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10823 NE Entrance Road • San Antonio, Texas 78216-6001 • (210) 824–9421 TO: HOLDERS OF SA226 SERIES SERVICE INFORMATION MANUALS Attached is SA226 Series Service Bulletin 226-27-081, Pitch Trim Actuator Upper Attach Fittings Inspection, Issued: April 13, 2016; Revised: June 27, 2016.
An operator reported stress corrosion cracks on pitch trim actuator upper attach fi ttings in the bolt holes and in the web radii of the fi ttings.
This Service Bulletin removes and performs an initial detailed visual inspection, liquid penetrant inspection (LPI) and high frequency eddy current (HFEC) inspection of the upper pitch trim actuator attach fi ttings for cracking in the bolt holes and the web/fl ange radius.
This revision defi nes compliance requirement in step 1.D. if previous revision of this service bulletin was complied with, clari fi es steps 2.A.6)b) and 2.B.1), changes "as" to "or" in second note under 2.A.6)d), adds alternative parts to 3. Material Listing and adds Figure 3 to show bushing location and orientation.
Please replace the Service Bulletin and Chapter 27 Index pages.
P.O. Box 790490 • San Antonio, Texas 78279–0490 • (210) 824–9421
CHAPTER 27 – FLIGHT CONTROLS CHAPTER 27 INDEX Page 7 of 8
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX 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.
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 NOT ISSUED 27-069 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 Issued: February 8, 1971 Revised: April 13, 2016
CHAPTER 27 – FLIGHT CONTROLS
NUMBER DATE TITLE AIRCRAFT EFFECTIVITY SA226 SERIES INDEX CHAPTER 27 INDEX Page 8 of 8 Issued: February 8, 1971 Revised: June 27, 2016 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 Bearings 27-076 09-04-14 Inspection of the Aileron Link All SA226 Series Airplanes Rod, Bellcrank, and Aileron Hinge Bracket for Damage 27-077 08-18-14 Inspection/Repair of Wiring All SA226 Series Airplanes Harnesses in the Vertical Stabilizer 27-078 10-08-15 Inspection of Cockpit Control All SA226 Series Airplanes Column Horizontal Tube for Cracks 27-079 04-23-15 Inspection of Rudder Bellcrank All SA226 Series Airplanes (R) 09-21-15 (R) 10-12-15 27-080 11-05-15 Inspection of the Elevator All SA226 Series Airplanes (R) 02-23-16 Control System Rod End Bearings 27-081 04-13-16 Pitch Trim Actuator Upper All SA226 Series Airplanes (R) 06-27-16 Attach Fittings Inspection
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 1 of 8
SERVICE BULLETIN SA226 SERIES
FLIGHT CONTROLS
PITCH TRIM ACTUATOR UPPER ATTACH FITTINGS INSPECTION
1. PLANNING INFORMATION A. Effectivity:
All SA226 Series Airplanes.
B. Reason:
An operator reported stress corrosion cracks on pitch trim actuator upper attach fi ttings in the bolt holes and in the web radii of the fi ttings.
This revision de fi nes compliance requirement in step 1.D. if previous revision of this service bulletin was complied with, clari fi es steps 2.A.6)b) and 2.B.1), changes "as" to "or" in second note under 2.A.6)d), adds alternative parts to 3. Material Listing and adds Figure 3 to show bushing location and orientation.
C. Description:
Remove and perform an initial detailed visual inspection, liquid penetrant inspection (LPI) and high frequency eddy current (HFEC) inspection of the upper pitch trim actuator attach fi ttings for cracking in the bolt holes and the web/fl ange radius.
D. Compliance:
Mandatory.
Initial Inspection: Recommended as soon as possible and no later than 600 fl ight hours, or 12 calendar months, whichever occurs fi rst, from the date of this bulletin.
Repeat Inspection: Continue to repeat inspect upper pitch trim actuator attach fi ttings IAW step 2. Accomplishment Instructions in this bulletin every 5,000 fl ight hours or 5 calendar years, whichever occurs fi rst from the date of this service bulletin.
If steps 2.A.6)c) through 2.A.6)e) AND steps 2.B and 2.C were complied with per the initial issue of this service bulletin, the initial inspection requirement of this service bulletin is considered to be satis fi ed. Otherwise, additional compliance with this R1 revision of the service bulletin is required.
E. Approval:
FAA Approved for Engineering Design.
F. Manpower:
M7 Aerospace estimates 16 manhours to perform the initial inspection which includes removal and installation. This estimate is for direct labor only accomplished by an experienced crew. Adjust the estimate with operator task hour data as necessary.
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 2 of 8
SERVICE BULLETIN SA226 SERIES G. Material - Cost and Availability:
Contact M7 Aerospace Spares/Sales Department for Cost and Availability.
