Rajay Turbo Service Letters

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Transcription

Rajay Turbo Service Letters
7101 FAIR AVENUE
.
NORTH HOLLYWOOD,
RAJAY/ROTO-MASTER
SERVICE
Rajay
Industries
is
Rajay
turbochargers,
pumps
are
no longer
91605
-
AIRCRAFT
LETTERS
in
business.
controllers,
available
CALIFORNIA
actuators
and scavenge
from:
Roto-Master
7101 Fair Avenue
North Hollywood,
91605
CA.
(818) 982-4500
Rajay
kit
available
parts,
service
and technical
information
through:
Century
Aircraft
Corporation
Drive
10001 American
Amarillo,
(806)
Sky Ox parts,
Texas
79111
335-2806
service
and technical
information
from:
Sky-Ox Ltd.
P-0. Box 500
Saint
Josephs,
(616)
(800)
is
Michigan
49085
925-8931
253-0800
TELEX
NO
657390
(ROTOMASTER
AN ECHLIII
LSA) . CABLE:
COMPANY
ROTOTURBO
is available
(818)
982-4500
RAJAY CORPORATION
Service
Date :
November
Models
Affected:
7,
1963
"Turbo
Subject:
Inspection
Time
At next
of Compliance:
Instruction
Service
200** Apache
of Catb
routine
Letter
(PA 23TS & PA23TSl60)
Box Check
Valve
Hinge
Tabs
inepection
It has been noted that the hinge tabs tn the Carb Box Assembly,
P/N RJ 0028-100,
have shown excessive
wear in service.
The material
for
the tabs has been changed from aluminum
to steel
in the production
parts.
Parts
in service
should be visually
inspected
at the next routine
inrpection
and subsequently
at LOO hour intervals
until
replaced.
Tabs
worn in excess of l/l6
inch require
the Carb Box Assembly be replaced.
Thir assembly
is avallabla
from the factory
for an exchange price
of
$12.50 per assambly.
The carb Box Asaambly may be replaced
by any aircraft
machanic.
Any questions
regarding
this subject
should be directed
Corporation,
2602 East Wardlov Road.,
Long Beach, Californfa
FAA APPROVED
to the
90807.
Rajay
No.
1
.9AJAY CORPORATION
Service
Instruction
SEWICE LET'TEFiNO. 2
date:
October 26,
Models Affected:
All &jay Turbocharged
31% 10 Turbochargers.
Subject:
Inspection
Time of Compliance:
Within next 25 hours service
operation interval
thereafter
1964
aircraft
of Turbocharger
,equipped with model
turbine
scroll.
and at each 100 hours
until replaced.
It has been noted that radial cracks have appeared on some turbine scr0l.l.~
of the Rajay model 31910 Turbochargers
as shown in the figure
below. No case
of complete failure
has been observed nor reported.
The affected F&jay model 31910 Turbochargers
are to be inspected within the
next 25 hours service and at each 100 hour operation interval
thereaf’ter
etil
replaced.
This inspection will consist of careful visual scrutiny of the exterior
If
of the turbine scroll,
particularily
in.the area marked on the figure below.
cracks
are observed,
install. a placard in full view of the pilot to mad
"TURBOCHARGER
INOPERATIVE". Upon replacement of the cracked turbine. scroll,
the
placard may be removed. Modification
to correct this problem Is in uork.
,st gas
Possible cracks in
this area
It is requested Ra$ty Corporation,
2602 E. Wardlou Road, Long Beach,
California
90807, be notified
of airplane type, serial number, registration
number, owner, Turbocharger serial numbers, date and approximate hours in
service with turbochargers
at the time of initial
inspection.
FAA APPROVED
October 28. 1964
Service
January 6, 1965
Xodels Affected:
"Turbo Commander 5009"
Zubject:
Inspection
Time Compliance:
At next routine
LZtt3r
110.
of Air Box Assembly Check Valve Hinge Tabs
inspection
It has been noted that the hinge tabs in the Air Pox Assembly, &jay
P/N 35 2016-l & -2, have shown excessive wear under some conditions
of
service.
Parts in service should be visually
inspected at the next routine
inspection and subsequently at 100 hour flight
oueration
intervals
until
replaced.
Tabs worn in excess of l/16 inch require the Air Box Assembly
be replaced.
Xodified Air aOx Assemblies are available
from the factoyJ
for an exchange price of $20.00 ner assembly. The Air Box Assembly
may be replaced by any aircraft
mechanic.
Any questions regarding
Cornoration,
2602 3. Xardlow
.7.AAAgraved
January 6, 1965
this subject should be directed to .3ajay
.Xd., Long &each, California
90807.
3
UJAY CORPORATION
Service
Date:
April
Instruction
16, 1965
Service
Models Affected:
Riley Turbo Rocket
Subject:
Inspection
Time Compl.iance:
At next routine
of Compressor Discharge
Letter
Box Check
No. 4
Valve
Hinge Tabs
inspection
It has been noted that the hinge tabs in the Compressor Discharge @x
P/N RJ 1006.31/-41,
have shown excessive uear in service.
The
for the tabs has been changed
f'rom aluminum to steel in production
parts.
Assembly,
materhl
Parts in service should be visually
inspected at the next routine
inspection and subsequently at 100 hour intervals
until replaced.
Tabs
worn in excess of I /16 Inch require the Compressor Discharge ': Assembly be
replaced.
This assembly
is available
from the Rajay Factory for an exchange
price of $12.50 per assembly..
The Compressor
Discharge Assembly may be
replaced by auy Aircraft
Mechanic.
Any questions
regarding this subject should be directed to The Rajay
Corporation,
2602 East Wardlow Road, Long Beach. California
90807
RAJAY CORPORATION
Service
Lnstruction
July
1, 1965
Models
Affected:
Subject:
Time
of Compliance:
Turbo
Comanche
Ground
operation
Upon receipt
250 (PA 24-250)
of fuel
of this
and Turbo
boost
pumps
service
letter
Aztec
(PA 23-250)
Lnvestigation
Into
the cause of reported
engine
driven
fuel pump malfunctions
In the above aircraft
models indicates
the possibility
of the pumps
running
dry.
This condition
could exist
with excessive
vapor in the fuel
system due to prolonged
ground operation
or extreme
hot weather operation.
To eliminate
the possibility
of running
the engine
driven
fuel pumps
fuel boost pumps are to be "ON" for all ground operations.
dty, the electric
A placard
to this effect
is In the process of manufacture
and will
be furnished when available.
Any questions
regarding
this subject
should
Corporation,
2602 East Wardlow Road, Long Beach,
FAA Approved
July 1. 1965
be directed
California
to Rajay
90807.
RAJAY CORPORATION
Service
Instruction
July
14,
Subject:
Models
Time
Senrlce
1965
Inspection
Turbocharged
Affected:
of Compliance:
All
Rajay
Following
Recommendations
Following
Lycoming
Engines
Turbocharged
Lycoming
Overboost
Letter
No.
6
of Rajay
Engines
Overboost
T’he attentlon
of all operators
of Rajay Turbocharged
Lycoming
engines
is
directed
to Lycomlng
Servlce
Instruction
No. 1023i3 dated January
15, 1965.
It
is suggested
that the recmendationo
set forth
in the above Service
Instruction
be applied
to Lycoming
engines
equipped
with Rajay Turbochargers.
Adherence
to
these recommendations
will
contribute
to continued
satisfactory
operation
of the
Rajay Turbocharger/Lycoming
engine combination.
Any questions
regarding
poration,
2602 East Mardlow
FAA Approved
July 14, 1965
this
Road,
subject
ehouid
be directed
to the
Long Beach, California
90807.
*
Rajay
Cor-
RAJAY CORPORATION
Service
Instruction
July
21,
Model
Service
1965
Affected:
Rajay
Subject:
Time
of Compliance
Engine
:
Upon
Turbocharged
Mount
receipt
Piper
PA30 Mn
Letter
No.
7
Comanche
Protection
of imterial
It
ha8 been noted
that some deterioration
of the engine emunt surface
paint
has occurrad
on the lower RH engfne mount8 of the l’brbocherged
Twin Comanche.
This can be attributed
to the increased
temperature
in the
due CO relocated
zxh6U8t
Stacks.
pro-
tection
Bred
Aircraft
in. service
should be inspected
upon receipt
of this service
Letter
notify
Rajay Corporation
for material
if deterioration
of paint
is in evidence,
to correct
this defiefoncy
per the instructions
and 8ketch below.
(This
treatment
is incorporated
in all
ln8tallations
subsequent
to this date)
and
Sand mount tube8 to bare metal and remove grease and
oil vith
solvent.
Make CQrt8i.n surfsce is Completely
Apply 2 brush coata of Extra High H-170 Heatdty.
Rem paint
on moderately
warm but not
hot surface.
Allow 12 hour8 drying
between coats.
Any questions
2602 &tat Wardlow
regarding
this subject
should be directed
Long Beach, California
90807.
Road,
to Rajay
Corporation,
RAJAY CORPORATZOFI
Service
Date:
October
Nodels
Affected:
1,
Service
1965
Turbo
Twin Comanche
Subject:
Inspection
Time
At next
of Compliance:
Instruction
Piper
of Alternate
routine
Letter
No.
8
PA-30
Air
Inlet
Valve
Bracket
inspection
It has been noted that the Alternate
Air Inlet
Valve Bracket
P/N RJ 0605-71
hinge holes in parts manufactured
prior
to June 1965, have shown excessive
wear in
service.
Parts manufactured
subsequent
to June 1965 incorporate
brass reinforced
hinge pin holes and therefore
have Increased
wear resistence.
-.
Parts in service
should be vtsually
inspected
at the next routine
inspection.
Those parts incorporating
the brass reinforcement
require
no further
special
attentions.
Those parts without
the brass reinforcement
should be inspected
for a maximum wear
elongation
of the hinge pin holes of l/16 inch.
If elongation
does not exceed l/16
inch the parts should be reinspected
at intervals
of 100 hours of service
until
replaced with the reinforced
bracket.
The Alternate
Air Inlet
Valve/Bracket
Assy
RJ 0605-S/-71
is available
from the factory
for $5.00 each.
The Valve/Bracket
Assy
may be replaced
by any aircraft
mechanic.
Any questions
2602 East Wardlow
FAA Approved
regarding
this subject
should be directed
Road, Long Beach, California
90807.
to Rajay
Corooration,
RAJAY CORPORA'ITON
Service
Date:
December
Models
Affected:
14,
Time
Service
Alternate
of Compliance:
Lc has been
(operation
from
tributed
to the
possibility
the
air source.
All
corporate
filtered
-.,
;
1965
Turbo
Subject:
Instruction
Operator's
Twin Comanche
source
for
Piper
PA-30
fuel
nozzle
bleed
Letter
No.
air.
option
noted that during
sustained
operation
under heavy dust conditions
unimproved
airfields)
some fuel nozzle
contamination
can be atpresent
source of fuel nozzle
bleed air.
To eliminate
this problem
factory
is offering
a kit for field
retrofit
to provide
filtered,
production
kits
manufactured
subsequent
to December 12, 1965 inair source for fuel nozzle bleed air.
Operators
interested
in the above
by contacting
the Rajay factory
direct
Long Beach, California
9080.7.
retrofit
kit may obtain
- The Rajay Corporation,
parts
and instructions
2602 E. Wardlow Road,
9
RAJAY CORPORATION
Service
Instruction
May 23,
Subject:
Models
Time
Relocation
Affected:
of
It
charger
desirable
Service
1967
Compliance:
Piper
of T/C Oil
PA30 Turbo
At next routine
hours operation.
has come to the attention
oil warning light
power
location.
of
wire
Warning
Letter
Light
No.
10
Power Wire.
Twin Comanche
inspection
or within
the manufacturer
is not fnstalled
’
next
100
the turboin the most
.
The turbocharger
oil warning
light
wire is presently
connected
to the Stall
Warning Circuit
Breaker.
This wire and the corresponding
placard
is to be moved to the Flap Solenoid
Circuit
Breaker.
Enter
this action
in the Aircraft
Log on date accomplished.
Any questions
Corporation,
P. 0.
FAA APPROVED
regarding
Box 207,
this subject
should
Long Beach, California
be directed
90801.
to Rajay
June
12,
Zyme
Instruction
Service
Affected:
of
CORPORATLON
1967
Subject:
Models
IUJAY
Service
Compliance
Inspection
of
Turbo Mn
IO-3200ClA
Coaanche
: At
next
Turbo
oil
8uppLy
- Piper
Letter
No.
11
hose:
PA30 fitted
.vlth
Lycaming
engines.
routine
inqmctlon.
