SERVICE INFORMATION NO. SI-1D2

Overhaul Activities: Compliance must be accomplished on all subject flow dividers listed in 1, A prior to return to service. E. APPROVAL: None. F. MANPOWER: Undetermined. Energy Co~trds Division 717 N. Bendix Dr.. South Bend. Indiana 46620 RS 43 SUBJECT: FLOW DIVIDERS FOR BENDIX FUEL INJECTION SYSTEMS. INSPECTION .4Nn MODIFICATIr3N OF i. PLANNING INSTRUCTIONS: (Continued) G. MATERIAL AVAILABILITY: Part Number Nomenclature Availabili~I 2538998 Gasket Bendix Product Support Centers: 902646K1 Screw 7262 N. W. 54 Street Minnii, Florida 33166 Telephone: 305-887-7426 1120 Howell Street North Kansas City, Missouri 64116 Telephone: 816-842-9093 317 C(,rey Way South San Francisco, California 94080 Telephone: 415-588-5619 130 Finii Court Farniinffdale, L.I.. New York 11735 Telephone: 516-293-4741 Product 84 Loctite A or C Loctite C(,rporation Newinyton, Connecticut 06111 H. TOOLING: None. I, WEIGHT AND BALANCE: No effect, J. REFERENCES: None. K. PUBLICATIONS AFFECTED: Overhaul Manual and Illustrated Parts Breakdown Flow Dividers used with the RS-RSA Fuel Injection System, Form 15-540A, 15 July 1974. 2. ACCOMPLISHMENT INSTRUCTIONS: A, Operating Activities: (1) Gain access to the flow divider assembly. (2) Visually check Flow Divider Parts List Number to determine whether the provisions of this bulletin apply, (3) If applicable, remove all lines from the flow divider assembly. Cap and plug all open lines and fittings with suitable protective coverings. Remove flow diviher from engine. (4) With the flow divider on a suitable work bench, remove the four Countersunk Screws P /N 902646K1, Cover Assembly P ’N 2523747 and Casket P’N 2537013. (Refer to Figure 1. index 1, 2, 3, and 4.) NOTE Screws 902646K1 have been installed with Loctite A or C and may nee’d localized heat applied for eas~ renloval, Use a suitable screwdriver to preclude damage to screws and.´•~or flow divider housing, (5) During reassembly (refer to figure 1), install new Casket P N 2538998, Cover P/N 2523747 and new Screws P/N 902646KI if required. Prior to installation, apply Luctite, Grade A or C, to the first two threads of screws. Tighten screws tc-, 8-11 pound-inches torque. (6) Reidentify flow divider as follows: (a) Scribe a dash 2 (-2) after P’L number. 2 2~ RS 43 SUBJECT: FLOW DNIDERS FOR BENDIX FUEL IN~JECTION SYSTEMS, INSPECTION AND MODIFICATION OF 2. ACCOMPLISHMENT INSTRUCTIONS: (Continued) REMOVE SOLID GASKET P/N 2537013 (RED~ 4 3 PARTS LIST NO. LOCATION INSTALL NEW GASKET P/N 2538998(8801 4 3 \1 i C GASKET P/N 2523348 ´•(BLACK,~CCEPTI\BLE i P~INT BLUE DOT APPROX. 1/4 INCH DIAMETER HERE. C-3664’ Figure 1. (b) Paint a blue dot next to flow divider inlet approximately 1/4 inch in diameter. (7) Reinstall flow divider on engine, remove all caps and plugs from lines and fittings and reconnect. I Tighten fittings to 25-30 pound-inches torque. Use care to properly tighten fittings to prevent dam- age and fuel leaks. (8); Perform a ground operational check to insure satisfactory engine performance. CAUT ION After shutdown, examine engine for evidence of fuel leaks. Correct all fuel leaks prior to flight. B. Overhaul Activities: (1) Prior to return to service replace solid Gasket P/N 2537013 with new Gasket P/N 2538998. (2) Reference: Bendix Overhaul Manual, Form 15-540A, dated 15 July 1974. (3) Reidentify flow divider as follows: (a) Scribe a dash 2 (-2) after P//L number. (b) Paint a blue dot next to flow divider inlet approximately 1/4 inch in diameter. RS 43 SUBJECT: FMW DIVIDERS FOR BENDI~ FUE L INJECTION SYSTE:MS. INSPECTTON AND MODIFICATION OF 3. M ATE RIA L IN FORM ATION: New Part Number Quantity Nomenclature Old PartNumber Disposition 2538998 1 Gasket 2537013 Scrap 90264 6K1 4 Screws 902 646K1 Replace as necessary. 4. TESTING: No effect. i´• S General Aviation Division Rockwell Internat~onal Bethanv, Oklahoma 73008 _´•r SERVICE INFORMATION NO. SI-106 DATE: March 6, 1975 EFFECTIVITY: MODEL 112 (SEE LYCOMING SERVICE BULLETIN NO. 376). SUBJECT: LYCOMING SERVICE BULLETIN NO. 376, RECOMMENDED COMPLIANCE: AT NEXT INSPECTION PERIOD OR AT NEXT MAGNETO OVERHAUL, WHICHEVER OCCURS FIRST, The reason for issuing this Service Information Letter is to recommend compliance with the attachedLycoming Service Bulletin No, 376. e LYCOMI IV G DrVISION WILLIAMSPORT, PENNSYLVANIA 17701 ri3o00oV8w (L~) DATE: November 22, 1974 Service Bulletin No. 376 (Supersedes Service Instructions No. 1269 and 1281) Engineering Aspects are FAA (DEER) Approved SUBJECT: Bendix Service Bulletin No. 556B MODELS AFFECTED: P/N 10-51360-30 O-235-C1, -C2A, -E2A, -G2A, -F. O-290-D, -D2, -D2B. 0-320- A2A, -A2B, -A3A, -A3B, -B1A, -B2B, -B3B, -D1A, -D2A, -E1A, -E2A. IO-320-BlA, -B1C, -B2A, -C1A. O-360-A1A, -A2A, -A3A, -A4A, -A1H, -A1E6, -B2A, -C1A, -C2A, -C2B, -D2A, -D2C, IO-360 -B4A. VO-360-A1A. P/N 10-349365-2- O-235-C2B, -F2B. O-360-D1F, -D2F, -D2C, -E1C, -E1F, -E2E, -E2 F, -E2C, (Wide deck). IO-320-B1A, -D1A, -D1B, AIO-320-A1B, -B1B, -C1B. 0-360-A1F, -A2F, -A1F6, -A1G, -A2G, -A1G6, -A2F, -C2A, -D2A. AIO-360-A1B, -B1B. IO-360-A1B, -A1B6, -A2B, -B1E, -B1F, -B2E, -B2F, -C1C, -C1D6, -ClE6, -F1A. TIME OF COMPLIANCE: As required by subject bulletin. Bendix Service Bulletin No. 556B reprinted herewith in its entirety, pertains to removal of a sintered iron magneto drive shaft bushing and replacement with a machined steelbushing. Owners and operators of applicable Avco Lycoming aircraft engines must comply with this bushing replacement within the time limitations specified in Bendix Bulletin No. 556B. c Eieotrioei Components SERVICE BULLETIN 5568 Division Engineering Aspects Sidney. N. Y. 13838 are FAA Approved Printed August 1974 Page 1 of 2 Pages AIRCRAFT SUBJECT: Shouldered magneto drive shaft bushing, change from sintered iron to machined solid steel. REASON FOR BULLETIN: To inform users of subiect change required on certain magnetos to reduce the possibility of bushing flange failure during service. EQUIPILIENT AFFECTED: S4LN´•21 P/N 10-5136025 S4LN-1208 P/N 10-349285-2 S4LN-21 P/N 1051360-26 S4LN-1208 P/N10´•349285-4 S4LN-21 P/N 10-51360-30 S4LN1209 PIN10´•349305-2 S4LN´•21 P/N 10-51360-31 S4LN-1227 P/N10-349355-1 S4LN-21 P/N 10-51360-45 82LN-1227 P/N10349365-2 S4LN-21 P/N 10-51360-46 S4LN-1227 P/N10-349365´•6 S6RN-21 P/N 10-51365´•35 S6HN-1208 P/N 10-349290-6 S6LN-21 P/N 10-51365-39 S6LN1208 P/N 10-349290-7 S6LN-21 P/N 10-51365-42 S6LN1209 PIN 10-340310´•5 j4LIJ-iOU !?"O !O??L\7!"-6 r/lu I u- i 630us-J S4LN-200 P/N 10-163005-5 SGRN-1227 PIN10-34Y370-5 S4LN-200 S6LN-1227 P/N10-349370-6 P/N 10´•163005-7 S4LN-204 P/N10´•1630451 S6LN-200 P/N 10´•163010´•’3 SGRN´•200 P/[J 10-163010-7 S6LN-200 PIN 10-163010-11 SGL.N-20´•1 P/N10´•163050-2 I S6LN-%O~! P/FJ 10163050-6 Member of GAMP. Page 1 of 2 C.rnernl avl;lrloll Pssnclll(lr,ll Service Bulletin No. 376 Maintenance (Sl,srel Parts Af fectcrl: 1051Gs’J Bu~i,iiiii. -.ln’arail Iron. UNDERCUT 10-51655 Eushin~, sln’~rri! iron. 10-56591 Uushing, siiireiitl iron. Compliance: At next inspection period or at next magneto overhaul period, whichever ir sci~eduled :Il-rr. MACHINED STEEL SINTERED IRON Detailed Instructions: Field rcilsrtr indicate that the sinturad irn~, I,ushing now Figure 1 installc~l on the lirred Fart numtsr magnetos are breaking away at the I,llsllinq fl.in(lc. For this re~soii, replar.emrnt plate first to determine the bushing type currently of all sintured iron I,ushin~s now in usu wi:C the machined installed. solid stc!el bushing (Sco Fig. 1) is strongl´•; recommended. All magnetos having Black name plate mL,st I,e visually If tl,e Illannrto n;lme plate Part Numbel´• nppcnrs in the above checked for the type of I,uslling used regartlless of name EOIJIPMENT AFFECTED liaiii,g. i;is!~cct the magneto name plate data other than the part numbar. TABLEI Alphai AlphJ/ Alpha Numerical Numerical Numerical Change Change Change Ma(lnetoP/N BushingPIN Designation MagnetoPiN BushingP/N Designation MannetoPiN BushingP/N Designation 10-51360-25 10-163049 Gt 10-1630055 10-163049 El 10´•349305-2 10-163049 Dl 10´•51360´•26 10-163049 Fl 10-163005´•7 10-153049 Fl 10-349365-1 10-163049 Dr 10-51360-30 10-163049 10-163045-1 10-163049 El 10349365-2 10-163049 10-51360-31 10-163049 Fl 10´•163010-3 10-357193 Fl 10-348365-6 10-163049 B1 10-51360-45 10-163019 C1 10-163010-7 10-357193 F1 10´•349290-6 10-3571~-3 D´•1 10-5136046 10-163049 B1 10´•163010-11 10-357193 El 10-359290-7 10-357193 D1 10´•51365-35 10-357193 G1 10-163050-2 10-357193 Fl 10-349310-5 10´•357193 Dt 10-51386-39 10-357193 G1 10´•163050´•6 10´•357193 Fl 10-349310-6 10-357193 D1 10-51365-42 10-391421 G1 10-349285-2 10-163049 Dt 10-349370-5 10-357193 D1 10-163005-3 10-163049 El 10-349285-4 10-163039 D1 10-349370-6 10-357193 D1 g´•Becomes new part number. See paragraph (a) under Part Identification Required. All magnetos with a red name plate having the alpha/numer- Part Identification Required: ical change desigl,ation listed in Table t have the solid bush- All magnetos below the specified Serial Numbers or change ing. Magnetos having name plater with a change designation designations modified in compliance with this bulletin, or higher than the table listing (i.e.: Table i listing Fl;name checked and found already in compliance, must be reidenti- Pl.tP F2. G1.´•tc.) also hs~´• !L.z cc!ir! :re-l b-r!´• rlea as tollows: fny. Magnetos with name~ plates having a designation lower than that listed in Table 1 must be visually checked for la) Magnetos P/N 10-51360-30 and 10´•341)3652 become bushing type actually on the magneto in question. new parr numbers 10-51360-37 and 10-349365´•3 All magnetos with a Blue name plate (Bendix Remanufac- respectively. Overstamp the’magnEto name plate with tured) magnetos having Serial Number 349001 or above the new part number suffix, -37 or -3 as applicable. have the new bushing. All below this SiN must be visually (bl All other magnetos specified in the EQUIPMENT checked for bushing type. AFFECTED listing shall be identified by stamping ;.Ths machined rolid rteel burhing P/N 10-153049 hat been the lower left corner ot the name plate with a lie.’ available as a replacement part for some time. (Reference high letter "8". Bendix Service Bulletin 556 issued May 1972. also printed as Avco/Lycoming Service Instruction 1269 issued Decem´• As soon as compliance with this bulletin is accomplished her 1972 and Bendix revision 556A printed April 1974.) make the appropriate entry in the Engine Log Book. Therefore. some magnetos below the listed serial numbers or change designations may have had the 10-163049 Part Required Per Article: bushing previously installed as a field replacement. 