Service Information and ADs - the Commander Owners Group

Transcription

I:
SERVICE
DATE:
SL-1
LETTER NO.
EFFECTIVITY:
Rockwell
SUBJECT:
Rudder
Commander
112
S/N
Apri 1
3
1973
30,
through
79
Assembly
RECOMMENDED
than the next 100 hour inspection or
90 days, whichever occurs first, unless rudder
is cracked then compliance will be required
No
COMPLIANCE:
later
prior
to
next
flight.
APPROVAL:
FAA-DER
Approved
PURPOSE:
Service
skin on
investigation has revealed that the
the aft portion of the rudder assembly
may need to be stiffened in order
cracks from forming on the skin.
As
a
to
prevent
solution,the following instructions
are
recommended:
LNSTRUCTLONS:
i.
If cracks are found, replace the
Inspect exterior of rudder.
witii
rudder
new
a
assembly (P/N 44006-1).
assembly
rudder
"NOTE
all of the rudder assembli~s ordered from the factory
after March 29, 1973 will have already been modified.
rudder.
2.
Remove
3.
Drill
n.
EZark rivet center
the
rivets.
Insert
channel
of
5.
top and bottom rivet holes
and
position
through rivet
(Page
1
of
3)
line
on
channel
through lightening
channel
hole.
so
that
Drill
on
sides of
then mark
hole
center
and
both
on
line
cleco,
locating line
the
for
rudder.
for
one
leading edge
of
rudder
rivet
is
visible
one
end
(Page
2
of
3)
r-´•
6.
Position channel
hole.
Drill and
so
rivet
that
line
is
centered
7.
Drill
8.
Paint rivet heads with minimum amount of
9.
Check
10.
remaining
holes
balance of
in the remaining
cleco.
through
rudder
and
rudder
rebalance
skin and channel,
touch up
then rivet.
paint.
if necessary.
Replace rudder adding AN960-416L washer under head of lower hinge
bolt.
11.
Make
the
following entry in the Airframe Logbook:
P/N 44315-3 installed in rudder in
compliance with Rockwell Commander 112, Service
Channel,
Letter
i.
No.
or
Rudder
Assembly, P/N 44006-1, replaced in
compliance with Rockwell Commander 112, Service
12,
Mail
Letter No.
i.
compliance
card and
request
(Form CSA-2)
to
accompanying warranty labor adjustment
Albany Aircraft Division.
the
"NOTE"
The channel (P/N 44315-3) and~all necessary rivets
have been enclosed with this Service Letter.
If a
is needed, it can be ordered, free of
new rudder
charge, directly from:
SPARES
SALES
ROCKWEILL
DEPARTMENT
INTERNATIONAL
ALBANY AIRCRAFT
P.
O,
Box
DIVISION
1748
Albany, Georgia
31702
912/435-6161
The Albany Aircraft Division will warranty labor for
with this Service Letter up to a maximum of one hour
replacement
or
2
hours
for
compliance
for
installation of the channel
rudder
(P/N 44315-3).
1. 7s
-1
/n/s7s3L~
Fc~
ii’i
ig f_
/e~
O(RLC~
-I-´•´•4----f~-
.S E c T
A
A’
C
HER~ Y
Clt 2~2´•C9-- q-
/O
i62
f~l YET
W~-Q
oR
REF
KL- pc~4
RVII oa -4-
HucK
1offoL
YC’IPIC
XI~ETS
SERVICE
LETTER
SUBJECT:
NO.
SL-2
Inspection
~FFECTIVITY:
of
Spar Attach Points
Rockwcll
Number
Commander
63.
COF1PLIAI\JCE:
Within
next
APPROVAL:
FAA-DER
PURPOSE:
Service
10
112
1973
Horizontal
on
Serial Number
3
Stabilizer.
through Serial
flight.
of
hours
25,
April
Date:
approved
investigation has disclosed that bolts of the
length may have been used in attaching the
of
the
horizontal stabtilizcr to the lower fin on
spar
the vertical stabilizer.
This may result in_possible
of
the
bolt
holes.
elongation
incorrect
INSTRUCTIONS:
i.
attach bolts on the horizontal
stabilizer by sighting upwards along each side of the
vertical stabilizer.
Each bolt should have at least
one
but
the
nut.
not
checked
seal
2.
8 aft
Inspect the
for
cement
Remove
the
remove
the
3
than
more
In
addition,
possible
for
threads
of
each
protruding through
the
should
nuts
by inspecting
movement
be
the
torque
cracks.
fiberglass dorsal assembly fairing and
fourl/$" bolts that hold the spar on the
horizontal stabilizer to the lower fin´•
of the vertical
stabilizer.
When removing these bolts, count the
number of complete turns required to remove each bolt.
If more than 12 complete turns are required, this
If 12 or fewer
indicates that the bolts ar~’ too long.
turns
proceed
3.
If
requiredl-"install
are
ing-each
to
to
steps
8
excessively long
Step 2;
or
stabilizer
original bolts, torqu-
the
inch-lbs. plus shank
fiberglass dorsal assembly
50-70
if
and
friction.
fairing then
9.
bolts
are
looseness
any
spar attachment
noted
is
in
noted
Step 1 and/ox
in
the
horizontal
points, proceed with
Steps 4 through 9.
4.
(Page
1
of
3)
rudder, elevator and upper fin
vertical stabilizer.
Remove
the
on
the
5.
the
Remove
8
and
forward
2
attach bolts.
stabilizer and
horizontal
the
re-install
the
in
holes
the
the
vertical fin
elongation, if none
lower
assembly for signs of bolthole
appears
stabilizer
horizontal
aft
~Visually inspect
stabilizer (per
in any of the
horizontal
If elongation
Step 6).
boltholesl repair per ESK 112-334 and proceed
Step 6.
has
6.
The
RE-AS SEMBLY
(8)
rear
occurred
attach bolts
(AN960-416
used).
should
washers
a minimum of
(2)
AN960-516 if 5/16 bolts
first, with
installed
bolt
or
to
have
be
per
been
Since it will be necessary to torque the bolt head,
increase the maximum torque value by an amount equal to
The shank friction shall be
the shank friction.
The torque valve for
measured with a torque wrench.
1/4 inch bolts is 50-70 inch-lbs., for 5/16 inch bolts
is
After
bolts
the
inspect
the
more
have
bolts
than
not more
If
inch-lbs.
100-140
than
to
three
three
been properly torqued, visually
determine that at least one and
threads extend through the nut.
threads
show,
add
an
--4,
additional
washer.
forward´•attach bolts require a minimum of (2)
washers tone AN960-416L and one AN960-416 washer)
The
and
7.
Re-install
See
Note:
8.
be
shall
Make
the
torqued
per
the
above
procedure.
items removed in the previous steps.
Maintenance Manual for rigging procedures.
following entry in
Rockwell
Aircraft
the
airframe
Service
Letter
SL-2 complied with.
Oversized
bolts used.
Number
size
9.
(Page
2
of
3)
Complete
not
used.
and
mail
logbook:
Over-
bolts
(Indicate Which)
the
enclosed
compliance
card.
-f´•-~Uii;l-
~111-_
t~XISTINC PLATE NI7TS
TC
PARTS
~R /’r’n^S1305-3 BOLTS
.’,OLL
s/(;
;X
C~
cR ~N46S-5/6i
W~SNZRS
/N
LIN~
WI~H
ESK
.3125/.3/r0
112-334
PARTS
MAT/NG´•
INSTAL~ NAS680A5
WITH Bi~lND RIY~+S (2
EV~AR SIDE
p,vD
PLATL’ NUf´•S
Ir~LUSI/
Req’o)
Isrnce
ii7 /oa-/-p´•o
irS
RIE~M
/N-C~ss
PLPCES
2
PI~ACSS
1
~L/
i
R~AM
TO
WITH
MATING
.3125~j120 IN LINE
PARTS
INSTALL
1.
MS 203Lfi~:5r?4 NU7TOAQC/r’ TO /OO-~O/N-LSs
~e P~ACLS
i
;3I
OR
NASIIOS-7 OR
AN960-5/6L WilSH~ER
i
I/
i/
ek33
I
\I
P\
BRIGI
RECEIVED BY
gs,
aTP
~I
L,
.h
sej
SERVTCE
r\iO. ST,-112-3
July
RI;ITEC~TIVTTTY:
Rockwell C~ommnlxlcr 112
SIrl3JE~T:
Engine exhnust systclll
S/N
rc´•tn
197:~
~:1
inill~ nllt tol^rluc.
n Eco M MENI)E n
COMI’LIANCE:
At next 100 hour
APPROVAL:
FAA
PI~IRPOSE:
Recent informati.on supplied hy T,J’comi.nF
tlznt- tile
current 100-140 in, -Ib, torclrle for Ehe
crth:i~lat
enpine
syt;tcln
should be incrc:ased.
inspection.
TNSTR UCTTO NS
1,
With upper and lower
engine
2,
to
Make tile
cowlina
removeil, t.c,rc-(lle
\~r.lc::
160-180 in. -Ib.
~ollowing entry
in en~-irro
lo!s;book:
Sc~\lice I,ctter SI,´•1112-3
with this date
.3.
M n.il
co m
PZ ia
bang
nr:l:achinF exl~luse pil~cJs
ircl´•a Er 1 )´•i v is ion.
tc~
complied
R1
SERVICE LETTER NO. SL-112-4
DATE:
December
1973
17,
SERIAL NO’S 3 THRU 111 AND 113 THRU 125.
112,
EFFECTIVITY:
MODEL
SUBJECT:
GROSS WEIGHT INCREASE.
RECOMMENDED
COMPLIANCE:
AT OWNER’S DISCRETION.
APPROVAL:
FAA
PURPOSE:
To raise maximum allowable takeoff gross
Approved.
weight
from 2550 pounds to 2650 pounds.
INSTRUCTIONS:
a.
Place aircraft
b.
Remove and discard existing main
Manual.
c.
Install 600
d.
Remove aircraft from
e.
If maximum indication of
flap position indicator is 35 degrees,
f.
If maximum indication of
flap position
g,
Remove
x
on
6,
6
jacks.
ply
tires
on
landing
left and
gear tires
right
main
as
outlined in applicable airplane Maintenance
landing gears using existing tubes.
jacks.
existing airspeed
indicator is 40
degrees,
it does not need to be reworked.
from aircraft,
remove
indicator from aircraft.
Send existing airspeed indicator, 6513197-002 dial
(indicated airspeed)
or
existing flap position indicator (i~necessary) with 48013-RE3 decal
approved FAA instrument repair station to be reworked as follows:
and
i.
On
Edo-Aire indicator, remove existing dial and
65B198-002 dial (indicated airspeed).
On
Marine indicator, tieinark existing dial
No. 65B197-002 dial (indicated airs~eed).
install
65B198-002 dial
(true airspeed)
and SW-407370-3 bezel to
65B19La;002
dial
(indicated
an
airspeed)
or
2,
to
with
agree
markings
on
enclosed
part
NOTE
The
enclosed dial will not fit Aero
therefore it is necessary to~iemark
i3;
and
Recalibrate
indicator
4.
5.
airspeed
recertify
neidentify
Edo-Aire indicated
Marine
existing
indicator;
Aero
Maiine
indicator.
indicator.
to
J41B-2.
airspeedlindicator
to EA-51752-02-ACM and true
airspeed
indicator
to EA-51752-02T-ACM,
6.
On
flap
position indicator,
by aligning
as
0
remove
existing
degree reference mark
on
bezel and install 48013-RE3 decal
decal with 0
degree
mark
on
existing
over
existing
dial
dial and trim decal
necessary.
CAUTION
Use extreme caution
i.
j.
7.
Install SW-407370-3 bezel
8.
Reidentify
reworked
on
Remove
seats, carpet
not to
flap position
flap position indicator
Reinstall reworked airspeed indicator and
beneath floor between
so as
and floor
fuselage
panels
Sta.
damage
indicator hand.
indicator.
to 304AA-35.
flap position
indicator
as necessary to gain
127. 25 and Sta. 144. 26.
(if removed)
access
to
flap
in aircraft.
actuator switches located
Page
1 of 3
I<.
i.
Set
screw on flap switch holder
2) degree position (see Figure i.
Loosen set
35
ill.
Itecheck
flaps
screw on
n.
2) degrees using protractor.
to 35
flaps
flap
Recheck flaps
tightened.
with
protractor
to
and relocate down micro switch
assure
correct switch and
flap
motor
so
that
motor cuts off at the
flap
operation
and then
tighten
set
switch holder.
in 35
degree position
u.
Reinstall items removed in step j.
p.
Remove
existing airspeed
limitation
to
assure
placard
that down micro switch did not
and install 49071-11
move
when set
screw was
placard.
WOtB
Revision
"i~",
dated November
Flight Manual must be inserted
in compliance with this Service
SUPPLY DATA:
The following parts required to comply
by Spare Sales Department, Commander Aircraft Division,
5, 1973, of Model 112
in Flight Manual to be
Letter.
with this Service Letter
Rockwell
QTY
PART NO.
DESCRIPTION
1
ea.
1
ea.
48013-RE3
49071-11
Decal
Placard
2
ea.
600
1
ea.
65B197-002
1 ea.
ELECTRICAL LOAD:
Not
AIRCRAFT RECORDS:
6
Tire,
Dial
or
6
65B198-002
Dial
Bezel
furnished,
at
no
Oklahoma
charge,
73008.
CODE NO.
0031838
Ply Type
LTI
(indicated airspeed)
(true airspeed)
SW- 407 370- 3
6848200
0082152
0082153
Applicable.
WEIGHT AND BALANCE DATA:
Service Letter No.
x
are
International, Bethany,
Make
SL-112-4,
Not
Applicable;-
appropriate entry
dated December
in aircraft
17, 1973,
permanent maintenance records as follows:
Weight Increase", accomplished
entitled "Gross
(date)
Fill in completely, enclosed self-addressed compliance card and mail. This Compliance Card must be
received at Commander Aircraft Division, Bethany, Oklahoma no later than March 17, 1974 for labor warranty
consideration. A maximum of ten (10) hours will be allowed for labor provided that properly executed Warranty
Labor Request is sent in with Compliance Card.
T’~cre 2 of 3
MOTOR OMITTED
FOR CLARITY
EXISTING DOWN
MICRO SWITCH
O
-I
EXISTING
400 FLAP
LOCATION (REF)
STRIKER
2
EXISTING
00 FLAP
EXISTING
250 FLAP
350 FLAP
LOCATION
(REF)
LOCATION
(REF)
(REF)
LOCATION
Figure 1.
PRF~F
3 Or 3
DATE:
EFFECTIVITY:
MODEL
SUBJECT:
FLX~ORBOARD VIBRATION
112,
January 15, 1974
SERIAL NO’S 3 THRU 125.
RECOMMENDED
COMPLIANCE:
APPROVAL:
FAA
PURPOSE:
To reduce vibration
Approved
on
right forward floorbdard.
INSTRUCTIONS:
a.
Remove
existing scuff plate
b.
Remove
existing carpet
c.
Remove any
d.
from
forward cabin
right forward
from
remaining glue
right
carpet.
cabin floorboard.
from floorboard.
Locate and install 43645-2 stiffener
(see Figure 1.
on
right forward
cabin floorboard
Adhesive
using if1300- 3M Scotch Grip
e.
Remove foam rubber pad from carpet in
f.
Reinstall existing right forward cabin carpet using 3642A Tuf-Grip Adhesive.
g.
Reinstall
existing
scuff
plate
on
area
right forward
shown in
cabin
Figure 1.
carpet.
SUPPLY DATA:
The following parts required to comply with this Service Letter are furnished, at no charge,
by Spare Sales Department, Commander Aircraft Division, Rockwell International, Bethany, Oklahoma 73008..
QTY
PART NO.
DESCRIPTION
1
43645-2
Stiffener
ea.
ELECTRICAL IX)AD:
Not
Applicable.
Not
Applicable.
AIRCRAFT RECORDS:
Make appropriate entry in aircraft permanent maintenance records as follows:
Service Letter No. SL-112-5, dated January 15, 1974, entitled "Floorboard
Vibration", accomplished
A maximum of two
(2)
hours will be allowed for labor provided that
a
properly
executed
Warranty
(date)
Labor Re-
quest is sent in with Compliance Card.
PaRe 1 of
2
EXISTING SCUFF PLATE
(REF)
RELNSTALL AFTER MAKING
STIFFENER INSTALLATION
4.
B.
i. 50r~
00RBL
350r,,/
STA
~62.
50
STA
84.16
43645-2 STIFFENER
INSTALL ON FLOOR
AFTER REMOVING CARPET
TZIGHT
FORWARD CABIN CARPET
(REF)
43645-2 STIFFENER
(REF)
8. 0"
4. 0"
REMOVE FOAM RUBBER PAD FROM
CARPET AS INDICATED BY SHADED AREA
Figure
i.
Rockwell International
General Aviation Divi*on
5001 North Rockwell Avenue
Bathany. Oklahoma 73008
SERVICE LETTER NO. SL-112-6A
(’I’his Service Letter replaces Service Letter No.
DATE:
SL-112-6,
dated
January 15, 1974,
August 9,
entirety.)
in its
1974
SERIAL NO’S 3 THRU 111 AND 113 THRU 125.
112,
EFFECTIVITY:
Model
SUBJECT:
IMPROVED CABIN VENTILATION.
RECOMMENDED
AT OWNER’S DISCRETION. (THIS SERVICE LETTER NO. SL-112-6A IS BEING
ISSUED ONLY TO CORRECT THE SUPPLY DATA AND INSTALLATION INSTRUCTIONS
COMPLIANCE:
OF SERVICE LETTER NO. SL-112-6. IF BASIC SERVICE LETTER NO. SL-112-6
KAS BEEN COMPLIED WITH, DISREGARD THIS SERVICE LETTER.)
APPROVAL:
FAA DER
PURPOSE:
To
Approved.
provide
a means
to increase
air flow
cooling
through
overhead vents.
FOR AIRCRAFT W~HOUT RADIO ANTENNA INSTALLED IN DORSAL ASSEMBLY.
PART I
INSTRUCTIONS
vertical fin
a.
Remove
b.
Remove and discard
c.
Locate, drill and install 44217-3 leading edge skin
d.
Locate 43650-1 dorsal
e.
Using
f.
Install MS21047-L08
g.
Install 43650-1 dorsal assembly
U-nuts (see Figure 1.).
h.
Reinstall
existing
tip.
upper vertical fin
existing
assembly
on
leading edge
PART II
existing
nutplate (4 places)
vertical fin
assembly.
existing leading edge clip
on
aircraft(see Figure 1.).
aircraft and trim to fit.
a hole finder, drill twenty-six (26) 0. 252
match holes in aircraft skin (see Figure 1.).
on
and
skin and dorsal
on
0.
dorsal
aircraft
002)
inch diameter holes in dorsal
assembly
to
assembly (see Figure 1.).
using existing
screws, washers and four
(4)
C8104-832-4
tip.
FOR AIRCRAFT WITH RADIO ANTENNA INSTALLED IN DORSAL ASSEMBLY.
INSTRUCTIONS:
vertical fin
a.
Remove
b.
Remove and discard
c.
Disconnect radio antenna leads from dorsal
d.
Locate and drill a O. 128-inch diameter hole in 44217-3
stiffener (see Figure 1.).
e.
Locate,
f.
Locate 43650-1 dorsal
g.
Using
h.
Install MS21047-L08
existing
existing
tip.
upper vertical fin
drill and install 44217-3
assembly
assembly
leading edge
on
leading edge
and
skin and
skin.
remove
and discard
leading edge
existing
dorsal
assembly.
skin and drill and install 48732-1
existing leading edge clip
on
aircraft(see Figurel.).
aircraft and trim to fit.
a hole finder, drill twenty-six (26) 0. 252
match holes in aircraft skin (see Figure 1.).
nutplate (4 places)
on
(f
dorsal
0.
002)
inch diameter holes in dorsal
assembly
to
Page
1 of 5
i.
Remove interior overhead
j.
Remove and discard
k.
paneling
necessary to
gain
access to
3
radio antenna cable.
existing overhead radio antenna cable.
Install 43650-1 dorsal assembly
U-nuts
as
on
aircraft using existing screws, washers and four
(4)
C8104-832-4
(see Figure 1.).
i.
Reinstall existing vertical fin tip.
m.
Locate and drill two (2) 0. 187-inch diameter holes and
skin at Sta. 130. 00 (see Figure 2.).
n.
Install 071-1007-00 radio antenna kit
o.
Install 155-2010-00 antenna cable
p.
Reinstall interior overhead
one
(1)
0. 437-inch diameter hole in top of fuselage
(see Figure 2.).
(see Figure 3.).
paneling.
Letter are furnished at no charge,
following parts required to comply with this Service
Bethany, Oklahoma 79008.
Rockwell
International,
Aviation
General
Division,
by Spares Sales Department,
SUPPLY DATA:
The
PART I
PART II
QTY
QTY
PART NO.
DESCRIPTION
1
ea.
1
ea.
43650-1
Dorsal
1
ea.
1
ea.
44217-3
Leading Edge
48732-1
071-1007-00
155-2010-00
Stiffener
Radio Antenna Kit
4
4
ea.
ea.
ELECTRICAL LOAD:
1
ea.
1
ea.
1
ea.
4
ea.
4
ea.
Assy
Skin
Radio Antenna Cable
U-Nut
C8104-832-4
MS21047-L08
CODE NO.
Nutplate
0060203
0082245
0059485
2719248
NotApplicable.
Not
Applicable.
records as follows:
Make appropriate entry in aircraft permanent maintenance
AIRCRAFT RECORDS:
Part I accomCabin
Ventilation",
entitled
"Improved
dated
1974,
August 9,
Service Letter No. SL-112-6A,
plished~;
Fill in
PartIIaccomplished
mail. General Aviation Division will allow
the enclosed self-addressed compliance card and
I and a maximum of eight (8) hours
of.Part
for
labor
performance
maximum of seven (7) hours
issued without receipt of both Comof Part II of this Service Letter. No credit will be
completely
credit for a
labor for performance
Labor
pliance Card and properly executed Warranty
Page 2
(date)
of 5
Request
Form.
MS20426AD4 RIVET
0. 250" I)IA. HOLE
USE EXISTING
U-NUTS
(4 PLS)
4´•
44217-3 LEADING
(REF)
EDGE SKIN
EXISTING LEADING
,EDGE
RIB
(REF)
MS20426AD4 RIVET
\O
js
PLS)
I
VERTICAL FIN
TIP
C8104-832-4
U-NUT
(REF)
(4 PLS)
REINSTALL EXISTING LEADING
EDGE CLIP
O/
NAS1398D4 BLIND
RIVET
(REF)
STARTING AT TOP
INSTALL NAS1398D4
BLIND RIVET BETWEEN
43650-1 DORSAL
ASSY (REF)
EXISTING THIRD AND
FOURTH RIVETS (6 PLS)
(TYP
BOTH
SIDES)
43650-1 DORSAL ASSY
44217-3 LEADING
EDGE SKIN
DRILL 0. 250/0. 254" DIA.
HOLE (26 PLS). USE
EXISTING HARDWARE
43650-1 DORSAL
ASSY (REF)
EXISTING DORSAL
FAIRING
(4 REQD)
(8 REQD)
MS21047-L08 NUTPLATE
(REF)Mszo426A3
Figure
RIVET
1.
PageSoffj
a
/STA
B
\130. OOj
STA
\zsz.
vl
98. 00"
091-0039-00 INSULATOR
024-5003-00
WIRE
089-8007-00 WASHER
008-0033-00 TERMINAL
(REF)
1~
A
TERM~AL(REF)
\4-pq-
[2 PLS)
1\ \041-1233-00
(REF)
j
(REF)
047-1256-00 BOX
REQD)
1-INCH LONG
(REF)
(REF)
(REF)
/STA
30.
089-2013-00 NUT
(REF)
0. 437" DIA. HOLE
VIEW AA
(2 PLS)
0. 718"
ANTENNA
-$-CL
CABLE
FUSELAGE SKIN
(REFj
r-2.
FWD
Figure 2.
M
~d
EDGE SKIN
WIRE,
(2 PLS)
32pfCAPACITOR
48732-1 STIFFENER
MS20426AD3 RIVET (2
(REF)
089-8005-00 WASHER
155-2010-00
B
44211-3 LEADING
(REF)
NO.22 TLFLON INSULATED HOOKUP
(REF)
T1
0. 128" DIA. HOLE
(REF)
DOUBLER
089-8007-00 WASHER
CONNECTOR
090-0061-00 SPRING
(REF)
(REF)
FIBER WASHER
030-0009-00
(REF)
P
(REF)
089-5577-05 SCREW
010-0010-00
078-0014-00 CLIP
(REF)
(REF)
091-0040-00 INSULATOR
ASSY
(REF)
OF AIRCRAFT
125
6.
187" DIA.HOLE
(2 PLS)
EXLST~G ADF
