SERVICE BULLETIN NO. 1355A

Piper PA-32R Lance · Service Bulletins

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Overview

This Service Bulletin No. 1355A from Piper Aircraft addresses the inspection and potential replacement of the tee bar assembly in various Piper aircraft models, including the PA-32R-300 Lance. It supersedes the previous bulletin (SB 1355) and clarifies inspection instructions while correcting a reference error. The bulletin mandates compliance for affected aircraft, particularly those with 3,500 or more hours of time in service. It outlines a two-part compliance process: an initial inspection for cracks and a replacement procedure if cracks are found. The document emphasizes the importance of addressing any structural cracks before flight to maintain safety and compliance with FAA regulations.

Initial inspection required within 100 hours TIS for aircraft with 3,500 or more hours TIS.
Recurring inspections every 100 hours TIS until compliance with replacement is achieved.
Cracks in the tee bar assembly must be addressed before the next flight.
Replacement of the tee bar weldment assembly is mandatory if cracks are found.
Ensure no more than 0.010 inches of free play exists between control components.

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Originally published by piperowner.org. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.

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Document details

Type: Service Bulletins
Year: 2022
Pages: 10
File size: 1.1 MB
Publisher: piperowner.org

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In this document

Compliance Time

For aircraft with 3,500 or more hours time in service (TIS), initial compliance with the inspection is required within the next 100 hours TIS. Following this, recurring inspections must occur every 100 hours TIS until compliance with the replacement procedure is achieved.

Inspection Instructions

The inspection involves gaining visual access to the tee bar assembly and checking for cracks, especially at welded joints. If cracks are found, the tee bar weldment must be replaced before the next flight. If no cracks are found, the area must be cleaned and painted according to maintenance guidelines.

Replacement Procedure

If cracks are discovered, the replacement of the tee bar weldment assembly is required. The procedure includes removing the control wheels and columns, installing the new weldment assembly, and ensuring no more than 0.010 inches of free play exists between components.

Material Required

For compliance, the following materials may be needed: one tee bar weldment assembly, up to four brass shims (0.005 in.), and twelve locking clip turnbuckles. Parts should be procured from a Piper Approved Service Center.

Warnings

The bulletin includes a critical warning against flying with known cracks in the aircraft structure, as this may compromise the aircraft's design strength and safety.

Safety notes

Flight with known cracks in the aircraft structure is not allowed. Cracks must be repaired before the next flight.