10-163049 Bushing, machined steel. replaces 10-51659. Figure 1 illustrates the two different typer of bushings 10-357193 Bushing, machined steel, replaces 10-51655. involved. Detinite identi fication is possi ble by checking 10-391421 Bushing. Inachined steel, replaces i 0-56591. for the existance of, or lack of, the approximately .062 x .005 deep undercut immediately behind the flange of Special Tools Required: the bushing. None If examination reveals the presence of rintcred iron bushing, it must be replaced imlnediately with the mach- Man Hours Required: ined solid steel bushing as sl,ccified in Table i. Hr. per magneto After asicmbly of the new bushing on the magnrto, torqlle Wei(lht Change: the assrmbly nut to 15-25 Ib, ft. and install a new cotter pin. Negligible Page 2 of 2 .IP i General Aviation Division ah ROckwell International Bethany. Oklahoma 73008 SERVICE INFORMATION NO. SI-108 20 June 1975 LYCOMING SERVICE BULLETIN NO. 385 MODELS AFFECTED: MODEL 112 (SEE LYCOMING SERVICE BULLETIN NO. 385 FOR ENGINE SERIAL NUMBERS AFFECTED). REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH THE ATTACHED LYCOMING SERVICE BULLETIN NO. 385. COMPLIANCE: ENGINES WITH 400 HOURS OR MORE THAN 400 HOURS TIME W SERVICE BY WHOM WORK WILL BE ACCOMPLISHED: APPROVED SERVICE CENTER. APPROVAL: SEE LYCOMING SERVICE BULLET~N NO. 385. ESTIMATED MAN HOURS: SEE LYCOMING SERVICE BULLETIN NO. 385. C PARTS DATA: SEE LYCOMING SERVICE BULLETIN NO. 385. SPECIAL TOOLS: SEE LYCOMING SERVICE BULLETIN NO. 385. ACCOMPLISHMENT INSTRUCTIONS: 1. Comply with Lycoming Service Bulletin No. 385. ~LECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. PUBLICATIONS AFFECTED: NO CHANGE TO ROCKWELL INTERNATIONAL PUBLICATIONS. RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Lycoming Service Bulletin No. 385, dated April 4,- 1975, entitled "Oil Pump Impeller and Drive Replacement", accom- plished (date) ~iAVe6 LYCOMING DIVISION WILLIAMSPORT, PENNSYLVANIA 17701 ~oOUooYo (L~) DATE: Aprilll, 1975 Service Bulletin No. 385 Engineering Aspects are FAA (DEER) Approved SUBJECT: Oil Pump Impeller and Drive Replacement MODELS AFFECTED AND TIME OF COMPLIANCE: ttSerial Numbers of Serial Numbers of Engines ’Engine Model Applicable Engines Not Applicable to this Bulletin Time of Compliance 0-235 Series 11268-15 thru 12098-15 12099-15, 12101-15 and up and 12100-15 0-320 Series 33329-27 thru 41054-27 41055-27 and up O- 320- E2D: 41029-27 and up 0-320-E3D:41017-27,41021-27 and up During engine overhaul; if engine has been operated beyond normal O- 320-B and -D 6809- 39 thru 6971-39 6972- 39 and up overhaul period, as specified in S. I. 1009V the modification must IO-320-B1A 4953-55 thru 5270-55 5271-55 and up be accomplished before any ad- ditional time is.accumulated. i~IO-320 Series 292-66 thru 296-66 297-66 and up 0-360 Series 18550-36 thru 19846-36 19817-36 19818-36 O IO-360-B, -E, -FI 10146-51thru 13540-51 13541-51 and up 19847-36 and up AEIO-360-B 1 10179-51 thru 13616-51 1 13617-51 and up IO- 360- A, -C, -D 10146-51 thru 13540-51 13541-51 and up IO-360-A1B6D 9598-51 thru 13529-51 13530-51 and up AEIO-360-A 10179-51 thru 13616-51 13617-51 and up AIO-360 Series 171-63 thru 208-63 209-63 and up Engines that have ac cu mu lated 400 or more hours of service since LIO- 36~ 634-67 thru 1059-67 1060-81andup new, remanufactured or over- hauled must be modified in ac- TIG-360 116-64 thru 145-64 146-64 and up i cordance with this bulletin within next 50 hours of operation. 0-540 Series 15327-40 thru 17105-40 17106-40 and up 17098-40, 17103-40 and engines modified in accordance with Ser- vice Bulletin No. 381. I ___ IO- 540 Series 10536-48 thru 12896-48 12897-48 and up j with Service Bulletin No. 381. Engines modified in accordance i All of the engines listed ill this column that were remanufactured at Avco Lycoming and shipped between Decetl7ber 21, 1972 and December 10, 1974 are suhjectto the modific~tion described in this bulletin. However, during remanufncture nlfluy’ of these engines were I,uilt with oil pump drive components that are satisfactory fo r continued st~ r~. ic c aiicl Iiot subject to the mocli licatioii he rein requi red, see inspec tion paragraph to determine if compliaiice is rcclui~rtl. Tn aclci 11~)11 10 1 jli~ Cll~illcS listed by serial numt,crs in this column, all engines modified to incorporate hardened impellrl´•s ill with Service Inslructioll No. 1272, inclddinfi 0-235. 0-290, 0-320, 10-320, LIO-320, 0-340, 0-3Bu. iilo-:;:io. VO-360, IO-360, TIO-360, LIO-360, 0-340 and i0-540 are subject to compliance with this I,ullc~!:i. ’t~iial !Illmbcrs of nian~ engines shown in this list the suffix "A"; this letter suffix has no siRnilic´•~iii´•e iiist,iat as this bulletin is c:oncerncd and therefore has been omitted. Page 1 of 4 MemberolGAMPi General Avlallon ManufJcrurers Assocl;ltlon Yervice Bulletin No. 385 REFERENCE: During April, 1S70 newly designed oil pump impeiiers, Inade of sintered iron and featuring a Woodruff key in the drive shaft were introduced in production of some loui and sis cylinder Avco Lvcoming engines: this change was offered to owners of earlier built engint’s t,V Service Instruction No. 1230. However, it became evident that although not subject to failure, the wear characteristics of the new drive were not comparable to the earlier design and a further change was introduced in December, 1972 to provide a hardened drive impeller; this is described in Service Instruction No. 1272. In addition to the hardened sintered iron drive impeller, a steel impeller was also used in some engines, It is now evident that the area of the Woodruff keyway in the hardened drive impeller and the steel impeller is subject to severe wear and eventual failure and consequently the drive components are now further modified as herein described. This modification consists of replacing the oil pump drive shaft and drive impeller to eliminate the Woodruff key drive which has proven to be the cause of excessive wear in the keyway of the hardened drive impeller. Therefore, it is recommended that all of the applicable engines listed above, as well as any others that may have been modified in accordance with Service instruction No. 1272, use the following procedure for parts replacement. NOTE The modifications shown inService Instruction No. 1272 are no longer recommended and the instruction may be considered as-inactive and non-applicable. Actually, engines that were never modified to incorporate the hardened sintered iron impellers as described in Service Instruction No. 1272, are not subject to the modification required by this bulletin. INSPECTION: Applicable remanufactured engines shipped after December 21, 1972 should be inspected to determine if this modification is required: first of all, if the engine log book indicates the engine has not been modified in accordance with Service Instruction No. 1230 or No. 1272, proceed to remove the accessory drive cover from the mounting pad at the lower right side of the accessory housing to obtain access to the area between the crankcase and the accessory housing. On some engines this accessory drive pad is not machined, in this event it will be necessary to remove either the left magneto or the ’fuel pump to obtain access to the area between the crankcase and the accessory housing. Regardless of which accessory pad is used, determine if the oil pump idler gear is secured with a cotter pin at the location shown in fly re 1. This can be accomplished using an inspection mirror, preferably an illuminated one. If the cotter pin is visible, it is unnecessary to perform the modification required by this bulletin. PROC EDURE: rCC necessitates removalof the accessory housing the pro- cfs~jc.’. Essentially this modification consists of replacing the oil pump drive shaft and drive impeller; since this ,1 ’~d cedure varies by engine model and airframe instal- at Ilt~on. Usually, Lhi. can be removing c’ only the accessory housing; however, on engines where the accessory housing is attached to the sump with i studs and nuts instead of capscrews it will be nec essary also to remove the sump. *1. Unless the entire sump is to be removed it is housing to not damage the gasket between the sump g;i/ ver$ important during remo~.al of the accessory and the accessory housing. if it is damaged, the partial gasket supplied with the kit may be instal- led as described in step i´•: 2. After the accessory housing has been removed, disassemble the oil pu mp and carefully inspect both the housing and oil pump cover for damage, if iDL tl? TH~FT iS CEC;j"ECI 3. Reassemble the oil pump using the new drive ´•C:,TH A rnT;EV F.li. AT T~( SiOSI; shaft and drive impeller supplied with the kits shown TiDN MCJDIFiT,~Th3’F´•J:C Nr~T REOUIPEi) in the following "Pnrts Data" section. See figure 2. Be sure all of the parts are lubricated thoroufihlp Fi~re i. Intrrlorr View of Accessory Housin~ Showing during assembly. Afte;´• assenlblv, turn the drive Location (,I Cotter Pin ill Oil Pu nip Idlei Shnl’t t Before removing the fuel puml,, be sure the cnm on the hub of the idlc´•r ~cnr is not in position to exert force on the arni of the fuel pump: if it is, damage to the niountin~ threads aill c~c´•ru r when Lhe fuel iwmP is re,noved. Page 2 of 4 q Service Bulletin No. 385 shalt several revolutions to dfterniine if it nioves 5. When rcnsse!l!bli!l~ ~he nrcessory housing align freely; if not, open the pump and correct the cause the idler gcnrs ill their exace position for engage- before the unit is reassembled on the engine, ment with the timini~ geni on the camshaft. See no. 60294-7 overhaul manual for assembly procedure. 4. Before returning the accessory housing to the engine it is necessary to replace the gasket on the 6. After reassembly, time the magnetos to the en- mating flange between the sump and the accessory gine and run the engine to check oil pressure and housing if it has been damaged. (If the sump has magneto drop-off; check for any noticeable variance been removed the entire sump gasket is replaced. from normal oil pressure and significant change To replace the rear portion of the sump gasket, lay from normal magneto drop-off. the gasket on the sump flange and cut it diagonally with a sharp knife to obtain a line to line match between the ends of the old and new gaskets. Use 7. Compliance with this modification should be POB gasket compound for sealant. noted in the aircraft records. Full credit allowance for parts and labor will be made in accordance with the following schedule for compliance with this bulletin. Claims must be filed with nearest Avco Lycoming Distributor and be accompanied with engine serial numbers. Engines with 0 to 400 hours servicetime $50.00 Engines with 400 to 800 hours service time $35. 00 Engines with 800 to 1200 hours service time $20. 00 Engineswith 12000r morehours servicetime materials only PARTS DATA: LW-14129 Gasket Kit, Oil Pump Shaft Replacement (4 cylinder engines) consists of: (1) 60096 fuel pump gasket, (3) 62224 magneto gasket, (1) 73818 ac- cessory housing gasket, (2) LW-12681, -1200 series magneto gasket, (1) LW-13353 oil sump gasket. LW- 14230 Gasket Kit, Oil Pump Shaft Replacement (6 cylinder engines) consists of: (1) 60096 fuel pump gasket, (3) 62224 magneto gasket, (1) 73818 ac- cessory housing gasket, (2) LW-12681, -1200 series magneto gasket, (1) LW-14128 e: oil sump repair gasket. LW-14131 Oil Pump Shaft Replacement Kit (4 cylinder engines) consists of: (1) 61174 oil pump drive shaft, (1) LW-14038 drive impeller. LW- 14132 Oil Pump Shaft Replacement Kit (4 cylinder, dual drive magneto engines) consists of: (1) LW-14040 oil pump drive gear, (1) LW-14038 drive impeller. LW-14133 Oil Pump Shaft Replacement Kit (6 cylinder engines) consists of: (1) 74641 oil pump drive shaft, (1) LW-14038 drive impeller. Page 3 of 4 I~uiletiii No. 385 r--------------- 4 AND 6 CYLINDER ENGINES u USE EITHER 78532 DRIVEN IMPELLER 8 SHAFT ASSEMBLY (IRON) OR ’b"~ LW-13775 DRIVEN IMPELLER a SHAFT ASSEMBLY (ALUMINUM) ~´•14 4 AND 6 CYLINDER ENGINES DRIVING IMPELLER P/N LW-14038 REPLACES 6 CYLINDER ENG1NES I ;s-~- IDRIVING IMPELLER P/N’S~LW-12897 /N 74641 DRIVE SHAFTREPLACES AND P/N 77313 WHICH HAVE KEYWAY. DRIVE SHAFT WITH KEYWAY P/N 78619 ;ioR1 4 CYLINDER ENGINES WITHMAGNETO INSTALLATIONS e i ~s´• DUAL P/N LW-14040 OIL PUMP DRIVE GEAR, REPLACES P/N’S LW-IO3I6 4 CYLINDER ENGINES P/N 61174REPLACES LW-12916 DRIVE SHAFT WITH KEYWAY P/N 75288 Figure 2. Oil Pump Drive Assenibly Pnb’e 4 ot’ ´•1 i General Aviation Division ROckwell International Bethany, Oklahoma 73008 SERVICE INFORMATION NO. SI-112 25 July 1975 BENDIX SERVICE BULLETIN NQ. 580 MODELS AFFECTED: MODE~S 500, 500A, 500B, 5005, 500U, 560A, 560E, 560F, 680, 680E, 680F, 680FL, 680FL(P), 680F(P), AND 720, SERIAL NO’S 231 AND SUBS, MODEL 685, SERIAL NO’S 12000 TI-IRU 12066, AND MODEL 112, SERIAL NO’S 3 AND SUBS. REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH THE ATTACHED I3ENDIX SERVICE BULLETIN NO. 580. COMPLIANCE: SEE BENDIX SERVICE BULLETIN NO. 580. BY WHOM WORK WILL BE ACCOMPLISWED: A P MECHANIC OR EQUIVALENT. APPROVAL: NOT APPLICABLE. ESTIhllATED MAN HOURS: SEE BENDIX SERVICE BULLETIN NO. 580. PARTS DATA: 1 ea. Bendix Service Bulletin No. 580. SPECIAL TOOLS: NONE. ACCOMPLISHMEN~ INSTRUCTIONS: i. Comply with Bendix Service Bulletin No. 580 whenever screws are loosened on magnetos. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANCE. PUBLICATIONS AFFECTED: NO CHANGE TO ROCKWE~L INTERNATIONAL PUBL,ICATIONS. RECORD COMPLIANCE: NOT APPLICABLE. ~i41u Electrical eomponenqs Division SERVICE BULLETIN NO. 580 Sidnev. N. Y. 13838 Printed February 1975 Page 1 of 1 Page i AIRCRAFT SUBJECT: Breakage of Captive Lockwashers. REASON FOR BULLETIN: To recommend inspection of Captive Lockwasher whenever a screw 10-35936-7 is loosened or removed. EQUIPMENT AFFECTED: All s-2o. s-2o0, s-60o, s-1 200 and D-2000 Series Magnetos. NlaintBnance (Spare) Parts Affected: CAUTION 10-35936-7 Screw with lo~kwasher. Be sure all pieces of a broken washer are removed from the inside of the magneto. Compliance: Any time the screws are loosened or removed. Parts Required Per Article: Not applicable. Application of Parts: 5-20 Series breaker contact securing screws and capacitor Special Tools Required: securing screw, None, 5-200, 5-600, D-2000 Series breaker contact securing screws. Man Hours Required: S-l 200 breaker contact securing screws and coil lead Negligible. clamp securing screw. VVeight Change: Not applicable. Detailed Instructions: The captive lockwasher on some screws 10-35936-7 is breaking or cracking after the screw is tightened. This breakage is due to hydrogen embrittlement of a certain group of parts. For all practical purposes the lockwasher will perform normally until the screw is loosened or removed. Vl)henever a 10-35936-7 screw is loosened or removed for any reason, carefully inspect lockwasher for breakage or cracking las evidenced by loss of normal offset). If the lockwasher is intact, the screw may be retightened to 20-25 Ib.-in. of torque. NOTE All screws with lockwashers must be replaced REW 10-3593~-f at overhaul. (Tarqus to 20-25 Ibi-init If the lockwasher is missing, broken or cracked, replace the screw with a new 10-35936-7 screw with captive Typical S-20 Series Magneto lockwasher and tighten to 20-25 Ib.-in. of torque. Figure I v ii ‘e I~ RDCkWell Intern~hanal -B Bi 6-I C L1 F I .-1 General Aviation Divirion 5001 North Rockwell A Bethany, Oklahoma 73008 SERVICE INFORMATION NO. SI-128 12 March 1976 LYCOMING SERVICE INSTRUCTIONS NO. 132$ MODELS AFFECTED: MODEL 112 (SEE LYCOMING SERVICE INSTRUCTIONS NO. 1325 FOK ENGINE SERIAL NUMBERS AFFECTED). REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH LYCOMING SERVICE INSTRUCTIONS NO. 1325. COMPLIANCE: AT OWNER’S DISCRETION, BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT, APPROVAL: SEE LYCOMING SERVICE INSTRUCTIONS NO. 1325. ESTIMATED MAN HOURS: TWO (2) HOURS. PARTS DATA: SEE LYCOMING SERVICE INSTRUCTIONS NO. 1325. SPECIAL 1’00LS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. Comply with the attached Lycomin6r Service Instructions No, 1325, ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. PUBLICATIONS AFFECTED: NO CHANGE TO ROCKWELL INTERNATIONAL PUBLICATIONS, RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Lycoming Service Instructions No. 1325, dated October 3, 1975, entitled "Timing Chan6re for 10-360 Series Engines", accompli isaFtc~l w 1 ~7AVCO LYCOMING DIVISION WILLIAMSPORT, PENNSYLVANIA 177Q1 s ct, DATE: October 3, 1975 Service Instruction No. 1335 Engineering Aspects are FAA (DEER) Approved SUDJECT: Timing Change for 10-360 Series Engines MODELS AFFECTED: IO-360-A series (not -A1BGD), -C, -D series, HIO-360-C1A, -C1B, AEIO-360-A1D6 with serial numbers prior to 14435-51; IO-360-C1n6 with serial numbers prior to 14445-51; LIO-360-C1E6 with serial numbers prior to 1063-67; and AIO-360-A1A, -A1R, B1B with serial Iiumbeie prior to 219- 63; TTO- 360-A1B with serial nu mbers prior to 145-64. See Service Dulletin No. 380 for IO-360-ClC and -C1F models. TIME OF COMPLIANCE: At overhaul or at owner’s discretion. Certain advantages in engine operation have been 1. With the left niagneto removed from the engine, found by changing engine timing from 25" ETC to 20" remove the impulse coupling. Replace it with a Iiew ETC and 1´•educing the lag angle to 15" on i mpulse coup- coupling LW-391429. See the latest revision of ling magnetos and 15" retard angle on retard breaker Bendix Electrical Coml~onents Division publication niagnctos whichcvei´• is applicable. Significant L-G45 for inipulse coupling replacenient procedure. nlcnts in engiiie operating characteristics are achieved Use only the proper Dendix puller for removing in above listed aircraft engine installations particularly coupling. in the areas of normal operation and cold weather starting. During cruise operation, cooler cylinder head 2. Reinstall the magnelo on the engine and retime temperatures can be expected resulting in improved both magnetos using the 20‘’ timing mark on the seivice life of intake and exhaust valves. During full starter ring gear instead of the 25’ mark. See Avco thiottle operaliori the new spark setting will retluce L yoom ing Operator’ s Manu al No. 60297- 12 for igni- possibility of detonation during extreme cold wenther tion tinting procedure. operation. Consequently this modification has been 3. Replace the engine nameplate with a new one, 4 incorporated in the production of new engines. This Avco Lycoining P/N 61548 which indicates new niodificntion may be incorporated in engines in ser- tinting angle. Also restamp the magneto nameplate vice as follows: to indicate the iuagneto is -9, -10, or -55 instead of -3, -6 or -45. NOTE Remove the left nla~neto from the engine alld as- certain if it is an iinpulse coupling or retard breaker The new mjgneto impulse coupling, LW- n~agncto. II the magncto has an impulse coupling pro- 391249 is available througli all Avco Ly- ceed as follows: coming distributors. PARTS DATA: 15" Lag Angle Magneto P/N Replaces Ma6nuto P/N Mag. Model Engine Application LW-349365-9 LW-349365-3 S4LN-1227 IO- 360-A1U, -A1B6, -C1C, -C1F, -CID6, -C1E6, AIO- 360-A1A, -A1D, -B1B, AEIO- 360-A1B6 LW-349365- 10 LW-349365-6 S4RN- 1227 LIO- 360-C1E6 LW-513GO-55 LW-51360-45 S$LN-21 IO- 360-A1D LW-391429 15’’ Lab’ angle magneto impulse coupling (replaces LW-34!)359 ooupling). 61548 Engine nanlcplate (rcl,laccs Iianiot,Latu with 25" UTC timing). See Avco Lycolning Service Instruction No. 1304 lor,rocurement procedure. Mumbur ol GAMA ORIGINAL As Page I of 2 ~2/ c´ ~i- AECEIVED i3Y P17P Manu~aclurers Aosocialion Service Instruction No, 1325 proceed as follows: NOTE L-526 for the proper method of reducing the retard i-i 1 If the left magneto was a retard breaker magneto, Electrical Components Division publication No. angle of the magneto to 150. 2. When this has been accotnplished replace the Do not perform this procedure on L IO- 360- magneto on the engine and retime both magnetos C1E6 engines equipped with LW-349285-8 using the 20" timing mark on the starter ring gear or LW-163005-12 magnetos inasmuch as instead of the 25" mark. See Avco Lycoming Op- these have the 15" retard angle. erator’ s Manual No.60297- 12 for timing procedures. 3. Replace engine nameplate with a new one, P/N 1. When left mqgneto has been removed from the 61548 which indicates new timing angle. Also, re- engine and has been identified as a retard breaker stamp the magneto nameplate the magneto is -7 or magneto, consult the latest revision of Bendix -11 instead of -1 or -2. PARTS DATA: 15" Retard Angle Magneto P/N Replaces Magueto P/N I Mag. Model I Engine Application LW- 3492 85- 7 LW- 3492 85- 1 S4LN- 1208 1O- 360- A1C, -C 1C, D1A, HZO- 360- GIB, AlO- 360-A1A, TIO- 360-A1B LW-349285-8 S4RN- 1208 LIO- 360-C1E6 LW- 163005-11 LW- 163005-2 S4LN-200 IO- 360-A1A, -C1A, HIO- 360-C1A, AEIO- 360-A1A LW- 368005-12 S4RN-200 LIO- 360-C 1 E6 61548 Eiigine nameplate (replaces nameplate with 250 ETC timing). See Avco Lycoming Service Instruction No. 1304 for procurement procedure. ,_j 18484, 18485 These nun~bers for Avco Lyconiing reference only. Page 2 of 2 t) -:la 6’ Rockwell International i_´• GlneraI Aviation Divi,ion 5001 North Rockwell Avenue Bethany. Oklahoma 73008 SERVICE INFORMATION NO. SI-132 11 May 1976 BEG\IQIX SERvlCE RULLEBIN NO. 583 MODELS AFFECTED: MODELS 500, 500P,, 500B, 50CU, 500S, 520, 560, 560A, 560E, 560F, 680, 680E, 680F, S80F(:?), 680FL, 680FL(P), AND MODEL 720, SERIAL NO’S 1 THRU 1876, MODEL 500S, SERIAL NO’S 3050 THRU 3275, MODEL 685, SERIAL NO’S 12000 TERU 12066, MODEL 112, SERIAL NO’S 1 THRU 473, MODEL 114, SERIAL NO’S 14000 THRU 14016, AND MODEL S-2R, SERIAL NO’S 14161~t THRU 2173R AND 5000R THRU 5082R. REASON FOR PUBLICATION: RECOMMEND COM:PLIANCE WITH PARTS II AND LlI OF BENDIX SERVICE BULLETIN NO. 583. WOIP FAA AIRWORTHINESS DIRECTIVE 76-07-12 PERTAINS TO THIS SAME SUBTECT. COMPLIANCE: SEE AIRWORTHINESS DIRECTIVE 76-07-12. BY WHOM WORK WILL BE ACCOMPLISHED: PART II PILOT PART III A& P MECHANIC OR EQUIVALENT r- APPROVAL: SEE BENDIX SERVICE BULLETIN NO. 583. ESTIMATED MAN HOURS: SEE BENDIX SERVICE BULLETIN NO. 583. PARTS DATA: SEE BENDIX SERVICE BULLETIN NO. 583. SPECIAL TOOLS: NONE. ACCOMPLISIIMENT INSTRUCTIONS: 1. Comply with Parts II and III of the attached Bendi:R Service Bulletin No. 583. ELECTRICAL LOAD: NO CHR;l~c;E. WEIGHT AND BALANCE: NO CHaNGE. PUBLICATIONS AFFECTED: NO RE$UJRED TO ROCKWELL INTERNATIONAL PUBLICATIONS. RECORD COMPLIANCE: Make rtpp-opria.te entry in wircr~bft maintenance records as follows: Bendix Service Bulletin No. 583, tia.tril At-ii 1378. entit2. rl ’Ignitioc Switches, Rotary Action, Key or Lever Actuated, Twist-To-Start, Push-?’o-S:ert, Twist-To-Start/Push-To-Prime Types", accomplished (date) PRRe 1 of 1 Electriical Components Division 1w38 SERVICE BULLETIN NO. 583 Printed April 1976 Page 1 of 7 Pages AIRCRAFT SUBJECT: Ignition Switches, Rotary Action, Key or Lever Actuated, Twist-To- Start, Push-To-Start, Twist-To-Start/Push-To-Prime Types. REASON FOR BULLETIN: I ’To alert all users of above 8endix Switch Types of possible personnel hazard. 11 70 provide a check procedure to detect a faulty Switch. III To provide Field Repair and Replacement Instructions and Identification. EQUIPMENT AFFECTED: B Ignition Switches; Refer to Table I. TABLE I. BENDIX AIRCRAFT IGNITION SWITCHES, ROTARYACTION, KEY OR LEVER ACTUATED. Switch Function Key Lever Switch Part Number X 10-357200-1 Twist-To-Start X 10357 230-1, -2, 10-357260-1 10-126630-1 X 10-126690-1 X 10-357210-1 Push-To-Start I I X 10-357240-1, 10-357270-1 X 10-126680-2 X 10´•157440-1. -2, -3, -4, -21 Twist-To-Start X 10-357220-1 X 1 0-3 57 250- 1 1 0- 3 5 7 280- 1 Push-To-Prime X 10-126680-1 X 10-126660-1, -4 NOTE:"SWITCH FUNCTION," TABLE I ABOVE, IS USED AS AN APPLICABLE MEANS FOR INITIAL FRONT VIEW SWITCH IDENTIFICATIOIU SINCE ACTUAL PART NUM3ERS ARE ON THE SWITCH HOUSING ANDBECOME VISIBLE ON LY AF TE R SW ITCH BECOMES ACCESSIU LE FOR EXAM I NATION. Maintenance (Spare) Parts Affected: Numbers in Table I to a possible personnel hazard, (II) Same as In Table I above, provides a way by which a faulty switch can be detected and (III) provides instructions to cover field repair/ Compliance: rep:acement of the switch and identification of switches Parts 1 and II Immediate once repaired or replaced. Part III As soon as practicable after accomplishment of Part II. PART I. Possible Hazard Description. Detailed Instructions: Field reports indicate that occasionally switches per- This bulletiii (I) alUII, oil u~crs and holders of Bendix forming the "Switch Function" listed in Table I have Aiicraft Ignlrionn SwitL~hc’´• Iistc!