RECEIVER
(REF)
i
BEFORE REWORK
~EMOVE 42pf
KR 85
CAPACITOR
1
16
L_
_
_
_
P851
I
~LIJ
AFTER REWORK
DISCONNECT, REMOVE
AND DISCARD EXISTING
RADIO ANTENNA CABLES
155-2010-00 RADIO
ANTENNA CABLE
EXISTING AD
RECEIVER
(REF)
KR 85
StcA/C
GND
10
11
12
13
14
15
16
L-----lpS51
50
pf
SENSE ANT
047-1256-00 BOX
155-2010-00 CABLE
(REF)
(REF)
Figure
3.
Page
5 of 5
CQmmander AlrCrafi blvlslon
R~3;ckwell
::’i
:i
nXi:OklRBinr i-73~aR:i:-
i
´•li
~-::is":l-::::::: :-i$_’i
.:-I;
:i:,::::::
.-i:-;:- i :1--;--~-
DATE:
112,
Q.;-
~-i-
December
3, 1973
SERIAL NO’S 3 TIIRU 106 tZND 108 TIIRU 111.
EFFECTIVITY:
MODEL
SUBJECT:
INSTALLRTION OF NLERON TIEIM TAB
RECOMMENDED
COMPLIANCE:
APPROVAL:
FAA
PURPOSE:
To
provide
a
simplified
means
of
adjusting
lateral trim
during rigging.
INSTRUCT~ONS:
a.
Using 42346-1
aileron trim tab
surface of aileron
template, locate,
as
drill and install aiteron trim tab
on
lower outboard
(see Figure 1.)
CAUTION
Precautions should be taken
through
b.
so
as
not to drill
upper aileron skin.
Recheck balance of aileron assembly.
WOTE
Balance to be 0 to 4. 0
inch-pounds trailing edge
heavy.
c.
Fill in and mail enclosed compliance card.
SUPPLY DATA:
Parts required to comply with this Service Letter may be purchased from Spare Sales Department, Commander Aircraft Division, Rockwell International, Bethany, Oklahoma 73008. Referel~ce this Service
Letter, and aircraft model and factory serial number when ordering the following parts:
QTY
PART NO.
DESCRIPTION
1
ea.
42346-1
Aileron Trim Tab
8
ea.
Cn2249-4-1
Blind Rivet
ELECTRICAL LOAD:
Not
Service Letter No.
accomplished
1953300
Applicable.
AIRCRAFT RECORDS:
CODE NO.
Make
SL-112-7,
(date)
Not
Applicable.
appropriate entry
dated December
in aircraft
3, 1973,
permanent
maintenance records
as
entitled "Installation of Aileron Trim
follows:
Tab",
Page lof
2
SERVICE LETTER NO.
LE FT WING
SL~-112-7
(nE Fl
oil
LF: FT
AILEAON (RE Fl
I
II
O
r‘--´•--
__U
I--
´•-´•:i.
CR2249-4-1 BLIND
RIVET (8 REQD)
j
W.S.
191.20
42346-1 AILERON TRTM 7‘AB
Figure
"lge
2 of 2
i.
a
i.´•-
sr~
~F 1 I
dn
In
1~D
General Aviation Division
Rockweli International
r
ld~
Bethany. Oklahoma
DATE:
112, SERIAL
73008
September 27! 1974
NO’S 3 THRU 187.
EFFECTIVITY:
MODEL
SUBJECT:
ENGINE FRONT BAFFLE ASSEMRLY INPROVEMENT.
RECOMMENDED
COMPLIANCE:
APPROVAL:
FAA
PURPOSE:
To
PART I
Approved.
prevent engine
front baffle
assembly
cracking.
from
MODEL 112, SERIAL NO’S 3 THRU 155.
INSTRUCTIONS:
top engine cowling assembly.
a.
Remove
b.
ncmt,ve and discard
c.
Stop drill
d.
Locate, drill and install 46241-1 doubler
e.
Cut slots in
f.
Install 46240-1 bracket
g.
Attach reworked engine front baffle assembly to 46240-1 bracket
h.
Reinstall
i.
Proceed to AIRCRAFT RECORDS.
PART II
cracks
any
engine
existing bracket From
in
engine
front baffle
on
front baffle
assembly
engine
center of
engine
assembly using
on
engine
frcint halrle
a
No.
front baffle
assembly (scF Fil:ure i.).
40 drill.
to match slots in 46241-1 doubler
(see Figure 1.).
using existing hardware (see Figure i.).
case
(see Figure 1.).
MODEL
112, SERIAL
NO’S 156 THRU 187.
INSTRUCTIONS:
a.
Remove
b.
Remove hardware
c.
Locate, drill and install 46241-1 doubler
d.
Cut slots in
e.
Reattach
attaching existing bracket to center of engine front baffle assembly (see Figure 1.).
engine front baffle assembly
engine
front baffle
assembly
to
on
engine front baffle assembly (see Figure 1.).
to match slots in 46241-1 doubler
(see Figure I.).
existing bracket (see Figure I.).
WOTI
existingscrew
(2 places).
Discard
screw
f.
Reinstall top
and
use
AN526-1032-7
engine cowling assembly.
Page 1 of 2
SUPPLY DATA:
Parts
required
to
Rockwell Commander Distributor.
when ordering the following parts:
comply
with this Service Letter may be pl´•ocured froln
your nearest
Letter, aircraft model and factory serial number
Reference this Service
PART I
PART II
QTY
QTY
1
1
ea.
1
ea.
2
ea.
2
ea.
AN526-1032-7
Screw
4
ea.
AN960- 10L
Washer
1519000
2
ea.
MS20364-1032C
Nuts
0065075
PART NO.
ea.
ELECTRICAL LOAD:
Not
46240-1
Bracket
46241-1
Doubler
CODE NO.
0056847
Applicable.
AIRCRAFT RECORDS:
DESCRIPTION
Not
Applicable.
Make appropriate
entry
Service Letter No. SL-112-8, dated September
(date)
ment", Part 1 accomplished
in aircraft
27, 1974,
Part II
permanent maintenance records
entitled
"Engine
accomplished
Front Baffle
as
follows:
Assembly Improve-
(date)
46240-1 BRACKET
46241-1 DOUBLER
MS20426AD3 RIVET
(4 PLS)
AN5 26 103 2 7 SCREW
AN960-10L WASHER (2 REQ)
M520364-1032C NUT
(2 PLS)
ENGINE FRONT BAFFLE ASSY
Figure 1.
Dage
2 of 2
(REF)
7
~fa
~R
Bethany, Oklahoma
DATE: October
EFFECTIVITY:
MODEL
SUBJECT:
INSPECTION OF BRAKE SYSTEM CLAMPS.
RECOMMENDED
COMPLIANCE:
WITHIN NEXT 100-HOURS OR NEXT ANNUAL INSPECTION.
112,
SERIAL NO’S 3 THRU
73008
25, 1974
220.
WOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING
WITH THIS SERVICE LETTER CONTACT GENERAL AVIATION
DIVISION, ROCKWELL INTERNATIONAL, CUSTOMER SERVICE
DEPARTMENT, BETHANY, OKLAHOMA 73008.
APPROVAL:
FAA DER
PU RPOSE:
To assure proper clearance between
Approved.
clamp assembly
and tire.
LNSTRUCTIONS:
a.
b,
and assure that clamp assemblies, located on main landing gear
installed as shown in Figure 1.
If necessary, relocate clamps as shown in Figure i.
Inspect
SUPPLY DATA:
Not
ELECTRICAL LOAD:
assembly,
are
properly
Applicable.
Not
Applicable.
Not
Applicable.
AIRCRAFT ~RECORDS: Make appropriate entry in aircraft permanent maintenance records as follows:
Service Letter No. SL-112-10, dated October 25, 1974, entitled "lnspection of Brake System Clamps",
accomplished
(date)
i
~c---EXISTING CLAMP ASSY
(REF)
O
r’
NO PART OF CLAMP TO
LEFT MAIN LANDING GEAR
PROTRUDE BEYOND STRUT
SHOWN,
RIGHT MAIN LANDLNG GEAR OPPOSITE
TOWARD TIRE MORE
TIIAN 0.07"
Plgur´• I,
~I´•
:A
i´•x
5
r
1~e
I"
´•a’’’
i´•
Bethany. Oklahoma
73008
:sta
SERVICE LETTER NO. SL-112-11 R1
DATE: November
25, 1974
112,
EFFECTIVITY:
MODEL
SUBJECT:
LANDING GEAR
RECOMMENDED
COMP LLANC E:
DURING NEXT 100-HOUR INSPECTION on WITHIN 60 DAYS A FTER RECEIPT OF
SQUAT
SWITCH INSTALLATION.
THIS SERVICE LETTER.
WOTL
IF ANY PROBLEMS ARE ENCOUNTETZED WHILE COMPLYING
WITH THIS SERVICE LETTER CONTACT GENERAL AVIATION
DIVISION, ROCKWELL INTERNATIONAL, CUSTOMER SERVICE
APPROVAL:
FAA DER
PURPOSE:
To
Approved.
provide
an
improved landing gear squat switch to prevent rain, slush and
snow
from causing squat switch to freeze.
INSTRUCTIONS:
a.
Jack aircraft
b.
~3isconnect,
from
c.
right
as
outlined in
remove
main
and discard
landing
Locate and drill two
applicable
Maintenance Manual.
existing landing
gear squat
switch,
bracket ~uld
attaching hardware
gear.
(2)
0.001) inch
0.160
diameter holes in
right
landing
main
gear
yoke (see
Figure i.).
d.
Locate and drill
a
0.218
0.002)
inch diameter hole 0.50-inch
deep
in
ridlt
main
landing
gear trunnion
(see Figure 1,).
e.
Tap hole drilled
f.
Install and
spiral
in
d. to
step
1/4-28 threads (see Figure I.).
crimp 60620-1 pin (3 places)
wrap and
cover
on
lead wires of 1EN1-6B
in 1-480305-0 connector
g.
Press 60620-1
h.
Install 45028-7 bracket and 1ENI-GB switch
i.
Plug
pins
switch,
vinyl tubing (see Figure 1.).
wire bundle with No.5
connector of 1ENI-GB switch into
wrap wires with
SWP-1/4
(see Figure 1.).
on
right
main
existing mating
landing
connector
gear
on
yoke (see Figure i.).
aircraft.
WOTI
Dead-end,
i.
k.
coil and stow three unused wires
Install AN4-5A bolt and AN316-4R check nut
Adjust squat
switch
as
right
main
landing
connector.
gear trunnion
(see Figure i.).
follows:
I.
Place
2.
Adjust switch, by raising
jack
on
near
under
right
wheel.
or
lowering
gear with
jack,
so
that switch actuates within
1/4-inch
of full extension of gear.
WOTE
Measurement is taken at base of oleo strut.
3.
Remove
jack from under wheel.
Page 1 of
3
i.
Functional test
m.
Remove
SUPPLY DATA:
jacks
landing
system to
gear
proper
operation of squat
switch.
from aircraft.
Parts
required
to
Rockwell Commander Distrihutor.
when
assure
comply with this Service Letter may be purchased throudi your nearest
Reference this Service Letter, aircraft model and factory serial number
ordering the following parts:
CODE NO.
QTY
PART NO.
DESCRIPTION
1
ea.
45028-7
Bracket
1
ea.
1EN1-GB
Switch
4023500
1
ea.
1-480305-0
Connector
0062301
3
ea.
60620-1
Pin
0062342
1
ea.
AN316-4R
Nut
0355000
1
ea.
AN4-5A
Bolt
0505000
2
ea.
AN526-632-14
Screw
0056710
2
ea.
AN960-6
Washer
1539000
2
ea.
MS21083N06
Nut
2718684
4 It.
No. 5
Vinyl Tubing
3796960
4 ft.
SWP-1/4
Spiral Wrap
3690054
1
No.
Service Letter
ea.
ELECTRICAL LOAD:
NotApplicable.
WEI[GHT AND BALANCE DATA:
Not
Applicable.
Make appropriate entry in aircraft permanent maintenance records as follows:
AIRCRAFT RECORDS:
Service Letter No. SL-112-~1, dated November 25, 1974, entitled "Landing Gear Scluat Switch Installation’’,
accomplished
’nge
2 of 3
(date)
SERVICE LETTER NO. SL-112-ll
EXISTING RIGHT MAIN LANDING
GEAR TRUNNION (REF)
1EN1-GB SWITCH
450213-7 I~ltACKET
AN5ZF-F32-14 SCREW
AN960-6 WASHER
MS21083N06 NUT
/t(2
PLS)
o"S’
~o
I
DRILL 0.216’’/0.220’’ HOLE
J
D
(TAP 1/4-28
THREADS) INSTALL
0.50" DEEP
0"30
EXISTING RIGHT MAIN
LANDING GEAR YOKE (REF)
AN4-5A BOLT AND
AN316-4R NUT
1-480305-0
i
0.159’’/0.161’’
DIA. HOLE
COUNTERBORE: LOWER
2 1 3 ~cCONNECTOR
SURFACE FOn NUT
0.25"
60620-1 PIN
(1 EA.WIRE)
cu
010
FJILU
d
1ENI-GB
SWITCH
IIT~m
DEAD-END, COIL
THREE UNUSED
STOW
WIRES
NEAR CONNECTOR
Figure
1.
Page
3 of 3
´•~’’4:1
m.~ %B aiBI 1 I’1L1
1JI
i~h
Bethany.
DATE:
112,
8, AND 10 THRU
SERIAL NO’S 3,
EFFECTIVITY:
MODEL
SUBJECT:
RIVET REPLACEMENT.
Oklahoma
73008
January 17, 1975
225.
RECOMMENDED
DURING NEXT 100 HOUR INSPECTION OR NEXT ANNUAL
COMPLIANCE:
INSPECTION,
WHICHEVER OCCURS FIRST.
WOPE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS
SERVICE LETTER, CONTACT GENERAL AVIATION DIVISION, ROCKWELL
INTERNATIONAL, CUSTOMER
OKLAHOMA
SERVICE
DEPARTMENT, BETHANY,
73008.
APPROVAL:
FAA DER Approved.
PURPOSE:
To
prevent fuselage
skins from
cracking.
INSTRUCTIONS:
(4) existing
left BLltboard rivets from lower fuselage skin in
a.
Remove four
b.
Install CR2249-5-2 rivet, CR2249-5-3 rivet
c.
Locate, drill and install
d.
e.
one
(1)
(2 places)
area
and CR2249-5-4 rivet
shown in
(see Figure 1,).
CR2249-5-2 rivet midspaced between fourth and fifth rivet
Locate, drill and install CR2249-4-2 rivet (2 places) midspaced between fifth and sixth
and seventh rivet ~see Figure 1.).
Fill out and mail
ea.
ea.
purchased locally.
Service Letter
No. SL-112-12
Compliance Card
ELECTRICAL LOAD:
Not
Applicable.
AIRCRAFT RECORDS:
Service Letter No.
rivet a~ld sixth
#QTE
Blind rivets may be
1
(see Figure i.).
Compliance Ca~d.
SUPPLY DATA:
1
Figure 1.
Make
SL-112-12,
Not
Applicable.
appropriate entry in aircraft permanent maintenance records as follows:
dated January 17, 1975, entitled "Itivet neplacement’l, accoinplished
(date)
Page 1 of 2
a
a
298.50
275. 12
Z 120. 50
148.00
1
Z 82.75
Z 64.00
p
ill
i-T--
_i
i
I
205.00
230.50
I----
z as.s0
Z 63.41
Zj8.00
Z 28. 58
0
22.00
27.50
62.50
85.00
123.00
1
168.32
178.00
263.00
C
r
M
REMOVE AND REPLACE
co
WITH CR2249-5-4 BLIND
-i
RIVET
Cm
;J
OUTED
z
ADD CR2249-4-2
BLIND RIVET
O
OI/
O
O
O
RE.LIOVE AND REPLACE
CR2249-3-3 BLIND
REMOVE AND REPLACE
WITH CR2243-5-2 BLIND
ADD CR2249-5-2
BLIND RIVET
RIVET
RIVET
VIEW LOOKICPUrG UP AT BOTTOM OF AIRCRAFT
O
11´• General Avlatlon blvlslon
r~a Rockwell International
I´•-´•
IA~L
1I~L
d
Bethany. Oklahoma
SERV~CE
ncvjsion No. 1
NO. S~-I-112-]3
DATE:
112, SERIAL
6 THRU
NO’S.
EFFECTIVITY:
MODEL
SUBJECT:
NOISE n\r ADF AUDIO.
73008
~ftlNE 17, 1975
220.
RECOMMENDED
AT OWNER’S DISCRETION
COMPLIANCE:
WOTI
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH TH~S SERVICE
GENERAL AVIATION
LETTER, CONTACT
DIVISION, ROCKWELL INTER-
NATIONAL, CUSTOMER
BETHANY, OKLAHOMA
APPROVAL:
FAA DER
PURPOSE:
To
SERVICE
73008.
DEPARTMENT,
Approved.
provide
a
capacitor
to reduce noise in ADF audio.
INS TRUCTIONS
(see Figure 1.).
a.
Cut slots in 43025-1 bracket
b.
Install CGS292U 050BD1
c.
Install wire leads and MS25171-1S
capacitor
on
43025-1 bracket with two
nipple (2 pls)
on
(2) MS21919DG22 clamps (see Figure 1.).
CGS292U 050BD1 capacitor
(see Figure i.).
d.
Loosen nuts on left and right cabin heat control cables and right defroster control cable and install
items assembled in step b. and c. and retighten nuts (see Figure 1.).
e.
Connect
capacitor
to aircraft electrical
system
as
shown in Figure 1.
Parts required to comply with this Service Letter may be purchased as a kit through your
SUPPLY DATA:
nearest Rockwell Commander Distributor. Reference this Service Letter, aircraft model and factory serial
number when ordering Service Letter SL-112-13 kit consisting of the following parts:
PART NO.
DESCRIPTION
43025-1
AN960D10
CGS292U 050BI)1
Washer
Capacitor
1859016
3 ft.
M5086/1-18-9
Wire
3844850
2
ea.
MS21044N3
Nut
2719213
2
ea.
Clamp
1
ea.
2734000
2748902
3
ea.
2
ea.
2
ea.
1
ea.
MS21919DG22
MS25036-102
MS25036-103
MS25171-1S
MS27039-1-10
No. SL-112-13
1
ea.
2
ea.
1
ea.
ELECTRICAL LOAD:
Bracket
Terminal
Terminal
dated
2748903
Nipple
2758000
Screw
Service Letter
2759267
Not
Applicable.
AIRCRAFT RECORDS: Make appropriate entry in aircraft maintenance records
SL-112-13,
1555000
Not.Applicable.
No.
CODE NO.
QTY
May 19, 1975, entitled
"Noose in ADF
as
follows:
Service Letter
Audio",
Page
1 of 2
H.CABIN MEAT CONTROL
(3
(REF)
AEAT CONTROL
Il DEFROSTER
IREF)
L DEFROSTER CONTROL
MS2503F-103 TERMINAL
(REF)
INSTRUMENT SUB-PANEL
MS25171-1S NIPPLE
o. 375 SLOT
(3 PI,S)
43025-1 RRACKET
CGS292U 050 BDI
CAPACITOR
MS21919DG22 CLAMP
MS27039-1-10 SCREW
AN960n10 WASNER
MS21044N3 NUT
(2 PLS)
5A
~-I ADF
CI3 7
MS25036-102 TEnMINAL
F5A20
TERMINAL
P10
Fi9Lire
I’a~e
2 of 2
1.
(hEF)
General Aviation Divi~ion
Bethanv. Oklahoma 73008
11 September 1975
DOOR POST DOUBLER MODIFICATION
MODELS AFFECTED:
MODEL
REASON FOR PUBLICATION:
TO REINFORCE DOOR POST DOUBLER.
COMPLIANCE:
DURING NEXT ANNUAL INSPECTION.
112,
WOTI
COMPLYING WITH THIS SERVICE LETTER, CONTACT
ROCKWELL
INTERNATIONAL,
GENERAL AVIATION
DIVISION, CUSTOMER SERVICE DEPARTMENT,
BETHANY, OKLAHOMA 73008.
BY WHOM WORK WILL BE ACCOMPLISHED:
A
P
MECHANIC OR EQUIVALENT.
APPROVAL:
FAA DER
ESTIMATED MAN HOURS:
THREE
PARTS DATA:
FABRICATE LOCALLY.
SPECIAL TOOLS:
NONE.
Approved.
(3)
HOURS.
ACCOMPLISHMENT INSTRUCTIONS:
1.
Remove left and right sunvisors and door post
upholstery
to
Figure 1.).
2.
Fabricate two
gain
access
(2) strap doublers, O.’lO-inch wide, from 0.040 2024-T3
to sunvisor brackets
(see
aluminum.
WOll
Length is shown in Figure 1. Doubler to extend two (2)
rivets above and below trimmed area (around sunvisor
bracket) on door post doubler picking up two (2) rivets
through upholstery clip
3.
Drill out
right
4.
elcisting
door
on
door
post.
rivets in area shown in Figure 1., and install fabricated doublers
post doublers using MS20470AD4 rivets.
Reinstall door post
upholstery
on
elcisting
left and
and sunvisors.
Page
1 of 2
UPPER END OF
ADDED DOUBLER
L´•´•´•
OVERHEAD INTERIOR
MOLDING (REF)
0.70"
WLDE.FARRICATE
STRAP
DOUBLERLENGTH
TO
EXTEND ABOVE AND BELOW
SUNVISOR BRACKET AS
SHOWN.
O
MS20470AD4 RIVET
(5 PLS)
SUNVISOR BRACKET
(REF)
DOOR POST
GNITSXE)F R(
DOUBLER
TRIMMED AREA
EXISTING UPHOLSTERY
CLIP(RE Fl
B
LOWER END OF
ADDED DOUBLER
VIEW LOOKING OUTB’D AT LEFT DOOR POST
RIGHT SIDE OPPOSITE
Figure 1.
E~ECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
PUBLICATIONS AFFECTED:
NONE.
Service Letter
RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows:
SL-112-14, dated 11 September 1975´•, entitled "Door Post Doubler Modification", accomplished
No.
(date)
P~ge 2 of 2
Rockwe Ilntemsnonal
~m
Gdneral Aviation Divirion
5001 North Rockwell Avenvo
Bethany. Oklahoma 730a[1
11 September 1975
PITOT HEAD ASSEMBLY ~JZODOFICATION
112, SERIAL
NO’S 3 THRU 350.
MODELS AFFECTED:
MODEL
TO REPLACE AIRSPEED PLASTIC HOSI" WITH ALUMINUM TUBING ON
PITOT HEAD ASSEMBLY TO PREVENT OVERHEATING.
COMPLIANCE:
DURING NEXT 100-HOUR INSPECTION.
WOTI
WITH THIS SERVICE LETTER CONTACT ROCKWELL INTERNATIONAL, GENERAL AVIATION DIVISION, CUSTOMER
SERVICE
APPROVAL:
A
P MECHANIC OR
EQUIVALENT.
FAA DER Approved.
TWO
(2)
HOURS.
PARTS DATA:
Reference this Service Letter, aircraft model and
5.84.
nearest Rockwell Commander Distributor for
SL-I12-15 kit consisting of the followiilg:
No.
Letter
Service
when
number
serial
ordering
factory
WOTE
Price
subject
to
change without notice.
CODE NO.
QTY
PART NO.
DESCRIPTION
1
48611-5
Tube
lea.
262-P-1/4
Union
52i4590
I
ea.
68F
Connector
7205990
1
ea.
Service Letter No~ SL-112-15
ea.
SPECIAL TOOLS:
1/4
X
1/8
Instructions
NONE.
Page I
of 2
Remove
attaching pitot
screws
head
2.
Disconnect
3.
Remove and discard
4.
Cut off
5.
Install. 48611-5 tube
6.
Connect 48611-5 tube to existing
7.
neinstall
pitot
8.
Perform
leakage
assembly
access cover
to wing and pull down
on
pitot head assembly i
plastic hose from pitot head assembly.
seven
(7)
edsting
connector from
inches from end of
head
on
existing plastic
pitot head assembly using
plastic
assembly and
test
pitot head assembly.
as
hose
access
hose.
68F
1/4
X
1/8
using 262-P-1/4
cover
on
outlined in the Model 112
connector
union
(see Figure 1.).
(see Figure 1.).
wing.
Airplane Maintenance’Manual,
Section VIII.
EXISTING PLASTIC HOSE
262-P-1/4
UNION
I’s
48611-5 TUBE~
8
a
~T-7
~g
a
68F
1/4
X
6~
1/8 CONNECTOR
a
e
a
e
ACCESS COVER
PITOT HEAD ASSY
Figure 1.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
The Illustrated
porated at the
RECORD COMPLIANCE:
No. SL-112-15, dated 11
Page
2 of 2
Make
ParC~ C~italolS changes recluircd by.this
next scheduled
appropriate entry
September 1975,
in
document will be incor-
change/revision.
al-rplane
entitled "Pitot Head
maintena.nce recordsas follows:
Service Letter
Assembly Moc~ification", accomplished
(date).
dc,I
RREN
´•Isssk
7p´•
liE
LILF ~Bke
Rmkwelllnternanonal
(Supersedes
Service Letter No.
SL-112-lg)
10 March 1977
IMPROVED FUEL DRAIN VALVE INSTALLAflON
MODELS AFFECTED:
MODEL
112,
NOTE
If basic Service Letter No. SL-112-16 has been
Service Letter.
I:
complied
with, disregard this
PROVIDE A FULLY SEALED DRAIN VALVE TO LESSEN THE
POSSIBILITY OF FUEL LEAKAGE.
COMPLIANCE:
NOTE
WITH THIS SERVICE
LETTER, CONTACT YOUR NEAREST
ROCKWELL COMMANDER DISTRIBUTOR OR YOUR ROCKWELL
COMMANDER REGIONAL SERVICE MANAGER (REFERENCE
SERVICE INFORMATION NO. SI-123).
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
FOUR
EQUNALENT.
Approved.
(4) HOURS.
PARTS DATA: Parts required to comply with this Service Letter may be purchased as a kit for $40. 37 from
your nearest Rockwell Commander Distributor. Reference this Service Letter, aircraft model and factory
serial number when ordering Service Letter Mo. SL-112-16A kit consisting of the following:
Price subject to change without notice
QTY
PART NO.
DESCRIPTION
CODE NO.
2
971DK
Drain Valve Kit
7903060
EACH KIT CONSISTS OF:
1 856B
Nut
ea.
Drain Valve
1
971D
1006C
1
MS29513-020
O-Ring
1
Retainer
1
pt.
1
ea.
PRC-1321, Class
PRC-1422, Glass
1
ea.
F391
Sampler
1
ea.
Servic e Letter No. SL- 112- 16A
Instructions
SPECIAL TOOLS:
B
Sealant
A
sealant
0045692
