SD3-60 AIRCRAFT MAINTENANCE MANUAL CHAPTER 54 - NACELLES TABLE OF CONTENTS. Chapter Section Subject Subject Page

Transcription

1 CHAPTER 54 - NACELLES TABLE OF CONTENTS Chapter Section Subject Subject Page NACELLE - REMOVAL/INSTALLATION General 401 Removal 401 Installation ENGINE MOUNTING FRAME ATTACHMENTS TORQUE LOADING General NACELLE ATTACHMENT BRACKETS (FRONT SPAR) - INSPECTION/ CHECK Applicability 601 Purpose 601 Special Tools and Equipment 601 Job Set-Up Information for Surface Scan 603 Job Set-Up Information for Rotary Scan 603 Acceptance Criteria 605 Reporting Procedure 605 Close Out 605 Repeat Procedure NACELLE MOUNTING PLATES (REAR SPAR) - INSPECTION/CHECK Applicability 601 Purpose 601 Special Tools and Equipment 601 Job Set-Up Information for Surface Scan 602 Job Set-Up Information for Rotary Scan 605 Acceptance Criteria 605 Reporting Procedure 605 Close Out 606 Repeat Procedure CONTENTS Page 1

2 AMM NACELLE - REMOVAL/INSTALLATION 1. General CAUTION: ALL PIPE CONNECTIONS, ELECTRICAL PLUGS AND SOCKETS AND ACCESSORY DRIVE PADS MUST BE FITTED WITH BLANKS IMMEDIATELY ON REMOVAL; CONVERSELY, WHEN INSTALLING ENSURE THAT THE BLANKS ARE REMOVED. ENSURE THAT PIPES ARE CORRECTLY CLIPPED ON RE-INSTALLATION TO PREVENT FRETTING ON ADJACENT COMPONENTS. ALL PRE-FORMED PACKING O-RINGS AND GASKETS FREED OR EXPOSED DURING REMOVAL OPERATIONS ARE TO BE DISCARDED AND NEWLY REPLACED ON RE-ASSEMBLY. (WHEN REPLACING, LUBRICATE WITH FLUID TO BE USED IN APPROPRIATE SYSTEM OR LINE). UNLESS OTHERWISE STATED, ALL PIPE UNIONS AND ADAPTERS SHOULD BE TIGHTENED. REFER TO , PB1. Special Tools and Equipment:- Torque spanners (set to required values) Hoist 2. Removal A. Preparation for removal (1) Remove the engine Refer to , pb1. B. Engine mounting frame removal (1) Support the engine mounting frame on suitable hoist take up slack. (2) On the engine mounting frame, upper right foot fitting, remove bolts (4 off), washers (8 off), slotted nuts (4 off) and split pins (4 off), noting position. Discard split pins. (3) On the engine mounting frame, upper left foot fitting, remove bolt (4 off), washers (4 off), washers (4 off), slotted nuts (4 off) and split pins (4 off), noting position. Discard split pins. (4) On the engine mounting frame, lower left and right outer foot fitting, remove bolts (4 off), washers (4 off), washers (4 off), slotted nuts (4 off) and split pins (4 off), noting position. Discard split pins. (5) On the engine mounting frame, lower left and right inner foot fitting, remove bolts (4 off), washers (4 off), washers (4 off) and self locking nuts (4 off), noting position. Discard self locking nuts Page 401 Jun 30/01

