ALERT SERVICE BULLETIN

The purpose of revision 1 of this ALERT SERVICE BULLETIN is to clarify the effectivity and the inspection procedure. Revision 1 of this ALERT SERVICE BULLETIN has an effect on the execution of the compliance with Revision 0 for helicopters which have not done the inspection of the internal side of the landing gear tube (paragraph 3.B.2.b.). No. EC130-32A013 Revision 0 2022-02-15 Page 5/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 1.D. DESCRIPTION This ALERT SERVICE BULLETIN makes sure that there is no corrosion on the external and internal sides of the landing gear tubes. 1.E. COMPLIANCE 1.E.1. Compliance at H/C manufacturer level Not applicable. 1.E.2. Compliance in service It is the operator who does the work on the helicopter and on non-installed equipment. Helicopters/installed equipment or parts: - For helicopters which have not complied with Revision 0 of this ALERT SERVICE BULLETIN: . Helicopters with landing gear that was operated in standard conditions and with a date of first installation on the helicopter before February 16, 2016: .. Comply with paragraph 3. not more than 24 months and 73 days after you received Revision 0 of this ALERT SERVICE BULLETIN. Refer to the issue date on the page footer. . Helicopters with landing gear that was operated in specific and severe atmospheric operating conditions and first installed between February 16, 2016 and February 15, 2022: .. Comply with paragraph 3.: - Not more than 24 months and 73 days after you received Revision 0 of this ALERT SERVICE BULLETIN. Refer to the issue date on the page footer. Or, - Not more than 7 years after the first installation of the landing gear (the first limit you get to is applicable). . Helicopters with landing gear that was operated in specific and severe atmospheric operating conditions and first installed before February 16, 2016: .. Comply with paragraph 3. not more than 12 months and 36 days after you received Revision 0 of this ALERT SERVICE BULLETIN. Refer to the issue date on the page footer. - For helicopters which have only done the external inspection through Revision 0 of this ALERT SERVICE BULLETIN: . Comply with paragraph 3.B.2.b (internal inspection) of this ALERT SERVICE BULLETIN in accordance with the compliance time of Revision 0. Refer to the issue date on the page footer. NOTE 10 Removal of the landing gear is not necessary to do only the internal inspection. - For helicopters which have done the external and internal inspections through Revision 0 of this ALERT SERVICE BULLETIN: . No more action is required. No. EC130-32A013 Revision 0 2022-02-15 Page 6/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ Non-installed equipment or parts: - For Landing gears or parts which have not complied with revision 0 of this ALERT SERVICE BULLETIN: . Comply with paragraph 3. (but this is not applicable to paragraphs 3.B.1. and 3.B.3.) of this ALERT SERVICE BULLETIN before installation on the helicopter. - For Landing gears or parts which have only done the external inspection through Revision 0 of this ALERT SERVICE BULLETIN: . Comply with paragraph 3.B.2.b. (internal inspection) of this ALERT SERVICE BULLETIN in accordance with the compliance time of Revision 0. Refer to issue date on the page footer. - For Landing gears or parts which have done the external and internal inspections through Revision 0 of this ALERT SERVICE BULLETIN: - No more action is required. 1.F. APPROVAL Approval of modifications: Not applicable. Approval of this document: The technical information contained in this ALERT SERVICE BULLETIN Revision 0 was approved on February 15, 2022 under the authority of EASA Design Organization Approval No. 21J.700 for civil version helicopters subject to an Airworthiness Certificate. The technical information contained in this ALERT SERVICE BULLETIN Revision 1 was approved on October 14, 2022 under the authority of EASA Design Organization Approval No. 21J.700 for civil version helicopters subject to an Airworthiness Certificate. 