Issued: February 24, 1997 Revised: December 5, 2014 226-27-060 R2 Page 1 of 1 P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421 

# SERVICE BULLETIN

Revision Transmittal Sheet TO: HOLDERS OF SA226 SERIES SERVICE INFORMATION MANUALS

This is Revision 2 to SA226 Series Service Bulletin 226-27-060, CONTROL COLUMN ROLLER BEARING AND ELEVATOR ROD END BEARING INSPECTION / REPLACEMENT , Issued: December 11, 1996; Revised: December 5, 2014. 1. REASON This service bulletin has been completely re-written to address issues and differences between the earlier revision of the bulletin, AD 97-02-02, SA226 Illustrated Parts Catalog (IPC) Chapters 27-30-02 and 27-30-03, and the SA226 Maintenance Manual Chapter 05-10-00. All changes are denoted by revision bar in the left hand margin. 2. INSTRUCTIONS A. This Service Bulletin has been completely reprinted. Remove and discard all pages of prior issue and replace with this revision.
B. Place this revision transmittal sheet in front of the service bulletin. C. Please insert the attached revised Service Bulletin Index pages.P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421CHAPTER 27 – FLIGHT CONTROLS

CHAPTER 27 INDEX Page 7 of 9 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

27-054 05-22-95 Rudder Torque Tube SA226-T, S/N T258-275, Drain Hole T277-291, SA226-T(B), S/N T(B)276, T(B)292-417, SA226-AT, S/N AT043-074, SA226-TC, S/N TC222-419. 27-055 08-09-95 Rudder Control Lock Weldment SA226-T, S/N T258-275, and Bellcrank Inspection- T277-291, Optional Improved Strength SA226-T(B), S/N T(B)276, Rudder Torque Tube, Control T(B)292-417, Lock Weldment and Aluminum SA226-AT, S/N AT043-074, Bellcrank Installation SA226-TC, S/N TC222-419. 27-056 00-00-00 NOT ISSUED 27-057 09-08-95 Rudder Trim Tab Actuator All SA226 Series Airplanes Decal 27-058 05-15-96 Rework of UP/DOWN Elevator All SA226 Series Airplanes Quadrant Stops and LH/RH Rudder Bellcrank Stops 27-059 00-00-00 NOT ISSUED 27-060 12-11-96 Control Column Roller Bearing All SA226 Series Airplanes (R) 02-24-97 and Elevator Rod End Bearing (R) 12-05-14 Inspection/Replacement 27-061 06-16-97 Control Column Pivot All SA226 Series Airplanes Improvement 27-062 11-18-98 Installation of Simmonds All SA226 Series Airplanes Precision P/N DL5040M5 with Barber Colman, P/N and/or DL5040M6 Pitch Trim 27-19008-001/-002 Pitch Actuator (PTA) Trim Actuator Installed. 27-063 05-11-99 Installation of P/N All SA226 Series Airplanes (R) 12-27-99 DL5040M8, Simmonds with P/N 27-19008-001/-002/ (R) 11-18-02 Precision Pitch Trim -004/-005/-006/-007 Bar Actuator (PTA) ber-Colman PTA Installed.

Issued: February 8, 1971 Revised: December 5, 2014CHAPTER 27 INDEX Page 8 of 9 CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX

Issued: February 8, 1971 Revised: September 04, 2014 27-064 03-08-99 Installation of All SA226 Series Airplanes 27-19008-006/-007 with P/N 27-19008-001/-002/ Barber-Colman Pitch Trim -004/-005 Barber-Colman Actuator (PTA Installed. PTA
27-065 12-05-00 Installation of Fairleads All SA226 Series AT and TC at F.S. 174.06 Airplanes 27-066 09-29-03 Life Limit for Rudder Gust All SA226 Series Airplanes Lock Assembly, Part Number 27-70066-001, of 5000 Hours 27-067 04-02-04 Inspection of 26-72003 Rudder All SA226 Series Airplanes Pedals for cracks
27-068 00-00-00 NOT ISSUED
27-069 00-00-00 NOT ISSUED 27-070 09-19-08 Gravel Guard Installation All SA226 Series Airplanes 27-071 04-28-09 Pilot's and Copilot's Control All SA226 Series Airplanes Column Access Panels Modi fi cation 27-072 06-27-11 Flight Control Cable SA226-T, S/N T265, T267 Replacement SA226-T(B), S/N T(B)348 SA226-TC, S/N TC277 SA226-AT, S/N AT071, AT072, AT073 27-073 06-10-11 Inspection and Repair / All SA226 Series Airplanes (R) 09-06-11 Replacement of Pitch Trim (R) 10-14-11 Actuator Fuselage Fittings 27-074 06-06-13 Inspection and Lubrication of All SA226 Series Airplanes (R) 09-30-13 the Aileron Control Cable (R) 10-23-13 Chain in the Pilot's and Co- Pilot's Control Columns 27-075 09-04-14 Inspection/Replacement of the All SA226 Series Airplanes Aileron Control System Rod End BearingsIssued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 1 of 14 