Full document text

Date: March 14, 2022 (S)(M) SERVICE BULLETIN NO. 1355A PIPER CONSIDERS COMPLIANCE MANDATORY Piper Aircraft, Inc. 2926 Piper Drive Vero Beach, FL, U.S.A. 32960 (OVER) ATA/JASC: 2701 Service Bulletin (SB) 1355A supersedes SB 1355 in its entirety. Aircraft that were previously made compliant with SB 1355 are in compliance with SB 1355A. SUBJECT: TEE BAR ASSEMBLY INSPECTION REASON FOR REVISION: SB 1355A clarifies instructions and corrects a reference error MODELS AFFECTED: SERIAL NUMBERS AFFECTED: PA-28-140 Cherokee 28-20001 through 28-26946; 28-7125001 through 28-7725290 PA-28-150/-160 Cherokee 28-1 through 28-4377; 28-1760A PA-28-180 Cherokee 28E-13; 28-03; 28-671 through 28-5859; 28-7105001 through 28-7205318 PA-28-235 Cherokee Pathfinder 28-03; 28E-11; 28-10001 through 28-11378; 28-7110001 through 28-7710089 PA-28-236 Dakota 28-7911001 through 28-8611008; 2811001 through 2811050 PA-28-151 Warrior 28-7415001 through 28-7715314 PA-28-161 Cadet 2841001 through 2841365 PA-28-161 Warrior II 28-7716001 through 28-8216300; 28-8316001 through 28-8616057; 2816001 through 2816109 PA-28-161 Warrior III 2816110 through 2816119; 2842001 through 2842420 PA-28-180 Archer 28-E13; 28-7305001 through 28-7505261 PA-28-181 Archer II 28-7690001 through 28-8690056; 28-8690061, 28-8690062; 2890001 through 2890205 PA-28-181 Archer III 2890206 through 2890231; 2843001 through 2843949; 2881001 through 2881481 PA-28-181 Piper Pilot 100i 28020001 through 28020024 PA-28-201T Turbo Dakota 28-7921001 through 28-7921095 PA-28R-180 Arrow 28R-30002 through 28R-31270; 28R-7130001 through 28R-7130013 PA-28R-200 Arrow 28R-35001 through 28R-35820; 28R-7135001 through 28R-7135229 PA-28R-200 Arrow II 28R-7235001 through 28R-7635545 PA-28R-201 Arrow III 28R-7737002 through 28R-7837317; 2837001 through 2837061; 2844001 through 2844185 SERVICE BULLETIN NO. 1355A PAGE 2 of 10 PA-28R-201T Turbo Arrow III 28R-7703001 through 28R-7803374; 2803001 through 2803012 PA-28RT-201 Arrow IV 28R-7918001 through 28R-8218026 PA-28RT-201T Turbo Arrow IV 28R-7931001 through 28R-8631005; 2831001 through 2831038 PA-32-260 Cherokee Six 32-03; 32-04; 32-1 through 32-1297; 32-7100001 through 32-7800008 PA-32-300 Cherokee Six 300 32-15; 32-21; 32-40000 through 32-40974; 32-7140001 through 32-7940290 PA-32R-300 Lance 32R-7680001 through 32R-7880068 PA-32RT-300 Lance II 32R-7885002 through 32R-7985106 PA-32RT-300T Turbo Lance II 32R-7787001; 32R-7887002 through 32R-7987126 PA-32R-301 Saratoga SP 32R-8013001 through 32R-8613006; 3213001 through 3213028; 3213030 through 3213041 PA-32R-301 Saratoga II HP 3213029; 3213042 through 3213103; 3246001 through 3246244 PA-32R-301T Turbo Saratoga SP 32R-8029001 through 32R-8629008; 3229001 through 3229003 PA-32-301 Saratoga 32-8006002 through 32-8606023; 3206001 through 3206019; 3206042 through 3206044; 3206047; 3206050 through 3206055; 3206060 PA-32-301T Turbo Saratoga 32-8024001 through 32-8424002 PA-32R-301T Saratoga II TC 3257001 