# LYCOIIIIIIIIG 

# MANDATORY \\ illi:un,Jwrc. I '\

**~~ul** t .-... \. T el. +1-800-258-3279 (U.S. and Canada) Tel. +1-570 - 323 - 6181 (Interna t ional) 

## I 

# SERVICE BULLETIN I Fax . +1-570-327-7101 www . lycoming . com DA T E: O ctobe r 1 0. 20 1 4 Serv i ce Bull eti n No . 6 1 4A (S up e r sedes Se r v i

ce Bull etin No . 6 1 4) En g ineerin g A s p ects are F

A A A pp r oved SU BJ ECT : E xhau s t S ys te m I ns pec ti o n and T urb oc h ar ge r Mo untin g B r acket R ep l a ce m e nt MOD ELS AFF ECTE D: Lycom in g En g ine M o de l T I0- 54 0 -A .J I A with a S eri al Numb e r I d e nt ifi e d in Ta b le I o r an y T I 0- 5 40-A J IA w ith a T urb o c harge r Mount in g B ra cke t Pu r chase d as a Spar e be tw ee n Ap r il S, 2 0 12 an d May 29 , 20 14 T I M E Of C OMP LI A NCE: Th e R eq u ired Acti o n mu s t be co mp l ete d wi th in th e next 25 ho u r s or n e x t sc hed u l e d ma int e nance e v e nt ( wh i c h e v e r occ ur s fir s t) f o r :


# I

R EAS ON FOR REV IS I ON: • Eng in es id e ntiti ed in Tab le I w ith 0 to 4 0 0 h o ur s tim e in se r vice s ince new, r e built , o r ove rh a ul e d. • En g in es w ith a tur boc h arge r m o untin g br ac k e t purch as ed as a s pare b e t we e n Apr il 5, 2 01 2 a n d M ay 29, 20 1 4 , w ith 0 to 400 ho urs t im e in se rv i ce s in ce br acket rep l aceme nt. • R e turn tur boc h ar ge r mo untin g br acke t s c urre nt ly in s t oc k. T h e R equired Act io n must be comp l e t

ed at n ex t ove rhaul fo r: • Eng i nes i de n t ifi ed in Ta bl e I with ove r 4 00 ho u r s tim e in se rv i ce s in ce n

evv r e buil t , o r ove rh a ul e d . • En g ine s w ith a turb oc h ar ge r mo untin g brac k e t pur c h ased as a s pa r e betwee n Apr i l 5 , 2012 a nd May 29 , 20 14 , w i th ove r 400 h o ur s t im e in s erv i c e s inc e bra c k e t r e pl ace m e nt. En g ine s e rial numb e r L
- 1 3 9 6 1 -6 1 E was adde d to Tabl e I . T her e are n o o th e r changes. NOT E I nco mp l e te re v i e w o f all t he informat i o n in th is d oc u m e nt ca n cau se e rro r s . R ead the en tire Se r vice Bu lle tin to make s ure you h ave a co m pl e t e und er s t a ndin g o f th e req uirem e nts . Thi s Se r vi ce Bul l e t in co ntains turb o charge r m o untin g brac k e t r ep lac e ment in s tru ct i o ns, d i sasse mb l y/ in s p ec tio n /asse mb ly in s tru c tio n s fo r the ex h a u s t sys t e m (F ig ures I a nd 2), and wa rran ty in s tru c ti o n s f o r s p ecific Lyco min g e n g in e mo de l s TI 0- 540-A J I A. id e n t i f

i ed in Tabl e I. T hi s manda to ry in s p ec t io n a nd tu rboc h arge r m o untin g bracke t re pl ace m e nt mu st be do ne o n e n g in es id ent ifi e d in th e T im e o f Com p iia nce above. Tab le I Se ri a l Nu mb e r s of A f fected Lyco min g Engi n e Mode l s T I 0
- 540
- A J I A En g in e Seri al N umb e r Engin e Se ria l N um be r En g in e Se ri a l N u mbe r En g in e Se ri a l N umb e r L-6748-6 1 E L- 1 3 8 2 8-61 E L- I 3832
- 6 1 E L-1 3 843
- 61 E L-1 3 81 7-6 1 E L- 13 8 31
- 61 E L- 13833-6 1 E L- I 3 84 7
- 6 1 E L

