COCKPIT VOICE / FLIGHT DATA RECORDER (CVFDR) KIT YAW RATE RECORDING CAPABILITY, ADDITION OF.

Transcription

1 TECHNICAL BULLETIN November 2017 MODEL AFFECTED: 429 SUBJECT: COCKPIT VOICE / FLIGHT DATA RECORDER (CVFDR) KIT YAW RATE RECORDING CAPABILITY, ADDITION OF. HELICOPTERS AFFECTED: Serial numbers through and through [Serial number 57325, and subsequent will have the intent of this bulletin accomplished prior to delivery.] COMPLIANCE: At customer s option. DESCRIPTION: The current CVFDR installation (BHT-429-II-6) does not record yaw rate as a separate parameter. India s Directorate General of Civil Aviation (DGCA) require onboard Flight Data Recorder (FDR) to record this parameter. Other Civil Aviation authorities may in the future require this additional requirement. This Technical Bulletin provides modifications to the CVFDR kit installation , -103 or -105 and instructions how to get the Data Acquisition Flight Recorder (DAFR) upgraded. PART I provides wiring modifications instructions that are required to be accomplished before PART II. If not accomplished in the required order, unexpected faults will occur. PART II provides instructions to send the DAFR unit back to the vendor to be upgraded with the new configuration file that support the addition of the yaw rate parameter. Applicability of this bulletin to any spare part shall be determined prior to its installation on an affected helicopter. Page 1 of 12

2 APPROVAL: The engineering design aspects of this bulletin are Transport Canada Civil Aviation (TCCA) approved. CONTACT INFO: For any questions regarding this bulletin, please contact: MANPOWER: Bell Helicopter Product Support Engineering - Intermediate Helicopters Tel: / / pseinter@bh.com Approximately 4.0 man-hours are required to complete PART I and PART II of this bulletin. This estimate is based on hands-on time and may vary with personnel and facilities available. WARRANTY: There is no warranty credit applicable for parts or labor associated with this bulletin. MATERIAL: Required Material: The following material is required for the accomplishment of this bulletin and may be obtained through your Bell Helicopter Textron Supply Center. Part Number Nomenclature Qty (Note) W Plate-Marking 1 (1) 04049L24-02N24 Cable A/R (1) W4 Tubing 1 (1) Insulating Tubing 1 (1) W4 Tubing, ID Heat 1 (1) Band 1 (1) DD78M10JVL Connector 1 (1) M39029/ Contact 2 (1) M85049/93-08 Shield Support Ring 1 (1) (3) M85049/93-10 Shield Support Ring 1 (3) S HN Solder Sleeve 1 (1) S200-2-W Shield Termination 1 (1) D (-090) Data Acquisition Flight Recorder 1 (2) Page 2 of 12

3 NOTES: 1. Part of kit PN B. 2. DAFR part number D (-090) becomes D (-090) with the new configuration software SW REL If needed. Consumable Material: The following material is required to accomplish this bulletin, but may not require ordering, depending on the operator s consumable material stock levels. This material may be obtained through your Bell Helicopter Textron Supply Center. Part Number Nomenclature Qty Reference * Tape TY3 CL1 A/R C Insulation Tape-.625 Wide A/R C-548 * C-XXX numbers refer to the consumables list in the BHT-ALL-SPM, Standard Practices Manual SPECIAL TOOLS: BAND-IT Tool (or equivalent) for EMI Band PN will be required and may be procured locally. WEIGHT AND BALANCE: Not affected. ELECTRICAL LOAD DATA: Not affected. REFERENCES: BHT-429-IPBS-5, Illustrated Parts Breakdown BHT-429-MM-1, Maintenance Manual BHT-429-MM-3, Maintenance Manual BHT-ELEC-SPM, Electrical Standard Practice Manual PUBLICATIONS AFFECTED: BHT-429-IPBS-5, Illustrated Parts Breakdown, Chapter 96 BHT-429-II-6, Installation Instruction, Cockpit Voice / Flight Data Recorder kit BHT-429-MMS-5, Maintenance Manual Supplement, Chapter 97 Page 3 of 12

