P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421 TO: HOLDERS OF SA227 SERIES SERVICE INFORMATION MANUALS
Attached is SA227 Series Service Bulletin 227-27-060, Inspection of the Elevator Control System Rod End Bearings, Issued: November 5, 2015; Revised: February 23, 2016. This revision removes the NAS43HT4-4 spacers from the elevator control links to quadrant hardware stack-up shown in Figures 1 and 4, and adds to the *Note in Figure 4 to allow use of one NAS43HT4-4 spacer in place of two AN960-416L washers if necessary. Please replace existing Service Bulletin 227-27-060 IR with the attached Service Bulletin and replace revised Chapter 27 Index pages.P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421CHAPTER 27 – FLIGHT CONTROLS SA227 SERIES INDEX

CHAPTER 27 INDEX Page 1 of 6 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY 27-001 07-08-81 Elevator Return SA227-AC, S/N AC420 and Spring and Attaching up, Bolts Inspection SA227-AT, S/N AT423 and up. 27-002 09-14-81 Relocation of SA227-AC, S/N AC420 (R) 10-25-85 Elevator Down through AC473, Spring SA227-AT, S/N AT423 through AT469. A27-003 11-13-81 Replacement of Pins SA227-AC, S/N AC420 in Aileron Control through 432, and 455 System through AC458, 473, and 475, SA227-AT, S/N AT423, 427, 439 and 446. A27-004 12-03-82 Removal of Second SA227-TT, S/N TT421-541, (R) 01-06-83 Clutch from CONRAC SA227-AC, S/N AC420-551, SAS Servo SA227-AT, S/N AT423-549.
27-005 09-19-84 Dual Push-Pull Rod SA227-AT, S/N AT423-633, (R) 08-12-85 Assembly - Aileron SA227-AC, S/N AC406, 415, (R) 03-27-92 Trim Tab Control AC416, 420-633. 27-006 02-15-85 Conrac SAS System SA227-TT, S/N TT421-541, (R) 09-16-85 Inspection and SA227-AT, S/N AT423-585, (R) 11-04-85 Recalibration SA227-AC, S/N AC406, 415, (R) 04-15-88 CATEGORY III AC416, 420-603. (R) 02-10-93 (R) 05-06-96 (R) 06-12-13 27-007 12-13-83 Rudder Torque Tube SA227-TT, S/N TT421-555, SA227-AC, S/N AC415, 416, and AC420-578, SA227-AT, S/N AT423-577. 27-008 10-19-84 SAS2 Power Compensation SA227-TT, S/N TT421-555. (R) 02-25-85 Relay Wiring 27-009 03-23-84 Replacement of Turn SA227-TT, S/N TT421-579 (R) 07-23-93 and Slip Indicator SA227-AT, S/N AT423-579 SA227-AC, S/N AC406, 415, 416, 420-581

27-010 05-15-84 Rudder Pedal Rework (For Company Use ONLY) (R) 05-23-84 Issued: July 8, 1981 Revised: June 12, 2013CHAPTER 27 INDEX Page 2 of 6 CHAPTER 27 – FLIGHT CONTROLS SA227 SERIES INDEX

NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

Issued: July 8, 1981 Revised: March 24, 1987 27-011 04-09-85 Rudder Gust Lock SA227-TT, S/N TT421-555, Rework SA227-AT, S/N AT423-570, SA227-AC, S/N AC406, 415, 416, and AC420-575. 27-012 03-20-85 Rework or Replacement SA227-TT, S/N TT421-555, of 27-71016 Bellcrank SA227-AC, S/N AC406, Assembly 415, 416, and 420-584, SA227-AT, S/N AT423-577.
27-013 07-01-85 RESCINDED
27-014 07-31-85 Rudder Pedal Bellcrank SA227-TT, S/N TT421-555, Hardware Inspection SA227-AC, S/N AC406, 415, 416, 420-606, SA227-AT, S/N AT423-602.
27-015 10-24-85 Aileron Control Cable SA227-TT, S/N TT421-555, Fairlead Installation SA227-AT, S/N AT423-618, AT625-633, SA227-AC, S/N AC406, 415, 416, and AT420-633.
27-016 10-21-85 Alternate Elevator SA227-TT, S/N TT421-555, (R) 01-03-86 Gust Lock SA227-AC, S/N AC423-631B, (R) 02-18-86 SA227-AT, S/N AT406, 415, 416, and AT420-632.
27-017 02-12-86 Install Grease SA227-TT, S/N TT421-555, Fitting in Aileron SA227-AC, S/N AC406, 415, Trim Tab Actuator 416, and 420-633, SA227-AT, S/N AT423-631.
27-018 06-17-86 Pitch Trim Actuator SA227-TT, S/N TT421-541, (R) 10-31-86 Replacement except 447, 465, 471, (R) 03-24-87 Category III 483, 521. SA227-AT, S/N AT423-631. SA227-AC, S/N AC406, 415, 416, 420-661.CHAPTER 27 – FLIGHT CONTROLS SA227 SERIES INDEX

CHAPTER 27 INDEX Page 3 of 6 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

Issued: July 8, 1981 Revised: January 10, 1990 27-019 03-05-87 Improved SAS Servo SA227-TT, S/N TT421-541, Idle Control Assembly SA227-AT, S/N AT423-631B, Category III SA227-AC, S/N AC406,415, 416, and 420-662, except 650, 653, 654, 655, and 658. 27-020 06-25-87 Improved SAS Servo SA227-AT, S/N AT423-695 (R) 08-30-89 Assembly SA227-AC, S/N AC406,415, Category III 416, 420-723
27-021 06-08-87 Aileron Trim Cable SA227-TT, S/N TT421-541, Drum Guard Pin SA227-AT, S/N AT423-631, Category III SA227-AC, S/N AC406, 415, 416, 420-633.
27-022 06-18-87 Rudder Bellcrank SA227-TT, S/N TT421-541, Improvements SA227-AT, S/N AT423-631, Category III SA227-AC, S/N AC420-677. 27-023 12-11-87 Flap Rib Reinforcement SA227-TT, S/N TT421-541, Category III SA227-AT, S/N AT423-695, SA227-AC, S/N AC406, 415, 416, 420-723.
27-024 02-19-88 Aileron Bellcrank SA227-TT, S/N TT421-541, Housing Modi fi cation SA227-AT, S/N AT423-695, Category III SA227-AC, S/N AC406, 415, 416, 420-711. 27-025 01-27-88 Rudder Hinge Bolts SA227-TT, S/N TT421-541, Category III SA227-AT, S/N AT423-631, SA227-AC, S/N AC406, 415, 416, 420-643.
27-026 07-26-89 Elevator Control SA227-AT, S/N AT423-612, Cable Hardware SA227-AC, S/N AC406, 415, Category III 416, 420-556, 558-612.
27-027 01-10-90 CANCELLEDCHAPTER 27 INDEX Page 4 of 6 CHAPTER 27 – FLIGHT CONTROLS SA227 SERIES INDEX

NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

Issued: July 8, 1981 Revised: April 22, 2008 27-028 01-22-90 Elevator Torque Tube SA227-TT, S/N TT421-541, (R) 06-26-97 SA227-AT, S/N AT423-695, SA227-AC, S/N AC406, 415, 416, 420-772, SA227-BC, S/N 420-772
27-029 06-06-91 Rudder Cable Attach SA227-TT, S/N TT421-444, (R) 04-22-08 Hardware SA227-AT, S/N AT423-440, Category III SA227-AC, S/N AC406, 415, 416, 420-448.

