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Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07 TITLE FLIGHT
CONTROLS - PILOT AND
COPILOT RUDDER PEDAL
PUSHROD
LINKAGE
INSPECTION
EFFECTIVITY MODEL SERIAL
NUMBERS B200GT BY - 335 , BY - 356 , BY - 443 , BY - 453 , BY - 454 B200CGT BZ - 4 thru BZ - 9 B300 FL - 1 173 thru FL - 1 175 , FL - 1 177 , FL - 1 181 , FL - 1 184 thru FL - 1 186 , FL - 1 189 , FL - 1 193 , FL - 1 197 thru FL - 1202 , FL - 1210 , FL - 121 1 , FL - 1213 , FL - 1218 , FL - 1220 thru FL - 1222 , FL - 1225 , FL - 1228 thru FL - 1230 , FL - 1232 , FL - 1233 , FL - 1240 thru FL - 1242 , FL - 1244 , FL - 1245 , FL - 1249 thru FL - 1251 , FL - 1253 , FL - 1257 thru FL - 1259 , FL - 1262 , FL - 1265 , FL - 1266 , FL - 1269 , FL - 1271 , FL - 1275 , FL - 1276 , FL - 1277 , FL - 1280 , FL - 1284 , FL - 1286 , FL - 1287 , FL - 1290 , FL - 1291 , FL - 1293 , FL - 1296 , FL - 1305 , FL - 1310 , FL - 1315 thru FL - 1317 , FL - 1319 , FL - 1320 B300C FM - 78 thru FM - 86 , FM - 88 , FM - 90 thru FM - 92 , FM - 94 , FM - 96 thru FM - 107 , FM - 1 10 NOTE:
The airplanes listed in the ef fectivity above that have the digital flight data recorder , DFDR , installed are af fected by this service document.
REASON During installation of the rudder pushrod rod end the incorrect type of rivet that attaches the rod end may have been installed.
If the incorrect rivet was installed this could cause the rudder pushrod tube to separate from the rod end.
Failure to comply can result in loss of rudder control which can result in loss of control of the airplane during flight or ground operations.
DESCRIPTION This service document provides parts and instructions to inspect the pilots and copilot's rudder pushrods for the correct rivets and replace them as required.
COMPLIANCE MANDA T OR Y .
This service document must be accomplished on airplanes that have the DFDR installed.
NOTE:
Any identified soft rivet (no marking) regardless of rivet location and / or left and right pushrods , must be replaced in the time stated within the compliance section
• No mark (alloy code A):
1 100 or 3003 pure aluminum
• Dimple (alloy code AD) 21 17 aluminum alloy MTL - 27 - 07 July 25 , 2025 Page 1 of 8 T extron A viation Customer Service , P .O.
Box 7706 , Wichita , KS 67277 , U.S.A.
1 - 316 - 517 - 5800 This document contains technical data and is subject to U.S.
export regulations.
This information has been exported from the United States in accordance with export administration regulations.
Diversion contrary to U.S.
law is prohibited.
ECCN:
9E991
COPYRIGHT © 2025
MTL - 27 - 07 Page 2 July 25 , 2025 Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07 Criteria Compliance T ime Inspection Within 20 flight hours or 30 days from the service document date , which ever occurs first.
If 2 soft rivets are found adjacent to each other on the same rod end for one pushrod.
Before next flight.
If 1 soft rivet and 1 hard rivet are installed on any of the 4 rod ends.
Within 200 flight hours or 12 month inspection , which ever occurs first.
A service document published by T extron A viation may be recorded as completed in an aircraft log only when the following requirements are satisfied:
1) If the aircraft serial number is identified within the (Ef fectivity Section) , the mechanic must use all technical data while accomplishing the instructions within this service document.
The mechanic must maintain compliance to aviation acceptable standard practices and regulations (CFR).
2) The mechanic must correctly use and install all applicable parts supplied with the service document kit.
Only with written authorization from T extron A viation can substitute parts or rebuilt parts be used to replace new parts.