4 ACCOMPLISHMENT INSTRUCTIONS: PART I Wiring Modifications 1. Prepare the helicopter for maintenance. 2. Open the battery access door (100B) and disconnect the battery. (BHT-429-MM-1, Chapter 6). 3. Remove the upper bay door, left side (100DL) (BHT-429-MM-1, Chapter 6). 4. Locate the connector (3960AT1J8) on the LH Signal Distribution Matrix (SDM) (BHT-429-MM-3, Figure 98-6). 5. Locate the DAFR connector (3130A3P1) (BHT-429-IPBS-5, Figure 96-1). 6. Route and secure wire cable assembly with existing harness from the connector (3960AT1J8) to the DAFR connector (3130A3P1). 7. Disassemble connector (3130A3P1). 8. Trim the wire cable jacket and shield. (Figure 3, View A and B) 9. Install shield termination (10, Figure 2) over window trimmed jacket. 10. Install insulation sleeve (3, Figure 2) over trimmed jacket and shield. 11. Remove band (7, Figure 2). 12. Install new band (7, Figure 2) over existing shield terminations. Make sure to include the newly installed shield termination from wire cable FDR-021A Terminate wire FDR-021A24 at the DAFR connector (3130A3P1) (Table 1). 14. Assemble connector (3130A3P1). Do not connect to the DAFR at this time. 15. Do a continuity check between (3960AT1P8) and (3130A3P1) on newly installed wiring (Figure 1). 16. Remove and discard the dust cap from the LH SDM (3960AT1J8) located on the LH nose bulkhead. 17. Connect (3960AT1P8) to the receptacle (3960AT1J8) located on the LH SDM and (3130A3P1) to the CVFDR. 18. Make an entry in the helicopter logbook and historical service records indicating compliance with PART I of this Technical Bulletin. Page 4 of 12

5 PART II - Data Acquisition Flight Recorder (DAFR) Upgrade 1. Prepare the helicopter for maintenance. 2. Verify the part number on the DAFR label. If the part number is D or D , go to step 7, otherwise go to step 3 (Figure 4). -NOTE- The DAFR new configuration file is not field loadable therefore, it must be returned to the vendor for an update. 3. Contact Penny & Giles at the following Points of Contact to coordinate the update of the DAFR. Penny & Giles Phone : Fax : Pg-support@curtisswright.com 4. Remove the DAFR from the aircraft and send it back to Penny & Giles for update (BHT-429-MMS-5, chapter 97). 5. Upon return from Penny & Giles, verify the part number and the configuration file release version on the DAFR label. It should be D or D with configuration software SW REL01 (Figure 4). 6. Re-install the DAFR using the existing hardware (BHT-429-MMS-5, Chapter 97). 7. Perform the Cockpit Voice / Flight Data Recording System operational check (BHT- 429-MMS-5, paragraph 97-32, step 1 through 8). 8. If the PGS replay software is available, go to next step, otherwise, go to step 10. -NOTE- The following test requires the PGS replay software and the database file DB V1.arb procurable from Penny & Giles. A short hover / flight with a 360 degrees pedal turn is required to notice Body Yaw Rate (ADAHRS CHA) signal amplitude. Page 5 of 12

6 9. Using the PGS software, make sure the parameter is valid as follow: a. With the PGS software running, select Edit Groups from the Databases dropdown menu as shown below; b. Create a new tab using the New Group button and add the parameter Body Yaw Rate (ADAHRS CHA) Page 6 of 12

7 c. Body Yaw Rate (ADAHRS CHA) shown below at 5 sec / div; 10. Make an entry in the helicopter logbook and historical service records indicating compliance with PART II of this Technical Bulletin. 11. Amend any aircraft records referencing , -103 or -105 Cockpit Voice / Flight Data Recorder Kit according to the following table: PRE-TB POST TB FM per FM per FM per Page 7 of 12

8 Wire From Pin Hardware To Pin Hardware Note FDR-021A24 WHT 3960AT1P A3P1 43 M39029/ , 2 FDR-021A24 BLU 3960AT1P A3P1 44 M39029/ , 2 FDR-021A24 SHLD 3960AT1P A3P1 SHLD S HN 1, 3, 4 NOTES: 1. Assemble in accordance with the BHT-ELEC-SPM, Electrical Standard Practice Manual. 2. Wire end termination preparation to be per the BHT-ELEC-SPM, Electrical Standard Practice Manual. 3. Used for terminating the shield of a single conductor or multi-conductor cable. Table 1 - Wire Termination details Page 8 of 12

9 Figure 1 - Wiring diagram Page 9 of 12

10 Figure 2 - Cable / Harness Assembly Architecture Page 10 of 12

11 Figure 3 - Wire Stripping Dimensions Page 11 of 12

12 Figure 4 - DAFR Label Page 12 of 12