through 3257483 PA-32-301FT Piper 6X 3232001 through 3232074 PA-32-301XTC Piper 6XT 3255001 through 3255027; 3255051 PA-34-200 Seneca 34-E4; 34-7250001 through 34-7450220 PA-34-200T Seneca II 34-7570001 through 34-8170092 PA-34-220T Seneca III 34-8133001 through 34-8633031; 3433001 through 3433172; 3448001 through 3448037 PA-34-220T Seneca IV 3448038 through 3448079; 3447001 through 3447029 PA-34-220T Seneca V 3449001 through 3449514 PA-44-180 Seminole 44-7995001 through 44-8195026; 4495001 through 4495013; 4496001 through 4496524 PA-44-180T Seminole 44-8107001 through 44-8207020 COMPLIANCE TIME: Part I. Inspection For aircraft with 3,500 or more hours time in service (TIS), initial compliance is to occur within the next 100 hours TIS. Thereafter, a recurring inspection shall occur every 100 hours TIS, until compliance with Part II has been accomplished. NOTE: Modification of the tee bar assembly as described in Part II, or installation of a replacement tee bar assembly with the features shown in Figure 1, Detail B, will relieve the recurring inspection requirement in Part I. Part II. Replacement Compliance is to occur, if cracks are found, prior to next flight. Otherwise, at owner/ operator discretion, compliance with Part II will relieve the recurring inspection requirements described in Part I. APPROVAL: The engineering aspects of this service document have been shown to comply with the applicable Federal Aviation Regulations and are FAA approved. SERVICE BULLETIN NO. 1355A PAGE 3 of 10 PURPOSE: A review of service history reveals that cracks may develop in the tee bar assembly of the affected aircraft. This service bulletin provides instructions for the recurring inspection of the tee bar assembly for cracks. Replacement of the installed tee bar weldment assembly with the applicable new tee bar weldment assembly specified in Table 1 will eliminate the need for a recurring inspection. INSTRUCTIONS: NOTES: • The term weldment is defined as “a unit formed by welding together an assembly of pieces.” A tee bar weldment is the welded metal assembly that is a portion of the complete tee bar assembly (see Figure 1). • Temporary removal of some interior components and/or access panels may be required in order to accomplish the instructions described in this service bulletin. • Prior to inspection, wipe surfaces clean using a soft cloth dampened with isopropyl alcohol, mineral spirits, naphtha, or other suitable cleaning agent. • The inspections described in this service bulletin shall be accomplished using a 10X magnifier, a mirror and a suitable light source or other equipment capable of providing equal or better resolution. Part I. Inspection WARNING: FLIGHT WITH KNOWN CRACKS IN THE AIRCRAFT STRUCTURE IS NOT ALLOWED. AN AIRPLANE WITH A CRACK IN STRUCTURE MAY NO LONGER MEET ITS TYPE DESIGN AND MAY NO LONGER POSSESS ITS TYPE DESIGN STRENGTH. ANY CRACKS DISCOVERED IN THE AIRCRAFT STRUCTURE MUST BE REPAIRED PRIOR TO THE NEXT FLIGHT.