27-030 Not Issued 27-031 02-18-95 Improved Flap Position All SA227 Series Airplanes and SAS Compensator Potentiometers (Pots) 27-032 08-31-92 Yaw Damper Removal SA227-AT, S/N AT420-504. Category IV SA227-AC, S/N AC406, 415, 416, 420-504. 27-033 05-19-94 Rudder Bellcrank Hinge SA227-TT, S/N TT421-541, Assembly Rework SA227-AT, S/N AT423-695, SA227-AC, S/N AC406, 415, 416, 420-789, SA227-BC, S/N 420-789 27-034 12-15-94 Increased Service Life All SA227 Series Airplanes (R) 01-05-96 of 27-42030 Rudder Bellcrank 27-035 05-22-95 Rudder Torque Tube All SA227 Series Airplanes Drain Hole 27-036 08-09-95 Rudder Control Lock Weldment SA227-TT, S/N TT421-541 and Bellcrank Inspection - SA227-AT, S/N AT423-695 Optional Improved Strength SA227-AC, S/N AC406, 415, Rudder Torque Tube, Control 416, 420-783 Lock Weldment and Aluminum SA227-BC, S/N BC762, 764, Bellcrank 766, 771-774, 777, 779, 781 and 783
27-037 Not Issued 27-038 09-08-95 Rudder Trim Tab Actuator All SA227 Series Airplanes DecalCHAPTER 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, 2014CHAPTER 27 INDEX Page 6 of 6 CHAPTER 27 – FLIGHT CONTROLS SA227 SERIES INDEX

