Issued: June 16, 1997 227-27-042

Page 1 of 9

SERVICE BULLETIN

SA227 SERIES AIRCRAFT

Flight Controls

Control Column Pivot Improvement

1. PLANNING INFORMATION

A. Effectivity:

All SA227 Series Airplanes

B. Reason:

To provide operators with an improved control column pivot design that adds strength

as well as maintainability to the installation.

C. Description:

Replace existing CF-5/8-S roller bearing, 26-21352 doubler with new 27-21169 control

column pivot. Inspect existing 26-21065 bracket for cracks, remove and replace bracket

if cracks are found. The new pivot consists of a 27-21169-007 fitting which is provided

undrilled (fastener holes to be picked up from old doubler) , a KRJ8-UDYB-016 bearing

(KARON) is installed in the fitting with LOCTITE 609, and 27-21169-005 pin is installed

in the existing bearing cup on the control column, pin installation is accomplished by

match drilling the bearing cup to the pin through-hole (SAT1518 tool jig available) and

installing spring pin and safety wire.

NOTE: Kit A will include SAT1518 tool jig, control column, and Kit B will include

parts for one ship set.

D. Compliance:

Highly Recommended, accomplish at next scheduled access, in conjunction with Phase or

Letter Check Inspection.

E. Approval:

FAA Approved for Engineering Design.

F. Manpower:

It is recommended that owners obtain an estimate from their nearest Fairchild Aircraft (FA)

authorized Service Facility/Maintenance Department.
Issued: June 16, 1997 227-27-042

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SERVICE BULLETIN

SA227 SERIES AIRCRAFT

G. Material-Cost and Availability:

(1) Cost:

Because of pricing fluctuations, individual cost estimates should be obtained from your

normal material procurement outlet.

Additional material cost information may be contained in the Index or the Letter of

Transmittal.

(2) Availability:

Parts are available.

H. Tooling-Price and Availability:

No special tooling required.

I. Weight and Balance:

Increase (+) weight 0.16 pound, increase (+) moment 15.37 inch-pounds.

J. Reference:

Fairchild Aircraft (FA) Drawing 26-71004, 26-21352, 27-21000 and 27-21169.

NOTE: References are for manufacturers’ use only.

K. Other Publications Affected:

SA227 Series Illustrated Parts Catalog (IPC) and Maintenance Manual (MM).
Issued: June 16, 1997 227-27-042

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SERVICE BULLETIN

SA227 SERIES AIRCRAFT

2. ACCOMPLISHMENT INSTRUCTIONS

A. Removals

NOTE: Surface finish of bare metal, surface cleaning, fastener hole drilling, countersinks, deburring and fastener installation shall be accomplished as

described in SA226/227 Series Structural Repair Manual (SRM) Chapter

51, unless otherwise noted. Clamp and/or Cleco all parts as they are drilled

to prevent part shifting.

(1) Remove cockpit furnishings and floorboards as required to gain access to Pilots

(LH) and Copilots (RH)control column roller bearings.

(2) Remove existing LH/RH CF-5/8-S control column roller bearing and 26-21352 doubler,

scrap attaching hardware.

NOTE: Make note of washer stack up between LH/RH roller bearing and doubler,

these washers were used for shims and the same number of AN960C816

and/or AN960C816L washers will need to be installed between new

KRJ8-UDYB-016 bearing and head of 27-21169-005 pin to maintain

control column position on final installation.

NOTE: Removed LH/RH 26-21352 doubler(s) will be used to pick up fastener

holes on new LH/RH 27-21169-007 fitting and should be marked on

removal to avoid confusion (LH, RH, up, down, forward, aft, inboard,

outboard).

(3) Inspect LH/RH 26-21065 bracket for cracks, no cracks allowed. Remove and

replace LH/RH 26-21065 bracket if cracks are found.

(4) Remove LH/RH roller bearing and nutplates from 26-21352 doubler, retain roller

bearing attaching hardware and scrap nutplates.

(5) Install roller bearing on opposite side of 26-21352 doubler using previously

removed hardware, as shown in FIGURE 1.

(6) Push LH/RH roller bearing into bearing hole of LH/RH 27-21169-007 fitting from

inboard side (flat side), align so that top of 26-21352 doubler is parallel to top

of fitting and clamp as required to prevent movement during drilling.

(7) Using the existing fastener holes in LH/RH 26-21352 doubler as guides, drill

0.190 to 0.194 inch diameter hole through LH/RH 27-21169-007 fitting (inner

attach holes), 4 places, as shown in FIGURE 1.

(8) Remove clamp from LH/RH 27-21169-007 fitting. Scrap LH/RH 26-21352

doubler, bearing and attaching hardware.
Issued: June 16, 1997 227-27-042

Page 4 of 9

SERVICE BULLETIN

SA227 SERIES AIRCRAFT

(9) Layout and drill 0.190 to 0.194 inch diameter hole through LH/RH 27-21169-007

fitting (outer attach holes), 4 places, as shown in FIGURE 2. Deburr holes, 8

places.