3 SD3-60 AIRCRAFT MAINTENANCE MANUAL (6) Remove the engine mounting frame and hoist from the area. C. Nacelle removal (1) Gain access to the air conditioning piping in centre wing Section, outboard of wing Stn (2) Locate and disconnect coupling Pt.No (3) In bleed air line, identify lagged venturi assembly Pt. No. SD and disconnect from lagged pipe Pt. No. SD /5. (4) In the Nacelle structure, locate and disconnect pipe assembly Pt. No. SD and union Pt. No.AN815-4C from lagged pipe Pt. No.SD /5. Remove O-Ring Pt. No. BAS S. (5) In the Nacelle structure, locate and disconnect electrical connectors at pressure switch HE and fuel blowdown solenoid valve V (6) Cut Ty-raps to release wing electrical cables from the nacelle structure. (7) Disconnect wiring from Terminal Blocks TB45 (left) or TB46 (right). (8) Disconnect wiring from Earth Points E231 (left) or E232 (right). (9) Disconnect electrical connectors at pressure switch Pt. No. HE and oil pressure transmitter Pt. No G-1. (10) Disconnect wiring from Terminal Stud FTB4. (11) Locate plug mounting assembly Pt. No. SD on forward nacelle face, remove and retain bolts (2 off). Leave the mounting assembly attached to the electrical connector. (12) Remove and retain bolts (13 off) and washers (13 off) from lower edge of fire shield. (13) Remove and retain (2-off) P-clips Pt. No. HT0813/5/C from lower edge of fire shield. (14) In right hand engine area, locate fuel supply line Pt. No. SD and remove P-clip Pt. No. AS 4525/20), Bolt, nuts and washers. (15) Remove and retain bolts (12 off) and washers (12 off) securing the left hand fire shield access cover. Remove access cover. (16) Remove and retain bolts (11 off) and washers (11 off) securing the right hand fire shield access cover. Remove access cover. (17) Remove and retain (2-off) P-clips Pt. No. HT08 13/12/C from fire shield access cover Page 402 Jun 30/01

4 3. Installation (18) Locate pipe assembly Pt. No. SD XA in the oil pressure line and disconnect from union Pt. No. AN832-4C. (19) Slacken off bulkhead union Pt. No. AN832-4C to gain access to bracket fittings. (20) Remove bolts (4 off) and washers (4 off) securing Bracket to bulkhead. Remove packing from between the bracket assembly and the bulkhead. (21) Remove bracket assembly Pt. No. SD /C complete with bulkhead union, nuts, washer, O-rings, pressure transducer, tee piece and pressure switch. (22) Locate flexible return hose on top of oil cooler, disconnect at union Pt. No. SD XB. CAUTION: ENSURE THAT MOUNTS ARE THE ONLY CONNECTION BETWEEN ENGINE SUPPORT STRUCTURE AND WING AT THIS STAGE. (23) Inspect attachments to nacelle and ensure it is clear to lift the engine support structure. Secure engine support structure and support in cradle on suitable hoist Take up slack. (24) At forward attachment points, release retainer brackets on both sides of the fitting by removing bolts, slotted nuts, washers and split pins. Discard split pins. (25) Remove and retain bolts, slotted nuts, washers and split pins from forward attachment points. Discard split pins. (26) Remove and retain shoulder bolt, slotted nut, washer and split pin from left and right rear attachment points. Discard split pins. (27) Carefully ease engine support structure mounts and lower clear of wing pick-up points. A. Nacelle installation (1) Secure Engine support structure and support in cradle on suitable hoist. (2) Inspect attachments to nacelle and ensure it is clear to lift engine support structure to mate with wing pick-up points. (3) Fit shoulder bolt Pt. No. SD XA, slotted nut Pt. No. A103-G-S, washer Pt. No. SP152-G and new split pin Pt. No. SP90-C7 to left and right rear attachment points. (4) Fit bolts Pt. No. A112-22Q, slotted nuts Pt. No. A110-Q-S, washers Pt. No. SP148-Q and new split pins Pt. No. SP90-G11 to forward attachment points. (5) At forward attachment points, secure retainer brackets Pt. No. SD on both sides of the fitting by fitting bolts Pt. No. A102-4D or A102-5D, slotted nuts Pt. No. A103- D-S, washers Pt. No. SP148-D and new split pins Pt. No. SP90-C Page 403 Jun 30/01

