SERVICE BULLETIN SB 500-34-005
ECLIPSE EA500 · Service Bulletins
Overview
This service bulletin (SB 500-34-005) addresses the upgrade of the Pitot/Angle-of-Attack (AOA) system for the Eclipse EA500 aircraft. It outlines the mandatory modifications required to eliminate icing issues in the Pitot/AOA system, which can lead to erroneous airspeed and angle-of-attack readings.
- Mandatory modification for aircraft serial numbers 000001 through 000064.
- Upgrade includes new Pitot/AOA probes and tubing assembly with a water trap.
- Current system may lead to icing and inaccurate readings.
- Compliance required within 60 days to remove operational restrictions.
- FAA approved as an alternative method of compliance.
- No weight and balance changes required.
- No electrical load data changes required.
- Interchangeability of parts is not allowed; both probes must be replaced.
Document
Source
Originally published by eclipse.aero. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type ·
- Service Bulletins
- Year ·
- 2007
- File size ·
- 973 KB
- Publisher ·
- eclipse.aero
- Language ·
- en
What is the SERVICE BULLETIN SB 500-34-005?
The SERVICE BULLETIN SB 500-34-005 is a service bulletins for the ECLIPSE EA500, dated 2007.
Where does the SERVICE BULLETIN SB 500-34-005 come from?
This copy of the SERVICE BULLETIN SB 500-34-005 was originally published by eclipse.aero and is hosted on Sprinkle as a free, searchable reference copy.
What year was the SERVICE BULLETIN SB 500-34-005 published?
The SERVICE BULLETIN SB 500-34-005 — the ECLIPSE EA500 service bulletins on file — is dated 2007.
Most owners only have the POH. Here's the essential set for the ECLIPSE EA500.
- Pilot's Operating Handbook / AFM
- Checklist
- Maintenance Manual
- Parts Catalog (IPC)
- Systems & Wiring
- Service Bulletins on file
- Type Certificate (TCDS)
More ECLIPSE EA500manuals & documents
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In this document
Planning Information
Details the effectivity of the service bulletin, reasons for the upgrade, and compliance requirements.
Material Information
Lists required parts, kits, and special tooling needed to accomplish the service bulletin.
Accomplishment Instructions
Provides step-by-step procedures for safely removing and installing the Pitot/AOA assembly.
Warnings and Cautions
Includes important safety warnings and cautions related to the maintenance procedures.
Approval
Confirms FAA approval for the service bulletin as an alternative compliance method.
Relevant Publications
References the Aircraft Maintenance Manual and Aircraft Flight Manual for further guidance.
Safety notes
- Ensure electrical connector is disconnected before applying power to avoid injury.
- Use care when removing tubing to prevent damage to fittings.
- Follow all safety procedures outlined in the Aircraft Maintenance Manual.
Full document text
A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 1 of 19 Form Identification To Be Determined NUMBER: SB 500-34-005 rev B MODEL: Eclipse EA500 SUBJECT: Pitot/Angle-of-Attack (AOA) System Upgrade 1. PLANNING INFORMATION A. Effectivity (1) Aircraft Aircraft Serial Numbers 000001 through 000064. (2) Spares • Pitot/Angle-of-Attack (AOA) probe spares part numbers 100435-23 and 100435-24 must be purged from stock. • Pitot/AOA tubing assembly spares part numbers 34-114372-1002, 34-114373-1002, 34- 114374-1002, 34-114375-1002 must be purged from stock. B. Reason The current Pitot/AOA probes and tubing assembly do not effectively eliminate the formation of ice in the Pitot/AOA system for all combinations of moisture and temperature. This condition can occasionally lead to erroneous angle-of-attack and airspeed information. C. Description This service bulletin (SB) upgrades the Pitot/AOA probes and modifies the related tubing assembly, adding a water trap. The new Pitot/AOA probes and tubing assembly eliminate the possibility of icing in the Pitot/AOA system. D. Relevant Publications Aircraft Maintenance Manual (AMM), P/N 06-117751, latest Rev. Aircraft Flight Manual (AFM), P/N 06-100106, latest Rev. E. Compliance Eclipse Aviation Corporation considers this to be a mandatory modification that must be accomplished within 60 days to remove the operational restrictions referenced in the Temporary Revisions (TR) Number 7 or Number 9 of the Airplane Flight Manual (AFM) P/N 06-100106, Revision 3. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 2 of 19 Form Identification To Be Determined F. Approval This Service Bulletin is FAA Approved by the Manager, Airplane Certification Office, ASW-150, by letter dated July 10, 2007, as an Alternative Method Compliance with AD 2007-13-11, effective date June 27, 2007. Airplanes can be operated in accordance with Airplane Flight Manual Revision 3 or later FAA approved revision after the airplane has been modified in accordance with the information in this Service Bulletin. G. Weight and Balance Change None. H. Electrical Load Data Change None. I. Software Accomplishment Summary Not Applicable. J. References Aircraft Maintenance Manual (AMM), P/N 06-117751, latest Rev. Illustrated Parts Catalog (IPC), P/N 06-117752, latest Rev. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 3 of 19 Form Identification To Be Determined 2. MATERIAL INFORMATION A. Materials The following parts and/or kits are required for this SB. Part Number Description Qty Required 34-121975-1001 Kit contents: 34-114372-1003 34-114373-1003 34-121967-1002 34-121969-1001 34-121971-1002 34-121979-1001 WSI-4-5 AS1035D040404 AS5168D04 CB3001AA3-6P750 CCR274CS-3-021PR MS21919WDG4 MS51859-21 NAS1149D0332J NAS1801-3-5 NAS1801-3-6 NAS1801-3-8 Mod Kit, Installation Pitot System, Cabin Assy Kit contents: Tube Assy – Pitot No. 2 Right Tube Assy – Pitot No. 1 Left Pitot/AOA, Probe to Bulkhead Tube Assy – Trap, Pitot/AOA, Nose LH Tube Assy – Trap, Pitot/AOA, Nose RH Tube Assy – Bulkhead to Tee, Pitot Flange, Support Fitting, Tee, Standard and Reducer, Flared Fitting, Plug, Tube End, Flared Standoff, Locking Thread, Adhesive Bonded Cherry Pull-Thru Rivet, Universal Head Clamp, Loop Type, Cushioned Support Washer, Flat – Plastic (Nylon) Washer, Flat Screw, Hex Head, Cruciform Recess, Full Thread, Alloy Steel, 160,000 PSI Screw, Hex Head, Cruciform Recess, Full Thread, Alloy Steel, 160,000 PSI Screw, Hex Head, Cruciform Recess, Full Thread, Alloy Steel, 160,000 PSI 1 1 1 2 1 1 4 2 4 4 4 4 8 4 8 4 2 2 34-121983-1001 Kit contents: 100435-39 100435-40 Mod Kit, Pitot/AOA Probes, Nose, Instl: Kit contents: Sensor, Pitot AOA, W-Drain and Female AN Fitting, Left Sensor, Pitot AOA, W-Drain and Female AN Fitting, Right 1 1 1 PFE50-1501 Drawing for Blankets, Fwd Bulkhead 1 A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 4 of 19 Form Identification To Be Determined B. Tooling The following special tooling/support equipment is required to accomplish this SB. Nomenclature Part Number Use Ground Power Unit (GPU) Allstar 450, AllStar G.S.E., Hobart GPU- 400, Hobart GPU-600, Bycan PS-28100, or equivalent Supplies electrical power to airplane. Thermocouple Thermometer Fluke 52 II or equivalent Checks Pitot/AOA probe temperature. Air Data Test Set Barfield DPS450 or Barfield DPS500 Checks integrity of Pitot/AOA system. Air Data Accessories Kit ADA500945 Contains parts necessary to interface air data test set with aircraft Pitot/AOA system. Avio Maintenance Computer (AMC) EAC 20-120576-1001 Simulates Weight-on-Wheels (WOW) and adjusts Vapor Cycle System (VCS) doors. USB to Ethernet adapter SMC2209 Serves as interface to connect Ethernet cable to copilot’s arm rest Ethernet Crossover Cable EAC 87-120877-1001 Connects AMC to aircraft. C. Interchangeability/Intermixability of Parts None. Both Pitot/AOA probes must be replaced when performing this SB. D. Part Re-identification None. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 5 of 19 Form Identification To Be Determined 3. ACCOMPLISHMENT INSTRUCTIONS A. Procedure (1) Make aircraft safe for maintenance. Refer to AMM 20-00-01-051-921-001. (2) Apply power to aircraft. Refer to AMM 24-40-00-051-921-001. (3) Prepare the aircraft for removal and installation of Pitot/AOA assembly as follows (Refer to Figure 1): (a) On the MFD ENVIR synoptic page, select and check the display for: • AIR COND: OFF (6) • DEFOG: OFF (7) • FWD Fan: OFF (5) • AFT Fan: OFF (4) (b) On the MFD ENVIR synoptic page, select and check AIR COND: AUTO, then establish the following conditions: • AFT Fans: AUTO • FWD Fans: AUTO • Cockpit Temp: MAX COOL • Cabin Temp: MAX COOL (c) Make sure the Vapor Cycle System (VCS) forward door (16) and aft door (10) are fully open. (d) Power down the aircraft by setting the SYS BATT switch (3) and START BATT switch (1)
