ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 1 OF 2 

# SERVICE BULLETIN
BAE SYSTEMS (OPERATIONS) LIMITED, PRESTWICK INTERNATIONAL AIRPORT, AYRSHIRE, KA9 2RW, SCOTLAND. 57-JA140140

TRANSMITTAL SHEET This page transmits the original issue of Service B ulletin 57-JA140140. TITLE: WINGS - INSPECTION OF WING MAIN SPAR AROUND RIB 36 INSPECTION

REASON During fatigue testing of the wing, cracking was di scovered in the wing main spar at rib 36. If the cracking is not detected a failure of the wing may occur. INSTRUCTIONS FOR INCORPORATION Add complete Service Bulletin pages 1 to 34 at Orig inal Issue.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 2 BLANKORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 1 OF 34 

# SERVICE BULLETIN
BAE SYSTEMS (OPERATIONS) LIMITED, PRESTWICK INTERNATIONAL AIRPORT, AYRSHIRE, KA9 2RW, SCOTLAND. 57-JA140140

TITLE: WINGS - INSPECTION OF THE WING MAIN SPAR ARO UND RIB 36 INSPECTION 1. PLANNING INFORMATION A. Effectivity All Jetstream 3200 Series aircraft, Post Mod JM8229

. B. Reason Life extension programme requirement. C. Description The main spar inboard of rib 36 is inspected by X-r ay. The main spar fasteners at rib 36 and outboard of rib 36 are removed and a rotary edd y current inspection is performed. An access hole is drilled into the wing bottom skin to allow a rotary eddy current inspection of the underlying tooling hole in the ma in spar at rib 36. Work comprises:- - De-fuel the aircraft. - Jack and trestle the aircraft. - Remove wing to fuselage fairing panels and wing a ccess panels, sufficient to allow removal of the rib 36 bottom external straps (2 off ). - Remove the rib 36 bottom external straps. - The single row of 3/16 in. (4.7 mm) dia. counters unk fasteners inboard of rib 36 (2 off), that pass through the main spar only, are rem oved and a rotary eddy current inspection is performed on the holes. - Rotary eddy current inspection is performed on th e single row of 1/4 in. (6.35 mm) dia. fastener holes at rib 36 (2 off). - The 8 rows of 3/16 in. (4.7 mm) dia. countersunk fasteners outboard of rib 36 (20 off) that pass through the bottom skin and main spar, ar e removed and a rotary eddy current is performed on the holes. - The position of the rib 36 tooling hole in the ma in spar is located on the wing bottom skin. The position of the tooling hole is located u sing an eddy current probe. - A hole is drilled through the wing bottom skin to reveal the underlying tooling hole in the main spar at rib 36. - The PSR sealant within the tooling hole is cleane d out and a rotary eddy current inspection is performed on the tooling hole. - X-ray inspection is performed on the main spar in board of rib 36.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 2 D. Manpower 96 man-hours (Including 4 hours for eddy current and 3 hours to perform radiography) Mechanical skills are necessary. E. Material - Cost and Availability
None. F. Weight and Balance Not affected. G. Aircraft Noise Levels Aircraft noise is not affected.
H. Electrical Load Data Not affected. I. Software Accomplishment Summary Not applicable. J. References - Aircraft Maintenance Manual, Chapters 06, 07 and 28. - Non-Destructive Inspection Manual, Chapter 20. - Structural Repair Manual, Chapter 51. K. Publications Affected
None. Operators are requested to advise the Business Supp ort Team, Technical Publications, BAE SYSTEMS (Operations) Limited, Prestwick Interna tional Airport, Ayrshire, KA9 2RW, SCOTLAND of the accomplishment of this service bulletin and request the necessary revisions for the affected manuals. L. Family Tree Of Modification Relationships Not applicable.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 3 M. Approval The initial inspections must be performed at or bef ore 54 000 landings. The inspections have to be repeated thereafter ever y 14 300 landings. The technical content of this service bulletin is t o be the subject of EASA Airworthiness Directive consultation. The technical content of this service bulletin is a pproved under the authority of Design Organisation Approval No. EASA.21J.047.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 4 BLANK PAGESERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 5 2. ACCOMPLISHMENT INSTRUCTIONS DUPLICATE INSPECTION WHENEVER ANY PART OF THIS SYSTEM IS DISMANTLED, ADJ USTED, REPAIRED OR RENEWED, DETAILED INVESTIGATION MUST BE MADE ON COM PLETION TO ENSURE THAT DISTORTION, TOOLS, RAGS OR ANY OTHER LOOSE ART ICLES OR FOREIGN MATTER SUCH AS COULD IMPEDE THE FREE MOVEMENT AND S AFE OPERATION OF THE SYSTEM ARE NOT PRESENT AND THAT THE SYSTEMS AND INSTALLATIONS IN THE WORK AREA ARE CLEAN. WHENEVER ANY PART OF EITHER THE MAIN OR ANY OTHER A SSOCIATED SYSTEM IS DISMANTLED, ADJUSTED, REPAIRED OR RENEWED, THAT PART OF THE SYSTEM THAT HAS BEEN DISTURBED SHALL BE SUBJECTED TO A DUP LICATE INSPECTION FOR SECURITY OF LOCKING DEVICES, FULL AND FREE MOVE MENT, DIRECTION AND TENSION CHECKS AND, FOR AIRCRAFT ON THE BRITISH REG ISTER, THE COMPLETION OF THIS WORK SHALL BE CERTIFIED IN ACCOR DANCE WITH THE BRITISH CIVIL AIRWORTHINESS REQUIREMENTS, SECTION A , CHAPTER A6-2 OR IN THE CASE OF AIRCRAFT NOT ON THE BRITISH REGISTER, T HE EQUIVALENT NATIONAL STANDARD. WARNING: MAKE SURE THE AIRCRAFT AND THE AIRCRAFT SY STEMS ARE MADE