No individual or corporate organization other than T extron A viation is authorized to make or apply any changes to a T extron A viation - issued service document or flight manual supplement without prior written consent from T extron A viation.
T extron A viation is not responsible for the quality of maintenance performed to comply with this document , unless the maintenance is accomplished at a T extron A viation - owned Service Center .
CONSUMABLE MA TERIAL Y ou must use the consumable materials that follow , or their equivalent , to complete this service document.
NAME NUMBER MANUF
ACTURER USE Corrosion Resistant Primer Graco Supply Company 2056 S.
Edwards Ste.
C Wichita , KS 67213 Corrosion Resistant Primer .
Color Chemical Film T reatment U074093 (Alodine 1 132 T ouch n Prep) T extron A viation Parts Distribution WW2.TXT A V .COM / P AR TS T o prepare bare aluminum surface for intermediate primer .
Bonderite M - CR 1 132 , (formerly the Alodine 1 132 T ouch - n - prep) are both approved for small touch up areas , generally less than 6 inches square.)
Isopropyl Alcohol Commercially A vailable T o clean metal surfaces prior to bonding.
T OOLING No specialized tooling is required to complete this service document.
REFERENCES Beechcraft Super King Air B200GT / B200CGT Fusion Maintenance Manual Beechcraft Super King Air B300 / B300C Fusion Maintenance Manual Beechcraft Structural Inspection and Repair Manual
PUBLICA TIONS
AFFECTED None
Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07
ACCOMPLISHMENT
INSTRUCTIONS
1.
Prepare the airplane for maintenance.
A.
Make sure that the airplane is electrically grounded.
B.
Make sure that all switches are in the OFF / NORM position.
C.
Disconnect electrical power from the airplane.
(1) Disconnect external electrical power .
(2) Disconnect the main airplane battery .
D.
Attach maintenance warning tags to the battery and external power receptacle that have "DO NOT
CONNECT
ELECTRICAL POWER -
MAINTENANCE IN PROGRESS" written on them.
2.
Remove the pilot and copilot seats.
• For all Beechcraft Model B300 airplanes , refer to the Beechcraft Super King Air B300 / B300C Fusion Maintenance Manual , Chapter 25 , Pilot and Copilot Seat - Removal / Installation.
• For all Beechcraft Model B200 airplanes , refer to the Beechcraft Super King Air B200GT / B200CGT Fusion Maintenance Manual , chapter 25 , Flight Compartment Seat Removal / Installation.
3.
Remove the 131A TL , 141A TL , 132A TR , 142A TR , 31 1CL (B200 Model Airplanes ) , and 31 1BL (B300 Model Airplanes) Access Panels.
(Refer to the applicable Beechcraft Maintenance Manual , Chapter 6 , Airplane Access Panels - Description and Operation.)
4.
(Refer to Figure 1 , Sheet
1) Using a high powered flashlight and an inspection mirror , inspect the four attaching rivets on the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod as follows:
NOTE:
Any identified soft rivet (no marking) regardless of rivet location and / or left and right pushrods , must be replaced in the time stated within the compliance section
• No mark (alloy code A):
1 100 or 3003 pure aluminum
• Dimple (alloy code AD) 21 17 aluminum alloy A.
If any of the four rivets do not have the dimple marking on the center of the rivet head or if the marking can not be determined on the rivet head , go to Step
4.
A.
(1).
(1) Mark all rivets without a dimpled marking on the center of the rivet head with an indelible marker .
NOTE:
The marking of the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod is to help the technician remember which rivets have been installed incorrectly into the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod.
MTL - 27 - 07 July 25 , 2025 Page 3
MTL - 27 - 07 Page 4 July 25 , 2025 Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07 B.
If all four rivets have a clear dimple marking on the center of the rivet head , go to Step
5.
5.
Repeat Step 4 for the right 129 - 524126 - 0013 Right Pilot's Rudder Pushrod , the 129 - 524126 - 001 1 Left Co - Pilot's Rudder Pushrod , and the 129 - 524126 - 0013 Right Co - Pilot's Rudder Pushrod.