1.G. MANPOWER Airbus Helicopters recommends that the personnel who will do this ALERT SERVICE BULLETIN have this qualification: Qualification: 1 Mechanical Technician. The man-hours are an estimate given for information only and for a standard helicopter configuration. Estimated Man-hours: 2 hours for the Mechanical Technician to do the inspection. The helicopter downtime is an estimate given for information only and for a standard helicopter configuration. The estimate of the helicopter downtime is half a day for the inspection. No. EC130-32A013 Revision 0 2022-02-15 Page 7/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 1.H. WEIGHT AND BALANCE There is no change in weight and moment. 1.I. POWER CONSUMPTION Not applicable. 1.J. SOFTWARE UPGRADES/UPDATES Not applicable. 1.K. REFERENCES These documents are necessary to comply with this ALERT SERVICE BULLETIN: Aircraft Maintenance Manual (AMM) AMM: 32-11-00, 4-1: Removal / Installation - Landing gear - Skid Type Landing Gear AMM: 32-11-00, 4-2: Disassembly / Assembly - Landing gear - Skid Type Landing gear AMM: 32-11-00, 8-1: Rivet Replacement - Skid / Front Crossbeam link assembly - Skid type Landing Gear AMM: 60-00-00, 3-1: General Safety Instructions - Mechanical Assemblies - General - Mechanical Systems Standard Practices Manual (MTC) MTC: 20-02-05-404: Assembly by screws and nuts - Joining MTC: 20-02-06-404: Safetying with cotter pins - Safetying and locking assemblies MTC: 20-04-01-102: Use of cleaning products on individual parts and on aircraft - Cleaning MTC: 20-04-01-402: Cleaning of removed individual parts with liquid solvents - Cleaning MTC: 20-04-04-403: Touch-up of the Alodine 1200 protection (Bonderite M-Cr 1200) - Surface treatment before painting MTC: 20-04-05-101: Painting equipment and paint touch-ups - General - Paint and primer application procedure MTC: 20-04-05-402: Application of Primer EPOXY P05-P20 - Paint and primer application procedure MTC: 20-07-02-201: Helicopter parked in repair shop - Safety instructions MTC: 20-07-03-408: Appearance checks on an aircraft after an inspection or repair - Technical instructions MTC: 20-08-05-103: Monitoring of parts in operation - marking - service life customization - General rules applicable to aircraft MTC: 20-90-01-104: Types of corrosion - Standard corrosion practices MTC: 20-90-03-101: Inspection methods - Corrosion detection MTC: 20-90-03-106: Ultrasonic detection - Corrosion detection MTC: 20-90-04-101: General - Corrosion treatment MTC: 20-90-04-301: Anti-corrosion products - Corrosion treatment MTC: 20-90-04-401: General reconditioning method for corroded surfaces - Corrosion treatment MTC: 20-90-04-402: Specific treatment procedures - Corrosion treatment MTC: 20-90-05-101: General information - Repairs MTC: 20-90-05-401: Alodine 1200 treatment (aluminum alloys) - Repairs Information Notice (IN) IN 3481-I-00: The Marketplace: an AirbusWorld eOrdering service IN 3785-I-00: Introduction of the digital Service Bulletin reporting service SB Insight No. EC130-32A013 Revision 0 2022-02-15 Page 8/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 1.L. OTHER AFFECTED PUBLICATIONS Airbus Helicopters will update the manuals shown below in relation to this ALERT SERVICE BULLETIN: - Aircraft Maintenance Manual (AMM) - Master Servicing Manual (MSM). Airbus Helicopters will update the AMM and the MSM when the customer sends an order for them. 1.M. PART INTERCHANGEABILITY OR MIXABILITY This ALERT SERVICE BULLETIN has no effect on the interchangeability and mixability. No. EC130-32A013 Revision 0 2022-02-15 Page 9/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 2. EQUIPMENT OR PARTS INFORMATION 2.A. EQUIPMENT OR PARTS: PRICE - AVAILABILITY - PROCUREMENT Price If the corrosion is more than the criteria and aligned with your Technical Event report, Airbus Helicopters will apply a special commercial policy for new components, based on the age of the landing gear. Availability Contact the Sales and Customer Relations Department to know the delivery lead times. Procurement Send an order for the necessary quantities to the Airbus Helicopters Network Sales and Customer Relations Department: Airbus Helicopters Etablissement de Marignane Direction Ventes et Relations Client 13725 MARIGNANE CEDEX FRANCE In the purchase order, write the information that follows: - The mode of transport - The destination - The serial numbers of the helicopters to change. 