SAFE AS DETAILED IN THE APPLICABLE CHAPTERS OF THE AIRCRAFT MAINTENANCE MANUAL. WARNING: THE MINIMUM CLEARANCE BETWEEN MOVING AND S TRUCTURAL PARTS

MUST BE 0.2 IN (5.1 MM) UNLESS OTHERWISE STATED. CAUTION: TO AVOID DAMAGE, MAKE SURE BEFORE MOVING C ONTROLS THAT

CONTROL RUNS AND CONTROL SURFACES ARE FREE FROM OBSTRUCTION. CAUTION: TAKE CARE NOT TO DAMAGE STRUCTURE WHEN MAT ERIAL IS CUT OR

DRILLED. REMOVE ALL UNWANTED MATERIAL FROM THE WORK AREA. CAUTION: IF AN ELECTRICAL CONNECTION OR CONNECTOR I S DISMANTLED,

ASSEMBLED OR REPLACED, DO A CONTINUITY CHECK AND, I F APPLICABLE, A SCREEN BONDING CHECK BEFORE THE ASSEM BLY IS CONNECTED TO EQUIPMENT. NOTE: Abbreviations used in the accomplishment inst ructions of this service bulletin are: AMM - Aircraft Maintenance Manual. A/R - As Required. FSH - Full Screen Height. NDI - Non-Destructive Inspection. NDT - Non-Destructive Testing. SRM - Structural Repair Manual.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 6 A. Preparation (1) Refer to AMM Chapter 12-10-28. De-fuel the airc raft. (2) Jack and trestle the aircraft in accordance wit h AMM Chapter 07-10-00. Wing jacks are to be located at wing Stn. 36. B. Accomplishment Inspection (1) Remove wing to fuselage fairing panels and wing access panels, sufficient to allow removal of the rib 36 bottom external straps (2 off). (2) Refer to Figures 1 and 2. Remove the rib 36 bot tom external straps. NOTE: To remove the bolts through the straps, skin and main spar at rib 36 (2 off), it

