P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421 TO: HOLDERS OF SA227 SERIES COMMUTER CATEGORY SERVICE INFORMATION MANUALS Attached is SA227 Series Commuter Category Service Bulletin CC7-27-032, 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 CC7-27-032 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

Issued: May 19, 1994 CHAPTER 27 INDEX Page 1 of 4 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY 

### SA227 SERIES COMMUTER CATEGORY

27-001 00-00-00 NOT ISSUED 27-002 02-18-95 Improved Flap Position SA227-CC, S/N CC784, and SAS Compensator 790-853 Potentiometers (Pots) SA227-DC, S/N DC784, 790-853
27-003 05-19-94 Rudder Bellcrank Hinge SA227-CC, S/N CC784-845 Assembly Rework SA227-DC, S/N DC784-845 27-004 12-15-94 Increased Service Life SA227-CC, S/N CC784, (R) 01-05-96 0f 27-42030 Rudder 790-880 Bellcrank SA227-DC, S/N DC784, 790-880 27-005 05-22-95 Rudder Torque Tube SA227-CC, S/N CC784, Drain Hole 790-885 SA227-DC, S/N DC784, 790-885 27-006 08-09-95 Rudder Control Lock Weldment SA227-CC, S/N CC784, and Bellcrank Inspection - 790-881 Optional Improved Strength SA227-DC, S/N DC784, Rudder Torque Tube, Control 790-881 Lock Weldment and Aluminum Bellcrank.
27-007 NOT ISSUED 27-008 09-08-95 Rudder Trim Tab Actuator SA227-CC, S/N CC784, Decal 790-874 SA227-DC, S/N DC784, 790-874
27-009 05-15-96 Rework of UP/DOWN Elevator SA227-CC, S/N CC784-880 Quadrant Stops and LH/RH and 883 Rudder Bellcrank Stops SA227-DC, S/N DC784-880 and 883 27-010 12-11-96 Control Column Roller Bearing SA227-CC, S/N CC784, (R) 02-24-97 and Elevator Rod End Bearing 790-884 (R) 12-05-14 Inspection/Replacement SA227-DC, S/N DC784, 790-884

Revised: December 5, 2014CHAPTER 27 INDEX Page 2 of 4 Issued: May 19, 1994 CHAPTER 27 – FLIGHT CONTROLS NUMBER DATE TITLE AIRCRAFT EFFECTIVITY 

### SA227 SERIES COMMUTER CATEGORY

27-011 06-16-97 Control Column Pivot SA227-CC, S/N CC784, Improvement 790-891, 894 SA227-DC, S/N DC784, 790-891, 894 27-012 07-18-97 Flap Position Indication / SA227-CC, S/N CC784, Control Circuit Modi fi cation 790-887, 889-903 SA227-DC, S/N DC784, 790-887, 889-903 27-013 07-27-99 Installation of P/N DL5040M8, SA227-CC, S/N CC784, (R) 12-27-99 Simmonds Precision Pitch Trim 790-892, 894-896 (*1)(*2)(*3) (R) 11-18-02 Actuator (PTA) SA227-DC, S/N DC784, (R) 01-30-03 790-892, 894-896 (*1)(*2)(*3) See Service Bulletin for (*1) (*2) (*3) 27-014 11-18-98 Installation of Simmonds All SA227 Series Commuter Precision P/N DL5040M5 Category Airplanes and/or DL5040M6 Pitch Trim with Barber Colman, P/N Actuator (PTA) 27-19008-001/-002 Pitch Trim Actuator Installed 27-015 03-08-99 Installation of All SA227 Commuter (R) 03-23-99 P/N 27-19008-006/-007 Category Airplanes Barber-Colman Pitch Trim with P/N 27-19008-001/-002/ Actuator (PTA) -004/-005 Barber-Colman PTA installed. 27-016 09-29-03 Life Limit for Rudder Gust All SA227 Series Commuter Lock Assembly, Part Number Category Airplanes 27-70066-001, of 5000 Hours 27-017 04-02-04 Inspection of 26-72003 Rudder All SA227 Series Commuter Pedals for cracks Category Airplanes 27-018 09-24-04 Modi fi cation of Vertical SA227-CC, S/N784, 790- (R)03-06-09 Stabilizer Aft Spar to 799, 801-804 (R)03-19-10 Facilitate Installation of SA227-DC, S/N784, 790-799, New P/N 27-19332-003 801-804 Rudder Trim Tab Actuator
27-019 00-00-00 NOT ISSUED
27-020 00-00-00 NOT ISSUED