(1/2 pt.)
Drain
Cup
0045694
2289150
NONE.
1.
Defuel aircraft
as
follows:
WAIWIWO
Gasoline fumes
present during defueling operation; therefore,
prevent fire hazards. Smoking
on or around the aircraft is not permitted during defueliag procech~re.
Fire protection. equipment must be immediately avaih~Jae.
are
extreme caution must be exercised to
I’~ge i of 3
n.
PLace aircri~t
Level surface.
b.
C;round aircraft and
c.
Remove
d.
Discolmect fuel inlet
e.
ground
any
engine cowling.
supply
engine-driven
line to
fuel pump.
Connect defueling hose to fuel inlet supply line and place end of hose in fuel container.
container is determined by amount of fuel to be drained.
Remove fuel tanks filler caps.
g.
Place fuel selector valve to DOTH.
h.
Place master
battery switch
to
ON,
or
attach
i.
Place
auxiliary fuel pump switch to FUEL
j.
Place
audliary fuel pump switch
i.
to aircraft.
defueling ecluipment
f.
k.
an
auxiliary power unit
Size of
to the aircraft.
PUMP.
to OFF when fuel
stops pumping.
Drain residual fuel from all drains.
Remove drain
nuts to 100
2.
on
Remove lower
hose, reconnect fuel inlet supply line to engine-driven fuel pump and torque "B"
inch-pounds.
wing
access covers as necessary
to facilitate removal of lower
wing fuel drains located at
WS 83.34.
3.
4.
5.
Remove and discard
existing. left and right lower wing fuel drains, located at WS 83.34.
30 holes
Using 1006C valve retainer as a template, locate and drill two (2) No.
kit
of
drain
valve
1.).
(see Figure
wing skins for installation
Thoroughly clean
methyl ethyl
with
all
surfaces,
ketone
to which
(MEK) using
sealing compound
clean paper towels
is to be
or
small
in left and
applied, around fuel
paint brush and wipe
right
lower
valve retainer
clean.
WOTL
Clean
an area
6.
longer and wider than the width
provide maximum bonding.
of the
finally
sealant to
applied
Install 1006C valve retainer.
Apply 1422,
Class A sealant to rivets upon installation.
WOTE
Sealant must extrude
evenly around the rivets.
fillet after installation.
7.
Brush rivets with 1422, Class A sealant to form
tl.
Install 971D drain valve, MS29513-020 O-ring. and 856B nut.
a
Torque
nut 480 to 690
inch-pounds (see
Fi6~re 1.).
9.
Reinstall and reseal lowrr wing access coverjs), using PRC-1321 Class B sealant,
Model 112 Airplane Maintenance Mallual, Section V.
10.
Inspect ~uld pressure check
check for
possible
the tallks after
as
sealing compound has cured (approdmately
outlined in the
8 to 10 hours) atld
leaks.
CAUTION
attempt to apply pressure to the tallks without first seali!lg
off all lines and vents, and without an adequate regulator to central
of 9/2 psi !13.8 inches
pressure. T)o not pressurize the tank in excess
Do not
of
Pa~rp 3.~lf 3
water-manometer)
or
damage
may
occur.
SERVICE LETTER NO. SL-112-1BA
TYPICAL BOTH WINGS
971D DRAIN VALVE
I
856B NUT
I~
,1006C
RETA~ER
MS20470AD4 RIVET (2 PLS)
MS29513-020 O-RING
LOWER WING SKIN
(REF)
(REF)
EXISTING HOLE
W~G
t
STA.
83.34
DRILL NO. 30 HOLE
(2 PLS)
AFTi)
0.93"----~tc----0.93"
Figure
airplane
11.
Refuel
12.
Functional test fuel drain valves to
as
assure
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
The
I.
Airplane
proper
Maintenance
Manual, Section
II.
operation.
changes required by this document
Catalog.
have been
incorporated
in the
Illustrated Parts
Letter
RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows: Service
Fuel Drain Valve Installation", accomplished
entitled
10
’Improved
dated
March1977,
SL-112-16A,
No.
(date)
Page 3
of 3
Rochweii internafional
~Wi
9 October 1975
FUEL PUMP WIRING SUPPORT
MODELS AFFECTED:
MODEL
SECURE FUEL PUMP ELECTRICAL LEAD TO PRECLUDE
DAMAGE TO
LEAD DUE TO EXCESSIVE MOVEMENT.
COMPLIANCE:
112,
.~DURING NEXT 100-HOUR INSPECTION.
WOtP
COMPLYING
WITII THIS SERVICE LETTER CONTACT ROCKWELL
INTERNATIONAL, GENERAL AVIATION DIVISION, CUSTOMER
SERVICE
BY WHOM WORK WILL BE
APPROVAL:
ACCOMPLISHED:
FAA DER
DEPARTMENT, BETHANY,
A
OKLAHOMA
P MECHANIC OR
73008.
EQUIVALENT.
Approved.
THIRTY
(30)
MINUTES.
PARTS DATA:
Parts required to comply with this Service Letter
may be purchased as a kit through your
nearest Rockwell Commander Distributor for: Kit No. 1
$.46, KitNo. 2 gj .35. Reference thisService
Letter, aircraft model and factory serial number when ordering Service Letter No.
SL-112-17, kit consisting
of the following:
WOTE
Price
KIT NO.
1
2
subject.
to
change
without notice.
AIRPLANE EFFECTIVITY
Serial No’s. 4 thru 187.
Serial No’s. 188 thru 354.
Kit 1
Kit 2
QTY
QTY
PART NO.
DESCRIPTION
CODE NO.
1
ea.
1
ea.
4
ea.
4
ea.
Clamp
Ty-rap
2731500
1
ea.
MS21919DC2
MS3367-1-9
MS27039-1-08
1
ea.
MS203F5-1032C
Nut
2894125
2759266
2705090
Vinyl Sleeving
3797000
Screw
2 ft.
2 It.
tt5
1
1
Service Letter No. SL-112-17 Instructions
ea.
ea.
SPECIAL TOOLS:
(MIL-i-7444B)
NONE.
T’:IRe
1 c,f%
i
ACCOMPLISHMENT INSTRUCTM3NS:
1.
Assure that master switch is OFF.
2.
Remove upper
3.
Remove
4.
On
engine cowling.
plug from fuel pump
wire lead and install H5
villyl sleeving
on
wire and reinstall
plug.
187, drill a 0.199"/0.204" diameter hole in firewall and clamp fuel
using MS21919DG2 clamp, MS27039-1-08 screw and MS20365-1032C nut and
wiring using MS3367-1-9 ty-raps as required.
airplane serial
numbers 4 thMu
pump wire to firewall
secure
WOTE
Hole location
optional
airplane serial numbers 188 thru 354, clamp fuel pump wire to firewall with MS21919DG2 clamp using
elristing hardware and secure wiring using MS3367-1-9 ty-raps as required (see Figure i.).
5.
On
6.
Reinstallupper engine cowling.
FIREWALL
(REF)
MS3367-1-9
TY-RAP (2 PLS)
#5
(MIL-I-7444B)
VINYL SLEEVE
COWL FLAP
CABLE
(REF)
EXISTING PLUG
(REF)
MS21919DG2 CLAMP
PICKUP EXISTING HARDWARE
THAT ATTACHES AN EXISTING
CLAMP TO AFT FIREWALL
VIEW LOOKING AFT
FUEL PUMP
(REF)
MS3367-1-9
nola
TY-RAP
(2 PLS)
ILLUSTRATION SHOWN IS FOR
SERIAL NO’S 188 THRU 354 ONLY.
Figure
EL.ECTRTCAL LOAD:
no CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
PlrRLICATIONS AFFECTED:
NONE.
Make appropriate entry in airplane maintenance records as follows: Service
(date)
SL-112-17, dated 9 October 1975, entitled "Fuel Pump Wiring Support", accomplished
RECORD COMPLIANCE:
No.
i.
Page 2 of
2
Letter
sF~
IY100
aBGkWes Internafiensl
General Aviation Divi,ion
Bethany. Oklahoma 7300R
28 October 1975
ENGINE MANIFOLD PRESSURE TUBE MODIFICATION
MODELS AFFECTED:
MODEL
ADD BEAD TO END OF ENGINE MANIFOLD PRESSURE TUBE FOR
IMPROVED HOSE RETENTION.
COMPLIANCE:
DURING NEXT 100-HOUR INSPECTION
112, SERIAL
NO’S 3 THRU 380.
ROt~
WITH THIS SERVICE
LETTER, CONTACT
ROCKWELL INTER-
NATIONAL, GENERAL AVIATION DIVISION, CUSTOMER
A
P MECHANIC OR
APPROVAL:
FAA DER
ONE
PARTS DATA:
NONE.
SPECIAL TOOLS:
TUBE BEADING TOOL.
(1)
SERVICE
EQUIVALENT.
Approved.
HOUR.
1.
Remove upper
2.
Disconnect manifold pressure gage hose from tube assembly mounted
3.
Remove manifold pressure tube from engine.
4.
Bead end of manifold pressure tube
5.
Reinstall modified manifold pressure tube
engine cowling.
on
engine.
(see Figure 1.).
on
engine and reconnect manifold pressure gage
hose
using
existing clamp.
Zj.
Reinstall upper engine cowling.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
NO CHANGE.
RECORD COMPLIANCE:
Service Letter No.
accomplished
SL-~12-18,
Make appropriate entry in airplane maintenance records as follows:
dated 28 October 1975, entitled "Engine Manifold Pressure Tube Modi~ication"
(date)
Page 1 of
2
x
MANIFOLDY
i-’
HOSE
(REF)
EXISTING
CLAMP
i’
9
MANIFOLD PRESSURE TUBE
EXISTING
CLAMP
i;
)i
ri
I r
0.250
0.125!!
MAX. RADIUS
(+.031)"
0.031"
BEAD HEIGHT
0. 002"
MAX. RADIUS
Figure 1.
Page
2 of 2
Rockwell
ill~
Internatld~l
DiY(lion
Oln´•re) Aule(ibn
5M)1 North Rockwell Avenue
Belhany. Oklahoma 73008
Revision No. 1
19 December 1975
SfATIC SUMP DRAIN
MODELS AFFECTED:
MODE~
PROVIDE A SUMP bRAf~N FOR PITOT STAT~C SYSTEM.
COMPLIANCE:
UrITMN NEXT 50-HOURS TIME IN SERVTCE.
112,
SERIAL NO’S 3 THRU 437
rlafr
fF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLMNG
WITH THIS SERVICE LETTER, CONTACT ROCKWELL INTERNATIONAL, GENERAL AVIATION DIVISION, CUSTOMER
SERVICE
DEPARTMENT, BBTHANY, OKLAHOMA
A
APPROVAL:
FAA DER
THREE
MECHANIC
P
OR
73008
EQUIVALENT
Approved.
(3)
HOURS.
PARTS DATA: Parts required to comply with this Service Letter may be purcha.sed as a kit through your
nearest Rockwell Commander Distributor for 84.08 (J). Reference this Service Letter, aircraft model and
factory
serial number when
ordering Service Letter
No. SL-112-19 kit
consisting
of the
following:
wa~a
Price
subject
to
change
without: notice.
QTY
PART NO.
DESCRIPTION
1
ea.
48601-7
Tube
1
ea.
264N
1
ea.
Service Letter No.
SPECLAL TOOLS:
1./4
CODE NO.
0659444
Tee
Instru ctions
NONE.
1.
Remove interior console
2.
Remove knobs from control levers.
3.
Remove
4.
Reinove and discard existing elbow from static
5.
Install 264N
quadrant plate
1/4
to
cover.
gain
access
tee and 48601-7 tube
to static
on
static
source
source
source
selector valve.
selector valve
(see Figure i.).
selector valve and reconnect
existing tube (see
Page 1
of 2
6.
7.
Perform leakage test
as
Airplane
Maintenance Manual. Scctic,n VIII.
Reinstall qundrant plate, control lever knobs and interior donsolr
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
The
ii
cover.
Flight Manual, Maintenance MalluR1 and Illustrated Parts Crltaloji chnnRes
required by this document will be incorporated at the next sclieduled chnn~e
revision.
jI
I
STATIC SOURCE
Bj~
(REF)
-:.1I´•u
REMOVE
EMSTING ELBOW
AND INSTALL
264N
1/4
TEE
EMSTING TUBE
Figure
RECORD COMPLIANCE:
Letter No.
Page 2
of 2
SL-112-19,
Make
i.
appropriate entry in airplane mainten~ulce records as follows:
1975, entitled "Static Sump Drain", accomplished
dated 3 December
Service
(date)
Rockwell Internattonal
Bethilny. Oklahomil 7300R
SERVICE LETTER NO. SL,-112-21
7 January 1976
MAIN LANDING GEAR TRUNNION LUG MODIFICATION
AND/OR RETRACT CYLINDER ATTACH BOLT REPLACEMENT
MODELS AFFECTED:
PART f
MODEL
PART II
MODEL
112,
112,
PROVIDE FLAT SURFACE TO ALLOW CONE SPACER TO SEAT
PROPERLY ON TRUNMON LUG AND/OR REPLACE RETRACT CYLINI)ER
ATTACH BOLT.
DURING NEXT ANNUAL INSPECTION OR WITHIN NEXT 100-HOURS
TIME IN SERVICE, WHICHEVER OCCURS FIRST.
COMPLIANCE:
IC)tB
WITH THIS SERVICE
LETTER, CONTACT ROCKWELL
INTER-
NATIONAL, GENERAL AVIATION DIVISION, CUSTOMER
SERVICE DEPARTMENT, BETHANY, OKLAHOMA 73008.
P MECHANIC OR
A
EQUIVALENT.
APPROVAL:
FAA DOA SW-2
SPOTFACE TRUNNION LUG AND REPLACE RETRACT CYLINDER
ATTACH BOLT
EIGHT (8) HOURS.
REPLACE RETRACT CYLINDER ATTACH BOLT ONLY
TWO (2) HOUI~LS.
Approved.
PARTS DATA:
nearest Rockwell Commander Distributor for ff; 3.66 (H). Reference this Service Letter, aircraft model altd
factory serial number when ordering Service Letter No. SL-112-21 kit consisting of the following:
WOTE
Price
subject
to
change
without notice.
QTY
PART NO.
DESCRIPTION
CODE NO.
2 ea.
2 ea.
MS20002C6
MS21250-06026
Washer
2706340
2719681
1
Service Letter No.SL-112-21
Instructions
ea.
AIRPLANE JACKS
SPECIAL TOOLS:
Bolt
(3)
AND
1.187"/1.250"
DIAMETER SPOTFACE.
PARTI
1.
Jack airplane
as
Airplane
Maintenance Manual, Section II.
PnRe 1 nf
n
SERVfCE LETTER NO. SL-112-21
1.
187"/1.
250" SPOTFACE
TO o. 06.. DEPTH
j
_(
AFT
I)
0.03" FILLET
(-B~
RETRACT
WASHER
i ’1
o
TRUNNION
ASSY
iMS21250-06026
,I
130LT
Figure
Page 2 of 3
i.
i
SERVICE LETTER NO. SL-~12-21
2.
Remove and discard existing bolt and washer
cylinder to lug on trunnion.
3.
Spotface lug
on
left and
right
main
(under
bolt
head)
landing gear trunnions
that attaches outboard end of retract
Figure i.
to dimensions shown in
WOll
Spotface must be
to
remove
perpendicular
to hole.
It may be necessary
landing gear assemblies from airplane to spotface
lug.
4.
5.
cylinder
head) (see Figure i.).
Attach retract
Check
operation
of
to
landing
lug
on
gear
trunnion
system
using MS21250-06026
as
bolt and MS20002C6 washer
Airplane
(under
bolt
Maintenance Mallual?
Section VI.
jacks from airplane.
6.
Remove
7.
Proceed to RECORD COMPLIANCE.
PART II
airplane
I.
Jack
2.
Remove and discard
3.
Remove
as
Airplane
Maintenance
Ma~lual, Section
II.
existillg bolt and washer (under bolt head) that attaches outboard end of main landing
retract
cylinder to lug on main landing gear trunnion and install M821250-06026 bolt and MS20002C6
gear
washer (under bolt head) (see Figure I.).
jacks
from
airplane.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
PUBLICATIONS A´•FFECTED:
The Illustrated Parts
incorporated
Catalog changes rerluired by
at the next scheduled
this document will be
change/revision.
Service
RECORD COMPLIANCE:
Modification
and/or
Trunnion
Gear
entitled
"Main
Lug
dated
7
Landing
Letter No. SL-112-21,
January 1976,
Retract
Cylinder Attach
Bolt
Replacement", accomplished~
Page 3 of
3
Rockwell Internationa
C´•n´•r´•l Avi´•tion Divilion
5001 North Aoc~mll Avenue
Bethanv. OClshoma 730~8
26 January 1976
NOSE LANDING GEAR STRUT MODIFICATION
MODELS AFFECTED:
MODEL
ELIMINATE NOISE IN NOSE LANDING GEAR STRUT ASSEMBLY.
COMPLIANCE:
A?’ OWNER’S DISCRETION.
1121 SERIAL NO’S
4 THRU
380. 383. 384. 386 THRU 434.
WOIE
1F ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH
THIS SERVICE LETTER, CONTACT YOUR NEAREST ROCKWELL
COMMANDER DISTRIBUTOR OI~ YOUII ROCKWELL COMMANDER
REGIONAL SERVICE MANAGER. REFERENCE SERVICE INFORMATION NO. S1-123.
BY WHOM WORK WILL nE ACCOMPLISHEI):
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
FOUR
PARTS DATA:
Parts required to
EQUIVALENT.
Approved.
(4) HOURS.
with this Service Letter may be purchased as a kit through
your
Reference this Service Letter, aircraft model and factory serial
Service Letter No. SL-112-22 kit: consisting of the following:
comply
nearest Rockwell Commander Distributor.
number when
ordering
WOTL
Price subject to
change
QTY
PART NO.
An
45032-1
An
45032-3
r
Service Letter No. SL-112-22
ea.
without notice.
DESCRIPTION
($7.34 (11) each)
($6.71 (I-I) each)
Washer (Matl thickness is 0.032-inch)
(Mntl thickness is 0.016-inch)
Instructions
Washer
+Specify quantity when ordering parts.
SPECIAL TOOLS:
NONE.
1.
Jack airplane
2.
With
and
3.
as
outlined in Model 112
Airpl~le Mainten,ulce Manua.l.
Section IV.
torque tube firmly against lower collar, check R:1P dimension between nose landing gear trunnion
torque tube.
Gap should not be Inore than 0.020-inch or less than 0.005-inch (sec Fi~ure i.).
I1 gap between
nose
Rear trurulion ;tnd
torque tube
is less than
0.020-inch, proceed
to
step 14.
Page 1 of 3
TRUNNION(REF)
I
REMOVE
/I
BOLTS\
~o
COLLAR AND BODY
ASSY
ADD 45032-t OR
(REF)
45032-3 WASHER
REMOVE LOWER DRAG
TRREL~NION(REF)
BRACE BOLT
TORQUE TUBE
ASSY
(REF)
O
COLLAR
(REF)
i
r
o. ozo"
TORQUE
TUBE
Figure 1.
Page
2 of 3
(REF)
gear trunnion and torque tube is
4.
If gap between
5.
Disconnect
6.
Remove lower
7.
Remove bolts
attaching trunnion
8.
Remove
gear strut
nose
nose
nose
gear
more
than 0.02O-inch proceed to
step 5.
steering cables and down springs.
drag brace bolt at
strut attach
to
point.
body and collar assembly (see Figure 1.).
assembly from
trunnion
assembly (see Fi~re 1.).
WOtt
It may be necessary to partially retract
remove strut assembly.
g.
Install 45032-1
than 0.020-inch
and/or
45032-3 washer
as
required
l;uldin~
gear to
to obtain clcar;~ncc‘ not less than O.OOfi-inrh
c,r
Inc,rr
(sec Fi~re 1.).
10.
Reinstall strut assembly in Irunnion assembly.
11.
Reconnect
12.
Reconnect down
13.
Functional test landing gear system to
Maintenance Manual, Sectio,l VI.
14.
Remove
drag brace
to strut
springs
assembly.
and steering cables.
assure
proper
operation
as
Airplane
airplane from jacks.
ELECTRICAL LOAD:
NO CHANCE.
WEIGHT AND BALANCE:
NO CHANGE.
incorporated
RECORD COMPLIANCE:
SL-112-22,
(date)
Letter No,
nose
Make
dated 26
Catalog chrulges required by
change/revision.
appropriate entry in airplane maintenance records as follows: Service
January 1976, entitled "Nose Landing Gear Strut Modification", accomplished
Page 3 of 3
Rockwell Internatior
C´•nerel Aviltion Divi~ion
5001 North Roc~well Avenue
Bethany. olrlehome
‘j3008
25 February 1976
INTERNAL CORROSION PROTECTION
MODEL
MODELS AFFECTED:
112,
PROVIDE INTERNAL CORROSION PROTECTION FOR FLAP TORQUE
ELEVATOR HORN ASSEMBLY, ELEVATOR PUSH-ROD ASSEMBLY
AND RUDDER HORN ASSEMBLY.
TUBE,
DURING NEXT ANNUAL INSPECTION.
COMPI,IANCE:
WO1I
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH
COMMANDER DISTRIBUTOR OR YOUR ROCKWELL COMMANDER
REFERENCE SERVICE INFORMA-
REGIONAL SERVICE MANAGER.
TION NO. SJ-123.
A
BY WHOM WORK WILL DE ACCOMPLISHED:
APPROVAL:
FAA DOA SW-2
THIRTEEN
EQUIVALENT.
Approved,
(13) HOURS.
following material required
The
PARTS DATA:
P MECHANIC OR
to
comply with this Service Letter
purchased locally:
may be
QTY
PART NO.
DESCRIPTION
1
Sprayon Products,Inc.
Sprayon No. 710
Rust Preventative
ea.
with nozzle
(15 oz.
extension)
can
NONE.
SPECIAL TOOLS:
Remove
remove
screws attaching fiberglass stinger
stinger from airplane.
baggage curtain
Remove aft
3.
Relieve tension
4.
Remove bolts from rudder
5.
Disconnect elevator actuator rod.
6.
Remove six
7.
Remove elevator
8.
Remove bolt
9.
Remove bolts
bly
10.
from
(6)
fuselage,
disconnect tail
navigation light wiring and
baggage compartment.
from
2.
on
to aft
rudder cables and disconnect cables from rudder.
screws
hinges and
and two
(2) bolts
hinge bolts and
attaching
elevator
remove
remove
rudder from
at the inboard end of elevator.
elevators from
push-rod assembly
attaching elevator
airplane.
horn
airplane.
assembly
Spray interior of elevator push-rod assembly,
Sprayon No. 710 (see Figure 1.).
airplane.
to elevator horn
assembly.
to horizontal stabilizer and
elevator horn
remove
elevator horn
assem-
assembly and rudder horn assembly with
Page 1 of 3
I
TORQUE TUBE MOUNT ASSY
~t,
m
,B
FLAP TORQUE TUBE
SPRAYON NO. 710
(TYPICAL)
(ai;:
~B
o
DRILL 0. 250"
6
’-le
DIA HOLE
FLAP ACTUATOR LEVER
C
B
ELEVATOR HORN
ASSY
8
~3
a
RUDDER HORN
i:ii
ELEVATOR
ASSY
PUSH-RODC-t~i
Figure 1.
Page 2 of 3
ASSY
11.
neinstall elevator horn assembly
using existing hardware.
12.
Reinstall elevators
13.
Reinstall rudder
on
14.
Rig elevator and
rudder control
15.
Reconnect tail
16.
Remove
17.
Drill
a
rear
on
airplane
airplane
on
horizontal stabilizer and reconnect to elevator
and reconnect elevator actuator rod
and reconnect cables using
system
as
outlined in the
assembly
as
using e~dsting hardware.
e~xisting hardware.
Airplane
navigation light wiring and reinfitail stinger
seats and noorboard
push-rod assembly
on
necessary to
Maintenance
Manual, Section VII.
airplane.
gain
0.250-inch diameter hole in the top of the nap torque tube.
tube mount assembly (see Figure I.).
access
to
nap torque
Hole to be located
tube
assembly.
just inboard of
right torque
flap
actuator lever
18.
Remove inboard bolt from
19.
Spray interior
20.
Reinstall bolt, removed in step
21.
Reinstall noorboard assembly and
22.
Reinstall baggage curtain in baggage
of
nap torque
tube with
18.,
(see Figure 1.).
Sprayon
in
rear
No. 710
nap actuator
(see Figure i.).
lever.
seats.
compartment.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
NONE.
Make appropriate entry in airplane maintenance records