- 138 19
- 6 1E L-1 3 82 3
- 6 1 E L -1 3839-6 1 E L
- 13 855- 6 1 E I SSUED R EV I SE D PA G E N O
. R EV I S I ON



## ~ General Aviation

**~,** Manufacturers Association MO 

### I DA Y 

### I YEAR M O 

### I DA Y 

### I Y EA R I o f 1 2 A 07 

### I 24 

### I 1 4 10 

### I 1 0 

### I 1 4 0 2014 t\\CO Coi]JO rauoo 1 \ ll

**lu s**  R eserved L yco mi n g Eng •n es 1$ a davlsio n of t h 'Co Corporal eo n

### Table I ( Cont. ) Serial N umb e r s o f Affected L y

c o min g E ngine Model s TI0- 540-J\J IA L-1 3 856
- 61 E L- 1 3 947-61 E lr 

### 140 I 1-6 I E RL- 2 55 1 -61 E L- 1 3 857
- 61E L- 1 3948
- 61 E L- 1 40 1 3
- 6 1 E RL-2848-61 E L- 1 3866 -61 E L-13949 -61 E L
- 1

40 1 4
- 6 1 E RL-3450-61 E L- 1 3867 -61 £ L-13950-61 E L- 1 40 15 -61 E RL-4138 -6 1 E L-13873-61 E L-1 3 960-61 E L-14017
- 61 E RL
- 7243
- 61 E L-1 3 882
- 61 E 

# I L
- 1 3 96 1- 61 E L
- 14024-6 1 E RL-7 5 1 2
- 6 1 E L-1 3 883
- 6 1 E L-1 3 962-61 E L-1402 5-61 E RL-8 43 5-61 E L-1 3 884
- 6 1 E L-1 3 967
- 61 E L- 1 4026-61 E RL-8767-61 E L-13885-6 1 E L-1 3 973-61 E L-14028
- 61 E R L-8914-61 E L-13886-61 E L- 1 3975
- 61 E L-14034
- 6 1 E RL-8979-61 E L- 1 3895 -61 E L- 1 39 76-61 E L- 1 4054-6 1 E RL-9399-6 1 E L-13896-61 E L- 1 3979 -61 E L- 1 4055-6 1 E RL-9466-61 E L- 1 3898-61 E L- 1 398 1- 6 1£ L- 1 4056-6 1 E RL- 9618-6 1 E L-1 3 900
- 61 E L-1 3 983
- 6 1 E L -14057-61 E RL -9663
- 61 E L-1 3 902-61 E L-1 3 98 4
- 61 E L -14062-61 E RL-1 0098
- 61 E L
- 1 3907-6 1 E L-1 3 99 3
- 61 E L-1 4 06 3 -61 E R L-1 019 4- 61 E L- 1 3 913
- 6 I E L-13996-61 E L- 1 4066-61 E RL-10249-61 E L- 1 39 15
- 6 1 E L-1399 7-61£ L-14067-6 1 E R L- 1 06 1 5-6 1 E L- 1 3930-6 1E L-13998 -61 E L-14069-61 E RL- 1 I0 I I -61 E L-1393 1- 61£ L-1 3 999-61 E L-1407 1 -61 E RL- 1 2 1 2 1-61 E L-13934-61 E L-14000-61 E L-14076
- 6 1 E RL- 1 2 163-6 1 E L

-1 3 936-61 E L-1400 1
- 61 E L -14077-61 E RL-1 2343- 61 E L

-1 3 9 3 8-61 E L-14003-61 E RL -1726
- 61 E RL-1 335 2-61 E L-1 3 939-61 E L- 1 4004-61 E RL-1 8 1 0-61 E RL-1 3 60 1-61 E L-1 3 946-61 E L- 1 4005-6 1 E RL
- 1 862
- 61 E Required Action Ex h a u s t System Di sasse mbl y and Removal 

### & cA UT I O N BE F ORE DIS ASS EMBLY O F THE EXH A UST S Y STE M , IF THE E NG I N E HA D BE E N OPERATING, LET T HE ENGINE AN D T HE E X H AU S T SYST EM C OOL F OR I HO UR OR LO N GER AFTER ENG I N E S H UTDOWN TO PR EVENT BURNS. NOT E T hi s procedur e appl i e s o nl y to ex hau st sys t em co mp o ne n ts (Figure 3) lh al are in sta ll e d on the Lycoming TJ0- 540-A J IA eng in e at the fact or y and not a irfram e- in s talled ex h aust sys te m co mponents. As a p o int o f refe r ence, Figure 4 identifie s s ome of th e fac t or

y -in s talled ex haust c omponents on th e e ng in e and airfram e -in s talled exhaust comp o n e nts around the turb o charger.

