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Issued: June 16, 1997 226-27-061 Page 1 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES Flight Controls Control Column Pivot Improvement
1. PLANNING INFORMATION A. Effectivity:
All SA226 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 226-27-061 Page 2 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES 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:
SA226 Series Illustrated Parts Catalog (IPC) and Maintenance Manual (MM).
Issued: June 16, 1997 226-27-061 Page 3 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
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, d rill
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 226-27-061 Page 4 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
(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 226-27-061 Page 5 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
(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 SA226 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 226-27-061 Page 6 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
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. SB226-27-061 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 226-27-061-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 226-27-061-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 226-27-061 Page 7 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
CONTROL COLUMN IMPROVED PIVOT
INSTALLATION INSTRUCTIONS FIGURE 1 26B270471 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 226-27-061 Page 8 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
CONTROL COLUMN IMPROVED PIVOT
INSTALLATION INSTRUCTIONS FIGURE 2 26B270472 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 CINSPECT 26-21065 BRACKET FOR CRACKS. IF ANY CRACKS ARE FOUND, REMOVE AND REPLACE BRACKET.
Issued: June 16, 1997 226-27-061 Page 9 of 9
SERVICE BULLETIN AIRCRAFTSA226 SERIES
CONTROL COLUMN IMPROVED PIVOT
INSTALLATION INSTRUCTIONS FIGURE 2, VIEW B-B AND C-C 6B270612B 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.