RECORD COMPLIANCE:
No. SL-112-23, dated 25 February 1976, entitled’lnternal Corrosion Protection",
as
follows:
Service Letter
accomplishe~
Page
3 of 3
r
;YE
1
a,J
I~
rut rJ ~L
1L
n
ROCkWBlllntsmatlona
General Aviation Divi~ion
Bethany. Oklahoma 73008
23
April 1976
BAGGAGE RESTRAINT REPLACEMENT
112,
MODELS AFFECTED:
MODEL
AN UNKNOWN NUMBER OF BAGGAGE RESTRAINTS WERE SEWN WITH
IMPROPER THREAD. THIS SERVICE LETTER IS BEING ISSUED TO
CORRECT THIS SITUATION.
UPON RECEIPT OF THIS SERVICE LETTER AND REPLACEMENT
COMPLIANCE:
BAGGAGE RESTRAINT.
WOtli
LETTER, CONTACT YOUR NEAREST
I
WITH THIS SERVICE
ROCKWELL COMMANDER DISTRIBUTOR on YOUR ROCKWELL
COMMANDER REGIONAL SERVICE MANAGER
L.
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
THIRTY
(30)
(REFERENCE
EQUIVALENT.
Approved.
MINUTES.
Parts required to comply with this Service Letter may be purchased through your nearest
PARTS DATA:
Rockwell Commsllder Distributor for $40.00 (H). Reference this Service Letter, aircraft model and factory
serial number when ordering: Service Letter No. SL-112-24 kit consisting of the following:
DESCRIPTION
PART NO.
QTY
1
ea.
49010-3
Baggage Restraint
1
ea.
Service Letter No.
Instructions
SL-112-24
NONE.
SPECIAL TOOLS:
to
baggage restraint, located in baggage compartment, through baggage compartment door.
1.
Gain
2.
Remove
3.
Install 49010-3 baggage restraint in
access
existing baggage restraint
from
airplane.
airplane.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANCE.
NONE.
RECORD COMPLIANCE:
SL-112-24,
(date)
Letter No.
appropriate entry in airplane maintenance records as follows: Service
April 1976, entitled "Baggage Restraint Replacement", accomplished
Make
dated 23
Page
i of I
1
´•u
I~
~L
Rockweil Internabon.l
General Aviation Divirion
13 April 1976
ALTERNATE STATIC SOURCE CORRECTION PLACARD REPLACEMENT
112,
MODELS AFFECTED:
MODEL
PROVIDE AN ALTERNATE STATIC SOURCE CORRECTION PLACARD WITH
COMPLETE INFORMATION. ADDITION OF MINUS SIGNS TO ALTITUDE
CORRECTION COLUMN TO INDICATE THAT CORRECTION REDUCES INDICATED ALTITUDE.
UPON RECEIPT OF PLACARD
COMPLIANCE:
AND/OR
THIS SERVICE: LETTER.
WOtl
THIS SERVICE
LETTER, CONTACT
YOUR NEAREST ROCKWELL
REGIONAL SERVICE MANAGER (REFERENCE SERVICE INFORMATION
SI-123).
NO.
OWNER/OPERATOR.
APPROVAL:
FAA DOA SW-2
FIFTEEN
PARTS DATA:
Parts required to
comply
(15)
Approved.
MINUTES.
with this Service Letter for aircraft Serial Numbers 381 thru 471
only,
may be ordered as a kit through your nearest Rockwell Commander Distributor on a no charge basis. Reference
this Service Letter, aircraft model and factory serial number when ordering Service Letter No. SL-112-25 kit
consisting of the following:
QTY
PART NO.
1
ea.
49307-181
Placard
1
ea.
Service Lel-ter No. SL-112-25
Instructions
DESCRIPTION
SPECIAL TOOLS:
NONE.
1.
On aircraft Serial Numbers 3 thru
a.
Inspect
the
eldsting alternate static
Correction column.
minus
2.
signs
If there
source
are no
follows:
as
correction card for minus
minus
signs
Remove and discard
side of instrument
through 471, proceed
edsting
panel.
as
signs
in the Altitude
in the Altitude Correction
to indicate that the Altitude Correction is
On Aircraft Serial Numbers 381
a.
380, proceed
a
column,
add
reduction from the Indicated Altitude.
follows:
alternate static source correction
placard
located
on
the upper left
WOTC
It is
b.
Install 49307-181
correction
acceptable
to install
new
placard
placard on instrument: panel
placard was installed.
over
existing placard.
in area where
existing alternate
static
source
Page 1 of
2
SERVlCE LETTER NO. SL-112-25
ELECTRICAL LOAD:
NO
WEIGHT AND BALANCE:
NO CHANCE.
NONE.
RECORD COMPLIANCE:
Service Letter No.
SL-112-25,
Replacement" accomplished
Page
2 of 2
CHANGE.;s
Make
dated 13
appropriate entry in airplane maintenance records as follows:
April 1976, entitled "Alternate Static Source Correction Placard
~(date)
npR
~9iC
i,
;´•ic~
I-iiiZ
i:
i
:i,
(i
´•i;
Rackwell International
Cene~al Aviation Divi~ion
5001 No~rh Rockwell Avenue
Ueihany, Oklahoi~a 13008
SEIIVICE LETTER NO. SL-112-28
2
September 1976
ELEVATOR TRIM TAB ACTUATOR SEAL INSTAL1ATION
MODEL
MODELS AFFECTED:
112,
SEItIAL NO(S 381
THRU
475,
AND MODEL
112TC,
SERIAL
NO’S 13000 THRU 13016,
PREVENT MOISTURE FROM ENTERING ELEVATOR TRIM TAB
ACTUATOR
DURING NEXT 100-HOUR. INSPECTION OR ANNUAL INSPECTION.
COMPLIANCE:
nota
IF ANY PROBLEMS ARE ENCOU:NTERED WHILE COMPLYING WITH
THIS SERVICE LETTER, CONTACT YOUR N~AREST ROCKWELL
COMMANDER DISTRIBUTOR ORIYOUR ROCKWEiL COMMANDER
NO. SI-123).
A
nY WHOM WORK WILL UE ACCOMPLISHED:
:FAA DOA SW-a
APPROVAL:
TWO
Parts
PARTS DATA:
required
to
(2)
P MECHANIC
qR EQUIVALENT.
Approved.
HOURS.
comply with this Service
Letter may be
purchased
as a
kit
through
your´•
nearest Rockwell Commander Distributor for $19.37 (K). Reference this Service Letter, aircraft model and
factory serial number when orderiIlg Service Letter No. SL-112-28 kit consisting of the following:
QTY
PART NO.
DESCRIPTION
2 ea.
565003-1
Bracket
2_
565004-1
Seal Retainer
Washer
ea.
AM960PD10L
MS21044N3
4 ea;
2 6a,
2 aa.
a eg...
1
eB.:
CODE NO.
1:
1584000
Nut
2119213
MS27039-1-09
Sc rew
2769381
5-0310-910R
O-Ring
3707940
Service Letter No.
Instructions
SL-112-28
NONE.
SPECIAL TOOLS:
i.
Disconnect elevator trim tab push rod assembly from elevator trim tab actuator rod,
2.
EEemove
ele:vator
tri
m
tab actuator
access cover
from elewato r
asser~bly.
WOIE
It may be necessary to
r´•ernove
elevator
assembly
to
perform,
the following installation.
3..
To assure that
a~l:moisture
is removed
from elevator trim tab actuator, apply heat to actuator withla
heat b~n.
Page 1 of 2
S~I: I1VICli :L,E:’I"I’1´•:%~ NO
SI,´•´•´•´•1:12-2H
STEP 1
i.. C: V ATOR ´•1’Iilh~l rl’ A U
AC’I’ I) ATOR
i
(H~ F’
’~-I_SE:AL, WT?’H tlEAD OF ONE
OF TIII´•: %’ULLOWING:
PH1221-B2 SEALAMT
PRO-SEAL 707-112
now CORNIN(; SILICONE
SEAL HERE WITH ONE
STEP 2
S-0310-910R
OE’ THE FOLLOWING:
PH1221-B2 SEALANT
PRO-SEAL 707-82
DOW CORNING SILICONE
O-RTNC;I
-IlfPJi ~t
BRACKET
565004-1 SEAL RETAINER
0.190’’/0.194’’
DIA HOLE
MS27039-1-09 SCREW
AET~GI)PDML WASHER
MS21044M3 NUT
Figure
Add
4.
a
bead of PR1221-B2 sealanl,
as shown in Fi8~re 1.
or
Pro-Seal
(2 REQD)
i.
707-82,
or
Dow
Coming
Silicone around elevator trim
tab actuator
tab actuator,
Install S-0310-ylOR O-ring, 565004-1 seal retainer and 565003-1 bracket on elevator trim
MS27039-1-09
drill a 0.192 (-t. 0.002) inch diameter hole through bracket and elevator spar and install
MS21044N3 nut (see Figure 1.).
screw, AN960PD10L washer (2 places) and
5.
Cover clevis
6.
Coming
joint and both ends: elf roll pin with either PR1221-B2 sealant, Pro-Seal 707-82
(see Figure 1.).
or
Dow
Silicone
WOTE
Sealant Inust not
actuator is
push
fully
rod
7.
Reconnect elevator trim tab
8.
Reinstall elevator trim tab actuator
come
in contact with seal retainer when
retracted.
assembly
to elevator trim tab actuator rod.
access cover on
ELE:CTEIICAL LOAD:
NO CHANCE.
WEIC;1IT ANT> BALANCE:
NO CHANGE.
PUULICATIONS AFFECTED:
incorIx,rated
SL-112-28,
(date)
Page
2 c,f 2
dated
Catalog change reyuired by
at the Ilext scheduled
change/revision.
appropriate elltry in airplane maintenance records as follows: Service Letter
2 September 1976, entitled "Elevator Trim Tab Actuator Seal Installation", accomplished
NECORD COMPLJAMCE:
No.
elevator assembly.
Make
Service Letter
(Supersedes
Service Letter No.
SL-112-29,
GeMrsl Aviation Divition
dated 3 September 1976, in its entirety.)
4 April 1980
EXHAUST STACK SUPPORT INSTALLATION
13108 AND MODEL ~1STCA,
MODEL 112TC SERIAL NO’S 13001 THRU
13276 AND 13300 THRU
SERIAL NO’S 13150 THRU 13195, 13250 THRU
13309.
MODE LS AF FEC TED:
NOtE
HAS NOT BE~EN COMPLIED
IF BASIC SERVICE LETTER NO. SL-112-29
LETTER.
WITH, COMPLY WITH PART I OF THIS SERVICE
THE TYPE OF CLAMP AS
IF THE EXHAUST STACK STRUT CLAMP IS
WITH PART I ONLY
COMPLY
FIGURE
1.,
SHOWN IN DETAIL "A OF
OF THIS SERVICE LETTER.
THE TYPE OF CLAMP AS
IF THE EXHAUST STACK STRUT CLAMP IS
WITH PART II ONLY
COMPLY
FIGURE
1.,
SHOWN ZN DETAIL "B" OF
OF THIS SERVICE LETTER.
IMPROVE EXHAUST STACK SUPPORT INSTALLATION.
COMP LIANC E:
WITHIN NEXT 100-HOURS TIME IN SERVICE.
WOta
COMPLYING WITH
LETTER, CONTACT YOUR NEAREST ROCKWELL
SERVICE FACILITY.
AUTHORIZED
COMMANDER
THIS SERVICE
APPROVAL:
FAA DOA SW-2
TWO
(2)
P MECHANIC OR
A
EQUIVALENT.
Approved.
HOURS.
be procured through your nearest RockParts required to comply with this Service Letter may
PARTS DATA:
$39.39. Reference this
or Kit No. 2
1
No.
Kit
$83.28
for:
well Commander Authorized Service Facility
No. SL-112-29A kit
Letter
Service
number when ordering
Service Letter, aircraft model and factory serial
consisting of the following:
Price
Kit No. 1
Kit No. 2
rubject
to
change without notice
Part I
PartII
Pagelof4
Kit No.2
Kit No.l
QTY
QTY
2
ea.
1
ea.
1
ea.
1
ea.
2
ea.
1
ea.
1
ea.
PART NO.
DESCRIPTION
CODE NO.
MS27975-4
645006-43
Clevis
Strut Assy
2759600
645006-47
645006-59
AN3C6A
Strut
Bolt
0300601
Bolt
0050078
Jam Nut
Washer
0355000
1518000
Nut
2709400
Lockwasher
2894468
Assy
Clamp Assy
2
ea.
1
ea.
3
ea.
AN3C7A
AN316-4R
AN960C10
MS20500- 1032
1
ea.
MS35333-40
1
ea.
1
1
ea.
1
ea.
ea.
Compliance Card
Instructions
Service Letter No.
SL-112-29A
NONE.
SPECIAL TOOLS:
STRUT ASSEMBLY AND CLAMP ASSEMBLY REPLACEMENT.
PART I
cowling from engine.
1.
Remove upper
2.
Remove and discard
3.
Install 645006-59 clamp assembly
4.
Install AN316-4R
eldsting strut assemblies (645006-9, 645006-11
assembly (645006-3), existing devises and attaching hardware.
jam
nut and MS27975-4 clevis
on
645006-51), eldsting clamp
(see Figure 2.).
exhaust stack
on
and
645006-43 and 645006-47 strut assemblies.
WOTE
Do not
5.
nut
on
strut assemblies.
nut
Install 645006-43 strut assembly, 645006-47 strut assembly and MS35333-40 lodrwasher (under
in
installed
to
connect
assembly
and
clamp
temporarily
upper end of -47 strut assembly) on engine
step
6.
tighten
3.
on
(see Figure 2.).
to center of cutout in engine cowling and adjust strut
centered
the
in
position in cutout with a minimum clearance of 0.50assemblies to secure exhaust outlet
all possible installainch and tighten exhaust stack clamp assembly and all nuts as required to relieve
Loosen exhaust stack
tion
clamp, position exhaust stack
pre-load.
cowling
engine.
7.
Install upper
8.
Fill out and mail
9.
PART II
on
Compliance Card
and
specify
that Part I has been
accomplished.
CLAMP ASSEMBLY REPLACEMENT.
cowling from engine.
1.
Remove upper
2.
Remove and discard
3.
Remove and discard
4.
Install 645006-59 clamp assembly
elristing upper strut assembly from engine and retorque nuts
inch-pounds (see Figure 2.).
hardware
Page 2 of 4
on
engine 50
to 70
existing clamp assembly from exhaust stack (see Figure 2.).
(see Figure 2.).
on
exhaust stack and
e~sting strut assemblies using e~sting
SERVICE LETTER SL-112-29A
DETAIL A
re,
DETAIL B
EXHAUST
STACK
(REF)
a
a
II
a
a
Figure 1.
REMOVE AND DISCARD
VIEW LOOKING FWD
EXISTING STRUT ASSY
EXISTING HARDWARE
(TORQUE 50 TO 70 IN-LBS
(IF INSTALLED)
AND SAFETY
WIRE)
EXISTING HARDWARE
(TORQUE 65 TO 85 IN-LBS)
U
REPLACE EXISTING
LOCKWASHER WITH
MS35333-40
LOCKWASHERI
L
TURBOSTRUT
FWDI)
MS27975-4
CLEVIS
(RE Fl
645006-43
STRUT ASm
EXHAUST STACK
645006-47
(REF)
STRUT ASSY
AN316-4R
JAM NUT
AN316-4R
JAM NUT
f~\
645006-59 CLAMP
ASm
(REF)
MS27975-4
AN3C7A BOLT
AN960C10 WASHER
MS20500-1032 NUT
CLEVIS
AN3C6A BOLT
MS20500-1032 NUT
NOTE:
UPON COMPLETION OF THIS SERVICE LETTER. ALL INSTALLATIONS
SHOULD BE IN ACCORDANCE WITH THIS ILLUSTRATION
Figure
AN3C6A BOLT
MS20500-1032 NUT
645006-59
CLAMP ASSY
(REF)
VIEW LOOKING INBD
2.
Page 3 of
4
5.
and adjust strut assemblies, as necessary,
Position exhaust stack to center of cutout in engine cowling
with a minimum clearance of 0.50-inch
cutout
in
centered
the
position
to secure exhaust stack outlet in
to relieve all possible installation
exhaust stack clamp assembly and all nuts as required
and
tighten
pre-load.
engine.
6.
Install upper cowling
7.
Fill out and mail
8.
on
Compliance Card and specify
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
NO.
NONE.
that Part II has been
accomplished.
maintenance records
RECORD COMPLIANCE: Make appropriate entry inairplane
Installation",
Stack
"Exhaust
Support
entitled
4
dated
1980,
April
No. SL-112-29A,
(date)
Page 4 of 4
PartIIaccomplished
(date)
as
follows: Service Letter
Part I
accomplished
s
I~
a
"I
;li
Rockwell International:
General AviatiPn Divi~ion
Berhany. Oklahoma 73008
3 Septelnber 1978
FUEL PRESSURE SNUBBER INSTALLATION
SERIAL NO’S. 13000 THRU
112TC,
13091.
MODELS AFFECTED:
MODEL
PREVENT FLUCTUATION OF F’UEL PRESSURE GAGE.
COMPLIANCE:
DURING NEXT 100-HOUR INSPECTION OR ANNUAL INSPECTION.
nttta
IF ANY PROBLEMS ARE ENCOUNTERED WHILE: COMPLYING
WITH THIS SERVICE LETTER, CONTACT YOUR NEAREST
COMMANDER REGIONAL SERVICE MANAGER (REFERENCE
SERVICE INFORMATION NO;
SI-123).
A
P MECHANIC OR
APPROVAL:
FAA WA SW-2 Approved.
TWO
EQUIVALENT.
(2) HOURS.
comply with this Service Letter may be obtained asa kit through your nearest
Reference this Service Letter, aircraft model and factory Serial
at
no charge.
Rockwell Commander Distributor
the followingl
Immber when ordering Service Letter No. SL-112-30 kit consisting of
PARTS DATA:
Parts
rt~uired
to
CODE NO.
DESCRIPTION
PART NO.
QTY
1
ea
1BAHXX
Pressure Snubber
1
ea.
615049-55
Tube
1
ea.
Instructions
1
ea.
Assy
4282990
Compliance Card
NONE.
SPECIAL TOOLS:
1.
Remove and discard
eldsting fuel pressure line from engine firewall
to manifold
pressure/fuel
pressure
gage.
existing elbow from pressure port of manifold
2.
Remove
3.
Apply teflon tape
pressure/fuel
pressure gage.
to threads of 1BAHXX pressure snubber and install snubber in pressure
port Of manifold
pressure/fuel pressure gage (see Figure 1.).
4.
Apply teflon tape to threads
5.
F’ill out and mail
of
Compliance
existing elbow, removed
in
step 2., and install: elbow and 615049-55 tube
Card.
Page 1 cif 2
SEIIVICE
NO. SL-112-30
615049-55 TUBE: ASSY
1SAHXX PRESSURE SNUBBER
MANIFOLD
II-
EXISTING
(REF)
---FUEL
VFllr
PRESSURE/
FUEL PRESSURE GAGE
VENT
LINE
(RE Fl
VIEW LOOKING AF7
I
VIEW LOOKING INBD
EXISTING ELBOW
(RE Fl
Figure
ELECTRICAL LOAD::
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANCE.
incorporated
i.
Catalog changes required by
change/revision.
RECORD COMPLIANCE:
Service Letter
St-ll2-SO, dated 3 Septemberl978, entitled "Fuel Pressure Snubber Installation", accomplished
No.
(date)
ii’;
Page 2 of 2
´•n.Y
1 F IIUSLlb~ 141~
1~ e ~s, ~s
n
General Aviecion Divieion
5001 North Rockvvell Avenue
Belhany. Oklahoma 73008
SERVICE LETTER NO. SLr112-´•31
24
September 1976
DEFROSTER VALVE COVER REPLACEMENT
MODEL
MODELS AFFECTED:
112, SERIAL NO’S 381, 383,
384 AND 386 THRU 474.
DE FROS?’ER VALVE COVER ASSEMBLY MAY HAVE A DE
FECTIVE WELD.
THIS SERVICE LETTER IS BEING ISSUED TO CORRECT THIS SITUATION.
COMPLIANCE:
NOTE
TF ANY PROBLEMS ARE ENCOUNTERED WIIILE COMPLYING WITH
REGIONAL SERVICE MANAGER (REFERENCE SERVICE INFORMA-
SI-123).
TION NO.
A
P MECHANIC OR
APPROVAL:
FAA DOA SWr2 Approved.
ONE
(1)
EQUIVALENT.
HOUR.
comply with this Service Letter may be purchased as a kit through your
$32.52 (A). Reference this Service Letter, aircraft model and
when
Service
Letter
No. SL-112-31 kit consisting of the following:
number
serial
Ordering.
factory
PARTS DATA:
Parts
required
to
nearest Rockwell Commander Distributor for
NOTE:
Price
subject to change without notice.
QTY
PART NO.
DESCRIPTION
1
48072-501
706 (MIL-S-38249,Type I)
Cover Assy
Sealant (1/2 pt
Service Letter No.
$L-112-31
Instructions
ea.
1 ea.
1 ea.
COPE NO.
can)
00~5´•658
NONE.
SPECIAL TOOLS:~
1.
Remove upper
2.
Disconnect flex ducts from defroster valve cover,
3.
Remove and discard
4.
Install 4$072-501 defroster valve cover assembly using elcisting hardware and seal around outer
perimeter of cover assembly with Coast Pro-Seal 700, MIL-S-38249, Type I (see Figure 1,).
5.
Reconnect e)uist;ing flex ducts to
6.
Ileinstall upper engine
engine cowling.
eldsting defroster valve
new
cover
defroster valve
cover
assembly using e~dsting clamps.
cowling.
Page 1 of 2
SERVICI1: LETTE:R NO. SL-112-31
E"rrrm~
!a-
cr’
EXISTING CLAMP AND
FLEX DUCT
jo
(REF)
o.~
ca-
II
U
I
C$9
/~Bb(I
II
II,/
’~J´•
EXISTING CLAMP
(REF)
EXISTING FLEX
DUCT (REF)
EXISTING HARDWARE
REMOVE AND REPLACE EXISTING
DEFROSTER COVER ASSY WITH
NEW 48072-501 COVER ASSY
Figure I.
ELECTRICAL, LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
The Illustrated Parts Catalog change required by this document will be
at the next scheduled change/revision,
incorporated
Service
SL^112-31, dated 24 September, 1976, entitled "Defroster Valve Cover Replacement", accomplished
RECORD COMPLZANCE:
Letter No.
(date)
Pane 2 nf 2
O´•n´•r´•~ Aviation Divi~ion
Berhany. Oklahoma 73008
21 October 1976
TAKEOFF AND LANDING CHECKLIST PLACARD INSTALLATION
112TC, SERIAL NO’S
13000 THRU 13076 AND 13078 THRU 13149.
MODELS AFFECTED:
MODEL
TO PROVIDE PLACARDS AS DEFINED ZN THE MODEL 112TC PILOT’S
OPE RATING HANDBOOK.
COMPLIANCE:
WITHIN 25-HOURS AFTER RECEIPT OF THIS SERVICE LETTER AND
PLACARDS.
WOTE
IF ANY PROBLEMS
THIS SERVICE
ARE
ENCOUNTERED WHILE COMPLYING WITH
REGIONAL SERVICE MANAGER (REEERENCE SERVICE INFORMATION
NO.
SI-123).
OWNER/OPERATOR
APPROVAL:
FAA DOA SW-2
FIVE
(5)
Approved.
MINUTES.
Parts required to comply with this Service Letter are furnished at
Aviation Division and consist of the following:
General
International,
PARTY DATA:
QTY
PART NO.
DESC Rli~TION
1
ea.
1
1
ea.
49307-245
49307-247
Service Letter No.
Placard
Placard
Instructions
ea.
no
charge by Rockwell
SL-112-32
NONE.
SPECIAL TOOLS:
1.
Remove and discard
elcisting Takeoff
and
Landing
Checklist
placards installed
below
engine gage
clusters.
WOTg
If removal of elristing
placards
is
difficult, place
new
placards
over
elcisting placards.
2.
Install 49307-247 placard on instrument
and fuel quantity indicators).
3.
Install 49307-245
sub-panel
below left
engine gage
placard on instrument sub-panel below right engine
temperature, cylinder head temperature and rudder trim indicator).
cluster
(voltmeter,
gage cluster
toil
ammeter
pressure, oil
Page 1 of 2
r
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
NONE.
Senrice Letter
RECORD COMPLIANCE: Make appropriate entry in airplane maintenance records as follows:
accomPlacard
Checklist
Installation",
and
’Takeoff
entitled
21
Landing
October 1978,
No. SL-112-32, dated
plished
Page 2 of 2
(date)
General Avietion Divbion
5001 North Aockwell Avenue
Bechany. Oklahoma 73008
4 November 1976
ANTI-COLLISION LIGHT RESISTOR INSTALLATION
MODEL
MODELS AFFECTED:
112TC,
112, SERIAL NO’S 381 THRU 484, AND MODEL
SERIAL NO’ S 13000 THRU 13067.
no~a
If airplane has
disregard
optional
flashing
lower
beacon
installed,
this Service Letter.
POSSIBLE CONTINUOUS ILLUMINATION OF FLASHING BEACON WHEN
AIRPLANE IS EQUIPPED WITH ONLY THE VERTICAL STABILIZER
BEACON.
COMPLIANCE:
DURING NEXT 25-HOURS TIME IN SERVICE.
WOIE
COMMANDER REGIONAL SERVICE MANAGER
FAA DOA SW-2
ONE
(1)
P MECHANIC OR
A
APPROVAL:
(REFERENCE