(l I,y functiori arid Part been found to leave the right magneto "Live" or "Hot." Bendi Electrical ~e,il ComponentsDivision SERVICE BULLETIN NO. 583 Snlnrv Ne~York 13838 Printed April 1976 Page 2 of 7 Pages The condition may exist when the switch Key/Lever is condition described until the switch has been replaced rotated slightly pastthe normal indicated "OFF" or repaired. position. It has also been reported that the switch may stick in this position. As an added precautionary measure, positive ignition grounding prior to correction of a switch fault can be WARNING accomplished by fabricating a jumper lead and tem- Should the propeller be moved by hand las during pre´• porarily installing it between the magneto primary ground flight) and a "Hot" magneto condition exist, the engine out:let or terminal of the magneto to a clean engine may fire and cause injury to personnel. ground point. All appropriate precautions shall be exercised by all Using the applicable primary grounding terminal kit personnel associated with an aircraft having the switch selected from Table II, assemble a grounding lead. TABLE II. APPLICABLE PRIMARY GROUNDING TERMINAL KlTS. Magneto Series Repair Kit Part Number or Wire. S20 Series Use Kit P/N 10-52305 for magneto P/N’s 10-51365-1, -2, -7, -13, -14, -15, -16, -17, -20, -25, -26, -27, -28, -29, -30, -31, -32, -33, -34, -35, -40, -42, -43, -44, -46, -47, -48, -53, -54. 39-79_020-5, -6. -8. -10 13.-14,-16. Use Kit P/N 10-52305-1 for magnetos P/N’s 10-51360-1,-10, -11, -25, -26, -29. Use Kit P/N 10-52306 for magnetos P/N’s -5, -6, -7, -8, -15, -17, -18, -19, -20, -21, -22, -23.-24,-25,-41. Use Kit P/N 10-157209 for magneto P/N’s 10-51360-45, -47, -48, -49. 10-51365-57, 10-79020-11, 17,-18,-19. S-200, S-600 Use Kit P/N all magneto P/N’s. Series S700 Series Use Kit P/N 10-171192 all magneto P/N’s. S-1200 Series Use jumper wire with No. 1r3 eyed terminar at magneto end, alligator clip at engine ground end. 02000 Series Use Kit P/N 10-3826;98 all magneto P/N’s. Remove the regulal´• aircraft switch lead at the magneto. are removed and the regular switch leads reinstalled. Install the jumper lead to the magneto and connect the other end to a convenient clear; engine grounding poin;. A log book entry must then be made signifying that the The engine will now be inoperative until the jumper leads condition has been corrected. 3 Electrical Bendix Cii~ Components Division SERVICE BULLETIN NO. 583 Printed April 1976 Page 3 of 7 Pages PART II. Switch Fault Detection Procedures. 3. Rotate the switch key or lever to the Procedure to accomplish compliance and detection of the extreme limit of its travel in the "OFF" problem descl.ibed in Part I is as follows. Procedure A may position direction. (This may be slightly be accomplished by observing engine operation during past the normal "OFF"positian of the switch positioning. Procedure B may be accomplished by switch.) Manually hold the switch con- checking, using a continuity device such as an ohmmeter trol there and observe the continuity or timing light, device indication. Procedure A Check using engine reactions. 4. Reaction of the continuity device should 1. Observing the engine manufacturers indicate that continuity exists between ground run-up procedures allow the ground and each individual switch (mag- engine to reach operating temperatures neto primary) lead. and perform a normal magneto check. 5. When the switch key or lever is released 2. With the engine at normal idle, rotate the from the manually held "Past OFF" switch key or lever through the "OFF" position, it should automatically return detent to the extreme limit of its travel to the normal "OFF" position. Each in the "OFF" position direction. switch (magneto primary) lead should 3. If the engine continues to run with the indicate continuityfrom the lead to switch manually held in the "Past OFF" ground. position, it is an indication that one magneto is still "Hot" or ungrounded. Any switch exhibiting a"Hot"magneto conditionTaetected 4. When the switch key or lever is released using either Procedure A or B, should be repaired or from the manually held "Past OFF" replaced at the earliest opportunity. position, it should automatically return to the normal "OFF" position where the Light Aircraft Ignition Switches of the rotary action "Hot" magneto condition should no type are primarily mechanical in construction, consisting longer exist and the engine should die. of springs, contactors, a contact plate and rotating parts 5. Any switch exhibiting a "Hot" magneto within a housing. As is true with most mechanical assem- condition when in the "Past OFF" blies, switches are subject to wear. Use of either Procedure position should be repaired or replaced A or B will detect a switch wear malfunction as well as (Ref: Part III) at the earliest possible provide a check on switch-to-magneto circuitry. The opportunity. procedures therefore would be appropriate for inclusion in aircraft operating routines at periodic check periods. Procedure B Using Continuity Device. 1. Remove the switch (magneto primary) Part III. Repair or Replacement. leads from both magnetos. A. Switches identified by 10-125XXX and 10- WARNING 157XXX Series Part Numbers are no longer During switch continuity checks, removal, repair, or manufactured and are superseded by the 10- replacement, both magnetos are "Hot." Should the 357XXX series switches. propeller be moved by hand during this time, the engine may fire and cause injury to personnel. Field repair of any of these series switches is not recommended beyond replacement of the 2. Connect a continuity device between support plate and switch contacts. It is also each switch (maqneto primary) lead recommended that if a new support plate is at the magnero end and a good ground installed, new contacts (3 required per switch) on the engine, also be installed at the same time. Electrioall Components Division SERVICE BULLETIN NO. 583 Sldnry~ New Yolk 10838 Printed April 1976 Page 4 of 7 Pages Table III provides superseding Switch Assembly Each Repair Kit contains a new support plate Part Numbers as well as Repair Kit Numbers. and three new contacts. TABLE Ill. PART NUMBER APPLICABILITY. Switch Switch Superseded Repair Kit P/N Function P/N By TwistTo- Start 1 0- 357 200- 1 10-357230-1, -2 1 ______ 1 (10-357510 10-357260-1 10-126690-1 10-357200-1 10-126630-1 10-357230-1 Push-To-Start 10-357210-1 10-357240-1 10-357270-1 10-126680-2 10-357210-1 10-357515 10-15744(31-1 10´•357270-1 10-157440-2 10-357270-2 10-157440-3 10-357270-2 1 0-1 57440-4 1 0´•´•3 57240- 1] 10-157440-21 1 10-357270-1 Twist-To-S;ari 10-357220-1 i10-357510 Push-To-Prime 10-357250-1 10-357280-1 10-126680-1 1 10-357220-1 10-126660-1 10-357250-1 10-126660-4 10-357280-2 B. To install a new Support Plate and Contacts, c. Directly beneath the support plate proceed as follows using Figure 1 as a guide for are three contacts, spring loaded parts identification, against the support plate. Care- fully separate the support plate 1. Disassembly and Inspection. from the main switch assembly a. Hold switch in a vertical position, and remove the three contacts and support plate up, springs (3 or 9). b. Using firm finger pressure, hold d. Retain the springs for use during the support plate against the switch reassembly. Discard old support housing while removing the two self plate and contacts. :appin(l screws. Retain screws for e. inspect remainder of switch assem- us during reassembly. bly for smoothness of operation Electrical Components Division SERVICE BULLETIN NO. 583 S~diirv NA(N YOrk ~jeje Printed April 1976 Page 5 of 7 Pages SELF TAPPING SCREW (2) SUPPORT PLATE 8 SWITCH HOUSING CONTACTS (3) SPRINGS (3 or 9) Figure 1. Identification of Switch Parts. and check the rotor for any visible and carefully install support plate defects. If any faults are found, to housing, observing that contacts replacement of the complete switch move into recesses. assembly is recommended using d. Holding plate against housing, turn Table III for replacement part key or lever through all switch number information. positions. If it does not turn freely 2. Reassem bly. through the detent positions, re- a. Apply a light coating of Beacon check contact, springs, and support P-290" non-conductive grease o; assembly. equivalent to contact surfaces e. Once switch operation is satis- contact wells in rotor and insulating factory, reinstall and tighten self surfaces over which contacts slide. tapping screws holding support b. Reinstall contact loading springs plate to switch housing. (3 or 9) in rotor. Position new con´• f. After svcritch has been completely tacts over springs so contacts will reassembled, check it for ease of move into triangular recesses when operation. There shall be little or pressure is applied. no drag between stops. Check for c. Locate boss on new support plate positive stops in all positions. over locating slot in switch housing Check switch action for a positive and free spring return from the Available from Esso Standard Oil Co., "START" position to the "BOTH" Johnson City, N. Y. 13790. position. The switch shall not Electrical ~omponents Division SERVICE BULLETINNO. 583 Sldnry N,´•w Ynr* )38jb Printed April 1976 Page 6 of 7 Pages spring back beyond or "overtravel" other suitable electrical continuity the "BOTH" position. indicating device, check the switch g. For switches with "Push" features, for proper electrical operation. check lever or key for a free push´• Refer to Table IV, V, or VI for ing action in proper switch posi- the switch type being tested. tions and for proper spring return There must be a continuity indi- from pushed position. cation between the terminals listed for each switch position. There 3. Testing. must be NO continuity between a. Remove any wires or jumpers these terminals and any other which may be present on the termi- terminal, between any other termi- nals at the rear of the switch. nals or between any terminal end b. Using an ohmmeter, timing light or the switch housing. TABLE IV. CONTINUITY’TEST, TWIST TO START. TABLE V. CONTINUITY TEST, PUSH TO START. Switch Continuity Only Switch Continuity Only Position Between Terminals Position Between Terminals OFF R and GRD I I OFF R and GRD L and GRD L and GRD L and R Sand PR R L and GRD R and unmarked next R L and GRD I I I to R R and unmarked R and GRD L R and unmarked next L R and GRD to R GRD and unmarked R and unrlarked next to R GRD and unmarked BOTH R and unmarked next BOTH R and unniarked to R START (twist and hold) GRD andunmarked j I START (twist and hold, do not GRD and unmarked S and BUT I I push) next to R L and BO r I L and BO L and LR I 1 I Land LR BO and LR BO and iR START (twist, push and hold) Same as above, plus BAT and un- marked next to BO. 7 Electrical eomponents Division S~onrr rur~ Yill~ 1)838 SE RV IC E BU L L ET IN NO. 583 Printed April 1976 Page 7 of 7 Pages TAB LE V I. CONTINU ITY TEST, TWIST TO STA RT- b. Switches repaired under Part I1I PUSH TO PRIME utilizing Repair Kits, P/N 10- 357510 or 10-357515 which have Switch Continuity Only a white dot on the plate adjacent Position Between Terminals to the Bendix marking will be in compliance with this Bulletin and a OFF RandGRD log book entry signifying Bulletin L and GRD com~liance shall be made. L and R I c. New replacement switches are iden´• S and PR tified by a four digit date code stamped on the switch housing LandGRD under the Bendix part number. R and unmarked Installation of a switch so iden- tified should be noted by an L R and GRD accompanying log book entry as R and unmarked being in compliance. GRD and unmarked BOTH R and unmarked Parts Required Per Article: t- As required, Part III, Table 111. STA RT (twisl and hold, do not GR~ and unmarked push) S and BAT L and BO Special Tools Required: Land LR None. 80 and LR RIME (twist, push and hold) Same as above, plus Man Hours Required: BAT and PR 1 Check Procedure Negligible. 