------; LIGHT oun CMC LIGHT ON DURING ________ ____, • • OPTICS DRI VE? NO ' ' YES I ,---.---~-----, llEJ ~ CD I -· NO ----· ~ - ~ • G&N POWER OPTICS - OFF ,----- TRUNNION COMMAND •.•• f ~ - REGISTER FA ILURE ,. ,--...,....--~----,., , ~ ~ LICHT OUT? , I . • I -__,--=:- ,.. ~ Yi:S ~ ~ - - -~ I 'J{1 IS UPLINK BLOC!(ED ? >-- .--...----------, -~ ~ ~ I • OPTICS ZERO-OH .,._.ll.L. TRUNNION OCD\J 6 1 YES _ • OPTICS MODE· MAN COUNTER FAILED - e OPTICS COUPLINC - DIRECT e G&N POWl:R OPTICS~ e VJ6N9 1E e OPTICS CONTROL - .--....---------f0 .__.I~ CMD SHAFT < ONLY ~ • ~ SHAFT OCOU ~ • UP TLM - BLOCK 1---------------i COUNTER FAILED NO 1-------=-:------, RI CHA~S WITH SHAFT CMD? 141---------1 LI GHT OUP j YES • • .• r-.,....--....L-----(--A 1 .; ~ ~ ~ ., ' . . . IN!.INK COUNTER FAILED ,. "' ,, ~ ~ . ' I W Ttble 6-6. Special Subroutines (Sheet 5 of 6). .; "!_.:J:,;;. ;;,._:~~~ k...,. . .,_ ~11> ..,, O':l I ..i::,.. co 'll \.. ':: l .. ~ ' ... ~ lliJ l::J l.EJ lD 0 IMU CANNOT BE FINE AI.IG!l[O ~ \') ., _ ·,-., 7 P1,L.-.. 1 IS GYRO TORQUI NG ~ YES - GYRO TORQUII-IG -.:- .. IS ISS ON IN PROCESS? • TERMINATE GYRO TORQUIN, COMMAND REGISTER FAIL URE © IMU CANNOT 11£ COARSE ~UGNED. Al!CN 8Y CAGING •• LIGHT OUT? '------------..1 AND /OR FINE ALIGN NO - 1 jr NO l- I NO -------✓- 0 POWER DOWN !MU I,. 24 I ~ G) @) THE CMC IS UNUSABLE. FURTHER MALFUNCTION ISOlATIOH L=!. ~ CAN DETERMINE WHICH COUNTER HAS FAILED BUT MR£ IS COARSE ALIGN ~ TERMINATE COARSE ALIGN ~ OCDU COMMAND I IS NO ACTION THAT CAN Bf TAK£N TO MAK£ M CMC IN PROCESS? REGISTER FAILURE USABLE ~ I . NOi 100 Gil • I -------'N0""---1 iob&N POM:R, IMU - OFF LIGHT OUT? - I C l YES ...--r-------. -1d ~ ~ ~ · • Vl6N21[ • I ~ ..!!9..__., • Vl6N2!l: -- UNISOlATEO ISS "'NY REGISTER t.l~O OR • RECORD GIMBAL < 's COUNTER FAILED OR , ~NCREAi:' :TING AT EXTREME e V41N2!l: FAIL DETECTOR FAILED I RATE 7 e CMD GIMBAL < 's 5° FROM IYES PRESENT ANO MONITOR <:HANG£ WITH Vl6N2!l: l -::._7 '9'i ANY REGISTER REMAINS I' ~ -:.,; UNCHANGED OR INCREMENTS I: PIPA COUNTER FAIL URE AT EXTREME RATE? l CORRESPONOINC TO FAILED l I I RE GISTER READING .--~--------~ I _ .. ~ lV ' .---------~ ICDU COUNTER FAILURE I 1 -- l . ~ 33 l CORRESPONDING TO FAILED ..RJ .EJ REGISTER READING • VllN2E NO • 25!: ~ Tl COUNTER FAILURE • Rl CHANGES 144 EVERY SEC? ..._ _______ __., ii • YES ~ ~ ~ ~ • 57E • 24E • JOE ~ i-!1L. ~ UNISOI.AITD CMC _ COUNITR FAIUJRE ,.. _ Rl INCREMENTS 144 RI INCREMENTS ONCE AND "'" SECO:? ~ ",1 ~ I SEC? o,1vo,cr "'Fns""' .______ ·•· ,· . , 6.1 ~ l!!J ~ :. ,_ ,. T5 • COUNTER FAILURE f.oun1NK COUNTER FAIWRE T2 COUNTER FAILUIIE • ,. , ;; • I ,. :.,. ~ . c/.. " •·-• -~ 'TbhlA h-h ~nP.l"i~l ~11hrcrn+;nAo /C:hAAt Fi of S\ V T . .;(1' ·, .,.. MASSACHUSETTS UTE OF TECHNOLOGY ........................................................................ 19 ................ _ MURAN BOSTON 

Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures change - May 1968

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Guidance and Control System (GC) - Malfunction Procedure Symptoms - Proposed Procedures changes - November 11, 1968

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Fort Hays State University