ISS U ED R EV ISED PAGE NO. R E V ISION MO 

## I DAY 

## I Y EAR MO 

## I DAY 

## I YEAR 2 of I 2 A S. B. 6I4 07 

## I 24 

## I 14 I O 

## I IO 

## I 14NOTE Th is procedure can be done on an engine installed in an airframe.

I'

Examine T h i s Sadd l e R e i nforced Weld Jomt 

## I T urbocharge r /.::: 

### , ,.... .........**Jt., ~~-** 

# ~i~f**( ~** 

# ~~**'-"'"** M oooOog "'"""

## '-..J**· T**  .. k urbo 011 Dra u1 T an Ex l laust P i pes

Figure 1 In stalled Exhaust System ( # I , #3, # 5 Cyl inder- R i ght Side of Eng ine)
Exhau st Pi p es

Exa mi ne T hi s S add l e R ei nforce d W el d J oi nl Figure 2 

# . . ,

Ins ta lled Exhaust Syste m (#2 , #4 , #6 Cylinder- Left Side of Eng ine) ISSUED REVISED PAGE NO. REVlSIO N MO 

## I DAY 

## I YEAR MO 

## I DAY 

## I YEAR 3 of 12 A 07 

## I 24 

## I 14 1 0 

## I 10 

## I 14 S . B. 614Left Exhaust Ptpe for Cyhnder 2 Adapt e r for Exhaust Pipe Cylinder 4

Lef

t Exhaus t P ipe f o r Cy l ind er 6

MO 0

7 Exhau s t Trans i t i on Assembly

I SSUE D 

## I D AY 

## I Y EA R 

## I 2 4 

## I I4 M O I O E x hau s t Flange Gask e t

Exhaus t P t pe for Cylinder 2

Exhaus t Pipe fo r Cylinder 5

Exhaus t Bypass Valve

Tu t bocharger Fi g ure 3 N ut

Adapter ( for bhaust Pipe forCyltnderl)

Exhaust Pipe f or Cy linder I 

### Exam i ne Thi s S a

ddl e R

e inforced We l d Joint Exhaust Ptpe f or Cylinde r 3

Ex h au s t Pipe f or lnt e r cyli nd e r 5

T I0 -54 0 -A J IA T u r bo c ha r ge d Ex h a u st Sys te m R EV IS E D P AGE NO
. R E V I S I O N 

## I DAY 

## I Y EA R 4 o f I 2 S .B. 6I 4 A 

## I I O 

## I I 4I. Identify affected engines in Tab l e I that are either installed in your aircraft or i n your inventory. 2 . Before disassembly e ither draw a sketch or take a photograph of the exhaust system instal l ed on the e ngine and attached to the airframe for referenc e on reassembly. 3. Make a copy of the : Exha ust Syste1n I nspection /Asse 1 nb l y Checklist included in this Service Bulletin for eac h affected engine to be examined as a record of inspection and r ep lac e ment of the tu rbocharger mount i ng brack et i n compliance w ith th is Service Bul l et i n . 4. To access, the exhaust system, remove any a irframe components as necessary per the airframe manufacturer's instructions.

- , •• - ... 1

Figure 4 Installed Exhaust System 5 . Rem ove the bolt and self-locking nut from the exhaust system end of the cab l e assembly (Figure 5). Discard th e self
locking nut. Alrlntakc /

# ~ 

# I 

# / . /

T urbocharger I

Bol l Figure 5 Exhaus t System End of the Cable Assembly 6. Remove the V-band coupling f rom the following two slip joint connecti ons (F i gure 3) on the exhaust system: • Exhaust pipe for intercylinder number 5 and exhaust transition assembly connection • Exhaust transit ion assembly and exhaust bypass valve connection 7. Remove and discard the gasket (F i gure 3) fr om each of the two removed V-band coup l ings . 