2. Repair Procedure- liZ Hour 4. Identification. a. Switches checked and found satis- factory for continued use; make Weight Change: log book entry signifying com´• None. pliance with this bulletin. ´•´•´•h’":~T::-:- -´•rU~- ~I) Aockwell International ;-"-ip i4´• V General Aviation Divirion 5001 North Rockvvell Avenue -il ´•;:iil Bethany. Oklahoma 73008 __ ___j SERVICE INFORMATION NO. SI-134 14 May 1976 ASSURE GROUNDING OF VHF COMM ANTENNA MODELS AFFECTED: MODEL 112, SERIAL NO’S 167 THRU 369 AND 399 THRU 474 EQUIPPED WITH THE DORN AND MARGOLIN TYPE DM C70-1 VHF COMMUNICATlONS ANTENNAS. REASON FOR PUBLICATION: MOVEMENT OF THE VOR/ILS OR ADF INDICATOR NEEDLE DURING OPERATION OF THE VHF TRANSMITTER ON LOWER FREQUENCIES MAY BE DUE TO INSUFFICIENT GROUNDING OF THE VHF COMMUNI- CATIONS ANTENNA. THIS SERVICE INFORMATION LETTER IS BEING ISSUED TO ASSURE PROPER GROUNDING OF THE ANTENNA. COMPLIANCE: AT OWNER’S DISCRETION. BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC on EQUIVALENT. APPROVAL: NOT APPLICABLE. ESTIMATED MAN HOURS: TWO (2) HOURS. PARTS DATA: NOT APPLICABLE. SPECIAL TOOLS: LOW SCALE ’rORQUE WRENCH WITH 3/8 INCH SOCKET. OHMMETER TO CHECK CONTINUITY BETWEEN ANTENNA BASE PLATE AND FUSELAGE. ACCOMPLISHMENT INSTRUCTIONS: 1 Remove center headliner panels as necessary to gain access to antenna base plates. 2. To assure positive base plate grounding of the antennas, torque base plate mounting screws (4 places), in a criss cross pattern, not to exceed 20 inch pounds or until continuity can be read between antenna base plate and aircraft with antenna cable removed from the antenna. CAUTION Do not over-torque the mounting screws as physical damage may result to the antenna. 3. Reinstall center headliner panels. ELECTRICAL LOAD: NO CHANGE:. WEIGHT AND NO CHANGE. PUBLICATIONS A$FECTED: NONE. RECORD COMPLIANCE: NOT APPLICABLE: r~ ’d ~1 rLJ ~L Rockwell General Aviation Divirion CJ001 North Hockvvell Avenug Bethanv. Oklaholnil ~3b08 SERVICE INFORMATION NO. SI-135 6 October 1976 EIX)-AIIIE MITCIIELL SERVICE BIJLLETIN NO. MB-12 MODELS AFFEC?’EJ): MODEL 112, SERIAL NO’S. 3 THRU 470 EQLTIPPED WITH EDO-AIRE MITCHELL’S CENTURY I, CENTURY II23 OR CENTURY III AUTOPILOT KIT. REASON FOR PUBLICATION: RECOMMEND COMPLIANCE WITI-I EDO-AIRE MITCHELL SERVICE BULLETIN NO. MB-12. COMPLIANCE: SEE EDO-AIRE MITCHELL SERVICE BULLETIN NO. MB-12. nY WHOM WORK WILL BE ACCOMPLISHED: APPROVED EDO-AIRE MITCHELL OR RQCKWELL COMMANDER DISTRIBUTORS. APPROVAL,: SEE EW-AIRE MITCHELL SERVICE BULLETIN NO. MB-12. ESTIMATED MAN HOURS: SEE EDO-AIRE MITCHELL SERVICE BULLETIN NO. MB-12. PARTS DATA: SEE: EDO-AIRE M~CHELL SERVICE BULLETIN NO. MB-12. SPECIAL TOOLS: NONE. ACCOMPI,ISHMEN1’ INSTRUCTIONS: 1. Comply with Edo-Aire Mitchell Service Bulletin No. MB-12. EL,ECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. PUBI,ICATIONS AFFECTED: NO CHANGE REQUIRED TO ROCKWELL INTERNATIONAL PUBLICATIONS. RECORD COMP LIANCE: Make appropriate entry in aircraft maintenance records as follows: Edo-Aire Mitchell Service Bulletin No. MB-12, dated June 11, 1976, entitled ’aoll Servo Installation", accomplished (date) Parre 1 of i. SERVICE BULLETIN NO M~-12 FAA-DER 4I’PKOVED DATE 6-11-76 ~do-Aire Mi~chell TO Rockwell International, and EIIO-AIRE IVIITCHELL OtJners of Rockwel% Conunander Model 112 Aircraft, having SUBJLCT installed one of tht~ Autopilot Kite listed below, Roll Servo installation Riilletin affects tile Rockwcl.l Commander Model 112 aircraft: which have the following EAM Autopilot Kitsinstnllod: AUTO1)ILO’T MODI1I, NO: I\UTOPILOT TYPrl: S’rc: ~G1502Sb N(364 Century I sre SA1503SW N(363 Century ill STC SA1504SW At(362 Century iii All c,f the affected autopil.ot Instnllationy use an identical roll servt´• Instal:- I.ation. A report has been received from field that for these instatlations; it mav be:possible for the aifcron balance cable to become sufficlentlv slack so i-isto all.ow the roll servo brid:le cable clamp to contact the right: rudder cabl.e and t:hereeftex to cause a restriction In the´•a~lron control, systcn, date, tl-~ste have been no reports of such an event ~actually occurring, A thoran#h inspection and analysis has been conducted, with’ the inspections invol.vlu~ scverai Aircraft. DurLng these :inspections no evidence was Eaund to in~fic:nre that for these aircraft any colltrol cable interference had ever occurred. The subsequent annLyYis of data resulting from the investigations; did not determine that: an operational ailecon control retrrction was actuall.y possible, During rlie inspections, however, it wR8 obherved a pgssibility does exit;t for tlie aileron balance cable, ´•If sufficiently slack, to get under the servo cable guard, Thiscondition will not result in ;t control system restriction, but it Is undesirable because of ~he resulting in(:r@ased wear. Edo-Aire Mitchell believes these aircraft should be retrofit~:ad with cable guard bracket, P/N 7A16~h-2, the result of a recent And´•unrel;ited product ilnprovement. The purpose ul this Service HulLefin is to retrofit the affected aircraft installations with the current production c:abLe clamp.bol’tcs and servo cable guards. 1 of 5 ~1 EDO´•AIRE MITCHELL P´• O´• BOX B10 MUNICIPAL AIRPORT MINERAL WELLS, TEXAS 76067 (817) 325´•2517 MAN))A’I’OKY Al’ THE NEXT 100 HOUR OK ANNUAL -cl For the Rockwell Commander Model 112 aircr;ift which have installed one of the s´•. listed Autopilot Modelu, it is mandatory during the next LOO Hour or Annual Inspection, to accomplish The following: I. Lnspect the roll servo inseallation to determine if the bridle cable clamps, P/N 42A184-1, use Bolts, P/N 3S2L5 (AN3-5A, 10-32 x 5/8Lr. The longer bolts used in earlier installations were P/N 38106 (AN3-6A, 10-32 x 25/32L). The roll servo installation is located under the cabin floor, just aft of the main wing spar between the aircraft centerline and the right Hide of the fuselage. 2. If it is determined the AN3-5Ai 10-32 x 5/8L bolts are not used on the 42A184-1 cable clamp, the existing bolts are to be replaced with the 5/8 inch long bolts. The bolts should be replaced, using the procedure given in Paragraph 3 below. 3. After removing the existing bolts, check to see that the aileron cables are clean and free of dirt, grease, or oil at the point of clamp contact. Check the aileron control cable tension and adjust as necessary to within the manufacturers specification for this aircraft, Adjust the bridle cable tension to ten pounds, plus or minus two pounds, and tighten the 3S215 clamp bolts and 2838 nuts (AN36T-1032, Steel) to 55 5 inchpounds of-torque with a mini- mum gap remaining between clamphalves of ,005 inch after torquing. 4. The roll servo cable guards, P/N 741696-2, are to be installed on the roll servo. There are three of these guiiirds, to be locatedi_u´• in place of the existing guards, and as shown-on Drawing No. 69D943. After installation of the 3S215clc?mp bolts, and adjustment of cable tension as given above, adju~t the cable guard brackets to within 1/32" of the capstan O.D. and secure with the 6-32 screws provided, 5. After the,above is accomplished, ol,erate the allcron contral.s through their complete range of travel. Check to see that no binding or restrictlons’exist due to this servo Installation. 6. After the completion of the inspection and:parte replacement, as required, this service bulletin shall be replaced with the aircraft service records and a log book entry made to ~eflect compliance with Edo-Aire Mitchell Service Bulletin NB-12. Parts Kit, PK MB-12 should be ordered to comply with this Service Bulletin. The Parts Kit will be furnished atno charge. For Owners whose autop~lat, or Model 112 aircraft is in warranty, Edo-hire Mitchellwill pay an addi- tional allowance for labor. 2 of 5 Il:cio-i\Lie Mfcct~cll Lll~trlt,utorM anil Dcnl.crs, or RockweTI International I,l:;l:rll,ul:or~; ;Mlttl I,cnlcrH alny ~il,l’ly Tor Inl,l,r rc?lmhur~cment for the inspection orld irl~tnllntlon of the rtrclulrcd I)RTtH. (I’1II.H Jnbor re:lmbursement is for a ninxlniuni (I1 $20.00 I,er ;iirc:r:ITt InHtolluLlnII,, ctnd is available only ;~l’l’r"vctl Mlrcllcll c,r I~c,c´•kweL1 ]nLc!rual´•l~,nnl and DealerR.. Y.ligllt. stlouLd noc~ be ;I:i (1 result: of this replacement. When ordering the Parts Kit and/or submitting claims for labor reimbursement under this Service BulletFn, MU-12, the following information must be included: i. ~ircrafC Model and Serial Number, 2. Autopilot Model (AIC Number). 3. Autopilot Serial Number. Carl J. Director, Products and Service EaOlAIRE MITCHELL 3 ol 5 ORIGII\IAL qS RECEIVED Bi T?a;;P ’I/ f. I*.l;yn REVISIO*S 5 ii ii~l ORIGI NAL As 3 FF L" ~.TL l.’´•s-´•- IIE-E4CED PER E O a~T RECUVU) BY ATP 0 I PdY/569 P~C ~CO KCVISED PE9 F´•ECO´•r- 6:; .e arrr f 019 i, OL/jrgg-r P i ro A/RCRAF7-E ---t i /3) r~ Not5S 8 i- T/GHTEN CL~QMPBW7T TO 5~25/N. LbJ A/LERON/fiUDD~iP EX/S~NG PC/LLL~Y CkBL~ .OOSM/NGdP BRL(CXE~ LIFT~R TORPU~YC I NU~S(T*P/CdL) L j A S~ /Vo7;E e NOTE-5 70 SL~PYO WPJTAN ROTA 7/ON~ REiL1OY~ i i ~OPPIPOX. 57;P~P. COvEZ ~OND R~YLFRSE M070R LEilDS ON 2. aPJusT rre ~TEM /GZ) Fd~ZL_rLID A~D/OR T~ AX O I RUDDER /NTERCONN~CT CAP_~ ,CYST~M TO A M~V/MUM OF CL~4MNCE BETW~EN T~E i A/L,SRor/ CA6L85 CONN~CT CABLE CLAMPAND 7H5 3AS~ a 1 111 1 Iii LSCE NOJE 2 R~N;P T~ 7wE SERY/CE /NFO~QMAT/ON CfTA/’S CON P/i~iZtW/ /28,oa II ii (~2 pRR/r/AL BULKX~AD ~S P r 2. PoS/T/O~ TrlE C4PLsT~ly GV~RDS TO Y~t f OF 7-~ Q,D.. 4, ao;rvsT COBLE TO W/TY/r/ TH;f JOLEanNCP OUT 6Y TLcE ~KRCRAFJ i 6w 9 ANt~ IE~JS/ON 73icf gR/DLE MA /N SPA R CL1BLcr m /orzLss. 1 ii N-n STA/NL ~-9S STLf~EL .~/L Efi3rJ Csri SEcr/,, (/TEM ZOI 4ZA/84-/ CA~LLF C~’F /7 /8 /g R~;C.) 7-~3P y/t~-W A7- PA14 R~/LXk/EAD Fls*~;/zs. ~D CLaAs’PB~TLC ;45 SXPWN, Q 1ii 3 /4)(K~L C~EE) by /O 3 (R~i /2 (2) ZZJ‘i~jit Q s 7 19 ie /7 7ISl/o ;Q~) (0) (4) (2) --r i 2 s~ No~ 3 jji ’i 1~1 I P/N L OCR7~N W/fX 2 19 2 533 Nc/;r, PN-=54 :d_iZ CONTROL /N ii´•ci 21 iB 5Z/a PoS/T/CW 1 2117 95/52 -sCAaw_~N-s_e -6 ,ORB 43A50 3^US~i/NG 9’ O I,r 42A24~ 1 ciaMP 4 C~ 4 2(/3 42A/73-/ CABLE /4 781’73~9 /2 S2i9-C BR/DL~-CrBLE 6 IN 45 205 1 i "s 8 )(4) 7I8 /O /zl/e 45/34 r3/ASXL~R,. 2 S" ANTQC-CIO ~2) p) 8 8 ZSIB 619 2534 /JL~7; q d 6 9-r4L4 5 8 4 7 ,’547/ liZL AN5,7-c-~JZRB PART/AL 4 Is SS2/5 ~oL 7; P~s-J r X=~9L ~INJ -5A I jl V Ii (G;X9Y~ /14 7BR35-/ Zl(arF1) 1. I i 3 i 7B835 i 2 i I I ii i II i II 3Tr IITEmlP4ai~UUIEP I 3tSCPiPi:-´•- i~R ji’."" LIST OF MITERI~LS I !j :1.I. EDO-AIRE MITCHELL C-27-72 i :iL7 ~S t ru´• rltriro 1 MII(ER*L WELLS, TEXIS 2.--.