Permanent Repair Procedure for Lightning Strike Burn Marks on A320 Skin Plates

SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 17 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Skin aboutblank 11 Figure 002 531111300011 SHEET 17 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Skin YES YES YES NO REAM UP HOLE IN SKIN ECCENTRICALLY IN DIRECTION OF DAMAGE TO ENABLE A BUSH INSTALLATION AS SHOWN IN ACTION LIST STEP BY STEP SEE SHEET 5 DO A CHECK AT EACH STEP IF DAMAGE IS REMOVED BY ROTATING PROBE TESTING INSTALL BUSH ANDOR FASTENER AS PER ACTION LIST APPLY AGAIN THE SURFACE SEE SHEET 5 DAMAGE REMOVED BY ABOVE PROCEDURE TO REMOVE DAMAGE PROVIDED THAT ABOVE MENTIONED RESTRICTION IS FOLLOWED DRILL HOLE STARTING WITH MINIMUM DIAMETER SEE SHEET 4 NECESSARY TO REMOVE DAMAGE AS PER ACTION LIST SEE SHEET 5 AND MAKE SURE BY ROTATING PROBE TESTING THAT SEE NTM TASK 511001250801 OF 645 mm 02539 in AS SHOWN IN ACTION LIST AND CHECK AT EACH STEP SEE SHEET 5 NO DAMAGE IS FOUND IF DAMAGED ENLARGE HOLE STEP BY STEP UP TO A MAXIMUM DIAMETER BY ROTATING PROBE TESTING THAT NO DAMAGE IS FOUND SEE NTM TASK 511001250801 NO YES CONSIDER REPAIR TO BE ALLOWABLE REWORK AS PER RELEVANT TASK NO DO THE PERMANENT REPAIR REPAIR OR CONTACT AIRBUS BEFORE NEXT FLIGHT DO THE PERMANENT REPAIR REPAIR OR CONTACT AIRBUS BEFORE NEXT FLIGHT PROTECTION SEE 517512 NO APPLICABLE FOR BURN MARKS ON SKIN CAUSED BY LIGHTNING STRIKES FOR A SKIN THICKNESS NOTE FOR DISTANCE CENTERLINE BETWEEN TWO REPAIR FASTENERS RESTRICTION FASTENER INSTALLATION AND REMOVAL METALLIC STRUCTURE FASTENER OVERSIZE AND ALTERNATIVES INSTALL OR REPLACE COUNTERSUNK FASTENERS FASTENERS HOLE AND DRILL DATA METALLIC STRUCTURE REFERENCE FILLING OF EXISTING COUNTERSINKS SEE 514211 SEE 514300 SEE 514611 SEE 514411 SEE 517115 SEE NTM TASK 511001250801 SEE 531111 SEE 531111 REPAIR OF PAINT COATINGS SEE 517512 32 mm 0126 in CONTACT AIRBUS OTHERWISE IF BURN MARK IS LOCATED AT A DISTANCE 15 mm 059 in FROM AN EXISTING FASTENER NO MORE THAN FIVE BURN MARKS BETWEEN TWO STRINGERS AND TWO FRAMES SEE SHEET 4 YES DAMAGE REMOVED DAMAGE REMOVED IS REWORK PERFORMED SEE SHEET 4 REWORK SKIN BURN MARK WITHOUT EXCEEDING ALLOWABLE PERMANENT REWORK LIMITS REFER TO RELEVANT TASK FOR ALLOWABLE PERMANENT REWORK LIMITS AND APPLICABILITY 01 01 NSR53111125JAM000A0106 SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 27 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Existing Fasteners aboutblank 11 Figure 002 531111300011 SHEET 27 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Existing Fasteners YES NO YES TO REMOVE HOLE DAMAGE ENLARGE HOLE STEP BY STEP UP TO A MAXIMUM DIAMETER OF 645 mm 02539 in AS SHOWN IN ACTION LIST AND DO A CHECK SEE SHEET 5 AT EACH STEP BY ROTATING PROBE TESTING SEE NTM TASK 511001250801 THAT NO DAMAGE IS FOUND NO YES NO DRILL OUT DAMAGED