H. Tooling-Price and Availability:
Refer to the SA226 Maintenance Manual (MM) for required tooling for rigging of pitch trim control system if necessary.
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 SDR Review Item;
SA226 Maintenance Manual, 27-40-02;
SA226 Illustrated Parts Catalog (IPC) 27-40-02, Figure 1.
NOTE: References are for manufacturers’ use only.
K. Other Publications Affected:
ST-UN-M002 Airframe Airworthiness Limitations Manual.
2. ACCOMPLISHMENT INSTRUCTIONS A. Removals and Inspection:
1) Position horizontal stabilizer full leading edge up for easier access to pitch trim actuator (PTA) upper attach fi ttings.
2) Remove electrical power from the aircraft. Disconnect main batteries and Ground Power Unit (GPU). Tag out breakers and switches to prevent injury to personnel or damage to the aircraft.
3) Placard cockpit pitch trim controls " DO NOT USE" to prevent damage to aircraft or injury to personnel.
4) Gain access to PTA upper attach fi ttings.
5) Mark the upper attach fi ttings with their position (LH or RH) and mark their lateral/ vertical location on the stabilizer spar to ensure the same rod end to fi tting lug alignment is maintained when reinstalled.
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 3 of 8
SERVICE BULLETIN SA226 SERIES WARNING: DISCONNECTING BOTH PTA ROD ENDS FROM UPPER
ATTACH FITTINGS WILL ALLOW HORIZONTAL STABILIZER
TO PIVOT WITHOUT RESTRAINT AND MAY CAUSE INJURY TO
UNSUSPECTING PERSONNEL AND/OR DAMAGE TO AIRCRAFT STRUCTURE OR COMPONENTS. CARE MUST BE TAKEN TO
SUPPORT LEADING EDGE OF STABILIZER WHILE PTA IS DISCONNECTED FROM STABILIZER.
NOTE: The following instructions require removal of the fi ttings from the stabilizer spar. It is permitted to perform these inspections with fi ttings still installed provided operator/technician has the access to perform the inspection correctly, i.e., one bolt may be removed at a time and hole inspected, etc.
NOTE: It is recommended to remove one fi tting at a time as this aids installation.
6) The following instructions apply to both upper attach fi ttings:
a) Remove hardware securing PTA rod end to upper attach fi tting (See Figure
1). Inspect hardware for condition and replace as required.
b) Remove hardware securing upper attach fi tting to horizontal stabilizer and remove fi tting from stabilizer (See Figure 1). Inspect hardware for condition and replace as required. Bushings do not need to be removed. If aircraft records show Service Letter 226-SL-031 has been complied with and fi ttings have not been replaced since compliance, proceed with the following steps.
Otherwise, inspect each side of the fi tting lugs IAW 226-SL-031 in conjunction with the following inspections.
c) Detail visual inspect for cracks and corrosion over entire surface of fi tting using good light (100 fc minimum).
d) Perform a liquid penetrant inspection (LPI) of the fi tting radius area for cracks in accordance with SA226/227 Structural Repair Manual (SRM) Chapter 51- 30-07 (See Figure 2 for inspection areas).
NOTE: Liquid penetrant inspection requires removal of primer/paint and cleaning of surface.
NOTE: It is permissible to substitute HFEC or ultrasonic inspection method IAW SRM 51-30-07 in lieu of LPI.
e) Perform a high frequency eddy current (HFEC) inspection of the fi tting to stabilizer bolt holes (4 off per fi tting) shown in Figure 1 in accordance with SA226/227 SRM, Chapter 51-30-07 (See Figure 2 for inspection areas).
NOTE: The fi tting is fabricated from a 2000 series aluminum alloy.
NOTE: A manual or rotary hole probe method for each hole is acceptable (Probe must be capable of detecting fl aw sizes ≤ 0.030 inch (0.762 mm)).
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 4 of 8
SERVICE BULLETIN SA226 SERIES B. Installation:
1) If any cracks or corrosion are found, replace the attach fi tting (Refer to step 3.
Material Listing for correct replacement part numbers):
a) If installing 27-43062-011R or -019R fi tting (without bushings installed), refer to Figure 3 for bushing location and orientation. If necessary, line ream bushing holes in fi tting to 0.4380/0.4385 inch (11.125/11.138mm) diameter and install bushings wet with primer IAW SA226/227 SRM Chapter 51-30-02.
b) Match drill fi tting with 4x attach holes 0.250/0.254 inch (6.35/6.45 mm) diameter to holes in stabilizer spar, ensuring the fi tting is located in the same position as marked on spar in step 2. A. 5).
c) Re-identify fi tting with drilled assembly part number determined in step 2.B.1) minus the "R" (i.e., 27-43062-013 or -015).
d) Proceed to step 2.B.3).
2) If no cracks or corrosion are found, reinstall fi tting as follows.