- ii I´•)i ill. I --~I- I sGi*Et~ IITLE ~eS:- :-´•.:;;TP _~i/s 73 i! r-----~ --~-7 -1 IAK3GL~ Y""’i Lf’arf~l S’rc’i;Y--J~ I i ~wc,-i Ir Tm 1 L Cc-p~--X. S/ uti: ´•ss, .´•.isn )(L_II L _ /Z S.Cu I ~P?LICntioN I i L_. I__~´•t r ;i i j. -~´•L 6-11176 I>K- MB- 12 Parts List for i~tchell Service Bulletin No, MB-12 coverin6r Roll Servo Installation for Rockwell Commander Model 112 Qnty. Part No. De sc ription 3 7A1696-2 Cable Guard 3 3S215 Bolts Rockwellktemat~nal w i; Oanaral Aviation Dividon 5001 North Rockwell Avenue Bethany. Oklahoma 73008 SERVICE INFORMATION NO. SI-137 20 October 1976 ENGINE OPERATING TIPS MODELS AFFECTED: MODEL 112TC, SERIAL NO’S 13000 AND SUBS. REASON FOR PUBLICATION: PROVIDE OPERATING TIPS TO PILOTS FOR LYCOMING TO-360-C1A6D ENGINE. COMPLIANCE: DURING ALL ENGINE OPERATIONS. BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPERATOR. APPROVAL: NOT APPLICABLE. ESTIMATED MAN HOURS: NOT APPLICABLE. PARTS DATA: NONE. SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: I. Leaning is permissible during t~ud. 2. The mixture must be full rich for all takeoffs regardless of field elevation. 3. Never use full throttle for takeoff. It may be necessary to retard the throttle slightly during the takeoff roll to avoid overshooting the desired manifold pressure. 4. The pop off valve will NOT prevent the manifold pressure from exceeding red line. 5, Peak E.G.T. and the red line on the E.C.T. gauge are NOT the same. The red line is the maldmum allowable Turbine Inlet Temperature. 6. For different power settings, altitudes, and outside air temperatures, peak EGT will occur at a different temperature each time the engine is leaned. 7. It is recommended that cruise power be maintained during the descent. Just prior to initiating the descent, and again at 2000 foot intervals during the descent, enrichen the mixture by 50-100 degrees on the E.G.T. gauge. 8. The mixture should be full rich during approach and landing. 9. Every effort should be made to keep the manifold pressure and R.P.M. within their green arcs during all flight operations. 10. Allow the engine to idle for 5 minutes prior to engine shut down. Usually talo~ing back to the ramp will fulfill this requirement. 11. Make all throttle movements smoothly and carefully. 12. When using 42 inches of manifold pressure for climb out, a climb speed of 86 knots may be used if is cooling properly. Increase speed as required to 100 knots for cooling in warmer ambient temperatures ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. PUBLICATIONS AFFECTED: NONE. RECORD COMPLIANCE: NOT APPLICABLE. Page 1 of 1 ~i Ii ~O] i$PI I d TB Rockwell Internation~ Oenersl Aviation Division 5001 North Hockwcll Avenue Bethany, pklahomb 730()8 SERVICE INFORMATION NO. SI-138 11 April 1977 LOWEB BAFFLE ASSEMBLY MODIFICATION MODELS AFFECTED: MODELS 112TC AND 11ZTCA, SERIAL NO’S 13001 THRU 13169. REASON FOIt PUBLICATION; TO PREVENT THE LOWER BAFFLE ASSEMBLY FROM COMU~G IN CONTACT WITH THE LhND~TJG I;IGHT. THIS COULD POSSIBLY CRACK THE LANDLEJG L1’GHT OIL CAUSEnN ELECTRICAL SHORT. COMPLIANCE: AT OWNER’S DISCRETION. NO’tE IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYLNG WITH THIS SERVICE INFORMnTION, CONTACT YOUR NEAREST nOCKWELL COMMANDER DLSTRTBUTOR OR YOUR nOCKSn/ELL COMMANDER REGIONAL SERVICE MANAGER. BY WHOM WORK WILL BE ACCOMPLISHED.’ A P MECHANIC on EQUIVALEN’S. AP PRO~VAL: NOT APPLICABLE:. ESTIMATED MAN HOURS: TWO (2) HOURS. PARTS DATA: NOT APPLICABLE. SPECLAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: I. Remove upper and lower engine cowling as outlined in the Airplane Maintenance Manual., Section IV. 2. Remove staples through seal and baffle plate on lower baffle assembly in area to be trimmed (see 3. Trim lower left baffle plate as shown in Figure 1. 4. Rcinstall upper and lower engine cowling as outlined in the Airplane Maintenance Manual, Section 1V. ELECTRICAL LOAD: NO CHANGE. WEICIZIT AND BALANCE: NO CHANGE. I’UBLICATZONS AFFECTED: The Illustrated Parts Catalog change required by this: document will bt´• incorpor´•ated atthe next scheduled change/revision, ~t7E:C01[2L, COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: SeMrice Xnfor- Ination No. SI-138, dated 1.1 April 1977, entitled "Lower Baffle Assembly Modification", ELcoomplisheci Page 1 of 2 i: SERVICE INFOE1MATLON NO. SI1~38 C) O ooo 0 o y lo o 0 c o o 0 0 o o 0 O i TRIM %XISI~MG LEFT BAFFLE PLATE GS SHOWN BY SHADED AREA 0.7S"R i r------- -~f 10 O O 0 0 O O c 0 0 o 0 0 o liu -UI L-U vrr 1~ Cn)~L1(´•e Il-r-~ 1 I 1 1 1,7 1 -i´• L^- LOWER BAFFLE ASSY FWD VIEW LOQKING DOWN Figure i. 3 nT 3 ~Jll SERVICE PUBLICATIONS vevision notice Gulfstream Aerospace SERVICE INIFORMATION NO. SI-142 REVISION NO. 1 7 August 1987 FUEL VENT CHECK VALVE BALL INSPECTION This Revision Notice is being issued to delete Model 112, Serial Nos. 4 thru 380. Model and Serial No. effectivities are changed to read as follows: MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NOS. 3 AND 381 THRU 536 AND 13000. MODELS 112TC AND 11BTCA, SERIAL NOS. 13001 THRU 13166. MODEL 114, SERIAL NOS. 14001 THRU 14226. Page lofl pq RP-: Rockwell Internafiona9 7 ~"E G´•naral Aviation Divi~ion 5001 North Rockwell Avenue 2-a´• Bethany. Oklahoma 73008 i´•’!~ SERVICE INFORMATION NO. SI-142 15 September 1977 FUEL VENT CHECK VALVE BALL INSPECTION MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NO’S 3 THRU 536, MODELS 112TC AND 112TCA, SERIAL NO’S 13000 THRU 13166 AND MODEL 114,’SERIAL NO’S 14000 THRU 14226. REASON FOR PUBLICATION: POSSIBLE LEAKAGE OF FUEL VENT CHECK VALVES. COMPLIANCE: AT OWNER’S DISCRETION. WOTIE IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION, CONTACT YOUR NEAREST ROCKWELL COMMANDER DEALE R/DISTRIBUTOR OR YOUR ROCKWELL COMMANDER REGIONAL SERVICE MANAGER. BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT. APPROVAL: NOT APPLICABLE. ESTIMATED MAN HOURS: FOUR (4) HOURS. PARTS DATA: Contact your nearest Rockwell Commander Dealer/Distributor for 3/8-inch Type 5052 hollow aluminum balls (Code 5486401). SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. If fuel leakage is evident at lower fuselage fuel Vent outlet, proceed to step 3. IYOTL Fuel leakage may be observed at lower fuselage fuel vent outlet particularly when the tanks are full. 2. If no leaks are evident at lower fuselage fuel vent outlet, disregard this Service Information Letter. 3. Defuel airplane as outlined in the Airplane Maintenance Manual, Section II. 4. Remove outboard fuel cell access plate to gain access to fuel vent check valve. 5. Remove outboard wing access plate to facilitate removal of fuel vent check valve. 6. Disconnect left and right fuel vent tube assemblies from left and right fuel vent check valves. 7. Remove screws attaching htel vent check valves to left and right sing ribs at(W.S. 142.40 and remove check valves from airplane. 8. Remove cotter pin and ball from fuel vent check valves. 9. Place check valve balls in a small container of Avgas. 10. If check valve balls float, reinstall in e~sting fuel vent check valves using new AN380-2-6 cotter pins (see Figure 1.). Page 1 of3 2~ SERVICE INFORMATION NO. SI-142 EXISTING FUEL VENT HARDWARE TUBE ~REF) FUEL VENT CHECK ALVE (REF) WS 142.40 AN3 80- 2- 6 COTTER PIN FUEL VENT CHECK VALVE (REF) I t O CHECK EXISTING BALL BY PLACING IN A CONTAINER QF AVGAS, IF IT RIGHT INSTALLATION SMOWN FLOATS REINSTALL WITH NEW COTTER PIN. IF IT SINKS REPLACE WITH NEW LEFT INSTALLATION OPPOSITE 3/8" TYPE 5052 HOLLOW ALUMINUM BALL USING NEW COTTER PIN. Figure i. 11. If check valve balls do not float, discard eltisting balls and install new 3/8-inch balls using new AN380-2-6 cotter pins (see Figure 1.). 12. Reinstall eldsting fuel vent check valves in airplane using e~sting hardware. 13. Reconnect left and right fuel vent tube assemblies to fuel vent check valves. 14. Thoroughly clean all surfaces, to which sealing compound is to be applied, around fuel vent check valve and valve attaching screws with Methyl Ethyl Ketone (MEK) using clean paper towels or small paint brush and wipe clean. WOTE Clean an area longer and wider than the width of the finally applied sealant to provide ma~mum bonding. 15. Brush fuel vent check valve attaching screw heads and area around check valves with 1422, Class A sealant. Page 2 of 3 SERVICE INFORMATION NO. SI-142 18. Reinstall and reseal lower wing access covers, using PRC-1321, Class B sealant, as outlined in the applicable Airplane Maintenance Manual, Section V. 17. Inspect and pressure check the tanks after sealing compound has cured (approximately 8 to 10 hours) and check for possible leaks. CAUTIOW 1 CAUTION Do not attempt to apply pressure to the tanks without first sealing off all lines and vents, and without an adequate regulator to control pressure. Do not pressurize the tank in excess of 1/2 PSI (13.8 inches of water manometer) or structural damage may occur. 18. Refuel airplane as outlined in the applicable Airplane Maintenance Manual, Section II. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHA_NGE. SPARES AFFECTED: YES. PUBLICATIONS AFFECTED: NONE. RECORD COMPLIANCE: NOT APPLZCABLE. Page 3 of jl Rockwell International ;:´•1 ii´• ii "i´•11 c" La:General Aviation Division iml Na,nn,l,,la,... Bethany. Oklahoma 73008 SERVICE INFORMATION NO. SI-144 2 November 1977 ENGINE MUFFLER MODIFICATION MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NO’S 3 THRU 544. REASON FOR PUBLICATION: TO EXTEND ENGINE MUFFLER LIFE. COMPLIANCE: AT OWNER’S DISCRETION. NOTE IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION LETTER, CONTACT YOUR NEAREST ROCKWELL COMMANDER DEALE R/DISTRIBUTOR OR SE RVICENTER. BY WHOM WORK WILL BE ACCOMPLZSHED: A P MECHANIC OR EQUIVALENT AND A CERTIFIED HELI ARC WELDER. APPROVAL: NOT APPLICABLE. PARTS DATA: Procure locally 20 gauge (0.0375-inch) 321 stainless steel sheet MIL-S-6721. SPECIAL TOOLS: HELI ARC WELDING MACHINE. ACCOMPLISHMENT INSTRUCTIONS: 1. Remove upper and lower cowling from as outlined in the Airplane Maintenance Manual, Section IV. 2. Remove muffler from engine and inspect for cracks. 3. If cracks are found, install a new muffler and proceed to step 6. 4. If no cracks are found, fabricate two (2) doublers from 20 gauge (0.0375-inch) 321 stainless steel sheet MIL-S-6721 as shown in Figure 1. 5. Install doublers, fabricated in step 4., on eldsting muffler by Hell Are welding around the inside diameter, the outside diameter and between the two doublers (see Figure 1.). 6. Install modified muffler or a new muffler on the engine. 7. Reinstall upper and lower cowling on the en~ne as outlined in the Airplane Maintenance Manual, Section IV. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANCE. SPARESAFFECTED: YES. RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Service Informa- tion No. SI-144, dated 2 November 1077, entitled ’’Engine Muffler Modification", Page 1 of 2 SERVICE INFORMATION NO. SI-144 ~I2.60" DIA 5.00" DIA //I EXISTING MUFFLER (REF) MAKE TWO DOUBLERS FROM 20 GAUGE (0.0375") 321 STAINLESS STEEL MIL-S-6721 AS SHOWN ABOVE INSPECT THIS AREA AND IS NO CRACKS ARE FOUND INSTALL TWO DOUBLERS AS SHOWN BY HELI ARC WELDING AROUND INSIDE AND OUTSIDE DIAMETERS OF DOUBLERS AND AT THE TWO PLACES WHERE THEY JOIN. Figure i. Page 2 of 2 -tl I on 3( Rockwell International a 9 General Aviation Divilion 5001 North Rockwell Avenue Bethany. Oklahoma 7300s SERVICE INFORMATION NO. SI-145 7 November 1977 IMPROVED INDUCTION AIR BOX INSTALLATION MODELS AFFECTED: MODELS 112TC AND 112TCA, SERIAL NO’S 13000 THRU 13249. REASON FOR PUBLICATION: TO PROVIDE INSTALLATION INSTRUCTIONS FOR AN IMPROVED INDUCTION AIR BOX ASSEMBLY. COMPLIANCE: WHEN REPLACING EXISTING P/N 615042-1 INDUCTION AIR BOX ASSEMBLY WITH IMPROVED P/N 615042-501 INDUCTION ATR BOX ASSEMBLY IOTE IF ANT PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION LETTER, CONTACT YOUR NEAREST ROCKWELL COMMANDER DEALER/DISTRIBUTOR OR SERVICENTER. BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT. APPROVAL: NQT APPLICABLE. ESTIMATED MAN HOURS: FOUR (4) HOURS. PARTS DATA: Contact your nearest Rockwell Commander Dealer/Distributor for P/N 615042-501 Induction Air Box Assembly. SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. Remove upper and lower cowling from engine as outlined in the Airplane Maintenance Manual, Section IV. 2. Disconnect Eer duct from elbow on top of induction air box assembly. 