It ham been noted that deterioration
of the Turbo oil
SUQQ~~
ho60
(P/Y 624000-4-0224)
has taken place in 8amc installations.
This hoae
irmtallatlon
should be inspected
to insure
it I6 properly
fnat&lled
and
remaining
free and clear
of the turbine
scroL1 as shown in the rkstch
belw:
--..,
624000-4-0224
HOSi3 ASSY
Quartions
CORPORATION,
regarding
this subject
rbould
be directed
to RA.tAY
P. 0. Box 207, Long Beach, Catifornia
90801,
-___
_-_--
.-.-.
.-...
-_
.-
.
-
-.
----y-
,
L
_-
-
7
-.--
“7
-
--TyT->zf-
QUA..’
.I
‘.
I
‘,
.
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.
,
-
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.,.
RAJAY CORPORATION
Sewice
April
22,
Modal
Affected:
Instruction
Service
1968
Letter
Subject:
Rajay Turbocharged
Piper PA30 Twin Comanche
(Prior
to mfg. S/N30-1718
Engine Nouct Protection
Time of Compliance:
Within
It
the nex:
25 flight
No. 13
houra
noted
that some deterioration
of the engine mount
surface
hae occurred
on the lower IM engine
mounts
of the Turbo
Twin Comanche.
This condition
can be attributed
to an inadequate
amount of
heat and corrosion
reoidtant
paint (silver
in color)
applied
at time of
lnetallation
of the turbocharger
system prior
to :.lfs S/N 30-1718.
protection
has been
paint
Aircraft
in service
should be lnrpected
upon receipt
of thir
instrucand if deterioration
of the subject
part is in evidence,
notify
Rajay Corporation
for material
to correct
this deficiency
per the inrtructlona and sketch below.
tion
F/RE WA LL
ti
Any
P.O.
questiona
Send mount tubes to bare metal in shaded area
shown and remove grease and oil with solvent.
Make certain
surface
is completely
dry.
APPlY
2 brush coats or 3 spray coats of Extra High
H-170 Heat- Rem paint
on moderately
wans bvt not
hot surface.
Allow 12 hours drying
between coats.
regarding
30x 207, Long Beach,
this subject
should
California
90801.
be directed
to Rajay
FAA APPROVZD
Corporation,
RAJAY
Service
CO RPO RATION
Instruction
August 5, 1968
Service
Affected;
Models
Piper Model PA-30 Turbo Twin
Subject:
~gine
Time of Compliance:
Operator's
driven
fuel
Letter
No, 14
Comanche
pump vent fitting.
option.
C&rent production Piper Model PA-30 Turbo Twin Comanche's are
being furnished with new type engine driven fuel pump vent fitting.
This fitting
la manufactured with a very small oriffce
at the fuel
pump vent port.
This orifice
restricts
the loss of fuel in event
of a fuel pump diaphragm rupture to less than four (4) gallons
per hour.
The subject fitt%ng,
RJ 0631 Tee, is available
from Rajay
Corporation,
P. 0. Box 207, Long Beach, California
90801, for
$5.00 each. This fitting
Fa a direct
replacement for the AN826-20
fitting
presently installed
in aircraft
PA30-1766 and previous.
FAAAPPRDVED
f
.- . *--.’
-.-
_.
.-. _-..-
__
.-
RAJAY
INDUSTRIES,
SERVICE
DATE:
February
23,
INC.
INSTRUCTION
1970
SERVICE
LETTER
MODELS AFFECTED:
ALL dash numbers of Rajay Turbocharger
eystm
Lube Scavenge
Pump P/N R.J 1025 and RJ 1045
S/N 800 6 previous
RI 1025
S/N 585 & previous
RJ 1045
TIME OF COMPLIANCE:
Within
next
25 operating
To prevent
the possible
dieengagment
pin from the pump homing
the
service
should be accompllshed:
retaining
hours
of the
following
internal
fix
ring
for
79-028-125-0~87
pumpr
ESNA
(Or EquIvalentI
into
Contact
California
required.
Rajap
90801,
Industries,
Inc.,
Phone 213/426-0346
NO. t5
P. 0. Box 207,
for any further
Hole
Beach,
information
Long
in
RAJU INDUSTRIES, INC.
SERVICE XRX!RUCTION
DA=:
July 7, 1970
MXELS &tFFmmD:
SEaVICE LETER NO. 16
ALLRAJApTuRBOcHQRc;EDmNEY&2oE(super21)and
IeaF (Epecutlve)
Aircraft
Tl3SClFCOMF'LIANCE:DURINGALLOPERATIONS
Ithaaconm
to om attentlontbatscam
operators of the above aircraft
have been experiencing
reduced emdce ISe from t&e& Rajay Turbocharged
MlgbSS.
We~~coPfrusdvitheomebllgins~r~facilitiesandit
appear8 thatineachaaae
of reduced m~rvitx Ufe them ie mldemca of long
[email protected]
temperatux-86,
Inv53vof
above6okpowerbe
of amtdy
the above, it is recwnded
that all turbocharged opration
atBeetPouermirtum3
setting or richer.
This Is an EGT
1~125%
0n the
rich
side
of
peak.
Questiona on the above shouldbe
or Rajay Industries,
Inc., P.O.Box
phone (213) 426-0346.
FAADERAPPRUVED
directed to your localRajayDealer
207,Lor43Beach,
Califomia90807,
RBJAX IRDUSTRIES, INC.
-Cg
Di'STlUiCTIOl?
DdIIEI
SmvI~rbETTmm.
July 7,1970
TPB OF CoMPLIANa:
-DISGZETIOR
..-
.P
APPROX.
90°
PRE- LaAD
The nauRJ4120-31 UaateGateReturnSpri,ng
ia available from stoak
for ti.85 eaah. Tbla pal00 lebaemd ontheRJ412O&ad.ngbd4greturxd
byu. s. Mallupoare~t
PAADIWAPPROVED
17
INDUSTRIES,
INC.
SERVICE INSTRUCTION
RAJAY
DATE:
February
PARTS
AFFECTED:
3,
SERVICE
1971
LETTER
NO. 18
OLD STYLE OXYGEN OUTLET ASSEMBLIES
TIME OF COMPLIANCE:
WHEN NECESSARY
All old style
oxygen outlet
assemblies
will
not accept the
The valve body may be modified
quick-disconnect
hose fittings.
compatible
with both aid and new style
fittings.
Remove valve body from regulator
(or manifold)
with
(Do not lose valve and spring).
Modify
body as shown:
l/4
new Rajay
to be
allen
wrench.
NEU
Reassemble
90801,
Contact
Phone
after
cleaning
RAJAY INDUSTRIES,
No. 213/426-0346,
all
parts
with
iso-pro
INC.,
P. 0. Box 207,
to obtain
additional
alclhol
Long Beach,
information.
or equivalent.
California
RAJAY 1NDUSTRI ES, I NC.
SERVI GE INSTRUCTION
DATE:
SEPTEMBER
MODELS
AFFECTED:
TIME OF
DUCT
SECTI
FUTURE
SERVI
TURBOCHARGED
RAJAY
COMPLIANCE:
THERE
HAVE
RETAINING
PRESSOR
ON ANY
1972
5,
OPERATORS
BEEN
STUD8
ISOLATED
BACKING
DI
PIPER
SCRET
REPORTS
OUT
AND
ON OF THE
TURBOCHARGER,
INSTALLATIONS,
A REVISED
PA-30
MODELS
LETTER No.
GE
AND
19
PA-39
I ON
of
THE
TURBOCHARGER
INDUCTION
INGESTED
INTO
THE
COMPRECLUDE
THIS
FROM
OCCURRING
BEING
To
A3S’EMBLY
WILL
BE
USED
AS
SHOwN
BELOW:
NAS 183-L-8
STUD
AN 310-4 NUT
4 EACH REOUI RED
SAFETY
WIRE
MS 33540
2
THIS
OPERATORS
fRoM
RAJAY
(213)
INSTALLATION
DI SCRET I ON.
INDUSTRIES,
426-0346.
FAA DER APPROVED
MAY
ANY
INC.,
BE
PERrOWED
FURTHER
P.O.
AS
INFORMATION
Box
207,
A FIELD
LONG
(.030
DIA.)
TOP To
BOTTOM
F~ACES
MODIF\CATIoN
REOUIRED
BEACH,
MAY
AT
BE OBTAINED
CAL I FORNI A 90801,
PER
As
SHOWN
RAJAY INDUSTRIES,
Smv ICE INwRUCT
INC.
ION
.
DATE: APRIL 16, 1974
SUBJECT:
MODELS
PUMP
FUEL
AFFECTED:
LETTER No. 20
SERVICE
F ITT
ING
RAJAY
ALL
mO253-2
INLET
INSPECT
ION
TURBOCHARGED
(NOT
LYCOMING
ROO253-501
OR
APPC
ICABLE
FUEL
IN
ALT
ENGINES
FITTED
WITH
FUEL
PUMPS
WITH
9/16-18
TO PUMPS
WITH
TAPERED
PIPE
RAJAY
UNF THREADED
THREADED
PORTS)
T
IME
OF
&MPL
IANCE:
ANYTIME
INCREASE
PRESSURE
FLUCTUATES
DETERIORATES
OR
WITH
ITUDE
.
THE
ATTENTION
OF
ALL
OPERATORS
RECO~ENDAT
IONS
TO THE AFFECTED
TO GONT INUED
COW
INAT ION.
..
SAT
JET
FORTH
ENGINEa.
1sf
ANY QUESTIONS
INC.,
P. 0.
Box
AcfoRr
REGARDING
207,
of
FiOO253-501
w ITH RAJAY RO0253.-2
OR
SERV ICE BULLET IN NO. 374 DATED
F ITTED
RAJAY
FUEL
15,
LYCOHING
THESE
OPERAT
THE
THIS
LONG BEACH,
OF
SUBJECT
LYCOMING
PUMPS 18 DIRECTED
1974.
IT IS SUGGESTED
MARCH
IN THE
ABOVE
ADHERENCE
TO
ION
TURBOCHARGED
SERVICE
BULLETIN
RECOMMENDATIONS
WILL
RA~JAY TUREOCHARGER/LYWM
SHOULD
CAL IFORN IA 908Q1,
SE
DIRECTED
(213)
TO
ENGINES
TO LYCOM ING
THAT THE
BE APPL IEI)
CONTRIBUTE
ING ENG INE
RAJAY
INDUSTRIES,
426-0346,
.
FAA DER AF'F'ROVED
APRIL
16,
1974
RAJAY
INOUSTRIES,
SERVICE
MAY 15,
DATE:
EQUIPWENT
INC.
INSTRUCTION
SERV ICE
1976
AFFECTED:
ALL
<
AIRCRAFT
ANO
AIRCRAFT
ENGINES
LETTER
EQUIPPED
UITH
NO.
21
RAJAY
TURBOCIARG~R~
To:
AIRCRAFT
ANO
ENGINE
AIRCRAFT
OPERATORS
MANUFACTURERS
ANO
AIRCRAFT
MODIFICATION
&
MAINTENANCE
0ASCS
TIME
OF
WITHIN
COMPLIANCE:
25
NEXT
HOURS
SERVICE
ANO
SUBSEQUENTLY
AS
SCHEOULED
BELOU.
SUS
INSPECTION
JEcT:
OF
TURBINE
TUR~OCNARGER
(EXHAUST)
HOUSING
REASON:
CRACUS
HAIRLINE
IN
RAJAY
ARE
FITTED
APPL
I CABLE.
OOCS
NOT
UITN
TURBINE
APPEAR
TO
DISTRESS
A
SEEN
MOUSING
A
PARTS
SKETCH
FOR
UNITS
Tl4E
CRACK
OF
AREA
HAVE
THE
NOT
SEEK
IN
OF
IN
SERVICE
UPUAROS
AS
INOICATE
TO
INLET
INLET
THEREFORE
NAND
TURBINE
OF
10
NO
YEARS
3/4
AN0
INCM
IN
LOCATION.)
GAS
INLET
CRACKS
THIS
IN
AREA
T ION:
OESCRIP
IT
UNT
IS
I L
RECOMnENOCO
TML
LATER,
200
IS
DISTRICT
CMANOE
25
SUOJECT
OR
LENGTH,
TO
REPORT
8330-2,
FORK
LATER,
HOURS
SERVICE
UNTIL
REPLACED
UNIT
IN
SQSEOULE
TC 59-11
A
THE
ANO
BE
INSPCC
T ION
TO
CHANGE
P/N
APPROPRIATE
FROM
SHOULD
9~0~
I T
HOUS
I NCS
BE
“El*
OF
CFCECT
ANO
TC 60-17
THE
THIS
CONTIN-
“0”
CHANCE
TURBOCliARaER
MODEL.