6.
Depending upon the inspection of the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod do as follows:
NOTE:
Any identified soft rivet (no marking) regardless of rivet location and / or left and right pushrods , must be replaced in the time stated within the compliance section
• No mark (alloy code A):
1 100 or 3003 pure aluminum
• Dimple (alloy code AD) 21 17 aluminum alloy A.
If all sixteen rivets for the 129 - 524126 - 001 1 Left and 129 - 524126 - 0013 Right Pilot's and Co - Pilot's Rudder Pushrod's has a dimple marking on the rivet head , then go to Step
13.
B.
Regardless of the inspection results , if there are two or one marked rivet on the same rod end for any of the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrods , go to Step
7.
7.
Remove the marked rivet(s) from the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod as follows:
A.
(Refer to Figure 2 , Sheet
1.)
Starting from the pilot's left rudder pushrod , remove the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod as follows:
(1) Disconnect the electrical connector from the rudder pedal input force transducer .
(2) Remove and discard the two MS24665 - 132 Cotter Pins.
(3) Remove and discard the two MS17825 - 3 Nuts.
(4) Remove and keep the two bolts and washers from the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod.
CAUTION:
Prior to the removal of any rivet from the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod , the pushrod should be placed in a clamping device so that the pushrod does not move or rotate when removing the marked rivet.
Failure to secure the pushrod may oversize the hole within the pushrod assembly .
B.
Remove the marked rivet from the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod.
(Refer to the Beechcraft Structural Inspection and Repair Manual , Chapter 20 , Fastener Installation and Removal.)
C.
Clean out the drilled hole using Isopropyl Alcohol.
D.
Apply Color Chemical Film T reatment to all bare aluminum.
E.
Install a MS20470AD4 - 12 Rivet , wet with Corrosion Resistant Primer into the existing drilled hole.
(Refer to the Beechcraft Structural Inspection and Repair Manual , Chapter 20 , Fastener Installation and Removal.)
F .
Repeat Step
7.
A.
thru
7.
E.
for any additional marked rivet on the removed rudder pushrod.
8.
(Refer to Figure 2 , Sheet
1.)
Starting from the pilot's left rudder pushrod , install the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod:
NOTE:
The installation of the 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod is the same for all of the rudder pushrods.
A.
Install the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod with the kept bolts and washers.
B.
Install a MS17825 - 3 Nut onto each end of the 129 - 524126 - 001 1 Left Pilot's Rudder Pushrod.
C.
T orque the two MS17825 - 3 Nuts.
(Refer to the Beechcraft King Air Chapter 20 Standard Practices - Airframe , Chapter 20 , Bolt Installation and T orque Application - Maintenance Practices.)
Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07 D.
Install a MS24665 - 132 Cotter Pin(s) into each torque MS17825 - 3 Nut(s).
E.
Connect the electrical connector to the rudder pedal input force transducer .
F .
Repeat Step 9 for the three remaining 129 - 524126 - 001 1 Left or 129 - 524126 - 0013 Right Pilot's or Co - Pilot's Rudder Pushrod.
9.
Remove the maintenance warning tags and connect the airplane battery .
10.
Do a full swing , from left to right , of the rudder control system and make sure that each primary stop is touched.
1.
Do the Rudder Pedal Input Forces T ransducer Functional T est.
(Refer to the applicable Maintenance Manual , Chapter 31 , Rudder Pedal Input Forces T ransducer - Adjustment / T est.)
12.
Install the 131A TL , 141A TL , 132A TR , 142A TR , 31 1CL (B200 Model Airplanes ) , and 31 1BL (B300 Model Airplanes) Access Panels.
(Refer to the applicable Beechcraft Maintenance Manual , Chapter 6 , Airplane Access Panels - Description and Operation.)
13.
Install the pilot and copilot seats.