EQUIVALENT.
Approved.
HOUR.
with this Service Letter may be purchased locally or may be purCommander Distributor for $12.17. Reference this Service
Rockwell
through your nearest
aircraft model and factory serial number when ordering Service Letter No. SL-112-34 kit consisting
PARTS DATA:
chased as a kit
Parts
required
to
comply
Letter,
of the following:
Price
aubiect
to
change without notice
PART NO.
DESCRIPTION
ea.
0600E
ea.
AN960D10
Ohmite Resistor
Washer
5 ft.
M5086/1-18-9
Wire
2
ea.
1
ea.
Terminal
2
ea.
MS21044N3
MS25036-103
MS35207-263
1
ea.
Service Letter No.
Instructions
QTY
2
2
(100 Watt,
3
Ohm)
Nut
Screw
SL-112-34
SPECIAL TOOLS:
NONE.
1.
Gain access to
fuselage frame
at Station 205.00
through baggage compartment
door.
Page 1 of 2
SERVICE LETTER NO. 8~1-112-34
2.
Remove upper and lower center aft bulkhead
3.
Disconnect
4.
battery
from
airplane
electrical
panels from baggage compartment.
system.
Locate, drill and install 0600E Ohmite resistor (or equivalent 3 Ohm, 100
(see Figure 1.).
Watt
resistor)
on
fuselage
frame
Step 4.
airplane electrical system (see Figure 1.).
5.
Connect resistors installed in
6.
Reconnect
7.
Reinstall upper and lower center aft bulkhead
battery
to
airplane
to
electrical system.
panels
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
in
baggage compartment.
Catalog
and
Airplane
Maintenance Manual
required by this document will be incorporated
changes
change /revi sion
Make appropriate entry in airplane maintenance records as follows: Service Letter
RECORD COMPLIANCE:
No. 8L-112-34, dated 4 November 1976, entitled "Anti-collision Light Resistor Installation", accomplished
(d ate)
W.L.
1.00"
\50.0
t
0600E OHMITE RESISTOR
(2 REQ’D)
(100 WATT,3 OHM)
MOUNTED ON FWD AND AFT SIDE OF
FRAME AT F. S. 205.00
0. 190"/0. 194" DIA. HOLE
MS35207-263 SCREW
AN960D10 WASHER
MS21044N3 NUT
(2 PLS)
VIEW LOOKING AFT AT LOWER
RIGHT SIDE OF FRAME AT F.S. 205.00
MS25036-103
TERMINAL
M5086/1-18-9
WIRE
GND-18
2
L29C18
M5086/1-18-9
VENDOR FURNISHED
0600E OHMITE RESISTORS
OR EQUIVALENT 100 WATT, 3 OHM
FLASHER BEACON
POWER SUPPLY
Figure
Page
2 of 2
I.
WIRE
(REF)
ei´•i;-´•i
I
I~ RackwelllnternBno~l
´•Ir~A
´•4r
~Bi r
imss
~w,
ed
~L
General Aviation
Divillion
Bethany. OklahomB 73008
7January 1977
CARBURETOR REPLACEMENT
112TC,
MODELS AFFECTED:
MODEL
PROVIDE AN IMPROVED CARBURETOR.
COMPLIANCE:
NOIE
NO. SI-123).
A
P MECHANIC OR
APPROVAL:
FAA DOA SW-2
TWO
PARTS DATA:
Parts
required
(2)
EQUIVALENT
Approved.
HOURS.
to
comply with this Service Letter may be ordered as a kit through your nearest
Carburetor P/N LW-15504 will be supplied on an exchange
$687.70 A.
basis. A credit of $687.70 A will be issued upon receipt of old carburetor P/N LW-14689, a properly executed
Warranty Material/Labor Adjustment Request Form and a Compliance Card. Reference this Service Letter,
aircraft model and factory serial number when ordering Service Letter No. SL-112-35 kit consisting of the
following:
Rockwell Commander Distributor for
WOtE
Price
subject
to
change without
QTY
PART NO.
DESCRIPTION
49307-99
49307-103
LW-15504
Placard
1
ea.
1
ea.
1
ea.
1
ea.
1
ea.
notice.
CODE NO.
Placard
Carburetor
Compliance
Service Letter No.
2564573
Card
Instructions
SL-112-35
SPECIAL TOOLS:
NONE.
1.
Remove
2.
Install. LW-15504 carburetor
3.
Remove and discard
4.
Install 49307-103
existing carburetor
and fuel quantity
from
as
airplane
outlinect
eldsting Takeoff
placard
on
indicators).
ul
and
instrunlent
as
outlined in the
the
Airplane
Airplane Maintenance Manual,
Maintenance
Landing Checklist placlards
sub-panel below
Manual,
Section IV.
Section TV.
installed below
Il´•fr: engine gage cluster
cnhine
jia~e cla´•;ters.
(voltmctel´•,
i
placard on instrument sub-panel below right en6ine gage
temperature, cylinder head temperature and rudder trim indicator).
5.
Install 49307-99
6.
Verify Pilot’s Operating Handbook Revision dated 7 January 1977
7.
Verify proper Operation
8.
A Rockwell
Operating Handbook
of en~ine per Pilot’s
Distributor/Dealer
must fill out
a
cluster
toil
pressure, oil
is inserted in Manual.
as
stated in Sections N and X.
Warranty Material/Labor Request Form and the Compliance
International, Bethany, Oklahoma, using the standard
Card and return the old carburetor to Rockwell
parts
return
procedure.
WOTIE
(2) hours labor
accomplished.
A maximum of two
that
step 8.
is
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
incorporated
Make
RECORD COMPLIANCE:
No. SL-112-35, dated 7 January
will be allowed
provided
Catalog change required by
change/revision.
appropriate entry in airplane maintenance
1977, entitled "Carburetor Replacement",
records
as
WOTE
When this Service Letter has been complied with, it is no
longer necessary to comply with Rockwell International
Service Letter No. SL-112-32.
Fa~e 2 of 2
follows:
Service Letter
i
*t
:’i
t:´•
1:
~,´•y P:i";
;:i
~APk
General Aviation Divillion
5001 North Rock~Nell Avenue
Bec),any. Oklahoma 73008
25 February 1977
IGNITION SWITCH BUS BAR REMOVAL
11ZTCA, SERIAL NO’S 13000
THRU 13189.
MODELS AFFECTED:
MODELS 112TC and
SERVICE
TO PROVIDE EASIER ENGINE STARTING AND HELP PROLONG
LIFE OF STARTER.
COMPLIANCE:
WOtE
COMPLYING WITH
NO.
SI-123).
P
A
APPROVAL:
FAA DOA SW-2
ONE
PARTS DATA:
NONE.
SPECIAL TOOLS:
NONE.
(1)
MECHANIC OR EQUIVALENT.
Approved.
HOUR.
1.
Assure that the master switch is in the OFF
2.
Remove
ignition switch
bus bar located
on
position.
ignition switch
between terminals R and GRD
(see Figure 2.).
REMOVE BUS BAR BETWEEN
TERMINALS "R" AND ’%RD"
a
i-------- IGNITION SWITCH
(REF)
VIEW LOOKING AFT
Figure
1.
I’;\t~c!
1 of ’L
E: L.E:C’I’ IUC AL
NO CHANGE.
LOAD:
W ~´•:IC;H1’ AND UALANCE:
NO CIANGE.
I’III~LICATIONS AFFECTED:
The
be
N(I.
CC)hllPLIANCE:
dated 25
SL-112-36,
I’age 2 ~,f 2
Airplane Maintenance Manual Change required by this
incorporated at the next scheduled chsnge/revision.
document will
Service Letter
(date)
February 1977, entitled ’Ignition Switch Bus Bar Removal", accomplished
;II
i.
:i
:’i
1:i
"li: :dilt5-,
I~
i;
Rockwelll Internaaional
;;i;
~.Ii
i:
:r
;"ii
Genural Avlarlon Dlvi,lon
I;
5001 Norrli Hockwell Avel,us
setllsr~v_
i~"":b
13008
SERVICE ZETTER NO.::L--112-37
29
April
1977
ENGINE TO AIRFRAME EROUND CABLE INSTALLATION
MODEL
MOUELS AFFECTED:
HI;:ASON FOH. PUEILICA’I’ION:
13000 THRU
13149.
TO INIPROPER/
TO PRE:VENT MAGNE’rIC COMPASS INTERFER~NCE: DUE
INSUFFICIENT BONDING OF ENGINE TO AIRFRAME GROUND. THIS HAS
’r0 ACHIEVE
BEEN NOTED ON CERTAIN AIRCRAF’I’ I3Y BEING UNABLE
PFIOPEH. COMPASS HEADINC;S.
COMPASS EltnOIt
W17’HrM NE:XT 100-HOURS TIME IN SERVICE IF STANDBY
DEGREES.
TEN
WITHIN
(10)
COMPE:NSATF:I)
UE:
CANNOT
COMI’LIANCE:
NOT6
THIS SERVICE
IF ANY PROUI~EMS ARE ENCOUNTERED WZITLE COMPLYING WITH
DISTRIBUTOR
COMMANDER
ROCKWELL
LE7’TER, CONTACT YOUR NEAREST
OR YOUR ROCKWELL COMMANDER REGIONAL SERVICE MANANGiER.
UY WIIOM WORK WILL, BE: ACCOMPLISBED:
r) MECHANIC OIZ
A
A I’PRC)VAL
FAA DOA SW-2
ESTIIL~IATEI) MAN HOUIZS:
FOUR
EQUIVALENT.
Approved.
(4) HOURS,
be purchased through youI nearest
Parts required to corrlply with 1Ns Service L,el;ter may
I)AR’rS I)ATA:
Service Letter, aircraEi nlodel and factory serial
12ockwell Cotnmander I)istribulor for $22.0’3. Reference this
of the following:
nulrlber wherl ordering. Service L,ttlter No. SL-´•112-37 kit consisting
Price rul,jecr
to
chanye without notiL~
QTY
PART NO.
I)ESCRIPTION
1
ea,
1
ea.
43780-’3
43780-17
Clip
cJLip
1
ea.
48030-450
c;round Cable
CODE NO.
CONSISTING OF:
’30 in.
Z
pa,
Cable
Terminal
M5086/2-6-9
MS25036-´•120
NIS25036-121
1 ea.
]15111A1
’30-in.
AN3-121\
i
ea.
Terir~insl
Sleeving
Uolt
0267000
0505000
1555000
1567000
ea,
hM4-5A
Bell.
ea.
ANn60D10
Washer
%ea.
AN960D41f
ANRGO-5!8
1~8213(374´•-05-04
Washer
3
ea.
MS~1044N3
1
Nut
2’; i 21 4
ua.
NIS::.1044N´•1
3
M:jZ~ !11 9LX;´•2
1
ea.
Clamp
Clamp
Clnlnp
Clamp
Clamp
%74(1000
ea.
1
3
Cn.
Z
en,
2
tia.
3
o~.
I
ea.
2
ea
1
MX2!319115
j~ilS%: 9:
1
c;i.
NIS21~19117
NISBI. 919112
Washer
l!j37C)00
13olt
2706829
Nut
2’719213
MS27739-1-0ti
MS3 5338-´•4 5
Screw
N1~1;3 548!3- 20S
C ro nlmet
Lock wash e r
’,;i)
i.74b~%:(,
%Hn’4;1´•i~
2 i, oT!
1
Spacer
NAS´•2:)1,1:,3-45
Se PvicC I~ntter No.
2’74
S L,- 1 1 2- 37
711:$1 TuCtic)llS
PRf~e 1. of 6
SERVICE LETT~K NO. SL-112-37
IEEMOVE: EXISTING
C;ROUNZ) CABLE
L7
\r
VIEW 100KrNE AFT AT TOP OF ENGINE
AND FWB SIDE OF FIREWALL
Figure
1.
DE:C;AUSSINCI ZINC;.
SI’ECIAL, ’1’OOLS:
AC COM:PI,IS[-IMEN’I’ INSTRUCTIONS
i.
A~;suri! that
2.
Hernove upper
master switch is in tt~e OFF
airplane
clll´•jne cowling.
Renlcjve lower en~ine
I.
cowlin6r
Hcrnove left d(-,or scuff
inlel´•ior side
position.
as
outlillect in Ule
Airplatlc! Mairllc?nance Manual,
plate and cl~,c,r jaml~ moulding
a.s
Section IV.
necessa.r´•y to facilitate removal elf IcL‘t f~,l;\r/nrcl
panel.
5.
Ittenlove Icel: forwnrd interior side
A.
I´•Eenlove Rlld discard
existinK en~ine ground strap (sec Figur´•e i.).
i.
Neln~jvc‘ and tliscard
existing gl‘c,lli!nel frtjnl left aft baffle :Issembly and install MS35411~-20S grc,l;ln~et
(sec FYgure 2.).
panel.
SEHVICE I,E:TTER NO.
SL-112-37
--1
’OI
OI.
:~33
48030-450 GROUPJD CARLE
AND P3A6 S’l’hnTEn WLILE:
ALTEI~NATOR
6A4P)’FER(
wInE:
IZEPI,ACE EXIST~C; CTZOMMET
WITH MS35489c20S GROMME’JI
LE:F?’ I,OWEW. IZEAR ENGLNhl
c
UAFFLE
(REI’)
VIEW LOOKING AFT AT LEFT BAFFLE
AND LEFT UNDERSIDE OF ENGINE
Figure
2.
STARTEIZ
,ZI,’T~RNATOIZ
/i
i
(REF)
MS2191YH7 CLAMP
MS21919H6 CLAMP
P4AG ALTE:RNA’I’OR
(REF)
48030-450
?I
CI~AMI’r I-1X-‘7GTZOU’ND
Q:ii
.J_OL:;-b,
cn ar~E
M821(319H5
rzxrs?´•lr~c;
C bhnZI’S
4378()-17 GL~LI’
M1320071-05-04 BOLT
ANStiO-51G WnSllrIE:I2
MS2191’3H7 CLhMP
hI:jS5~38-4Ii L(X:KWASHER
MS20074-05-04 130-,
AN960-~lri WR.-;HI1R.
MS3533~-´•15 1!X’KWhSHEn
di
VIEW LOOKING UP AT SIARVER ANI~ ALTERNATOR
~_._.._..._.._j
Figure
3.
l’ii:´•´•´•
~,r n
LE?’?‘EIINC),
SL,-112-37
F’Il1EWALL STA. (jZ. ijg
(EZEF)
STA.
,j
LEFT UPPEH
STA.
8’s. 00
STA.
62. 50
27. 50
ENCrLNE MOUNT
(REF)
48030-450 GROUND CABLE:
AND P3AG STARTER W~E
EXTSTIN
;rrll
I CLAMP
(REF)(2
PLS)
C
P4A8 ALTERNATOR
WTRE
EXISTING
CLAMP (2
I
PLS)
RIEMOVE EXISTING CLAMP
AND ]CNSTALL MS21’319Ii12
CLAMP
I,
VIEW FROM LEFT SIDE AT ENGINE AND FIREWAIL
Fiyure
i!.
Irlstalll 43’7N0- 17
(2 PLS)
clil~
on
4.
en~rj ne wit,i rv15%0074--05-04 bult, il.ri~6O- 5! 0 washer and M535338-45 lockwaslii-r
(sce E’il~urc´• 3.).
if.
´•28030-450 ground cnble
tj,,l, wili: al.ternalor
]o.
c,n
engine with MS20074-05-04 holt, AN960-51B wnsher and MS35R311´•-45
gl´•ound r:;tbli:;:tlt to Brt´•wall witl~ exisl:j!lg
wire P4AG in tlie iill~lle:Ll’eiZ.
I.iickwastlel alld I´•oute
P3A6 starter
L,,1:a!;, iirill and inutall 43780-5 clip with MS2047(1AD3 ri~et (see Fi~ure
wire,
5,).
but Illalnta.ill
SERVICE I,ETTER NO.
S’rA.
STA.
27.50
62.50
SL-112-37
ST’A.
85.00
43780-5 CLIl~
STA.
S’I‘A.
80. 30
STA.
02. 50
85. 00
MS21(31(3UC;4 CI~AMP
MS27039-1-08 SCREW
hN960D10 WASHER
MS21044N3 NUT
A
7(:LII’AND
CLAMP
(2 PLS)
-~‘--‘-7-----
i~/
Y,
4803U-41i0 C;IZOIIND
CAU~E
MS21t119;3G4
a~
CI~AMP
1.25"-/
ANS-1LA BOL.I.
NAS43Dr)3-44i SPACER
AN960U10 WASHER
MS21044N3 NU’r
ji
;e
j
j
1. 25"
(2 PLS)
--7A
AN9(iOD416 WASHER (2 REQD)
M521044N4 NUT
VIEVV A-A
VIEVI~E LOOKING INBOARD AT LEET SIDE
Figure
II.
I(oute 480:t0´•-450
~N4-5A
bolt,
gruuntl
ca.ble
S.
through engirle firew~ll anil att::~ch to luselage frallle,;~l
(2 places) and MS210491´•I´•.i crut (see Figure 4. and 5.).
Stl!
,:’i´•:’r,~ \i´•ltil
AN9GOD416 wsskcr
NOTE
Maint~Lin
sel,aration
wire: ill cabin
12.
betwsen 48030-11110
clrounl cable and P2UB starter
area.
In!;l;~L1. MSZ191’Jr)(;4 cla.lnp (3
fj.
c;lt,li! (sce
p],zces)
between ~usel;cl:r S\;1.
Ci2.5C) nlltl S1:;~.
t(O. 30 tc,
sul,l,ill~t I:´•l’i’L´•i./!
P;i~:e 5 (,1: tj
SE:F(:VIC’E LE:T’I’E:H NO. SL-l.liC-37
13.
eKisiing clarups
14.
enE~lle collll,~rtlrienlnl and install
MS2191y~l
new
V
as
ill
showo
7()(), NT1L-S-3U2r1(3, ’I’yl,e
wire:;.routcd throuyh li~eL\I;I11 1~runlrnet with I!rc,~ct;tl
~t´•:li
iiy iLi
ill
1
or
al Fnt)
foSw;ird
inler´•ior side
panel,
door
jamb nlouldin~
1(5.
I~e:illstall Icft
tCi.
Reinstnll upper and lower
17.
S~villg Ille colul,:1~s, with airplane on a corllpass rose,
Set:llon VIII, under Map~elje Colllpass Compensation.
cc,wlillg;ls outlined
hirpl,ule
in the
as
and Icfl door scufl:
Nlaintcnauce
plate.
Manual,
Section IV.
outlined in Ihe Airplarltl Nlainl~-’narlce
WOtlE
Any
18.
Ii compass error is
folio ws:
more
than
error
less than
10 degrees,
"10 degrees
is
acceptable.
demag~net;iee engine
lirewall. with
a
degaussin~ ring
as
CAUTION
A/1 degaussing must be done by
performing such worl~,
a
repair´•
thor0u~hly experienced
elation
in
ii.
r-lelnuve ma~netic compass from
i,.
Remove upper
airpla~le.
enbine cowling.
degaussing ring over area shown below.
circular motions approldmately four (4) times,
Place
c.
Turn
degaussing ring ON, move over area in slow
move degaussing ring away from air´•pla.ne
and then
structure.
I/
AREA TO BE
DE1MAGNET/ZED
wear
130 Ilot t~r.n
F.
lieinstall magrlctic: cc,mpass and upper en~ine cowling.
e.
12epeat step 17.
tct assure that
:;I.-11~´•´•´•37,
id;ltt:~j
dated 2(J
coulpass iuterference
i
structur´•e.
cists.
NO CILI\NG E.
LOIIT BNn nALANCE:
C:C)MPI.,IANC:L´•::
no
airpl´•a""
NO CHANC;E.
t;C1~IT.I(I:XI’IONS AFFEL‘?’E:D:
N~,.
away from
d.
LOB1):
\jv
degaussing Ilnl~ OFF’ urltil well
will L,c~
l’he Illustratr?d Parts C:atalog chanl~e recluil´•ed by tills doculllent
scheduletl
c!larll5o/’rc?vision.
next
the
at
incolp"’"ted
alJl,ropriate entr´•y
A~,ril 1077, entitled
Make
in
airplane
maintrtnancc‘ rc!corcls
to Airfranlu Ground Cat,le
as
follows:
Installation",
St!xvic´•e I,~´•
i4%
oanaral Aviation DiviJon
BethSny. Oklahoma 73008
9 August 1977
LANDING GEAR RETRACT CYLINDER RETAINER
AND/OR LOCKWASHER INSTALLATION
MODELS 112TC
MODELS 112 AND 112B, SERIAL NO’S 3 TIIRU 544 AND
AND 11%TCA, SERTAL NO’S 13000 THRU 13195.
MODELS AFFECTED:
REASON FOR PUBLlCATION:
OF THE MAIN
THE RETAINER IS TO PREVENT LOSS OF ATTACHMENT
LOOSE ZN
BECOMES
BEARING
IF
CYLINDER
RETRACT
LANDING GEAR
OF ROD
END. THE LOCKWASHER IS TO PREVENT ROTATING
CYLINDER
LANDING GEAR RETRACT
END NUT ON NOSE LANDING GEAR AND MAIN
CYLINDERS.
WITHIN NEXT TWENTY-FIVE
COMPLIANCE:
(25)
HOURS TIME IN SERVICE.
WO’IE
COMPLYING WITH
ROCKWELL
THIS SERVICE LETTER CONTACT YOUR NEAREST
OR YOUR ROCKWELL COMCOMMANDER
DEALER/DISTRIBUTOR
MANDER REGIONAL SERVICE MANAGER.
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
TWO
EQUIVALENT.
Approved.
(2) HOURS.
Letter may be ordered through your nearest Rockwell
PARTS DATA: Parts required to comply with this Service
this Service Letter, aircraft model and factory serial
Reference
cost.
at
no
Dealer/Distributor
Commander
of the following:
number when ordering Service Letter No. SL-112-39 kit consisting
112TC and
Models 112 and 112B, Serial No’s 3 thru 544 and Models
13000 thru 13185.
Model 111TCA, SerialNo’s 13186 thru 13195.
Kit No. 1
Kit No. 2
Kit No. 1
Kit No. 2
QTY
QTY
2
1
ea.
2
1
1
ea.
ea.
ea.
ea.
1
2
ea.
1
1
ea.
Serial No’s
DESC RIPTION
Retainer Washer
PART NO.
795003-1
M535333-41
M535333-42
ea.
112TCA,
Lockwasher
Lockwasher
Compliance Card
ea.
Instructions
AIRPLANE JACKS AND A STAKING TOOL.
SPECIAL TOOLS:
airplane
outlined in the Airplane Maintenance Manual, Section n.
1.
Jack
2.
Disconnect
3.
Loosen rod end nut and remove rod
4.
retract cylinder and
Install MS35333-41 lockwasher and existing rod end on nose landing gear
1.).
Figure
retract
(see
of
threads
cylinder
and rod end all the way down on
5.
Check drag brace assembly at knuckle
as
nose
landing gear retract cylinder
at
landing gear trunnion.
end,
area
to assure that
drag brace is resting
on
run
nut
stop.
Page
1 of 5
´•---------´•--------I-´•
IERVICE LETTER NO. SL-112-39
O
EXISTING NUT OZEF)
ER ROD
(REF)
-41
LOCKWASHE R
Figure i.
6.
Extend cylinder piston to m~udmum length and
adfust rod end hole to 0.250
trunnion for cushion. Finger tighten nut against cylinder rod.
7.
Realign hole
in rod end with hole in trunnion and install
0.03)
inch
past hole in
eldsting hardware.
IYOlr
The
8.
Collapse
nose
drag stay of
landing
gear
pounds against cylinder rod
the
drag brace assembly should be resting
on
the
stop.
necessary to gain access to rod end nut and torque nut 60 to 85 inchand bckwasher while holding cylinder rod
securely.
ae
9.
Remove bolts attaching the Inboard end of the left and
right main landing gear retract cylinder to the
side brace assemblies.
10.
Loosen rod end nut and
11.
Install MS35333-42 lockwasher and erdstfng ~od end
remove
rod end.
(see Figure 2.).
on
left and
right
main
landing
gear retract
cylinder
WOlt
On Models 112TC and 112TCA with Serial No’s 13186 thru
proceed to 8tep 13.
12.
On Models 112 and 112B with Serial No’s 3 thru 544 and
Models 112TC and I1OTCA with Serial No’s
13000 thru 13185, proceed as follows:
a.
Remove bolts attaching outboard end of Left and
right main
the landing gear trunnion and remove
cylinders.
an
Page 2
13195,
of 5
landing
gear retract
cylinders to lug
SERVICE LETTER NO. 6L-112-39
EXISTING
NUT
CYLINI)ER
ROD
(REF)
26635333-42
UX~KWASHER
P X/
795003-1
RETRACT
CYLMDER
RETAWING
WASHER
(REF)
EXISTING
WASHERS
(REF)
CONE SPACER
(REF)
TRUNNJON
ASSY
Z
(REF)
EXISTING BOLT
(REF)
figur~
b.
Inspect cylinder
figure 3.
end
plug bearings
2.
to assure that the
bearings
are
properly
staked as shown in
WO’IE
There should be six (6) stake marks equally spaced on each side of
bearing. Staking should deform the metal next to the bearing.
c.
If
d.
If bearings
bearings
are
properly staked, proceed
to
step 12.e.
are not properly staked, hand stake bearings six (6) equal spaces around bearing
(see Figure 3.) using a staking tool that conforms to dimensions shown in Figure 3.
sfOTg
Fabricate
bearing
a
block from
when
1/2-inch phenollc
material for backing up
staking (see Figure 3.).
Page
3 of 5
8ERVICE LETTER NO. 6L-112-39
STAKING TOOL
,025"
.020"
0.015" MINIMUM LIP
I
0.05"
.005"
T6ibii RA"US
I
RETRACT
CYLINDER
´•´•3´•i~´•
(RE Fl
BEARING
TYPlCAL TOOTH SECTION
(REF)
0.125"(TYP
6
PLS)
I1~T
I
13.00"
HOLE
0.65"
2.00"
4.00"
FABRICATE FROM 0.50" PHENOLIC
MATERIAL AND USE FOR BACKING
UP BEARINGS WHEN STAKING
Figure 3.
e.
Reconnect the left and right main landing gear retract
cylinders to lug on the landing gear
trunnions with existing hardware and add 195003-1 retainer washer
(see Figure 2.).
i.
Proceed to
step 13.
13.
Iiun rod end and nut all the way
14.
Check the main
on the stop.
15.
Push retract cylinder piston all the
way in the cylinder
short of hole in drag brace assembly for cushion.
16.
landing
on
threads of the main landing gear retract cylinder.
gear aide brace
assembly
at knuckle
area
to
assure
that the side brace is
resting
body and adfust rod end hole to 0.30
0.03)
Finger tighten nut against cylinder rod end.
Align hole
Page 4 of 5
in rod end with hole in
drag brace assembly and install eldsting hardware.
inch
SERVICE LETTER NO. 6L-r12-39
I’
ROTS
The side
stay of the side brace assembly should be resting
17.
Torque rod end nut 95 to 110 inch-pounds against
securely.
18.
Perform
an
Manual,
Section VI.
Remove
jacks
19.
operational
from
check of the
airplane
the