# & CAUT I ON DO NOT USE ETCH TOOLS , GRAPH I TE LEAD P E NCIL , OR SCRIBE TO APPLY AN IDENTIFIER MARK O N EXHAUST PIP ES . USE E ITHER A NO N-GRAPHITE MARKER SUCH AS COLORBRI TE NO . 2127 OR 4127 OR A MARKS-A-LOT . 8. For reference , prior to exhaust system disassembly , us e either a non-graph ite mark e r such as Colorbrite No . 2127 or 4127 or a Marks-A-Lot marker to identify the exhaust system pipes on each s id e of the engine (Figure 3). ISSUED REVISED PAGE NO. REVISIO N MO 

## I DAY 

## I YEAR MO 

## I DAY 

## I YEAR S.B. 614 5 of 12 A 07 

## I 24 

## I 14 10 

## I 10 

## I 14

# & CAUT I ON AS A S AF E TY PRE C A UT ION , USE THR EE P E OP LE TO C OMPL E T E TH E NEXT S T E PS T O PR EVE NT INJ U RY AN D PA RT S FROM FA LLING . 9. Whil e o n e pe r so n re mov e s the se lf -l oc ki n g nut s and was h e r s ( Fi g ure 3) fr o m the vert ical p o rti o n of th

e three ex h a us t pip es o n th e 2
-4
- 6 (eve n numb e r ed ) cy l ind e r s id e of the e n g ine ( Figur e 2) . t wo peo pl e lowe r a n d re move t h e ex ha us t pip es and put th e m o n a c l e an wo rk s urf ac e . Di s card th e se l f
lock in g nut s an d g as ket f ro m e ach exha u st p i p e fl an ge a t th e cy lind e r h ead . I 0. R e pea t th e prev i o u s s t e p f o r the th r ee ex hau s t pip es o n th e 1- 3
- 5 (od d-numb e r ed ) c y lind e r s ide o f th e e n g in e (fig ure I). I I. Di sco nn ec t th e hose a nd air inlet tube fr o m the turb oc harge r ( fi g ure 6 ) .

ISSUE D R EV ISED MO 

## I DAY 

## I Y EAR MO j DAY j 07 

## l 24 

## l 1 4 10 

## I 1 0 

## I YEAR 1 4 Fi g ure 6 Turb oc ha rge r
PA G E NO . 6 o f 1 2 

# ---- .. 

# ----

R

EVI S ION ;\ S.B . 6 1 4N ut Lock Washer Washe r

Turbo O il D rain Tank - Turbocharger Mo u nting B racke t

Screw F igure 7 . tl

T urbo Oil D rain T ank S u pport B racket

# ~ViewA Lock Washe r Washer Turbo Oil Drain Tank and Support Bracket 12. D isconnect and put a cap on the two hoses connected to fittings on the tu rb o o i l drain t ank (Figure 7) and the hose connected to fitting on the turbocharger (Figure 7
- View A). 1 3. Remove the vertical bolt, washe r , an d self- lock i ng nut from the lug on the exhaust transition assemb l y (Fig u re 6) . NOTE In the n ext step, keep the 90° bracket (Figu re 7) and clamps attached to the hoses. 1 4. Remove t he screw , was h er, lo ck washe r , and nut from the po rti on of the 90° bracket t h at attaches to the turbo oil dra i n tank support bracket and turbocharger mounting bracket (F igu re 7) . Discard the lock washe r. 15. Remove the horizontal bolt , two was hers , lock washe r, and nut from t he l ug on the t ransit ion assembly and r ear turbo support bracket (F i g ure 6) . Discard the l ock washe r . Remove and keep t h e lug. 16. Support the turbocharger assemb l y and remove t h e self -l ocking nuts and washers from the studs and tu rboc h arger mount in g bracket on the o il sump (Figu re 6) . Discard t he se lf-l ock i ng nuts. 17. Carefully remove , as a unit, the turbocharger from the eng in e stil l attac h ed to t he exhaust trans it ion assemb l y , turbocha r ger mount in g bracket , tu rb ocha rge r oi l drain tank, and its suppo rt bracket. Pu t the assembly on a clean work surface . 1 8. Bend down the tabs of the lock plate (F i gu re 6) . 19. Remove the two bo lts , spacer, a nd lockp la te th at attach the turbocharger mounting bracket to the turbocha r ge r (F i gu r e 6). Di scard the lockplate. Keep the spacer for reassembly. 20. Remove the se l f-locki ng nut a nd was her from the stud that attaches the tu rbocharger mounting bracket to the exhaust transition assembly (F i gu re 6) . Discard the self- lock i ng nut. ISSUED REVISED PAG E NO. REVISIO N M O 