• For all Beechcraft Model B300 airplanes , refer to the Beechcraft Super King Air B300 / B300C Fusion Maintenance Manual , Chapter 25 , Pilot and Copilot Seat - Removal / Installation.
• For all Beechcraft Model B200 airplanes , refer to the Beechcraft Super King Air B200GT / B200CGT Fusion Maintenance Manual , Chapter 25 , Flight Compartment Seat Removal / Installation.
14.
Make an entry in the airplane logbook that states compliance and method of compliance with this service document.
NOTE:
T extron A viation recommends that compliance with all service documents is reported to a maintenance tracking system provider .
• Complete a record of compliance.
(Maintenance T ransaction Report , Log Book Entry , or other record of compliance.)
• Put a copy of the completed record of compliance in the airplane logbook.
• Send a copy of the completed record of compliance to the maintenance tracking system provider used.
MTL - 27 - 07 July 25 , 2025 Page 5
Beechcraft Hawker Beechcraft SERVICE LETTER TEXTRON ÀVIATION Cessna MANDATORY MTL-27-07 E78481 0000001° Rudder Pedal Pushrod
• (Reference) Rivets to Inspect Rivets to Inspect MS20740AD4-12 MS20740AD4-12 Rivet Rivet (As Required, 2 Total) (As Required, 2 Total)
DETAIL A (View Looking Down at Rudder Pushrod) NOTE: The Pilot's and Co-Pilot's rudder pushrods are typical to each other.
Figure 1. Rivet Pushrod Inspection (Sheet 1) MTL-27-07 Page 6 July 25, 2025
Beechcrafi Hawker Beechcraft SERVICE LETTER TEXTRON ÀVIATION Cessna MANDATORY MTL-27-07 E78482 00001 Rudder Pedal (Reference) MS24665-132 Cotter Pin (As Required, 2 Total) MS17825-3 Nut -(As Required, 2 Total) Washer (Reference) Connector Bolt (Reference) (Reference) 129-524126-0011 (Left) Force Transducer 129-524126-0013 (Right) Rudder Pedal Pushrod (Reference) (Reference)
DETAIL A Figure 2. Rudder Pushrod Installation (Sheet 1) MTL-27-07 July 25, 2025 Page 7
MTL - 27 - 07 Page 8 July 25 , 2025 Beechcraft SER VICE LETTER MANDA T OR Y MTL - 27 - 07 MA TERIAL
INFORMA TION The parts below may be required to complete this service letter .
NEW P / N QUAN- TITY KEY WORD OLD P / N
INSTRUCTIONS /
DISPOSITION MS20470AD4 - 12 4 T otal Per Pushrod (As Required) Rivet V arious Discard old , Install new .
MS24665 - 132 2 T otal Per Pushrod (As Required) Cotter Pin Same Discard old , Install new .
MS17825 - 3 2 T otal Per Pushrod (As Required) Nut Same Discard old , Install new .
* Please contact your Regional T extron A viation Parts Distribution Customer Support T eam for current cost and availability of parts listed in this service document.
Phone at 1 - 800 - 835 - 4000 (Domestic) or 1 - 316 - 517 - 5603 (International).
For more information , please visit the T APD Support & Aftermarket Account Management website at https:
/ / ww2.txtav .com / Parts.
Based on availability and lead times , parts may require advanced scheduling.
Beechcraft OWNER
ADVISOR Y MTL - 27 - 07 TITLE FLIGHT
CONTROLS - PILOT AND
COPILOT RUDDER PEDAL
PUSHROD
LINKAGE
INSPECTION T O:
Beechcraft Model B200GT , B200CGT , B300 , and B300C Aircraft Owner REASON During installation of the rudder pushrod rod end the incorrect type of rivet that attaches the rod end may have been installed.
If the incorrect rivet was installed this could cause the rudder pushrod tube to separate from the rod end.
Failure to comply can result in loss of rudder control which can result in loss of control of the airplane during flight or ground operations.
COMPLIANCE MANDA T OR Y .
This service document must be accomplished by airplanes that have the DFDR installed.