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1. Gain visual access to the top center portion of the tee bar assembly, as shown in Figure 1. Identify the configuration of the tee bar weldment assembly. • If the local area conforms to Figure 1, Detail A, then recurring inspections are required. Proceed to Step 2. • If the local area conforms to Figure 1, Detail B, then the factory original tee bar assembly has already been replaced with a tee bar assembly containing the required features (i.e., gusset) and is already in compliance with Part II. Therefore, no recurring inspections are required. Proceed to Part II, Step 8. 2. Examine the area shown in Detail A for cracks, with special emphasis on welded joints. NOTE: For inspection and paint guidance, refer to FAA Advisory Circular AC 43.13-1B, “Acceptable Methods, Techniques, and Practices – Aircraft Inspection and Repair.” This free document is available for download from the FAA at https://www.faa.gov/regulations_policies/advisory_circulars/. a. If the paint is cracked, chipped or peeled in the vicinity of the inspection areas, or if there is evidence of corrosion (such as staining or blistering), then a fluorescent penetrant inspection is required as described in Step b, below. Prepare the surface by removing the paint using Cee-Bee A-202 paint stripper, or an equivalent. Wipe off any residue, in the areas where the paint was removed, with isopropyl alcohol. NOTE: Paint must be removed using chemical processes only. The use of abrasives or other mechanical methods to remove the paint will hide the existence of any discontinuities, making an accurate inspection impossible. NOTE: Follow the paint stripper manufacturer’s instructions, including the use of proper ventilation, and/ or the use of personal protective equipment (PPE), as applicable. b. Perform a fluorescent dye penetrant inspection per FAA Advisory Circular AC 43.13-1B, Chapter 5, Section 5. • If any cracks are discovered, then the tee bar weldment must be replaced prior to next flight. Proceed to Part II. • If no cracks are discovered, apply primer and topcoat to bare metal, per the applicable Piper Airplane Maintenance Manual (AMM) or Service Manual (SM) and FAA Advisory Circular AC 43.13-1B, Chapter 6. Proceed to Step 3. 3. Perform a functional check on any systems that were disturbed during this inspection. 4. Make a logbook entry documenting compliance with Part I of this service bulletin. SERVICE BULLETIN NO. 1355A PAGE 4 of 10 Part II. Replacement 1. Order and install one (1) each, of the applicable tee bar weldment assembly, per Table 1. 2. To replace the tee bar weldment assembly, first, in accordance with Section 27-10-00 of the applicable Piper AMM or Section V of the applicable SM, remove the control wheels and the control column tee bar assembly from the aircraft. 3. Remove all sprockets, the control wheel columns, and hardware (bolts, nuts, washers) from the tee bar weldment assembly and retain them for reinstallation. Replace any hardware on condition. 4. Assemble the control wheel tee bar assembly (refer to Figure 2): Install the sprockets, control wheel columns, and hardware, which were removed from the original weldment assembly in the previous step, onto the replacement tee bar weldment assembly. 5. Reinstall the control column tee bar assembly and control wheel columns, in accordance with Section 27-10-00 of the applicable Piper AMM or Section V of the applicable SM. If necessary, so that there is no greater than 0.010 in. of free play (relative motion) and no drag exists between the control columns and sprocket assemblies, add Brass Shims, Piper P/N 62833-152, no more than two (2) per side, as shown in Figure 3. 6. Reinstall the control wheels in accordance with Section 27-10-00 of the applicable Piper AMM or Section V of the applicable SM. 7. Perform a functional check on any systems that were disturbed to gain access for, and during, this modification. 8. Make a logbook entry documenting compliance with Part II of this service bulletin. SERVICE BULLETIN NO. 1355A PAGE 5 of 10 Figure 1 Tee Bar Assembly – Weldment DETAIL A DETAIL B TEE BAR ASSEMBLY LOOKING FORWARD SOME COMPONENTS REMOVED FOR CLARITY FWD UP TEE BAR WELDMENT DETAIL A LOOKING FORWARD AT CONTROL COLUMN TEE BAR WELDMENT WITHOUT GUSSET UP DETAIL B LOOKING FORWARD AT CONTROL COLUMN TEE BAR WELDMENT WITH GUSSET UP SERVICE BULLETIN NO. 1355A PAGE 6 of 10 Figure 2 Tee Bar Assembly – Weldment Assembly Installation BEARING P/N 542-372 (2 EACH) CONTROL COLUMN ASSEMBLY (REF) TEE BAR WELDMENT FWD UP BEARING P/N 452-389 (4 EACH) TEE BAR ASSEMBLY P/N 28F40A003-001 SHOWN (OTHERS ARE SIMILAR) EXPLODED VIEW (TYPICAL) SOME COMPONENTS REMOVED FOR CLARITY NOTE: Tee Bar Weldment Assembly P/N 28F40A003-xxx components