## I DAY 

## I YE AR MO 

## I DAY 

## I YEAR S.B . 614 

## I I I 

# I 7 of 12 A 07 24 14 10 10 1421. Remove the turbocharger mounting bracket and send th i s bracket to Lycoming Engines to receiv e a replacement bracket as per warranty terms in this Service Bulletin. Refer to the rep lacement parts list iry the " Warranty Instructions " s e ction ofthis Service Bu lletin. 22. Remove the three bolts , three self-locking nuts and three washers that attach the exhaust transition assembly to the turbocha rger (Fi g ure 6). D i scard the self-locking nuts. Exha u st System I n spection 

# & CA U TION CRACKED E XHAUST P IPES IN ANY EXHAUST SYSTEM COMPONE N T , ESPEC I ALLY WELD E D JOINTS, CAN CAUSE TOXIC GASES , SUCH AS CARBON MONOXIDE , TO ENTER THE COCKPIT. NOTE Send any part that is cracked or damaged to Lycoming Engines for replacement under warranty terms ident ified in th i s Service Bul l etin . I. Use a I Ox power magnifying glass to examine the weld joints of the exhaust pipe for cylinder # 3 (Figure 3). Closely examine the sadd l e reinforced we l d jo i nt (F igures 8 and 9). I f any cracks or damage are found , replace t he exhaus t pipe.

Figure 8

Sadd l e Inspect with 1OX power magnifying glass . 

### 1 Figu r e 9 Saddle 2. Examine the # 2 cy l inder exhaust flange for damage or distortion . The flange must be straight and have no s i gns of exhaust l eaking past t he gasket. If the flange or pipe is distorted or damage , rep lace t he p ipe. 3. Exam i ne the # 2 cy linder exhaust port for signs of an exhaust leak or pulled exhaus t studs. If evidence of leakage , damage , or pulled studs are found , replace the cylinder. 4. Compl e te a visual inspection on the ent ire exhaust system (Figures I , 2 , and 3) for any signs of leaks , distortion , or damage. Examine clos e ly at all weld joint s . Replace any damaged component. 5 . Clean the exhaust pipes and flanges w ith approved solvents . Remove carbon or exhaust residue from s lip joint mating surfaces with a red Scotch- Brite T M pad or equiva l ent ab rasive pad . Remove any debr is. Visually examine the cleaned exhaust pipes.