may be necessary to: (a) Remove the sealing block above the main spar. T his may result in having to replace the sealing block and anchor nuts. (b) Drill the countersunk heads off the 2 bolts at rib 36, remove the external straps and remove the remaining length of bolts usi ng a stud puller. (3) After removal of the external straps, re-fasten rib 36 to the bottom skin with temporary fasteners. (4) Perform a rotary eddy current inspection, in ac cordance with Appendix 1, on the single row of 1/4 in. (6.35 mm) dia. fastener holes at rib 36 (2 off). (5) Remove the single row of 3/16 in. (4.7 mm) dia. countersunk fasteners inboard of rib 36 (2 off) that pass through the main spar only . Perform a rotary eddy current inspection of the holes in accordance with Appendix 1. (6) Remove the 8 rows of 3/16 in. (4.7 mm) dia. cou ntersunk fasteners outboard of rib 36 (20 off) that pass through the bottom skin and m ain spar. Only 50% of the fasteners may be removed at any one time. Perform a rotary eddy current inspection of the holes in accordance with Appendix 1. (7) Refer to Figure 2. Locate the position of the u nderlying tooling hole in the main spar using the dimensions shown on Figure 2. and ma rk the approximate position on the bottom skin. This mark is intended only as a guide to where the tooling hole is located. (8) Confirm the position of the main spar underlyin g tooling hole using the NDT technique contained in Appendix 1. (9) Insert shim steel between the bottom skin (and doubler) and the main spar at the location of the tooling hole in order to protect th e main spar during the drilling operation. If necessary, remove fasteners attaching the landing angle to the bottom skin (and doubler).SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 7 (10) Drill a 1/8 in. (3.2 mm.) dia. hole in the bot tom skin (and doubler) at the location of the tooling hole. Remove the shim steel and check t he proximity of the drilled hole to the underlying tooling hole. Gradually increase the dia. of the drilled hole to align the centre of the drilled hole with the centr e of the tooling hole. The final dia. of the drilled hole should be 1/4 in. (6.35 mm.) di a. to match the dia. of the tooling hole. Oversizing the drilled hole in the skin and d oubler up to 3/8 in. is permitted if required to align the drilled hole with the tooling hole. Oversizing above 0.25 in. must be reported to BAE SYSTEMS before proceeding. (11) Drill out and remove the PSR sealant within th e tooling hole. (12) Perform a rotary eddy current inspection of th e tooling hole in accordance with Appendix 1. (13) Apply brush Alocrom 1200, in accordance with S RM 51-30-63, to any bare metal within the tooling hole and the drilled hole in the skin and doubler. (14) Apply Epoxy Primer, in accordance with SRM 51- 30-66, to any bare metal within the tooling hole and the drilled hole in the skin a nd doubler. (15) Fill the tooling hole and the drilled hole in the skin and doubler using PR1422 or PR1782 sealant. (16) Perform X-ray inspection of the main spar inbo ard rib 36 in accordance with Appendix 2. (17) Any defects observed during the above inspecti ons must be reported to BAE Systems before proceeding. NOTE: Appendix 2 can be performed before, during or after the removal of the external straps at rib 36. C. Recovery (1) Replace the external straps, sealing block (if required) and all removed fasteners with new or serviceable items (for fastener details refer to Drawing No’s. 1379149B and 1379209B). Wet assemble in accordance with SRM 51-50-10. (2) Any over-sizing of fastener holes must be repor ted to BAE Systems before proceeding. (3) Replace all removed fairings and access panels. (4) Make certain work area is clean, and clear of t ools and miscellaneous equipment. (5) Refer to AMM Chapter 07-10-00. Remove jacks and trestles and lower aircraft. (6) Close up. (7) Aircraft records: (a) Add service bulletin number 57-JA140140 to the aircraft records.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 8 (b) Add Mod JM8230 to the aircraft records.

