# Piper Service Bulletin 1409: Revision A - Rights: © Piper. Filed by the FAA in regulations.gov docket FAA-2023-2241; AD 2023-25-02 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - Document: [Piper Service Bulletin 1409](https://openairdocs.org/service-documents/piper/sb-1409.md) - Title as filed: Piper Service Bulletin No. 1409A - Pages: 8 - PDF: https://openairdocs.org/files/sha256/67/56/6756838d025f0ecee3960aca5dee81e42c898e608dc8aea4a76166ae9912bf0b - Page: https://openairdocs.org/service-documents/piper/sb-1409/file/6756838d025f ## Text Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 (OVER) Date: November 21, 2023 (S) SERVICE BULLETIN NO. 1409A PIPER CONSIDERS COMPLIANCE MANDATORY ATA/JASC: 2701 Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 Service Bulletin (SB) 1409A supersedes SB 1409 in its entirety. SUBJECT : CONTROL COLUMN ASSEMBLY INSPECTION REASON FOR REVISION : SB 1409A clarifies the flight limitations defined in Part II, adds additional affected Production Order numbers, and revises the instructions and installation hardware differences between aircraft models in Part III. MODELS AFFECTED : SERIAL NUMBERS AFFECTED : PA-46-350P M350 4636811 thru 4636814, 4636816 thru 4636829 PA-46-500TP M500 4697692 thru 4697700 PA-46-600TP M600 4698224 thru 4698240, 4698242 thru 4698274 COMPLIANCE TIME : Before further flight, except as provided in Part II. APPROVAL : The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved. PURPOSE : On some of the affected aircraft, a retaining ring may be missing from the left and/or right control column mounts, which is secured to the pressure bulkhead. If the retaining ring is absent, possible loss of pitch and roll controls could occur during flight. This service bulletin mandates a one-time inspection of the control column mounts to verify the installation of the retaining ring and, if required, to install a retaining ring. INSTRUCTIONS : NOTE : Some steps in these instructions are identified as “required for compliance” (RC). If this service bulletin is mandated by an airworthiness directive (AD), the steps identified as RC must be done to comply with the AD. Steps not identified as RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in this service bulletin, if the RC steps can be done and the airplane can be put back in a serviceable condition. Part I. Temporary Grounding THE ABOVE AFFECTED AIRCRAFT ARE GROUNDED UNTIL FURTHER NOTICE, EXCEPT AS PROVIDED FOR IN PARTS II AND III OF THIS SERVICE BULLETIN. ### Page 2 SERVICE BULLETIN NO. 1409A PAGE 2 of 8 Part II. Allowance for a One-Time Flight Aircraft are allowed a one-time flight to reach the nearest Piper Aircraft Dealer/Service Center or other appropriate MRO facility that is capable of performing the inspection(s) and/or repair(s) described in Part III. Until the aircraft is made compliant with Part III, the following operating limitations shall be in place: • One flight in VFR conditions with minimum required crew only assuming the preflight checks below are successful. • Prior to flight, verify normal, unrestricted movement of the primary flight controls. • Prior to flight, verify elevator and aileron controls for proper operation and expected control forces. CAUTION : IN FLIGHT , IF THE CONTROL COLUMN FEELS OR VISUALLY APPEARS TO BE LOOSE, HAS A SUBSTANTIAL INCREASE IN CONTROL FORCE REQUIREMENTS, OR HAS A REDUCTION IN CONTROL AUTHORITY , LAND AS SOON AS POSSIBLE. IF THE AUTOPILOT IS USED, PAY CLOSE ATTENTION TO UNUSUAL "AIL" OR "ELE" OUT-OF-TRIM ANNUNCIATIONS. IF OUT-OF-TRIM ANNUNCIATIONS APPEAR, PERFORM THE "AUTOPILOT OUT-OF-TRIM" EMERGENCY CHECKLIST IN THE APPROPRIATE PILOT OPERATING HANDBOOK. IF THE OUT-OF-TRIM INDICATIONS CONTINUE TO OCCUR OR CANNOT BE RESOLVED, DO NOT USE THE AUTOPILOT FOR THE REMAINDER OF THE FLIGHT. NOTE : Refueling stops are permitted. RC – Part III. Inspection NOTE : The temporary removal of interior components, access panels and other aircraft components may be required in order to accomplish these instructions. NOTE : The instructions that follow apply to both left and right sides of the aircraft. NOTE : With the exception of the cotter pin, Piper P/N 424-052 (MS24665-134), retain all hardware for reinstallation. (Applies