3) Ensure entire fi tting is alodined and primed prior to installation, otherwise fi nish IAW SA226/227 SRM, Chapter 51-30-02, including the attachment holes.
4) Fay seal fi tting to stabilizer spar IAW SA226/227 SRM, Chapter 51-30-03.
5) Secure fi tting to stabilizer with AN4-7A bolts, AN960-416L washers and MS21042L4 nuts (See Figure 1). Torque nuts 65-90 inch lbs (7.34-10.17 Nm).
6) Secure PTA rod end to upper attach fi tting (Refer to SA226 IPC 27-40-02, Fig 1 and Service Letter 226-SL-031 for part numbers, correct hardware orientation and stack-up). Torque nuts 100-140 inch lbs (11.30-15.82 Nm).
C. Return to Service:
1) Reconnect main batteries and reconnect Ground Power Unit to aircraft. Remove tags from switches and breakers.
2) Remove placard from cockpit pitch trim controls installed in Step 2.A.3).
3) Remove tags from breakers and switches pulled in step 2.A.2) and reset.
4) Perform Operational Test - Actuator Time Check IAW SA226 MM, Section 27-40-02.
5) Perform Operational Test - Indicating and Warning IAW SA226 MM, Section 27- 41-03 or 27-42-03 as appropriate for airplane S/N.
6) Install all access panels and components removed to perform this service bulletin.
D. Complete aircraft records in accordance with 14 CFR 43.9.
E. Complete and return service bulletin Compliance Form to M7 Aerospace Technical Publications Department. Email: MetroTech@M7Aerospace.com
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 5 of 8
SERVICE BULLETIN SA226 SERIES
3. MATERIAL LISTING
ITEM PART NUMBER QTY LH/RH Upper Attach Fitting Assy. § (Airplane S/N AT001-074; TC201-419) 27-43062-013R * AR As an alternative to 27-43062-013R Fitting Assembly, the following parts may be assembled:
Fitting § 27-43062-019R * 1 Bushing NAS77A-5-26 ** 1 Bushing NAS77A-5-38 ** 1 LH/RH Upper Attach Fitting Assy. § (Airplane S/N T201-417) 27-43062-015R * AR As an alternative to 27-43062-015R Fitting Assembly, the following parts may be assembled:
Fitting § 27-43062-011R * 1 Bushing NAS77A-5-26 ** 1 Bushing NAS77A-5-38 ** 1 Upper Attach Fitting Assembly to Stabilizer Hardware:
Bolt AN4-7A ** ҂ AR Washer AN960-416L ** ҂ AR Nut MS21042L4 ** ҂ AR PTA Rod End to Upper Attach Fitting Hardware Ref SA226 IPC 27-40-02, Fig 1 or Service Letter 226-SL-031 AR § M7 Aerospace Sales Support item: M7-Sales@M7Aero.com. Fitting Assembly comes with NAS77A-5-26 and NAS77A-5-38 bushings installed.
* An "R" following the part number indicates the attach bolts holes (4 off) are omitted, to be located on installation to match existing aircraft structure.
** Customer furnished material.
҂ Alternate bolts NAS6204, NAS6304, NAS6704 (measure grip length as required) and alternate washers NAS1149F0432P and NAS1149G0432P are permitted. Permissible to adjust washer thickness to ensure correct torque and installation of bolt if alternate hardware or aircraft build requires adjustment.
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 6 of 8
SERVICE BULLETIN SA226 SERIES 62708101
PITCH TRIM
ACTUATOR AN4-7A BOLT AN960-416L WASHER MS21042L4 NUT REFER TO 226 IPC 27-40-02, FIG 1 AND SERVICE LETTER 226-SL-031
FOR HARDWARE PART NUMBERS AND STACK-UP
UPPER ATTACH
FITTINGS ROD ENDS FIGURE 1
LOCATOR - UPPER ATTACH FITTINGS
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 7 of 8
SERVICE BULLETIN SA226 SERIES FIGURE 2
UPPER ATTACH FITTING INSPECTION AREAS 62708102
RADIUS AREA, BOTH SIDES (PROBABLE CRACK LOCATION)
FITTING TO STABILIZER ATTACH BOLT HOLES, 4 PLACES (PROBABLE CRACK LOCATION)
ACTUATOR LUG
PITCH TRIM ACTUATOR
UPPER ATTACH FITTING
Issued: April 13, 2016 Revised: June 27, 2016 226-27-081 R1 Page 8 of 8
SERVICE BULLETIN SA226 SERIES 27-43062 FITTING NAS 77A-5-38 BUSHING NAS 77A-5-26 BUSHING
LUGS OF
FITTING FWD
0.008 INCH A A
VIEW A - A SHOWN AS SECTION THROUGH CENTER OF BOLT HOLES.
(PILOT SIDE SHOWN FOR CLARITY, CO-PILOT SIDE IS SAME).