ISSUED REVISED PAGE NO. RE VIS ION MO 

## I DAY 

## I YEAR M O 

## I DAY 

## I YEAR S . B. 614 

## I I 

# I I 8 o f 12 A 07 2 4 14 10 10 14Ex h a u s t System Asse mbly and In s ta ll ation I. Apply a unif orm coa ting of Loctit e ® C5-/\00 an ti-seize compound or eq ui va lent to the s l ip joint mating surfaces (F i gu r e 3) of the exhaust pipes. 2. Assemb le the exha us t pipes at the s lip j oi n ts and make s ure th ere is n o binding of th e joined part s. If a n y bindin g o r ti g htness is found , r ep l a ce the exhaust p ip es . 3. Apply a uniform coat o f Loct ite® C5-A ® an ti -se i ze co mp o und or equ ivalen t t o th e stud (Figure 6) on the exhau st tra n s it ion assemb ly . NOTE Whe n installing ex hau s t system components do not fully tighten any fasteners until all co m ponents of th e ex hau st sys t em are prope rly a li gned and the fasteners can be torqued eve nl y. Components mu s t be able to be manipulated to a lign them. 4 . Attach the ex h aust tran sit i o n assemb l y to the turbocharger (Figure 6) wi th the two bolt s, three washers , and three n ew se lf -locking nut s hand-tight. 5. I nsta ll the lu g on th e ex h a u st transit i o n assemb ly wi th th e ve rti ca l bo lt , was he r , and new self-locking nut (F i gu r e 6) h and-t ig ht. 6. App l y a unif orm coat of Loctite ® C5-A ® anti-se i ze compound or equivalent to the threads of th e tw o bolts that attach the new turbocharg er mounting bracke t , lockpl ate, and s pa ce r t o the turbocha rger. 7. In stall the new turbocharger mountin g bracket P IN 07 A22265 on th e tu rbocharge r ( Fi gure 6) and th e stud on the exhaust trans it ion assembly with the two bolts , space r , and new l ockplate. T orque th e t wo bolts to 160 to 190 in.- lb . ( 18 to 21 Nm). Bend th e tabs ( Fi gu re 6) of the lockplate into pl ace. 8. Install the turbocharger mo untin g bracke t with th e turb oc harg e r a nd ex hau s t tran s it i on assemb l y o n the s tuds o n the o iI s ump (F i g ure 6) w ith the was h e r s and n ew se lf-lock in g nu ts hand-ti g ht. 9. I nstall the washer a nd new se lf
- locking nut o n the stud on the exhaust trans iti on asse mb ly h and-tight. I 0. I nstall the horizontal bolt through the lug on th e exha ust transition assembly with a washer, and n ew se lf -l ocking nut ( Fi g ure 6) hand
- tight. II. I ns t a ll the screw , washer , a nd new se l f-l ock i ng nu t that attac h es th e turbocharge r oil drain tank suppo rt bracket , and 90° bracket w ith the c l amps attac h ed , to th e turb oc harger mounting br acke t ( Fig ure 7). Torque the c l a mp s to 49 in .-lb. (5.5 Nm). 1 2. Apply a uniform coa t of L oc tite ® C5-A ® a nli -se i ze compound or equiva l e nt to th e fi r st thre e threads of eac h exhaust s tud in a ll six cyl in der hea d s. 

# & CAUT IO N USE CARE TO SUPPO RT T H E ENT I RE EXHAUS T SYS TEM DURI NG INSTALLATION. DO NOT F OR CE. PR Y , OR B EN D COMPONENTS DURING FINAL A LI GNMEN T TO PR EVEN T D AMAGE TO THE PARTS. 13. Assemb l e the exhaust sys tem o n th e engine as app li cab l e . NO T E R

e fer to the l atest r ev i s i o n of Lyco min g Se rvice I nstruct ion N o. S l-1562 f o r ex hau st sys t e m in stal lati o n gu id e lin es. 14. Refer to the pre-di sasse mbly photo o r sketc h. Attach each exhaus t pipe t o the co rresponding cy l inder head each with a new flange gasket. new washers , and new self
- locking nuts. Do not ful ly torque the self
- loc ki ng nut s . ISSUED REVISED PA GE NO . R EV ISION MO 