rod end and lockwasher while
landing gear system
and fill out and mail
on
as
outlined in the
Complaince
stop.
holding cylinder
Airplane
rod
Maintenance
Card.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
YES
The Illustrated Parts Catalog changes required by this document will be
incorporated at the next scheduled change/revision.
Service
records as follows:
RECORD COMPLIANCE: Make appropriate entry in the airplane maintenance
Retract Cylinder Retainer and/or Lockwasher
Letter No. SL-112-39, dated 9 August 1977, entitled ’Zan$ing Gear
Installation", accomplished
(date)
Page 5 of 5
General Aviation DivLion
25 July 1977
SHAFT COLLAR INSPECTION AND MODIFICATION
FLIGHT CONTROL COLUMN SHAFT
MODELS AFFECTED:
MODELS 112 AND 112B, SERIAL NO’S 221 THRU 544 AND MODELS
112TC AND 112TCA, SERIAL NO’S 13000 THRU 13192.
DURING EXTREME COLD WEATHER THE CONTROL COLUMN SHAFT
COLLAR P/N 47355-1 MAY SHRINK IN SIZE. THIS SHRINKAGE CAN
INCREASE ELEVATOR CONTROL FORCES BEYOND ACCEPTABLE
LIMITS.
SLOTTING THE COLLAR WILL ELIMINATE THIS POSSIBILITY.
COMPLIANCE:
NOTE
YOUR NEAREST
OR YOUR
ROCKWELL COMMANDER REGIONAL SERVICE MANAGER.
LETTER, CONTACT
WITH THIS SERVICE
ROCKWELL COMMANDER
DEALER/DISTRIBUTOR
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
INSPECTION ONLY
EQUTVALENT.
Approved.
ONE
(1)
INSPECTION AND REWORK
PARTS DATA:
NOT APPLICABLE.
SPECIAL TOOLS:
0.010" FEELER
GAUGE,
HOUR.
THREE
(3)
HOURS.
0.005" STEEL SHIMS AND A HACKSAW.
i.
Check left and
feeler gauge.
right control columns for clearance between control column shaft and collar
Minimum clearance should be 0.010 inch.
using
a
NOTE
Collar is l.GO-inch
2.
long.
If clearance between control column shaft and collar is 0.010-inch
or
greater, proceed
to RECORD
COMPLIANCE.
3.
If clearance between control column shaft and collar is less than
retaining ring from
control column shaft
0.010-inch, proceed
as
follows:
(see Figure 1.).
a.
Remove
b.
Move control column full aft.
c.
Slide control column shaft collar aft away from control column mount.
Page
1 of 2
d.
Cut
a
slit in collar with
0.050-inch
a
hacksaw blade
or
equivalent cutting tool.
Maldmum width of cut to be
(see Figure 1.).
Ix;*l;"~;;"l
CAUTION
Insert
a
shaft to
e.
After cut
through
shim used to
f.
steel shim between collar and control column
protect shaft while collar
collar is
completed,
is
being
remove
all
cut.
rough edges from
collar and
remove
protect control column shaft.
Reinstall collar and retainer ring into control column shaft mount.
INSERT FEELER
RETAINER
RING
(REF)
d
GAUGE IN AREA
BETWEEN COLLAR
AND SHAFT
AFTI)
I
I
\I
ii
~J
COLUMN
SHAFT
(REF)
i
CONTROL COLUMN SHAFT
COLLAR (REF)
SLIT MAY BE MADE AT ANY
ANGLE UP TO 450 EITHER
SIDE OF THE SHAFT CENTERLINE
CONTROL COLUMN SHAFT
COLUMN SHAFT
COLLAR
Figure
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
NOT APPLICABLE.
I.
Service
RECORD COMPLIANCE:
Letter No. SL-112-40, dated 25 July 1977, entitled "Fllght Control Column Shaft and Shaft Collar Inspection
and Modi~fication" accomplished
(date)
Page 2 of
2
Roci<well International
Oaneral Aviation DiviriDn
Bethany, Oklahoma 73008
30
September 1977
RUDDER TRIM CONTROL ASSEMBLY INSPECTION AND MODIFICATION
MODELS AFFECTED:
MODELS 112 AND 112B, SERIAL NO’S 381 THRU 544 AND MODELS
112TC AND 11%TCA, SERIAL NO’S 13002 THRU 13108 AND 13151 THRU
13195.
TO IMPROVE RUDDER TRIM AND PREVENT THE POSSIBLE BOTTOMING
OF RUDDER TRIM SPRING AT EXTREME TRIM CONDITION.
COMPLIANCE:
WOTE
THIS SERVICE LETTER CONTACT YOUR NEAREST ROCKWELL
OR YOUR ROCKWELL COMCOMMANDER
DEALER/DISTRIBUTOR
MANDER REGIONAL SERVICE MANAGER.
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
PART I
TWO
EQUIVALENT.
Approved.
(2)
PART II-THREE
HOURS.
(3) HOURS.
Parts required to comply with this Service Letter may be ordered through your nearest
PARTS DATA:
Rockwell Commander Dealer/Distributor for: Part I, $5.86, Part I1, $17.79. Reference this Service Letter,
aircraft model and factory serial number when ordering Service Letter No. SL-112-41kit consisting of the
following:
PIICLI
IUt)JOC1
PART I
PART II
QTY
QTY
PART NO.
to
Change without notice
DESCRIPTION
Fitting
ea.
1
1
ea.
1
1
ea.
1
ea.
47482-RE1
565006-1
565007-1
1
ea.
1
ea.
ea.
Outer Spring
Inner Spring
Instructions
NONE.
SPECIAL TOOLS:
PART I
1.
Remove cotter
pin from eltisting nut
on
rudder trim control
assembly shaft and back
nut off threads
(see Figure 1.).
2.
Turn rudder trim control assembly knob counterclockwise until stop is contacted and then turn control
exactly six (6) complete turns and clamp a stiff straight edge to pilot’s rudder pedals.
knob clockwise
WOTE
With
a
straight edge clamped
position.
to the rudder
pedals,
the rudder trim will
be in the neutral
Page 1 of 5
3.
Check for 0.50
0.03)
inch dimension between rudder trim control
assembly fitting
and side
plate
(see Figure 1.).
4.
If dimension between rudder trim control assembly fitting and side
straight edge from pilot’s rudder pedals and proceed to Part II.
5.
If dimension between rudder trim control
straight edge from pilot’s
rudder
assembly fitting
and side
plate
exceeds
plate
is 0.50
0.53-inch,
remove
0.03) inch,
remove
pedals.
knob and
6.
Remove rudder trim control
7.
Disconnect forward shaft of rudder trim control
assembly
nut, loosened
in
step 1., from shaft.
assembly from top of pilot’s right
rudder
pedal support
assembly
8.
Disconnect rudder trim indicator cable from rudder trim control
control assembly from airplane.
9.
Disassemble rudder trim control
assembly
1
and discard
cnunow
CAUtlON
When
removing roll pin from
springs are compressed.
10.
Install
new
end
fitting,
assembly
and
remove
rudder trim
eldsting springs.
1
care
should be taken because
565006-1 inner spring and 565007-1 outer spring and reassemble rudder trim control
11.
12.
Reinstall rudder trim control
Reinstall
knob
e~dsting washers,
(see Figure 2.).
assembly
in
nut and cotter
airplane using elristing hardware.
pin,
removed in
step 1.,
13.
Reconnect rudder trim indicator cable to rudder trim control
14.
Check rudder trim indicator
15.
rig~jng
as
outlined in the
and rudder trim control
assembly
assembly.
Airplane
Maintenance
Manual,
Section VII.
PART II
1.
2,
Remove rudder trim control
assembly
knob and nut from shaft.
Disconnect forward shaft of rudder trim control
assembly from top of pilot’s right rudder pedal support
assembly.
3.
Disconnect rudder trim indicator cable from rudder trim control
control assembly from airplane.
4.
Disassemble rudder trim control
assembly
and discard
CAUtlON
~,uno*
When
removing roll pin from end fitting,
springs are compressed.
5.
Install
new
565006-1 inner
spring
and 565007-1 outer
assembly
and
remove
rudder trim
existing springs.
I
should be taken because
care
spring
and reassemble rudder trim control
bly (see Figure 2.).
6.
Page
Remove and discard
2 of 5
eldsting fitting from
rudder trim control
assembly bracket (see Figure 2.).
assem-
MS20470AD4
PILOTS RIGHT
---tl
rr~7l
RIVET
(4 PLS)
RUDDER PEDAL
SUPPORT ASSY
(RE: Fl
EXISTING BRACKET
(REF)
EXISTING FITTING
47482-RE1 FITTING
(PART I)
(PART II)
1100
RUDDER TRIM
i
INDICATOR
i
II
CABLE
I
I
,1
Ii’.
I
II
_I~ II
I
I
I
~c---RUDDER TRIM
CONT ROL
I
ASSY KNOB
EXISTING SIDE
I
(REF)
o.50"--tl
PLATES
I
CI
COTTER PIN AND
EXISTING NUT
Figure
i.
Page 3 of 5
EXISTING COTTER PIN
EXISTING FITTING
47482-RE1 FITTING
EXISTING CONTROL
(REF)
AND NUT
~n
/KNOB (REF)
jSb‘
(PART I)
(PART II)
EXISTING
WASHERS (REF)
0./
1-
SIDEEXIsTINe
RUDDER TRIM
CONTROL ASSY
c
EXISTING
ci
PLATES
SHAFT
(REF)
(REF)
EXISTING
END FITTING
(REF)
EXISTING
ROLL PIN
:e
(RE Fl
EXISTING
FORWARD
SHAFT
(REF)
565006-1 INNER SPRING
565007-1 OUTER SPRING
Figure
7.
Reconnect rudder trim control
2.
assembly forward shaft
to
top
of
pilot’s right
rudder
pedal support
assembly
8.
Place
9.
Install
eldsting
eldsting
washers and 47482-RE1
nut and knob
on
fitting
on
rudder trim control
rudder trim control
assembly shaft (see Figure 2.).
assembly shaft.
WOTE
Do not
10.
Turn rudder trim control
knob clockwise
51.
run
exactly
nut
on
threads until
fitting
is located and riveted to bracket.
assembly knob counterclockwise until stop is contacted and then turn control
(6) complete turns and clamp a stiff straight edge to plot’s rudder pedals.
six
Position 47482-RE1 fitting on rudder trim control assembly shaft to 0.50
Figure 1. and clamp fitting to rudder trim control assembly bracket.
in
Page 4 of 5
0.03)
inch dimension shown
i
Drill and install 47482-RE1
’12.
fitting
on
rudder trim control
assembly bracket with MS20470AD4 rivets
(4 places) (see Fiyre i.).
i
pin
rudder trim control
assembly shaft.
13.
Reinstall eldsting nut and cotter
14.
Reconnect rudder trim indicator cable to rudder trim control
15.
Check rudder trim indicator
16.
rigging
on
as
outlined in the
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
NO.
incorporated
RECORD COMPLIANCE:
No.
SL-112-41,
Part I
dated 30
assembly.
Section VII.
Catalog changes required by this document will
appropriate entry in airplane maintenance records as follows:
September 1977, entitled ’audder Trim Control Assembly Inspection
(date)
PartIIaccomplished
Make
be
change/revision.
Service Letter
and
Modification",
Page 5 of 5
General Aviation Divirion
7 October 1977
MANIFOLD PRESSURE GAUGE MODIFICATION
MODELS 112 AND 112B, SERIAL NO’S 3 THRU 544 AND MODELS 112TC
112TCA, SERIAL NOPS 13000 THRU 13195.
MODELS AFFECTED:
AND
TO PROLONG GAUGE LIFE AND PREVENT GAUGE FROM STICKING
AND BECOMING SLUGGISH.
COMPLIANCE:
WOTL
THIS SERVICE LETTER CONTACT YOUR NEAREST ROCKWELL
DEALERJDISTRIBUTOR OR YOUR ROCKWELL
COMMANDER
REGIONAL SERVICE MANAGER.
APPROVAL:
FAA DOA SW-2
ONE
(1)
P MECHANIC OR
A
COMMANDER
EQUIVALENT.
Approved.
HOUR.
Parts required to comply with Part I of this Service Letter may be purchased through your
PARTS DATA:
nearest Rockwell Commander Dealer/Distributor for 810.32. Reference this Service Letter, aircraft model
and factory serial number when ordering Service Letter No. SL-112-42 Mt consisting of the following:
Price rubiect to change without notice
DESCRIPTION
QTY
PART NO.
1
ea.
MS20822- 4D-HXX
1
ea.
1
ea.
Pressure Snubber
Compliance
Card
Instructions
HIOTE:
No
parts
are
required for Part II.
NONE.
SPECIAL TOOLS:
PART I
Models 112 and
112B,
Serial No’s 3 thru 540 and Models 112TC and
112TCA,
Serial No’s 13000
thru 13169.
1.
Disconnect manifold pressure tube
assembly from eldsting fitting
in manifold pressure gauge
port (see
Figure i.).
2.
Remove and disconnect
3.
Remove and discard
eldsting manifold pressure gauge fitting.
Phillips head dampening
screw
located inside manifold pressure
port of
manifold
pressure gauge.
Page 1 of 3
EXISTING MANIFOLD
PRESSURE TUBE ASSY
FUEL
IPRESS.
1 VENTFUEL
f
EXISTING MANIFOLD
PRESSURE GAUGE
MANIFOLD
(RE Fl
PRESS.
MS20822-4D-HXX SNUBBER~
OR EXISTING SNUBBER
Figure i.
4.
Apply teflon tape (3M
No.
547
or
equivalent)
to threads of MS20822-4D-HXX pressure snubber
as
follows
Place end of teflon
a.
tape
two
(2)
threads in from end of male
pipe
threads and hold tape
firmly
with thumb.
Stretch
b.
tape against threads and wind clockwise
tape has been broken.
one
(1) lap.
Continue to hold
tightly against
threads until
NOTE
Do not
attempt to
winding.
tear
tape sideways.
Snap tape
off in
same
direction
used for
5.
Install MS20822-4D-HXX pressure snubber in manifold pressure gauge
(see Figure 1.).
6.
Connect
(see
7.
Fill out and mail
PART II
1.
e~sting manifold
Model
pressure tube
Compliance Card
112B,
and
assembly
proceed
to pressure snubber
to RECORD COMPLIANCE.
Serial No’s 541 thru 544 and Model
Disconnect manifold pressure tube
Remove
3.
Remove and discard Phillips head
of manifold pressure gauge.
Page 2 of 3
e~sting
112TCA,
assembly from elcisting
port (see Figure 1.).
2.
1.).
Serial No’s 13170 thru 13195.
pressure snubber in manifold pressure gauge
pressure snubber from manifold pressure gauge.
dampening
screw
(if installed)
located inside manifold pressure port
4.
Apply
as
teflon tape
follows:
a.
b.
(3M
No. 547
or
equivalent)
Place end of teflon tape two
thumb
Stretch
(2)
to threads of
elristing
threads in from end of male
tape against threads and wind clockwise
tape has been broken.
one
(1) lap.
threads until
pressure
snubber,
pipe threads
removed in
and hold
Step 2.,
tape firmly
with
Continue to hold tightly against
WOTE
Do not
attempt to
winding.
tear
tape sideways.
Snap tape off
in
same
direction
used for
5.
Install
8.
Reconnect
7.
Fill out and mail
eldsting
pressure snubber in manifold pressure gauge
elristing manifold
pressure tube
assembly
to
(see Figure i.).
eldsting
pressure snubber
(see Figure 1.).
Compliance Card.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
YES.
Catalog
and
Airplane Maintenance
Manual
changes
required by this document will be incorporated at the next scheduled
change/revision.
RECORD COMPLLANCE: Make appropriate entry in
airplane maintenance records
SL-112-42, dated 7 October 1977, entitled "Manifold Pressure
No.
(date)
PartIIaccomplished
(date)
as
follows:
Gauge Modification",
Part I
Service Letter
accomplished
Page 3 of 3
6
G´•nn´•l Avinion DivYon
Bethsnv. OL~lehome 73008
26 October 1977
OIL PRESSURE INDICATOR
MODELS AFFECTED:
PART I
PART II
AND/OR OIL
PLACARD REPLACEMENT
MODELS 112TC AND 112TCA, SERIAL NO’S 13000 THRU 13178.
MODEL 11OTCA, SERIAL NO’S 13179 THRU 13195.
RELOCATE THE oa PRESSURE INDICATOR RED LINE TO PROVIDE MORE
MARGIN AND PROVIDE A PLACARD WITH NEW OIL GRADE REQUIREMENTS.
COMPLIANC E:
880’78
ROCKWELL COMMANDER DEALER/DISTRIBUTOR OR YOUR
ROCKWELL COMMANDER REGIONAL SERVICE MANAGER.
A
APPROVAL:
FAA DOA SW-2
PART I
PART H
PARTS DATA:
Parts
Rockwell Commander
factory
Approved.
REPLACE OIL PLACARD AND OIL PRESSURE INDICATOR
TWO (2) HOURS.
REPLACE OIL PLACARD
THIRTY (30) MINUTES.
with this Service Letter may be ordered through your nearest
Reference this Service Letter, aircraft model and
no charge.
Service Letter No. SL-112-43 kit consisting of the following:
ordering
at
Models 112TC and
Model
112TCA,
112TCA, Serial No’s 13000 thru 13178.
Serial No’s 13179 thru 13195.
Part I
Part II
QTY
QTY
PART NO.
1
ea.
40132-503
855000-5
1
ea.
1
ea.
1
ea.
1
ea.
EQUIVALENT.
required to comply
Dealer/Distributor
serial number when
Part I
Part II
P MECHANIC OR
DESCRIPTION
Oil Placard
Oil Pressure Indicator
Service Letter No. SL-112-43 Instructions
SPECIAL TOOLS:
NONE.
PART I
REPLACE OIL PLACARD AND OIL PRESSURE INDICATOR.
1.
Remove and discard
eldsting
oil
placard
2.
Install 40132-503 oil
placard
on
oil filler door.
3.
Disconnect and
ture and rudder
located
on
underside of oil filler door.
right instrument cluster (cyllnder head
from lower instrument panel.
remove
trim)
4.
Remove oil presrmre incticator from instrument cluster.
5.
Install
new
855000-5 oil pressure indicator in eldsting
right
temperature,
oil pressure, oil
tempera-
instrument cluster.
Page
1 of 2
6.
Reidentify right instrument cluster to P/N 855000-513 by ink stamping.
7.
Reinstall
8.
Reconnect ail pressure tube
right
instrument cluster in lower Instrument
Reconnect the electrical
’9.
Manual,
PART II
assembly
wiring
to the
panel using eldsting
hardware.
to oil pressure indicator.
right
instrument cluster
as
shown in the
Airplane
Maintenance
Section X.
REPLACE OIL PLACARD ONLY.
1.
Remove and discard
eldsting oil placard
2.
Install 40132-503 oil
placard
on
located
on
underside of oil filler door.
oil filler door.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
YES.
The Pilot’s
Operating Handbook, the Airplane Maintenance Manual and
Catalog changes required by this document will be
the Illustrated Parts
RECORD COMPLIANCE:
No.
SL-112-43,
Part I
Page
2 of 2
Make
appropriate entry in airplane maintenance records as’follows: Service Letter
1977, entitled "Oil Pressure Indicator and/or Oil Placard Replacement",
PartIIaccomplished
Idate)
dated 26 October
O´•n´•ral Aviation Divilion
Bethany. Oklahoma 730(38
August 1978
30
SECURING PITOT HEATER WIRES
MODELS AFFECTED:
MODELS 112 AND 112B, SERIAL NO’S 13000 AND 3 THRU 544,
MODELS 112TC AND 111TCA, SERIAL NO’S 13001 THRU 13271.
TO PREVENT POSSIBLE FRAYING OF PITOT HEATER WIRE INSULATION.
COMPLIANCE:
DURING NEXT 100-HOURINSPECTION.
WOTE
WITH THIS SERVICE LETTER, CONTA%T YOUR NEAREST
ROCKWELL COMMANDER AUTHORIZED SERVICE FACILITY.
P MECHANIC OR
A
EQUIVALENT.
APPROVAL:
FAA DOA SW-2
THIRTY (30) MINUTES.
SECURE HEATER WIRES
ONE-HALF
ONE
MODIFY PTTOT HEAD ASSEMBLY
The
PARTS DATA:
following material required
to
Approved.
comply
with this Service Letter may be
QTY
PART NO.
DESCRIPTION
1
RTV-106
Silicone Sealer (6
ea.
oz.
(1.5) HOURS.
procured locally:
tube)
NONE.
SPECIAL TOOLS:
1.
2.
Remove
screws
attaching pitot
head
assembly
access cover
to
wing and pull down
pitot
on
head
assembly.
Check dimension from top of pitot heater(s) to top of pitot head assembly to assure that pitot heater~s)
properly in pitot head assembly. Dimension should be 0.375-inch to 0.50-inch (see Figure
is installed
pitot heater(s)
top of pitot head assembly is less than 0.50-inch, proceed
3.
If dimension from top of
to step 5.
4.
If dimension from top of pitot heater(s) to top of pitot head assembly is greater than
pitot head assembly from wing and proceed as follows:
pitot heater(s)
from
a.
Remove
b.
Ream 0.1875-inch diameter
c.
Inspect pitot
d.
If
e.
If evidence of
no
Reinstall
assembly
frayed
frayed
O.[iO-inch,
remove
pitot head assembly.
hole(s)
heater wires for
evidence of
to
1.)
to
depth specified
possible fraying
insulation
insulation
or
or no
in
Figure
of insulation
bare wires eldst,
bare wires
reconnect
bare wires.
proceed
e~dst, repair
pitot heater(s) on pitot head assembly,
and proceed to step 8.
or
1.
as
to
step
f.
necessary and
pitot
tube
proceed
to
step
i.
assembly to pitot head
Page
1 of 3
SINGLE HEATER PITOT HEAD
o. 1875" DIA.
HEATER WIRES
(REF)
HOLE
i
i
I,,,,
i:
t
I
i
3. 70"
a
ACCESS COVER
’I I’
RTV 106 WLICONE
(REF)
I
JIj If
M~J d
II
8
HEATER (REF)
PITOT HEAD ASSY
(REF)
DUAL HEATER PITOT HEAD
o.
HEATER WIRES
J
375"~0.
500"
(REF)
ACCESS COVER
a
(REF)
RTV 100 SUIICONE
SEALANT
0. 1875" DIA. HOLE
(2 PLS)
e
g
I I
2. 70"
ITOT
HEATERS
PITOT HEAD ASSY
(REF)
ii
I;i;;
,I
II
(REF)
-’J
Figure
Page 2 of 3
I
i.
ii 1
3. 70"
5.
Inspect pitot heater
6.
If
7.
If evidence of
8.
Apply RTV-108
9.
Reinstall
10.
Perform
no
evidence of
pitot
wires for
frayed
frayed
possible fraying of insulation
insulation
or no
bare wires
insulation
or
bare wires
silicone sealer
on
pitot
head
leakage
assembly
test
as
and
outlined in the
heater wires and
Airplane
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
YES.
on
as
to
step 8.
necessary and
proceed
to
step 8.
top of pitot heater(s) (see Figure 1.).
wing.
Maintenance
incorporated
RECORD COMPLJANCE:
No. SL-112-44, dated 30
exist, proceed
exist, repair
access cover on
and bare wires.
Manual, Section VIII.
Catalog changes required by
change/revision.
Make appropriate entry in airplane maintenance records as follows: Service
August 1978, entitled "Securing Pitot Heater Wires", accomplished
(date)
Letter
Page 3 of 3
Service Letter