3. Disconnect controls from induction air box assembly. 4. Disconnect clamp attaching defroster flex duct to clip on top of induction air box assembly. 5. Remove cover assembly from top of eldsting induction air box assembly and remove filter. WOTE Retain filter for later installation. 6. Remove eldsting screws (4 places) attaching cowl flap control support assembly to bottom of induction air box assembly. 7. Remove insulation from aft side of firewall, as necessary, to expose rivets attaching induction air box assembly to firewall. 8. Drill out rivets attaching induction air box assembly to firewall and remove induction air box assembly from airplane. Page 1 of 3 SERVICE INFORMATION NO. SI-145 615042-501 INDUCTION 0.35" TYP ,AIR BOX ASSEMBLY +iilJ~0.35"TYPf t I It -t 3 EQUAL SPACES -t i t !I II+ +~MS20615-4M RNET (TYP) II -t II I!+ t ii I; -e II /EXISTING FIREWALL (REF) Ij t II I~t ii If t I I, ;____II 0.35"TYP VIEW LOOKING FWD Figure i. Page 2 of 3 SERVICE INFORMATION NO. SI-145 9. Locate, drill and install 615042-501 induction air box assembly on firewall using MS20615-4M rivets (see Figure 1.). NOTE Back drill through existing holes on firewall and add four (4) holes in upper flange of box assembly, firewall and firewall channel. 10. Apply Coast Proseal 700, MIL-S-38249, Type 1 (or equivalent) sealant on upper and lower edges and side flanges of induction air box assembly. 11. Reinstall cowl flap control support on bottom of induction air box assembly using edsting hardware. 12. Remove cover assembly from top of new induction air box assembly, install existing filter and reinstall cover assembly. 13. Reinstall e~sting clamp on defroster duct and attach to clip on top of induction air box assembly using elristing hardware. 14. Reconnect controls to induction air box assembly using edsting hardware. 15. Reinstall flex duct on elbow located on top of induction air box assembly. 16. Check rigging of the induction air box assembly to assure that the door is closed when the control lever, located on the control pedestal, is in the COLD position. 17. Reinstall the upper and lower cowling as outlined in the Airplane Maintenance Manual, Section IV. 18. Reinstall edsting insulation on aft side of firewall with EC 1403 adhesive. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. SPARES AFFECTED: YES. PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at the next scheduled change/revision. RECORD COMPLIANCE: NOT APPLICABLE. Page 3 of 3 SERVICE PUBLICATIONS vevision notice Gulfs~ream Aerospace SERVICE INFORMATION NO. SI-147 REVISION NO. 1 7 August 1987 SPARES REPLACEMENT FUEL VENT CHECK VALVE INSTALLATION This Revision Notice is being issued to delete Model 112, Serial Nos. 4 thru 380. Model and Serial No. effectivities are changed to read as follows: MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NOS. 3 AND 381 THRU 544 AND 13000. MODELS 112TC AND 112TCA, SERIAL NOS. 13001 THRU 13270. MODEL 114, SERIAL NOS. 14001 THRU 14407. Page 1 of 1 Rockwell Internafion; O´•rurll Avi´•tion Diviion 5001 North Rockmll Avenue &thsny. O~lahoma 73008 SERVICE INFORMATION NO. SI-147 21 July 1978 SPARES REPLACEMENT FUEL VENT CHECK VALVE INSTALLATION MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NO’S 3 THRU 544 AND 13000, MODELS 112TC AND 112TCA, SERIAL NO’S 13001 THRU 13270, AND MODEL 114, SERIAL NO’S 14000 THRU 14407. REASON FOR PUBLICATION: TO PROVIDE INSTALLATION INSTRUCTIONS FOR AN IMPROVED FUEL VENT CHECK VALVE. COMPLIANCE: WHEN REPLACING EXISTING PART NO. 48538 FUEL VENT CHECK VALVE WITH NEW REPLACEMENT PART NO. 35C6A FUEL VENT CHECK VALVE. WO’lli IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WTTH THIS SERVICE INFORMATION LETTER, CONTACT YOUR NEAREST ROCKWELL COMMANDER AUTHORIZED SERVICE FACILITY. BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT. APPROVAL: FAA DOA SW-2 Approved. ESTIMATED MAN HOURS: FOUR (4) HOURS. PARTS DATA: Contact your nearest Rockwell Commander Authorized Service Facility for the new substitution/ replacement fuel vent check valve kit Part No. 48509-450. SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. Defuel airplane as outlined in the Airplane Maintenance Manual, Section n. 2. Remove left and right outboard fuel cell access plates to gain access to fuel vent check valves. 3. Remove left and right outboard wing access plates to facilitate removal of fuel vent check valves. 4. Disconnect left and right fuel vent tube assemblies from left and right fuel vent check valves. 5. Remove screws attaching fuel vent check valves to left and right wing ribs at W.S. 142.40 and remove and discard check valves. 6. Plug holes in wing ribs with MS20470AD6 rivets and seal as outlined in the applicable Airplane Mainte- nance Manual, Section II under Sealing Procedures. 7. Disassemble 35C6A fuel vent check valve as follows (see Figure 1.): a. Loosen lamb nut on elbow. b. Remove B-nut from elbow. c. Remove lamb nut from elbow. d. Remove and discard large washer. $r~L Page 1 of 3 SERVICE INFORMATION NO. SI-147 PLUG EXISTING HOLE WS\ WITH MS20470AD6 RIVET EXISTING FUEL 42.40) !2 PLS) (SEE STEP 8.) UPPER WING VENT TUBE ASSY (RE Fl SKIN (REF) 3.25" -(A T"1’-7 r---~ O1 1.20" O ii I j ;-I-I---- 1 I I, ii A 48509-7 PLATE CAUTION: VENT VALVE MUST BE INSTALLED WITH 35C6A FUEL VALVE OPENING VENT CHECK POINTED DOWN VALVE COVTBD VIEW LOOKING FWD INTERCOSTAL (REF) ELBOW (REF) MS21919DF6 MS20470AD4 CLAMP RIVET INTERCOSTAL JAMB NJT (REF) (RE Fl O B-NUT (REF) VIEW A-A AN3-5A BOLT NAS43DD3-10 SPACER AN960-10 WASHER MS21044N3 NUT 35C8A FUEL VENT CHECK VALVE (LARGE WASHER REMOVED) LEFT INSTALLATION SHOWN RIGHT INSTALLATION OPPOSITE ~ipur´• i. 3Page 2 oi 3 SERVICE INFORMATION NO. SI-147 8. Reassemble 35C6A fuel vent check valve as follows (see Figure 1.): a. Install jamb nut on elbow and run nut all the way up on threads. b. Install B-nut on elbow, assuring that the neat ball is inside the B-nut, and tighten B-nut on elbow. c. Torque jamb nut against B-nut. 9. Locate, drill and install 48509-7 plate on left and right wing intercostals (see Figure 1.). 10. Install 35C6A fuel vent check valves on left and right fuel vent tube assemblies (see Figure 1.). 11. Install MS21919DF6 clamps (see Figure 1.). 12. Reinstall and reseal lower wing access plates, using PRC-1321, Class B sealant, as outlined in the applicable Airplane Maintenance Manual, Sect~on V. 13. Inspect and pressure check the tanks after sealing compound has cured (approlcimately 8 to 10 hours) and check for possible leaks. CAUT ION Do not attempt to apply pressure to the tanks without first sealing off all lines and vents, and without an adequate regulator to control pressure. Do not pressurize the tank in excess of 1/2 PSJ (13.8 inches of water manometer) or structural damage may occur. 14. Refuel airplane as outlined in the applicable Airplane Maintenance Manual, Section II. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. SPARESAFFECTED: YES. PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at the nerrt scheduled change/revision. RECORD COMPLIANCE: Make appropriate entry in airplane Maintenance records as follows: Service Infor- mation No. SI-147, dated 21 July 1978, entitled "Spares Replacement Fuel Vent Check Valve Installation", Page 3 I Rockwell Internationai General Aviation Divi~ion 5001 North Rockwell Avenue Bethany. Oklahoma 73008 1 5 SERVICE INFORMATION NO. SI-148 28 March 1978 SPARES REPLACEMENT FUEL PUMP INSTALLATION MODELS AFFECTED: MODEL 112, SERIAL NO’S 3 THRU 380. REASON FOR PUBLICATION: TO PROVIDE INSTALLATION INSTRUCTIONS FOR SPARES REPLACE- MENT FUEL PUMP. COMPLIANCE: WHEN REPLACING EXISTING PART NO. A8120A FUEL PUMP WITH NEW REPLACEMENT PART NO. A8120C FUEL PUMP. WO’IE IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION LETTER CONTACT YOUR NEAREST ROCKWELL COMMANDER DEALER/DI~TRIBUTOR OR SERVICENTER. BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT. APPROVAL: FAA DOA SW-2 Approved. ESTIMATED MAN HOURS: Sur (6) HOURS. PARTS DATA: Contact your nearest Rockwell Commander Dealer/Distributor or ServiCenter for the new Spares replacement fuel pump kit part number 635021-450. SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. Cain access to the battery, located in the aft fuselage, through the baggage compartment door. 2. Remove baggage compartment liner, as necessary, to expose battery. 3. Remove cover from battery and disconnect battery cables from battery. 4. Remove upper and lower cowling from en~jne as outlined in the Airplane Maintenance Manual, Section IV. 5. Assure that the master battery switch is in the OFF position and the fuel selector is also in the OFF position. 6. Open gascolator and drain fuel. 7. On Serial Numbers 221 thru 380, disconnect gascolator drain cable from top of gascolator. 8. Disconnect tube assemblies and hoses from fuel pump and gascolator and cap all fuel lines. 9. Disconnect electrical wiring from fuel pump. 10. Remove fuel pump and gascolator from firewall. 11. Plug eldsting holes in firewall with existing screws and MS20365-416C nut (4 places) (see Figure 1.). 12. Reduce brake system pressure to zero, remove and discard elristing brake tube assembly, forward of engine firewall, that is routed from pilot’s right brake cylinder over to copilot’s right brake cylinder and cap firewall fittings. 13. Remove gascolator from e~isting fuel pump. Page 1 of 5 SERVICE INFORMATION NO. SI-148 VIEW LOOKING DOWN 46308-1 BRACKET ASSY 46099-227 TUBE ASSY (REPLACES TUBE ASSY REYOVED IN STEP 12;) i FWD AN9111-ZJ NIPPLE ENGINE FIREWALL (REPLACES FITTING (REF) I REMOVED IN STEP 17.) /L 0) (O EXISTING FUEL SUPPLY TUBE ASSY (REF) MS29512-06 O-RING AND EXISTING ELBOW I I EXISTING GASCOLATOR AND NUT C-~ (RE Fl 6-1/4F5CS PIPE ADAPTER MS29512-06 O-RING ’EXISTING GASCOLATOR DRAIN CABLE (S/N 221 THRU 380) (REF) VIEW LOOKING AFT MS21919H40 CLAMP A8120C FUEL PUMP ’I 1’5" AN3-5A BOLT AN960-10L WASHE R (I)/ I ENGINE FIREWALL NAS43DD3-8 SPACER (REF) (BETWEEN BRACKET ASSY AND CLAMP) EXISTING DRAIN FITTING (REF) jEXISTING FUEL PUMP i~ I) 10 O IDRAIN HOSE (REF) O PLUG HOLES MS20365-416C NUT AND EXISTING SCREW (4 PLS) EXISTING STIFFENER (RE Fl EXISTING GASCOLATOR DRAIN HOSE (REF) Figure 1. Page 2 of 5 SERVICE INFORMATION NO. SI-148 14. Remove eldsting drain fitting from fuel pump and retain fitting for later installation. 15. Remove eldsting elbow and nut from fuel pump and retain elbow and nut for later installation. 16. Discard e~isting fuel pump and O-rings. 17. Remove and discard e~sting fitting from the right port of the gascolator. 18. Install existing elbow and nut (removed in step 15.)., MS29512-06 O-ring (2 places) and 6-1/4F5GS pipe adapter on A8120C fuel pump (see Figure 1.). 