only to PA-46-600TP M600 aircraft.) NOTE : Unless specified otherwise, torque threaded fasteners according to the applicable Piper Airplane Maintenance Manual (AMM). NOTE : The control column mount assemblies with the potential for a missing retaining ring, Piper P/N 485-083 (MS16625-2075), are limited to the following Production Orders: • M01274373 • M01296002 • M01332457 • M01338268 • M01327594 The Production Order will be marked on the part. If it can be determined that a control column mount assembly is from a different Production Order at any time during this inspection, then no further disassembly is required. NOTE : Regardless of the findings, report the results of this inspection to Piper electronically by completing and submitting the Inspection Feedback Form at https://techpubs.piper.com/feedback. 1. RC – Remove the control column. Refer to chapter 27-10-00 of the appropriate Piper AMM for removal instructions. 2. RC – Locate the area identified in Figure 1. 3. RC – Remove the 2 bolts and washers that secure the aileron quadrant assembly to the pressure bulkhead, which are accessible from the forward side of the pressure bulkhead. 4. RC – Remove the hardware securing the mount assembly to the quadrant assembly. • On PA-46-350P M350 & PA-46-500TP M500 aircraft, remove the nut and washer from the shaft on the forward side of the quadrant assembly. • On PA-46-600TP M600 aircraft, remove the cotter pin, nut and washer from the shaft on the forward side of the quadrant assembly. Discard the cotter pin. 5. RC – Slide the mount assembly forward to remove it from the shaft of the quadrant assembly. 6. RC – Inspect the mount assembly for the Production Order number of the part and make note of it. In addition, take photos of both sides of the mount assembly with the Production Order number visible. ### Page 3 SERVICE BULLETIN NO. 1409A PAGE 3 of 8 7. RC – Verify the mount assembly conforms to type design as shown in Figure 2. a. Examine the mount assembly for the presence of the retaining ring, Piper P/N 485-083 (MS16625-2075), When properly installed, the retaining ring will nest inside a machined groove. 1) If the retaining ring is present, no action is required. Proceed to step 8. 2) If the retaining ring is not present, action is required before proceeding to step 8. a) Examine the bearing installed in the mount block. Determine if a retaining compound is applied to the bearing, securing it in the mount block. (1) If retaining compound is present, no action is required. Proceed to step b). (2) If retaining compound is not present, action is required. Remove the bearing from the block mount, apply an approved retaining compound (see Table 1), and reinstall the bearing into the mount block. Allow retaining compound to cure as required. b) Order and install the retaining ring into the mount assembly. 8. RC – Reinstall the mount assembly onto the shaft of the quadrant assembly. Reinstall washer and nut. • On PA-46-350P M350 & PA-46-500TP M500 aircraft, final torque on nut shall be 50–70 in•lb, plus friction drag. • On PA-46-600P M600 aircraft, initially torque nut to 50 in•lb, plus friction drag. Then set torque wrench to 70 in•lb plus friction drag and slowly tighten until the cotter pin hole and nut castellation align. Install a new cotter pin. 9. RC – Reinstall the quadrant assembly to the pressure bulkhead with the installation hardware (2 bolts and washers) that was removed in step 3. Wet install the installation hardware with an approved Type 1/1LD sealant (see Table 2). Apply sealant to the bottom surface of fastener head, fastener shank, and underside of any washers. Verify sealant squeezes out around complete periphery of fastener head. Refer to Table 3 for application time (work life) of Type 1/1LD sealants. NOTE : Sealant may be applied with the equivalent method of applying sealant around the hole on the head side in area that will make contact with fastener head. 10. RC – Reinstall the control column. Refer to chapter 27-10-00 of the appropriate Piper AMM for installation instructions. 11. RC – Perform a functional check on any systems that were disturbed during this inspection. 