Oarural Avinion Divltlon
5001 North Rockwall AvanW
Bemany. Oklahoma 73008
14 September 1979
NOSE GEAR DOWN SPRINGS INSPECTION
AND/OR REPLACEMENT
MODELS 112 AND 112B, SERIAL NO’S. 13000 AND 3 THRU 544,
MODEL 112TC, SERIAL NO’S 13001 THRU 13108, AND MODEL
SERIAL NO’S. 13150 THRU 13299.
MODELS AFFECTED:
TO ASSURE PROPER TENSION OF NOSE GEAR DOWN SPRINGS.
COMPLIANCE:
11ZITCA,
WOTE
COMMANDER AUTHORIZED SERVICE FACILITY.
P MECHANIC OR
A
APPROVAL:
FAA DOA SW-2
TWO
EQUIVALENT.
Approved.
(2) HOURS.
Replacement gear down springs, part numbers P227-27 inner spring and P227-28
procured through your nearest Rockwell Commander Authorized Service Facility.
P~PiATS DATA:
may be
outer
spring,
CALIBRATED SCALE FOR PULL TESTING SPRING TENSION.
SPECIAL TOOLS:
airplane
outlined in the
Jack
2.
Disconnect lower end of inner and outer gear down
3.
Using
as
calibrated
a
scale,
check
pull
tension of
springs from
nose
gear down
Inner
Spring
7.69 inches
Outer
Spring
7.63 inches
If either
as
spring tension load
springs.
landing
gear.
Tensions should be
24 to 30
pounds
23 to 28
pdunds
step 3.,
is not within load limits listed in
spring tension loads are within load limits listed in step 3.,
springs to nose landing gear.
If
6.
With the nose
as follows:
Model
landing
gear
112, SerialNo’s.
as
remo~ie and
replace
both
follows:
springs
extended,
assure
that
nose
gear
reconnect lower ends of nose gear down
drag
brace is overcenter
(see Figure 1.)
1 thru 380:
cylinder lock engaged on the nose gear actuating cylinder and the drag brace in a
position, the drag brace must be resting on the overcenter stop at the knuckle area.
With the
laxed
b.
nose
necessary.
5.
a.
the
LOAD
EXTENDED LENGTH
4.
Section II.
1.
Push up
on
the
drag
brace
pivot point and check for
a
re-
clearance of 0.040 to 0.125-inch.
Page 1 of
2
~51
NOSE GEAR DRAG BRACE
MUST BE AGAINST STOP
(OVERCENTER)
NOSE GEAR
DOWN SPRINGS
NOSE LANDING GEAR
(REF)
;4"
Figure i.
c.
correct, readjust
Manual, Section VI.
If clearance is not
Maintenance
nose
gear
actuating cylinder
112B, SerialNo’s. 13000 and 381 thru 544,
112TCA, Serial No’s. 13150 thru 13299.
Models 112 and
and Model
a.
Check
b.
If the
the
drag
brace
assembly
at knuckle
area
to
assure
drag brace is not resting on the stop, readjust
Airplane Maintenance Manual, Section VI.
7.
Check
8.
Remove
9.
Fill out and mail
operation
of
landing
gear
system
as
Model
outlined in the
that
nose
as
112TC,
outlined in the
Airplane
Serial No’s 13001 thru 13108
drag
brace is
gear
actuating cylinder
resting
on
the
as
stop.
outlined in
Airplane Maintenance Manual, Section VJ.
airplane from jacks.
Compliance Card.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
NO.
Airplane Maintenance Manual change required by
The
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service
Letter No. SL-112-45, dated 14 September 1979, entitled "Nose Gear Down Springs Inspection and/or
Replac ement’’
Page
2 of 2
accompli
~ill
SERVICE PUBLICATIONS
Gulf~tream Amer~can
revision notice
CORPORATION
Commndr D~vidon‘
8001 North Rockmll Avenue.
Betheny, Oklehole 73008
Revision No. 1
27 October 1981
ELEVATOR AND RUDDER HINGE FITTING INSPECTION
AND/OR REPLACEMENT
APPROVAL:
Page
1 of 5
CHANGE:
FAA DOA SW-2
Approved.
PARTS DATA:
Kit No. 1
Kit Nd. 2
eTY
em
PART NO.
DESCRIPTION
WAS:
1
ea.
44285-1
Elevator Fitting
NOW:
2
ea.
44285-1
Elevator
Fitting
Page 1 of 1
Y’""´•"’""~’
Service Letter
amnl Av*Hon DivWon
MXI( North Aookweil Avmon
Lth~iny, OkMoml 73008
14 November 1979
ELEVATOR AND RUDDER HINGE FITTING INSPECTION
AND/OR REPLACEMENT
MODELS 112 AND 112B, SERIAL NO’S 13000 AND 3 THRU 544 AND
MODELS 112TC AND 11PTCA, SERIAL NO’S 13001 THRU 13309.
MODELS AFFECTED:
POSSIBLE ELONGATION OF HOLES IN HINGE FITTINGS AND CRACKS
IN RUDDER SPAR.
COMPLIANCE:
WITHIN NEXT 100-HOURS TIME IN SERVICE OR NEXT ANNUAL
INSPECTION, WHICHEVER OCCURS FIRST.
WOTE
THIS SERVICE
COMMANDER AUTHORIZED SERVICE FACILITY.
A
P MECHANIC OR
EQUIVALENT.
APPROVAL:
FAA DOA SW-2
ESI~IMATED ~UIAN HOURS:
REPLACE BUSHINGS AND BEARINGS
Approved.
INSTALL DOUBLERS
EIGHT
REPLACE F~TINGS- FOUR
PARTS DATA:
Parts required to
(4)
HOURS.
HOURS.
with this Service Letter may be
Kit No. 1
$65.38; Kit No. 2
Letter, aircraft model and
number
of the
(4)
(8) HOURS.
well Commander Authorized
comply
Facility for:
factory serial
FOZTR
procured through your nearest Rock$91.10. Reference this Service
when ordering Service Letter No. SL-112-46 kit consisting
following:
Price ,ubiact
to
chengs without notin
Kit No. 1
Kit No.2
QTY
QTY
PART NO.
DESCRIPTION
2
ea.
2
ea.
44006-RE3
Angle Doubler
2
ea.
2
ea.
SNm
2
ea.
2
ea.
2
ea.
2
ea.
3
ea.
3
ea.
1
ea.
1
ea.
4
ea.
4
1
ea.
40113-3
44006-RE5
40111-507
40121-105
FF-411-1
F316G x .3125
44254-501
44285-1
1
1
ea.
ea.
1
1
1
ea.
ea.
Shim
Bu shing
Bushing
Bearing
Bearing
Rudder
Fitting
Fitting
Compliance Card
Elevator
ea.
Service Letter No.
SL-112-46
ea.
SPECIAL TOOLS:
Instructions
NONE.
1.
Remove cotter
2.
Take hold of upper portion of rudder and
check for play at upper hinge fitting.
~pin
and loosen nut
on
upper rudder
attempt
hinge fitting.
to
move
rudder
tip forward-to-aft
and
left-to-right
to
Page 1 of 5
3.
Remove rudder
1
assembly
as outlined in the Airplane Maintenance Manual, Section
VII, and c~lscard
Retain other hardware for reinstallation of rudder
assembly.
existing
oilite
4.
Remove
tip assembly from
5.
If
bushing.
rudder.
play is evident in upper rudder hinge fitting, per step 2.,
fitting. Retain existing shims and hardware for installation
remove and
of
new
discard
existing
upper
hinge
hinge fitting.
WO’IE
If
play
no
6.
Dye penetrant inspect the bend
7.
If
8.
If cracks
no
cracks
are
are
is
detected,
do not
remove
hinge fitting.
radius of rudder spar, in area of
upper
found in bend radius of
rudder,
in
area
found in bend radius of rudder spar, in
a.
Remove upper four (4) rivets,
(total of eight (8) rivets).
b.
Remove upper six
c.
Stop
d.
Locate,
e.
If
ercisting hinge fitting
hinge fitting.
f.
Install
(6)
upper
attaching
a
No.40
(0.098)
drill and install 44006-RE3
is to be
area
hinge fitting, proceed
of upper
cracks.
to
hinge fitting, proceed
skin to spar, from left and
rivets from rudder
drill all cracks with
of upper
hinge fitting, for
assembly leading edge
right
skin
step
as
follows:
side of rudder
assembly
lap.
diameter drill.
angle doubler (2 places)
on
rudder
assembly (see Figure i.).
trim 0.06-inch to O.O’l-inch from each end of
used,
9.
or new 44254-501 hinge fitting, 44006-RE5
(2 places) using eldsting hardware (see Figure 1.).
shim
(2 places)
existing
and 40113-3 shim
WO’CE
44006-RE5 shims to be installed butted against skins.
g.
Install MS20470AD3 rivet
h.
Repaint
i.
Proceed to
rudder
assembly surfaces
Install
10.
Reinstall tip
11.
Remove and discard
12.
Install FF-411-1
44254-501 hinge
on
in rudder
as
14.
rudder
~fitting (if discarded
erdsting
bearing
Take hold of elevator
play
lap.
per
step 5.)
and
e~sting
shims
using e~sting hardware.
assembly.
oilite
bearing from
in upper vertical fin
Remove cotter pin and loosen nut
to check for
sldn
necessary.
tip
and
at outboard
on
upper vertical fin
hinge
(see Figure 1.).
13.
leading edge
step 10.
9.
new
(6 places)
and
ream
hinge.
hole in
left and right elevator outboard
attempt to move
hinge fitting.
new
bearing
to
0.317/0.318-inch
hinge fitt;ings.
outboard end of elevator forward-to-aft and
up-and-down
15.
Remove left and right elevators as outlined in the
Airplane Maintenance Manual, Section YII, and discard
existing oilite bushings. Retain other hardware for reinstallation of elevators.
16.
If
no
17.
If
play
Page
2 of 5
play
is evident in outboard
is evident in outboard
hinge fitting,
hinge fitting,
per
per
step 14., proceed
step 14., proceed
as
to
step 18.
follows:
-,--_
RUDDER
(REF)
WOTE
i
INSTALL 44006-RE3 ANGLE
DOUBLER WITH 0. 98" FLANGE
AGAINST SPAR FLANGE
44006-RE5
SHIM-
BUTT AGAINST SKIN
BEFORE DRILLING
EXISTING HARDWARE
(REF)
44006-RE3
ANGLE DOUBLER
o, 98~1
(REF) (2 PLS)
)7
40113-3 SHIM
j
0. 88"
MS20470AD4 RIVET
EXISTING OR NEW
44254-501 HINGE FITTING
EXISTING HARDWARE
(RE Fl
I
PICKUP EXISTING
RIVET LOCATIONS
WP
0
FF-411-1
O
(TYP)
I
1~1
II
BEARING
RUDDER
NAS1738B4 (CR2249-4)
RIVET (3 PLS) TO BE
IN LINE WITH RIVETS
IN SIDE FLANGE
(REF)
~I
VERTICAL FIN
HINGE (REF)
jO
I1
44006-RE3
111~
1
I
I
II[
I II
o
ANGLE DOUBLER
111
40111-105
BUSHING
I
111
I
II’
111
MS20470AD3
O
(1.35" TYP
~IP
RIVET
(6 PLS)
I
111
1
´•-_;L,I
III
o
111
LEADING EDGE
SKIN LAP
Figur~
1.
Page
3 of 5
I;
m
I
r
I
TI
HORIZONTAL
40111-105BU$ING
EXISTING OR NEW
44285-1 HINGE
c~
STABILIZER
m
(REF)
~cl
/I
EXISTING‘
1j
HARDWARE
(REF)
EXISTING HARDWARE
FITTING
(REF)
F316G
BEARING
N
TI
O
i/ j
?L´•
-Tr~rT----
40111-107 BUSHING
EXISTING HARDWARE
F316G
(REE)
BEARING
ELEVATOR
(RE Fl
OUTED
HORI ZONTAL
STABILI ZE R
HINGE (REF)
ELEVATOR
(RE Fl
tip from elevator.
a.
Remove
b.
edsting blind rivets and MS20426AD
hinge fitting attaching nuts.
c.
Remove
Remove and discard
rivets in
area
of
hinge fitting
to
gain
access
to
e~sting hinge fitting.
WOTE
Replace
44285-1 hinge
center
fitting
hinges if
elevator
holes
are
elongated.
using e~isting
hardware
(see Figure 2.).
d.
Install
e.
Attach skin to elevator structure using MS20426AD4 rivets and NAS1738B4 blind rivets.
new
elevator surfaces
f.
Repaint
g.
Iieinstall
tip
on
as
on
necessary.
elevator.
eldsting oilite bearings from horizontal stabilizer center and outboard hinges.
18.
Remove and discard
19.
Install F316G bearing (4 places) on horizontal stabilizer center and outboard
bearings to 0.317/0.318-inch (see Figure 2.).
20.
Reinstall rudder assembly on airplane as outlined in the Airplane
using existing hardware and 40111-105 bushing (see Figure 1.).
hinges
Maintenance
and
Manual,
ream
hole in
Section
VII,
WOTE
Tighten
nuts until
full slot to
21.
align
hinge fitting contacts bushing and then tighten nut one (1)
pin hole in bolt and then install cotter pin.
with cotter
right elevator assemblies on airplane as outlined in the Airplane Maintenance Manual,
VII, using eldsting hardware, 40111-107 bushing (center hinge) and 40111-105 bushing (outboard
hinge) (see Figure 2.).
Reinstall left and
Section
WOTI
Tighten
nuts until
full slot to
align
hinge fitting
with cotter
22.
Check rig~ng of elevators and rudder
23.
Fill out and mail
as
bushing and then tighten nut one
hole in bolt and then install cotter pin.
contacts
pin
outlined in the
Airplane
Maintenance
Manual,
(1)
Section VII.
Compliance Card.
ELECTRICAL LOAD:
NO CHANGE.
WEIGHT AND BALANCE:
NO CHANGE.
SPARES AFFECTED:
NO.
The
Airplane
required by
Maintenance Manual and Illustrated Parts Catalog changes
incorporated at the next scheduled change/
revi sion.
Make an appropriate entry in airplane maintenance records as follows: Service
Letter No. SL-112-46,dated 14 November 1979, entitled "Elevator and Rudder Hinge Fitting Inspection and/or
RECORD COMPLIANCE:
Replacement",
Page
5 of 5
~c,
Service Letter
eu~fstream Amerisan
C()RPORATI()N
Commander Divirion
5001 North Rockwell Avenue.
L
19 June 1981
INSPECTION OF TURBOCHARGER HEAT SHIELD
MODELS 112TC AND
MODELS AFFECTED:
112TCA, SERIAL NOS.
13001 THRU 13309.
POSSIBLE ENGINE MOUNT STRUCTURAL DAMAGE DUE TO RUBBING OF TUR-
BOCHARGER HEAT SHIELD.
COMPLIANCE:
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE LETTER, CONTACT YOUR
NEAREST GULFSTREAM COMMANDER AUTHORIZED
SERVICENTER.
APPROVAL:
A
P MECHANIC OR
EQUIVALENT.
FAA DOA SW-2 APPROVED.
TWO (2) HOURS.
1 EACH COMPLIANCE CARD.
PARTS DATA:
NONE.
SPECIAL TOOLS:
cowling
from
engine.
1.
Remove upper
2.
Inspect engine mount, adjacent
3.
If
no
damage
to
turbocharger
is evident and clearance between
heat
shield, for possible damage
turbocharger
heat shield and
to
engine
engine
mount
(refer
to
mount is 0.50-inch
Figure 1).
or
more, pro-
ceed to step 7.
4.
If contact between turbocharger heat shield and engine mount is evident but no major damage has occured (see step
6), remove heat shield and trim to provide a clearance of 0.50-inch between heat shield and engine mount (refer to
Figure 1).
5.
Reinstall heat shield,
6.
If extensive
damage
assuring that 0.50-inch
to
tion Customer Service
7.
Reinstall upper
8.
Fill out and mail
engine mount is evident (any penetration
Department for further instructions.
cowling
ELECTRICAL LOAD:
on
of the tube), contact Gulfstream American
Corpora-
engine.
Compliance
Card.
NO CHANGE.
WEIGHT AND BALANCE:
SPARES AFFECTED:
clearance is maintained.
NO CHANGE.
NO.
NONE.
Page
lofa
Make an appropriate entry in airplane maintenance records as follows:
RECORP COMPLIANCE:
SL-112-47, dated 19 June 1981, entitled "Inspection of Turbocharger Heat Shield", accomplished
Service Letter No.
(date)
VIEW LOOKING DOWN AND AFT AT ENGINE
ENGINE FIREWALL
(REF)Y’
ENGINE MOUNT (REF)
TURBOCHARGER
HEAT SHIELD (REF)
TURBOCHARGER HEAT
SHIELD
(REF)
RMRm
o
o
TRIM HEAT SHIELD ONLY
IN AREA OF ENGINE MOUNT
IF NECESSARY.
IIFWD
DO NOT TRIM MORE THAN
0.625" FROM THIS EDGE.
DEBURR ALL SHARP EDGES.
oO
Figure
Page
2 of 2
1.
Service Letter
Gulfstream American
CORP<)RATION
Commllnd´•r Divi,ion
5001 No,th RockwEII Avenue,
Bethany, OklIhoma 73008
26 July 1982
WIRE BUNDLE CLAMP REPLACEMENT
MODELS AFFECTED:
MODELS 112 AND 112B, SERIAL NOS. 1 THRU 644 AND 13000.
MODELS 11BTC AND 11STCA, SERIAL NOS. 13001’rI~HRU 13265
TO PREVENT POSSIBLE LOSS OF WIRE BUNDLE CLAMPS RESULTING IN
POSSIBLE HANGING UP OF LANDING GEAR.
COMPLIANCE:
NOTE
ANY PROBLEMS ARE ENCOUNTERED WHILE
YOUR NEAREST GULFSTREAM COMMANDER SINGLE
.ENGINE SERVICE FACILITY.
IF
APPROVAL:
A
P MECHANIC OR
EQUIVALENT.
SIX AND ONE-HALF (6.5) HOURS.
PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED
PARTS DATA:
FOR 139.39.
THROUGH YOUR NEAREST GULFSTREAM COMMANDER SINGLE ENGINE SERVICE FACILITY
ORDERING
WHEN
NUMBER
SERIAL
FACTORY
AND
MODEL
AIRCRAFT
REFERENCE THIS SERVICE LETTER,
SERVICE LETTER NO. SL-112-48 KIT CONSISTING OF THE FOLLOWING:
PRICE SUBJECT TO CHANaE WITHOUT NOTICE
BTY
3
ea.
3
1
ea.
10
ea.
25
ea.
10
ea.
2
ea.
16
ea.
2
ea.
ea.
14
ea.
14
ea.
16
ea.
4
ea.
50
ea.
16
ea.
30 ft.
1
ea.
I
ea.
PART NO.
DESCRIPTIION
43780-3
43780-4
AN3H3A
AN3-4A
AN960D10
MS21044N3
MS21919DG4
Clip
Clip
MS21919DG5
MS21919DG6
MS27039-1-11
MS27130-A25
MS3367-1-9
MS3367-2-9
MS3367-4-9
MS35338-43
500004-2
Bolt
Bolt
Washer
Nut
Clamp
Clamp
Clamp
Screw
Rivnut
Tiedown Strap
Tiedown Strap
Tiedown Strap
Lockwasher
Spiral Wrap
Compliance Card
Instructions
Page
1 of 12
W.S.
66.0
66.00
rl
1
43780´•3 CLIP
O.3$~´•
(3 PLS)
I
0.45"
I
I
CIUTBD
rOUTBD
0.36"
O$´•~h‘C3:
,-z--0.36"
-r
_;\
I
I
I
4.6~
.0.20"
0.45"
ii
/I
I
3.80"
VIEW LOOKING DOWN
I
I
I
1
13.60"
LEFT INSTALLATION SHOWN
RIGHT INSTALLATION OPPOSITE
Figure
Page 2 of 12
1
SPECIAL fOOLS:
RIVNUT PULLER AND NO. 10-32 UNF-SB TAP.
CAUTION
Care should be taken to prevent damage to electrical
while performing this modifiction.
wiring
Remove and discard all stick-on type wire bundle clamps from left and
remove all adhesive and foam residue carefully.
right
2.
Remove and discard all tiedown straps
landing
3.
Remove any existing spiral wrap from electrical wiring in main
for cut or damaged wires and repair or replace as necessary.
4.
Locate, drill and install 43780-3 clip (3 places) on lower side of wing skin in left wheel well using MS20426AD3
rivets. Rivet heads are to be on top of wing skin (refer to Figure 1).
5.
Locate, drill and install
1.
main
landing
gear wheel wells.
Clean and
43780-4
MS20426AD3 rivets. Rivet heads
securing electrical wiring
clip (3 places)
are
to be
on
on
Locate and drill 0.252 (~0.002) inch diameter hole (7
of MS27130-A25 rivnuts (refer to Figure 2).
7.
Deburr all holes,
to Figure 2).
8.
Locate and drill
a
area
landing
lower side of
top of wing skin (refer
6.
prime
in main
places)
to
gear wheel well
wing skin
in
area.
Check
right wheel
wiring
well
using
Figure 1).
in left and
around holes with zinc chromate
gear wheel wells.
right wheel
well
area
for installation
primer and install MS27130-A25;rivnuts (refer
0.159-inch (No. 21) diameter hole, 0.63-inch deep, in
by 0.50-inch deep (refer to Figure 3).
right
main
landing
gear trunnion.
Tap
10-32 UNFdB threads in hole
9.
Check left and
right
main gears for location of dawn lock switch.
10.
If down lock switch is located
on
11.
If down lock switch is located
midway down
upper end of
drag brace assembly, proceed
on
drag
brace
to
assembly, proceed
step 12. (refer
as
to
Figure 4).
follows (refer to
Figure 5):
a.
Locate and drill
b.
Separate
c.
Assure that down lock switch cable is clean arid then wrap cable with 500004-2
d.
Reroute down lock switch cable aft along rib at wing station 47.30 to landing gear cylinder hose.
Secure cable to station 47.30 rib using MS21919DG5 clamp (2 places), AN3-4A bolt (2 places),
AN960D10 washer (2 places) and MS21044N3 nut (2 places).
e.
a
0.194-inch diameter hole in wing station 47.30 rib (if
down lock switch cable from other cables at
wing station
necessary).
47.30.
spiral
wrap.
Secure downlock switch cable to landing gear cylinder hose using MS3367-1-9 tiedown strap and then
routing cable down along top of drag brace assembly to down lock switch. Secure cable to top
of drag brace assembly using MS3367-1-9 tiedown strap (2 places).
continue
NOTE
Allow sufficient slack in cable, at down lock switch, to
assure proper movement of gear.
f.
Proceed to step 12.
Page
3 of 12
B
X
gg
8
R
5:
E.
d
m´•
0,
8
I
I
llB
STATION DIAGRAM
0.250"10.254" DIA. HOLE
MS27130-A25 RIVNUT
(3 PLS)
A
n,n
11iKe
n
l.so~l
In
--I
ii
5.75(’
BFOR
IR0MODEL
34 112,
S/N’S 1 THRU
ii4.20’~
7.0
12.0"
TOOLING
HOLE (REF)
7.50"n n~.n
0.250"/0.254" DIA. HILE
VIEW A-A
MS27130-A25 RIVI UT
OPS)
U U 5.70"j)4.20"
LOOKING INBD
RIB FOR MODELS 112
AND 1128, UN’s 431 THRU
544 AND 13000 AND ALL
MODELS 11276 AND 11PTCA
5.0"
10.0"
18.0"
THRU S/N 13265
0.45"
6.4(Y’
I~C- 6´•70"
I
c3.0´•’1
WHEEL WELL
RIB
1.Li5"
1.50"
I
i
I;
,CLOSEOUT
_
VIEW B-B
LOOKING FWD
J
0.;3 ’/0.254" DIA. HOLE
Ms! :30-A25 RIVNUT
(3 1 i
RIGHT INSTALLATION SHOWN
LEFT INSTALLATION OPPOSITE
lure
Page 4 of 12
2.
(Sheet 1 of 2)
a
O
8~
f
5:
a
1
E
STATION DIAGRAM
W.S.
47.30
4.0"
1.05"
0.250"/0.254" DIA. HOLE
MS27130´•A25 RIVNUT
rl!
tourePI
-t
WING FWD
AUXILIARV SPAR
VIEW C-C
LOOKING FWD
Figure
2. (Sheet 2 of 2)
Page 5
of 12
CORNER
(REF?
DRILL 0.159" DIA. HOLE (NO. 21 DRILL)
0.63" DEEP AND TAP NO. 1032 UNF-SB
THREADS 0.50" DEEP
1.00"
43780-4 CLIP
(REF) (SEE FIGURE 1)
CORNER
CENTER HOLE MIDWAY
BETWEEN CORNERS
OF FORGING
(REF)
VIEW A
MS21919DG4 CLAMP
AN3H3A BOLT
ANZ)BOD10 WASHER
MS35338-43 LOCKWASHER
SAFETY WIRE TO AIR VALVE
O -~f:
8EE VIEW A
RIGHT MAIN
LANDING GEAR
I
(REF)
STRUT AIR
VALVE (655)
MS3367-2-9
TIEDOWN STRAP
1~1
WRAP ELECTRICAL CABLES
WITH 500004´•2 SPIRAL WRAP
AND SECURE WITH MS3367
TIEDOWN STRAPS. TIEDOWN
STRAPS TO BE SPACED APPROXIMATELY SIX (6) INCHES APART
AL~V
MS3387-4-9
TIEDOWN STRAP
M53367-1-9
TIEDOWN
STRAP
RIGHT INSTALLATION
GROUND CONTACT
SWITCH (REF)
Figure
Page 6 of 12
3. (Sheet 1 of 2)
VIEW OF TYPICAL
TIEDOWN FOR SECURING
HOSE OR TUBE ASSY
TO
ELECTRICAL CABLE
WRAP ELECTRICAL CABLES WITH
500004-2 SPIRAL WRAP AND SECURE
WITH MS3367 TIEDOWN STRAPS.