19. Apply teflon tape (3M No. 547 or equivalent) to threads of AN911-2J nipple and erdsting fuel pump drain fitting (removed in step 14.) as follows: a. Place tenon tape two (2) threads in from end of male pipe threads and hold tape firmly with thumb. b. Stretch tape against threads and wind clockwise one (1) lap. Continue to hold tightly against threads until tape has been broken. WOTE Do not attempt to tear tape sideways. Snap tape off in same direction used for winding. 20. Install edsting drain fitting on fuel pump (see Figure i.). 21. Install AN911-2J nipple on existing gascolator (see Figure 1.). 22. Install gascolator on A8120C fuel pump (see Figure 1.). 23. Temporarily install 46308-1 bracket assembly and MS21919H40 clamp on A8120C fuel pump (see Figure 1.). 24. Position A8120C fuel pump and elcisting gascolator against en~jne firewall and connect e~sting tube assemblies and hoses to fuel pump and gascolator (see Figure 1.). 25. Temporarily install 46099-227 tube assembly (see Figure i.). 26. Mark position of 46308-1 bracket assembly on engine firewall and mark bracket assembly upper attach- ing hole on en~jne firewall (see Figure i.). WOTIE Assure that 46099-227 tube assembly does not rub against bracket assembly grommet and that 46308-1 bracket assembly is oriented with 5 degree tilt as shown in Figure 2. 27. Remove 46099-227 tube assembly from airplane. 28. Disconnect tube assemblies and hoses from fuel pump and gascolator and remove fuel pump and gascolator from airplane. 29. Remove 46308-1 bracket assembly and clamp from fuel pump. 30. Drill and install 46308-1 bracket assembly on engine firewall. Observe 0.50-inch minimum edge distance on stiffener and 5 degree tilt down to gascolator (see Figure 2.). WOTO Remove any rivets from engine firewall that interfere with installation of bracket assembly and replace with MS20427M4-4 flush rivets. 31. Install 46099-227 tube assembly on en~ne firewall fittings (see Figure 1.). 32. Install A8120C fuel pump and eldsting gascolator and connect tube assemblies and hoses to fuel pump and gascolator (see Figure 1.). Page 3 of 5 SERVICE INFORMATION NO. SI-148 0. 166"/0. 170" DIA HOLE LEGEND: EXISTING HOLES IN BRKT TO BE MS35207-245 SCREW LEFT OPEN Q) AN960-8 WASHER HOLES TO BE ADDED PICKING UP MS21044-N08 NUT FIREWALL STIFFENER (4 PLS) 46308-1 BRACKET I: ASSY (REF) VIEW LOOKING AFT 0. 30" MIN Ih__l_____ --7---- (REF) I FIREWALL STIFFENER olO. 30" MIN ENGINE FIREWALL(REF) ~m FUEL PUMP REMOVED FOR CLARITY Figure 2. FUEL PUMP CBSFUEL PUMP CBS 1 183 &1 A20 b270 &1 s20 FUEL PUMP FUEL PUMP SERIAL NO’S 3 THRU 187 SERIAL NO’S 188 THRU 380 Figure 3. Page 4 of 5 SERVICE INFORMATION NO. SI-148 33. On Serial Numbers 221 thru 380, reconnect gascolator drain cable to top of gascolator (see Figure 1.). 34. Connect fuel pump to airplane electrical system (see Figure 3.). 35. Assure that all fuel lines are tightened and no fuel leaks are evident. 36. Reconnect battery cables to battery and install cover on battery. 37. Reinstall baggage compartment liner. 38. Bleed brakes as outlined in the Airplane Maintenance Manual, Section VI. 39. Reinstall upper and lower cowling on engine as outlined in the Airplane Maintenance Manual, Section IV. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. SPARES AFFECTED: YES. PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and Illustrated Parts Catalog changes required by this document will be incorporated at the next scheduled change/ revision. RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Service Infor- mation No. SI-148, dated 28 March 1978, entitled "Spares Replacement Fuel Pump Installation" accomplished (date) Page 5 of 5 Rockwell International Service Information General Aviation Divilion 5001 North Rockwell Avenue Bethany, Oklahoma 73008 SERVICE INFORMATION NO. SI-149A (Supersedes Service Information No. SI-149 dated 17 March 1978 in its ~entirety) 13 September 1979 HYDRAULIC POWER PACK VENT PORT SCREW ADJUSTMENT MODELS AFFECTED: MODELS 112 AND 112B, SERIAL NO’S 13000 AND 3 THRU: 544, MODELS 112TC AND 11%TCA, SERIAL NO’S 13001 THRU 13309 AND MODELS 114 AND 114A, SERIAL NO’S 14000 THRU 14540. REASON FOR PUBLICATION: TO PREVENT THE POSSIBILITY OF THE HYDRAULIC POWER PACK VENT PORT BEING INADVERTENTLY CLOSED. COMPLIANCE: WHEN REPLACING POWER PACK AND UPON EVIDENCE OF SLOW LANDING GEAR EXTENSION. WOTE IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION, CONTACT YOUR NEAREST ROCKWELL COMMANDER AUTHORIZED SERVICE FACILITY. BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPE RATOR. APPROVAL: NOT APPLICABLE. EST~VIATED MAN HOURS: THIRTY (30) MINUTES. PARTS DATA: NOT APPLICABLE. SPECIAL TOOLS: NONE. ACCOMPLIS;HMENT INSTRUCTIONS: 1. Gain access to the hydraulic power pack, located on the left side of the aft fuselage, through the baggage compartment door. 2. Remove the left side baggage compartment access panel to expose the hydraulic power pack. 3. Check ~hydraulic power pack vent port to assure that clearance between vent port washer and hydraulic power pack boss s a minimum of 0.06 inch (see Figure 1.). WOTE Vent is under washer. 4. If clearance between hydraulic power pack vent port washer and hydraulic power pack boss is a minimum of 0.06 inch, proceed to step 6. 5. If clearance between hydraulic power pack vent port washer and hydraulic power pack boss is less than 0.06 inch, adjust vent screw to obtain proper clearance of 0.06 inch minimum (see Figure 1.). 6. Reinstall the left aide baggage compartment access panel. ELECTRICAL LOAD: NO CHANGE. WEIGHT AND BALANCE: NO CHANGE. SPARESAFFECTED: NO. Page 1 of 2 SERVICE INFORMATION NO. SI-149A 3 0.06" MIN. EXISTING VENT I_ SCREW (REF) EXISTING WASHER (REF) tHYDRAULIC POWER PACK BOSS (REF) VENT HOLE (REF) HYDRAULIC HYDRAULIC VENT PORT POWER PACK SCREW 1 I\ J (REF) HYDRAULIC FILL PORT Figure I. PUBLICATIONS AFFECTED: The Airplane Maintenance Manual change required by this document will be incorporated at the next scheduled change/revision. RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Service Information No. SI-149A, dated 13 September 1979, entitled "Hydraulic Power Pack Vent Port Screw Adjustment", accomplished (date) Page 2 of 2 Rockwell International Owr~ *vbtion Di*hion soot Narth Rockvrrll Avsnus B~th´•ny. O~llhoma 73008 SERVICE INFORMATION NO. SI-157 17 November 1978 ROCKWELL-COLLINS SERVICE BULLETIN NO. 8 MODELS AFFECTED: THE FOLLOWING EQUIPPED WITH COLLINS MICROLINE TDR-950 TRANSPONDER WITH UNIT SERIAL NO’S. 8100 THRU 8600: MODEL 112, SERIAL NO’S 446 THRU 499 AND 13000, MODEL 112B, SERIAL NO’S 500 THRU 544, MODELS 112TC AND 11%TCA, SERIAL NO’S. 13001 THRU 13195, 13250 THRU 13276, MODEL 114, SERIAL NO’S. 14000 THRU 14437 AND MODEL 5005, SERIAL NO’S. 5269 THRU 3316. REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH ROCKWELL-COLLINS SERVICE BULLETIN NO. 8. COMPLIANCE: WITHIN NEXT FIFTY (50) HOURS TIME IN SERVICE. BY WHOM WORK WILL BE ACCOMPLISHED: AN AUTHORIZED COLLINS SERVICE AGENCY. APPROVAL: SEE ROCKWELL-COLLLNS SERVICE BULLETIN NO. 8. ESTIMATED MAN HOURS: ONE (1) HOUR. PARTS DATA: See Rockwell-Collins Service Bulletin No. 8. SPECIAL TOOLS: NONE. ACCOMPLISHMENT INSTRUCTIONS: 1. Comply with Rockwell-Collins Service Bulletin No. 8. ELECTRICAL LOAD: NOCHANGE. WEIGHT AND BALANCE: NO CHANGE. SPARES AFFECTED: NO. PUBLICATIONS AFFECTED: NONE. RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Service Infor- mation No. SI-157, dated 1? November 1978, entitled "Rockwell-Collins Service Bulletin No. 8", accomplished (date) Page 1 of 1 Rod~well-Collins I SERYICE BULLETIN Collins General Aviation Division/Rockwell International TDR-95O TRANSPONDER (622-2092-001 THROUGH -006) SERVICE BULLETIN NO 8 REPLY PULSE SPACING i. Planning Information A. Effectivity Mandatory on all TDR-950 Transponders with serial numbers between 8100 and 8600. B. Reason Encoder clock generator inductor L15 may exhibit inductance variations caused by temperature shock. Depending upon the extent of value change, some units may generate replies that do not meet the 20.3 cls +0.1 Cls pulse spacing specification for framing pulses Fl and F2. Although the transponder will appear to be operating properly in the cockpit (reply lamp will flash when responses are made to valid interrogations), air traffic control plan position indicators may not paint responses because of the erroneous framing pulse period. In this case, pilot reports on units experiencing this problem may include "inoperative unit" or "intermittent operation". C. Description (1) Technical Inductive variations in L15 will cause the decoder clock generator frequency to change. The resulting frequency shift may be sufficient to cause reply pulse spacing to fall outside of equipment specifications. To correct this problem, inductor L15 is replaced with a component that is not susceptible to temperature shock or inductance variation over the temperature and humidity ranges experienced during normal operating conditions. (2) Physical Inductor L15 is replaced with a component of the same value that does not drift with changes in temperature and humidity. Oct 16/78 TDR-950 SE 8 ~z Page 1 of 4 Rockwefl-Cdlins I SERVICE BULLETIN Collins Qeneral Aviation Division/Rockwell International D. Approval Conforms to FAA TSO-C74c. E. Manpower (1) An estimated 60 minutes is required to perform the subject modification and test circuit performance. (2) The time required to test the TDR-950 as a result of this modification will not be affected. F. Material Cost and Availability The component listed in paragraph 3 is required to modify one TDR-950 Transponder. This part is available for shipment within 30 days after receipt of order at a price of $0.65 (price subject to change without notice). The part may be obtained from your regional customer service manager. All orders should specify the Collins part number of the desired component and reference TDR-950 service bulletin 8. Collins Avionics/Rockwell International will bear the cost for implementation of this service bulletin including 60 minutes labor. G. Tooling Price and Availability None. H. Weight and Balance No effect. I. References (1) Other Service Bulletins/Service Information Letters This service bulletin obsoletes TDR-950 Transponder service information letter 2-78 entitled "F1/F2 Pulse Spacing", dated September 26, 1978. Incorporation of this service bulletin does not depend upon other service bulletins or modifications to the TDR-950 Transponder. TDR-950 SE 8 Page 2 Oct 16/78 Rod~well-Collins I SERVICE BULLETIN Collins General Aviation Division/Rockwell International (2) Other Publications Affected The third edition of the TDR-95O Transponder instruction book, Collins part number 523-0766464, will include the changes described in this service bulletin. J. Test Equipment No modifications to the specified test equipment is required to test the TDR-950 Transponder as a result of this modification. 2. Accomplishment Instructions A. Modification Procedure (1) Remove the transponder top and bottom covers to provide access to the circuit card. (2) Locate old inductor L15 and remove told L15 is located adjacent to L8; refer to partial component location diagram included in this bulletin). (3) Position new L15 as shown in the partial component location diagram. Wrap one lead of new L15 around the grounded end of R71 and insert the other lead into the hole vacated by old L15. Ensure L15 is located as close as possible to R71 as shown in the illustration. (4) Replace unit top and bottom covers and perform the test procedures included in paragraph C. B. Identification Procedure Use a knife to remove the number 8 on the modification plate and cover t