NOTE: Operators are reminded of the necessity to in form the Business Support Team, Technical Publications, BAE Systems (Operations) Li mited, Prestwick International Airport, Ayrshire, KA9 2RW, SCOTLAND, of the accomplishment of this service bulletin in order to obtain the nec essary revisions for the affected manuals, see paragraph 1.K. Publications Affected, of this service bulletin.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 9 3. MATERIAL INFORMATION NOTE: The following material data is provided on a 'per' aircraft basis. Use the applicable

material kit number shown to order the parts requir ed. A. New parts supplied as material kit None. B. Replacement Parts - Operators Supply

Part No. Description 1 st Oversize (1/64) 2 nd Oversize

(1/32) Qty

(Req’d per a/c) Comment

PR1422 or PR1782 Sealant - - As required - 1379170B401 Sealing Block - - 1 - 1379170B402 Sealing Block - - 1 - MS21059L5 Anchor Nut - - 4 - NAS7403-6 Bolt - CSK NAS7403-6X NAS7403-6Y 14 - NAS7403-7 Bolt - CSK NAS7403-7X NAS7403-7Y 10 - NAS7403-8 Bolt - CSK NAS7403-8X NAS7403-8Y 8 - NAS7403-30 Bolt - CSK NAS7403-30X NAS7403-30Y 6 - NAS7403-31 Bolt - CSK NAS7403-31X NAS7403-31Y 10 - NAS7403-32 Bolt - CSK NAS7403-32X NAS7403-32Y 16 - NAS7403-34 Bolt - CSK NAS7403-34X NAS7403-34Y 8 - NAS7404-8 Bolt - CSK NAS7404-8X NAS7404-8Y 18 - NAS7404-10 Bolt - CSK NAS7404-10X NAS7404-10Y 2 - NAS7404-11 Bolt - CSK NAS7404-11X NAS7404-11Y 8 - NAS7404-12 Bolt - CSK NAS7404-12X NAS7404-12Y 6 - NAS7404-13 Bolt - CSK NAS7404-13X NAS7404-13Y 14 - NAS7404-14 Bolt - CSK NAS7404-14X NAS7404-14Y 12 - NAS7404-45 Bolt - CSK NAS7404-45X NAS7404-45Y 4 -

NAS7405-45 Bolt - CSK NAS7405-45X NAS7405-45Y 4 Oversize may be required at this position AS8600-D Nut N/A N/A 72 AS8600-E Nut N/A N/A 60 SP124-D Washer N/A N/A 72 SP124-E Washer N/A N/A 60 SP71-608 Rivet - CSK N/A N/A 8SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 10 BLANK PAGESERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 11 Wing Main Spar Around Rib 36

Figure 1SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 12 Area of Inspection Around Rib 36 Figure 2SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 13 

## APPENDIX 1
EDDY CURRENT INSPECTION INSTRUCTION Examination of the Wing Main Spar Lower Boom and Sl ab at Rib 36

A. Instruction Reference (1) None. B. Safety Precautions (1) For the relevant safety precautions refer to ND T Manual, Part 1, Chapter 20-00-00, Paragraph 3. C. Procedure (1) Application (a) This instruction is to be applied to all BAe Je tstream 32 aircraft at the intervals defined in the relevant Service Bulletin or Maintenance Document. (2) Component to be examined (a) Wing main spar lower boom and slab, left and ri ght (refer to Figures 3 and 4). (3) Area of examination (a) Tooling hole under rib 36 and adjacent fastener positions (refer to Figures 3 and 4). (4) Purpose of examination (a) Part A – Low frequency eddy current inspection The low frequency, phase analysis, eddy current in spection is applied to locate and mark the position of the tooling hole on the wing lower skin. The marked position of the tooling hole facilitates the drilling operation, through the lower skin and doubler, to uncover the tooling hole for further inspection. (b) Part B – Rotary eddy current inspection The rotary phase analysis, eddy current inspection inspects the tooling hole and adjacent fastener holes for fatigue cracks, 0.0 50 in. (1.27 mm) in length, or greater, which initiate in the hole bores and pr opagate fore and aft.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 14 (5) Equipment required