## I DAY 

## I YEAR MO 

## I DAY 

## I YEA R S.B. 614 

## I I I I 9 of 12 A 07 24 1 4 10 10 1415. Make s ur e the re are no gaps at pipe connection s and all p ip es ar e correctly a lig ned before the final torque of th e f aste ners . NOT E The V-band co upl in g at th e ex haust transition mu s t be correct ly a li g ned . In co rrect alignment of the V-band co upling at the exhaust transiti o n i s an indication that the exha u s t syste m is not co rrect l y in s tall e d . If the V -b and coupl in g does not a lign, adjust the ex hau st sys tem co mp o n e nt s unt i l the V
- band coup ling i s in co rrect a li g nm en t. A s li g ht adj u s tment to the turb oc harger o rienta ti o n a l so can be made t o correct the V-band co uplin g al i g nment. I 6. After va lidat i o n of the al i gnment and configuration of the ex ha u s t p ip es, s lide the V-band coupling w ith a n ew gasket ove r th e ex h aust pipe for intercyl ind e r number 5 a nd ex ha us t tra ns ition assembl y con nection. Pre ss the V-b and coupling on th e flang es . 17. Co mple t e fina l torques to e nsure all fastener s are t o rqu ed : A. T o rque th e V-band coup I ing at the exhaust pipe for inte r cy lind e r number 5 and exhaust tran s iti o n a sse mbly co nn ect ion to 85 in.-lb. (I 0 Nm). R efe r to th e l ate s t revision of Lycoming Service In s truction N o . S l -1 23 8 f o r Assembly and T o rqu e Proce dures for V-Bancl Couplings . B. Torque th e nut s that attac h the ne'v v turbochar ge r mo untin g bracke t (F igu re 6) to the oi l s ump to 30 ft .-lb s . (4 0.7 Nm). C. Torque th e se lf
- lock ing nut s that attach th e ex ha u st tran s it ion assemb ly (Figure 6 ) to the turb oc harger to 30 ft.- lb s . (4 0.7 Nm). D. Torque th e nut that attach es the ex h aust tra n s iti o n assembly t o th e turb oc harger mounting brac k et ( Fi g ure 6) to 3 0 ft.-lb s . (40 .7 N m ) . E . Torque the nut s that attach the exhaust pipes to the cy lind e r s (F i gure 3) to 96 in.-lb. ( II N m)
- o n a ll cy lind e r s. 1 8. R emove th e caps fr o m the three h oses . Con n ect o n e hose to th e turbocha r ge r ( Figure 7
- V i ew A) and th e o th e r two hoses to th e turbo oil drain tank (F ig ure 7). 1 9 . Lubric a t e th e in s i de of the hose for the air intake tube w ith e n g in e oi l mixture ( 15% pre-lubricant (S TP o r e quiva l ent) and 85% SA E 50 mineral-ba se av i at i on-grade lubricating o i l ) a nd connect the air int ake tub e to th e turbocharger (Figure 6) . Torque the clam ps t o 35 in . -lb. (4 Nm ). 20. I n s ta ll the V-bancl co up l ing and new ga sket at th e ex h a us t bypass va lve and exhaust tr ansit i on asse mbly co nn ect io n. Torque the V -ba nd coup ling to 85 in.- lb. (9 . 6 Nm). 2 1 . I n s tall th e ex h a u s t sys tem end of th e cable asse mb ly ( Fi g ure 5) wit h a bolt and n ew sel f- l ocking nut. Torque the nut to 96 in.-lb. (I 0.9 Nm). 22. R e fer to the a ir frame manufacturer 's maintenance m anua l and re in sta ll a ll airframe compone nts prev io u s ly r e m ove d to ga in access to the Lycom ing ex hau s t sys t e m. 23. R eco rd re pl acement of turb och arger mo untin g bracket, any co rrec ti ve act io n , and comp lian ce w ith thi s Service Bulletin in th e e n g in e logbook.

ISSUED REV ISED PAGE NO. REV IS I ON MO 

## I DAY 

## I YEA R MO 

## I DAY 

## I YEAR 10 of 12 S .B. 6 1 4 07 

## I 24 

## I 14 10 

## I 10 

## I 14 1\Wa r ra n ty I nstruct i o n s and Re pl aceme n t Parts for Eng in es/P a r ts Af f ected bv Se r v ic e B ull et in No. 614 l. Contact an Autho r ized Lycoming Distributor to order the rep lacement pa r ts listed below. Parts Necessary f or Re qui• ·ed Act i on Part Name Lycom in g Pa rt N u m b er Qty. BRACKET . Turbo mounting 07A22265 I NUT , 3/8-24 self- l ocking MS20500-624 8 LOCKPLATE LW-12291 I GASK E T , Exhaust flange LW-18234 12 GASKET , V-band coupling , 2- 1 /4 tube 78246 I WASHER , 1 /4 plain AN960C416 24 NUT , I/4
- 20 se lf
- lock i ng STD-2044 25 GASKET , V-band coupling, 2-1 /4 tube 75845 1 WASHER, No. I 0 i nternal l ock STD-251 I Add itio n a l Par t s T h at Cou l d be Necessary Based o n Res ul ts of Inspect i o n Cyl i nder Kit 05K22680 I ADAPTER , Exhaust p ipe, cyl. no. I 40G22384 I P IPE , Exhaust, inter. cyl. no. 5 40822267 I FLANGE , Exhaust manifold 40C2238 1 I ADAP T ER , Exhaust p ipe , cy l. no.4 40G22384 I PIPE , Exhaust , cyl. no . I 40822190 I PI P E , Exhaust , cyl. no . 2 40822318 I P IPE , Exhaust. cyl. no. 3 40822621 I PfPE , Exhaust, left , cy l. no. 4 40822379 I PTPE , Exhaust, cy l. no. 5 40822193 1 PTPE , Exhaust , left , cy l. no. 6 40822380 1 PI P E , Ex h aust , cy l. no. I with EGT probe ho l e* 40823387 I PIPE , Exhaust , cy l. no. 2 with EGT probe ho l e* 40823386 I PIPE , Exhaust. cy l. no. 3 with EGT probe ho l e* 40823388 l PI P E , Exhaust , cyl. no. 4 with EGT probe hole* 40823385 l PlPE , Exhaust , cy l. no . 5 wit h EGT probe ho l e* 40823389 I PIP E, E xhaust , cyl. no. 6 with EGTprobe hole* 40823384 I 