~~~~~~~~~
LETTER.
ABOVE.
MAOC
AT
FINDINGS
TO
INTO
LATER,
TO
RECEIPT
PER
IT
PUT
OR
ANY
TIME
THE
CRACK
BY
COMPLETtNG
THE
LOCAL
FAA
THE
CHANCE
LETTERS
BEACH,
CA 90801,
IS
THE
OBSERVED
TO
MALFUNCTION
GENERAL
AVI
ATI
OR
ON
OFFICE.
IT
IS
ANTICIPATED
AVAILABLE
ON
TO
:
REVISED
OBTAIN
FAA -
TURBINE
PER
SMOUN
ABOVE
JuNIE..~,*‘~~.
RAJAY
CONTACT
426-0346,
APPROVAL
TMC
INCN
FAA
"A"
UITMIN
RECOMPlENOCO
REPORT,
INSPCCTION
WITH
HOURSINTERVALS
OF
3/4
BEYOND
IT
REPLACED
INSPECTION
AT
REPLACEMENT
OEFECT
IS
TC 82-11
THE
INITIAL
EXTENO
Tl4C-COLLOVING
UNIT
OR
INSPECTIONS
BE
RAPIOLY
EXAMPLES
THE
NOUSING
TURBOCHARI~ERS
TC 82-11
ANO
POSSIBLE
OR
TURBINE
Tnrsc
PROPAGATE
EXHAUST
UED
THE
TC 60-11,
DOES
TONQUE
OF
325EF10.
AND
ITEM.
THAT
AREA
TONGUE
325E10,
TC 59-11,
AIRUORTNINESS
IN
IN
TNC
NURSER
TKIS
PRESSING
PARTING
(SEE
LENGTH.
BE
IN
315Flo,
INOICATES
APPARENT
NAIRLINE
OISCOVEREO
301E10,
MODELS
INVESTIGATION
EXTERNAL
SNOV
HAVE
TUR~OCMARGER
INOUSTRICS,
FURTHER
OER.
APPROVED
~NC.,
INFORMATION
P.O.
Box
AS
207,
AVAILABLE.
LONO
PHONE
(213)
WILL
*
m
PAGE: ? O? 2
RAJAY INDUSTRIES,
A .suw*
of 7-h
rffstu
INC.
Comntion
No.
21A
(.%PERSEDES
SERVICE
FAA AWROVEO
INSPCCTION
EQUIPMLNT
ALL
AFFECT~O:
DISTRIBUTION
TO:
COMPLI
OF TURBOCMAROER
AIRCRAFT
AIRCRAFT
AND
OF
21
DATED
1976)
1976
9,
SUBJECT:
TIME
LETTER
MAY 15,
AUGUST
DATE:
SERVICE
LETTER No.
AT
ANCE:
ANO
AIRCRAFT
THt
TURBINE
ENGINES,
EQUIPPED
ENGINE
MANUFACTURERS
-
*ANO
MAINTENANCE
MODIFICATION
NeXT
ENGINE
YHICWEVER
(EXHAUST)
MAJOR
COMES
RAJAY
WITH
OR
TUROOCNARQER
OF
THC
HOUSINGS
TURBOCWARGERS
AIRCRAFT
OPERATORS
BASES
OVERMAUL,
FIRST.
REASON:
HAIRLINE
IN
CRACKS
RAJAY
NAVE
SEEN
OISCOVLALD
ARE-
PITTLO
.,_,
APPI.
t CABLE.
YIT~
,.*’
DOES
NOT
TURII~NE
EXTERNAL
WOUSINQ
INvESTIOATI~N
APPEAR
TO
DISTRESS
IN
3OlE10,
TUROOGHARG~R.WOOELS
PART
A
l
TWIS
iWSSlNG
APPARENT
TONOW
AREA
CRACK
DOES
AIRUORTMINESS
IN
UNITS
NOT
ITEM.
THAT
TURSINE
MOUSING
INLET
325E10, ANO 325EF10,
TMESIZ TUROOCHARSCRS
TC 59-11, TC 60-11,
AND TC 82-11 AS
NUWSLRS
INIICATES
SE
TNE
315F10,
NAVE
9EEN
IN
RR~RASATL
RAPIDLY
EXAMPLES
IN
SERVICE
UPWARDS
THEREFORE
HAND
INDICATE
10
TO
NO
YEARS.
PURPOSZ
INSPECTIOU
FOR
WOOCLS
3QlE10,
TuRalNE
MOUSING
HAIRLINC’CRACKS
315Fl0,
PART
IN
TWC
TURBINE
HOUSINQ
INLET
IN
THESE TURBOCHARGeRS
325E10, AN0 325EFlO.
RUHBERS
TC 59-1-l. TC 60-11,
OR TC 82-11
RAJAY
TuRaocNARoEIt’
ARE
AS
FITTED
WITH
APPLICABLE.
INSTRUCTIONS:
tT
IS
RECOMMENDED
CONTINUEO
TC 60-11
THE
"0"
(SEE
THE:
CHANGE
TURBOCNARCLR
REPLACE~IENT
EXTENO
THAT
UNTIL
THE
UNIT
OR
INSPECTION
IS
SCNEDULE
REPLACEU
LATER
,
OR
YITH
THE
OF
82-11
TC
THIS
LETTER
No. TC
PART
“A”
BE
"E"
59-11
CMANGE
OR
PUT
INTO
CHANGE
LATER,
LPFLCT
OR
AN0
LATER,
APPROPRIATL
TO
MODEL.
OF
B~YONO
SKETCHES
THE
3/4
SUSJECT
IUCH
UNIT
IN
LENGTH
SHOULD
IN
BE
TYPE
MAOE
A
AT
CRACKS
ANY
TIME
TME
ANO
OVER
2
CRACK
IS
INCWCS
IN
01)SERVLD
TYPE
6
TO
CRACKS.
BELOW)
~~~:~~~~~~~~~~~~~~p~::~~~:
-c>::;:
THIS
0‘
*ALA
TO 3/4
0
a
ALLOWABLE
INCH
’
0
TYPE
A
\,,>
2600
EAST WARDLOW
ROAD
/ P.O. BOX
207
/
LONG
BEACH,
CALIFORNIA
90801
/ PHONE
(213)
4260346
PACE 2 OF 2
POSSIELE
AREA
VIEW
TURBO
OF
TURBINE
CENTER
HOUSING
SECTION
:
11
IS
OEFECT
AVIATION
RECOMMENOEO
REPORT,
OISTRICT
TO
REPORT
fi4A
FORM
OFFICE.
THIS
2
INCHES
WITH
TYPE
OR
IN
TO
REMOVED.
VIEW
ENLAROEO
-..
CRACKS
ALLOWABLE
THE
8330-2,
OF
AREA
CRACIED
B
INSPtCTION
AN0
FINOINCS
TO
SUBMIT
IT
BY
COMPLETING
TO
THE
LOCAL
THE
FAA
MALFUNCTION
QENERAL
RAJAY INDUSTRIES,
A 3tbdky
of Thm TOXJIW Coqwntion
INC.
XBdl
SERVICE LETTER
Date:
April
No. 22
3, 1978
Model Affected:
AllRaj&y
Turbocharged
Mooney
M 20 E (Super 21) and M 20 F
(Executive)
Aircraft
Subject:
Oil seepage into
exhaust pipe
Time of Compliance:
Customer Option
not required
overboard
- Compliance
Oil has appeared in the overboard
exhaust pipe of a few of
the subject
airplanes
prior
to engine start-up.
This is
caused by oil from the turbocharger
oil outlet
line draining
into the turbocharger
bearing housing during periods
of
engine idleness.
Some of this oil seeps out the turbocharger shaft seal and into the overboard
exhaust pipe.
This
oil clears
up after
running the engine a short time and no
oil leaks during normal engihe operation.
For owners who desire to eliminate
replacement
kit is available
for
price is effective
thru December
The modification
the turbocharger
fire shielding
Contact
Rajay
Attachment:
2600
EAST
WAADLOW
this oil seepage,
$125.00 from Rajay.
31, 1978.
a parts
This
adds a MS28885-8 check valve and replaces
oil outlet
hose with two shorter
hoses and
as shown on attached
E.O. 440.
for
E.O.
ROAD
any additional
information.
440
/ P.O.
BOX
207
/ LONG
BEACH,
CALIFORNIA
90801
/ PHONE
(213)
426-0346
.
.
’
RAJAY INDUSlRIES,
A SuMdiuy
of The Texsnu
e
INC.
Gmpmation
SERVICE LETTER
Date:
October
Inspection
and replacement
cation
system check valve.
Equipment
Affected:
Helio
of
Reason:
Purpose:
*Continental
EAST
WARDLOW
aircraft
listed
PA30 & 39
PA32-260
PA24-250
PA24-400
PA-23 and
PA-23-160
PA-23-235
and
PA-23-250
(B)
PA-23-250
and
PA-E23-250
(C)
B95
M20 A,B,C,D,&G
"310 I & J
*310 C,D,E,F,&G
"180
*182
"310 Rocket
H-295
Beechcraft
Mooney
Cessna
Time
All
of
Model
Piper
2
1978
Subject:
Aircraft
2600
2,
No. 23
Page 1 of
Compliance:
At next
required.
scheduled
turbocharger
lubri-
as follows:
STC No.
E.O.
SA787WE
SA1557WE
SA811wE
SA2359WE
934
930
942
942
SA4-1637WE
939
SA539WE
933
SA840WE
SA153SO
SA1156WE
SA181SO
SA2383SO
SA1157WE
SA1032WE
SA212SO
SA156SO
903
941
940
938
935
936
937
932
931
maintenance
or
No.
as
In-service
experience
has shown that the o-ring
seal may be dislodged
from the valve
seat and cause
restriction
of oil flow to the turbocharger
bearing.
To replace
check valve
P/N B-4C2-25
with an
improved
P/N 532A-2M.P-18*
check valve
(Continental
engine)
or P/N 532A-2MP-27
check valve
(Lycoming
engine).
engines
ROAD
use-18
/ P.O.
BOX
207
I
LONG
BEACH,
CALIFORNIA
90801
I PHONE
(213)
4264346
.,’
SERVICE LETTER #23
Page 2 of 2
For
each
1.
2.
3.
affected
Aircraft
Model
Remove
Install
incorporating
existing
check valve
new check valve
P/N
P/N
(Optional)
If so equipped,
(Optional)
Remove Pressure
Plug old port
with AN913-1D
Switch
Rajay
Turbochargers:
P/N B-4C2-25
532A-2MP-27
on aircraft
with Lycoming
engines
532A-2MP-18"on
aircraft
with Continental
engines
relocate
low oil pressure
switch
as shown below
Check Valve:
Remove P/N B-4C2-25
Install
P/N 532-2MP-2
or
7
a*
(Optional)
Low oil press
switch
(relocated)
AN825-1D Tee
AN910-1D Union
Reqd. to move
switch
FAA Approved:
.
*Continental
engines
use - 18
/-h?
.
DEPARTMENT
FEDERAL
OF TRANSPORTATION
AVIATION
AOMINISTRATION
WESTERN
REGION
P 0 BOX 91007. WORLwAr
POSTAL CtNTtR
LOS ANCELLS. WLIFOIINIA 90009
MAY
1 1979
In Reply
Refer to:
AWE-140:GDR:8110-8
Rajay Industries,
P. 0. Box 207
Long Beach, CA
Reference:
90801
Mr. R. Lloyd
Director
of Engineering
Attention:
Subject
Incorporated
:
Approval
of Rajay Industries
Service
Letter
incorporating
new check valve in turbocharger
Rajay
letters
dated
10/2/78
No. 23
oil system
and 11/22/78
Gentlemen:
We have received
the Engineering
Orders to the affected
Drawings
and
Service
Information
Letter
No. 23 submitted
with the reference
Rajay
letters,in
which you show the replacement
of existing
turbocharger
oil
system-check
valve with an improved
type for the following
affected
aircraft
models:
Aircraft
Model
STC No.
Piper
PA30&39
PA32-260
PA24-250
PA24-400
PA-23 and
PA-23-160
PA-23-235
and
PA-23-250
(B)
PA-23-250
and
PA-E23-250
(C)
895
M20, A,B,C,D&G
*310 I & J
+310 C,D,E,F,&G
*180
*182
*310 Rocket
H-295
SA787WE
SA1557WE
SA811WE
SA2359WE
934
930
942
942
SA4-1637WE
939
SA539WE
933
SA840WE
SA153SO
SA1156WE
SA181SO
SA2383SO
SA1157WE
SA1032WE
SA212SO
SA156SO
903
941
940
938
935
936
937
932
931
Beechcraft
Mooney
Cessna
Helio
E.O.