12. Regardless of the findings, report the results of this inspection to Piper electronically by completing and submitting the Inspection Feedback Form at https://techpubs.piper.com/feedback. Include the Production Order number and photo(s) of each mount assembly as requested in step 6. 13. Make a logbook entry documenting compliance with this service bulletin, specifically stating the results of this inspection. ### Page 4 SERVICE BULLETIN NO. 1409A PAGE 4 of 8 TABLE 1 APPROVED RETAINING COMPOUNDS Product Name Piper Part Number Viscosity Strength Full Cure Time Color Loctite 609 189-977 Low High 6 Hours Green Loctite 680 279-027 Medium High 168 hours Green TABLE 2 APPROVED TYPE 1/1LD SEALANTS Product Name Color Cured Hardness Class / Work Life Typical Time (Hours) Piper Part NumberTack Free Cure 2.5 oz 6.0 oz Royal WS-8032 Dark Gray ≥48A B-½ <4 <6 279-428 279-432B-2 <6 <9 279-429 279-433 PPG PR-2007 Dark Brown ≥45A B-½ 4 6 279-426 279-430B-2 <6 8 279-427 279-431 TABLE 3 TYPE 1/1LD SEALANT APPLICATION TIME (WORK LIFE) Work Life B-½ Temperature (°F) 40–55 55–70 70–85 85–100 100–115 Relative Humidity <10% 16 Hours 8 Hours 4 Hours 2 Hours 1 Hours 10–25% 8 Hours 4 Hours 2 Hours 1 Hours 30 Min. 25–40% 4 Hours 2 Hours 1 Hours 30 Min. 15 Min. 40–70% 2 Hours 1 Hours 30 Min. 15 Min. 7 Min. 70–85% 1 Hours 30 Min. 15 Min. 7 Min. 4 Min. >85% 30 Min. 15 Min. 7 Min. 4 Min. 2 Min. Work Life B-2 Temperature (°F) 40–55 55–70 70–85 85–100 100–115 Relative Humidity <10% 64 Hours 32 Hours 16 Hours 8 Hours 4 Hours 10–25% 32 Hours 16 Hours 8 Hours 4 Hours 2 Hours 25–40% 16 Hours 8 Hours 4 Hours 2 Hours 1 Hour 40–70% 8 Hours 4 Hours 2 Hours 1 Hour 30 Min. 70–85% 4 Hours 2 Hours 1 Hour 30 Min. 15 Min. >85% 2 Hours 1 Hour 30 Min. 15 Min. 7 Min. ### Page 5 SERVICE BULLETIN NO. 1409A PAGE 5 of 8 Figure 1 (Sheet 1 of 2) Control Column Inspection OUTBD FWD UP FLIGHT CONTROLS - COCKPIT 3D VIEW (COMPONENTS REMOVED FOR CLARITY) SEE DETAIL A ### Page 6 SERVICE BULLETIN NO. 1409A PAGE 6 of 8 Figure 1 (Sheet 2 of 2) Control Column Inspection NOTES: (1) Cotter Pin only used on PA-46-600TP. (2) PA-46-600TP: Castellated Nut, Piper P/N 603-877 (MS14145-4) PA-46-500TP / PA-46-350P: Self-Locking Nut, Piper P/N 404-530 (MS21042-4) SECTION B−B CROSS-SECTION OF AILERON QUADRANT ASSEMBLY (LH SHOWN, RH OPPOSITE) COTTER PIN (SEE NOTE 1) Piper P/N 424-052 (MS24665-134) CONTROL COLUMN MOUNT ASSEMBLY (SEE FIGURE 2) NUT WASHER (SEE NOTE 2) SHAFT RETAINING RING Piper P/N 485-083 (MS16625-2075) DETAIL A AILERON QUADRANT ASSEMBLY VIEW LOOKING DOWN (LH SHOWN, RH OPPOSITE) B B PRESSURE BULKHEAD BOLT WASHER (2 PLACES) FWD OUTBD FWD UP ### Page 7 SERVICE BULLETIN NO. 1409A PAGE 7 of 8 Figure 2 Control Column Mount Assembly BLOCK MOUNT BEARING RETAINING RING Piper P/N 485-083 (MS16625-2075) UP UP AFT ### Page 8 SERVICE BULLETIN NO. 1409A PAGE 8 of 8 MATERIAL REQUIRED : Per aircraft: • On PA-46-600TP aircraft only, Two (2) each, Cotter Pin, Piper P/N 424-052 (MS24665-134) • On condition, one or two (1–2) each, Retaining Ring, Piper P/N 485-083 (MS16625-2075) • On condition and as required, approved Retaining Compound (See T able 1 for product names and Piper P/Ns) • As required, approved Type 1/1LD Sealant (See T able 2 for product names and Piper P/Ns) AVAILABILITY OF PARTS : Procure Locally or Your Piper Approved Service Center – Find your local service center at https://www.piper.com/ EFFECTIVITY DATE : This service bulletin is effective on November 22, 2023. SUMMARY : Applicable factory participation is limited to new aircraft in warranty at the time of compliance. Factory participation will remain in effect for a period of time not to exceed 180 days from the effectivity date of this service bulletin. Please contact your Piper Approved Service Center to make arrangements for compliance with this service bulletin in accordance with the compliance time indicated. NOTE: Please notify the factory of any address/ownership corrections. Changes should include aircraft model, serial number, and current owner’s name and address. Corrections and/or changes should be directed to: PIPER AIRCRAFT , INC. Attn: Customer Service 2926 Piper Drive Vero Beach, FL 32960 or: CustomerService@piper.com Please include in subject line: “Aircraft ownership update” --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.