are shown in blue. BEARING P/N 452-388 (2 EACH) SERVICE BULLETIN NO. 1355A PAGE 7 of 10 FWD UP BRASS SHIMS (SEE NOTE) CONTROL COLUMN ASSEMBLY – TYPICAL LOOKING OUTBOARD PILOT SIDE SHOWN (COPILOT SIDE SIMILAR) NOTE: Brass Shims P/N 62833-152 may be added between the control column assembly and sprocket assembly, so that free play is no greater than 0.010 in. and no drag exists. SHAFT ASSEMBLY SPROCKET ASSEMBLY BEARING AILERON CONTROL SPROCKET SHAFT UNIVERSAL (FLEX) JOINT Figure 3 Brass Shim P/N 62833-152 Installation Location SERVICE BULLETIN NO. 1355A PAGE 8 of 10 TABLE 1 TEE BAR WELDMENT ASSEMBLY REPLACEMENT PARTS MODEL NUMBER EFFECTIVITY ASSEMBLY P/N 28F40A003 “DASH” PA-28-140 28-20002 through 28-21445 702 28-21446 through 28-21845, 28-21931 through 28-21934, 28-23242 through 28-26956; 28-7125001 through 28-7725290 703 28-21846 through 28-21930, 28-21935 through 28-23241 707 PA-28-150 28-1231 through 28-2977 702 28-2978 through 28-3377, 28-4118 through 28-4377 703 28-1 through 28-1230 705 28-3378 through 28-4117 707 PA-28-151 28-7415001 through 28-7715314 703 PA-28-160 28-1231 through 28-2977 702 28-2978 through 28-3377, 28-4118 through 28-4377 703 28-1 through 28-1230 705 28-3378 through 28-4117 707 PA-28-161 28-7716002 through 28-8616057; 2816001 through 2816119; 2841001 through 2841365; 2842001 through 2842420 703 PA-28-180 28-1231 through 28-2977 702 28-E13; 28-2978 through 28-3377; 28-4118 through 28-5869; 28-7102001 through 28-7305611; 28-7405001 through 28-7505261 703 28-671 through 28-1230 705 28-3378 through 28-4117 707 PA-28-181 Archer III 28-7690001 through 28-8690056; 2890001 through 2890231; 2843001 through 2843701, 2843703 through 2843942; 2881001 through 2881481 703 PA-28-181 Piper Pilot 100i 28020001 through 28020024 703 PA-28-201T 28-7921001 through 28-7921095 703 PA-28-235 28-10002 through 28-10719 702 28-E11; 28-10944 through 28-11393; 28-7110001 through 28-7710089 703 28-10720 through 28-10943 707 PA-28-236 28-7911001 through 28-8611008; 2811001 through 2811050 703 PA-28R-180 28R-30005 through 28R-30481, 28R-30483 through 28R-31279; 28R-7130001 through 28R-7130029 706 PA-28R-200 28R-30482; 28R,35001 through 28R-35830; 28R-7135001 through 28R- 7635545 706 PA-28R-201 28R-7737002 through 28R-7837317; 2837001 through 2837061; 2844001 through 28444185 706 PA-28R-201T 28R-7703001 through 28R-7803372; 2803001 through 2803015 706 PA-28RT-201 28R-7918001 through 28R-8218026 706 PA-28RT-201T 28R-7931001 through 28R-8631004; 2831001 through 2831038 706 SERVICE BULLETIN NO. 1355A PAGE 9 of 10 MODEL NUMBER EFFECTIVITY ASSEMBLY P/N 28F40A003 “DASH” PA-32-260 32-1 through 32-300 701 32-301 through 32-600 704 32-601 through 32-960 708 32-961 through 32-1320; 32-7100001 through 32-7300076; 32-7400001 through 32-7800008 704 PA-32-300 32-40000 through 32-40415 708 32-40416 through 32-41018; 32-7140001 through 32-7940290 704 PA-32-301 32-8006001 through 32-8606023; 3206001 through 3206098 704 PA-32-301FT 3232001 through 3232074 704 PA-32-301T 32-8024001 through 32-8424002 704 PA-32-301XTC 3255001 through 3255051 704 PA-32R-300 32R-7680001 through 32R-7880068 704 PA-32R-301 32R-8013001 through 32R-8613006; 3213001 through 3213041 704 PA-32R-301HP 3213029, 3213042 through 3213103; 3246001 through 3246244 704 PA-32R-301T 32R-8029001 through 32R-8629008; 3229001 through 3229003 704 PA-32R-301TC 3257001 through 3257493 704 PA-32RT-300 32R-7885002 through 32R-7985106 704 PA-32RT-300T 32R-7787001, 32R-7887002 through 32R-7987126 704 PA-34-200 34-7250001 through 34-7450220 704 PA-34-200T 34-7570002 through 34-8170092 704 PA-34-220T (III, IV, V) 34-8133001 through 34-8633031; 3447001 through 3447029; 3448001 through 3448079; 3449001 through 3449310, 3449312 through 3449322, 3449324, 3449325, 3449410, 3449415 through 3449419, 3449421 through 3449458, 3449460 through 3449466 709 PA-34-220T (V) 3449311, 3449323, 3449326 through 3449409, 3449411 through 3449414, 3449420, 3449459, 3449467 through 3449514 710 PA-44-180 44-7995001 through 44-8195026; 4495001 through 4495013; 4496001 through 4496524 703 PA-44-180T 44-8107001 through 44-8207020 703 TABLE 1 (CONT’D) TEE BAR WELDMENT ASSEMBLY REPLACEMENT PARTS SERVICE BULLETIN NO. 1355A PAGE 10 of 10 MATERIAL REQUIRED: On condition, per aircraft: • One (1) each, the applicable Weldment Assembly, per Table 1 • Up to four (4) each, Brass Shim (0.005 in.), Piper P/N 62833-152 (discard any unused) • 12 each, Locking Clip Turnbuckle, Piper P/N 554-979 (MS21256-1) AVAILABILITY OF PARTS: Your Piper Approved Service Center – Weldment Assembly and Brass Shims; Clip Turnbuckles – procure locally EFFECTIVITY DATE: This service bulletin is effective upon receipt. SUMMARY: 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”

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