Revised: March 19, 2010CHAPTER 27–FLIGHT CONTROLS

Issued: May 19, 1994 CHAPTER 27 INDEX Page 3 of 4 NUMBER DATE TITLE AIRCRAFT EFFECTIVITY 

### SA227 SERIES COMMUTER CATEGORY

27-021 00-00-00 NOT ISSUED
27-022 00-00-00 NOT ISSUED
27-023 09-19-08 Gravel Guard Installation All SA227 Commuter Category Airplanes 27-024 06-10-11 Inspection and Repair / All SA227 Commuter (R) 09-06-11 Replacement of Pitch Trim Category Airplanes (R) 10-14-11 Actuator Fuselage Fittings
27-025 05-17-11 SAS Power Advance Indicator All SA227 Commuter Lights Modi fi cation Category Airplanes 27-026 06-06-13 Inspection and Lubrication of All SA227 Commuter (R) 09-30-13 Aileron Control Cable Chain in Category Airplanes (R) 10-23-13 the Pilot's and Copilot's Control Columns 27-027 09-04-14 Inspection/Replacement of the All SA227 Commuter Aileron Control System Rod Category Airplanes End Bearings 27-028 09-04-14 Inspection of the Aileron Link All SA227 Commuter Rod, Bellcrank, and Aileron Category Airplanes Hinge Bracket for Damage 27-029 08-18-14 Inspection/Repair or Wiring All SA227 Commuter Harnesses in Vertical Stabilizer Category Airplanes 27-030 10-08-15 Inspection of Cockpit Control All SA227 Commuter Column Horizontal Tube for Category Airplanes Cracks 27-031 04-23-15 Inspection of Rudder Bellcrank All SA227 Commuter (R) 09-21-15 Category Airplanes (R) 10-12-15 27-032 11-05-15 Inspection of the Elevator All SA227 Commuter (R) 02-23-16 Control System Rod End Category Airplanes Bearings

Revised: February 23, 2016CHAPTER 27 INDEX Page 4 of 4 Issued: May 19, 1994 CHAPTER 27 – FLIGHT CONTROLS NUMBER DATE TITLE AIRCRAFT EFFECTIVITY 

### SA227 SERIES COMMUTER CATEGORY

INTENTIONALLY LEFT BLANK

Revised: February 23, 2016CC7-27-032 R1 Page 1 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 Commuter Category 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.CC7-27-032 R1 Page 2 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 Commuter Category 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 Commuter Category Maintenance Manual, 27-00-00; SA227 Commuter Category 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 Commuter Category Illustrated Parts Catalog (IPC) 27-30-10; SA227 Commuter Category Maintenance Manual (MM) 27-30-00; SA227 Commuter Category Phase and Letter Check Inspection Manuals.CC7-27-032 R1 Page 3 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 eachCC7-27-032 R1 Page 4 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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.CC7-27-032 R1 Page 5 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 placards and restore power and hydraulics. 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.CC7-27-032 R1 Page 6 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 ǂCustomer 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. ¤ See AMM 12-20-10 for alternate grease to MIL-PRF-81322. TABLE 1 MATERIAL LISTING FOR CONTROL LINKS / ATTACHMENT HARDWARE (SEE FIGURES 4 AND 5 FOR PROPER STACK-UP)CC7-27-032 R1 Page 7 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 CB2703201R1

FIGURE 1 LOCATOR - ELEVATOR CONTROL LINKSCC7-27-032 R1 Page 8 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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

### 808

CB2703202CC7-27-032 R1 Page 9 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

Issued: November 5, 2015 Revised: February 23, 2016 FIGURE 3 IN-PLANE ROTATION OF ROD END BEARING WITHIN RACE CB2703203CC7-27-032 R1 Page 10 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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 **

CB2703204R1 ** (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.CC7-27-032 R1 Page 11 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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

CB2703205 * (SEE 3. MATERIAL LISTING FOR ALTERNATE P/N)CC7-27-032 R1 Page 12 of 12 

# SERVICE BULLETIN SA227 SERIES COMMUTER CATEGORY

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

### SERVICE BULLETIN COMPLIANCE FORM

CC7-27-032 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.

* * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * * *
Aircraft Model Aircraft Serial Number

Bulletin Issue Date Revision Date Aircraft Registration Number Operator/Owner

Time on Aircraft Date Accomplished
CommentsM7 AEROSPACE LLC P. O. BOX 790490 SAN ANTONIO, TEXAS 78279–0490

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