5 SD3-60 AIRCRAFT MAINTENANCE MANUAL (6) Reconnect return hose to top of oil cooler at union Pt. No. SD XB. (7) Replace O-ring Pt. No AS located between tee piece and union Pt. No. AN832-4C, do not fully tighten union. (8) Fit bracket assembly Pt. No. SD /C complete with bulkhead union Pt. No. AN832-4C, nuts Pt. No. AN924-4C, washer Pt. No. SP150-L, O-rings Pt. No. AS , pressure transducer Pt. No G-1, tee piece Pt. No. AN938-4C and pressure switch Pt. No. HE (9) Secure bracket to bulkhead using, bolts (4 off) Pt. No. A104-3-D, throat washers (4 off) Pt. No. SD /B and packing Pt. No. SD /A. (10) Fully tighten bulkhead union Pt. No. AN832-4C. (11) Reconnect pipe assembly Pt. No. SD XA in the oil pressure line to union Pt. No. AN832-4C. (12) Fit P-clips (2-off) Pt. No. HT08 13/12/C to fire shield access cover. (13) Fit right hand fire shield access cover and secure using bolts (11 off) Pt. No. A D and washers (11 off) Pt. No. SP-154-D. (14) Fit left hand fire shield access cover and secure using bolts (12 off) Pt. No. A D and washers (12 off) Pt. No. SP-154-D. (15) In right hand engine area, locate fuel supply line Pt. No. SD and fit P-clip Pt. No. AS 4525/20, bolt Pt. No. A102-2-B, nut Pt. No. AS-8600-B and washer Pt. No. SP 151-B. (16) Fit P-clips (2-off) Pt. No. HT0813/5/C to lower edge of fire shield. (17) fit bolts (13-off) Pt. No. A104-1-D and washers (13-off) Pt. No. SP-154-D to lower edge of fire shield. (18) Secure plug mounting assembly Pt. No. SD on forward nacelle face, using bolts (2-off) Pt. No. A B. (19) Reconnect wiring to Terminal Stud FTB4. (20) Reconnect electrical connectors at pressure switch Pt. No. HE and oil pressure transmitter Pt. No G-1. (21) Reconnect wiring from Earth Points E231 (left) or E232 (right). (22) Reconnect wiring from Terminal Blocks TB45 (left) or TB46 (right). (23) Secure wing electrical cables to the nacelle structure using Ty-raps Page 404 Jun 30/01

6 (24) In the Nacelle structure, locate and reconnect electrical connectors at pressure switch HE and fuel blowdown solenoid valve V (25) In the Nacelle structure, replace O-ring seal Pt. No. BAS S and reconnect pipe assembly Pt. No. SD and union Pt. No. AN815-4C to lagged pipe Pt. No.SD /5. (26) In bleed air line, identify lagged venturi assembly Pt. No. SD and reconnect to lagged pipe SD /5. (27) Locate and reconnect coupling Pt. No B. Engine mounting frame installation (1) Support the engine mounting frame on suitable hoist and position to enable fitment. (2) On the lower left and right inner foot fitting of the engine mounting frame, fit bolts (4 off) Pt. No. MS , washers (4 off) Pt. No. MS20002C6, washers (4 off) Pt. No. MS and new self locking nuts (4 off) Pt. No. H20 6. (3) On the lower left and right outer foot fitting of the engine mounting frame, fit bolts (4 off) Pt. No. MS , washers (4 off) Pt. No. MS20002C6, washers (4 off) Pt. No. MS200026, slotted nuts (4 off) Pt. No. SL4108JC and new split pins (4 off) Pt. No. SP90C7. (4) On the upper left foot fitting of the engine mounting frame, fit bolt (4 off) Pt.No. MS , washers (4 off) Pt.No. MS20002C6, washers (4 off) Pt.No. ST160J1 9XB, slotted nuts (4 off) Pt.No. SL4108JC and new split pins (4 off) Pt.No. SP90C7. (5) On the upper right foot fitting of the engine mounting fit bolt (4 off) Pt.No. MS , washers (4 off) Pt.No. MS20002C6, washers (4 off) Pt.No. MS200026, slotted nuts (4 off) Pt.No. SL4108JC and new split pins (4 off) Pt.No. SP90C7. (6) Torque bolts. Refer to , pb1. (7) Remove hoist from the area. C. Completion (1) Install the engine. Refer to , pb Page 405 Jun 30/01

