SERVICE BULLETIN - Plane-Power | Alternators
CESSNA 310Q · Service Bulletins
Overview
This Service Bulletin No. 209 addresses the inspection of alternator mounting brackets for specific alternators installed on various Cessna aircraft models, including the Cessna 185. It outlines the affected part numbers, the reason for the bulletin, and the compliance requirements for aircraft owners and operators. The bulletin emphasizes the importance of using the most recent revision for safety and compliance, detailing the steps necessary for inspection and corrective actions if issues are found. It is crucial for maintenance personnel to follow the instructions carefully to ensure airworthiness and safety.
- Affected alternator part numbers include 10-1050, AL12-50C, and others.
- Compliance with inspection is required at the next scheduled or annual inspection.
- Inspect for stress cracks in the alternator mounting bracket P/N 10-9003.
- Gaps between the alternator mounting bracket and spacers must be ≤ 0.007 inches.
- Contact Hartzell Engine Technologies for technical support regarding this bulletin.
Document
Source
Originally published by planepower.aero. Sprinkle hosts a reference copy with an added summary, specifications and searchable full text.
Document details
- Type
- Service Bulletins
- Year
- 2024
- Pages
- 8
- File size
- 837 KB
- Publisher
- planepower.aero
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In this document
Planning Information
The bulletin identifies affected alternator part numbers and the corresponding mounting kits. It specifies that alternators P/Ns 10-1050, AL12-50C, 10-1050C, SAL12-70C, 10-5050C, and TAL24-70C are impacted, particularly when installed with specific mounting kits. Affected aircraft models include various Cessna models such as the 185, 182, and 206.
Compliance
Compliance with the inspection requirements is mandatory at the next scheduled aircraft inspection or at the next annual inspection, whichever comes first. This ensures that any potential issues with the alternator mounting bracket are addressed promptly.
Inspection Procedure
The inspection involves verifying the alternator and mounting bracket part numbers and checking for stress cracks in the mounting bracket. If cracks are found, the bulletin provides guidance on obtaining replacements and performing corrective actions. Specific measurements, such as ensuring gaps do not exceed 0.007 inches, are critical during the inspection.
Corrective Action
If the alternator mounting bracket is found to be cracked or if the gap exceeds the specified measurement, corrective actions must be taken. This includes installing shims to achieve the required alignment and ensuring that all components are properly torqued and secured.
Contact Information
For further assistance regarding this Service Bulletin, contact Hartzell Engine Technologies Product Support via phone, fax, or email. The bulletin provides specific contact details for technical support.
Safety notes
- Perform all inspections in accordance with the most recent revision of this Service Bulletin to avoid unsafe conditions.
- Use of obsolete information may result in serious injury or property damage.
Full document text
SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection Rev. New: 04 Oct. 2024 SB 209 © 2024 - Hartzell Engine Tech - All rights reserved Page 1 of 8 2900 Selma Highway M ontgomery, AL 3 6 108 USA Tel: 3 3 4-386-5400 F ax: 3 3 4-386-5450 1. Planning Information A. Effectivity (1) Plane Power alternator P/Ns 10-1050 or AL12-50C, 10-1050C or SAL12-70C, and 10-5050C or TAL24-70C are affected by this Service Bulletin (SB). (a) Alternator P/Ns 10-1050 or AL12-50C installed with mounting kit P/N 10-9099 are affected by this SB. (b) Alternator P/Ns 10-1050C or SAL12-70C installed with mounting kit P/N 10-9099 are affected by this SB. (c) Alternator P/Ns 10-5050C or TAL24-70C installed with mounting kit P/N 10-9099A are affected by this SB. (2) Alternators, mounting kits, and aircraft model/series affected by this SB are shown in Table 1. NOTE: Table 1 is for reference only and is not an all-inclusive list of aircraft affected by this SB. It is the responsibility of the owner/operator to verify whether an affected alternator and mounting kit may be installed. WARNING: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS SERVICE BULLETIN. INFORMATION CONTAINED HEREIN MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH THIS SERVICE BULLETIN OR THE USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. REFER TO THE PLANE-POWER WEBSITE, WWW.PLANEPOWER.AERO, FOR THE MOST RECENT REVISION LEVEL OF THIS SERVICE BULLETIN. B. Concurrent Requirements (1) None C. Reason (1) Installed alternators mounting kits listed in section 1.A could contain a cracked alternator mounting bracket P/N 10-9003 due to non-shimmed gaps between the alternator and alternator mounting