# SERVICE BULLETIN SA226 SERIES

Flight Controls Control Column Roller Bearing and Elevator Rod End Bearing Inspection / Bolt Replacement 1. PLANNING INFORMATION A. Effectivity: All SA226 Series Airplanes
B. Reason: (1) To prevent possible fatigue failure of control column pivot bearing. (2) To prevent damage to elevator rod end bearing retainer/dust covers by ensuring appropriate hardware con fi guration for the attachment of the elevator rod assembly to the elevator walking beam and control column. (3) To prevent possible fatigue failure of the elevator control rod to elevator walking beam attach bolt. This service bulletin has been completely re-written to address issues and differences between the earlier revision of the bulletin, AD 97-02-02, SA226 Illustrated Parts Catalog (IPC) Chapters 27-30-02 and 27-30-03, and the SA226 Maintenance Manual Chapter 05-10-00. All changes are denoted by revision bar in the left hand margin. C. Description: This service bulletin addresses three separate issues that are identi fi ed herein as 1.C.(1): Control Column Pivot, 1.C.(2): Elevator Rod End, and 1.C.(3): Elevator Rod Assembly Attachment Hardware. See Table 1 for compliance requirements. (1) Control Column Pivot (see Figure 1) To prevent fatigue cracking of the control column pivot bearing, three possible actions are required: (a) Inspect security of control column roller pivot con fi guration by application of torque to the pivot bearing and ensuring no movement occurs as de fi ned in this service bulletin, or; (b) Replace the control column pivot bearings and associated hardware with new or newly de fined parts and ensure the security of control column pivot by application of torque to the pivot bearing and ensuring no movement occurs as de fi ned in this service bulletin, or; (c) Incorporate the revised control column pivot con fi guration de fi ned in Service Bulletin 226-27-061.Issued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 2 of 14 (2) Elevator Rod Ends (see Figure 2) To ensure the integrity of the elevator control system rod, the following action is required: (a) Inspect elevator control rod end(s) for excessive wear or possible damage to bearing retainer/dust covers. Replace rod ends if damaged. (3) Elevator Rod Assembly Attachment Hardware (see Figure 2)To ensure the integrity of the elevator control system rod attachment bolt, the following actions are required: (a) Inspect elevator control rod assembly attachment hardware con fi guration to ensure the speci fi c hardware and hardware arrangement is as de fi ned by this service bulletin, and; (b) Replace elevator rod assembly to elevator walking beam attachment bolt and washer with new parts as required by this service bulletin. D. Compliance: Mandatory . Actions in accordance with Table 1 requirements.Issued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 3 of 14 

# SERVICE BULLETIN SA226 SERIES

Condition Initial Action Repetitive Action Control Column Pivot Bearing has been torque checked, or replaced per SB 226-27-060 (any revision) within the last 10,000 hours TIS. Accomplish the following:
In aircraft records, within 200 hours TIS after the effective date of this SB, indicate date of last torque check, and either: (1) Replace control column pivot bearing per Step 2.B. within 10,000 hours TIS <2> or within the next 1,000 hours TIS from the date of bulletin, whichever occurs later.

or

------------------------------------------------------------- (2) Incorporate SB 226-27-061 per Step 2.C. <3><4>, within 10,000 hours TIS <2> or withinthe next 1,000 hours TIS from the date of bulletin, whichever occurs later. <7> Accomplish the corresponding repetitive action:

(1) Replace control column pivot bearing per Step 2.B. every 10,000 hours TIS <2>.

or

------------------------------------------------------------------ (2) No repetitive action. <3><4>.

Control Column Pivot Bearing has not been torque checked, or replaced, within the last 10,000 hours TIS per SB 226-27-060 (any revision). Accomplish one of the following: (1) Torque check pivot bearing per Step 2.A. within 200 hours TIS after the effective date of this SB, and replace control column pivot bearing per Step 2.B. within the next 1,000 hours TIS from the date of bulletin <6>

or

------------------------------------------------------------- (2) Torque check pivot bearing per Step 2.A. within 200 hours TIS after the effective date of this SB, and incorporate SB 226-27-061 per Step 2.C. <3><4>, within the next 1,000 hours TIS from the date of bulletin <6><7> Accomplish the corresponding repetitive action: (1) Replace control column pivot bearing per Step 2.B. every 10,000 hours TIS <2>.

or

------------------------------------------------------------------ (2) No repetitive action. <3><4>

Control column pivot con figuration has been revised per SB 226-27-061. In aircraft records, indicate completion of Step 2.C. of this Service Bulletin. <3> No repetitive action.

Elevator rod attachment hardware and its con fi guration complies with SB 226-27-060 (any revision), at the date of this SB. (There has been no con figuration changes since original compliance with the SB) In aircraft records, indicate current date as compliance with SB 226-27-060, and replace the elevator rod to walking beam attachment bolt per Step 2.D. within 10,000 hours TIS <2> or within 1,000 hours from the date of this SB, whichever occurs later. Replace elevator rod bolt per Step 2.D. every 10,000 hours TIS <2>.

Elevator rod attachment hardware and its con fi guration does NOT comply with SB 226-27-060 (any revision). Within next 200 hours TIS from the effective date of this SB, comply with Step 2.D. Replace elevator rod bolt per Step 2.D. every 10,000 hours TIS <2>.



### TABLE 1 COMPLIANCE REQUIREMENTSIssued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 4 of 14 Notes: <1> Compliance with this Service Bulletin requires complying with Step 2.D. AND with either Step 2.A. or 2.B. or 2.C. <2> From time of last replacement <3> Incorporation of SB 226-27-061 complies with Supplemental Inspection Document (SID) Supplemental Inspection No. 27-31-01 and eliminates the control column pivot bearing time replacement requirement. (Replace pivot bearing every 10,000 hours TIS) <4> The column pivot con fi guration must be revised per SB 226-27-061 prior to 35,000 hours airplane total TIS or within the next 1,000 hours TIS from the effective date of this Service Bulletin, whichever occurs later. 5 TIS - Time in Service (Flight Hours) <6> Performing a replacement bearing initial action within 200 Hours TIS after the effective date of this SB has the bene fi t of eliminating the need for the initial torque check and allows for an additional 10,000 hours TIS prior to the need for repetitive action. <7> There is an additional requirement to comply with SB 226-27-061 per the Supplemental Inspection Document (SID). Therefore, if SB 226-27-061 is not complied with here, compliance with 226-27-061 will be required per the Supplemental Inspection Document (SID).



### TABLE 1 NOTES <1>Issued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 5 of 14 

# SERVICE BULLETIN SA226 SERIES

E. Approval: This Service Bulletin is approved by the FAA Airplane Certi fi cation Of fice (ACO), ASW150. F. Manpower: M7 Aerospace estimates the following manhours to accomplish the different aspectsof this service bulletin. The estimate is for direct labor only accomplished by an experienced crew. Adjust the estimate with operator task hour data as necessary. (1) Control Column Pivot, pivot bearing torque check (Step 2.A.) - 2 hours (2) Control Column Pivot, pivot bearing replacement (Step 2.B.) - 8 hours (3) Control Column Pivot, new pivot design (Step 2.C.) - 20 hours (4) Elevator Rod Ends and Attach Bolt (Step 2.D.) - 4 hours G. Material-Cost and Availability: (1) Cost: Because of pricing fl uctuations, 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: Negligible
NOTE : It is recommended the aircraft operating weight be re-established after incorporating 20 service bulletins classi fi ed as having negligible impact on aircraft weight and balance. This recommendation is derived from data provided in FAA Advisory Circular 120-27.
J. Reference: M7 Aerospace Drawing 26-71004 (latest FAA Approved revision) M7 Aerospace Drawing 26-21352 (latest FAA Approved revision)
NOTE: References are for manufacturers’ use only.Issued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 6 of 14 K. Other Publications Affected: SA226 Series Illustrated Parts Catalog (IPC) SA226 Series Maintenance Manual (MM) ST-UN-M002, SA226 Airframe Inspection Manual 2. ACCOMPLISHMENT INSTRUCTIONS Compliance with this Service Bulletin requires complying with Steps 2.D. and with either Step 2.A. or 2.B. or 2.C. Refer to Table 1. A. Control Column Pivot Bearing Inspection (1) Remove cockpit furnishings and fl oorboards as required to gain access to Pilot's and Copilot's control column roller bearings and elevator control rod end(s) as indicated in the SA226 Maintenance Manual, Chapter 25. (2) Layout and enlarge Pilot's and Copilot's cutout as shown in FIGURE 1. Deburr and surface finish bare metal with alodine and epoxy polyamide primer in accordance with SA226/227 Structural Repair Manual (SRM), Chapter 51-32-02. (3) Using a calibrated torque wrench, apply 60.0 inch/pounds (+5.0 / -0.0 in-lbs) torque to the MS21044N4 nut securing the Pilot's and Copilot's control column roller bearings to the 26-21352-001 or -005 doubler assemblies. No movement is allowed. (4) If nut movement occurs, remove and replace components and hardware per Step 2.B. B. Control Column Pivot Bearing Replacement (1) Remove cockpit furnishings and fl oorboards as required to gain access to Pilot's and Copilot's control column roller bearings and elevator control rod end(s) as indicated in the SA226 Maintenance Manual, Chapter 25. (2) Layout and enlarge Pilots and Copilots cutout as shown in FIGURE 1. Deburr and surface fi nish bare metal with alodine and epoxy polyamide primer in accordance with SA226/227 SRM, Chapter 51-32-02. (3) Remove the CF-5/8-S bearings, MS21044N4 nuts and associated washers and the 26-21352-001 or -005 doubler assemblies and associated hardware indicated in Figure 1.Issued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 7 of 14 

# SERVICE BULLETIN SA226 SERIES

CAUTION : PAY PARTICULAR ATTENTION TO SA226 MAINTENANCE MANUAL CHAPTER 27-30-01 WITH REGARDS TO BLOCKING WHEN DISCONNECTING/WORKING WITH ELEVATOR CONTROL CABLES DUE TO SPRING TENSION ON CABLES. (4) Destroy or permanently mark the removed CF-5/8-S bearings to ensure no future use of the bearings. (5) Install new CF-5/8-S bearings (or acceptable alternates listed in Step 3) with MS21042L4 nuts and associated washers per Figure 1 using a calibrated torque wrench to apply 70.0 in-lbs (+5.0 / -0.0 in-lbs) torque to the nut and bearing. Install 26-21352-007 doubler assemblies or 26-21352-007P doublers per Figure 1.
NOTE : The 26-21352-001 doubler assembly is attached to the airplane structure using MS21042L3 nuts, AN3-5A bolts, and AN960-10L washers. The 26-21352-005 doubler assemblies incorporate MS21073L3 nutplates in place of the MS21042L3 nuts. P/N 26-21352-007P doubler is available with only the roller bearing stud hole drilled and may be used to replace either the -001 or -005 doubler assemblies, but requires match drilling of the 26-21352-007P doubler to the airframe or removed doubler for the AN3-5A attach bolt hole locations (4 places). MS21073L3 nutplates may be installed or MS21042L3 nuts and AN960-10L washers may be used. (6) Proceed to Step 2.D. C. Control Column Pivot Alternate Design This step offers an alternate method of compliance to Steps 2.A. and 2.B. (1) Comply with the latest FAA approved revision of Service Bulletin 226-27-061. (2) Proceed to Step 2.D.
NOTE : Compliance with Step 2.C. removes the pivot bearing 10,000 hour replacement requirement outlined in Table 1 for Steps 2.A. and 2.B. D. Elevator Control Rod(1) Remove the elevator control rod attached to the elevator walking beam and control column as shown in Figure 2 and as described in the SA226 MM, Chapter 27-30-02 or Chapter 27-30-10.
CAUTION : PAY PARTICULAR ATTENTION TO SA226 MAINTENANCE MANUAL CHAPTER 27-30-01 WITH REGARDS TO BLOCKING WHEN DISCONNECTING/WORKING WITH ELEVATOR CONTROL CABLES DUE TO SPRING TENSION ON CABLES.Issued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 8 of 14 (2) Inspect rod end bearing retainer/dust covers for evidence of creasing or other damage as shown in Figure 2. If any creasing or other damage is found , remove and replace rod end(s). (3) Check elevator control rod ends for excessive wear. Grasp the control rod fi rmly in one hand and with the other hand attempt to move the inner ring radially back and forth in the bearing face. Any perceptible radial play between the inner ring and the race indicates excessive wear and the bearing shall be replaced. (4) If the elevator control rod is disassembled to replace one or both of the rod end bearings, the control rod must be reassembled with: (a) length adjusted to meet elevator control system rigging and travel requirements of SA226 MM, Chapter 27-00-00, (b) Both witness holes in control rod covered by installed bearings, (c) each bearing installed 90° (+/- 3°) to each other and, (d) control rod jam nuts with 40 in-lbs (+/- 5 in-lbs) torque.
CAUTION : DO NOT ATTEMPT TO TIGHTEN THE CONTROL ROD ASSEMBLY JAM NUTS WHILE CONTROL ROD IS INSTALLED SINCE THIS WILL CAUSE CREASING OF ROD END BEARING RETAINER/DUST COVER.
NOTE: To prevent creasing, the rod end retainer/dust covers, the control rod length should be adjusted with the jam nuts tightened fi nger tight and the elevator control system travel checked in accordance with SA226 MM, Chapter 27-00-00. Remove the control rod assembly and tighten jam nuts by holding the rod ends with a wrench on the fl at of the bearing housing while torquing the jam nut to 40 in-lbs (+/- 5 in-lbs). Ensure that control rod criteria of Step 2.D.(4) is met. (5) Reinstall elevator control rod. Use hardware and hardware arrangement as shown in FIGURE 2. Replace bolt (P/N NAS6604D31 or previously replaced NAS6604D34 (with more than 10,000 hours TIS) with a new bolt (P/N NAS6604D34) and install a new washer (P/N AN970-4).
NOTE: Use AN960-416 and/or AN960-416L washer(s), shown on either side of rod end bearings, as required for clamp up. Ensure that the AN310-4 nut does not ride on the shank of the NAS6604D34 bolt. (6) Adjust elevator and aileron cable tensions and perform elevator and aileron control system travel/adjustment as described in SA226 MM, Chapter 27-00-00, Chapter 27-10-00, and Chapter 27-30-00. (7) Replace all cockpit furnishings and fl oorboards removed to accomplish this inspection/replacement.Issued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 9 of 14 

# SERVICE BULLETIN SA226 SERIES

E. Complete aircraft records according to 14 CFR 43.9. F. Complete and return service bulletin Compliance Form to M7 Aerospace Technical Support Department. Email: MetroTech@M7Aerospace.com. Fax: 210-820-8626.
3. MATERIAL LISTING Replacement or alternate parts approved via M7 Aerospace drawings are acceptable substitutes for use in accomplishing this bulletin. The following materials are required to accomplish the instructions outlined in this service bulletin. SB226-27-060 Kit A, B or C can be ordered and will contain all materials listed except common stock items which may be obtained locally or ordered separately. KIT A - INSPECTION ONLY - ALL AIRPLANES NEW P/N QTY. KEYWORD OLD P/N DISPOSITION AN310-4 * 2 Nut MS21083N4, Scrap MS20365-428 AN970-4 * 1 Washer N/A N/A AN960-416 * A/R Washer N/A N/A (NAS1149C0463R is acceptable alternate washer) AN960-416L * A/R Washer N/A N/A (NAS1149C0432R is acceptable alternate washer) MS24665-132 * 2 Cotter Pin N/A N/A NAS6604D34 * 1 Bolt NAS6604D31 Scrap NAS6604D12 * 1 Bolt AN4-( ) Scrap Or Alternate AN4-12 226-27-060-PL-A 1 Packing List N/A N/A

KIT B - INSPECTION AND REPLACEMENT AIRPLANE S/N: T, T(A), T(B)201-371, TC201-372 AND AT001-074 ONLY NEW P/N QTY. KEYWORD OLD P/N DISPOSITION 226-27-060 Kit A 1 Inspection Kit N/A N/A 26-21352-007P 2 Doubler 26-21352-001 Scrap or -005 AN3-5A * 8 Bolt N/A N/A AN960-10L * 8-16 Washer N/A N/A (NAS1149F0332P is acceptable alternate washer) AN960C416 * A/R Washer N/A N/A (NAS1149C0463R is acceptable alternate washer) Continued Next PageIssued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 10 of 14 KIT B - INSPECTION AND REPLACEMENT (continued) AIRPLANE S/N: T, T(A), T(B)201-371, TC201-372 AND AT001-074 ONLY NEW P/N QTY. KEYWORD OLD P/N DISPOSITION AN960C416L * A/R Washer N/A N/A (NAS1149C0432R is acceptable alternate washer) CF-5/8-S 2 Roller Bearing CF-5/8-S Scrap (CRS-10-1) § 2 Roller Bearing CF-5/8-S Scrap (MS21440-102) § 2 Roller Bearing CF-5/8-S Scrap MS21042L4 * 2 Nut MS21044N4 Scrap MS21073L3 * 8 Nutplate MS21042L3 Scrap MS20426AD3 * 16 Rivet N/A N/A REP4M6 2 Rod End (RH thread) REP4M6 Scrap (MS21151-8) 226-27-060-PL-B 1 Packing List N/A N/A

KIT C - INSPECTION AND REPLACEMENT AIRPLANE S/N: T(B)372-417, TC373-418, 419 ONLY NEW P/N QTY. KEYWORD OLD P/N DISPOSITION 226-27-060 Kit A 1 Inspection Kit N/A N/A 26-21352-007P 2 Doubler 26-21352-001 Scrap or -005 AN3-5A * 8 Bolt N/A N/A AN960-10L * 8-16 Washer N/A N/A (NAS1149F0332P is acceptable alternate washer) AN960C416 * A/R Washer N/A N/A (NAS1149C0463R is acceptable alternate washer) AN960C416L * A/R Washer N/A N/A (NAS1149C0432R is acceptable alternate washer) CF-5/8-S 2 Roller Bearing CF-5/8-S Scrap (CRS-10-1) § 2 Roller Bearing CF-5/8-S Scrap (MS21440-102) § 2 Roller Bearing CF-5/8-S Scrap MS21042L4 * 2 Nut MS21044N4 Scrap MS21073L3 * 8 Nutplate MS21042L3 Scrap MS20426AD3 * 16 Rivet N/A N/A REP4M6 1 Rod End (RH thread) REP4M6 Scrap (MS21151-8) Continued Next PageIssued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 11 of 14 

# SERVICE BULLETIN SA226 SERIES

KIT C - INSPECTION AND REPLACEMENT AIRPLANE S/N: T(B)372-417, TC373-418, 419 ONLY NEW P/N QTY. KEYWORD OLD P/N DISPOSITION
REP4ML6 1 Rod End (LH thread) REP4ML6 Scrap (MS21151-9) 226-27-060-PL-C 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 acceptable substitute for Roller Bearing P/N CF-5/8-S.Issued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 12 of 14 FIGURE 1 CONTROL COLUMN ROLLER BEARING INSPECTION / REPLACEMENT INSTRUCTIONS 6B270601 COPILOTS CONTROL COLUMN INSPECTION INSTRUCTIONS: APPLY 60.0 INCH/POUNDS (+ 5.0 / - 0.0 IN-LBS) OF TORQUE AT MS21044N4 NUT. IF NUT/ROLLER BEARING MOVES PRIOR TO REACHING 60.0 INCH/POUNDS OF TORQUE, REMOVE AND REPLACE CF-5/8-S ROLLER BEARING, 26-21352-001/-005 DOUBLER ASSEMBLY AND REPLACE MS21044N4 NUT WITH MS21042L4 NUT.