NUMBER DATE TITLE AIRCRAFT EFFECTIVITY

Issued: July 8, 1981 Revised: February 23, 2016 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 27-058 10-08-15 Inspection of Cockpit Control All SA227 Series Airplanes Column Horizontal Tube for Cracks 27-059 04-23-15 Inspection of Rudder Bellcrank All SA227 Series Airplanes (R) 09-21-15 (R) 10-12-15 27-060 11-05-15 Inspection of the Elevator All SA227 Series Airplanes (R) 02-23-16 Control System Rod End Bearings227-27-060 R1 Page 1 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 Flight Controls Inspection of the Elevator Control System Rod End Bearings 1. PLANNING INFORMATION A. Effectivity: All SA227 Series Airplanes. B. Reason: An operator reported a crew was performing fl ight control checks before take-off and noted something was wrong with the elevator control. Review of the elevator control system by maintenance personnel found the control link assembly located between the elevator torque tube and the elevator quadrant broken. This revision removes the NAS43HT4-4 spacers from the elevator control links to quadrant hardware stack-up shown in Figures 1 and 4, and adds to the *Note in Figure 4 to allow use of one NAS43HT4-4 spacer in place of two AN960-416L washers if necessary. C. Description: Inspect both control link assemblies between the elevator torque tubes and the elevator quadrant for frozen (stiff, hard to move) bearings, or broken/cracked links (rod ends). Replace rod ends if required and inspect mating quadrant for any signs of related damage. Otherwise, lubricate bearings, reinstall elevator control link assemblies, check system rigging/freeplay, and repeat inspection at next interval speci fi ed below. D. Compliance: Mandatory. 1) If fl ight crew reports abnormally high resistance when operating the elevators, perform Step 2.A. INSPECTION OF ELEVATOR CONTROL LINKS - INSTALLED prior to next fl ight. 2) For reasons other than 1.D.1), at the next zone related Phase or Letter Check inspection or next 600 fl ight hours (but no later than 6 calendar months), whichever occurs later, perform Step 2.B. INSPECTION OF ELEVATOR CONTROL LINKS - REMOVED. 3) Continue to repeat inspect elevator control link assemblies IAW Step 2.B. INSPECTION OF ELEVATOR CONTROL LINKS - REMOVED at both locations (1 per elevator). Repeat on an annual basis after compliance with applicable Step 1.D.1) or 1.D.2) threshold inspection. 4) Continue to repeat lubrication of rod end bearings (male and female) on both elevator control link assemblies IAW Step 2.E every 3 to 6 months, concurrent with Step 1.D.3) when possible. For aircraft located in climates conducive to corrosion, lubricate using the shorter interval. For aircraft with the previous lubricant application still present, it is permissible to use the longer interval. Adjust this 3 to 6 month interval as required to maintain lubricant on bearings at all times.227-27-060 R1 Page 2 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 5) The repeat inspection and lubrication tasks will be added to the Phase and Letter Check programs. E. Approval: FAA Approved for Engineering Design. F. Manpower: M7 Aerospace estimates 2 manhours to perform the inspect/torque check and a further 4 hours for rod end bearing replacement and rigging checks. This estimate is for direct labor only. G. Material - Cost and Availability: Contact M7 Aerospace Spares/Sales Department for Cost and Availability. See Table 1 for listing. H. Tooling-Price and Availability: Refer to the SA227 Maintenance Manual (MM) for required tooling for rigging of control system. I. Weight and Balance: None. The weight of the rod ends is comparable. 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: M-5813 M7 Aerospace White Paper; M7 Aerospace SDR Review Item; SA227 Maintenance Manual, 27-00-00; SA227 Illustrated Parts Catalog (IPC) 27-30-10, Figure 1; M7 Aerospace Drawing 27-43000 (latest FAA approved revision). NOTE: References are for manufacturers’ use only. K. Other Publications Affected: SA227 Illustrated Parts Catalog (IPC) 27-30-10; SA227 Maintenance Manual (MM) 27-30-00; SA227 Phase and Letter Check Inspection Manuals.227-27-060 R1 Page 3 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 2. ACCOMPLISHMENT INSTRUCTIONS A. Inspection of Elevator Control Links - Installed: Refer to Figure 1 for location of the elevator control link rod end bearings to be checked. The subject rod end bearings are directly attached to the elevator quadrant and to the elevator torque tube at the inboard end of each elevator. Check each control link assembly as follows: 1) Remove panel 808 (see Figure 2) on the RH side of the vertical stabilizer to gain access to the elevator quadrant. 2) Ensure both rod ends on both elevator control link assemblies are intact. 3) Physically rotate the control link assemblies about their longitudinal axis in situ by hand. Do not remove any hardware at this stage. 4) If the control link assemblies rotate freely under hand force: a) Hand lube the elevator control link rod end bearings with MIL-PRF-81322 grease with link installed. Work in the grease by rotating link. b) Reinstall panel 808 and return aircraft to service. c) Perform procedures in step 2.B at the next zone related Phase or Letter Check inspection or next 600 fl ight hours (but no later than 6 calendar months), whichever occurs later. 5) If the control link does not rotate freely under hand force, or if link feels very stiff (slight movement only), proceed with Step 2.B. B. Inspection of Elevator Control Links - Removed: 1) Disconnect electrical power from the aircraft and remove GPU. Disconnect main batteries. Tag out circuit breakers and switches to prevent injury to personnel or damage to the aircraft. 2) Placard the cockpit controls of the elevator and trim system "DO NOT OPERATE/ MOVE". 3) Unless access has already been attained (Step 2.A.1) above), remove panel 808 (see Figure 2) on the RH side of the vertical stabilizer to gain access to the elevator quadrant. 4) Locate the elevator control link assemblies on each side of the quadrant. Each control link assembly consists of a male rod end (HM-4M) attached to elevator quadrant and a female rod end (HF-4M) attached to elevator torque tube, secured with a nut (AN316-C4R). Both control link assemblies must be checked. 5) Remove both elevator control link assemblies from the vertical stabilizer. 6) Initially by applying fi nger pressure, determine if the spherical bearing in each227-27-060 R1 Page 4 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 control link rod end can be rotated in-plane within the outer race of the rod end bearing (see Figure 3 for in-plane rotation illustration). a) When performing the in-plane rotation check, inspect rod end bearings (male and female) for corrosion and general condition. b) Only during the initial compliance with Step 2.B. Inspection of Elevator Control Links - Removed, perform a magnetic particle inspection or liquid penetrant inspection to check for cracks on male rod end exposed threads, taking care to avoid any penetrant fl uid entering the bearing race area. Repetitive magnetic particle or liquid penetrant inspections of the male rod ends are not required during the repeat inspections called for in Step 1.D.3). If for any reason the male rod end threads at the nut appear to be damaged, the nut must be rotated to expose the threads and threads under the nut inspected. c) The bearing should move smoothly and freely without any binding or sticking. If not, perform Step 2.C. Torque Check Procedure to determine if the bearing must be replaced or may be reinstalled. d) Replace any rod end that fails the torque check or is found to have corrosion or other damage. Replace affected rod end(s) IAW Step 2.D. (see Step 3 Material Listing for parts). e) If the rod end bearings are not found to have corrosion or other damage, rotate freely and smoothly without any sloppiness, the control link assemblies may be reinstalled. Proceed to Step 2.E. C. Torque Check Procedure: 1) This method simply inserts a standard 1/4" diameter bolt through the rod end to be checked. The bolt must be of suf fi cient grip length to allow installation of the NAS1149* washer (of 0.032 min thickness) under the head, and nut, MS21042L4, with one or two threads showing past the end of the nut. 2) While holding the bolt head, lightly torque the nut to approximately 30-50 in-lbs. This provides adequate clamping support to measure the breakout friction of the rod end bearing. 3) Obtain a torque wrench with a reading tolerance of +/- 0.5 in-lbs or better. Ensure the wrench is in calibration and is capable of measuring 4 to 7 in-lbs torque.4) The torque wrench is then reset and applied to the bolt head only, rotating inplane to measure the breakout torque of the bearing. A torque greater than 5 in-lbs indicates the rod end bearing needs replacement. Values less than 5 in-lbs permit the rod end bearing to remain in service. a) Torque greater than 5 in-lbs - replace the affected rod end IAW Step 2.D. b) Torque less than or equal to 5 in-lbs - return to relevant Step 2.B. to complete inspection and in-plane rotation check of remaining rod end bearings.227-27-060 R1 Page 5 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 D. Link Rod End Replacement: 1) Whether the existing bearings are "frozen" or do not meet the torque requirement, or by choice of the operator, the rod end should be removed and replaced with a new rod end (see Step 3. Material Listing). 2) Prior to disassembly of a control link assembly, note orientation of rod ends and length of link assembly. Either using witness marks or some form of marking, note orientation with respect to the elevator quadrant and elevator torque tube as the new rod end must be installed in the same orientation and link assembly must have same length as removed. These features must be maintained to avoid any interference with other parts of the system. 3) Discard the old rod end and install the new rod end. Reassemble the system using the witness marks or other orientation marking as noted above. Torque the AN316-C4R jam nut which secures the male and female rod ends to each other (Ref AMM 20-10-00). E. Hand lube the elevator control link rod end bearings with MIL-PRF-81322 grease. Install elevator control links to elevator quadrant and elevator torque tubes (see Figures 4 and 5 for correct stack-up, and Step 3. Material Listing for part numbers). F. Visually check the installation for correct orientation, positioning, and location of parts. Correct any noted discrepancies (See Figures 4 and 5). G. Restore all systems disturbed by the steps above to perform this inspection/replacement. Check elevator rigging and free play IAW MM section 27-00-00. H. Remove warning placards from cockpit controls of the elevator and trim system. I. Perform several elevator operation cycles while looking for clearance between all parts and proper operation. Correct any noted discrepancies. J. Reinstall panel 808. K. Complete aircraft records in accordance with 14 CFR 43.9. L. Complete and return service bulletin Compliance Form to M7 Aerospace Technical Publications Department. Email: MetroTech@M7Aerospace.com.227-27-060 R1 Page 6 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 3. MATERIAL LISTING