2.B. LOGISTIC INFORMATION Not applicable. No. EC130-32A013 Revision 0 2022-02-15 Page 10/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 2.C. EQUIPMENT OR PARTS REQUIRED PER HELICOPTER/COMPONENT Kits to be ordered for one helicopter or one assembly: Key Word Qty New P/N Item Former P/N → Instruction Blanking cap A/R 350A41-4004-00 or 350A41-6006-20 1 350A41-4004-00 or 350A41-6006-20 Consumables to be ordered separately: Refer to the Tasks and Work Cards identified in this ALERT SERVICE BULLETIN and the list below. Key Word Qty P/N CM Item Alodine 1200 A/R / CM 324 2 Primer P05 A/R DHS186-111-20 CM 487 3 Primer P20 A/R DHS186-111-40 CM 488 4 NOTE When you order primer P05 (DHS186-111-20), you will also order hardener (DHS186-111-21) and thinner (DHS186-111-22). You can send an order for the consumables from the AirbusWorld Marketplace through e-ordering (IN 3481-I-00). If you cannot get access to e-ordering, please contact your Logistic Focal Point. Special tools: Refer to the Tasks and Work Cards indicated in this ALERT SERVICE BULLETIN and the list below: Key Word Qty P/N or equivalent Item Borescope 1 Commercial zz Olympus 45MG ultrasonic thickness gauge or equivalent 1 Commercial yy Virtual-45MG-EETC software opt or equivalent 1 Commercial Thru Coat Transducer D7908 or equivalent 1 Commercial Standard aluminum 2024 step blocks 1 Commercial 2.D. EQUIPMENT OR PARTS TO BE RETURNED Not applicable. No. EC130-32A013 Revision 0 2022-02-15 Page 11/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 3. ACCOMPLISHMENT INSTRUCTIONS 3.A. GENERAL - Comply with the general safety instructions for mechanical assemblies. Refer to Task 60-00-00, 3-1 (AMM). - Comply with the instructions about the assembly by screws and nuts. Refer to Work Card 20-02-05-404 (MTC). - Comply with the instructions about the safetying with split pins. Refer to Work Card 20-02-06-404 (MTC). - Comply with the general instructions about helicopters parked in a repair shop. Refer to Work Card 20-07-02-201 (MTC). - Comply with the general information about the types of corrosion. Refer to Work Card 20-90-01-104 (MTC). - Comply with the inspection methods for corrosion detection. Refer to Work Card 20-90-03-101 (MTC). - Comply with the instructions about ultrasonic corrosion detection. Refer to Work Card 20-90-03-106 (MTC). - Comply with the instructions about anti-corrosion products for corrosion treatment. Refer to Work Card 20-90-04-301 (MTC). - Comply with the general method for restoring corroded surfaces. Refer to Work Card 20-90-04-401 (MTC). - Comply with the specific treatment procedures for corrosion. Refer to Work Card 20-90-04-402 (MTC). - Comply with the general information about repairs. Refer to Work Card 20-90-05-101 (MTC). 3.B. WORK STEPS CAUTION MAKE SURE THAT YOU PREVENT ALL POSSIBLE FOD. 3.B.1. Preliminary steps - Park the helicopter in a maintenance shop. - Install the appropriate access equipment. - Remove the landing gear. Refer to Task 32-11-00, 4-1 (AMM). 