7 AMM ENGINE MOUNTING FRAME ATTACHMENTS TORQUE LOADING 1. General Refer to Figure 1. This section details those nacelle located attachment bolts/nuts which have been subjected to special torque considerations and are painted green.. NOTE: Bolts/nuts with red witness marks are torque controlled to standard values. Refer to , pb1.) Page 1 Jun 30/01

8 SD3-60 AIRCRAFT MAINTENANCE MANUAL Special torque requirements - Engine Mounting Fame Figure Page 2 Jun 30/01

9 AMM NACELLE ATTACHMENT BRACKETS (FRONT SPAR) - INSPECTION/CHECK This inspection procedure must only be performed by a person trained and approved to Personnel Certification in Non-Destructive Testing (PCN) NAS410 or EN4179, level II or level III. NOTE: This inspection can be performed in conjunction with the following inspections:- Nacelle Mounting Plates (rear spar) - Refer to , pb601. Wing/Nacelle Attachment Lugs (rear spar) - Refer to , pb601. The procedure is derived from MW-S EC. 1. Applicability Part No: SD (4-off left). Alternative SD SD (4-off right). Alternative SD Material: DTD 5104 Forged Billet Al oy 2. Purpose To detect fatigue cracking at all accessible surfaces, with particular attention to edges (refer to Figure 602). 3. Special Tools and Equipment Portable Eddy Current Flaw Detector: Hocking Locator 2d Semi-shielded Nfe 500 kh Probe AL35-45 Standard Nfe Calibration Block (SCB) 33A103 Rotary Eddy Current Drive Unit Rotary Probes, GE Inspection Technologies:- 619P012F051 3/16 diameter (0.188 in.) 619P016F051 1/4 diameter (0.250 in.), 619P026F051 13/32 diameter (0.406 in.) and 619P040F051 5/8 diameter (0.625 in.) Rotary Calibration Block (with in. holes drilled at 90 degrees to object hole) - AL35-45 NOTE: Equivalent eddy current equipment may be used, provided that it meets the requirements of this procedure. The equipment must be capable of resolving the reference notches in the calibration reference standard at the required level of resolution and sensitivity Page 601

10 SD3-60 AIRCRAFT MAINTENANCE MANUAL Attachment Bracket - Removal/Installation Figure Page 602

11 4. Job Set-Up Information For Surface Scan A. Preparation (1) Render the aircraft electrically safe. Refer to , pb301. (2) Remove the left nacelle. Refer to , pb401. (3) Remove access panel 440AB. Refer to , pb1. (Figure 8). (4) Remove each of the two sets (4-off) attachment brackets (1) as follows (Figure. 601):- NOTE: Make a note of the position of the different bolts, saddle strips and saddle plate for subsequent installation. (a) Remove the twenty stiffnuts (2), twenty special washers (3) and twenty bolts (4), (5) and (6). NOTE: Discard the stiffnuts and retain the washers and bolts Also retain the saddle plate (7) and two saddle strips (8) which are subsequently disconnected. (5) Make sure the attachment brackets (1) are clean and free of chipped or flaking paint. (6) Make sure the attachment bracket holes are not damaged and do not have burrs. B. Calibrate the test equipment for surface scan Portable:Eddy Current Flaw Detector (1) Set up in accordance with the manufacturer s instructions. (2) Connect the probe and obtain a response from the 0.5 mm slot in the SCB. C. Inspection NOTE: Adjust to give 80% Full Scale Height (FSH). Identify the areas to be inspected on the attachment brackets. Refer to Figure 602. (1) Balance the probe on the component and compensate for lift off effect. (2) Perform the scan on the area indicated. 5. Job Set-Up Information For Rotary Scan A. Preparation (1) Ensure that para 4.A. has been completed before continuing Page 603