Location / Item Part Number Alternate P/N Quantity At Elevator Quadrant: Control Link Rod End, Male HM-4M MM-4M-18 § 2 Bolt NAS464P4-38 ǂ NAS6204-38D ǂ 1 Washer AN960-416L ǂ 2 * Spacer NAS43HT4-4 ǂ 2 Nut AN310-4 ǂ 1 Cotter Pin (Use with HM-4M) MS24665-153 ǂ 1 On Elevator Control Link: Jam Nut AN316-C4R ǂ 2 At Elevator Torque Tubes: Control Link Rod End, Female HF-4M MW-4M-17 § 2 Bolt NAS464P4-14 ǂ NAS6204-14D ǂ 2 Washer AN960-416 ǂ 4 Washer AN960-416L ǂ A/R ** Spacer, (INBD) NAS43HT4-5 ǂ 2 Spacer, (OUTBD) NAS43HT4-10 ǂ 2 Nut AN310-4 ǂ 2 Cotter Pin MS24665-153 ǂ 2 On Rod End Bearings: Grease MIL-PRF-81322 ǂ ¤ A/R § M7 Aerospace Sales Support item: M7-Sales@M7Aero.com ǂ Customer Furnished Material. * Extra washer may be added under nut to ensure proper torque on nut and cotter pin installation are met. ** Optional, 1 or 2 washers may be installed as required for proper bearing clamp-up or nut/cotter pin installation. ¤ MIL-PRF-23827 may be used as an alternate to MIL-PRF-81322. TABLE 1 MATERIAL LISTING FOR CONTROL LINKS / ATTACHMENT HARDWARE (SEE FIGURES 4 AND 5 FOR PROPER STACK-UP)227-27-060 R1 Page 7 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 ELEVATOR CONTROL LINK ASSEMBLIES (EACH ASSEMBLY CONSISTS OF 1 MALE ROD END, 1 FEMALE ROD END AND 1 JAM NUT)