(10) Enlarge existing bearing through-hole in LH/RH 26-21065 bracket, as shown in

FIGURE 1.

(11) Temporarily place new KRJ8-UDYB-016 bearing in LH/RH 27-21169-007 fitting

and check for proper fit in LH/RH 26-21065 bracket.

NOTE: It is permissible to remove a maximum of two (2) rivets if their location

interferes with top of fitting or bearing, rivet hole(s) may be left open.

(12) Remove KRJ8-UDYB-016 bearing from LH/RH 27-21169-007 fitting.

(13) Temporarily install LH/RH 27-21169-007 fitting and using outer fastener holes

in fitting as guides, drill 0.190 to 0.194 inch diameter hole through LH/RH

26-21065 bracket, 4 places.

(14) Remove LH/RH 27-21169-007 fitting and deburr holes in LH/RH 26-21065

bracket, 4 places.

(15) Locate SAT1518 tool jig onto LH/RH 26-71004 bearing cup on control column,

tighten at desired position (0° to 90°) and drill 0.125 to 0.129 inch diameter hole

through both sides of cup, as shown in FIGURE 2.

(16) Remove tool jig and deburr holes.

(17) Repeat Steps 2.A. (2) through (16) for opposite side.

B. Installation

(1) Locate MS21073L3 nutplate on outboard side of LH/RH 27-21169-007 fitting,

8 places and drill 0.097 to 0.102 inch diameter hole, 2 places each nutplate,

deburr holes, 16 places. Countersink inboard side of nutplate fastener holes,

100° x 0.175 to 0.183 inch diameter, 16 places, as shown in FIGURE 2.

(2) Install MS21073L3 nutplate, using 2 each, MS20426AD3-( ) rivets on outboard

side of LH/RH 27-21169-007 fitting, 8 places, as shown in FIGURE 2.

(3) Clean bearing hole of LH/RH 27-21169-007 fitting and KRJ8-UDYB-016 bearing,

install bearing from flat side of fitting, using LOCTITE 609.

(4) Install LH/RH 27-21169-005 pin into LH/RH bearing cup, align bearing cup/pin

holes, install MS171532 spring pin and safety in accordance with MS33540

using MS20995C32 lockwire.
Issued: June 16, 1997 227-27-042

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SERVICE BULLETIN

SA227 SERIES AIRCRAFT

(5) Install required stack up of AN960C816 and/or AN960C816L washers (determined in Step 2.A. (2) Note) onto LH/RH 27-21169-005 pin.

(6) Position LH/RH 27-21169-007 fitting onto LH/RH 27-21169-005 pin, install 8

each AN3-4A bolts and AN960-10L washers.

(7) Repeat Steps 2.B. (1) through (6) for opposite side.

(8) Perform elevator functional check, as described in SA227 MM.

(9) Replace all cockpit furnishings and floorboards removed to accomplish this

inspection/replacement.

C. Complete aircraft records according to F.A.R. 43.9.

D. Complete and mail Service Bulletin compliance form.
Issued: June 16, 1997 227-27-042

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SERVICE BULLETIN

SA227 SERIES AIRCRAFT

3. MATERIAL LISTING

Replacement or alternate parts approved via Fairchild Aircraft drawings are acceptable

substitutes for use in accomplishing this bulletin.

The following materials are required to accomplish the instructions outlined in this service

bulletin. SB227-27-042 Kit A or B can be ordered and will contain all materials listed except

common stock items which may be obtained locally or ordered separately.

KIT A - Contains SAT1518 Tool Jig, Control Column.

NEW P/N QTY. KEYWORD OLD P/N DISPOSITION

SAT1518 1 Tool Jig, N/A N/A

Control Column

227-27-042-PL-A 1 Packing List N/A N/A

KIT B - Contains Parts for One Ship Set, Except Common Stock Items.

NEW P/N QTY. KEYWORD OLD P/N DISPOSITION

27-21169-007 2 Fitting 26-21352-001, Scrap

-005, -007 or -007P

27-21169-005 2 Pin CF-5/8-S Scrap

AN3-4A * 16 Bolt AN3-5A Scrap

AN960-10L * 16 Washer AN960-10L Scrap

AN960C816 * A/R Washer AN960C416 Scrap

AN960C816L * A/R Washer AN960C416L Scrap

KRJ8-UDYB-016 § 2 Bearing N/A N/A

MS171532 2 Spring Pin N/A N/A

MS21073L3 * 16 Nutplate N/A N/A

MS20426AD3-( ) * 32 Rivet MS20426AD3 Scrap

609 * A/R LOCTITE N/A N/A

227-27-042-PL-B 1 Packing List N/A N/A

* Indicates materials are common stock items which will not be included in the kit.

These parts may be obtained locally or ordered separately.