No.
BUSINESS
FIRST
CLASS PERMIT
REPLY MAIL
3130
LONG BEidH;
RAJAY INDUSTRIES,
P-0.
BOX 207
Long
Beach,
Service
CA
CALIFORNIA
INC.
90801
Letter
No.
24
Sht.
TO PREVENT POSSIBLE ISSUANCE OF AN A.D:PLEASE
DO MODIFICATION
PER THIS SERVICE LETTER'A.S.A.P.
AND RETURN COMPLETED CARD TO RAJAY INDUSTRIES,
Aircraft
*-..,
Make
Model
Serial
Number
Total
Time
S.M.O.H.
Reg. No.
Total
Time
Engine(s)
Turbocharger
Turbocharger
Turbocharger
Turbocharger
Model No.
Part No. RJ
Serial
No.
Time Since New
State when .recommended
accomplished:
modification
INC;
Year
Total
Airframe
Time
Date of Rajay
T/C Purchase
(LH)
(IX)
(LH)
(LH)
(hrs)
4 of
(=I)
(=I
(N-I)
(Nil
Kf
(staking
three,-screws)-%as
(Date)
A&P Lit.
BY
No.
(Signature)
Note mechanic,
owner or pilot
must fill
mechanic
must enter
time,
date,
S/N of
P/N in log book after
above modification.
Shop Name
City
Is aircraft
based
Owner ' s Name
City
in above
statement.
A/C & T/C, plus T/C
Address
State
Zip
here?
Address
State
Zip
A&P
model &
4
--
.
.
.
.
2
We find the
Information
copy of each
information
changes to the type design
and the referenced
Service
Letter
acceptable.
Accordingly,
we are returning
to you one
of the subject
engineering
orders
and drawings
for your
and file,
and we shall
keep the other copies
in our file.
Sincerely,
-?
ROBERT E. FOLLENSBEE
Chief,
Propulsion
Branch
Enclosures
FAA Approved
Date:
February
7, 1979
Subject:
Securing
attachment
turbocharger
screws.
Models
Affected:
housing
flange
Piper
Seneca PA34-200
with
Rajay Model 3OlElO
Model
turbochargers
added per STC SA2937WE.
301ElO-2
turbochargers
supplied
to Lycoming
and Enstrom
Helicopter
Corporation.
The above
model number turbochargers
with
serial
numbers
higher
than 70484 are excluded
from the provisions
of this
service
letter.
All Rajay
turbochargers
with
sand cast
(single
piece)
bearing
housings
are also excluded.
Reason:
There have been field
reports
of oil
leakage
between
the bearing
housing
flange
and bearing
housing
on Rajay Model
301ElO-2
turbochargers
during
flight.
This
service
letter
specifies
a recommended
inspection
schedule
and'describes
the recommended
modification
and its time of
compliance.
The recommended
modification
is
needed to prevent
possible
oil
leakage
through
the mating
faces of the turbocharger
bearing
housing
and bearing
housing
flange
due to torque
loss of the three
attaching
screws.
This may
cause accelerated
engine
oil
consumption
inflight.
--n_-.
't
Type
of
Compliance:
RECOMMENDED
Time
of
Compliance:
See Below
A.
Inspection
before
Modification:
1,
Prior
to next flight
and every
flight
thereafter,
until
the recommended
modification
has been completed,-inspect
the underside
of the lower
cowling
and interior
of the
exhaust
pipes
at the exit
end for evidence
of oil
leakage.
2,
Within
hours
a.
2600
bearing
EAST
WARDLOW
the next
thereafter:
25 hours
Check for play
housing
flange
ROAD
/ P.O.
BOX
of
service
time
or loose connection
and bearing
housing.
207
/ LONG
BEACH,
CALIFORNIA
and
between
90801
every
25
bearing
/ PHONE
(2131
42643~
b.
a.
Check for evidence
of oil
housing
flange
and bearing
leakage
housing.
between
bearing
See Fig.
1.
LXodification:
Immediate
compliance
with this modification
is necessary
if any looseness
is detected
in the turbocharger
or if
Even
any oil
leakage
from the bearing
housing
is found.
if there
is no looseness
or oil
leakage,
this
modification
should
be completed
at the next aircraft
annual
inspection
or at the next engine
or turbocharger
overhaul.,
whichever
comes
first.
The modification
is to be completed
as
follows:
1.
Remove
the
turbochargers
from
aircraft.
2.
Scribe
mating
index mark on bearing
housing
and
bearing
housing
flange
so they can later
be reassembled
in the same position.
(See Fig.
1 and
2).
3.
Remove compressor
housing
using
a 5/32 allen
wrench
to remove
(6)
countersunk
cap screws that
secure
the compressor
housing
to the bearing
housing
assembSeparate
these two components
and remove the
ly.
It may be necessary
to tap the compressor
gasket.
housing
gently
with
a plastic
mallet
while
holding
the bearing
housing
assembly.
4.
Tighten
flange
pounds
(3) cap screws that secure
bearing
to bearing
housing
evenly
to 80-100
and stake in two places
as shown in
housing
inch
Figure
2.
5.
Inspect
compressor
housing
gasket
surface
for damage
and remove old gasket
material
residue.
Clean gasket
surfaces
and install
new compressor
housing
gasket.
(Rajay
P/N TC-6-44)
6.
Reinstall
compressor
housing
to bearing
and secure with
six cap screws.
Tighten
ternately
to 80 to 100 inch-pounds.
7.
Remove
ducting.
8.
Reinstall
turbochargers.
Torque
turbine
V-Band to 15-20 inch-pounds.
Retorque
flight
or run-up.
9.
Indicate
compliance
with the modification
described
the "B. Modification"
portion
of this
service
letter
by metal stamping
or scribing
the number
"24" at
corner
of nameplate.
(See Fig.
3).
all
evidence
of
oil
from
inlet
housing
evenly
flange
& al-
and exhaust
housing
after
next
in
BEAWN
10.
When this modification
is
in the aircraft
log book,
serial
number,
turbocharger
dnd serial
number(s).
11.
Complete
service
and
letter
completed
it must
along
wit;
the
aircraftbe entered
model number,
part
number
return
compliance
card
to Rajay Industries,
attached
Inc.
MOUSING
‘I
CHECK
FCR
LOOSENESS
FIG. 1 CROSS SECTION
TURIOCMARGER
of
On.t.EAU%E
0~2
FIG. 2 VIEW Of
_-
BRG.
HOUSING
FLLNGE
to
this
*
0
e
RAJAY INDUSI’RIES,
INC.
SERVICE BULLETIN
Date :
July
Subject:
Recommended Overhaul
No. 25
6, 1979
Procedures
for
Sky-Ox
Equipment
The following
Service
Bulletin
addresses
the problem of recommended
overhaul
times for Sky-Ox equipment
as supplied
by Rajay Industries,
Inc.
These recommendations
are based on regulations
as specified
by
the controlling
agencies
or Rajay's
years of experience
in servicing
Sky-Ox equipment.
Additionally,
all oxygen equipment
should be maintained,in
the field
in accordance
with AC 43.13.
CYLINDERS:
Cylinders
must be maintained
and hydrostatically
tested according
to the Code of Federal Regulations,
Title
49, Chapter I, Paragraph
173.34.
This regulation
specifies
hydrostatic
testing
at periodic
intervals
depending on the specification
stamped on the cylinder.
For specification
DOT-3AA, the cylinder
must be
retested
every 5 years.
For DOT-3HT the interval
is
reduced to every 3 years.
Cylinders
with suspected
damage should be.inspected,
and retested
as needed,
immediately.
REGULATORS:
Rajay recommends that all Sky-Ox regulators
be inspected and repaired
whenever leaks,
damage or malfunctions
occur or are suspected.
In any event,
the regulator
should be inspected
according
to its
usage rate as follows:
Equipment Usage
Recommended Inspections
Daily
Every year
Once per week
Every two years
Once per month
Every five years
The above recommendations
are to be used as a guide
and are not to be construed
as rigid
rules.
Individual
experience
may dictate
shorter
or longer
inspection
intervals
and, subject
to local
approving
authorities,
these intervals
may be altered.
--,,\
/'
2600
EAST
WARDLOWROAD
/ P.O. BOX 207 / LONG
BEACH,
CALIFORNIA
90801
/ PHONE
(213)
426-0346
Service
MASKS:
Service
station
Service
or masks
equipment
Bulletin
No.
25
Masks should be periodically
cleaned with a mild
soap solution,
as usage warrants.
Sufficient
care
should be exercised
to avoid damaging the microphone in those masks, so equipped.
As a minimum,
the masks should be cleaned during the times when
the regulator
and cylinder
are being inspected.
for Sky-Ox equipment
can be obtained
from any FAA repair
certified
to work on Sky-Ox Brand regulators
and cylinders.
may also be obtained
by returning
the regulator,
cylinder
to the factory,
by insured
means.
Address all returned
with instructions
on what is to be done, to:
Sky-Ox Repairs
% Rajay Industries,
Inc.
2600 E. Wardlow Rd.
Long Beach, CA 90801
Sincerely,
RJWAY INDUSTRIES,
-7
INC.
Sht
R&MY INDUSTRIES,
SERVICE
1 of
4
INC.
LETTER
No. 26
Rev. N/C
FAA Approved
Date:
July
Subject:
Resetting
of Flow
Oxygen Regulators
Equipment
Affected:
28,
1980
Rates
of
Sky-Ox
Sky-Ox* Models 2600A, 2600B, 2800A, 2800B,
2900A and 2900B oxygen regulators.
Other
possible
numbers
located
on the regulators
are 2779-A-2,
2776-A-3
& 2777-A.
Regulator Models 2700A and 2700B, also designated 2779-A-4
(four
outlets)
used on portable.Sky-Ox
systems SK-lo,
have adequate
oxygen flow to 20,000
feet and are excluded from the requirements
of this
service
letter.
Models
gulators
portable
2600A and 2600B are
normally
installed
oxygen systems.
two-outlet
on Model
reSK-9
Models 2800A and 2800B are pre-set
regulators for multi-outlet
oxygen systems
permanently
installed
in aircraft.
They can
be installed
as part of FAA STC approved
kits
as listed
in the "Aircraft
Affected"
section
of this
service
letter.
They can
also be installed
as separate
parts
or
assemblies
and locally
approved
by FAA
form 337.
When approved
in this
latter
manner,
the complete
installation
system
is sometimes
designated
SK-101.
Models 2900A and 2900B are automatic,
altitude
compensating
regulators
for multioutlet
oxygen systems permanently
installed
in aircraft.
They can be installed
as part
of FAA STC approved
kits
as listed
in the
*Possibly
or Rajay
2600
EAST
WARDLOW
sold by Air-Ox
of Portland,
Industries
as "Sky-Ox".
ROAD
/ P.O. BOX
207 / LONG
BEACH,
OR, Dye-Ox
CALIFORNIA
90801
of
Phoenix,
/ PHONE
(213)
AZ,
426-0346
Sht
SERVICE LETTER No.
26 Rev.
2 of
N/C
section
of this
service
"Aircraft
Affected"
letter.
They can also be installed
as separate
parts
or assemblies
and locally
approved
by FAA form 337.
When approved
in this
latter
manner,
the complete
installation
system is sometimes
designated
SK-1001.
Aircraft
Affected:
Aircraft
Make
Travel
Air
Bonanza
Cessna 180
Cessna
182
Cherokee
Seneca
Twin Comanche
Aircraft
with a portable
SK-10 Sky-Ox
oxygen system on-board
or with a locally
approved
Sky-Ox system fixed
installation.
The following
aircraft
with a Sky-Ox fixed
system installed
per the applicable
STC
are also affected.
Aircraft
Model
55 & 95 Series
33 & 35 Series
G,HCJ
(S/N 18051313
& Subsequent)
E thru P
.(S/N 18253599
& Subsequent)
PA32-260
& 300
PA34-200
PA30 & 39
Applicable
S.T.C.
SA2977WE
SA2978WE
SA2979WE
SA2980WE
SA2933WE
SA2932WE
SA2849XE
Type
of
Compliance:
MANDATORY
Time
of
Compliance:
Prior
to next usage of oxygen system.
FAA AD will
soon be issued
requiring
pliance
within
60 days.
An
com-
Reason:
The affected
regulators
may not meet the
FAA minimum required
oxygen flow rate
under all circumstances
when set by the
former
method.
Purpose:
To reset
the affected
regulators
using a
method which better
simulates
altitude
and
insures the flow rate meets FAA minimums
under all circumstances.
4
Sht
SERVICE
Instructions:
A.
LETTER No.