TIEDOWN STRAPS TO BE SPACED
APPROXIMATELY SIX (81 INCHES
APART.
43780-3 CLIP (REF)
(SEE FIGURE i),
y~
srZ1R
TUBEASSY(REF)
SECURE ELECTRICAL
WIRING TO THE TUBE
ASSY WITH TIEDOWN
UPLOCK SWITCH
(REF)
HOSE ASSY
(REF)
.Irso
I
ALLOW SUFFICIENT SLACK
TO ASSURE PROPER
GEAROPERAtlON
VIEW LOOKING OUTED
AT LEFT GEAR
Figure 3. (Sheet 2 of 2)
Page?
of 12
RIGHT INSTALLATION SHOWN
LEFT INSTALLATION OPPOSITE
LANDING
GEARI
(REFI
’i
Gt.
ws
47.30
DOWN LOCK SWITCH
(SEE STEP 10.)
DRAG BRACE ASSV
(REF)
VIEW LOOKING UP AND AFT
AT RIGHT WHEEL WELL
Figure
Page
8 of 12
4.
EXISTING
TOOLING HOLE
(REF
EXISTING OR
ADDED 0.194"
DIA. HOLE
~eJ
O.M)"
WS
47
DOWN LOCK SWITCH
(RE
43780´•3 CLIP
MS3387 TIEDOWN
STRAP
(REF)
ALLOWSUFFICIENT
O
SLACK TO ASSURE
PROPE R GEAR OPERATION
I
DRAG BRACE
ASSY
(REF)
W/
.1(
O
SEE FIG. 8 FOR PARTS
CALLOUT
VIEW LOOKING UP
AT LEFT WHEEL WELL
Figure 5. (Sheet
1 of
2)
Page
9 of 12
HVDRAULIC HOSE
(REF)
SEE FIG. g FOR PARTS.
CALLOUT
I
WWN LOCKSWITCH
GABLE
(REF)
MS3367 TIEDOWN
STRAP
WS 47.30 RIB
(REF)
r
GEAR
CYLINDER
GNIDNAL)FER(
*anra
STRAP
nasv (REFI
L
L/
C/
VIEW LOOKING UP
AT LEFT WHEEL WELL
Figure 5. (Sheet 2
Page 10 of 12
of
2)
j
EZrm
O MS219190G4 CLP´•MP
SCREW
O MSnOlkl-ll
ANSBODIO WASHER
SIZE OF CLAMPS MAY BE
CHANGED TO FIT WIRE BUNDLES.
MSZlslgDG5 CLAMP
MS3533S43 LOCKWASHER
AN3~4A BOLT
O AN960D10
WASHER
WRAP ALL ELECTRICAL WIRING
IN WHEEL WELL WITH 600004-2
MSZ191sDG6 CLAMP
SPIRAL WRAP AND SECURE WITH
MS3367Q-B TIEDOWNS.
MSZ1W4N3 NUT
jll
VIEW LOOKING DOWN
LI/
I I
I
ON LEFT WING
II 0~
1 )I
’1
~I
0
L’
SECURE TO
BRAKE TUBE
WITH MS3367-4-9
TIED~WN STRAP
OLI I
O
I
’og
I
I
o
I
I
1
I
II
O
/I
’O
43780´•4 CLIP
(3PLS)
I
I,
I
I’
I
I
rPI TO DOWN LOCK
I I SWITCH(SEE STEP 11)
I)
I
I
I
lli
\I
I
I
lo
il~
I
---I_L
II08
’11~1
i 1
I
I
-----I
ii
111
I
1 I
OQll~>
O
;00
I
I
I
_
_
W. S.
W. S.
66.0
W. S.
26.50
47.30
VIEW LOOKING DOWN
ON RIGHT WING
ij
8
I
I
I
II
I
1
I
43780-4 CLIP (3 PLS)
~I
I
ii
Ir
I
I i
O~I
I
II
I I
I
II
,0.
II
II O
I
I II
I
’111
(I
1 I
(I
I I
II
I
II
I I
1
I
,1
I
TO DOWN LOCK
I
I
SWITCH (SEE STEP 11)
I
I-
W.
S.B .O
W. S.
47.30
W.S.
28.50
Fi~ure 6
Page 11 of 12
SERVICE LETTER NO SL-112-48
gear wheel well
cleaned prior to
wrapping
with
spiral
12.
Assure that electrical cables in main
13.
Wrap electrical cables with 500004-2 spiral wrap and secure ~cables using MS21919DG clamps and MS3367
tiedown straps. Tiedown straps should be spaced approximately six (6) inches apart (refer to Figure 6).
14.
Jack
15.
Retract and extend main
airplane
landing
as
landing
outlined in Section IZ of the
landing
gear to
Airplane
assure
are
Maintenance Manual.
that
no
interference exists between electrical cables and
gear.
16.
Touchup paint
17.
Remove jacks from
18.
Fill out and mail
ELECTRICAL LOAD:
as
necessary.
airplane.
Compliance
SPARES AFFECTED:
Card.
NO CHANGE.
NO CHANGE.
WEIGHT AND BALANCE:
NO.
NONE.
Make an appropriate entry in airplane maintenance records as follows:
RECORD COMPLIANCE:
SL-112-48, dated 26 July 1982, entitled "Wire Bundle Clamp Replacement", accomplished
No.
Page 12 of 12
wrap.
Service Letter
(date)
9
Service LetterWilry
Post
Airport
7200 N.W. 63rd
Bethanv. OK 73008
Date
July I,
1999
EMERGENCY GEAR EXTENSION VALVE COVER PLATE ORIENTATION
INSPECTION AND ArTACHMENT IMPROVEMENT, AND INSPECTION ANDIOR
REPLACEMENT OF FUEL LINE
MODELS AFFECTED: Model 112 and 11213, S/N 3 thru 544 and 13000, Model 112TC and 1 12TCA,
S/N 13001 thru 13309
REASON FOR
~ce. the possibi~ty
:-II~--; ri;:i :,1::- ~xtension ~alve Co~r
of the
Emergency
field maintenance personnel.
Com~any strongl; recommends:that
COMPLIANCE:
the
procedures
Gear
found in the
accomplishment instructions section ofthis service letter be followed.
BY WHOM WORK WILL BE ACCOMPLISHED: A
P Mechanic
or
equivalent
Engineering design aspects are FAA approved.
APPROVAL:
Part I:
.25 hours
Part II:
1.0 hours
Part III:
6.0 hours
Part IV:
2,0 hours
PARTS DATA:
QTY
1
Part I:
NA
PartII:
NA
PartIII:
QTY
1
PART NUMBER
Service Letter
SL-112-50
PART NUMBER
Part may be ordered from:
DESCRIPTION
Fuel Line
46099-171
The 46099-171 Fuel Line is used
DESCRIPTION
as a
replacement
in aircraft equipped with
a
635019-3 Fuel Line
Commander Aircraft Company
7200 N.W. 63rd Street
Bethany,
OK 73008
USA
(405) 495-8080
(405) 495-8383
Phone
Fax
Page
1 of 8
PARTS DATA:
Part IV:
(con’t)
QTY
PART NUMBER
DESCRIPTION
-1
3
MS2713 t -2K
Blind Rivnut
3
NAS391-B4P
Washer
3
MS24693-C4
Screw
SPECIAL TOOLS
REQUIRED:
Part IV: Rivnut
puller
Part I: Removal of the
I.
Emergency Gear Extension Valve Cover Plate and Attachment Hole Inspection
Remove the three screws attaching the
discard the
Set the
screws.
cover
Emergency’Gear Extension Valve Cover to the center console and
aside for later use.:’-
2.
the carpet away from the center console
Extension Valve is exposed.
3.
Refer to Figure 1 Examine the area around the Emergency Gear Extension Valve.
Carefully peal
holes for the three
screws
attaching
the
Emergency
so
that the
around the
Emergency
Gear
Verify that the location
Gear Extension Valve Cover to the center console
match the correct hole locations A, B, and C.
4. If there is an attachment screw hole at location D indicating that the
Cover was installed upside down at some point, proceed to Part II.
5.
area
Emergency Gear Extension Valve
Ifthe cover was installed correctly and there is no additional attachment screw hole at location D,
proceed
to Part IV.
Part II:
1.
Inspection of the
Fuel Line
Refer to
Remove the friction control knob
S/N 13000 thru
(S/N
Figures
1 and 2
thru 499)
or
two
fricitian control knobs (S/N 500 thru 544 and
13309).
NOTE
Place the fuel selector knob in the OFF
2.
Remove the fuel selector knob and the selector
3.
Remove the
screws
4.
Remove the
screws
5.
Remove the console
6.
Remove the
7.
plate from the
position,
center console.
attaching the console cover to the center console.
attaching the quadrant cover plate to the center console.
cover
from the center console.
attaching the
slotted forward console
cover to the center console.
Move the throttle lever forward until it clears the throttle warning microswitch. Raise the
quadrant cover
plate and the forward console cover to permit inspection of the fuel line for nicks or scratches in the area
screws
where the bottom screw ofthe
improperly attached Emergency Gear Extension Valve Cover attached to
the center console.
a.
If no damage to the fuel line is found, reattach the center console parts Part II,
steps 1 thru 6 in reverse
order), proceed to Part IV.
b.
If a nick
proceed
Page
2 of 8
or
scratch is found in the
to Part III.
area
being inspected,
or
any other
damage
to
the fuel is found,
CONSOLE
COVER
EMERGENCY
NOISETXRAEG
VALVE
49061-101
EMERGENCY GEAR
EXTENSION VALVE
COVER
CORRECT
SCREW
LOCATION ’A’
INCORRECT
SCREWI
LOCATIONC,
I
Ls~
II
IINCORREC
ISCREW
FRICTION
CONTROL
KNOB (PIP)
LOCATION
CORRECT
SCREW
LOCATION
ICI
_t´•
I
FWD
FRICTION
INCREASE
.o
INCORRECT
SCREW
LOCATION
’D’
FUEL LINE
(INSIDE CENTER
CONSOLE)
CORRECT
SCREW
LOCATION ’B’
Figure
PART III:
i.
Replacement
Remove the
the
covers
W.L.
43.44
1.
of the Fuel Line
screw
attaching the
from the
center
forward and aft
console. Refer
clamps securing
to
center
Figure
console
covers to
the center console and
remove
2.
the Fuel Line to the side of the center console.
2.
Remove the two
4.
Disconnect any bindings tying the static line to the Fuel Line.
Loosen the fitting connecting the Fuel Line to the fuel selector valve.
NOTE
shop rags inside the center console under each end of the
Fuel Line to capture any fuel still present in the fuel line.
Place
5.
Loosen the
fitting connecting the
Fuel Line
to
the firewall union.
iii’’iiiiiiiii
Do not
permit
the firewall union to turn while
loosening
the
fitting.
Page
3 of 8
FUEL
SELECTOR
KNOB
SELECTORPLATE
AFT CENTER
FORWARD
CENTER
CONSOLE
COVER
CONSOLE
.COVER
FORWARD
CONSOLE
COVER
b
CENTER
CONSOLE
RH SIDE
O
oly;
o
CENTER
CONSOLE
LH SIDE
0,
Figure
6.
As
7.
Pull the forward
8.
gently
a
possible, pull
the aft
fitting of the
fitting of the Fuel
Pull the yoke fully aft.
9.
2.
Fuel Line away from the fuel selector valve.
Line away from the firewall union.
Remove the Fuel Line from the aircraft by working it
through the center console tunnel forward and to
right behind the instrument panel It may.be necessary to disconnect the.right hand defroster ductin~
to accomplish this step.
10. Install the replacement Fuel Line. Once the line has been
reinstalled, check both fittings for leaks.
1 i. Reinstall the center console
parts. Reinstallation steps are the opposite of the removal steps.
the
Il. Proceed to Part IV.
Page
4 of8
SERVICE LETTER NO. SL-I 12-50
Part IV:
i.
Emergenc]v Dump
Valve Cover Plate Attachment
Improvement
Figure 3. Plug the existing upper hole of the Emergency Gear Extension Valve Cover Plate ~´•ith
or equivalent.
Enlarge the two remaining holes to .125 diameter.
Drill an additional .125 diameter hole in the location shown in Figure 3.
Paint the cover plate to match the interior of the aircraft.
When the paint is dry, draw an arrow and write the word ’UP’ on the back side of the p late in a contrasting
color as shown in Figure 4.
Using a drill stop set to .125 or other form of marking, enlarge the forward and lower attachment holes
in the center console LH side panel to .155 +.002/-.000 dia. Using the cover as a template, drill a .ISs
Refer to
Duramix #1040
2.
5.
6.
upper aft attachment.
notches in the three attachment holes as shown in
+.002/-.000 dia. hole for the
7.
Cut the
keyway
cover
Figure
5. Install three MS271jl-2K
Rivnuts.
8.
9.
Plug the old upper attachment hole and any improperly drilled attachment holes with any of the following:
a.
CR2673-3-01Rivet
b.
CR2249-4-01 Rivet
c.
Driven BJ-3
or
BJ-4 Rivets.
Reattach the carpet to the center console.
cover plate using three MS24693-C4 Screws and three NAS391-B4P Washers
10. Reattach the
Figure
as
shown in
6.
PLUG
EXISTING
HOLE
sui
DRILL
ENLARGE
EXISTING
TO
DIA
IE II
HOLE
.125
.125
DIA
ii
ENIARGE
TO
.125
EXISTING
HOLE
DIA
l.oo
Figure
3. Cover Plate Modifications
Page
5
of 8
SERVICE LETTER NO. SL-I12-eO
~IARK
ii~
C=NTRAST!NG CaL~:R
Figure 4.
View from Back Side of Part
CENTER CONSOLE
LH
SIDE
EMERGENCY
GEAR
VALVE COVER
i
EXTENSION
(REF)
IF PRESENT, PLUG IMPROPERLY
DRILLED HOLE
.155+.002/-.000 DIA 8(
CUT KEYWAY NOTCH PER MS27131,
MATCH TO COVER PLATE, 3 PLACES.
MS27131-2K NUT, PLAIN,
BLIND
RIVIVUT, PROTRUDES FARSIDE (KEYED),
INSTALL FROM NEAR SIDE, 3 PLACES.
if
PRESENT, PLUG IMPROPERLY DRILLED HOLE
Figure
Page
6 of 8
,F.
SERVICE LETTER NO. SL-112-~0
COVER PLATE
MS24693-C4 SCREII~(
~AS391-84P ~ASHER
3 PLACES
Figure
ELECTRICAL LOAD: No
Change
WEIGHT AND BALANCE: No
SPARES AFFECTED:
No
6.
Change
Change
PUBL ICATIONS AFFECTED: The appropriate Maintenance Manuals will be amended as necessary by normal
revision action at
a
future date.
COMPLIANCE SECTION: Make
an
appropriate
entry
Letter No. SL-112-50, dated July 1,
Orientation
Fuel Line",
nance
in
airplane
maintenance records
as
follows: Service
1sds, entitled "Emergency Gear Extension Valve Cover
Inspection and Attachment Improvement, and Inspection and/or Replacement of
Reiain this Service Letter with the airplane ~naintedate
accumplished
records.
Page
7 of 8
This page
Page
8 of8
intentionally left
blank
Service Letter
7200 N.W. 63rd
Bethany, OK
73008
Date
July 31,
2001
INSPECTION OF CONTROL CABLE TERMINALS
MODELS AFFECTED: Models 112, 112B, 112TC, and 112TCA
To inform
operators of the possibility of primary flight control cable
cracking, initiated by surface corrosion, on cables that have 15
terminals
years time in service.
COMPLIANCE:
Commander Aircraft
Accomplishment
Company strongly
recommends that the
procedures
found in the
Instructions section of this service letter be followed within the next 100
or at the next annual inspection, whichever occurs first, and at every
thereafter
annual inspection
on any primary flight control cable that has 15 years time in service
hours time in service
or
longer.
flight control cable is replaced, the inspection procedure described in Part I of the
Accomplishment Instructions of this Service Letter is not required on that cable until it has 1 5
If a primary
years time in service.
BY WHOM WORK WILL BE ACCOMPLISHED: A
APPROVAL:
Engineering design aspects
are
Part I
SPECIAL TOOLS
Replacement cables
or
equivalent
approved.
4 hours
Part II
PARTS DATA:
FAA
P Mechanic
3 hours for each cable
for Part II
can
be
purchased from Commander Aircraft Company.
REQUIRED: 10X Magnifier
Part I
i.
2.
3.
Inspect
all MS21260 Terminals installed
on
primary flight control
cables for corrosion
or
cracking
safety wire or lockpin clips prior to inspection.
Using a 10X magnifier, visually inspect the shaft area of the threaded end of the terminal, close to the
wrench flats and the swaged end of the terminal for evidence of stress corrosion pits or cracking.
If no evidence of stress corrosion pits or cracking is found, verify cable tension is correct and safety the
terminal/turnbuckle barrel per the appropriate maintenance manual. Proceed to the Compliance Section
Remove
of this Service Letter.
4.
If evidence of stress corrosion
pits
or
cracking
is found, Proceed to Part n of the
Accomplishment
Instructions of this Service Letter.
Page
1 of 2
SERVICE LETTER NO. SL-113-’ 1
ACCOMPLISHMENT INSTRUCTIONS
Part II
Replacement
assembly
Remove and replace, per the appropriate maintenance manual, any cable assembly found to have evidence
i.
pits or cracking.
Once a cable assembly has been replaced, the inspection procedure described in Part I of this Service Letter
is not required on that cabl2 until it has 15 years time in service.
Proceed to the Compliance Section of this Service Letter.
of
2.
3.
of cable
(con’t):
stress
corrosion
ELECTRICAL LOAD: No
Change
WEIGHT AND BALANCE: No
SPARES AFFECTED:
No
Change
Change
The
appropriate
Maintenance Manuals will be amended
normal revision action at
COMPLIANCE SECTION:
Make
an
appropriate entry
a
in
airplane maintenance records
Service Letter No. SL-112-51, dated
July
2 of 2
as
31, 2001, entitled
Control Cable Terminals", accomplished
date
Letter with the airplane maintenance records.
Page
as
necessary
future date.
follows:
"Inspection
of
Retain this Service
by
Service Letter
Gulfstream American
C<)RPOHATI<)N
Commander Divilion
5001 North Rockwell Avenue,
Berhany, Oklahoma 73008
SERVICE LETTER NO. SL-112TC-27A
(Supersedes Service
Letter No.
SL-112TC-27, dated
4 June
1976, in its entirety)
I
18 January 1982
1
CABIN NOISE REDUCTION
MODELS AFFECTED:
MODEL
13001 THRU 13063.
NOTE
IF BASIC SERVICE LETTER NO. SL-112TC-27 HAS BEEN
COMPLIED WITH, DISREGARD THIS SERVICE LETTER.
COMPLIANCE:
REDUCE NOISE LEVEL WITHIN CABIN AREA.
NOTE
IF
ANY
PROBLEMS
ARE
ENCOUNTERED WHILE
YOUR NEAREST GULFSTREAM COMMANDER SINGLE
ENGINE SERVICE FACILITY.
APPROVAL:
A
P MECHANIC OR
EQUIVALENT
SEVEN (7) HOURS.
PARTS DATA:
PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH I
NEAREST GULFSTREAM
COMMANDER SINGLE
ENGINE
SERVICE
FACILITY FOR
$189.13.1
REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING I
YOUR
SERVICE LETTER NO. SL-112TC-27A KIT CONSISTING OF THE FOLLOWING:
Price
sub]ect
to
change without notice.
QTY
PART NO.
DESCRIPTION
1
ea,
315007-3
Stiffener
1
ea:
315007-4
Stiffener
lea.
315007-5
lea.
315007-6
Clip
Clip
2
ea.
315008-3
Panel
2
ea.
315008-5
Panel
2
ea.
315008-7
1
ea.
49083-9
Panel
Blanket
1
ea.
49083-11
lea.
49083-13
1
ea.
49083-15
1
ea.
49083-17
1
ea,
49083-19
2
ea.
49083-33
Blanket
Blanket
Blanket
Blanket
Blanket
Blanket
2
ea.
49310-25
Blanket
2
ea.
49310-27
2
ea.
49310-29
Blanket
Blanket
EC2216 A/R
Ipt.
lea.
Service Letter No. SL-112TC-27A
lea.
SPECIAL TOOLS:
Epoxy
Compliance
CODE NO.
2299801
Card
Instruction
NONE.
Page
1 of 5
PARTI
pilot
and
copilot
1.
Remove
2.
Remove left and
right
scuff plates.
3.
Remove left and
right
lower
4.
Remove left and
right door jamb moulding
5.
Remove ash trays from left and
6.
Remove left and
7.
Remove carpet from forward cabin
right
seats.
plastic frames.
right
as
necessary to facilitate removal of forward side
forward side
panels.
panels.
panels.
forward side
area.
PART II
where noise reduction
panels
to be installed with 400
1.
Sand all
2.
Wipe sanded
3.
Install 315007-3 and -4 stiffeners and 315007-5 and -6
areas
area
are
clean with Stoddard solvent
or
grit sandpaper (see Figures
1 and 2.).
equivalent.
clips
as
shown in
Figure
2.
NOTE
I
1
Bond stiffener to fuselage skin
to stiffener before installation.
required
4.
Cut and trim 49083 blankets
5.
Apply
6.
Cut and trim 49310-25 and -27 blankets
7.
Apply
8.
Install 49310-29 blankets
9.
Reclean floor
as
to clear
by applying EC2216
equipment
installed
on
A/B epoxy
aft side of engine ffiewall (see
Figure 2.).
EC1403 adhesive to rubber side of trimmed blankets and attach to firewall.
as
required
to install above and below stiffeners installed in
EC1403 adhesive to trimmed blankets and attach to
area
by inserting
blanket
with Stoddard solvent
10.
Immediately after cleaning floor
II.
Press 315008
panels
in
place
area
or
fuselage skin (see Figure 2.).
through airframe lightening holes.
equivalent.
apply a-part
and utilize
step 3. above.
weights
EC2216 A/B
to hold
Epoxy
to cleaned
panels against
area.
floor surface until epoxy has cured.
NOTE
Allow
epoxy
to
cure
for
a
minimum
of 8
hours
before
installing carpet.
1
equipment removed
12.
Install
13.
Fill out and mail
ELECTRICAL LOAD:
Compliance Card.
NO CHANGE.
WEIGHT AND BALANCE:
The
WEIGHT (LBS)
16
Page
2 of 5
in Part I.
weight and
balance
change resulting
II-ARM (INCHES)
76.1
from this Service Letter installation is
H-MOMENT (INCH-LBS)
1247
as
follows:
GERVICE LETTER NO. SL-112TC-27A
5,
j/l
r-
i
FWD
I
315008-3
icl I
315008-5PANEL
PIIRCRAFT
CL
VIEW LOOKING DOWN
AT CABIN FLOOR
Figure
i.
Page 3
ol 5
SERVICE LETTER NO. BL-112TC-27A
~a,
COAT SURFACE WITH
49310-25 BLAM(ET
(TYP BOTH SIDES)
EC2216A/B
EPOXY
STA
80.3
~TA\
I
62.5
I
:;:::I
10-29 BLANKET
(TYP
BOTH
SIDES)
9.00"
49310-27 BLANKET
(TYP BOTH SIDES)
315007-3 STIFFENER AND
315007-5 CLIP SHOWN
315007-4 STIFFENER
AND 315001-6 CLIP OPPOSITE
FIREWALL
(REF)
MS20615M4 RIVET
-C~
a4
RIVET70AD4
49083-9 BLANKET
49083-17 BLANKET
49083-11 BLANKET
49083-13 BLANKET
FIREWALL
(RE Fl
WOIIE
TRIM FIREWALL BLANKETS
AS NECESSARY TO CLEAR
INSTALLED EQUIPMENT
49083-33
BLANKET
(2 PLS)
49083-19 BLANKET
49083-15 BLANKET
Cigur´• 2.
Page
4 of 5
NONE.
Make appropriate entry in airplane maintenance records
RECORD COMPLIANCE:
112TC-27A, dated 18 January 1982, entitled "Cabin Noise Reduction", accomplished
as
follows:
Service Letter No.
""I
I
Page
5 oP 5

Service Information and ADs - the Commander Owners Group

Transcription

Similar documents

Inżynier Utrzymania Ruchu – Elektryk

Davis Development Group and Landerhaven Corporate

Serial Number Designations

Kessington before and after

Aries Windvane Mounting Instructions

Tudeshk ref. 20588 Around 1950 Related to the Nain carpets Soft

Equinox Map

RG FLOOR - ReF. 6667 - "LONDON"

Auction

NORMAN ROCKWELL THE DUGOUT