FASTENER DO THE ROTATING PROBE TESTING FOR DAMAGE EVALUATION DO THE PERMANENT REPAIR SEE 531111 REPAIR OR CONTACT AIRBUS BEFORE NEXT FLIGHT SEE NTM TASK 511001250801 DAMAGE REMOVED FINDINGS NO YES IS REWORK PERFORMED APPLICABLE FOR BURN MARKS ON EXISTING FASTENERS CAUSED BY LIGHTNING STRIKES FASTENER INSTALLATION AND REMOVAL METALLIC STRUCTURE FASTENER OVERSIZE AND ALTERNATIVES INSTALL OR REPLACE COUNTERSUNK FASTENERS FASTENERS HOLE AND DRILL DATA METALLIC STRUCTURE FILLING OF EXISTING COUNTERSINKS SEE 514211 SEE 514300 SEE 514611 SEE 514411 SEE 517115 NOTE REFERENCE REPAIR OF PAINT COATINGS SEE 517512 DAMAGE IN FASTENER HOLE REMOVED REAM UP HOLE IN SKIN ECCENTRICALLY IN DIRECTION OF DAMAGE TO ENABLE A BUSH INSTALLATION AS SHOWN IN ACTION LIST STEP BY STEP SEE SHEET 5 DO A CHECK AT EACH STEP IF DAMAGE IS REMOVED BY ROTATING PROBE TESTING SEE NTM TASK 511001250801 INSTALL BUSH ANDOR FASTENER AS PER ACTION LIST APPLY AGAIN THE SURFACE SEE SHEET 5 PROTECTION SEE 517512 NSR53111125JAM000B0105 SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 37 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Existing Fasteners andor Adjacent Skin aboutblank 11 Figure 002 531111300011 SHEET 37 Skin Plates Lightning Strike Permanent Repair of Burn Marks on Existing Fasteners andor Adjacent Skin NO YES YES NO YES YES APPLICABLE FOR BURN MARKS ON EXISTING FASTENERS ANDOR ADJACENT SKIN CAUSED BY LIGHTNING STRIKES OR BURN MARKS ON SKIN ONLY LOCATED AT A DISTANCE 15 mm 059 in FROM AN EXISTING FASTENER ROW DRILL OUT DAMAGED FASTENER FOR DAMAGE EVALUATION DO THE ROTATING PROBE TESTING FINDINGS IN FASTENER HOLE TREAT SKIN DAMAGE BEFORE FASTENER INSTALLATION TREAT SKIN DAMAGE BEFORE FASTENER INSTALLATION NOTE FASTENER INSTALLATION AND REMOVAL METALLIC STRUCTURE REFERENCE FASTENER OVERSIZE AND ALTERNATIVES INSTALL OR REPLACE COUNTERSUNK FASTENERS FASTENERS HOLE AND DRILL DATA METALLIC STRUCTURE FILLING OF EXISTING COUNTERSINKS SEE 514211 SEE 514300 SEE 514611 SEE 514411 SEE 517115 DO THE PERMANENT REPAIR SEE 531111 REPAIR OR CONTACT AIRBUS BEFORE NEXT FLIGHT NO DAMAGE IN FASTENER HOLE REMOVED AND SKIN DAMAGE REMOVED BY REAMING TO REMOVE HOLE DAMAGE ENLARGE HOLE STEP BY STEP TO A MAXIMUM DIAMETER OF 645 mm 02539 in AS SHOWN IN ACTION LIST AND DO A CHECK AT EACH STEP BY ROTATING SEE SHEET 5 PROBE TESTING SEE NTM TASK 511001250801 THAT NO DAMAGE IS FOUND ANDOR REWORK SKIN BURN MARK WITHOUT EXCEEDING ALLOWABLE PERMANENT REWORK LIMITS REFER TO RELEVANT TASK FOR ALLOWABLE PERMANENT REWORK LIMITS AND APPLICABILITY DO A CHECK FIRST IF DAMAGES CAN BE REWORKED BY ONLY INCREASING THE COUNTERSINK DEPTH FOR WHICH AN APPLICABLE FASTENER CAN BE INSTALLED REAM UP HOLE IN SKIN ONLY ECCENTRICALLY IN DIRECTION OF DAMAGE TO ENABLE A BUSH INSTALLATION AS SHOWN IN ACTION LIST REMOVED BY ROTATING PROBE TESTINGSEE NTM TASK 511001250801 STEP