(a) The following equipment was used during the dev elopment of this inspection instruction and was found to be acceptable. Part A – Low Frequency Eddy Current Inspection (1) Instrument: Elotest B1 v4 phase analysis eddy c urrent instrument with B1-RS adapter, from Rohmann (UK) Ltd. (2) Probe: Reflection, part number RR207-5/4F, 500 Hz. – 20 kHz, from Olympus NDT. (Ref. Fig. 5) (3) Lead: Part number EK-2-HF/1 from Rohmann (UK) L td. (4) Reference standard: Part number SSI 57-10-227/1 (Ref. Figs. 5, 6 and 7)

Part B – Rotary Eddy Current Inspection (1) Instrument: Elotest B1 v4 phase analysis eddy c urrent instrument with B1-RS adapter, from Rohmann (UK) Ltd. (2) Rotor: Mini-rotor attachment for Elotest B1, re ference number MR3, from Rohmann (UK) Ltd. (3) Probe 1: 3/16 in. (4.7 mm) dia., 4 in. (50.8 mm ) working length, part number MRRP-RUK-1-3/16-4 in., from Rohmann (UK) Ltd. (4) Probe 2: 0.25 in. (6.35 mm) dia., 4 in. (50.8 m m) working length, part number MRRP-RUK-1-0.25-4 in., from Rohmann (UK) Ltd. (5) Lead: Part number, RK-2-N/1, from Rohmann (UK) Ltd. (6) Calibration standard: Aluminium calibration block for rotary (dynamic) ed dy

current testing, cross-drilled hole type (Ref. NTM Part 6, 20-00-00)

NOTE: Any comparable eddy current equipment may be used provided it satisfies

the requirements of this instruction and is capable of resolving the tooling hole and the 1/16 in. (1.58 mm) dia. hole in the ca libration standards at the required level of sensitivity. (6) Preparation (a) Refer to Para’s. 2.A. and 2.B.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 15 (7) Component (a) To accomplish Part B ensure drilling operation has been carried out and the tooling hole is accessible for inspection. (b) Tooling hole and bolt hole bores must be clean and free from burrs. (c) Visually check the inspection areas for damage prior to inspection. (8) Examination procedure Part A – Low Frequency Eddy Current Inspection

Initial settings: Refer to manufacturer’s instructi ons. Alarm: Optional – Refer to manufacturer’s instructi ons. Frequency: Set to 1 kHz. Gain: Set to produce required sensitivity. Pre-amp: 10 dB. Y spread: 20 dB. X spread: 0 dB. Filter: Band: Set to Static. High pass: Set to Off. Low pass: Set to 10 Hz. Bandwith limiter: Set to On. Timebase/Display: Y/X. Dot position Reference Fig. 5.

(9) Sensitivity setting (Ref. Fig. 5) (a) Place the probe on the surface of the calibrati on standard away from the sub-surface hole and balance the instrument. (b) Set lift-off effect to horizontal and to the le ft. (c) Slide the probe over the sub-surface hole and n ote the response. Adjust the instrument settings to obtain a maximum signal from the hole of 50 per cent Full Scale Height (FSH).SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 16 Approaching the hole from any direction will cause the spot to rise as the probe

recognises the edge of the hole, however as the pro be centralises over the hole the spot will fall. The spots lowest position will indicate the precise centre of the hole. Approach from various directions to ensure ac curacy. (10) Inspection procedure (Ref. Fig. 4) (a) Place the probe on the wing lower skin directly under rib 36 and balance the instrument. (b) Search the area in the anticipated position of the tooling hole (Ref. Fig 2) and identify the sub-surface hole. (c) Centralise the probe over the hole applying the search techniques used during calibration. (d) Accurately mark the probe centre to provide cen tre for the drilling operation. Part B – Rotary Eddy Current Inspection

Initial settings: Refer to manufacturer’s instructi ons. Alarm: Render inoperative. Frequency: Set to 500 kHz. Gain: Set to produce required sensitivity. Pre-amp: 30 dB. Y spread: 0 dB. X spread: 0 dB. Filter: Band: Set to Dynamic. High pass: Set to 500 Hz. Low pass: Set to 2.5 Hz. Bandwidth limiter: Set to On.