### * For use wit h Cessna OEM G 1000 EGT Indication Syste ms o nl y . 2. Upon rece i pt , complete the i nsta l lation procedu r e . 3 . Return t he r e moved turbocharger mount i ng bracket P / N 07A22265 and any cracked or damaged exhaust system components to Lycoming Eng i nes through the same Autho ri zed Lycoming D i str ibutor that orde r ed the r ep lacement turbo mo unt i ng bracket P / N 07A22265 and fi le a warranty cla i m for: A. Re i mbursement of the replacemen t parts. B. Assoc iated Fre i ght. C. Removal and Re i nstal lat ion Labo r Allowance of not mo r e than 8 ho u rs. If you have any quest ions , contact Lycoming F i eld Service by phone at 570-327
- 7222 or 877-839-7878 . NOTE Warranty considerat ion is available fo r 12 months from the date of i ssue of this Service Bulletin. ISSUED R E VIS ED PAGE NO. REVISION MO 

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# I 14Ex h a u s t S ys t e m I n specti o n / As s emb ly C h ecld ist E n g i n e Seri a l N umber: Dat e of Ins p ect i o n Ho urs of e n g ine serv i ce: I nspectio n do n e by: Task F i nd in gs/Corr ective Act i on Use a I Ox powe r m ag nif yi ng g lass to exa m i n e t h e we l d joi nt s o f t h e ex h a u st p ipe fo r cy li nd e r # 3 . G i ve specia l a tte n t i o n to t h e sadd l e r ein fo r ce d wel d jo in t (F i g ur es 8 a n d 9) . Exa m i ne t h e st ud s th at attac h t he ex h a u s t p ipe o n t h e # 2 cyl ind e r fo r a n y i nd i ca ti o n t ha t t h ey h ave pull e d away fro m t h e c yl ind e r hea d . E x a min e th e ex ha u s t tra n s iti o n a s se mbl y (F i g ure 3) , its fl a n ge , a nd s lip jo i nt s f o r cracks , b ul ges , d e nts , or res i du e. Co mp l ete a v i s u a l i n s p e c t i o n o n th e e ntir e ex ha u st syste m for a n y s i g n s o f leaks , di sto r t i

o n , or dam age . Exa min e c l osely at al l we l d j o i nts . Clea n t he ex ha u s t syste m w ith a pp rove d so lve nt s. R e m ove c a rb o n or ex hau st r es i d ue off of s l i.R joi nt ma tin g s urfa c es wit h a re d Scotc h
Bri te "' p a d o r e qui va l e nt a bras i ve pa d. A ppl y a un ifo r m coa t i ng o f L oc t ite® C5
- A ® a nt i-seize o r eq ui val e nt to th e s lip jo in t m a tin g s ur faces , asse mble t he exha u st p ip es at th e sl ip j o int s a nd tes t f o r fr ee d o m of m ove m e nt. R e p lace t he t u rboc h a rge r m o un t in g brac ket. Ret urn the re m ove d t u rboc h a r ge r m o un ti n g b rac k e t a nd a n y crac ked o r da m aged ex h a u s t syste m co m pone n ts to Lyco m i n g E n g in es .

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