BY STEP DO A CHECK AT EACH STEP IF DAMAGE IS SEE SHEET 5 SEE NTM TASK 511001250801 BURN MARK BURN MARK A A A A REPAIR OF PAINT COATINGS SEE 517512 DAMAGES REMOVED BY SKIN AND HOLE ABOVE PROCEDURE DAMAGE REMOVED INSTALL BUSH ANDOR FASTENER AS PER ACTION LIST APPLY AGAIN THE SURFACE SEE SHEET 5 PROTECTION SEE 517512 YES IS REWORK PERFORMED NO NO NSR53111125JAM000C0106 SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 47 Skin Plates Lightning Strike Permanent Repair Example 1 aboutblank 11 Figure 002 531111300011 SHEET 47 Skin Plates Lightning Strike Permanent Repair Example 1 FR FR STGR STGR ORIGINAL FASTENER BURN MARK LEGEND EXAMPLE FOR MAXIMUM OF FIVE BURN MARKS PER FRAMESTRINGER BAY OR WITHIN 180 mm 709 in FOR UNSTIFFENED AREAS MINIMUM 25 x D1 D2 NOTE D1 AND D2 MAXIMUM DIAMETER OF BURN MARK 72 mm 0283 in D1 AND D2 D2 D1 01 01 NSR53111125JAM000D0101 SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 57 Skin Plates Lightning Strike Permanent Repair Action List aboutblank 11 Figure 002 531111300011 SHEET 57 Skin Plates Lightning Strike Permanent Repair Action List 93 mm 0366 in 606 mm 02386 in 645 mm 02539 in 646 mm 02543 in 93 mm 0366 in REAM UP 16 mm 0063 in AT DIAMETER DO THE CUTOUT AS NECESSARY 72 mm 0283 in 64 mm 0252 in R2 INSTALL BUSH DO THE REPAIR OR CONTACT AIRBUS FOR APPLICABILITY AREA SEE TASK 530011300022 03 58 mm 0228 in 605 mm 02382 in 68 mm 0268 in 64 mm 0252 in R1 03 496 mm 01953 in 579 mm 02280 in 64 mm 0252 in 458 mm 01803 in 495 mm 01949 in 56 mm 0220 in 48 mm 0189 in R2 04 435 mm 01713 in 457 mm 01799 in 52 mm 0205 in 48 mm 0189 in R1 04 372 mm 01465 in 434 mm 01709 in 48 mm 0189 in 04 MINIMUM 56 mm 0220 in 48 mm 0189 in R2 FOR ALUMINUM PANEL MINIMUM 48 mm 0189 in FOR TITANIUM PANEL SKIN SKETCH 1 2 20 mm DIA 079 in 1 REPAIR MATERIALS ITEM NAME MATERIALREMARKS THICKNESS mm in REPAIR WASHER PLUG FASTENER 31364T3LN9073 OR US EQUIVALENT CLAD 2024T3 SEE 513100 16 0063 OR SEE 514300 1 2 NOTE VALUES IE 48 mm 0189 in ARE ROUNDED R1 MEANS FIRST OVERSIZE R2 MEANS SECOND OVERSIZE FOR FASTENER REPLACEMENT AND RESPECTIVE HOLE AND SEE 514411 DRILL DATA MAKE SURE THAT AFTER CLEAN UP OF HOLE THE FASTENER HOLE PITCH IS AS PER RELEVANT CHAPTER MINIMUM EDGE MARGIN 15 x D IS MAINTAINED IF NOT REPAIR THE AFFECTED PART SEE 514700 IF COUNTERSINK IS INCREASED A MINIMUM CYLINDRICAL PART MUST EXIST IF THE HOLE AFFECTS A MILLED STEP APPLY RELEVANT PROCEDURE THE INSTALLATION OF A WASHER FROM THE INTERNAL SIDE IS MANDATORY FOR REPAIR AFFECTING SKIN ONLY AND FOR SKIN THICKNESS UP TO 3 mm 012 in SEE 514611 AFTER FINAL REAMING HILOK MUST BE INSTALLED HILOK MUST BE INSTALLED IF DIAMETER 68 mm 0268 in INSTALLATION OF STEEL NUT IS MANDATORY WHEN ORIGINAL FASTENER NUT WAS A STEEL NUT 02 03 05 04 06 HOLE DIAMETER WITH NO CRACK INDICATION BE INSTALLED AS PER TABLE 1 02 FOR FASTENERS FOR REPAIR OF