(11) Sensitivity settings (Ref. Fig. 8) (a) Select spot (Y/X) display. (b) Adjust the instrument to produce a vertical sig nal from the 1/16 in. (1.58 mm) dia. cross-drilled hole in the rotary calibrati on block. (c) Select timebase (Y/T) display.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 17 (d) Set signal from cross-drilled hole to 100 per c ent FSH. (e) Select spot (Y/X) display. (f) Set signal from cross-drilled hole to 30 deg. a nti-clockwise. (g) For each dia. probe used, repeat operations (a) to (f) prior to inspection. (12) Inspection procedure (Ref. Fig. 4). (a) Select spot (Y/X) display. (b) Scan the full length of the tooling hole and tw o adjacent fastener holes 0.25 in. (6.35 mm), three positions per side. (c) Scan the full length of the 3/16 in. (4.7 mm) d ia. fastener holes, twenty positions per side. (d) By careful manipulation maximise any signals. (13) Acceptance criteria Part A – Low Frequency Eddy Current Inspection (a) Interpretation (1) Interpret signals (Ref. Fig. 5). (b) Accept/Reject criteria (1) Accurately mark probe centre to provide centre for drilling operation. Part B – Rotary Eddy Current Inspection (a) Interpretation (1) Interpret signals (Ref. Fig. 9). (2) Select timebase (Y/T) display to ascertain the amplitude and direction of each signal. (b) Accept/Reject criteria (1) Vertical signals over 20 per cent FSH that cann ot be attributed to probe handing or material interfaces shall be considered as a crack. (2) All other signals over 40 per cent FSH, irrespe ctive of angle, that cannot be attributed to probe handling or material interfa ces shall be considered as a discontinuity. NOTE: The word discontinuity is a generic term for faults such as cracks, corrosion and mechanical damage.SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 18 (14) Examination standard

(a) All cracks and discontinuities are to be recor ded in the relevant

aircraft documentation and the appropriate BAE SYST EMS approved repair/rectification action taken. (15) Reporting procedure (a) Report all crack/discontinuities on Operator R eport Form. (b) Also include:

(1) Aircraft constructor’s number. (2) Aircraft registration. (3) Flying hours/landings. (4) SB number. (5) Component/serial number. (6) Location/length of crack or discontinuity/signa l amplitude per cent FSH. (16) Additional information

(a) Related documents. (1) NDI Manual, Part 6, Chapter 20-00-00, Eddy Curr ent Inspection, General. (2) Test equipment manufacturer’s handbook.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 19 Area of Inspection – Main Spar Lower Boom at Rib 36 Figure 3SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 20 Main Spar - Inspection Figure 4SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 21 Instrument Calibration and Probe Details

Figure 5SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 22 Calibration Standard Part Number 57-10-227/1 – Mate rial Details Figure 6SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 23 Calibration Standard Part Number 57-10-227/1 – Hole Details Figure 7SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 24 Typical Screen Display – Rotary (Dynamic) Eddy Curr ents Figure 8SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 25 Spot (Y-X) Display Showing Signal Angles

Figure 9SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 26 BLANK PAGESERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 27 