NOTE:
Regardless if there are two adjacent or one marked rivet on the same rod end all marked rivet(s) needs to be replaced at the same time that is stated within the compliance section.
NOTE:
If any of the left and / or right rudder pushrods have two adjacent soft rivets on any one of the pushrod ends , then all of the soft rivets on any rod ends of the left and / or right pushrod ends , the soft rivets must be replaced.
Criteria Compliance T ime Inspection Within 20 flight hours or 30 days from the service document date , which ever occurs first.
If 2 soft rivets are found adjacent to each other on the same rod end for one pushrod.
Before next flight.
If 1 soft rivet and 1 hard rivet are installed on any of the 4 rod ends.
Within 200 flight hours or 12 month inspection , whichever occurs first.
LABOR HOURS WORK PHASE LABOR - HOURS Modification
16.0 MA TERIAL A V
AILABILITY P ART NUMBER A V
AILABILITY COST MS20470AD4 - 12 * * MS24665 - 132 * * MS17825 - 3 * * * Please contact your Regional T extron A viation Parts Distribution Customer Support T eam for current cost and availability of parts listed in this service document.
Phone at 1 - 800 - 835 - 4000 (Domestic) or 1 - 316 - 517 - 5603 (International).
MTL - 27 - 07 July 25 , 2025 Page 1 of 2 T extron A viation Customer Service , P .O.
Box 7706 , Wichita , KS 67277 , U.S.A.
1 - 316 - 517 - 5800 This document contains technical data and is subject to U.S.
export regulations.
This information has been exported from the United States in accordance with export administration regulations.
Diversion contrary to U.S.
law is prohibited.
ECCN:
9E991
COPYRIGHT © 2025
MTL - 27 - 07 Page 2 July 25 , 2025 Beechcraft OWNER
ADVISOR Y MTL - 27 - 07 For more information , please visit the T APD Support & Aftermarket Account Management website at https:
/ / ww2.txtav .com / Parts.
Based on availability and lead times , parts may require advanced scheduling.
W
ARRANTY This service document is mandatory .
Eligible airplanes may qualify for parts and labor coverage to the extent noted in the Labor Hours and Material A vailability sections of this document.
Eligibility:
Airplanes identified within the serial number ef fectivity of this service document must have active Airframe warranty coverage on the original issue date of this document and the coverage must be active on the day the work is accomplished.
Parts Coverage:
T extron A viation - owned and T extron A viation - authorized Service Facilities , operators , or other maintenance facilities may submit a claim for the parts required to accomplish this service document as defined in the Material A vailability section of this document.
Labor Coverage:
T extron A viation - owned and T extron A viation - authorized Service Facilities rated to perform maintenance on the specific model of Beechcraft Aircraft may submit a claim for the labor necessary to accomplish this service document as defined in the Labor Hours section of this document.
Credit Application:
After this service document has been accomplished , a claim must be submitted to T extron A viation within 30 days of the service document completion.
Claims for compliance of this service document are to be filed as a W4 type claim.
Please submit your claim form online at ww2.txtav .com / Parts or email the completed T extron A viation Claim Form to warranty@txtav .com .
If submitted on - line a Return Authorization will be provided.
If a paper claim is submitted your claim will be entered into the system and a Return Authorization will be sent to you.
The Return Authorization must accompany any required return parts (see Material A vailability ) , to the point of purchase.
Parts to be returned to T extron A viation should be forwarded to:
TEXTRON A VIA TION P AR TS
DISTRIBUTION W
ARRANTY
ADMINISTRA TION BLDG P43 DOCK R5 7123 SW BL VD Wichita , KS 67215 Expiration:
July 31 , 2027 (after this date the owner / operator assumes the responsibility for compliance costs) T extron A viation reserves the right to void continued airplane warranty coverage for the parts af fected by this service document until the service document is accomplished.
NOTE:
As a convenience , service documents are now available online to all our customers through a simple , free - of - charge registration process.
If you would like to sign up , please visit the Customer Access link at support.txtav .com to register .