BURN FASTENER NOMINAL DIAMETER TO MARKS ON SKIN OR AS PER 514211 OR TABLE 2 FOR FASTENERS REPLACEMENT FOR BURN MARKS ON EXISTING FASTENERS 05 ACTION NOTE 35 mm 0138 in 371 mm 01461 in 4 mm 016 in MINIMUM 52 mm 0205 in 48 mm 0189 in R1 FOR ALUMINUM PANEL MINIMUM 44 mm 0173 in 417 mm 016417 in R1 FOR TITANIUM PANEL ACTION LIST 04 MINIMUM 64 mm 0252 in FOR ALUMINUM PANEL MINIMUM 52 mm 0205 in 48 mm 0189 in R1 FOR TITANIUM PANEL MINIMUM 64 mm 0252 in FOR ALUMINUM PANEL MINIMUM 56 mm 0220 in 48 mm 0189 in R2 FOR TITANIUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL 06 ON FR48 TITANIUM UPPER PANELSTEEL BUSH INSTALLATION IS NOT PERMITTED FOR 300 mm 1181 in AROUND THE STANDBY COMPASS BUSH HAS TO BE MADE FROM A286 CRES WITHIN THIS AREA REFER TO FIGURE 001 SHEET 2 FIT FOR BUSHWASHERFASTENER INSTALLATION SEE SKETCH 1 FOR COLD EXPANSION OF FASTENER HOLES SEE 514800 FIGURE 002 AROUND THE HOLE TO MAKE SURE A PROPER SEE 517020 TITANIUM PANEL WITH TOOL 42N COLD EXPAND ALUMINUM PANEL OR SEE 514800 OR INCREASE DIAMETER 16 mm 0063 in MINIMUM FOR ALUMINUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL OR INCREASE DIAMETER 16 mm 0063 in MINIMUM FOR ALUMINUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL OR INCREASE DIAMETER 16 mm 0063 in MINIMUM FOR ALUMINUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL OR INCREASE DIAMETER 16 mm 0063 in MINIMUM FOR ALUMINUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL OR INCREASE DIAMETER 08 mm 0031 in MINIMUM FOR TITANIUM PANEL TITANIUM PANEL WITH TOOL 44N COLD EXPAND ALUMINUM PANEL OR TITANIUM PANEL WITH TOOL 60N COLD EXPAND ALUMINUM PANEL OR TITANIUM PANEL WITH TOOL 61N COLD EXPAND ALUMINUM PANEL OR TITANIUM PANEL WITH TOOL 63N COLD EXPAND ALUMINUM PANEL OR TITANIUM PANEL WITH TOOL 80N COLD EXPAND ALUMINUM PANEL OR TITANIUM PANEL WITH TOOL 81N COLD EXPAND ALUMINUM PANEL OR SEE 514800 SEE 514800 SEE 514800 SEE 514800 SEE 514800 SEE 514800 SEE SHEET 6 TABLE 1 NSR53111125JAM000E0104 SRM A320 ST1 Rev num 144 01Feb2023 Figure 002 531111300011 SHEET 67 Skin Plates Lightning Strike Permanent Repair Fastener Table 1 aboutblank 11 Figure 002 531111300011 SHEET 67 Skin Plates Lightning Strike Permanent Repair Fastener Table 1 MS20470AD D DD NAS1242AD D DD HL10VF HL110VF HL11VF HL111VF HL411VF NAS1097AD D DD NAS1241AD D DD HL410VF FASTENER DIAMETER CODE TABLE 1 SKIN THICKNESS COUNTERSUNK HEAD PROTRUDING HEAD 5 6 8 5 6 8 5 6 8 X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X X M X X X X X X X X X X X X X X X X X LEGEND INSTALLATION PERMITTED MAXIMUM COUNTERSUNK DEPTH 12 mm 0047 in MILL FLUSH PROTRUDING PART M INSTALLATION PERMITTED X INSTALLATION NOT PERMITTED 15 mm 0059 in 15 mm 0059 in 25 mm 0098 in 25 mm 0098 in 32 mm 0126 in 07 TABLE 1 FASTENERS FOR REPAIR OF BURN MARKS ON SKIN NOTE ALTERNATIVE FASTENERS 07 SEE 514300 NSR53111125JAM000F0103