§ Indicates KAMATICS Part Number.
Issued: June 16, 1997 227-27-042

Page 7 of 9

SERVICE BULLETIN

SA227 SERIES AIRCRAFT

CONTROL COLUMN IMPROVED PIVOT

INSTALLATION INSTRUCTIONS

FIGURE 1

7B270421

EXISTING 26-21352-001/-005/-007 OR -007P DOUBLER ASSEMBLY

EXISTING 26-21352-001/-005/-007 OR -007P DOUBLER ASSEMBLY

FWD INBD

(1) REMOVE CF-5/8-S ROLLER BEARING AND 4 NUTPLATES, IF INSTALLED, FROM

 26-21352 DOUBLER.

(2) INSTALL ROLLER BEARING ON OPPOSITE SIDE OF DOUBLER.

(3) POSITION DOUBLER ONTO INBOARD SIDE OF NEW 27-21169-007 FITTING.

(4) CLAMP DOUBLER AND FITTING TOGETHER, MATCH DRILL FITTING,

 0.190 TO 0.194 INCH DIAMETER HOLE, 4 PLACES, USING EXISTING FASTENER

 HOLES IN DOUBLER AS GUIDE.

26-21352 DOUBLER

(1) (2) (3) (4) 27-21169-007 FITTING

INCREASE EXISTING 0.750 INCH DIAMETER

HOLE TO 1.00 INCH DIAMETER HOLE.

COPILOTS SIDE, LOOKING OUTBOARD

(PILOTS SIDE OPPOSITE)

COPILOTS SIDE, LOOKING FORWARD

(PILOTS SIDE OPPOSITE)

COPILOTS SIDE, LOOKING DOWN

(PILOTS SIDE OPPOSITE)

FWD

COPILOTS SIDE, LOOKING OUTBOARD

(PILOTS SIDE OPPOSITE)

FWD

EXISTING FASTENERS THAT INTERFERE WITH

27-21169-007 FITTING MAY BE REMOVED AND

HOLES LEFT OPEN, (2 MAXIMUM).

INSPECT 26-21065 BRACKET FOR

CRACKS. IF ANY CRACKS ARE FOUND,

REMOVE AND REPLACE BRACKET.
Issued: June 16, 1997 227-27-042

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SERVICE BULLETIN

SA227 SERIES AIRCRAFT

CONTROL COLUMN IMPROVED PIVOT

INSTALLATION INSTRUCTIONS

FIGURE 2

7B270422

COPILOTS CONTROL COLUMN

(PILOTS SIDE OPPOSITE)

A

DETAIL A

(PILOTS SIDE OPPOSITE)

FWD

DRILL 0.125 TO 0.129 INCH DIAMETER HOLE

THROUGH CUP, USING SAT1518 TOOL JIG.

CAN BE CLOCKED FROM 0° TO 90° AS REQUIRED.

0° TO 90°

27-21169-005 PIN

AN960C816 AND/OR

AN960C816L WASHER(S)

QUANTITY AS REQUIRED

FOR SHIMMING.

AN3-4A BOLT

AN960-10L WASHER

8 PLACES

27-21169-007 FITTING

SHOWN WITH,

KRJ8-UDYB-016 BEARING

INSTALLED.

MS21073L3 NUTPLATES

OMITTED FOR CLARITY.

INSTALL MS171532 SPRING PIN,

SAFETY USING MS20995C32

LOCKWIRE.

B

B C

INSPECT 26-21065 BRACKET C

FOR CRACKS. IF ANY CRACKS

ARE FOUND, REMOVE AND

REPLACE BRACKET.
Issued: June 16, 1997 227-27-042

Page 9 of 9

SERVICE BULLETIN

SA227 SERIES AIRCRAFT

CONTROL COLUMN IMPROVED PIVOT

INSTALLATION INSTRUCTIONS

FIGURE 2, VIEW B-B AND C-C

7B270422B

VIEW C-C

27-21169-007 FITTING

COPILOTS SIDE - LOOKING INBOARD

(PILOTS SIDE OPPOSITE)

VIEW B-B

COPILOTS SIDE - LOOKING OUTBOARD

(PILOTS SIDE OPPOSITE)

FWD

FWD

1.345 INCH

1.345 INCH

27-21169-007 FITTING

DRILL 0.097 TO 0.102 INCH

DIAMETER HOLE, 2 PLACES

EACH NUTPLATE.

COUNTERSINK FAR SIDE OF

FITTING, 100° X 0.175 TO 0.183

INCH DIAMETER, 16 PLACES.

INSTALL MS21073L3 NUTPLATE

ON NEAR SIDE OF FITTING,

USING 2 EACH, MS20426AD3-( ),

8 PLACES.

DRILL 0.190 TO 0.194 INCH

DIAMETER HOLE, 8 PLACES

(4 PLACES MATCH DRILLED

TO 26-21352 DOUBLER).

26-21352 DOUBLER

(SHOWN FOR REFERENCE

ONLY)

KRJ8-UDYB-016 BEARING

INSTALL FROM

FAR SIDE, USING

LOCTITE 609.