ELEVATOR QUADRANT

ELEVATOR TORQUE TUBE 7B2706001R1

FIGURE 1 LOCATOR - ELEVATOR CONTROL LINKS227-27-060 R1 Page 8 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 2 ELEVATOR QUADRANT ACCESS PANEL 808 808

7B2706002227-27-060 R1 Page 9 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 3 IN-PLANE ROTATION OF ROD END BEARING WITHIN RACE 7B2706003227-27-060 R1 Page 10 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 4 CONTROL LINK ATTACHMENT AT QUADRANT MS24665-153 COTTER PIN

AN310-4 NUT AN960-416L WASHER *

EXISTING BUSHING (NAS77)

AN960-416L WASHER *

NAS464P4-38 BOLT ** ELEVATOR QUADRANT HM-4M BEARING **

HM-4M BEARING **

7B2706004R1 ** (SEE 3. MATERIAL LISTING FOR ALTERNATE P/N) EXISTING BUSHING (NAS77)

* AN EXTRA WASHER MAY BE ADDED UNDER NUT AND/OR HEAD OF BOLT TO ENSURE PROPER TORQUE ON NUT AND COTTER PIN INSTALLATION ARE MET. IT IS PERMISSIBLE TO USE ONE NAS43HT4-4 SPACER IN PLACE OF TWO AN960-416L WASHERS.227-27-060 R1 Page 11 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 5 CONTROL LINK ATTACHMENT TO ELEVATOR TORQUE TUBE AN960-416L WASHER (OPTIONAL INSTALLATION OF 1 OR 2

WASHERS, (2PL) AS REQUIRED FOR PROPER BEARING CLAMP-UP AND NUT/COTTER PIN INSTALLATION)

AN960-416 WASHER

HF-4M ROD END * NAS43HT4-5 SPACER AN960-416 WASHER NAS464P4-14 BOLT *

AN310-4 NUT MS24665-153 COTTER PIN

NAS43HT4-10 SPACER

7B2706005

* (SEE 3. MATERIAL LISTING FOR ALTERNATE P/N)227-27-060 R1 Page 12 of 12 

# SERVICE BULLETIN SA227 SERIES

Issued: November 5, 2015 Revised: February 23, 2016 INTENTIONALLY LEFT BLANK

### SERVICE BULLETIN COMPLIANCE FORM

227-27-060 R1

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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