12 SD3-60 AIRCRAFT MAINTENANCE MANUAL Attachment Bracket - Inspection Area Figure Page 604

13 B. Calibrate the test equipment for rotary scan Portable Eddy Current Flaw Detector (1) Set up in accordance with the manufacturer s instructions. (2) Select the time base display and use the 13/32 (0.406 in.) rotary probe to adjust the equipment to give 50% Full Screen Height (FSH) from the in. cross drilled reference bolt. NOTE: The signal to noise ratio should be 12 db. (3) Select spot display and adjust the angular displacement of the reference hole signal to a position 30 degrees anticlockwise of vertical. C. Inspection NOTE: This signal position is consistent with mechanical damage. A signal that appears more vertical should be considered a defect indication. (1) Put the probe in a hole and allow the rotational speed to stabilise. (2) Move the probe slowly down the bore in increments and interpret the signals. (3) Repeat steps (a) and (b) for the remaining nineteen holes. 6. Acceptance Criteria Any discontinuity indication which cannot be attributed to probe handling or geometric effects, is to be considered a defect signal. 7. Reporting Procedure Record and report all rejections to Bombardier Aerospace:- SRPSA@aero.bombardier.com (preferred), or Telephone: Customer Response Center (CRC) Local and International North America only JET-1247 ( ) Toll Free 8. Close Out (1) Install each of the two sets (four-off) attachment brackets (1) to the nacelle as follows (refer to Figure 601):- (a) Put the saddle plate (7) and two saddle strips (8) in the positions noted during removal Page 605

14 SD3-60 AIRCRAFT MAINTENANCE MANUAL (b) Put the attachment brackets (1) in position and attach with the twenty retained bolts (4), (5) and (6), the twenty retained special washers (3) and the twenty new stiffnuts (2) in the positions noted during removal. (c) Torque tighten the fasteners. Refer to , pb1. (2) Install access panel 440 AB. Refer to AMM, , Figure 8. (3) Install the left nacelle. Refer to , pb Repeat Procedure (1) Repeat para 4. thru para 8. inclusive for the right nacelle Page 606

15 AMM NACELLE MOUNTING PLATES (REAR SPAR) - INSPECTION/CHECK This inspection procedure must only be performed by a person trained and approved to Personnel Certification in Non-Destructive Testing (PCN) NAS410 or EN4179 level II or level III. NOTE: This inspection can be performed in conjunction with the following inspections:- Nacelle Attachment Brackets (front spar) - Refer to , pb601. Wing/Nacelle Attachment Lugs (rear spar) - Refer to , pb601. The procedure is derived from MW-S EC. 1. Applicability Part No: SD (pre mod 7737), or SD (post mod 7737) 8-off Material: L93 3 swg (pre mod 7737), or 7075 T73511 QQA-200/11 (post mod 7737) 2. Purpose To detect fatigue cracking at all accessible surfaces, with particular attention to edges (refer to Figure 602). 3. Special Tools and Equipment Portable Eddy Current Flaw Detector: Hocking Locator 2d Semi-shielded Nfe 500 kh Probe AL35-45 Standard Nfe Calibration Block (SCB) 33A103 Rotary Eddy Current Drive Unit Rotary Probes, GE Inspection Technologies:- 619P012F051 3/16 diameter (0.188 in.) 619P016F051 1/4 diameter (0.250 in.) 619P026F051 13/32 diameter (0.406 in.) and 619P040F051 5/8 diameter (0.625 in.). Rotary Calibration Block (with in. holes drilled at 90 degrees to object hole) AL35-45 NOTE: Equivalent eddy current equipment may be used, provided that it meets the requirements of this procedure. The equipment must be capable of resolving the reference notches in the calibration reference standard at the required level of resolution and sensitivity Page 601