3.B.2. Procedure 3.B.2.a. External inspection (Figure 4) - Remove the landing gear fairing (not shown) from the rear crossbeam (a). Refer to Task 32-11-00, 4-2 (AMM). - Clean the outer side of the landing gear tubes (a), (c), (d) and (e) (Detail A, Figure 4). Refer to Work Card 20-04-01-102 (MTC) and Work Card 20-04-01-402 (MTC). NOTE 1 Zones B, C, D, E, F and M are included in the cleaning and the inspection of the landing gear tubes (a), (c), (d) and (e). - Do an external visual inspection of the landing gear tubes (a), (c), (d) and (e) to make sure that there are no cracks and no corrosion. . If you find at least one crack: .. Contact Airbus Helicopters at the address that follows to get a technical solution: ... Airbus World: Technical Request Management https://airbusworld.helicopters.airbus.com ... E-mail: support.technical-airframe.ah@airbus.com ... Fax: + 33 (0) 4 42 85 99 66 No. EC130-32A013 Revision 0 2022-02-15 Page 12/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ . If you find any corrosion within zones C or E: .. Disassemble the landing gear. Refer to Task 32-11-00, 4-2 (AMM). .. Remove the corrosion from all the zones. Refer to Work Card 20-90-04-101 (MTC). . If you find corrosion only within zones B, D, F or M: .. Remove the corrosion from the zone. Refer to Work Card 20-90-04-101 (MTC). . Then, in all cases, comply with paragraph 3.B.2.b. 3.B.2.b. Internal inspection (Figure 4) - With the borescope (zz), examine the inner side of the landing gear tubes (a), (c), (d) and (e) for corrosion and cracks. Refer to Detail A, Figure 4, and to the criteria of Table 3. NOTE 2 If only the internal inspection is to be done, removal of the landing gear is not necessary. NOTE 3 To examine zones E and D, make sure that the length of the borescope (zz) is sufficient and the diameter is less or equal to 8 mm (.098 in). NOTE 4 To do the borescope inspection of the landing gear tubes (a), (c), (d) and (e), you can remove the screws (j) or the blanking cap assembly (b) (Detail D, Figure 4). Refer to the principle of Task 32-11-00, 4-2 (AMM). NOTE 5 To do the borescope inspection of the landing gear tube (a), you can remove the screws (k) (Detail D, Figure 4). Refer to the principle of Task 32-11-00, 4-2 (AMM), if necessary. NOTE 6 You can use the holes of the screws (not shown) at clamp position F to do the borescope inspection in zones E and D, if necessary. No. EC130-32A013 Revision 0 2022-02-15 Page 13/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ - Clean the inner side of the landing gear tubes (a), (c), (d) and (e). Refer to Work Card 20-04-01-102 (MTC) and Work Card 20-04-01-402 (MTC), if necessary. . If you find at least one crack or leafing corrosion or exfoliant corrosion (Figures 1 and 2): .. Contact Airbus Helicopters at the address that follows to get a technical solution: ... Airbus World: Technical Request Management https://airbusworld.helicopters.airbus.com ... E-mail: support.technical-airframe.ah@airbus.com ... Fax: + 33 (0) 4 42 85 99 66 Figure 1 Figure 2 . If you find any corrosion within zones C or E: .. Disassemble the landing gear. Refer to Task 32-11-00, 4-2 (AMM). .. Remove the corrosion from all the zones. Refer to Work Card 20-90-04-101 (MTC). .. Comply with paragraph 3.B.2.c. . If you find corrosion only within zones B, D, F or M: .. Remove the corrosion from the zone. Refer to Work Card 20-90-04-101 (MTC). .. Comply with paragraph 3.B.2.c. . If you do not find external nor internal corrosion nor cracks: .. Install the screws (j) or the blanking cap assembly (b) or (1) and the screw (k). Refer to Task 32-11-00, 4-2 (AMM) (Detail D, Figure 4). .. Comply with paragraph 3.B.2.d. No. EC130-32A013 Revision 0 2022-02-15 Page 14/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 3.B.2.c. Permitted criteria - With the Ultrasonic thickness gauges Olympus 45MG (or equivalent) (yy) and Work Card 20-90-03-106 (MTC), measure the remaining thickness of the landing gear tubes in the zones where you removed corrosion. NOTE 7 The measurement of the remaining thickness with ultrasonic thickness gauges should usually be done on surfaces without protection after a local sanding of the protections (not applicable to a-scan device). Device calibration can be done with: - Step calibration block made of 2024 aluminum or - 2 different edges of landing gear tubes and a caliper. NOTE 8 When you use the Ultrasonic thickness gauges Olympus 45MG (or equivalent) (yy), it is not necessary to remove the paint to do the check of the thickness of the landing gear tubes. No. EC130-32A013 Revision 0 2022-02-15 Page 15/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ - Interpret the results as shown in Table 3: Figure 3 - If the corrosion is not more than the criteria in Table 3: . Comply with paragraphs 3.B.2.d. - If the corrosion is more than the criteria in Table 3: . Contact Airbus Helicopters at the address that follows to get a technical solution: .. Airbus World: Technical Request Management https://airbusworld.helicopters.airbus.com .. E-mail: support.technical-airframe.ah@airbus.com .. Fax: + 33 (0) 4 42 85 99 66 Table 3 Zones Location Permitted criteria M Below the two half-bearings of the rear crossbeam (a). Make sure that there is a minimum thickness of: - 7.4 mm (.275 in.) on the top of the tube (Figure 3). - 8.1 mm (.318 in.) on the sides of the tube (Figure 1). - 8.4 mm (.330 in.) on the bottom of the tube (Figure 3). Over 100 mm (3.937 in.) inboard and 100 mm (3.937 in.) outboard of the clamp. B1 On the LH/RH fitting, in the rear crossbeam (a) fitting zone (Detail B, Figure 5). Make sure that there is a minimum thickness of 8.0 mm (.314 in.). B2 On the LH/RH rear crossbeam (a), in the fitting zone (Detail B, Figure 5). Make sure that there is a minimum thickness of 7.3 mm (.287 in.). C1 On the LH/RH skid assemblies (c) and (e) (Detail C, Figure 5). Make sure that there is a minimum thickness of 3.0 mm (.118 in.). C2 On the fitting, in the junction zone of the LH/RH skid assemblies (c) and (e) (Detail C, Figure 5). Make sure that there is a minimum thickness of 3.0 mm (.118 in.). D Zone of the LH/RH front footstep. Make sure that there is a minimum thickness of 3.1 mm (.122 in.). E On the front crossbeam (d). Make sure that there is a minimum thickness of 3.0 mm (.118 in.). On the LH/RH skid assembly (c). Make sure that there is a minimum thickness of 2.0 mm (.078 in.). F Below the half-bearings of the front crossbeam (d). Make sure that there is a minimum thickness of 3.9 mm (.153 in.). From 100 mm (3.937 in.) outboard of the LH clamp to 100 mm (3.937 in.) outboard of the RH clamp. Top of the tube Bottom of the tube Side of the tube Side of the tube No. EC130-32A013 Revision 0 2022-02-15 Page 16/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 3.B.2.d. Complementary actions - Bellow the collar in zones M and F (Figure 4) and in the reworked zones, apply: . Chemical conversion coating (Alodine 1200) (2). Refer to Work Card 20-90-05-401 (MTC). . A double layer of chromate Primer P05 (3) and Primer P20 (4). Refer to Work Card 20-04-05-101 (MTC). - If the landing gear has not been disassembled and if rivets are loose and/or missing and if there is no corrosion evidence, replace all the missing or loose rivets. Refer to Task 32-11-00, 8-1 (AMM). - If the landing gear has been disassembled during the compliance of paragraph 3.B.2.a. or paragraph 3.B.2.b., assemble the landing gear. Refer to Task 32-11-00, 4-2 (AMM). - If the landing gear fairing (not shown) has been removed during the compliance of the paragraph 3.B.2.a., install the landing gear fairing (not shown) on the rear crossbeam (not shown). Refer to Task 32-11-00, 4-2 (AMM). - Comply with paragraphs 3.B.3. and 3.C. 3.B.3. Final steps - Install the landing gear. Refer to Task 32-11-00, 4-1 (AMM). - Remove the access equipment. - Clean and restore the work zones and the helicopter. Refer to Work Card 20-07-03-408 (MTC). - Set the helicopter to flight condition. No. EC130-32A013 Revision 0 2022-02-15 Page 17/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 3.C. RECORD OF COMPLIANCE Compliance with this document: - Record the full compliance with this ALERT SERVICE BULLETIN, with the revision number, in the helicopter