26 Rev.
3 of
N/C
Regulator
Models 2600A, 2600B, 2800A
ana
1.
Inspect
Sky-Ox oxygen system regulator
and determine
if it is
Note that only the
affected.
Models 2700A, 2700B (2779-A-4)
four-outlet
regulators
are not
affected.
If it is Model 2600A,
2600B, 2800A or 2800B proceed
as follows.
2.
First
inspect
further
to see if
there
is a part
number 500014-01,
500014-02
or 500016-01
stamped
or etched
on.
Next determine
if
there
is a letter
"A" or "RA"
stamped just
under the left
'side
of the serial
number.
Example:
7955641
or
7955641
RA
A
If any of the above numbers or
letters
are stamped on the reguit has already
been reset
lator,
and can be safely
used with no
further*action
required.
However,
the limits
of items 6 & 7
following
apply.
If neither
numbers or letters
are present,
proceed
to item 3 following.
3.
Remove regulator,
safely
package
it and return
it to Rajay Sky-Ox
Sales,
at the address
shown on
this
letter.
4.
Rajay will
reset
free of charge,
freight
paid.
5.
A letter
enclosed
lator
will
explain
and its effect.
6.
The Models 2600A and 2700B regulators
will
be reset
to provide
adequate
flow up to 20,000
feet.
7.
The
be
Up
up
the regulator,
and return
it
with the reguwhat was done
Models 2800A and 2800B will
reset
to provide
adequate
flow
to 25,000
feet
for a pilot
and
to 9 passengers.
4
Sht
SERVICE LETTER No.
B.
26 Rev.
4 of
N/C
Regulator
Models 2900A and 2900B
Inspect
Sky-Ox oxygen system re1.
gulator
to determine
if it is
affected.
If it is a Model 2900A
or 2900B, proceed
as follows.
2.
First
inspect
further
to see if
there
is a part number 500015-01
stamped or etched
on.
Next
determine
if there
is a letter
"A" stamped
just under the left
side of the serial
number.
Example:
7955641
A
If either
of the above number or
letter
is stamped on the regulait has already
been reset
tor,
and can be safely
used with no
further
action
required.
However,
the limits
of item 5
following
apply.
If neither
the number or the letter
is
stamped on, proceed
to item 3
following.
3.
Telephone
or write
Rajay Industries
and indicate
you have a
Model 2900A or 2900B regulator.
4.
If you choose,
you may request
Rajay to send an instrument
panel
placard
indicating
an oxygen system
limit
of 20,000
feet.
5.
Alternately,
you may immediately
send your regulator
back to Rajay
for resetting
to a limit
of 25,000
feet
for a pilot
and up to 9 passengers.
6.
If desired,
you can apply the
placard
immediately
and send
in the regulator
for resetting
to
a 25,000
feet
limit
at some more
convenient
time before
December
31,
1980.
If more information
Rajay Sky-Ox Sales
is needed,
by mail or
contact
telephone.
4
7101
FAIR
AVENUE
NORTH
.
HOLLYWOOD,
CALIFORNIA
June
91605
24,
FAA APPROVED
SERVICE
Subject:
Rajay Turbocharger
Model 325ElO-2
charger
Turbine
(Exhaust)
Housings
letter
0 or E and/or
600510-02.
Equipment
Affected:
Distirubtion
To:
Time of
Aircraft
Piper
Piper
Piper
Piper
Piper
Mooney
*
(213)
982-4500
1982
LETTER
NO. 27
Inspection
of
P/N TC-60-00
Turbo-
Model
Turbo Arrow
III (PA-28R-201T)
Turbo Arrow
IV (PA-28-RT-201T)
Turbo Dakota
(PA-28-201T)
Seneca
II (PA-34-ZOOT)
Seneca III
(PA-34-220T)
231 (M20K)
ManufacturersEngine ManufacturersMaintenance
and/or
Aircraft
Aircraft
Aircraft
Bases-
Modification
Inspection
of turbocharger
housing
is required
at first
200 hour unit
time in service,
and subsequently
at the
time intervals
specified
by FAR 591.169
(ie.
100 hours
when carring
people
or giving
flight
instructions
for
hire,
annually
for all others).
Compliance:
Reason:
Formation
of hairline
cracks
have been discovered
in the exhaust
inlet
area of
turbine
housing
TC-60-11
(600510-02)
used on Model 325ElO-2
Rajay turbochargers
In some cases,
the crack
in the tongue
area has
in production
since
June,
1976.
propagated
through
the outer
wall
of the turbine
housing.
Therefore,
field
and/or
propagation
inspection
monitoring
of subject
hairline
is required
cracks
in
to detect
the
turbine
possible
housing.
formation
Instructions:
Perform
visual
"/N 600510-02,
in View 3.
A.
Turbocharger
1.
inspection
of the turbine
to determine
existence
of
Inspection
housing
P/N TC-60-11
Rev.
Type C, Stage 2 cracks***
D or E and/or
as indicated
Instructions
Installed
Turbocharger
Inspection
- After
an initial
200 hours
time-inservice
operation
and each subsequent
inspection,
visually
inspect
the
turbine
housing
outer
wall
for complete
penetration
of type
"Cl', Stage
2, Cracks
per View 3.
See Section
B instructions
for more information.
TELEX
NO
65139O(ROTOMASTER
AN
6CllWl
LSA,
COMPANY
.
CABLE.
ROTOTURBO
ROTO-MASTER
INC.
-2-
2.
a.
housing
w ith a new
If Outer Wall Is Penetrated
- Rep lace the turbine
housing
and rep lace the
P/N 600510-02
(TC-60-11)
(TCM P/N 643930"')
gasket with a new P/N 600400-00
(TC-6-30)
(TCM P/N 643932** ) gasket,
in accordance
with the Manintenance
Manual G70*, and Section
6 instrucUse a new P/N 600510-04
(TCM P/N
tions
prior
to the next flight.
643931**)
if available.
b.
If Outer Wall Is Not Penetrated
perform
a removed turbocharger
follow
and Section
B instructions.
- At the
inspection
next
per
scheduled
inspection,
the instructions
to
- Remove the turbocharger
(see Section
Removed Turbocharger
Inspection
instructions
fonowing)
and inspect
for cracks as shown in View 1.
a.
If No Cracks Are Found - Reinstall
turbocharger
scheduled
inspection,
reinspect
per "Installed
- paragraph
preceding.
b.
If An Internal
instructions
and at the
Turbocharger
Crack Is Found - Remove turbine
housing
per
and inspect
for cracks as shown in View 2.
next
Inspection"
Section
6
(1)
If All Internal
Cracks Are Within
Limits
- The turbine
housing
may be continued
in service
temporarily
if a crack within
the
limits
of View 1 and 2 is found,
but the turbine
housing
must be
removed for reinspection
every 100 hours of service
time.
If,
in the future,
the crack exceeds the limits
of View 1, 2, or 3,
take action
as described
in sub-paragraph
(2) following.
(2)
If An Internal
Crack Exceedes The Limit
- In this case a new turbine
housing
and.gasket
should be installed.
If a new housing
is unavailable,
the old one can be used temporarily,
but it must be reinspected
per Views 1, 2 and 3 every 25 hours of service
until
replaced.
In any case, when a crack penetrates
the outer wall as
shown in View 3, the turbine
housing
and gasket must be replaced
prior
to the next flight.
NOTE:
Since earlier
Seneca II aircraft
may not have the subject
turbine
housing
installed,
take special
care to inspect
the
part number per the Section
B instructions.
If unable
to precisely
letter,
assume it is
inspections,per
this
determine
the part number
an affected
turbine
housing
Service
Letter.
or revision
and perform
If the old turbine
housing
(P/N TC-60-11,
Rev. 0 or E or
P/N 600510-02)
is replaced
with a new one that is affected
by this Service
Letter,
this Service
Letter
will
still
apply
after
the housing
accumulates
200 hours service
time.
After
this
replacement
with a new 600510-04
Service
Letter
no longer
applies.
turbine
housing,
PAGE 1 OF 9
SEPTEMBER 24, 1982
REVISION
A
7101
FAIR
AVENUE
.
NORTH
SERVICE
HOLLYWOOD,
CALIFORNIA
LETTER
91605
.
December
30,
(213)
962-4500
NUMBER 27
FAA APPROVED
REFERENCE:
AD 82-27-03
SUBJECT:
Rajay
(Effective
Turbocharger
Inspection
P/N TC-60-11
600510-01,
Turbine
and/or
600510-02.
Applies
AFFECTED:
325ElO
of Turbocharger
Housings
EQUIPMENT
Model
1982)
to
affected
all
airplanes
certificated
that
installed
have
engines
all
in
Rajay
and
categories
turbocharger
model
325ElO.
DISTRIBUTION
Time
of
TO:
Aircraft
Manufacturers-
Aircraft
Engine
Aircraft
Maintenance
Inspection
Compliance:
housing
of
and/or
the
Modification
Basesturbine
turbocharger
required:
Within
at
Manuafcturers-
the
50 hours
next
inspection,
unit
time
aircraft
annual
whichever
Then
at
in
or
comes first,
200
hour
service,
or
100
hour
and
time-in-service
intervals.
Reason:
Formation
of
of
the
turbocharger
600510-02)
used
since
June
1976.
area
(tongue
turbine
cracks
hairline
has
turbine
on
Model
In
area)
some
been
housing
discovered
(Rajay
325ElO
Rajay
cases,
the
may have
part
number
in
through
the
the
housing.
TELEX
NO
65~1390(ROJOMASJER
AN
ECHLIll
LSAJ
COMPANY
l
the
turbochargers
crack
propagated
in
CABLE
ROJOJURBO
inlet
area
TC-60-11
in
production
above
referenced
outer
wall
or
of the
SERVICE
LETTER
NUMBER 27
PAGE 2 OF 9
SEPTEMBER
visual
Therefore,
"Time
of
and/or
propagation
Compliance"
Upon
replacement
Ala,
AZb(2)
Ductile
inspection
of
subject
of
the
with
a
to
new
as
detect
hairline
referenced
the
cracks
subject
P/N
no longer
required
paragraph,
Ni-Resist),
Letter
is
600510-04
the
per
P/N
above
housing.
instructions
turbine
(TCM
1982
formation
turbine
housing
improved-material
in
possible
in
turbine
24,
housing
643931**),
(D5S
this
Service
P/N
TC-60-11
applies.
DESCRIPTION:
Perform
and/or
a visual
P/N
indicated
A.
“...
inspection
600510-01,
in
the
600510-02,
Figure
Turbocharger
of
2,
Views
to
turbine
housing
determine
existence
of
cracks
as
1, 2 and 3.
Inspection
(See
Section
B for
detailed
inspection
instructions)
1.
Inspection
of
initial
50
and/or
at
hours
next
whichever
unit
Turbocharger
and
inspect
the
ascertain
possible
presence
as shown
a.
If
in
Outer
P/N
Wall
and
the
for
Is
presence
not
of
with
and
cracks
cracks
the
operation
hours
at
every
than
May
turbine
inspection,
200
hours
31,
1983.
housing
penetrating
-
the
Replace
a new P/N
new P/N
prior
Turbocharger
of
later
Penetrated
gasket
turbocharger
- After
to
outer
3.
housing
of
100
Turbocharger
gasket
64393p*)
Inspection
inspect
View
and/or
thereafter
but
Visually
643931**)
port
first,
Engine
time-in-service
annual
time-in-service,
wall
on
Turbocharger
aircraft
occurs
housing
2.
Installed
to
Removed
turbine
as shown
next
from
housing
in
600510-04
600400-00
the
View
the
(TCM
(TC-6-30)
P/N
(TCM
flight.
Engine
through
1.
turbine
the
Visually
exhaust
SERVICE
LETTER
NUMBER 27
PAGE 3 OF 9
SEPTEMBER
a.
If
No Cracks
the
turbine
the
200 hours
the
unit
b.
If
Are
A.l.
If
for
Found
of
housing
may
in
Cracks
are
Views
1,
be
returned
the
crack
monitor
2
200 hours
If
An Internal
in
Views
gasket
of
and
at
inspection
of
2 or
must
in
to
found
within
then
the
service,
the
turbine
but
propagation
then
The
the
replaced
A.1.a
housing
View 3.
3,
Exceeds
3,
be
and
turbine
continue
at
next
and
time-in-service.
Crack
1,
specified
the
- remove
as shown
Internal
subsequent
(2)
wall
turbocharger,
repeat
Is
cracks
limits
to
outer
or
1982
above
Crack
All
inner
reinstall
time-in-service
per
inspect
(1)
- on the
housing,
An Internal
and
Found
24,
Limit
- as shown
turbine
with
new
housing
and
housing
as
above.