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to OFF, and the BUS TIE switch (2) to OPEN. WARNING: MAKE SURE FOLLOWING STEP IS DONE. IF ELECTRICAL CONNECTOR STAYS CONNECTED AND POWER IS APPLIED, AFT VCS DOOR WILL CLOSE AND MAY CAUSE INJURY. (e) Disconnect electrical connector (15) from aft VCS actuator (9). (f) Remove bolt (14), washer (13), nut (12), and cotter pin (11) to disconnect VCS actuator (9) from aft VCS (outlet) door (10). (g) Remove nose access panel 211 CT (22). Refer to AMM 06-50-00-051-A-871-001. (h) Remove pilot seat (18) and copilot seat (17). Refer to AMM 25-11-10-001-011-001. (i) Remove right center console kick panel 222 FZ (19) and left center console kick panel 221 FZ (20). Refer to AMM 06-50-00-051-A-871-001. (j) Remove insulation blankets from forward bulkhead. Refer to AMM 25-80-10-001-011-001. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 6 of 19 Form Identification To Be Determined Figure 1. Initial Set-Up Before Removal and Installation of Pitot/AOA Assembly (Sheet 1 of 4) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 7 of 19 Form Identification To Be Determined Figure 2. Initial Set-Up Before Removal and Installation of Pitot/AOA Assembly (Sheet 2 of 4) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 8 of 19 Form Identification To Be Determined Figure 3. Initial Set-Up Before Removal and Installation of Pitot/AOA Assembly (Sheet 3 of 4) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 9 of 19 Form Identification To Be Determined Figure 4. Initial Set-Up Before Removal and Installation of Pitot/AOA Assembly (Sheet 4of 4) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 10 of 19 Form Identification To Be Determined Note: Removal of the Pitot/AOA assembly is the same for both sides with the exception of accessibility. Access to the right AOA/Pitot probe assembly is obtained through the aft VCS (outlet) door (10). Access to the left Pitot/AOA probe is obtained through Oxygen Bottle cover 211 JZ (21). (4) Remove left Pitot/AOA probe and tubing assembly as follows (Refer to Figure 2): (a) Disconnect electrical connector (1) from Pitot/AOA probe P/N 100435-23 (4). (b) Disconnect tubing assembly P/N 34-114375-1002 (5) from Pitot/AOA probe (4). CAUTION: MAKE SURE TO USE CARE WHEN REMOVING TUBING FROM BULKHEAD ELBOW FITTING P/N AS1038D0404 (8). FAILURE TO USE CARE CAN RESULT IN DAMAGE TO FITTING. (c) Disconnect and remove tubing assembly P/N 34-114375-1002 (5) from bulkhead elbow fitting P/N AS1038D0404 (8). (d) Remove screw P/N NAS1801-3-8 (12), washer P/N NAS1149D0732J, and clamp P/N MS21919WDG4 (11) from rudder pedal mount. (e) Disconnect tubing assembly P/N 34-114373-1002 (10) from Air Data Computer (ADC) 1 (9). CAUTION: MAKE SURE TO USE CARE WHEN REMOVING TUBING FROM BULKHEAD ELBOW FITTING P/N AS1038D0404 (8). FAILURE TO USE CARE CAN RESULT IN DAMAGE TO FITTING. (f) Disconnect and remove tubing assembly P/N 34-114373-1002 (10) from bulkhead elbow fitting P/N AS1038D0404 (8). CAUTION: MAKE SURE TO USE CARE WHEN REMOVING BULKHEAD ELBOW FITTING P/N AS1038D0404 (8) AND BULKHEAD NUT FITTING P/N AS5178D04 (6). FAILURE TO USE CARE CAN RESULT IN DAMAGE TO FITTINGS. (g) Remove bulkhead nut fitting P/N AS5178D04 (6) and bulkhead elbow fitting P/N AS1038D0404 (8) from forward bulkhead (7). Keep bulkhead nut and elbow fittings. (h) Remove screws P/N NAS8702-2 (3) and Pitot/AOA probe P/N 100435-23 (4). (5) Repeat step 4 to remove right Pitot/AOA probe and tubing assembly. Refer to drawings 34- 121975-1001 and 34-121983-1001 for correct P/N removal. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 11 of 19 Form Identification To Be Determined Figure 2. Pitot/AOA Assembly Removal (Sheet 1 of 2) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 12 of 19 Form Identification To Be Determined Figure 2. Pitot/AOA Assembly Removal (Sheet 2 of 2) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 13 of 19 Form Identification To Be Determined (6) Install left Pitot/AOA probe and tubing assembly as follows (Refer to Figure 3): (a) Loosely install bulkhead nut fitting P/N AS5178D04 (5), two nylon washers P/N MS51859-21 (6, 8), and bulkhead elbow fitting P/N AS1038D0404 (9). Note: Make sure arrow displayed on tubing P/N 34-121967-1002 (14) points towards the ADC and the arrow displayed on tubing P/N 34-121969-1001 (12) points toward the drain. (b) Loosely connect tubing P/N 34-121967-1002 (14) and tubing P/N 34-121969-1001 (12) to tee P/N AS1035D040404 (13). (c) Connect and secure tubing P/N 34-121967-1002 (14) to bulkhead elbow fitting P/N AS1038D0404 (9). (d) Install Pitot/AOA probe P/N 100435-39 (4) with screws P/N NAS3702-2 (3). (e) Do electrical bonding of Pitot/AOA probe (4) to aircraft. Refer to AMM 20-03-00. Resistance must be 2.5 milliohms or less. (f) Connect electrical connector (1) to Pitot/AOA probe P/N 100435-39 (4). (g) Connect tee P/N AS1035D040404 (13) to Pitot/AOA probe P/N 100435-39 (4). (h) Torque the following connections. Refer to EAC P1020. 1. Tubing P/N 34-121967-1002 (14) and tubing P/N 34-121969-1001 (12) to tee P/N AS1035D040404 (13). 2. Tee P/N AS1035D040404 (13) to Pitot/AOA probe P/N 100435-39 (4). (i) Install standoff P/N CB3001AA3-6P for clamp MS21919WDG4 (11). Refer to sheet 2, section H-H of drawing 34-121975-1001. (j) Install clamp P/N MS21919WDG4 (11). Refer to sheet 2, section H-H of drawing 34- 121975-1001. (k) Secure tubing P/N 34-121969-1001 (12) to clamp P/N MS21919WDG4 (11). (l) Install plug fitting P/N AS516D04 (10) into tubing P/N 34-121969-1001 (12). (m) Loosely connect tubing P/N 34-121979-1001 (16) to bulkhead elbow fitting P/N AS13038D0404 (11). (n) Loosely connect tubing P/N 34-114373-1003 (18) and tubing P/N 34-121979-1001 (20) to tee P/N AS1035D040404. (o) Loosely connect tubing P/N 34-114373-1003 (18) to ADC 1 (15). (p) Torque the following connections. Refer to EAC P1020. 1. Tubing P/N 34-121979-1001 (20) and tubing P/N 34-114373-1003 (18) to tee P/N AS1035D040404 (19). 2. Tubing P/N 34-114373-1003 (18) to ADC 1. 3. Bulkhead elbow fitting P/N AS13038D0404 (9) and bulkhead nut fitting P/N AS5178D04 (5). (q) Install standoffs P/N CB3001AA3-6P for clamps MS21919WDG4 (15, 17). Refer to sheet 2, section A-A and section B-B of drawing 34-121975-1001. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 14 of 19 Form Identification To Be Determined Figure 3. Pitot/AOA Assembly Installation (Sheet 1 of 2) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 15 of 19 Form Identification To Be Determined Figure 3. Pitot/AOA Assembly Installation (Sheet 2 of 2) A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 16 of 19 Form Identification To Be Determined Note: Existing standoff P/N CB3001AA3-6P for clamp P/N MS21919WDG4 (24) may have to be moved in order to clamp tubing correctly. Refer to sheet 2, section B- B of drawing 34-121975-1001. (r) Install clamps P/N MS21919WDG4 (15, 17, 24). Refer to sheet 2, section A-A and section B-B of drawing 34-121975-1001. (s) Secure tubing P/N 34-114373-1003 (12) to clamps P/N MS21919WDG4 (17, 24). (t) Secure tubing P/N 34-121979-1001 (20) to clamp P/N MS21919WDG4 (15). (u) Install plug fitting P/N AS516D04 (21) into tubing P/N 34-121979-1001 (20). (7) Repeat step 6 to install right Pitot/AOA probe and tubing assembly. Refer to drawings 34- 121975-1001 and 34-121983-1001 for correct P/N installation. (8) Do a Pitot and Static System Leak Test for Un-pressurized Airplanes. Refer to AMM 34-10-00- 071-701-001. (9) Do an Angle-of-Attack Test. Refer to AMM 34-10-00-071-701-004. (10) Do a Pitot and Static Anti-ice System