16 SD3-60 AIRCRAFT MAINTENANCE MANUAL 4. Job Set-Up Information For Surface Scan A. Preparation (1) Render the aircraft electrically safe. Refer to , pb301. (2) Remove the left nacelle. Refer to , pb401. (3) Remove access panel 440AB. Refer to , pb1. (Figure 8). (4) Remove each of the two sets (4-off) of mounting plates (1) as follows (refer to Figure 601):- NOTE: Make a note of the position and orientation of the different fasteners for subsequent installation. (a) Remove the six stiffnuts (2), six washers (3) and six bolts (4). NOTE: Discard the stiffnuts and retain the washers and bolts. (b) Remove the six stiffnuts (5), six washers (6), six bolts (7) and two throat plates (8). NOTE: Discard the stiffnuts and retain the washers, bolts and throat plates. Also retain the packing plate (9) that is subsequently disconnected with the two mounting plates (1) from the channel and ed member. (5) Make sure the mounting plates are clean and free of chipped or flaking paint. (6) Make sure the mounting plate holes are not damaged and do not have burrs. B. Calibrate the test equipment for surface scan Portable Eddy Current Flaw Detector: (1) Set up in accordance with the manufacturer s instructions. (2) Connect the probe and obtain a response from the 0.5 mm slot in the SCB. C. Inspection NOTE: Adjust to give 80% Full Scale Height (FSH). NOTE: Identify the areas to be inspected on the mounting plates. Refer to Figure 602. Portable Eddy Current Flaw Detector (1) Balance the probe on the component and compensate for lift off effect Page 602

17 Mounting Plates - Removal/Installation Figure Page 603

18 SD3-60 AIRCRAFT MAINTENANCE MANUAL Mounting Plates - Inspection Area Figure Page 604

19 (2) Perform the scan on the area indicated. 5. Job Set-Up Information For Rotary Scan Refer to Figure 602 A. Preparation (1) Ensure that para 4.A. has been completed before continuing. B. Calibrate the test equipment for rotary scan Portable Eddy Current Flaw Detector (1) Set up in accordance with the manufacturer s instructions. (2) Select the time base display and use the 13/32 (0.406 in.) rotary probe to adjust the equipment to give 50% Full Screen Height (FSH) from the in. cross drilled reference bolt. NOTE: The signal to noise ratio should be 12 db. (3) Select spot display and adjust the angular displacement of the reference hole signal to a position 30 degrees anticlockwise of vertical. C. Inspection NOTE: This signal position is consistent with mechanical damage. A signal that appears more vertical should be considered a defect indication. (1) Put the probe in a hole and allow the rotational speed to stabilise. (2) Move the probe slowly down the bore in increments and interpret the signals. (3) Repeat steps (1) and (2) for the remaining eleven holes. 6. Acceptance criteria Any discontinuity indication which cannot be attributed to probe handling or geometric effects, is to be considered a defect signal. 7. Reporting Procedure Record and report all rejections to Bombardier Aerospace:- SRPSA@aero.bombardier.com (preferred), or Telephone: Customer Response Center (CRC) Local and International North America only JET-1247 ( ) Toll Free Page 605

20 SD3-60 AIRCRAFT MAINTENANCE MANUAL 8. Close Out (1) Install each of the two sets (4-off) of mounting plates (1) to the nacelle as follows (refer to Figure 601):- (a) Put the two mounting plates (1) and the packing plate (9) in position, between the channel and ed member. (b) Install the six retained bolts (7), the six retained washers (6), the six new stiffnuts (5) and the two throat plates (8) in the positions noted during removal. (c) Install the six retained bolts (4), the six retained washers (3) and the six new stiffnuts (2) in the positions noted during removal. (d) Torque tighten the fasteners. Refer to , pb1. (2) Install access panel 440 AB. Refer to AMM, , Figure 8. (3) Install the left nacelle. Refer to , pb Repeat Procedure (1) Repeat para 4 thru para 8 inclusive for the right nacelle Page 606