CAUTION
In
any
case,
housing
as shown
replaced
If
prior
a crack
engine
inspections
View
the
penetrates
3,
next
the
hoses,
the
turbine
outer
wall
housing
and
of
a turbine
gasket
must
be
flight.
penetrated
components,
unable
turbine
a crack
in
to
has
and replace
If
when
the
housing,
clamps
inspect
and mounts
for
the
possible
surrounding
heat
damage
as necessary.
to
determine
housing,
per
the
assume
this
Service
part
it
is
Letter.
number
or
an
affected
revision
letter
part
and
of
the
perform
SERVICE
LETTER
NUMBER 27
PAGE 4 OF 9
SEPTEMBER
B.
Detail
In
Inspection
certain
turbine
per
Views
1 and
housing
from
2.
housing,
a
it
inspect
remove
the
the
aircraft
the
of
the
nozzle
blanket
turbine
(See
for
maintenance
cracks
manifold
that
be
from
the
must
be
turb ine
the
in
seen
as
on
the
turb ine
per
View
installed
shown
1.)
internal
cracks
from
turbocharger
inspect
penetrating
so
Figure
to
turbocharger
can
is
housing
complete
the
V-band
the
be removed.
for
exhaust
coupling
near
may be possible
walls
removal
thermal
must
outer
event,
area
If
it
and
without
any
internal
View
inner
3,
In
disconnected
To
installations,
housing
aircraft.
1982
Instructions
aircraft
the
24,
the
aircraft
as
2,
per
manual.
CAUTION
Before
removing
housing
gaskets
gasket.
(P/N
1.
2.
the
turbocharger,
are
available.
600400-00
Remove
the
Figure
1.)
the
housing
exhaust
sure
spare
Do
not
or
TCM P/N 643932**)
or TC-6-30
turbine
Disconnect
make
attempt
blanket
manifold
(if
by
to
turbine
reuse
installed).
removing
the
(See
the
coupling
V-bands.
3.
Make
"index
aluminum
bearing
reinstalled
4.
5.
in
Remove
the
housing
V-band
Remove
the
inspect
6.
marks"
per
joint
with
While
the
heat
shield
on
housing
the
(P/N
nut
so
the
and
housing
turbine
and
housing
rotational
on
the
will
be
position.
carefully
remove
the
bearing
600391).
turbine
housing
Description
from
A.l.
a rawhide
housing
turbine
same correct
V-band
for
the
mallet
is
condition
off,
the
and
will
2.
Light
help
inspect
and/or
bearing
housing
tapping
separate
the
foreign
turbine
object
and
at
the
them.
wheel
damage.
and
SERVICE
LETTER
NUMBER 27
PAGE 5 OF 9
SEPTEMBER
NOTE:
When
should
be
rotating
the
in
it
replace
a.
If
(or
turbine
heat
not,
wheel
shield
and
a Roto-Master
or
be contacted.
of
the
turbine
600400-00
housing
TCM P/N
inspection,
surfaces
10.
parts
the
adjacent
If
a new P/N
a new turbine
After
off,
1982
or
housing
TC-6-30
gasket
or
TCM P/N
gasket.
600510-04
9.
the
should
all
with
is
be difficult.
remove
643932**
with
representative
Carefully
and
housing
contact
should
TCM service
7.
turbine
24,
appropriately
housing
the
turbine
the
same
the
order
two mating
housing
or
mandated
in
needed,
Roto-Master
P/N
643931**).
clean
on the
Reinstall
is
original
and bearing
a
by
diameters
new
this
gasket
housing.
turbine
housing
inspection
rotational
and
as
onto
the
bearing
must
be
pressed
position.
NOTE:
The
turbine
together
11.
housing
while
the
tapping
on
the
tighten
and seat
Assure
that
bearing
V-band
is
V-band
the
the
rotational
and
with
is
V-band
in
nut
being
reinstalled.
a rawhide
mallet
A light
will
help
to
V-band.
turbine
position
V-band
housing
housing
(use
the
approximate
to
15
to
is
the
marks
same
20
in
the
made
position
exact
earlier),
and
inch/pounds
same
the
tighten
torque.
the
Do
not
1)
and
Do
not
overtighten.
12.
Reinstall
check
the
for
reinstall
turbine
free
if
blanket
rotation
rotation
of
is
(if
used
the
turbine
difficult
or
-
see
Figure
wheel.
scraping
noises
are
heard.
13.
Reinstall
maintenance
and fittings
the
turbocharger
manual.
are
on
Take
clean,
special
undamaged
the
aircraft
care
that
per
all
and unobstructed.
aircraft
oil
lines
SERVICE LETTER
NUMBER 27
PAGE 6 OF 9
SEPTEMBER
If
14.
housing
is
Malfunction
15.
Check
that
the
after
next
flight
V-band
or
because
Report,
torque
of cracks,
Form 8330-2
is
still
complete
and submit
15 to
run-up.
and Notes:
Teledyne
Continental
plans
additional
to
Motors
offer
Fair
(TCM)
a rebuilt
information,
Roto-Master,
7101
Defect
FAA GAD0 office.
Roto-Master
For
or
local
References
**
replaced
contact:
Inc.'
Avenue
North
Hollywood,
ATTN:
Aircraft
CA
Field
91605
Sales
Manager
part
numbers.
exchange
program.
20
24,
1982
the
to
inch/pounds
FAA
the
,
‘.
.’
.*’I’ ,’“‘)
‘k /
PRACTICE
'TURBINE
V-BAND
INLET
CLAMP
TYPICAL TURBOCHARGER INSTALLATION;
EXHAUST SYSTEM ARRANGEMENT WILL VARY
WITH AIRCRAFT
APPLICATION
FIG.
1
.
.
\
sERvi
PAGE
ROTO-MASTER
VIEW 1
INC.
Turbine
Sept
Housing
Exhaust
Inlet
Internal
cE
27
LETTER
8 of 9
24,1982
Cracks.
, I NTERNAL CRACK
Cracks
are
in this
allowable
length
of
area
to a
.75
inch
maximum.
NOTE
Do not
the
line
misrepresent
casting
in this
as a crack.
FIT:
7 TIIRRI
NF HOIISING
VIEWS
parting
area
ROTO-MASTER
sEfwcE
INC.
LETTER
27
PAGE 9 OF 9
24,
SEPT.
VIEW
2
View
of
Turbine
Housing
with
turbo
center
section
removed
Cracks
in
area
to
3/4
3
View
of
Turbine
Housing
with
external
inch.
in
area
to
this
allowable
Cracks
VIEW
1982
this
allowable
2 inches.
cracks
No cracks
any
length
this
area.
of
in
I f cracked,
replace
FIG.
2 (cont.)
TURBINE
HOUSING
VIEWS
immediately.
SERVICE
..-
q
',O 0
(
LETTER 27A
ADDENDUM
February
9, 1983
Page 1 of 1
4'
7101
FAIR
AVENUE
.
NORTH
SERVICE
The following
information
should
be attached
thereto
HOLLYWOOD,
LETTER
Roto-Master
turbochargers
after
600510-04
05s Ductile
Ni-Resist
by AD 82-27-03.
The following
Rajay
serial
turbine
325ElO-1
the older
STC's
Service
and 325ElO-2.
model number
are
affected
SE14WE
LYC 10-320,
SE154SO
LYC O-360
SE32WE
LYC 10-360,
-x,
is affected
has a serial
982-4500
Letter
27A and
The new Rajay
325ElO-1
and is
with a
not affected
by AD 82-27-03:
ENGINES
engine
that
(213)
affected
by AD 82-27-03
has the
The 600510-04
05-S Ductile
AD has the letters
"ON" cast on
STC
The TCM TSiO-360
Rajay turbocharger
.
number 203570 came equipped
housing
and are therefore
3 Ni-Resist
housing
that
is
the outside
of the scroll.
housing
that
terminates
this
scroll.
engine
91605
27A ADDENDUM
is an addendum
to Roto-Master
and made a part thereof.
The model number 325ElO
includes
models
model number 3AT6EElOJ2
is identical
to
also affected
by AD 82-27-03.
The 600510-02
Type
letter
"N" cast on
Ni-Resist
turbine
the outside
of the
CALIFORNIA
by AD 82-27-03
number prior
LXO-320
LIO-360
when it is equipped
to 203570.
with
a
The other
engines
mentioned
in the AD do not come factory
equipped
with a Rajay
model 325ElO turbocharger.
The Rajay
systems
for these engines
do not use a
model 325ElO turbocharger.
These engines
are affected
by AD 82-27-03
only when
model
325ElO or 3AT6EElOJ2
has been installed
in place of the original
turbocharger
by an FAA field
approval
or a non Rajay STC.
The engines
that
fall
into
this
catagory
are as follows:
Lycoming
O-320,
Continental
TO-360,
O-470,
O-540,
10-470,
and TIO-540
10-520,
and TIO-540
The Rajay turbine
inlet
gasket
part number is RJO115.
The Rajay turbine
discharge
gasket
part number is RJ0114.
The turbine
inlet
and discharge
V-band
clamps
are tightened
to 20-30 in. lbs.
The TCM TSIO-360
does not use turbine
inlet
or discharge
gaskets.
JELEX
NO
65-1390
IROJOMASTER
AN
ECHLll
LSA)
COMPANV
l
CABLE
ROTOJURBO
A Suotrarary
ol The
Tcxsrar
Corporalron
SERVICE LETTER
Oate: August 3. 1981
FAA Approved
A. Subject:
8.
C.
All Aajay turbocharger oil supply. drain, fuel and air hose assemblies that were changed or
modified per the installation drawing for the appropriate Rajay Turbocharger installation Kit.
Equipment Affected:
All aircraft fitted with an FAAsPMA approved Rajay Turbocharger(s) Installation covered by
Supplemental Type Certificate as affected.
Distribution:
Aircraft
Aircraft
Aircraft
Aircraft
Trme of Compliance:
At the next 100 hours time-in-service or at the next annual aircraft inspection whichever
occurs first.
a. PIJ~~OSK
/
II
I
,
/
Operators and/or Owners
Modification Bases
Maintenance Bases
Manufacturers
Field service reports have indicated instances of deterioration of the flexible fluid hose (oil.
fuel, and air) installed on aircraft powerplant equipped with F&jay turbocharger(s) systems
although proper inspection and maintenance practice requires replacement of subject hoses
at specified intervals as referenced in the MIL-STU-1523.
Since these hose assemblies are probably installed in connection with the tuhocharger
having a possible degree of temperature higher than the original. therefore maintenance
and inspection at specific intervals must be assured to prevent hose deterioration and
in-flight failure.
I
I
I
No. 28
-x
It has been found that these hose assemblies are not inspected for condition as often
as they should be. and therefore improper function of hoses has occurred due to their
overaging and deterioration. Hose assemblies found damaged must be replaced prior to the
next flight.
E.
Instructions:
Inspect the affected hose assemblies listed in Part F as follows:
1.
Hose Assrmbiirs Without Firesleeves - Every fuel, oil and air hose assembly called out on the Aajay
Installation Drawing for the reference STCs that is not firesleeved must be inspected for age and condition and
must be replaced within three (3) years from the tagged manufactured date with a firesleaved hose assembly
per instruction 2. Hoses damaged, deteriorated and/or in un-airworthy condition, must be replaced prior to the
next flight.
2.
Hose Assemblies With Firesleeves - All fuel. oil and air firesleeved hose assemblies called out on the Rajay
Installation Drawing for the STCs must be replaced according to the date that the hose was manufactured.
This date is shown on the metal tag wrapped around the hose assembly itself.
Reference MIL-STO-1523, paragraph 5.2.3. for assembly date code and Table 1 for age limitations. For
each subject hose assembly replaced, substitute a firrrlerved hose assembly of identical design as shown in
Part F.
3.
The hose assemblies listed in this Service letter are those which were part of the turbocharger installation
modification per respective Supplemental Type Certilicai;?. ‘rowever. all other power plant hose assemblies
whrch are part of the original Aircraft Type Certification should be inspected for airworthy condition and/or
replaced as necessary following thtr Service Letter guideline.
Note 1.
We recommend that powerplant fuel hoses running from the firewall to the fuel pump
and from the fuel pump to the fuel control servo or carburetor also be inspected (and
replaced wrth firesleeved equivalents if necessary).
Note 2.
Since the affected air hoses are not listed in this service letter, contact Rajay
Industries for air hose correct part number replacement information.
Service Letter No. 28
AAJAY INOUSTRIES. INC.
Pqcr AIWC
JCOrd dl
Bcrch
Bonms
H35. J35
K35. M3S.
N35. P35.
35.33
35.A33.
35.933.