bracket ears. (2) This SB is to advise the field of a potential condition and to supply inspection criteria to identify affected alternators using alternator mounting bracket P/N 10-9003. SB 209 Rev. New: 04 Oct. 2024 Page 2 of 8 © 2024 - Hartzell Engine Tech - All rights reserved SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection Alternator P/N * Mounting Kit P/N** Aircraft Make Aircraft Model/Series 10-1050 - OR - AL12-50C 10-9099 Kit with Bracket P/N 10-9003 Cessna Aircraft Corporation 182, A, B, C, D, E, F, G, 210, A, B, 210-5 (205), 185, A) (185B, C, 180, A, B, C, D, E, F, G, 206, P206) Lockheed Martin Aeronautics Company 402-2 Sierra Hotel Aero Inc. Navion D, E, F, G Interceptor Aircraft Corporation 200, A, B, C, D Textron Aviation Inc. H35, J35, K35, M35, N35, P35, 35-33, 35-A33, 35- B33, 35-C33, 35, A35, B35, C35, D35, E35, F35, G35, 35R 10-1050C - OR - SAL12-70C 10-9099 Kit with Bracket P/N 10-9003 Bellanca Aircraft, Inc. 14-19-2, 14-19-3, 14-19-3A with STC SA10682SC installed) Textron Aviation Inc. 35, A35, B35, C35, D35, E35, F35, G35, 35R, with STC SA10682SC installed, and modified by STC con- version to O-470 or IO-470, H35, J35, K35, M35, N35, P35, 35-33, -A33, -B33, -C33 with STC SA10682SC installed, 180, A, B, C, D, E, F, G, 182, A, B, C, D, E, F, G, H, 185, A, B, C, D, 210, A, 210-5 (205), -5A (205A), 206, P206 with STC SA10682SC installed Interceptor Aircraft Inc. 200, A, B, C, D with STC SA10682SC installed Sierra Hotel Aero Inc. Navion A, B, D, E, F, G, H, (L-17A & L-17B), with STC SA10682SC installed, and modified by STC conver- sion to O-470 or IO-470 Lockheed Martin Aeronautics Company 402-2 with STC SA10682SC installed 10-5050C - OR - TAL24-70C 10-9099A Kit with Bracket P/N 10-9003 Textron Aviation Inc. 95-55, -A55, -B55, -B55A with STC SA10682SC in- stalled, 310, A (USAF U-3A), B, C, D, E (USAF U-3B), F, G, H, I, J, K with STC SA10682SC installed Fred Garcia 480 with STC SA10682SC installed Twin Commander Aircraft LLC 500A with STC SA10682SC installed Table 1 - Aircraft Effectivity * Either of the two P/Ns listed may be found on the alternator datatag ** See Fig. 1 for bracket P/N 10-9003 location Rev. New: 04 Oct. 2024 SB 209 © 2024- Hartzell Engine Tech - All rights reserved Page 3 of 8 SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection D. Description (1) This Service Bulletin provides Instructions for Continued Airworthiness (ICA). E. Compliance (1) Compliance with section 3.A of this SB is required at the next scheduled aircraft inspection from the release date of this SB or at the next annual aircraft inspection, whichever occurs first. (2) Compliance with the Accomplishment Instructions is the terminating action for this SB. F. Approval (1) FAA acceptance has been obtained on the technical data in this publication that affects type design. G. Manpower (1) Up to one (1.0) hours labor for alternator mounting bracket removal and installation, includes installation of shim. H. References (1) Applicable Aircraft Service Instructions or Maintenance Manual (2) Applicable Aircraft AFM or POH (3) HET 14-2001 - TAL24-7OC Installation Instructions (4) HET 10-9001 - AL12-50C Installation Instructions (5) HET 14-6001 - SAL12-7OC Installation Instructions I. Weight and Balance (1) No Change 2. Materials Required A. If required in accordance with Section 2.A. Inspection, or Section 3.B. Corrective Action (1) Lock-Nut (2) .032” safety wire SB 209 Rev. New: 04 Oct. 2024 Page 4 of 8 © 2024 - Hartzell Engine Tech - All rights reserved SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection Inspection Area Figure 1 - Alternator Mounting Bracket Inspection Area 10-9003 Typical Bracket P/N Location Cut Edge* Alternator Mounting Bracket Ears * Linear machining marks may be visible on the cut edge of the alternator mounting bracket/ears. They do not represent cracks. Rev. New: 04 Oct. 2024 SB 209 © 2024- Hartzell Engine Tech - All rights reserved Page 5 of 8 SERVICE B ULLETIN SERVICE BULLETIN No. 209
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Alternator Mounting Bracket Inspection 3. Accomplishment Instructions WARNING 1: THIS PROCEDURE MUST BE PERFORMED BY COMPETENT AND QUALIFIED PERSONNEL WHO ARE FAMILIAR WITH THE AIRFRAME AND ENGINE SYSTEM MAINTENANCE. FAILURE TO DO SO MAY RESULT IN PHYSICAL INJURY, EQUIPMENT DAMAGE AND/OR ECONOMIC LOSS. WARNING 2: DO NOT USE OBSOLETE OR OUTDATED INFORMATION. PERFORM ALL INSPECTIONS OR WORK IN ACCORDANCE WITH THE MOST RECENT REVISION OF THIS SERVICE BULLETIN. INFORMATION CONTAINED HEREIN MAY BE SIGNIFICANTLY CHANGED FROM EARLIER REVISIONS. FAILURE TO COMPLY WITH THIS SERVICE BULLETIN OR THE USE OF OBSOLETE INFORMATION MAY CREATE AN UNSAFE CONDITION THAT MAY RESULT IN DEATH, SERIOUS BODILY INJURY, AND/OR SUBSTANTIAL PROPERTY DAMAGE. REFER TO THE PLANE-POWER WEBSITE FOR THE MOST RECENT REVISION LEVEL OF THIS SERVICE BULLETIN, WWW.PLANEPOWER.AERO. CAUTION: REFER TO THE APPLICABLE MANUFACTURER’S MAINTENANCE MANUALS O R S E R V I C E I N S T R U C T I O N S T O G A I N A C C E S S T O T H E A I R F R A M E O R ALTERNATOR. IN ADDITION, ANY PREFLIGHT OR IN-FLIGHT OPERATIONAL CHECKS REQUIRE USE OF THE APPROPRIATE AFM OR POH. A. Inspection (1) If previous compliance cannot be verified through aircraft or engine maintenance records, use the same references to determine if an affected alternator has been installed. Refer to section 1.A, Effectivity. (2) If effectivity of the alternator cannot be established using aircraft or engine maintenance records, utilize the applicable aircraft engine maintenance manual to gain access to the alternator and inspect the alternator and alternator mounting bracket against criteria found in section 1.A of this SB. (a) If the alternator is affected per section 1.A and alternator mounting bracket P/N 10-9003 is installed (Fig. 1), inspect the alternator mounting bracket ears for stress cracks. See Fig. 1, Inspection Area. NOTE: Linear machining marks may be visible on the cut edge of the alternator mounting bracket/ears. They do not represent cracks. 1) If the alternator mounting bracket is cracked, contact HET Product Support for assistance in obtaining a new alternator mounting bracket and shims and continue to 3.B, corrective action. SB 209 Rev. New: 04 Oct. 2024 Page 6 of 8 © 2024 - Hartzell Engine Tech - All rights reserved SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection 2) If the alternator mounting bracket is not cracked, see Fig. 2 for the following: a) Loosen the tension-arm bolt (5) holding belt tension. b) Loosen the bracket-ear/arm bolt (3). NOTE: The Alternator, tension arm, and bracket arm should be in a free state. c) Align the alternator and spacers (1) & (2) to one side of the alternator mounting bracket. d) Use a feeler gauge and inspect the gap between the alternator mounting bracket ear and spacer. e) Record gap measurement. 1: The measured gap should be ≤ 0.007. 2: If the measured gap is not ≤ 0.007, continue to 3.B, Corrective Action. 3: If the measured gap is ≤ 0.007, perform the following: a: Tension dive alternator drive belt in accordance with aircraft/engine maintenance manual and service instructions. Torque the bolt (5) to 140 in/lbs and install .032” safety wire. NOTE: The aircraft/engine manufacturer’s torque value, if supplied, supersedes the above recommended torque. b: Install a new lock-nut and torque the bolt (3) and lock-nut (4) to 160-190 in/lbs. (b) If the alternator and alternator mounting bracket part numbers are not affected per section 1.A, continue to 3.C. Return to Service. B. Corrective Action See Fig. 2 for the following: (1) With the alternator, tension arm, and bracket arm in a free state, align alternator pulley and engine drive pulley. (2) Press spacers (1) & (2) against the alternator. (3) Install shims between the spacer (1) and/or (2) and the alternator mounting bracket until a combined gap between the alternator spacers (1 & 2) and alternator bracket of ≤ 0.007 is achieved. NOTE: Shims may be split between forward and rear gaps to align the alternator pulley to the engine drive pulley. (4) Install a new lock-nut (4) onto bolt (3). Do not torque the lock-nut (4) at this time. Rev. New: 04 Oct. 2024 SB 209 © 2024- Hartzell Engine Tech - All rights reserved Page 7 of 8 SERVICE B ULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection 1 4 2 3 Figure 2 - Alternator and Alternator Mounting Bracket Assembly 5 Alternator Mounting Bracket PN 10-9003 Tension Arm Bracket Arm Flat Washer Flat Washer (5) Using a feeler gage, verify total thickness of gaps is ≤ 0.007. (6) Tension alternator drive belt in accordance with aircraft/engine maintenance manual and service instructions. Torque the bolt (5) to 140 in/lbs and install .032” safety wire. NOTE: The aircraft/engine manufacturer’s torque value, if supplied, supersedes the above recommended torque. (7) Torque the bolt (3) and lock-nut (4) to 160-190 in/lbs. C. Return to Service (1) Close all access doors and covers opened to gain access to the alternator in accordance with applicable airframe and/or engine maintenance manual. D. Maintenance Record (1) Make an appropriate logbook entry noting compliance with this Service Bulletin. SB 209 Rev. New: 04 Oct. 2024 Page 8 of 8 © 2024 - Hartzell Engine Tech - All rights reserved SERVICE BULLETIN SERVICE BULLETIN No. 209 Alternator Mounting Bracket Inspection 4. Contact Information A. Contact HET Product Support for all communications regarding the technical content of this Service Bulletin. (1) Phone +1.334.386.5400 (Option 2) (2) Fax +1.334.386.5450 (3) E-mail at techsupport@hartzell.aero (4) Address Hartzell Engine Technologies LLC - ATTN: Product Support 2900 Selma Highway Montgomery, AL 36108 USA
What's in the CESSNA 310Q TCDS
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