documents. - Record the full compliance with this ALERT SERVICE BULLETIN (see IN 3785-I-00 for instructions): QR code or hypertext link NOTE 9 The recording of compliance with ALERT SERVICE BULLETINS in the SB Insight tool does not replace the recording in the helicopter documents. ASB EC130-32A013 Identification of modifications on equipment or parts: - Identify the landing gears or parts. Refer to table below and Work Card 20-08-05-103 (MTC). Key Word Old MP/N New MP/N MOD Marking type Landing gear assembly 350A41-0077-0201 350A41-0077-0201 + ASB No. 32A013 / Indelible ink 350A41-0080-1102 350A41-0080-1102 + ASB No. 32A013 / Indelible ink 350A41-0080-1103 350A41-0080-1103 + ASB No. 32A013 / Indelible ink 350A41-0081-0201 350A41-0081-0201 + ASB No. 32A013 / Indelible ink 350A41-0082-0101 350A41-0082-0101 + ASB No. 32A013 / Indelible ink 350A41-0082-0102 350A41-0082-0102 + ASB No. 32A013 / Indelible ink No. EC130-32A013 Revision 0 2022-02-15 Page 18/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ Key Word Old MP/N New MP/N MOD Marking type Front crossbeam 350A41-0042-20 350A41-0042-20 + ASB No. 32A013 / Indelible ink 350A41-4000-00 350A41-4000-00 + ASB No. 32A013 / Indelible ink 350A41-4000-01 350A41-4000-01 + ASB No. 32A013 / Indelible ink 350A41-6003-00 350A41-6003-00 + ASB No. 32A013 / Indelible ink Rear crossbeam 350A41-4001-00 350A41-4001-00 + ASB No. 32A013 / Indelible ink 350A41-0058-20 350A41-0058-20 + ASB No. 32A013 / Indelible ink 350A41-6004-00 350A41-6004-00 + ASB No. 32A013 / Indelible ink LH skid assembly 350A41-0045-00 350A41-0045-00 + ASB No. 32A013 / Indelible ink 350A41-0069-00 350A41-0069-00 + ASB No.32A013 / Indelible ink 350A41-0069-01 350A41-0069-01 + ASB No. 32A013 / Indelible ink 350A41-6002-0101 350A41-6002-010 + ASB No. 32A0131 / Indelible ink 350A41-6002-0201 350A41-6002-020 + ASB No. 32A0131 / Indelible ink RH skid assembly 350A41-0044-00 350A41-0044-00 + ASB No. 32A013 / Indelible ink 350A41-0068-00 350A41-0068-00 + ASB No. 32A013 / Indelible ink 350A41-0068-01 350A41-0068-01 + ASB No. 32A013 / Indelible ink 350A41-6002-0001 350A41-6002-0001 + ASB No. 32A013 / Indelible ink 350A41-6002-0301 350A41-6002-0301 + ASB No. 32A013 / Indelible ink 3.D. OPERATING AND MAINTENANCE INSTRUCTIONS Not applicable. No. EC130-32A013 Revision 0 2022-02-15 Page 19/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ k j b 1 j k Back to paragraph 3.B.2.a. Back to paragraph 3.B.2.b. Back to paragraph 3.B.2.d. Figure 4 PRE MOD 072899 POST MOD 072899 See Figure 5 See Figure 5 See Figure 5 See Figure 5 a c d e ZONE E ZONE D ZONE F ZONE E ZONE D ZONE M No. EC130-32A013 Revision 0 2022-02-15 Page 20/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ Back to Figure 4 Back to Table 3 Figure 5 See Figure 4 PRE MOD 072899 a ZONE B1 c - e ZONE B2 f a ZONE C2 ZONE C1 c - e f See Figure 4 See Figure 4 See Figure 4 POST MOD 072899 ZONE B2 ZONE B1 a c - e ZONE C2 ZONE C1 c - e a b 1 No. EC130-32A013 Revision 0 2022-02-15 Page 21/21 Revision 1 2022-10-17 This document is available on the Internet: www.airbushelicopters.com/techpub/ 4. APPENDIX RESPONSE FORM for ALERT SERVICE BULLETIN No. 32A013 "Inspection of the landing gear" Complete the form and send it to: - Airbus World: Technical Request Management: https://airbusworld.helicopters.airbus.com - E-mail: support.technical-airframe.ah@airbus.com - Fax: + 33 (0) 4 42 85 99 66 General information H/C Type: S/N: Delivery Date: FH: Number of landings: Replacement of landing gear parts P/N Designation Reason for replacement Date Table of recording results Result (photo) Part concerned Location (M, B1, B2, C1, C2, D, E, F) Type Damage size (approx.) Thickness after rework Thickness in healthy zone near the damage Example Front crossbeam Below the junction collar Surface corrosion 20 mm X 30 mm 4.2 mm 5 mm Date: _____________ Signature: _____________ Please make a copy of this page. The original form must stay in the ALERT SERVICE BULLETIN.