CSB Technical Portions FAA Approved

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Laurence Leonard
7 years ago
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1 CSB--002 REASON FOR ACTION Hairline Crack in FLAP RIB 2. PURPOSE To inspect the FLAP RIB 2 and the wing RIB 1 AFT for any damage or crack. COMPLIANCE Mandatory MODELS AFFECTED From Liberty XL-2 Aircraft SN0001 to SN0088, SN0091 and SN0092. It has been reported to Liberty Aerospace that a hairline crack has been found around one (1) of the three (3) bolts securing the starboard inboard PLATE FLAP HINGE COMMON (135A ) to the FLAP RIB 2 (135A /610). The root cause for the crack formation is under investigation. Deploying the flaps above the flap limiting speed may cause such cracks. The following procedure details the mandatory inspection that must be conducted on your Liberty XL-2 flap and wing skeleton structure before next flight. Procedure 1. FLAP RIB 2 Inspection Fully deploy the flap. Inspect the FLAP RIB 2 for damage or cracks (may be present as a black line from the crack) by looking thru the FLAP RIB 1 aft lightning hole. Pay particular attention to the rib web around the washers of the three (3) AN3 bolts securing the PLATE FLAP HINGE COMMON (135A ) to the FLAP RIB 2 (135A /610). This inspection must be conducted on both the port and the starboard flap. This inspection may be conducted on the fully deployed flap using an inspection mirror and a flash light. Nonetheless it is recommended to remove the wing in accordance with Chapter 57 of the Liberty XL-2 Maintenance Manual. Phone: C

2 CSB--002 Port flap shown only, similar inspection must be performed on the starboard flap Flap skin removed for clarity Look thru this lightning hole Areas of interest Phone: C

3 CSB--002 Note: Hairline cracks are hard to detect, they are often represented as black irregular lines as they collect oil, grime and dust. It is recommended to use a borescope to perform a close up inspection. The following picture illustrates what may be found: Cleaned Damaged FLAP RIB 2 Hairline Crack If no crack is found, circle the NO for no crack found in the record table located on the last page of this Critical Service Bulletin, continue flying. If any cracks are found, do not continue flying, the aircraft must be grounded, circle the YES for crack present on the port and / or starboard FLAP RIB 2 and return to Liberty Aerospace Technical Support. A rework instruction kit will be provided (RKI-CSB--002). Phone: C

4 2. Wing RIB 1 AFT Inspection CSB--002 Remove the wings in accordance with Chapter 57 Liberty XL-2 Maintenance Manual. Inspect the wing RIB 1 AFT for damage or cracks (may be present as a black line from the crack) by looking thru the wing RIB 0 AFT lightning holes. Pay particular attention to the rib web around the washers of the three (3) AN3 bolts securing the HINGE PLATE (COMMON WING) (135A ) to the wing RIB 1 AFT (135A /556). This inspection must be conducted on both the port and the starboard wing. Stbd wing shown only, similar inspection must be performed on the port wing Wing skin removed for clarity Areas of interest Look thru this lightning hole If no crack is found, circle the NO for no crack found in the record table located on the last page of this Critical Service Bulletin, continue flying. Re-install the wings in accordance with Chapter 57 Liberty XL-2 Maintenance Manual. If any cracks are found, do not continue flying, the aircraft must be grounded, circle the YES for crack present on the port and / or starboard wing RIB 1 AFT and return to Liberty Aerospace Technical Support. A rework instruction kit will be provided. Phone: C

5 CSB--002 Compliance Times: Perform initial flap and wing inspection before next flight. When the aircraft reaches a total tach time of 340 hours, the aircraft must be grounded and the mandatory repair (RKI-CSB--002) installing reinforcement must be performed irrespective of whether cracks are or are not present from previous inspections. Aircraft beyond a total tach time of 340 hours must have the Liberty Aerospace approved repair to both port and starboard flap before next flight. Aircraft with less than 340 hours of tach time and no cracks on either part may be operated for a total of 340 hours tach time while subjected to a flap inspection as defined within this Critical Service Bulletin every 25 flight hours. 1. The flap inspection detailed within this document must be performed every 25 flight hours from initial inspection without exceeding a total of 340 hours of tach time. If the inspection yields that there are no cracks, continued inspection can be performed until a crack in the FLAP RIB 2 is recorded. All 25 hour inspection results must be submitted to Liberty Aerospace Technical Support to demonstrate compliance with this critical service bulletin. 2. If the initial inspection or any of the subsequent 25 hour inspections yield that there are cracks in the FLAP RIB 2, and/or the wing RIB 1 AFT, the aircraft must remain AOG (Aircraft On the Ground). Reinforcement parts must be installed in accordance with the approved document supplied by Liberty Aerospace Technical Support (RHI-CSB--002) must be conducted prior to next flight. Phone: C

6 CSB--002 Please fill the Flap Skeleton Inspection Matrix and the five (5) items listed below and return this page to Liberty Aerospace Technical Support by scanned , regular mail, or FAX, indicating that this CSB has been received and complied with. This table must be filled out and returned to Liberty Aerospace Technical Support after each incremental inspection is completed. The costs of all compliance actions identified in this Service Bulletin will be covered under the Liberty XL-2 Warranty as listed as: $65.00 USD per one (1) hour. Regular Mail: ATTN: Technical Support Liberty Aerospace Melbourne, FL Or FAX: Phone: C

7 CSB--002 Flap Skeleton Inspection Matrix: Inspection Time Port Flap Starboard Flap Recorded Tach Time Date Completed Cracks Found Y/N Locations Cracks Found Y/N Locations Initial Inspection Initial Tach plus 25 hrs Initial Tach plus 50 hrs Initial Tach plus 75 hrs Repair Performed (1.) LIBERTY AIRCRAFT SERIAL NUMBER (2.) AIRCRAFT TACH TIME AT INSPECTION (3.) INITIAL FLAP INSPECTION RESULTS (4.) INITIAL WING INSPECTION RESULTS (5.) INSPECTION COMPLETION DATE Owner / Operator s Name Crack in port FLAP RIB 2 YES NO Crack in stbd FLAP RIB 2 YES NO Crack in port wing RIB 1 AFT YES NO Crack in stbd wing RIB 1 AFT YES NO Owner / Operator s Address Owner / Operator s Telephone Owner / Operator s Signature Phone: C

Service Bulletin No. SB 06-2-23 MANDATORY SERVICE BULLETIN. Safetying of standard and flop-type fuel pickup tubes.

VAN S AIRCRAFT, INC. 14401 NE Keil Road, Aurora, Oregon, USA 97002 PHONE 503-678-6545 FAX 503-678-6560 www.vansaircraft.com info@vansaircraft.com Service Bulletin No. SB 06-2-23 MANDATORY SERVICE BULLETIN