test. Refer to AMM 30-30-00-071-701-001. WARNING: MAKE SURE ELECTRICAL POWER IS NOT APPLIED BEFORE DOING NEXT STEP. IF ELECTRICAL CONNECTOR IS CONNECTED WHILE POWER IS APPLIED, AFT VCS DOOR WILL CLOSE AND MAY CAUSE INJURY. (11) Connect VCS actuator (9, Figure1) to door (10, Figure 1). (12) Connect electrical connector (15, Figure 1) to VCS actuator (9, Figure 1). (13) Do a VCS doors adjustment/test. Refer to AMM 21-10-10-071-921-001. (14) Modify insulation blankets. Refer to drawing PRE50-1501. (15) Attach insulation blankets. Refer to AMM 25-80-10-041-411-001. (16) Install right center console kick panel 222 FZ and left center console kick panel 221 FZ. Refer to AMM 06-50-00-051-A-871-001. (17) Install pilot and copilot seats. Refer to AMM 25-11-10-041-411-001. (18) Install oxygen bottle cover 211 JZ and nose access panel 211CT. Refer to AMM 06-50-00- 051-A-871-001. (19) Remove all tools, equipment, and unwanted material from work area. (20) If all other maintenance is complete, return aircraft to service. Refer to AMM 20-00-02-051- 921-001. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 17 of 19 Form Identification To Be Determined B. Limitations and Procedures Both Pitot/AOA probes P/N 100435-39 and P/N 100435-40 must be installed with new tubing assembly referenced in this service bulletin (SB). Replace the existing LOG OF TEMPORARY REVISIONS (Page LOTR-1) of the AFM with the new one supplied as Attachment A of this SB. Eclipse Aviation Corporation considers this to be a mandatory modification that must be accomplished within 60 days to remove the operational restrictions referenced in the Temporary Revisions (TR) Number 7 or Number 9 of the Airplane Flight Manual (AFM) P/N 06-100106, Revision 3. C. Cost Cost of Parts and Labor will be the responsibility of Eclipse Aviation Corporation after obtaining concurrence from Eclipse Aviation Product Support for Scheduling. A L E R T SERVICE BULLETIN SB 500-34-005 Issued: 10 July 2007 — Rev B 18 of 19 Form Identification To Be Determined 4. RECORD OF COMPLIANCE Upon completion of this SB, make an appropriate maintenance-record entry specifying the SB number (including kit part number and serial number, if applicable). Eclipse Aviation Corporation recommends that parts lists associated with any of the following installed as part of this SB also be filed for future reference: • kits, • wiring diagrams, or • Instructions for Continued Airworthiness (ICA) 5. NOTIFYING ECLIPSE AVIATION On completing this SB, the operator/maintainer shall complete the attached Compliance Record and send it to Eclipse Aviation via regular mail, fax, or e-mail. Mailing Address: Eclipse Aviation Corporation ATTN: Customer Care 2503 Clark Carr Loop SE Albuquerque, NM 87106 Fax: 1-505-241-8802 E-mail: customercare@EclipseAviation.com SERVICE BULLETIN COMPLIANCE RECORD SB 500-34-005 rev B: Pitot/Angle-of-Attack(AOA) System Upgrade MODEL _____________ AIRPLANE S /N __________ REG. NO . ___________ TOTAL TIME ______ ( HOURS) OWNER NAME : ______________________________________________________________________ ADDRESS : ______________________________________________________________________ ______________________________________________________________________ TELEPHONE NO. (XXX) ____________________________ FAX NO . (XXX) ________________________ COMPLIANCE WITH SB 500-34-005 REV B Description of Work Performed (Inspection | Modification | Repair | Option Installation | Defect or Damage Found, if applicable) ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ ___________________________________________________________________________________ DATE _______________ WORK PERFORMED BY ____________________________________________________________ ( PRINTED) WORK PERFORMED BY __________________________________________________________ ( SIGNATURE ) COMPANY __________________________________________________________ ADDRESS __________________________________________________________ ADDRESS __________________________________________________________ TELEPHONE ___________________ FAX ____________________