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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 Modi fi 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 Modi fi 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 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 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 con fi 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 con fi 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 con fi 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 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 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), ASW-
150.
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.