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Letter No. 28
Mi4
SAi58SO
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Nolo
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pl4nt
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ta at h4rw
mtmr
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and so. NOIO 2.
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4411,
Service Letter No. 28
RAJAY INDUSTRIES. INC.
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350.4.al60
11114174S016.0
624000.4.0160
624(300.6.0300
111f417.6S.0360
624QOO.60.0360
350.6.0220
624000 4.0260
94F0lwoa4M260
94F0loa0a4ml20
94f01CW04Fo120
IIIf4I7.4S.OI20
624000.4.0120
36El100006LlOO90
36mlOO006MX)90
l56fOOl.60.0090
624100~60.0090
94miomo3mi6a
94mloaoo3oo18o
11IF417.3S.0180
624000.3.5160
94FO6OOM)6FO210
94F0600006M210
l1lF503.60.0210
624023.60.0210
94FOlOOa06F0204
94Faloaoa6fa204
111F417.60.0204
624oM.60.0204
94mNlaaMFa25a
94f0100OO6F0054
94F0100006F0054
1l1f417.60.0054
624OOO.60-0054
94F0100OO6FO330
94f0100006F0330
lllf417.6S.0330
624000.60.0330
624OUI.8-0450
(lllfso1.Es015a~
111F501.60.0450
624040.60.0450
62UlUl.&O2u)
(lllF6o1-8SO24o~
lllF5ol.aLl-a24a
624010.60-0240
624040.6-0360
iilF502.a~.0380
624040.60-0360
111F417-6sa220
624OOO.60.0220
624OOO.CO120
(lllH1?4.S-o120)
111F4174S0120
024000.c0120
111F417-450160
624OOO.4.0160
824000.4.0064
(111H174sux4)
111f4174S.0054
624000.4.0054
94miomo4m25o
lllF417JS.0250
621000.4.0250
lllF417.6S0360
lllF417.60.0360
6240W.80.0330
Piper
onra
PA-24.200
SA2937WE
(ha
Nmm 1. la
phmlwlhm9rmdu~
Ir a# hour)
othrr
pwer
Notr2.
h#bH-6000-8
I 15
Mll-H.6000.6
I 10
94Kl1aam4fwa4
lllF4l?-ISOO64
62UJlJO.4.0064
SA3555Wt
lll4l7.4S.0360
(35040360~
lllf4174S-0360
624000.40360
'111417.15.0220
(3504.022Oj
lllf417.4S0220
624000.4.0220
948xoma3m29a
94rnlu3aa3rJl29o
111F417.3S.0290
624000.3.0290
9410?ooouf0240
94f07awll9m240
111f502.65.0240
624Ou1.6D.0240
94mllnmo6M160
1111417.6s.0180
624000.6D-0160
94Falmao6M120
111f41?-6S.0120
624000.60.0120
WO1OOUOUM54
94f01wao4ma54
11 lf417.4s.0054
[email protected]
368010(300600190
36MKXXl6W190
156F00l.60.0190
624lOOWJ-0190
MIL.H.6000.6
wfh
AE102-14.0140
2650-14.&l
Mll.H.6000.6
VJltll
AE102.14.0090
I 15
x IO
2650.14.:090
bech
Trlrrlllr
95, 995.
6951. 09511
E95
sAi53sa
(See Nlm I. la
planI lud hourlnd
la alI hour.)
o1hr power
SW NoI8 2.
156001.60-0130
#010006001301
156F001.60.0130
624100.60-0130
lllf41?-bS-0360
(624ooo64160)
11IF417.6S.0360
624IBO600360
lllf4l?-lS-0094
([email protected]+OO94)
624aooJ.0094
~i1f4l74s-o25a
1350.M250)
lllf417-1S.0250
624000.4.
?50
11141?4s-0360
111F4171S.0360
6240004.0360
11141?4S-0220
lllF417JS.0220
624000.4.0220
111417.4S.0160
1350.4-01601
1111417-4s.0180
624000-4.0180
350-4.0360
1l1f417.4S.0360
624000.4.0160
ll1F417.4S0094
AIR HOSEREPLACEMENTINFORMATION
Ref: Service Letter No. 28
Affected
Aircraft
September
21,
Inspect And
Or Replace
Old Hose Assy
(Stratoflex
aeech
3onanza
s35, v35,
V35A, V35B,
35-C33A,
E33A, E33C,
F33A, F33C
SA2556WE
93B0100003D0170
93B0100004D0100
93B010000~D0340
93B0100003D0340
193FOOO-3D-0170
193FOOO-LD-0100
193FOOO-40-0340
193FOOO-3D-0340
103698-01
103699-01
103699-02
103698-03
.k!ro
SA683WE,
359-3D-0280
359-3D-0164
359-2D-0240
193FOOO-3D-0280
193FOOO-3D-0164
193FOOO-2D-0240
103698-10
103698-12
103697-12
Piper
Apache
PA-23 &
PA-23-160
-3
iper
Apache
PA-23 &
PA-23-160
SA126OWE
AN6270-3-22
(359-3D-0220)
AN6270-3-19
(359-3D-0190)
193FOOO-3D-0220
103698-07
193FOOO-3D-0190
103698-02
SALl637WE
AN6270-3-15
193FOOO-3D-0150
103698-06
Piper Aztec
PA-23-235 h
?A-23-250
SAj39WE
359-3D-0100
359-20-0340
359-413-0260
359-40-0170
359-20-0190
359-2D-0070
359-3D-0300
193FCOO-3D-0100
193FOOO-2D-0340
193FOOO-4D-0260
193FOOO-4D-0170
193FOOO-2D-0190
193FOOO-2D-0070
193FOOO-3D-0300
103698-C5
103697-11
103699-04
103699-05
103697-06
103697-09
103698-13
Piper Aztez
PA-23-250 &
PA-E23-250
Serb1 X0.
27-2505 &
SA84OWE
AN6270-4-26
AN6270-2-24
AN627C-2-14
AN6270-3-24
AN6270-3-14
AN6270-4-34
AN6270-2--34
193FOOO-40-07.60
193FOOO-2D-0240
193FOOC-2D-0140
193FOOO-3D-0240
193FOOO-3D-0140
193FOOO-4D-0340
193FOOO.?D-0310
103699-04
103697-12
103697-14
103698-14
103698-15
103699-02
103697-11
SA1252WE
AN6270-2-34
AN6270-2-19
AN6270-2-17
193FOOO-2D-0340
193FOOO-2D-0190
193FOOO-2D-0170
103697-11
103697-06
103697-07
1
Commander
5OOA
Subs.
Beech
Bonanza
"75, 535,
5, M35
.35, P35,
35-33
35433,
35-a33,
35-C33, E33,
F33
Install
(If
New Hose Assy
Necessary)
P/N)
(Ralay
1981
Supplemental
Type
Certificate
Mode
*
Date:
P/N)
RAJAY
INC.
range l-.Air
LjOO-300,
G500-30C
Series
II
SA2637WE
359-3D-0120
359-3D-0100
359-2D-0220
359-213-0200
359-2D-0190
359-2D-0170
193FOOO-3D-0120
193FOOO-3D-0100
193FOOO-2D-0220
193FOOO-2D-0200
193FOOO-ZD-0190
193FOOO-ZD-0170
103698-04
103698-05
103697-15
103697-04
103697-06
103697-07
Helio
H295
SA156SO
359-2D-0240
359-2D-0170
193FOOO-2D-0240
193FOOO-2D-0170
103697-12
10369767
Helio
H395
SA125SO
359-2D-0240
359-2D-0170
193FOOO-2D-0240
193FOOO-2D-0170
103697-12
103697-07
SA22&3WE
AN6270-2-40
AN6270-2-30
AN6270-3-19
M6270-2-36
AN6270-2-10
193FOOO-2D-0400
193FOOO-2D-0300
193FOOO-3D-0190
193FOOO-2D-0360
193FOOO-2D-0100
103697-03
103697-02
103698-02
103697-08
103697-01
SA2270WE
AN6270-4-29
359-4D-0260
359-4D-0170
359-4D-0140
193FOOO-4D-0290
193FOOO-4D-0260
193FOOO-4D-0170
193FOOO-4D-0140
103699-03
103699-04
103699-05
103699-06
Lake
LA-4-200
SA2990WE
AN6270-3-34
193FOOO-3D-0340
103698-03
Piper
Lance
PA-32R-300
SA3512!JE
93B0100004DD200
93BOlOOOO4DD260
93B0100004D0100
93B0100004DO140
93B0100002D0190
193FOOO-4D-0220
193FOOO-4D-0260
193FOOO-4D-0100
193FOOO-2D-0140
193FOOO-2D-0190
103699-11
103699-04
103699-01
103699-06
103697-06
Mooney
tl20A, M20B,
M20C, M20D,
H20G
SA1156WE
AN6270-3-15
359-3D-0190
(~~6270-3-19)
193FOOO-3D-0150
193FOOO-3D-0190
103698-06
103698-02
Mooney
M20E, M2OF
SA1411WE
359-3D-0340
(AN6270-3-34)
359-3D-0120
359-3D-0020
359-3D-0160
193FOOO-3D-0340
103698-03
193FOOO-3D-0120
193FOOO-3D-0220
193FOOO-3D-0160
103698-04
103698-07
103698-08
Sritten
Norman
u
INDUSTRIES,
Islander
BN-2, BN-2A,
BN-2A-6,
BN-2A-8,
BN-2A-9
Lake
'A-4, LA-h
J
Page 3 of 4
PAGE 1 OF 7
APRIL 23, 1986
7101 FAIR AVENUE
*
SERVICE
NORTH
HOLLYWOOD,
LETTER
CALIFORNIA
91605
-
(818)
982-4500
27A,
Rajay
NUMBER 29
REFERENCE:
AD 82-27-03,
Roto-Master
Service
Letter
21.
SUBJECT:
Roto-Master
(formerly
Rajay)
turbocharger
turbine
This procedure
also includes
housing
inspection.
one time EGT gauge installation
and/or
redlining,
and then periodic
calibration
checks thereafter.
EQUIPMENT
TIME
Letter
All aircraft
and rotorcraft
equipped
Roto-Master
turbochargers
regardless
turbine
housing,
or application.
AFFECTED:
DISTRIBUTION
Service
TO:
Aircraft
Aircraft
OF COMPLIANCE:
and Engine
Maintenance
with Rajay
of model,
Manufacturers
and/or
Modification
DESCRIPTION:
This service
areas:
A.) To establish
the
existence
of turbine
Bases
letter
addresses
procedure
for a periodic
housing
cracks,
and to
set
the
following
inspection
serviceable
to
detect
limits.
B.) To install
a redlined
EGT gauge if not previously
so equipped,
redline
and/or
placard
and calibrate
the existing
gauge to clearly
the pilot
of the "never
to exceed temperature"
for the particular
application.
To recommend
or
The following
turbocharger
turbine
housing
inspection
and gauge calibration
should
be
incorporated
as part of the regularly
scheduled
aircraft
annual
or 100 hour inspection
as normally
required
for the particular
aircraft
application.
--...
/'
C.)
a
operating
procedures
that
will
extend
turbocharger
three
the
or to
inform
life.
REASON:
Hairline
thermal
stress
relief
cracks
had previously
tongue
area of some older
non-ductile
Ni-Resist
Rajay
SL 27A and AD 82-27-03
require
inspection
of 600510-02
ductile
turbine
housings
to safeguard
against
cracks
housing
wall section
and permit
exhaust
gas to enter
If cracks
were found that
exceeded
the allowable
limits,
be replaced
with the new 600510-04
(TCM P/N 643931*)
turbine
housing
and service
letter
27A would no longer
TELEX
NO. 6.51390
(ROTOMASTER
AN
ECNllfl
ISA).
COMPANY
CABLE:
been discovered
in the
turbine
housings.
(Note:
and TC-60-11
nonthat could
permeate
the
the engine
compartment.)
the housings
were to
D5S Ductile
Ni-Resist
apply.
t?OTOTURBO
ROTO-MASTER
INC.
SERVICE LETTER
PAGE 2 OF 7
APRIL 23, 1986
-.
The foregoing
inferred
that
the new 0% Ductile
Ni-Resist
turbine
housings
This is not the case as all
aircraft
would function
in a crack free state.
turbocharger
turbine
housings
are subject
to hairline
thermal
stress
relief
This is particularly
true of the Roto-Master
and
cracks
of varying
degrees.
Rajay turbine
housings
that
have been exposed
to exhaust
gas temperatures
(EGT) in excess of 1650 degrees
F.
Subsequent
to the promulgation
of SL 27A
and AD 82-27-03
there
have been. reports
of cracked
housings
on less severe
applications
that were not covered
by the AD, as well as some new 600510-04
(TCM P/N 643931")
05s Ductile
Ni-Resist
replacement
turbine
housings.