## APPENDIX 2
RADIOGRAPHIC INSTRUCTION Examination of the Wing Main Spar Boom and Slab Inb oard of Rib 36 A. Instruction Reference (1) None. B. Safety Precautions (1) For the relevant safety precautions refer to ND T Manual, Part 1, Chapter 20-00-00, Paragraph 3. C. Procedure (1) Application (a) This instruction is to be applied to all BAe Je tstream 32 aircraft at the intervals defined in the relevant Service Bulletin or Maintenance Document. (2) Component to be examined (a) Wing main spar lower boom and slab, inboard of rib 36, left and right (Ref Fig. 10). (3) Area of examination (a) Fastener holes adjacent inboard of rib 36. (4) Purpose of examination (a) The inspection is intended to detect fatigue cr acks which initiate in the fastener holes and propagate fore and aft. (5) Equipment and materials required The following equipment was used during the develop ment of this inspection instruction and was found acceptable. (a) Seifert Eresco MF2 200CP X-ray set. Focal spot size 0.059 in. x 0.059 in. (1.5 mm x 1.5 mm). (b) Film – Fuji IX 100 (for details refer to Table 1). NOTE: Any comparable X-ray equipment and materials may be used provided they satisfy the requirements of this instruction ( The focal spot size must not exceed that detailed in Paragraph 5.(a)).SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 28 (6) Preparation for inspection

(a) Refer to Para’s. 2.A. and 2.B: (b) Component (1) Ensure that sealant is removed from the rib 36 to main spar intersection. This must be done thoroughly to ensur e that the film can be placed in close contact with the front spar and rib 36. Reinstate sealant in accordance with the SRM on completion of the inspection. (7) Examination procedure (a) Film details
Table 1. Type Size (in.) Size (cm) Quantity per aircraft FUJI IX 100 Ref. Fig. 11 Ref. Fig. 11 6 NOTE: FUJI IX 100 film was used for this inspection , but other manufacturer’s fine grain, medium speed film may be substituted. (8) Film identification (a) Unique reference number traceable to the specif ic inspection details. (b) Film number. (c) Film location and orientation, such as side and direction. (9) Film location (a) Film is located as shown in Figures 10 and 11. Film should be hard against rib 36 and the main spar web. (10) Tube head location (a) The X-ray tube head is located directly beneath and normal to the main spar (Ref. Fig. 10). (11) Exposure details (a) Expose films as detailed in Figures 10 and 12. (12) Interpretation (a) Cracks typically appear as more dense linear in dications.SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 29 (b) Corrosion typically appears as more dense areas or individual spots irregular in shape with poorly defined extremities. It is generally agreed that corrosion of less than 10 per cent in depth of the total thickness penetrated by the X-ray beam will not be readily detected by c onventional radiographic methods. (13) Accept/Reject criteria (a) Any crack like indication, material loss/corros ion or obvious damage is to be reported in the appropriate aircraft documentation and the appropriate approved repair/rectification action taken. (14) Reporting procedure (a) Report all crack/discontinuities on Operator R eport Form. (b) Also include:

(1) Aircraft constructor’s number. (2) Aircraft registration. (3) Flying hours/landings. (4) SB number. (5) Left or right wing. (6) Position, direction and length of crack or disc ontinuity/ per cent FSH. (15) Additional information

(a) Ensure all test equipment is removed from the a ircraft on completion of work.SERVICE BULLETIN

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ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 31 Area of Inspection – Wing Main Spar Lower Boom and Slab Figure 10SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 32 Film Sizes and Positioning Figure 11SERVICE BULLETIN

ORIGINAL ISSUE JUN 26/14 57-JA140140 PAGE 33 Exposure Details Sheet Figure 12SERVICE BULLETIN

57-JA140140 ORIGINAL ISSUE JUN 26/14 PAGE 34 BLANK PAGESERVICE BULLETIN 

## OPERATOR REPORT FORM This Operator Report Form is required to be complet ed and returned to: BAE SYSTEMS Regional Aircraft, Repair Design Office, Building 37, Prestwick International Airport, Ayrshire, KA9 2RW, SCOTLAND. Tel No. +44 (0) 1292 67 5276. Fax No. 01292 675432.

Title Wing – Inspection of Wing Main Spar Around Ri b 36.
Service Bulletin No. Operator Aircraft Registration No. Aircraft

Constructors No. Flying Hours No. of landings

57-JA140140. Initial Issue Description of inspection results, include all mark ed up figures and sketches: