Issued: February 24, 1997

Revised: December 5, 2014

227-27-041 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 SA227 SERIES SERVICE INFORMATION MANUALS

This is Revision 2 to SA227 Series Service Bulletin 227-27-041, 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, SA227 Illustrated Parts 

Catalog (IPC) Chapters 27-30-30 and 27-30-40, and the SA227 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) 824–9421
CHAPTER 27 – FLIGHT CONTROLS

SA227 SERIES INDEX

CHAPTER 27 INDEX

Page 5 of 6

NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

27-039 05-15-96 Rework of UP/DOWN Elevator All SA227 Series Airplanes 

 Quadrant Stops and LH/RH 

 Rudder Bellcrank Stops

27-040 NOT ISSUED

27-041 12-11-96 Control Column Roller Bearing All SA227 Series Airplanes 

 (R) 02-24-97 and Elevator Rod End Bearing

 (R) 12-05-14 Inspection/Replacement

27-042 06-16-97 Control Column Pivot All SA227 Series Airplanes 

 Improvement

27-043 07-18-97 Flap position Indication / All SA227-AC, AT and BC 

 Control Circuit Modifi cation 

 Airplanes

27-044 11-18-98 Installation of Simmonds All SA227 Series Airplanes 

 (R) 12-03-98 Precision P/N DL5040M5 with Barber Colman, P/N 

 and/or DL5040M6 Pitch Trim 27-19008-001/-002 Pitch

 Actuator (PTA) Trim Actuator Installed

27-045 05-11-99 Installation of P/N DL5040M8, All SA227 Series Airplanes 

 (R) 12-27-99 Simmonds Precision Pitch Trim

 (R) 11-18-02 Actuator (PTA)

27-046 03-08-99 Installation of All SA227 Series Airplanes 

 P/N 27-19008-006/-007 with P/N 27-19008-001/-002/

 Barber-Colman Pitch Trim -004/-005 Barber-Colman PTA

 Actuator (PTA) installed.

27-047 12-05-00 Installation of Fairleads SA227-AT, S/N AT423-621,

 at F.S. 174.06 SA227-AC, S/N AC406, 415,

 416, 420-621

27-048 09-29-03 Life Limit for Rudder Gust All SA227 Series Airplanes 

 Lock Assembly, Part Number

 27-70066-001, of 5000 Hours

27-049 04-02-04 Inspection of 26-72003 All SA227 Series Airplanes 

 Rudder Pedals for cracks

27-050 09-24-04 Modifi cation of Vertical All SA227 Series Airplanes 

 (R)03-06-09 StabilizerAft Spar to

 (R)03-19-10 Facilitate Installation of

 P/N 27-19332 Rudder

 Trim Actuator

27-051 09-19-08 Gravel Guard Installation All SA227 Series Airplanes

Issued: July 8, 1981

Revised: December 5, 2014
CHAPTER 27 INDEX

Page 6 of 6

CHAPTER 27 – FLIGHT CONTROLS

SA227 SERIES INDEX

NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

Issued: July 8, 1981

Revised: September 04, 2014

27-052 04-28-09 Pilot's and Copilot's Control SA227 Series S/N 420 to 723

 Column Access Panels Mod

27-053 06-10-11 Inspection and Repair / All SA227 Series Airplanes

 (R) 09-06-11 Replacement of Pitch Trim 

 (R) 10-14-11 Actuator Fuselage Fittings

27-054 06-06-13 Inspection and Lubrication of All SA227 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

27-055 09-04-14 Inspection/Replacement of the All SA227 Series Airplanes 

 Aileron Control System Rod 

 End Bearings

27-056 09-04-14 Inspection of the Aileron All SA227 Series Airplanes 

 Link Rod, Bellcrank, and 

 Aileron Hinge Bracket for 

 Damage

27-057 08-18-14 Inspection/Repair or Wiring All SA227 Series Airplanes 

 Harnesses in Vertical Stabilizer 

 
Issued: December 11, 1996

Revised: December 5, 2014

227-27-041 R2

Page 1 of 12

SERVICE BULLETIN

SA227 SERIES

Flight Controls

Control Column Roller Bearing and Elevator Rod End Bearing Inspection / Bolt 

Replacement

1. PLANNING INFORMATION

A. Effectivity:

All SA227 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 confi 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, SA227 Illustrated Parts Catalog 

(IPC) Chapters 27-30-30 and 27-30-40, and the SA227 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 identifi 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 confi guration by application of 

torque to the pivot bearing and ensuring no movement occurs as defi ned in 

this service bulletin, or;

(b) Replace the control column pivot bearings and associated hardware with new 

or newly defi ned parts and ensure the security of control column pivot by application of torque to the pivot bearing and ensuring no movement occurs as 

defi ned in this service bulletin, or;

(c) Incorporate the revised control column pivot confi guration defi ned in Service 

Bulletin 227-27-042.
Issued: December 11, 1996

Revised: December 5, 2014

SERVICE BULLETIN

SA227 SERIES

227-27-041 R2

Page 2 of 12

(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 confi guration to 

ensure the specifi c hardware and hardware arrangement is as defi 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

227-27-041 R2

Page 3 of 12

SERVICE BULLETIN

SA227 SERIES

Condition Initial Action Repetitive Action

Control Column Pivot Bearing 

has been torque checked, or 

replaced per SB 227-27-041 (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 227-27-042 per Step 2.C. 

<3><4>, within 10,000 hours TIS <2> or 

within the 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 227-27-041 

(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 227-27-042 

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 confi guration has been revised per 

SB 227-27-042.

In aircraft records, indicate completion of 

Step 2.C. of this Service Bulletin. <3>

No repetitive action.

Elevator rod attachment 

hardware and its confi guration complies with SB 227-

27-041 (any revision), at the 

date of this SB.

(There has been no confi guration changes since original 

compliance with the SB)

In aircraft records, indicate current date as 

compliance with SB 227-27-041, 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 confi guration does NOT comply with 

SB 227-27-041 (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 REQUIREMENTS <1>
Issued: December 11, 1996

Revised: December 5, 2014

SERVICE BULLETIN

SA227 SERIES

227-27-041 R2

Page 4 of 12

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 227-27-042 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 confi guration must be revised per SB 227-27-042 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 benefi 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 227-27-042 per the 

 Supplemental Inspection Document (SID). Therefore, if SB 227-27-042 is not 

 complied with here, compliance with 227-27-042 will be required per the 

 Supplemental Inspection Document (SID). 

TABLE 1 NOTES <1>
Issued: December 11, 1996

Revised: December 5, 2014

227-27-041 R2

Page 5 of 12

SERVICE BULLETIN

SA227 SERIES

E. Approval:

This Service Bulletin is approved by the FAA Airplane Certifi cation Offi ce (ACO), ASW150.

F. Manpower:

M7 Aerospace estimates the following manhours to accomplish the different aspects 

of 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 classifi 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

SA227 SERIES

227-27-041 R2

Page 6 of 12

K. Other Publications Affected:

SA227 Series Illustrated Parts Catalog (IPC) 

SA227 Series Maintenance Manual (MM)

ST-UN-M001, SA227 Airframe Airworthiness Limitations 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 SA227 Maintenance Manual, Chapter 25.

(2) Layout and enlarge Pilot's and Copilot's cutout as shown in FIGURE 1. Deburr 

and surface fi nish 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. or 2.C., otherwise proceed to Step 2.D.

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 SA227 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

227-27-041 R2

Page 7 of 12

SERVICE BULLETIN

SA227 SERIES

CAUTION: PAY PARTICULAR ATTENTION TO SA227 MAINTENANCE MANUAL 

CHAPTER 27-30-10 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 227-27-042.

(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 SA227 MM, Chapter 

27-30-10.

CAUTION: PAY PARTICULAR ATTENTION TO SA227 MAINTENANCE MANUAL 

CHAPTER 27-30-10 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

SA227 SERIES

227-27-041 R2

Page 8 of 12

(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 SA227 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 SA227 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 SA227 MM, Chapter 27-00-00.

(7) Replace all cockpit furnishings and fl oorboards removed to accomplish this 

inspection/replacement.

E. Complete aircraft records according to 14 CFR 43.9.
Issued: December 11, 1996

Revised: December 5, 2014

227-27-041 R2

Page 9 of 12

SERVICE BULLETIN

SA227 SERIES

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. SB227-27-041 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 - INSPECTION ONLY

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

227-27-041-PL-A 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.

KIT B - INSPECTION AND REPLACEMENT

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

227-27-041 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)

Continued Next Page
Issued: December 11, 1996

Revised: December 5, 2014

SERVICE BULLETIN

SA227 SERIES

227-27-041 R2

Page 10 of 12

KIT B - INSPECTION AND REPLACEMENT (Continued)

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

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 2 Rod End (RH thread) REP4M6 Scrap

(MS21151-8)

REP4ML6 1 Rod End (LH Thread) REP4ML6 Scrap

(MS21151-9)

227-27-041-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 acceptable substitute for Roller Bearing P/N CF-5/8-S.
Issued: December 11, 1996

Revised: December 5, 2014

227-27-041 R2

Page 11 of 12

SERVICE BULLETIN

SA227 SERIES

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 NUT
Issued: December 11, 1996

Revised: December 5, 2014

SERVICE BULLETIN

SA227 SERIES

227-27-041 R2

Page 12 of 12

FIGURE 2

ELEVATOR CONTROL ROD, ROD END BEARING

INSPECTION / REPLACEMENT INSTRUCTIONS

6B270602

F.S. 116

F.S. 107

F.S. 98

CONTROL

COLUMN

CONTROL COLUMN

A

A

ELEVATOR CONTROL

WALKING BEAM

ELEVATOR CONTROL

WALKING BEAM

CL

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)

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) 
SA227 SERIES 

SERVICE BULLETIN COMPLIANCE FORM

227-27-041 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.

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Aircraft Model Aircraft Serial Number 

Bulletin Issue Date Revision Date 

Aircraft Registration Number 

Operator/Owner 

Time on Aircraft 

Date Accomplished 

Comments
 FAIRCHILD AIRCRAFT 

P. O. BOX 790490

 SAN ANTONIO, TEXAS 78279–0490

(Staple)

ATTN: Technical Support Department

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