All of
the newly reported
cracks
were internal
and as they do not propagate
rapidly,
the housings
could
still
be considered
serviceable.
The cracks
therefore,
operating
cases.
A.)
were attributable
to high exhaust
gas temperatures
(EGT) and,
we must conclude
that
a lack of proper
instrumentation
and/or
procedures
were major
contributing
factors
in a majority
of these
TURBINE
HOUSING
INSPECTION
AND ACCEPTABLE
SERVICE
LIMITS:
A dye penetrant
inspection
of the turbine
housing
to determine
the existence
be included
as
of cracks
as indicated
in figure
2, Views 1, 2 and 3 should
part of the aircraft
annual
or 100 hour inspection
as normally
required
for
the aircraft
application.
-y
Detailed
Inspection
and Assembly
Instructions:
NOTE:
Before
removing
the
gaskets
are available.
for parts
list)
turbocharger,
Do not
make
attempt
the
turbocharger(s)
per
2.
Remove
the
turbine
blanket
3.
Disconnect
4.
Scribe
"index
marks"
on the turbine
housing
and on the aluminum
bearing
housing
so the turbine
housing
can be reinstalled
in the same rotational
position.
If a new housins
is to be installed.
transfer
the mark on the
old housing
to the same location
on the new housing.
5.
Remove
bearing
6.
Remove the turbine
housing
joint
with a rawhide
mallet
inspect
per figure
2.
exhaust
(if
pipes
the V-band nut and carefully
housing
(V-band
P/N 600391).
from
will
Maintenance
housing
Fig.
1
Remove
any remaining
Aircraft
necessary
turbine
the gaskets.
(See
1.
housing
the
sure the
to reuse
manual.
installed).
by removing
remove
the
large
the bearing
housing.
help separate
them.
the
coupling
V-band
V-bands.
from
Light
tapping
Dye penetrant
the
at
the
29
ROTO-MASTER
INC.
SERVICE LETTER
PAGE 3 OF 7
APRIL 23, 1986
CAUTION!
IF CRACKS ARE FOUND THAT PENETRATE THE OUTER WALL OF THE HOUSING OR
EXCEED THE LIMITS
SHOWN IN FIGURE 2, REPLACE THE HOUSING WITH THE
HOUSING SPECIFIED
IN FIGURE 1.
CRACKED TURBINE HOUSINGS CANNOT BE
REPAIRED BY WELDING OR ANY OTHER PROCESS.
DO NOT REPLACE A 600510-04
(TCM 643931*)
"DN" TYPE TURBINE HOUSING WITH THE OLD STYLE 600510-02
(TCM 643930*)
"N" TYPE TURBINE HOUSING. THE OLD 600510-02
(TCM 643930")
"N" TYPE TURBINE HOUSINGS MUST BE INSPECTED PER AD 82-27-03
AND SERVICE
LETTER 27.
IF A CRACK HAS PENETRATED THE HOUSING INSPECT THE
SURROUNDING ENGINE COMPONENTS, HOSES, CLAMPS, AND MOUNTS FOR POSSIBLE
HEAT DAMAGE.
REPAIR OR REPLACE DAMAGED PARTS AS NECESSARY.
7.
While
the
and spring
housing
is off,
visually
inspect
the turbine
wheel,
ring
for condition
and/or
foreign
object
damage.
heat
shield,
NOTE:
When the turbine
shield
into the
the heat shield
off,
the spring
--h
i
li
housing
is off,
the spring
ring
should
push the heat
turbine
wheel,
and rotating
it should
be difficult.
If
is loose,
or if pieces
of the spring
ring
have broken
ring
must be replaced.
8.
Carefully
remove all parts
of
a new P/N 600400-00
or TC-6-30
9.
After
inspection,
surfaces
on the
clean
turbine
the turbine
or TCM P/N
housing
643932*
and inspect
the two mating
housing
and bearing
housing.
gasket
gasket.
diameters
and replace
with
and gasket
CAUTION!
INSPECT THE PILOT DIAMETER ON THE ALUMINUM BEARING HOUSING FOR EROSION
DUE TO OVERTEMPERATURE OR CHEMICAL ATTACK.
THE PILOT DIAMETER SHOULDER
MUST BE CAPABLE OF RADIALLY LOCATING THE TURBINE HOUSING TO WITHIN
.Oll
TIR.
A BEARING HOUSING THAT CANNOT POSITIVELY
LOCATE THE TURBINE
HOUSING WILL ALLOW THE TURBINE WHEEL TO RUB ON THE HOUSING AND MUST BE
REPLACED.
10.
Reinstall
the
this
inspection
position.
same or a new turbine
housing
onto the bearing
housing
in
as appropriately
the original
mandated
rotational
by
NOTE:
The turbine
housing
the V-band is being
rawhide
mallet
will
11.
Assure that the turbine
the marks made earlier),
and tighten
the V-band
overtighten.
and bearing
housing
must be pressed
together
reinstalled.
A light
tapping
on the V-band
help to tighten
and seat the V-band.
housing
is in the same rotational
the V-band is in the approximate
nut to 15 to 20 inch/pounds
torque.
while
with a
position
(use
same position
Do not
29
ROTO-MASTER
1
r-l...,
12.
INC.
Reinstall
turbine
noises
SERVICE LETTER
PAGE 4 OF 7
APRIL 23, 1986
the turbine
blanket
Do not reinstall
wheel.
are heard.
(if
if
used) and check for free rotation
of
rotation
is difficult
or scraping
29
the
13.
Reinstall
the turbocharger
on the aircraft
per aircraft
maintenance
manual.
Take special
care that
all
oil
lines
and fittinqs
are clean,
Insure
that
check valves
are correctly
undamaged
and unobstructed.
Rajay aftermarket
turbocharger
installed
for applications
requiring
them.
kits
use a turbine
inlet
and outlet
gasket.
(P/N RJ0115 and RJ0114
respectively)
The TCM* TS10360 does not use turbine
inlet
or discharge
gaskets.
Tighten
the inlet
and outlet
V-band clamps
to 20-30 in-lbs.
14.
Perform
a ground
runup to check for air,
oil
or exhaust
leaks
while
also
listening
for scraping
noises
emanating
from the turbo.
Many
installations
are only designed
to compensate
for altitude
and therefore
Recheck
that
the torque
for
will
not make boost during
a ground
runup.
all
V-bands
is still
correct
after
next flight
or long run-up.
15.
If a turbine
housing
is replaced
because
of cracks
that
have exceeded
the
serviceable
limits,
complete
an FAA Malfunction
or Defect
Report,
Form
8330-Z
and submit
to the local
FAA GAD0 office.
Please
also indicate
when
or if the EGT gauge had been redlined
and calibrated
per steps B. and C.
of this
service
letter.
B.)
EXHAUST
TEMPERATURE
GAUGE INSTALLATION
AND REDLINING.
Turbine
housing
life
can be extended
considerably
by taking
care not to exceed
the maximum rated
turbine
inlet
temperature.
In many installations
the pilot
has no way of knowing
if the maximum EGT is being
exceeded
because
there
is no
redline
or even numbers on the gauge.
In some cases an EGT gauge was never
installed.
Any turbocharged
engine
should
have an EGT gauge installed
if not
so equipped.
Existing
installations
should
have the gauge calibration
checked.
The gauge should
be clearly
redlined
at the maximum
allowable
temperature.
Gauges with actual
temperature
numbers may be placarded
with the
EGT limits
instead
of being redlined.
Engines
originally
Type Certificated
(T.C.)
with a turbocharger
should
have
the gauge redlined
per the engine
and/or
aircraft
manufacturers'
EGT
specification
as applicable.
Never exceed 1650 degrees
F for Rajay
or
Roto-Master
turbochargers
in any application.
1600 degrees
F or less is
recommended
for longer
life
on these applications.
If the turbocharger
must be used.
If
was installed
the STC does
per an STC, the
not specify
a limit,
limits
specified
never exceed
by the STC
1600 deg. F.
CAUTION!
OPERATING WITHIN SPECIFIED
EGT LIMITATIONS
MAY RESULT IN HIGHER FUEL
CONSUMPTION RATES THAN MAY HAVE BEEN PREVIOUSLY ATTAINABLE
WITH
EXCESSIVE LEANING.
FUEL FLOW RATES SHOULD BE CONFIRMED BEFORE RELYING
ON PRIOR OR PUBLISHED
FUEL RANGE CALCULATIONS.
ROTO-MASTER
INC.
SERVICE LETTER
PAGE 5 OF 7
APRIL 23, 1986
29
--_
C.)
RECOMMENDED OPERATING
PROCEDURES.
like
that
of most engine
parts,
is adversely
affected
by
Turbine
housing
life,
extremes
and/or
sudden changes
in temperature.
A very severe thermal
shock
occurs
during
an abru t change from a high EGT lean cruise
setting,
to a low
The turbine
housing
is suddenly
chilled
by
power setting
prior'ddescent.
the blast
of cold outside
air,
especially
at altitude
or in cold weather.
Making
a gentle
transition
from lean cruise
to a lower temperature
setting
whenever
possible
will
extend
the life
of the turbine
housing.
Some turbocharger
manufacturers
require
an extended
idling
period
prior
to
shutdown
to prevent
the cast iron bearing
housing
from coking.
Rajay
and
Roto-Master
Aircraft
turbochargers
have aluminum
bearing
housings
and do not
Extended
idling
prior
to shutdown
is not
have an oil
coking
problem.
required,
or harmful
to a Rajay or Roto-Master
turbocharger.
Figure
1.
PART NUMBER INTERCHANGE
Old
/I.%,
3
./'
P/N
600509-01
600509-02
600510-01
600510-02
600511-01
600511-02
600511-03
600511-04
TC-6-30
TC-59-11
TC-60-11
TC-82-11-l
TC-82-11-2
TC-248-11-l
TC-248-11-2
RJ0114
RJ0115
*
Teledyne
Description
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Turbine
Continental
Replace
Housing
FlO
Housing
F80
Housing
E80
Housing
El0
Housing
FlO-LH
Housing
FlO-RH
Housing
F80-LH
Housing
F80-RH
housing
gasket
Housing
FlO
Housing
El0
Housing
FlO-LH
Housing
FlO-RH
Housing
F80-LH
Housing
F80-RH
inlet
gasket
outlet
gasket
Motors
(TCM)
600509-03
600509-04
600510-03
600510-04
600511-05
600511-06
600511-07
600511-08
600400-00
600509-03
600510-04
600511-05
600511-06
600511-07
600511-08
RJ0114
RJ0115
part
With
P/N
TCM P/N*
643931
643932
t--
t"
643931
Not
Not
Used
Used
numbers.
CAUTION!
ANY TC 60-11 OR 600510-02
(TCM 643930*)
OLD STYLE NON DUCTILE NI-RESIST
TURBINE HOUSINGS THAT ARE STILL
IN SERVICE MUST BE INSPECTED PER AD
THESE HOUSINGS ARE TREATED SEPARATELY IN SERVICE LETTER 27A.
82-27-03.
THIS SERVICE LETTER DOES NOT SUPERSEDE AD 82-27-03
OR SL 27A.
THIS
SERVICE LETTER ONLY APPLIFS-IN
THESE APPLICATIONS
AFTER THE HOUSING HAS
BEEN REPALCED WITH A NEW DUCTILE D5S NI-RESIST
600510-04
HOUSING.
For
further
information
contact:
Roto-Master
Inc.
7101 Fair Ave.
North
Hollywood,
(818) 982-4500
CA. 91605
ROTO-MASTER
INC.
SERVICE
LETTER
29
PAGE6 OF7
APRIL
VIEW 1 Turbine
Housing
Exhaust
Inlet
Internal
23,
1986
Cracks
INTERNAL
Cracks
are
CRACK
in
this
allowable
length
of
area
to
.75
inch
maximum.
NOTE
Do not
the
line
misrepresent
casting
in
this
as a crack.
FIG 2 TURBINE
HOUSING
VIEWS
parting
area
a
RO TO-MASTER
INC.
SERVICE
LETTER
29
PAGE 7 OF 7
APRIL
VIEW 2
View of
Turbine
Housing
with
turbo
center
section
1986
23,
removed
Cracks
area
to
in
allowable
.75
Cracks
area
to
VIEW 3
View
of
Turbine
housing
with
exterpal
inch.
in
this
allowable
2 inches.
cracks
No cracks
i
.,
length
this
area.
TURBINE HOUSING VIEW
in
cracked,
replace
,,..-_-
of
any
If
FIG. 2 (CON-L)
this
immediately.

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