26-21352-001 OR 26-21352-005 DOUBLER ASSEMBLY

(1 EACH, 2 PLACES) FOR 26-21352-007P DOUBLER MATCH DRILL FOR AN3-5A BOLT HOLES, DRILL 0.097 TO 0.102 INCH DIAMETER, 2 PLACES EACH MS21073L3 NUTPLATE, COUNTERSINK FAR SIDE, 100o x 0.175 TO 0.183 INCH DIAMETER, INSTALL USING MS20426AD3 RIVETS. 

# A

DETAIL A (PILOTS SIDE TYPICAL) FWD

CF-5/8-S ROLLER BEARING (1 EACH, 2 PLACES) REINSTALL AN960C416 AND/OR AN960C416L WASHERS USED AS SHIMS

AN3-5A BOLT AN960-10L WASHER MS21042L3 NUT (FOR 26-21352-001 DOUBLER ASSEMBLY) (4 EACH, 2 PLACES) OR AN3-5A BOLT AN960-10L WASHER (FOR 26-21352-005 DOUBLER ASSEMBLY) (4 EACH, 2 PLACES) MS21044N4 NUT (1 EACH, 2 PLACES) AN960-416 AND/OR AN960-416L WASHERS AS REQUIRED TO PROVIDE CLAMP UP OF BEARING TO DOUBLER. TORQUE NUT TO 70.0 INCH POUNDS (+ 5.0 / - 0.0 IN-LBS). ENLARGE CUTOUT BY 1.0 INCH, EACH END. TRIM ANGLE FLANGE TO MATCH CUTOUT. DEBURR AND SURFACE FINISH BARE METAL USING EPOXY POLYAMIDE PRIMER.

1.0 INCH 1.0 INCH

IF FOUND LOOSE REPLACE WITH MS21042L4 NUTIssued: December 11, 1996 Revised: December 5, 2014 226-27-060 R2 Page 13 of 14 

# SERVICE BULLETIN SA226 SERIES

6B270602 F.S. 116 F.S. 107 F.S. 98 CONTROL COLUMN

CONTROL COLUMN 

# A

A

ELEVATOR CONTROL WALKING BEAM ELEVATOR CONTROL WALKING BEAM C L

SECTION A-A (LOOKING INBOARD) NAS6604D34 BOLT AN960-416 WASHER

AN960-416 WASHER

AN310-4 NUT MS24665-132 PIN AN970-4 WASHER MS21151-8 ROD END (RH THREAD) AND (EITHER END) MS21151-9 ROD END (LH THREAD)

MS21151-8 ROD END (RH THREAD) AIRPLANE S/N: T201-371, TC201-372 AND AT001-074 ONLY FWD F W D AN960-416LWASHER AN960-416 WASHER AN960-416L WASHER

AN310-4 NUT

NORMAL ROD END CREASED ROD END REMOVE & REPLACE RETAINER / DUST COVER

**BEARING** CREASED (FRONT SIDE) CREASED (BACK SIDE) NAS6604D12 BOLT (BOLT HEAD INBOARD)

HARDWARE ARRANGEMENT SHOWN ABOVE IS CRITICAL TO OBTAIN CORRECT CLAMP UP MS24665-132 PIN

HARDWARE ARRANGEMENT SHOWN BELOW IS CRITICAL TO OBTAIN CORRECT CLAMP UP ELEVATOR CONTROL ROD

AN960-416 AND/OR AN960-416L WASHER(S) (AS REQUIRED FOR CLAMP UP)

FIGURE 2 ELEVATOR CONTROL ROD, ROD END BEARING

INSPECTION / REPLACEMENT INSTRUCTIONSIssued: December 11, 1996 Revised: December 5, 2014 

# SERVICE BULLETIN SA226 SERIES

226-27-060 R2 Page 14 of 14 INTENTIONALLY LEFT BLANK

### SA226 SERIES SERVICE BULLETIN COMPLIANCE FORM

226-27-060 R2

TO: OPERATOR OR SERVICE FACILITY ACCOMPLISHING BULLETIN Please complete this compliance form, and mail according to the instructions on the reverse side.
Thank you for returning this form.

* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *

Aircraft Model Aircraft Serial Number

Bulletin Issue Date Revision Date
Aircraft Registration Number
Operator/Owner

Time on Aircraft
Date Accomplished

CommentsFAIRCHILD AIRCRAFT P. O. BOX 790490 SAN ANTONIO, TEXAS 78279–0490

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